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ATP Grid Index to Manufacturer’s Publications:

Hartzell Propeller
Hartzell Propellers and Governors for Reciprocating Engines
Maintenance Publications

Section Topic

General Information

01 Hydro-Selective Propeller (Manual No. 100D)

Models HC-12X20, HC-D2X20, HC-D3X20-6L
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions

Model Designation
Description
Installation Instructions
Operating Instructions
Service Instructions
Disassembly Instructions
Assembly Instructions
Trouble Shooting Modernization
Parts List
Model HC-12X20-7 and 8
Dash 7 and 8 Models
Supplement No. 1 HC-D2X20-7, -8
Supplement No. 2 HC-D3X20-6L

Supplement No. 3 HC-D2X20-3

Supplement No. 4 HC-12V20-7D and -80
Supplement No. 5 HC-D2V20-7D and -80

Supplement No. 6 HC-D3V20-6L

Service Bulletin No. 32 C-49-2B and -2C Hub Spider
Service Bulletin No. 82 A-38 Ball Bearing

02 Hydro-Selective Propeller (Manual No. 100E)

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Section Topic

Model HC-D2V20-3,-7,-8/D3V20-6L/D2MV20-3,-7,-8/D3MV20-6L
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions
Letter of Transmittal (Highlights of Changes)
List of Effective Pages
Service Document List
Airworthiness Limitations

Introduction
Description and Operation
Testing and Fault Isolation
Automatic Test Requirements
Disassembly
Cleaning
Check
Repair
Assembly
Fits and Clearances
Special Tools, Fixtures and Equipment
Illustrated Parts List
HC-D2V20-3
HC-D2MV20-3
HC-D3V20-6L
HC-D3MV20-6L
HC-D2V20-7 and 8
HC-D2MV20-7 and 8
HC-D3MV20-8D

03 Constant Feathering Propellers (Manual No. 105A)

Speed
Models HC-92(ZW)F-2A, HC-92(ZW)K-2A
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions

Overhaul
Introduction
Overhaul Instructions
Balance
Wear Tolerances
Lubrication

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Section Topic

Service Troubles and Remedies

Parts Lists
Introduction
Group Assembly Parts List
HC-92ZF-2A/-2B, HC-92ZK-2A/-2B
HC-92WF-2A/-2B

04 3 Blade, Constant Speed and Feathering (Manual No. 108A)

Models HC-B3(Z,W,P,R)30-2E, HC-B3P30-1B, HC-B3P30-1
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions

Overhaul
Description
Overhaul Instructions
Errata Sheet No. 1
Balance
Errata Sheet No. 2
Wear Tolerances
Lubrication
Service Troubles Remedies
Parts List
Introduction
Group Assembly Parts Lists
Governor
Supplement No. 1 HC-B3Z30-2E, HC-B3W30-2E
Supplement No. 2 HC-B3P30-1 (Non-Feathering)
Supplement No. 3 HC-B3P30-1B (Grnd Adj/Fixed Pitch)

05 2 Blade, Constant Speed and Feathering (Manual No. 109A)

Models HC-A2XF-2/-2A, HC-A2XK-2, HC-A2XL-2
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions

Overhaul
Description
Overhaul Instructions
Balance
Wear Tolerances

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Section Topic

Lubrication
Service Troubles Remedies
Parts List
Introduction
Group Assembly Parts List
Differentiating Parts List

06 2 Blade, Constant Speed (Manual No. 110)

Models BHC-92ZF-1D1, HC-92ZK-8D/-8L
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions

Overhaul
Description
Overhaul Instructions
Errata Sheet No. 1
Balance
Wear Tolerances
Errata Sheet No. 2
Lubrication
Service Troubles Remedies
Parts Lists
Introduction
Group Assembly Parts List

Supplement No. 1 HC-92ZK-1D

Supplement No. 2 HC-92WK-1D

07 Feathering Three-Blade Propeller (Manual No. 111)

Models HC-B3Z20-2A/10151B-8
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions

Overhaul
Introduction
Overhaul Instructions
Test Procedure
Lubrication
Parts List
Introduction

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Section Topic

Group Assembly Parts Lists

08 Feathering Three-Blade Propeller (Manual No. 112A)

Models HC-B3Z30-2B/9349/10151, HC-B3W30-2B/W9349/W10151
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions

Overhaul
Introduction
Overhaul Instructions
Test Procedure
Lubrication
Parts List
Introduction
Group Assembly Parts Lists

09 Compact Non-Feathering/Aerobatic Prop (Manual No. 113B)

Models For Two, Three, and Four Blade Propeller
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions
Letter of Transmittal (Highlights of Changes)
List of Effective Pages
Service Documents List
Airworthiness Limitations

Introduction
Description and Operation
Testing and Fault Isolation
Automatic Test Requirements
Disassembly
Cleaning
Check
Repair
Assembly
Fits and Clearances
Special Tool, Fixtures, and Equipment
Illustrated Parts List
Two Bladed -1 Propeller Parts
Two Bladed -4 Propeller Parts

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Section Topic

Three Bladed -1 Propeller Parts

Three Bladed -4 Propeller Parts
Four Bladed Propeller Parts

10 Constant-Speed Propellers (Manual No. 114B)

HC-8()X,HC-A()X,HC-9()Z,HC-9()W,HC-B()Z,HC-B()W,HC-A()V
List of Chapters (Table of Contents)
Manufacturer’s Introduction
Record of Revisions
Record of Temporary Revisions

Model Designation
Description
Propeller Installation Instructions
Governors
Disassembly Instructions
Inspection
Repair and Replacement
Assembly
Balance
Wear Tolerances
Lubrication
Service Troubles
Parts List
Cutaway Views of Typical Assemblies
Supplement No. 1 Reversible Prop Model HC-A3VF-7
Supplement No. 2 Addition of HC-B3R20-4

Supplement No. 3 Addition of ()HC-92WF-8E

Supplement No. 4 Addition of HC-B3W30-4
Supplement No. 5 HC-83V()-() Similar to HC-83X()-O
Supplement No. 6 Ground Adjustable Prop HA-A2V20-1B

11 Steel Hub Propeller (Manual No. 114C)

Models for Two Blade and Three Blade Propellers
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions
Letter of Transmittal (Highlights of Changes)
List of Effective Pages
Service Document List
Airworthiness Limitations

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Section Topic

Introduction
Descritpion and Operation
Testing and Fault Isolation
Automatic Test Requirements
Disassembly
Cleaning
Check
Temporary Revision No. 002
Repair
Assembly
Fits and Clearances
Special Tools, Fixtures, and Equipment
Illustrated Parts List

12 Compact Constant Speed/Feathering Prop (Manual No. 1170)

Models for Two Blade, Three Blade, and Four Blade Props
List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions
Letter of Transmittal (Highlights of Changes)
List of Effective Pages
Service Document List
Airworthiness Limitations

Introduction
Description and Operation
Testing and Fault Isolation
Automatic Test Requirements
Disassembly
Cleaning
Check
Repair
Assembly Procedures
Fits and Clearances

Special Tools, Fixtures, and Equipment

Illustrated Parts List
Cylinder Spring Assemblies
Propeller Assemblies
Spinner Assembly Parts
Spinner Mounting Kit Parts

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Section Topic

13 Propeller Counterweight Governors (Manaul No. 121B)

List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions

Introduction
Description
Installation
Operation
Service Inspection, Maintenance, and Lubrication
Disassembly, Inspection, Repair, and Reassembly
Test Procedure

14 Propeller Hydromatic Governors (Manual No. 123)

List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions
Addendum Overhaul Info for 468-4 Propeller Governor

Introduction
Description
Installation
Operation
Service Inspection, Maintenance, and Lubrication
Disassembly, Inspection, Repair, and Reassembly
Test Procedure

Appendix I Repair and Modification Procedures

15 Governor Maintenance Manual (Manual No. 1308)

List of Chapters (Table of Contents)
Record of Revisions
Record of Temporary Revisions
Letter of Transmittal (Highlights of Changes)
List of Effective Pages
Service Document List
Airworthiness Limitations

Introduction
Description and Operation
Testing and Fault Isolation

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Section Topic

Automatic Test Requirements

Disassembly
Cleaning
Check
Repair
Assembly and Testing
Specifications
Special Tools, Fixtures and Equipment
Illustrated Parts List
A Series
B-2 Series
B-3 Series
B-4 Series
C-3 Series
C-4 Series
D Series
E-2 Series
E-3 Series
E-4 Series
E-5 Series
E-6 Series
E-8 Series
F-2 Series
F-3 Series
F-4 Series
F-6 Series
F-8 Series
H Series
U-3 Series
U-3-15 Series
U-8 Series
V-l Series
V-2 Series
V-3 Series
V-4 Series
V-5 Series
V-12 Series
C-137-()B()T-Drive AssemblY

End of Index

Page 9 of 9
Copyright O Aircraft ~echnical Publishers
08115/2002
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I
 100D

~i ad 03 H:C Ila%20,H:C -D2X2 O, HC-D3X ~0-dL

DESCRIPTION
INSTALLATION
pltOT OPERATION

´•INSP f: C710N and

MAINT fT NANCE

pARTS LIST

AVE
 RECOBD OF REVISIONS

~´•$;a´• 100D

MFG REV
NO DESCRIPTION ISSUE DATE ATP REV DATEI INSERTED BY
 RECORD OF TEMPORARY REVISIONS

100D
ATP REV INSERT DATE REV REMOVE
TEMP
DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY
REV NO
 %,o N T E N TS;

MODEL HC 12x20

Illustrations inside front and back

cover

I Model Designation

II Description

III Installation Instructions

Iv Operating Instructions
i
V Service Instructions

VI Disassembly Instructions

VII Assembly Instructions

VIII Trouble Shooting Modernization

LX Parts List

MODEL HC 12x20-7 and 8

X Dash 7 and 8 biodels

Page 26

Illustration for Section X

Pages 16 and 17

Fifth Printing
ISeptember, 1951)
 ON 1

R´•IODEL ’I)F,SIGNA’rlON

A--HUB MODEL DESIGNATION

The diagrammatic description is self explanatory. R dash and a number added

to the hub model designation indicates a minor change which does not affect the eligi-
bility.

KC-12X23-1

Parts List

S. A. E. propeller shaft size

Blade Shank Size

Number of blades

/HC-Hartzell Controllable
(HA-Hartzell Adjustable

B--BLADE MODEL DESIGNATION

The blade model designation consists of four numbers. The first group of two
numbers denotes the diameter of the propY’ller in inches. The second group of two
numbers denotes the basic model number or templates used. The left hand version is
"L" preceding the blade model designation. For example:
designated by an

Blade Model Designation

_
I
L 8427 CR -2

I I Diameter reduced 2 Inches.

I Reworked from 86-in. diameter

Type of Plastic Material

Basic Model Number of Templates Used

Diameter in inches

I Left Hand Version

 I

IcZQ 38
10 8 45 41 43

12---~
14~

1
i’
I
2 I i; 42

44

28~ I ((Oj)l I I I 46

5’

18- 30

27 1

22 2
:i 35
235= 32 31 29

<P

1__
(PARTS DIAGRAMI

SEC CATAIOC NUMBER SHEET FOR PARfS IDEI´•ITIFICATION

d2
 SECTLON II

UESCnfltTION

A--CONTROL
The
The Hydro-Selective Propeller is a hydraulic controllable propeller.
Hartzell
pitch of the blades can be set to ally prr:determined value
within the normal operating
control to the position ~corresponding to the en-
range by moving the cockpit proper
all the way in for
gine speed desired. For example, the push-pull control is pushed
will
take-off, and is pulled out foy high speed and cruise. An intermediate position
provide an intermediate pitch setting or rpm value.

B-BLADES

The blades are special plastic composition known as "Hartzite". The mater-
of a
vibra-
ial has unusually good properties for propellers, such as high strength, good
and salt water. The blades
tion qualities, and is impervious to the effects of weather
is equally high. As
are made as thin as metal blades, consequently the efficiency

"Hartzite" absorbs vibrations, it results in smoother operation than most propeller

materials.

C--HUB

and inexpensive, consisting essentially of a

The hub assembly is unusually simple
steel hub element, blade clamps to which are fastened counterweights, blade bearings
the
and the hydraulic jack unit. The hydraulic unit consists of a cylinder bolted to
ball bearing which translates the motion from
enginecrank case, a movable pistion, a

piston to the rotating hub assembly by means of two links, and the
valve. Engine oil pressure is used to acuate the mechanism.
~y8_r8dlid\servo
D ~"ODELS HC-12x20-1, 2, 3, 4, 5, and 6 ~See Section X for dash 7 and 8).

The HC-12x20-1 model has approximately 10 to 14 degrees pitch range, which is

sufficient for normal low and high speed control. The cylinder is designed specifi-

to mount the Continental E-185 engine, either directly with studs or indirectly
cally on

with brackets.

The -2 model is similar to the -1 except the pitch range is 33 degrees which
enables the pitch to be reversed for ground or water handling. Also, the cylinder
mounts to
directly engine having a standard SAE 20 spline
any
thrust plate.

The -3 model is the same as the -2except the cylinder is larger, therefore will op-
erate on lower engine oil pressures. (8-7/8 0. D. for -3 as compared to 7-5/8 0. D. for
-2 model.)

assembled with three counterweight configurations, as follows:

The-3 propeller was

Model HC-12x20-3 has counterweights that measure 4.65 inches between the ex-

treme points of the long corner or edge.

Model HC-12x20-3A has counterweights that measure 4.5 inches long and do not

9
have a large notch along the inside corner to provide clearance for the pro-i
milled
peller hub nut. rerluires the 1/8’’ irlcrea~s in length which is accomplish;
?’his model
ed by attaching 1/8’’ or two 1,’16" I-,lates on tt~e end of the counterweight using two
10´•-32 cap screws one inch apart cent´•r~lly located.

Model HC-12x20-3C has countc´•rweightns 4.5 inches long; however, there is a large
notc/h milled along the inside cornel´• to provide clearance for the hub nut.

The -4 model is essentially the same as the -1 model except for the cylinder mount-
ing provision. Whereas the -1 model is designed specifically to mount on the Contin-
ental E-185 engine, either with brackets or directly with studs, the -4 model utilizes
the -2 cylinder which mounts on the standard S.A.E. thrust plate.

The -5 model is an improved version of the -1. The links which transmit the mo-

tion from the hydraulic element to the blades have been replaced in the -5 model by
push rods and forks.

The -6 model is essentially the same as the -5 model except for the cylinder
mounting provision. It utilizes the -2 cylinder which mounts on the standard SAE
thrust plate.

SECTION III

INSI’ALLATION INSTnUCTIONS

When the propeller leaves the factory completely assembled and partly filledj
it is
with grease. The pitch of the blades is set for its particular application and ehe
clamp and blades are marked with matchinglines.

A--INSTALLING PROPELLER

i. Clean crankshaft and crankcase nose section. Install bronze rear cone against
the thrust nut. In Ranger engine installations, the thrust nut (Ranger Part No.
7815) must be removed and turned down in a lathe to 3.210+.005 over all diameter.

2. The hydraulic cylinders for model KC-12x20-1, used on North American built
Navions, were mounted on the Continental E-18Fjengine with sheet metal brackets.
This was necessitated because at the first part of the program the engine had no Ir~o-
visions for
bolting the
cylinder directly on to the engine crankcase. Later the D series
engines came through with four tapped holes for this purpose. Therefore, two cylin-
der mounting instructions are necessary:

a. For Continental engines recjuiring brackets:

Locate the valve near the top of the engine, remove cylinder from propeller assem-

bly and secure it to the mounting brackets, which presumably are already bolted
to the engine, with Alien head
making screws assembly sure the
fully is seated
on the
pilot flange of the engine crankcase. Be sure that the brackets pull the
cylinder up tight against the engine crankcase; otherwise failures of ~he brackets
 throu~h-bolts engine to push the
and propeller components will result. Loosen on

ir necessirq. Safeiy Alien head screws and

assembly back against the cranlrcase,
torque through-bolts.

b. engines having provisions to bolt th Fl cylinder directly to crankcase:

For
Install a 1/64"
Locate valve near tc,p of engine and lemovr, pistun from cylinder.
hard paper gasket between the cylinder and the crankcase. (It is also recom-
mended that gasket compound be used.) Use elastic stop nuts and aluminum
washers on the studs inside the cylinder. Studs or nuts NIUaT NOT extend out

more than 5/8 inches from the surface of the cylinder, else the piston will be pre-
vented from receeding fully.

3. Check the inner and outer "O" Rings, also the "0" ring grooves, of the piston
for cuts or other defects that may cause oil leaks, and install "O" rings and felt seal
on piston.

4. Oil the crackshaft, rings and the inner surface of the cylinder.
rear cone, "0"
A thin film of antiseize compound (Specification AN-C-53) or an equivalent mixture
of 70 per cent white lead and 30 per cent engine oil by volume is advisable on the
threads of the engine shaft.

5. Attach the proper hydraulic fittings onto the valve body.

crankshaft and align wide hub spline with shaft blind

6. Place propeller on

In the of the -2 and -3 models, turn the nut about two threads
~Pd(lthe (if used).
ne

making
shaft
case

sure the threads have engaged properly. Never use force to start
che nut.

7. Turn the piston so the number stamped oil the flange matches with the same
ii number stamped on the front edge of the cylinder and so that the three pins in the

cylinder will line up with the holes in the piston.

8. By hitting the inboard portion of the blades with the palm of the hands, enter
the piston into the cylinder taking precautions not to cut the "0" rings in the process.
The valve body should be at either extreme of its stroke in order to allow air to escape
from the cylinder.

As soon as possible start the nut on th~ threads of the shaft and then push the
piston into the cylinder by applying hand pressure on the counterweights.

9. Tighten the nut on the crankshaft using a bar about 3 or 4 feet long with a

force of 50 Ibs.--maximum effort of a man pulling with one hand.

10. With piston bottomed in the cylinder, check travel of piston by measuring
between jack plate (5) and shoulder of hub. The travel should be .413 to .375 on
models -1 and -5,.507 to .469 on model -4, and 1.062 to 1.094 on models -2 and -3.
Shim behind cone (6) if distance insufficilnt. Safety nut to engine shaft.

11. Install 3/8" to 1/2" I. D. flexible hose from pressure side of the engine to

_F;
the lever side of the valve a.nd from the engine cr´•anltcase to valve. This hose.must’
be sulriciently long and arranged so that the valve can be moved in and out freely.
Locate the drain fitting in the cranlccase as close to the valve as possible--not over
18 inches.

12. With the cockpit reverse control line forward tin the case of the reversible

propeller) just off the locked position. attach this control line at the propeller to the
shol´•t end of the lever (42) on the valve (41) making sure that the clamping bolt is
tight against the braclret on the cylinder. When movin.g the cockpit reverse control
lever into the locked position, there should, be an increase in tension due to the slack
being taken up in the lines.

13. piston bottomed in the cylinder, the cockpit propeller control handle
With
pulled approximately
out 2]/4" from the instrument panel, and valve body located
midway between the cotter pin and the base of the guide pin; attach the propeller
pitch control line to the valve lever. (Valve body shown in mid-position on parts dia-
gram.)

14. With the piston bottomed in the cylinder, check the emergency stop screws on

the inboard end of clamps for clearance with the llub. If necessary, file the head on

screws to paper clearance between the screw and hub.

B--ADJUSTING PROPELLER CONTROL FOR PROPER GROUND OR STATIC RPM

1. Start and warm upengine and check propeller action. The full throttle max:
imum static rpm, with cockpit propeller control full forward, should be held to limil
listed in CAA Aircraft Specification. (P,pm for best rate of climb should not exceea
max engine speed.)

2. If static rpm is too high pull back on propeller control until correct rpm is
obtained. Stop engine and adjust propeller low pitch stop scr´•t?w which limits the
valve travel. On -1 and -5 models this stop screw is located in a bracket carried by the
valve lever. The end of the screw bumps against the back of the cylinder when the

propeller is pulled into low pitch. For the -2 and -3 models this by a
screw is held
bracket that is bolted to the cylinder. It isadjusted to limit the movement of the val-
ve lever. For the -4 and -6 models the screw adjusts directly against the valve body.

3. If static rpm is too low, stop engine and back off enough on low pitch stop
screw and run lip engine again as in paragraph 2.

4. If the correct rpm cannot be reached because the jack plate is against the
shoulder on the hub, reset the blade pitch about one degree, or 1/32 inch measured at
the scribe marks, for each 100 rpm desired.

propeller should never operate with the jack plate against the shoulder be-
The
cause cylinder oil pressure is then equal to the engine oil pressure. This pressure.
the
which may be considerably higher than normal cylinder operating pressure, loads up
both the propeller thrust bearing and the engine thruSt beariIlg needlessly. The
minimum clearance should be about .010?’.

-G-
 in Parf,s
F,. After run-up fill propeller blade bearings with grease recommended
hub,
,ist using zerk fittings on cla.mps. Stop when grease appeal´•s between clamp and
Care must be taken that the pressure does no’i blow out gaskets in clamps.

6. Check pitch control in flight for proper oper´•ating range.

SECTION IV

PILOT OPERATING INSTRUCTIONS

A-HIGH-LOW PITCH

The Hartzell-Hydro-Selective Propeller operates with engine oil pressure to reduce

pitch, and centrifugal force created by the counterweights to increase pitch. A servo
valve regulates the oil flow to provide any desired pitch setting within limits of pitch
control in the same manner
range. The pilot regulates the valve with a push pull
that he regulates the throttle. He pushes the control IN to INCREASE RPM and pulls
it OUT to DECREASE RPM, The blade follows the control precisely, the rpm will re-
flect this movement immediately.

a. WARM-UP

During warm-up the pitch control should be IN or in low pitch. Then set rpm at
1500 with the throttle and check pitch change once or twice. This will also fill

cylinder with warm oil.

b. TAKE-OFF

No pitch control is necessary, The rpm should increase to nearly the desired
climbing value by the time the airplane leaves the ground without changing the
pitch control,

c. CLIMB

If rpm exceeds the limit allowed it may be decreased by pulling back on the pitch
control until the desired value is reached.

d. CRUISE

Pull control out to cruise position. If manifold pressure gauge is available

pitch
the rpm and manifold pressure can be correlated with pitch control and throttle
as recommended by engine manufacturer for best fuel consumption or best en-

gine performance,

e, LONG RANGE CRUISE

Maximum cruise econcmy dictates low airspeed, low rpm anrl fairly mani- high
fold pressure, For these conditions the pitch must be high. This can be obtained
´•I
 with pitch control pulled OUT to desired value of rpm and manifold pressure.

f. LANDING

Fush control. in before landing in order to be in a position to take-off again if nec-

essary. Taxi in low pitch.

B--REVERSE PITCEI

Model HC-12x20-2 and -3, reversible propellers, go into reverse pitch with engine
oil pressure and comes out of reverse by centrifugal force created by the counter-
weights.
Before attempting to reverse the pitch the rpm must be reduced to 1200 or less
for engines having oil pressure less than 50 Ibs. Generally, the lower rpm the less is
the time for the’´•pitch to go completely into reverse, depending on the oil pressure
available at idling speeds.

For the Sea-bee installation, unscrew and push up the reversing control and slowly
push towards the rear. DO NOT FORC~. The Dilot can feel the control yield to his
pressure indicating that the pitch is changing. When the control is all the way back
the pitch is in reverse and the pilot can then apply throttle. UNDER NO CONDI-
TIONS SHOULD ONE OPEN TI´•IE THROTTLE WHILE TIIE REVERSE CONTROL IS
IN AN INTERMEDIATE POSITION. If there is any doubt whether the pitch is com-

pletely in the
reverse
open throttle slowly to avoid the possibility of the engine racing.
Never let the engine exceed 2500 in reverse in the case of Franklin Engine 6AL500.

In order to come out of reverse the rpm should be set AT LEAST 1200. The high
er the rpm without exceeding the limitation of apDroximately 2500, the fasterfhe

pitch changes out of reverse.

Apply forward pressure to the reverse control until it slips into the lock position.
LOCK. Any monetary rpm increase up to the limitation of the engine is not to be a
cause of concern as some speed up is inevitable when the pitch goes through zero.

G--PROPELLER CARE

It is advisable to turn the propeller into a horizontal

position on preparing the
ship fol~ tie-down or hstngering. In this position it will not
permit water to drain be-
tween the clamp and hub into the blade bearing, and in this position the propeller can-
not be damaged by hitting the overhead portion of the hanger.
Since the blades are solid "Hartzite" through and through with good weathering
characteristics, covers for them al.e not anecessity. It is advisable, however, to cover
the hub and hydraulic elements with a waterproof hood when storing in the open. In
cleaning the propeller, use grease-cutting soap and water to wash the blades and ca~-
bon tetrachloride or naptha to clean the hub. Most automobile waxes used on the
blades will give them lustre and protection. A waxed surface is also of some advantage
aerodynamically.
In order to minimize water erosion in the case of the "Sea-bee", all water taxy-
ing should be done in low pitch and with wing flaps down.

The pilot should perform the daily visual inspection as listed in Section V, Part A.
a_
 SECTLON V

Sl[i;nVICE INSTKUCT~ONS

A--DAILY VISUAL INSPECTLOIL’

The propeller should he regularly and carefully inspected visually for the follow-
ing:

i. Excessive oil leaks in the hydraulic element and valve. Replace "0" rings
when necessary. A true source of leaks can best be discovered by standing off to a
side clear of the propeller and watching the valve and cylinder, or by wiping all visible
oil from the engine, propeller and cowling and then starting the engine for a very
short period of time.

2. ~rease leaks through the clamp gaskets. Replace gaskets if necessary as de-
scribed in Section V’II, Part D. Use non-hardening gasket, compound.

3. Cracks in the hub or clamps, and particularly the links in linkplate (5). Never
hesitate performing a magnetic check at the first sign of a crack.

Bn~ises, dents or cracks in the blades. See CAA Manual 18 for the allowable
4.
damage to be airworthy. (Major repairs should be made only by a certified agency or
the factory.) The metal leading edge is stainless steel and is expected to crack
around the leading’ edge only along the scribed lines put in the metal for this purpose.
Missing metal or loose rivets should be repaired. See Section VIII Part E instruc-
~ns for replacing rivets. HAVE THE TIPPING REPAIRED VVHEN SMALL PITS AP-
EAR ON THE TIPS. This isespecially true on the propellers used on amphibians.
If the water penetrates the stainless steel tipping, the plastic beneath it can be dam-
aged beyond repair in a very short period of time if the punishment is severe. Armor

tipping should be refiled to a sha,´•p edge at the first sign of pits on the leading edge.

5. Check the scribed lines on the clamps and blades to see if they are matching.
The reason for this precaution is to detect blades tllat may slowly be twisting to flat
pitch because the clamps are not tight enough on the shanks of the blades. These
matching lines must be present originateIy and can be scribed in with a scale and
scriber. See Section VIII, Part F.

6. Check blades for free movement in the hub. Grab counterweights and move
both forward and then backward making sure at the time that the valve is against
the cotter pin of the guide pin. In this position, oil can bleed out of the cylinder.

7. Check pitch control connections to valve lever. especially true in the

This is

case of the reverse control connection on propellers. The head

the HC-12x20-2 and -3
of the bolt attaching this contl.ol line to the valve lever should be hard against the stop

bracket on the cylinder. Check by pulling on the valve body. See Section III Part
A-12 for attaching this control to the lever.

B--50 HOUR INSPECTION

1. Follow the regular inspection procedures as listed under Part A.

a
 2. Check wear in valve lever linkage. TCeI~ls.ce pins or lever if excessively worn
?’he valve lever is extremely sensat;ive, and for correct ol,el.ation the valve should re-
spond immediately with the movements of the cockl,it contl´•ol, Replace worn parts if
pitch control is not precise.

3. Grease the thrust bearing located in the hydraulic element by any of the three
methods. Too much grease will it to overheat. Use
cause
only the recommended
greases listed~in Section IX.

a. Take the screws out of the cover plate on the Diston and drop about two tea-
spoonful of grease between the cover plate and piston.
b. If a zerkfitting is in the piston, pump about one-ilalf cubic inch of grease
into the bearing.
c. Remove the propeller from the engine unit
as a including the piston. Work
grease in the 1/16 crack between the I. D. of bearing using ones fingers.
4. Grease blade bearing with zcrk gun. Care should be exercised
whe~ pumping
grease into the zerk fitting, else excessive pressure will blow out the
gaskets. Grease
should be added until it starts coming out around
joint between the clamp and hub.
Vnless the bearings are kept flooded with grease they will become
rough and eventual-
ly cause the propeller to stick. See list of recommended gl´•eases in Section IX.

5. Check tightness of linkscrew (25) and also wear between

screw and link of
(5). Linkgcrew (25) must be tight in clamp (2´•1´•) else it will work and
possibly brea.k.
Torque to approximately 30 foot pounds. Safety with wirelock (28) in such a
way ~hat
wire tends to tighten screw. Replace screw if badly worn.

6. Check clamp gaskets for leakage of grease. For remedy see Section VTI Par.t D.

C--250 HOUR INSPECTION (or coincide with

engine overhaul).
1. Remove propeller and disassemble.

2. hiiagnifiux steel parts.

3. Replace worn parts.
4. Assemble.

SEC’I’ION VI

DISBSSEMB~LI INSTRUCTIONS
The parts will be referred to by name and number aslisted in the Parts List Sec-
tion IX which refers to the exploded view and general
drawing shown on the cover.
A--REMOVAL OF HUB AND BLADE ASSEMBLY FROM ENGINE

a. Without piston and cylinder.

1. Remove wirelocks (28) and linkscrews ~(25).
2. Replace linkscrews in the same clamps from which they were removed.
3. Remove safety screw (3.6) in nut (15)’ and turn nut off of
engine shaft.
-10-
 4. Remove hub fl´•om engine shaft anti place away from possible damage.

b. With piston and cylinder

i. F,emove cotter pin (38) from valve guide on valve b~acltct (40).
possible. ~alve
2. Grab counterweights and pull piston as far out of cylinder as

must be in 2ligh pitch position in order to bleed air into cylinder.

(16) in nut (15) and turn nut off engine sha’ft.
3. Remove safety screw

instruction 2 above until piston is entirely out of cylinder. Provide a

4. Repeat
pan to catch the oil draining from cylinder.
5. Remove hub from engine shaft and place on stub shaft of a work bench.

6. Remove cylinder and valve parts from engine.

OF PROPELLER BLADES.

the linkscrews in the

1. Remove piston from propeller assembly replacing
clamps from which they were removed.

2. Scribe matching lines on blades and clamps.

Take nuts off of bolts (12) and Alien screws (14) using Alien
3. (13) remove

wrench (5/’16" across the flats).

4. Record blade serial number with the clamp number for each side of the pro-

peller.
5. Remove clamp halves (8) and (24) from assembly. The blade is then free to

pulled off of pilot tube in hub.

0 DEMOVAL OF siADE BEARING

1. Pull "O’’ ring (26) out of the groove in hub and roll it back on the hub.

2. Spring snap ring (27) and move back into the "0"ring groove.
NOTE: Hold the’ bearing togt:ther or use two small 0 clamps, for this operation will´•
permit the two races of the bearings to part allowing the balls to come out.

3. Tap the bearing (22) back toward the snap I´•ing and off of split ring (25).
4. Remove split ring and the bearing, snap ring and "0" ring will then be free
to come off the hub.

D--REMOVAL OF JACK ASSEMBLY FROM PISTON ASSEMBLY

1.Back wire retainer (31) out of slot using plyers. A sharp 1/16" dia. piano
wire bent 90 degrees will aid in´• prying the wire retainer (34) out to where it can be
reached with plyers.
2. Push or tap jack plate out of the bearing using preferably
the a cylinder of
steel whose O. D. is slightly less the I. D. of the bearing.

E-REMOVAZ OF BEARING FRONI PISTON

1. Remove screws (35) holding on cover plate (4).

-11-
 2. Push or tap beal´•ing (3) out of piston (2). Support the piston on the front
rim. Us,3 drift punch applied to the inner
a
edge of the bearing.

F--DO NOT remove count;erweig´•hts from clamps theg

as are pinned at the factory and
should not be loosened.

DO NOT remove links from jack assembly (5). If links should be replaced return
assembly to factory.
DO NOT interchange cylinders and pistons for they are paired by stamped num-
bers on the outer edges of both.
DO NOT interchange the valve body and valve the "C" series valve
plate on assem-

blies.

SECTION VII

ASSEIVHBI,Y INSTRUCTIONS

The parts will be referred to by name and number as listed in the Parts List
Sec-
tion IX which refers to the exploded view and
general drawing shown on the cover.

A--INSTALLATiON OF JACK LN BEARING

1. Push or tap jack-plate ´•(5) in bearing (3) ~ith.the cover I,late (4) and gasket’
(32) between the two. The groove just inside the inner race of the bearing must
match the groove in the jack plate.

2. Install wire retainer (34) through stot in jack plate. (5). Use to work;
plyers i
wire around groove.

B--INSTALLATION OF BEARING IN PISTON

1. Grease bearing (3) with 1/2 cubic inch of grease. (see greases recommended
listed in Section IX).
2. Press bearing (3) in piston (2). Slight press fit is required. Use gasket
compound between bearing and piston to insure tight fit if necessary.
3. Use gasket compound on gasket (32).
4. Insert lock washers (33) and (35) in
screws cover plate (4) and piston (2).
C--INSTALLATION OF BLADE BEARING

1. Install "O" ring (26) over tube in hub (7) past the "0" ring groove.
2. Install snap ring (27) in "0" ring’groove.
3. Install bearing (22) over tube with the NARROW RACE PI_IACED ON FIRST.
4. Move bearing against snap ring and install like numbered split ring (23) just
back of the thrust shoulder on hub.
5. Tap bearing over split ring until against shoulder.
6. Slip snap ring from "O" ring groove and place between bearing and shoulder
of hub.

-12-
 7. Poll "O" ring into groove.

D--INSTALLATION OF’ PROPELLEIZ

to Grease
1. propeller blade .r;hnnk piln!; I,ul:,~ hole with grease, conforming
Fill
below as this will
Specificatio~ls listed in PR1-l:i List. Be sure air is not trapped grease
heads of
affect balance of propeller. (For ar~d -3 propellers insf:nll stc?lting lug over
with flole in clamp when pitch is set
two screws at base of blade. Lug must match up
properly).
2. Place propeller blade on tube of hub.

around the blade shank in the inboard

3. Put hardening gasket compound
groove.
4. Install MATCHING pair of clamps (8) and (21).
compound both
-5. Place gaskets I10) inplace withnon-hardening gasket on

sides of gaskets.
6. Insert screws (14) and bolts (12) in the same direction to avoid inlel´•ference

with valve.
20 foot Ibs.
7. Tighten screws (14) and nuts (13) evenly, torque approximatelg
tube of hub. If tight, correct cause of
8. Check freeciomof blades on pilot
If thi’s is sufficient without Permitting the
tight~ness by’.losening outer nuts slig.Mly.
ilacie io turn in the clamps, then refer to the causes of friction listed in Section VIII,
Part A.
the prope:ler assembly using link screws (25).
9. Install jackplate (5) on

10. With the jackplate stgainst the shoulder on the hub, set the angles of the
blades at the 30-in. station by loosening clamps curd rotating blades in clamps. Set
pitcll as indicated in table below.

Engine Install,ziion
I -3 1 -3 -4 -5

Continental E-185 12" 1 I 1 12´•

10"
nanger 6-440C-2 1 I 200 1
6-440C-5

I I 180 180
Franklin 6AL500
I _I _

jack plate and hub.

Note: A 1-1/16 to 2-3/32 spacer must be used between

11. Scribe matching lines on the blades and clamp.

12. Tighten the nuts (13) until snug or torque. Check tight-
not over 20 foot ib.
torque of 2000 inch Ib.
-6 models. A
ness of blades in clamp in the case of -1, -4. -5 and
determine whether it might slip in
should be applied to the blade near the rooi to
the clamps aild file the
flight. If the blades slip in metal to metal clamps,
s remove
.005 at time.
two pads on the ears of the one clamp-half. Remove only
a

-13-
 13. Carefully check the an~les malting sure the jackplate is against the shoulder
on the hub or´• against spacer as not!,d for -2 and models. The angles of the blades
should be wit;hin ~z degree of each other al~d M de::ree of the correct angle setting.

14. Fol~ -2 and -3 propellers drill stakir-~g lug t´•hrou6h hole in clamp using .154
dia. dr´•ill. IXole sho~lld be only 5/10 deep. DI-ive stal:ing i~in in hole flush with surface
of clamp. Staking pin is necessary to pi~everit blade frorn turning in clamp.

E--EALANCE

1. Remove hydraulic element from blade hub assembly.

2. Install balancing jackplate assembly (These may be obtained from factory).
jackplal;e should rest against hub shoulder. Wedge blades out, using small wedges be-
tween hub and clamps.
3. Install balancing mandlel using the cone seats for cerztering. Do not use the
I. D. of the huh.

4. Check horizontal balance by laying weight slugs (47) in the corner of the
blade and clamp. Record no. of slugs on clamp.
5. Apply a vertical force of about 50-100 Ib: near tip of each blade and check
vertical balance having the heavy´• blad~ uli´• La31 slugs on the hut~:-end of the clamp.
Record no. of slugs on the side of hub.

6. Repeat item 5 above with propeller rotated 180 degrees and check vertical bal-
ance having the heavy blade up and record slugs.
7. If the two recorded number of slugs for vertical balance have occurred on the
same side of the hub, correct amount of slugs to use is one half of the sum.

If the two recorded number of slug’s for vertical balance have occured on opposite
sides of the hub, the correct amount of slugs to’ use is one-half of the difference and
placed on the side with the greater number.

Divide the vertical balance slugs to maintain the horizontal balance within one

slug. Vertical baia.nce should be held within four slugs at the worst condition. Do
not attach more than eight slugs on two fillister head screws.

8. Install slugs on clamps temporarily and again check balance.

9. Grease blades with zerk gun equally on both sides. See Section V Part B-4.

10. Check horizontal and vertical balance. Add grease until in balance.

11. Safety fillister head screws.

F--INSTALLATION OF LINKSCREWS

1. Attach hydraulic element with linkscrews.

2. Tighten linkscrews with alien wrench using 30 ft. Ibs. torque. The tapered
shoulder on the screw must be seated on the tapered countersink in the clamp.
3. If the hole in the head of the linkscrew does not line up so that when the
wirelock is in place, the spring or stress should tend to tighten the linkscrew; then
center punch the proper location and drill a hole with a No. ´•11 drill.

--1A
 SECTIBN VILI

1’ROIJB‘I[,E 51[IOOTIN~ nN1) IMPROV~LMk:N’L’S

Following is a list of the possible ailments and the remedy.

A--FAILURE FOR PITCH TO CHANGE

to low pitch properly,

1. pitch changes to high pitch but will not change
If the
the cause is generally low engine oil pressure. For proper functioning with a 7f/4
inch diameter cylinder the pressure should not be below 45 psi, and with an 8-7/8 in.

dia. cylinder, not below 30 psi. If it is no;pressure, refer to the causes of friction as

listed below.

2. pitch changes to low pitch but will not change to high pitch properly,
If the
The drain line
the cause is usually a drain line that is either too small or too long.
it should return directly to the
should never be less than a 3/8" line, and if possible
Also refer to the causes of fric-
crankcase through a distance of not over 18 inches.
tion as listed below.

the
3. pitch does not change properly toward bath high and low pitch,
If the
cause is usually due to an excessive amoun~ of friction
which minimizes the hydraulic

and counterweight forces or a combination of low oil pressure and a drain line that
is too small or too lollg.

The of friction are:

causes
centrifugal
due to fol.ce the presence of a small
a. Improper grease which, or

fit of the blade on the pilot tube.

amount of water, solidifies and causes a tight
Use recommended greases as listed in Section IX.

b. The snap ring (27) wedged beneath the inboard race of the blade bearing.
halves and
This condition can be detected by carefully removing one of the clamp
described Section
noting the position of the ring. By removing this snap ring as
the ring will not jam -Between the
VI, Part C, and it
springing apart slightly,
bearing and hub.

pilot tube. See Part I

c. Insufficient clearance between the blade bore and the
of this section for the amount of clearance necessary.

that do not have

d. squeezing of the blade by the clamps: For early clamps
Over
baits
metal to metal contacting surfaces on each corner, it is possible to tighten
the pilot tube.
(12) to the point where theblade is deformed and tightens upon
If
This overtightness can be detected by backing off the castellated nuts (13!
and
this frees the rotation of the blades on the tube of the hub, then disassemble
Part D,
assemble the blades as described in Section VI, Part B, and Section VII,
If the blade has taken permanent set, it should be
using new clamp gaskets. a

reamed with a installed And properly tightened. The hole size should be
clamp
1.502 1.504 with the clamp mounted on blade alone and properly tightened.

of the hub due to vibration and centrifugal force:

e. Pilot tubes that slip out
-15-
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-~050

ORIGINAL
As Received 8y
;z7~ ATP
 Some tubes whicl.i ~.ind inl],~´•operr p~ess fits, might n´•ork loose and slide outward
ly until t~ley press Ilal:cl a~ainst t,lle bott´•om of the hole ir~ the blade shank.

This condition can be detected by tfic wil´•elock and lin’kscrew and then
backing off the castellated nuts on the clatilp. If the blade does not rotate freely
condi-
even upon removing the nuts from the bolts, the indications point to the
tion of a loose tube. In order to check furthel~, I´•emove the blade as outlined in
Section VI, Part B, and measure t~le length of the pilot tube extending beyond the
hub. This dimension should be 3 3/4"-t1/32".

If the tube has slipped slightly, it should be replaced by one which is .002 greater
in diameter for the portion which fits into the hub. Tube pullers are available
for service establishments as are oversize tubes. New tubes may be pressed in
using an arbor press. (In emergencies where no press is available the tube may
be driven in with a wooden mall.) Check replaced tubes for fit by attempting to
Dull it with a puller by putting a toryue of 30 ft. Ibs. on the tube-puller screw,
having the threads well greased, or by appiying´• the maximum force of one man
with his hands ten inches apart. If the tube does not slip in the hub it is suffic-

iently tight. If the tube slips, install one of greater oversize.

f. Insufficient clearance between the end of the hub and the end of the blade:
This can be checked by moving the blade by hand in and out, radially. There

should be a slight end movement. If there is no clearance, the end of the blades
should be scraped a few thousands of an inch at a time until clearance is produc-
ed. Clearances should be at least .005.

B--IMPROPER RPM SETTXNGS

1. Static rpm too low:

The limits for full throttle maximum static rpm are listed in the CAA Aircraft

(It; is the rpm that will permit the rated engine speed´•during the best
Specification.
rate of climb.) Adjust stdp that controls the valve lever travel that the proper rpm
so

is obtained. The correct procedure is given in Section III, Part B.

If the valve leverstop controlling the travel of the push pull control because
is not
it is limited in the cockpit, then loosen the control housing clamp next to the valve
and move the control housing toward the propeller until the stop on the lever limits
the lever movement. Then adjust stop to give proper static rpm.

If thepiston travel is limited by the hub ´•low ~piteh stop (when.jack plate touches.

hub) then the pitch of the blades must be reduced. See Section III, Part B4.

2. Static rpm too high:

This condition readily be corrected by running the engine at full th~ottle
can

and pulling back on the cockpit propeller control until the correct static rplp’ is ob-
tained. Then stop engine and a.djust prop"ller low pitch stop screw until it bears
against the controlling surface.
3. Cruise rpm too high with respect to manifold pressure: The high pitch posi-
tion is not correct and is due to:

a. Improper travel of the piston in relation to the hub. This stroke can be

-18-
 with recommended strokes as listed in Section III, Part
checked and
C11´•lr=:r to see if the piston is actually ~ot;toming in cylinder.
The piston
A10.
11´•’32’’ fo!. the -2, -3, -4 models or
c.:´•7´•-ld exie~d::out from the cylinder about.
If tile piston does not bottom,
about, lilG’" for the -1 and -5 models.
1..,32"
remove pistol-i cause. If
and clirnin~tepiston is bot.toming correctly and stroke
thick to provide correct
insufficient, then acid shim behind rear cone sufficiently
stroke.
The push-pull control
b. Insufficient movement of the cockpit control lines:
through the full stroke.
lines must Ilave sufficient travel to actuate the piston
and observing
This can by running the engine up on the ground
be determined
\i!hethcr the piston moves through its stroke in response
to moving the push-pull
for low pitch stop,
control. If the control limits the travel of the piston, except
See Section III, Part
then rework the control until sufficient travel is obtained.
A13.
the short
c. tight: If the reversing control does not pull
Reverse control not
the bracket it will be impos-
end of the valve lever (pivot point) up tight against
and may be impossible to
sible to adjust the high-low pitch control satisfactorily
the bracket, loosen the
ob~ain full high pitch. To pull the lever pivot back against
and slide housing away from propel-
clamp holding the push-pull control housing
Tighten clamp. See Section III, Part
ier until pivot is hard against bracket.
A12.

C--OIL LEAKAGE
and adjacent parts, listed
?.here are several sources of oil leakage in the propeller
as follows:

1. "O" rings in hydraulic element. These rings may leak if:

determined that AN-6227 rings origi-
a. They become flat and hard. It has been
After few hours they
nally specified will not stand up at engine temperatures.
a

leak oil. Remedy--Use only Plastic and Rubber

become hard and flatten out and
Specification 11222-76 rings.

b. They are cut or nicked during, assembly. Remedy--replace.

becomes nicked rough. Remedy--Polish out
c. "O" ring grooves in piston or

nick with fine emery cloth.

scratched. Remedy--Polish out nicks
d. Surface of cylinder becomes rough or

with fine emery cloth.

noted
2. "0" rings in servo valve. This ringmay leak for the same reasons as
valve with chrome plated valve having doub-
r;bove under Item C1. Remedy--replace
valves and
le "0" rings. This type of valve is a recen’i, improvement over the original
the original
the factory byexchanging old valve. Incidentally,
may be obtained from
The chrome valves have elimin-
va.lves were the principle source of oil leakage.
new

atedl this source.

with soft paper gasket be-
3. gasket. Early asselnblies were put together
Valve
valve and allowed
tween valve and Fiston. It was found that vibration loosened the
hard paper gasket 1/64" thick. Also use
oil to leak past the gasket. Remedy--use
thin gasket compound.
-19-

ORIGINAL
As Received BY
ATP
 4. ~Hydraulic lines leak, the valve,
near nemecly--replace.
5. Piston
guide pins. Early models of the -1 propeller mounted on the Con-
tinental engine have three guide pills pressed into the cylinder from the rear to guide
the piston. As these pins were not backed up by the
engine they sometimes worked
loose, thereby allowing oil to leak. Remedy--1´•etu~n cy;inder and piston to fac~ol´•y
for late model pins which are pressed in from the fro~lt and riveted over at the rear.

6. Engine crankshaft seal. Oil leaking from this source is thrown by centrifu-
gal force into the propeller hydraulic element and works out through the thrust bear-
ing. Consequently, the oil appears to come from the smaller "0’’ rings. As this
source is quite common but difficult to recognize, it is recommended that the engine
seal be replaced if oil persists in coming from the hydraulic element after the above
remedies have been put into effect.

D--GREASE LEAKAGE

’I~’here are two of grease leaks. The bearing’ (3) and blade
sources bearings (22).
The grease leaking from bearing (3) is seen coming’ from between the
jar,kpiate (5)
and the cover plate (4). This leak is caused by over-greasing the bearings and
s~ops
when the excess grease is thrown off. Grease leaking from bearing (22) is seen com-
ing through the clamp gaskets and around the blade and clamp. By the use of seal-
ing compounds as described in Section VII, Part D-3 and’5, and new gaskets this leak
can be eliminated.

E--REPLACEMENT OF RIVETS

Rivets which break off or come out of the tipping should be replaced immediately
This can be done without removing the propeller fl´•om the airplane. All broken rivets,
whether they be 3/32" or 1/8" diameter brass or copper, should be replaced with 1./8"
annealecl copper having a 7/32" diameter flat head.
Replacing a 1/8" rivet.
1. If both heads of the broken rivet are still in place, center punch on the center
of the head and drill 1/8" deep with 1/16" drill.

2. Cut out the head with 90 degree countersink but do not cut the steel
a
tipping.
3. Punch out the old rivet with a 1j8" drift punch.
4. Redimple the metal tipping with 90 degree dimple.
5.
Insert,rivet from flat side of blade;

6. Cut rivet off leaving 3/16" or 1/4" extending. beyond the metal.
7. Head rivet with bucking iron and hammer using very light tapping strokes.
8. For smooth surface the vacant cavities around the rivet can be filled in with
a

solder and acid flux and then filed. Replacing a 3/32" rivet is similar to a 1/8" rivet
except tools must conform to the smaller size. The rivet hole should then be enlarged
for 1/8" rivet.

F--BLADES TURNING IN CLAMPS (-1, -4, and -5 propellers only.)

Natched lines on the blade and clamp halves are provided for determining
whether the blades are turning in the clamps. If slippage occurs remove the lock
-20-
 the
vire (28) and linksc~ew (25). Then tighten n~lts (13) and bolt (12) checking
Then check tightness of the
il´•eedorn of the blades on the hub to avoid over tightenin~.
blades in the clamp by applping 2000 inch pound moment
near the root of the blade by
means of a lever having a cut out to fit the blade section.

tube and will not withstand a 2000 inch

If the blade freezes on the hub pilot
File .005 off the metal contacting surfaces at
tile Made.
pound twisting force, remove
alone.
the corners of the clamps Imetal clamps)
to metal and put clamps on the blades
Ream hole in blade to
Tighten bolts so that metal contacting surfaces pull up tight.
for tightness of blade
1.502 1.r>04. Reassemble blade and clamp on hub and check
in clamp and also freedom of blade to rotate on pilot tube. (Use grease to fill pilot
hole for assembly.) See Section VII, Part D
at the corners of the
clamps do not have the metal contacting~ surfaces
If the
the blade is determined
parting line (early models), the tightness of the clamps
on

freeze an the tubes after the clamps

solely by the tightness of bolts (12). If the blades
to pass the torque test, then the pilot tube hole in the
are drawn up tight enough

blade must be reamed as noted above.

G--END PLAY IN BLADES

load on the blade and
The propeller was designed for the tube to take the bending
the bearing was then not
the ballbearing to take the centrifugal force. Preloading on
is as affective as a large amount;
necessary, very small amount of end play
thus, a

amount will not affect the airworthiness of the pro-

there~orc, an end play of any
at which time it is taken up by a wedge
peller. It is considered, however, in balancing
Dlaced between the hub and clamp.

H-BLADE TRACK
A few thousandths clearance be-
A tolerance of 1/4 inch in track is provided.
in the hub may result in as much as 3/:6"
tween the hole in the blade and the tube
fresdom at the tip of the propeller when the propeller is dry. With grease in the pilot
tube hole the play at the blade tip should be largely eliminated. It is sometimes nec-
tube and
essary to whirl the propeller
to force the grease in the space between the
hole.
number and letter. The num-
necently, the blade serial numbers include a dash
and the letter refers to track.
ber refers to balance as described in Part K

Due to variations of warpage which occursduring the manufacture of the pro-

"I-Il’ designates a track above the blue-
peller, three track dimensions were necessary,
dimension and "L" below the blueprint dimen-
print dimension, "C" on the blueprint
be assembled in a hub without
J_on. Two "H", two "C" and two "L" blades can
combination and "C" and "L" may be possible
checking the t;rack. A, "I-I" and "C"
within 1/4" tolerance. An "H" and "L" com-
but must be checked and maintained
should be made on the tip just back of the
bination should never be used. This check
metal tipping.
TUBES
I--WEAR IN BLADE BORE AND HUB
1.501 inches in diameter, as measured with
blades bore should be 1.502
clamp in place and pulled tight.
--2 1-
 If this hole is worn or oversize ii slloul~ be re-leamecl for an oversize pilot tubf
1.507 1.509 inches with clamp in plclce. New ove~´•.size tubes designated as the -5 tubes
should replace the standard tubes. R -5 should then be statnped behind the serial
n~unbei´• of the blades and hub for identification
puiposes.

J---WEAIZ IN TI´•IE BLADL~ BEARING

I’he ball bearings which hold the blades will last almost inclclinitely if they are
kept in grease. If, however, they are allowed to
dl.y for. any long period of time
I.utl
they will oxidize at
points of contact of balls and race. This is evidenced by the pres-
ence of red rust. The result is that the bearings will become
pitted, which may pre-
vent the pitcl-1 from changing. Minor
roughness will not affect propeller operation.
Replace bearings only if roughness is pronounced.

K--BLADE IMPROVEMENTS

The propeller blade Design L8427 as used the Sea-bce installation is

on subjected
to severe operating conditions due to the water splay and larg.e waves. The outer 6"
of the tip may wear throug~h in a relatively short period of time. To offset this prob-
lem the armored tip was developed. This tip adds about .090 more metal on 8" of the
tips and brings the leading edge to a very sharp point. The life of the blade is extend-
ed considerably by this
improvement, however, pilot care such as holding the rpm
as low as possible with
flaps do!vn while taxiing on water will aid a great deal in ex-
tending the life of the blades. Ry filing the armored tipping to a
first sign of pits will also aid in
sharp edge 3 the
exl;ending the life of the blades.
This improvementnecessitated two balance mast;ers. They are
designated as
and -2 which are stamped
after the serial number of the blades. These balance masters
have also been used for repair
purposes. Do not assemble a -1 blade with a -2 blade
and an unarmored blade with an armored blade. This
balance system was only stlart-
ed at the time of armored
tipping and all blades without a dash number are u&lally
-1 balance.

Propeller Blade Design 8428 was previously an 8628 as used on Continental

E-185 engine installations. This change in the propeller necessitated two masters
for this design, designated by a -1 and -2
following the serial number of the blade. A
-1 propeller must not be assembled with a -2
propeller.
G-HYDRAULIC ELEMENT IMPROVEMENTS
The guide pins have been increased in size to 7/16" in diameter and are installed
through the inside of the cylinder with the end
extending out the back and headed
over a steel washer. In this manner pins can not be pushed out
inadvertently on
assembiy and the added strength will alleviate
possibiiity of failure.
M--NEW CYLINDER M[OUNTING PROVISION FOR CONTINENTAL E-185 "D"

SERIES ENGINE

The "D" series engines provides four lugs on che nose for 5/16" cap~ screws or
studs. The cylinder for the dash 1 and dash 5 model propellers now have four
new

holes drilled through the cylinder for bolting on to the engine. In

making this instal-
-22-
 Al-
~tion it is recommended that the follow;ng pnrt,s be used: 4 NAS183-5-7A studs,
uminum Washers AN9BOD516 and AN 265-524 fibi~e inserted nuts.

N--VALVE IMPROVE´•IENTS

Oil leakage from the servo large part of the leakage problem.
valve czccounts for a

This has been eliminated by using two "0’ rings, plating the stem and rap-
chrome
the two parts are hand-fit-
ping the bore in valve body to the size of the stem. Since
it and is
ted, they are not interchangable. This new valve has a "C" stamped on
called the "C" series valve. Old valves may be exchanged at the factory for new ones.

O T~ASH 5 PROPELLER

The dash 5 propeller is an improved version of the dash 1 propeller, which incor-
links.
porates all the improvements mentioned above plus new type of pitch control
The links in jack plate assembl.y (5) are replaced with rods and forks. These rods

slide in lugs which are made integral with the hub. This feature prevents cocking
of
of the piston, which reduces the possibility of oil leakage, and possible breakage
the links and guide pins. Dash 5 propellers will be available after January i, 1948.

-23-
 SE(.:’I’ION IS

1’nTl’lS I,IST

~e 1 NO. REO. PER PROP.

Illu81rations DESCRIPTIONS PART NO. Model Dash No.
123456
1 1 Cylinder B-35 1
E-68 1
B-68A 1 1
1.3-1388 1 1 X
C-17 1
2 Piston C-36 1
C-67 1 1 1 1
D-78 1
3 Ball Bearing A-38 1 1 1 1 1
4 Cover Plate f3-12-1 1 1 1 1 1
B-12-3 1
5 Jack with Link 92-1 (RH) -1 1 1
and Washer 02-2 (LH) 1 1
B-109 1 1
8 1 Rear Cone A-50-1 1 1 1
A-50-4 1 1
7 1 IIub with Pilot 1 94-1 1 1
Tubes 94-2 1 1
94-5 1 r
8 Clamp half I C-3 See Illustration 24
9 Propeller blade 8428 2 2 2 2 a
L8427 2 2
10 Clamp Gasket I A-47 4 4 4 4 .4 a
11 Clamp Washer AN960-616 4 4 a 4 4 4
12 Clamp Bolt AN6-21 1 4 4 4 4 4 4
13 Nut I AN355-6 4 4 4 4 4 4
14 Socket Head Cap 3/8-24x1JC 4 4 4 4 4 4
Screw
15 20 Spline Nut A-G3 1 1 1 1 1 1
16 Safety Screw or Pin 1 1 1 1 1 1
17 1 Snap Ring A-40 i 1 1 1 1
38 Front Corle A-42 1 1 1 1 1 1;
]9 Blade Angle Stop A-75 I ´•z 2 2 2 2 a
20 I Washer I AN960-41 6LX 2 2 2 2 2 a
ar Cotter Pill AN380-3-3 11 11 11 11 11 11
22 Thrust Bearing A-14 2 2 2 2 2 a
23 Split Ring A-16 1 2 2 2 2 2 2
24 Counterweight C-fiG-~ 1 2 2 2 2 2
Clamp Half C-6(i-3 1 2
25 Linkscrew A-7 Z 2 2 2
A-98 2 2
26 "0" Ring Seal H228-70-33 2 2 2 2 2 2
27 Snap Ring Eaten Nol. 6 2 2 2 2 2 a
28 Linkscrew I A-64 1 2 2 2 2
Wirelock
29 Outer "O" Ring H222-70-67 1 1 1 I 1
Seal I H222-i0-72 1
30 Inner "O" Ring Seal H222-70-44 1 2 1 2 2 2
31 1 Felt Seal A-$4 i 1 1 1
32 1 Cover Plate Gasket R-73 1 1 1 1 1
33 1 Washer AN936A-10 12 12 12 12 12 12
34 Bearing Wire Retainer A-43 I 1 1 1 1 1 1
35 1 Screws I AN501-A-10-6 12 12 12 12 12 12
36 Socket Head Cap 1/4-28x3 /4 2 2 2 2 2 2
Screws
37 Gasket I A-71-1 1 I 1
A-71-2 I 1 1 1
38 Cotter Pin AN380-2-2 1 3 3 3 3 3 3
39 "0" Ring Seal H222-70-10 1 1 1 1 2 2
40 1 Valve Plate I A-56-1 1 ´•1 1
A-56-2 1 1 1
41 Valve Body B-59-1 I 1 1 1
B-59-2 1 1 1 1

-24-
 I~

P~RTS LIS’I’--COSTINIJED

1 I
-------;ii i valve
1 1
A-)OIA
A-108 1 1
AIIJ3!13-13 I I 1 1 1 1
´•13 L.ci~cr Pin
A-41 1 1
54 Valv´• Lever
A-102 1
Bracket
A-105 1 1
Discontinued
45 Valve Spring
4 4 2 2 2
Filuster Head Screw AN501-A-10-6
46
A-4e
47 Weight Slug i
48 Filuster Read AN501-A-10-4,
Screw 5 g,6

RECOMMENDED GREASES:
fact that water sometimes gets into the pro-
i. Experience has brought to iight the
water. will mix with certain types of greases
peller blade clamp assembly. This This may result in
in consistency.
and cause them to become hard and chalky
as the blades may become tight on
the pilot tubes.
poor operation of the propeller,
ior water resistance, tackiness, Lubricating
2. A number of greases have been tested
properties when mixed with water, an~ viscosity under variu~s temperatures. The
are recommended in the order of listing:
following greases

(a) Lubriplate 630 AA

Fiske Brothers, Toledo, Ohio.

(b) Stroma HT-I (2-801 Grease)

Union Oil Co. of California.

(c) RPNI Aviation Grease No. 2

Standard Oil Co. of California.

(d) Stroma LT-1 (2-815 Grease)

Union Oil Co. of California.

(e) RPM Aviation Grease No. 1

Standard Oil Co. of California.

(f) Lubriplate 707

Fiske Brothers, Toledo, Ohio.

(g) Mobilgrease Aero Lo-Hi PD-535-K

Socony Vacuum Oil Co.

(h) No. 84 Medium Grease

Keystone Lubricating Co.

(i) Texaco Regal Starfak Special.

-25-
 SECTIONN ,Y.

IIC’-12x20-$ and 8 models

Tile dasl? 7 and dash 8 models reflect basic

a chnnge inthe design of the hy-
draulic element (See assembly drawing).
The "0" rings are replaced by a synthetic rubber diap~ll´•ag.m; the object being
to eliminate all possibilities of oil leakage. The valve is moved; to the rear of the cylin-
der in order to be located within the
engine cowling. All rotating elements of the
propeller are identical to the dastl 5 desig~n. There are
selreral configul´•ations of
these models, which have interchangable parts with few
excet~tions as noted below:

A--MODELS

i. HC-12x20-7: This model is designed to fit Continental E-185 engine only.

2. HC-12x20-8: This model will fit
any engine having S. 1A. E, standard 20 spline
shaft and nose plate.

3. Both the dash 7 and dash 8 models have sevel´•al

partg configurations as list-
ed ill thefollowing table:
Model Hub Clamp Jack kssembly Cylinder
HC-12x20-7 C-49-2A 0-3-1 I3-109-2 0-111-7
HC-12x20-7A C-49-1A C-3-1 B-109-3 C-111-7
HC-12x20-7r, C-49-2A 0-3-3 B-109-4 C-111-7
HC-12x20-8 C-49-2A C-3-1 B-109-2 C-111-8
HC-12x20-8A C-49-1A C-3-1 B-109-3 C-111-8
HC-12x20-8B C-49-28 C-3-3 B-109-4 0-111-8

All other parts are interchangable.

B--INSTALLATION

The installation of the dash 7 and dash 8 models is the same as for the other mod-
els described previously except for the hydraulic element, whi~h is outlined in detail
below

1. Remove piston from cylinder by removing A-12L valveilink screw and sliding
piston forward off piston guide rods.

2. Remove diaphragm B-119 by removing outer and in~er plates B-120 and
A-113.

3. The cylinder is mounted on the

engine nose with the guide pins A-122 in the
horizontalplane. It may be necessary to trim the cowling td clear the guide
pin
brackets. After the cowling is trimmed
proceed to install cyli~der onto engine nose.
In order to eliminate all possibilities of oil leaks it
is recominended that a paper
-26-
 C-lll. and the face of the engine, together with bas-
gasket be used between cylinder
ket compound.

the Continental "D" series engines with

30. The cylindei- C-lll-7 is mounted on

4 Alien head cap screws (5/16-18). Use 1 1G thick a.luminurn or copper washers

under the heads of the screws. Re sul.e the screws do not bottom in the engine
otherw’ise oil will leak out.
tapped hole before pulling up tight on the cylinder;
screws with wire through drilled holes in screw
head.
Safety
with
3b. The cylinder C-lll.-7 is mounted on the early undamI)ened engines a

sheet metal bracket which is screwed to the rear of the cylinder.

3c. The cylinder plate of any engine having an SAE

C-lll-8 is bolted to the nose
and gas-
standard nose with the six studs provided on the engine. I~se a gasket
Icet compound between engine and cylinder. Also use washer
and "Elastic Stop
the latter is recommended as oil will not leak past the
Nut" on inside of cylinder;
threads.

4. diaphragm with inner and outer diaphragm rings. Important

Install rubber
out past the edges of the
--tighten all screws uniformly until the rubber squeezes
rings 1/16 inch. Breakage of the rings may result if only a few’screws are tightened
up at a time.

lines to valve. An 18 inch line is required for the pressure

5. Install hydraulic
The drain line should be as short as possible. Use
;de for the dash 7 installation.
4 I. D. flexible hose.

6. Grease front face of rubber diaphragm and install piston. Connect A-f18
wire running to other screws
link with piston, using A-121 screw. Safety screw with
on piston.

7. Install propeller hub and blade assembly.

8. Connect control wire to valve lever A-117. ´•For Navions, this re-
push-pull
of engine (facing‘ rear of engine from
quires shifting the control wire from left side
the wire at the front can be reworked
cockpit) to right side. The bracket supporting
with resp~ct to
by riveting angle plate to support the wire in the proper po~silion
on an
in forward position
the lever. When connecting wire to level. A-117, position piston
and valve body 3/18 inch from valve plate (near mid position); also push-pull control
inch. (When piston is in forward position
should be pulled out from dash about 1/8
it extends out in front of R-120 Plate by 1/8 inch. When in neutral position, piston
front face is 1/16 behind face of E-120 plate).
both
9. Check travel of piston. The total travel should be 3~8", or 3/16" on

do not exist the

position of diaphrag‘m. If these dimensions
rear
sides of neutral
cone should be shimmed or reduced in length to provide above travel.

to provide proper static R~M. Shut

10. Runup engine and set pitch control

-27-
 off engine and set low stop scl´•e~ on lin fl 118 so tha’s it touches va!v: body. Cher´•k
engine static again to assul´•e proper sto~ setling. Shut; off eng´•ine and check c:leal´•-
ance between jack plate B-87 and hub when in low
pitch. This can be done with the
engine running by standing to one side of
pi.opellci and obsel.ving clearance gap. A
1’18" clearance Inust exist;; otherwise the Ihrust
be;ti´•ings in p.rlopeller and engine will
be loaded up needlessly Chcclr high pitch travel by pulling control back to limit
and :Torcing piston back by pushing on
countrl-weigllts. ?’he vjalve lever should have
sufficient travel so that the valve can be positioned at the center of its travel while
the piston C 112 is at rear end of its travel of 3;8 inch. This lajtter check will
provide
assul’ance of obtaining full RPM
range available during flight.

11. Safety feature: In the event

a leak should developlin the diaphragm or

cylinder, the oil supply to

cylinder can be shut off during flight by pulling the prop
control wire to the extreme rear, past the normal high
pitch seltting. The mechanical
stop will limit the high pitch while the valve will shut off the oil. In order for this
feature to be effective there must be provided sufficient travel in the
push-pull wire
and lever so as to position the valve body in front of the neuti.al
position while the
C-112 piston is in the extreme rear position. Whether the valve
actually closes can also
be checked with’engine running full throttle
by slowly reducinf: engine speed with
prop control. If the prop control has a slight travel of say 1~L)´•1 after the RPM stops
dropping, this indicates that the valve is closed.

B--SERVICE PROBLEMS

The diaphragm hydraulic element ha; proven to be entirely reliable and free
from oil leakage when installed properly. ?’o date all leaka~e troubles have been
traced to the following:

(a) mounting bolts not properly installed; eit)le~ they

bottomed in the crank-
or were not pulled
case
up tight on the washers;

S (b) diaphragm screws not tight enough;

(c) engine shaft seal leaking excessive amount.

In order to eliminate the

problem of oil from a leaky engine shaft seal flooding
the thrust bearing and coming out the front of the hydraulic element, a drain hole
has been provided in cylinder C-lll. Tests indicate that the drain will handle any
normal leakage without any reaching the thrust
bearing.; b~t when the leakage
reaches extreme amounts (1 qt. per hr.) i~ flood the bearing, in which case a
may
new seal should be installed.

It is desirable, in connection with the oil dl´•Rin. to provide a drain tube to carry
the oil outside of the engine compartment..

The service life of the diaphragm has not been determined to date. It‘ is recom-
mended that it be replaced during the major ovel´•haul or at 250: hours.
-28-
 IIl\lt’r%EI,I., PfLOPELLER Angust 3, 1938
P~1´•ts List
Motfcl EIC-12x20-7 -8/8428
Also HC-12s%O-SA, -7R, -8n, -8B/8428 (See note below)
Ofy. Model DJsh No.
Parf Change
NnME Per Prop. -7 -8
No. Letfer

8428 O 2 x x

;::C-3 GG Clamp 2 x x

2 x
n-14 C fearing, blade x

C Split ninh´• z x x
A-ZG
B-17 Q Counterwcight 2 x x

A-24 B Pilot Tube 2 x x

A-38 Ball Bearing’ 1 x x

A-42 B Cone, front 1 x x

A-43 Retainer, Wire 1 x x

R-46 Snap Rin.g 1 x x

A-/17 n Casket. claml, 4 x x

x
A´•48 A Weight Slug x

"C-49 S Hub 1 x x

A-50-1 C: Cone, Rear 1 x x

A-53 D Ring, Blade 2 x x

B-55 B tralve Assembly 1 x x

A-5Fi E Plate, Valve 1 x x

P,-57 B Tube, Valve 1 x x

A-58 D Guide Pin ’1 x x

B-59 N Valve Bod~ 1 x x

A-G3 n Nut-Prop Huh 1 x x

ff-65 Pin, Countc~weight Dowel 2 x x

Assembly Counterweight 2 x x

A-66
71-1 B Gasket 1 x x

A-72 L Blade Shank Details 2 x x

E-73 Gasket, Cover Plate 1 x x

A-81 Shank Screws 24 x x

"R´•87 B Jack 1 x x

C-C34 Assembly, Hub Tube 1 x x

n-95 C Block, Pitch Change 2 x x

A-06 E Fork, Pitch Change 2 x x

A-97 F Rod, Push 2_ x x

A-08 A Screw, push rod 2 x x

H-109 D Assembly, jack plate 1 x x

C-171-7 C Cylinder, diaphragm 1- x

C-lll-8 C Cylinder. diaphragm 1 x

C-112 ’t3 Piston, diaphl:agm 1: x x

A-113 Plate, inner diaphragm 1 x x

A-11I1 Pin, staking fork 2 x x

A-115 Pin, staking push rod 2 x x

R-11BA Bushing, push rod 2 x x

A-11GB Bushing, push rod 2 x x

A-117 B Lever, Valve 1 x x

’:’NOTE Models -7 and -8 ~equil´•es C-4D-2A hub, C-3-1 clamp and B-109-2 jack ass’y.
Models -7A and -8A require C-49-1A hub, C-3-1 clamp, aind R-109-3 jack ass’y.
Models -713 and -8B require C-40-2A hub, C-3-3 clamp and B-109-4 jack ass’y.
All other parts are interchang’able.
-29-
Parts List IIAnTZELP, FnOlPELILIER Page Twb
Model IiC-12x20-7 -8/8428
Part Change Qty. Elodel Wsh No.
No. Leffer NAME Per´• Prop. -7 -8
A-118 B r,ink, Valve :1 x x
E-119 Diaph~agm 1 x x
B-120 Plate, outer diaphragm 1 x
A-121 Screw, Valve Link I x
A-122 Rod, Piston Guide 2 x x
D-125 Assembly, Model HC-12x20 1 x
-7. -8
AN501-A10-6 Screws 12 x
ANlj01-A10-12 Screws 26 x x
AN380-2-2 Cotter pin 3 x
AN380-2-3 Cotter pin 11 x x
Eaten No. 6 Snap Ring 2 x
1/4-28 Zerk Fitting 5 x x
H222-70-10 "0" Ring (Valve) 2 x x
~PL,ASTIC RUBBER SPEC.
H222-70-33 "O" Ring (Clamp) 2 x
3/8-24x1 1/4 Alien Head Screw (Clamp) 4
7/16-20-1 1/4 Alien Head Screw (Cltwt.) 4 x
1/4-28-3/4 Alien Head Screw (Valve) 2
AN6-21 Bolt (Clamp) 4 x
AN355-G Nut (Clamp) 4 x
AN960-616 Washer (Clamp) 4 t
AN960-516LX Washer (For A-75-2) 2 x
AN501-A10-4 Screw (A-48) 2 x
AN393-13 Fin (A-44) 1 x
AN936A-10 Lock Washer 38 x x
 Zj´•l

\9 i

´• rI´•
~3´•,i c
.sn
.C C-
.´•r~´•
i
f" 5 v’~

r’
.J
$;1-? J
1 4 i´•

´•...~i’ 61f
a "I´•´•
ii c~1
ii
f;; ,i´• t
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is;
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(ai f~ t;
I~--=
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I’´•´•-´•´•
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r^´• t4 ;1)
iii

ORIGINAL
As Received By
ATP
h
 iL700 1.
~LtlN1IIIL LOOU

SUBJECT r of I´•lodcls -8

DZSCUSSTON: The -8 models a~e to the

-8 model.a except: for the i~act that
A-971. split bcnrines and C-C)99 huh of ~IC´•-n2%20
~epZace t~-le sl,lj.tl hub spit~er and solid
benrj.ng~ of the liC-1.2X%O. T~ie compl.ete p~rts
IJ-~t oS C~.io IlC-1)2S20-7, -U encloocd.

OVfSR!Li\TTT,
Ovc7:´•T~n.ul. of the SZC-D2X%O prupell.el-s is
the same as fo~ ~C-12X20 models, excc~t Eo~ ~he
installation of the n-971 bcarFngs; for this yee

~nrtze%l Manual II~ or (flC).

F’IIA-DO~I´•- 3EA B~I’KOVEn I-IAKTZELL TROPE%LEK, T.NC. Approved 3uly 37, 1.967

As s ly
PIQUA,
PAT~%S
01´•120J~TS’d: UY L1´• i

BC´•´•D2X20-7 &-8 r)av-id

131: aaring
Vice Pres. G C;c.n
L)- ~050
N~tmi,cr i’,cc;ll´•ir~:u

WC-D2X20 ~IC-D2X20
C:i~nge -7
;;ctll~er´• TJart Nurnbefi Nomenc: l.al_ure

1. Z
1340-Ei% llllT3 SP:CDKTr TJNIT
1 1.
I~ C-C)(P9-I Hul3 Sph:ler
1 i
E C-936f-1 DP-tJ~E linl~
2. 7
A-´• 1.23 Lug s
PlaHtic ISusl´•iings 2
A- 11.Gh-l
2 2.
A-158L Yilo~ Tuhes
Sh,-~ft 1
Ir’ h- 1. 55 )3ushi.ng,

I-~UU PhR%S
2 2
PKP-909-8 "CC" K~ngs, Blade
2
A-971 Split Uear~ngfi, Elade
Wire n~n6$9 Bearing 2
A A-2Q%7
2 2
A-31k Uall Spacers, Bearine
Gukde Rings, BearFng 2
n-9r2
Guidzz Retention 2 2
A A-916 Wi~re Rings,
Ken~ Cone 3 I
A-IS4 Spacers,
1. 1
ri- so´•´• i. Rear Cone
q 1 I
h-63-U’ Sha~t Nut
L 1
i: A-156 eul.ler King
I 3_
n-Lt6 S´•nRP li.FnE,
I. I
G 1?-8LE7 SLiE~ty P:ln, Shaft Nut

2 2
83 8-12. CLAMP h COUNTERWEIG~IT BSS’Y
T
2 .2
~q C-3-IA Clamp
2
:C n-295 Linkscrew
3. 2
i) 1\-´•´•2 85 Sta.l~ice V-j.n, LinL,screw
2 2
833-8 CourlTer~wei.ghC Unit
4´• /L
m-%036-14 Cap Screwu, Cztwt
Soc!~e-ir Ilcnd
4 !e
I) A-285 StakLng PFns, Sk.Hd.Cap Sc.
2
13 n-6~5 St~ting Pbn, Countcrweight
4 L~
M~1.5001´•-1 Zcrk Pittines
4 1~
i~-´•Lk7´•´•´•1 Clr-~np Gask~ts
.1 R-282 Soclce~ Scrfws, CLamF,
Soc~et Screw 4 4
AN38ft-3-22 Cotter Pins,
r2´• Polnl: 4 I;
i:: h- 2017 C:l.arnw ]3o3~ts,
4. 1!
A1\19gU-63.6
4 ii.
h´•´•2t)1,3 (:R.aiuj~ Nu~s
4 ’C
No, 3

CI,~P RSSC/CXh%’IZI) VAK’L’S

i3-´•rca i.:r?:t.,:-!nce Rs c?c~

!t
Screws, RaLsnce ~Jeieht hc; Nce il~´•!
Zl~l.trlEcsb I’-j.t::c.rl´• i;!lanl;e 2 2
Cot~er Pl.ns, i.
u~e
O.E~
 !LC~UOnn3EA API)RUVED P;ZO1ZELLER, 3:NC, Approved July 27, 1367
PZQUIZ, 01-110
R,s I.y s e mb PART S LZST
Drawing IIC-D2X20-7 Si -8 David Bicrniann
Dn2050 Vice Pres. ~IGcn. Mannqcr
Nu!nbe~ i:e!u~c.-r3;I

i;ange
HC-n2X20 ~C-D2X%O
X)art I Nomcnclnture -7 -8

I´•
E BYDR~ULIC UN%T I
L C- 3.3. 1- 7 Cylii.mder Uxlft: 1
L C-llL-7 B@t~l Gyl.~nder 1
E 1’ n-222 Guide Rods, Cylinder 2

1; Stalring Pins, Guide Rod 2

G 1 A-2037 Socke~ ~ead Cap Screws 4
h I n- 128 Waslrers 4
R I A-135
Moun~ing I
B-119-2 Diapk~agm 1
C A- 1. 1.3- 2 ZnneR-Rl.ny,, 1
AN501A10-18 Screws, Irtner Ring Mountlne 8
B 0-120 Outer Ring, Diaph~aem 1
AN501A1U-L2 Screws, Outer Ring Mounting 18
AN9 3 GhlO Lock Washel,-s 18
~1 C-Z1%-2 Pis~on L
M C-la.2-7, ’Pis~oxr 1
n-II6J3-1 Plas~ic Bushkngs 2
~13.9L-4CN x5 ~elicoil 1
G A-38U B~arZng 1
13 U- 73 Gasket, Cover Plate 1
c I’ R-12-7 Cover P13~e, Bearing 1
AN501h10-6 Screws, Cover Plate 12
hN93gAIO Locl~ Washers 1 22
MS15001-1 Zesk Fit~ing 1
No, 3 Lub~icnp 1
N B-109’-9 Jack Plate Unit(w/o Spinner) 1
P R-n7-1 Jack Plate 1
J A- 9 7- 7 Push Rods, Jack Plate 2
L n-114-F Stakine Pj.ns, Push Rod 2
A-82L For~s, Push Rod 2
I, t A- 124-A St-ca.klng Pins, Fork 2
N B-109-9h Jack Plate Unit (w Spinner) 1
P B-87C-1 Sack Pla~e I
J 7-7 lieds, Jack Plate 2
L A-214-F StakinE Pins, Push Rod 2
n-821 Forks, Push Rod 1 2
]L n-124-k Stnking PFns, Fork 1 2

2 o~
 IWITZE:ZLl’f:OPErLr:R, TNC. ApproveJ Jul 27, 1’)67
Fnh-DOn-3EI~ APPROVED

As s eml,’ly
P~QUA, O~IO
PART S ZIIST Uy U-~
Davi~
IIC-D2X20-7 S: -8
Vice Pres. Gcn.
n-2050
j:ec.7ui.rcc~

HC-D2X20 HC-D%X~O
C han I, e
Norncnc.la tu~^ -7
Lcl:~eri Part: Nunlher

E 191-813 BYDRAIJLIC 1IMLT I I 1

1
A-X81 Gaslret, Enginn Mounting
"O" Rings, Stud Mounting 6
PRP-´•302-7
1
L C-P11-8 Cylinder Uni~
I
L C-T1L-8 Z)etJEl Cyl~nder
Guide Rods, CyLinde~ 2
E A-122
2
L h-114-B S~aking Pins, Guide Rod
EXas~ic Nuts, Eng. Mounting 6
A-2043
1
E B-129-2 niaphragm
I
0 R-f13-2 Inner Ring, Diaphragm
AM501A10-10 Screws, Tnner Rine Mounting
Ou~er Ring, Diaphragm
1
B B-120
28
hN501A10-%2 Screws, Outer Ring Mounting
Lock Washers 16
AN93GhLO
P%ston Un~t i
TJI C-112-2
Pis~on 1
P/r C-112-2
2
A-11GB-I Plasr-ic nushFngs
1
S~1191-L-I´•CN x
1
h-38B Bearine
1
]3 B-73 Gasket, Cover Pla~e
1
0 B-12-7 Cover Plate, nearing
12
AN501.A10-6 Screws, Cover Elate
Lock rJashers 12
RN93GA10
Zerk ´•1
MS1S001-1
1
No. 3 Lubricap
Unit(w/o Spinner) 1
N B-109-9 Jack Plate
1
P B-87-1 Jack Plate
2
J h- 9 7- 7 rush Rods, Jack Plate
2
r., A- LL4-I~ StakJ.ng Pins, Push Rod
2
m A-821 Forks, Push Rod
2
L A-114-A Pins, Fork
1
N D-109-9A Jack Piate Unit (w Spinner)
Jack Plate I
P l3-87C-l
2
J A-97-7 Push Rods, Jack Plate
2
L,
A-21_4-F Staking Pins, Push Rod
2
rC A-821 ~orks, Push Rad
2
i., A- ba4-A Staking Pins, Fork

SaP8
FM-´•I)Dn-3Eh APFTIOVED rrN~TZELT, ~PR.I)PELLER, ZP3C. Approved JUly 27, 1967
PI(2UA, O~’i?O
As s c.mT-, ly PRR’;C’ L%ST By
´•i´•8 ua~id i:icrmann
Drawinji
D-2050
Number
1-~-----1*1
ItC-D2X20 i-~C-132)120
:ilanp,e
Vart, N~:lmbeT Ni, mt: n r: 1 a tr ur: c
-7 -8 i
.et~_cr

VAX,~i’E LZSSEM:CZY (N~.VTBN O~IL;Y) I.

i 93-h
R-266 Valve Unit i J
X B-1G7 Body a

F I Spool I 1.

rna-90%-10 ’PO’s R~nZSg VaLv" i 2

13 A- 180 1 L-i.nl~ Arua i 1

mN393-Z7 1 Clev~s Pin I
AN3 9 3 2 L Clcv´•-is p´•j,n I 1

hN 3 8 0 2- 2 I Cat~ter ~ins 1 3
hN393-23 CLev~s Pin 1
n-126 1
Spacer
D A.- 18rt-6 L,i.nZe Arm 1.
1
AN50%h10-LQ Screw, Stop Ad~justment 1
AN3G~J´•-a032 Nut:, S~ay? I
A.- 203 8- an 1 SocZcc~ Weadd Cap Screws 1 2
B
2
RNBB 8- c~´•aG i
1
j GEiskct, Val..\re ~launtl.nG

i VAI,VE ASSE~IIl:I,Y. 1.
Valve Unil: I 1
H- J,G 6
1 5,
B-1~7 Eodly
I 1
n-168 Spooi
(1011 ~til.n6s, Valve 2 2
1>IIY-902-ao
I,inte Arm 1 ´•I
R- 1. 87
Clevis Pin 1 1
nN393-17
Clev-~s PFn 1 Z
AN393-21.
rl.ns 3 3
hr~380- 2´•´• 2 Cotter
CZewi.s Yin i. Z
hN3 B 3 23
1 L
A-r26 Spacer
IZ,-ink Arm I a. I
D h- 1 8 LI.~ 6
1 I
Screw, Srop Ar15 ustment
1 1
AN365-2032 ~ut, S~op
Soclr:ct: ZIe4d Ca.p Screws a. 2
1:; R´•´• 203 8- 5.0
2 2
AN36U-4EG a

I r a
rZ h~7n-2 Gasket, VaZve Mounting

4- of~
 AI~PROVED HI\,RTZEZZ P1IOPEtLEK, INC. Approved July 27, 1967
PT.(2UA, O!i10
PART S ra:slxl
3r:C´•´•n2);20´•´•7 E~ -O David
_ij::awir´•lg
Vice Prc~s. G C,cn. I´•:anaecr
DU%O50
NuIllbcr I~eau´•ireu

HC-D2X20 HC-D2X20
C:::117 nge
i~::iil:ccclal:ure -7 -8
,!::~l:Er i"aT1: Mt;lllll>t.?"

33-(: VA%VE ~SSFPD:I:,Y (SLrI’iS"n I\:i\VIOMB I 1

Valve Uni~ Z
~-166
1.
:r, ’II´•- l.G, 7 Body
1
r’ A´•´•1G8 Spool.
"O" Rin6~, Valve 2
PnI’-902-´•LO
I
11 n~- l.t3o 1 %i.n4i~ Ar´•m
Pin I
1
AN393-21 ie2evis Pin
Pins 3
RN380-2-2 Colter
CTevi.s Pin L
A.N393-23
Snace~ 1
R-L26
I,Lmfe Arm L
]S A´•´•´•L04-:I
1
AN50~A10-10 Scvzw, S~op nd~ustment
BLss~ic Nut, Stop 1
AN3~5-1032
Socke~ I-Ee~d Cap Screw~ 2
13 n´•´•~zsrEs´•-26
3,
Ar\r360´•-4´•~.e I iJ38~l.erS
Va’l.ve Mounting 2
:14 n- ´•i~ I.- a r,aulxets,
U%ock 1
D A´•´•~72

53-hG vns;v~ (NhVLON w/GOVI I

a~- 1.6 6 ~la%ve Unit 1

1
:i: 1.2-´• LG7 rrocly
n.- s,r,a Sp~ok I
P
1.’)~ X’´•´• 0 2´•´•´• I. W 1’’0" KFngo, Valve 2

A- ’J. 73- 2 Il~i_nte nrm 1

E:
A.N393´•´•´•1.7 f13.evis P-~.n I
B,ra3~!t-2´•´•3. C:o~t-.er X1:i.n L

r?.- I) 11R-´•20 Socket J-iead Cap Screws 2

2;
~N960´•-41G I’i~ras)ael3s 2

A´•:´•’l n.´•´•2 r,aslrct, Val..ire Mounting L

(.I 93´•´•ini: BSSEisit:tY (S-I~IVION

w/GOV~ L

B´•:´•:tGt; Valve UnFt: 1

1.
1:: I n´•´•~ 1. 67 !:ody
h´•i;:E.Cj 8 I 1
’tC;" Kin~r:9, Vnlvr. 2
T’j:!~’´•;´• ’3~a_-´• I.r,
R´•;´• 73-´• Li 1
f:l.c-.v´•J.s I’;.r-1 1

I,:oZ;ter Pin Z

A.´•- 2 C)3 Si-´• 7. O :_;c;c.lrc.i-. ETead Cap Screws 2

f!
P:19 6 0´•´• 4 :i. 6 ‘r,i;-2 s ti e 3.- 9 2
n´•´•71´•-2 [(~nf!cci:s, Valve M‘ounting 1
\3~ cliCI 8
ic.,l
 Approved July 2.7, 1C167

navid Uit:~i:ma.nn
Gcn,
1?Tun~bi3r

ZIC- D2X20%XI2i)
i´•´•
I I I
i ´•:´•7 -’J

I:: !:’´•’:´•:i´•:i:lic ’’r" i:l::i:vi: 1.

1~ i
I,
2;’ j X
4_
1.
’;j,li~:ti´•.c:.!-s, 4
’I-i‘TO´•´•´•’i ji’Cay.!.orlk. i;il.il::o, i4uv, Flou.n~fng 4
E I 1
n i L, Ili]r 1
1 n´•´•:l. s i. F a_l-ini‘i´• sc.:rt~!J 2
Rr.J C: r, r~% F:: 4
ri7.!t.´•4 KayBock Ili~i:s 2

2
Il.ol!!p Frounr;-inl: 2
AN960´•:t or. W’ashe~s, .i\clel. C,l.ii:;:p MoUXI1,:L;lg 2
y10 :i ;ICay:l.osk i´•i!?!;:;, Clnmp Mou!lt:lnt~ 2
,1 A´•-´•´• :IrfS´•´• :Z Stl\PdB
835206 Gashet, i.
"’,i.’" ;~!:´•ive Mo´•t,J.7t;~ng 3
ii-; 1,
AM960´•´•´•43;5 Ic
i
H i. 0- CI
31

GFonnet, (O.J, k%ul@) i.

PY&22~bD El.bo~sr ’3i:" 3
~320e- 2 1.
AF16270-´•6c´•~Q Hose .I:!;-.´•I.t:! 1_
I A-i. 73.´•´•4 j Li.nk; 1
3~729- 7 i Verni eT r::´•,lr!.:rc´•:L. 1.
I
5 Pieoe Beech Conj~l.cC1. i.
1. i

PId31~-4R Ctreck Nvt, C!)ilil%:;>?. i.

AN742~$e ~AdaL ’:I´•~!i’i’:: I!~sai-c?: Contrc~. Z
6-cGBx-s 90" Fu.al. L3.ne 2

Ad~2CO-6-29 )Iote FI)eI ~iho L

19N74?pl 2C Ac)el ;;:l:;::;t ]:,4.na

6 os´•
E%1A-DOA-3EA APPROVED IIARTZELL PROE>T~T,LEK, INC. Approved July 27, 1967
PIQUlt, OH’I.O
4s s emb ly PART S LIST By
rawing HC-D2X20-7 -8 DQvid B~crmann
D-;?O50 Vice Pres. Gen. Man~jier
Nuinbe~

HC-D2X20 IlC-D2X20
::ian6e -7 -8
Part: Nornc~nclature

A-%O60 (NAVION) "T" DRIVE KZT 1

D C-137-IB "T" Drive Unit I 1
AN823-6P Elbow, 450 2
F A-213 Coupling, Governor Drive 1
~57354D Gasket, Woodward Govi Mtg. 1
A;- ZR IIartzell Governor 1
AN9~0-Sa6 Washers, Governor Mounting 4
IITO- 5 IKay3_ock Nuts, Gov, ~iounting 4
E ~-197 Bracket j 1
A A-299 Link 1
D A-121 Link Screw I´• 1
AN960-416 Washers 4
E110-4 Kaylock Nuts 2
AN% 7g- 6 Ball Joint I 1
AN742I)7C Adel Clamps 2
AN501A10-10 Screws, Adel Clamp Mounting 2
A.M960-10L Washers, Adel Clamp Mo~nting 2
W%0-3 Kaylock Nuts, Clamp Mounting 2
J A-148-2 Studs, "T" Drive Mounting 2
~352061 Gasket, B-145 Mounting 1
AN404S-PP Gaskets, "T" Drive Mounting 3
~530371 ZIeat Shield, Fuel Pump 1
fLN960-4a6 Washers, "T" Drive Mounting 4
H10-4 Keylock Nuts, "T" Drive Mtg. 4
AN6260-6-48 IHose, Oil Line I
nN742D12C Adel Clamps, Oil Line 2
AM822-6D Elbow, 900 3
~3204-2 Coupling Adaptor 1
AN6 2 70- 6- 10 IHose, Drain I 1
3B A- 17 3- 4 ILil’lk, Valve 1 1
3A729-7 Vernier Control 1
5Piece ’IBeeck Gronrmct, vernier cont~rop 1
AN742D7C IAdel Clamp, Vernier Control 1
AN316-4K (Check Nut, Vernier Control 1
Lllh-DOA-3EA APPROVED HARTZELZI PROPELLEK, TNd. Approved July 27, 1967
PIQUA, OHIO
Assembly PCtRTS LTST By
Drawing HC-D2X20-7 Cc -8
D12050
Vic@ Pres. Fen.
Numher

:bnn6el I HC-D2X20 WC-D2X20

\~tcr 17axt Na~cncbature -7 -8
FO~i 13200 Cc 215 BEECEI WUB KEEP;RCEMEMT
H C-175-1 Beech Adap~or (~"Dia 1.
35-960026-12 Beceh Supparf: Assenihfy 2
35-960026-14 Deech Dome L

~OR R203 I~EECH HU~ REPEaACEME~r

H I C- X, 7 5- 2 ~eecti SD~nner Z
35-960010-12 Beech Support Asseml>2ly 2
35-´•960026-%4 Beech Dome 1

E~ 1D1166, ASSEMBLY 1. r
D D-163 Dame, Sginner 1 1
A-130 Bushing I L
E C-142 Bulkhead Unit 1
AN526Cf032R7 Screws, Dome Mounting 1 10 1 10

8 6~5 8 1 r
Vlllyn. 8 CIF R
 ~0. 2
100D

SUDJECT: Addition of M~del KC-D3X~O-6L

The HC-D3~20-GL n~dcl is iden~ical in to

DISCIJSSIOI\J:
~he HC-~2X20-7, two-blzded propeller
it has blajes. The parts list is g~ven
in the pa~es.

OVERI~.TK,
I)ROCE.UUI:ES: Ovsl:baul. and assenlbly of t:he HC-D31[20-GT,
for t:~e
prop@ller is sui-,stentFa~ly the same as
WC-D2X20-7, and also ~or the HC-23n20 r~odels,
for the ~ns:allntion of the ~-371 b,-,-z´•J.nSs.
except
Tiihis is described in ~ianual 1L4 or 11C).
Approved: HARTZELL PROPELLER, INC.
PIQUA, OHIO

David Biermann
PARTS LIST
Vice Pres. Gen. Mgr.
Model HC-D3X20-6L

June 21, 1962

A.ssemblv Drawing D-360

Part No. Nomenclature r equired

1
840-65 HUB SPIDER UNIT
C-1482 H i r

A-158L Pilot s

A-155 Bushing D 1

HUB ASSOCIA TED PARTS

A-971 Split Bearing F 3

A-2027 Bearing Retention Ring 3

A-972 Guide Ring B 3

A-974 Wire Retention Ring 3

PRP-909-6 "O" Ring 3

A-50-1 Rear Cone Q 1

A-186 Spacer, Rear Cone B 1

A-63-B or B-2063 Hub Retention Nut H 1

A-870 Puller Ring D 1

834-1 Guide Collar Unit L 1

B-352 Nut, Guide Collar A 1

PRP-909-13 "O" Ring, Nut Retention 1

A-847 Hub Nut Safety Pin E 1

838-29 CLAMP COUNTERWEIGHT

ASSEMBLY W 3

For L8433H-2 Blades)

C-3-3A Clamp AA-N 3

A-295 Linkscrew E 3

A-285 Staki Pin, Linkscrew D 3

NIS-15001-1 Zerk Fittings 6

833-4 Counte rwe i t Unit B 3

A-65 Counterweight Staking Pin A 3

Zerk Fittings 6
MS-15001-1
833-4 Counterweight Unit B 3

Counterweight Staking Pin A 3

A-65
A-2036-30 Socket Head Cap Screws, Ctwt. 6

Staking Pins, Sk. Hd. Cap Screw D 6

A.-285
Clamp Gaskets F 6
A -47 -1
A.-282 Socket crews

AN380-3-2 Cotter s.

A.-2017 C Bolts
A.N960-626 W ers

Elastic Nuts 6
A.N364-624

Page 1 of 2
Hartzell Propeller, Inc.

Parts List Model HC-D3X20-6L

June 21, 1962
Approved

Part No. Nomenclature I Letter Required

91-6L HYDRAULIC UNIT I D I 1

D-351-3 Jack Plate Assembly I J 1

Jack Plate B 1
B-356
Push Rods A-B 3
A-826-10
Rod E 1 3
A--114-F Staking Pins,
Forks I 3
A-821L-1
I Socket Set Screws, Fork I 1 3
1032x3/16
A.-827-7 Sleeves, Rod I R 1 3

I G 1 3
A-970-3 Spacers
Washers C 3
A-965
Flexlock Nuts 3
AN364-720
Cylinder Unit 1
#100
Cylinder N 1
C-77
Pin I 3
A-11-A
A-312 Nut 1 1 3

Piston P 1
D-58
PRP-902-72 "O" Ring, Piston Outer I I 1

PR P-902 -44 "0" Ring, Piston Inner I i 1

A-38A Bearing I D I 1

Gasket B 1
B-73
1 Cover Plate I B I 1
B-12-3
Screws 12
AN501A10-6
Washers 12
AN936A10
NIS-15001-1 Zerk Fittings 1 I 1

Wire B 1
A.-43
A-76 Stop, Lever I A I 1

I C I 1
A-41 Stop, Pitch
Screws 4
AN501A10-6
Washers 4
A.N936A.10

VALVE ASSEMBLY A 1
93-D
Valve Unit D 1
B-299
Valve Body G 1
B-301
1 A 1
A-302 I Rod
Staking, Pin, Rod D 1
A-285 1
PRP-902-10 1 "O" Ring I I 1
1
A-307 I Spool I E

A-303 1 Pin I B I 1

I A 1
A.-306-A I Spring
AN380-3-2 I Cotter Pins 1 1 2

I F 1
A-44 I Link
AN3 94 -2 1 I Clevis Pin I I 1

I 1 3
AN380-2-2 I Cotter Pins
Socket Head Cap Screws I 1 2
A-2038-6 1
A.-71-2 I Gasket I B I 1

Page 2 of 2
 SUPPLEMENT NO. 3
MANUAL 100D

October 17, 1969

Parts List for HC-n2X20-3 is attached herewith and is a part

of Manual 100D.
I~AA-DOil-3Ek AP~PROVED IJsaRTZELL PKOPELLEB, IIJC, Approved Octobet- 19, 1967
PTQUA,
Ssser~bZy
OPII6EWS’d: ny~
E)ROPELI;ER MODEL Davi.c;‘i;ir:-rmann
Jrawing
HC-D2X20-3 Vice Pres, G Gen,
D-330
N~unScr Rcquireci

HC-D2X20-3
C~ange
i
KU13 SPIDER UPaIT 1
I 840-62
Hub Spider i
E C-999-lL
2
E AI11~AI1 Bush~ngs, Lug
1
F hli5S Bushing, Shaft
Pilot TuE~es 2
M A-a5&L
1
D A- 16 5-3 1 Spacer Rtmg,

_KUB ASSOC~ED
I’O" Kings, Blade 2
PnP~5109´•´•8
2
Z A-971 Split Bearings, Blade
Wire Ringe, Beer~ng 2
A A-2027
Ball Spacers, Bearing 2
G A- 3’6,1
Cu.rde Rings, Bearin~ 2
C A-972
Wire Kings, Guide Rel;ention 2
A A-994
1
R A-186 Spacer, Rear eone
Rear Cone i
A-SO-i
Shaft Nut 1
A-63-B
RuZler King 1
C A1156
1
A-46 Snap King
1
C A-847 JSafety Pin, Shaft Nut:

AH 838-29 C~AMP COUNTERWELGI~T PLSS’Y 1 2

2
BQ C13-3A CLamp
Lir~kscrew 2
I A129~
2
D A-285 S~aking Pin, L~nkscrcw
Z
833-4 Counterweight Unit
Socket Head Cap Screws, Ctwt 4
F A-2036-30
4
D s’e A~285 Staking Pins, Sk,~d.Cap Sc,
2
B R-GS Staking Pin, Counterwe~ght
Zerk FittLngS 4
~iS1500111
4
F A-47-1 Clamp Gasket~
Socker Screws, Clamp 4
J A-282
Cotter Pins, Socket Screw
4
AN380-3-2
4
C A-2017 Clamp Bolts, 12 Po$nt
Washers 4
AN960-616
4
A12043 Clamp Nuts
4
No, 3 LuGricaps

CLh~iP PIUITS
i3alance We´•i6hts As Ncccdcd
E I ii-48
Weight As Needed
i-~501h10-( Screws, Balance
2
j A- 9 S-A IBlock8, Pitch Change
2
1
E’M-BO~-SEA AI~PROVED HARTZELI, INC. Approved October 19, 1967
FZQUA, CHIC
Assem~ly PARTS LIST BY
Drawi.ng PROPELLER MODEL Da; id Eieumann
D-330 HC-D2X20-3 Vice Pres,& 6cn. I~anay:er
Number

Change HC-D2X20-3
Letter Part Number Nomenclature
G 9r-3E EIYDIIAULIC UNIT I
~ioo Matched Piston Cylinder I
A D178 Piston 1
O C- 77 i Cylinder L
X A-11-A Guide Pins 3
A-312 Nuts, Guide Pin 3
rRP1902-72 "C" Ring, Piston 1
PRP1902-44 "O" Ring, Piston 1
C A-41 Stop, Valve Spoor I
A A17~ Stop, Valve Lever 1
AN501AIO-6 Screws, Slop 4
AW936A10 Washers 4
G A138-BG Thrust Bearing 1
B B-73 Gasket, Cover Plate I
C B-L2-3 Cover Plate 1
ANSO1A1OIG Screws, Cover Plate 12
AN336A10 Washers, Cover Plate 12
MS15001-1 Zerk Fitting 1
N B-209110 Jack Plate Unit 1
P B-87F Jack PLate 1
7: A197-3E Push Rods 2
L A-I1Lc-F Staking Pins, Push Rod. 2
K A-821L Forks, Push Rod 2
L A-114-A Staking Pins, Fork 2
B A-43 Wire Retention Ring, Rearing 1
A1181 Casket, Mounting 1.
A-2043 Elastic Nuts, Mounting 1 6

B I 93-D VALVE ASSEMBLY I

D B-299 Valve Unit 1
I B-301 Valve Body 1
PRP-902-10 "O" Ring 1
E A-307 Valve Spool I
A A1302 Guide Rod 1
D A-285 Staking Pin, Guide Rod Z
C A-303 Pin, Valve L~nk 1
AN380-312 Cotter Pin 2
A A-306-A Spring I
G A-44 Linlt, Valve I
P,M394-21 Clevis Pin, Link 1
AN38013-2 Cotter Pin
R I
~-71-2 Gasket, Valve
B Mounting 1
R~2038-6 Socket Head Cap Screws, Mtg,
 ?JO. 4
MANUAL 100D

October 30, 1975

ADDITION OF PROPELLER MODELS

HC-12V20-7D AND -8D

The HC-12V20-( propeller is identical to the HC-12,Y20-(

propeller except A-1496 pilot tubes are used instead of the ~-13SL
pilot tubes. The hub assembly is thereby changed from 830-8 to
840-127. The applicable blades must incorporate the "V" shank
retention.

Overhaul procedures for the HC-12V20-7D and -8D

propellers are
the same as for the HC-12X20-7D and -8D propellers.
 SUPPLEME~T NO. 5
31ANUAL 100D

June 16, 1976

ADDITION OF PROPELLER MODELS

HC-D2V20-7D AND -8D

Propeller models HC-D2V20-7D and -8D are identical to models

HC-D2)[20-7D and -8D respectively except that hub unit 830-61 is
replaced by 840-123.
 SUPPLE,MENT NO. 6
bLANUAL 100D

November 5, 1976

ADDITION OF PROPELLER MODEL

HC-D3V20-6L

Propeller model HC-D3V20-6L is identical to model HC-D3X20-6L

except that hub spider unit 840-65 is
replaced by 840-85.
 HARTZELZ, PROPELLER, INC,
PIQUA, OliIO

~tANDATORY "FAA NPPROVED" Amended August rl., i 1,

y
BULLETIN NO. 32) AD NOTE 64-28-1 March 9, 1955

SUBJECT: RepZaccment Of The Old ~-49-23 and -2C Hub Spider.

EPFECTIVZTY: propeller Models IIC-12X20-L, 2, 3, 5, 75 installed prirnarily

on Nauions and Seabees having C-49-2B and C-49-2C hub
spiders.
Serial Numbers affected range between 4220 and 5400,

CAUS]ES AND
EFFECTS: Recently a crack developed in a C-49-2B hub spider which
originated from a smal.L radii.zs machined at the rear where the
jack plate or spinner bulkhead engages, The location where
a crack might be! expected to
appear is shown on the sketch on
Bage. a,

RE9UIRED
ACTZ_ON: Replace the C-49-2B or C-49-2C hub spider with a C-L57 or
C1999 hub spider at next overhaul period; but not later than
500 hours time in service after last overhaul. Until this
is accomplished, visually inspect the hub spider within 10
hours of time in sezvice and at 25 hour intervals thereafter.

The C-49 hub spider can be identified by the fact that it

has provisions far a front: shnft cone 85 well as a rear cone,
The C-157 hub incorporates a sleeve bushing replacing the
front cone, The C-999 hub spider, which is of the latest
design, is similar to the C1157 except it has flanged blade
arms which retain split bearings.

Replacement of the hub spiders require new blade bearings

and associated parts,

Installation of the C-LS7 spider requires adding the letter

"C"
to the dash nuinber for propellers having dash numbers
1 to 8 inclusive, Example: HC-12X20-1A becomes -1AC,
Models -71\ and -7n will become -7C upon complying with this
bulletin,

Installation of the C-999 hub spider into the HC-12X20-3,

-7 or -8 results in EIC-n2X20-3, -7 or -8,

-----~_

Page 1 of: 3
 ~ar$%ell Propeller, Inc,
Piegeta, Ohio
M;andatory "FAA APPROVED" Amended Aug. 11, 1964
~_n-I2lctin No. 32,,pd Note 64-28-1~Cont’d_) March 9, 1955

SK~TCH:

CLclMP

~i Jil~kP/Ii77cE

NC/S

Page 2 of 3
 C~ Of C-157-j Hubs
o
Chara@e~ristfe Of ~-49-( Wubs 3Rlv
c\
E---------=i
~-a

~L?
L?5

efi
j
I
.L87 Ii. As SoS_id OnC-157-( Ht~zs

c o
~li

ii´•1 o: Ytjrr:
a r~
C;~E:
i re,

j fI
I/ ij U U O

i jr nIic~
77~
i
jiI
I
I
I c:
M

ri
ij
r
I n
i~e
R
W
iit
O I
d
r:C i
i,
Z;g
j j :187 C-49-Z3c_-2C
Ii. (As Shown Dash On
ii

of
i! Iiiihgl

II
i
’X:I I
i .@85 Ii. Or! C-49-1 1A -2 -21? Ku~s ii’nsv.
Dotted,)
I

’I Differenees Setween HC-1SX20

(3 aJ
c o

I I i f I IC-49-L, IA, 2,6: 2A Dott~d, Cesh, EL SOlid

a LirLCS
F: ~e
C-49-2B, -2C Dash iincs dL

=il C-157-( Solid Lices OnEy

~sl

kO C
i B~J ?art No. IIcw Shok´•n

k ´•re
C3~
riOkC
r( O ’re
Q) I ~-)U
Nt5tcif~l

Fe t;r Cre
rd rg 3
 PROP)ELLER, INC.
PXQUA, OHIO
Revised June 2, 19611
P)I~LEETIN NO. 82 "FAA AP_P_ROVEDIL_ April 27, 1962

"UBJECT: Failures In A-38 Ball BearinHUsed In HC-12X20-7, -8

ProEeller In Navion Beech 35, Bellance,
Stinson L-5 And 108 Aircraft

~ISCUSSION: During the past several years, there have been several
failures of the A-38 ball bearing used in the hydraulic
unit of the HC-r2X20-7 and -8 propellers, The immediate
causeof failure is believed to be fatigue failure of
the metal cage which separates the balls. This allows
the balls to jamb and freeze, An early landing is
made necessary as the pitch change mechanism deteriorates
rapidly,

Failures have been bearings which have

observed only in
the two halves of the cage riveted together, In fact, it
is believed that the failure starts with al rivet failure,
Some bearings in service do not have rivets, and there have
been no record of failure with these.

AC’IL‘ION: Inspect the A-38 bearing. This can be accomplished by the

following procedure: (See Sketch)

(a) Remove the propeller from the engine by unscrewin~

A-63B shaft nut and the hub including the
p~stonljack assembly.
(b) RenK~ve the piston-jack assembly from the hub assembly
by rotating the blades so that the guide rods can be
free from the guide lugs,
(c) Remove 8-109 jackplate from A-38 bearing, This can be
done in an arbor press by supporting C-112 piston on the
table and applying a force to the rear of the Jackplate
from the inside of A-38 bearing. Remove A-43 wire from early prop
(d) Remove 8-12 cover plate from 0-112 piston by removing
the ANS01AlO screws,

(e) inspect the A-38 bearing.

(E) If the A-38 bearing is to be replaced, remove it from
the 0-112 piston with the arbor press as noted in (c),

All A-38 bearings which have riveted cages replaced by must be

A-38 bearings which have crimped cages, or preferably with
bearings which have bakelite cages (A-38B), within the next
100 hours of operation, or not later than January i, 1966,

IME~ORTANT: The A-38R bearings with bakelite cages will taL

thrust in only
direction; hence, must be
one installed with
the side of the
bearing which is marked "Thrust Here" yrcssed
into the piston first, so that the wording "Thrust Here" is
hidden from view after it: is installed in the piston.

Page 1 of 2
 PropelBer, inc,
Revi~sed June f965
plq;aa,
Bulletin No, 82 "FAA APPKOVED" April 27, 1962

"CTfON: Reassemble propeller in reverse order of di~sassembly.

on t’ d)
Upon completion of the inspection and action, if necessary,
regarding replacement of the A-3e bearings having the
riveted cage; paint a white spot about 3/4 inch in diameter
on the front of the piston where it is visible,

The bearing should be greased at 100 hour ~n;ervals with

about one tablespoon full of grease only, DO NOT OVERGREASE.

C-NI-R

O-lrt

IJ-126__PLpT~ ,o(lTFR 01*pN(pR~

R-/13
638
~-43 RFTAINC4
c ir2

ANSOIAIO-6 JCRE~NS
8-it COYC~R

´•1 9~:
Br~ P´•ag
U?r
I pu391i~/
Tt;s
r;d3BNU´•T

B-/o3
JncY PLArr Y

8-87
P~5H
a-96 F’lnN

rr-9~ OCOCK

611 OR~IN

Pal;e 2 of 3_
02
 HARTZELL
I Revision 2
61-10-00
June 2001

HYDRO-SELECTIVE PROPELLER
OVERHAUL MANUAL

HC-D2V2013
H C- D3V20-6 L
HC-D2V20-7
HC-D2V2018
HC-D2MV2013
H C- D3 M V2 016 L
HC-D2M V2017
HC-D2M V2018
HC-D3MV20-8D

HartzellPropeller Inc.
One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.
Phone: 937.778.4200
Fax: 937.778.4365
(This page is intentionally blank.)

61 11 0100
 RECORD OF REVISIONS

100E
MFG REV
NO DESCRIPTION ISSUE DATE ATP REV DATEI INSERTED BY

1 See Highlights 4/1/00 7/10/00 ATP/DG

2 See Highlights 6/01 9/3/01 ATP/RCL

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

RECORD OF REVISIONS

This is a permanent historical record of revisions inserted into this manual.

Revision I Issue Date Revision Issue Date

100E 3/98 4/06/98 ATP/Q4

1 00 10/2 ATP

2 6/01 9/3/01 ATP/RCL

Page
RECORD OF REVISIONS 61-10-00 1Mar/98
 PROPELLER M*NUAL
HARTZ a LL

RECORD OF REVISIONS

This is a permanent historical record of revisions inserted into this manual.

Revision Issue Date Revision I Issue Date

ber Date I Inserted I Inserted By I I Number I Date

Page
RECORD OF REVISIONS 61’1 0’00 2Mar/98
 RECORD OF TEMPORARY REVISIONS

L$-~ 100E
DATE REV REMOVE
TEMP ATP REV INSERT
ISSUE DATE DATE BY REMOVED INCOR BY
REV NO DESCRIPTION
9/00 3/1 9/01 ATP/BH 9/3/01 2 ATP/RCL
001
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

RECORD OF TEMPORARY REVISIONS TO THIS MANUAL

this page to show all Temporary Revisions inserted into this manual.
Update

Date Date

Inserted Inserted Removed Removed

TRNumber Issuel)ate

001 9/00/00 3/19/01 ATP~BH

Page 1

RECORO OF TEMPORPIRY REVIS~ONS

61 -1 0-00 Mar/98
 PROPELLER
HA RTZ E LL MA:N~ToEENANCE
E001LAUNAM

RECORD OF TEMPORARY REVISIONS TO THIS MANUAL

Update this page to show all Temporary Revisions inserted into this manual.

Date Date
TRNumber IssueDate Inserted Inserted By I Removed Removed

RECORD OF TEMPORARY REVISIONS 61’1 0’00 Mar/98Page 2

HARTZELL PROPELLER INC. HARTZ E LL
One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.
Telephone: 937.778.4200
Fax: 937.778.4365
MANUAL REVISION TRANSMITTAL
Manual 1 OOE
Hydro-Selective Propeller Overhaul Manual
for models HC-D2V20-3, HC-D3V20-6L,
HC-D2V20-7, HC-D2MV2018, HC-D2MV20-3, HC-D3MV20-6L,
HCID2MV20-7, HC-D2MV20-8 and HC-D3MV20-8D

Manual 100E. Rev. 2 Dated June. 2001

Attached is a copy of Revision #2 to Hartzell

Manual 100E.

Page Control Chart for Revision #2:

Remove Insert
Page No. Page No.

COVER/INSIDE COVER COVEWINSIDE COVER

REVISION HIGHLIGHTS REVISION HIGHLIGHTS

pages 1 and 2 pages 1 and 2

SERVICE DOCUMENT LIST SERVICE DOCUMENT LIST

pages 1 and 2 pages 1 and 2

LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES

pages 1 and 2 pages 1 and 2

TABLE OF CONTENTS TABLE OF CONTENTS

pages 5 through 8 pages 5 through 8

INTRODUCTION INTRODUCTION
pages 1 through 14
pages 1 through 10

DISASSEMBLY DISASSEMBLY

pages 309 through 312 pages 309 through 312

CHECK CHECK

pages 501 and 502 pages 501 and 502

pages 509 and 510 pages 509 and 510

DISASSEMBLY DISASSEMBLY
701 and 702 pages 701 and 702
pages
724 pages 711 through 724
pages 711 through
727 and 728 pages 727 and 728
pages
pages 735 through 740 pages 735 through 740

743 and 744 pages 743 and 743.1

pages
pages 743.2 and 744
pages 749 and 750 pages 749 and 750
pages 767 through 774
pages 767 through 772
ILLUSTRATED PARTS LIST ILLUSTRATED PARTS LIST
1012 pages 1009 through 1012
pages 1009 through
1017 through 1020 pages 1017 through 1020
pages
1025 through 1030 pages 1025 through 1030
pages
1038 pages 1035 through 1038
pages 1035 through
1046 pages 1043 through 1046
pages 1043 through
1058 pages 1055 through 1058
pages 1055 through
1067 through 1070 pages 1067 through 1070
pages
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

REVISION 2 HIGHLIGHTS

Revised the Cover, Highlights, List of Effective Pages, and Service Document List to
reflect the manual revision.

Revised the Introduction chapter to reflect current information.

Revised the Disassembly chapter.

Removed the clamp disassembly instructions and referred the reader to the
Hartzell Standard Practices Manual 202A (61-01-02) for the instructions.

Removed the bushing removal instructions and referred the reader to the
Hartzell Standard Practices Manual 202A (61-01-02) for the instructions.

Revised/corrected the instructions in the Disassembly chapter.

Added dimensional inspection criteria for balance weights in the Check chapter.
Revised the Assembly chapter.
Added a provision to install a reversed bolt in the blade clamp.
Added the instructions for the application of sealant to the blade clamp.
Revised/corrected the instructions in the Disassembly chapter.
Revised parts listings, as necessary, in the Illustrated Parts List chapter.

REVISION HIGnLIOHTS 61’10-00 Rev.

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

REVISIONS HIGHLIGHTS

1. Introduction

A. General

This is a list of current revisions that have been issued against this manual. Please
compare to RECORD OF REVISIONS page to ensure that all revisions have been
added to the manual.

B. Components
(1) Revision No. indicates the revisions incorporated in this manual.
(2) Issue Date is the date of revision.

(3) Comments indicates the level of the revision.

(a) New Issue is a new manual distribution. The manual is distributed in its
entirety. All the revision dates are the same and no change bars are

used.

(b) Reissue is a revision to existing manual that includes major content

an

and/or major format changes. The manual is distributed in its entirety. All
the revision dates are the same and no change bars are used.

(c) Major Revision is a revision to

existing manual that includes major
an

content or minor format

changes over a large portion of the manual. The
manual is distributed in its entirety. All the revision dates are the same,
but change bars are used to indicate the changes incorporated in the
latest revision ofthe manual.

(d) Minor Revision is a revision to

existing manual that includes minor
an

content changes to the manual. Only the revised pages of the manual are
distributed. Each page retains the date and the change bars associated
with the last revision to that page.

Revision No. Issue Date Comments

Original, Manual 1 OOE Mar/98 New

Revision 1 Apr/GO Minor Revision
I Revision 2 Jun/Gl Minor Revision

REVISION HIOnLIOnTS 61’10’00 Rev.

 PROPELLER MAINTENANCE MANUAL
#A,RT Z E L L 100E

LIST OF EFFECTIVE PAGES

Chapter Page Date Chapter Page Date

Cover/inside Cover Jun/Gl Repair 601-603 Mar/98

Revision Highlights 1-2 Jun/Ol Repair 604-606 Apr/GO

Record of Revisions 1-2 Mar/98 I I IAssembly 701-702 Jun/Gl

Record of Temporary I 1Assembly 703 Mar/98

Revisions 1-2 Mar/98 I IAssembly 704-709 Apr/GO
I Service DocumentList 1-2 Jun/Ol
I IAssembly 710 Mar/98
Airworthiness Limitations 1-2 Mar/98 I I IAssermbly 711 Apr/GO
I Listof Effective Pages 1-2 Jun/Ol I I IAssembly 712-713 Jun/Gl
Table of Contents 1 Mar/98 I I IAssembly 714 Apr/GO
Table of Contents 24 Apr/GO I I IAssemblv 715 Jun/Gl
Table of Contents 5 Jun/Ol I IAssemblv 716 Mar/98
Table of Contents 6 Apr/GO I IAssermbly 717 Apr/GO
Table of Contents 7 Jun/Gl I I IAssemblv 71&719 Jun/Gl
Table of Contents 8-10 Apr/GO I I lAssemblv 720-721 Apr/GO
Introduction 1-2 Jun/Ol IIIAssemblv 722-723 Jun/Gl
Introduction 3 Apr/GO Ill~tssembly 724-725 Apr/GO
Introduction 4-14 Jun/Ol IIIAssemblv 726 Mar/98

Description and Operation 1-7 Apr/GO I I IAssembly 727 Apr/GO

Description and Operation 8 Mar/98 I I IAssemblv 728 Jun/Gl
Description and Operation 9-10 Apr/GO I I IAssembly 729-734 Apr/GO
Testing and Fault Isolation 101-102 Mar/98 I I 18ssemblv 735 Jun/Gl

Testing and Fault Isolation 103-105 Apr/GO I I 18ssembly 736-737 Apr/GO

Testing and Fault Isolation 106-108 Mar/98 I I 18ssemblv 738 Jun/Gt
Automatic Test I 18ssembly 739 Apr/GO
Requirements 201-202 Mar/98
740 Jun/Ol
Disassembly 301-308 Apr/GO IIIAssembly 741-743 Apr/GO
Disassembly 309-311 Jun/Gl
743.1-743.2 Jun/Gl
Disassembly 312 Mar/98
744-749 Apr/GO
Disassembly 313-314 Apr/GO IIIAssemblv 750 Jun/Ol
Disassembly 315 Mar/98
751-766 Apr/GO
Disassembly 316-318 Apr/GO IIIAssemblv 767-774 Jun/Gl
Cleaning 401-404 Mar/98
Fits and Clearances 801-806 Mar/98
Check 501-502 Jun/Ol
Special Tools, Fixtures
Check 503-505 Apr/GO ,,d Equipment 901-904 Mar/98
Check 506 Mar/98 I Illlustrated Parts List 1001-1008 Apr/GO
Check 507 Apr/GO I I Illlustrated Parts List 1009 Jun/Ol
Check 508 Mar/98 I I Illlustrated Parts List 1010 Apr/GO
Check 509 Apr/GO I I Illlustrated PartsList 1011 Jun/Ol
Check 510 Jun/Ol I I Illlustrated PartsList 1012-1016 Apr/GO

1
LIST OF EFFECTIVE PAGES 61-10-00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL iooE

LIST OF EFFECTIVE FAG ES

Chapter Page Date Chapter Page Date

Illustrated Parts List 1017 Jun/Ol

Illustrated Parts List 1018 Apr/GO

Illustrated Parts List 1019 Jun/Ol

Illustrated Parts List 1020-1024 Apr/GO

Illustrated Parts List 1025 Jun/Ol

Illustrated Parts List 1026-1028 Apr/GO

Illustrated Parts List 1027 Jun/Gl

Illustrated Parts List 1028 Apr/GO

Illustrated Parts List 1029 Jun/Gl

Illustrated Parts List 1030-1036 Apr/GO

lilustrated Parts List 1035 Jun/Ol

Illustrated Parts List 1036 Apr/GO

Illustrated Parts List 1037-1038 Jun/Gl

Illustrated Parts List 1039-1042 Apr/GO

Illustrated Parts List 1043 Jun/Gl

Illustrated Parts List 1044 Apr/GO

Illustrated Parts List 1045 Jun/Gl

Illustrated Parts List 1046-1054 Apr/GO

Illustrated Parts List 1055 Jun/Ol

Illustrated Parts List 1056 Apr/GO

Illustrated Parts List 1057 Jun/Gl

Illustrated Parts List 1058-1068 Apr/GO

Illustrated Parts List 1067 Jun/Ol

Illustrated Parts List 1068 Apr/GO

Illustrated Parts List 1069 Jun/Gl

Illustrated Parts List 1070 Apr/GO

2
LIST OF EFFECTIVE PPIOES 61 -1 0-00 Rev. 1 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1000

SERVICE DOCUMENT LIST

Sewice Dec. Incorporation Sewice Dec. Incorporation

No. Rev./Date No. Rev./Date

SL 61T Mar/98

SL 177 Mar/98

I HC-SL-61-206
HC-SL-61-211
Jun/Ol
Jun/Ol

SERVICE DOCUMENT LIST 61-10-00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

SERVICE DOCUMENT LIST

Service Dec. Incorporation Service Dec. Incorporation

No. Rev./Date No. Rev./Date

I SERVICE DOCUMERTLIST 61 -10-00 RevP~iPage

2
 PROPELLER MAINTENANCE MANUAL
H~RTZ ELL 100E

TABLE OF CONTENTS

REVISION HIGHLIGHTS 1

RECORD OF REVISIONS 1

RECORD OF TEMPORARY REVISIONS 1

SERVICE DOCUMENTS LIST

AIR WORTHINESS LIMITATIONS 1

LIST OF EFFECTIVE PAGES 1

TABLE OF CONTENTS t

INTRODUCTION 1

1. Statement of Purpose
Publications 4
2. Required
A. Hartzell Publications 4

B. References to Hartzell Publications 4

C. Vendor Publications 4

3. Personnel Requirements 5

4. Calendar Limits and Long Term Storage 5

A. Calendar Limits 5

B. Term Storage 5
Long
Life and Service 6
5. Component
A. Overhaul 6

6
B. Damage
C. 6
Repair. . . . . . . . . . . . . . . . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•
7
D. Component Life
6. Definitions 8

7. Abbreviations 10

OFCONTENTS 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 100E

DESCRIPTION AND OPERATION 1

1 Description of Propeller and Systems 3

A. General Description (Construction) 3

B. General Description (Forces) 4

C. General Description (Control) 5

D. Detail Propeller Description 5

(1) Propeller Model HC-D2(V,MV)20-3( 5

(2) Propeller Model HC-D3(V,MV)20-6( 5

(3) Propeller Model HC-D(2,3)(V,MV)20-7( -8( 6

2. Model Designation System 7

A. Propeller Model Designation 7

B. Blade Shank Designation 7

C. Conversion From V Shank to MV Shank 7

TESTING AND FAULT ISOLATION 101

1. Trouble-Shooting Guide 103

A. Pitch changes to high pitch, but will not change to low pitch properly. 103

B. Pitch changes to low pitch, but will not change to high pitch properly. 103

C. Pitch does not change properly toward both high and low pitch. 1 03

D. Friction 104

E. Blade Slippage in Blade Clamp. 104

F Oil Leakage 105

G. Grease Leakage, Blade Split Bearing 105

I-i. Grease Leakage, Piston to Jack Plate Bearing 105

I. Blades Not Tracking 107

J. End-Play Movement of Blades 107

K. In-and-Out Movement of Blades. 107

L. Fore-and-Aft Movement of Blades. 107

M. Radial Movement of Blades 107

N. Excessive Propeller Vibration 108

61-10-00
 PROPELLER MAINTENANCE MANUAL
C(ARTZELL 100E

AUTOMATIC TEST REQUIREMENTS 201

DISASSEMBLY 301

1. Removal of the Propeller Assembly from the Engine 303

A. General 303

303
B. Spinner Removal
303
C. Propeller Removal
D. HC-D2(V,MV)20-3 PROPELLER MODELS ONLY 304

E. HC-D3(V,MV)20-6L PROPELLER MODELS ONLY 306

HC-D(2,3)(V,MV)20-7 and -8( PROPELLER MODELS ONLY 308

I F.
309
2. Marking Before Disassembly
309
3. Propeller Disassembly
309
A. Preparation for Disassembly
309
B. Clamp and Counterieight Disassembly
C. Blade and Mounting Parts Disassembly 313

D. Hub Disassembly 314

E. Jack Plate and Hydraulic Piston Disassembly 316

F. B-93-D ValveDisassembly
MV)20-3 and HC-D3(V,MV)20-6L Propellers 317
HC-D2(V,
G. B-93-A, -B, -C Valve Disassembly
HC-D2(V,MV)20-7 and -8 Propellers 317

H. B-93-AG, -BG, -CG Valve Disassembly

HC-D2(V,MV)20-7 and -8 Propellers 317

I B-93-E Valve
HC-D3MV20-8D
Disassembly
Propellers 317

CLEANING 401

1. General Procedures for Cleaning Parts 403

Procedures 403
2. Specific Cleaning
CHECK 501

503
1. Inspection Interval Requirements.......
503
2. Mandatory Inspection Requirements
A. Thrust Bearing 503

503
B. Rubber Diaphragm

TABLEOFCONTENTS 61110100 Rev.lPAap~1)030

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

1 3. Inspection Requirements 503

A. Visual Inspection 503

B. Penetrant Inspection 503

C. Magnetic Particle Inspection 503

D. Dimensional Inspection 504

4. Replacement Requirements 504

5. Repair 504

6. Hub Unit Inspection 504

7. Blade Clamp Inspection 504

3. Blade Inspection 504

9. Blade Split Bearing Inspection 507

10. Bearing Guide Ring 507

11. Guide Collar Inspection 509

12. Spacer 510

13. A-38B(G) Thrust Bearing 510

REPAIR 601

1. General 603

A. Shot Peening 603

B. Minor Damage to Metal Parts 603

2. Blade Repair 603

3. Hub Unit Repair 603

4. Blade Clamp Repair 603

5. Spinner Assembly Repair 604

6. Guide Collar Repair 604

7. Hub Lug Repair 604

ASSEMBLY PROCEDURES 701

1. General 703

2. Specific Assembly and Installation Procedures 705

3. Blade and Mounting Parts Assembly 705

4. Installation of Blades and Clamps 711

61-10-00
 PROPELLER MAINTENANCE MANUAL
RTZ c LL 1 OOE

5. Setting Blade Pitch 715

A. HC-D2V20-3 715

B. HC-D2MV20-3

C. HC-D3V20-6L 725

D. HC-D3MV20-6L

E. HC-D2(V, MV)20-7 and -8( 737

F. HC-D3MV20-8D 740

All Models 743.2

I G. Sealant CM93 Application
6. Jack Plate and Hydraulic Piston Assembly 744

A. HC-D2(V, MV)20-3 and HC-D3(V, MV)20-6L

(Hydraulic Unit Assemblies 91-E and 91-6L) 744

B. HC-D(2, 3)(V, MV)20-7 and -8(

(Hydraulic Unit Assemblies 91-7DS, 91-8DS, and 91-8DT) 745

7. Valve Reassembly 746

A. Reassembly of B-93-D Valve 746

B. Reassembly of B-93-A, -B, -C Valve 746

C. Reassembly of B-93-AG, -BG, -CG Valve 746

D. Reassembly of B-93-E Valve 746

8. Installing the Propeller Assembly on the Aircraft 747

A. Model HC-D2V20-3 747

B. Model HC-D2MV20-3 751

C. Model HC-D3V20-6L 757

D Model HC-D3MV20-6L 761

E. Models HC-D(2, 3)(V, MV)20-7 and -8( 767

F. Propeller Installation Troubleshooting

HC-D2(V, MV)20-3 and HC-D3(V, MV)20-6L 771

FITS AND CLEARANCES 801

1. Torque Values

TABLEOFCONTENTS 61-10’00
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 100E

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT 901

ILLUSTRATED PARTS LIST 1001

1. Introduction 1003

A. General 1003

B. Using the Illustrated Parts List 1003

2. The Illustrated Parts List

A. Detailed Parts List 1004

B. Revisions 1006

C. Vendors 1007

Illustrated Parts List for HC-D2V20-3 1009

Illustrated Parts List for HC-D2MV20-3 1017

Ilustrated Parts List for HC-D3V20-6L 1025

Illustrated Parts List for HC-D3MV20-6L 1033

Illustrated Parts List for HC-D2V20-7, 8 1043

Illustrated Parts List for HC-D2MV20-7, 8 1055

Illustrated Parts List for HC-D3MV20-8D 1067

6
TABLE OF CONTENTS 61 -1 0-00 Rev. 1 Ap~OOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

LISTOF FIGURES

Model Designation System Figure 1 ..........................9

Checking Blade Movement Figure 101 106

Abnormal Vibration Figure 102 108

Removing Bearing Retention Ring Figure 301 312

Blade Split Bearing Figure 501 506

Guide Collar Figure 502

Spider Hub Onto Rotatable Fixture Figure 701 704

Hub Spider Arm Bliild-Up Figure 702 706

Blade and Flange Mounting Parts Figure 703 708

CM93 Sealant Application Figure 704 710

Checking Blade Height Figure 705 714

Setup Spacer for HC-D2 (V,MV)20-7 Figure 706 71 5

Using Padded Blade Bar to Check for Blade Slippage Figure 707 716

Reverse Stop Travel Length Figure 708 720

I Puller Ring Position Figure 708.1 723

Identification of B-109-9( )Jack Plate Figure 709 726

Reverse Stop Travel Length and Reverse Stop Thickness Figure 710 730

Identification of B-109-9( )Jack Plate Figure 711 736

Setup Spacer for HC-D2(V,MV)20-7 and -8 Figure 712 737

Setup Spacer for HC-D3MV20-8D Figure 713 740

Temporary Two-Piece Blade Spacer for HC-D3MV20-8D .......Figure 714 741

I Sealant CM93 Application Figure 714.1 743.1

Determining Torque Value of a Standard Torque Wrench

with Adaptor Figure 801 803

CONTENTS 61’10’00
 PROPELLER MAINTENANCE MANUAL
)1649 RTZ I- LL 1 OOE

LISTOF FIGURES CONT’D

HC-D2V20-3
Propeller Assembly Figure 1001
Clamp Assembly Figure 1002 1010
91-3E Hydraulic Unit Figure 1003.....,,,. 1012
93-D Valve Assembly Figure 1004............... 1014

HC-D2MV20-3
Propeller Assembly Figure 1 005
Clamp Assembly Figure 1006 1018
91-3E Hydraulic Unit Figure 1007............... 1020
93-D Valve Assembly Figure 1008.....,.,.,.. 1022

HC-D3V20-6L
Propeller Assembly Figure 1009 1024
Clamp Assembly Figure 1010 1026
91-6L Hydraulic Unit Figure 1011 1028
93-D Valve Assembly Figure 1012............... 1030

HC-D3MV20-6L
Propeller Assembly Figure 1013 1032
Clamp Assembly Figure 1014............... 1034
91-6L Hydraulic Unit Figure 1015............... 1036
93-D Valve Assembly Figure 1016............... 1040

HC-D2V20-7, 8
Propeller Assembly Figure 1 01 7 1042
Clamp Assembly Figure 1018 1044
91-7DS,-8DS Hydraulic Unit Figure 1019.....,,,, 1046
93-A,-B,-C Valve Assembly Figure 1020.....,.,,., 1050
93-AG,-BG,-CG Valve Assembly Figure 1021 1052

HC-D2MV20-7, 8
Propeller Assembly Figure 1022 1054
Clamp Assembly Figure 1023 1056
91-7DS,-8DS Hydraulic Unit Figure 1024.....,,,, 1058
93-A,-B,-C Valve Assembly Figure 1025 1062
93-AG,-BG,-CG Valve Assembly Figure 1026.....,,,, 1064

HC-D3MV20-8D
Propeller Assembly Figure 1027
Clamp Assembly Figure 1028 1068
91-8DT Hydraulic Unit Figure 1029............... 1070
93-E Valve Assembly Figure 1030............... 1072

61-10-00
 PROPELLER MAINTENANCE MANUAL
)IIA,RTZ E LL 100E

LIST OF TABLES

Component Inspection Criteria Table 501 507

Torque Values Table 801

Blade Tolerances Table 802......,

9
TABLE OF CONTENTS 61’1 0-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HP~ RTZ c LL 1 OOE

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I TABLE OF CONTENTS 61 -1 0-00 Rev. 1 Apr/GOPage 10

 PROPELLER MAINTENANCE MANUAL
HA, RTZ ELL 100E

AIRWORTHINESS LIMITATIONS

The Airworthiness Limitations section is FAA approved and specifies maintenance required
under 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program
has been FAA approved.

FAA APPROVED

date:
FEB2611B
by:
r~ Royace Prather
Manager, Chicago Aircraft Certification Office,
ACE-1 15C
Federal Aviation Administration

Log of Revisions to Airworthiness Limitations

Rev. No. Description of Revision Rev. No. Description of Revision

AIRWORTHINESS LIMTTATIONS 61-1 0-00

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

AIRWORTHINESS LIMITATIONS

A. The FAA establishes specific life limits for certain component parts as well as the
entire propeller. Such limits require replacement of the identified parts after a
specified number of hours of use.

B. Life Limits

Propeller models affected by this manual currently do not have any life limited parts.

FAA APPROVED
FEB 261998
by: date:
-dC, Royace Prather
Manager, Chicago Aircraft Certification Office,
ACE-1 15C
Federal Aviation Administration

Page
AIRWORTHINESS UNIITATIOHS S1’1 0’00 2Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CONTENTS

1. Statement of Purpose
4
2. Required Publications
A. Hartzell Publications 4

B. References to Hartzell Publications 4

C. Vendor Publications 4

5
3. Personnel Requirements
5
4. Calendar Limits and Long Term Storage
A. Calendar Limits 5

6
B. Long Term Storage
5. Component LifeandService ........................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•7

A. Ovemaul 7

B. 7
Damage
7
C. Repair
9
D. Component Life
6. Definitions 10

7. Abbreviations 13

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 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 100E

(This page is Intentionally blank.)

I INTRODUCTION 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

1. Statement of Purpose

A. This manual provides overhaul procedures for two- and three-bladed steel hub
Hyd re-Selective propel I e rs man ufactu red by Hartzell P ropell e r I nc.
B. Contact the Product SupportDepartment of Hartzell Propeller Inc. concerning any
maintenance problems or to request information not covered in this publication.

Hartzell Product Support may be reached during business hours (8:00 a.m.

through 5:00 p.m., United States Eastern Time) at (937) 778-4379.

After business hours, you may leave a message on our 24 hour product support
line at (937) 778-4376. A technical representative will contact you during normal
business hours. Urgent AOG support is also available 24 hours per day, seven
days per week via this message service.

Additional information is available on our website at www. hartzellDroP.com.

NOTE: When calling from outside the United States, dial (001) before dialing the
above telephone numbers.

C. This manual is to be used in propeller repair stations by personnel who are trained
and experienced with Hartzell products. This manual does not provide complete
i nformation fo r an i nexperienced tech n ician to attempt propel ler ove rhau I without
supewision.
D. This manual is intended to be the primary source of overhaul information for
two- and th ree-bladed steel hub Hydro-Selective propellers. This manual no longer
contains blade overhaul procedures. Refer to the appropriate Hartzell manual for
blade overhaul. In addition to this manual, the reader must consult active Service
Bulletins, Service Letters, Service Advisories, and Service Instructions for
information concerning two- and three-bladed steel hub Hydro-Selective propellers,
or their related components, that may not yet have been incorporated into the latest

revision of this manual.

E. This manual makes reference to other Hartzell manuals that provide important
details for procedures such as anodizing, penetrant inspection, and overhaul
procedures for steel hubs.
F. Where possible, this manual is written in the format specified by ATA Specification
No. 100.

61-10108
 PROPELLER MAINTENANCE MANUAL
~IA,RTZ ELL 100E

2. Reauired Publications

A. Hartzell Publications

(1) In addition to this manual, one or more of the following publications are

required for information regarding specific recommendations and

procedures to maintain propeller assemblies.

Manual No. ATA No. Title

Manual 126 61-00-26 Set of Active SE, SA, SL, SI

Manaul 127 61-16-27 Spinner Assembly Maintenance Guide

Manual 133 61-13-33 Aluminum Blade Overhaul Manual

Manual 165 61-00-65 Illustrated Tool and Equipment Manual

Manual 202 61-01-02 Standard Practices Manual

Manual 159 61-02-59 Hartzell Propeller Inc. Application Guide

(2) For Hartzell service literature and revisions, contact:

Hartzell Propeller Inc. Telephone: 937.778.4200

Attn: Service Documents Secretary Fax: 937.778.4365
One Propeller Place
Piqua, Ohio 45356-2634 U.S.A

I Selected information is also available

www hartzellr>ro~. com.
on Hartzell Propeller’s website at

B. References to Hartzell Publications

(1) Item references th roughout the text i n this manual refer to item numbers in the
Illustrated Parts ListChapter. The item numbers appear in parentheses
directly following the part name. Only the item base number will appear in the
text of the manual. Item base numbers and the alpha variants of the base
numbers will appear in the illustrated parts list. There are two reasons for the
use of alpha variants:

(a) A part may be superseded, replaced, or obsoleted by another part. For

example, the self lockingnut (A-2043) that is item 20 was superseded by

the self
locking nut (A-2043-1) that is item 20A.
(b) An Illustrated Parts List may contain multiple configurations. Effectivity
codes are used to distinguish different part numbers within the same list.
For example, configuration may use a propeller mounting bolt (B-
one

3339-1 that is item 30, yet another configuration uses a propeller

mounting bolt (B-3347) that is item 30A. Effectivity codes are very
important in the determination of parts in a given configuration.

INTRODVCTION 61’10’00 Rev.8q~fiieO;l

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

For further
1 (2) Special tooling may be required for procedures in this manual.
Illustrated Tool
tooling information, refer to Hartzell Manual 165A (61-00-65),
the
and Equipment Manual. The reference numbers for tooling appear with
For
prefix "TE" directly following the tool name to which they apply.
example, a template that is reference number 133 will appear as: template
TE133.
materials.
(3) Certain instructions throughout this manual refer to consumable
Specific approved materials are listed in Hartzell Manual 202A (61-01-02),
Standard Practices Manual, Table 801. The reference numbers for

consumable materials appear with the prefix "CM" directly following the
material to which they apply. For example, an approved adhesive that is
reference number 16 will appear as: adhesive CM16. Only those items

specified may be used.

C. Vendor Publications

None.

3. Personnel Reauirements
have
Personnel inspecting, repairing, and overhauling steel hub propellers must
of propeller parts require a
adequate training and experience. Inspection and repair
and supervisory
high degree of skill. Therefore, personnel with inspection
Certificate and a
responsibility are expected to have an FAA Propeller Repairman’s
minimum of 18 months practical experience with Hartzell steel hub propeller
is strongly
overhaul. Participation in Hartzell training classes and propeller seminars
recommended.

4. Calendar Limits and Long Term Storage

A. Calendar Limits
create a need
The effects of exposure to the environment over a period of time
for overhaul regardless of flight time. Therefore, a calendar limit
propeller
between overhauls is specified in Service Letter 61( and in the propeller
owner’s manual. Experience has shown that special care, such as keeping
an

limit.
aircraft hangared, is not sufficient to allow extension of the calendar

NOTE 1: Start date for calendar limit is when the propeller is first installed on
removal
an engine. Calendar limit is not interrupted by subsequent

and/or storage.

NOTE 2: Start date for calendar limit should not be confused with warranty
the date of
start date (which, with certain exceptions, is normally
sale to the first retail customer).

,,,,,,,o,,, 61 -1 0-00
 PROPELLER MAINTENANCE
HA RTZ E LL E001LAUNAM

B. Long Term Storage

(1) Propellers that have been in storage have an additional inspection
requirement before installation. Refer to Hartzell Standard Practices Manual
202A (61-01-02), Chapter 700, Packaging and Storage.

(2) Additional inspection requirements for propellers with 0 hours since new or
overhaul:

(a) Ifpropeller has been in storage for two years or less, a visual
inspection is required before installation.
(b) Ifpropeller has been in storage for more than two years, it must be
disassembled and inspected for internal corrosion, and seals and
lubricants must be replaced before installation.

I INT.~.ucno, 61-10-00 Page 6

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 100E

5. ComPonent Life and Service

A. Overhaul

(1) Overhaul is theperiodic disassembly, cleaning, inspecting, repairing as

with approved
necessary, reassembling, and testing in accordance
standards and technical data approved by the administrator.

(2) The overhaul interval is based on (operating time) or on

hours of service
calendar time. At such specified periods, the propeller hub assembly and
the blade assemblies should be completely disassembled and inspected for
cracks, wear, corrosion, and other unusual or abnormal conditions. As

specified, certain parts should be repaired, and certain other parts should
be replaced.

(3) Overhaul is to be completed in accordance with the latest revision of the

applicable component maintenance manual and other publications

applicable to, or referenced in, the component maintenance manual.
B. Damage
(1) Airworthy Damage
Airworthy damage is damage that does not affect the safety or flight
characteristics of the propeller system. The maximum limits of airworthy
damage are specified in the "Check" section. Although a blade may
continue in service with airworthy damage, this type of damage should be
repaired at the earliest practical time to prevent further damage to the
system
(2) Unairworthy Damage
Unairworthy damage is damage that exceeds the maximum limits of
airworthy damage. Unairworthy damage can affect the safety or flight
characteristics of the propeller system. This type of damage must be
repaired before the next flight. Exceptions to this policy may be possible
but require written authorization from Hartzell Propeller Inc.

C. Repair
(1) Minor Repair
is that which may be done safely in the field by a certified
Minor repair
aircraft mechanic.

Refer to Hartzell Manual 133C (61-13-33) for the repair criteria for aluminum
blades.

NOTE: Removing significant amounts of metal from an aluminum blade

The propeller
may render it below minimum width orthickness.
needs to be inspected by an approved propeller repair station to
determine whether it is below published minimums.

I ,,,,,,,,o, 61-10-00
 PROPELLER MP~NUAL
HARTZELL

(2) Major Repair

(a) Major repair is correction of damage that cannot be done by elementary
operations.
(b) Major repair work must be accepted by an FAA certified individual,
preferably one that holds a Factory Training Certificate from Hartzell
Propeller. The servicing facility must meet facility, tooling, and personnel
requirements and is required to participate in Hartzell Sample Programs
as defined in the Hartzell Standard Practices Manual 202A (61-01-02).

I 61-10-00 Rev
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

D. Component Life

NOTE: Certain components, or in some cases an entire propeller, may be life

limited. It is a regulatory requirement that a record of the time since
new be maintained for all life limited parts.

(1) Component life is expressed in terms of hours of service ~Time Since New,
TSN) and in terms of hours of service since overhaul (Time Since Overhaul,
TSO

NOTE: TSNTTSO is considered as the time accumulated between rotation and

landing (i.e. flight time).
(2) Both references are necessary in defining the life of the component. Some
parts are "life limited," which means that they must be replaced after a
specified period of use (TSN).
(3) When a component assembly undergoes an overhaul, the TSO is
or

returned to zero hours. Time Since New (TSN) can never be returned to

zero.

NOTE: Repair without overhaul does not affect TSO or TSN.

(4) Time Since New (TSN) records must be maintained in the propeller
logbook along with Time Since Overhaul (TSO).
Blades and hubs sometimes replaced while in service or at overhaul.
(5) are

Maintaining separate TSN and TSO histories for a replacement hub or

blade is required. Other propeller components do not require time tracking
unless specifically noted in Hartzell service publications.

(a) Hub replacement

1 If the hub isreplaced, the replacement hub serial number must be
recorded (the entry signed and dated) in the propeller logbook. The
propeller will assume the serial number of the replacement hub.

NOTE: Propeller assembly serial numbers are impression stamped

on the hub. Refer to the Parts Identification and Marking

chapter of Hartzell Standard Practices Manual 202A

(61 -01 -02) for stamping information.
2 The TSO and TSN of the replacement hub must be recorded and
maintained in the propeller logbook. The TSN and TSO of the
remaining propeller components are not affected by the hub
replacement and must be maintained separately.

I INTRODUCTION 61-10-00 Rev

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

6. Definitions

Term Definition

Annealed softening of material caused by overexposure to heat

Blade Station refers to a location on an individual blade for blade inspection

purposes. It is a measurement from the blade "zero" station to
a location on a blade, used to apply blade specification data in

blade overhaul manuals (Note: do not confuse blade station

with reference blade radius; they may not originate at the
same location.)

Brinelling ...........................a depression caused by failure of the material in

compression

Corrosion gradual wearing away or deterioration caused by chemical

action

Crack irregularly shaped separation within a material, usually

visibleas a narrow opening at the surface

Depression ....surface area where the material has been compressed but
not removed

Distortion alteration of the original shape or size of a component

Erosion .............................gradual wearing away or deterioration caused by action of

the elements

Exposure leaving material open to action of the elements

Fretting .........,damage that develops when relative motion of small

displacement takes place between contacting parts,
wearing away the surface

Gauge (Bearing Ball) .........a term to describe an amount by which the mean
diameter may differ from the nominal diameter.

Gouge .........,.surface area where material has been removed

Horizontal Balance............ balance between the tip and the butt of the blade

Impact Damage ................damage that occurs when the propeller blade or hub
assembly strikes, or is struck by, an object while in flight or

on the ground

INTRODUCTION 61-10-00
 PROPELLER MAINTENANCE MANUAL
HPA RT Z E L L 1 OOE

Term Defin_ition

Nick removal ofpaint and possibly a small amount of material,

not exceeding one layer

Onspeed condition in which the RPM selected by the pilot through

the propeller condition lever and the actual engine
(propeller) RPM are equal

Overhaul(MPI) theperiodic disassembly, inspection, repair, refinish,

and reassembly of a propeller assembly

Overspeed condition in which the RPM of the propeller or engine

exceeds predetermined maximum limits; the condition in
which the engine (propeller) RPM is higher than the RPM
selected by the pilot through the condition lever

Overspeed Damage damage that occurs when the propeller hub assembly
rotates at a speed greater than the maximum limit for
which it is designed

Fitting formation of a number of small, irregularly shaped

cavities in surface material caused by corrosion or wear

Porosity an aggregation of microvoids; see "Voids"

Reference Blade Radius a distance from the propeller hub centerline to a location on
ablade, used for blade angle measurement in an
assembled propeller. A yellow adhesive stripe (blade angle
reference tape CM160) usually
is located at the reference
blade radius location.(Note: do not confuse reference
blade radius with blade station; they may not originate at
the same location.)

Rolling compressive rolling process for the retention area of

single shoulder blades which provides improved strength
and resistance to fatigue

Scratch same as "Nick"

Shot Peening process where steel shot is impinged on a surface to

create compressive surface stress which provides
improved strength and resistance to fatigue

61 -1 0-00 Rev
 PROPELLER MAINTENANCE MANUAL
c LL 100E

Synchrophasing a form of
propeller sychronization in which not only the
RPM of the engines (propellers) are held constant, but
also the position of the propellers in relation to each
other

Track In an propeller, a measurement of the

assembled
location of the blade tip with respect to the plane of
rotation, used to verify face alignment and to compare
blade tip location with respect to the locations of the
other blades in the assembly

Underspeed the condition in which the actual engine (propeller) RPM

is lower than the RPM selected by the pilot through the
condition lever

Vertical Balance balance between the leading and trailing edges; this
cannot be changed on composite blades

Voids air gas that has been

or trapped and cured into a

laminate

Windmilling the rotation of an aircraft propeller caused by air flowing

over it while it is not operating

INTRODUCTION 61’10’00 Rev

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

7. Abbreviations

Abbreviation Term

AN............. Army-Navy
AOG AircraftOn Ground
ATA Air Transport Association
FAA Federal Aviation Administration
Ft-Lb........... Foot-Pound
ID Inside Diameter
In-Lb Inch-Pound
IPL Illustrated Parts List
Lbs Pounds
MIL-X-XXX Military Specification
MPI Major Periodic Inspection
I MS Military Standard
OD ............Outside Diameter
NAS National Aircraft Standards

I N´•m............ Newton-Meter
PSI Pounds per Square Inch
RPM Revolutions per Minute
TBO Time Between Overhaul

I TSN ............Time Since New

TSO Time Since Overhaul

INTRODVCTION 61-10-00
 PROPELLER
HA RTZ E LL MAI1NOSENANCE MANUAL

(Th is page is i ntentionally blan k.)

Page 14
INTRODUCTION 61’10’00 Rev.PJuniOl
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CONTENTS

1. Description of Propeller and Systems 3

A. General Description (Construction) 3

B. General Description (Forces) 4

C. General Description (Control) 5

D. Detail Propeller Description 5

(1) Propeller Model HC-D2(V,MV)20-3( 5

(2) Propeller Model HC-D3(V,MV)20-6( 5

(3) Propeller Model HC-D(2,3)(V,MV)20-7( 8( 6

2. Model Designation System

A. Propeller Model Designation 7

B. Blade Shank Designation 7

C. Conversion From V Shank to MV Shank 7

FIGURES

Figure 1 9
I Model Designation System

OESCRIPTION *ND OPER~TION S1 -1 0’00 Rev. 1

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

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I sl-lo-oo
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

Description of Propeller and Systems

A. General Description (Construction)

(1) The propellers covered in this manual are capable of either constant speed
operation or attaining a blade angle through manual selection by the pilot while
in flight. All of these propellers use aluminum blades and are intended for use
with reciprocating engines.

(2) HartzellHydro-Selective propellers change blade pitch through hydraulic

actuation that is controlled manually. Manual control allows the pilot to select a
blade angle by moving a cockpit control to result in a desired RPM setting.

(3) Hartzell Constant Speed propellers use a device called a governor to sense
engine RPM and will change blade angle automatically to maintain an RPM
selected by the pilot.
(4) Blade angles range from a low positive blade angle to a high positive blade

angle or from a high positive blade angle to a negative blade angle.

Feathering is not possible with these propellers.
(5) HartzellHydro-Selective propellers consist primarily of a propeller assembly, a

hydraulic unit, and a valve assembly.

(6) Hartzell Constant Speed propellers have a governor, a T-drive unit, and

hyd raulic hose con necti ng the governor and the hyd rau lic un it.
(7) A manually controlled propeller assembly consists of a central steel hub that
mounts on the engine splined shaft. Blades are attached to the hub and are
retained by two piece blade clamps and thrust bearing assemblies. A
hydraulic unit consisting of a cylinder, piston, and pitch change linkage is
attached to the face of the engine case encircling the splined engine shaft and
propeller. A valve assembly is attached to the hydraulic unit and supplies oil to
the piston and cylinder. Oil supplied from the engine or governor through the
valve assembly is pumped into a cavity defined by the engine mounted cylinder
and piston. The piston and cylinder do not rotate with the propeller, but remain
fixed to the engine although the piston will move linearly in response to the
changing volume of oi I. This linear movement is transmitted through a th rust
bearing to a jack plate unit that is also part of the hydraulic unit. The thrust
bearing allows the nonrotating piston to be linked to the jack plate unit that
rotates with the propeller. The jack plate unit acts as the linkage between
piston linear movement and blade pitch change. The jack plate unit is attached
to link screws on the inboard side of each blade retention clamp and translates
the linear piston motion into rotational movement of the blade clamp and blade
to result in blade pitch change while the propeller assembly is rotating.

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 PROPELLER MAINTENANCE MANUAL
HARTZELL iooE

(8) A constant speed propeller also is constructed and configured as described

for the manually controlled propeller assembly with the following additions.
Many engines on which a constant speed propeller is mounted are not
designed with an accessory drive pad for attachment of a governor. A device
identified as a T-drive unit is installed between the engine and the fuel pump.
The T-drive unit drives the subject accessory and provides an additional
accessory drive pad for the attachment of a governor. Governor control oil is
supplied through external high pressure hosing to a valve attached to the
hydraulic cylinder and piston to cause a blade angle change and maintain a
constant engine RPM as selected by the pilot.

(9) Blade retention on early propeller models is designated with a "V" in the
propeller model. This blade retention type used two shoulders on the blade
shank outside diameter. The blade shank shoulders are engaged by a two
shoulder blade clamp that encircles the blade root and retains the blade onto a

thrust bearingand blade arm of the central hub. Blade retention on later
propeller models is designated with an "MV" in the propeller model. This blade
retention type uses a single shoulder on the blade shank outside diameter. A
single shoulder blade clamp encircles the blade shank and retains the blade
onto a thrust bearing and blade arm of the central hub.

B. General Description (Forces)

While the propeller is operating the following forces are constantly present: i)
counterweight force, 2) centrifugal twisting moment of each blade, and 3) blade
aerodynamic twisting forces. The counterweight forces rotate the blades to higher
blade angles, while the centrifugal twisting moment of each blade is toward lower
blade angle. Blade aerodynamic twisting force is usually very small in relation to the
other forces that can attempt to increase or decrease blade angle.

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 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

C. General Description (Control)

(1) The summation of the propeller forces higher pitch (low RPM) and is
is toward
opposed by a variable force toward lower pitch thigh RPM). The variable force
is oil under pressure from a governor or is engine oil that is pilot controlled
through a valve. The variable oil force toil supply) is supplied to the hydraulic
cylinder and piston on the face of the engine case encircling the splined
engine shaft and propeller. Increasing the volume of oil within the piston and
cylinder will decrease the blade angle and increase propeller RPM.
Decreasing the volume of oil will increase blade angle and decrease propeller
RPM. Changing blade angle will vary the load on the engine and result in a
change of engine and propeller RPM. On constant speed installations the
governorwill maintain a constant RPM (within limits) independent of where the
th rottle is set. On manually controlled propellers the pilot selects a blade angle
through a cable attached to a valve on the hydraulic cylinder and piston to
select a higher or lower RPM, as desired. The manually controlled valve will
allow engine oil under pressure to enter the piston and cylinder cavity, or will
allow oil to leave the piston and cylinder cavity and return to engine drain.

(2) Reverse blade angle operation only available on manually controlled

is
propeller models. The constant speed propeller models covered in this manual
are not reveisible.

D. Detailed Propeller Description

(1) Propeller Model HC-D2(V,MV)20-3()
(a) This propeller model uses manual control and is reversing. The basic
components of this propeller assembly consist of a propeller, a hydraulic
unit and a valve assembly.

(b) A blade angle range up to 33 degrees enables reverse thrust operation

for ground or water handling. To accommodate the blade angle range,
O-rings provide the seal between the hydraulic unit piston and cylinder.
(c) The hydraulic unit is designed so the cylinder will attach to an engine with
an SAE 20 splined thrust plate that uses six attachment points. This

requires 6 holes in the cylinder to receive 6 studs from the engine and is
secured in place with one nut on each stud.

(2) Propeller Model HC-D3(V,MV)20-6(

(a) This propeller model uses manual control and is reversing. The basic
components of this propeller assembly consist of a propeller, a hydraulic
unit, and a valve assembly.

(b) A blade angle range up to 33 degrees enables reverse thrust operation

for ground or water handling. To accommodate the blade angle range,
O-rings provide the seal between the hydraulic unit piston and cylinder.

DESCRIPTION *NDOPER*TION 61-10-00

 PROPELLER MAINTENANCE MANUAL
HP~ RT Z E L L 100E

(c) The hydraulic unit is designed so the cylinder will attach to an engine with
an SAE 20 splined thrust plate that uses six attachment points. This

requires 6 holes in the cylinder to receive 6 studs from the engine and is
secured in place with one nut on each stud.

(3) Propeller Model HC-D(2,3)(V,MV)20-7( 8(

(a) This propeller model may be controlled manually or by a governor, and is
always non-reversing. If governing (constant speed), the basic
components of this propeller assembly consist of a propeller, a hydraulic
unit, a valve assembly, a governor, and a T-drive unit. If manual control is
used, the basic components of this propeller assembly consist of a
propeller, a hydraulic unit, and a valve assembly.
(b) This propeller model series is capable of approximately 14 degrees of
blade angle range and uses a rubber plate or diaphragm to seal between
the piston and the cylinder.

(c) On -7( models the hydraulic unit is designed so the cylinder of the
hydraulic unit will attach to Continental E-l 85 and E-225 engines that use
four attachment points. This requires 4 holes in the cylinder to receive 4
socket head cap screws that are threaded into the engine.

(d) On -8( models the hydraulic unit is designed so the cylinder will attach
to an engine with an SAE 20 splined thrust plate that uses six attachment
points. This requires 6 holes in the cylinder to receive 6 studs from the
engine and is secured in place with one nut on each stud.

DESCRIPTION*NDOPERPITION 61’10’00
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

2. Model Designation System

A. Propeller Model Designation

Hartzell uses a designation system (outlined in Figure 4) to
model number
identify specific propeller and blade assemblies. An example model number
would be HC-D3V20-6L/V8433, where the slash mark separates the propeller
and blade designations.
The propeller model impression stamped on the propeller hub. The
number is
blade model number is impression stamped on the butt end of the blade, as

I well as ink stamped or identified by a label on the camber side of the blade.

B. Blade Shank Designation

Hartzell blades are often referred to as "D" shank, "Y" shank, etc. For most
blades, the shank type is identified in the prefix letters of the blade model
designation. For example, blade model number V8433N means the blade
has a

"V" shank;however, there are exceptions to this rule. For example, "Y" shank
blades do not use the letter "Y" in the model designation. The same basic blade

type may have more than one shank type, e.g. V8433N, MV8433N.

Refer to Hartzell Manual 133C (61-13-33), Aluminum Blade Manual for more

information on blade shank designs.

C. Conversion From V Shank to MV Shank

(1) "V" shank models, which have double-shoulder configuration, have additional
repetitiveinspections required by Airworthiness Directive AD 97-18-02.
(2) "MV" shank models, which have a single-shoulder configuration, are not

affected by the AD.

(3) "V" shank blades can be converted to "MV" shank to avoid the inspections
required by AD 97-18-02.

(4) Approval Basis:

FAA
(a) The MV blade and propeller designs are approved under the same

Propeller Type Certificate as previous V shank propellers.

DESCRIPTION ANDOPERATION
61’1 0’00 Rev. 1 PAapTCf~d/O
 PROPELLER
nARTZELL MP.:NO~EENPINCE M*NUP.L

(b) Many existing FAA Aircraft

Type Certificate Data Sheets for the old
aircraft affected by this Bulletin are unlikely to be revised to specifically
reflect approval of the new MV type propellers. However, MV type
propellers are approved for use on all applications that previously used X
or V shank blades. There is a statement in the recently revised FAA

Propeller Type Certificates for the )HC-(A,D)(2,3)MV( models that says

the "MV" can be substituted for propeller models with "X" or "V" in the
same location.

NOTE: Similar conditions have existed for many years where V shank
blades were used to replace earlier X shank blades and A or D
type hubs were used to replace earlier 1 or 8 type hubs.
Applicable FAA Propeller Type Certificates have statements like:
"...V may be substituted for X..." or "...A can be substituted for 8...".
For many older propeller designs, the FAA Aircraft Type
Certificate was never updated and may show, for example, a
HC82YK-2 propeller even though a later HC-A2VK-2 propeller is
usable and approved.
Also, note that if a FAA Aircraft Type Certificate calls for a later
propeller design (like A2VK), typically there is no provision to
alloiu use of earlier designs (like 82XK).

DESCRIPTION AND OPERATION 61’1 0’00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1OOE

STEEL HUB, RECIPROCATING ENGINE

HC D 2 V 20 7 L blade model number

I
REFER TO HARTZELL MANUAL 133C FOR ALUMINUM BLADES.

LEFT HAND ROTATION

i7
3 8.875" DIAMETER CYLINDER, 4.65" LONG
COUNTERWEIGHTS
SPECIFIC DESIGN
6 91-6L HYDRAULIC UNIT
FEATURES
USESS1-7DS HYDRAULIC UNIT
8 USES 91-8DS HYDRAULIC UNIT
8D USES 91-8DT HYDRAULIC UNIT

20 SAE 20 SPLINE

V DOUBLE SHOULDER, INTERNAL NEEDLE BEARING,C-3 CLAMP

MV SINGLE SHOULDER, INTERNAL NEEDLE BEARING, D-6831-()

NO.OFBLADES20R3

SPLITBEARING RETENTION, HYDRAULIC PITCH CHANGE MECHANISM

BASIC HUB DESIGN
MOUNTED ON ENGINE

HC- HARTZELLCONTROLLABLE

Model Designation System

Figure 1

9
DESCRIPTION AND OPERATION 61 I10-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

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I DE5CRIPTIONANDOPER~ITION 61-10-00 Rev. 1 Apr/GOPage 10

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CONTENTS

1. Trouble-Shooting Guide 103

A. Pitch changes to high pitch, but will not change to low pitch properly. 103

B. Pitch changes to low pitch, but will not change to high pitch properly. 1 03

C. Pitch does not change properly toward both high and low pitch. 103

D. Friction 104

E. Blade Slippage in Blade Clamp. 104

F Oil Leakage 105

G. Grease Leakage, Blade Split Bearing 105

H. Grease Leakage, Piston to Jack Plate Bearing 105

i. Blades Not Tracking 107

J. End-Play Movement of Blades 107

K. In-and-Out Movement of Blades. 107

L. Fore-and-Aft Movement of Blades. 107

M. Radial Movement of Blades 107

N. Excessive Propeller Vibration 108

FIGURES

Checking Blade Movement Figure 101 106

Abnormal Vibration Figure 102 108

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 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

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Page
TESTING AND FAULT ISOLATION 61 -1 0-00 102Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

1. Trouble-Shooting Guide

The purpose of this guide is to help isolate probable causes and suggests possible
remedies for some of the more common propeller service problems. In all cases, the
remedyfor a problem should follow the procedures detailed in the applicable section
of this manual.

Problem Probable Cause Remed~

Nicked crushed line causing Oil pressure for the 7.25 inch
I changesto high
A. Pitch or

pitch, but will not change low engine oil pressure. (184.1 mm) diametercylinder
to low pitch properly.
should not be below 45 psi and
with a 8-7/8 inch (225.4 mm)
I diameter cylinder, not below 30 psi.

or Excessive friction, which See 1.D. "Friction".

minimizes the hydraulic and
countennreight forces.

to low Drain line that is either too small Drain line should never be less
B. Pitch changes
long. than 3/8 inch (9.6 mm) line, and
I pitch, but will not change or too a

if possible it should return directly

to high pitch properly.
to the crankcase through a

distance of not over 18 inches

(457 mm).
1

I or Excessive friction, which See 1 .D. "Friction".

minimizes the hydraulic and
counterweight forces.

C. Pitch does not change Combination of low oil pressure See section A. and B. above.

properly toward both high and a drain line that is too small
and low pitch. or too long.

I or Excessive friction, which See 1 .D. "Friction".

minimizes the hydraulic and
counterweight forces.

or Failure of the A-38( )thrust Replace the A-38( thrust bearing

bearing, having a riveted cage, with an A-
38B thrust bearing having a
bakelite cage.

of Impropergreasing of the A-38( Grease the thrust bearing with one

bearing.
thrust
tablespoon of high speed bearing
grease CM139.

Deterioration of the rubber

Replace the rubber
diaphragm. diaphragm.

103

TESTING AND FAULT ISOLATION 61-1 0-00 Rev. 1 Apr/GOPage

 PROPELLER
HARTZELL MI\:NO~EENANCE MANUAL

Problem Probable Cause Remedy

D. Friction Solidified grease. Use recommended greases.

or Balls in the blade

split-bearing Replace the split-bearing
are unusually rough, corroded, assembly.
or chipped.

I or The snap ring is wedged Replace the snap ring.

beneath the inboard race of the
blade bearing.

or Over-tightening of blade Disassemble blade clamps and

clamps. reassemble using new clamp
gaskets. Follow assembly
instructions and retorque.

or Pilot tubes slipped out of hub. Reposition the pilot tube.

Replace the pilot tube with another

that hasa 0.002 inch (0.051 mm)

greaterdiameter. Referto
Standard Practices Manual 202A
(61-01-02).

or Lack of lubrication. Add approved grease to blade

clamp lubrication fittings.
E. BladeSlippage in Lubricant action of sealer has Follow rework procedure to correct
Blade Clamp. reduced the friction between slippage.
blade and clamp.

or There is not enough clamping Increase clamping action as

action, necessary. Refer to Clamp
Overhaul section of Hartzell
Manual 202A (61-01-02).

104
TESTING AND FAULT ISOLATION 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

Problem Probable Cause Remedy

F. OilLeakage O-ring deterioration. Replace O-ring.

or Piston O-ring grooves nicked or Polish out nick with fine emery
rough. cloth.

or Surface of cylinder is rough or Polish out nicks with fine emery

scratched, cloth.

or Servo valve O-rings. Replace with double 0- rings.

or Valve gasket leaking. Replace soft paper gasket

between valve and piston with an

A-71-2. Also use thin gasket

compound.

or Hydraulic lines leaking. Tighten or replace hydraulic lines.

or Engine crankshaft seal leaking Replace engine crankshaft seal.

Note: Oil is thrown by centrifugal force into the propeller hydraulic
element and works out through the thrust bearing, appearing
to come from the smaller O-rings. This is a common source,
but difficult to recognize. Replace the engine seal if oil
continues to come from the hydraulic unit after following the
steps above.

G. Grease LeakageBlade
Split Bearing I mproperly torqued or loosel Replace missing lubrication caps.
Torque lubrication fitting to 50
I missing lubrication fitting.
6.5(bl-ni
N´•m).

or Defective lubrication fittings. Replace defective lubrication

fittings.

or Grease leaks past blade clamp Loosen blade clamp bolts and
seal and gaskets. replace gaskets.

or G rease leaks from between Remove blade and clamp. Add

blade and clamp. approved gasket compound in
radius of blade. Reassemble
blade and clamp.

H. Grease Leakage Excess grease. None. Leak stops when excess

Piston to Jack Plate Bearing grease is thrown off.

Source is from between jack
plate and cover plate.
Add only designated amount of
grease.

105
TESTING AND FAULT ISOLATION 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

APS50W

Fore and
aft blade
movement

Radial play in
blade

In and out blade

movement

L/

End-play
in blade

ORIGINAL
As Received By
ATP

Checking Blade Movement

Figure 101

TESTING AND F*ULT ISOLATION 61 -1 0-00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

Problem Probable Cause Remedy

Ground strike damage. Referto appropriate blade overhaul

i. Blades Not
manual for repair procedure.
Tracking

or Hub pilot tubets) distorted. Follow pilot tube replacement

procedure.

or Blade facets) out of alignment. Ref er to applicable blade overhaul

manual for blade face alignment
procedure.

J. End-Play Buildup of wear or repair Total 0.100-in. (2.54-mm) end play

Movement of Blades tolerances, is permissible.
Refer to Figure 101.

K. In-and-Out Buildup of wear or repair Without grease in blade clamps

Movement of Blades. tolerances. and split-bearings, maximum

allowable for-and-aft movement is
Refer to Figure 101.
0.100 inch (2.54 mm).

With grease in blade clamps and

split-bearings, there should be no
fore-and-aft movement in the
blades.

L. Fore-and-AftMovement Buildup of wear or repair Total 0.100 incht2.54mm) fore-

tolerances, and-aft movement is permissible.
of Blades.
Refer to figure 101.

Radial Movementof Buildup of wear or repair Radial movement of 0.5 degree is

M.
Blades. tolerances. permissible.
Refer to figure 101.

Page 107

TESTING FIND F~ULT ISOL~TION

61 -1 0-00 Mar/98
 PROPELLER
HARTZELL E001LAUNAM

Problem Probable Cause Remedy

N. Excessive Propeller Blade slipped in clamp. Inspect blade-to-blade angles and

Vibration reset angles.

Referto Figure 102 or Cracked blade clamp. Magnetic particle inspect blade
clamp and replace defective part.

or Bent, cracked, or damaged See appropriate Hartzell Blade

blade. Overhaul manual.

or Cracked or damaged hub. See Steel Hub Overhaul section of

Hartzell Manual202A, Standard
Practices.

ORIGINAL
As Received By
ATP

Inspect the seal of the blade

clamp for grease leakage.
Inspect the blade clamp
for cracks.

Abnormal Vibration
Figure 102

TESTING AND FAULT ISOLATION 61-10-00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1000

AUTOMATIC TEST REQUIREMENTS (NOT APPLICABLE)

NOTE: Per ATA 100 specification this space is reserved for automatic test
requirements. Such requirements are not applicable to the Hartzell
propellers addressed in this manual.

Page 201

AUTOMATIC TEST REQUIREMENTS

61 ’1 0’00 Mar/98
 PROPELLER
HARTZ ELL MA:NO~EENANCE MANUAL

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Page
AUTOMATIC TEST REQUIREMENTS 61-10-00 202Mar/98
 PROPELLER MAINTENANCE MANUAL
H ~A RTZ E L L 1 OOE

CONTENTS

1. Removal of the Propeller Assembly from the Engine 303

A. General 303

B. Spinner Removal 303

C. Propeller Removal 303

D. HC-D2(V,MV)20-3 PROPELLER MODELS ONLY 304

E. HC-D3(V,MV)20-6L PROPELLER MODELS ONLY 306

F. HC-D(2,3)(V,MV)20-7 and -8( PROPELLER MODELS ONLY 308

2. Marking Before Disassembly 310

3. Propeller Disassembly 310

A. Preparation for Disassembly 310

B. Clamp and CounteMieight Disassembly 310

C. Blade and Mounting Parts Disassembly 313

D. Hub Disassembly
E. Jack Plate and Hydraulic Piston Disassembly 316

F. Disassembly
B-93-D Valve
HC-D2(V,MV)20-3 and HC-D3(V,MV)20-6L Propellers 317

G. B-93-A, -B, -C Valve Disassembly

HC-D2(V,MV)20-7 and -8 Propellers 317

H. B-93-AG, -BG, -CG Valve Disassembly

HC-D2(V,MV)20-7 and -8 Propellers 317

B-93-E Valve Disassembly

I HC-D3MV20-8D Propellers 317

FIGURES

Removing Bearing Retention Ring Figure 301 312

DISASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 100E

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I DISASSEMBLY 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

1 Removal of the ProPeller Assembly from the Engine

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED AS THEY
MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY THAT ARE
NOT CONTAINED IN THIS MANUAL OR THE HARTZELL OWNER’S
MANUAL.

CAUTION: USE ADEQUATE PRECAUTIONS TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

A. General
when
The following propeller removal instructions are to be used as a reference
removing a propeller in accordance with the airframe manufacturer’s
maintenance manual.

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIMILARLY IDENTIFY

PARTS IN ANY MANNER WHICH MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OF THE PROPELLER.

B. Spinner Removal

CAUTION: TO PREVENT DAMAGE TO THE BLADE AND BLADE PAINT,

WRAP THE BLADE SHANKS IN SEVERAL LAYERS OF MASKING
OR DUCT TAPE BEFORE REMOVING THE SPINNER DOME, IF
INSTALLED.

(1) Remove and discard fasteners that attach the spinner dome to the bulkhead.

(2) Remove the spinner dome and store it with care.

C. Propeller Removal

WARNING: MAKE SURE THE SLING IS RATED UP TO 500 POUNDS (227KG)

I TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY

DURING INSTALLATION.

(1) Support the propeller assembly using a suitable sling and mobile hoist.

(2) Remove the hub lock safety pin (190).

loosen the hub nut (180) and unthread from the engine shaft
(3) Completely
threads.

NOTE: Because the hub nut is pulling the propeller hub off the tapered rear
cone (200), there will be significant resistance to the loosening of the
hub nut.

61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

D. HC-D2(V,MV)20-3 PROPELLER MODELS ONLY

CAUTION: VALVE MUST BE IN HIGH PITCH POSITION TO BLEED AIR INTO

THE CYLINDER.

(1) Twist the counterweights (340) toward high pitch so the push rods back out of
the hub lugs.

NOTE: Push rods will move toward the engine

(2) Slide the hub on the
engine shaft far enough to allow the jack assembly push
rods (800) to completely slide out of the hub lugs.

(3) Turn the jack plate unit (770) until the pitch change forks (810) disengage from
the pitch change blocks (220).

CAUTION: DO NOT ETC H, SC R IBE, PUNC H MARK, OR S I M ILARLY I DE NTI FY

PARTS IN ANY MAN N ER THAT MAY BE HARM FU L TO TH E
STRENGTH OR FUNCTION OF TH E PROPELLER.

(4) Reference the blocks (220), if reusable, to the forks (810) to insure reassembly
with the same fork.

(5) Remove the blocks (220) from the forks (810).

(6) Pull the hub (10) with blades from the engine shaft.
(7) Place the propeller on a propeller cart for transport.
(8) Disconnect the reverse pitch control cable from the hydraulic valve lever the
short end extending from the valve spool).
(9) Disconnect the pitch control cable from the hydraulic valve lever (the
reverse

long end extending from the valve spool).

WARNING: OIL WILL BE RELEASED FROM THE CYLINDER AND

PISTON CAVITY WHEN THE PISTON IS REMOVED FROM
THE CYLINDER. PLACE A PAN UNDER THE HYDRAULIC
UNIT TO CATCH THE RELEASED OIL.

(10) Remove the hydraulic oil supply and drain lines from the hydraulic valve
mounted on the propeller piston.

(11) Pull thejack plate unit (770), hydraulic piston (510), and all accompanying
parts out of hydraulic cylinder (540).

NOTE: The valve assembly (1000) is still attached to the hydraulic piston
(510) and the hydraulic cylinder is still attached to the engine.

DISPISSEMBLY 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CAUTION: THE EXACT COMBINATION OF REAR CONE AND SPACERS

MUST BE REUSED OR PROPELLER MAY NOT REACH LOW
PITCH(COULD UNDERSPEED)OR HIGH PITCH (COULD
OVERSPEED).
(12) Remove the rear cone (200) and spacers (210).

NOTE: The spacers are used to adjust the position of the propeller with the
engine and hydraulic unit. The positioning assures that the blade
pitch movement of the propeller is within the movement range of the
hydraulic piston.
Remove the six nuts holding the cylinder (540) to the engine mounted studs.
(13)
(14) Remove the cylinder (540) and gasket (650) from the engine.
1 the valve assembiy (1000)
(16) Remove the two screws (1250) and disassemble
from the hydraulic piston (510).
(16) Remove the gasket (1010).

NOTE: The gasket may need to be scraped off of the valve body (1 040) or the
hydraulic piston (510).

,,,,,,,,,,Y 61110100
 PROPELLER
HARTZELL MPI:ND~EENPINCE MPINVP~L

E. HC-D3(V,MV)20-6L PROPELLER MODELS ONLY

(1) Remove the (31 5) and washers (31 4) from the ends of the th ree push
n uts rods
protruding from the jack assembly (770).

NOTE: Keep the nuts (315) and washers (314) with the propeller and jack
assembly.

CAUTION: VALVE MUST BE IN HIGH PITCH POSITION TO BLEED AIR

INTO THE CYLINDER.

(2) Twist the counterweights (340) toward high pitch so the push rods back out
of the guide collar bushings in the guide collar (300).

NOTE: Push rods will move toward the engine

1 (3) Slide the hub on the
engine shaft far enough to allow the jack assembly push
rods (800) to completely slide out of the guide collar (300).
(4) Turn the jack plate unit (770) until the pitch change forks (810) disengage from
the pitch change blocks (220).

CAUTION: DO NOT ETCH, SCRIBE, PU NCH MARK, OR S I M ILARLY IDENTI FY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OF TH E PROPELLE R.

(5) Reference the blocks (220), if reusable, to the forks (810) to insure reassembly
with the same fork.

(6) Remove the blocks (220) from the forks (810).

(7) Pull the hub (10) with blades from the engine shaft.
(8) Place the propeller on a propeller cart for transport.
(9) Remove the reverse stops (313) and sleeves (312) from the ends of the three
push rods protruding from the jack assembly (770).

NOTE: Keep the reverse stops (313) and sleeves (312) with the propeller and
jack assembly (770).
(10) Disconnect the reverse pitch control cable from the hydraulic valve lever( the
short end extending from the valve spool).
(1 1) Disconnect the pitch control cable from the hydraulic valve
reverse lever (the
long end extending from the valve spool).

WARNING: OIL WILL BE RELEASED FROM THE CYLINDER AND

PISTON CAVITY WHEN THE PISTON IS REMOVED FROM
THE CYLINDER. PLACE A PAN UNDER THE HYDRAULIC
UNIT TO CATCH THE RELEASED OIL.

DISIPSSEMBLY 61-10-00
 PROPELLER MAINTENANCE MANUAL
H P~ RTZ I- L L 1 OOE

(12) Remove the hydraulic oil supply and drain lines from the hydraulic valve
mounted on the propeller piston.

(13) Pull the jack plate unit (770), hydraulic piston (510), and all accompanying
parts out of hydraulic cylinder (540).

NOTE: The valve assembly (1000) is still attached to the hydraulic piston (510)
and the hydraulic cylinder is still attached to the engine.

CAUTION: THE EXACT COMBINATION OF REAR CONE AND SPACERS

MUST BE REUSED OR THE PROPELLER MAY NOT REACH LOW
PITCH (COULD UNDERSPEED) OR HIGH PITCH (COULD
OVERSPEED).
(14) Remove the rear cone (200) and spacers (210).

NOTE: The spacers are used to adjust the position of the propeller with the
engine and hydraulic unit. The positioning assures that the blade
pitch movement of the propeller is within the movement range of the
hydraulic piston.
(15) Remove the six nuts holding the cylinder (540) to the engine mounted studs.

(16) Remove the cylinder (540) and gasket (650) from the engine.
(17) Remove the two (1250) and disassemble the valve assembly (1000)
screws

from the hydraulic piston (510).

(16) Remove the gasket (1010).

I NOTE: The gasket may need to be scraped off the valve body (1 040) or the
hydraulic piston (510).

61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1006

F. HC-D(2,3)(V,MV)20-7 and -8( PROPELLER MODELS ONLY

(1) Rotate the blades to high pitch by gripping the blade counterweight on each
blade clamp.
(2) Rotate the blades until the push rods protruding from the jack plate unit slide
out of each of the two hub lug bushings.

NOTE: On HC-D3MV20-8D propeller models only, the three push rods

protruding from the jack plate unit will slide out of each of three guide
collar mounted bushings.

(3) Rotate the jack plate unit to allow each fork to disengage each pitch change block.
(4) For 2-bladed propellers, remove the pitch change t>lock from each blade clamp
linkscrew.

NOTE: For 3-bladed propellers, the pitch change block is removed with the
blade clamps.

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY IDENTIFY

PARTS IN ANY MANNER THAT MAY f3E HARMFUL TO THE
STRENGTH OR FUNCTION OF TH E PROPELLE R.

(5) If reusable, reference the blocks (220) to the forks (810) to insure reassembly
with the same fork.

(6) Remove the blocks (220) from the forks (810).

(7) Using the support sling, slide the propeller from the engine splined shaft and
lift the propeller from the engine.

(8) Place the propeller and the associated parts on a suitable cart for
transportation.
(9) On non-governing installations, disconnect the ail~plane’s push-pull pitch
control from thehydraulic valve link (1 140).

NOTE: On governing installations the cockpit control is for RPM control and
connects to the governor. On nongoverning installations the cockpit
control is to the valve attached to the cylinder (510) and provides for
direct pitch control only.

(10) Remove the screw (950) that attaches the hydraulic valve link (1 130) to the
hydraulic piston (530).

DIS~SSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL iOOE

I CAUTION: OILWILL COME OUTOF THE CYLINDER AND PISTON CAVITY

WHEN THE PISTON IS REMOVED FROM THE CYLINDER. PLACE A
PAN UNDER TH E HYDRAULIC UN IT TO CATCH THE ENGI NE OIL.

(1 1 Disconnect the hydraulic oil supply and the drain lines from the hydraulic valve
that is mounted on the cylinder (51 0).

1 (12) Pull the jack plate unit (770), hydraulic piston (51 0), and all related parts off the
guide pins of the hydraulic cylinder (540).

NOTE: The valve assembly (1 000) is still attached to the hydraulic piston (51 0)
and the hydraulic cylinder (540) is still attached to the engine.

CAUTION: THE EXACT COMBINATION OF REAR CONE AND SPACERS

MUST BE REUSED OR THE PROPELLER MAY NOT REACH LOW
PITCH (UNDERSPEED) OR HIGH PITCH.
(13) Remove the rear cone (200) and spacers (210).

NOTE: The spacers are used to adjust th e position of the p repeller with the

I engine and hydraulic unit so that the blade pitch movement of the
propeller is within the movement range of the hydraulic piston.
(14) Remove the screws (700) from the inner ring (680).

(15) Remove the inner ring (680) from the diaphragm (660).

1 (16) Remove the screws (600) and washers (590) from the outer ring (610).

(17) Remove the outer ring from the diaphragm (660).

(18) Remove the rubber diaphragm (660) from the cylinder (540).
(19) Remove the six nuts holding the cylinder (540) to the engine-mounted studs.

(20) Remove the cylinder ~540) and gasket (650) from the engine.
(21) Remove the two screws (1250).and disassemble the valve assembly (1000)
from the hydraulic cylinder (51 0).

(22) Remove the gasket (1010).

be scraped off the valve body (1040) the

NOTE: The gasket may need to or

cylinder (51 0).

,,,,,s,,,,Y 61110100
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

2. Markincr Before Disassemblv

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY IDENTIFY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and any
other serial-numbered parts and compare with the data in the propeller
logbook.
(2) Keep parts with theirrespective assemblies and note the locations of these
parts to minimize reassembly problems with propeller balance and blade
angle setting.

CAUTION: USE CRAYON OR SOFT NON-G RAPH ITE PENCIL CM1 62 TO

MARK PARTS.

(3) Number blades counterclockwise from the serial number of the propeller
hub las viewed from the front, or side opposite the engine).
1 (4) Reinstall each blade on the hub arm from which it was removed, if
possible.
1 (5) Record on paper each blade serial number and its matching hub arm and
clamp.

3. Propeller Disassemblv

A. Preparation for Disassembly

I Install the propeller assembly on the rotatable fixture on the assembly table, as
shown in Figure 701.
B. Clamp and Counterweight Disassembly

NOTE: Refer to the Blade Clamp Overhaul chapter of Hartzell Standard Practices
Manual 202A (61-01-02), for information on clamp disassembly, inspection,
and repair.
(1) Remove the clamp-halves (440) from each hub arm.

NOTE: Remove the blocks (220) for 3-bladed propellers now.

(2) Remove and discard the outboard clamp bolts (450), nuts (470) and
washers (460) from each clamp.

NOTE: If there was interference between the spinner and the clamp bolt, the
outboard leading edge bolt in the clamp may have been installed with
the head of the bolt positioned on the counterweight side of the clamp.

61-10-00
 PROPELLER MAINTENANCE MANUAL
c LL 100E

(3) Remove and discard the inboard clamp socket screws (420) and cotter

pins (410) or safety wire from each clamp.

(4) Clamp Overhaul chapter of Hartzell Standard Practices
Refer to the Blade
Manual 202A (61-01 -02), for counterweight removal instructions.

(5) Remove and discard the clamp gasket (430) from each clamp.

CAUTION: RECORD THE LOCATION AND NUMBER OF BALANCE

WEIGHTS ON THE PROPELLER BEFORE DISASSEMBLY.
AFTER OVERHAUL ASSEMBLY, USE THIS INFORMATION TO
HELP STATIC BALANCE THE PROPELLER.

(6) Remove all balance weights and attaching screws, where applicable.
Discard the screws.

(7) Remove and discard all lubrication fittings (400, 405) and lubrication fitting
caps (480).

NOTE: On Republic Seabee installations a clamp lubrication fitting (400) may

interfere with the piston-mounted valve. These lubrication fittings were
cut down to the hex and silver soldered. At overhaul after lubrication,
these modified fittings are replaced with a lubrication plug in the clamp
hole facing the engine.

DISASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

APSOlglB
APS0213

STEP TWO

STEP THREE

Legend:
1. Blade
2. Wire Retention Ring
3. Guide Ring
4. BallSpacer
5. Bearing Balls
6. Bearing Retention Ring
7. O-ring

Removing Bearing Retention Ring

Figure 301

Page
DISASSEMBLY 61’10’00 312Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

C. Blade and Mounting Parts Disassembly

NOTE: Item numbers are from Figure 301

(1) Beginning with blade position number one, remove the bearing retention
ring (6) from its groove in the inboard race of the blade retention split
bearing.
(2) Remove the two halves of the inboard bearing race.

(3) Remove and discard the ball spacer (4) and bearing balls (5).

(4) Clip, remove, and discard the blade O-ring (7).

(5) Use a punch at several places on the outboard edge of the
mallet and soft
guide ring (3) to drive the ring inboard over the shoulder of the hub arm.
I Refer to Figure 301, Step One.

(6) Remove the wire retention ring (2) that had been covered by the guide ring.
Discard the wire retention ring if it is sprung.

Turn the halves of the inboard bearing race so the split is at the top. Refer
(7)
to Figure 301, Step Two.

(8) At thesplit, place one of the bearing balls between the outboard split-
I bearing race and inboard shoulder of the hub arm.
(9) Using a soft mallet, lightly tap the inboard top edge of the guide ring to

dislodge the split outboard race from the guide ring.

Remove the halves of the they become separated from the
(10) race as

retention ring.
45 degrees and the ring
(11) Tilt the guide ring inboard approximately remove

by sliding it outboard over the shoulder of the hub Refer to Figure

I arm.

301, Step Three.

,,,,,,,,,,Y 61110100
 PROPEL"R
nARTZELL YA:NW~ENANCE MANUAL

D. Hub Disassembly
(1) HC-D2(V,MV)20-3, HC-D2(V,MV)20-7 AND HC-D2(V,MV)20-8 PROPELLER
MODELS ONLY

(a) Remove the snap ring (170) to release the puller ring (160) and hub nut
1 (180) from the hub unit(l0).
(b) Remove the puller ring (160) and hub nut(l80).

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE
HARMFUL TO THE STRENGTH OR FUNCTION OF THE
PROPELLER.

(c) Remove the bushing (50) if the hub is to be cadmium plated. The bushing
may be removed using a soft drift. The bushing must be clocked to the
hub to assure the same orientation and proper centering of the hub on the
engine shaft at reinstallation. If a new bushing is required, the hub must
be returned Hartzell Propeller Inc. for installation of the bushing.

(d) Remove and discard two bushings (40) if the hub is to be cadmium plated
Using damage the hub tabs, drill out the bushings. Refer to the
care not to

guide collar bushing replacement procedures in the Special Adhesive

and Bonding Procedures chapter of Hartzell Standard Practices Manual
202A.

(e) Removal instructions for the pilot tube may be found in the Steel Hub
Overhaul chapter of Hartzell Standard Practices Manual O2A (61 -O 1 -02).
(2) HC-D3(V,MV)20-6L AND HC-D3MV20-8D PROPELLER MODELS ONLY

(a) Loosen and remove the guide collar nut (310).

NOTE: The guide collar is still firmly clamped to the guide collar nut (310).
(b) Remove and discard the O-ring (290) from the hub (10).
(c) Loosen the socket head cap screw in the guide collar (300) and remove
the guide collar.

I (d) Remove the puller ring (160) and hub nut(l80).

D,,,,,,, 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE
HARMFUL TO THE STRENGTH OR FUNCTION OF THE
PROPELLER.

(e) Remove the bushing (50) if the hub is to be cadmium plated. The
bushing may be removed using a soft drift. The bushing must be
clocked to the hub to assure the same orientation and proper centering
of the hub on the engine shaft at reinstallation. If a new bushing is
required, the hub must be returned Hartzell Propeller Inc. for installation of
the bushing.

(f) Removal instructions for the pilot tube may be found in the Steel Hub
Overhaul chapter of Hartzell Standard Practices Manual 202A.

DISASSEMBLY 61’10’00
 PROPELLER
HARTZ E LL MA:NO~EENANCE MANUAL

E. Jack Plate and Hydraulic Piston Disassembly

(1) HC-D2(V,MV)20-3 and HC-D3(V,MV)20-6L PROPELLER MODELS ONLY

(a) Support the outside of diameter of the piston (510) facing the jack plate
unit (770). Place a round plate (simple tool) on the inboard edge of the
jack plate unit on the side opposite the forks. Push on the round plate to
I drive the jack plate unit and attached bearing (670) off the hydraulic
piston.
NOTE: The press fit between the hydraulic piston and the bearing (670) is
released in this operation.

(b) Remove the screws (760) and washers (750).

(c) Remove the cover plate (720) and cover plate gasket (710) from the
piston (510).
(d) Reach into the center bore of the jack plate unit (770) with a pair of
I diagonal cutters, grab the tang of the wire ring (930) and gradually work
the ring out of the groove between the bearing inner race and the jack
plate casting (780).
(e) Using appropriate fixturing, remove the bearing (670) from the jack plate
unit (770).

NOTE: The bearing (670) is pressed onto the jack plate unit (770) and
must be pressed off or driven off with a soft drift.
(2)
I HC-D(2,3)(V,MV)20-7 AND -8(
(a)
PROPELLER MODELS ONLY

Support the outside diameter of the piston (510) facing the jack plate unit
(770). Place a round plate (simple tool) on the inboard edge of the jack
plate unit on the side opposite the forks. Push on the plate to drive the
I jack plate unit off the hydraulic piston.
NOTE: The press fit between the hydraulic piston and the bearing (670) is
released in this operation.

(b) Remove the screws (760) and washers (750).

(c) Remove the cover plate (720) and cover plate gasket (710) from the
hydraulic piston (510).
(d) Using appropriate fixturing, remove the bearing (670) from the
hydraulic piston (510).
NOTE: The bearing (670) is pressed into the hydraulic piston (510) and
must be pressed off or driven off with a soft drift.

DISASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
~49 RTZ F L L 1 OOE

F. B-93-D Valve Disassembly HC-D2(V,MV)20-3 and HC-D3(V,MV)20-6L

Propellers
(1) Lift the loop of the spring (1 180) off the groove in the guide pin (1200).

1 (2) Remove the cotter pin (1 170) that holds the other end of the spring (1 180) to
the valve body.
(3) Remove the cotter pin (1220) from the end of the guide rod (1210).
(4) Slide the valve spool (1050) and the guide pin (1200) out of the valve body
(1040).
(5) Remove the guide pin (1200) that connects the valve link (1240) and valve
spool (1050).
(6) Remove the valve link (1240) from the valve spool (1050).

1 (7) Remove the O-ring (1230) from the valve body (1040). Discard the O-ring.

G. B-93-A, -B, -C Valve Disassembly HC-D2(V,MV)20-7 and -8 Propellers

(1) Remove the cotter pin (1070) and clevis pin (1080).
(2) Remove the cotter pin (1075)pin (1100). Disassemble the
and clevis links

(1140) and (1130), and the spacer (1090).

(3) Remove the stop nut (1110) and stop screw (1120) from the link (1130).
(4) Slide the valve spool (1050) out of the valve body (1040).
(5) Remove the O-rings (1060) from the valve body (1040). Discard the O-rings.

H. B-93-AG, -BG, -CG Valve Disassembly HC-D2(V,MV)20-7 and -8 Propellers

(1) Remove the cotter pin (1070) and clevis pin (1080). Disassemble the link
(1130) from the valve spool (1050).

(2) Slide the valve spool (1050) out of the valve body (1040).
(3) Remove the O-rings (1060) from the valve body (1040). Discard the O-rings.

i. B-93-E Valve Disassembly HC-D3MV20-8D Propellers

(1) Remove the cotter pin (1070) and clevis pin (1080).
(2) Remove the cotter pin (1075) and clevis pin (1100). Disassemble the links
(1140) and (1130), and the spacer (1090).
(3) Remove the stop nut (1 1 10) and stop screw (1 120) from the link (1 130).
(4) Slide the valve spool (1050) out of the valve body (1040).
(5) Remove the O-rings (1060) from the valve body (1040). Discard the O-rings.

61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

(This page is intentionally blank.)

I olsnsse.s~v 61-10-00 Rev. 1 Apr/GOPage 318

 PROPELLER MAINTENANCE MANUAL
H~ RTZ ELL 1 OOE

CONTENTS

1. General Procedures for Cleaning Parts 403

2. Specific Cleaning Procedures 403

Page
CLEANING 61 -1 0-00 401Mar/98
 PROPELLER MAINTENANCE MANUAL
H19 RTZ E LL 1 OOE

(This page is intentionally blank.)

Page
CLEANING 61’10’00 402Mar/98
 PROPELLER MAINTENANCE MANUAL
H~ RTr E L L i OOE

1. General Procedures for Cleaning Parts

Refer to Hartzell Standard Practices Manual 202A, Chapter 100.

2. SPecific Cleaning Procedures

A. Cleaning Steel Parts for Magnetic Particle Inspection

Refer to Hartzell Standard Practices Manual 202A (61-01-02), Chapter 200.

B. Cleaning Steel Parts for Cadmium Re-Plating Procedures

Refer to Hartzell Standard Practices Manual 202A (61-01-02), Chapter 1500.

CLEANING 61 -1 0-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

(This page is intentionally blank.)

61 -1 0-00
 PROPELLER MAINTENANCE MANUAL
HP~RTZ c LL 100E

CONTENTS

1. Inspection Intewal Requirements 503

2. Mandatory Inspection Requirements 503

A. Thrust Bearing 503

8. Rubber Diaphragm 503

3. Inspection Requirements 503

A. Visual Inspection 503

B. Penetrant Inspection 503

C. Magnetic Particle Inspection 503

D. Dimensional Inspection 504

4. Replacement Requirements 504

5. Repair 504

6. Hub Unit Inspection 504

7. Blade Clamp Inspection 504

8. Blade Inspection 504

9. Blade Split Bearing Inspection 507

10. Bearing Guide Ring 507

11.Guide Collar Inspection 509

12. Spacer.......... ´•´•´•´•´•´•´•´•510

13. A-38B(G) Thrust Bearing 510

14. Balance Weight 510

FIGURES

Blade Split Bearing Figure 501 506

Guide Collar Figure 502 508

TABLES

Component Inspection Criteria Table 501 507

cnac~e 61 -10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

(ihis page is intentionally blank.)

I 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

1. Ins~ection Interval Reauirements

Refer to the Airworthiness Limitations section of this manual for information on life

limited components.

2. Mandatory Inspection Reauirements

A. Thrust Bearing
82(
with AD 65-21-04 and Service Bulletin the A-38( thrust bearing
To comply
must be inspected and replaced as necessary. Repeat the inspection every 100
hours and grease the thrust bearing with high speed bearing grease CM139.

Refer to the AD and the associated Service Bulletin for complete instructions.

B. Rubber Diaphragm
To comply with AD 65-21-04, Service Letter 48( and Service Letter 61(

HC-D2-(V,MV)-(7,8) Hartzell Hydro-Selective propellers require the replacement

of the rubber diaphragm (P/N 8-119-2) at intervals not to exceed 24 months or
250 hours of operation, whichever occurs first. An inspection of the rubber
diaphragm is required every 6 months.
Refer to the AD and the associated Service Letters for complete instructions.

3. Inspection Reauirements

A. Visual Inspection
all parts. Parts with obvious defects damage are to be
Visually inspect or

removed from service.

B. Penetrant Inspection
Follow the penetrant inspection found
procedures for in Hartzell Standard

Practices Manual 202A (61-01-02), Chapter 300.

C. Magnetic Particle Inspection

Follow the procedures formagnetic particle inspection found in Hartzell Standard
Practices Manual 202A (61-01-02), Chapter 200.

61-10-00
 PROPELLER
HARTZ ELL MPII1NOSENANCE MANUAL

D. Dimensional Inspection
(1) Dimensionally inspect parts, as required. Refer to Table 501.

(a) When measuring the diameter of a part using a two point measuring
instrument, take at least two measurements, unless otherwise
specified. When two measurements are taken, obtaining a
measurement outside the specified tolerance at any
point of
measurement is cause for retirement of the
part. Alternately, take eight
evenly spaced measurements, unless otherwise specified. When eight
measurements are taken (two of eight measurements may be out of
specified tolerance), obtaining a measurement outside the specified
tolerance on three or more measurements is cause for retirement of
the part. This alternate method may not be used to accept a diameter
that has obvious damage.

(b) When measuring the diameter of a part with a three point measuring
instrument, take one measurement. A measurement outside the
specified tolerance is cause for retirement of the part.

Replacement Reauirements

Replace all parts that have cracks, parts with obvious defects or damage found
during visual inspection, or parts that would affect operation or serviceability if
repai red.

15. Repair

Repairable part defects are noted in the inspection criteria in Table 501. Repair
procedures are found in the Repair section of this manual, unless otherwise stated.

1 6. Hub UnitlnsPection

Refer to Hartzell Manual 202A (61-01-02), Standard Practices, Steel Hub Overhaul,
Chapter 1700 for requirements and procedures for inspecting steel hub units

7. Blade Clamr, Inspection

Refer to Hartzell Manual 202A (61-01-02), Standard Practices, Blade Clamp

Overhaul, Chapter 2000, for requirements and procedures for inspecting clamps.

13. Bladelnsoection
Refer to Hartzell Manual 133C (61-13-33) for requirements and procedures for
inspecting aluminum blades.

CHECK 61’10’00
 PROPELLER MAINTENANCE MANUAL
H~ARTZ c LL 100E

(This page is intentionally blank.)

505
cHEcK61-10-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

APS6068a
APS6069
5016
5017

Cracks
Chips

Outer
diameter

Chips

Outer
.i.:.i.:.i.:.ii.i.:.i.:.i.:.i.:.i.:.i.:.i.:.i.:.i.:.i.:.i.

diameter
liiiliiiiii(b’
iiiiiiiiil~

No visible
T
chipping,

i Radial
cracks,
allowed in this
(dashed-lines).
or fretting,
area

i:!:i:!:iiiii~
.´•i:i:;´•.´•;´•.´•i´•.´•;*

I´•Outerameter
Blade Split Bearing
Figure 501

Page
CHECK 61-10-00 506Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

(9. BladeSDlitBearina Inspection

A. Visually inspectthe outer All indications of fretting must Remove fretting indications with
diameter of all bearing be removed. a Scotch BriteTM pad.
races for indications of
ft´•etting damage.

B. Visuallyinspectthe ball No indications of fretting are None. Retire the bearing races.

track of each bearing race allowed.

for indications of fretting
(refer to Figure 501).

C. Visually inspectthe spilt No chips or cracks are allowed. None. Retire the bearing races.

lines of all bearing races

for chipping or cracks
(refer to Figure 501).

D. Dimensionally inspectthe 0.005 inch (0.12 mm) depth of None. Retire the bearing races.

depth of pitting or damage pits or damage is allowed.

in the ball track of each
bearing race.

E. Bladesplitbearing races No cracks are allowed. None. Retire the bearing races.

must be inspected using

the magnetic particle
method at each overhaul.

10. Bearing Guide Ring

A Magnetic particle inspect No cracks are allowed. None. Retire the ring.
and re-cadplate.

507
61-10-00 RevPlaaAep~Page
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

BSD4985

Cracks typically occur in

the area near the socket
head cap screw opening

_i;’llt-i 1

ORIGINAL
As Received By
ATP

Guide Collar
Figure 502

Page
CHECK 61-10-00 508Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

I 11. Guide Collar Inspection

A. Visually inspectthe guide No cracks are allowed. None. Retire the guide collar.
collar for cracks. Refer to
Figure 502 for typical
crack locations.

8. Visually inspecttheguide Maximum depth of damage may Polish the damaged area, if less
I collar for nicks, gouges, or not exceed 0.020 inch (0.50 mm). than 0.020 inch (0.50 mm), and
other damage. Alodine coat.

C. Inspectthe guide collar No cracks are allowed. None. Retire the guide collar.

using the dye penetrant

method.

D. Dimensionally inspectthe If thebushing is worn more than Bushings that have an ID

I ID of the guide collar 0.008 inch (0.20 mm) ovality, greater than 0.511 (12.97 mm)
bushings. See Figure 502, replace it. Refer to Figure 502 inch must be removed and

I Item D. for bushing ID requirements. replaced. Repair

Refer to the
chapter of this manual for
replacement procedures.

509
CHECK 61-10-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HA,RT Z E L L 1 OOE

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

12. SPacer

None. Retire the spacer.

I A. Visually inspectthe
spacer for wear or
No indications of
damage are
wear or

permitted.
damage.

13. A-38B(G~ Thrust Bearing

A. Visually inspectthe Maximum permissible depth of Polish the damaged area if

I external surfaces for damage is 0.005 inch(0.12 mm) 0.005 inch (0.12 mm) deep or
less. Retire the bearing if it does
corrosion or nicks.
not fit tightly in the piston and
jackplate after polish. Retire the
bearing if the damaged area
exceeds 0.005 inch (0.12 mm)
deep.

B. Rotational freedom. Bearing races must rotate None. Retire the thrust bearing.
smoothly on cage supported balls
with no perceptible catch or
roughness.

C. Visually inspectthe ball No indications of corrosion or None. Retire the thrust bearing.
I track surface of each race. damage are permitted.

14. Balance Weight

A. Visually inspectthe No corrosion is permitted. Light corrosion must be removed

balance weight for Maximum permitted depth of by glass bead cleaning. Replace
indications of corrosion pitting is 0.005 inch (0.13 mm). the balance weight if depth of
and pitting. pitting exceeds 0.005 inch
(0.13 mm).

B. Visually inspectfor A few scratches are acceptable; Replate the balance weight in
cadmium plate coverage. otherwise, cadmium plate must accordance with the Cadmium
completely cover the balance Replating chapter of Standard
weight. Practices Manual 202A
(61-01-02).

510
CHECK 61-10-00
 PROPELLER MAINTENANCE MANUAL
H19 RTZ E LL 1 OOE

CONTENTS

1. General 603

A. Shot Peening 603

B. Minor Damage to Metal Parts 603

2. Blade Repair. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 603

3. Hub Unit Repair 603

4. Blade Clamp Repair 603

5. Spinner Assembly Repair 604

6. Guide Collar Repair 604

7. Hub Lug Repair 604

REP~IR61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

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61 -1 0-00
 PROPELLER MAINTENANCE MANUAL
HA RT~ E L L OOE

WARNING: DO NOT ATTEMPT IN THE FIELD ANY REPAIR, REPLACEMENT,

REWORK, REPLATING, REANODIZING OR RE-SHOT PEENING
PROCEDURE NOT SPECIFICALLY AUTHORIZED BY HARTZELL
PROPELLER INC. OR NOT SPECIFICALLY REFERRED TO IN
HARTZELL MANUALS. CONTACT THE FACTORY FOR GUIDANCE
ABOUT THE AIRWORTHINESS OF ANY PART WITH UNUSUAL
WEAR OR DAMAGE.

1. General

A. Shot Peening

CAUTION: THE PEENING MARKS ON CERTAIN PROPELLER PARTS ARE

NOT TOOL MARKS AND SHOULD NOT BE REMOVED.

Certain surfaces of propeiier assembly parts have been shot peened at the

factory to improve fatigue strength.

Shot peened surfaces may need re-shot peening because of rust, galling, or
nicks. Refer to Hartzell Standard Practices Manual 202A (61-01-02) Chapter
1400 for shot peening procedure. Re-shot peening must be done only by
Hartzell-approved facilities. A list of approved Facilities may be found in Hartzell
Standard Practices Manual 202A (61-01-02), Approved Facilities, Chapter 1900.

B. Minor Damage to Metal Parts

Eliminate all evidence of scratches, nicks, burrs, and other minor damage by
using a fine emery cloth or Scotch Brite pad. Be sure to blend the polished area
surrounding area. Use extreme care to completely
in with the remove the
damage while removing as little material as possible.
Make sure the part is still within tolerance after any type of repair. Refer to the
Check section and the Fits and Clearances section of this manual.

2. Blade Repair

For aluminum blade repair, replacement, and rework instructions, refer to Hartzell
Manual 133C (61-13-33),

3. Hub Unit Repair

Refer to the Steel Hub Overhaul section of Hartzell Manual 202A (61-01-02),
Standard Practices, for requirements and procedures for repairing steel hub
units.

4. Blade Clamp Repair

Refer to the Blade Clamp Overhaul section of Hartzell Manual 202A (61-01-02),
Standard Practices, for requirements and procedures for repairing clamps.

REPAIR~1’10’00
 PROPELLER MAINTENANCE MANUAL
HP~ RTZ E L L 1 998

5. Spinner Assembly Repair

Refer to Hartzell Manual 127 (61-16-27), Spinner Assembly Maintenance Instruction

Guide, for requirements and procedures for repairing spinner assemblies.

6. Guide Collar RePair

A. Replacement of Guide Collar Bushings

(1) Using care not to damage the guide collar, drill out the oversized
bushing(s)
I (2)
fI.)303(
the bushing(s) (303) being replaced is located at the split, drill out the

staking pin.
1 (3) Install A-116D-1bushing(s) (303). Refer to the Special Adhesive and
Bonding Procedures chapter of Hartzell Standard Practices Manual 202A
(61-01-02) for guide collar bushing replacement procedures.
1 (4) Install a new staking pin (307) if the bushing(s) (303)
A-114-C at the split
was replaced. Peen the end of the staking pin.
1 (5) Ream the bushing(s) (303) to 0.508 0.510 inch (12.90 12.95 mm) in
diameter.

the A-2038-12 socket head cap (305), if necessary.

1 (6) Replace screw

7. Hub Lug Reoair

A. Replacement of the A-1 23 Hub Lug Bushing

CAUTION: DO NOT DAMAGE HUB LUG.

(1) Drill out the bushing(s) (40), using care not to damage the hub lug.
I (2) Do not use an oil-based cleaning agent on the parts before bonding.
(3) Materials Refer to Hartzell Standard Practices Manual 202A (61 -01 -02)
Consumable Materials, Table 801:

(a) Adhesive CM96

(b) Solvent, CM11, CM22, CM41, CM44, CM106 or equivalent

(4) Preparation
(a) Remove (or verify the lack of) plating from the steel surface to be
bonded.

(b) Dip the hub lug in the approved solvent to remove oil, grease and other
contaminates.

REP~IR 61’10’00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CAUTION: DO NOT DIP THE BUSHING DIRECTLY INTO THE SOLVENT.

bushing (40), if necessary, by wiping with clean rag dipped in

I (c) Clean the a

the approved solvent.

(5) Installation

(a) Check the adhesive CM96 for expiration before use.

WARNING: THE APPROVED ADHESIVE IS AN EYE IRRITANT, AND

BONDS SKIN IN SECONDS. IN CASE OF EYE OR MOUTH
CONTACT, HOLD EYE LID OR MOUTH OPEN AND FLUSH
WITH WATER. IF FINGERS BECOME BONDED, APPLY
SOLVENT (ACETONE OR NAIL POLISH REMOVER) TO
CONTACT AREA AND CAREFULLY PRY SKIN APART.

WARNING; AVOID PROLONGED BREATHING OF VAPORS. USE WITH

ADEQUATE VENTILATION.

small amount of adhesive CM96 into a suitable container. The

I (a) Pour a

container must be deep enough to ensure that a minimum of 50 percent

of the bushing length is covered with adhesive.

I (b) Place one bushing (40) into the adhesive, coating at least one half
end of
of the bushing length. Immediately press the bushing into the hub lug bore
using a bushing application tool and a suitable press. A spindle of a
drill press works well for this application.

(c) Press the bushing (40) into the hublug with one continuous motion.
Intermittent movement of the bushing can cause the adhesive to fail.

(d) Remove excess adhesive with a clean, dry rag.

(6) Cure

(a) Adhesive CM96 attains fixture strength (20 percent of maximum

strength) in 30 60 seconds.
(b) Full bond strength is achieved in 24 hours.

(7) Inspection
I (a) Following the cure time, test the bushing (40) to 300 pounds (1334 N).

REPAIRG1’10’00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

(This page is intentionally blank.)

I RIPAIR 61’10’00
 PROPELLER MAINTENANCE MANUAL
H~ RTZ E L L 100E

CONTENTS

1. General 703

2. Specific Assembly and Installation Procedures 705

3. Blade and Mounting Parts Assembly 705

4. Installation of Blades and Clamps 711

5. Setting Blade Pitch 715

A. HC-D2V20-3 715

B. HC-D2MV20-3

C. HC-D3V20-6L 725

D. HC-D3MV20-6L 731

E. HC-D2(V, MV)20-7 and -8( 737

F. HC-D3MV20-8D 740

I G. Sealant CM93 Application All Models 743.2

6. Jack Plate and Hydraulic Piston Assembly 744

A. HC-D2(V, MV)20-3 and HC-D3(V, MV)20-6L

(Hydraulic Unit Assemblies 91-E and 91-6L) 744

B. HC-D(2, 3)(V, MV)20-7 and -8(

(Hydraulic Unit Assemblies 91-7DS, 91-8DS, and 91-8DT) 745

7. Valve Reassembly 746

A. Reassembly of B-93-D Valve 746

B. Reassembly of B-93-A, -B, -C Valve 746

C. Reassembly of B-93-AG, -BG, -CG Valve 746

D. Reassembly of B-93-E Valve 746

8. Installing the Propeller Assembly on the Aircraft 747

A. Model HC-D2V20-3 747

B. Model HC-D2MV20-3 751

C. Model HC-D3V20-6L 757

D. Model HC-D3MV20-6L 761

E. Models HC-D(2, 3)(V, MV)20-7 and -8( 767

F. Propeller Installation Troubleshooting

I HC-D2(V, MV)20-3 and HC-D3(V, MV)20-6L 772

~SSEMBLYG1’10’00
 PROPELLER MAINTENANCE MANUAL
H19 RTZ E L L 1 OOE

FIGURES

Hub Onto Rotatable Fixture Figure 701 704

Hub Arm Build-Up Figure 702 706

Blade and Mounting Parts Figure 703 708

CM93 Sealant Application Figure 704 710

Checking Blade Height Figure 705 714

Setup Spacer for HC-D2V20-3 Figure 706 715

Using Padded Blade Bar to Check for Blade Slippage Figure 707 716

Setup Spacer for HC-D2MV20-3 Figure 708 71 9

I Puller Ring Position Figure 708.1 723

Reverse Stop Travel Length Figure 709 724

Reverse Stop Travel Length and Reverse Stop Thickness Figure 710 730

Identification of 8-109-9( )Jack Plate Figure 711 736

Setup Spacer for HC-D2(V,MV)20-7 and -8 Figure 712 737

Setup Spacer for HC-D3MV20-8D Figure 713 740

Temporary Two-Piece Blade Spacer for HC-D3MV20-8D Figure 714 741

Figure 743.1
I Sealant CM93 Application 714.1

TABLES

Spacer Selection Table 701 752

61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

ASSEMBLY PROCEDURES

1. General

A. Unless instructed otherwise, lubricate all O-rings with lubricant CM12 before

installing them in the propeller assembly.

B. Refer to Hartzell Manual 202A (61-01-02), Standard Practices, for steel hub

assembly procedures.
C. Refer to Harttell Manual 133C (61-13-33), Aluminum Blade Overhaul, for blade bore

plug and blade bore bearing installation procedures.

D. Refer to Hartzell Manual 202A (61-01-02), Standard Practices, for blade clamp
assembly procedures.

E. Read all assembly instructions before beginning the assembly procedures.

WARNING: DURING ENGINE INSTALLATION OR REMOVAL, USING THE

PROPELLER TO SUPPORT THE WEIGHT OF THE ENGINE IS NOT
AUTHORIZED. UNAPPROVED INSTALLATION AND REMOVAL
TECHNIQUES MAY CAUSE DAMAGE TO THE PROPELLER WHICH
MAY LEAD TO FAILURE RESULTING IN AN Al RCRAFT ACCI DENT.

F. Be sure propeller is removed before engine is removed from or installed in the

ai rf rame

WARNING: WH EN REMOVING AN D INSTALLING THE PROPELLER, FOLLOW TH E

AIRFRAME MANUFACTURER’S MANUALS AND PROCEDURES, AS
THEY MAY CONTAIN ISSUES VITAL TO Al RCRAFT SAFETY THAT ARE
NOT CONTAI N E D IN HARTZELL OWN E R’S MAN UALS.

G. Follow the ai rf rame man ufactu re r’s instructions fo r instal ling and removi ng the p repel ler.
If such instructions are not in the airframe manufacturer’s manual, then follow the
instructions in the appropriate Hartzell PropellerOwner’s Manual. However, mechanics
must consider that the propeller owner’s manual does not describe important
procedures that are beyond Hartzell’s control. In addition to propeller installation
procedures, items such as rigging, installation and adjustment of de-ice equipment and
propeller synchronization devices are normally found in the airframe manufacturer’s
manuals.

ASSEMBLY 61 -1 0-00
 PROPELLER MAINTENANCE MANUAL
HARlrZELL 100E

NOTE: Centerline of base of Rotatable Fixture establishes

nPssaosa
station reference for setting blade angle.

Hub Unit
(2-bladed or 3-bladed)
G BST-2912-2 Spline Spindle TE122

Rotatable Fixture
’d As
ORIGINALATP
Received By

BST-2912

Hub Onto Rotatable Fixture

Figure 701

704
ASSEMBLY 61’10’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

2. SDecificAssemblvand Installation Procedures

A. Observe the following procedures for assembly and reinstallation of specific units and
assemblies.

NOTE: All item references are to Figures 1001 through 1025, unless otherwise
noted.

B. Blade and Spline Mounting Parts Assembly

Mount the hub unit the rotatable fixture of the assembly table as shown in Figure 701.
I
on

Tighten the shaft nut.

3. Bladeand Mounting PartsAssemblv

A. Assemblyforall models.

CAUTION: BE SU RE THE I NTE RNAL RECESS OF TH E BEARING GU IDE RING

FACES OUTBOARD WH EN THE G U IDE RING IS SLI PPE D OVE R
THE BLADE ARM FLANGE OF THE HUB UNIT.

(1) Use alight mallet and special tool TE309 (Figure 702) to drive a blade retention
I split-bearing guide ring (80) onto one blade arm flange of the hub unit (10).
NOTE: guide ring far enough onto the blade arm flange that the ring
Drive the
forms a narrow channel on the inboard surface of the flange.

(2) Repeat this guide ring installation procedure for the other blade arm flanges on the
I hub.

(3) Use lubricant CM12 to lightly grease the inboard surface of each blade arm
flange.
(4) Place the halves of an outboard bearing race (matched set) in position over one
I hubarm.

NOTE: The break-line for the bearing race halves should be perpendicular to
the table top.

(5) Use a combination of tools TE309 and TE108 to press theguide ring far enough
onto the outboard bearing race to allow insertion of the wire retention ring (70) into
the groove in the blade arm flange (Figure 702).

(6) Install the wire retention ring.

61 -1 0-00
 PROPELLER MINUAL
HARTZELL

APSO1Sla

Puller Tool
TE108(BT-223)

Tool TE309
(BST-3062)

Guide Ring
(80)

Split Bearing Race

(100)
Adapter Ring
BT-223-10
Hub Arm
Wire Retention Ring
(10)
(70)

Light Mallet

Guide Ring -------j(

(80)

TE309
(BST-3061)

Hub Arm (10)

Hub Arm Build-Up

Figure 702
ORIGINAL
As Received By
706
ATP 9~SSEMBLY 61’10’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL iooE

(7) Use tools TE309 and TE108 (Figure 702) to pull the bearing guide ring (80)
outboard far enough to allow the wire retention ring (70) and the guide ring (80) to
I contact each other. The wire retention ring will fit in the recess of the guide ring.

CAUTION: THE WIRE RETENTION RING MUST BE FULLY ENCLOSED TO

ENSURE IT IS NOT PINCHED.

(8) Check to make sure the wire retention ring is fully enclosed.
(9) Lubricate the blade O-ring (150) with lubricant CM12 and slide it over the blade
arm flange of the hub to a location inboard of the thrust bearing. Leave it there for
use later in thereassembly.
(10) Repeat Steps 3.A.(4) through 3.A.(9) for the remaining hub arms.
I (11) Remove the hub unit from the rotatable fixture on the assembly table and
to hold the hub unit shown in
use

special tool TE309 (Figure 702) as Figure 703.

NOTE: The arm of the hub

being fitted with bearing races must be facing down
so that the hub flange and guide ring form a "cavity" that will hold the

bearings.

WARNING: THE BREAK LINE OF THE BEARING-HALVES MUST BE AT A

RIGHT ANGLE TO THE BREAK LINE OF THE BLADE CLAMP-
HALVES.

CAUTION: ANY GAP BETWEEN THE HALVES OF THE OUTBOARD BEARING

RACE SHOULD BE NO GREATER THAN 0.001 INCH (0.025 mm).
I (12) Install the ball
the outboard
bearing spacer(l30) and the required number of bearing balls onto
bearing races, taking care not to scratch the races.
(13) Apply a slight amount of sealant CM93 to the broken edges of the inboard bearing
I race (matched set). Wipe clean any excess sealant that may extrude into the

bearing area when the bearing halves are joined.

1 (14) Place the inboard halves of the bearing race around one blade arm of the hub unit
and install the wire bearing ring (140) to hold the halves in place.
retention

CAUTION: THE OPENING OF THE RETENTION RING MUST BE AT A RIGHT

ANGLE TO THE PARTING LIN E OF TH E INBOARD BEARING RAC E.

1 (15) Apply a small bead of sealant CM93 to the inboard bearing race at the chamfer
(break point) in order to evenly fill the void in the chamfered area of the race.

ASSEMBLY S1 ’1 0’00
 PROPELLER MAINTENANCE MANUAL
H19 RT Z E L L 1 OOE

APS0213
APS8131
APS5014A I
Blade Assembly

BallBearing
Spacer

~bpm-8s,nnl
Bearing
Retention
Ring
O-Ring

Hub

o "Cavity" where split

_
bearing halves
will be installed

Tool TE309
(BST-3062)

O-ring
Ball spacer
Ring

Bearing

Bearing installation Bearing race chamfer

Blade and Mounting Parts

Figure 703
ORIGINAL
As Received By
708
ATP
ASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

CAUTION: EXCESSIVE USE OF SEALANT COULD CAUSE UNEVEN

SEATING BETWEEN BLADE CLAMP AND BEARING RACE.

O-ring (150) outboard into place against the bearing

I (16) Slide the blade race.

(17) Wrap wide masking tape around the outside diameter of the bearing assembly to
hold the parts in place.

I (1 8) Repeat these assembly procedures for each of the other blade arms on the
.tinubuh

709
ASSEMBLY 61 ’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

APS0417
APSO426a

Or 0.1875in.
(4.763mm)~d
CM93

0.3750 in. (9.525 mm)

~dT
CM46

Enlarged View

CM93

CM93

ORIGINAL
As Received By
ATP

CM93 Sealant Application

Figure 704

nssalVlelY 61-10’00
 PROPELLER MAINTENANCE MANUAL
HARTZELL iooE

4. Installation of Blades and Clamps

A. Installationforall models

APPLICABLE, EACH BLADE SHOULD BE REINSTALLED ON

I CAUTION: IF
THE HUB ARM FROM WHICH IT WAS REMOVED AT
DISASSEMBLY.

(1) As specified in the Disassembly Procedure, each blade should have an

identifying number to ensure correct assembly.

(2) Turn thepropeller on the rotatable fixture and using a gage and adjustable pointer

I (3)
as shown in Figure 705, check the height at the tip of each blade

NOTEI Blade heights at the tip should not vary more than 0.06 inch

Stand Blade One in vertical position (base up, tip down) and fill the pilot tube
cavity with grease CM12 to the top of the bottom (inboard) bearing race level.
(1.5 mm).

Referto Hartzell Standard Practices Manual 202A, Propeller Lubrication chapter,

I for lubrication guidelines.

WARNING: AIR TRAPPED IN THE GREASE CAN AFFECT PROPELLER

BALANCE AFTER RUN-UP.

(4) making sure no air is trapped

After in the grease, press the blade onto the
1
matching hub pilot tube.
NOTE: A slight amount of grease will ooze out around the pilot tube if the blade
has been lubricated correctly.

(5) In consecutive order, repeat the lubrication and reinstallation procedure for the
remaining blades.

CAUTION: BE SURE TO USE APPROVED HARDENING GASKET COMPOUND

ON THE SHOULDER RADIUS OF THE BLADE BASE.

Spread approved gasket compound CM46 the shoulder radius of the blade
1 (6) on

base in the area where it will be in contact with the blade clamp. Refer to Figure
704.

NOTE: A bead ofgasket compound CM48 approximately 0.25 inch ~6.4 mm)
wide and 0.06 inch (1.5 mm) thick is sufficient.

CAUTION: THE PARTING LINE OF THE CLAMP HALVES MUST BE AT A

RIGHT ANGLE TO THE PARTING LINE OF THE I NBOARD BEARING
RACE.

1 (7) Place a gasket (430) between each of the clamp half parting surfaces.

*SSEMBLY 61-1 0-00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

(8) Permit a (1.59 mm) of gasket material to be evenly

maximum of 0.06 inch
exposed through the edges on each blade clamp-half parting surface.

CAUTION: M ETAL-TO-M ETAL CONTACT IS N ECESSARY WH E RE TH E

INBOARD CLAMP LUGS MEET.

(9) Trim the gasket material as necessary to permit metal-to-metal contact where the
clamp lugs meet.

CAUTION: DO NOT TORQUE THE OUTBOARD CLAM P BOLTS AT THIS

STAG E OF ASSEMBLY.

1 (10) Insert the outboard clamp bolts (450) and clamp washers (460) and fasten them
with clamp nuts (470). Hand tighten.

NOTE 1: This step helps align the clamp gasket.

NOTE 2: If the standard clamp bolt installation causes interference with the
spinner dome, reverse the position of the outboard clamp bolt (450).
Install the leading edge bolt in the clamp with the head of the bolt
located on the counterweight side of the clamp. Only one clamping bolt
per clamp (adjacent to blade leading edge) is reversed. Refer to
Figure 704.1.

CAUTION: TORQUE THE INBOARD CLAMP SOCKET SCREWS IN THE

SEQUENCE SPECIFIED.

(1 1) Insert the inboard clamp socket screws (420).

CAUTION: DO NOT EXCEED 40 FT-LB (54 N´•m) TORQUE ON INBOARD

CLAMP SOCKET SCREWS.

(12) Torque each inboard clamp socket screw in increments of 10 ft-lb (14 N´•m) to the
required torque. Refer to the Torque Table in the Fits and Clearances chapter of
this manual.

CAUTION: DO NOT TOUCH TH E CLAM P WITH TH E DRI LL WH ILE DRILLING TO

SAFETY THE INBOARD CLAMP SOCKET SCREWS.

(13) With a #42 (0.0935 inch [2.375 mml) drill bit, drill the head of each inboard clamp
socket screw.

1 (14) Safety each socket screw with three loops of 0.032 inch (0.81 mm) safety wire or
cotter pin.

(1 5) Repeat the blade clamp installation procedures for the remaining propeller
blades.

1 (16) Check the rotational freedom of each blade on the pilot tube of the hub.

ASSEMBLY 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

W1W17

Nut (470)
Q Washer (460)

Bolt (450), Reversed

CounteMleight Half
of the Clamp

Counterweight

Clamp with the Outboard Leading Edge Clamp Bolt in the Reversed Position
Figure 704.1

,,,,,,Y 61 -1 0-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

APS0094

I NOTE: Figure for purpose of illustrating the procedure for checking

blade height.

Propeller mounted on assembly table

NOTE: Blade height at the tips

should not vary
more than

0.06 inch (1.5 mm).

Height gage with adjustable pointer

Checking Blade Height

Figure 705

~ISSEMILY 61-10-00
 PRQPELLER MAINTENANCE MANUAL
HA.RT Z E L L 100E

5. Setting Blade Pitch

A. HC-D2V20-3

(1) Make an aluminum or steel setup spacer with an inside diameter larger than the

hub and an outside diameter small enough that the spacer does not interfere with
the clamps (Figure 706). The thickness of the spacer must be 1 .093 0.010 inch
(27.76 0.25 mm).
NOTE: The setup spacer is used only for set up. The setup spacer is not used
when installing the propeller on the ai rcraft.

(2) Put the jack plate unit (770) over and around the rotatable fixture on the build table.
Repeat with the setup spacer. Rest the unit and the spacer on the table.
(3) Mount the hub unit on the rotatable fixture of the assembly table as shown in Figure
701.

MAKE SURE THE POSITION OF THE PULLER RING (160) IS

I CAUTION:
CORRECT. REFER TO FIGURE 708.1

(4) Install the hub nut (1 80) and the puller ring (160).
(5) Tighten the hub nut(l80).
(6) Install the snap ring (1 70) inside the groove in the hub (10) and encircling the hub
nut (1 80).
(7) Lift the jack plate unit (770) into position.
(8) Line up the push rods (800) with the holes in the guide lugs (60) that are welded to
the hub.

APS6138

Inside diameter

I
0.010 inch
I 1.093
(27.76 0.25 mm)

f
Outside diameter

Setup Spacer for HCID2V20-3

Figure 706

ASSEMBLYG1’10’00
 PROPELLER MAINTENANCE MANUAL
RTZ E L L 100E

NOTE: Figure illustrates the process for checking blade slippage

in propeller models with blade clamps.

Fully assembled
propeller

Padded blade bar

close to blade shank

Suitable weight at p~osition

fortorquing blade assembly
to:

~67 Ft-Lb (226 N´•m)

for aluminum blade

Using Padded Blade Bar to Check for Blade Slippage

Figure 707

ASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CAUTION: MAKE SURE THE BLOCK (220) HAS A SLIDE FIT IN THE FORK.
BEVEL THE BLOCK TO ALLOW HUB CLEARANCE.

(9) Rotate the blades until the forks (810) slide onto the blocks (220) and the push
rods (800) enter the guide lugs (60).
1 (16) Move the jack plate unit (770) away from the table until the 1 .093 inch (27.76 mm)
thick setup spacer is pinched between the jack plate (770) and the spacer ring
(320) that is already pressed onto the hub shoulder. This defines the high blade
pitch position for the blade clamps.
(1 1) Rotate the blades in the clamps to low pitch position.
NOTE: Refer to theapplicable aircraft Specifications Manual or Hartzell
Application Guide for the specific angle required.

CAUTION: LOW PITCH BLADE ANGLE MUST BE WITHIN rt 0.5 DEGREE OF

THE CORRECTSETTING.

1 (12) Set low pitch with the jack plate unit (770) in full forward position against the setup
spacer and the hub.

(13) Torque the outboard clamp nuts. Referto the torque table in the Fits and
Clearances chapter of this manual.

CAUTION: LOW PITCH BLADE ANGLE OF ALL BLADES MUST BE WITHIN A

TOLERANCE OF 0.1 DEGREE OR A MAXIMUM OF 0.2 DEGREE
VARIANCE FROM EACH OTHER.

(14) Check low pitch blade angle of all blades within a tolerance of 0.1 degree or a
maximum of 0.2 degree variance from each other. If blades do not meet tolerance,
reset the blades in the clamps.

(15) Using a padded blade bar, check blade tightness in the clamp by applying a
torque of 167 ft-lb (226 N´•m) to the blade near the blade root (Figure 707).
NOTE: Checking blade tightness ensures that a blade will not slip in flight.

(16) Recheck blade angles to assure no slippage has occurred.

(17) Turn the propeller on the rotatable fixture. Using a gage and adjustable pointer as
shown in Figure 705, check the height at the tip of each blade

NOTE: Blade heights at the tip should not vary more than 0.06 inch (1 .5 mm).

61 -1 0-80
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 100E

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIMILARLY IDENTIFY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OF TH E PROPELLE R.

(18) Using a crayon or a soft, non-graphite pencil, mark the position of the jack plate
unit (770) in relation to the hub

NOTE: Marking the jack plate-to-hub position will make sure that the correct
orientation is maintained when assembling on the aircraft and engine.
(1 9) Pull the jack plate unit (770) toward the table.
(20) Rotate the jack plate unit (770) and disengage the forks (810) from the blocks
(220).
(21) Identify the block (220) location and orientation for installation of the propeller on
engine.
(22) Remove the jack plate unit (770) and the setup spacer from the propeller.
NOTE: The setup spacer is used only during set up. The setup spacer is not
used when installing the propeller on the aircraft.

(23) Remove the propellerfrom the build bench.

1 (24) Static balance the propeller in accordance with the Static Balance chapter of
Hartzell Standard Practices Manual 202A (61-01-02).

(a) Static balance will require a jack plate only to hold blades relative to each
other.

(b) Insert plastic or aluminum.wedges between the blade clamps and the hub.

(c) Use fixturing with a rear cone and a front nut to support the propeller for
balancing.
(25) Affix one label TOR-504 to the OD of one of the blade clamps.

CAUTION: ON A REPUBLIC SEABEE INSTALLATION A CLAMP LUBRICATION

FITTING MAY INTERFERE WITH THE PISTON MOUNTED VALVE.
TO AVOID DAMAG ING TH E VALVE, I NSTALL A LU BRICATION
PLUG (400) IN THE CLAMP HOLE FACING THE ENGINE, AT
OVERHAUL AFTER LUBRICATION.

(26) Lubricate the propeller in accordance with the Propeller Lubrication chapter of
Hartzell Standard Practices Manual 202A (61-01-02).

ASSEYBLY 61’10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL ioo~

B. HC-D2MV20-3

(1) Make an aluminum or steel setup spacer with an inside diameter of 3.25 inches

(82.55 mm) and an outside diameter of 3.50 inches (88.9 mm). The thickness of
the spacer must be 1.060 0.010 inch (26.92 ~t 0.25 mm) (Referto Figure 708).
NOTE 1: To make it easier toposition the setup spacer on the hub, cut the setup
spacer into two equal pieces.
NOTE 2: The setup spacer is used only for set up. The setup spacer is not used
when installing the propeller on the aircraft.

Put the jack plate unit (770) and around the rotatable fixture the build table.
(2) over on

Repeat with the setup spacer. Rest the unit and the spacer on the table.

(3) Mount the hub unit on the rotatable fixture of the assembly table as shown in Figure
701.

MAKE SURE THE POSITION OF THE PU LLER RING (160) IS

I CAUTION:
CORRECT. REFER TO FIGURE 708.1

(4) Install the hub nut (1 80) and the puller ring (160).
(5) Tighten the hub nut(l 80).
Install the snap ring (170) inside the groove in the hub (10)and encircling the hub
(6)
nut(l 80).
(7) Lift the jack plate unit (770) into position.
(8) Line up the push rods (800) with the holes in the guide lugs (60) that are welded to
the hub.

APS6138

Inside diameter

I
1.060 0.010 inch
(26.92 It 0.25 mm)

f
Outside diameter

Setup Spacer for HC-D2MV20-3

Figure 708

61-10-00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

CAUTION: MAKE SURE THE BLOCK (220) HAS A SLIDE FIT IN THE FORK.
BEVEL THE BLOCK TO ALLOW HUB CLEARANCE.

(9) Rotate the blades until the forks(810) slide onto the blocks (220) and the push
rods (800) enter the guide lugs (60).

(10) Move the jack plate unit (770) away from the table until the jack plate (770)
contacts the spacer ring (320) that is already pressed onto the hub shoulder. This
is the reverse blade pitch position for the blade clamps.

(1 1) Rotate the blades in the clamps to -1 1 .5 ´•t 0.5 degrees. This is the reverse blade
angle for the propeller.
NOTE 1: Use of a rubber mallet to rotate the blade in the clamp is
acceptable.
NOTE 2: Propellers assembled in accordance with this procedure will not
meet the Aircraft Type Certificate Data Sheet (TCDS)
specification for reverse blade angle. An FAA form 337 is
req u i red to return the propel le r/ai rcraft to service. (I nstallation of
"MV" shank blade clamps requires the non-standard reverse
blade angle for clearance purposes.)

(12) Torque the outboard clamp nuts. Refer to the torque table in the Fits and
Clearances chapter of this manual.

CAUTION: LOW PITCH BLADE ANGLE OF ALL BLADES MUST BE WITHIN A

TOLERANCE OF 0.1 DEGREE OR A MAXIMUM OF 0.2 DEGREE
VARIANCE FROM EACH OTHER.

(13) Check that the reverse pitch blade angle of all the blades is within a tolerance of
0.1 degree or a maximum of 0.2 degree variance from each other. If blades do not
meet the tolerance, reset the blades in the clamps and recheck the reverse pitch.

(14) Using a padded blade bar, check blade tightness in the clamp by applying a
torque of 167 ft-lb (226 N´•m) to the blade near the blade root (Figure 707).
NOTE: Checking blade tightness ensures that a blade will not slip in flight.
(15) Recheck blade angles to assure no slippage has occurred.

(16) Move the jack plate(770) toward the table to allow clearance to place the two-
piece set-up spacer between the jack plate and the spacer ring (320).
(1 7) Move the jack plate unit (770) away from the table until the jack plate pinches the
set-up spacer against the spacer ring (320) that was previously pressed onto the
hub shoulder. This is the high pitch position forthe blade clamps.

61-10-00
 I
PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

Measure the high pitch blade angle to confirm that it is a minimum of 19.5
(18)
degrees.

CAUTION: HIGH PITCH BLADE ANGLE OF BOTH BLADES MUST BE WITHIN

A TOLERANCE OF 0.1 DEGREE OR A MAXIMUM OF 0.2
DEGREE VARIANCE FROM EACH OTHER.

(19) Check the high pitch angle of both blades to confirm they are within a
blade
If
tolerance of 0.1 degree or a maximum of 0.2 degree variance from each other.
blades do not meet tolerance, reset the blades in the clamps and recheck the high
pitch blade angle.
NOTE: acceptable to have greater than 0.2 degree variance at
It is
reverse if required to maintain a maximum of 0.2 degree
variance
at high pitch.

(20) Turn the propeller on the rotatable fixture. Using a gage and adjustable pointer as
shown in Figure 705, check the height at the tip of each blade

NOTE: Blade heights at the tip should not vary more than 0.06 inch (1 .5 mm).

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARKOR SIMILARLY IDENTIFY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OFTHE PROPELLER.

(21) Using a crayon or a soft, non-graphite pencil, mark the position of the jack plate
unit (770) in relation to the hub.

NOTE: Marking the jack plate-to-hub position will make sure that the correct
orientation is maintained when assembling on the aircraft and engine.

(22) Pull the jack plate unit (770) toward the table.
(23) Rotate the jack plate unit (770) and disengage the forks (810) from the blocks
(220).
the
(24) Identify block (220) location and orientation for installation of the propeller on
engine.
(25) Remove the jack plate unit (770) and the setup spacerfrom the propeller.
NOTE: The setup spacer is used only during set up. The setup spacer is not
used when installing the propelleron the aircraft.

(26) Remove the propellerfrom the build bench.

Practices
(27) Static balance the propeller in accordance with Hartzell Standard
Manual 202A (61-01-02), Chapter 600, Static and Dynamic Balance.

ASSEMBLYG1’10’00
 PROPELLER M~NUAL
HARTZELL

(a) Static balance will require a jack plate only to hold blades relative to each
other.

I (b) Insert plastic or aluminum wedges between the blade clamps and the hub.
(c) Use fixturing with a rear cone and a front nut to support the propeller for
balancing.

CAUTION: ON A REPUBLIC SEABEE INSTALLATION A CLAM P LU BRICATION

FITTING MAY INTERFERE WITH THE PISTON MOUNTED VALVE.
TO AVOID DAMAGING THE VALVE, INSTALL A LUBRICATION
PLUG (400) IN THE CLAMP HOLE FACING THE ENGINE, AT
OVERHAULAFTER LUBRICATION.

(28) Affix one label TOR-504 to the OD of one of the blade clamps.
(29) Lubricate the propeller in accordance with the Propeller Lubrication chapter of
Hartzell Standard Practices Manual 202A (61-01-02).

ASSEMBLY 61’10’00 RevP2aSJeun:02:

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1000

W10440

Hub (10)

PLiller Ring (160) Snap Ring(l70)

Hub Nut (180)

Puller Ring Position

Figure 708.1

6~SSEMBLY 61 -1 0-00
 PROPELLER
HARTZELL M*I1NOSENANCE MANUAL

APS6132

Reverse Stop
(313)
Fork I I Washer
(31 0) (31 4)
Travel

Nut

Sleeve
(315)
(312)
Guide Collar
(300)

Reverse Stop Travel Length

Figure 709

ASSEMBLY 61-10-00 Rev. 1 Apr/GOPage 724

 PROPELLER MAINTENANCE MANUAL
H~A RTZ E L L 1006

I C´• HC-D3V20-6L

NOTE: High pitch is set when on the assembly table, but reverse pitch is only
checked (not set) for reverse stop.

(1) Put the hydraulic unit (500) over the fixture on the build table and rest the unit on
the table.

Mount the hub unit on the rotatable fixture of the assembly table as shown in Figure
I (2)

CAUTION: THE THICK ARM OF THE PITCH CHANGE BLOCK MUST BE

TOWARD THE ENGINE.

(3) Install a fork (810) on each push rod (800). Do not tighten the set screw (830).

(4) Put a sleeve (312) on each of the push rods (800) with the flange-end of the sleeve
toward the jack plate and the fork.

CAUTION: THE REVERSE STOP (313) ON THE PUSH ROD (800) WILL
PREVENT THE SLEEVE (312) FROM PUSHING THE GUIDE
COLLAR BUSHING OUT OF THE GUIDE COLLAR.

(5) Locate a reverse stop (313) that meets the required length for your propeller.
Reverse stop width is selected to obtain reverse pitch and is determined by the
amount of travel required from reverse pitch to high pitch. Each degree equals

1 1/32 inch (0.031 inch [0.79 mrn]) in length.

NOTE: Example:
Reverse pitch 11 degrees
High pitch 20 degrees
Total travel 31 degrees 31/32 inch (0.969 inch [2.46 mml) of travel
Reverse stop (31 3) thickness must allow the calculated travel length
between the reverse stop setting on the shoulder of the sleeve (31 2)
and the guide collar (300). See Figure 709.
I
(6) Slide a reverse stop (313) on each sleeve (312) and push rod (800).

CAUTION: MAKE SURE THE BLOCK (220) HAS A SLIDE FIT IN THE FORK.
BEVEL THE BLOCK TO ALLOW HUB CLEARANCE.

Install the pitch change block (220) onto each clamp linkscrew (380).
I (7)
(8) Lift the jack
blocks.
plate unit (770) into position on the hub to engage the pitch change

(9) Rotate the blades until the forks (810) can slide onto the blocks (220).

,,,,,,,,61 -1 0-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

(10) Align the forks (810) with the pitch change blocks (220) and snug the set screws
(830) in the forks.
NOTE: Do not peen the fork to set the screw because the fork will be removed
after assembly is complete. Safety procedure is accomplished after
installation on the engine.

(1 1 Install the
guide collar (300) by positioning it over the push rods (800) so the push
rods pass through the guide collar bushings. Maintain the alignment of the fork
(810) and pitch change block (220).
(12) 1 nstall and torq ue the guide collar nut (3 1 O). Ref er to torq ue table in chapter 800.
(13) Tighten the guide collar (300) against the shoulder on the guide collar nut (310).
(14) Install a washer (31 4) and a nut (315) on the end of each push rod protruding
th rough the gu ide collar bush i ngs.

(15) Loosen the set screws (830) in the fork (810).

(1 6) Tighten the nuts (31 5) until snug.
NOTE: Do not peen the fork to set the screw because the fork will be removed
after assembly is complete. Safety procedure is accomplished after
installation on the engine.

(17) Position each fork (810) to fully engage the pitch change blocks (220).
(18) Pull the jack plate unit (770) back toward the table rotating the clamps to a high
pitch position.
NOTE: When the propeller is at high pitch, the nuts (315) and washers (314) on
the end of thepush rods will be firmly against the guide collar (300).
(10) Rotate the blades in the clamps to high pitch position.
NOTE: Refer to theapplicable aircraft Specifications Manual of Hartzell
Application Guide for the
specific angle required.

CAUTION: HIGH PITCH BLADE ANGLE MUST BE WITHIN 0.5 DEGREE OF

TH E CORRECT S ETTI NG.

(20) Torque the outboard clamp nuts. Referto the torque table in Chapter 800.

ASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

I CAUTION: HIGH PITCH BLADE ANGLE OF ALL BLADES MUST BE WITHIN A

TOLERANCE OF 0.1 DEGREE OR A MAXIMUM OF 0.2 DEGREE
VARIANCE FROM EACH OTHER.

(21) Check high pitch angle of all blades within a tolerance of ~t 0.1 degree or a
blade
maximum of 0.2 degree variance from each other. If blades do not meet tolerance,
reset the blades in the clamps and re-check the high pitch blade angle.

(22) Using a padded blade bar, check blade tightness in the clamp by applying a
torque of 167 ft-lb (226 N´•m) to the blade near the blade root (Figure 707).
NOTE: Checking blade tightness ensures that a blade will not slip in flight.

(23) Recheck the blade angles to assure no slippage has occurred.

(24) Turn the propeller on the rotatable fixture. Using a gage and adjustable pointer as
shown in Figure 705, check the height at the tip of each blade.

NOTE: Blade heights at the tip should not vary more than 0.06 inch (1 .5 mm).

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIMILARLY IDENT1FY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OFTHE PROPELLER.

(25) Mark the position of the jack plate unit (770) using a crayon or a soft, non-graphite
pencil.
(26) Remove the nuts (31 5) and washers (314) from the push rods (800).
Mark the forks (810), (312), reverse stops (31 3), and jack plate push
sleeves rods
(27)
(800) to insure correct matching of parts when installed on engine.
(28) Pull the jack plate unit (770) toward the table allowing the sleeve (31 2), reverse

stop (313), and fork (810) to slide off each push rod (800).
(29) Remove forks (810), sleeves (312) and reverse stops (313) and slide on

appropriate push rod (800).

(30) Install a washer (31 4) and nut (315) on the end of each push rod (800).
I NOTE: Tighten the nut enough that it does not come off the end of the push rod.
This will keep the parts together.

.,,,,,,,61 -10-00
 PROPELLER MAINTE NANCE MANUAL
HA RTZ E e L 100E

CAUTION: DO NOT ETCH, SCRIBE, PU NCH MARK O R SI M ILARLY I DENTI FY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OFTHE PROPELLER.

(31) Identify the block (220) location and orientation for installation of the propeller on
the engine.

(32) Remove the block (220) and keep it with the propeller.
1 (33) Static balance the propeller in accordance with the Static Balance Chapter of
Hartzell Standard Practices Manual 202A (61-01-02),

(a) Static balance will require a jack plate only to hold blades relative to each
other.

(b) Insert plastic or aluminum wedges between the blade clamps and the hub.
(c) Use fixturing with a rear cone and a front nut to support the propeller for
balancing.

CAUTION: ON A REPUBLIC SEABEE INSTALLATION A CLAM P LUBRICATION

FITTING MAY INTERFERE WITH THE PISTON MOUNTED VALVE.
TO AVOID DAMAG ING TH E VALVE, INSTALL A LUBRICATION
PLUG (400) IN THE CLAMP HOLE FACING THE ENGINE, AT
OVERHAULAFTER LUBRICATION.

(34) Affix one label TOR-504 to the OD of one of the blade clamps.
(35) Lubricate the propeller in accordance with the Propeller Lubrication chapter of
Hartzell Standard Practices Manual 202A (61-01-02),

ASSEMBLY 61-10’00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

(This page is intentionally blank.)

Page 729
I PISSEMsLYG1-1 0-00 Rev. 1Apr/GO
 PROPELLER
HARTZELL MA:F~EFNANCE
E001LAUNAM

APS6132

Reverse Stop
(31 3)
Fork I I Washer
(810) (31 4)
Travel

Nut

Sleeve (315)
(312)
Guide Collar
(300)
ORIGINAL
As Received By
ATP

HSSPACE.XLS

PART NO. "A" DIMENSION wlo29s

A-970-10 0.300 inch ~7.62 mrn

A-970-9 0.270 inch (6.85 mm

A-970-8 0.240 inch (6.09 mm

A-970-7 0.210 inch (5.33 mm

A-970-6 0.180 inch 14.57 mm

A-970-5 0.150 inch (3.81 mm

A-970-4
A-970-3
A-970-2
A-970-1
0.120 inch (3.04
0.090 inch 12.28
0.060 inch (1.52
0.030 inch (0.76
mm

mrn

mm

m
--II--´•
Reverse Stop Travel Length and Reverse Stop Thickness
Figure 710

A~BEMBLY ~1’10’00 Rev. 1 Apr/GOPage 730

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

D. HC-D3MV20-6L

NOTE: High pitch is set when on the assembly table, but reverse pitch is only
checked (not set) for reverse stop.

CAUTION: USE THE HYDRAULIC UNITTHATWILL BE USED DURING FLIGHT.

THE HYDRAULIC UNIT MUST CONSIST OF THE JACK ASSEMBLY
(770) AND PISTON (510) WITH THE ATTACHED VALVE ASSEMBLY
(1000).

NOTE: A fit check between the bladeclamp assemblies and the valve assembly is
performed later in the assembly process.
Put the hydraulic unit (500) over the fixture on the build table and rest the unit on
(1)
the table.

(2) Mount the hub unit on the rotatable fixture of the assembly table as shown in Figure
701 Tighten the shaft nut.

CAUTION: THE THICK ARM OF THE PITCH CHANGE BLOCK MUST BE

TOWARD TH E ENGINE.

(3) Install a fork (810) on each push rod (800). Do not tighten the set screw (830).

(4) Put a sleeve (312) on each of the push rods (800) with the flange-end of the sleeve
toward the jack plate and the fork.

CAUTION: THE REVERSE STOP (313) ON THE PUSH ROD (800) WILL
PREVENT THE SLEEVE (312) FROM PUSHING THE GUIDE
COLLAR BUSHING OUT OF THE GUIDE COLLAR.

(5) Locate a reverse stop (31 3) that meets the required length for your propeller.
Reverse stop width is selected to obtain reverse pitch and is determined by the
amount of travel required from reverse pitch to high pitch. Each degree equals
1/32 inch (0.031 inch [0.79 mml) in length.
NOTE: Example:
Reverse pitch 11 degrees
High pitch 20 degrees
Total travel 31 degrees 31/32 inch (0.969 inch [2.46 mml) of travel
Reverse stop (31 3) thickness must allow the calculated travel length
between the reverse stop setting on the shoulder of the sleeve (312)
and the guide collar (300). See Figure 710.

AssEMBLYG1 ’1 0’00
HARTZ a LL PROPELLERMA:No~EEN"NCE MANUAL

(6) Slide a reverse stop (313) on each sleeve (312) and push rod (800).

CAUTION: MAKE SURE THE BLOCK (220) HAS A SLIDE FIT IN THE FORK.
BEVEL THE BLOCK TO ALLOW HUB CLEARANCE.

(7) Install the pitch change block (220) onto each clamp linkscrew (380).
(8) Lift the jack plate unit (770) into position on the hub to engage the pitch change
blocks.

(9) Rotate the blades until the forks (810) can slide onto the blocks (220).
(10) Align the forks (810) with the pitch change blocks (220) and snug the set screws
(830) in the forks.
NOTE: Do not peen the fork to set the screw because the fork will be removed
after assembly is complete. Safety procedure is accomplished after
installation on the engine.

(1 1) Install the guide collar (300) by positioning it overthe push rods (800) so the push
rods pass through the guide collar bushings. Maintain the alignment of the fork
(810) and pitch change block (220).
(1 2) Install and torque the guide collar nut (310). Refer to torque table in chapter 800.
(13) Tighten the guide collar (300) against the shoulder on the guide collar nut (31 0).
(14) Install a washer (314) and a nut (315) on the end of each push rod protruding
th rough the guide col lar bushings.

(15) Loosen the set screws (830) in the fork (810).

(1 6) Tighten the nuts (31 5) until snug.
NOTE: Do not peen the fork to set the screw because the fork will be removed
after assembly is complete. Safety procedure is accomplished after
installation on the engine.

(17) Position each fork (810) to fully engage the pitch change blocks (220).
(1 8) Pull the jack plate unit (770) back toward the table rotating the clamps to a high
pitch position.
NOTE: When the propeller is at high pitch, the nuts (315) and washers (314) on
the end of the push rods will be firmly against the guide collar (300).
(19) Rotate the blades in the clamps to high pitch position.
NOTE: Refer to theapplicable aircraft Specifications Manual of Hartzell
Application Guide for the
specific angle required.

ASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
RT Z LL 100E

CAUTION: HIGH PITCH BLADE ANGLE MUST BE WITHIN 0.5 DEGREE OF

THE CORRECT SETTI NG.

(20) Torque the outboard clamp nuts. Refer to the torque table in Chapter 800.

CAUTION: HIGH PITCH BLADE ANGLE OF ALL BLADES MUST BE WITHIN A

TOLERANCE OF 0.1 DEGREE OR A MAXIMUM OF 0.2 DEGREE
VARIANCE FROM EACH OTHER.

(21) Check high pitch blade angle of all blades within a tolerance of 0.1 degree or a
maximum of 0.2 degree variance from each other. If blades do not meet tolerance,
reset the blades in the clamps and re-check the high pitch blade angle.

(22) Using a padded blade bar, check blade tightness in the clamp by applying a

torque of 1 67 ft-lb (226 N´•m) to the blade near the blade root (Figure 707).
NOTE: Checking blade tightness ensures that a blade will not slip in flight.

(23) Recheck the blade angles to assure no slippage has occurred.

(24) Rotate the blades by hand to reverse pitch position.
NOTE: When the propeller is in reverse pitch position, the reverse stop washer
(313) is pinched between the guide collar (300) and the shoulder on the
sleeve (31 2).

(25) Slowly turn the propeller on the rotatable fixture to identify if there is clearance
between the blade clamp assemblies (330) and the valve assembly (1000).

(26) If there is interf erence, conti nue with step 5.D.(27). If there is interference
no

continue with the following steps:

(a) Identify a dimension required to space the clamp assembly (330) and valve
assembly (1000) apart and re-establish positive clearance.
(b) Increase the thickness of the stop (31 3) with the dimension required
reverse

to re-establish positive clearance between the clamp assembly (330) and the
valve assembly(1000).

1 Refer to Figure 710 for a listing of reverse stop thicknesses.

2 Select single stop with the required thickness, or several stops that
a

add up to the required thickness.

(c) Remove the nuts (31 5) and washers (314) from the ends of the three push
rods protruding from the jack assembly (770).
NOTE: Keep the nuts (315) and washers (314) with the propeller and jack
assembly.
(d) Twist the counterweights (340) toward high pitch so the push rods back out
of the guide collar bushings in the guide collar (300).

NOTE: Push rods will move toward the build bench.

.,,,,,,Y61-10-00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

(e) Allow the jack assembly push rods (800) to completely slide out of the guide
collar (300).

(f) Turn the jack plate unit (770) until the pitch change forks (81 0) disengage
from the pitch change blocks
(220).
(g) Install the stop (313) with the new dimension thickness onto the
reverse

sleeve (312) and push rod (800).

(h) Lift the jack plate unit (770) into position on the hub to engage the pitch
change blocks (220).
(i) Rotate the blades until the forks (810) can slide onto the pitch change blocks
(220).
(j) Align the push rods (800) and sleeves (312) with the guide collar bushings.
(k) Slide the push rods (800) and sleeves (312) through the guide collar
bushings.
(I) Install a washer (31 4) and nut (31 5) on the end of each push rod protruding
through the guide collar bushings
(m) Tightenthenuts(315) untilsnug.
(n) Rotate the blades by hand to reverse pitch position.
NOTE: When the propeller is in reverse pitch position, the reverse stop
washer (313) will be pinched between the guide collar (300) and
the shoulder on the sleeve (312)

to) Slowly turn the propeller on the rotatable fixture to verify if there is clearance
between the blade clamp assemblies (330) and the valve assembly(1000).

(27) Repeat steps 8.d.(24) through 8. D.(26)(o) until clearance between the blade
clamp assemblies (330) and the valve assembly (1000) is achieved.
(28) Turn the propeller on the rotatable fixture. Using a gage and adjustable pointer as
shown in Figure 705, check the height at the tip of each blade.

NOTE: Blade heights at the tip should not vary more than 0.06 inch (1 .5 mm).

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIM ILARLY IDENTI FY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OF TH E PROPELLE R.

(29) Mark the position of the jack plate unit (770) using a crayon or a soft, non-graphite
pencil.
(30) Remove the nuts (315) and washers (314) from the push rods (800).
(31) Mark the forks (810), sleeves (312), reverse stops (313), and jack plate push rods
(800) to insure correct match i ng of parts when installed on engine.

nsseMBLv 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

(32) (770) toward the table allowing the sleeve (312),

Pull the jack plate unit reverse

stop (313), and fork (810) to slide off each push rod (800).
(81 0), sleeves (312) and stops (31 3) and install the
I Remove forks reverse
(33)
appropriate push rod (800).
(34) Install a washer (314) and nut (315) on the end of each push rod (800).
rod.
NOTE: Tighten the nut enough that it does not come off the end of the push
This will keep the parts together.

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIMILARLY IDENTIFY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OFTHE PROPELLER.

(35) Identify the block (220) location and orientation for installation of the propeller on
the engine.

(36) Remove the block (220) and keep it with the propeller.
(37) Static balance the propeller in accordance with Hartzell Standard Practices
Manual 202A, Chapter 600, Static and Dynamic Balance.

(a) Static balance will require a jack plate only to hold blades relative to each
other.

(b) Use plastic or aluminum wedges to insert between the blade clamps and the
hub.

(c) Use fixturing with a rear cone and a front nut to support the propeller for
balancing.

CAUTION: ON A REPUBLIC SEABEE INSTALLATION A CLAMP LUBRICATION

FITTING MAY INTERFERE WITH THE PISTON MOUNTED VALVE.
TO AVOID DAMAGING THE VALVE, INSTALL A LUBRICATION
PLUG (400) IN THE CLAMP HOLE FACING THE ENGINE, AT
OVERHAUL AFTER LUBRICATION.

(38) Affix one label TOR-504 to the OD of one of the blade clamps.
of
(39) Lubricate the propeller in accordance with the Propeller Lubrication chapter
Hartzell Standard Practices Manual 202A (61-01-02).

.ss,,,,, 61-10-00 RevP2aSJeun:30~

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

APSGM)5A

8-109-9 Jack Plate

The cross-hatching represents the

area where material may or may not

be present.

The B-l 09-9 jack plate (thick) has

material in the cross-hatched area.

The B-l 09-9A (thin) does not have

material in the cross-hatched area.

B-l 09-9A Jack Plate

Identification of 81109-9( )Jack Plate

I Figure 711

736
61-10-00
 PROPELLER MAINTENANCE MANUAL
H RT r E L L 1 OOE

I E. HC-D2(V, MV)20-7 and -8(

(1) Make a setup spacer with an inside diameter larger than the hub and an outside
diameter small enough that the spacer does not interfere with the clamps (Figure
71 2). A setup spacer TE420 may be purchased for this purpose. Refer to Hartzell
I Tool and Equipment Manual 165A (61-00-65).

NOTE 1: The setup spacer is used only during set up and is not used when
installing the propeller on the aircraft.
NOTE 2: The hydraulic unit may have either a B-l 09-A or a B-l 09-9 jack plate
unit i nstalled (Figu re 71 1
I
The B-l 09-9A (thinnerjack plate) is used in the hydraulic unit (500) if
either a C-l 75 or C-l 75-2 spinner adapter ring is installed on the hub.

The B-l 09-9A is also used if a C-165-( ring is installed instead of a

spinner adapter ring. The C-l 75, the C-l 75-2, or the C-l 65-2 is press
fit onto the neck of the hub on the side facing the engine and against a
shoulder next to the blade arms.
If spinner adapter or 0-165-2 ring is installed on the hub, the
no 8-109-
9 (thickerjack plate) must be used in the hydraulic unit (500).

(2) Put the jack plate unit (770) and the setup spacer(s) over and around the rotatable
fixture on the build table. Rest the unit and the spacer on the table.

1 (3) Mount the hub unit on the rotatable fixture of the assembly table as shown in Figure
701.

APS6130

Inside diameter approximately

3.27 inch (82.9 mm)

0.125 inch
(3.17 mm)

Outside diameter approximately

3.53 inches (89.6 mm)

Setup Spacer for HCID2(V, MV)20-7 and -8

I Figure 712

61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 100E

MAKE SURE THE POSITION OF THE PULLER RING

I CORRECT. REFER TO FIGURE 708.1
(160) IS

(4) Install the hub nut (1 80) and puller ring (1 60).
(5) Tighten the hub nut(l 80).
(6) Install the snap ring (170) in the groove in the hub (10)and encircling the hub nut
(180).
(7) Lift the jack plate unit (770) into position.
(8) Line up the push rods (800) with the holes in the guide lugs (60) that are welded to
the hub.

CAUTION: MAKE SURE THE BLOCK (220) HAS A SLIDE FIT IN THE FORK.
BEVEL THE BLOCK TO ALLOW HUB CLEARANCE.

(9) Rotate the blades until the forks (810) slide onto the blocks (220) and the push
rods (800) enter the guide lugs (60).
(10) Move the jack plate unit (770) away from the table, rotating the clamps to a low
pitch position.
(1 1) Move the jack plate unit (770) until the 0.125 inch (3.17 mm) thick setup spacer is
pinched between the jack plate (770) and the spacer ring that is pressed onto the
hub shoulder. This is the low pitch position for the blade clamps.

(12) Rotate the blades in the clamps to low pitch position.

NOTE: Refer to the applicable aircraft Specifications Manual or Hartzell
Application Guide fsr the specific angle required.

CAUTION: LOW PITCH BLADE ANGLE MUST BE WITHIN 0.5 DEGREE OF

THE CORRECTSETTING.

(13) Set low pitch with the jack plate unit (770) in full forward position against the set up
spacer and the hub.

(14) Torque the outboard clamp nuts. Refer to the torque table in the Fits and
Clearances chapter in this manual.

CAUTION: LOW PITCH BLADE ANGLE OF ALL BLADES MUST BE WITHIN A

TOLERANCE OF 0.1 DEGREE OR A MAXIMUM OF 0.2 DEGREE
VARIANCE FROM EACH OTHER.

(15) Check low pitch blade angle of all blades within a tolerance of 0.1 degree or a
maximum of 0.2 degree variance from each other. If blades do not meet tolerance,
reset the blades in the clamps and recheck the low pitch blade angle.

~SSEMBLY 61-10-00
 PROPELLER MAINTENANCE MANUAL
H ~A RTZ F L L 100E

(16) Using a padded blade bar, check blade tightness in the clamp by applying a
torque of 167 ft-lb (226 N´•m) to the blade near the blade root (Figure 707).
NOTE: Checking blade tightness ensures that a blade will not slip in flight.
(17) Recheck blade angles to assure no slippage has occurred.
1 (18) Using gage and adjustable pointer as shown in Figure 705, turn the
a propeller on
the rotatable fixture and check the height at the tip of each blade

I NOTE: Blade heights at the tip should not vary more than c 0.06 inch (1 .5 mm).

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIMILARLY I DENTIFY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OFTHE PROPELLER.

1 (19) Using a crayon or a soft, non-graphite pencil, mark the position of the hydraulic
unit (500).

NOTE: Marking the jack plate-to-hub position will make sure that the correct
orientation is maintained when assembling on the aircraft and engine.

(20) Pull the jack plate unit (770) toward the table.
(21) Rotate the jack plate unit (770) and disengage the forks (810) from the blocks
(220).
(22) Remove the jack plate unit (770) and the setup spacer from the propeller.
NOTE: The setup spacer is used only during set up and is not used when
i nstal ii ng the propel le r on the ai re raft.

(23) Remove the propellerfrom the build bench.

(24) Static balance the propeller in accordance with Hartzell Standard Practices
Manual 202A, Chapter 600, Static and Dynamic Balance.

(a) Static balance will require a jack plate only to hold blades relative to each
other.

I (b) Use plastic or aluminum wedges to insert between the blade clamps and the
hub.

(c) Use fixturing with a rear cone and a front nut to support the propeller for
balancing.
(25) Affix label TOR-504 to the OD of a blade clamp.
I
one

(26) propeller in accordance with Hartzell Standard Practices

Lubricate the Manual
202A, Chapter 400, Propeller Lubrication.

.,,,,,,,61-10-00
 PROPELLER MAINTENANCE MANUAL
H119 RT Z E L L 100E

F. HC-D3MV20-8D

(1) Make a setup spacer with an inside diameter larger than the hub and an outside
diameter small enough that the spacer does not interfere with the clamps (Figure
71 3). A setup spacer TE420 may be purchased for this purpose. Refer to Hartzell
Tool and Equipment Manual 165A (61-00-65),

NOTE: The setup spacer is used only during setup and is not used when

installing the propeller on the aircraft.

(2) Put the jack plate unit (770) and the setup spacer(s) over and around the rotatable
fixture on the build table. Rest the unit and the spacer on the table.

(3) Mount the hub unit on the rotatable fixture of the assembly table as shown in Figure
701.

I CAUTION: MAKE SURE THE POSITION OF THE PULLER RING

CORRECT. REFER TO FIGU RE 708.1
(160) IS

(4) Install the hub nut (1 80) and puller ring (1 60).
(5) Tighten the hub nut (1 80).
(6) Install the snap ring (1 70) in the groove in the hub (10) and encircling the hub nut
(180).

APS6130

Inside diameter

0.125 inch
(3.17 mm)

Outside diameter

Setup Spacer for HCID3MV2018D

Figure 713

nsseM8Lv 61-10100
 PROPELLER MAINTENANCE MANUAL
H~RTZ ELL 100E

(7) Lift the jack plate unit (770) into position.

(8) Line up the push rods (800) with the holes in the guide collar (300).

CAUTION: MAKE SURE THE BLOCK (220) HAS A SLIDE FIT IN THE FORK.
BEVEL THE BLOCK TO ALLOW HUB CLEARANCE.

(9) Rotate the blades until the forks(810) slide onto the blocks (220) and the push
rods (800) enter the guide collar (300).

(10) Make atwo-piece temporary blade spacer 0.21 1 inch (5.35 mm) thick, with an OD
small enough not to inte rf ere with the hub and an ID large enough to fit around the
guide rod (550) (Figure 714).
NOTE: The two-piece blade spacer is to be temporarily installed between the
fork and the guide collar and used to position the pitch change
hardware when moving the blades in the clamps at low pitch. After the
blades are in position, the blade spacer is removed.

(1 1) Place the locally fabricated two-piece blade spacer on a guide rod (550).

(12) Move the jack plate unit (770) away from the table, rotating the clamps to a low
pitch position.
NOTE: The temporary two-piece blade spacer is positioned between the fork
and the guide collar.

W10287

0.211 inch
(5.35 mm)

Temporary Two-Piece Blade Spacer for HCID3MV20-8D

Figure 714

61-10-00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

(13) Move the jack plate unit (770) until the 0.125 inch (3.17 mm) thick setup spacer is
pinched between the jack plate (770) and the hub shoulder. This is the low pitch
position for the blade clamps.
(14) Rotate the blades in the clamps to low pitch position.
NOTE: Refer to the applicable aircraft Specifications Manual or Hartzell
Application Guide, Manual 159 (61-02-59) for the specific angle
required.

CAUTION: LOW PITCH BLADE ANGLE MUST BE WITHIN 0.5 DEGREE OF

THE CORRECT SETTI NG.

(15) Set low pitch with the jack plate unit (770) in full forward position against the set up
spacer and the hub.

(16) Torque the outboard clamp nuts. Refer to the torque table in the Fits and
Clearances chapter in this manual.

CAUTION: LOW PITCH BLADE ANGLE OF ALL BLADES MUST BE WITHIN A

TOLERANCE OF 0.1 DEGREE OR A MAXIMUM OF 0.2 DEGREE
VARIANCE FROM EACH OTHER.

(17) Check low pitch blade

angle of all blades within a tolerance of ~t 0.1 degree or a
maximum of 0.2 degree variance from each other. If blades do not meet tolerance,
reset the blades in the clamps.

(18) Using a padded blade bar, check blade tightness in the clamp by applying a

torque of 167 ft-lb (226 N´•m) to the blade near the blade root (Figure 707).
NOTE: Checking blade tightness ensures that a blade will not slip in flight.
(19) Recheck blade angles to assure no slippage has occurred.

(20) Remove th e two- pi ece temporary space r from the propel le r.

(21) Turn the propeller on the rotatable fixture and check the height at the tip of each
blade using a gage and adjustable pointer as shown in Figure 705.
NOTE: Blade heights at the tip should not vary more than -e 0.06 inch (1 .5 mm).

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIMILARLY IDENTIFY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OFTHE PROPELLER.

(21) Mark the position of the hydraulic unit (500) using a crayon or a soft, non-graphite
pencil.
NOTE: Marking the jack plate-to-hub position will make sure that the correct
orientation is maintained when assembling on the aircraft and engine.

61-10-00
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

(22) Pull the jack plate unit (770) toward the table.
(23) Rotate the jack plate unit (770) and disengage the forks (810) from the blocks
(220).
(24) Remove the jack plate unit (770), temporary low pitch spacer, and the setup
spacerfrom the propeller.
NOTE: The setup spacer is used only during setup and is not used when
installing the propeller on the aircraft.
(25) Remove the propellerfrom the build bench.
Practices
(26) Static balance the propeller in accordance with Hartzell Standard
Manual 202A (61-01-02), Chapter 600, Static and Dynamic Balance.

Static balance will require a jack plate only to hold blades relative to each
(a)
other.

(b) Use plastic or aluminum wedges to insert between the blade clamps and the
hub.

(c) Use fixturing with a rear cone and a front nut to support the propeller for
balancing.
(27) Affix one label TOR-504 to the OD of a blade clamp.
Practices Manual
(28) Lubricate the propeller in accordance with Hartzell Standard
202A (61-01-02), Chapter 400, Propeller Lubrication.

61 -1 0-00
 PROPELLER
HA RTZ E LL MA:NO~EENANCE MANUAL

W10348

CM93 Sealant

Sealant CM93 Application

Figure 714.1

743.1
,,,E,,L, 61110-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

G. Sealant CM93 Application All Models

The application of sealant CM93 to the blade/blade clamp interface is an optional

procedure that may provide additional protection against corrosion of the blade
retention components.

CAUTION 1 TO AVOID PERMAN ENT DAMAGE TO TH E BLADE RETENTION

COMPONENTS CAUSED BY TRAPPED CHEMICALS, THIS
PROCEDURE MUST BE PERFORMED FOLLOWING TH E
ASSEMBLY OF A PROPELLE R AFTE R OVERHAUL OR AFTE R ANY
OTH ER PROCEDU RE I NVOLVING DISASSEMBLY AND CLEAN i NG
OF THE PROPELLER BLADE RETENTION COMPONENTS.

CAUTION 2. TO-ASSURE PROPER ADHESION OF SEALANT CM93, BLADE

AND BLADE CLAMP SURFACES MUST BE FREE OF GREASE
AND DIRT.

(1) After performing the check for blade slippage in the clamp, fill the external void at
the blade/blade clamp interface with a 0.25 inch (6.35 mm) maximum bead of
sealant CM93, around the entire circumference of blade, as shown in Figure
714.1.

NOTE: Do not allow sealant CM93 to extend onto the surface of the clamp
where balance weights and de-ice hardware are installed.

(2) Allow the sealant to cure for a minim um of two hou rs, before retu m i ng the propell e r
to service.

.,,,,,,,61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

6. Jack Plate and Hydraulic Piston Assembly

CAUTION 1 DO NOT interchange cylinders and pistons. They are paired by stamped
numbers on the outer edges of both units.

I CAUTION 2: DO NOT interchange the valve body and valve plate on the "C" series valve
assemblies.

A. HC-D2(V, MV)20-3 and HC-D3(V, MV)20-6L

(Hydraulic Unit Assemblies 91-E and 91-6L)
(1) Hand pack the bearing (670) with high speed bearing grease CM139.

CAUTION: BEARING SURFACE MARKED "TH RUST HERE" MUST BE

PRESSED INTO PISTON FIRST.

(2) Press the bearing (670) into the piston (510). A slight press fit is required. If
necessary, use gasket compound CM93 between the bearing and the piston to
insu re tight fit.

I NOTE: A bearing will take thrust in only one direction. The words "Thrust Here"
are marked on the bearing and are not visible after the bearing is

installed in the piston.

(3) Install the gasket (710) and cover plate (720).

(4) Install lock washers
(750) and screws (760) in the cover plate (720) and into the
piston (510). Torque the screws as required per Torque Values Table 801 in the
Fits and Clearances chapter of this manual.

NOTE: Gasket may require trimming after the cover plate is installed.
(5) Press the jack plate (770) into the bearing (670)
NOTE: The groove just inside the inner race of the bearing must match the
groove in the jack plate.

(6) Insert the wirering (930) in the groove between the bearing inner race and the jack
plate casting (730). Use pliers to work the wire ring around groove.

PISSEMBLY 61-10-00
 PROPELLER MAINTENANCE MANUAL
HIA RTZ E LL 100E

B. HC-D(2,3)(V,MV)20-7 and -8(

(Hydraulic Unit Assemblies 91-7DS, 91-8DS, and 91-8DT)
(1) Hand pack the bearing (670) with high speed bearing grease CM139.

CAUTION: BEARING SURFACE MARKED "THRUST HERE" MUST BE

PRESSED INTO PISTON FIRST.

(2) Press the bearing (670) piston (510). A slight press fit is required. If
into the
to insure
necessary, use gasket compound between the bearing and the piston
a

tight fit.

I NOTE: A bearing will take thrust in only one direction. The words "Thrust Here"
are marked on the bearing and are not visible after the bearing is

installed in the piston.

(3) Install the gasket (710) and cover plate (720).

(4) Insert lock washers(750) and screws (760) in the cover plate (720) and piston
(510). Torque the screws as required, per Torque Values Table 801 in the Fits
and Clearances chapter of this manual.

,ss,,,,,61 -1 0-00
 PR6PELLER
HARTZELL MA:N~EENANCE MANUAL

7. Valve Reassembly

A. Reassemblyof B-93-D Valve

(1) Install the O-ring (1230) in the valve body(1040).
(2) Install the guide pin (1200) connecting the valve link(1240) and valve spool
(1050).
(3) Slide the valve spool (1050) and the guide pin (1200) into the valve body (1040)
while sliding the guide pin (1200) onto the guide rod (1210).

(4) Install the cotter pin (1 1 70) in the valve body (1040) to hold the other end of the
spring.
(5) Attach the end of the spring into the cotter pin loop.
(6) Attach the other end of the spring (1 180) on the groove in the guide pin (1200).

B. Reassembly of B-93-A, -B, -C Valve

(1) Install two O-rings (1230) in the valve body(1040).

(2) Slide the valve spool (1050) into the valve body (1040).
(3) Install the stop nut (1 1 10) and stop screw (1 120) on the link (1 130).
(4) Assemble the links (1 140) and (1 130), and the spacer(1090). Install the clevis pin
(1 100) and the cotter pin (1075).
(5) Attach the link(l 140) to the valve spool (1050) with the clevis pin (1080) and
cotter pin (1070).

C. Reassembly of B-93-AG, -BG, -CG Valve

(1) Install two O-rings (1230) in the valve body (1 040).

(2) Slide the valve spool (1050) into the valve body (1040).
(3) Connect the link (1 1 30) to the valve spool (1 050). Install the clevis pin (1 080) and
the cotter pin (1070).

D. Reassemblyof B-93-E Valve

(1) Install two O-rings (1230) in the valve body (1 040).
(2) Slide the valve spool (1050) into the valve body (1040).
(3) Install the stop nut (1 1 10) and stop screw (1 120) on the link(l 130).
(4) Assemble the links (1 140) and (1 130), and the spacer (1090). Install the clevis pin
(1 100) and the cotter pin (1075).
(5) Attach the link(l 140) to the valve spool (1050) with the clevis pin (1080) and
cotter pin (1070).

61-10-00 RevP:gABpr~06
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

8. Installing the Propeller Assembly on the Aircraft

I A. Model HC-D2V20-3

(1) Use six elastic nuts to attach the cylinder (540) to six studs protruding from the
engine.
1 (2) Make sure that the studs do not extend more than 0.5 inch (12 mm) above the
bottom inside surface of the cylinder.
Piston travel may be limited if the studs extend more than 0.5 inch
I NOTE 1
(12 mm) above the bottom inside surface of the cylinder.
NOTE 2: If the hydraulic valve was not removed from the piston, position the valve
body at either extreme of the valve stroke to allow air to escape from
the cylinder.

CAUTION: BE SURE TO REINSTALL THE PISTON AND CYLINDER REMOVED

AT DISASSEMBLY. FOR REASSEMBLY ORIENTATION REFER TO
DISASSEMBLY MAR~INGS.

(3) Turn the piston so the number stamped on the flange lines up with the number
stamped on the front edge of the cyiinder, and the pins (550) in the cylinder (540)
line up with the appropriate holes in the piston (510).

NOTE: Cylinder-to-piston guide rods may bind in the piston if the original
cylinder and piston combination is changed

CAUTION: DO NOT DAMAGE THE O-RINGS WHEN INSTALLING THE PISTON

I NTO TH E CYLI N DER.

(4) (770) and piston assembly (510) into the cylinder (540).
Install the jack plate unit
Use a rubber mallet as necessary to bottom the piston in the cylinder.

(5) hydraulic valve assembly onto the piston with a gasket (1 010) and two
Install the
screws (1250). Safety the two screws.

(6) Clean the engine shaft.

(7) Oil the engine shaft.

(8) Install the spacers and the rear cone.

1 (9) Place the propeller on the engine shaft and align the wide hub spline, if applicable,
with the shaft blind spine.

,ss,,,,Y 61 11 0100
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

(This page is intentionally blank.)

I ASSEMBLY 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL ioM

(10) Install a pitch change block (220) on each link screw (380).

CAUTION 1: USE MARKINGS MADE DURING BENCH ASSEMBLY TO MATCH

THE FORKS (810), BLOCKS (220), SLEEVES (312) AND REVERSE
STOPS (313).

CAUTION 2: MAINTAIN BLOCK ORIENTATION AND MATCH WITH THE SAME

LINKSCREW AS ESTABLISHED DURING BENCH ASSEMBLY AND
ADJUSTMENT.

Rotate the hub relative to the jack plate forks and rotate the blades on the hub.
(1 1)
NOTE: The rotation will make it easier to slide the folks (810) onto the blocks

(220).

CAUTION: NEVER USE FORCE TO START THE HUB NUT (180).

(12) Turn the hub nut (1 80) onto the engine shaft. Make sure the threads have engaged
properly.
(1 3) Torque the hub nut on the engine shaft and safety. Refer to Torque Values Table
801 in the Fits and Clearances chapter in this manual.

(14) assembly (1000) on the piston (510) using two screws (1250) and
Install the valve
the gasket (1010). Safety the screws (1250) together.

(15) Check piston travel by measuring between the jack plate and hub shoulder. Travel
should be 1.062 to 1.094 inch (26.98 to 27.78 mm).

CAUTION: HOSE MUST BE LONG ENOUGH TO ALLOW VALVE TO MOVE

FREELY WITH THE PISTON.

ID flexible hose from

1 (16) Install 3/8 (0.37 to 0.50 inch [9.6 to 12.7 mml)
inch to 1/2 inch
the pressure side of the engine to the lever side of the valve.

CAUTION: LOCATE THE CRANKCASE DRAIN FITTING AS CLOSE TO THE

VALVE AS POSSIBLE--NOT OVER 18 INCHES (457 mm).

I (17) Install 3/8 inch to 1/2 inch (0.37 to 0.50 inch [9.8 to
the e ngi ne cran kcase to the valve.
12.7 mml) ID flexible hose from

(18) Position the cockpit reverse control line forward just off the locked position.

(19) Attach the reverse control line at the propellerto the short end of the lever on the
valve, making sure the clamping bolt is tight against the bracket on the cylinder.
NOTE: There should be an increase in line tension when moving the cockpit
reverse control lever i nto the locked position.

.ss,,,,,61 -1 0-00
 PROPELLER MAINTE NANCE MANUAL
~ARTZELL 1000

(20) Bottom the piston in the cylinder.

(21) Pull out the
cockpit propeller control handle approximately 2.25 inches (57 mm)
from the instrument panel and position the valve spool midway between the cotter
pin and the base of the guide pin.

I (22) Attach the propeller pitch control line to the valve lever.
(23) Adjust propeller static RPM

(a) Determine the current static RPM.

NOTE: The limits for full throttle maximum static RPM are listed in the FAA
Aircraft Specification.
1 Start and warm up the engine and check for propeller action.
2 Determine what fu II th rottle maximum static RPM is obtained with
cockpit propeller control full forward for low pitch.
(b) Static RPM Set Too Low.

1 Stop the engine.

2 Adjust the cockpit lever th row to allow movement of the valve lever to a
lower pitch.

(c) Static RPM Set Too High.

1 Pull back on the propeller control until the correct RPM is obtained.

2 Stop the engine.

3 Adjust the cockpit lever throw to reduce the movement of the valve lever,
resulting in a higher pitch.
(24) Setting Reverse Pitch
(a) Adj ust the reverse pitch with a stop screw against the valve link.

CAUTION: MAINTAIN A MINIMUM CLEARANCE OF 0.125 INCH (3.18 mm)

BENVEEN THE JACK PLATE AND THE HUB SHOULDER TO
PREVENT TH E TH RUST BEARINGS IN THE PROPELLE R AND
ENGINE FROM BEING LOADED UNNECESSARILY.

I (b) Make sure there is a minimum 0.125 inch (3.18 mm) clearance between the
jack plate and the hub shoulderwhen in full reverse.

1 (25) Check the pitch control in flight for proper operating range.

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 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

B. Model HC-D2MV20-3

(1) Use six elastic nuts to attach the cylinder (540) to six studs protruding from the
engine.
(2) Make sure that the studs do not extend more than 0.5 inch (12 mm) above the
bottom inside surface of the cylinder.
NOTE 1 Piston travel may be limited if the studs extend more than 0.5 inch
(12 mm) above the bottom inside surface of the cylinder.
NOTE 2: If the hydraulic valve was not removed from the piston, position the valve
body at either extreme of the valve stroke to allow air to escape from
the cylinder.

CAUTION: BE SU RE TO REI NSTALL THE PISTON AND CYLINDER IN THE

SAME ORI ENTATION AS WHEN REMOVED AT DISASSEMBLY.
FOR REASSEMBLY ORIENTATION REFER TO DISASSEMBLY
MARKINGS.

(3) Turn the piston (510) so the number stamped on the flange lines up with the
number stamped on the front edge of the cylinder, and the pins (550) in the
cylinder (540) line up with the appropriate holes in the piston (510).
NOTE: Cylinder-to-piston guide rods may bind in the piston if the original
cylinder and piston combination is changed

CAUTION: DO NOT DAMAG E THE O-RINGS WHEN I NSTALLING THE PISTON

INTO THE CYLINDER.

(4) Install the jack plate unit (770) and piston assembly (510) into the cylinder (540).
Use a rubber mallet as necessary to bottom the piston in the cylinder.

(5) hydraulic vake assembly (1000) onto the piston (510) with a gasket
Install the
(1 010) and two screws (1 250). Safety the two screws.
(6) Clean the engine shaft.

(7) Oil the engine shaft.

(8) Install one spacer (21 0) and the rear cone (200).
(9) Place the propeller on the engine shaft and align the wide hub spline, if applicable,
with the shaft blind spine.

(10) Install a pitch change block (220) on each link screw (380).

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 PROPELLER MAINTENANCE MANUAL
H~A RTZ E L L looE

CAUTION 1: USE MARKINGS MADE DURING BENCH ASSEMBLY TO MATCH

THE FORKS (810) AND BLOCKS (220). MAINTAIN THE BLOCK
OR I E NTATION AN D MATC H WITH TH E SAM E LI N KSCREW AS
ESTABLISHED DURING BENCH ASSEMBLY AND ADJUSTMENT.

CAUTION2: MAINTAIN BLOCK ORIENTATION AND MATCH WITH THE SAME

LINKSCREW AS ESTABLISHED DURING BENCH ASSEMBLY AND
ADJUSTMENT.

(1 1) Rotate the hub relative to the jack plate forks and rotate the blades on the hub.

NOTE: The rotation will make it easier to slide the forks (810) onto the blocks
(220).
(12) Confirm that a minimum of five (5) threads on the engine shaft are available for
threading on the hub nut(l80).

CAUTION: N EVE R USE FORCE TO START TH E H UB N UT (1 80).

(13) Turn the hub nut (180) onto the engine shaft. Make sure the threads have engaged
properly.
(14) Torque the hub nut on the engine shaft and safety. Referto Torque Values Table
801 in the Fits and Clearances chapter in this manual.

(1 5) Rotate the blades by hand toward low pitch until the jack plate (770) contacts the
spacer ring (320). Confirm that there is a minimum of 0.025 inch (0.63 mm)
clearance between each clamp (330) and the valve (1000).

Part Number Height Effect on Reverse Blade Angle

A-165-6 0.478 st 0.010 Set Up
(12.14 0.25 mm)

A-165-5 0.543 st 0.010 -1.5- 2.0 degree less reverse than A-165-6.
(13.79 st 0.25 mm)

A-1 65-4 0.513 0.010 -0.6 1.0 degree less reverse than A-1 65-6.
(13.03 st 0.25 mm)

Spacer Selection
Table 701

61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 1008

valve (1000),
(16) If there is insufficient clearance between the clamps (330) and the
measure the gap to determine how much clearance
is needed. Remove and

reassemble the propeller in accordance with steps 8.A.(16)(a) through 8.A(16)(c),

clearance.
using the alternate spacer ring (320) that will provide adequate
Refer to Table 701 for blade angle changes that will result from the
(a) reverse

installation of alternate spacer rings.

(b) Remove the propeller in accordance with propeller removal in Chapter 300,
Disassembly, in this manual.

WARNING: DO NOT RESET BLADES IN CLAMPS TO COMPENSATE FOR

REVERSE BLADE ANGLE CHANGE.

(c) Reassemble the propeller in accordance with steps 5.8.(2) through 5.B.(9j
and 5.B.(16)through 5.8(26), using the correct dash number spacer ring
clearance
(320)(see Table 701) to provide 0.025 inch (0.63 mm) minimum
between each clamp (330) and the valve (1000).

(d) Reinstall the propeller in accordance with steps 8.8.(6) through 8.8.(14).

(17) Confirm the proper high pitch blade angle as follows:

CAUTION: THE VALVE MUST BE IN HIGH PITCH POSITION TO BLEED

AIR INTO THE CYLIN DER.

(1) Rotate the blades by hand toward high pitch, until travel is limited by the
hydraulic unit (500).
(2) Measure the high pitch blade angle to confirm that it is a minimum of 19.5
degrees.
(3) If thehigh pitch blade angle is less than 19.5 degrees, follow steps (a)
through (d) below, to remove the propeller and install additional spacer(s)
(210) to achieve the desired high pitch blade angle.
(a) Remove the propeller in accordance with propeller removal in Chapter
300, Disassembly, in this manual.

(b) Remove the rear cone (200) and spacer (210).

NOTE: Each additional spacer will increase high pitch angle by
approximately 1 .5 degrees.
(c) Reinstall the rear cone (200) with additional spacer(s) (210) to achieve
19.5 degrees minimum.
NOTE: It is recommended that the minimum number of spacers
(210) be used to achieve the required blade angle.
(d) Reinstall the propeller in accordance with paragraph 8.8.(6) through
8. B.(14) in this chapter.

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 PROPELLER
HARTZ E LL MAI1NOSENANCE MANUAL

I (This page is intentionally blank.)

I ASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CAUTION: HOSE MUST BE LONG ENOUGH TO ALLOW THE VALVE TO MOVE

FREELY WITH THE PISTON.

(0.37 to 0.50 inch [9.6 to 12.7 mml)

Install 3/8 inch to 1/2 inch ID flexible hose from
(18)
side of the valve.
pressure side of the engine to the lever

CAUTION: LOCATE THE CRANKCASE DRAIN FITTING AS CLOSE TO THE

VALVE AS POSSIBLE--NOT OVER 18 INCHES (457 mm).

Install 3/8 inch to 1/2 inch (0.37 to 0.50 inch [9.6 to 12.7 mml) ID flexible hose from
(19)
the engine crankcase to the valve.
(20) Position the cockpit reverse control line forward just off the locked position.
(21) Attach the reverse propeller to the short end of the lever on the
control line at the
valve, making sure the clamping bolt is tight against the bracket on the cylinder.
NOTE: There should be an increase in line tension when moving the cockpit
reverse control lever into the locked position.

(22) Bottom the piston in the cylinder. Pull out the cockpit propeller control handle
approximately 2.25 inches (57 mm) from the instrument panel and position the
valve spool midway between the cotter pin and the base of the guide pin.

(a) Attach the propeller pitch control line to the valve lever.
(23) Adjust propellerstatic RPM
(a) Determine the current static RPM.

NOTE: The limits for full throttle maximum static RPM are listed in the FAA
Aircraft Specification.
action.
1 Start and warm up the engine and check for propeller

2 Determine what full throttle maximum static RPM is obtained with

cockpit propeller control full forward for low pitch.
(b) Static RPM Set Too Low.

1 Stop the engine.

2 Adjust the cockpit lever throw to allow movement of the valve lever to a
lower pitch.

(c) Static RPM Set Too High.

1 Pull back on the propeller control until the correct RPM is obtained.

2 Stop the engine.

3 Adjust the cockpit lever throw to reduce the movement of the valve Lever,
resulting in a higher pitch.

ASSEMBLY 61 ’1 0’00
 PROPELLER
HARTZELL

(24) Setting Reverse Pitch

(a) Reverse pitch is adjusted with a stop screw against the valve link.

CAUTION: MAINTAIN A POSITIVE CLEARANCE BETWEEN THE JACK

PLATE AND THE HUB SHOULDER TO PREVENT THE
THRUST BEARINGS IN THE PROPELLER AND ENGINE FROM
BEING LOADED UNNECESSARILY.

(b) Check that there is a positive clearance between the jack plate and the hub
shoulderwhen in full reverse.

(25) Check the pitch control in flight for proper operating range.

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 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1000

I C. Model HC-D3V20-6L

(1) Use six elastic nuts to attach the cylinder (540) to six studs protruding from the
engine.

1 (2) Check to make sure that the studs do not extend over 0.5 inch (i 2.7 mm) above
the bottom inside surface of the cylinder.
NOTE 1: Piston travel may be limited if the studs extend over 0.5 inch (12.7 mm)
above the bottom inside surface of the cylinder.

NOTE 2: If the hydraulic valve was not removed from the piston, position the valve
body at either extreme of the valve stroke to allow air to escape from
the cylinder.

CAUTION 1 MAKE SURE TO REINSTALL THE PISTON AND CYLINDER

REMOVED AT DISASSEMBLY. FOR REASSEMBLY ORIENTATION
REFER TO DISASSEMBLY MARKINGS.

CAUTION 2. DO NOT DAMAGE TH E O-R I NGS WHEN INSTALLING THE PISTON

I NTO TH E CYLINDER.

allow attachment of the piston (510) and

(3) Position the propeller on a drum or tire to
jack plate assembly (770) combination.
I NOTE 1 Cylinder-to-piston guide rods may bind in the piston if the original
cylinder and piston combination is changed.
NOTE 2. For ease piston (510) and
of installation it is recommended that the
jack plate assembly (770), that were previously joined together, be
installed on the propeller before installation on the engine.

CAUTION 1: USE MARKINGS MADE DURING BENCH ASSEMBLY TO MATCH

THE FORKS (810), BLOCKS (220), SLEEVES (312) AND REVERSE
STOPS (313).

CAUTION 2: MAI NTAIN BLOCK O RIENTATION AN D MATC H WITH THE SAM E

LINKSCREW AS ESTABLISHED DURING BENCH ASSEMBLY AND
ADJUSTMENT.

(4) Install a pitch change block (220) on each clamp linkscrew (380).

(5) Remove the push rod nut (315) and the washer (314) from each push rod (800).
(6) Remove the reverse stop (313) and sleeve (312)from each push rod (800).

(7) Slide the reverse stop (31 3) onto the sleeve (312). Rest the reverse stop against
the shoulder of the sleeve.

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 PROPELLER
HA RTZ E LL MAI1NOSENANCE MANUAL

(8) Insert the sleeve (312) with the reverse stop (313) into the appropriate guide collar
hole.

NOTE: The sleeve and reverse stop are inserted from the engine side of the
guide collar.

CAUTION: THE THICK ARM OF THE PITCH CHANGE BLOCK MUST BE

TOWARD THE ENGINE.

(9) Slide the appropriate fork (810) onto the pitch change block (220).
(10) Insert thepush rods of the jack plate assembly (770) (with the piston (51 0)
attached) through the fork (810), sleeve (31), reverse stop (313) and guide collar
(300).
(1 1) Install a washer (314) and nut (315) on the end of each push rod (800) and tighten.
(12) Align the forks (810) with the pitch change blocks (220) and torque set screw
1 (230). Refer to Torque Values Table 801.
(13) Prick punch between the set screw (830) and the fork (810) to lock the set screw
in place.
(14) Cleanthe engineshaft.
1 (15) Oiltheengineshaft.
(16) Install the spacers (200) and rear cone (190).
(1 7) Place the propeller and the hydraulic unit (without the cylinder and the hydraulic
I valve) on the engine shaft and align the wide hub spline, if applicable, with the
shaft blind spline.

CAUTION: MAKE SU RE TO REINSTALL TH E PISTON AND CYLINDER

REMOVED AT DISASSEMBLY. FOR REASSEMBLY ORIENTATION
REFER TO DISASSEMBLY MARKINGS.

(18) Turn the piston so the number stamped on the flange lines up with the number
stamped on the front edge of the cylinder and the pins (550) in the cylinder (540)
line up with the appropriate holes in the piston (510).
(19) Install the jack plate unit (770) and the piston assembly (510) into the cylinder
(540). Use a rubber mallet, as necessary, to bottom the piston in the cylinder.

CAUTION: N EVE R USE FORCE TO START TH E H UB N UT (1 80).

(20) Install the hub nut
(1 80) onto the engine shaft. Make su re the th reads have
engaged properly.
(21) Torque the hub nut (1 80) on the engine shaft. Referto Torque Values Table 801

61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

two screws ~1250) and

(22) Install the valve assembly (1000) on the piston (510) using
the gasket (101 0). Safety the screws (1250) together.

(23) Check piston travel by measuring between jack plate and hub shoulder. Travel
should be 1.062 to 1 .094 inch (28.98 to 27.78 mm).

CAUTION: HOSE MUST BE LONG ENOUGH TO ALLOW VALVE TO MOVE

FREELYWITH THE PISTON.

(0.37 to0.50 inch [9.6 to 12.7 mml)

Install 3/8 inch to 1/2 inch ID flexible hose from
1 (24)
lever side of the valve.
pressure side of the engine to the

CAUTION: LOCATE THE CRANKCASE DRAIN FITTING AS CLOSE TO THE

VALVE AS POSSIBLE--NOT OVER 18 INCHES (457 mm).

12.7 mml) ID flexible hose from

(25) Install 3/8 inch to 1/2 inch (0.37 to 0.50 inch [9.6 to
the engine crankcase to the valve.
off the
(26) Position the cockpit reverse control line forward (reversible propeller) just
locked position.
end of the lever on the
(27) Attach the reverse control line at the propeller to the short
the cylinder.
valve, making sure the clamping bolt is tight against the bracket on
NOTE: There should be an increase in line tension when moving the cockpit
reverse control lever into the locked position.
handle
piston in the cylinder. Pull out the cockpit propeller control
I (28) Bottom the
approximately 2.25 inches (57 mm) from the instrument panel and position
the

valve spool midway between the cotter pin and the base of the guide pin.

(a) Attach the propeller pitch control line to the valve lever.
(29) Adjust propellerstatic RPM
(a) Determine the current static RPM.

NOTE: The limits for full throttle maximum static RPM are listed in the FAA

Aircraft Specification.

I 1 Start and warm up the engine and check for propeller action.
2 Determi ne what full th rottle maxi mum static R PM is obtai ned with
cockpit propeller control full forward for low pitch.
(b) Static RPM Set Too Low.

1 Stop the engine.

I 2 Adjust the cockpit lever throw to allow movement of the
valve lever to a

lower pitch.

,s,,,,,Y 61 11 0100
 PROPELLER
HA RT Z E L L MA:NO~EENANCE MANUAL

(c) Static RPM Set Too High.

1 Pull back on the propeller control until the correct RPM is obtained.
2 Stop the engine.
3 Adjust the cockpit lever th row to reduce the movement of the valve lever,
resulting in a higher pitch.
(30) Setting Reverse Pitch
(a) Reverse pitch is adjusted with a stop screw against the valve link.

CAUTION: MAINTAIN A MINIMUM CLEARANCE OF 0.010 INCH (0.25 mm)

BETWEEN THE REVERSE STOP (313) AND THE GUIDE
COLLAR(300) TO PREVENT THE THRUST BEARINGS IN THE
PROPELLER AND ENGINE FROM BEING LOADED
UNNECESSARILY.

I (b) Check that there is a minimum 0.010 inch (0.25 mm) clearance between the
reverse stop (31 3) and the guide collar when the propeller in full reverse.
(31) Check pitch control in flight for proper operating range.

ASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

D. Model HC-D3MV20-6L

(1) Use six elastic nuts to attach the cylinder (540) to six studs protruding from the
engine.
(2) Check to make sure that the studs do not extend over 0.5 inch (12.7 mm) above
the bottom inside surface of the cylinder.
NOTE 1: Piston travel may be limited if the studs extend over 0.5 inch (12.7 mm)
above the bottom inside surface of the cylinder.
valve
NOTE2E: If the hydraulic valve was not removed from the piston, position the
allow air to escape from
body at either extreme of the valve stroke to
the cylinder.

CAUTION 1 MAKE SURE TO REINSTALL THE PISTON AND CYLINDER

REMOVED AT DISASSEMBLY. FOR REASSEMBLY ORIENTATION
REFE R TO D I SASSEM BLY MARKI NGS.

CAUTION 2. DO NOT DAMAGE THE O-RINGS WHEN INSTALLING THE PISTON

I NTO TH E CYLI N DER.
and
(3) Position the propeller on a drum or tire to allow attachment of the piston (51 0)
jack plate assembly (770) combination.
NOTE 1: Cylinder-to-piston guide rods may bind in the piston if the original
cylinder and piston combination is changed.
NOTE 2: For ease piston (510) and
of installation it is recommended that the
be
jack plate assembly (770), that were previously joined together,
installed on the propeller before installation on the engine.

CAUTION 1: USE MARKINGS MADE DURING BENCH ASSEMBLY TO MATCH

THE FORKS (810), BLOCKS (220), SLEEVES (312) AND REVERSE
STOPS (31 3).

CAUTION2: MAINTAIN BLOCK ORIENTATION AND MATCH WITH THE SAME

LINKSCREW AS ESTABLISHED DURING BENCH ASSEMBLY AND
ADJUSTMENT.

(4) pitch change block (220) on each clamp linkscrew (380).

Install a

rod (800).
(5) Remove the push rod nut (315) and the washer (314) from each push

(6) Remove the reverse stop (313) and sleeve (312) from each push rod (800).

(7) Slide the reverse stop (313) onto the sleeve (312). Rest the reverse stop against
the shoulder of the sleeve.

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 PROPELLER
HARTZ ELL MA:N~NANCE MANUAL

(8) Insert the sleeve (312) with the reverse stop (313) into the appropriate guide collar
hole.

NOTE: The sleeve and reverse stop are inserted from the engine side of the
guide collar.

CAUTION: THE THICK ARM OF THE PITCH CHANGE BLOCK MUST BE

TOWARD TH E ENGI NE.

(9) Slide the appropriate fork (810) onto the pitch change block (220).
(10) Insert thepush rods of the jack plate assembly (770) (with the piston (510)
attached) through the fork (810), sleeve (31), reverse stop (313) and guide collar
(300).
(1 1) Install a washer (314) and nut (315) on the end of each push rod (800) and tighten.
(12) Align the forks (810) with the pitch change blocks (220) and torque set screw
(230). Refer to Torque Values Table 801
(13) Prick punch between the set screw (830) and the fork (810) to lock the set screw
in place.

(14) Cleantheengine shaft.

(15) Oil the engine shaft:
(16) Install the spacers (200) and rear cone (1 90).
(1 7) Place the p repel ler and the hydraulic un it (without the cyl i nder and the hydraulic
valve) on the engine shaft and align the wide hub spline, if applicable, with the
shaft blind spline.

CAUTION: MAKE SURE TO REINSTALL THE PISTON AND CYLINDER

REMOVED AT DISASSEM BLY. FOR REASSEMBLY ORI ENTATION
REFER TO DISASSEMBLY MARKINGS.

(18) Turn the piston so the numberstamped on the flange lines up with the number
stamped on the front edge of the cylinder and the pins (550) in the cylinder (540)
line up with the appropriate holes in the piston (510).

(19) Install the jack plate unit (770) and the piston assembly (510) into the cylinder
(540). Use a rubber mallet, as necessary, to bottom the piston in the cylinder.

CAUTION: NEVER USE FORCE TO START THE HUB NUT(180).

(20) Install the hub nut
(1 80) onto the engine shaft. Make sure the th reads have
engaged properly.
(21 Torque the hub nut (1 80) on the engine shaft. Ref er to Torque Values Table 80 1

ASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HARTZELL IbOE

two screws (1250) and

(22) Install the valve assembly (1000) on the piston (51 0) using
the gasket ~1010). Safety the screws (1250) together.
and hub shoulder. Travel
(23) Check piston travel by measuring between jack plate
should be 1.062 to 1.094 inch (26.98 to 27.78 mm).

(24) Rotate the blades by hand to reverse pitch position.

NOTE: When the propeller is in reverse pitch position, the reverse stop washer
the
(313) is pinched between the guide collar (300) and the shoulder on
sleeve (31 2).
is clearance
(25) Slowly turn the propeller on the engine shaft to identify if there
between the blade clamp assemblies (330) and the valve assembly (1000).

(26) If there is no interference, continue with step 8. D.(28). If there is interference

continue with the following steps:
and valve
(a) Identify a dimension required to space the clamp assembly (330)
assembly (1000) apart and re-establish positive clearance.
(b) Increase the thickness of the reverse stop (31 3) with the dimension required
and the
to re-establish positive clearance between the clamp assembly (330)
valve assembly(1000).

1 Refer to Figure 710 for a listing of reverse stop thicknesses.

2 Select asingle stop with the required thickness, or several stops that
add up to the required thickness.

(c) Remove the nuts (31 5) and washers (314) from the ends of the three push
rods protruding from the jack assembly (770).
and jack
NOTE: Keep the nuts (315) and washers (314) with the propeller
assembly.
(d) Twist the counterweights (340) toward high pitch to move the push rods (800)
and sleeve (312)toward the engine are far as they will travel.

(e) Loosen and unthread the hub nut (180)from the engine shaft.

NOTE: pull the propeller away from the engine and allow the push
This will
rods (800) and sleeves (312) to slide out of the guide collar (300)
on the engine side of the guide collar.

Allow the jack assembly push rods (800) to completely slide out
of the guide
(f)
collar (300).

(g) Turn the jack plate unit (770) until the pitch change forks (810) disengage
from the pitch change blocks (220).

ASSEMBLY 61 ’1 0’00
 PROPELLER
HA RTZ E LL MA:N6~NANCE MANUAL

(h) Install the reverse stop (31 3) with the new dimension thickness onto the
sleeve (312) and push rod (800).
(i) Position the jack plate unit (770) and the hub to engage the pitch change
blocks (220).
(i) Position the blades so the forks (810) can slide onto the pitch change blocks
(220).
(k) With the propeller blades at high pitch, align the push rods (800) and sleeves
(312) with the guide collar bushings by rotating the propeller hub orjack plate
unit (770) relative to each other.

(I) Slide the push rods (800) and sleeves (312) through the guide collar
bushings by rotating the blades to reverse pitch.

CAUTION: N EVER USE FORCE TO START TH E H UB N UT (1 80).

(m) Thread the hub nut (180) onto the engine shaft. Make sure the threads have
engaged p rope rly.
(n) Torque the hub nut (180) on the engine shaft. Referto Torque Values Table
801.

to) Install a washer (314) and nut (315) on the end of each push rod protruding
th rough the guide collar bushings

(p) Tighten the nuts (31 5) until snug.

(q) Rotate the blades by hand to reverse pitch position.
NOTE: When the propeller is in reverse pitch position, the reverse stop
washer (313) will be pinched between the guide collar (300) and
the shoulder on the sleeve (312)

(r) Slowly turn the propeller on the engine to verify if there is clearance between
the blade clamp assemblies (330) and the valve
assembly(1000).
(27) Repeat steps 8.d.(24) through 8. D.(26)(o) until clearance between the blade
clamp assemblies (330) and the valve assembly (1000) is achieved.

CAUTION: HOSE MUST BE LONG ENOUGH TO ALLOW VALVE TO MOVE

FREELY WITH THE PISTON.

(28) Install 3/8 inch to 1/2 inch(0.37 to 0.50 inch [9.6 to 12.7 mml) ID flexible hose from
pressure side of the engine to the lever side of the valve.

ASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

CAUTION: LOCATE THE CRANKCASE DRAIN FITTING AS CLOSE TO THE

VALVE AS POSSIBLE--NOT OVER 18 INCHES (457 mm).
12.7 mml) ID flexible hose from
(29) Install 3/8 inch to 1/2 inch (0.37 to 0.50 inch [9.6 to
the e ng i ne cran kcase to the valve.

(30) Position the cockpit reverse control line forward (reversible propeller) just off the
locked position.
(31 Attach the reverse control line at the propeller to the short end of the lever on the
sure the clamping bolt is tight against
the bracket on the cylinder.
valve, making
NOTE: There should be an increase in line tension when moving the cockpit
reverse control lever into the locked position.
handle
(32) Bottom the piston in the cylinder. Pull out the cockpit propeller control
and position the
approximately 2.25 inches (57 mm) from the instrument panel
valve spool midway between the cotter pin and the base of the guide pin.

(a) Attach the propeller pitch control line to the valve lever.
(33) Adjust propeller static RPM
(a) Determine the current static RPM.

The limits for full throttle maximum static RPM are listed in the FAA
NOTE:
Aircraft Specification.
1 Start and warm up the engine and check for propeller action.
with
2 Determi ne what full th rottle maxi mum static RPM is obtained
cockpit propeller control full forward for low pitch.
(b) Static RPM Set Too Low.

1 Stop the engine.

valve lever to
Adjust the cockpit lever throw to allow movement of the
a
2
lower pitch.

(c) Static RPM Set Too High.

is obtained.
1 Pull back on the propeller control until the correct RPM
2 Stop the engine.
of the valve lever,
3 Adjust the cockpit lever throw to reduce the movement
resulting in a higher pitch.

ASSEMBLY 61 ’1 0100
 PROPELLER
HA RTZ E LL MAI1NOSENANCE MANUAL

(34) Setting Reverse Pitch

(a) Reverse pitch is adjusted with a stop screw against the valve link.

CAUTION: MAINTAIN A MINIMUM CLEARANCE OF 0.010 INCH (0.25 mm)

BETWEEN THE REVERSE STOP (313) AND THE GUIDE
COLLAR(300) TO PREVENT TH E TH RUST BEARINGS IN THE
PROPELLER AND ENGINE FROM BEING LOADED
UNNECESSARILY.

(b) Check that there is a minimum 0.010 inch

(0.25 mm) clearance between the
reverse stop (313) and the guide collar when the
propeller in full reverse.
(35) Check pitch control in flight for proper operating range.

ASSEMBLY 61’10’00
 I
PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

E. Models HC-D(2, 3)(V, MV)20-7 and -8(

(1) Install a gasket (650) between the cylinder and the engine face.

I (2) Install the cylinder (540)

CAUTION:

(a)
Make
before
on

sure
the

the
engine

screws do not bottom in the

pulling up tight on the cylinder,
Propeller model HC-D2(V, MV)20-7 installed on
or an

Continental "0" series

engine tapped hole
oil leak will occur.

engines: Install cylinder (540) using screws (640) and washers (630).
Safety the screws.

APPLY GASKET COMPOUND CM93 AROUND THE

THREADS
CAUTION:
NEAR THE HEADS OF THE SOCKET HEAD CAP SCREWS.

(b) Propeller model HC-D2(V, MV)20-7 installed on early undampened engines:

to the rear of the
Install the cylinder (540) by attaching a sheet metal bracket

I (c)
cylinder with screws.
Propeller model HC-D2(V, MV)20-8 installed on engines
standard 20 spline shaft and nose:
with S.A.E.

1 Install the cylinder (540).

2 Install O-ring (940) and a nut (730)

an on each of the six studs provided
on the engine.

NOTE: If necessary, trim the cowling to provide clearance for the guide
pin brackets.
0.5 inch (1 2.7 mm) above the bottom
(3) Make that the studs do not extend over
1 sure

inside surface of the cylinder.

NOTE: Piston travel may be limited if the studs extend over 0.5
inch (12.7 mm)
above the bottom inside surface of the cylinder.

(4) Install the rubber diaphragm withinner ring (680) and screws (700).
I (5) Install the outer diaphragm ring (610) using washers (590) and screws (600).

CAUTION: RINGS MAY BREAK IF SCREWS ARE NOTTIGHTENED

UNIFORMLY.
out 0.0625 inch
Tighten screws uniformly in turn until the rubberdiaphragm
comes
(6)
I (t .58 mm) past the edges of the rings.
the valve
NOTE: If the hydraulic valve was not removed from the piston, position
air to escape from
body at either extreme of the valve stroke to allow
the cylinder.

ASSEMBLY 61 ’1 0’00 ReVP2agJeu~:

 PROPELLER
HARTZELL MA:NO~EENANCE MANUAL

1 (7) Turn the piston so the number stamped on the flange lines up with the number
stamped on the front edge of the cylinder, and the pins (550) in the cylinder (540j
line up with the appropriate holes in the piston (510).

(8) Install the jack plate unit (770) and piston assembly (51 0) on the cylinder (540).
(9) Clean the engine shaft.

(1 O) Oil the crankshaft with engine oil.

(1 1) Install the spacers (210) and the rear cone (200) on the engine shaft.
(12) Put thepropeller on the crankshaft and align the wide hub spline, if applicable, with
the shaft blind spine.

CAUTION 1: USE MARKINGS MADE DURING BENCH ASSEMBLY TO MATCH

THE FORKS (810), BLOCKS (220), SLEEVES AND REVERSE (312)
STOPS (313).

CAUTION 2: MAINTAIN BLOCK ORIENTATION AND MATCH WITH THE SAME

LINKSCREW AS ESTABLISHED DURING BENCH ASSEMBLY AND
ADJUSTMENT

(13) Install a pitch change block (220) on each linkscrew (380).

(1 4) Rotate the hub relative to the jack plate forks, and rotate the blades on the hub.
NOTE: The rotation will make it easier to slide the forks
(810) onto the blocks
(220).
(15) If the hub nut (1 80) is already attached to the hub (1 O) with a previously installed
puller ring (160) and a snap ring (170), go to step 8.6.(18).

CAUTION: MAKE SURE THE ENGINE SHAFT AND THE HUB

NUT(180)
THREADS HAVE ENGAGED PROPERLY. DO NOT USE FORCE TO
STARTTHEHUBNUT(180).
(16) Tum the hub nut (1 80) on the engine shaft with the puller ring (160) installed in the
OD groove of the hub nut (180).

NOTE: Hold the puller ring (160) on the hub nut(l80) until the hub nut is turned
on the engine shaft and into the front bore of the hub (10). The hub bore
will prevent the puller ring (160) from falling out of the OD groove of the
hub nut(l80)

(17) Install the snap ring (1 70) into the ID groove of the hub front bore. Go to step
8.E.(19).

ASSEMBLY 61’10’00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CAUTION: MAKE SURE THE ENGINE SHAFT AND THE HUB NUT (180)
FORCE TO
THREADS HAVE ENGAGED PROPERLY. DO NOT USE
START TH E HUB N UT (1 80).

(18) Turn the hub nut(l80)on the engine shaft.

shaft and against the hub (10). Referto
(19) Torque the hub nut (1 80) on the engine
Torq ue Values Table 801
valve assembly (1000) on the cylinder
(20) Install a gasket ~101 0) and the hydraulic
(540) using two screws (1 150).
(21) Safetythe screws (1 150) together.
hole (530) using the screw (950).
(22) Attach the link (1 130) to the piston attachment
(23) Saf ety wire the screw (950) in an airworthy manner to the other screws (760) on
the piston.

1 (24) Install the hydraulic lines to the valve.

Use 0.75 inch (1 9 mm) ID flexible hose for the drain line.
(a)
Make the drain line as short as possible (less than 18 inches [457 mml).
(b)
An 18-inch (457 mm) long line is necessary for the pressure side of -7
I (c)
installations.
out of the valve housing approximately
1 (25) Position the valve spool so that it comes
1 .31 inches(33.2 mm)(neutral position).
0.12 inch (3.0 mm)from the
1 (26) Pull out the push-pull control approximately
dashboard

1 (27) Connect the push-pull control wire to the valve lever.

the left side of the
NOTE: For Navion Installations: Shift the control wire from
from the cockpit).
engine to the right side (facing the rear of the engine
each side of
1 (28) Make sure that the piston travel is 3/16 inch (0.1 87 inch [4.76 mml)
inch (0.375 inch [9.6 mml).
neutral position of the diaphragm with a total travel of 318
travel, if
NOTE: Adjust the spacers behind the rear cone to provide required
necessary.

1 (29) Adjust propeller static RPM

The limits for full throttle maximum static RPM are listed in the FAA
NOTE:
Aircraft Specification.
it has than thread holding it to the link
(30) Turn the screw (1 120) until no more one

(1130).

,,,,,,,Y 61 11 0100
 PROPELLER
HA RTZ E LL MA:N60~NANCE MANUAL

(31) Start the engine and check for propeller action.

(32) Find the full throttle maximum static RPM obtained with the
cockpit propeller
control full in the forward position for low pitch.

(33) Shut down the engine.

(34) Reposition the cockpit control lever bracket, as necessary, to allow either more
lever travel for higher RPM or less travel for lower RPM.

I NOTE: Thisadjustment is for the coarse RPM setting only. Fine RPM
adjustment will be done later with the screw (1 120) installed on the link
(1130).
(35) Restart the engine and verify static RPM.

(38) Repeat steps 8.0.33 and 8.0.34, as necessary.

(37) When coarse RPM adjustment is close, shut down the engine with the control lever
in full forward position.

(38) Loosen the nut (1 1 10) on the screw (1 120).

(39) Reposition the screw (1 120) and tighten so it isjust touching the valve spool.
Small movements of the (1 1 20) will result in
screw slight RPM changes
to achieve static RPM.

(40) Start the engine and determine RPM.

(41 Shut down the engine with the control lever in full forward position.

(42) Adjust the screw (1 120) until the desired RPM is reached.

(43) Check the jack plate-to-hub clearance at low pitch.

(a) Run the engine to fu II th rottle maxi mom RPM with the
cockpit propeller control
in full forward position for low pitch.

CAUTION: MAINTAIN A MINIMUM CLEARANCE OF 0. 125 INCH (3.17 mm)

BETWEEN THE JACK PLATE AND THE HUB SHOULDER TO
PREVENT THE THRUST BEARINGS IN THE PROPELLER AND
ENGINE FROM BEING LOADED UNNECESSARILY.

(44) Stop the engine and make sure there is a 0.125 inch (3.17 mm) gap between the
jack plate (780) and hub when the propeller is in low pitch.

ASSEMBLY 61’q 0’00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1000

(45) Check high pitch travel.

(a) Pull the cockpit control to the movement limit.

I (b) Push on the counterweights to force the piston back.

(c) Make sure there is sufficient travel that the valve can be
positioned at the
center of its travel while the piston is at the rear (toward engine) of its 3/8 inch

(9.53 mm) travel.

NOTE: Checking full travel of the valve lever assures availability of full
RPM range during flight.

WARNING: THERE MUST BE SUFFICIENT TRAVEL OF THE VALVE BEYOND

I H IGH PITCH TO PERMITTHE OIL SUPPLY TO THE CYLINDER TO

BE SHUT OFF DU RING FLIGHT IF THERE IS A LEAK IN THE
DIAPHRAGM.

(46) Checkfor oil shut off.

(a) Make sure there is sufficient travel in the push-pull wire and lever to position
the valve body in front of the neutral position while the piston is in the extreme
rear position.
(b) Check the valve closing.

1 R un the engine full th rottle and slowly reduce engine speed with the
propellercontrol.
2 Slight propeller control travel of approximately 0.5 inch (12 mm) after
the RPM stops dropping indicates that the valve is closed.

P.88EMBLY 61’1 0’00

 PROPELLER MAINTENANCE
HARTZ E LL E001LAUNAM

F. Propeller Installation Troubleshooting HC-D2(V, MV)20-3 and HC-D3(V, MV)20-6L

(1) Insufficient Movement of the Cockpit Control

The push-pull control lines must have sufficient travel to actuate the
piston
through the full stroke.
(a) Start and warm up the engine.
I (b) Monitorthe piston as it moves through its stroke in response to the push-pull
control movement.

(c) Rework the control until sufficient travel is obtained.

1 Bottom the piston in the cylinder.

2 Pull out thecockpit propeller control approximately 2.25 inches (57 mm)
from the instrument panel.

3 Locate the valve spool midway between the cotterpin and the base of
the guide pin.
4 Attach the propeller pitch control line to the valve lever.
(2) Reverse Control Not Tight

NS2IEI: If thereversing control does not pull the short end of the valve lever (pivot
point) up tight against the bracket, it will be impossible to satisfactorily adjust
the high-low pitch control. It
may also be impossible to reach full high pitch.
(a) Loosen the clamp that holds the push-pull control
housing.
(b) Move the housing away from the propeller.

(c) Pull the lever pivot back against the bracket.

(d) Tighten the clamp.

(e) Position the cockpit reverse control line forward, just off the locked position.
(f) Attach the control line at the propellerto the short end of the lever on the
valve.

NOTE: Make sure the clamping bolt is tight against the bracket on the
cylinder.
(g) Move the cockpit reverse control lever into the locked position.
There should be increased tension in the line due to the
take-up of
slack.

ASSEMBLY 61’10’00 RevP2aSJeun:07:

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1000

(3) Cruise RPM Too High

(a) Im proper piston travel

1 Bottom the piston in the cylinder.

NOTE: Make surepiston is at the bottom in the cylinder. The
the
1/32 inch (0.031
piston should extend from the cylinder about
the
inch [0.79 mml). If the piston is not at the bottom, remove
I
piston and eliminate the cause.
the jack plate and
2 Check the travel of the piston by measu ring between
to 1 .094 inches (26.98
the shoulder of the hub. Travel should be 1 .062
to 27.78 mm).
the
1 3 Install a spacer (210) behind the cone, if necessary, to provide
correctstroke.

Install additional spacers (210) behind the cone, as necessary, to

I
a

provide the correct stroke.

,,s,,,,, 61-10-00
 PROPELLER MAINTENANCE
HA RTZ E LL E001LAUNAM

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s I\SSEMBLY 61-10-00 Page 774

Rev. 2 Jun/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 100E

CONTENTS

1. Torque Values

FIGURES

Determining Torque Value of a Standard Torque Wrench with Adaptor...... Figure 801 803

TABLES

Torque Values Table 801 804

Blade Tolerances Table 802 805

Page
FITS AND CLEARANCES 61-10-00 801Mar/98
 PROPELLER MAINTENANCE MANUAL
~IARTZ ELL 100E

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Page
FITS AND CLEARANCES 61110100 802Mar/98
 PROPELLER MAINTENANCE MANUAL
HPI. RTZ E LL 100E

1 Torque Values

Threaded fasteners and hardware are the weakest components inassembly. Vibration
an

can cause an improperly tightened fastener to fail in a matter of minutes. Proper tension in
a fastener depends on a variety of known load factors and can influence fastener service

life. Proper tension is achieved by application of measured torque.

Accurate wrenches and professional procedures will result in precision tensioning.

When an adaptor is used with a torque wrench, use the equation in Figure 801 to
determine the torque value.

APS212

Torquing Adaptor
Standard Torque Wrench

1.00 foot 7’ 0.50 foot

(304.8 mm) (152.4 mm)

tactual toraue reauired~ x (toraue wrench length) torque wrench reading

to achieve required
(torque wrench length) (length of adaptor)
actual torque

EXAMPLE:
reading on torque
wrench with 6-inch
100 Ft-Lb (136 N-m)x 1 ft (304.8 mm~ _

66.7 Ft-Lb (228.6 mm) adaptor

1 ft (304.8 mm) 0.50 ft (228.6 mm)
(901 N-m) for actual torque of
100 Ft-Lb (136 N-m)

Determining Torque Value of a Standard Torque Wrench with Adaptor

Figure 801

FITSANDCLEPIR*NCES 61-10-00 PagMea~

 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

Torque"
Part Number Nomenclature foot ds newton-meter I i unds

A-63B Shaft Nut, 20-Spline 450 610 5400

A-279 Lubrication Fitting 4 5 50

A-304 Link Screw 35-45 47-61 420-540

A-321 Screw, Socket, Clamp 40 54 480

A-2017 or A-2043-1 Bolt, Clamp 35 47 420

A-2036-( Cap Screw, Socket Hd. 65 88 780

(counterweight)
A-2038-( Cap Screw, Nylon Socket 4 5 48

(Guide Collar)
8-352 Guide Collar Nut
125-150 170-203 1500-1800
B-3840-12 Screws, Cover Plate 1.5 2 18

B-3359 Nut, Elastic 12 16 144

Aluminum Blade, mounted in blade clamp 167 226 2004

Torque tolerance is 10% unless otherwise noted.

Torque Values
Table 801

FITS AND CLEARANCES 61-10-00

 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

Tolerances Affectinathe

Balance Tolerance 1 slug A-48

Blade Track ~t 0.06 inch (1.5 mm)

Blade End Play 0.100 inch max. (2.54 mm)

(See Figure 101)

Radial Play in Blade 0.5 degree

(See Figure 101)

Fore and Aft Movement at Tip 0.1 inch max (2.54 mm)
(See Figure 101)

Blade Pitch Setting Tolerance 0.2 degree

Between Blades

Blade Tolerances
Table 802

FITS AND CLEARANCES 61-10-00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

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FITS AND CLEARANCES 61 ’1 0100

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

CONTENTS

1. Minimum Facility and Tooling Requirements 903

A. Tooling 903

B. Facilities 903

2. Special Tools 903

A. Special Tools 903

B. Listings 903

SPECIIL TOOLS, FIXTVRES, FIND EL~UIPMENT 61 -1 0-00

 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 100E

(This page is intentionally blank.)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT 61’1 0’00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

1. Minimum Facility and Tooling Reauirements

A. Tooling
Propeller repair stations approved to overhaul Hartzell propellers are expected to
possess precision fixtures, tools, and blade tables for blade inspection and
rework. Except as specifically required in this manual, locally fabricated tooling is
acceptable for most repair and inspection operations.
B. Facilities

(1) Grinding, plating, and painting of propeller components have the potential
for health and safety hazards beyond that of other areas of a typical
workshop. It is expected that such areas be in compliance with industry
standards and governmental regulations concerning occupational safety
and health, as well as environmental protection.

(2) Workshop areas segregated to prevent contamination. Separate

need to be
areas should be designated for cleaning, inspection, painting, plating, and

assembly. Propeller balancing must be performed in a draft free area.

2. Special Tools

NOTE: responsibility of the repair station to determine the special tooling

It is the
required for the propeller they are servicing or overhauling. The applicable
overhaul manual and the numerical index of Manual No. 165A provide
necessary information. Hartzell maintains no exact list of tools required for
specific models of propellers or levels of service.
A. Special Tools

Hartzell Tool and Equipment Manual No. 165A contains a listing special tools
of
available from Hartzell. The manual also includes vendor lists for other specialty
tooling not sold by Hartzell.
B. Listings
The Introduction section of Manual No. 165A provides information about what is
included in the listings and how to quickly locate tools.

SPECIP~L TOOLS, FIXTURES, *ND EaUIPMeNT 61 ’1 0’00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

(This page is intentionally blank.)

Page
SPECIAL TOOLS, FIXTURES, AND EPUIPMENT 61’1 0’00 904Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 100E

CONTENTS

1. Introduction 1003

A. General 1003

Parts List 1003

B. Using the Illustrated
2. The Illustrated Parts List

A. Detailed Parts List 1004

B. Revisions 1006

C. Vendors 1007

Illustrated Parts List for HC-D2V20-3 1009

Illustrated Parts List for HC-D2MV20-3 1017

Ilustrated Parts List for HC-D3V20-6L 1025

Illustrated Parts List for HC-D3MV20-6L 1033

Illustrated Parts List for HC-D2V20-7 and 8.................. 1043

Illustrated Parts List for HC-D2MV20-7 and 8 1055

Illustrated Parts List for HC-D3MV20-8D 1067

ILLUSTRATED PARTS LIST 61 -10-00

 PROPELLER YPINUPIL
HARTZELL

FIGURES

HC-D2V20-3
Propeller Assembly Figure 1001
Clamp Assembly Figure 1002 1010
91-3E Hydraulic Unit Figure 1003.....,.,., 1012
93-D Valve Assembly Figure 1004.....,

HC-D2MV20-3
Propeller Assembly Figure 1 005
Clamp Assembly Figure 1006.....,.,., 1018
91-3E Hydraulic Unit Figure 1007.....,.,... 1020
93-D Valve Assembly Figure 1008.....,..,.., 1

HC-D3V20-6L
Propeller Assembly Figure 1009 1024
Clamp Assembly Figure 1010............... 1026
91-6L Hydraulic Unit Figure 1011 1028
93-D Valve Assembly Figure 1012.....,..,.., 1030

HC-D3MV20-6L
Propeller Assembly Figure 1 01 3 1 032
Clamp Assembly Figure 1014.....,.,.. 1034
91-6L Hydraulic Unit Figure 1015............... 1036
93-D Valve Assembly Figure 1016.....,..,.., 1040

HC-D2V20-7 and 8
Propeller Assembly Figure 101 7 1 042
Clamp Assembly Figure 1018.....,.,..
91-7DS,-8DS Hydraulic Unit Figure 1019.....,,,,, 1046
93-A,-B,-C Valve Assembly Figure 1020.....,,,,, 1050
93-AG,-BG,-CG Valve Assembly Figure 1021 1052

HC-D2MV20-7 and 8
Propeller Assembly Figure 1022 1 054
Clamp Assembly Figure 1023.....,,, 1056
91-7DS,-8DS Hydraulic Unit Figure 1024.....,,,,, 1058
93-A,-B,-C Valve Assembly Figure 1025.....,,,,, 1062
93-AG,-BG,-CG Valve Assembly Figure 1026.....,,,, 1064

HC-D3MV20-8D
Propeller Assembly Figure 1027 1 066
Clamp Assembly Figure 1028.....,.,.,.. 1068
91-8DT Hydraulic Unit Figure 1029.....,,,. 1070
93-E Valve Assembly Figure 1030.....,,, 1072

61-10-00
 PROPELLER MAINTENANCE MANUAL
H RT Z E L L 100E

1. Introduction

A. General

(1) configurations for the

This Illustrated Parts List contains all of the current
specified propellers manufactured by Hartzell Propeller Inc. and supersedes
any prints that may have previously been supplied for part and assembly
information. The parts lists contained within the Illustrated Parts List are to be
used for verifying the configuration of propeller models and ordering parts.

CAUTION: ILLUSTRATIONS IN THE ILLUSTRATED PARTS LIST ARE TO BE

USED FOR IDENTIFYING PARTS AND SHOULD NOT BE USED
AS A MAINTENANCE REFERENCE FOR ASSEMBLY.

(2) Figures are for reference only. The figures provide general views of parts. For
ease of illustration, typical views of some parts were created and shown in

multiple figures. For this reason, illustrated parts may not exactly reflect parts
contained in some propeller assemblies.

B. Using the Illustrated Parts List

(1) Every effort has been made to include all of the propellers and configurations
manuf actu red by Hartzell P repel le r I nc. If an ove rhau I facility has q uestions
about a propeller configuration as stated in the Illustrated Parts List, contact
the Hartzell Propeller Product Support Department.

(2) Basic Propeller Parts: Refers to all of the propeller components that may be
unique to a particular propeller model.

,,T,,lsT61’10’00
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

The Illustrated Parts List

A. Detailed Parts List

The Detailed Parts List consists of theFigure/item Number, Part Number,

Description, Configuration Change Code, Effectivity Code and Units Per Assembly.
Space is reserved for the Airline Stock Number. The following is an explanation of
each column.

(1) Fig/ltem Number

(a) Number refers to the illustration where items appear. Item
Figure
Numbers are assigned in broken sequence to allow the insertion of
subsequent additional parts. Items listed but not illustrated are identified
by a dash to the left of the item number.
(b) Alpha variants will be used to add additional items. There are two
reasons for the use of alpha variants:
1 A part may have an alternate, or may be superseded, replaced, or
obsoleted by another part. For example, the socket head cap screw
(A-2037) that is item 640 was replaced by the socket head cap
screw (A-2037-2C) that is item 640A.

2 An Illustrated Parts List may contain multiple configurations.

Effectivity codes are used to distinguish different part numbers
within the same list. For configuration may use a
example, one

cylinder (C-l 1 1-7) that is item 540, yet another configuration uses a
counterweight (C-111-8) that is item 540A. Effectivity codes are
very important in the determination of parts in a given configuration.

(2) Part Number

Use the Hartzell part number when ordering the part from Hartzell or a Hartzell
approved distributor. Digits of Hartzell Part Numbers have no significance
other than to identify a part.
(3) Airline Stock Number

Space is reserved for the Airline Stock Number.

(4) Nomenclature

This column identifies the item. The relationship of parts to assembly is

indicated by the useof indentations. This column may also contain vendor
CAGE codes, as applicable. Information regarding part alternative,
supersedure, replacement, or obsolescence may also be found in this column.
Refer to Revisions, below, for further information regarding alternate,
superseded, replaced or obsoleted parts.

61-10-00
 PROPELLER MAINTENANCE MANUAL
H~RTZ ELL 100E

(5) Effectivity Code (EFF CODE)

The effectivity column prefix and/or suffix of the propeller model to
shows the
which the parts apply. In some cases, the specific engine or aircraft
manufacturer may be called out. Effectivity codes assigned apply only to the
figure/listing in which they appear. Parts common to all end items show no
code.

A HC-D2(V,MV)20-7, Navion only, without governor

B HC-D2(V,MV)20-7 Navion only, with governor

´•C HC-D2(V,MV)20-7 Bonanza, withoutgovernor

D HC-D2(V,MV)20-7 Bonanza, with governor

E HC-D2(V, MV)20-8 All except Super Navion, without governor

F HC-D2(V,MV)20-8 Super Navion, without governor

G HC-D2(V,MV)20-8 Super Navion, with governor

´•H HC-D2(V,MV)20-7 LuscombellA

Parts common to ail end items show no code.

(6) Units Per Assembly (UPA)

Designates the total quantity of an item required for the next higher assembly
or subassembly.

AR As Required
RF Reference Only no part quantity.

NOTE: Be sure to check the number of assemblies required before ordering

parts that are part of an assembly.

P~RTS LISTG1’10’00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

B. Revisions

(1) Alternate

Alternate parts are identified

by the term "ALTERNATE" in the Description
column. Alternate items are considered airworthy for continued flight and
existing stock of parts may be used for maintenance and/or repair. The new or
alternate part numbers may be used interchangeably when ordering/stocking
new parts.
(2) Supersedure
Part changes are identified
by the terms "SUPERSEDES ITEM Or

"SUPERSEDED BY ITEM in the Description column. Superseded

items are considered airworthy for continued flight and existing stock of
superseded parts may used for maintenance and/or repair. Superseded parts
may no longer be available, and the new part number must be used when
ordering/stocking new parts.
(3) Replacement
Part changes identified by the terms "REPLACES ITEM Or
"REPLACED BY ITEM in the
Description column are considered
airworthy for continued flight, but must be replaced with a part with the new part
number at overhaul. Existing stock of replaced parts may not be used for
maintenance and/or repair of effected assemblies. Replaced parts may no
longer be available, and the new part number must be used when ordering/
stocking new parts.
(4) Obsolescence

Obsolete parts are identified by "OBS" in the Units Per Assembly (UPA)
column. Obsolete items are considered unairworthy for continued flight.

(5) Service Documents and Airworthiness Directives

(a) In the event of modification or rework of an existing part, the supersedure,

replacement, or obsolescence of a part, or the addition of parts installed
by a Service Bulletin (SB) or Service Letter (SL), the SE or SL number
will appear in the Description column as "SB or "SL after
the description.

(b) When a SE has arelationship to an Airworthiness Directive (AD), the AD

will be shown in parentheses after the SE number as SE
(AD

sl-lo-oo
 PROPELLER MAINTENANCE MANUAL
HA RT~ZI c L L 100E

C. Vendors

(1) Many O-rings, fasteners, and other vendor supplied hardware listed in Hartzell
manuals have previously been specified with AN, MS, NAS or vendor part
number. To provide internal controls and procurement flexibility, Hartzell has
made engineering changes to provide all O-rings, fasteners, and hardware
with a Hartzell part number. Parts shipments from Hartzell will specify only the
Hartzell part numbers.

(2) Some O-rings, fasteners, and hardware manufactured in accordance with

established industry specifications (certain AN, MS, NAS items) are
acceptable for use in Hartzell products without additional standards imposed
by Hartzell. Refer to Manual 202A (61-01-01 Chapter 2200, Vendor Cross
Reference, fora listing of part number interchangeability. Where allowable,
both the Hartzell part number item and AN, MS, NAS, and other specified
vendor numbers items can be used interchangeably. The Hartzell part number
must be used when ordering these parts from Hartzell.

ILLVSTRI\TED P~RTS LIST 61 -1 0-00

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1008

APS5093

200
220

10

150 500
140

;r~)~_130
9P,o6j
120

40 20110 100
50
80
160 b/a~ ~,70
180

170 190

ORIGINAL
As Received By
ATP

HC-D2V20-3 Propeller Assembly

Figure 1001

1008
ILLUSTRATED PARTS LIST 61 -1 0-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART AIRLINE DESCRIPTION CHG m luPn

FIG./ITEM
NUMBER STOCKNUMBER I ~234rs7 CODE CODE
NUMBER

1001

HC-D2V20-3 PROPELLER ASSEMBLY RF

-1

HUB UNIT 1
10 840-124

´•´•PILOTTUBE 2
20 A-1496-(
SUPERSEDED BY ITEM 20A

´•´•PILOTTUBE 2
20A D-7080-(
SUPERSEDES ITEM 20

´•´•HUB 1
-30 C-999-1L

A-1 16A-1~ I I´•´•´•BUSHING 2

40

A-155 ´•´•BUSHING 1
50

A-974 WIRE RETENTION RING 2

70

GUIDE RING 2
80 A-972

A-971 SPLIT BEARING UNIT 2

-90

´•´•RACE 4
100 A-971-B

B-61 44-2 ´•´•BEARING, BALL 36

110

"RACE 4
120 A-971-A

BALL SPACER 1
130 A-311

BEARING RETENTION RING 2

140 1 A-2027

C-331 7-230 O-RING, BLADE 2

150

PULLER RING 1
160 A-156

A-46 SNAP RING 1

170

HUB NUT 1
180 A-63B

A-847 HUB SAFETY PIN 1

190

REAR CONE 1
200 A-50-1

A-186 SPACER, REAR CONE AR

210

BLOCK, PITCH CHANGE 2

220 A-95-A

A-165-3 SPACER RING 2

-320

HYDRAULIC UNIT RF
500 C-91-3E

D-330
ITEM NOT ILLUSTRATED

HC-D2V20-3 Propeller Assembly

1009
ILLUSTRATED PARTS LIST 61-10-00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

410

430

400 o
380

8
a
/~O
n’ 350
360
340
370
390405~ Y/’/ 450

3´•´•
470
460
440

HC-D2V2013 Clamp Assembly

Figure 1002

1010
ILLVSTRATED PARTS LIST 61’1 0-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HAR~TZELL 100E

FIG.IITEMI PART AIRLINE DESCRIPTION CHG m luPn

NUMBER NUMBER STOCKNUMBER 1234587 CODEI CODE

1002

-330 838-29 CLAMPASSEMBLY RF

340 A-833-4 COUNTER WEIGHT UNIT 2

350 A-65 COUNTER WEIGHT DOWEL PIN 2

360 A-2036-30 SOCKET HEAD CAP SCREW 4

370 A-285 STAKING PIN, CAPSCREW 4

380 A-295 LINK SCREW, PUSH ROD 2

390 A-285 STAKING PIN, LINKSCREW 2

400 8-6588-1 LUBRICATION FITTING 2

400A 8-6855 LUBRICATION PLUG 2

405 8-6588-1 LUBRICATION FITTING 2

410 8-3838-3-2 COTTER PIN 4

420 A-321 SOCKET SCREW 4

430 A-47-1 ´•´•GASKET 4

440 C-3-3A ´•´•CLAMP 2

450 A-2017 CLAMP BOLT 2

460 A-2031 ´•´•WASHER 4

470 A-2043-1 CLAMP NUT 4

-480 8-6544 ´•´•LUBRICAP 4

-483 8-3840-( WEIGHT SCREW AR

-484 A-48 BALANCEWEIGHT AR

ITEM NOT ILLUSTRATED

HCID2V20-3 Clamp Assembly

1011
ILLUSTRATED PARTS LIST 61 -1 0-00 Rev. 2 Jun/OlPage
 PROPELLER MAINTE NANCE MANUAL
HARTZELL 100E

APS5098

650
910

620 690
550
900
920

b
920 910
960
890

790 540
820
OS
800
510

3
670
930
710

750720
760
810 780

HC-D2V20-3 91-32 Hydraulic Unit

Figure 1003

1012
PPIRTS LIST 61 -1 0-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL iaoE

PART AIRLINE DESCRIPTION CHG I EA IUPA

NUMBER NUMBER STOCKNUMBER 1 1234587 CODE CODE

1003

-500 C-91-3E HYDRAULIC UNIT 1

510 D-78 ´•´•PISTON 1

540 C-77 ´•´•CYLINDER 1

550 A-11-A GUIDE PIN 3

-570 A-312 ´•´•NUT 3

620 C-331 7-445 ´•´•O-RING 1

650 A-181 GASKET 1

670 A-38-BG ´•´•BEARING,THRUST 1

690 C-3317-341 O-RING 1

710 8-73 GASKET,COVER PLATE 1

720 8-12-3 COVER PLATE 1

-730 A-2043-1 ELASTIC NUT 6

-740 A-181 ´•´•GASKET 1

750 8-3864-39 INTERNAL LOCK WASHER, PLATE 12

760 8-3840-6 FILISTERHEADSCREW, PLATE 12

-770 8-109-10 JACK PLATE UNIT 1

780 B-87F ´•´•´•JACKPLATE 1

790 A-i 14-F ´•´•´•ROD,STAKINGPIN 2

800 A-97-3E PUSH ROD 2

810 A-821L I I´•´•´•FORK 2

820 A-1 14-8 ´•´•´•STAKINGPIN,FORK 2

890 A-76 ´•´•STOP, LEVER 1

900 A-41 ´•´•STOP, PITCHCONTROLVALVE 1

910 8-3840-6 FILISTER HEAD SCREW, STOP 4

920 8-3864-39 INTERNAL LOCK WASHER, STOP 4

930 A-43 WIRE RETENTION 1

960 8-6588-1 LUBRICATION FITTING (SEE NOTE 1) 1

-963 8-6855 PLUG(SEE NOTE 1) 1

NOTE 1: After greasing the A-38(

bearina. reDlace the 8-6588-1
lubricavCon fitting with
the 8-6855 plug.

ITEM NOT ILLUSTRATED

HC-D2V20-3 91-3E Hydraulic Unit

1013
ILLUSTRATED PARTS LIST 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

APS6002

8 1270
1240

1050

1/ 1200
1210
1260
g,

1220

1180
x/
aT~ i,’ 1100
1250

1170
1010

ORIGINAL
As Received By
ATP

HC-D2V2013 9310 Valve Assembly

Figure 1004

1014
ILLUSTRATED PARTS LIST 61 -1 0-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART I AIRLINE DESCRIPTION CHG I EA IUPA

NUMBER NUMBER STOCKNUMBER 1 1234587 CODE CODE

1004

-1000 B-93-D VALVEASSEMBLY 1

1010 A-71-2 ´•´•GASKET 1

-1030 8-299 ´•´•VALVEUNIT 1

1040 8-301 ´•´•´•VALVEBODY 1

1050 A-307 ´•´•´•VALVESPOOL 1

1170 1 8-3838-3-2 COTTER PIN 1

1180 1 A-306-A ´•´•´•SPRING 1

1190 A-285 ´•´•´•STAKINGPIN 1

1200 A-303 GUIDE PIN 1

1210 A-302 GUIDE ROD 1

1220 8-3838-3-2 COTTER PIN 1

1230 1 C-3317-112 ´•´•´•O-RING I I I 1

1240 1 A-44 ´•´•VALVELINK 1

1250 A-2038-6 1´• I´•´•SOCKETHEADSCREW 2

1260 8-3838-2-2 COTTER PIN, A238-6 S. HD. SCREW 2

1270 8-6644-21 CLEVIS PIN 1

ITEM NOT ILLUSTRATED

HC1D2V20-3 9310 Valve Assembly

1015
ILLUSTRATED PARTS LIST 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

APS5093

210

220

10

150 500

3 140

Pb6j110 40 20
120
130

100
50
80
160´•
70
180

170 190
S,4

ORIGINAL
As Received BY
ATP

HCID2MV20~3 Propellet Assembly

Figure 1005

1016
ILLUSTRATED PARTS LIST 61 -1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART AIRLINE DESCRIPTION CHG I EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE CODE

1005

HC-D2MV20-3 PROPELLER ASSEMBLY 1

-1

840-124 HUB UNIT 1

10 1

´•´•PILOTTUBE 2
20 A-1496-(
SUPERSEDED BY ITEM 20A

´•´•PILOTTUBE 2
20A D-7080-(
SUPERSEDES ITEM 20

C-999-1L ´•´•HUB 1
-30

40 A-i 16A-1 ´•´•´•BUSHING 2

50 A-155 ´•´•BUSHING 1

70 A-974 WIRE RETENTION RING 2

80 1 A-972 GUIDE RING 2

1 A-971 SPLIT BEARING UNIT 2

-90

100 A-971-B ´•´•RACE 4

110 B-61 44-2 ´•´•BEARING, BALL 36

120 A-971-A ´•´•RACE 4

A-311 BALL SPACER 1

130

A-2027 BEARING RETENTION RING 2

140 1

C-331 7-230 O-RING, BLADE 2

150

PULLER RING 1
160 1 A-156

170 1 A-46 SNAPRING 1

A-63B HUB NUT 1

180

A-847 HUBSAFETY PIN 1

190

A-50-1 REAR CONE 1

200

A-186 SPACER, REAR CONE 1

210 1

A-95-A BLOCK, PITCH CHANGE 2

220

A-165-6 SPACER RING 1

-320

(USED FOR NEW PROPELLER ASSEMBLY)

SPACER RING, SE HC-SB-61-241 AR

-320A A-165-(4,5)
HYDRAULIC UNIT RF
-500 C-91-3E

D330
ITEM NOT ILLUSTRATED

HC-D2MV20-3 Propeller Assembly

1017
ILLUSTRATED PARTS LIST 61 ’1 0’00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

420
410

430

380 400 o

’d

n’ 350~g
360340
370/ 39O

,/’,450
470
3´•´•
460
440

HC-D2MV20-3 Clamp Assembly

Figure 1006

1018
61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

AIRLINE DESCRIPTION CHG EFF UPA

PART
STOCK NUMBER CODEI CODE
NUMBER NUMBER 1234567

1006

CLAMPASSEMBLY 1
-330 838-1029

COUNTER WEIGHT UNIT 2

340 A-833-4

COUNTER WEIGHT DOWEL PIN 2

350 A-65

SOCKET HEAD CAP SCREW 4

360 A-2036-30

STAKING PIN, CAP SCREW 4

370 A-285

LINK SCREW, PUSH ROD 2

380 A-295

STAKING PIN, LINKSCREW 2

390 A-285

LUBRICATION FITTING 2
400 8-6588-1

LUBRICATION PLUG 2
400A 8-6855

LUBRICATION FITTING 2
405 8-6588-1

COTTER PIN 4
410 B-3838-3-2

SOCKET SCREW 4
420 A-321

´•´•GASKET 4
430 1 A-6871-1

CLAMP 2
440 D-6831-3A

´•´•CLAMPBOLT 2
450 A-2017

´•´•WASHER 4
460 A-2031

CLAMP NUT 4
470 A-2043- 1

´•´•LUBRICAP 4
-480 1 8-6544

WEIGHT SCREW AR
-483 8-3840-(
BALANCEWEIGHT AR
-484 A-48

ITEM NOT ILLUSTRATED

HC-D2MV20-3 Clamp Assembly

1019

ILLUSTRATED PARTS ,lsT 61 -1 0-00 Rev. 2 Jun/OlPage

 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 100E

APS5098

650
910
920
900
550
620 690

920 910
960
890

790 540
820
OF
800

M 510

670
930

’II
760
750720
710

810 780

HC-D2MV20-3 91-36 Hydraulic Unit

Figure 1007

1020
ILLUSTRATED PARTS LIST 61 -1 0-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

PART AIRLINE DESCRIPTION CHG EFF IUPA

NUMBER NUMBER STOCKNUMBER 1234587 CODE CODE

1007

-500 C-91-3E HYDRAULIC UNIT 1

510 D-78 ´•´•PISTON 1

540 C-77 ´•´•CYLINDER 1

550 A-11-A GUIDE PIN 3

-570 A-312 ´•´•NUT 3

620 C-331 7-445 ´•´•O-RING 1

650 1 A-181 ´•´•GASKET 1

670 A-38-BG I I´•´•BEARING,THRUST 1

690 C-331 7-341 ´•´•O-RING 1

710 8-73 GASKET,COVER PLATE 1

720 8-12-3 COVER PLATE 1

-730 A-2043-1 ELASTIC NUT 6

-740 A-181 ´•´•GASKET 1

750 8-3864-39 INTERNAL LOCK WASHER, PLATE 12

760 B-3840-6 FILISTER HEAD SCREW, PLATE 12

-770 B-l 09-10 JACK PLATE UNIT 1

780 B-87F ´•´•´•JACKPLATE 1

790 A-1 14-F ´•´•´•ROD,STAKINGPIN 2

800 A-97-3E I I PUSH ROD 2

810 A-821L I I´•´•´•FORK 2

820 A-114-8 ´•´•´•STAKINGPIN,FORK 2

890 A-76 ´•´•STOP, LEVER 1

900 A-41 STOP, PITCH CONTROLVALVE 1

910 8-3840-6 FILISTER HEAD SCREW, STOP 4

920 8-3864-39 INTERNAL LOCKWASHER, STOP 4

930 A-43 WIRE RETENTION 1

960 8-6588-1 LUBRICATION FITTING (SEE NOTE 1) 1

-963 8-6855 PLUG(SEE NOTE 1) 1

NOTE 1: After greasing the A-38(

bearina, replace the 8-6588-1
fitting with
the 8-6855 plug.

ITEM NOT ILLUSTRATED

HC-D2MV2013 91-3E Hydraulic Unit

1021
ILLUSTRATED PARTS LIST61-10-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

Apssoo2

e 1270
1240

1050

1040
1210
1230
1/ 1200
1260rS

1220

1180
x,
aT’ i,’ 1100
1250

1170~ 1010

ORIGINAL
As Received By
ATP

HCID2MV2013 93-D Valve Assembly

Figure 1008

1022
ILLUSTRATED PARTS LIST 61’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART I AIRLINE DESCRIPTION CHG I EFF IUPA

NUMBER NUMBER ISTOCK NUMBER I 1 2 3 4 s s 7 CODEI CODE

1008

-1000 8-93-D VALVEASSEMBLY 1

1010 A-71-2 ´•´•GASKET 1

-1030 1 8-299 ´•´•VALVEUNIT 1

1040 8-301 ´•´•´•VALVEBODY 1

1050 A-307 ´•´•´•VALVESPOOL 1

1170 8-3838-3-2 COTTER PIN 1

1180 A-306-A ´•´•´•SPRING 1

1190 A-285 ´•´•´•STAKINGPIN 1

1200 A-303 GUIDE PIN 1

1210 A-302 GUIDE ROD 1

1220 8-3838-3-2 COTTER PIN 1

1230 C-3317-112 1 I´•´•´•O-RING 1

1240 A-44 ´•´•VALVELINK 1

1250 A-2038-6 SOCKET HEAD SCREW 2

1260 8-3838-2-2 COTTER PIN, A238-6 S. HD. SCREW 2

1270 8-6644-21 CLEVIS PIN 1

ITEM NOT ILLUSTRATED

HC-D2MV2013 931D Valve Assembly

1023
ILLUSTRATED PARTS LIST 61-10-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
H~ RTZ E L L 1 OOE

APS5092

210
200
220

10

312

c~ 500

290 150
310

bao
30050 /´•1
~g_cS
120
30
110
100

70

ORIGINAL
As Received By
ATP

HCID3V2016L Propeller Assembly

Figure 1009

61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART AIRLINE DESCRIPTION CHG I EFF UPA

NUMBER NUMBER STOCK NUMBER I 1 2 3 4 J e7 CODE CODE

1009

-1 HC-D3V20-6L PROPELLER ASSEMBLY 1

10 840-85 HUB UNIT 1

20 A-1496-( I I´•´•PILOTTUBE 3
SUPERSEDED BY ITEM 20A

20A D-7080-( ´•´•PILOTTUBE 3

SUPERSEDES ITEM 20

-30 C-1482 1 I.. HUB 1

50 A-155 ´•´•BUSHING 1

70 A-974 WIRE RETENTION RING 2

80 A-972 GUIDE RING 2

-90 A-971 SPLIT BEARING UNIT 2

100 1 A-971-B I I´•´•RACE 4

110 1 B-61 44-2 ´•´•BEARING,BALL 36

120 1 A-971-A ´•´•RACE 4

130 1 A-31 1 BALL SPACER 1

140 A-2027 1 I BEARING RETENTION RING 2

150 1 C-331 7-230 0-RING, BLADE 2

160 A-870 PULLER RING 1

180 A-63B HUB NUT 1

190 A-847 HUBSAFETY PIN 1

200 A-50-1 REAR CONE 1

210 1 A-186 SPACER, REAR CONE AR

220 1 A-95-A BLOCK, PITCH CHANGE 3

290 1 C-331 7-235 O-RING, NUT 3

300 1 834-1L GUIDE COLLAR UNIT 1

-303 A-1 16D-1 PLASTIC BUSHING 3

-305 A-2038-12 SELFLOCKING SOCK. HD CAP SCREW 1

-307 A-i 14C ´•´•STAKINGPIN 3

-310 B-352 NUT, GUIDE COLLAR 1

312 A-827-7 SLEEVE 3

313 A-970-2 REVERSESTOP 3

314 A-965 WASHER 3

315 A-848 NUT 3

500 91-6L HYDRAULIC UNIT RF

0360
ITEM NOT ILLUSTRATED

HC-D3V20-6L Propeller Assembly

1025
ILLUSTRATED PARTS LIST 61 ’1 0-00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HP~ RTZ E L L 1 225

nps509s

420
410

430

400 o
380

/~O
n’ 350
360
340
´•1390
370
405
450

470
3´•´•
460
440

HCID3V20-6L Clamp Assembly

Figure 1010

1026
ILLUSTRATED PARTS LIST 61’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 100E

PART I AIRLINE DESCRIPTION CHG EFF IUPA

NUMBER I NUMBER STOCK NUMBER I 1 2 3 4 s B 7 CODE CODE

1010

-330 838-29 CLAMPASSEMBLY 3

340 833-4 COUNTER WEIGHT UNIT 3

350 A-65 COUNTER WEIGHT DOWEL PIN 3

360 A-2036-30 SOCKET HEAD CAP SCREW 6

370 A-285 STAKING PIN, CAP SCREW 6

380 A-295 LINK SCREW, PUSH ROD 3

390 A-285 STAKING PIN, LINKSCREW 3

400 1 B-6588-1 LUBRICATION FITTING 3

400A B-6855 LUBRICATION PLUG 3

405 8-6588-1 LUBRICATION FITTING I I 1 3

410 B-3838-3-2 COTTER PIN 6

420 A-321 ´•´•CLAMPSOCKET 6

430 A-47-1 ´•´•GASKET 6

440 C-3-3A ´•´•CLAMP I I 1 3

450 A-2017 ´•´•CLAMPBOLT 6

460 A-2031 ´•´•WASHER I I I 6

470 A-2043-1 CLAMP NUT I I 1 6

-480 B-6544 LUBRICAP 6

-483 B-3840-( WEIGHT SCREW AR

-484 A-48 BALANCEWEIGHT AR

ITEM NOT ILLUSTRATED

HC-D3V20-6L Clamp Assembly

1027
ILLUSTRATED PARTS LIST 61-10-00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

APS6000

650

920910
620
690
550
900
b
920 910
960

890
540
790
830
800
M 510

670
930
710

750720
760

810 780

HCID3V20-6L 91-6L Hydraulic Unit

Figure 1011

1028
,,,,,,,,,,,,,,w LIST 61 -1 0-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

AIRLINE DESCRIPTION CHG I EFF UPA

PART
STOCK NUMBER I CODE CODE
NUMBER NUMBER 1 2 3 4 5 6 7

1011

HYDRAULIC UNIT 1
-500 91-6L

´•´•PISTON 1
510 D-78

´•´•CYLINDER 1
540 i C-77

GUIDE PIN 3
550 A-ii-A

´•´•NUT 3
-570 1 A-312

´•´•O-RING 1
620 C-331 7-445

´•´•GASKET 1
650 A-181

´•´•BEARING, THRUST 1
670 A-38-BG

´•´•O-RING 1
690 C-331 7-341

GASKET, COVER PLATE 1

710 8-73

COVER PLATE 1
720 8-12-3

ELASTIC NUT 6
-730 1 A-2043
SUPERSEDED BY ITEM 730A

ELASTIC NUT 6
-730A 1 A-2043-1
SUPERSEDES ITEM 730

INTERNAL LOCK WASHER, PLATE 12

750 8-3864-39

FILLISTER HEAD SCREW, PLATE 1

760 8-3840-6

´•´•JACKASSEMBLY 1
-770 1 B-351-3

´•´•´•JACKPLATE 1
780 8-356

ROD, STAKING PIN 3

790 A-1 14-8

PUSH ROD 3
800 1 A-826-10

´•´•´•FORK 3
810 A-921-1L

SET SCREW 3
830 1 A-2039

´•´•STOP, LEVER 1
890 A-76

STOP, PITCH CONTROLVALVE 1

900 1 A-41

FILISTER HEAD SCREW, STOP 4

910 1 8-3840-6

INTERNAL LOCK WASHER, STOP 4

920 8-3864-39

WIRE RING 1
930 1 A-43

LUBRICATION FITTING (SEE NOTE 1) 1

960 8-6588-1
PLUG NOTE 1) 1
-963 1 8-6855 (SEE
NOTE 1: After greasing the A-38(
bearin~, replace the 8-6~588-1
lubrica~ion titting with
the B-6855 plug.

ITEM NOT ILLUSTRATED

HC-D3V20-6L 91-6L Hydraulic Unit

1029

ILLUSTRATED PARTS LIST 61-10-00 Rev. 2 Jun/OlPage

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1006

APS6M)2

8 1270
1240

1050

1/ 1200
1210
1230 1260
1040
H,

1220

1180
x/
sCI,/ 1100
1250

1170
1010

HC-D3V2016L 93-D Valve Assembly

Figure 1012

1030
ILLUSTRATED PARTS LIST 61’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

AIRLINE DESCRIPTION CHG EFF IUPA

PART
STOCK NUMBER 1234587 CODE CODE
NUMBER NUMBER

1012

VALVEASSEMBLY 1
-1000 93-D

´•´•GASKET 1
1010 A-71-2

´•´•VALVEUNIT I I I 1
-1030 8-299

´•.´•VALVEBODY 1
1040 8-301

´•´•´•VALVESPOOL 1
1050 A-307

COTTER PIN 1
1170 8-3838-3-2

´•.´•SPRING 1
1180 A-306-A

´•´•´•STAKINGPIN 1
1190 A-285

GUIDE PIN 1
1200 A-303

GUIDE ROD 1
1210 A-302

COTTER PIN 1
1220 8-3838-3-2

O-RING 1
1230 C-3317-112

´•´•VALVELINK 1
1240 A-44

SOCKET HEAD SCREW 2

1250 A-2038-6

COTTER PIN, SOCKET HEAD SCREW 2

1260 8-3838-2-2

CLEVIS PIN 1
1270 8-6644-21

ITEM NOT ILLUSTRATED

HC-D3V20-6L 931D Valve Assembly

1031

ILLUSTRPITED P~RTS LIST 61 -1 0-00 Rev. 1 Apr/GOPage

 PROPELLER
HARTZELL MA:NO~EENANCE MANUAL

APS5092

210
200
220

10

312

’IPg~,!

500
315 314

310 290

16050ao
20150140
620
I

~:80 3006‘:\8Y~,FZ30 110

100

70

ORIGINAL
As Received sy
ATP

HC-D3MV20-6L Propeller Assembly

Figure 1013

1032
ILLUSTRATED PARTS LIST 61’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART I AIRLINE DESCRIPTION CHG I EFF IUPA

NUMBER I NUMBER STOCK NUMBER I 1 2 3 4 s s7 CODE CODE

1013

-1 HC-D3MV20-6L PROPELLER ASSEMBLY 1

10 1 840-85 HUB UNIT 1

20 A-1496-( ´•´•PILOTTUBE 3

-30 C-1482 1 I.. HUB 1

50 A-155 I I.. BUSHING 1

70 A-974 WIRE RETENTION RING 2

80 A-972 GUIDE RING 2

-90 A-97 i SPLIT BEARING UNIT 2

100 A-971-B ´•´•RACE 4

110 B-61 44-2 ´•´•BEARING, BALL 36

120 A-971-A I I.´•RACE 4

130 A-311 BALL SPACER I I I 1

140 A-2027 BEARING RETENTION RING 2

150 C-331 7-230 O-RING, BLADE 2

160 A-870 I I PULLER RING 1

180 A-63B HUB NUT 1

190 A-847 HUB SAFETY PIN 1

200 A-50-1 REAR CONE 1

210 A-186 SPACER, REAR CONE 1

220 1 A-95-A BLOCK, PITCH CHANGE 3

290 C-331 7-235 O-RING, NUT 3

300 834-1L GUIDE COLLAR UNIT 1

310 B-352 NUT, GUIDE COLLAR 1

312 1 A-827-7 SLEEVE 3

313 A-970-2 REVERSE STOP 3

314 1 A-965 WASHER 3

315 A-848 NUT I I 1 3

500 91-6L HYDRAULIC UNIT RF

ITEM NOT ILLUSTRATED

HC-D3MV20-6L Propeller Assembly

1033
ILLUSTRATED PARTS LIST 61-10-00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

~pssossn

420
410

430

380 40~
S~
n/ 350
360
340
370/
450

470
460
440

ORIGINAL
As Received By
ATP

HC-D3MV2016L Clamp Assembly

Figure 1014

1034
61-10-00
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

AIRLINE DESCRIPTION CHG I EFF UPA

PART
NUMBER STOCK NUMBER 1234587 CODE CODE
NUMBER

1014

CLAMPASSEMBLY 3
-330 838-1 029

COUNTER WEIGHT UNIT 3

340 1 833-4

COUNTER WEIGHT DOWEL PIN 3

350 A-65

SOCKET HEAD CAP SCREW 6

360 A-2036-30

STAKING PIN, CAP SCREW 6

370 A-285

LINK SCREW, PUSH ROD 3

380 A-295

STAKING PIN, LINKSCREW 3

390 A-285

8-6588-1 LUBRICATION FITTING 3

400

LUBRICATION PLUG 3
400A 8-6855

LUBRICATION FITTING 3
405 8-6588-1

B-3838-3-2 COTTER PIN 6

410

´•´•CLAMPSOCKET 6
420 A-321

GASKET 6
430 A-6871-1

´•´•CLAMP 3
440 D-6831-3A

CLAMP BOLT 6
450 A-2017

A-2031 ´•´•WASHER 6
460

CLAMP NUT 6
470 A-2043-1

´•´•LUBRICAP 6
-480 8-6544

WEIGHT SCREW AR
-483 8-3840-(
BALANCEWEIGHT AR
-484 1 A-48

ITEM NOT ILLUSTRATED

HC-D3MV20-6L Clamp Assembly

1035
ILLUSTRATED PARTS LIST 61-10-00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 100E

APS6000

650
910

620
690
550
900
920
.g,
920 910
960

890
~-rTT\ 540
790
830 /oa
800 510

670
930
710

750720
760

810 780

HC-D3MV2016L 9116L Hydraulic Unit

Figure 1015

1036
ILLUSTRATES PARTS LIST 61’1 0-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

PART AIRLINE DESCRIPTION CHG I EFF UPA

NUMBER I NUMBER STOCK NUMBER 1234587 CODEI CODE

1015

-500 1 91-6L HYDRAULIC UNIT 1

510 D-78 ´•´•PISTON 1

540 1 C-77 ´•´•CYLINDER 1

550 1 A-11-A GUIDE PIN 3

-570 A-312 ´•´•NUT 3

620 C-331 7-445 ´•´•"O"RING 1

650 1 A-181 ´•´•GASKET 1

670 A-38-BG ´•´•BEARING,THRUST 1

690 C-331 7-341 ´•´•"O"RING 1

710 8-73 GASKET,COVER PLATE 1

720 8-12-3 COVER PLATE 1

-730 A-2043 ELASTIC NUT 6

SUPERSEDED BY ITEM 730A

-730A 1 A-2043-1 ELASTIC NUT 6

SUPERSEDES ITEM 730

750 8-3864-39 INTERNAL LOCK WASHER, PLATE 1

760 8-3840-6 FILLISTER HEAD SCREW, PLATE 12

-770 8-351-3 ´•´•JACKASSEMBLY 1

780 8-356 ´•´•´•JACKPLATE 1

790 A-1 14-E ROD, STAKING PIN 3

800 A-826-10 PUSH ROD 3

810 A-921-1L ´•´•´•FORK 3

830 A-2039 SET SCREW 3

-840 A-827-7 ´•´•´•SLEEVE 3

-850 1 A-970-4 ´•´•´•SPACER 3

-860 1 A-965 ´•´•´•WASHER 3

-870 1 A-848 ´•´•´•NUT 3

-880 1 A-970-2 ´•´•´•SPACER 3

ITEM NOT ILLUSTRATED

HC-D3MV20-6L 91-6L Hydraulic Unit

1037
ILLUSTRATED PARTS LIST ~1 -1 0’00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

(This page is intentionally blank.)

I ILLVSTRPITEDPARTSLIST 61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 100E

PART AIRLINE DESCRIPTION CHG EFF IUPA

NUMBER NUMBER STOCK NUMBER I 1 2 3 4 s sT CODEI CODE

1015

890 A-76 ´•´•STOP, LEVER 1

900 A-41 STOP, PITCH CONTROLVALVE 1

910 8-3840-6 FILISTER HEAD SCREW, STOP 4

8-3864-39 INTERNAL LOCK WASHER, STOP 4

920

930 A-43 WIRE RING 1

960 8-6588-1 LUBRICATION FITTING (SEE NOTE 1) 1

-963 8-6855 PLUG (SEE NOTE 1) 1

NOTE 1: After greasing the A-38(

bearina, replace the 8-6588-1
lubricaXion titting with
the 8-6855 plug.

ITEM NOT ILLUSTRATED

HC-D3MV20-6L 91-6L Hydraulic Unit

1039
ILLUSTRATED PARTS LIST 61-10-00
 PROPELLER MANUIL
HARTZ ELL

APS6002

8 1270
1240

1050

1200
1210
1260
1040 1230

1220

1180

1190
1250

1170
1010

ORIGINAL
As Received By
ATP

HC-D3MV20-6L 931D Valve Assembly

Figure 1016

1040
ILLUSTRATED PARTS LIST 61’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
H4 RTZ ELL 1006

PART AIRLINE DESCRIPTION CHG EFF IUPA

STOCK NUMBER CODE CODE

NUMBER I NUMBER 1234167

1016

VALVEASSEMBLY 1
-1000 93-D

´•´•GASKET 1
1010 A-71-2

´•´•VALVEUNIT 1
-1030 8-299

´•´•´•VALVEBODY 1
1040 8-301

´•´•´•VALVESPOOL 1
1050 A-307

COTTER PIN 1
1170 8-3838-3-2

´•´•´•SPRING 1
1180 A-306-A

´•´•´•STAKINGPIN 1
1190 1 A-285

GUIDE PIN 1
1200 A-303

GUIDE ROD 1
1210 1 A-302

COTTER PIN 1
1220 8-3838-3-2

´•´•´•O-RING 1
1230 C-3317-112

´•´•VALVELINK 1
1240 A-44

SOCKET HEAD SCREW 2

1250 1 A-2038-6

COTTER PIN, SOCKET HEAD SCREW 2

1260 B-3838-2-2

CLEVIS PIN 1
1270 8-6644-21

ITEM NOT ILLUSTRATED

HC-D3MV20-6L 93-0 Valve Assembly

1041

ILLUSTRATED PARTS LIST ~1 ’1 0-00 Rev. 1 Apr/GOPage

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1000

APS5094

210

200

220

10

9RPao9160 T40
q:,
50
20~ U)1 01 08
120
130

70

170 190 -r
l/(a-x

ORIGINAL
As Received By
ATP

HC-D2V20-(7,8) Propeller Assembly

Figure 1017

1042
ILLUITRP~TED P~RTS LIST 61’1 0-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 100E

DESCRIPTION CHG I EFF UPA

PART AIRLINE
STOCK NUMBER CODEI CODE
NUMBER NUMBER 1234587

1017

HC-D2V20-7, 8 PROPELLER ASSEMBLY 1

-1

HUB UNIT 1
10 1 840-123

´•´•PILOTTUBE 2
20 A-1496-(
SUPERSEDED BY ITEM 20A
2
20A D-7080-( I I´•´•PILOTTUBE
SUPERSEDES ITEM 20

´•´•HUB 1
-30 C-999-1

´•´•´•BUSHING 2
40 A-i 16A-1

´•´•BUSHING 1
50 A-155

WIRE RETENTION RING 2

70 A-974

GUIDE RING 2
80 1 A-972

SPLIT BEARING UNIT 2

-90 A-971

´•´•RACE 4
100 1 A-971-B

´•´•BEARING, BALL 36
110 8-61 44-2

´•´•RACE 4
120 A-971-A

BALL SPACER 1
130 A-311

BEARING RETENTION RING 2

140 A-2027

O-RING,BLADE 2
150 1 C-3317-230

PULLER RING 1
160 A-156

SNAP RING 1
170 1 A-46 I I
HUB NUT 1
180 A-63B

HUBLOCKSAFETY 1
190 1 A-847

REAR CONE 1
200 A-50-1

CONE SPACER 1
210 A-186

BLOCK, PITCH CHANGE 2

220 1 A-95-A

SPINNER ADAPTER RING C,D,E 1

-250 1 C-l 75-2

SPINNER ADAPTER RING (ALTERNATE) C,D,E 1

-250A C-175-1

SPINNER ADAPTER RING (ALTERNATE) C,D,E 1

-2508 I A-1 65-2

SPINNER ADAPTER RING (ALTERNATE) C,D,E 1

-250C A-i 65-3

not using C-l 75-(1,2) A-165-(2,3) ring on the back of the hub must
NOTE: Props a or

use the B-109-9 jack assembly.

HEX HEAD BOLT 4
-260 1 B-3977-11

NUT 4
-270 8-6652-7

D-205o
ITEM NOT ILLUSTRATED

HC-D2V20-(7, 8) Propeller Assembly

1043

ILLUSTRATED PARTS LIST61-10-00 Rev. 2 Jun/OlPage

 PROPELLER
HA RTZ E LL MA:NOTOEENANCE MANUAL

420
410

430

400

~B, o

FB d

360
/3 80
340
390
370
v/’/ 450

~p´•´•
470
460
440

HC-D2V20-(7, 8) Clamp Assembly

Figure 1018

61 -1 0-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART AIRLINE DESCRIPTION CHG I EFF UPA

NUMBER NUMBER STOCK NUMBER I 1 2 4 s s 7 CODEI CODE

1018

-330 838-12 CLAMPASSEMBLY 2

B-l 7-6A ´•´•COUNTERWEIGHT 2

340

A-65 COUNTERWEIGHT DOWEL PIN 2

350

A-2036-12 SOCKET HEAD CAP SCREW 4

360

A-285 STAKING PIN, CAP SCREW 4

370

A-295 LINK SCREW, PUSH ROD 2

380

A-285 STAKING PIN, LINKSCREW 2

390

8-6588-1 LUBRICATION FITTING 2

400

8-6588-1 LUBRICATION FITTING 2

405

8-3838-3-2 COTTER PIN 4

410

A-321 SOCKET SCREW 4

420

A-47-1 ´•´•GASKET 4
430

C-3-1 A ´•´•CLAMP 2
440

A-2017 ´•´•CLAMPBOLT 4
450

A-2031 ´•´•WASHER 4
460

A-2043-1 ´•´•CLAMPNUT 4
470

´•´•LUBRICAP 4
-480 8-6544

WEIGHT SCREW AR
-483 8-3840-(
A-48 BALANCEWEIGHT AR
-484

ITEM NOT ILLUSTRATED

HC-D2V20-(7, 8) Clamp Assembly

1045
ILLUSTRATED PARTS ,lsT 61 -1 0-00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 100E

APS5097

950

550
580
650
B
630
640

530

540

960

660

680

800
820
790
S 590
610
700

510600
520
670

7; 750
720
710

760

810 780

HC-D2V20-(7, 8) 91-7DS,-8DS Hydraulic Unit

Figure 1019

1046
ILLUSTRATED PARTS LIST 61’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART AIRLINE DESCRIPTION CHG I EFF UPA

NUMBER STOCK NUMBER I 2 3 4 a s 7 CODE CODE

NUMBER 1

1019

-500 C-91-7DS HYDRAULIC UNIT A,B,C,D,HI 1

HYDRAULIC UNIT E,F,G 1

-500A C-91-8DS

´•´•PISTON 1
510 C-112-2

´•´•´•BUSHING 2
520 A-1 168-1

´•´•´•HELICOIL 1
530 8-6711-0500

´•´•CYLINDER A,B,C,D 1
540 C-111-7

540A C-111-8 ´•´•CYLINDER E,F,G

GUIDE ROD 2
550 A-122

´•´•´•STAKINGPIN 2
580 A-1 14-8

LOCK WASHER 18
590 8-3864-39

´•´•SCREW 18
600 B-3840-12

OUTER RING 1
610 8-120

´•´•WASHER A,B,C,D 4
630 A-128

SCREW, SOCKET HEAD CAP A,B,C,D 4

640 A-2037
REPLACED BY ITEM 640A

SCREW, SOCKET HEAD CAP A,B,C,D 4

640A A-2037-2C
REPLACES ITEM 640

´•´•GASKET A,B,C,D 1
650 A-135

´•´•GASKET E,F,G 1
650A A-1 81

´•´•DIAPHRAGM 1
660 8-119-2

´•´•BEARING,THRUST 1
670 A-38B

INNER RING 1
680 8-113-2

´•´•SCREW 8
700 8-3840-10

´•´•GASKET 1
710 8-73

COVER PLATE 1
720 B-l 2-7

1 I´•´•NUT E,F,G 6
-730 A-2043-1

LOCK WASHER 12
750 8-3864-39

´•´•SCREW 12
760 8-3840-6

ITEM NOT ILLUSTRATED

HC-D2V201(7,8) 9117DS,18DS Hydraulic Unit

1047

ILLUSTRATED PARTS LIST 61-10-00

 PROPELLER
HARTZ E LL MA:NOTOEENANCE MANUAL

(This page is intentionally blank.)

I ILLU8TRe~,TEDPIRTSLIST 61-10-00 Page

n,laprmo
1048
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 100E

DESCRIPTION CHG I EFF UPA

PART AIRLINE
CODE CODE
NUMBER NUMBER ISTOCKNUMBER 1234167

1019

´•´•JACKPLATEASSEMBLY 1
-770 B-109-9A

JACK PLATEASSEMBLY (ALTERNATE) 1

-770A B-109-9

using a C-l 75-(1 ,2) or A-165-(2,3) ring on the back of the hub must
NOTE: Props not
use the B-l 09-9 jack assembly.

´•´•´•JACK 1
780 1 B-87C-1

STAKING PIN, ROD 2

790 A-114F

PUSH ROD 2
800 A-97-7

810 A-821 ´•´•´•FORK I I 1 2

´•´•´•STAKINGPIN,FORK 2
820 A-1 14-8

´•´•O-RING E,F,G 6
-940 C-331 7-012

´•´•SCREW 1
950 A-121

LUBRICATION FITTING (SEE NOTE 1) 1

960 8-6588-1
1
-963 8-6855 PLUG(SEE NOTE 1)
NOTE 1: After greasing the A-38(
bearing, replace the 8-6588-1
lubrication fitting with
the 8-6855 plug.

ITEM NOT ILLUSTRATED

HCID2V20-(7,8) 9117DS,~8DS Hydraulic Unit

1049

ILLUSTRATED PASTS LIST 61 ’1 0’00 Rev. 1 Apr/GOPage

 PROPELLER
HA RTZ E L L MAI1N~ToEENANCE
E001LAUNAM

APS5099

1080-a ~Y1100
1050, ,1140

1060
1090
1040 1070

i 1120
e

1110

O 1075
1150

1130

1010

ORIGINAL
As Received By
ATP

HC-D2V20-(7,8) 93-A,IB,-C Valve Assembly

Figure 1020

1050
61-10-00
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

AIRLINE DESCRIPTION CHG EFF UPA

PART
CODE CODE
NUMBER NUMBER ISTOCKNUMBER 1234687

1020

VALVEASSEMBLY A 1
-1000 B-93-A

VALVEASSEMBLY C,E,H 1
-1GOOA 8-93-8

VALVEASSEMBLY F 1
-10008 B-93-C

´•´•GASKET 1
1010 A-71-2

´•´•WASHER 2
-1020 8-3837-0463

´•´•VALVEUNIT 1
-1030 8-166

´•´•´•BODY 1
1040 A-167

´•´•´•SPOOL 1
1050 A-168

´•´•´•O-RING 2
1060 C-3317-112

COTTER PIN 2
1070 8-3838-2-2

COTTER PIN 2
1075 8-3838-2-2

CLEVIS PIN 1
1080 8-6646-17

´•´•SPACER 1
1090 A-1 26

CLEVIS PIN 1
1100 8-6646-23 1´•
STOP NUT 1
1110 8-3870-1032

STOP SCREW 1
1120 8-3840-10

LINK 1
1130 A-i 84-6

´•´•LINK A 1
1140 A-180

´•´•LINK C 1
1140A A-187

SCREW, SOCKET HEAD CAP 2

1150 A-2038-10

ITEM NOT ILLUSTRATED

HC~D2V20-(7,8) 93-A,-B,IC Valve Assembly

1051

IUUSTRATED PARTS LIST 61 ’1 0’00 Rev. 1 Apr/GOPage

 PROPELLER
HARTZ ELL MA:NO~EENANCE MANUAL

APS5099A

1080

1050

1040
1070

e 1130

1010

1160

1015

ORIGINAL
As Received By
ATP

HC-D2V20-(7,8) 93-AG,IBG,-CG Valve Assembly

Figure 1021

1052
61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL iODE

PART I AIRLINE DESCRIPTION CHG I EFF IUPA

NUMBER NUMBER ISTOCK NUMBER I 1 2 3 4 s s 7 CODEI CODE

1021

-1000 B-93-AG VALVE ASSEMBLY B 1

-100GA B-93-BG VALVEASSEMBLY D 1

-1 0008 B-93-CG VALVEASSEMBLY G i

1010 A-71-2 ´•´•GASKET 1

1015 A-71-2 ´•´•GASKET G 1

-1020 1 8-3837-0463 WASHER 2

-1030 8-166 ´•´•VALVEUNIT 1

1040 A-167 ´•´•´•BODY 1

1050 1 A-168 ´•´•´•SPOOL 1

1060 C-3317-112 O-RING 2

1070 B-3838-2-2 COTTER PIN 1

1080 8-6646-23 CLEVIS PIN 1

1130 A-i 73-2 ´•´•LINK B 1

1130A A-1 73-4 ´•´•LINK D 1

11308 A-i 73-5 ´•´•LINK G 1

-1150 A-2038-10 SCREW, SOCKET HEAD CAP 2

1160 A-171 EXTENSION BLOCK G 1

ITEM NOT ILLUSTRATED

HCID2V20-(7,8) 93-AG,IBG,-CG Valve Assembly

1053
ILLUSTRATED PARTS LIST (il-10-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 1000

APS5094

220

~B

150
140
120

FPbO9:8´• 16070
40 20
110
100
80

170 190C

ORIGINAL
As Received BY
ATP

HCID2MV20-(7,8) Propeller Assembly

Figure 1022

1054
61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1WE

PART I AIRLINE DESCRIPTION I CHG I EA IUPA

NUMBER I NUMBER I STOCKNUMBER 1 1234567 CODEI CODE

1022

-1 HC-D2MV20-7, 8 PROPELLER ASSEMBLY 1

10 840-123 HUB UNIT 1

20 A-1496-( I I´•. PILOTTUBE 2

SUPERSEDED BY ITEM 20A

20A D-7080-( I I´•´•PILOTTUBE 2

SUPERSEDES ITEM 20

-30 C-999-1 1 I´•´•HUB 1

40 A-1 16A-1 I I.´•´•BUSHING I I 1 2

50 A-155 I I´•´•BUSHING 1

70 A-974 1 I WIRE RETENTION RING 2

80 A-972 GUIDE RING I I 1 2

-90 A-971 I I SPLIT BEARING UNIT 2

100 A-971-B I I´•´•RACE 4

110 8-61 44-2 ´•´•BEARING, BALL 36

120 1 A-971-A I I´•. RACE I I 1 4

130 A-311 I I BALL SPACER I I I 1

140 A-2027 1 I BEARING RETENTION RING 2

150 C-331 7-230 O-RING, BLADE 2

160 A-156 PULLER RING I I I 1

170 A-46 SNAP RING 1

180 A-63B HUB NUT I I I 1

190 A-847 HUB LOCK SAFETY I I I 1

200 A-50-1 REAR CONE 1

210 A-186 CONE SPACER 1

220 A-95-A BLOCK, PITCH CHANGE 2

-250 C-l 75-2 1 I SPINNER ADAPTER RING C,D,E 1

-250A C-175-1 SPINNER ADAPTER RING C,D,E 1

-2508 A-165-2 SPACER RING C,D,E 1

-250C A-165-3 SPACER RING C,D,E 1

NOTE: Props not using a ,2) or A-1 65-(2,3) ring

C-l 75-(1 on the back of the hub must
use the B-l 09-9 jack assembly.
-260 8-3977-11 HEX HEAD BOLT I I 1 4

-270 8-6652-7 NUT 4

D-2050
ITEM NOT ILLUSTRATED

HC-D2MV20-(7,8) Propeller Assembly

1055
ILLUSTRATED PARTS LIST 61-10-00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
HA,RTZ ELL 100E

420
410

430

400 o

350 a

s
a

360
P3 80
340
390
370
405~ V

450

3´•´•
470
460
440

HC-D2MV20-(7,8) Clamp Assembly

Figure 1023

1056
ILLUSTRATED PARTS LIST 61’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART AIRLINE DESCRIPTION CHG Imlupn

FIG.nTEM
NUMBER STOCKNUMBER I ~234567 CODE I CODE
NUMBER

1023

CLAMPASSEMBLY 2
-330 838-1012

´•´•COUNTERWEIGHT 2
340 B-l 7-6A

COUNTERWEIGHT DOWEL PIN 2

350 A-65

SOCKET HEAD CAP SCREW 4

360 A-2036-12

STAKING PIN, CAP SCREW 4

370 A-285

LINK SCREW, PUSH ROD 2

380 A-295

STAKING PIN, LINKSCREW 2

390 A-285

LUBRICATION FITTING 2
400 8-6588-1

LUBRICATION FITTING 2
405 8-6588-1

COTTER PIN 4
410 8-3838-3-2

SOCKET SCREW 4
420 A-321

´•´•GASKET 4
430 A-6871-1

´•´•CLAMP 2
440 D-6831-1A

CLAMP BOLT 4
450 A-2017

´•´•WASHER 4
460 A-2031

´•´•CLAMPNUT 4
470 A-2043-1

´•´•LUBRICAP 4
-480 8-6544

WEIGHT SCREW AR
-483 8-3840-(
BALANCEWEIGHT AR
-484 A-48

ITEM NOT ILLUSTRATED

HC-D2MV20-(7,8) Clamp Assembly

Page 1057

ILLUSTRPITED PPIRTS LIST 61 -1 0-00 Rev. 2 JunlOl

 PROPELLER
HA RTZ E LL MA:N6~EENANCE
EOOiLAUNAM

APS5097

950

650
580
550

630
640

530
n
540

960

660

790
OF
S 610700
800
P; 520
510600
590

670

710

750720
760

810 780

HC-D2MV20-(7,8) 91-7DS, -8DS Hydraulic Unit

Figure 1024

1058
61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART I AIRLINE DESCRIPTION CHG I EA IUPA

NUMBER STOCKNUMBER 1 1234667 CODEI CODE

NUMBER

1024

-500 C-91-7DS HYDRAULIC UNIT I IA,B,C,D,H 1

C-91-8DS HYDRAULIC UNIT E,F,G 1

-500A

C-112-2 ´•´•PISTON 1
510

A-1 168-1 ´•´•´•BUSHING 2

520 1

8-6711-0500 ´•´•´•HELICOIL 1
530

C-111-7 ´•´•CYLINDER A,B,C,D 1

540

540A C-111-8 ´•´•CYLINDER E,F,G

GUIDE ROD 2
550 1 A-122

A-i 14-8 ´•´•´•STAKINGPIN 2

580

´•´•LOCKWASHER 18
590 8-3864-39

8-3840-12 ´•´•SCREW 18
600

8-120 OUTER RING 1

610

A-128 ´•´•WASHER A,B,C,D 4

630 1

A-2037 SCREW, SOCKET HEAD CAP A,B,C,D 4

640
REPLACED BY ITEM 640A

A-2037-2C SCREW, SOCKET HEAD CAP A,B,C,D 4

640A
REPLACES ITEM 640

´•´•GASKET A,B,C,D 1
650 A-135

´•´•GASKET E,F,G 1
650A I A-181

8-119-2 ´•´•DIAPHRAGM 1
660

A-38B ´•´•BEARING,THRUST 1
670

8-113-2 INNER RING 1

680

8-3840-10 ´•´•SCREW 8
700

8-73 ´•´•GASKET 1
710

COVER PLATE i
720 B-l 2-7

-730 A-2043-1 ´•´•NUT E,F,G 6

LOCK WASHER 12
750 8-3864-39

´•´•SCREW 12
760 8-3840-6

ITEM NOTILLUSTRATED

HCID2MV201(7,8) 9117DS, 18DS Hydraulic Unit

1059

ILLUSTRATED PARTS LIST 61-10-00 Rev. 1 Apr/GOPage

 MANUAL
HA RT Z E L L

(This page is intentionally blank.)

I ILLUSTRlr.DPI\RTSLI~r 61-10-00 Page 1060

Revl*piiM
 PROPELLER MAINTENANCE MANUAL
HARTZELL IwE

PART AIRLINE DESCRIPTION CHG EA IUPA

NUMBER NUMBER STOCKNUMBER I 12a45s7 CODEI CODE

1024

-770 B-l 09-9A ´•´•JACKPLATEASSEMBLY 1

-770A B-l 09-9 JACK PLATEASSEMBLY 1

NOTE: Props not using a C-175-(1,2) or Al 65-(2,3) ring on the back of the hub must
use the 8-109-9 jack assembly.

780 B-87C-1 ´•´•´•JACK 1

790 1 A-114F STAKING PIN, ROD 2

A-97-7 1 I´• PUSH ROD 2

800

810 A-821 I I´•´•´•FORK 2

820 A-i 14-8 STAKING PIN, FORK 2

-940 C-331 7-012 ´•´•O-RING E,F,G 6

950 A-121 ´•´•SCREW 1

960 B-6588-1 LUBRICATION FITTING (SEE NOTE 1) 1

8-6855 PLUG (SEE NOTE 1) 1

-963 1
NOTE 1: After greasing the A-38(
bearing, replace the 8-6~588-1
lubrication fitting with
the B-6855 plug.

ITEM NOT ILLUSTRATED

HC-D2MV20-(7,8) 9117DS, -8DS Hydraulic Unit

1061
ILLUSTRATED PARTS LIST61-10-00
 PROPELLER
HARTZ ELL MA:N6~NANCE
E001LAUNAM

APS5099

10801100
1050, ,1140

1060
1090
1040 1070

1120
e
1110

O 1075
1150

1130
e

1010

ORIGINAL
As Received By
ATP

HCID2MV201(7,8) Valve Assembly

Figure 1025

61-10-00
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

FIG.IITEM PART AIRLINE DESCRIPTION CHG ER IUPA

NUMBER NUMBER STOCKNUMBER 1234167 1 CODE CODE

1025

-1000 B-93-A VALVEASSEMBLY A 1

-1000A 8-93-8 VALVEASSEMBLY C,H 1

-10008 B-93-C VALVEASSEMBLY F 1

1010 A-71-2 ´•´•GASKET 1

-1020 8-3837-0463 ´•´•WASHER 2

-1030 B-l 66 ´•´•VALVEUNIT 1

1040 A-167 ´•´•´•BODY 1

1050 A-168 ´•´•´•SPOOL 1

1060 C-3317-112 ´•´•´•O-RING 2

1070 8-3838-2-2 COTTER PIN 2

1080 8-6646-17 CLEVIS PIN 1

1090 A-126 ´•´•SPACER 1

1100 8-6646-23 CLEVIS PIN 1

1110 8-3870-1032 STOP NUT 1

1120 8-3840-10 STOP SCREW 1

1130 A-1 84-6 ´•´•LINK 1

1140 A-1 80 ´•´•LINK A 1

1140A A-187 I I.. LINK C 1

-1 150 A-2038-10 SCREW, SOCKET HEAD CAP 2

ITEM NOTILLUSTRATED

HC-D2MV20-(7,8) 931A,-B,-C Valve Assembly

1063
ILLUSTRATED PARTS LIST 61-10-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL iOOE

APS5099A

1080
-B
1050

1060
1040
1070

e 1130

1010

1160

1015

ORIGINAL
As Received By
ATP

HC-D2MV20~(7,8) 931AG,-BG,-CG Valve Assembly

Figure 1026

1064
61-10-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

AIRLINE DESCRIPTION CHG ER UPA

FIG./ITEM PART
STOCKNUMBER CODE CODE
NUMBER NUMBER 1234567

1026

VALVEASSEMBLY B 1
-1000 B-93-AG

B-93-BG VALVEASSEMBLY D Il
-1GO0A

B-93-CG VALVEASSEMBLY G 11
-10008

´•´•GASKET 1
1010 A-71-2

´•´•GASKET G 1
1015 1 A-71-2

´•´•WASHER 2
-1020 8-3837-0463

´•´•VALVEUNIT 1
-1030 8-166

´•´•´•BODY 1
1040 A-167

´•´•´•SPOOL 1
1050 A-168

´•´•´•O-RING 2
1060 C-331 7-112

COTTER PIN 1
1070 8-3838-2-2

CLEVIS PIN 1
1080 B-6646-17

´•´•LINK B II
1130 A-1 73-2

LINK D 1
1130A A-173-4 1. I´•
´•´•LINK G 1
11308 1 A-173-5

SCREW, SOCKET HEAD CAP 2

-1150 1 A-2038-10

EXTENSION BLOCK G 1
1160 A-171

ITEM NOT ILLUSTRATED

HC-D2MV20-(7,8) 931AG,~BG,-CG Valve Assembly

1065

ILLUSTRATED PARTS LIST 61-10-00 Rev. 1 Apr/GOPage

 PROPELLER
HA RTZ E LL MA:ND~EENANCE
E001LAUNAM

APS5092A

220

1~ a

~oo

310 290 160

WI oao 20
50
120
300 130

180110100
190 80

70

ORIGINAL
As Received By
ATP

HC-D3MV2018D Propeller Assembly

Figure 1027

1066
ILLUSTRATED PARTS LIST 61’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

FIG.IITEM PART AIRLINE DESCRIPTION CHG ER IUPA

NUMBER NUMBER STOCKNUMBER 1234567 CODEI CODE

1027

-1 HC-D3MV20-8D PROPELLER ASSEMBLY 1

10 840-85 HUB UNIT 1

20 1 A-1 496 ´•´•PILOTTUBE 3

SUPERSEDED BY ITEM 20A

20A D-7080-( PILOT TUBE 3

SUPERSEDES ITEM 20

-30 C-1482 ´•´•HUB 1

50 1 A-155 I I´•´•BUSHING 1

70 A-974 WIRE RETENTION RING 2

80 A-972 GUIDE RING 2

-90 A-971 SPLIT BEARING UNIT 2

100 A-971-B ´•´•RACE 4

110 B-61 44-2 ´•´•BEARING, BALL 36

120 A-971-A ´•´•RACE 4

130 A-311 BALL SPACER 1

140 A-2027 BEARING RETENTION RING 2

150 C-3317-230 O-RING, BLADE 2

160 1 A-870 PULLER RING 1

180 1 A-63B HUB NUT 1

190 1 A-847 HUBSAFETYPIN 1

200 A-50-1 REAR CONE 1

220 A-95-A BLOCK, PITCH CHANGE 3

290 C-3317-235 O-RING, NUT 3

300 D-7260 GUIDE COLLAR UNIT 1

-303 A-116D-1 PLASTIC BUSHING 3

-305 1 A-2038-12 SELF-LOCKING SOCK. HDCAPSCREW 1

-307 1 A-i 14C ´•´•STAKINGPIN 1

-310 1 C-6033 NUT, GUIDE COLLAR 1

500 1 91-8DT HYDRAULIC UNIT 1

E=1263
ITEM NOT ILLUSTRATED

HC-D3MV20-8D Propeiler Assembly

1067
ILLUSTRATED PARTS LIST 61-1 0-00 Rev. 2 Jun/OlPage
 PROPELLER MAINTENANCE MANUAL
)II~ RTZ F LL 100E

420
410

430

400 o

350 a

/-o ‘‘´•z
360 ~380
340
390
370
Y/’ /r
450

470
460
440

HC-D3MV20-8D Clamp Assembly

Figure 1028

1068
ILLUSTRATED PARTS LIST 61 -1 0-00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 100E

AIRLINE DESCRIPTION CHG I EA IUPA

PART
STOCKNUMBER 1234567 CODE CODE
NUMBERI NUMBER

1028

CLAMPASSEMBLY 3
-330 1 838-1012

COTTER PIN 2
410 8-3838-3-2

SOCKET SCREW 2
420 A-321

´•´•GASKET 1
430 A-6871-1

´•´•CLAMPBOLT 2
450 1 A-2017

´•´•WASHER 2
460 A-2031

CLAMP NUT 2
470 1 A-2043-1

´•´•LUBRICAP 2
-480 8-6544

´•´•CLAMPUNIT 1
-485 D-7838-1012

´•´•´•COUNTERWEIGHT 1
340 B-1 7-6A

COUNTERWEIGHT DOWEL PIN 1

350 1 A-65

SOCKET HEAD CAP SCREW 2

360 A-2036-12

STAKING PIN,CAPSCREW 2
370 1 A-285

LINK SCREW, PUSH ROD 1

380 A-295

STAKING PIN, LINKSCREW 1

390 1 A-285

LUBRICATIONFITTING 2
400 8-6588-1

´•´•´•CLAMP 1
440 D-6831-1A

WEIGHT SCREW AR
-483 8-3840-(
BALANCEWEIGHT AR
-484 1 A-48

ITEM NOT ILLUSTRATED

HC-D3MV20~8D Clamp Assembly

Page 1069
ILLUSTRPITED P~RTS LIST 61 -1 0-00 Rev. 2 Jun/01
 PROPELLER
HARTZELL E001LAUNAM

W10153

950

580 650
550

630
640

530

540

960

660

680

790

S590610 700

800
9;, 520
5;0600

670

710

720
750
760

810 780

HC-D3MV20-8D 9118DT Hydraulic Unit

Figure 1029

1070
ILLUSTRATED PARTS LIST 61’1 0’00 Rev. 1 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 100E

PART AIRLINE DESCRIPTION CHG DF IUPA

NUMBER STOCKNUMBER CODE CODE

NUMBER 1234567

1029

91-8DT HYDRAULIC UNIT 1

-500

C-112-2 ´•´•PISTON 1
510

A-1 168-1 ´•´•´•BUSHING 2

520

8-6711-0500 ´•´•´•HELICOIL 1
530

C-111-8 ´•´•CYLINDER 1
540

A-122 GUIDE ROD 2

550

A-1 14-8 ´•´•´•STAKINGPIN 2

580

8-3864-39 LOCK WASHER 18

590

8-3840-12 ´•´•SCREW 18
600

8-120 PLATE, OUTER DIAPHRAGM 1

610

´•´•WASHER 4
630 A-128

A-2O37-2C SCREW, SOCKET HEAD CAP 4

640

´•´•GASKET 1
650 A-181

´•´•DIAPHRAGM 1
660 8-119-2

´•´•BEARING,THRUST 1
670 A-38-B

´•´•PLATE, INNER DIAPHRAGM 1

680 A-1 13-2

8-3840-10 ´•´•SCREW 8
700

A-2043-1 ´•´•NUT 6
-730

´•´•JACKASSEMBLY 1
-770 C-7261

´•´•´•JACKPLATE 1
780 C-7262

A-1 14-F ROD, STAKING PIN 3

790

A-97-7 PUSH ROD 3

800

´•´•´•FORK 3
810 1 A-821

´•´•´•STAKINGPIN,FORK 3
820 A-1 14-8

C-331 7-012 ´•´•O-RING 6

-940

A-121 SCREW 1
950

LUBRICATION FITTING (SEE NOTE 1) 1

960 8-6588-1

PLUG (SEE NOTE 1) 1

-963 8-6855

NOTE 1: After greasing the A-38(

bearing, replace the 8-6~588-1
lubrication fitting with
the 8-6855 plug.

ITEM NOT ILLUSTRATED

HC-D3MV2018D 91-8DT Hydraulic Unit

1071
ILLUSTRATED PARTS LIST 61-10-00 Rev. 1 Apr/GOPage
 PROPELLER
HA RTZ E LL MA:No~NANCE
E001LAUNAM

APS5099

1100

10807~
1050, ,1140

1060
,I 1090
1040 1070

1120
e
1110

1075
1150

1130
e

1010

ORIGINAL
As Received By
ATP

HCID3MV2018D 931E Valve Assembly

Figure 1030

1072
1,,,,,,,,,,,,,,,,, 61-10-00
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 100E

AIRLINE DESCRIPTION CHG I EA UPA

FIG./ITEM PART
NUMBER STOCK NUMBER 1234587 CODE CODE
NUMBER

1030

VALVEASSEMBLY 1
-1000 93-8

´•´•GASKET 1
1010 A-71-2

´•´•WASHER 2
-1020 8-3851-0463

´•´•VALVEUNIT 1
-1030 8-166

´•´•´•BODY 1
1040 A-167

´•´•´•SPOOL 1
1050 A-168

´•´•´•O-RING 2
1060 C-3317-112

COTTER PIN 1
1070 8-3838-2-2

1075 8-3838-2-2 COTTER PIN I I I 1

CLEVIS PIN 1
1080 8-6646-17

´•´•SPACER 1
1090 A-1 26

CLEVIS PIN 1
1100 8-6646-23

STOP NUT 1
1110 8-3870-1032

STOP SCREW 1
1120 8-3840-10

´•´•LINK 1
1130 A-1 84-3

LINK 1
1140 A-180

SCREW, SOCKET HEAD CAP 2

-1 150 B-3384-8H

ITEM NOTILLUSTRATED

HC-D3MV20-8D 93-E Valve Assembly

1073

ILLUSTRATED PARTS LIST61-10-00 Rev. 1 Apr/GOPage

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 100E

(This page is intentionally blank.)

1074
ILLUSTRATED PARTS LIST 61’1 0’00
03
LHANDBOOK 1
OVERHAUL
INSTRUCTIONS

HC-92tLWk-2A

Hartzell Propeller, Inc.

PIQUA,
 RECORD OF REVISIONS

la,´•
MFG REV
NO DESCRIPTION ISSUE DATE ATP REV DATEI INSERTED BY
 RECORD OF TEMPORARY REVISIONS

d~´•
TEMP
REV NO DESCRIPTION ISSUE DATE
ATP REV
DATE
INSERT
BY
DATE
REMOVED
REV
INCOR
REMOVE
BY
 TABLE OF CONTENTS

PART I OVER HAU L I NSTRU CTIONS

Section I Introduction

General I

Description of propeller operation

Section 1I Overhaul Instructions 1

Special Tools--Table I. 1

A. Removal of Propeller from Engine-I-1C-92~F-2A. 2

B. Removal of Propeller from EnSine--HC-92~K-2A. 2
C. Disassembly of Propeller--both R/Iodels 2
D. Cleaning 3

E. Inspection 3
F. Repair or Replacement 3
G. Assembly 4´•

Section IIZ Balance 5

Section IV ~Venr Tolerances 6

Hub-Table II Wearing Surfaces 6
Blade-Table III Repair Tolerances 6

Section V List of Approved Grease 7

Section VI Service Troubles and Remedies 7

PART II PAFaTS LIST

Section I Introduction 8

Section II Group Assembly Parts List 8

HC-92~1;-2A 9

HC-92~K-2A 12

NOTE: Installa.tion, Ope,´•ation cllzrl Gcllelc~l Se,´•vice n,´•e sllDiects

´•~ohich al´•e cove~´•ed ill the Ha,txel2 P,.opellc´•)´• ,IlnlllrcLI."
 PART I OVERHAUL

SCCTION

INTRODUCTION

GENERAL.
Ix,rltloli
This handbook contains overhaul instmctionr for
CI´•nl,iluRal \iola i""""’ of the ploprlh´•l
the mndsls RC-92ZF-2h, ~IC-SPn’F-SA, HC-S2ZK-ZA,
dul´• to thr illtiOli O/ (J1C CnCinP
and HC-OBWR-PA. The "Z" Shanks incorporate
\tnl’l".d. A~ \pV’d\ oi o~l´•I ’1I1III)II1 the TtDl)s all´• Ir-

hron~-e shr.ver while the ~’W" shanks use a needle c~´•litlilus;,l the i,mlll´•llrr to

bearing at tile outer end. The "F’~ Range has six 1/2 he ivarhl´•ll´•d at an\ liial´•
inch bolts on;14 inch holt circle, while the "K’~ Range
has six I~ inull holts on a 4K bolt circle. All four SECTION I I
models are conrtnn~ speed and fenthBinR. OVERHAUL INSTRUCTIONS

Table I.--SPECIAL OVERH*UL TOOLS

DES~CKIPTION.
*pplir~bls
.].li~´• HC-92~P-2A and HC-92:K-2A i,mpc´•ll~:rp ail.
Mod~l Modoi
(I´•a~bllinS t)pcr drsigned lot rnginer in tba nc-prr-?* HC´•P~I-?*
I ul, to :I(I(I bOI.L.POh.(.l rung~´•
/\-1331 Wrcn~h for /1-1315
Illr\ d~´•´•iel’(’d t’I bl´• conllollrd i,? i, eu\l:lool
ill
Mnun,inp Srrs. X
Illuunlrdu~l lhl´• I´•ngios and iulq,l) illg i.n~illr oil through
8´•8~1-1 Wronrh for /\.888.2 RLll.tL
\hsl~ (;lxrl´•nor oii pirxxull: r0.2?j p.s.i.
the illoi"’ll~´•, Nul on Spring *IILmbls X X
,aael´• i li~l. pircll.\~hilc´• attach-
,.,i lli til(´• i,lildl´• c:inlol,´• illcll´•aic pitch i\ .plinS assist) C-BIS RI(YrL for *IL.mbl*.l
’"’hO’’"B Spring X X
tlir dolina lbl: I~arhrling opclalion
PI´•a~hrlill. Ihl´• pitcli i, arcolllpli,hcd hy ol,lniliir a \alrr PropsllPr ToblL X Y

in lhl´• s´•hil´•li allox~ thl´• icalhclinR rplinR r~l

sx-lsa solon.i.s *rbor X X
Ih’l´• I,il net cli the plopcllrr and bad. into the

IIGURI I--Mod.l HC-P1~-1* PropcllLI inll.llsd on T.in ~ngina *ir~r.ft

ORIGINAL
.1.
As Received By
ATP
A. REMOVAL OF PROPELLER FROM d. Rotate piston assembly (52), link arlns

ENGINE--HC-92~F-2A. !55)from link screw (19).

Kernove piston assembly (52) from cylinder (60).

(See Figure 2.)
a. Remove spinner dome (70) by taking out screws (71
PISTON (52).
b. Remove propeller from engine by first driving the
two dowel pins (10) out of the flange. Use a punch and a´• ?’ake out screws (54), removing safety link bar !53).
drive the pins back towards the engine. Take out the 6
b. Obtain a long 10-32 screw and insert it into pin
flang-e mounting screws (9). The propeller and spinner Use this as a puller for removing
bulkhead (72) can then be removed from the engine.
(59). pin i59) which
;s a press fit. KeInove link arms (55).
c. Remove the spinner bulkhead (72) from the pro- c. 12e~nove "0" ring (63) and felt seal (61).
peller by unscrewing nut (42) and lemo\ing bolts (7:~)
and washers (4´•0) and (41). The bulkhead (72) can NOTE: Uo not attempt to remove plastic Bzcshing
then be slipped from the propeller flange. (j8).
NOTE: In some eases the dowel pins (10) may be
located behind the automatic high pitch stop ns- FEATHERING SPRING ASSEMBLY (43).
semDEy (54). It will then be necessary to feather
the propeller and remove these brockets before a. Remove screws (66) and feathering stops (65). Re-
removing the pins (lo). move front split rings (67) by first sliding entire spring
NOTE: ilt this point the propeller may be taken assembly further into the cylinder 160) by about ~4
to the overhaul facility or shipped to the factory. inch. Kemove spring assembly from cylinder (60).

B. REMOVAL OF PROPELLER FROM

ENGINE--HC-92~K-2A. CAUTION

(See Figure 3.)

Do not attempt to disassemble the feathering
a. Remove spinner dome (7()) by taking´•out screws i 71). spring sub-assembly unless Special l.ool No. C-845,
h. Feather the fixture for assembly of feathering springs, is
propeller. Use blade arms on each blade to
decrease pitch. Use two screw drivers to hold the high available; or some equally safe device is used. If
this feathering spring is defective and no fixture is
pitch stop pins (36) out so blades can he feathered.
available, a new one should be installed. Return
c. Remove both automatic stop assemblies (34) by tak- old one to factory for repair or replacement.
ing out screws (39).
b. Place the assembly in the fixture and
d. Take six flange mounting compress the
out screws (2) and (3) feathering springs (47) and (48). When the springs
using special wrench A-1327.
are compressed, slide the rear
spring retainer (45) back
e. Remove propeller from 0" pilot tube (4´•9) and remove the rear
engine, also "0" ring´•(ll) spring split re-
and mounting shim (14). tainer (46). This allows the rear spring retainer (45),
the springs (47) and (48), the spacer tube (50), and the
NOTE: At this point the propeller ma2/ be taken outer mushroom (44´•) to be removed from the pilot tube
to the ove~haul facilityor shipped to the factoT?d.
(49). Remove "O" ring (51).
C. DISASSEMBLY OF PROPELLER (both
Models HC-92~F-2A and HC-92~K-2A). CYLINDER (60).

U"Sc’ew cylinder (60) using

Mount the propeller propeller
table with the
on a
a.
square bar inserted in
flange secured face down. (In the case of the HC-92bF-
$otS provided.
2A model, which may be in the feathered position, it will h. Kemovi: "O" ring (62).
be necessary to feather the blades and remove the auto-
maticc stop assemblies) (34).
BLADES AND CLAMPS.
REMOVAL OF PISTON ASSEMBLY (52). a. With ink and scale, mark matching lines on blades
(1) and clamps i16). Record blade serial number with
CAUTI O N clamp number for each side of propeller.
b. Remove the screws (16) and (26) from the
clamp,
a"d’emove clamp halves (16). Kemove gaskets
Propeller must be feathered before piston is (27).
removed. Remove the blades (1).

C. F’‘O’" the clamps (16) remove the lubricator

a. Unscrew nut (64) using wrench 0-842-1. To keep fittinqs
pilot tube (49) from turning, use a socket wrench to
(21)’ bala"ce weights (28), and automatic high pitch
apply torque in opposite direction. stops (29) by removing screws (30).

b. Slide d. Kernove the cotter pin (22). Remove and discard

piston (56) off pilot tube (49).
counterweight mounting screws (25). These screws
c. Kemove cotter pin (32) and link screw sleeve (33) should be I´•eplaced immediately with new ones.
both sides.
Torque
to 65 Ib. ft. Safety with cotter, pin (22).

-e-
 e. Visually inspect the blades for cracks, particularly
CAUTION around the shank retention area and at the leading
edge near the tip.
operations, it is not neces-
In normal overhaul f. Inspect the bearings for excessive wear or chafing.
counterweights f17) from clamp- r\ certain amount of marking of the halls and races is
sary to remove

counterweight assembly (15). If either clamp or to be expected and is not necessarily a reason for re-

counterweight is defective, use a complete new placement. Only when the bearings show pit marks
clamp-counterweight (15) at overhaul, which are .002" deep and definitely feel rough, are the
balls or races to be replaced. Bearing life ordinarily is

BLADE BEARINGS. greater than 1000 hours.

of groove in the hub, and tube (4) for slippage. The tube should
Inspect pilot
a. poll "O" ring (7) out 8´•
extend from hub 33/4 inches only. If this distance is
out
hack onto the hub spider.
greater, the indication is that the tube has slipped out
NOTE: Use small "C" clamps or other means to of the hub spider. An oversize tube should replace the
hold bearing races together, as this operation will
one which slipped.
permit races to part, allowing balb to roll out.

b. Slide the bearing (5) back onto the hub toward the
"O" ring (7).
F. REPAIR OR REPLACEMENT.
K"mo"e all rust, galling marks and nicks flolll the
c. Kemove the split ring (6). This will allow the bear-
huh Spider arms with crocus cloth or fine emery. Kust,
ing (5) and "0" ring (7) to be removed from the hub.
galling and nicks ale stress raisel´•s which rclduce the
fatigue life of the hub. Do not polish ~lnless nc´•rc´•ssarv
A~rTOMATIC HIGH PITCH STOP
as spider arms have been rolled
the to impl´•n~´•c´• tl;e
ASSEMBLY (34).
fatigue strength. (The roll marks are not tool marks

a. I)isassemble each high pitch stop assembly by re- and should not be remo~´•ed.) If the hlade pilot tube ii)
moving the cotter pin (38). This allows spring (37), is to he replaced in the huh, due either to excessi\´•e
and pin (36) to be removed from the bracket (35). wear, or due to the fact that it has slipped out slightl!
from the spider, it is necessary to use a new tube ha~´•in#
a.002" to.003" oversize diamete, over thcl 2"" length
HITB SPIDER ASSEMBLY (2).
which presses into the huh spider hole. press the: ne\*.
If of the huh spider sub-assembly (2)
inspection tube !4) into the huh spider (3) leaving exactly
a.

shows that tho hub pilot tubes (4´•) require replacement,

9~
inches of the length exposed. Be sul´•e the hc´•a~v end of
they may be pulled from the spider (3) by means of an the tube is inserted into the hub. Test the luhe for
appropriate gear or bearing puller. tightness by apply 5000 Ib. force on the tube. If it
slips with this force, it must be replaced with a lal´•ger
tube of say .003" to .004" oversize.
CAUTION
b. Kcplace the counterweight mounting screws 124) as
noted above. Use only the specified parts as the) ar-e
heat treated to a high strength.
Do not use heat on the hub for any reason, as

it may warp the huh and draw the temper. c. Keplace all gaskets, "0" rings, and cotter pins.
d. Nicks deep or scratches in c\,lindcl´•
Ina)´• he i6())
D. CLEANING.
cause replacement, particularly if tht´• marks are in
for
a. Wipe all dirt and grease off all parts. the region of the piston "O" ring during norlnai cruise

b. Clean all parts, except felt seal (61) with solvent, flight. Scratches in the leathrring rt´•gion may he tol-
erated if not too deep.
and dry.
e. Keplating (cadmiurn) of steel parts is I´•ccoll~Incndrd
c. Apply a rust preventative compound on all parts
of time, shipped.
if the original plating has hcen wol´•n off ol´• if damaged
which are to be stored for any length or
nicks scratches.
by or

d. Keep in clean and dry place before reassembly.

CAUTION
E. INSPECTION.
a. Inspect all wearing parts according to tolerances
specified in TABLE II. Replace parts not coming ’I’he hub spider al~ns i~) and I,ilot tu~,c.s 14)
within specified limits. should be masked. ATtt´•t´• I,lating the I,al.ts.thc’). Illust
be baked in an oven at:1500 F. I,lus ol´• rllirlus 253 1’(,1- 3
b. Inspect the blades according to the tolerances in
hO"’S to eliminate possihili~v of hvd,´•oSrn c´•llll,rittlr-
.Table III. Replace a blade which falls below the listed
mc´•nt. High strength bolts, huh and cl;tmp I,al.ts
~ninimum dimensions upon repair.
are I,articularly suscc´•l,tihle to this c´•ffcct.
Failule of
c. Visually inspect all metal surfaces. Keplace or re- the part may result unless this baking is accolnp-
finish any bearing or wear surface which has a visible lishcd. If proper plating facilities al´•c´• ~lot a\-ailahlr.
nick, dent or other distortion. the l’"’tS should t,e painted with a suitable alumin-
umm or lacquer paint.
d. Magnetically inspect all steel parts fol´• clacks not

\´•isihle to the eye. f. 12~´•l,air blades according to CAA Manual.

-3-
g. Blade bushings. If the blade bushing is worn beyond d. Pull the hearing (5) and split ring (6) outward
specified tolerances, the blades should be returned to against the shoulder of the hub spider. lioll the "0"
thefactory to be rebushed. These bushings seldom weal, ring (7) into its groove behind the bearing (5.
however, to the point where they must he replaced.
h. Piston Assembly (52). In case the link pin (59) is
CLAMPS AND BLADES.
loose in the piston (56), (this should be a light press fit),
the piston and link arms (55) should either be returned NOTE: In ordel´• to assemble the pl´•opelle?´• and
set the pitch ILccurcLtel2/, It is highl?/ aclvantcLgeous
to the factory to be reamed out .005" oversize and fitted
to use a special propeller table ltaviny a shaft
with a .005" oversize pin (59);or an A- 1464-1 link pin as- WhhC1h can be melted with the hzcblfla7cae. Air or
sembly be used to replace the present pin (59) and link oil pressure (100 p.s.i. minimum) should be cLvail-
bar (53). The former is preferable as the hole in the able in the shaft to actuate the piston.

piston will not wear as fast as when the A-1464-1 as- table shaft, sealing
a. Mount the hub on the propeller
sembly is used. Keplacement of the plastic hushing (58) Fasten with bolts
is seldom necessary. If it must be replaced, the piston
the flange with "O" ring (11). or

(56) should be returned to the factory. clamps.

b. Fill the hlade pilottube hole with a waterproof
G. ASSEMBLY. grease as specified under the list of ’’Greases Kecom-
mended."
(See Figures 2 and 3 for hoth Models.)
NOTE: Be sure no air is trapped below the
Keassembly is accomplished hy revelsing the opera-
~7’e(LSe as tlliS will affect the balance.
tions noted for disassembly, as follows:
c. Install blade (1) on the same pilot tube (4) frorn
which it was originally removed. Place a hardening
AUTOMATIC HIGH PITCH STOP
gasket compound (commercial automotive type) around
ASSEMBLY (34). the blade shank in the shoulder radius.
a. Keassemble the automatic high pitch stop assenlhlies
d. Install the correct MA?’CHING clamp and coun~er-
by inserting into each bracket (35) a pin (36) and
spring (37). Use a cotter pin to hold the parts. ?’he Weight suh-assembly (15), with new clamp gaskets (27).
Fasten the parts together with socket head screws i 26)
spring end should be hent around the cotter pin to
and the Ferry head clamp screws i2:~) with nuts (24).
preclude any possibility of it being unscrewed from the
assembly. ’Tighten the socket head screws (26), and Ferry screws
(23) in order to check for friction.
FEATHEKING SPRING SUB-ASSEMBLY (43). NOTE: The pitch will be set after the propeller
is assembled after which the clamp bolts will be
NOTE: When assembling or disassembling the fi,lally tightened and sclfetied.
feathering spring yub-auuembly (49), it is impercl-
tive that a safe means of eompreusing the springs e. Install the lubricator fittings (21) and high pitch
(47) and (48) be used. TSlis is afforaed 6y the (30). Wire safety.
use of S’peciul Tool No. C-845.
stop plates (29), using screws

a. onto the pilot tube (4´•9) outer mushroom

Assemble f´• Check for friction or binding of the blades when I´•o-
t"ted about their axis. If the blades tend to bind as a
(44), spacer tube (50), inner spring (48), outer spring
’esult of tightening the clamp bolts (26) to 60 Ib. ft.
(47), and rear spring retainer (45). Insert the above
assembled parts in the spring compressing fixture and torque, it will be necessary to remove the clamp and
hlade and reduce the diameter of the pilot tube (4) by
compress the springs until the rear spring split retainer
.001 to.0015 inches over a 11/4 inch length nearest the
(46) can he assembled in the groove near the end of the
hub spider. ’I’his can he done with fine emery paper
pilot tube (49). Kelease spring tension.
and crocus cloth. (This problem is also covered in
h. Install "O" ring (51) into groove at threaded end bulletin No. 53 and presumably has heen taken care of
of pilot tube (49). for all propellers in service.)

BLADE BEARINGS.
CYI,INDER (60).
a.Place a blade mounting "0" I´•ing (7) on each leg of
the huh spider assembly (2). Kelt the "0" I´•in:r hack a´• Clean the thread of the cylinder (60) and the hub.

towards the center of the hub. Insert "O" ring (62) in the cylinder groove behind the
threads. Apply gasket compound (non-hardening com-
b.Install the blade mounting bealing j5) o\´•c´•r the Incl.cial automotive type) to the threads. Screw the
hub spider. cylinder (60) onto the huh. Use a one inch square har
ai~out:l long as a wrench, applied to the slot in the
feet
cvlindcl. l’ighten the cylinder hard against the huh
CAUTIO N ~about 200 ft. Ih. torque).

h. Inspect inside of cylinder to be sure "0" ring (62)

I~e sure the thin race is installed lil.st. has not hccn forced out of place.

c. Install like-numhcrrd I>lade mounting sl,lit I.inl: (6) c. Inspect around the dl´•i\´•e slot to he sure: har has not
into the spacc´• between th~´• hearing and th~´• huh sl,idcl raised an), c´•daes which might cut the "0~’ ring in the
arm.
l,iston. Peen edges if necessary.

-4-
INSTALLING FEATHERING SPRING d. Check the blade angle again at the low pitch setting,
Sub-Assembly (43). asthe torquing of the blade may have resulted in slight
movement.
a. Slide the feathering spring sub-assembly (43) into
the cylinder (60) and bore of the hub spider (3) until e. Check the feathering angle by allowing the fcather-
the grooves in the end of the cylinder are.exposed. ing spring to feather the
propeller. See airplane spcci-
lication for correct feathering angle. In case the feath-
b. Install the front split rings (67) into the groove in
the cylinder. Pull the feathering spring sub-assembly
ering angle is not within prescribed limits, the piston
forward to lock the rings in the groove.
assembly (52) must be removed and the feathering
stops (65) adjusted. If the feathering angle is greater
c. Secure the feathering spring sub-assembly and the than specified, add shims under the stops (65);:i’i inch
in place by means of the feathering stop (65) thick for 10 pitch change desired. If the feathering
split rings
and screws (66). Safety screws with wire. angle is less than specified, the feathering stops should
he riled down inch for 10 pitch change desired.

PISTON.

a. Install link
arms (55) in piston (56). Drive link CHECK FOR GENERAL OPERATION,
arm mounting pins (59) through holes in piston and FRICTION AND LEAKAGE.
arms. Install safety link bar (53) with screws (54).
Wire safety.
a. Cycle the propeller with air and note general opera-
tion for possible friction, etc.
h. Check link arms (55) for free mocrement in piston b. Hold full pressure
(56)slots.
on piston and check for leakage
past piston "O" ring (63), cylinder "O" ring (62), and
c. Install a new "0" ring (63) and felt seal (61) into guide rod "0" ring (51). Oil applied at these poillts
their respective grooves in piston (56). Soak the felt will bubble if air is leaking out.
seal with oil after assembly in the piston.

d. Prepare the piston for installation by careful in- INSTALLATION AUTOMATIC HIGH PITCH
spection for sharp edges. Oil the "0" ring (6:I) and STOP ASSEMBLY (34) ANL) PLATES (29).
cylinder (60), and also pilot tube "O" ring (51).
a.Install automatic high pitch stop plates i29) with
e. Slide the piston (56) onto the cylinder (60). (30). The propeller should be feathclrd for this.
scl´•cws

that the free ends of link Safety with wire.

f. Kotate piston (56) so arms

(55) can be aiembled onto link screws (19). b. Install automatic high pitch stop brackets (34) with
bolts (39). Check operation of automatic stop mechan-
S´• Insert link screw sleeve (33) between link screw (19) ism by cycling propeller between low pitch and high
and hole in link arm (55). Insert cotter pin (32).
pitch. Check engagement of stop pins i36) and stop
h. Move piston into full feathered position (back plates (29). Both pins should engage plates at some
against hub assembly) so that the threaded end of pilot time within .010 inch. File plates as required if ncces-
tube (49) protrudes through the end of the piston (56). sary. Check feathering by holding stop pins (36) out
Screw the nut (64) onto pilot tube (49). Torque the so that plates (29) can pass. Check for clearance and
nut (64) to 150 ft. Ib. Restrain the pilot tube (49) from possible friction between parts.
turning by applying a socket wrench to the hex located NOTE: The automatic high pitch stop brackets
at the end.
(Y4) must be removed befol´•e inutalling the
NOTE’: The pilot tube (89) can be forced througk,
IIC-92~LK-1A propeller on the engine as two of the
the end of the piston by pressing down on tl~e
mounting screws are covered by these Bracl~ets.
These brackets need not be removed before in-
blade counterwezghts.
stalling the propeller, however.

SETTING BLADE PITCH.

SECTION III
a. Apply air or oil pressure through bore of the table
spindle, to force the piston against the low pitch stop. BALANCE
Hold this position,
a. Ritlance the propeller assc´•mhly hcfol´•~
SI´•c´•ase is
b. Loosen the outer addcd to the clamps, and check again aftol.
clamp screws (23) only.
Set each glcase is:
blade with added. Balance with pitch at high value I,ins iS6) c´•n-
a protractor located the 30 inch radius.
at r

See airplane specification for low blade pitch setting. gaged with plate) (29).
Tighten the blade clamps. Torque the outer clamp h. Either a suspension s)stclrll ol´• an ;11´•bol´• oil
screws (23) to 60 ft. Ib. torque and the innc:r screws knife edges may be used for balancing. In c.~´•c´•rlt tile
(26) to 30 ft. Ib, torque. Safety the latter with cotter suspension system is used, it is essential that the ccntcl
key through hole drilled in head, of gra\´•ity of the propeller be locatc´•d at ol´•
sliahtly h~´•]ow
c. Check the blade against turning in the clamp by thc I’ivot of the balance cquiplncnt; othcl.wisc´• inaccu-
torquing the blade to 175 ft. Ib. Use a blade bar and a ’acics will result.

weight. If blade moves in the clamp, the clamp must c.l~ornove the end play from the hlade cla~rlp as-
be removed and the clamp parting line at the outer
scmhlic´•s hy driving identical small wcdg~´•s h~´•t\L´•ccn thr
corners filed slightly (remove .005"-.010" each sul´•face),
blade clamps and huh spider, at identical locatiorls.
to allow the clamp to engage blade shoulders rrlore

firmly. d. I~olt I,lopeller to b;~lancc´• a~´•i,ol´•, or´• ~vil´•e balarlccl.

-5-
 NOTE: The foltowing Balaflce procedure cLpplies mined For \crtical balance. If the slugs under "g" and
onlZl to balance arbor method. "i" are added to the same side of the blade, tl~e total

c. Check horizontal balance by laying slugs (28) in slugs required for vertical balance is the average of "g
and If the slugs under a"d are added to
corner of blade and clamp. Kecord number of slugs
required for balance. opposite sides of the blade the difference between the
two numbers is added to the side requil´•ing the greatest
f. With the propeller in horizontal position, apply 50-100 number.
Ib. downward force to each blade tip. This takes up the
k. Horizontal balance determined under "e" must be
clearance between hub and blades in one direction.
maintained by properly dividing the slugs required
with heavy blade up. Add
g. Check vertical balance Under "j" between the two blades.
weight slugs (28) to light side of clamps. Kecord num-

for balance. i. Attach the slugs to the clamps with screws (31) and
ber required
again check horizontal balance. Safety with wire. Do
h. liotate blade 1800 frorn horizontal position as noted ,,,t.ttach more than 4 slugs with each pair of screws.
in "f" above and applS 50-100 Ib. to each blade tip.
This takes up the clearance opposite to that noted m~ Add amounts of grease to each blade, holding
equal
under "f." horizontal balance constant, until clamps are com-

vertical balance. I(ecord number of pletely full, as evidenced by grease starting to come out
i. Again check
around circumference of hub spider at ’LO" ring (7).
weight slugs. Avoid blowing out "0" ring and gaskets (27) with ex-
The final number of weight slugs be deter- cessive pressure.
j. can now

SECTION IV.WEAR TOLERANCES

Table Il, TOLERANCES OF WEARING SURFACES, HC-92~

Item Replace if dimension

Port Description of Measurement Specified is above or below
No. or

Max. Min. Max. Min.

1.7186 1.7180 1.7185

1 A-130~ Pilot Tube O.D., Inner 1YI inch 1.7187
1.7203 1.719T
1A A-1308 Pilot Tube O.D., Outer 1 inch
a A-1308 Pilot Tube Assembly, length extending beyond
C-1304 Hub Spider s~-Cia 33k--I$ 3~4_C_jg
1.7185 1.7186 1.7185
3 A-1884 Pilot Tube O.D., Inner l’/e inch
1.5760 1.3755 1.5740
4 A-1884 Pilot Tube O.D., Outer l’ia inch
5 A-1884 Pilot TUbe, length extending beyond hub spider 3~Y4-C-,1, 33/4-7$ 33~C5g
1.7225 1.7215 1.724
B Blode 8ulhing I.D.
3.782 3.780 3.785
7 C-852-1 Piston, A-862 Pushing I.D.
.3745 .3750 .3755
8 C-852-1 Piston, Pin hole l.D.
3.778 3.776 3.773
8 8-854 Cylinder O.D.
.985 .984 .981
10 8-855-A Pilot Tube Diameter O.D.
A-856 Mushroom bore .988 .986 .993
11
2.243 2.241 2.235
la A-857 Spring Retoiner O.D.
.3755 .3750 .3785
´•L3 A-861-3 Link Arms I.D. Smell End
A-861-3 Link Arms I.D. Large End .5635 .5625 .5645
14
A-9a4 8ushing LD. .502 .501 .504
15
15620 .5615 .5600
16 A-944 Bushing O.D.
.5005 .4995 .4970
17 A-304 Link Screw O.D.
440 min. 600 min. 400 min. 550 min.
18 Feathering Spring Assembly compression lood (Ibs.)
Extended Compressed Extended Compressed
2% 2%

is Balonce Tolerance 1 Slug A-1305

20 Blade Trock
Bbde End Play .060
21
Fore ond Aft Movement of Blade Tip .068 .100
23

TABLE 111, BLADE REPAIR TOLERANCES

Blade Designs 8447 and 8447-12A

Blade Design 8847
(Exclude 36)*

Thickness Width
Thickness Width

Radius SpeEifieb Minimum Specified Minimum Radius Specified Minimum Specified Minimum

12 1.360 1.304 5.750 5.587 14 1.360 1.304 6.10 5.928

18 .845 .798 1 6.520 1 6.321 20 .845 .757 6.520 1 6.318
?4 .560 .517 1 6.320 6.091 26 .560 1 1497 6.320 6.080
30 .397 1 .354 5.750 5.460 32 .397 .355 5.750 5.948
36 ".283 ".231 1 *4.660 *4.196 38 .283 .233 4.660 1 4.188

-6-
 SECTION V 4. GulflexA.
This grease is recommended for the blade ball
LUBRICATION bearings as it will not bleed oil in hot ~´•cather.
j~ KPM Aviation Grease No. 2
A. General Properties of Grease Required. Standard Oil Co. of California.
6. Stroma LT-I (2-815 Grease)
An~ grease used must ha\´•e the following properties: Union Oil Co. of California.
(a). Waterproof. 7. KPM A\´•iation Grease No. 1
!b). Temperature range between -150andF Standard Oil Co. of California.
1500 F; or --100 to 1000 F if operation is 707
8. Lubriplate
in cold climate. Fiske RI´•othel´•s,’Tolcdo, Ohio.
cc). Freedom from separating oil from soap base 9´• Mobilgrease Arte Lo-Hi PI)-535-K
due to centrifugal force or high tempera- Socony Vacuum Oil Co.
ture. 10. No. 84 Medium Grease

id). Low Friction. Ke)stone Lubricating Co.

11. ’I’rsaco liegal Stalfas Special.
B, List of Approved Grease, by Spec. or Name. 12´• iMolub-Allov No. 2 Grease -100 F.
No. 1 GI´•ease -2jO F.
1. MIL-G-2382$
Illlpelial Oil gr Grease Co.
2. 630 AA Los Angeles, Califolllia.
Lubriplate
Fiske 131´•others. Toledo, Ohio. I:i. Gr´•lman)´•--Calypso1 H729
?’his grease will bleed oil in hot weather. It is I´•ec- Gclnlan Cal)psol Collll,all)´•, l)usscldorl.
onlmcndcd only for lubrication of the blade pilot
tubes: but not the blade bearings.

:i. Stroma HT-1 !2-801 Grease) C, proper times and amounts of grease are
Union Oil Co. of California. mentioned during assembly procedures.

SECTION VI SERVICE TROUBLES AND REMEDIES

Trouble Probable Cause Remedy

FAILURE If rpm fails to increase but will Set relief valve in governor to provide necessary prersure, up to
OF PITCH reduce: Low oil pressure. 275 psi.
TO CHANGE
If rpm change in both direc- See "Excersive Friction in Hub Mechanism, below. Isolate friction
tions is sluggish: Excessive fric- in each blade by uncoupling pirton and resting each blade
tion in hub mechanism. reporotely, before tearing propeller down.
Newly-installed governor has Check and correct.
wrong direction of rotation, or
has bypass plug in wrong hole.

EXCESSIVE FRICTION Pilot tube has slipped out slight- Tear down and check distance pile, tube extends from hub spider.
IN HUB MECHANISM ly and is rubbing hard against Should be 3% inches. If more, remove pilot tube and replace with
end of hole in blade. a tube .002 in. overtire at hub end.

Blade bushing seized on pilot Polish pilot tube and blade bushing with fine emery paper and
tube. reassemble.

Blade ball bearings unusually Replace bearing.

rough or broken.

Friction in various moving parts Check parts individually. If tightness i, encountered in sliding
of pitch control mechanism. parts, increase clearances slightly. Apply oil externally to mov-
ing ports.
IMPROPER RPM Static rpm too low. Governor ha, high rpm stop. os well os propeller low pitch stop.
Either the governor or the propeller stop may limit maximum rpm.
To determine which is causing trouble, open the throttle and
move governor control back and forth slowly.

If maximum rpm is reached BEFORE governor stop is reached,

propeller stop is probably limiting the rpm. If this is the core,
loosen blade clamp outer bolts and rotate blades in clampr.
Reduce blade angle about 10 for each 100 rpm increase. (10
equalr inch circumference at blade root.)
If maximum rpm is reached AT SAME TIME or governor stop is
reached, governor stop is propably limiting the maximum rpm. Re-
odjurt governor stop to obtain proper rpm. One turn of governor
stop screw equal, about 17 rpm. Turn stop screw out to in-
crease rpm.
Governor stop should limit high rpm, with propeller stop reached
at 50 to 100 rpm beyond. This allows for variations in engine
power without affecting maximum rpm.

-7-
Trouble Probable Cause Remedy
Static rpm too high. Reduce by screwing governor stop in, one turn for each 17 rpm
reduction.

FAILURE TO Governor control doer not pro- Provide sufficient travel in governor control. Governor must
FEATHER vide enough travel to allow drain oil out of propeller during feathering.
governor to move hard against
high pitch stop.
Excessive friction. See "Excessive Friction in Hub Mechanism."

High pitch stop pin foils to Check for burrs on pins. Check for rtiffness of spring. If propeller
slide out at feathering rpm, feathers at high rpm’s but fails to feather at low rpm’s, too-stiff
spring is indicated. Reduce length of spring by one or two turns.
Weak or broken feathering Replace.
spring.
SURGING (Whon governor Air trapped in propeller octuat- Provision should be incorporated in engine to allow
trapped air to
control is changed rapidly ing piston or in engine shaft. ercape from system during one half of the pitch change cycle.
or rough air is Exercise propeller by changing pitch or feothering before each
encountered.) flight.
Governor pressure too low. Adiust governor relief pressure so that rate of pitch change is
the same in both directions.

Excessive friction in pitch See "Excessive Friction in Hub Mechanism."

change mechanism.
Governor lacks sufficient Change or adjurt speeder spring. Thir gives governor more
dampening. stability, but maker pitch control more senritive, which may, in
turn require re-rigging of control to offset higher spring rate.
Changing to stiffer speeder spring should be done only after all
other factors are checked and corrected.

011 LEAKAGE Faulty "O" ring seals follows: as Oirasremble and inspect "G" rings and the surfacer they seal.
Front of rear cone between Replace "O" rings if defective. Replace cylinder if surface ir
engine rhaft and hub, scratched or nicked in area where ’’O" ring slider. Use gasket
Between hub and cylinder. compound on cylinder threadr when replacing. Peen down
Between piston and cylinder raised placer caused by tightening of cylinder with bar.
at front of piston.

GREASE LEAKAGE Grease leaks post clamp seal Loosen clamp bolts and replace gaskets. Standard thickness of
(Only source of gasketr. garket is .050, but.060 gaskets ore available in care .050 garketr
grease leakage is are not compresred sufficiently to hold.
blade bearings.)

Grease leak, from between lnrcribe blade with ink pencil to assure correct blade angle on
or

blade and clamp. reassembly, and blade and clamp. Add gasket compound
remove
in radiur of blade butt. Replace blade and clamp.

END PLAY IN Buildup of manufacturing Total end ploy of .060 is permirsible.

BLADES I tolerances.

BLADE TRACK Tolerance of inch h allowed.

BLADE FIT ON I I With manufacturing toleroncer,

the maximum that the blade tip
HUB PILOT TUBE can be moved fore and aft is .068, without grease in blade
clamps and bearingr. With grease, the movement is nil. If blade
tip fore-and-oft movement increaser to .100 dry, blade requirer
factory re-burhing.

PART III PARTS LIST

S~CTION I

INTRODUCTION

The first column in each parts list is the figure and If you do not know the part number, you may refer
index number. This refers to the illustration and index to the
applicable illustration and then find the index
number of each part. For example, if you are ordering number assigned to it (15). Look in the parts listing,
a blade clamp assembly and want to seehow and where
and read the part number, 838-30.
it locates on the general assembly, this column indicates
either Figure 2 or 3, index number 15. I,ooking at Fig-
ure 2 or 3 in the group assembly Parts List, index num- HOW TO ORDER.
her 15, the appearance and location of the clamp as-
sembly may be easily found, also the details of all parts It is important that the Palt Number, Part Name
contained in this’sub-assembly. and Model Number be given when ordering parts.

-8-
 HARTZELL PROPELLER, INC.
PIQUA, OHIO
PARTS LIST
PROPELLER MODELS
HC-92ZF- 2A 6 -2B
HC-92ZK-2A 6 -2B I Number Required

Code I I 1 HC- 9 2ZF I HC- 92ZK

No. Number Nomenclature -2A -28 -2A -2B

Part

2 840-21 HUB SPIDER UNIT 1

3 C-1304-5 Hub Spider 1 1

4 A-1308 Pilot Tubes 1 2 2

2 840-23 HUB SPIDER UNIT 1

Ci1314 Hub Spider 1
3
A-1308 Pilot Tubes 2
4

840-46 HUB SPIDER UNIT I I I I 1

2
3 C-1314-4 Hub Sp~der I I I I 1

4 A-1308 Pilot Tubes I I I 1 2

HUB ASSOCIATED PARTS

7 PRP-909-7 "O" Ring, Blade 2 2 2 2

A-1303A Bearing, Blade 2 2 2 2

5
A-1889 Ball Spacer, Bearing (Optionp 2 2 2 2

6 A11331 Split Ring 2 2 2 2

PRF-909-6 "O" Ring, Shaft 1 1
.5002 x 1" Danley Dowel Pins 2 2
A-1333-4
v or Hex Head Bolts 6 6
A-2040
AN960-816 Washer s 6 6
11 PRP- 902- 3 2 "0" Ring, Shaft 1 1
14 B-1322 Shim 1 1

12 A-1328 12 Point Bolts 4 4

13 A-1315 12 Point Bolts j I 1 2
13 A-1333 Hex Head Bolts I I I 1 2

838-30 CLAMP 6 COUNTERWEIG)IT ASS’Y 2 2 2 2

16 C-1301 Clamp 2 2 2 2

19 A-304 Linkscrew 2 2 2 2

20 A-285 Staking Pin; Linkscrew 2 2 2 2

17 833-7 Counterweight Unit .t 2 2 2 2

A- 2036- 30 Socket Head Cap Screws, Ctwt~ 4 1 4 4 4
25
22 A-285 Staking Pins, Sk.Hd.Cap Sc, 4 4 4 4
A-65 Staking Pin, Counterweight 2 2 2 2
18
21 ~S15001-1 Zerk Fittings 4 4 4 4

27 A-1306 Clamp Gaskets 4 4 4 4

26 A-282 Socket Screws, Clamp 1 4 4 4 4
AN380- 3- 2 Cotter Pins, Socket Screw 4 4 4 4
A-1372 Clamp Bolts, 12 Po.rnf 1 4 4 4 4
24 A-1373 Clamp Nuts 4 4 4 4
No. 3 Lubricaps 4 4 4 4

t-ion~l, use ~-AU380;3-ZCbtter Pins.

-9-
 HARTZELL PROPELLER, INC,
PIQUA, OHIO
PARTS LIST
PROPELLER MODELS
HC-92ZF-2A 6 -2B
HC-92ZK-2A 6 -2B r Number Reauire

Code
HC-92ZF HC192ZK
No. hart Number Nomenclature
__
I -24 I -2B I -U I -2B
CLAMP ASSOCIATED PARTS
28 k-1305 Balance Weights As Ne ed ed
31 AN501A1OI( Screws, Balance Weight As Ne ed ed
29 A-881-1 Stop Plate 2 2
29 A-881 Stop Plate 2 2
AN960-10 or -10L Washers, Stop Prate 4
30 AN501Ar016 Screws, Stop Plate 4 4 4 4
33 A-944 Sleeve, Linkscrew 2 2 2 2
32 AN380-3-3 Cotter Pin, Sleeve 2 2 2 2

34 830-2 AUTO HIGH PITCH STOP UNIT 2

35 B-882-1 Bracket 2
36 A-883 P~n 2
37 A-884 Spr~ng 2
AN936A10 Washer 2
38 AN380-3-3 Cotter Pin 2

34 830-4 AUTO HIGH PITCH STOP UNIT 2

35 B-882-4 Bracket 2
36 A-883 Pin 2
37 A-884 Spring 2
AN936A10 Washer 2
38 AN380-3-3 Cotter Pin 2

34 830- 9 AUTO HIGH PITCH STOP UNIT 2

35 B-984 Bracket 2
36 A-883 P~n 2
37 A-884 Spring 2
AN936A10 Washer 2
38 AN380-3-3 Cotter Pin I I 1 2

34 830-12 AUTO HIGH PITCH STOP UNIT 2

35 B-882-12 Bracket 2
36 A-883 Pin 2
37 A1884 Spring 2
AN936A10 Washer 2
38 AN380-3-3 Cotter P~n 2

AUTO STOP MOUNTING PARTS

A-1338-1 Bracket 2
39 AN74-5 Hex Head Bolts 4 4 4 4

-10-
 HARTZELL PROPELLER, ’3[NC.
PZQUA, OHIO
PARTS LIST
PROPEUER MODELS
HC- 92ZF- 2A 6 2B
HC192ZK-2A 6r -2B Number Require~

Code I I I HC- 9 2ZF I HC- 9 2ZK

No. Part Number Nomenclature -2A 2B -2A -2B

831- 5A SPRING ASSEMBLY I i 1 1 1

43
B-855A Pilot Tube 1 1 i 1
49
A-856 Mushroom 1 1 1 1
44
A-860~1 Spacer Tube 1 1 1 1
50
B-953 Spring, Inner 1 1 1 1
48
B-853 Spring, Outer 1 1 1 1
47
A-857 Spring Retainer, Rear 1 1 i 1
45
1 1 1 1
46 A-858 Split Retainer, Rear

52 832124 PISTON ASSEMBLY 1 1 1 1

C-852-6 Piston Unit I 1 1 1
56
A-1464 Link Pin Unit 2 2 2 2
3,54,
2 2 2 2
54 AN501A10-6 Safety Screws
A-861-3 Link Arms 2 2 2 2
55

HYDRAULIC ASSOCIATED PARTS

62 PRP- 909-13 "0" Ring, Cylinder 1 1 1 1

6r B-854 Cylinder 1 I 1 1
Front 1 1 1 1
A-859 Split Retainer,
2 2 2 2
A-899-( Feather~Lng Stops
bu AN501A1016 Screws, Feathering Stop 4 4 4 4
51 PRP- 914- i 2 "0" Ring, Pilot Tube 1 1 1 1

63 PRP-902-46 "O" Ring, Piston 1 1 1 1

61 A-863 Dust Seal, Piston 1 1 1 1

64 A-880-2 Flexlock Nut, Piston 1 1 1 1

68 835-13 SPINNER ASSEMBLY 1 1

70 C-888-4 Dome, Spinner 1 1

71 AN526C1032R7 Screws, Dome 14 14

72 C-807-1 Bulkhead Unit 1 1

73 AN4-15A Hex Head Bolts 4 4

40 AN960-416 Washers 4 4
41 AN960-k16L Washers 4 4
42 H10-4 Kaylock Nuts 4 4

68 835-6P SPINNER ASSEMBYL (Polished) 1 1

70 C-888-4P Dome, Spinner (Polished) 1 1

71 AN526C1032R7 Screws, Dome 14 14
69 C-885P Adaptor Ring Unit 1 1

835-16 SPINNER ASSEMBYL 1 1

0-888-4 Dome 1 1

AN526C1032R7 Screws, Dome Mounting 14 14

1 1
C-885 ptor

-11-
 21

24
31 28

24 22

21a/ 2517
Ilo~´• Is

rF
2016
27
32
16 ´•,_ -_-19

54
6
61

2629 33
59

55
72

71
bs

P 70

10
ENGINE
‘Q, SHA;FT

I
rla3 46

45
56

o.
I

37

36 50r; 64 42

41

3835
~nj
39~
P
62
as

43 67
~13

6o65
B,c66
49

FIGURE i--Model HC-9~dF-2A Propeller, Exploded View

 HARTZELL PROPELLER INC.
PIQUA, OHIO
PARTS LIST
B PROPELLER MODELS´•
HC-92WF-2A
HC192WK-2B Number Re4uire

Code HC- 9 2WF- 2A HC- 9 2WK- 2B

No. Part Number Nomenclature

2A 840- 109 HUB SPIDER UNIT 1

3A C-1304-5 Hub Spider 1
4A A-1884 Pilot Tubes 2

2A 840-88 HUB SPIDER UNIT 1

3A C-1314-4 Hub Spider 1
4A A11884 Pilot Tubes 2

HUB ASSOCIATED PARTS

7 PRP-909-7 "O" Ring, Blade 2 2
5 A-1303A Blade Bearing 2 2
A-1889 Ball Spacer, Bearing 2 2
6 A-1331 Split Ring 2 2
10 .5002 x 1" Danley Dowel Pins 2
8 PRP-909-6 "O" Ring, Shaft 1
A-1333-4~---)
9 1 ´•r ~---IHex Head Bolts 6
A-2040 1
AN960-816 Washers 6
PRP-902-32 "O" Ring, Shaft 1
14 B-1322 Shim 1
13 A-1333 Hex Head Bolts 2
12 A-1328 12 Point Bolts 4

838-30 CLAMP COUNTERWEIGHT ASS’Y 2 2

16 C-1301 Clamp 2 2
19 A-304 Linkscrew 2 2
20 A-285 Staking Pin, Linkscrew 2 2
17 833-7 Counterweight Unit 2 2
25 1 A-2036-30 Socket Head Cap Screws, Ctwt~ 4 4
22 A1285 Staking Pins, Sk.Hd.Cap Sc. 4 4
18 A-65 Staking Pin, Countexweight 2 2
21 MS15001-1 Zerk Fittings 4 4
27 A-1306 Clamp Gaskets 4 4
26 A-282 Socket Screws, Clamp 4 4
AN3 80- 3- 2 Cotter Pins, Sk. Sc. 4 4
23 A-1372 Clamp Bolts, 12 Point 4 4
24 A-1373 Clamp Nuts 4 4
No. 3 Lubr´•lcaps 4 4

-13-
 HARTZELL PROPELLER, ZNC,
PIQUA, OHIO
PARTS LIST
PROPELLER MODELS
HC-92WF-2A
HC-92WK-2B Number Reauired

Code
No.
HC-92WF-2A HC-92WK-2B
Part Number Nomenclature

CLAMP ASSOCIATED PARTS

28 A-1305 Balance Weights As Needed As Needed
31 AN501A10-( Screws, Balance Weights As Needed As Needed
29 A-881-r Stop Plate 2
29 A-881 Stop Plate 2
AN960~10L or -10 Washers 4
30 AN501A10-6 Screws, Plate 4 4
33 lA-944 Sleeve, Linkscrew 2 2
32 IAN380-3-3 Cotter Pin, Sleeve 2 1 2
2-45 Parker "O" Ring, Blade 2 2

34 830-4 IAUTO HIGH PITCH STOP UNIT 2

35 B-882-4 IBracket 1 2
36 A-883 Pin 2
37 1 -A-884 Spring 2
AN936A10 IWasher 2
38 AN3 80- 3- 3 ICotter Pin 2

34 830-9 IAUTO HIGH PITCH STOP UNIT 2

35 B-984 IBracket 2
36 A-883 Pin 2
37 A-884 ISpring 2
AN936A10 IWasher 2
38 AN3 80- 3- 3 /Cotter Pin 2

39 IAN74-5 r~ex Head Bolts 4 4

43 1831- 5A ISPRING ASSEMBLY 1 1

49 B-855A IPilot Tube 1 1
44 A-856 tMushroom 1 1
50 A-860-1 $pacer Tube 1 1
48 B-953 ~pring, Inner 1 1
47 B-853 ~pring, Outer 1 1
45 A-857 ~pring Retainer, Rear 1 1
46 A-858 ~plit Retainer, Rear 1 1

52 18 3 2- 24 1PISTON ASSEMBLY 1 1
56 C-852-6 $iston Unit 1 1
3,54,58 A-1464 ~ink Pin Units 2 2
54 AN501A10-6 Fjafety Screws 2 2
55 A-861-3 tink Arms 2 2

-14-
 HARTZELL PROPELLER, INC.
PIQUA, OHIO
PARTS LIST
PROPELLER MODELS
HC-92WF-2A
HC- 9 2WK- 2B __
I Number Require

Code HC-92WF-2A HC-92WK-2B

No. Part Number Nomenclature

HYDRAULIC ASSOCIATED PARTS

B-854 Cylinder 1 1
60
PRP- 909-13 "0" Ring, Cylinder 1 1
62
A-859 Split Retainer, Front 1 1
67
Feathering Stop Plates 2 2
65 A-899-(
4 4
66 AN501A10-6 Screws, Stop Plate
PRP-914-12 "O" Ring, Pilot Tube 1 1
51
PRP-902-46 "O" Ring, Piston 1 1
63
A-863 Dust Seal 1 1
61
A- 880- 2 Flexlock Nut, Piston 1 1
64

835-13 SPINNER ASSEMBLY 1

68
C-888-4 Dome, Spinner 1
70
AN526C1032R7 Screws, Dome Mounting 14
71
C-807-1 Bulkhead Unit 1
72
AN4-15A Hex Head Bolts 4
73
40 AN960-416 Washers 4
AN960-416L ashers 4
H10-4 Kaylock Nuts 4

835-6P SPINNER ASSEMBLY (Polished) 1

611
C-888-4P Spinner (Polished) 1
70 Dome,
AN526C1032R7 Screws, Dome Mounting 14
71
C-885P lAdaptor Ring (Polished) 1
69

835-16 SPINNER ASSEMBLY 1

68
C-888-4 Spinner 1
70
AN526C1032R7 IScrews, Dome Mounting 14
71
I
69 C-885 IAdaptor Ring Unit

68 83 5- 3 0 ISPINNER ASSEMBLY 1
1
70A C-1904-1 p~ome, spinner
71 AN526C1032R7 IScrews, Dome Mounting 14
C-885 IAdaptor Ring Unit 1
69

-15-
 21

24
24
22
8/
25
21
17

18

///I
I/

c~V e-----------------
2016
27
I
16
-----(iP~ 19
8
23

61
~a----- 53
5

59
29 33
7
I
55 1 I Fo

41
ENGINE
SHAFT
31
~v
r

46
56‘C:y 56 69

71
68

37 14 i13D‘ ~L5
i~Q 70
50
36 11 64

38

35 Ijt,
12 48

a.
62

60
a3 44

C
p~ 66
49
FIGURE J--Model HC-PZtK-2A Propeller, Exploded View

51
04
 108A

HANDBOOK

OVERHAUL
INSTRUCTIONS

PROPELLER MODEL
BC-B3Z30-2E
3 BLADE, CONSTANT

SPEED AND FEATHERING

HC-B3’6J30-2E
HC-B3P30-2E
HC-B3R30- 2E FAA APPROVED
HA-B3P30- 1B
HC-B3P30-I.

HARTZELL PROPELLER, INC,, P’IQUA, OHIO

 RECORD OF REVISIONS

MFG REV
NO DESCRIPTION ISSUEDATE ATPREVDATEI INSERTED BY
 RECORD OF TEMPORARY REVISIONS

ATP REV INSERT DATE REV REMOVE

TEMP
DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY
REV NO
 TADLE O~-- CONTEN-TS

/n 1 a I (1 n~ ~n a a 7e A ~-J nl
1 B~PI’\M U

Section I 1

I
Description of I,1´•opcllcl.

SectionlI Instl´•uct;ons I

Special Tools Table I

A. Removal of P1´•opelle~ from Engine I-IC-B3%30-2~ 2

2
]B. Disassembl): ofPropcllcl´•
3
C. Cleaning
3
D. Inspection
3
r;. r\cpn;l. or Replflccmcnt
3
I~. ~ssembly

Section III ~nlance 5

SectionIV ~\’ear?’olcrnnccs G

I-lub l’able II ~Vcnl´•incS G

a..~.
?’olc~nnccj 6
Blade Table IiT Repair
Table IV Tot-clue V~lues G

Section \r List of Apl,1´•ovcd Grc~se I

i
Section Scrv;ce T1´•oublcs and
r~crni´•tlies

88

Sectior.i I Introduction 8

P,ll.ts Liit 9
Section II Group r2sscm~,ly
X1C-E3Z30-2E 9

Go\´•clrlol-- hIodification foi

P
c~ It-9n5 Ilng;i-ics i’

NO~’E: Ope,ntion nntl Gei~ei´•rtl Se,´•z~ice nl´•e sNI,jccf8 zlJ!icil

rc,´•e cc,r´•e,´•cc2 tlte E~lto.tzcll "lilcj~ri´•’s I’iv,l.,Ellc,´•

ORIGINAL AS RECEIWED BV ATP.

 PART I-OVERHAUL

SECTION 1

DESCRIPTION

The model HC-B3Z30-2E is a 3-blade constant speed and feathering propeller de-
signed for engines in the 400 to 500 horsepower class having S.A.E. 30 spline shafts.
This model supersedes the earlier HC-93Z30-2C and 2E models. The HC-B3Z30 model
HC-
utilizes split type blade bearings, together with a modified hub spider, whereas, the
93230 propeller utilized solid blade bearings retained by split rings.

The dash 2E model has a larger hydraulic pitch actuating piston than the earlier
dash 2C. This larger piston makes for bettersynchronization of twin engine aircraft.

This propeller is designed to be controlled by governor mounted on the engine

Governor oil pressure (0 to 300 psi
supplying engine oil through the propeller shaft.
range) decreases the pitch, while counterweights attached to the blade clamps increase pitch.
A spring assists the counterweights during the feathering operation. Feathering the pitch
is accomplished by opening a valve in the governor which allows the feathering spring
the
to force the oil out of the propeller and baclll.into the engine, thereby increasing
blade angle to the feathered position.

of the
Centrifugal stops prevent feathering of the propeller, due to the action
spring, when the engine is stopped. At speeds of over 500 RPM, the stops are re-

moved by centrifugal force, allowing the propeller to be feathered at any time.

Unfeathering is accomplished by any of several methods as follows:

(a) Restarting the engine will provide oil pressure to unfeather the propeller.
be
(b) An oil*air accumulator sealed by a valve when the propeller is feathered, can
utilized to provide pressure for unfeathering.
(c) An electric operated oil pump can be used to pump oil back into the propeller
for unfeathering.

SECTHON II

OVERHAUL INSTRUCTIONS

Part No. Nomenclature

B-840 Shaft NutWrench

461 Spanner Wrench,831-12 Spring Assembly
B-842 Wrench for A-830-1 Nut on Spring Assembly
C-845 Fixture for Assembly of feathering Spring
Propeller Table, 30 Spline Spindle
Bldancing Equipment, Wire or Arbor
BT-222 Ass’bly Tool for Pressing A-1852 Ring on C-1853 Hub Spider
BT-223 Puller tool A-1852 Ring
for
B-844 Tool for Pressing A-1308 Pilot Tube into C-1853 Hub Spider
SK-274 Piston Fixture Used for Balancing
 A. RElklOVAL OF PROPELLER FROM (c) Front tile cjanlps (19) I´•elllove the lul,ricalor rillin#s
ENGXNE (See Figure II) 122). Remove the stop plates (32) by takiny oLlt screws
(33). Remove the bahlce weights (30) by taking out
(a) Remove spinner dome (69) by taking out screws 170) screws (31).

id) Remove the counterweight mounting screws (28).

WARN I NG These screws should be replaced immediately with new
I, ones. Torque to 65 ft. Ib. Safety with cotter pin.
Feather propeller before removing nut (46). (Use
CAUTION
blade bars to compress feathering spring so that
high stop pin (76) can be pushed out allow
to

propeller to be feathered. An alternate method In normal overhaul operations, it is not necessary

is to start engine and feather propeller.) to remove the counterweights from the clamp and

counterweight assernbty (18). If either the clamp

(6) Remove nut (46) using special tool B-842. Remove
or counterweigfit requires replacing, the entire as-
screws (59), nuts (58) and washers (57). Remove the
three link pin assemblies (55) by taking out screws (56).
sembly should be replaced. If the parts are to be
replated, the counterweight (27) should be
(c) Remove piston assembly (49). From the piston, re- stamped with the serial number corresponding to
move the "0" ring (61) and felt seal (62). the clamp (19). After plating reinstall counter-
weight on corresponding clamp. Use new bolts.
(d) Unscrew feathering spring sub-assembly by unscrew- The dowel pin (29) need not be removed com-
ing spring retainer (44) from cylinder (10). pletely.
(e) Remove propeller shaft safety lock ring (17). (e) Remove bushing (3´•1) and pitch change link arm

(f) Use special tool No. B-840, the propeller shaft nut (60) by taking out cotter pin(35).
wrench, to unscrew propeller shaft nut (7). This does
not remove the nut, but forces the propeller off the en- BLADE BEARINGS
gine shaft. When the propeller is off the shaft, remove
(a) Slip wire ring (15) from groove formed in inner
the hub mounting cone (6), the hub mounting "O" ring
bearing race (12) and remove two halves of inner bear-
(11), and the rear bulkhead assembly (71j or (85) as ing race (12). (It is assumed that the balls have been
the case may be.
removed when the clamps were removed).
NOTE: If the propeller is not to Be overhauled
immediatety after removing from the engine, it (b) Using Special Tool RT-222, drive guide ring (13) in
nzay be reassembled at this point for storage 07 slightly towards the center of hub (3) only enough to un-
shipment to the overhauling activitll bll followiny, cover wire ring (16), which can then be removed. Using
in general, the reverse order of disassembEy.
Special Tool RT-223, pull guide ring (13) from hub (3),
Remove two halves of outer race of bearing (12).
Bi DI~ASSEMBI,Y OF PROPELLER
(c) Remove "O" ring (14).
Mount the propeller on a table having a 30 spline
shaft Stub extending up from the surface. FEATHERING SPRING SUB-ASSEMBLY

CYLINDER (10) CAUTION

(a) Use a i-inch square bar as a wrench to unscrew the

cylinder (10). From the cylinder remove "O" ring (9j. Do not attempt to disassemble the featherina
the collar spring sub-assembly (37) unless Special Tool No.
(b) From piston guide (63), remove screws
the.fixture for assembly of feathering
C-845,
(67). is available.
springs,
(c) Removel of cylinder (r0) also frees the propeller
:rhaft nut (I)and puller ring (8). (a) Place feathering spring sub-assembly (37) in the
fixture and compress the springs (41), (42), and (43).
Slide the retainer ring (40) back on the pilot tube (38)
CLAMPS AND BLADES and remove the split ring (39). Release the spring com-
(a) With ink and a scale; mark matching lines on the pression slowly and remove retainer ring (40), springs
blades (1) and the clamps (19). Record each blade serial (41), (42), and (43). Remove spring retainer (44) and
number with the corresponding clamp number. "0" ring (471 from pilot tube (38). Remove
stop screws
(45) from spring retainer (44),
(b) Remove the screws (24), (25) and nuts (26) from
the clamps (19). Remove the clamp halves and the SPINNER BULKHEAD WITH STOPS
clamp gaskets (23). Remove the blades (1). (AND ANTI-ICING RING)
CAUT IO N Ca) Remove nuts (83), washers (82), (81) and (80),
and bolt (79), to free automatic high pitch stop asseln-
bliss (74), and the anti-icing ring (86) front the
When the clamps (19)are removed, the balls from head assembly (72).
the bearings (12) may drop out. Either catch the
balls in a container as they drop out, or remove (b) Disassemble the high pitch stop assernblics by i´•e-

one clamp (19) carefully at a time, and hold the moving from each the cotter pin (78). This allows the
bearing races together so the balls cannot escape spring (77) and pin (76~ to be relrlovcd froln the
until they can he caught in a container. bl´•nc~rt (75).

-2-
 (c) Kerllo~e travel tube unit (91) and hose (C30) by tak- the hub sl,ider tube (4) into the hub
ltole. Press the new

ing "Ut SC’eu´•s a92) and nut (93). spider (3 leaving exactly 33~ inches of the length ex-
posed. Vie sure tile 2lcavy end of the t~lbe is inserted into
HIJD SWDER ASSEAIBLY the hub. Test the tube for tightness by applying j000 Ib.
force on the tube. II it slips with ttlis fol‘ce, it lill.lSt be
II inspection of the hub spider sub-assembly shows
I´•eplacedwith a lal%er tube of say .003" to .004" oversize.
that any of the hub pilot tubes (4) require Icpiacement,
they may be pulled from the hub spider (3) by means of (b) KePlace tile counterweight illounting screws (28) as
an al)PTOP’iat" bearing puller, noted above. Use only tile specified parts as they are
heat treated to a high strength.
NOTE.- Dct Ilot verrlove tke hub pilot tlbes (4)
unkss Special 7’ooE ~o. 844, t]ce fiztlc?.o fo,. p?ess-
(c) Keplace all gaskets,’;C)" rings, arld colter pins.
ing the hulr pilot i~be into the huD, iv az´•tiluhle to
aid i71. insklling the replacenzent tube. Nicks or deep scratci-les in cylinder (10) Inay be
(d)
cause for rcplacenlent, particularly if the marks are ill the
C. CLEAN~WG region of the piston ;’C)’’ ring dul´•ing~ normal crllise flight.
Scratches in the feathering region Inay be tolerated if
(a) \\’il,e all dirt and grease off all parts. not too deep.
(b) Clean ail parts, except felt seal (61) with solvent, (e) Keplatirlg (cadmiuln) of steel parts is recommended
and dry, if thF~ nt´•;a;n~l nlatjnrr h119 been ~vorn off or if damaged
---a----- I-------´•~

(c) Apply by nicks or scratches.

a rPastprcl´•entative conlpound on all parts
wtlich are to be staretl for an): length of tirrle, or sl~ipped.

(dj JCeep in clt´•~n and dry place before reasselllbly.

D. INSPEC~ltON
The hub spider amis (3) and pilot tubes (4)
should be Inasked. ATter plating the parts, they
(a) Inspect all wearing parts according to tolerances
Inust be baked in an oven at 3500 F. I,lus or
specified in ?’nKLE II. Keplace parts not coining within
Ininus 25" fol´• 3 hours to eiirilinste possibility of
sI’ecificd jillli~i.
hydrogen emblittlenlcnt. Hi~h slrengt2l bolts, hub
(b) Illspect tire bIarlcs according to the tolerances in and clalrlp parts are to this
?’AHI,E IIT. a blade which falls belo~y the: listed effect. Failul´•e of the par´•t Irlny r´•esult unless this
minimuln dilmmsions Lrpon Icpair.
baking is accornl,lished. If proper´• plating facilities
are not available, the parts should be painted ~vith
(c) Visually inspect all metal s~ufaces. 1Ceplace or I´•e-
a suitable alulrlinl~m or lacclucr paint.
finish any bearing or wear surface wftich ilas a visible
nick, dens: or other distortion. (f) Rcpair´• blades according to CAA Manual.

(d) Magnetically inspect all steel parts for cracks not (g) I3lade bushings. If the blade bushing is worn beyond
visible to the eye.
specified tolerances, the blades should be: returned to the
(e) Visually inspect the blades for cl´•acks, ~,articularly factory to I:,e rcbushed. These bushings seldo~n wear,
around the shank retention and however, to the point where they must be replaced.
area at the leading edge
near the tip.
]F. ASSI:R´•IBI,Y
(f) Inspect tlae
bearings for escessive wear or chafing.
A certain ;unount of Inalking of the balls and I´•aces is to (See Fig. II)
be exyec~ted and is not necessarily a reason for replace- Keassemble ill reverse order of disassemhly as follows:
ment. Only when the bearings show pit mar´•ks which are
.002" deep and definitely feel louah, are the balls or races IZIJLI(PIEthD SUB-ASSER/IRL,Y (81i) (Anri-icingr)
to be replaced. I)earing life ordinarily is greater than Reassemble the automatic high pitch stop sub-as-
1000 hours.
selnblies by inserting into each bracket (75),pin j761,arld

(g) Insprct pilot tube (4) for slippage. The tube should spring (77). Use a cotter pin (76) to hold the parts. 7’he
extend front hub 33G inches only. If this distance is
out Sl’ring end should be bent around the cotter pin to pr.e-
C1"’1" ""Y I’os"ibility of it being Linscrewcd frolrl the
greater, tile indication is that the tube has slipl,ed out of
the hub spider. An ovelsizo tube should replace the one asse"’bly.
which slipped.
(b) Position the anti-icing ring (86) on the back side of
the bulkhead (72), and the automatic ~ligh pitch stoI~
E. REPATR ANLP REP‘I.,ACT:M‘ENT assemblies (74) on the front side. Assemble the parts to-

(n) Retnove all Sether using bolts (79), washers (80), (81), and i82),
rust,‘galling marks and nicks fl´•om ttle
and nut (83);also bolt (87),\2´•asher !88), and nut (89).
hub spider allla wit~l crocus cloth or fine emery. Rust, De sure tile thick plastic washer (80j is between the
galliIlg arld nicks ale stress raisers which reduce the
high stop bracket (74) and bul~head (72);also tlie I II
fatigue life of the hub. l)o not polisl~ unless neccssal´•y, as thick plastic washei (81) is between the steel ´•Ivasher (82)
tile sl,idel´• arrm tlave hcen rolicct to impro~:e tile fatiaue
and I,ulkhead (72), as the I,lastic is usctl to prevent chaf-
strength. (The roll marks are not tool nlar´•ks and sholld
not t3r frmovcrl.) If tlte l,lade pilot: t~lbe (4´•) is to be re-
ing of t2ie alu~niniim. Clacks sniiictiincs are cariscd by
I’laccd in tile Ilob, due either to excessi~´•e wear, or duc
c~-lafing.
to the fact that it has
slipped slifihtly fioin tile spider,
out (c) Connect travel tiibe unit (91) with anti-icing iing
it is necessary to use a new tribe having a .002" to .003" unit (86) by r!~eans
of hose (90). Secur´•e with screws (92)
oversize diameter over the 21~" length which presses into and nllts (I13).

-3-
 FEATHEKIKG SE’RING SUB-ASSEMBLY (37 NOTE: Be sure 7io air iv trnl,pecl Lelolo the U?´•c~tse
as this zcill affect balance.
NOTE: When assemblingd29cLssenLDling the
or
fecLtlering spting sllb-assembly ~57), it is impern- (c) Install blade (1) on the same pilot tribe ´•(4) fl.olll
tive that a safe means of comp,´•essing tl~e sp,´•ings
which it was rcmo\´•ed. place a hardening gasket cori~-
be used. This is ~ffol´•ded b21 the use of Special
Tool No. C-8/t5. pound automotive type) the blade
shank in the shoulder radills.
(a) Assc~nble onto pilot tube (38) spring retainer (44),
springs (41), (42), and (43), and retainer. ring (40). (d) Referring to the asscrllble link
clamp asselnbly,
Compress the springs in,fi~ture.C-845 and insert split (60), sleeve (34) ontolink screw (20), and safety with
cotter pin (35). Assemble high pitch stop plate (32)
rings ~39) in groove formed inpilot tube (38). Release
with (33) and wire safety. Install lubrication
springs, allowing Split rings (39) tonest in cavity fornled screws

in retainer ring (40). fittings (22).

(b) Install "O" ring (57) in groove at end of thread of NOTE: The link arm cannot be installed afte?´• the
pilot tube (38). clamp is installed Deen2cse of lack of clearance.
(c) Insert feathering stop screws::(45).
(e) Install the correct matching clamp and counter-
BLADE BEARINGS
~veight sub-assembly (18), with new clamp gaskets (23).
(.2)
NOTE: This process can best be ncconlplished BU
(a) Slip "O" ring (14) over flange of hub spider (3). peeling back masking tape fl.om about 180 degrees
of the bearing on the top side. Then install tl~e
(b) Slip uide
ring (13) with internal recess facing out, one-half of .clamp that has the collnterlueight.
o~´•er blade flange of’ hub spider (3). Using Special
arm Then peel the tape f?’onl the lowe?´• half of the
Tool No. RT-222, dPive guide ring (13) far enough onto Bearing whick´• is esposed, and install tile otlte?´•
clamp half. Slip the clamp gnsketN (’9) between
frange to allow´• wire ring (16) to be inserted into groove the clamps at the parti~lg line. This p?ocedure
formed in hub flange. Using Special.Tbol BT-223, pull will locate tl~e il~llel´• bearing race p~?´•ting line at
guide iing (13) back out over the top of wire ring (13) right angles u´•ith tile blade clclmp pcL?ting line,
far the wire will allow. WHICH IS ESSENTIAL.
as as ring
Fasten the cIanlp halves together with socket head
(C) In order to mount the outer bearing races (12)i in
the nest formed by the hub flaIlge and guide ring (13) SC’eWS (24), and bolts (25) with nuts (26). Tighten the
the hub should be supported with the pilot tube of the Socket head screws (24), and nuts (26) in order to check
beinrr fitted, down. BT-222 for friction of the blade when being rotated on the hub.
arm facing Spccial_Tool can

be used t~ support the hub by setting: it on a bench with

the large diameter used as a base, and the pilot tube (4) NOTE: The pitch will Be set after the propeller is
inserted in the hole of the tool. Plade the two outer assembled, after which the clamtp Dolts will De
finallll tightened and saletied.
halves of the bearing (12) in the nest formed by guide
ring f 13) with the fractured surfaces accurately matched.
(f) Check for friction or binding of blades when rotated
Snap the otlter bearing race (12) into the nest using a about their axes. If blades tend to bind as a result of
light hammer and soft punch made of aluminum or
tightening the clamp bolts to 60 ft. Ib. torque, it will be
copper. Do not scratch the bearing race. Tap the bear-
necessary to remove the clamp and blade, and polish the
ing race docvn all around until it is solid
inner portion of the pilot tube (4) with fine emery paper
against the hub flanSe. The fractured parting line of the
until sufficient clearance is obtained to insure no binding:
""Oth with a discontinuity of no more
fi~ at that point.

(dS h/lount the inner races of bearing (12) on a hltb ann CYLINDER (10)
(3) and install wire ring (15) to sectlre inplace. Locate
the bearing parting line fore and aEt or parallel willl the (a) Clean the threads of the cylinder (10) and the hub.
hub shaft axis.
(b) Insert the collar clamping screws (67) in the guide
(e) Fill the bearing (12) with corllplelllent ofballs. collar sub-assembly (63). Place the guide collar sub-
Using I inch masking tape, tvl8p the bearing O.n, to assembly over the end of the piston (10), abutting
hold the bearing races together so the balls cannot fall against the flanSe shoulder. The collar chamfer nlust
during handling. Snap the ’;0" ring (14) into bear- fac~ the hub.
ing chanli~l´•.
(c) Place the puller ring (8) over shaft nut (7).
CLAMPS AND BLADES (d) Install the cylinder "0" rings (9) in the cylinder bc-
hind the threads. Apply gasket conlpound jnon-harden-
NOTE: In orrles´• to nsssaahle the propeller and set
the shaft to nctlbate the piston. ing automotive type) to the threads.
special propeller thl,le ~lnaing a shaft
which nLates:~eith the propeller hlLB. Air or oil (ef Screw the cylinder (10) the hub (3). Use a
onto
1 inch sclual-e bar about 3 feetlong as a wrench, apl,licc!
pressure (100 psi min.) ~sholtld be a~iailable in
the shaft to rcctzlnte the pzston. to the slot in the cylinder. Tighten the c~lintlcl haltl
against the hub, (about 200 ft. Ib torcllle).
(a) Mount the hub on the table shaft using the same
Inorlntingr l,al.ts
as for the airplane, so thatthe hilb is (f) Inspect the inside of the cylinder to be "O’I lin~
scaled at the rear cone with an "0" ring, and tile shaft i9) has not been forced out of place.
nut holds the h~tb in place.
(g) TnSpect around the dri\´•e slot to be sul´•e tllal t~lr I,nl
(b) Fill the blade pilot tribe hole with grease as specified has not raised the edges, peen down anv raised etlgcs so
undel´• the list of "Grcases Recommended." they will not cut the "0" ring inside the piston.

i-=-´•-:::-: ----:--1 -4-

L._-_~L
 10/29/68

ERRATA SHEET NO, 1

MANUAL NO. 108A

Page 5

PISTON ASSEMBI~J, Item (f): Ch~nge 150 ft. Ib. torque

to read 75-100 ft. Ib.

IV TORQUE VALUES

A1880-1 Nut: Change torque to read75-100 Ib.ft. or

800-1200 Ib. in.

 IPU’STAL,LIL~C; FEGTHERING SPRING ering spring to feather the propeller. Sec airplane speci-
fications for correct feathering angle. In case, the feath-
SUB-ASS~fBLY (37)
ering angle should be increased, relnove the piston and
turn the feathering stop scretvs (45) farther into
the
(a) Slide the f~athering spring sllb-assembly (57) into
tile cylinder 41d)) and tighten using Special C~rench 461. spring retainer (44).To reduce featheling angle, unscrew
the screws. One turn of the screw equals about one
degree pitch change. Safety ~vire the screws (45) after
PISTON ASSEILIBLY (49) the feathering angle has been set.

(a) Install’Ya" ring (61) and felt seal (62) into their
(e) ifhe propeller is now ready for balancing. It is
respective grooves in the piston assembly (49). The "O" necessary to remove the piston (49) and feathering
ring goes in tile second groove, while the felt seal goes in order inrtall the balancing
h the first
groove.
Soak the ielt seal in engine oil after ;ef~iub ´•arsembly (37) to

assembling it Pnto piston; also tile "0" ring (61) and

pilot tube LCO‘" +ing (47).

(b) Slide the piston (49) onto the cylinder (10), insert-
SECTION III
ing the guide rods (52) into the bushings (65) of guide
rod unit (63‘31~ Leave the collar loose on the cylinder
BALANCE PROCEDURE
until the pitch change links (60) are fastened to the
piston.
the cylinder so the Ditch BALANCING
(c) Rotate the piston on

change link aaans (60) will fit into the slots in the piston.
Insert link pin assembly (55) to secure link to piston. Do (a) Install Special Piston Fir;ture SK-274 to replace the
not safety. piston (49) to hold the blades at low or high pitch during
the balancing operation.
(d) Tighten the clamping (67) so that collar (63)
shoulders against cylinder (10). Torque the screws (67) (b) Balance the propeller assembly before grease, is add-
4 to 7 ft. Ib. Safety with wire, unless self locking (niloc~c) ed to the blade clamps, and check again after grease is
screws are used.
added.

(c) It is recommended that a suspension balance system

~W Following the instructions for the balancing

be used.
CAU~TION
apparatus, set it to locate the center of gravity of the pro-
peIlcr before attempting to balance the propeller.

Tighten each of the 3 screws (67) a little at a (d) Place an aluminuln wedge between the hub and each
time so that the piston guide rods continue to slide of the blade clamps to remove any possible end play of
freely until the clamp is snug´•. the blade before balancing the propeller. Be sure that all
three of the wedges are close to the same weight, al-
(ej InstallwssIler (57), screw (59) and jam nut (58) though a slight difference in weight, at a point so close
in the end of each of the piston guide rods. Snug tighten. to the center of balance, will not effect the total balance
of the propeller beyond acceptable limits.
tr) Force the the guide (38). rod
3C. Screw nut (46) qn
pistonTo
~l‘orqueto 73-100ft.lb.
´•r~d.
(e) The propeller is balanced by the addition of balance
NOTE~e pilot tube (38) can be lorced through
weights, Part No. A-1305 (fig. 2-1, ref. 14) to the blade
tile enit’~of the ton b?J pres.ring down on the clamp assemblies (3) opposite the heavy side.
bEude coFa~utnuuights.
(f) Lay the balance weights in the corner formed by the
blade and clamp, until proper balance is obtained. Since
SETTING n~5DE PITCH
this is a three~blade propeller, the weight recluired to
balance is divided in half, and half of the weight is
(a) Apply air or oil pressure through the bore of the
placed dn the clamp of each of the blades opposite the
table spindle, to force the piston against the low pitch side.
Hold this position, he"vy
stops. Apply 1~00 to 125 psi pressure.

(b) Set each with a protractor located at 30-inch (p) Each clamp provides six positions for the balance
radius. See the airplane specifications for low pitch set- weights. Locate the weights to fit any of the available
tinS. Tighten tile blade clamps bolts, 30 ft. Ib. for bolts positions, until the propeller is brought into balance. Do
not attach more than four weights with each pair
of
(2j~),and a] it. Ib. for-bolts (25).
fillister head screws. A total of eight weights Ina~ be

~c) Check the blade against tuming in the clamp by placed on each side of each blade clamp, if required.
torquing tile blade to 170 ft. Ib. Usea blade bar and a attached the hlade
weight. If the blade moves in the clamp, the clamp (h) After the weight s~ujis are to

must be and the clamp parting line at the outer clamps,grease the clamps with a gun, pumping an eclual
the number of shots into each clamp.
corners filed dightly to allow the clamp to engage
blade shoulders more firmly.
(j) Recheck the balance. If out of balance, correct by
adding gIease or further slugs until the propeller is agairl
(d) Check tI~e low pitch blade angle after torquing the
blade. Check the featl´•lering angle by allowing the feath- brought into balance.

-5-
 ERRATA SHEET NO, 2

MANUAL NO. 108A

December 7, 1970

Page 6, Table III, Blade Repair Tolerances should read as

follows:

10152-5~ Blade

8 3.870 1/ 2.890~
4.825 1.610
12
.333 .457 5.500 1.120
18
32,90 33.50 .088 .152 5,816 .802
24
29,30 Se 29.34 -,122 -,058 5.982 .580
30
36 25,80 26.20 -,242 -,178 5.655 .430
23.79 -.357 -.293 ~,514 .330
42 23.30
.315
43
.285
.247
~p.
.208
46

10160-6 Blade

8 3.870 2,840 J:

4.825 1,775
12
.428 .492 5.500 1,198
Is
32.90 33.50 .088 .152 5,816 .812
24
29,3";:Se~irp 29.3" -.092 -.028 5.982 .630
30
-,217 -,153 5,666 .476
36 25.80
23.79 -.347 -.283 4.532 .365
42 23,30
,345
4
.308
.261
.225
46´•
 SECTION IV WEAR TOLERANCES AND TORQUE VALUE~S

Table Ii. TOLERANCES OF WEARING SURFACES, HC-B3Z30-2E

Replace if Dimension is
obove or below
Item Specified

Max. Min. Max. Min.

No. Port or Description of Measurement

1.7185 1.7180 1.7165

I I""e’ II~, inch
1 A1308 Piler Tube O.D. 1.7203 1.7197 1.7187
I Outer 1 inch
2 A-1308 Pilot Tube Assembly, length extending beyond
$.~:d 3J~ --~6 3% f%
C-t304 Hub Spider
1.7225 1.7215 1.724
3 8tade Bushing l.D.
4.282 4.278 4.270
4 C-1802 Piston, P.-862-1 Bushing I.D.
.3765 .3755 .380
5 C-1802 Pbton, Pin hole 1.0.
4.278 4.276 4.273
6 8-1803 Cylinder O.D.
.735 .734 .731
7 M68-2W Pilot Tube Diameter O.D.
.738 .736 .741
8 A-1827 Spring Assembly
.510 .508 .515
9 834-7 Guide toller Bushing I.D.
.3755 .3750 .3785
10 A-861-3 Link Arms I.D. Small End
.5635 .5625 .5645
11 Aa613 link Arms I.D. Large End
.502 .501 .504
12 A-944 Bushing I.D.
.5620 .5615 .5600
13 A-944 Bushing OID.
.5005 .4995 .4970
14 A-3a4 Link Screw O.D.

15 Balance Tolerance 1 Slug

A-1305

16 Blade Track +Xs

17 Blade End’ Ploy .060

18 Fore and Aft Movement of Blade Tip. .068 .100

19 81a$e Pitch Setting at 30" Sto. for R-985 Engine, Low 170

20 Blade Pitch Setting at 30" Sta. for R-985 Engine, Feather 870 C%

T/1SLE Ill. BtADE: REPAIR TOLERANCES

Angle Face Alignment Width Thickness

Radius
Min. Max. Min. Max. (Min.) (Min.)

10160-6 Blade

3.870 2.890 TABLE IV TORQUE VALUES

8
12 4.825 1.775
.428 5.500 1.198 Model HC-B3Z
2418 32.0 5.816 .810
30 295 Set 29,3 -.028 5.982 .630
36 25~8 -.153 5.655 .476
PO’t or Torque Torque
42 23.3 -.347 -.283 4.470 .365
.345 Location Hub Lb. ft. Lb. in.
43M Bolt Size on
.308
44~
.261
45~4 Shaft nut, 30 spline 500-600 6000-7200
.225 8-1814
46
Outer blade clamp bolt 65 780
~C,--20
Inner blade clamp socket 40 480
10152-5’/1 Blade ~--20 screw

65 780
~C6--20 Counterweight socket screw

8 3.870 2.890 45-50 540-600

%-20 A-304 link screw
12 4.825 1.610
Socket at end of guide rods 10 120
18 .393 .452~c% 5.500 1.120 31~--24 screw

~"’5.816 .800 100-200 1200-2400

24 21LZ 24.7 .088 A-i 8~tF´•FPlup 4~
30 2EL5 Set 20.5 5.982 .580 d-886SrlNuf-bt~Ha brpifitlrj 75-100 800-1200
36 17~0 -.178 5.655 .430 4 48
.330 1/4-28 834-7, Guide collar unit
62 ~L.357 -.293 4.418
.315
43~1 Parts to be checked for Slip
.285
44~2
.247
as~ BIQde Blode mounted in blode clemp 167 2000
46W .208

ALL """:!I-S
Tu,\,,l.l,r BASED
Ol\j NOr´•I-LL;~;(; 17,~’1’,:1 ij-I;Z-ADS..
TOLERA12iC~ Is lo~o
-6- U~ILESS U7-1IERWIS~ S7~ATED,
 SECTION V S.Stroma LT-I (2-815 Grease!
Union Oil Co. of California.
LUF3RICATION
6, Lubriplate 630 AA
FisE;e Urothers, Toledo, Ohio.
A. General Properties of Grease Required, This grease will bleed oil in Ilot weatl~er. It is
Any ~rease used have the recommended only for lubrication of the blade
must following´• properties: pilot
tubes; but not the blade bearings.
(a) Waterproof.
7, KPM Aviation Grease No. 1
Temperature range bet~ecn --150 F and Standard Oil Co. of California.
~j00 F; or --400 to 100" F if operation is in
8. Lubriplate 707
cold climate.
Fiske Rrothers, Toledo, Ohio.
(c) Freedom from separating oil from SOap base
g,
due to centrifugal force or high temperature, h4obilgrease Aero Lo-f-Ii PD-535-K
Socony Vacuum Oil Co.
(d) Low friction. 10, No. 84 Medium Grease
Keystone Lubricating Co.
B. List of PLppraved Z;rease, by Spec. or Name, Il, Te?taco Regal Starfax Special
rrs~ag ~c,
12 Molub-Alloy No. 2 Grease --100 F.
a. Stroma llr-1 (Z-BO1 Grease) b6 No. I Grease -250 F.
Union Oil Co. of California. Imperial Oil Grease Co.
Los Angeles, California.
3, Gulflex A.
13. Germany Cal~psol W729
This grease is recommended for the blade ball bear-
German Calypsol Company, Dusseldorf.
ings as it will not bleed oil in hot weather.
4, RPM Aviation Grease No. 2 G. h~oper times and amounts of
grease are
Standard Oil Co. of California. mentioned during assembly prqcedures.

SECTION VI SERVICE TROUBLES REMEDIES

?rouble Probable Cause Remedy

FPtlLURE if rpm foils to increase but will Set relief valve in governor to provide necessary pressure, to 300
up
OF PITCH reduce: Low oil pressure. psi with 50 psi engine pressure, no flow.
70 CHANGE
If rpm change in both directions See "Excessive Friction in Hub Mechanism," below. Isolate friction
is Iluggish: Excessive friction in in each blade by uncoupling piston and testing each blade
hub mechanism. separately, before tearing propeller down.
Newly-installed governor has Check and correct.
wrong direction of rotation, or
has by-pass plug in wrong hole.

R´•985-148 engines only-- install A-1834 plug (or equivalent) with PRP-902-15 "0" ring.
The crankshoft plug A-1834
may be loose or not present.

EXCESSIYE WltCIION Pitot tube has slipped out s)ight´• Tear down and check distance pilot tube extends from hub spider.
IN HUB MFCMANIS~ ly and is rubbing hard ogains( Should be 33/4 inches. ´•If more, remove pilot tube and replace with
end. of hole in blade. a tube .002 in. oversize at hub end.

Blade bushing seized on pilot Polish pilot tube and blade bushing with fine emery paper and
tube. reassemble.

Blade ball bearings unusually Replace bearing.

rough or chipped.
Friction in various
moving parts Check parts individually. If tightness is encountered in sliding
parts,
of Ditch control mechanism, increase clea’ronces slightly. Apply oil externally to moving parts.

1MPROPER RPM Static rpm too low. Governor has high rpm stop, as well as propeller low pitch stop.
Either the governor or the propeller stop-may limit maximum
rpm.
To determine which is causing trouble, open the throttle and move
governor control back and forth slowly.
If maximum rpm is reached BEFORE governor stop is reached
propeller stop is probably limiting the rpm. if this is the case,
loosen blade clamp outer bolts and rotate blader in clamps.
Reduce blade angle aboutlo for each 100 rpm increase. (10
equals inch circumference at blade root.)
If maximum rpm is reached AT SAME TIME as governor stop is
reached,governor stop is probably limiting the maximum rpm.
Reodjustgovernor stop to obtain proper rpm. One turn of
governor stop screw equals about 17 rpm. Turn stop screw Out
to increase rpm.

Governor stop should limit high rpm, with propeller stop reached at
50 to 100 rpm beyond. This allows for variations in engine power
without affecting maximum rpm.

-7-
Trouble Probable Cause I Remedy

Static rpm too high. Reduce by screwing governor stop in, one turn for each 17 rpm
reduction.

FAILURE TO I´• Governor control does not pro- I Provide sufficient travel in governor control. Governor must drain
FEATHER I vide enough travel to allow oil out of propeller during feathering.
governor to move hard against
high pitch stop.

Excessive friction. See "Excessive Friction in Hub Mechanism."

High pitch stop pin fails to slide Check for burrs on pins. Check for stiffness of spring. If propeller
out at feathering rpm. feathers at high rpm’s but fails to feather at low rpm’s, too-stiff
spring is indicated. Reduce length of spring by one or two turns.
Weak or broken feathering Replace.
spring.
SURGING (WIIen gove,´•nor Air trapped in propeller adwat- Provision should be incorporated in engine to allow trapped air to
control is changed rapidly ing piston or in engine shaft, escape from system during one-half of the pitch change cycle. Ex-
or rough air is ercise propeller by changing pitch or feathering before each flight.
encountered.) is the
Governor pressure too low. Adiust governor relief pressure so that rate of pitch change
some in both directions.

Excessive friction in pitch be "Excessive Friction in Hub Mechanism."

change mechanism.

Governor lacks sufficient Change stiffer speeder spring. This gives governor more stability,
to
dampening, but makes pitch control more sensitive, which may, in turn require
re-rigging of control to offset higher spring rate. Changing to
stiffer speeder spring should be done only after all other factors
are checked and corrected.

011 LEAKAGE Faulty "O" ring seals follows: as Disassemble and inspect "O" rings and the surfaces they seel. Re-
Front of between
rear cone place "O" rings if defective. Replace cylinder if surface is scratched
engine shaft and hub, or nicked in area where "O" ring slides. Use gasket compound
Between hub and cylinder. on cylinder threads when replacing. Peen down raised places
Between piston and cylinder caused by tightening of cylinder with bar.
at front of piston.

GREASE LEAKAGE Grease leaks past clamp seal Loosen clamp bolts and replace gaskets. Standard thickness of
IOnly source of gaskets. gasket is .050, but .060 gaskets are available in case .050 gaskets
grease leakage is ore not compressed sufficiently to hold.
bkde hearings.)
Grease leaks from between Inscribe blade with ink or pencil to assure correct blade angle on
blade and clamp. reassembly, and remove blade and clamp. Add gasket compound
in radius of blade butt. Replace blade and clamp.
END PLAY Buildup of manufacturing I Total end play of .060 is permissible.
1N BLADES tolerances.

BLADE TRACK I I Tolerance of t/s inch is allowed.

B1ADE FIT ON With manvfacturing tolerances, the maximum that the blade tip
Hwe PILOT TUBE I 1 con be moved fore and aft is .068, without grease in blade clamps

and bearings. With grease, the movement is nil. If blade tip

fore-and-aft movement increases to .100 dry, blade requires factory
re-bushing.

lI FaARTI~

SECTION I

INTRODUCTION

The first column in each parts list is the figure and If you do not know the part number, you may refer

index number. This ref~l´•s to tile illustration and in~ex to the applicable illustr´•ation and then find the intles
numbcf of ench part. For exalnple, if you are ordering number assigned to it (18). Look in tile parts listing,
a blade clamp assembly and want to see how and \vhete and read the part n~unbcr, 838-28.
it locates os the Scncral asselnbly, this column indicates
Figure 2, index number 18. Looking at Figul´•e 2 in the

group assenlbty Parts List, inde?r n~mlbel´• 18? the appcar-

HOW TO ORDER
ance and location of the clamp asselnbly nlay be easily

found, alsa the details of all parts contained in this suh- It is importarlt thrtt the Part Nulnbcr. Pal´•t i\Tanle

assembly, and Model Numbel´• be Si\lcn when oldcling parts.

-8-
 SECTION II

GROUP ASSEMBLV PARTS LIST

Model HC-83r30-2E

INOTE: Parts s9c~rked not to be removed from svh-assembly)

Code No. I Part No.

Description No. Req’d.

1 :I I Blade ._..._~_..
a

2 ’f 8-1818 I HUB SPIDER ASSEMBLY 1

3 9 C-1853 Hub Spider 1
4* A-1308 Pilot Tube 3
......~..._

5* A-1817 Bushing 1

ASSOCIATED PARTS
6 :1 A-1812 Rear tone 1
7 8-1814 Hub Nut ......_..__
1
8 A-1813 Puller Ring 1
9 PRP-909-13 "O" Ring, Cylinder 1
10 8´•1 803-1 Cylinder 1
11 PRP-909-9 "O" Ring, Shaft Cone i
12 A-1851 Blade Bearing 3
13 A-i 852 Ring, Guide 3
14 PRP-909-7 "O" Ring, Blade tree note "A") 3
IS Wire Ring, Bearing 3
16 1 A-t855 Wire Ri~gl Guide Retainer 3
17 A-1848 lock Ring I 1

18 ii 838´•28 CLAMP ASS CMBLY 1 3

19 :1 c-1301 Clamp 3
20* A-30´•1 Link Screw 3
21’ A-285 Staking Pin 3
22 5010 Zerk Fitting 6
23 A-1306 Clamp Gasket 6
24 A-282 Socket 1 6
25 1 tCd--2O x 2j~B Mounting Bolt, (Ferry Screw) 6
26 AN363-720HT Mounting Nut 6
27 833-14 Counterweight Assembly 3
28 316--20 x 3/4 Counterweight Screw 6
29* A-65 Staking Pin 1 3

ASSOCIATED PARTS, BLADE CLAMPS

30 ’1 A-i 305 Weights, Balance as req’d.
31 AN501-A110-6 Screws, Weight 6
32 A-881 Plate, Stop 3
53 AN3H-2A Screws, Plate 1 6
34 ‘1 A´•944 Bushing, Link Screw .._....
3
35 AN380-3-3 Cotter Pin, Bushing 3
36

37 d 431-12 I FEATHERING SPRING SUB-ASSEMBLY 1

38 1 8-868-2A 1 Pilot Tube I 1
39 1 A-867 Split Ring 1
40 1 A-i 829 Retainer Ring 1
41 8-1826 Outer Spring I 1
42 8-1825 Middle Spring 1
43 g 8-1824 1 Inner Spring 1
44 1 A-1827 Spring Retainer I 1
45 AN501-A10-12 Stop Screw 1 4
Not Shown A-1849 1 Sleeve, Spring --.---i--------------------------- f 1
ASSOCIATED PARTS
46 A-880-1 I Flexlock Nut I 1
47 d PRP-91 4-8 1 "O" Ring, Nut I 1

48 a 8-1368-3 PISTON JACX UNIT 1

49 ´•1 C-l 802 1 Piston
54 1 C-1802 I Det. i, Piston ........._.____
I
St* 1 A-862-1 Bushing 1
52’ 1 A-817-2 Guide Rod 1 3
53’ 1 A-114-8 I Staking Pin 1 3
54’ ii A-946 1 Bushing, Pin 3
55 i A-1464 I Link Pin Unit 1 3
56 d AN501-A10-6 I Safety Screw 1 3
57 ;1 A-i 444 Washer i 3
58 II AN316-5R I Jam Nut 3
59 1 f(b--24 x Socket Head Screw 3
60 1 A-861-3 1 Link Arm 1 3

-9-
 SECTION II

GROUP ASSEMBLY PARTS LIST (con-t.)

Model HC-B3Z30-2E

AjSOCIATED PARTS

61 r PRP-9(12-50 "O" Ring, Piston 1

62 1 A-863 Felt Seal, Piston 1

63 1 8367A I GUIDE COLLAR UNIT I i

64 8-1836-1 1 Guide Collar I 1

65* 1 A-116-D Plastic Bushing 1 3
66’ 1 A-114-D Sicking Pin 1 3
67 1 %-28 x 1% I Socket Screw I 1

68 1 836-168 1 SPi NN ER ASSEMBLY I 1

69 1 C-1872 1 Dome I 1
70 1 AN526C-1032-R8 i Screw 1 24
71 1 D-1870R I Bulkhead with Stops I 1
72 1 01821-6 1 Bulkhead I 1
73’ 1 A-894-1 1 Pins 1 3
74 1 830-8 1 Auto High Stop Unit 1 3
75 1 B-1 353 1 Bracket 1 3
76 1 A-883 1 Pin 1 3
77 1 A-844 1 Spring 1 3
78 1 AN380-3-3 I Cotter Pin 1 3
79 1 AN4H-15A I Hex 8011 1 6
80 1 A-i 865 Washer, Plastic (~21) thick) 6
81 1 A-i 864 Washer, Plastic (~C611 thick) 6
82 1 AN960-10 I Washer 1 6
83 AN-364-1032 I Flexlock Nut 1 6

84 1 836´•178 SPINNER ASSEMBLY, ANTI-ICING I 1

69 1 C-1872 1 Dome I 1
70 1 AN526C-1032-R8 I Screws 1 24
85 I D-1871R 1 Bulkhead with Stops and Slinger Ring I 1
72 1 0-1821´•7 1 Bulkhead I 1
73’ 1 A-894-1 1 Pins 1 3
76 1 830-8 1 Auto High Stop Unit 3
75 1 B-l 353 1 Bracket 1 3
76 1 A-883 1 Pin 1 3
771 A-884 1 Spring 1 3
78 1 AN380-3-3 I Colter Pin 1 3
79 1 AN4H-15A I Hex Bolt 1 6
so 1 A-1865 1 Washer, Plastic (%2~’ thick) 1 6
81 1 A-1 864 Washer, Plastic [~b" thick) 1 6
82 1 AN960-10 I Washer 1 6
83 1 AN364-1032 I Flexlock Nut 1 6
86 1 C-2128 1 Anti-icing Ring Nut 1
87 1 AN526C-1032-R8 I Screw 1 6
88 f AN960-10 I Washer 1 6
89 1 AN363-1032 I Flexlock Nut 1 6
90 I A-1 866 1 Hose 1 3
91 1 &2149 1 Travel Tube Unit 1 3
92 632 x% Slotted flat head screws 1 6
93 1 AN365-632 Elastic Self-Locking Nuts 6

SPECIAL ENGINE SHAFT PARTS

94 r PRP-902´•15 I "O" Ring, Shaft Plug I 1

95 1 A-1834 1 Shaft Plug 1
Installed in R-9s5-148 Engines Only

NOTE"A"~ For Propeller serial number IOON to T29N, and also 131-N, PRP-914-45 "O" ring was

used because the mating chomfer on the bearing (12) was smell. If new bearings are

ins~alled, use PRP-909-7 "O" ring as listed.

-10-
 26

31

28
22P 27
18
~c---- 29
16- Pi

19
II
13 ,I
94 23

1)\
´•s~ :´•~´•d
PI IS PI
25
20, 1 -o,
a

15

p 24\ab~ ,2

81 73,’
i-~1

4\
‘´•d61 31

54
,5

60 u,p,
P
n
9

(P nd
i
I 11 Il n
s)l ;V/O

I76cdU/fl
3
177 1
40 T
14 12
86 78 gj,l B
51
’,175 i, 49 5\4\ 46 70
n~
P 37 42 cu

/4,-..-1’´• 80

~66\\
13

4B
69 1 C~
7
67 e~ 65
I
IS
72 72 17
73 38

88jq
89
93 169
84J70 181
185 74BJ ´•;I8J74
79
80

82
79
80
81
82
63
65 1J P

10
47

91
C 92
86
87
88

90
 III

GOVERNOR MODIFICATION FOR USE ON

P. W. R-985 ENGINES.

In FigJre III is shown a Hamilton-Standard So~´•er- (b) Replace speeder spring with Hartzell Part A-259.
nor Model 1A2G5 modified for use ivith the Hartzell
(cf Adjust spacer length to So\.ern down to 1500 +j0
HC-B3Z30-2E propeller when installed on the P S~ W
1Z~PM andbypass at 1300 to 1´•100 KPh´•I.
K-985 engine. This modification consists of the following:
(d) Set plliley stop for 2350 KP~VI.
(a) Replace pressure relief valve spring with Har´•tzell
Part A-308. This should provide 300 410 psi pressure Install Hartzell P~arne Plate.
(e)
with 50 psi enSihe pressure. No flow condition.
Part C-3

CAUT1ON Serial
MODIFIED BY
(Nome) (Address)
Do not add washers to any springs to increase

as the resulting pressure may be exces- NOTE: Gove?nor oaerknul should be done onlll by
pressure,
sive when the oil is cold. Excessive pressu´•e may governor specialists aeco~rding to establisl~ed
rupture the propeller piston, standards.

Two full threads

Adjvst spacer length for

governing to 1500 "30
and bypass at 1300 to
400 R.P.M.

Replace speeder spring

with HARTZELL A-259
Set stop for 2350 R.P.M.

Replace pressure relief valve

spring with HARTZELL A-308
HARTZ~LL PROP, INC ~rlTZLLL PRO~
lo""T
INC

Spring for 300 f 10 PSI Max,

with a 50 PSI oil suppfy.

o o

permitted
O
NOTE: Washers are not
ender spring,

o o

Modification of 1A2G5 Governor to HARTZELL C-3

FIG. 3
Use on R-985 engines with HC-B3Z30 propeller.

-iz-
 February 20, 1963´•
NC. i

OVERHAUL MANUAL 108A

~DELS HCIB3Z30i2E and HC-B3W30-2E

INTRODUCTION: The. MC1B3W30-2E propeller is identical to the

~tC-B3230-2E inodel except far the installation
of needle bearings in the blade shanks. ~nual
r08A, therefore, is applicable in all respects
except for the slightly rnodifled parts lists.
#o special tools are required for the earlier
rooctel,

PA’fETS LIST DIFFERENCES: HUB ASSEMBLIES

HC-B3Z30-2E ~ICLB3W30-2E

84Q-34EIub Spider Unit 840-74 Hub Spider Unit

A11308 Pilot Tube A-L884 Pilot Tube
C-1853 Hub Spider C-1853 Hub Spider
A11817 Bushing A-1817 Bushing

BLADE ASSEMBLIES

L0152-~S W10152-5~
10160-6 w10160-6

"i"" Shank Incorporates "tJ" Shank Incorporates

A-1309 Bushing A-1347 Bushing

A-1349 Spacer

Torrington Needle Bearings

JH-2216
BH-2216 (optional)

WEAR TOLERANCES The wear tolerances listed in Section IV,

Table II are applicable for the corresponding
parts in the "W" shank propeller assembly.
All overhaul procedures are identical for
both propellers. Replacement of the needle
bearings at overhaul is not considered
necessary.
 NO, 2 1/14/69
OVERHAUL 108A

propeller Model EiC-B3P30-1 (non-feathering)

The HC-B3P30-1 propeller is identical to the HC,B3P3012E

6XC ept:

831-12 Eeathe´•Ping spring assembly of the -2E model is

mod´•lfied to 831-12B by add´•lng an A-1869 spacer to make
the~ -1 model,

See Parts List dated ~arch 10, 1967,

dverhaulpr0cedures are to those for HC-B3P30-2E

propellers,
 HARTZEEL PROr)ELLER, TNC´• Appuoved March 10, 1967

Assembly
PTQUA,
PARTS OHZOLIS1C By
PROPELLER MODEL David Biexmann
Drawing 6 Gen. Manaaer
NC-B3P30-2E Vice Pres.
D-1860
i~twnber Re re

Change
Let~ert Part ffuniber Nomenclature

SPIDER UNLT
1
c 1 840-34 HUB
1
Z Clr853 Hub Spider
3
N A-T308 Pilot Tubes
1
F A- 1817 ]Bushing

HUB ASSOCIATED PARTS

3
N A-1851 split Bearing, Blade
3
B A-1877 Bearing Retention King
3
J A-1889 Ball Spacer, Bearing
3
A A-1852 Guide Ring, Bearing,
3
A A-1854 Wire Ring, Guide Retention
3
PRP-909-10 1’6" Ring, Blade
H 1 A1183-2i1 Rear Cone
Shaft: I
PRP-904)-9 "O" Ring,
Shaft 1
PRP-914-41 I"O" Ring,
C B11894 shaft Nut
1
A-1848 Safety Pin

t 838-72 i CLAMP 6 COUMIERWEIGHT ASS’Y

C Ci1977 1 Clamp
10 A-304 Linkscrew
3
D A-285 Staking Pin, Linkscuew
3
833-14 Counterweight Unit
6
F A-fk036-32 Socket Head Cap Screws,Ctwt.
6
D A-285 Staking Pins, Sk.Hd.Cap Scs.
3
A I A-tiS Staking Pin, Counrerweight
MS15001-1 Izerk Fittings
1 Al 13´•0 6.- 1 Clamp Gaskets
6
J A-282 Socket Sdrews, Clamp
6
AN380- 3- 2 Cotter Pins, Socket Screws
6
c I ’A-137 2 Clamp Bolts, 12 Point
D A-W73 Clamp Nuts
Mo. 3 Lubricaps

CZI~AMP ASSOCIATED PARTS

As Needed
B IA11305 Balance Weight~s
AN50LA10-( Weight: Screws

i A-881 IStop Plates

A-2016 Plate Screws
A-944 Sleeve, Linkscxew
3
AN380-3-3 ICotter Pin, Sleeve

_
.;"O" D o~n. Page 1 of 4
It. L1
 HARTZELL PROPF,~LER, INC. March 10, 1967
Approved
P3CQUA, OHIO
Assembly PARTS LTST By
Drawing PROPELLER ~ODEL David Biewmann
D-1860 HC-B3P30-2E Vice Pres, Gen, Man&.,r
Number Reauire

Change
Ilet~ter Part Number I Nomenclature

O 834-7A. 1 GUIDE COLLAR UNIT 1

kA B11836- 1 Guide Collar 1
E A-1I~B-I Plastic Bushings 3
L A-P~4-2 Staking ]P~n 1
B A-2038114 NylockSocket Head Screw(
Cap 1

831-12 Feathering Spring Assembly 1

Af B-8~8A-2 Pilot Tube 1
T A-1827 Spring.RetEliner Cup 1
E A-f849 Spacer Tube 1
A 11-1824 Spring,Inner 1
B B-P825 Spring, Middle, 1
C B-1826 Spring, Outer 1
´•A A-1829 Spring Retainer 1
1 A-8~7 Split Retainer, Rear I 1

O B11368-3 PISTON ASSEMBLY 1

W 0-1802 Piston Unit 1
k C-1802 Det,nl Piston I
Q A1862-1 Plastic Bushing 1
Q A--8rf-2 1 Guide Rods 3
L A-114-B Sta~ing Pins, Rod. 3
F A-946 Bronz~ Bushings 6
C A-2031 Socket Head Cap Screws 3
AN316-38 Checle Nuts 3
B A-P444 Washers ´•3
D A13~464 L~nk Pin Units 3
APCSaZA1016 Safety Screws 3
Y A-861-3 Zink Arms 3

HYDRAUL~TC ASSOCIATED PARTS

O I B-18Q3-1; I Cylinder 1
~RP-909-13 "O"~Ring, Cylinder 1 I
AN503Af0-6 Featherfng Stop Screws 4
PRP-SbL4-8 "Q" Ring, Pilot Tube I 1
"O" Ring, Piston 1
n B-1843 Dust Seal 1
F A1880- ~L FlexZock Nut, Piston I 1

Page 2 of 4
 March 10, 1967
HARTZEL;L PROPELLERI INC. Approved
PIQUA, 0)110

Assembly PA~ifS I;TST By

Da id Biermznn
i)rawing PROPELLEB MODEL
Vice Pres. Gen. Mana2ler
D-1860 HC-B3P30-2E
Mwnber Re~

Change
Letter Part.NumbeT 1
1
836-16SPR SPLNNE;R ASSEMBLY
1
H C-L872P Dome, Spinner (Polished)
24
AN526C1032R8 Screws, Dome Mounting
1
M D-1870R Bulkhead Assembly
1
M D-L870L1R Bulkhead Unit
3
830-ire Auto High Pitch Stop Units
3
T B-1353-1 Bracket
E A-883 Pin
3
E A-884 Spring
Washer 3
AN936A10
3
AN380-3-3 Cotter Pin
6
AN4-16A Hex Head Bolts
6
A-1865 Plastic Washers (Thin)
(Thick) 6
A-1864 i Plastic Washers
AN9 6 O1 416 Washe.r s
6
HLO-~ Kaylock Nuts

1
836-27SPR ANTI-ICIfSG SPINNER ASSEMBLY
1
H C-1872P Dome, Spinner (Polished)
24
AN5 26 0103 2RS Screws, Dome Mo~nting
1
Q Anti-icing Bulkhead Assembly
1
Q D-1871-1R Bulkhead Unit
3
830-ire Auto High Pitch Stop Units
T 1 B11353-1 Bracket
i
E 1 A-883 IPin
E 1 A-884 ~Spring
AN936A10 Washer
3
AN380i3-3 Cotter Pin
1
A A-21fi7 Anti-icing K~t
i
H C-2128 Slinger Ring Unit
6
AN52~Cf032R91 Screws, Ring Mounting
6
AN9 6’0- 10 Washers, Ring Mounting
6
H10-3. fl(aylock Nuts, Ring Mounting
A A-1866 Hose
3
H B12149 Travel Tube Unirs
Slotted Flat Head Screws
6
632 x.~’! 6
~3365-632: Elastic Nuts, Tube Mounting
6
ANLc-1GA Hex Head Bolts
6
A-1865 Plastic Washers (Thin)
(ThFck) 6
A-1864 Plastic Washers
AN9 60- 416 IWashers
H10-4 IRaylock Nuts

Page3 of4
 HARTZELL PROPELLER, INC. Approved March lij, 1P~7
PTQUA, OHXO
Ass emb ly PARTS LIST
Drawing PROPELLER MODEL David Biermann
D12860 HC-B3P30-2E Vice Pres. Gen, Mana
NuI~nberneauired

Change
Letterl Part: Number Nomenclature

c-3 KARTZETJL GOVERNOR I 1

0-3 ICTT I GOVERNOR KIT I

210,XXX WOODWARD GOVERNOR 1 1

NOTE= kll’Prdtt Whitney. R-985-14B Engine~s

must be pi in of the
one following
methods;

1. Modi~y orliginaT~ plug as shown in

drawing I D-1860.

2. Remove orfiginal plug and install

Hartzell 1PLug;
I ‘lA’1334 Plug (1 15/16 -16 Thr~ads)
or

1 lh-1834c1 Plug (i 3/4 -16 Thrkads)

Page 4 o% 4
 SUPPLEMEMI NO´• 3 1/14/69

O’VERHAZUL MANUAL 108A

Propeller Model HA-B~PSO-TB

Gro~nd Adgust~ble Fkxed Pitch

is essentially the asthe

ThS~s propeller same
unit is locked in one
Eeatbering version except the hydraulic
the ground by adjusting
position. The pitch may be adjusted
on

a screw which protrudes from the front of the piston.

those given for Model

Overhaul procedures:are identical to

HC-B3P30- 2E.

A parts list Is provided herewith.

 ~ssembly PARTS TL~IST
-Y

Drawins FROPEI;LER blODEL

1)-1940~ HAIIS3P30-1~I3, HA-B3Z30-1B Vice E~res. h C-cn.
FAA-DOI\-3Eh APPROVED I l~csuired

’Chsc~cl i Ilp)~ 1)211

Letter Part N~ynbcr ’1Nomenclature

P I 8CtO~3L, ’)NUi3 SPIDER UNIT I 1 I 1

hA 1 C11853 i Hub Spider I 1 I I
n t ´•A1130S Pilot; Tubes 1 3: 1 3
z: ~1--; ,4-1817 1 Bushing I 1 I 1´•

HUB ASSOCXATED PARTS

a.; 1 11-1851 1 Split Bearing 1 3 1 3
B f A-I877 1 Wire Ring, Bearing Retention) 3 1 3
1, 1~-7-889 1 Ball Spacer (Optional) i 3 1 3
A r 1",-1852 1 Guide Ring, Bearing 1 3 1 3
A Wire Ring,’ Guide Retention 3 3
I>Rp-909-10 ’’O" Ring, Blade i s~ 1 3
P~P1914-41´• I "o" Ring, Shaft (Optionttl) 1 I I

P~P-S)09-9 i "C" Ring, Shaft (Optional) 1; I I

B:‘´•1~-1322-1 lRear Cone (W~th Spinner) 1 .1
I,rl-1856 IRear Cone (W/O Spinner) 1´•~ 1 I
PRP-902-15 I I "O" Ring, Shaft Plug i 1 1! I 1
~1857 i shaft Plug(l 15/r6~16 Thd) 1’ I 1
or

1~11857-1 Shaft: Plug(l 3/4 16 Thd) 1´•I I 1

.’D 11B-1;894´• I Shaft Nut I I I
B 1 A-18´•L~8. i Safety Pin I 1 t 1

A 1 Q38-73 .ICZAMP 4 COUNTERWEIGtrr ASS’Y i. 3

´•J 3’.. ~C-1977 1 Clamp ,3
L´• 1 A-304 Ilinltscretr ;i 3
D g A-285 IStaIt´•Lng Pin, Linkscrew 1 .’;´•3
E I B-1311 I Counterwcight 1 3
´•F f A- 2036-30 1 Socket IIead Cap Screws,Ctwt. I 6
I) i ~k A-285 IStakfng Pins, Sk,Hd,Cap Scs,l 6
D 1 k-65 IStaking Pin, Counterweight I 3
P"S15001-1’~ )2crk Fittings ´•I:. 6
Z A-l306-I IClamD Gaskets 1 6
j A-282 ISodEEt Screws, Clamp 1 6

C
i ~380-3-2
A-I372
Cotter Pins,
ClanD Bolts, 12
Socke-t Screw
Pbint
6
6
D t i.- A11373 Clamp Nuts 6
No, 3 Lubr:ic np s I G

CLAEIP ASSOCIATED PARTS

.~A-1JOS IBalance~ Weights As Needed As Needed
IWeisbt Screvs 1 G 1 6
B´• ]X-944 jSlcevc, Linkscrcw 1´• 3 1 3
~3 80- 3- 3 Pin, Sleeve 1 3 1 _.3
sN~: Optionai,use AN360-3-2 Goyter Pins. I Pap,e 1 of~
 AssernSLy I´•IST f3Y
Drar~ing PROPELLER ~IODEL 1 i3avic: Biermann
D-1S)40 WA-B3P30-1B, IZA-E3230-1B Vice Pres. Gen.
FAPi-DOA-3EA APPROVED 1 Nu;ns er ne quir~ed

c~oncei I I´•
I ()pll 112(1
Lctterl Part Wumber I Nomenclature
031c´•16 I GOLDE: CO1L~AR UN’IIT I 1´• t 1
~A I B:113g-4 IGuide Collar I 1 f 1
E f AI1SSDIL Plastic nush~ngs 3 1 3
Stalring Pin I i
S f lF-2038-lrj 1 Socket Head Cap Scxewl L i 1

Q 1 8-L36Ecl PISTON ASSEEIBLY I 1 I 1’

S I C- 181 i Piston unit 1 1 I 1
S. f 6-1816 Det;,~l Piston I 1 I 1
a I 1~-8Q2 fPlastic Pushing I 1 1
q 1 A-817-2- 1 Guide Rods 1 3 1 3
J t ~-lr4-P1´• StarcLng Pins, Guide Rods 1 3~ 1 3
A-944 IBronze Bush´•Lngs I 8 1 d
6- f ~-203:7 ~Eidctcet Head Cap Screws 1 3 t 3
AZT318-38 fCheck Nuts 1 3 3
W~shers 3 3
]D f ~ink; Pin Un~ts 3 i 3
Safety Screws 31 3
A-86´•1-3 Arms 1 3 3

i IPitch AdJustment Assembly I 1 I 1

~-1943 fEiushuoom I 1 I 1
3/3-´• 24 x ’1~2" Socfcet: Set: Screws ’1 2 1 2
h~ 11)41 jRBlainer i 1 1
E-I 3 IFlcxloc~ Nut; i 1 I 1
1 IPllor: Tube I 1 I 1

i I´•ZYDII~ULIC ASSOCIATED PARTS

~-S54 Cylfndcr I 1 z
"O" Ring, Cylfnde’r 1 I
1~-$59 Split Retainer, Front:
Flare, ~ushroom
I.
1
I
1L I
I ~SO1ALOL 10 1Screws, Plate
"O" Ring, Pilot T~ibe
I 8 8
i
J"O":Ring, Piston 1 1 I I
Ii tn~ 3 IDuSt Seaf, Piston I 1 1
yn-8~s-1 lFlcx’oock Nut, Piston I 1 1 1

,I la3- ~ss JSPkNNER (No Stops) I

ASSE~BLY 1 I 1´•
Irt I C- 1872 IDomc, Spinner (No´•t: Polished) 1 I
hN5~C1032R8 1Screws, Dome Mount´•finZ 1 24 1 24
.rI.3 E)-2870~:1R iBulkhead unit (No Stops) I 1 1

P-c--- _.7 .9
 HARTZELL PnOPELLER, INC, Approved November 11., 1958
PTQUA, OHIO
Assembly PARTS L3[ST By
PROPELZ~ER MOD&L i]ovid GiermJnn
3rnwins
.0-1940 ~IA-B3P30-18, HA-D3Z30-1B ViccPrcs. Gen.

FhA-DOA-EA3 APPROVED lie izco

11211
Chacgel’ 1 Ilplt
%etcer! Fart Number Noncnclature

AEE t 538-50 i CISI~IP 6r COUMTERWEZGKT ASS’Y 1 3

AN1380-3-2 Cotter Pins 1 6
3 A- 282 t Socket Screws, Clamp I r 6
i A-304 I l;inkscrew I 1 3
11 I h- 285 I Staking Pin, Linkscrew I 1 3
E: t Countcrweight Unit I I 3
f ´•knr2Q5 Stziking Pins, Sk, M),CapSc 6
F 1 A12036-30 i Socket Need Screws 6

I- t A-1306 Gaskets I 6
~S1500L-1 F´•Lttings 6
Zerl~ 6

I
A-1373 ClamI~ Nuts
h-1372 C1~ Bolts 6.
O
3
~s CIL301 Cl(unp
D A-6r Stnk~ng fin, 3

il~. 3 ’Lubricaps 6

Use A-1855 Spac~rs as required ~or spinner a8sembly.

05
i
HANDBOOK
I-i

B
Ir

51

8:"~

x:,

:1

2 BLADE, CONSTANT
SPEED AND FEATHERING

D.O.A.-F.A.A. Approved

~Op
;-~a..´•
ER, INC.
;;’´•’:i

i´•:

:I I

;´•-´•’te‘´•P~
-:i::Mclnuol 109A
It:´• i;-:-.; i,´•’M’:´•-´•
;~a
 RECORD OF REVISIONS

´•C8~´•
MFG REV
NO DESCRIPTION ISSUE DATE ATP REV DATEI INSERTED BY
 RECORD OF TEMPORARY REVISIONS

ATP REV INSERT DATE REV REMOVE

TEMP
ISSUE DATE DATE BY REMOVED INCOR BY
REV NO DESCRIPTION
 TAE?LE OF CONTENTS
IP~FQ)T II INSTRUCTI~NS

Sec.tion I 1

Description of propeller operation 1

Section II Over´•haul Instructions

Special Tools Table I 1

A-i. Removal of Propeller from Engine HC-A2XF-2 2

A-2. Removal of Propeller from Engine

HC-A~XK and HC-A2XL 2

B. Disassembly of Propeller 2

C. Cleaning 3

P). Inspection ........._.._.._

3

X~, Repair and Replacement 3

F. Assembly 3

Section III Balance 5

Section Wear Tolerances 6

Huh Table II Wearing Surfaces 6

Blade Table III Repair Tolerances 6

Table I~! Torque Values 6

Section V List of ApP’oved Greases 7

Section VT Service Troubles and ReInedies 7

PBR~ II PAR’rrS LI~T

Section I Introduction ........._ ........._

8

Section II Group Assembly Parts List

Models HC-AZXF, K and L-2 9

Sectioal III Parts List 12

Parts List Differen~iating between

I1[C-A2XF-2 aiid I-1C-82XF-2B ........._...
12

Parts List Differenriating betwc~pn

HC-h2XF-2 and HC-X2XF-2A 12

ArOTEa InstalEation, OpcraCiorL rtnd General St´•rvice are subjects which

ul´•e covr:1´•ed in thr! Hartzell "0zc:szer’a Propeller Manlull,"

JUNE (O~(
 PART COVERHAUL

SECTION

DESCRIPTION Centrifugal stops prevent feathering of the propel-

ler, to the action of the spring, when the engine is
due

The HC-A2X( )-2 Propeller is a P-blade constant itopped At speeds of over 500 RPM, the stops are
rcmoucd by centrifugal for-cc, allowing the propeller to
speed andfeathering propeller designed for engines in
the 150 to300 H.P, class having "F,~’ or "L" type be feathered at any time.

mounting silafts. The "F" ilange olilhei six

Ilange Unfeathering is acconlplirherl by any of several
ih-inch bolts on a Cinch bolt circle plun two %-inch ,,,,thods as follows:
dowel pin.. The "K" flange otilires six %-inch bolts
on a 4Ya-inch bolt circle. Tile "L" flange otilizei six (a) Restarting the engine will provide oil pressure to
bolts 43/n-inch bolt circle. unieather the propeller.
7/L6-inch on a

(b) An oil-air accumulator, sealed by a valve when the

The HC-APX series propellers supersede the earlier
propeller is feathered, can be utiii,ed to provide pressure
HC-82X models. The HC-ASX series ulilhe split type I,, anieathering
blade retention bearings, together with a modified hub oil pump can be used
A, electric operated to poolp
spider; whereas, the HC-82X series propellers utilbed ~il hack into tile propeller for unfeatherjng.
solid blade bearings retained by split rings. This change
was made in order to stiffen the hub and tlicreby SECTION II
achieve greater smoothness. OVERHAUL INSTRUCTIONS
The differences in the parts lists of the IIC-A1XP-P Table I. SPECIAL OVERHAUL TOOLS
and HC-82X1;-2B are given in Part II, Section III
P.nNo. Nom´•nllotun
Thin propeller is designed to be controlled
by a Sou- 8´•842´•1 Wrench for A´•880-2 Nut on Spring Auembly
cmol´• mounted on the engine supplying engine oil
C-845 Fixture for Assembly of Feothering Spring
through the propeller shaft. Gpvcmoloil i,ressure !0 to

300 pSi range) decreases the pitch while coun~erweigbra PmpBller Tob!e
attached to the blade clamps increase pitch. A spring
assists the counterweights durinlr the leathering opera- 8~´•222-1 Assembly Tool for Prsr.ing A-Pi? Ring on

tion. Peatheiing the pitch is accomplished by opening C-PB2hu_bipider

a valve in the governor which allows the leathering Puller Tool for A-972
81.-223-1 Ring
spring to force the oil out of the propeller and back Tool for PresinSPilotTllb. into Hub
into the engine, thereby increasing the blade angle to
8’844 Spider
5K-274 piston Fixture Used for 8aloncing
the feathered position.

ORIGINAL
As Received By
~IGURI i--Model HC´•*PX So,iol Pr.pallsr ATP
 A-i. REMOVAL OF PROPELLER FROM (d) Rotate piston assembly (65),
uncoupling link
ENGINE--MODEL HC-A2XF-2 (See arms (69) from the link screws (23). liernove piston
Figure 2.) assembly.
(a) Remove spinner dome PISTON ASSEMBLY (65)
(80) by taking out screws

(81). (a) Take out screws (68) and relnove link pin unit
(67). Remove link arms (69).
WARNING (b) Remove "O" ring (75) and felt seal (76).
NOTE: Do not attempt to remove
plastic bushing Irom ~diston.
Feather propeller before removing high pitch
FEATHERING SPRING ASSEMBLY (57)
stop sub-assembly (44). Use blade bars to com-
press feathering spring so that the high stop pin (a) Remove screws (74) and stops (73). Remove front
(47) can be pushed out to allow propeller to split rings (72) by first sliding entire sprint: assembly
feather. An alternative method is to start the further into the cylinder (70) by about ~4-inch. Re-
engine and feather the propeller, move spring assembly from
cylinder.
(b) Disconnect the
spinner bulkhead (82) by removing
nuts (56), washers
(55) and (54´•) and bolts (53).
(c) Remove the propeller from engine by removing
I~ CAUTIO N

bolts (12) from the engine-propeller flange. Work the Do not disassemble the feathering
attempt to
propeller off the engine shaft (which is being held by spring sub-assembly (57) unless special tool
the two dowel pins (11) by applying a forward thrust No. C-845, the fixture for assembly of the feather-
and a fore and aft motion of the blade tips. It may also ing springs, is available; or some equal device is
be possible to drive the dowel pins back, using a punch. used. If this feathering spring is defective and no
Remove "O" ring (9). fixture is available, a new one should be in-
(d) Remove the spinner bulkhead from the engine stalled. Return the old one to the
factory for
flange. repair or replacement.
(e) Remove automatic high pitch stop sub-assembly (b) Place the assembly (57) in the fixture and com-
(4´•4) from propeller flange by removing bolts (52). press the feathering springs (61) and (62). Slide the
rear spring retainer (63) back on the pilot tube (58)
A-2. REMOVAL OF PROPELLER FROM and remove the rear spring
split retainer (64). Slowly
ENGINE MODELS HC-A2XK and release the spring compression and the
remove assembly
HC-A2XL from the fixture. Parts (63) (60)
(See Figure 2.) (62) (61) and (59)
can be removed from the
(a) Remove spinner dome assembly. Remove "O" ring
(84) by removing screws
(77).
(81).
CYLINDER (70)
WARNING (a) Unscrew cylinder (70) using a square bar inserted
in the slots provided.
(b)Remove "O" ring (71).
Feather propeller before removing high pitch
stop sub-assembly (45) as described under A-i BLADES AND CLAMPS
above.
(a) With ink and scale, mark matching lines on blades
(b) Remove high stop sub-assembly (45) by removing (1) and clamps (22). Record blade serial number with
bolts (52). clamp number for each side of propeller.
(c) Remove mounting bolts (16) (17) (18) or (19) as
(b) Remove the nuts (36) bolts (34´•) and (32) and
the case
may be, rerrlove the clamp halves
(22). Remove gaskets (31).
(d) Remove propeller from engine, including "O" ring Remove blades (1).
(10) and shim (13) or (14).
(c) From the clamp (22) remove the lubricator fittings
(25), and automatic high pitch stops (39) by removing
B. DISASSEMBLY OF PROPELLER screws (40).

Inasmuch as the only differences in the HC-A2XF, (d) Remove cotter pins (33), and remove and discard
K, and L propellers are in the mounting flanges and counterweight mounting screws (29). These screws
spinners, the disassembly is identical, so ail three models should be replaced immediately with new ones.
Torque
will be taken together. to 65 Ib. ft. Safety with cotter pin (30).
Mount the propeller on a table, securing the
mounting flange. CAUT I O N

REMOVAL OF PISTON ASSEMBLY (65) In normal overhaul operations, it is not neces-

(a) Unscrew nut (78) using wrench B-842-1. To keep sary to removecounterweights (26) or (27)
from the assembly (20) or !21), unless the parts
pilot tube (58) iroIrl turning, Ilse a socket wrench to
are to be replated, for which
apply torque in opposite direction, complete disassem-
bly must be made. Since the counterweig-hts are
(b) Slide piston (66) off pilot tube (58) by applying matched to the clamps (by virtue of the dowel
a force to the counterweights (26).
pins) it is not possible to interchange these parts.
(c) Remove cotter pin (dr2) and link screw sleeve (4´•1), If either is defective, replace the entire
both sides. assembly
(20) or (21).

-2-
BLADE BEARINGS galling and nicks are stress raisers which reduce the
fatigue life of the hub. Do not polish unless necessary, as
(a) Remove the balls Iroln the bearinga. the spider arms have been rolled to improve the fatiglic
(b) lieInove the inner races j5) of the beatings by re-
strength. (?’he roll Inarks are not tool rrlarks and should
moving the wire ring from the groove. not be removed.) If the blade pilot tube j4) is to be re-
placed in the hub, due either to excessive weal‘, or due
(c) Using special tool BT-222-1, combined with 13T- to the fact that it has slipped out slightly floln tile spidcl´•,
223-1, push guide ring (6) in slightly towards the center it is necessary to use a new tube having a .002" to .003/’
of the hub (3) only enough to uncover wire ring (7),
which then be removed. Using special tool nT- oversize diameter over the length which Illesses into
can
Remove the the hub spider hole. Press the new tube (4) into the llub
223-1, pull guide ring (6) from hub (3).
outer two halves of bearing race (5). spider (3) leaving exactly :13~ inches of the length es-
posed. Be sure the heavy end of the ttlbe is inserted into
(d) Remove "O" ring (8). the hub. Test. the tube for tightness by al,I,lying 5000 Ib.
force on the tube. If it slips with this fol.cc, it Illllst be
HUB SPIDER ASSEMBLY (2)
replaced with a larger tube of say .003" to.004’~ oversize.
(a) inspection
If spider sub-asscrubly shows
of the hub
screws (29) as
that the pilot tubes (4) reqllire replacerrlent, they may
(b) Replace the countcrweighl.
noted above. Use only the specified I,al.ts as tl~cy are
be pulled by means of an appropriate bearing pllller.
l’"at treated to a fligh stlengt2l.
This usually necessitates the part being returned to the
factory for this operation. (c) Replace all gaskets, "0" rings,;lncl cotter. j~ins.
AUTOMATIC HIGH PITCH STOP ASSEMBLY (d) Nicks or dceI, scratches in cylinder (70) Illay be
cause fol´• Ici,lacclnent, I,alticularly if tile Illal-ks al´•e irl tile
(4´•4´•) or (45).
region of the piston ’i()’’ I´•illS dlll´•illg norlnall ciiiise-fli&ht.
(a) high pitch stop asselnbly by I´•c-
nisassernble each Scratches in the fcatheling region Illa~ be tolerated if
Inoving cotter pin (49), washer (50) spring (48) and not too deep.
pin (47). of steel parts is recolllrllended
(e) Replating (cadlrlillrll)
C. CLEANING if the original plating 2las been wo~´•n off ol´• if dalllaged

by nicks or scratches.
ja) Wipe all dirt and grease off all parts,
(b) Clean all parts, except felt seal (76) with solvent,
CAUTIO N
and dry.
preventative conlpound all parts
(c) Apply a. rust on
’I’he hl~h spider arrrls (31 and Pilot tubes (4)
which are to be stored for any length of tilrle, shil,I’ed.
or
sholllcl be Inasked. Alter I,latinS the parts, they
in clean and dry place befol´•e reasselllbly. must be baked in an oven at 9500 F. l,lus ol´•
(d) Keep
lninus 250 for~.7 hours to elilllinate possibility of
D. INSPECTION hydrogen elnbrittlernent. High strength bolts, huh
tolerances and clamp parts are particularly susceptible to this
(a) Inspect all wearing parts accordinl: to
effect. Failure of the part may result unless this
specified in TABLE II. Replace parts not coming within
specified limits. baking is accomplished. If proper plating facilities
are not available, the parts should be painted with
(b) Inspect the blades according to tile tolel.ances in a suitable alurllinuln or laccluer I,aint.
TARLE III. Replace a blade whict~ falls below the listed
rrlinirnum dimensions upon repair. (f) Repair blades according to FAA Manual.
(8) Blade bushings. If the blade is ~´•orn be)lond
(c) Visually inspect all metal surfaces. Replace or re-
finish any bearing or wear surface which has a visible spccified tolerances, the blades be I´•cturned to the

nick, dent or other distortion. factory to be rcbushed. ’I’hese bushings scldolrl wear,
however, to the point where they be replaced.
(d) Magnetically inspect all steel parts for cracks not

visible to the eye.

F. ASSEMBLY
(e) Visually inspect the blades for cracks, particularly (See Pig. 2.)
around the shank retention area and at the leading edge
Kcassernble in reverse ordel´• of disasselnbly.
near the tip.
(f) Inspect t2le bearings for excessive wear or chafing. AUTOMATIC HIGH PITCH STOP
A certain amount of marking of the balls and races is to ASSEMBLY (44) OR (45).
be expected and is not necessarily a reason for replace-
(a) Assemble pin (47), spring (48), washer (50) and
rnent. Only when the bearings show pit marks which are
cotter pin (49) into high pitch stop bracket (46) or (51).
.002" deep and definitely feel rough, are the balls or races
to be replaced. Bearing life ordinarily is greater than ASSEMBLY OF BEARINGS ONTO HUB SPIDER
1000 hours.

(g) Inspect pilot tube (4´•) for slippage. The tube should (a) spider (2) on propeller table.
Mount hub

extend out from hub 3~j/4inches only. If this distance is (b) Using special tool BT-222-1, colnbined with tool
of
greater, the indication is that the tube has slipped out BT-223-1, push guide ring (6) hub spider bealing
onto

the hub spider. An oversize tube should replace the one retention flange. The chamfered end of ring (6) rrlrtst
which slipped. face the center of the hub, and the counterbored end
face out. Push ring (6) until the inner edge over´•hangs
E. REPAIR AND REPLACEMENT the inner flange face of hub spider /3) by about 1116-
marks and nicks from the inch. This provides a nest to fit the two of outer
(a) Remove all rust, galling
hub spider arms with crocus clothor fine emery. Rust, bearing race (5). Unscrew tool BT-223-1 about j~ inch

-3-
 to allow for inserting outer bearing race
(5) in nest pro- NOTE: The pitch will De set after the propeller
vided by ring (6). Adjust S1’-223-1 so that fingers is completely assemhlerl, after which tlze clamp
press
Dolts will De torqued and safetierl.
against bearing race and BT-222-1 presses against ring
(6). Screw ring (6) further onto hub and bearing race (e) Install the lubricator fittings (25) anti hig~-1 stol,
(5) until the groove in flange is uncovered. Plates (39) using screws (40) and washers (43). Wire
safety.
cAUTIO (f) Check for friction or binding of the blades when
related about their axe~. If the blades tend to bind after
tile bolts (32) and nuts (36) are tightened, it will be
It is important that. the
two bearing halves be
necessary relllo\e the c!a~nps anti blades and I´•elicve
to
matched perfectly at
the fractured surfaces and
tile friction,
wllate\cr the cause; whether it be friction
held flat:
against the inner face of the hub flange I,etween blatle and I,ilot tube j4) or friction I,etween
when the ring (6) is forced into place,
tile end of the blade and tile end of the hub arm. spiller
(c) Insert wire ring (7) in groove.
CYLINDER (70)
(d) liernove tool RT-222-1 and install tool B’l’-223-1
so that fingers rest against inner edge of
ring (6). Pull (a) Insert "O"
ring (7´•1) in the cylinder´• gloove behind
ring (6) out: over the wire ring (7); Il~e threads. Apl,ly non-hardening gasket
corrll,o~tnd to
the threads. Screw cylinder (70) onto
(e) Install "O" ring (8) over hub retention arln, in to- (3). Use a
i-inch scluare bar about 3-4 feet long as a
wards the center of the hub as far as possible, wr´•cnch, alJ-
plied to tt~e slot in the cylinder, l’ightcn the cylintiel
(f) Install inner bearing race (5); hold halves together hard against the hub 200 ft. Ib. tol.c.jrlc).
with wire ring.
(b) Inspect inside of the cylinder to be suic the 1’0’!
IMPORTANT: Locate bearing parting line fore ring (71) is still in place.
and aft or parallel with hub shaft axis.
(c) Inspect the slots to be sure tile t,al has not
(g) Fill bearings with balls. Pack with grease. raised the edges which Inight cut tile "0"
ring. Peen
(h) Roll "O" ring (8) out against bearing race.
cclges if necessary.
(i) Wrap masking tape around outside of bearing (5) FEATHERING SI’RINC SUR-ASSEMBLY (57)
and ring (6) so the balls will not fall out. This will be
NOTE: Whenassemblinll feethoin!l spring S%L6-
Iemoved when clamps are installed,
assembl~ (57), it is essential tlLcct a safe metcrts of
compressing tl,e springs ((il) and (ciB) he used.
?’his is nffo?´•clecl b~ the use of rs special tool
BLADES AND CLAMPS No. C-845.

NOTE: In order to assemDle the propeller and set (a) Assemble onto pilot: ttlbe (58) Irlushroonl
pitch accuratel?J, it is highlll advantageous to use (59) springs (61) and (62) spacer (60), anti rear
a special propeller table .having a shaft which spring retainer (63). Insert the above assell~blt:d parts
mates with the propeller hu8 flanlle. nil´• or oil in the spring coIrlpressiIlg fixture (l’ool
pressure! (100 psi min.) should De available in the
C-0´•15) and
shaft to actuate the piston. compress the springs Ilntil the rear sl,lit r.ctaincl (64´•)
can be asselnl>led in the
groove proviclccl in the end of
(a) Mount. the hub on the propeller table shaft, sealing
pilot tribe (58). lielease spring coml,lcssion so that re-
the flange with LLO" ring (9) or (10). Fasten with bolts rainer (64) fits into the nest Irlachinecl in the end of
or clamps.
retainer (63).
(b) Fill the blade pilot tube hole with a grease as (b) Slide tile feathering sI,ling sub-asscrrlbly (57) into
specified under "Greases Kecornmended."
cylinder (70) and the bore of hub spider (3) Ilntil the
NOTE: Be sure no air is trapped below the grooves in the end of the cylinder (70) are exposed.
grease as this will upset the balance.
(c) Install fl.ont split I-ings (72) into the groove in the
(c) Install blade (I) on the same pilot tube (4) Irolrl cylinder (70). Pull the feathering spring: sub-assclnl>ly
which it was removed. Place a hardening gasket com- forward to lock the rings (72) in
place.
pound (commercial automotive type) around the blade
shank in the shoulder radius. (d) Secure the sltb-assclnbly (57) and the rings (72)
in place by means of
fcathering stop (73) and screws
(d) Install the correct matching clarnl, and counter- (74). Safety with wire
weight sub-assembly (20) ol´• (21) with new clamp
gaskets (31). (e) Install "O" ring /77) in groo~e at end of threatls
in pilot tube (58).
NOTE: Tkis ocess can best Deaccomplished
by
peeling back tP~ nzaukin~ tape from abozLt 1800 PISTON
of the bearing on the top side. Then install the (65)
one-half of clamp that has the eounte~weight. (a) Install link amis (69) in
Then peel the tape from the lower half of the I,iston 166). Install link
bearing which is ezposed, and install the other
pin unit (67) and safety screw (68). Wire safety the
clamp half. Slip the clamp gaskets (51) Between latter.
the clamps at the parting line. This
procedure (b) Check link
will locate the inner bearilzg race parting line at arrrls (69) for free nlovement in piston
right angles with the clamp parting line WHICH (66) slots.
IS ESSENTIAL.
(C) Install a new "0" ring (75) and felt seal (76) into
Fasten the clamp halves together with socket screws the grooves in piston (66). Soak the felt seal in
oil. Oil
(32), bolts (34), washers (35) and nuts (36). ?Iffhten the L’O" ring.
socket screws (32) and nuts (36) and check for friction
id) Oil the cylinder (70) and "0" ring (77) at end of
of the blade when being rotated on the hub,
pilot tube.

-4-
 that plates (39) Check for clearance
(e) Slide the piston (65) onto cylinder (70) out so can pass.
a"d possible friction between parts.
(f) liotate piston (65) so the free ends of the link arms

(69) can be assembled over link screws (23). NOTE: The automatic ILigh pitch stop brackets
(44) must be removed before installing tile HC-
(g) Insert link screw sleeve (41) between screw (23) A2XL,K propeller on the engine as two of tl~e
and hole in link arm (69). Insert cotter pin (42). mounting screwscovered by these b?´•aekets.
are
These brackets need not be removed before in-
(h) Move piston (85) into full feathered position stalling the HC-A1XF propeller, Iloweve´•r.
(back assembly) so that the threaded
against the hub
end of tl;e pilot tube 58protrudes thru the end of
(68). Screw )86(
nut (78) onto pilot tube SECTION III
)I:iston
Torque the nut (78) to 75-100 Ib. ft. Restrain BALANCE
a socket
pilot tube (58) from turning
wrench to the hex located at the (a) Balance the propeller assembly befol´•e grease is added
to the clamps, and check again after gl´•ease is added.
Balance with Pitctl at high value-pins j47) engaged with
SETTING THE BLADE PITCH
plate (39).
(a) Apply air oil pressure through bore of the table
or (b) Either a suspension systerrl ol´• an arbor Illounted on
spindle, to force the piston against the low pitch stop. knife edges may be used for balancing. In event the sus-
Hold t~lis position. I’ension system is used, it is esseIltial tllal the ccntcr´• of
(b) Loosen tile outer clamp screws (34´•) only. Set each gravity of the propeller be located at ol- slightl~ I,elo\v
the pivot of the balance
blade with a protractor located at the 30-inch radius,
’‘acies will
See airplane specification for low blade pitch setting.
Tighten the blade clamps. Torque the clanlp (c) I,lay froII1 tt~e blatle clallll, assclll-
Kelnove tile end
screws (34) to 30 ft. Ib. torclue and the inner screws by driving
blies identical slnall wedges bet\~een the blade
(32) to 4´•0 ft. Ib. torcjue. Safety the latter with cotter clamps and hub spider, at identical locations.
Itey through hole drilled in ~lead. (d) Bolt propeller to balance ar~or., ol‘ wire balancer.
(c) C~-leck the blade against tul´•ning in the clamp by NOTE: The following balntlce p?´•ocedrc~e
torcluing the blade to 167 ft. Ib. Use a blade bar and a applies only to balance albo~ nlethod.

weight. If blade moves in the clamp, the clamp rrlust (e) Check horizontal balance by laying slugs i:17) irl
be removed and the clamp parting line at the outer Kccol´•d of slugs
corner of blade and clamp.
corners filed slightly (remove .005"-.010" each surface),

to allow the clamp to engage blade slloulders nlol´•e

required for balance.
firrrlly. (f) With the propeller in horizontal I,ositiorlt
50-100 Ib, downward force to each I,lade til, ’I‘his
(d) Check the blade sngle again at the low pitch sct- takes "I’ the Clearance between hrlh al~tl blaries it~ olle
ting, as the torquing of the blade may have I´•esulted in direction.
slight movement.
(g) Check vertical balance with heavy blade ui, Add
ic) Check the realherinl: anale by allowing´• thr feather- weight (37) to light side of clalllps. Kccold
ing spr´•ing to feather the propeller. See airplane specifi- ber required for balance.
cation for correct feathering angle. In case the feather-
ing angle is not, within prescribed limits, the piston as- (h) Kotate blade 1800 fro~n horizontal I,osition as Ilotcd
in "f" above and apply 50-100 Ib. to cactl blade til’
sembly (65) must be removed and the i‘eathering stops
?’his takes uI, tile clearance ol,posite to that noted
(73) adjusted. If the feathering angle is greater than
under "f".
specified, add shims under the stops (73); 1/32-inch
thick for 10 pitch change desired. If the featherin~ Again check vertical balance. Kccol´•d nulltbcr of
angle is less than specified, the feathering stops should weight slugs.
be filed down 1/32 inch for 10 pitch change desired.
(j) The final nunlber of weight slugs can now be de-

termined for vertical balance. If the slugs under

CHECK FOR GENERAL OPERATION, and "i" are added to the same side of the blade, the
FRICTION AND LEAKAGE total slugs required for vertical balance is the average
Of (LS)) and "i." If the slugs under (iR)~ and "i?’ are added
(a) Cycle the propeller with air and note general opcra- to opposite sides of the blade the difference between
tion fol´• possible friction, etc.
the two numbers is added to tile side I-cquiring the
(b) Hold full pressure on piston and check for leakage greatest number.
past piston "0" ring 75), cylinder "O" ring (71), and (k) Horizontal balance deterlnincrl ~lndcr "e´•’ Inust be
guide rod ;’0" ring (77). Oil applied at these points Inaintained by properly dividin~ the slugs rcrluired unclcl´•
will bubble if air is leaking out.
L’j" between the two blades.
INSTALLATION AUTOMATIC HIGH PITCH (1) Attach the slugs to the clamps with scl-ews (38) and
again check horizontal balance. Safety with wile. Do
STOP ASSEMBLY (44) and (45)
not attach Inore than 4 slugs with each pail- of screws.
(a) Install automatic high pitch stop brackets (4´•4´•) or
(4´•5) with bolts (52). Check operation of alltolnatic (m) Add eclual alnounts of grease to eacll blade, hold-
stop mechanism by cycling propeller between low pitch ing horizontal balance constant, until clarlll,s al-e corrl-
and high pitch. Check engagement of stop pins (47) pletely full, as evidenced by gleasr starting to cornc ollt
and stop plates (39). Both pins should engage plates at around cil´•cumference of hub spider at "O" ring (8).
some time within .010 inch. File plates as recluired if Avoid blowing out "0’~ ring and gaskets (31) with cx-
Check feathering by holding stop pins (47) cessive pressure.
necessary.

-5-
 SECTION IV, WEAR TOLERANCES

TABLE II. TOLERANCES OF WEARING SURFACES

MODELS HC-A2XF, L, K

Item
No. part
Replace if dimension
or Description of Measurement Specified is above or below

Max. Min. Max. Min.

1. A-158 Pilot Tube O.D. 1.4990 1.4987 1.4977
2. A-158 Pilot Tube Assembly, length Extending beyond
Hub Spider 3K+~i6 s3~ Xs 3~+W
3. Blade Bushing I.D. 1.5015 1.5005 1.5030
4. C-852-1 Piston, Plastic Bushing I.D. 3.782 3.780 3.785
5. C-852- Piston, Pin Hole Dia. .3765 .3755 .3795
6. 8-854 Cylinder O.D. 3.778 3.776 3.773
7. B-855A Pilot Tube Dia. O.D. .985 .984 .981
8. A-856 Mushroom Bore .988 .986 .993
9. A-857 Spring Retainer O.D. 2.243 2.241 2.235
10. A-961-3 Link Arms I.D. Small End .3755 .3750 .3785
11. A-961-3 Link Arms I.D. Large End .5635 .5625 .5.645
12. A-944 Bushings l.D. .502 .501 .504
13. A-944 Bushings O.D. .5620 .5615 .5600
14. A-304 Link Screw O.D. .5005 .4995 .4970
15. Feathering Spring Assembly, Compression Load 440 Extended 600 Compr’ed 400 Extended 550 Compr’ed

16. Blade End Play .060

17. Fore and Aft Movement of Blade Tip (98" Dia.) .068 .100
18. Blade Track or W Between Blades.
19. Balance Tolerance 1 Slug A-48

TABLE III.-- BLADE REPAIR TOLERANCES

Angle Face Alignment Width Thickness
Rad. Min. Max. M. Max.

Angle Face Alignment Width Thickness 8833 Blade

Rad. Min. Max. Min. Max. (Min.) (Min.)
9
4.700 1.980
12
5.726 1.095
7636D Blade 18 31.10 32.10 .103 .167 6.310 .692
26 240 24.60 .082 .018 6.070 .472
32 200 Setup .164 .098 5.450
9 4.700 1.980 .340
38 16.80 17.20 .242 .178 4.190
12 5.572 1.095 .233
18 410 420 .138 .202 5.702 .666
24 370 37.60 --.072 .008 5.312 .449 9333(3 and 93336-3 Blade
30 33.20 Setup .192 .128 4.450 .319
36 29.80 30.20 -.242 -.178 No limit No Limit 9% 4.704 1.980
13
5.720 1.095
20 410 420 .122 .058 6.307
8433-6 Blade -12 .693
28 36.50 37,10 .472 -.408 6.070 .472
34 33.20 Setup .682 --.618 5.450 .376
40 29.80 30.20 .832 -.768 4.200
9 4.700 1.980 .286
12 5.720 1.095
18 410 420 .138 .202 6.200 .625
24 370 37.60 .072 -.008 5.985 .471 TABLE IV. Torque Valves
30 33.20 Setup .192 .128 5.380 .337 Model HC-A2X Series
36 29.80 30.20 .242 .178 No Limit No Limit
Par. or
Torque Torque
Palt Sire Locoltion Hub
on Lb. Ft. Lb. In.
8433 Blade 8453-2 and -4
~6-20 "L" flange mounting 40 480
%-20 "F" and "K" flange mounting 60-70 720-840
9 4.700 1.980 1~-24 Outer blade clamp bolts 22 360
12 5.720 1.095 K-24 Inner blade clamp socket screw 40 480
18 410 420 .138 .202 6.200 .625
24 370
Counterweight socket screw 65 780
37.60 .072 .008 6.000 .473 ~-20 A-304 Link Screw 45-50 540-600
30 33.20 Setup .192 .128 5.460 .341 A-880-2 Nut, front of piston--feathering 75-100
36 29.80 30.20 .242 .178 4.200 .234
800-1200
Blade Blade installed in Blade Clamp 167 2000

-6-
 SECTION V 6. Stroma LT-1 (2-815 Grease)
Union Oil Co. of California.
LUBRICATION
7. Lubriplate 630 AA
A. General Properties of Grease Required. Fiske Brothers, Toledo, Ohio.
This grease will bleed oil in hot weather. It is rec-
Any grease used must have the following properties: ommended only for lubrication of the blade j,ilot
tubes but not the blade bearings.
(a). Waterproof.
8. KPM Aviation Grease No. 1
(b). Temperature range between -150 F and
Standard Oil Co. of California.
1500 F; or -4´•00 to 1000 F if operation is
in cold climate. 707
9. Lubriplate
Freedom from separatinl: oil from soap base Fiske Brothers, Toledo, Ohio.
(c).
due to centrifugal force or high tempera- 10. Mobilgrease Aero Lo-Hi PD-535_K
ture.
Socony Vacuum Oil Co.
(d). Low Friction. 11. No. 84 Medium Grease

Name. Keystone Lubricating Co.

B. List of Approved Greases, by Spec. or
12. I’exaco Regal Starfax Special.
i. Hartzell DG Grease.
13. Molub-Alloy No. 2 Grease -100 E‘.
2. Stroma HT-1 (2-801 Crease) No. 1 Crease -250 F.
Union Oil Co. of California. Oil Grease Co.
InlI’erial
for blade Los Angeles, California.
3. Gulf lex Moly bushings
4. Gulflex A. 14´•. Germany Calypsol H729
German Calypsol Colnpany, I)usseldolf.
This grease recommended for the blade
is ball
bearings as it will not bleed oil in hot weather.
C. Proper times and amounts of grease are
5. RPM Aviation Grease No. 2
Standard Oil Co. of California. mentioned during assembly procedures.

SECTION VI SERVICE TROUBLES AND REMEDIES

Tiouble Probable Cooee Remedy

FAILURE If rpm fails to increase but will Set relief valve in governor to provide necessary pressure, up to

OF PITCH reduce: Low oil pressure. 275 psi.

TO CHANGE ___-

If rpm change in both directions See "Excessive Friction in Hub Mechanism," below. Isolate friction in
is sluggish: Excessive friction in each blade by uncoupling piston and testing each blade separately,
hub mechanism. before tearing propeller down.

Newly-installed governor has Check and correct.

wrong direction of rotation, or
has bypass plug in wrong hole.

EXCESSIVE FRICTION Pilot tube has slipped out slight- Tear down and check distance pilot tube extends from hub spider.
IN HUB MECHANISM ly and is rubbing hard against Should be 33~ inches. If more, remove pilot tube and replace with a
end of hole in blade. tube .002 in, oversize at hub end.

Blade bushing seized on pilot Polish pilot tube and blade bushing with fine emery paper and re-

tube. assemble.

Blade ball bearings unusually Replace bearing.

rough or broken.

Friction in various moving ports Check parts individually. If tightness is encountered in sliding parts,
of pitch control mechanism, increase clearances slightly. Apply oil externally to moving parts.

IMPROPER RPM Static rpm too low. Governor has high rpm stop, as well as propeller low pitch stop. Either
the governor or the propeller stop may limit maximum rpm. To de-
termine which is causing trouble, open the throttle and move governor
control back and forth slowly.
If maximum rpm is reached BEFORE governor stop is reached, propeller
stop is probably limiting rpm. If this is the case, loosen blade clamp
outer bolts and rotate blades in clamps. Reduce blade angle about i"
for each 100 rpm increase. (10 equals inch circumference at
blade root.)
If maximum rpm is reached AT SAME TIME os governor stop is reached.

governor stop is the maximum rpm. Readjust gover-

probably limiting
nor stop to obtain proper rpm. One turn of governor stop screw equals
about 17 rpm. Turn stop screw out to increase rpm.
Governor stop should limit high rpm, with propeller stop reached at 50
to 100 rpm beyond. This allows for variations in engine power with-
out affecting maximum rpm.

-7-
 Trouble probable Cause Remedy
Static rpm too high Reduce by screwing governor stop in, one turn for each 17 rpm
reduction.
FAILURE TO Governor control does not pro- Provide sufficient travel in governor control. Governor must drain oil
FEATHER vide enough travel to allow out of propeller during feathering.
governor to move hard against
high pitch stop.
Excessive friction. See "Excessive Friction in Hub Mechanism."

High pitch stop pin fails to slide Check for burrs on pins. Check for stiffness of spring. If propeller
out atfeathering rpm. ieathers at high rpm’s but fails to feather at low rpm’s, too-stiff spring
is indicated. Reduce length of spring by one or two turns.

Weak or broken feathering Replace.

spring.
SURGING Air trapped in propeller Provision should be
actuat- incorporated in engine to allow trapped air to
(When governor ing piston or in engine shaft, escape from system during one half of the pitch change cycle.
control is Exercise propeller by changing p;tch or feathering before each flight.
changed rapidly
or rough air Governor pressure too low. Adiust governor relief pressure that of
so rate pitch change is the
is encountered.) same in both directions.

Excessive friction in pitch See "Excessive Friction in Hub Mechanism."

change mechanism.
Governor lacks sufficient Change adjust speeder spring. This gives governor more stability,
or

dampening. but makes pitch control more sensitive, which, may in turn require
re-rigging of control to offset higher spring rate. Changing to stiffer
speeder spring should be done only after all other factors are checked
and corrected.

OIL LEAKAGE Faulty "O" ring seals follows: as Disassemble and inspect "O" rings and the surfaces they seal. Replace
Front of rear cone between "O" rings if defective. Replace cylinder if surface is scratched or
engine shaft and hub. nicked in area where "O" ring slides. Use gasket compound on
Between hub and cylinder. cylinder threads when replacing. Peen down raised places caused by
Between piston and cylinder tightening of cylinder with bar.
at front of piston.
GREASE LEAKAGE Grease leaks past clamp seal Loosen clamp bolts and replace gaskets. Standard thickness of gasket
(Only source of gaskets. is .050, but .060 gaskets are available in case .050 gaskets are not

grease leakage compressed sufficiently to hold.

is blade bearings.)
Grease leaks from between Inscribe blade with ink pencil to assure correct blade angle on re-
or
blade and clamp. assembly, and blade and clamp. Add gasket compound in
remove
radius of blade butt. Replace blade and clamp.

END PLAY IN Buildup of manufacturing

BLADES tolerances. Total end play of .060 is permissible.
BLADE TRACK Tolerance of ~e inch is allowed.

BLADE FIT ON With manufacturing tolerances, the maximum that the blade
tip can
HUB PILOT TUBE be moved fore and oft is .068, without grease in blade
clamps and
bearings. With grease, the movement is nil. If blade tip fore-and-aft
movement increases to .100 dry, blade requires
factory re-bushing.

PART II PARTS LIST

SECTION

INTRODUCTION

The first column in each parts list is the figure and If you do not know the
part nurnher, you may refer
index number. This refers to the illustration and index the
to applicable illustration and then find the index
number of each part. For example, if you are ordering
number assigned to it (20). Look in the parts
a blade clamp assembly and want to see how and where
listing,
and read the part number, 838-10.
it locates on the general assembly, this column indicates
Figure 2, index number 20. Looking at Figure 2 in the
g-roup assembly Parts List, index number 20, the appear- HOW TO ORDER.
ance and location of the
clamp assembly may be easily
found, also the details of all parts contained in this It is important that the Part Number, Part Name
sub-assembly, and Model Number be given when orderinfi parts.

-8-
 SECTION II

GROUP ASSEMBLV PARTS LIST

Models HC-A2XF, K, and L-2

Feathering

No. Required
Code No. Part No. Description F-2 K-2 L-2

1 Blade -------------------------I
2 2 2

2F 840-52 HUB SPIDER UNIT (840-37 interchangeable) 1

3F C-981-3 Hub Spider I 1

4 A-158L Pilot Tube ---------------1 2

2L 840-39 HUB SPIDER UNIT I 1

C-982-1 Hub Spider 1
3L
4 A-158L Pilot Tube 2

2K 840-40 HUB SPIDER UNIT

3K C-982-2 Hub Spider 1
4 A-158L Pilot Tube ----------1 2
A-2027 Wire Rings, Bearing 2 2 2
A-311 Bal I Spacers, Bearing ----------1 2 2 2

HUB ASSOCIATED PARTS

A-971 Split Bearing 2 2 2
5
A-972 Guide Ring j 2 2 2
6
A-974 Wire Ring, Retainer 2 2 2
7
8 PRP-909-8 Blade "O" Ring 2 2 2

P
10
11
PRP-909-6
PRP-902-32
.5002 x 1
"O" Ring, Hub Mounting
"O" Ring, Hub Mounting
D. Dowel Pin
::::::::I 1

2
1 1

12 A-1328-1 12 Point Bolt (A-2040 or A-1333-4 Opt.) b

8-933´•1 Shim, L Flange 1
13
8-1322 Shim, K Flange 1
14
A-898-2 Washer 4
15
A-988 Bolt 4
16
A-988-1 Bolt 2
17
A-1333 or 3 Ferry Screw 2
18
A-1328 Ferry Screw 1 4
19
A-1381 Washers (AN960-816 Opt.) 1 6

Allsma(e CLAMP AND COUNTERWEIGHT SUB-ASSEMBLY 2 2 2

20 838-10
1 Depsndina (For 8433 and 8833 Blades)
On Bloder
21 838-11 j Ulsd CLAMP AND COUNTERWEIGHT SUB-ASSEMBLY 1 2 2 2
(For 7636 and 8433-12 Blades)
(838-11 same os 838-10 except
on d38-IO odd A-890-I slug to

8-271 counterweight, making

833-2 Counlerweight Assemblyl
22 C-3-5A Clamps
23 A-304 Link Screw
24 A-285 Staking Pin
25 MS15001-1 Clamp Zerk Fitting 1 4 4 4

26 B-271-1 Counterweight 2
27 833-2 Counterweight 2 2
28 A-65 Counterweight Staking Pins.. 2 2 2
29 A-2036-30 Socket Head Cap Screw4 4 4

30 A-285 Staking Pins (AN38D-3-2 Opt.) 4 4 4

31 A-47-1 Clamp Gaskets 4 4 4

32 A-282 Clamp Mounting Socket Screws 4 4 4
33 AN380-3-2 Cotter Pins -1 4 4 4
34 A-2017 Clamp Bolts, 12 Point 4 4 4
35 AN960-616 Clamp Mounting Washers 4 4 4
36 A-2043 Clamp Nuts 4 4 4
No. 3 Lubricaps 4 4 4

CLAMP ASSOCIATED PARTS

37 A-48 Balance Weight As Needed
38 AN501A10-6 Weight Screw As Needed
39 A-881 Stop Plate 2 2 2
40 AN501A10-6 or -5 Stop Screws 4 4 4
41 A-944 Sleeve, Link Screw 2 2 2
42 AN380-3-3 Sleeve, Cotter Pin 2 2 2

44 830-2A AUTOMATIC HIGH PITCH STOP SUB-ASSEMBLY 2

46 8-882-1A High Pitch Stop Bracket 2
47 A-883 High Pitch Stop Pin 2
48 A-884 High Pitch Stop Spring 2
49 AN380-3-3 Spring Mounting Cotter Pins 2
50 AN936A10 Washer, Internal Lock 1 2

-9-
45 830-9 AUTOMATIC HIGH PITCH STOP SUB-ASSEMBLY 2
51 8-984 Bracket, High Pitch Stop 2
48 A-884 High Pitch Stop Spring 2
47 A-883 Hish Pitch Stop Pin 2
49 AN380-3-3
2
50 AN936A10 Washer, Internal Lock 2
830-9A AUTOMATIC HIGH PITCH STOP UNITS 2
8-984-1 2
A-883 Pin 1 2
A-884 Spring 1 2
AN936A10 Washer 2
AN380-3-3 Cotter Pin _
1 2
AUTOMATIC HIGH PITCH STOP ASSOCIATED PARTS
52 AN5H4A Mounting Bolt 4
53 AN415A Mounting Bolt 4
54 AN960-416 Mounting Washer 4 8
55 AN960-416L 4
56 AN363-428 Mounting Nut (H10-4 Alternate) 4
AN74-5 Hex Head Bolts 1 4 4
57 831-5A FEATHERING SPRING SUB-ASSEMBLY 1 1 1
58 B-855A Pilot Tube 1 1
59 A-856 Outer Mushroom 1 1 1
60 A-860-1 Feathering Spacer Tube 1 1 1
61 8-953 Feathering Spring Inner (Heavy) 1 1 1
62 8-853 Feathering Spring Outer 1 1
63 A-857 Rear Retainer, Spring 1 1 1
64 A-858 Rear Split Retainer, Spring I 1 1 1
65 1 832-24 PISTON ASSEMBLY I 1 1
66 C-852-6 Piston Jack Unit I 1 1 1
67 A-i 464 2 2 2
68 AN501A10-6 Safety Bor Mounting Screws 2 2 2
69 A-861-3 Link Arms 2 2 2

HYDRAULIC ASSOCIATED PARTS

70 1 8-854 Cylinder 1 1 1
71 1 PRP-909-13 Cylinder "O" Rings 1 1 1
72 A-85P Split Retainer 1 1 1
73 A-899 Feathering Stop 1 2 2 2
74 AN501A10-6 Stop Screw 1 4 4 4
75 PRP-902-46 "O" Ring I 1 1 1
76 A-863 Dust Seal I 1 1 1
77 PRP814-12 "O" Ring, Pilot Tube I 1 1 1
78 A-880-2 Piston Nut 1 1 1

79 835-13 SPINNER SUB-ASSEMBLY 1

80 C-888-4 Spinner Dome I 1
81 AN526C1 03287 Screws 14
82 C-807-1 Bulkhead I 1

83 835-6P SPINNER SUB-ASSEMBLY 1 1

84 1 C-888-4P Spinner Dome 1 1
81 AN526C1 03287 Screws 14 14
85 C-885P Bulkhead Adaptor I 1 1
835-16 SPINNER ASSEMBLY 1 1
C-888-4 Dome, Spinner 1 1
AN526C1032R7 Screws. Dome Mounting 14 14
C-885 Adapter Ring Unit I 1 1

-10-
 ENGINE SHAFT

12 37 9, ~c, 29

n I t~4 26
0 1 27
C 3F 20
54
Am 28 21
h)

On
I I
9
I L/I
22

25

24
-.-e, 53

Y 23

31
n

N
x
67
5
41 65
81
e i 79 80
43
I 76

P 32~

33 ~40
39
0-- B

75
F

fl:
F
ENGINE SHAFT

h)
83
54 4
sl

I
I
d 3K

84
n
B
x
to
61
\63’
I
n7J
9a

6.’P:-
62
a I,

a ~d v 10
61 72

18 19
n 13 4 53
71 73
52
g 3L 57
lo 74
b 70 K-L

58

17
9~
 SECTION III

PARTS LIST DIFFERENTIATING BETWEEN PARTS LIST DIFFERENTIATING BETWEEN

HC-A2X F-2 AND HC-82XF-2B HC-A2XF-2 AND H C-A2X F-2A

Code Part No. Nomenclature HC´•A2XF-2 HC-82XF-2B Code Part No. Nomenclature HC-A2XF-2 HC-A2XF-SA

2F 840-37 Hub Spider Unit 1 56 831-5A Feathering Spring

3F C-981 Hub Spider 1 Sub-Assembly 1
57 855A Pilot Tube 1
2F 840-3 Hub Spider Unit 1 62 857 Rear Retainer,
3F C-801-2 Hub Spider 1
Spring 1
5 A-971 Split Bearing 2
56 831-1A Feathering Spring
5 A-14-A Blade Bearing 2
Sub-Assembly 1
6 A-972 Guide 57 855-2A Pilot Tube 1
Ring 2
A-159 62 857-1 Rear Retainer,
Split Ring 2
7 A-974 Wire Ring Retainer 2 Spring 1

All other part8 All other parts are common to bothdesigns.

are common to bothdeJigns.
NOTE: The HC-APXF-2A Propeller is used only on
McDermotf Widgeon Conversion. It corre-
sponds to the old HC-82XF-2C Model.

-18-

Printed in U.S.A.
06
N D B O~K

a BLADE, CONSTANT SPEED

F.A,A, Approved I M"""""’o

~L ER, I N.C.
 RECORD OF REVISIONS

Paa
MFG REV
NO DESCRIPTION ISSUE DATE ATP REV DATEI INSERTED BY
 RECORD OF TEMPORARY REVISIONS

ATP REV INSERT DATE REV REMOVE

TEMP
DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY
REV NO
 TABLE OF CONTENTS

PART I OVERHAUL INSTRUCTIONS

Section I

Description of Propeller Operation

Section II Overhaul Instruction.F

Special Tools-Table I

A-I. Removal of Propeller Engine--BHC-92ZF-1DI

from

A-2. Removal of Propeller from Engine-HC-92ZK-8D,-8L---´•

B-l. Disassembly of Propeller-BHC-927,F- 1D1

’L
B-2. Disassembly of Propeller-HC-92ZK-8D,-8L
3
C. Cleaning
3
D. Inspection
3
E. Repair and Replacement
BHC-92ZF-1D1 3
F-l. Assembly
HC-92ZK-8D,-8L 4
F-2. Assembly
5
Section III Balance
6
Section IV Wear Tolerances
6
Hu~-Table II Wearing Surfaces
6
Blade--Table III Repair Tolerances
Table IV Values 6
Torque
Creases 7
Section V List of Approved
Section VI Service Troubles and Remedies......

PAR~ II PAR~S LIST

8
Section I Introduction
Section II Group Assembly Parts List

Model BHC-92ZF-1D 1 9

Section II Group Assembly Parts List

Model He-92ZK-8D,-8E 10

NBTE: Installation, f)peration

and General Service are subjects lohieh
are covered in tie Hartzell "Owner’a Propeller
Manzlal."

ORIGl~)r$b As
RECEIVED BY. ~4´•1TP
 PART COVERHAUL

SECTION
DESCRIPTION
The BIIC-92ZF-IDI ha i-blade eonwnt speed (b) Remove the prooller from theengine by removing
pm-
piler designed for engine.in the 150-300 B.P. class bolts (14) and washers (16) from the ngine-propller
having nn "P" gpe mountng dugs. The "P" npnge flnnger Work the propeller off the engine shaft wtuch u
utiliaa *x K-inch bolts on a Cinch bolt circle plus two being held by two dowel (15), by applying a for-
K-ineh dinmeta dowel pina The dash 1Di design wprd thnul and a fore and aft motion of the blade tip*
It may aim be possible to drive the dowel pina back,
oprates with governor oil preasurs to ndua pitch Md
b~a to Tb~..B’. prr- Ydng p~b ~cmw."O" Mg
coding the Nc tn the design indicates da the PIP (E) Remove the pmncr bulkhead by rmwi~8
~1UU (55), washers (54) and bolts (53).
piler Range dowel pins us located i. the l´•B" pod~ioa
The HC-92WC-BD, -8L is also a 2´•blnds, U)lllfPllt
A-2 REMOVAL OF PROPELLER FROM
pmpll´•r designed for engines in the 1M to 300 ENGINE-MODEL HC-92ZK´•8D,-8L
n.P. elpu, having the "K" hips flangr The
mounti~
"K" dugs utillcl *I bobs on ~W-inch bolt (See Fig,4)
~ble Tho dub ED nod st q*W vilh gonmo. 9
Raoouc ´•pnar dom. (U) by
pressure to lamr pitch and binds n*Lt- ~1 wor~g rrrw

)km.
mgmoment to rrdua pitch. The dash ED L a right
bud pmpller, while the dpth 8L r idt hand

SECTION II
OVERnAUL INSTRUCTIONS
Bbolu Remove L10"
r~.np, by

riog (L1)
rrm~y mnunt-

Pnd shim (13).

sr, DISASSEMBLY OF PROPELLER,

T´•bl´• i.- SPECIAI OVERnAUL TOOLS MODEL BHC-92ZF´•1DI (Sce Fig, 9)
Rop(ln Mnant the pmpllsr on a table, securing the~mg.
hllldng Equlpmmt. Win a *rba hp´• to the spindle rut;rr
sake rwl fa Pnulns pilotTuk Int~ nub SpLI´•r
REMOVIU. OF PISTON
A-i. REMOVAL OF PROPELLER FROM
ENGINE MODEL BHC´•92ZF-ID1
i~)Unrm* auu (Bi imn bnh puton ~e md~
(5) Looan a +m !40) lantcd in forks (39).
(Sec Fig. 5) lfl Slide the pllon-sude rod nrembly lonnrd off the
tpioocr hme (s0) bl 1´•Li~ um. vuh´•n 112), rod tloovot (*I).

noua,- I*od´•l ~KA1U´•IDI sKHIII 1´• Mod* ´•II

-I- ORIGINAL
As Received By
ATP
(d) Remove felt seal (97) and "O’ ring (46) from REMOVAL OF GUIDE COLLAR UNIT
the piston (34). (a) Drive guide collar dowel pins (8) out thru rear of
propeller nange.
CAUTION
(b) Remove the socket head screws retaining the guide
collar unit (7) allowing guide collar to be removed from
hub spider (3).
DO NOT attempt to remove dowel pin
REMOVAL OF SPINNER LUG
(38) or guide rod (37) as these parts are
permanently installed at the factory. Also, to) Unscnw bolts (6) rrmoving spinner lugs (5).
do not nmove plastic bushing (36) from
inside the piston. RZ. DISASSEMBLY OF PROPELLER,
MODEL HC192W(~8D, ~8L (Sec Fig. 4)
REMOVAL OF CYLINDER
Mount the propeller on a table, securing the flange
(a) Unscrew cylinder (44) using a squan bar inserted to a Spindle fixtun.
in the slots provided
(6) Remove "O" ring (45). REMOVAL OF PISTON
(a) Unscrew nuts (36) from both piston guide rods
REMOVAL OF BLADES AND CLAMPS (30).
With ink and scae, mark matching lines on blade~
(b) Loosen set screws (33) located in forks (32).
(a)
and clamps (18). Record blade serial number with (9) Slide the piston-guide rod assembly forward off the
(1)
clamp number for each side of propeller.
cylinder (38), reieasing washers (35), sleeves (34), and
fo’ks (92).
(b) Remove the nuts (90), bolts (29), and (27), and (d) Remove felt seal (39) and "0" ring (37) from in-
nmove clamp haves (18). Remove gaskets (26). Re-
side of piston (27).
move blades (1).

(c) From the clamp (18) nmove the lubricator fittings

(21). CAUTION
(d) Remove and discard counterweight mounting scnws
(24). These scnws should be replaced immediately with DO NOT attempt to remove dowel pin
new ones. Torque to 65 ft. Ib. safety with cotter pin (25).
(31) or guide rod (30) as these are wrma-
installed at the factory. Aim, do
CAUTIO N
piston
yltne.)82(
not nmove plastic bushing (29) from the

In normal overhaul operations, it is not REMOVAL OF CYLINDER

necessaF/ to remove counterweights (22) Unscrew cylinder (38) using a xjuare bar inserted
from the clamps (18), unless the parts m slots provided.
must be npiated for which complete dis-
(9) Remove "O" ring (40).
assembly must be made. Since the ~ounter-
weights an matched to the clamps (by REMOVAL OF BLADES AND CLAMPS
virtue of the dowel pins) it is not possible
to) With ink and scale, mark matching lines on blades
to interchange these parw´• If the counter-
(1) and clamps (15). Record blade serial number with
weight !22) is defective, a new one can be clamp number for each side of propeller.
installed; but if the clamp (rs) is defec- (b) Remove the mts (23), bolts (22),and (20), and n-
tive, the entire assembly must be replaced move clamp hahzs (15). Remove gaskets (19). Remove
blades (1).
(e) Remove and discard lnnsccew (19). This can ordi-
(c) From the clamp (15) nmove the lubricator fittings
narily be done by unscrewing tbe linlKnw without re-
(18).
moving staking pin (20), as the latter will sheat off.
After linkscnw is nmoved the pin (20) can be remond (6) Remove and discard linkscnw (16). This can ordi-
from the clamp with a small punch. wily be done by unscnwing the lintscrew without n-
(t) Install new linkscnw (19) in clamp. Torque to moving staking pm (17), as the latter will sheat off. After
linkscnw is removed, the pin (17) can be nmoved from
3540 ft. Ib. Remove linkscrew and.examine the cone
the clamp with a ynall punch.
seat of the scnw and clamp to be sure that then paM
an 15% seating, as this f urtranely important. Re- (9) Install new linkscnw (16). Torque to 3540 ft. Ib.
Remove linlscrew and examine the cone seat of the
install linlwcrewand torque to 35´•cW) ft. Ib, Safety with
scnw and the clamp to be sun these parts are 75% seat-
new pin (20), and stake.
i"g’
m this is extremely important Reinatall linkscrew

RE‘MOVAL and torque to 35-40 ft. Ib. Safety with new pin (17),
OF BLADE BEARINGS
and stake.
(a) Place a container beneath the ball bearing (10) to
catch the bah when nleased. r
REMOVAL OF BLADE BEARINGS
~b) Roll "O" ring (12) out of its grool~ ia the hub (a) Place a container beneath the ball bearing (8) to
spider, using a screw driver. This nleasei the bearing, catch the bails when teleased.
allowing the balls to drop out. (6) Roil the "0" ring (10) out of its groove in the hub
(c) Sliae the bearing races (10) in towards the centet spider, using a screw driver. This nleases the bearing,
of the hub allowing split rings (11), bearing (10), and allowing the bah to dop out.
"’O’ ring (12) to be removed. Discard splittings (11). (c) Sli~e the bearing (8) in towards the center of the

-P-
 ERRATA SHEET NO. 1
MANUAL NO, 110

Page 3: F-l,--Assembly of Guide Collar Unit,

Change the caution note to read:

Short aluminum pins are inserted in the "A" dowel pin

holes to stake the guide collar while 1 inch long steer
dowel pins are installed in "8" holes for installing the
propeller on the engine,
 hub, allowing split rings (9) to be removed. may be cause for replacement, particularly if the marks

(d) Remove bearing (8), and "0" ring (10). are in the region of the piston "O" ring during normal
REMOVAL OF GUIDE COLLAR UNIT cruise-flight. Scratches in the other regions may be tol-
e’SLtCd if not too deep.
(a) Drive staking dowel pin (6) back thru propelk
flange. (e) Replating (cadmium) of steel parts is recommended
Unscrew socket head collar if the original plat~ng has been worn off or if damaged
(b) screws holding guide
unit (5) together. Remove guide collar(5). by nicks or scratches.

C.
)a(GNIAELC Wipe
all dirt and grease off all paru.
I~
(b) Clean all parts, except felt seal (97) or (39) with The hub spider arms (3) and pilot tubes
solvent, and dry. (9) should be masked After plating the
(c) Apply a rust pnventative compound on ah parts
parts, theymust be baked in an oven at
which are to be stored for any length of time, or shipped
3500 F. plus or minus 250 for 3 hours to
(d) Keep in clean and dry place before nassembly.
eliminate possibility of hydrogen unbrit-
D INSPECLTON tlement, High strength bolts, hub and

all wearing parts according to tolerances

clamp parts are particularly susceptible to
(a) Inspect this effect. Failure of the part may result
specified in TABLE II. Replace parts not coming within unless this baking is accomplished. If prop-
specified Iknin er plating facilities are not available, the
(b) Inspect the blades according to the tolerances in parts should be painted with a suitable
TABLE III. Replace a blade which falls below the listed aluminum or lacquer paint.
minimum dime~sions upon repa~r.
(c) Visually inspect ail metal surfaces. Replace or n- (f) Repair blades according to CAA Manual.
finish any bearing or wear surface which has a visible (8) Blade bushings. If the blade bushing is worn beyond
nick, dent or other distortion. specified tolerances, the blades should be nturned to the
(d) Magnetically inspect all steel parts for cracks not factory to be nbushed. These bushings seldom wear:
visible to the eye. however, to the point where they must be npiaced,
(e) Visually inspect the blades for cacks, particularly
around the shank rrtention ana and at the leading edge F,1. ASSEMBLY, MODEL
near the tip.

(f) Inspect the bearings for excessive wear or chafing.

(See Fig. 3)
A certam amount of marking of the balls and races is to Reassemble in reverse order of disassembly.
be expected and is not necessarily a reason for nplace-
ASSEMBLY OF SPINNER LUG ONTO
ment. Only when the bearings show pit marks which an
HUB SPIDER
.002" deep and definitely feel rough an the balls or
races to be replaced. Bearing life ordinarily is gnater than
Attach lug (5) to nange of hub spider (3) with
1000 hours. scnws (6). Wire safety.
(g) Inspect piler tube (4) for slippage. The tube should ASSEMBLY OF GUIDE COLLAR UNIT
extend out from hub 33k inches only. If this distance is
(a) Install guide collar unit(7) on hub spider (3), using
greater, the indication is that the tube has slipped out of socket head
the hubspider. An ovenize tube should replace the one
scnws to clamp halves together. Before
which slipped.
scnws are tightened, line up the notch in the collar unit
(7) with the dowel pin hole in the hub spider. Tighten
E. REPAIR AND REPLACEMENT scnws to 2-9 ft. Ib. torque.

(b) Inert dowel pin (8) in flange from nar, until it

(9) Remo~e 811 rust, galling marks and nicks from the
enters the notch machined into g~ide collar (7).
hub spider arms with crocus cloth or fine emery. Rust,
galling and nicks an suoss raisers which reduce the
i "eccs3a~’,
the spider arms have been rolled to unprove the fatigue
strength. (The roll marks are not tool marks and shouM Do not confuse dowel pin (15), which ir
not be nmoved) If the blade pilot tube (9) is to be n-
used for installing the propeller on the
placed in the hub, due either to excessive wear, or due
t~ the fact that it has slipped out slightlyfrom the spider,
engine with dowel pin (8).
it is necessary to use a new tube a.002" to.003" ASSEMBLY OF BLADE BEARINGS ONTO
ovenize diameter over the length which
21/9"
pnsses into
the hub spider hole. Press the new tube (4) ii~to the hub
HUB SPIDER
(a) Mount hub spider on
propeller table.
spider (3) leaving aractly 3VI inches of the length ex- (b) Place a blade mountmg "0" Mg (12) on each leg
posed. Be sun the heavy end of the tube is inserted into of the hub spider (3). Roll the "0" ring back toward;
the hub. Test the tube for tightness by applying 5000 Ib.
th, center of the hub.
force on the tube. If it slips with this rdtce h must he
(C) Install the blade mounting hearing (10) on the hub
replaced with a leger tube of say.OO3" r~009" o\zni~e.
spider.
(6) Replace the counterweight mounting3cnws as noted
above. Use onlyr the specified parts as they are heat
a high stnngth.

Replace all gaskew,"0" rings, and cotter pina

I~I deep in cylinder (99) or (38) Be sun the thin race is installed rmt

-5-
 d
(d) Install NEW like-numbered blade mounting split value specified for aircraft. Tighten outer clamp screws
rings (It) between the bearing and the spider arm (29) 60;65 ft. Ib. torque.
shoulder. (b) Release pressure and move pitch into high value.
(e)~Pull the bearing (10) and split ring (11) outward Set the second blade to match the first blade, within
agamst the shoulder of the hub spider. Roll the "0" about .20. Torque outer screws (29) to 60-65 ft. Ib.
ring (12) into its groove behind the bearing (10). Torque inner clamp screws to 40 ft. Ib. Safety with
cotter key thru drilled hole in the head.
CLAMPS AM) BLADES
(c) Check the blade against turning in the clamp by
NOTE: in order to cussemble the propeller and torquing the blade to 167 ft. Ib. Use a blade bar and a
set the pitch (zoourcctely, it is ~dvont4gsous
to use o spsciol propslla* t4b2s hoving cr
weight attached to the end. If the blade moves, or rocks
in the clamp, the clamp must be removed and the dif-
ehcZt which matcls with th9 70Pll~* hat
fbnye. Air or oil prsssurs (100 pm nr,rr) ficulty rectified. Expenence has shown thirt the clamp
should be av~ilobls in the ohc~ft to ~otu4to gaskets (26) may prevent the clamps from tightening on
the piston the blades. The gaskets can be trimmed at the outer hole

(a) Mount the hub on the propeller table shaft, sealing slightly to allow the clamp to come together closer.
the nangewith "O" ring (13). Fasten with bolts or Also, the outer corner of the clamps might require fiiing
by .005-.OLO. (Coat filed area with aluminum lacquer.)
bkde pilot hole with a gear m specified (8ulletin 69 also covers this subject.) I
under "GREASES RECOMMEEjDED." (d) Check the blade angle again at high pitch, as torqu-
ing of the blade may have moved it.
NOTE: Be sure no oir is tropped below the
grsc~ss Irs this will upset hahnes.
CHECK FOR GEEJERAL OPERATION, FRICTION
AND LEAKAGE i
(c) Install blade (1) on the same pilot tube (9) from
which it was received. Place a hardening gasket com- !9) Cycle the pitch with the counterweights for possible
friction.
pound (commercial automotive type) around the blade
shank in the shoulder adi~u (b) Hold full pressure on piston and check for leakage
(d) Install the correct matching clamp and countet- past piston "O" ring (46) and cylinder "O" ring (45).
weight subassembly (17) with new clamp gaskets (26). Spread ail around these points, as air bubbles will indi-
Fasten the clamp halves together with scnws (27), bolts
cate leakage. ;i
(29), and nuts(30). Tighten these scnws and check F12. ASSEMBLY, MODEL HC192ZK18D, 8L
blade for friction on the hub when rotated Remove
(Sec Pig. 4)
blade, and cornct for friction if too tight.
Reassemble in reverse order of disassembiy.
NOTE: TL pitoh toiU be wt ofter the pro-
ASSEMBLY OF GUIDE COLLAR UMT
pellsr is cotnplstoly ossemblsd, ofter urhioh
the Ebmp bolts ~iU be torqued 4nd sofstisd. to) guide collar unit (5),using socket head screws
Install
(e) Install the lubricator fittings (21). to clamp the two halves together. Before screws are 2)
tightened, line up the notch in the collar unit (5) with
INSTALLATION OF CYLINDER the dowel pin hole in the hub flange. Tighten screws to
(a) Insert "O" ring in the cylinder (49) groove
(45) 2~ ft. Ib. torque.
behind the thni~ds. Apply a snail amount of non- (b) Insert dowel pin (6) in flange from rear and until
hardening gasket compound to the thnada Scnw it enters the notch machined into the guide collar (5).
cylinder (44) onto hub (3). Use a 1-inch squan bar ASSEMBLY OF BLADE BEARINGS ON
about 34 feet long as a wrench, applied to the slot in HUB SPIDER
the cylinder. Tighten the cylinder hard against the hub
(a)Mount hub spider (2) on propeller table.
(about 200-300 ft. Ib. torque). (b) Place a blade mounting "O" ring (10) on each leg
(6) Inspect the inside of the cylinder to be sun the of hub spider (3). Roll the "0" ring back towards the
"O" ring (45) is in place,
center of the hub.
(c) Inspect around the slots to be sure the bar has not (c) Install the blade mounting bearing (I)) over the hub
raised the edges which might cut the "0" ring of the
spider.
piston; Peen edges if necessary.
INSTALLATION OF
)a(NOTSIPring (46)
Install "0"
new and felt seal (47) in
CAUTION

piston (34). Oil these parts. Be sun the thin race is installed fint.
(b) Fit new pitch change block (48) snug in fork (39)
and install block on linksctew (19). (p) Install NEW like-numbered blade mounting split
(C) Install piston asnmbly (33) over cylinder (44), MB (9) betwem the bearing and the spider arm
Shoulder.
feeding guide rods (37) thru forks (39), and sleeves (41)
which must be fitted into the bushings of guide collar (e) Pull the bearing (8) and split ring (9) outward
clamp (7). Install washer (42) and nut (43) onto rod against the shoulder of the hub spider. Roll the "0"
(37). Torque to 20 ft. Ib. ring (10) into its groove behind bearing (8).
(8) Tighten set scnw (40) 2-3 ft. Ib. torque. Prick CLAMPS AND BLADES
punch around set scnw to safety. NOTE: le,oldet to osssnsble tL propeller
ord wt the piteh czaaurot´•ly, it is czdvc~n-
SETFING BLADE PITCH t(sOwns to speeiol propeller table hcrv-
use a

Loosen outer clamp screws (29) ing o sholt which with the propsllsr
(a) only. Apply air
or oil pressure to P"fP", to force piston agatwt IOW pitch
h~ flanBe. Air or oil (100
’min3 should be ovoilobe in the shaft to Ps~’
stop. Hold dds positidn and set on blade to proper oatuate tho piston.
(a) Mount the hub on the propeller table shaft, sealing gether closer. Also, the outer corner of the clamps might
with
the flange with "O" ring (11). Fasten with bolts or require filing by .005-.010 inch. (Coat filed ana
clamps aluminum lacquer.) (Bulletin 69 also covers this subject.)
(b) Fillthe blade pilot hole with grease as specified (e) Check the blade angle in low pitch again, as torqu-
under "GREASES RECOMMENDED." ing of the blade may have moved a
NOTE: Be no clia is t~ppsd klow the CHECK FOR G~YERAL OPERATION,
grease w this will upset the bQ1Qncs. FRICTION AND LEAKAGE
(c) Install blade (1) on the same pilot tube (4) from Cycle the pitch for possible friction.
which it was received. Place a hardening gasket com- Hold full prrssure~on piston and cheek for leakage
(b)
pound (commercial automotive type) around the blade past the piston "0" rmg [37) and cylinder
"0" ring
shank in tht shoulder radius.
(40). Spnad oil around these points as air bubbles will
(4) Install the correct matching clamp and counter- indicate leakage.
weight subassembly (14) with new clamp gaskets (19).
Fasten the clamp haves together with scnws (20), bolts
(22) and nuts (23). Tighten these scnws and check SETCT1ON III
blade for friction on the hub when rotated. Remove BALANC~
blade and comet for friction if too tight.
(a) Balance the propeller assembly before gnase is
NOTE: The pitali will be wt crfte+ the pro- added to the clamps, and check again after gnase is
1Mlt~ is COl~pbtdly ofter Wjlieh
Ih´• E~np bolts will bs to~qusd ond safstisd
added. Balance with pitch about ~idway between low
and high pitch.
(e) Install the lubricator fittings tig). (b) Either a suspension system or an arbor mounted on
knife edges may be used for balancing. In the event the
INSTALLATION OF CYLINDER
suspension system is used it is essential that the center
(a) Insert (ro,, ring (40) in the cylinder (38) groove of gravity of the propeller be located at or slightly below
behind the thnada Apply a small amount of non- the pivot of the balance equipment; otherwise maccu-
hardening gasket, compound to the thnadn Screw acies will nsult.
cylinder (38) onto hub (3). Use a i-inch square bar (c) Remove the end play from the blade clamp assrm-
about 3-4 feet long as a wrench, applied to the slot in the blies by driving identical small wedges between the blade
cylinder. Tighten the cylinder t~d against the hub clamps and hub spider, at identical locations.
(about 200-300 ft. Ib. torque). (d) Bolt propeller to balance arbor, or win balancer.
(b) Inspect the inside of the cylinder to be sure the procsduze
NOTE: The following op
"O"ring (40) is in place. plies only to bahnce arbor method
(c) Inspect around the slots to be sure the bar has not
raised the edges which might cut the "0" ring of the´• Check horizontal balance by laying slugs in corner
piston. peen ~dges if necessary. of blade and clamp. Record number of slugs nquired
for balance.
INSTAUATION OF PISTON
(f) With the propeller in horizontal position, apply
"0" ring (37) and felt seal (39) in 50-100 Ib. downward force to each bladetip. This takes
(a) Install new
dinetion.
piston (27). Oil these parts. UP the clearance between hub and blades in one
(b) Fit new pitch change block (41) snug in fork (32) (g) Check vertical balance with heavy blade up. Add
and install block on linkscnw (16). weight slugs to light side of clamps. Record number n-
(c) Install piston assembly (26) over cylinder (38), quind for balance.
feeding guide rods (30) duu forks (92), and sleeves (h) Rotate blade 1800 from horizontal position as noted
in "f’ above and apply 50-100 Ib. to each blade tip This
(34), which must be fitted into the bushings of guide
collar (5). Install washer (35) and nut (36) onto rod takes up the clearance opposite to that noted under "f’.

(30). Torque to 20 ft Ib. (11 Again check vertical balylcc. Record number of
(d) Tighten set screw (33) 2-3 ft. Ibs. torque. Prick waght slue;s.
(j) The final number of weight slugs can how be de-
punch around set scrm to safety.
termined for vertical baance. If the slugs under "g"
SETI~INC BLADE PFTCH and "i" an added to the same side of the blade, the to~H1
nquirsd for vertical baance is the avenge of "g"
(a) Loosen outer clamp scnws (22 o~lly. the slugs under
(6) With no air pnssure, set low pitch on both blades to opposite sides of the blade the-dif~aence between the

per aircraft speciiicatio~Tighten outer clamp scnws two numbers is added to the side requiring the greatest
(22) to 60-65 ft. Ib. torque Torque inner scnws (20) number.
to 40 ft. Ib. (L) Horizontal balance determined under "e" must be
(c) Witg air pnssun, iacnase pitch to high stops and maintained by properly dividing the slugs nquired under
check blade angl~ ’(i" between the two blades.
(6) Check the blade against in the clamp by
turnine~ (1) Attach the slugs to the clamps with screws and again
torquing the blade to 167 ft. Ib. Use a blade bar and check horizontal balance. Safety with win. Do not at-
a weight attached to the e~d. If the blade Inoveq or tach mon than 4 slugs with each pair of screws.
rocks t3 the clamp, the clamp must be and the (m) Add equal amounts of grease to each blade, holding
difficulty nctif~d. Expaimce has shown that the horizontal b~alance constant, until clamps are completely
clamp gaskets (19) may pnvent the clamps from full, as evidenced by gnase starting to come out around
ening or~the blades. These gaskets can be trimmed at circumfennce of hub spider at "0" ring. Avoid blowing
the outer hole slightly to allow the clamp to come to- out "0" rihg and gaskets with excessive pressun.
 SECTION IV. WEAR TOLERANCES
Table II. TOLERANCES OF WEARING SURFACES
MODELS BHC-92ZF-?0~ 6r HC-9aZK-8D, -8L

Roplaeo It Dim´•n~ion
Port or SgoJf/ad i~ Abovo or 8´•low
No. of
Max. Min. Max. Min.

1 A-1308 Pilot Tub´• O.D. I I"nr 1W inch 1.7185 1.7180 1.7165

I Outorl inch 1.7203 1.7197 1.7187
2. A-1308 Pilot fub´• M´•mion Bryond Hub Saidor 3% +Y( sM -tCe 345 +W -9-

3. Blado Bulhlng i. 0. 1.7225 1.7215 1.7240

4 Ag61 Plo~tic Bu,hing in Pl~ton. i. 0. 3.781 3.780 3.790
5. 8-806 Cylind´•r,O.D. 3.778 3.776 3.773
6. 8319 Bu~hlngl m Guido Collar, i. D. .506 .504 .f10
7. Ag21.1 RodSioovo,O.D. .5002 .4998 .4995
I A-811 Fit k05A BloJr to Fork
9. &Ilanc´• toIoranco 1 dug A-1305
10. Blado track’
11. lod´• End Play .060
12. Ilado Foro and Ah Movomont at tip .100 .068 .110

TABLE III. BLADE REPAIR TOLERANCES TABLE IV. TORQUE VALUES FOR IM-
PORTANT SCREWS, NUTS,
rcnn AND TWREADED PARTS
*ngk Ang~cmt Wldch IL*L~wu
~adkn Min. I*o´•. Min. Mo~ (Mln.) ~M1´•.)

8447 1 8447-124L (hrducl´• 36)

8
12
1.110
137
2667
1.304 r*n
Terq~ Vol~ CT
18 31.3 31.9 .158 .222 6121 .798
11 2d3 -.032 .032 6~091 ~17
30 21.93i1up 21.9 -.152 -.098 1460 .354 Ouhr Clomp Balk, %-20 60´•6~
36 18.8 19.2 -.227 -.163 1196 .231
InnrClomp SocL´•t Sann, 3C-24 40
8847 Counhmoight Su´•w, Z(rlO 65
B 1110 2.668 "F" and "K" Maunting Suom, l~i-20 60´•70
11 5.928 1.304
Cvllndr 904300
20 30.5 .158 .222 d318 .757
26 25.5 26.1 -.072 -.008 6.080 .497 Pkcon Guid´• Rod Nut, ~c10 20
32 21.9S´•tup 21.9 -.192 -.128 5.448 .355
38 18.8 19.2 -.242 -.178 l188 213
Unlucrm, ~-20 45´•50

C;LL r...

.6.
 MANUAL NO. 110

(CORRECTI ONS)

(1) PAGE 6, TABLE IV. TORQUE VALUES, STAMP THE FOLLOWING

UNDER TABLE IV.:

"ALL TORQUES ARE VALUES BASED

ON NON-LUBRICATED THREADS.
TOLERANCE ON TORQUE IS 10%.
UNLESS OTHERWISE STATED."

(2) PAGE 7, SECTION V, LUBRICATION, B. i.

DELETE "MZL-G-3278"
STAMP IN "MIL-G-23827"

(3) SUPPLEMENT NO. 1 STAPLED IN BACK.

(4) SUPPLEMENT NO. 2 DATED SEPTEMBER 21, 1965,

AND PARTS LIST HC-92iJK-1D DATED JANUARY 18, 1965
STAPLED IN BACK.

ALL MANUALS NOS. 110

CORRECTED AS OF 10/14/66
 6. Stroma LT-1 (2-815 Grease)
SECTION V
Union Oil Co. of California.
LU BRICATION 630 AA
1. Lubriplate
Fiske Brothers, Toiedo, Ohio.
It is recom-
A. General Properties of Grease Required This grease will bleed oil in hot weather.
for lubrication of the blade-pilot tubes
mended only
Any grease used must have the following properties: but not the blade bearings.

(a). Waterproof. 8. RPM Aviation Grease No. 1

Standard Oil Co. of California
range between 150 F and 1500
(b), Temperature
F; or -400 to 1000 F if operation is in cold g Lubriplate 707
climate. Fiske Brothers, Toledo, Ohio.

(c). Freedom from separating oil from soap base iO Mobilgrease Aero Lo-Hi PD-535-K
due to centrifugal force or high temperature. Socony Vacuunl Oil Co.
(d). Low friction. 11. No. 81 Medium Grease
Keystone Lubricating Co.
B, List of Approved Greases, by Spec or Name Texaco Regal Starfax Special.
12.
1´• Illlllr 13. Molub-Alloy No. 2 Grease 100 F.
No. 1 Grease --250 F.
2. Stroma HT-1 (2-801 Grease)
Union Oil Co. of California. Imperial Oil Crease Co.
Los Angeles, California
3. Gulflex Moly for blade bushings.
14. Germany--Calypsol 11728
4 Gulflex A. GermanCalypsol Company, Dusseldorf.
This grease is recomnlended for the blade ball
bearings as it will not bleed oil in hot weather.
C. Proper times and amounts of grease are
5. RPM´•Aviation Grease No. 2
mentioned during assembly procedures
Standard Oil Co. of California.

REMEDIES
SECTION VI SERVICE TROUBLES AND
L )robobl´• Cou~´• R´•mody
to
If rpm fails to ina´•ou but will S´•( Irlkt ralvo in go*ornor to plo*id´• nocessory prossuro, up
CAILURR
r´•duc~ ton ail promuro. 275 mi.
Or PI’ICn
TO CnANOE below. Isdate frictian in
If rpm chango in both 533 "Excussiw Friction in Hub Mechanism,"
blade separately,
is duggbhl Exc´•uiv´• frictian in each blade by uncoupling piston and testing each
hub mechanism. boforo toaring prapoll´•r down.

N´•wly-indall´•d gorornar hasr Chachandcorrect.

mong dlroctian of rotation, or
has bypass plug in wrong hole.
ham hub spider.
pilot tubo has slippod out dighe T´•ar down and ch´•JI distance pilot tubo extonds
U(CEJSIVI FIICIION with a
ShouM bo 3W inchr If moro, remoce pilot tube and replace
IN nut MRcnANlsM ly and b rubbing hard against
end of halo in blade. tubo.001 in. av´•n~ at tho hub end.

PdlA pilot tube and blado bushing with fine emery papor and r,
Node bushing rix´•d on pilot
tubo. omomblo.

Elado ball boarings unusually Roplaco boarlng.

rough OF brdcen.
Chwk pam individually. If tightness b encountered in diding pam,
Friction in various moving pam
of pitch control mechanism. increasecl´•arancr~lghdy. Apply oil extornally to moving porh
low pitch ~top. Either
3knk rpm too low. Govomor has high rpm stop, as well as propoiler
IMPROpER RIM limit maximum rpm. To d~
th, gorrnor or tho proFnllr stop may
tormino which b causing trouble, open the
throttle and move governor
control bace and forth dowly.
b reached, propeller
If maximum rpm b roached BEK)RE governor stop
If this is the eer. loosen blade clamp
stop is probably limiting rpm,
Reduce blade angle about 10
outer bolts and ratato blades in clamps.
II for rpm increase. (10 ´•qual~ jj~
~achblad´• mot.)100
inch circumference at

as govornar stop is reached,

reached AT SAME TIME
rpm b
the maximum rpm. Read/ust gov´•~-
governaF stop i? probaMy limiting
nor stop to obtain proper rpm.
Ono turn of governor stop screw ´•qwle
about II rpm. Turn nap rr´•w out to increase rpm.
t Oovornor stap should limit hrgh rpm, with propeller stap
beyond. This allows for variations
reached at 50
in engine power without
to 100 rpm
affecting maximum rpm.

-7-
 Troublo probable Cous´• R´•m´•dy

Statk rpm too high Roduco by scrowing governor stop in, ono turn for oach 17 rpm
reduction.

sulOlClo Air troppod In proonilnroduot- Pr.*i*on lould b´• inaorporold in ´•n~in´• to allor hopp´•d .ir to B
(Wh´•n govarnor ing piston or in ´•ngino saft. ~rap´• from systom during ono half of tho pitch chango cyclo.
control is tccrcir propollor by changing pitch or foathoring boforo wch flight.
changad rapidly
or rough air Gousmor pr´•uun too low. Adiust govornor roliot prossuro r that rate of pitch chango is th´•
is oncountamd,) rmo in both dir´•clioru.

Exc´•sivo Mdion In pitch Sao "hc´•uiv´• Friction in Hub Mocannsm."

change mochanium.
Govnnor laclu rfficlont Chango m adlustspoodor spring. This gives governor mar stability,
damponing, but mokr pitch control maro wndtiv´•, whick, may in turn r´•auiro
rrigging of central to offrt highor spring rate. Changing to stiffor
spoodor spring should a done only attor all othor factors are ch´•ckod
and corroctod.

OIL UAKAOI Faulty "0" ring rab cu fdlomt Oirsrmblo and inspoct "0" rings and tho surfacns thoy snal. Rlplacn
hont of atwoon
roar cono "0" rings it dofoctivo. lIoplacn cylinder if surfoco is scratched or nick~d
ongino shaft and hub, in ar´•a whore "0" ring Ilid~ Uls gasket compound on cylinder
Ilotwoon hub and cylinder. thr´•ads whon replacing. Foan down raird places courd by tightoning
lIotwoon piston and cyllndor at cylindor with bar.
at front of piston,

ORIAS1 UAKAOE I Oroar Ioais past damp ral clamp aoth and roplac´• ga~k´•k. Standard thici(noss of gaskot
(Onlv sourco of gaduh h .OJO, but .060 gaskots ar available In car .050 gask´•ts am not
gcaco Ioakaga comprrrd sutflciontly to hdd.
b blaao b´•arin~)

Gnor Iaaks tram atwaon Inscrba blada with inh pencil to assur corroct blado angle on r~-
or
blodo and damp. asrmbly, and blado and clamp. Add C(olk´•t compound in
romova
radius of blodo bun. Roplaco blado and clamp.

CND CUV Suildup of manufacturing total and play at .060 b pormimiblo.

IN ~LADCS to(oroncor

bUDI tRACK Toi´•mnc´• of W inch h allowod.

SLADI Rt ON
nut nlot tvlL
With manufacturing ta´•oanca, tho maximum that the blado tip con
a moml far and aft h .068, without groar in blado clamps and
8
b´•arinqr Wa groar, tho mowmont b nil. It blado tio tar~ond´•aft
maromant incrrnr to .100 dry, blade nquim factory r;bushing.

PART II PARTS LISTS

SECTION
INTROOUCTlON

The first column jn each parts list is the figure and If you do not know the part number, you may refer to
index number. ’fhis refers to the illustration and index the applicable illustration and then find the index num-
number of each part. For example, if you are ordering
bor assigned to it(17). Look hn the parts listing, and
a blade clamp assembly and want to see~ow and where
it locates on the genenl assembly, this cllumn indicates mad tht pan number, 838~8.
Figure 3 index number 17. Looking at figun 3 in the
group assembly Parts List, index number 17, the appear- HOW TO ORDER
ance and location of the clamp assembly may belasily

bounc~ aim the details of all parts contained in this sub-

assembly.
It is important that the Part
Model Number be given when
Number, Part Name and
ordering parts.
C

’8’
 LIST
GROUP ASSEMBLY PARTS
Modd BnC-92ZF-101

Na Roquirod
Codo No. Car, No.

Wad´•

HUB SPIDER UNIT

c

2 840´•4~ 1
SpM´•r Hub 1
3 C-13016
k1308 Tub´•, Pilot 1
4
k1338 Spinnr 1
AN7~J
n´•xn´•ad----------------- 1
6
8319 Guklo Collar Unit 1
1
A-957-1 P~n, OuM´• Cdlar Dmol

rssocurED PARTS, nUI 2

k1303A Booring, lad´• 2
10
JplH.-´• 1
11
Ring,lad´• 1
11’5 PRP´•POPd "Q’ Rln(l, Shaft
Bolt, Hox H´•ad, Hub Mounting -L´•----------
6
14 AN8H7A 2
.5002x1 Pin, Danlor Dow´•l 6
15
16 AN060´•816

838-48 ASSEMBLY, CLAMP 2

17
ta C-1301-1 Clamp 2
A-295 Unluam 2
19
A-2BJ Pin, Lnnuaaw Stating 2
20
X~010 FHting, Z´•rk 1
11
bt 3513 Counhrmight 1
22
A´•65 Pin. Counkfil´•igh( Sk~ing 4
n3
Sum, Counhnnight Sockot 1
Zlc20x3~
A-28S Pin. Cnunhr*rnIohI SoJul Sam Staking
26
26 k1306 Ga~rr Clamp 4
A-282 Scr´•w, Clamp Sockut
17
AN38052 Pin. Sockot ScnrrCo~kr
28
Sam Clamp Fmy 4
29 KrlOx2W
AN363-720H.T. Nut, Clamp R´•xloJI
30
ASSOCIATED PARTS, CUMP Nnd´•d
Ar

A-1305 W´•ighk, BolaK´• 1

31
Sa´•m,W´•ight
32

33 b828
ASSEMI)LY.´• PISTON I
b966 Pbton ´•Unl 1
34 Pbton
35 b966 Dot. ~1 1
A862 ~nhinO, Paatic 1
36
A8261 Punk Rod 1
37
A.IICF Psn, Rod Staking 2
38
k811-1 Fork 1
39
Sockot Hoad Sam, Pork
40
k821-1 Slum, Rod ~----L----- 1
11
A-965 Warh´•r 1
42
AN361120 Nut, Floaiook
43
ASSOCIATED PARTS, HYDRAULIC 1
44 8806 Cylindor 1
PRP-000´•13 I~CT’ Ring, Cyllnd´•~ 1
45
PRP-001J6 "o" Ring, Pbtoa 1
46
AglO S´•al. O~- 1
47
A-9IA
PHrh Chango
48 1
ASSU~LV, SPINNER
49 837-3 1
Docm ----´•--L--
10
50 61337
Mouncing 1
St L~N52M1031R7
Buiklmad 1
52 C1336
AN7CS Bob, Hu H#d 1
53
AN060116L 1
W Nut, Nulock
55 AN361~8
WSEMRLY. SPINNER
49 snJ 1
.C1337-T
Dorm(Polbh´•d) 10
50 5a´•m, Domo Mounting
ANSlbC1031R7 1
51
C-1336 1
52 Bolt, H´•x H´•ad
AN1CS 4
53 W~nh´•r
D 54
55
AN060´•4\6L
AN36U28 Nut, Pioxlock
4

-0-

’I
 SECTION II

GROUP ASSEMBLY PARTS LIST

Modol nC-9aZK-8D, -8L

Codo No. Pal) No. Drcription -80 -8L

1 Blad´• ---I--
--´•---------1 2 2
84032 ASSEMBLY, HUs 1
2 I

01314-3 Spidm, Hub 1

3
k1308 Tubo, Pilot 2
8318 Guid´• Cdlar Unit,, t
5
A-1332-2 Pin, Staking 2
6
ASSEMBLY, HUB 1
2 8U~32L __.,_..____

C-l 31C3 Spid´•r,Hub 1

3 I-~-
._,_,___..__I

A-i 308 Tub´•, Plot 2

8319 Gukd´• Coilar Unit 1
6 A-1331-1 P~n, Sloking ,...~---..1.
2
ASSOCIATED PARTS, HUB
8 A-i 3034 8´•o~ing, 81odo 2 2
2 2
9 k1331
~9´• Split Blad´• Saal 2 2
10 PRP-009-7 Ring, 1.

PRP-902-32 "O" Ring, Shaft 3991 1 t

11 ....~...---I----------

12 k1333 Lit, Mounting 6 6

13 b1322 Shim 1 1
11 83831 ASSEMBLY, CLAMP- 2
IS 01301-2 Clamp 2
16 A-295 1 Unlacr´•w ,--1-
2
17 A-285 I Pin. Unhcnw 2
18 ~M10 FHHng, Z´•rlt 4
19 A-1306 I G~1, Clamp 1
A-282 Scrow, Sockot Hood 1
20
21 AN38052 Pin, Cothr 4
22 Scrow, F´•rry 4
23 AN363J20 H.T. Nut, R´•xl#~ 4
14 83835 ASSEMBLY, CLAMP 2
IS 01301-4 Clamp- 2
16 A-295 Unkuaow 1----1
2
17 A-285 Pin,. UnkKnw- 2
18 1n010 FHHnO, Z´•rk .-1-.1...-..
2
19 k1306 Orukot, Clamp
20 kZ12 Scow, Sockot Hoad .I.I

21 AN380´•3-1 I Pin, Cottor 1-.

4
22 fC20x2H Saow, Pony 4
23 1 AN363-720 H.T. Nut, n´•xloct 1
ASSOCIATED PARTS, CLAMP
24 A-1305 Waight, Llanc´• I
At N´•sd´•d
25 ANS01A10-6 I Saow, Woight 1 4
26 BBZB-BL I SUBASSEMBLY, PISTON JACK 1
27 b966 1 Pi~ton Unit 1
18 b966 Dot. 1 I PWon -I---.~
1
29 ABBE B(ahing, Pladk 1
30 Aa2~ Pud Rod I
1
31 A-I1CP Pin, Rod Staking ,I--.. ....-I
2
32 1 AB211-l I Foc´•k 1
33 Scrm, Sat --.I------ 1 2
34 1 Ag?F1 Skm, Rod... 2
35 I A-PbS I ´•---´•1 2
36 AN36C720 I Nut, F1´•xloc~ 2
26 b82&8 SUBASSEMBLY, PISTON JACK 1
27 b966 1 P~ton Unit. 1
28 1 8966 Dot. 1 I P~on 1
29 1 ASbZ Llhing, Pla~tic I-.I----
1
30 A8268 1 Rnh Rod, 2
31 A-IICF Pin, Rod Staking ,1.
2
32 Agll-l I Fo~ I-
1
33 103nla(e Scnw, Sot 2
31 A-827-1 1 Skm, Rod 2
35 A´•965 1 Wa3Hr 2
36 1 AN361720 I Not, R´•xlock s
2
ASSOCIATED PARTS, HYDRAULIC
37 PRP-001Jb "CT’ Ring, Pl~ton 1 1
38 SSgB Cyllndr 1 1
39 A-810 Jool, Polt, 1 t
40 PRP-909-13 "O" Ring, Cyllndr 1 1
41 1 A-PS´•A locic, PHch Chango 2 2
42 83M ASSEMBLY, SPINNER 1 1
43
44
1 C885
CgSaJ
Adaptor, Spinn~
Domo, Spinnr- I
1
C
45 1 ANS26C1031RB Jcnm, Domo Mounting -I--^,.
01 14

-LO-
 31
31

37
t= h--- n
33
/n 39
17
18
16

21

6
~-=Z_LL_ 30
lo
c
A.
ENGINE SHAnae~,
12
~e
37

~s b
f 7
i \k3
11
1~ IS
r

I U/ll II16 1
I
31
5

P
13 U 1
b ~I-r%UI; 3910\
33

34
37
ii 7 38

t
49
P’ "~j

34
 ’49

15 24

23

18

15

/I h- C´•
P
16

19 j
10
10
fX
11 s=~ ,44 11 H
43

i 44
ENGINE SHAFT
´•aP~
Q
13

i
8/ II
a4 (3
11 CC
32
33
31 30 96
31
22
37

27
 SUPPLEMENT NO. 1
MANUAL NO. 110

INCLUSION OF PROPELLER MODEL HC-92ZK-1D

INTRODUCTION:

The HC-92~K-1D propeller is nearly

identical to the HC-92ZF-1D1
for the shaft mounting
propeller listed in this manual, except
provisions and a few other details.

The differences are listed below:

Model Model
HC-92ZF-1D1 HC-92ZK-1D
Code
part Number Part Number
No. Nomenclature

840-48 840-32L
2 Hub Spider Unit
14 Mounting Bolts AN8H7A (6) A-1333(4), A-1333-2 (2

33 Piston Assembly B-828 B-828-8

34 Piston Unit B-966 B-966-8
35 Piston B-966 Det.l B-966 Det.l
36 Bushing, Plastic A-862 A-862
37 Push Rod A-826-r A-826-8

38 Pin, Rod Staking A-114-F A~114-G

39 Fork A-821-1 A-821-1
40 Screw, Socket 10-32x3j16 10-32x3/16
41 Sleeve A-~27-1 A-827-1
42 ~asher A-365 A-965
43 Nut, Flexlock AN365-720 AN364-720

is the 835-6P or 835-16 for the HC-92ZK-1D.

The spinner
 ~I!?.RTZELL Il~C
PIQUA, OHIO

SeptemLer 21, 1965

NC, 2
NO. 110

T~-.e Ii:-3~.:K-1 is identical IIC-92ZKll, except that needle

to the
i,e~ri:-ts ar9 incorporated into the blade shanks, replacing the
oirc~e of the bronze bushin~s, The 84O-93 hub spider unit
:e and the A-18i~-( pilot tubes replace the A-1308.
~he huhs are identical.

Trre Sla~e siianks incorporate needle bearings, and the blade model
car~-ies the prefix ’’W" to identify the shank configuration.

.-,ttacheci Darts list for the HC-92WK-1D propeller which lists

is a

all current ~arts as of January 18, 1965. Most of the bolts now
carry Wartzell. part numbers instead of commercial or AN numbers

since ~oirs which are obtained commercially cannot be relied upon

to iiieet tile stren~th requirements imposed.

’iable IT, Tolerances of ~Jearing Surfaces is revised to read as

fullows:

Replace if dimension
Specified is above or below

~ax Min Max Min

i.. A-1884 Pilot Tube O.D, f 1.7185 1.7180 1 1 1.7165

(;nner 1-1/8 inch) j
la. A-1~84 Pilot Tube O.D. f 1.3760 1.3755 1.3740
i
f~-
(Gutel- 1-1/~ inch)

2, Pilot Tube, j 3-3N 1116 j 1-9/11- 1/1~ i 3-3/11~ 1/8

Len~th extendin~
beyond hub spider

All ot~er items listed in Table II remain the same for HC-92WK-1 as for
HC-92ZEC-1.

Page 1 of 1

r
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 TABLE OF CONTENTS

Page

PART I OVERHAUL INSTRUCTIONS 1

Section I. Introduction 1

1-1. General 1

1-6. Purpose 1

Section II. Overhaul Instructions 2

2-1. Special Tools Required 2

2-3. Disassembly 2

2-11. Cleaning 3

f 2-12. Inspection 3

2-13. Testing 3

2-14. Repair or Replacement 3

2-15. Lubrication 5

2-16. Reassembly 5

Section III. Test Procedure 8

Section IV. Lubrication g

PART II PARTS LIST 9

Section I. Introduction 9

Section II. Group Assembly Parts List 10

 PART I OVERHAUL

SECTION I

INTRODUCTION

1-1. GENERAL

1-2. This handbook contains overhaul instructions

"rate I!ublication. Repair parts of the propeller are

listed In the Illustrated Parts Breakdown.

for the Model HC-B3Z20-2A variable-pitch, feather-
ing propeller manufactured by Hartzell Propeller, 1-6. PURPOSE
Inc., Pique, Ohio. (See figure 1-1.)
1-7. The Model HC-B3Z20-2A Propeller Is a three-
1-3. Sections I, II and III of this handbook contain blade feathering propeller designed for engines in the
overhaul and test instructions for the model HC- 300 to 450 horsepower range. It is designed to use
B3Z20-2A Propeller. engine oil pressure for decreasing pitch and counter-
weights to Increase pitch. A spring assists the counter-
weights during the feathering operation. Centrifugal
1-4. Overhaul and test procedures for models inclu-
stops prevent feathering of the propeller due to action
ded Section IV are the same as the proceduresdiffer-
in given
of the spring when the engine Is stopped. At speeds of
In Sections II and III, except for the specific
over B00 rpm the stops are removed by centrifugal
ences noted by the applicable Difference Data Sheets.
force, allowmg the propeller to be feathered at any
time. The design of the pitch control mechanism re-
1-5. and Service Instructions for the
Operation quires an oil pr’essure of 200 pounds! which is supplied
Model HC-B3Z20-2A. Propeller are provided in a sep- by a governor mounted on the engine.

E i

ORIGINAL
As Received Sv
.:_i
ATP

Figure 1-1. Model HC-B3Z20-2A Propeller, General View

 SECTION II

OVERHAUL INSTHUCTIONS

2-1. SPECIAL OVERHAUL TOOLS REQUIRED. c. Remove the piston (28). From the piston remove
the "0" ring (129) and felt seal (30).
2-2. Special tools required for the overhaul of the
Model HC-B3Z20-2A propeller are listed in Table I. d. Remove the outer mushroom plate (31) by tak-
ing out the screws (32). Remove the front split ring
2-3. DISASSEMBLY. (See figure 2-1.) (33),thus exposed. This permits the feathering spring
sub-assembly (34) to be withdrawn through the front
2-4. REMOVAL OF PROPELLER FROM ENGINE. Of the propeller.

e. Remove propeller shaft safety pin (49).

NOTE

f. Use Special Tool No. B-840, the propeller shaft

In most cases the propeller will be received for
nut wrench, to
unscrew the propeller shaft nut (51).
overhaul in a partially disassembled condition.
This does not remove the nut, but it causes the nut to
If this is the case, perform only as many of the
force the propeller off the engine shaft. When the
following steps a. through f. as are necessary, propeller is off the shaft, remove the hub mounting
checking to be sure that all parts are present, cone (43), the hub mounting "O" ring
(44) and the
rear bulkhead assembly (58).
a. Remove spinner dome assembly (54) by taking
out the screws (55), and the screws (57) which
attach the fluid delivery tubes (56). Remove the NOTE
fluid delivery tubes (56).
If the propeller is not to be overhauled immed-
iately after removing it from the engine, it may
be reassembled at this point for storage or ship-
W A R N I N C ment to the overhauling activity by following,
in general, the reverse order of disassembly.

2-5. CYLINDER.
Feather propeller before removing nut (21).
(Use blade bars to compress feathering spring a. Use a i-inch square bar as a wrench to unscrew
so that high stop pin (61) can be pushed out to
the cylinder (45). From the cylinder remove an "O"
allow propeller to be feathered.)
ring (46).
b. Remove the nut (21), using Special Tool No. B- b~ From the piston guide collar (47) remove the
842. Remove the screws (22), nuts (23) and washers
screws (48).
(24). Remove the three link pin assemblies (25) by
taking out the screws (26).
c. Removalofthe cylinder (45) also frees the pro-
peller shaft nut (51). From the nut remove the hub
Table I. SPECIAL OVERHAUL TOOLS puller ring (50).

2-6. CLAMPS AND BLADES.

Part Procuring Service 1
Nomenclature
Number Stock Number
a. With ink and a scale, mark matching lines on the
B-840 Shaft Nut Wrench blades (1) and the clamps (3). Record the blade
serial number with clamp number for each side of the
B-842 Wrench, for A-880-1 propeller.
Nuton Spring Assembly

B-843 Table Spindle for Pro- b. Remove the screws (5) and the clamp screws
peller Assembly (6), washers (7) and nuts (8) from the clamps (3).
Remove the clamp halves and the blade clamp gaskets
B-844 Fixture for Pressing
(9). Remove the blades (1).
Pilot Tube in Hub

C-845 Fixture for Assembly c. From the clamps (3) remove the lubricator fit-
of Feathering Springs tings (4). Remove the automatic high pitch stops (10)
by taking out the bolts (11), and the balance weights
BT-222 IAssembly Tool for
(14) by talring out the screws (15).
Pressing A-1852 Ring
on C-1853 Hub Spider
I d. Remove the cotter pin (12).Remove and discare
BT-223 Puller Tool for A-1852 the counterweiffht mounting screws (13). These
Ring screws should be replaced immediately with new ones.

Torque to 65 ft. Ib. Safety with cotter pin (12).

 2-10. HUB SPIDER ASSEMBLY. If inspection of
CAUTION a the hub spider subassembly shows that any of the hub
pilot tubes (53) require replacement, they may be
pulled from the hub spider (52) by means of an appro-
priate bearing puller.
In normal overhaul operations it is not neces-
sary to remove the counterweights from the NOTE
clamp and counterweight assembly (3). If the
counterweights are defective, use a complete
Do not remove the hub pilot tubes unless Spe-
new clamp and counterweight assembly (3) at cial Tool No. B-844, the fixture for pressing the
overhaul.
hub pilot tube into the hub, is available to aid
in installing the replacement tube.
e. Remove the bushing (16) by taking out the cotter
pin (17). This also frees the pitch change link (27). 2-11. CLEANING.

a. Wipe all dirt and grease off all parts with a

2-7. BLADE BEARINGS.
clean, lintless rag, keeping the parts separated so as
not to allow them to scratch or nick each other.
a. Slip wire ring from groove formed in inner bear-
ing race(19) and remove two halves of inner bearing b. Clean all parts except the felt seal (30) with soI-
race (19). (It
is assumed that the balls have been re-
vent, Specification P-S-661a, and blow dry with com-
moved when the clamps were removed). pressed air.

b. Using Special Tool BT-222, drive guide ring (18) c. Apply a rust preventive compound to bearings
in slightly towards the center of hub (52) only enough and all parts which are to be stored or set aside for
to uncover wire ring (68),which can then be removed. any length of time.
Using Special Tool BT-223, pull guide ring (18) from
hub (52). Remove two halves of outer race of bear- d. Wrap the parts or keep them covered to prevent
ing (19). an accumulation of dust or dirt before reassembly.

c. Remove "O" ring (20). 2-12. INSPECTION.

2-8. FEATHERING SPRING SUBASSEMBLY. a. Inspect all wearing parts according to the toler-
ances specified in Table II. Replace any part not
coming within the specified limits.

CAUTION b. Inspect the blades according to the tolerances

listed in Table III. Replace a blade which falls below
the listed minimum dimension upon repair.

Do not attempt to disassemble the feathering c. Visually inspect all metalsurfaces. Replace or
spring subassembly unless Special Tool No. refinish any bearing or wear surface which has a vis-
C-845, the fixture for assembly of feathering ible nick, dent or other distortion.
spring, is available.
d. Magnaflux all steel parts.
a. Place the assembly in the fixture and compress
2-13. TESTIhTG. Testing of individual components
the feathering spring (37). When the spring is com- is not feasible.
pressed, slide the rear retainer ring (36) back on the
pilot tube (40) and remove the rear split ring (35).
This allows the rear retainer ring (36), the spring 2-14. REPAIR OR REPLACEMENT.
(37), the outer mushroom bushing (39) and the outer
a´• Remove all rust, galling and nicks from the hub
spring mushroom (38) to be removed from the pilot
spider arms with crocus cloth or very fine emery
tube (40).
paper. Rust, galling and nicks are stress raisers
which reduce the fatigue life of the hub. Do not polish
b. Remove the pilot tube "O" ring (41) and the unless necessary, because the hub surfaces have been
stop screws (42).
put into compression by rolling.
2-9. RING, STOP AND BULKHEAD ASSEMBLY. b. A,.,,tter of procedure, replace all "O" rings
and the felt gasket (30) with new parts at reassembly.
a. Remove the bolts (64),washers (65 and 66) and Replace all cotter pins at reassembly.
nuts (67) to free the automatic high pitch stop assem-
blies and the anti-icing ring (63) from the bulkhead c. Replace the counterweight mounting screws
assembly (58). (13) at reassembly with new parts. Use only the spec-
ified parts, as their strength has been carefully deter-
b. Disassemble the high pitch stop assemblies by mined and is correct for the application.
removing from each the cotter pin (59). This allows
the spring (60) and pin (61) to be removed from the d. Repair damaged blades in accordance with
bracket (62). standard Air Force procedures.
 i. Blade
2. Propeller anti-icing shoe
3. Clamp and counter-
weight subassembly I\

~i"p
4. Lubricator fitting
5. Socket head clamp screw
6. Ferry head clamp screw
7. Washer
8. Nut, self locking ~8
9. Blade clamp gasket
10. Automatic high pitch
<S -´•C\~2
stop
9
11. Bolt
12. Cotter pin
13. Counterweight

14. Balance
screw
weight
mounting 319\6 2‘7
1.5. Screw 20
16. Bushing 5
~o t
17. CotteY´•pin 0’166 \1 53
18. Lock ring o,62
64
19. Blade mounting bearing 63 ,52
20. Blade mounting ’LO" ring
49
21.
2s24

.28notusNiP
Set
23. Nut screw59
Flat washer

435048 hi4645
24.
44
25. Link pin assembly
26. Screw 69
27. Pitch change link 51

29. "0" ring

30. Felt seal Y
31. Outer mushroom plate 35
32. Screw 36
33. Front split ring
37
34. Feathering spring
subassembly S
35. Rear split ring
36. Rear retainer ring 38
37. Feathering spring 33
42
34

I
38. Outer spring mushroom
40 32
39. Outer mushroom bushing
40.
41.
Pilot tube
Pilot tube "O" ring
41~0
42. Screw 25
55
43. Hub mounting cone
a
44. Hub mounting "0" rinff 30 57
45. Cylinder 29
46. Cylinder "O" ring
47. Guide collar
48. Screw
49. Propeller nut safety pin 56
50. Hub puller ring
51. Hub retention nut
52. Hub spider
53. Hub pilot tube
54. Dome assembly
55. Screw 58. Bulkhead assembly 62. Bracket 66. Washer
56. Fluid delivery tube 59. Cotter pin 63. Anti-icing ring 67. Nut
assembly 60. Spring 64. Bolt 68. Wire ring,
57. Screw 61. Pin 65. Washer guide retainer
69. Bushing

Figure 2-1. Model HC-B3Z20-2A Propeller, Exploded View

 Table II. TOLERANCES OF WEARING SURFACES

Replace if dimension is
Item Specified above or below
No.
Part or Description of Measurement
Max. Min. Max. Min.

1. A-1308 Pilot Tube 4:i;’9’7"’’ 1 I

2. 1 A-13Q8 Pilot TubeAssembly, length
extending beyond C-1351 Hub Spider
3. Blade Bushing I.D. 1.7225 1.7215 1.724
4. C-1451 Piston, A-862 Bushing I.D. 3.782 3.780 3.790
5. C-1451 Piston, A-946 Bushing I.D. .3765 .3755 .3795
6. 1 B-854 Cylinder O.D. 3.778 3.776 1 1 3.773
7. B-86S-1A Pilot Tube Diameter O.D. .735 .734 1 1 .731
8. A-1365 Mushroom Bushing .738 .736 .741
9. A-866 Spring Retainer O.D. 1.248 1.246 1 1 1.242
10. B-14P2 Collar, Bushing I.D. .510 .508 .515
11. A-861-3 Link Arms I.D. Small End .3755 .3750 .3785
12. A-861-3 Link Arms I.D. Large End .5635 ,5625 .5645
13. A-914 Bushing I.D. .502 .501 .504
14. A-944 Bushing O.D, .5620 .5615 1 1 .5600
15. A-304 Link Screw O.D. .5005 .4995 .4970
16. Feathering Spring Assembly compression 450 min. 650 min. 400 min. 600 min.
load (pounds) Extended Compressed Extended Compressed

17. Blade Pitch Setting, Low Pitch 16-1~LO$-00 -1~LO, @30"Sta.; t .1" Between Blades.
18. Blade Pitch Setting, FeatherinlS 86" Max., 85" Min.
19. Balance Tolerance I 1 Slug A-1305
20. Blade Track +1/16
21. Blade End Play .060
22. Fore and Aft Movement of Blade Tip .068 .100

2-15. LUBRICATION. 2-17. HUB SPIDER ASSEMBLY.

If the pilot tubes (53) were removed from the

a. Lubricate the blade pilot tubes with grease, Spe-
hub spider (52), it is necessary to use Special Tool No.
cification MIL-G-3278, or with greases listed in section
B-844 to aid in replacing the tubes. Place the hub
IV. spider on the spindle of the fixture, with the emptly
pilot tube hole pointing upward. Replace the remov-
b. Lubricate the blade bearings and other moving able supporting member of the fixture.
parts of the mechanism with grease, Specification
b. Place the fixture and hub on the table of a 25-
MIL-G-3278, or with greases listed in Section IV. ton press, and press pilot tube into hub spider for a
depth of 2-Y4, inches, or until 3-~ inches .010 ex-
c. Proper times and amounts for application of tends about end surface of branch of hub. Be sure the
grease are mentioned as necessary during reassembly pilot tube enters hub squarely. Use spacer sleeve fur-
procedures. nished with Special Tool No. B-844 to maintain 3-3,~,
inches. NOTE: The tube must have a press fit of
2-16. REASSEMBLY. (See figure 2-1.) .002 .003.

Table III. BLADE REPAIR TOLERANCES

10151-8 Blade

Thickness Width

Radius Specified Minimum Specified Minimum

18 .970 .921 6.265 6.080

24 .735 .689 6.520 6.303

30 .560 .515 6.430 6.164

36 .470 .418 5.990 5.612

42 No Limit No Limit
~L.e i.

;COLERnih~, il;l;l ;.__

i

Table IV. TOR&UE VALUES FOR IMPORTANT b. Slip guide ring (18), with internal recess facing
SCREWS, NUTS AND THREADED PARTS out, blade arm flange of hub spider (52). Use
over
mallet to start guide ring (18) onto hub spider flange.
Install Special Tool BT-222 over blade arm. Slip the
Index
Part
Torque t,, halves of outer bearing race (19) into place with
No. Ft. Lb. the backs of the races resting against the inner faces
of the hub arm retention flanges. The fingers of the
5 Clamp Screw 40 BT-222 tool should rest against the bearing race sur-
6 Screw 65 faces. The bearing fractured surfacesshould be
13 Counterweight Screw 65 accurately matched. Using BT-222 tool, draw guide
21 Nut 75-120 ring (18) over the hub retention flanges and outer
23 Nut 10 bearing races (19), far enough to allow wire ring
51 Shaft Nut 450 (68) to be inserted into groove formed in hub flangs.
48 Screw 4 Using Special Tool BT-223, pull guide ring (18) back
45 Cylinder 200 over the top of wire ring (68) as far as thering will
allow.

c. Mount the inner races of bearing (19) on a hub

2-18.ANTI-ICING RING, STOP AND BULKHEAD arm (54) and install wire ring to secure in place.
ASSEMBLY. Locate the bearing parting line fore and aft or garal-
lel with the hub shaft axis.
a. Reassemble the automatic high pitch stop assem-
blies by inserting into each bracket (62) a pin (61) d. Fill the bearing (19) with full complement of
and a spring (60). Use a cotter pin (59) to hold the balls. Using 1 inch masking tape, wrap the bearing
parts. O.D. to hold the bearing races together so the balls
cannot fall out during handling. Snap the "0" ring
b. Position the anti-icing ring (63) on the back side
(14) into bearing chamber.
of the bulkhead assembly (58), and the automatic
high pitch stop assemblies on the front side. Assemble 2-21. CLAMPS AND BLADES.
the parts together, using the bolts (64), washers (64
and 66) and nuts (67). Place the thinner washers NOTE
(66) between the stop assemblies and the bulkhead,
and the thick washers (65) between the nuts (67) and In order to set the pitch prior to installation on
the anti-icing ring (63). the engine, it is necessary to completely assem-
ble the propeller on a bench having Special
2-19. FEATHERING SPRING SUBASSEMBLY. Tool No. B-843, a table spindle having a spline
identical to that of the engine shaft, attached
NOTE to its surface. Air or oil pressure should be
When assembling or disaasemblinff the feather- available in the shaft to actuate the piston
ing spring subassembly (34), it is imperative against the low pitch stop. After the pitch is
that a safe means of compressing the set it will be necessary to remove the piston
spring.
and feathering spring assembly in order to bal-
(38) be used. This is afforded by the use of
ance the propeller and subsequently install it
Special Tool No. C-845, the fixture for assem-
in the engine.
blinff feathering springs.
Mount the hub assembly as thus far assembled
a. Insert the pilot tube (40) and oute~ mushroom
0" the table spindle, Special Tool No. B-843, sealing
bushing (39) into the outer spring mushroom (38).
Place the feathering spring (37) over the pilot tube the rear cone (43) with an "O" ring (44).
(40), extending into the outer spring mushroom (38). b. Install the hub retention nut (51). Insert the
hub puller ring (50), with the flange toward the top of

I CAUTION
the assembly.

3lade pilot tube hole level with

specified in "Lubrication," paragraph 2-15.
grease as

The large end of the spring (37) mates with

the mushroom (38). NOTE
b. Use Special Tool No. C-845 to compress the B,,,,, that no air is trapped below the grease
spring (37), and install the rear retainer ring (36) as this will eventually affect the balance of the
and the rear split ring (35). Release the pressure on
propeller.
the feathering spring. The parts should now be held
together by the force of the spring. d. Install the blade (1) on the same hub pilot tube
(53) from which it was originally removed. Place a
c. Install the pilot tube "O" ring (41) on the end of
hardening gasket compound (commercial automotive
the pilot tube (40). type) around the blade shank in the shoulder radius.
d. Install the stop screws (42) into the outer spring Attach the automatic high pitch stop plates (10)
e.
mushroom (38). on the base of the blade clamp and counterweight sub-
2-20. BLADE BEARINGS. assemblies (3) by means of the bolts (11). Install
links (27) and bushings (16) on clamp and counter-
a. Slip "O" ring (14) over flange of hub spider weight subassemblies !3).Safety with cotter pin (17).
(52). Install the correct MATCHING clamp and counter-
weight subassemblies (3), with new blade clamp b. Prepare the piston for installation by careful in-
gaskets (9). Fasten the parts together with the socket spection for sharp edges. Oil the "0" ring (29) and
head clamp screws (5) and the Ferry head clamp the cylinder (45) with oil, Specification MIL-L6082A.
screws (6) with washers (7) and nuts (8). Tighten Also oil the pilot tube ’’O" ring (41) with the same oil.
~nly the socket head screws (5).
c. Slide the piston (28) onto the cylinder (45), in-
NOTE serting the piston guide rods into the bushings of the
guide collar (47). Leave the collar loose on the cyl-
The pitch will be set after the assembly of the inder until the pitch change links are installed onto
piston, after which the outermost clamp the blade clamps.
screws (6) will be tightened.
d. Rotate the piston on the cylinder so that the
f. Install the lubricator fittings (4). pitch change links (27) will fit into the slots in the
piston.
g. Check for friction orbinding of blades when ro-
tated about their axes. Correct the condition if they e. Insert the pin of the link pin assembly (25) into
do not turn freely. the bushing in the piston (28), through the end of the
pitch change link (27), and secure with the screw
2-22. CYLINDER. (26). Safety-wire the screws.

a. Clean the threads of the cylinder (45) and the f. Tighten the clamping screws (48) in the collar
hub. (47),so that the collar shoulders against the cylinder
(45). Torque the screws (48) only about 4 to 7 ft. Ib.
b. Insert the collar clamping screws (48) loosely Safety-wire screws (48) unless self locking screws
into the guide collar (47). Place the guide c6llar sub- are used.
assembly over the propeller as thus far assembled,
with the beveled edge of the center hole facing up-
ward. Y, CAUTION

c. Install the cylinder "O" ring (46) in the cylinder

behind the threads. Apply gasket compound (non- Tighten each of the three screws (48) a little
hardening commercial automotive type) to the at a time so that the piston guide rods continue
threads. to slide freely until the clamp is snug.

d. Screw the cylinder (45) onto the hub. Use a one-

g’ Install the set screw (22), washer (24) and jam
inch-square bar about three feet long as a wrench, in the end of each of the piston guide rods.
nut (23)
applied to the slot in the cylinder. Tighten the cylin- These form the low pitch stops. Torque to 18 ft. Ib.
der hard against the hub (about 200 ft. Ib. torque).

e. Inspect inside of cylinder to be sure that the ’’0" h´• Screw the nut (21) onto the end of the pilot tube
ring (46) has not been forced out of place. (40). Torque the nut (21) to 75-120 ft. Ib.

f. Inspect around the drive slot to be sure that the NOTE

bar has not raised any edges. Peen down any raised
The pilot tube (40) can be forced through the
edges so that they will not cut the "0" ring inside the
end of the piston by pressing down on the blade
piston,
counterweights.
2-23.INSTALLING FEATHERING SPRING SUB-
ASSEMBLY. 2-25. SETTING BLADE PITCH.

a. Slide the feathering spring subassembly into the Apply air or oil pressure through the bore of the
cylinder and propeller shaft bore until the grooves in
table spindle, to force the piston against the low pitch
the end of the cylinder (45) are exposed. stops. Holdthis position.

b. Install the front split rings (33) into the groove b. Set each blade with a protractor located at 30-
in the cylinder. Pull the feathering spring subassem- inch radius. S´•ee the airplane specification for the low
bly forward to lock the rings into the groove. blade pitch setting. Tighten the blade clamps and
safety-wire the screw (5). Torque screw (5) to 40 ft.
c. Secure the feathering spring subassembly and lb. and screw (6) to 65 ft. Ib.
the split rings in place by means of the outer mush-
room plate (31), attached to the outer spring mush- c. Check the blade against turning in the clamp by
room (38j by means of the screws (32). torquing the blade to 175 ft. Ib. Use a blade bar and a
weight. If the blade moves in the clamp, the clamp
2-24. PISTON. must be removed and the clamp parting line at the
corners filed slightly to allow the clamp to engage the
a. Install the "0" ring (29) and the felt seal (30) blade shoulders more firmly.
into their respective grooves in the piston (28). The
Pelt seal goes in the groove nearest the back end of the d. Check the feathering blade angle by allowing
piston, the "0" ring goes into the second´• groove. Soak the feathering spring to feather the propeller. See the
the felt seal in oil, Specification MIL-L-Ci082A, after airplane specification for the correct feathering angle.
assembling it into the piston. In case the feathering angle should be increased, re-
move the piston and turn the featherinff stop screws 2-26. The propeller is now ready for the balancing
(42) farther into the outer spring mushroom (38). To operation, which should be accomplished in accord-
reduce the feathering angle, unscrew the screws (42). ance with Section III. After balancing, the propeller
Safety-wire the screws (42) after the feathering angle should remain in its partially-disassembled state until
has been set, ready for reinstallation on the engine.

SECTION III
TEST PROCEDURE

3-1. BALANCING. 3-6. Lay the balance weights in the corner formed by
the blade and clamp, until proper balance is obtained.
3-2. Balance the propeller assembly before grease is
Since this is a three-blade propeller, the weight re-
added to the blade clamps, and check again after
quired to balance is divided in half, and half of the
grease is added. weight is placed on the clamp of each of the blades
3-3. It is recommended that a suspension balance Opposite the heavy side.
system be used. Following the instructions for the
balancing apparatus, set it to locate the center of 3-7. Each clamp provides six positions for the bal-
gravity of the propeller before attempting to balance ance weights. Locate the weights to fit any of the
the propeller. available positions, until the propeller is brought into
balance. Do not attach more than four weights with
3-4. Place an aluminum wedge between the hub and each pair of filister head screws. A total of eight
each of the blade clamps to remove any possible end-
weights may be placed on each side of each blade
play of the blade before balancing the propeller. Be clamp, if required.
sure that all three of the wedges are close to the same

weight, although a slight difference in weight, at a 3-8. After the weight slugs are attached to the blade
point so close to the center of balance, will not affect
the total balance of the propeller beyond
clamps, grease the clamps with a gun, pumping an
.stimilelbatpecca equal number of shots into each clamp.

3-5. The propeller is balanced by the addition of bal- 3-9. Recheckthe balance. If out of balance, correct
ance weights, Part No. A-1305 (fig. 2-1, ref. 14) to the by adding grease or further slugs until the propeller
blade clamp assemblies (3) opposite the heavy side. is again brought into balance.

SECTION IV

LUBRICATION

4-1. GENERAL PROPERTIES OF GREASE RE- 6. Lubriplate 630 AA

&UIRED. FiskeBrothers, Toledo, Ohio.
Any grease used must have the following properties: This grease will bleed oil in hot weather. It is
recommended only for lubrication of the blade
a. Waterproof. pilot tubes; but not the blade bearings.
b. Temperature range between --15" F and 150" 7. RPNI Aviation Grease No. 1
F; or --40" to 100" F if operation is in´•cold climate.
Standard Oil Co. of California.
c. Freedom from separating oil from soap base due 8. Lubriplate 707
to centrifugal force or high temperature.
F’iske Brothers, Toledo, Ohio.
d. Low friction.
9. Mobilgrease Aero Lo-Hi PD-535-K
Socony Vacuum Oil Co.
4-2. LIST OF APPROVED GREASE, BY SPEC. OR 10. No. 84 Medium Grease
NAME. Keystone Lubricating Co.

i. I
MIL-G-238271 11. Texaco Regal Starfax Special.
Stroma HT-1 (Z-801 Grease) 12. Molub-Alloy No. 2 Grease --10´ F.
2.
Union Oil Co. of California. No. 1 Grease --25" F.

Gulflex A.
Imperial Oil and Grease Co.
3.
Los Angeles, California.
This grease is recommended for the blade ball
bearings as it will not bleed oil in hot weather. 13. Germany--Calypsol H729
4. RPM Aviation Grease No. 2 German Calypsol Company, Dusseldorf.
Standard Oil Co. of California.
4-3. PROPER TIMES 4ND AMOUNTS OF GREASE
6. Stroma LT-1 (2-815 Grease) ARE MENTIONED DURING ASSEMBLY PROCED-
Union Oil Co. of California. URES.
 PART II DARTS LIST

SECTION I

INTKOI)U CTION

1-1. HOW TO USE THE LISTS. the parts listing, following the consecutive index num-
bers until you reach 14. In the second or "Part No."
colu"n you will find the correct part number, A-1305.
The first column in each listing is the figure and
index number column. This refers to the illustration
and index number of each part. For example, if you The third column is the "Description" column
are ordering a balance weight and want to see where and gives the correct nomenclature to be used when
and how it locates on the general assembly, this col- ordering parts.
umn indicates figure 1, index number 14. Looking at
figure 1 in the Group Assembly Parts List, index num- 1-2. HOW TO ORDER.
ber 14, the appearance and location of the balance
weight may easily be found. IT IS IMPORTANT THAT THE PART NUM-

If you do not know the part number for the bal-

BER, PART NAME, OR MODEL NUMBER, SERIES
LETTERS AND SERIAL NUMBER BE GIVEhT
ance weight, locate it on the applicable illustration--
and then find the index number assigned to it. Look in WHEN ORDERING PARTS.
 SECTION II

GROUP ASSEMBLY PARTS LIST

Part Description Units Usable

Index No.l Number 1 2 3 4 5 6 Per Assy On Code

1- No Number PROPELLER WITH SPINNER 1

1- HC-B3Z20-2A I PROPELLER ASSY 1
-1 10151B-8 BLADE, With anti-icing shoe 3
-2 279-404 SHOE, Propeller anti-icing (BEA) 3
1- 838-17 CLAMP AND COUNTERWEIGHT SUBASSY 3
-3 838-DET-1-17 CLAMP, Ctw., Linkscrew subassembly 3
-4 5010 FITTING, Lubricator (LIN) 1
-5 A-282 SCREW, Socket head clamp 2
-6 COMM SCREW, Clamp, Ferry hd., 2
7/16-20 x 2 (FCSS)
-7 AN960-716 WASHER 2
-8 AN363-720 NUT 2
-9 A-1306 GASKET, Blade clamp 2
-10 A-881 STOP, Automatic high pitch 1

(ATTACHING PARTS)
-11 AN3H-2A BOLT 2

-12 AN380-3-2 I COTTER PIN 2

-13 COMM I SCREW, Sec. hd., Counterweight mounting, 2
7/16-20 x 31~ in. (SPS)
-14 A-1305 WEIGHT, Balance AR

(ATTACHING PARTS)
-15 AN501A10-8 SCREW 2

-16 A-944 1 BUSHING 3

(ATTACHING PARTS)
-17 AN380-3-2 COTTER PIN 3

-18 RING 3
-19 A-1851 I BEARING, Blade mounting 3
-20 PRP909-7 I RING, "O", Blade mounting, compound 3
122-70 (PLRB)
-68 WIRE RING, Guide retainer 3
1- B-1368 1 PISTON JACK SUBASSY 1

(ATTACHING PARTS)
-21 A-880-1 I NUT 1

-22 COMM I SCREW, Set, 5/16-24 x 1, 3

hdls knurled cup pt
-23 COMM I NUT, 5/16-24, SAE 3
-24 COMM I WASHER, Flat, 5/16 SAE 3
-25 A-1464 LINK PIN ASSY 3

(ATTACHING PARTS)
-26 AN501A10-6 SCREW 3

-27 A-861-3 1 LINK, Pitch change 3

-28 C-1451 I PISTON 1
-29 PRP902-46* RING, "O", Compound 122-70 1
(PLRB)
-30 A-863 1 SEAL, Felt 1
-31 A-1369 PLATE, Outer mushroom 1

Corresponding MS29513 "0" rings may be substituted for PRP "0" rings except for PRP902-46.
10
gure Part Description Units Usable
dex No.l Number I 1 2 3 4 5 6 Per Assy On Code

(ATTACHING PARTS)
1-32 AN501A10-4 I. SCREW ...................................................................I
4

-33 A-859 1 RING, Front split 1

-34 831-10 1 SPRING SUBASSP, Feathering 1
-35 A-867 1 RING, Rear split 1
-36 A-866 1 RING, Rear retainer 1
-37 B-1363 1 SPRING, %eathering 1
-38 13-1364 1 MUSHROOM, Outer spring 1
-39 A-1365 1 BUSHING, Outer mushroom 1
-40 B-868-1A I TUBE, Pilot 1
-41 PRP914-8 I RING, "O", Pilot tube (PLRB) 1
-42 AN510A10-10 SCREW 2
-43 A-50-5 CONE, Hub mounting 1
-44 PRP909-7 I RING, "O", Hub mounting (PLRB) 1
-45 B-854 1 CYLINDER 1
-46 PRP909-13* RING, "O", Cylinder (PLRB) 1
1- 834-1 1 COLLAR SUBASSY, Piston guide 1
-47 B-1402 I COLLAR, Guide I
-48 COMM SCREW, Socket hd., 1~-28 x 1 8
-49 A-847 PIN, Propeller nut safety I
-50 A-870 I RING, Hub puller :I
-51 A-63-B I NUT, Hub retention 1
1- 840-55 1 HUB SPIDER SUBASSY :I
-52 C-1968 SPIDER, Hub 1
-53 A-1308 I TUBE, Pilot hub 3
-69 A-155 BUSHING :I
1- 836-7 SPINNER ASSY 1
-54 D-1367-2 1 DOME ASSY 1

(ATTACHING PARTS)
-55 AN526-1032R81 SCREW 12

-56 50-960056 TUBE ASSY, Fluid delivery (BEA) 3

(ATTACHING PARTS)
-57 AWS26-1032R81 SCREW 3

1- 850-1 1 RING, STOP AND BULKHEAD ASSY 1

-58 D-1414-1 I BULKHEAD ASSY 1
1- 830-5 STOP ASSY, Automatic 3
high pitch
-59 AN380-2-2 I COTTER PIN 1
-60 A-884 1 SPRING 1
-61 A-883 PIN .....................................,.................I
1
-62 B-882-5 BRACKET 1
-63 D-1433 1 RING, Anti-icing ...........................................I
1

(ATTACHING PARTS)
-64 AN4H-15A I BOLT .............................................................I
6
-65 AN960-416 I WASHER 6
-66 AN960-416L I WASHER 6
-67 AN364-428 1. NUT 6

I I I I I
Corresponding 1VIS29513 "O" rings may be substituted for PRP "O" rings except for PRP902-46.

11
I i

68

..CZ)
I

18\9 2~
65

ol 66 1~
b 20

53

,52
49
23

I~O
59
43
L34
69;P24
r~iPanit,
35

37
´•´•;~it; 46
45

,9

38
33

i 4

57

56

Figure i. Model HC-B3Z20-2R Propeller, Exploded View

12
08
.;´•´•j:i .unuil ~u iib-\

´•..r i iii i ii iii

s´•´•´•i´•l;´•i´•li´•:i i i:li´•ii
E R H ~B U L II Fa S T FZ id C T I O S
iiiiiiiiiiiiiiiiiiiiiiiiiiiiiiij~ \M r B H PBRTS LIST
iiiiiijiiiiiiiiiiiiiiiiiiiiiiiiiii

ji’j :::jli::j.i´•il´•:j i:´•´•;li:

MODELS HC-B3Z30-2B/9349/ 10151
HC-~3\1’30-zni W9349/ W101.51

;´•:l.jl;ijilij:l.ji!li i i i i
I iii i iiiiii iiiiiiiii i ii i iiii

HARTZELL PW~PEhLEW, INC.

PIQUA, OHIO

D.O.A. -’F.A.A. Approved

REPR~INT NOV. 1976

 RECORD OF REVISIONS

Pa~´•
MFG R
NO DESCRIPTION ISSUE DATE ATP REV DATEI INSERTED BY
 RECORD OF TEMPORARY REVISIONS

ATP REV INSERT DATE REV REMOVE

TEMP
DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY
REV NO
 TABI,II: OF CONTF,NTS

Page

PART I OVF,RWAUL INSTRUC:TIONS 1

Section I. Introduction 1

1-1. General 1

1-6. Pul´•pose 1

3
Section II. Ovel´•haul Instructions

2-1. Special Tools Required 2

2-3. Disassembly 2

2-11. Cleaniltg 3

2-12. Inspection 3

2-13. Testing

Replacement 3
2-14. Repair oi´•

2-15. Lubrication

2-10. Reassembly 5

Test P1´•ocedure 8
Section III.

O~e 8
Section IV. Lubrication

PART II PARTS LIST

Introduction 9
Section I.

10
Section II. Group Assembly Parts I,ist

NOTE: The difference between the I-IC-B3Z30-2B and the

HC-B3W30-2B propellers lies in the blade pilot tube
and pilot tube bearings which are located in the shank.
The former has plain bushings while the latter has a
needle bearing replacing the plain bushing at the outer
end of the pilot tube only.

The parts lists are. identical except for the parts noted below:

Model: IIC-B3Z30-2B HC-B3W30-2B

Blade: 9349 or 10151 W9349 or W10151

840-34 840-74
Hub Spider Assembly:
C-1853 C-1853
Hub Spider
A-1308 A-1884
Tube, Pilot
A-1817 A-1817
Bushing

Overhaul procedures are identical for both designs in ge,ie~al.

 PART I--OVERHAUL

SECTION I

INTKODUCTION

GENERAL arate publication. Repair pnrta of the propeller are

listed in the Illustrated Parts Breakdown.

1-2. This handbook contains overhaul instructions
for the Model HC-B3’So-2B variable-pitch, feather- 1-6. PURPOSE
ing propeller manufactured by IIartzell Propeller.
Inc., Pigoa, Ohio. (See figure 1 i.) L-7. The Model HC-B3130-2B Propeller is a three-
blade feathering propeller designed for engines in the
1-3. Sections I, II and III of this handbook contain 300 to 450 horsepower range. It is designed to use
overhaul and test instructions far the model HC- engine oil pressure for decreusillg pitch and eounter-
B3:30-2B Propeller. weights to increase pitch. A spring assists the counter-
weights during the feathering operation. Centrifugal
1-4. Overhaul and test procedures for models inelu- stops prevent feathering of the ilropeller due to action
ded in Section 1V are the same as the procedures given of the spring when the engine is.itopped. At apeeds of
in Sections II and III, except for the specific differ- over 500 rpm the stops are I´•emoved by centrifugal

ences noted by the applicable DiffeEenee Data Sheets, fol´•ee, allowing the propeller to be feathered at any
Lime. The design of the pitch control mechanism re-
1-5. Operation and Service Instructions far the quil´•cs an oil pressure of SC~ pounds, which is supplied
Model HC-BSt30-2B Propeller are provided in a scp- by a governor mounted on the engine.

ORIGINAL
Received By
ATP

Figure 1-1. ModelHC-B3’30-2B Propeller, General Yiew

 SECTION II

INSTRUCTIONS

2-1. SPECIAL OVERHAUL TOOLS RE&UIRED. d. Remove the outer mushroom plate (31) by tak-
ing out the screws (32). Remove the front split ring
2-2. Special tools required for the overhaul of the (33),thus exposed. This permits the feathering spring
Model HC-B3 WL)V-LIU
Z "D
all;
’:-C-~
IIJL~U 111 lilLllt:
T
i. sub-assembly (34) to be withdrawn through the front
of the propeller.
2-3. DISASSEMBLY. (See figure 2-1.)
e. Remove propeller shaft safety pin (49).
2-4. REMOVAL OF PROPELLER FROM ENGINE.
f. Use Special Tool No. B-840, the propeller shaft
nut wrench, to unscrew the propeller shaft nut (51).
NOTE
This does not remove the nut, but it causes the nut to
force the propeller off the engine shaft. When the
In most cases the propeller will be received for
propeller is off the shaft, remove the hub mounting
overhaul in a partially disassembled condition.
cone (43), the hub mounting "0" ring
If this is the case, perform only as many of the (44) and the
rear bulkhead assembly (58).
following steps a. through f. as are necessary,
checking to be sure that all parts are present.
NOTE
a. Remove spinner dome assembly (54) by taking
out the screws (55). If the propeller is not to be overhauled immed-
iately after removing it from the engine, it may
be reassembled at this point for storage or ship-
ment to the overhauling activity by following,
WARN IN C in general, the reverse order of disassembly.

2-5. CYLINDER.

Feather propeller before removing nut (21).

a. Use a i-inch square bar as a wrench to unscrew
(Use blade bars to compress feathering spring the cylinder (45). From the
so that high stop pin (61j can be pushed out to
cylinder remove an "O"
ring (46).
allow propeller to be feathered.)

b. Remove the nut (21), using Special Tool No. B- b´• From the piston guide collar (47) remove the
842. Remove the screws (22), nuts (23) and washers Screws (48).
(24). Remove the three link pin assemblies (25) by
taking out the screws (26). c. Removal of the cylinder (45) also frees the pro-
peller shaft nut (51)’. From the nut remove the hub
c. Remove the piston (28). From the piston remove puller ring (50).
the "0" ring (29) and felt seal (30).
2-6. CLAMPS AND BLADES.
Table I. SPECIAL OVERHAUL TOOLS
a. With ink and a scale, mark matching lines on the
Part Procuring Service blades (1) and the clamps (3). Record the blade
No"e"clature serial number with clamp number for each side of the
Number Stock Number
propeller.
B-840 Shaft Nut Wrench
b. Remove the screws (6) and the clamp screws
B-842 Wrench, for A-880-1 (6), and nuts (8) from the clamps (3). Remove the
Nut on Spring Assembly
clamp halves and the blade clamp gaskets (9). Re-
B-843 Table Spindle for Pro- move the blades (1).
peller Assembly
c. From the clamps i3) remove the lubricator fit-
B-844 Fixture for Pressing
tings (4). Remove the´•automatic high pitch stops (10)
Pilot Tube in Hub
by taking out the bolts (11), and the balance weights
C-845 Fixture for Assembly (14) by taking out the screws (15).
of Feathering Springs
d. Remove the cotter pin (12). Remove and discard
BT-222 IAssembly Tool for the counterweightmounting screws (13). These
Pressing A-1852 Ring screws should be replaced immediately with new ones.
on C-1853 Hub Spider
Torque to 65 ft. Ib. Safety with cotter pin (12).
BT-223 Puller Tool for A-1852
Ring NOTE: If these parts are replated, this should be
done with counter\Yeights removed.
 2-10. HUB SPIDER ASSEMBLY. If inspection of
CAUTION the hub spider subassembly shows that any of the hub
pilot tubes (53) require replacement, they may be
pulled from the hub spider (52) by means of an appro-
In normal overhaul operations it is not neces- priate bearing puller.
sary to remove the counterweights from the NOTE
clamp and counterweight assembly (3). If the Do not remove the hnb pilot tubes unless Spe-
counterweights are defective, use a complete ciai Tool No. B-844, the fixture for pressing the
new clamp and counterweight assembly (3) at
hub pilot tube into the hub, is available to aid
overhaul.
in installing the replacement tube.

e. Remove the bushing (16) by taking out the cotter 2-11. CLEANING.
pin (17). This also frees the pitch change link (27).
a. Wipe all dirt and grease off all parts with a
clean, lintless rag, keeping the parts separated so as

2-7. BLADE BEARINGS. not to allow them to scratch or nick each other.

b. Clean all parts except the felt seal (30) with sol-
a. Slip wire ring from groove formed in inner bear-
vent, 8pecification P-S-66la, and blow dry with com-
ing race (19) and remove two halves of inner bearing
race (19). (It is assumed that the balls have been re- pressed air.
moved when the clamps were ~´•emoved).
c. Apply a rust preventive compound to bearings
and all parts which are to be stored or set aside for
b. Using Special Tool BT-222, drive guide ring (18) ,,y length of time.
in slightly towards the center of hub (52) only enough
to uncover wire ring (68), which can then be removed. d~ Wrap the parts or keep them coveretl to prevent
Using Special Tool BT-223, pull guide ring (18) irom an accumulation of dust or dirt before reassembly.
hub (52). Remove two halves of outer race of bear-
ing (19). 2-12. INSPECTION.

Remove "O"
a. Inspect all wearing parts according to the toler-
c. ring (20). in Table II.
ances specified Replace ally part not
coming within the specified limits.
2-8. FEATHERING SPRING SUBASSEMBLY.
b. Inspect the blades according to the tolerances
listect in Table III. Replace a blade which falls below
the listed minimum dimension upon repair.

e. inrlli´•ct ilil met:ll sol.fsce* Replace or

refnish any bearing oi´• ~´•eRr surface which has a vis-
Do not attempt to disassemble the feathering ible nick, dent or other distortion.

spring subassembly unless Special Tool No.

C-845, the fixture for assembly of feathering
d. Magnaflux all steel parts.
spring, is available.
2-13. TESTING. Tesling of individual components
is not feasible.
a. Place the assembly in the fixture and compress
the feathering spring (37). When the spring is com- REPAIR OR REPI,ACEMENT.
pressed, slide the rear retainer ring (36) back on the
a. Remove all rust, galling and nicks from the hub
pilot tube (40) and remove the rear split ring (35).
This allows the rear retainer ring (36), the spring spider arms with crocus cloth or very fine emer~
(37), the outer mushroom bushing (39) and the outer P"per. Rust, galling aiid nicks are stress raisers
which reduce the fatigue life of the hub. Do not polish
spring mushroom (38) to be removed from the pilot
tube (40). unless necessary, because the hub surfaces have been
put into compression by rolling. Replate if necessary
with cadmium only. Bake after plating 350´•F for
b. Remove the pilot tube "O" ring (41) and the
3 hours.
stop screws (42).
b. As a matter of procedure, replace all "0" rings
2-9. RING, STOP AND BULKHEAD ASSEMBLY. ..d the felt gasket (30) with new parts at reassembly,
Replace all cotter pins at reassembly.
a. Remove the bolts i64),washers (65 and 66) and
nuts (67) to free the automatic high pitch stop assem- c. Replace the counterweight mounting screws
blies and the anti-icing ring (63) from the bulkhead (13) at reassembly with new parts. Use only the spec-
assembly (58). Remove feed tubes (56). ified parts, as their strength has been carefully deter-
mined and is correct for the application.
b. Disassemble the high pitch stop assemblies by
removing from each the cotter pin (59). This allows d. Repair damaged blades in accordance with
the spring (g0) and pin (61) to be removed from the standard FAA procedures. Anodize by acid
bracket (62). method only.
 1. Blade
2. Propeller anti-icing shoe
3. Clamp and counter-
weight subassembly I\ ~i)2
4. Lubricator fitting
5.
6.
8.
Socket head clamp screw
Ferry head clamp screw
Nut, self locking
liY
9. Blade clamp gasket 68
10. Automatic high pitch
stop
C;
II.

13.
.21tloB Cotter pin
Counterweight mounting 6
3 li\lf(7,2j1 ’9

screw
;14. Balance weight 19
9_ -P
I6 27
16.
17.
18.
.51nipretoCScrew53
Bushing
t
Lock ring
65

5
10
20

66 II
19. Blade mounting bearing 62
20.
21.
22.
.32tuN
Blade

Set screw
Nut
mounting "O" ring 63

6i
58r
~ia64 ,52
43

5~I24
24. Flat washer59 7
25. Link pin 43
assemblySO
26.
27.
Screw
Pitch change link
44
69d
q469145
Piston
29. .82gnir"O 70
30.
31.
Felt seal
Outer mushroom plate PI
50
~jly48
32. Screw 35
33. Front split ring 36
34. Feathering spring
37
subassembly
35. Rear split ring
36. Rear retainer ring
37. Feathering spring 38
38. Outer spring mushroom 33
42

I 3432
39. Outer mushroom bushing
40. Pilot tube 40
41. Pilot tube "O" ring
42. Screw
sl~O
43. Hub mounting cone
44. Hub mounting "0" ring
45 Cylinder
46. Cylinder "0" ring
29
47. Guide collar
48, Screw
49. Propeller nut safety pin
50. Hub puller ring
61. Hub retention nut
62. Hub spider
53. Hub pilot tube
54. Dome assembly
55. Screw
56. Fluid delivery tube 60. Spring 64. Bolt 68. Wire ring,
assembly 61. Pin 65. Washer guide retainer
58. Bulkhead assembly 62. Bracket 66. Washer 69. Rushing
59. Cotter pin 63. Anti-icing ring 67. Nut 70. "0" Ring

Figure 2-1. Model IHC-B3~30-2B Propeller, Exploded View

 Table II. TOLERANCES OF WEARING STTRFACES

Replace if dimension is
Item Specified above or below
Part or Description of Measurement
No. Max. Min. Max. Min.

1.7185 1.7180 1.7165

i. A-1308 Pil6t Tube (Inner 11~ Inch, O.D.)
1.7200 1.7197 1.7187
(Outer 1 Inch, O.D.) 1.7165
A-1884 Pilot Tube (Inner End) 1.7185 1.7180
1A.
1.3760 1.3750 1.3735
(Outer End)
2. A-1308 Pilot Tube Assembly, length 3-i7~+1/1S
extending beyond C-1351 Hub Spider 1.724
1.7225 1.7215
3. Blade Bushing I.D.
1.3770 1.3760 1.3780
3A. Blade Needle Bearing (Outer End)
3.782 3.780 3.790
4. C-1816 Piston, A-862 Bushing I.D.
.3765 .3755 .3795
5. C-1816 Piston, A-946 Bushing I.D.
3.778 3.776 3.773
6. B-854 Cylinder O.D.
.735 .734 .731
7. B-868-4A Pilot Tube Diameter O.D.
.738 .736 .74’
8. A-1365 Mushroom Hushing 1.474
1.488 1.479
9. A-866-3 Spring Retainer, O.D.
.508 .515
10. B-1810-1 Collar, Bushing I.D.
.3755 .3750 .3785
11. A-861-3 Link Arms I.D. Small End
.5635 .5625 .5645
12. A-861-3 Link Arms I.D. Large End
.502 .501 .504
13. A-914 Bushing I.D.
.5620 .5615 .5600
14. A-944 Bushing O.D.
.5005 .4995 .4970
15. A-S04 Link Screw O.D.
450 min. 650 min. 400 min. 600 min.
16. Ii’eathering Spring Assembly compression
Extended Compressed Extended Compressed
load (pounds)
2-%;
"+0", r’, @30"Sta.; I .1’ Between Blades.
17. Blade Pitch Setting, Low Pitch 16-1~ 85" Min.
18. Blad-e Pitch Setting, Feathering 86" Max.,
19. Balance Tolerance 1 Slue A-1305
20. Blade Track ~1/16
Blade End Play .060
21,
Tip .068 .100
22. Fore and Aft Movement of Blade

2-17. HUB SPIDER ASSEMBLY.

2-15. LUBRICATION.
If the pilot tubes (53) were removed from tho
a.
a. Lubricate the blade pilot tubes with grease, Spe- hub spider (52), it is necessary to use Special Tool No.
listed in
cification MIL-G-23827, or with grease B-844 to aid in replacing the tubes. Place the hub
section IV. spider on the spindle of the fixture, with the emptly
pilot tube hole pointing upward. Replace the ~emov-
b. Lubricate the blade bearings and other moving able supporting member of the fixture.

parts of the mechanism with grease, Specification b~ Place the fixture and hub on the table of a 25-
MIL-G-3278, or with greases listed in Section IV. ton press, and press pilot tube into hub spider for a

of depth of 2-1~, inches, or until 3-9/1. inches -t .010 ex-

c. Proper times and amounts for application tends about end surface of branch of hub. Be sure the
during reassembly pilot tube enters hub squarely. Use spacer sleeve fur-
grease are mentioned as necessary
nished with Special Tool No. B-844 to maintain 3-´•11,
procedures.
inches. NOTE: The tube must have a press fit of
.002 .003.
2-16. REASSEMBLY. (See figure 2-1.)
Table III. BLADE REPAIR TOLERANCES
10151-8 Blade
9349 Blade

Thickness Width
Face I I I I I
Angle Alignment Minimum
Radius idth+lThickness+ Radius Specified Minimum Specified
Min. Max. Min. ax. Man.
.970 .921 6.265 6.080
3 I I I I 1 4.045 z.a70 1 1 18

.689 6.520 6.303

1 .735
13 -T 1 i. 1 15.717 1 1.095 24

1 1 .693 1 6.~64
20 T;il." 1 42." 1-.122 -.058 6.310 1 30 .560 .515 6.430

28 36.5" 37.1" .472 .408 6.070 .472 5.612

.470 .418 5.990
36
33.2" -.682 .618 5.440 .376
34 Setup No Limit
42 No Limit
30.2" -.832 .768 4.180 .285
40 29.8"
 All torques are values based on non-lubricated threads. Tolerance on torque is ~L 10% unless otherwise stated.

Table IV. TOR&UE VALUES FOR IMPORTANT b.

Slip guide ring (18), with internal recess facing
SCREWS, NUTS AND THREADED PARTS out, blade arm flange of hub spider (52).
over Use
mallet to start guide ring (18) onto hub spider
Aange.
Install Special Tool BT-222 over blade arm.
Index Torque Slip the
Part t,o halves of outer bearing race (19) into
No. Ft. Lb. placewith
the backs of the races resting against the inner
faces
of the hub arm retention flanges. The
fingers of the
5 Clamp Screw 40 BT-222 tool should rest against the
bearing race sur-
6 Screw 65 faces. The bearing: fractured surfaces should be
13 Counterweight Screw 65 accurately matched. Using BT-222 tool, draw guide
21 Nut 75-120 ring (18! over the hub retention flanges and outer
23 Nut 10 bearing races (19), far enough to allow wire ring
51 Shaft Nut 600 (68) to be inserted into groove formed in hub flangs.
48 Screw 4 Using Special Tool BT-223, pull guide ring (18) back
45 Cylinder 200 over the top of wire ring
!68) as far as the ring will
allow.

c. Mount the inner races of bearing (193 on a hub

2-18.
ANTI-ICING RING, STOP AND BULKHEAD arm (54) and install wire ring to secure in place.
ASSEMBLY. Locate the bearing parting line fore and aft or
paral-
a. Reassemble the automatic high pitch stop assem- lel,with the hub shaft axis.
blies by inserting into each bracket (62) a pin (61) d. Fill the
bearing (19) with full complement of
and a spring (60). Use a cotter pin (59) to hold the balls. Using
1 inch masking tape, wrap the
bearing
parts. O.D. to hold the bearing races together so the balls
cannot fall out during handling. Snap the "0" ring
b. Position the anti-icing ring (63) on the back side
of the bulkhead assembly
(14) into bearing chamb~;´•.
(58), and the automatic
high pitch stop assemblies on the front side. Assemble 2-21. CLAMPS AND BLADES.
the parts together, using the bolts (64), washers (64
and 66) and nuts (67). Place the thinner washers NOTE
(66) between the stop assemblies and the bulkhead,
and the thick washers (65) between the nuts (67) and In order to set the pitch prior to installation on
the anti-icing ring (63). Assemble feed tubes the engine, it is necessary to
(56). completely assem-
ble the propeller on a bench
2-19.
having Special
FEATHERING SPRING SUBASSEMBLY. Tool No. B-843, a table spindle ahaving spline
identical to that of the engine shaft, attached
NOTE
to its surface. Air or oil pressure should be
When assembling or disassembling the feather- available in the shaft to actuate the piston
ing spring subassembly (34), it is imperative against the low pitch stop. After the pitch is
that a.sa-fe means of compressing the spring set it will be necessary to remove the
piston
(38) be used. This is afforded by the use of and feathering spring assembly in order to bal-
Special Tool No. C-845, the fixture for ance the propeller and
assem- subsequently install it
bling feathering springs. in the engine.

a. Insert the pilot tube (40) and outer mushroom MOU"t the hub assembly as thus far assembled
bushing (39) into the outer spring mushroom (38). 0" the table spindle, Special Tool No.
B-843, sealing
Place the feathering spring (37) over the pilot tube the rear cone (123) with an "O" ring
(44).
(40), extending into the outer spring mushroom (88). b. Install the hub retention nut (51). Insert the
hub puller ring (S0j, with the flange toward the
top of
the assembly.
CAUTION
c. Fill the blade pilot tube hole level with
grease as
specified in "Lubrication," paragraph 2-15.
The large end of the spring (37) mates with
the mushroom (38).
NOTE
b. Use
Special Tool No. C-845 to compress the Be sure that no air is trapped below the
grease
spring (37), and install the rear retainer ring (36) this will eventually affect the balance of the
as
and the rear split ring (35). Release the pressure on
propeller.
the feathering spring. The parts should now be held
together by the force of the spring, d. Install the´•blade (1) on the same hub pilot tube
(53) from which it was originally removed. Place a
c. Install the pilot tube "O" ring (41) on the end of
hardening gasket compound jcommercial automotive
the pilot tube (40).
type) around the blade shank in the shoulder radius.
d. Install the stop screws (42) into the outer spring
Attach the automatic high pitch stop plates (10)
mushroom (38).
on the base of the blade clamp and counterweight sub-
2-20. BLADE BEARINGS. assemblies (3) by means of the bolts (11). Install
links (27) and bushings (16) on clamp and counter-
a. Slip "O" ring (14) over flan~ of hub spider weight subassemblies !3).Safety with cotter pin (17).
(52). Install the correct MATCHING clamp and counter-
weight subassemblies (3), with new blade clamp b. Prepare the piston for installation by careful in-
gaskets (9). Fasten the parts together with the socket spection for sharp edges. Oil the "0" ring (29) and
head clamp screws (5) and the Ferry head clamp the cylinder (45) with oil, Specification MILLG082A.

screws (6) and nuts (8). Tighten only the socket Also oil the pilot tube "O" ring (41) with th~ same oil.
head screws (5).
c. Slide the piston (28) onto the cylinder (46), in-
NOTE serting the piston guide rods into the bushings of the
guide collar (47). Leave the collar loose on the cyl-
inder until the pitch change links are installed onto
The pitch will be set after the assembly of the
the blade clamps.
piston, after which the outermost clamp
screws (6) will be tightened.
d. Rotate the piston on the cylinder so that the

f. Install the lubricator fittings (4). pitch change links (27) will fit into the slots in the
piston.
g. Check for friction orbinding of blades when ro-
tated about their axes. Correct the condition if they e. Insert the pin of the link pin (25) into
do not turn freely. the bushing in the piston (28), through the end of the
pitch change link (27), and secure with the screw
2-22. CYLINDER. (26). Safety-wire the screws.

a. Clean the threads of the cylinder (45) and the f. Tighten the clamping screws (48) in the collar
hub. ,47),so that the collar shoulders against the cylinder
(45). Toryue the screws (48) only about 4 to 7 ft. Ib.
b. Insert the collar clamping screws (48) loosely Safety-wire screws (48) unless self locking screws
into the guide collar (47). Place the guide collar sub- are used.
assembly over the propeller as thus far assembled,
with the beveled edge of the center hole facing up-
ward. CAUTION jC:

c. Install the cylinder "O" ring (46) in the cylinder

behind the threads. Apply gasket compound (non- Tighten each of the three screws (48) a little
hardening commercial automotive type) to the at a time so that the piston guide rods continue
threads. to slide freely until the clamp is snug.

d. Screw the cylinder (45) onto the hub. Use a one- Install the set screw (22), washer (24) and jam
R~
inch-square bar about three feet long as a wrench, .,t (23) in the end of each of the piston guide rods.
applied to the slot in the cylinder. Tighten the cylin- These form the low pitch stops. Torclue to 18 ft. Ib.
der hard against the hub (about 200 ft. Ib. torque).
h. Screw the nut (21) onto the end of the pilot tube
e. Inspect inside of cylinder to be sure that the ’’0"
has not been forced out of place. (40). Torque the nut (21) to 75-120 ft. Ib.
ring~(46)
NOTE
f. Inspect around the drive slot to be sure that the
bar has not raised any edges. Peen down any raised
The pilot tube (40) can be forced through the
edges so that they will not cut the "0" ring inside the end of the piston by pressing down on the blade
piston. counterweights.

2-23.INSTALLING FEATHERING SPRING SUB-

2-25. SETTING BLADE PITCH.
ASSEMBLY.

Slide the feathering spring subassembly into the

Apply air or oil pressure through the bore of the
table spindle, to force the piston against the low pitch
a.

cylinder and propeller shaft bore until the grooves in stops. Hold this position.
the end of the cylinder (45) are exposed.

Install the front split rings (33) into the groove b´• Set each blade with a protractor located at 30-
b.
in the cylinder. Pull the feathering spring subassem- inch radius. See the airplane specification for the low
blade pitch setting. Tighten the blade clamps anti
bly forward to lock the rings into the groove.
safety-wire the screw (5). Torque screw (5) to 40 t’t.
c. Secure the feathering spring subassembly and Ib. and screw (6) to 65 ft. Ib.
the split rings in place by means of the outer mush-
room plate (31), attached to the outer spring
mush- c. Check the blade against turning in the clamp by
room (38) by means of the screws (32). torquingthebladeto 175ft. Ib. Useabladebarand a
weight. If the blade moves in the clamp, the clamp
2-24. PISTON. must be removed and the clamp parting line at the
corners filed slightly to allow the clamp to engage
the

a. Install the "0" ring (29) and the felt seal (30) blade shoulders more firmly.
into their respective grooves in the piston (28). The
felt seal goes in the nearest the back end of the d. Check the feathering blade angle by allowing
groove
the "0" ring into the second groove. Soak the feathering spring to feather the propeller. See the
piston, goes
the felt seal in oil, Specification MIL-L-6082A after airplane specification for the correct featherinff an~le.
In case the feathering angle should be increased, re-
assembling it into the piston.
move the piston and turn the feathering stop screws 2-26. The propeller is now ready for the balancing
(42) farther into the outer spring mushroom (38). To operation, which should be accomplished in accord-
reduce the feathering angle, unscrew the screws (42). ance with Section III. After balancing, the propeller
Safety-wire the screws (42) after the feathering angle should remain in its partially-disassembled state until
has been set. ready for reinstallation on the engine.

SECTION III
TEST PROCEDURE

3-1. BALANCING. 3-6. Lay the balance weights in the corner formed by
the blade and clamp, until
3-2. Balance the propeller assembly before grease is proper balance is obtained.
Since this is a three-blade propeller, the weight re-
added to the blade clamps, and check again after
quired to balance is divided in half, and half of the
grease is added.
weight is placed on the clamp of each of the blades
3-3. It is recommended that a suspension balance opposite the heavy side.
system be used. Following the instructions for the
balancing apparatus, set it to locate the center of 3-7. Each clamp providessix positions for the bal-
gravity of the propeller before attempting to balance ance weights. Locate the weights to fit any of the
the propeller. available positions, until the propeller is brought into
balance. Do not attach more than four weights with
3-4. Place an aluminum wedge between the hub and
each pair of filister head screws. A total of eight
each of the blade clamps to remove any possible end-
weights may be placed on each side of each blade
play of the blade before balancing the propeller. Be clamp, if required.
sure that all three of the wedges are close to the same

weight, although a slight difference in weight, at a

3-8. After the weight slugs are attached to the blade
point so close to the center of balance, will not affect
b&lsnee of the propeller beyond acceptable clamps, grease the clamps with a gun, pumping an
equal number of shots into each clamp.

3-5. The propeller is balanced by the addition of bal- 3-9. Recheck the balance. If out of balance, correct
ance weights, Part No. A-1305 (fig. 2-1, ref. 14) to the by adding grease or further slugs until the propeller
blade clamp assemblies (3) opposite the heavy side. is again brought into balance.

SECTION IV

LUBRICATIOIV

4-1, GENERAL PROPERTIES OF GREASE RE- 7. Lubriplate 630 AA

&UIRED. Fiske Brothers, Toledo, Ohio.
Any grease used must have the following properties: This grease will bleed oil in hot weather. It is
recommended only for lubrication of the blade
a. Waterproof. pilot tubes; but not the blade bearings.
b. Temperature range between --15" F and 150" 8. RPM Aviation Grease No. 1
F; or --40" to 100" F if operation is in cold climate.
Standard Oil Co. of California.
c. Freedom from separating oil from soap base due
9. Lubriplate 707
to centrifugal force or high temperature.
Fiske Brothers, Toledo, Ohio.
d. Low friction.
1‘0. Mobilgrease Aero Lo-Hi PD-535-K
4-2. LIST OF APPROVED GREASE, BY SPEC. OR Socony Vacuum Oil Co.
NAME. .11. No. 84 Medium Grease
1. MIL-G-23827 (Low Temp., --65" F.) Keystone Lubricating Co.
2. Str,oma HT-1 (Z-801 Grease) 12. Texaco Regal Starfax Special.
Union Oil Co. of California.
13. Molub-Alloy No. 2 Grease --10" F.
3. Texaco Marfak No. 3. No. 1 Grease --25" F.

4. Gulflex A. imperial Oil and Grease Co.

This grease is recommended for the blade ball Los Angeles, California.
bearings as it will not bleed oil in hot weather. 14. Germany--Calypsol H729
5. RPM Aviation Grease No. 2 German Calypsol Company, Dusseldorf.
Standard Oil Co. of California.
4-3. PROPER TIMES AND AMOUNTS OF GREASE
6. Stroma LT-1 (2-815 Grease) ARE MENTIONED DURING ASSEMBLY PROCED-
Union Oil Co. of California. URES.
 PART II PARTS LIST

SECTION I

INTKODU CTION

the parts listing, following the consecutive index num-

1-1. HOW TO USE THE LISTS.
bers until you reach 14. In the second or "Part No."
colum" you will find the correct part number, A-1.705.
The firstcolumn in each listing is the figure and
index number column. This refers to the illustration
and index number of each part. For example, if you The third column is the "Description" column
are ordering a balance weight and
want to see where and gives the correct nomenclature to be used when
and how it locates on the general assembly, this col- ordering parts.
umn indicates figure 1, index number
14. Looking at
figure 1 in the Group Assembly Part~ List, index num-
HOW TO ORDER.
1-2.
ber 14, the appearance and location of the balance
weight may easily be found. IT IS IMPORTANT THAT THE PART NUM-
RER, PART NAME, OR MODEI, NUMRER, SERIES
If you do not know the part number for the bal-
Ilr~TTERS AND SEIIIAL ME GIVEN
ance weight, locate it on the applicable illustration--
and then find the index number assigned to it. Look in WHEN ORDERING; PARTS.
 SECTION II

GROUP ASSEMBLY PARTS LIST

igure
Index No.l
Part
Number 123456
Description Units
Per Assy.
C-B3ZYU-2B
h Units
Per Assy.
C-B3W30-

1- No Number PROPELLER WITH SPINNER 1 1

1- HC-B3Z30-2B PROPELLER ASSY. .........,._,_
1 1
-1 9349 or 10151 BLADE, (Also Blades W9349 and W10151) 3 3
-2 C-2131-2 SHOE, Propeller anti-icing 3 3
1- 838-17 CLAMP AND COUNTERWEIGHT SUBASSY 3 3
-3 838-DET-1-17 CLAMP, Ctw., I,inkscrew subassembly 3 3
-4 MS-15001-1 FITTING, Lubricator (LIN) 1 1
-5 A-282 SCREW, Socket head clamp 2 2
-6 COMM SCREW, Clamp, Ferry hd., 2 2
7/16-20 x 21/e (FCSS)
-8 AN363-720H.T NUT 2 2
-9 A-1306 GASKET, Blade clamp 2 2
-10 A-881 STOP, Automatic high pitch 1
1

(ATTACHING PARTS)
-11 AN3H-2A BOLT 2 2

-12 AN380-3-2 COTTER PIN 2

-13 COMM SCREW, Sec. hd., Counterweight mounting, 2 2
7/16-20 x 31~ in. (SPS)
-14 A-1305 I WEIGHT, Balance AR AR
(ATTACHING PARTS)
-15 AN501A10-8 SCREW 2 2

-16 A-944 1 BUSHING 3 3

(ATTACHING PARTS)
-17 AN380-3-2 COTTER PIN 3 3

-18 A-1852 1 LOCK RING 3 3

-19 A-1851 BEARING, Blade mounting 3 3
-20 PRP909-7 RING, "O", Blade mounting, compound .........,._
3 3
122-70 (PLRB)
-68 A-1854 WIRE RING, Guide retainer 3 3
1- B-1368 PISTON JACK SUBASSY 1 1

(ATTACHING PARTS)
-21 A-880-1 I NV’r 1 1

-22 COMM SCREW, Socket Head, 5/16-24 x 3 3

-23 COMM NUT, AN316-5R 3 3
-24 A-1444 WASHER, 3 3
-25 A-1464 LINK PIN ASSY 3 3

(ATTACHING PARTS)
-26 AN501A10-6 SCREW 3 3

-27 A-861-3 1 LINK, Pitch change 3 3

-28 C-1816 I PISTON 1 1
-29 PRP902-46* I RING, "O", Compound 122-70 ........._._.__
1 1
(PLRB)
-30 A-863 SEAL, Felt 1
1
-31 A-1369-1 i´•r,ATE, Outer mushroom 1 1
(ATTACHING PARTS)
1-32 AN501A10-4 SCREW 4 4

Corresponding MS29513 "O" rings may be substituted for PRP "0" rings except for PRP902-46.
10
 Units Ullits
igure Part Description Per Assy. Pel´• Assy.
ndex No.l Number 1 2 3 4 5 6

I 1
-33 A-859 RING, Front split
SPRING SUBASSP, Feathering I 1
-34 831-17
1 1
-35 A-867 RING, Rear split
1 1
-36 A-866-3 RING, Rear retainer
SPRING, Feathering i 1
-37 B-1363-2
I 1
-38 B-1364 MUSHROOM, Outer spring
1 1
-39 A-1365 BUSHING, Outer mushroom
i 1
-40 B-868-4A TUBE, Pilot
1 1
-41 PRP914-8 RING, "O", Pilot tube (PLRB)
SCREW 2 2
-42 AN501A10-8
I 1
-43 A-1812-1 CONE, Hub mounting
I 1
-44 PRP909-9* RING, "O", Hub mounting (PLRB)
1 1
-45 B-854 CYLINDER
1 1
-46 PRP909-13* RING, "O", Cylinder (PLRB)
COLLAR SUBASSY, Piston guide 1 1
1- 834-6
1 1
-47 B-1810-1 COLLAR, Guide
3 3
-48 COMM SCREW, Socket hd., l/q,-28 X ll~L
1 I
-49 A-1848 PIN, Propeller nut safety
I 1
-50 A-1813 RING, Hub puller
1 1
-51 B-1814 NUT, Hub retention
1
1- 840-34 HUB SPIDER SUBASSY
1
-52 C-1853 SPIDER, Hub
3
-53 A-1308 TUBE, Pilot hub
1
-69 A-1817 BUSHING .........................................1...

I 1
1- C-2535 SPINNER ASSY (Anti-icing)......................................´•´•´•´•´•
1 I
-´•54 C-2531-2 DOME ASSY

(ATTACHING PARTS)
15 15
-55 AN526C1032R91 SCREW

-56 R-2149-1 1 TUBE ASSY, Fluid delivery ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•I

s

(ATTACHING PARTS)
12 12
-57 AN526C1032R81 SCREW

1 I
1- C-2534-3 RING, STOP AND BULKHEAD ASSY
BULKHEAD ASSY 1 1
-58 C-2534-2
n :I
1- 830-8 STOP ASSY, Automatic
high pitch
COTTER PIN 1 I
-59 AN380-2-2
1 1
-60 A-884 SPRING
PIN 1 1
-61 A-883
BRACKET 1 t
-62 B-1353
1 1
-63 C-2128-1 RING, Anti-icing
(ATTACHING PARTS)
BOLT 6 6
-64 AN4H-15A
WASHER 12 12
-65 AN960-416
6 6
-66 4-1865 WASHER
NUT 6 6
-67 AN364-428
1 1
1- C-2504 SPINNER ASSEMBLY (Non-anti-icing)
1 1
-54 C-2531-2 DOME ASSEMBLY
15 15
-55 AN526C1032R SCREW
1 1
1- C-2534 BULKHEAD ASSEMBLY With Stops..........
1 1
-58 C-2534-1 BULKHEAD ASSEMBLY
S 3
1- 830-8 STOP ASSFIMBLY, Automatic high

-70 PRP-914-41 "O" RING, (Optional) 1

840-74 HUB SPIDER SUBASSEMBLY 1
1-
C-1853 HUB SPIDER i 1 3
-52
A-1884 PILOT TUBE 1
c53
A-1817 BUSHING
-69
for PRI’909--1G.
Corresponding MS29513 "O" rings may be substituted for PRP "O" rings except

11
 1 68

~5

Io 4
66 11
62

ss
,52
58/ 49
;!3
61 22
$1 t-59

Y 46
35
45

38

42 33

j
34
40 32

55~d

Figure i. Model HC-B3~30-2B Propeller, Exploded View

09
 FAAApproved
i? I Manual No. 1138, Rev. 24 HARTZELL
61-1 0-13
April 2001

Compact Non-Feathering(-l) and

Aerobatic (-4) Propeller
Overhaul and I\llaintenance Manual
Two Blade Three Blade Four Blade

BHC-C2YF-1 B(L)(F) HC-C3YF-1(R)(L)(F) HC-C4YF-1(E)

CHC-C2YF-1 B(L)(F) PHC-C3YF-1MF HC-F4YR-1
DHC-C2YF-1 B(L)(F) PHC-C3YF-1 R(F)
HC-C2YF-1 B(L)(F) HC-C3YN-1(F)
HC-C2YK-1 B(L)(F) HC-C3YR-1A
HC-C2YL-1 B(L)(F) HC-C3YR-1MF
HC-C2YR-1 B(F) HC-C3YR-1(R)(L)(F)
HC-E2YL-1B(L)(F) HC-E3YR-1 R(L)F
HC-E2YR-1 B(L)(F) HC-F3YR-1ARF
HC-E2YR-1(S)(F) HC-F3YR-1 RF

6j HC-F2YL-1F
HC-F2YR-1(F)
PHC-G3YF-1E
HC-G3YF-1 RF
BHC-G2YF-1 BF PHC-GSYF-lRF
BHC-12YF-1 BF HC-H3YF-1 RF
HC-12YF-1 BF PHC-H3YF-1 RF
HC-12YR-1BF HC-13YR-1E
BHC-J2YF-1 B(F) H%-13YR-1 RF
BHC-J2YF-1C PHC-J3YF-1MF
BHC-L2YF-1 BF HC-JSYF-1 RF
HC-M2YR-1 BF PHC-J3YF-1 RF
8l-lC-C2YF-4(8)(F) EHC-L3YF-1 RF
HC-C2YF-4(B)(F) PHC-L3YF-1 RF
MC-C2YK-4(A, B,C)(F) HC-L3YF-1 RF
HC-C2YL-4(B)(F) I HC-M3YR-1 RF
HC-C2YR-4(A,B,C)(L)F HC-C3YF-4(B)F
HC-C2YR-4E PHC-C3YF-4(B)F
HC-C2YR-4G HC-C3YN-4(B)F
BHC-12YF-4(B)F HC-C3YR-4A
HC-12YF-4(B)F HC-C3YR-4(B)F
BHC-L2YF-4(B)F I HC-C3YR-4G
HC-L2YF-4(B)F PHC-H3YF-4BF

HartzellPropeller Inc.
One Propeller Place
Pique, Ohio 45356-2634 U.S.A.
Phone: 937.778.4200
Fax: 937.778.4365
 i

(This page is intentionally blank.)

INSIDE COVER 61’1 0’1 3

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24 See Highlights 4/1/01 9/3/01 ATPIRCL

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

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23 tnI~c/o

24 (F~/04 9/3/01 ATP/RCL,

RECORD OF REVISIONS 61 -1 0-1 3 Rev 17

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

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TRNumber IssueDate Inserted Inserted Removed Removed

RECORD OF TEMPORARY REVISIONS 61 -1 0-1 3 Rev. 17

 PROPELLER MAINTENANCE MANUAL
MP~ RTZ c L L 113B

RECORD OF TEMPORARY REVISIONS TO THIS MANUAL

Update this page to show all TEMPORARY REVISIONS inserted into this manual.

Date Date
TRNumber IssueDate Inserted Inserted Removed Removed

RECORD OF TEMPORARY REVISIONS 61 ’1 0’1 3 Rev. 17

HARTZELL PROPELLER INC. HARTZELL
One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.
Telephone: 937.778.4200
Fax: 937.778.4365 MANUAL REVISION TRANSMITTAL
Manual 113B (61-10113)
Compact Non-Feathering (-1) and Aerobatic (-4) Propeller
Overhaul and Maintenance Manual

REVISION #24 dated A~ril. 2001

113B.
Attached is a copy of Revision #24 to Hartzell Manual

Page Control Chart for Revision #24:

Remove Insert
Page No. Page No.

COVER COVER

pages 1 and 2 pages 1 and 2

REVISION HIGHLIGHTS REVISION HIGHLIGHTS

pages 1 and 2 pages 1 and 2

AIRWORTHINESS LIMITATIONS AIRWORTHINESS LIMITATIONS

pages 1 and 2 pages 1 and 2

LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES

pages 1 and 2 pages 1 through 4

TABLE OF CONTENTS TABLE OF CONTENTS

pages 3 through 8 pages 3 through 8

INTRODUCTION INTRODUCTION

pages 1 through 10 pages 1 through 12

CHECK CHECK

pages 5-5 and 5-6 pages 5-5 and 5-6

pages 5-9 and 5-10 pages 5-9 and 5-10
pages 5-17 and 5-18 pages 5-17 and 5-18

REPAIR REPAIR
6-10 pages 6-1 through 6-16
pages 6-1 through
ASSEMBLY ASSEMBLY

pages 7-1 and 7-2 pages 7-1 and 7-2

pages 7-5 through 7-14 pages 7-5through 7-14
pages 7-17 through 7-24 pages 7-17 through 7-24
pages 7-27 and 7-28 pages 7-27 and 7-28
pages 7-28.1 and 7-28.2
pages 7-29 and 7-30 pages 7-29 and 7-30
pages 7-37 and 7-38 pages 7-37 and 7-38
pages 7-43 and 7-44 pages 7-43 and 7-44

FITS AND CLEARANCES FITS AND CLEARANCES

pages 8-5 and 8-6 pages 8-5 and 8-6

ILLUSTRATED PARTS LIST ILLUSTRATED PARTS LIST

pages 10-41 and 10-42 pages 10-41 and 10-42

pages 10-59 through 10-62 pages 10-59 through 10-62
pages 10-67 through 10-110 pages 10-67 through 10-110
pages 10-111 and 10-111.1 pages 10-111 and 10-111.1
pages 10-111.2 and 10-112 pages 10-111.2 and 10-112
pages 10-113 through 10-116 pages 10-113 through 10-116

NOTE: When the manual revision has been inserted in the manual, record the information
required on the Record of Revisions page in this manual.
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 113B

REVISION HIGHLIGHTS

Revised Cover, Highlights, and List of Effective Pages to reflect the manual

revision.

Added model HC-C2YR-4CF/FC8475-6 to the Ainnrorthiness Limitations chapter.

Revised the Introduction chapter

Added definitions for Blade Station, Gauge (Bearing Ball), Reference Blade

Radius, and Track.

Updated hub replacement under the Component Life section.

Revised the Check chapter:

Revised the cylinder inspection criteria.

Revised Figure 5-3, Pitch Change Block Identification/Dimensional Criteria.

Revised the procedure for repair of damaged cylinder wrench attachment holes.

Added additional spinner part numbers to the bulkhead modification section.

Revised the Repair chapter:

Added spinner bulkhead modification for three-bladed propellers.
Revised the Assembly chapter:
Revised the CAUTION concerning bearing balls.
Revised the compact hub assembly procedures and referred the reader to
Hartzell Manual 202A (61-01-02).

Referred the reader to Hartzell Standard Practices Manual 202A (61-01-02) for
mounting flange stud installation instructions and removed the mounting flange
stud installation instructions.

Revised the instructions concerning torquing the piston nut.

Added a section "Application of Blade Angle Reference Tape" to the Assembly

chapter.
Revised Table 8-1, Torque Values, in the Fits and Clearances chapter.
Revised the illustrated parts list to include various changes and corrections.

HIGHLIGHTS 61-10-13 Rev 24PABpSr~b:

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

REVISIONS HIGHLIGHTS

1. Introduction

A. General

This is a list of current revisions that have been issued against this manual.
Please compare to RECORD OF REVISIONS page to ensure that all revisions
have been added to the manual.

B. Components
(1) Revision No. indicates the revisions incorporated in this manual.

(2) Issue Date is the date of revision.

(3) Comments indicates the level of the revision.

(a) New Issue is manual distribution. The manual is distributed in its

a new

entirety. All the revision dates are the same and no change bars are used.

(b) Reissue is a revision to anexisting manual that includes major content

and/or major format changes. The manual is distributed in its entirety. All
the revision dates are the same and no change bars are used.

(c) Major Revision is revision to an existing manual that includes major

a

content or minor format changes over a large portion of the manual. The
manual is distributed in its entirety. All the revision dates are the same, but
change bars are used to indicate the changes incorporated in the latest
revision of the manual.

(d) Minor Revision is a revision to an existing manual that includes minor

content changes to the manual. Only the revised pages of the manual are
distributed. Each page retains the date and the change bars associated
with the last revision to that page.

Revision No. Issue Date Comments

Revision 17 Nov/97 Total rewrite

Revision 18 Feb/99 Minor Revision
Revision 19 Mar/99 Minor Revision
Revision 20 Apr/99 Minor Revision
Revision 21 Aug/99 Minor Revision
Revision 22 Jun/GO Major Revision
Revision 23 Dec/GO Minor Revision
I Revision 24 Apr/Ol Minor Revision

REVISION HIGHLIGHTS 61’1 0’1 3 Rev.

2
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

LIST OF EFFECTIVE PAGES

Date Chapter Page Date

Chapter Page

Cover/inside Cover 1 and 2 Apr/Gl I I Check 5-18 Jun/GO

Revision Highlights 1 and 2 Apr/Gl i I I Repair 6-1 and 6-2 Apr/Gl

1 and 2 Jun/GO I I I Repair 6-3 Jun/GO

Record of Revisions

Record of Temporary 1 and 2 Jun/GO I I I Repair 6-4 thru 6-5 Apr/Gl

Revisions
IIIRepair 6-6 Jun/GO

Jun/GO
Service Document List 1 and 2
I I Repair 6-7 thru 6-16 Apr/Gl
AiMlorthiness Limitations 1 and 2 Apr/Ol I I I Assembly 7-1 and 7-2 Apr/Ol
List of Effective Pages 1 and 2 Apr/Ol I I I Assembly 7-3 and 7-4 Jun/GO

Jun/GO
Table of Contents 1 thru 3
I I I Assembly 7-5 Apr/Ol
Table of Contents 4 Apr/Ol I I Assembly 7-6 Jun/GO

Jun/GO
Table of Contents 5
I I I Assembly 7-7 thru 7-10 AprlOl
Table of Contents 6 and 7 Apr/Gl i I I Assembly 7-11 Jun/GO

Jun/GO
Table of Contents 8
I I I Assembly 7-12 and 7-13 Apr/Gl
Introduction 1 and 2 Apr/Gl I I I Assembly 7-14 thru 7-28 Jun/GO

Introduction 3 Jun/GO
I I I Assembly 7-18 and 7-19 Apr/Ol
Introduction 4 thru 12 Apr/Gl I I I Assembly 7-20 and 7-21 Jun/GO

Description and Operation 1 thru 6 Jun/GO

I I I Assembly 7-22 and 7-23 Apr/Ol
Description and Operation 5 Dec/GO
I I I Assembly 7-24 through 7-28 Jun/GO

Description and Operation 6 Jun/GO

I I I Assembly 7-28.1 and 7-78.2 Apr/Gl
Testing and Fault Isolationt-l thru 1-10 Jun/GO
I I I Assembly 7-29 Apr/Ol
Jun/GO
Automatic Test 2-1 thru 2-2
I I Assembly 7-30 Jun/GO
Requirements
Assembly 7-31 Dec/GO
Disassembly 3-1 thru 3-8 Jun/GO
Assembly 7-32 thru 7-36 Jun/GO
Cleaning 4-1 thru 4-2 Jun/GO
Assembly 7-37 Apr/Gl
Check 5-1 thru 5-4 Jun/GO
Assembly 7-38 thru 7-42 JunlGO
Check 5-5 Apr/Gl
Assembly 7-43 Apr/Ol
Check 5-6 thru 5-9 Jun/GO
Assembly 7-44 Jun/GO
Check 5-10 Apr/Ol
Fits and Clearances 8-1 thru 8-4 Jun/GO
Check 5-11 thru 5-16 Jun/GO
Fits and Clearances 8-5 Apr/Ol
Check 5-17 Apr/Gl

LIST OF EFFECTIVE PAGES 61 11 011 3 Rev. 24~AapSr/eOlPage

 PR6PELLER
HARTZELL M*~NANCE
B311LAUNAM

LIST OF EFFECTIVE PAGES

Chapter Page Date Chapter Page Date

I Fits and Clearances 8-6 Jun/GO I I I Illustrated Parts List 10-87 Apr/Ol

Special Tools, Fixtures, 9-1 thru 9-4 Jun/GO I I I Illustrated Parts List 10-88 Jun/GO
andEquipment
Illustrated Parts List 10-89 Apr/Gl
Illustrated Parts List 10-01 and 10-2 Dec/GO
Illustrated Parts List 10-90thru 10-92 Jun/GO
Illustrated Parts List 10-03 thru 10-41 Jun/GO
Illustrated Parts List 10-87 Apr/Ol
Illustrated Parts List 10-42 Apr/Ol
Illustrated Parts List 10-88 Jun/GO
Illustrated Parts List 10-43thru 10-58 Jun/GO
Illustrated Parts List 10-89 Apr/Gl
Illustrated Parts List 10-59 Apr/Ol
Illustrated Parts List 10-90thru 10-92 Jun/GO
Illustrated Parts List 10-60 Jun/GO
illustrated Parts List 10-93 Apr/Gl
Illustrated Parts List 10-61 Apr/Gl
Illustrated Parts List 10-94 Jun/GO
Illustrated Parts List 10-62thru 10-66 Jun/GO
Illustrated Parts List 10-95 Apr/Ol
Illustrated Parts List 10-67 Apr/Gl
Illustrated Parts List 10-96 Jun/GO
Illustrated Parts List 10-68 Jun/GO
Illustrated Parts List 10-97 Apr/Ol
Illustrated Parts List 10-69 Apr/Gl
Illustrated Parts List 10-98 Jun/GO
Illustrated Parts List 10-70 Jun/GO
Illustrated Parts List 10-99 Apr/Gl
Illustrated Parts List 10-71 Apr/Ol
Illustrated Parts List 10-100 Jun/GO
Illustrated Parts List 10-72 Jun/GO
Illustrated Parts List 10-101 Apr/Gl
Illustrated Parts List 10-73 Apr/Ol
Illustrated Parts List 10-102 Jun/GO
Illustrated Parts List 10-74 Jun/GO
illustrated Parts List 10-103 Apr/Gl
Illustrated Parts List 10-75 Apr/Ol
Illustrated Parts List 10-104 Jun/GO
Illustrated Parts List 10-76 Jun/GO
Illustrated Parts List 10-105 Apr/Ol
Illustrated Parts List 10-77thru 10-79 Apr/Ol
Illustrated Parts List 10-106 Jun/GO
Illustrated Parts List 10-80 Jun/GO
Illustrated Parts List 10-107 Apr/Gl
Illustrated Parts List 10-81 Apr/Gl
Illustrated Parts List 10-108 Jun/GO
Illustrated Parts List 10-81.1 and 10-81.2 Dec/GO
Illustrated Parts List 10-109 Apr/Ol
Illustrated Parts List 10-82and 10-83 Apr/Gl
illustrated Parts List 10-110 and 10-111 Jun/GO
Illustrated Parts List 10-84 Jun/GO
Illustrated Parts List 10-111.1 and 10-111.2Dec/GG
Illustrated Parts List 10-85 Apr/Ol
Illustrated Parts List 10-112 Jun/GO
Illustrated parts List 10-86 Jun/GO
Illustrated Parts List 10-113 Apr/Ol

LIST OF EFFECTIVE PAGES 61’1 0’1 3 Rev. 24 Apr/OlPage 2

 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

LIST OF EFFECTIVE PAGES

Date Chapter Page Date

Chapter Page

Illustrated Parts List 10-114 Jun/GO

Illustrated Parts List 10-115 Apr/Ol

Illustrated Parts List 10-116 thru 10-132 Jun/GO

LIST OF EFFECTIVE PAGES 61-10-13 Rev. 24 Apr/OlPage

 PROPELLER
HA RTZ E L L MA:N:3EsNANCE MANUAL

LIST OF EFFECTIVE PAGES

Chapter Page Date Chapter Page Date

LIST OF EFFECTIVE PAGES 61 ’1 0’1 3 Rev. 24 Apr/OlPage 4

 PROPELLER MAINTENANCE MANUAL
HA RT Z E LL 1138

SERVICE DOCUMENT LIST

The following is a list of service documents that have been incorporated.

Document Date of Document Date of

Number Manual Number Manual

SE 142B Rev. 17 Nov/97

HC-SB-61-224 Rev. 18 Feb/99

SI 152 Rev. 17 Nov/97

SI 202A Rev. 17 Nov/97

SL 100 Rev. 17 Nov/97

SL 82A Rev. 18 Feb/99

SL 155A Rev. 17 Nov/97

SL SL-61-17_0 Rev. 18 Feb/99

SL SL-61-177 Rev. 18 Feb/99

SL SL-61-179 Rev. 18 Feb/99

IISLSL-61-199 I Rev. 22Jun/00

SERVICE DOCUMENTS LIST 61

-1 0-1 3 R"´•
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

SERVICE DOCUMENT LIST (CONT’D)

The following is a list of service documents that have been
incorporated.

Document Date of Document Date of

Number Manual Number Manual

I 61-10-13 Rsv. 22
2
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

CONTENTS

HIGHLIGHTS

RECORD OF REVISIONS 1

RECORD OF TEMPORARY REVISIONS 1

SERVICE DOCUMENTS LIST

AIRWORTHINESS LIMITATIONS

LIST OF EFFECTIVE PAGES 1

TABLE OF CONTENTS 1

I
1. List of Illustrations

2. List of Tables 8

INTRODUCTION 1

1. Statement of Purpose 3

A. General 3

Publications 4
2. Required
A. Hartzell Publications 4

B. References to Hartzell Publications 4

5
I C. Vendor Publications

3. Personnel Requirements 5

4. Calendar Limits and Long Term Storage 5

A. Calendar Limits
6
B. Long Term Storage
6
5. Component Life and Service
A. Overhaul

B. 6
Damage
7
C. Blade Repair
7
D. Component Life
8
6. Working Definitions
7. Abbreviations 10

T,,,,o, CONTENTS 61’10’13 Rev. 22

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

DESCRIPTION AND OPERATION 1

1. Description
A. General 3

B. Components 3

2. Operation 3

A. Compact Constant Speed Non-Feathering Propellers (-1) 3

B. Constant Speed Aerobatic Propellers (-4) 3

3. R-flange Hub Substitution for K-flange Hub 6

TESTING AND FAULT ISOLATION 1-1

1. Trouble-Shooting Guide 1-3

A. Pitch Control Difficulty. 1-3

B. Friction. 1-3

C. Abnormal Propeller Vibration. 1-5

D. Blades Not Tracking. 1-5

E. End-Play Movement of the Blade. 1 -7

F In-and-Out Movement of the Blade. 1-7

G. Fore-and-Aft Movement of the Blade 1-7

H. Radial Play in the Blade. 1-7

I. Oil Leakage 1-8

J. External Grease Leakage 1-8

2. Lightning Strike on Hub or Blade 1-9

AUTOMATIC TEST REQUIREMENTS 2-1

DISASSEMBLY 3-1

1. Removal of the Propeller Assembly from the Engine 3-3

A. General

B. Spinner Disassembly 3-3

C. Propeller Removal 3-3

2. Marking Before Disassembly 3-3

3. Removal of the Propeller De-icer System (where applicable) 3-4

61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 113B

3-4
4. Propeller Disassembly
3-4
A. Disassembly of the Propeller Pitch Change Parts
3-6
B. Hub Disassembly
Fork Disassembly 3-6
C. Pitch Change
Block Disassembly 3-6
D. Pitch Change
Unit Disassembly 3-6
E. Split-Hub
3-7
5. Blade Disassembly
3-7
A. Blade Bearing System Disassembly
CLEANING 4-1

CHECK 5’1

Interval Requirements 5-3

1. Inspection
5-3
2. Inspection Requirements
5-4
3. Replacement Requirements
5-4
4. Repair
5. Hub Unit Inspection
Procedures 5-4
6. Specific Inspection
Checks 5-4
7. Specific
5’5
A. Cylinder
B. Fork 5’6

C. Pitch Stop 5-7

High
5’7
D. Hub Bolt Inspection
E. Hub Unit 5’7

5-8
F Low Pitch Stop Screw
G. Piston 5-9

5-11
H. Pitch Change Block
5-13
i. Pitch Change Rod..............
J. Preload Plate 5’15

Race 5-17
K. Retention Bearing
5-18
L. Spring

CONTENTS 61’10’13 Rev.

 PROPELLER
nARTZELL

REPAIR 6-1

1, Repair Requirements 6-3

A, Aluminum Parts

B, Steel Parts 6-3

2, Specific Repair Requirements 6-4

A, Repair of Damaged Cylinder Wrench Attachment Holes, 6-4

B, Spinner Bulkhead Modification 6-5

ASSEMBLY 7-1

1, Blade Assembly Procedures 7-3

A, General, 7-3

B, Installation of the Pitch Change Knob (Composite Blades Only), 7-3

C, Installation of the Blade Bearing Race and Balls 7-5

D, Installation of the Preload Bearing Inside Race to the

Preload Plate Spindle 7-5

I 2, Compact Hub Assembly Procedures

A, Preparation of the hub for assembly,
7-9

7-9

B, Two Blade Compact Hub Blade Installation 7-15

C, Three Blade Compact Hub Blade Installation 7-20

D, Four Blade Compact Hub Blade Installation 7-24

E, Hydraulic Pitch Change Unit Assembly 7-29

F. Installation of the Lubrication Fitting 7-43

3, Counten~veight Installation (Aerobatic Only) 7-44

4, Propeller Lubrication 7-44

5, Static Balance 7-44

FITS AND CLEARANCES 8-1

i, Torque Values
SPECIAL TOOL, FIXTURES, and EQUIPMENT.............................................................,.., 9-1

1, Minimum Facility and Tooling Requirements 9-3

A, Tooling 9-3
B, Facilities 9-3
2, Special Tools
A, Special Tools 9-3
B, Listings 9-3

61-10-13 Rev.a4PAap~b:
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

ILLUSTRATED PARTS LIST 10-1

1. Introduction 10-5

A. General 10-5

B. Using the Illustrated Parts List 10-5

C. Propeller Assemblies Configured with a De-ice System 10-5

2. The Illustrated Parts List

A. Detailed Parts List 10-6

B. Revisions 10-7

C. Vendors 10-3

3. F and N Flange Studs

4. Two Bladed Propeller Improvements 10-0

5. Three Bladed Propeller Improvements 10-10

A. New Hub part Numbers 10-10

B. Three Bladed -1( and -1R( Propeller Models 10-10

6. A-3204 and A-3204-2 Set Screws 10-10

1 0-1 17
Spinner Assembly Parts
Spinner Mounting Kit Parts 10-130

T,,,EO, CONTENTS 61’10’13 Rev. 22

 PROPELLER
HA RTZ E L L MA:N:3EsNANCE MANUAL

LIST OF ILLUSTRATIONS

Propeller Model Designation System Figure 1 .......................4

Checking Blade Movement Figure 1-1 1-6

Cylinder Figure 5-1 5-5

Low Pitch Stop Screws Figure 5-2 5-8

Pitch Change Block Identification/Dimensional Criteria Figure 5-3 5-10

Pitch Change Rod Figure 5-4 5-12

Preload Plate Figure 5-5 5-14

Retention Bearing Inspection Figure 5-6 5-16

Installing the Reinforcing Brackets Figure 6-1 6-6

Bulkhead Cutout Dimensions Figure 6-2 6-8

Bulkhead Template Figure 6-3

I Three-bladed

Three-bladed
Propeller Bulkhead
Propeller Bulkhead
Modification Dimensions

Modification Template
Figure 6-4
Figure 6-5
6-14

6-15

Installation of the Blade Retention Bearing Figure 7-1 7-4

Pressing the Preload Bearing onto the Preload Plate Spindle Figure 7-2 7-4

Installation of the Preload Plate to the Blade Shank Figure 7-3 7-6

Applying the Clamping Tool TE24 to the Blade Assembly Figure 7-4 7-6

Installing the Anti-rotation Plate Figure 7-5 7-7

I Spark Gap Screw, PHC-G3YF-1E and HC-13YR-I E Propellers Figure 7-6 7-8

Spark Gap Screw, HC-C3YR-4(A,G) and HC-C2YR-4(E,G) Figure 7-7 ..........,..7-11

Installation of the Flange O-Ring in the Engine Half Hub Flange Figure 7-8 7-13

Installation of the Engine-Side Hub Half on the Assembly Stand Figure 7-9 7-14

Blade Number One Installed in the Hub Figure 7-10 7-15

Installing the Cylinder-Side Hub Half Figure 7-11 7-16

Installation of Blade Number 1 Figure 7-12 7-18

Installation of Sealant on the Hub Parting Surface Figure 7-13 7-19

Installing Hub Half in Preparation forTightening Preload Plate Figure 7-14 7-20

Tightening Preload Plate Hex Head Screw and Jam Nut Figure 7-15 7-21

Pitch Change Blocks Installed on Blades Two and Three Figure 7-16 7-22

Pitch Change Fork Installed on Blades Two and Three Figure 7-17 7-23

61-10-13
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

LIST OF ILLUSTRATIONS (Cont’d~

Installation of Blade One into Hub Figure 7-18 7-24

Installation of Front Half of Hub Figure 7-19 7-25

Installation of Pitch Change Fork Figure 7-20 7-26

Installation of Blade Number One into the Hub Figure 7-21 7-27

Installation of Sealant Between the Hub Halves Figure 7-22 7-28

Wire Harness Bracket Location Figure 7-23 7-31

Installation of High Pitch Stop Split Ring Retainer Figure 7-24 7-32

Installation of High Pitch Stop and High Pitch Stop O-Ring Figure 7-25 7-32

Installing the A-2213-( Spring Figure 7-26 7-36

the Pitch Change Rod Figure 7-27 7-36

Installing the Piston on

Cotter Pin Installation Figure 7-28

Installing the Piston on the Pitch Change Rod Figure 7-29 7-38

Figure 7-30 7-38

Installing the D-6509-( Spring
Installing the Cylinder with Cylinder Torque Wrench
Adapter TE153 Figure 7-31 7-40

Low Pitch Stop Figure 7-32 7-41

Installing the
Blade Track Figure 7-33 7-42
Checking
Hub Leak Check Figure 7-34 7-43

Installed in Hub Figure 7-35 7-44

Lubrication Fittings
Determining Torque Value of a Standard Torque Wrench
with Adaptor Figure 8-1 8-3

Two Blade Propeller Exploded View Figure 10-1 10-11

Three Blade Propeller Exploded View (Except -1MF and -1E) Figure 10-2 10-12

Three Blade -1MF and -1E Propeller Exploded View Figure 10-3 10-13

Four Blade Propeller Exploded View Figure 10-4 10-14

Blade Exploded View Figure 10-5

F Flange Mounting Parts Figure 10-6 10-16

N Flange Mounting Parts Figure 10-7 10-17

I CONTENTS 61 -1 0-1 3 Rev

 PROPEL"R
HARTZELL MA:N~PINCE MPINUIL

LIST OF TABLES

Component Description Table 1-1 ......................7

Component Inspection Criteria Table 5-1 5-5

Piston Dimensional Inspection Criteria Table 5-2 5-9

Pitch Change Rod Identification Table 5-3 5-13

A-2420-( High Pitch Stop Heights Table 7-1 7-34

B-6515-( High Pitch Stop Heights Table 7-2 7-35

Torque Values Table 8-1 8-5

Blade Tolerances Table 8-2 8-6

-1, -1A, and -1B Propeller Model Part Substitutions Table 10-1 10-9

T~BLE OF CONTENTS 61’1 0’13 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1138

AIRWORTHINESS LIMITATIONS

The Airworthiness Limitations section is FAA approved and specifies maintenance

required under 43.16 and 91.403 of the Federal Aviation Regulations unless an
alternative program has been FAA approved.

FAA APPROVED

I by: date: jlLls~On

~Royace H. Prather
Manager, Chicago Aircraft Certification Office,
ACE-1 15C
Federal Aviation Administration

Log of Revisions to Airworthiness Limitations

Rev No DescriPtion of Revision II Rev No. I Description of Revision

20 Added model:

HC-C2Y R-4C F/FC8477A-4

Added model:

I
24

HC-C2YR-4C F/FC8475-6

AIRWORTHINESS LIMITATIONS 61-10-13 Rev. 24 Apr/OlPage

 PROPELLER MAINTENANCE MANUAL
HP~ RT Z E L L 113B

AIRWORTHINESS LIMITATIONS

1. The FAA establishes specific life limits for certain component parts, as well as the entire
propeller. Such limits require replacement of the identified parts after a specified number
of hours of use.

2. The following data summarizes all current information concerning Hartzell life limited parts
as related to propeller models affected by this manual. These parts are not life limited on

other installations; however, time accumulated toward life limit accrues when first operated
on ai rcraft/eng i ne/p repeller com bi nations listed, and contin ues regard less of su bseq u ent
installations (which may or may not be life limited).
A. The following specifies life limits for blades only. Associated hub parts are not
list
affected. Blade models shown are life limited only on the specified applications.

Aircraft Engine
Ine I
ProPeller Blade Life Limit

Mooney PFM Porsche BHC-J2YF-1 C/87421 3,000 hours

I Aviat Pitts S-2B LycomingAEIO-540-D4A5 HC-C3YR-1 An690C 12,500 hours

Aviat Pitts S-2S Lycoming AEIO-540-D4A5 HC-C2YR-4CF/FC8477A-4 2,000 hours
Aviat Pitts S-2B Lycoming AEIO-540-D4A5 HC-C2YR-4CF/FC8477A-4 2,000 hours
SOCATATB30 Lycoming AEIO-540-L1 B5D HC-C2Y2-4C4/FC8474-5 4,000 hours

B. The following list specifies life limits for parts other than blades. Parts listed are life
limited only on the specified applications.

Ai re raft Engine Propeller Hub Unit Life Limit

Aviat Pitts S-2S Lycoming AEIO-540-D4A5 HC-C2YR-4CF/FC8477A-4 2,000 hours

Aviat Pitts S-2B Lycoming AEIO-540-D4A5 HC-C2YR-4CF/FC8477A-4 2,000 hours

I
SOCATATB90 Lycoming AEIO-540-L1 B5D HC-C2Y2-4C4/FC8474-5 4,000 hours
("A" suffix serial numbers)
SOCATATB-30 Lycoming AEIO-540-L1 B5D HC-C2Y2-4C4/FC8474-5 16,000 hours
("B" suffix serial numbers)

FAA APPROVED

I bv’ date: 1H 1L~

Royace H. Prather
Manager, Chicago Aircraft Certification Office,
ACE-1 15C
Federal Aviation Administration

2
~LIRWORTnlNESS LIMITATIONS 61 -1 0-1 3 Rev. 24 Apr/OlPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

CONTENTS

3
1. Statement of Purpose. . . . . . . . .´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•
3
A. General
4
2. Required Publications
4
A. Hartzell Publications. . . . . . .´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
4
B. References to Hartzell Publications
5
C. Vendor Publications
5
3. Personnel Requirements
Term Storage 6
4. Calendar Limits and Long
6
A. Calendar Limits
6
B. Long Term Storage. . . . . . . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•
Life and Service 7
5. Component
7
A. Overhaul. . . . . . . . . . . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•
7
B. Damage
7
C. Blade Repair
8
D. Component Life
Definitions 9
6. Working
12
7. Abbreviations

INTRODUCTION 61’10’13 ReV.24PAap~b:

 PROPELLER
HARTZ E LL MA:NI~EsNANCE MANUAL

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I INTRODUCTION 61’10’13 Rev. 24

Page 2
Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

INTRODUCTION

1. Statement of PurPose

A. General

(1) This manual provides maintenance and overhaul procedures for non-feathering
(-1) and compact (-4) propellers manufactured by Hartzell Propeller Inc.

(2) Contact the Product Support Department of Hartzell Propeller Inc. concerning
any maintenance problems or to request information not covered in this
publication.
Hartzell Product Support may be reached during business hours (8:00 a.m.

through 5:00 p.m., United States Eastern Time) at (937) 778-4379.

After business hours, you may leave a message on our 24 hour product
support line at (937) 778-4376. A technical representative will
contact you

during normal business hours. Urgent AOG support is also available 24

hours per day, seven days per week via this message service.

Additional information is available on our website at www. hartzellProP.com.

NOTE: When calling from outside the United States, dial (001) before dialing
the above telephone numbers.

(3) This manual is written with the intent that it is to be used by propeller repair
stations with personnel who are trained and experienced with Hartzell products.
This manual does not provide complete information for an inexperienced
technician to attempt propeller overhaul without supervision.

(4) This manual is intended to be the primary source of overhaul information for
non-feathering (-1) and compact (-4) propellers. This manual no longer
contains blade overhaul procedures. Refer to the appropriate Hartzell manual
for blade overhaul. In addition to this manual, the reader must consult active
Service Bulletins, Service Letters, Service Advisories, and Service Instructions
for information concerning these procedures that may have not yet been
incorporated into the latest revision of this manual.

(5) This manual makes reference to other Hartzell manuals, particularly the
Hartzell Standard Practices Manual No. 202A (61-01-02), which provides
important details for procedures such as anodizing, penetrant inspection, and
overhaul procedures for hubs.

is written in the format specified by ATA

(6) Where possible, this manual
Specification No. 100.

,,,,o,,,,,,, 61-10-13
 PROPELLER MAINTENANCE MANUAL
H19 RT Z E L L 1138

2. Reauired Publications

A. Hartzell Publications

(1) In addition to this manual, one or more of the following publications are
required for information regarding specific recommendations and procedures to
maintain propeller assemblies.

Hartzell
Manual No. ATA No. Title
115 61-00-15 Propeller Owner’s Manual, Aluminum Blades
145 61-00-45 Propeller Owner’s Manual, Composite Blades
126 61-00-26 Set of active SE, SA, SL, SI
127 61-16-27 Spinner Assembly Maintenance Guide
133C 61-13-33 Aluminum Blade Overhaul Manual
135F 61-13-35 Composite Blade Maintenance Manual
165A 61-00-65 Illustrated Tool and Equipment Manual
202A 61-01-02 Standard Practices Manual
159 61-02-59 Hartzell Propeller Inc. Application Guide

(2) For Harttell service literature and revisions, contact:

Hartzell Propeller Inc. Telephone: 937.778.4200

Attn: Service Documents
Secretary Fax: 937.778.4365
One Propeller Place
Piqua,Ohio 45356-2634 U.S.A

B. References to Hartzell Publications

(1) Item references throughout the text in this manual refer to item numbers in the
Illustrated Parts List
Chapter. The item numbers appear in parentheses directly
following the part name. Only the item base number will appear in the text of
the manual. Item base numbers and the alpha variants of the base numbers
will appear in the illustrated parts list. There are two reasons for the use of
alpha variants:
(a) A part may be superseded, replaced, or obsoleted by another part. For
example, the blade O-ring (C-3317-339) that is item 540 was superseded
by the blade quad ring seal (B-3883-4339) that is item 540A.

(b) An Illustrated Parts List may contain multiple configurations. Effectivity

codes are used to distinguish different part numbers within the same list.
For example, configuration may use a blade bushing (A-2413) that is
one

item 565, yet another configuration uses a blade bushing (A-2413-2) that
is item 565A. Effectivity codes are very important in the determination of
parts in a given configuration.

61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

(2) Special tooling is required for procedures throughout this manual. For further
tooling information, refer to Hartzell Manual No. 165A (61-00-65), Illustrated
Tool and Equipment Manual. The reference numbers for tooling appear with
the prefix "TE" directly following the tool name to which they apply. For
example, a template that is reference number 133 will appear as: template
TE133.

(3) Certain instructions throughout this manual refer to consumable materials.

Specific approved materials are listed in Hartzell Manual 202A, (61-01-02)
Standard Practices Manual, Table 8-1. The reference numbers for
consumable materials appear with the prefix "CM" and directly follow the
material to which they apply. For example, an approved adhesive that is
reference number 16 will appear as: adhesive CM16. Only those items

specified may be used.

C. Vendor Publications

None.

3. Personnel Reauirements

Personnel performing inspection, repair, and overhaul of propellers must have

adequate training and experience. Inspection and repair of propeller parts require a
high degree of skill. Therefore, personnel with inspection and supervisory
responsibility are expected to have an FAA Propeller Repairman’s Certificate and a
minimum of 18 months practical experience with Hartzell compact propeller
overhaul. Participation in Hartzell training classes and propeller seminars is
strongly recommended.

I INTnooucnoN 61-10-13 a.. 21P~o:

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

4. Calendar Limits and Long Term Storage

A. Calendar Limits

The effects of exposure to the environment over a period of time create a

need for propeller overhaul regardless of flight time; therefore, a calendar
limit between overhauls is specified in Service Letter 61( and in the
propeller owner’s manual. Experience has shown that special care, such as

keeping an aircraft hangared, is not sufficient to allow extension of the

calendar limit.

NOTE 1: Start date for calendar limit is when the propeller is first installed
on an engine. Calendar limit is not interrupted by subsequent
removal and/or storage.

NOTE 2: Start date for calendar limit should not be confused with
warranty start date (which, with certain exceptions, is normally
the date of installation by the first retail customer).

B. Long Term Storage

Propellers that have been in storage have an additional
inspection requirement
before installation. Refer to the Packaging and Storage chapter of Hartzell
Standard Practices Manual 202A (61-01-02).

I sl-lo-13
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1138

5. Component Life and Service

A. Overhaul

(1) Overhaul is the periodic disassembly, cleaning, inspecting, repairing as

necessary, reassembling, and testing in accordance with approved

standards and technical data approved by the administrator.

(2) The overhaul interval is based on (i.e. flight time) or on

hours of service
calendar time. At such specified periods, the propeller hub assembly and
the blade assemblies should be completely disassembled and inspected for
cracks, wear, corrosion, and other unusual or abnormal conditions. As
specified, certain parts should be repaired, and certain other parts should
be replaced.
(3) Overhaul is to be completed in accordance with the latest revision of the
applicable component maintenance manual and other publications applicable
to, or referenced in, the component maintenance manual.

(4) For overhaul interval information, refer to Service Letter 61~ Owner’s
Manual 115N (61-00-15), or Owner’s Manual 145 (61-00-45).

B. Damage
General procedures for overspeed, foreign object strike (including bent blades),
and fire/heat damage are found in the Special Inspections chapter of Hartzell
Standard Practices Manual 202A (61-01-02).

(1) Airworthy Damage

Airworthy damage isdamage that does not affect the safety or flight
characteristics of the propeller system. The maximum limits of airworthy
damage are specified in the "Check" section. Although a part may continue
in service with airworthy damage, this type of damage should be repaired at
the earliest practical time to prevent further damage to the system.

(2) Unairworthy Damage

Unairworthy damage is damage that exceeds the maximum limits of
airworthy damage. Unairworthy damage can affect the safety or flight
characteristics of the propeller system. This type of damage must be
repaired before the next flight. Exceptions to this policy may be possible,
but require written authorization from Hartzell Propeller Inc.

C. Blade Repair
(1) For aluminum bladerepair criteria, refer to Hartzell Aluminum Blade Overhaul
Manual 133C (61-13-33).

(2) Forcomposite blade repair criteria, refer to Hartzell Maintenance Manual for

Composite Blades 1 35F (61-13-35).

I INTRODVCTION 61 -1 0-13 ReV 24PA~:

 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

D. Component Life

NOTE: Certain components, or in some cases an entire propeller, may be life

limited. It is a regulatory requirement that a record of the time since new
be maintained for all life limited parts.

(1) Component life is expressed in terms of total hours of service (Time Since
New, TSN) and in terms of hours of service since overhaul (Time Since
Overhaul, TSO).

NOTE: TSNTTSO is considered as the time accumulated between rotation

and landing (i.e. flight time).
(2) Both references necessary in defining the life of the component. Some
are

parts are "life limited," which means that they must be replaced after a
specified period of use (TSN).
(3) When a component or assembly undergoes an overhaul, the TSO is
returned to zero hours. Time Since New (TSN) can never be returned to
zero.

NOTE: Repair without overhaul does not affect TSO or TSN.

(4) Time Since New (TSN) records must be maintained in the propeller logbook
along with Time Since Overhaul (TSO).

(5) Blades and hubs are sometimes replaced while in service or at overhaul.
Maintaining separate TSN and TSO histories for a replacement hub or blade is
required. Other propeller components do not require time tracking unless
specifically noted in Hartzell service publications.
(a) Hub replacement
1 If the hub is replaced, the replacement hub serial number must be
recorded (the entry signed and dated) in the propeller logbook. The
propeller will assume the serial number of the replacement hub.

NOTE: Propeller assembly serial numbers are impression

stamped on the hub. Refer to the Parts Identification and
Marking chapter of Hartzell Standard Practices Manual
202A (61-01-02) for stamping information.

2 The TSO and TSN of the replacement hub must be recorded and
maintained in the propeller logbook. The TSN and TSO of the
remaining propeller components are not affected by the hub
replacement and must be maintained separately.

61-10-13,,.,,~:
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

6. Working Definitions
maintenance personnel in
A basic understanding of the following terms will assist
maintaining and operating Hartzell propeller systems.

Term Definition

Annealed softening of material due to overexposure to heat

Blade Station refersto a location on an individual blade forblade

inspection purposes. It is a measurement from the blade
"zero" station to a location on a blade, used to apply
blade specification data in blade overhaul manuals (Note:
do not confuse blade station with reference blade radius;
they may not originate at the same location.)
Brinelling a depression caused by failure of the material in

compression
Corrosion gradual wearing away or deterioration caused by
chemical action
Crack irregularly shaped separation within a material, usually
visible as a narrow opening at the surface
Debond. separation of two materials that were originally
bonded in a separate operation.
Delamination internal separation of the layers of a composite material
Depression. surface area where the material has been compressed
but not removed
Distortion alteration of the original shape or size of
component
a

Erosion. gradual wearing away or deterioration caused by action

of the elements
Exposure leaving material open to action of the elements
Fretting damage that developes when relative motion of small
displacement takes place between contacting parts,
wearing away the surface
term to describe amount by which the mean
Gauge (Bearing Ball)
I
a an

diameter may differ from the nominal diameter.

Gouge............... surface where material has been removed

area

Horizontal Balance balance between the tip and the butt of the blade
Impact Damage damage that occurs when the propeller blade or hub
assembly strikes, or is struck by, an object while in

flight or on the ground

61-10-13 Reu
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

Term Definition

Nick removal of paint and possibly a small amount of

metal (or not exceeding one layer of composite material)
Fitting. formation of a number of small, irregularly shaped
cavities in surface material caused by corrosion or
wear

Porosity an aggregation of microvoids; see "Voids"

Onspeed condition in which the RPM selected by the pilot
through the propeller condition lever and the actual
engine (propeller) RPM are equal
Overhaul (MPI) the periodic disassembly, inspection, repair, refinish,
and reassembly of a propeller assembly
Overspeed. condition in which the RPM of the propeller or engine
exceeds predetermined maximum limits; the condition
in which the engine (propeller) RPM is higher than the
RPM selected by the pilot through the condition lever
Overspeed Damage..... damage that occurs when the propeller hub assembly
rotates at an RPM greater than the maximum engine
RPM as specified in the Aircraft Type Certificate Data
Sheet

Reference Blade Radius. a distance from the

propeller hub centerline to a location
on a blade, used for blade angle measurement in an
assembled propeller. A yellow adhesive stripe (blade
angle reference tape CM160) is usually located at the
reference blade radius location. (Note: do not confuse
reference blade radius with blade station; they may not
originate at the same location.)
Rolling compressive rolling process for the retention area of
single shoulder blades which provides improved
resistance to fatigue
Scratch. same as "Nick"
Shot Peening processwhere steel shot is impinged on a surfaceto
create compressive surface stress which provides
improved resistance to fatigue
Split delamination of a composite blade extending to the
blade surface, normally found near the trailing edge
or tip

Synchronizing. setting all propellers at exactly the same RPM

Synchrophasing a form of propeller sychronization in which not only

the RPM of the engines (propellers) are held constant,

but also the position of the propellers in relation to each
other
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

Term Definition

Track in assembled propeller, a measurement of the

an

location of the blade tip with respect to the plane of

rotation, used to verify face and to compare
alignment
blade tip location with respect to the locations of the
other blades in the assembly

Underspeed. the condition in which the actual engine (propeller)

RPM is lower than the RPM selected by the pilot
through the condition lever
Vertical Balance........ balance between the leading and trailing edges; this
cannot be changed on composite blades
Voids air or gas that has been trapped and cured into a
laminate
Windmilling. the rotation of an aircraft propeller caused by air
flowing over it while the engine is not operating

61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

7. Abbreviations

Abbreviation Term

AN Army-Navy
AOG AircraftOn Ground
ATA AirTransport Association
FAA.........., Federal Aviation Administration
Ft-Lb Foot-Pound
ID Inside Diameter
In-Lb........... Inch-Pound
IPL Illustrated Parts List
Lbs............ Pounds
MIL-X-XXX Military Specification
I MS Military Standard
MPI Major Periodic Inspection
OD Outside Diameter
NAS National Aircraft Standards
PSI Pounds perSquare Inch
RPM Revolutions perhllinute
TBO Time Between Overhaul
TSN......,.., Time Since New
TSO Time Since Overhaul

INTROOUCTION 61-10-13
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 113B

CONTENTS

´•´•´•´•´•´•´•´•´•3
1. Description
A. General 3

3
B. Components
3
2. Operation
3
A. Compact Constant Speed Non-Feathering Propellers (-1)
B. Constant Speed Aerobatic Propellers (-4) 3

Hub Substitution for K-flange Hub 6

3. R-flange

LIST OF ILLUSTRATIONS

Figure 1 4
Propeller Model Designation System

DESCRIPTION AND OPERATION

61 ’1 0’1 3 Rev. 22
 PROPELLER MAINTENANCE MANUAL
H ld~ RTZ E L L Ilss

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I D,,,,,,,,, 61 -1 0-1 3 Rav

 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 113B

1. Description

A. General

Hartzell compact propellers use aluminum or composite blades mounted in an

aluminum hub. The hub is held together with bolts and contains the pitch
changing mechanism. The pitch change components include the piston, piston
rod, and blade actuating components.
B. Components
The model designation system for propellers described in this manual is outlined

I in Figure 1.

2. Operation

A. Compact Constant Speed Non-Feathering Propellers (-1)

Constant utilize oil pressure from an engine
speed non-feathering propellers
mounted governor to move the blades into high pitch or reduced RPM. A spring
and centrifugal twisting moment of the blades moves them to low pitch in the
absence of governor oil pressure.

B. Constant Speed Aerobatic Propellers (-4)

Constant speed aerobatic propellers utilize oil pressure from an engine mounted
on the blade shanks
governor to move the blades into low pitch. Counterleights
move the propeller to high pitch. This arrangement is necessary
because

aerobatic aircraft occasionally encounter situations where the engine is

supplying little or no oil pressure. To increase pitch in order to prevent engine
overspeed in the event of loss of oil pressure, a pressure-to-increase-pitch
propeller is required.
Constant speed propellers utilizing an accumulator (HC-C3YR-IA)
aerobatic
work in the same manner as constant speed non-feathering propellers. Oil
blades to high pitch or
pressure from an engine mounted governor moves the
reduced RPM. The centrifugal twisting moment of the blades moves them to low
pitch in the absence of governor oil pressure. During inverted flight or in
maneuvers which cause engine oil pressure to be less than the pressure
from

the accumulator, a check valve allows accumulator oil to be supplied to the

governor to maintain the appropriate pitch and prevent overspeed.

DESCRIPTION AND OPERATION 61 ’1 0’1 3 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1198

B HC C 2 Y F 1 BF blade model

r
I
REFER TO HARTZELL MANUAL 133( FOR ALUMINUM BLADES.
REFER TO HARTZELL MANUAL 135( FOR COMPOSITE BLADES.

MINOR MODIFICATIONS
BLANK TO4 CHARACTERS
(SEE NEXT PAGE)

SPECIFIC DESIGN I 1 CONSTANTSPEED, NOCOVNTERWEIGHT

FEATURES OIL PRESSURE TO HIGH PITCH CENTRIFUGAL FORCE TO LOW

14 OIL PRESSURE TO LOW PITCH COUNTERWEIGHTS TO HIGH PITCH

BOLT DOWELS NO. OF BOLTS TYPICAL ENGINE

CIRCLE- IN. NO. DIAMETER OR STUDS

HUB MOUNTING F 4´•00 2 1/2 6 (1/2") CONTINENTAL

L 4.75 2 5/8 6 (7/16")
FLANGE
0-290, 0-320LYCOMING
K 4.75 4bushings 3/4 6 (1/2") LYCOMING
R 4.75 5bushlngs 3/4 6 (1/2") LYCOMING
N 4.25 2 1/2 8 (9/16") GTS10520

BLADESHANKTYPE
"Y" SHANK RETENTION SYSTEM, ALUMINUM BLADE,
(METAL BLADES)
ORINTEGRAL PITCH CHANGE ARM
BLADE RETENTION SYSTEM "Y" SHANK RETENTION SYSTEM, COMPOSITE BLADE,
INTE GRALOR BOLTON PITCH CHANGE ARM
(COMPOSITE BLADES)
NUMBER OF BLADES

FLANGE DISTANCE FROM HUB

DESIGNATION PARTING LINE TO FLANGE FACE

C F 3.250
K,R,L 4.187 (HC-C4YR-()= 4.312)
N 3.375
E F,K,R,L 9.187
N 8.375
F R,L 7.187
HUB EXTENSION
G F 4.250
CHARACTERISTIC
H F,N 7.500
R 6.187
F 5.250
J F 6.500
L F 3.750
M R,L 6.750

HC: HARTZELL CONTROLLABLE SINGLE ACTING

BLANK 90AND270 DEGREESCLOCKWISE CONTINENTAL

B- 30AND210DEGREESCLOCKWISE-CONTINENTAL, FRANKLIN,ANDPORSCHE
C 150 AND 330 DEGREES CLOCKWISE LYCOMING AND CONTINENTAL
DOWELLOCATION --I D 60 AND240 DEGREES CLOCKWISE CONTINENTAL
E OAND180 DEGREESAND PROPELLERTDC MARKS
ALIGNED-CONTINENTAL
P 0 AND 180 DEGREES AND PROPELLERTDC MARKS
ALIGNED-CONTINENTAL

Propeller Model Designation System

Figure 1

Page 4
DEOCRIPTION AND OPERITION 61 -1 0-1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1138

BHC-C2YF-1BF

-r
MINOR MODIFICATIONS
-1 PROPS
BLANK TO 4 OHAn.
(prints 0-1740, D-2291, D-2425, 0-2600, 0-6233, E-6749, E-7334)

A C2YF: DIFFERENTSPINNER MOUNTING PARTS;

A-CPYK: DIFFERENTP.C. ROD, FORK
A-HC-CBYR-IA: COMPOSITEBLADE
A HC-F3YR-1ARF:ONE PIECE HUBEXTENSION
I B 2 BLADE: DIFFERENT CYLINDER, P.C. ROD,
SPRING, LOW PITCH STOP
B HC-M2YR-1BF: COMPOSITE BLADE
C BHC-JPYF-1C: COMPOSITE BLADE
D A-2476-3 SPINNER MOUNTING KIT
E C4YF: 8-2984 SPACER with 8-1738 STUDS
E HC-13YR-1E, PHC-GSYF-I E: COMPOSITE BLADE
F LARGE PITCH CHANGE KNOB, FORK
H A-2478-8SPINNER MOUNTING KIT
L-LEFTHANDROTATION
M- 3BLADE: DIFFERENTCYLINDER, P.C.ROD,
SPRING, LOW PITCH STOP
R 3 BLADE: LARGE CYLINDER AND PISTON
J-LEFTHANDTRACTOR
S- HUBEXTENSION

-4 PROPS
(prints D-2265, D-4215, D-4570, E-1801, E-7183, E-7230)

A 2 BLADE: A-2476-8 SPINNER KIT (attaches to hub)

A- HC-C3YR-4A: COMPOSITEBLADE, DIFFERENTCYLINDER,
PISTON, FORK
B 2 BLADE: -2 CYLINDER, LOW STOP SCREW
B 3 BLADE: -2 CYLINDER, LOW STOP SCREW
C 2 BLADE: -2 CYLINDER, LOW STOP SCREW,
and A-2476-8 KIT
E CSYR4E:COMPOSITE BLADE
F LARGE PITCH CHANGE KNOB, FORK
G C2YR-4G, C3YR-4G:COMPOSITE BLADE

Propeller Model Designation System (cont’d)

figure 1

DESCRIPTION FIND OPERPlnON 61

-1 0-1 3 Rev. 23
Dec/GOPage
 PROPELLER
HARTZELL MPI:N~ANCE MPINUPIL

3. R-flanae Hub Substitution for K-flanae Hub

A. Two similar flange designs have been used to mount Hartzell propellers to
Lycoming engines the K-flange and the R-flange. The flange type is part of the
propeller model designation system.
B. Hartzell Propeller Inc. has been manufacturing an improved design of the R-
flange propeller hub for installation on K-flange and R-flange applications. This
allows for the manufacturing of one flange shape without requiring the Aircraft
Type Certificates to be changed to add additional propeller model designations.
C. R-flange propeller hubs will fit and operate properly on K-flange engines;
however, K-flange propellers manufactured with the original hub design will not
fit on R-flange engines.

D. If the replacement of the hub is required, the overhauling facility must ensure
that the propeller model designation (i.e., K or R) is correct according to the
aircraft type certificate. Overhaul facilities may reidentify R-flange hubs as K-
flange hubs (when required by the model designation) by restamping the hub
model designation.

E. Converting an original design K-flange to an R-flange hub is not authorized.

I DESCRIPTION ANO OPERATION 61 -1 0-1 3 Rev 22

 PROPELLER; MAINTENANCE MANUAL
HARTZELL 1138

CONTENTS

1. Trouble-Shooting Guide 1-3

A. Pitch Control Difficulty. 1-3

B. Friction. 1-3

C. Abnormal Propeller Vibration. 1-5

D. Blades Not Tracking. 1-5

Movement of the Blade. 1-7

E. End-Play
F In-and-Out Movement of the Blade. 1-7

G. Fore-and-Aft Movement of the Blade 1-7

in the Blade. 1-7

H. Radial Play
Oil 1-8
i. Leakage
J. External Grease Leakage 1-8

Hub Blade 1-9

2. Lightning Strike on or

FIGURES

Blade Movement Figure 1-1 1-6

Checking

TESTING AND FPIULT ISOL~TION 61 -1 0-1 3 Rev

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

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TESTING AND FAULT ISOLATION 61 11 0’13 Rev.

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

1. Trouble-Shooting Guide

The purpose of this guide is to help isolate probable causes and suggest possible
In all cases,
remedies for some of the more common propeller service problems.
the applicable
the remedy for a problem should follow the procedures detailed in
section of this manual.

Problem Probable Cause Remedy

Excessive friction in moving parts. Refer to problem B. Friction.

A. PitchControl Difficulty.

or Oil leaking past piston causing Disassemble the propeller and

underspeed (-4 propeller). Oil inspect thepiston O-rings and
will leak out of the low pitch piston-to-cylinder sealing surfaces.
stop bleeder hole. Replace the defective O-ring(s).

or Oilleaking past the piston, Using caution because the grease/

between the pitch change rod oil may be under pressure, verify
and hub (engine-side), or by removing lubrication fitting
a

between the pitch change from the hub; a dark grease/oil

rod and shaft plug causing mixture will run out.

overspeed (-1 propeller). Hub

will fill with oil. Disassemble the propeller and
inspect hub-to-pitch change
the
rod O-rings and the piston O-rings,
as applicable. Inspect the piston-

to-cylinder sealing surfaces and

the pitch change rod sealing
surfaces, as applicable. Replace
the O-ring(s).

Lack of lubrication. Add approved lubrication.

B. Friction.

or Blade preloadisexcessive. Disassemble the propeller and

readjust the blade preload.

or Balls in the blade retention Replace the blade retention split

split bearing are unusually bearing assembly.
rough, corroded, or chipped.

or Insufficientclearance between Check/increase the clearances

the variousmoving parts in the between the individual parts as

pitch change mechanism. necessary to decrease friction in

the mechanism.

1-3

TESTING AND FAULT ISOLATION

61 -1 0-1 3 Rev.
 PROPELLER
HARTZ ELL MA:N1TjsNANCE MANUAL

(This page is intentionally blank.)

1-4
TESTING AND FAULT ISOLATION 61 -1 0’13
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1136

Problem Probable Cause Remedy

Bent, cracked, or damaged Refer to Hartzell Aluminum Blade

C. Abnormal Propeller
Vibration. blade. Overhaul Manual 133C (61-13-33)
or Hartzell Composite Blade

Maintenance Manual 135F

(61-13-35).

or Crackedordamaged hub. Refer to Chapter 1300, Aluminum

Hub Overhaul, in Hartzell Standard
Practices Manual 202A (61-01-02).

or Incorrectbalance of the Refer to the Static and Dynamic

Balance chapter of Hartzell
propeller.
Standard Practices Manual 202A
(61-01-02).

Blades nottracking. Refer toproblem D. Blades Not

D. Blades NotTracking, or
Tracking.
Foreign object strike
damage. Refer to the Special Inspections
chapter of Hartzell Standard
Practices Manual 202A (61-01-02),
for inspection procedure.

1-5

TESTING *ND FAULT ISOLPITION

61 -1 0-1 3 Reu.
 PROPELLER MANUIL
HARTZELL

APS5003B
NOTE: Refer to Table 8-2, Blade Tolerances.

Fore and
Radial play in aft blade
blade
ilrzT~ movement

~cr
In and out blade
movement
i
End-play
in blade

Checking Blade Movement

Figure 1-1

1-6
TESTING AND FAULT ISOLATION 61-10-13 Rev.
 PROPELLER MAINTENANCE MANUAL
HARTZELL iiSB

Problem Probable Cause Remedy

repair Disassemble the propeller and

E. End-Play Movementof Buildup of wear or

the Blade. tolerances, reset the preload.

Refer to Figure 1-1.

or Blade retention bearing is worn. Inspect/Replace the blade

retention bearing.

or Blade alignment bearing is Replace the blade alignment

worn. bearing.

repair Disassemble the propeller and

F. In-and-Out Movementof Buildup of wear or

the Blade. tolerances. reset the preload.

Refer to Figure 1-1.

or Blade retention bearing is worn. Inspect/Replace the blade

retention bearing.

G. Fore-and-Aft Buildup of wear or repair Disassemble the propeller and

Movement of the Blade. tolerances, reset the preload.
Refer to Figure 1-1.
or Blade retention bearing is worn. Inspect/replace the blade
retention bearing.

or Blade alignment bearing is Replace the blade alignment

worn. bearing.

H. Radial PlayintheBlade. Pitch change fork is worn. Disassemble the propeller.

Inspect and replace parts, as
required.

or Pitch change knob bushing is Disassemble the propeller.

worn. Inspect and replace parts, as
required.

or Pitch change block is worn. Disassemble the propeller.

Inspect and replace parts, as

required.

1-7

AND FAVLT ISOLATION 61 -1 0-1 3 Reu. 2~e,jgpPage

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

Problem Probable Cause Remedy

i. Oil Leakage Faulty O-ring seal between the Remove the propeller from the
engine flange and the engine andinspect the O-ring and
propeller mounting flange. the sealing surface. Replace the
defective O-ring.

or Engine crankshaftseal Refer to the engine manufacturer’s

leaking. manual for the appropriate action.

or Faulty O-ring seal on the hub Disassemble the propeller and

extension plug. inspect the O-rings and the sealing
surfaces. Replace the defective
O-ring(s).

or FaultyO-ringseal betweenthe Remove the cylinder and inspect

cylinder-side hub-half and the the O-ring and the
sealing surface.
cylinder (-4 propeller). Replace defective O-ring.

or Faulty internal propellerO-ring Disassemble the propeller and

between the hub and the pitch inspect the piston O-ring and pitch
change rod (-4 propeller). change rod-to-hub sealing surface
(cylinder side). Replace defective
O-ring.

or Faulty seal between the nut Remove the nut and replace the
and the cylinder(-l propeller). seal.

J. External Grease Leakage Improperly torqued or loose/ Replace the lubrication fitting.
missing lubrication fitting. Torque lubrication fitting in
accordance with Table 8-1.

or Ball not seated properly in the Replace the lubrication fitting.

lubrication fitting. Torque lubrication fitting in
accordance with Table 8-1.

or Grease leaking between the Disassemble the propeller and

blade and the hub. inspect the hub-to-blade seal and
sealing surfaces. Replace the
defective seal.

1-8
TESTING AND FAULT ISOLATION 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

Liahtnina Strike on Hub or Blade

In the event of a propeller lightning strike, an inspection is required before further flight.
strike on the propeller usually leaves arcing damage on
the blade, as
A lightning
evidence of where it entered or left the area near the tip of the blade. Refer to Hartzell
Practices Manual 202A (61-01-02), for
the Special Inspections chapter of Standard
lightning strike inspection criteria.

TESTING AND FAULT ISOLATION

61 ’1 0’1 3 Rev.
 PROPELLER
HA RTZ E LL MA:NIT3EsNANCE MANUAL

(This page is intentionally blank.)

1-10
TESTING AND FAULT ISOLATION 61’1 0’13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

AUTOMATIC TEST REQUIREMENTS (NOT APPLICABLE~

NOTE: Per ATA 100 specification this space is resewed for automatic test
the Hartzell
requirements. Such requirements are not applicable to
propellers addressed in this manual.

2-1

AUTOYATIC TEST REOUIREMENTS

61’1 0’1 3 Page
Rev. 22 Jun/GO
 PROPELLER
HARTZELL MA:N:jsNANCE MANUAL

(This page is intentionally blank.)

I *UTOLI~LT1CTESTREWIREMENTS 61-10-13Rev22Ju~VO
Page
2-2
 PROPELLER MAINTENANCE MANUAL
H RT Z LL 1138

CONTENTS

1. Removal of the Propeller Assembly from the Engine 3-3

A. General 3-3

B. Spinner Disassembly 3-3

C. Propeller Removal 3-3

2. Marking Before Disassembly 3-3

3. Removal of the Propeller De-icer System (where applicable) 3-4

4. Propeller Disassembly 3-4

A. Disassembly of the Propeller Pitch Change Parts 3-4

B. Hub Disassembly 3-6

C. Pitch Change Fork Disassembly 3-6

D. Pitch Change Block Disassembly 3-6

E. Split-Hub Unit Disassembly 3-6

5. Blade’ Disassembly 3-7

A. Blade Bearing System Disassembly 3-7

DIISSEMsLY 61-10-13 ReY.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

(This page is intentionally blank.)

I DISASSEMBLY 61’10’13 Rev.

 PROPELLER MAINTENANCE MANUAL
H 49 RT Z E L L 113B

1 Removal of the Propeller Assemblvfrom the Engine

WARN ING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED AS THEY MAY
CONTAIN I SSU ES VITAL TO Al RC RAFT SAFETY THAT ARE NOT
CONTAINED IN THIS MANUAL OR THE HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTIONS TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
Al RCRAFT ENGINE AND WHEN IT IS STORED.

A. General

The propeller should be removed from the aircraft in accordance with the airframe
manufacturer’s maintenance manual. The following propeller removal instructions are to
be used as a reference when removing a propeller in accordance with the airframe
manufacturer’s maintenance manual.

B. Spinner Disassembly
(1) Remove the screws and washers that attach the spinner dome to the engine side
bulkhead unit

(2) Remove the spinner dome store with care.

C. Propeller Removal
(1) Insure that the ai rcraft is safe for maintenance in accordance with the ai rf rame
manufacturer’s maintenance manual.

(2) Place drain pan beneath the propeller to catch oil that will drain from the
a

propeller piston and engine shaft.

(3) Using a suitable sling and hoist, support the propeller during removal.
(4) Expose the propeller mounting hardware and remove the safety wire.
(5) Remove and discard the propeller mounting hardware.
(6) Remove the propeller from the aircraft.

2. MarkinaBefore Disassemblv

1. Mount the propeller assembly on the rotatable fixture on the assembly table.

2. Record the serial number and model number of the hub and the blades and
compare with the data in the propeller logbook.

DISPISSEMBLY 61’1 0’1 3 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIMILARLY IDENTI FY

PARTS IN ANY MANNER WHICH MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OFTHE PROPELLER.

3. In orderto minimize reassembly problems with the propeller balance and blade
angle settings, keep all blades and pitch change components with their respective
assemblies. Note the location and orientation of these parts when disassembling
the propeller. All marks made on parts must be made with a crayon or a soft, non-
graphite pencil.
4. Each blade should be reinstalled in the hub socket from which it is removed.
Number the blades counterclockwise from the serial number impression stamped
on the propeller hub unit when facing the propeller cylinder.

3. Removal of the Prooeller De-icer System (where apPlicable)

NOTE: propeller is equipped with a de-icer system, follow the instructions in the
If the
appropriate de-icer system manufacturer’s manual for removal of the slip ring
and other components.

A. Remove the wire clamps or tie wraps from the de-icer lead wires. Disconnect the de-
icer lead wires from the terminal strip (where applicable).

B. Remove the bolts and screws that attach the bulkhead and slip ring to the hub.
C. Remove the bulkhead balance weights and attaching screws.

4. Propeller Disassemblv

A. Disassembly of the Propeller Pitch Change Parts

NOTE: Record the location and orientation (where applicable) of each part in the
propeller hub assembly. This will simplify the assembly process and
minimize the effort required to set the required blade angles.

(1) Remove the low pitch stop jam nut.

(2) Remove the seal from the low pitch stop.

I DISPISSEMBLY 61-10-13 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

CAUTION: THE LOW PITCH STOPS IN AEROBATIC PROPELLERS MAY

DEFORM DUE TO CONTACT BETWEEN THE PITCH CHANGE ROD
AND THE LOW PITCH STOP. DEFORMATION OF THE END OF THE
LOW PITCH STOP COULD CAUSE THE CYLINDER LOW PITCH
STOP THREADS TO BE DEFORMED DURING REMOVAL OF THE
LOW PITCH STOP. IF RESISTANCE INCREASES DURING NORMAL
REMOVAL OF THE LOW PITCH STOP, REMOVE THE LOW PITCH
STOP BY TURN ING IT INTO THE CYLINDER AFTER REMOVAL OF
THE CYLINDER.

(3) Remove the low pitch stop from the cylinder.

(4) Remove the propeller cylinder using the cylinder wrench TE1 53.
Remove and discard the cotter key from the pitch change rod nut.
(5)

CAUTION: PISTON IS UNDER SLIGHT FORCE IN -1 MODELS.

(6) Remove the pitch change rod nut from the pitch change rod.
(7) Remove the piston from pitch change rod.
(8) Remove the spring (-1 only).
(9) Remove the high pitch stop.
(10) Remove the high pitch stop split retaining ring.
(1 1) Remove the pitch change rod.
1 (12) Remove the hub bolts, nuts and washers. Discard the nuts and washers. If the
bulkhead is mounted to the propeller with the hub bolts, the spinner
spinner
bulkhead will be removed at this time.

(13) Remove the cylinder half of the hub unit.

(14) Remove blade number one from the hub.

(15) Remove the pitch change fork.

(16) Remove the pitch change blocks from the pitch change knobs.
(17) Remove the remaining blades from the hub.

DISASSEMsLY 61-10-13 ReY.

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 113B

B. Hub Disassembly

CAUTION: DO NOT ATTEMPT TO REMOVE THE EXTENSION SHAFT FROM

H U BS WITH BOLT-ON EXTENS IONS. EXTE NS ION S HAFTS AR E
PRESSED TOGETHER AND THE BOLTS ARE PRESSED
TH ROUGH THE HOLES.

(1 Remove the lubrication fittings from the hub halves.

(2) Remove the mounting flange attachment hardware. Referto Hartzell Manual 202A,
Aluminum Hub Overhaul procedures, for special procedures for removing
mounting flange attachment hardware.

CAUTION: DO NOT DAMAG E THE MATING SURFACE BETWEEN THE HUB

HALVES DURING REMOVAL OF THE HUB GUIDE BUSHING.

(3) Remove the hub guide bushing.

C. Pitch Change Fork Disassembly

(1) Two-Bladed Propeller Pitch Change Fork Disassembly
(a) Remove and discard the spring pins and plastic rubbing plates from the pitch
change fork.
(b) Pitch change forks with steel plates and brass rivets should be upgraded to
the configu ration. Refer to the Repai r section of this man ual for
cu rrent

information on upgrading pitch change forks to the current configuration

(2) Three-Bladed and Four-Bladed Propeller Pitch Change Fork Disassembly

Remove the pitch change fork buttons.
D. Pitch Change Block Disassembly
Remove and discard the pitch change block button from the pitch change block (if
applicable).
E. Split-Hub UnitDisassembly
(1) Remove the engine-side hub half from the rotatable fixture.
(2) Remove the spinner bulkhead from the rotatable fixture if applicable.

I 31-10-13,,
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

5. Blade Disassemblv

A. Blade Bearing System Disassembly

(1) Remove and discard the blade seal (540).
(2) Remove the hub-side bearing race (530).

(3) Remove and discard the ball bearings (520).

(4) Remove and discard the ball spacer (510).
(5) Remove and discard the pitch change knob bushing (565) from the blade.
(6) Disassemble the pitch change bracket (composite blades only).
Remove and discard the blade pitch change unit bolts (570) and washers
(a)
(567).
(b) Remove the blade pitch change unit (560) and the dowel pin (550).

(7) Remove and discard the jam nut (420) and set screw (430) from each preload
plate (440).
(8) Remove the preload plate (440).
(9) If installed, remove the anti-rotation plate (433) from the preload plate (440).

(10) Remove and discard the spring pins (435) from the preload plate (440).
(11) Remove the bearing retention ring (460) using a brass drift.
(12) Remove the blade-side bearing race (490) of the blade retention split-bearing.
NOTE: bearing race is hard to remove, position a brass punch
If the at the

bearing split and carefully tap to loosen the bearing(s).

(1 3) Referto Hartzell Manual 133C (61-13-33), Aluminum Blade Overhaul Manual or
Hartzell Manual 135F (61 -13-35), Composite Blade Overhaul Manual for blade
overhaul procedures.

DISASSEMBLY 61’10’13 Rev.

 PROPELLER MAINTENANCE MANUAL
HP~ RTr E LL 1138

(This page is intentionally blank.)

I DISPISSEM.LY 61-10-13 Rev

3-8
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

1. General Procedures for Cleaning Parts

Refer to the Cleaning chapter of Hartzell Standard Practices Manual

202A (61-01-02).

2. Specific Cleaning Procedures

A. Cleaning Steel Parts for Magnetic Particle Inspection

Refer to the Magnetic Inspection chapter of
Particle Hartzell Standard

Practices Manual 202A (61-01-02).

B. Cleaning Steel Parts for Cadmium Re-Plating Procedures

Refer to the Cadmium Replating chapter of Hartzell Standard Practices
Manual 202A (61-01-02).
C. Cleaning Steel Parts for Penetrant Procedures

Refer to the Dye Penetrant Inspection chapter of Hartzell Standard Practices

I Manual 202A (61-01-02).
D. Cleaning Aluminum Parts for Chromic Acid Anodizing Procedures

Refer to the Chromic Acid Anodizing chapter of Hartzell Standard Practices

Manual 202A (61-01-02).

CLEANING 61’1 011 3 ReV.

 PROPELLER
HARTZ ELL MA:N:3EsNANCE MANUAL

(This page is intentionally blank.)

I CLEANING 61’10’13 Rev.

 PROPELLER MAINTENANCE MANUAL
H~A RT Z c L L 113B

CONTENTS

1. Inspection Intewal Requirements .............5-3

2. Inspection Requirements 5-3

3. Replacement Requirements 5-4

4. Repair 5-4

5. Hub Unit Inspection 5-4

6. Specific Inspection Procedures 5-4

7. Specific Checks 5-4

A. Cylinder 5-5

B. Fork 5-6

C. High Pitch Stop 5-7

D. Hub Bolt Inspection 5-7

E. Hub Unit 5-7

F. Low Pitch Stop Screw 5-8

G. Piston 5-9

H. Pitch Change Block 5-11

i. Pitch Change Rod 5-13

J. Preload Plate 5-15

K. Retention Bearing Race 5-17

L. Spring

CHECK 61-10-13 Rev.

 PROPELLER MAINTENANCE MANUAL
H II~ RTZ E L L 113B

LIST OF ILLUSTRATIONS

Cylinder
Low Pitch Stop Screws Figure 5-2 .........5-8

Pitch Change Block Identification/Dimensional Criteria Figure 5-3 5-10

Pitch Change Rod Figure 5-4 5-12

Preload Plate.......... Figure 5-5 5-14

Retention Bearing Inspection Figure 5-6 5-16

LIST OF TABLES

Component Inspection Criteria Table 5-1 5-5

Piston Dimensional Inspection Criteria Table 5-2......,... 5-9

Pitch Change Rod Identification Table 5-3.........5-13

CHECK 61-10-13 Rev.

 PROPELLER MAINTENANCE MANUAL
H ~A RT Z E L L 1138

1. lnsoection Interval Reauirements

A. Refer to the Airworthiness Limitations chapter of this manual for information on

life limited components and mandatory inspections.

B. Refer to Hartzell Service Letter 61( for overhaul periods of Hartzell propellers.

2. Inspection Reauirements

A. Inspect all wearing parts to determine whether or not they meet the

specifications in Table 5-1, Component Inspection Criteria, in this chapter.

NOTE: Any serial-numbered part found unairworthy must be retired in
accordance with the Mandatory Parts Retirement Procedure chapter in
the Harzell Standard Practices Manual 202A (61-01-02).

B. Visual Inspection
Visually inspect all parts.

C. Penetrant Inspection
Penetrant inspect aluminum parts, as required. Refer to Table 5-1. Follow the
procedures for penetrant inspection found in the Dye Penetrant Inspection chapter of
Hartzell Standard Practices Manual 202A (61-01-02), for inspection of aluminum parts.

D. Magnetic Particle Inspection

Magnetically inspect steel parts, as required. Refer to Table 5-1. Follow the
procedures for magnetic particle inspection found in the Magnetic Particle
Inspection chapter of Hartzell Standard Practices Manual 202A (61-01-02), for
inspection of steel parts.
E. Dimensional Inspection
(1) Dimensionally inspect parts, as required. Refer to Table 5-1.

(a) When measuring the diameter of a part with a two point measuring
instrument, take at least two measurements, unless otherwise
specified. Obtaining a measurement outside the specified tolerance at
any point of measurement is cause for retirement of the part.
Alternately, take eight evenly spaced measurements, unless otherwise
specified. Obtaining a measurement outside the specified tolerance on
three or more measurements is cause for retirement of the part (two of
eight measurements may be out of specified tolerance). This alternate
method may not be used to accept a diameter that has obvious
damage.
(b) When measuring the diameter of a part with a three point measuring
instrument, take one measurement. A measurement outside the
specified tolerance is cause for retirement of the part.
(2) Inspectthe part features to the number of decimal places specified. If three
decimal places are specified, inspect the part to three decimal places only.

CHECK 61’10’13
 PROPELLER MAINTENANCE MANUAL
HP~ RTZ E L L 1138

3. Replacement Reauirements

Replace all parts that have cracks, wear, obvious defects, or damage found during
visual inspection that do not meet serviceable limits.

4. Re~air

Repairable part defects are noted in the inspection criteria in the Check chapter of
this manual. Repair procedures are found in the Repair chapter of this manual,
unless otherwise stated.

5. Hub Unit InsPection

Refer to the Aluminum Hub Overhaul chapter of Hartzell Standard Practices Manual
202A (61-01-02), for requirements and procedures for inspecting aluminum hub
units.

6. Soecific Inspection Procedures

A. Daily Inspection Procedures

(1) Refer to Hartzell Manual No. 115N (61-00-15), Propeller Owner’s Manual,
for daily inspection procedures of propellers with aluminum blades.
(2) Refer to Hartzell Manual No. 145 (61-00-45), Propeller Owner’s Manual, for
daily inspection procedures of propellers with composite blades.
B. Propeller Blade Assembly Inspection
(1) Refer to Hartzell Manual No.133C (61-13-33) for specific instructions on

aluminum blade inspection procedures.

(2) Refer to Hartzell Manual No. 135F (61-13-35) for specific instructions on

composite blade inspection procedures.

C. Refer to the Special Inspections chapter of Hartzeil Standard Practices Manual
202A (61-01-02), for foreign object strike inspection procedures.
D. Refer to the appropriate manufacturer’s manual for de-ice system inspection
procedures, if applicable.
E. Refer to Hartzell Manual 127 (61-16-27) for spinner´• assembly inspection
proceduves.

7. Specific Checks

See Table 5-1 for specific component checks.

CnECK 61110-13 Rev.

 PROPELLER MAINTENANCE MANUAL
H11~ RT Z E L L 113B

Component Inspection Criteria

Table 5-1

Inspect Serviceable Limits Corrective Action

A. CYLINDER
(Item 50)(Refer to Figure 5-1)

(1) Visually inspect the anodized 0.003 inch depth allowed on OD, None. Replace the cylinder
coating of the cylinder for otherwise, no discernible damage
wear, nicks, scratches or allowed.
other damage.

(2) Visually inspect the cylinder 1/4 of one thread accumulated See the Repair chapter of this
wrench attachment threads damage per wrench attachment manual for repair of cylinder
for damage, hole is allowed, wrench attachment threads.

(3) Ifrepaired with a slimsert, The minimum wall thickness under If the wall thickness under the
dimensionally inspect the the point of the drill is 0.080 inch point of the hole is less than
wall thickness under the (2.03 mm). 0.080 (2.03 mm), the cylinder
point of the cylinder wrench must be replaced.
attachment holes.

(4) Visually inspect the low pitch No damage is allowed. None. Replace the cylinder.
stop threads for damage.

Low Pitch Stop

Cylinder Wrench
Attachment Holes

Wall _1]
thickness

Cylinder
Figure 5-1

5-5
cnecK
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

Component Inspection Criteria

I Table 5-1

Inspect Serviceable Limits Corrective Action

B. FORK
(Item 190)

(1) Visually inspect the cadmium The maximum allowable depth of Damage must be repaired. Refer
plating of the fork (excluding damage is 0.003 inch (0.076 mm). to the Repair chapter in this
the slots, threaded bore and manual for general repair
tapered section of the bore) procedures of steel parts. Some
for wear, scratches, or other surfaces may appear rough tin
damage, the "as forged" condition),
rework of such surfaces is not
required.

If repaired, replate the fork and

bake in accordance with the
Cadmium Replating chapter of
Hartzell Standard Practices
Manual 202A.

(2) Visually inspect the threaded One damaged thread is allowed. None. Replace the fork.
portion of the fork bore for
damage.

(3) Visually inspect the tapered The maximum allowable depth of None. Replace the fork.

I portion of the fork bore for damage is 0.003 inch (0.076 mm).
wear, nicks, fretting or other
damage.

(4) Visually inspect the fork slots The maximum allowable depth of None. Replace the fork.
for damage. damage is 0.006 inch (0.15 mm).

(5) Magnetic particle inspectthe No relevant indications allowed. None. Replace the fork.
fork.
NOTE: It is not necessary
to strip the fork
before magnetic
particle inspection.

5-6
cnEcK
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1138

Component Inspection Criteria

I Table 5-1

Serviceable Limits Corrective Action

Inspect

C. HIGH PITCH STOP

(Item 120)

The maximum depth of damage is Refer to the Repair chapter of

(1) Visually inspect the surface
of the high pitch stop for 0.05 inch (1.2 mm). this manual for repair

wear, nicks, scratches, procedures.

corrosion, or other damage.

(2) Visually inspectthe high Pushed up material may not be Blend the pushed up material
above or outside the machined with the surrounding area. Refer
pitch stop for material
pushed up above the surface of the part. to the Repair chapter in this
surrounding surface.
manual for repair procedures.

A 1/32
NOTE: Use the appropriate dash numbered high pitch stop to get the high pitch stop angle.
in blade angle. Refer
inch (0.79 mm) change in height yields approximately degree change
1

to Table 7-1 or Table 7-2.

D. HUB BOLT INSPECTION

I (Items 250, 260)

Hub bolts that are used to bolt the hub halves together may be reused when they are inspected
in accordance with the following procedure. Bolts that are used on hub extensions must be
replaced at overhaul.

Corrosion, scoring, thread None. Replace the bolt.

(1) Perform a Visual inspection
of each bolt. damage, or any other defects are

unacceptable.

(2) Magnetic particle inspect No relevant indications allowed. None. Replace the bolt.
each bolt.
NOTE: It is not necessary
to strip the bolt
before magnetic
particle inspection.

(3) Visually inspect the Cadmium plate must completely Replate and bake the bolt in
cadmium plate coverage cover the hub bolt. accordance with the Cadmium

on the bolt. Replating chapter of Hartzell

Standard Practices Manual 202A
(61-01-02).
E. HUBUNIT

Perform the inspection of the hub in accordance with the Aluminum Hub
Overhaul chapter

of Hartzell Manual 202A.

5-7

CHECK S1 -1 0-1 3 Rev

 PROPELLER
HARTZELL MPI:N~NANCE MPINUIL

Component Inspection Criteria

I Table 5-1

Inspect Serviceable Limits Corrective Action

F. LOWPITCH STOPSCREW
(Item 40)(Refer to Figure 5-2)

(1) Visually inspectthe pitch No damage allowed. None. Replace the low pitch stop
change rod contact surface screw.
for damage.

(2) Visually inspect the threaded One damaged thread is allowed. None. Replace the low pitch stop
portion of the low
pitch stop screw.
screw for damage.

(3) Inspect the air bleed hole in This air passage must be clean None. Replace the low pitch stop
the center of low pitch stop and unobstructed. screw if the air passage cannot be
screw. (Aerobatic(-4) cleared.
Propellers Only)
NOTE: All A-2421-1 Low Pitch Stop Screws are obsolete for installation on aerobatic (-4)
propellers and must be
replaced with A-4252 Low Pitch Stop Screws. The A-4252 Low
Pitch Stop Screws have an enlarged contact surface for the pitch change rod and are
used with 8-2428-1 Cylinders.

NOTE: A-2421-1 Low Pitch Stop Screws have an air passage A-2421 Low Pitch Stop Screws
do not have an air passage.

a242~.111 a4252.lif a4257.lif

24NF-3A-24UNRF-3A,-18 x 1 3/,

contact’1
4

enlarged
surface

A-2421-1 A-4252 A-4257

Low Pitch Stop Screws

I Figure 5-2

CHECK 61-10-13 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

Component Inspection Criteria

I Table 5-1

Inspect Serviceable Limits Corrective Action

I
G. PISTON(ltemSO)

(1) Dimensionally inspect "A". Refer to Table 5-2 for "A" Pistons exceeding the "A"
dimensional limits. dimension limits in Table
1 5-2 must be replaced.

(2) Visually inspect the surface The maximum allowable depth of None. Replace the piston.
of the piston for nicks, damage is 0.005 inch (0.12 mm).
scratches or other damage.

(3) Visually inspect areas "8" Dimensionally inspect area(s) Pistons with dimensions
through "E" of the piston for showing wear in accordance with exceeding the limits of
I wear. Table 5-2. Table 5-2 must be
replaced.
NOTE: Pistons were a felt seal groove. Current production pistons
originally manufactured with
no longer have felt
a seal groove, however, the original pistons were not made obsolete
by this improvement. A piston does not have to be retired if it has a felt seal groove.

I Diamete"E"
"A"
I Diameter I

"B" "D"
C
Width Diameter

"C"
Diameter
PISTON.XLS
,I
"A" "B" "C" "D" E"
Part Number Maximum Maximum Minimum Maximum Minimum
Diameter Width Diameter Diameter Diameter

8-2280 0.738 inch 0.335 inch 4.725 inch 0.856 inch 5.165 inch

(18.745 mm) (8.509 mm) (120.015 mm) (21.742 mm) (131.191 mm)

8-2419 0.738 inch 0.270 inch 4.358 inch 0.856 inch 4.706 inch

(18.745 mm) (6.858 mm) (110.693 mm) (21.742 mm) (119.532 mm)

8-6511 0.738 inch 0.335 inch 4.725 inch 0.856 inch 5.165 inch

(18.745 mm) (8.509 mm) (120.015 mm) (21.742 mm) (131.191 mm)

Piston Dimensional Inspection Criteria

I Table 5-2

CHECK 61’1 0’1 3 Rev

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

APS2058
BLOCK.XLS

1 Z
Diameter

Y F Dash
Number

Part Number "X" Minimum "Y" Minimum "2" Minimum Hole Diameter Maxi

A-2217-1 Not a wear surface, no 1.011 inch 0.905 inch 0.6250 inch
measurement required (25.67 mm) (22.98 mm) (15.875 mm)

A-2217-2 Not a wear surface, no 1.009 inch 0.905 inch 0.6250 inch
measurement required (25.62 mm) (22.98 mm) (15.875 mm)

A-2217-3 0.870inch 0.870inch 0.905inch 0.6890inch

(22.09 mm) (22.09 mm) (22.98 mm) (17.500 mm)

A-2217-4 0.870inch 0.870inch 0.905inch 0.6250inch

(22.09 mm) (22.09 mm) (22.98 mm) (15.875 mm)

A-3253 0.871 inch Not a wear surface, no 0.745 inch 0.6250 inch

(22.12 mm) measurement required (18.92 mm) (15.875 mm)

A-3253-1 0.869 inch Not a wear surface, no 0.745 inch 0.6250 inch

(22.07 mm) measurement required (18.92 mm) (15.875 mm)

A-3253-2 0.869 inch Not a wear surface, no 0.745 inch 0.6890 inch
(22.07 mm) measurement required (18.92 mm) (17.500 mm)

A-3253-3 0.874 inch Not a wear surface, no 0.745 inch 0.6890 inch

(22.19 mm) measurement required (18.92 mm) (17.500 mm)

Pitch Change Block Identification/Dimensional Criteria

Figure 513

5-10
CHECK 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

Component Inspection Criteria

I Table 5-1

Inspect Serviceable Limits Corrective Action

H. PITCHCHANGE BLOCK
(Item 200)

(1) Visually inspect the pitch The maximum allowable depth of None. Replace the pitch change
change block for damage. damage is 0.005 inch (0.12 mm). block.

(2) Visually inspect the pitch pitch change block shows

If the None. Replace the pitch change
change block for wear. wear, dimensionally inspect block.
according to Figure 5-3.

(3) Magnetic particle inspect the No relevant indications allowed. None. Replace the pitch change
pitch change block, block.

NOTE: To identify the pitch change blocks, refer to Figure 5-3.

NOTE: The pitch change knob hole in the pitch change knob block is offset toward the thin wall.
Pitch change blocks should be installed in the fork with the thin wall toward the engine-
side hub half during initial assembly.

5-11
CCIECK 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

aps2059

A B

Overall Length

Pitch Change Rod

Figure 514

5-12
CHECK 61’10’13
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

Component Inspection Criteria

Table 5-1

Serviceable Limits Corrective Action

Inspect

i. PITCH CHANGE ROD

(Item 140)
(Refer to Figure 5-4)

(1) Visually inspect the chrome Any area worn below the chrome None. Replace the pitch change
plating is for replacement. rod.
plating of the pitch change cause

rod for damage.

(2) Visually inspect fordamage One damaged thread is allowed. None. Replace the pitch change
to external threads.
rod.

is allowed. Remove all foreign material.

(3) Visually inspect the oil supply No foreign material
bore using a borescope or
fiberoptic flashlight.

(4) Dimensionally inspect area A 0.733 inch (18.61 mm) minimum None. Replace the pitch change
of the pitch change rod. diameter (see Figure 5-4). rod.

(5) Dimensionally inspect area B 0.663 inch (16.84 mm) minimum None. Replace the pitch change
of the pitch change rod. diameter (see Figure 5-4). rod.

(6) Perform a magnetic particle No cracks are allowed. None. Replace the pitch change
rod.
inspection of the pitch
change rod.

PCID.XLS

Part Number loverall Length (inch) Overall Length (mm) Difference if Same Length

A-2418-1 8.225 208.91

8.600 218.44 Drilled through hex end

A-2418-2

A-2418-3 14.815 376.30

12.815 325.50 Solid on hex end

A-2418-4

8.600 218.44 Solid on hex end

A-2418-5

A-2418-6 13.127 333.42

12.815 325.50 Drilled through hex end

A-2418-7

A-2418-8 8.850 224.79

A-2418-9 13.565 344.55

Pitch Change Rod Identification

Table 5-3

5-13

CHECK 61-10-13
 PROPELLER
HARTZELL M*:N:3EBNP~NCE
B311LAUNIPM

APS6283
APS6284

4.810 inch (122.18 mm)

Minimum Lip Diameter

Preload Plate 0.060 inch

Threads
(1.53 mm)
Minimum
Lip Thickness

Inner Blade Bore Bearing Race

1.249 inch
(31.73 mm)
Minimum
Diameter

Y I

Preload Plate
Figure 5-5

CHECK 61’10-13 Rev. 22 Jun/GOPage 5-14

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

Component inspection Criteria

Table 5-1

Serviceable Limits Corrective Action

Inspect

J. PRELOAD PLATE
(Item 440)(Refer to Figure 5-5)

(1) Visually inspect the internal Two (2) damaged threads are None. Replace the preload plate.
threads for damage, allowed.

(2) Dimensionally inspectthe Minimum allowable diameter is None. Replace the inner ring
OD of the inner ring 1.249 inch (31.73 mm). using gear puller TE98.

NOTE: Inner ring (450) removal at overhaul is required only if the bearing is beyond
serviceable limits.

(3) Visually inspect the inner False brinelling with no depth is None. Replace the inner ring
ring (450) OD for brinelling, allowed. Brinelling with any depth using gear puller TE98.
is not allowed.

(4) Visually inspect the inner None allowed. None. Replace the inner ring
ring (450) OD for corrosion using gear puller TE98.
or damage.

Clean with Scotch Brite" pad to

(5) Visually inspect the outboard If the outboard "lip" is damaged, a

dimensionally inspect. Minimum remove any evidence of fretting.

"lip" OD and thickness.
allowable lip thickness is 0.060 If beyond serviceable limits,
inch (1.53 mm). Minimum replace the preload plate.
allowable lip OD is 4.810 inch
(122.18 mm).

No cracks are allowed. None. Replace the preload plate.

(6) Penetrant inspectthe
visible surfaces of the
preload plate.
NOTE: If the inner ring is
not removed, the
preload plate
surfaces hidden by
the innerring need
not be inspected.

61-10-13
 PROPELLER
HARTZELL MA:IIT~NANCE
8311LAUNAM

APS6068A
APS6069
5016
5017

::´•i´•:´•i´•:´•i´•:´•i´•:
4Outer
diameter

No fretting allowed
Radial in this area

(dashed-lines).

Idiameter
:;:::::;::’:’i’:’:’´•’: ´•:´•1´•:´•i´•

’’’’’’’’’’:’’’;’’’;’’’’’’’;’’’;’’;’’’;’’’;’‘:;:::;:;::::’i:’:!:’:i:’:::’:i::’
Outer
:;:;:;:;:’:::’:;:;:;:’:::::;:;:;:;’’ ’ ’ :’ ’:’ ’:’:’i’:’i’:’i‘:’i’:’i’:’i’

RetentionBearing Ispection
Figure 5-6

5-16
CHECK 61-10’13 Rev. 22 Jun/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

Component Inspection Criteria

Table 5-1

Inspect Serviceable Limits Corrective Action

K. RETENTION BEARING RACE

(Items 490, 530)
(Refer to Figure 5-6)

(1) Visually inspect the ball bearing groove shows

If the ball None. Replace the retention
bearing groove for damage. wear,dimensionally inspect. bearing race.
Maximum allowable depth of
damage is 0.005 inch (0.12 mm).

(2) Visually inspectthe outer Fretting damage is allowed. Must Using a Scotch Brite" pad or
diameter of the bearing not affect the tight fit of the blade equivalent, clean the area throughly
race for fretting damage, bearing race with the guide ring. to minimize fretting damage.

If the guide ring is not tight. None. Replace the bearing race.

1 (3) Magnetic particle inspect No cracks are allowed. None. Replace the retention
the bearing race, bearing race.

5-17
CHECK 61-10-13
 PROPELLER
HARTZELL M*:N~ANCE MANUPIL

Component Inspection Criteria

I Table 5-1

Inspect Serviceable Limits Corrective Action

L. SPRING
(Item 110)

(1) Visually inspect the Maximum allowable depth of None. Replace the spring.
A-2213-( spring for damage is 0.003 inch (0.076
wear, polish marks or mm).
other damage.

(2) Dimensionally inspect the The minimum free length is 3.00 None. Replace the spring.
free length of the inches (76.2 mm).
A-2213-() spring.

(3) Visually inspect the Maximum allowable depth of None. Replace the spring.
8-6509-() spring for damage is 0.005 inch (0.13 mm).
wear, corrosion, or other
damage.

(4) Dimensionally inspect the The minimum free length is 4.25 None. Replace the spring.
free length of the inches (107.9 mm).
8-6509-() spring.
NOTE: Do not strip the zinc plating from the 8-6509-( spring. If plating is removed, replace the
spring.

5-18
CHECK 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

CONTENTS

1. Repair Requirements 6-3

A. Aluminum Parts

B. Steel Parts 6-3

2. Specific Repair Requirements 6-4

A. Repair of Damaged Cylinder Wrench Attachment Holes. 6-4

I B. Spinner Bulkhead Modification for Two-bladed Compact Prepellers 6-5

C. Spinner Bulkhead Modification for Three-bladed Compact Propellers 6-11

ILLUSTW~TIONS

Installing the Reinforcing Brackets Figure 6-1 6-6

Two-bladed Propeller Bulkhead Cutout Dimensions Figure 6-2 6-8

Two-bladed Propeller Bulkhead Template Figure 6-3 6-9

Three-bladed Propeller Bulkhead Modification Dimensions Figure 6-4 ..........6-14

Three-bladed Propeller Bulkhead Modification Template Figure 6-5 6-15

61-10-13
 PROPELLER MANUAL
HARTZ E LL MA:E~BNANCE

(This page is intentionally blank.)

I 61-10-13
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 113B

1. ReDairReauirements

A. Aluminum Parts

(1) Eliminate all evidence of scratches, nicks, burrs, and other minor damage using a

fine emery cloth or scotch-brite pad. Be sure to blend the polishing in with the
surrounding area. Use extreme care to completely remove the damage while
removing as little material as possible.
(2) Make sure part is still within tolerance after any type of minor repair. Refer to
the
the Check chapter of th is man ual.

(3) Anodized parts that have been reworked must be reanodized as described in the

I Chromic Acid Anodizing chapter of Hartzell Manual 202A.

B. SteelParts

(1) Eliminate all evidence of fretting, nicks, burrs and other minor damage using a fine
emery cloth or scotch-brite pad. Be sure to blend the polishing in with the
surrounding area. Use extreme care to completely remove the damage while
removing as little material as possible.
(2) Make sure the part is still within tolerance after any type of minor repair. Refer to
I the Check chapter of this manual.

(3) Cadmium plated parts which have been repaired must be replated as described
I in the Cadmium Replating chapter of Hartzell Manual 202A.

REPAIR 61’10’13 Rev.

 PROPEL"R
nARTZELL MA~INCE MANU~L

2. SPecific RePairReauirements

NOTE: Balance weight attachment hole and grease fitting hole repair procedures are
described in the Aluminum Hub Overhaul chapter of Hartzell Manual 202A
(61-01-02),
A. Repair of Damaged Cylinder Wrench Attachment Holes.
(1) General.

(a) Several models of aluminum hub propellers have th readed holes in the
fo rwa rd end of th e p repel ler cyl i n de r fo r attach me nt of wrench es d u ri ng
assembly and disassembly. Damage to these holes is repairable in
accordance with the following procedure.

I (b) Perform the procedure on cylinders with the following part numbers only.
B-2428-()
8-2281

(2) Procedure.

(a) Use TE410 (Hartzell P/N 86986-258), Cut off the counterbored end of the
Slimsert to remove the counterbore and locking teeth.

(b) Drill thedamaged hole to diameter 0.281 +0.004 -0.001 inch (7.13 +0.101
0.025 mm) with a maximum depth of 0.440 inch (1 1.17 mm) at the corner of
the hole. Make sure that the drill is centered and square with the hole.

(c) I nspect the wall thickness under the point of the hole in acco rdance with the
Check chapter in this manual.

(d) Th read the hole to 5/1 6-24 U N F-3B using a bottom tap.
NOTE: The resu Itant th read wi II be non-standard due to the larger than
normal minor diameter of 0.280 0.285 inch (7.1 1 7.23 mm)
produced by the previous drill operation.
(e) Chemical conversion coat the tapped hole. Refer to the Chromic Acid
Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02),
(f) Spray the Slimsert and the tapped hole with primer CM127.
(g) Coat the Slimsert with thread locking compound CM74.
(h) Install the modified Slimsert flush to 0.020 inch (0.508 mm) below the part
su rf ace, using installation tool TE3 1 4.

NOTE: Step drill, reamer, and swage tool are not required because the
counterbored end is cut off.

(i) Check the installed Slimsert using a 1/4-28 UN F-3A bolt.

(j) Allow the repaired parts to cure for 12 hours before assembly.

61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

B. Spinner Bulkhead Modification for Two-bladed Compact Propellers

Since April, 1997, Hartzell Propeller has been producing an improved two bladed
compact propeller hub that incorporates a modification designed to improve the
reliability of the fillet area of the hub. The improved style hub has considerable material
added to the forging in the blade retention area. Hartzell no longer manufactures the
earlier style hub.

NOTE: The improved style hub is identifiable by a different part number (referto the
Illustrated Parts List) and the suffix letter "B" at the end of the hub serial
number and the propeller serial number. It is also visibly different from
previous hubs due to material added to the forging in the blade retention
area.

This change necessitates modification of spinner bulkheads to provide clearance when

replacing an earlier style hub with an improved style hub. Previously manufactured
bulkheads for the spinner assemblies will need to be modified to properly fit the
improved style compact hub. Bulkhead modifications are only necessary when installing
an improved style hub.

Installation of an earlier style spinner bulkhead on an improved style hub requires

bulkhead modification, except for spinner bulkheads mounted to starter ring gears, that
are not affected by these instructions. The modification may be done in accordance

with the procedures given below. A list of affected spinner bulkhead part numbers is
given for each procedure. Operators with non-Hartzell spinners should consult the
appropriate type certificate holder for modification instructions.
(1) Procedure A

I (a) The procedures given in Procedure A are for two-bladed propeller spinner
bulkheads that already have reinforcing brackets installed from the factory.
The modification will remove material from the bulkhead and brackets to
allow clearance for new style hubs.

I All two-bladed compact spinner bulkhead P/N’s are listed below:

C-2283-1 C-2283-2 C-2283-2P C-2283-4 C-2283-5

C-2283-6 C-2294 0-2294-2 C-2294-3P C-2299-1

I C-2299-2P
C-2469-3
C-2469
C-2472-1
C-2469-1
C-2472-2
C-2469-1L
C-3228
C-2469-2
C-3283-1
C-3283-2 C-3295 C-3534 C-3534-1 C-3569
C-4567 0-4534 0-4812 0-4825 D-5258
0-5751 0-5751-1 0-5751-1L
(b) Remove material from the bulkhead to provide clearance forthe new style
hub. Make cutouts in accordance with the dimensions given in Figure 6-2.

1 Fabricate a template to match the broken lines in Figure 6-3.

61-10-13
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1138

CAUTION: CHECK THE DIMENSIONS OF THE TEMPLATE BEFORE

CUTTING THE BULKHEAD.

2 Align the holes in the template with the mounting holes on the bulkhead.
3 Mark the areas to be removed.

4 Remove material using a mill, nibbler, grinder, or other appropriate

tooling.
NOTE: For best results, remove material using a milling machine.
5 Remove all burrs and rough edges.
6 Inspect the cutout forthe proper dimensions. Bulkhead must be retired
from service if the dimensions are exceeded.

Apply zinc-chromate primer to the exposed edge of the steel reinforcing

brackets.

8 Vibra etch a "B" after the serial number on the bulkhead.

9 Install the spinner bulkhead to propeller hub.

APS6249

A-3263-3
Bracket Rivets

Flush fit between

A-3263-3 bracket and bulkhead

Installing the Reinforcing Brackets

I Figure 6-1

REP~IR 61-10-13 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

(2) Procedure B

I (a) The procedures given in Procedure a are for two-bladed propeller bulkheads
that do not have reinforcing brackets installed at the factory. Brackets must
be installed on these bulkheads before material is removed to provide
additional structural support.

Two way compact spinner bulkhead P/N’s listed below:

C-2472

NOTE: Bulkhead reinforcing bracket P/N A-3263-3 (qty 4 per bulkhead) is

required to accomplish this procedure.

(b) Install reinforcing brackets on the bulkhead.
NOTE: It is critical that reinforcing brackets be installed flush with the
contour of the bulkhead. It may be necessary to bend the brackets
slightly for proper fit. (See Figure 6-1 Use hub bolts or a suitable
alternate to hold the template in place on the bulkhead.

1 Ream the hub bolt mounting hole in the bracket to 0.404 0.413 inches

(10.26 10.49 mm).

2 Ream the bracket rivet holes (4 per bracket) using a #30 twist drill.
Deburr all the holes.

NOTE: Cured structural adhesive may prevent the bracket from lying
flush on the bulkhead. Remove excess adhesive using 120
grit sandpaper.
3 Place reinforcing bracket on the engine side of the spinner bulkhead.
a

Align the mounting holes and clamp the bracket in place, ensuring that
the bracket is flush with the bulkhead surface.

4 Using a #30 twist drill, drill rivet holes (4 per bracket) through the
bulkhead, using the rivet holes in the bracket as a template. Deburr all
the holes.

NOTE: Relocate, or log book any bulkhead part number

record in the
that may be covered by a reinforcing bracket.

5 using AN 470 AD 4-7(MS20470AD4-7)

Install the bracket rivets. Rivet
in accordance with aircraft standard practices.

6 Complete steps 2.B.(2)(b)lthrough 2.B.(2)(b)4forthe remaining

brackets.

NOTE: reinforcing brackets will not

Installation of the bulkhead
require a longer hub mounting bolt.
(c) Comply with the steps outlined in Procedure A.

61-10-13
 PROPELLER MANV~L
HARTZELL

APS6250

2X R 0.597rt0.010 inch
(15.16~t0.25 mm)

I /C-’

P o~ I
R 0.250~0.010 inch
(6.35~0.25 mm)
2X 3.264~.010 inch 14X R 0.250rt0.010 i
(82.91 rt0.25 mm) (6.35~t0.25 mm)

i
o o
a 0.398~.010inch
10.10~0.25mm O

4X (21.406+0.007/-0.002 inch
(10.31 +0.17/-0.050 mm)

Two-bladed Propeller Bulkhead Cutout Dimensions

Figure 6-2

6-8
sl-lo-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL H38

APSM51

Two-bladed Propeller Bulkhead Template

Figure 6-3

6-9
sl-lo-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

(This page is intentionally blank.)

I 61-10-13
6-10
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

C. Spinner Bulkhead Modification for Three-Bladed Compact Propellers

(1) Reason

(a) HartzellPropeller has begun production of an improved th ree-bladed

compact propeller hub. The improved style hubwill incorporate a
modification designed to improve the reliability of the fillet area of the hub.

(b) Previously manufactured hubs will no longer be available; only improved style
hubs will be available from Hartzell.

NOTE: The improved style hub is identifiable by a different part number

(refer to the Illustrated Parts List) and the suffix letter "B" at the end
of the hub serial number and the propeller serial number. It is also
visibly different from previous hubs due to material added to the
forging in the blade retention area.
(c) The improved style hub has considerable material added to the forging in the
blade retention area. This change necessitates modification or replacement
of currently installed spinner bulkheads to provide clearance when replacing
a previous style hub with an improved style hub.

(d) Previously man uf actu red bu Ikheads listed in the effectivity will need to be
modified or replaced to properly fit the improved style compact hub.
Bulkhead modifications or replacement, are only necessary for hub mounted
bulkheads installed on the new style hub.

(2) Material Introduced for New Spinner Bulkheads

(a) Spinner bulkheads with part numbers listed in the table below may be
modified to be installed on the improved hub.

Previous Modified Spinner Previous Modified

Spinner
Assembly Bulkhead P/N Bulkhead P/N Assembly BulkheadP/N BulkheadP/N

A-837-12 C-3286(P) C-3286-1 (P) C-3575-1 C-3576-1 (P) C-3576-3(P)

A-2295-1 C-2294-1 (P) C-2294-1 2(P) C-4582 C-4583(P) C-4583-2(P)
A-2295-2 C-2294-4(P) C-2294-13(P) C-4582-1 C-4583-1 (P) C-4583-3(P)
A-2295-4 C-2294-1 O(P) C-2294-1 4(P) C-6446 D-6448(P) D-6448-1P

C-3535 C-3539(P) C-3539-1 (P) D-5495L C-3539(P) C-3539-1 (P)

C-3535-1 C-3539(P) C-3539-1 (P) 0-6750 D-6753(P) D-6753-1(P)
C-3535-2 C-3539(P) C-3539-1(P) D-6841 D-6839(P) D-6839-1(P)
C-3570 C-3571(P) C-3571-1(P) D-6936 C-3571(P) C-3571-1(P)
C-3575 C-3576(P) C-3576-2(P) 1 D-7067 D-7065(P) D-7065-1(P)

NOTE: Newly purchased spinner assemblies will include a spinner bulkhead that
may be used with either the improved style orthe previous style propeller
hub.

~1-10-13
 PROPELLER MAEIUAL
HARTZELL

(b) Certain hub models contain a hub unit that is

longer produced by Hartzell
no

Propeller Inc. The hydraulic components on these propellers are

incompatible with the improved hub design and must be changed if a new
h ub is instal led. Ref er to the section, Th me-bladed Propeller Improvements,
in the Illustrated Parts List chapter of this manual.

(c) Spinner bu Ikhead part n umbers that are aff ected, but can not be modif led,
must be replaced. Ail th ree-bladed compact spinner bulkhead part n umbers
listed below cannot be modified and must be replaced when a new hub is
installed:

Spinner Assembly Previous Bulkhead P/N RePlacement Bulkhead P/N

A-835-38 C-3279 C-3279-1

D-7086 D-7084(P) D-7084-1(P)
D-5732 D-5734(P) D-5734-1(P)

(d) Spinner assembly part numbers that are affected but cannot be modified, will
have to be replaced. All three-bladed compact spinner assemblies with part
numbers listed below cannot be modified and must be replaced when a new
hub is installed:

Previous Previous Previous Current Current Current

Spinner Assv. Bulkhead P/N Dome P/N SPinner Assv. Bulkhead P/N Dome P/N
A-3284 C-3283-(P) C-3282-(P) A-3284-2(P) C-3283-3(P) C-3282-4(P)
A-4203-1 C-3283-(P) C-3282-3(P) A-4203-2(P) C-3283-3(P) C-3282-5(P)

(3) Accomplishment Instructions

NOTE: Propeller hub changes may only be performed by an FAA approved or

foreign equivalent propeller repair facility. Spinner bulkhead
modifications may be performed by a certificated mechanic.

(a) I nstallimproved style p repeller h ub in acco rdance with the Assembly

an

chapterofthis manual.
1 Install hydraulic components (if required) in accordance with the
new

Assembly chapter of this man ual. Refer to the section, Th me-bladed

Propeller Improvements, in the Illustrated Parts List chapter of this
manual.

(b) Replace the spinner bulkhead and spinner assembly (if required) in
accordance with the Installation and Removal chapter of Hartzell Owner’s
Manual 1 15N (61-00-15) or Manual 145 (61-00-45),

6-12
REPAIR 61110113 Rev. 24 Apr/OlPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

(c) The modification of a three-bladedpropeller spinner bulkhead may be done

in accordance with the procedure given below:

NOTE: A spinner bulkhead that is mounted on a starter ring gear is not

Operators with non-Hartzell
affected by these instructions.
spinners should consult the appropriate type certificate holder for
modification instructions.

1 Remove material from the bulkhead to provide clearance for the

improved style hu b. Mod ify the bulkhead in accordance with the
dimensions given in Figure 6-4.
NOTE: For best results, remove material using a milling machine.
2 Fabricate a template to match the solid lines in Figure 6-5.

CAUTION: CHECK THE DIMENSIONS OF THE TEMPLATE BEFORE

CUTTING TH E BULKHEAD.

i! Align the holes in the template over the mounting holes on the bulkhead.
4 Use hub bolts or a suitable alternate to hold the template in place on the
bulkhead.

5 Mark the areas to be removed.

6 Remove material using a mill, nibbler, grinder, or other appropriate

tooling.
71 Remove all tool marks, burrs, and rough edges.
8 Inspect the cutout for proper dimensions. (Refer to Figure 6-4 and
Figure 6-5.) The bulkhead must be retired from service if the
dimensions are exceeded.

9 Apply zinc-chromate primer CM67 to the exposed edge of the steel

reinforcing brackets.
10 Vibra etch a "B" after the serial number on the bulkhead.

61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

wlo40s

BUDE Q

3X 0.597~0.010inch
(15.16~0.25 mm)

3X 3.26 ~0.010 inch

(82.8~0.25 mm)
liln2olcl

BUIDE E
BUI~E E

n Paint the exposed surfaces with Zinc Chromate Primer CM67

Three-bladed Propeller Bulkhead Modification Dimensions

Figure 6-4

6-14
REPAIR 61’10’13
 I

111
II
N
m
BLADE (L r
;bTI I I I

P,
cD
a 4X R 0.250 ~0.030 inch
’CI 0.597 ~0.010 inch O
(6.3510.76 mm)
o (15.16~0.25mm) 4

nca e
"E
a9 ~i
CD~

a g
o
m n
-o
c
I
B I I I I I I
Q) I 1 I 3.26 ~0.010 inch
(82.81t0.25 mm)
~I
3
1_1,0201CI

4.060 ~0.005 inch C

O (1 03.12~0.12 mm)

~Ln
 PROPELLER MAINTENANCE
HA RTZ E L L B311LAUNAM

(This page is intentionally blank.)

I REPIIR 61-10-13 Page 6-16

Rev. 24Apr/Ot
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

CONTENTS

1. Blade Assembly Procedures 7-3

A. General. 7-3

B. Installation of the Pitch Change Knob (Composite Blades Only). 7-3

C. Installation of the Blade Bearing Race and Balls 7-5

D. Installation of the Preload Bearing Inside Race to the

Preload Plate Spindle
7-9

I
2. Compact Hub Assembly Procedures

A. Preparation of the hub for assembly. 7-9

B. Two Blade Compact Hub Blade Installation 7-15

C. Three Blade Compact Hub Blade Installation 7-20

D. Four Blade Compact Hub Blade Installation 7-24

E. Hydraulic Pitch Change Unit Assembly 7-29

F Installation of the Lubrication Fitting 7-43

3. Counterweight Installation (Aerobatic Only) 7-44

4. Propeller Lubrication
5. Static Balance 7-44

LIST OF ILLUSTRATIONS

Installation of the Blade Retention Bearing Figure 7-1 ...........7-4

Pressing the Preload Bearing onto the Preload Plate Spindle........ Figure 7-2......,...7-4

Installation of the Preload Plate to the Blade Shank Figure 7-3...........7-6

Applying the Clamping Tool TE24 to the Blade Assembly Figure 7-4...........7-6

Installing the Anti-rotation Plate Figure 7-5........... 7-7

Spark Gap Screw, PHC-G3YF-1E and HC-13YR-1E Propellers...... Figure 7-6...........7-8

Spark Gap Screw, HC-C3YR-4(A,G) and HC-C2YR-4(E,G) Figure 7-7......, 7-11

Installation of the Flange O-Ring in the Engine Half Hub Flange.... Figure 7-8......... 7-13

Installation of the Engine-Side Hub Half on the Assembly Stand Figure 7-9.........7-14

Blade Number One Installed in the Hub Figure 7-10.......7-15

Installing the Cylinder-Side Hub Half Figure 7-11 .......7-16

Installation of Blade Number 1 Figure 7-12....... 7-18

ASSEMBLY 61’10’13 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

LIST OF ILLUSTRATIONS (Cont’d~

Installation of Sealant on the Hub Parting Surface Figure 7-13.....,7-19

Installing Hub Half in Preparation for Tightening Preload Plate Figure 7-14.....,7-20

Tightening Preload Plate Hex Head Screw and Jam Nut................ Figure 7-15.....,7-21

Pitch Change Blocks Installed on Blades Two and Three Figure 7-16.....,7-22

Pitch Change Fork Installed on Blades Two and Three Figure 7-17....., 7-23

Installation of Blade One into Hub Figure 7-18....., 7-24

Installation of Front Half of Hub Figure 7-19....., 7-25

Installation of Pitch Change Fork Figure 7-20....., 7-26

Installation of Blade Number One into the Hub...... Figure 7-21 .......7-27

Installation of Sealant Between the Hub Halves Figure 7-22....., 7-28

Application of Blade Angle Reference Tape Figure 722.1 ..7-28.1

Wire Harness Bracket Location Figure 7-23....., 7-31

Installation of High Pitch Stop Split Ring Retainer Figure 7-24.......7-32

Installation of High Pitch Stop and High Pitch Stop O-Ring Figure 7-25.......7-32

Installing the A-2213-( Spring Figure 7-26.....,7-36

Installing the Piston on the Pitch Change Rod Figure 7-27....., 7-36

Cotter Pin Installation Figure 7-28......

Installing the Piston on the Pitch Change Rod Figure 7-29....., 7-38

Installing the D-6509-( Spring Figure 7-30....., 7-38

Installing the Cylinder with Cylinder Torque Wrench

Adapter TE153 Figure 7-31

Installing the Low Pitch Stop Figure 7-32.......7-41

Checking Blade Track Figure 7-33.......7-42

Hub Leak Check Figure 7-34

Lubrication Fittings Installed in Hub Figure 7-35....., 7-44

LIST OF TABLES

A-2420-( High Pitch Stop Heights

I B-6515-( High Pitch Stop Heights
Table 7-1

Table 7-2
7-34

7-35

ASSEMBLY 61’10’13
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1138

NOTE: Lubricate all O-rings with approved lubricant CM12 unless otherwise stated.

NOTE: Read all instructions completely before beginning the ASSEMBLY

procedures.

1. Blade Assembly Procedures

A. General.

(1) Aluminum Blades

Refer to Hartzell Manual 133C, Aluminum Blade Overhaul, for information on

installing the blade bore plug, blade bore bearing and pitch change knob
bushing, bearing race and retention ring.

(2) Composite Blades

Refer to Hartzell Manual 135F, Composite Blade Maintenance Manual, for

information on installing the blade bore plug, blade bore bearing and pitch
change knob bushing, bearing race and retention ring.
B. Installation of the Pitch Change Knob (Composite Blades Only).

(1) Install the dowel pin (550) into the pitch change knob bracket (560).
(2) Install the pitch change knob bracket.

CAUTION: THE SAFETY WIRE WHICH GOES THROUGH THE LOOP ON

THE PITCH CHANGE KNOB BRACKET SHOULD NOT
INTERFERE WITH THE TRAVEL OF THE BLADE OR CONTACT
THE PRELOAD PLATE. INSTALL THE SAFETY WIRE WITH THE
PIG-TAIL ON THE BOLT. IF THE SAFETY WIRE IS INSTALLED
WITH THE PIG-TAIL ON THE PITCH CHANGE BRACKET LOOP,
THE PIG-TAIL MAY INTERFERE WITH THE FIT BETWEEN THE
PITCH CHANGE KNOB BRACKET AND THE PRELOAD PLATE
SLOT.

(3) Install the pitch change knob bracket bolts (570) and torque in accordance with
I Table 8-i, Torque Values, and safety wire with 0.020 inch stainless steel wire.

ASSEMBLY 61’10’13 Rev.

 PROPELLER
HARTZELL MI:N:3EsNPINCE MINWL

Blade O-Ring

Ball Spacer
Blade Bearing Race

Bearing Race Retaining Ring

Installation of the Blade Retention Bearing

Figure 7-1

APS2026

Preload Bearing

I Preload Plate

I
Preload Plate Spindle

Pressing the Preload Bearing onto the Preload Plate Spindle

I Figure 7-2

ASSEMBLY 61’10’13 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

C. Installation of the Blade Bearing Race and Balls

(1) Cover the blade O-ring (540) with grease CM12 and install on the blade.

(2) Install the ball spacer (510) on the blade flange.

CAUTION: ALL THE BEARING BALLS IN A SINGLE BEARING MUST BE OF

THE SAME SIZE AND GAUGE. ALL BEARING BALLS SUPPLIED
BY HARTZELL ARE THE SAME GAUGE.

(3) Assemble the bearing balls (520) onto the blade butt using a small amount of

grease around the bearing balls.

NOTE: Composite blades use smaller balls and a different ball spacer than
aluminum blades.

(4) Place the blade retention bearing hub race (530) on the balls.

NOTE: The split bearing race parting line should be perpendicular to the hub

parting line when assembled.

D. Installation of the Preload Bearing Inside Race to the Preload Plate Spindle
(1) Place the preload plate in a fixture and press the blade bore bearing (450)
inside race over the preload plate (440) spindle (see Figure 7-2). On preloads
that do not maintain a press fit for the race, apply thread locking compound
CM74 to the preload plate (440) spindle.

(2) applicable, install the anti-rotation plate (433)

If on the preload plate (440).
Refer to Figure 7-5.

(a) Install the roll pins (435) in the anti-rotation plate (433).

CAUTION: DO NOT LEAVE THE PRELOAD PLATE IN PROLONGED

CONTACT WITH THE APPROVED SOLVENT.

(b) Clean the preload plate (440) with solvent CM44 or CM106. The surface
must be absolutely clean and thoroughly dry.
(c) Clean the anti-rotation plate (433) with solvent CM44 or CM106. The
surface must be absolutely clean and thoroughly dry.

ASSEMBLY 61’10’13 Rev.

 PROPELLER MPINUAL
HARTZELL

APS2024

Blade O-Ring
Hub Bearing Race

Grease
Preload Plate

Installation of the Preload Plate to the Blade Shank

Figure 7-3

APS2019

Applying the Clamping Tool TE24 to the Blade Assembly

Figure 7-4

7-6
P~SSEMBLY 61’10-13 Rev.
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

WARNING 1: THE APPROVED ADHESIVE IS AN EYE IRRITANT, AND

BONDS SKIN IN SECONDS. IN CASE OF EYE OR MOUTH
CONTACT, HOLD EYE LID OR MOUTH OPEN AND FLUSH
WITH WATER. IF FINGERS BECOME BONDED, APPLY
SOLVENT (ACETONE OR NAIL POLISH REMOVER) TO
CONTACT AREA AND CAREFULLY PRY SKIN APART.

WARNING 2: AVOID PROLONGED BREATHING OF VAPORS. USE WITH

ADEQUATE VENTILATION.

(d) Apply the adhesive CM71 over the protruding ends of the roll pins (435)
and the bonding surface of the preload plate (440).
(e) Position the anti-rotationplate (433) on the preload plate (440) and apply
firm finger pressure. Immediately place the preload plate in a clamping
fixture and clamp the anti-rotation plate to the preload plate until the
adhesive CM71 is cured.

(3) Install the socket head screw (430) in the preload plate (440).
(4) Install the nut on the screw (420).
(5) Place approximately one tablespoon of grease CM12 on top of the preload
plate inner bearing race spindle. This will force grease into the blade bore
bearing when the preload plate is installed on the blade.
(6) Install the preload plate (440) onto the butt of the blade (Figure 7-3).
(7) Hold the bearing assembly to the blade butt with the clamping tool TE24

(Figure 7-4).
W102B6

Preload Plate (440)

~iincratationPate
Roil Pin (435)

Installing the Anti-rotation Plate

Figure 715

I 61-10-13,,
 PROPELLER
HARTZELL MPI:N~PINCE MANUPIL

APS2060A
APS5089A

d lo
~3 Ic~
0.935 0.010 Inch
(23.75~ 0.25 mm)

Nut(336)
Spark Gap Screw
Locknut Torque to
(334)
20 2 In-Lb
(335)
Torque to (2.3 0.2
20 ~t 2 In-Lb N´•m)
(2.3 0.2 N´•m)

Spark Gap Screw, PHC-G3YF-1E and HC-13YR-1E Propellers

Figure 7-6

7-8
sl-lo-13
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

2. ComPact Hub Assembly Procedures

protractor TE96, TE97, equivalent when measuring a blade angle.

I Use
Refer to the Hartzell Tool and
or

Equipment Manual 165A (61-00-65).

A. Preparation of the hub for assembly.

NOTE 1: Verify spinner and bulkhead assembly and installation procedures

the
before beginning assembly of the hub. Use the alternate hub assembly
nuts and bolts that are supplied with a spinner mounting kit, if applicable.

NOTE 2: Verify the installation of the BFGoodrich electric de-ice system before

beginning the assembly of the hub, if applicable.

installation of the Hartzell anti-ice system before beginning the

NOTE 3: Verify the
assembly of the hub, if applicable.

(1) Install the pitch change rod guide bushing (160) into the cylinder-side hub half
non-feathering (-1) propeller. Refer to the Hartzell Standard Practices
I of a

Manual 202A (61-01-02) for installation instructions.

pitch change rod guide bushing (230) into the engine-side hub half
Install the of
(2)
a non-feathering (-1) propeller that has an extension. Refer to the Hartzell

Standard Practices Manual 202A (61-01-02) for installation instructions.

(3) spark gap screw (334) into cylinder-side

Install the hub half (PHC-G3YF-1E
and HC-13YR-1E propellers only).
I (a) Turn a locknut (335) onto the spark gap screw (334) until the screw

threads can be seen at both ends of the nut.

(b) Add the second nut (336) to the screw.

(334), (336), and locknut (335) combination in the

I (c) Install the screw nut

right balance hole of the cylinder side hub half (Figure 7-6).

NOTE: Thecylinder side of the hub must be resting on the parting line
when locating the balance hole for the screw.

(d) Set a gap of 0.935 0.010 inch (23.75 ~t 0.25 mm) between the head
(334) and the hub.

I
of the screw

(e) Hold the screw (334) in place to maintain the gap setting and hand

tighten both nuts against the hub.

Maintaining the gap, torque the locknuts (334, 335) to 20 2 In-Lb

I (f)
(2.3 0.2 N´•m).

NOTE: Hold the screw in place to maintain the gap setting when

torquing the locknuts.

I (g) Check the gap setting.

ASSEMBLY 61’10’13 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

(This page is intentionally blank.)

I I,,,..,, sl-lo-13
 PROPELLER MANUAL
HARTZELL

(4) Install the

spark gap screw (334) into the cylinder-side hub half (HC-C3YR-
4[A,G] and HC-C2YR-4[E,G] propellers only).
(a) Install the spark gap screw (334) in the right balance hole of cylinder
side hub half (Figure 7-7).
NOTE: The cylinder side of the hub must be resting on the parting line
when locating the balance hole for the screw.

CAUTION: TO PREVENT DAMAGE TO THE SCREW LOCKING

MECHANISM, DO NOT TORQUE THE SCREW IN THE
BALANCE HOLE.

(b) Turn the sparkgap screw (334) into the balance hole until the screw
bottoms out in the hole.

NOTE: The locking mechanism causes resistance when turning the

screw in the hole. Stop turning the screw when the resistance
increases, indicating that the screw has bottomed in the hole.

(c) The gap between the head of the screw (334) and the blade clamp will
be set later in the assembly procedure.

APS2060A
apsroses

Gap between the head

of the screw and the

0.049 ~t
eclamp.I-
dalbI
0.044 Inch
(1.24 1.11 mm)

Spark Gap Screw

(334)

Spark Gap Screw, HC-C3YR-4(A,G) and HC-CPYR-4(E,G)

Figure 7-7

ASSEMBLY 61’1 0’1 3 Rev

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

(This page is intentionally blank.)

Page 7-12
I Rev. 24Apr/Ol
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 1138

Install the hardware to the engine-side hub half.

propeller flange attaching
I (5)
Refer to the Aluminum Hub Overhaul chapter of the Hartzell Standard
Practices Manual 202A (61-01-02) for procedures to install the propeller
mounting hardware.

pitch change rod O-ring (150) in the cylinder-side hub half

where
(6) Install the
rod O-ring, non-
applicable. Aerobatic(-4) propellers use a pitch change
feathering (-1) propellers use a pitch change rod bushing.
hub half (Figure 7-8).
(7) Install the flange mounting O-ring (320) on the engine-side
hub half of hubs with
(8) Install the extension plug (300) into the engine-side
extensions.

(a) Install the extension plug OD O-ring (290j on the extension plug.

(b) Install the extension plug ID O-ring (220) in the extension plug.

Install the extension plug in the engine-side hub half.

(c)

APS2012

r
j-"

Installation of the Flange O-Ring in the Engine Half Hub Flange

Figure 7-8
I

.,,,,,,Y 61’10’13
 PROPELLER
HARTZ E LL MA:N:3EsNANCE MANUAL

(9) Install the

pitch change rod O-ring (220) in the engine-side hub half. If the hub
isan extended hub design, the pitch change rod O-ring is installed in the hub

extension plug ID.

I (10) Install the engine-side hub half on the propeller assembly stand (Figure 7-9).
(11) Coat the bearing seats of the blade retention sockets with a thin film of grease
CM12.

(12) Coat the blade O-ring grooves with a thin film of grease CM12.

APS2013

Installation of the Engine-Side Hub Half on the Assembly Stand

I Figure 7-9

ASSEMBLY 61’10’13
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1138

B. Two Blade Compact Hub Blade Installation

blade assembly into the socket of the engine-side hub

(1) Install the number one

I half (Figure 7-10).

Center the slot in the preload plate (440) at the hub parting line.
(2)

NOTE: The blade knob slot in the preload plate should be positioned to allow
the blade to travel within the full blade angle range without restriction.

(3) Install the cylinder-side hub half.

nps2000

Centerthe preload
plate slot at the hub
parting line.

Blade Number One Installed in the Hub

Figure7-lO

ASSEMBLY 61’10’13
 PROPELLER
HARTZELL MA~PINCE MP~NVAL

(4) Install 2 bolts (250), 2 washers (270), and 2 nuts (280) in the hub and torque in
I accordance with Table 8-1.

CAUTION: IMPROPER PRELOAD CAN CAUSE THE BLADES TO BE LOOSE

IN THE HUB.

(5) Tighten the preload socket set screw (430) through the open end of the hub.
The loose blade will become rigid in the hub as the socket screw is tightened.
Tighten the preload socket screw until the tip of the blade stops moving
vertically. Gently move the tip of the blade to ensure that the blade is properly
seated in the retention socket. Loosen the preload socket screw and retighten.
Once the blade tip stops moving, turn the socket screw an additional ’/4 turn
further into the preload plate. The Fits and Clearances chapter contains a
torque table listing torque values.

APS2039

Installing the Cylinder-Side Hub Half

I Figure 7-11

ASSEMBLY 61’10’13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

(6) Check the blade for free rotation. If the blade is not free, the following friction
items should be checked:

(a) Blade O-ring.

(b) The needle rollers in the blade bore bearing may be skewed. Check the
needle rollers to verify that they are parallel to the axis of rotation.
(7) Remove the cylinder-side hub half.

(8) Apply one drop of thread locking compound CM21 to the threads of the socket
screw (430).
1 (9) Torque the jam nut (420) in accordance with Table 8-1. Be sure to secure the
set screw to prevent it from moving during the installation and torquing of the
jam nut.

(10) Remove blade number one. Use the blade retention components clamp TE24
to hold the bearing halves together.
(11) Install blade number two into the hub and set the preload using the procedures
outlined in steps 2.B.(1) to 2.B.(9).

ASSEMBLY 61’10’13 Rsv.P2a29Jeu7n~

 PROPEL"R
HARTZELL M*:N:S~PINCE MANVAL

(12) Install blade number one and the pitch change parts (Figure 7-12).
(a) Install the block buttons (210) into the pitch change block (200).
(b) Apply anti-seize compound CM118 to the outside of each pitch change
knob bushing.
(c) Apply anti-seize compound CM118 to each pitch change block groove of
the pitch change fork (190) and to the fork threads.

(d) Install a pitch change block (200) on each pitch change knob, with the
round extension away from the blade.

NOTE: When installing new pitch change blocks, verify the orientation
of the pitch change block. Pitch change blocks should be
installed in the fork with the thin wall toward the engine-side hub
half during initial assembly. Blocks marked for orientation during
disassembly should be reassembled following those markings.

CAUTION: MAKE SURE THE TAPER IN THE FORK MATCHES THE

TAPER IN THE PITCH CHANGE ROD. IF THE PITCH
CHANGE ROD IS IMPROPERLY ATTACHED TO THE FORK,
THE SEATING AREA OF THE PITCH CHANGE ROD WILL BE
DAMAGED.

(e) Install the fork (190) on the pitch change block of blade number two.

APS2021

Installation of Blade Number 1

Figure 7-12

ASSEMBLY 61’10’13
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

Slide the pitch change block for blade number one into the fork with the
(f)
red side out or toward the open side of the fork.

(g) Reinstall blade number one in the hub socket.

(13) Installation of the Cylinder-Side Hub Half of the Two Blade Hub

NOTE: Hubs manufactured with a hub seal groove no longer use the
parting
A-2436 hub parting seal. Fill the groove with sealant CM92 and
continue the assembly procedure.
(a) Place a bead of sealant CM92 on the hub mating surfaces. The quantity
of sealant applied mating surfaces must be sufficient to allow a
to the
small amount to be squeezed out along the entire parting surface when
the hub bolts are properly torqued (Figure 7-13).

CAUTION: VERIFY THAT THE BLADE O-RING OR QUAD RING IS IN

THE O-RING GROOVE WHEN INSTALLING THE CYLINDER-
SIDE HUB HALF.

(b) Install the cylinder-side hub half.

two bolts (250), washers (270), and nuts (280) at the hub
(c) Install only
center.

APS2037

Hub Mating Surface

Installation of Sealant on the Hub Parting Surface

Figure 7-13

I
 PROPELLER
HARTZ E LL MA:N:3EsNANCE MANUAL
C. Three Blade Compact Hub Blade Installation

(1) Install the number one blade assembly into the socket of the engine-side hub
half.

(2) Center the slot of the preload plate (440) at the hub parting line.

NOTE: The blade knob slot in the preload plate should be positioned to allow
the blade to travel within the blade angle range without restriction.
(3) Install cylinder-side hub half.

(4) Bolt the hub together using 3 bolts (250), 3 washers (270) and 3 nuts (280) and
torque in accordance with Table 8-1 (Figure 7-14).

aps2060.lil

q
z a

car,

Installing Hub Half in Preparation for Tightening Preload Plate

Figure 7-14

nssEMeLv 61110-13
 PROPELLER MAINTENANCE MANUAL
HI~ RT Z E L L 1138

CAUTION: IMPROPER PRELOAD CAN CAUSE THE BLADES TO BE LOOSE

IN THE HUB.

(5) Tighten the preload socket set screw (31) through the open end of the hub.
The loose blade will become rigid in the hub as the socketscrew is tightened.

Tighten the preload socket screw tip of the blade stops moving
until the
vertically. Gently move the tip of the blade to ensure that the blade is properly
seated in the retention socket. Loosen the preload socket screw and retighten.
Once the blade tip stops moving, turn the socket screw an additional ’/4 turn
I further into the preload plate (Figure 7-15). The Fits and Clearances chapter
contains a torque table listing torque values.

APS2061

‘Y"1

Tightening Preload Plate Hex Head Screw and Jam Nut

I Figure7-15

,s,,,,,Y 61110113
 PROPELLER MANUAL
HARTZELL

(6) Check the blade for free rotation. If the blade is not free, the following friction
items should be checked:

(a) Blade O-ring.

(b) The needles in the blade bore bearing may be skewed. Check the needles
to verify that they are parallel to the axis of rotation.

(7) Remove the cylinder-side hub half.

(8) Apply one drop of thread locking compound CM21 on the threads of the socket
screw.

(9) Torque the jam nut (420) in accordance with Table 8-1. Be sure to secure the
set screw to prevent it from moving during the installation and torquing of the
jam nut.

(10) Remove blade number one. Use the blade retention components clamp TE24
to hold the bearing halves together.
(11) Install blade numbers two and three into the hub using procedures outlined in
steps 2.C.(1) to 2.C.(9).
(12) Installation of Blade Number One Including Pitch Change Parts

(a) Install the pitch change fork buttons on the pitch change fork.
(b) Apply anti-seize compound CM118 to the outside of each pitch change
knob bushing.

APS2005

Thin Side of

Block is hctChange
iPnwoD a

Pitch Change Blocks Installed on Blades Two and Three

Figure 7-16

I 61-10-13
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 113B

(c) Apply anti-seize compound CM118 to the fork threads and to each pitch
change block groove of the pitch change fork.

I (d) Install a pitch change block (200)

round extension away from the blade.
on each pitch change knob, with the

NOTE: When installing new pitch change blocks, veri~y the orientation
of the pitch change block. Pitch change blocks should be
installed in the fork with the thin wall toward the engine-side hub
half during initial assembly. Blocks marked for orientation during
disassembly should be reassembled following those markings.

CAUTION: MAKE SURE THE TAPER IN THE FORK MATCHES THE

TAPER IN THE PITCH CHANGE ROD. IF THE PITCH
CHANGE ROD IS IMPROPERLY ATTACHED TO THE FORK,
THE SEATING AREA OF THE PITCH CHANGE ROD WILL BE
DAMAGED.

(e) Install the fork (190) on the pitch change blocks of blade numbers two and
three (Figure 7-17).
(f) Reinstall blade number one in the engine-side hub half socket. Slide the
pitch change block into the fork.

I (g) Position the center of the slots in the preload plate (440) on the plane of
the parting line of the hub.

APS2010

I-

Pitch Change Fork Installed on Blades Two and Three

Figure 7-17

~SSEMBLY 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

(13) Installation of the Cylinder-Side Hub Half of the Three Blade Hub

(a) Place a bead of sealant CM92 on the hub mating surfaces. The quantity
of sealant applied to the mating surfaces must be sufficient to allow a
small amount to be squeezed out along the entire parting surface when
the hub bolts are properly torqued.

I CAUTION: VERIFY THAT THE BLADE O-RING OR QUAD RING IS IN

THE O-RING GROOVE WHEN INSTALLING THE CYLINDER-
SIDE HUB HALF.

(b) Install the cylinder-side hub half.

(c) Install only three bolts (250), washers (270), and nuts (280) at the hub

I center and torque in accordance with Table 8-1.

D. Four Blade Compact Hub Blade Installation

(1) Install blade number one and blade number two assemblies into the sockets of
I the engine-side hub half (Figure 7-18).
(2) Center the slot of the preload plate (440) at the hub parting line.

NOTE: The blade knob slot in the preload plate should be positioned to allow the
blade to travel within the full blade angle range without restriction.

APS2042

Installation of Blade One into Hub

I Figure 7-18

~SSEMBLY 61-10-13
 PROPELLER MAINTENANCE MANUAL
H~A RTZ E L L 113B

(3) Install the cylinder-side hub half.

(4) Install 4 bolts (250), 4 washers (270), and 4 nuts (280). Torque in accordance

I with Table 8-1 (Figure 7-19).

CAUTION: IMPROPER PRELOAD CAN CAUSE THE BLADES TO BE LOOSE

IN THE HUB.

(5) Tighten the preload socket set screw (31) through the open end of the hub.
The loose blade will become rigid in the hub as the socket screw is tightened.
Tighten the preload socket screw until the tip of the blade stops moving
vertically. Gently move the tip of the blade to ensure that the blade is properly
seated in the retention socket. Loosen the preload socket screw and retighten.
Once the blade tip stops moving, turn the socket screw an additional ’/4 turn
further into the preload plate.

APS2038

Installation of Front Half of Hub

Figure 7-19
I

ASSEMBLY 61’10’13
 PROPELLER MAINTENANCE MANUAL
HA,RTZ E LL 1138

(6) Check blade for free rotation. If the blade is not free, the following friction items
should be checked:

(a) Blade O-ring.

(b) The needles in the blade bore bearing may be skewed. Check the needles
to verify that they are parallel to the axis of rotation.

(7) Remove the cylinder-side hub half.

(8) Apply one drop of thread locking compound CM21 on the threads of the socket
screws.

1 (9) Torc(ue the jam nut (420) in accordance with Table 8-1. Be sure to secure the
set screw to prevent it from moving during the installation and torquing of the
jam nut.

(18) Remove blade numbers oneUse the blade retention components

and two.
clamp TE24 tool to hold the blade retention bearing together.

(11) Install blade numbers three and four into the hub using procedures outlined in
steps 2.D.(1) to 2.D.(9).

APS2041

Thin Side of
Pitch Change
Block is Down

Installation of Pitch Change Fork

I Figure 7-20

~SSEMBLY 61-10-13
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 1132

Installation of Blades One and Two Including Pitch Change Parts

(12)
Install blade number two into the engine-side hub half.
(a)
(b) Apply anti-seize compound CM118 to the outside of each pitch change
knob bushing.
of
(c) Apply anti-seize compound CM118 to each pitch change block groove
the pitch change fork and the fork threads.
the
(d) Install a pitch change block (200) on each pitch change knob, with
round extension away from the blade.

NOTE: When installing new pitch change blocks, verify the orientation
of the pitch change block. Pitch change blocks should be
installed in the fork with the thin wall toward the engine-side hub
half during initial assembly. Blocks marked for orientation during
disassembly should be reassembled following those markings.

CAUTION: MAKE SURE THE TAPER IN THE FORK MATCHES THE

TAPER IN THE PITCH CHANGE ROD. IF THE PITCH
CHANGE ROD IS IMPROPERLY ATTACHED TO THE FORK,
THE SEATING AREA OF THE PITCH CHANGE ROD WILL BE
DAMAGED.

Install the fork (190) on the pitch change blocks (200) of blade numbers
(e)
two, three, and four (Figure 7-20).

APS2044

Installation of Blade Number One into the Hub

Figure 7-21

ASSEMBLY 61’10’13
 PROPELLER
HARTZELL YA:PPaEBNPINCE MINUAL

(f) Install the

pitch change block for blade number one in the fork. Reinstall
blade number one in the engine-side hub half socket (Figure 7-21).

(g) Position the center of the slots in the preload plate on the plane of the
parting line of the hub.

NOTE: The blade knob slot in the preload plate should be positioned to
allow the blade to travel within the blade angle range without
restriction.

(13) Installation of the Cylinder-Side Hub Half of the Four Blade Hub

(a) Place a bead of sealant CM92 on the hub mating surfaces. The quantity
of sealant applied to the mating surfaces must be sufficient to allow a
small amount to be squeezed out along the entire parting surface when
the hub bolts are properly torqued (Figure 7-22).

CAUTION: VERIFY THAT THE BLADE O-RING OR QUAD RING IS IN

THE O-RING GROOVE WHEN INSTALLING THE CYLINDER-
SIDE HUB HALF.

(b) Install the cylinder-side hub half.

(c) Install only four bolts (250), washers (270), and nuts (280) at the hub
center and torque in accordance with Table 8-1.

APS2040

Hub Mating Surface

Installation of Sealant Between the Hub Halves

Figure 7-22

I ASSEMBLY 61-10-13 Page 7-28

Rev. 24 Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1138

W10313
APS0050A

Cambe’

from
Measure distance
reference
hub centerto O"
b~aderadius \ocation
b\ade face

Reference blade
radius location
(Blade Face)

Yellow Blade Angle

Reference Tape
CM160

Application of Blade Angle Reference Tape

Figure 7-22.1

7-28.1
 PROPELLER UANUPIL
HARTZELL

E. Application of Blade Angle Reference Tape

CAUTION: DO NOT CONFUSE REFERENCE BLADE RADIUS WITH BLADE

STATION. REFERENCE BLADE RADIUS AND BLADE STATION
OF THE SAME NUMBER MAY NOT ALWAYS INDICATE THE
SAME LOCATION ON THE BLADE.

Reference blade radius is measured from the center of the propeller hub to a
predetermined reference location on the blade for blade angle measurement.
Blade stations are used during the repair or overhaul process of a blade to define a
blade span location for dimensional measurement.

(1) Establish a reference blade radius location

(a) Refer to the Aircraft Type Certificate Data Sheet or the Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the reference blade radius
location specified for the applicable aircraft installation.

(b) Beginning with blade one, measure from the center of the propeller hub to
the reference blade radius location specified. Refer to Figure 7-22.1.

(c) Apply yellow blade angle reference tape CM160 to the face side of the
a

blade at the reference blade radius location, perpendicular to the blade

centerline. Refer to Figure 7-22.1.

NOTE: Place the reference tape CM160 so that the reference blade
radius location runs through the centerline of the tape.

(d) Repeat steps 4.E.(1)(b) and 4.E.(1)(c) for the remaining blades in the hub
assembly.
(e) Place a pattern cut-out over each blade
angle reference tape CM160 and
spray each yellow blade angle reference tape CM160 with clear lacquer
CM129 to prevent peeling.

61-10-13
 PROPELLER MAINTENANCE MANUAL
HA, RTZ ELL 1138

I F. Hydraulic Pitch Change Unit Assembly

(1) Insert the pitch change rod (140) through the cylinder-side hub half and into the
fork (190). Torque the pitch change rod in accordance with Table 8-1.
(2) Blade Angle Check
(a) Compact Non-Feathering (-1) Propellers only.
1 Install the cylinder (50) hand tight on the cylinder-side hub half.

2 Install the low pitch stop (40) cylinder(50). The low pitch
into the
stop does not have to be set to the appropriate low pitch angle. The
cylinder and low pitch stop only provide a contact point for the pitch
change rod while checking for 0.2 degrees tolerance between
blades.

3 Rotate the blades until the pitch change rod contacts the low pitch
stop and check the blade angles at the 30 inch radius of all of the
blades.

4 Turn one or more of the pitch change blocks if the blade angle differs
more than 0.2 degree between blades. To turn blocks, remove the

cylinder (50), and front half of the hub. Make the appropriate
adjustments to the pitch change blocks (200). Reassemble the
propeller, and recheck the blade angle tolerance between blades
following -1 propeller steps E.2.(a).l through E.2.(a).3 above.

NOTE: Pitch change blocks should be installed in the fork with the
thin wall toward the engine-side hub half during initial
assembly. Rotating pitch change block 180 degrees
the
will decrease the pitch of the corresponding blade 0.3 to
0.4 degree on a tractor propeller. Rotating the pitch
change block 180 degrees will increase the pitch of the
corresponding blade 0.3 to 0.4 degree on a pusher
propeller. It is also possible to bring the blades within
tolerance by rotating the fork 180 degrees on two-blade
and four-blade propellers.
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

(b) Aerobatic (-4) Propellers only.

1 Install the split ring (130) into the pitch change rod (140) groove.

2 Slide high pitch stop sleeve (120) over the pitch change rod (140)
and split ring (130).
3 Thread piston rod nut (70) finger tight onto pitch change rod (140).
4 Rotate blades toward high pitch until piston rod nut (70) contacts the
high pitch stop sleeve (120) and check blade angles at the 30 inch
radius of all of the blades

5 Turn one or more of the pitch change blocks if the blade angle differs
more degree between blades. To rotate blocks, remove rod
than 0.2
nut (70), high pitch stop sleeve (120), split ring (130) and front half of
the hub. Make the appropriate adjustments to the pitch change
blocks (200). Reassemble the propeller and recheck the blade angle
tolerance between blades following -4 propeller steps E.2.(b).l
through E.2.(b).4 above.

NOTE: Pitch changeblocks should be installed in the fork with the

thin wall toward the engine-side hub half during initial
assembly. Rotating the pitch change block 180 degrees
will decrease the pitch corresponding blade 0.3 to
of the
0.4 degree on a tractor propeller. Rotating the pitch
change block 180 degrees will increase the pitch of the
corresponding blade 0.3 to 0.4 degree on a pusher
propeller. It is also possible to bring the blades within
tolerance by rotating the fork 180 degrees on two-blade
and four-blade propellers.

~SSEMBLY 61-10-13
 PR6PELLER MANUAL
HARTZELL

(c) Remove the low pitch stop (40) from the cylinder (50) and remove the
cylinder from the cylinder-side hub half.
(d) Install the
remaining hub bolts (250 and 260), washers (270), and nuts
(280). Torque in accordance with Table 8-1.

NOTE 1: It is the responsibility of the propeller maintenance facility to

ensure that the
appropriate spinner and mounting parts have
been installed. Refer to the Hartzell Application Guide Manual
159 (61-02-59) for spinner assembly application information.

NOTE 2: Spinner bulkheads that are attached to the propeller with the
hub clamping bolts will be installed at this time. Verify the
location of all washers and spacers during this procedure.

(e) For HC-I3YR-1E propeller Install two washers (275), wire harness
bracket (276), one washer (270), and one Flexlock nut (281) (Figure 7-23).

APS5090A
APS5091

Hub, Cylinder Side

Washer
(275)

Wire Harness
rr T1
rcn ~aa, Bracket (276)

Flexlock Nut ~3
(281)

Wire Harness Bracket

Wire Harness Bracket Location

Figure 7-23

ASSEMBLY 61 ’1 0’1 3 Rev.

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

APS2028

High Pitch Stop Split Ring

Retainer

Z
’7~
Installation of High Pitch Stop Split Ring Retainer
Figure 7-24

APS2011

Piston ID O-Ring
(100)

High Pitch Stop

(120)

Cylinder
(170)

Installation of High Pitch Stop and High Pitch Stop OIRing

Figure 7-25

61-10-13
 PROPELLER MAINTENANCE MANUAL
HPI.RTZ E LL 1138

(3) Installation of the piston and cylinder

(a) Install the split retainer (130) on the pitch change rod (140) groove (Figure
1 7-24).
(b) Install thehigh pitch stop (120) over the pitch change rod (140) and
retainer (130) (Figure 7-25). Use the appropriate dash numbered high
I pitch stop to get the high pitch stop angle. A 1/32 (0.031) inch (0.79 mm)
change in height yields approximately 1 degree change in blade angle.
I Refer to Table 7-1 or Table 7-2 for high pitch stop dimensions and part
numbers.

(c) Perform apreliminary check of blade high pitch stop angle. Move the
blades into a low pitch position and then move the blades into high pitch
by pushing down on the high pitch stop (120).

,,s,,,,, 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

HIGHSTOP.XLS

Height I Height Part Number

Height I Height
Part Number
nch mm nch mm

A-2420-42 0.730 18.54 A-2420-27 1.180 29.97

A-2420-41 0.760 19.30 A-2420-26 1.210 30.73

A-2420-40 0.790 20.06 A-2420-25 1.240 31.49

A-2420-39 0.820 20.82 A-2420-24 1.270 32.25

A-2420-38 0.850 21.59 A-2420-23 1.300 33.02

A-2420-37 0.880 22.35 A-2420-22 1.330 33.78

A-2420-36 0.910 23.11 A-2420-21 1.360 34.54

A-2420-35 0.940 23.87 A-2420-20 1.390 35.30

A-2420-34 0.970 24.63 A-2420-19 1.420 36.06

A-2420-33 1.000 25.40 A-2420-18 1.450 36.83

A-2420-32 1.030 26.16 A-2420-17 1.480 37.59

A-2420-31 1.060 26.92 A-2420-15 1.510 38.35

A-2420-30 1.090 27.68 A-2420-14 1.540 39. 11

A-2420-29 1.120 28.44 A-2420-13 1.570 39.87

A-2420-28 1.150 29.21

A-24201( )High Pitch Stop Heights

Table 7-1

7-34
~SSEMBLY 61-10’13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

Height Height
Part Number
(inch) (mm)
8-6515-8 3.330 84.58

8-6515-7 3.285 83.43

8-6515-6 3.240 82.29

8-651 5-5 3.195 81.15

B-6515-4 3.150 80.01

8-651 5-3 3.105 78.86

8-6515-2 3.060 77.72

B-6515-1 3.015 76.58

B16515-( )High Pitch Stop Heights

Table 7-2

7-35
ASSEMBLY 61-10-13 Rev. 22 Jun/GOPage
 PROPELLER
HARTZELL MA:N~INCE MINUAL

APS2029

Spring (110)

li-~i j

Installing the A-2213-( )Spring

Figure 7126

APS2014

Pitch Change Rod (140)

Cotter Pin (60)

Nut (70)

Piston (90)

Piston OD O-Ring (80)

Spring (110)

Installing the Piston on the Pitch Change Rod

Figure 7-27

ASSEMBLY 61’10’13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1133

(d) Install the high pitch stop O-ring (100) (Figure 7-25).
(e) Install the spring (For a propeller using the A-2213-i i spring).

1 Install the spring (110) over the pitch change rod (140) (Figure 7-26).

NOTE: Compact non-feathering propellers (-1) have springs.

Compact aerobatic propellers (-4) do not have springs.
2 Slide the piston (90) onto the pitch change rod (140) with the piston
ID O-ring groove facing the high pitch stop (Figure 7-27). Compress
the spring with the piston to expose enough threads on the pitch
change rod to allow the piston nut to be started.

CAUTION: DO NOT TORQUE THE PISTON NUT (70) BEYOND

I 3 Install the
THE MAXIMUM TORQUE ALLOWED IN TABLE 8-1.

piston nut (70) onto the rod and torque to the minimum

allowance in accordance with Table 8-1. If the hole in the rod and the
slot in the nut do not align, continue to slowly torque the nut until
alignment is achieved.

CAUTION: DO NOT ALLOW THE COTTER PIN TABS TO BE

BENT OVER THE END OF PITCH CHANGE ROD.
COTTER PIN TABS BENT OVER THE END OF THE
PITCH CHANGE ROD INTERFERE WITH THE LOW
PITCH STOP.

4 Safety with the cotter pin (60) as shown in Figure 7-28.

APS2015

Cotter Pin (60)

Nut (70)

Pitch Change Rod (140)

Cotter Pin Installation

Figure 7-28

61-10-13
 PROPELLER
nARTZELL MA:N~N*NCE MANUPIL

W10193

Pitch Change Rod (140)

Cotter Pin (60)

Nut (70

Piston (90)

Piston OD O-Ring (80)

Installing the Piston on the Pitch Change Rod

Figure 7-29

W10213

Piston (90)

High Pitch Stop (120)

Pitch Change Rod (140)

Spring (110)

Installing the D-6509-( )Spring

Figure 7-30

ASSEMBLY 61’10-13
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 1138

(f) Installing the spring (For a propeller using the D-6509~( spring).
1 Slide the piston (90) onto the pitch change rod (140) with the piston
ID O-ring groove facing the high pitch stop (Figure 7-29).
2 Install the piston nut (70) torque in accordance with
onto the rod and
Table 8-1. If the hole in the rod and the slot in the nut do not align,
continue to torque the nut until alignment is achieved.

CAUTION: DO NOT ALLOW THE COTTER PIN TABS TO BE

BENT OVER THE END OF PITCH CHANGE ROD.
COTTER PIN TABS BENT OVER THE END OF THE
PITCH CHANGE ROD INTERFERE WITH THE LOW
PITCH STOP.

3 Safety with the cotter pin (60) as shown in Figure 7-28.

CAUTION: DO NOT REMOVE THE ASSEMBLED PITCH

CHANGE ROD/PISTON BY ATTACHING A
WRENCH TO THE COTTER-PINNED NUT (70);
USE THE END OF THE PITCH CHANGE ROD.

4 Unthread the assembled pitch change rod/piston from the fork and
remove from the hub.

5 Lubricate both ends of the spring (110) with CM12.

NOTE: Compact non-feathering propellers (-1) have springs.

Compact aerobatic propellers (-4) do not have springs.
6 Stand the spring (1 10) in place over the pitch change rod bore hole in
the hub.

7 Move the blades to low pitch position.

CAUTION: DO NOT INSTALL THE ASSEMBLED PITCH

CHANGE ROD/PISTON BY ATTACHING A
WRENCH TO THE COTTER-PINNED NUT (70);
USE THE END OF THE PITCH CHANGE ROD.

8 Insert the assembled pitch change rod/piston through the spring

(110), the cylinder-side hub half, and into the fork (190) (Figure 7-30).

NOTE: The spring (110) is compressed when the pitch change

rod/piston is turned into the fork (190).
9 Torque the pitch change rod (140) in accordance with Table 8-1.

BSSEMBLY 61-10-13 Rev.P2829Jeu7~09

 PROPELLER MAINTENANCE MANUAL
HP~ RTZ E LL 1138

I (g) Install the piston OD O-ring (80) in the piston (90) O-ring groove.

NOTE: Pistons were originally manufactured with a felt seal groove.

I Current production pistons no longer have a felt seal groove;
however, the original pistons were not made obsolete by this
improvement. When installing the piston O-ring on a piston with
a felt seal groove, be sure to place it in the appropriate groove.

Compact non-feathering propellers (-1) will have the O-ring

placed in the groove closest to the hub. Compact aerobatic
propellers (-4) will have the O-ring placed in the groove farthest
away from the hub.

(h) Install the cylinder O-ring (170) in the groove at the base of the cylinder

I (i)
attachment threads formed in the cylinder-side hub half.
Apply a bead of sealant CM92 on hub O-ring at the point where the
cylinder and hub will meet at installation (Aerobatic (-4) Propellers only).
(j) Lubricate the cylinder (50) attachment threads with lubricant CM12.

(k) Install the cylinder (50) onto the hub (Figure 7-31).
(I) Attach the cylinder torque wrench adapter TE153 to the cylinder (50)
(Figure 7-31).
(m) Torque the cylinder (50) in accordance with Table 8-1.

APS2023

Cylinder with Cylinder Torque Wrench

I Installing the
erugiF35Adapter
7-31 1ET
P~SSEMBLY 61’10’13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1133

to the low pitch stop (40) and

(n) Apply thread locking compound CM21 screw

I to)
install in the

Check the low

cylinder (Figure 7-32).
pitch stop angle.
1 Rotate the blades to the low pitch position and set the propeller pitch
in accordance with the aircraft Type Certificate Data Sheet.

2 Adjust the low pitch angle with the low pitch stop screw (40).

NOTE 1: To increase pitch, turn the low pitch stop clockwise. To

decrease pitch, turn the low pitch stop counterclockwise.

NOTE 2. Ifchanging the low pitch stop does not change blade
angle, verify that the slots in the preload plate are not
interfering with the pitch angle.
(40) (Compact Non-
I (p) (20) on the low pitch stop
Install the seal screw

Feathering (-1) Propellers only).

(q) Install the washer (30) on the low pitch stop screw (40) (Aerobatic (-4)
I
Propellers only).

W10215
Low Pitch Stop

\L_v
Seal orWasher
(20 or 30)
Refer to the
instructions.

"llh
Low Pitch
Stop Screw
(40)

Installing the Low Pitch Stop

Ii Figure 7-32

ASSEMBLY 61’10’13
 PROPELLER MPINV*L
HARTZ a LL

(r) Install low pitch stop jam nut (10) and torque in accordance with Table 8-1.

NOTE: Hold the low pitch stop screw (40) in place with an Alien wrench
when applying torque to the low pitch stop jam nut (10).
(s) Perform final low pitch angle check.

(t) Check the blade track (Figure 7-33). Refer to the Fits and Clearances
chapter, in this manual for blade track limits.

(4) For propellers HC-C3YR-(4A,4G) and HC-C2YR-(4E,4G) only Set a gap of

0.049 0.044 inch (1.24 -1- 1.11 mm) between the head of the spark gap screw
and the blade clamp. Refer to Figure 7-7.

APS6275A

Checking Blade Track

Figure 7-33

ASSEMBLY 61’10’13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

I G. Installation of the Lubrication Fitting

(1) install the lubrication fittings in the hub and torque in accordance with Table
8-1. Leave out one lubrication fitting in the cylinder-side of the hub for leak
testing of the hub.

(2) While the hub is installed on the propeller test stand, cycle the propeller to
purge air trapped in the hub.

(3) With the propeller actuated with air pressure, apply soap solution CM122 to the
lubrication fitting hole (Figure 7-34).

NOTE: To prevent the soap solution CM122 from being drawn into the hub,
wipe off the soap solution CM122 before releasing the air pressure.

(4) Any indication of air exiting the hub requires troubleshooting.

(5) After the leak check, install the remaining lubrication fitting in the hub and

torque in accordance with Table 8-1 (Figure 7-35).

APS2016

j~J

Hub Leak Check

Figure 7-34

AS8EMBLY 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

3. Counterweiaht Installation (Aerobatic Only)

Refer to Hartzell Manual 133C (61-13-33),

Aluminum Blade Overhaul, or Hartzell
Manual 135F (61-13-35),Maintenance Manual for Composite Propeller Blades, for
installation of counterweights.

4. Propeller Lubrication

Lubricate the
propeller in accordance with the Propeller Lubrication chapter of Hartzell
Standard Practices Manual 202A (61-01-02),

5. Static Balance

Perform static balance of the propeller in accordance with the Static and Dynamic
Balance chapter of Hartzell Standard Practices Manual 202A (61-01-02),

APS2030

,cF~

Lubrication Fittings Installed in Hub

I Figure 7-35

nssEnneLv 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

CONTENTS
8-3
1. Torque Values.............

LIST OF FIGU RES

Determining Torque Value of a Standard Torque Wrench

with Adaptor Figure 8-1 8-3

LIST OF TABLES

Table 8-1 8-5

Torque Values
I Blade Tolerances Table 8-2 8-6

nTs aND CLEARANCES 61 -1 0-1 3 R6Y

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

(This page is intentionally blank.)

I 61’1 0’13 RsY

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1138

Toraue Values

Threaded fasteners and hardware are the weakest components in an assembly.

Vibration can cause an improperly tightened fastener to fail in a matter of minutes.

tension in fastenerdepends on a variety of known load factors and can

Proper a

influence fastener service life. Proper tension is achieved by application of measured

torque.
Accurate wrenches and professional procedures will result in precision tensioning.
is used with torque wrench, the equation in Figure 8-1 to
When an adaptor a use

determine the torque value.

APS212

Torquing Adaptor
Standard Torque Wrench

1.00 foot 7- 0.50 foot

(304.8 mm) (152.4 mm)

torque wrench reading

tactual toraue reauired) x ttoraue wrench length) _

to achieve required
(torque wrench length) (length of adaptor) actual torque

EXAMPLE: reading on torque

wrench with 6-inch
100 Ft-Lb (136 N´•m)x 1 ft (304.8 mm)~
66.7Ft-Lb (152.4 mm) adaptor
1 ft (304.8 mm) 0.50 ft (152.4 mm)
(90.1 N´•m) for actual torque of
100 Ft-Lb (136 N´•m)

Determining Torque Value of a Standard Torque Wrench with Adaptor

Figure 8-1

FITS IZND CLEPIRPINCES 61 -1 0-1 3 ReV.

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1138

(This page is intentionally blank.)

I FTTS AND CLEPIRP~NCES 61 -1 0-1 3 Rev.

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

CAUTION: TORQUE VALUES ARE BASED ON NON-LUBRICATED THREADS,

U NLESS OTH E RWISE STATE D IN TABLE 8-1

I TORQUEP.XLS

Item Part
No. Number Descri n T ue Ft-Lb To e In-Lb T ue N´•m

10 8-3359 Nut, Jam, Low Pitch Stop 30 360 41

(-4 application)

8-3359 Nut, Jam, Low Pitch Stop 15 180 20

(-1 application)

8-3807 Nut, Jam, Low Pitch Stop 30 360 41

(-4 application)
120 150 wet 1440 1800 wet 162 203 wet
50 8-2428-() Cylinder

1 B-2281-() Cylinder 120 150 wet 1440 1800 wet 162 203 wet

C-6510 Cylinder 120 150 wet 1440 1800 wet 162 203 wet

15-60
I 70 A-22 1 1 Piston Rod Nut
Refer to NOTE 2
180 972 20 81

140 A-2418-( Piston rod fitted to fork 40 wet 480 wet 54

C-6512 Piston rod fitted to fork 40 wet 480 wet 54

280 A-2043-1 Hub clamping nut 20 22 240 264 27 30

330 A-0279 Lubrication Fitting 50 5

360 A-2044 "F" Fiange Mounting

A-3257 "N" Flange Mounting
400 A-2069 "K" 8 "R" Flange Mtg.
A-2498 "L" Flange Mounting
420 8-3368 Preload lock nut 10 120 14

570 8-3830 Pitch Chg. Knob Bracket Screw 20 240 27

B-3385-5H Pitch Chg. Knob Bracket Screw 28 336 38

Use mounting torque specified on propeller installation torque decal. Decal

usage is provided in Hartzell Standard Practices Manual 202A (61-01-02), Parts
and Identification and Marking Appendix A.

I NOTE 1 Torque tolerance is 1 0 percent unless otherwise noted. Refer to the Assembly
chapter of this manual when wet torque is designated.

I NOTE 2: Ref er to the text i n the Assembly chapte r of th is man ual.

Torque Values
Table 8-1

8-5
FITS AND CLEARANCES 61 -1 0-1 3 Rev
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 1138

Tolerances Affecting the Blades

In-and-Out Blade Play Noneallowed

End Play (leading edge to trailing edge) See Note 1 below.

Fore-and-Aft (Face to camber) See Note 1 below.

Radial Play (pitch change) 0.5 degree

measured at
referencestation

Blade Track Aluminum Blades rt 0.063 inch (1.60 mm)

or 0.125 inch (3.18 mm) total

Blade Track Composite Blades 0.125 inch (3.18 mm)

or 0.250 inch (6.35 mm) total

Blade Pitch Setting Tolerance 0.2degree

Between Blades at Low Pitch

NOTE 1: Blades are intended to be tight in the

propeller; however,
slightmovement is acceptable if the blade returns to its
original position when released. Blades with excessive
movement, or that do not return to their original position
when released may indicate internal wear or damage that
should be referred to an authorized propeller repair
station.

NOTE 2: For blade movement illustration, referto Figure 1 -1

Blade Tolerances
Table 8-2

8-6
FITS AND CLEARANCES 61 -1 0-1 3 Rev
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 113B

CONTENTS

9-3
1. Minimum Facility and Tooling Requirements
9-3
A. Tooling
B. Facilities 9’3

Tools............. ´•´•´•´•´•9-3
2. Special
9-3
A. Special Tools
9-3
B. Listings

Page 9-1

SPECIAL TOOLS, FIXTURES, FIND EOUIPMENT

61 -1 0-1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 113B

(This page intentionally blank.)

I SPECIAL TOOLS, FIXTURES, AND EOUIPMENT 61 -1 0-1 3 Rev

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1136

1. Minimum FacilitvandToolina Reauirements

A. Tooling
Propeller repair stations approved to overhaul Hartzell propellers are expected to
blade inspection and
possess precision fixtures, tools, and blade tables for
rework. Except as specifically required in this manual, locally fabricated tooling is
acceptable for most repair and inspection operations.
B. Facilities

(1) Grinding, plating, and painting of propeller components have the potential
for health and safety hazards beyond that of other areas of a typical
workshop. It is expected that such areas be in compliance with industry
standards and governmental regulations concerning occupational safety
and health, as well as environmental protection.
(2) Workshop areas segregated to prevent contamination. Separate
need to be
areas should be designated for cleaning, inspection, painting, plating, and

assembly. Propeller balancing must be performed in a draft free area.

2. Special Tools

NOTE: It is theresponisibility of the repair station to determine the special tooling

required for the propeller they are servicing or overhauling. The applicable
overhaul manual and the numerical index of Manual No. 165A provide
for
necessary information. Hartzell maintains no exact list of tools required
specific models of propellers or levels of service.
A. Special Tools

Hartzell Tool and Equipment Manual No. 165A contains a listing of special tools
available from Hartzell. The manual also includes vendor lists for other specialty

tooling not sold by Hartzell.

B. Listings
The Introduction section of Manual No. 165A provides information about what is
included in the listings and how to quickly locate tools.

Page 9-3

I SPECIAL TOOLS, FIXTURES, IND E~UIPMENT

61 -1 0-1 3 RB" 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

(This page intentionally blank.)

I SPECInL TOOLS. FIXTURES, ~ND E(IUIPMENT 61 -1 0-1 3 Rat

 PROPELLER MAINTENANCE MANUAL
H RT 2 E L L 1138

CONTENTS

1. Introduction
A. General 10-6

the Illustrated Parts List 10-5

B. Using
with De-ice System 10-5
C. Propeller Assemblies Configured a

2. The Illustrated Parts List 10’6

A. Detailed Parts List 10’6

B. Revisions

C. Vendors
Studs 10-8
3. F and N Flange
10-9
4. Two Bladed Propeller Improvements. . . . . . . . . . ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
10-10
5. Three Bladed Propeller Improvements
10-10
A. New Hub part Numbers. . . . . . . . . . . . . . . . . .´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
and -1R( Propeller Models 10-10
B. Three Bladed -1~
6. A-3204 and A-3204-2 Set Screws 10-10

10-117
Spinner Assembly Parts
10-130
Spinner Mounting Kit Parts
TWO BLADED -1 PROPELLER PART
10-18
(B)(C)(D)HC-C2YF-1 B(L)(F)
10-20
HC-C2YK-1B(L)(F)
HC-C2YL-1 B(L)(F) ´•´•´•´•´•´•´•´•10-22
10-24
HC-C2YR-1B(F)
10-26
HC-E2YL-1B(L)(F)
10~28
HC-E2YR-1B(L)(F)
10-30
HC-E2YR-1(S)(F)
HC-F2YL-1F 10-32
10-34
HC-F2YR-1(F)
BHC-G2YF-1 BF
10-38
(B)HC-12YF-1BF
HC-12YR-1BF 10-40
10-42
BHC-J2YF-1B(F)
BHC-J2YF-1C
BHC-L2YF-1BF 10’46

HC-M2YR-1 BF 10-48

ILLUSTRATED PARTS LIST 61 -1 0-1 3

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

TWO BLADED -4 PROPELLER PARTS

(B)HC-C2YF-4(B)(F) 10-50
HC-C2YK-4(A,B,C)(F) 10-52
HC-C2YL-4(B)(F) 10-54
HC-C~YR-LC(A,B,C)(L) 10-56
HC-C2YR-4E 10-58
HC-C2YR-4G 10-60
(B)HC-12YF-4(B)F
(B)HC-L2YF-4(B)F 10-64
THREE BLADED -1 PROPELLER PARTS

HC-C3YF-1(R)(L)(F) 10-66
PHC-C3YF-1MF 10-68
PHC-C3YF-1R(F) 10-70
HC-C3YN-1(F) 10-72
HC-C3YR-1 A 10-74
HC-C3YR-1MF 10-76
HC-C3YR-1(R)(L)(F)
HC-E3YR-1R(L)F 10-80
I HC-F3YR-1ARF
HC-F3YR-I RF 10-82
PHC-G3YF-1E 10-84
(P)HC-G3YF-1 RF 10-86
(P)HC-H3YF-1RF 10-88
HC-13YR-1E
HC-13YR-1RF 10-92
PHC-J3YF-1MF 10-94
(P)HC-J3YF-1 RF 10-96
(P)(E)HC-L3YF-1RF 10-98
HC-M3YR-1RF

THREE BLADED -4 PROPELLER PARTS

(P)HC-C3YF-4(B)F 10-102
HC-C3YN-4(B)F 10-104
HC-C3YR-4(B)F 10-106
HC-C3YR-4A
HC-C3YR-4G

I PHC-H3YF-4BF ........._,,,
.~10-111.1

FOUR BLADED PROPELLER PARTS

HC-C4YF-1(E) 10-112
HC-F4YR-1 10-114

ILLVSTRATED PARTS LIST 61’1 0-1 3 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

LIST OF ILLUSTRATIONS

View Figure 10-1 10-11

Two Blade Propeller Exploded
View -1MF and -1E) Figure 10-2...... 10-12
Three Blade Propeller Exploded (Except
View Figure 10-3...... 10-13
Three Blade -IMF and -1E Propeller Exploded
View......... Figure 10-4...... 10-14
Four Blade Propeller Exploded
View Figure 10-5...... 10-15
Blade Exploded
Parts...... Figure 10-6...... 10-16
F Flange Mounting
N Flange Mounting Parts Figure 10-7......10-17

LIST OF TABLES

........Table 10-1 10-9

I -1, -1A and -1B Propeller Model Part Substitutions

ILLUSTRATED PARTS LIST

61 ’1 0’1 3
 PROPELLER MANUAL
HA RTZ E LL MA:N1T3EsNANCE

(This page is intentionally blank.)

I ILLUSTRATED PARTS LIST 61’1 0’1 3

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

lntroducti_o_n

A. General
for the
(1) This Illustrated Parts List contains all of the current configurations
covered in this
specified propellers manufactured by Hartzell Propeller Inc.
for
manual and supersedes any prints that may have previously been supplied
contained within the Illustrated
part and assembly information. The parts lists
models and
Parts List are to be used for verifying the configuration of propeller
ordering parts.

CAUTION: ILLUSTRATIONS IN THE ILLUSTRATED PARTS LIST ARE TO BE

USED FOR IDENTIFYING PARTS AND SHOULD NOT BE USED
AS A MAINTENANCE REFERENCE FOR ASSEMBLY.

(2) Figures are for reference only.figures provide general views of parts.
The
For ease of illustration, typical views of some parts were
created and shown
not exactly reflect
in multiple figures. For this reason, illustrated parts may

parts contained in some propeller assemblies.

B. Using the Illustrated Parts List

(1) Every effort has been made to include allapplicable propellers and
this manual. If an
configurations manufactured by Hartzell Propeller Inc. in
in the
overhaul facility has questions about a propeller configuration as stated
Illustrated Parts List, contact the Hartzell Propeller Product Support
Department.
that may be
(2) Basic Propeller Parts: Refers to all of the propeller components
unique to a particular propeller model.
(3) Spinner Mounting Kits have been included in this manual. responsibility
It is the

of the propeller maintenance facility to ensure that the appropriate spinner and
Guide
mounting parts have been installed. Refer to the Hartzell Application
Manual 159 (61-02-59) for spinner assembly application information.

(4) Spinner Parts: These components are application specific. Most propeller
installation
models have more than one spinner possibility and require the
information for the particular application to determine the appropriate spinner.

(5) )-Flange Parts: Refers to the type of flange parts used on a particular
propeller model.
(6) Balance Parts: These components are common to most compact propellers.

C. Propeller Assemblies Configured with a De-ice System

is not configured with a
The Illustrated Parts List assumes the propeller assembly
de-ice system. For de-ice part information, refer to the BF Goodrich Replacement
for the applicable de-ice
Parts List, the BF Goodrich general arrangement drawing
or the airframe manufacturer’s maintenance
manual.
kit,

ILLUSTRATED PARTS LIST

61’1 0’1 3
 PROPELLER
HARTZELL MA:N~ANCE M~NUAL

2. The Illustrated Parts List

A. Detailed Parts List

The Detailed Parts List consists of the Figure/item Number, Part Number,
Description, Effectivity Code and Units Per Assembly. The following is an
explanation of each column:
(1) Fig/ltem Number

(a) FigureNumber refers to the illustration where items appear. Item

Numbers are assigned in broken sequence to allow the insertion of

subsequent additional parts. Items listed but not illustrated are identified
by a dash to the left of the item number.

(b) Alpha variants will be used to add additional items. There are two reasons
for the use of alpha variants:

1 A part may have an alternate, or may be superseded, replaced, or

obsoleted by another part. For example, the two way aluminum hub
(D-2201-3) that is item 180 was superseded by the two way aluminum
hub (D-6529-1) that is item 180A.

2 An Illustrated Parts List may contain multiple configurations.

Effectivity codes are used to distinguish different part numbers within
the same list. For example, one configuration may use a blade
bushing (A-2413) that is item 565, yet another configuration uses a
blade bushing (A-2413-2) that is item 565A. Effectivity codes are
very
important in the determination of parts in a given configuration.
(2) Part Number

Use the Hartzell part number when ordering the part from Hartzell or a Hartzell
approved distributor. Digits of Hartzell Part Numbers have no significance other
than to identify a part.

(3) Description
This column identifies the item. The relationship of parts to assembly is
indicated by the use of indentations. This column may also contain vendor
CAGE codes, as applicable. Information regarding part alternative,
supersedure, replacement, or obsolescence may also be found in this column.
Refer to Revisions, in this section, for further information regarding alternate,
superseded, replaced, or obsoleted parts.
(4) Effectivity Code (EFF CODE)
The effectivity column shows the prefix and/or suffix of the propeller model to which
the parts apply. In some cases, the specific engine or aircraft manufacturer
may be
called out. Effectivity codes assigned apply only to the figure/listing in which
they
appear. Parts common to all end items show no code.

ILLUSTRPlrrD PIRTS LIST 61 -10-13

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

(5) Units Per Assembly (UPA)

total quantity of item required for the next
Units perassembly designates the an

higher assembly or subassembly.

B. Revisions

(1) Alternate

Alternate parts are identified by the term "ALTERNATE" in the Description

and
column. Alternate items are considered airworthy for continued flight
and/or repair. The part
existing stock of parts may be used for maintenance
numbers may be used interchangeably when ordering/stocking new parts.

(2) Supersedure
Part changes identified by the terms "SUPERSEDES ITEM
are
or

"SUPERSEDED BY ITEM in the Description column. Superseded items

are considered airworthy for continued flight

and existing stock of superseded

parts may be used for maintenance and/or repair. Superseded parts may
no

longer be available, and the new part number must be used when ordering/
stocking new parts.

(3) Replacement
or "REPLACED
Part changes identified by the terms "REPLACES ITEM
BY ITEM in the Description column are considered airworthy for continued
number at overhaul.
flight, but must be replaced with a part with the new part
and/or repair of
Existing stock of replaced parts may not be used for maintenance
the new part
effected assemblies. Replaced parts may no longer be available, and
number must be used when ordering/stocking new parts.

(4) Obsolescence

Obsolete parts are identified by "OBS" Assembly (UPA)

in the Units Per
column. Obsolete items are considered unairworthy for continued flight.

(5) Service Documents and Airworthiness Directives

(a) In the event of modification or rework of an existing part, the supersedure,

replacement, or obsolescence of a part, or the addition of parts installed
the SE SL number will
by a Service Bulletin (SB) or Service Letter (SL),
or

"SB "SL after the

appear in the Description column as
or

description.
the AD will
(b) When a SE has arelationship to an Airworthiness Directive (AD),
be shown in parentheses after the SE number as SE (AD

ILLUSTRATED PARTS LIST

61’1 011 3
 PROPELLER
HA RTZ E LL MA:N:3EsNANCE MANUAL

C. Vendors

(1) Many O-rings, fasteners, and other vendor supplied hardware listed in Hartzell
manuals have previously been specified with AN, MS, NAS or vendor part
number. To provide internal controls and procurement flexibility, Hartzell has
made engineering changes to provide all O-rings, fasteners, and hardware with
a Hartzell part number. Parts shipments from Hartzell will
specify only the
Hartzell part numbers.

(2) Some O-rings, fasteners, and hardware manufactured in accordance with

established industry specifications (certain AN, MS, NAS items) are acceptable
for use in Hartzell products without additional standards imposed by Hartzell.
Refer to the Vendor Cross Reference chapter of Hartzell Standard Practices
Manual 202A (61-01-02), for a listing of part number interchangeability. Where
allowable, both the Hartzell part number item and AN, MS, NAS, and other
specified vendor numbers items can be used interchangeably. The Hartzell part
number must be used when ordering these parts from Hartzell.

3. F and N flanae Studs

The installation of studs in F and N flange propeller models is dependent upon the
propeller application. Refer to the Aluminum Hub Overhaul chapter of Hartzell Manual
202A for specific part and installation requirements.

ILLUSTRATED PARTS LIST 61’1 0’1 3

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

4. Two Bladed ProPeller improvements

A. Two Bladed -l,-1A, and -1B Propeller Models

The part propeller models specified in this illustrated parts listing are of the
lists for
latest configurations produced by Hartzell Propeller Inc. Some models were
made
produced as -1 or -1A models (Example: HC-C2YK-1). Improvements were
in the production of these propellers and are denoted by the -18 (Example:
HC-

C2YK-1B). The improvements included a new spring, pitch change rod, pitch
change fork, and cylinder. The -1 and -1A models are not obsolete; however,
identical to
replacement parts may not be available. The -18 model propellers are
-1 or -1A models except for substituting the parts as listed in Table 10-1.

-1 -1A Parts -1B Parts

Description or

8-2224 8-2428 8-2428-1

Cylinder or

Piston Rod A-2418 or A241 8-1 A-2418-2

Fork 8-2410, 8-2410-1, or 8-2410-2 8-2457-1 or B-2457-2

St)Tj A-2213 A-221 3-1

-1, -1A and -1B Propeller Model Part Substitutions

Table 10-1

B. Two Bladed -1() and -1()F Propeller Models

Improvements were production of two-bladed propeller models in the

made in the
form of the F-knob blade. Propeller models using blades with the strengthened pitch
of the model
change knob are denoted by the addition of an "F" at the end
designation (Example: HC-C2YK-1BF). These propellers use larger forks
to

accomodate the increased size of the pitch change blocks.

ILLUSTRATED PARTS LIST 61’1 0’1 3

 PROPELLER MANUAL
HARTZ ELL

5. Three Bladed ProPeller Improvements

A. New Hub Part Numbers

Improvements were made in the production of three-bladed propeller models in the

form of an improved three-bladed compact propeller hub. Improved style hubs have
new part numbers and are identifiable by the suffix letter "B" at the end of the hub

serial number and the propeller serial number. The improved style hubs are visibly
different from previous hubs due to material added to the forging in the blade
retention area.

B. Three Bladed -1( and -1R( Propeller Models

Hartzell Propeller Inc.

currently produces hub units for only -1R( propeller models.
Hub units for the-1( propeller models are no longer procurable. The hydraulic
units of the -1( propeller models are incompatible with the new -1R( propeller
hub unit and must be changed if a new hub is installed. By incorporating the new
design hub and the accompanying hydraulic components, the -1( propeller
becomes a -1R( propeller and uses the parts listed for the -1R( propeller.

6. A-3204 and A-3204-2 Set Screws

A. A-3204 and A-3204-2 set screws with a certain hardness are to be removed from
field stocks.

NOTE: There have been several reports of broken A-3204 set screws. Two
contributing factors are the hardness and, in some screws, the depth of
the hex recess on the end of the screw (used for the internal wrench) was
aligned with the end of the external jam nut, which combined to form a

highly stressed area in the screw thread.

B. Screws that must be removed from stock are identifiable by their color.

(1) New screws with the desired hardness are color coded with a dull "olive green"
color. Any screws with "olive green" color are serviceable.

(2) Previous screws were a bright "bronze" color. Any screws of the "bronze" color
are not to be used and may be returned to Hartzell (via the source of
procurement) for credit or replacement.

ILLUSTRATED PARTS LIST 61 -1 0’1 3

 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 113B

PWAY.PLT
W1028’ 360

350

320
300
230 310
290

220
=1Cc~370
340

260
P: 180

170 280
160 270

140~240

210
330
190
120
250
200

(K, L, AND R FLANGE)

180

"‘1 100 (C~?

T 80
70

n~40 20
30
414
50

(E2YL FLANGE)
180
410
390
10
400

380

412

41 390
400

Two Blade Propeller Exploded View

Figure 10-1

Page 10-11

ILLUSTRATED PARTS LIST 61~10113 Rev. 22 Jun/GO

 PROPELLER
HARTZELL MA:NI~EsNANCE
B311LIUNAM

3way.plt

360

350

320

230 300
310

220
c-
~Zei (F N flange)
340
180

334

336
260

280
170
,a 270
160 195
150

140
130

250
120
200
110

190
\r
60
(K, L, AND R FLANGE)
100 180

90

281

80
70
270

380
50
40
30
20
10

41O 390 i76

400 275

Three Blade Propeller Exploded View (Except -1MF and -1E)

Figure 10-2

ILLUSTR~TEO PARTS LIST 61’1 0-1 3 Rev. 22 Jun/GOPage 10-12

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

dways.plt

360

350

320
300
230 310

220
=44370
340

(F 8 N FLANGE)
180

260

280

170 270
,a-
Iso 195

150

140
130

250/ 200

190

$g~:
380

""I i"~,=s;‘\
90

280
110 80
70 270

1202040
10
50

410 ’390

400

Three Blade -1MF and -1E Propeller Exploded View

Figure 10-3

Page 10-13

ILLUSTRATED PARTS LIST

61-10-13 Rev. 22 Jun/GO
 PROPELLER
HARTZELL

4WAY.PLT

360

359

320

300
310
290

370
230
340
220

180
(F N FLANGE)

260

280

270
170
o

160

130
140 330

"kj\, q
240

195
120 250
110 60
190

200

100 380

r$;180 70
80
90

(K, L, &R FLANGE)

740
10
20
30
50::400 410
390

Four Blade Propeller Exploded View

Figure 10-4

ILLUSTRATEO LIST 61’1 0-1 3 Rev. 22 Jun/GOPage 10-14

 PROPELLER
HARTZELL MA~ERNANCE
B311LAUNAM
W10189

550

567470

565

560
540

570520440
430

420
490

Blade Exploded View

Figure 10-5

ILLUSTRATEO PARTS LIST 61 ’1 0-1 3 Rev. 22 Jun/GOPage 10-15

 PROPELLER
HARTZ ELL MPI:N1:~BNPINCE MANUAL

F-FLNO1.PLT

PROPELLER FLANGE

370
340

320

ENGINE FLANGE
O

P,

350

360

F Flange Mounting Parts

Figure 1016

ILLUSTRATED PARTS LIST 61 -1 0-1 3 10-16

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1136

N-FLANGE.PLT

PROPELLER FLANGE

340 370

320

ENGINE FLANGE O
I~

350

360

N Flange Mounting Parts

Figure 10-7

Page 10-17

ILLUSTRP~TED P~RTS LIST 61 -1 0-1 3 Rev. 22 Jun/GO

 PROPELLER
HARTZELL

FIG.IITEM I PART DESCRIPTION EFF UPA

NVMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 8-3359 ELASTIC STOP NUT 1
20 1 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
so 1 8-2428-1 CYLINDER UNIT 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD 1
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-2 ROD, PISTON 1
170 1 C-3317-247 ´•O-RING, CYLINDER 1
180 1 D-2201-1 HUB, TWO WAY ALUMINUM HC- I 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180AI D-6531-1 HUB, TWO WAY ALUMINUM HC- I 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
18081 D-22o1-5 HUB, TWO WAY ALUMINUM BHC- I 1
SUPERSEDED BY ITEM 180C, PRE SL HC-SL81-179
180CI 0-6531-2 HUB, TWO WAY ALUMINUM BHC- I 1
SUPERSEDES ITEM 1808, POST SL HC-SLB1-179
180DI D-22o1-9 HUB, n/vO WAY ALUMINUM CHC- I 1
SUPERSEDED BY ITEM 180E, PRE SL HC-SL-61-179
180EI D-6s31-3 HUB, TWO WAY ALUMINUM CHC- I 1
SUPERSEDES ITEM 180D, POST SL HC-SL-61-179
180FI D-2201-11 HUB, TWO WAY ALUMINUM DHC- I 1
SUPERSEDED BY ITEM 180G, PRE SL HC-SLS1-179
180Gi D-6531-4 HUB, TWO WAY ALUMINUM DHC- I 1
SUPERSEDES ITEM 180F, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-6‘1-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 1 8-2457-3 FORK, PITCH CHANGE 1
-192 1 A-3323 RUBBING PLATES 2
-193 1 8-3842-0500 SPRING PIN 4
200 1 A-2217-4 BLOCK, PITCH CHANGE -1B 1 2
A-2217-3 BLOCK, PITCH CHANGE -18(L)F 2
210 A-3212 BUTTON, PITCH CHANGE BLOCK -1B 1 2
210AI A-3212-1 BUTTON, PITCH CHANGE BLOCK -1B(L)F 2
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF I I 1
250 1 A-2431 BOLT, HEXAGON HEAD 6
260 1 A-2432 BOLT, HEXAGON HEAD 4
270 1 8-3834-0632 .WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 LUBRICATION FITTING 4
-331 1 8-6544 CAP, LUBRICATION FITTING 4

ITEM NOT ILLUSTRATED D-2425

(B)(C)(D)HC-CPYF-~ B(L)(F)

ILLUSTRP~TED P*RTS LIST 61 ’1 0’1 3 Rev. 22 Jun/GOPage 10-18

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 113B

FIGJITEM I PART DESCRIPTION EFF UPA

NUMBER I NUMBER I I CODE

BLADE RETENTION PARTS

10-5-419 1 8-2256 1 PRELOAD PLATE ASSEMBLY I 1 2
420 1 8-3368 NUT, JAM HEXAGON I I 1
430 1 A-3204 SET SCREW, SOCKET DRIVE I I 1
440 1 8-2222 PLATE, BLADE PRELOAD I 1
450 1 8-6679 1 INNER RING I I 1
460 A-2204 RETENTION RING, BEARING 2
490 1 A-2202-8 1 BLADE BEARING, BLADE RACE I 1 2
510 1 8-3211 1 BALL SPACER I 1 2
520 1 8-6144 1/2" DIAMETER STEEL BALL I 1 50
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 1 A-2202-A BLADE BEARING, HUB RACE I 1 2
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 1 2
565 1 A-2413 BUSHING, BLADE I -lB 1 2
A-241 3-2 1 .BUSHING, BLADE -1 B(L)F 2

F-FLANGE MOUNTING PARTS

10-6 320 1 C-3317-226 O-RING, FLANGE I I 1
340 r A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 1 6
A-2429-4 1 STUD, HUB MOUNTING, REFER TO NOTE 1 I 1 6
350 1 A-1381 ´•WASHER, HARD, STAINLESS 6
360 1 A-2044 1 SELF LOCKING NUT I 1 6
370 1 8-6138-8-9 1 DOWEL PIN I 1 2

BALANCE PARTS
-9000 8-3840-( SCREW(AN501A10-( MS35266-( AR
-9020 A-2424(A)-( BALANCE WEIGHT I IAR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A ~61-01-02)

D-2425
ITEM NOT ILLUSTRATED
(B)(C)(D)HC-CPYF-1 B(L)(F)

Page 10-19
ILLUSTR~TED P~RTS LIST ~1 -1 0-1 3 Rev. 22 Jun/GO
 PROPELLER
HARTZELL B311LAUN~M

FIG./ITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER
CODE

BASIC PROPELLER PARTS

10-1 10 8-3359 ELASTIC STOP NUT
1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP
1
50 8-2428-1 CYLINDER UNIT
1
60 8-3838-3-5 COTTER PIN (AN380-3-5)
1
70 A-2211 NUT, PISTON ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 B-2419 PISTON
100 1 C-3317-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER
1
140 A-241 8-2 ROD, PISTON 1
170 C-331 7-247 O-RING, CYLINDER 1
180 D-2201-3 HUB, TWO WAY ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180A D-6529-1 .HUB, TWO WAY ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
160A A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-2457-3 FORK, PITCH CHANGE 1
-192 A-3323 RUBBING PLATES
2
-193 8-3842-0500 SPRING PIN
200 A-2217-4 BLOCK, PITCH CHANGE -1B 2
A-2217-3 BLOCK, PITCH CHANGE
-IB(L)F 2
210 A-3212 BUTTON, PITCH CHANGE BLOCK -1B 2
210A A-3212-1 BUTTON, PITCH CHANGE BLOCK
-1B(L)F 2
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 6
260 A-2432 BOLT, HEXAGON HEAD 4
270 8-3834-0632 ´•WASHER, FLAT, STEEL 10
280 A-2043-1 NUT, SELF LOCKING 10
330 A-279 LUBRICATION FITTING
4
-331 8-6544 CAP, LUBRICATION FITTING 4

ITEM NOT ILLUSTRATED D-2425

HC-C2YK-1 B(L)(F)

ILLUSTRATED PARTS LIST 61’1 0-1 3 Rev. 22 Jun/GOPage 10-20

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1138

FIG.IITEM PART I DESCRIPTION I EFF IUPA

NUMBERI NUMBER I I CODE

BLADE RETENTION PARTS

10-5-419 1 8-2256 1 PRELOAD PLATE ASSEMBLY I 1 2
420 1 8-3368 NUT, JAM HEXAGON 1
430 1 A-3204 SET SCREW, SOCKET DRIVE 1
440 1 8-2222 PLATE, BLADE PRELOAD 1
450 1 8-6679 INNER RING i I 1
460 1 A-2204 RETENTION RING, BEARING 2
490 1 A-2202-8 BLADE BEARING, BLADE RACE 2
510 1 8-3211 I BALL SPACER I 1 2
520 1 8-6144 1 1/2" DIAMETER STEEL BALL I 1 50
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 1 A-2202-A BLADE BEARING, HUB RACE 2
540 1 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 2
565 1 A-2413 ´•BUSHING, BLADE -1B 1 2
A-241 3-2 BUSHING, BLADE -1B(L)F 2

K-FLANGE MOUNTING PARTS

320 1 C-3317-228 .O-RING, FLANGE 1
380 1 A-2067 STUD, HUB MOUNTING 6
390 1 A-1381 ´•WASHER, HARD, STAINLESS 6
400 1 A-2069 NUT, HEXAGON CASTLEATED I I 6
410 1 8-3842-0750 1 SPRING PIN I 1 6

BALANCE PARTS
-9000 8-3840-( SCREW(AN501A10-( MS35266-( AR
-9020 A-2424(A)-( BALANCE WEIGHT I I AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-2425
ITEM NOT ILLUSTRATED
HC-CSYK-1 B(L)( Fl

Page 10-21
ILLUSTRATED PARTS LIST 61 ’1 0’1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 8-3359 ELASTIC STOP NUT 1

20 1 8-6747 SEAL, WASHER 1

40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1

50 1 8-2428-1 CYLINDER UNIT 1

60 8-3838-3-5 COTTER PIN (AN380-3-5) 1

A-2211 NUT, PISTON ROD 1

70
80 C-3317-348-1 O-RING, PISTON OD 1
PISTON 1
90 1 8-2419
C-331 7-018 O-RING, PISTON ID 1
100
A-2213-1 SPRING, LOW PITCH RETURN 1
110
SPACER, HIGH PITCH STOP 1
120 A-2420-(
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1

140 1 A-2418-2 ROD, PISTON 1

170 1 C-3317-247 ´•O-RING, CYLINDER 1

180 1 D-2201-7 HUB, TWO WAY ALUMINUM 1

SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179

180AI D-6529-2 HUB, TWO WAY ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
160A
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
240 1 A-2249 ´•´•BUSHING, GUIDE 1

190 1 8-2457-3 FORK, PITCH CHANGE 1

RUBBING PLATES 2
-192 1 A-3323
-193 1 8-3842-0500 SPRING PIN I 1 4

200 1 A-2217-4 BLOCK, PITCH CHANGE -18 1 2

200A A-2217-3 BLOCK, PITCH CHANGE -1B(L)F 2

210 1 A-3212 BUTTON, PITCH CHANGE BLOCK -18 1 2

210A A-3212-1 BUTTON, PITCH CHANGE BLOCK -18(L)F 2

220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1

250 1 A-2431 BOLT, HEXAGON HEAD 6

260 1 A-2432 BOLT, HEXAGON HEAD 4

270 1 8-3834-0632 ´•WASHER, FLAT, STEEL 10

280 1 A-2043-1 NUT, SELF LOCKING 10

330 1 A-279 LUBRICATION FITTING 4

-331 18-6544 CAP, LUBRICATION FITTING 4

D-2425
ITEM NOT ILLUSTRATED
HC-C2YL-1 B(L)(F)

10-22
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BLADE RETENTION PARTS

10-5-419 1 8-2256 PRELOAD PLATE ASSEMBLY 2

420 1 8-3368 NUT, JAM HEXAGON 1

430 1 A-3204 SET SCREW, SOCKET DRIVE 1

440 1 8-2222 1 PLATE, BLADE PRELOAD 1

450 1 8-6679 INNER RING 1

460 1 A-2204 RETENTION RING, BEARING 2

490 1 A-2202-B BLADE BEARING, BLADE RACE 2

510 1 8-3211 BALL SPACER I 1 2

520 1 8-6144 112" DIAMETER STEEL BALL I 1 50

-520A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A BLADE BEARING, HUB RACE 2

540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2

540A 8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 2

565 1 A-2413 BUSHING, BLADE -1B 1 2

565A A-2413-2 BUSHING, BLADE -1B(L)F 2

L-FLANGE MOUNTING PARTS

320 1 C-3317-228 O-RING, FLANGE 1

380 1 A-2247-1 STUD, HUB MOUNTING 6

390 1 A-2482 ´•WASHER, HARD, STAINLESS 6

400 1 A-2498 NUT, HEXAGON CASTLEATED 6

410 1 8-3842-0625 1 ´•SPRINGPIN 6

BALANCE PARTS
´•SCREW(AN5D1A10-( MS35266-( AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS -APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-2425
ITEM NOT ILLUSTRATED
HC-C2YL-1 B(L)(F)

Page 10-23
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM 1 PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 ELASTIC STOP NUT 1
20 1 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2428-1 CYLINDER UNIT 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD 1
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1

(LENGTH TO SUIT PITCH REQUIREMENTS)

130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-2 ROD, PISTON 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 1 0-2201-17 HUB, TWO WAY ALUMINUM I I 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-BI-179
180AI D-6529-1 HUB, TWO WAY ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-G1-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 1 8-2457-3 1 FORK, PITCH CHANGE 1
-192 1 A-3323 RUBBING PLATES 2
-193 1 8-3842-0500 SPRING PIN 4
200 1 A-2217-4 BLOCK, PITCH CHANGE -18 1 2
200A A-2217-3 BLOCK, PITCH CHANGE -1BF 1 2
210 1 A-3212 BUTTON, PITCH CHANGE BLOCK -18 1 2
210A A-3212-1 BUTTON, PITCH CHANGE BLOCK -1BF 1 2
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD 6
260 1 A-2432 BOLT, HEXAGON HEAD 4
270 1 8-3834-0632 WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 LUBRICATION FITTING I 1 4
-331 1B-6544 CAP, LUBRICATION FITTING 4

D-2425
ITEM NOT ILLUSTRATED
HC-CZYR-IB(F)

Page 10-24
ILLUSTRATED PARTS LIST 61 -1 0-1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
NUT, JAM HEXAGON 1
420 1 8-3368
430 1 A-3204 SET SCREW, SOCKET DRIVE 1

PLATE, BLADE PRELOAD 1

440 1 8-2222
1 8-6679 INNER RING 1
450
460 1 A-2204 RETENTION RING, BEARING 2

490 1 A-2202-8 BLADE BEARING, BLADE RACE 2

510 1 8-3211 BALL SPACER 2

520 1 8-6144 1/2" DIAMETER STEEL BALL 50

-520A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A I BLADE BEARING, HUB RACE 2

540 1 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2

540A 8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 2

565 1 A-2413 BUSHING, BLADE -18 1 2

565A A-2413-2 BUSHING, BLADE -1BF 1 2

R-FLANGE MOUNTING PARTS

320 1 C-3317-228 O-RING, FLANGE 1

380 1 A-2067 STUD, HUB MOUNTING 6

390 1 A-1381 ´•WASHER, HARD, STAINLESS 6

400 1 A-2069 NUT, HEXAGON CASTLEATED 6

410 1 8-3842-0750 SPRING PIN 6

BALANCE PARTS
´•SCREW(AN501A10-( MS35266-( AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-2425
ITEM NOT ILLUSTRATED
HC-CPYR-1 B(F)

Page 10-25
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART DESCRIPTION I EFF IUPA

NUMBER I NUMBER I I CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 ELASTIC STOP NUT I I 1
20 1 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2428-1 CYLINDER UNIT I I 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD I I 1
80 1 C-3317-348-1 O-RING, PISTON OD I I 1
90 1 8-2419 1 PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID I I 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 1 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-2 ROD, PISTON 1
170 C-331 7-247 O-RING, CYLINDER 1
180 1 D-2483-1 HUB, TWO WAY ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-B1-179
180AI D-6562-1 HUB, TWO WAY ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-B1-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
230 1 A-2245-1 BUSHING, ENGINE-SIDE HUB HALF 1
SUPERSEDED BY ITEM 230A, PRE SL HC-SL-61-179
230AI A-2245-3 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
SUPERSEDES ITEM 230, POST SL HC-SL-61-179
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 1 8-2457-3 1 FORK, PITCH CHANGE 1
-192 lA-3323 1 RUBBING PLATES 2
-193 1 8-3842-0500 1 SPRING PIN I 1 4
200 1 A-2217-4 1 BLOCK, PITCH CHANGE -18 1 2
200AI A-2217-3 1 BLOCK, PITCH CHANGE -1B(L)F 2
210 1 A-3212 1 BUTTON, PITCH CHANGE BLOCK -18 1 2
210AI A-3212-1 1 BUTTON, PITCH CHANGE BLOCK -1B(L)F 2
250 1 A-2431 BOLT, HEXAGON HEAD 6
260 1 A-2432 BOLT, HEXAGON HEAD 4
270 1 8-3834-0632 1 .WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING 10
290 1 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 lA-2481 EXTENSION PLUG I I 1
310 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 lA-279 LUBRICATION FITTING I 1 4
-331 16-6544 CAP, LUBRICATION FITTING 4

D-3235
ITEM NOT ILLUSTRATED
HC-ESYL-1 B(L)(F)

Page 10-26
ILLUSTRATED PARTS LIST 61’1 0’1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 113B

PART DESCRIPTION EFF IUPA

FIG.IITEM I
CODE
NUMBERI NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
1
420 1 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 1 A-3204
1
440 1 8-2222 PLATE, BLADE PRELOAD
INNER RING 1
450 1 8-6679
RETENTION RING, BEARING 2
460 1 A-2204
BLADE BEARING, BLADE RACE 2
490 1 A-2202-8
BALL SPACER 2
510 8-3211
1/2" DIAMETER STEEL BALL 50
520 1 8-6144
1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
-520AI 8-6144-650
BLADE BEARING, HUB RACE 2
530 1 A-2202-A
2
540 1 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A
QUAD RING SEAL, BLADE, REPLACES ITEM 540 2
540A 8-3883-4339
1 A-2413 BUSHING, BLADE -1B 1 2
565
-18(L)F 2
565A A-2413-2 BUSHING, BLADE

L-FLANGE MOUNTING PARTS

1
320 1 C-3317-228 ´•O-RING, FLANGE
2
380 1 A-2247-1 STUD, HUB MOUNTING
2
390 A-2482 .WASHER, HARD, STAINLESS
NUT, HEXAGON CASTLEATED 2
400 1 A-2498
SPRING PIN 2
410 1 8-3842-0625
HEX BOLT 4
412 1B-6489-25
8-6526-7 1 ´•WASHER 4
414

BALANCE PARTS
MS35266-( AR
-9000 8-3840-( SCREW(AN501A10-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-3235
ITEM NDT ILLVSTRATED
HC-E2YL-1 B(L)(F)

Page 10-27

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1~38

FIG.IITEM PART I DESCRIPTION I EFF IUPA

NUMBERI NUMBER I I CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 ELASTIC STOP NUT I I 1
20 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2428-1 1 CYLINDER UNIT I I 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD 1
80 1 C-3317-348-1 O-RING, PISTON OD I I 1
90 1 8-2419 PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID I I 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER I I 1
140 1 A-2418-3 ROD, PISTON 1
170 1 C-3317-247 O-RING, CYLINDER I I 1
180 1 D-2477-3 HUB, TWO WAY ALUMINUM I I 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180A D-6564-1 1 ´•HUB,TWOWAYALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 A-2245 1 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
160A A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF I I 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
230 1 A-2245-1 1 BUSHING, ENGINE-SIDE HUB HALF I I 1
SUPERSEDED BY ITEM 230A, PRE SL HC-SL-61-179
230A A-2245-3 1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF I I 1
SUPERSEDES ITEM 230, POST SL HC-SL-61-179
240 1 A-2249 BUSHING, GUIDE I I 1
190 1 8-2457-3 FORK, PITCH CHANGE I I 1
-192 1 A-3323 RUBBING PLATES I 1 2
-193 1 8-3842-0500 1 SPRING PIN I 1 4
200 1 A-2217-4 BLOCK, PITCH CHANGE -1B 1 2
200A A-2217-3 BLOCK, PITCH CHANGE -1B(L)F 2
210 1 A-3212 .BUTTON, PITCH CHANGE BLOCK -1B i 2
210A A-3212-1 BUTTON, PITCH CHANGE BLOCK -18(L)F 2
250 1 A-2431 BOLT, HEXAGON HEAD I 1 6
260 1 A-2432 BOLT, HEXAGON HEAD I 1 4
270 1 B-3834-0632 WASHER, FLAT, STEEL I i 10
280 1 A-2043-1 NUT, SELF LOCKING I 1 10
290 1 C-3317-226 O-RING, EXTENSION PLUG OD I I 1
300 1 A-2481 1 EXTENSION PLUG I I 1
310 1 C-3317-115-1 O-RING, EXTENSION PLUG ID I I 1
330 1 A-279 1 LUBRICATION FITTING I 1 4
-331 18-6544 CAP, LUBRICATION FITTING I 1 4

D-3235
ITEM NOT ILLUSTRATED
HC-EPYR-1 B(L)(F)

ILLUSTF~TED PPIRTS LIST 61 -1 0’1 3 Page

Rev. 22 Jun/GO
10-28
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 113B

DESCRIPTION EFF UPA

PART
NUMBER CODE
NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 8-2256
1
420 1 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 1 A-3204
1
440 1 8-2222 PLATE, BLADE PRELOAD
INNER RING 1
450 1 8-6679
RETENTION RING, BEARING 2
460 1 A-2204
BLADE BEARING, BLADE RACE 2
490 1 A-2202-8
510 1 8-3211 BALL SPACER I 1 2

8-6144 1/2" DIAMETER STEEL BALL 50

520
.1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
-520A 8-6144-650
BLADE BEARING, HUB RACE 2
530 1 A-2202-A
2
540 1 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A
QUAD RING SEAL, BLADE, REPLACES ITEM 540 22
540AI 8-3883-4339
1 A-2413 BUSHING, BLADE -1B 1 2
565
-1B(L)F 2
565A A-2413-2 BUSHING, BLADE

R-FLANGE MOUNTING PARTS

1
320 1 C-3317-228 1 O-RING, FLANGE
6
380 1 A-2067 STUD, HUB MOUNTING
´•WASHER, HARD, STAINLESS 6
390 1 A-1381
6
400 1 A-2069 NUT, HEXAGON CASTLEATED
SPRING PIN 6
410 1 8-3842-0750

BALANCE PARTS
MS35266-( AR
-9000 8-3840-( .SCREW(AN501A10-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-3235
ITEM NOT ILLUSTRATEO
HC-EPYR-I B(L)(F)

Page 10-29

ILLUSTRATED PARTS LIST 61’1 0’1 3 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1138

FIG.IITEM I PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 B-3359 1 ELASTIC STOP NUT I I 1
20 1 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP I I 1
50 1 8-2428-1 1 CYLINDER UNIT I I 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD 1
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 1 PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID I I 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN I I 1
120 A-2420-( SPACER, HIGH PITCH STOP I I 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-4 ROD, PISTON -1(F) 1
140AI A-2418-3 ROD, PISTON -1 S(F) 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 1 C-3230-3 HUB, TVO WAY ALUMINUM -1(F) 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180A C-6559-1 HUB, TWO WAY ALUMINUM -1(F) 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
1808 C-3230-4 HUB, TWO WAY ALUMINUM -1S(F) 1
SUPERSEDED BY ITEM 180C, PRE SL HC-SL-61-179
180C C-6559-2 HUB, TWO WAY ALUMINUM -lS(F) 1
SUPERSEDES ITEM 1808, PRE SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF i
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
230 1 A-2245-1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF I I 1
SUPERSEDED BY ITEM 23DA, PRE SL HC-SL-61-179
230AI A-2245-3 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF I I 1
SUPERSEDES ITEM 230, POST SL HC-SL-61-179
240 1 A-2249 ´•´•BUSHING, GUIDE I I 1
190 8-2457-3 FORK, PITCH CHANGE I i 1
-192 lA-3323 RUBBING PLATES I 1 2
-193 1 8-3842-0500 1 SPRING PIN I 1 4
200 1 A-2217-4 BLOCK, PITCH CHANGE -1( 2
200AI A-2217-3 1 BLOCK, PITCH CHANGE -1( )F 2
210 1 A-3212 BUTTON, PITCH CHANGE BLOCK -1( 2
210AI A-3212-1 BUTTON, PITCH CHANGE BLOCK -1( )F 2
250 1 A-2431 BOLT, HEXAGON HEAD 6
260 1 A-2432 BOLT, HEXAGON HEAD I 1 4
270 1 8-3834-0632 WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING I I 10
290 1 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 1 A-2481 1 EXTENSION PLUG I I 1
310 1 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 1 A-279 LUBRICATION FITTING 4
-331 1B-6544 CAP, LUBRICATION FITTING 4

D-3292
ITEM NOT ILLUSTRATED
HC-EPYR-1 (S)(F)

ILLUSTRP~TED PARTS LIST ~1 -1 0-1 3 Rev. 22 Jun/GOPage 10-30

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER CODE
NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
1
420 1 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 1 A-3204
PLATE, BLADE PRELOAD 1
440 1 8-2222
INNER RING 1
450 1 8-6679
RETENTION RING, BEARING 2
460 1 A-2204
BLADE BEARING, BLADE RACE 2
490 1 A-2202-8
BALL SPACER 2
510 1 8-3211
1/2" DIAMETER STEEL BALL 50
520 1 8-6144
1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
-520AI 8-6144-650
BLADE BEARING, HUB RACE 2
530 A-2202-A
2
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A
QUAD RING SEAL, BLADE, REPLACES ITEM 540 2
540A 8-3883-4339
BUSHING, BLADE -1( 2
565 1 A-2413 1
-1( )F 2
565A1 A-2413-2 BUSHING, BLADE

R-FLANGE MOUNTING PARTS

O-RING, FLANGE 1
320 1 C-3317-228
STUD, HUB MOUNTING 6
380 1 A-2067
6
390 1 A-1381 ´•WASHER, HARD, STAINLESS
NUT, HEXAGON CASTLEATED 6
400 1 A-2069
1 8-3842-0750 ´•SPRINGPIN 6
410

BALANCE PARTS
.SCREW(AN501A10-( MS35266-( AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS- APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-3292
ITEM NOT ILLUSTRATED
HC-EPYR-1 (S)(F)

Page 10-31

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIG.IITEM PART I DESCRIPTION I EFF IUPA

NUMBER I NUMBER I I CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 1 ELASTICSTOPNUT I I 1
20 1 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 B-2428-1 1 CYLINDER UNIT 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD I I 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 1 PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID I I 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP I I 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-4 ROD, PISTON 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 1 C-3230-5 HUB, TWO WAY ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180A C-6559-3 .HUB, TWO WAY ALUMINUM I I 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF I I 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
230 1 A-2245-1 BUSHING, ENGINE-SIDE HUB HALF 1
SUPERSEDED BY ITEM 230A, PRE SL HC-SL-61-179
230AI A-2245-3 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
SUPERSEDES ITEM 230, POST SL HC-SL-61-179
240 1 A-2249 ´•´•BUSHING, GUIDE I I 1
-241 lA-3229 1 EXTENSIONBOLT I 1 6
-242 1 8-3834-0663 1 ´•´•EXTENSIONWASHER I 1 6
-243 1 A-2043-1 1 EXTENSION NUT I 1 6
190 1 8-2457-3 FORK, PITCH CHANGE 1
-192 1 A-3323 1 RUBBINGPLATES I 1 2
-193 1 8-3842-0500 1 SPRING PIN I 1 4
200 1 A-2217-3 BLOCK, PITCH CHANGE I 1 2
210 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK I i 2
250 1 A-2431 BOLT, HEXAGON HEAD I 1 6
260 A-2432 BOLT, HEXAGON HEAD I 1 4
270 8-3834-0632 WASHER, FLAT, STEEL 10
280 A-2043-1 NUT, SELF LOCKING 10
290 1 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 1 A-2481 EXTENSION PLUG 1
310 1 C-3317-115-1 O-RING, EXTENSION PLUG ID I I 1
330 1 A-279 LUBRICATION FITTING I 1 4
-331 8-6544 CAP, LUBRICATION FITTING I 1 4

D-3292
ITEM NOT ILLUSTRATED
HCIF2YL-1F

ILLUSTRATEO PPIRTS LIST 61 -1 0’1 3 Rev. 22 Jun/GOPage 10-32

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BLADE RETENTION PARTS

10-5-419 1 8-2256 PRELOAD PLATE ASSEMBLY I r 2

420 NUT, JAM HEXAGON 1

1 8-3368
430 1 A-3204 SET SCREW, SOCKET DRIVE 1

PLATE, BLADE PRELOAD 1

440 1 8-2222
450 1 8-6679 INNER RING 1

460 1 A-2204 RETENTION RING, BEARING 2

490 1 A-2202-B BLADE BEARING, BLADE RACE 2

510 8-3211 I ´•BALLSPACER 2

520 1 8-6144 1/2" DIAMETER STEEL BALL 50

-520A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 1 A-2202-A BLADE BEARING, HUB RACE 2

540 1 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2

540A 8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 2

565 1 A-2413-2 BUSHING, BLADE 2

L-FLANGE MOUNTING PARTS

320 1 C-3317-228 O-RING, FLANGE 1

380 1 A-2247-1 STUD, HUB MOUNTING 6

390 1 A-2482 WASHER, HARD, STAINLESS 6

400 1 A-2498 NUT, HEXAGON CASTLEATED 6

410 1 8-3842-0625 SPRING PIN 6

BALANCE PARTS
SCREW (AN501A10-( MS35266-( AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-3292
ITEM NOT ILLUSTRATED
HC-F2YL-1F

Page 10-33
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 1 ELASTICSTOPNUT 1
20 1 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2428-1 CYLINDER UNIT I I 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD 1
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 PISTON 1
100 1 C-3317-018 O-RING, PISTON ID 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1

(LENGTH TO SUIT PITCH REQUIREMENTS)

130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-4 ROD, PISTON 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 C-3230-3 HUB, TWO WAY ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180AI C-6559-1 HUB, TWO WAY ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
230 1 A-2245-1 BUSHING, ENGINE-SIDE HUB HALF 1
SUPERSEDED BY ITEM 230A, PRE SL HC-SL-61-179
230AI A-2245-3 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF I I 1
SUPERSEDES ITEM 230, POST SL HC-SL-61-179
240 1 A-2249 ´•´•BUSHING, GUIDE 1
-241 1A-3229 EXTENSION BOLT I I 6
-242 1 8-3834-0663 EXTENSION WASHER I 1 6
-243 1 A-2043-1 1 EXTENSION NUT I 1 6
190 1 8-2457-3 1 FORK, PITCH CHANGE 1
-192 1 A-3323 RUBBING PLATES 2
-193 1 8-3842-0500 1 ´•´•SPRINGPIN 4
200 1 A-2217-4 BLOCK, PITCH CHANGE -1( 2
200AI A-2217-3 BLOCK, PITCH CHANGE -1( )F 2
210 1 A-3212 BUTTON, PITCH CHANGE BLOCK -1( 2
210AI A-3212-1 BUTTON, PITCH CHANGE BLOCK -1( )F 1 2
250 1 A-2431 BOLT, HEXAGON HEAD 6
260 1 A-2432 BOLT, HEXAGON HEAD I 1 4
270 1 8-3834-0632 WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING 10
290 1 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 1 A-2481 EXTENSION PLUG I I 1
310 1 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 1 A-279 LUBRICATION FITTING 4
-331 1B-6544 CAP, LUBRICATION FITTING 4

D-3292
ITEM NOT ILLUSTRATED
HC-FSYR-1 (F)

10-34
ILLUSTRATED PARTS LIST 61 ’1 0’1 3 Rev. 22 Jun/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF IUPA

FIG.IITEM
NUMBER NUMBER CODE

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
NUT, JAM HEXAGON 1
420 1 8-3368
SET SCREW, SOCKET DRIVE 1
430 1 A-3204
PLATE, BLADE PRELOAD 1
440 1 8-2222
INNER RING 1
450 1 8-6679
RETENTION RING, BEARING 2
460 1 A-2204
BLADE BEARING, BLADE RACE 2
490 1 A-2202-8
8-3211 BALL SPACER 2
510
1/2" DIAMETER STEEL BALL 50
520 1 8-6144
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

BLADE BEARING, HUB RACE 2

530 1 A-2202-A
1 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2
540
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 2

1 A-2413 1 .BUSHING, BLADE -1( 2

565
A-241 3-2 ´•BUSHING, BLADE -1( )F 2

R-FLANGE MOUNTING PARTS

O-RING, FLANGE 1
320 1 C-3317-228
STUD, HUB MOUNTING 6
380 1 A-2067
´•WASHER, HARD, STAINLESS 6
390 1 A-1381
NUT, HEXAGON CASTLEATED 6
400 1 A-2069
SPRING PIN 6
410 1 8-3842-0750

BALANCE PARTS
SCREW(AN501A10-( MS35266-( AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-3292
ITEM NOT ILLUSTRATED
HC-FZYR-1(F)

Page 10-35

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART I DESCRIPTION I EFF IUPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 1 ELASTIC STOP NUT I I 1
20 1 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2428-1 1 CYLINDER UNIT I I 1
60 1 8-3838-3-5 1 COTTER PIN I I 1
70 1 A-2211 NUT, PISTON ROD I I 1
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 1 PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-2 ROD, PISTON I I 1
170 1 C-3317-247 ´•O-RING, CYLINDER 1
180 1 D-6531-6 HUB, TWOWAYALUMINUM I I 1
160 1 A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 1 8-2457-3 1 FORK, PITCH CHANGE 1
-192 1 A-3323 1 RUBBING PLATES I 1 2
-193 8-3842-0500 1 SPRING PIN I 1 4
200 1 A-2217-3 1 BLOCK, PITCH CHANGE 2
210 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
220 1 C-3317-115-1 1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 1 BOLT, HEXAGON HEAD 6
260 A-2432 BOLT, HEXAGON HEAD 4
270 1 8-3834-0632 WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 A-279 1 LUBRICATION FITTING I 1 4
-331 18-6544 CAP, LUBRICATION FITTING 4

D-2425
ITEM NOT ILLUSTRATED
BHC-G2YF-1 BF

ILLUSTRP~TED PIRTS LIST 61 -1 0’1 3 Rev. 22 Jun/GOPage 10-36

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
NUT, JAM HEXAGON 1
420 1 8-3368
SET SCREW, SOCKET DRIVE 1
430 1 A-3204
PLATE, BLADE PRELOAD 1
440 1 8-2222
INNER RING 1
450 1 8-6679
RETENTION RING, BEARING 2
460 1 A-2204
A-2202-8 BLADE BEARING, BLADE RACE 2
490
BALL SPACER I 1 2
510 1 8-3211
520 1 8-6144 1/2" DIAMETER STEEL BALL 50

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

A-2202-A BLADE BEARING, HUB RACE 2

530
C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2
540
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 2

565 1 A-2413 BUSHING, BLADE -18 1 2

BUSHING, BLADE -1 B(L)F 2

A-241 3-2

F-FLANGE MOUNTING PARTS

1 C-3317-228 O-RING, FLANGE 1
10-6 320
1 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6
340
A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6

WASHER, HARD, STAINLESS 6

350 1 A-1381
360 1 A-2044 SELF LOCKING NUT 6

370 1 8-6138-8-9 DOWEL PIN 2

BALANCE PARTS
SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02)

D-2425
ITEM NOT ILLUSTRATED
BHC-GPYF-1 BF

Page 10-37

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 113B

FIG.IITEM PART I DESCRIPTION I EFF IUPA

NUMBER I NUMBER I I CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 ELASTIC STOP NUT I I 1
20 1 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2428-1 CYLINDER UNIT 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PISTON ROD I 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 PISTON 1
100 1 C-3317-018 O-RING, PISTON ID 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 1 SPLIT RING, HIGH PITCH STOP RETAINER I I 1
140 1 A-2418-2 ROD, PISTON I I 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 1 D-4214-1 HUB, TWO WAY ALUMINUM BHC I 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180AI D-6554-2 1 HUB, TWO WAY ALUMINUM I BHC- 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
18081 0-4214-2 HUB, TVO WAY ALUMINUM I HC- 1
SUPERSEDED BY ITEM 180C, PRE SL HC-SL-61-179
180CI D-6554-1 HUB, TWO WAY ALUMINUM HC- I 1
SUPERSEDES ITEM 1808, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-81-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
240 1 A-2249 BUSHING, GUIDE 1
190 1 8-2457-3 FORK, PITCH CHANGE 1
-192 A-3323 1 RUBBING PLATES I 1 2
-193 1 8-3842-0500 1 SPRING PIN 4
200 1 A-2217-3 BLOCK, PITCH CHANGE 2
210 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD I 1 6
260 1 A-2432 BOLT, HEXAGON HEAD I 1 4
270 1 8-3834-0632 WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 1 LUBRICATION FITTING I 1 4
-331 1 8-6544 CAP, LUBRICATION FITTING 4

D-2425
ITEM NOT ILLUSTRATED
(B)HC-IPYF-1BF

ILLUSTRATED PARTS LIST 61 -1 0’1 3 Rev. 22 Jun/GOPage 10-38

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF IUPA

FIG./ITEM
CODE
NUMBER( NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
1
420 1 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 1 A-3204
1
440 1 8-2222 PLATE, BLADE PRELOAD
INNER RING 1
450 1 8-6679
RETENTION RING, BEARING 2
460 1 A-2204
BLADE BEARING, BLADE RACE 2
490 A-2202-8
BALL SPACER 2
510 1 8-3211
1/2" DIAMETER STEEL BALL 50
520 1 8-6144
1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
8-6144-650
BLADE BEARING, HUB RACE 2
530 1 A-2202-A
O-RING, BLADE, REPLACED BY ITEM 540A 2
540 C-3317-339
QUAD RING SEAL, BLADE, REPLACES ITEM 540 2
8-3883-4339
2
565 1 A-2413-2 BUSHING, BLADE

F-FLANGE MOUNTING PARTS

1
10-6 320 C-3317-228 O-RING, FLANGE
6
340 1 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1
6
A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1
6
350 1 A-1381 ´•WASHER, HARD, STAINLESS
SELF LOCKING NUT 6
360 1 A-2044
370 1 8-6138-8-9 DOWEL PIN 1 2

BALANCE PARTS
MS35266-( AR
-9000 8-3840-( SCREW(AN501A10-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02)

D-2425

ITEM NOT ILLUSTRATED

(B)HC-ISYF-I BF

Page 10-39

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 113B

FIG.IITEM I PART DESCRIPTION I EFF IUPA

NUMBERI NUMBER I I CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 1 ELASTICSTOPNUT 1
20 1 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2428-1 1 CYLINDER UNIT 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PISTON ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 1 PISTON I I 1
100 C-331 7-018 O-RING, PISTON ID 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN I I 1
120 A-2420-( SPACER, HIGH PITCH STOP I I 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 lA-2418-2 ROD, PISTON 1
170 lC-3317-247 O-RING, CYLINDER 1
180 lD-4214-7 HUB, TWO WAY ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180AI D-6557-1 HUB, TWO WAY ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
240 1 A-2249 ´•BUSHING, GUIDE 1
190 1 8-2457-3 FORK, PITCH CHANGE 1
-192 lA-3323 RUBBING PLATES I 1 2
-193 1 8-3842-0500 1 SPRING PIN I 1 4
200 1 A-2217-3 BLOCK, PITCH CHANGE 2
210 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD I I 6
260 1 A-2432 BOLT, HEXAGON HEAD I 1 4
270 1 8-3834-0632 WASHER, FLAT, STEEL I I 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 1 LUBRICATION FITTING I 1 4
-331 1B-6544 CAP, LUBRICATION FITTING 4

D-2425
ITEM NOT ILLUSTRATED
HC-12YR-1BF

ILLUSTF~TED PIRTS LIST 61 -1 0’1 3 Rev. 22 Jun/GOPage 10-40

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEMI PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE ASSEMBLY 2
420 8-3368 NUT, JAM HEXAGON 1
430 A-3204 SET SCREW, SOCKET DRIVE 1
440 8-2222 PLATE, BLADE PRELOAD 1
450 8-6679 INNER RING 1
460 1 A-2204 RETENTION RING, BEARING 2
490 A-2202-8 BLADE BEARING, BLADE RACE 2
510 8-3211 BALL SPACER 2
520 8-6144 1/2" DIAMETER STEEL BALL 50
-520A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 A-2202-A BLADE BEARING, HUB RACE 2
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2
540A 8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 2
565 A-2413-2 BUSHING, BLADE 2

R-FLANGE MOUNTING PARTS

320 C-331 7-228 O-RING, FLANGE 1
380 A-2067 STUD, HUB MOUNTING 6
390 A-1381 WASHER, HARD, STAINLESS 6
400 A-2069 NUT, HEXAGON CASTLEATED 6
410 1 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( SCREW(AN501A10-( MS35266-( AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-2425
ITEM NOT ILLUSTRATED
HC-IPYR-1 BF

Page 10-41
ILLVSTRATED PARTS LIST 61 -1 0-1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART I DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2428-1 CYLINDER UNIT 1
60 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PISTON ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 8-2419 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-4 ROD, PISTON 1
170 C-331 7-247 O-RING, CYLINDER 1
180 D-2484-2 HUB, TWO WAY ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180AI D-6552-2 HUB, TWO WAY ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
230 A-2245-1 BUSHING, ENGINE-SIDE HUB HALF 1
SUPERSEDED BY ITEM 230A, PRE SL HC-SL-61-179
A-2245-3 BUSHING, ENGINE-SIDE HUB HALF 1
SUPERSEDES ITEM 230, POST SL HC-SL-61-179
240 1 A-2249 BUSHING, GUIDE 1
190 1 8-2457-3 FORK, PITCH CHANGE 1
-192 A-3323 RUBBING PLATES 2
-193 1 8-3842-0500 SPRING PIN 4
200 1 A-2217-4 BLOCK, PITCH CHANGE -1B 2
A-2217-3 BLOCK, PITCH CHANGE -1BF 2
210 A-3212 BUTTON, PITCH CHANGE BLOCK -lB 2
210AI A-3212-1 BUTTON, PITCH CHANGE BLOCK -1BF 2
250 A-2431 BOLT, HEXAGON HEAD 6
260 A-2432 BOLT, HEXAGON HEAD 4
270 8-3834-0632 WASHER, FLAT, STEEL 10
280 A-2043-1 NUT, SELF LOCKING 10
290 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 A-2481 EXTENSION PLUG 1
310 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 A-279 LUBRICATION FITTING 4
-331 8-6544 CAP, LUBRICATION FITTING 4

D-2291
ITEM NOT ILLUSTRATED
BHC-JSYF-1 B(F)

ILLUSTRATED PARTS LIST 61 -1 0-1 3 Rev. 24 Apr/OlPage 10-42

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

PART DESCRIPTION EFF IUPA

FIG.IITEM
CODE
NUMBER NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
1 0-5 -419 8-2256
1
420 1 8-3368 NUT, JAM HEXAGON
1
430 1 A-3204 SET SCREW, SOCKET DRIVE
1
440 1 8-2222 PLATE, BLADE PRELOAD
INNER RING 1
450 1 8-6679
RETENTION RING, BEARING 2
460 1 A-2204
BLADE BEARING, BLADE RACE 2
490 1 A-2202-8
BALL SPACER 2
510 8-3211
1/2" DIAMETER STEEL BALL 50
520 8-6144
PIECE BOX) RF
-520A B-6144-650 1/2" DIAMETER STEEL BALL (650
BLADE BEARING, HUB RACE 2
530 1 A-2202-A
2
540 1 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A
QUAD RING SEAL, BLADE, REPLACES ITEM 540 2
540A B-3883-4339
BUSHING, BLADE -18 1 2
565 A-2413
BUSHING, BLADE -IBF 2
565A A-2413-2

F-FLANGE MOUNTING PARTS

i
10-6 320 C-3317-228 O-RING, FLANGE
6
340 1 A-2429-3 STUD, HUB MOUNTING. REFER TO NOTE 1
6
A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1
6
350 1 A-1381 WASHER, HARD, STAINLESS
SELF LOCKING NUT 6
360 1 A-2044
DOWEL PIN 2
370 8-6138-8-9

BALANCE PARTS
MS35266-( AR
-9000 8-3840-( .SCREW(AN501A10-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
P RACTICES MAN UAL 202A (61 -01 -02)

D-2291

ITEM NOT ILLUSTRATEO

BHC-JPYF-IB(F)

Page 10-43

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 1 ELASTIC STOP NUT 1
20 1 8-6747 SEAL, WASHER I I 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2428-1 1 CYLINDER UNIT 1
60 1 B-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD 1
80 1 C-3317-348-1 1 O-RING, PISTON OD 1
90 1 8-2419 1 ’PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID 1
110 lA-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH PITCH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-4 ROD, PISTON 1
170 1 C-3317-247 O-RING, CYLINDER I 1
180 1 D-2484-2 HUB, TWO WAY ALUMINUM 1
SUPERSEDED BY ITEM 1 80A, PRE SL HC-SL-61-179
180A D-6552-2 HUB, TWO WAY ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF I I 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
160A A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
230 1 A-2245-1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
SUPERSEDED BY ITEM 230A, PRE SL HC-SL-61-179
230A A-2245-3 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF I I 1
SUPERSEDED BY ITEM 230A, PRE SL HC-SLdl-179
230AI A-2245-3 BUSHING, ENGINE-SIDE HUB HALF I I 1
SUPERSEDES ITEM 230, POST SL HC-SL-61-179
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 1 8-2457-3 1 FORK, PITCH CHANGE I I 1
-192 lA-3323 ´•´•RUBBINGPLATES I 1 2
-193 18-3842-0500 SPRING PIN I 1 4
200 1 A-2217-3 BLOCK, PITCH CHANGE 2
210 lA-3212-1 BUTTON, PITCH CHANGE BLOCK 2
250 1 A-2431 BOLT, HEXAGON HEAD I I 6
260 1 A-2432 BOLT, HEXAGON HEAD 4
270 1 8-3834-0632 1 WASHER, FLAT, STEEL 6
275 1 8-3834-0663 ´•WASHER, FLAT, STEEL 4
280 1 A-2043-1 NUT, SELF LOCKING 6
285 1 8-3599 NUT, SELF-LOCKING 4
290 1 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 1 A-2481 1 EXTENSION PLUG I I 1
310 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 1 A-279 1 LUBRICATION FITTING I 1 4
-331 18-6544 CAP, LUBRICATION FITTING 4

D-2600
ITEM NOT ILLUSTRATED
BHC-J2YF-1C

ILLUSTRP;TED PPIRTS LIST 61’1 0-1 3 Rev. 22 Jun/GOPage 10-44

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF UPA

FIG.IITEM
NUMBERI NUMBER CODE

BLADE RETENTION PARTS

2
10-5 420 1 8-3368 NUT, JAM HEXAGON
430 1 A-3204-1 SET SCREW, SOCKET DRIVE 2

1 C-1934 PLATE, BLADE PRELOAD 2

440
1 A-1272 INNER RING 2
450
RETENTION RING, BEARING 2
460 1 8-1041
BLADE BEARING, BLADE RACE 2
490 C-792-8
BALL SPACER 2
510 1 8-793
520 1 8-6144-1 3/8" DIAMETER STEEL BALL 66

-520A 8-6144-1500 3/8" DIAMETER STEEL BALL (1500 PIECE BOX) RF

530 C-792-A BLADE BEARING, HUB RACE 2

540 1 8-3317-339 O-RING, BLADE 2

REPLACED BY ITEM 540A

540A 8-3317-340 O-RING,BLADE 2

REPLACES ITEM 540

565 1 A-2413-2 BUSHING, BLADE 2

F-FLANGE MOUNTING PARTS

1 C-3317-228 O-RING, FLANGE 1
10-6 320
6
340 1 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1
A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6

WASHER, HARD, STAINLESS 6

350 1 A-1381
1 A-2044 SELF LOCKING NUT 6
360
8-6138-8-9 DOWEL PIN 2
370

BALANCE PARTS
MS35266-( AR
-9000 8-3840-( SCREW(AN501A10-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE i. FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02)

P2600
ITEM NOT ILLUSTRATED
BHC-J2YF-1C

Page 10-45

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1138

FIG.IITEM I PART I DESCRIPTION I EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 1 ELASTIC STOP NUT I I 1
20 1 8-6747 SEAL, WASHER I 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP I I 1
50 1 B-2428-1 1 CYLINDER UNIT I I 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD I I 1
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 1 PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID I I 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN I I 1
120 A-2420-( SPACER, HIGH PITCH STOP I I 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER I I 1
140 1 A-2418-2 ROD, PISTON 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 1 D-2201-19 HUB, TWO WAY ALUMINUM I I 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-81-179
180AI D-6531-5 1 HUB, TWO WAY ALUMINUM I I 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-81-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
240 1 A-2249 BUSHING, GUIDE 1
190 1 8-2457-3 FORK, PITCH CHANGE 1
-192 lA-3323 1 RUBBING PLATES I 1 2
-193 1 8-3842-0500 1 SPRING PIN I 1 4
200 1 A-2217-3 BLOCK, PITCH CHANGE 2
210 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD 6
260 1 A-2432 BOLT, HEXAGON HEAD 4
270 8-3834-0632 WASHER, FLAT, STEEL 10
280 A-2043-1 NUT, SELF LOCKING 10
330 A-279 1 LUBRICATION FITTING I 1 4
-331 8-6544 1 CAP, LUBRICATION FITTING I 1 4

0-2425
ITEM NOT ILLUSTRATED
BHC-LPYF-1 BF

ILLUSTRATED P*RTS LIST 61’1 0’1 3 Rev. 22 Jun/GOPage 10-46

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBERI NUMBER CODE

BLADE RETENTION PARTS

10-5-419 1 8-2256 PRELOAD PLATE ASSEMBLY 2

420 1 8-3368 NUT, JAM HEXAGON 1

430 1 A-3204 SET SCREW, SOCKET DRIVE 1

440 1 8-2222 PLATE, BLADE PRELOAD 1

450 1 8-6679 INNER RING 1

460 1 A-2204 RETENTION RING, BEARING 2

490 1 A-2202-8 BLADE BEARING, BLADE RACE 2

510 1 8-3211 BALL SPACER 2

520 1 8-6144 1/2" DIAMETER STEEL BALL 50

-520AI 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A BLADE BEARING, HUB RACE 2

540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2

540AI 8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 2

565 1 A-2413-2 BUSHING, BLADE 2

F-FLANGE MOUNTING PARTS

10-6 320 C-3317-228 O-RING, FLANGE 1

340 1 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6

340AI A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6

350 1 A-1381 ´•WASHER, HARD, STAINLESS 6

360 1 A-2044 SELF LOCKING NUT 6

370 1 8-6138-8-9 1 ´•DOWELPIN 2

BALANCE PARTS
SCREW(AN501A10-( MS35266-( AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02)

0-2425
ITEM NOT ILLUSTRATED
BHC-L2YF-1BF

Page 10-47
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIC.IITEM PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 ELASTIC STOP NUT 1
20 1 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2428-1 CYLINDER UNIT 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 PISTON 1

100 1 C-3317-018 O-RING, PISTON ID 1

110 1 A-2213-1 SPRING,LOW PITCH RETURN 1
120 A-2420-() SPACER, HIGH PITCH STOP 1

(LENGTH TO SUIT PITCH REQUIREMENTS)

130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-2 1 ROD, PISTON 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 1 D-4214-7 HUB, TWO WAY ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-179
180AI D-6557-2 HUB, TWO WAY ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-179
160AI A-2245-2 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDES ITEM 160, POST SL HC-SL-61-179
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
SUPERSEDED BY ITEM 160A, PRE SL HC-SL-61-179
240 1 A-2249 BUSHING, GUIDE 1
190 1 8-2457-3 FORK, PITCH CHANGE 1
-192 1 A-3323 RUBBING PLATES I 1 2
-193 1 8-3842-0500 1 SPRING PIN 4

200 1 A-2217-3 BLOCK, PITCH CHANGE 2

210 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD 6
260 1 A-2432 BOLT, HEXAGON HEAD 4
270 1 8-3834-0632 ´•WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 LUBRICATION FITTING 4
-331 18-6544 CAP, LUBRICATION FITTING 4

D-2425
ITEM NOT ILLUSTRATED
HC-M2YR-1BF

Page 10-48
ILLUSTRATED PARTS LIST 61 -1 0-1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
420 1 8-3368 NUT, JAM HEXAGON 1

430 1 A-3204 SET SCREW, SOCKET DRIVE 1

440 1 8-2222 .PLATE, BLADE PRELOAD 1

450 1 8-6679 INNER RING 1

460 1 A-2204 RETENTION RING, BEARING 2

490 1 A-2202-B BLADE BEARING, BLADE RACE 2

510 1 B-3211 BALL SPACER 2

520 1 8-6144 1/2" DIAMETER STEEL BALL 50

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 1 A-2202-A BLADE BEARING, HUB RACE 2

540 1 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 2

8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 2

565 1 A-2413-2 BUSHING, BLADE 2

R-FLANGE MOUNTING PARTS

320 1 C-3317-228 ´•O-RING, FLANGE 1

380 1 A-2067 STUD, HUB MOUNTING 6

390 1 A-1381 ´•WASHER, HARD, STAINLESS 6

400 1 A-2069 NUT, HEXAGON CASTLEATED 6

410 1 8-3842-0750 1 ´•SPRINGPIN 6

BALANCE PARTS
SCREW(AN501A10-( MS35266-( AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-2425
ITEM NOT ILLUSTRATED
HC-M2YR-1BF

Page 10-49
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION I EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 ELASTIC STOP NUT I -4F I 1
10AI B-3807 ELASTIC STOP NUT I -48F I 1
30 1 8-3834-0663 WASHER I -4F I 1
8-3851-1 032 WASHER, AN960-1016L, THIN, FLAT -4BF I 1
40 1 A-4252 LOW PITCH STOP -4F I 1
40AI A-4257 LOW PITCH STOP I -48F I 1
50 1 8-2428-1 CYLINDER I -4F I 1
50AI 8-2428-2 CYLINDER I -48F I 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD 1
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 B-2419 PISTON I I 1
100 1 C-3317-018 1 O-RING, PISTON ID I I 1
120 A-2420-( SPACER, HIGH STOP I I 1

(LENGTH TO SUIT PITCH REQUIREMENTS)

130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER I I 1
140 1 A-2418-5 1 ROD, PISTON I I 1
150 1 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF I I 1
170 1 C-3317-247 1 O-RING, CYLINDER 1
180 1 D-6530-1 HUB, TVO BLADED ALUMINUM HC- I 1
180Al D-6530-2 HUB, TWO BLADED ALUMINUM BHC- I 1
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 1 C-2457-3 PITCH CHANGE FORK 1
-192 1 A-3323 1 RUBBING PLATES I 1 2

-193 1 8-3842-0500 SPRING PIN I 1 4

200 i A-2217-4 PITCH CHANGE BLOCK -4( 2
200AI A-2217-3 1 PITCH CHANGE BLOCK -4( )F 2
210 1 A-3212 BUTTON, PITCH CHANGE BLOCK -4( 2
210Ai A-3212-1 BOTTON, PITCH CHANGE BLOCK -4( )F 2
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD I 1 6
260 1 A-2432 BOLT, HEXAGON HEAD I 1 4
270 1 8-3834-0632 ´•WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 LUBRICATION FITTING 4
-331 1B-6544 CAP, LUBRICATION FITTING 4

D-2265
ITEM NOT ILLUSTRATED
(B)HC-CPYFQ(B)(F)

10-50
ILLUSTRATED PARTS LIST 61 ’1 0’1 3 Rev. 22 Jun/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

DESCRIPTION EFF UPA

FIG.IITEM PART
CODE
NUMBER NUMBER

BLADE RETENTION PARTS

2
10-5-419 8-2256 PRELOAD PLATE ASSEMBLY
1
420 8-3368 NUT, JAM HEXAGON
1
430 A-3204 SET SCREW, SOCKET DRIVE
1
440 1 8-2222 PLATE, BLADE PRELOAD
1
450 8-6679 INNER RING
RETENTION RING, BEARING 2
460 A-2204
BLADE BEARING, BLADE RACE 2
490 A-2202-8
2
510 8-3211 BALL SPACER
50
520 8-6144 1/2" DIAMETER STEEL BALL
BOX) RF
-520A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE
2
530 A-2202-A BLADE BEARING, HUB RACE
2
540 8-3883-4339 QUAD RING SEAL, BLADE
-4( 2
565 A-2413 1 BUSHING, BLADE
-4( )F 2
A-241 3-2 BUSHING, BLADE

F-FLANGE MOUNTING PARTS

1
10-6 320 C-3317-228 O-RING, FLANGE
6
340 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1
6
340A A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1
6
350 A-i 381 WASHER, HARD, STAINLESS
SELF LOCKING NUT 6
360 A-2044
2
370 1 8-6138-8-9 DOWEL PIN

BALANCE PARTS
AR
-9000 8-3840-( SCREW (AN501A10-( MS35266-(
AR
-9020 A-2424(A)-( BALANCE WEIGHT

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD~ FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02)

D-2265

ITEM NOT ILLUSTRATED

(B)HC-C2YF-4(8)(F)

Page 10-51

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 113B

FIG.IITEM I PART DESCRIPTION I EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 1 ELASTICSTOPNUT t4(F),-4A(F) 1
10AI 8-3807 1 ELASTICSTOPNUT ~B(F),-4C(F) 1
30 1 8-3834-0663 ´•WASHER t´•4(F),-4A(F) 1
30A 8-3851-1032 WASHER, AN960-1016L, THIN, FLAT ~B(F),-4C(F) 1
40 1 A-4252 LOW PITCH STOP t4(F),-4A(F) 1
40AI A-4257 LOW PITCH STOP ~B(F),-4C(F) 1
50 1 8-2428-1 1 CYLINDER t4(F),-4A(F) 1
50AI 8-2428-2 CYLINDER -(4B(F),-4C(F) 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PISTON ROD I
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 1 PISTON 1
100 1 C-3317-018 O-RING, PISTON ID 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER I I 1
140 1 A-2418-5 ROD, PISTON I I 1
150 1 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 1 D-6522-1 HUB, TWO BLADED ALUMINUM 1
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 1 C-2457-3 PITCH CHANGE FORK 1
-192 1 A-3323 1 RUBBING PLATES 2
-193 1 8-3842-0500 1 SPRING PIN 4
200 1 A-2217-4 1 PITCH CHANGE BLOCK -4( 2
A-2217-3 1 PITCH CHANGE BLOCK -4( )F 2
210 1 A-3212 BUTTON, PITCH CHANGE BLOCK -4( 2
210AI A-3212-1 BOTTON, PITCH CHANGE BLOCK -4( )F 2
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD I 1 6
260 1 A-2432 1 BOLT,HEXAGONHEAD 4
270 1 8-3834-0632 WASHER, FLAT, STEEL I I 10
280 1 A-2043-1 NUT, SELF LOCKING I I 10
330 1 A-279 LUBRICATION FITTING 4
-331 18-6544 CAP, LUBRICATION FITTING 4

D-2265
ITEM NOT ILLUSTRATED
HC-C2YK-4(A,B,C)(F)

61-10-13 Rev. 22 Jun/GOPage 10-52

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 1 B-2256 PRELOAD PLATE ASSEMBLY 2

420 1 8-3368 NUT, JAM HEXAGON 1

430 1 A-3204 SET SCREW, SOCKET DRIVE i

440 1 8-2222 PLATE, BLADE PRELOAD 1

450 1 8-6679 INNER RING 1

460 1 A-2204 RETENTION RING, BEARING 2

490 1 A-2202-B BLADE BEARING, BLADE RACE 2

510 1 8-3211 BALL SPACER I 1 2

520 1 8-6144 1/2" DIAMETER STEEL BALL 50

-520AI 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A BLADE BEARING, HUB RACE 2

540 8-3883-4339 QUAD RING SEAL, BLADE 2

565 1 A-2413 BUSHING, BLADE -4( 2

565Al A-2413-2 BUSHING, BLADE -4( )F 2

K-FLANGE MOUNTING PARTS

320 C-331 7-228 ´•O-RING, FLANGE 1

380 A-2067 STUD, HUB MOUNTING 6

390 1 A-1381 WASHER, HARD, STAINLESS 6

400 1 A-2069 NUT, HEXAGON CASTLEATED 6

410 1 8-3842-0750 SPRING PIN 6

BALANCE PARTS
SCREW (AN501A10-( MS35266-( AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-2265
ITEM NOT ILLUSTRATED
HC-CPYK-4(A,B,C)(F)

Page 10-53

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 ELASTIC STOP NUT -4(F) 1

10AI 8-3807 ELASTIC STOP NUT -4B(F) 1

30 1 8-3834-0663 WASHER -4(F) 1
8-3851-1 032 WASHER, AN960-1016L, THIN, FLAT -4B(F) 1

40 1 A-4252 1 LOWPITCHSTOP -4(F) 1

A-4257 1 LOWPITCHSTOP -4B(F) 1

50 1 B-2428-1 CYLINDER -4(F) 1

8-2428-2 CYLINDER -4B(F) 1

60 8-3838-3-5 COTTER PIN (AN380-3-5) 1

70 1 A-2211 NUT, PISTON ROD 1

80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 PISTON 1

100 1 C-3317-018 O-RING, PISTON ID 1

120 A-2420-( SPACER, HIGH STOP 1

(LENGTH TO SUIT PITCH REQUIREMENTS)

130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1

140 1 A-2418-5 1 ROD, PISTON 1

150 1 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1

170 1 C-3317-247 O-RING, CYLINDER 1

180 1 D-6522-2 HUB, TWO BLADED ALUMINUM 1

240 1 A-2249 ´•´•BUSHING, GUIDE 1

190 1 C-2457-3 PITCH CHANGE FORK 1

-192 1 A-3323 RUBBING PLATES 2

-193 1 8-3842-0500 SPRING PIN 4

200 A-2217-4 PITCH CHANGE BLOCK -4( 2

200AI A-2217-3 PITCH CHANGE BLOCK -4( )F 2

210 1 A-3212 BUTTON, PITCH CHANGE BLOCK -4( 2
210AI A-3212-1 BOTTON, PITCH CHANGE BLOCK -4( )F 2

220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1

250 1 A-2431 BOLT, HEXAGON HEAD 6
260 1 A-2432 BOLT, HEXAGON HEAD I 1 4

270 1 8-3834-0632 WASHER, FLAT, STEEL 10

280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 LUBRICATION FITTING I 1 4

-331 18-6544 CAP, LUBRICATION FITTING 4

D-2265
ITEM NOT ILLUSTRATED
HCIC2YL-4(B)(F)

Page 10-54
ILLUSTRATED PARTS LIST ~1’1 0’1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
1
420 1 8-3368 NUT, JAM HEXAGON
1 A-3204 SET SCREW, SOCKET DRIVE 1
430
1 8-2222 PLATE, BLADE PRELOAD 1
440
1 8-6679 .INNER RING 1
450
1 A-2204 RETENTION RING, BEARING 2
460
BLADE BEARING, BLADE RACE 2
490 1 A-2202-8
BALL SPACER 2
510 1 8-3211
1/2" DIAMETER STEEL BALL 50
520 1 8-6144
-520A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

A-2202-A BLADE BEARING, HUB RACE 2

530
QUAD RING SEAL, BLADE 2
540 1 8-3883-4339
565 1 A-2413 1 BUSHING, BLADE -4( 2

BUSHING, BLADE -4( )F 2

565A A-2413-2

L-FLANGE MOUNTING PARTS

1
320 1 C-3317-228 O-RING, FLANGE
6
380 1 A-2247-1 STUD, HUB MOUNTING
1 A-2482 WASHER, HARD, STAINLESS 6
390
1 A-2498 NUT, HEXAGON CASTLEATED 6
400
SPRING PIN 6
410 1 8-3842-0625

BALANCE PARTS
MS35266-( AR
-9000 8-3840-( .SCREW(AN501A10-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

0-2265
ITEM NDT ILLUSTRATED
HC-CPYL-4(8)(F)

Page 10-55

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 1 8-3359 ELASTIC STOP NUT -4F, -4AF 1
10AI 8-3807 ELASTIC STOP NUT ~4B(L)F, 4CF 1
30 1 8-3834-0663 1 WASHER -4F, -4AF 1
8-3851-1 032 WASHER, AN960-1016L, THIN, FLAT t48(L)F, 4CF 1
40 1 A-4252 1 LOW PITCH STOP -4F, -4AF 1
A-4257 LOW PITCH STOP ~4B(L)F, 4CF 1
50 1 8-2428-1 CYLINDER -4F, -4AF 1
8-2428-2 CYLINDER ~4B(L)F, 4CF 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PISTON ROD 1
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 1 B-2419 PISTON I I 1
100 1 0-3317-018 O-RING, PISTON ID 1
120 A-2420-( SPACER, HIGH STOP 1

(LENGTH TO SUIT PITCH REQUIREMENTS)

130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER I I 1
140 1 A-2418-5 ROD, PISTON 1
150 1 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
170 1 C-3317-247 ´•O-RING, CYLINDER 1
180 1 D-6522-1 HUB, TWO BLADED ALUMINUM 1
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 C-2457-3 PITCH CHANGE FORK I I 1
-192 lA-3323 RUBBING PLATES I 1 2
-193 1 8-3842-0500 1 SPRING PIN 4
200 1 A-2217-3 PITCH CHANGE BLOCK 2
210 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK I 1 2
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF I I 1
250 1 A-2431 BOLT, HEXAGON HEAD I 1 6
260 1 A-2432 BOLT, HEXAGON HEAD I 1 4
270 1 8-3834-0632 WASHER, FLAT, STEEL I I 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 1 LUBRICATION FITTING I 1 4
-331 18-6544 CAP, LUBRICATION FITTING I 1 4

D-2265
ITEM NOT ILLUSTRATED
HC-C2YR-4(A, B, C)(L)F

Page
ILLUSTRP.TED PP~RTS LIST 61 -1 0-1 3 Rev. 22 Jun/GO
10-56
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF UPA

FIG.IITEM
NUMBER CODE
NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
1
420 1 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 1 A-3204
1
440 1 8-2222 PLATE, BLADE PRELOAD
INNER RING 1
450 1 8-6679
RETENTION RING, BEARING 2
460 1 A-2204
BLADE BEARING, BLADE RACE 2
490 A-2202-8
BALL SPACER 2
510 1 8-3211
1/2" DIAMETER STEEL BALL 50
520 8-6144
.1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
-520A 8-6144-650
BLADE BEARING, HUB RACE 2
530 1 A-2202-A
2
540 1 8-3683-4339 QUAD RING SEAL, BLADE
BUSHING, BLADE 2
565 1 A-2413-2

R-FLANGE MOUNTING PARTS

1
320 C-331 7-228 ´•O-RING, FLANGE
6
380 1 A-2067 STUD, HUB MOUNTING
6
390 1 A-1381 ´•WASHER, HARD, STAINLESS
6
400 1 A-2069 NUT, HEXAGON CASTLEATED
SPRING PIN 6
410 1 8-3842-0750

BALANCE PARTS
MS35266-( AR
-9000 8-3840-( SCREW(AN501A10-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-2265
ITEM NOT ILLUSTRATED
HC-CLYR~(A,B,C)(L)F

Page 10-57

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART I DESCRIPTION EFF IUPA

NUMBER I NUMBER I I CODE

BASIC PROPELLER PARTS

10-2 10 1 8-3807 1 ELASTIC STOP NUT
30 1 B-3851-1032 WASHER I I 1
40 1 A-4257 1 LOW PITCH STOP I I 1
50 1 8-2428-2 1 CYLINDER I I 1
60 1 8-3838-3-5 1 COTTER PIN I I 1
70 1 A-2211 NUT, PITCH CHANGE ROD I I 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 1 PISTON I I 1
100 1 C-3317-018 O-RING, PISTON ID 1
120 A-2420-() SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-5 ROD, PISTON 1
150 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 1 D-6522-1 1 HUB, TWO BLADED ALUMINUM 1
240 1 A-2249 ´•´•BUSHING, GUIDE I I 1
190 1 8-6433 1 PITCH CHANGE FORK I I 1
192 1 8-3323 1 RUBBING PLATE I 1 2
193 1 8-3842-0500 1 SPRING PIN I 1 4
200 1 A-2217-3 1 PITCH CHANGE BLOCK I 1 2
210 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK 1
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD I I 6
260 1 A-2432 BOLT, HEXAGON HEAD I 1 4
270 1 8-3834-0632 WASHER, FLAT, STEEL I 1 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 1 LUBRICATION FITTING I 1 4
-3311 8-6544 1 CAP, LUBRICATION FITTING I 1 4
334 1 8-7073-L1 1 HEX HEAD BOLT 2

E-7230
ITEM NOT ILLUSTRATED
HC-C2YR14E

Page
ILLUSTRATED PARTS LIST ~1 -1 0-1 3 Rev. 22 Jun/GO
10-58
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

DESCRIPTION EFF UPA

FIG.IITEM PART
NUMBER CODE
NUMBER

BLADE RETENTION PARTS

2
1 10-5-419 8-6437 PRELOAD PLATE ASSEMBLY
1
420 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 A-3204-1
ANTIROTATION PLATE 1
433 8-6436
SPRING PIN 2
435 8-3842-0375
1
440 C-6435 PLATE, BLADE PRELOAD
SI 1616 INNER RING 1
450 A-1272
RETENTION RING, BEARING 2
460 8-1041
BLADE BEARING, BLADE RACE 2
490 C-792-8
BALL SPACER 2
510 1 8-793
3/8" DIAMETER STEEL BALL 66
520 8-6144-1
3/8" DIAMETER STEEL BALL (1500 PIECE BOX) I I RF
8-6144-1-1500
BLADE BEARING, HUB RACE 2
530 C-792-A
2
540 C-331 7-340 ´•O-RING, BLADE
PITCH CHANGE KNOB ASSEMBLY 2
545 8-6569-(
´•´•PIN. DOWEL 1
550 8-6138-5-5
1
560 C-1862-( BRACKET, PITCH CHANGE KNOB
1
565 A-241 3-2 ´•´•BUSHING, BLADE
WASHER 2
567 8-3834-0532
4
570 B-3385-5H BOLT, HEX HEAD

R-FLANGE MOUNTING PARTS

1
320 C-331 7-228 ´•O-RING, FLANGE
6
380 A-2067 STUD, HUB MOUNTING
6
390 A-1381 WASHER, HARD, STAINLESS
6
400 A-2069 NUT, HEXAGON CASTLEATED
SPRING PIN 6
410 8-3842-0750

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 1 A-1305

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

E-7230
ITEM NOT ILLUSTRATED
HC-CPYR-~E

Page 10-59
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24 Apr/Ol
 PROPELLER
HARTZELL B311LAUNAM

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3807 ELASTIC STOP NUT 1
30 8-3851-1 032 WASHER 1
40 A-4257 LOW PITCH STOP 1
50 8-2428-2 CYLINDER 1
60 8-3838-3-5 COTTER PIN 1
70 1 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 8-2419 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
120 A-2420-() SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-5 ROD, PISTON 1
150 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
170 C-331 7-247 O-RING, CYLINDER I I 1
180 1 D-6522-1 HUB, TWO BLADED ALUMINUM 1
240 1 A-2249 BUSHING, GUIDE 1
190 8-6433 PITCH CHANGE FORK 1
192 8-3323 RUBBING PLATE 1
193 8-3842-0500 SPRING PIN 2
200 A-2217-3 PITCH CHANGE BLOCK 2
210 A-3212-1 BUTTON, PITCH CHANGE BLOCK 1
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD 6
260 A-2432 BOLT, HEXAGON HEAD 4
270 8-3834-0632 WASHER, FLAT, STEEL 10
280 A-2043-1 NUT, SELF LOCKING 10
330 A-279 LUBRICATION FITTING 4
-331 8-6544 CAP, LUBRICATION FITTING 4
334 8-7073-L1 HEX BOLT 2

E-7358
ITEM NOT ILLUSTRATED
HC-CPYR-$G

ILLUSTRATES PARTS LIST 61’1 0-1 3 Rev. 22 Jun/GOPage 10-60

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

1 105-419 8-6437 PRELOAD PLATE ASSEMBLY 2
420 8-3368 NUT, JAM HEXAGON 1
430 A-3204-1 SET SCREW, SOCKET DRIVE 1
433 8-6436 ANTIROTATION PLATE 1
435 8-3842-0375 SPRING PIN I 1 2
440 C-6435 PLATE, BLADE PRELOAD 1
450 A-1272 SI 1616 INNER RING 1
460 8-1041 RETENTION RING, BEARING 2
490 C-792-8 BLADE BEARING, BLADE RACE 2
510 8-793 BALL SPACER 2
520 8-6144-1 3/8" DIAMETER STEEL BALL 66
-520A 8-6144-1-1500 3/8" DIAMETER STEEL BALL (1500 PIECE BOX) RF
530 C-792-A BLADE BEARING, HUB RACE 2
540 C-331 7-340 O-RING, BLADE 2
545 8-6569-( PITCH CHANGE KNOB ASSEMBLY I 1 2
550 8-6138-5-5 ´•´•PIN, DOWEL 1
560 C-1862-( BRACKET, PITCH CHANGE KNOB 1
565 A-2413-2 ´•´•BUSHING, BLADE 1
567 B-3834-0532 ´•WASHER 2
570 8-3385-5H BOLT, HEX HEAD 4

R-FLANGE MOUNTING PARTS

320 C-331 7-228 O-RING, FLANGE 1
380 A-2067 STUD, HUB MOUNTING 6
390 A-1381 WASHER, HARD, STAINLESS 6
400 A-2069 NUT, HEXAGON CASTLEATED 6
410 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
-9020 A-1305 BALANCE WEIGHT I IAR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

E-7358
ITEM NOT ILLUSTRATED
HC-CPYR-4G

Page 10-61
ILLUSTRATED PP~RTS LIST ~1 -1 0-1 3 Rev. 24Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIO.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-1 10 8-3359 ELASTIC STOP NUT -4F 1
10A B-3807 ELASTIC STOP NUT -4BF 1
30 8-3834-0663 WASHER -4F 1
30A 8-3851-1032 WASHER, AN960-1016L, THIN, FLAT -4BF I 1
40 A-4252 LOW PITCH STOP -4F I 1
40A A-4257 LOW PITCH STOP -4BF I 1
50 8-2428-1 CYLINDER -4F I 1
50A 8-2428-2 CYLINDER -48F I 1
60 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PISTON ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 8-2419 PISTON I I 1
100 C-3317-018 O-RING, PISTON ID 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-2418-5 ROD, PISTON 1
150 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
170 C-3317-247 O-RING, CYLINDER 1
180 D-6555-2 HUB, TWO BLADED ALUMINUM BHC- 1
180A D-6555-1 HUB, TWO BLADED ALUMINUM HC-
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 C-2457-3 PITCH CHANGE FORK 1
-192 1 A-3323 RUBBING PLATES 2
-193 8-3842-0500 SPRING PIN 4
200 A-2217-3 PITCH CHANGE BLOCK 2
210 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 6
260 A-2432 BOLT, HEXAGON HEAD 4
270 8-3834-0632 WASHER, FLAT, STEEL 10
280 1 A-2043-1 NUT, SELF LOCKING 10
330 1 A-279 LUBRICATION FITTING 4
-331 8-6544 CAP, LUBRICATION FITTING 4

D-2265
ITEM NOT ILLUSTRATED
(B)HC-ISYF-YB)F

Page
ILLVSTRATED PARTS LIST 61 -1 0-1 3 Rev. 22 Jun/GO
10-62
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART I DESCRIPTION I EFF UPA

NUMBERI NUMBER I I CODE

BLADE RETENTION PARTS

10-5-419 1 8-2256 1 PRELOAD PLATE ASSEMBLY I 1 2
420 1 8-3368 NUT, JAM HEXAGON 1
430 1 A-3204 1 SET SCREW, SOCKET DRIVE 1
440 1 8-2222 PLATE, BLADE PRELOAD I I 1
450 1 8-6679 1 INNER RING I I 1
460 1 A-2204 RETENTION RING, BEARING 2
490 1 A-2202-B BLADE BEARING, BLADE RACE 2
510 1 8-3211 1 BALL SPACER I 1 2
520 1 8-6144 1 1/2" DIAMETER STEEL BALL I f 50
-520A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 1 A-2202-A BLADE BEARING, HUB RACE 2
540 1 8-3883-4339 QUAD RING SEAL, BLADE 2
565 1 A-2413-2 BUSHING, BLADE 2

F-FLANGE MOUNTING PARTS

10-6 320 1 C-3317-228 .O-RING, FLANGE 1
320 1 C-3317-228 ´•O-RING, FLANGE 1
340 1 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6
340AI A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6
350 1 A-1381 I ´•WASHER, HARD, STAINLESS I I 6
360 1 A-2044 1 SELF LOCKING NUT 6
370 1 8-6138-8-9 1 DOWEL PIN I 1 2

BALANCE PARTS
-9000 8-3840-( ´•SCREW(AN501A10-( MS35266-( AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE i: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02)

D-2265
ITEM NOT ILLUSTRATED
(B)HC-ISYF-I(B)F

Page 10-63
61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF IUPA

FIG.IITEM
CODE
NUMBER NUMBER

BASIC PROPELLER PARTS

ELASTIC STOP NUT -4F I 1
10-1 10 1 8-3359
ELASTIC STOP NUT -4BF I 1
10AI 8-3807
8-3834-0663 ´•WASHER -4F I 1
30
8-3851-1032 WASHER, THIN, FLAT (AN960-1016L) -4BF I 1

LOW PITCH STOP -4F I 1

40 1 A-4252
LOWPITCHSTOP -48F I 1
40AI A-4257 1
´•CYLINDER -4F I 1
50 8-2428-1
CYLINDER -4BF I 1
8-2428-2
1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5)
1
70 1 A-2211 NUT, PISTON ROD
1
80 C-3317-348-1 O-RING, PISTON OD
PISTON 1
90 1 8-2419
1
100 1 C-3317-018 1 O-RING, PISTON ID
1
120 A-2420-( SPACER, HIGH STOP
(LENGTH TO SUIT PITCH REQUIREMENTS)
SPLIT RING, HIGH PITCH STOP RETAINER 1
130 1 A-867
1
140 1 A-2418-5 ROD, PISTON
1
150 1 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF
I I 1
170 1 C-3317-247 ´•O-RING, CYLINDER
HUB, TWO BLADED ALUMINUM BHC- I 1
180 1 D-6530-10
HUB, TWO BLADED ALUMINUM HC-
180A D-6530-9
1
240 A-2249 ´•´•BUSHING, GUIDE
PITCH CHANGE FORK 1
190 1 C-2457-3
´•.RUBBING PLATES 2
-192 i A-3323
´•´•SPRINGPIN 4
-193 1 8-3842-0500 1
PITCH CHANGE BLOCK 2
200 1 A-2217-3
BUTTON, PITCH CHANGE BLOCK 2
210 1 A-3212-1
O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
220 1 C-3317-115-1
6
250 1 A-2431 BOLT, HEXAGON HEAD
4
260 1 A-2432 BOLT, HEXAGON HEAD
10
270 1 8-3834-0632 ´•WASHER, FLAT, STEEL
10
280 1 A-2043-1 NUT, SELF LOCKING
LUBRICATION FITTING 4
330 1 A-279
4
-331 8-6544 CAP, LUBRICATION FITTING

D-2265
ITEM NOT ILLUSTRATED
(B)HCIL2YF14(B)F

Page 10-64
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
nARTZ ELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 2
10-5-419 1 8-2256
1
420 1 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 1 A-3204
440 8-2222 PLATE, BLADE PRELOAD 1

8-6679 1 INNER RING 1

450
RETENTION RING, BEARING 2
460 1 A-2204
BLADE BEARING, BLADE RACE 2
490 1 A-2202-8
BALL SPACER 1 2
510 1 8-3211
1/2" DIAMETER STEEL BALL 50
520 1 8-6144
1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
-520A 8-6144-650
BLADE BEARING, HUB RACE 2
530 1 A-2202-A
QUAD RING SEAL, BLADE 2
540 1 8-3883-4339
BUSHING, BLADE 2
565 1 A-2413-2

F-FLANGE MOUNTING PARTS

O-RING, FLANGE 1
10-6 320 1 C-3317-228
A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6
340
340A A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6

WASHER, HARD, STAINLESS 6

350 1 A-1381
360 1 A-2044 1 SELF LOCKING NUT 6

DOWEL PIN 2
370 1 8-6138-8-9

BALANCE PARTS
SCREW(AN501A10-( MS35266-( AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02)

D-2265
ITEM NOT ILLUSTRATED
(B)HC-L2YF-4(B)F

Page 10-65

ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART I DESCRIPTION I EFF UPA

NUMBERI NUMBER I I CODE

BASIC PROPELLER PARTS

10-2 10 1 8-3359 1 ELASTIC STOP NUT I I 1
20 1 8-6747 SEAL, WASHER I I 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2428-1 1 CYLINDER -1(L)(F)I~I
8-2281 CYLINDER -1R(L)(F) 1
60 1 8-3838-3-5 AN380-3-5 COTTER PIN I I 1
70 1 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-348-1 O-RING, PISTON OD -1(L)(F) 1
80AI C-3317-426-1 O-RING, PISTON OD -1R(L)(F) 1
90 1 8-2419 1 PISTON -1(L)(F) 1
8-2280 1 PISTON -1 R(L)(F) 1
100 1 C-3317-018 ´•O-RING, PISTON ID I I 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN I I 1
120 A-2420-( SPACER, HIGH STOP I I 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-2 ROD, PISTON I I 1
170 1 C-3317-247 ´•O-RING, CYLINDER -1(L)(F) 1
170AI C-3317-251 ´•O-RING, CYLINDER -1R(L)(F) 1
180 1 0-3251-3 HUB, THREE BLADED ALUMINUM -1(L)(F)
SUPERSEDED BY ITEM 180A. HUB REPLACEMENT REQUIRES
UPGRADE OF PROPELLER FROM -1() TO -1R( REFER TO
PARAGRAPH 5.8 IN THIS CHAPTER. I I 1
180AI D-3251-3R HUB, THREE BLADED ALUMINUM -1 R(L)(F) 1
SUPERSEDED BY ITEM 1808, PRE SL HC-SL-61-199
18081 E-7154-1R HUB, THREE BLADED ALUMINUM -1R(L)(F) 1
SUPERSEDES ITEMS 180, 180A, POST SL HC-SL-61-199
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 1 A-2249 ´•´•BUSHING, GUIDE I I 1
190 1 8-3252 1 PITCH CHANGE FORK -1(R)(F) 1
190AI 8-3252-L PITCH CHANGE FORK, LEFT TURNING I -1RL(F) 1
195 1 A-3256 NYLON BUTTON, FORK 3
200 1 A-3253-2 1 PITCH CHANGE BLOCK -1( )F 3
A-3253 1 PITCH CHANGE BLOCK -1( 3
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF I I 1
250 1 A-2431 BOLT, HEXAGON HEAD 9
260 1 A-2432 BOLT, HEXAGON HEAD 6
270 1 8-3834-0632 1 ´•WASHER, FLAT, STEEL I 1 15
280 1 A-2043-1 NUT, SELF LOCKING I 1 15
330 1 A-279 1 LUBRICATION FITTING I 1 6
-331 1 8-6544 CAP, LUBRICATION FITTING I 1 6

0-3250
ITEM NOT ILLUSTRATED
HC-C3YF-1(R)(L)(F)

ILLUSTR~TED P*RTS LIST 61 -1 0-1 3 Rev. 22 Jun/GOPage 10-66

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE ASSEMBLY 3
420 1 8-3368 NUT, JAM HEXAGON 1
430 A-3204 SET SCREW, SOCKET DRIVE 1
440 8-2222 PLATE, BLADE PRELOAD 1
450 8-6679 INNER RING 1

460 A-2204 RETENTION RING, BEARING 3

490 A-2202-8 BLADE BEARING, BLADE RACE 3
510 8-3211 BALL SPACER 3
520 1 8-6144 1/2" DIAMETER STEEL BALL 75
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 1 A-2202-A BLADE BEARING, HUB RACE 3
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3
565 A-2413 BUSHING, BLADE -1( 3
A-241 3-2 BUSHING, BLADE -1( )F 3

F-FLANGE MOUNTING PARTS

10-6 320 C-3317-228 O-RING, FLANGE 1
320 C-3317-228 O-RING, FLANGE 1
340 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6
A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6
350 1 A-1381 WASHER, HARD, STAINLESS 6
360 i A-2044 SELF LOCKING NUT 6
370 8-6138-8-9 DOWEL PIN 2

BALANCE PARTS
-9000 8-3840-( SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE i: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

D-3250
ITEM NOT ILLUSTRATED
HC-C3YF-1(R)(L)(F)

Page 10-67
ILLUSTRATED PARTS LIST 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-3 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 3/8" STAT O SEAL 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 C-6510 CYLINDER 1
60 8-3838-3-5 AN380-3-5 CO7TER PIN I I 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-6511 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 8-6509-1 SPRING, LOW PITCH RETURN 1
110AI 8-6509 SPRING, LOW PITCH RETURN (ALTERNATE) 1
120 8-6515-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 C-6512 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 1 D-3251-8R HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180A/ E-7154-2R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 i A-2249 BUSHING, GUIDE 1
190 1 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 1 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-332 8-6544 CAP, LUBRICATION FITTING 6

E-6921
ITEM NOT ILLUSTRATED
PHC-CSYF-~MF

ILLUSTRATED PPIRTS LIST 61 -1 0-1 3 Rev. 22 Jun/GOPage 10-68

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBERI NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE UNIT 3
420 8-3368 NUT, JAM HEXAGON 1
430 A-3204 SET SCREW, SOCKET DRIVE 1
440 8-2222 PLATE, BLADE PRELOAD 1
450 1 8-6679 INNER RING 1
460 1 A-2204 RETENTION RING, BEARING 3
490 1 A-2202-8 BLADE BEARING, BLADE RACE 3
510 A-3211 BALL SPACER 3
520 A-6144 1/2" DIAMETER STEEL BALL 75
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 A-2202-A BLADE BEARING, HUB RACE 3
540 8-3883-4339 QUAD RING SEAL, BLADE 3
565 A-241 3-2 ´•BUSHING, BLADE 3

F-FLANGE MOUNTING PARTS

1006 320 C-3317-228 O-RING, FLANGE 1
340 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6
A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6
350 A-1381 WASHER, HARD, STAINLESS 6
360 A-2044 SELF LOCKING NUT 6
370 8-6138-8-9 DOWEL PIN 2

BALANCE PARTS
-9000 8-3840-( SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

E-6921
ITEM NOT ILLUSTRATED
PHC-C3YFI1MF

Page 10-69
ILLUSTRATED PARTS LIST ~1’1 0’1 3 Rev. 24Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2281 CYLINDER 1
60 8-3838-3-5 AN380-3-5 COTTER PIN 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-2 ROD, PISTON 1
170 C-3317-251 O-RING, CYLINDER 1
180 D-3251-8R HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7154-2R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK -1( )F 3
A-3253 PITCH CHANGE BLOCK -1( 3
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

0-3250
ITEM NOT ILLUSTRATED
PHC-C3YF-1R(F)

ILLUSTRP~TED PPIRTS LIST 61 -1 0-1 3 Rev. 22 Jun/GOPage 10-70

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BLADE RETENTION PARTS

10-5 -419 8-2256 PRELOAD PLATE ASSEMBLY 3
420 8-3368 NUT, JAM HEXAGON 1
430 A-3204 SET SCREW, SOCKET DRIVE 1
440 8-2222 PLATE, BLADE PRELOAD 1
450 8-6679 INNER RING 1
460 A-2204 RETENTION RING, BEARING 3
490 1 A-2202-8 BLADE BEARING, BLADE RACE 3
510 1 8-3211 BALL SPACER 3
520 1 8-6144 1/2" DIAMETER STEEL BALL 75
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 A-2202-A BLADE BEARING, HUB RACE 3
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3
565 A-2413 BUSHING, BLADE -1( 3
A-241 3-2 BUSHING, BLADE -1( )F 3

F-FLANGE MOUNTING PARTS

10-6 320 C-3317-223 O-RING, FLANGE 1
340 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6
A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6
350 A-1381 WASHER, HARD, STAINLESS 6
360 A-2044 SELF LOCKING NUT 6
370 8-6138-8-9 DOWEL PIN 2

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

D-3250
ITEM NOT ILLUSTRATED
PHC-C3YF-1R(F)

Page 10-71
ILLUSTRATED PARTS LIST 61-10-13
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2428-1 CYLINDER 1
60 1 8-3838-3-5 AN380-3-5 COTTER PIN i
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 8-2419 PISTON 1
100 1 C-3317-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-2 ROD, PISTON 1
170 C-3317-247 O-RING, CYLINDER 1
180 D-3276-1 HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7152-1 HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK -1( )F 3
A-3253 PITCH CHANGE BLOCK -1( 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 1 A-2432 BOLT, HEXAGON HEAD 6
270 1 8-3834-0632 WASHER, FLAT, STEEL 15
280 1 A-2043-1 NUT, SELF LOCKING 15
330 1 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

D-3250
ITEM NOT ILLUSTRATED
HC-C3YN-1(F)

ILLUSTRATED P~RTS LIST 61-10’13 Rev. 22 Jun/GOPage 10-72

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE ASSEMBLY 3

420 1 8-3368 NUT, JAM HEXAGON 1

430 A-3204 SET SCREW, SOCKET DRIVE 1

440 8-2222 PLATE, BLADE PRELOAD 1

450 8-6679 INNER RING 1

460 1 A-2204 RETENTION RING, BEARING 3

490 1 A-2202-8 BLADE BEARING, BLADE RACE 3

510 i 8-3211 BALL SPACER 3

520 8-6144 1/2" DIAMETER STEEL BALL 75

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A BLADE BEARING, HUB RACE 3

540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3

8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3

565 A-2413 BUSHING, BLADE 3

A-2413-2 BUSHING, BLADE -1( )F 3

N-FLANGE MOUNTING PARTS

10-7 320 C-3317-228 O-RING, FLANGE 1

340 A-3254 HUB MOUNTING STUD 8

350 A-2048-2 WASHER, HARD, STAINLESS 8

360 A-3257 SELF LOCKING NUT 8

370 8-6138-8-8 DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-3250
ITEM NOT ILLUSTRATED
HC-CSYN-1 (F)

Page 10-73
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24Apr/Ol
 PROPELLER
HARTZELL MI:N:3EBNANCE
8311LAUNAM

FIG.IITEM I PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2281 CYLINDER 1
60 8-3838-3-5 AN380-3-5 COTTER PIN 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 1 C-3317-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-2 ROD, PISTON 1
170 C-3317-251 O-RING, CYLINDER 1
180 D-3251-1R HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7157-1R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 BUSHING, GUIDE 1
190 8-3252-2 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

D-6233
ITEM NOT ILLUSTRATED
HC-C3YR-1 A

IILVSTRP~TED PARTS LIST 61’1 0’1 3 Rev. 22 Jun/GOPage 10-74

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5 420 8-3368 NUT, JAM HEXAGON 3

430 A-3204-1 SET SCREW, SOCKET DRIVE 3

440 1 8-1924 PLATE, BLADE PRELOAD 3

450 A-1272 INNER RING 3

460 A-1041 RETENTION RING, BEARING 3

490 C-792-B BLADE BEARING, BLADE RACE 3

510 1 8-793 BALL SPACER 3

520 790100012 3/8" DIAMETER STEEL BALL 99

SUPERSEDED BY ITEM 520A
8-6144-1 3/8" DIAMETER STEEL BALL 99
SUPERSEDES ITEM 520
8-6144-1500 3/8" DIAMETER STEEL BALL (1500 PIECE BOX) RF

530 C-792-A BLADE BEARING, HUB RACE 3

540 C-3317-339-3 O-RING, BLADE 3

REPLACED BY ITEM 540A
C-3317-340 O-RING, BLADE 3
REPLACES ITEM 540
PITCH CHANGE KNOB ASSEMBLY 3
545 8-6569-(
550 790960755 NAS 607-5-5 DOWEL PIN 1
SUPERSEDED BY ITEM 550A
NAS 607-5-5 DOWEL PIN 1

(V24692) 8-6138-5-5
PITCH CHANGE KNOB BRACKET 1
560 C-1862-(
565 A-241 3-2 ´•´•BUSHING, BLADE 1

570 8-3830 BOLT, PITCH CHANGE KNOB 6

R-FLANGE MOUNTING PARTS

320 C-331 7-228 ´•O-RING, FLANGE 1

380 A-2067 STUD, HUB MOUNTING 6

390 A-1381 WASHER, HARD, STAINLESS 6

400 A-2069 NUT, HEXAGON CASTLEATED 6

410 8-3842-0750 SPRING PIN 6

BALANCE PARTS
SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

0-6233
ITEM NOT ILLUSTRATED
HC-C3YR-1 A

Page 10-75
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 113B

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-3 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 3/8" STAT O SEAL 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 C-6510 CYLINDER 1
60 8-3838-3-5 AN380-3-5 CO’ITER PIN 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 1 8-6511 PISTON 1
100 1 C-3317-018 O-RING, PISTON ID 1
110 8-6509 SPRING, LOW PITCH RETURN 1
120 8-6515-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 C-6512 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 D-3251-1R HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7157-1R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 1 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 ´•WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

E-6B51
ITEM NOT ILLUSTRATED
HC-C3YR-1MF

ILLUSTRATEO PARTS LIST 61-10-13 Rev. 22 Jun/GOPage 10-76

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE UNIT 3
420 8-3368 NUT, JAM HEXAGON 1

430 1 A-3204 SET SCREW, SOCKET DRIVE 1

440 1 8-2222 PLATE, BLADE PRELOAD 1
450 8-6679 INNER RING 1
460 A-2204 RETENTION RING, BEARING 3
490 A-2202-8 BLADE BEARING, BLADE RACE 3
510 A-3211 BALL SPACER 3

520 A-6144 1/2" DIAMETER STEEL BALL 75

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 A-2202-A BLADE BEARING, HUB RACE 3
540 8-3883-4339 QUAD RING SEAL, BLADE 3
565 A-241 3-2 BUSHING, BLADE 3

R-FLANGE MOUNTING PARTS

320 C-331 7-228 O-RING, FLANGE 1
380 A-2067 STUD, HUB MOUNTING 6
390 A-1381 WASHER, HARD, STAINLESS 6
400 A-2069 NUT, HEXAGON CASTLEATED 6
410 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

E-6851
ITEM NOT ILLUSTRATED
HC-C3YRI1MF

Page 10-77
ILLUSTRATED PARTS LIST 61-10-13
 PRdPELLER
HARTZELL MA:N~ANCE
B311LAVNAM

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2428-1 CYLINDER -1(L)(F) 1
8-2281 CYLINDER -1R~L)(F) 1
60 8-3838-3-5 AN380-3-5 COTTER PIN I I 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-348-1 O-RING, PISTON OD -I(L)(F) 1
C-3317-426-1 O-RING, PISTON OD -1R(L)(F) 1
90 1 8-2419 PISTON -I(L)(F) 1
8-2280 PISTON -1 R(L)(F) 1
100 C-331 7-018 O-RING, PISTON ID I I 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-2 1 ’ROD, PISTON 1
170 C-331 7-247 O-RING, CYLINDER -1(L)(F) 1
1 C-331 7-251 O-RING, CYLINDER -1R(L)(F) 1
180 D-3251-1 HUB, THREE BLADED ALUMINUM -1(L)(F) 1
SUPERSEDED BY ITEM 180A. HUB REPLACEMENT REQUIRES
UPGRADE OF PROPELLER FROM -1()TO -1R( REFER TO
PARAGRAPH 5.8 IN THIS CHAPTER.
180AI D-3251-1R HUB, THREE BLADED ALUMINUM -1R(L)(F) 1
SUPERSEDED BY ITEM 1808, PRE SL HC-SL-61-199
180BI E-7157-1R HUB, THREE BLADED ALUMINUM -1R(L)(F) 1
SUPERSEDES ITEM 180A, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK -1(R)(F) 1
190AI B-3252-L PITCH CHANGE FORK, LEFT TURNING -1 RL(F) 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK -1( )F 3
A-3253 PITCH CHANGE BLOCK -1( 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 1 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

ITEM NOT ILLUSTRATED D-3250

HC-C3YR-1(R)(L)(F)

ILLUSTRATED PARTS LIST 61 -1 0-1 3 Rev. 24 Apr/OlPage 10-78

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

DESCRIPTION EFF IUPA

FIG.IITEM PART
CODE
NUMBER NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 3
10-5 -419 8-2256
1
420 i 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 A-3204
1
440 8-2222 PLATE, BLADE PRELOAD
INNER RING 1
450 8-6679
RETENTION RING, BEARING 3
460 A-2204
BLADE BEARING, BLADE RACE 3
490 A-2202-8
BALL SPACER 3
510 8-3211
1/2" DIAMETER STEEL BALL 75
520 8-6144
1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
8-6144-650
BLADE BEARING, HUB RACE 3
530 A-2202-A
3
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A
QUAD RING SEAL, BLADE, REPLACES ITEM 540 3
8-3883-4339
-1( 3
565 A-2413 BUSHING, BLADE
-1( )F 3
A-241 3-2 BUSHING, BLADE

R-PLANGE MOUNTING PARTS

1
320 C-331 7-228 O-RING, FLANGE
6
380 A-2067 STUD, HUB MOUNTING
6
390 A-1381 WASHER, HARD, STAINLESS
6
400 1 A-2069 NUT, HEXAGON CASTLEATED
SPRING PIN 6
410 8-3842-0750

BALANCE PARTS
SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

D-3250
ITEM NOT ILLUSTRATED
HC-CBYR-1(R)(L)(F)

Page 10-79
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24 Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2281 CYLINDER 1
60 8-3838-3-5 1 AN380-3-5 COTTER PIN 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-3 ROD, PISTON 1
170 1 C-3317-251 O-RING, CYLINDER 1
180 1 D-3261-3 HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7161-1R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
230 1 A-2245-1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK -1RF I 1
190AI 8-3252L PITCH CHANGE FORK, LEFT TURNING -1RLF I 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK -1( )F 3
A-3253 PITCH CHANGE BLOCK -1( 3
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
290 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 A-2481 EXTENSION PLUG 1
310 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

D-4245
ITEM NOT ILLUSTRATED
HC-E3YR-1 R(L)F

ILLUSTRATED PARTS LIST 61 -1 0-1 3 Rev. 22 Jun/GOPage 10-80

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEMI PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE ASSEMBLY 3
420 8-3368 NUT, JAM HEXAGON 1
430 A-3204 SET SCREW, SOCKET DRIVE 1
440 8-2222 PLATE, BLADE PRELOAD 1
450 8-6679 INNER RING 1
460 1 A-2204 RETENTION RING, BEARING 3
490 A-2202-8 BLADE BEARING, BLADE RACE 3
510 8-3211 BALL SPACER I 1 3
520 8-6144 1/2" DIAMETER STEEL BALL 75
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 A-2202-A BLADE BEARING, HUB RACE 3
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3
565 A-241 3-2 BUSHING, BLADE 3

R-FLANGE MOUNTING PARTS

320 C-331 7-228 O-RING, FLANGE 1
380 A-2067 STUD, HUB MOUNTING 6
390 A-1381 WASHER, HARD, STAINLESS 6
400 A-2069 NUT, HEXAGON CASTLEATED 6
410 8-3842-0750 SPRING PIN I 1 6

BALANCE PARTS
-9000 8-3840-( ´•SCREW I I AR
-9020 A-2424(A)-( BALANCE WEIGHT I I AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-4245
ITEM NOT ILLUSTRATED
HC-EBYR-l R(L)F

Page 10-81
ILLVSTRATED PARTS LIST 61 -1 0-1 3 Rev. 24Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART I DESCRIPTION EFF IUPA

NUMBER NUMBER I I CODE

BASIC PROPELLER PARTS

10-2 10 1 8-3359 ELASTIC STOP NUT i
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2281 1 CYLINDER I I 1
60 8-3838-3-5 1 COTTER PIN I I 1
70 A-2211 NUT, PITCH CHANGE ROD I I 1
80 C-3317-426-1 O-RING, PISTON OD I I 1
90 8-2280 PISTON I I 1
100 C-331 7-018 O-RING, PISTON ID I I 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP I I 1

(LENGTH TO SUIT PITCH REQUIREMENTS)

130 1 A-867 1 SPLIT RING, HIGH PITCH STOP RETAINER I I 1
140 1 A-2418-4 1 ROD, PISTON I I 1
170 C-331 7-251 O-RING, CYLINDER 1
180 E-7161-2R HUB, THREE BLADED ALUMINUM 1
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
230 A-2245-1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HAL.F 1
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252 1 PITCH CHANGE FORK I I 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK I 1 3
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6

(WHEN USING SPINNER MOUNTING KIT, REPLACE BOLTS [250] WITH

BOLTS IN KIT, IF APPLICABLE. REFER TO HARTZELL APPLICATION
GUIDE MANUAL 159 [61-02-59].)
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
290 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 A-2481 EXTENSION PLUG 1
A-2481-3 EXTENSION PLUG, OPTIONAL I I 1
310 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 A-279 LUBRICATION FITTING 6
-331 1 8-6544 CAP, LUBRICATION FITTING 6

D-4520
ITEM NOT ILLUSTRATED
HC-F3YR-1ARF

PARTS LIST ~1 -1 0’1 3 Page 10-81.1

Rev. 23 Dec/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-4-419 8-2256 PRELOAD PLATE ASSEMBLY 3

420 1 B-3368 NUT, JAM HEXAGON 1

430 1 A-3204 SET SCREW, SOCKET DRIVE 1

440 1 8-2222 PLATE, BLADE PRELOAD 1

450 1 8-6679 INNER RING 1

460 1 A-2204 RETENTION RING, BEARING 3

490 1 A-2202-8 BLADE BEARING, BLADE RACE 3

510 1 8-3211 BALL SPACER I 1 3

520 1 8-6144 1/2" DIAMETER STEEL BALL 75

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 1 A-2202-A BLADE BEARING, HUB RACE 3

540 1 8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3

565 1 A-2413-2 BUSHING, BLADE 3

R-FLANGE MOUNTING PARTS

320 1 C-3317-228 ´•O-RING, FLANGE 1

380 1 A-2067 STUD, HUB MOUNTING 6

390 1 A-1381 ´•WASHER, HARD, STAINLESS 6

400 1 A-2069 NUT, HEXAGON CASTLEATED 6

410 1 8-3842-0750 1 ´•SPRINGPIN 6

BALANCE PARTS
SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-4520
ITEM NOT ILLUSTRATED
HC-F3YR-1ARF

Page 10-81.2
ILLUSTRATED PARTS LIST 61-10-13 Rev. 23 Dec/GO
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 1138

FIOJITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 83359 ELASTIC STOP NUT 1

20 &6747 ´•SEAL; WASHER 1

40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1

50 &2281 ´•CYLINDER 1

60 8-3838-3-5 AN380-3-5 COTTER PIN 1

70 A-2211 NUT, PITCH CHANGE ROD 1

80 C-3317-426-1 O-RING, PISTON OD 1

90 8-2280 PISTON 1

100 C-331 7-018 ´•O-RING, PISTON ID 1

110 A-2213-1 SPRING, LOW PITCH RETURN 1

120 A-2420-( SPACER, HIGH STOP 1

(LENGTH TO SUIT PITCH REQUIREMENTS)

130 A-867 SPLIT RING, HIGH PITCH STOPRETAINER I I 1

140 A-241 8-4 ROD, PISTON I I 1

170 C-3317-251 ´•O-RING, CYLINDER 1

180 C-3327 HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7160-1R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HGSL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
230 A-2245-1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HAL.F 1

240 A-2249 ´•´•BUSHING, GUIDE 1

-241 A-3229 EXTENSION BOLT 6

-242 8-3834-0663 EXTENSION WASHER 6
-243 A-2043-1 EXTENSION NUT I I 6
190 8-3252 PITCH CHANGE FORK i I 1

195 A-3256 NYLON BUTTON, FORK 3

200 A-3253-2 PITCH CHANGE BLOCK 3
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834~0632 ´•WASHER, FLAT, STEEL 15
280 1 A-2043-1 NUT, SELF LOCKING 15
290 C-3317-226 O-RING, EXTENSION PLUG OD 1

300 A-2481 EXTENSION PLUG 1

A-2481-3 EXTENSION PLUG, OPTIONAL 1

310 1 C-3317-115-1 O-RING, EXTENSION PLUG ID 1

320 C-331 7-228 ´•O-RING, FLANGE 1

330 A-279 LUBRICATION FITTING 6

-331 8-6544 CAP, LUBRICATION FITTING I 6

D4520
ITEM NOT ILLUSTRATED
HCIF3YRI1 RF

ILLVSTAATED PARTS LIST 61’1 0’13 Rev. 24

10-82
Apr/OlPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF UPA

FIG.IITEM
NUMBER NUMBER CODE

BLADE RETENTION PARTS

8-2256 PRELOAD PLATE ASSEMBLY 3
10-5-419
NUT, JAM HEXAGON 1
420 1 8-3368
SET SCREW, SOCKET DRIVE 1
430 A-3204
8-2222 PLATE, BLADE PRELOAD 1
440
8-6679 INNER RING 1
450
460 A-2204 RETENTION RING, BEARING 3

490 A-2202-8 BLADE BEARING, BLADE RACE 3

510 8-3211 BALL SPACER 3

1/2" DIAMETER STEEL BALL 75
520 1 8-6144
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

A-2202-A BLADE BEARING, HUB RACE 3

530
C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3
540
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3

565 1 A-2413-2 BUSHING, BLADE 3

R-FLANGE MOUNTING PARTS

320 C-331 7-228 O-RING, FLANGE 1

A-2067 STUD, HUB MOUNTING 6

380
390 A-1381 WASHER, HARD, STAINLESS 6

400 A-2069 NUT, HEXAGON CASTLEATED 6

410 8-3842-0750 SPRING PIN 6

BALANCE PARTS
SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-4520
ITEM NOT ILLUSTRATED
HC-F3YR-1RF

Page 10-83
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 C-6510 CYLINDER 1
60 8-3838-3-5 COTTER PIN 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-6511 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 8-6509-1 SPRING, LOW PITCH RETURN 1
120 8-6515-4 SPACER, HIGH STOP 1
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 C-6512 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 D-3251-15 HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7154-5R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252-2 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 1 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6
334 8-7051-57 SET SCREW 3
335 1 8-3808-3 SELF LOCKING HEX NUT 3
336 1 8-3839-3 HEX NUT 3

E-7334
ITEM NOT ILLUSTRATED
PHC-G3YF-1E

ILLVSTRATED PARTS LIST 61’1 0’1 3 Rev. 22 Jun/GOPage 10-84

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 lC-7242 PRELOAD PLATE ASSEMBLY 3

420 18-3368 NUT, JAM HEXAGON 1

430 A-3204-1 SET SCREW, SOCKET DRIVE 1

440 8-1924 PLATE, BLADE PRELOAD 1

450 A-1272 INNER RING 1

460 A-1041 RETENTION RING, BEARING 3

490 C-792-8 BLADE BEARING, BLADE RACE 3

510 18-793 BALL SPACER 3

520 18-6144-1 3/8" DIAMETER STEEL BALL 99

-520A 8-6144-1500 3/8" DIAMETER STEEL BALL (1500 PIECE BOX) RF

530 C-792-A BLADE BEARING, HUB RACE 3

540 C-331 7-340 O-RING, BLADE 3
PITCH CHANGE KNOB ASSEMBLY 3
545 8-6569-(
550 8-6138-5-5 DOWEL PIN 1

560 C-1862-( PITCH CHANGE KNOB BRACKET 1

565 A-241 3-2 ´•´•BUSHING, BLADE 1

570 8-3830 BOLT, PITCH CHANGE KNOB 6

F-FLANGE MOUNTING PARTS

10-6 320 C-3317-228 O-RING, FLANGE 1

340 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6

340A A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6

350 A-1381 WASHER, HARD, STAINLESS 6

360 A-2044 SELF LOCKING NUT 6

370 18-6138-8-9 DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

E-7334
ITEM NOT ILLUSTRATED
PHC-G3YF-1E

Page 10-85
ILLUSTRATED PARTS LIST 61-10-13 Apr/Ol
Rev. 24
 PROPELLER
HARTZELL MI\~3EsNANCE
8311LAUNAM

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 1 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2281 .CYLINDER 1
60 8-3838-3-5 AN380-3-5 COTTER PIN 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 1 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-2418-2 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 1 0-3251-15 HUB, THREE BLADED ALUMINUM PHC- I 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SLB~-199
180AI E-7154-5R HUB, THREE BLADED ALUMINUM PHC- I 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
18081 D-3251-11R HUB, THREE BLADED ALUMINUM HC- 1
SUPERSEDED BY ITEM 180C, PRE SL HC-SL-61-199
180CI E-7154-4R HUB, THREE BLADED ALUMINUM HC- 1
SUPERSEDES ITEM 1808, POST SL HC-SL-61-199
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 1 A-279 LUBRICATION FITTING 6
-331 18-6544 CAP, LUBRICATION FITTING 6

D-3250
ITEM NOT ILLUSTRATED
(P)HC-G3YF-1RF

ILLUSTRATED PARTS LIST ~1 -1 0-1 3 Rev. 22 Jun/GOPage 10-86

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF UPA

FIG./ITEM
NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE ASSEMBLY 3

420 8-3368 NUT, JAM HEXAGON 1

430 1 A-3204 SET SCREW, SOCKET DRIVE 1

440 8-2222 PLATE, BLADE PRELOAD 1

450 8-6679 INNER RING 1

460 A-2204 RETENTION RING, BEARING 3

490 A-2202-8 BLADE BEARING, BLADE RACE 3

510 8-3211 BALL SPACER 3

520 8-6144 1/2" DIAMETER STEEL BALL 75

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A BLADE BEARING, HUB RACE 3

540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3

8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3

565 A-2413-2 BUSHING, BLADE 3

F-FLANGE MOUNTING PARTS

C-3317-226 O-RING, FLANGE 1
10-6 320
340 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6

A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6

350 A-1 381 WASHER, HARD, STAINLESS 6

360 A-2044 SELF LOCKING NUT 6

370 8-6138-8-9 DOWEL PIN 2

BALANCE PARTS
SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE i: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

D-3250
ITEM NOT ILLUSTRATED
(P)HC~G3YF-1RF

Page 10-87
ILLUSTRATED PARTS LIST 61-10-13 Apr/Ol
Rev. 24
 PROPELLER
HARTZELL MA~INANCE
8311L*UN~PM

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2281 CYLINDER 1
60 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-6 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 0-3285-11 HUB, THREE BLADED ALUMINUM HC- 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-B1-199
180AI E-7156-1R HUB, THREE BLADED ALUMINUM HC- I 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
18081 D-3285-13 HUB, THREE BLADED ALUMINUM PHC- 1
SUPERSEDED BY ITEM 180C, PRE SL HC-SLB~-199
180CI E-7156-5R HUB, THREE BLADED ALUMINUM PHC- 1
SUPERSEDES ITEM 1808, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
230 A-2245-1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
290 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 A-2481 EXTENSION PLUG 1
310 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 A-279 LUBRICATION FITTING 6
-331 1 8-6544 CAP, LUBRICATION FITTING 6

ITEM NOT ILLUSTRATED D-4245

(P)HC-H3YF-1RF

ILLVSTRATED PARTS LIST 61-10-1 3 Rev. 22 Jun/GOPage 10-88

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF UPA

FIG.IITEM
NUMBER NUMBER CODE

BLADE RETENTION PARTS

8-2256 PRELOAD PLATE ASSEMBLY 3
10-5-419
NUT, JAM HEXAGON 1
420 1 8-3368
SET SCREW, SOCKET DRIVE 1
430 1 A-3204
8-2222 PLATE, BLADE PRELOAD 1
440
INNER RING 1
450 8-6679
460 A-2204 RETENTION RING, BEARING 3

A-2202-8 BLADE BEARING, BLADE RACE 3

490
510 8-3211 BALL SPACER 3

8-6144 1/2" DIAMETER STEEL BALL 75

520
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A BLADE BEARING, HUB RACE 3

C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3

540
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3

565 A-241 3-2 BUSHING, BLADE 3

F-FLANGE MOUNTING PARTS

C-3317-228 O-RING, FLANGE 1
10-6 320
A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6
340
A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6

A-i 381 WASHER, HARD, STAINLESS 6

350
360 A-2044 SELF LOCKING NUT 6

8-6138-8-9 DOWEL PIN 2

370

BALANCE PARTS
´•SCREW AR
-9000 8-3340-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

NOTE i: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

D-4245
ITEM NOT ILLUSIRATED
(P)HC-HBYF-1RF

Page 10-89

ILLUSTRATED PARTS LIST 61-10-13 Rev. 24 Apr/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 1 B-6747 SEAL, WASHER 1
40 1 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 C-6510 CYLINDER 1
60 1 B-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 1 C-3317-426-1 O-RING, PISTON OD 1
90 1 8-6511 PISTON 1
100 C-331 7-018-1 O-RING, PISTON ID 1
110 8-6509-1 SPRING, LOW PITCH RETURN 1
llOAI 8-6509 SPRING, LOW PITCH RETURN 1
120 8-6515-4 SPACER, HIGH STOP 1
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 C-6512 ROD, PISTON 1
170 C-331 7-251-1 O-RING, CYLINDER 1
180 D-2841 HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-B1-199
180AI E-7159-1R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 ´•´•BUSHING, GUIDE
190 8-3252-2 FORK, PITCH CHANGE 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
270 8-3834-0632 WASHER, FLAT, STEEL, THIN 15
275 B-3834-0663 WASHER, FLAT, STEEL, THICK 6
276 B-6265 BRACKET, WIRE HARNESS 3
280 A-2043-1 NUT, SELF LOCKING 12
281 B-3599 NUT, FLEXLOCK 3
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6
334 8-3840-20 SCREW (REPLACED BY ITEM 334A) 3
8-7051-57 CUP POINT SET SCREW (REPLACES ITEM 334) 3
335 B-3808-3 NUT, SELF LOCKING 3
336 8-3839-3 NUT (NAS1423-3) 3

E-6749
ITEM NOT ILLUSTRATED
HC-ISYR-1 E

ILLUSTRATED PARTS LIST 61’1 0’1 3 Rev. 22 Jun/GOPage 10-90

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 C-7242 PRELOAD PLATE ASSEMBLY 3

420 8-3368 NUT, JAM HEXAGON 1

430 A-3204-1 SET SCREW, SOCKET DRIVE 1

440 C-1924 PLATE, BLADE PRELOAD 1

450 A-1272 SI 1616 INNER RING 1

460 8-1041 RETENTION RING, BEARING 3

480 A-665 PLUG, BLADE 3

485 A-1271 BEARING, NEEDLE ROLLER 3

490 C-792-8 BLADE BEARING, BLADE RACE 3

510 8-793 BALL SPACER 3

520 1 8-6144-1 3/8" DIAMETER STEEL BALL 99

8-6144-1500 3/8" DIAMETER STEEL BALL (1500 PIECE BOX) RF

530 C-792-A BLADE BEARING, HUB RACE 3

540 C-331 7-339 O-RING, BLADE 3

REPLACED BY ITEM 540A
C-3317-340 ´•O-RING, BLADE 3
REPLACES ITEM 540
PITCH CHANGE KNOB ASSEMBLY 3
545 8-6569(
550 NAS6075-5 ´•´•PIN. DOWEL 1

(V24692) 8-6138-5-5
BRACKET, PITCH CHANGE KNOB 1
560 C-1862-(
565 A-2413-2 ´•´•BUSHING, BLADE 1

570 1 8-3830 BOLT, TWELVE POINT 6

580 582627-1 DE-ICE KIT (OAJJO) 1

R-FLANGE MOUNTING PARTS

320 C-331 7-228 O-RING, FLANGE 1

380 A-2067 STUD, HUB MOUNTING 6

390 A-1381 ´•WASHER, HARD, STAINLESS 6

400 A-2069 NUT, HEXAGON CASTLEATED 6

410 1 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS- APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

E-6749
ITEM NOT ILLUSTRATED
HC-13YR-1E

Page 10-91
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24Apr/Ol
 PROPELLER
HARTZELL MA:E~*NCE
B311L~PUNAM

FIG./ITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2281 ´•CYLINDER 1
60 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 1 C-3317-426-1 O-RING, PISTON OD 1
90 1 8-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING,LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-2 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 D-2841 HUB, THREE BLADED ALUMINUM HC- 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7159-1R HUB, THREE BLADED ALUMINUM HC- 1
SUPERSEDES ITEM 180 POST SL HC-SL-61-199
18081 D-3251-16R HUB, THREE BLADED ALUMINUM PHC- 1
SUPERSEDED BY ITEM 180C, PRE SL HC-SL-61-199
180CI E-7155-1R HUB, THREE BLADED ALUMINUM PHC- 1
SUPERSEDES ITEM 1808, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 ..NYLON BU~FON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

ITEM NOT ILLUSTRATED D-6011

(P)HC-13YR-1RF

ILLVSTRATED PARTS LIST 61’1 0’1 3 Rev. 22 Jun/GOPage 10-92

 PROPELLER MAINTENANCE MANUAL
nA RTZ E LL 113B

DESCRIPTION EFF UPA

FIG.IITEM PART
NUMBER CODE
NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 3
10-5-419 8-2256
1
420 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 A-3204
1
440 8-2222 PLATE, BLADE PRELOAD
INNER RING 1
450 8-6679
RETENTION RING, BEARING 3
460 A-2204
BLADE BEARING, BLADE RACE 3
490 A-2202-8
BALL SPACER 3
510 8-3211
1/2" DIAMETER STEEL BALL 75
520 8-6144
1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
8-6144-650
BLADE BEARING, HUB RACE 3
530 A-2202-A
3
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A
QUAD RING SEAL, BLADE, REPLACES ITEM 540 3
8-3663-4339
BUSHING, BLADE 3
565 A-241 3-2

R-FLANGE MOUNTING PARTS

1
320 C-331 7-228 O-RING, FLANGE
6
380 A-2067 STUD, HUB MOUNTING
6
390 A-1381 WASHER, HARD, STAINLESS
6
400 A-2069 NUT, HEXAGON CASTLEATED
SPRING PIN 6
410 8-3842-0750

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-6011
ITEM NOT ILLUSTRATED
HC-13YR-1RF

Page 10-93

ILLUSTRATED PARTS LIST 61-10-13 Rev. 24 Apr/Ol

 PROPELLER
HARTZELL MA:F~NANCE
B311L*UN~PM

FIGJITEM PART DESCRIPTION EFF UPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-3 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 ´•SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW. LOW PITCH STOP 1
50 C-6510 ´•CYLINDER 1
60 8-3838-3-5 COTTER PIN 1
70 1 A-2211 NUT, PITCH CHANGE ROD 1
80 1 C-3317-426-1 O-RING, PISTON OD 1
90 8-6511 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 1 8-6509-1 SPRING, LOW PITCH RETURN 1
120 8-6515-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 D-6869 ROD, PITCH CHANGE 1
170 C-331 7-251 O-RING, CYLINDER 1
180 D-3285-12 HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7156-4R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 1 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
230 1 A-2245-1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER. FLAT, STEEL 15
280 1 A-2043-1 NUT, SELF LOCKING 15
290 C-3317-226 O-RING, EXTENSION PLUG O.D. 1
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION 6

E-6868
ITEM NOT ILLUSTRATED
PHC-J3YF-1MF

ILLUSTRATEO PARTS Llm 61’1 0-13 Rev. 22 Jun/GOPage 10-94

 PROPELLER MAINTENANCE MANUAL
nARTZELL 1138

DESCRIPTION EFF UPA

FIG.IITEM PART
CODE
NUMBER NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE UNIT 3
10-5-419 8-2256
1
420 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 A-3204
1
440 8-2222 PLATE, BLADE PRELOAD
INNER RING 1
450 8-6679
RETENTION RING, BEARING 3
460 A-2204
BLADE BEARING, BLADE RACE 3
490 A-2202-B
BALL SPACER 3
510 A-3211
1/2" DIAMETER STEEL BALL 75
520 A-6144
RF
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX)
BLADE BEARING, HUB RACE 3
530 A-2202-A
QUAD RING SEAL, BLADE 3
540 8-3883-4339
3
565 A-241 3-2 BUSHING, BLADE

F-FLANGE MOUNTING PARTS

1
10-6 320 C-3317-228 O-RING, FLANGE
6
340 A-2429-5 STUD, HUB MOUNTING
6
350 A-1381 WASHER, HARD, STAINLESS
SELF LOCKING NUT 6
360 A-2044
DOWEL PIN 2
370 8-6138-8-9

BALANCE PARTS
SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

E-6868
ITEM NOT ILLUSTRATED
PHC-J3YF-1MF

Page 10-95
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24Apr/Ol
 PR6PELLER
HARTZELL MA:N~NANCE
B311LAUNAM

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 1 8-2281 CYLINDER 1
60 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-4 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 D-3285-9 HUB, THREE BLADED ALUMINUM HC- 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7156-3R HUB, THREE BLADED ALUMINUM HC- 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
18081 D-3285-12 HUB, THREE BLADED ALUMINUM PHC- I 1
SUPERSEDED BY ITEM 180C, PRE SL HC-SL-61-199
180CI E-7156-4R HUB, THREE BLADED ALUMINUM PHC- 1
SUPERSEDES ITEM 1808, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
230 A-2245-1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
250 1 A-2431 BOLT, HEXAGON HEAD 9
260 1 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
290 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 A-2481 EXTENSION PLUG 1
310 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

D´•4245
ITEM NOT ILLUSTRATED
(P)HC-J3YF-1RF

ILLUSTRATED PARTS LIST 61’1 0-13 Rev. 22 Jun/GOPage 10-96

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER CODE
NUMBER

BLADE RETENTION PARTS

8-2256 PRELOAD PLATE ASSEMBLY 3
10-5-419
1
420 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 A-3204
440 8-2222 PLATE, BLADE PRELOAD 1

8-6679 INNER RING 1

450
460 1 A-2204 RETENTION RING, BEARING 3

490 A-2202-8 BLADE BEARING, BLADE RACE 3

8-3211 BALL SPACER 3

510
8-6144 1/2" DIAMETER STEEL BALL 75
520
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

A-2202-A BLADE BEARING, HUB RACE 3

530
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3

8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3

565 A-2413-2 ´•BUSHING, BLADE 3

F-FLANGE MOUNTING PARTS

C-3317-223 O-RING, FLANGE 1
10-6 320
340 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6

A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6

350 A-1381 WASHER, HARD, STAINLESS 6

360 A-2044 SELF LOCKING NUT 6

8-6138-8-9 DOWEL PIN 2

370

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

D-4245
ITEM NOT ILLUSTRATED
(P)HC-J3YF-1RF

Page 10-97
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24 Apr/Ol
 PR6PELLER
HARTZELL MA~T3EsNANCE
B311LAUNAM

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2281 CYLINDER 1
60 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 1 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-2 ROD, PISTON 1
170 1 C-3317-251 O-RING, CYLINDER 1
180 D-3251-1OR HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-B~-199
180AI E-7154-3R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 1 A-2249 ´•´•BUSHING, GUIDE 1
190 i 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 1 A-279 LUBRICATION FITTING 6
-331 1 B-6544 CAP, LUBRICATION FITTING 6

D-3250
ITEM NOT ILLUSTRATED
(P)(E)HC-L3YF-1RF

ILLUSTRP;TED PARTS LIST 61’1 0’13 Rev. 22 Jun/GOPage 10-98

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

DESCRIPTION EFF UPA

FIG.IITEM PART
CODE
NUMBER NUMBER

BLADE RETENTION PARTS

3
10-5-419 8-2256 PRELOAD PLATE ASSEMBLY
1
420 8-3368 1 NUT, JAM HEXAGON
1
430 A-3204 SET SCREW, SOCKET DRIVE
1
440 8-2222 PLATE, BLADE PRELOAD
1
450 8-6679 INNER RING
RETENTION RING, BEARING 3
460 A-2204
BLADE BEARING, BLADE RACE 3
490 A-2202-8
BALL SPACER 3
510 8-3211
75
520 8-6144 1/2" DIAMETER STEEL BALL
RF
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX)
BLADE BEARING, HUB RACE 3
530 A-2202-A
3
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A
3
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540
3
565 A-241 3-2 BUSHING, BLADE

F-FLANGE MOUNTING PARTS

1
10-6 320 C-3317-228 O-RING, FLANGE
6
340 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1
6
A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1
6
350 A-1381 WASHER, HARD, STAINLESS
SELF LOCKING NUT 6
360 A-2044
2
370 8-6138-8-9 DOWEL PIN

BALANCE PARTS
SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

D-3250

ITEM NOT ILLUSTRATED

(P)(E)HC-L3YF-1RF

Page 10-99

ILLUSTRATED PARTS LIST 61-10-1 3 Rev. 24 Apr/Ol

 PROPELLER
HARTZELL MA:F~IN*NCE
8311LAUN~PM

FIG./ITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP 1
50 8-2281 CYLINDER 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING,LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-2 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 D-2841-1 HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7159-2R HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 ..NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

ITEM NOT ILLUSTRATED D-6011

HC-M3YR-1RF

i,,,,,,,,,,,,,, 61-10-13 Rev. 22

10-100
egaPOG/nuJ
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 1138

DESCRIPTION EFF UPA

FIG.IITEM PART
CODE
NUMBER NUMBER

BLADE RETENTION PARTS

3
10-5-419 8-2256 PRELOAD PLATE ASSEMBLY
1
420 8-3368 NUT, JAM HEXAGON
1
430 A-3204 SET SCREW, SOCKET DRIVE
1
440 8-2222 PLATE, BLADE PRELOAD
1
450 8-6679 INNER RING
3
460 A-2204 RETENTION RING, BEARING
BLADE BEARING, BLADE RACE 3
490 A-2202-8
3
510 8-3211 BALL SPACER
75
520 8-6144 1/2" DIAMETER STEEL BALL
RF
B-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX)
3
530 A-2202-A BLADE BEARING, HUB RACE
3
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A
3
8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540
3
565 A-241 3-2 BUSHING, BLADE

R-FLANGE MOUNTING PARTS

1
320 C-3317-228 ´•O-RING, FLANGE
6
380 A-2067 STUD, HUB MOUNTING
6
390 A-1381 WASHER, HARD, STAINLESS
6
400 A-2069 NUT, HEXAGON CASTLEATED
6
410 8-3842-0750 SPRING PIN

BALANCE PARTS
AR
-9000 8-3840-( SCREW
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-6011
ITEM NOT ILLUSTRATED
HC-M3YR-1RF

Page 10-101

ILLUSTRATE~ PPIRTS LIST 61 -1 0-1 3 Rev. 24 Apr/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIG./ITEM PART I DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 1 8-3359 ELASTIC STOP NUT -4F I 1
10AI 8-3807 ELASTIC STOP NUT -48F
30 1 8-3851-0663 WASHER -4F I 1
8-3851-1 032 WASHER (AN960-1016L) -48F I 1
40 1 A-4252 LOW PITCH STOP -4F I 1
A-4257 LOW PITCH STOP -4BF 1
50 8-2428-1 ´•CYLINDER -48 1
8-2428-2 CYLINDER -48F 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 1 A-2211 NUT, PITCH CHANGE ROD 1
80 1 C-3317-348-1 O-RING, PISTON OD 1
90 8-2419 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING,LOW PITCH RETURN 1
120 A-2420-() SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 1 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-2 ROD, PISTON 1
170 1 C-3317-247 O-RING, CYLINDER 1
180 D-3251-4 HUB, THREE BLADED ALUMINUM HC- 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7167-1 HUB, THREE BLADED ALUMINUM HC- 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
18081 D-3251-7 HUB, THREE BLADED ALUMINUM PHC- 1
SUPERSEDED BY ITEM 180C, PRE SL HC-SL-61-199
180CI E-7167-2 HUB, THREE BLADED ALUMINUM PHC- I 1
SUPERSEDES ITEM 1808, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 1 A-2249 BUSHING, GUIDE 1
190 1 8-3252 PITCH CHANGE FORK I I 1
195 1 A-3256 NYLON BUTTON, FORK 3
200 1 A-3253-2 PITCH CHANGE BLOCK 3
220 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 ´•WASHER, FLAT, STEEL 15
280 1 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 1 8-6544 CAP, LUBRICATION FITTING 6

D-4215
ITEM NOT ILLUSTRATED
(P)HC-CBYF-´•Q(B)F

ILLUSTRATED PARTS LIST 61 ’1 0’1 3 Rev. egaPOG/nuJ22

10-102
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE ASSEMBLY 3

420 8-3368 NUT, JAM HEXAGON 1

430 A-3204 SET SCREW, SOCKET DRIVE 1

440 8-2222 PLATE, BLADE PRELOAD 1

450 8-6679 INNER RING 1

460 A-2204 RETENTION RING, BEARING 3

490 A-2202-8 BLADE BEARING, BLADE RACE 3

510 1 8-3211 BALL SPACER I 1 3

520 1 8-6144 1/2" DIAMETER STEEL BALL 75

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A BLADE BEARING, HUB RACE 3

540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3

8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3

565 A-241 3-2 BUSHING, BLADE 3

F-FLANGE MOUNTING PARTS

10-6 320 C-3317-223 O-RING, FLANGE 1

340 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6

A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6

350 A-1381 WASHER, HARD, STAINLESS 6

360 A-2044 SELF LOCKING NUT 6

370 8-6138-8-9 DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

D-4215
ITEM NOT ILLUSTRATED
(P)HC-C3YF-4(B)F

Page 10-)03
ILLUSTRATED PARTS LIST 61-1 0-13 Rev. 24 Apr/Ol
 PROPELLER
HARTZELL B311LAVNAM

FIO.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT -4F I 1
10AI 8-3807 ELASTIC STOP NUT -4BF
30 8-3834-0663 ´•WASHER -4F i
8-3851-1 032 WASHER (AN960-1016L) -48F 1
40 A-4252 LOW PITCH STOP -4F 1
A-4257 LOW PITCH STOP -4BF 1
50 8-2428-1 CYLINDER -4F I 1
8-2428-2 CYLINDER -48F I 1
60 1 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 8-2419 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
110 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-() SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-2 ROD, PISTON 1
170 C-3317-247 O-RING, CYLINDER 1
180 D-3276 HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7162-1 HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
240 A-2249 BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 1 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

D-4215
ITEM NOT ILLUSTRATED
HC-CBYN-~(B)F

ILLUSTRATED PARTS LIST 61’1 0’1 3 Rev. 22

10-104
egaPOG/nuJ
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE ASSEMBLY 3

420 1 8-3368 NUT, JAM HEXAGON 1

430 1 A-3204 SET SCREW, SOCKET DRIVE 1

440 8-2222 PLATE, BLADE PRELOAD 1

450 8-6679 INNER RING 1

460 A-2204 RETENTION RING, BEARING 3

490 A-2202-8 BLADE BEARING, BLADE RACE 3

510 8-3211 BALL SPACER 3

520 8-6144 1/2" DIAMETER STEEL BALL 75

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A BLADE BEARING, HUB RACE 3

540 1 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3

8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3

565 A-2413-2 BUSHING, BLADE 3

N-FLANGE MOUNTING PARTS

10-7 320 C-3317-228 O-RING, FLANGE 1

340 A-3254 HUB MOUNTING STUD 8

350 A-2048-2 WASHER, HARD, STAINLESS 8
360 A-3257 SELF LOCKING NUT 8

370 8-6138-8-8 DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-4215
ITEM NOT ILLUSTRATED
HC-C3YN-4(B)F

Page 10-105
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24 Apr/Ol
 PROPELLER
HARTZELL 8311LAVNAM

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3359 ELASTIC STOP NUT -4F 1
10A1 8-3807 ELASTIC STOP NUT -4BF
30 B-3851-0663 WASHER -4F 1
8-3851-1 032 WASHER (AN960-1016L) -4BF I 1
40 A-4252 LOW PITCH STOP -4F 1
A-4257 LOW PITCH STOP -4BF 1
50 8-2428-1 CYLINDER -4F 1
8-2428-2 ´•CYLINDER -4BF 1
60 8-3838-3-5 COTTER PIN (AN380-3-5) 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 1 8-2419 PISTON 1
100 1 C-3317-018 O-RING, PISTON ID 1
120 A-2420-() SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-5 ROD, PISTON 1
150 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
170 C-331 7-247 O-RING, CYLINDER 1
180 D-3251-2 HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7172-1 HUB, THREE BLADED ALUMINUM 1
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
240 A-2249 BUSHING, GUIDE 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 1 A-3253-2 PITCH CHANGE BLOCK I 1 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

ITEM NOT ILLUSTRATED D-4215

HC-CSYRI~(B)F

ILLVSTRATED PARTS LIST 61’1 0’1 3 Rev. 22

10-106
egaPOG/nuJ
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE ASSEMBLY 3
420 8-3368 NUT, JAM HEXAGON 1

430 A-3204 SET SCREW, SOCKET DRIVE 1

440 8-2222 PLATE, BLADE PRELOAD 1

450 8-6679 INNER RING 1

460 A-2204 RETENTION RING, BEARING 3

490 A-2202-8 BLADE BEARING, BLADE RACE 3

510 8-3211 BALL SPACER 3

520 8-6144 1/2" DIAMETER STEEL BALL 75

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 1 A-2202-A BLADE BEARING, HUB RACE 3

540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 3

8-3883-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 3

565 A-241 3-2 BUSHING, BLADE 3

R-FLANGE MOUNTING PARTS

320 1 C-3317´•228 O-RING, FLANGE 1

380 A-2067 STUD, HUB MOUNTING 6

390 A-1381 ´•WASHER, HARD, STAINLESS 6

400 A-2069 NUT, HEXAGON CASTLEATED 6

410 8-3842-0750 SPRING PIN 6

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

D-4215
ITEM NOT ILLUSTRATED
HC-C3YR-4(B)F

Page 10-107
ILLUSTRATED PARTS LIST 61-1 0-13 Rev. 24 Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 113B

FIG.IITEM PART DESCRIPTION I EFF UPA

NUMBER NUMBER I I CODE

BASIC PROPELLER PARTS

10-2 10 8-3807 ELASTIC STOP NUT
30 B-3851-1 032 WASHER 1
40 A-4257 LOW PITCH STOP I I 1
50 8-2281-1 ´•CYLINDER I I 1
60 8-3838-3-5 COTTER PIN 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 B-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
120 A-2420-() SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-5 ROD, PISTON 1
150 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
170 C-3317-251 O-RING, CYLINDER 1
180 D-3251-2R HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7172-1R HUB, THREE BLADED ALUMINUM
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
240 A-2249 ´•´•BUSHING, GUIDE 1
190 8-3252-2 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 1 A-2431 BOLT, HEXAGON HEAD 9
260 i A-2432 BOLT, HEXAGON HEAD 6
270 1 B-3834-0632 WASHER, FLAT, STEEL 15
280 1 A-2043-1 NUT, SELF LOCKING 15
330 1 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6
334 8-7073-L1 HEX BOLT 3

E-7183
ITEM NOT ILLUSTRATED
HC-C3YR-4A

ILlUSTRATED PARTS LIST 61’1 0-1 3 Rev. 22

10-108
egaPOG/nuJ
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIG.IITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 C-7242 PRELOAD PLATE ASSEMBLY 3
1
420 8-3368 NUT, JAM HEXAGON
430 A-3204-1 SET SCREW, SOCKET DRIVE 1

440 C-1924 PLATE, BLADE PRELOAD 1

450 A-1272 SI 1616 INNER RING 1

460 8-1041 RETENTION RING, BEARING 3

490 C-792-8 BLADE BEARING, BLADE RACE 3

510 8-793 BALL SPACER 3

520 1 8-6144-1 3/8" DIAMETER STEEL BALL 99

8-6144-1-1500 3/8" DIAMETER STEEL BALL (1500 PIECE BOX) RF

530 C-792-A BLADE BEARING, HUB RACE 3

540 C-3317-340 O-RING, BLADE 3

PITCH CHANGE KNOB ASSEMBLY 3
545 8-6569(
550 8-6138-5-5 ´•´•PIN. DOWEL 1

BRACKET, PITCH CHANGE KNOB 1

560 C-1862-(
565 A-2413-2 ´•´•BUSHING, BLADE 1

570 8-3830 BOLT, TWELVE POINT 6

R-FLANGE MOUNTING PARTS

320 C-331 7-228 O-RING, FLANGE 1

380 A-2067 STUD, HUB MOUNTING 6

390 A-1381 WASHER, HARD, STAINLESS 6

400 A-2069 NUT, HEXAGON CASTLEATED 6

410 1 8-3842-0750 SPRING PIN 6

BALANCE PARTS
SCREW AR
-9000 8-3840-(
-9020 A-1929 BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

E-71 83
ITEM NOT ILLUSTRATED
HC-C3YR-4A

Page 10-109
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24 Apr/Ol
 PROPELLER
HARTZELL MA:N:3EsNANCE
8311LAUNAM

FIGJITEM I PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-2 10 8-3807 ELASTIC STOP NUT
30 8-3851-1 032 WASHER 1
40 A-4257 LOW PITCH STOP 1
50 8-2281-1 1 CYLINDER 1
60 8-3838-3-5 1 COTTER PIN 1
70 A-2211 NUT, PITCH CHANGE ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 C-331 7-018 ´•O-RING, PISTON ID 1
120 A-2420-() SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-5 ROD, PISTON 1
150 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
170 C-3317-251 O-RING, CYLINDER 1
180 D-3251-2R HUB, THREE BLADED ALUMINUM 1
SUPERSEDED BY ITEM 180A, PRE SL HC-SL-61-199
180AI E-7172-1R HUB, THREE BLADED ALUMINUM
SUPERSEDES ITEM 180, POST SL HC-SL-61-199
240 A-2249 ´•´•BUSHING, GUIDE 1
190 1 8-3252-2 PITCH CHANGE FORK 1
195 1 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
250 A-2431 BOLT, HEXAGON HEAD 9
260 A-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6
334 8-7073-L1 HEX BOLT 3

E-1801
ITEM NOT ILLUSTRATED
HC-C3YR-4G

ILLUSTRATED PARTS LIST 61 -1 0-1 3 Rev. 22

10-110
egaPOG/nuJ
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 C-7242 PRELOAD PLATE ASSEMBLY 3
420 8-3368 NUT, JAM HEXAGON 1
430 A-3204-1 SET SCREW, SOCKET DRIVE 1
440 C-1924 PLATE, BLADE PRELOAD 1
450 A-1272 1 SI 1616 INNER RING 1
460 8-1041 RETENTION RING, BEARING 3
490 C-792-8 BLADE BEARING, BLADE RACE 3
510 8-793 1 BALL SPACER 3
520 8-6144-1 3/8" DIAMETER STEEL BALL I 1 99
8-6144-1-1500 3/8" DIAMETER STEEL BALL (1500 PIECE BOX) RF
530 C-792-A BLADE BEARING, HUB RACE 3
540 C-331 7-340 ´•O-RING, BLADE 3
545 8-6569( PITCH CHANGE KNOB ASSEMBLY 3
550 8-61 38-5-5 ´•´•PIN. DOWEL 1
560 C-1862-( BRACKET, PITCH CHANGE KNOB 1
565 A-241 3-2 ´•´•BUSHING, BLADE 1
570 8-3830 BOLT, TWELVE POINT 6

R-FLANGE MOUNTING PARTS

320 C-331 7-228 O-RING, FLANGE 1
380 A-2067 STUD, HUB MOUNTING 6
390 A-1381 WASHER, HARD, STAINLESS 6
400 A-2069 NUT, HEXAGON CASTLEATED 6
410 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
-9020 A-1305 BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

E-1801
ITEM NOT ILLUSTRATED
H C-C3YR-4G

Page 10-111
ILLUSTRATED PARTS LIST 61’1 0’1 3 Rev. 24 Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIGJITEM PART DESCRIPTION EFF UPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-4 10 8-3807 ELASTIC STOP NUT 1
20 8-3851-1032 WASHER 1
40 A-2457 SOCKET SET SCREW 1
50 8-2428-2 CYLINDER 1
60 8-3838-3-5 AN380-3-5 COTTER PIN 1
70 A-2211 NUT, PISTON ROD 1
80 C-3317-348-1 O-RING, PISTON OD 1
90 8-2419 PISTON 1
100 C-331 7-018 O-RING, PISTON ID 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIFIEMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 1 A-2418-12 ROD, PISTON 1
170 lC-3317-247 O-RING, CYLINDER 1
180 E-7169-1 HUB, THREE WAY ALUMINUM 1
160 lA-2245-1 BUSHING, PITCH CHANGE ROD, FRONT 1
240 A-2249 BUSHING, GUIDE 1
150 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
190 8-3252 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 3
200 A-3253-2 PITCH CHANGE BLOCK 3
250 A-2431 BOLT, HEXAGON HEAD 9
(WHEN USING SPINNER MOUNTING KIT, REPLACE BOLTS [250] WITH
BOLTS IN KIT, IF APPLICABLE. REFER TO HARTZELL APPLICATION
GUIDE MANUAL 159 [61-02-59].)
260 lA-2432 BOLT, HEXAGON HEAD 6
270 8-3834-0632 WASHER, FLAT, STEEL 15
280 A-2043-1 NUT, SELF LOCKING 15
290 C-3317-145 O-RING, EXTENSION PLUG OD 1
300 A-2481 EXTENSION PLUG 1
310 C-3317-115-1 O-RING, EXTENSION PLUG ID 1
330 A-279 LUBRICATION FITTING 6
-331 8-6544 CAP, LUBRICATION FITTING 6

E-7455
ITEM NOT ILLUSTRATED
PHCIH3YF-4BF

ILLUSTRATED PARTS LIST 61 -1 0’1 3 Page 10-111.1

Rev. 23 Dec/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF UPA

FIG.IITEM
NUMBER CODE
NUMBER

BLADE RETENTION PARTS

PRELOAD PLATE ASSEMBLY 3
10-5-419 8-2256
1
420 8-3368 NUT, JAM HEXAGON
SET SCREW, SOCKET DRIVE 1
430 A-3204
PLATE, BLADE PRELOAD 1
440 8-2222
INNER RING 1
450 1 8-6679
RETENTION RING, BEARING 3
460 A-2204
BLADE BEARING, BLADE RACE 3
490 A-2202-B
BALL SPACER 3
510 8-3211
1/2" DIAMETER STEEL BALL 75
520 8-6144
1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
8-6144-650
BLADE BEARING, HUB RACE 3
530 A-2202-A
QUAD RING SEAL, BLADE 3
540 8-3883-4339
3
565 A-241 3-2 BUSHING, BLADE

F-FLANGE MOUNTING PARTS

1
10-6 320 C-3317-228 O-RING, FLANGE
6
340 A-2429-4 STUD, HUB MOUNTING
6
350 A-1381 WASHER, HARD, STAINLESS
SELF LOCKING NUT 6
360 A-2044
DOWEL PIN 2
370 8-6138-3-9

BALANCE PARTS
SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

E-7455
ITEM NOT ILLUSTRATED
PHC-H3YF-4BF

Page 10-111.2

ILLUSTRATED PARTS LIST 61-10-13 Rev. 24 Apr/Ol

 PRdPELLER
HARTZELL B311LAUNAM

FIG./ITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BASIC PROPELLER PARTS

10-4 10 8-3359 ELASTIC STOP NUT 1
20 1 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW 1
50 8-2281 CYLINDER 1
60 8-3838-3-5 AN380-3-5 COTTER PIN 1
70 A-2211 NUT, PISTON ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
110 A-2213-1 SPRING, LOW PITCH RETURN
100 C-331 7-018 O-RING, PISTON ID 1
120 A-2420-( SPACER, HIGH STOP 1
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER t
140 A-241 8-2 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 E-4501-5 HUB, FOUR WAY ALUMINUM 1
160 A-2245 BUSHING, PITCH CHANGE ROD, FRONT 1
240 A-2249 BUSHING, GUIDE 1
190 C-4503 PITCH CHANGE FORK 1
195 A-3256 NYLON BUTTON, FORK 4
200 A-3253-2 PITCH CHANGE BLOCK 4
220 C-3317-115-1 O-RING, PITCH CHANGE ROD, REAR 1
250 A-2431 BOLT, HEXAGON HEAD 12
260 A-3203 BOLT, HEXAGON HEAD 8
270 8-3834-0632 WASHER, FLAT, STEEL 20
280 A-2043-1 NUT, SELF LOCKING 12
285 8-3599 NUT, SELF LOCKING 8
330 lA-279 LUBRICATION FITTING 8
-331 18-6544 CAP, LUBRICATION FITTING 8

ITEM NOT ILLUSTRATED D-1740

HC-C4YF-1(E)

ILLUSTRATED PARTS LIST 61’1 0’1 3 Rev. 22

10-112
egaPOG/nuJ
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIGJITEM PART DESCRIPTION EFF UPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5 -419 8-2256 PRELOAD PLATE ASSEMBLY 4

420 8-3368 NUT, JAM HEXAGON 1

430 A-3204 SET SCREW, SOCKET DRIVE 1

440 1 8-2222 PLATE, BLADE PRELOAD 1

450 1 8-6679 INNER RING 1

460 A-2204 RETENTION RING, BEARING 4

490 A-2202-8 BLADE BEARING, BLADE RACE 4
510 8-3211 BALL SPACER 4

520 8-6144 1/2" DIAMETER STEEL BALL 100

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

530 A-2202-A BLADE BEARING, HUB RACE 4
540 8-3883-4339 QUAD RING SEAL, BLADE 4

565 A-241 3-2 BUSHING, BLADE 4

F-FLANGE MOUNTING PARTS

10-6 320 1 C-3317-228 O-RING, FLANGE 1

340 1 A-2429-3 STUD, HUB MOUNTING, REFER TO NOTE 1 6

A-2429-4 STUD, HUB MOUNTING, REFER TO NOTE 1 6
340 8-1738 STUD, HUB MOUNTING" -18 1 6
"THE 8-1738 HUB MOUNTING STUD IS USED ON F-FLANGE
PROPELLERS THAT INCORPORATE A SPACER BETWEEN
THE ENGINE FLANGE AND THE PROPELLER FLANGE.
350 1 A-1381 ´•WASHER, HARD, STAINLESS 6
360 1 A-2044 SELF LOCKING NUT 6
370 8-6138-8-9 DOWEL PIN 2

BALANCE PARTS
-9000 8-3840-( SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

NOTE 1: FOR THE HUB MOUNTING STUD FOR A

SPECIFIC INSTALLATION, REFER TO THE ALUMINUM
HUB OVERHAUL CHAPTER OF HARTZELL STANDARD
PRACTICES MANUAL 202A (61-01-02).

0-1740
ITEM NOT ILLUSTRATED
HC-C4YF-1(E)

Page 10-113
ILLUSTRATED PARTS LIST 61-10-13 Rev. 24 Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBERI NUMBER CODE

BASIC PROPELLER PARTS

10-4 10 8-3359 ELASTIC STOP NUT 1
20 8-6747 SEAL, WASHER 1
40 A-2421 SOCKET SET SCREW, LOW PITCH STOP i
50 8-2281 CYLINDER 1
60 8-3838-3-5 AN380-3-5 COTTER PIN 1
70 A-2211 NUT, PISTON ROD 1
80 C-3317-426-1 O-RING, PISTON OD 1
90 8-2280 PISTON 1
100 C-331 7-018 O-RING, PISTON I.D. 1
110 1 A-2213-1 SPRING, LOW PITCH RETURN 1
120 A-2420-( SPACER, HIGH STOP
(LENGTH TO SUIT PITCH REQUIREMENTS)
130 A-867 SPLIT RING, HIGH PITCH STOP RETAINER 1
140 A-241 8-9 ROD, PISTON 1
170 C-331 7-251 O-RING, CYLINDER 1
180 D-4502-1 HUB, FOUR WAY ALUMINUM 1
160 A-2245 BUSHING, PITCH CHANGE ROD, CYLINDER-SIDE HUB HALF 1
230 A-2245-1 BUSHING, PITCH CHANGE ROD, ENGINE-SIDE HUB HALF 1
240 A-2249 BUSHING, GUIDE 1
-241 A-3229 EXTENSION BOLT 6
-242 8-3834-0663 EXTENSION WASHER 6
-243 A-2043-1 EXTENSION NUT 6
190 C-4503 PITCH CHANGE FORK 1
200 A-3253-2 PITCH CHANGE BLOCK 4
210 A-3256 NYLON BUTTON, FORK 4
250 A-2431 BOLT, HEXAGON HEAD 12
260 A-3203 BOLT, HEXAGON HEAD 8
270 1 8-3834-0632 WASHER, FLAT, STEEL 20
280 1 A-2043-1 NUT, SELF LOCKING 20
290 C-3317-226 O-RING, EXTENSION PLUG OD 1
300 A-2481 EXTENSION PLUG 1
310 C-3317-115-1 O-RING, EXTENSION PLUG I.D. 1
330 A-279 LUBRICATION FITTING 8
-331 8-6544 CAP, LUBRICATION FITTING 8

D-540
ITEM NOT ILLUSTRATED
HC-F4YR-1

ILLUSTRATED PARTS LIST 61’1 0’1 3 Rev. 22

10-114
egaPOG/nuJ
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER CODE

BLADE RETENTION PARTS

10-5-419 8-2256 PRELOAD PLATE ASSEMBLY 4
420 8-3368 NUT, JAM HEXAGON 1
430 A-3204 SET SCREW, SOCKET DRIVE 1
440 1 8-2222 PLATE, BLADE PRELOAD 1
450 1 8-6679 INNER RING 1

460 1 A-2204 RETENTION RING, BEARING 4

490 A-2202-8 BLADE BEARING, BLADE RACE 4
510 8-3211 BALL SPACER 4
520 8-6144 1/2" DIAMETER STEEL BALL 100
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
530 A-2202-A BLADE BEARING, HUB RACE 4
540 C-3317-339 O-RING, BLADE, REPLACED BY ITEM 540A 4
8-3833-4339 QUAD RING SEAL, BLADE, REPLACES ITEM 540 4
565 A-2413-2 BUSHING, BLADE 4

R-FLANGE MOUNTING PARTS

320 C-331 7-228 O-RING, FLANGE 1
380 A-2067 STUD, HUB MOUNTING 6
390 A-1381 WASHER, HARD, STAINLESS 6
400 1 A-2069 NUT, HEXAGON CASTLEATED 6
410 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( .SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE MANUAL 159 (61-02-59)

0-540
ITEM NOT ILLUSTRATED
HC-F4YR-1

Page 10-115
ILLUBTRATeD PARTS LIST 61 -1 0’1 3 Rev. 24 Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1138

(This page is intentionally blank.)

ILLUSTRPITED PPIRTS LIST 61’1 0’1 3 Page 10-116

Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

FIG.IITEM PART I I DESCRIPTION EFF IUPA

NUMBER I NUMBER I 1 ~234567 CODE

835-23(P) SPINNER ASSEMBLY

C-1904-2(P) SPINNER DOME I I 1
C-2472(P) BULKHEAD UNIT 1
SUPERSEDED BY PART NUMBER C-2472-3
PRE SL HC-SL-61-179
C-2472-3(P) BULKHEAD UNIT 1
SUPERSEDES PART NUMBER C-2472
POST SL HC-SL-61-179
AN526C1 032R8 ´•SCREW I 1 14
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-B1-170
-lB-3845-8 ´•SCREW I 1 14
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 FIBRE WASHER I 1 14

835-36(P) SPINNER ASSEMBLY

C-1904-5(P) SPINNER DOME I I 1
C-885-3(P) ADAPTER RING UNIT I I 1
B-2480(P) FILLER PLATE I 1 3
AN526C1 032R8 ´•SCREW I 1 27
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
B-3845-8 1 I .SCREW I 1 27
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 I I FIBRE WASHER I 1 27

835-38(P) SPINNER ASSEMBLY

C-1904-4(P) SPINNER DOME I I 1
C-3279(P) BULKHEAD UNIT, SUPERSEDED BY PART C-3279-1(P) 1
PRE SL HC-SL´•G1-199
C-3279-1(P) BULKHEAD UNIT, SUPERSEDES PART C-3279(P) 1
POST PRE SL HC-SL-B1-1 99 1 I 1
AN526C1 032R8 1 I ´•SCREW I 1 15
REPLACED BY PART NO. B-3845-8
PRE SL HC-SL-61-170
B-3845-8 1 I .SCREW I 1 15
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 I I .FIBRE WASHER I 1 15

835-41(P) SPINNER ASSEMBLY

C-4205(P) .SPINNER DOME I I 1
C-885-4(P) ADAPTER RING UNIT I I 1
B-2480(P) FILLER PLATE I 1 2
AN526C1 032R8 1 I .SCREW I 1 22
REPLACED BY PART NO. B-3845-8
PRE SL HC-SL-61-170
B-3845-8 1 I ´•SCREW I 1 22
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 I I .FIBRE WASHER I 1 22

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page 10-117
ILLUSTRATED PARTS LIST 61 -1 0-1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF IUPA

FIG.IITEM
NUMBER NUMBER 1234567 CODE

835-42(P) SPINNER ASSEMBLY

SPINNER DOME 1
C-4205-1(P)
BULKHEAD UNIT 1
C-2472-1(P)
SUPERSEDED BY PART NUMBER C-2472-4
PRE SL HC-SL-61-179
BULKHEAD UNIT 1
C-2472-4(P)
SUPERSEDES PART NUMBER 0-2472-1
POST SL HC-SL-61-179
´•SCREW 14
-IAN526C1032R8
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 ´•SCREW 14
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
FIBRE WASHER 14
A-1020

835-43(P) SPINNER ASSEMBLY

SPINNER DOME 1
C-1904-6(P)
BULKHEAD UNIT 1
C-3279(P)
AN526C1 032R8 ´•SCREW 15
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 ´•SCREW 15
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL61-170
I A-1020 FIBRE WASHER 15

835-47(P) SPINNER ASSEMBLY

SPINNER DOME 1
C-1904-5(P)
ADAPTER RING UNIT 1
C-4549(P)
FILLER PLATE 3
B-4522(P)
AN526C1032R8 ´•SCREW 27

REPLACED BY PART NO. 8-3845-8

PRE SL HC-SL-61-170
8-3845-8 ´•SCREW 27
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
FIBRE WASHER 27
A-1020

835-50L(P) SPINNER ASSEMBLY

SPINNER DOME 1
D-4824L(P)
BULKHEAD UNIT 1
D-4825(P)
SUPERSEDED BY PART NUMBER C-4825-1
PRE SL HC-SL-B1-179
BULKHEAD UNIT 1
D-4825-1(P)
SUPERSEDES PART NUMBER D-4825
POST SL HC-SL-61-179
AN526C1 032R8 ´•SCREW 14

REPLACED BY PART NO. 8-3845-8

PRE SL HC-SL-61-170
8-3845-8 ´•SCREW 14

REPLACES PART NUMBER AN526C1032R8

POST SL HC-SL-61-170
FIBRE WASHER 14
A-1020

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page 10-118
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER I NUMBER I 1 1234587 CODE

835-52(P) SPINNER ASSEMBLY

D-5769(P) SPINNER DOME 1

C-4549(P) ADAPTER RING UNIT I I 1

B-4522(P) FILLER PLATE I 1 3

B-3845-8 ´•SCREW 27
A-1020 FIBER WASHER I 1 27

836-52(P) SPINNER ASSEMBLY

C-2495-1(P) ´•DOME, SPINNER 1

C-2469(P) BULKHEAD UNIT 1

SUPERSEDED BY PART NUMBER C-2469-2
PRE SL HC-SL-61-179
C-2469-2(P) BULKHEAD UNIT I I 1
SUPERSEDES PART NUMBER C-2469
POST SL HC-SL-61-179
AN526C1032R8 SCREWS, SPINNER DOME 18
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 ´•SCREW I 1 18
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 FIBRE WASHER 18

836-60(P) SPINNER ASSEMBLY

C-2495-1(P) SPINNER DOME 1
BULKHEAD UNIT 1
C-2469-1(P)
SUPERSEDED BY PART NUMBER C-2469-3
PRE SL HC-SL-61-179
C-2469-3(P) BULKHEAD UNIT I I 1
SUPERSEDES PART NUMBER C-2469-1
POST SL HC-SL-61-179
AN526C1 032R8 ´•SCREW 18
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 ´•SCREW 1 I la
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 FIBRE WASHER 18

A-2295(P) SPINNER ASSEMBLY 1

C-2294(P) BULKHEAD UNIT I I 1

SUPERSEDED BY PART NUMBER C-2294-5
PRE SL HC-SL-B1-179
C-2294-5(P) BULKHEAD UNIT 1
SUPERSEDES PART NUMBER C-2294
POST SL HC-SL-81-179
DOME UNIT I I 1
C-3532-4(P)
AN526C1032R8 ´•SCREW 12
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 ´•SCREW I 1 12
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 FIBRE WASHER 12

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page 10-119
ILLUSTRATED PARTS LIST 61’1 0’1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER I 1 1234587 CODE

A-2295-1(P) SPINNER ASSEMBLY t

C-2294-1(P) BULKHEAD UNIT, SUPERSEDED BY PART C-2294-12(P) 1

PRE SL HC-SL-61-199
C-2294-12(P) BULKHEAD UNIT, SUPERSEDES PART C-2294-12(P) 1
POST PRE SL HC-SL-61-199
C-3532-5(P) DOME UNIT 1
AN526C1 032R8 ´•SCREW 12
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
.18.3845.8 ´•SCREW 12
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 I I FIBRE WASHER 12

A-2295-4(P) SPINNER ASSEMBLY 1

C-2294-10(P) BULKHEAD UNIT, SUPERSEDED BY PART C-2294-14(P) 1

PRE SL HC-SL-61-199
C-2294-14(P) BULKHEAD UNIT, SUPERSEDES PART C-2294-12(P) 1

POST PRE SL HC-SL-61-199

C-3532-21(P) DOME UNIT I I 1

8-3845-8 ´•SCREW I 1 12
A-1020 FIBRE WASHER I 1 12

A-2297(P) SPINNER ASSEMBLY 1

C-2294-2(P) BULKHEAD UNIT 1

SUPERSEDED BY PART NUMBER C-2294-7
PRE SL HC-SL-61-179
C-2294-7(P) BULKHEAD UNIT I I 1
SUPERSEDES PART NUMBER C-2294-2
POST SL HC-SL-61-179
C-3532-9(P) DOME UNIT 1
AN526C1 032R8 ´•SCREW I 1 12
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 ´•SCREW I 1 12
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
I A-1020 FIBRE WASHER 12

A-2298-2(P) SPINNER ASSEMBLY I I 1

C-2299-1(P) BULKHEAD UNIT I I 1

SUPERSEDED BY PART NUMBER C-2299-4
PRE SL HC-SL-61-179
C-2299-4(P) BULKHEAD UNIT 1
SUPERSEDES PART NUMBER C-2299-1 1
POST SL HC-SL-61-179
C-3532-12(P) DOME UNIT 1
AN526C1 032R8 ´•SCREW 16
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
-18-3845-8 ´•SCREW 16
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-G1-170
A-1020 FIBRE WASHER I 1 16

ITEM NOT ILLUSTRATED

Spinner Assembly Par~s

Page 10-120
ILLUSTF~TED PP~RTS LIST 61’1 0-1 3 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER I 1 CODE
NUMBER 1234567

C-2513-5(P) SPINNER ASSEMBLY

.DOME, SPINNER 1
C-2531-10(P)
ADAPTER RING UNIT (W/ FILLER PLATES) 1
C-2512-5(P)
AN526C1 032R8 ´•SCREW 20
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
´•SCREW 20
8-3845-8
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL61-170
I I I FIBRE WASHER 20
A-1020

C-3245-1(P) SPINNER ASSEMBLY

BULKHEAD UNIT 1
C-3228(P)
SUPERSEDED BY PART NUMBER C-3228-1
PRE SL HC-SL-61-179
BULKHEAD UNIT 1
C-3228-1(P)
SUPERSEDES PART NUMBER C-3228
POST SL HC-SL-61-179
´•DOME, SPINNER 1
C-3241-1(P)
´•CAP, DOME 1
8-3242(P)
SAFETY SCREW, CAP 2
8-3840-6
´•SCREW, CAP 3
8-3866-50
AN526C1 032R8 ´•SCREW 14

REPLACED BY PART NO. 8-3845-8

PRE SL HC-SL-61-170
´•SCREW 14
-18-3845-8
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
FIBRE WASHER 14
A-1020

A-3293(P) SPINNER ASSEMBLY

BULKHEAD UNIT 1
C-3295(P)
SUPERSEDED BY PART NUMBER C-3295-1
PRE SL HC-SL-61-1 79
BULKHEAD UNIT 1
C-3295-1(P)
SUPERSEDES PART NUMBER C-3295
POST SL HC-SL-61-179
´•DOME, SPINNER 1
C-3294(P)
.SCREW 14
AN526C1 032R8
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
´•SCREW 14
-18-3845-8
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SLB1-170
FIBRE WASHER 14
A-1020

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page 10-121
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 113B

FIG.IITEM PART DESCRIPTION I EFF IUPA

NUMBER NUMBER 1234587 1 CODE

C-3533(P) SPINNER ASSEMBLY

C-3534(P) BULKHEAD UNIT I I 1
SUPERSEDED BY PART NUMBER C-3534-2
PRE SL HC-SL-61-179
C-3534-2(P) BULKHEAD UNIT 1
SUPERSEDES PART NUMBER C-3534
POST SL HC-SL-61-179
C-3532(P) ´•DOME, SPINNER 1
-IAN526C1032R8 I I´•SCREW 16
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 ´•SCREW I 1 16
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 I I FIBRE WASHER 16

C-3535(P) SPINNER ASSEMBLY

C-3539(P) BULKHEAD UNIT, SUPERSEDED BY PART C-3539-1(P) 1
PRE SL HC-SL-61-199
C-3539-1(P) BULKHEAD UNIT, SUPERSEDES PART C-3539(P) 1
POST PRE SL HC-SL-61-199
C-3532-1(P) ´•DOME, SPINNER 1
AN526C1 032R8 1 I´•SCREW I 1 15
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 1 I´•SCREW I 1 15
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 I I .FIBRE WASHER 15

C-3535-1(P) SPINNER ASSEMBLY

C-3539(P) BULKHEAD UNIT, SUPERSEDED BY PART C-3539-1(P) 1
PRE SL HC-SL-61-199
C-3539-1(P) I I BULKHEAD UNIT, SUPERSEDES PART C-3539(P) 1
POST PRE SL HC-SL-61-199
C-3532-7(P) ´•DOME, SPINNER 1
AN526C1 032R8 ´•SCREW 15
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 ´•SCREW 15
REPLACES PART NUMBER AN526C1032F18
POST SL HC-SL-61-170
A-1020 I I FIBRE WASHER I 1 15

C-3552(P) SPINNER ASSEMBLY

C-3553(P) ADAPTOR RING I I 1
C-3532-2(P) ´•DOME, SPINNER I I 1
AN526C1 032R8 ´•SCREW 12
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 1 I. SCREW 12
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 FIBRE WASHER 12

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

ILLUSTRATED PARTS LIST 61 -1 0’1 3 Rev. 22egaPOG/nuJ10-122

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART I I DESCRIPTION I EFF IUPA

NUMBER I NUMBER I 1 1234b67 CODE

C-3552-1(P) SPINNER ASSEMBLY

C-3553(P) ADAPTOR RING I I 1

C-3532-3(P) ´•DOME, SPINNER 1

AN526C1 032R8 1 I .SCREW I 1 12
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 1 I .SCREW I 1 12
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 I I FIBRE WASHER I 1 12

C-3568(P) SPINNER ASSEMBLY

C-3569(P) BULKHEAD UNIT I I 1
SUPERSEDED BY PART NUMBER 0-3569-1
PRE SL HC-SL61-179
C-3569-1(P) BULKHEAD UNIT I I 1
SUPERSEDES PART NUMBER C-3569
POST SL HC-SL-61-179
C-3532-13 ´•DOME, SPINNER 1
AN526C1 032R8 1 I ´•SCREW I I Is
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
-lB-3845-8 1 I ´•SCREW i 1 16
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL61-170
A-1020 I I FIBRE WASHER I 1 16

C-3570( SPINNER ASSEMBLY

C-3571(P) BULKHEAD UNIT, SUPERSEDED BY PART C-3571-1(P) 1
PRE SL HC-SL-B1-199
C-3571-1(P) BULKHEAD UNIT, SUPERSEDES PART C-3571(P) 1
POST PRE SL HC-SL-61-199 I I 1
C-3532-14(P) ´•DOME, SPINNER I 1 1
AN526C1 032R8 1 I .SCREW I 1 18
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
-18-3845-8 1 I ´•SCREW I 1 18
REPLACES PART NUMBER AN526C1032RB
POST SL HC-SL-61-170
A-1020 I I .FIBRE WASHER I 1 18

C-3575(P) SPINNER ASSEMBLY

C-3576 BULKHEAD UNIT, SUPERSEDED BY PART C-3576-2(P) 1
PRE SL HC-SL-61-199
C-3476-2(P) I I BULKHEAD UNIT, SUPERSEDES PART C-3576(P) 1
POST PRE SL HC-SL-B1-199 I I 1
C-3532-15(P) ´•DOME, SPINNER 1
AN526C1 032R8 1 I .SCREW I 1 18
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
-18-3845-8 1 I ´•SCREW I I 18
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL61-170
A-1020 I I FIBRE WASHER I 1 18

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page 10-123
61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1138

PART DESCRIPTION EFF IUPA

FIG.IITEM
NUMBER 1234567 CODE
NUMBER

C-3575-1(P) SPINNER ASSEMBLY

BULKHEAD UNIT, SUPERSEDED BY PART C-3576-3(P) 1
C-3576-1(P)
PRE SL HC-SL-61-199
BULKHEAD UNIT, SUPERSEDES PART C-3576-1(P) 1
C-3576-3(P)
POST PRE SL HC-SL-6‘1-199
´•DOME, SPINNER 1
C-3532-16(P)
´•SGREW 18
AN526C1032R8
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
´•SCREW 18
8-3845-8
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL´•61-170
FIBRE WASHER 18
A-1020

A-4209(P) SPINNER ASSEMBLY

ADAPTOR RING 1
C-3259-1(P)
´•DOME, SPINNER 1
C-4250-1(P)
´•CAP, DOME 1
8-3264
CAP SCREW (AN507-832R8) 3
8-3838-50
.SCREW 12
AN526C1 032R8
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
´•SCREW 12
8-3845-8
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
FIBRE WASHER 12
A-1020

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page 10-124
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART DESCRIPTION EFF IUPA

NUMBER I 1 1234587 CODE

NUMBER

D-4511(P) SPINNER ASSEMBLY

BULKHEAD UNIT 1
D-4513(P)
DOME, SPINNER 4 HOLE 1
D-4512(P)
SUPERSEDED BY D-4512-2(P)
PRE SL HC-SL-61-183
DOME, SPINNER 8 HOLE 1
D-4512-2(P)
SUPERSEDES D-4512(P)
POST SL HC-SL81-183
.SCREW 4 HOLE 1 4
MS24693C50
REPLACED BY PART NO. 8-3866-50
PRE SL HC-SL-61-170
8-3866-50 ´•SCREW 4 HOLE 1 4

REPLACES PART NUMBER AN526C1032R8

POST SL HC-SL-61-170
8-3866-50 ´•SCREW 8 HOLE 1 8
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
´•CAP 4 HOLE I 1
C-4523(P)
SUPERSEDED BY C-4523-2(P)
´•CAP 4 HOLE I 1
C-4523-2(P)
SUPERSEDES C-4523(P)
SUPERSEDED BY D-4523-5(P)
PRE SL HC-SL-61-183
.CAP 8 HOLE I 1
D-4523-5(P)
SUPERSEDES C-4523-2(P)
POST SL HC-SL-81-183
SAFETY SCREW (AN501A10-6) 2
8-3840-6
´•SCREW 16
AN526C1 032R8
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
´•SCREW 16
8-3845-8
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-Q1-170
FIBRE WASHER 16
A-1020

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page 10-125
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART I I DESCRIPTION I EFF IUPA

NUMBER I NUMBER I 1 12344g7 CODE

D-4511-1(P) SPINNER ASSEMBLY

D-4513(P) BULKHEAD UNIT I I 1
C-451 2-1(P) ´•DOME, SPINNER 1
MS24693C50 ´•SCREW I 1 4
REPLACED BY PART NO. 8-3866-50
PRE SL HC-SL-61-1 70
8-3866-50 1 I ´•SCREW I 1 4
REPLACES PART NUMBER MS24693C50
POST SL HC-SL-61´•170
B-3860-8L ´•WASHER, DIMPLED I 1 4
C-4523P I I .CAP I I 1
8-3840-6 SAFETY SCREW (AN501A10-6) 2
AN526C1032R8 ´•SCREW I 1 16
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
-18-3845-8 1 I ´•SCREW I 1 16
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-B1-170
A-1020 I I .FIBRE WASHERS I 1 16

C-4565(P) SPINNER ASSEMBLY

C-4567(P) BULKHEAD UNIT I I 1
SUPERSEDED BY PART NUMBER C-4567-1
PRE SL HC-SL-61-179
I C-4567-1(P) BULKHEAD UNIT 1
SUPERSEDES PART NUMBER C-4567 1
POST SL HC-SL-81-179
C-4568(P) ´•DOME, SPINNER 1
AN526C1 032R8 1 I ´•SCREW I 1 14
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 1 I .SCREW I 1 14
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 I I FIBRE WASHER I 1 14

C-4582(P) SPINNER ASSEMBLY

C-4583(P) BULKHEAD UNIT, SUPERSEDED BY PART C-4583-2(P) 1
PRE SL HC-SL-61-199
C-4583-2(P) BULKHEAD UNIT, SUPERSEDES PART C-4583(P) 1
POST PRE SL HC-SL-61-199 I I 1
C-4586(P) ´•DOME, SPINNER 1
AN526C1 032R8 1 I .SCREW I 1 18
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-B1-170
-18-3845-8 1 I ´•SCREW I 1 18
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 I I .FIBRE WASHER I 1 18

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page
ILLUSTRATEO PARTS LIST 61 -1 0-1 3 10-126
Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
nARTZELL 1138

FIG.IITEM PART DESCRIPTION EFF IUPA

NUMBER NUMBER I 1 1234587 CODE

D-4810(P) SPINNER ASSEMBLY

BULKHEAD UNIT I I 1
D-4812(P)
SUPERSEDED BY PART NUMBER D-4812-1
PRE SL HC-SL-61-179
BULKHEAD UNIT 1
I D-4812-1(P)
SUPERSEDES PART NUMBER D-4812 1
POST SL HC-SL-61-179
C-3532-17 .DOME, SPINNER 1

AN526C1 032R8 ´•SCREWS 12

REPLACED BY PART NO. B-3845-8
PRE SL HC-SL-61-170
8-3845-8 ´•SCREW 12
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 FIBRE WASHERS 12

D-5205(P) SPINNER ASSEMBLY

BULKHEAD UNIT, SUPERSEDED BY PART D-4561-7(P) 1
D-4561-3(P)
PRE SL HC-SL-61-199
BULKHEAD UNIT, SUPERSEDES PART D-4561-3(P) 1
D-4561-7(P)
POST PRE SL HC-SL-61-199 I I 1

´•DOME, SPINNER 1
D-5206(P)
.CAP, DOME 1
C-4563(P)
MS24693C50 CAP SCREWS (MS24693C50) 3

AN526C1 032R8 1 ´•SCREWS 18

REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 I´•SCREW 18
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
A-1020 FIBRE WASHERS 1 18

D-5413(P) SPINNER ASSEMBLY

BULKHEAD UNIT 1
C-2294-3(P)
SUPERSEDED BY PART NUMBER C-2294-8
PRE SL HC-SL61-179
BULKHEAD UNIT 1
C-2294-8(P)
SUPERSEDES PART NUMBER C-2294-3
POST SL HC-SL-61-179
C-3532-1 8(P) ´•DOME, SPINNER 1

AN526C1032R8 ´•SCREWS 12

REPLACED BY PART NO. 8-3845-8

PRE SL HC-SL-B1-170
8-3845-8 ´•SCREW 12

REPLACES PART NUMBER AN526C1032F18

POST SL HC-SL-61-170

D-5421(P) SPINNER ASSEMBLY

BULKHEAD UNIT 1
D-5423(P)
D-5422(P) ´•DOME, SPINN
AN526C1 032R8 ´•SCREWS 12

REPLACED BY PART NO. 8-3845-8

PRE SL HC-SL-61-170
8-3845-8 ´•SCREW 12

REPLACES PART NUMBER AN526C1032R8

POST SL HC-SL-61-170
A-1020 .FIBRE WASHERS 12

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page 10-127
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 113B

FIG.IITEM I PART DESCRIPTION EFF IUPA

NUMBER NUMBER 1234567 1 CODE

D-5495L(P) SPINNER ASSEMBLY

C-3539(P) BULKHEAD UNIT, SUPERSEDED BY PART C-3539-1(P) 1
PRE SL HC-SL-61-199
C-3539-1(P) BULKHEAD UNIT, SUPERSEDES PART C-3539(P) 1
POST PRE SL HG-SL81-199
D-5496L(P) ´•DOME, SPINNER 1
AN526C1032R8 ´•SCREWS 12
REPLACED BY PART NO. 8-3845-8
PRE SL HC-SL-61-170
8-3845-8 1 I .SCREW I 1 12
REPLACES PART NUMBER AN526C1032R8
POST SL HC-SL-61-170
I A-1020 I I FIBRE WASHERS I 1 12

D-5732(P) SPINNER ASSEMBLY

D-5734(P) BULKHEAD UNIT, SUPERSEDED BY PART D-5734-1(P) 1
PRE SL HC-SL-61-199
D-5734-1(P) BULKHEAD UNIT, SUPERSEDES PART D-5734(P) 1
POST PRE SL HC-SL-61-199
D-5733(P) ´•DOME, SPINNER I I 1
8-3845-8 ´•SCREW I 1 15
A-1020 I I FIBRE WASHER I 1 15

D-6750(P) SPINNER ASSEMBLY

D-6753(P) BULKHEAD UNIT, SUPERSEDED BY PART D-6753-1(P) 1
PRE SL HC-SL-61-199
D-6753-1(P) BULKHEAD UNIT, SUPERSEDES PART D-6753(P) 1
POST PRE SL HC-SL-61-199 I I 1
D-6751-( )C(P) .DOME, SPINNER 1
-lB-3845-8 1 I .SCREWS I 1 18
A-1020 I I .FIBRE WASHER I 1 18

D-6841(P) SPINNER ASSEMBLY

D-6839(P) BULKHEAD UNIT, SUPERSEDED BY PART D-6839-1(P) 1
PRE SL HC-SL-61-199
D-6839-1(P) BULKHEAD UNIT, SUPERSEDES PART D-6839(P) 1
POST PRE SL HC-SL-61-199
D-6840(P) ´•DOME, SPINNER I I 1
8-3845-8 1 I .SCREW I 1 15
A-1020 I I FIBRE WASHER I 1 15

D-6936(P) SPINNER ASSEMBLY

C-3571(P) BULKHEAD UNIT, SUPERSEDED BY PART C-3571-1(P) 1
PRE SL HC-SL-61-199
C-3571-1(P) BULKHEAD UNIT, SUPERSEDES PART C-3571(P) 1
POST PRE SL HC-SL-61-199 I I 1
D-6935(P) ´•DOME, SPINNER 1
8-3845-8 .SCREW I 1 18
A-1020 I I FIBRE WASHER I 1 18

D-7086(P) SPINNER ASSEMBLY

D-7084(P) BULKHEAD UNIT, SUPERSEDED BY PART D-7084-1(P) 1
PRE SL HC-SL-61-199
D-7084-1(P) BULKHEAD UNIT, SUPERSEDES PART D-7084(P) 1
POST PRE SL HC-SL-61-199 1
D-7085(P) ´•DOME, SPINNER 1
8-3845-8 1 I ´•SCREW 12
A-1020 I I FIBRE WASHER 12

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

ILLUSTRATED PARTS LIST 61 -1 0-1 3 Rev. 22egaPOG/nuJ10-128

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART DESCRIPTION EFF UPA

NUMBER I NUMBER I 1 1234167 CODE

D-7267(P) SPINNER ASSEMBLY

BULKHEAD UNIT 1
D-7084(P)
´•DOME, SPINNER 1
D-7266(P)
8-3845-8 ´•SCREW 12

A-1020 FIBRE WASHER 12

D-7327(P) SPINNER ASSEMBLY

BULKHEAD UNIT 1
D-7233(P)
´•DOME, SPINNER 1
D-7325(P)
-lB-3845-8 ´•SCREW 12

A-1020 FIBRE WASHER 12

ITEM NOT ILLUSTRATED

Spinner Assembly Parts

Page 10-129
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

FIG.IITEM I PART DESCRIPTION EFF IUPA

NUMBER NUMBER I 1 12345g7 CODE

A-2476-4 SPINNER MOUNTING KIT

A-2246-4 ´•SPACERS I 1 4
A-2433 HEX HEAD BOLTS 4

A-2476-6 SPINNER MOUNTING KIT

(USE WITH 835-38 8 C-3535-1 SPINNER ASSY)
A-2246-4 ´•SPACERS 6
1 A-2433 1 I HEX HEAD BOLTS 6

1 A-2476-6 1 I SPINNER MOUNTING KIT

-lA-2246-4 1 I ´•SPACERS 6
A-2433 1 I HEX HEAD BOLTS I I 6

A-2476-7 1 I SPINNER MOUNTING KIT

A-2246-3 1 I ´•SPACERS I 1 6
A-2433 1 I HEX HEAD BOLTS I I 6
8-3599 1 I FLEXLOCK NUT I 1 6
8-3834-0663 ´•WASHERS I 1 6

A-2476-8 1 I SPINNER MOUNTING KIT

A-2246-4 ´•SPACERS I 1 4
A-2433 HEX HEAD BOLTS 4
8-3599 FLEXLOCK NUT 4
8-3834-0663 ´•WASHERS 4

A-2476-9 1 I SPINNER MOUNTING KIT

-lA-2246-4 ´•SPACERS 6
1 A-2433 HEX HEAD BOLTS I 1 6
8-3599 FLEXLOCK NUT I 1 6
-IAN960-616 I I ´•WASHERS I 1 18
REPLACED BY PART NUMBER 8-3834-0663
PRE SL HC-SL-61-170
8-3834-0663 1 I ´•WASHER I 1 18
REPLACES PART NUMBER AN960-616
POST SL HC-SL-61-170

1 A-2476-14 SPINNER MOUNTING KIT

-lA-2246 ´•SPACERS 4
1 A-2433 HEX HEAD BOLTS 4
8-3599 FLEXLOCK NUTS 4

A-2476-18 1 I SPINNER MOUNTING I<IT

-lA-2246-4 .SPACER 8
A-3433 1 I HEX HEAD BOLT 8
8-3599 1 I SELF-LOCKING NUT 8
8-3834-0663 ´•WASHER I 1 8

A-2476-19 SPINNER MOUNTING KIT

A-2246-3 ´•SPACERS I 1 4
A-2433 HEX HEAD BOLTS I 1 4
8-3599 FLEXLOCK NUT I 1 4
-IAN960-616 ´•WASHER I 1 8
REPLACED BY PART NUMBER 8-3834-0663
PRE SL HC-SL-BI-170
8-3834-0663 ´•WASHER I 1 8
REPLACES PART NUMBER AN960-616
POST SL HC-SL-61-170

ITEM NOT ILLUSTRATED

Spinner Mounting Kit Parts

10-130
ILLUSTRATED PARTS LIST 61’1 0’1 3 Rev. 22egaPOG/nuJ
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1138

PART DESCRIPTION EFF IUPA

FIG.IITEM
NUMBER NUMBER I 1 1234567 CODE

A-2476-20 SPINNER MOUNTING KIT

A-2246-8 ´•SPACERS 8

HEX HEAD BOLTS 8

A-3203
FLEXLOCK NUT 8
8-3599
´•WASHERS 8
AN960-616
REPLACED BY PART NUMBER 8-3834-0663
PRE SL HC-SL-61-170
´•WASHER 8
8-3834-0663
REPLACES PART NUMBER AN960-616
POST SL HC-SL-61-170

1 A-2476-23 SPINNER MOUNTING KIT

A-2246-8 ´•SPACERS 6

A-3203 HEX HEAD BOLTS 6

8-3599 FLEXLOCK NUT 6

8-3834-0663 ´•WASHERS 6

A-2476-25 SPINNER MOUNTING KIT

-lA-2246-4 ´•SPACERS 6
HEX HEAD BOLTS 6
A-2433
FLEXLOCK NUT 6
1 8-3599
´•WASHERS 6
8-3834-0663

A-2476-26 SPINNER MOUNTING KIT

SUPERSEDED BY PART NUMBER A-2476-7
A-2476-7 SPINNER MOUNTING KIT
SUPERSEDES PART NUMBER A-2476-26
´•SPACERS 6
-lA-2246-3
HEX HEAD BOLTS 6
A-2433
FLEXLOCK NUT 6
8-3599
´•WASHERS 6
-18-3834-0663

A-2476-27 SPINNER MOUNTING KIT

´•SPACERS 4
-lA-2246-9
HEX HEAD BOLTS 4
A-3207
FLEXLOCK NUT 4
8-3599
´•WASHERS 4
-18-3834-0663

A-2476-29 SPINNER MOUNTING KIT

´•SPACER 6
-lA-2246
HEX HEAD BOLT 6
A-3207
FLEXLOCK NUT 6
8-3599
8-3834-0663 ´•WASHER 6

A-2476-32 SPINNER MOUNTING KIT

´•SPACER 4
-lA-2246
HEX HEAD BOLT I 1 4
A-3207
FLEXLOCK NUT 4
8-3599
´•WASHER 4
8-3834-0663

ITEM NOT ILLUSTRATED

Spinner Mounting Kit Parts

Page 10-131
ILLUSTRATED PARTS LIST 61-10-13 Rev. 22 Jun/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 113B

(This page is intentionally blank.)

I ILLUSTRPITED PPIRTS LIST 61 -1 0-1 3 10-132

10
 114B

G
unuFEbr
CONTENTS
MODELS
HC-8( )X Series; HC-A( )X Series
HC-9( )Z Series; HC-9( )W Series
HC-B( )Z Series; HC-B( )W Series
HC-A( )V Series
I. MODEL DESIGNATION
II. DESCRIPTION
III. PROPELLER INSTALLATION INSTRUCTIONS
IV. GOVERNORS
V. DISASSEMBLY INSTRUCTIONS
VI. INSPECTION
VII. REPAIR AND REPLACEMENT
VIII. ASSEMBLY
IX. BALANCE
X. WEAR TOLERANCES
XI. LUBRICATION
XII. SERVICE TROUBLES
XIII. PARTS LIST
XIV. CUTAWAY VIEWS OF TYPICAL ASSEMBLIES

NOTE:

C FI*

FAA
FAA

MARCH. 1962

REPRINTED AUGUST. 1965

REPRINTED SEPTEMBER. 1970

 RECORD OF REVISIONS

Manual 114B
MFG REV
NO DESCRIPTION ISSUEDATE ATPREVDATE INSERTEDBY

Reissued 911 970 ATP

 RECORD OF TEMPORARY REVISIONS

p ATP REV INSERT DATE REV REMOVE

REV NO DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY

 INTRODUCTION

The present manual is for the purpose of ena-

bling the mechanic to overhaul propellers only. It
does not cover installation, operating instructions, or
service instructions; as these subjects are covered by
separate owners manuals which are furnished to the
owner.

The purpose of this manual is to up date or

supplement Manuals 101 and 103 which are now out

of print, and to cover a number of newer propeller
models not previously covered in 103 or other
manuals.

The propellers covered in this manual are all

similar in construction and operation; hen’ce, it is
possible to describe the important methods of over-
haul which are common to all without endless rep~eti-
tion. In order to accomplish this end, references are
made to part names throughout the discussion; the
part numbers are omitted. Each propeller, however,
is covered in the parts list; and there are representa-
tive cut-away drawings given to illustrate the basic
features.

This manual may be updated at any time´• in the

future by adding new parts lists as they become
available.

Other manuals covering similar propellers are

listed as follows:

Manual Number Propellers Covered

105 HC-92ZF-2, K-2A; HC-92WK-2A:; HC-92WF-2A
108 HC-B3Z30-2E; HC-B3W30-2E
109 HC-ABXF, K, L-2; HC-ABVF, K, 20-2
110 HC-92ZF-1, K-8 HC-92WK-1
112 HC-B3Z30-2B; HC-B3W30-2B
118 HC-B3TN-2, -3, -5 (Turbo-prop)

j.
 SECTION I

MODEL DESIGNATION

Hartzell Controllable

I Basic Hub Model Designation

I I Specific Design Features

1_ I r
BHC-AZXF-1D1

II Equipped with A-14-B Bearings

I
I
Removable Guide Collar (-1, -8 only)

-1 Constant Speed Counterweight Type

-6~-Constant Speed, No Counterweight
-sl
-2 Feathering
-3~Reversing and Constant Speed
-51
-4 Constant Speed, No Counterweight
F, 4" Bolt Circle Flange
G, SAE No. 2 (s/8 bolts) Flange (Obsolete)
L, SAE No. 2 (7/16 bolts) Flange
Hub Mounting Provisions K, SAE No. 2 (~z bolts) Flange
20, SAE 20 Spline
30, SAE 30 Spline

I X, Double Shoulder
Blade Shank
Z, Single Shoulder
I V,Double Shoulder, Needle Bearings
Number of Blades
)W, Single Shoulder, Needle Bearings

8, Light Hub
A, Same as 8 Except With Split Bearing Retention
Basic Hub Design
9, Heavy Hub
B, Same as 9 Except With Split Bearing Retention

Location of Dowel Pin in "F" Flange

’;o ~bR )jE N

NOR BLANK
FOR j~))
,~,I
BLRNX
BLADEs i; \BLADE
iOA ~E" T/e FOR ~pl)

sP

DPWEL P/N LdGA;r/ONS F~OR DOWEL PIN LOCAT/ONS FOR

IWO 8 LADE PROPL~LLIRS. THREE BLADE PROPELLERS.
REAR YIZW OF PROPL~LLIR REAR VIEM/ OF PROPELLER
 SECTION II
DESCRIPTION
MODELS HC-8( )X( HC-A( )X(
HC-9( )Z( HC-B( )Z(
CONSTANT SPEED FEATHERING REVERSING

A. CONSTRUCTION The HC-9( )Z( models are also manufac-

The constructii~n of all
tured in 2 and 3-blade versions, constant speed and
propellers in this series is
similar, in that the hub consists of a central spider fe"thering; but not reversing. It is made with the
which is fastened to the engine shaft, and which F, K, 20, and 30 spline shaft mounting.
supports the blades with a tube extending up inside The HC-B( )Z( models are manufactured in
of the blade roots. Blade clamps connect the blade 3-blade versions only, constant speed and feathering,
shanks with the blade retention bearings. A hy- and with provisions for F, K, 20, and 30 spline shafts.
draulic cylinder is mounted on the rotational axis, and This series is similar to the HC-9( )Z( series
is connected to the blade clamps for pitch actuation. except it incorporates the later split bearing retention
The hub parts system.
are made of steel forgings; while

the blades are generally made of aluminum forgings. The HC-A( )V( models are similar to the
HC-A( )X(models except needle bearings are
B. CONTROL installed in the blade shanks replacing a portion of
the bronze bushings.
Governor oil pressure which is
piped to the
propeller through the engine shaft is used to change HC-B( )W(
The models are similar to the
pitch in one direction; while centrifugal forces acting HC-B( )Z( models except needle bearings are
on the blades and weights attached to the blade installed in the blade shanks replacing a portion of
clamps are used to change pitch in the opposite direc- the bronze bushings.
tion. Propellers employing counterweights, attached Propeller installation instructions, operating in-
to the blade clamps, utilize governor oil pressure to
structions, and service instructions are contained in
reduce blade pitch, and centrifugal force to increase the owner’s manual and will not be duplicated here.
pitch. Propellers not employing counterweights util-
ize governor pressure to increase pitch while centri-
fugal twisting moments acting on the blades to reduce
pitch. SECTION III
Penthering propellers utilize oil from the gover-
nor pitch and counterweights plus a spring
to reduce PROPELLER INSTALLATION
to feather. Feathering is accomplished in the absence INSTRUCTIONS
of governor pressure.

Reversible propellers are similar to the feather- TABLE I. SPECIAL TOOLS

ing propellers, for pitch actuation from low pitch to Part No. Nomenclature
feathering pitch. In order to go from low pitch to
461 Spanner Wrench, 831-12 Spring
reverse pitch, a second oil system is incorporated,
Assembly
independent of the governor control; which is put B-840 Shaft Nut Wrench For ~3AE 20 30 Spline
into play by a manually actuated valve. Oil pressure B-842 Wrench for A-880-1 Nut on Spring
applied to this second oil line moves the pitch from Assembly
low position to reverse position. B-842-1 Wrench for A-880-2 Nut on Spring
Draining the oil
allows the feathering spring to move the pitch from
Assembly
B-844 Tool for Pressing Pilot Tube into Hub
reverse to low.
Spider
C-845 Fixture for Assembly of Feathering
C. MODELS Spring
Propeller Table
The HC-8( )X( models are manufactured in Propeller Table, 30 Spline Spindle
2 and 3-blade versions, constant speed feathering, Balancing Equipment, Wire or Arbor
and reversing, and for all types of shaft mountings BT-222 Assembly Tool for Pressing A-1852
shown in the Model Designation diagram except 30 Ring on C-1853 Hub Spider
BT-222-1 Assembly Tool for Pressing A-972
spline.
Ring on C-982 Hub Spider
The HC-A( )X( models are similar to the BT-223 Puller Tool for A-1852 Ring
BT-223-1 Puller Tool for A-972 Ring
earlierHC-8( )X( series exceptthe blade bearing
SK-274 Piston Fixture Used for Balancing
retention has been changed to the split bearing type.
 SECTION IV
GOVERNORS

There are three governor types which can be Fl These are surplus governors, overhauled and
used with the propellers listed in this manual. modified to suit the various applications.

A. Woodward 210,000 Series C. Hoof 1,000,000 Series.

B. HartzellModelsB-( C-( D-( and

SECTION V

DISASSEMBLY INSTRUCTIONS

In view of the fact that this manual covers a removing the wire ring from the groove.
large number of propeller models, the instructions
(3) Using special tool BT-222-1, combined with
will be given in general terms applicable to all models.
BT-223-1, push guide ring in slightly towards center
1. Install the propeller on a propeller bench hav- of the hub only enough to uncover wire ring, which
ing provisions to receive the particular engine shaft can be removed. Using tool BT-223-1, pull guide
in question. ring from hub. Remove outer two halves of bearing.
2. Remove the hydraulic piston and pitch actua-
ting linkage systems. (b) HC-B( )7, HC-B( )W Series.
3. Remove the blade clamps. Same as (a) above except for the use of BT-222
and BT-223 tools.
4. Remove the blades from the hub spider.
6. Feathering spring sub-assembly (fe´•athering
5. Remove the blade retention bearing races and reversing propellers only).
rom the hub spider. In the case of the HC-8( )X
and HC-9( )Z series propellers, removal of the bear-
ings is quite simple and obvious; however, in the case
of the HC-A( )X and HC-B( )Z series, removal of CAUTION
the bearing from the hub spider requires the use of
special tools. (See Manuals 108 and 109.)
Do not attempt to disassemble the feathering
(a) HC-A( )X, HC-A( )V Series. spring sub-assembly unless special tool No.
C-845 is available. With this tool, the
(1) Remove the balls from bearings.
assembly can be compressed until the retain-
(2) Remove the inner races of the bearing by ing rings are free.

SECTION VI
INSPECTION

(a) Inspect all wearing parts according to tol- ticularly around the shank retention area and at the
erances specified in TABLE II. Replace parts not leading edge near the tip.
coming within specified limits.
(f) Inspect the bearings for excessive wear or
(b) Inspect the blades according to the toler- chafing. A certain amount of marking of the balls
and races is to be expected and is not necessarily a
ances in TABLE III. Replace a blade which falls
reason for replacement. Only when the bearings
below the listed minimum dimensions upon repair.
show pit marks which are .002" deep and definitely
(c) Visually inspect all metal surfaces. Replace fee´•l rough, are the balls or races to be replaced.
or refinish any bearing or wear surface which has a Bearing life ordinarily is greater than 1000 hours.
visible nick, dent or other distortion.
(g) Inspect pilot tube for slippage. The tube
should extend out from hub 3~7/4, inches only. If this
(d) Magnetically inspect all steel parts for
cracks not visible to the eye. distance is greater, the indication is ths~tthe tube has
slipped out of the hub spider.~ An oversize tube
(e) Visually inspect the blades for cracks, par- should replace the one which slipped.
 SECTION VII
REPAIR AND REPLACEMENT

(a) Remove all rust, galling marks and nicks bolts, hub, and clamp parts are particularly
from the hub spider arms with crocus cloth or fine susceptible to this effect. Failure of the
emery. Rust, galling and nicks are stress raisers part may result unless this baking is accom-
which reduce the fatigue life of the hub. Do not plished. If proper plating facilities are not
polish unless necessary, as the spider arms have been available, the parts should be painted with
rolled to improvethe fatiguestrength. (The~ roll a suitable aluminum or lacquer paint.
marks are not tool marks and should not be removed.) (f) Repair blades according to Fig. 1.
If the blade pilot tube is to be replaced in the hub, due (g) Blade bushings. If the blade bushing is
either to excessive v~2ar, or due to the fact that it has worn b´•eyond specified tolerances, the blades should
slipped out slightly from the spider, it is necessary to be returued to the factory to be rebushed. These
use a new tube having a .002" to .003" oversize di- bushings seldom wear, however, to the point where
ameter over the 2Ys" length which presses into the they must be replaced.
hub spider hole. Press the new tube into the hub (h) Recommended Overhaul Procedures Re-
spider leaving exactly 33~ inches of the length ex- garding Replacement of A-14 Bearings and A-159
pose~d. Be sure~ the heavy end of the tube is inserted Split Rings.
into the hub. Test the tube for tightness by applying
HIartzell Models: HC-83XF-1A; HC-83XF-3A,
5000 Ib. force on the tube. If it slips with this force,
it must be replaced with a larger tube of say .003" to
3AL, 3B; HC-83X´•20-1A, -1B, 1C; HC-8ZXF-1DB;
HC-82XF-2B, 2C; HC-82XK-2B, 2C; HC-83X20-2C;
.004" oversize.
HC-83XF-2A.
(b) Replace the counterweight mounting screws.
Use only the specified parts as they are heat treated 1. The above propellers originally were manu-
to a high strength, factured with A-14-A bearings and A-159 split rings.
(c) Replace all gaskets, "0" rings, and cotter The present overhaul procedure´• calls for replacing
pins. the split rings at overhaul.
(d) Nicks or deep scratches in cylinder may be 2. These basic propellers are now approved also
cause for replacement, particularly if the marks are with the A-14-R bearings and A-969 split rings. Since
in the region of the piston "O" ring during normal the A-969 split ring is heavier than the A-159 split
cruise-flight. Scratches in the feathering region may ring, it is not necessary to follow the practice of
be tolerate~d if not too deep. replacing them at subsequent overhauls.
(e) Replating (cadmium) of steel parts is rec- 3. We recommend that during overhaul, if thF´•
ommended if the original plating has been worn off or A-14-A bearings must be replaced due to wear; the
if damaged by nicks or scratches. be replaced with the A-14-B bearings. Then the
A-159 split rings must be replaced by the A-969 split
rings, in order that these parts fit togethe~r properly.
CAUTION
4. Upon making this modification, the figure "1"
is added to the dash number, as: HC-83XF-1A be-
The hub spider arm and pilot tubes should comes HC-83XF-1A1.

be masked. After plating the parts, they 5. This practice of updating propellers is being
must be baked in an oven at 350" F. plus or practiced in our overhaul department. It is re´•com-
minus 25" for 3 hours to eliminate possibility men´•ded that it be followed by all field service stations
of hydrogen embrittlement. High strength also.

Figure 1. SKETCH OF TYPICAL NICKS AND METHOD OF REMOVAL

5-~

Recommended method
for removinff nicks by SECTION AA--Niek in
riffle file and orocus
f"ce of blade removed
by file and crocus cloth
Exaggerated view of cloth. Blend deepest
ils recommended.
A
nicks inleading edge. portion of nick into lead-
ing edge aligmnent with Exaggerated view of
smooth cu~res. nick in face of blade.
 SECTION VIII
ASSEMBLY

(See representative assembly drawings for parts Propeller Model HC-AZXF-I and BHC-ABXF-1:
position) Install Ii/a inch long dowel pins in "A" location of
the mounting flange for HC-ABXF-1 propellers and
The description of the assembly will be general 7/8 inch long dowel pins in "A" location for
since it is intended to cover a variety of as~emblies. BHC-AZXF-1 propellers as shown below.
Certain important details which are common to all
models will be spelled out precisely.

A. ASSEMBLY OF GUIDE COLLAR UNIT ON HUB

(Constant speed propellers only)
(a) Constant speed propellers having "F", "L",
(Por HC-A2XF-1) IS
"K" flanges.
(p,r BHC-APXF-1)8
1. Install guide collar unit on hub spider, using .soor oln.
socket head screws to clamp halves together. Before DOWEL PINS

screws are tightened, line up the notch in the collar

unit with the dowel pin hole in the hub spider.
Tighten screws to 2-4 ft. Ib. torque.
2. Insert dowel pin in flange from rear, until it
enters the notch machined into guide collar.
8~4-4 GUIDE COLLAR

CAUTION

(b)Constant speed propellers having 20 spline

For HC-ABXF-1, HC-92ZF-1, and some shaft. The guide collar unit used on the 20 spline
HC-82XF-1 propellers only, the dowel pins propellers may be either of two types (1) clamping
used for installing the propeller are 13/8 type and (2) integral with spinner hub. In either
inches long and are usedalso to stake the case, these can be installed on the hub or propeller
guide collar, installed in "A" location, table spindle at the start of the build up.
For BHC-AZXF-1, BHC-92ZF-1, and some
HC-82XF-1DB propellers, short aluminum B. ASSEMBLY OF BEARINGS ONTO HUB SPIDER
pins are inserted in the "A" dowel pin holes
to stake the guide collar; while 1 inch long
(a) HC-8( )Xand HC-9( )ZSeries.
steel dowel pins are installed in the "B" 1. Install proper "O" ring over hub spider arms
holes for installing the propeller on the past the "0" ring grooves.
engine.
2. Install blade bearing--THIN RACE FIRST.
NOTE: HC-92ZF-1 is covered more completely in
Manual No. 110. 3. Install proper split ring. These are paired
"nd Stamped accordingly.
Propeller Model HC-82XK-ID--Be sure the
dowel pin A-1332-2 is a drive fit thru the hole in the 4. Press bearing over split ring against split ring
flange of the propeller hub, and securely engages the shoulder.
notch which is milled into the 834-9 guide collar as
shown below. 5. Roll "O" ring into groove.

(b) HC-A( )X and HC-B( )Z series.

1. Mount hub spider on propeller table.
2. Using special tool BT-222, combined with tool
BT-223, push guide ring onto hub spider bearing
PROPELLER MOVNTING FLANGE I retention flange. The chamfered end of ring must
face the center of the hub, and the counterbored end
face out. Push ring until the inner edge overhangs
the inner flange face of hub spider by about 1/16-inch.
This provides nest to fit the two halves of outer
a

bearing Unscrew tool BT-223 about ~iL inch to

race.
V allow for inserting outer bearing race in nest provided
A-1332-2 PIN --Il
by ring. Adjust BT-223 so that fingers press against
COLLAR
bearing race and BT-222 presses against ring. Screw
e34-9 GUIDE
ring further onto hub and bearing race until the
groove in flange is uncovered.
 NOTE: The pitch will be set after the propeller
CAUTION G~ is completely assembled, after which the clamp bolts
will be torqued and safetied.

It is important that the two bearing halves (e) Install the lubricator fittings and high sto~
be matched perfectly at the fractured sur-
plates if propeller is feathering type.
faces and held flat against the inner face of
(f) Check for friction or binding of the blades
the hub flange when the ring is force´•d into when rotated about their axes. If the blades tend to
place. bind after the bolts are tightened, it will be necessary
to remove the clamps and blades and relieve the fric-
3. Insert wire ring in grove. tion, whatever the cause; whether it be friction be-
tween blade and pilot tube or friction between the end
4. Remove tool BT-222 and install tool BT-223
of the blade and the end of the hub spider arm.
so that fingers rest against inner edge of ring. Pull
ring out over the wire ring.
D. INSTALLATION OF CYLINDER
5. Install "O ring over hub retention arm, in
towards the center of the hub as far as possible. (a) (Two blade feathering propellers and 2 and
3-blade constant speed propellers only.) These
6. Install inner bearing race; hold halves to- mode!ls generally do not have guide collars installed
gether with wire ring. back of the cylinder except for the 20 spline version;
hence the cylinder can be installed on flange mounted
IMPORTANT: Locate bearing parting line fore
and aft or parallel with hub shaft axis. propellers by inserting the "0" ring in the groove
provided, and screwing the cylinder into place. (Use
7. Fill bearings with balls. Pack with grease, non-hardening gasket compound in threads.) Torque
about 200 ft. Ib. using a bar in the slot provided.
8. Roll "O" ring out against bearing race.
(For 20 and 30 spline shaft mounted propellers)
9. Wrap masking tape around outside of bearing
These mo´•dels have the hub nut and puller ring in-
and ring so the balls will not fall out. This will be
stalled in the hub before the cylinder is installed.
removed when clamps are installed.
(b) (Three blade and two blade 20 spline
C. ASSEMBLY OF BLADES ONTO HUB SPIDER feathering propellers) These propellers have guide
collars installed back of the cylinder, which must be
NOTE: In order to assemble the propeller and
installed when, the cylinder is installed. Install "O"
set pitch accurately, it is highly advantageous to use ring in groove provided and screw cylinder on hut
a special propeller table having a shaft which mates
using gasket compound on threads. Torque to about
with the propeller hub flange. Air or oil pressure 200 ft. Ib. using bar in slot provided.
(100 psi min.) should be available in the shaft to
actuate the piston. (For 20 and 30 spline propellers) These models
have the hub nut and puller ring installed in the hub
(a) Mount the hub on the propeller table shaft. before the cylinder is installed.

(b) Fill the blade pilot tube hole with a grease

E. INSTALLATION OF FEATHERING SPRING
as specified under "Greases Recommended."
(For feathering propellers only)
NOTE: Be sure no air is trapped below the
grease as this will upset the balance. NOTE: In order to assemble a feathering spring
sub-assembly, it is important that asafe means for
(c) Install blade the~ same pilot tube from
on compressing the springs are used. This can be done
which it was removed. Place a hardening gasket best with special tool No. C-845.
compound (commercial automotive type) around the
blade shank in the shoulder radius. (a) Install spring assembly onto cylinder with
provisions available for each model, viz. split rings or
(d) Install the correct matching clamp and screw threads.
counterweight sub-assembly with new clamp gaskets.
F. INSTALLATION OF PISTON
NOTE: For split bearings only. This process can
best be accomplished by peeling back the masking (a) Feathering propellers
tape from about 180" of the bearing on the top side.
Then install the one-half of clamp that has the 1. Install link arms in piston. Install link pin
counterweight. Then peel the tape from the lower half unit and safety screw. Wire safety the latter.
of the bearing which is exposed, and install the other
2. Check link arms for free movement in piston
clamp half. Slip the clamp gaskets between the
slots.
clamps at the parting line. This procedure will locate
the inner bearing race parting line at right angles 3. Install a new "0" ring and felt seal into the
with the clamp parting line WHICH IS ESSENTIAL. grooves in piston. Soak the felt seal in oil. Oil the
"0" ring.
Fasten the clamp halves together with socket
4. Oil the cylinder and "0" ring at end of pilot.
screws, bolts, washers and nuts. Tighten soc.ket tube.
screws and nuts and check for friction of the blade
when being rotated on the hub. 5. Slide the piston onto cylinder.
 6. Rotate piston so the free ends of the link arms grease is added. Balance with pitch about midway
can be assembled over link screws. between low and high pitch.

7. Insert link screw sleeve between screw and (b) Either a suspension system or an arbor
lold in link arm. Insert cotter pin. mounted on knife edges may be used for balancing.
In the event the suspension system is used, it is es-
8. Move piston into full feathered position (back
sential that the center of gravity of the propeller be
against the hub assembly) so that the threaded end
located at or slightly below the pivot of the balance
of the pilot tube protrudes through the end of the
piston. Screw the nut onto pilot tube. Torque the equipment; otherwise inaccuracies will result.
nut to 75-100 Ib. ft. Restrain the pilot tube from
(c) Remove the end play from the blade clamp
turning by applying asocket wrench to the hex
assemblies by driving identical small wedges between
located at the end.
the blade clamps and hub spider, at identical loca-
tions.
(b) Constant speed, non-feathering propellers.
(d) Bolt propeller to balance arbor, or wire
i. Install new "0" ring and felt seal in piston. balancer.
Oil these parts.
2. Fit new pitch change block snug in fork and
NOTE: The following balance procedure applies
install block on linkscrew.
only to balance arbor method.
3. Install piston assembly over cylinder, feeding
guide rods through forks, and sleeves, which must be
fitted into the bushings of guide collar. Install washer Check horizontal balance by laying slugs in
(e)
of blade and clamp. Record number of slugs
and nut onto rod. Torque to 20 ft. Ib. corner

required for balance.

4. Tightellset screw 2-3 ft. Ibs. torque. Prick
punch around set screw to safety. (f) With the propeller in horizontal position,
apply 50-100 Ib. downward force to each blade tip.
G. SETTING BLADE PITCH This takes up the clearance between hub and blades
in one direction.
(a) Loosen outer clamp screws only.
(g) Check vertical balance with heavy blade up.
(b) With air pressure,pitch on both
set low
Add weight slugs to light side of clamps. Record
blades per aircraft specification. Tighten outer number required for balance.
clamp screws. See Tables of Torque Values.
(c) Without air pressure, increase pitch to high (h) Rotate blade 180" from horizontal position
noted in "f" above and apply 50-100 Ib. to each
stops and check blade angle, as

blade tip. This takes up the clearance opposite to

(d) Check the blade against turning in the that noted under "f".
clamp by torquing the blade to 167 ft. Ib. Use a blade
bar and a weight attached to the end. If the blade
(i) Again check vertical balance. Record num-
moves, or rocks in the clamp, the clamp
must be re-
rectified. Experience has ber of weight slugs.
moved and the difficulty
shown that the clamp gaskets may prevent the clamps
from tightening on the blades. These gaskets can be (j) The final number of weight slugs can now be
trimmed at the outer hole slightly to allow the clamp determined for vertical balance. If the slugs under
to come together closer. Also, the outer corner of the "g" and "i" are added to the same side of the blade,
clamps might require filing by .005-.010 inch. (Coat th, total slugs required for vertical balance is the
filed area with aluminum lacquer.) (Bulletin 69 also If the slugs under "g" and
average of "g" and "i".
covers this subject.) "i" are added to opposite sides of the blade the dif-

(e) Check the blade angle in low pitch again, ference between the two numbers is added to the side
as torcluing of the blade may have moved it. requiring the greatest number.

(k) Horizontal balance determined under "e"

H. CHECK FOR GENERAL OPERATION,
must be maintained by properly dividing the slugs
FRICTION AND LEAKAGE
required under "J between the two blades.
(a) Cycle the pitch for possible friction.
(1) Attach the slugs to the clamps with scre´•ws
(b) Hold full pressure on piston and check for and again check horizontal balance. Safety with
leakage past the piston "O" ring and cylinder "O" wire. Do not attach more than 4 slugs with each pair
ring. Spread oil around these points as air bubbles of screws.
will indicate leakage.

SECTION IX (m) Add equal amounts of grease to each blade,

holding horizontal balance constant, until clamps are
RALANCE completely full, as evidenced by grease starting to
come out around circumference of hub spider at "O"
(a) B alanc e the propeller assembly before ring. Avoid blowing out "0" ring and gaskets with
grease is added to the clamps, and check again
after excessive pressure.
 TABLE II. TOLERANCES OF WEARING SURFACES

Replace if dimension
Specified is above or below
Max. Min. Max. Min.
1. A-158 Pilot Tube O. D. (HC-8( )X series.) HC-A( )X 1.4990 1.4987 1.4977
la. A-1496 Pilot Tube, Inner End ("V" Shank) 1.499 1.4985 1.497
Ib. A-1496 Pilot Tube, Outer End ("V" Shank) 1.252 1.2515 1.250
2. A-1308 Pilot Tube O. D. (HC-9( )Z series.) HC-B( )Z Inner 11/4,inch 1.7185 1.7180 1.7165
Outer 1 inch 1.7203 1.7197 1.7185
2a. A-1884 Pilot Tube, Inner End ("W" Shank) 1.7185 1.718 1.7165
2b. A-1884 Pilot Tube, Outer End ("W" Shank) 1.376 1.3755 1.374
3. Distance Pilot Tube extends beyond hub tall models)
33/4~+1/16 33/4~-1/16 3~ 1/8
4. Blade bushing I. D. (HC-8( )X series.) HC-A( )X 1.5015 1.5005 1.5030
4a. Blade Needle Bearing "V" Shank) 1.253 1.252 1.254
5. BladeBushingI.D. (HC-9( )Z series.) HC-B( )Z 1.7225 1.7215 1.724 5:
5a. Blade Needle Bearing (’LW" Shank) 1.377 1.376 1.378
3
6. All pistons, A-862 bushing I. D. 3.782 3.780 3.790 p in
M
7. C-852-1 Piston Pin Hole I. D. .3765 .3755 .3795 c? n
oo 8. All pistons having A-946 Bushing I. D. .3765 .3755 .3795
9. Cylinder B-854, B-806
r0
3.778 3.776 3.773
10. B-855 Pilot Tube diameter tall flange mounted Feathering propellers) .985 .984 .980
11. B-868 Pilot Tube diameter O. D. .735 .734 .731
12. A-856 Mushroom I. D. .988 .986 .993 ~j
in
13. A-871 Mushroom I. D. .738 .736 .741
14. A-866 Spring Retainer O. D. 1.248 1.240 1.235
14a. A-866-2 Spring Retainer O. D. 1.411 1.402 1.397
15. A-857 Spring Retainer O. D. 2.243 2.241 2.237
16. B-1402, B-892, B-824, 834-4 Guide collar bushing I. D. .510 .508 .515
17. A-861 Link arms, small end tall models) .3755 .3750 .3785
18. A-861 Link arms, large end I. D. (Used with A-944 bushing) .5635 .5625 .5645
19. A-944 Bushing I. D. .502 .501 .504
20. A-944 Bushing O. D. .5602 .5615 .5600
21. A-304, A-7-1, Link screw O. D. .5005 .4995 .4970
22. Balance Tolerance 1 slug A-48 or A-1305
23. Blade Track or or 1/16 or 1/8 between blades
24. Blade End Play .060
25. Fore and Aft Movement of Blade Tip .100 max., no grease
 TABLE IV. TORQUE VALUES

+11 torques are values based on non-lubricated threads. Tolerance on torque is t 10’i: unless otherwise stated.

Model MC-82X; HC-83X, WC-A2X, HC-A3X,W Series

Part or Torque Torque

Bolt Size Location on Hub Lb. Pt. Lb. In.

3/8 24 I’G" Flange Mounting 30 360

7/16-20 "L" F’lange Mounting 50 600

1~L 20 ’LF" and "K" Flange Mounting unless specified otherwise 60 70 720 840
A-63B Shaft Nut, 20 Spline~ ;1 450 5400

3/8 24 Outer Blade Clamp Bolts ANG-2.1A,(See Addendum below) i 22 264

3/8 24 Inner Blade Clamp Socket Screw 40 480

7/16 20 Counterweight Socket Screw 65 780

-24 Flexlock Nut, End of Push Rod, Non-Fe´•a.thering 20 240
7/16
10 32 Set Screw in Pitch Change Fork, Non-Feathering 2 3 24 36

1/2 20 A-304 and A-295 Linkscrew 45 50 540 600

-20 A-7 Linkscre~w 35 40 420 480
7/16
1~ 28 834-4, -8, -9 Guide Collar Unit Flange Mounted, Non-Feathering 8 10 96 120
Socket Screw at End of Guide Rods, Feathering Prop 10 120
5/16 24
A-880-1, -2 Nut, at Front of Piston, Feathering 75 100 800 1200

1~ 28 834-3 Guide Collar Unit (B-824 Clamp) 10 12 120 144

l/q, 28 834-1 Guide Collar Unit (B-824 Clamp) 4 48

Parts to be checked for slip

B-824 Guide Rod Clamp Mounted on Hub 150 200 2800 2400
3lade Blade~ Installed in Blade Clamp 167 2000

Model HC-92Z,V; HC-93Z; HC-B2Z; HC-B3Z,W Series

Part or Torque Torque

Bolt Size Location on Hub Lb. Pt. Lb. In.

"F" and "K" Flange Mounting unless specified otherwise 60 70 720 840
1/2 20
A-63B Shaft Nut, 20 Spline 450 5400
B-1814 Shaft Nut, 30 Spline 600 7200
Outer Blade Clamp Bolt 60 65 720 780
7/16-20
3/8 20 Inner Blade Clamp Socket Screw 40 480
7/16 20 Counterweight Socket Screw 65 780
Flexlock Nut, End of Push Rod, Non-Feathering 20 240
7/16 20
10 32 Set Screw in Pitch Change Fork, Non-Feathering 2 3 24 36

1/2 20 A-304 and A-295 Linkscrew 45 50 540 600

1~ 28 834-4, -8, -9 Guide Collar Unit, Non-Feathering, Flange Mounted 8 10 96 120
24 Socket Screw at End of Guide Rods, Feathering 10 120
5/16
-2 Nut at End of Piston, Feathering 75 100 800 1200
A-8´•80-1,
l/g 28 834-1, -7, Guide Collar Unit 4 48

Parts to be checked for slip

Blade Blade Mounted in Blade Clamp 167 2000

ADDENDUM NO. 1 3/8 24 Outer Clamp Bolt alternate is 12 point head type.
(35 Ib. ft. torque or 420 Ib, in. torque)
 TABLE III. BLADE REPAIR TOLERANCES

Angle li‘ace Alignment Width" Thickness’

Radius Min. Max. Min. Max. (Min.) (Min.
7636D, -2, -4 Blade
9 4.700 1.980
12 5.572 1.095
18 41" 42" .138 .202 5.702 .666
24 37" 37.6" -.072 -.008 5.312 .449
30 33.2" Setup -.192 -.128 4.450 .319
36 29.8" 30.2" -.242 -.178 No Limit No Limit

8433-6, -7, -10, -12 Blade

9 4.700 1.980
12 5.720 1.095
18 41" 42" .138 .202 6.200 .625
24 37" 37.6" .072 i.008 5.985 .471
30 33.2" Setup -.192 .128 5.380 .337
36 29.8" 30.2" .242 -.178 No Limit No Limit

8433, -2, -4 Blade

9 4.700 1.980
12 5.720 1.095
18 41" 42" .138 .202 6.200 .625
24 37" 37.6" -.072 -.008 6.800 .473
30 33.2" Setup -.192 -.128 5.460 .341
36 29.8" 30.2" -.242 .178 4.200 .234

8833, -BBlade
9 4.700 1.980
12 5.726 1.095
18 31.1" 32.1" .103 .167 6.310 .692
26 24" 24.6" -.082 -.018 6.070 .472
32 20" Setup -.164 -.098 5.450 .340
38 16.8" 17.2" .242 -.178 4.190 .233
9333~, -3 Blade

91/2 4.704 1.980

13 5.720 1.095
20 41" 42" -.122 -.058 6.307 .693
28 36.5" 37.1" -.472 -.408 6.070 .472
34 33.2" Setup .682 -.618 5.450 .376
40 29.8" 30.2" -.832 -.768 4.200 .286

8447, -12A, 8447A-12A Blade

8 4.052 2.649
12 5.587 1.304
18 31.10 32.1" .158 .222 6.340 .799
24 25.7" 26.3" -.032 .032 6.123 .518
30 21.9" Setup 21.9" .152 -.088 5.462 .355
36 18.8" 19.2" .232 -.168 4.203 .263
8847 Blade
8 4.038 2.660
14 5.842 1.304
20 30.5" 31.5" .158 .222 6.307 .799
26 25.5" 26.1" -.047 -.017 6.110 .517
32 21.9" Setup 21.9" -.152 -.088 5.450 .355
38 18.8" 19.2" -.242 .178 4.188 .233
10151-8 Blade
18 .293 .357 6.071 .922
24 32.9" 33.5" .038 .102 6.306 .690
30 29.4" Setup 29.4" -.122 -.058 6.175 .516
36 25.6" 26.0" -.242 -.178 5.655 .422
42 22.6" 23.0" -.357 -.293 No Limit No Limit
12 5.355 1.501
8 4.043 2.854
All Minimum Requirements. Exclude 36

10
 Angle Face Alignment Width* Thickness*
Radius Min. Max. Min. Max. (Min.) (Min.)
10133D-3 Blade

91/2 4.704 1.983

12 5.355 1.501
18 39.0" 40.1" .293 .357 6.071 .922
24 32.9" 33.5" .038 .102 6.300 .691
30 29.4" Setup 29.4" -.122 .058 6.188 .517
36 25.6" 26.0" -.242 .178 5.695 .425
42 22.6" 23.0" -.357 -.293 4.645 .318
48 19 9" 20.3" -.532 .468 No Limit No Limit

10152-51/2 Blade
8 3.870 2.890
12 4.825 1.610
18 .393 .457 5.500 1.120
24 32.9" 33.5" .088 .152 5.816 .802
30 29.3" Setup 29.3" -.122 -.058 5.982 .580
36 25.8" 26.2" -.242 -.178 5.655 .430
42 23.3" 23.7" -.357 -.293 4.514 .330
431/2 .315
441/2 .285
451/2 .247
46~2 .208

10160-6 Blade
8 3.870 2.890
12 4.825 1.775
18 .428 .492 5.500 1.198
24 32.9" 33.5" .088 .152 5.816 .812
30 29.3" Setup 29.3" -.092 -.028 5.982 .630
36 25.8" 26.2" -.217 -.153 5.666 .476
42 23.3" 23.7" -.347 -.283 4.532 .365
431~ .345
44j~ .308
4Sj~ .261
46 .225

9349 Blade
8 4.045 2.870
13 5.720 1.095
20 41" 42" -.122 -.058 6.310 .693
28 36.5" 37.1" -.472 .408 6.097 .472
34 33.2" Setup -.682 -.618 5.450 .376
40 29.8" 30.2" -.832 .768 4.200 .286

9350 Blade
8 4.045 2.870
13 5.720 1.095
20 41" 42" .108 .172 6.310 .693
28 36.5" 37.1" -.122 -.058 6.097 .472
34 33.2" Setup -.222 -.158 5.450 .376
40 29.8" 30.2" -.262 -.198 4.200 .286

All Minimum Requirements.

SECTION XI
LUBRICATION
A. GENERAL PROPERTIES OF GREASE (c) Freedom from separating oil from soap
REQUIRED base due to centrifugal force or high temp-
erature.
Any grease used must have the following Low Friction.
(d)
properties
B. LIST OF APPROVED GREASES, by spec, or name
(a) Waterproof. 1. Hartzell DG Grease (rated at~100" to
(b) Temperature range between -15" F. and ~L165" F.)
150" F; or -40" to 100" F if operation is 2. Stronnrs´•HT-l (Z-801 Grease)
in cold climate. Union Oil Co. of California

11
 3. Gulflex A 8. Lubriplate 707
This grease is recommended for the blade ball F’iske Brothers, Toledo, Ohio
bearings as it will not bleed oil in hot weather. 9. Mobilgrease Aero Lo-Hi PD-535-K
4. RPM Aviation Greas~ No. 2 Socony Vacuum Oil Co.
10. No. 84 Medium Grease
Standard Oil Co. of California
Keystone Lubricating Co.
5. Stroma LT-1 (2-815 Grease) 11. Texaco Regal Starfax Special
Union Oil Co. of California 12. Molub-Alloy No. 2 Grease -10" F.
6. Lubriplate 630 AA No. 1 Grease -25" F.
Fiske Brothers, Toledo, Ohio Imperial Oil Grease Co.
This grease will bleed oil in hot weather. It is Los Angeles, California
recommended only for lubrication of the~ blade 13. Germany Calypsol H442
pilot tubes but not the blade bearings. German Calypsol Company, Dusseldorf

7. RPM Aviation Grease No. 1 C. Proper times and amounts of grease are mentioned
Standard Oil Co. of California during asembly procedures.

SECTION XII
SERVICE TROURLES

Trouble Probable Cause Remedy

FAILURE If rpm fails to increase but Set relief valve in governor to provide necessary pres-
OF PITCH will re´•duce: Low oil pressure. sure, up to 275 psi.
TO CHANGE
If rpm change in both direc- See "Excessive Friction in Hub Mechanism," below.
tions is sluggish: Excessive Isolate friction in each blade by uncoupling piston and
friction in hub mechanism. testing each blade separately, before tearing propel-
ler down.

Newly-installed governor has Check and correct.

wrong direction of rotation,
or has bypass plug in wrong
hole.
EXCESSIVE Pilot tubehas slipped out Tear down and check distance pilot tube extends from
FRICTION IN slightly and is rubbing hard hub spider. Should be 33/s inches. If more, remove
NUB MECHANISM against end of hole in blade, pilot tube and replace with a tube .002 in. oversize at
hub end.

Blade bushing seized on pilot Polish pilot tube and blade bushing with fine emery
tube, paper and reassemble.

Blade ball bearings unusually Replace bearing.

rough or broken.

Friction in various moving Check parts individually If tightness is encountered

parts of pitch control mech- in sliding parts, increase clearances slightly. Apply
anism. oil externally to moving parts.
IMPROPER RPM Static rpm too low. Governor has high rpm stop, as well as propeller low
pitch stop. Either the governor or the propeller stop
may limit maximum rpm. To determine which is
causing trouble, open the throttle and move governor
control back and forth slowly.
If maximum rpm is reached BEFORE governor stop is
reached, propeller stop is probably limiting rpm. .Tf
this is the case, loosen blade clamp outer bolts and
rotate blades in clamps. Reduce blade angle abou~ 1"
for each 100 rpm increase. (1" equals k inch circum-
ference at blade root.)
If maximum rpm is reache:d AT SAME TIME as gov-
ernor is reached, governor stop is probably limiting
the maximum rpm. Readjust governor stop to obtain
proper rpm. One turn of governor stop screw equals
about 17 rpm. Turn stop screw out to increase rpm.
Governor stop should limit high rpm, with propelle:
stop reached at 50 to 100 rpm beyond. This allows
for variations in engine power without affecting max-
imum rpm.

12
 Trouble Probable Cause Remedy
Static rpm too high Reduce by screwing governor stop in, one turn for
each 17 rpm reduction.

FAILURE TO Governor control does not Provide sufficient travel in governor control. Gover-
FEATHER provide enough travel to al- nor must drain oil out of propeller during feathering.

low governor to move hard

against high pitch stop.
Excessive friction. See "Excessive Friction in Hub Mechanism."

High pitch stop pin fails to Check for burrs on pins. Check for stiffness of spring.
slide out at feathering rpm. Ifpropeller feathers at righ rpm’s but fails to feather
at low rpm’s, too-sti’ff spring is indicated. Reduce
length of spring by one or two turns.
Weak or broken feathering Replace.
spring
SURGING Air trapped in propeller ac- Provision should be incorporated in engine to allow
(When governor tuating.piston or in engine trapped air to escape from system during one half of
control is shaft. the pitch change cycle. Exercise propeller by chang-
changed rapidly ing pitch or feathering before each flight.
or rough air Adjust governor relief pressure so that rate of pitch
Governor pressure too low.
is eneountere&) same in both directions.
change is the
Excessivefriction in pitch See "Excessive Friction in Hub Mechanism."
change mechanism.

Governor lacks sufficient Change or adjust speeder spring. This gives governor
dampening, more stability, but makes pitch control more sensitive,
which, may in turn require re-rigging of control to
offset higher spring rate. Changing to stiffer speeder
spring should be done only after all other factors are
checked and corrected.

OIL LEAKAGE Faulty L’O" ring seals as fol- Disassemble and inspect "O" rings and the surfaces
lows: they seal. Replace L’O" rings if defective. Replace
Front of rear cone between cylinder if surface is scratched or nicked in area
engine shaft and hub, where "0" ring slides. Use gasket compound on
Between hub and cylinder. cylinder threads when replacing. Peen down raised
Between piston and cyl- places caused by tightening of cylinder with bar.
inder at front of piston.
GREASE LEAKAGE Grease leaks past clamp seal Loosen clamp bolts and replace gaskets. Standard
(Only source of gaskets. thickness of gasket is .050, but.060 gaskets are avail-
able in case .050 gaskets are not compressed suffi-
grease leakage
is blade bearings.) ciently to hold.

Grease leaks from between Inscribe blade with inkor pencil to assure correct

blade and clamp. blade anglereassembly, and remove blade and

on

clamp. Add gasket compound in radius of blade butt.

Replace blade and clamp.
END PLAY IN Buildup of manufacturing Total end play of .060 is permissible.
BLADES tolerances.

BLADE TRACK Tolerance of 1/8 inch is allowed.

BLADE FIT ON With manufacturing tolerances, the maximum that

HUB PILOT TUBE the blade tip can be moved fore and aft is .068, with-
out grease in blade clamps and bearings. With
grease, the movement is nil. If blade tip fore-and-aft
movement increases to .100 dry, blade requires fac-
tory re-bushing.

13
 SECTION XIII

PARTS LISTS
Model HC-8BXF-1DB1
Assembly Drawing D-809

Part No. Nomenclature No. Required

840-19B HUB SPIDER UNIT 1

C-801-11B Hub Spider 1
A-158L Pilot Tube 2
834-4 Guide Collar Assembly 1
B-1326-2 Guide Collar 1
A-116-A-1 Plastic Bushing 2
A-114-C Staking Pin 4
A-2038-10 Socket Screw 2
A-957 Safety Pin 2
HUB ASSOCIATED PARTS
A-14-B Blade Bearing 2
A-969 Split Ring 2
.5002x1 Danley Dowel Pin 2
A-2040 or A-1333-4 Hub Mounting Bolt 6
PRP-909-6 Blade Hub "O" Ring 3
838-2 CLAMP COUNTERWEIGHT ASSEMBLY 2
C-3-1A Clamp 2
A-295 Link Screw 2
A-285 Staking Pin, Linkscrew 2
MS15001-1 Zerk Fitting 3
B-891-1 Counterweight Sub-Assembly 2
A-65 Counterwe~ight Staking Pin 2
A-2036-30 Mounting Bolt 4
A-285 Staking Pin 4
A-47-1 Clamp Gasket 4
A-282 Socket Screw 4
AN380-3-2 Cotter Pin 4
A-2017 Clan~p Bolts 4
AN960-616 Moun~ing Washer 4
A-2043 Ckamp Muts 4
CLAMP ASSOCIATED PARTS
A-48 Balance Weight As Needed
AN501-A10-6 Weight Screws 4
B-S28 PISTON ASSEMBLY 1
B-966 Piston (B-805 interchangeable) 1
A-862 Plastic Bushing 1
A-826-1 Push Rod 2
A-114-F Staking Pin 2
A-921-1 Fork 2
A-2039 Set Screw 2
A-827-1 Rod Sleeve 2
A-965 Washer 2
A-848 E’lexlock Nut 2

HYDRAULIC ASSOCIATED PARTS

B-806 Cylinder 1
PRP-909-13 Cylinder "O" Ring 1
PRP-902-46 Piston "O" Ring 1
A-81.0 Fe´•lt Seal 1
A-95-A Block, Pitch Change 2
835-13 SPINNER ASSEMBLY 1
0-888-4 Dome 1
0-807-1 Bulkhead 1
AN526C1032R7 Screws, Dome Mounting 14

14
 Part No. Nomenclature No.Required
SPINNER MOUNTING PARTS
A-846-3 Lug, Spinner 4
A-2051 Hex Head Bolt 4
AN960-416L Washer 4
AN363-428 Flexlock Nut or H10-4 Kaylock Nuts 4
AN4H-14A Hex Head Bolt 4

PARTS LIST Model HC-82XF-1D

Assembly Drawing D-809
Part No. Nomenclature No. Required

840-19 HUB SPIDER UNIT 1

C-801-11 Hub Spider 1
A-158L Pilot Tubes 2
A-846-3 Spinner Lugs 4
A-957 Staking Pin 2

834-4 Guide Collar Unit 1

B-1326-2 Guide Collar 1
A-116A-1 Plastic Bushings 2
A-2038-10 Nylock Socket Head Cap Screws 2
1" Staking Pins, Guide Collar 2
.5002 x

HUB ASSOCIATED PARTS

PRP-906-6 "O" Rings, Blade 2
Blade Bearings 2
A-14-A
Split Rings, Bearing 2
A-159
"O" Ring, Shaft I
PRP-909-6
A-1333-4 Hex Head Bolts 6
A-2040 or
CLAMP COUNTERWEIGHT ASSEMBLY 2
838-2
Clamp 2
C-3-1A
Linkscrew 2
A-295
Staking Pin, Linkscrew´• 2
A-285
Counterweight Unit 2
B-891-1
Socket Head Cap Screws, Ctwt. 4
A-2036-30
A-285 Staking Pin, Sk. Hd. Cap Sc. (AN380-.3-2 Cotter Pin 4
Staking Pin, Counterweight Optional) 2
A-65
Zerk Fittings 4
MS15001-1
Clamp Gaskets 4
A-47-1
Socket Screws, Clamp 4
A-282
Cotter Pins, Socket Screw 4
AN380-3-2
Clamp Bolts, 12 Point 4
A-2017
Washers 4
AN960-616
4
A-2043 Clamp Nuts
4
No. 3 Lubricap8
CLAMP ASSOCIATED PARTS
Balance Weights As Needed
A-48
Screws, Balance Weight As Needed
AN501A10-(
2
A-95-A Blocks, Pitch Change
PISTON ASSEMBI,Y 1
B-828
Piston Unit 1
B-966-1
Piston (B-805 interchangeable) 1
B-966
Push Rods 2
A-826-1
2
A-114-G Staking Pins, Push Rod
Plastic Bushing 1
A-862
Forks 2
A-921-1
Socket Set Screws, Fork 2
A-2039
2
A-827-1 Sleeves, Push Rod
2
A-965 Washers, Push Rod
2
A-848 Flexlock Nuts, Push Rod
HYDRAULIC ASSOCIATED PARTS
1
PRP-909-13 "O" Ring, Cylinder Mounting´•
1
B-806 Cylinder
Dust Seal, Cylinder 1
A-810
1
PRP-920-46 "O" Ring, Piston
1
835-13 SPINNER ASSEMBLY
1
C-888-4 Dome, Spinner
14
AN526C1032R7 Screws, Dome Mounting
1
C-807-1 Bulkhead U ’t
15
 Part No. Nomenclature No. Required
SPINNER ASSEMBLY (Continued)
AN4H14A Hex Head Bolts 4
AN960-416L Washers 4
H10-4 or AN363-428 Keylock Nuts 4
A-2051 Hex Head Bolt 4
B-(x)-(x) GOVERNORS, HARTZELL 1
F-(x)-(x) GOVERNORS, HARTZELL 1
(x), 210, (xxx) GOVERNORS, WOODWARD 1
1A4, 1M12, 1P12, 1&12 GOVERNORS, HAMILTON-STANDARD 1

PARTS LIST
Assembly Drawing D-851 Model HC-82XL-2B, -2C

Part No. Nomenclature No. Required

-2B -2C
840-58 HUB SPIDER ASSEMBLY 1
C-801-18 Hub Spider 1
A-158L Pilot Tube 2

840-30 HUB SPIDER ASSEMBLY 1

C-801-14 Hub Spider 1
A-158L Pilot Tube 2
ASSOCIATED PARTS FOR 840-58 840-30
A-311 Ball Spacer (Optional) 2 2
A-14-A Bearing 2 2
A-159 Split Ring 2 2
PRP-909-6 Blade Mtg. "O" Ring 2 2
PRP-902-32 Shaft Mtg. "O" Ring 1 1
B-933-1 Shim, Flange Mtg. 1 1
A-988 Screw, Prop. Mtg. 4 4
A-898-2 Washers 4 4
A-988-1 Screw, Prop. Mtg. (A-943-1 Optional-- 2
A-987 Ferry Screw Conversion from -213) 2
(For 7636 8433-12 Blades)
838-11 CLAMP COUNTERWEIGHT SUB-ASSY. 2 2
C-3-5A Clamps 2 2
A-304 Linkscrew 2 2
A-285 Staking Pin, Linkscrew 2 2
MS-15001-1 Clamp Zerk Fitting 4 4
B-271-1 Counterweight 2 2
A-2036-30 Counterweight Socket Screws 4 4
A-285 Staking Pins, Ctwt. Socket Sc. (AN-380-3-2 Cotter 4 4
A-65 Counterweight Staking Pin Pin Optional) 2 2
A-47-1 Clamp Gaskets 4 4
A-282 Clamp Mounting Socket Screws 4 4
AN380-3-2 Cotter Pins, Clamp Sk. Sc. 4 4
A12017 Clamp Bolts 4 4
AN960-616 Clamp Mounting Washers 4 4
A-2043 Clamp Mounting Lock Nuts 4 4
No. 3 Lubricaps 4 4
CLAMP ASSOCIATED PARTS
A-48 Balance Weight As Neede;d
AN501A10-6 We~ight Screw 4 4
A-881 StopPlate 2 2
AN501A10-6 Stop Screws 4 4
A-944 Sleeve, Linkscrew 2 2
AN380-3-3 Sleeve Cotter Pin 2 2
830-2 AUTOMATIC HIGH PITCH STOP ASSY. 2
B-882-1 High Pitch Stop Bracket 2
A-883 High. Pitch Stop Pin 2
A-884 High Pitch Stop Spring 2
AN936A10 Washer 2
AN380-3-3 Cotter Pin 2

16
 Nomenclature No. Required
Part No.
-2B -2C

830-9 AUTOMATIC HIGH PITCH STOP ASSY. 2

B-984 High Pitch Stop Bracket 2
A-883 High Pitch Stop Pin 2
A-884 High Pitch Stop Spring 2
AN936A10 Washer 2
AN380-3-3 Spring Mounting Cotter Pins 2

AUTOMATIC HIGH PITCH STOP

ASSOCIATED PARTS
AN74-5 Mounting Bolt 4 4

831-5A FEATHERING SPRING SUB-ASSEMBLY 1 1

B-S55A Pilot Tube 1 1
A-856 Outer Mushroom 1 1
A-860-1 Feathering Spacer Tube 1 1
B-953 Feathering Spring Inner (Heavy) 1 1
B-853 Feathering Spring Outer 1 1
A-857 Rear Spring Retainer 1 1
A-858 Rear Split Retainer 1 1

832-24 PISTON ASSEMBLY 1 1

Piston Jack Unit 1 1
C-852-6
Piston 1 1
C-852-6 Det. #1
A-862 Plastic Bushing 1 1
Bushing 4 4
A-946
A-1464 Link Pin Unit 2 2
AN501A10-6 Safety Screws 2 2
Link Arms 2 2
A-861-3
HYDRAULIC ASSOCIATED PARTS
B-854 Cylinder 1 1
PRP-909-13 Cylinder "O" Ring 1 1
A-859 Split Retainer, Front 1 1
A-899 Feathering Stops 2 2
AN501A10-6 Screws, Feathering Stop 4 4
PRP-902-46 "O" Ring, Piston 1 1
A-863 Dust Seal 1 1
PRP-914-12 "O" Ring, Pilot Tube 1 1
A-880-2 Flexlock Nut, Piston 1 1

835-6P SPINNER ASSEMBLY 1 1

C-888-4P Spinner Dome 1 1
C-885P Bulkhead Adaptor 1 1
AN526C1032R7 Button Screws 14 14

PARTS LIST
Model HC-82X20-1B
Assembly Drawing D-823
Part No. No~nenclature No. Required

840-5 HUB SPIDER UNIT 1

C-157-5 Hub Spider 1

A-1S8L Pilot Tube 2
A-155 Bushing 1
Guide Collar Unit 1
834-3
HUB ASSOCIATED PARTS
A-14-A Blade Bearing 2
A-159 Split Ring 2
PRP-909-6 "O" Ring, Blade 2
A-50-3 Rear Cone 1
PRP-909-7 "O" Ring, Hub Monnting 1
A-870 Puller Ring 1
A-63-B Hub Nut 1
Pin Safety, Hub Lock 1
A-S47

17
 Part No. Nomenclature No. Required

838-25 CLAMP ASSEMBIIY (838-21 Alternate) 2

C-3-1A Clamp 2
A-295 Linkscrew 2
A-285 Staking Pin, Linkscrew 2
MS-1Tj001-1 Zerk Fitting 6
833-24 Counterweight Unit 2
A-65 Counterweight Staking Pin 2
A-2036-30 Counterweight SocketHead Screw 4
A-285 Socket Screw Staking Pin 4
A-47-1 Clamp Gasket 4
A-282 Socket Screw 4
AN580-3-2 Cotter Pin 4
A-2017 Clamp Bolts 4
A-2043 Clanip Nuts 4
AN960-616 Washer 4

CLAMP ASSOCIATED PARTS

A-48 Balance Weight As Needed
AN501A10-6 Weight Screws 4

B-828-3 PISTON ASSEMBLY 1

B-966-3 Piston Unit 1
B-966 Piston (B-805 interchangeable) 1
A-862 Plastic Bushing 1
A-826-3 Push Rod 2
A-114F Rod Staking Pin 2
A-821-1 Fork 2
61-2039 Set Screw 2
A-827-2 Rod Sleeve 2
A-965 Washer 2
A-848 Flexlock Nut 2
A-970 Spacer 2
HYDRAUI,IC ASSOCIATED PARTS
B-806-1 Cylinder 1
PRP-909-13 Cylinder "O" Ring 1
PRP-902-46 Piston "O" Ring 1
A-810 Dust Seal 1
A-SS-A Block, Pitch Change 2
835-15 SPINNER ASSEMBLY (No Stops) 1
e-888-4 Dome (Not Polished) 1
AN526C1032R7 Dome Mounting Screws 14
C-807-6 Bulkhead 1

PARTS LIST
Moldel HC-82XL-1D
Drawing D-809

Part No. Nomenclature No. Require~d

HC-82XL, -1D

840-29 HUB SPIDER SUB-ASSEMBLY 1

C-801-12 Hub Spider 1
834-4 Guide Collar Unit 1
A-158L Blade Pilot Tubes 2
A-1332-1 Staking Pin, Collar 2

ASSOCIATED PARTS
A-14-A Blade´• Mounting Bearings 2
A-159 Blade Mounting Split Ring 2
PRP-909-6 Blade Mounting’LO" Rings 2

18
 No. Required
Part No. Nomenclature
HC-82XL, -1D

838-20 CLAMP COUNTERWEIGHT SUB-AS,$Y. 2

C-3-1A Clamp 2
B-271-2 Counterweiffht Assembly 2
A-65 Counterweight Staking Pin 2
A-295 Linkscrews 2
A-285 Staking Pins, Linkscrew 2

ASSOCIATED PARTS FOR 838-20

CLAMP COUNTERWEIGHT SUB-ASSY.
A-47-1 Clamp Gaskets 4
A-48 Balance Weights As Needed
A-95-A Pitch Change Blocks 2
A-282 Clamp Mounting Socket Screws 4
A-2017 Clamp Mounting Bolts 4
A-2043 Clamp Mounting Self Locking Nuts 4
MS15001-1 Zerk Fitting 4
AN380-3-2 Counterweight Mounting Cotter Pins 4
AN501-A10-6 Balance Weight Mounting Screws 4
A-2036-30 Counterweight Mounting Socket Screws 4
AN960-616 Washer 4
A-285 Staking Pin 4
B-828-8 PISTON JACK SUB-ASSEMBLY 1
B-966 Piston (B-805 interchangeable) 1
A-826-8 Push Rod 2
A-921-1 Fork 2
A-827-1 Bushing 2
A-965 Washer 2
A-848 Nut, Flex Lock 2
A-2039 Set Screw 2
A-862 Plastic Bushing 1
A-114-F Rod Staking Pins 2

ASSOCIATED HYDRAULIC PARTS

PnP-902-46 "O" Ring, Piston Seal 1
B-806 Cylinder 1
A-810 Felt Seal 1
PRP-909-13 Cylinder "O" Ring 1

835-6 SPINNER SUB-ASSEMBLY 1

C-888-4 Spinner Dome 1
C-885 Spinner Adaptor 1
AN526C1032R7 Screws 14

PROPELLER MOUNTING PARTS

PRP-902-32 "O" Ring 1
A-943-1 Screw, E’lange Mounting 6
B-933-1 Shim, Plastic 1

PARTS LIST

Assembly Drawing D-865 Model HC-82X20-2, -2A

No. Required
Part No. Nomenclature
-2 -2A

840-5 HUB SPIDER SUB-ASSEMBLY 1

G-157-5 Hub Spider (C-157-4 Hub Spider for -2) 1
A-158L Pilot Tubes 2
A-155 Hub Bushings 2

19
 No. Required
Part No. Nomenclature
-2 -2A

ASSOCIATED PARTS
A-50-3 Rear Cone 1 1
A-63-B Hub Retention Nut 1 1
A-14-A Blade Mounting Bearings 2 2
A-159 Split Rings 2 2
A-870 Hub Puller Ring (Not Req’d With B-2063) 1 1
PRP-909-7 "O" Ring, Hub Shaft 1 1
PRP-909-6 "O" Ring Blade 2 2
A-847 Retention Nut Safety Pin, Hub 1 1

838-8 (For 8433

and 9333 Blades) CLAMP COUNTERWEIGHT SUB-ASSY. 2 2
C-3-5 Clamps 2 2
833-1 Counterweights 2 2
A-65 Counterweight Staking Pins 2 2
A-285 Staking Pin, Linkscrew 2 2
A-7-2 Linkscrew 2 2
A-47-1 Clamp Gaskets 4 4
A-48 Balance Weights As Needed
A-282 Clamp Mounting Socket Screws 4 4
AN501-A10-6 Balance Weight Mounting Screws 4 4
A-2017 Clamp Mounting BQltS 4 4
A-2043 Clamp Mounting Lock Nuts 4
AN960-616 Clamp Mounting Washers 4 4
1?-2036-30 Counterweight Mounting Socket Screws 4 4
A-285 Staking Pins (AN380-3-2 Optional) 4 4
AN380-3-2 Cotter Pins 4 4
MS15001-1 Zerk Fitting 4 4
No. 3 Lubricaps 4 4

CLAMP ASSOCIATED PARTS

A-944 Sleeve, Linkscrew 2 2
AN380-3-3 Cotter Pin 2 2
A-881 High Pitch Stop Plate 2 2
AN501A10-6 Plate Screw 4 4

830-2 AUTOMATIC HIGH PITCH STOP 2 2

B-882-1 High Pitch Stop Bracket 2 2
A-883 High Pitch Stop Pin 2 2
A-884 High Pitch Stop Spring 2 2
AN936A10 Washer 2 2
AN380-3-3 Spring Mounting Cotter Pins 2 2
831-7 FEATHERING SPRING ASSEMBLY 1
B-1405 Feathering Spring 1
A-866 Spring Rear Retainer 1
A-867 Spring Rear Split Retainer 1
B-868A Pilot Tube 1
A-871 Outer Mushroom 1
831-2 FEATHERING SPRING ASSEMBLY 1
B-1405 Feathering Spring 1
A-866 Spring Rear Retainer 1
A-867 Spring Rear Split Retainer 1
B-868 Pilot Tube 1
A-871 Outer Mushroom 1
A-818 Feathering Spacer Tube 1
A-819 Feathering Spacer Ring 1
832-10 PISTON ASSEMBLY 1
A-979-1 Link 2
AN501-A10-6 Mounting Screws 4
A-861-1 Link Arms 2
C-852-2 Piston 1
A-862 Plastic Piston Bushing 1
A-872 Link Arm Mounting Pins 2
AN501A10-18 Screw 1

20
 No. Required
Part No. Nomenclature
-2 -2A

832-11 PISTON ASSEMBLY 1

C-852-3 Piston 1
A-862 Plastic Bushing 1
A-817-2 Rod 2
A-114-F Pin 2
A-979-1 Link 2
A-872 Link Arm Mounting Pin 2
AN501A10-6 Mounting Screw 4
AN501A10-18 Screw 1
A-861-1 Link Arm 2

HYDRAULIC ASSOCIATED PARTS

B-854 Cylinder 1 1
A-863 Piston Felt Dust Seal 1 1
PRP-909-13 "O" Ring, Piston Seal 1 1
PRP-902-46 "O" Ring, Cylinder 1 1
834-2 Guide Collar Unit 1 1
A-859 Front Split Retainer 1 1
A-899 Feathering Stop 2 2
AN501A10-6 Stop Screw 4 4
A-880-1 Flexlock Nut 1 1
PRP-914-8 Pilot Tube "O" Ring 1 1

835-1S SPINNER ASSEMBLY 1 1

C-888-4 Spinner Dome 1 1
AN526C1032R7 Screws, Dome Mounting 14 14
C-807-2S Spinner Bulkhead 1 1

PARTS LIST

ModelHC-82XF-2B, -2B1, -2C

Assembly Drawing D-851
No. Required
Part No. Nomenclature 2B 2B1 2C
cRepalR
ONIY)

HUB SPIDER ASSEMBLY 1 1 1

840-3
C-801-2 Hub Spider 1 1 1
Pilot Tube 2 2 2
A-1S8L
HUB ASSOCIATED PARTS
A-14-A Blade Mtg. Bearings 2 2
A-159 Split Rings 2 2
A-14-B Blade Bearing 2

A-969 Split Ring 2

PRP-409-6 "O" Ring, Hub Mtg. 1 1 1
"O" Ring, Blade 2 2 2
PRP-909-6
A-2040 or A-1333-4 Hub Mtg. Hex Bolts 6 6 6
Hub Mtg. Dowel Pin 2 2 2
.5002x1 Danley

21
 No. Required
Part No. Nomenclature 2B 2B1 2C
(REPAIR

ONLY)

838-10 CLAMP COUNTERWEIGHT ASSEMBLY 2 2 2

C-3-5A Clamps 2 2 2
833-2 Counterweight 2 2 2
A-65 Counterweight Staking Pins 2 2 2
A-304 Linkscrew 2 2 2
A-285 Staking Pin 2 2 2
A-2036-30 Counterweight Screw 4 4 4
AN380-3-2 Counterweight Cotter Pin 4 4 4
A-47-1 Clamp Gaskets 4 4 4
A-282 Clamp Mounting Socket Screws 4 4 4
A-2043 Clamp Mounting Lock Nuts 4 4 4
A-2017 Clamp Bolts 4 4 4
AN960-616 Clamp Mounting Washers 4 4 4
No. 3 Lubricaps 4 4 4
MS15001-1 Clamp Zerk Fitting 4 4 4
A-285 Staking Pin, Socket Screw (AN380-3-2 Optional) 4 4 4
CLAMP ASSOCIATED PARTS
A-48 Balance Weight As Needed
AN501-A10-6 Weight Screw 4 4 4
A-881 Stop Plate 2 2 2
AN501A10-6 Stop Screws 4 4 4
A-944 Sleeve, Link Screw 2 2 2
AN380-3-3 Sleeve Cotter Pin 2 2 2
830-2 AUTOMATIC HIGH PITCH STOP ASSY. 2 2 2
B-882-1 High Pitch Stop Bracket 2 2 2
A-883 High Pitch Stop Pin 2 2 2
A-884 High Pitch Stop Spring 2 2 2
AN380-3-3 Spring Mounting Cotter Pins 2 2 2
AN936A10 Washer 2 2 2
AUTOMATIC HIGH PITCH STOP
ASSOCIATED PARTS
AN74-5 Hex Head Bolts 4 4 4
AN4-15A Hex Head Bolts 4 4 4
H10-4 Kaylock Nuts 4 4 4
AN960-416L Mounting Washer 4 4 4
AN363-428 Flexlock Nut (Optional) 4 4 4
831-5A FEATHERING SPRING ASSEMBLY 1 1
A-856 Outer Mushroom 1 1
A-857 Spring Rear Retainer 1 1
A-858 Spring Rear Split Retainer 1 1
B-853 Feathering Spring, Outer 1 1
B-953 Feathering Spring, Inner (Heavy) 1 1
B-855A Pilot Tube 1 1
A-860-1 Feathering Spacer Tube 1 1
831-1A FEATHERING SPRING ASSEMBLY 1
A-856 Outer Mushroom 1
A-857-1 Spring Rear Retainer 1
A-858 Spring Rear Split Retainer 1
B-853 Feathering Spring 1
B-85~5-2A Pilot Tube 1
A-860-1 Feathering Spacer Tube 1
B-953 Spring, Feathering, Inner 1
832-24 PISTON ASSEMBLY 1 1 1
C-852-6 Piston Jack Unit 1 1 1
C-852-6 Det. #1 Piston 1 1 1
A-862 Plastic, Piston Bushing 1 1 1
A-946 Bronze Bushings 4 4 4
AN501-A10-6 Safety Bar Mounting Screws 4 4 4
A-861-3 Link Arms 2 2 2
A-1464 Link Pin Units 2 2 2

22
 No. Required
Part No. Nomenclature 2B 2B1 2C
(REPAIR
ONLY)

HYDRAULIC ASSOCIATED PARTS

B-854 Cylinder 1 1 1
PRP-909-13 Cylinder "O" Ring 1 1 1
A-859 Split Retainer Front 1 1 1
A-899 Feathering Stop 2 2 2
AN501-A10-6 Stop Screw 4 4 4
A-880-2 Piston Nut 1 1 2
PRP-914-12 "O" Ring, Pilot Tube 1 1 1
PRP-902-46 "O" Ring 1 1 1
A-863 Dust Seal 1 1

835-13 SPINNER ASSEMBLY 1 1 1

C-888-4 Spinner Dome 1 1 1
AN526C1032R7 Button Head Rivets 14 14 14
C-807-1 Spinner Bulkhead 1 1 1

PARTS LIST

Model HC-82XK-2B, -2B1, -2C1

Assembly Drawing D-851
No. Required
Part No. Nomenclature
2B 2B1 2C1

840-36 HUB SPIDER SUB-ASSEMBLY 1 1

C-960 Hub Spider 1 1
A-158L Pilot Tubes 2 2

840-31 HUB SPIDER SUB-ASSEMBLY 1

C-960-2 Hub Spider 1
A-1S8L Pilot Tubes 2

ASSOCIATED PARTS FOR 840-36 and 840-31

A-14A Bearing 2
A-14B Bearing 2 2
A-159 Split Rings 2
A-969 Split Rings 2 2
PRP-902-32 Shaft Mtg. "O" Ring 1 1 1
PRP-909-6 Blade Mtg. "O" Ring 2 2 2
B-1322 Shim, Flange Mtg. 1 1 1
A-1328 8crew, Prop Mtg. 4 4 4
A-1315 Screw, Prop Mtg. 2 2
A-1333 or -3 Screw, Prop Mtg. 2

838-10 (For 8433 and 8833 Blades)

CLAMP COUNTERWEIGHT SUB-ASSY. 2 2 2

C-3-5A Clamps 2 2 2
833-2 Counterweight 2 2 2
A-65 Counterweight Staking Pins 2 2 2
A-304 Linkscrew 2 2 2
A-285 Staking Pin, Linkscrew 2 2 2
A-2036-30 Counterweight Screw 4 4 4
AN380-3-2 Counterweight Cotter Pin 4 4 4
A-47-1 Clamp Gaskets 4 4 4
A-282 Clamp Mounting Socket Screws 4 4 4
A-2043 Clamp Mounting Lock Nuts 4 4 4
Clamp Bolts 4 4 4
A-2017
Staking Pin (AN380-3-2 Optional Cotter Pin) 4 4 4
A-285
4 4 4
AN960-616 Clamp Mounting Washers
4 4 4
No. 3 Lubricaps
4 4 4
MS15001-1 Clamp Zerk Fitting

23
 No. Required
Part No. Nomenclature
2B 2E1 2C1

CLAMP ASSOCIATED PARTS

A-48 Balance Weight As Needed
AN501-A10-6 Weight Screw 4 4 4
A-881 Stop Plate 2 2 2
AN501A10-6 Stop Screws 4 4 4
A-944 Sleeve, Link Screw 2 2 2
AN380-3-3 Sleeve Cotter Pin 2 2 2

830-2 AUTOMATIC HIGH PITCH STOP SUB-ASSY. 2 2

B-882-1 High Pitch Stop Bracket 2 2
A-883 High Pitch Stop Pin 2 2
A-884 High Pitch Stop Spring 2 2
AN380-3-3 Spring Mounting Cotter Pins 2 2
AN936A10 Washer 2 2

830-9A AUTOMATIC HIGH PITCH STOP SUB-ASSY. 2

AN380-3-3 Spring Mounting Cotter Pins 2
A-884 High Pitch Stop Spring 2
B-984-1 High Pitch Stop Bracket 2
A-883 High Pitch Stop Pin 2
AN936A10 Washer 2

AUTOMATIC HIGH PITCH STOP

ASSOCIATED PARTS
AN74-5 Hex Head Bolt 4 4 4
831-5A FEATHERING SPRING SUB-ASSEMBLY 1 1 1
A-856 Outer Mushroom 1 1 1
A-857 Spring Rear Retainer 1 1 1
A-858 Spring Rear Split Retainer 1 1 1
B-853 Feathering Spring Outer 1 1 1
B-953 Feathering Spring Inner (Heavy) 1 1 1
B-8S5A Pilot Tube 1 1 1
A-860-1 Feathering Spacer Tube 1 1 1

832-24 PISTON ASSEMBLY 1 1 1

C-852-6 Piston Jack Unit 1 1 1
C-852-6 Det. #1 Piston 1 1 1
A-862 Plastic, Piston Bushing 1 1 1
A-946 Bushing 4 4 4
ANSO1-A1‘0-6 Safety Bar Mounting Screws 2 2 2
A-861-3 Link Arms 2 2 2
A-1464 Link Assembly 2 2 2

HYDRAULIC ASSOCIATED PARTS

B-854 Cylinder 1 1 1
PRP-909-13 Cylinder "O" Ring 1 1 1
A-859 Split Retainer Front 1 1 1
A-899 Feathering Stop 2 2 2
ANS01-A10-6 Stop Screw 4 4 4
A-880-2 Piston Nut 1 1 1
PRP-914-12 "O" Ring, Pilot Tube 1 1 1
PRP-902-46 "O" Ring 1 1 1
A-863 Dust Seal 1 1 1

835-6P SPINNER SUB-ASSEMBLY 1 1 1

C-888-4P Spinner Dome 1 1 1
C-885P Bulkhead Adaptor 1 1 1
ANS26C1032R7 Button Screws 14 14 14

24
 PARTS LIST

Model HC-82XK-1D
Assembly Drawing D-809
Part No. Nomenclature No. Required

H’UB SPIDER UNIT 1

840-33
Hub Spider 1
C-960-1
A-158L Pilot Tube 2
Guide Collar Unit 1
834-9
Staking Pin, Collar 2
A-1332-2
HUB ASSOCIATED PARTS
Blade Bearing 2
A-14A
Split Rings 2
A-159
A-1333-3 Mounting Bolts 6
"O" Ring 1
PRP-902-32
Shim 1
B-1322
Blade Hub "O" Ring 3
PRP-909-6
Hex Head Bolts 2
A-1333-2
CLAMP COUNTERWEIGHT ASSEMBLY 2
838-2
Clamp 2
C-3-1A
Link Screw 2
A-295
Staking Pin, Linkscrew 2
A-285
Zerk Fitting 3
MS15001-1
A-47-1 Clamp Gasket 4
A-282 Socket Screw 4
A-48 Balance Weight As Needed
ANS01-A10-6 Weight Screws 4
Clamp Bolts 4
A-2017
Moun~ing Washer 4
AN960-616
Clamp Nuts 4
A-2043
Counterweight Assembly 2
B-891-1
Counterweight 2
B-271
Stop 2
A-293
2
A-272-2 Weight Slug
4
A12036-30 Mounting Bolt
Cotter Pin 4
AN880-3-2
Counterweight Staking Pin 2
A-65
Staking Pin 4
A-285
B-828-8 PISTON ASSEMBLY 1
Piston (B-966 interchangeable) 1
B-805
Plastic Bushing 1
A-862
Push Rod 2
A-826-8
A-921-1 Fork 2
Set Scre~w 2
A-2039
Rod Sleeve 2
A-827-1
Staking Pin 2
A-1T4-F
Washer 2
A-g6S
Flexlock Nut 2
A-848
HYDRAULIC ASSOCIATED PARTS
Cylinder 1
B-806
Cylinder "O" Ring 1
PRP-909-13
Piston "O" Ring 1
PRP-902-46
Felt Seal 1
A-810
Block, Pitch Change 2
A-SS-A
834-9 GUIDE COLLAR ASSEMBLY
Guide Collar 1
B-1326-1
Plastic Bushing 2
A-116-A-1
Staking Pin 4
A-114-C
Socket Screw 2
A-2038- 10
SPINNER ASSEMBLY 1
836-6
Spinner Dome 1
C-888-4
Spinner Adaptor 1
C-885
AN526C1032R7 Screws 14

Governor--Woodward 210,000 series or Harteell B-2.

25
 PARTS LIST
Model HC-83XF-1A, -1Al
Assembly Drawing D-1475

No. Required
Part No. Nomenclature
-1A -1Al
840-69 RUB SPIDER UNIT 1 1
0-1426-1 Hub Spider (With Lugs) 1 1
A-1S8L Pilot Tubes 3 3

HUB ASSOCIATED PARTS

A-14-A Blade Bearings 3
A-14-B Blade Bearings 3
A-159 Split Ring 3
A-1)69 Split Ring 3
PRP-909-6 "O" Ring, Blade 3 3
PRP-909-6 "O" Ring, Shalt 1 1
A-2040 Hex Head Bolts 6 6
AN960-816 Washers 6 6
.5002x1" Danley Dowel Pins 2 2
838-61 CLAMP ASSEMBLY 3 3
C-3-1A Clamp 3 3
A-295 Linkscrew 3 3
A-285 Staking Pin, Linkscrew 3 3
MS-15001-1 Zerk Fittings 6 6
833-4B Counterweight Unit 3 3
A-65 Staking Pin, Counterweight 3 3
A-2036-30 Socket Head Cap Screws, Counterweight 6 6
A-285 Staking Pins, Socket Screw 6 6
A-47-1 Clamp Gaskets 6 6
A-282 Clamp Socket Screws 6 6
AN380-3-2 Cotter Pins, Socket Screw 6 6
A-2017 Clamp Bolts 6 6
AN960-616 Washers 6 6
A-2043 Clamp Nuts 6 6
CLAMP ASSOCIATED PARTS
A-48 Balance Weights As Nee´•ded
AN501A10-6 Weights 6 6
B-1378-3 PISTON ASSEMBLY 1 1
B-1421-1 Piston Unit 1 1
B-1421 Piston 1 1
A-862 Plastic Bushing 1 1
A-826-1 Push Rods 3 3
A-114-G Staking Pins, Rod 3 3
A-1926 Forks 3 3
A-2039 Socket Set Screws 3 3
A-827-1 Sleeves, Rod 3 3
A-965 Washers 3 3
A-848 Flexlock Nuts 3 3
HYDRAULIC ASSOCIATED PARTS
B-806 Cylinder 1 1
PRP-909-13 "O" Ring, Cylinder 1 1
A-810 Dust Seal 1 1
PRP-902-46 "O" Ring, Piston 1 1
A-95-A Block, Pitch Change 2 2
835-9 SPINNER ASSEMBLY 1 1
C-888-6 Dome 1 1
AN526C1032R8 Screws 9 9
C-807-8 Bulkhead 1 1
836-18 SPINNER ASSEMBLY 1 1
D-1367-6 Dome 1 1
AN526C1032R8 Screw 12 12
D-1415-4 Bulkhead 1 1

26
 No. Required
Part No. Nomenclature
-1A -1Al

836-19 SPINNER ASSEMBLY (Anti-Icing) 1 1

D-1367-7 Dome 1 1
AN526C1032RS Screw 12 12
D-1415-6 Bulkhead (Anti-Icing) 1 1
Beech Trave~l Tubes 3 3

SPINNER MOUNTING PARTS

A-846 or -3 Spinner Lugs 4 4
AN4H4A Hex Head Bolts 4 4
A.N4H14A Hex Head Bolts 4 4
AN960-416 Washers 4 4
AN363-428 Flexlock Nuts (H10-4 KaylockAlternate) 4 4

PARTS LIST
Models HC-83X20-1A, -1B, -1C, -1Al, -1BI, -1C1
Assembly Drawing D-1420

No. Required
Part No. Nomenclature
1A 1B 1CI 1Al 1B1 1C1

840-12 HUB SPIDER UNIT 1 1 1 1 1 1

C-1404-4 Hub Spider 1 1 1 1 1 1
A-158L Pilot Tube 3 3 3 3 3 3
A-155 Bushing 1 I 1 1 1 1
KUB ASSOCIATED PARTS
A-14-A Blade Bearing 3 3 3
A-14-B Blade Bearing 3 3 3
A-159 Split Ring 3 3 3
A-969 Split Ring 3 3 3
PRP-909-6 "O" Ring, Blade 3 3 3 3 3 3
A-S0-5 Rear Cone 1 1
A-50-3 Rear Cone 1 1 1 1
PRP-909-7 "O" Ring, Shaft 1 1 1 1 1 1
A-63-B Hub Nut 1 1 1 1 1 1
A-870 Puller Ring 1 1 1 1 1 1
A-847 Safety Pin, Hub 1 1 1 1 1 1

838-21(838-25 Alternate) CLAMP ASSEMBLY 3 3 3 3 3 3

C-3-1A Clamp 3 3 3 3 3 3
A-295 Linkscrew 3 3 3 3 3 3
A-285 Staking Pin, Linkscrew 9 3 3 3 3 3
MS-15001-1 Zerk Fitting 6 6 6 6 6 6
833-17 Counterweight Unit 3 3 3 3 3 3
A-65 Staking Pin, Counterweight 3 3 3 3 3 3
A-2036-30 Socket Head Cap Screws, Counterweight 6 6 6 6 6 6
A-285 Staking Pins, Sk. Screw 6 6 6 6 6 6
A-47-1 Clamp Gasket 6 6 6 6 6 6
A-282 Clamp Socket Screw 6 6 6 6 6 6
AN380-3-2 Cotter Pin, Sk. Screw 6 6 6 6 6 6
A-2017 Clamp Bolts 6 6 6 6 6 6
AN960-616 Washer 6 6 6 6 6 6
A-2043 Clamp Nuts 6 6 6 6 6 6

B-1378-5 PISTON ASSEMBLY 1 1

B-1421-5 Piston Unit 1 1
B-1421 Piston 1 1
A-862 Plastic Bushing 1 1
A-826-5 Push Rod 3 3
A-114-G Staking Pins, Rod 3 3
A-1926 Forks 3 3
A-2039 Socket Set Screw 3 3
A-827-8 Sleeves, Rod 3 3
A-965 Washer 3 3
Flexlock Nut 3 3
A-848
A-970 High Stop 3 3
A-970-3 High Stop 3 3

27
 No. Required
Part No. Nomenclature
1A 1B 1C 1Al 1B1 1C1
B-1378-1 PISTON ASSEMBLY 1 1
B-1421-5 Piston Unit 1 1
B-1421 Piston 1 1
A-862 Plastic Bushing 1 1
A-826-5 Push Rod 3 3
A-114-G Staking Pins, Rod 3 3
A-1926 Fork 3 3
A-2039 Socket Set Screw 3 3
A-827-6 Sleeve, Rod 3 3
A-965 Washer 3 3
A-848 Flexlock Nut 3 3
A-970-1 High Stop 3 3
B-1378-4 PISTON ASSEMBLY 1 1
B-1421-5 Piston Unit 1 1
B-1421 Piston 1 1
A-862 Plastic Bushing 1 1
A-826-S Push. Rod 3 3
A-114-G Staking Pin, Rod 3 3
A-1926 Fork 3 3
A-2039 Socket Set Screw 3 3
A-827-6 Sleeve, Rod 3 3
A-965 Washer 3 3
A-848 Flexlock Nut 3 3
A-970-3 High Stop 3 3
HYDRAULIC ASSOCIATED PARTS
B-806-1 Cylinder 1 1 1 1 1 1
PRP-909-13 "O" Ring Cylinder 1 1 1 1 1 1
A-810 Dust Seal 1 1 1 1 1 1
PRP-902-46 "O" Ring, Piston 1 1 1 1 1 1
A-95-A Blocks, Pitch Change 3 3 3 3 3 3
836-15R SPINNER ASSEMBLY 1 1
D-1367-6 Dome 1 1
AN526C1032R8 Screw 12 12
D-1387RH Bulkhead 1 1
AN526C1032R7 Screw 12 12
835-8 SPINNER ASSEMBLY 1 1 1 1
C-888-6 Dome 1 1 1 1
AN526C1032R7 Screw I) 9 9 9
C-lp29 Bulkhead 1 1 1 1

PARTS LLST
Model HC-83X20-2C, -2C1, -2CL
Assembly Drawing D-1400
No. Reqwired
Part No. Nomenclature
2C 2C1 2CL
840-12 HUB SPIDER UNIT 1 1 1
C-1404-4 Hub Spider 1 1 1
A-158L Pilot Tube 3 3 3
A-155 Bushing 1 1 1
HUB ASSOCIATED PARTS
A-50-3 Rear Cone 1 1 1
PRP-909-7 Hub "O" Ring 1 1 1
A-63-B Hub Nut 1 1 1
A ´•870 Puller Ring 1 1 1
A-847 Pin, Safety 1 1 1
A-159 Split Ring 3 3
A-14-A Blade Bearing 3 3
PRP-909-6 Blade "O" Ring 3 3 3
A-14-B Bearing, Blade 3
A-969 Split Ring 3

28
 No. Required
Part No. Nomenclature
20 201 2CL

838-6 CLAMP ASSEMBLY (8433, 8833 Blades) 3 3

C-3-5A Clamp 3 3
833-4 Counterweight Unit 3 3

838-23 CLAMP ASSEMBLY (9333 blades) 3 3

C-3-SA Clamp 3 3
833-413 Counterweight Unit 3 3

838-18 CLAMP ASSEMBLY (L8433, L8433H Blades) 3

C-3-5AL Clamp 3
833-4 Counterweight Unit 3

838-23L CLAMP ASSEMBLY (L9333CH-3, -5 Blades) 3

C-3-SAL Clamp 3
833-4L Counterweight 3

COMMON CLAMP PARTS

A-304 Link Screw 3 3 3
A-285 Staking Pin, Linkscrew 3 3 3
MS15001-1 Zerk Fitting 6 6 6
A-65 Counterweight Staking Pin 3 3 3
A-2036-30 Counterweight Socket Head Screws 6 6 6
A-285 Counterweight Sc. Staking Pin (or AN380-3-2) 6 6 6
A-47-1 Clamp Gasket 6 6 6
A-282 Socket Scre~w 6 6 6
AN380-3-2 Cotter Pin 6 6 6
A-2017 Clamp Bolts 6 6 6
AN9 60-616 Mounting Washer 6 6 6
Clamp Nuts 6 6 6
A-2043

CLAMP ASSOCIATED PARTS

A-48 Balance Weights As Needed
AN501A10-6 Weight Screws 6 6 6
A-944 Sleeve, Linkscrew 3 3 3
AN580-3-3 Cotter Pin, Linkscrew 3 3 3
A-881 ,"Jtop Plate 3 3 8
Plate Screws 6 6 6
A-2016

FEATHERING SPRING ASSEMBLY 1 1

831-7 (obsolete)
Pilot Tube 1 1
B-868A
Split Ring; 1 1
A-867
A-866 Retainer Ring 1 1
Spring 1 1
B-1405
Mushroom 1 1
A-871
Nut "O" Ring 1 1
PRP-914-8
FEATHERING SPRING ASSEMBLY 1 1 1
831-11 (current)
Pilot Tube 1 1 1
B-868A
Mushroom 1 1 1
A-871
Spring Retainer 1 1 1
A-866
1 1 1
A-867 Split Retainer
1 1 1
B-l 363-1 Spring
Nut "O" Ring 1 1 1
PRP-9 14-8
HYDRAULIC ASSOCIATED PARTS
A-859 Split Retainer Ring 1 1 1
Feathering Stop 2 2 2
A-899
Stop Mounting Screw 4 4 4
ANS01A10-4
Flexlock Nut 1 1 1
A-880-1
PRP-902-46 Piston "O" Ring 1 1 1
Dust Seal 1 1 1
A-863
Cylinder 1 1 1
B-854
Cylinder "O" Ring 1 1 1
PRP-909-13

29
 No. Required
Part No. Nomenclature
2C 2C1 2CL

832-14 PISTON ASSEMBLY 1 1

C-1401-3 Piston Unit 1 1
C-1401-3 Det. #1 Piston 1 1
A-862 Plastic Bushing 1 1
A-817-2 Guide Rod 3 3
A-114-B Rod Staking Pin 3 3
A-946 Pin Bushing 6 6
A-2037 Socket Set Screw 3 3
A-1444 Washer 3 3
AN316-5R Jam Nut 3 3
A-861-3 I,ink Arm 3 3
A-1464 Link Pin Unit 3 3
ANS01-A10-6 Screw 3 3

832-14L PISTON ASSEMBLY 1

C-1401-3L Piston Unit 1
C-1401-3L Det. #1 Piston 1
A-862 Plastic Bushing 1
A-817-2 Guide Rod 3
A-114-B Rod Staking Pin 3
A-946 Pin Bushing 6
A-2037 Socket Set Screw 3
A-1.444 Washer 3
AN316-5R Jam Nut 3
A-861-3L Link Arm 3
A-1464 Link Pin Unit 3
AN501-A10-6 Screw 3

834-1 GUIDE COLLAR UNIT 1 1

B-1402 Guide Collar 1 1
A-116-D-1 Plastic Bushing 3 3
A-114-C Staking Pin 6 6
A-2038-12 Socket Head Cap Screw 1 1

834-1L GUIDE COLLAR UNIT 1

B-1402L Guide Collar 1
A-116-D-1 Plastic Bushing 3
A-114-C Staking Pin 6
A-2038-12 Socket Head Cap Screw 1

835-108 SPINNER ASSEMBLY 1 1

C-888-6 Dome 1 1
AN526C1032R7 Dome Mounting Screws 12 12
C-807-7S Bulkhead (With 830-5 Stops) 1 1
C-807-10 Bulkhead (Without Stops) 1 1
830-5 Auto High Pitch Stop Units 3 3
B-882-5 Bracket 3 3
A-883 Pin 3 3
A-884 Spring 3 3
AN936A10 Washer (Internal Lock) 3 3
AN380-3-3 Cotter Pin 3 3

835-11S SPINNER ASSEMBLY 1

C-888-6 Dome 1
AN526C1032R7 Dome Mounting Screws 12
C-807-7LS Bulkhead (With 830-53; Stops) 1
C-807-10 Bulkhead (Without Stops) 1
830-SL Auto High Pitch Stop Units 3
B-882-5L Brackets 3
A-888 Pin 3
A-884 Spring 3
AN936A10 Washer (Internal Lock) 3
AN380-3-3 Cotter Pin 3

30
 PARTS LIST

Model HC-ABXF-1, -1A, K-l, El, and

BHC-A2XF-1, -1A
Assembly Drawing D-985
No. Required
Part No. Nomenclature HC BHC HC BHC HC HC
F-l F-l F-1A F-1A K-l L-l

840-42 HUB SPIDER UNIT 1

C-981-1 Hub Spider 1
A-158L Pilot Tubes 2
834-4 Guide Collar Unit 1
.5002x11~ Danley Dowel Pins 2
A-846-3 Spinner Lug,q 4
A-2051 Hex Head Bolts 4

840-47 HUB SPIDER UNIT 1

C-981-2 Hub Spider 1
A-158L Pilot Tubes 2
834-4 Guide Collar Unit 1
A-957-1 Collar Staking Pins 2
A-846-3 Spinner Lugs 4
A-2051 Hex Head Bolts 4

840-50 HUB SPIDER UNIT 1

C-981-3 Hub Spider 1
A-158L Pilot Tubes 2
834-9 Guide Collar Unit 1
.5002x1s/i~ Danley Dowel Pins 2
A-846-1 or -4 Spinner Lugs 4
A-2051 Hex Head Bolts 4

840-51 HUB SPIDER UNIT 1

C-981-S Hub Spider 1
sl-1St)L Pilot Tubes 2
834-9 Guide Collar Unit 1
A-957 Collar Staking Pina 2
A-846-1 or -4 Spinner I,ugs 4
A-2051 Hex Head Bolts 4

840-45 HUB SPIDER UNIT 1

C-982-2 Hub Spider 1
A-1S8L Pilot Tubes 2
834-9 G~iide Collar Unit 1
A-1332-2 Collar Staking Pins 2
A-1333-3 Hex Head Bolts 2
A-1333-2 Hex Head Bolts 2

840-44 HUB SPIDER UNIT 1

C-982-1 Hub Spider 1
A-158L Pilot Tubes 2
834-9 Guide Collar Unit 1
A-1332-2 Collar Staking Pins 2
A-943-1 Hex Head Bolts 4

HUB ASSOCIATED PARTS

A-311 Ball Spacer 2 2 2 2 2 2
A-971 Blade Bearing (Split´•) 2 2 2 2 2 2
Bearing, Wire Retention 2 2 2 2 2 2
A-2027
2 2 2 2 2 2
A-972 Hoop, Bearing Guide
2 2 2 2 2 2
A-974 Ring, Wire Retention
Blade "O" Ring 2 2 2 2 2 2
PRP-909-8
PRP-909-6 Hub "O" Ring 1 1 1 1
Dowel Pins 2 2
.5002x1
A-1328-1 12 Point Bolts (A-2040 or A-1333-4 Hex Head 6 6 6 6
A-1381 Washers (AN960-816 Optional) Optional) 6 6 6 6
Hub "O" Ring 1 1
PRP-902-32
Shim 1
B-933-1
Shim 1
B-1322
Hex Head Bolt 2
A-943-1
Hex Head Bolt 2
A 1333-3

31
 No. Re<yuired
Part No. Nomenclature HC BHC HC BHC HC HC
F-l F-l F-1A F-1A K-l El

838-2 CLAMP ASSEMBLY 2 2 2 2 2

C-3-1A Clamp 2 2 2 2 2
A-295 Linkscrew 2 2 2 2 2
A-285 Staking Pin, LinkPcrew 2 2 2 2 2
MS-15001-1 Zerk Fittings 4 4 4 4 4
B-891-1 Counterweiffht Unit 2 2 2 2 2
A-65 Staking fin, Counterweight 2 2 2 2 2
A-2036-30 Socket Head Cap Screws 4 4 4 4 4
A-285 Staking Pins, Socket St. (AN380-3-2 Cotter 4 4 4 4 4
A-47-1 Clamp Gaskets Pin Optional) 4 4 4 4 4
A-282 Socket Screws, Clamp 4 4 4 4 4
AN380-3-2 Cotter Pins, Socket Sc. 4 4 4 4 4
Ac2017 Clamp Bolts 4 4 4 4 4
AN960-616 Washers 4 4 4 4 4
A-2043 Clamp Nuts 4 4 4 4 4
838-20 CLAMP ASSEMBLY 2
C-3-1A Clamp 2
A-295 Linkscrew 2
A-285 Staking Pin, Linkscrew 2
MS-15001-1 Zerk Fitting 4
B-271-2 Counterweight Unit 2
A-65 Counterweight Staking Pin 2
A-2036-30 Counterweight Socket Screws 4
A-28Ei Counterweight Sc. Staking Pins (AN380-3-2 4
A-47-1 Clamp Gaskets Cotter Pin Optional) 4
A-282 Socket Screws 4
AN380-3-2 Cotter Pins 4
A-2017 Clamp Bolts 4
AN960-616 Washers 4
A-2043 Clamp Nuts 4
CLAMP ASSOCIATED PARTS
A-48 Balance Weight As Needed As Needed
.hN501A10-6 Weight Screw 4 4 4 4 4 4
B-828 PISTON ASSEMBLY 1 1 1 1
B-966-1 Piston Unit 1 1 1 1
Pi-966 Pi~toh 1 1 1 1
A-862 Plastic Bushing 1 1 1. 1
A-826-1 Push Rods 2 2 2 2
A-114-G Ro~d Staking Pins 2 2 2 2
A-921-1 Forks 2 2 2 2
A-2039 Socket Head Set Screws 2 2 2 2
A-827-1 Rod Sleeves 2 2 2 2
A-965 Washers 2 2 2 2
A- 848 Flexloc.k Nuts 2 ´•2 2 2
B-828-8 PISTON ASSEMBLY 1 1
B-966-8 Piston Unit 1 1
B-966 Piston 1 1
A-862 Plastic Bushing 1 1
A-826-8 Push Rods 2 2
A-114-G Rod Staking Pins 2 2
A-921-1 Forks 2 2
A-2039 Socket Head Set Screws 2 2
A-827-1 Rod Sleeves 2 2
A-965 Washers 2 2
A-848-1 Flexlock Nuts 2 2
HYDRAULIC ASSOCIATED PARTS
B-806 Cylinder 1 1 1 1 1 1
PRP-909-13 Cylinder "O" Ring 1 1 1 1 1 1
A-810 Dust Seal 1 1 1 1 1 1
PRP-902-46 Piston "O" Rili~ 1 1 1 1 1 1
A-SS-A Block, Pitch Change 2 2 2 2 2 2

32
 No. Required
Nomenclature Hr: BHC HC BHC HC HC
Part No,
F-l F-l F-1A F-1A K-l G1

SPINNER ASSEMBIJY (No Stops) 1 1

835-6
Dome (No doublers, H.T., Not Polished) 1 1
C-888-4
Screws 14 14
ANS26C1032R7
1 1
C-885 Adaptor Ring
SPINNER ASSEMBLY (No Stops) 1 1 1 1
835-13
Dome´• (Not Polished) 1 1 1 1
C-888-4
ANS26C1032R7 Screws 14 14 14 14
Bulkhead (No Stops) 1 1 1 1
C-S07-1
SPINNER MOUNTING PARTS
Hex Head Bolts 4 4 4 4
AN4-14A
Washers 4 4 4 4
AN960-416
Kaylock Nuts (AN363-428 Flexlock Optional) 4 4 4 4
H10-4

PARTS LIST

Model HC-A2X20-1
Assembly Drawing D-2025

Part No. Nomenclature No. Required

HUB SPIDER UNIT 1

840-63
Hub Spider 1
C-2026
Pilot Tube 2
A-1S´•8L
Bushing 1
A-1S5
HUB SPIDER UNIT (Optional) 1
840-67
Hub Spider 1
C-2026-2
Pilot Tube 2
A-1S8L
Bushing 1
A-1S5
HUB ASSOCIATED PARTS
Ball Spacer 2
A-311
Blade Bearing 2
A-971
Bearing Retention Ring 2
A-2027
Guide Ring 2
A-9’i2
Wire Retention Ring 2
A-974
"O" Ring, Blade 2
PRP-909-8
Guide Collar Unit 1
834-3B
Rear Cone 1
A-50-3
"O Ring, Shaft 1
PRP-909-7
A-63-B Hub Nut 1
A-870 jar B-2063
Puller Ring (Not Req’d With B-2063) 1
1
A-847 Pin Safety, Hub Lock
CLAMP ASSEMBLY 2
838-25
Clamp 2
C-3-1A
Linkscrew 2
A-295
Staking Pin 2
A-285
Zerk Fitting 6
MS-15001-1
Counterweight Unit 2
833-24
Counterweight Staking Pin 2
A-65
Counterweight Socket Head Screw 4
A-2036-32
Socket Screw Staking Pin 4
A-286
Clamp Gasket 4
A-47-1
Socket Screw 4
A-282
Cotter Pin 4
AN380-3-2
4
A-2017 Clamp Bolts
4
A-2043 Clamp Nuts
Washer 4
AN960-6´•16
Lubricaps 4
No. 3
CLAMP ASSOCIATED PARTS
Balance Weight As Needed
A-48
4
ANS01A10-6 Weight Screws
33
 Part No. Nomenclature No. Required
B-828-3 PISTON ASSEMBLY 1
B-966-3 Piston Unit 1
B-966 Piston 1
A-862 Plastic Bushing 1
A-826-3 Push Rod 2
A-114G Rod Staking Pin 2
A-921-1 Fork 2
A-2039 Set Screw 2
A-827-i Rod Sleeve 2
A-970-4 Spacer 2
A-965 Washer 2
A-848 Flexlock Nut 2
HYDRAULIC ASSOCIATED PARTS
B-806-1 Cylinder 1
PRP-909-13 Cylinder "O" Ring 1
PRP-902-46 Piston "O" Ring 1
A-810 Dust Seal 1
A-95-A Block, Pitch Change 2
835-15 SPINNER ASSEMBLY (No Stops) 1
C-888-4 Dome (Not Polished) 1
AN526C1032R7 Dome Mounting Screws 14
C-807-6 Bulkhead 1

Assembly Drawing PARTS LIST

D-220 Model -4B(")

Nomenclature
No. Required
Part No.
-4 -4A -4B

840-66 HUB SPIDER UNIT 1 1 1

C-2026-1 Hub Spider 1 1 1
A-158L Pilot Tube 2 2 2
A-218 Bushing 1 1 1
HUB ASSOCIATED PARTS
A-311 Ball Spacer 2 2 2
834-3 Guide~ Collar Unit (Without Spinner) 1
A-971 Blade Bearing 2 2 2
A-972 Guide Ring 2 2 2
A-974 Wire Retention Ring 2 2 2
PRP-909-8 "O" Ring, Blade 2 2 2
Puller Ring (Not
A-2053A-219 ~or B-2059 Shaft Nut
Req’d With B-2059) 1
1
1
1
1
1
A-2054 Seal, Shaft Nut 1 1 1
PRP-909-10 "O" Ring, Outer Sea´•l 1 1 1
PRP-909-9 (’O)’ Ring, Inner Seal 1 1 1
AN380-3-3 Cotter Pins, Seal Safety 4 4 4
834-10 Guide´• Collar Unit, Spinner Mtg. 1
834-11 Guide Collar Unit, Spinner Mtg, 1
A-2027 Wire Bearing Ring 2 2 2
838-2 CLAMP ASSEMBrtY 2 2 2
C-3-1A Clamp 2 2 2
A-295 Linkscrew 2 2 2
A-2;85 Staking Pin 2 2 2
MS-15001-1 Zerk Fitting 6 6 6
B-891-1 Countemveight Unit 2 2 2
A-65 Counterweight Staking Pin 2 2 2
A-2036-30 Counterweight Socket Head Screw 4 4 4
A-285 Socket Screw Staking Pin (AN380-3-2 Cotter Pin 4 4 4
A-47-1 Clamp Gasket Optional) 4 4 4
A-282 Socket Screw 4 4 4
AN380-3-2 Cotter Pin 4 4 4
Ai2017 Clamp Bolts 4 4 4
A12043 Clamp Nuts 4 4 4
AN960-616 Washer 4 4 4
No. 3 Lubricaps 4 4 4
Denotes dash number of A-224 Oil Seal Assy. See next chart for breakdown.
34
 No. Required
Part No. Nomenclature
-4 -4A -4B

CLAMP ASSOCIATED PARTS

A-48 Balance~ Weight As Needed
ANS01A10-6 Weight Screws 4 4 4

B-828-3 PISTON ASSEMBLY 1 1 1

B-966-3 Piston Unit 1 1 1
B-966 Piston 1 1 1
A-862 Plastic Bushing 1 1 1
A-826-3 Push Rod 2 2 2
A-114F Rod Staking Pin 2 2 2
A-921-1 Fork 2 2 2
A-2039 Set Screw 2 2 2
A-827-2 Rod Sleeve 2 2 2
A-965 Washer 2 2 2
A- 848 Flexlock Nut 2 2 2
A-970-4 Spacer 2 2 2

HYDRAULIC ASSOCIATED PARTS

B-806-1 Cylinder 1 1 1
PRP-909-13 Cylinder "O" Ring 1 1 1
PRP-902-46 Piston "O" Ring 1 1 1
A-863 Dust Seal 1 1 1
A-S5-A Block,Pitch Change 2 2 2

OIL TRANSFER SEAL ASSEMBLY 1 1 1

A-224-(*)
(See parts list below)

PARTS LIST

Moldel Oil Transfer Seal Assy.

No. Required
Part No. Nomenclature
A-224 A-224-1 A-224-2

A-216 Slip Ring Sleeve 1

A-221 Ring 4 4 4
A-216-1 Slip Ring Sleeve 1 I
B-214 Cap, Slip Ring 1 1 1
A-217 Screw, Oil Transfer 1 1 1
PRP-902-6 "O" Ring, Screw Seal 1 1 1
455354 National Seal 1 1
AN75A25 Hex Head Bolts 4 4 4
Washers 4 4 4
AN960-416
B-215 Slip Ring 1
Gasket 1 1 1
A-135
Slinger, Oil 1 1
A-228
1 1
A-234 Cone, Rear
slip Ring 1 1
B-241
Ring "B" 1
A-237
"O" Ring, Compound 12137 or 17507 1
PRP-909-13
"0" Ring, Teflon 1
Halogen 6227-236
"O" Ring, Compound 141-70 1
PRP-909-18
Ring "A" 1
A-236
4
A-239 Clip, Spring
Pin (Optional) 1
A-242
1
A-884-3 Spring (Optional)
SPS Rolled Pin 1
31-8-062-1000

Denotes dash number of A-224 Oil Seal Assembly.

35
 PARTS LIST
Optional Spinners for use on the Hartzell
ModelHC-A2X20-4, -4A, -4B Propeller

Part No. Nomenclature

No. Required
-4 -4A -4B
837-6 HARTZELL SPINNER FOR BEECH 35 1
C-227 Bulkhead 1
C-226 Dome 1
ANS26C1032RS Screws 12
AN7-11 Bolts 4
AN365-720 Nuts (A-1373, A-2498 Optional) 4
BEECH SPINNERS FOR BEECH 35 SERIES
For Beech Hub Models B200 and 215
#3.51960026-12 Beech Support Assembly 1
#36-960026-14 Beech Dome 1
AN4-6 Bolts 4
AN310-4 Nuts 4
For Beech Hub Model R203
#35-960010-12 Beech Support 1
#35-960026-1;?1 Beech Dome 1
AN7-6 Bolts 4
AN310-7 Nuts 4

NOTE: FOR BEECH MODELS ONLY: Modify dome´• as follows:

1, Install B-223 pilot on center cut hole in front bulkhead to clear
piston.
2. Enlarge blade cutouts to clear blades, etc.

PARTS LIST
Models HC-A3XF-2, -2A, -2B, -2C; PHC-A3XF-2B
Assembly Drawing D-1495
No. Required
Part No. Nomenclature HC HC HC PHC HC
-2 -2A -2B -2B -2C
840-80 HUB SPIDER UNIT 1
C-1477-1 Hub Spider 1
A-158L Pilot Tubes 3
840-64 HUB SPIDER UNIT 1 1 1 1
C-1’477 Hub Spider 1 1 1 1
A-1S8L Pilot Tubes 3 3 3 3
HUB ASSOCIATED PARTS
A-971 Blade Bearing, Split 3 3 3 3 3
A-2027 Wire Ring, Bearing 3 3 3 3 3
A-311 Ball Spacer (Optional) 3 3 3 3 3
A-972 Guide Ring 3 3 3 3 3
A-974 Wire Retention Ring 3 3 3 3 3
PRP-909-6 "O" Ring, Blade 3 3 3 3 3
PRP-909-6 "O" Ring, Shaft 1 1 1 1 1
.5002x1 Hub Dowel Pins 2 2 2 2 2
AN960-816 Washers, Hub Mounting 6 6 6* 6* 6
A-2040 or A-1333-4 Hex Head Bolts 6 6 6* 6* 6
838-52 CLAMP ASSEMBLY (For use with 9333C-3 Blades) 3
C-3-5A Clamp 3
A-304 Linkscrew 3
A-285 Staking Pin, Linkscrew 3
MS-15001-1 Zerk Fittings 6
833-26 Counterweight Unit 3
A-65 Counterweight Staking Pin 3
A-2036-32 Ctwt. Socket Head Cap Screws 6
A-285 Staking Pins, Ctwt. Sk. Sc. (AN380-3-2 Cotter Pin 6
A-47-1 Clamp Gaskets Optional) 6
~e (18_~_A_N_9_60-816 WaShers pr (6) -2482_1 Washers With (6) A-2041 or A- 1333-5 Hex Head Bolts
When 836-36P Spinner Assembly Is Installed.
36
 No. Required
Part No. Nomenclature HC HC HC: PHC HC
-2 -2A -2B -2B -2C

CLAMP ASSEMBLY (For 9333C-3 Blades, Cont’d)

A-282 Socket Screws, Clamp 6
AN580-3-2 Cotter Pins, Sk. Sc. 6
A-2017 Clamp Bolts 6
AN960-616 Washers 6
A-2043 Clamp Nuts 6

838-11A CLAMP ASSEMBI,Y (For use with 7636D Blades) 3 3

C-3-5A Clamp 3 3
A-304 Linkscrew 3 3
A-285 Staking Pin, Linkscrew 3 3
MS15001-1 Zerk Fittings 6 6
B-271-1A Counterweight Unit 3 3
A-65 Counterweight Staking Pin 3 3
A-2036-30 Ctwt. Socket Head Cap Screws 6 6
A-285 Staking Pins, Ctwt. Sk. Sc. (AN380-3-2 Cotter Pin Optional) 6 6
A-47-1 Clamp Gaskets 6 6
A-282 Socket Screws, Clamp 6 6
AN380-3-2 Cotter Pins, Sk. Sc. 6 6
A-2017 Clamp Bolts 6 6
AN960-616 Washers 6 6
A-2043 Clamp Nuts 6 6

838-6 CLAMP ASSEMBLY (For use with 8433 8833 Blades) 3 3

C-3-5A Clamp 3 3
A-304 Linkscrew 3 3
A-285 Staking Pin, Linkscrew 3 3
MS15001-1 Zerk Fittings 6 6
833-4 Counterweight Unit 3 3
A-65 Counterweight Staking Pin 3 3
A-2036-30 Ctwt. Socket Head Cap Screws 6 6
A-285 Staking Pins, Ctwt. Sk. Sc. (AN380-3-2 Cotter Pin Optional) 6 6
A-47-1 Clamp Gaskets 6 6
A-282 Socket Screws, Clamp 6 6
AN380-3-2 Cotter Pins, Sk. Sc. 6 6
A-2017 Clamp Bolts 6 6
AN960-616 Washers 6 6
A-2043 Clamp Nuts 6 6
CLAMP ASSOCIATED PARTS
A-29 Weight Slugs 9 9
A-48 Balance Weights As Needed
ANS01A10-6 Weight Screws 6 6 6 6 6
A-881 Stop Plate (A-881-2 Optional) 3 3 3 3
A-2016 Hex Head Bolts 6 6 6 6
A-944 Sleeve, Linkscrew 3 3 3 3 3
AN380-3-3 CotterPin, Sleeve 3 3 3 3 3

830-4 AUTO STOP UNIT 3 3 3 3

B-882-4 Bracket 3 3 3 3
A-883 Pin 3 3 3 3
A-884 Spring 3 3 3 3
AN936A10 Washer 3 3 3 3
AN380-3-3 Cotter Pin 3 3 3 3
AUTO STOP ASSOCIATED PARTS
AN74-5 Hex Head Bolts 6 6 6 6
831-4 FEATHERING SPRING ASSEMBLY 1 1 1 1 1
B-855A Pilot Tube 1 1 1 1 1
A-856 Mushroom 1 1 1 1 1
B-953 Inner Spring 1 1 1 1 1
B-853 Outer Spring 1 1 1 1
A-860-3 Spacer Tube 1 1 1 I 1
A-857 Spring Retainer 1 1 1 1 1
A-858 Split Ring 1 1 1 1 1
832-17 PISTON ASSEMBLY 1 1 1 1 1
C-1401-2 Piston Unit 1 1 1 1 1
Piston 1 1 1 1 1
C-1401-2 Det. #1
A-862 Plastic Bushing 1 1 1 1 1

37
 No. Required
Part No. Nomenclature HC HC HC PHC HC
-2 -2A -2B -2B -2C
PISTON ASSEMBLY (Continued)
A-817-2 Guide Rods 3 3 3 3 3
A-ll´•4-F Staking Pins, Rod 3 3 3 3 3
A-946 Bronze Bushings 6 6 6 6 6
A-1464 Link Pin Units 3 3 3 3 3
AN501A10-6 Safety Screws 3 3 3 3 3
A-1444 Washers 3 3 3 3 3
A-2037 Socket Head Cap Screws 3 3 3 3 3
AN316-5R Jam Nuts 3 3 3 3 3
A-861-3 Link Arms 3 3 3 3 3
834-1 GUIDE COLLAR UNIT 1 1 1 1 1
B-1402 Guide Collar 1 1 1 1 1
A-116D-1 Plastic Bushings 3 3 3 3 3
A-2038-12 Socket Head Cap Screw 1 1 1 1 1
A-114-C Staking Pin 1 1 1 1 1
ASSOCIATED PARTS
B-854 Cylinder 1 1 1 1 1
PRP-909-13 "O" Ring, Cylinder 1 1 1 1 1
A-859 Split Retainer Ring 1 1 1 1 1
A-899( Stop Plates 2 2 2 2 2
AN501A10-6 Screws, Stop Plate 4 4 4 4 4
PRP-902-4´•6 Piston "O" Ring 1 1 1 1 1
A-863 Dust Seal 1 1 1 1 1
PRP-914-12 "O" Ring, Pilot Tube I 1 1 1 1
A-880-2 Flexlock Nut 1 1 1 1 1
A-153~6 Spacer, Spring 1
SPINNER BOLT, NUT WASHER KIT
AN4-16A Hex Head Bolts 6 6 6 6 6
A-1864 Plastic Washers (Thick) 6 6
AN960-416 Washers 6 6 6
AN960-416L Washers 12 12 12 12 12
H10-4 Kaylock Nuts 6 6 6 6 6
836-18P SPINNER ASSEMBLY (No Stops) 1 1 1
D-1367-6 Dome (Polished) 1 1 1
D-1415-4 Bulkhead Unit 1 1 1
AN526C1032R8 Screws 12 12 12
836-19P ANTI-ICING SPINNER ASSEMBLY (No Stops) 1 1 1
D-1367-7P Dome (Polished) 1 1 1
AN526C1032R8 Screws 12 12 12
D-1415-6 Bulkhead Assembly 1 1 1
D-1415-5 Bulkhead Unit 1 1 1
D-1433 Slinger Ring 1 1 1
836-37P SPINNER ASSEMBLY (No Stops) 1 1
C-1872-4 Dome (Polished) 1 1
D-1976-8R Bulkhead Assembly 1 1
ANS26C1032R8 Screws 18 18
´•*836-36P ANTI-ICING SPINNER ASSEMBLY (No Stops) 1 1
0-1872-4 Dome (Polished) 1 1
ANS26C1032RS Screws 18 18
D-1976-6R Bulkhead Assembly 1 1
D-1976-5R Bulkhead Unit 1 1
A-2688 Anti-Icing Kit 1 1

Use (18) AN960-816 Washers or (6) A-2482-1 Washers With (6) A-2041 or A-1333-5 Hex Head Bolts
When 836-36P Spinner Assembly Is Installed.

38
 PARTS LIST

Assembly Drawing D-1446

Model HC-A3XK-2, -2A
No. Required
Part No. Nomenclature
-2 -2A

840-56 HUB SPIDER SUB-ASSEMBLY 1 1

C-1476 Hub Spider 1 1
A-158L Pilot Tube 3 3
HUB ASSOCIATED PARTS
A-2027 Bearing Retention Ring 3 3
A-971 Blade Bearing, Split 3 3
A-972 Guide Ring 3 3
A-974 Wire Ring 3 3
PRP-909-6 "O" Ring, Blade 3 3
B-1,322 Shim, Hub Mounting 1 1
PRP-902-32 "O" Ring 1 1
A-1333-3 Hex Head Bolt 3 3
A-1328 Screw, Ferry 3 3
A-311 Ball Spacer 3 3
838-51 CLAMP ASSEMBLY 3
C-3-5A Clamp 3
A-304 Linkscrew 3
A-285 Staking Pin, Linkscrew 3
MS-15001-1 Zerk Fitting 6
833-15 Counterweight Assembly 3
A-65 Counterweight Staking Pin 3
A-2036-30 Counterweight Screws 6
P;N380-3-2 Cotter Pin, Counterweight 6
A-47-1 Clamp Gasket 6
A-282 Socket Screw 6
A-2017 Clamp Bolts 6
AN960-616 Mounfing Washer 6
A-2043 Clamp Nut 6
A-285 Staking Pins, Socket Head Cap Screw 6
838-60 CLAMP ASSEMBLY 3
C-3-SA Clamp 3
A-304 Linkscrew 3
A-285 Staking Pin, Linkscrew 3
MS-15001-1 Zerk Fitting 6
B-1437-1 Counterweight Assembly 3
A-65 Counterweight Staking Pin 3
A-2036-32 Counterweight; Scre´•ws 6
P+N880-3-2 Cotter Pin 6
A-47-1 Clamp Gasket 6
A-282 Socket Screw 6
A-2017 Clamp Bolts 6
AN960-616 Mounting Washer 6
A-2043 Clamp Nuts 6
A-285 Staking Pina, Socket Head Cap Screw 6
CLAMP ASSOCIATED PARTS
A-48 Balance Weights As Needed
ANS01-A10-6 Screw, Balance Weight 6 6
A-881 Auto, Stop Plate 3 3
AN3H5A Hex Head Bolts, Plate 6 6
A-944 Screw Bushing 3 3
AN380-3-3 Cotter Pin, Sleeve 3 3
830-9B AUTO STOP UNIT 3 3
B-984-2 Bracket 3 3
A-883 Pin 3 3
A-884 Spring 3 3
AN380-3-3 Cotter Pin 3 3
AN93´•6A10 Washer 3 3
AUTO STOP MOUNTING PARTS
AN74-5 Hex Head Bolts 6 6

39
 No. Required
Part No. Nomencl9~tu;e
-2 -2A

831-4 F%ATHERING SPRING UNIT 1 1

B-8S5A Pilot Tube Unit 1 1
A-85´•8 Split Ring 1 1
A-857 Spring Retainer 1 1
A-860-3 Spacer Tube 1 1
B-953 Inner Spring 1 1
B-853 Outer Spring 1 1
A-856 Mushroom 1 1

832-17 PISTON ASSEMBI~Y 1 1

C-1401-2 Piston Unit 1 1
C-1401-2 Det. #1 Piston 1 1
A-862 Plastic Bushing 1 1
A-817-2 Guide Rod 3 3
A-114-B Staking Pin 3 3
A-946 Bushing 6 6
A-1444 Washer 3 3
AN316-5R Jam Nut 3 3
A-2037 Socket Set Screw 3 3
A-1464 Safety Link 3 3
AN501A10-6 Safety Screw 3 3
A-861-3 Link Arm 3 3

834-1 GUIDE COLLAR UNIT 1 1

B-1402 Guide Collar 1 1
A-116D-1 Plastic Bushing 3 3
A-114C Staking Pin 1 1
A-2 038-12 Socket Cap Screw 1 1

ASSOCIATED PARTS
B-854 Cylinder 1 1
PRP-909-13 "O" Ring, Cylinder 1 1
PRP-902-46 "O" Ring, Piston 1 1
A-863 Dust Seel 1 1
A-8ri9 Split Retainer Ring 1 1
A-899 Stop Plate 2 2
AN501-A10-6 Screws, Stop Plate 4 4
PRP-914-12 "O" Ring 1 1
A-880-2 Flexlock Nut 1 1

835-14 SPINNER ASSEMBLY 1

C-888-6 Spinner Dome 1
ANS26C1032R7 Scre~ws 15
C-885-1 Spinner Adaptor 1

C-2513 SPINNER ASSEMBLY (AERO DESIGN) 1 1

C-2531-1 Dome 1 1
C-2512 Adaptor Assembly 1 1
AN526C1032R8 Screws 15 15
ANS26C1032R7 Screws 6 6

PARTS LIST
Mc~del HC-A3X20-2, 12L
Assembly Drawing D-1485

No. Required
Part No. Nomenclature
-2 -2L

840-65 HUB SPIDER UNIT 1 1

C-1482 Hub Spider 1 1
A-1S8L Pilot Tube 3 3
A-155 Bushing 1 1
 No. Required
Part No. Nomenclature
-2 -2L

HUB ASSOCIATED PARTS

A-311 Ball Spacer 3 3
A-971 Blade Bearing 3 3
A-2027 Wire Ring, Bearing 3 3
A-972 Guide Ring 3 3
A-974 Wire Retention Rin~ 3 3
PRP-909-8 Blade ’’O" Ring 3 3
A-50-3 Rear Cone 1 1
PRP-909-7 "O" Ring Shaft 1 1
A-63-B Hub Nut 1 1
A-870 t
or B-2063
Puller Ring(Not Req’d With B-2063) 1
1
1
1
A-847 Pin, Safety

838-6 CLAMP ASSEMBLY (8433, 8833 Blades) 3

C-S-5A Clamp 3
833-4 Counterweight Unit 3

838-23 CLAMP ASSEMBLY (9333 Blades) 3

C-3-SA Clamp 3
833-4B Counterweight Unit 3
A-890 Weight Slugs 3
AN4H7A HexHead Bolts 6

838-18 CLAMP ASSEMBLY (L8433, L8433H Blades) 3

C-3-SAIL Clamp 3
833-4 Counterweight Unit 8

838-23L CLAMP ASSEMBLY (L9333CH-3, -5 Blades) 3

C-S-SAL Clamp 3
833-4L Counterweight Unit 3
A-890-5 Weight Slugs 3
AN4H1OA Hex Head Bolts 6

838-52 CLAMP ASSEMBLY (9333(=-3 Blades) 3

C-3-5A Clamp 3
833-26 Counterweight Unit 3

COMMON CLAMP PARTS

A-304 Linkscrews 3 3
A-285 Staking Pin, Linkscrew 3 3
MS-15001-1 Zerk Fitting 6 6
A-65 Counterweight Staking Pin 3 3
A-2036-30 (-32 for Counterweight Socket Head Screws 6 6
A-285 838-52)‘ Counterweight Sc. Staking Pin (AN380-3-2 Cotter 6 6
A-47-1 Clamp Gasket Pin Optional) 6 6
A-282 Socket Screw 6 6
AN380-3-2 Cotter Pin 6 6
A-2017 Clamp Bolts 6 6
XN960-616 Washer 6 6
A-2043 Clamp Nuts 6 6
No. 3 Lubricaps 6 6

CLAMP ASSOCIATED PARTS

A-48 Balance Weight As Needed
ANS01A10-6 Weight Screw 6 6
A-944 Sleeve, Linkscrew 3 3
AN380-3-3 Cotter Pin, Linkscrew 3 3
A-881 Stop Plate 3 3
Plate Screw 6 6
A-2016
832-14 PISTON ASSEMBLY 1
C-1401-3 Piston Unit 1
C-1401-3 Det. ~1 Piston 1
A-862 Plastic Bushing 1
A-817-2 Guide Rod 3
A-114-B Rod Staking Pin 3

41
 No. Required
Part No. Nomenclature
-2 -2L

A-946 Bronze Bushing 6

A12037 Socket Screw 3
A-1444 Washer 3
AN316-5R Jam Nut 3
A-861-3 Link Arm 3
A-1464 Link Pin Unit 3
ANS01A10-6 Safety Screw 3
832-14L PISTON ASSEMBLY 1
C-1401-3L Piston Unit 1
C-1401-3L Det. #1 Piston 1
A-862 Plastic Bushing 1
A-817-2 Guide Rod 3
A-114-B Rod Staking Pin 3
A-946 Bronze Bushing 6
A-2037 Socket Screw 3
A-1444 Washer 3
AN316-5R Jam Nut 3
A-861-3L Link Arm 3
A-1464 Link Pin Unit 3
AN501A10-6 Safety Screw 3

834-1 GUIDE COLLAR UNIT 1

B-1402 Guide Collar 1
A-116D-1 Plastic Bushing 3
A-114-C Staking Pin 1
A-2038-12 Socket Head Cap Screw 1

834-13; GUIDE COLLAR UNIT 1

B-1402L Guide Collar 1
A-116D-1 Plastic Bushing 3
A-114-C Staking Pin 1
A-2038-12 Socket Head Cap Screw 1

831-11 FEATHERING SPRING ASSEMBLY 1 1

B-868A Pilot Tube 1 1
A-871 Mushroom 1 1
B-1363-1 Spring 1 1
A-866 Spring Retainer, Rear 1 1
A-867 Split Retainer, Rear 1 1

HYDRAULIC ASSOCIATED PARTS

B-854 Cylinder 1 1
PRP-909-13 Cylinder "O" Ring 1 1
A-859 Split Retainer, Front 1 1
A-899 Feathering Stop 2 2
ANS01A10-6 Stop Mounting Screw 4 4
PRP-914-8 Nut "O" Ring 1 1
PRP-902-46 Piston "O" Ring 1 1
A-863 Dust Seal 1 1
A-880-1 Flexlock Nut, Piston 1 1
835-10S SPINNER ASSEMBLY (With Stops) 1
C-888-6 Dome 1
AN526C1032R7 Dome Mounting Screw 15
C-807-7S Bulkhead (With 830-5 Stops) 1
C-807-10 Bulkhead (Without Stops) 1
830-5 Auto High Pitch Stop Units 3
B-882-5 Bracket 3
A-883 Pin 3
A-884 Spring 3
AN936A10 Washer (Internal Lock) 3
AN380-3-3 Cotter Pin 3
AN4-15A Hex Head Bolt 6
AN960-416 Washer 6
H10-4 Kaylock Nut 6

42
 No. Required
Part No. Nomenclature
-2 -2L

835-113 SPINNER ASSEMBLY (With Stops) 1

C-888-6 Dome 1
AN526C1032R7 Dome Mounting Screw 15
C-807-7LS Bulkhead (With 830-5L Stops) 1
C-807-10 Bulkhead (Without Stops) 1
830-5L Auto High Pitch Stop Unit 3
B-882-5L Bracket 3
A-883 Pin 3
A-884 Spring 3
AN936A10 Washer (Internal Lock) 3
AN380-3-3 Cotter Pin 3
AN4-15A Hex Head Bolt 6
AN960-416 Washer 6
H10-4 Kaylock Nut 6

836-6SP SPINNER ASSEMBLY (Polished, With Stops) 1

D-1367-6P Dome (Polished) 1

AN526C1032RS Dome Mounting Screws 24
D-1414-6 Bulkhead (With 830-5 Stops) 1

836-7SP SPINNER ASSEMBLY 1

(Anti-Icing, Polished, With Stops)
D-1367-7P Dome (Polished) 1
ANS26C1032R8 Dome Mounting Screw 24
D-1414-7 Anti-Icing Bulkhead (With 830-5 Stops) 1

836-7ASP SPINNER ASSEMBLY 1

(Anti-Icing, Polished, With Stops)
D-1367-7AP Dome (Polished) 1
AN526C1032R8 Dome Mounting Screw 24
D-1414-7 Anti-Icing Bulkhead (With 530-5 Stops) 1

836-22SPR SPINNER ASSEMBLY 1

(Anti-Icing, Polished, With Stops)
C-1888P Dome (Polished) 1
AN526C1032RS Dome Mounting Screw 24
D-1871-7R Anti-Icing Bulkhead (With 830-18 Stops) 1

PARTS LIST
Model HC-A3XK-4

Assembly Drawing D-1484

Part No. Nomenclature No. Required

840-56 HUB SPIDER UNIT 1

C-1476 Hub Spider 1

A-1S8L Pilot Tube 3

HUB ASSOCIATED PARTS

A-311 Ball Spacer (Optional) 3
A-971 Split Bearing, Blade 3
A-2027 Wire Retention Ring, Bearing 3
A-972 Guide Ring 3
A-974 Wire Retention Ring 3
PRP-909-6 "O" Ring, Blade 3
PRP-902-32 "O" Ring, Shaft 1
B-1322 Shim 1
A-1333-3 Hex Head Bolts 6

43
 Part No. Nomenclature No. Required
838-58 CLAMP ASSEMBLY 3
C-3-1E Clamp 3
MS-15001-1 Zerk Fitting 6
B-1480 Counterweight 3
A-2036-22 Socket Head Cap Screw, Co;unterweight 6
A-47-1 Gaskets, Clamp 6
A-282 Socket Screw, Clamp 6
AN380-3-2 Cotter Pin, Sk. Sc. 6
A-2017 Clamp Bolts 6
AN960-616 77CTasher 6
A-2043 Clamp Nuts 6
CLAMP ASSOCIATED PARTS
A-48 Balance Weight As Needed
ANS01A10-6 Weight Screw 6
A-944 Sleeve 3
AN380-3-3 Cotter Pin, Sleeve 3
832-33 PISTON ASSEMBLY 1
C-1881-1 Piston Unit 1
C-1881-1 Det. #1 Piston 1
A-862-2 Plastic Bushing 1
A-946 Bronze Bushing 6
A-817-4 Guide Rod 3
A-114-G Sta.king Pin 3
A-2037 Socket Head Cap Screw 3
AN316-5R Check Nut 3
A-1444 Washer 3
A-1464 Zlink Pin Unit 3
ANS01A10-6 Safety Screw 3
A-861-3L Link Arm 3

HYDRAULIC ASSOCIATED PARTS

B-18´•82 Cylinder 1
PRP-909-13 "O" Ring, Cylinder 1
PRP-902-50 "O" Ring, Piston 1
B-1843 Dust Seal 1
834-7B Guide Collar Unit 1
C-2513 SPINNER ASSEMBLY (Optional) 1
C-2531-1 Spinner Dome 1
ANS26C1032RS Screw, Dome Mounting 15
C-2512 Adaptor Ring Assembly 1
ANS26C1032R7 Screw, Dome Mounting 6

PARTS LIST
Model HC-92ZK-1D
Assembly Drawing D-1334
Part No. Nomenclature No. Required
840-32 HUB ASSEMBLY 1
C-1314-4 Hub Spidt~r 1
A-1308 Pilot Tubes 2
834-9 Guide Collar Unit 1
A-1332-2 Staking Pins, Guide Collar 2
A-1333 Hex Head Bolts 2
A-1333-2 Hex Head Bolts 2
HUB ASSOCIATED PARTS
A-1889 Ball Spacer 2
A-1303A Bearing, Blade 2
A-1331 Split Ring 2
PRP-909-7 "O" Ring, Blade Seal 2
PRP-902-32 "O"´• Ring, Shaft Seal 1
A-1333 Hex Head Bolts 2
B-1322 Shim 1

44
 Part No. Nomenclature No. Required

838-68 CLAMP COUNTERWEIGHT ASSEMBLY 2

C-1301-1 Clamp 2
A-295 Linkscrew 2
A-285 Linkscrew Staking Pin 2
MS-15001-1 Zerk Fitting 2
B-1354-4 Counterweight 2
A-2036-32 Socket Head Cap Screws, Ctwt. 4
A-285 Staking Pins, Sk. Sc. 4
A-65 Staking Pin, Ctwt. 2
Gaskets 4
A-1306
A-282 Socket Screws 4
AN380-3-2 Cotter Pins 4
A-1372 Clamp Bolts 4
A-1373 Clamp Nuts 4
No. 3 Lubricaps 4

CLAMP ASSOCIATED PARTS

2-45 Parker "O" Ring, Blade 2

A-1305 Balance Weight As Needed

AN501A10-6 Weight Screws 4

B-828-8 PISTON ASSEMBLY 1

B-966-8 Piston Unit 1

B-966 Piston 1
A-862 Plastic Bushing 1
A-826-8 Push Rods 2
A-114G Rod Staking Pina 2
A-921-1 Forks 2
A-2039 Set Screws, Fork 2
A-827-1 Rod Sleeves 2
A-965 Washers 2
A-848 Flexlock Nuts 2

ASSOCIATED HYDRAULIC PARTS

B-806 Cylinder 1
PRP-909-13 "O" Ring, Cylinder 1
PRP-902-46 "O" Ring, Piston 1
A-810 Felt Seal 1
A-SS-A Block, Pitch Change 2

C-2513-3 SPINNER ASSEMBLY 1

C-2512-3 Spinner Adaptor Ring Unit 1

C-2531-8 Spinner Dome 1
AN526C1032R7 Screws, Dome Mounting 16

PARTS LIST
Model BHC-928F-8D
Assembly Drawing D-1334

No. Required
Part No. Nomenclature
-8D

840-68 HUB ASSEMBLY 1

C-1304-6 Hub Spider 1
A-1308 Pilot Tubes 2
834-8 Guide Collar Unit 1
AT957-1 Staking Pins, Guide Collar 2
A-846-4 Brackets, Spinner 4
A-2051 Hex Head Bolts, Bracket Mtg. 4

45
 Part No. No. Required
Nomenclature
-8D

HUB ASSOCIATED PARTS

A-1889 Ball Spacer 2
A-1303A Bearing, Blade 2
A-1331 Split Ring 2
PRP-909-7 "O" Ring, Blade Seal 2
PRP-909-6 "O" Ring, Shaft Seal 1
A-2040 or A-1333-4 Hex Head Bolts 6
AN960-816 Washers 6
.5002x1 Danley Dowel Pins 2

838-31 CLAMP ASSEMBLY 2

C-1301-2 Clamp 2
A-295 Linkscrew 2
A-285 Linkscrew Staking Pin 2
MS-15001-1 Zerk Fitting 2
A-1306 Caskets, Clamp 4
A-282 Screws, Socket Head 4
AN380-3-2 Cotter Pins 4
A-1372 Clamp Bolts 4
A-1373 Clamp Nuts 4
No. 3 Lubricaps 4

CLAMP ASSOCIATED PARTS

2-45 Parker "O" Ring, Blade 2
A-1305 Balance Weight As Needed
ANS01A10-6 Weight Screws 4

B-8ZS-9L PISTON ASSEMBLY 1

B-966-11 Piston Unit 1
B-966 Piston 1
A-862 Plastic Bushing 1
A-826-11 Push Rods 2
A-114G Rod Staking Pins 2
A-921L-1 Forks 2
A-2039 Set Screws, Fork 2
A-827-1 Rod Sleeves 2
A-965 Washers 2
A-848 Fle~lock Nuts 2

ASSOCIATED HYDRAULIC PARTS

B-806 Cylinder 1
PRP-909-13 "O" Ring, Cylinder 1
PRP-902-46 "O" Ring, Piston 1
A-810 Felt Seal 1
A-SS-A Blocks, Pitch Change 2

835-13 SPINNER ASSEMBLY 1

C-807-1 Spinner Bulkhead 1
C-888-4 Spinner Dome (Not Polished) 1
AN526C1032R7 Screw, Dome Mounting 14
AN4-14A Hex Head Blots 4
AN960-416L Washers 4
H10-4 Kaylock Nuts 4

46
 PARTS LIST
Assembl y Drawing D-1334 Model HC-92ZK-8D t -8L
No. R´•equired
Part No. Nomenclature -8L
-8D

HUB ASSEMBLY 1
840-32
Hub Spider 1
C-1314-4
Pilot Tubes 2
A-1308
Guide Collar Unit 1
834-9
2
A-1332-2 Staking Pins, Guide Collar
Hex Head Bolts 2
A-1333
2
A-1333-2 Hex Head Bolts

HUB ASSEMBLY 1
840-32L
Hub Spider 1
C-1314-4
Pilot Tubes 2
A-130´•8
Guide Collar Unit 1
834-8
Staking Pins, Guide Collar 2
A-1332-2
Hex Head Bolts 2
A-1333
Hex Head Bolts 2
A-1333-2
HUB ASSOCIATED PARTS
Ball Spacer 2 2
A-1889
Bearing, Blade 2 2
A-1303A
2 2
A-1331 Split Ring
"O" Ring, Blade Seal 2 2
PRP-909-7
"O" Ring, Shaft Seal 1 1
PRP-902-82
Hex Head Bolts 2 2
A-1333
Shim 1 1
B-1322
CLAMP ASSEMBLY 2
838-31
Clamp 2
C-1301-2
Linkscrew 2
A-295
Linkscrew Staking Pin 2
A-285
MS-15001-1 Zerk Fitting 2
Gaskets, Clamp 4
A-1306
Screws, Socket Head 4
A-282
Cotter Pins 4
AN380-3-2
4
A-1372 Clamp Bolts
Nuts 4
A-1373 Clamp
Lubricaps 4
No. 3
CLAMP ASSEMBLY 2
838-85
Clamp 2
C-1301-4
Linkscrew 2
A-295
Staking Pin, Linkscrew 2
A-285
Zerk Fitting 2
MS-15001-1
Gaskets 4
A-1306
Socket Screws 4
A-282
Cotter Pins 4
AN380-3-2
4
A-1372 Clamp Bolts
Clamp Nuts 4
A-1373
4
No. 3 Lubricaps
CLAMP ASSOCIATED PARTS
Parker "O" Ring, Blade 2 2
2-45
A-1305 Balance Weight As Needed
4 4
ANS01A10-6 Weight Screw
PISTON ASSEMBLY 1
B-828-8L
Piston Unit 1
B-966-8
B-966 Piston 1
A-862 Plastic Bushing 1
Push Rods 2
A-826-8
A-114G Rod Staking Pins 2
A-921E1 Forks 2
Set Screws, Fork 2
A-2039
Rod Sleeves 2
A-827-1
Washers 2
A-965
Flexlock Nuts i!
A- 848
47
 Part No. No. Required
Nomenclature
-8D -8L
B-828 PISTON ASSEMBLY 1
B-966-8 Piston Unit
1
B-966 Piston 1
A-862 Plastic Bushing
1
A-826-8 Push Rods 2
A-114G Rod Staking Pins
2
A-921-1 Forks 2
A-2039 Set Screws, Fork 2
A-827-1 Rod Sleeves 2
A-965 Washers 2
A-848 Flexlock Nuts 2
ASSOCIATED HYDRAULIC PARTS
B-806 Cylinder 1 1
PRP-909-13 "O" Ring, Cylinder 1 1
PRP-902-46 "O" Ring, Piston 1 1
A-810 Felt Seal 1 1
A-SS-A Blocks, Pitch Change 2 2
835-6P SPINNER ASSEMBLY 1 1
C-885P Spinner Adaptor 1 1
C-888-4P Spinner Dome (Polishe´•d) 1 1
AN526C1032R7 Screws, Dome Mounting 14 14
835-16 SPINNER ASSEMBLY 1 1
C-885 Spinner Adaptor 1 1
C-888-4 Spinner Dome (Not Polished) 1 1
AN526C1032R7 Screws, Dome Mounting 1´•4 14

413
 PARTS LIST

Assembly Drawing D-1950 Model HC-93ZF-2

No. Required
Part No.
Nomenclature
-2A -2B

HUB SPIDER ASSEMBLY 1 1

840-7
1 1
C-1951 Hub Spider
Pilot Tube 3 3
A-1308
ASSOCIATED PARTS
6 6
A-2040 Bolts, Hub Mounting
Dowel Pin 2 2
.5002 xl
3 3
A-1303A Bearing, Blade
3 3
A-1331 Split Ring
"O" Ring, Shaft 1 1
PRP-909-6
"O" Ring, Blade 3 3
PRP-909-7
COUNTERWEIGHT SUB-ASSY. 3 3
838-22 CLAMP
3 3
C-1301 Clamp
3 3
833-11 Counterweight (For Cessna 620)
B-1953 (Alternate Counterweight)
3 3
A-65 Pin, Counterweight Staking
Linkscrew 3 3
A-304
6 6
A-1306 Gasket, Clamp
6 6
A-282 Screw, Socket Head
Screw. Socket Head 6 6
A-2036-30
6 6
A-1372 Clamp Bolts
2 2
A-285 Staking Pin, Linkficrew
4 4
AN380-3-2 Cotter Pin
4 4
MS15001-1 Zerk Fitting
4 4
A-1373 Clamp Nut
4 4
No. 3 Lubricaps
4 4
A-28% Staking Pin, Socket Screw
CLAMP ASSOCIATED PARTS
3 3
A-881-1 Stop Plate
G 6
AN3H2A Plate Bolt
As Needed
AW501A10-6 Screw, Balance Weight
As Needed
8-1305 Balance Weiffhts
3 3
AN380-3-3 Cotter Pin
3 3
A-944 Sleeve, Linkscrew
3 3
830-4 AUTOMATIC HIGH PITCH STOP ASSY.
3 3
B-882-4 Bracket, High Pitch Stop
3 3
A-883 Pin, High Pitch Stop 3
3
A-884 Spring, High Pitch Stop 3
3
AN-380-3-3 Cotter Pin
3 3
AN936A10 Washer
FEATHERING SPRING SUB-ASSEMBLY 1
831-4
Pilot Tube 1
B-855A
1
B-853 Spring, Feathering, Outer
Mushroom 1
A-856
1
A-857 Retainer, Spring
1
A-858 Split Ring
1
B-953 Spring, Feathering, Inner
1
A-860-3 Tube Spacer

831-8 FEATHERING SPRING SUB-ASSEMBLY

1
B-868A Pilot Tube
1
B-1428 Spring, Outer
B-1405 Spring
1
A-867 Split Ring
1
A-871 I\lushroom
1
A-1427 Retainer, Spring
1
A-1955 Spacer Spring

49
 Part No. No. Required
Nomenclature
-2A -2B

832-14 PISTON SUB-ASSEMBLY

1
C-1401-3 Piston
A-862 Bushing, Plastic 1
A-861-3 Link, Arm 3
A-1464 Link Pin Unit
3
AN501A10-6 Safety Screw 3
A-946 Bushing 6
A-114-F Pin, Guide 3
A-817-2 Rod, Guide 3
AN316-5R Nut, Jam 3
A-1444 Washer
3
A-2037 Socket Screw 3
832-17 PISTON SUB-ASSEMBLY 1
C-1401-2 Piston
A-862 Bushing, Plastic 1
A-861-3 Link, Arm 3
A-1464 Link Pin Unit 3
AN501A10-6 Safety Screw 3
A-946 Bushing 6
A-114-B Pin, Guide 3
A-817-2 Rod, Guide 3
AN316-5R Nut, Jam 3
A-1444 Washer 3
A-2037 Socket Screw
3

HYDRAULIC ASSOCIATED PARTS

B-854 Cylinder 1 1
PRP-909-13 "O" Ring
1 1
A-863 Seal, Dust 1 1
PRP-902-46 "O" Ring
1 1
A-859 Split, Retainer 1 1
A-899 Stop, F~athering 2 2
A-880-1 Nut
A-880-2 1
Nut 1
AN501A10-4 Stop Screws 4 4
PRP-914-12 Pilot Tube "O" Ring 1
PRP-914-8 Pilot Tube "O" Ring
1
834-1 GUIDE COLLAR SUB-ASSEMBLY 1 1
B-1402 Collar, Pilot 1 1
A-2038-12 Screw, Socket Head 1 1
A-116-D-1 Bushing, Plastic 3 3
A-114-C Staking Pin 1 1
836-2 SPINNER SUB-ASSEMBLY (LARGE)
D-1409 Spinner Dome 1 1
D-1415 Spinner Bulkhead Assembly 1 1
AN526C1032R8 Screws, Button, Head 18 18

PARTS LIST
Model HC-93Z20-1A1, -1B1
Assembly Drawing D-1375

Part No. No. Required

Nomenclature
-1Al -1B1

840-15 HUB SPIDER UNIT

1 1
C-1351 Hub Spider 1 1
A-1308 Pilot Tube 1 1
A-1SS Bushing Shaft 1 1

50
 No. Required
Part No. Nomenclature -1Al -1B1

HUB ASSOCIATED PARTS

3 3
A-1303A Bearing, Blade
3 3
A-1331 Split Ring
"O" Ring, Blade 3 3
PRP-909-7 1
"O" Ring, Shaft 1
PRP-909-7 1
Rear Cone 1
A-50-5
1 1
A-63-B Nut, Hub Retention
A-870
or B-2063
Ring, Hub Puller(Not Req’d With B-2063) 1 1
1 1
A-847 Pin, Safety
Ball Spacer (Optional) 3 3
A-1889
CLAMP COUNTERWEIGHT SUB-ASSY. 3
838-41
3
C-1301-1 Clamp
Linkscrew 3
A-295
3
A-285 Staking Pin, Linkscrew
Zerk Fitting 3
MS15001-1
Counterweight Unit 3
833-16
6
A-2036-32 Screw, Socket Head Ctwt.
Staking Pin, Socket Screw 6
A-285
3
A-65 Pin, Counterweight, Staking
6
A-1306 Gasket, Clamp
6
A-282 Screw, Socket Head
Cotter Pin 6
AN380-3-2
6
A-1372 Clamp Bolts
6
A-1373 Clamp Nuts
6
No. 3 Lubricaps
COUNTERWEIGHT SUB-ASSY. 3
838-42 CLAMP
3
C-1301-1 Clamp
Ilinkscrew 3
A-295
3
A-285 Staking Pin, Linkscrew
Zerk Fitting 3
MS15001-1
3
833-16B Counterweight Unit
6
A-2036-32 Ctwt.SocketScrews
6
A-285 Staking Pins, Socket Screw
3
A-65 Ctwt. Staking Pin
6
A-1306 Clamp Gasket
6
A-282 Clamp Socket Screw
6
AN380-3-2 Cotter Pin, Socket Sc.
6
A-1372 Clamp Bolts 6
A-1373 Clamp Nuts
6
No. 3 Lubricaps
CLAMP ASSOCIATED PARTS
Balance Weightc3 As Needed
A-1305 6 6
AN501A10-6 Weight Screws
1 1
13-1378 PISTON JACK ASSEMBLY
1 1
B-1421 Piston
1 1
A-862 Plastic Bushing
3 3
A-114-F Rod Staking Pin
3 8
A-826-5 Push Rod
3 3
A-921-1 Fork
3 3
A-2039 Socket Set Screw
3 3
A-827-3 Rod Sleeve
3 3
A-970-2 High Stop
3 3
A-965 Washer
3 3
A1848 Flexlock Nut
ASSOCIATED PARTS
1 1
B-806-1 Cylinder 1
1
PltP-909-13 "O" Ring, Cylinder
1 1
A-863 Dust Seal
1 1
PRP-902-46 "O" Ring
2 2
A-95-A Pitch Change Block

51
 Part No. No. Required
Nomenclature
1Al -1B
836-15B SPINNER SUB-ASSY. (Not Polished, No Stops) 1 1
D-1367-6 Spinner Dome (Not Polished) 1 1
D-1387RH Bulkhead (No Stops) 1 1
AN526C1032R8 Screws, Dome Mounting 12 12
AN526C1032R7 Screws, Dome Mounting 12 12
836-23P SPINNER ASSEMBLY 1 1
C1872P Spinner Dome 1 1
AN526C1032RS Screws, Dome Mounting 24 24
D-1389 Bulkhead 1 1

PARTS LIST
Model HC-B3Z20-1
Assembly Drawing D-1980

Part No. No lature

--1------

840-55 HUB SPIDER UNIT

1
C-1968 Hub Spider
1
A-1308 Pilot Tube
A-155 Bushing, Shaft
HUB ASSOCIATED PARTS
A-1854 Wire Retention Ring
3
A-1SS1 Split Bearing
A-1852 3
Guide Ring
3
PRP-909-10 "O" Ring, Blade
3
PRP-909-7 "O" Ring Shaft
1
A-50-5 Rear Cone
1
A-63-B
A-870 tor B-2063 Nut, Hub Retention
Ring, Hub Puller(Not Req’d With B-2063)
1
1
A-847 Pin, Safety 1
A-1889 Ball Spacer (Optional)
3
838-42 CLAMP COUNTERWEIGHT SUB-ASSY. 3
C-1301-1 Clamp 3
A-295 Linkscrsw 3
A-285 Staking Pin, Linkscrew 3
MS-15001-1 Zerk Fitting
3
833-1613 Counterweight Unit 3
A-2036-32 Screw, Socket Head Ctwt. 6
A-2135 Staking Pin, Socket Screw (AN380-3-2 Optional) 6
A-65 Pin, Counterweight, Staking 3
A-1306 Gasket, Clamp 6
A-282 Screw, Socket Head 6
AN380-3-2 Cotter Pin
6
A-1372 Clamp Bolts 6
A-1373 Clamp Nuts 6
No. 3 Lubricaps 6
CLAMP ASSOCIATED PARTS
A-1305 Balance WeighB
As Needed
AN501A10-6 Weight Screws 6
B-1378 PISTON JACK ASSEMBLY
1
B-1421-5 Piston Unit
1
B-1421 Piston
1
A-862 Plastic Bushing
1
A-114-G Rod Staking Pin
3
A-826-S Push Rod
A-921-1 3
Fork
3
A-2039 Socket Set
A-827-3 3
Rod Sleeve
3
A-970-( High Stop
A-965 3
Washer
A- 848 3
Flexlock Nut

52
 Part No Nomenclature No. Required

ASSOCIATED PARTS
1
I3-806-1 Cylinder
1
PRP-909-13 "O" Ring, Cylinder
Dust Seal 1
A-863
1
PRP-902-46 "O" Ring
2
A-95-A Pitch Change Block
1
836-15B SPINNER ASSY. (Not‘Polished, No Stops)
1
D-1367-6 Spinner Dome (Not Polished)
1
D-1387RH Bulkhead (No Stopa)
12
AN526C1032R8 Screws, Dome Mounting
12
AN526C1032R7 Screws, Dome Mounting
1
836-23P SPINNER ASSEMBLY (Anti-Icing, No Stops)
Dome 1
C-1872P Spinner
1
D-1389 Bulkhead, Anti-Icing (No Stops)
24
AN526C1032R8 Screws

PARTS LIST
Blodel HA-B3Z30-1
Assembly Drawing C-l 885
Part No Nomenclature No. Required
1
840-84 HUB SPIDER UNIT
1
C-1853 Hub Spider
1
A-1817 Bushing
3
A-1308 Pilot Tube
HUE ASSOCIATED PARTS
3
A-1851 Split Bearing, Blade 3
A-1852 Guide Ring
3
A-1854 Wire Retention Ring
3
A-1877 Wire Ring, Be~aring
3
PRP-909-7 "O" Ring, Blade
1
A-1856 Rear Cone
1
B-1814 Or B-1894 Hub Nut
B-1894) 1
A-1813 Puller Ring (Not Req’d With
1
A-1848 or A-847 Hub Nut Safety

838-50 CLAMP ASSEMBLY

C-1301 Clamp
3
A-304 Linkscrew
3
A-285 Staking Pin, Linkscrew
3
IMS-15001-1 Zerk Fitting
3
B-1311 Counterweight
6
A-2036-32 Ctwt. Socket Screws
6
A-285 Staking Pins, Socket Screw
3
A-65 Staking Pin, Countenveight
6
A-1306 Clamp Gaskets
6
A-282 Socket Screws, Clamp
6
A-1372 Clamp Bolts 6
A-13f3 Clamp Nuts
CLAMP ASSOCIATED PARTS
As Needed
A-1305 Balance Weights
6
AN501A10-6 Weight Screws
3
A-944 Sleeve, Linkscrew
3
AN380-3-3 Cotter Pin, Sleeve
ASSOCIATED PARTS
1
B-1859 Cylinder, Adju~table
1
PRP-909-13 "O" Ring, Cylinder
1
B-1875 Nut, Piston Adju~ting
1
C-1874 Piston, Adjustable
1
B-1876 Nut, Piston Lock
3
A-1464 Link Pin Units
3
A-1868 Link Arms
1
A-1857 Shaft Plug´•
1
PRP-SQS-15 "O" Rin g, P1 ug

53
 PARTS LIST
Model PC-P3ZP-2A -2B
Assembly Drawing D-1975

Part No. No. Required

Nomenclature
-2A -2B

840-57 HUB SPIDER ASSEMBLY 1 1

C-1967 Hub Spider 1 1
A-1308 Pilot Tubes 3 3

HUB ASSOCIATED PARTS

A-1851 Split Bearing, Blade 3 3
A-1877 Bearing Retention Ring 3 3
A-1852 Guide Ring
3 3
A-1854 Wire Retention Ring
3 3
PRP-909-7 "O" Ring, Blade 3 3
PRP-909-6 "O" Ring, Hub Mounting 1 1
.5002x1 Danley Dowel Pin 2 2
A-1328-1 12 Point Bolts
6 6
A-1381 Washer 6 6
A-1889 Ball Spacer (Optiona1) 3 3
838-17 CLAMP COUNTERWEIGHT ASSEMBLY 3 3
C-1301 Clamp 3 3
A-304 Linkscre~w 3 3
A-285 Staking Pin, Linkscrew 3 3
MS-15001-1 Zerk Fitting 3 3
833-16 Counterweight Unit 3 3
A-2036-32 Cap Screws, Counterweight 6 6
~i-65 Pin, Counterweight Staking 3 3
A-1306 Gaskets, Clamp 6 6
A-282 Socket Head Screws, Clamp 6 6
AN380-3-2 Cotter Pins 6 6
CiaFnP Bolts
AA’,1372
1379 Clamp Nuts
6
6
6
6
A-285 Staking Pins, Socket Screw (AN380-3-2 Cotter Pin 6 6
CLAMP ASSOCIATED PARTS Optional)
A-944 Sleeve, Linkscre~w 3 3
AN380-3-3 Cotter Pin 3 3
A-881-1 Stop Plate 3 3
A-2016 Hex Head Bolts 6 6
A-1305 Balance Weight As Needed
AN501A10-6 Weight Screw~ 6 6
831-4 FEATHERING SPRING ASSEMBLY 1
B-855A Pilot Tube 1
A-856 Mushroom 1
A-860-3 Spacer Tube 1
B-953 Spring, Inner 1
B-853 Spring, Outer 1
A-857 Spring Retainer 1
A-858 Split Retainer 1

831-8 FEATHERING SPRING ASSEMBLY 1

B-868A Pilot Tube
1
A-871 Mushroom
1
B-1363-1 Spring, Inner 1
A-1SS5 Spring Spacer 1
B-1428 Spring, Outer
A-1427 1
Spring Retainer i
A-867 Split Retainer 1

54
 No. Required
Part No. Nomenclature -2B
-2A

PISTON ASSEMBLY 1
832-14
1
C-1401-3 Piston Unit
Piston 1
C-1401-3 Det. #1 1
A-862 Bushing, Plastic
6
A-946 Bushing
Guide Rods 3
A-817-2
3
A-114-B Staking Pins, Rod
Washers 3
A-1444
Jam Nuts 3
AN316-5R
3
A-2037 Socket Head Cap Screws
Link Pin Units 3
A-1464
3
AN501A10-6 Safety Screws
Link Amns 3
A-861-3
PISTON ASSEMBLY 1
832-17
Piston Unit 1
C-1401-2
Piston 1
C-1401-2 Det. #1 1
A-862 Bushing, Plastic
6
A-946 Bushing
Guide Rods 3
A-817-2
3
A-114-B Staking Pins, Rod
Washers 3
A-1444
Jam Nuts 3
AN316-5R
Socket Head Cap Screws 3
A-2037 3
A-1464 Link Pin Units
3
AN501A10-6 Safety Screws
Link Arms 3
A-861-3
GUIDE COLLAR SUB-ASSEMBLY 1 1
831-1
1 1
B-1402 Collar, Pilot
1 1
A-2038-12 Screw, Socket Head
3 3
A-116D-1 Bushing Plastic
1 1
A-114-C Staking Pin
HYDRAULIC ASSOCIATED PARTS
1 1
B-854 Cylinder
"O" Ring, Cylinder 1 1
PRP-909-13 1
1
A-859 Split Retainer
2 2
A-899 Stops, Feathering
4 4
AN501A10-6 Screws, Feathering Stop
1 1
A-863 Dust Seal
1 1
PRP-902-46 "O" Ring, Piston
1
PRP-914-8 "O" Ring, Pilot Tube
"O" Ring, Pilot Tube 1
PRP-914-12
Nut 1
A-880-1
Nut 1
A-880-2
3 3
830-15 AUTO HIGH PITCH STOP ASSEMBLY
3 3
B-882-4B Bracket, High Pitch Stop
3 3
A-883 Pin, High Pitch Stop
3 3
A-884 Spring, High Pitch Stop
3 3
AN936A10 Washer
3 3
AN380-3-3 Cotter Pin
AUTO STOP MOUNTING PARTS
6 6
AN$HSA Hex Head Bolts
6 6
AN4-15A Hex Head Bolts
6 6
AN960-416 Washers
6 6
H10-4 Kaylock Nuts
1 1
836-26 SPINNER ASSEMBLY (Anti-Icing, No Stops)
1 1
C-1888 Spinner Dome
1 1
D-1976-2R Bulkhead Assembly, Anti-Icing
24 24
AN526C1032RS Screws, Dome Mounting
1 1
836-25 SPINNER ASSEMBLY (No Anti-Icing)
(No Stops)
1 1
C-1888 Spinner Dome 1
Bulkhead Assembly 1
D-1976-4R 24
Mounting 24
ANS26C1032R8 Sere w, D ome

55
 PARTS LIST
Assembly Drawing
E-2030 Model HC-A3X20-5L--Left Hand Reversible
Part No. Nomenclature No. Required
840-65 HUB SPIDER UNIT 1
C-1482 Hub Spider 1
A-1S8L Pilot Tubes 3
A-1S5 Bushing 1
HUB ASSOCIATED PARTS
A-971 Blade Bearing, Split 3
A-2027 Bearing Retention Ring 3
A-972 Guide Ring 3
A-974 Wire Retention Ring 3
PRP-909-6 Blade "O" Ring 3
A-50-3, -1 Rear Cone (-3 with spinner) 1
(-1 without spinner)
PRP-909-7 Shaft "O" Ring 1
A-63-B
A-~870 )or B-2063
Hub Nut
Puller Ring (Not
Req’d With
1
1
A-847 Hub Nut Lock B-2043)
1
A-311 Ball Spacer (Optional) 3
838-36 CLAMP ASSEMBLY 3
C-3-1AL Clamp 3
A-304 Linkscrew 3
A-28´•5 Staking Pin, Linkscrew 3
MS-15001-1 Zerk Fitting~s 9
B-2007 Counterweight 3
A-2036-16 Counterweight Socket Screws 6
A-285 Staking Pins, Ctwt. Sk. Sc. 6
A-65 Counterweight Staking Pin 3
A-47-1 Clamp Gaskets 6
A-282 Socket Screws 6
AN380´•3-2 Cotter Pins
6
A-2017 Clamp Bolts 6
AN960-616 Washers 6
A-2043 Clamp Nuts 6
No. 3 Lubricaps 6
CLAMP ASSOCIATED PARTS
A-48 Balance Weight As Needed
ANS01A10-6 Weight Screws 6
A-944 Sleeve, Linkscrew 3
AN380-3-3 Sleeve Cotter Pin 3
831-15 FEATHERING SPRING ASSEMBLY 1
B-2001 Pilot Tube
1
A-2010 Spacer Ring 1
A-871 Mushroom 1
B-1363-1 Feathering Spring 1
A-866-2 Spring Retainer 1
A-867 Split Retainer 1
832-27 PISTON ASSEMBLY 1
C-1401-5L Piston Unit
C-1401-5L Det. #1 Piston
1
A-862 Plastic Bushing
1
A-946 Bronze Bushings
6
A-817-S Guide Rods
A-114-B 3
Rod Staking Pins
3
A-1464 Link Pin Unite
3
ANS01A10-6 Safety Screws 3
A-1444 Washe~
3
AN316-SR Check Nuts
s
-2037 Socket Screws
3
-2008 Link Arms
3

56
 Part No. Nomenclature No. Required

GUIDE COLLAR UNIT 1

834-1L
Guide Collar 1
B-1402L
Plastic Bushings 3
A-11~D-1
1
A-114-C Staking Pin
Socket Screw 1
A-2038-12
VALVE ASSEMBLY "E" 1
D-2006
Tube End "A" 1
A-2004
Tube "D" 1
B-2002
1
A-2011 Staking Pin, Valve
Tube "C" 1
A-2005
Tube End "B" 1
A-2003
"O" Ring, End "A" 2
PRP-902-21
"O" Ring, End "B" 1
PRP-902-21
HYDRAULIC ASSOCIATED PARTS
1
B-854 Cylinder
"O" Ring 1
PRP-909-13 Cylinder
Tube "O" Ring 1
PRP-914-8
Piston Fle~xlock Nut 1
A-880-1
Dust Seal 1
A-863
Piston "O" Ring 1
PRP-902-46
1
A-859 Split Retainer
2
A-899-1 Feathering Stops
4
ANS01A10-6 Stop Screws
SPINNER ASSEMBLY 1
835´•10
Dome 1
C-888-6
Bulkhead Assembly 1
C-807-7
15
AN526C1032R7 Screws, Mounting

PARTS LIST

Model HC-A2X20-5G--Left Hand I Reversible

Assembly Drawing E-2015

Nomenclature No. Required

Part No.

HUB SPIDER UNIT 1

840-67 1
C-2026-2 Hub Spider
2
A-1S8L Pilot Tubes
1
A-1S5 Bushing
HUB SPIDER UNIT 1
840-70 1
C-2026-3 Hub Spider
2
A-1S8L Pilot Tubes
1
A-1S5 Bushing
HUB ASSOCIATED PARTS
2
A-971 Blade Bearing, Split
2
A-2027 Bearing Retention Ring
2
A-972 Guide Ring
2
A-974 Wire Retention Ring
2
PRP-909-6 Blade "O" Ring
1
-1 Rear Cone (-3 with spinner)
A-50-3,
(-1 without spinner)
1
PRP-909-7 Shaft "O" Ring
1
Hub Nut
A-63-B
A-870 )or B-2063 Puller Ring (NOt Req’d With B-2063) 1
1
A-847 Hub Nut Lock

57
 Part No. Nome 1 ture
838-36 CLAMP ASSEMBLY 2
C-3-1AL Clamp 2
A-304 Linkscrew 2
A-255 Staking Pin, Linkscrew 2
MS-15001-1 Zerk Fittings 6
B-2007 Counterweight 2
A-2036-16 Counterweight Mounting Screws 4
A-285 Staking Pins, Sk. Hd. Screws 4
A-65 Counterweight Staking Pin 2
A-47-1 Clamp Gaskets 4
A-282 Socket Screws 4
AN380-3-2 Cotter Pins 4
A-2017 Clamp Bolts 4
AN960-616 Washers 4
A-2043 Clamp Nuts 4
No. 3 Lubricaps 4
CLAMP ASSOCIATED PARTS
A-48 Balance Weight As Needed
AN501A10-6 Weight Screws 4
A-944 Sleeve, Linkscrew 2
AN380-3-3 Sleeve Cotter Pin 2
831-15 FEATHERING SPRING ASSEMRLY 1
B-2001 Pilot Tube 1
A-2010 Spacer Ring 1
A-871 Mushroom 1
B-1363-1 Feathering Spring 1
A-866-2 Spring Retainer 1
A-867 Split Retainer 1
832-25L PISTON ASSEMBLY 1
C-852-8 Piston Unit 1
C-852-8 Det. #1 Piston
1
A-862 Plastic Bushing 1
A-817-2 Guide Rod
2
A-114-B Rod Staking Pins
2
A-1464 Link Pin Units
2
AN501A10-6 Safety Screws 2
A-1444 Waahers 2
AN316-5R Check Nuts
2
A-2037 Socket Screws
2
A-2008 Link Arms
2
834-2 GUIDE COLLAR UNIT
1
B-892 Guide Collar
1
A-116D-1 Plastic Bushing
2
A-2038-12 Socket Screw
D-2006 VALVE ASSEMBLY "E"
1
A-2004 Tube End "A"
1
A-2005 Tube "C"
A-2003 Tube~ End "B"
1
PRP-902-21 "O" Ring, End "B"
1
PRP-902-21 "O" Ring, End "A"
2
A-2011 Staking Pin, Valve 1
B-2002 Tube "D"
HYDRAULIC ASSOCIATED PARTS
B-854 Cylinder 1
PRP-909-13 Cylinder "O" Ring 1
PRP-914-8 Tube "O" Ring
1
A-880-1 Piston Flexlock Nut
1
A-863 Dust Seal
1
PRP-902-46 Piston "O" Ring
A-859 1
Split Retainer 1
A-899-1 Feathering Stops 2
AN501A10-6 Stop Screws 4
835-17 SPINNER ASSEMBLY
1
C-888-4 Dome
1
C-807-11 Bulkhead 1
AN526C1032R7 Screws, Mounting 14
58
 PARTS LIST

Model HC-83XF-3A, -3AL, -3B

Feathering and Reversing

Assembly Drawing D-1450

No. Required
Part No. Nomenclature 3B
3A 3AL

HUB SPIDER UNIT 1 1 1

840-20
Hub Spider 1 1 1
C-1426-2
3 3 3
A-158L Pilot Tube

HUB ASSOCIATED PARTS

Blade Bearing 3 3 3
A-14-B
3 3 3
A-969 Split Ring
Blade "O" Ring 3 3 3
PRP-909-6
1 1 1
PRP-909-6 Hub "O" Ring
2 2 2
.5002x1 Danley Dowel Pin
12 Point Bolt 6 6 6
A-1328-1
Washer 6 6 6
A-1381
3 3 3
A-311 Ball Spacer
3 3
838-33 CLAMP ASSEMBLY
3 3
C-3-1C Clamp
Link Screw 3 3
A-304
3 3
A-285 Staking Pin, Linkscrew
9 9
MS-15001-1 Zerk Fitting
3 3
833-4 Counlterweight Unit
6 6
A-2036-30 Counterweight Socket Head Screws
Cotter Pin 6 6
A-285 Staking Pin, Socket Screw (AN380-3-2
Optional) 3 3
A-65 Counterweight Staking Pin
6 6
A-47-1 Clamp Gasket
Socket Screw 6 6
A-282
6 6
AN380-3-2 Cotter Pin
Bolts 6 6
A-2017 Clamp
6 6
AN960-616 Washer
6 6
A-2043 Clamp Nuts

3
838-53 CLAMP ASSEMBLY
3
C-3-1CL Clamp
Linkscrew 3
A-304
3
A-2135 Staking Pin, Linkscrew
Zerk Fitting 9
MS315001-1
3
833-4L Counterweight Unit
Ctwt. Socket Screw 6
A-2036-30 6
A-285 Staking Pin, Socket Sc. (AN380-3-2 Cotter Pin
Ctwt. Staking Pin Optional) 3
A-65
6
A-47-1 Clamp Gasket
6
A-282 Socket Screw
6
AN380-3-2 Cpt;tea Pin, Socket Screw
6
A-2017 c;lamp Bolts
6
AN960-616 Washer
6
A-2043 Clamp Nuts

CLAMP ASSOCIA.TED PARTS

As Needed
A-48 Balance Weight
6 6 6
AN501-A10-6 Weight Screw
3 3 3
A-881 Stop Plate
6 6 6
A-2016 Plate Screws
3 3 3
A-944 Sleeve, Linkscrew
3 3 3
AN380-3-3 Sleeve Cotter Pin
18 18 18
AN960-10L Washers

59
 Part No. No. Required
Nomenclature
3A 3AL 3B

831-13 FEATHERING REV. SPRING ASSY. 1 1 1

B-1465 Pilot Tube 1 1 1
A-1459 Spring Retainer Unit 1 1 1
A-1452 Spring Cup Retainer 1 1 1
A-1458 Retainer Sleeve 1 1 1
B-1461 Spacer Tube 1 1 1
B-1454 Spring Inner 1 1 1
B-1453 Spring Outer 1 1 1
A-1460 Spring Retainer 1 1 1
A-867 Split Retainer 1 1 1
A-1466 Reverse Indicator (Optional) 1 1 1
B-1470 VALVE ASSEMBLY "C" 1
B-1469 Valve "B" 1
B-1468 Valve "A" 1
A-114-G Staking Pin 1
PRP-902-17
2
#5008-150 Truarc Snap Ring 1
B-1457 VALVE ASSEMBLY "C" 1 1
B-1456 Member "B" 1 1
B-1455 Member "A" 1 1
PRP-902-17 "O" Ring 3 3
l/nxl Staking Pin 1 1
1/8X1~ Staking Pin 1 1
834-1A GUIDE COLLAR UNIT 1 1
B-1402A Guide Collar 1 1
A-116D-1 Bushing 3 3
A-2038-12 Socket Head Screw 1 1
A-114C Staking Pin 1 1
834-1AL GUIDE COLLAR UNIT 1
B-1402AL Guide Collar 1
A-116D-1 Bushing 3
A-2038-12 Socket Head Cap Screw 1
A-114C Staking Pin 1
B-1368-4 PISTON ASSEMBLY 1 1
C-1451-1 Piston 1 1
C-1451-1 Det. #1 Piston Casting 1 1
A-862 Plastic Bushing 1 1
A-817-1 Guide Rod 3 3
A-114E Rod Staking Pin 3 3
A-946 Bronze Bushing 6 6
A-1444 Washer 3 3
AN316-SR Jam Nut 3 3
A-2037 Socket Head Screw 3 3
A-1464 Link Pin Unit 3 3
ANS01-A10-6 Safety Screw 3 3
B-1901 Link Arm 3 3
B-1368-4L PISTON ASSEMBLY 1
C-1I51-1L Piston Unit
1
C-1451-1L Det. #1 Piston Casting 1
A-862 Plastic Bushing 1
A-817-1 Guide Rod
3
A-114E Rod Staking Pin 3
A-946 Bronze Bushing
6
A-1444 Washer 3
AN816-SR Jam Nut
3
A-2037 Socket Head Cap Screw
3
A-1464 Link Pin Unit
3
AN501A10-6 Safety Screw 3
B-1901L Link Arm

60
 No. Required
Part No. Nomenclature 3AL 3B
3A

HYDRAULIC ASSOCIATED PARTS

1 1 1
B-854-1 Cylinder
1 1 1
PRP-909-13 Cylinder "O" Ring
1 1 1
A-859 Split Retainer, Front
1 1 1
A-1467 Stop Plate
4 4 4
ANS01A10-6 Plate Screws
4 4 4
AN501A10-10 Stop Screws
28+4 28-+4 28+4
AN960-10 Washers, Stop Screw
1 1 1
PRP-902-46 Piston "O" Rings
1 1 1
A-863 Dust Seal
1 1 1
PRP-914-8 "O" Ring
Flexlock Nut 1 1 1
A-880-1

3 3
830-4 AUTO HIGH PITCH STOP UNIT
3 3
B-882-4 Bracket
3 3
A-883 Pin
3 3
A-884 Spring
3 3
AN936A10 Washer
Cotter Pin 3 3
AN380-3-3

AUTO HIGH PITCH STOP UNIT 3

830-4L
Bracket 3
B-882-4L
Pin 3
A-883
3
A-884 Spring
3
AN936A10 Washer
Cotter Pin 3
AN380-3-3

AUTO STOP ASSOCIATED PARTS

6 6 6
AN4H5A Hex Head Bolt
6 6 6
AN4-15A Hex Head Bolt
6 6 6
AN960-416 Washer
6 6 6
AN960-416L Washer
6 6 6
H10-4 Kaylock Nut

1 1 1
836-25P SPINNER ASSEMBLY
1 1 1
C1888P Spinner Dome
1 1 1
D-1976-4R Spinner Bulkhead
24 24 24
AN526C1032R8 Mounting Screws
1 1 1
836-26P SPINNER ASSEMBLY (Anti-Icing)
1 1 1
C1888P Spinner Dome
1 1 1
D-1976-2R Spinner Bulkhead
24 24 24
AN526C1032R8 Mounting Screws

1 1 1
Governor, Woodward 210,000 Series
or Hartzell B-3
1 1 1
A-2528 Valve A&sembly
1 1 1
C-2014 Plumbing Layout Drawing

61
 PARTS LIST

Models EHC-ASVF-$; PHC-ASVF-4 -4(D); HC-A3VK-4

Assembly Drawing D-1484

No. Required
Part No. Nomenclature EHC- PHC- PHC- HC-
A3VF A3VF A3VF A3VK
-4 -4 -4(D) -4

840-77 HUB SPIDER UNIT

C-1476 Hub Spider
1
A-1496 Pilot Tubes

840-83 HUB SPIDER UNIT

1 1
C-1477-1 Hub Spider
1 1
A-1496 Pilot Tubes
3 3

840-102 HUB SPIDER UNIT 1

C-1477-3 Hub Spider 1
A-1496 Pilot Tubes 3

HUB ASSOCIATED PARTS

PRP-909-8 "O" Rings, Blade 3 3 3 3
A-971 Split Bearings, Blade 3 3 3
A-2027 Wire Rings, Bearing 3 3 3 3
A-311 Ball Spacers, Bearing 3 3 3 3
A-972 Guide Rings, Bearing 3 3 3 3
A-974 Wire Rings, Guide Retention 3 3 3 3
.5002 x 1" Danley Dowel Pins 2 2 2
PRP-909-6 "O" Ring, Shaft 1 1 1
B-1344 Plate, Spinner Mounting 1 1
A-1328-2 12 Point Bolts 6 6 6
PRP-902-32 "O" Ring, Shaft
1
B-1322 Shim
A-1333-3 Hex Head Bolts
6
A-2482-1 Washers 6
A-1381 Washers 6 6

838-58 CLAMP COUNTERWEIGHT ASSEMBLY 3 3 3 3

C-3-1E Clamp 3 3 3 3
B-1480 Counterweight Unit 3 3 3 3
A-1372 12 Point Bolts, Counterweiffht 6 6 6 6
MS15001-1 Zerk Fittings 6 6 6 6
A-47-1 Clamp Gaskets 6 6 6 6
A-282 Socket Screws, Clamp 6 6 6 6
AN380-3-2 Cotter Pins, Socket Screw 6 6 6 6
A-2017 Clamp Bolts, 12 Point 6 6 6 6
AN960-616 Washers 6 6 6 6
A-2043 Clamp Nuts 6 6 6 6
No. 3 Lubricaps 6 6 6 6

CLAMP ASSOCIATED PARTS

A-48 Balance Weights As Needed
AN501A10-(6) Screws, Balance Weight As Needed
A-944 Sleeves, Counterweight Pin 3 3 3 3
AN380-3-3 Cotter Pins, Sleeve 3 3 3 3

834-7B GUIDE COLLAR UNIT 1 1 1 1

B-1836-2 Guide Collar 1 1 1 1
A-116D-1 Plastic Bushings 3 3 3 3
A-114-2 Staking Pin, Bushing 1 1 1 1
A-2038-14 Nylock Socket Head Cap Screw 1 1 1 1

62
 No. Required
EHC- PHC- PHC- HC-
Part No. Nomenclature A3VF A3VF A3VK
A3VF
-4 -4 -4(D) -4

1 1 1 1
832-33 PISTON ASSEMBLY
1 1 1 1
C-1881-1 Piston Unit
1 I 1 1
C-1881-1 Det. #1 Piston
1 1 1 1
A-862-2 Plastic Bushing
3 3 3 3
A-817-4 Guide Rods
3 3 3 3
A-114-B Staking Pins, Rod 6 6
6 6
A-946 Bronze Bushings
3 3 3 3
A-2037 Socket Head Cap Screws, Rod
3 8 3 3
AN316-6R Check Nuts, Guide Rod
3 3 3 3
A-1444 Washers, Guide Rod 3
3 3 3
A-1464 Link Pin Units
3 3 3 3
AN501A10-6 Safety Screws, Link Pin Unit 3 3
3 3
A-861-3L Link Arms
HYDRAULIC ASSOCIATED PARTS
1 1 1 1
PRP-909-13 "O" Ring, Cylinder Mounting
1 1 1 1
B-1882 Cylinder 1 1 1
1
B-1843 Dust Seal, Piston
1 1 1 1
PRP-902-50 "R" Ring, Piston
1
837-8 SPINNER ASSEMBLY
1
C-226-1 Dome, Spinner
12
AN526C1032R8 Screws, Dome Mountinbr
1
C-1399 Bulkhead Unit
1
B-1345-1 Ring, Spinner MountinR
4
AN5-10A Hex Head Bolts
AN960-516rJ Washers
4
H10-5 Kaylock Nuts
1
837-9 SPINNER ASSEMBLY
1
C-226-2 Dome, Spinner
12
AN526C1032R8 Screws, Dome Mounting
1
C-1399 Bulkhead Unit
1
B-1345 Ring, Spinner Mounting~
AN5-14A Hex Head Bolts
AN960-516 Washers
H10-5 Kaylock Nuts

C-2513 SPINNER ASSEMBLY

C-2531-1 Dome, Spinner
21
AN526C1032R8 Screws, Dome Mounting 1
C-2512 Adaptor Ring Unit

PARTS LIST

Models HC-A3VK-2, -2A, -2B, -2C

Assembly l)rawing D-1446
o. Keg

Part No. Nomenclature HC-ASVK

-2 -2A -2B -2C

HUB SPIDER UNIT 1111

840-77 1 1
1 1
C-1476 Hub Spider
3 3 3 3
A-1496 Pilot Tubes
HUB ASSOCIATED PARTS
"O" Rings, Blade 3333
PRP-909-8 3 3
3 3
A-971 Split Bearings, Blade
3 3 3 3
A-2027 Wire Rings, Bearing
3 3 3 3
A-311 Ball Spacers, Bearing
3 3 3 3
A-972 Guide Rings, Bearing
3 3 3 3
A-974 Wire Rings, Guide Retention
1 1 1 1
PRP-902-32 "O" Ring, Shaft
1 1 1 1
B-1322 Shim
3 3 3 3
A-1333-3 Hex Head Bolts
3 3 3 3
A 1328 12 Point Bolts

63
 No. Required
Part No. Nomenclature
HC-A3VK
__

COMMON CLAMP PARTS

C-3-5A Clamp 3 3 3 3
A-304 Linkscrew 3 3 3 3
A-285 Staking Pin, Linkscrew 3 3 3 3
A-285 Staking Pins, Sk. Hd. Cap Sc. (AN380-3-2 Cotter 6 6 6 6
A-65 Staking Pin, Counterweight Pin Optional) 3 3 3 3
MS15001-1 Zerk Fittings 6 6 6 6
A-47-1 Clamp Gaskets 6 6 6 6
A-282 Socket Screws, Clamp 6 6 6 6
AN380-3-2 Cotter Pins, Socket Screw 6 6 6 6
A-2017 Clamp Bolts, 12 Point 6 6 6 6
AN960-616 Washers 6 6 6 6
A-2043 Clamp Nuts 6 6 6 6
No. 3 Lubricaps 6 6 6 6
838-6 CLAMP COUNTERWEIGHT ASSEMBLY 3
833-4 Counterweight Unit 3
A-2036-30 Socket Head Cap Screws, Ctwt. 6
838-11A CLAMP COUNTERWEIGHT ASSEMBLY 3
B-271-1A Counterweight 3
A-2036-30 Socket Head Cap Screws, Ctwt. 6
838-51 CLAMP COUNTERWEIGHT ASSEMBLY 3
833-15 Counterweight Unit 3
A-2036-30 Socket Head Cap Screws, Ctwt. 6
838-60 CLAMP COUNTERWEIGHT ASSEMBLY 3
B-1437-1 Counterweight 3
A-2036-32 Socket Head Cap Screws, Ctwt. 6
CLAMP ASSOCIATED PARTS
A-48 Balance Weights As Needed
AN501A10-(6) Screws, Balance Weight As Needed
A-881 Stop Plates, High Pitch 3 3 3 3
AN960-10 Washers, Plate Mounting 24 24 24 24
AN3H5A Hex Head Bolts, Plate 6 6 6 6
A-944 Sleeves, Linkscrew 3 3 3 3
AN380-3-3 Cotter Pins, Sleeve 3 3 3 3
A-29 Weight Slugs, Counterweight 9
AN501A10-8 Screws, Weight Slug 6
830-9B AUTO HIGH PITCH STOP UNITS 3 3 3 3
B-984-2 Bracket 3 3 3 3
A-883 Pin 3 3 3 3
A-884 Spring 3 3 3 3
AN936A10 Washer 3 3 3 3
AN380-3-3 Cotter Pin 3 3 3 3
AUTO STOP MOUNTING PARTS
AN74-5 Hex Head Bolts 6 6 ´•6 6
834-1 GUIDE COLLAR UNIT 1 1 1 1
B-1402 Guide Collar 1 1 1 1
A-116D-1 Plastic Bushings 3 3 3 3
A-114-C Staking Pin, Bushing 1 1 1 1
A-2038-12 Nylock Socket Head Cap Screw 1 1 1 1
831-4 SPRING ASSEMBLY 1 1 1 1
B-855A Pilot Tube 1 1 1 1
A-856 Mushroom 1 1 1 1
A-860-3 Spacer Tube 1 1 1 1
B-953 Spring, Inner 1 1 1 1
B-853 Spring, Outer 1 1 1 1
A-857 Spring Retainer, Rear 1 1 1 1
A-858 Split Retainer, Rear 1 1 1 1

64
 No. Required
Part No. Nomenclature HC-A3VK
-2 -2A -2B -2C

PISTON ASSEMBLY 1111

832-17
1 1 1 1
C-1401-2 Piston Unit
1 1 1 1
C-1401-2 Det. W1 Piston
1 1 1 1
A-862 Plastic Bushing
3 3 3 3
A-817-2 Guide Rods
3 3 3 3
A-114-B Staking Pins, Guide Rod
6 6 6 6
A-946 Bronze Bushings
3 3 8 3
A-2037 Socket Head Cap Screw, Rod
3 3 3 3
AN316-5R Check Nuts, Guide Rod
3 3 3 3
A-1444 Washers, Guide Rod 3 3
3 3
A-1464 Link Pin Units
3 3 3 3
AN501A10-B Safety Screws, Link Pin Unit 3 3 3
3
A-861-3 Link Arms
3 3 3 3
A-970 Low Stop Spacer (Optional)

HYDRAULIC ASSOCIATED PARTS

1111
PRP-909-1.3 "O" Ring, Cylinder Mounting
1 1 I 1
B-854 Cylinder 1 1 1
Front 1
A-859 Split Retainer, 2 2 2 2
A-899-( Feathering Stop Plates 4
4 4 4
AN501A10-6 Screws, Stop Plate 1 1 1
1
A-863 Dust Seal, Piston
1 1 I 1
PRP-902-46 "O" Ring, Piston 1
1 1 1
PRP-914-12 "O" Ring, Pilot Tube 1
1 1 1
A-880-2 Flexlock Nut, Piston

1 1
835-14 SPINNER ASSEMBLY
1 1
C-885-1 Adaptor Ring Unit 1
1
C-888-6 Dome, Spinner 15
15
AN526C1032R7 Screws, Dome Mounting

1 1
C-2513 SPINNER ASSEMBLY
1 1
C-2512 Adaptor Ring Unit 1
1
C-2B31-1 Dome, Spinner
16 16
AN526C1032R8 Screws, Dome Mounting
5 5
AN526C1032R7 Screws, Dome Mounting

111
C-2513-2 SPINNER ASSEMBLY
1 i 1
C-2512-2 Adaptor Ring Unit 1 1
1
C-2531-5 Dome, Spinner 15 15
15
ANS26C1032R7 Screws, Dome Mounting

(Optional) 1111
A-2350 ANTI-ICING KIT
3 3 3 3
A-2351 Elbow, 90" 3 3
3 3
A-2352 Flexible Tube Assembly 3
3 3 3
B-2853 Travel Tube Unit

835-40 SPINNER ASSEMBLY

C-1904 Dome
15
AN526C1032R7 Screws, Dome Mounting
1
C-885-1 Adaptor Ring

65
 PARTS LIST
Models HC-A3VF-2, -2B, -2D; EHC-A3VF-2B; PIPC-ASVF-BR, -2C, -2D
Assembly Drawing D-1495

No. Required
Part No. Nomenclature HC HC
HC EHC PHC PHC PHC
2 -2B -2B -2C
840-82 HUB SPIDER UNIT FOR HC-A3VF
1 1 1
C-1477 Hub Spider
1 1 1
A-1496 Pilot Tubes 3 3 3
840-83 HUB SPIDER UNIT FOR PHC-A3VF
1 1 1
C-1477-1 Hub Spider
1 1 1
A-1496 Pilot Tubes
3 3 3
840-102 HUB SPIDER UNIT FOR EHC-A3VF
1
C-1477-3 Hub Spider
1
A-1496 Pilot Tubes
3
HUB ASSOCIATED PARTS
PRP-909-8 "O" Rings, Blade 3 3 3 3 3
A-971 Split Bearings, Blade 3 3 3 3 3
A-2027 Wire Rings, Bearing 3 3 3 3 3
A-311 Ball Spacers, Bearing 3 3 3 3 3
A-972 Guide Rings, Bearing 3 3 3 3 3
A-974 Wire Rings, Guide Retention 3 3 3 3 3
.5002 x 1" Danley Dowel Pins 2 2 2 2 2
PRP-909-6 "O" Ring, Shaft 1 1 1 1 1
A-1328-( 12 Point Bolts--A-1328-2 used only on EHC 6 6 6 6 6
Models on Heron (Caribbean)
A-2040 or A-1333-4 Hex Head Bolts (Optional) 6 6 6 "6
A-2041 or A-1333-5 Hex Head Bolts (Optional) ""6 6
A-1381 Washers 6 6 6 6 6
A-2482-1 Washers (Optional) 6
838-6 CLAMP COUNTERWEIGHT ASSEMBLY 3
C-3-5A Clamp 3
A-304 Linkscrew 3
A-285 Staking Pin, Linkscrew 3
833-4 Counterweight Unit 3
A-2036-30 Socket Head Cap Screws, Ctwt. 6
A-285 Staking Pins, Sk. Hd. Cap Sc. (AN380-3-2 Cotter 6
A-65 Staking Pin, Counterweight Pin Optional) 3
MS15001-1 Zerk Fittings 6
A-47-1 Clamp Gaskets 6
A-282 Socket Screws, Clamp 6
AN380-3-2 Cotter Pins, Socket Screw 6
A-2017 Clamp Bolts, 12 Point 6
AN960-616 Washers 6
A-2043 Clamp Nuts 6
No. 3 Lubricaps 6
838-11A CLAMP COUNTERWEIGHT ASSEMBLY 3 3
C-3-5A Clamp 3 3
A-304 Linkscrew 3 3
A-285 Staking Pin, Linkscrew 3 3
B-271-1A Counterweight 3 3
A-2036-30 Socket Head Cap Screws, Ctwt. 6 6
A-285 Staking Pins, Sk. Hd. Cap Sc. (AN380-3-2 Cotter 6 6
A-65 Staking Pin, Counterweight Pin Optional) 3 3
MS15001-1 Zerk Fittings 6 6
A-47-1 Clamp Gaskets 6 6
A-282 Socket Screws, Clamp 6 6
A~380-3-2 Cotter Pins, Socket Screw 6 6
A-2017 Clamp Bolts, 12 Point 6 6
AN960-616 Washers 6 6
A-2043 Clamp Nuts 6 6
No. 3 Lubricaps 6 6
X
NOTE: Only HC Models Aero and Beagle. NOTE:
on Only EHC Models on Heron(Caribbean).
66
 No. Required
Part No. Nomenclature HC HC
HC EHC PHC PHC PHC
-2 -2B -2B -2C -2D

838-23 CLAMP COUNTERWEIGHT ASSEMBLY 3

C-3-5A Clamp 3
A-304 Linkscrew 3
A-285 Staking Pin, Linkscrew 3
833-4B Counterweight Unit 3
A-2036-30 Socket Head Cap Screws, Ctwt. 6
A-285 Staking Pins, Sk. Hd. Cap Sc. (AN380-3-2 Cotter 6
A-65 Staking Pin, Counterweight Pin Optional) 3
MS15001-1 Zerk Fittings 6
A-47-1 Clamp Gaskets 6
A-282 Socket Screws, Clamp 6
AN380-3-2 Cotter Pins, Socket Screw 6
A-2017 Clamp Bolts, 12 Point 6
AN960-616 Washers 6
A-2043 Clamp Nuts 6
No. 3 Lubricaps 6

838-10 CLAMP COUNTERWEIGHT ASSEMBLY 3 3

C-3-5A Clamp 3 3
A-304 Linkscrew 3 3
A-285 Staking Pin, Linkscrew 3 3
833-2 Counterweight Unit 3 3
A-2036-30 Socket Head Cap Screws, Ctwt. 6 6
A-285 Staking Pins, Sk. Hd. Cap Sc. (AN380-3-2 Cotter 6 6
A-65 Staking Pin, Counterweight Pin Optional) 3 3
MS15001-1 Zerk Fittings 6 6
A-47-1 Clamp Gaskets 6 6
A-282 Socket Screws, Clamp 6 6
AN380-3-2 Cotter Pins, Socket Screw 6 6
A-2017 Clamp Bolts, 12 Point 6 6
AN960-616 Washers 6 6
A-2043 Clamp Nuts 6 6
No. 3 Lubricaps 6 6

838-52 CLAMP COUNTERWEIGHT ASSEMBLY 3

C-3-5A Clamp 3
A-304 Linkscrew 3
A-285 Staking Pin, Linkscrew 3
833-26 Counterweight Unit 3
A-2036-32 Socket Head Cap Screws, CtwD. 6
A-285 Staking Pins, Sk. Hd. Cap Sc. (AN380-3-2 Cotter 6
A-65 Staking Pin, Counterweight Pin Optional) 3
MS15001-I Zerk Fittings 6
A-47-1 Clamp Gaskets 6
A-282 Socket Screws, Clamp 6
AN380-3-2 Cotter Pins, Socket Screw 6
A-2017 Clamp Bolts, 12 Point 6
AN960-616 Washers 6
A-2043 Clamp Nuts 6
No. 3 Lubricaps 6

CLAMP ASSOCIATED PARTS

A-48 Balance Weights As Needed
AN501A10-(6) Screws, Balance Weight As Needed
A-29 Weight Slugs, Counterweight 9 9
AN501A10-10 Screws, Weight Slug 6 6
A-890-9 Weight Slug, Counterweight 3
AN4H5A Hex Head Bolts, Weight Slug 6
A-881 Stop Plates 3 3 3 3
A-2016 Hex Head Bolts, Stop Plate 6 6 6 6
A-944 Sleeves, Linkscrew 3 3 3 3 3
AN380-3-3 Cotter Pins, Sleeve 3 3 3 3 3

67
 No. Required
Part No. Nomenclature HC HC
HC EHC PHC PHC PHC

830-4 AUTO HIGH PITCH STOP UNITS

3 3 3 3
B-882-4 Bracket
3 3 3 3 3
A-883 Pin
3 3 3 3
A-884 Spring 3 3 3 3
AN936A10 Washer
3 3 3 3
AN380-3-3 Cotter Pin
3 3 3 3
AUTO STOP MOUNTING PARTS
AN74-5 Hex Head Bolts 6 G 6 6 6
834-1 GUIDE COLLAR UNIT 1 1 1 I 1
B-1402 Guide Collar 1 1 1 I 1
A-116D-1 Plastic Bushings 3 3 3 3 3
A-114-C Staking Pin, Bushing 1 1 1 1 1
A-2038-12 Nylock Socket Head Cap Screw 1 1 1 1 1
831-4 SPRING ASSEMBLY 1 I I 1 1
B-855A Pilot Tube 1 1 1 1 1
A-856 Mushroom 1 1 I 1 1
A-860-3 Spacer Tube 1 1 1 1 1
B-953 Spring, Inner 1 I 1 1 1
B-853 Spring, Outer 1 1 1 1 1
A-857 Spring Retainer, Rear 1 I 1 1 1
A-858 Split Retainer, Rear 1 1 1 1 1
832-17 PISTON ASSEMRI,Y 1 1 1 1 1
C-I401-2 Piston Unit 1 1 1 1 1
C-1401-2 Det. #1 Piston 1 1 1 1 1
A-862 Plastic Bushing 1 1 1 1 1
A-817-2 Guide Rods 3 3 3 3 3
A-114-B Staking Pins, Guide Rod 3 3 3 3 3
A-946 Bronze Bushings 6 6 6 6 6
A-2037 Socket Head Cap Screws, Rod 3 3 3 3 3
AN316-5R Check Nuts, Guide Rod 3 3 3 3 3
A-1444 Washers, Guide Rod 3 3 3 3 3
A-1464 Link Pin Units 3 3 3 3 3
AN501A10-6 Safety Screws, Link Pin Unit 3 3 3 3 3
A-861-3 Link Arms 3 3 3 3 3
HYDRAULIC ASSOCIATED PARTS
PRP-909-13 "O" Ring, Cylinder Mounting 1 1 1 1 1
B-854 Cylinder 1 1 1 1 1
A-1536 Spacer, Spring Assembly 1
A-859 Split Retainer, Front 1 1 1 1 1
A-899-( Stop Plates, Feathering Adj. 2 2 2 2 2
AN501A10-6 Screws, Stop Plate 4 4 4 4 4
A-863 Dust Seal, Piston 1 1 1 1 1
PRP-902-46 "O" Ring, Piston 1 1 1 1 1
PRP-914-12 "O" Ring, Pilot Tube 1 1 1 1 1
A-880-2 Flexlock Nut, Piston 1 1 1 I 1
SPINNER MOUNTING PARTS
AN4-16A Hex Head Bolts 6 6 6 6 6
AN960-416L Washers (1/32") 12 12 12 12 12
A-1864 Washers (1/16") 6 6 6 6 6
H10-4 Kaylock Nuts 6 6 6 6 6
835-29 SPINNER ASSEMBLY 1 1
C-1904 Dome, Spinner 1 1
AN526C1032R7 Screws, Dome Mounting 15 15
C-807-8 Bulkhead Unit
1 1

68
 __

HC HC
Part No. Nomenclature
HC EHC PHC PHC PHC
-2 -2B -2B -2C -2D

835-31 ANTI-ICING SPINNER ASSEMBLY f

C-1904 D´•ome, Spinner 15
AN526C1032R7 Screws, Dome Mounting 1
C-807-13A Bulkhead Assembly
C-807-8A Bulkhead Unit
C-2357 Slinger Ring Unit 3
AN960-616 Washers, Ring Mounting
A-2352-1 Flexible Tube Units
B-2358 Travel Tube Units
6
AN501A10-6 Screws, Travel Tube Mounting

1
836-18P SPINNER ASSEMBLY
1
D-1367-6 Dome, Spinner
24
AN526C1032R8 Screws, Dome Mounting
1
D-1415-4 Bulkhead Unit

1
836-19P ANTI-ICING SPINNER ASSEMBLY
1
D-1367-7P Dome, Spinner
12
AN526C1032R7 Screws, Dome Mounting
3
AN526C832R8 Screws, Travel Tube Mounting
1
D-1415-6 Bulkhead Assembly
1
D-1415-5 Bulkhead Unit
1
D-1433 Slinger Ring Unit
1 I
836-25 SPINNER ASSEMBLY
1 1
C-1888 Dome, Spinner
24 24
AN526C1032RS Screws, Dome Mounting
1 1
D-1976-4R Bulkhead Assembly
1 1
D-1976-3R Bulkhead Unit
1 1
Nut, Bolt, and Washer Kit
1 1
838-26 ANTI-ICING SPINNER ASSEMBLY
I 1
C-1888 nome, Spinner
24 24
AN526C1032RS Screws, Dome Mounting
1 1
D-1976-2R Bulkhead Assembly
1 1
D-1976-1R Bulkhead Unit
1 1
A-2588 Anti-Icing Kit
1 1
Nut, Bolt, and Washer Kit

836-36P ANTI-ICING SPINNER ASSEMBLY

C-1872-4 Dome, Spinner 18
AN526C1032RS Screws, Dome Mounting
D-1976-6R Bulkhead Assembly
D-1976-5R Bulkhead Unit
A-2588 Anti-Icing Kit 1
Nut, Bolt, and Washer Kit

836-37P SPINNER
ASSEMBLY1
C-1872-4 Dome, Spinner 18
AN526C1032R8 Screws, Dome Mounting
D-1976-8R Bulkhead Assembly
D-1976-7R Bulkhead Unit
1
Nut, Bolt, and Washer Kit

836-45 SPINNER ASSEMELY (For HC-2D Only)1

C-3090-1 Dome 24
AN526C1032R8 Screws, Dome Mounting 1
D-1976-4R Bulkhead Assembly

69
 PARTS LIST
Assembly Drawing D-1485
Models HC-A3V20-2. -2L

Part No. No. Required

Nomenclature
-2 -2L
840-85 HUB SPIDER UNIT
1 1
C-1482 Hub Spider
1 1
A-1496 Pilot Tubes
3 3
A-155 Bushing 1 1
HUB ASSOCIATED PARTS
A-971 Blade Bearing, Split 3 3
A-2027 Bearing Retention Ring 3 3
A-311 Ball Spacer 3 3
A-972 Guide Ring 3 3
A-974 Wire Retention Ring 3 3
PRP-909-8 Blade "O" Ring 3 3
A-50-3 Rear Cone 1 1
PRP-909-7 "O" Ring, Shaft 1 1
A63-B I Hub Nut 1 1
A-870 r 0’ Puller Ring (Not req’d with B-2063) 1 1
A-847 Safety Pin, Hub Nut 1 1
838-6 CLAMP ASSEMBLY (V8433, V8833-2
Blades) 3
C-3-5A Clamp 3
833-4 Counterweight Unit 3
838-23 CLAMP ASSEMBLY 3
(V9333C, V9333C-3 Blades)
C-3-5A Clamp 3
833-4B Counterweight Unit 3
A-890 Weight Slugs 3
AN4H7A Hex Head Bolts 6
838-18 CLAMP ASSEMBLY
3
(VL8433, VL8433H Blades)
C-3-5AL Clamp 3
833-4 Counterweight Unit 3
838-23L CLAMP ASSEMBLY
3
(VL9333CH, -3. -5 Blades)
C-3-5AL Clamp 3
833-4L Counterweight Unit 3
A-890-5 Weight Slugs 3
AN4H1OA Hex Head Bolts
6
838-52 CLAMP ASSEMBLY (9333C-3 Blades) 3
C-3-5A Clamp 3
833-26 Counterweight Unit 3
COMMON CLAMP PARTS
A-304 Linkscrew 3 3
A-285 Staking Pin, Linkscrew 3 3
MS15001-1 Zerk Fittings 6 6
A-65 Counterweight Staking Pin 3 3
A-2036-30 (-32 for Socket Head Cap Screws, Ctwt. 6 6
A-285 838-52) Staking Pins, Sk. Hd. Cap Sc. (AN380-3-2 Cotter 6 6
A-47-1 Clamp Gaskets Pin Optional) 6 6
A-282 Socket Screws, Clamp 6 6
AN380-3-2 Cotter Pins, Sk. Sc. 6 6
A-2017 Clamp Bolts 6 6
AN960-616 Washers 6 6
A-2043 Clamp Nuts 6 6
No. 3 Lubricaps 6 6
CLAMP ASSOCIATED PARTS
A-48 Balance Weights As Needed
AN501A10-6 Weight Screws 6 6
A-944 Sleeve, Linkscrew 3 3
AN380-3-3 Cotter Pin, Sleeve 3 3
A-881 Stop Plate 3 3
A-2016 Hex Head Bolts, Stop Plate 6 6

70
 No. Required
Part No. Nomenclature
-2 -2L

832-14 P’ISTON ASSEMBLY 1

C-1401-3 Piston Unit 1
C-1401-3 Det. #1 Piston 1
A-862 Plastic Bushing 1
A-817-2 Guide Rods 3
A-114-B Rod Staking Pins 3
A-946 Bronze Bushings 6
A-2037 Socket Head Cap Screws 3
A-1444 Washers 3
AN316-5R Jam Nuts 3
A-861-3 Link Arms 3
A-1464 Link Pin Units 3
AN501A10-6 Safety Screws 3

832-14L PISTON ASSEMBLY 1

C-1401-3L Piston Unit 1
C-1401-3L Det. #1 Piston 1
A-862 Plastic Bushing 1
A-817-2 Guide Rods 3
A-114-B Rod Staking Pins 3
A-946 Bronze Bushings 6
A-2037 Socket Head Cap Screws 3
A-1444 Washers 3
AN316-5R Jam Nuts 3
A-861-3L Link Arms 3
A-1464 Link Pin Units 3
AN501A10-6 Safety Screws 3

834-1 GUIDE COLLAR UNIT 1

B-1402 Guide Collar 1
A-116-D1 Plastic Bushing 3
A-114-C Staking Pin 1
A-2038-12 Socket Head Cap Screw 1

834-1L GUIDE COLLAR UNIT 1

B-1402L Guide Collar 1
A-116-D1 Plastic Bushing 3
A-114-C Staking Pin 1
A-2038-12 Socket Head Cap Screw 1

831-11 FEATHERING SPRING ASSEMBLY 1 1

B-868A Pilot Tube 1 1
A-871 Mushroom 1 1
B-1363-1 Spring 1 1
A-866 Spring Retainer, Rear 1 1
A-867 Split Retainer, Rear 1 1

HYDRAULIC ASSOCIATED PARTS

B-854 Cylinder 1 1
PRP-909-13 Cylinder "O" Ring 1 1
A-859 Split Retainer, Front 1 1
A-899-( Feathering Stops 2 2
AN501A10-6 Screws, Feathering Stop 4 4
PRP-914-8 "O" Ring, Pilot Tube 1 1
PRP-902-46 Piston "O" Ring 1 1
A-863 Dust Seal 1 1
A-880-1 Flexlock Nut 1 1

71
 No. Required
Part No. Nomenclature
-2 -2L

835-108 SPINNER ASSEMBLY (With Stops) 1

C-888-6 Dome 1
AN526C1032R7 Dome Mounting Screw 15
C-807-7S Bulkhead (With 830-5 Stops) 1
C-807-10 Bulkhead (Without Stops) 1
830-5 Auto ~High Pitch Stop Units 3
B-882-5 Bracket 3
A-883 Pin 3
A-884 Spring 3
AN936A10 Washer (Internal Lock) 3
AN380-3-3 Cotter Pin 3
AN4-15A Hex Head Bolts 6
AN960-416 Washers 6
H10-4 Kaylock Nuts 6

835-11S SPINNER ASSEMBLY (With Stops) 1

C-888-6 Dome 1
ANS26C1032R7 Dome Mounting Screw 15
C-807-7LS Bulkhead (With 830-5L Stops) 1
C-807-10 Bulkhead (Without Stops) 1
830-5L Auto High Pitch Stop Units 3
B-882-5L Bracket 3
A-883 Pin 3
A-884 Spring 3
AN936A10 Washer (Internal Lock) 3
AN380-3-3 Cotter Pin 3
AN4-15A Hex Head Bolts 6
AN960-416 Washers 6
H10-4 Kaylock Nuts 6

836-6SP SPINNER ASSEMBLY (Polished, With Stops) 1

D-1367-6P Dome (Polished) 1
AN526C1032R8 Dome Mounting Screws 24
D-1414-6 Bulkhead (With 830-5 Stops) 1

836-7SP SPINNER ASSEMBLY 1

(Anti-Icing, Polished, With Stops)
D-1367-7P Dome (Polished) 1
ANS26C1032R8 Dome Mounting Screw 24
D-1414-7 Anti-Icing Bulkhead (With 830-5 Stops) 1

836-7ASP SPINNER ASSEMBLY 1

(Anti-Icing, Polished, With Stops)
D-1367-7AP Dome (Polished) 1
AN526C1032R8 Dome Mounting Screw 24
D-1414-7 Anti-Icing Bulkhead (With 830-5 Stops) 1

836-22SPR SPINNER ASSEMBLY 1

(Anti-Icing, Polished, With Stops)
C-1888P Dome (Polished) 1
AN526C1032R8 Dome Mounting Screw 24
D-1871-7R Anti-Icing Bulkhead (With 830-18 Stops) 1

836-20SP SPINNER ASSEMBLY (With Stops) 1

C-1888 Dome 1
AN526C1032R8 Dome Mounting Screw 12
D-1871-6R Bulkhead (With 830-18 Stops) 1
AN526%1032R7 Dome Mounting Screw 12

72
 PARTS LIST

Model BHC-92ZF-1D1

Assembly Drawing D-1340

Part No. Nomenclature No. Required

HUB SPIDER UNIT 1

840-48
Hub Spider 1
C-1304-6
Pilot Tubes 2
A-1308
Guide Collar Unit 1
834-9
B-1326-1 Guide Collar 1
A-116A-1 Plastic Bushings 2
2
A-2038-10 Nylock Socket Head Cap Screws
2
A-957-1 Staking Pins, Guide Collar

HUB ASSOCIATED PARTS

Blade Bearings 2
A-1303A
A-1889 Ball Spacers 2
2
A-1331 Split Rings
"O" Rings, Blade 2
PRP-909-7
Parker "O" Rings, Blade 2
2-45
"O" Ring, Shaft 1
PRP-909-B
2
.5002 x 1" Danley Dowel Pins
1 Pair
B-1344 Plates, Spinner Mtg. (Pair)
Hex Head Bolts 6
A-1328-2

CLAMP COUNTERWEIGHT ASSEMBLY 2

838-48
2
C-1301-1 Clamp
Linkscrew 2
A-295
2
A-285 Staking Pin, Linkscrew
Counterweight Unit 2
B-1354-4
Socket Head Cap Screws, Ctwt. 4
A-2036-32
4
A-285 Staking Pins, Sk. Hd. Cap Scs. (AN380-3-2 Cotter
Pin Optional) 2
A-65 Staking Pin, Counterweig´•ht
Zerk Fittings 4
MS15001-1
4
A-1306 Clamp Gaskets
4
A-282 Socket Screws, Clamp
4
AN380-3-2 Cotter Pins, Socket Screws
4
A-1372 Clamp Bolts, 12 Point
4
A-1373 Clamp Nuts
4
No. 3 Lubricaps
CLAMP ASSOCIATED PARTS
Balance Weights As Needed
A-1305
4
AN501A10-( Weight Screws
PISTON ASSEMBLY 1
B-828-9
Piston Unit 1
B-966-11
Piston 1
B-966
Plastic Bushing 1
A-862
2
A-826-11 Push Rods
2
A-114-G Staking Pins, Rod
2
A-921-1 Forks
2
A-2039 Socket Set Screws, Fork
A-827-1 Rod Sleeves
A-965 Washers
2
A-848 Flexlock Nuts

HYDRAULIC ASSOCIATED PARTS

1
B-806 Cylinder
1
PRP-909-13 "O" Ring, Cylinder
1
PRP-902-46 "O" Ring, Piston
1
A-863 Dust Seal
2
A-S5-A Blocks, Pitch Change

73
 Part No.

837-3 SPINNER ASSEMBLY 1

C-1337 Dome, Spinner 1
AN526C1032R8 Screws, Dome Mounting 10
C-1336 Bulkhead Unit 1
B-1345 Ring, Spinner Mounting 1
AN5-13A Hex Head Bolts 4
AN960-516L Washers 4
H10-5 Kaylock Nuts 4
837-4 SPINNER ASSEMBLY (POLISHED) 1
C-1337-1 Dome, Spinner (Polished) 1
AN526C1032R8 Screws, Dome Mounting 10
C-1336 Bulkhead Unit 1
B-1345 Ring, Spinner Mounting 1
AN5-13A Hex Head Bolts 4
AN960-516L Washers 4
H10-5 Kaylock Nuts 4

B-(X)-(X) GOVERNOR, HARTZELL 1

F-6-(X) GOVERNOR, HARTZELL 1
X, 210, XXX SERIES GOVERNOR, WOODWARD 1
1A4, 1M12, 1P12, 1&12 GOVERNORS, HAMILTON-STANDARD 1

PARTS LIST
Model HC-B3WF-2
Assembly Drawing D-1995

Part No. Nomenclature No. Required

840-115 HUB SPIDER UNIT 1

C-1967 Hub Spider 1
A-1884 Pilot Tubes 3
HUB ASSOCIATED PARTS
A-1889 Ball Spacer 3
A-1851 Split Bearing, Blade 3
A-1877 Bearing Retention Ring 3
A-1852 Guide Ring 3
A-1854 Wire Retention Ring 3
PRP-909-7 "O" Ring, Blade 3
PRP-909-6 "O" Ring, Hub Mounting 1
.5002x1 Danley Dowel Pins 2
A-1328-1 12 Point Bolts 6
A-1381 Washer 6
838-81 CLAMP COUNTERWEIGHT ASSEMBLY 3
C-1301 Clamp 3
A-304 Linkscrew 3
A-285 Staking Pin, Linkscrew 3
MS-15001-1 Zerk Fitting 3
833-11 Counterweight Unit 3
A-2036-30 Socket Head Cap Screws, Ctwt. 6
A-285 Staking Pins, Cwt. Sk. Hd. Cap Sc. (AN380-3-2 Cotter 6
A-65 Counterweight Staking Pin Pin Optional) 3
A-1306 Gaskets, Clamp 6
A-282 Socket Screws, Clamp 6
AN380-3-2 Cotter Pins, Socket Screw 6
A-1379 Clamp Bolts 6
A-1373 Clamp Nuts 6

CLAMP ASSOCIATED PARTS

A-944 Sleeve, Linkscrew 3
AN380-3-3 Cotter Pin, Sleeve 3
A-881-4 Stop Plate 3
A-2016 Hex Head Bolts, Plate 6
A-1305 Balance Weights As Needed
AN501A10-6 Weight Screws g

74
 Part No. Nomenclature No. Required

FEATHERING SPRING ASSEMBLY 1

831-4
Pilot Tube 1
B-855A
Mushroom 1
A-856
1
A-860-3 Spacer Tube
1
B-953 Spring, Inner
1
B-853 Spring, Outer
1
A-857 Spring Retainer
1
A-858 Split Retainer

PISTON ASSEMBLY 1
832-17
Piston Unit 1
C-1401-2
Piston 1
C-1401-2 Det. 1
1
A-862 Bushing, Plastic
Bushings, Bronze 6
A-946
Guide Rods 3
A-817-2
3
A-114-B Staking Pins, Rod
Washers 3
A-1444
Jam Nuts 3
AN316-5R
Socket Head Cap Screws 3
A-2037
Link Pin Units 3
A-1464
3
AN501A10-6 Safety Screws
Link Arms 3
A-861-3

1
834-1 GUIDE COLLAR UNIT
Guide Collar 1
B-1402
1
A-2038-12 Socket Head Cap Screw
3
A-116D-1 Plastic Bushings
1
A-114-C Staking Pin

HYDRAULIC ASSOCIATED PARTS

1
B-854 Cylinder
"O" Ring, Cylinder 1
PRP-909-13
1
A-859 Split Retainer
2
A-899 Stops, Feathering
4
AN501A10-6 Screws, Feathering Stop
Dust Seal 1
A-863
1
PRP-902-46 "O" Ring, Piston
1
PRP-914-12 "O" Ring, Pilot Tube
A-880-2 Nut

3
830-31 AUTO HIGH PITCH STOP ASSEMBLY
3
B-882-4D Bracket, High Pitch Stop
3
A-883 Pin, High Pitch Stop
A-884 Spring, High Pitch Stop
Washer
33
AN936A10 3
AN380-3-3 Cotter Pin

AUTO STOP MOUNTING PARTS

6
AN4H5A Hex Head Bolts
AN4-15A Hex Head Bolts
AN960-416 Washers
H10-4 Kaylock Nuts
6
A-1864 Washer

836-29 SPINNER ASSEMBLY 3~

C-1904 Spinner Dome
1
C-807-8 Bulkhead Assembly
24
AN526C1032R7 Screws, Dome Mounting

75
 PARTS LIST

Model HC-B3WF-4
Assembly Drawing D-3315

Part No. Nomenclature No. Required

840-115 HUB SPIDER UNIT 1

C-1967 Hub Spider 1
A-1884 Pilot Tubes 3

HUB ASSOCIATED PARTS

A-1851 Split Bearing, Blade 3
A-1877 Wire Retention Ring, Bearing 3
A-1889 Ball Spacer 3
A-1852 Guide Ring 3
A-1854 Wire Retention Ring 3
PRP-909-10 "O" Ring, Blade 3
PRP-909-6 "O" Ring, Shaft 1
A-1328-2 12 Point Bolts 6
.5002 x 1" Danley Dowel Pins 2

838-79 CLAMP ASSEMBLY 3

C-1301-8 Clamp 3
B-3309-1 Counterweight Unit 3
A-2036-16 Socket Head Cap Sc., Ctwt. 6
MS15001-1 Zerk Fittings 3
A-1306 Gaskets, Clamp 6
A-282 Socket Screws, Clamp 6
AN380-3-2 Cotter Pins, Socket Screw 6
A-1372 Clamp Bolts 6
A-1373 Clamp Nuts 6
No. 3 Lubricaps 3

CLAMP ASSOCIATED PARTS

A-1305 Balance Weights As Needed
AN501A10-6 Weight Screws 6
A-944 Sleeve 3
AN380-3-3 Cotter Pin, Sleeve 3

832-36 PISTON ASSEMBLY 1

C-1881-2 Piston Unit 1
C-1881-2 Det. 1 Piston 1
A-862-2 Plastic Bushing 1
A-946 Bronze Bushings 6
A-817-4 Guide Rods 3
A-114-B Staking Pins, Rod 3
A-2037 Socket Head Cap Screw 3
AN316-SR Check Nuts 3
A-1444 Washers 3
A-1464 Link Pin Units 3
AN501A10-6 Safety Screws 3
A-861-3L Link Arms 3

HYDRAULIC ASSOCIATED PARTS

B-1882-2 Cylinder 1
PRP-909-13 "O" Ring, Cylinder 1
PRP-902-50 "O" Ring, Piston 1
B-1843 Dust Seal 1
834-7B Guide Collar Unit 1

837-15 SPINNER ASSEMBLY 1

C-226-4 Dome 1
C-1399-2 Bulkhead Unit 1
AN526C1032RS Dome Mounting Screws 12

76
 PARTS LIST

Model HC-B3W20-4
Assembly Drawing D-3320

Nomenclature No. Required

Part No.

1
840-84 HUB SPIDER UNIT
1
C-1968 Hub Spider
3
A-1884 Pilot Tubes
1
A-155 Bushing, Shaft

HUB ASSOCIATED PARTS

3
A-1851 Split Bearing, Blade
3
A-1877 Wire Retention Ring, Bearing
3
A-1889 Ball Spacer
3
A-1852 Guide Ring
3
A-1854 Wire Retention Ring
3
PRP-909-10 "O" Ring, Blade
PRP-909-7 "O" Ring, Shaft
A-50-5 Rear Cone
A-63B Shaft Nut
A-847 Safety Pin, Nut
PRP-902-22 "O" Ring
A-870 Ring, Puller

838-79 CLAMP ASSEMBLY

C-1301-8 Clamp
3
B-3309-1 Counterweight Unit
A-2036-16 Socket Head Cap Sc., Ctwt.
MS15001-1 Zerk Fittings
A-1306 Gaskets, Clamp
6
A-282 Socket Screws, Clamp
AN380-3-Z Cotter Pins, Socket Screw
A-1372 Clamp Bolts 6
A-1373 Clamp Nuts 3
No. 3 Lubricaps

CLAMP ASSOCIATED PARTS

A-1305 Balance Weights
As
Ngeeded
AN501A10-6 Weight Screws 3
A-944 Sleeve
AN380-3-3 Cotter Pin, Sleeve

832-33 PISTON
Piston Unit
ASSEMBLY1
C-1881-1
C-1881-1 Det. 1 Piston
A-862-2 Plastic Bushing
A-946 Bron2;e Bushings
A-817-4 Guide Rods
A-114-B Staking Pins, Rod 3
A-2037 Socket Head Cap Screw
3
AN316-5R Check Nuts
3
A-1444 Washers 3
A-1464 Link Pin Units
AN501A10-6 Safety Screws 3
A-861-3L Link Arms

HYDRAULIC ASSOCIATED PARTS

B-1882-1 Cylinder 1
PRP-909-13 "O" Ring, Cylinder
1
PRP-902-50 "O" Ring, Piston
1
B-1843 Dust Seal 1
834-7B Guide Collar Unit

77
 OP~T/OUAL
-a5
-s~ 4S~EhnBLY
2a3f."
´•SR CUECX NV~
-11*4 WASW~R

LINK P/EJ

10-26J7UAMP B~OU-S

CP*8 ELAST/C NUTJ

PIG_BR0NZE BUW/N6S

’I~WI-l r~RK N~NGZ

SOCXET SCREI~CWP
IPNJ$O-J-~L
WE/GWT I/N~
22 sx. r/n up sB

/M
p-

tb lts Tf.LBs FOFI

IO-I~O EWC rNE 6NLY

P-909-N ’1)’R
1l~ Y K~ I
A-~a27 wIar R)YG
;e-llPJ DUST S~L

A-311 BRLL SPAo~R

LOpt.l 1
NOTE: TOROUE
~URN/NG /N COi/NT~R- tLDCKW/SE

Model HGA3XK-4 Constant Speed

 SUPPLEMENT NO. 1
MANUAL E;IO. 114B

Aprill3, 1971

REVERSIBLE PROPELLER MODEL HC-A3VF-7

(See Drawing D-3650)

This model is similar to the -2 feathering models listed else-

where in this manual. The pitch range has been increased to

provide for the reverse pitch, and a Beta valve

introduced along
the propeller axis to control the reverse pitch range. The
normal operating pitch range is controlled by a governor in the
same manner as for the -2 feathering propellers.

Overhauling the -7 propeller consists of the same general operations

as other propeller listed in this manual, except for certain
details given below.

1) Removal of the propeller from the engine involves certain

precautions in order to avoid damaging the Beta valve.

a) Remove the B-1368-10 piston assembly by disconnecting the

link pin units A-1464, A-2037 socket screws, and A-880-1
nut from the front of the piston,

b) Remove 831-37 spring assembly by removing the

the AN50LF~10-8
screws, A-1467 platei and A-859 split retainer.

c) Remove the propeller from the shaft by removing the A-1328

screws from the propeller flange.

CAUTION: When pulling the propeller off the shaft, use

care not to bend the Beta valve feedback rod B-3606 which
extends through the hub.

2) Disassemble propeller and overhaul it per instructions listed

in this manual.
Supplement No. 1
Manual No, L14~B
Page Two

3) Remove the Beta valve assembly C-3636 from the engine shaft
as follows,

the A-3621-2 fitting from the rear end of the B-3633

a) Remove
rod. This protrudes from the rear of the engine case.

of the engine drive

b) Remove the snap ring from the front
and the Beta valve assembly C-3630 from the
shaft, remove

shaft.

4) Disassemble the C-3~30 Beta valve assembly by pulling the

B-3631 sleeve from the B-3632 spool. Remove the spring pin

from the B-3631 sleeve, using a drift punch.

sleeve and R-3632

5) Inspect for wear, particularly the B-3631
and the
spool, and also the ends of the B-3606 feedback rod
B-3633 rod.

New Part Dimension Replace if Above or Below

Max. Min, Max Min.

Sleeve B-3631 I,D. ,6253 .6250 .627

Sleeve B-3631 O,D. .750 .748 .746
.6247 .6244 .6235
SpoolB-3632 O.D.

For other wear points, replace if wear exceeds .003.

6) Assemble C-3530 Beta valve.

a) Assemble A-3619-1 pin, A-3641 washer, PRP-914-2 "0" ring,

and B-3606 rod into end of B-3631 sleeve. Insert new

31-8-125-0750 SPS spring pin in holes at the joint between

the B-3606 rod and B-3631 sleeve. Use a conical punch
to form effective
andswage both ends of the spring pin
rivet heads within the chamfered ends of the hole. It is

essential that this pin cannot possibly work itself out.

7) Replace rings and reassemble Beta valve in reverse

all "O"
order of disassembly. Reinstall in the engine shaft.

in order removed.
when it was
8) Replace propeller reverse as

Also see Owner’s Manual 106( for installation instructions,

 HARTZELL PROPELLER, ZNC, Approved April 13, 1971

Assembly
PIQUA,
STRAPOIHO LTST
David Biermann
Drawing KC-A3VF-7 President
D-’3650
Number Requireg

Change
Part Number Nomcnclat;ure

C 840-52 .HUB SPIDER UNIT I 1

~ub S3ider 1
U C-1477
3
P,-149 G f Pilot TuT~

KUR ASSOCIATED PARTS

3
J A-971 Split Bearing, Blade
Wire Ring, Bearing Retentio 3
A A-2027
Bell Spacer 3
G A-311
Guide Ring 3
D A-972
3
A A-974 Wire Ring, Guide Retent~on
’’d" Ring, Blade 3
PRP-909-8
"O" Ring, Shaft: 1
PZ?P-90S)-6
2
.5002 x 1 Danley Dowel Pins
12 Point Bolts 6
J A-132S-1
6
A-2387, 1 wassers

,,L 838-80 CLAMP ASSEMBLY 1 3

3
BQ C-3-LA Clam:,
Lint;cscrew 3
i A-304
3
D A-285 Staking Pin, Linkscrew
Zerk Fittings 6
MS1S001-1
3
B 833-29RL Counterweight Unit
6
G A-2036-24 Socket Head Cap Screw,Ctwt.
6
D ~33´•11-285 Staking Pins,Cwt.Sk.Hd.Scs.
3
E A-65 Staking Pin, Counterweight
ii
F A-47-1 Clamp Gaskets
Socket: Screws Clamp 6
J A- 252

r C
AN380-3-2
A-2017
Cotter Pins, Socket Screws
Clamp Bolts
6

AN960-616 Washers
A-2043 Clamp Nuts
6.
No. 3 1 Luhricaps

CLAMP ASSOCIATED PARTS

As Needed
C A-48 Balance Weights
6
BN501A10-( 1 Weight Screws
3
C I A-9LP4´• Sleeve, Linkscrew
Cotter Pin, Sleeve 3
AN380-3-3
6
A-890-12 Weight Slu~s
6
AN4´•HI1A Hex Head Bolts

Cotter ~ins. Page 1 of 3

JcNOTEt: Optional, use Ah~380-2-2
 HARTZELI, PROPELLER, TNC. Approved April 13, 1971
PTQUk, OHIO
Assembly PARTS LZST
Drawing David Biermann
HCIA3V~-7
D-3650 President
Number Reauir~d

Change
Letter~ Part Number Nomenclature

A 831-37 1 FEATITERING SPRING ASS.EMBLY 1

C B-3421-1 Pilot Tube Unit I 1
B
1 A-3613 1 Cup, Sprine Retainer 1
C B-146r Spacer Tube I I
R R- 1454 1 Spring, Inner 1
A I B- 1453 1 Spring, Outer t I
f3 a- 1460 I Spring Retainer I I
J 1 A-567 Split Retainer I 1
hN3H3A KexHead Bolts 1 4´•

q B-13G 8- 10 1 PISTON ASSEMBLY j 1

AC C- 1451- 2 Piston Unit 1
AG 0-1451-2 Det,~ Piston I 1
T A- 862 E Plastic Bushing I I
F A-946 1 Bronze Bushing t 6
R A1817-1 Guide Rods 1 3
N A-114-B Rod Staking Pins i 3
E A-1464 Link Pin Units 1 3
AN5 01AI 0- 6 i. Safety Screws i 3
s 1 A-144´•4 1 Washers 1 3
AN316- 5R f Jam Nuts 1 3
G A- 203 7 1 Socket Head Cap Screws 3
L B-1901 t Link Arms 3

M I 834-LA I GUIDE CCZLZC1R UNIT I 1

Q I B-1402A I Guide Callar I 1
E A- 116D- I Plastic Bushings 3
N I A- 114-0 1 Staking Pin i 1
C i A-2038-22 Socket bread Can Screw 1

HYDRAULIC ASSOCIATED PARTS

V I B- 854´•- 1 I Gylinder I I
PRP- 909-13 f "O" Ring, Cylinder 1.
PP;fl- 914- 8 i "O" Ring, Pilot Tube i 1
B 1 A-863 1 Dust Sea.l I 1
PRP-902-46 "O" Ring, Piston I 1
D 1 A-859 1 Split Retainer I I
A-1467 I Plate, Ring Retention I 1
AN501A10-8 Screws, Plate 4
I A- 880- 1 FlexToek Nut:. Piston 1

Page 2 of 3
 HARTZELI, pRO Approved April 13, 1971
PIQUA, OKLO
Assembly PARTS LIST
DrawiMg HC-A3VF-7
David Biermann
D-3Q50 President
Number Re4~ixed

letterf Fart; Number Nomenclature

F i C-J630 BETA VALVE ASSE~LYNQ. 3 1

A-3622 1 Cap, Rod End 1
PRP-902-1 "O" Ring, Cap 1
A A-3621-2 Fitting, Rod End I 1
A-3634 Bushing I 1
AP;S316-7R Check Nut 1
PRp-902-9~ I "O" Ring, Cover 1
C B-3611 Cover, Engine 1
PiSP-914-41 "O" Ring, Cover
A B-3633 Push-PullRod
n B-3610 I RE~tainer, Spring I.
A A-3607 Spring, Outer I
A A-3~i08 I Spring, Inner 1
PBf- 9 24- 2 1 "O" Ring, Sleeve t 1
31-s-1240750 SPS Spring Pin 1
11-302 Shaft Adaptor I I
B-3632 1 Spool, Beta Valve 1
D A-3B19-1 Pin, Indicator 1
B B-3631 Sleeve, Beta Valve 1
PRP- 9 14- 12 "0" Ring, Shaft I 1
"O" Ring, Shaft I
PRP 9 O 2´•- 14 "0" Ring, Sleeve i 2
PRP3-902-7 "O" Ring, Rod I
A-3S36 Sleeve´• t 1
P1N365-524 Nut, Seaf-Locking I 1
B B-3606 Rod Feed Back 1
P,-3641 ~Ja s~er 1 .1
ANI) ASSOCIATED PARTS
A6 B- 852- 40 BraeZ(e t: 3
AN4)ISA Hex Head Bolts 6
ANrc-15A I Hex Head Bolts G
AN960-416L 1 WBshers 1 18´•
HIO-4 I Kavlock Nuts __6

835-35) SPI~NEI: AS SEMBLY I

0-3624 Dome, Spinner I I
T 0-507-8 i Bulkhead Unit I
AN52 6c=103 2R7 Screws, Dome I IS

Page 3 of 3
 C*LUL~

n la-~L2/-Z a3Cz,-/; a-sss/ nooro

V SHANR BLADE

B*O-BL HUB SI’IDEl UNIT

n-14P6 P!LOT TUBES
C-1477 IIUB ZPIDER

CLAI~IP AS50C/ATED PARTS

ANlolAlo-(l StRELYJ, BALANCE WT
A-ls BALANCE WEIGHTS
ANJ80-J-3 COTTER PIN, SLEEVE
A-944 SLEEYE, LINKSCAEW

KEV VALVE Arrr

A-36W BUSH/N6
BLADE MOUNTING PARTS
A-BELL tAP. ROD r3
A-974 WIRE RETENTION RING,GOIDE
I CAP
A-36ZI-Z nTT~NC, ROD END \I Ifil
AUJ/I-7R CUEtX NUT I I#B, l~"iiP II
A-971 SPLIT BEARING.BLAD~
PRP- 90L-9 "0"81110, COVER
PRP-919-8 "D’~ BLADE

PAP-flA-AI’D.. Rim. COVER

8-36/0
POSH-PULL ROD
IB ’ii I V/rY Ig(l I
834-14 GLI/D~E COLLAR UNIT
lr
A-3607 5l"3llYG. II1 a I M I
s-erl-l CYLINDER
A-3608 SPR/nnG
I
A-BLJ DU c~ SEAL
PRr- 9/4-E "O "RN~6.
5-125-0750 SPS SPA/Yr6 PIN\\\\ IA I I

8-3602 ADAPTOR Itl I A-"’ SPLIT RETAINER, FRONT

Iht~-´•.ia I A-’*C7 PLATE, RING RETENTION

0-3632 5POOL.B5T;4 VALVE
*r~9´•I PIN, IIIDIC*TOR
ANromlo-8 SCREWS,PLATE

s-~631 BETA WLVE

PRP-

P-M-/c"o’: A-880-I

-SoZ-n‘o’R~S.SLa "o~’R/nt.Roo
8 A-3636 SLEE YE
8 AN365-524 N117;
B-3~06 RoD,FEED BACK

9641 HASllER I I l~d II I I IWllx i C-d’ ’1 i--~

ROD II a I I I Vum~yyt, \C, \I

HUB MOUNT11* PARTS ~Y Y~i 0 K--~l I 831-37

4~ \I\ I II i 1 \mld-J92/-IP/LO~ 71155 UNIT
ii ii lln~H3A HEX HEAD
A-13tS-l /Z POINT BoLTS
A- WASHERI A-16/J SPR/N6 RETA/AlER CUP
´•I"
B-I* sPR~S
BRACKET MT% PARTS SPACER 7ZIBE
IN4HIA HEY HEAD BOLTS ~Y C\ VX I M1M~ IA-lZdO SPR~1116 RETj
-416L WASHERS(IB) 1Y /HJ I \r/ ~A-Bd7 SPLI~ RE’IA/NER REAR
AN4-/IA HEY HEAD
8-1368-10 PISTo~ ASS
WIG-I KAYLDCK NUTS
-I*I/-r P/STod UNIT
-4L BRACI(ET A- L/W~ PIN UX/7S
ANIO/A/d-I SCRE~S
LINAC ARMS
v
-NII WASH~ERS
An~I6-IR CHEEC- IYUTS
A-LOJI SOCXET HEAD CAP SCRE

/TtW ~1 \8’e-Bo CLA~P ASSfmB

831-39 SPINNER ASSEMBLY
CLAMP
t-807-d BULKIIEAD UNIT ~SE (2) P~-890-12 WEltHT SLUGS PER COUNT~RWLICHT
Co UNIT
AN IL6(103LR7 SERE WS, DOME 7 WITH(ZJ AW4HIILI HLX HD. BOLTS PER SLUG.
A-ar
C-36L4 SPINNER DOME
A-LBI ’S7;4X/Nt P/NS.SX. ND. CAP 5t.S
CLArlP GASXETS
A ´•roll CLAMP BoL7rS
ANP60-6I6 WASHER~
-EO43 CLA~P ~TS
~La-z 50cxrr HEAD CAP
A-

A-200 STAAX/HO P/n/.

MSIZO~I-l IZRX
1-id) SQCXZT SC~Ervs oo *or rc~lr I I I

ANJBO-J-L COTTER P/NS SX SC owG arpoa~ ~k

wluu
/Z 29
no J LueA/cAPs I 1NI CUINOLZ ´•~D t.a.
rrlcn I I .a~ t.olo
´•~WD ~0*r
’NgrE´• uSr ANJBO-L-L CI~R PINS DU REPAIR. HARTZELL ´•.´•~´•rrr
~wcln ~y
PROPELLER INC. HIIB MOD~Z WLI´•´•U UYLLI OTYU´•LY *bRI

Hc-nfVF-7
DIV. O~ LllnlLL *IDV)~1U YC
IO.UD 0-3650
 SUPPLEMENT NO, 2

MAN~JAL NO, 114B

May 27, 1971

ADDITION OF HC-B3R20-4

i, Model HC-B3R20-4 is non-counterweighted propeller with

a

constant speed capabilities only, The basic hub is a 20

spline version, The hydraulic unit is the -4 version used
on other propellers,

2, Overhaul procedures are the same as listed for the HC-B3(

series,

3, The parts list is attached herewith,

 KARTZELL PKOPELLER, INC, Approved May 27, 1971
PXQUA, OI´•IIO
Assembly
Drawing
PARTS LIST
By~ David Biermann
MODEL HC-B3W20-4 President
DT3320
MODEL HC-n3R20-4 I_ Required

Change
Lefter Z>art Number Nomenclature I w BOTH

840- 84 HUB SPIDER UNIT g 1

q 1 C-1968 1 Hub Spider 1
M A-1884 Pilot Tubes 1 3
G A-155 I Bushin~. Shaft I

KUB ASSOCIATED PARTS

N A-1851 i Split Bearing, Blade 3
B A-1877 Wire Retention Ring, 3
L 1 $1-1889 Ball Spacer 1 3
B 1 A-1.852 f Guide Ring 3
A A-1854 1 Wire Retention Ring 1 3
PRP-909-10 t "O" Ring, Blade 3
PRP- 909- 7 t "O" Ring, Shaft e 1
a A-50-5 I Rear Cane i 1
K I A-63B Shaft Nut i I
A- 847 t Safety Pin, Nut I
PRP-9 02´•´• 22 j "O" Ring 1
B A1870 I Ring, Puller _
_I 1

AM i 838-79 i CLAMP ASSEMBLY 3

C-1301-8 3
BP Clamp
H 1 B-3309-1 Caunterweight Unit 3

G A-2036-16 Socket Head Cap Sc., Ct~Jt. 6

MS15001-I Zerk Fittings 3
1 A-1306 6
1 Gask.ets, Clamp
a A-282 Socket Screws, Clamp 6
AN38003-2 Cotter Pins, Socket; Screw 6
6
D 1 A-1372 Clamp Bolts
1 6
E A-1373 Clamp Nuts
No. 3 Lubricaps 3

CLAMP ASSOCIATED PARTS

’B I A-1305 Balance Weights As Needed
AN50LA10-6 I Weight Screws 6
A-944 Sleeve, 1 3
c, 1
AN38~3-3 Cotter Pin. Sleeve 3

Page 1 of 2

i
 MARTZELL PROPELLER, TNC. Approved May 27, 1971
PTQUA, OKTO
Assembly PARTS tfST
Drawing Dav‘id Biexnann
MODEL HC-B3W20-4 President:
D-3320
MODEL HC-B3R20-re er Re ulr

Change
X;etter( Part: Number Nomenclature r w BO~M R

B 832-33 1 PLSTON ASSEMBLY 1

N C-1881-1 Piston Unit i 1
N C-1881il Det,~ Piston r 1
T A- 86 2- 2 1 Plastic Bushing 1
F Al 946 1 Bronze Bushings i 6
R A-817-4 Guide Rods 1 3
N A1114-B Staking Pins, Rod 1 3
G A12037 ISocket: Head Cap Screw 3
AN316-5R Check Nuts 1 3
B 1 A-1444 1 Washers 1 3
E A-1464 1 Link Pin Units 1 3
ANS 01AT016 Safety Screws 3
AB Al 861- 3I, Link Arms 1 3

HYDRAULlC ASSOClATED PARTS

G B-1882-1 Cylinder t 1
PRP- 9 0 9 13 1 "O" Ring, Cylinder I 1
PRP1902-50 I "O" Ring, Piston i 1
B B-1843 t Dust Seal 1
O 834- 7B Guide Collar Unit I
B 838-84 1 CLAMP ASSEMBLY 1 3
J C-1977 t Clamp 1 3
H B-3309-1 ICounterwefght Unit 3
C; 1 A-2036-16 Socket Head Cap Sc,, Ctwt, 1 6
MS15001-1 Zerk Fittings 3
i A-1306 Gaskets, Clamp
J A-282 Socket Screws, Clamp 6
AN3 80- 3- 2 Cotter P~ns, Socket Screw 6
D 1 A-1372 Clamp Bolts
E I Al 1373 Clamp Nuts
No. 3 Lubricaps 3

Page 2 of 2
 SUPPLEMENT NO, 3
MANUAL NO, 114’8

March 28, 1972

ADDITION OF )HC-9nJF-8E

’I~hls model ~Ls Model )HC-92ZF-8D except for the

similar to

parts l~sted’below,

’)HC-92ZF-8D ()HC-92WF-8E

(P) Hut~´• Spider Assembly 840-68 840- 117

(2) Pflot Tubes A-1308 A-1884
~4) Brackets A-846-4 A-1338
 SUPPLEMENT NO. 4
MANUAL NO. 114B

May 15, 1972

ADDITION OF HC-B3W30-4

19 Model HC-B3W30-4 is a non-counterweighted propeller with

constant speed capabilities only. It is identical to the
HC-B3Z30-4 except it has a needle bearing installed in the
end of the pilot tube which extends
up inside of the butt
of the blade.

2) Overhaul procedures are the same as all the HC-BSWI series.

3) The parts list is attached herewith.

 1972
WUI~TZF;LL PROPELLER, TNC, Approved May 15,
PIQUA, OHZO
Assembly PARTS LTST
Drawing HC-B3WJO-4 David Biermann
HC-B3Z30-4 President
D-f895
Number Resuired

Change
fetter Parts Number i Nomenclature "W" BOTH "Z"

D 840-34 B HUB SPIDER UNIT 1

AA 1 C-2853 Hub Spider 1
N A-2308 Pilot Tubes 3
G A-1817 Bushing I 1

D 1840-74 HUB SPIDER UNIT I

AA 1 C-1853 Hub Spider 1
N A-L884 Pilot Tubes 3
G A-1817 .I Bushing 1

HUB ASSOCIATED PARTS

B A-1877 Bearing Retention Ring 3
N A-1851 Split Bearing, Blade 3
M A-1889 Ball Spacer, Bearing 3
B A-1852 Guide Ring,Bearing 3
A A-1854 Wire Retention Ring 3
PRP-909-10 "O" Ring, Blade 3
B lA-1855 Spacer f As Needed
A-1856 Rear Cone 1
PRP-909-9 "O"´•Ring, Shaft I 1
PRP-914-4P "O" Ring, Shaft 1
E B-P894 Shaft Nut 1
B A-1848 Safety Pin 1
G A-1834 or A-1834-1 Shaft Plug 1
PIiP-902-15 I"O" Ring,Shaft Plug 1

AO $38-66 CLAMP 8 COUNTERWEIGHT 3

BF C-1301-8 I Clamp 3
9 B-3309 Counterweight Unit 3
H 1 A-2036-22 Socket Head Cap Screw 6
MS15001-1 zerk Fitting 1 6
No, 3 Lubricaps 1 6
K A-130~ Gaskets, Clamp 6
A-282 Socket Screws, Clamp 6
ANJ80-3-2 Cotter Pins, Socket Screw 6
D A-1372 Clamp Bolts 1 6
E A-1373 Clamp Nuts 6

CLAMP ASSOCIATED PARTS

B tA-1305 Balance Weights As Needed
AN501A10-6 Weight Screws 6
C 18-944 Sleeve 3
AN380-3-3 Cotter Pin, Sleeve 3

Prnp 1 nf 2
 HARTZELL PROPELLER, INC, Approved May 15, 1972
PXQUA, OHZO
Assembly PARTS L~ST
Drawing NC-B3W30-4 David Biermann
HC-B3230-4 President
D-f895
Number Reauire

Cfiange
LetterI Part Number ~Jomene l:a t ur e I "wl( BOTH llZ"

B 1832-33 1 PISTON ASSEMBLY i 1

w I C-’lgS1-I. i Piston Unit 1
N C-188r-1 Det,l Piston I 1
v t A-ssz-2 Plastic Bushing 1
F A-946 Bronze Bushing 6
R 6-817-4 Guide Rods 1 3
N A-114-B Staking Pins, Rod 3
G A-;ta37 Socket Head Cap Screws 3
AN316- 5R Check Nuts 1 3
B t A-1444 Washers 1 3
E j A-]1464 Link Pin Units 1 3
AN501A18-6 Safety Screws 3
AB a-8(il-3E I Link Arms 1 3

HYDRAULIC ASSOCIATED PARTS

G fB-1882-1 j Cylinder r 1
PRP-909-13 I "O" Ring, Cylinder I 1
PRP-902-50 "O" Ring, Piston 1
B ]8-1&43 Dust Seal I 1
a 3834-7~ IGuide Collar Unit I 1

Page 2 of 2
´•4~
 ORIGINAL
~UPPLEME)IT
As Received By MP~UAL N13. i 1LF 3
ATP

September 14, 1976

Propeller ~odel HC-83VC is similar to ~lodel

described in the manual.
HC-S3X( 1-(

The HC-83V( )-I propeller uses the same parts and construction
procedures as Model HC-83X(
except for the hub unit. The
following list shows the applicable hub unit for each
configuration. propeller

Propeller Hub Unit

HC-8 3VF-2( 840-138
HC-83VF-3( 840-129
HC-8 3V20-1( 840-128
HC 8 3V 2 0 2 840-86

Applicable blades for the HC-83V( type propellers must be

preceded with a "V" designation such as V8433.
 February 26, 1980

MANUrlL 114 R

SUPPLEFIENT ~ii. 6

Ground kdjustable Propeller 2:odel HA-A2V20-1B

This propeller is essenti;lly the same as the HC-A2V20-1

constant speed version exce~t the hydraulic unit is~replaced
by an adjustable unit. Pitch adjustment is accomplished by
the screT,J protruding from t~e front of t’ne piston.

Overhaul procedures are ilentical to those given for model

HC-fl2V20-1.

A parts list is available upon request.

Su?plement added to manual 04/15/80

ORIGINAL AS RECEIVED BY ATP.

11
 F.A.A. Approved
~bi Manual No. 114C HARTZELL
61110-14

I August 20 1Revisan
5

STEEL HUB PROPELLER

MAINTENANCE MANUAL
Two Blade Three Blade

BHC-A;ZVF-IA BHC-A2MVF-1A HC-A3VF-2 HC-A3VK-2BL EHC-A3MVF-4

HC-A2VF-1 A HC-A2MVF-1A HC-A3VF-2A HC-A3VK-2C PHC-A3MVF-4

HC-A2VF-2 HC-A2MVF-2 HC-A3VF-2B HC-A3VK-4 PHC-A3MVF-4D

HC-A2VF-2A HC-A2MVF-2A EHC-A3VF-2B HC-A3V20-1B HC-A3MVF-SA

HC-A2VF-2B HC-A2MVF-2B PHC-A3VF-2B HC-A3V20-1D HC-A3MVF-SAL

BHC-A2VF-3 BHC-A2MVF-3 PHC-A3VF-2C HC-A3V20:1E HC-A3MVF-5R

HC-A2VK-1 HC-A2MVK-1 HC-A3VF-2D HC-A3V20-1F PHC-A3MVF-5R

HC-A2VK-2 HC-A2MVK-2 PHC-A3VF-2D HC-A3V20-2 HC-A3MVK-2

HC-A2VL-I HC-A2MVL-1 HC-A3VF-2C HC-A3V20-2L HC-A3MVK-2A

HC-A2VL-2 HC-A2MVL-2 HC-A3VF-3L HC-A3V20-3L HC-A3MVK-2B

HC-A2VL-GF HC-A2MVL-GF EHC-A3VF-4 HC-A3MVF-2 HC-A3MVK-2BL

HC-A2V20-1A HC-A2MV20-1A PHC-A3VF-4 HC-A3MVF-2A HC-ASMVK-2C

HA-A2V20-1B HA-A2MVBO-1B PHC-A3VF-4D HC-A3MVF-2B HC-A3MVK-4

HC-A2V20-2 HC-A2MV20-2 HC-A3VF-5A EHC-A3MVF-2B HC-A3MV20-1B

HC-A2MV20-2A HC-A3VF-5AL PHC-A3MVF-2B HC-A3MV20-ID

HC-A2V20-3L HC-A2MV20-3L HC-ASVFdR PHC-A3MVF-2C HC-A3MV20-IE

HC-A2V20-4A1 HC-A2MV20-4A1 PHC-A3VF-SR HC-A3MVF-2D HC-A3MV20-IF

HC-A3VK-2 PHC-A3MVF-2D HC-A3MV20-2

HC-A3VK-2A HC-A3MVF-2C HC-A3MV20-2L

HC-A3VK-20 HC-A3MVF-3L HC-A3MV20-3L

HartzellPropeller Inc.
One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.
I Phone: 937.778.4200
Fax: 937.778.4365
PROPELLER MAINTENANCE MANUAL
114C

I~

(This page is intentionally blank.)

2
COVER 61 -1 0’14 Rev. 5
 RECORD OF REVISIONS

Manual 114C
MFG REV
NO DESCRIPTION ISSUEDATE ATPREVDA INSERTED BY

2 See Highlights 12/99 3/6/00 ATP/DG

3 See Highlights 2/00 7/10/00 ATP/DG

4 See Highlights 1/01 4/30/01 ATP/JB

5 See Highlights 8/01 12/10/01 ATP/MT

 PROPELLER MAINTENANCE MANUAL
HP~ RT Z c L L 114C

RECORD OF REVISIONS TO THIS MANUAL

Revision I Issue Date Revision I Issue Date

3/98 4/20/98 ATP/FTP

1 6 99 1 9 20 /99: ATP /MB

2 12/99 13/6/2000 ATP/DG

2/~n 7/10/00 ATP/DG

4 1/01 4/30/0 ATP/JB

5 8/01 12/10/01 ATP/P~

RECORD OF REVISIONS 61-10-14 PagelMar/98

 PROPELLER
HA RTZ E L L MA:N~TdEcNANCE
C411LAUNAM

RECORD OF REVISIONS TO THIS MANUAL

Revision I Issue Date I I I Revision I Issue Date

mber I Date I Inserted I Inserted By I I Number I Date I Inserted I Inserted B

RECORD OF REVISIONS 61 -1 0-1 4

 RECORD 6F TEMPORARY REVISIONS

Bp~
TEMP
REV NO
Manual 114C

DESCRIPTION ISSUE DATE

ATP REV
DATE
INSERT
BY
DATE
REMOVED
REV
INCOR
REMOVE
BY

002 61-10-14:512 12/99 3/6/00 ATP/DG

9/00 4/30/01 ATP/JB 4/30/01 4 ATP/JB

003 61-10-14:726

2/01 12/1 0/01 5 ATP/MT

004 61-10-14:730
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

RECORD OF TEMPORARY REVISIONS

Date Date

TR Numberl Issue Date Inserted Inserted Removed Removed

ooi 8/01/98 9/21/98 ATP/~P 9/201991 ATP/MB

002 12/99 3/6/2000 ATP/DG

003 9/00 4/30/01 ATP/JB /30/01 A"P/~F

12/10/01
004 2/01 a 11

RECORDOFTEMPORARY REVISIONS 61’1 0-1 4 PagelMar/98

 PROPELLER
HA RTZ E LL MA:N~ECNANCE
C411LAUNAM

RECORD OF T_EMPORARY REVISIONS

Date Date
TR Numberl Issue Date Inserted Inserted Removed Removed

RECORD OF TEMPORARY REVISIONS 61 11 011 4 Page

2Mar/98
HARTZELL PROPELLER INC.
One Propeller Place H A RTZ E L L
Piqua, Ohio 45356-2634 U.S.A.

Telephone: 937.778.4200
Fax: 937.778.4321
MANUAL REVISION TRANSMITTAL

MANUAL 114C (61-10-14)

Steel Hub Propeller Maintenance Manual

REVISION 5 dated August 2001

114C.
Attached is a copy of Revision 5 to Hartzell Manual

Page Control Chart for Revision 5

Remove Insert

Chapterl Chapter/
Page No. Page No.

COVER and COVER and

Inside Cover Inside Cover

REVISION HIGHLIGHTS REVISION HIGHLIGHTS

pages 1 and 2 pages 1 and 2

LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES

pages 1 and 2 pages 1 and 2

TABLE OF CONTENTS TABLE OF CONTENTS

18 pages 1 through 18
pages 1 through

DISASSEMBLY DISASSEMBLY

pages 303 and 304 pages 303 and 304

pages 349 and 350 pages 349 and 350

CHECK CHECK

pages 501 and 502 pages 501 and 502

pages 515 through 530 pages 515 through 530

ASSEMBLY ASSEMBLY

pages 705 through 708 pages 705 through 708

pages 731 and 732 pages 731 and 732
TR-004
pages 769 and 770 pages 769 through 770.2
pages 777 and 778 pages 777 through 778.10

ILLUSTRATED PARTS LIST ILLUSTRATED PARTS LIST

pages 1001 and 1002 pages 1001 and 1002

pages 1067 through 1070

NOTE: When the manual revision has been inserted in the manual, record the
information required on the Record of Revisions page in this manual.
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

REVISION 5 HIGHLIGHTS

Added the A-224-4 Oil Transfer Unit Assembly to the DISASSEMBLY, CHECK,
ASSEMBLY, and ILLUSTRATED PARTS LIST chapters.
Added instructions for marking the position of the low pitch stop nut on splined-hub
-3 propeller models before removing the propeller from the assembly table.

Incorporated TR-004 in the ASSEMBLY chapter.

REVISIONHIOHLIOHTS 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

REVISIONS HIGHLIGHTS

1. Introduction

A. General

This is a list of current revisions that have been issued against this manual. Please
compare to RECORD OF REVISIONS page to ensure that all revisions have been
added to the manual.

B. Components
(1) Revision No. indicates the revisions incorporated in this manual.
(2) Issue Date is the date of revision.

(3) Comments indicates the level of the revision.

(a) New Issue is a new manual distribution. The manual is distributed in its
entirety. All the page revision dates are the same and no change bars are
used.

(b) Reissue is a revision to an

existing manual that includes major content and/or
major format changes. The manual is distributed in its entirety. All the page
revision dates are the same and no change bars are used.

(c) Major Revision is a revision to

an existing manual that includes major content

or minor format changes over a large portion of the manual. The manual is
distributed in its entirety. All the page revision dates are the same, but
change bars are used to indicate the changes incorporated in the latest
revision of the manual.

(d) Minor Revision is a revision to an existing manual that includes minor content
changes to the manual. Only the revised pages of the manual are distributed.
Each page retains the date and the change bars associated with the last
revision to that page.

Revision No. Issue Date Comments

Original Mar/98 New Issue

Revision 1 Jun/99 Minor Revision
Revision 2 Dec/99 Minor Revision
Revision 3 Feb/GO Minor Revision
Revision 4 Jan/Ol Minor Revision
Revision 5 Aug/Ol Minor Revision

REVISIONHIOHLIGHTS 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ ELL 114C

LIST OF EFFECTIVE PAGES

Date Chapter Page Date

Chapter Page

Cover 1/2 Aug/Ol Assembly 701 n05 Jan/Ot

Revision Highlights 1/2 Aug/Ol 1 I lAssembly 706 Aug/Ol

Record of Revisions 112 Mar/98 Assembly 707 Jan/Ol

Record of Temporaty I I IAssembly ZBln08 Aug/Gl

Revisions 1/2 Mar/98 709/713 Mar/98
Assembly
Service Document Assembly 714n15 Jan/Ol

List 112 Mar/98 Assembly 716 Mar/98

Assembly 717 Jan/Gl

AiMlorthiness
Mar/98 Assembly 718/719 Mar/98
Limitations 1/2
Assembly 720 June/99
List of Effective Pages 1/2 Aug/Ol
Assembly 721/722 Mar/98
Table of Contents 1/18 Aug/Ol
114 Jan/Ol Assembly 723/730 Jan/Ol
Introduction
Introduction 5/6 Dec/99 I(I Assembly 731 Aug/Ol
7/12 Jan/Ol Assembly 732/769 JanlOl
Introduction

Description and I I IAssembly 770/770.2 Aug/Ol

Mar/98 Assembly 771m7 Jan/Ol
Operation 1/10

Testing and Fault I I IAssembly 778/778.10 Aug/Ol

June/99 Assembly 779/794 Jan/Ol
Isolation 101
Fits and Clearances 801/802 Mar/98
Testing and Fault
102/1 08 Mar/98 Fits and Clearances 803-804 June!99
Isolation
Fits and Clearances 805 Mar/98
Automatic Test
Mar/98 Fits and Clearances 806/808 June/99
Requirements 201/202
301/303 Mar/98 Special Tools, Fixtures
Disassembly
and Equipment 901/914 Mar/98
Disassembly 304 Aug/Ol
Illustrated Parts List 1001 Feb/GO
Disassembly 305/348 Mar/98

349 Aug/Ol I I Illustrated PartsList 1002 Aug/Ol

Disassembly
Illustrated Parts List 1003/1010 Jan/Ol
Disassembly 350/357 Mar/98
Illustrated Parts List 1011/1012 June/99
Disassembly 358/362 June/99
Illustrated Parts List 1013/1014 Mar/98
Cleaning 401/402 Mar/98
Illustrated Parts List 1015/1018 Jan/Ol
Check 501/502 Aug/Ol
Illustrated Parts List 1019/1022 Dec/99
Check 503/511 Mar/98
Illustrated Parts List 1023/1024 Mar/98
Check 512 Dec/99
Mar/98 Illustrated Parts List 1025/1026 June/99
Check 513/514
Illustrated Parts List 1027/1028 Dec/99
Check 515/530 Aug/Ol
Illustrated Parts List 1029/1034 June/99
Repair 601/602 June/99
Illustrated Parts List 1035/1038 Jan/Ol
Repair 603/604 Mar/98
Illustrated Parts List 1039/1044 Mar/98
Repair 605 Jan/Ol
Illustrated Parts List 1045/1046 Dec/99
Repair 606 Mar/98
Illustrated Parts List 1047/1050 June/99
Repair 607 Jan/Ol
Illustrated Parts List 1051/1054 Jan/ct
608/609 Mar/98
Repair
Repair 610 June/99

USTOFEFFECTIVEP~GES 61-10-14
 PROPELLER
HARTZ ELL C411L~UNAM

LIST OF EFFECTIVE PAGES

Chapter Page Date Chapter Page Date

Illustrated Parts List 1055/1058 Mar/98

Illustrated Parts List 1059/1062 Jan/Ol
Illustrated Parts List 1063/1066 June/99
Illustrated PartsList 1067/1070 Aug/Ol

61-10-14 2
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 114C

SERVICE DOCUMENT LIST

Service Dec. Incorporation Service Dec. Incorporation

No. Rev./Date No. Rev./Date

SERVICEDOCUMENTLIST 61’10’14 PagelMar/98

 PROPELLER
HARTZ E LL MA:N1~CNANCE MANUAL

(This page is intentionally blank.)

SERVICE DOCUUENT LIST

61 11 011 4
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

CONTENTS

REVISION HIGHLIGHTS 1

RECORD OF REVISIONS 1

RECORD OF TEMPORARY REVISIONS 1

AIRWORTHINESS LIMITATIONS

LIST OF EFFECTIVE PAGES 1

TABLE OF CONTENTS 1

INTRODUCTION 1

Statement of 3
1. Purpose
Publications 4
2. Required
A. Hartzell Publications 4

B. References to Hartzell Publications 4

C. Vendor Publications 4

5
3. Personnel Requirements
4. Calendar Limits and Long Term Storage 5

A. Calendar Limits
5
B. Long Term Storage
Life and Service 6
5. Component
A. Overhaul 6

6
B. Damage
7
C. Repair
D. Component Life

6. Definitions 8

7. Abbreviations 11

DESCRIPTION AND OPERATION 1

´•´•´•´•3
1. Description
4
2. Operation
4
A. Constant Speed, Nonfeathering With Counterweights
4
B. Constant Speed, Nonfeathering Without CounteMleights
4
C. Constant Speed Feathering
5
D. Constant Speed Feathering and Reversing
7
3. Model Designation System.............
7
A. Propeller Model Designation
7
B. Blade Shank Designation
C. Conversion From V Shank to MV Shank................................................´•´•´•´•´•´•´•´•´•´• 7

I 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

TESTING AND FAULT ISOLATION 101

1. Trouble-Shooting Guide 102

A. Excessive Friction in Hub Mechanism 102

B. Excessive Friction in Piston 103

C. Failure to Feather.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103

D. Failure to Change Pitch 103

E. Surging RPM or Torque 103

F. Oil Leakage 105

G. Grease Leakage 105

H. End-Play Movement in Blade 107

I. In and Out Movement in Blade 107

J. Fore and Aft Movement in Blade 107

K. Blades not Tracking

L. Radial Play in Blade 107

M. Blade Slippage in Blade Clamp 108

N. Excessive Propeller Vibration ..........,._ ..........._

108
AUTOMATIC TEST REQUIREMENTS 201

DISASSEMBLY 301

1. Removal of Hartzell Feathering Propellers 307

2. Disassembly of Flanged-Hub Models in the -1 and -6 Series 307

A. Spinner Disassembly 307

B. Propeller Removal 307

C. Marking Before Disassembly 309
D. Removing Piston 309
E. Removing Cylinder 309

F Clamp and Counterweight Disassembly 311

G. Blade Mounting Parts Disassembly 313

H. Hub Unit Disassembly 313

3. Disassembly of Splined-Hub, Two-Blade Models in the -1 Series (Except HA-

A2(MV,V)20-1B) 314
A. Spinner Disassembly 314

B. Propeller Removal 314

C. Marking Before Disassembly 314

I TPIBLEOFCONTENTS 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

315
D. Piston Disas embly. . . . . . . . ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
315
E. Removing Cylinder
315
F. Clamp and CounteMleight Disassembly
Parts Disassembly 315
G. Blade Mounting
315
H. Hub Unit Disassembly
Blade Models in the -1 Series 316
4. Disassembly of Splined-Hub, Three
316
A. Spinner Disassembly
316
B. Propeller Removal
316
C. Marking Before Disassembly
317
D. Piston Disas embly. . . . . . . . .´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
317
E. Removing Cylinder
317
F. Clamp and Counterweight Disassembly
Parts Disassembly 317
G. Blade Mounting
317
H. Hub Unit Disassembly
Model HA-A2(MV,V)20-1B 318
5. Disassembly of
A. Spinner Disassembly .......................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•318

318
B. Propeller Removal
Before Disassembly 319
C. Marking
319
D. Disassembling Pitch Adjustment Assembly
319
E. Clamp Disassembly
Parts Disassembly 319
F. Blade Mounting
319
G. Hub Unit Disassembly
Models in the -2 Series 320
6. Disassembly of Flanged-Hub
320
A. Spinner Disassembly
321
B. Propeller Removal
321
C. Marking Before Disassembly
Piston 323
D. Removing
323
E. Removing Feathering Spring Assembly
323
F. Removing Cylinder
323
G. Clamp and Counterweight Disassembly
Parts Disassembly 325
H. Blade Mounting
325
i. Start Lock Disassembly
the Feathering Spring Assembly...........................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´• 326
J. Disassembling
326
K. Hub Unit Disassembly

R983
I TlsLEOFCONTEMS 61-10-14 Rev. 5 Aug/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

7. Disassembly of Splined-Hub Models in the -2 Series 327

A. Spinner Disassembly 327

B. Propeller Removal 329

C. Marking Before Disassembly 329

D. Propeller Disassembly 330

E. Removing Cylinder 330

F. Clamp and Counterweight Disassembly 330

G. Blade Mounting Parts Disassembly 331

H. Start Lock Disassembly 331

i. Disassembling the Feathering Spring Assembly 331

J. Hub Unit Disassembly 331

8. Disassembly of Flanged-Hub Models in the -3 Series 332

A. Spinner Disassembly 332

B. Propeller Removal 332

C. Marking Before Disassembly 333

D. Spinner Bulkhead and Piston Disassembly 335

E. Feathering Spring Disassembly 336

F. Cylinder and Guide Collar Unit Disassembly................................................ 336

G. Clamp and Counterweight Disassembly 337

H. Blade and Flange Mounting Parts Disassembly 337

i. Disassembling the Feathering Spring Assembly ........._.,, 337

J. Hub Spider Unit Disassembly 337

9. Disassembly of Splined-Hub Models in the -3 Series 338

A. Spinner Disassembly 338

B. Propeller Removal 338

C. Marking Before Disassembly 339

D. Spinner Bulkhead and Piston Disassembly 340

E. Cylinder and Guide Collar Unit Disassembly 340

F. Clamp and Counterweight Disassembly 341

G. Blade Mounting Parts Disassembly ........................1.................................... 341

H. Disassembling the Feathering Spring Assembly 341

i. Hub Spider Unit Disassembly 341

I rasLrormmEms 61.10-14 Rev. 5

Page 4
Aug/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Models in the -4 Series 342

1 O. Disassembly of Flanged-Hub
342
A. Spinner Disassembly
342
B. Propeller Removal
343
C. Marking Before Disassembly
Piston 345
D. Removing
345
E. Removing Cylinder
345
F. Clamp and Counterweight Disassembly
Parts Disassembly 346
G. Blade Mounting
347
11. Disassembly of HC-A2(MV,V)20-4A1
347
A. Spinner Disassembly
347
B. Propeller Removal
C. Oil Transfer Unit Removal 348

348
D. Marking Before Disassembly
348
E. Piston Disas embly. . . . . . . .´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
348
F. Removing Cylinder
349
G. Clamp and Counterweight Disassembly
Parts Disassembly 349
H. Blade Mounting
349
i. Hub Unit Disassembly
Oil Transfer Unit Disassembly 349
I J.

Models in the -5(A,AL) Series 350

12. Disassembly of Flanged-Hub
350
A. Spinner Disassembly
350
B. Propeller Removal
C. Beta Valve Removal 351

Before Disassembly 351

D. Marking
351
E. Spinner Bulkhead Removal
F. Start Lock Removal 351

353
G. Piston Disas embly. . . . . . . . ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
353
H. Feathering Spring Disassembly
353
i. Cylinder and Guide Collar Unit Disassembly. . . . . . . . . . .´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
354
J. Clamp and Counterweight Disassembly
354
K. Blade Mounting Parts Disassembly
355
L. Hub Spider Unit Disassembly
355
M. Start Lock Disassembly

TABLEOFCONTENTS 61110114
 PROPELLER
HARTZELL M*:N1~PINCE M~UVUIL
13, Disassembly of Flanged-Hub Models in the -5R Series 357

A. Spinner Disassembly 357

B, Beta Control Unit Removal 357

C. Propeller Removal 357

D, Marking Before Disassembly 358

E, Spinner Bulkhead, Start Lock, Beta Rod, and Piston Disassembly 358

F. Feathering Spring Disassembly 359

G, Cylinder and Guide Collar Unit Disassembly 360

H, Clamp and Counterweight Disassembly 360

I, Blade Mounting Parts Disassembly 361

J, Hub Unit Disassembly 361

K, Start Lock Disassembly 362

CLEANING 401
CHECK 501

1, Inspection Interval Requirements 503

2. Inspection Requirements 503

3, Replacement Requirements 503

4. Repair 503
5. Hub Unit Inspection 503

6. Blade Clamp Inspection

7. Blade Inspection 503
8, Spinner Assembly Inspection 503

9, Cylinder Inspection 504

10, Piston Inspection 504

11 Link Arm Inspection 505

12. Blade Split Bearing Inspection 507

13. Bearing Guide Ring 507

14. Low Stop Rod (Beta Rod) Inspection 509

15, Low Stop Collar (Beta Ring) Inspection 511

16. Pitch Change Rod Inspection 512

17. Feathering Spring Inspection 512

18, Auto High Pitch Stop Unit Inspection 512

19. Guide Collar Inspection 513

I 61-10-14 Rev. 5
Page 6
Aug/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

514
20. Spring Retainerlnspection
21. Rear Cone
515

Pin 516
22. Spring
517
23. Oil Slinger
519
24. Oil Seal Rings
520
25. Slip Ring
521
26. Slip Ring Sleeve..........
522
27. Pipe Plug
523
28. Spring
29. Transfer Seal Button 524

525
30. Bolt

31. Washer
527
32. Slip Ring Cap
33. Oil Transfer 528
Plug
34. Elbow

REPAIR 601

1. General 603

603
A. Shot Peening
603
B. Minor Damage to Metal Parts
603
2. Blade Repair.........
603
3. Hub Unit Repair
603
4. Blade Clamp Repair. . . . . . . . .´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•
604
5. Spinner Assembly Repair..
604
6. Cylinder Repair
604
7. Piston Repair
604
A. Plastic Bushing Removal and Replacement.......
Link Pin Unit Safety Screw Hole 605
B. Repair of
607
8. Beta Ring Repair
´•´•´•607
A. General Repair.............
607
B. Interior Surface Repair
807
9. Guide Collar Repair. . . . . . . . . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•
607
A. Replacement of Guide Collar Bushings
609
10. Carbon Block Assemblies

TABLEOFCONTENIS 61110114
 PROPELLER
nARTZ a LL MPI:NIT~SIANCE M~NUAL

A, Repair of Binding Problems 609

B, Replacement of A-3026 Carbon Block Unit in the A-3044

Carbon Block Assembly 609

11 Rework of A-304 Linkscrew on HC-A3V( Propeller Assemblies 610
ASSEMBLY 701
1, General 709
2, Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series 711
A, Hub Unit Assembly 71 1
B, Installing Guide Collar
C, Reassembling Blade Mounting Parts 715
D, Assembling Clamp and Counterweight, 719
E, Installing Blades and Clamps 719
F. Installing the Cylinder 721
G, Installing Piston Assembly 723
H, Application of Blade Angle Reference Tape 725
i, Setting Blade 727
J, Providing for Visual Detection of Blade Slippage in Clamp........................., 729
K, Sealant CM93 Application 731
L, Checking Blade Track 731
M, Decal Replacement
N, Propeller Removal from Assembly Table 732
3, Assembly of Two-Blade, Splined-Hub Models in the -1 Series,
Except HA-A2(V,MV) 20-1B 733
A, Hub Unit Assembly 733
B, Installing Guide Collar
C, Blade Mounting Parts Assembly 733
D, Assembling Clamp and Counterweight 733
E, Installing Blades and Clamps 733
F. Installing the Cylinder 734
G, Installing Piston Assembly 734
H, Application of Blade Angle Reference Tape 734
I, Setting Blade Angle
J, Providing for Visual Detection of Blade Slippage in Clamp 735
K, Sealant CM93 Application 735
L, Checking Blade Track 735

I 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

M. Decal Replacement
From Assembly Table 735
N. Propeller Removal
series 736
4. Assembly of Three-Blade, Splined-Hub Models in the -1
A. Hub Unit Assembly 736

B. Installing Hub Unit and Spinner Bulkhead 736

C. Blade Mounting Parts Assembly 736

D. Assembling Clamp and CounteMleight 736

E. Installing Blades and Clamps 736

F Installing the Cylinder

G. Installing Piston Assembly 736

H. Application of Blade Angle Reference Tape 737

i. Setting Blade Angle

J. Providing for Visual Detection of Blade Slippage in Clamp 738

K. Sealant CM83 Application 738

L. Checking Blade Track 738

M. Decal Replacement
From Assembly Table 738
N. Propeller Removal
739
5. Assembly of HA-A2(V,MV) 20-1 B
A. Hub Unit Assembly 739

B. Blade Mounting Parts Assembly 739

C. Assembling Clamp and Link Arms ...i.

739

Blades and Clamps 740

D. Installing
740
E. Installing the Cylinder
Adjustment Assembly 740
F Assembly of Pitch

740
G. Installing Pitch Adjustment Assembly
Piston Assembly 740
H. Installing
741
i. Application of Blade Angle Reference Tape
J. Setting Blade Pitch

in Clamp 741
K. Providing for Visual Detection of Blade Slippage
L. Sealant CM93 Application 742

Blade Track 742

M. Checking
742
N. Decal Replacement
From Assembly Table 742
O. Propeller Removal

i TI\BLEOFCONTE~S 61-10-14
 PROPELLER M*NUQL
HARTZELL

6. Assembly of Flanged-Hub Models in the HC-A( )(F,K,L)-2 Series 743

A. Hub Unit Assembly 743

B. Blade Mounting Parts Assembly 743

C. Assembling Clamp and Link Arms 743

D. Installing Blades and Clamps 744

E. Installing the Cylinder land Guide Collar, as Applicable) 744

F Feathering Spring Assembly ...............i....................................................... 745

G. Feathering Spring Assembly Installation 745

H. Installing Piston Assembly 746

i. Start Lock Unit Reassembly 747

J. Start Lock Unit Installation

K. Application of Blade Angle Reference Tape 747

L. Setting Blade Angle. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 748

M. Providing for Visual Detection of Blade Slippage in Clamp 749

N. Sealant CM93 Application 749

O. Checking Blade Track 749

P. Decal Replacement
Q. Propeller Removal From Assembly Table 749

7. Assembly of Splined-Hub Models in the -2 Series 750

A. Hub Unit Assembly 750

B. Blade Mounting Parts Assembly 750

C. Spinner Bulkhead and Start Lock Assembly 750

D. Assembling Clamp and Counterweight 751

E. Installing Blades and Clamps 751

F Installing the Cylinder and Guide Collar 751

G. Feathering Spring Assembly 752

H. Feathering Spring Assembly Installation 752

i. Installing Piston Assembly 753

J. Application of Blade Angle Reference Tape 754

K. Setting Blade Angle. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 754

L. Providing for Visual Detection of Blade Slippage in Clamp 755

M. Sealant CM93 Application 755

N. Checking Blade Track 756

O. Decal Replacement 756

I 61-10-14 Page
Rev. 5 Aug/01
10
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 114C

From Assembly Table 756

P Propeller Removal
Models in the -3 series 757
8. Assembly of Flanged-Hub
A. Hub Unit Assembly 757

Parts Assembly 757

B. Blade Mounting
757
C. Assembling Clamp and Counterweight
758
D. Installing Blades and Clamps............
1 of 2) 758
E. Beta System Installation ~Part
759
F. Installing the Cylinder and Guide Collar
760
G. Feathering Spring Assembly
760
H. Feathering Spring Assembly Installation
Piston Assembly 760
i. Installing
of Blade Angle Reference Tape 761
J. Application
Reverse and Feather Blade Angles 762
K. Setting
763
L. Beta System Installation (Part 2 of 2)
Low Pitch Blade Angle 763
M. Setting
Runout Check 765
N. Final Beta Ring
Visual Detection of Blade Slippage in Clamp 765
O. Providing for
P Sealant CM93 Application 765

765
Q. Checking Blade Track
765
R. Decal Replacement
From Assembly Table 765
S. Propeller Removal
766
9. Assembly of Splined-Hub Models in the -3 series
766
A. Hub Unit Assembly
Installation (Part 1 of 3) 766
B. Beta System
Parts Assembly 766
C. Blade Mounting
767
D. Assembling Clamp and Counterweight
Blades and Clamps........... 767
E. Installing
Installation (2 of 3) 767
F Beta System
768
G. Installing the Cylinder
768
H. Feathering Spring Assembly
768
i. Feathering Spring Assembly Installation
768
J. Installing Piston Assembly
Blade Angle Reference Tape 769
K. Application of
Reverse and Feather Blade Angles 769
L. Setting

61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

M, Beta System Installation (Part 3 of 3) 770

N, Setting Low Pitch Blade Angle 770

O, Final Beta Ring Runout Check 770

P Providing for Visual Detection of Blade Slippage in Clamp 770

Q, Sealant CM93 Application

R, Checking Blade Track 770

S, Decal Replacement
T Propeller Removal From Assembly Table 770

10, Assembly of Flanged-Hub Models in the -4 Series 771

A. Hub Unit Assembly 771

B, Blade Mounting Parts Assembly 771

C, Assembling Clamp and Counterweights 771

D, Installing Blades and Clamps 771

E, Installing the Cylinder and Guide Collar 771

F Installing Piston Assembly 772

G, Application of Blade Angle Reference Tape 773

H, Setting Blade Angle. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . , , . 773

i. Providing for Visual Detection of Blade Slippage in Clamp........................., 774

J, Sealant CM93 Application 774

K, Checking Blade Track 774

L, Decal Replacement 774

M, Propeller Removal From Assembly Table 774

11, Assembly of Splined-Hub Model HC-A2(V,MV)20-4A1 775

A, Hub Unit Assembly 775

B, Blade Mounting Parts Assembly 775

C, Installing Guide Collar

D, Assembling Clamp and Counterweight 776

E, Installing Blades and Clamps 776

F. Installing the Cylinder 776

G, Installing Shaft Seal 776

H, Installing Piston Assembly 776

i, Application of Blade Angle Reference Tape 777

J, Setting Blade Angle

K, Providing for Visual Detection of Blade Slippage in Clamp 778

I asrEorcoNnlrr. 61~10-14 Page 12

Rev. 5Aug/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

778
L, Sealant CM93 Application
Blade Track 778
M. Checking
N, Decal Replacement
From Assembly Table 778
O. Propeller Removal
P Oil Transfer Unit Assembly....... 778.1

Models in the -5R Series 779

12. Assembly of Flanged-Hub
779
A, Hub Unit Assembly
B, Blade Mounting Parts Assembly 779

780
C, Assembling Clamp and Countennreight
Blades and Clamps 780
D. Installing
1 of 2) 780
E. Beta System Installation (Part
781
F. Installing the Cylinder and Guide Collar
782
G, Feathering Spring Assembly
783
H, Feathering Spring Assembly Installation
Piston Assembly 783
i, Installing
J. Start Lock Unit Reassembly 784

K, Start Lock Installation 784

Reference Tape........... 784

L. Application of Blade Angle
Reverse and Feather Blade Angles 785
M. Setting
786
N. Beta System Installation (Part 2 of 2)
Low Pitch Blade Angle 786
O. Setting
Runout Check 787
P Final Beta Ring
787
Q, Setting Start Lock Blade Angle
for Visual Detection of Blade Slippage in Clamp 787
R. Providing
S. Sealant CM93 Application 787

787
T Checking Blade Track
´•´•´•´•´•´•´•´•´•´•787
U. Decal Replacement
From Assembly Table 788
V. Propeller Removal
of Flanged-Hub Models in the -5(A,AL) Series 788
13. Assembly
788
A, Hub Unit Assembly
Parts Assembly 788
B, Blade Mounting
788
C. Assembling Clamp and CounteMleight
Blades and Clamps 789
D. Installing

TABLEoFCoNTENTs 61’10’14 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 114C

E. Installing the Cylinder and Guide Collar 789

F. Feathering Spring Assembly 790

G. Feathering Spring Assembly Installation 790

H. Installing Piston Assembly 790

I. Start Lock Unit Reassembly 791

J. Start Lock Unit Installation

K. Application of Blade Angle Reference Tape 792

L. Setting Blade Angle

M. Providing for Visual Detection of Blade Slippage in Clamp 793

N. Sealant CM93 Application 793

O. Checking Blade Track 793

P Decal Replacement
Q. Propeller Removal From Assembly Table 793

FITS AND CLEARANCES 801

1. Wear Tolerances 802

2. Torque Values
SPECIAL TOOLS, FIXTURES, AND EQUIPMENT 901

ILLUSTRATED PARTS LIST 1001

HC-A2V20-4A1 1003

HC-A2MV20-4A1 1005

HC-A2V(F,K,L)-2(A,B) 1007

HC-A2MV(F,K,L)-2(A,B) 1009

HC-A2V(F,K,L)-(1 ,6)(A,F) 1011

HC-A2MV(F,K,L)-(1 ,6)(A,F) 1013

HC-A3VK-2(A,B,C,BL) 1015

HC-A3MVK-2(A,B,C, BL)
(E,P)HC-A3V(F,K)-4(D) 1019

(E,P)HC-A3MV(F,K)-4(o) 1021

HC-A3V20-2(A, L)
HC-A3MV20-2(A,L) 1025

(E,P)HC-A3VF-2(A,B,C,D) 1027

(E,P)HC-A3MVF-2(A,B,C,D) 1029
HA-A2V20-1B 1031

I 61-10-14 Page
Rev. 5 Aug/Ol
14
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

HA-A2MV20-IB 1033

HC-A2V20-2 1035

1037
HC-A2MV20-2()
HC-A2V20-1A 1039

HC-A2MV20-1A 1041

1043
HC-A3V20-I(B,D,E,F)
1045
HC-A3MV20-1 (B,D,E,F)
BHC-A2VF-3 1047

BHC-A2MVF-3 1049

HC-A3VF-3L 1051

HC-A3MVF-3L 1053

HC-A3VF-5(A,B,L,AL, BL)
HC-A3MVF-5(A,B,L,AL,BL) ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•1057

1059
(P)HC-A3VF-SR
1061
(P)HC-A3MVF-5R
HC-A3V20-3L 1063

HC-A3MV20-3L

I Oil Transier Unn Assemb y 1"9

TABLEOFCONTENTS 61’10’14
 PROPELLER MAINTE NANCE MAN UAL
HP~ RTZ E LL 1140

LIST OF ILLUSTRATIONS

Steel Spider.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 1 ...........................3

Counterweight and Blade Location on a Steel Hub

Assembly in Reverse Pitch Figure 2 5

Checking Blade Movement Figure 101 106

Abnormal Vibration Figure 102 108

Removing Piston and Cylinder Figure 301 308

Clamp Assembly Figure 302

Removing Bearing Retention Ring Figure 303 312

Models in the -2 Series Figure 304 322

Placing Spring Assembly in Special Fixture Figure 305 326

Models in the Splined-Hub -2 Series Figure 306 328

Models in the -3 Series Figure 307 334

Models in the -4 Series Figure 308 344

Models in the -5(A,AL) Series Figure 309 352

Models in the -5R Series Figure 310 356

Link Arm Figure 501 505

Blade Split Bearing Figure 502 506

Low Stop Rod (Beta Rod) Figure 503 508

Low Stop Collar (Beta Ring) Figure 504 510

Guide Collar Figure 505

Rear Cone Figure 506 515

Spring Pin Figure 507 516

Oil Slinger Figure 508 517

Oil Seal Rings Figure 509 518

Slip Ring Figure 510 520

Slip Ring Sleeve Figure 511 521

Pipe Plug Figure 512 522

Spring Figure 513 523

Transfer Seal Button Figure 514 524

Slip Ring Cap Figure 515 526

TIBLEOFCONTENTS 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

LIST OF ILLUSTRATIONS

Figure 516 528

Oil Transfer Plug

Figure 517 529

Elbow...........

Figure 601 606

Repairing Interior Surface of Beta Ring..............................´•´•´•´•
Figure 602 608
Carbon Block Assembly

Linkscrew Rework Limits for Hub Clearance

Figure 603 610
on HC-A3V( Propellers
Pin Figure 701 710
Inserting The Staking
Figure 702 712
Pin Drive-Fit (K or L Flange)
Figure 703 712
"A" and "B" Positions

Figure 704 714

Hub Arm Build-Up

Parts Figure 705 716

Blade and Flange Mounting
Figure 706 718
CM93 Sealant Application
Figure 707 722
Installing Piston and Cylinder
Figure 708 724
Application of Blade Angle Reference Tape
Figure 709 726
Setting the Blade Angle
in Clamp Figure 710 728
Providing for Visual Detection of Blade Slippage

Using Padded Blade Bar to Check for Blade

Figure 711 728
Slippage in Clamp
Figure 712 730
Sealant CM93 Application
Figure 713 730
Checking Blade Track

Warning Decal Part No. WAR-001 for Dynamically

Figure 714 732
Balanced Propeller

Runout with Dial Indicator Figure 715 764

Checking Beta Ring
Figure 716 770.1
Information Tag on Beta Return Spring
Figure 717 778.1
Checking End-Gap on the Oil Seal Rings
718 778.2
Installing the Oil Transfer Plug Using the Installation Tools........ Figure
Figure 719 778.4
A-224-4 Oil Transfer Unit

Figure 720 778.6

Installing the Oil Seal Rings into the Slip Ring
Clearance Between the Slip Ring Groove Side and
Figure 721 778.6
the Oil Seal Ring

Figure 722 778.7

A-221-() Oil Seal Ring Characteristics

TABLEOFCONTENTS 61110114
 PROPELLER MANUAL
HARTZELL

LIST OF ILLUSTRATIONS

Installing the Ring Compressor on the Slip Ring and

Oil Seal Rings Figure 723

Insatlling the Slip Ring and Oil Seal Rings into the
Slip Ring Sleeve Figure 724 778.9

Determining Torque Value of a Standard Torque

Wrench with Adaptor......................................................... Figure 801 805

Torque Wrench Adaptor Figure 901 903

Spring Compressor................................................................ Figure 902 904

Adjustable Riser Fixture and Bench-Top Protractor Figure 903 905

Spring Compressor Fixture Figure 904 906

Beta Rod Retainer Installation Tool Figure 905 907

Digital Protractor Figure 906

Beta System Puller Figure 907

Retention Bearing Puller......................................................... Figure 908 910

Propeller Table Spindle Figure 909 91 1

Shaft Nut Wrench Figure 910 912

Press Tool Figure 911 913

Oil Transfer Unit Assembly Figure 10-1 1068

TP~sLEOFCONTENIS 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

AIRWORTHINESS LIMITATIONS

The Airworthiness Limitations section pproved and specifies maintenance required

is FAA
under 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program
has been FAA approved.

FAA APPRO~ED

date: FEs2s1096
by:
Royace Prather
Manager, Chicago Aircraft Certification Office,
ACE-1 15C
Federal Aviation Administration

AIRWORTHINESS LIMITATIONS REVISIONS

Rev. No. Description of Revision Rev. No. Description of Revision

~IRWORTHINESS LIMIT~TIONS 61 -1 0’1 4

 PROPELLER
HARTZELL MA:N:4ECNANCE MANUAL

AIRWORTHINESS LIMITATIONS

A. The FAA establishes specific life limits for certain component parts as well as the
entire propeller. Such limits require replacement of the identified parts after a
specified number of hours of use.
B. Life Limits

Propeller models affected by this manual currently do not have any life limited parts.

FAA APPROVED

by: date: FEB261gge

Royace Prather
Manager, Chicago Aircraft Certification Office,
ACE-1 15C
Federal Aviation Administration

AIRWORTHINESS LIMITP~TIONS 61 -1 0-1 4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

CONTENTS

3
1. Statement of Purpose
4
2. Required Publications
A. Hartzell Publications

References to Hartzell Publications 4

B.
4
C. Vendor Publications
5
3. Personnel Requirements
5
4. Calendar Limits and Long Term Storage
5
A. Calendar Limits
5
B. Long Term Storage
6
5. Component LifeandService
A. Overhaul 6

6
B. Damage
7
C. Repair. . . . . . . . ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´• ´•
7
D. Component Life
8
6. Definitions
11
1 7. Abbreviations

INTRODUCTION 61’10’14 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 114C

(This page is intentionally blank.)

I INTRODUCTION 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

1. Statement of Purpose

A. This manual provides overhaul procedures for two- and three-bladed, "A" type, steel
h ub propellers man ufactu red by Hartzell Propeller I nc.

B. Contact the Product Support Department of Hartzell Propeller Inc. concerning any
maintenance problems or to request information not covered in this publication.
Hartzell Product Support may be reached during business hours (8:00 a.m. through
5:00 p.m., United States Eastern Time) at (937) 778-4379.

After business hours, you may leave a message on our 24 hour product support line
at (937) 778-4376. AOG support is also available 24 hours per day, seven days per
week via this message service.

Additional information is available on our website at www. hartzellDroD.com.

NOTE: When calling from outside the United States, dial (001) before dialing the
above telephone numbers.

C. This manual is to be used in propeller repair stations by personnel who are trained
and experienced with Hartzell products. This manual does not provide complete
information for an inexperienced technician to attempt propeller overhaul without
supervision.
D. This manual is intended to be the primary source of overhaul information for two-
and three-bladed, "A" type, steel hub propellers. This manual no longer contains
blade overhaul procedures. Refer to the appropriate Hartzell manual for blade
overhaul. In addition to this manual, the reader must consult active Service
Bulletins, Service Letters, Service Advisories, and Service Instructions for
information concerning two- and three-bladed steel hub propellers, or their related
components, that may not yet have been incorporated into the latest revision of
this manual.

E. This manual makes reference to other Hartzell manuals, particularly the Hartzell
Standard Practices Manual No. 202A (61-01-02), that provide important details for
procedures such as anodizing, penetrant inspection, and overhaul procedures for
steel hubs.

F. Where possible, this manual is written in the format specified by ATA Specification
No. 100.

INTRODUCTION 61’10’14 Rev.

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

2. Reauired Publications

A. Hartzell Publications

(1) In addition to this manual, one or more of the following publications are

required for information regarding specific recommendations and

procedures to maintain propeller assemblies.
Manual No. ATA No. Title

Manual 106 61-00-06 Propeller Owner’s Manual and Log Book

Manual 126 61-00-26 Set of active SE, SA, SL, SI
Manual 133 61-13-33 Aluminum Blade Overhaul Manual

Manual 165 61-00-65 Illustrated Tool and Equipment Manual

Manual 202 61-01-02 Standard Practices Manual

I Manual 159 61-02-59 Hartzell Propeller Inc. Application Guide

(2) For Hartzell service literature and revisions, contact:

Hartzell Propeller Inc. Telephone: 937.778.4200

Attn: Service Documents Secretary Fax: 937.778.4321
One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.

information
www
sihT.mocDrleztah can also be found on Hartzell Propeller’s website at

B. References to Hartzell Publications

(1) Item references throughout the text in this manual refer to item numbers in the
Illustrated Parts List Chapter. The item numbers appear in parentheses directly
following the part name. Only the item base number will appear in the text of the
manual. Item base numbers and the alpha variants of the base numbers will
appear in the illustrated parts list. There are two reasons for the use of alpha
variants:

(a) A part may be superseded, replaced, or obsoleted by another part. For

example, the self locking nut (A-2043) which is item 20 was superseded by
the self locking nut (A-2043-1) which is item 20A.

(b) An Illustrated Parts List may contain multiple configurations. Effectivity

codes are used to distinguish different part numbers within the same list.
For example, one configuration may use a propeller mounting bolt (8-3339-
1) which is item 30, yet another configuration uses a propeller mounting
bolt (8-3347) which is item 30A. Effectivity codes are very important in the
determination of parts in a given configuration.

61-10-14
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 114C

1 (2) Special tooling may be required for procedures in this manual. For further
tooling information, refer to Hartzell Manual 165A (61-00-65), Illustrated
Tool and Equipment Manual. The reference numbers for tooling appear
with the prefix "TE" directly following the tool name to which they apply.
For example, a template that is reference number 133 will appear as:
template TE133.
1 (3) Certain instructions throughout this manual refer to consumable materials.
Specific approved materials are listed in Hartzell Manual 202A (61-01-02),
Standard Practices Manual, Table 801. The reference numbers for
consumable materials appear with the prefix "CM" directly following the
material to which they apply. For example, an approved adhesive that is
reference number 16 will appear as: adhesive CM16. Only those items
specified may be used.

C. Vendor Publications

BFGoodrich manuals for maintenance repair of de-ice

Consult appropriate or

systems.

3. Personnel Reauirements

Personnel inspecting, repairing, and overhauling steel hub propellers must have
adequate training and experience. Inspection and repair of propeller parts require
a high degree of skill. Therefore, personnel with inspection
and supervisory
and
responsibility are expected to have an FAA Propeller Repairman’s Certificate
a minimum of 18 months practical experience with
Hartzell steel hub propeller
overhaul. Participation in Hartzell training classes and propeller seminars is

strongly recommended.

4. Calendar Limits and Long Term Storage

A. Calendar Limits

The effects of exposure to the environment over a period of time create a

need for propeller regardless of flight time. Therefore, a calendar

overhaul
limit between overhauls is specified in Service Letter 61( and in the propeller
owner’s manual. Experience has shown that special care, such as keeping an

aircraft hangared, is not sufficient to allow extension of the calendar limit.

NOTE 1: Start date for calendar limit is when the propeller is first installed
on an engine. Calendar limit is not interrupted by subsequent

removal and/or storage.

NOTE 2: Start date for calendar limit should not be confused with
warranty start date (which, with certain exceptions, is normally
the date of sale to the first retail customer).

INTRODUCTION 61’10’14
 PROPELLER MANUPIL
HARTZELL

B. Long Term Storage

Propellers that have been in

I storage have an additional

inspection requirement before
installation. Refer to the Packaging and Storage chapter of Hartzell Standard
Practices Manual 202A (61-01-02),

5. Component Life and Service

A. Overhaul

(1) Overhaul is the periodic disassembly, cleaning, inspecting, repairing as

necessary, reassembling, and testing in accordance with approved

standards and technical data.

(2) The overhaul interval is based on hours of service

(operating time) or on
calendar time. At such specified periods, the propeller hub assembly and
the blade assemblies should be completely disassembled and inspected
for cracks, wear, corrosion, and other unusual or abnormal conditions. As
specified, certain parts should be repaired, and certain other parts should
be replaced.
(3) Overhaul is to be completed in accordance with the latest revision of the
applicable component maintenance manual and other publications
applicable to, or referenced in, the component maintenance manual.

(4) For overhaul interval information, see Service Letter 61( or Owner’s
Manual 106(
B. Damage
(1) Airworthy Damage
Airworthy damage is
damage that does not affect the safety or flight
characteristics of the
propeller system. The maximum limits of airworthy
I damage are specified in the Check chapter of this manual. Although a
blade may continue in service with airworthy damage, this type of
damage should be repaired at the earliest practical time to prevent
further damage to the system.

(2) Unairworthy Damage

Unairworthy damage is damage that exceeds the maximum limits of
airworthy damage. Unairworthy damage can affect the safety or flight
characteristics of the propeller system. This type of damage must be

I before the next flight. Exceptions to this policy may be possible,

deriaper.cnI
but require written authorization from Hartzell Propeller

INTRODUCTION 61110114
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 114C

C. Repair
133C
For blade repair criteria, refer to Hartzell Aluminum Blade Overhaul Manual
(61-13-33).
D. Component Life

NOTE: Aluminum composite blades, or in some cases an entire propeller,

or
that a record of
may be life limited. It is a regulatory requirement
the time since new be maintained for all life limited parts.

(1) Component life is in terms of hours of service (Time Since New, TSN)
expressed
and in terms of hours of service since overhaul (Time Since Overhaul, TSO).

NOTE: TSNTTSO is considered as the time accumulated between rotation and

landing (i.e. flight time).

(2) Bbth references are necessary in defining the life of the component. Some parts
are "life limited," which means that they must be replaced after a specified
period of use (TSN).
(3) When component or assembly undergoes an overhaul, the TSO is returned to
a

zero hours. Time Since New (TSN) can never be

returned to zero.

NOTE: Repair without overhaul does not affect TSO or TSN.

(4) Time Since New (TSN) records must be maintained in the propeller logbook,
along with Time Since Overhaul (TSO).
(5) Blades and hubs are replaced while in service or at overhaul.
sometimes
is
Maintaining separate TSN and TSO histories for a replacement hub or blade
I required. Other propeller components do not require time tracking unless
specifically noted in Hartzell service publications.
(a) Hub replacement

1 replaced, the replacement hub serial number must be

If the hub is
recorded (the entry signed and dated) in the propeller logbook. The
propeller will assume the serial number of the replacement hub.

NOTE: Propeller assembly serial numbers are impression stamped

on the hub. Refer to the Parts Identification and Marking

chapter of Hartzell Standard Practices Manual 202A

(61 -01 -02) for stamping information.
2 The TSO and TSN of the replacement hub must be recorded and
maintained in the propeller logbook. The TSN and TSO of the
remaining propeller components are not affected by the hub
replacement and must be maintained separately.

61 -1 0-1 4
 PROPELLER
HARTZELL MA:N:4ECN~INCE M~NUAL

6. Definitions

Term Definition

Annealed softening of material caused by overexposure to heat

Blade Station refers to a location

on an individual blade for blade inspection

purposes. It is a measurement from the blade "zero" station to

a location on a blade, used to apply blade specification data in

blade overhaul manuals (Note: do not confuse blade station

with reference blade radius; they may not originate at the
same location.)

Brinelling ................................a depression caused by failure of the material in

compression

Corrosion ...............................gradual wearing away or deterioration caused by chemical

action

Crack irregularly shaped separation within a material, usually

visibleas a narrow opening at the surface

Debond separation of two materials that were originally bonded in a

separate operation.

Delamination internal separation of the layers of a composite material

Depression ............................surface area where the material has been compressed but
not removed

Distortion alteration of the original shape or size of a component

Erosion gradual wearing away or deterioration caused by action of

the elements

Exposure leaving material open to action of the elements

Gauge (Bearing Ball) ...........,the prescribed small amount by which the lot mean diameter
should differfrom the nominal diameter, this amount being
one of an established series of amounts.

Gouge ....................................surface area where material has been removed

Horizontal Balance balance between the tip and the butt of the blade

INTROOUCTION 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Term Definition

Impact Damage .........damage that occurs when the propeller blade or hub
assembly strikes, or is struck by, an object while in flight or
on the ground

Nick removal ofpaint and possibly a small amount of material,

not exceeding one layer

Onspeed ................................condition
in which the RPM selectedby the pilot through the
propeller condition lever and the actual engine (propeller)
RPM are equal

Overhaul(MPI) .......................the periodic disassembly, inspection, repair, refinish, and

reassembly of a propeller assembly

Overspeed .............................condition
in which the RPM of the propeller or engine
exceeds predetermined maximum limits; the condition in
which the engine (propeller) RPM is higherthan the RPM
selected by the pilot through the condition lever

Overspeed Damage damage that occurs when the propeller hub assembly
rotates at a speed greater than the maximum limit for which
it is designed

Fitting formation of a number of small, irregularly shaped cavities in

surface material caused by corrosion or wear

Porosity ...............an aggregation of microvoids; see "Voids "Rolling

compressive rolling process for the retention area of single
shoulder blades which provides improved strength and
resistance to fatigue

Reference Blade Radius a distance from thepropeller hub centerline to a location on a

blade, used for blade angle measurement in an assembled
propeller. A yellow adhesive stripe (blade angle reference tape
CM160) is usually located at the reference blade radius
location. (Note: do not confuse reference blade radius with
blade station; they may not originate at the same location.)

Scratch same as "Nick"

.....process where steel shot is impinged on a surface to

Shot Peening create

compressive surface stress which provides improved

strength and resistance to fatigue

,,,,,,,o,,, 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Term Definition

Split delamination of a composite blade

extending to the blade
surface, normally found near the trailing edge or tip

Synchronizing ......setting all propellers at exactly the same RPM

Synchrophasing a form of
propeller sychronization in which not only the RPM
of the engines (propellers) are held constant, but also the
position of the propellers in relation to each other

Track In assembled
propeller, a measurement of the location of

I
an

the blade tip with

respect to the plane of rotation, used to
verify face alignment and to compare blade tip location with
respect to the locations of the other blades in the assembly

Underspeed ........the condition in which the actual engine (propeller) RPM is

lower than the RPM selected by the pilot through the
condition lever

Vertical Balance balance between the leading and trailing edges; this cannot
be changed on composite blades

Voids air or gas that has been trapped and cured into a laminate

Windmilling ..........the rotation of an aircraftpropeller caused by air flowing

over it while it is not operating

INTRODUCTION 61-10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

7. Abbreviations

Abbreviation Term

AN Army-Navy
I AOG Aircraft On Ground
ATA AirTransport Association
CSU Constant Speed Unit
FAA Federal Aviation Administration
Ft-Lb Foot-Pound
ID Inside Diameter
In-Lb Inch-Pound
IPL Illustrated Parts List
Lbs Pounds
MIL-X-X-X Military Specification
MPI Major Periodic Inspection
MS Military Standard
OD Outside Diameter
NAS National Aircraft Standards
N´•m Newton-Meter
I
PSI Pounds per Square Inch
RPM Revolutions per Minute
TBO Time Between Overhaul

I TSN Time Since New

TSO Time Since Overhaul

INTRODUCTION 61-10-14
 PROPELLER MANUAL
HA RTZ E LI: MA:N:4ECNANCE

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I INTRODUCTION 61’1 0’1 4 Page 12

Rev. 4 Jan/Ol
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

CONTENTS

´•´•´•´•´•´•´•´•3
1. Description
4
2. Operation
With CounteMleights 4
A. Constant Speed, Nonfeathering
4
B. Constant Speed, Nonfeathering Without Counterweights
4
C. Constant Speed Feathering
and Reversing 5
D. Constant Speed Feathering
7
3. Model Designation System
7
A. Propeller Model Designation
7
B. Blade Shank Designation
C. Conversion From V Shank to MV Shank 7

LIST OF ILLUSTRATIONS

Steel Spider Figure 1 ...........................................´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•3

and Blade Location Steel Hub Assembly in

Counterweight on a

5
Reverse Pitch Figure 2

DESCRIPTION AND OPERATION 61 ’1 0’1 4

 PROPELLER MAINTENANCE
HA RTZ E LL C411LAUNAM

(This page is intentionally blank.)

DESCRIPTION AND OPERATION 61 11 0~1 4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

1. Description

Hartzell steel hub propellers are speed assemblies that use a steel
constant

spider (Figure 1) as the central component or hub. Propeller blades and

bearing assemblies are assembled on the spider arms and are held in place
by two-piece steel clamps. A steel cylinder is threaded onto the steel spider
and an aluminum piston is placed over the cylinder. Link arms connect the
piston to the steel clamps to control blade angle. Depending on the model of
the propeller, steel hub assemblies may use counterweights or a spring or
both.

APS2063

SteelSpider
Figure 1

DESCRIPTION ANDOPERPITION 61 -1 0-1 4

 PROPELLER
HA RTZ E LL MA:N:4ECNANCE MANUAL

2. Operation

A. Constant Speed, Nonfeathering With Counterweights

(1) Constant speed, nonfeathering assemblies with counterweights use oil
pressure to decrease the blade angle and centrifugal force on the
counterweights to increase the blade angle.
(2) When the engine speed drops below the RPM for which the governor is
set, the force of thespeeder spring overcomes the rotational force of the
governor flyweights. The flyweights tilt inward and lower the pilot valve,
which allows high-pressure governor oil to flow into the propeller and
move the piston outward. The movement of the piston decreases the

blade angle and allows the engine to return to the on-speed setting.

(3) When the engine speed increases above the RPM for which the
governor is set, the governorflyweights overcome the force of the
speeder spring. The governor flyweights tilt outward and raise the pilot
valve, which connects the propeller oil volume to drain. Centrifugal force
acting on the counterweights pushes oil out of the propeller to increase
the blade angle and allow the engine to return to the on-speed setting.

(4) The -1 steel hub propeller models are constant speed, nonfeathering
with counterweights.
B. Constant Speed, Nonfeathering Without Countennreights
(1) Constant speed non-feathering assemblies without counterweights use oil
pressure to increase the blade angle. The centrifugal twisting moment of
the blades decreases the blade angle.

(2) The -4 and -6 steel hub propeller models are constant speed,
nonfeathering without counterweights.
C. Constant Speed Feathering
(1) Constant speed feathering assemblies use oil pressure to decrease the
blade angle. A combination of counterweights and the feathering spring
are used to increase the blade angle.

(2) Feathering is accomplished by connecting propeller oil to drain (engine

sump). When the governor feathering mechanism is activated, oil is
ported from the propeller to the drain. The combined force of the
counterweights and feathering spring moves the blades to the feather
position.
(3) The time necessary to feather the propeller is dependant on the size of
the oil passage from the propeller to the engine and the force exerted
by the spring and counterweights. The feathering process is normally
accomplished within ten seconds.

DESCRIPTIDN AND OPERATIDN 61 -1 0-1 4

 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 114C

(4) Unfeathering thepropeller is accomplished by repositioning the governor

control to the normal flight range. The engine is restarted and after
several revolutions the governor increases oil pressure and moves the
blades out of the feather position.

(5) The -2 steel hub propeller models are constant speed feathering.
D. Constant Speed Feathering and Reversing
(1) Constant speed reversing assemblies are feathering propellers that allow
increased blade angle travel into the reverse pitch range (Figure 2).
Also, a hydraulic low pitch stop is introduced.

NOTE: Right hand shown.

APS2065

Positive counterweight
angle to be maintained in I ´•c+----- Piston
reverse position

Cruise

Counterweight

1 Blade clamp
Feather
Blade

Reverse
blade angle

Counterweight and Blade Location on a Steel Hub Assembly in Reverse Pitch

Figure 2

DESCRIPTION AND OPERATION 61 -1 0’1 4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(2) The hydraulic low

pitch stop prevents the blade angle from entering the
reverse range unless commanded. This unit consists of an engine-
mounted beta valve that eliminates governor oil to the propeller when
the blade angle reaches the low blade angle position. The beta valve is
actuated by a linkage connected to the piston and to a pilot control.
(3) The -3 and -5 steel hub, reciprocating engine, propeller models are
constant speed feathering and reversing.

(a) The beta feedback linkagefor the -3 and -5R models is external to
the propeller hub. Linear motion is trasmitted from the rotating hub
to the fixed engine by the collar and carbon block assembly.
(b) The beta feedback linkage for the -5 models consists of a beta tube
mounted concentric with the propeller shaft that serves as an oil
passage.

DEBCRIPTION AND OPERPITION 61 -1 0-1 4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

3. Model Designation System

A. Propeller Model Designation

Hartzell uses a model number designation system (outlined in Figure 4) to

identify specific propeller and blade assemblies. An example model

number would be HC-A2MVF-3/M1 0282A+6, where the slash mark
separates the propeller and blade designations.
The propeller impression stamped on the propeller hub.
model number is
The blade model number is impression stamped on the butt end of the
blade, as well as ink stamped or labelled on the camber side of the
blade.

B. Blade Shank Designation

Refer to Hartzell Manual 133C (61-13-33), Aluminum Blade Manual for
more information on blade shank designs.

C. Conversion From V Shank to MV Shank

"V" shank models, which have double-shoulder configuration, have

additional repetitve inspections required by Airworthiness
Directive 97-18-02.

"MV" shank models, which have a single-shoulder configuration, are not

affected by the Airworthiness Directive.

"V" shank blades be converted to "MV" shank to avoid the inspections

can

required by the Ainnrorthiness Directive. After conversion, the propeller model

number changes to reflect the conversion. For example, AC-A2V20-1N8433N
becomes AC-A2MV20-1/MV8433N

AD97-18-02 does not apply to )HC-A( )MV( propellers. These propellers

are equipped with "MV" blade shank retention systems.

DESCRIPTION ANOOPER~TION 61’1 0’1 4

 PROPELLER
HARTZELL C411LIPUNAM

B HC A 2 V F 1 D1 blade model number

L,SEE
REFER TO HARTZELL MANUAL 133C FOR ALUMINUM BLADES
REFER TO HARTZELL MANUAL 135F FOR COMPOSITE BLADES

NEXT TWO PAGES

i COUNTERWEIGHTS, OIL TO DECREASE PITCH, NO SPRING

2 FEATHERING, COUNTERWEIGHTS, OIL TO DECREASE
PITCH, FEATHERING SPRING
3- REVERSING
SPECIFIC DESION--( q NO COUNTERWEIGHT, OIL TO INCREASE PITCH,
FEATURES EXTENDED LINK SCREW
(see next page 4A.COUNTERWEIGHT, OIL TO DECREASE PITCH
for exceptions) 5 REVERSING, FEATHERING, COUNTERWEIGHTS
6 NO COUNTERWEIGHT, OIL TO INCREASE PITCH

BOLTCIRCLE DOWELS NO.OFBOLTS TYPICAL

(inches) NO. DIA. OR STUDS ENGINE

MOUNTING 4.00 2 1/2 6 (1/2") CONTINENTAL

FLANGE 4.75 6 (7/16") LYCOMING 0-290, 0-320
4.75 6 (1/2") LYCOMING
SAE 20 SPLINE

BLADESHANK
I V DOUBLE SHOULDER BLADE RETENTION SYSTEM
MV SINGLE SHOULDER BLADE RETENTION SYSTEM

NO. OF 3

BASIC LIGHT HUB, SPLIT BEARING RETENTION, SUPERSEDES 8,

HC I HARTZELL CONTROLLABLE
HA I HARTZELL ADJUSTABLE GROUND ADJUSTABLE

DOWEL
LOCATIONI BLANK

B
C
D-
90 AND 270 DEGREES CLOCK
0 AND 180 DEGREES
WISE, CONTINENTAL
CLOCKWISE, LYCOMING
30 AND 210 DEGREES CLOCKWISE, CONTINENTAL
150 AND 330 DEGREES CLOCKWISE, LYCOMING
60 AND 240 DEGREES CLOCKWISE, CONTINENTAL
E- 0 AND 180 DEGREES AND PROPELLER AND TC MARKS ALIGNED, CONTINENTAL
P 0 AND 180 DEGREES AND PROPELLER AND TC MARKS ALIGNED, CONTINENTAL

DESCRIPTION AND OPERATION 61 11 0-1 4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

BHC-A2VF-1 D1
T
MINOR
MODIFICATION

FLANOED:

I ~HC-APV(F.K.U-1. -6 IPrint D-985~ 1 ~HC-APMVIF.K.U-1. -6 (Print D-985)

-1 Counterweights, non-feathering, oil pressure to -1 Counterweights, non-feathering, oil pressure to

decrease pitch, no spring decrease pitch, no spring

-6 No counterweights, non-feathering, oil -6 No counterweights, non-feathering, oil

pressure to increase pitch, no spring pressure to increase pitch, no spring

PISTON, SPINNER,
1A- DIFFERENT HUB, 1A- DIFFERENT HUB, PISTON, SPINNER,

"A" DOWEL LOCATION, ALUMINUM DOWEL "A" DOWEL LOCATION, ALUMINUM DOWEL

BHC "B" DOWEL LOCATION, STEEL DOWEL BHC "B" DOWEL LOCATION, STEEL DOWEL

HC-AZVIF.K.LI-P (print D-980) HC-APMVIF.K.U-P (Drint D-980~

A DIFFERENT SPRING ASSY. A DIFFERENT SPRING ASSY.

B DIFFERENT SPRING ASSY., C-2530 SPINNER, B DIFFERENT SPRING ASSY., C-2530 SPINNER,
830-12 STOP UNIT 830-12 STOP UNIT

D-1495~ 1 (Drints D-1446&D~

I IHC-ASVIF.KI-2 lorints D-1446

A 838-60 CLAMPASSY. A 838-1060 CLAMP ASSY.

B 838-11ACLAMP ASSY. B 838-1011A CLAMP ASSY.

C 838-6 CLAMP ASSY. C 838-1006CLAMP ASSY.
D 838-23 CLAMP ASSY. D 838-1023 CLAMPASSY.

L- LEFTHAND ROTATION L- LEFT HAND ROTATION

EHC 840-83 HUB ASSEMBLY EHC 840-83 HUB ASSEMBLY

PHC 840-102 HUB ASSEMBLY PHC 840-102 HUB ASSEMBLY

(~HC-A2VF-3 (Drint D-2950) 1 ~HC-APMVF-8 (orint D-2950

NO MINOR MODIFICATIONS/LETTER CHANGES NO MINOR MODIFICATIONS/LETTER CHANGES

BHC FOR WREN BHC FOR WREN

HC-AIVF-BL (Drint D-2970) HC-ASMVF-BL (Drint 0-2970)

L LEFT HAND ROTATION L LEFT HAND ROTATION

HC-ABMVIF.K)4 (orint D-1484)

I IHC-ABVIF.Kld IDrint D-1484~
Non-feathering, oil to increase pitch, no
Non-feathering, oil to increase pitch, no
countennreights but have countemreightlike arm to

countennreights but have counterweightlike arm to

connect link arms to side of clamp
connect link arms to side of clamp D- DIFFERENT SPINNER
D DIFFERENT SPINNER EHC 840-102 HUB ASSEMBLY
EHC 840-102 HUB ASSEMBLY PHC 840-83 HUB ASSEMBLY
PHC 840-83 HUB ASSEMBLY
HC-A3MVF-SIA.AU (Drint D-3600~
HC-ABVF-SIA.AL) ~Drint D-3600)
A FOR LYCO GO-480, 838-1077 CLAMP
A FOR LYCO GO-480, 838-77 CLAMP ASSEMBLY, ASSEMBLY, 8-1457 REVERSE VALVE
8-1457 REVERSE VALVE L LEFT HAND ROTATION
L LEFT HAND ROTATION
(IHC-A3MVF-SR (orint D-3670~
I ~HC-AIVF-SR (Drint D-3670~
R- BETARING
R- BETARING HC- FOR LYCO GO-480
HC- FOR LYCO GO-480 PHC- FOR CONT TSIO-520, 8-2984-3 HUB SPACER,
PHC- FOR CONT TSIO-520, B-2984-3 HUB SPACER, A-3419-5 STOP PLATES, D-5494 REVERSING
A-3419-5 STOP PLATES, D-5494 REVERSING PARTS
PARTS

Page
DESCRIPTION AND OPERATION 61 -1 0-1 4 9Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 114C

BHC-A2VF-1 D1
T
MINOR
MODIFICATION

20 SPLINE:

HC-A?VZO-1IDrint D-20251
A 834-3A GUIDE COLLAR
A 834-3A GUIDE COLLAR

HA-AgMVZO-1B (Drint D-1930)

HA-A2V20-1B (orint D-1930)
GROUND ADJUSTABLE BLADE PITCH
GROUND ADJUSTABLE BLADE PITCH
NO OIL SUPPLY NEEDED
NO OIL SUPPLY NEEDED

HC-A2V20-2 Iorint D-20201 HC-A2MV20-2 (Drint D-2020)

NO MINOR MODIFICATIONS/LETTER CHANGES NO MINOR MODIFICATIONS/LETTER CHANGES

HC-A2V20-3L larint D-4530~ HCA2MV20-3L (Drint D-4530~

Feathering, reversing with beta ring Feathering, reversing with beta ring
A FOR LYC G0480 ENGINE, A-4117 REVERSING A FOR LYC GO480 ENGINE, A-4117 REVERSING
VALVE ASSY VALVE ASSY
B FOR LYC GO435 ENGINE, A-2372 REVERSING B FOR LYC GO435 ENGINE, A-2372 REVERSING
VALVE ASSY VALVE ASSY
L LEFT HAND ROTATION L LEFT HAND ROTATION

HC-A2V20-4A1 (Print 0-220~ HC-A2MV20-4A1 (Drint D-220)

Countennreighted, pressure to decrease pitch, oil Countennreighted, pressure to decrease pitch, oil
transfer unit ports governor oil over engine shaft transfer unit ports governor oil over engine shaft
O.D. to propeller piston O.D. to propeller piston
A USES A-224() OIL TRANSFER UNIT, 834-10 A USES A-224( OIL TRANSFER UNIT, 834-10
GUIDE COLLAR GUIDE COLLAR
B DISCONTINUED, 834-11 GUIDE COLLAR B DISCONTINUED, 834-11 GUIDE COLLAR
1 LATEST SEAL KIT FOR OIL TRANSFER UNIT 1 LATEST SEAL KIT FOR OIL TRANSFER UNIT

HC-A3V20-1 IDrints 0-1492. D-27211

HC-A3MV20-1 (Drints D-1492. D-2721
A- OBSOLETE, RBY -1B
A OBSOLETE, REPLACED BY -1B
8- A-50-3CONE
B- A-50-3CONE
C- OBSOLETE, RBY -1D
C OBSOLETE, REPLACED BY-1D
D- A-50-5CONE
D- A-50-5CONE
E A-50-5CONE,838-25R CLAMP E- A-50-5CONE, 838-1025RCLAMP
F SAME AS "E" EXCEPT DIFFERENT
F- SAMEAS"E" EXCEPTDIFFERENT
SPINNER
SPINNER

HC-A3V20-2 (Print D-1485)

HC-A3MV20-2 (orint D-14851
-2 (With 8433 blades) 838-6 Clamps, -2 (With 8433
blades) 838-1006 Clamps,
830-5 Stops
830-5 Stops
-2 (Wlth 9333 blades) 838-23 Clamps -2 (With 9333 blades) 838-1023 Clamps
-2 (With 9333CH blades) 838-23 Clamps, -2 (With 9333CH blades) 838-1023 Clamps,
830-18 Stops
830-18 Stops
A- NOSTOPS
A- NOSTOPS
L LEFT HAND ROTATION
L LEFT HAND ROTATION

HC-A3V20-3L ~Drint D-4519~

HC-A3MV20-3L (Drint D-4519)
Feathering, reversing with beta ring
L
Feathering, reversing with beta ring
LEFT HAND ROTATION
L LEFTHAND ROTATION

DESCRIPTION AND OPERATION 61-10-14 Page

10Mar/98
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

CONTENTS

102
1. Trouble-Shooting Guide
A. Excessive Friction in Hub Mechanism 102

B. Excessive Friction in Piston 103

C. Failure to Feather 103

Pitch 103
D. Failure to Change
RPM 103
E. Surging or Torque
105
F. Oil Leakage
105
G. Grease Leakage
Movement in Blade 107
H. End-Play
In and Out Movement in Blade 107

I I.

J. Fore and Aft Movement in Blade 107

107
K. Blades not Tracking
Radial in Blade 107
L. Play
in Blade Clamp 108
M. Blade Slippage
108
N. Excessive PropellerVibration

LIST OF ILLUSTRATIONS

101 100
Checking Blade Movement Figure
AbnormalVibration Figurel02 ´•´•´•´•´•´•´•´•´•´•´•´•108

TESTING AND FAULT ISOLATION 61 ’1 0’1 4

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 114C

1. Trouble-Shooting Guide

The purpose of this guide is to help isolate probable causes and suggests possible
remedies for some of the more common propeller service problems. In all cases, the

remedy for a problem should follow the procedures detailed in the applicable section of
this manual.

Problem Probable Cause Remedy

A. Excessive Friction Insufficient clearance between Check moving parts individually for
in Hub Mechanism various moving parts in the pitch interference.
change mechanism.

Balls in the blade split-bearing Replace the blade

are split-bearing
unusually rough, corroded, or assembly
chipped.

The pilot tube has slipped out Follow Disassembly Procedure for the
slightly and is rubbing hard hub spider unit. Refer to Allowable
against the end of the cavity in the Wear Limits Table in section 800.
blade.
If the hub pilot tube extends more than
3.8125 inches beyond the outer edge
of the hub spider, follow replacement
procedure.

Lack of lubrication Add approved grease to blade clamp

zerks.

Snap ring is wedged under Replace snap ring.

inboard race of blade bearing.

TESTING AND FAULT ISOLATION 61-10-14 Page

102Mar/98
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

Problem Probable Cause Remedy

Pistonbushing is scraping Check inside diameter of phenolic

B, Excessive Friction
in Piston against wall of cylinder bushing. Refer to Allowable Wear Limits
Table in Section 800.

Check roundness of the bushing. Follow

replacement procedure if necessary.

Check outside diameter of cylinder. Refer

to Allowable Wear Limits Table in Section
800. Follow cylinder replacement
procedure if necessary.

Remove any evidence of wear or chafing

onthe cylinder. Follow repair procedure
as applicable.

Excessive friction in moving Refer to Problem A, "Excessive Friction in

C. Failure to Feather
Hub Mechanism."
parts.

Feathering spring is weak or Replace the feathering spring.

broken.

Excessive friction in moving Refer to Problem A, "Excessive Friction in

D. Failure to Change
Hub Mechanism.
Pitch parts.

NOTE: Isolate the friction in each blade

(Sluggish RPM in
both directions) by uncoupling the piston and testing each
blade individually before disassembling
the propeller.

Oil passages are not clear and Check out the hydraulic system.
open.

Excessive friction in pitch Refer to Problem A, "Excessive Friction in

Surging RPM or
the Hub Mechanism."
Torque change mechanism.

trapped in the propeller

Air is The engine should have provision for
actuating piston or in the engine allowing trapped air to escape from the
shaft. system during one-half of the pitch cycle.

Before each flight, exercise the propeller

by changing pitch or feathering.

Reset beta ring runout to specified limits.

Beta ring runout is excessive,
causing vibration of carbon See Assembly Section.
block.

Page
TESTINOANDFAULT ISOLP~TION 61-10-14 103Mar/98
 PROPELLER MAINTENANCE
HA RT Z E L L C411LAUNAM

(This page is intentionally blank.)

TESTING AND FAULT ISOLATION 61 ’1 0’1 4 Page

104Mar/98
 PROPELLER MAINTENANCE MANUAL
RTZ c L L 114C

Problem Probable Cause Remedy

Oil Leakage Faulty O-ring seal between Disassemble the propeller and inspect
hub spider and cylinder. the O-ring and the surfaces it seals.
Replace defective O-ring.
Use approved hydraulic sealant on O-
ring groove of hub at top of cylinder
mounting threads when O-ring is
replaced.

Replace the cylinder if its surface is

Faulty O-ring seal between
scratched gouged in the area where
piston and cylinder. or

the O-ring slides.

Felt seal is displaced. Replace felt seal.

Faulty O-ring on pilot tube. Replace O-ring.

Faulty propeller mounting Replace O-ring.

O-ring.

G. Grease Leakage Improperly torqued or loose Replace defective lubrication fittings.

lubrication fitting.
Replace missing lubrication fitting caps.

NOTE: The blade Defective lubrication fitting. Torque lubrication fitting to 50 inch-

clamp/split-bearing is pounds.
the only source for
grease leakage.
NOTE: If propeller rpm exceeds 2300
maximum, safety wire the lubrication
fitting caps with 0.0e0-inch (0.51-mm)
minimum diameter stainless steel wire.

Grease leaks past blade Loosen blade clamp bolts and replace
clamp seal gaskets, gaskets, sealant, and gasket compound.

Grease leaks from between Remove blade and clamp. Add approved
blade and gasket compound in radius of blade.
clamp,
Reassemble blade and clamp.

No silicone sealant onclamp Remove blade and clamp. Add approved

radius of bearing-to-clamp gasket compound in radius of
clamp.
interface. Reassemble blade and clamp.

Page
TESTING AND FAULT ISOLATION 61-10-14 105Mar/98
 PROPELLER
HARTZELL MA~T4ECN*MCE MINUAL

APS5003

Fore and
aft blade
movement

play in

In and out blade

movement

End-play in blade

Checking Blade Movement

Figure 101

TESTING AND FAULT ISOLATION 61-10-14 Page

106Mar/98
 PROPELLER MAINTENANCE MANUAL
H~RTZ ELL 114C

Problem Probable Cause Remedy

H, End-Play movement Buildup of wear or repair Total O.lOO-inch end-play is

in Blade tolerances, permissible.

Refer to Figure 101. Refer to Allowable Wear Limits Table

in Section 800.

In-and-Out Movement Buildup of wear or repair Without grease in blade clamps and
in Blade tolerances. split-bearings, maximum allowable in-
and-out movement is 0.100 inch.
Refer to Figure 101.
With grease in blade clamps and
split-bearings, there should not be
any in-and-out movement in the
blades.

Refer to Allowable Wear Limits Table

in Section 800.

J. Fore-and Aft Movement Buildup of allowable wear or Total of 0.100 inch fore-and-aft
in Blade repair tolerances, movement in permissible.

Refer to Figure 101. Refer to Allowable Wear Limits Table

in Section 800.

II, Blades not Tracking Ground strike damage. Refer to appropriate blade overhaul
manual for repair procedure.

Refer to Standard Practices Manual

202A.

Hub pilot tube(s) distorted. Followpilot tube replacement

procedure in Standard Practices
Manual 202A.

Blade facets) out of alignment. Refer to the applicable blade overhaul

manual for face alignment procedure.

C, Radial Play in Blade Wear in link arm screw hole or Total 0.5" is permissible. See
pin hole. Allowable Wear Limits Table in
Section 800.

Page
TESTING AND FAULT ISOLATION 61-10-14 107Mar/98
 PROPELLER
HARTZELL Y*:N:4ECNANCE MINU~L

WARNING: ABNORMAL GREASE LEAK OR VIBRATION CAN BE AN INDICATION

OF A FAILING PROPELLER BLADE OR BLADE RETENTION
COMPONENT. AN IN-FLIGHT BLADE SEPARATION CAN RESULT IN A
CATASTROPHIC AIRCRAFT ACCIDENT.
Problem Probable Cause Remedy
M~ Blade Slippage in Lubricant action of sealer Follow rework procedure to correct slippage.
Blade Clamp has reduced the friction
between blade and clamp.

There is not enough Increase clamping action as necessary. Refer

clamping action. toClamp Overhaul section of Manual 202A
(61-01-02).

N, Excessive Propeller Blade slipped in clamp. Inspect blade-to-blade angles and reset angles.
Vibration

Refer to Figure 102. Cracked blade clamp. Mag particle inspect blade clamp and replace
defective part.

Bent, cracked, or damaged See Hartzell Manual 133C for Blade Overhaul
blade. procedures.

Cracked or damaged hub. See Steel Hub Overhaul section of Hartzell

Manual 202A, Standard Practices.

Link arm is worn. Inspect link arm and replace as necessary.

Link arm is disconnected Threads in piston are worn or damaged. Repair

from piston. threads by using slimsert. See repair section of
this manual.

Inspect the seal of the blade

clamp for grease leakage.
Inspect the blade clamp
for cracks.

Abnormal Vibration
Figure 102

TESTING AND FAULT ISOLATION 61-10-14

 PROPELLER MAINTENANCE MANUAL
WARTZELL 114C

NOT APPLICABLE

NOTE: According to ATA 100 specification this space is reserved for automatic test

requirements. Such requirements are not applicable to the propellers

addressed in this manual.

Page
AUTOMPITICTEST RE~UIREMENTS 61 -1 0-1 4 201Mar/98
 PROPELLER MAINTENANCE
HA RTZ E L L C411LAUNAM

(This page is intentionally blank.)

AUTOMATIC TEST REOUIREMENTS 61 ’1 0’´•1 4

 PROPELLER MAINTENANCE MANUAL
HP~ RT r E L L 114C

CONTENTS

1. Removal of Hartzell Feathering Propellers 307

2. Disassembly of Flanged-Hub Models in the -1 and -6 Series 307

A. Spinner Disassembly 307

B. Propeller Removal 307

C. Marking Before Disassembly 309

D. Removing Piston 309

E. Removing Cylinder 309

F. Clamp and Countennreight Disassembly 311

G. Blade Mounting Parts Disassembly 313

H. Hub Unit Disassembly 313

3. Disassembly of Splined-Hub, Two-Blade Models in the -1 Series

(Except HA-A2(MV,V)20-1B) 314

A. Spinner Disassembly 314

B. Propeller Removal 314

C. Marking Before Disassembly 314

D. Piston Disassembly 315

E. Removing Cylinder 315

F. Clamp and CounteMleight Disassembly 315

G. Blade Mounting Parts Disassembly 315

H. Hub Unit Disassembly 315

4. Disassembly of Splined-Hub, Three Blade Models in the -1 Series 316

A. Spinner Disassembly 316

B. Propeller Removal 316

C. Marking Before Disassembly 316

D. Piston Disassembly 317

E. Removing Cylinder 317

F. Clamp and Countennreight Disassembly 317

G. Blade Mounting Parts Disassembly 317

H. Hub Unit Disassembly 317

5. Disassembly of Model HA-A2(MV,V)20-IB 318

61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 114C

A. Spinner Disassembly 318

B. Propeller Removal 318

C. Marking Before Disassembly 319

D. Disassembling Pitch Adjustment Assembly 319

E. Clamp Disassembly 319

F. Blade Mounting Parts Disassembly 319

G. Hub Unit Disassembly 319

6. Disassembly of Flanged-Hub Models in the -2 Series 320

A. Spinner Disassembly 320

B. Propeller Removal 321

C. Marking Before Disassembly 321

D. Removing Piston 323

E. Removing Feathering Spring Assembly 323

F. Removing Cylinder
G. Clamp and CounteMleight Disassembly 323

H. Blade Mounting Parts Disassembly 325

i. Start Lock Disassembly. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 325

J. Disassembling the Feathering Spring Assembly 326

K. Hub Unit Disassembly 326

7. Disassembly of Spl ined-H ub Models in the -2 Series 327

A. Spinner Disassembly 327

B. Propeller Removal 329

C. Marking Before Disassembly 329

D. Propeller Disassembly 330

E. Removing Cylinder. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 330

F. Clamp and Counterweight Disassembly 330

G. Blade Mounting Parts Disassembly 331

H. Start Lock Disassembly. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 331

i. Disassembling the Feathering Spring Assembly 331

J. Hub Unit Disassembly 331

8. Disassembly of Flanged-Hub Models in the -3 Series 332

A. Spinner Disassembly 332

OIBASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Removal 332
B. Propeller
C. Marking Before Disassembly 333

D. Spinner Bulkhead and Piston Disassembly 335

E. Feathering Spring Disassembly 336

F. Cylinder and Guide Collar Unit Disassembly 336

G. Clamp and Counterweight Disassembly 337

H. Blade and Flange Mounting Parts Disassembly.......................................... 337

i. Disassembling the Feathering Spring Assembly 337

J. Hub Spider Unit Disassembly 337

9. Disassembly of Splined-Hub Models in the -3 Series 338

A. Spinner Disassembly 338

B. Propeller Removal 338

C. Marking Before Disassembly 339

D. Spinner Bulkhead and Piston Disassembly 340

E. Cylinder and Guide Collar Unit Disassembly 340

F. Clamp and Counterweight Disassembly 341

G. Blade Mounting Parts Disassembly 341

H. Disassembling the Feathering Spring Assembly 341

i. Hub Spider Unit Disassembly 341

10. Disassembly of Flanged-Hub Models in the -4 Series 342

A. Spinner Disassembly 342

B. Propeller Removal 342

C. Marking Before Disassembly 343

D. Removing Piston 345

E. Removing Cylinder 345

F. Clamp and Counten~veight Disassembly 345

G. Blade Mounting Parts Disassembly 346

11. Disassembly of HC-A2(MV,V)20-4A1 347

347
A. Spinner Disassembly
B. Propeller Removal 347

C. Oil Transfer Unit Removal 348

D. Marking Before Disassembly 348

,,,,,,,,,,Y 61 11 0’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

E. Piston Disassembly 348

F. Removing Cylinder
G. Clamp and Counterweight Disassembly 349

H. Blade Mounting Parts Disassembly 349

i. Hub Unit Disassembiy 349

I J. Oil Transfer Unit Disassembly 349

12. Disassembly of Flanged-Hub Models in the -5(A,AL) Series 350

A. Spinner Disassembly 350

B. Propeller Removal 350

C. Beta Valve Removal 351

D. Marking Before Disassembly 351

E. Spinner Bulkhead Removal 351

F. Start Lock Removal 351

G. Piston Disassembly 353

H. Feathering Spring Disassembly 353

i. Cylinder and Guide Collar Unit Disassembly 353

J. Clamp and Counterweight Disassembly 354

K. Blade Mounting Parts Disassembly 354

L. Hub Spider Unit Disassembly 355

M. Start Lock Disassembly 355

13. Disassembly of Flanged-Hub Models in the -5R Series 357

A. Spinner Disassembly 357

B. Beta Control Unit Removal 357

C. Propeller Removal 357

D. Marking Before Disassembly 358

E. Spinner Bulkhead, Start Lock, Beta Rod, and Piston Disassembly 358

F. Feathering Spring Disassembly 359

G. Cylinder and Guide Collar Unit Disassembly 360

H. Clamp and Counterweight Disassembly 360

i. Blade Mounting Parts Disassembly 361

J. Hub Unit Disassembly 361

K. Start Lock Disassembly 362

61-10-14
 PROPELLER MAINTENANCE MANUAL
H~RTZ E LL 114C

LIST OF FIGURES

Removing Piston and Cylinder Figure 301 308

Clamp Assembly Figure 302 310

Removing Bearing Retention Ring Figure 303 312

Models in the -2 Series Figure 304 322

Placing Spring Assembly in Special Fixture Figure 305 326

Models in the Splined-Hub -2 Series Figure 306 328

Models in the -3 Series Figure 307 334

Models in the -4 Series Figure 308 344

Models in the -5(A,AL) Series Figure 309 352

Models in the -5R Series Figure 310 356

DISP~SSEMBLY 61-10-14
 PROPELLER
HA RTZ E L L MA:N1~CNANCE MANUAL

(This page is intentionally blank.)

Page
DISASSEMBLY 61 11 011 4 306Mar/98
 PROPELLER MAINTENANCE MANUAL
HA,RTZ ELL 114C

1. Removal of Hartzell Featherinq Propellers

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

WARNING: HARTZELL FEATHERING PROPELLERS MUST BE IN THE FEATHER

POSITION BEFORE ATTEMPTING REMOVAL OF PROPELLER
FROM AIRCRAFT. IF THE PROPELLER IS NOT CONTROLLED
DURING FEATHERING PROCEDURES, PERSONAL INJURY MAY
OCCUR AND DAMAGE TO THE PROPELLER PISTON WILL OCCUR.

A. When feathering propeller manually, control propeller with blade paddle.

B. Move blade enoughto release pressure on high stop pin, depress pin, then slowly
release blade pressure to allow stop plate to pass the pin.

C. On the last blade, when releasing the stop pin, be careful to control the propeller as
it will be ready to feather.

2. Disassemblv of Fianced-Hub Models in the -1 and -6 Series

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
bulkhead

(2) Remove the spinner dome.

NOTE: If the propeller is equipped system, follow the

with a de-icer
manufacturer’s instructions for removing whatever components
are necessary for propeller removal.

B. Propeller Removal
(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove and discard the bolts from the flange of the hub.

(3) Remove the propeller from the crankshaft of the aircraft engine.
(4) Remove and discard the propeller mounting O-ring.
(5) Remove the rear bulkhead from the hub flange, or the adaptor ring from
the engine starter ring gear.
(6) Place propeller on propeller cart for transportation.

61-10-14
 PROPELLER
HARTZELL MA:N:4ECNANCE YANUAL

aps6133

legend:
1. flexlock nut
2. push rod
3. piston ´•t’-’
4. fork
5. sleeve
6. washer
cylinder ‘p
8. O-ring ´•i´•´•;-
´•B
9. felt seal
10. staking pin.
11. O-ring
12. bushing
13. ~k 13
pitch change block
8 link screw

Removing Piston and Cylinder

Figure 301

Page
DISASSEMBLY 61 ’1 0’14 308Mar/98
 PROPELLER MAINTENANCE MANUAL
H~A RTZ E LL 114C

C. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL
TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
any other serial-numbered parts and compare with the data in the
propeller logbook.
(2) In order to minimize reassembly problems with propeller balance and
blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on parts must be made with crayon or soft, non-graphite
pencil. Blades should be numbered counterclockwise from the serial
number of the propeller hub las viewed from the front, or piston, side).

(4) Each blade must be reinstalled on the hub spider arm from which it was

removed, where possible. Record on paper each blade serial number

and its matching hub arm and clamp.
D. Removing Piston

NOTE: Item numbers are from Figure 301.

(1) Mount the propeller assembly on the rotatable fixture of a propeller

assembly table.

(2) Remove nuts (1) from ends of push rods (2).

(3) Pull piston (3) off, leaving forks (4) and sleeves (5) in place.
(4) While removing piston, the blades may need to be rotated until piston
can be rotated to allow block (13) to slide off of link screw.

(a) Remove block (13) from fork (4).

(b) Loosen set screw in each fork.

(5) Remove forks and sleeves and piston push rods.

(6) Remove O-ring inside piston (11).

E. Removing Cylinder
(1) Remove dust seal from outside diameter groove in cylinder.
(2) Unscrew the cylinder (7) from the hub by placing a one-inch-wide steel bar
into the slots in the cylinder. There may be some "drag" caused by the
O-ring (8).
(3) Remove and discard O-ring (8).

61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1140

clamp2.plt

legend:
1. cotter pin
2. dowel pin
3. roll pin
4. link screw

5. socket screw

6. clamp gasket
clamp bolt
8. nut
9. counterweight mounting cap screw

10. counterweight
11
11. clamp

1´•

i/
9

3A

I Clamp Assembly
Figure 302

DISASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
H19 RTZ E L L 114C

F. Clamp and Counterweight Disassembly

NOTE: Item numbers are from Figure 302.

(1) Remove all balance weights and attaching screws, where applicable.
Discard screws.

(2) Use a round bottom metal stamp or electric pencil and identify clamp
serial number on each corresponding counterweight.

(3) Remove and discard all outboard clamp bolts (7) and nuts (8).
(4) Remove and discard all inboard clamp socket screws (5) and cotter
pins (1) or safety wire.

(5) Remove all clamp halves (11) from the hub spider arms.

NOTE: Refer to the Clamp Overhaul Section of Hartzell Manual 202A

(61-01-02), Standard Practices, for information on clamp
inspection and repair.
(6) Remove and discard clamp gasket (6).
(7) Remove and discard all lubrication fittings and their caps.

NOTE: Steps (8) through (10) do not apply to -6 series propellers, which
have no counterweights installed.

(8) Remove and discard the hex head counterweight slug attaching bolts, if
applicable. Remove the counterweight slugs, if applicable.
(9) Remove and discard the socket head counterweight mounting cap
screws (9) attaching counterweight (10) to clamp (11).

NOTE: Remove roll pin (3A) by punching inboard and prying out.

(10) Remove counterweight (10) from clamp by twisting to free dowel pin (2)
from the clamp.

NOTE: Counterweight (10) is attached to clamp (11) by a dowel

pin (2), which remains with the counterweight.
(11) Remove each blade assembly from the hub.

.,,,,,,,,,Y 61-10114
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 114C

legend:
1. blade
2. wire retention ring
3. guide ring
4. ballspacer
5. bearing races and balls
6. bearing retention ring
7. O-ring
STEP ONE

STEP THREE

aps213

Removing Bearing Retention Ring

Figure 303

DISASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA,RTZ E LL ´•I~lse

G. Blade Mounting Parts Disassembly

NOTE 1: Item numbers are from Figure 303.

NOTE 2: Bearing races are in matched sets (two races in each set). Do not mix with
other bearing races.

(1) Beginning with blade position number one, remove the bearing retention
ring (6) from its groove in the inboard race of the blade retention split
bearing.
(2) Remove the two halves of the inboard bearing race.

(3) Remove and discard the ball spacer (4) and bearing balls (5).
(4) Clip, remove, and discard the blade O-ring (7).
(5) Use a mallet and soft punch at several
places on the outboard edge of
the guide ring (3) to drive the ring inboard over the shoulder of the hub
spider arm. See Figure 303, Step One.
(6) Remove the wire retention ring (2) that had been covered by the guide
ring. Discard wire retention ring if it is sprung.
(7) Turn the halves of the inboard bearing race so the split is at the top.
See Figure 303, Step Two.

(8) At the split, place one of the bearing balls between the outboard split-
bearing race and inboard shoulder of the hub spider arm.

(9) Using a soft mallet, lightly tap the inboard top edge of the guide ring to
dislodge the split outboard race from the guide ring.
(10) Remove the halves of the race as they become separated from the
retention ring.
(11) Tilt the guide ring inboard approximately 45" and remove the ring by
sliding it outboard over the shoulder of the hub spider arm. See Figure
303, Step Three.
H. Hub Unit Disassembly
(1) Remove and discard both socket head cap screws from guide collar unit
located between the bladearms and hub flange.

(2) Remove guide collar from hub.

(3) Follow the procedure in the Steel Hub Overhaul section of Hartzell Standard
Practices Manual 202A (61-01-02) for pilot tube removal.

DISASSEMBLY 61 ’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

3. Disassemblv of Splined-Hub, Two-Blade Models in the -1 Series ~ExceDt HA-

A2(MV.V~20-1 B)

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
engine-side bulkhead unit.

(2) Remove the spinner dome.

NOTE: If the propeller is de-icer system, follow the

equipped with a

manufacturer’s instructions for removing whatever components

are necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

B. Propeller Removal

(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove the nuts from the ends of the piston-mounted push rods.

(3) Pull the piston forward to allow the push rods to exit the guide collar.

(4) Rotate the piston to move the forks away from the clamps and link screws.

(5) Remove the blocks from the forks and remove the piston from the cylinder.
Sleeves and forks will remain on the piston push rods at this time.

(6) Remove safety pin from engine shaft nut.

(7) Remove nut from engine shaft, pulling propeller hub from engine shaft.

(8) Remove rear cone and spinner bulkhead from engine shaft.

(9) Place propeller on propeller cart for transportation.

C. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL
TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
any other serial-numbered parts and compare with the data in the
propeller logbook.

DIS*SSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HP~ RTZ LL 114C

(2) In order to minimize reassembly problems with propeller balance and

blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on parts must be made with crayon or soft, non-graphite
pencil. Blades should be numbered counterclockwise from the serial
number of the propeller hub las viewed from the front, or piston, side).

(4) Each blade must be reinstalled on the hub spider arm from which it was
removed, where possible. Record on paper each blade serial number
and its matching hub arm and clamp.

D. Piston Disassembly
(1) Loosen set screw in each fork.

(2) Remove forks, sleeves, and spacers from piston push rods.

(3) Remove O-ring inside piston.

E. Removing Cylinder
(1) Unscrew the cylinder from the hub by placing a one-inch-wide steel bar into
the slots in the cylinder. There may be some "drag" caused by the O-ring.

(2) Remove and discard O-ring.

F. Clamp and Counterweight Disassembly
Procedure is the same as for flanged-hub models in the -1 and -6 series.

G. Blade Mounting Parts Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

H. Hub Unit Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

DIS~SSEMBLY
61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

4. Disassemblv of Splined-Hub, Three Blade Models in the -1 Series

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
engine-side bulkhead unit.

(2) Remove the spinner dome.

NOTE: If the propeller is equipped with a de-icer

system, follow the
manufacturer’s instructions for removing whatever components
are necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

B. Propeller Removal

(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove the nuts from the ends of the piston-mounted push rods.

(3) Remove fork set screws.

(4) Pull piston off cylinder and remove from propeller.

NOTE: Rod sleeves, high pitch stop washers, and fork should slide off each
piston push rod during piston removal and are to be removed from
the propeller when the piston is removed.

(5) Remove safety pin from engine shaft nut.

(6) Remove nut from engine shaft, pulling propeller hub from engine shaft.

(7) Remove rear cone and spinner bulkhead from engine shaft.

(8) Place propeller on propeller cart for transportation.

C. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL
TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
any other serial-numbered parts and compare with the data in the
propeller logbook.

DISASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

(2) In order to minimize reassembly problems with propeller balance and

blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.
(3) All marks made on parts must be made with crayon or soft, non-g raphite

pencil. Blades should be numbered counterclockwise from the serial

number of the propeller hub las viewed from the front, or piston, side).
(4) Each blade must be reinstalled on the hub spider arm from which it was

removed, where possible. Record on paper each blade serial number

and its matching hub arm and clamp.
D. Piston Disassembly
(1) Remove O-ring inside piston.
E. Removing Cylinder
(1) Unscrew the cylinder from the hub by placing a steel bar one-inch wide into
the slots in the cylinder. There may be some "drag" caused by the O-ring.
(2) Remove and discard O-ring.
F. Clamp and Counterweight Disassembly
Procedure is the same as for flanged-hub models in the -1 and -6 series.

G. Blade Mounting Parts Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

H. Hub Unit Disassembly

Follow the procedure in the Steel Hub Overhaul section of Hartzell Standard
Practices Manual 202A (61-01-02) for pilot tube removal.

61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

5. Disassemblv of Model HA-A2(MV,V)20-1B

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
engine-side bulkhead unit.

(2) Remove the spinner dome.

NOTE: If the propeller is equipped with a system, follow the

de-icer
manufacturer’s instructions for removing whatever components
are necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

B. Propeller Removal

(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove safety wire and safety screws from link pin units on piston.
(3) Remove link pin units.

(4) Remove cotter pins from clamp link screws.

(5) Remove link screw sleeves and link arms.

(6) Loosen and remove locking nut from pitch change rod in center of piston unit.

(7) Remove piston unit.

(8) Remove O-ring from pitch change rod, if installed.

(9) Remove dust seal from inside of piston unit.

(15) Remove O-ring from inside of piston unit, if installed.

(11) Remove screws in pitch adjustment assembly that are holding a round ring in
place.
(12) Remove plate (round ring).
(13) Remove two-piece split retainer.

(14) Remove pitch adjustment assembly.

(15) Unscrew and remove cylinder from hub by placing a steel bar, one-inch wide,
into the slots in the cylinder. There may be some drag caused by the O-ring.

DISP~SSEMBLY 61’10-14
 PROPELLER MAINTENANCE MANUAL
H IC(L RT Z c L L 114C

(16) Remove and discard O-ring.

(17) Remove safety pin from engine shaft nut.

(18) Remove nut from engine shaft, pulling propeller hub from engine shaft.
(19) Remove rear cone and shaft O-ring from engine shaft.
(20) Place propeller on propeller cart for transportation.
C. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL
TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
any other serial-numbered parts and compare with the data in the
propeller logbook.
(2) In order to minimize reassembly problems with propeller balance and
blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on parts must be made with crayon or soft, non-graphite
pencil. Blades should be numbered counterclockwise from the serial
number of the propeller hub las viewed from the front, or piston, side).
(4) Each blade must be reinstalled on the hub spider arm from which it was

removed, where possible. Record on paper each blade serial number

and its matching hub arm and clamp.

D. Disassembling Pitch Adjustment Assembly

(1) Remove pitch change rod from pitch adjustment assembly.
(2) Remove lock nut from threaded retainer.

(3) Loosen and remove socket set screw.

(4) Loosen and remove retainer from pitch adjustment assembly housing
("mushroom").
E. Clamp Disassembly
The procedure for clamp disassembly is the same as for flanged-hub models in
the
the -1 and -6 series, except that there are no counterweights. Instead, set screws
are installed in the clamp counterweight attachment holes. Remove the set screws.

F. Blade Mounting Parts Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

G. Hub Unit Disassembly

Follow the procedure in the Steel Hub Overhaul section of Hartzell Standard
Practices manual 202A (61-01-02) for pilot tube removal.

DISASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

6. Disassemblv of Flanaed-Hub Models in the -2 Series

WARNING: HARTZELL FEATHERING PROPELLERS MUST BE IN THE FEATHER

POSITION BEFORE ATTEMPTING REMOVAL OF PROPELLER
FROM AIRCRAFT. IF THE PROPELLER IS NOT CONTROLLED
DURING FEATHERING PROCEDURES, PERSONAL INJURY MAY
OCCUR AND DAMAGE TO THE PROPELLER PISTON WILL OCCUR.

CONTROL PROPELLER WITH BLADE PADDLE WHEN

FEATHERING PROPELLER MANUALLY.

MOVE BLADE ENOUGH TO RELEASE PRESSURE ON HIGH STOP

PIN, DEPRESS PIN, THEN SLOWLY RELEASE BLADE PRESSURE
TO ALLOW STOP PLATE TO PASS THE PIN.

ON THE LAST BLADE, WHEN RELEASING THE STOP PIN, BE

CAREFUL TO CONTROL THE PROPELLER AS IT WILL BE READY
TO FEATHER.

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
bulkhead.

(2) Remove the spinner dome.

NOTE: If the propeller is equipped with a de-icer system, follow the

manufacturer’s instructions for removing whatever components
are necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

Page
DISP~SSEMBLY 61-10-14 320Mar/98
 PROPELLER MAINTENANCE MANUAL
HP~ RT Z: E L L 114e

B. Propeller Removal

(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove and discard the bolts and washers from the flange of the hub.

(3) Remove the propeller from the crankshaft of the aircraft engine.
(4) Remove and discard the propeller mounting O-ring.
(5) Remove high pitch stop bracket(s) from hub flange and rear spinner
bulkhead.

NOTE: For Lycoming mounting only: step 6 uncovers bolts used for
fastening the propeller to the engine.
(6) Remove the high pitch stops.
(7) Remove spinner bulkhead from starter ring gear or hub as applicable.
(8) Place propeller on propeller cart for transportation.
C. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL
TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
any other serial-numbered parts and compare with the data in the
propeller logbook.
(2) In order to minimize reassembly problems with propeller balance and
blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on parts must be made with crayon or soft, non-graphite
pencil. Blades should be numbered counterclockwise from the serial
number of the propeller hub las viewed from the front, or piston, side).

(4) Each blade should be reinstalled on the hub spider arm from which it
was removed, where possible. Record on paper each blade serial
number and its matching hub arm and clamp.

DISPISSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
RTZ E L L 1140

aps 6134

,O
19 2

18
17

1516 16

12 11 legend:
4 1. piston retaining nut
14-
7 2. link screw

13~
d,6 3.4. cylinderpiston
6.5. pilot tubebushing
7. link arm
Z 8. link pin unit
109 20 felt seal
9.
1 8
10. O-ring
11. feathering spring assembly
12. front spring retainer split rings
13. pilot tube O-ring
14. outer mushroom
15. feathering spacer tube
16. inner feathering spring
17. rear sping retainer
18. rear split retainer
19. O-ring
20. safety screw

Models in the -2 Series

Figure 304

Page
OIS~SSEMBLY 61-10-14 32 Mar/98
 PROPELLER MAINTENANCE MANUAL
CIARTZELL 114C

D. Removing Piston

NOTE: Item numbers are from Figure 304.

(1) Mount the propeller assembly on the rotatable fixture of a propeller
assembly table.

WARNING: BE SURE PROPELLER IS FEATHERED BEFORE REMOVING

THE PISTON NUT.

(2) Remove piston retaining nut (1).

(3) Remove safety wire and link pin safety screws (20).
(4) Remove link pins (8).
(5) Remove socket head screws, check nuts, washers, and low stop spacers
from the end of the piston-mounted guide rods, as applicable.
(6) Slide piston (3) off cylinder (4) and pilot tube (5).
(7) Remove dust seal from inside diameter of piston.
(8) Remove O-ring from inside diameter of piston.
E. Removing Feathering Spring Assembly

CAUTION: DO NOT FORCE FEATHERING SPRING TO RELEASE SPLIT

RINGS iN CYLINDER. FORCING SPRING MAY CAUSE
RELEASE OF SPLIT RING RETAINERS IN SPRING ASSEMBLY.

(1) Remove feathering stops (not shown; held by two screws per stop).

(2) Remove front spring retainer split rings (12) by first pushing the spring
assembly into the cylinder about 1/4 inch, allowing split rings to fall out of

groove in cylinder.

(3) Remove spring assembly from front of cylinder.

F. Removing Cylinder
(1) Unscrew cylinder (4) from the hub by placing a steel bar i-inch wide into the
slots in the cylinder. There may be some "drag" caused by the O-ring (19).

(2) Remove and discard O-ring (19).

G. Clamp and Counterweight Disassembly
NOTE: Item numbers are from Figure 302.

(1) Remove all balance weights and attaching screws, where applicable.
Discard screws.

(2) Use round bottom metal stamp or electric pencil and

a identify clamp
serial number on each corresponding counterweight.

(3) Remove and discard all outboard clamp bolts (7) and nuts (8).

,,,,ssc,,,
61-10-14
 PROPELLER MAINTENANCE MANUAL
HA,RTZ E LL 114C

(This page is intentionally blank.)

Page
DISASSEMBLY 61 11 0114 324Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(4) Remove and discard all inboard clamp socket screws (5) and cotter
pins (1) or safety wire.

(5) Remove all clamp halves (11) from the hub spider arms.

NOTE: Refer to the Clamp Overhaul Section of Hartzell Manual 202A

(61-01-02), Standard Practices, for information on clamp
inspection and repair.
(6) Remove cotter pin from link screws.

(7) Remove link screw sleeves.

(8) Remove link arms.

(9) Remove and discard clamp gasket (6).

(10) Remove and discard all lubrication fittings and their caps.

(11) Remove and discard the hex head counterweight slug attaching bolts, if
applicable. Remove the counterweight slugs, if applicable.
(12) Remove and discard the socket head counterweight mounting cap
screws (9) attaching counterweight (10) to clamp (11).

NOTE: Remove roll pin (3A) by punching inboard and prying out.

(13) Remove counterweight (10) from clamp by twisting to free dowel pin (2)
from the clamp.

NOTE: Counterweight (10) is attached to clamp (11) by a dowel

pin (2), which remains with the counterweight.
(14) Remove stop plate mounting fasteners (two per stop plate) and remove

stop plates from clamps.

(15) Remove each blade assembly from the hub.

H. Blade Mounting Parts Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

I. Start Lock Disassembly

(1) Remove cotter pin from bracket.

WARNING: SPRING IS COMPRESSED AND WILL BE RELEASED WHEN THE

COTTER PIN IS REMOVED.

(2) Remove washer from bracket.

(3) Remove spring from bracket.

(4) Remove pin from bracket.

OISISSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HP~ R~ Z E L L Il~e

J. Disassembling the Feathering Spring Assembly

WARNING: THE FEATHERING SPRING ASSEMBLY IS PRELOADED TO

APPROXIMATELY 400 POUNDS FORCE. USE EXTREME
CAUTION WHEN REMOVING IT FROM THE PROPELLER AND
WHEN DISASSEMBLING IT.

(1) Use the benchtop fixture TE59 to compress the spring for disassembly
(Figure 305).
(2) Remove and discard the split rear retainer.

(3) Allow the feathering spring assembly to expand to its unloaded length,
and remove it from the special fixture.

(4) Disassemble remaining spring assembly component parts.

K. Hub Unit Disassembly
Follow the procedure in the Steel Hub Overhaul section of Hartzell Standard
Practices Manual 202A (61-01-02) for pilot tube removal.

aps4997

Placing Spring Assembly in Special Fixture

Figure 305

DISASSEMBLY
 PROPELLER MAINTENANCE MANUAL
H~ RTZ E LL 114C

7. Disassemblv of Splined-Hub Models in the -2 Series

WARNING: HARTZELL FEATHERING PROPELLERS MUST BE IN THE FEATHER

POSITION BEFORE ATTEMPTING REMOVAL OF PROPELLER
FROM AIRCRAFT. IF THE PROPELLER IS NOT CONTROLLED
DURING FEATHERING PROCEDURES, PERSONAL INJURY MAY
OCCUR AND DAMAGE TO THE PROPELLER PISTON WILL OCCUR.

CONTROL PROPELLER WITH BLADE PADDLE WHEN

FEATHERING PROPELLER MANUALLY.

MOVE BLADE ENOUGH TO RELEASE PRESSURE ON HIGH STOP

PIN, DEPRESS PIN, THEN SLOWLY RELEASE BLADE PRESSURE
TO ALLOW STOP PLATE TO PASS THE PIN.

ON THE LAST BLADE, WHEN RELEASING THE STOP PIN, BE

CAREFUL TO CONTROL THE PROPELLER AS IT WILL BE READY
TO FEATHER.

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
bulkhead.

(2) Remove the spinner dome.

NOTE: If the propeller is equipped with a de-icer system, follow the

manufacturer’s instructions for removing whatever components
are necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

DISASSEMBLY 61-10-14
 PROPELLER
HARTZELL MA:N;T4ECNANCE MANUAL

aps6134

legend:
1. piston retaining nut
2. link screw
3. piston
4.5. cylinderpilot tube
6. bushing
7. link arm
8. link pin unit
9. feltseal
10. O-ring
11. feathering spring assembly
12. front spring retainer split rings
13. pilot tube O-ring
14. outer mushroom
15. feathering spacer tube s
17, rear sping retainer
18. rear split retainer
2
19. O-ring 19
20. safety screw
21. washer 18
22. check nut 17
I
23. socket head cap screw

16
15

14-
´•~SI
;´•";"I
23
1211

1
5~ ~CP
13

9
10

321

4P

20
1 8

Models in the Splined-Hub ~2 Series

Figure 306

Page
DISASSEMBLY 61 11 0114 328Mar/98
 PROPELLER MAINTENANCE MANUAL
H~A RT Z E LL 114C

B. Propeller Removal
(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove piston nut (1).

(3) Remove safety wire and link pin safety screws (20).

(4) Remove link pins.

(5) Remove washer (21), check nut (22), and socket head cap screw (23)
from each piston guide rod.
(6) Slide piston (3) off cylinder (4) and pilot tube (5).
(7) Remove and discard dust seal and O-ring from inside diameter of piston.

CAUTION: DO NOT FORCE FEATHERING SPRING TO RELEASE SPLIT

RINGS IN CYLINDER. FORCING SPRING MAY CAUSE RELEASE
OF SPLIT RING RETAINERS IN SPRING ASSEMBLY.

(8) Remove feathering stops. They are held by two screws each.

(9) Remove front spring retainer rings (12) by first pushing the spring
assembly into the cylinder about 1/4 inch, allowing the split rings to fall
out of the groove in the cylinder.

(10) Remove spring assembly from front of cylinder.

(11) Remove hub nut safety pin.
(12) Insert tool TE146 into thecylinder to loosten the hub nut. A puller ring
on the hub nut will engage the cylinder to pull the hub free from the

rear cone and engine splines.

(13) After hub nut is completely loosened, remove propeller from the splined
shaft of the engine.
(14) Place propeller on propeller cart for transportation.
(15) Remove and discard O-ring that was between engine and hub shaft.

(16) Remove rear cone.

(17) Remove spinner bulkhead.

C. Marking Before Disassembly

CAUTLON: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL
TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
data in the
any other serial-numbered parts and compare with the
propeller logbook.

,,,,,,,,B, 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(2) In order to minimize reassembly problems with propeller balance and

blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on parts must be made with crayon or soft, non-graphite

pencil.
Blades should be numbered counterclockwise from the serial
number of the propeller hub las viewed from the front, or piston, side).

(4) Each blade should be reinstalled on the hub spider arm from which it
was removed, where possible. Record on paper each blade serial
number and its matching hub arm and clamp.
D. Propeller Disassembly
Mount propeller on a rotatable fixture of a propeller assembly table.

E. Removing Cylinder
(1) Unscrew the cylinder (4) from the hub by placing a one-inch-wide steel bar into
the slots in the cylinder. There may be some "drag" caused by the O-ring.
(2) Remove and discard O-ring.
F. Clamp and Counterweight Disassembly
NOTE: Item numbers are from Figure 302.

(1) Remove all balance weights and attaching screws, where applicable.
Discard screws.

(2) Use a round bottom metal stamp or electric pencil and identify clamp
serial number on each corresponding counterweight.
(3) Remove and discard all outboard clamp bolts (7) and nuts (8).
(4) Remove and discard all inboard clamp socket screws (5) and cotter
pins (1) or safety wire.

(5) Remove all clamp halves (11) from the hub spider arms.

NOTE: Refer to the Clamp Overhaul Section of Hartzell Manual 202A

(61-01-02), Standard Practices, for information on clamp
inspection and repair.
(6) Remove cotter pin from link screws.

(7) Remove link screw sleeves.

(8) Remove link arms.

(9) Remove and discard clamp gasket (6).

(10) Remove and discard all lubrication fittings and their caps.

(11) Remove and discard the hex head counterweight slug attaching bolts, if
applicable. Remove the counterweight slugs, if applicable.

61 -1 0-1 4
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

(12) Remove and discard the socket head counterweight mounting cap
screws (9) attaching counterweight (10) to clamp (11).

NOTE: Remove roll pin (3A) by punching inboard and prying out.

(13) Remove counterweight (10) from clamp by twisting to free dowel pin (2)
from the clamp.

NOTE: Counterweight (10) is attached to clamp (11) by a dowel

pin (2), which remains with the counterweight.

Remove stop plate mounting fasteners (two per stop plate) and remove
(14)
stop plate from clamps.
(15) Remove each blade assembly from the hub.

G. Blade Mounting Parts Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

H. Start Lock Disassembly

(1) Remove cotter pin from bracket.

WARNING SPRING IS COMPRESSED AND WILL BE RELEASED WHEN THE

COTTER PIN IS REMOVED.

(2) Remove washer from bracket.

(3) Remove spring from bracket.

(4) Remove pin from bracket.

I. Disassembling the Feathering Spring Assembly

WARNING: THE FEATHERING SPRING ASSEMBLY IS PRELOADED TO

APPROXIMATELY 400 POUNDS FORCE. USE EXTREME
CAUTION WHEN REMOVING IT FROM THE PROPELLER AND
WHEN DISASSEMBLING IT.

(1) Use the bench-top fixture TE59 to compress the spring for disassembly.

(2) Remove and discard the split rear retainer.

expand to its unloaded length and

(3) Allow the feathering spring assembly to

remove it from the special fixture.

(4) Disassemble remaining spring assembly component parts.

J. Hub Unit Disassembly
Follow the procedure in the Steel Hub Overhaul section of Hartzell Standard
Practices manual 202A (61-01-02) for pilot tube removal.

61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1140

8. Disassemblv of Flanaed-Hub Models in the -3 Series

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
bulkhead.

(2) Remove the spinner dome.

NOTE: If the propeller is equipped with a de-icer system, follow the

manufacturer’s instructions for removing whatever components
are necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

B. Propeller Removal

(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove and discard the Truarc snap ring that retains the carbon block

assembly to the beta linkage.

Disassemble lever guide to allow lever to move, facilitating removal of
(3)
carbon block from beta ring.

(4) Use special tool TE100 to compress beta system. This will move the
beta ring toward the propeller and allow access to the propeller
mounting bolts.
(5) Remove and discard the bolts or nuts from the flange of the hub.

(6) Remove the propeller from the crankshaft of the aircraft engine.

(7) Remove and discard the propeller mounting O-ring.

(8) Remove spacer from engine flange as applicable.
(9) Remove O-ring from 1.D. of spacer if spacer is installed.

(10) Remove the bulkhead from the hub flange.

(11) Place propeller on propeller cart for transportation.

olsAssEnnsLv 61110-14
 PROPELLER MAINTENANCE MANUAL
H~A RTZ LL 114C

C. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL TO
THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and

any other serial-numbered parts and compare with the data in the
propeller logbook.
(2) In order to minimize reassembly problems with propeller balance and
blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on parts must be made with crayon or soft, non-graphite
pencil. Blades should be numbered counterclockwise from the serial
number of the propeller hub las viewed from the front, or piston, side).

(4) Each blade should be reinstalled on the hub spider arm from which it
was removed, where possible. Record on paper each blade serial
number and its matching hub arm and clamp.

DISASSEMBLY
61-10-14
 PROPELLER
HARTZ E LL MA:N:4ECNANCE MANUAL

aps 6135

CARBON RLOC~ ASSY

2.legend:link
1. piston retaining
screw
nut
21

3. piston 22
4. cylinder
6. bushing
7. link arm
8. link arm mounting pin
9. felt seal

20.
..91gnir-O 01sgnir
11. feathering spring assembly
12. front spring retainer split
O-ring
hub 23
21. low stop collar
22. nut
23. rod
24. safety screw

/‘"A

19 20
12

36
f

s I 24

Models in the -3 Series

Figure 307

Page
DISASSEMBLY 61 -10-14 3 4Mar/98
 PROPELLER MAINTENANCE MANUAL
H~RTZELL 114C

CAUTION: BE SURE THE PROPELLER IS IN FEATHERED POSITION

BEFORE BEGINNING DISASSEMBLY PROCEDURES.

D. Spinner Bulkhead and Piston Disassembly

See Figure 307.

CAUTIONr MAKE NOTE OF THE DE-ICE SLIP RING MOUNTING

HARDWARE ORIENTATION. REPLACEMENT SPACER
WASHERS AND SPECIAL "BELLVILLE" WASHERS IN THE DE-
ICER SYSTEM MUST BE INSTALLED PRECISELY IN REVERSE
SEQUENCE AT REASSEMBLY.

(1) Mount the propeller assembly on the rotatable fixture of a propeller assembly
table.

(2) If thepropeller is equipped with a de-icer system, follow instructions in

the appropriate manufacturer’s manual for removal of the slip ring and
other de-icer system components.

Loosen the jam nuts (22) that the beta rods (23) to the low stop
(3) secure

collar (21).

CAUTION: DURING REMOVAL OF BETA RODS, BE CAREFUL NOT TO

COCK THE BETA RING AND DAMAGE THE THREADS. TURN
RODS OUT OF BETA RING TWO TURNS AT A TIME.

(4) Unscrew the beta rods from the beta ring, two turns at a time, and
remove the beta ring.

(5) Remove and discard all fasteners that attach the bulkhead to the spinner
support plate.
(6) Remove and discard the jam nuts (22) on the ends of the beta
rods (23).
(7) Remove and discard the piston retaining nut (1).
Rotate blades by hand from feather to reverse. Do not use blade
(8)
paddle.
(9) Remove and discard all link pin units (8) and safety screws.

(10) Disconnect the link arms (7) from the piston unit (3).

(11) Remove the piston unit (3).

(12) Remove and discard the piston O-ring (10) and the felt dust seal (9).

(13) Remove and discard pitch change rod O-ring.

OISPISSEMBLY
61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

E. Feathering Spring Disassembly

See Figure 307.

CAUTION: DO NOT FORCE THE FEATHER SPRING TO RELEASE THE

SPLIT RINGS IN THE CYLINDER. FORCING THE SPRING MAY
CAUSE THE RELEASE OF THE SPLIT RING RETAINERS IN
THE SPRING ASSEMBLY, RESULTING IN THE EXPLOSIVE
RELEASE OF THE SPRINGS.

(1) Remove feathering stops (not shown). Stops are retained with two screws

each.

(2) Remove front spring retainer split rings (12) by first pushing the spring
assembly into the cylinder about 1/4 inch, allowing split rings to fall out of
groove in piston.

(3) Remove feathering spring assembly from cylinder.

F. Cylinder and Guide Collar Unit Disassembly
See Figure 307.

(1) Loosen the Nylock socket head cap screws in the guide collar unit so

the guide collar can be shifted.

WARNING~ CYLINDER IS RETAINING BETA SPRINGS UNDER LOAD.

CYLINDER AND GUIDE COLLAR WILL "POP UP" VERY
ABRUPTLY WHEN DISENGAGED FROM HUB.

CAUTION: UNSCREW THE CYLINDER SLOWLY AND CAREFULLY TO

AVOID DAMAGING THE THREADS OR BENDING THE BETA
RODS.

(2) Unscrew the cylinder (4) from the hub by placing a steel bar i-inch wide into
the slots in the cylinder. There may be some "drag" caused by the O-ring (19).

(3) Remove and discard cylinder O-ring (19).

(4) Remove guide collar.

(5) Remove beta springs.

(6) Remove the propeller beta rods (23) from the spinner support plate.

DISASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

G. Clamp and Counterweight Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

H. Blade and Flange Mounting Parts Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

I. Disassembling the Feathering Spring Assembly

WARNING: THE FEATHERING SPRING ASSEMBLY IS PRELOADED UP TO

1000 POUNDS FORCE. USE EXTREME CAUTION WHEN
REMOVING IT FROM THE PROPELLER AND WHEN
DISASSEMBLING IT.

(1) Use the benchtop fixture TE59 to compress the spring for disassembly
(Figure 305).
(2) Remove and discard the split rear retainer.

(3) Allow thefeathering spring assembly to expand to its unloaded length,

and remove it from the special fixture.

(4) Disassemble remaining spring assembly component parts.

J. Hub Spider Unit Disassembly
(1) Remove and discard the fasteners that attach the spinner support plate
to the hub unit.

(2) Remove the spinner support plate.

(3) Remove and discard the Truarc snap rings that hold the guide lugs.

(4) Remove and discard the guide lugs.

(5) Follow the procedure in the Steel Hub Overhaul section of Hartzell
Standard Practices manual 202A (61-01-02) for pilot tube removal.

61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

9. Disassemblv of Splined-Hub Models in the -3 Series

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
bulkhead.

(2) Remove the spinner dome.

NOTE: If the propeller is equipped with a de-icer system, follow the

manufacturer’s instructions for removing whatever components are

necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

B. Propeller Removal
See Figure 307.

(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove and discard the Truarc snap ring that retains the carbon block
assembly to the beta linkage.
(3) Disassemble lever guide to allow lever to move, facilitating removal of carbon
block from beta ring.
(4) Remove and discard piston retaining nut (1).
(5) Rotate blades by hand from feather to reverse. Do not use blade paddle.
(6) Remove and discard all link pin units (8) and safety screws.

(7) Disconnect the link arms (7) from the piston unit (3).
(8) Remove the piston unit (3).
(9) Remove and discard the piston O-ring (13) and felt dust seal (9).

CAUTION: DO NOT FORCE THE FEATHER SPRING TO RELEASE THE

SPLIT RINGS IN THE CYLINDER. FORCING THE SPRING MAY
CAUSE THE RELEASE OF THE SPLIT RING RETAINERS IN THE
SPRING ASSEMBLY, RESULTING IN THE EXPLOSIVE RELEASE
OF THE SPRINGS.

(10) Remove feathering stops (not shown). Stops are retained by two screws each.

OISASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(11) Remove front spring retainer split rings (12) by first pushing the spring
assembly into the cylinder about 1/4 inch, allowing split rings to fall oout of
groove in cylinder.

(12) Remove feathering spring assembly from cylinder.

(1 3) Remove hub nut safety pin.
(14) Insert special tool TE146 into the cylinder and engage the hub nut.

Loosen the hub nut to the end of the engine shaft threads. A puller ring on the
(15)
hub nut will engage the cylinder and pull the hub free from the rear cone and

engine spline shaft.

(16) Remove propeller from the crankshaft of the engine.

(17) Remove and discard the O-ring that was between the engine shaft and

propeller hub.

(18) Remove rear cone.

(10) Remove the bulkhead from the hub flange.

(20) Place propeller on propeller cart for transportation.
C. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL
TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
with the data in the
any other serial-numbered parts and compare
propeller logbook.
(2) In order to minimize reassembly problems with propeller balance and
blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on parts must be made with crayon or soft, non-graphite
Blades should be numbered counterclockwise from the serial
pencil.
number of the propeller hub las viewed from the front, or piston, side).

(4) Each blade should be reinstalied on the hub spider arm from which it
was removed, where possible. Record on paper each blade
serial
number and its matching hub arm and clamp.

olsnsschneLv
61-10-14
 PROPELLER
HARTZELL M*:N:4ECNPINCE MINUAL

CAUTION: BE SURE THE PROPELLER IS IN FEATHERED POSITION

BEFORE BEGINNING DISASSEMBLY PROCEDURES.

D. Spinner Bulkhead and Piston Disassembly

See Figure 307.

CAUTION: MAKE NOTE OF THE DE-ICE SLIP RING MOUNTING

HARDWARE ORIENTATION. REPLACEMENT SPACER
WASHERS AND SPECIAL "BELLVILLE" WASHERS IN THE
DE-ICER SYSTEM MUST BE INSTALLED PRECISELY IN
REVERSE SEQUENCE AT REASSEMBLY.

(1) Mount the propeller assembly on the rotatable fixture of a propeller assembly
table.

(2) If thepropeller is equipped with a de-icer system, follow instructions in

the appropriate manufacturer’s manual for removal of the slip ring and
other de-icer system components.

(3) Loosen the jam nuts (22) that secure the beta rods (23) to the low stop
collar (21).

CAUTION: DURING REMOVAL OF BETA RODS, BE CAREFUL NOT TO

COCK THE BETA RING AND DAMAGE THE THREADS. TURN
RODS OUT OF BETA RING TWO TURNS AT A TIME.

(4) Unscrew the beta rods from the beta ring, two turns at a time, and
remove the beta ring.

(5) Remove and discard all fasteners that attach the bulkhead to the spinner
support plate.
(6) Remove and discard the jam nuts (22) on the ends of the beta
rods (23).

E. Cylinder and Guide Collar Unit Disassembly

See Figure 307.

(1) Loosen the Nylock socket head cap screws in the guide collar unit so the guide
collar can be shifted.

WARNING: CYLINDER IS RETAINING BETA SPRINGS UNDER LOAD.

CYLINDER AND GUIDE COLLAR WILL "POP UP" VERY
ABRUPTLY WHEN DISENGAGED FROM HUB.

CAUTION: UNSCREW THE CYLINDER SLOWLY AND CAREFULLY TO

AVOID DAMAGING THE THREADS OR BENDING THE BETA
RODS.

(2) Unscrew the cylinder (4) from the hub by placing a one-inch-wide steel bar into
the slots in the cylinder. There may be some "drag" caused by the O-ring (19).

DIS~SSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(3) Remove and discard cylinder O-ring (19).

(4) Remove guide collar.

(5) Remove beta springs.

(6) Remove the propeller beta rods (23) from the spinner support plate.
F. Clamp and Counterweight Disassembly
Procedure is the same as for flanged-hub models in the -1 and -6 series.

G. Blade Mounting Parts Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

H. Disassembling the Feathering Spring Assembly

WARNING: THE FEATHERING SPRING ASSEMBLY IS PRELOADED UP TO

1000 POUNDS FORCE. USE EXTREME CAUTION WHEN
REMOVING IT FROM THE PROPELLER AND WHEN
DISASSEMBLING IT.

(1) Use the benchtop fixture TE59 to compress the spring for disassembly
(Figure 305).
(2) Remove and discard the split rear retainer.

(3) Allow the feathering spring assembly to expand to its unloaded length,
and remove it from the special fixture.

(4) Disassemble remaining spring assembly component parts.

I. Hub Spider Unit Disassembly
(1) Remove and discard the fasteners that attach the spinner support plate
to the hub unit.

(2) Remove the spinner support plate.

(3) Remove and discard the Truarc snap rings that hold the guide lugs.
(4) Remove and discard the guide lugs.
(5) Follow the procedure in the Steel Hub Overhaul section of Hartzell
Standard Practices manual 202A (61-01-02) for pilot tube removal.

DISASSEMBLY 61-10-14
 PROPELLER
HARTZELL M*:N~PINCE M*NUAL

10.Disassemblv of Flanaed-Hub Models in the -4 Series

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
engine-side bulkhead unit.

(2) Remove the spinner dome.

NOTE: If the propeller is

equipped with a de-icer system, follow the
manufacturer’s instructions for removing whatever components
are necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

B. Propeller Removal

(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove and discard the bolts from the flange of the hub.

(3) Remove the propeller from the crankshaft of the aircraft engine.
(4) Remove and discard the propeller mounting O-ring.
(5) Remove the rear bulkhead from the hub flange.

NOTE: If the propeller is equipped with

de-icer system, follow the
a

manufacturer’s instructions for removing the slip ring and other

components.
(8) Place propeller on propeller cart for transportation.

DISISSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

C. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL TO
THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
with the data in the
any other serial-numbered parts and compare
propeller logbook.
(2) In order to minimize reassembly problems with propeller balance and
blade angle setting, keep parts with their respective assemblies and
note

the locations of these parts.

(3) All marks made on parts must be made with crayon or soft, non-graphite
serial
pencil. Blades should be numbered counterclockwise from the
number of the propeller hub las viewed from the front, or piston, side).

Each blade should be reinstalled on the hub spider arm from which it
(4)
was removed, where possible. Record on paper each blade serial
number and its matching hub arm and clamp.

DISASSEMBLY 61 11 011 4
 PROPELLER M*NU~L
HARTZELL

aps 6136

legend:
1. piston retaining nut
2. link screw
3. piston
4. cylinder
6. bushing
7. link arm
9. felt seal
10. O-ring
11. O-ring
12. hub i2
13. guide rod
H
14. socket head cap screw, washer,
and check nut
15. safety screw
16. link pin unit

14
3\ I

c~ ’aYrl,~ 67
8
10

4D

15
16

Models in the -4 Series

Figure 308

o,,,,,,,,,, 61 -1 0-1 4
 PROPELLER MAINTENANCE MANUAL
H~ RTr E LL 114C

D. Removing Piston

NOTE: Item numbers are from Figure 308.

(1) Mount the propeller assembly on the rotatable fixture of a propeller

assembly table.

(2) Slide piston (3) forward.

(3) Remove and discard link pin unit (16) and safety screw (15) at each link arm

location.

(4) Disengage link arm (7) from the piston (3).

(5) Remove washer (14), check nut (14), and socket head cap screw (14) from
the end of each piston guide rod.
(6) Slide piston (3) off cylinder (4).
(7) Remove and discard dust seal and O-ring from inside diameter of piston.
E. Removing Cylinder
(1) Loosen the socket head cap screw in the guide collar to facilitate guide
collar removal.

(2) Unscrew the cylinder (4) from the hub by placing a one-inch-wide steel
bar into the slots in the cylinder. There may be some "drag" caused by
the O-ring (11).
(3) Remove guide collar along with the cylinder.
(4) Remove and discard O-ring (11).
F. Clamp and Counterweight Disassembly

NOTE: Item numbers are from Figure 302.

(1) Remove cotter pin from link screw in each counterweight.

(2) Remove bushing and link arm from link screw in each counterweight.
(3) Remove all balance weights and attaching screws, where applicable.
Discard screws.

(4) Use round bottom metal stamp or electric pencil and

a identify clamp
serial number on each corresponding counterweight.

(5) Remove and discard all outboard clamp bolts (7) and nuts (8).
(6) Remove and discard all inboard clamp socket screws (5) and cotter
pins (1) or safety wire.

DISASSEMBLY 61’10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(7) Remove all clamp halves (11) from the hub spider arms.

NOTE: Refer to the Clamp Overhaul Section of Hartzell Manual 202A

(61-01-02), Standard Practices, for information on clamp
inspection and repair.
(8) Remove and discard clamp gasket (6).
(9) Remove and discard all lubrication fittings and their caps.

(10) Remove and discard the twelve-point counterweight mounting bolts (9)
attaching counterweight (10) to clamp (11).
(11) Remove counterweight (10) from clamp.
(12) Remove each blade assembly from the hub.

G. Blade Mounting Parts Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

DlsAssEl\neLv 61 -1 0’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

11.Disassemblv of HC-A2~MV,V)20-4A1

A. Spinner Disassembly
(1) Remove and discard the fasteners that attach the spinner dome to the
bulkhead unit.

(2) Remove the spinner dome.

NOTE: If the propeller is equipped with de-icer system, follow the

a

manufacturer’s instructions for removing whatever components are

necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

B. Propeller Removal

(1) Support propeller assembly using a suitable sling and mobile hoist.

(2) Remove nuts from ends of piston-mounted push rods.

(3) Pull piston forward to allow push rods to exit guide collar.

(4) Rotate piston to move forks away from clamps and link screws.

(5) Remove blocks from forks and remove piston from cylinder. Sleeves, spacers,
and forks will remain on piston push rods at this time.

(6) Remove and discard O-ring from inside diameter of piston.

(7) Remove and discard dust seal from O.D. of cylinder.

(8) Remove four cotter pins in shaft nut holding the propeller onto the engine
splined shaft.

(9) Remove the shaft nut seal. This is a ring encircling the shaft nut. It
metal has

in its inside diameter and an O-ring in a groove on its

an O-ring groove a on

outside diameter.

(10) Remove and discard both O-rings from the shaft nut seal.

(11) Remove safety wire from shaft nut tube and engine shaft.

(12) Insert special tool TE146 into the cylinder to engage the shaft nut.

(1 3) Loosen shaft nut to the end of the engine threads. A puller ring on the shaft nut
and hub loose from the cone and splined engine shaft.
will pull the cylinder rear

DISPISSEMBLY
61-10-14
 PROPELLER NIANUAL
HARTZELL

(14) Remove propeller from engine shaft.

(15) Remove spinner bulkhead from guide collar unit.

(16) Remove rear cone from engine shaft.

(17) Place propeller on propeller cart for transportation.

C. Oil Transfer Unit Removal

(1) Remove hydraulic line to oil transfer unit.

(2) Remove four hex head bolts holding oil transfer unit to the engine.
(3) Remove oil transfer unit and gasket between oil transfer unit and engine.
D. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL
TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
any other serial-numbered parts and compare with the data in the
propeller logbook.
(2) In order to minimize reassembly problems with propeller balance and
blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on parts must be made with

crayon or soft, non-graphite
pencil. Blades should be numbered counterclockwise from the serial
number of the propeller hub las viewed from the front, or piston, side).

(4) Each blade must be reinstalled on the hub spider arm from which it was
removed, where possible. Record on paper each blade serial number
and its matching hub arm and clamp.
E. Piston Disassembly
(1) Loosen set screw in forks.

(2) Remove forks, sleeves, and spacers from piston push rods.

(3) Remove and discard O-ring inside piston.

F. Removing Cylinder
(1) Unscrew the cylinder from the hub by placing a one-inch-wide steel bar into the
slots in the cylinder. There may be some "drag" caused by the O-ring.
(2) Remove and discard O-ring.
(3) Remove shaft nut and puller ring.

,,,,ss,,,,, 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

G. Clamp and Counterweight Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

H. Blade Mounting Parts Disassembly

Procedure is the same as for flanged-hub models in the -1 and -6 series.

I. Hub Unit Disassembly

Procedure is the same as for models in the -1 and -6 series, except that
flanged-hub
guide collar is clamped with hex head bolts instead of socket head cap screws.

J. OilTransfer Unit Disassembly

NOTE: The the (3030) and the spring pin (3040) were
rear cone removed when the

propeller was removed from the engine.

(1) Remove and discard the gasket (5020).

CAUTION: WHEN REMOVING THE BACKUP RING (3010) AND LIP SEAL RING
(3020), DO NOT DAMAGE THE SLIP RING CAP (4050).
(2) Remove and discard the back up ring (3010) and the lip seal ring (3020).

(3) Remove the oil line elbow (5010) from the slip ring cap (4050).

(4) Remove and discard the ring retainer (5000) that holds the oil transfer plug (4090)
in place.
(5) Remove the oil transfer plug (4090) from the slip ring cap (4050).

(6) Remove the pipe plug (4020) from the slip ring cap (4050).

(7) Remove the spring (4030) from the slip ring cap (4050).

(8) Remove the transfer seal button (4040) from the slip ring cap (4050j.

(9) Remove the rear cone (3030) from the slip ring (3080).

(10) Remove and discard the gasket (3050) from the rear cone (3030).

(1 1) Remove the oil stinger (3060) from the slip ring cap (4050).

(12) Remove the slip ring (3080) and oil seal rings (3070,3090) from the slip ring
sleeve (4000).

CAUTION: DO NOT STRETCH OR BEND THE OIL SEAL RINGS WHILE

REMOVING FROM THE SLIP RING (3080) GROOVE, THE OIL SEAL
RINGS ARE VE RY BRITTLE AND WILL BREAK EASI LY.

(13) Remove the oil seal rings (3070, 3090) from the slip ring (3080).
(14) Remove the slip ring sleeve (4000) from the slip ring cap (4050).

(15) Remove and discard the O-ring (4010) from the slip ring sleeve (4000).
(16) Remove and discard the O-ring (4010) from the slip ring cap (4050).

DISASSEMBLY
61’10’14
 PROPELLER MAINTENANCE MANUAL
HP~ RT~ c L L 114e

12.Disassemblv of Fianced-Hub Models in the -5(A,AL) Series

WARNING: HARTZELL FEATHERING PROPELLERS MUST BE IN THE FEATHER

POSITION BEFORE ATTEMPTING REMOVAL OF PROPELLER FROM
AIRCRAFT. I F THE PROPELLER IS NOT CONTROLLED DU RING
FEATHERING PROCEDU RES, PERSONAL INJU RY MAY OCCUR AND
DAMAGE TO THE PROPELLER PISTON WILL OCCUR.

CONTROL PROPELLER WITH BLADE PADDLE WHEN FEATHERING

PROPELLER MANUALLY.

MOVE BLADE ENOUGH TO RELEASE PRESSURE ON HIGH STOP

PIN, DEPRESS PIN, THEN SLOWLY RELEASE BLADE PRESSURE TO
ALLOW STOP PLATE TO PASS THE PIN.

ON THE LAST BLADE, WHEN RELEASING THE STOP PIN, BE

CAREFUL TO CONTROL THE PROPELLER AS IT WILL BE READY TO
FEATHER.

A. Spinner Disassembly
(1) Remove and discard the screws and fiber washers that attach the spinner
dome to the engine-side bulkhead unit.

(2) Remove the spinner dome.

NOTE: If the propeller is equipped with a de-icer system, follow the

manufacturer’s instructions for removing whatever components
are necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY THAT
ARE NOT CONTAINED IN THIS MANUAL OR THE HARTZELL
OWNER’S MANUAL.

B. Propeller Removal

CAUTION: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

(1) Support propeller assembly using a suitable sling and mobile hoist.
(2) Remove the safety wire from the propeller mounting bolts.

(3) Remove and discard propeller mounting bolts and carefully remove the
propeller assembly from the aircraft engine.
(4) Remove and discard the propeller mounting O-ring.
(5) Place propeller on propeller cart for transportation.

DISASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 114C

C. Beta Valve Removal

(1) Remove staking pin.

(2) Slide beta valve assembly out of engine.
(3) Remove three O-rings from outside diameter of valve.

D. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL
TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
the data in the
any other serial-numbered parts and compare with
propeller logbook.
(2) In order to minimize reassembly problems with propeller balance and
blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on parts must be made with crayon or soft, non-graphite
Blades should be numbered counterclockwise from the serial
pencil.
number of the propeller hub las viewed from the front, or piston, side).

(4) Each blade should be reinstalled on the hub spider arm from which it
was removed, where possible. Record on paper each blade
serial
number and its matching hub arm and clamp.

E. Spinner Bulkhead Removal

(1) Mount propeller assembly on the rotatable fixture of a propeller assembly table.

(2) Remove bolts holding spinner bulkhead to start locks.

(3) Remove bulkhead.

F. Start Lock Removal

Remove the start locks from the hub flange. Two hex head bolts secure each start

lock.

,,,,,,,,Y 61-10-14
 PROPELLER
HA RTZ E LL MAI1N~EcNANCE
C411LAUNAM

///I

9
38
2810 15 14

~1 12

1C~29
30

C;e\t
16
,/32\
B
i,i
~Q.

18 1
17

-6’i j 23
24 25

21 22 27
legend:
~o
1. flexlock nut
22. guide collar
2. piston 12. link arm
23. socket head cap screw
3. link pin unit 13. spring assembly 24. o-ring
4. safety screw 14. hex head bolt
25. hub
5. check nut and washer 15. o-ring 26, link screw
6. socket head cap screw 16. clamp 27. cotter pin
7. guide rod 17. bushing 28. pin
8. plastic bushing 18. head hex bolt, plate 29. hex head bolt
9. o-ring 19. stop plate 30. washer
10. felt dust seal 20. cylinder 31. auto
11, link screw high pitch stop unit
bushing 21. staking pin 32. kaylock nut

Models in the -5(A,AL) Series

Figure 309

DISASSEMBLY 61110114
 PROPELLER MAINTENANCE MANUAL
H~ RT r LL 114C

G. Piston Disassembly
(1) Remove piston nut.

(2) Remove and discard link pin unit (3) and safety screw (4).

(3) Remove washer, check nut, and socket head cap screw from the end of each

piston guide rod.

(4) Slide piston unit off the cylinder and remove.

(5) Remove and discard O-ring and felt seal from the inside diameter of the piston.
H. Feathering Spring Disassembly

NOTE: Item numbers are from Figure 309.

WARNING: THE FEATHERING SPRING ASSEMBLY IS PRELOADED TO

APPROXIMATELY 1000 POUNDS FORCE. USE EXTREME
CAUTION WHEN REMOVING IT FROM THE PROPELLER.

(1) Remove and discard the feather stops (14) and safety wire, where
applicable.
(2) Remove the screws in front retainer that retain the ring retention plate.

(3) Remove front spring retainer split rings by first pushing the spring assembly
into the cylinder about 1/4 inch, allowing split rings to fall out of the groove in
the cylinder.

(4) Remove the feathering spring assembly (13) and use benchtop fixture
TE59 to compress the spring for disassembly.

(5) Remove and discard the split rear retainer.

(6) Allow the feathering spring assembly to expand to its unloaded length,
and remove it from the special fixture.

(7) Disassemble the remaining spring assembly components.

i. Cylinder and Guide Collar Unit Disassembly

CAUTION: UNSCREW THE CYLINDER SLOWLY AND CAREFULLY TO

AVOID DAMAGE TO THE THREADS.

Loosen the Nylock socket head cap screw (23) inside the guide collar
(1)
unit (22), so the guide collar can be shifted.

oISASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

J. Clamp and Counterweight Disassembly

NOTE: Item numbers are from Figure 302.

(1) Remove all balance weights and attaching screws, where applicable.
Discard screws.

(2) Use a round bottom metal stamp or electric

pencil and identify clamp
serial number on each corresponding counterweight.
(3) Remove and discard all outboard clamp bolts (7) and nuts (8).
(4) Remove and discard all inboard clamp socket screws (5) and cotter
pins (1) or safety wire.

(5) Remove all clamp halves (11) from the hub spider arms.

NOTE: Refer to the Clamp Overhaul Section of Hartzell Manual 202A

(61-01-02), Standard Practices, for information on clamp
inspection and repair.
(6) Remove cotter pins in link screw.

(7) Remove link screw sleeves.

(8) Remove link arms.

(9) Remove and discard clamp gasket (6).

(10) Remove and discard all lubrication fittings and their caps.

(11) Remove and discard the hex head counterweight slug attaching bolts, if
applicable. Remove the counterweight slugs, if applicable.
(12) Remove and discard the socket head counterweight mounting cap
screws (9) attaching counterweight (10) to clamp (11).

NOTE: Remove roll pin (3A) by punching inboard and prying out.

(13) Remove counterweight (10) from clamp by twisting to free dowel pin (2)
from the clamp.

NOTE: Counterweight (10) is attached to clamp (11) by a dowel

pin (2), which remains with the counterweight.
(14) Remove stop plate mounting fasteners (two per stop plate) and remove the
stop plate from each clamp.
(15) Remove each blade assembly from the hub.

K. Blade Mounting Parts Disassembly

Procedure is the same as for models in the -1 and -6 series.

DISASIEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

L. Hub Spider Unit Disassembly

Follow the procedure in the Steel Hub Overhaul section of Hartzell Standard
Practices Manual 202A (61-01-02) for pilot tube removal.

M. Start Lock Disassembly

WARNING: SPRING IS COMPRESSED AND WILL ATTEMPT TO

FORCEFULLY LEAVE THE START LOCK HOUSING WHEN THE
COTTER PIN IS REMOVED.

(1) Remove cotter pin from bracket.

(2) Remove washer from bracket.

(3) Remove spring from bracket.

(4) Remove pin from bracket.

DISPISSEMBLY
61-10114
 PROPELLER
HA RTZ E L L C411LAUNAM

legend:
aps 6137
1, rod end ring 21. bushing 37. nut
2. pitch adjust nut 22. clamp 38. high pitch stop
3. flexlock nut 23. jam nut 39. bolt
4. piston 24. low stop collar 40. washer
5. link pin unit 25. hub 41. nut
6. safety screw 27. o-ring 42. hex-head bolt
7. spring 28. socket head capscrew 43. nut
8. o-ring 29. guide collar 44. washer
9. felt dust seal 30. staking pin 45. plate screw
10. link screw bushing 31. cylinder 46. split retainer ring
11. link arm 32. washer 47. retention plate
12. retainer ring 33. link screw 48. carbon block assembly
13. beta spring 34. cotter pin 49. hex head bolt
14. beta rod 35. hex head bolt 50. spinner support plate
15. beta rod retainer 36. stop plate
16. check nut
17. elastic nut
18. hex head bolts
19. o-ring
;1"~rZ
9j
20. spring assembly 8

;ori19 18
f
46
20

1o
44
,e, 11
pc-42
\"‘´•´•\cB´•/s
3x
’i:
~P
17

49

s~39
21 35
36
o´•
1P\
37 38

23 -----L-e

1,
2928
253 i´•32 34
7

i,, 512C
Models in the -5R Series
Figure 310

DISASSEMBLY 61 -1 0-1 4
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 114C

13.Disassemblv of Flanaed-Hub Models in the -5R Series

WARNING: FOR SAFETY REASONS, PLACE THE PROPELLER IN THE

FEATHER POSITION BEFORE IT IS REMOVED FROM THE
AIRCRAFT.

A. Spinner Disassembly
Remove and discard the fasteners that attach the spinner dome to the
(1)
bulkhead.

(2) Remove the spinner dome.

NOTE: If the propeller is equipped with a de-icer system, follow the

manufacturer’s instructions for removing whatever components
are necessary for propeller removal.

WARNING: DURING PROPELLER REMOVAL, AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST BE FOLLOWED BECAUSE
THEY MAY CONTAIN ISSUES VITAL TO AIRCRAFT SAFETY
THAT ARE NOT CONTAINED IN THIS MANUAL OR THE
HARTZELL OWNER’S MANUAL.

B. Beta Control Unit Removal

NOTE: Item numbers are in Figure 310.

Disconnect the engine beta linkage and carbon block assembly from the
(1)
beta ring (24).
(2) Use special tool TE100 to compress the beta system and pull the beta
ring forward to expose the propeller mounting bolts and washers.

C. Propeller Removal

CAUTI_ON: USE ADEQUATE PRECAUTION TO PROTECT THE PROPELLER

ASSEMBLY FROM DAMAGE WHEN IT IS REMOVED FROM THE
AIRCRAFT ENGINE AND WHEN IT IS STORED.

(1) Support propeller assembly using a suitable sling and mobile hoist.

Remove the safety wire from the propeller mounting bolts.

(2)
(3) Remove and discard propeller mounting nuts.

(4) Carefully remove the propeller assembly from the aircraft engine.

(5) Remove and discard the propeller mounting O-ring.

(6) Remove spacer from engine flange as applicable. Keep spacer on

propeller flange to assist further disassembly.

(7) Place propeller on propeller cart for transportation.
(8) Decompress and remove the special beta system tool.

DlsnssEusLv
61-10-14
 PROPELLER
HARTZ ELL MA:N:4ECNANCE MANUAL

D. Marking Before Disassembly

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY IDENTIFY
PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OF THE PROPELLER.

(1) Record the serial number and model number of the hub, blades, and
any
other serial-numbered parts and
compare with the data in the propeller
logbook.
(2) In order to minimize reassembly problems with propeller balance and
blade angle setting, keep parts with their respective assemblies and note
the locations of these parts.

(3) All marks made on must be made with crayon or soft,

parts non-graphite
I pencil. Blades should be numbered counterclockwise from the
serial number located on the propeller hub las viewed from the
propeller
front, or
piston, side).

I (4) Where possible, each blade should be reinstalled on the hub arm from
which it was removed. Record on paper each blade serial number and
clamp serial number and their matching hub arm serial numbers.
E. Spinner Bulkhead, Start Lock, Beta Rod, and Piston
Disassembly
(1) Mount propeller assembly on the rotatable fixture of a propeller assembly
table.

1 (2) If thepropeller is equipped with a de-ice system, follow instructions in

the appropriate manufacturer’s manual for removal of the
slip ring and
other de-ice system components.

(3) Loosen the jam nuts (23) that secure the beta rods (14) to the beta ring
(24). Then loosen jam nuts (16).
I Steps (4) through (6) apply to model PHC-A3VF-SR, only:
(4) Remove and discard the elastic nuts (17) that retain the propeller beta
rod end ring (1).

(5) Remove the rod end ring (1).

1 (6) Remove and discard the propeller beta rod check nuts (16).
CAUTION: DURING REMOVAL OF BETA RODS, BE CAREFUL NOT TO
COCK THE BETA RING AND DAMAGE THE THREADS. TURN
RODS OUT OF BETA RING TWO TURNS AT A TIME.

CAUTION: DO NOT ALLOW THE PITCH CHANGE ROD TO TURN WHILE

THE NUT IS BEING REMOVED.

DISASsEMBLY 61110114
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Unscrew the beta rods (14) from the beta ring two turns at a time and
(7)
remove the beta ring.
(8) Remove spinner bulkhead and start locks from spinner mounting ring.

(9) Remove and discard the large flexlock nut (3) on the end of the pitch
change rod.
hand from feather to Do not use blade
(10) Rotate blades by reverse.

paddle.
(1 1) Remove and discard all link pin units (5) and safety screws (6).

(12) Disconnect the link arms (11) from the piston unit.
(13) Remove the piston unit (4).
(14) Remove and discard the piston O-ring (8) and the felt dust seal (9).

(15) Remove and discard the pitch change rod O-ring (19).
F. Feathering Spring Disassembly

WARNING: THE FEATHERING SPRING ASSEMBLY IS PRELOADED TO

APPROXIMATELY 1000 POUNDS FORCE. USE EXTREME
CAUTION WHEN REMOVING IT FROM THE PROPELLER.

Remove and discard the feather stops (14) and safety wire, where
(1)
applicable.
(2) Remove screws in front of spring retainer that retain the ring retention plate.

(3) Remove front spring retainer split rings by first pushing the spring assembly
into the cylinder about 1/4 inch, allowing split rings to fall out of the groove in
the cylinder.

(4) Remove the feathering spring assembly (13) and use benchtop fixture
TE59 to compress the spring for disassembly.

(5) Remove and discard the split rear retainer.

(6) Allow the feathering spring assembly to expand to its unloaded length,
and remove it from the special fixture.

(7) Disassemble the remaining spring assembly components.

DISASSEMBLY 61110114
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

G. Cylinder and Guide Collar Unit Disassembly

(1) Loosen the Nylock socket head cap screw (28) in the side of the guide
collar unit so the guide collar (29) can be shifted. See Figure 310.

WARNING: THE CYLINDER IS RETAINING THE BETA SPRINGS UNDER

LOAD. THE CYLINDER (31) AND GUIDE COLLAR (29) WILL
"POP UP" VERY ABRUPTLY WHEN DISENGAGED FROM HUB.

CAUTION: UNSCREW THE CYLINDER (31) SLOWLY AND CAREFULLY

TO AVOID DAMAGING THE THREADS OR BENDING THE
BETA RODS (14).

(2) Use a square-bar of appropriate size, one inch wide to fit into the slot in
the top of the cylinder (31) and serve as a wrench to slowly unscrew the
cylinder from the hub unit. Remove the cylinder (31) from hub (25).
(3) Remove the guide collar unit from the beta rod assemblies.

(4) Remove and discard the cylinder O-ring (27).

(5) Release, remove, and discard the reverse return springs (7).
(6) Remove the propeller beta rods (14) from the spinner support plate (50).
(7) Remove and discard the beta rod retainers (15) and retainer rings (12).
H. Clamp and Counterweight Disassembly

NOTE: Item numbers are from Figure 302.

(1) Remove all balance weights and attaching screws, where applicable.
Discard screws.

(2) Use a round bottom metal stamp or electric pencil and identify clamp
serial number on each corresponding counterweight.
(3) Remove and discard all outboard clamp bolts (7) and nuts (8).
(4) Remove and discard all inboard clamp socket screws (5) and cotter
pins(l) or safety wire.

(5) Remove all clamp halves (11) from the hub spider arms.

NOTE: Refer to the Clamp Overhaul Section of Hartzell Manual 202A

(61-01-02), Standard Practices, for information on clamp
inspection and repair.
(6) Remove cotter pin in link screw.

(7) Remove link screw sleeve.

(8) Remove link arms.

DISAsSEMBLY 61110114 RevPJaugnee~3/s690

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(9) Remove and discard clamp gasket (6).

(10) Remove and discard all lubrication fittings and their caps.

(11) Remove and discard the hex head counterweight slug attaching bolts, if
applicable. Remove the counterweight slugs, if applicable.
(12) Remove and discard the socket head counterweight mounting cap
screws (9) attaching counterweight (10) to clamp (11).

NOTE: Remove roll pin (3A) by punching inboard and prying out.

(13) Remove counterweight (10) from clamp by twisting to free dowel pin (2)
from the clamp. Dowel pin remains with counterweight.

(14) Remove start lock plates (36) from clamps, where applicable.

(15) Discard mounting screws (35).

(16) Inspect plates damage. Retain for reuse if in good
for corrosion or

condition. Where possible, each plate should be reattached during

reassembly to the ssame clamp it was removed from.
(17) Remove each blade assembly from the hub.

I i. Blade Mounting Parts Disassembly

Procedure is the same as for models in the -1 and -6 series.

I J. HubUnitDisassembly
(1) Remove and discard the hex head bolts (49) that fasten the spinner support
plate (50) to the hub spider unit (25).
(2) Remove split spinner support plate.
(3) Remove and discard snap rings on bushings.
(4) Remove and discard guide lugs.
(5) Remove hub from table.

Remove O-ring from spacer I.D. and spacer. Remove O-ring from
(6) remove

spacer O.D.

(7) Remove studs from hub.

NOTE: Studs are held into hub with epoxy.

(8) Follow the procedure in the Steel Hub Overhaul section of Hartzell Standard
Practices manual 202A (61-01-02) for pilot tube removal.

DlsnssEhneLv 61-10-14
 PROPELLER
HARTZELL MPI:N~PINCE YINUPIL

I K. Start Lock Disassembly

WARNING: SPRING IS COMP RESSED AN D WILL ATTEMPT TO FORCE FU LLY

LEAVE THE START LOCK HOUSING WHEN THE COTTER PIN IS
REMOVED.

(1) Remove cotter pin from bracket.

(2) Remove washer from bracket.

(3) Remove spring from bracket.

(4) Remove pin from bracket.

DlsnssEhnE1Lv 61-10114
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

1. General Procedures for Cleaning Parts

Refer to Hartzell Standard Practices Manual 202A (61-01-02).

2. Specific Cleaning Procedures

A. Cleaning Steel Parts for Magnetic Particle and Dye Penetrant Inspection

Refer to Hartzell Standard Practices Manual 202A (61-01-02).

Parts for Cadmium Replating Procedures
B. Cleaning Steel
Refer to Hartzell Standard Practices Manual 202A (61-01-02).

61-10-14
 PROPELLER
HARTZ ELL MA:N1~ECNANCE MANUAL

(This page is intentionally blank.)

Page
CLEANING 61110114 402Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

CONTENTS

503
1. Inspection Interval Requirements
503
2. Inspection Requirements
503
3. Replacement Requirements
503
4. Repair
503
5. Hub Unit Inspection
503
6. Blade Clamp Inspection.......
503
7. Blade Inspection
503
8. Spinner Assembly Inspection
504
9. Cylinder Inspection
504
10. Piston Inspection
505
11. Link Arm Inspection
507
12. Blade Split Bearing Inspection
507
13. Bearing Guide Ring
509
14. Low Stop Rod (Beta Rod) Inspection
511
15. Low Stop Collar (Beta Ring) Inspection
512
16. Pitch Change Rod Inspection
512
17. Feathering Spring Inspection
512
18. Auto High Pitch Stop Unit Inspection
513
19. Guide Collar Inspection
514
20. Spring Retainer Inspection
515
21. Rear Cone

Pin 516
22. Spring
517
23. Oil Slinger
519
24. Oil Seal Rings
520
25. Slip Ring
521
26. Slip Ring Sleeve
522
27. Pipe Plug
523
28. Spring
524
29. Transfer Seal Button
525
30. Bolt

CHECK 61’10’14 RevP5aSAeu~:

 PROPELLER
HA RTZ E LL MA:N;T4ECNANCE MANUAL

31. Washer

32. Slip Ring Cap 527

33. Oil Transfer Plug 528

34. Elbow 529

LIST OF FIGURES

Link Arm Figure 501 505

Blade Split Bearing Figure 502 506

Low Stop Rod (Beta Rod) Figure 503 508

Low Stop Collar (Beta Ring) Figure 504 510

Guide Collar Figure 505

Rear Cone Figure 506 515

Spring Pin Figure 507 516

Oil Slinger Figure 508 517

Oil Seal Rings Figure 509 518

Slip Ring Figure 510 520

Slip Ring Sleeve Figure 511 521

Pipe Plug Figure 512 522

Spring Figure 513 523

Transfer Seal Button Figure 514 524

Slip Ring Cap Figure 515 526

Oil Transfer Plug Figure 516

Elbow

CHECK 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

1. Inspection Interval Reouirements

Refer to the Introduction this manual for information on inspection interval

requirements.

2. Inspection Reauirements

A. Visual Inspection
all parts.
Visually inspect Parts with obvious defects or damage are to be
removed from service.

B. Fluorescent Penetrant Inspection

Follow the proceduresfor penetrant inspection found in Hartzell Manual 202A
(60-01-02), Standard Practices.

C. Magnetic Particle Inspection

Follow the procedures for magnetic particle inspection found in Hartzell Manual
202A (60-01-02), Standard Practices.

D. Dimensional Inspection
Dimensionally inspect parts as specified. When measuring the diameter of a

part, take at least two measurements unless otherwise specified. If any

measurement is outside the specified tolerance, retire the part.

3. Replacement Reauirements

Replace all parts that have cracks, parts with obvious defects or damage found
during visual inspection, or parts that would affect operation or serviceability if
repaired

4. Repair

Repairable part defects are noted in the inspection criteria. Repair procedures are

found in theRepair section of this manual, unless otherwise stated.

5. Hub Unit Inspection

Refer to the Steel Hub Overhaul section of Hartzell Manual 202A (61-01-02),
Standard Practices, for requirements and procedures for inspecting steel hub units.

6. Blade Clamp inspection

Refer to the BladeClamp Overhaul section of Hartzell Manual 202A (61-01-02),

Standard Practices, for requirements and procedures for inspecting clamps.

7. Blade InsPection

Refer to Hartzell Manual 133C (61-13-33) for aluminum blades and Manual 135F
(61-13-35) for composite blades.

3. Spinner Assembly Inspection

Refer to Hartzell Manual 127 (61-16-27), Spinner Assembly Maintenance Guide, for

requirements and procedures for inspecting components of spinner assemblies.

cnEcK 61-10-14 PagMea~

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

9. Cvlinderlnspection

A. Visually inspectthe All threads must be free of None. Retire the cylinder.
condition of all threaded defects, wear, or chafing, or the
surfaces on the cylinder. cylinder must be retired from
service.

B. Visually inspectthe Cylinders with flaking or wear If blemished area is greater than
condition of the chrome through the chrome finish must be 0.005 inch deep,
retire the part. If
finish. removed from service and less than 0.005 inch deep, return
repaired if within corrective action it to the Hartzell Service Center
limits. for evaluation and possible
rechroming.

C. Magneticparticle inspect No cracks are allowed. None. Retire the cylinder.

the
cylinder at each
overhaul.

D. Dimensionally inspect any Any cylinder with scratches or If blemished area is greater than
scratches gouges that
or gouges deeper than 0.001 inch 0.005 inch deep, scrap the part.
appear in the normal must be removed from service If less than 0.005 inch deep,
operating area of the and repaired if within corrective return it to the Hartzell Service
cylinder. action limits. Center for evaluation and
possible rechroming.

10. Pistonlnspection

A. Visually checkfor proper Adequate threads must be Ensure correct safety screw is
fitting of link arms to piston present in piston to hold safety installed. (A short screw in
unit with safety screws. screw in place: at least three combination with worn threads
thread lengths are sufficient. can cause link
pin to disconnect
from piston.) Repair threads in
piston unit by using a slimsert.
See Repair Section.

B. Fluorescentpenetrant No cracks are allowed. None. Retire the piston.

inspect the entire piston.

D. Visually inspectthe hole at No dimensional limits. Damage None. Retire the piston.
the front of the piston for must not interfere with the sealing
damage caused by ability of the O-ring.
inserting or removing the
feathering spring pilot tube.

´•´•E´•´• 61-10-14
 PROPELLER MAINTENANCE MANUAL
~IARTZELL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action
Inspect
11. Link Arm Inspection

link with indications of None. Retire the link arm.

A. Visually inspecteach link Any arm

arm for indications of distortion must be retired from

twisting or distortion. service. Flatness should be less
than 0.015 inch.

link hole link None. Retire the link arm.

B. Visuallyinspectthe linkpin Any pin or screw

hole and the link screw hole hole that has been worn in an

of each link arm. oblong shape is cause for

retirement of the link arm.

No cracks allowed. None. Retire the link arm.

C. Link arms must beinspected are

using the magnetic particle

method at each overhaul.

Refer to Wear Limits Table in Link arms that exceed the

D. Dimensionally inspectthe
section 800. maximum allowed I.D. of the link
I.D. of the link pin hole and
link screw hole of each link pin or link screw holes must be
retired from service.
arm (refer to Figure 501).

Refer to Wear Limits Table in None. Retire the link arm.

E. Dimensionally inspectthe
thickness of the link arm section 800.

(refer to Figure 501).

npsnoa7

Link Pin Hole

Link Screw Hole

Thickness C
NOTE: B-1901 Link Arm shown. Others Similar.

Link Arm
Figure 501

Page
CHECK 61-10-14 505Mar/98
 PROPELLER
HARTZELL MI:N~PINCE M~NU*L

5016.TIF
5017.TIF

Cracks
Chips

:´•i´•:´•!´•:´•i´•:

:´•i´•:´•i´•:´•i* i´•:´•(´•´•l´•

No visible chipping,
cracks, or fretting,
allowed in this area

(dashed-lines)

´•i´•:´•

´•i´•:´•i´•:´•i´•;:i~

Blade Split Bearing

Figure 502

CHECK 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action

Inspect

12. Blade Split Bearing Inspection

All indications of fretting must be Remove fretting indications with

A. Visually inspectthe outer
diameter of all bearing removed. a Scotch BriteTM pad.
races for indications of
fretting damage.

B. Visually inspectthe ball If indications of fretting are None. Retire the bearing races.

track of each bearing race present the races must be retired

for indications of fretting from service.

(refer to Figure 502).

C. Visually inspectthe split If chips or cracks are present the None. Retire the bearing races.

lines of all bearing races for races must be retired from

chipping or cracks (refer to service.

Figure 502).

D. Dimensionally inspectthe The races must be retired from None. Retire the bearing races.

depth of pitting or damage service if pits or damage exceed

in the ball track of each 0.002 inch deep.
bearing race.

E. Bladesplitbearing races No cracks are allowed. None. Retire the bearing races.

must be inspected using

the magnetic particle
method at each overhaul.

13. Bearing Guide Ring

No cracks allowed. None. Retire the ring.

A Magnetic particle inspect are

and re-cad plate.

Page
CHECK 61-10-14 507Mar/98
 PROPELLER
HARTZELL MPI:N1~ECNANCE M*NUAL

OBETAROD.TIF NBETAROD.TIF

Threaded
Area

Machined
Retaining Retaining
0.125 1 I Ring Rings
Inch

1/32 Inch Radius Typ.

Retainer

0.370 Inch Minimum O.D.

Threaded
Area

B-3002-() B-3476(A)-()

Low Stop Rod (Beta Rod)

Figure 503

CHECK 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action

Inspect

14. Low Stoo Rod (Beta Rod)

inspection

A"Y rod with indications of None. Retire the low stop rod.
A. Visuallyinspecteach rod
distortion must be retired from
for indications of bending or

distortion, service.

Damage that wears through the None. Retire the low stop rod.
B. Visuallyinspecteach rod
chrome surface is cause for
for damage that penetrates
the chrome finish.
retirement of the rod.

Damage or wear exceeding 10" None. Retire the low stop rod.
C. Visually inspectthe
of circumference is cause for
condition of the threaded
of each rod. retirement of the rod.
areas

Damage, deformation, or wear to None. Retire the low stop rod.

D. Visuallyand dimensionally
the ring exceeding 0.010 inch is
inspect the machined
cause for retirement of the rod.
retaining ring on older style
[B-3002-( )1 rods. See
Figure 503.

removed
NOTE: Newer rods incorporate a pressed-on retainer and retaining rings which are
style
manual for installation
and discarded at overhaul. Refer to the Assembly section of this
procedures.

No cracks are allowed. None. Retire the low stop rod.

E. Each rodmustbe
inspected using the
magnetic particle method at
each overhaul.

Refer to Figure 503 for applicable None. Retire the low stop rod.
F. Dimensionally inspectthe
limits.
O.D, of each rod.

Page
CHECK 61-10-14 509Mar/98
 PROPELLER
HA RTZ E LL MA:N:4ECNANCE MANUAL

BETACOLR
COLRDETA

a´•´•´•~ I

F --t----t~l B

View A

Surface D
G (0.083 inch minimum)
1
_I
Surface
1_-f
Surface p~lfrJDn
T
G (0.073 inch minimum)

Surface C

Low Stop Collar (Beta Ring)

Figure 504

CHECK 61110114
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

15. Low Stop Collar (Beta Rina~

Inspection

A. Visually inspectthecollar No cracks are allowed. None. Retire the low stop collar.
for cracks.

of The maximum depth of None. Retire the low stop collar.

B. Visually inspect bottom
threaded holes for impressions in this area is 0.004
indications of
impressions inch.
or dimples made by the low

stop rods.

C. Dimensionally inspectany The maximum depth of scratches None. Retire the low stop collar.
scratches on the collar. is 0.004 inch.

D. Dimensionally inspectany Depressions in the groove less Refer to the Repair chapter of
depressions or gouges in than 0.007 inch must be this manual if the damage is
the groove of the collar. removed. Depressions in the within the allowable limits. Retire

groove that exceed 0.007 inch the low stop collar if damage
are cause for retirement of the exceeds the allowable limit.
collar.

E. Dimensionally inspectthe The maximum allowable width is None. Retire the low stop collar.
width of the groove in the 0´•.510 inch.
collar.

F: Dimensionally inspectthe The I.D. of the collar may not None. Retire the low stop collar.
I.D. of the collar. exceed 5.4270 inches.

G. Dimensionally inspectthe The width may not be less than None. Retire the low stop collar.
width of the flanges on the 0.083 inch at any one point on
collar. Check a minimum the top flange, or less than 0.073
of four separate points on inch at any one point on the
each flange. bottom flange.

H. Visually inspectarea No wear allowable. None. Retire the low stop collar.
beginning on the side
opposite the lugs extending
0.1875 inch toward the lug
side of the inner surface as

shown.

i. Visually inspect inner Grooves/scratches less than Ifgrooves/scratches are deeper

surface, excluding H, 0.007 inch deep do not require than 0.007 inch, polish inner
above, but including inner repair, surface, maintaining maximum
surface of lug areas for I.D. of 5.4270 inches. See "F"

grooves/scratches. above.

Page
CHECK 61-10-14 51 Mar/98
 PROPELLER MAINTENANCE MANUAL
H~RTZELL 114C

TEMPORARY REVISION NO. 002

To Manual 61-10-14

NOTE: Record the incorporation of this temporary revision on the RECORD OF

TEMPORARY REVISIONS sheet at the front of the manual.

Insert in CHECK, facing page 513 (Mar/98).

Reason for issue: Revision of serviceable limits for pitch change rod threads.

NOTE: The remainder of this page is intentionally blank, see page 1 of this
Temporary Revision.

TR-002
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1140

Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

16. Pitch Change Rod Inspection

A. Visually inspectthe pitch No cracks are allowed. None. Retire part.

change rod for indications
of cracks.

B. Visually inspectthe
I threaded areas of thepitch
1/4 of one

accumulated
thread total
damage is allowed.
None. Retire part.

change rod for damage.

C. Eachpitch change rod No cracks are allowed.

None. Retire part.
must beinspected using the
magnetic particle method at
each overhaul.

D. Dimensionally inspectthe See wear tolerance chart in None. Retire part.

O.D. of the
pitch change section 800 for minimum O.D.
rod.

17. Featherina SDrina Insoection

A. Visually inspecteach No noticeable loss of material. None. Retire part if corrosion

feathering spring for canot be removed safely and
indications of pitting or
completely.
corrosion.

B. Each feathering spring must No cracks are allowed. None. Retire the spring.
beinspected using the
magnetic particle method at
each overhaul.

18. Auto High Pitch Stop Unit

inspection

A. Visual Inspection No damage allowed. None. Retire the part.

B. FluorescentPenetrant No cracks allowed. None. Retire the part.

inspection

CHECK TR-002
 PROPELLER MAINTENANCE MANUAL
H19 RTZ c LL 1140

Componentlnspectlon Criteria a

d
i,,,,, Serviceable Limits Correethr. Aetlon
I
16. Pitch Change Rod Inspection

No cracks allowed. None. Retire part.

A. Visually inspectthe pitch are

change rod for indications

of cracks.

None. Retire part.

I Visually inspect the
threaded areas of the pitch
114 of one thread total
accumulated damage is allowed.
change rod for damage.

C. Each pitchchangerod No cracks are allowed. None. Retire part.

must be inspected using
the magnetic particle
method at each overhaul.

D. Dimensionally inspectthe See wear tolerance chart in None. Retire part.

is OD of the pitch change rod. section 800 for minimum 00

17. Featherina SDrina lnsoection

A. Visually inspecteach No noticeable loss of material. None. Retire part if corrosion

feathering spring for canot be removed safely and

indications of pitting or completely.
corrosion.

8. Each featheringspring No cracks are´• allowed. None. Retire the spring.

must be inspected using
the magnetic particle
method at each overhaul.

18. Auto High Pitch Stop Unit

Inspection

A. Visual Inspection No damage allowed. None. Retire the part.

8. Fluorescent Penetrant No cracks allowed. None. Retire the part.

inspection

NOTE: Please see the

TEMPORARY
REVIS~ON
that revises this page.

C~ECKPage 512
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 114C

Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

19. Guide Collar Inspection

No cracks allowed. None. Retire the guide collar.

A. Visually inspectthe guide are

collar for cracks. Refer to

Figure 505 for typical crack
locations.

B. Visually inspectthe guide Maximum depth of damage may Polish damaged area, if less
collar for nicks, gouges, or not exceed 0.020 inch. than 0.020 inch, and Alodine
other damage, coat.

No cracks allowed. None. Retire the guide collar.

C. Inspectthe guidecollar are

using the dye penetrant

method.

D. Dimensionally inspectthe If bushing is worn more than Bushings having an l.D. greater
I.D. of the guide collar 0.008 inch ovality, replace it. See than that allowed must be
tolerance chart in section removed and replaced. Refer to
bushings. wear

800 forbushing I.D. the Repair chapter of this manual

requirements. for replacement procedures.

BSD4985

Q1
Cracks typically occur in
\C)
the area near the socket
head cap screw opening

~3/

Guide Collar
Figure 505

Page
CHECK 61-10’14 513Mar/98
 PRDPELLER
HARTZELL M*:N1~NANCE MPINUIL

Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

20. SDrina Retainer Inspection

A. Visually inspectthe spring No cracks are allowed. None. Retire the part.
retainer for cracks.

B. Dimensionally inspectthe No worn ovality exceeding 0.005 None. Retire the part.
pitch change rod hole (I.D.) inch.
of the spring retainer.

C. Inspectthespring retainer No cracks are allowed. None. Retire the part.

using the dye penetrant
method.

CnEcK 61-10-14 P.L~,4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action

Inspect

21. RearConer3030~
Figure 506

A. Visually inspectthe OD Surface finish must be 63 micro None. Replace the rear cone.

taper surf ace "A" and finish or smoother.

surface "B" of the rear Except for very light scratches, no
cone for damage and damage is allowed.
surface finish.

Surface must be smooth with no Remove burrs with a file; otherwise,

B. Visuallyinspectthe ID
surface "C" for damage. burrs adjacent to the four half round replace the rear cone if it is beyond
channels or slot, serviceable limits.
Except for very light scratches, no
damage is allowed.

slotfor There must be no material or Remove gasket with CM41 ,CM106

C. Visuallyinspectthe
gasket or adhesive adhesive on either surface of the orequivalent. Remove adhesive by
residue. slot. soaking in solvent or by plastic
media blasting in accordance with
the Cleaning chapter in the Hartzell
Standard Practices Manual 202A
(61-01-02).

W10429
Slot
Slot or break at the half
round channel.

Half Round
Channel

Rear Cone
Figure 506

515
CHECK 61-10’14 Rev. 5 Aug/OlPage
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1140

Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

22. SPrina Pin (3040~

Figure 507

A. Visually inspectthe spring The spring pin must not be bent. None. Replace the spring pin.
pin for straightness.

B. Visually inspectthe spring No damage is allowed. None. Replace the spring pin.
pin for damage.

W10459

Spring Pin
Figure 507

CHEC~ 61-10-14 516

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action

Inspect

23. Oil Slinaer (3060~

Figure 508

A. Visually inspect the oil No bends, warps, gouges, or None. Replace the oil slinger.
slinger ring for damage and corrosion are allowed. Random
corrosion. light scratches no deeper than
0.003 inch (0.08 mm) are
acceptable.

B. Visually inspecttheoil If wear caused by the slip ring or None. Replace the oil slinger.
slinger ring for wear, rear cone is present, then
dimensionally inspect depth of
wear.Maximum allowable depth of
material loss on either side is
0.003 inch (0.075 mm).

C. Dimensionally inspectthe Maximum allowable ID is 2.383 None. Replace the oil slinger.
ID of the oil slinger. inches (60.52 mm).

W10449

Wear

f\
Maximum Idis 2.383
inches (60.52 mm).

Oil Slinger
Figure 508

517
CHECK 61’10-14 Rev. 5 Aug/OlPage
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

W10454

Acceptable Unacceptable Unacceptable

Side "A"

Side "B"
End

Thickness

Height

Oil Seal Rings

Figure 509

518
CHECK
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action

Inspect

24. OilSeal Rings (3070.3090)

Figure 509
The end gap must be uniform None. Replace the oil seal ring.
A. Visually inspect the end
across the entire end surfaces. A
Sap.
wedge shape opening is
unacceptable. Referto Figure 509.

sides "A" A dark gray surface indicates no None. Replace the oil seal ring.
B. Visually inspect
and "B" for wear. wear. If either surface is shiny, then

dimensionally inspect the

thickness from side "A" to "B"
Minimum allowable thickness is
0.0915 inch (2.324 mm)

C. Dimensionally inspectthe Minimum allowable height is 0.122 None. Replace the oil seal ring.
height of the cross section inch (3.10 mm).
from the ID to the OD.

519
CHECK 61-10-14 Rev. 5 Aug/OlPage
HARTZELL PROPELLERM":N:~N"NCEMANVAL
Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

25. Slip Rina(3080~

Figure510

A. Dimensionally inspectthe Maximum allowable groove width is None. Replace the slip ring.
width of grooves "A" and "B". 0.198 inch (5.03 mm). Minimum
allowable groove width is 0.193
inch (4.90 mm).

B. Dimensionally inspectthe Minimum allowable OD is 2.565 None. Replace the slip ring.
OD of grooves "A" and "B", inches (65.15 mm).

C. Visually inspectsurfaces Except for light scratches, no None. Replace the slip ring.
"C" and "D" for damage. damage is allowed. Surfaces must
be smooth.

D. Visually inspectthe ID The surface must be generally Remove burrs with a file and crocus
surface "E" for damage. smooth with no burrs adjacent to cloth; otherwise, replace the slip
the four half round channels. ring if it is beyond serviceable
Except for light scratches, no limits.
damage is allowed.

W10425

,E

E~ I I +t- E

O I 1 111’1

OD OD

I//NI

Slip Ring
Figure 510

520
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action

Inspect

26. Slip Ring Sleeve (4000~

Figure511

A. Visuallyinspectthe IDfor No visible wear is allowed. None. Replace the slip ring sleeve.
weargroovescausedby
the oil seal rings.

W1W27

Wear

Slip Ring Sleeve

Figure 511

521
CHECK 61-10-14 Rev. 5 Aug/OlPage
 PROPELLER MANUPIL
HARTZELL

Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

27. Pipe Plug (4020~

Figure512

A. Visually inspectthe 1/2 thread total accumulated None. Replace the pipe plug.
th reads for damage. damage is acceptable.

B. Visually inspectthe pipe No corrosion is allowed. None. Replace the pipe plug.
plugforcorrosion.

C. Visually inspectthe Sufficient flat surface must remain None. Replace the pipe plug.
wrenching flats for on two opposing flats to allow
damage. torque to be applied by an open-
end wrench.

W1M53

Wrenching Flats

Pipe Plug
Figure 512

´•´•E´•´• 61-10-14 Rev. 5 Aug/OlPage 522

 PROPELLER MAINTENANCE MANUAL
H~ RT Z E L L 114C

Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

28. Sorina(4030~
Figure 51 3

A. Dimensionally inspectthe Minimum acceptable length is Stretch the spring by pulling on the
length of the spring. 0.875 inch (22.22 mm), ends, maximum acceptable length
is 1.125 inches (28.57 mm).

B. Countthe coilstoverify the Spring must have 10 to 11 coils None. Replace the spring.
correct spring, total.

C. Visually inspectfor Maximum allowable depth of None. Replace the spring.

damage, damage is 0.003 inch (0.075 mm).

W10452

l---I
Length of spring must be 0.875 to
1.125 inches (22.22 to 28.57 mm).

Spring
Figure 513

523
CHECK 61’10-14 Rev. 5 Aug/OlPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

29. TransferSeai Button (4040)

Figure514

A. Visually inspectfor No Corrosion is allowed. Remove light corrosion with glass

corrosion, bead cleaning, otherwise replace
the transfer seal button.

B. Visually inspectfor Scratches, pitting,or random None. Replace the transfer seal
damage. indentations are acceptable to a button.
depth of 0.005 inch (0.13 mm).

C. Visually inspectforwear. Wear to disk thickness, disk None. Replace the transfer seal
diameter, shoulder height, or button.
shoulder width must not exceed
the limits listed in Figure 513.

W10450
Shoulder

All IIA

f~.icf
Disk

ButtonTable.xls

Feature DescriDtion Dimension

A I Shoulder Width 0.100 inch (2.54 mm minimum
B Disk Diameter 0.429 inch (10.90 mm minimum
C Disk Thickness 0.040 inch 1.02 mm minimum
D I Shoulder Heiaht 10.040 inch (1.02 mm) minimum

Transfer Seal Button

Figure 514

CHECKPage 524
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action

Inspect

30. Bolt(4060~

A. Visually inspect each bolt. Corrosion, scoring, thread damage, None. Replace the bolt.
or any other damage is
unacceptable

No relevant indications are allowed. None. Replace the bolt.

B. Magneticparticle inspect
each bolt in accordance
with the Magnetic Particle
Inspection chapter in the
Hartzell Standard
Practices Manual 202A
(61-01-02).
NOTE: It is not necessary
to strip the bolt
before magnetic
particle inspection.

C. Visually inspect the Cadmium plate must completely Replate the bolt in accordance with
cadmium plate coverage cover the bolt. the Cadmium Replating chapter in
on the bolt, the Hartzell Standard Practices
Manual 202A (61-01-02).

31. Washer(4070~

A. Visually inspectthe Maximum allowable depth of None. Replace the washer.

washerforcorrosion, wear, damage is 0.005 inch (0.13 mm).
or damage. Sufficient flat surface must remain
tosupport the bolt head.

B. Visually inspectthe Except for a few abraided corners Replate the washer in accordance
cadmium plate coverage andlight scratches, cadmium plate with the Cadmium Replating
on the washer, must completely cover the washer. chapter in the Hartzell Standard
Practices Manual 202A (61-01-02).

CHECK 61-10-14
 PROPELLER
HARTZ ELL MA:N;T~EcNANCE
C411LAUNAM

W10423

Internal
Surface

r
j_

~-6------2 External Surface

Slip Ring Cap

Figure 515

CHECKPage 526
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action

Inspect

32. Slit, Ring Car, (4050~

Figure 515

A. Dimensionally inspectthe Maximum allowable diameter is None. Replace the slip ring cap.
bore "A". 0.335 inch (8.51 mm).

B. Dimensionally inspectthe Maximum allowable diameter is None. Replace the slip ring cap.
ID of the shoulder "B". 4.256 inches (108.10 mm).

C. Visually inspectthe 1/2 of one thread total accumulated None. Replace the slip ring cap.
threaded holes "C" and "D" damage is acceptable perthreaded
for th read damage, hole.

D. Inspectthebore "E". Verify that the lip seal ring (3020) None. Replace the slip ring cap.
and back up ring (3010) will fit tight
in bore "E".

E. Visually inspectfor No corrosion is allowed. Remove light corrosion with glass

corrosion, bead cleaning; otherwise, replace
the slip ring cap.

F. Visually inspectthe Maximum allowable depth of None. Replace the slip ring cap.
external surfaces for damage is 0.040 inch (1 .01 mm).
damage. Damage must not interfere with the
function of the oil transfer unit.

G. Visually inspect the Maximum acceptable depth of Removed pushed up material by

internal surfaces for damage is 0.01 0 inch (0.25 mm). polishing. Replace the slip ring cap
damage. No pushed up material beyond if beyond serviceable limits.
surrounding surfaces is allowed.
Damage must not interfere with the
function of the oil transfer unit.

527
CHECK 61-10-14 Rev. 5 Aug/OlPage
 PROPELLER MAINTENANCE MANUAL
MA RTZ E L L 114C

Component Inspection Criteria

Inspect Serviceable Limits Corrective Action

33. Oil Transfer Plug

Figure5le

A. Visually inspect the OD No visible wear is allowed. None. Replace the oil transfer plug.
"A" for wear.

B. Dimensionally inspectthe Minimum allowable OD is 0.421 None. Replace the oil transfer plug.
OD "B" for wear. inch (10.69 mm).

C. Visually inspectfor No corrosion or pitting is allowed. None. Replace the oil transfer plug.
corrosion.

W10426

A B

Oil Transfer Plug

Figure 516

CHECKPage 528
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Component Inspection Criteria

Serviceable Limits Corrective Action

Inspect
34. Elbow(5010~
Figure517

A. Visually inspect the elbow No corrosion is allowed. None. Replace the elbow.
forcorrosion.

B. Visually inspectthe machine 1/2 thread total accumulated None. Replace the elbow.
threadsfordamage. damage is acceptable.

C. Visually inspect the pipe 1/2 thread total accumulated None. Replace the elbow.
threads for damage. damage is acceptable.

D. Visually inspectthefitting Surface must be smooth with no None. Replace the elbow.
end surface for scratches scratches or surface damage.
orsurface damage.

E. Visuallyinspectthe Sufficient flat surface must remain None. Replacetheelbow.

wrenching flats for to allow torque to be applied with
damage. an open-end wrench.

F. Visually inspectthe elbow No cracks are allowed. None. Replace the elbow.
for cracks.

W10451

Fitting End

I
I

MachineThreads
*I
I

:I jl I

Wrenching Flats

Pipe

Elbow
Figure 517

529
CHECK 61-10-14 Rev. 5 Aug/OlPage
 MANUAL
HA RTZ E LL

(This page is intentionally blank.)

CHECK 61110114 Rev. 5 Aug/OlPage 530

 PROPELLER MAINTENANCE MANUAL
H19 RTZ E L L 114C

CONTENTS

1. General 603

A. Shot Peening 603

B. Minor Damage to Metal Parts........................................................................... 603

2. Blade Repair 603

3. Hub Unit Repair 603

4. Blade Clamp Repair 603

5. Spinner Assembly Repair 604

6. Cylinder Repair 604

7. Piston Repair 604

A. Plastic Bushing Removal and Replacement 604

B. Repair of Link Pin Unit Safety Screw Hole 605

8. Beta Ring Repair 607

A. General Repair 607

B. Interior Surface Repair 607

9. Guide Collar Repair 607

A. Replacement of Guide Collar Bushings 607

10.Carbon Block Assemblies 609

A. Repair of Binding Problems 609

B. Replacement of A-3026 Carbon Block Unit in the A-3044

Carbon Block Assembly 609

I 11.Rework of A-304 Linkscrew on HC-A3V( Propeller Assemblies 610

LIST OF ILLUSTRATIONS

Repairing Interior Surface of Beta Ring Figure 601 606

Carbon Block Assembly Figure 602 608

Linkscrew Rework Limits for Hub Clearance

on HC-A3V( Propellers Figure 603

61110114
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(This page is intentionally blank.)

602
REPAIR 61110114
 PROPELLER MAINTENANCE MANUAL
WARTZELL 114C

WARNING: DO NOT ATTEMPT IN THE FIELD ANY REPAIR, REPLACEMENT,

REWORK, REPLATING, REANODIZING OR RE-SHOT PEENING
PROCEDURE NOT SPECIFICALLY AUTHORIZED BY HARTZELL
PROPELLER INC. OR NOT SPECIFICALLY REFERRED TO IN
HARTZELL MANUALS. CONTACT THE FACTORY FOR GUIDANCE
ABOUT THE AIRWORTHINESS OF ANY PART WITH UNUSUAL
WEAR OR DAMAGE.

1. General

A. Shot Peening

CAUTION: THE PEENING MARKS ON CERTAIN PROPELLER PARTS ARE

NOT TOOL MARKS AND SHOULD NOT BE REMOVED.

Certain surfaces of propeller assembly parts have been shot peened at the

factory to improve fatigue strength.

Shot may need re-shot peening. Refer to Hartzell Standard
peened surfaces
Practices Manual 202A (61-01-02) for shot peening procedure. Re-shot peening
must be done only by Hartzell-approved facilities.

B. Minor Damage to Metal Parts

Eliminate all evidence of scratches, nicks, burrs, and other minor damage by
using a fine emery cloth or Scotch Brite pad. Be sure to blend the polished area
in with the surrounding area. Use extreme care to completely remove the
damage while removing as little material as possible.
Make the part is still within tolerance after any type of repair. Refer to the
sure

Check section and the Fits and Clearances section of this manual.

2. Blade Repair

For bladerepair, replacement, and rework instructions, refer to Hartzell Manual

133C (61-13-33).

3. Hub Unit Repair

Refer to the Steel Hub Overhaul section of Hartzell Manual 202A (61-01-02),
Standard Practices, for requirements and procedures for repairing steel hub
units.

4. Blade Clamp Repair

Refer to the Blade Clamp Overhaul section of Hartzell Manual 202A (61-01-02),
Standard Practices, for requirements and procedures for repairing clamps.

REP*IR 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

5. Spinner Assembly Repair

Refer to Hartzell Manual 127 (61-16-27), Spinner Assembly Maintenance

Instruction Guide, for requirements and procedures for repairing spinner
assemblies.

6. Cylinder RePair

CAUTION: THE CYLINDER MAY BE REGROUND AND RECHROMED IF

NECESSARY, BUT ONLY AT THE HARTZELL PROPELLER INC.
FACTO RY.

(1) Remove any evidence of gouging or wear on the cylinder within repair
limits.

(2) Replace the cylinder if threaded areas are damaged.

(3) Replace the cylinder if any scratches in the operating area are deeper
than 0.001 inch. Rework of the cylinder to a depth of 0.005 inch
followed by rechroming is possible, but rechroming may only be
accomplished by the factory.

7. Piston Repair

A. Plastic Bushing Removal and Replacement

NOTE: The following procedures must be performed by a skilled machinist.

(1) Remove the oversized plastic bushing, using care not to damage the
bushing groove.

(2) Remove any remaining adhesive from the bushing groove by cleaning
with solvent CM106.

(3) Install the

plastic bushing in the piston. Refer to the Special Adhesive
and Bonding Procedures chapter of Hartzell Manual 202A (61-01-02),
Standard Practices, for procedures.

(4) Ream the plastic bushing to within tolerance found in table in section
800 of this manual.

(5) Check the runout of the plastic bushing to the bore of the piston
outboard of the plastic bushing groove. The runout must be within 0.002
inch.

REPAIR 61 ’10’14
 PROPELLER MAINTENANCE MANUAL
nA RTZ E LL 1140

B. Repair of Link Pin Unit Safety Screw Hole

I For piston units with link pin unit safety screw holes with 10-32UNF-3B
(1)
threads: When damaged, these threaded holes may be repaired by using
I a modified Slimsert.

NOTE: In the past, helicoil repairs were also authorized. Existing helicoils
are acceptable; however, future repairs are to be made using a
modified Slimsert and the following procedure:
I (2) The tools and the part necessary to make a Slimsert repairto the link pin unit

safety screw holes are as follows:

(a) 0.221 inch (5.61 mm) Diameter No. 2 Drill

(b) Repair kit TE421

1 Drive Wrench (TE353)

2 B-6986-192 Slimsert

3 1/4-28UN F-3B Bottom Tap TE423

CAUTION: MAKE SURE THE DRILL IS CENTERED AND PERPENDICULAR TO

THE HOLE.

(3) Remove the damaged threads using the #2 drill.

CAUTION: MAKE SURE THE TAP TE423 IS PERPENDICULAR TO THE HOLE.

the 1/4-28UNF-3B bottom tap TE423, re-tap the hole to a depth of

(4) Using
0.220 to 0.270 inch (5.59 to 6.85 mm).

NOTE: This will insure that the Slimsert does not extend into the slot and
interfere with the link arm.

(5) Clean the newly drilled and tapped hole with solvent CM106.
Place the Slimsert in the lathe and the counterbored end of the
(6) remove

Slimsert.

Loctite Primer CM127 to the Slimsert and the tapped hole.

(7) Apply
(8) Apply thread locking compound CM74 to the Slimsert

(9) Install the slimsert by using the drive wrench TE353 so that the Slimsert is
flush, or slightly below flush, with the outboard surface of the piston.

REPAIR 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1140

APS0198

No damage allowed in this

area.

3/16 inch

5.427 inches maximum

Repairing Interior Surface of Beta Ring

Figure 601

Page
REPAIR 61’10-14 606Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

8. Beta Ring RePair

A. General Repair
(1) Use a soft cotton wheel to polish the beta ring.
(2) Replace the beta ring if it has any cracks.

B. Interior Surface Repair

The internal surface of the beta ring may be repaired if it is worn or scraped:

(1) Use 80- to 120-grit sandpaper emery, finishing with

or 240-grit polishing
compound, to smooth the internal surface.

(2) Replace the betaring if the diameter of the interior surface is more than
5.427 inches. See Figure 601.

(3) Replace the beta ring if it is damaged in the area beginning on the side
opposite the lugs and extending 3/16-inch toward the lug side on the
inner surface as shown in Figure 601.

9. Guide Collar RePair

A. Replacement of Guide Collar Bushings

(1) Using care not to damage the guide collar, drill out the oversized

bushing(s)
(2) If the bushing being replaced is located at the split, drill out the staking
pin.
(3) Refer to the Special Bonding Procedures section of
Adhesive and
Hartzell Manual 202A (61-01-02) for guide collar bushing replacement
procedures.
(4) Using a center punch, install a new staking pin if the bushing at the split
was replaced. Peen the end of the staking pin.
1 (5) Ream the bushing(s) as required to achieve ID specified in chart in section
800 of this manual.

61 -1 0-1 4
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 114C

B-3843-25PP
External Retainer A-4543 T-Head Cotter Pin

Ring A-3025 Yoke Unit

(AN380-2-2 optional)

Yoke Pin

A-3027 A-3026 Block Unit

Clevis Pin

Side Clearance 0.001-0.002

A-3044 Carbon
inch When Installed
Block Assembly
Maximum of 0.010 side
clearance is permitted. Block
O should be replaced is this
value is exceeded.

8-3001-( Beta Ring

Carbon Block Assembly

Figure 602

Page
REPPIIR 61-10-14 608Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

10.Carbon Block Assemblies

A. Repair of Binding Problems

The clearance between the yoke pin and the corresponding linkage (beta lever
a buildup of plating and foreign
bushing) may become too close because of
between the two pieces. This may cause a binding action and result
particles
in excessive wear to the carbon block, low stop collar, and beta linkage.

Inspect the beta lever and carbon block interface for free movement. If there is

binding:
(1) Disconnect the beta linkage and remove the carbon block assemblies from

the beta collar.

(2) Polish the yoke pin to provide adequate clearance and eliminate binding.

(3) Reinstall the carbon block assembly into the beta collar.

NOTE: Use a dry lubricant between the yoke pin and beta lever.

(4) Install the carbon block on the lever supplied by the airframe engine
manufacturer.

(5) Reassemble the beta linkage and inspect for operation and safety.
B. Replacement of A-3026 Carbon Block Unit in the A-3044 Carbon Block
Assembly
See Figure 602.

(1) Remove cotter pin from the end of the clevis pin.
(2) Slide pin from assembly and remove and discard carbon block unit.

(3) Inspect yoke for wear or cracks. Replace if necessary.

(4) Install new carbon block unit and slide a new clevis pin into place.

(5) Secure with T-head cotter pin as shown in Figure 602.

(6) Refit Carbon Block

(a) Fit the block to the low stop collar with a side clearance of 0.001 to
0.002 inch (Figure 602).

Establish the required clearance by dressing the block sides as needed.

(b)

REPAIR 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZE LL 114C

11.Rework of A-304 Linkscrew on HC-A3V( Propeller Assemblies

When adjusting the
pitch range of some propeller assemblies, the linkscrew may contact
the hub. When this happens, the full blade angle range cannot be achieved. This condition
can be eliminated by grinding the linkscrew to remove material and allow clearance.

NOTE: Until
recently, hubs were modified during production in the factory by removing
enough material to allow linkscrew clearance. While this practice was
acceptable, and there are airworthy hubs still in use that were modified in this
manner, this type of modification is no longer recommended.

(A) Remove only enough material from the linkscrew to allow clearance with the hub.
(See Figure 603).

NOTE: Removal of material from the linkscrew will likely intersect the two adjacent
holes on that side of the linkscrew.

(B) Ensure that there is sufficient material surrounding the remaining, unaffected holes in
the linkscrew to support the safety cotterpin.

APS5016A

Removal of material
Ensure that there is sufficient from the linkscrew will
material surrounding these likely intersect these
holes to support the two adjacent holes.
cotterpin.

Material may be
removed from this area.

0.50 inch (12.7 mm) minimum

I

Linkscrew Rework Limits for Hub Clearance on HC-ASV( Propellers

Figure 603

REPAIR 61110114 RevPJa~,sO

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

CONTENTS

General 709
1.

Models in the -1 and -6 Series 711

2. Assembly of Two-Blade, Flanged-Hub
71 1
A. Hub Unit Assembly
711
B. Installing Guide Collar
Parts 715
C. Reassembling Blade Mounting
719
D. Assembling Clamp and CounteMleight.
719
E. Installing Blades and Clamps
721
F. Installing the Cylinder. . . . . .,. . . . . . . . . .´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
723
G. Installing Piston Assembly
725
H. Application of Blade Angle Reference Tape
727
i. Setting Blade Angle
Detection of Blade Slippage in Clamp 729
J. Providing for Visual
731
K. Sealant CM93 Application
Blade Track. 731
L. Checking
732
M. Decal Replacement
732
N. Propeller Removal from Assembly Table
3. Assembly of Two-Blade, Splined-Hub Models in the -1 Series,
´•´•´•´•´•´•´•733
Except HA-A2(V,MV) 20-1B
733
A. Hub Unit Assembly
733
B. Installing Guide Collar
733
C. Blade Mounting Parts Assembly
733
D. Assembling Clamp and Counterweight
733
E. Installing Blades and Clamps
734
F. Installing the Cylinder. . . . . . . . . . . . . . .´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
734
G. Installing Piston Assembly
Reference Tape 734
H. Application of Blade Angle
735
i. Setting Blade Angle
Detection of Blade Slippage in Clamp 735
J. Providing for Visual
735
K. Sealant CM93 Application
Blade Track 735
L. Checking
735
M. Decal Replacement
735
N. Propeller Removal From Assembly Table
Page 701

nssEMeLv 61-10-14 Rev. 4 Jan/Ol

 PROPELLER
HARTZELL MA:N~N4NCE MANUAL

4. Assembly of Three-Blade, Splined-Hub Models in the -1 series 736

A, Hub Unit Assembly

B. Installing Hub Unit and Spinner Bulkhead 736

C, Blade Mounting Parts Assembly 736

D, Assembling Clamp and Counterweight......................................................... 736

E, Installing Blades and Clamps 736

F Installing the Cylinder,

G, Installing Piston Assembly 736

H, Application of Blade Angle Reference Tape 737

i, Setting Blade Angle 737

J. Providing for Visual Detection of Blade Slippage in Clamp 738

K, Sealant CM83 Application 738

L. Checking Blade Track 738

M, Decal Replacement 738

N, Propeller Removal From Assembly Table 738

5, Assembly of HA-A2(V,MV) 20-1B 739

A, Hub Unit Assembly

B, Blade Mounting Parts Assembly 739

C, Assembling Clamp and Link Arms 739

D, Installing Blades and Clamps 740

E. Installing the Cylinder. 740
F Assembly of Pitch Adjustment Assembly 740

G, Installing Pitch Adjustment Assembly 740

H, Installing Piston Assembly 740

i, Application of Blade Angle Reference Tape 741

J, Setting Blade Pitch 741

K, Providing for Visual Detection of Blade Slippage in Clamp 741

L, Sealant CM93 Application 742

M, Checking Blade Track 742

N, Decal Replacement 742

O, Propeller Removal From Assembly Table 742

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

743
6. Assembly of Flanged-Hub Models in the HC-A( )(F,K,L)-2 Series
743
A. Hub Unit Assembly
743
B. Blade Mounting Parts Assembly
743
C. Assembling Clamp and Link Arms
744
D. Installing Blades and Clamps
Applicable) 744
E. Installing the Cylinder land Guide Collar, as

745
F Feathering Spring Assembly
745
G. Feathering Spring Assembly Installation
746
H. Installing Piston Assembly
747
i. Start Lock Unit Reassembly
747
J. Start Lock Unit Installation

Reference Tape 747

K. Application of Blade Angle
748
L. Setting Blade Angle
for Visual Detection of Blade Slippage in Clamp 749
M. Providing
749
N. Sealant CM93 Application
749
O. Checking Blade Track
749
P Decal Replacement
749
Q. Propeller Removal From Assembly Table
in the -2 Series 750
7. Assembly of Splined-Hub Models
750
A. Hub Unit Assembly
750
B. Blade Mounting Parts Assembly
Assembly 750
C. Spinner Bulkhead and Start Lock
751
D. Assembling Clamp and Counterweight...
Blades and Clamps 751
E. Installing
751
F. Installing the Cylinder and Guide Collar.....
752
G. Feathering Spring Assembly
752
H. Feathering Spring Assembly Installation
753
i. Installing Piston Assembly
Reference Tape 754
J. Application of Blade Angle
754
K. Setting Blade Angle
755
L. Providing for Visual Detection of Blade Slippage in Clamp
755
M. Sealant CM93 Application

61-10-14
 PROPEL"R
HARTZELL MA:N1~NANCE MANUAL

N, Checking Blade Track 756

O, Decal Replacement 756

P. Propeller Removal From Assembly Table 756

8, Assembly of Flanged-Hub Models in the -3 series 757

A, Hub Unit Assembly 757

B, Blade Mounting Parts Assembly 757

C, Assembling Clamp and Counterweight........................................................, 757

D, Installing Blades and Clamps 758

E, Beta System Installation (Part 1 of 2) 758

F Installing the Cylinder and Guide Collar, 759

G, Feathering Spring Assembly 760

H, Feathering Spring Assembly Installation 760

I, Installing Piston Assembly 760

J. Application of Blade Angle Reference Tape 761

K, Setting Reverse and Feather Blade Angles 762

L, Beta System Installation (Part 2 of 2) 763

M, Setting Low Pitch Blade Angle 763

N, Final Beta Ring Runout Check....................................................................., 765

O, Providing for Visual Detection of Blade Slippage in Clamp 765

P. Sealant CM93 Application 765

Q, Checking Blade Track 765

R, Decal Replacement 765

S, Propeller Removal From Assembly Table 765

9, Assembly of Splined-Hub Models in the -3 series 766

A, Hub Unit Assembly ,,,,,,,,,,,,_

766

B, Beta System Installation (Part 1 of 3) 766

C, Blade Mounting Parts Assembly 766

D, Assembling Clamp and Counterweight.....................................................,.,, 767

E, Installing Blades and Clamps 767

F Beta System Installation (2 of 3) 767

G, Installing the 768
H, Feathering Spring Assembly 768

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

Runout Check 770

O. Final Beta Ring
for Visual Detection of Blade Slippage in Clamp....... 770
P Providing
770
Q. Sealant CM93 Application
Blade Track 770
R. Checking
770
S. Decal Replacement
770
T. Propeller Removal From Assembly Table
Models in the -4 Series 771
10. Assembly of Flanged-Hub
A. Hub Unit Assembly 771

771
B. Blade Mounting Parts Assembly
771
C. Assembling Clamp and Counterweights
771
D. Installing Blades and Clamps............
771
E. Installing the Cylinder and Guide Collar
772
F Installing Piston Assembly
Reference Tape 773
G. Application of Blade Angle
773
H. Setting Blade Angle........
for Visual Detection of Blade Slippage in Clamp 774
i. Providing
774
J. Sealant CM93 Application
774
K. Checking Blade Track
´•´•´•´•´•´•774
L. Decal Replacement
774
M. Propeller Removal From Assembly Table
775
11. Assembly of Splined-Hub Model HC-A2(V,MV)20-4A1
775
A. Hub Unit Assembly
Parts Assembly 775
B. Blade Mounting
775
C. Installing Guide Collar...
and Counterleight 776
D. Assembling Clamp
776
E. Installing Blades and Clamps
776
F. Installing the Cylinder
776
G. Installing Shaft Seal
776
H. Installing Piston Assembly
Reference Tape 777
i. Application of Blade Angle
777
J. Setting Blade Angle...
Detection of Blade Slippage in Clamp..... 778
K. Providing for Visual
778
L. Sealant CM93 Application

Pags 705

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

M, Checking Blade Track 778

N, Decal Replacement
O, Propeller Removal From Assembly Table 778
P Oil Transfer Unit Assembly
12, Assembly of Flanged-Hub Models in the -5R Series 779

A, Hub Unit Assembly 779

B, Blade Mounting Parts Assembly 779

C, Assembling Clamp and Counterweight 780

D, Installing Blades and Clamps 780

E, Beta System Installation (Part 1 of 2) 780

F. Installing the Cylinder and Guide Collar 781
G, Feathering Spring Assembly 782
H, Feathering Spring Assembly Installation 783

i, Installing Piston Assembly 783

J, Start Lock Unit Reassembly ..........................i............................................, 784

K. Start Lock Installation ........i........................................................................, 784

L, Application of Blade Angle Reference Tape 784

M, Setting Reverse and Feather Blade Angles 785

N, Beta System Installation (Part 2 of 2) 786

O, Setting Low Pitch Blade Angle 786

P Final Beta Ring Runout Check 787

Q, Setting Start Lock Blade Angle 787

R, Providing for Visual Detection of Blade Slippage in Clamp 787

S, Sealant CM93 Application 787

T: Checking Blade Track 787
U, Decal Replacement ,,,,,,,,,787

V, Propeller Removal From Assembly Table 788

13, Assembly of Flanged-Hub Models in the -S(A,AL) Series 788
A, Hub Unit Assembly 788
B, Blade Mounting Parts Assembly 788

C, Assembling Clamp and Counterweight 788

D, Installing Blades and Clamps 789

61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

789
E. Installing the Cylinder and Guide Collar........
790
F. Feathering Spring Assembly
790
G. Feathering Spring Assembly Installation
790
H. Installing Piston Assembly
791
i. Start Lock Unit Reassembly
J. Start Lock Unit Installation

Reference Tape 792

K. Application of Blade Angle
L. Setting Blade Angle
for Visual Detection of Blade Slippage in Clamp 793
M. Providing
793
N. Sealant CM93 Application
793
O. Checking Blade Track
793
P. Decal Replacement
From Assembly Table 793
Q. Propeller Removal

Page 707
ASSEMBLY 61-10-1 4 Rev. 4 Jan/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 114C

LISTOF ILLUSTRATIONS

Inserting The Staking Pin Figure 701 710

Pin Drive-Fit (K or L Flange) Figure 702 712

"A" and "B" Positions Figure 703 712

Hub Arm Build-Up Figure 704 714

Blade and Flange Mounting Parts Figure 705 716

CM93 Sealant Application Figure 706 718

Installing Piston and Cylinder Figure 707 722

Application of Blade Angle Reference Tape Figure 708 724

Setting the Blade Angle Figure 709 726

Providing for Visual Detection of Blade Slippage in Clamp Figure 710 728

Using Padded Blade Bar to Check for

Blade Slippage in Clamp Figure 711 728

Sealant CM93 Application Figure 712 730

Checking Blade Track Figure 713 730

Warning Decal Part No. WAR-001 for

Dynamically Balanced Propeller........................................ Figure 714 732

Checking Beta Ring Runout with Dial Indicator Figure 715 764

Information Tag on Beta Return Spring Figure 716 770.1

Checking End-Gap on the Oil Seal Rings Figure 717 778.1

Installing the Oil Transfer Plug Using the Installation Tools........ Figure 718 778.2

A-224-4 Oil Transfer Unit Figure 719 778.4

Installing the Oil Seal Rings into the Slip Ring Figure 720 778.6

Clearance Between the Slip Ring Groove Side and

the Oil Seal Ring Figure 721 778.6

A-221-() Oil Seal Ring Characteristics Figure 722 778.7

Installing the Ring Compressor on the Slip Ring and

Oil Seal Rings Figure 723

Insatlling the Slip Ring and Oil Seal Rings into the
Slip Ring Sleeve Figure 724 778.9

61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

1. General

A. Unless instructed otherwise, lubricate all O-rings with lubricant CM12 before

installing them in the propeller assembly.

B. Refer to Hartzell Manual 202A (61-01-02), Standard Practices, for steel hub

assembly procedures.

C. Refer to Hartzell Manual 133C (61-13-33), Aluminum Blade Overhaul, for

blade bore plug and blade bore bearing installation procedures.

D. Refer to Hartzell Manual 202A (61-01-02), Standard Practices, for blade

clamp assembly procedures.

E. After propeller is reassembled, refer to Hartzell Manual 202A (61-01-02),

Standard Practices, for lubrication procedures.

F. After propeller is reassembled, refer to Hartzell Manual 202A (61-01-02),

Standard Practices, for static balancing procedures.

G. Read all assembly instructions before beginning the assembly procedures.

WARNING: DURING ENGINE INSTALLATION OR REMOVAL, DO NOT USE

THE PROPELLER TO SUPPORT THE WEIGHT OF THE ENGINE.
UNAPPROVED INSTALLATION AND REMOVAL TECHNIQUES
MAY CAUSE DAMAGE TO THE PROPELLER, WHICH MAY LEAD
TO FAILURE RESULTING IN AN AIRCRAFT ACCIDENT.

H. Be sure propeller is removed before engine is removed from or installed in the

airframe.

WARNING: WHEN REMOVING AND INSTALLING THE PROPELLER,

FOLLOW THE AIRFRAME MANUFACTURER’S MANUALS AND
PROCEDURES, AS THEY MAY CONTAIN ISSUES VITAL TO
AIRCRAFT SAFETY THAT ARE NOT CONTAINED IN HARTZELL
OWNER’S MANUALS.

I. Follow the airframe manufacturer’s instructions for installing and removing the
propeller. If such instructions are not in the airframe manufacturer’s manual,
then follow the instructions in the appropriate Propeller Owner’s
Hartzell
Manual. However, mechanics must consider that the propeller owner’s manual
does not describe important procedures that are beyond Hartzell’s control. In
addition to propeller installation procedures, items such as rigging and
preflight testing of flight low pitch blade angle, installation and adjustment of
de-ice equipment, and propeller synchronization devices are normally found in
the airframe manufacturer’s manuals.

ASSEMBLY 61’10’14
 PROPELLER
HARTZ E LL MA:NI~ECNANCE MANUAL

staking pin

Inserting The Staking Pin

Figure 701

Page
AssEnnsLv 61 -1 0-14 710Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 114C

2. Assembly of Two-Blade, Flanaed-Hub Models in the -1 and -6 Series

A. Hub Unit Assembly

(1) Follow the procedure in the Steel Hub Overhaul section of Hartzell
Standard Practices manual 202A (61-01-02) for pilot tube installation.

(2) Mount hub on the rotatable fixture of a propeller assembly table.

B. Installing Guide Collar

(1) Insert the socket head cap screw(s) into the guide collar. Before
tightening the screw(s), line up the notch in the collar with the
staking pin hole in the hub spider.

NOTE 1: The staking pin used for aligning the propeller on the
engine flange is also used to stake the guide collar.

NOTE 2: The pin for the BHC-A2VF-1 and BHC-A2MVF-1 is steel.

In all other models the pin is aluminum.

(2) Insert the staking pin into the hub

flange from the rear until it enters
the notch machined in the guide collar (Figure 701). The pin should
extend 1/2 inch beyond the hub flange.

(3) If the guide collar does not have a notch:

(a) For K and L flanges:

1 Position the collar so it is properly located to receive the
piston guide rods.

2 Spot face the edge of the collar approximately 1/8 inch

deep to receive the aluminum staking pin.
(b) For F flange:
1 Install four spinner lugs.
2 Position the collar so it is properly located to receive the
piston guide rods.

3 Spot face the edge of the collar approximately 1/8 inch

deep to receive the staking pin.

NOTE: There are pins in two spots on the collar to keep the
collar from rotating.

(4) Tighten socket head cap screws. See torque table in chapter 800.

ASSEMBLY 61-10-14
 PROPELLER
HARTZELL MPI:N1~ANCE M*NU*L

Propeller mounting flange

Staking

Guide collar

Pin DrivelFit (K or L Fiange)

Figure 702

"A"

"B"

Staking pin I II II~

Guide collar

"A" and "B" Positions

Figure 703

ASSEMBLY
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(5) For models HC-ASVK-1D and HC-AZMVK-~D, only:

Be sure staking pin is a drive-fit through the hole in the flange of
the
the propeller hub and securely engages the notch milled into the guide
collar (Figure 702).

(6) For models HC-APVF-1 and HC-APMVF-1, only:

Install dowel pin in "A" location of mounting flange (Figure 703).

(7) For models BHC-ASVF-1 and BHC-ASMVF-~, only:

Install dowel pin in "B" location of mounting flange (Figure 703).

ASSEMBLY 61’10’14
 PROPELLER MP~NUIL
HARTZELL

APS0198

PullerTool
TE108(BT-223)

(BST-3062)

Guide Ring

Split Bearing

a
Hub Spider Adapter Ring BT-223+10

Wire Retention Ring

Light Mallet

;22=-:
Guide Ring ---JY

TE309
(BST-3062)

Hub Spider Arm

Hub Arm BuildlUp

Figure 704

nssEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 114C

C. Reassembling Blade Mounting Parts

the rotatable fixture of the assembly table.
(1) Mount the hub spider on

Tighten bolts (snug).

CAUTION: BE SURE THE INTERNAL RECESS OF THE BEARING GUIDE

RING FACES OUTBOARD WHEN THE GUIDE RING IS SLIPPED
OVER THE BLADE ARM FLANGE OF THE HUB SPIDER UNIT.
blade
(2) Use a light mallet and special tool TE309 (Figure 704) to drive a
hub
retention split-bearing guide ring onto one blade arm flange of the
spider unit.

NOTE: Drive the guide ring far enough onto the blade arm flange that
the ring forms a narrow channel on the inboard surface of the

flange.
of
(3) Use approved lubricant CM12 to lightly grease the inboard surface
each blade arm flange.
(4) Place the halves of an outboard bearing race (matched set) in position
over one hub spider arm.

NOTE 1: The break-line for the bearing race halves should be

perpendicular to the table top.

NOTE 2: Be sure the races are a matched set.

(5) Use combination of tools TE309 and TE108 to press the guide ring far
a
of the wire
enough onto the outboard bearing race to allow insertion
retention ring into the groove in the blade arm flange (Figure 704).

(6) Install the wire retention ring.

(7) Use tools TE309 and TE108 (Figure 704) to pull the bearing guide ring
outboard far enough to allow the wire retention ring and the guide ring
to

contact each other. Wire retention ring will fit in recess of guide ring.

TO
CAUTION: THE WIRE RETENTION RING MUST BE FULLY ENCLOSED
ENSURE IT IS NOT PINCHED.

(8) Check to make sure the wire retention ring is fully enclosed.
it
(9) Lubricate the blade O-ring with approved lubricant CM12 and slide over
1
the blade arm flange of the hub to a location inboard of the thrust
bearing. Leave it there for use later in the reassembly.
(10) Repeat Steps C.2 through C.9 for the other hub spider arm(s).

Page 715

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MINU~L
HARTZ a LL

APSM13
d´•-:´•I
Wire Retention Ring
Guide Ring
Ball
Beanng
Spacer

RetentionBearing Ring

O-Ring

APSMD7

SpiderHub

~T /1111 ~h\ "Cavity" where split

bearing halves will
be installed

Tool TE309
(BST-3062)

O-ring
Ball spacer
Ring

Bearing Bearing race chamfer

Bearing installation
APS5014

Blade and Flange Mounting Parts

Figure 705

nssennslv 61-10114
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

and
(11) Remove the hub unit from the rotatable fixture on the assembly table
use special tool TE309 to hold the hub
unit vertical as shown in Figure
705.

NOTE: The arm bearing races must be

of the hub being fitted with
I
facing down so that the hub flange and guide ring form a
"cavity" that will hold the bearings.
AT A
CAUTION 1: THE BREAK LINE OF THE BEARING-HALVES MUST BE
RIGHT ANGLE TO THE BREA~ LINE OF THE BLADE CLAMP-
HALVES.

CAUTION 2: ANY GAP BETWEEN THE HALVES OF THE OUTBOARD

BEARING RACE SHOULD BE NO GREATER THAN 0.001 INCH.

CAUTION 3. ALL BEARING BALLS INSTALLED IN A SINGLE BEARING

MUST BE OF THE SAME GAUGE. BEARING BALLS SUPPLIED
I BY HARTZELL ARE OF THE SAME GAUGE.

(12) Install the ball bearing spacer and the required number of bearing balls
onto the outboard bearing races, taking care not to scratch the races.

(13) Apply slight amount of sealant CM93 to the broken edges of the
a
that
inboard bearing race (matched set). Wipe clean any excess sealant
when the bearing halves are joined.
may extrude into bearing area

(14) Place inboard halves of bearing race around one blade arm of the hub
unit and install the wire bearing retention ring to hold the halves in place.

CAUTION: THE OPENING OF THE RETENTION RING MUST BE AT A

RIGHT ANGLE TO THE PARTING LINE OF THE INBOARD
BEARING RACE.
at chamfer
(15) Apply a small bead of sealant CM93 to inboard bearing race
of the
(break point) in order to evenly fill the void in the chamfered area
race.

CAUTION EXCESSIVE USE OF SEALANT COULD CAUSE UNEVEN

SEATING BETWEEN BLADE CLAMP AND BEARING RACE.

(16) Slide the O-ring outboard in place against the inboard bearing race.

(17) Wrap wide masking tape around the outside diameter of the bearing
assembly to hold the parts in place.
for the other blade arm(s) on the hub
1 (18) Repeat these assembly procedures
unit.

ASSEMBLY 61110114
 PROPELLER MANUAL
HARTZ E LL MA:F~ECNANCE

APSW17

O 0.1875 in. (4.763 mm)

O
CM93

0.3750 in. (9.525 mm)

~dT
APS0426 CM46
Enlarged View

CM93

CM93 Sealant Application

Figure 706

61-10-14
 PROPELLER MAINTENANCE MANUAL
H 19 RTZ E L L 114C

D. Assembling Clamp and Counterweight.

(1) Refer to Clamp Overhaul section of Manual 202A (61-01-02),
(2) After each clamp and counterweight is assembled, peen the back of the
counterweight flush against the clamp-half.
E. Installing Blades and Clamps

CAUTION: IF POSSIBLE, EACH BLADE SHOULD BE REINSTALLED ON

THE HUB SPIDER ARM FROM WHICH IT WAS REMOVED AT
DISASSEMBLY.

(1) With the hub assembly in the horizontal position, follow the prescribed
procedure for Checking Blade Track.

(2) Stand blade number one up, tip down) and fill
in vertical position (base
the pilot tube cavity with CM12 grease to the top of the bottom
(inboard) bearing race level.

WARNING: AIR TRAPPED IN THE GREASE CAN AFFECT PROPELLER

BALANCE AFTER RUN-UP.

(3) After making sure no air is trapped in the grease, press the blade onto
its matching hub pilot tube.

NOTE: A slight amount of grease will ooze out around the pilot tube
if the blade has been lubricated correctly.
(4) In consecutive order, repeat the lubrication and reinstallation procedure
for the other blade(s).

CAUTION: BE SURE TO USE HARDENING GASKET COMPOUND CM46

ON THE SHOULDER RADIUS OF THE BLADE BASE.

(5) Spread approved gasket compound CM46 on the shoulder radius of

the blade base in the area where it will be in contact with the blade
clamp (Figure 706).

NOTE: A bead approximately 0.25 inch wide and 0.06 inch thick is
sufficient.

(6) Place a small bead of sealant CM93 to both clamp halves on a portion
of the mating surfaces and in the inboard bearing radius as shown in
Figure 706.

CAUTION: THE PARTING LINE OF THE CLAMP-HALVES MUST BE AT A

RIGHT ANGLE TO THE PARTING LINE OF THE INBOARD
BEARING RACE.

(7) Remove the masking tape used to temporarily hold the blade split-
bearing together.

PISSEMBLY 61-10-14
 PROPELLER MANUAL
HARTZ ELL

(8) Install the matching clamp-half to which the counterweight is attached.

(9) Place a gasket between each of the clamp-half parting surfaces.

(10) Install the other clamp half.

I CAUTION 1:A 0.06-INCH (1.59 MM) MAXIMUM OF GASKET MATERIAL

SHOULD BE EVENLY EXPOSED THROUGH THE LIPS ON
EACH CLAMP-HALF PARTING SURFACE. HOWEVER, GASKET
MATERIAL MUST BE TRIMMED AS NECESSARY TO
PROVIDE METAL-TO-METAL CONTACT WHERE THE CLAMP
LUGS MEET.

I CAUTION 2. DO NOT TORQUE THE OUTBOARD CLAMP BOLTS AT THIS

STAGE OF ASSEMBLY.

(11) Insert the outboard clamp bolts and fasten them with clamp nuts.

(12) Hand-tighten the clamp nuts.

NOTE: This step helps align the clamp gasket, but the clamp bolts
should not be torqued at this stage.
(13) Insert inboard clamp socket screws.

CAUTION 1: DO NOT EXCEED RECOMMENDED TORQUE ON INBOARD

CLAMP SOCKET SCREWS. SEE TORQUE TABLE, CHAPTER
800.

CAUTION 2: INBOARD CLAMP SOCKET SCREWS MUST BE TORQUED IN

THE SEQUENCE SPECIFIED.

(14) Tighten the socket screws by increasing torque with a conventional

I 5/16-inch Alien wrench.

NOTE: Torque socket head screws in 10-lb increments (10, 20, etc.)
alternating between screws at each increment.

CAUTION: DO NOT CONTACT THE CLAMP WHILE DRILLING THE

INBOARD CLAMP SOCKET SCREWS.

(15) With a #42 size bit, drill the head of each inboard clamp socket screw.

nssEhnsLv 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 114C

(16) Safety each socket screw with a cotter pin in such a way that the
cotter pin contacts the clamp-half and prevents any tendency for the
screw to back out of the clamp.

NOTE: To ensure clearance, use three loops of safety wire CM131

to safety the socket screw; a cotter pin may cause clearance

problems.
for each of the
(17) Repeat these blade clamp reinstallation procedures
other propeller blades.

(18) Check freedom of blades on pilot tube of hub.

F. Installing the Cylinder

(1) Clean threads on hub and cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER.
CM134 in the groove of the
(2) Apply a bead of hydraulic sealant adhesive
Install O-ring into cylinder
spider hub where the cylinder O-ring will fit.
chamfer, facing spider hub.
Hand the cylinder onto the hub spider unit.
(3) screw

fit the slot provided for it in

(4) Use asquare bar of appropriate size to
the top of the cylinder, and torque the cylinder against the hub spider
unit (see torque table in Chapter 800).

NOTE: Tighten cylinder flush with shoulder on hub. Early drag and
tightness is caused by O-ring, which acts as seal and safety.
(5) Inspect the slot in the top of the cylinder to make sure the square-bar
wrench used for torquing did not raise any sharp edges or damage the
th reads.

(6) Remove any sharp edges in the wrench slot on top of the cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER. HYDRAULIC SEALANT ADHESIVE IN THE
CYLINDER MAY CONTAMINATE THE AIRCRAFT ENGINE
OIL.
not been
(7) Inspect the inside of the cylinder to make sure the O-ring has
forced out of place during the cylinder installation procedure.

ASSEMBLY 61 ’1 0’14
 PROPELLER MAINTENANCE MANUAL
H19 RT Z E L L 114C

legend:
1. flexlock nut
2. push rod i,´•..
3. piston
4. fork B ’iii

5. sleeve
6. washer
7. cylinder ::B
8. O-ring
9, felt seal 1"7i
10. staking pin
11. O-ring
12. bushing 13
13. pitch change block
link screw
8

61

1110

Installing Piston and Cylinder

Figure 707

ASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1140

G. Installing PistonAssembly
Refer to Figure 707
I (1) Lubricate the piston O-ring (Il)with approved lubricant CM12 and
carefully install it in the groove provided for it in the piston (3).

1 Cut the n.ce.8ary length d fe f dust maisr al a~ soa~ n avlatian

(21 res

grade reciprocating engine oil.

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line with a smooth,
fuzz-free surface.

(3) Install the felt dust seal (9) in the groove provided for it in the cylinder (7).

(4) Install pitch change block (13) on each clamp link screw.

Install fork (4) on each pitch change block (13j with thick portion of fork
(5)
on side facing propeller assembly bench.
(6) Slide sleeve (5) into guide collar holes. The shoulder of the sleeve should
be on the side of the guide collar that faces away from the propeller
assembly bench.

thecylinder (7) and the push rods (5) through the

(7) Slide piston (3) over

forks, sleeves, and guide collar.

NOTE: It may be necessary to rotate the guide collar slightly to

achieve proper alignment with the fork, pitch change block, and
clamp link screw.

(8) Tighten guide collar clamping fasteners.

(9) Install washer (6) and locking nut (1) on the end of each push rod (2) and
I torque in accordance with Torque Values Table 802 in chapter 800.

fork pitch change block (13) and torque set

(4) with screw in
(10) Align
accordance with the Torque Values table in chapter 800.

Page 723
ASSEMBLY 61110114 Rev. 4 Jan/Ol
 PROPELLER MAINTENANCE MANUAL
H~ RTZ E L L 114e

W10313
APS0050A

~ec´• ~s

Reference blade
radius location
(Blade Face)

Blade Face

ri___l-----
Yellow Blade Angle
Reference Tape
CM160

Application of Blade Angle Reference Tape

Figure 708

9~,,,,,, 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

H. Application of Blade Angle Reference Tape

CAUTION: DO NOT CONFUSE REFERENCE BLADE RADIUS WITH

BLADE STATION. REFERENCE BLADE RADIUS AND BLADE
STATION OF THE SAME NUMBER MAY NOT ALWAYS
INDICATE THE SAME LOCATION ON THE BLADE.

Reference blade radius is measured from the center of the propeller hub to a
predetermined reference location on the blade for blade angle measurement.
Blade stations are used during the repair or overhaul process of a blade to define a
blade span location for dimensional measurement.

(1) Establish a reference blade radius location

(a) Refer to the Aircraft Type Certificate Data sheet, Supplemental

Type Certificate Data sheet, or the Hartzell Propeller Application
Guide, Manual 159 (61-02-59), for the reference blade radius
location specified for the applicable aircraft installation.

(b) Beginning with Blade One, measure from the center of the propeller
hub to the reference blade radius location specified. Refer to

Figure 708.

(C) Apply a yellow bladereference tape CM160 to the face side

angle
of the blade at the reference blade radius location, perpendicular to
the blade centerline. Refer to Figure 708.

NOTE: Place the reference tape CM160 so that the reference

blade radius location runs through the centerline of the
tape.
for the remaining blades in
(d) Repeat steps 2.H.(l)(b) and 2.H.(l)(c)
the hub assembly.

(e) Place a pattern cut-out over each blade angle reference tape
CM160 and spray the blade angle reference tape with clear lacquer
CM129 to prevent peeling.

~SEMBLY 61-10-14
 PROPEL"R
HARTZELL MPI~ANCE MANUP~

Bench Top Protractor

Riser Fixture TE48

Setting the Blade Angle

Figure 709

nssmnslY 61-10114
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1140

I i. Setting Blade Angle

not been
NOTE: At thisstage of assembly the outboard clamp bolts have
tightened because adjustments of blade angle may involve some
disassembly procedure.
(1) Apply 125 to 150 psi (8.62 to 10.34 bars) pressure to the piston through
the rotatable fixture on the propeller assembly table.
(2) Force the piston to full reverse or lowest pitch position.

(3) Use a hand-held benchtop protractor at the reference blade radius

or

specified in the Hartzell Propeller Application Guide, Manual 159

(61-02-59), to adjust the angle of the blades. Refer to Figure 709.

NOTE 1. When the lock nut and washer on the end of each piston push
the guide collar, the pitch change mechanism
rod are against
is at low pitch.

NOTE 2. Refer to the applicable Aircraft Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.
(4) Rotate the blades to low pitch position in the loose clamps.

of all blades must be within 0.2 degree of each

NOTE: The angle
other at low pitch or a floating pitch.
the outer clamp bolts. Refer to Torque Table 802 in
(5) Tighten the nuts on

Chapter 800.
Check to make that high pitch can be reached.
(6) sure

NOTE: Refer to the applicable Aircraft Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.

Page 727

ASSEMBLY 61110114 Rev. 4 JanlOl

 PROPELLER
HARTZELL MI:N~ANCE MANU~L

APS0216

Blade base

Red plastic O
tape O
--I It-
0.25 inch to
0.50 inch

Blade clamp

Providing for Visual Detection of Blade Slippage in Clamp

Figure 710

APSa2l0b

Fully assembled
propeller

Padded blade bar

close to blade shank

Using Padded Blade Bar to Check for Blade Slippage in Clamp

Figure 711

728
PISSEMBLY 61-10’14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

J. Providing for Visual Detection of Blade Slippage in Clamp

(Ij With the propeller still mounted the rotatable fixture of the assembly
on

table, proceed as follows to provide for visual detection of slippage

between the blade base and the blade clamp.

CAUTION: DO NOT USE A PUNCH OR SCRIBE A LINE ON THE BLADE

BASE. THIS COULD START A CRACK IN THE BLADE.

(a) When the correct pitch has been established in each blade, place
a strip of red plastic tape down the base and across
the clamp of

blade number one as shown in Figure 710.

Carefully slit the tape along the line where the blade and blade
(b)
clamp meet.
(c) Spray the pieces of tape with lacquer so cleaning solvent will not

wash them off.

(d) Repeat this procedure on the other blade assemblies.

CAUTION: DO NOT PLACE THE PADDED BLADE BAR IN THE AREA

OF THE DE-ICE BOOT WHEN TORQUING A BLADE
ASSEMBLY. PLACE THE BAR IN THE THICKEST AREA
OF THE BLADE, JUST OUTBOARD OF THE DE-ICE
BOOT. USE ONE BLADE BAR PER BLADE.

(e) Use apadded blade bar (Figure 711) to apply torque to each
blade assembly per the Torque Values Table in the Fits and
Clearances chapter of this manual. Torque blade toward reverse.

(f) Recheck blade angles per the instructions in this chapter.

(g) If necessary to correct blade slippage, refer to the Blade Clamp

Overhaul chapter of Hartzell Standard Practices Manual 202A
(61-01-02).

Page 729

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Sealant CM93 Application

I FI4ure712

NOTE: Blade height at the tips

should not vary more than

1 0.125 inch (3.18 mm).

Propeller mounted on assembly table

Height gauge with adjustable pointer

Checking Blade Track

I Flgure713

ASBEMBLy 61-10-14
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 1149

K. Sealant CM93 Application

The application of sealant CM93 to the blade/blade clamp interface is an optional
blade
procedure that may provide additional protection against corrosion of the
retention components.

CAUTION 1 TO AVOID PERMAN ENT DAMAG E TO TH E BLADE RETENTION

COMPONENTS CAUSED BY TRAPPED CHEMICALS, THIS
PROCEDURE MUST ONLY BE PERFORMED FOLLOWING THE
ASSEM BLY OF A PROPELLE R AFTER OVE RHAU L OR AFTE R ANY
OTHER PROCEDURE INVOLVING DISASSEMBLY AND CLEAN I NG
OF THE PROPELLER BLADE RETENTION COMPONENTS.

CAUTION 2: TO ASSURE PROPER ADHESION OF SEALANT CM93, BLADE

AND BLADE CLAMP SURFACES MUST BE FREE OF GREASE
AN D D I RT.

(1 After performing the check for blade slippage in the clamp, fill the external void at
the blade/blade clamp interface with a(6.35 mm) maximum bead of
0.25 inch
sealant CM93, around the entire circumference of blade, as shown in Figure 712.

(2) Allow the sealant to cure for a minimum of two hours, before returning the propeller
to sewice.

NOTE: Do not allow the sealant CM93 to extend onto the surface of the clamp,
where balance weights and de-ice hardware are installed.

L. Checking BladeTrack
(1 Mount the propeller on a rotatable fixture and check the height at the tip
centerpoint of the highest blade, using a scale with at least. 1/32 inch (0.79 mm)
divisions and adjustable pointer, as shown in Figure 713.

(2) Rotate the propeller and measure the variation of each blade.

NOTE: Blade height at the tips should not vary more than 0.125 inch (3.18 mm).

E6SEUBLY 61-10-14
 PROPELLER
HARTZELL MI:N~NANtE MINU~L

I M. Decal Replacement
(1) All CAUTION decals, informational decals, and identification decals on the
propeller assembly must be replaced after overhaul or major repair.
(2) Refer to the
appropriate Hartzell blade overhaul manual for blade decal
replacement instructions.
(3) If applicable, apply Warning Decal Part No. WAR-001 to the engine-side of the
bulkhead (Figure 71 4).
N. Propeller Removal from Assembly Table
(1 Remove the propeller from the rotatable fixture on the propeller assembly table.
(2) Install the spinner bulkhead as applicable.

(3) Place the propeller on a propeller cart for transportation.

APS5020

\N A R N I N G
fH1S PROPELLER HAS
BEEN DYNAMICALLV
gALANCED.
Nn WAR´•OO1

Apply to bulkhead unit.

Warning Decal Part No. WAR-001 for Dynamically Balanced Propeller

Figure714

ASSEMBLY 61’10’14 RevP4aSJean:~:

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

-1 Series.
3. Assembly of Two-Blade. Splined-Hub Models in the

Except HA-A2(V.MV) 20-1B

A. Hub UnitAssembly
Follow the pilot tube installation procedure in the Steel Hub Overhaul
(1)
chapter of Hartzell Standard Practices Manual 202A.

(2) Mount hub on the splined shaft of a rotatable fixture of a propeller

assembly table.

Thread hub nut and puller ring onto rotatable fixture to secure hub.
(3)

Use hub nut and puller ring that will go with the propeller when
NOTE:
mounted on an engine.
B. Installing GuideCollar
Position two pieces of guide collar bracket around center shaft of hub
(1)
between blade arms and propeller assembly table.

NOTE: Make sure that the correct side of the guide collar is facing the
hub. Spot faces for push rod locking nut and washer to seat

must face toward table.

Install two socket head cap screws (A-2038-12) loosely into guide collar.
(2)
shoulder hub next to blade arms and
(3) Position guide collar up against on

tighten

NOTE: Guide collar may need to be repositioned later to properly

align with piston push rods.
C. Blade Mounting Parts Assembly

(1) Follow "Blade Mounting Assembly" procedure described for

Parts
of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
I this chapter."As embly
D. Assembling Clamp and Counterweight
(1) Refer to Clamp Overhaul chapter of Hartzell Standard Practices Manual
202A.
the back of the
(2) After eachclamp and counterweight is assembled, peen
oounterweight flush against the clamp half.
E. Installing BladesandClamps
(1) Follow "lnstalling Blades and Clamps" procedure described for "Assembly
Lhis
Flanged-Hub Modsis in the -I and -6 Ser as’ n

Page 733

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

F. Installingthe Cylinder
(1) Follow "lnstalling the Cylinder" procedure described for "Assembly of Two-
Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
G. Installing PistonAssembly
Refer to Figure 707
I (1) Lubricate the piston O-ring (Il)with approved lubricant CM12 and
carefully install it in the groove provided for it in the piston (3).
Cut the necessary
I (2) length of felt dust
grade reciprocating engine oil.
seal material and soak it in aviation

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line with a smooth,
fuzz-free surface.

(3) Install the felt dust seal (9) in the groove provided for it in the cylinder (7).

I
(4) Slide the A-970-( spacer (not shown) onto each sleeve (5), against the
shoulder of the sleeve.

(5) Slide the sleeve (5) with the A-970-() spacer (not shown) into the guide
collar holes.

NOTE: The shoulder of the sleeve and A-970-( spacer should be on

the side of the guide collar facing away from the propeller
assembly bench.

(6) Install the pitch change block (13) on each clamp link screw.

(7) Install the fork (4) on each pitch change block (t 3), with the thick portion
of the fork on the side facing the propeller assembly bench.
(8) Slide the piston (3) over the cylinder (7) and the push rods (5) through the
forks, sleeves, spacers, and guide collar.

NOTE: It may be necessary to rotate the guide collar slightly to

achieve proper alignment with the fork, pitch change block, and
clamp link screw.
(9) Tighten the guide collar clamping fasteners.
(10) Install the washer (6) and locking nut (1) on the end of each push rod (2)
and torque in accordance with Torque Values Table 802 in chapter 800.
(11) Align the fork (4) with the pitch change block (13) and torque the set
screw in accordance with Torque Values Table 802 in chapter 800.
i-i. Application of Blade Angle Reference Tape
(1) Follow "Application of Blade Angle Reference Tape" described for
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
this chapter.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

i I. Setting Blade Angle

(1) Follow "Setting Blade Angle" procedure described for "Assembly of Two-
Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
J. Providing for Visual Detection of Blade Slippage in Clamp

(1) Follow "Providing for Visual Detection of Blade Slippage in Clamp"

described for "Assembly of Two-Blade, Flanged-Hub Models in the -1 and
-6 Series" in this chapter.

K. Sealant CM93 Application

(1) Follow "Sealant CM93 Application" described for "Assembly of Two-
Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
L. Checking BladeTrack
(1) Follow "Checking Blade Track" described for "Assembly of Two-Blade,
Flanged-Hub Models in the -1 and -6 Series" in this chapter.
I M. Decal Replacement
(1) Follow "Decal Replacement"described for "Assembly of Two-Blade,
Flanged-Hub Models in the -1 and -6 Series" in this chapter.

N. PropellerRemoval FromAssemblyTable
(1) Remove the locking nuts and washers from the ends of the piston push
rods and keep them with the propeller.
Remove the piston from the propeller. Rotation of the blades and piston
(2)
will be necessary.

the ends of the push rod

locking nuts and washers from

I
NOTE 1: The
must be kept with the propeller.

NOTE 2: Tape the sleeves and A-970-( spacers on the piston push
rods to keep them from falling off and becoming lost before
the propeller is installed on the engine.

(3) Remove the pitch change blocks.

NOTE: Pitch change blocks, piston and guide collar must be identified
to ensure proper orientation and installation with the correct
clamp when the propeller is installed on the engine.

(4) Remove the propeller from the rotatable fixture on the propeller assembly
table. Use special tool TE146 on the hub nut.

NOTE: The hub nut and puller ring will remain with the propeller held

between the hub and the cylinder.

(5) Install the spinner bulkhead, as applicable.

(6) Place the propeller on a propeller cart for transportation.

Page 735
~ZSSEMBLY 61 -10-14 Rev. 4 Jan/Ol
 PROPELLER M*NUAL
HARTZELL

4. Assembly of Three-Blade. Splined-Hub Models in the -1 series

A. Hub UnitAssembly
(1) Follow the pilot tube installation procedure in the Steel Hub Overhaul
I chapter of Hartzell Standard Practices Manual 202A (61-01-02).
B. Installing Hub Unitand Spinner Bulkhead
(1) Mount the spinner bulkhead on the rotatable fixture of a propeller
assembly table.

1 (2) Install the rear cone and mount the hub on the splined shaft of a rotatable
fixture of a propeller assembly table.
1 (3) Thread the hub nut and puller ring onto the rotatable fixture to secure the
hub.

I NOTE: Use the hub nut and puller ring that will go with the propeller
when mounted on an engine.

C. Blade Mounting Parts Assembly

(1) Follow "Blade Mounting Parts Assembly" procedure described for

I this chapter."As embly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in

D. Assembling Clamp and Counterweight

(1) Refer to Clamp Overhaul chapter of Hartzell Standard Practices Manual
I 202A (61-01-02),
(2) After eachclamp and counterweight is assembled, peen the back of the
counterweight flush against the clamp half.
E. Installing Bladesand Clamps
(1) Follow "lnstalling Blades and Clamps" procedure described for "Assembly

I of Two-Blade,
chapter.
Fianged-Hub Models in the -1 and -6 Series" in this

F. Installingthe Cylinder
(1) Follow "lnstalling the Cylinder" procedure described for "Assembly of Two-
I Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
G. Installing PistonAssembly
Refer to Figure 707.
I (1) Lubricate the piston O-ring (11) with approved lubricant CM12 and
carefully install it in the groove provided for it in the piston (3).

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

Cut the necessary length of felt dust seal material and soak it in aviation
(2)
grade reciprocating engine oil.

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line
with a smooth,
fuzz-free surface.

(3) Install the felt dust seal (9) in the groove provided for it in the cylinder (7).

(4) Slide the A-970-( high pitch stop spacer (not shown) on the sleeve (5),
against the shoulder of the sleeve.

NOTE: The high stop spacer length is selected to suit high pitch
requirements. The correct spacer should have been with the
propeller when it was disassembled.
(5) Slide the sleeve (5) A-970-() high stop spacer into the bulkhead
with the

I holes. The shoulder of the sleeve and the A-970-(

should be on the side of the bulkhead facing away
high stop spacer
from the propeller

assembly bench.
Install the pitch change block (13) on each clamp link screw.
(6)

I (7)

(8)
Install the fork
of the fork

Slide the
on
(4) on

the side
each pitch change block (13), with the thick portion
facing the propeller assembly bench.
piston (3) over the cylinder (7) and the push
forks, sleeves, high stop spacers, and bulkhead.
rods (5) through the

NOTE: It may be necessary to rotate the guide collarslightly to

achieve proper alignment with the fork, pitch change block, and
clamp link screw.

(9) Install the washer (6) and locking nut (1) on the end of each push rod (2)
and torque in accordance with Torque Values Table 802 in Chapter 800.

(10) Align the fork (4) with the pitch change block (13) and torque the set
screw in accordance with Torque Values Table 802 in Chapter 800.
H. Application of Blade Angle Reference Tape

(1) Follow "Application Angle Reference Tape" described for

of Blade
Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
"Assembly of
this chapter.

i. Setting Blade Angle

(1) Follow"Setting Blade Angle" procedure described for "Assembly of Two-

Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.

NOTE: A-970-( high stop length is selected to obtain the correct

high pitch. The correct length should have been previously
installed.

Page 737

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MINUAL
nARTZELL

J. Providing for Visual Detection of Blade Slippage in Clamp

(1) Follow "Providing for Visual Detection of Blade Slippage in Clamp"
described for "Assembly of Two-Blade, Flanged-Hub Models in the -1 and
-6 Series" in this chapter.

K. Sealant CM93 Application

(1) Follow "Sealant CM93 Application" described for "Assembly of Two-
Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
L. Checking BladeTrack

(1) Follow"Checking Blade Track" described for "Assembly of Two-Blade,

Flanged-Hub Models in the -1 and -6 Series" in this chapter.
M. Decal Replacement
(1) Follow "Decal Replacement" described for "Assembly of Two-Blade,
Flanged-Hub Models in the -1 and -6 Series" in this chapter.

N. PropellerRemoval FromAssemblyTable
(1) Remove the locking nuts and washers from the ends of the piston push
rods, and keep them with the propeller.

(2) Remove the piston from the propeller. Rotation of blades and piston will
be necessary.

NOTE 1: Locking nuts and washers from the ends of the push rod must
be kept with the propeller.

NOTE 2: Tape the sleeves and A-970-( high stop spacers on the push
rods to keep them from falling off and becoming lost before
the
I (3) Remove the
propeller is installed
pitch change blocks.
on the engine.

NOTE: Pitch change blocks must be identified to ensure

proper
orientation and installation with the correct clamp when the
propeller is installed on the engine.
(4) Remove the propeller from the rotatable fixture on the propeller assembly
table. Use special tool TE146 on the hub nut.

NOTE: The hub nut and puller ring will remain with the propeller, held
between the hub and the cylinder.

(5) Remove the bulkhead from the rotatable fixture.

(6) Place both the propeller and bulkhead on a propeller cart for
transportation.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 114C

5. Assembly of HA-A2(V.MV~ 20-1B

A. Hub UnitAssembly
Follow the pilot tube installation procedure in the Steel Hub Overhaul
(1)
chapter of Hartzell Standard Practices Manual 202A.

(2) Mount the hub the splined shaft of a rotatable fixture of a propeller
1 on

assembly table.
Thread the hub nut and puller ring onto the rotatable fixture to secure the
1 (3)
hub.

I NOTE: Use the hub nut and puller ring that will go with the propeller
when mounted on an engine.

B. Blade Mounting Parts Assembly

Parts Assembly" procedure described for
(1) Follow "Blade Mounting
of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
I this chapter."As embly
C. Assembling Clamp and Link Arms

Refer to the Blade Clamp Overhaul Chapter of Hartzell Standard Practices

(1)
Manual 202A (61-01-02).
(2) After each clamp is assembled:

(a) Peen the back of the countenrueight flush against the clamp-half.

CAUTION: A LINK ARM CANNOT BE INSTALLED ON THE CLAMP-

HALF AFTER THE CLAMP HAS BEEN INSTALLED ON
THE HUB.

I (b) Install the link screw sleeve in the large hole of the link arm.

(c) Fit the link arm onto the link screw.

NOTE: The raised shoulder on the link arm must face outboard,
toward the clamp.
Push the sleeve cotter pin through the hole in the end of the link
(d)
screw.

(e) Open the cotter pin to safety it.

I
NOTE: The link arm should move freely on the link screw.

and
I (f) Repeat these assembly procedures for the other clamps
counterweights.

Page 739

nssEAnsLv 61110-14 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

D. Installing Blades and Clamps

(1) Follow "lnstalling Blades and Clamps" procedure described for "Assembly

I of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in this

chapter.

NOTE: No counterweight is installed. References to counterweight do

not apply.
E. Installingthe Cylinder
(1) Follow "lnstalling the Cylinder" procedure described for "Assembly of Two-
I Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
F. Assemblyof Pitch AdjustmentAssembly
(1) Insert A-1941 retainer into the B-364 mushroom through the inside bore.

(2) Thread the B-6670-A8 socket head set screw into the 8-364 mushroom,
and lock the A-1941 retainer fully against the mushroom shoulder.

(3) Thread the A-880-1 lock nut onto the A-1941 retainer and tighten the nut
against the 8-364 mushroom with 100 Ft-Lb torque.
(4) Thread the B-1942 pitch change rod into the pitch adjustment assembly,
with the threaded end facing toward the piston to be installed later.

G. Installing Pitch AdjustmentAssembly

I (1) Insert the shoulder of the

inch into the cylinder,
pitch adjustment assembly about 0.25 (6.35 mm)
and insert the split rings into the groove in the
cylinder.

I (2) Place the plate (round ring) over the pitch adjustment assembly shoulder
and split rings. Make sure that the pitch adjustment assembly is tight
against the split rings to keep them from sliding out of the groove in the
cylinder.
1 (3) Insert the through the plate
screws and tighten them into the pitch
adjustment assembly shoulder.

I NOTE: The screws

installed on
will be
the
safety
engine.
wired together after the propeller is

H. Installing PistonAssembly
I (1) Lubricate the piston O-ring with approved lubricant CM12 and install it in
the groove provided for it in the piston (groove closest to bushing).
Installation of this is optional, as no oil needs to be sealed in the
propeller.

I (2) Cut the necessary length of felt

grade reciprocating engine oil.
dust seal material and soak it in aviation

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line with a smooth,

fuzz-free su~face.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1140

(3) Install the felt dust seal (9) in the groove provided for it in the cylinder
(groove closest to the opening of the cylinder).

I (4) Install the

NOTE:
O-ring

in the
on the pitch change

Installation of this part is

propeller.
rod.

optional, as no oil needs to be sealed

(5) Slide the piston onto the cylinder and slide the pitch change rod through
the hole in the piston.

(6) Thread the locking nut onto the pitch change rod, but do not tighten.

(7) Attach the link arms to the piston ears with link pin units and safety
screws.

NOTE: The link pin screw andsafety screws will be safety wired
together when the propeller is installed on the engine.
i. Application of Blade Angle Reference Tape
(1) Follow "Application of Blade Angle Reference Tape" described for
in
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series"
this chapter.

J. Setting Blade Pitch

(1) Rotate the pitch change rod completely into the pitch adjustment
assembly, and then back out about one inch (25.4 mm).

(2) Tighten the lock nut on the pitch change rod against the piston.

(3) Use hand-held bench-top protractor at the reference blade radius

or

specified in the Hartzell Propeller Application Guide, Manual 159 (61-02-

59), to adjust angle of the blades. Refer to Figure 709.

NOTE 1: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.

NOTE 2: The blade angle of all blades must be within 0.2 degree of

I (4)
(5)
each other at the selected

Rotate the blades to the desired

Tighten the nuts on the

802 in Chapter 800.
outer
pitch
pitch.
in the loose

clamp bolts. Refer to

clamps.
Torque Values Table

K. Providing for Visual Detection of Blade Slippage in Clamp

I (1) Follow "Providing for Visual Detection of Blade Slippage in Clamp"
described for "Assembly of Two-Blade, Flanged-Hub Models in the -1 and
1 -6 Series" in this chapter.

Page 741

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MANUPIL
HARTZELL

L. Sealant CM93 Application

(1) Follow "Sealant CM93 Application" described for "Assembly of Two-

Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
M. Checking Blade Track

(1) Follow"Checking Blade Track" described for "Assembly of Two-Blade,

Flanged-Hub Models in the -1 and -6 Series" in this chapter.
N. Decal Replacement
(1) Follow "Decal Replacement" described for "Assembly of Two-Blade,
Flanged-Hub Models in the -1 and -6 Series" in this chapter.
O. Propeller Removal From Assembly Table
(1) Remove the link screws and the screws holding the link arms.

(2) Disconnect the link arms from the piston.

(3) Remove the lock nut on the pitch change rod.

(4) Remove the piston.

(5) Remove the pitch adjustment assembly from the cylinder.
(6) Remove the propeller from the rotatable fixture on the propeller assembly
table. Use special tool TE146 on the hub nut.

NOTE: The hub nut and puller ring will remain with the propeller, held
between the hub and the cylinder.

(7) Place the propeller on a propeller cart for transportation.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
nA RTZ E L L 114C

6. Assembly of Flanaed-Hub Models in the HC-A( )(F.K.L)-2 Series

A. Hub UnitAssembly
Follow the pilot tube installation procedure in the Steel Hub Overhaul
(1)
chapter of Hartzell Standard Practices Manual 202A (61-01-02).
B. BladeMounting PartsAssembly
(1) Follow "BladeMounting Parts Assembly" procedure described for
in
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series"

I (2)
this chapter.

Mount the hub on the rotatable fixture of a propeller assembly table.

C. Assembling Clamp and Link Arms

Refer to the Blade Clamp Overhaul Chapter of Hartzell Standard

(1)
I Practices Manual 202A (61-01-02).
(2) After each clamp is assembled:

(a) Peen the back of the counterweight flush against the clamp-half.

CAUTION: A LINK ARM CANNOT BE INSTALLED ON THE CLAMP-

HALF AFTER THE CLAMP HAS BEEN INSTALLED ON
THE HUB.

(b) Install the link screw sleeve in the large hole of the link arm.

(c) Fit the link arm onto the link screw.

NOTE: The raised shoulder on the link arm must face outboard,
toward the clamp.

(d) Push the sleeve cotter pin through the hole in the end of the link
screw.

(e) Open the cotter pin to safety it.

I
NOTE: The link arm should move freely on the link screw.

for the other clamps and

I (f) Repeat these assembly procedures
counterweights.
(g) Install the stop plate on the inboard surface of the clamp half
without a counterweight. Use two hex head bolts or screws, as
applicable. Safety wire the fasteners together.

NOTE: Washers sometimes installed between the stop

are

plate and clamp to reposition the stop plate for

improved fit with the start lock used.

Page 743

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPEL"R
HARTZELL M*:F~PINCE MANUAL

D. Installing BiadesandClamps
(1) Follow "lnstalling Blades and Clamps procedure described for "Assembly

I of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in

.retpahcsiht
E. Installing the Cylinder land Guide Collar, as Applicable)

NOTE: A guide collar is installed on three-blade propellers in this series, but not on
two-blade propellers.

WARNING: DO NOT INSTALL A GUIDE COLLAR ON TWO-BLADE

PROPELLERS OF THIS MODEL SERIES. FOR TWO-BLADE
PROPELLERS, IGNORE STATEMENTS THAT DESCRIBE HOW
TO INSTALL A GUIDE COLLAR. GUIDE COLLAR
INSTRUCTIONS APPLY ONLY TO THREE-BLADE PROPELLERS
OF THIS MODEL SERIES.

(1) Install the socket head cap screw into the guide collar.

CAUTION: MAKE SURE THAT THE CHAMFER OF THE GUIDE COLLAR IS

FACING THE CYLINDER SHOULDER AND THAT THE LARGER
INSIDE DIAMETER OF THE GUIDE COLLAR IS FACING AWAY
FROM THE CYLINDER FOR HUB CLEARANCE.

(2) Install the guide collar onto the smaller diameter shoulder of the cylinder.
Do not tighten the guide collar, but allow it to rotate on the cylinder to
facilitate installation on the hub.

(3) Clean the threads on the hub and cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER.

(4) Apply a bead of

hydraulic sealant adhesive CM134 in the groove of the
hub where the cylinder O-ring will fit. Install the O-ring into

I
the cylinder
chamfer, facing the hub.
(5) Hand screw the cylinder onto the hub unit (with guide collar, if installed).
(6) Usea square bar of appropriate size to fit the slot provided for it in the

top of the cylinder, and torque the cylinder against the hub spider unit
(see Torque Values Table 802 in Chapter 800).

NOTE: Tighten the cylinder flush with the shoulder on the hub. Early
drag and tightness is caused by the O-ring, which acts as a
seal and safety.

(7) Inspect
the slot in the top of the cylinder to make sure the square-bar
wrench used for torquing did not raise any sharp edges or damage the
threads.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HA RT Z E LL 114C

(8) Remove any sharp edges in the wrench slot on top of the cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER. HYDRAULIC SEALANT ADHESIVE IN THE
CYLINDER MAY CONTAMINATE THE AIRCRAFT ENGINE OIL.
not been
(9) Inspect the inside of the cylinder to make sure the O-ring has
forced out of place during the cylinder installation procedure.

F. Feathering Spring Assembly

(1) Slide the front spring retainer (mushroom) onto the pitch change rod, with

I (2)
the flat plate portion facing the threaded end of the pitch change rod.
Slide the spacer tube onto the
retainer (mushroom).
pitch change rod against the spring

1 the spacer tube and against the front spring retainer

(3) spring
Slide the over

(mushroom).
(4) Install the spring retainer and split ring using special fixture TE59 to
rear

I compress the springs and allow insertion

of the pitch change rod.
of the split rings into the groove

G. Feathering Spring Assembly Installation

(1) Insert the shoulder of the front spring retainer (mushroom) approximately
0.25 inch (6.35 mm) into the cylinder, and insert the split rings into the
groove in the cylinder.
retainer (mushroom) against the split ring to hold it
(2) Slide the front spring
in place.
1 (3) Install the feathering stop plates ("L" cross section) with two screws per

plate.

I NOTE 1: The height of the feathering stop plates will determine the
propeller feathering blade angle. A higher feathering stop plate
will result in a lower feather blade angle, and a lower plate will
result in a higher feather blade angle.

NOTE 2: Reuse the feathering stop plates that were removed during
disassembly. They should have the correct feathering stop
plate height.
1 (4) Safety the feathering stop plate screws.

Page 745

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MANUAL
HARTZ ELL

H. Installing PistonAssembly

I
(1) Lubricate the O-ring with approved lubricant CM12 and install it on the
pitch change rod in the groove provided for it.
(2) Lubricate the piston O-ring with approved lubricant CM12 and carefully
install it in the groove provided for it in the piston.

I (3) Cut the necessary length of felt

grade reciprocating engine oil.
dust seal material and soak it in aviation

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line with a smooth,

fuzz-free surface.

(4) Install the felt dust seal in the groove provided for it in the piston.
(5) Slide the piston into place over the cylinder.

NOTE 1: Piston guide rods are only installed on three-blade propellers

of this model series and not on two-blade propellers of this
model series.

NOTE 2: The guide rod is not removed from the piston during overhaul
unless it is damaged or some other condition warrants its
removal

(6) Align the piston guide rods, where applicable, with the holes provided for
them in the guide collar unit.

(7) Install the free end of each link arm in the slot provided in the piston.

I (8)

CAUTION:
Install all link pin units.

ENSURE THE PROPER SAFETY SCREW IS INSTALLED AND

THAT ADEQUATE THREADS ARE AVAILABLE IN THE PISTON

I UNIT TO HOLD THE SCREW IN PLACE. AT LEAST THREE

THREAD LENGTHS ARE SUFFICIENT. DO NOT BIND THE LINK
ARM.

(9) Actuate the propeller assembly by hand to make sure the propeller beta
rods, where applicable, are straight and that the piston moves freely.
(10) Make sure the guide collar unit is seated solidly against the cylinder at
the correct radial location.

NOTE: If necessary, shift the guide collar unit radially to provide the
correct alignment between the piston and the guide rods,
where applicable.

(11) When the necessary alignment is confirmed, use an Alien wrench with
torquing adapter to tighten the Nylock socket head cap screw in the guide
collar unit. Torque in accordance with Torque Values Table 802 in the Fits
and Clearances Chapter of this manual.

ASSEMBLY 61’10’14 F~evP4aSJean:;tf)

 PROPELLER MAINTENANCE MANUAL
nARTZ E LL 114C

(12) Move the piston into full feathered position (back against the hub
I assembly) so the threaded end of the pitch change rod protrudes through
the end of the piston.
flexlock nut onto the end of the pitch change rod.
(13) Thread the large
Use wrench the nut and socket on the rod to torque the
pitch change
(14) a on

nut in accordance with Torque Values Table 802 in the Fits and
Clearances chapter of this manual.

Install the socket head cap screw, washer(s) and check nut on the end of
(15)
each piston guide rod.

i. Start Lock Unit Reassembly

(1) Insert the pin into the start lock bracket.

I (2)
(3)
Insert the

Compress
the cotter
spring
the
pin
bracket. Secure the cotter
into start lock bracket,

spring, install
into the bracket to
pin.
the washer
against
on
the pin.
top of the spring, and insert
retain the washer, spring, and pin in the

J. StartLockUnit Installation

(1) Attach each start lock unit tone per blade) with two bolts to the propeller
hub flange.
the pins and hold them in place with wire inserted in the hole in
(2)
I the brackettcarteR.ydob
NOTE 1: Pins will be released later for adjustment of start lock angle.
Pins are now retracted to aid assembly.

NOTE 2. On "F" flange propellers of this model series, the spinner

bulkhead attaches to the start lock unit. On "L" and "K" flange
propellers, the bulkhead is a ring that attaches to the engine
starter ring gear.
K. Application of Blade Angle Reference Tape
for
(1) Follow"Application of Blade Angle Reference Tape" described
Series" in
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6
this chapter.

Page 747

ASSEMBLY 61~10114 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

I L. Setting BladeAngle

NOTE: At this
stage of assembly the outboard clamp bolts have not been tightened
because adjustments of blade angle may involve some disassembly
procedure.
(1) Apply 125 to 150 psi (8.62 to 10.34 bars) pressure to the piston through
the rotatable fixture on the propeller assembly table.
(2) Force the piston to lowest pitch position.
(3) Use bench-top protractor at the reference blade radius specified in the
a

Hartzell Propeller Application Guide, Manual 159 (61-02-59), to adjust the

angle of the blades. Refer to Figure 709.

NOTE: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.
(4) Rotate the blades to low pitch position in the clamps.

I (5)
NOTE: Blade

Tighten the nuts on the

802 in Chapter 800.
angle
other at low
of all blades must be within 0.2
pitch.
outer clamp bolts. Refer to
degree of each

Torque Values Table

(6) Check the angle of each blade and verify that the maximum blade angle
I variance between blades is 0.2 degree. If it is not, reset the blades in the
clamps.
1 (7) Remove the air from the propeller piston and allow the pitch change
mechanism to reach feather position.

I (8) Use bench-top protractor at the reference blade radius specified in the
a

Hartzell Propeller Application Guide, Manual 159 (61-02-59), to check

feather blade angle.

NOTE 1: Refer to theapplicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.

NOTE 2: If the feather angle is incorrect, the

piston will need to be
removed and different height feathering stops will need to be
installed. A higher feathering stop will reduce feather blade
angle and a lower feathering stop will increase feather blade
angle.
1 (9) Apply air pressure toward high pitch.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(10) Remove the link pins and disengage the link arms.

(11) Rotate the clamps by hand.

(12) Release the pins in the start lock brackets to allow them to engage the
start lock plates on the inboard side of clamps.

(13) Use a bench-top protractor at the reference blade radius specified in the
Hartzell Propeller Application Guide, Manual 159 (61-02-59), to check the
start lock blade angle.

(14) File the start lock plates to adjust start lock angle if necessary.

NOTE: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.
(15) Install the link pin units, safety screws.

(16) Using CM131, safety wire the screws.

M. Providing for Visual Detection of Blade Slippage in Clamp

Follow"Providing for Visual Detection of Blade Slippage in Clamp" described for
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
N. Sealant CM93 Application
Follow "Sealant CM93 Application" described for "Assembly of Two-Blade, Flanged-
Hub Models in the -1 and -6 Series" in this chapter.

O. Checking Blade Track

Follow "Checking Blade Track" described for "Assembly of Two-Blade, Flanged-Hub
Models in the -1 and -6 Series" in this chapter.
P. Decal Replacement
Follow "Decal Replacement" described for "Assembly of Two-Blade, Flanged-Hub
Models in the -1 and -6 Series" in this chapter.
Q. PropellerRemoval FromAssemblyTable
(1) Unfasten the bolts that hold the propeller hub to the rotatable fixture of the
propeller assembly table.

~2) Remove the propeller assembly and place it on a propeller cart for

transportation.
(3) Attach the spinner bulkhead to the start locks, as applicable.

NOTE: On "F" flange propellers of this model series, the spinner

bulkhead attaches to the start lock units. On "L" and "K" flange
propellers the bulkhead is a ring that attaches to the engine
starter ring gear.

~SEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

7. Assembly of Splined-Hub Models in the -2 Series

A. Hub UnitAssembly
(1) Follow the pilot tube installation procedure in the Steel Hub Overhaul
I chapter of Hartzell Standard Practices Manual 202A (61-01-02).
B. BladeMounting PartsAssembly
(1) Follow "Blade Mounting Parts
Assembly" procedure described for

I "Assembly
thischapter.
of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in

C. Spinner Bulkhead and Start Lock Assembly

(1) Insert the pin into the start lock bracket.

(2) Insert the spring into the start lock bracket against the pin.
(3) Compress the spring and install the washer on top of the spring. Insert
the cotterpin into the bracket to retain the washer, spring, and pin in the
bracket. Secure the cotter pin.

(4) Install the spinner bulkhead onto the rotatable fixture of a propeller
assembly table.

(5) Install the onto the rotatable fixture of propeller assembly

I
rear cone a

table, against the spinner bulkhead.

(6) Install the two or three (equal to the number of blades) start lock units
onto the spinner bulkhead with bolts, nuts, and washers.
(7) Retract thepins and hold them in place with wire inserted in the hole in
bracket body.

NOTE: Pins will be released later for adjustment of start lock angle.
Pins are now retracted to aid assembly.
I CAUTION: BE SURE TO INSTALL THE REAR CONE BETWEEN THE HUB
AND SPINNER BULKHEAD.

(8) Mount the hub the rotatable fixture of propeller assembly table. Use

I
on a

tool TE146 to tighten the hub nut.

NOTE
:special Use the hub nut and puller ring that will be used to mount the
propeller on the engine.

ASSEIWBLY 61-10’14
 PROPELLER MAINTENANCE MANUAL
H ~A RT Z E L L 114C

D. Assembling Clamp and Counterleight

I (1) Refer to the Blade Clamp Overhaul Chapter of Hartzell Standard
Practices Manual 202A (61-01-02).
(2) After each clamp and counterweight is assembled:

(a) Peen the back of the counterweight flush against the clamp-half.

CAUTION: A LINK ARM CANNOT BE INSTALLED ON THE CLAMP-

HALF AFTER THE CLAMP HAS BEEN INSTALLED ON
THE HUB.

(b) Install the link screw sleeve in the large hole of the link arm.

(c) Fit the link arm onto the link screw.

NOTE: The raised shoulder on the link arm must face outboard,

I clamp.
toward the

(d) Push the sleeve cotter pin through the hole in the end of the link
screw.

(e) Open the cotter pin to safety it.

NOTE: The link arm should move freely on the link screw.

(f) Repeat these assembly procedures for the other clamps and
I
counterweights.
(g) Install the stop plate on the inboard surface of the clamp half
without a counterweight. Use two hex head bolts.

(h) Safety wire the fasteners together.

E. Installing Blades and Clamps
(1) Follow "lnstalling Blades and Clamps" procedure described for "Assembly
Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
I of
.retpahcsiht
F. Installing the Cylinder and Guide Collar
(1) Install the socket head cap screw into the guide collar.

(2) Install the guide collar onto the smaller diameter shoulder of the cylinder.
Do not tighten the guide collar, but allow it to rotate on the cylinder to
facilitate installation on the hub.

CAUTION: MAKE SURE THAT THE CHAMFER OF THE GUIDE COLLAR IS

FACING THE CYLINDER SHOULDER AND THAT THE LARGER
INSIDE DIAMETER OF THE GUIDE COLLAR IS FACING AWAY
FROM THE CYLINDER FOR HUB CLEARANCE.

NOTE: Splined-hub models have the hub nut and puller ring installed in
the hub before the cylinder is installed.

~SEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 114C

(3) Clean the threads on the hub and cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER.

(4) Apply a bead of

hydraulic sealant adhesive CM134 in the groove of the
hub where the cylinder O-ring will fit. Install the O-ring into the cylinder

I (5)
chamfer, facing the hub.
Hand screw the cylinder onto the hub unit.

(6) Use square bar of appropriate size to fit the slot provided for it in the
a

top of the cylinder, and torque the cylinder against the hub unit (see
Torque Values Table 802 in Chapter 800).

NOTE: Tighten the cylinder flush with the shoulder on the hub. Early
drag and tightness is caused by the O-ring, which acts as the
seal and safety.

(7) Inspectthe slot in the top of the cylinder to make sure the square-bar
wrench used for torquing did not raise any sharp edges or damage the
threads.

(8) Remove any sharp edges in the wrench slot on top of the cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER. HYDRAULIC SEALANT ADHESIVE IN THE
CYLINDER MAY CONTAMINATE THE AIRCRAFT ENGINE OIL.

(9) Inspect the inside of thecylinder to make sure the O-ring has not been
forced out of place during the cylinder installation procedure.
G. Feathering SpringAssembly
(1) Slide A-2010 spacer and
one one A-6027 spacer onto the pitch change
rod for HC-A3V20-2A only.

(2) Slide the front

I
spring retainer (mushroom) onto the pitch change rod with,
the flat plate portion facing the threaded end of the pitch change rod.

(3) Slide the

spring over the pitch change rod and front spring retainer
(mushroom).

I
(4) Install the rear spring retainer and split ring, using special fixture TE59 to
compress the springs and allow insertion of the split rings into the groove
of pitch change rod.

H. Feathering SpringAssembly Installation

(1) Insert the shoulder of front spring retainer (mushroom) approximately 0.25
inch (6.35 mm) into the cylinder, and insert the split rings into the groove
in the cylinder.

1,,,,,, 61-10-14
 PROPELLER MAINTENANCE MANUAL
nA RTZ E LL 114C

the split ring to hold it

(2) Slide the front spring retainer (mushroom) against
in place.
section) with two screws per
(3) Install the feathering stop plates ("L" cross

plate.

I NOTE 1: The height of the feathering stop plates will determine the
propeller feathering blade angle. A higher feathering stop plate
will result in a lower feather blade angle and a lower plate will
result in a higher feather blade angle.

NOTE 2: Reuse the feathering stop plates removed during disassembly.

They should have the correct height.
(4) Safety the feathering stop plate screws.

I. Installing Piston Assembly

CM12 and install it the
I (1) Lubricate the O-ring withapproved lubricant on

rod in the groove provided for it.

pitch change
(2) Lubricate the piston O-ring with approved lubricant CM12 and carefully
install it in the groove provided for it in the piston.

(3) Cut the necessary length of felt dust seal material and soak it in aviation

I grade reciprocating engine oil.

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting
line with a smooth,

fuzz-free surface.

(4) Install the felt dust seal in the groove provided for it in the piston.

(5) Slide the piston into place over the cylinder.

NOTE: The rod is not removed from the piston during overhaul
guide
unless it is damaged or some other condition warrants its
removal.

(6) Align the piston guide rods with the holes provided for them in the guide
collar unit.

(7) Install the free end of each link arm in the slot provided in the piston.

(8) Install all link pin units.

I CAUTION: ENSURE THE PROPER SAFETY SCREW IS INSTALLED AND
THAT ADEQUATE THREADS ARE AVAILABLE IN THE PISTON
UNIT TO HOLD THE SCREW IN PLACE. AT LEAST THREE
THREAD LENGTHS ARE SUFFICIENT. DO NOT BIND THE LINK
ARM.
the propeller beta
(9) Actuate the propeller assembly by hand to make sure
rods are straight and that the piston moves freely.
Page 753

ASSEMBLY 61110114 Rev. 4 Jan/Ot

 PAOPELLER
HARTZELL MA:N1T4ECNANCE MANUAL

(10) Make sure the guide collar unit is seated solidly against the cylinder at
the correct radial location.

NOTE: If necessary, shift the guide collar unit radially to provide the
correct alignment between the piston and the guide rods,
where applicable.
(11) When the necessary alignment is confirmed, use an Alien wrench with
torquing adapter to tighten the Nylock socket head cap screw in the guide
collar unit. See torque values table in chapter 800.

1 (12) Move the piston into full feathered position (back against the hub
assembly) so that the threaded end of the pitch change rod protrudes
through the end of the piston.
(13) Thread the large flexlock nut onto the end of the pitch change rod.

(14) Use a wrench on the nut and socket on the

pitch change rod to torque the
nut in accordance with Torque Values Table 802 in Chapter 800.

(15) Install the socket head cap screw, washer(s), and check nut on the end of
each piston guide rod.

J. Application of Blade Angle Reference Tape

Follow "Application of Blade Angle Reference Tape" described for "Assembly of Two-
Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
K. Setting Blade Angle

NOTE: At this
stage of assembly the outboard clamp bolts have not been tightened
because adjustments of blade angle may involve some disassembly
procedure.
(1) Apply 125 to 150 psi (8.62 to 10.34 bars) pressure to the piston through
the rotatable fixture on the propeller assembly table.
(2) Force the piston to the lowest pitch position.
(3) Use bench-top protractor at the reference
a blade radius specified in the
Hartzell Propeller Application Guide, Manual 159 (61-02-59), to adjust the
angle of the blades. Refer to Figure 709.

NOTE: Refer to the

applicable Type Certificate Data sheet,
Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.

I
(4) Rotate the blades to low pitch position in the

NOTE: Blade
rehto.spmalc
angle of all blades
at low pitch.
must be within 0.2 degree of each

,ss,,,,, 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

1 (5) Tighten the nuts on the outer clamp bolts. Refer to Torque Values Table
802 in Chapter 800.

(6) Check the angle of each blade and verify that the maximum blade angle
variance between blades is 0.2 degree. If it is not, then reset the blades
in the clamps.
(7) Remove air from the propeller piston and allow the pitch change
mechanism to reach feather position.
bench-top protractor at the reference blade radius specified in the
I (8) Use a

Hartzell Propeller Application Guide, Manual 159 (61-02-59), to check the

feather blade angle.

I NOTE: If the feather angle piston will need to be

is incorrect, the
removed and different height feathering stops will need to be
installed. A higher feathering stop will reduce feather blade
angle and a lower feathering stop will increase feather blade
angle.
(9) Apply air pressure toward high pitch.
(10) Remove the link pins and disengage the link arms.

(11) Rotate the clamps by hand.

(12) Release the pins in the start lock brackets to allow them to engage the
start lock plates on the inboard side of the clamps.
(13) Use a bench-top protractor at the reference blade radius specified in the
Hartzell Propeller Application Guide, Manual 159 (61-02-59), to check
start lock blade angle.

NOTE: Refer to theapplicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 1 59 (61-02-59), for the specific
angle required.
(14) File the start lock plates to adjust start lock angle, if necessary.

(15) Install the link pin units, safety screws.

(16) Using CM131, safety wire the screws.

L. Providing for Visual Detection of Blade Slippage in Clamp

Follow"Providing for Visual Detection of Blade Slippage in Clamp" described for
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
M. Sealant CM93 Application
Follow "Sealant CM93 Application" described for"Assembly of Two-Blade, Flanged-
Hub Models in the -1 and -6 Series" in this chapter.

Page 755
ASSEMBLY 61110114 Rev. 4 Jan/Ol
 PROPELLER
nARTZ ELL M*:N1~ANCE MPINVPIL

N. Checking Blade Track

Follow "Checking Blade Track" described for "Assembly of Two-Blade, Flanged-Hub

Models in the -1 and -6 Series" in this chapter.
O. Decal Replacement
Follow "Decal Replacement" described for "Assembly of Two-Blade, Flanged-Hub
Models in the -1 and -6 Series" in this chapter.
P. Propeller Removal From Assembly Table

(1) Remove the piston.

(2) Completely loosen the hub nut with special tool TE146.
(3) Remove the propeller and place it on a propeller cart for transportation.
(4) Remove the spinner bulkhead with start locks attached, and place it on a

propeller cart fortransportation.

1 (5) Keep the rear cone with the propeller if it is intended for propeller
installation on the engine.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1140

8. Assembly of Flanaed-Hub Models in the -3 series

A. Hub UnitAssembly
(1) Follow the pilot tube installation procedure in the Steel Hub Overhaul
chapter of Hartzell Standard Practices Manual 202A (61-01-02).

I CAUTION: THE END OF THE STUD WITH A DRILLED HOLE MUST

PROTRUDE FROM THE HUB AND THE ADJACENT THREADS
MUST BE KEPT FREE OF LOCKING COMPOUND CM16.

(2) Steps 8.(2)(a) through 8.(2)(d) apply to HC-A3VF-3L only. Apply locking
compound CM16 to the threads of the A-2983 studs and thread them into
the hub.

(a) Install the O-ring around the neck of the 6-2982 hub flange spacer.
(b) Install the O-ring inside the ID groove in the hub flange spacer.

(c) Press fit four dowels pins in two holes tone at either end), allowing
them to protrude approximately 0.5 inch (12.7 mm).
Slide the hub flange spacer onto the studs that protrude from the
(d)
Hub Flange.
B. Blade Mounting Parts Assembly
(1) Follow "Blade Mounting Parts Assembly" procedure described for
in
"Assembly of Two-Blade, Flanged-Hub Models in the -1 an -6 Series"

I (2)
this chapter.
Mount the hub on the rotatable fixture of a propeller assembly table.

C. Assembling Clamp and Counterweight

Refer to the Blade Clamp Overhaul chapter of Hartzell Standard Practices
(1)
I Manual 202A (61-01-02).
After each clamp and counterweight is assembled:
(2)
(a) Peen the back of the counterweight flush against the clamp half.

CAUTION A LINK ARM CANNOT BE INSTALLED ON THE CLAMP-

HALF AFTER THE CLAMP HAS BEEN INSTALLED ON
THE HUB.

Install the link sleeve in the large hole of the link arm.
I (b) screw

(c) Fit the link arm into the link screw.

NOTE: The raised shoulder on the link arm must face outboard,
toward the clamp.

Push the sleeve cotter pin through hole in the end of the link screw.
(d)
(e) Open the cotter pin to safety it.

NOTE: The link arm should move freely on the link screw.

I (f) Repeat these assembly procedures for the other clamps and
counterweights.
Page 757

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER
HA RTZ E LL MA:N1~ECNANCE MANUAL

D. Installing Blades and Clamps

Follow "lnstalling Blades and Clamps" procedure described for "Assembly of Two-
I Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
E. Beta System Installation (Part 1 of 2)

(1) Using hex head bolts, attach the two-piece spinner mounting ring to the
propeller mounting flange ton the side facing the blade arms).
(2) Install theguide lugs into the spinner mounting plate and secure them with
the snap ring in the groove of the guide lug. The
snap ring should be on
the side of the spinner mounting plate facing the engine.

CAUTION: THE BETA ROD RETAINER RINGS (THREE-SEGMENT

COMPRESSION RINGS) MUST BE ASSEMBLED WITH THEIR
SHARP EDGES AGAINST EACH OTHER.

(3) Slide two retainer rings over the inboard end of one propeller beta rod
and into the groove provided for them in the rod.

NOTE: The rounded edges of the retainer rings must face away from
each other.

(4) Use the special tool TE65 to crimp the retainer rings together by
I compressing them to a 0.550 inch (13.97 mm) maximum outside
diameter.

(5) Slide a beta rod retainer over the outboard end of the propeller beta rod
and down onto the crimped keeper rings. (This retainer will later support
a spring.) The crimped keeper rings fit down inside the beta rod retainer
ID recess.

(6) Slide a beta spring onto the outboard end of the beta rod.

(7) Use special tool TE29 to compress the beta spring by hand to
approximately half its length.

NOTE: Leave the special tool the spring to aid further

on assembly
procedures.
(8) Follow these procedures for the remaining propeller beta rod
subassemblies.

(9) Insert the assembled beta rods through the guide bushings provided for
them in the spinner support plate.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
H A RT Z E L L 114C

F. Installing the Cylinder and Guide Collar

Install the socket head cap screw into the guide collar.
(1)
I CAUTION: MAKE SURE THAT THE CHAMFER OF THE GUIDE COLLAR IS
FACING THE CYLINDER SHOULDER.

(2) Install the guide collar onto the smaller diameter shoulder of the cylinder.
I Do not tighten the guide collar; allow it to rotate on the cylinder to

facilitate installation on the hub.

(3) Clean the threads on hub and cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER.

hydraulic sealant adhesive CM134 in

bead of the groove of the
(4) Apply a

hub where the cyl inder O-ring will fit. Install the O-ring into the cylinder

chamfer, facing the hub.

for it in the guide collar.
(5) Slide a beta rod through each hole provided
(6) Hand screw the cylinder onto the hub unit (with guide collar installed.)
fit the slot provided for it in the
(7) Use a square bar of appropriate size to
unit (see
top of the cylinder, and torque the cylinder against the hub
Torque Values Table 802 in chapter 800).

NOTE: Tighten the cylinder flush with the shoulder on the hub. Early
drag and tightness is caused by the O-ring, which acts as a
seal and safety.

(8) Inspectthe slot in the top of the cylinder to make sure the square-bar
wrench used for torquing did not raise any sharp edges or damage the

threads.

(9) Remove any sharp edges in the wrench slot on top of the cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER. HYDRAULIC SEALANT ADHESIVE IN THE
CYLINDER MAY CONTAMINATE THE AIRCRAFT ENGINE
OIL.
not been
~10) Inspect the inside of the cylinder to make sure the O-ring has
forced out of place during the cylinder installation procedure.

Page 759

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

G. Feathering Spring Assembly

(1) For BHC-A2VF-3 only, slide the spacer onto the pitch change rod.
(2) Slide the front spring retainer (mushroom) onto the pitch change rod, with
the flat plate portion facing the threaded end of the pitch change rod.
(3) Slide the spacer tube onto the pitch change rod against the spring
retainer (mushroom).

1 (4) Slide the

spring over the spacer tube and against the front spring retainer
(mushroom).

I
(5) Install the spring retainer and split ring using special
rear fixture TE59 to
compress the springs, allowing insertion of the split rings into the groove
of the pitch change rod.

H. Feathering Spring Assembly Installation

I
(1) Insert the shoulder of the front spring retainer (mushroom) approximately
0.25 inch (6.35 mm) into the cylinder, and insert the split rings into the
groove in the cylinder.

(2) Slide the front spring retainer (mushroom) against the split ring to hold it
in place.
1 (3) Install the feathering stop plates ("L" cross section) with two screws per
plate.

I NOTE 1: The height of feathering stop plates will determine the propeller
feathering blade angle. A higher feathering stop plate will
result in a lower feather blade angle and a lower plate will
result in a higher feather blade angle.

NOTE 2: The feathering stop plates removed during disassembly should

have the correct feathering stop plate height. They should be
reused.

1 (4) Safety the feathering stop plate screws.

i. Installing PistonAssembly
I (1) Lubricate the pitch change rod O-ring with approved lubricant CM12 and
install it in the groove provided for it in the pitch change rod.
1 (2) Lubricate the piston O-ring with approved lubricant CM12 and carefully
install it in the groove provided for it in the piston.

I
(3) Cut the necessary length of felt dust seal material and soak it in aviation
grade reciprocating engine oil.

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line with a smooth,

fuzz-free surface.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 114C

(4) Install the felt dust seal in the groove provided for it in the cylinder.
beta rods with the holes provided for them in the
(5) Align the propeller
piston.
(6) Slide the piston into place over the cylinder.
(7) Install the free end of each link arm in the slot provided in the piston.

(8) Install all link pin units.

CAUTION: ENSURE THE PROPER SAFETY SCREW IS INSTALLED AND

THAT ADEQUATE THREADS ARE AVAILABLE IN THE PISTON
UNIT TO HOLD THE SCREW IN PLACE. AT LEAST THREE
I THREAD LENGTHS ARE SUFFICIENT. DO NOT BIND THE LINK
ARM.

Actuate the propeller assembly by hand to make sure the propeller beta
(9)
rod, where applicable, is straight and that the piston moves freely.
(10) Make sure the guide collar unit is seated solidly against the cylinder.

NOTE: If necessary, shift the guide collar unit radially to provide the
correct alignment between the piston and the beta rods.

(11) When the necessary alignment is confirmed, use an Alien wrench with
torquing adapter to tighten the Nylock socket head cap screw in the
guide collar unit. See Torque Values Table 802 in chapter 800.
I (12) Remove tool TE29 from each beta spring and allow the
special spring
to extend between the guide lug and guide collar.

1 (13) Move the piston into full feathered position (back against the hub
assembly) so that the threaded end of the pitch change rod protrudes
through the end of the piston.
nut onto the end of the pitch change rod.
(14) Thread the large flexlock
(15) Use a wrench on the nut and socket on the pitch change rod to torque
the nut in accordance with Torque Values Table 802 in Chapter 800.

J. Application of Blade Angle Reference Tape

Follow"Application of Blade Angle Reference Tape" procedure described for
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.

Page 761

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

I K. Setting Reverse and Feather Blade Angles

NOTE: At this stage of assembly the outboard clamp bolts have not been tightened
because the blades have not been located in the clamps.

(1) Apply 125 to 150 psi (8.62 to 10.34 bars) pressure to the piston through
the rotatable fixture on the propeller assembly table.
(2) Force the piston to reverse pitch position.
(3) Use abench-top protractor at the reference blade radius specified in the
Hartzell Propeller Application Guide, Manual 159 (61-02-59), to adjust the
angle of the blades. Refer to Figure 709.

NOTE: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.
(4) Rotate blades to reverse pitch position in the clamps.

I
NOTE: Blade angle of all blades must be within 0.2 degree of each
other at low pitch.
(5) Tighten the nuts on the outer clamp bolts. Refer to Torque Values Table
802 in Chapter 800.

(6) Release the pressure to the piston.

(7) Use abench-top protractor at the reference blade radius specified in the
Hartzell Propeller Application Guide, Manual 159 (61-02-59), to check
feather angle of the blades. Adjust if required. Refer to Figure 709.

(8) To increase the feathering angle, remove the piston and install a shorter
A-899-( feather stop. To decrease the feather angle, install a longer
A-899-() feather stop.

NOTE: Never shims under the stop to decrease the feather angle.
use

A change in feather stop length of 0.031 inch (0.79 mm) will

change the blade angle approximately 1 degree.
(9) Install the safety screws in the link pin units.
(10) Using CM131, safety wire the screws.

ASSEMBLY 61’10’14 RevP4aSJean~:

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1140

L. Beta System Installation (Part 2 of 2)

(1) Thread a jam nut onto the engine side of each beta rod.

I CAUTION: DO NOT FORCE THE BETA RODS INTO THE BETA RING.
THEY COULD DIMPLE THE BETA RING GROOVE AND
INTERFERE WITH THE CARBON BLOCK. THIS WOULD CAUSE
THE BETA RING TO BE SCRAPPED.

(2) Thread beta rod at a time into the threaded holes in the beta ring to
one

a depth of two threads each time. Use an open

end wrench on the flats of

I (3)
the beta rod to turn the beta rod.

Repeat the above process with each beta rod in succession several times
until each beta rod is completely threaded into the beta ring.

(4) Unthread each beta rod out of the beta ring one full thread and then
tighten the jam nuts while holding the beta rods stationary with an open
end wrench.

dial indicator to check the runout of the beta ring at full feather.
I (5) Use a

See Figure 715 for setup.

CAUTION: BETA RING RUNOUT MUST BE KEPT WITHIN 0.010-INCH

TOTAL.

Adjust the beta rods and jam nuts to adjust runout.

(6)
(7) This step applies only if a beta system ring, rod end is required.
Install the check nut each beta rod on the piston end.
(a) on

(b) Install the ring, rod end.

(8) Install the lock nut on each beta rod and tighten.
M. Setting Low Pitch Blade Angle
Install lock nut each beta rod on the piston end.
(1) one on

air pressure until low pitch is reached.

(2) Pressurize the piston with partial

NOTE~ applicable Type Certificate Data sheet,

Refer to the
Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.
Use Bench top protractor at the reference blade radius specified in the

I
(3)
Propeller Application Guide, Manual 159 (61-02-59), to adjust the
lleztraH.907
angle of the blades. Refer to Figure
just contact the piston with
(4) Adjust each lock nut on each beta rod to ear

the piston at low pitch.

(5) Check blade angle of all blades and determine if blade angle variance
from blade to blade is within 0.2 degree of each other. If not, the blades
must be slipped in the blade clamps (clamps loosened) and the blade
angle setting procedure repeated.

Page 763

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER
HARTZ ELL MA:N:4ECNANCE MANUAL

APS5018

Checking Beta Ring Runout with Dial Indicator

Figure 715

ASSEMBLY 61’10’14 764

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

N. Final Beta Ring Runout Check

CAUTION: BETA RING RUNOUT MUST BE KEPT WITHIN 0.010-INCH

TOTAL. ADJUST AS NECESSARY.
at low pitch and piston is just touching the lock nuts on
(1) With the propeller

I (2)
(3)
each beta rod, check the beta

Refer to Figure
Pressurize the
runout.
715 for the

propeller
ring
setup.
runout.

to reverse blade angle and check the beta ring

O. Providing for Visual Detection of Blade Slippage in Clamp

Follow "Providing for Visual Detection of Blade Slippage in Clamp" procedure
in
described for "Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series"
this chapter.

P. Sealant CM93 Application

Follow "Sealant CM93 Application" "Assembly of Two-Blade, Flanged-
described for
Hub Models in the -1 and -6 Series" in this chapter.

Q. Checking Blade Track

Follow"Checking Blade Track" described for "Assembly of Two-Blade, Flanged-Hub
Models in the -1 and -6 Series" in this chapter.

I R. Decal Replacement
Follow "Decal Replacement" described for"Assembly of Two-Blade, Flanged-Hub
Models in the -1 and -6 Series" in this chapter.

I S. Propeller Removal From Assembly Table

(1) Loosen bolts holding propeller hub to the rotatable fixture of the propeller
assembly table.

~2) Remove propeller assembly and place on propeller cart for transportation.

(3) Attach spinner bulkhead to spinner mounting plate, as applicable.

Page 765

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

9. Assembly of Splined-Hub Models in the -3 series

A. Hub Unit Assembly

Follow the pilot tube installation procedure in the Steel Hub Overhaul chapter of Hartzell
I Standard Practices Man~al 202A (61-01-02).
B. Beta System Installation (Part 1 of 3)
I (1) Position the support plate from the propeller assembly table to a position
near the blade arms and encircling the neck of the hub.

(2) Install piece at a time of the three-piece support collar between the
one

support plate and hub neck.

1 (3) Install three A-2038-12 socket head cap screws in the support collar to
lightly clamp it to the hub neck.
(4) Position the radius of the support collar against the hub shoulder radius
next to the blade arms.

NOTE: The support plate should be resting on the support collar

between the blade arms and support collar.

(5) Attach the support plate to the support collar with hex head bolts,
washers, and nuts. The bolt heads must face the blade arms to assure
clearance with the clamps.

(6) Install the guide lugs in the

support plate and attach the snap rings

I
to the
guide lugs to secure them in place.

NOTE: Snap rings must be on the engine side of the support plate.
(7) Rotate the assembly on the hub neck to locate the guide lugs in the
appropriate location to receive beta rods later.

NOTE: Lightly secure the support collar to the hub, as further

adjustment to align it with the beta rods will probably be
required.
C. Blade Mounting Parts Assembly
(1) Follow "Blade Mounting Parts
Assembly" procedure described for
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series"

I
in
thischapter.
(2) Install the low stop collar (beta ring) around the rotatable fixture and lay it
on the propeller assembly table with the threaded bosses facing
away
from the table.

I
(3) Install the support plate around the rotatable fixture and lay it on top of the
low stop collar.

(4) Install the rear cone on the rotatable fixture of the propeller assembly
table.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1146

(5) Mount the hub on the rotatable fixture of the propeller assembly table. Use

special tool TE146 to tighten the hub nut.

NOTE: Use the hub nut and puller ring that will go with the propeller
when mounted on an engine.

D. Assembling Clamp and Counterweight

Follow"Assembling Clamp and Counterweight" procedure described for "Assembly of
I Flanged-Hub Models in the -3 Series" in this chapter.
E. Installing Blades and Clamps
Follow "Installing Blades and Clamps procedure described for "Assembly of Two-
I Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
F. Beta System Installation (2 of 3)

CAUTION: BETA ROD RETAINER RINGS (THREE-SEGMENT

COMPRESSION RINGS) MUST BE ASSEMBLED WITH THEIR
SHARP EDGES AGAINST EACH OTHER.

Slide two retainer rings over the inboard end of one propeller beta rod
(1)
and into the groove provided for them in the rod.

NOTE: The rounded edges of the retainer rings must face away from
each other.

(2) Use thespecial tool TE65 to crimp the retainer rings together by
compressing them to a 0.550 inch (13.97 mm) maximum OD.
Slide beta rod retainer the outboard end of the propeller beta rod
(3) a over

and down onto the crimped keeper rings. (This retainer will later support
a spring.) The crimped keeper rings fit down inside the beta rod retainer
ID recess.

(4) Slide a beta spring onto the outboard end of the beta rod.

Use special tool TE29 to compress the beta spring by hand to

(5)
approximately half its length.

NOTE: Leave the special tool on the spring to aid further assembly
procedures.
(6) Follow these procedures for the remaining propeller beta rod
subassemblies.

Insert the assembled beta rods through the guide bushings provided for
(7)
them in the spinner support plate.

Fags 767
PISSEMBLY 61-10-14 Rev. 4 Jan/Ol
 PROPELLER
HARTZELL MPI:N~CNANCE MANUIL

G. Installing the Cylinder

Follow "lnstalling the Cylinder" procedure described for "Assembly of Flanged-Hub
Models in the -3 Series" in this chapter.

NOTE: This splined-hub model has a hub nut and puller ring installed in the hub
before the cylinder is installed.

H. Feathering Spring Assembly

(1) Slide the spacer and pitch adjust washers onto the pitch change rod.

(2) Slide the front spring retainer (mushroom) onto the pitch change rod, with
the flat plate portion facing the threaded end of the pitch change rod.
(3) Slide the
spring over the spacer tube and against the front spring retainer
(mushroom).

I
(4) Install the rear spring retainer and split ring using special fixture TE59 to
compress the springs, allowing insertion of the split rings into the groove
of the pitch change rod.

i. Feathering SpringAssembly Installation

Follow"Feathering Spring Assembly Installation" procedure described for "Assembly of
Flanged-Hub Models in the -3 Series" in this chapter.
J. Installing Piston Assembly
(1) Lubricate the pitch change rod O-ring with approved lubricant CM12 and
install it in the groove provided for it in the pitch change rod.

1 (2) Lubricate the piston O-ring with approved lubricant CM12 and carefully
install it in the groove provided for it in the piston.
(3) Cut the necessary length of felt dust seal material and soak it in aviation

I grade reciprocating engine oil.

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line with a smooth,

fuzz-free surface.

(4) Install the felt dust seal in the groove provided for it in the cylinder.
(5) Align the propeller beta rods with the holes provided for them in the
piston.
(6) Slide the piston into place over the cylinder.
(7) Install the free end of each link arm in the slot provided in the piston.
(8) Install all link pin unit and safety screws.

ASSEMBLY 61’10’14 RevP4agJean~I:

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1146

I CAUTION: ENSURE THE PROPER SAFETY SCREW IS INSTALLED AND

THAT ADEQUATE THREADS ARE AVAILABLE IN THE PISTON
UNIT TO HOLD THE SCREW IN PLACE. AT LEAST THREE
I THREAD LENGTHS ARE SUFFICIENT. DO NOT BIND THE LINK
ARM.

beta
(9) Actuate the propeller assembly by hand to make sure the propeller
rod, where applicable, is straight and that the piston moves freely.
(10) Make sure the guide collar unit is seated solidly against the cylinder.

NOTE 1: If necessary, shift the guide collar unit radially to provide the
correct alignment between the piston, beta rods, and support
collar and support plate combination.

NOTE 2: If necessary, shift the support collar and support plate radially
to provide the correct alignment between the piston and the
beta rods and guide collar, where applicabie.

(11) When the necessary alignment is confirmed, use an Alien wrench with
torquing adapter to tighten the Nylock socket head cap screw in the
guide collar unit. See Torque Values Table 802 in Chapter 800.

CAUTION: ENSURE THE SUPPORT COLLAR IS FIRMLY AGAINST THE

HUB SHOULDER RADIUS NEXT TO THE BLADE ARMS.

When the necessary alignment is confirmed, final tighten the socket

(12)
head cap screws in the support collar.

1 (13) Remove special tool TE29 from each beta spring and allow the spring
to extend between the guide lug and guide collar.

1 (14) Move the piston position (back against the hub

into full feathered
assembly) so that the threaded end of the pitch change rod protrudes
through the end of the piston.
(15) Thread the large flexlock nut onto the end of the pitch change rod.

(16) Use a wrench on the nut and socket on the pitch change rod to tighten
the nut. The nut will be torqued when the propeller is installed on the
engine.
K. Application of Blade Angle Reference Tape
"Application of Blade Angle Reference Tape" procedure described for
Follow
"Assembly of Flanged-Hub Models in the -1 and -6 Series" in this chapter.
L. Setting Reverse and Feather Blade Angles
Follow"Setting Reverse and Feather Blade Angles" procedure described for
"Assembly of Flanged-Hub Models in the -3 Series" in this chapter.

Page 769

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER
HARTZELL MPI:N:4ECNINCE M*NVAL

M. Beta System Installation (Part 3 of 3)

Follow "Beta System Installation (Part 2 of 2)" described for "Assembly of Flanged-Hub
Models in the -3 Series" in this chapter.
N. Setting Low Pitch Blade Angle
Follow "Setting Low Pitch Blade Angle" described for "Assembly of Flanged-Hub
Models in the -3 Series" in this chapter.

O. Final Beta Ring Runout Check

Follow "Final Beta Ring Runout Check" described for "Assembly of Flanged-Hub
Models in the -3 Series" in this chapter.
P. Providing for Visual Detection of Blade Slippage in Clamp
Follow"Providing for Visual Detection of Blade Slippage in Clamp" described for
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
Q. Sealant CM93 Application

Follow "Sealant CM93 Application" described for "Assembly of Two-Blade, Flanged-

Hub Models in the -1 and -6 Series" in this chapter.
R. Checking Blade Track

Follow "Checking Blade Track" described for "Assembly of Two-Blade, Flanged-Hub

Models in the -1 and -6 Series" in this chapter.
S. Decal Replacement
Follow "Decal Replacement" described for "Assembly of Two-Blade, Flanged-Hub
Models in the -1 and -6 Series" in this
chapter.
T. Propeller Removal From Assembly Table

(1) Remove the ring rod end as applicable.

(2) On propeller model HC-A3MV20-3L only, remove the self-locking nut, ring
rod end, and check nut from the end of each beta rod and keep them
with the propeller.

NOTE: A single self-locking nut and spacer (if installed) will still be
installed on each beta rod. Do not remove the self-locking nut
and spacer.

(3) Release the air pressure to reach high pitch.

61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

CAUTION: TO DETERMINE THE LOCATION OF LOW PITCH WHEN THE

PROPELLER IS REASSEMBLED, A PRECISE LOCATION OF
THE LOW PITCH SELF-LOCKING NUT MUST BE
ESTABLISHED. MEASUREMENT WITH A RULER IS NOT
SUFFICIENT.

(4) Using a dialcaliper, measure the distance from the inboard surface of
each self-locking low pitch nut to the end of the corresponding beta rod.
pitch nut measurement,
(5) Using a separate information tag for each low
record the distance measured from the inboard surface of the self-locking
low pitch nut to the end of the beta rod. Refer to Figure 716.

Securely attach each information tag to its corresponding beta return

(6)
spring on the beta rod.
(7) Remove the self-locking low pitch nut from each beta rod.

W1M13

Beta Rod

Information tag for

measurement of low pitch
Beta Return
Spring

Information Tag on Beta Return Spring

Figure 716

.,,,..,Y 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(8) Remove the piston.

1 Remove the piston nut.

2 Remove the safety screw from each link pin unit.

3 Remove each link pin unit.

4 Slide the link arms out of the piston slots.

5 Slide the piston off the cylinder.

(9) Completely loosen the hub and hub nut using special tool TE146

(16) Remove the propeller assembly and place it on a propeller cart for
transportation.

NOTE: The hub nut and puller ring will remain with the propeller, held
between the hub and cylinder.
(11) Remove the rear cone if it is to be used for propeller installation on the
engine.

61-10-14
 PROPELLER MAINTENANCE MANUAL
nARTZ E LL 114C

10. Assembly of Flanaed-Hub Models in the -4 Series

A. Hub Unit Assembly

Follow the pilot tube installation procedure in the Steel Hub Overhaul chapter of Hartzell
Standard Practices Manual 202A (61-01-02).
B. Blade Mounting Parts Assembly
(1) Follow "Blade Mounting Assembly" procedure described for
Parts
of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
I this chapter."As embly
Mount the rotatable fixture of propeller assembly table.
(2) on a

C. Assembling Clamp and CounteMleights

I (1) Refer to the Blade Clamp Overhaul Chapter of Manual 2024 (61-01-02).

(2) After each clamp is assembled:

I (a) Install the link screw sleeve in the large hole of the link arm.

(b) Fit the link arm onto the link screw.

NOTE: The raised shoulder on the link arm must face outboard,
toward the counterweight.
I (c) Push the sleeve cotter
screw.
pin through the hole in the end of the link

(d) Open the cotter pin to safety it.

NOTE: The link arm should move freely on the link screw.

(e) Repeat these assembly procedures for the other clamps.

I
D. Installing Blades and Clamps
(1) Follow"lnstalling Blades and Clamps" procedure described for "Assembly
of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in this
chapter.
E. I nstalling the Cylinder and Guide Collar

Install the socket head cap into the guide collar.

(1) screw

CAUTION: MAKE SURE THAT THE CHAMFER OF THE GUIDE COLLAR IS

FACING THE CYLINDER SHOULDER.

(2) Install the guide collar onto the smaller diameter shoulder of the cylinder.
Do not tighten the guide collar, but allow it to rotate on the cylinder to
facilitate installation on the hub.

models have the hub nut and puller ring installed in

NOTE: Splined-hub
the hub before the cylinder is installed.

Page 771

nssEMeLv 61-10-14 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

1 (3) Clean the threads on hub and cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER.

(4) Apply a bead of hydraulic sealant adhesive CM134 in the groove of the

hub, where the cylinder O-ring will fit.

(5) Lubricate the cylinder O-ring with approved lubricant CM12 and install it in
the groove in the cylinder, facing the hub.

(6) Hand screw the cylinder onto the hub unit with the guide collar installed.

(7) Use a square bar of appropriate size to fit the slot provided for it in the

top of the cylinder, and torque the cylinder against the hub unit (see
Torque Values Table 802 in Chapter 800).

NOTE: Tighten the cylinder flush with the shoulder on the hub. Early
drag and tightness is caused by the O-ring, which acts as a
seal and safety.

1 (8) Inspect the slot in the top of the cylinder to make sure the square-bar
wrench used for torquing did not raise any sharp edges or damage the
threads spring retainer slot.

I
or

(9) Remove any sharp edges in the wrench slot on top of the cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER. HYDRAULIC SEALANT ADHESIVE IN THE
CYLINDER MAY CONTAMINATE THE AIRCRAFT ENGINE OIL.

1 (10) Inspect the inside of the cylinder to make sure the O-ring has not been
forced out of place during the cylinder installation procedure.
F. Installing Piston Assembly
I (1) Lubricate the piston O-ring with approved lubricant CM12 and carefully
install it in the groove provided for it in the piston.
(2) Cut the necessary

I
length of felt dust seal material and soak it in aviation
grade reciprocating engine oil.

NOTE 1: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line with a smooth
fuzz-free surface.

NOTE 2: The guide rod is not removed from the piston during overhaul
unless it is damaged or some other condition warrants its
removal.

(3) Install the felt dust seal in the groove provided for it in the piston.
(4) Slide the piston into place over the cylinder.
(5) Align the piston guide rods with the holes provided for them in the guide
collar unit.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1146

(6) Install the free end of each link arm in the slot provided in the piston.

(7) Install all link pin units.

I CAUTION: ENSURE THE PROPER SAFETY SCREW IS INSTALLED AND

THAT ADEQUATE THREADS ARE AVAILABLE IN THE PISTON
UNIT TO HOLD THE SCREW IN PLACE. AT LEAST THREE
I THREAD LENGTHS ARE SUFFICIENT. DO NOT BIND THE LINK
ARM.

(8) Actuate the propeller assembly by hand to make sure the piston moves

freely.
(9) Make sure the guide collar unit is seated solidly against the cylinder at

the correct radial location.

NOTE: If necessary, shift the guide collar unit radially to provide the
correct alignment between the piston and the guide rods.

(10) When the necessary alignment is confirmed, use an Alien wrench with
in the guide
torquing adapter to tighten the Nylock socket head cap screw
collar unit. Torque per Torque Values Table 802 in the Fits and

I (11)
Clearances chapter of this manual.

Install the socket head cap screw,

piston guide rod.
jam nut and washer on the end of each

G. Application of Blade Angle Reference Tape

Follow"Application of Blade Angle Reference Tape" procedure described for
"Assembly of Flanged-Hub Models in the -1 and -6 Series" in this chapter.
H. Setting Blade Angle

NOTE: stage of assembly the outboard clamp bolts have

At this not been tightened
because the blades have not been located in the clamp.

(1) Force the piston fully against the cylinder or toward the propeller
assembly table.

NOTE: This is low pitch position of the pitch change mechanism and

clamps.
(2) Use bench top protractor at the reference blade radius specified in the
a

Hartzell Propeller Application Guide, Manual 159 (61-02-59), to the adjust

angle of the blades Refer to Figure 709.

NOTE: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.

Page 773

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER
HARTZELL M*:N~PINCE MANUIL

(3) Rotate blades to low pitch position in the clamps.

NOTE: Refer to the applicable Type Certificate Data sheet,
Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide for the specific angle required.
(4) Tighten the nuts on the outer
clamp bolts. Torque per Torque Values
Table 802 in the Fits and Clearances chapter of this manual.

(5) Check the blade angles of all blades and verify that maximum blade angle
variance is within 0.2 degree. If not, then reset the blades in the clamps.

NOTE: Refer to theapplicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.
(6) Apply air pressure to the piston through the rotatable fixture on the
propeller assembly table.
1 (7) Force the piston to high pitch (when guide rod washers bottom on the
guide collar).
(8) Check the blade angles to make sure that high pitch can be reached.

(9) Release the air pressure and hand rotate blades to low pitch.
i. Providing for Visual Detection of Blade Slippage in Clamp
Follow "Providing for Visual Detection of Blade Slippage in Clamp" procedure
described for "Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
this chapter.

J. Sealant CM93 Application

Follow "Sealant CM93 Application" described for "Assembly of Two-Blade, Flanged-
Hub Models in the -1 and -6 Series" in this chapter.
K. Checking Blade Track

Follow"Checking Blade Track" procedure described for "Assembly of Two-Blade,

Flanged-Hub Models in the -1 and -6 Series" in this chapter.
L. Decal Replacement
Follow "Decal
Replacement" procedure described for "Assembly of Two-Blade,
Flanged-Hub Models in the -1 and -6 Series" in this chapter.
M. Propeller Removal From Assembly Table

(1) Unfasten the bolts that hold the propeller hub to the rotatable fixture of the
propeller assembly table.

1 (2) Remove the propeller assembly and place it on a propeller cart for
transportation.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

CAUTION: ON "K" FLANGE INSTALLATIONS A SHIM THAT IS INSTALLED

I BETWEEN THE ENGINE AND PROPELLER MUST BE

SUPPLIED, ALONG WITH PROPELLER MOUNTING BOLTS AND
ENGINE-TO-HUB O-RING.

(3) Spinner Bulkhead Installation

NOTE: On "K" flange installations the bulkhead is a ring that attaches

to the engine starter ring gear. On "F" flange installation a
plate is captured between the engine flange and the head of
I the propeller mounting bolts, and extends beyond the OD of
the engine flange. A ring is added to the plate and the
bulkhead attaches to the ring and plate with hex head bolts.

1 1. Assembly of Splined-Hub Model HC-A2(V.MV~20-4A1

A. Hub Unit Assembly

Follow the pilot tube installation procedure in the Steel Hub Overhaul chapter of Hartzell
Standard Practices Manual 202A.

B. Blade Mounting Parts Assembly

Parts Assembly" procedure described for
(1) Follow "Blade Mounting
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
this

I (2)
chapter.Place the guidecollar around the rotatable fixture on the propeller
assembly bench for later attachment. Make sure the large center bore
chamfer is facing away from the assembly bench.

(3) Install the rear cone on the rotatable fixture of a propeller assembly table.

I (4) Mount the hub

special

NOTE:
on

tool TE146 to
the rotatable fixture of
tighten

Use the hub nut and

propeller on the
the hub nut.

puller ring
engine.
a propeller assembly table. Use

that will be used to mount the

C. Installing Guide Collar

(1) Insert two B-3386-14H hex head bolts into the guide collar for clamping.

collar from the table and position it against the small radius
(2) Lift the guide

I (3)
shoulder

Position the holes in the

push rods.
on the hub, immediately
guide
next to the blade

collar appropriately
arms.

to receive the piston

collar clamping bolts to hold the guide collar in

(4) Slightly tighten the guide
place.

Page 775

ASSEMBLY 61~110114 Rev. 4 Jan/Ol

 PROPELLER MANUAL
HA RTZ E ILL

D. Assembling Clamp and Counterweight

I (1) Refer to the Blade

Practices Manual
Clamp Overhaul Chapter
202A (61-01-02),
of Hartzell Standard

(2) After eachclamp and counterweight is assembled, peen the back of the
counterweight flush against the clamp-half.
E. Installing Blades and Clamps
Follow "Installing Blades and Clamps" procedure described for "Assembly of Two-
I Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
F. Installing the Cylinder
Follow"lnstalling the Cylinder" procedure described for "Assembly of Two-Blade,
I Flanged-Hub Models in the -1 and -6 Series" in this chapter.
G. Installing Shaft Seal
(1) Lubricate the O-ring with approved lubricant CM12 and carefully install it
in the A-2054 shaft seal ID groove provided for it.
(2) Lubricate the O-ring with
approved lubricant CM12 and carefully install it
in the A-2054 shaft seal OD groove provided for it.

(3) Slide the shaft seal between the shaft nut and cylinder, just below the
cotter pin holes.

1 (4) Insert the cotter pins in the shaft nut holes provided for them. The cotter
pins will hold the shaft seal in place.
Fl. Installing Piston Assembly
See Figure 707.

I (1) Lubricate the piston O-ring (Il)with approved lubricant CM12 and
carefully install it in the groove provided for it in the piston (3).

1 (2) Cut the necessarylength of felt dust

grade reciprocating engine oil.
seal material and soak it in aviation

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line with a smooth,

fuzz-free surface.

(3) Install the felt dust seal (9) in the groove provided for it in the cylinder (7).
(4) Install the pitch change block (13) on each clamp link screw.

(5) Install the fork (4) on each pitch change block (13) with the thick portion
of the fork on the side facing the propeller assembly bench.
(6) Slide the spacer (not shown) onto each sleeve (5), against the shoulder of
sleeve.

ASsEMRLy 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 1140

(7) Slide the sleeve with spacer (not shown) into the guide collar holes.
(5)
The shoulder of the sleeve and spacer must be on the side of the guide
collar facing away from the propeller assembly bench.

thecylinder (7) and the push rods (5) through the

(8) Slide the piston (3) over

forks, sleeves, spacers, and guide collar.

NOTE: Some rotation of the guide collar may be necessary to achieve

proper alignment with the fork and link screw.

(9) Tighten the guide collar clamping fasteners.

I (10) Install the washer (6) and locking nut (1) on the end of each push rod (2)
and tighten.
the fork (4) with the pitch change block (13) and torque the set screw
(11) Align
in accordance with the torque specified in Torque Values Table 802 in

chapter 800.

I. Application of Blade Angle Reference Tape

Follow"Application of Blade Angle Reference Tape" procedure described for
"Assemblyof Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
J. Setting BladeAngle

NOTE: At this stage of assembly the outboard clamp bolts have not been tightened
because the blades have not been located in the blade clamps.

Il (1) Apply 125 to 150 psi (8.62 to 10.34 bars) air pressure to the piston
through the rotatable fixture on the propeller assembly table.
(2) Force the piston to lowest pitch position.

NOTE 1: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.

NOTE 2: When lock nut and washer on end of each piston push rod are

against guide collar, the pitch change mechanism is at low

pitch
(3) Use bench-top protractor at the reference blade radius specified in the
I a

Hartzell Propeller Application Guide, Manual 159 (61-02-59), to adjust the

angle of the blades.
(4) Rotate the blades to low pitch position in the loose clamps.

NOTE: Blade angle of all blades must be within 0.2 degree of each
other at low pitch.
(5) Tighten the nuts on the outer clamp bolts. Refer to Torque Values Table
802 in Chapter 800.

ASSEMBLY 61110114
 PROPELLER MAINTENANCE MANUAL
HIP~ RTZ E LL Il4C

(6) Release the air pressure and rotate the propeller to high pitch by hand,
twisting the counterweights.
(7) Confirm high pitch with a bench top protractor at the reference blade
radius.

NOTE: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.
K. Providing for Visual Detection of Blade Slippage in Clamp
Follow "Providing for Visual Detection of Blade Slippage in Clamp" procedure
described for "Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
this chapter.

L. Sealant CM93 Application

Follow "Sealant CM93 Application" procedure described for "Assembly of Two-Blade,
Flanged-Hub Models in the -1 and -6 Series" in this chapter.
M. Checking Blade Track

Follow"Checking Blade Track" procedure described for "Assembly of Two-Blade,

Flanged-Hub Models in the -1 and -6 Series" in this chapter.
N. Decal Replacement
Follow "Decal
Repladement" procedure described for "Assembly of Two-Blade,
Flanged-Hub Models in the -1 and -6 Series" in this
chapter.
O. Propeller Removal From Assembly Table
(1) Remove the lock nut and washer from the end of each piston push rod.

(2) Loosen the fork set screw.

(3) Remove the piston.

(4) Remove the shaft nut cotter pins.
(5) Remove the seal shaft nut.

(6) Completely loosen the hub and shaft nut with special tool TE146.

(7) Remove the propeller assembly and place on a propeller cart for
transportation.
(8) Remove the rear cone if it is to be used for propeller installation on the
engine.

I Y.Ma~ 61-10-14 Rev. 5 Aug/OlPage 778

 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

P. Oil Transfer UnitAssembly

rings (3070, 3090). Refer to Figure 717.

(1) Check the end-gap of the oil seal

(a) Insert an oil seal ring (3070, 3090) into the slip ring sleeve (4000).

(b) Measure the gap of the oil seal ring; the gap must be 0.006 to 0.008 inch

(0.15 to 0.20 mm).

(c) Make the gap is uniform. Refer to
sure Figure 508 in the Check chapter of
this manual.

If the gap measures less than 0.006 to 0.008 inch (0.1 5 to 0.20 mm) or the
(d)
uniform and correct gap.
gap is not uniform, use a file to attain a

(e) Remove the oil ring seal (3070, 3090) from the slip ring sleeve (4000).
(f) Repeat the end-gap check procedure for the remaining oil seal rings
(3070,3090).

End-gap must be 0.006 to 0.008

inch (0.15 to 0.20 mm).

End-gap must
be uniform:

Slip Ring
Sleeve (4000)

Checking EndlGap on the Oil Seal Rings

Figure 717

61-10-14
 PROPELLER
HARTZ ELL M*:N1~NI\NCEMPINUAL

W10455
W1W56
Slip Ring Cap Slip Ring
Oil Transfer Plug (4050) Sleeve (4000)
(4090)

Locally
P g
Procured Tool
TE73

O-rings (4010)

Slip Ring Cap

(4050)
o.

TE73

Oil Transfer Plug

Locally Procured Tool

(4090)

Installing the Oil Transfer Plug Using the Installation Tools

Figure 718

ASSEMBLY 61’10-14
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

(2) Install an O-ring (4010) into O-ring groove in the hole in the slip ring sleeve (4000).

(3) Install the slip ring sleeve (4000) into the slip ring cap (4050).

oil
NOTE: Align the slip ring sleeve (4000) hole and installed O-ring with the
supply hole in the slip ring cap (4050).
(4) Installing the oil transfer plug (4090) into the slip ring cap (4050) and slip ring
sleeve (4000). Refer to Figure 71 8.

(a) Install locally procured installation tool into the shoulder-side of the oil
a

transfer plug (4090).

oil
(b) Install theO-ring pilot installation tool TE73 on the opposite end of the
transfer plug (4090).

(c) (4090) throught the oil supply hole of the slip ring
Insert the oil transfer plug
transfer plug contacts with the shoulder
cap (4050) until the shoulder of the oil
of the oil supply hole of the slip ring cap.

(d) Using a snap ring tool, install the internal snap ring (5000) into the groove
provided in the oil supply hole of the slip ring cap (4050).
(e) Remove TE73 from the oil transfer plug (4090) from the ID of the slip ring
sleeve (4000).

61-10-14
 M~INUAL
HARTZELL

W1D421

Oil Seal Ring (3070)

Notch in the Oil

Seal Ring

Elbow (501 0)

Oil SealRing
Oil Transfer Plug tL~ (3090)
(4090)
Oil Seal Ri
Snap Ring (5000)
(3070)

O-ring I Lj Mounting Bolt (4060)

Mounting Washer
Slip Ring Sleeve (4070)
(4000) Spring Pin
(3040)

Slip Ring (3080)

Rear Cone (3030)

Gasket (3050)

Transfer Seal Button III I) I IIII Backup Ring (3010)

(4040)

High Stop Spring

(4030) Lip Seal (3020)

Gasket (5020)/ Slip Ring Cap (4050)

Oil Slinger (3060)
Pipe Plug (4020)

A122414 Oil Transfer Unit

Figure 719

pssEnnsLY 61-10-14 Rev. 5 Aug/OlPae 778.4

 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

(5) Insert the transfer seal button (4040) into place through the pipe plug (4020) hole
of the slip ring cap (4050) and into the groove of the slip ring sleeve (4000).

NOTE: There is amanufactured groove on the OD of the slip ring sleeve (4000)
for installation of the transfer seal button (4040). Referto Figure 510 in
the Check chapter of this man ual.

(6) Place the spring (4030) in the pipe plug (4020) hole in the slip ring cap 14050) on

the transfer seal plug (4040).

(7) Apply threadlocking compound CM21 to the threads of the pipe plug (4020).

CAUTION: WHEN INSTALLING THE PIPE PLUG (4020), MAKE SU RE THAT

THE TRANSFER SEAL BUTTON (4040) REMAINS ENGAGED IN
THE SLIP RING SLEEVE (4000) GROOVE AND THE SPRING (4030)
REMAINS CENTERED ON THE SHOULDER OF THE TRANSFER
SEAL BUTTON (4040).
(8) Install the pipe plug (4020) into the in the slip ring cap (4050).

NOTE: The spring ~4030) will be compressed by the pipe plug (4020) when the

pipe plug is installed in the slip ring cap (4050).

(9) Install O-ring (4010) into the O-ring groove in the oil supply hole in the slip ring
an

cap (4050). Refer to Figure 719.

61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

W10457

ZCL~

Installing the Oil SealRings into the Slip Ring

Figure 720

W10458

Side Clearance Must be 0.001

to 0.006 inch (0.03 to 0.16 mm)

-~Cc-

Sllp Ring (3080)

Clearance Between the Slip Ring Groove Side and the Oil Seal Ring
Figure 721

778.6
ASSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

CAUTION 1 DO NOT STRETCH OR BEND THE O1L SEAL RINGS WHILE

INSTALLING I NTO THE SLIP RING (3080) G ROOVE, THE O1L SEAL
RINGS ARE VE RY BRITTLE AN D WILL BREAK EASI LY.

THE OIL SEAL RING (3070,3090) POSITION AND ORIENTATION IS

CAUTION2:
IMPORTANT TO PROPER OPERATIONAL LUBRICATION AND A
LONG WEAR LIFE. REFER TO FIGURE 722 FOR OIL SEAL RING
INDENTIFICATION.

(1 0) Install an ring (3090) in each of the two grooves of the slip ring (3080).
oil seal
Position the oil seal rings in the slip ring as shown in Figure 719.

NOTE Slide one end of the oil seal ring (3090) into the slip ring groove and
slowly push the remainder of the oil seal ring into the slip ring groove.
Refer to Figure 720.

(1 1) Install an ring (3070) in the outboard position of the grooves of the slip ring
oil seal
Orient
(3080). Position the oil seal rings in the slip ring as shown in Figure 719.
the notches in the oil seal rings to face away from the center of the slip ring

NOTE: Slide one end of the oil seal ring (3090) into the slip ring groove and
slowly push the remainder of the oil seal ring into the slip ring groove.
Refer to Figure 720.

side wall
(12) Check the remaining side clearance between the slip ring (3080) groove
and the oil seal ring (3090). The clearance must be 0.001 to 0.006 inch (0.03 to
0.15 mm). Refer to Figure 721. If the slide clearance is less than 0.001
inch (0.03

mm), refer to the Fits and Clearances chapter for instructions on how to repair the
groove.
W10419 Eight (8) evenly
W10420
spac_ed notches

Oil Seal Ring (3090) Oil Seal Ring (3070)

A-221-()Oil SealRing Characteristics

Figure 722

61-10-14
 PROPELLER
HARTZELL MP~hfTqECNANCE M*NU~L

W10431
W10432
W10434

Oil seal ring end-gaps must not align

with each other when installed in the
slip ring sleeve (3080).

ii"

Slip ring (3080) chamfer must face

towards the ring compressor.

Slip ring (3080)

Leave approximately 0.125 inch

(3.18 mm) of the slip ring out of
the ring compressor.

Installing the Ring Compressor on the Slip Ring and Oil Seal Rings
Figure 723

61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

CAUTION: ALIGNMENT OF ADJACENT OIL SEAL RING END-GAPS COULD

ADVERSLY AFFECT THE PROPELLER CONTROL AND
OPERATION.

(13) Position the end-gaps of the adjacent oil seal rings (3070,3090) to insure that they
do not align. Refer to Figure 723.

CAUTION: THE ID CHAMFER OF THE SLIP RING (3080) MUST FACE

TOWARDS TH E ENG IN E WH EN O1L TRANSFE R UN IT IS I NTALLED
ON THE ENGINE.

(14) Orient the slip ring (3080j with the ID chamfer facing the ring compressor. Refer to
Figure 723.

Refer
(15) Use a ring compressor to compress the oil seal rings (3070, 3090) in place.
to Figure 723.
(10) Apply reciprocating engine oil to the ID of the slip ring sleeve (4000).

W10433

Installation Block

7CC- ;LC5\r

Ring Compressor

Slip Ring Cap(4050)

Installing the Slip Ring and Oil Seal Rings into the Slip Ring Sleeve
Figure 724

61-10-14
 PROPELLER MPINUAL
HARTZ ELL

CAUTION: PRESSING THE SLIP RING TOO DEEP WILL ALLOW THE OIL SEAL
RINGS TO COME OUT OF THE SLIP RING AND WILL CAUSE
DAMAG E TO TH E UN IT WH EN I NSTALLED.

(17) Install the

slip ring (3080) and the oil seal rings (3070, 3090) into the slip ring
sleeve (4000). Referto Figure 724.

(18) Use solvent CM23 to clean the OD surface of the lip seal ring (3020) and the back
up ring (3010).
(19) Apply sealant CM46 to the OD surface of the lip seal ring (3020) and the back up
ring (301 0).
(20) Press the lip seal ring (3020) into thepropeller-side of the slip ring cap (4050) until
it contacts the shoulder. Referto Figure 71 9 for the correct orientation of the lip
seal ring.
(21) Press the back up ring (3010) into the propeller-side of the slip ring cap (4050)
until it rests
on the lip seal ring (3020). Refer to Figure 71 9.

CAUTION: MAKE SURE THE HOLE IN THE SLIP RING SLEEVE (4000) ALIGNS
WITH THE MOLE IN THE SLIP RING CAP (4050).
(22) For rear cone (3030) with the saw cut between two half round channels. Referto
Figure 506.

(a) Using adhesive CM10 or CM71, install the gasket (3050) in the slot of the
rearcone(3030).

NOTE: The adhesive is used to hold the gasket (3050) in place in the rear
cone (3030) during the installation on the engine.

(23) Place the (3030)and gasket (3050), pin (3040), oil line elbow (5010),
rear cone

gasket (5020), mounting bolts (4060), and mounting washers (4070) into a bag to
ship with the oil transfer unit.

NOTE: The rear cone(3030) and gasket (3050), pin (3040), oil line elbow
(5010), gasket (5020), mounting bolts (4060), and mounting washers
(4070) are not installed until the oil transfer unit assembly is installed on
the engine.

~ISSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

12. Assembly of Flanaed-Hub Models in the ´•5R Series

A. Hub Unit Assembly

Follow the pilot tube installation procedure in the Steel Hub Overhaul
(Ij
chapter of Hartzell Standard Practices Manual 202A (61-01-02).

CAUTION: THE END OF THE STUD WITH A DRILLED HOLE MUST

PROTRUDE FROM THE HUB AND THE ADJACENT THREADS
MUST BE KEPT FREE OF LOCKING COMPOUND CM16.

(2) Apply locking compound CM16 to the threads of the A-2983 studs and

thread them into the hub.

(3) Install the O-ring around the neck of the hub flange spacer.

(4) Install the O-ring inside the ID groove in the hub flange spacer.

(5) Press fit four dowel pins tone at either end). Allow each pin
in two holes
to protrude approximately 0.50 inch (12.7 mm).
I (6) Slide the hub flange spacer onto the studs protruding from the hub flange.

B. Blade Mounting Parts Assembly

(1) Follow "Blade Mounting Assembly" procedure described for
Parts
Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in
"Assembly of

I (2)
this chapter.

rv stop collar (beta ring)

table.
over the rotatable fixture of a

propeller assembly
Slide the spinner bulkhead the rotatable fixture.

I (3) over

(4)

61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 114C

C. Assembling Clamp and Counterweight

(1) Refer to the Blade Clamp Overhaul Chapter of Hartzell Standard

Practices Manual 202A (61-01-02),
(2) After each clamp is assembled:

(a) Peen the back of the counterweight flush against the clamp-half.

CAUTION: A LINK ARM CANNOT BE INSTALLED ON THE CLAMP-

HALF AFTER THE CLAMP HAS BEEN INSTALLED ON
THE HUB.

I (b) Install the link screw sleeve in the large hole of the link arm.

(c) Fit the link arm onto the link screw.

NOTE: The raised shoulder on the link arm must face outboard,
toward clamp.
I (d) Push the sleeve cotter pin through the hole in the end of the link
screw.

I (e) Open the cotter pin to safety it.

NOTE: The link arm should move freely on the link screw.

I (f) Repeat these assembly procedures for the other clamps and
counterweights.
(g)

I
Install the stop plate on the inboard surface of the clamp half
without a counterweight. Use two hex head bolts.

(h) Safety wire the fasteners together.

D. Installing Blades and Clamps
(1) Follow "installing Blades and Clamps" procedure described for "Assembly

I of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in

.retpahcsiht
E. Beta System Installation (Part 1 of 2)
(1) Using hex head bolts, attach the two-piece spinner mounting plate

I
to the
propeller mounting flange on the side facing the blade arms.

(2) Install theguide lugs into the spinner mounting plate and secure them with
a snap ring in the groove of the guide lug. The snap ring should be on

the side of the spinner mounting plate facing the engine.

61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

CAUTION: THE BETA ROD RETAINER RINGS (THREE-SEGMENT

COMPRESSION RINGS) MUST BE ASSEMBLED WITH THEIR
SHARP EDGES AGAINST EACH OTHER.

Slide the two retainer the inboard end of propeller beta

1 (3) rings over one

rod, into the groove provided for them in the rod.

NOTE: The rounded edges of the retainer rings must face away from

each other.

(4) Use thespecial tool TE65 (AST-2849) to crimp the retainer rings together
by compressing them to a 0.550 inch (13.97 mm) maximum OD.

(5) Slide a beta rod retainerthe outboard end of the propeller beta rod
over

and down onto the crimped keeper rings. (This retainer will later support
a spring.) The crimped keeper rings fit down
inside the beta rod retainer

I ID recegs.

(6) Slide a beta spring onto the outboard end of the beta rod.

(7) Use special tool TE29 (AT-725-1) to compress the beta spring by hand to

approximately half its length.

NOTE: Leave the special tool on the spring to aid further assembly
procedures.
Follow these procedures for the remaining propeller beta rod
(8)
subassemblies.

Insert the assembled beta rods through the guide bushings provided for
(9)
them in the spinner support plate.
F. Installing the Cylinder and Guide Collar
Install the socket head cap into the guide collar.
(1) screw

CAUTION: MAKE SURE THE CHAMFER OF THE GUIDE COLLAR IS

FACING THE CYLINDER SHOULDER.

(2) Install the guide collar onto the smaller diameter shoulder of the cylinder.
Do not tighten the guide collar, but allow it to rotate on the cylinder to
facilitate installation on the hub.

1 (3) Clean the threads on the hub and cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER.

(4) Apply a hydraulic adhesive CM134 in the

bead of groove of the hub

I (5)
where the cylinder O-ring will fit. Install the O-ring
chamfer, facing the hub.
Slide each beta rod through the hole provided
into the

for it in the
cylinder

guide collar.

61-10-14 RevP4a~ean:Os:
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

1 (6) Hand screw the cylinder onto the hub unit with the guide collar installed.

(7) Use asquare bar of appropriate size to fit the slot provided for it in the
top of the cylinder, and torque the c~linder against the hub unit (see
Torque Values Table 802 in Chapter 800).

NOTE: Tighten the cylinder flush with the shoulder on the hub. Early
drag and tightness is caused by the O-ring, which acts as a
seal and safety.

(8) Inspectthe slot in the top of the cylinder to make sure the square-bar
wrench used for torquing did not raise any sharp edges or damage the
threads.

(9) Remove any sharp edges in the wrench slot on top of the cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER. HYDRAULIC SEALANT ADHESIVE IN THE
CYLINDER MAY CONTAMINATE THE AIRCRAFT ENGINE OIL.

(10) Inspect the inside of the cylinder to make sure the O-ring has not been
forced out of place during the cylinder installation procedure.
G. Feathering Spring Assembly
(Ij Slide the retainer cup onto the pitch change rod with the cup

I
opening
facing away from the threaded end of the pitch change rod.
(2) Slide the spacer tube onto the pitch change rod and against the retainer
cup.

(3) Slide the springs over the spacer tube and into the retainer cup.

(4) Install the spring retainer and split ring using special fixture TE59´•to
rear

compress the springs. allowing insertion of the split ring into the groove of
the pitch change rod.

(5) Install four hex head bolts in the retainer cup center portion for feather
adjustment. Adjust each bolt an equal height above the retainer cup
surface.

NOTE: If during disassembly the bolt height was measured and

recorded, then set the bolts to this height.
1 (6) Safety wire the bolts.

61-10-14 RevP4aSJean~:
 PROPELLER MAINTENANCE MANUAL
nARTZELL 114C

H. Feathering Spring Assembly Installation

(1) Insert the shoulder of the retainer cup approximately 0.25 inch (6.35 mm)
and insert the split rings into the groove in the cylinder.
into the cylinder,
Slide the retainer cup against the split ring to hold it in place.
(2)
Install the ring retention plate over the split ring and retainer cup shoulder.
(3)
Thread the into the retainer cup shoulder to hold the ring retention
(4) screws

plate in place on the retainer cup shoulder.

the in the ring retention plate and safety wire the screws
(5) Tighten screws

to each other.

I. Installing PistonAssembly
CM12 and
(1) Lubricate the pitch change rod O-ring with approved lubricant
install it in the groove provided for it in the pitch change rod.

1 (2) Lubricate the piston O-ring with approved lubricant CM12 and carefully
install it in the groove provided for it in the piston.

Cut the necessary length of felt dust seal material and soak it in aviation
(3)

I grade reciprocating engine oil.

NOTE 1: The felt seal material should be cut on a 30 degree diagonal

line with a smooth,
so there will be an overlap at the parting

fuzz-free surface.

(4) Install the felt dust seal in the groove provided for it in the piston.
beta rods with the holes provided for them in the
(5) Align the propeller
piston.
(6) Slide the piston into place over the cylinder.

(7) Install the free end of each link arm in the slot provided in the piston.

(8) Install all link pin units and safety screws.

CAUTION: ENSURE THE PROPER SAFETY SCREW IS INSTALLED AND

THAT ADEQUATE THREADS ARE AVAILABLE IN THE PISTON
UNIT TO HOLD THE SCREW IN PLACE. AT LEAST THREE
I THREAD LENGTHS ARE SUFFICIENT. DO NOT BIND THE LINK
ARM.
the propeller beta
(9) Actuate the propeller assembly by hand to make sure
rods are straight and that the piston moves freely.
(16) Make sure the guide collar unit is seated solidly against the cylinder at

the correct radial location.

NOTE: If necessary, shift the guide collar unit radially to provide the
correct alignment between the piston and the beta rods.

ASSEMBLY 61110114
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(11) When the necessary alignment is confirmed, use an Alien wrench with
torquing adaptor to tighten the Nylock socket head cap screw in the guide
collar unit. See Torque Values Table 802 in Chapter 800.

(12) Remove the special tool TE29 from each beta spring and allow the spring
to extend between the guide lug and guide collar.

(13) Move the piston into the full feathered position (back against the hub
assembly) so that the threaded end of the pitch change rod protrudes
through the end of the piston.
(14) Thread the large flexlock nut onto the end of the pitch change rod.

I (15) Use a wrench on

the nut in accordance with

the nut and a socket the
pitch change rod to torque
on

Torque Values Table 802 in Chapter 800.

J. Start Lock Unit Reassembly
(1) Insert the pin into the start lock bracket.

(2) Insert the spring into the start lock bracket against the pin.
(3) Compress the spring, install the washer top of the spring, and insert
on

the cotter pin into the bracket to retain the washer, spring, and pin in the
bracket.

(4) Secure the cotter pin.

(5) Retract thepin and hold the in place with wire inserted in the hole in the
bracket body.

I NOTE: The pins will be released later for adjustment of the

angle. The pins are now retracted to aid assembly.
start lock

K. Start Lock Installation

(1) Position

I
one start lock unit per blade over the holes in the spinner
support plate for mounting the start lock units.
(2) Lift the spinner bulkhead against the spinner support plate and slide the
bolts through the start lock unit, the spinner support plate and, the spinner
bulkhead.

(3) Secure them with one washer and one lock nut on each bolt. Repeat for
all holes.

L. Application of Blade Angle Reference Tape

Follow"Application of Blade Angle Reference Tape" procedure described for
"Assembly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.

nsSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114c

I M. Setting Reverse and Feather Blade Angles

NOTE: stage of assembly the outboard clamp bolts have not been tightened
At this
because blade position relative to the clamp has not yet been set.

(1) Apply 125 to 150 psi (8.62 to 10.34 bars) air pressure to the piston
through the rotatable fixture on the propeller assembly table.
(2) Force the piston to reverse pitch position.

NOTE: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.
(3) Use abench-top protractor at the reference blade radius specified in the
Hartzell Propeller Application Guide, Manual 159 (61-02-59), to adjust the
angle of the blades, refer to Figure 709.
(4) Rotate the blades to reverse pitch position in the loose clamps.

NOTE: Blade angle of all blades must be within 0.2 degree of each
other at low pitch.
(5) Tighten the nuts on the outer clamp bolts. Refer to Torque Values Table
802 in Chapter 800.

(6) Release the pressure to the piston.

(7) Use abench-top protractor at the reference blade radius specified in the
Hartzell Propeller Application Guide, Manual 159 (61-02-59), to check and
adjust the feather angle of the blades. Refer to Figure 709.
(8) To increase the feathering angle, reduce the height of the hex head bolts
in the retainer cup. To decrease the feather angle, increase the height of
the hex head bolts in the retainer cup.

NOTE 1: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.

NOTE 2: A change in height of 0.031 inch (0.79 mm) will change the
blade angle approximately 1 degree.

PISSEMBLY 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 114C

N. Beta System Installation (Part 2 of 2)

(1) Thread a jam nut onto the engine side of each beta rod.

I CAUTION: DO NOT FORCE THE BETA RODS INTO THE BETA RING.
THEY COULD DIMPLE THE BETA RING GROOVE AND
INTERFERE WITH THE CARBON BLOCK. THIS WOULD CAUSE
THE BETA RING TO BE SCRAPPED.

(2) Thread one beta rod at a time into the threaded holes in the beta ring to

I
a depth of two threads each time. Use an open end wrench on the flats of
the beta rod to turn the beta rod.

(3) Repeat the above process with each beta rod in succession several times
until each beta rod is completely threaded into the beta ring.

(4) Unthread each beta rod out of the beta ring full thread, and then
one

tighten the jam nuts while holding the beta rods stationary with an open
end wrench.

I (5) Use
See
a dial indicator to check the runout of the beta
Figure 714 for setup.
ring at full feather.

CAUTION: BETA RING RUNOUT MUST BE KEPT WITHIN 0.010-INCH

TOTAL.

(6) Adjust the beta rods and jam nuts to adjust the runout.

(7) Install the check nut on the piston end of each beta rod.

(8) Install the piston end ring, rod end.

(9) Install the lock nut on each beta rod and tighten.
O. Setting Low Pitch Blade Angle
(1) Install one lock nut on the piston end of each beta rod.

(2) Pressurize the piston with partial air pressure to reach low pitch.

NOTE: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.

I
(3) Use a Bench top protractor at the reference blade radius specified in the
Hartzell Propeller Application Guide, Manual 159 (61-02-59), to adjust the
angle of the blades. Refer to Figure 709.

(4) Adjust the lock nut on each beta rod to just contact the piston ear with the
piston at low pitch.

I NOTE: Blade angle

other at low
of all blades must be within 0.2
pitch.
degree of each

~SSEMBLY 61110-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 114C

(5) Check the blade angle of all blade’s and determine if the blade angle
1 variance from blade td blade is within 0.2 degree of each
other. If not, the

blades must be in the blade clamps (clamps loosened) and the

slipped
blade angle setting procedure repeated.
I P. Final Beta Ring Runout Check

CAUTION: BETA RING RUNOUT MUST BE KEPT WITHIN 0.010-INCH

(0.25 MM) TOTAL. ADJUST AS NECESSARY.
at low pitch and the piston just touching the lock nuts
(1) With the propeller
on each beta rod, check the beta ring runout.

(2) Refer to Figure 713 for the setup.

Pressurize the propeller to reverse blade angle and check the beta ring
(3)
runout.

Q. Setting Start Lock Blade Angle

to engage the
(1) Release the pins in the start lock brackets to allow them
start lock plates on the inboard side of the clamps.
in the
(2) Use bench-top protractor at the reference blade radius specified
to adjust
Hartzell Propeller Application Guide, Manual 159 (61-02-59),
start lock blade angle.

NOTE: Refer to the applicable Type Certificate Data sheet,

I Supplemental Type Certificate Data sheet, or Hartzell Propeller

Application Guide Manual 159 (61-02-59), for the specific
angle required.
(3) File the start lock plates to adjust the start lock angle, if required.

R. Providing for Visual Detection of Blade Slippage in Clamp

Follow "Providing for Visual Detection of Blade Slippage in Clamp" procedure

-1 and -6 Series" in
described for "Assembly of Two-Blade, Flanged-Hub Models in the
this chapter.

S. Sealant CM93 Application

Follow "Sealant CM93 Application" procedure described for "Assembly of Two-Blade,
Flanged-Hub Models in the -1 and -6 Series" in this chapter.
T. Checking Blade Track

"Checking Blade Track" procedure described for "Assembly Two-Blade,

of
Follow
Flanged-Hub Models in the -1 and -6 Series" in this chapter.
I U. Decal Replacement
Follow "Decal Replacement" procedure described for "Assembly of Two-Blade,
Flanged-Hub Models in the -1 and -6 Series" in this chapter.

Page 787

ASSEMBLY 61110114 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

V. Propeller Removal From Assembly Table

(1) Loosen the boltsholding propeller hub to the rotatable fixture of the
propeller assembly table.
1 (2) Remove the propeller assembly and place it on a propeller cart for
transportation.

13. Assembly of Flanaed-Hub Models in the -5(A.AL) Series

A. Hub Unit Assembly

(1) Follow the pilot tube installation procedure in the Steel Hub Overhaul
I chapter of Hartzell Standard Practices Manual 202A
(61-01-02).
B. Blade Mounting Parts Assembly
(1) Follow "Blade Mounting Parts Assembly" procedure described for
I this chapter."As embly of Two-Blade, Flanged-Hub Models in the -1 and -6 Series" in

(2) Mount on the rotatable fixture of a propeller assembly table.

C. Assembling Clamp and Counterweight

(1) Refer to the Blade Clamp Overhaul Chapter of Hartzell Standard

Practices Manual 202A (61-01-02),
(2) After each clamp is assembled:

(a) Peen the back of the counterweight flush against the clamp-half.
CAUTION: A LINK ARM CANNOT BE INSTALLED ON THE CLAMP-
HALF AFTER THE CLAMP HAS BEEN INSTALLED ON
THE HUB.

I (b) Install the link screw sleeve in the large hole of the link arm.

(c) Fit the link arm onto the link screw.

NOTE The raised shoulder on the link arm must face outboard,

I (d) Push the sleeve cotter

the
drawotknil clamp.
pin through the hole in the end of the
screw.

NOTE: The link arm should move freely on the link screw.

I (e)
(f)
Open the cotter

Repeat these assembly procedures

pin to safety it.

for the other clamps and

counterweights.

I
(g) Install the stop plate the inboard surface of the clamp half
on
without a counterweight. Use two hex head bolts per plate.
(h) Safety wire the fasteners together.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 114C

D. Installing Blades and Clamps

(1) Follow "lnstalling Blades and Clamps" procedure described for "Assembly
Models in the -1 and -6 Series" in this
I .retpahcbuH-degnalF
of Two-Blade,

E. I nstalling the Cylinder and Guide Collar

Install the socket head cap screw into the guide collar.
(1)

I CAUTION: MAKE SURE THAT THE CHAMFER OF THE GUIDE COLLAR IS

FACING THE CYLINDER SHOULDER AND THAT THE LARGER
ID OF THE CYLINDER IS FACING AWAY FROM THE CYLINDER
FOR HUB CLEARANCE.

(2) Install the guide collar onto the smaller diameter shoulder of the cylinder.
I Do not tighten the guide collar, but allow it to rotate on the cylinder to
facilitate installation on the hub.

1 (3) Clean the threads on the hub and cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER.
the groove of the
(4) Apply a hydraulic sealant adhesive CM134 in
bead of
hub where the cylinder O-ring will fit. Install the O-ring into the cylinder

I (5)
chamfer, facing the hub.
Hand screw the cylinder onto the hub unit with the guide collar installed.

the slot provided for it in the

(6) Use asquare bar of appropriate size to fit
the hub unit (see
top of the cylinder, and torque the cylinder against
Torque Values Table 802 in Chapter 800).

NOTE: Tighten the cylinder flush with the shoulder on the hub. Early
drag and tightness is caused by the O-ring, which acts as a
seal and safety.

(7) Inspectthe slot in the top of the cylinder to make sure the square-bar
wrench used for torquing did not raise any sharp edges or damage the
th reads.

(8) Remove any sharp edges in the wrench slot on top of the cylinder.

CAUTION: DO NOT APPLY SEALANT TO THE THREADS OF THE

CYLINDER. HYDRAULIC SEALANT ADHESIVE IN THE
CYLINDER MAY CONTAMINATE THE AIRCRAFT ENGINE OIL.
not been
(9) Inspect the inside of the cylinder to make sure the O-ring has
forced out of place during the cylinder installation procedure.

,,,,,L, 61-10-14 RevP4aSJean~jJ

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

F. Feathering Spring Assembly

(1) Install four hex head bolts in the retainer cup center portion for feather
adjustment.
(2) Adjust each bolt an equal height above the retainer cup surface.

NOTE: If the bolt

height was measured and recorded during
disassembly, then set the bolts to this height.
(3) Slide the retainer cup onto the pitch change rod with the cup opening
facing away from the threaded end of the pitch change rod.
(4) Slide the spacer tube onto the pitch change rod and against the retainer
cup.

(5) Slide the springs over the spacer tube and into the retainer cup.

(6) Install the spring retainer and split ring using special fixture TE59 to
rear

compress the springs, allowing insertion of the split ring into the groove of
the pitch change rod.

(7) Safety wire the hex head bolts in the retainer cup.

G. Feathering Spring Assembly Installation

(1) Insert the feathering spring into the cylinder and insert the split rings into
the groove in the cylinder.
(2) Slide the retainer cup against the split ring to hold it in place.
(3) Install the ring retention plate over the split ring and retainer shoulder.

(4) Thread the screws into the retainer cup shoulder to hold the ring retention
plate in place on the retainer cup shoulder.

(5) Tighten the screws in the ring retention plate and safety wire the screws
to each other.

H. Installing Piston Assembly

I (1) Lubricate the pitch change rod O-ring with approved lubricant CM12 and
install it in the groove provided for it in the pitch change rod.

1 (2) Lubricate the piston O-ring with approved lubricant CM12 and carefully
install it in the groove provided for it in the piston.

(3) Cut the necessary length of felt dust seal material and soak it in aviation
grade oil.

NOTE: The felt seal material should be cut on a 30 degree diagonal

so there will be an overlap at the parting line with a smooth,

fuzz-free surface.

(4) Install the felt dust seal in the groove provided for it in the piston.

61-10-14
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 114C

(5) Slide the piston into place over the cylinder.

NOTE: The guide rod is not removed from the piston during overhaul
unless it is damaged or some other condition warrants its
removal.
with the holes provided for
(6) Align the piston guide rods, where applicable,
them in the guide collar unit.

(7) Install the free end of each link arm in the slot provided in the piston.

(8) Install all link pin units and safety screws.

I CAUTION: ENSURE THE PROPER SAFETY SCREW IS INSTALLED AND

THAT ADEQUATE THREADS ARE AVAILABLE IN THE PISTON
UNIT TO HOLD THE SCREW IN PLACE. AT LEAST THREE
I THREAD LENGTHS ARE SUFFICIENT. DO NOT BIND THE LINK
ARM.

(9) Actuate the propeller assembly by hand to make sure propeller beta
the

I rods, where applicable, are straight and that the piston moves freely.

(13) Make sure the guide collar unit is seated solidly against the cylinder at

the correct radial location.

NOTE: If necessary, shift the guide collar unit radially to provide the
correct alignment between the piston and the guide rods.

(11) When the necessary alignment is confirmed, use an Alien wrench with
in the guide
torquing adapter to tighten the Nylock socket head cap screw
collar unit. See Torque Values Table 802 in chapter 800.

I (12) Move the piston position (back against the hub

into full feathered
assembly) so that the threaded end of the pitch change rod protrudes
through the end of the piston.
nut onto the end of the pitch change rod.
(13) Thread the large flexlock
(14) Use wrench the nut and a pitch change rod to torque
socket on the

I
a on

the nut in accordance with the Torque Values Table 802 in chapter 800.

Install the socket head cap screw, washer(s), and check nut on the end of
~15)
each piston guide rod.

I. Start Lock Unit Reassembly

(1) Insert the pin into the start lock bracket.

(2) Insert the spring into the start lock bracket against the pin.

(3) Compress the spring, install the washer on top of the spring, and insert
the cotter pin into the bracket to retain the washer, spring and pin in the
bracket.

(4) Secure the cotter pin.

ASSEMBLY 61110114 RevP4asJea~l

 PROPELLER
HARTZ ELL MA:NI~ECNANCE MANUAL

(5) Retract thepin and hold it in place with wire inserted in the hole in the
bracket body.

I NOTE: The pins will be released later for adjustment of the

angle. The pins are now retracted to aid assembly.
start lock

J. Start Lock Unit Installation

Attach each start lock unit ~one per blade) with two bolts to the propeller hub flange.

NOTE: On propellers of this model series the spinner bulkhead attaches to the start
lock unit.

K. Application of Blade Angle Reference Tape

Follow "Application of Blade Angle Reference Tape" described for "Assembly of Two-
Blade, Flanged-Hub Models in the -1 and -6 Series" in this chapter.
L. Setting Blade Angle

NOTE: At this
stage of assembly the outboard clamp bolts have not been tightened
because blade position relative to the clamp has not yet been set.

CAUTION: BLADE ANGLE OF ALL BLADES MUST BE WITHIN 0.2

DEGREE OF EACH OTHER AT A LOW PITCH.

(1) Apply 125 to 150 psi (8.62 to 10.34 bars) air pressure to the piston
through the rotatable fixture on the propeller assembly table.
(2) Force the piston to reverse pitch position. (Piston push rods are bottomed
on guide collar.)
(3) Use bench-top protractor at the reference blade radius specified in the
HartzellPropeller Application Guide, Manual 159 (61-02-59), to adjust the
angle of the blades. Refer to Figure 709.

NOTE: Refer to the applicable Type Certificate Data sheet,

Supplemental Type Certificate Data sheet, or Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the specific
angle required.
(4) Rotate the blades to
I (5) Tighten the nuts on the
reverse

outer
pitch position
clamp
in the loose

bolts. Refer to
clamps.
Torque Values Table
802 in Chapter 800.

(6) Check the angle of each blade and verify that the maximum blade angle
variance between blades is 0.2 degree. If it is not, then reset the blades
in the clamps.

(7) Remove air from propeller piston and allow pitch change mechanism to
reach feather position.

ASSEMBLY 61’10’14
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

in the
(8) Use bench top protractor at the reference blade radius specified
a
check
Hartzell Propeller Application Guide, Manual 159 (61-02-59),
to

feather blade angle. Adjust if required.

NOTE If the featherangle is incorrect, remove the piston and adjust

the height of the feathering stop bolts in the spring
retainer
reduce the height of the four
cup. To increase feathering angle,
hex head bolts in the spring retainer cup. To decrease
head bolts
I feathering angle increase the height of the four hex
is
in the spring retainer cup. A height of .031 inch (0.79 mm)
approximately equal to 1 degree.

CAUTION: RESAFETY FEATHER STOP BOLTS TOGETHER.

them to engage the
(9) Release the pins in the start lock brackets to allow
start lock plates on the inboard side of the clamps.

at the reference blade radius specified in the

(10) Use a bench top protractor
Hartzell Propeller Application Guide, Manual 159 (61-02-59), to check
start lock blade angle.

(11) File the start lock plates to adjust the start lock angle, if required.

M. Providing for Visual Detection of Blade Slippage in Clamp

described for
Follow"Providing for Visual Detection of Blade Slippage in Clamp"
-1 and -6 Series" in this chapter.
"Assembly of Two-Blade, Flanged-Hub Models in the
N. Sealant CM93 Application
Follow "Sealant CM93 Application" "Assembly of Two-Blade, Flanged-
described for
Hub Models in the -1 and -6 Series" in this chapter.

O. Checking Blade Track

Follow"Checking Blade Track" described for "Assembly of Two-Blade, Flanged-Hub
Models in the -1 and -6 Series" in this chapter.

P. Decal Replacement
Follow "Decal Replacement" described for "Assembly of Two-Blade, Flanged-Hub
Models in the -1 and -6 Series" in this chapter.

Q. Propeller Removal From Assembly Table

Unfasten the bolts holding the propeller hub to the rotatable fixture of the
(1)
propeller assembly table.

and it propeller cart for

(2) Remove the propeller assembly place on a

transportation.

Page 793

ASSEMBLY 61110~14 Rev. 4 Jan/Ol

 PROPELLER MAINTENANCE
HA RTZ E L L C411LAUNAM
(3) Attach the spinner bulkhead to the start locks as applicable.
NOTE 1: On propellers of this model series the spinner bulkhead
attaches to the start lock units.

NOTE 2: A B-1457 reversing valve unit is installed in the engine shaft to

facilitate operation of this propeller model series. Three
O-rings and a staking pin are needed for installation of the
reversing valve unit.

ASSEMBLY 61110114
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

CONTENTS

802
1. Wear Tolerances
805
2. Torque Values

TABLES

803
Table 801 Wear Tolerances
806
Table 802 Torque Values

ILLUSTRATIONS

Standard Torque Wrench with Adaptor Figure 801 805

Determining Torque Value of a

FITS AND CLEARANCES

61-10-14 Page
BO~Mar/98
 PROPELLER MAINTENANCE
HA RTZ E LL C411LAUNAM
1. Wear Tolerances

Certain propeller assembly parts are subject to wear and

require replacement when
dimensions exceed the permissible range. Refer to Table 801 and
replaceout-of-
tolerance parts as necessary for safe operation.

FITS AND CLEARANCES 61 ’1 0’1 4

 Specified Dimension Specified Dimension Replace if Exceeds Replace if Exceeds
(Inches) (mm)
PartNumber Description
Max
(Inches)
Min Max
(mm)
Min Max Min Max Min
I

834-18,-18L GuideCollarbssembly
A-3674(L) Collar With Bushing, Guide Collar, 0.384 0.381 9.75 9.68 0.387 9.83 ~J
A-3023 Bushing Inside Diameter

834-1 -2A, -7B Guide Collar Assembly

N
B-l 402(B,L,BL), Bushing, Guide Collar, 0.510 0.508 12.95 12.90 0.513 13.03
1~
Inside Diameter
B-l 836-2, 8-892
Collars With A-1 16D-1
I I I I I I I

Bushing
r

834-3RA Guide Collar Assembly

B-824RA Collar With Bushing, Guide Collar, 0.510 0.508 12.95 12.90 0.513 13.03
A-i 16F-1 Bushing Inside Diameter I I I I I I I I I ’T1

O
834-10 Guide Collar Assembly
0.509 12.93
B-222-2 Collar With Bushing, Guide Collar, 0.506 0.504 12.85 12.80
F
P~116F-1 Bushing InsideDiameter
E
u, ~a
834-14 Guide Collar Assembly
8-2953 Collar With Bushing, Guide Collar, 0.378 0.376 9.60 9.55 0.381 9.68
Z
A-3023 Bushing Inside Diameter
O p
r
m 834-9 Guide Collar Assembly O~
0.504 12.85 12.80 0.509 12.93 E,
B-l 326-1 Collar With Bushing, Guide Collar, 0.506
Z
a-1 Isnl Bushing Inside Diamef er
r
0 A-862 Bushing, Piston, 3.782 3.780 96.06 96.01 3.786 96.164
Inside Diameter
C
A-862-2 Bushing, Piston, 4.284 4.282 108.81 108.76 4.288 108.92

0) Inside Diameter
I

B-855A, B-855-2A Pitch Change Rod 0.985 0.984 25.02 24.99 0.980 24.89
Shaft

1 D-5862, D-5862-5 Pitch Change Rod 0.735 0.734 18.67 18.64 0.731 18.57
Shaft
I

1 B-1465 Pitch Change Rod 0.736 0.735 18.69 18.67 0.732 18.59
Shaft

fs Wear Tolerances
~I (I, Table 801
 Specified Dimension Specified Dimension Replace if Exceeds Replace if Exceeds
Part Number Description (Inches) (mm) (Inches) (mm)
Max Min Max Min Max Min Max Min

B-2001 Pitch Change Rod 0.736 1 0.735 18.69 18.67 0.732 18.59 121
Shaft
’´•1
8-854, B-854-1 Cylinder Outside Dia. 3.778 3.776 95.96 95.91 3.773 95.83 N
B-l 882 Cylinder Outside Dia. 4.280 4.278 108.71 108.66 4.275 108.59
r
B-806, B-806-1 Cylinder Outside Dia. 3.780 3.778 96.01 95.96 3.775 95.89 1

A-304 Linkscrew 0.501 0.499 12.73 12.68 0.497 12.62

A-3067-2,-5 Bushing, Guide Lug, 0.378 0.376 9.60 9.55 0.382 9.70
’C]
Inside Diameter
O
A-944 Sleeve, Link Screw, 0.502 0.501 12.75 12.73 0.504
I! 12.80
Inside Diameter
F:
m
A-944 Sleeve, Link Screw, 0.562 0.561 14.28 14.25 1J
Z 0.560 14.22
Outside Diameter
O
r
B-3002-7, B-3475A-2 Z
m
Rod, Beta, 0.374 0.372 9.50 9.45 0.370 9.40 P
Outside Diameter O m
3LI Z

Z
B-1901 (L), A-861 -3(L) Link Arm, 0.5640 0.5630 14.326 14.300 0.5645 Z
14.338
O (Large Hole) Inside Diameter O
C:m
B-l 901(L), A-86 1 -3(L) LinkArm, 0.3770 0.3760 9.576 9.550 0.3775 9.589
(Small Hole) Inside Diameter Z
C
Q) B-1901(L), A-861-3(L) Link Arm, 0.415 0.405 10.54 10.29 0.400 10.16 1 F
(Large Hole Boss) Thickness

L
1 lA-1496 Tube, Pilot
(See Hartzell Standard (Inboard End)
C) Practices Manual 202A
’1 1161-01 -02fordimensions)
IP l1A1496 Tube, Pilot
(See Hartzell Standard (Outboard End)
Practices Manual 202A
61 -01 -02 for dimensions)

cp,
B-2952, B-3001-2 Ring, Beta, 0.503 0.501 12.78 12.73 0.510 12.95
GrooveWidth
cop

Wear Tolerances
Table 801
 PROPELLER MAINTENANCE MANUAL
H~A RT Z E L L 114C

2. Torque Values

Threaded fasteners and hardware are the weakest components in an assembly.

Vibration can cause animproperly tightened fastener to fail in a matter of minutes.
Proper tension in a fastener depends on a variety of known load factors and can
influence fastener service life. Proper tension is achieved by application of measured
torque.
Accurate wrenches and professional procedures will result in precision tensioning.
Refer to Table 802 for proper torque values on Hartzell propeller assembly hardware.

When an adaptor is used with a torque wrench, use the equation in Figure 801 to
determine the torque value.

APS212

Torquing Adaptor
Standard Torque Wrench

1.00 foot 7’ 0.50 foot

(304.8 mm) (152.4mm)

ttoraue wrench length)

torque wrench reading
tactual torque required) x
to achieve required
(torque wrench length) (length of adaptor)
actual torque

EXAMPLE:
reading on torque
wrench with 6-inch
100 Ft-Lb (136 N-m~ x 1 ft (304.8 mm~
_

66.7 Ft-Lb (228.6 mm) adaptor

1 ft (304.8 mm) 0.50 ft (228.6 mm)
(901 N-m) torque of
for actual
100 Ft-Lb (136 N-m)

Determining Torque Value of a Standard Torque Wrench with Adaptor

Figure 801

FITS FIND CLEPIRANCES S1 -1 0-1 4

 PROPELLER
HARTZ ELL MA:N1T~NANCE
C411LAUN~PM

Part I Torque"
Number Nomenclature foot-pounds newton-meter inch-pounds

A-279 Lubrication Fitting 4 5 50

A-304 Link Screw 35-45 47-61 420-540

A-321 Screw, Socket, Clamp 40 54 480

A-880-() Nut, Flexlock 120 163 1440

A-2043-1 Nut, Self-Locking, Hex 35 47 420

(Installs on Outer Clamp
Bolt)

A-2036-( Cap Screw, Socket Hd. 65 88 780

(counteMleight)

A-2038-( Cap Screw, 4 5 48

Nylon Socket
(Guide Collar)

A-3439 Nut, Jam, Beta 12 16 144

8-3359 Nut, Elastic 12 16 144

8-3384-( Bolt, Hex Head 3-8 4-11 36-96

A-2044 Nut, Self-Locking, 80-90 108-122 960-1 080

Propeller Mounting,
F Flange

A-63-B Nut, Shaft, 20 Spline 450 610 5400

B-3386-14H Bolts used to clamp 15-19 21-25 180-228
guide collar onto hub
(HC-A2(MV,V)20-4A1)

A-2037 Screw, Socket Head, Cap 10 14 120

8-3368 Nut, Check 10 14 120

A-2626-( Screw, Socket Head, Cap,( 2 3 25

for Start Lock Adjustment

Torque values are +10 percent unless otherwise noted.

Torque Values
Table 802

FITS AND CLEARANCES 61-10-14 RevlJune/gSPage 806

 PROPELLER MAINTENANCE MANUAL
H19 RT Z E L L 114C

Part Torque"
Number Nomenclature foot-pounds newton-meter inch-pounds
A-1 328 Bolt, 12-Point, 80-90 108-122 960-1 080
Propeller Mounting,
FFlange

A-2039 Screw, Set 2-3 3-4 24-36

(In Pitch Change Fork)

A-848-2 Nut, Flexlock 20-22 27-30 240-264

(End of Piston Rod)

A-1 333-3 Bolt, Hex Head, 60-70 81-95 720-840

Propeller Mounting,
K Flange

A-1 333-2 Bolts, 60-70 81-95 720-840

A-1328 and PropellerMounting,
A-1 333-3 KFlange
Lycoming 10-720 Engine 100-125 136-170 1200-1500

A-1333-3 Bolt, Hex Head, 60-70 81-95 720-840

Propeller Mounting,
K Flange
Lycoming 10-720 Engine 100-125 136-170 1200-1500

A-2016 Bolt, Stop Plate Mounting 2.5 3 30

A-2051 Bolt, Spinner Support 15 20 180

Plate Mounting

8-322 Bolt, Hex Head, 50 68 600

or A-943-1 P repeller Mou nting,

L Flange

B-3805 Bolt, Oil Transfer 18-22 24-30 216-264

Unit Mounting

A-2053 Nut, Shaft, 300+10 407+14 3600~1 20

or A-2059 Propel ler Mou nti ng

Torque values are +10 percent unless otherwise noted.

Torque Values
Table 802

807
FITS AND CLEARANCES 61-10-14 Rev 1 June/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Part Tor
Number Nomenclature foot-pounds newton-meter inch-pounds

B-806 Cylinder 125-150 169-203 1500-1800

B-806-1 Cylinder 125-150 169-203 1500-1800

8-854 Cylinder 125-150 169-203 1500-1800

B-854-1 Cylinder 125-150 169-203 1500-1800

B-1882 Cylinder 125-150 169-203 1500-1800

Aluminum Blade, mounted in blade clamp 167 226 2004

Torque values are +10 percent unless otherwise noted.

Torque Values
Table 802

FITS AND CLEARANCES 61-10-14 Rev 1 June/9 Page 808

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

CONTENTS

903
Torque Wrench Adaptor Figure 901
904
Spring Compressor Figure 902

903 905
Adjustable Riser Fixture and Bench-Top Protractor Figure
906
Spring Compressor Fixture Figure 904
905 907
Beta Rod Retainer Installation Tool Figure
908
~igital Protractor Figure 906
909
Beta System Puller Figure 907
910
Retention Bearing Puller Figure 908
911
Propeller Table Spindle Figure 909
912
Shaft Nut Wrench Figure 910
913
Press Tool Figure 911

Page 901
SPECIPiLTOOLS, FIXTURES, P´•NOE~UIPMENT
61-10-14 Mar/98
 PROPELLER
HA RTZ E L L MA:N:4ECNANCE MANUAL

SPECIAL TOOLING AND FIXTURES FOR SERVICING THE THREE-BLADE AND

FOUR-BLADE TURBINE PROPELLER

1. Refer to Hartzell Tool and Equipment Manual 165A (61-00-65) for

specialty tooling application and part numbers.
2. Variousspecial tools and fixtures are required for proper and efficient
disassembly and reassembly of the propeller. This list is for reference
only.
3. Most of these tools and fixtures are available from the factory. Order by
Part Number and Description from Manual 165A.

Part Number Description

TE5 Torquing Adapter for Propeller Mounting Bolt Wrench

TE29 Tool to Compress Beta Spring
TE48 Riser Fixture to Adjust Height of Bench-Top Protractor (optional)
TE59 Fixture for Assembly of the Feathering Spring
TE65 Installation Tool for Beta Rod Retainer Rings
TE96 Bench-Top Protractor to Set Blade Angle (optional)
TE97 Hand-Held Protractor to Set Blade Angle
TE100 Tool to Compress the Beta System
TE108 Puller Tool for Hub Split-Bearing Guide Ring
TE125 Rotatable Fixture for Mounting Propeller on Table
TE142 Wrench to Torque Outboard Clamp Bolts
TE146 Wrench to Tighten Mounting Shaft Nut on #20 Spline Propellers

SPECIAL TOOLS, FIXTURES, AND EPUIPMENT 61 ’1 0’1 4 PagMeas~

 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 114C

APS-543

Part Number: See Hartzell Tool Manual 165A for the required torque wrench adaptor
part numbers.

DescrilJtion: Wrench adaptor to install and torque mounting bolts. Used in conjunction
with a standard ’ln-inch square drive torque wrench.

Propeller
Mounting StandardTorque
Wrench
Flange
Aircraft Engine
/Ma~ndngFlange

Propeller
Mounting Mounting Torque Wrench Adaptor
O-ring Bolt

Torque Wrench Adaptor

Figure 901

Page 903
SPECULTODLS, FIXTURES,~NO EaUIPMENT
61 -1 0-1 4 Mar/98
 PRDPELLER MANUPIL
HARTZ E LL

Part Number: AT-725-1 (TE29)

Description: Spring compressor for beta springs during assembly.

Special
tool

Propeller

Beta

In use
Guide
ruarc Snap

Spring Compressor
Figure 902

8PeCIAL TOOLS, FIXTURES, AND EPUIPMENT 61 -1 0-1 4

 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 114C

nPs-tss-1

Part Number: CT-1075 (TE48)

measurements during assembly. Used in
Descriotion: Fixture to allow blade angle
conjunction with a bench-top protractor.

Bench-Top Protractor
PE 105 (TE96)

Riser Fixture
No. CT-1075

Adjustable Riser Fixture and Bench-Top Protractor

Figure 903

Page 905
SpECULTOOLS, FIXTURIS,PIND EL~UIPMENT
61’1 0-1 4 Mar/98
 PROPELLER MAINTENANCE
HA RT Z E L L C411LAUNAM

APS-545

Part Number: CST-2914 (TE59)

De~: Fixture to compress the feathering
spring sufficiently to allow assembly
or disassembly of the spring assembly.

Supersedes: C-845-2

Spring Compressor Fixture

Figure 904

SPECIAL TOOLS, FIXTURES, AND EOUIPMENT 61 ’1 0’1 4 Page

906Mar/98
 PROPELLER MAINTENANCE MAN UAL
H1~ RTr E L L 114C

APS-PO1

Part Number: AST-2849 (TE65)

Description: Tool tocrimp the beta rod retainers onto the beta rod. Used in

conjunction with a standard vise.

For best grip on

beta rod do not line

:´•r~´• up retainer ring slots

Beta Rod Retainer Installation Tool

Figure 905

SPECI*LTOOLS, FIXTURES, IIND E(IUIPMENT 61 -1 0-1 4

 PROPELLEA
HARTZELL MA:NIJ~CNPINCE MPINU~L

APS-336

Part Number: BST-2960-1 (TE97)

Description: Protractor to measure blade angles. May be used to check angles with
propeller installed on engine.
Supersedes: BST-2820 and CST-2880

BST-2960
Carrying Case

Digital Protractor
Figure 906

SPECI*L TOOLS, FIXTURES, *ND EQUIPMENT 61 -1 0’1 4

 PROPELLER MAINTENANCE MANUAL
~IARTZELL 1149

CPS-795

Part Number: CST-2987 (TE100)

Description: Puller to compress the beta system to gain access to the propeller
mounting bolts for propeller removal and installation,
Supersedes: CST-2834

d~-

In use

BetaSystem Puller
Figure 907

SPECI*LTODLS, FIXTURES,PIND EOUIPMEM

61-1 0-1 4
 PROPELLER MAINTENANCE
HA RT Z E L L C411LAUNAM

APS-189-1

Part Number: BT-223 (TE108)

Description: Puller to remove and install bearings on steel hub spiders. Used in
conjunction with BST-3061 and BST-3062.

O BST-3061 or BST-3062
to pull bearing guide ring into position

Retention Bearing Puller

Figure 908

Page
SPECIAL TOOLS, FIXTURES, AND ECJUIPMENT 61 ’1 0’1 4 910Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

APS-546

PartNumber: BST-2912(TE125) Spindle Base; supersedes: 8-843-2 (Includes

TE85)
BST-2912-1 (TE124) Flanged Hub Spindle; supersedes: BST-2812
(Includes TE4)
BST-2912-2 (TE122) #20 Spline Spindle; not shown (Includes
TE325)

Description: Spindle mounts to propeller table to allow pressurizing of propeller to

change pitch. Also allows rotating of the propeller.

8ST-2912-1
Flanged Hub Spindle

BST-2912
Spindle Base

Propeller Table Spindle

Figure 909

SPECULTOOLS,
61-10-14
 PROPELLER
HARTZELL MI:N~ANCE M*NUP.L

Part Number: BST-2804 (TE146)

Description: Wrench to tighten the propeller mounting shaft nut on #20, #30, and #40
splined propellers.
Supersedes: BT-2804, BST-840, and BST-2910

r- -1,__ _,j- _ _ _ _ _ _

o
--I

Shaft Nut Wrench

Figure 910

SPECIAL TOOLS, FIXTURES, ANo EGIUIPAIIENT 61 ’1 0’1 4 Page

912Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

Part~: BST-3062 (TE309)

Descriation: Used to press split bearings in steel hub propellers.

Press Tool
Figure 911

Page 913
SPECIALTOOLS, FIXTURES, FIND E~UIPMENT
61 -1 0-1 4 Mar/98
 PROPELLER MAINTENANCE
HA RT Z E L L C411LAUNAM

(This page is intentionally blank.)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT 61 ’1 0’1 4 Page

914Mar/98
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

CONTENTS

1003
HC-A2V20-4A1
1005
HC-A2MV20-4A1
1007
HC-A2V(F,K,L)-2(A,
1009
HC-A2MV(F,K,L)-2(A,B)
1011
HC-A2V(F,K,L)-(1 ,6)(A,F)
1013
HC-A2MV(F,K,L)-(I ,6)(A,F)
1015
HC-A3VK-2(A,B,C,BL)
1017
HC-ASMVK-P(A,B,C,BL)
1019
(E,P)HC-n3V(F,K)-4(D)
1021
(E,P)HC-A3MV(F,K)-4(D)
1023
HC-A3V20-2(A,L)
1025
HC-A3MV20-2(A, L)
1027
(E,P)HC-A3VF-2(A,B,C,D)
1029
(E, P)HC-A3MVF-P(A, B,C, D)
1031
HA-A2V20-1B
1033
HA-A2MV20-IB
1035
HC-A2V20-2
I HC-A2MV20-2()
1037

1039
HC-A2V20-1 A
1041
HC-A2MV20-1 A
1043
HC-A3V20-I(B,D,E,F)
1045
HC-A3MV20-1 (B,D,E,F)
1047
BHC-A2VF-3
1049
BHC-A2MVF-3
1051
HC-A3VF-3L
1053
HC-A3MVF-3L
1055
HC-A3VF-5(A,B,L,AL,BL)
1057
HC-A3MVF-5(A,B,L,AL,BL)
1059
(P)HC-A3VF-5R

1001

ILLUSTRATEDPARTSLIST 61-10-14
 PROPELLER
HARTZ ELL MA:N1T~SIANCE MANUAL

(P)HC-A3MVF-5R
HC-A3V20-3L 1063
HC-A3MV20-3L 1065
Oil Transfer Unit Assembly t 068

Oil Transfer Unit Assembly

Figure 10-1 ........._
1067

I,,,,,,,,,, 61-10-14
 PROPELLER MAINTENANCE MANUAL
HA,RTZ E L L 114C

i
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0-220-1
HC-A2V20-4A1

Page 1003/1004
ILLUSTRATED PARTS LIST 61-10-14 Rev. 4 Jan/Ol
 PROPELLER MAINTENANCE MANUAL
114C

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0-220-2A
HC-A2MV20-4A1

Page 1005/1006
ILLUSTRATED PARTS LIST 61 I10-14 Rev. 4 Jan/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

0-2530
1 ’F-Z.B’F-2P.5R)P MOUNn~j F)lii~S
0-2509 NEnDBOLTS

B-3875-18H HEX HEAD BOLTS h~ I t~xl 84()-95 84i) 16

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Page 1007/1008
ILLUSTRATED PARTS LIST 61-1014 Rev. 4 Jan/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

0-2530 A55tCYIBL~
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Page 1009/1010
ILLUSTRATED PARTS LIST 61 I10-14 Rev. 4 Jan/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1146

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D-985-1

Page 1011/1012
ILLUSTRATED PARTS LIST til-10-14 Rev 1 June/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1149

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 PROPELLER MAINTENANCE MANUAL
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Page 1059/1060
ILLUSTRATED PARTS LIST 61-10-14 Rev. 4 Jan/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZ E 114C

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Page 1061/1062
ILLUSTRATED PARTS LIST 61-10-14 Rev. 4 Jan/Ol
 PROPELLER MAINTENANCE MANUAL
HP~ RT’Z E L L 114C

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Page 1063/1064
ILLUSTRATED PARTS LIST 61-10-14 Rev 1 June/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1142

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Page 106511066
ILLUSTRATED PARTS LIST 61-10-14 Rev 1 June/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(This page is intentionally blank.)

I 61-10-14 Rev. 5 Aug/OlPage 1067

 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

A-224-4.PLT

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1068
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

FIG.IITEM PART AIRLINE DESCRIPTION EFF I UPA ORI

NUMBER NUMBER STOCK NO. 11234567 CODE

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3010 1 8-7288 ´•BACKUP RING 1 I Y

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3020

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Oil Transfer Unit Assembly

1069
ILLUSTRATED PARTS LIST 61-10-14 Rev.PageAug/Ol 5
 PROPELLER MAINTENANCE MANUAL
HARTZELL 114C

(This page is intentionally blank.)

I ILLUSTRATED PARTS LIST 81’1 0-1 4 Page 1070

Rev. 5
Aug/01
12
 FAA Approved
HARTZ E LL
i) Manual No. 1170
Revision7
61110-17
I Apri12001

Compact Constant Speed and

Feathering Propeller
Overhaul and Maintenance Manual

Two Blade: Three Blade:

BHC-C2YF-2( EHC-C3YF-2(
CHC-C2YF-2() I HC-C3YF-2()
DHC-C2YF-2( PHC-C3YF-2()
HC-C2YF-2() HC-C3YN-2()
HC-C2YK-2() HC-C3YR-2(
HC-C2YL-2() HC-E3YR-2(
HC-C2YR-2() HC-F3YR-2()
HC-E2YK-2() EHC-G3YF-2(
HC-E2YL-2( HC-G3YF-2(
6) HC-E2YR-2() PHC-G3YF-2(
HC-F2YL-2() HC-H3YF-2(
HC-F2YR-2( PHC-H3YF-2(
BHC-12YF-2( HC-H3YN-2(
HC-12YF-2( HC-13YF-2(
BHC-J2YF-2( I PHC-13YF-2(
BHC-L2YF-2( I HC-13YR-2(
HC-L2YF-2() PHC-J3YF-2(
HC-M2YL-2(
HC-M2YR-2(

Four Blade:

HC-C4YF-2( Allison engine applications:

HC-C3YF-5F
HC-C4YN-2()
HC-C3YN-5A
HC-C4YR-2()
HC-F4YR-2(

HartzellPropeller Inc.
One Propeller Place
i Piqua, Ohio 45356-2634 U.S.A.
Phone: 937.778.4200
Fax: 937.778.4365
(This page is intentionally blank.)

61-10-17
 RECORD OF REVISIONS

Manual 117D
MFG REV
NO DESCRIPTION ISSUEDATE ATPREVDATE INSERIEDBY

6 ISee Highlights 4/00 7/10/00 ATP/DG

7 ISee Highlights 4/01 10/01/01 ATPNP

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 117D

RECORD OF REVISIONS

This is a permanent historical record of revisions inserted into this manual.

Revision Issue Date Inserted Revision Date Inserted

Issue Date
Number Date Inserted By Number Inserted By

4 May/99

5 Aug/99 10/18/99 ATP/JX;

6 Apr/GO 07/10/20 ATP/DG

7 ~r/01 10/01/01 ATPIVP

1
RECORD OF REVISIONS 61 -1 0’1 7 Rev 9
 PROPELLER MAINTENANCE MANUAL
HA, RTZ ELL 117D

RECORD OF REVISIONS

This is a permanent historical record of revisions inserted into this manual.

Revision Issue Date Inserted Revision Date Inserted

Issue Date
Number Date Inserted By Number Inserted By

RECORD OF REVISIONS 61 ’i 0’1 7 Rev. 4 May/99Page 2

 RECORD OF TEMPORARY REVISIONS

Manual 117D
TEMP ATP REV INSERT DATE REV REMOVE
REV NO DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY

001 61-10-17:509 3/00 7/1 0/00 ATP/DG 10/01/01 7 ATPNP

002 61-10-17:767 7/00 10/01/01 ATPNP

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

RECORD OF TEMPORARY REVISIONS TO THIS MANUAL

Update this page to show all Temporary Revisions inserted into this manual.

Date Date
TRNumber IssueDate Inserted Inserted Removed Removed B

001 3/2000 7/10/2000 ATP/DG 0/01/01 ATP/VP

s
02 7/2000 0/01/01 ATPIVP

RECORD OF TEMPORARY REVISIONS 61-10-17 Rev. 4 May/99Page

 PROPELLER
HA RTZ E LL MA:N11;EDNANCE MANUAL

RECORD OF TEMPORARY REVISIONS TO THIS MANUAL

Update this page to show all Temporary Revisions inserted into this manual.

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2
RECORD OF TEMPORARY REVISIONS 61’1 0’ 1 7 Rev. 4
HARTZELL PROPELLER INC.
HARTZ ELL
One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.
Telephone: 937.778.4200
Fax: 937.778.4365

MANUAL REVISION TRANSMITTAL

Manual 117D
Compact Constant Speed and Feathering Propeller
Overhaul and Maintenance Manual

Manual 117D Revision 7. Dated Aoril 2001

Attached is a copy of Revision 7

Page Control Chart for Revision 7:

Remove Insert
Page No. Page No.

COVER COVER
pages 1 and 2 pages 1 and 2
REVISION HIGHLIGHTS REVISION HIGHLIGHTS
pages 1 and 2 pages 1 and 2
LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES
pages 1 and 2 pages 1 through 4

TABLE OF CONTENTS TABLE OF CONTENTS

pages 5 through 10 pages 5 through 10

INTRODUCTION INTRODUCTION
pages 1 through 4 pages 1 through 4

pages 7 through 10 pages 7 through 12

DESCRIPTION AND OPERATION DESCRIPTION AND OPERATION

pages 5 and 6 pages 5 and 6
TESTING AND FAULT ISOLATION TESTING AND FAULT ISOLATION
pages 103 and 104 pages 103 and 104
CHECK CHECK
pages 501 and 502 pages 501 and 502
pages 507 through 510 pages 507 through 510
pages 515 through 520 pages 515 and 516
pages 517 and 517.1
pages 517.2 and 518
pages 519 and 520
REPAIR REPAIR

pages 601 through 610 pages 601 through 618

ASSEMBLY ASSEMBLY
pages 701 through 704 pages 701 through 704

pages 709 and 710 pages 709 and 710

pages 713 through 718 pages 713 through 718
pages 725 and 726 pages 725 and 726
pages 731 and 732 pages 731 and 732
pages 733 and 734 pages 733 and 734
pages 734.1 and 734.2
pages 737 through 740 pages 737 through 740
Temporary Revision TR-002 Refer to NOTE
pages 765 through 768 pages 765 through 768

Page 1 of 2
Page Control Chart for Revision 7, Continued:

Remove Insert
Page No. Page No.

FITS AND CLEARANCES FITS AND CLEARANCES

pages 801 and 802 pages 801 and 802
pages 805 through 808 pages 805 through 808
ILLUSTRATED PARTS LIST ILLUSTRATED PARTS LIST
pages 1073 and 1074 pages 1073 and 1074
pages 1101 through 1146 pages 1101 through 1146
pagesll79throughll94 pagesll79throughll94
pages 1199 through 1210 pages 1199 through 1210
pages 1217 through 1236 pages 1217 through 1236

NOTE: Record the removal of a temporary revision on the

RECORD OF TEMPORARY REVISIONS page at the front of the manual.
 PROPELLER MAINTENANCE MANUAL
RT Z E L L 117D

REVISIOW HIGHLIGHTS

Revised Cover, Highlights, and List of Effective Pages to reflect the manual
revision.

Added information to the Introduction chapter.

Revised the Check chapter:
Revised the pitch change block, cylinder, and pitch change rod information in
Table 501, Component Inspection Criteria.
Revised the Repair chapter:
Revised the section "Repair of Damaged Cylinder Wrench Attachment Holes".

Added a section "lnstallation of a Roll Pin in the Two-piece 8-2491 Pitch

Change Rod".

Added spinner bulkhead modification for three-bladed propellers.

Revised the Assembly chapter:
Incorporated Temporary Revision TR-002.

Referred the reader to Hartzell Standard Practices Manual 202A (61-01-02) for
mounting flange stud installation instructions and removed the mounting flange
stud installation insructions from the overhaul manual.

Added a caution concerning bearing ball size and gauge.

Added information concerning the use of a protractor for blade angle

measurement.

Added a section "Application of Blade Angle Reference Tape".

Revised the section "Air Charge Pressures" in the Fits and Clearances chapter to
reflect current specifications.
Revised the Illustrated Parts List chapter to include various changes and
corrections.

sl-lo-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

REVISIONS HIGHLIGHTS

1. Introduction

A. General

This is a list of current revisions that have been issued against this manual.
Please compare to RECORD OF REVISIONS page to ensure that all revisions
have been added to the manual.

B. Components
(1) Revision No. indicates the revisions incorporated in this manual.

(2) Issue Date is the date of revision.

(3) Comments indicates the level of the revision.

1 New Issue is a new manual distribution. The manual is distributed in its

entirety. All the revision dates are the same and no change bars are
used.

2 Reissue is a revision toexisting manual that includes major content

an

and/or major format changes. The manual is distributed in its entirety.

All the revision dates are the same and no change bars are used.

3 Major Revision is a revision to

existing manual that includes major
an

content or minor format changes large portion of the manual.

over a
The manual is distributed in its entirety. All the revision dates are the
same, but change bars are used to indicate the changes incorporated
in the latest revision of the manual.

4 Minor Revision is a revision to

existing manual that includes minor
an

content changes to the manual. Only the revised pages of the manual
are distributed. Each page retains the date and the change bars

associated with the last revision to that page.

Revision No. Issue Date Comments

Revision 4 May/99 Reissue

Revision 5 Aug/99 Minor Revision
Revision 6 Apr/GO Minor Revision
I Revision 7 Apr/Ol Minor Revision

2
61-10-17 Rev.7Pb3~biPage
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 117D

LIST OF EFFECTIVE PAGES

Date Chapter Page Date

Chapter Page

Cover/Cover Back Apr/Ol I I IRepair 603 May/99

Revision Highlights 1-2 Apr/Ol I IRepair 604-605 Apr/Ol
Record of Revisions 1-2 May/99 I I (Repair 606-608 May/99
Record of Temporary I I IRepa’l 609-618 Apr/Gl
Revisions 1-2 May/99 IIIAssemblv 701 Apr/Gl
Service Document List 1-2 Apr/GO I 1Assemly 702 May/99
Airworthiness Limitations 1-2 May/99 I I IAssemblv 703-704 Apr/Gl
List of Effective Pages 1-2 Apr/Ol I I IAssembly 705-708 May/99
Table of Contents 1-4 Apr/GO I I 1Assembly 709 Apr/Gl
Table of Contents 5-10 Apr/Gl I I 1Assemblv 710-712 May/99
Introduction 1-2 Apr/Gl IIIAssemblv 713 Apr/Gl
Introduction 3 Apr/GO IJIBssembly 714-715 May/99
Introduction 4 Apr/Ol I(I~Ptssemblv 716-717 Apr/Ol
Introduction 5-6 May/99 II1Bssembly 718-724 May/99
I Introduction 7-12 Apr/Ol II(Assembly 725 Apr/Ol
Description and Operation 1-5 May/99 I IAssembly 726-730 May/99
I Description and Operation 6 Apr/Gl I I IAssembly 731 Apr/Ol
Description and Operation 7 May/99 I I 1Assembly 732-733 May/99
Description and Operation 8 Aug/99 I I IAssembly 734 Apr/Ol
Testing and Fault Isolation 101-102 May/99 I (Assembly 734.1-734.2 Apr/Gl
Testing and Fault Isolation 103 Apr/Ol I I (Assembly 735-737 May/99
Testing and Fault Isolation 104-108 May/99 I 1Assembly 738-739 Apr/Gl
Automatic Test Requirements 201 -202 May/99 I I JAssembly 740-764 May/99
Disassembly 301-320 May/99 IJIBssembly 765-768 Apr/Ol
Cleaning 401-404 May/99 l(lAssembiy 769-776 May/99
Check 501-507 May/99 Il IFitsandClearances 801-802 Apr/Gl
Check 502 Apr/Ol Il IFitsandClearances 803-804 Apr/GO
Check 503-507 May/99 Fits and Clearances 805 May/99
Check 508-509 Apr/Ol IFits and Clearances 806-808 Apr/Gl
Check 510-515 May/99 I ISpecial Tools, Fixtures
Check 516 Apr/Gl I land Equipment 901-904 May/99
Check 517 Apr/GO I Illlustrated Parts List 1001 Apr/GO
Check 517.1-517.2 Apr/Gl I Illlustrated Parts List 1002 May/99
Check 518 Apr/GO Illustrated Parts List 1003-1004 Apr/GO
Check 519 May/99 Illustrated Parts List 1005-1006 May/99
Check 520 Apr/Ol I Illlustrated Parts List 1007-1010 Apr/GO
Check 521-529 May/99 Illustrated Parts List 1011-1024 May/99
Check 530 Apr/GO Illustrated Parts List 1025 Apr/GO
Check 531-532 Apr/GO Illustrated Parts List 1026 May/99
Repair 601-602 Apr/Ol Illustrated Parts List 1027 Apr/GO

LIST OF EFFECTIVE PAGES 61-10-17 Rev.7PAap9rl~:Page

 PROPELLER
HARTZ E LL MA:N1~EDNANCE MANUAL

LIST OF EFFECTIVE PAGES

Chapter Page Date Chapter Page Date

Illustrated Parts List 1028 May/99 I I Illlustrated Parts List 1118-1119 May/99
Illustrated Parts List 1029 Apr/GO I I Illlustrated Parts List 1120 Apr/Gl
Illustrated Parts List 1030 May/99 I I Illlustrated Parts List 1121 May/99
Illustrated Parts List 1031 Apr/GO I Illlustrated Parts List 1122 Apr/Ol
Illustrated Parts List 1032 May/99 I I Illlustrated Parts List 1123 May/99
Illustrated Parts List 1033 Apr/GO I I Illlustrated Parts List 1124 Apr/Ol
Illustrated Parts List 1034 May/99 I Illlustrated Parts List 1125 May/99
Illustrated Parts List 1035 Apr/GO I I Illlustrated Parts List 1126 Apr/Ol
Illustrated Parts List 1036 May/99 I I Illlustrated Parts List 1127 May/99
Illustrated Parts List 1037 Apr/GO I I Illlustrated Parts List 1128 Apr/Ol
Illustrated Parts List 1038 May/99 I Illlustrated Parts List 1129 May/99
Illustrated Parts List 1039 Apr/GO I Illlustrated Parts List 1130-1131 Apr/Ol
Illustrated Parts List 1040 May/99 I I Illlustrated Parts List 1132-1133 May/99
Illustrated Parts List 1041 Apr/GO I I Illlustrated Parts List 1134 Apr/Ol
Illustrated Parts List 1042 May/99 I I Illlustrated Parts List 1135 May/99
Illustrated Parts List 1043 Apr/GO I I Illlustrated Parts List 1136 Apr/Ol
Illustrated Parts List 1044 May/99 I I Illlustrated Parts List 1137 May/99
illustrated Parts List 1045 Apr/GO I I Illlustrated Parts List 1138 Apr/Ol
Illustrated Parts List 1046 May/99 I I Illlustrated Parts List 1139 May/99
Illustrated Parts List 1047 Apr/GO I (Illustrated Parts List 1140 Apr/Ol
Illustrated Parts List 1048 May/99 I I Illlustrated Parts List 1141-1142 May/99
Illustrated Parts List 1049 Apr/GO I I Illlustrated Parts List 1143 Apr/GO
Illustrated Parts List 1050-1070 May/99 I I (Illustrated Parts List 1144 Apr/Ol
Illustrated Parts List 1071 Apr/GO I I Illlustrated Parts List 1145 Apr/GO
Illustrated Parts List 1072 May/99 I Illlustrated Parts List 1146 Apr/Ol
Illustrated Parts List 1073 Apr/Ol I Illlustrated Parts List 1147 Apr/GO
Illustrated Parts List 1074-1101 May/99 I Illlustrated Parts List 1148 May/99
Illustrated Parts List 1102 Apr/Ol Illustrated Parts List 1149 Apr/GO
Illustrated Parts List 1103 May/99 Illustrated Parts List 1150 May/99
illustrated Parts List 1104 Apr/Ol Illustrated Parts List 1151 Apr/GO
Illustrated Parts List 1105 May/99 Illustrated Parts List 1152-1158 May/99
Illustrated Parts List 1106 Apr/Ol Illustrated Parts List 1159 Apr/GO
Illustrated Parts List 1107 May/99 Illustrated Parts List 1160 May/99
Illustrated Parts List 1108 Apr/Ol Illustrated Parts List 1161 Apr/GO
Illustrated Parts List 1109 May/99 Illustrated Parts List 1162 May/99
Illustrated Parts List 1110-1112 Apr/Ol Illustrated Parts List 1163 Apr/GO
Illustrated Parts List 1113 Apr/GO Illustrated Parts List 1164 May/99
Illustrated Parts List 1114 Apr/Ol Illustrated Parts List 1165 Apr/GO
Illustrated Parts List 1115 Apr/GO I Illlustrated Parts List 1166 May/99
I Illustrated PartsList 1116-1117 Apr/Ol Illustrated Parts List 1167 Apr/GO

2
LIST OF EFFECTIVE PAGES 61’1 0’1 7 Rev.
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

LLST OF EFFECTLVE PAGES

Chapter Page Date Chapter Page Date

Illustrated Parts List 1168 May/99

Illustrated Parts List 1169 Apr/GO
Illustrated Parts List 1170 May/99
Illustrated Parts List 1171 Apr/GO
Illustrated Parts List 1172 May/99
Illustrated Parts List 1173 Apr/GO
Illustrated Parts List 1174 May/99
Illustrated Parts List 1175 Apr/GO
Illustrated Parts List 1176 May/99
Illustrated Parts List 1177 Apr/GO
Illustrated Parts List 1178 May/99
Illustrated Parts List 1179 Apr/GO
I Illustrated Parts List 1180-1189 Apr/Ol
Illustrated Parts List 1190 May/99
Illustrated Parts List 1191 Apr/GO
I Illustrated Parts List 1192-1193 Apr/Ol
Illustrated Parts List 1194 May/99
Illustrated Parts List 1195 Apr/GO
Illustrated Parts List 1196 May/99
Illustrated Parts List 1197 Apr/GO
Illustrated Parts List 1198 May/99
Illustrated Parts List 1199 Apr/GO
Illustrated Parts List 1200-1209 Apr/Ol
Illustrated Parts List 1210-1217 Apr/GO
Illustrated Parts List 1218-1227 Apr/Ol
Illustrated Parts List 1228 Apr/GO
Illustrated Parts List 1229 Apr/Ol
Illustrated Parts List 1230-1233 Apr/GO
illustrated Parts List 1234-1235 Apr/Gl
Illustrated Parts List 1236-1250 Apr/GO

3
LIST OF EFFECTIVE PAGES 61-10-17 Rev. 7 Apr/OlPage
 PROPELLER
nA RTZ E L L MA:N:7EDNANCE MANUAL

(This page is intentionally blank.)

LIST OF EFFECTIVE PAGES 61’1 0’1 7 Rev. 7PAap~4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

SERVICE DOCUMENT LIS

Service Dec. Incorporation Service Dec. Incorporation

No. Rev./Date No. Rev./Date

SA 40 Rev. 4 Ma

SE 142B Rev. 4 Ma

se HC-SB-~1-224 Rev. 4 M

SE HC-SB-61-226 Rev. 4 Ma

SI 102J Rev. 4 Ma

SI 108 Rev. 4M /99

SI 149 Rev. 4 /99

SI 152A Rev. 4M /99

SI 202A Rev. 4 Ma

SL 100 Rev. 4 Ma

SL 82A Rev. 4 /99

SL 155A Rev. 4 Ma

SL HC-SL-61-170 Rev. 4 Ma

SL HC-SL-61-177 Rev. 4 M

SL HC-SL-61-179 Rev. 4 Ma

L L 7 R

SERVICE DOCUMENT LIST

61’1 0’17 Rev
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 117D

SERVICE DOCUMENT LIST

Sewice Dec. Incorporation Sewice Dec. Incorporation

No. Rev./Date No. Rev./Date

i SERVICE DOCUMENT LIST 61’10’17 Rev.

2
 PROPELLER MAINTENANCE MANUAL
H~A RTr E L L 117D

CONTENTS

REVISION HIGHLIGHTS 1

1. Introduction 1

A. General 1

B. Components 1

RECORD OF REVISIONS 1

RECORD OF TEMPORARY REVISIONS 1

SERVICE DOCUMENT LIST 1

AIRWORTHIN ESS LIMITATIONS

LIST OF EFFECTIVE PAGES 1

TABLE OF CONTENTS 1

INTRODUCTION 1

1. State ment of Pu rpose

A. General 3

2. Required Publications 4

A. Hartzell Pu blications

B. References to Hartzell Publications 4

C. Vendor Publications 5

3. Personnel Requirements 5

4. Calendar Limits and Long Term Storage 5

A. Calendar Limits 5

B. Lo ng Te rm Sto rag e

5. Component Life and Service 6

A. Overhaul. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

B. Repair. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
C. Component Life 7

6. Definitions

7. Abbreviations 10

1
TABLE OF CONTENTS 61 -1 0-1 7 Rev. 4 May/99Page
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 117D

DESCRIPTION AND OPERATION 1

1. Description 3

A. General 3

B. Components 3

2. Operation 3

A. Compact Constant Speed and Feathering Propellers (-2) 3

B. Feathering, Turbine Propellers (-5) 4

3. Model Designation System 5

A. Propeller Model Description 5

B. Blade Shank Designation 5

TESTING AND FAULT ISOLATION 101

1. Trouble-Shooting Guide 103

A. Pitch Control Difficulty 103

B. Friction 103

C. Abnormal Propeller Vibration 103

D. Blades Not Tracking 105

E. End-Play Movement of the Blade................................................................ 105

F. In-and-Out Movement of the Blade. 105

G. Fore-and-Aft Movement of the Blade 105

H. Radial Play in the Blade. 105

I. Oil Leakage 106

J. External Grease Leakage 106

2. Lightning Strike on Hub or Blade 107

AUTOMATIC TEST REQUIREMENTS 201

DISASSEMBLY

1. Removing the Propeller Assembly from the Aircraft ........._.......,

303
2. Marking Before Disassembly 303

3. Removal of the Propeller Anti-ice or De-ice System (if applicable) .........,._.,,

303

A. De-ice System Removal 303

B. Anti-ice System Removal 303

TIBLEOFCONTENTS 61-10-17
 PROPELLER MAINTENANCE MANUAL
H ~A,RTZ ELL liib

4. Propeller Disassembly 304

A. Disassembly of the Propeller External Pitch Change Parts 304

B. Cylinder Disassembly 306

C. Cylinder Spring Disassembly 309

D. Cylinder High Pitch Stop Unit Disassembly

(Cylinders Without a Spring Assembly) 313

E. Hub Disassembly ("E" Hubs) 315

F. Disassembly of the Propeller Internal Pitch Change Parts 318

G. Hub Disassembly 319

H. Pitch Change Fork Disassembly 319

I. Pitch Change Block Disassembly 320

J. Blade Retention Parts Disassembly 320

K. Damper Disassembly 320

CLEANING 401

1. General Procedures for Cleaning Parts 403

2. Specific Cleaning Procedures 403

CH ECK .........._.._...

1. Inspection Interval Requirements 503

2. Inspection Requirements 503

3. Replacement Requirements 503

4. Repair 503

5. Hub Unit Inspection 504

6. Specific Inspection Procedures 504

7. Specific Checks 504

A. Spinner Nut 505

B. Spinner Spacer 505

C. Low Stop 507

D. Cylinder 508

E. Bracket, Auto High Stop

F. Pin, High Stop 510

61-10-17 Rev 4
 PROPELLER
HARTZELL MA:N1~E6JPINCE M~NUAL

G. Spring Guide 510

H. Plate, Retainer 510

i. Weight 511

J. Spring, Feathering (Cylinder) 512

K. Bracket, High Pitch Stop 512

L. High Pitch Stop Sleeve 512

M. Washer. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 513

N. Piston 515

O. Pitch Change Rod 517

P Fork 519

Q. Pitch Change Block 521

R. Hub Unit 521

S. Spacer ........._____ .........__,,,

T. Spring Guide 522

U. Spring, Feathering (Hub) 522

V. Spring, Feathering (Hub) 522

W. Spring Retainer 523

X. Hub Bolt Inspection 523

Y. Plug, Shaft .................................................................i................................

525

Z. Hex Head Spacer Tube 526

AA. Damper Weight 526

AB. Support Plate 527

AC. Blade Bearing Race 529

AD. Ring, Bearing Race Retention ........._,__

AE. Preload Plate 531

AF. Balance Weights 532

REPAIR

1. General Repair Requirements 603

A. Shot Peening 603

B. Aluminum and Steel Parts ........._____

2. Blade Repair 603

TPIBLEOFCONTENTS 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

3. Hub Unit Repair 603

4. Spinner Assembly Repair 603

5. Specific Repair Requirements 604

A. Repair of Damaged Cylinder Wrench Attachment Holes. 604

B. Spinner Bulkhead Modification for Two-bladed Compact Propellers 605

C. Spinner Bulkhead Modification for Three-bladed Compact Propellers 611

D. Installation of a Roll Pin in the Two-piece B-2491 Pitch Change Rod.........617

ASSEMBLY PROCEDURES 701

1. General 705

2. Compact Hub Assembly Procedures 707

A. Hub Preparation 707

3. Blade Assembly Procedures 709

A. Installation of the Blade Bearing Race and Balls 709

B. Preload Plate Assembly 711

4. Propeller Assembly Procedures 713

A. Blade Installation Two Blade Propeller 713

B. Blade Installation Three Blade Propeller 719

C. Blade Installation Four Blade Propeller 727

D. Application of Blade Reference Tape 734.1

E. Pitch Change Unit Assembly and Blade Tolerance Checks 735

F. 830-21 or 830-30 Stop Unit Assembly and Installation 741

G. Cylinder Spring Assembly Installation 743

H. Piston and Cylinder Installation 753

i. Hub Spring Installation 757

J. Setting the Blade Angles 765

5. Blade Track 772

6. Propeller Lubrication
7. Static Balance 772

8. Damper
A. Damper Assembly 775

TABLEOFCONTENTS 61-10-17
 PROPELLER
HARTZELL YI:N1~NPINCE MPINU~L

FITS AND CLEARANCES 801

1, Torque Values 803
2, Blade Tolerances 805
3, Air Charge Pressures 806
SPECIAL TOOLS, FIXTURES, AND EQUIPMENT 901
1, Minimum Facility and Tooling Requirements 903
A, Tooling
B, Facilities 903
2, Special Tools 903
A, Special Tools 903
B, Listings 903
ILLUSTRATED PARTS LIST

1, Introduction 1005
A. General 1005
B, Using the Illustrated Parts List 1005
C, Propeller Assemblies Configured with a De-ice System 1005
2, The Illustrated Parts List

A, Detailed Parts List 1006

B, Revisions

3, F and N Flange 1008

4, Pitch Change Knob

CYLINDER SPRING ASSEMBLIES 1021

PROPELLER ASSEMBLIES 1026
SPINNER ASSEMBLY PARTS 1241
SPINNER MOUNTING KIT PARTS 1248

I T~IBLE OF COnTTENTS 61 -1 0-1 7 Rev. 7

Page
Apr/Ol
6
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

LIST OF FIGURES

Propeller Model Designation System Figure 1 6

Checking Blade Movement Figure 101 104
Loosening the Spring Assembly Tool Figure 301 306
Placing the Assembling Tool TE9 in a Vise Figure 302 309
Positioning the Cylinder on the Assembly Tool Figure 303 310
Removing the First Two Screws Figure 304 311
Installing the Spring Compressor Assembly TE31 Figure 305 314
Compressing the Feathering Springs
with the Spring Compressor Assembly TE31 Figure 306 316
Removing the Blades Using Blade Retention
Components Clamp TE24 Figure 307 318
Low Stop Dimensions Figure 501 506
Cylinder Dimensional Inspection Criteria Figure 502 508
Weight Identification Figure 503 511
Washer Identification Figure 504 513
Piston Dimensional Inspection Criteria Figure 505 514
One-Piece Pitch Change Rod Figure 506 516
I Two-Piece Pitch Change Rod Figure 506.1 517.1
Pitch Change Block Identification/Dimensional Criteria Figure 507 520
Shaft Plug Figure 508
Blade Split Bearing Figure 509 528
Preload Plate Figure 510
Installing the Reinforcing Brackets Figure 601 607
Two-bladed Propeller Bulkhead Cutout Dimensions Figure 602 608
Two-bladed Propeller Bulkhead Template Figure 603 609
Three-bladed Propeller Bulkhead Cutout Dimensions ...........Figure 604 614
Three-bladed Propeller Bulkhead Template Figure 605 615
Installing a Roll Pin in the Two-Piece Pitch Change Rod Figure 606 617
Installing the Flange O-Ring in the Engine-Side
Hub Half Flange Figure 701 706
Installing the Engine-Side Hub Half on the
Rotatable Fixture Figure 702 706
Installing the Blade Retention Bearing Figure 703 708
Pressing the Inner Blade Bore Bearing Race on the
Preload Plate Spindle Figure 704 710
Installing the Preload Plate on the Blade Shank Figure 705 710
Applying the Clamping Tool TE24 to the Blade Assembly Figure 706 711
Installing Blade Number One in the Two-Way Hub................ Figure 707 714
Installing the Two-Way Cylinder-Side Hub Half........ Figure 708 715
Setting the Two-Way Preload Figure 709 716
Installing Blade Number One and the Pitch Change Parts Figure 710 717

T~BLEOFCONTENTS 61-10-17 Rsu./P~b:

 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 117D

LIST OF FIGURES CONT’D

Applying Sealant on the Two-Way Hub Parting Surface........ Figure 711 718
Installing Blade One in the Three-Way Hub Figure 712 719
Installing the Three-Way Hub Half Before
Tightening Preload Plate Figure 713 721
Tightening Preload Plate Hex Head Screw and Jam Nut....... Figure 714 722
Installing the Pitch Change Blocks on
Blades Two and Three Figure 715 724
Installing the Pitch Change Fork on

Blades Two and Three Figure 716 724

Applying Sealant Between the Three-Way Hub Halves......... Figure 717 726
Installing the Four-Way Cylinder-Side Hub Half... Figure 718 729
Installing the Pitch Change Fork Figure 719 731
Installing Blade Number One in the Four-Way Hub Figure 720 732
Applying Sealant Between the Four-Way Hub Halves........... Figure 721 733
Using the Torque Wrench Adaptor TE6 on the
Pitch Change Rod Figure 722 735
Using Spacer
a to Check Blade Angles Figure 723 736
Checking Blade Angles With the Bench Top
Protractor TE96 Figure 724 737
Using the Assembling Tool TE9 Figure 725 742
Attaching the High Stop Bracket to the Cylinder Figure 726 743
Positioning the Cylinder on the Assembling Tool TE9............ Figure 727 744
Installing the Assembly Guides TE319................................... Figure 728 744
Placing the Feathering Spring and Spring Retainer
in the Cylinder Figure 729 745
Installing the Washer on the Assembly Guides TE319 Figure 730 746
Positioning the Weight in the Cylinder.................................... Figure 731 746
Placing the Drilled Washer in the Cylinder Figure 732 747
Compressing the Feathering Spring Using Assembling
Tool TE9 Figure 733
Installing the Cylinder Cap Figure 734 749
Positioning the Drilled Washer for Installation
of the First Two Screws Figure 735 750
Positioning the Drilled Washer for Installation
of the Final Two Screws Figure 736 750
Installing the Final Two Screws Figure 737 751
Applying a Bead of Sealant Where the Cylinder and
Hub Meet Figure 738 753
Installing the Cylinder with Cylinder Torque Wrench
Adapter TE153 Figure 739
Installing the Spacer Figure 740
Installing the Spring Guide Figure 741 756

I 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

LIST OF FIGURES CONT’D

Figure 741.1 734.1

I Application of Blade Reference Tape
Installing the Small Diameter Feathering Spring
on the Pitch Change Rod Figure 742 758

Installing the Large Diameter Feathering Spring

on the Pitch Change Rod Figure 743 758

Installing the Spring Retainer on the Pitch Change Rod Figure 744 759

Installing the Spring Compressor Assembly TE31 Figure 745 760

Compressing the Feathering Springs with the

Spring Compressor Assembly TE31 Figure 746 760

Installing the Keeper on the Pitch Change Rod Figure 747 762
Parts for Adjusting the Pitch Angle Figure 748 764

Checking the Feather Angle With a Hand Held Protractor..... Figure 749 765
Hub Leak Check Figure 750
Checking Blade Track Figure 751 772

Damper Assembly Figure 752 774

Damper Installation Figure 753 776

Determining Torque Value of a Standard Torque Wrench

with Adaptor Figure 801 803
Two Way -2 With High Pitch Stop Assembly Figure 1001 1010
Two Way -2 With High Pitch Stop Assembly
and A-2273 Hub Spring Assembly Figure 1002 1011
Two Way -2 With High Pitch Stop Assembly
and A-1586 Hub Spring Assembly Figure 1003 1012
Two Way -2 With Cylinder Spring Assembly Figure 1004 1013
Three Way -2 With High Pitch Stop Assembly Figure 1005 1014
Three Way -2 With High Pitch Stop Assembly
and Hub Spring Assembly Figure 1006 1015
Three Way -2 With Cylinder Spring Assembly Figure 1007 1016
Four Way -2 With Cylinder Spring Assembly Figure 1008 1017
Three Way -5 With Cylinder Spring Assembly Figure 1009 1018
Blade Retention System Exploded View Figure 1010 1019

B-1589-( and B-1106 Cylinder Spring Assemblies Figure 1011 1020

8-3684 Cylinder Spring assembly Figure 1012 1022

Spinner Nuts Figure 1013 1024

F and N Flange Mounting Parts Figure 1014 1025

I 61-10-17
 PRO’ELLER
HARTZELL MPI:N1~EDNINCE MPINVP~L

LIST OF TABLES

Component Inspection Criteria Table 501 .505

Torque Values......................................................................... Table 801 804
Blade Tolerances Table 802 805
Air Charge Pressure (Decal CHP-221) Table 803 806
Air Charge Pressure (Decal CHP-226) Table 804 806
Air Charge Pressure (Decal CHP-227) Table 805 806
Air Charge Pressure (Decal CRP-323VV) Table 806 807
Air Charge Pressure (Decal CPR-41, CPR-33, CAU-002) Table 807 807
Air Charge Pressure (Decal CPR-22, CPR-22A, CAU-OO5)., Table 808 807
Air Charge Pressure (Decal CPR-700, CAU-003) Table 809 807
Air Charge Pressure (Decal CPR-27, CAU-006) Table 810 807
Air Charge Pressure (Decal CRP-104, CAU-OO4) Table 811 807
I Air Charge Pressure (Decal CPR-62) Table 812 807

sl-lo-17
 PROPELLER MAINTENANCE MANUAL
CIARTZELL 117D

AIRWORTHINESS LIMITATIONS

The Airworthiness Limitations section is FAA approved and specifies maintenance required
under 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program
has been FAA approved.

FAA APPROVED

by: date: L/1~4

c~ Royace Prather
Manager, Chicago Aircraft Certification Office,
ACE-I 15C
Federal Aviation Administration

Log of Revisions to Airworthiness Limitations

Rev. No. Description of Revision II Rev.No. I Description of Revision

3 (Mav/97)1Added limits for FC6660 (K

blade

4 (May/99)1Added limits for F(J)C6660(B,K)

blade

AIRWORTHINESS LIMITATIONS 61 -1 0-1 7 Rer 4

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

AIRWORTHINESS LIMITATIONS

A. The FAA establishes specific life limits for certain component parts as well as the
entirepropeller. Such limits require replacement of the identified parts after a
specified number of hours of use.
B. The following data summarizes all current information concerning Hartzell life
limited parts as related to propeller models affected by this manual. The following
list specifies life limits for blades only. Associated hub parts are not affected. Blade
models shown are life limited only on the specified applications. They are not life
limited on other installations; however, time accumulated toward life limit accrues
when first operated on aircraft/engine/propeller combinations listed and continues
regardless of subsequent installations (that may or may not be life limited).
C. Life Limits

The HC-C4YR-2 propeller currently does not have any life limited parts, except for
the FC6660(K) and F(J)C6660(B,K) blades, that are life limited on the following
applications:
Propeller Model Engine Aircraft Blade Life Limit

HC-C4YR-2/FC6660(K) Lycoming Twin Commander Aircraft 10,500 hours

Models TIO-540-J2B Models 500(B,S,U) as modified
and -J2BD by Merlyn Products, Inc.

HC-C4VR-2(L)/F(J)C6660(B,K) Lycoming Aerostar aircraft 10,500 hours

(T)10-540 Series Models PA60-601(P),602P
Models as modified by Machen

FAA APPROVED

by: date
c´•Lk Royace Prather
Manager, Chicago Aircraft Certification Office,
ACE-115C
Federal Aviation Administration

2
PIIRWORTHINESS LIMITIITIONS 61 -1 0’1 7 Rev 4
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

CONTENTS

1. Statement of Purpose
A. General 3

2. Required Publications 4

A. Hartzell Publications

B. References to Hartzell Publications 4

C. Vendor Publications 5

3. Personnel Requirements 5

4. Calendar Limits and Long Term Storage 5

A. Calendar Limits 5

B. Long Term Storage 6

5. Component Life and Service 6

A. Overhaul. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

B. Repair. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
C. Component Life 7

6. Definitions

7. Abbreviations 11

el-lo-17 ReV.7PAaSI~:
 PROPELLER MANUAL
HA RTZ E L L MA:N:7EDNANCE

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I 61-10-17 R,,p,a~:
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

INTRODUCTION

1. Statement of Purpose

A. General

(1) This manual provides maintenance and overhaul procedures for compact
constant speed and feathering propellers manufactured by Hartzell
Propeller Inc.

(2) Contact the Product Support Department of Hartzell Propeller Inc.

concerning any maintenance problems or to request information not
covered in this publication.
Hartzell Product Support may be reached during business hours (8:00 a.m.

through 5:00 p.m., United States Eastern Time) at (937) 778-4379.

After business hours, you may leave a message on our 24 hour product
support line at (937) 778-4376. A technical representative will contact you
during normal business hours. Urgent AOG support is also available 24
hours per day, seven days per week via this message service.

Additional information is available on our website at www. hartzelloroo.com.

NOTE: When calling from outside the United States, dial (001) before dialing
the above telephone numbers.

(3) This manual is written with the intent that it is to be used by propeller repair
stations with personnel who are trained and experienced with Hartzell
products. This manual does not provide complete information for an
inexperienced technician to attempt propeller overhaul without supervision.
(4) This manual is intended to be theprimary source of overhaul information for
compact constant speed and feathering propellers. This manual does not
contain blade overhaul procedures. Refer to the appropriate Hartzell manual
for blade overhaul. manual, the reader must consult
In addition to this
active Service Bulletins, Service Letters, Service Advisories, and Service
Instructions for information concerning these procedures that may have not

yet been incorporated into the latest revision of this manual.

(5) This manual makes reference to other Hartzell manuals, particularly the
Hartzell Standard Practices Manual No. 202A (61-01-02), that provides
important details for procedures such as anodizing, penetrant inspection,
and overhaul procedures for hubs.

(6) Where possible, this manual is written in the format specified by ATA

Specification No. 100.

61-10-17 REV
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

2. Reouired Publications

A. Hartzell Publications

(1) In addition to this manual, one or more of the following publications are
required for information regarding specific recommendations and
procedures to maintain propeller assemblies.

Hartzell
Manual No. ATA No. Title
115 61-00-15 Owner’s Manual
126 61-00-26 Set of active SE, SA, SL, SI
127 61-16-27 Spinner Assembly Maintenance Guide
133C 61-13-33 Aluminum Blade Overhaul Manual
165A 61-00-65 Illustrated Tool and Equipment Manual
202A 61-01-02 Standard Practices Manual
1 159 61-02-159 Hartzell Propeller Inc. Application Guide

(2) For Hartzell service literature and revisions, contact:

Hartzell Propeller Inc. Telephone: 937.778.4200

Attn: Service Documents Secretary Fax: 937.778.4365
One Propeller Place
Piqua,Ohio 45356-2634 U.S.A

Selected information is also available on Hartzell Propeller’s website at

www.hartzellProl3.com.

B. References to Hartzell Publications

(1) Item references throughout the text in this manual refer to item numbers in
the Illustrated Parts ListChapter. The item numbers appear in parentheses
directly following the part name. Only the item base number will appear in
the text of the manual. Item base numbers and the alpha variants of the
base numbers will appear in the illustrated parts list. There are two reasons
for the use of alpha variants:

(a) A part may be superseded, replaced, or obsoleted by another

part. For
example, the pitch change block (A-2217-1) that is item 400 was
superseded by the pitch change block (A-2217-2) that is item 400A.
(b) An Illustrated Parts List may contain multiple configurations.
Effectivity
codes are used to distinguish different part numbers within the same
list. Forexample, one configuration may use a pitch change knob
bushing (A-2413) that is item 3000, yet another configuration uses a
pitch change knob bushing (A-2413-2) that is item 3000A. Effectivity
codes are very important in the determination of parts in a
given
configuration.

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

(2) Special tooling may be required for procedures throughout this manual. For
further tooling information, refer to Hartzell Manual No. 165A (61-00-65)
Illustrated Tool and Equipment Manual. The reference numbers for tooling
which they
appear with the prefix "TE" directly following the tool name to
apply. For example, a template that is reference number 133 will appear as:
template TE133.
(3) Certain instructions throughout this manual refer to consumable materials.
Specific approved materials are listed in Hartzell Manual No. 202A (61-01-
02) Standard Practices Manual, Table 801. The reference numbers for
consumable materials appear with the prefix "CM" directly following the
material to whichthey apply. For example, an approved adhesive that is
reference number 16 will appear as: approved adhesive CM16. Only those
items specified may be used.

C. Vendor Publications

None.

3. Personnel Reauirements

Personnel inspecting, repairing, and overhauling aluminum hub propellers must

have adequate training and experience. Inspection and repair of propeller parts
require a high degree of skill. Therefore, personnel with inspection and
supervisory responsibility are expected to have an FAA Propeller Repairman’s
Certificate and a minimum of 18 months practical experience with Hartzell
aluminum hub propeller overhaul. Participation in Hartzell training classes and
propeller seminars is strongly recommended.

4. Calendar Limits and Long Term Storage

A. Calendar Limits

The effects of exposure to the environment over a period of time create a

need for propeller overhaul regardless of flight time. Therefore, a calendar
limit between overhauls is specified in Service Letter 61( and in the

propeller owner’s manual. Experience has shown that special care, such as
keeping an aircraft hangared, is not sufficient to allow extension of the
calendar limit.

NOTE 1: Start date for calendar limit is when the propeller is first installed
on an engine. Calendar limit is not interrupted by subsequent

removal and/or storage.

NOTE 2: Start date for calendar limit should not be confused with warranty
start date (which, with certain exceptions, is normally the date of
sale to the first retail customer).

INTROOUCTION 61 -1 0’17 Rev 4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

B. Long Term Storage

Propellers that have been in storage have an additional inspection requirement
before installation. Refer to the Packaging and Storage chapter of Hartzell
Standard Practices Manual 202A (61-01-02).

5. Component Life and Service

A. Overhaul

(1) Overhaul is the periodic disassembly, cleaning, inspecting, repairing as

necessary, reassembling, and testing in accordance with approved

standards and technical data approved by the administrator.

(2) The overhaul interval is based on hours of service (operating time) or on

calendar time. At such specified periods, the propeller hub
assembly and
the blade assemblies should be completely disassembled and
inspected
for cracks, wear, corrosion, and other unusual or abnormal conditions.
As specified, certain parts should be repaired, and certain other
parts
should be replaced.
(3) Overhaul is to be completed in accordance with the latest revision of the
applicable component maintenance manual and other publications
applicable to, or referenced in, the component maintenance manual.

(4) For overhaul interval information, refer to Service Letter 61( or Owner’s
Manual 115N.

B. Repair
(1) Repair
of small nicks and scratches can generally be performed by
mechanics in accordance with FAA Advisory Circular 43.13-1A without
consulting this manual.

(2) Whenever significant amounts of metal

are removed that may bring into

question if the blade is below minimum width or thickness, the propeller

must be inspected by an approved propeller repair station to determine if it
is below published minimums.

(3) For repair criteria, refer to Hartzell Aluminum Blade Overhaul Manual 133C
(61-13-33),

61-10-17
 PROPELLER MAINTENANCE MANUAL
HP~ RT Z E L L 117D

C. Component Life

NOTE: Certain components, or in some cases an entire propeller, may be

life limited. It is a regulatory requirement that a record of the time
since new be maintained for all life limited parts.
(1) Component life is expressed in terms of hours of service (Time Since New,
TSN) and in terms of hours of service since overhaul (Time Since Overhaul,
TSO).

NOTE: TSNTTSO is considered as the time accumulated between rotation

and landing (i.e. flight time).
(2) Both references arenecessary in defining the life of the component. Some
parts are "life limited," which means that they must be replaced after a
specified period of use (TSN).
(3) When a component assembly undergoes an overhaul, the TSO is
or

returned to zero hours. Time Since New (TSN) can never be returned to
zero.

NOTE: Repair without overhaul does not affect TSO or TSN.

(4) Time Since New (TSN) records must be maintained in the propeller
logbook, along with Time Since Overhaul (TSO).
(5) Blades and hubs are sometimes replaced while in service or at overhaul.
Maintaining separate TSN and TSO histories for a replacement hub or
blade is required. Other propeller components do not require time tracking
unless specifically noted in Hartzell service publications.

(a) Hub replacement

1 replaced, the replacement hub serial number must
If the hub is be
recorded (the entry signed and dated) in the propeller logbook.
The propeller will assume the serial number of the replacement
hub.

NOTE: Propeller assembly serial numbers are impression

stamped on the hub. Refer to the Parts Identification and
Marking chapter of Hartzell Standard Practices Manual
202A (61-01-02) for stamping information.

2 The TSO and TSN of the replacement hub must be recorded and
maintained in the propeller logbook. The TSN and TSO of the
remaining propeller components are not affected by the hub
replacement and must be maintained separately.

sl-1 0-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

6. Definitions

Term Definition

Annealed softening of material caused by overexposure to heat

Blade Station refers to a location on an individual blade for blade inspection

purposes. It is a measurement from the blade "zero" station to a
location on a blade, used to apply blade specification data in
blade overhaul manuals (Note: do not confuse blade station with
reference blade radius; they may not originate at the same
location.)

Brinelling a depression caused by failure of the material in compression

Corrosion gradual wearing away or deterioration caused by chemical

action

Crack irregularly shaped separation within a material, usually visible

as a narrow opening at the surface

Depression surface area where the material has been compressed but
not removed

Distortion alteration of the original shape or size of a component

Erosion gradual wearing away or deterioration caused by action of the

elements

Exposure leaving material open to action of the elements

Fretting damage that develops when relative motion of small

displacement takes place between contacting parts,
wearing away the surface

Gauge (Bearing Ballj .a term to describe an amounl by which me mean d ameter may
differ from the nominal diameter.

Gouge surface area where material has been removed

Impact Damage.......... damage that occurs when the propeller blade or hub
assembly strikes, or is struck by, an object while in flight or
on the ground

Nick removal of paint and possibly a small amount of material.

sl-lo-17 Rev
 PROPELLER MAINTENANCE MANUAL
HPI.RTr ELL 117D

Term Definition

Onspeed condition in which the RPM selected by the pilot through

the propeller condition lever and the actual engine
(propeller) RPM are equal

Overhaul ...........................the periodic disassembly, inspection, repair, refinish, and

reassembly of a propeller assembly

Overspeed condition in which the RPM of the engine

propeller or

exceeds predetermined maximum limits; the condition in

which the engine (propeller) RPM is higher than the RPM
selected by the pilot through the condition lever

Overspeed Damage .........damage that occurs when the propeller hub assembly
rotates at a speed greater than the maximum limit for
which it is designed

Fitting ...............................formation
of a number of small, irregularly shaped cavities
in surface material caused by corrosion or wear

Reference Blade Radius...a distance from the propeller hub centerline to a location
on a blade, used for blade angle measurement in an

assembled propeller. A yellow adhesive stripe (blade angle

reference tape CM160) is usually located at the reference
blade radius location. (Note: do not confuse reference blade
radius with blade station; they may not originate at the same
location.)

Rolling compressive rolling process for the retention area of

single shoulder blades, that provides improved strength
and resistance to fatigue

Scratch .............................same
as "Nick"

Shot Peening process where steel shot is impinged on a surface to

create compressive surface stress, that provides improved
strength and resistance to fatigue

Synchronizing setting all propellers at exactly the same RPM

Synchrophasing .........,..,a propeller sychronization in

form of which not only the
RPM of the engines (propellers) are held constant, but
also the position of the propellers in relation to each other

IWTRODUCTION 61’10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

Term Definition

Track In an assembled propeller, a measurement of the location of

the blade tip with respect to the plane of rotation, used to
verify face alignment and to compare blade tip location with
respect to the locations of the other blades in the assembly

Underspeed the condition in which the actual engine (propeller) RPM is

lower than the RPM selected by the
pilot through the
condition lever

Windmilling the rotation of an aircraft

propeller caused by air flowing over
it while it is not operating

INTRODUCTION 61-10-17
 PROPELLER MAINTENANCE MANUAL
H19 RT Z E L L 1170

7. Abbreviations

Abbreviation Term

AN............ Army-Navy
AOG AircraftOn Ground
ATA Air Transport Association
FAA............ Federal Aviation Administration
Ft-Lb Foot-Pound
ID Inside Diameter
In-Lb........... Inch-Pound
IPL Illustrated Parts List
Lbs............ Pounds
MIL-X-XXX Military Specification
I MS Military Standard
OD Outside Diameter
NAS National Aircraft Standards
N´•m Newton-Meter
PSI Pounds perSquare Inch
RPM Revolutions perl\ninute
TBO T~me Between Overhaul
TSN ............Time Since New
TSO Time Since Overhaul

INTRODUCTION 81’10’17 Rev. 7 Apr/OlPagell

 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1170

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I INTROWCTION 61-10-17 Page 12

Rev. 7Apr/Ol
 PROPELLER MAINTENANCE MANUAL
H RTZ E L L 117D

CONTENTS

1. Description 3

A. General 3

B. Components 3

2. Operation 3

A. Compact Constant Speed and Feathering Propellers (-2) 3

B. Feathering, Turbine Propellers (-5) 4

3. Model Designation System 5

A. Propeller Model Description 5

B. Blade Shank Designation 5

FIGURES

Propeller Model Designation System Figure 1 ..........................6

DESCRIPTION FIND OPERPITION 61 -1 0-1 7 Rev 4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

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DESCRIPTION AND OPERATION 61110117 Rev. 4 May/99Page 2

 PROPELLER MAINTENANCE MANUAL
H PIRTZ ELL 117D

1. Description

A. General

Hartzell compact propellers use aluminum blades mounted in an aluminum hub.

The hub is held together with bolts and contains the pitch change mechanism.
The pitch change components include the piston, pitch change rod, fork, pitch
change blocks, and pitch change knobs.
B. Components
The model designation system for propellers described in this manual is outlined
in Figure 1.

2. Operation

A. Compact Constant Speed and Feathering Propellers (-2)

(1) The -2 Series propellers are constant speed propellers that use an air
charge, spring, and counterweights (when applicable) to move the blades to
high pitch/feather position. Blade centrifugal twisting moment acts to move
the blades to low pitch, but the air charge, spring, and counterweights
overcome this force. Oil pressure against a propeller mounted hydraulic

piston opposes the counterweight, spring, and air charge forces to move the
blades to low blade angle (iow pitch).

(2) The action of the aircharge, spring, and counterweights tends to move the
blades to a higher blade angle thigh pitch), reducing engine RPM. Oil
pressure toward low pitch increases engine RPM.

(3) If oil pressure is lost during operation, the propeller will feather. Feathering
occurs because the air charge, spring, and blade counterweights are no

longer opposed by hydraulic oil pressure. The air charge, spring and blade
counterweights are then free to increase blade pitch to the feathering thigh
pitch) stop.
(4) Normal in-flight feathering of these propellers is accomplished when the
pilot pulls the propeller pitch control past the feather detent. This allows
control oil to drain from the cylinder and return to the engine sump. The
engine can then be shut down.
(5) Normal in-flight unfeathering is accomplished when the pilot positions the
propeller pitch control into the normal flight (governing) range and an engine
restart is attempted.

(6) Some aircraft are equipped with a hydraulic accumulator, which stores a
supply of oil under pressure. This oil supply is released to unfeather the
propeller during an in-flight engine restart. Pressurized oil is directed to the

propeller, resulting in blade angle decrease. The propeller begins to

windmill, and engine restart is possible.

DESCRIPTION FIND OPERPITION 61 -1 0’17 Rer 4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(7) When the engine is

stopped on the ground, it is undesirable to feather the
propeller, as the high blade angle inhibits engine starting. To prevent
feathering during normal engine shutdown on the ground, the propeller
incorporates spring energized latches. As long as propeller rotation is
approximately 800 RPM or above, the latches are disengaged by centrifugal
force acting on the latches to compress the springs. When RPM drops
below 800 RPM land blade angle is typically within 7 degrees of the low
pitch stop), the springs overcome the latch weight centrifugal force and
move the latches to engage the high pitch stops, preventing blade angle

movement to feather.

B. Feathering, Turbine Propellers (-5)

(1) The -5 Series propellers are constant speed propellers that use an air
charge, spring, and counterweights to move the blades to high pitch/feather
position. Blade centrifugal twisting moment acts to move the blades to low
pitch, but the air charge, spring, and counterweights overcome this force.
Oil pressure against a propeller mounted hydraulic piston opposes the
counterweight, spring, and air charge forces to move the blades to low
blade angle (low pitch).

(2) The action of the air charge, spring, and counterweights tends to move the
blades to a higher blade angle thigh pitch), reducing engine RPM. Oil
pressure toward low pitch increases engine RPM.
(3) If oil pressure is lost during operation, the propeller will feather. Feathering
occurs because the air charge, spring, and counterweights are no longer

opposed by hydraulic oil pressure. The air charge, spring, and blade
counterweights are then free to increase blade pitch to the feathering thigh
pitch) stop.
(4) Normal in-flight feathering of these propellers is accomplished when the
pilot pulls the propeller pitch control past the feather detent. This allows
control oil to drain from the cylinder and return to the engine sump. The
engine may then be shut down.
(5) Normal in-flight unfeathering occurs when the pilot positions the propeller
pitch control into the normal flight (governing) range and restarts the engine.
As engine speed increases, oil is directed to the propeller, and blade angle
decreases.

(6) Start lock latches are not employed on all -5 propellers. These propellers
will feather during normal engine shutdown.

DESCRIPTION FIND OPER~TION 61-10-17 Rev 4

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

3. Model Designation System

A. Propeller Model Designation

Hartzell uses a designation system (Figure 1) to identify
model number
specific propeller and blade assemblies. An example model number would be
HC-C2YF-2CUF/FC8468-3, with the slash mark separating the propeller
designation from the blade designation.
The propeller model number is impression stamped on the propeller hub. The
blade model number is impression stamped on the butt end of the blade, as
well as ink stamped or identified by a label on the camber side of the blade.

B. Blade Shank Designation

Refer to Hartzell Manual 133C (61-13-33), Aluminum Blade Manual for more

information on blade shank designs.

DESCRIPTION FIND OPERPITIO# 61 -1 0’17 Rev. 4

 PROPELLER
HARTZELL UA:N1:E~NANCE
D711LdUNIPM

B HC C 2 Y F 2 UF i blade model

r I
REFER TO HARTZELL MANUAL

MINOR MODIFICATIONS BLANK TO FIVE CHARACTERS

133( )FOR ALUMINUM BLADES.

(SEE NEXT PAGE)

I’
SPECIFIC DESIGN
FEATURES
2- FEATHERING, OIL PRESSURE TO LOW PITCH, AIR CHARGE AND SPRING
TO HIGH PITCH/FEATHER (SOME EXCEPTIONS), MAY OR MAY NOT HAVE
COUNTERWEIGHTS

CONSTANT SPEED, FEATHERING, OIL PRESSURE TO

LOW PITCH, COUNTERWEIGHTS, FEATHERING SPRING, AIR CHARGE

BOLT DOWELS NO. OFBOLTS TYPICALENGINE

CIRCLE IN. NO. DIAMETER OR STUDS

HUB MOUNTING F 4´•00 2 1/2 6 (1/2") CONTINENTAL

FLANGE ~L 4.75 4bushings 5/8 6(7/16") LYCOMING
0-290, 0-320
K 4.75 4bushings 3/4 6 (1/2") LYCOMING
R 4.75 5bushings 3/4 6 (1/2") LYCOMING
N 4.25 2 1/2 8 (9/16") GTS10520

BLADESHANKTYPE
i Y SHANK, ALUMINUM BLADE,
INTEGRAL PITCH CHANGE ARM

NUMBER OF BLADES

FLANGE DISTANCE FROM HUB

DESIGNATION PARTING LINE TO FLANGE FACE

C F 3.250
K,R,L 4.187 (HC-C4YR-()= 4.312)
N 3.375
E F 7.750
K,R,L 9.187
HUB EXTENSION N 8.375
F R,L 7.187
CHARACTERISTIC
G F 4.250
H F,N 7.500
R 6.187
F 5.250
J F 6.500
L F 3.750
M R,L 6.750

HC: HARTZELL CONTROLLABLE SINGLE ACTING

BLANK 90 AND 270 DEGREES CLOCKWISE CONTINENTAL

B 30 AND 210 DEGREES CLOCKWISE CONTINENTAL, FRANKLIN, AND PORSCHE
C 150 AND 330 DEGREES CLOCKWISE LYCOMING, CONTINENTAL
DOWEL LOCATION --I D 60 AND 240 DEGREES CLOCKWISE CONTINENTAL
E 0 AND 180 DEGREES AND PROPELLER TDC MARKS
ALIGNED CONTINENTAL
P 0 AND 180 DEGREES AND PROPELLER TDC MARKS
ALIGNED- CONTINENTAL

Propeller Model Designation System

Figure 1

6
DESCRIPTION AND OPERATION 61 -1 0-1 7 Rev 7PA~eO:Page
 PROPELLER MAINTENANCE MANUAL
~IARTZELL 117D

BHC-C2YF-2UF

T
MINOR MODIFICATIONS,
-2 TWO WAY PROPS:

)HC-(C,I,L,M )PY(F,K,L,R )-2_ PROPS (print D-2271)

B
C
D
830-21 STOP UNITS
COUNTERWEIGHTS, 830-30 STOP UNITS
A-2476-14 SPINNER MOUNTING KIT
up to five characters E A-2476-4 SPINNER MOUNTING KIT
F LARGE PITCH CHANGE KNOB, FORK
G DAMPER INSTALLED 8 A-2476-16 SPINNER MOUNTING KIT
H A-2476-8 SPINNER MOUNTING KIT
K SPECIAL AIR CHARGE DECAL, -3 MOUNTING STUDS
L LEFT HAND ROTATION
R 2 3 BLADE: LARGE DIA. CYLINDER AND PISTON

()HC´•(C,I,L,M )PY(F,K,L,R )-2C_U_ PROPS (print D-2292)

C-COUNTERWEIGHTS
D A-2476-14 SPINNER MOUNTING KIT
E A-2476-4 SPINNER MOUNTING KIT
F LARGE PITCH CHANGE KNOB, FORK
G DAMPER INSTALLED 8 A-2476-16 SPINNER MOUNTING KIT
H A-2476-8 SPINNER MOUNTING KIT
K SPECIAL AIR CHARGE DECAL, -3 MOUNTING STUDS
L LEFT HAND ROTATION
U FEATHER ASSIST SPRING KIT IN CYLINDER

HC-ESY(R,K,L)-P_B_ PROPS (print 0-2270)

B 830-21 STOP UNITS (non-counterweighted props)
F LARGE PITCH CHANGE KNOB, FORK
L LEFT HAND ROTATION
R 2 3 BLADE: LARGE DIA. CYLINDER AND PISTON
S A-2273 SPRING ASSY. IN HUB EXTENSION
T 8-1586 SPRING ASSY. IN HUB EXTENSION

HC-(E,F)1IY(R,L)-P_ PROPS (print D-3227)

F LARGE PITCH CHANGE KNOB, FORK
T 8-1586 SPRING ASSY. IN HUB EXTENSION
U 8-1589/1589-2 SPRING ASSY. IN CYLINDER

BHC-J2YF-SC_ PROPS (print D-2290)

C-COUNTERWEIGHTS
F LARGE PITCH CHANGE KNOB, FORK
U 8-1589/1589-2 SPRING ASSY. IN CYLINDER

Propeller Model Designation System (cont’d)

Figure 1

7
DESCRIPTION AND OPERATION 61’1 0’1 7 Rev. 4 May/99Page
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 117D

BHC-C2YF- 2 UF

MINOR
r
MODIFICATIONS,
-2 THREE WAY PROPS

HC-F3YR-2_
F
U
PROPS (print D-3265)
LARGE PITCH CHANGE KNOB, FORK
8-1589/1589-2 SPRING ASSY. IN CYLINDER

up to five characters HC-13YR-2(L)UF PROPS (print D-4090)

L LEFT HAND ROTATION
U 1589-2 SPRING ASSY. IN CYLINDER
F LARGE PITCH CHANGE KNOB, FORK
(P)HC-(E,J,H)3V(R,N,F)-2_ PROPS (print D-3280)
A E3YR-2: INTEGRAL HUB EXTENSION (no A, bolt-on
extension)
F LARGE PITCH CHANGE KNOB, FORK
K DIFFERENT MOUNTING STUDS
L LEFT HAND ROTATION
T B-1586 SPRING ASSY. IN HUB EXTENSION
U 8-1589/1589-2 SPRING ASSY. IN CYLINDER

(P,E)HC-(C,G,1)3V(R,N,F)-2_ PROPS (print D-3255, E-6062)

A C3YN-2L: DIFFERENT SPINNER MOUNTING KIT
PHC-13YF-2AL: DIFFERENT SPINNER MOUNTING KIT
D C3YN-2: DIFFERENT SPINNER INSTALLATION KIT/ASSY.
E C3YR-2: DIFFERENT SPINNER, 8-1106 SPRING ASSY. USABLE
F LARGE PITCH CHANGE KNOB, FORK
K C3YF-2: DIFFERENT SPINNER, MOUNTING STUDS
L LEFT HAND ROTATION
U B-1589/1589-2 SPRING ASSY. IN CYLINDER

-2 FOUR WAY PROPS

HC-C4Y(R,F,N)-2_ PROPS (print E-4510, E-4500)

E LONG STUDS WITH HUB EXTENSION
L LEFT HAND ROTATION

15 PROPS (prints D-3680, D-3690)

A CBYN: SAME AS -2 PROP EXCEPT TURBINE O-RINGS
F- LARGE PITCH CHANGE KNOB, FORK

Propeller Model Designation System (cont’d)

Figure 1

8
DESCRIPTION AND OPERATION 61-10-17
 PROPELLER MAINTENANCE MANUAL
HA,RTZ ~LL 1170

CONTENTS

1. Trouble-Shooting Guide 1 03

A. Pitch Control Difficulty. 103

B. Friction. 103

C. Abnormal Propeller Vibration. 103

D. Blades Not Tracking. 105

E. End-Play Movement of the Blade. 105

F In-and-Out Movement of the Blade. 105

G. Fore-and-Aft Movement of the Blade 105

H. Radial Play in the Blade. 105

I. Oil Leakage 106

J. External Grease Leakage 106

2. Lightning Strike on Hub or Blade 107

FIGURES

Checking Blade Movement Figure 101 104

TESTING ANO FAULTISOLATION S1’1 0’1 7

 PROPELLER MANUAL
HA Rf Z E LL

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102
TESTING AND FAULT ISOLATION 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 117D

1. Trouble-Shooting Guide

The purpose of this guide is to help isolate probable causes and suggest possible
remedies for some of the more common propeller service problems. In all cases,
the remedy for a problem should follow the procedures detailed in the applicable
section of this manual.

Problem Probable Cause Remedy

Excessive friction in moving Refer to problem B. Friction.

I A. PitchControl Difficulty.
parts.

Oil leaking past piston causing Disassemble the propeller and

underspeed. inspect the O-ring and piston-to-
cylinder sealing surfaces. Replace
defective O-ring.

B. Friction. Insufficient clearance between Check/increase the clearances

the variousmoving parts in the between the individual parts as

pitch change mechanism. necessary to decrease friction in

the mechanism.

or Ballsintheblade retention Replace the blade retention split

split bearing are unusually bearing assembly.
rough, corroded, or chipped.

or Bladepreload isexcessive. Disassemble the propeller and

readjust the blade preload.

or Lackof lubrication. Add approved lubrication.

C. Abnormal Propeller Bent, cracked, or damaged Refer to Hartzell Aluminum Blade

Vibration. blade. Overhaul Manual 133C (61-13-33).

or Crackedordamaged hub. Refer to Chapter 1300, Aluminum

Hub Overhaul, in Hartzell Standard
Practices Manual 202A (61-01-02).

103
TESTING AND FAULT ISOLATION 61-10-17 Rev. 7 Apr/OlPage
 PROPELLER
HARTZELL MPI:N~NINCE MANVAL

APS5003A

Fore and
Radial play in aftblade

p~ movement

In and out blade

movement
1
End-play
in blade

Checking Blade Movement

Figure 101

104
sl-lo-17
 PROPELLER MAINTENANCE MANUAL
RT Z cl L L 1176

Problem Probable Cause Remedy

D. Blades NotTracking. Foreign object strike damage. Refer to Hartzell Standard

Practices Manual 202A (61-01-
02), Chapter 1100, Special
Inspections for inspection
procedure.

E. End-Play Movementof Buildup of wear or repair Disassemble the propeller and

the Blade. tolerances. reset the preload.
Refer to Figure 101.

or Blade retention bearing is worn. Inspect/Replace blade retention

bearing.

or Blade alignment bearing is Replace the blade alignment

worn. bearing.

F. In-and-Out Movementof Buildup of wear or repair Disassemble the propeller and

the Blade. tolerances. reset the preload.
Refer to Figure 101.

or Blade retention bearing is worn. Inspect/Replace blade retention

bearing.

G. Fore-and-Aft Buildup of wear or repair Disassemble the propeller and

Movement of the Blade. tolerances. reset the preload.
Refer to Figure 101.

or Blade retention bearing is worn. Replace blade retention bearing.

or Blade alignment bearing is Replace the blade alignment

worn. bearing.

Fl. Radial Play intheBlade. Pitch change fork is worn. Disassemble the propeller.
Inspect and replace parts, as
required.

Pitch change knob bushing is Disassemble the propeller.

worn. Inspect and replace parts, as
required.

Pitch change block is worn. Disassemble the propeller.

Inspect and replace parts, as
required.

105
TESTING AND FAULT ISOLATION 61’1 0’1 7 Rev. 4 May/9 Page
 PRaPELLER MINUAL
HARTZELL

Problem Probable Cause Remedy

i. Oil Leakage Faulty O-ring seal between the Remove the propeller from the
engine flange and the engine and inspect the O-ring and
propeller mounting flange. the sealing surface. Replace
defective O-ring.

or Engine crankshaft seal Replace the engine crankshaft

leaking. seal.

or Faulty O-ring seal on the hub Disassemble the propeller and

extension plug. inspect theO-rings and the sealing
surfaces. Replace defective O-
ring(s).

or FaultyO-ring seal betweenthe Remove the cylinder and inspect

hub-half and the cylinder. theO-ring and the
sealing surface.
Replace defective O-ring.

or Faulty internal propellerO-ring. Disassemble the propeller and

inspect the
O-ring and pitch
change rod-to-hub sealing surface
(cylinder side). Replace defective
O-ring.

J. External Grease Leakage Improperly torqued or loose/ Replace missing lubrication fitting.
missing lubrication fitting. Torque lubrication fitting in
accordance with Table 801.

or Grease leaking between blade Disassemble the propeller and

and hub. inspect the hub-to-blade seal and
sealing surfaces. Replace
defective seal.

TESTING AND FAULT ISOLATION 61-10-17 Rev. 4 May/9 Page 106

 PROPELLER MAINTENANCE MANUAL
HA, RT~e LL 117D

2. Liahtnina Strike on Hub or Blade

In the event of apropeller lightning strike, an inspection is required before further flight.
A lightning strike on the propeller usually leaves arcing damage on the metal blade, as
evidence of where it entered or left the tip of the blade. Refer to Hartzell Standard
Practices Manual 202A (61-01-02), Chapter 1100, Special Inspections for lightning
strike inspection criteria.

TESTING AND FAULT ISOLATION 61’1 0’1 7

 PROPELLER
HA RTZ E L L MA:N1:E$JANCE
D711LAUNAM

(This page is intentionally blank.)

108
TESTING AND FAULT ISOLATION 6111 0117 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

AUTOMATIC TEST REQUIREMENTS (NOT APPLICABLE~

NOTE: Per ATA 100 specification this space is reserved for automatic test
requirements. Such requirements are not applicable to the Hartzell
propellers addressed in this manual.

~IUTOMPITIC TEST REOUIREMENTS 61 ’1 0’1 7

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(This page is intentionally blank.)

AUTOMATIC TEST REQUIREMENTS 61110-17 Rev. 4 May/9 Page 202

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117b

CONTENTS

1. Removing the Propeller Assembly from the Aircraft 303

2. Marking Before Disassembly 303

3. Removal of the Propeller Anti-ice or De-ice System (if applicable) 303

A. De-ice System Removal 303

B. Anti-ice System Removal 303

4. Propeller Disassembly 304

A. Disassembly of the Propeller External Pitch Change Parts 304

B. Cylinder Disassembly 306

C. Cylinder Spring Disassembly 309

D. Cylinder High Pitch Stop Unit Disassembly

(Cylinders Without a Spring Assembly) 313

E. Hub Disassembly ("E" Hubs) 315

F Disassembly of the Propeller Internal Pitch Change Parts 318

G. Hub Disassembly 319

H. Pitch Change Fork Disassembly 319

I. Pitch Change Block Disassembly 320

J. Blade Retention Parts Disassembly 320

K. Damper Disassembly 320

FIGURES

Loosening the Spring Assembly Tool Figure 301 .........,..,.._

306

Placing the Assembling Tool TE9 in a Vise Figure 302 309

Positioning the Cylinder on the Assembly Tool Figure 303 310

Removing the First Two Screws Figure 304 311

Installing the Spring Compressor Assembly TE31 Figure 305 314

Compressing the Feathering Springs

with the Spring Compressor Assembly TE31 Figure 306 316

Removing the Blades Using Blade Retention

Components Clamp TE24 Figure 307 318

DISASSEMBLY 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(This page is intentionally blank.)

D,,,,,,,,,, 61-10-17
 PROPELLER MAINTENANCE MANUAL
HA,RTZ ELL 117b

1. Removing the Propeller Assembly from the Aircraft

Refer to Hartzell Propeller Owner’s Manual 115N (61-00-15) for propeller removal.

2. Marking Before Disassemblv

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY IDENTIFY

PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE
STRENGTH OR FUNCTION OF THE PROPELLER.

A. Mount the propeller assembly on the rotatable fixture TE125 on the assembly
table TE129.

B. Record the serial number and model number of the hub, blades, and any other
serial-numbered parts and compare with the data in the propeller logbook.

CAUTION: GRAPHITE ("LEAD") PENCIL MARKS WILL CAUSE CORROSION.

C. Where possible, each blade should be reinstalled into the hub socket from which
it is removed. Number the blades counterclockwise from the serial number
impression stamped on the propeller hub unit. All marks made on parts must be
made with crayon or soft, non-graphite pencil.
D. Record on paper each blade serial number and its matching hub arm.

3. Removal of the Prooeller Anti-ice or De-ice System (if aDPlicable~

A. De-ice System Removal

NOTE: If the propeller is equipped with a de-ice system, follow the instructions in
the appropriate de-ice system manufacturer’s manual for removal of the
slip ring and other components.

(1) Remove the wire clamps or tie wraps from the de-ice lead wires. Disconnect
the de-ice lead wires from the terminal strip (where applicable).

(2) Remove the bolts and screws that attach the bulkhead and slip ring to the

hub, as applicable.
B. Anti-ice System Removal
(1) Remove the screws or bolts that attach the slinger ring unit to the hub.

(2) Remove the stinger ring unit.

(3) Remove the hub bolts that attach the bulkhead and the travel tube unit to
the hub.

(4) Remove the travel tube unit.

s1-lo-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

4. Propeller Disassemblv

WARNING: THE USE OF BLADE PADDLES TO MOVE BLADES CAN RESULT

IN THE OVERLOAD AND DAMAGE OF BLADE PITCH CHANGE
KNOBS. THIS DAMAGE IS NOT REPAIRABLE AND CAN RESULT
IN SEPARATION BETWEEN THE BLADE AND THE PITCH
CHANGE KNOB, CAUSING LOSS OF PITCH CONTROL DURING
FLIGHT.

A. Disassembly of the Propeller External Pitch Change Parts

WARNING: SOME MODELS OF THE -2 PROPELLER AND ALL OF THE -5

PROPELLERS INCORPORATE SPRINGS UNDER PRESSURE.
THE SPRINGS COULD BECOME LETHAL PROJECTILES AND
MUST BE CAREFULLY DISASSEMBLED ACCORDING TO
DIRECTIONS. TO ASSURE PERSONAL SAFETY, ALL -2 AND -5
PROPELLERS ARE DISASSEMBLED IN THE SAME MANNER.

NOTE 1: The propeller model number is recorded in the log book, and is also
stamped on the propeller hub. The propeller model number indicates the
presence of a cylinder spring kit by a "U" after the dash number. For
example: HC-C3YR-2LUF indicates a "U" spring kit. The following
propeller models have a "U" spring installed that is not indicated in the part
number: HC-C3YF-5F, HC-C3YN-5A, PHC-13YF-2AL.

NOTE 2: Other models may have cylinder springs without the "U" being present in
the propeller model number. The "U" cylinder spring kit may have been
installed after the propeller was in the field and the propeller may not have
been properly reidentified after installation.

(1) Remove the air valve cap, if present.

(2) Using an air gauge or other appropriate instrument, depress the needle in
the air valve (40) to release the air charge in the cylinder (70).

WARNING: INTERNAL CYLINDER AIR PRESSURE MUST BE REDUCED TO

ZERO BEFORE ATTEMPTING TO REMOVE THE AIR VALVE.

(3) Remove and discard the air valve (40).

(4) Remove the counterweights, if applicable. Refer to Hartzeil Aluminum Blade
Manual 133C (61-13-33),
(5) Remove the low pitch stop nut (30).
(6) Remove the low pitch stop (50).
(7) Remove and discard the low pitch stop O-ring (60).

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(8) Using air pressure in the rotatable fixture TE125, move the propeller to low

pitch position.

WARNING: HOLD THE PROPELLER BLADES AT LOW PITCH WITH AIR

PRESSURE IN THE ROTATABLE FIXTURE. REMOVAL OF THE
STOP SCREW (280) WITHOUT AIR PRESSURE COULD
RESULT IN SUDDEN AND EXPLOSIVE ROTATION OF THE
BLADES TO FEATHER PITCH, RESULTING IN PERSONAL
INJURY AND DAMAGE TO THE INTERNAL COMPONENTS OF
THE PROPELLER.

(9) Using the T-handle wrench TE381, remove the stop screw (280), washer
(290) (if used), feather stop washer (300), feather adjust washer(s) (310),
high pitch stop s’leeve (320), and high pitch adjust washer(s) (330).
NOTE: Record onpaper the number of washers both under the feathering
stop and on top of the feathering stop, to facilitate propeller
reassembly.
(10) Discard the stop screw (280), washer (290) (if used), feather stop washer
(300), feather adjust washer(s) (310), and high pitch adjust washer(s) (330).
Retain the high pitch stop sleeve (320).

(11) Release the air pressure in the rotatable fixture to allow the propeller to

move to feather position.

61-10-17
 PRDPELLER MPINUPIL
HARTZELL

B. Cylinder Disassembly

WARNING: USE EXTREME CAUTION WHEN REMOVING THE CYLINDER

AND FEATHERING SPRING ASSEMBLY. WHEN
COMPRESSED, THE FEATHERING SPRING ASSEMBLY IS
LOADED TO APPROXIMATELY 750 POUNDS (341KG) FORCE.
ENSURE THE SAFETY OF PERSONNEL IN THE VICINITY
DURING THE DISASSEMBLY PROCEDURES.

(1) Attach a cylinder wrench TE153 to the top of the cylinder (70).
(2) Insert the small threaded end of the feather assist spring assembling tool
TE9 into the cylinder and turn the tool into the end of the pitch change rod
(370) until tight.
NOTE: Using the spring assembling tool TE9 prevents the spring from
forcefully releasing if the spring retainer is broken or the screws are

damaged.
(3) Tighten the hex nut TE290 on the spring assembling tool TE9 until the guide
washer TE291 and the thrust bearing TE289 are snug against the cylinder
(70).
(4) Loosen the spring assembling tool TE9 hex nut TE290 approximately two
full turns (Figure 301).

APS6326

Loosening the Spring Assembly Tool

Figure 301

DIS~SSEMBLY 61-10’17
 PROPELLER MAINTENANCE MANUAL
H~A RTZ E LL 117D

CAUTION: DO NOT DAMAGE THE CYLINDER THREADS WHEN

REMOVING THE CYLINDER FROM THE HUB.

(5) Turn the cylinder wrench TE153 counterclockwise until the cylinder (70)
threads are free from the hub.

NOTE: The feathering spring assembly attached to the cylinder is removed

with the cylinder.

(6) Unthread the hex nut TE290 on the spring assembly tool TE9, allowing the
feather assist spring to gradually extend.

NOTE: The feather assist spring completely extended when the

is hex nut
TE290, washer TE291, and thrust bearing TE289 become loose.

(7) Remove the feather assist spring assembly tool TE9 and the cylinder
wrench TE153 from the cylinder (70).
(8) Remove the cylinder (70), with the feather assist spring assembly, from the

propeller.
(9) If a spring retainer and spring are present in the cylinder,
feather assist
continue to 4.C. Cylinder Spring Disassembly. if the cylinder contains only a

high pitch stop unit, continue to 4.D. Cylinder High Pitch Stop Unit
Disassembly

,,,,,,,,,,Y 61-10-17
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

(This page is intentionally blank.)

DlSASSEMBLY 61-10-17
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 1176

C. Cylinder Spring Disassembly

WARNLNG: WHEN COMPRESSED, THE FEATHERING SPRING ASSEMBLY

IS LOADED TO APPROXIMATELY 750 POUNDS (341 KG)
FORCE. ENSURE THE SAFETY OF PERSONNEL IN THE
VICINITY DURING DISASSEMBLY PROCEDURES.

CAUTION: DO NOT ATTEMPT TO DISASSEMBLE THE SPRING

ASSEMBLY WITH THE CYLINDER TORQUE WRENCH
ADAPTER TE153 ATTACHED TO THE CYLINDER.

(a) Place the assembling tool TE9 in a vise with the flattened portion of the
threaded rod TE287 between the jaws of the vise, and tighten the vise
(Figure 302).

APS6181

Placing the Assembling Tool TE9 in a Vise

Figure 302

61-10-17
 PROPELLER
HARTZELL M*:NI:EDNPINCE MINUIL

85T2853
W10033

Cylinder Cap
TE380

TE388

TE387

Cylinder
TE288 ~f j (70)

TE287

Hex Nut
TE290

Positioning the Cylinder on the Assembly Tool

Figure 303

OISASSEMBLY 61-10-17 Rev. 4 May/9 Page 310

 PROPELLER MAINTENANCE MANUAL
H119 RTr E LL 117D

CAUTION: DO NOT DAMAGE THE CYLINDER THREADS WHEN

INSTALLING THE CYLINDER CAP TE380.

(b) Install the cylinder cap TE380 on the cylinder (70) (Figure 303).
(c) Slide the cylinder (70) onto the assembling tool TE9 with the small opening
of the cylinder toward the vise (Figure 303).
(d) Put the drilled washer TE288 over the end of the set screw TE388 in the
end of the assembling tool TE9 (Figure 303).
(e) Install two nuts TE387 on the set screw TE388 (Figure 303).
(f) Turn the hex nut TE290 until the drilled washer TE288 is snug against the
weight (190) or retainer plate (200) with two screws (180) visible through the
large holes in the washer (Figure 304).
(g) Remove and discard the two screws (180).
(h) Loosen the hex nut TE290 until the drilled washer TE288 can be rotated
over weight (190)
the or retainer plate (200) and two screws (180) inside the
spring retainer (220).
(i) Turn the drilled washer TE288 until the heads of the remaining two screws

(180) can be seen through the large holes in the drilled washer TE288
(Figure 304).

APS6191

The first two

screws to be
removed

NOTE: For
illustration purposes,
the cylinder cap
TE380 has been
removed

Removing the First Two Screws

Figure 304

DISASSEMBLY ~1’10-17
 PROPELLER
HARTZELL MA:N1SEDNP~NCE MANUAL

(j) Tighten the hex nut TE290 until the drilled washer is secure against the
weight (190) or retainer plate (200).
(k) Remove the remaining two screws (180).
(I) Remove the cylinder cap TE380.

(m) Loosen the hex nut TE290 until the feather assist spring (230) is fully
released.

(n) Remove the two nuts TE387 and the drilled washer TE288.

to) Remove the weight (190) or retainer plate (200) and the washer (250).
(p) Remove and discard the spring retainer (220).
(q) Remove the feathering spring (230).
(r) Loosen and remove the screws (100) holding the high stop bracket
(240) in place.
(s) Remove the high stop bracket (240).
(t) Remove and discard the cylinder ID O-ring (90).

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

D. Cylinder High Pitch Stop Unit Disassembly (Cylinders Without a Spring Assembly)
(1) Attach a cylinder wrench TE153 to the top of the cylinder (70).

CAUTION: DO NOT DAMAGE THE CYLINDER THREADS WHEN

REMOVING THE CYLINDER FROM THE HUB.

(2) Remove the’cylinder (70).

(3) Remove the cylinder wrench TE153 from the cylinder (70).
(4) Remove and discard the four screws (100) attaching the stop unit (IlO)to
the inside of the cylinder (70).
(5) Remove the stop unit (110).
(6) Remove and discard the cotter pin (150).
(7) Remove the high stop pin (140).
(8) Remove and discard the auto high stop spring (130).

DISASSEMBLY 61’10117
 PROPELLER
HARTZ ELL MA:N~DNANCE MANUAL

APS6203

Spring Compressor Bolt TE284

Spring Compressor Slide TE283

Propeller
Mounting
Stud

Installing the Spring Compressor Assembly TE31

Figure 305

314
61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

E. Hub Disassembly ("E" Hubs)

NOTE: An example of and "E" hub part number is )HC-E( )Y( )-2.
(1) Using a sling, remove the propeller from rotatable fixture TE125 on the
assembly table TE129.
(2) Turn the propeller over and place on a support so the propeller mounting
flange is accessible.

NOTE: A sturdy barrel or drum with the rim well padded, may be used as a

support.
(3) Remove the extension plug (660).
(4) Remove and discard the extension plug OD O-ring (670).
(5) Remove and discard the extension plug ID O-ring (680).

CAUTION: SPRING COMPRESSOR ASSEMBLY TE31 IS DESIGNED FOR

USE WITH "R" OR "K" FLANGE PROPELLERS AND WILL NOT
ENGAGE THE SMALLER DIAMETER "L" FLANGE MOUNTING
STUDS.

NOTE: A new bolt with smaller ID thread may be fabricated to take the place of
a

the spring compressor bolt TE284, or an "R" or "K" flange style stud may
be used for disassembly purposes only.
(6) Install thespring compressor assembly TE31 on the propeller mounting
flange (Figure 305).
NOTE: The spring compressor assembly TE31 has six holes to clear the
studs already installed.

(a) Center the spring compressor slide TE283 on the spring retainer (560)
in the propeller hub bore and align the spring compressor bolts TE284
with the studs in the hub mounting flange.

NOTE: The spring may be compressed using only two of the three
spring compressor bolts TE284 supplied, positioned
approximately 180 degrees apart.
(b) Install the nuts on the spring compressor bolts TE284.

NOTE: The nuts should be positioned close to the heads of the spring
compressor bolts TE284.

(c) Turn the propeller mounting bolts into the ends of the spring
compressor bolts TE284 until tight (Figure 305).
NOTE: The spring compressor bolts TE284 have both ID and OD
threads.

DISASSEMBLY 61’10’17
 PROPELLER
HARTZ ELL M*~EDNANCE MANUAL

APS6204
APS6205

TE31
Fully
Compressed

Compressing the Feathering Springs with the Spring Compressor Assembly TE31
Figure 306

316
DISASSEMBLY 61-10-17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL IlfD

WARNING: WHEN COMPRESSED, THE FEATHERING SPRING ASSEMBLY

IS LOADED TO APPROXIMATELY 1000 POUNDS (454 KG)
FORCE. ENSURE THE SAFETY OF PERSONNEL IN THE
VICINITY DURING ASSEMBLY PROCEDURES.

CAUTION: TIGHTEN THE SPRING COMPRESSOR NUTS EVENLY TO

PREVENT BINDING.

(7) Compress the springs (540, 550) by evenly tightening the spring
compressor nuts (Figure 306).
NOTE: Tightening the spring compressor nuts will move the spring retainer
(560) beyond the groove in the pitch change rod (370) and allow the
removal of the keeper (570).

(8) Remove and discard the keeper (570) halves from the groove in the pitch
change rod (370).
(9) Decompress the springs (540)(550) by evenly loosening the spring
compressor nuts.

(10) Remove the spring compressor assembly TE31 from the propeller mounting
bolts.

(11) Remove the spring retainer (560).

(12) Remove the large diameter feathering spring (540).
(13) Remove the small diameter feathering spring (550).
(14) Remove the spring guide (530) (8-1586 Spring Assembly ONLY).
(15) Remove the spacer (520) (A-2273 Spring Assembly ONLY).
(16) Reinstall the propeller on the rotatable fixture TE125 on the assembly table
TE129.

61-10-17
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 117D

F. Disassembly of the Propeller Internal Pitch Change Parts

(1) Remove and discard the piston nut (340).

(2) Remove the piston (350).
(3) Remove and discard the piston O-ring (360).
(4) Using the wrench adapter TE6, remove the pitch change rod (370).
(5) Remove and discard the hub nuts (610) and washers (600).
(6) Remove the short and long hub bolts (580, 590).
NOTE: If thespinner bulkhead is mounted to the propeller with the hub bolts,
the spinner bulkhead will be removed at this time.
(7) Remove and discard the cylinder mounting O-ring (380) from the cylinder-
side hub half.

(8) Lift off the cylinder-side hub half.

NOTE: The hub half may be difficult to remove because sealant was applied
between the hub halves. A plastic wedge and rubber mallet may be
used to separate the hub halves.

(9) Remove and discard the pitch change rod O-ring (390) from the cylinder-
side hub half.

APS2044

5
C/~

Removing the Blades Using Blade Retention Components Clamp TE24

Figure 307

61’10’17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117b

(10) Using blade retention components clamp TE24, remove blade number one,
preload plate, and thrust bearing (Figure 307).
(11) Remove the pitch change fork (400).
(12) Remove the pitch change blocks (440).
(13) Using blade retention components clamp TE24, remove the remaining
blade(s).
(14) Remove the engine-side hub from the rotatable fixture.
(15) Remove and discard the pitch change rod O-ring (470) from the engine-side
hub half.

(16) Remove the spinner bulkhead from the rotatable fixture, if applicable.
G. Hub Disassembly
Refer to Hartzell Standard Practices Manual 202A (61-01-02), Chapter 1300,
Aluminum Hub Overhaul, for disassembly instructions.

H. Pitch Change Fork Disassembly

NOTE: Pitchchange forks with steel rubbing plates and brass rivets should be
upgraded to the current plastic rubbing plate configuration. Refer to
Chapter 600, Repair, in this manual for information on upgrading pitch
change forks to the current configuration.
(1) Two-Bladed Propeller Pitch Change Fork Disassembly
(a) Remove and discard the spring pins (430).
(b) Remove and discard the plastic rubbing plates (420).
(2) Three-Bladed and Four-Bladed Propeller Pitch Change Fork Disassembly
Remove and discard the pitch change fork buttons (410).

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

i. Pitch Change Block Disassembly

Remove and discard the pitch change block button (450) from the pitch change
block, if applicable.
J. Blade Retention Parts Disassembly Refer to Figure 1010.

(1) Remove and discard the blade seal (3010).

(2) Remove the hub-side bearing race (3020).
(3) Remove and discard the ball bearings (3030).
(4) Remove and discard the ball spacer (3040).
(5) Remove and discard the pitch change knob bushing (3000) from the blade.

(6) Remove and discard the jam nuts (3110) and set screws (3100) from each
preload plate (3090).
(7) Remove the preload plate (3090).
(8) Remove the bearing retention ring (3060) using a suitable gear puller or
brass drift.

(9) Remove the blade-side bearing race (3050) of the blade retention split-
bearing.
(10) Refer to Hartzell Manual 133C (61-13-33), Aluminum Blade Overhaul
Manual for blade overhaul procedures.

K. Damper Disassembly HC-C2YK-2C(L)G(F) and HC-C2YK-2C(L)GU(F) only

NOTE: Refer to Figure 752 for damper disassembly.
(1) Remove and discard the eight screws (990).
(2) Remove the hex head spacer tubes (910).
(3) Remove and discard the spring (920) and wa’shers (930)(940).
(4) Remove the sealant CM92 from between the damper weight (950) and the
plate (980).
(5) Separate the damper weight (950) and the plate (980).
(6) Remove and discard the silicone grommets (960) and the friction disc (970).

DlSASBEMBLY 61 -10-17 Rev

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

CONTENTS

1. General Procedures for Cleaning Parts 403

2. Specific Cleaning Procedures 403

CLEANING 61-10’17
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 117D

(This page is intentionally blank.)

CLEANING 61’10’17 Rev. 4 May/9 Page 402

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

1. General Procedures for Cleaning Parts

Refer to Hartzell Standard Practices Manual 202A, Chapter 100.

2. Specific Cleaning Procedures

A. Cleaning Steel Parts for Magnetic Particle Inspection

Refer to Hartzell Standard Practices Manual 202A, Chapter 200.

B. Cleaning Steel Parts for Cadmium Re-Plating Procedures

Refer to Hartzell Standard Practices Manual 202A, Chapter 1500.

C. Cleaning Steel Parts for Penetrant Procedures

Refer to Hartzell Standard Practices Manual 202A, Chapter 300.

D. Cleaning Aluminum Parts for Chromic Acid Anodizing Procedures

Refer to Hartzell Standard Practices Manual 202A, Chapter 1600.

CLEANING 61’1 0’1 7

 PROPELLER MAINTENANCE MANUAL
HA.RTZELL 117D

(This page is intentionally blank.)

CLEINING 61’10’17
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 117D

CONTENTS

1. Inspection Interval Requirements 503

2. Inspection Requirements 503

3. Replacement Requirements 503

4. Repair 503

5. Hub Unit Inspection 504

6. Specific Inspection Procedures 504

7. Specific Checks 504

A. Spinner Nut

B. Spinner Spacer 505

C. Low Stop 507

D. Cylinder. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .´•´•´•´•´•´•´•´•´•´•´•´•´•´•´• 508

E. Bracket, Auto High Stop 510

F Pin, High Stop 510

G. Spring Guide 510

H. Plate, Retainer 510

i. Weight 511

J. Spring, Feathering (Cylinder) 512

K. Bracket, High Pitch Stop 512

L. High Pitch Stop Sleeve 512

M. Washer 513

N. Piston

O. Pitch Change Rod

P Fork

Q. Pitch Change Block 521

R. Hub Unit

S. Spacer 521

T. Spring Guide 522

U. Spring, Feathering (Hub) 522

V. Spring, Feathering (Hub) 522

W. Spring Retainer 523

X. Hub Bolt Inspection

Y. Plug, Shaft 525

Z. Hex Head Spacer Tube 526

AA. Damper Weight

sl-lo-17
 PROPELLER
HARTZ E LL MA:N1TEDNANCE MANUAL

7, Specific Checks (cont’d)

AB. Support Plate 527
AC. Blade Bearing Race 529
AD. Ring, Bearing Race Retention 531
AE, Preload Plate 531
AF Balance Weights 532

FIGURES
Low Stop Dimensions Figure 501 506

Cylinder Dimensional Inspection Criteria ....Figure 502 508

Weight Identification Figure 503 511

Washer Identification Figure 504 513

Piston Dimensionai Inspection Criteria...... Figure 505 514

One-Piece Pitch Change Rod................ Figure 506 516

Two-Piece Pitch Change Rod Figure 506.1 517.1
Pitch Change Block Identification/Dimensional Criteria Figure 507 520

Shaft Plug Figure 508 524

Blade Split Bearing Figure 509 528
Preload Plate Figure 510 530

TABLES

Component Inspection Criteria ,,......,Table 501 505

I CHECK 61-10-17 Page 502

Rev. 7
Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

1. lnsoection Interval Reauirements

A. Refer to the Airworthiness Limitations Chapter of this manual for information on

life limited components and mandatory inspections.

B. Refer to Hartzell Service Letter 61( for overhaul periods of Hartzell propellers

2. Inspection Reauirements

A. Inspect all wearing parts to determine if they meet the specifications in Chapter
500, Check, of this manual.

NOTE: Any serial-numbered part found unairworthy must be retired in

accordance with Mandatory Parts Retirement Procedure, Chapter 1200
in the Hartzell Standard Practices Manual 202A (61-01-02).

B. Visual Inspection
Visually inspect all parts.
C. Penetrant Inspection
Penetrant inspect aluminum parts, as required. Refer to Table 501. Follow the
procedures for penetrant inspection found in Hartzell Standard Practices Manual
202A (61-01-02), Chapter 300 for inspection of aluminum parts.

D. Magnetic Particle Inspection

Magnetically inspect steel parts, as required. Refer to Table 501. Follow the
procedures for magnetic particle inspection found in Hartzell Standard Practices
Manual 202A (61-01-02), Chapter 200 for inspection of steel parts.

E. Dimensional Inspection
(1) Dimensionally inspect parts, as required. Refer to Table 501. When
measuring the diameter of a part, take at least two measurements unless
otherwise specified. Obtaining a measurement outside the specified
tolerance at any point of measurement is cause for retirement of the part.

(2) Inspect the part features to the number of decimal places specified. If three
decimal places are specified, inspect the part to three decimal places only.

3. Replacement Reauirements

Replace all parts that have cracks, wear, obvious defects, or damage found during
visual inspection that do not meet serviceable limits.

4. Reoair
of
Repairable part defects are noted in the inspection criteria in Chapter 500, Check,
this manual. Repair procedures are found in the Repair section of this manual,
unless otherwise stated.

CHECK 61’1 0’1 7

 PROPELLER
HA RTZ E LL MA:N1~EDNANCE MANUAL

5. Hub Unit Insi3ection

Refer to Hartzell Standard Practices Manual 202A (61-01-02), Aluminum Hub

Overhaul, Chapter 1300 for requirements and procedures for inspecting aluminum
hub units.

6. Specific Inspection Procedures

A. Refer to Hartzell Manual 115N (61-00-15), Propeller Owner’s Manual and Log
Book, for daily inspection procedures.
B. Refer to Hartzell Manual 133C (61-13-33) for requirements and procedures for
inspecting aluminum blades.

C. Refer to Hartzell Standard Practices Manual 202A

(61-01-02), Chapter 1-100,
Special Inspections, for foreign object strike inspection procedures.
D. Refer to theappropriate manufacturer’s manual for de-ice system inspection
procedures, if applicable.
E. Refer to Hartzell Manual 127 (61-16-27) for spinner assembly inspection
procedures.

7. Specific Checks

See Table 501 for specific component checks.

CHECK 61’10’17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

A. SPINNERNUT
(Items 10, 30)

(1) Visually inspect each Corners between the wrenching File away unwanted material
spinner nut for wrenching flats may be rounded. Two (2) displacement.
damage. wrenching flats must be
sufficiently undamaged to Replace the nut if a minimum of
withstand installation torque. No two (2) flats will not withstand
material may be displaced above installation torque.
or below the nut that could result
in interference with the mating
parts.

(2) Visually inspect each Maximum allowable depth of None. Replace the nut.

spinner nut for corrosion on material loss is 0.005 inch

all surfaces and wear on (0.13 mmj.
surfaces other than
wrenching flats.

(3) Visually inspectthe spinner Cadmium plating must be Replate the nut in accordance
nut for cadmium plate present on all surfaces. with Hartzell Standard Practices
coverage. Manual 202A (61-01-02),
Chapter 1500, Cadmium
Replating.
B. SPINNER SPACER
(Item 20)

(1) Visually inspect the spinner Maximum allowable depth of None. Replace the spinner
spacer for corrosion, wear, material loss is 0.003 inch spacer.
or damage. (0.08 mm);

(2) If a magnet attracts the Plating must be present on all Replate the spacer in
spinner spacer, visually surfaces, accordance with Hartzell
inspect the spinner spacer Standard Practices Manual 202A
for cadmium plate (61-01-02), Chapter 1500,
coverage. Cadmium Replating.

(3) If a magnet does not attract Material is stainless steel or None.

the spinner spacer, do not brass and cadmium plating is not
inspect for cadmium plate required.
coverage.

505
CHECK 61’10’17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

APS6256
LOW6TOP.XLS

"X"

Part No. "X" Dimension "Y" Dimension

A-2404-4 2.00 0.03 inch 0.500 0.010 inch

(50.8 0.8 mm) (12.70 0.05 mm)

A-2404-3 2.35 0.03 inch 0.700 0.010 inch

(59.7 0.8 mm) (17.78 0.05 mm)

A-2404-2 2.00 f 0.03 inch 0.600 0.010 inch
(50.8 0.8 mm) (15.24 0.05 mm)
A-2404-1 2.10 rt 0.03 inch 0.700 0.010 inch
(53.3 0.8 mmj (17.78 0.05 mm)
A-2404 2.25 0.03 inch 0.800 0.010 inch
(57.2 0.8 mm) (20.32 0.05 mm)

Low Stop Dimensions

Figure 501

506
CHECK 61-10’17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

C. LOVVSTOP
(Item 50)
(Refer to Figure 501)

(1) Visually inspect the pitch No damage is allowed. None. Replace the low stop.
change rod/low stop
contact surface for
damage.

(2) Visually inspect the One damaged thread is allowed. None. Replace the low stop.
external threads of the low
stop for damage.

(3) Visually inspect the internal One damaged thread is allowed. None. Replace the low stop.
threads of the low pitch
stop for damage.

(4) Visually inspect the air hole The air passage must be clean None. Replace the low stop if the
in the center of the low and unobstructed. air passage cannot be cleared.
stop.

(5) Visually inspect the Hard No loss of Hard Anodize is None. Replace the low stop.
Anodize on the surface of allowed.
the low stop.
NOTE: To identify the low stop, referto Figure 501.

507
61-10-17
 PROPELLER
HARTZELL MA:N:7EDNANCE MANUAL

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

D. CYLINDER
(Item 70)
(Refer to Figure 502)

(1) Visually inspect the All external surfaces: maintain a Lightly hand polish to blend out
external surfaces of the wall thickness of 0.079 inch (2.00 damage. No high spots are
cylinder for wear, nicks, mm), repaired area must be less allowed. If base aluminum is
scratches or other damage. thatn 0.5 inch(12.7 mm) in exposed, chromate conversion
diameter, repairs must be coat. Replace cylinder if damage
separated by a minimum of 0.5 is beyond limits.
inch (12.7 mm).

Damage in circular area "D" None. Replace the cylinder.

limited to 0.020 inch (0.508 mm)
depth. Sufficient flat surface
must remain to support the nut.

I (2) Visually inspect the cylinder 1/4 of

damage
one thread accumulated
per wrench attachment
Refer to the
this manual for
Repair chapter in
repair of cylinder
for damage. hole is allowed. wrench attachment threads.
APS6230
CYL.XLS

Low pitch stop threads

High pitch stop
Cylinder IIBII

"A"
"C" "D"
Wall
thickness
"E"

Cylinder wrench attachment hole

"A" "B" "C"

Part Number Bushing O-ring Groove Low Pitch Stop O-ring Groove
Maximum Diameter Maximum Diameter Maximum Diameter

8-2423-1 4.759inch 5.235inch 0.989inch

(120.88 mm) (132.97 mm) (25.12 mm)
8-2452-1 5.259inch 5.735inch 0.989inch
(133.58 mm) (145.77 mm) (25.12 mm)

Cylinder Dimensional Inspection Criteria

Figure 502

508
CHECK 61’10’17
 PROPELLER MAINTENANCE MANUAL
nARTZELL 1170

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

D. CYLINDER, cont’d

(3) If cylinder wrench The minimum wall thickness If the wall thickness under the
attachment holes are under the center point of the hole center point of the hole is less
repaired a slimsert,
with is 0.080 inch (2.03 mm). than 0.080 inch (2.03 mm), the
dimensionally inspect the cylinder must be replaced.
wall thickness, "E".

(4) Visually inspect the low No damage is allowed. None. Replace the cylinder.
pitch stop threads for
damage.

(5) Visually inspect the ID of If thecylinder bushing or See Hartzell Standard Practices
the cylinder bushing and surrounding area shows signs of Manual 202A, Chapter 900,
the immediate surrounding wear, dimensionally inspect. Special Adhesive and Bonding
cylinder wall area for signs Cylinder bushings with ID Procedures, for cylinder bushing
of bushing wear, dimensions exceeding the limits replacement procedures.
in Figure 502 must be replaced.

(6) Visually inspect the No unbonded areas are allowed. None. Replace the bushing. Refer

I adhesive bond of the

cylinder bushing.
to the Special Adhesive and
Bonding Procedures chapter of
Hartzell Standard Practices
Manual 202A for cylinder bushing
replacement procedures.

(7) Visually inspect the O-ring If theO-ring groove shows wear, Cylinders withO-ring groove
groove for wear. dimensionally inspect the ID of dimensions exceeding the limits
the O-ring groove in accordance of Figure 502 must be replaced.
with Figure 502.

(8) Visually inspect the One damaged thread is allowed. None. Replace the cylinder.
cylinder mounting th reads
for damage.

(9) Visually inspect the high One damaged thread is allowed None. Replace the cylinder.
pitch stop bracket per attachment hole.
attachment hole threads
for damage.
NOTE: Some older cylindersmay have smaller, additional holes in the high pitch stop bracket
attachment area. No inspection is required for the additional holes. If no large, threaded
holes (0.25 inch, 6.4 mm) are present, the cylinder may be sent to Hartzell for possible
modification.

(10) Visually inspect the low If the O-ring groove shows wear, Cylinders withO-ring groove
pitch stop O-ring groove. dimensionally inspect the ID in dimensions exceeding the limits
accordance with Figure 502. of Figure 502 must be replaced.

509
cnecK 61 -1 0-17
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

E. BRACKET. AUTO HIGH STOP

(Item 120)

(1) Visually inspect the bracket Maximum allowable depth of None. Replace the bracket.
(except the high stop pin material loss is 0.010 inch
bores) for corrosion, wear, (0.25 mm), except for the
or damage. bracketflange base.

For the bracket flange base that None. Replace the bracket.
attaches to the cylinder, the
maximum allowable depth of
material loss is 0.030 (0.76 mm)
in individual gouges.

(2) Visually inspect the high None allowed. None. Replace the bracket.
stop pin bores for corrosion
and damage.

(3) Visually inspect the If thehigh pitch stop pin bores None. Replace the bracket.
diameter of the high stop show wear, dimensionally
pin bores. inspect. Maximum allowable pin
bore ID is 0.503 inch (12.78 mm).

F. PIN. HIGHSTOP
(Item 140)

(1) Visually inspect the high None allowed. None. Replace the pin.
stop pin for corrosion,
wear, or damage.

G. SPRINGGUIDE
(Item 170)

(1) Visually inspect the spring Maximum allowable depth of None. Replace the spring guide.
guide for wear or damage, damage or wear is 0.010 inch
(0.25 mm).

H. PLATE. RETAINER
(Item 200)

(1) Visually inspect the plate None allowed. None. Replace the plate.
for corrosion, wear, or
damage.

510
61-10-17
 PROPELLER MAIMTENANCE ~ANUAL
RT Z E L L 1170

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

I. WEIGHT Coating to have 90 percent (90%) None. Replace the weight.

(Item 190) coverage. Coating may be
(Refer to Figure 503) completely worn away at edges
and corners. The maximum depth
(1) Visually inspecttheweight of damage for wear areas (dashed
for corrosion, wear, or lines) indicated in Figure 503 is
damage. 0.003 inch (0.08 mm).

APS6243A
APS6244A
APS6245

Areas of
allowable
wear.
A-1590 Weight

0.363 0.005 inch 0.486 0.003 inch

(9.22 0.13 mm) Areas of (12.34 0.08 mm)
allowable
wear.

C,\

B-317 B-318
B-317 and B-318 Weights

Weight Identification
Figure 503

511
CHECK 61-10-17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

J. SPRING. FEATHERING
(CYLINDER~
(Item 230)

(1) Visually inspectthe Maximum allowable depth of None. Replace the spring.
feathering spring for wear, damage is 0.005 inch (0.13 mm).
polish marks, or other
damage.

K. BRACKET, HIGH PITCH

STOP
(Item 240)

(1) Visually inspect the bracket Maximum allowable depth of Replace the bracket if corrosion,
for corrosion, wear, or damage is 0.010 inch (0.25 mm). wear, or damage exceeds the
damage. allowable depth of damage
Damage must not push
up
material above the normal Pushed up material on the
bracket surface that mates with referenced mating surfaces may
the cylinder (70) and washer be spot polished. Chromate
(250). Conversion coat the aluminum
surface where anodize has been
No damage is allowed on the removed through polishing.
washer (25) mating surface.
None. Replace the bracket.

(2) Visually inspectthe internal One-half damaged thread is None. Replace the bracket.
threads for damage. allowed.

L. HIGH PITCH STOP SLEEVE

(Item 320)

(1) Visually inspect the OD of The maximum depth of damage Smooth out damaged area.
the high pitch stop sleeve is 0.005 inch (0.13 mm). Replace if beyondserviceable
for wear, nicks, scratches, limits.
or other damage that would

affect fit or performance.

(2) Visually inspectthe Except for a few scratches and Replate and bake the high pitch
cadmium plate on the corners with cadmium plate stop sleeve in accordance with
surface of the high pitch missing, complete coverage is Hartzell Standard Practices
stop sleeve. required. Manual 202A (61-01-02),
Chapter 1500, Cadmium
Replating.

512
CHECK 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1170

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

M. WASHER
(Item 250)
(Figure 504)

(1) Identify the washer part If A-i 596 washer is present, None. Replace the washer.
number, refer to Figure replace with A-3744 washer.
504.

(2) Visually inspect the washer None allowed. None. Replace the washer.
for corrosion, wear, or

damage.

(3) Visually inspectthe Cadmium plate must completely Replate and bake the washer in
cadmium plate on the cover the washer. accordance with Hartzell
surface of the washer. Standard Practices Manual 202A
(61-01-02), Chapter 1500,
Cadmium Replating.

APS6247
APS6248

O 2.320 0.005 inch

O
(58.93 0.13 mm)

00´ ´•0´•
O/II I \\O

A-1596 Washer
A-3744 Washer
(obsolete replace at overhaul
with A-3744)

Washer Identification
Figure 504

513
CHECK 61 -1 0’1 7 Rev
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

APS6231
PISTON.XLS

"E"

B-3239
Piston Chamfer

71´•
"D" 1 0.052 0.09 inch
(1.32 2.4 mm)

15 degrees

f T
"B" "A"

If
Nut contact
su rface.

"A" "B" "C" "D" "E"

Part
Minimum Maximum Maximum Minimum Max. Surface
Number
Piston OD Bore ID O-ring ID O-ring Width Micro Finish

8-3237 4.746inch 0.739inch 0.982inch 0.146inch 16

(120.55 mm) (18.77 mm) (24.94 mm) (3.71 mm)

8-3239 5.246 inch 0.739 inch 0.982 inch 0.146 inch 16

(133.25 mm) (18.77 mm) (24.94 mm) (3.71 mm)

8-3683 4.746inch 0.739inch 0.982inch 0.146inch 16

(120.55 mm) (18.77 mm) (24.94 mm) (3.71 mm)

Piston Dimensional Inspection Criteria

Figure 505

514
CHECK 61’10’17 Rev. 4 Mayi9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

N. PISTON
(Item 350)
(Refer to Figure 505)

(1) Visually inspect the The maximum allowable depth of None. Replace the piston.
anodized surfaces of the damage is 0.005 inch (0.13 mm).
piston (that are not
referenced below or in
Figure 505), for wear,
nicks, scratches, or other
damage.

(2) Visually inspect the piston Anodize must be present on all None. Replace the piston.
OD for corrosion, wear, OD surfaces. The maximum
damage and anodize allowable damage is 0.030 inch
coverage. (0.08 mm) diameter with a depth
of 0.002 (0.51 mm). Damage
must not penetrate the anodize.
No pushed-up material is
allowed

(3) Visually inspect the piston If thepiston shows wear, None. Replace the piston.
areas "A", "B", "C", and dimensionally inspect. Pistons
"E". with dimensions exceeding the
limits in
Figure 505 must be
replaced.

(4) Visually inspect the nut Maximum allowable depth of None. Replace the piston.
contact surface for damage is 0.007 inch(0.18 mm).
corrosion, wear, or If damage is present,
damage. dimensionally inspect area "D".

(5) Visually inspect the C-3239 None. If the chamfer is not present,
piston for chamfer. machine chamfer in accordance
with chamfer dimensions in
Figure 505. Chromate
Conversion coat the aluminum
surface where the anodize has
been removed through
machining.

(6) Penetrant inspect the No relevant indications allowed. None. Replace the piston.
piston.
NOTE: Do not remove

the Hard Anodize.

515
61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

APS8282
APS6282A
APS6282B

Oil Hole wall (thin wall)

Oil Hole

IICII IIBII "A"

"D"

No repair is allowed at the smallest

diameter of the taper or within 0.093 inch
(2.36 mm).

-I’-Smallest diameter of the

0.093 inch (2.36 mm)

taper

One-Piece Pitch Change Rod

Figure 506

516
cneca 61-10-17
 PROPELLER MAINTENANCE MANUAL
HP~ RT Z E L L 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

O. PITCH CHANGE ROD

(Item 370)
(Refer to Figure 506)

(1) Visually inspect the chrome Any area worn below the chrome None. Replace the pitch change
plating of the pitch change plating is cause for replacement, rod.
rod for damage.

(2) Visually inspect the One damaged thread is allowed. None. Replace the pitch change
external threads for rod.
damage.

(3) Visually inspect the oil No foreign material is allowed. Remove all foreign material.
supply bore using a
borescope or fiberoptic
flashlight.

(4) Dimensionally inspect area Minimum allowable diameter is None. Replace the pitch change
"B" of the pitch change rod. 0.732 inch (18.59 mm). rod.

1 (5) Dimensionally inspect area Minimum allowable diameter is None. Replace the pitch change
"A" of the pitch change rod. 0.662 inch (16.82 mm). rod.

1 (6) Visually inspect the taper No corrosion, wear, or damage is Replace the pitch change rod if
area "D" for corrosion, allowed at the smallest diameter corrosion, wear, or damage is
wear, and damage. of the taper or within 0.093 inch beyond serviceable limits.
(2.36 mm) of the thread. If damage causes high spots
Remaining taper surface may above the existing surface,
have a maximum damage depth remove only the high spots.

of 0.004 inch (0.10 mm) over 10

percent (10%) of the surface
area.

(7) Visually inspect the pitch No bend is allowed. None. Replace the pitch change
change rod for rod.
straightness.

1 (8) Dimensionally inspect area Minimum allowable diameter is None. Replace the pitch change
"C" of the pitch change rod. 0.732 inch (18.59 mm). rod.

1 (9) Magnetic particle inspect No relevant indications allowed. None. Replace the pitch change
the pitch change rod. rod.
NOTE: Do not strip the
chrome plating.

517
cnEcK 61 -1 0-17 Rev. 6 Apr/GOPage
 PROPELLER
HARTZELL MA~PINCE
D711LAUN~PM

W10398
W10399

Oil Hole

Oil Hole Wall Tube Wall

(thick wall) (thin wall)

Roll Pin 8-6378-0375

No space is
allowed between
the shoulder and Pitch Change
0.47 inch th, tube Rod Shoulder
(11.9 mm)

Oil Hole

Two Pieces Two Pieces

Misaligned Aligned

Two-Piece 8-2491 Pitch Change Rod

Figure 506.1

517.1
CHECK ~1’10-17
 PROPELLER MAINTENANCE MANUAL
HP~ RT Z E L L 1170

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

O. PITCH CHANGE RODcont’d

Additionalinspection
requirements for the two-piece
B-2491-() ONLY.
(Item 370)
(Refer to Figure 506.1)
NOTE: Identify the pitch change rod to determine if the additional inspection requirements for the
two-piece pitch change rod are applicable. Look into the oil hole to determine if the pitch
change rod is of one-piece or two-piece construction. A one-piece pitch change rod will have
a thin tube wall the entire length of the tube. The two-piece pitch change rod will have both a

thick oil hole wall and a thin tube wall along the length of the tube. Refer to Figures 506 and
506.1.

(1) Visually inspect for indexing No space between the shoulder None. Discard the pitch change
(movement) between the and the tube and no misalignment rod.
two pieces where they are of the oil hole between the two
joined. pieces are allowed.

(2) Visually inspect forthe One roll pin must be present. Install a roll pin. Refer to the
presence of a roll pin Repair chapter of this manual for
approximately 180 degrees instructions to install the roll pin.
away from the oil hole.

517.2
CHECK el-lo-17
 PROPELLER
HA RTZ E L L MA:N:7EDNANCE MANUAL

(This page is intentionally blank.)

I cnEcK 61-10-17 Page 518

Rev. 6
Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

P. FORK
(Item 400)

(1) Visually inspect the Maximum allowable depth of Damage must be repaired. Refer
cadmium plating of the fork damage is 0.003 inch (0.08 mm). to the Chapter 600, Repair in
this manual for general repair
(excluding the slots,
threaded bore and tapered procedures of steel parts. Some
section of the bore) for surfaces may appear rough tin

scratches, or other the "as forged" condition),

wear,
rework of such surfaces is not
damage.
required.

If repaired, replate the fork and

bake in accordance with Hartzell
Standard Practices Manual
202A, Chapter 1500, Cadmium
Replating.

One thread is allowed. None. Replace the fork.

(2) Visually inspect the damaged
threaded portion of the fork
bore for damage.

None. Replace the fork.

(3) Visually inspect the tapered Maximum allowable depth of
portion of the fork bore for damage is 0.003 inch (0.08 mm).
wear, nicks, fretting or other
damage.

None. Replace the fork.

(4) Visually inspect the fork Maximum allowable depth of
slots for damage. damage is 0.006 inch (0.15 mm).

No relevant indications allowed. None. Replace the fork.

(5) Magnetic particle inspect
the fork.
NOTE: It is not necessa~y
to strip the fork
before magnetic
particle inspection.

519
CHECK Bi ’1 0’1 7 Rev. 4 May/9 Page
 PROPELLER
HARTZELL D711LAUNAI I

APS2058
BLOCK.XLS

1 1- Z

Diameter

XI:\\

1 Y F Dash
Number

Part Number "X" Minimum "Y" Minimum "2" Minimum Hole Diameter Maximu

A-2217-1 Not a wear surface, no 1.011 inch 0.905 inch 0.6250 inch
measurement required 1 (25.67 mm) (22.98 mm) (15.875 mm)

A-2217-2 Not a wear surface, no 1.009 inch 0.905 inch 0.6250 inch
measurement required (25.62 mm) (22.98 mm) (15.875 mm)

A-2217-3 0.870inch 0.870inch 0.905inch 0.6890inch

(22.09 mm) (22.09 mm) (22.98 mm) (17.500 mm)

A-2217-4 1 0.870 inch 0.870 inch 0.905 inch 0.6250 inch

(22.09 mm) (22.09 mm) (22.98 mm) (15.875 mm)

A-3253 0.871 inch Not a wear surface, no 0.745 inch 0.6250 inch
(22.12 mm) measurement required (18.92 mm) (15.875 mm)

A-3253-1 0.869 inch Not a wear surface, no 0.745 inch 0.6250 inch
(22.07 mm) measurement required (18.92 mm) (15.875 mm)

A-3253-2 0.869 inch Not a wear surface, no 0.745 inch 0.6890 inch
(22.07 mm) measurement required (18.92 mm) (17.500 mm)

A-3253-3 0.874 inch Not a wear surface, no 0.745 inch 0.6890 inch
(22.19 mm) measurement required (18.92 mm) (17.500 mm)

Pitch Change Block Identification/Dimensional Criteria

Figure 507

520
CHECK 61-10-17 Rev. 7 Apr/OtPage
 PROPELLER MAINTENANCE MANUAL
HA,RTZ ELL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

Q. PITCH CHANGE BLOCK

(Item 440)
(Refer to Figure 507)

(1) Visually inspect the pitch Maximum allowable depth of None. Replace the pitch change
change block for damage. damage is 0.005 inch (0.13 mm). block.

(2) Visually inspect the pitch If thepitch change block shows None. Replace the pitch change
change block for wear. wear, dimensionally inspect block.
according to Figure 507.

(3) Magneticparticle inspect No relevant indications allowed. None. Replace the pitch change
the pitch change block. block.

NOTE: To identify the pitch change blocks, refer to Figure 507.

NOTE: The pitch change knob hole in the pitch change knob block is offset from the block center.
Pitch change blocks should be installed in the fork with the thin wall toward the engine-
side hub half during initial assembly.
R. HUBUNIT
(Item 480)

Perform the inspection of the hub in accordance with Hartzell Standard Practices Manual
202A (51-01-02), Chapter 1300, Aluminum Hub Overhaul.

S. SPACER
(Item 520)

(1) Visually inspect the spacer Maximum allowable depth of None. Replace the spacer.
for corrosion, wear, or damage is 0.005 inch (0.13 mm).
damage.

(2) Visually inspect the spacer A maximum of 0.5 square inch None. Replace the spacer.
for Hard Anodize (3 square cm) missing is allowed
coverage. on external surfaces.

521
CHECK 61 -1 0-1 7 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

T. SPRINGGUIDE
(Item 530)

(1) Visually inspect the spring Maximum allowable depth of None. Replace the spring guide.
guide for wear or damage. damage is 0.020 inch (0.51 mm).

(2) Visually inspect the spring If the bore is worn, dimensionally None. Replace the spring guide.
guide bore for wear. inspect. Maximum allowable
bore ID is 0.677 inch (17.20
mm),

U. SPRING, FEATHERING
(HUB~
(Item 540)

(1) Visually inspect the Maximum allowable depth of None. Replace the spring.
feathering spring for wear, damage is 0.003 inch(0.08 mm).
polish marks, or other
damage.

V. SPRING, FEATHERING
IHUB~
(Item 550)

(1) Visually inspect the Maximum allowable depth of None. Replace the spring.
feathering spring for wear, damage allowed is 0.003 inch
polish marks, or other (0.08 mm).
damage.

CHECK fj1’10-17 Rev. 4 May/9 Page 522

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

W. SPRING RETAINER
(Item 560)

(1) Visually inspect the spring Maximum allowable depth of None. Replace the spring
retainer for corrosion, damage allowed is 0.003 inch retainer.
wear, or damage. (0.08 mm).

(2) Visually inspect the bore If the bore is damaged,

worn or None. Replace the spring
that encircles the keeper dimensionally inspect. Maximum retainer.
(570). allowable bore ID is 0.775 inch
(19.69 mm).

(3) Visually inspect the If the bore is damaged,

worn or None. Replace the spring
smallest bore that pilots dimensionally inspect. Maximum retainer.
the pitch change rod (370) allowable small bore ID is 0.672
inch (17.07 mm).

(4) Visually inspect the Cadmium plate must completely Replate and bake the spring
cadmium plate coverage cover the spring retainer, retainer in accordance with
on the spring retainer. Hartzell Standard Practices
Manual 202A (61-01-02),
Chapter 1500, Cadmium
Replating.

X. HUB BOLT INSPECTION

(Items 580, 590)
Hub bolts used to bolt the hub halves together may be reused when they are inspected in
accordance with the following procedure. Bolts used to attach hub extensions must be replaced
at overhaul. The following bolts may be inspected, re-plated as necessary, and re-used during
overhaul: A-1584, A-3203, A-3219-1, A-2431, A-2432, and A-2433.

(1) Visually inspect each bolt. Corrosion, scoring, thread None. Replace the bolt.
damage, or any other defects
are unacceptable.

(2) Magnetic particle inspect No relevant indications allowed. None. Replace the bolt.
each bolt.
NOTE: It is not necessary
to strip the bolt
before magnetic
particle inspection.

(3) Visually inspect the Cadmium plate must completely Replate the bolt in accordance
cadmium plate coverage cover the hub bolt, with Hartzell Standard Practices
on the bolt. Manual 202A (61-01-02),
Chapter 1500, Cadmium
Replating.

523
CHECK 61 ’1 0’1 7 Rev. 4 May/9 Page
 PROPELLER
HARTZ ELL MA:N1:EDNANCE
D711L*UNAM

APS6285
PLUG.XLS

Removal feature

"C"
1 "A"
f r
i,,D"

Part "A" "B" "C" "D"

Number Minimum O-ring Maximum O-ring Minimum Plug Maximum Bore
Groove OD Groove ID OD OD

A-2481 2.015 inch 0.846 inch 2.246 inch 0.670 inch

(51.18 mm) (21.49 mm) (57.05 mm) (17.02 mm)
A-2481-1 2.326inch 0.846inch 2.557inch 0.670inch
(59.08 mm) (21.49 mm) (64.95 mm) (17.02 mm)
A-2481-3 2.015inch 0.846inch 2.246inch 0.670inch
(51.18 mm) (21.49 mm) (57.05 mm) (17.02 mm)

Shaft Plug
Figure 508

CHECK ~1110-17 Rev. 4 May/9 Page 524

 PROPELLER MAINTENANCE MANUAL
H RT Z c L L 1170

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

Y. PLUG.SHAFT
(Item 660)
(Refer to Figure 508)

(1) Visually inspect the shaft None allowed. None. Replace the shaft plug.
plug for corrosion.

(2) Visually inspectthe O-ring If the shaft plug is worn or None. Replace the shaft plug.
groove OD ("A"). damaged, dimensionally inspect.
Shaft plugs with dimensions
exceeding the limits in Figure
508 must be replaced.

(3) Visually inspect the O-ring If the shaft plug is worn or None. Replace the shaft plug.
groove ID ("B"). damaged, dimensionally inspect.
Shaft plugs with dimensions
exceeding the limits in Figure
508 must be replaced.

(4) Visually inspect the shaft If the shaft plug is worn or None. Replace the shaft plug.
plug OD diameter ("C"). damaged, dimensionally inspect.
Shaft plugs with dimensions
exceeding the limits in Figure
508 must be replaced.

(5) Visually inspect the ID of If the shaft plug is worn or None. Replace the shaft plug.
the shaft plug bore ("D"). damaged, dimensionally inspect.
Shaft plugs with dimensions
exceeding the limits in Figure
508 must be replaced.

525
CHECK 61’10’1 7 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

Z. HEXHEAD SPACERTUBE
(Item 910)
(Refer to Figure 752)

(1) Visually inspect the spacer None allowed. None. Replace the spacer tube.
tube for corrosion, wear, or

damage.

AA. DAMPER WEIGHT

(Item 950)

(1) Visually inspectthe damper None allowed on the friction disc None. Replace the damper
weight for corrosion. mating surface or on fiber weight.
washer mating surface at eight
(8) places.

(2) Visually inspect the damper None allowed on the friction disc None. Replace the damper
weight for damage in the mating surface or on fiber weight.
form of nicks and/or washer mating surface at eight
gouges. (8) places. On all other surfaces
the maximum allowable depth of
damage of 0.005 inch (0.13 mm).

(3) Visually inspectthe None allowed. None. Replace the damper

damper weight for wear weight.
caused by the eight (8)
fiber washers.

(4) Visually inspect the damper Cadmium plate must completely Replate damper weight in
weight for cadmium plate cover the damper weight. accordance with Hartzell
coverage. Standard Practices Manual 202A
(61-01-02), Chapter 1500,
Cadmium Replating.

(5) Dimensionally inspectthe Minimum thickness from the None. Replace the damper
damper weight for wear friction disc
mating surface to weight.
caused by the friction disc. the opposite surface is 0.396
inch (10.06 mm).

526
cnEcK 61-10-17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
RTZ E LL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

AB. SUPPORT PLATE

(Item 980)

(1) Visually inspect the plate None allowed. None. Replace the support plate.
for corrosion, wear, or
damage on the friction disc
(970) mating surface.

(2) Visually inspect the plate Maximum allowable depth of None. Replace the support plate.
for corrosion, wear, or damage is 0.005 inch (0.13 mm).
damage on the remaining
surfaces.

(3) Magnetic particle inspect No relevant indications allowed. None. Replace the support plate.
the plate.
NOTE: It is not necessary
to strip the plate
before magnetic
particle inspection.

(4) Visually inspect the plate Cadmium plate must completely Replate the support plate in
for cadmium plate cover the plate. accordance with Hartzell
coverage. Standard Practices Manual 202A
(61-01-02), Chapter 1500,
Cadmium Replating. Baking is
not required.

527
CHECK 61’10’1 7 Rev. 4 May/9 Page
 PROPELLER
HARTZELL MA:Nlr~NANCE

APS6068a
APS6069
5016
5017

~u:
Iiameter
Outer

i"’
No fretting, allowed

i Radial in this
(dashed-lines).
area

Idiameter
Outer

Blade Split Bearing

Figure 509

528
CHECI( 61-10-17
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

AC. BLADE BEARING RACE

(Item 3020, 3050)
(Refer to Figure 509)

(1) Visually inspect the ball bearing groove shows

If the ball None. Replace the retention

bearing groove for damage, wear,dimensionally inspect. bearing race.

Maximum allowable depth of
damage is 0.005 inch (0.13 mm).

(2) Visually inspect the outer Fretting damage allowed. Must Using a Scotch Brite" pad or
diameter of the bearing not affecttight fit with the guide equivalent, clean the area
race for fretting damage, ring. throughly to minimize fretting
damage.

If the guide ring is not tight. None. Replace the bearing race.

No relevant indications allowed. None. Replace the retention

(3) Magnetic particle inspect
the bearing race. bearing race.

529
61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

APS6283
APS6284

4.810 inch (122.18 mm)

Minimum Lip Diameter

Preload Plate 0.060 inch

Threads (1.53 mm)
Minimum
Lip Thickness

Inner Blade Bore Bearing Race

1.249 inch
(31.73 mm)
Minimum
Diameter

Preload Plate
Figure 510

530
cnEcK 61-10-17 Rev. 6 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
H~ RTZ E L L 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

AD. RING. BEARING RACE

RETENTION
(Item 3060)

(1) Visually inspect the ring for depth of damage

No visible Clean with a Scotch Brite" pad to
corrosion, wear, or fretting. when compared to adjacent, remove any evidence of fretting.
undamaged surface.

Plating must be all Replate the ring in accordance

(2) Visually inspect the ring for present on

cadmium plating coveragei surfaces. with Hartzell Standard Practices

Manual 202A (61-01-02),
Chapter 1500, Cadmium
Replating.
AE. PRELOAD PLATE
(Item 3080)
(Refer to Figure 510)

(1) Visually inspect the internal Two (2) damaged threads are

threads for damage. allowed. None. Replace the preload

plate.
(2) Dimensionally inspectthe Minimum allowable diameter is
OD of the inner blade bore 1.249 inch (31.73 mm). None. Replace the inner blade
bearing race. bore bearing race using gear
puller TE98.
NOTE: Inner blade bore bearing race (3090) removal at overhaul is required only if the
bearing is beyond serviceable limits.

(3) Visually inspect the inner False brinelling with no depth is None. Replace the inner blade
blade bore bearing race allowed. Brinelling with any bore bearing race using gear
(3090) OD for brinelling. depth is not allowed, puller TE98.

(4) Visually inspect the inner None allowed. None. Replace the inner blade
blade bore bearing race bore bearing race using gear
(3090) OD for corrosion or puller TE98.
damage.

(5) Visually inspectthe if the outboard "lip" is damaged, Clean with a Scotch Brite" pad to

outboard "lip" OD and dimensionally inspect. Minimum remove any evidence of fretting.

thickness. allowable lip thickness is 0.060 If beyond serviceable limits,

inch (1.52 mm). Minimum replace the preload plate.
allowable lip OD is 4.810 inch
(106.17 mm).

(6) Penetrant inspectthe No cracks are allowed. None. Replace the preload
preload plate. plate.

531
CHECK 61 -1 0’1 7 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

Component Inspection Criteria

Table 501

Inspect Serviceable Limits Corrective Action

AF. BALANCE WEIGHTS

(Items 5040, 5050)

(1) Visually inspect the weights Maximum allowable depth of Polish to a maximum depth of
for corrosion, wear, or damage is 0.003 inch (0.08 mm). 0.005 inch (0.13 mm). If beyond
damage, the serviceable limits or the
corrective action limits, replace
the balance weight.

(2) Visually inspect steel Except for a few scratches and Replate the weight in
weights for cadmium corners with cadmium plate accordance with Hartzell
plating coverage. missing, complete coverage is Standard Practices Manual 202A
required. (61-01-02), Chapter 1500,
Cadmium Replating.

(3) Visually inspect aluminum Except for a few scratches and Re-anodize the weight in
weights for anodize corners with anodize coating accordance with Hartzeli
coverage, missing, complete coverage is Standard Practices Manual 202A
required. (61-01-02), Chapter 1600,
Chromic Acid Anodizing.

CHECK 61-10-17 Rev. 4 May/9 Page 532

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

CONTENTS

1. General Repair Requirements 603

A. Shot Peening 603

B. Aluminum and Steel Parts 603

2. Blade Repair. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ´•´•. ´•´•´• 603

3. Hub Unit Repair 603

4. Spinner Assembly Repair 603

5. Specific Repair Requirements 604

A. Repair of Damaged Cylinder Wrench Attachment Holes. 604

B. Spinner Bulkhead Modification for Two-bladed Compact Propellers 605

C. Spinner Bulkhead Modification for Three-bladed Compact Propellers 611

D. Installation of a Roll Pin in the Two-piece B-2491 Pitch Change Rod......... 617

FIGURES

Installing the Reinforcing Brackets Figure 601 607

Two-bladed Propeller Bulkhead Cutout Dimensions Figure 602 608

Two-bladed Propeller Bulkhead Template Figure 603 609

Three-bladed Propeller Bulkhead Cutout Dimensions ...........Figure 604 614

Three-bladed Propeller Bulkhead Template Figure 605 615

Installing a Roll Pin in the Two-Piece Pitch Change Rod .......Figure 606 617

.,p,,,61-10-17
 PROPELLER
HA RTZ E L L MA:N:7EDNANCE MANUAL

(This page is intentionally blank.)

I REPAIR 61’10-17 Page 602

Rev. 7
Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

WARNING: DO NOT ATTEMPT IN THE FIELD ANY REPAIR, REPLACEMENT,

REWORK, REPLATING, RE-ANODIZING OR RE-SHOT PEENING
PROCEDURE NOT SPECIFICALLY AUTHORIZED BY HARTZELL
PROPELLER INC. OR NOT SPECIFICALLY REFERRED TO IN
HARTZELL MANUALS. CONTACT THE FACTORY FOR GUIDANCE
ABOUT THE AIRWORTHINESS OF ANY PART WITH UNUSUAL
WEAR OR DAMAGE.

1. General Repair Requirements

A. Shot Peening

CAUTION: THE PEENING MARKS ON CERTAIN PROPELLER PARTS ARE

NOT TOOL MARKS AND SHOULD NOT BE REMOVED.

Certain surfaces of propeller assembly parts have been shot peened at the
factory to improve fatigue strength.
Shot peened surfaces may need re-shot peening because of rust, corrosion,
fretting, or nicks. Refer to Hartzell Standard Practices Manual 202A (61-01-02),
Chapter 1400 for shot peening procedure. Re-shot peening must be done only
by Hartzell-approved facilities. A list of approved Facilities may be found in
Hartzell Standard Practices Manual 202A (61-01-02), Chapter 1900, Approved
Facilities.

B. Aluminum and Steel Parts

(1) Eliminate all evidence of scratches, nicks, burrs, and other minor damage
by using a fine emery cloth or Scotch Brite" pad. Be sure to blend the
polished area in with the surrounding area. Use extreme care to completely
remove the damage while removing as little material as possible.
(2) Make the part is still within tolerance after any type of repair. Refer to
sure

the Check Chapter and the Fits and Clearances Chapter of this manual.

2. Blade RePair

For aluminum blade repair, replacement, and rework instructions, refer to Hartzell
Manual 133C (61-13-33),

3. Hub Unit Repair

Refer to Hartzell Manual 202A (61-01-02), Chapter 1300, Aluminum Hub

Overhaul, for requirements and procedures for repairing aluminum hub units.

4. Spinner Assembly Repair

Refer to Hartzell Manual 127 (61-16-27), Spinner Assembly Maintenance

Instruction Guide, for requirements and procedures for repairing spinner
assemblies.

61-10-17
 PROPELLER MAINTENANCE MANUAL
HA,RTZ ELL 1170

5. Specific RePair Requirements

NOTE: Balance weight attachment hole and grease fitting hole repair procedures are

I described in the Aluminum Hub Overhaul chapter of Hartzell Manual

.)20-20-16(A202
A. Repair of Damaged Cylinder Wrench Attachment Holes.

(1) General.

(a) Several models of aluminum hub propellers have threaded holes in the
forward end of the propeller cylinder for attachment of wrenches during
assembly and disassembly. Damage to these holes is repairable in
accordance with the following procedure.

(b) Perform the procedure only on cylinders with the following part
numbers:

8-2423-1 8-2452-1

(2) Procedure

(a) Use Slimsert TE410 (Hartzell P/N 8-6986-258). Cut off the
counterbored end of the Slimsert to remove the counterbore and
locking teeth.

(b) Drill the damaged hole to diameter 0.281 +0.004 -0.001 inch (7.13 +0.101
-0.025 mm) with a maximum depth of 0.440 inch (11.17 mm) at the corner
of the hole. Make sure that the drill is centered and square with the hole.

(c) Inspect the wall thickness under the point of the hole in accordance with
the Check chapter in this manual.

(d) Thread the hole to 5/16-24UNF-3B using a bottom tap.

NOTE: The resultant thread will be non-standard due to the larger than
normal minor diameter of 0.280 0.285 inch (7.11 7.23 mm)
produced by the previous drill operation.
(e) Chemical conversion coat the ta0pped hole. Refer to the Chromic Acid
Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02),
(f) Spray the Slimsert OD and the tapped hole with primer CM127.
(g) Coat the Slimsert OD with thread locking compound CM74.
(h) Install the modified Slimsert flush to 0.020 inch (0.51 mm) below the part
surface, using installation tool TE314.
NOTE: Step drill,
reamer, and swage tool are not required, because the
counterbored end is cut off.

(i) Check the installed Slimsert using a 1/4-28 UNF-3A bolt.

(j) Allow the repaired parts to cure for 12 hours before assembly.

REPPIIR 61-10-17 RevP7aBAepi~:

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

I B. Spinner Bulkhead Modification for T~o-bladed Compact Propellers

Since April, 1997, Hartzell Propeller has been producing an improved two bladed
compact propeller hub that incorporates a modification designed to improve the
reliability of the fillet area of the hub. The improved style hub has considerable
material added to the forging in the blade retention area. Hartzell no longer
manufactures the earlier style hub.

NOTE: The improved style hub is identifiable by different part number (refer to
a

the Illustrated Parts List) and the suffix letter "B" at the end of the hub
serial number and the propeller serial number. It is are also visibly
different from previous hubs due to material added to the forging in the
blade retention area.

Thischange necessitates modification of spinner bulkheads to provide clearance

when replacing an earlier style hub a with an improved style hub. Previously
manufactured bulkheads for the spinner assemblies will need to be modified to
properly fit the improved style compact hub. Bulkhead modifications are only
necessary when installing an improved style hub.
Installation of an earlier style spinner bulkhead on an improved style hub
requires bulkhead modification, except for spinner bulkheads mounted to starter
ring gears, that are not affected by these instructions. The modification may be
done in accordance with the procedures given below. A list of affected spinner
bulkhead part numbers is given for each procedure. Operators with non-Hartzell
spinners should consult the appropriate type certificate holder for modification
instructions.

(1) ProcedureA
I
(a) The procedures given in Procedure A are for two-bladed propeller
spinner bulkheads that already have reinforcing brackets installed from
the factory. The modification will remove material from the bulkhead
and brackets to allow clearance for new style hubs.

I All two-bladed compact spinner bulkhead P/N’s are listed below:

0-2283-1 0-2283-2 C-2283-2P 0-2283-4 0-2283-5

0-2283-6 0-2294 0-2294-2 C-2294-3P 0-2299-1
C-2299-2P 0-2469 0-2469-1 C-2469-1L 0-2472-1
0-2472-2 0-3228 0-3283-1 0-3283-2 0-3295
0-3534 0-3534-1 0-3569 0-4567 D-4534
D-4812 D-4825 D-5258 D-5751 D-5751-1
D-5751-1L

605
REPAIR 61’1 0’17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(b) Remove material from the bulkhead to provide clearance for the new

style hub. Make cutouts in accordance with the dimensions given in

Figure 602.
1 Fabricate a template to match the broken lines in Figure 603.

CAUILON: CHECK THE DIMENSIONS OF THE TEMPLATE

BEFORE CUTTING THE BULKHEAD.

2 Align the holes in the template with the mounting holes on the
bulkhead

3 Mark the areas to be removed.

4 Remove material using a mill, nibbler, grinder, or other appropriate

tooling.

NOTE: For best results, remove material using a milling machine.

5 Remove all burrs and rough edges.

6 Inspect the cutout for the proper dimensions. Bulkhead must be
retired from service if the dimensions are exceeded.

7 Apply zinc-chromate primer to the exposed edge of the steel

reinforcing brackets.
8 Vibra etch a "B" after the serial number on the bulkhead.

0 Install the spinner bulkhead to propeller hub.

(2) Procedure B

(a) The steps in Procedure B are for bulkheads that do not have
reinforcing brackets installed at the factory. Brackets must be installed
on these bulkheads, to provide additional structural support, before
material is removed.

Two way compact spinner bulkhead part numbers are listed below:

C-2472

NOTE: Bulkhead reinforcing bracket part number A-3263-3 (qty 4 per

bulkhead) is required to accomplish this procedure.

61-10-17
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 117D

(b) Install reinforcing brackets on the bulkhead.

NOTE: It is critical that reinforcing brackets be installed flush with the

contour of the bulkhead. It may be necessary to bend the
brackets slightly forproper fit. (See Figure 601.) Use hub bolts
or a suitable alternate to hold the template in place on the
bulkhead.

1 Ream the hub bolt mounting hole in the bracket to 0.404 0.413
inches (10.26 -10.49 mm).

2 Ream the bracket rivet holes (4 per bracket) using a #30 twist drill.
Deburr all the holes.

NOTE: Cured structural adhesive may prevent the bracket from

lying flush on the bulkhead. Remove excess adhesive
using 120 grit sandpaper.

APS6249

A-3263-3
Bracket Rivets

Flush fit between

A-3263-3 bracket and bulkhead

Installing the Reinforcing Brackets

Figure 601
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

3 Place reinforcing bracket on the engine side of the spinner

a

bulkhead. Align the mounting holes and clamp the bracket in

place, ensuring that the bracket is flush with the bulkhead surface.
4 Using a #30 twist drill, drill rivet holes (4 per bracket) through the
bulkhead, using the rivet holes in the bracket as a template.
Deburr all the holes.

NOTE: Relocate, or record in the

book any bulkhead part
log
number that may be covered by a reinforcing bracket.

5 Install the bracket using AN 470 AD 4-7(MS20470AD4-7) rivets.

Rivet in accordance with aircraft standard practices.

6 Complete steps 5.B.(2)(b)l through 5.B.(2)(b)5 for the remaining

brackets.

NOTE: Installation of the bulkhead reinforcing brackets will not

require a longer hub mounting bolt.
(c) Comply with the steps outlined in Procedure A.

61-10-17
 PROPELLER MAINTENANCE MANUAL
HP~ RT Z E L L 117D

APS6250

2X R 0.5973~0.010’1
7.54~0.25 mm)

?‘~J I I

Po
0.250~0.010 inch
(6.35~0.25 mm

2X 3.264~0.010 inch 4X IR 0.250~0.010 inch

(82.91rt0.25 mm) (6.35~0.25 mm)

I-’ 398~0.010 inch

b o .11’0.25
’I" O
mm

4X 0.406 +0.007/-0.002 inch

(10.31+0.18/-0.05 mm)

Two-bladed Propeller Bulkhead Cutout Dimensions

Figure 602

609
REPAIR 61’1 0’17
 PROPELLER
HA RTZ E L L MA:NI~E$JANCE
D711LAUNAM

APS6251

/I

Two-bladed Propeller Bulkhead Template

Figure 603

610
REPAIR 61’10’17
 PROPELLER MAINTENANCE MANUAL
H~ RT Z E L L 1170

C. Spinner Bulkhead Modification for Three Bladed Compact Propellers

(1) Reason

(a) HartzellPropeller has begun production of an improved three-bladed

compact propeller hub. The improved style hub will incorporate a
modification designed to improve the reliability of the fillet area of the
hub.

(b) Previously manufactured hubs will no longer be available; only

improved style hubs will be available from Hartzell.

NOTE: The improved style hub is identifiable by a different part number

(refer to the Illustrated Parts List) and the suffix letter "B" at the
end of the hub serial number and the propeller serial number. It
is are also visibly different from previous hubs due to material
added to the forging in the blade retention area.

(c) The improved style hub has considerable material added to the forging in
the blade retention area. change necessitates modification or
This
replacement of currently installed spinner bulkheads to provide clearance
when replacing a previous style hub with an improved style hub.

(d) Previously effectivity will need to

manufactured bulkheads listed in the
be modified or replaced to properly fit the improved style compact hub.
Bulkhead modifications or replacement are only necessary for hub
mounted bulkheads installed on the new style hub.

(2) Material Introduced for New Spinner Bulkheads

(a) Spinner bulkheads with part numbers listed in the table below may be
modified to be installed on the improved hub.

Spinner Previous Modified Spinner Previous Modified

Bulkhead P/N Bulkhead P/N Bulkhead P/N Bulkhead P/N
C-3565 C-3566(P) C-3566-6(P) D-1649 D-1648(P) D-1648-1(P)
C-3567 C-3566-1(P) C-3566-7(P) D-3273 C-3267(P) C-3267-4(P)
C-3567-1(L) C-3566-1(P) C-3566-7(P) D-3273-1(L) C-3267-1(P) C-3267-5(P)
C-3567-2 C-3566-2(P) C-3566-8(P) D-3273-2 C-3267-2(P) C-3267-6(P)
C-3567-4 C-3566-4(P) C-3566-10(P) D-4247 C-3566-3(P) C-3566-9(P)
C-3567-5(L) C-3566-5(P) C-3566-11(P) D-4578 D-4581(P) D-4581-1(P)
C-3567-6(L) C-3566-4(P) C-3566-10(P) D-4841 D-4877(P) 0-4877-1(P)
C-4558 D-4561(P) D-4561-4(P) D-4841-1 C-3566-4(P) C-3566-10(P)
C-4558-1 D-4561-1(P) D-4561-5(P) D-5205 D-4561-3(P) D-4561 -7(P)
C-4558-2 D-4561-2(P) D-4561-6(P) D-5489 D-5491(P) D-5491-1(P)
C-4558-3 D-4561-3(P) D-4561-7(P)

NOTE: Newly purchased spinner assemblies will include a spinner bulkhead

that may be used with either the improved or previous style propeller
hub.

,,,,,sl-1 0-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

(3) Accomplishment Instructions

NOTE: Propeller hub changes may only be performed by a FAA approved,

or foreign equivalent, propeller repair facility. Spinner bulkhead

modifications may be performed by a certificated mechanic.

(a) Install improved style propeller

an hub in accordance with the
Assembly chapter of this manual.
1 Install hydraulic components (if required) in accordance with
new

the Assembly chapter of this manual. Refer to the section, Three-

bladed Propeller Improvements, in the Illustrated Parts List
chapter of this manual.
(b) Replace the
spinner bulkhead and spinner assembly (if required) in
accordance with the Installation and Removal
chapter of Hartzell
Owner’s Manual 115N (61-00-15) or Manual 145 (61-00-45).

(c) The modification of a three-bladed propeller spinner bulkhead may be

done in accordance with the procedure given below:

NOTE: A spinner bulkhead that is mounted on a starter ring gear is not

affected by these instructions. Operators with non-Hartzell
spinners should consult the appropriate type certificate holder
for modification instructions.

1 Remove material from the bulkhead to provide clearance for the

improved style hub. Modify the bulkhead in accordance with the
dimensions given in Figure 604.

NOTE: For best results, remove material using a milling machine.

2 Fabricate a template to match the solid lines in Figure 605.

CAUTION: CHECK THE DIMENSIONS OF THE TEMPLATE

BEFORE CUTTING THE BULKHEAD.

3 Align the holes in the template over the mounting holes on the
bulkhead.

4 Use hub bolts or a suitable alternate to hold the template in place

on the bulkhead.

5 Mark the areas to be removed.

6 Remove material using a mill, nibbler, grinder, or other appropriate

tooling.

RIPPIIR 61’10’17
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 1170

7 Remove all tool raarst burrs, and rough edges.

8 Inspect the cutout for proper dimensions. (Refer to Figure 604 and
Figure 605.) The bulkhead must be retired from service if the
dimensions are exceeded.

9 Apply zinc-chromate primer CM67 to the exposed edge of the

steel reinforcing brackets.

10 Vibra etch a "B" after the serial number on the bulkhead.

613
REPAIR 61 ’1 0’1 7
 PROPELLER
HA RTZ E LL MA:N:7EDNANCE
D711LAUNAM

W10408

DUDE Q

X 0.597~0.010inch
(15.16rt0.25 mm)

3X 3.26 ~0.010 inch

(82.8~0.25 mm)
If~a2_alcl

j
34

suar Q
DUDE E

Paint the exposed surfaces with Zinc Chromate Primer CM67

Three-bladed Propeller Bulkhead Modification Dimensions

Figure 604

614
REPAIR 61’10’17 RevP7aSdbr~f/Page
 N
BLADE m
s I
(p I
;r

4X R 0.250 ~0.030 inch I I

(6.35~0.76 mm) h 1 0.597 +0.010 inch

;j (15.16~0.25mm)
\I I I I F
m
I 1 I a
_

n’ I \I I 1 I 1 3
,03 e
,e z
I
=r pm
~cD
09,
via

g
a o I I I I I I I
a

c
o
a
3.2610.010 inch
Q) I

I I (82.8~0.25 mm)
--I
(_1.020/CI
IL3
I, 1
I 4.060 ~0.005 inch --c)-l C
I I (103.12rt0.12 mm)

g~D
 PROPELLER
HA RTZ E L L MA:N;T7EONANCE MANUAL

(This page is intentionally blank.)

I 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

D. Installation of a Roll Pin in the Two-Piece B-2491-() Pitch Change Rod

(1) General

This procedure only for the two piece B-2491-( pitch change
is used rod.
Refer to the Check chapter of this manual for pitch change rod
identification.

(2) Procedure

(a) Locate the oil hole in the pitch change rod.

(b) Center punch a location approximately 180 degrees away from the oil
hole in the pitch change rod and 0.47 inch (11.9 mm) from the pitch
change rod shoulder. Refer to Figure 606.

CAUTION: DRILL THROUGH ONLY ONE SIDE OF THE PITCH

CHANGE ROD.

(c) Drill a 0.125 inch +0.004/-0.000 inch (3.17 mm +0.10/-0.00 mm) hole
through one side of the pitch change rod. Refer to Figure 606.

(d) Press a B-6378-0375 roll into the drilled hole, until the roll
pin pin is
flush to slightly below the surface of the pitch change rod.

(e) Peen the edge of the hole to secure the B-6378-0375 roll pin in the
pitch change rod.

Pitch Change Rod Oil Hole Roll Pin

Shoulder 8-6378-0375

Tube Portion

Peen the edge of the hole.

No space between the shoulder and the tube.

0.47 inch (11.9 mrn)

Installing a Roll Pin in the Two-Piece Pitch Change Rod

Figure 606

617
REPAIR 61’1 0’17 RevP7aSABp~b:Page
 PROPELLER
HARTZ ELL MA:N:7EDNANCE MANUAL

(This page is intentionally blank.)

I 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

CONTENTS

1. General 705

2. Compact Hub Assembly Procedures 707

A. Hub Preparation 707

3. Blade Assembly Procedures 709

A. Installation of the Blade Bearing Race and Balls 709

B. Preload Plate Assembly 711

4. Propeller Assembly Procedures 713

A. Blade Installation Two Blade Propeller 713

B. Blade Installation Three Blade Propeller................................................... 719

C. Blade Installation Four Blade Propeller.........,........................................... 727

D. Application of Blade Reference Tape 734.1

E. Pitch Change Unit Assembly and Blade Tolerance Checks 735

F 830-21 or 830-30 Stop Unit Assembly and Installation 741

G. Cylinder Spring Assembly Installation 743

H. Piston and Cylinder Installation 753

i. Hub Spring Installation 757

J. Setting the Blade Angles 765

5. Blade Track 772

6. Propeller Lubrication

7. Static Balance 772

8. Damper
A. Damper Assembly 775

,s,,,, 61-10-17
 PROPELLER
HARTZELL MA:N~NPINCE MANVIL

FIGURES

Installing the Flange O-Ring in the Engine-Side

Hub Half Flange Figure 701 706

Installing the Engine-Side Hub Half on the

Rotatable Fixture Figure 702 706

Installing the Blade Retention Bearing Figure 703 708

Pressing the Inner Blade Bore Bearing Race on the

Preload Plate Spindle Figure 704 710

Installing the Preload Plate on the Blade Shank Figure 705 710

Applying the Clamping Tool TE24 to the Blade Assembly Figure 706 711

Installing Blade Number One in the Two-Way Hub................ Figure 707 714

Installing the Two-Way Cylinder-Side Hub Half Figure 708 715

Setting the Two-Way Preload Figure 709 716

Installing Blade Number One and the Pitch Change Parts Figure 710 717

Applying Sealant on the Two-Way Hub Parting Surface........ Figure 711 718

Installing Blade One in the Three-Way Hub Figure 712 719

Installing the Three-Way Hub Half Before

Tightening Preload Plate Figure 713 721

Tightening Preload Plate Hex Head Screw and Jam Nut.......Figure 714 722

Installing the Pitch Change Blocks on

Blades Two and Three Figure 715 724

Installing the Pitch Change Fork on

Blades Two and Three Figure 716 724

Applying Sealant Between the Three-Way Hub Halves......... Figure 717 726

Installing the Four-Way Cylinder-Side Hub Half Figure 718 729

Installing the Pitch Change Fork Figure 719 731

Installing Blade Number One in the Four-Way Hub Figure 720 732

Applying Sealant Between the Four-Way Hub Halves Figure 721 733

Using the Torque Wrench Adaptor TE6 on the

Pitch Change Rod Figure 722 735

Using a Spacer to Check Blade Angles Figure 723 736

Checking Blade Angles With the Bench Top

Protractor TE96 Figure 724 737

~s,,,,, sl-lo-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIGURES. Cont’d

Figure 725 742

Using the Assembling Tool TE9
the High Stop Bracket to the Cylinder Figure 726 743
Attaching
the Cylinder the Assembling Tool TE9............ Figure 727 744
Positioning on

the Assembly Guides TE319 Figure 728 744

Installing
Placing the Feathering Spring and Spring Retainer
in the Cylinder.... Figure 729 745

Installing the Washer on the Assembly Guides TE319 ..........Figure 730 746

Positioning the Weight in the Cylinder.................................... Figure 731 746

the Drilled Washer in the Cylinder Figure 732 747

Placing
Compressing the Feathering Spring Using Assembling
Tool TE9 Figure 733..........

the Cylinder Cap Figure 734 749

Installing
Positioning the Drilled Washer for Installation
of the First Two Screws Figure 735 750

Positioning the Drilled Washer for Installation

of the Final Two Screws Figure 736 750

Figure 737 751

Installing the Final Two Screws
Applying a Bead of Sealant Where the Cylinder and
Hub Meet Figure 738.......

Installing the Cylinder with Cylinder Torque Wrench

Adapter TE153 Figure 739 754

Figure 740 756

Installing the Spacer
the Spring Guide Figure 741 756
Installing
734.1
I Application of Blade Reference Tape Figure 741.1

Installing the Small Diameter Feathering Spring

on the Pitch Change Rod Figure 742 758

Installing Large Diameter Feathering Spring

the
on the Pitch Change Rod Figure 743 758

the Spring Retainer the Pitch Change Rod ........Figure 744 759
Installing on

the Spring Compressor Assembly TE31 Figure 745 760

Installing
Compressing the Feathering Springs with the
Figure 746 760
Spring Compressor Assembly TE31
Installing the Keeper on the Pitch Change Rod Figure 747 762

ASSEMBLY 61 ’1 0’1 7
 PROPELLER
HARTZ E LL MA:N1~EDNANCE MANUAL

FIGURES, Cont’d

Parts for Adjusting the Pitch Angle Figure 748 764

Checking the Feather Angle With a Hand Held Protractor..... Figure 749 765

Hub Leak Check Figure 750

Checking Blade Track Figure 751 772

Damper Assembly Figure 752 774

Damper Installation Figure 753

I ~sE..LY61-10-17 Page
Rev. 7
704
Apr/Ol
 PROPELLER MAINTENANCE MANUAL
H 11~ RT Z E L L 1170

ASSEMBLY PROCEDURES

1. General

CAUTION: THE USE OF BLADE PADDLES TO MOVE BLADES OR ROTATE

PRELOAD PLATES CAN RESULT IN THE OVERLOAD AND DAMAGE
OF BLADE PITCH CHANGE KNOBS. THIS DAMAGE IS NOT
REPAIRABLE AND CAN RESULT IN SEPARATION BETWEEN THE
BLADE AND THE PITCH CHANGE KNOB, CAUSING LOSS OF PITCH
CONTROL DURING FLIGHT.

A. In preparation for reassembling and reinstalling a Hartzell Propeller, make sure that
all preliminary procedures have been followed.

B. Read all assembly instructions before beginning the assembly procedures.

C. Refer to Hartzell Manual 202A (61-01-02), Standard Practices for aluminum hub
assembly procedures.

D. Refer to Hartzell Manual 133C (61-13-33), Aluminum Blade Overhaul for blade bore
plug, blade bore bearing, and hub-side split bearing race installation procedures.

E. Properly protect ail unassembled components from damage.

F. Unless instructed otherwise, lubricate all O-rings with lubricant CM12 before
installing in the propeller assembly.

G. Observe applicable torque values. Refer to Table 801.

H. Safety wire per MS33540 using 0.032 inch (0.81 mm) safety wire unless otherwise
specified.

I. Verify the installation of the B.F. Goodrich electric de-ice system or Hartzell anti-ice
system, if applicable, before beginning the assembly of the hub.

61-10-17
 PROPELLER MANUAL
HA RTZ E L L MA:Nl:EDNANCE

APS2012

Tlis
j-o

Installing the Flange O-Ring in the Engine-Side Hub Half Flange

Figure 701

APS2013

Installing the Engine-Side Hub Half on the Rotatable Fixture

Figure 702

ASSEMBLY 61’10’17
 PROPELLER MAINTENANCE MANUAL
HIP~ RT Z c LL 117b

2. Compact Hub Assembly Procedures

A. Hub Preparation

NOTE: Verify the spinner and bulkhead assembly and installation procedures,
if applicable, before beginning the assembly of the hub. Use the
alternate hub clamping nuts and bolts that are supplied with a spinner
mounting kit.
(1) Refer to Hartzell Manual 202A (61-01-02), Standard Practices, Chapter 1300,
Aluminum Hub Overhaul for procedures to install the pitch change rod guide
bushings and the propeller mounting hardware.

(2) Install a new pitch change rod O-ring (390) in the cylinder-side hub half

(480).
(3) Install the shaft required, into the engine-side
plug (660), if hub half of hubs
with extensions that do not require a hub spring assembly. For non-

extended hubs proceed to step 3.A.(4).

NOTE 1: For propellers that require a hub spring assembly, the shaft plug will
be installed after completing the hub spring assembly installation.
NOTE 2: An example of an extended hub model number is: HC-E2YR-2BF.

(a) Install a new shaft plug OD O-ring (670) on the shaft plug.
(b) Install a new shaft plug ID O-ring (680) in the shaft plug.
(c) Install the shaft plug (660) in the engine-side hub half center bore.

NOTE: When installing, hold the shaft plug by the removal feature
(refer to Figure 509).
(4) flange mounting O-ring (40001
Install the on the engine-side hub half (480)
(Figure 701).
(5) Install a new pitch change rod O-ring (470) in the engine-side hub half.

NOTE: If the hub is an extended hub design, the pitch change rod O-ring is
installed in the hub shaft plug ID.

(6) Install and secureengine-side hub

the half on the rotatable fixture on the

propeller assembly table (Figure 702).

ASSEMBLY 61 ’1 0’1 7
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1170

APS2019

Blade Seal (3010)

Ball Spacer (3040)

Blade Bearing Race
(3050)
Bearing Race Retaining
Ring (3060)

Bearing Balls (3030)

Installing the Blade Retention Bearing

Figure 703

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

3. Blade Assembly Procedures

NOTE: The following procedure assumes that the blade has been inspected,
reworked, and repaired and that the blade bore plug, blade bore bearing, and
blade thrust bearings are installed per Hartzell Aluminum Blade Manual 133C
(61-13-33).

A. Installation of the Blade Bearing Race and Balls (Figure 703)

(1) Lubricate the blade seal (3010) with lubricant CM12 and install on the blade.

bearing (3050) with lubricant CM12.

1 (2) Lubricate the blade race

(3) Place the ball spacer (3040) on the blade bearing race (3050).

CAUTION: ALL THE BEARING BALLS IN A SINGLE BEARING MUST BE OF

THE SAME SIZE AND GAUGE. BEARING BALLS SUPPLIED BY
HARTZELL ARE THE SAME GAUGE.

(4) Using a small amount of lubricant CM12 around the bearing balls, place the
bearing balls (3030) in the openings of the ball spacer (3040) on the blade
race (3050).

CAUTION: THE BEARING RACE HALVES MUST HAVE MATCHING SERIAL

NUMBERS.

(5) Place the hub bearing race (3020) on the balls (3030) (Figure 705).
I NOTE: The split bearing race parting line must be perpendicular to the
hub parting line when installed in the hub.

ASSEMBLY 61 ’1 0’1 7
 PROPEL"R
CIARTZELL M*:N:7EDNINCE MPINUPIL

APS2026

Inner Blade Bore

Bearing Race (3090)

Preload Plate (3080)

Preload Plate Spindle

Pressing the Inner Blade Bore Bearing Race on the Preload Plate Spindle
Figure 704

APS2024A

Blade Seal
(3010)
Hub Bearing Race (3020

Lubricant
CM 12

Preload Plate
(3080)

Installing the Preload Plate on the Blade Shank

Figure 705

710
sl-lo-17
 PROPELLER MAINTENANCE MANUAL
H~RTZ c LL 117D

8. Preload Plate Assembly

(1) Place the preload plate in a fixture and press the blade bore bearing (3090)
inside race over the preload plate (3080) spindle (Figure 704).

NOTE: On preload plates that do not maintain a press fit for the race,
apply thread locking compound CM74 to the preload plate (3080)
spindle (Figure 704).
(2) Install the socket head screw (3100) in the preload plate so the end of the
screw protruding toward the blade butt is flush with the preload plate.
NOTE: The socket head screw will be repositioned later to set the blade

preload.
(3) Install the nut (3110) on the screw (3100).
(4) Place approximately one tablespoon of lubricant CM12 on top of the preload
plate inner bearing race spindle.
NOTE: Using this amount of lubricant will force lubrication into the blade
bore bearing when the preload plate is installed on the blade.

(5) Install the preload plate (3080) on the butt of the blade (Figure 705).
NOTE: For installation into the hub, hold the split bearing and preload plate
assembly to the blade butt with the clamping tool TE24 (Figure 706).

npssol9

Applying the Clamping Tool TE24 to the Blade Assembly

Figure 706

61-10-17
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

(This page is intentionally blank.)

712
ASSEMBLY 61’10’17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

4. Propeller Assembly Procedures

NOTE: Use protractor TE96, TE97, or equivalent when measuring a blade angle.
Refer ti, the Hartzell Tool and Equipment Manual 165A (61-00-65).

A. Blade Instaliation Two Blade Propeller

(1) Lubricate the hub blade retention radius with a thin film of lubricant CM12.

(2) Lubricate the hub seal grooves with a thin film of lubricant CM12.

CAUTION: BLADES MUST BE PRELOADED WHILE RESTING IN THE HUB

SOCKET THEY WILL OCCUPY WHEN ASSEMBLED. DO NOT
PRELOAD ALL THE BLADES IN THE SAME SOCKET.

(3) Install the number one blade assembly into the socket of the engine-side
hub half.

(4) Center the slot in the preload plate (3090) at the hub parting line (Figure
707).
I NOTE: Position the blade knob slot in the preload plate to allow the blade
to travel the full blade angle range without restriction.

CAUTION: IMPROPER PRELOAD CAN CAUSE THE BLADES TO BE

LOOSE IN THE HUB OR MAY EXERT EXCESSIVE PRESSURE
THAT CAN INTERFERE WITH PITCH CHANGE MOVEMENT.

(5) Setting the blade preload.

(a) Install the cylinder-side hub half (Figure 708).
(b) Bolt the hub halves together using two bolts (580), two washers (600),
and two nuts (610).
NOTE: The bolts are located midway between the blades (Figure 708).
(c) Torque the nuts (610) in accordance with Table 801.

(d) Tighten the preload socket set screw (3100) through the open end of the
hub (Figure 709).

NOTE: The loose blade will become rigid in the hub as the socket
screw is tightened.
(e) Tighten the preload socket set screw (3100) until the tip of the blade stops
moving vertically.

ASSEMBLY 61’1 0’17 RevP789Aspl~

 PROPELLER
HARTZ ELL MA:N1:EDNANCE MANUAL

(f) Loosen the preload socket screw (3100) and retighten. When the blade tip
stops moving, turn the socket screw an additional 1/4 turn into the preload
plate.
(g) Check the blade for free rotation. If the blade is not free, remove the blade
and check the following:
1 Blade seal (3010) for proper fit in the hub groove.

2 The needle rollers in the blade bore bearing may be skewed. The
needle rollers should be parallel to the axis of blade pitch change.

3 Blade preload may be too tight.

(h) Remove the two bolts (580), two washers (600), and two nuts (610).
(i) Remove the cylinder-side hub half (480).
(j) Apply one drop of thread locking compound CM21 to the threads of the
preload socket set screw (3100).

APS2000

o 8
a

o
Center the preload
d

plate slot at the hub

parting line.

Hub parting line.

Installing Blade Number One in the Two-Way Hub

Figure 707

ASSEMBLY 61’10’17
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 1170

(k) Torque the jam nut (3110) in accordance with Table 801.

NOTE: Be sure to prevent the socket screw from moving when torquing
the jam nut.

(6) Remove blade number one.

Install blade assembly number two into the socket of the engine-side hub
(7)
half.

(8) Center the slot of the preload plate (3090) at the hub parting line (Figure
707).
NOTE: The blade knob slot in the preload plate should be positioned to allow
the blade to travel the full blade angle range without restriction.

APS2039

Installing the Two-Way Cylinder-Side Hub Half

Figure 708

61-10-17
 PROPELLER
HA RTZ E L L MA:N~EDNANCE MANUAL

CAUTION: IMPROPER PRELOAD CAN CAUSE THE BLADES TO BE LOOSE

IN THE HUB OR CAN EXERT EXCESSIVE PRESSURE,
INTERFERING WITH PITCH CHANGE MOVEMENT.

(9) Set the bladepreload using the procedures outlined in steps 3.B(5)(a)
through 3.B(5)(k).
(10) Reinstallation of blade number one, including the pitch change parts.
(a) Install the pitch change block buttons (450) into the pitch change block
(440).
(b) Apply anti-seize
compound CM118 to the outside of each pitch change
knob bushing (3000).

(c) Apply anti-seizecompound CM118 to each pitch change block groove

of the pitch change fork (400).
(d) Apply anti-seize compound CM118 to the threads of the fork (400).
I (e) Install a pitch change block (440) on each blade pitch change knob,
with the round extension away from the blades.

NOTE: Check the orientation of the pitch change block. Pitch change
blocks should be installed in the fork with the thin wall toward
the engine-side hub half during initial assembly.

APS2020A

Setting theTwo-Way Preload

Figure 709

~.SSEMBLY 61-10-17 RevPrasABp~f)

 PROPELLER MAINTENANCE MANUAL
nARTZ ELL 1170

(f) Install the rubbing plate, if appiicable, on the fork. Refer to the Special
Adhesive and Bonding Chapter of Hartzell Standard Practices Manual
202A (61-01-02) for rubbing plate installation procedures.

CAUTION: MAKE SURE THE TAPER IN THE FORK MATCHES THE

TAPER IN THE PITCH CHANGE ROD. IF THE PITCH
CHANGE ROD IS IMPROPERLY ATTACHED TO THE FORK,
THE SEATING AREA OF THE PITCH CHANGE ROD WILL BE
DAMAGED.

(g) Install the fork (400) on the pitch change block (440) of blade number

I two.

blade number into the fork

(h) Slide the pitch change block (440) on one

(400).
NOTE: Be sure to maintain correct pitch change block orientation

(Figure 710).
(i) Reinstall blade number one in the hub socket (Figure 710).
Remove the blade retention components clamp TE24 from blade
(j)
number one.

APS2021

Installing Blade Number One and the Pitch Change Parts

Figure 710

ASSEMBLY 61 ’1 0’1 7
 PROPELLER
HARTZELL MPI:N1~EDNANCE MPINUIL

(11) Installing the cylinder-side hub half.

NOTE: Hubs manufactured with a hub parting su~ace seal groove no longer
use the A-2436 hub parting seal. Fill the groove with sealant CM92
and continue the assembly procedure.
(a) Place a bead of sealant CM92 on the hub mating surfaces (Figure 711).
NOTE: Use enough sealant on the mating surfaces so that a small
amount will besqueezed out along the entire parting surface
when the hub bolts are properly torqued.

CAUTION: BE SURE THE BLADE SEAL IS CORRECTLY ALIGNED IN

THE HUB GROOVE WHEN INSTALLING THE CYLINDER-
SIDE HUB HALF.

(b) Install the cylinder-side hub half.

NOTE: Use a rubber mallet to position the hub half.

(c) Positioned midway between each of the blade sockets on both sides,
install a bolt (580), washer (600), and nut (610) (Figure 708).

(d) Torque the nuts (610) in accordance with Table 801.

(12) Proceed to paragraph 3.E. Pitch Change Unit Assembly and Blade
Tolerance Checks, in this chapter.

APS2037

Sealant CM92

Applying Sealant on the Two-Way Hub Parting Surface

Figure 711

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 117D

B. Blade Installation Three Blade Propeller

(1) Lubricate the hub blade retention radius with a thin film of lubricant CM12.

(2) Lubricate the hub seal grooves with a thin film of lubricant CM12.

CAUTION: BLADES MUST BE PRELOADED WHILE RESTING IN THE

SOCKET THEY WILL OCCUPY WHEN ASSEMBLED. DO NOT
PRELOAD ALL THE BLADES IN THE SAME SOCKET.

Using clamping tool TE24, install the number one blade assembly into the
(3)
socket of the engine-side hub half (Figure 712).

Installing Blade One in the Three-Way Hub

Figure 712

61-10117
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 117D

(This page is intentionally blank.)

ASSEMBLY 61’10’17 Rev. 4 May/9 Page 720

 PROPELLER MAINTENANCE MANUAL
H19 RTZ E LL IltD

(4) Center the slot of the preload plate (3090) at the hub parting line (same as

for the two blade propeller Figure 707).

NOTE: The blade knob slot in the preload plate should be positioned to
allow the blade to travel the full blade angle range without
restriction.

CAUTION: IMPROPER PRELOAD CAN CAUSE THE BLADES TO BE

LOOSE IN THE HUB OR MAY EXERT EXCESSIVE PRESSURE
THAT CAN INTERFERE WITH PITCH CHANGE MOVEMENT.

(5) Setting the blade preload.

(a) Install the cylinder-side hub half (480) (Figure 713).
(b) Bolt the hub halves together using three bolts (580), three washers (600),
and three nuts (610) (Figure 713).
NOTE: The bolts are located midway between the blades.

as, a

Installing the Three-Way Hub Half Before Tightening Preload Plate

Figure 713

sl-lo-17 ,,,.~b
 PROPELLER
HARTZELL MPI:E~JEDNINCE MANUAL

(c) Torque the nuts (610) in accordance with Table 801.

(d) Tighten the preload socket set screw (3100) through the open end of the
hub (Figure 714).

NOTE: The loose blade will become rigid in the hub as the socket
screw is tightened.
(e) Tighten the preload socket screw until the tip of the blade stops moving
vertically.
(f) Gently move the tip of the blade to make sure the blade is properly seated
in the retention socket.

(g) Loosen the preload socket screw (3100) and retighten. When the blade tip
stops moving, turn the socket screw an additional 1/4 turn into the preload
plate.
(h) Check the blade for free rotation. If the blade is not free, remove the blade
and check the following:
1 Blade seal (3010) for proper fit in hub groove.

2 The needle rollers in the blade bore bearing may be skewed. The
needle rollers should be parallel to the axis of blade pitch change.

3 Blade preload may be too tight.

APS2061

‘Y "f

Tightening Preload Plate Hex Head Screw and Jam Nut

Figure 714

ASSEYBLY 61’10’17
 PROPELLER MAINTENANCE MANUAL
H RT Z E L L Ilte,

(i) Remove the three bolts (580), three washers (600), and three nuts (610).
(j) Remove the cylinder-side hub half (380).
(k) Apply one drop of thread locking compound CM21 on the threads of the
preload socket set screw (3100).
(I) Torque the jam nut (3110) in accordance with Table 801.

NOTE: Be sure to prevent the socket screw from moving when torquing
the jam nut.

(6) Remove blade number one.

(7) Install blade assemblies two and three into the sockets of the engine-side
hub half.

(8) Center the slot of the preload plate (3090) at the hub parting line (same as

for the two blade propeller Figure 707).

NOTE: The blade knob slot in the preload plate should be positioned to allow
the blade to travel the full blade angle range without restriction.
(9) Set the blade preload using the procedures outlined in steps 3.C(5)(a)
through 3.C(5)(1).
(10) Reinstallation of blade number one including the pitch change parts.
(a) Install the three pitch change fork buttons (410) on the pitch change
fork (400).
NOTE: The buttons press fit into the fork holes provided.
(b) Apply compound CM118
anti-seize to the outside of each pitch change
knob bushing (3000).

(c) Apply anti-seizecompound CM118 to each pitch change block groove

of the pitch change fork (400).
(d) Apply anti-seize compound CM118 to the threads of the fork (400).

PISSEMILY 61 -10-1 7
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

THE THIN SIDE OF p ~I

THE PITCH CHANGE
BLOCK IS DOWN
AND THE ROUND
EXTENSION IS AWAY o

FROM THE BLADE.

Installing the Pitch Change Blocks on Blades Two and Three

Figure 715

APS2010A

L-

Installing the Pitch Change Fork on Blades Two and Three

Figure 716

724
ASSEMBLY 61110-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(e) Install a pitch change block (440) on each blade pitch change knob
with the round extension away from the blades (Figure 715).
NOTE: Check the orientation of the pitch change block. Pitch change
blocks should be installed in the fork with the thin wall toward
the engine-side hub half during initial assembly.

CAUTION: MAKE SURE THE TAPER IN THE FORK MATCHES THE

TAPER IN THE PITCH CHANGE ROD. IF THE PITCH
CHANGE ROD IS IMPROPERLY ATTACHED TO THE FORK,
THE SEATING AREA OF THE PITCH CHANGE ROD WILL BE
DAMAGED.

NOTE: Forks manufactured in the 1980s were intended to be

universal (both left and right handed) and were tapered on
both sides. Universal forks are no longer manufactured.

(f) Install the fork (400) on the pitch change blocks of blades two and
three.

(g) Slide the pitch change block (440) for blade number one into the fork
(400).
(h) Insert the pitch change knob of blade number one into the pitch change
block (440) mounted on the fork (400) and rotate the blade into the hub
blade socket.

(i) Remove the blade retention components clamp TE24 from blade
number one.

,,,,,Y 61 -1 0-17
 PROPELLER
HARTZELL MA:N1~NANCE MPINUPIL

(11) Installing the cylinder-side hub half.

(a) Place a bead of sealant CM92 on the hub mating surfaces (Figure 717).
NOTE: Use enough sealant on the mating surfaces so that a small
amount will besqueezed out along the entire parting surface
when the hub bolts are properly torqued.

CAUTION: BE SURE THAT THE BLADE SEAL IS CORRECTLY

ALIGNED IN THE HUB GROOVE WHEN INSTALLING THE
CYLINDER-SIDE HUB HALF.

(b) Install the cylinder-side hub half.

NOTE: Use a rubber mallet to position the hub half.

(c) Positioned midway between each of the three blade sockets, install a
bolt (580), washer (600), and nut (610) (Figure 713).

(d) Torque the nuts (610) in accordance with Table 801.

(e) Proceed to paragraph 3.E. Pitch Change Unit Assembly and Blade
Tolerance Checks, in this chapter.

APS2040

Sealant CM92

Applying Sealant Between the Three-Way Hub Halves

Figure 717

61’16’17
 PROPELLER MAINTENANCE MANUAL
cLL 1170

C. Blade Installation Four Blade Propeller

(1) Lubricate the hub blade retention radius with a thin film of lubricant CM12.

(2) Lubricate the blade hub seal grooves with a thin film of lubricant CM12.

CAUTION: BLADES MUST BE PRELOADED WHILE RESTING 1N THE

SOCKET THEY WILL OCCUPY WHEN ASSEMBLED. DO NOT
PRELOAD ALL THE BLADES IN THE SAME SOCKET.

(3) Install blade assemblies one and two into the sockets of the engine-side
hub half.

(4) Center the slot of the preload plate (3090) at the hub parting line (same as

for the two blade propeller Figure 707).

NOTE: The blade knob slot in the preload plate should be positioned to allow
the blade to travel the full blade angle range without restriction.

~ISSEMBLY 61 -1 0-1 7
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

(This page is intentionally blank.)

728
ASSEMBLY 61’10’17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
H P~ RT Z E L L Ilfb

CAUTION: IMPROPER PRELOAD CAN CAUSE THE BLADES 10 BE

LOOSE IN THE HUB OR MAY EXERT EXCESSIVE PRESSURE
THAT CAN INTERFERE WITH PITCH CHANGE MOVEMENT.

(5) Setting the blade preload.

(a) Install the cylinder-side hub half.
(b) Bolt the hub halves together using four bolts (580), four washers (600),
and four nuts (610) positioned midway between each blade socket
(Figure 718).
(c) Torque the nuts (610) in accordance with Table 801.

(d) Tighten the preload socket set screw (3100) through the open end of the
hub.

NOTE: The loose blade will become rigid in the hub as the socket
screw is tightened.
(e) Tighten the preload socket set screw (3100) until the tip of the blade stops
moving vertically.
(f) Gently push on the tip of the blade to make sure the blade is properly
seated in the retention socket.

APS2038

Instaliing the Four-Way Cylinder-Side Hub Half

Figure 718

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(g) Loosen the preload socket screw (3100) and retighten. When the blade tip
stops moving, turn the socket screw an additional 1/4 turn into the preload
plate.
(h) Check the blade for free rotation. If the blade is not free, remove the blade
and check the following:
1 Blade seal (3010) for proper fit in the hub groove.

2 The needle rollers in the blade bore bearing may be skewed. The
needle rollers should be parallel to the axis of blade pitch change.
3 Blade preload may be too tight.
(i) Remove the four bolts (580), four washers (600), and four nuts (610).
(j) Remove the cylinder-side hub half (480).
(k) Apply one drop of thread locking compound CM21 on the threads of the
preload socket set screws (3100).
(I) Torque the jam nuts (3110) in accordance with Table 801.

NOTE: Be sure to prevent the socket screw from moving when torquing
the jam nut.

(6) Remove blades one and two.

(7) Install blade assemblies three and four into the socket of the engine-side
hub half.

(8) Center the slot of the preload plate (3090) at the hub parting line (same as

for the two blade propeller Figure 707).

NOTE: The blade knob slot in the preload plate should be positioned to allow
the blade to travel the full blade angle range without restriction.
(9) Set the blade preload using the procedures outlined in steps 3.D.(5)(a)
through 3.D.(5)(1).
(10) Reinstalling blades one and two including pitch change parts.
(a) Install the pitch change fork buttons (410) on the pitch change fork (400).
NOTE: The buttons press fit into the holes in the fork.

(b) Install blade two into the engine-side hub half.

(c) Center the slot of the preload plate (3090) at the hub parting line.
NOTE: The blade knob in the preload plate should be positioned to
allow the blade to travel the full blade angle range without
restriction.

(d) Apply anti-seize compound CM118 to the outside of each pitch change
knob bushing (3000).

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 1170

(e) Apply compound CM118

anti-seize to each pitch change block groove
of the pitch change fork (400).

(f) Apply anti-seize compound CM118 to the fork threads.

(g) Install a pitch change block (440) on each blade pitch change knob of
blades two, three and four, with the round extension away from the
blades.

NOTE: Check the orientation of the pitch change block. Pitch change
blocks should be installed in the fork with the thin wall toward
the engine-side hub half during initial assembly.

CAUTION: MAKE SURE THE TAPER IN THE FORK MATCHES THE

TAPER IN THE PITCH CHANGE ROD. IF THE PITCH
CHANGE ROD IS IMPROPERLY ATTACHED TO THE FORK,
THE SEATING AREA OF THE PITCH CHANGE ROD WILL BE
DAMAGED.

(h) Install the fork (400) on the pitch change blocks (440) of blades two,
three and four (Figure 719).

APS2041

c~-x

Thin Side of
Pitch Change
Block is Down

Installing the Pitch Change Fork

Figure 719

ASSENIBLY 61’1 0-17

 PROPELLER
HARTZ E LL MA:N:7EDNANCE MANUAL

(i) Slide the pitch change block (440) in the fork (400) for blade number one.

(j) Position the center of the slots in the preload plate on the plane of the
parting line of the hub.

NOTE: The blade knob slot in the preload plate should be positioned
to allow the blade to travel within the blade angle range
without restriction.

(k) Insert thepitch change knob of blade number one in the pitch change
block (440) mounted in the fork (400) and install the blade in the
engine-side hub half (Figure 720).

APS2044

Installing Blade Number One in the FourlWay Hub

Figure 720

01’10’17
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 117D

(11) Install the cylinder-side hub half.

(a) Place a bead of sealant CM92 on the hub mating surfaces (Figure 721).
NOTE: Use enough sealant mating surfaces so that a small
on the
amount will be squeezed out along the entire parting surface
when the hub bolts are properly torqued.

CAUTION: MAKE SURE THE BLADE SEAL IS CORRECTLY ALIGNED

IN THE HUB GROOVE WHEN INSTALLING THE
CYLINDER-SIDE HUB HALF.

(b) Install the cylinder-side hub half.

NOTE: Use a rubber mallet to position the hub half.

(c) Positioned midway between each of the four blade sockets, install a

bolt (580), washer (600), and nut (610) (Figure 718).

(d) Torque the nuts (610) in accordance with Table 801.

APS2040

Sealant CM92

Applying Sealant Between the Four-Way Hub Halves

Figure 721

61-10-17
 PROPELLER
HARTZELL MAI1NISEDNPINCE MPINUPIL

W10313
APS0050

I-

I
Camber

Grf´•i~
C- Measure distance
hub center to
blade radius
blade face
f’om
reference
\ocation on

Reference blade
radius location
(Blade Face)

Blade Face

Yellow Blade Angle

Reference Tape
CM160

Application of Blade Angle Reference Tape

Figure 721.1

ASSEMBLY 61’10’17 Rev. 7 Apr/OlPage 734

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

D. Application of Blade Angle Reference Tape

CAUTION: DO NOT CONFUSE REFERENCE BLADE RADIUS WITH BLADE

STATION. REFERENCE BLADE RADIUS AND BLADE STATION
OF THE SAME NUMBER MAY NOT ALWAYS INDICATE THE
SAME LOCATION ON THE BLADE.

Reference blade radius is measured from the center of the propeller hub to a
predetermined reference location on the blade for blade angle measurement.
Blade stations are used during the repair or overhaul process of a blade to define a

blade span location for dimensional measurement.

(1) Establish a reference blade radius location

(a) Refer to the Aircraft Type Certificate Data Sheet or the Hartzell Propeller
Application Guide, Manual 159 (61-02-59), for the reference blade radius
location specified for the applicable aircraft installation.

(b) Beginning with blade one, measure from the center of the propeller hub to
the reference blade radius location specified. Refer to Figure 721.1.

(c) Apply a yellow bladeangle reference tape CM160 to the face side of the
blade at the reference blade radius location, perpendicular to the blade
centerline. Refer to Figure 721.1.
NOTE: Place the reference tape CM160 so that the reference blade
radius location runs through the centerline of the tape.

(d) Repeat steps 4.D.(1)(b) and 4.D.(1)(c) for the remaining blades in the hub
assembly.
(e) Place a pattern cut-out over each blade reference tape CM160 and
angle
spray each yellow blade angle reference tape CM160 with clear lacquer
CM129 to prevent peeling.

61-10-17
 PROPELLER
HA RTZ E L L MA:N:7EDNANCE MANUAL

(This page is intentionally blank.)

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

D. Pitch Change Unit Assembly and Blade Tolerance Checks

(1) Insert the pitch change rod (370) through the cylinder-side hub half and start
the pitch change rod in the threads of the fork (400).

(2) Put the modified socket TE385 of the torque wrench adaptor TE6 in place
on the pitch change rod (370) (Figure 722).

(3) Insert the anti-rotation TE386 of the torque wrench adaptor TE6 into the
pin
hole in the modified socket TE385. Make sure the flat side of the anti-
rotation pin is toward the pitch change rod (370).

NOTE: The anti-rotation pin TE386 keeps the socket from turning on the

pitch change rod.

(4) Torque the pitch change rod (370) in accordance with Table 801.

(5) Move the blades by hand to make sure the blades have a full range of
movement from low pitch to feather pitch.

APS6276

Modified Socket
TE385

Anti-rotation Pin
Torque Wrench TE386
TE386

Using the Torque Wrench Adaptor TE6 on the Pitch Change Rod
Figure 722

ASSEMBLY 61 ’10-17
 PROPELLER
nARTZELL M~:N1:EDNPINCE MINUAL

APS6277

Pitch Change
Rod (370)

Pin
(customer
supplied)

Stop
(customer
supplied)

Using a Spacer to Check Blade Angles

Figure 723

61-10-17
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 117D

(6) Blade Angle Check

(a) Counterweighted -2 and counterweighted -5 propellers only
1 Insert a pin withappropriate diameter into the hole in the pitch
change rod (370) (Figure 723).
2 Place a stop between the pin and the hub.
NOTE: The stop should be long enough, approximately 2.25
inches (5.7 cm), to allow measurement of the blade angles
near low pitch.

3 Rotate the blades by hand until the pin contacts the stop, checking
that the pitch change parts are firmly engaging the pitch change knob
of the blades.

NOTE: Rotate the blades by hand toward high pitch to remove any

slight blade angular looseness.

APS6274

Checking Blade Angles With the Bench Top Protractor TE96

Figure 724

61-10-17
 PROPELLER MANUAL
HA RT Z E L L MA:N:7EDNANCE

CAUTION 1: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE
HARMFUL TO THE STRENGTH OR FUNCTION OF THE
PROPELLER.

CAUTION 2: GRAPHITE ("LEAD") PENCIL MARKS WILL CAUSE

CORROSION.

I 4 Mark a line on each blade at the 30-inch reference blade radius.

The line at the 30-inch reference blade radius is for

measurement reference purposes and will also be used
when checking the feather angle of the blade.

1 5 Check all the blade angles at the 30-inch reference blade radius for
0.2 degree maximum tolerance between blades (Figure 724).
6 If the blade angle differs more than 0.2 degree between blades, turn
one or more of the pitch change blocks (440).
a To turn the blocks, remove the pitch change rod (370), and the
cylinder-side hub half.
b Make the appropriate adjustments to the pitch change blocks
(440).
NOTE: Pitch change blocks should be installed in the fork with
the thin wall toward the engine-side hub half during
initial assembly. Rotating the pitch change block 180
degrees will decrease the pitch of the corresponding
blade approximately 0.3 to 0.4 degree on a tractor
propeller. Rotating the pitch change block 180 degrees
will increase the pitch of the corresponding blade
approximately 0.3 to 0.4 degree on a pusher propeller.
It is possible to bring pitch angles differing as much as
0.5 degree into 0.2 tolerance by rotating the blocks. It
is also possible to bring the blades within tolerance by
rotating the fork 180 degrees on two-blade and four-
blade propellers.

Z Reassemble the propeller, and recheck the blade angle tolerance

between blades following steps E.6.(a)l through E.6.(a)5 above.

61-10-17
 PROPELLER MAINTENANCE MANUAL
H P~ RTZ E L L 117D

(b) Non-counterweighted -2 propellers only

1 Install a stop (280) approximately
screw five turns into the end of the
pitch change rod (370).
NOTE: A stop screw locking mechanism drilled
that has had the
out may be used as a tool for setting the angle. A new stop
screw must be used for the final assembly of the propeller.

2 Install the cylinder (70) hand tight on the cylinder-side hub half.

3 Install the low pitch stop (50) in the top of the cylinder (70).
NOTE: The low pitch stop does not have to be set to the
appropriate low pitch angle. The cylinder and low pitch stop
only provide a contact point for the pitch change rod while
checking for 0.2 degrees tolerance between blades.
4 Rotate the blades by pitch change rod (370) with the
hand until the
stop screw (280) installed contacts the low pitch stop (50), checking
that the pitch change parts are firmly engaging the pitch change knob
of the blades.

NOTE: Rotate the blades by hand toward low pitch to remove any

slight blade angular looseness.

CAUTION 1: DO NOT ETCH, SCRIBE, PUNCH MARK OR SIMILARLY

IDENTIFY PARTS IN ANY MANNER THAT MAY BE
HARMFUL TO THE STRENGTH OR FUNCTION OF THE
PROPELLER.

CAUTION 2: GRAPHITE ("LEAD") PENCIL MARKS WILL CAUSE

CORROSION.

each blade at the 30-inch reference blade radius.

I 5 Mark a line on

NOTE: The line at the 30-inch reference blade radius is for

measurement reference purposes and will also be used
when checking the feather angle of the blade.

1 6 Check all the blade angles at the 30-inch reference blade radius for
0.2 degree maximum tolerance between blades (Figure 724).

~SSEMBLY 61’1 0’17 RevP7aBABp~i

 PROPELLER
HARTZELL MA~SEDNANCE MANUAL

7 If the blade angle differs more than 0.2degree between blades, turn
one or more of the pitch change blocks (440).
a To turn the blocks, remove the pitch change rod (370), and the
cylinder-side hub half.

b Make the appropriate adjustments to the pitch change blocks

(440).
NOTE: Pitch change blocks should be installed in the fork with
the thin wall toward the engine-side hub half during
initial assembly. Rotating the pitch change block 180
degrees will decrease the pitch of the corresponding
blade approximately 0.3 to 0.4 degree on a tractor
propeller. Rotating the pitch change block 180 degrees
will increase the pitch of the corresponding blade
approximately 0.3 to 0.4 degree on a pusher propeller.
It is possible to bring pitch angles differing as much as
0.5 degree into 0.2 tolerance by rotating the blocks. It
is also possible to bring the blades within tolerance by
rotating the fork 180 degrees on two-blade and four-
blade propellers.

8 Reassemble the propeller, and recheck the blade angle tolerance

between blades following steps E.6.(a)l through E.6.(a)5 above.

(7) When all the blades are within 0.2 degree of each other, install the
remaining hub bolts (580)(590), washers (600), and nuts (610).
(8) Torque the hub nuts (610) in accordance with Table 801.

~PSSEMBLY 61’10’17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

E. 830-21 or 830-30 Stop Unit Assembly and Installation

CAUTION: CHECK THE STOP UNIT FOR FULL PIN RETRACTION.

(1) Insert the high stop pin (140) in the stop bracket (120).
(2) Insert the high stop spring (130) in the high stop pin (140).
(3) Compress the spring (130) and insert the cotter pin (150).
(4) Spread the ends of the cotter pin (150).
NOTE: The cotter pin holds the high stop spring and the high stop pin in the

stop bracket.
(5) Repeat steps F.(1) through F.(4) for the remaining arms of the stop unit.

(6) the stop unit pins

Operate (140) by hand to check for full freedom of
movement of the pins.

(7) Position the stop unit (110) in the cylinder (70), aligning the holes in the stop
unit with the holes in the cylinder.

(8) Apply thread locking compound CM21 to the high pitch stop bracket screws

(100).
(9) Use the screws (100) to attach the stop unit (110) to the cylinder (70).
(10) Torque the screws (100) in accordance with Table 801.

(11) Install the cylinder ID O-ring (90) in the groove inside the cylinder (70).

ASSEMBLY 61 11 011 7
 PROPELLER
HARTZELL MA:N1~EDNANCE MANUAL

85T2853
APS6181

L~L

TE288

TE287

ASSEMBLING TOOL TE9

TE291
TE289
TE290

Assembling Tool TE9

positioned in vise

Using the Assembling Tool TE9

Figure 725

ASSEMBLY 61-10-17 Rev. 4 May/9 Page 742

 PROPELLER MAINTENANCE MANUAL
~IARTZELL 117D

F. Cylinder Spring Assembly Installation

CAUTION: ASSEMBLING TOOL TE9 MUST BE USED TO COMPRESS THE

CYLINDER MOUNTED SPRING.

(1) Place the assembling tool TE9 in a vise with the flattened portion of t~e
threaded rod TE287 between the jaws of the vise, and tighten the vise
(Figure 725).

CAUTION: DO NOT ATTEMPT 10 INSTALL THE SPRING ASSEMBLY WITH

THE CYLINDER TORQUE WRENCH ADAPTER TE153 ATTACHED
TO THE CYLINDER.

(2) Position the high pitch stop bracket (240) in thecylinder (70) and align the
holes in the bracket with the holes in the cylinder.
(3) Apply thread locking compound CM21 to the high pitch stop bracket screws

(100).
(4) Use the screws(100) to attach the high pitch stop bracket (240) to the

cylinder (70) (Figure 726).

(5) Torque the high pitch stop bracket screws (100) in accordance with Table
801.

(6) Install the cylinder ID O-ring (90) in the groove inside the cylinder (70).

APS6180

68
o High Pitch Stop
Bracket (240)
Screws (100)

Cylinder (70)

Attaching the High Stop Bracket to the Cylinder

Figure 726

61-10-17
 PROPELLER
HARTZ ELL MA:N~NANCE MP~NUAL

APS6182

Assembling Tool TE9

Cylinder (70)

Positioning the Cylinder on the Assembling Tool TE9

Figure 727

Assembly Guides
TE319

Assembling Tool TE9

High Pitch Stop

1JI~ Bracket (240)

Cylinder (70)

Instaliing the Assembly Guides TE319

Figure 728

61 -1 0’17 Rev
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(7) Put the cylinder (70) on the assembling tool TE9 with the small opening of
the cylinder toward the vise (Figure 727).

NOTE: The small diameter shoulder of the guide washer TE291 will fit, in the
small opening of the cylinder.
(8) Install the assembly guides TE319 into the screw holes in the high stop
bracket (240) (Figure 728).
NOTE: Make sure the assembly guides are installed 180 degrees apart.
(9) Place thefeathering spring (230) and spring retainer (220) over the
assembly guides in the cylinder (70) (Figure 729).

APS6184

Spring Retainer (220)

Feathering Spring
(230)

Cylinder (70)

Placing the Feathering Spring and Spring Retainer in the Cylinder

Figure 729
 PROPELLEA MANUAL
HARTZ ELL

APS6185

Washer (250)

Assembly Guides
TE319

Assembling Tool
TE9

Cylinder (70)

Installing the Washer on the Assembly Guides TE319

Figure 730

APS6186

Weight Spring (210)

Assembling Tool TE9

Weight (190)

Positioning the Weight in the Cylinder

Figure 731

el-lo-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(10) Position the washer (250) with the raised portion up and line up the holes in the
washer with the assembly guides TE319 (Figure 730).

(11) Slide the washer (250) on the assembly guides TE319 until the washer is snug
against the bottom of the spring retainer (220) (Figure 730).
NOTE: The raised part of the washer should be visible.
(12) For propellers using a stop weight (190) Place the high pitch stop weight
spring (210) in the groove around the halves of the weight (190).
NOTE: Position the spring connection point 90 degrees from the meeting
point of the weight halves.
(13) Line up two of the small holes in the weight (190) or retainer plate (200) with
the assembly guides TE319.

CAUTION: THE WEIGHT OR RETAINER PLATE MUST REST AROUND THE

LARGE DIAMETER OF THE THREADED ROD TE287.

(14) Slide the weight (190) or retainer plate (200) on the assembly guides TE319
until the weight or retainer plate rests around the large diameter of the threaded
rod TE287 and against the washer (250) at the bottom of the spring retainer
(220) (Figure 731).
(15) Line up the two small holes in the drilled washer TE288 with the assembly
guides TE319 (Figure 732).

APS6187

Two Nuts TE387

Guides Drilled Washer

Assembly
TE319 TE288

Placing the Drilled Washer in the Cylinder

Figure 732

ASSEMBLY 61 -1 0’1 7
 PROPELLER
HARTZELL MA:N1~EDNANCE MANUAL

(16) Slide the drilled washer TE288 on theassembly guides TE319 and over the
end of the set screw TE388 in the end of the assembling tool TE9.

(17) Install the two nuts TE387 on the set screw TE388 and tighten (Figure 732).

WARNING: WHEN COMPRESSED, THE FEATHERING SPRING ASSEMBLY

IS LOADED TO APPROXIMATELY 750 POUNDS (341 KG) FORCE.
ENSURE THE SAFETY OF PERSONNEL IN THE VICINITY
DURING ASSEMBLY PROCEDURES.

CAUTION: DO NOT EXCEED 10 FT-LB (34 N´•M) OF TORQUE WHEN

COMPRESSING THE SPRING.

(18) Turn the hex nut TE290 with the appropriate wrench to fully compress the
spring (230) (Figure 733).

APS6188

;s

Compressing the Feathering Spring Using Assembling Tool TE9

Figure 733

ASSEMBLY 61’10-17 Rev

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

CAUTION: DO NOT DAMAGE THE CYLINDER THREADS WHEN

INSTALLING THE CYLINDER CAP TE380.

(19) Apply lubricant CM12 to the threads of the cylinder cap TE380.

(20) Install the cylinder cap TE380 until snug (Figure 734).
NOTE: The cylinder cap is designed to accommodate two different size
cylinders. Make sure the cylinder cap threads are aligned with the
cylinder threads.

CAUTION: DO NOT APPLY SEALANT TO THE SCREW SHOULDER.

(21) Apply one drop of sealant CM21 to the threads of each of the first two
screws (180).
NOTE: Excessive sealant may inhibit weight movement.

APS6196

Assembly
Guides
TE319 Cylinder Cap TE380

Cylinder (70)

Installing the Cylinder Cap

Figure 734

ISSEMBLY fjl -1 0-1 7

 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

APS6189

First Two Screws

(180)

NOTE: For illustration

purposes, the cylinder
cap has been removed.

Positioning the Drilled Washer for Installation of the First Two Screws
Figure 735

APS6190

Position for the

final two screws

(180) visible
through the large
holes in the drilled
washer TE288.

Heads of the first two

screws are visible
NOTE: For illustration
through the smail holes purposes, the cylinder
in the drilled washer TE288. cap has been removed.

Positioning the Drilled Washer for Installation of the Final Two Screws
Figure 736

750
nSSEMBLY 61-10’17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(22) Install a screw (180) in each of the threaded holes that can be seen through the

large holes in the drilled washer TE288 (Figure 735).

(23) Torque the screws (180) in accordance with Table 801.

(24) Remove the assembly guides TE319.

(25) Loosen the hex nut TE290 until the drilled washer TE288 can be rotated past
the heads of the installed screws (180).
(26) Turn the drilled washer TE288 until the threaded holes for the remaining two
screws (180) can be seen through the large holes in the drilled washer TE288

(Figure 736).
(27) Tighten the hex nut TE290 to draw the drilled washer TE288 tight against the
heads of the two screws (180) already installed.

CAUTION: DO NOT APPLY SEALANT TO THE SCREW SHOULDER.

(28) Apply one drop of sealant CM21 to the threads of the final two screws (180).
NOTE: Excessive sealant may inhibit weight movement.

(29) Install a screw (180) in each of the threaded holes that can be seen through the

large holes in the drilled washer TE288 (Figure 737).

APS6191

Final Two Screws

(180)

NOTE: For illustration

purposes, the cylinder
cap has been
removed

Installing the Final Two Screws

Figure 737

61’1 0’17 Rev

 PROPELLER
HARTZELL MA:E~SEDNANCE MANU*L

(30) Torque the screws (180) in accordance with Table 801.

(31) Loosen the hex nut TE290 until the drilled washer is clear of the cylinder (70)
and the cylinder cap TE380.

(32) Remove the two nuts TE387 and the drilled washer TE288.

WARNING;: USE CARE WHEN HANDLING CYLINDERS WITH THE SPRING

ASSEMBLIES INSTALLED.

(33) Remove the cylinder (70) from the assembly tool TE9.

(34) For propellers using a stop weight Operate the weight (190) with a
screwdriver to check for full freedom of movement.

CAUTION: DO NOT DAMAGE THE CYLINDER THREADS WHEN

REMOVING THE CYLINDER CAP TE380.

(35) Remove the cylinder cap TE380.

NOTE: If possible, leave the cylinder cap in place on the cylinder until just
before installation as an additional safety precaution.
(36) Apply a HI-102 decal to the outside of the cylinder.
NOTE: Decal HI-102 was previously to be installed on the inside wall area of
the Spring Retainer. Due to reports of the decal coming loose and
interfering with the weights, its usage is no longer permitted in that
location.

nSSEMBLY 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

G. Piston and Cylinder Installation

(1) Install a new cylinder O-ring (380) at the base of the cylinder attachment
threads of the cylinder-side hub half.

(2) Install a new O-ring (360) in the groove in the small opening of the piston
(350).
(3) Install the piston (350) on the pitch change rod (370) with the small opening
toward the hub.

(4) Install the piston nut (340) on the pitch change rod (370).
(5) Torque the piston nut (340) in accordance with Table 801.

(6) Stack washers (330) (same number as were removed during disassembly)
on top of the pitch change rod (370).
NOTE: The number of washers determines the high pitch (start lock)
blade angle.
(7) Install the high pitch stop sleeve (320) over the pitch change rod (370) and
washers (330).
(8) Lubricate the outside of the piston (350) using lubricant CM12.

(9) Pour 2.25 fluid ounces (63.93 mi) of hydraulic oil CM157 into the piston (350).
(10) Apply a bead of sealant CM92 on the cylinder O-ring (380) where the
cylinder (70) and the hub (480) will meet at installation (Figure 738).
APS6198

O-ring (380)

Sealant CM92

/-t
~i3 j‘Hub(48~)

Applying a Bead of Sealant Where the Cylinder and Hub Meet

Figure 738

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(12) Apply lubricant CM12 to the cylinder (70) threads.

(13) Attach the cylinder torque wrench adapter TE153 to the cylinder (70) (Figure
739).
(14) For propellers with cylinder spring assemblies only Put the spring guide
(170) in the piston with the raised portion of the spring guide away from the
hub.

(14) Put the cylinder (70) over the piston (350).

(15) Insert the cylinder installation rod TE384 into the cylinder and press down to
push the high pitch stops apart, allowing the cylinder to drop into the
position to be started on the hub threads.
NOTE: The cylinder installation rod TE384 is not required for propellers
using-the retainer plate (200), i.e. dash five (-5) propellers.

APS2023A

Cylinder Torque Wrench

Adapter TE153

Cylinder (70)

j"

Installing the Cylinder with Cylinder Torque Wrench Adapter TE153

Figure 739

ASSEMBLY 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

CAUTION: DO NOT DAMAGE THE THREADS WHEN INSTALLING THE

CYLINDER.

(16) Start the cylinder (70) on the hub threads by hand.

NOTE: Make sure the cylinder threads are aligned with the hub threads.

(17) Torque the cylinder (70) according to Table 801.

(18) Remove the cylinder installation rod TE384, as applicable.

(19) Remove the cylinder torque wrench adapter TE153 from the cylinder (70).

61110117
 PROPELLER MPINUPIL
HARTZELL

APS6207

Spacer (520)

;7

Pitch Change Rod (370)

Installing the Spacer

Figure 740

APS6270

-‘Spring Guide (530)

Pitch Change Rod (370)

Installing the Spring Guide

Figure 741

61-10-17 Rev. 4 May/9 Page 756

 PROPELLER MAINTENANCE MANUAL
HIA RT Z E L L 117D

H. Hub Spring Installation

(1) Move the propeller to feather position.

WARNING: MAKE SURE SLINGS AND SUPPORTS ARE RATED UP TO 800

POUNDS (363KG) TO PREVENT PERSONAL INJURY.

(2) Using a sling, remove the propeller from the rotatable fixture on the
assembly table.
(3) Turn the propeller over and place on a support so the propeller mounting
flange is accessible.

NOTE: A sturdy barrel or drum with the rim well padded, may be used as a

support.
(4) For A-2273 hub spring assembly only slide the spacer (520) on the pitch
change rod (370) (Figure 740).
(5) For A-1586 hub spring assembly only slide the spring guide (530), with the
raised side up, on the pitch change rod (370) until the spring guide contacts the
hub (Figure 741).

.,,,,,,Y 61 -1 011 7
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 117D

APS6199

Installing the Small Diameter Feathering Spring on the Pitch Change Rod
Figure 742

APS6200

Installing the Large Diameter Feathering Spring on the Pitch Change Rod
Figure 743

758
ASSEMBLY 61’10-17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HIP~ RT Z E L L 117D

(6) Install the small diameter feathering spring (550) on the pitch change rod (370)
(Figure 742).
(7) Put the large diameter feathering spring (540) on the pitch change rod (370)
over the small diameter feathering spring (530) (Figures 742 and 743).

NOTE: For the A-1586 hub spring assembly only, make sure the large
diameter feathering spring (550) is positioned around the raised
surface of the spring guide (530).

CAUTION: THE RAISED SIDE OF THE SPRING RETAINER IS TOWARD THE

SPRINGS.

(8) With the raised side toward the springs, install the spring retainer (560) on the

pitch change rod (370) (Figure 744).

(9) Slide the spring retainer (560) on the pitch change rod (370) until the retainer is

resting against the springs (Figure 744).

APS6201
APS6202 The spring retainer (560) in position resting
against the springs.

~S\ h-

n
Positioning the spring retainer (560)
on the pitch change rod

Installing the Spring Retainer on the Pitch Change Rod

Figure 744

nssEMaLv 61’1 0’17

 PROPELLER MPINUP~L
HAPTZELL

APS6203

Spring Compressor Bolt TE284

Spring
Compressor
Nut
Spring Compressor Slide TE283

Propeller
mounting
bolt

Installing the Spring Compressor Assembly TE31

Figure 745

APS6204

TE31
Fully
Compressed

Hub Flange

Spring Compressor Slide Plate

Compressing the Feathering Springs with the Spring Compressor Assembly TE31
Figure 746

ASSEMBLY 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

CAUTION: SPRING COMPRESSOR ASSEMBLY TE31 IS DESIGNED FOR

USE WITH "R" OR "K" FLANGE PROPELLERS AND WILL NOT
ENGAGE THE SMALLER DIAMETER "L" FLANGE MOUNTING
STUDS.

NOTE: A new smaller I.D. thread may be fabricated to take the place of
bolt with a

the spring compressor bolt TE284, or an "R" or "K" flange style stud may
be used for assembly purposes only.

(10) Install the spring compressor assembly TE31 on the propeller mounting flange
(Figure 745).
NOTE: The spring compressor assembly TE31 has six holes to clear the
studs already installed.

(a) Center the spring compressor slide TE283 on the spring retainer (560) in
the propeller hub bore and align the spring compressor bolts TE284 with
the holes in the hub mounting flange.

NOTE: The spring may be compressed using only two of the three
spring compressor bolts TE284 supplied, positioned
approximately 180 degrees apart.
(b) Install the nuts on the spring compressor bolts TE284

NOTE: The nuts should be positioned close to the heads of the spring
compressor bolts TE284.

(c) Turn the propeller mounting bolts into the ends of the spring compressor
bolts TE284 until tight (Figure 746).

NOTE: The spring compressor bolts TE284 have both ID and OD

threads.

WARNING: WHEN COMPRESSED, THE FEATHERING SPRING ASSEMBLY

IS LOADED TO APPROXIMATELY 1000 POUNDS (454 KG)
FORCE. ENSURE THE SAFETY OF PERSONNEL IN THE
VICINITY DURING ASSEMBLY PROCEDURES.

CAUTION: TIGHTEN THE SPRING COMPRESSOR NUTS EVENLY TO

PREVENT BINDING.

(11) Compress the springs (540, 550) by evenly tightening the spring compressor
nuts (Figure 746).

NOTE: Tightening the spring compressor nuts will move the spring retainer
(560) beyond the groove in the pitch change rod (370) and allow the
installation of the keeper (570).

61-10-17
 PROPELLER
nARTZELL M*:NI~NANCE MARUAL

(12) Cut the keeper (570) at the notches and grind off the resulting burrs.

(13) Place the keeper (570) halves in the groove in the pitch change rod (370)
(Figure 747).
NOTE: Using a small amount of grease will keep the keeper halves in place
until the spring is decompressed.

CAUTION: MAKE SURE THE KEEPER DOES NOT DISLODGE FROM THE
PITCH CHANGE ROD GROOVE DURING SPRING
DECOMPRESSION.

(14) Decompress the springs by evenly loosening the spring compressor nuts.
(15) Remove the spring compressor assembly TE31 from the propeller mounting
bolts.

(16) Install the shaft plug (650) into the engine-side hub half.
(a) Install a new shaft plug OD O-ring (670) on the shaft plug.
(b) Install a new shaft plug ID O-ring (680) in the shaft plug.
(c) Install a new shaft plug (660) in the engine-side hub half center bore.

NOTE: When installing, hold the shaft plug by the removal feature
(refer to Figure 509).

APS6206

Keeper (570)
Pitch Change
Rod Groove

Spring
Retainer (550)

Installing the Keeper on the Pitch Change Rod

Figure 747

ASSEMBLY 61’10-17
 PROPELLER MAINTENANCE MANUAL
H~RTZ ELL 117D

(This page is intentionally blank)

763
ASSEMBLY 61 ’1 0’ 1 7 Rev. 4 May/9 Page
 PROPELLER
HARTZELL MA:N1~NANCE M~NUPIL

APS6237

Feather Total number of washers, both inside and outside the

Stop
Stop Screw (300) sleeve, sets the feather angle.
(280)

Washers inside the sleeve

sets high pitch angle.

Washer
(29ai’ Feather High High
Pitch Change
Adj ust Pitch Rod
Pitch
Washer stop Stop (370)
(310) Sleeve Washer
(320) (330)

*NOTE: In some propellers, the proper low pitch blade angle cannot be set even
though the high pitch stop sleeve and low pitch stop are correctly
positioned. This is due to the threaded low pitch stop bottoming in the
cylinder. In this situation, add washer(s) (290) as required to reposition
the low pitch stop between bottoming in the cylinder and a thread
minimum engagement when correct low pitch blade angle is obtained.

Parts for Adjusting the Pitch Angle

Figure 748

764
61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

i. Setting the Blade Angles (Refer to Figure 748)

NOTE 1: Grease may be used between the washers (310) and the feathering stop
(300) for ease of removal if blade angle adjustment is required. Washers
that fall into the propeller may be retrieved with a magnet.

NOTE 2: When setting feather or high pitch angles, the approximate degree of
movement achieved per washer is:
B-3851-0532 or A-2435-1 washer equals 1.5 degree
B-3851-0563 or A-2435 washer equals 3 degrees
(1) Install washers (310) and the feathering stop (300) on top of the high pitch
stop sleeve (320) using feathering tool TE383.
NOLE: The total number of washers, both inside and outside the sleeve,
sets the feather angle.
(2) Tighten the feathering tool TE383 into the pitch change rod (370) until snug.

1 (3) Check the feather blade angle at the reference blade radius previously
marked (Figure 749).
(a) If feather angle adjustment required, loosen the feathering tool TE383
is
and remove the feather stop (300) and washer(s) (310) by skewing the
tool sideways.
(b) Remove or add washer(s) (310) as needed.

NOTE: Add washers under the feather stop (300) to increase the
feather angle. Remove washers from under the feather stop to
decrease the feather angle.

APS0336

Checking the Feather Angle With a Hand Held Protractor

Figure 749

~SSEMBLY 61’1 0-17

 PROPELLER
HARTZELL MA:N~NPINCE MANU~L

(c) Install the washer(s) (310) and feather stop (300) with the feathering tool
TE383

I (d) Check the feather blade angle at the reference blade radius previously
marked.

1 (4) When the feather angle is correct, apply air pressure to move the propeller
into high pitch position, with the feathering tool TE 383 still installed.
NOTE: The stop unit pins (140) or the weight (190) will click into place
when the propeller is moved to high pitch.

(5) Release the air pressure to allow the high pitch stop pins (140) or the weight
(190) to hold the propeller at high pitch.

I (6) Check the high pitch

Refer to the
blade angles.
Type Certificate Data Sheet or the Hartzell Application
Guide for the propeller high pitch angle.

CAUTION: IF HIGH PITCH REQUIRESADJUSTMENT, CONTROL THE

BLADE ANGLE BY ADDING AIR PRESSURE TO THE
PROPELLER TO MOVE AND HOLD THE PROPELLER OFF
THE HIGH PITCH STOP LATCHES.

(a) If high pitch angle adjustment is

required, loosen the feathering tool
TE383 and remove the feather stop (300), washer(s) (310), high pitch stop
sleeve(320), and washers (330) from the pitch change rod (370) by
skewing the tool sideways.

CAUTION: AFTER THE FEATHER ANGLE HAS BEEN SET, THE TOTAL
NUMBER OF WASHERS (310, 330) MUST BE MAINTAINED.
CHANGING THE POSITIONS OF THE WASHERS TO
ACHIEVE HIGH PITCH WILL NOT EFFECT THE FEATHER
ANGLE. ADDING OR REMOVING ANY WASHERS (310, 330)
THAT HAVE ALREADY BEEN INSTALLED WILL CHANGE
THE FEATHER AND HIGH PITCH ANGLES.

(b) To decrease high pitch angle, move high pitch adjust washer(s) (330) from
between the high pitch stop sleeve (320) and the pitch change rod (370) to
between the high pitch stop sleeve (320) and the feather stop (300).
(c) To increasehigh pitch angle, move feather adjust washer(s) (310) from
between the high pitch stop sleeve (320) and the feather stop (300) to
between the high pitch stop sleeve (320) and the pitch change rod (370).

ASSEMBLY 61’10’17 RevP7aSAep~SI

 PROPELLER MAINTENANCE MANUAL
HA,RTZ ELL 117D

(d) Using the feathering tool TE383, reinstall the parts stack.

NOTE: The parts stack includes: washers (330), high pitch stop sleeve
(320), washers (310), feather stop (300), and stop screw (280).
(e) Release the air pressure to allow the high pitch stop pins (140) or the
weight (190) to hold the propeller at high pitch.

I angles.
(f) Check the high pitch blade

(g) Repeat step 4.1.(6) until angles are correct.

CAUTION: TO AVOID DAMAGE TO THE PROPELLER COMPONENTS, BE

SURE THE AIR PRESSURE IS APPLIED BEFORE REMOVING
THE FEATHERING TOOL TE383.

(7) When angles are correct, remove the feathering tool TE383.

NOTE: When removing the feathering tool TE383, make sure the washers
(310) and the feathering stop (300) stay in place on top of the high
pitch sleeve (320).
(8) Using magnet, remove only the feathering stop (300) from the washer
a

stack on top of the high pitch sleeve (320).

(9) Install the feathering stop (300) on the stop screw (280).
NOTE: The rubber lock on the threads of the stop screw makes it difficult to
put the feathering stop on the stop screw.
(10) Apply one drop of thread locking compound CM21 to the threaded end of the
1
stop screw (280).
(11) Using the T-handle wrench TE381, install the feathering stop (300) and the
stop screw (280) through the top of the cylinder (70) into the pitch change

rod (370), making sure that the washers (310) are still in position on top of
the pitch change rod (370).
A small amount of lubricant CM12 the head of the will hold
I NOTE: on screw

the screw to the T-handle wrench long enough to guide the screw
and the feathering stop into the threaded hole in the pitch change
rod.

(12) Tighten the stop screw (280) with the T-handle wrench TE381. Maintain a

minimum screw engagement of seven threads.

(13) Release the air pressure to allow the high pitch stop pins (140) or the weight
(190) to hold the propeller at high pitch.

nsslusLY 61 -1 0’17 RevP7agAep~

 PROPELLER
HA RTZ E L L MA:N1~EDNANCE MANUAL

1 (14) Re-check the high pitch blade angles.

CAUTION: IF HIGH PITCH REQUIRES

ADJUSTMENT, CONTROL THE
BLADE ANGLE BY ADDING AIR PRESSURE TO THE
PROPELLER TO MOVE AND HOLD THE PROPELLER OFF
THE HIGH PITCH STOP LATCHES.

(a) Ifhigh pitch angle adjustment is required, remove the stop screw (280),
feather stop (300), feather adjust washer(s) (310), high pitch stop sleeve
(320), and high pitch adjust washers (330) from the pitch change rod
(370).

CAUTION: AFTER THE FEATHER ANGLE HAS BEEN SET, THE TOTAL
NUMBER OF WASHERS (310, 330) MUST BE MAINTAINED.
CHANGING THE POSITIONS OF THE WASHERS TO
ACHIEVE HIGH PITCH WILL NOT EFFECT THE FEATHER
ANGLE. ADDING OR REMOVING ANY WASHERS (310, 330)
THAT HAVE ALREADY BEEN INSTALLED WILL CHANGE
THE FEATHER AND HIGH PITCH ANGLES.

(b) To decrease high pitch angle, move high pitch adjust washer(s) (330) from
between the high pitch stop sleeve (320) and the pitch change rod (370) to
between the high pitch stop sleeve (320) and the feather stop (300).
(c) To increase high pitch angle, move feather adjust washer(s) (310) from
between the high pitch stop sleeve (320) and the feather stop (300) to
between the high pitch stop sleeve (320) and the pitch change rod (370).

(d) Using the T-handle wrench TE381, reinstall the parts stack.
NOTE: The parts stack includes: high pitch adjust washer(s) (330), high
pitch stop sleeve (320), feather adjust washers (310), feather
stop (300), and stop screw (280).
(15) Tighten the stop screw (280)
with the T-handle wrench TE381. Maintain a
minimum screw engagement of seven threads.
(16) When the high pitch angle is correct, install a new low stop O-ring (60) in
the top of the cylinder (70).

CAUTION: THE LOW PITCH STOP MUST BE TURNED A MINIMUM OF

FIVE THREADS INTO THE CYLINDER.

(17) Install the low pitch stop (50) in the top of the cylinder (70).

I If necessary, refer to Figure 501, Low Stop Dimensions in the Check

chapter of this manual to determine the appropriate low stop for the
blade angle required.

PISSEMBLY 61-10-17 RevqasAep~

 PROPELLER MAINTENANCE MANUAL
H19 RT Z c L L 117D

(18) Check the low pitch stop angle.

(a) Rotate the blades to the low pitch position and set the propeller pitch in
accordance with the aircraft Type Certificate Data Sheet and/or the
Hartzell Application Guide.

(b) Adjust the low pitch angle with the low pitch stop (50).
NOTE: If adjusting the low pitch stop does not change the blade angle,
make sure that the slots in the preload plate are not interfering
with the pitch angle.
1 To increase pitch, turn the low pitch stop (50) clockwise.
2 To decrease pitch, turn the low pitch stop (50) counterclockwise.

CAUTION 1: BE SURE AIR PRESSURE IS APPLIED BEFORE

REMOVING THE STOP SCREW (280).

CAUTION 2: ADD WASHERS BETWEEN THE STOP SCREW (280)

AND THE FEATHER STOP (300) ONLY.

3 If low pitch cannot be obtained because the low pitch stop (50)
bottoms out or exceeds the five thread engagement minimum,
washers (290) may be added or removed between the stop screw
(280) and the feather stop (300) only.
NOTE: This will not change the feather thigh pitch) blade angle.
(19) Apply sealant CM21 where the low pitch stop (50) meets the cylinder (70).
(20) Hold the low pitch stop (50) from turning and install the check nut (30),
(21) Torque the check nut (30) in accordance with Table 801.

NOTE: Be sure to prevent the low pitch stop from moving when torquing the
check nut.

(22) Apply hydraulic thread locking compound CM134 to the threads of the air
valve (40).

NOTE: To reduce the required time between pressure checks, use primer
CM127 on the threads of the air valve (40) before applying hydraulic
thread locking compound CM134.
(23) Install the air valve (40) in the end of the low pitch stop (50) until tight.
NOTE: The air valve has tapered pipe threads. Turn the air valve into the low
pitch stop until tight.

61-10-17
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 1170

(24) Install the counterweights.

(a) Refer to the Hartzell Application Guide for the correct counterweight for
the propeller.
(b) Refer to Hartzell Manual 133C, Aluminum Blade Overhaul (61-13-33), for
counterweight installation.
(25) Check the clearance between the counterweights and the hub bolts.

NOTE: If necessary, loosen the nuts and turn the bolts in the hub to allow
the maximum clearance between the bolts and the
counterweights.

CAUTION: ROTATE TWO-WAY PROPELLERS SLOWLY TO BE SURE THE

COUNTERWEIGHTS CLEAR THE CYLINDER.

(26) Charge the propeller with air

NOTE: Hartzell Air Pressure Gauge Kit TE77 is available for charging the
propeller with air.

(a) If the label indicating

the proper charge pressure for the propeller is
missing or unreadable, refer to Chapter 800, Fits and Clearances in this
manual to determine the proper pressure.

(b) Using proper control, charge the cylinder with dry air or nitrogen.
NOTE: Nitrogen is the preferred charging medium.

(c) Apply solution CM122 to the air valve (40) pin to check for air leaks.

(d) Apply solution CM122 where the air valve (40) and the low pitch stop
(50) meet to check for air leaks.
(e) Apply solution CM122 where the low pitch stop (50) and the check nut
(30) meet to check for air leaks.
(f) Recheck the air charge pressure in the cylinder to be sure there are no air
leaks.

1 If primer CM127 was not used on the air valve (40), allow twelve
hours between pressure checks.

2 If primer CM127 was used on the air valve (40), allow two hours
between pressure checks.

ASSEMBLY 61’10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(27) Install the lubrication fittings.

(a) Install the lubrication fittings (1980) in the hub and torque in
accordance with Table 801.

NOTE: Leave one lubrication fitting out for leak testing of the hub.
(b) While the hub is installed on the propeller test stand, actuate the
propeller to lowpitch and apply solution CM122 to the lubrication fitting
hole (Figure 750).
(c) Cycle the propeller to purge air trapped in the hub. Any indication of air
exiting the hub requires troubleshooting of the propeller assembly.
(d) After leak check, install the remaining lubrication fitting (1980) in hub and
torque in accordance with Table 801.

APS2016

Hub Leak Check

Figure 750

ASSEMBLY 61 ’1 0’1 7
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

5. Blade Track

Check the blade track. The blade track of all aluminum blades must be within 1/8 inch of
each other (Figure 751).

6. Propeller Lubrication

Lubricate thepropeller in accordance with Hartzell Standard Practices Manual 202A,

Chapter 400, Propeller Lubrication.

7. Static Balance

Perform static balance of

propeller in accordance with Hartzell Standard Practices
Manual 202A, Chapter 600, Static and Dynamic Balance.

APS6275

i-
Checking Blade Track
Figure 751

61-10-17
 PROPELLER MAINTENANCE MANUAL
HI1~ RTZ c L L 117D

(This page is intentionally blank.)

773
ASSEMBLY 61 ’1 0’1 7 Rev. 4 May/9 Page
 PROPELLER
HARTZELL MA:N1:E~NPINCE
D711LAUNIPM

APS6252
APS6253

j
~‘´•´•r´•´•´•´•.

CM92
950

980

970
Spring Gap
0.280 0.290 inch
(7.11 7.37 mm

910 IzM~J \1 ~990

920
M92
930
940 960

Damper Assembly
Figure 752

ASSEMBLY 61’10’17 Rev. 4 May/9 Page 774

 PROPELLER MAINTENANCE MANUAL
H 49 RT Z E L L 117D

8. Damper

CAUTION: USE WITH A-2476-16 SPINNER MOUNTING KIT ONLY.

A. Damper Assembly
(1) Put the eight hex head spacer tubes (910) head down on a flat surface.

(2) Assemble the springs (920), metal washer (930), and fiber washer (940) as

shown in Figure 752.

(3) Position the damper weight (950) in place over the springs (920), washers
(930) (940), and hex head spacer tubes (910).
NOTE: The damper weight/friction disc mating surface should be positioned
away from the hex head spacer tubes.

(4) Install the eight silicone grommets (960) in place in the damper weight (950).
(5) Place the friction disc (970) on the silicone grommets (960).
(6) Put the support plate (980) in place (Figure 752).
(7) Apply sealant CM21 to the threads of the screws (990).
(8) Install the eight screws (990) and torque the screws (990) evenly around the
assembly, in accordance with Table 801

CAUTION: THE SPRING GAP MUST BE BETWEEN 0.280 AND 0.290 INCH
(7.11 7.37 MM) IN ALL EIGHT PLACES.
(9) Measure the spring gap. Maintain a spring gap of 0.280 0.290 inch (7.11
7.37 mm) in all eight places. To adjust the spring gap, replace the fiber washer
(940) or the hex spacer tube(s) (910) (Figure 752).

NOTE 1: The fiber washers vary in thickness. Measure the thickness of a

variety of washers and choose a washer that will bring the spring gap
within tolerance.

NOTE 2: The spacer tubes vary slightly in length. Selecting a spacer tube with
the specific length needed will bring the spring gap within tolerance.
(10) Apply a bead of sealant CM92 between the damper weight (950) and the
support plate (980) on both inboard and outboard sides of the support plate
(Figure 752).
(11) Apply decals OOSCT and TOR-2830 to the outboard surface of the damper
weight.
(12) Use the A-2276-16 spinner mounting kit when installing the C-1576 damper
assembly (Figure 753).
NOTE: Remove four of the 8-3834-0663 washers from the A-2276-16
spinner mounting kit when installing the C-1576 damper assembly.
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

APS6254

B-3834-0663
Washer

B-2043-1 iT~I ~llltl A-1584

Nut Cln~lli Hex Head Bolt

C-1576’Damper
Assembly

A-2246-5
A-2246-4
Spacer
Spacer

Damper Installation
Figure 753

776
ASSEMBLY 61’10’17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

CONTENTS

1. Torque Values 803

2. Blade Tolerances 805

3. Air Charge Pressures 806

FIGURES

Determining Torque Value

of a Standard Torque Wrench With Adaptor Figure 801 803

TABLES

Torque Values Table 801

Blade Tolerances Table 802 805

Air Charge Pressure (Decal CHP-221) ..............Table 803 807

Air Charge Pressure (Decal CHP-226) Table 804 807

Air Charge Pressure (Decal CHP-227) ............Table 805 807

Air Charge Pressure (Decal CRP-323W) ..............Table 806 807

Air Charge Pressure (Decal CPR-41, CPR-33, CAU-002)......Table 807 807

Air Charge Pressure (Decal CPR-22, CPR-22A, CAU-005) ...Table 808 807

Air Charge Pressure (Decal CPR-700, CAU-003) Table 809 807

Air Charge Pressure (Decal CPR-27, CAU-006) Table 810 807

Air Charge Pressure (Decal CRP-104, CAU-004) Table 811 807

Air Charge Pressure (Decal CPR-62) Table 812 ..............807

FITS AND CLEARANCES 61’1 0’1 7 RevP7aSABp~l

 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 117D

(This page is intentionally blank.)

I 61-10-17 Page 802

Rev. 7
Apr/Ol
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 1170

1. Torque Values

Threaded fasteners and hardware are the weakest components in an assembly.

Vibration improperly tightened fastener to fail in a matter of minutes.
can cause an
and can
Proper tension in a fastener depends on a variety of known load factors
influence fastener service life. Proper tension is achieved by application of measured
torque.
Accurate wrenches and professional procedures will result in precision tensioning.
torque wrench, the equation in Figure 801 to
When adaptor is used with
an a use

determine the torque value.

APS212

Torquing Adaptor
Standard Torque Wrench

1.00 foot 7’ 0.50 foot

(304.8 mm) (152.4 mm)

torque wrench reading

tactual toraue reauired) x ttoraue wrench length)
_

to achieve required
(torque wrench length) (length of adaptor)
actual torque

EXAMPLE:
reading on torque
wrench with 6-inch
100 Ft-Lb (136 N.m~ x 1 ft (304.8 mm~
66.7 Ft-Lb (152.4 mm) adaptor
I 1 ft (304.8 mm) 0.50 ft (152.4 mm)
(90.1 N´•m) for actual torque of
100 Ft-Lb (136 N´•m)

Determining Torque Value of aStandard Torque Wrench with Adaptor

Figure 801

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZ E LL 117D

CAUTION: TORQUE VALUES ARE BASED ON NON-LUBRICATED THREADS,

UNLESS OTHERWISE STATED IN TABLE 801.
NOTE: Torque tolerance is 10 percent unless otherwise noted. Refer to the
assembly chapter of this manual when wet torque is designated.
item Part Torque Torque Torque
No. Number Description Ft-Lb In-Lb N´•m

101 A-2405-2 Nut, spinner, cap side 15 20 180 240 20 27

30 A-2405-( )1 Nut, spinner, cylinder side 15 20 180 240 20 27

40 8-1938 Valve, air Torque until tight and no air leaks from around valve.

80 B-2423-1 Cylinder 120 150 wet 1440 1800 wet 163 203 wet

8-2452-1 Cylinder 120 150 wet 1440 1800 wet 163 203 wet

100 1 B-3841-( )1 Screw, high pitch stop bracket 4.2 50 5.7

180 A-1595-( )1 Screw, cylinder spring assembly 4 48 5.4

300 A-3205 Screw, stop 10-15 120-180 14-20

350 B-3807 Nut, piston 15-25 180-300 20-34

380 8-2491-( )1 Pitch change rod fitted to fork 40 wet 480 wet 54 wet

B-4505-( )1 Pitch change rod fitted to fork 40 wet 480 wet 54 wet

580 A-2431 Hub clamping bolt 20 22 240 264 27 30

590 A-2432 Hub clamping bolt 20 22 240 264 27 30

610 A-2043-1 Hub clamping nut 20 22 240 264 27 30

990 A-1 578 Screw, damper 8-10 96-120 11-14

A-2038-6 Screw, damper 8-10 96- 120 11-14

1980 A-0279 Lubrication Fitting 4.2 50 5.7

3110 8-3368 Preload lock nut 10 120 14

4040 A-2044 "F" Flange Mounting 70 80 840 960 95 108

Except( )HC-C3YF-5 80-90 960-1080 108- 122

A-3257 "N" Flange Mounting 90 100 1080 1200 122 136

1 14080 1 A-2069 "K" "R" Flange Mtg. 60 70 720 840 81 95

Except Lycoming 10 720 90 100 1080 1200 122 136

A-2498 "L" Flange Mounting 50 600 68

Torque Values
Table 801

804
FITS AND CLEARANCES 61-10-17 Rev. 6 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HP~ RT Z E L L 1170

2. Blade Tolerances

Tolerances Affectina the Blades

In-and-Out Blade Play None allowed

End Play (leading edge to trailing edge) See Note below.

Fore-and-Aft (Face to camber) See Note below.

Radial Play (pitch change) 0.5 degree

measured at
reference station

Blade Track 0.063 inch (1.60 mm)

or 0.125 inch (3.3 mm) total

Blade Pitch Setting Tolerance 0.2 degree

Between Blades at Low Pitch

NOTE: Blades are intended to be tight in the propeller, however, slight

movement is acceptable if the blade returns to its original position when
released. Blades with excessive movement, or that do not return to their
original position when released may indicate internal wear or damage
that should be referred to an authorized propeller repair station.

Blade Tolerances
Table 802

FITS AND CLEARANCES4 May/99

 PROPELLER
HARTZELL MA~NPINCE MANU~L

3. Air Charge Pressures

A. Basic pressures

(1) All four-blade compacts, refer to Table 807.

(2) All propellers with no counterweights and no spring, refer to Table 803.

(3) All
propellers with no counterweights and an "S" spring, refer to Table 804.
Except HC-E2YR-2RBS()- Table 805
(4) All propellers with counterweights and no spring, refer to Table 806.

Except: BHC-C2YF-2CKF/FC8459-8R(B) or

BHC-C2YF-2CLKF/FJC8459-8R(B) when installed on the Piper

PA-34-200T with Continental TSIO-360-E(B) or LTSIO-360-(B)
engines Refer to Table 812.

NOTE: For BHC-C2YF-2CKF/FC8459-8R(B) or BHC-C2YF-2CLKF/

FJC8459-8R(B) model propellers that have been upgraded
with the installation of a feather assist spring Refer to
Table 808.

NOTE: Propeller models indicated by in the exceptions below have a "U"

spring installed, which is not indicated in the part number.

Except: HC-C3YF-5F* Refer to Table 810

HC-C3YN-5A* Refer to Table 807
PHC-13YF-2AL* Refer toTable 807
PHC-J3YF-2(F) Refer to Table 811
I All four-blade compacts Table 807

(5) All propellers with counterweights and a "T" spring, refer to Table 807.

Except: HC-E3YR-2ATF on Fuji Model 700 Commander Refer to Table 809.

FITS AND CLEARANCES 61 -1 0’17

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(6) All propellers with counterweights anda "U" spring, refer to Table 807.

I Except: See Note under 3.A.(4), above.

(B)HC-C2VF-2(C)(L)(K)U( Refer to Table 808.

PHC-C3YF-2(L)KUF Refer to Table 808.

PHC-H3YF-2KUF when installed on the Avia Accord

Refer to Table 808.

PHC-C3YF-2U F/FC7663( )-2R when installed on the

Beech 95-(A,B)55(A,B) Baron with IO-470-L engines
Refer to Table 808.

HC-C2YL-2CU F/FC7663-4 when installed on the Piper PA-23,

PA-23-16O with 0-320 engines Refer to Table 808.

HC-C3YR-2UF/FC8468( )-6R when installed on the Aero

Commander 5008, 500S, 500U with Lycoming
IO-540-B1(A,C)5, IO-540-E1(A,B)5, or TIO-54O-J2B(D) engines
Refer to Table 808.

HC-C2YF-2CU F/FC8468( )-3 when installed on the Cessna

31 O(A,B,C,D,E,F,G,H), or E31OH, with 0-470-M or IO-470-D engines
Refer to Table 808.

HC-C2YK-2CUF/FC7666C(B)-4 when installed on the Beech 95,

B95, B95A, D95A, or E95 Travel Air with 0-360( and 10-360(
engines Refer to Table 808.

FITSPINDCLEPIRANCES 61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 117D

"F OC I P.S.I. Bar "F "C I P.S.I. Bar "F "C I P.S.I. Bar
100 38 1 188 13.1 1 1 100 38 1 53 3.7 1 1 100 38 1 86 6.0
90 32 1 185 12.9 70 21 1 50 3.5 1 1 90 32 1 84 5.8
80 27 1 182 12.7 40 4 1 47 3.3 1 1 801 27 1 82 1 5.7
70 21 1 178 12.4 1 1 10 -12 1 44 3.0 1 1701 21 1 80 1 5.6
60 16 1 175 12.2 -20 -29 1 42 2.9 1 1 60 16 1 78 5.4
10 172 12.0 50 10 1 76 5.3
Air Charge Pressure
40 1 4 1 1 4 7 5.2
30 1 1 165 11.5 1 (Decal CHP-226) 1 30 1 1 72 5.0
-7 1 162 1 11.3 Table 804 1 20) -71 70 1 4.9
-12 1 159 1 11.1 1 1 10 -12 1 68 1 4.7
0 -18 1 154 10.7 1 I"F "C I P.S.I. Bar 0 -18 1 66 4.6
-10 -23 1 152 10.6 -10 -23 1 64 4.5
-20 100 38 74 5.2
-29 1 149 10.4 -20 -29 1 62 4.3
-30 70 21 70 4.9
-34 1 146 10.2 -30 -34 1 60 4.2
40 4 66 4.6
AirCharge Pressure 1 101 -121 62 1 4.3 1 Air
Charge Pressure
(Decal CHP-221) 1-201 -29 1 58 1 4.0 1 (Decal CRP-323W)
Table 803 Air Table 806
Charge Pressure
(Decal CHP-227)
Table 805
OF OC I P.S.I. Bar OF OC I P.S.I. Kpa
100 to 70 38to21 1 41 2.9 1 1100to70 38to21 1 22 152
40 to 70 4 to 21 1 38 2.6 1 j 40 to 70 4 to 21 1 17 117
0 to 40 -18to4 1 36 2.5 1 I 0to40 -18to4 1 14 97
-30 to 0 -34to-181 33 2.3 -30 to 0 -34 to -18 1 9 62

Air
Charge Pressure Air
Charge Pressure
(Decals CPR-41, CPR 33, CAU-005) (Decals CPR-22, CPR-22A, CAU-005)
Table 807 Table 808

OF "C I P.S.I. Bar OF "C IP.S.I. Kpa

100to701 38to21 1 66 4.6 100 to 70 38to21 1 27 186
40 to 70 4 to 21 1 62 4.3 40 to 70 4 to 21 1 25 172
0 to 40 -18to4 1 58 4.0 0 to 40 -18to4 1 24 165
-30 to 0 -34to-181 53 3.7 -30 to 0 -34 to -18 1 22 152

AirCharge Pressure Air

Charge Pressure
(Decal CPR-700, CAU-003) (Decal CPR-27, CAU-006)
Table 809 Table 810

"F OC P.S.I. Bar

"F "C P.S.I. Kpa
100 38 104 7.2
70 21 1 98 6.8 100 to 701 38 to 21 1 62 427
40 4 1 92 6.4 40 to 70 4 to 21 1 57 393
0 to 40 -18 to 4 54 372
-20 -29 1 81 5.6 -30 to 0 -34 to -18 1 49 338

Air Charge Pressure AirCharge Pressure

(Decal CRP-104, CAU-004) (Decal CPR-62)
Table 811 Table 812

FITS AND CLEARANCES 61-10-17 Rev. 7 Apr/OlPage 808

 PROPELLER MAINTENANCE MANUAL
H~ RT Z E L L 117D

CONTENTS

1. Minimum Facility and Tooling Requirements 903

A. Tooling 903

B. Facilities 903

2. Special Tools 903

A. Special Tools 903

B. Listings 903

SPECIAL TOOLS, FI~URES, FIND E(IUIPMENT 61 -1 0’1 7

 PROPELLER MANUAL
HA RTZ E L L MA:N:7EDNANCE

(This page is intentionally blank.)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT 61’1 0’1 7 Rev. 4 May/9 Page 902
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

1. Minimum Facility and Tooling Reauirements

A. Tooling
Propeller repair stations approved to overhaul Hartzell propellers are expected
to

blade tables for blade inspection and

possess precision fixtures, tools, and
rework. Except as specifically required in this manual, locally fabricated tooling is
acceptable for most repair and inspection operations.
B. Facilities

(1) Grinding, plating, and painting of propeller components have the potential
for health and safety hazards beyond that of other areas of a typical
workshop. It is expected that such areas be in compliance with industry
standards and governmental regulations concerning occupational safety
and health, as well as environmental protection.

(2) Workshop areas need to be segregated to prevent contamination. Separate

areas designated for cleaning, inspection, painting, plating, and
should be
assembly. Propeller balancing must be performed in a draft free area.

2. Special Tools

NOTE: responsibility of the repair station to determine the special tooling

It is the
required for the propeller they are servicing or overhauling. The applicable
overhaul manual and the numerical index of Manual 165A provide necessary
information. Hartzell maintains no exact list of tools required for specific
models of propellers or levels of service.

A. Special Tools

Hartzell Tool and Equipment Manual 165A contains a listing of special tools
available from Hartzell. The manual also includes vendor lists for other specialty
tooling not sold by Hartzell,
B, Listings
The Introduction section of Manual 165A provides information about what is
included in the listings and how to quickly locate tools.

SPECIP.L TOOLS. FIXTURES,*hlO EOUIPYENT

61 -1 0-1 7
 PROPELLER MAINTENANCE
HARTZELL D711LAUNAM

(This page is intentionally blank.)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT 61’1 0’ 1 7 Rev. 4 May/9 Page 904
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

CONTENTS

1. Introduction 1005

A. General 1005

B. Using the Illustrated Parts List 1005

C. Propeller Assemblies Configured with a De-ice System 1005

2. The Illustrated Parts List 1006

A. Detailed Parts List 1006

B. Revisions

3. F and N Flange Studs.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´• 1008

4. Pitch Change Knob

CYLINDER SPRING ASSEMBLIES 1021

PROPELLER ASSEMBLIES 1026

SPINNER ASSEMBLY PARTS 1241

I SPINNER MOUNTING KIT PARTS 1248

TWO WAY -2 PROPELLER ASSEMBLIES

1026
(B)HC-C2VF-2B(D,E)(F)
1028
(B)HC-C~YFPC(D)(F)
(B)HC-C~YFPCDUF 1030
1032
(3 or D)HC-C2YF-2CH(r)
1034
(B or D)HC-C2YF-2CHU(F)
BHC-C2YF-2CKF 1036

BHC-C2YF-2CLK(F)
BHC-C2YF-2C(L)KU(F) 1040
EXCEPT CESSNA 310A-H 1042
(B)HC-C2YF-2CUF
HC-C2YF-2CUF CESSNA 310A-H 1044
1046
(B)HC-C2VF-2RB(D,E)(F)
1048
(C or D)HC-C2YF-2RB(D,E)(F)
HC-C2YK-2B(D,E)(F) 1050

HC-C2YK-2CD(F)
HC-C2YK-2CDUF 1054
1 056
HC-C2YK-2CE(F)
HC-C2YK-2CEUF EXCEPT PIPER PA44-180 1058
HC-C2YK-2CEUF PIPER PA44-180 1060

HC-C2YK-2CG(F) 1062

HC-C2YK-2CLE(F) 1064

HC-C2YK-2CLEUF EXCEPT PIPER PA44-180 1066

HC-C2YK-2CLEUF PIPER PA44-180 1068

HC-C2YK-2CLG(F) 1070

HC-C2YK-2C(L)GUF 1072
HC-C2YK-2CUF EXCEPT BEECH TRAVELAIR STC#SA00722CH 1074
HC-C2YK-2CUF BEECH TRAVELAIR STC#SA00722CH 1076

ILLUSTRATED PARTS LIST 61’1 0’1 7

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

TWO WAY -2 PROPELLER ASSEMBLIES (CONT’D~

HC-C2YK-2RB(D,E)(F) 1078
HC-C2YL-2CUF PIPER PA23 EXCEPT APACHE 1080
HC-C2YL-2CUF PIPER PA23 APACHE 1
HC-C2YL-2RB(F) 1084
HC-C2YR-2B(D,E)(F) 1086
HC-C2YR-2C(D)(F) 1088
HC-C2YR-2CDUF 1090
HC-C2YR-2CEUF EXCEPT PIPER PA44-180 1092
HC-C2YR-2CEUF PIPER PA44-180 1094
HC-C2YR-2CLEUF 1096
HC-C2YR-2CUF 1098
HC-C2YR-2RB(D,E)(F) 1100
HC-E2YK-2B(F) NO COUNTERWEIG HTS 1 1 02

HC-E2YK-2B(F) WITH COUNTERWEIGHTS 1104

HC-E2YK-2RB(F) NO COUNTERWEIGHTS 1106
HC-E2YK-2RB(F) WITH COUNTERWEIGHTS 1108
HC-E2YK-2RBS(F)
HO-E2YL-2B(L)(F) NO COUNTERWEIGHTS 1112
HC-E2YL-2B(L)(F) WITH COUNTERWEIGHTS 1114
HC-E2YL-2B(L)S(F) 1116
HC-E2YR-2(F) 1118
HC-E2YR-2B(F) NO COUNTERWEIGHTS 1120
HC-E2YR-2B(F) WITH COUNTERWEIGHTS 1122
HC-E2YR-2BT(F) 1124
HC-E2YR-2RB(F) NO COUNTERWEIGHTS 1126
HC-E2YR-2RB(F) WITH COUNTERWEIGHTS 1128
HC-E2YR-2RBS(F) 1130
HC-E2YR-2T(F)
HC-F2YL-2(F)
HC-F2YL-2UF 1136
HC-F2YR-2(F) 1138
HC-F2YR-2UF 1140
(B)HC-12YF-2CUF 1142
BHC-J2YF-2C(F) 1144
BHC-J2YF-2CUF
BHC-L2YF-2CF 1148
HC-L2YF-2CUF
HC-M2YL-2CEUF
HC-M2YR-2CEF
HC-M2YR-2C(L)EUF

61-10-17
 PROPELLER MAINTENANCE MANUAL
M~A RTZ c L L 117D

THREE WAY -2 PROPELLER ASSEMBLIES

(P)(E)HC-C3YF-2(F) 1158

(P or E)HC-C3YF-2U(F) 1160
HC-C3YF-2UF.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•11~2
PHC-C3YF-2(L)KU(F) 1164

HC-C3YN-2(F) 1166

HC-C3YN-2L(A)(F) ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•11 68

HC-C3YN-2L(A)(D)U(F) ´•´•´•´•´•´•´•´•´•´•´•´•1170

HC-C3YN-2U(F) ´•´•´•´•´•´•´•´•´•´•´•´•1172

HC-C3YR-2(F)
HC-C3YR-2(L)EU(F) ´•´•´•´•´•´•´•´•´•´•´•´•1176

HC-C3YR-2(L)U(F)
HC-E3YR-2(F)
HC-E3YR-2A(L)(F) 1182

HC-E3YR-2A(L)T(F) EXCEPT FUJI 700 1184

HC-E3YR-2AT(F) FUJI 700 1186

HC-E3YR-2T(F)
HC-F3YR-2(F) 1190

HC-F3YR-2U(F) 1192

(E)HC-G3YF-2(F) 1194

(E)HC-G3YF-2U(F) ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•1196

PHC-G3YF-2U(F)
HC-H3YF-2(F) 1200
HC-H3YF-2UF 1202
PHC-H3YF-2KUF 1 204

HC-H3YN-2(F) ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•1 206

HC-H3YN-2UF 1208

HC-13YF-2(F)
HC-13YF-2U(F) 1212

PHC-13YF-2AL 1214

HC-13VR-2(L)UF. . . . . . . . . . . . . . . . . . . . . ´•.´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´• 1216

PHC-J3YF-2(F) EXCEPT BARON ’58P’ 1218

PHC-J3YF-2(F) BARON ’58P’ 1220

PHC-J3YF-2U(F)
EXCEPT BARON ’58TC’ AND BARON’58P’WITH FC8468-6R BLADES 1222

PHC-JSYF-2U(F) BARON ’58TC’ 1224

PHC-J3YF-2U(F) BARON ’58P’ WITH FC8468-6R BLADES 1226

ILLUSTRATED PARTS LIST 61’1 0’1 7

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FOUR WAY -2 PROPELLER ASSEMBLIES

HC-C4YF-2(E) 1228
HC-C4YN-2 1230
HC-C4YR-2(L) 1232
HC-F4YR-2

THREE WAY -5 PROPELLER ASSEMBLIES

I HC-C3YF-5F
HC-C3YN-5A
1236

FIGURES

Two Way -2 With High Pitch Stop Assembly.......................... Figure 1001 1010

Two Way -2 WithHigh Pitch Stop Assembly

and A-2273 Hub Spring Assembly Figure 1002 1011

Two Way -2 WithHigh Pitch Stop Assembly

and A-1586 Hub Spring Assembly Figure 1003 1012

Two Way -2 With Cylinder Spring Assembly Figure 1004 1013

Three Way -2 WithHigh Pitch Stop Assembly Figure 1005 1014

Three Way -2 With High Pitch Stop Assembly
and Hub Spring Assembly Figure 1006 1015

Three Way -2 With Cylinder Spring Assembly Figure 1007 1016

Four Way -2 With Cylinder Spring Assembly Figure 1008 1017

Three Way -5 With Cylinder Spring Assembly Figure 1009 1018

Blade Retention System Exploded View Figure 1010.................... 1019

B-1589-( and 3-1106 Cylinder Spring Assemblies Figure 1011 1020

B-3684 Cylinder Spring Assembly Figure 1012 1022

Spinner Nuts Figure 1013 1024

I F and N Flange Mounting Parts Figure 1014 1025

ILLUSTRATED PARTS LIST 61-10-17

 PROPELLER MAINTENANCE MANUAL
H~A RTZ F L L IitD

1. Introduction

A. General

(1) This illustrated parts list contains all of the current configurations for
propellers manufactured by Hartzell Propeller Inc. and supersedes any
printsthat may have previously been supplied for part and assembly
information. The parts lists contained within the Illustrated Parts List are to
be used for verifying the configuration of propeller models and ordering
parts.

CAUTION: ILLUSTRATIONS IN THE ILLUSTRATED PARTS LIST ARE TO

BE USED FOR IDENTIFYING PARTS AND SHOULD NOT BE
USED AS A MAINTENANCE REFERENCE FOR ASSEMBLY.

(2) The figures for the illustrated parts list contain all of the parts that could be
used to make up any combination of propellers. Each propeller model list
has indexed parts which can be located on the appropriate figure. Not all of
the parts in any figure may be used in any one propeller model.

B. Using the Illustrated Parts List

(1) Every effort has been made to include all of the propellers and
configurations manufactured by Hartzell Propeller Inc. If an overhaul facility
has questions about a propeller configuration as stated in the Illustrated
Parts List, contact the Hartzell Propeller Product Support Department.

(2) Basic Propeller Parts: Refers to all of the propeller components that may be
unique to a particular propeller model.
(3) Spinner Mounting Kits have been included in this manual. It is the
responsibility of the propeller maintenance facility to ensure that the
appropriate spinner and mounting parts have been installed. Refer to the
Hartzell Application Guide for spinner assembly application information.

(4) Spinner Parts: These components are application specific. Most propeller
models have more than one spinner possibility and require the installation
information for the particular application to determine the appropriate
spinner.
(5) )-Flange Parts: Refers to the type of flange parts used on a particular
propeller model.
(6) Balance Parts: These components are common to all compact propellers.
C. Propeller Assemblies Configured with a De-ice System
The Illustrated Parts List assumes the propeller assembly is not configured with
ade-ice system. For de-ice part information, refer to the BF Goodrich
Replacement Parts List, the BF Goodrich general arrangement drawing for the
applicable de-ice kit, or the airframe manufacturer’s maintenance manual.

ILLUSTRATED PARTS LIST 61 -1 0-1 7

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

2. The Illustrated Parts List

A. Detailed Parts List

The Detailed Parts List consists of the Figure/item Number, Part Number,
Description, Effectivity Code and Units Per Assembly. Space is reserved for the
Airline Stock Number. The following is an explanation of each column.

(1) Fig/ltem Number

(a) Figure Number refers to the illustration where items appear. Item
Numbers are assigned in broken sequence to allow the insertion of

subsequent additional parts. Items listed but not illustrated are

identified by a dash to the left of the item number.

(b) Alpha variants will be used to add additional items. There are two
reasons for the use of alpha variants:

1 A part may be superseded, replaced, or obsoleted by another

part. For example, the self locking nut (A-2043) which is item 20
was superseded by the self locking nut (A-2043-1) which is item

20A.

2 An Illustrated Parts List may contain multiple configurations.

Effectivity codes are used to distinguish different part numbers
within the same list. For
example, one configuration may use a
propeller mounting bolt
(B-3339-1) which is item 30, yet another
configuration uses a propeller mounting bolt (8-3347) which is
item 30A. Effectivity codes are very important in the determination
of parts in a given configuration.

(2) Part Number

Hartzell part numbers are listed in the Part Number column. Use the part
number when ordering the part from Hartzeil or a Hartzell approved
distributor. Digits of Hartzell Part Numbers have no significance other than
to identify a part.
(3) Airline Stock Number

Space is reserved for the Airline Stock Number.

(4) Description
This column identifies the item. The relationship of parts to assembly are
indicated by the use of indentations. This column may also contain vendor
CAGE codes, as applicable. Information regarding part supersedure,
replacement, obsolecence may also be found in this column. Refer to
or

Revisions, below, for further information regarding superseded, replaced or

obsoleted parts.

ILLUSTRATED PARTS LIST 01’1 0’17

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(5) Effectivity Code (EFF CODE)

The effectivity column shows the prefix and/or suffix of the propeller model
to which the parts apply. In some cases, the specific engine or aircraft
manufacturer may be called out. Effectivity codes assigned apply only to the
figure/listing in which they appear. Parts common to all end items show no
code.

(6) Units Per Assembly (UPA)

Designates the total quantity of an item required for the next higher
assembly or subassembly.
B. Revisions

(1) Alternate

Alternate parts are identified by the term "ALTERNATE" in the Description

column. Alternate items are considered airworthy for continued flight and
existing stock of parts may be used for maintenance and/or repair. The new
or part numbers may be used interchangeably when ordering/
alternate
stocking new parts.
(2) Supersedure
~I

Part changes are identified by the terms "SUPERSEDES ITEM Or

"SUPERSEDED BY ITEM in theDescription Superseded

column.
items are considered airworthy for continued flight and existing stock of
superseded parts may be used for maintenance and/or repair. Superseded
parts may no longer be available, and the new part number must be used

when ordering/stocking new parts.

1 (3) Replacement
Part changes identified by the terms "REPLACES ITEM
"REPLACED BY ITEM Description column are considered
in the

airworthy for continued flight, but must be replaced with a part with the new
part number at overhaul. Existing stock of replaced parts may not used for
maintenance and/or repair of effected assemblies. Replaced parts may no
longer be available, and the new part number must be used when orderingl
stocking new parts.
1 (4) Obsolescence

Obsolete parts are identified by "OBS" in the Units Per Assembly (UPA)
column. Obsolete items are considered unairworthy for continued flight.

ILLUSTRATED PARTS LIST 61’1 0’1 7

 PROPELLER MAINTENANCE MANUAL
HA,RTZ cLL 117D

1 (5) Service Documents and Airworthiness Directives

(a) In the event of modification or rework of an existing part, the

supersedure, replacement, or obsolescence of a part, or the addition of
parts installed by a Service Bulletin (SB) or Service Letter (SL), the SE
or SL number will appear in the Description column as "SB or

"SL after the description.

(b) When a SE has a relationship to an Airworthiness Directive (AD), the

AD will be shown in parentheses after the SE number as SE
(AD
C. Vendors

(1) Many O-rings, fasteners, and other vendor supplied hardware listed in
Hartzell manuals have previously been specified with AN, MS, NAS or
vendor part number. To provide internal controls and procurement flexibility,
Hartzell has made engineering changes to provide all O-rings, fasteners,
and hardware with a Hartzell part number. Parts shipments from Hartzell will
specify only the Hartzell part numbers.
(2) Some O-rings, fasteners, and hardware manufactured in accordance with
established industry specifications (certain AN, MS, NAS items) are
acceptable for use in Hartzell products without additional standards
imposed by Hartzell. Refer to Manual 202A (61-01-01), Chapter 2200,
Vendor Cross Reference, for a listing of part number interchangeability.

3. F and N flanae Studs

The installation of studs in F and N flange propeller dependent upon the

models is
propeller application. Refer to the Aluminum Hub Overhaul Chapter of Hartzell
Manual 202A for specific part and installation requirements.

4. Pitch Change Knob

Improvements were production of two bladed propeller models in the

made in the
form of the F-knob blade. Propeller models using blades with the strengthened
pitch change knob are denoted by the addition of an "F" at the end of the model
designation (Example: HC-C2YK-2BF). These propellers use larger forks to
accommodate the increased size of the pitch change blocks.

61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

(This page is intentionally blank.)

ILLUSTRATED PARTS LIST 61’1 0’1 7

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

W10034
4040

4000
""S\
490 660
680
670

4050
470
4060
(F&N FLANGE)

590

380
ii;430610 600

´•~500 420

1990
1980
400

370 440
130 330

150 r..- 360 4060

I 140/o, 140
290 300
340
~i

f! 90 4090

100I
320
4070
310
4080

120 i 150
480
120,
480 4110 (EPYL FLANGE)
(L, K&R FLANGE)

100

70
1

ij $209 30
50 4100
4060

40
10

40904j~ 4080
4070

Two Way -2 with High Pitch Stop Assembly

Figure 1201

61-10-17 1010
 PROPELLER MAINTENANCE MANUAL
HI1~ RTZ E L L 117D

W10035
4040

490 66\0
4000

680
4030~t 560
670
540
4060
4050,/ I:o,,,
570~
V
470 5504060/~ a :~aL

K, sR

40904070
4080

’8~ 390
610

380~ 430 600

520
500

19801990 400
450

580
130 370 350 440

150 i/-- 130 330

360

140 300
290
140 340

90

:i
320

~BC\ 310
280
120
150

70

100320’q 10
30
50
60

40

Two Way -2 with High Pitch Stop Assembly and A-2273 Hub Spring Assembly
Figure 1002

ILLUSTRATED PARTS LIST 61’1 0’1 7 Rev. 4 May/9Page 1011

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

W10036
4040

403

4000
490 669
680
560
670
540
4060

570B i
470 5504069/i
,-(’L, K, 4090

o
,4070
I (i~J/ 4080

530
590-600610
380430
~500 420

1990 450
1980
400
580
370 350--_ 440

aJ´• 1.36/ 330

´•´•-O:""140 i
G 360

290 300

140 340

90
320
’I

310
280

120 1
150,

100 12020 t
40
10
30
50
70

Two Way -2 with High Pitch Stop Assembly and A-1586 Hub Spring Assembly
Figure 1003

ILLUSTRATED PARTS LIST 61’1 0’ 1 7 1012

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117b

W10037

4040
4030

4000
660
490 680
670

/C~7,
4050
4060 ´•´•/480
(F&N FLANGE)

590

390 610

"j\1990
\600
380
´•-~00 -420

450
400
580.
370 440

350-
330 Y 4060

360

290 300

ik 320
90´•9,/4070
340

160
4090

4080
310
\280
480
(L, K&R FLANGE)

I
"I209
70 100
50
30

10
40

Two Way -2 with Cylinder Spring Assembly

Figure 1004

1013
ILLUSTRATED PARTS LIST 61-10-17 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L 117D

W10038
4040
4030

490 660
680
670

470
4059.´•/ 610
4060,

590------- 1980 -‘1990

390

380-- B.’ 410

\~500

580
480
\B\440
350-,
130 400
370

‘r
130

´•´•´•k330
290 300
360

140
140,

y
310
320 90
340

4Y 4090
280
/j 4070
150
4080

120 .~´•´•120./
100 100

70

P9~102030
40
50

Three Way -2 with High Pitch Stop Assembly

Figure 1005

1,,,,,,,,,,,,,,,,,, 61-10-17 1014

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

W10039

4040
4030

4000
490 660
680 lo.
670 O
480 i:;

(L, K& R FLA‘N~,

~405Q´•/
570

4060
~55Q,

530
\r4070 -4080

590
410~ 600

390

380,500
1980 1990610
480

580
440
330 U 400

3701 150´•Zc:
i 360
290 00

150
d 140 340

90
130 320

310
140
280
120
1
I

100 100

i, a
P?10S"30
70

50

20

40

Three Way -2 with High Pitch Stop Assembly and Hub Spring Assembly
Figure 1006

ILLUSTRATED PARTS LIST 61’1 0’1 7 Rev. 4 May/9Page 1015

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

W10040

4040
4030

4000
490 660
680
670

i-J
4050.-/ 610
470
4060,

390
1980 i990
4

380 8- -410

;4 480\.500
cF&NFLANGE,
580
440
400
370
c~ 350,
330
4060 /O; .h´•,‘‘´•~

290 %00
b340LU 360

4090
90
320
60 4070
10

FLANGE)480
I

70
I
100
(L, K&R

50
30
20

40

Three’ Way -2 with Cylinder Spring Assembly

Figure 1007

ILLUSTRATED PARTS LIST 61’1 0’17 Rev. 4 May/9Page 1016

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

W10041
4040
4030

4000
490 660
680
670

4050
470
4060

(F&N FLANGE)

sio
600
390

380- b
: :1990
580
1980

400
500

‘9
410

370 440

350-

290 300
360i
:X
i

320
90 160340 I’
>4060

4070
4080

!o
4090

70 100 480
50 (L, K&R FLANGE)
30

40

Four Way -2 with Cylinder Spring Assembly

Figure 1008

1017
ILLUSTRATED PARTS LIST 61’1 0’1 7 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HA R~Z E L L 117D

W10042

4040
4030

4000
490 660
680
670

/C

470
:~7´•, 4050~-/ 610
4060

590 w ;980 1990

390

380 B´•
480
(F&N FLANGE)
580
440

400
370
i 350~
330

360

4´•:~310340
290

90
320
60
i
280

I
P?102093050 60 70 100

40

Three Way -5 with Cylinder Spring Assembly

Figure 1009

ILLUSTRATED PARTS LIST 61’1 0’1 7 Rev. 4 May/9Page 1018

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117b

APS6193A

/1

i;
i 3060
3000

3090

3010

30203080
3100

3030
3110

3040

I ~a Ii
3050

Blade Retention System Exploded View

Figure 1010

1019
ILLUSTRATED PARTS LIST 61110117 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HA RTZ E LL 117D

W10043

230 220

240

170

oo

250
u-210 190
180

B-1589-( land 8-1106 Cylinder Spring Assemblies

Figure 1011

ILLUSTRPITED PIRTS LIST 61 -1 0’17 1020

 PROPELLER MAINTENANCE MANUAL
HA RT Z E L L IlfD

FIG.IITEM PART AIRLINE DESCRIPTION I EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

1011
-160 8-1106 CYLINDER SPRING ASSEMBLY 1

170 A-1591 I I ´•´•GUIDE, SPRING 1

180 A-i 595-1 ´•´•SCREW 4
190 8-317 WEIGHT, START LOCK 1
210 A-1596-1 ´•´•´•SPRING, WEIGHT 1
220 B-1 592-1 ´•´•RETAINER, SPRING 1
230 B-1 594-1 ´•´•SPRING, FEATHERING 1
240 8-1593 ´•´•BRACKET I I 1
250 A-3744 ´•´•WASHER I I 1

160 8-1589 CYLINDER SPRING ASSEMBLY OBSOLETE

USE CYLINDER SPRING ASSEMBLY 8-1589-2

-160 8-1589-2 CYLINDER SPRING ASSEMBLY I I 1

170 A-1591 ´•´•GUIDE, SPRING 1
180 A-1595 ´•´•SCREW 4
190 A-1590 WEIGHT, START LOCK, SUPERSEDED BY ITEM 200P( I 1
190AI 8-318 WEIGHT, START LOCK, SUPERSEDES ITEM 200A 1
210 A-1 596 ´•´•´•SPRING, WEIGHT 1
220 B-1 592-1 ´•´•RETAINER, SPRING 1
230 B-1 594-1 ´•´•SPRING, FEATHERING 1
240 B-1 593 ´•´•BRACKET I I 1
250 A-3744 ´•´•WASHER I I 1

-160 8-1589-3 CYLINDER SPRING ASSEMBLY 1

170 8-4504 ´•´•GUIDE, SPRING 1

180 A-1 595 ´•´•SCREW I 1 4

190 A-1590 WEIGHT, START LOCK, SUPERSEDED BY ITEM 200PI I 1
190A1 8-318 WEIGHT, START LOCK, SUPERSEDES ITEM 200A 1
210 A-1596 ´•´•´•SPRING, WEIGHT 1
220 8-1592-1 ´•´•RETAINER, SPRING t
230 B-1 594-1 ´•´•SPRING, FEATHERING 1
240 B-1 593 ´•´•BRACKET 1
250 8-3744 ´•´•WASHER 1

ITEM NOT ILLUSTRATED

Cylinder Spring Assemblies

ILLUSTRP;TED PIRTS LIST 61 ’1 0’1 7 Rev. 4 May/9 Page 1021

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

Wla044

220
230

240

180

200

250

B-3684 Cylinder Spring Assembly

Figure 1012

61-10-17 1022
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART AIRLINE DESCRIPTION EFF IUPA

NUMBER NUMBER STOCKNUMBER 1234567 CODE

1012
-160 B-3684 CYLINDER SPRING ASSEMBLY 1

170 A-i 591 ´•´•GUIDE, SPRING 1

180 A-i 595 ´•´•SCREW 4

200 A-3681 ´•´•PLATE, RETAINER 1

220 B-1 592-1 ´•´•RETAINER, SPRING 1

230 B-1594-1 ´•´•SPRING, FEATHERING 1

240 B-1 593 ´•´•BRACKET 1

250 B-3744 ´•´•WASHER 1

ITEM NOT ILLUSTRATED

Page 1023
ILLUSTRATED PARTS LIST 61-10-17 Rev. 4May/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

APS6279A-E

A-2405 Nut A-2405-1 Nut A-2405 Nut A-2405-2 Nut

Configuration 1 Configuration 2

A-2405-3 Nut A-169-7Spacer A-2405-2 Nut

Configuration 3

Configuration 3 is the preferred combination and supersedes Configurations 1

and 2. Propellers may continue to use Configurations 1 or 2, although spinner
attachment to the low pitch stop may be difficult due to the spinner resting
improperly on the A-2405 nut. Changing to Configuration 3 provides a means of
adjustment for a more precise fit of the spinner attachment to the propeller.

Spinner Nuts
Figure 1013

ILLUSTRI\TED P~RTS LIST 61’1 0’1 7 Rev. 4 May/9Page 1024

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

PROPELLER
FLANGE
4020 4050

4000

N FLANGE

ENGINE I, g-o~ O
FLANGE

4030
PROPELLER
4040 FLANGE
4050
4020

4000

ENGINE

F FLANGE

4030

4040

F and N Flange Mounting Parts

Figure 1014

1025
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

FIG.IITEM PART AIRLINE I NOMENCLATURE EFF UPA

NUMBER NUMBER ISTOCK NUMBER I 1 2 3 4 s s 7 CODE

PROPELLER PARTS
1001 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 1 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-l 938 ´•VALVE, AIR 1
50 A-2404-1 1 I LOW STOP I I 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER I I 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-3317´•427-1 ´•O-RING, CYLINDER ID 1
100 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 830-21 1 I AUTO HIGH PITCH STOP UNIT I I 1
120 8-2406-1 BRACKET, AUTO HIGH STOP 1
130 A-884 1 I SPRING, AUTO HIGH STOP 4
140 A-2704-2 PIN, HIGH STOP 4
150 8-3838-3-5 COTTER PIN 4
280 A-3205 ´•SCREW 1
290 8-3837-0563 ´•WASHER I IAR
290A 8-3837-0532 ´•WASHER I IAR
300 1 A-2411-1 WASHER, FEATHER STOP 1
310 1 8-3837-0563 .WASHER, FEATHER ADJUST AR
310AI 8-3837-0532 WASHER, FEATHER ADJUST AR
320 1 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 ´•NUT, PISTON 1
350 1 8-3683 ´•PISTON 1
8-3237 ´•PISTON (ALTERNATE) 1
360 C-3317-210-1 ´•O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-2 FORK, PITCH CHANGE -2B(D,E) 1
SUPERSEDED BY ITEM 400A
8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 1 A-3323 1 I RUBBING PLATES I 1 2
430 1 8-3842-0500 SPRING PIN 4
440 1 A´•2217-1 BLOCK, PITCH CHANGE -PB(D,E) 2
SUPERSEDED BY ITEM 4408
A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) PB(D,E) 2
SUPERSEDED BY ITEM 4408
4408 A-2217-4 BLOCK, PITCH CHANGE -PB(D,E) 2
SUPERSEDES ITEMS 440 AND 440A
A-2217-3 BLOCK, PITCH CHANGE -2B(D,E)F 2
450 1 A-3212 BUTTON, PITCH CHANGE BLOCK -PB(D,E) 2
A-3212-1 BUTTON, PITCH CHANGE BLOCK -2B(D,E)F 2
470 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
(B)HC-C2V~-2B(D,E)(F)

ILLUSTRATED PARTS LIST 61 ’1 0-1 7 Rev. 4 May/9Page 1026

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117~

PART AIRLINE NOMENCLATURE EFF UPA

FIG.IITEM
NUMBER STOCK NUMBER I CODE
NUMBER 1 2 3 4 s s 7

480 1 D-2201-4 ´•HUB BHC- 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-6‘1-179

D-6530-2 ´•HUB BHC- 1

SUPERSEDES ITEM 480, POST SL HC-SLdl-179

D-2201 ´•HUB HC- I 1

SUPERSEDED BY ITEM 480C, PRE SL HC-SL-61-179

.HUB HC- 1
0-6530-1
SUPERSEDES ITEM 4808, POST SL HC-SLB1-179
GUIDE BUSHING 1
500 1 A-2249
.BOLT 6
580 A-2431
´•BOLT 4
590 A-2432
(WHEN USING SPINNER MOUNTING KIT, REPLACE
BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
´•WASHER 10
600 8-3834-0632
.NUT 10
610 A-2043-1
LUBRICATION FITTING 4
1980 8-6588-1
LUBRICATION FI~TING (ALTERNATE) 4
1980AI A-279
CAP, LUBRICATION FITTING 4
1990 1 8-6544
´•DECAL 1
-2000 1 CRP-323

1010 BLADE RETENTION PARTS

BUSHING, PITCH CHANGE KNOB -2B(D,E) 2
3000 A-2413
BUSHING, PITCH CHANGE KNOB -PB(D,E)F 2
A-2413-2
´•SEAL, BLADE 2
3010 1 8-3883-4339
SPLIT BEARING, HUB SIDE RACE 2
3020 1 A-2202-8
1/2" DIAMETER STEEL BALL 50
3030 8-6144
1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
8-6144-650
´•SPACER, BALL 2
3040 8-3211
SPLIT BEARING, BLADE SIDE RACE 2
3050 A-2202-A
RING, BLADE BEARING RACE RETENTION 2
3060 A-2204
PRELOAD PLATE UNIT 2
-3070 8-2256
PRELOAD PLATE 1
3080 8-2222
8-6679 RACE, INNER BLADE BORE BEARING 1
3090
SCREW, SOCKET HEAD 1
3100 1 A-3204
´•´•NUT, JAM 1
3110 8-3368

1014 F-FLANGE MOUNTING PARIS

´•O-RING, FLANGE 1
4000 1 C-3317-228
STUD, HUB MOUNTING 6
4020 A-2429-4
´•WASHER, HARD, STAINLESS 6
4030 1 A-1381
NUT, SELF LOCKING 6
4040 A-2044
.5002" X1 1/8" DOWEL PIN 2
4050 8-6138-8-9

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS -APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

0-2271
nEM NOi ILLUSTRATED
(B)HC-C2UF-2B(D,EKF)

Page 1027
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HA RTZ E L L 117D

FIG.IITEM PART AIRLINE NOMENCLATURE I EFF IUPA

NUMBER NUMBER STOCKNUMBER 1234567 CODE

PROPELLER PARTS
1001 10 1 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) i
20 1 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 1 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-1 938 ´•VALVE, AIR 1
50 A-2404-1 1 I LOW STOP 1
60 1 C-3317-117 O-RING, LOW STOP 1
70 1 8-2423-1 1 I´•CYLINDER 1
-80 1 A-862-3 BUSHING, CYLINDER 1
90 C-331 7-427-1 ´•O-RING, CYLINDER ID 1
100 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 1 830-30 AUTO HIGH PITCH STOP UNIT 1
120 8-2406-3 BRACKET, AUTO HIGH STOP 1
120A 8-2406-1 BRACKET, AUTO HIGH STOP (ALTERNATE) 1
130 A-884 ..SPRING, AUTO HIGH STOP 2
140 1 A-2407 PIN, HIGH STOP 2
150 1 8-3838-3-5 COTTER PIN 2
280 1 A-3205 1 I´•SCREW 1
290 8-3837-0563 1 I´•WASHER I IAR
290A 8-3837-0532 ´•WASHER AR
300 A-2411-1 .WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310AI 8-3837-0532 WASHER, FEATHER ADJUST AR
320 1 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 1 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 .WASHER, HIGH PITCH ADJUST AR
340 8-3807 ´•NUT, PISTON 1
350 8-3683 ´•PISTON 1
350A 8-3237 ´•PISTON (ALTERNATE) 1
360 C-331 7-21 0-1 ´•O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-2 FORK, PITCH CHANGE -2C(D) 1
SUPERSEDED BY ITEM 400A
8-2457-3 1 I FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 1 A-3323 RUBBING PLATES 2
430 1 8-3842-0500 SPRING PIN 4
440 A-2217-1 BLOCK, PITCH CHANGE -2C(D) 2
SUPERSEDED BY ITEM 4408
A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2C(D) 2
SUPERSEDED BY ITEM 4408
4408 A-2217-4 BLOCK, PITCH CHANGE -2C(D) 2
SUPERSEDES ITEMS 440 AND 440A
A-2217-3 BLOCK, PITCH CHANGE -2C(D)F 2
450 1 A-3212 BUTTON, PITCH CHANGE BLOCK -2C(D) 2
450A A-3212-1 BUTTON, PITCH CHANGE BLOCK -PC(D)F 2
470 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
(B)HC-CZYF-OC(D)(F)

ILLUSTRATED PARTS LIST 61’1 O IPage 1028

 PROPELLER MAINTENANCE MANUAL
nARTZELL 117D

FIG.IITEM PART AIRLINE I NOMENCLATURE EFF IUPA

NUMBER NUMBER STOCKNUMBER 1234567 CODE

480 D-2201-4 ´•HUB BHC- 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
480A D-6530-2 ´•HUB BHC- I 1

SUPERSEDES ITEM 480, POST SL HC-SL-61-179

4808 D-2201 ´•HUB HC- I 1
SUPERSEDED BY ITEM 480C, PRE SL HC-SL-61-179
D-6530-1 .HUB HC- I 1

SUPERSEDES ITEM 4808, POST SL HC-SL´•B~-179

GUIDE BUSHING 1
500 A-2249
A-2431 ´•BOLT 6
580
´•BOLT 4
590 1 A-2432
(WHEN USING SPINNER MOUNTING KIT, REPLACE
BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10
´•NUT 10
610 1 A-2043-1
8-6588-1 LUBRICATION FITTING 4
1980
A-279 LUBRICATION FITTING (ALTERNATE) 4
1980A
1990 1B-6544 CAP, LUBRICATION FITTING 4
.DECAL 1
-2000 CRP-323

1010 BLADE RETENTION PARTS

A-2413 BUSHING, PITCH CHANGE KNOB -2C(D) 2
3000
3000AI A-2413-2 BUSHING, PITCH CHANGE KNOB -2C(D)F 2

8-3883-4339 ´•SEAL, BLADE 2

3010
A-2202-8 SPLIT BEARING, HUB SIDE RACE 2
3020
8-6144 1/2" DIAMETER STEEL BALL 50
3030
1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
-3030AI 8-6144-650
8-3211 ´•SPACER, BALL 2
3040
A-2202-A SPLIT BEARING, BLADE SIDE RACE 2
3050
A-2204 RING, BLADE BEARING RACE RETENTION 2
3060
PRELOAD PLATE UNIT 2
-3070 1 8-2256
1 8-2222 PRELOAD PLATE 1
3080
8-6679 RACE, INNER BLADE BORE BEARING 1
3090
1 A-3204 SCREW, SOCKET HEAD 1
3100
8-3368 ´•´•NUT, JAM 1
3110

1014 F-FLANGE MOUNTING PARTS

´•O-RING, FLANGE 1
4000 C-331 7-228
4020 1 A-2429-4 STUD, HUB MOUNTING 6

1 A-1381 ´•WASHER, HARD, STAINLESS 6

4030
1 A-2044 NUT, SELF LOCKING 6
4040
8-6138-8-9 .5002" X 1 1/8" DOWEL PIN 2
4050

BALANCE PARTS
´•SCREW AR
-9000 B-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS -APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2271
.ITEM NDT ILLUSTRATED
(B)HC-CPYF-PC(D)(F)

Page 1029
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

FIG.IITEM I PART AIRLINE NOMENCLATURE I EFF UPA

NUMBER NUMBER STOCK NUMBER I 1 2 3 4 s 6 7 CODE

PROPELLER PARTS
1004 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-l 938 ´•VALVE, AIR 1
50 A-2404-1 1 I LOW STOP 1
50A A-2404-3 LOW STOP (ALTERNATE) 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 1 I. CYLINDER 1
-80 1 A-862-3 ´•´•BUSHING, CYLINDER 1
90 1 C-3317-427-1 ´•O-RING, CYLINDER ID 1
100 1 8-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
-160 1 8-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 160A
-160AI 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 160
280 A-3205 ´•SCREW 1
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 .WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 1 I WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 ´•NUT, PISTON 1
350 8-3683 ´•PISTON I I 1
350A 8-3237 ´•PISTON (ALTERNATE) 1
360 C-331 7-21 0-1 ´•O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 1 C-3317-210-1 .O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-3 FORK, PITCH CHANGE 1
420 A-3323 RUBBING PLATES I 1 2
430 8-3842-0500 1 I SPRING PIN I 1 4
440 1 A-2217-3 BLOCK, PITCH CHANGE 2
450 1 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2292
ITEM NOT ILLUSTRATED
(B)HC-CPYF-SCDUF

Page 1030
ILLUSTRATED PARTS LIST 61 ’1 0-17 Rev. 4May/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART AIRLINE I NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

480 1 D-2201-4 ´•HUB BHC- 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
D-6530-2 ´•HUB BHC- I 1
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
0-2201 ´•HUB HC- I 1

SUPERSEDED BY ITEM 480C, PRE SL HC-SL-G1-179

D-6530-1 ´•HUB HC- I 1

SUPERSEDES ITEM 4808, POST SL HC-SL-61-179

500 A-2249 GUIDE BUSHING 1

580 A-2431 ´•BOLT 6

590 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10

610 1 A-2043-1 ´•NUT 10

1980 1 A-279 LUBRICATION FITTING I 1 4

1990 1 8-6544 CAP, LUBRICATION FITTING 4

´•DECAL 1
-2000 1 CPR-41
-2020 1 CAU002 ´•DECAL 1

-2030 1 HI-102 ´•DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413-2 BUSHING, PITCH CHANGE KNOB 2

3010 8-3883-4339 ´•SEAL, BLADE 2

3020 A-2202-8 SPLIT BEARING, HUB SIDE RACE 2

3030 1 8-6144 1/2" DIAMETER STEEL BALL 50

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

3040 8-3211 ´•SPACER, BALL 2

3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 A-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 8-2256 PRELOAD PLATE UNIT 2

3080 8-2222 ..PRELOAD PLATE 1

3090 1 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 1 A-3204 SCREW, SOCKET HEAD 1

3110 1 8-3368 ´•´•NUT, JAM 1

1014 F-FLANGE MOUNTING PARTS

4000 C-331 7-228 .O-RING, FLANGE 1

4020 A-2429-4 STUD, HUB MOUNTING 6

4030 1 A-1381 ´•WASHER, HARD, STAINLESS 6

4040 1 A-2044 NUT, SELF LOCKING 6

4050 1 8-6138-8-9 .5002" X1 1/8" DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

0-2292
ITEM NOT ILLUSTRATED
(B)HC-CSYF-PCDUF

Page 1031
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM I PART I AIRLINE NOMENCLATURE EFF IUPA

NUMBER I NUMBER I STOCK NUMBER 1234587 CODE

PROPELLER PARTS
1001 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-l 938 ´•VALVE, AIR 1
50 1 A-2404-1 1 I .LOW STOP 1
60 1 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 1 I´•CYLINDER 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 ´•O-RING, CYLINDER ID 1
100 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 1 830-30 AUTO HIGH PITCH STOP UNIT 1
120 8-2406-3 BRACKET, AUTO HIGH STOP 1
120A 8-2406-1 BRACKET, AUTO HIGH STOP (ALTERNATE) 1
130 A-884 SPRING, AUTO HIGH STOP 2
140 A-2407 PIN, HIGH STOP 2
150 8-3838-3-5 COTTER PIN I 1 2
280 A-3205 ´•SCREW I I 1
290 1 8-3837-0563 1 I. WASHER I IAR
8-3837-0532 1 I. WASHER I IAR
300 1 A-2411-1 WASHER, FEATHER STOP 1
310 1 8-3837-0563 WASHER, FEATHER ADJUST AR
310AI B-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 .SLEEVE, HIGH PITCH STOP 1
330 1 A-2435 .WASHER, HIGH PITCH ADJUST AR
A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 1 8-3807 .NUT, PISTON 1
350 8-3683 1 I. PISTON I I 1
8-3237 ´•PISTON (ALTERNATE) 1
360 C-331 7-21 0-1 ´•O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210´•1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-2 FORK, PITCH CHANGE -2CH I 1
SUPERSEDED BY ITEM 400A
8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 A-3323 1 I RUBBING PLATES I 1 2
430 1 8-3842-0500 SPRING PIN 4
440 1 A-2217-1 BLOCK, PITCH CHANGE -2CH 1 2
SUPERSEDED BY ITEM 4408
A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2CH 1 2
SUPERSEDED BY ITEM 4408
4408 A-2217-4 BLOCK, PITCH CHANGE -2CH 1 2
SUPERSEDES ITEMS 440 AND 440A
A-2217-3 BLOCK, PITCH CHANGE -2CHF 1 2
450 1 A-3212 BUTTON, PITCH CHANGE BLOCK -2CH 1 2
A-3212-1 8U7TON, PITCH CHANGE BLOCK -2CHF 1 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-227(
ITEM NOT ILLUSTRATED
(B or D)HC-CSYF-PCH(F)

ILLUSTRP;TED P~RTS LIST 61’1 0’1 7 Rev. 4 May/9Page 1032

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCKNUMBER 1234587 CODE

480 D-2201-18 ´•HUB BHC- 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-6‘1-179
0-6530-5 ´•HUB BHC- 1

SUPERSEDES ITEM 480, POST SL HC-SL-61-179

.HUB DHC- 1
D-2201-20
SUPERSEDED BY ITEM 480C, PRE SL HC-SL-61-179
D-6530-6 ´•HUB DHC- I 1

SUPERSEDES ITEM 4808, PRE SL HC-SL-81-179

1 A-2249 GUIDE BUSHING 1
500
580 1 A-2431 ´•BOLT 6
´•BOLT 4
590 1 A-2432
(WHEN USING SPINNER MOUNTING KIT, REPLACE
BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 .WASHER 10

610 A-2043-1 ´•NUT 10

LUBRICATION FITTING 4
1980 1 8-6588-1
LUBRICATION FITTING (ALTERNATE) 4
1980AI A-279
1990 1 8-6544 CAP, LUBRICATION FITTING 4

CRP-323 .DECAL 1
-2000

1010 BLADE RETENTION PARTS

A-2413 BUSHING, PITCH CHANGE KNOB -2CH 2
3000
A-2413-2 BUSHING, PITCH CHANGE KNOB -2CHF 2

´•SEAL, BLADE 2
3010 1 8-3883-4339
SPLIT BEARING, HUB SIDE RACE 2
3020 A-2202-8
3030 1/2" DIAMETER STEEL BALL 50
1 8-6144
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

8-3211 ´•SPACER, BALL 2

3040
SPLIT BEARING, BLADE SIDE RACE 2
3050 A-2202-A
RING, BLADE BEARING RACE RETENTION 2
3060 1 A-2204
-3070 1 8-2256 PRELOAD PLATE UNIT 2

1 8-2222 PRELOAD PLATE 1

3080
RACE, INNER BLADE BORE BEARING 1
3090 1 8-6679
A-3204 SCREW, SOCKET HEAD 1
3100
8-3368 ´•´•NUT, JAM 1
3110

1014 F-FLANOE MOUNTING PARTS

1 C-3317-228 ´•O-RING, FLANGE 1
4000
STUD, HUB MOUNTING 6
4020 1 A-2429-4
´•WASHER, HARD, STAINLESS 6
4030 1 A-1381
NUT, SELF LOCKING 6
4040 1 A-2044
8-6138-8-9 .5002" X1 1/8" DOWEL PIN 2
4050

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2271
ITEM NOT ILLUSTRATED
(8 or D)HC-CPYF-SCH(F)

1033
ILLUSTRATED PARTS LIST 61 I10-17 Rev. 6 Apr/GOPage
 PROPELLER MAINTENANCE MANUAL
HARTZELL ~17D

FIG.IITEM PART I AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER I STOCK NUMBER 1234567 1 CODE

PROPELLER PARTS
1004 10 lA-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 1k169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 lA-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-l 938 ´•VALVE, AIR 1
50 A-2404-1 1 I .LOW STOP I I 1
60 1C3317-117 O-RING, LOW STOP 1
70 8-2423-1 1 I. CYLINDER I I 1
-80 A-862-3 BUSHING, CYLINDER 1
90 C-331 7-427-1 ´•O-RING, CYLINDER ID 1
100 18-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
-160 18-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 160A
-160AI 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 160
280 A-3205 1 I´•SCREW 1
300 A-2411-1 ´•WASHER 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 lA-2435 WASHER, HIGH PITCH ADJUST AR
330AI A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 18-3807 ´•NUT, PISTON 1
350 1B-3683 ´•PISTON 1
350AI 8-3237 ´•PISTON (ALTERNATE) 1
360 10-3317-210-1 ´•O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 1B-2457-2 FORK, PITCH CHANGE QCHU I 1
SUPERSEDED BY ITEM 400A
400AI 8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 A-3323 1 I RUBBING PLATES I 1 2
430 8-3842-0500 1 I ..SPRING PIN I 1 4
440 A-2217-1 BLOCK, PITCH CHANGE -2CHU 1 2
SUPERSEDED BY ITEM 4408
440AI A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2CHU 2
SUPERSEDED BY ITEM 4408
44081 A-2217-4 BLOCK, PITCH CHANGE -2CHU 2
SUPERSEDES ITEMS 440 AND 440A
440CI A-2217-3 BLOCK, PITCH CHANGE -2CHUF 1 2
450 lA-3212 BUTTON, PITCH CHANGE BLOCK -2CHU 1 2
450AI A-3212-1 BUTTON, PITCH CHANGE BLOCK -2CHUF 1 2
470 lC-3317-115-1 .O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2292
ITEM NOT ILLUSTRATED
(B or D)HC-CSYF-PCHU(F)

61-10-17 1034
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 117D

FIG.IITEM I PART AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

480 1[)-2201-18 .HUB BHC- 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
480A D-6530-5 ´•HUB BHC- 1

SUPERSEDES ITEM 480, POST SL HC-SL-81-179

4808 D-2201-20 .HUB DHC- I 1

SUPERSEDED BY ITEM 480C, PRE SL HC-SLBI-179

480C D-6530-6 ´•HUB DHC- 1

SUPERSEDES ITEM 4808, POST SL HC-SL-61-179

GUIDE BUSHING 1
500 A-2249
580 lA-2431 ´•BOLT 6
´•BOLT 4
590 A-2432
(WHEN USING SPINNER MOUNTING KIT, REPLACE
BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
´•WASHER 10
600 18-3834-0632
´•NUT 10
610 lA-2043-1
LUBRICATION FITTING 4
1980 lA-279
CAP, LUBRICATION FITTING 4
1990 1B-6544
´•DECAL 1
-2000 CPR-41
.DECAL 1
-2020 ICAU002
´•DECAL 1
-2030 HI-102

1010 BLADE RETENTION PARTS

3000 lA-2413 BUSHING, PITCH CHANGE KNOB -2CHU 12
BUSHING, PITCH CHANGE KNOB -2CHUF 2
3000AI A-2413-2
´•SEAL, BLADE 2
3010 8-3883-4339
SPLIT BEARING, HUB SIDE RACE 2
3020 A-2202-B
1/2" DIAMETER STEEL BALL 50
3030 8-6144
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
-3030A
´•SPACER, BALL 2
3040 8-3211
SPLIT BEARING, BLADE SIDE RACE 2
3050 A-2202-A
RING, BLADE BEARING RACE RETENTION 2
3060 lA-2204
PRELOAD PLATE UNIT 2
-3070 18-2256
PRELOAD PLATE 1
3080 1B-2222
RACE, INNER BLADE BORE BEARING 1
3090 1B-6679
SCREW, SOCKET HEAD 1
3100 lA-3204
´•´•NUT, JAM 1
3110 8-3368

1014 F-FLANGE MOUNTING PARTS

´•O-RING, FLANGE 1
4000 lC-3317-228
STUD, HUB MOUNTING 6
4020 1k2429-4
´•WASHER, HARD, STAINLESS 6
4030 IA-1381
NUT, SELF LOCKING 6
4040 A-2044
.5002" X1 1/8" DOWEL PIN 2
4050 18-6138-8-9

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2292
-ITEM NOT ILLUSTRATED
(8 or D)HC-CBYF-PCHU(F)

Page 1035
ILLUSTRATED PARTS LIST 61-1017 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

FIG.IITEM PART AIRLINE I NOMENCLATURE I EFF UPA

NUMBERI NUMBER STOCKNUMBER 1234587 CODE

PROPELLER PARTS
1001 10 lA-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 lA-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 lA-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 18-1938 ´•VALVE, AIR 1
50 A-2404-1 1 I LOW STOP I I 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 1 I´•CYLINDER I I 1
-80 lA-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 ´•O-RING, CYLINDER ID 1
100 1B-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 1830-30 AUTO HIGH PITCH STOP UNIT 1
120 8-2406-3 BRACKET, AUTO HIGH STOP 1
120AI 8-2406-1 BRACKET, AUTO HIGH STOP (ALTERNATE) 1
130 1A-884 SPRING, AUTO HIGH STOP 2
140 lA-2407 PIN, HIGH STOP 2
150 8-3838-3-5 COTTER PIN I 1 2
280 lA-3205 1 I. SCREW I I 1
290 18-3837-0563 1 I´•WASHER AR
290A 1 8-3837-0532 ´•WASHER I IAR
300 IA-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310AI 8-3837-0532 WASHER, FEATHER ADJUST AR
320 1A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 lA-2435 WASHER, HIGH PITCH ADJUST AR
330AI A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 18-3807 ´•NUT, PISTON 1
350 18-3683 ´•PISTON 1
350AI 8-3237 ´•PISTON (ALTERNATE) 1
360 lC-3317-210-1 ´•O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 1(=-3317-210-1 .O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 1B-2457-3 FORK, PITCH CHANGE 1
420 lA-3323 RUBBING PLATES 2
430 1B-3842-0500 SPRING PIN 4
440 lA-2217-3 BLOCK, PITCH CHANGE 2
450 lA-3212-1 BUTTON, PITCH CHANGE BLOCK 2
470 1C3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
BHC-CPYF-PCKF

ILLUSTRATED PARTS LIST Cjl -1 0-1 7 Rev. 4 May/9Page 1036

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER STOCKNUMBER 1234587 CODE

480 D-2201-25 ´•HUB 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
D-6530-11 ´•HUB f
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
D-2201-18 ´•HUB (ALTERNATE) 1

SUPERSEDED BY ITEM 480C, PRE SL HC-SL-61-179

D-6530-5 .HUB (ALTERNATE) 1

SUPERSEDES ITEM 4808, POST SL HC-SL-61-179

500 A-2249 GUIDE BUSHING 1

580 1 A-2431 ´•BOLT 6

590 1 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 1 8-3834-0632 ´•WASHER 10

610 1 A-2043-1 ´•NUT 10

1980 8-6588-1 LUBRICATION FITTING 4

1980AI A-279 LUBRICATION FITTING (ALTERNATE) 4

1990 8-6544 CAP, LUBRICATION FITTING 4

-2000 CRP-323 ´•DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413-2 BUSHING, PITCH CHANGE KNOB 2

3010 8-3883-4339 ´•SEAL, BLADE 2

3020 A-2202-8 SPLIT BEARING, HUB SIDE RACE 2

3030 8-6144 1/2" DIAMETER STEEL BALL 50

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

3040 8-3211 ´•SPACER, BALL 2

3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 A-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 1 8-2256 PRELOAD PLATE UNIT 2

3080 1 8-2222 PRELOAD PLATE i

3090 1 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 A-3204 SCREW, SOCKET HEAD I I 1

3110 8-3368 ´•´•NUT, JAM 1

1014 F-FLANGE MOUNTING PARTS

4000 1 C-3317-228 ´•O-RING, FLANGE 1

4020 1 A-2429-3 STUD, HUB MOUNTING 6

4030 1 A-1381 .WASHER, HARD, STAINLESS 6

4040 1 A-2044 NUT, SELF LOCKING 6

4050 1 8-6138-8-9 1 I .5002" X1 1/8" DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS- APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

0-2271
ITEM NOT ILLUSTRATED
BHC-C2YF-2CKF

Page 1037
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

FIG./ITEM PART AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER STOCKNUMBER 1234567 CODE

PROPELLER PARTS
1001 10 1 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 1 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 i A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 1 8-1938 ´•VALVE, AIR 1
50 1 A-2404-1 LOW STOP I I 1
60 1 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 ´•O-RING, CYLINDER ID 1
100 8-3841-1 0 SCREW, HIGH PITCH STOP BRACKET 4
-110 830-30 AUTO HIGH PITCH STOP UNIT I I 1
120 8-2406-3 BRACKET, AUTO HIGH STOP 1
120A 8-2406-1 BRACKET, AUTO HIGH STOP (ALTERNATE) 1
130 1 A-884 SPRING, AUTO HIGH STOP 2
140 1 A-2407 PIN, HIGH STOP 2
150 1 8-3838-3-5 COTTER PIN 2
280 1 A-3205 1 I´•SCREW 1
290 1 8-3837-0563 1 I. WASHER AR
290A 8-3837-0532 1 I.WASHER AR
300 1 A-2411-1 .WASHER, FEATHER STOP 1
310 1 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 1 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 1 A-2435 .WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 1 8-3807 ´•NUT, PISTON 1
350 1 8-3683 ´•PISTON 1
350A 8-3237 ´•PISTON (ALTERNATE) 1
360 1 C-3317-210-1 ´•O-RING, PISTON ID 1
370 1 8-2491-3 ROD, PITCH CHANGE 1
380 1 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 1 C-3317-210-1 .O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 1 8-2457-2 FORK, PITCH CHANGE -PCLK 1
SUPERSEDED BY ITEM 400A
400A 8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 1 A-3323 RUBBING PLATES I 1 2
430 18-3842-0500 1 I ..SPRING PIN I 1 4
440 1 A-2217-1 BLOCK, PITCH CHANGE -2CLK 1 2
SUPERSEDED BY ITEM 4408
440A A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -PCLK 2
SUPERSEDED BY ITEM 4408
4408 A-2217-4 BLOCK, PITCH CHANGE -2CLK 2
SUPERSEDES ITEMS 440 AND 440A
440C A-2217-3 .BLOCK, PITCH CHANGE -PCLKF 2
450 1 A-3212 BUTTON, PITCH CHANGE BLOCK -2CLK 2
450A A-3212-1 .BUTTON, PITCH CHANGE BLOCK -PCLKF 2
470 C-3317-115-1 .O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
BHC-CPYF-PCLK(F)

Page 1038
61-10-17 Rev. 4May/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM I PART AIRLINE I NOMENCLATURE EFF IUPA

NUMBER I NUMBER STOCKNUMBER 1 1234167 CODE

480 D-2201-25 ´•HUB 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-B1-179
D-6530-11 ´•HUB 1

SUPERSEDES ITEM 480, POST SL HC-SL-61-179

D-2201-18 ´•HUB (ALTERNATE) 1

SUPERSEDED BY ITEM 480C, PRE SL HC-SLB~-179

D-6530-5 ´•HUB (ALTERNATE) 1

SUPERSEDES ITEM 4808, POST SL HC-SL-B1-179

500 A-2249 GUIDE BUSHING f

580 1 A-2431 ´•BOLT 6

590 1 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS iN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10

610 A-2043-1 .NUT 10

8-6588-1 LUBRICATION FITTING 4

1980
1980AI A-279 LUBRICATION FITTING (ALTERNATE) 4

1990 8-6544 CAP, LUBRICATION FITTING 4

-2000 1 CRP-323 ´•DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413 BUSHING, PITCH CHANGE KNOB -2CLK 1 2

A-2413-2 BUSHING, PITCH CHANGE KNOB QCLKF 1 2

3010 1 8-3883-4339 ´•SEAL, BLADE 2

3020 1 A-2202-8 SPLIT BEARING, HUB SIDE RACE 2

3030 1 8-6144 1/2" DIAMETER STEEL BALL 50

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

3040 1 8-3211 ´•SPACER, BALL 2

3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 1 A-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 8-2256 PRELOAD PLATE UNIT 2

3080 8-2222 PRELOAD PLATE 1

3090 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 1 A-3204 SCREW, SOCKET HEAD 1

3110 1 8-3368 ´•´•NUT, JAM i

1014 F-FLANGE MOUNTING PARTS

4000 C-331 7-228 ´•O-RING, FLANGE 1

4020 A-2429-3 STUD, HUB MOUNTING 6

4030 A-i 381 ´•WASHER, HARD, STAINLESS 6

4040 1 A-2044 NUT, SELF LOCKING 6

4050 1 8-6138-8-9 .5002" X 1 1/8" DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 B-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

0-2271
ITEM NOT ILLUSTRATED
BHC-C31YF-PCLK(F)

1039
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GOPage
 PROPELLER MAIMTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART I AIRLINE I NOMENCLATURE I EFF IUPA

NUMBER NUMBER STOCKNUMBER 1234587 CODE

PROPELLER PARTS
1004 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-1 938 ´•VALVE, AIR 1
50 A-2404-1 1 I LOW STOP I I 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 1 I´•CYLINDER I I 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 ´•O-RING, CYLINDER ID 1
100 8-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
-160 8-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 160A
-160A 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 160
280 A-3205 1 I´•SCREW I I 1
300 A-2411-1 .WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP f
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330AI A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 ´•NUT, PISTON 1
350 1 8-3683 1 I. PISTON I I 1
350A 8-3237 ´•PISTON (ALTERNATE) 1
360 1 C-3317-210-1 ´•O-RING, PISTON ID 1
370 1 8-2491-3 ROD, PITCH CHANGE 1
380 1 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 1 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 1 8-2457-2 FORK, PITCH CHANGE QC(L)KU 1
SUPERSEDED BY ITEM 400A
400AI 8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 1 A-3323 RUBBING PLATES 2
430A18-3842-0500 SPRING PIN 4
440 1 A-2217-1 BLOCK, PITCH CHANGE -2C(L)KU 2
SUPERSEDED BY ITEM 4408
440AI A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2C(L)KU 2
SUPERSEDED BY ITEM 4408
4408 A-2217-4 BLOCK, PITCH CHANGE -PC(L)KU 2
SUPERSEDES ITEMS 440 AND 440A
440CI A-2217-3 BLOCK, PITCH CHANGE IPC(L)KUF 2
450 A-3212 BUTTON, PITCH CHANGE BLOCK -2C(L)KU 2
450A A-3212-1 .BUTTON, PITCH CHANGE BLOCK I-2C(L)KUF 2
470 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

0-2292
ITEM NOT ILLUSTRATED
BHC-CSYF-SC(L)KU(F)

ILLUSTRATED PARTS LIST 61 ’1 0’1 7 Rev. 4 May/9Page 1040

 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

FIG.IITEM I PART AIRLINE NOMENCLATURE EFF IUPA

NUMBERI NUMBER STOCKNUMBER 12345~7 CODE

480 1 D-2201-25 ´•HUB 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
480A D-6530-11 ´•HUB 1
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
48081 D-2201-18 ´•HUB (ALTERNATE) 1
SUPERSEDED BY ITEM 480C, PRE SL HC-SL-61-179
480C D-6530-5 .HUB (ALTERNATE) 1
SUPERSEDES ITEM 4808, POST SL HC-SLdl-179
500 1 A-2249 GUIDE BUSHING 1

580 1 A-2431 ´•BOLT 6

590 1 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10
610 1 A-2043-1 ´•NUT 10

1980 1 A-279 LUBRICATION FITTING 4

1990 1 B-6544 CAP, LUBRICATION FITTING 4

-2000 CPR-41 ´•DECAL 1

-2020 CAU002 ´•DECAL 1

-2030 HI-102 ´•DECAL 1

1010 BLADE RETENTION PARTS

3000 lA-2413 BUSHING, PITCH CHANGE KNOB -2C(L)KU 2

3000A A-2413-2 BUSHING, PITCH CHANGE KNOB I-PC(L)KUF 2

3010 1B-3883-4339 ´•SEAL, BLADE 2
3020 IA-2202-B SPLIT BEARING, HUB SIDE RACE 2

3030 1B-6144 1/2" DIAMETER STEEL BALL 50

-3030A B-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
3040 18-3211 ´•SPACER, BALL 2

3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 lA-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 1B-2256 PRELOAD PLATE UNIT 2

3080 18-2222 PRELOAD PLATE 1

3090 1B-6679 RACE, INNER BLADE BORE BEARING 1

3100 1A3204 SCREW, SOCKET HEAD 1

3110 1 8-3368 ´•´•NUT, JAM 1

1014 F-FLANGE MOUNTING PARTS

4000 C-331 7-228 ´•O-RING, FLANGE 1

4020 A-2429-3 STUD, HUB MOUNTING 6

4030 IA-1381 ´•WASHER, HARD, STAINLESS 6

4040 A-2044 NUT, SELF LOCKING 6

4050 18-6138-8-9 .5002" X 1 1/8" DOWEL PIN 2

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-~292
ITEM NOT ILLUSTRATED
BHC-CSYF-1C(L)KU(F)

Page 1041
ILLUSTRATED PARTS LIST ~1 -1 0-17 Rev. 6Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG./ITEM I PART AIRLINE NOMENCLATURE I EFF IUPA

NUMBER NUMBER STOCK NUMBER I 1 3 4 Is 7 CODE

PROPELLER PARTS
1004110 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-l 938 ´•VALVE, AIR 1
50 A-2404-1 LOW STOP 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER 1
-80 A-862-3 BUSHING, CYLINDER 1
90 C-331 7-427-1 ´•O-RING, CYLINDER ID 1
100 8-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
-160 1 8-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 160A
-160A 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 160
280 1 A-3205 ´•SCREW 1
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A B-3837-0532 .WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 ´•NUT, PISTON 1

350 8-3683 .PISTON 1

350A 8-3237 ´•PISTON (ALTERNATE) 1

360 C-331 7-21 0-1 ´•O-RING, PISTON ID 1

370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-3 FORK, PITCH CHANGE 1
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN 4
440 A-2217-3 BLOCK, PITCH CHANGE 2
450 lA-3212-1 BUTTON, PITCH CHANGE BLOCK 2
470 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2292
ITEM NOT ILLUSTRATED
(B)HC-CPYF-PCUF EXCEPT CESSNA 310A-n

1042
61-10-17
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 117D

FIG.IITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER I 1 2 3 4 5 s7 CODE

480 1 D-2201 .HUB HC- I 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-B1-179
D-6530-1 ´•HUB HC- I 1
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
D-2201-4 ´•HUB BHC- I 1
SUPERSEDED BY ITEM 480C, PRE SL HC-SL-61-179
0-6530-2 ´•HUB BHC- I 1
SUPERSEDED BY ITEM 480D, PRE SL HC-SL-61-179
0-6530-11 ´•HUB BHC- I 1

SUPERSEDES ITEMS 480B,480C

500 A-2249 GUIDE BUSHING 1

580 1 A-2431 ´•BOLT 6

590 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10

610 A-2043-1 .NUT 10

1980 A-279 LUBRICATION FITTING 4

1990 8-6544 CAP, LUBRICATION FITTING 4

-2000 CPR-41 ´•DECAL 1

-2020 CAU002 ´•DECAL 1

-2030 HI-i 02 ´•DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413-2 BUSHING, PITCH CHANGE KNOB 2

3010 8-3883-4339 ´•SEAL, BLADE 2

3020 A-2202-B SPLIT BEARING, HUB SIDE RACE 2

3030 8-6144 112" DIAMETER STEEL BALL 50

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

3040 1 8-3211 ´•SPACER, BALL 2

3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 1 A-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 8-2256 PRELOAD PLATE UNIT 2

3080 8-2222 PRELOAD PLATE 1

3090 8-6679 1 I RACE, INNER BLADE BORE BEARING 1

3100 A-3204 SCREW, SOCKET HEAD 1

3110 1 8-3368 ´•´•NUT, JAM 1

1014 F-FLANGE MOUNTING PARTS

4000 1 C-3317-228 ´•O-RING, FLANGE 1

4020 1 A-2429-4 STUD, HUB MOUNTING 6

4030 A-1381 ´•WASHER, HARD, STAINLESS 6

4040 A-2044 NUT, SELF LOCKING 6

4050 8-6138-8-9 ’.5002" X1 1/8" DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2292
ITEM NOT ILLUSTRATED
(B)HC-C2YFI2CUF EXCEPT CESSNA 310A-H

Page 1033
ILLUSTRATED PARTS LIST ~1’10’17 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

FIG.IITEM PART AIRLINE NOMENCLATURE EFF IUPA

NUMBERI NUMBER STOCKNUMBER 1234567 CODE

PROPELLER PARTS
1004 10 1 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-l 938 ´•VALVE, AIR 1
50 A-2404-1 LOW STOP 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 ´•O-RING, CYLINDER ID 1
100 8-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
-160 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
280 A-3205 ´•SCREW 1
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 ´•NUT, PISTON 1

350 8-3683 ´•PISTON 1

350A 8-3237 ´•PISTON (ALTERNATE) 1
360 C-331 7-21 0-1 ´•O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-3 FORK, PITCH CHANGE 1
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN 4
440 A-2217-3 BLOCK, PITCH CHANGE 2
450 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2292
ITEM NOT ILLUSTRATED
HCICPYF-PCUF CESSNA 310A-H

Page 1044
61-1 0-17 May/99
Rev. 4
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM I PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCKNUMBER 1234587 CODE

480 D-2201 ´•HUB 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179

D-6530-12 ´•HUB 1

SUPERSEDES ITEM 480, POST SL HC-SL-61-179

A-2249 GUIDE BUSHING 1
500
580 1 A-2431 ´•BOLT 6

1 A-2432 ´•BOLT 4
590
(WHEN USING SPINNER MOUNTING KIT, REPLACE
BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10

610 A-2043-1 ´•NUT 10

A-279 LUBRICATION FITTING 4

1980
1990 8-6544 CAP, LUBRICATION FITTING 4

-2000 1 CPR-41 ´•DECAL 1

1 CAU002 ´•DECAL 1
-2020
1 HI-102 ´•DECAL 1
-2030

1010 BLADE RETENTION PARTS

3000 A-2413-2 BUSHING, PITCH CHANGE KNOB 2

3010 8-3883-4339 ´•SEAL, BLADE 2

3020 A-2202-8 SPLIT BEARING, HUB SIDE RACE 2

3030 8-6144 1/2" DIAMETER STEEL BALL 50

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

1 8-3211 ´•SPACER, BALL 2

3040
3050 1 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

RING, BLADE BEARING RACE RETENTION 2

3060 1 A-2204
-3070 8-2256 PRELOAD PLATE UNIT 2

8-2222 PRELOAD PLATE 1

3080
8-6679 RACE, INNER BLADE BORE BEARING 1
3090
A-3204 SCREW, SOCKET HEAD 1
3100
1 8-3368 NUT, JAM 1
3110

1014 F-FLANCE MOUNTING PARTS

C-331 7-228 .O-RING, FLANGE 1
4000
4020 A-2429-4 STUD, HUB MOUNTING 6

4030 1 A-1381 ´•WASHER, HARD, STAINLESS 6

NUT, SELF LOCKING 6

4040 1 A-2044
4050 1 8-6138-8-9 1 I .5002" X 1 1/8" DOWEL PIN 2

BALANCEPARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

0-2292
ITEM NOT ILLUSTRATED
HCICSYF-PCUF CESSNA 310A-H

Page 1045
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART I AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER I STOCK NUMBER I l2345s7 CODE

PROPELLER PARTS
1001 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 1 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 1 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 1 8-1938 ´•VALVE, AIR 1
50 A-2404-1 LOW STOP 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2452-1 ´•CYLINDER I I 1
-80 A-862-6 ´•´•BUSHING, CYLINDER 1
90 1 C-3317-431-1 ´•O-RING, CYLINDER ID
100 1 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 1 830-21 AUTO HIGH PITCH STOP UNIT 1
120 8-2406-1 BRACKET, AUTO HIGH STOP 1
130 A-884 SPRING, AUTO HIGH STOP 4
140 A-2704-2 PIN, HIGH STOP 4
150 8-3838-3-5 1 I COTTER PIN I 1 4
280 A-3205 1 I. SCREW I I 1
290 8-3837-0563 1 I´•WASHER I IAR
290A 8-3837-0532 ´•WASHER AR
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 .WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 1 A-2499i10 SLEEVE, HIGH PITCH STOP 1
330 1 A-2435 WASHER, HIGH PITCH ADJUST AR
330AI A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 1 8-3807 ´•NUT, PISTON 1
350 1 8-2455 ´•PISTON I I 1
REPLACED BY ITEM 350A
350AI 8-3239 1 I´•PISTON I I 1
REPLACES ITEM 350
360 C-331 7-21 0-1 ´•O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-251 O-RING, CYLINDER MOUNTING
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 1 8-2457-2 FORK, PITCH CHANGE -2RB(D,E) 1
SUPERSEDED BY ITEM 400A
400AI 8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 1 A-3323 1 I RUBBING PLATES I 1 2
430 1 8-3842-0500 1 I SPRING PIN I 1 4
440 A-2217-1 BLOCK, PITCH CHANGE -PRB(D,E) 2
SUPERSEDED BY ITEM 4408
440A A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2RB(D,E) 2
SUPERSEDED BY ITEM 4408
4408 A-2217-4 BLOCK, PITCH CHANGE -PRB(D,E) 2
SUPERSEDES ITEMS 440 AND 440A
440C A-2217-3 BLOCK, PITCH CHANGE C2RB(D,E)F 2
450 A-3212 BUTTON, PITCH CHANGE BLOCK -PRB(D,E) 2
450A A-3212-1 .BUTTON, PITCH CHANGE BLOCK J´•PRB(D,E)F 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
(B)HCC2VF-2RB(D,E)(F)

ILLUSTRP;TED
P~RTS LIST 61’1 0’1 7 Rev. 4 May/9Page 1046
 PROPELLER MAINTENANCE MANUAL
nARTZELL 1170

FIC.IITEM PART AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER STOCK NUMBER I 1 2 3 4 a a 7 CODE

480 D-2201-4R ´•HUB BHC- I 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
480A D-6530-2R ´•HUB BHC- I 1
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
4808 D-2201R ´•HUB HC- I 1
SUPERSEDED BY ITEM 480C, PRE SL HC-SL-B1-179
D-6530-1R ´•HUB HC- I 1

SUPERSEDES ITEM 4808, POST SL HC-SL61-179

500 A-2249 GUIDE BUSHING 1

580 A-2431 ´•BOLT I 1 6

590 1 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 1 8-3834-0632 ´•WASHER 10

610 1 A-2043-1 ´•NUT 10

1980 1 8-6588-1 LUBRICATION FITTING 4

1980A A-279 1 I LUBRICATION FITTING (ALTERNATE) 4

1990 1 8-6544 CAP, LUBRICATION FITTING 4

-2000 1 CRP-323 ´•DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413 BUSHING, PITCH CHANGE KNOB -2RB(D,E) 2

3000AI A-2413-2 BUSHING, PITCH CHANGE KNOB ~2RB(D,E)F 2

3010 1 8-3883-4339 ´•SEAL, BLADE 2

3020 1 A-2202-8 SPLIT BEARING, HUB SIDE RACE 2

3030 1 8-6144 1/2" DIAMETER STEEL BALL I 1 50

-3030AI 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

3040 1 8-3211 ´•SPACER, BALL 2

3050 1 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 1 A-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 8-2256 PRELOAD PLATE UNIT 2

3080 8-2222 PRELOAD PLATE 1

3090 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 1 A-3204 SCREW, SOCKET HEAD 1

3110 1 8-3368 ´•´•NUT, JAM 1

1014 F-FLANGE MOUNTING PARTS

4000 1(=-3317-228 ´•O-RING, FLANGE 1

4020 A-2429-4 STUD, HUB MOUNTING 6

4030 1 A-1381 ´•WASHER, HARD, STAINLESS 6

4040 1 A-2044 NUT, SELF LOCKING 6

4050 8-6138-8-9 .5002" X1 1/8" DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2271
ITEM NOT ILLUSTRATED
(B)HC-C2VF-2RB(D,E)(F)

Page 1047
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

FIG.IITEM I PART AIRLINE I NOMENCLATURE EFF IUPA

NUMBERI NUMBER STOCKNUMBER 12a4se7 CODE

PROPELLER PARTS
1001 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-l 938 ´•VALVE, AIR 1
50 A-2404-1 LOW STOP 1
60 C-3317-117 O-RING, LOW STOP 1
70 1 8-2452-1 ´•CYLINDER 1
-80 1 A-862-6 ´•´•BUSHING, CYLINDER 1
90 1 C-3317-431-1 ´•O-RING, CYLINDER ID
100 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 1 830-21 AUTO HIGH PITCH STOP UNIT 1
120 1 8-2406-1 BRACKET, AUTO HIGH STOP 1
130 1 A-884 SPRING, AUTO HIGH STOP 4
140 A-2704-2 PIN, HIGH STOP 4
150 8-3838-3-5 1 I COTTER PIN 4
280 A-3205 ´•SCREW I I 1
290 8-3837-0563 ´•WASHER AR
290A 8-3837-0532 ´•WASHER AR
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 ´•NUT, PISTON 1
350 8-2455 ´•PISTON I I 1
REPLACED BY ITEM 350A
350AI 8-3239 ´•PISTON 1
REPLACES ITEM 350
360 C-331 7-21 0-1 ´•O-RING, PISTON ID 1
370 1 8-2491-3 ROD, PITCH CHANGE 1
380 1 C-3317-251 O-RING, CYLINDER MOUNTING
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 1 8-2457-2 FORK, PITCH CHANGE -2RB(D,E) 1
SUPERSEDED BY ITEM 400A
400AI 8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 1 A-3323 1 I RUBBING PLATES 2
430 1 8-3842-0500 SPRING PIN I 1 4
440 1 A-2217-1 BLOCK, PITCH CHANGE -2RB(D,E) 2
SUPERSEDED BY ITEM 4408
440A A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2RB(D,E) 2
SUPERSEDED BY ITEM 4408
44081 A-2217-4 BLOCK, PITCH CHANGE -2RB(D,E) 2
SUPERSEDES ITEMS 440 AND 440A
A-2217-3 BLOCK, PITCH CHANGE ~2RB(D,E)F 2
450 1 A-3212 BU‘TTON, PITCH CHANGE BLOCK -2RB(D,E) 2
450AI A-3212-1 BUTTON, PITCH CHANGE BLOCK ~2RB(D,E)F 2
470 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
(C or D)HC-C2YF-2RB(D,E)(F)

Page 1048
ILLUSTRATED PARTS LIST 61 -1 0-1 7 Rev. 4May/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER ISTOCKNUMBER 1234187 CODE

480 D-2201-8R ´•HUB CHC- I 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SLB~-179
480A D-6530-3R .HUB CHC- I 1

SUPERSEDES ITEM 480, POST SL HC-SL-61-179

4808 D-2201-10R ´•HUB DHC- I 1
SUPERSEDED BY ITEM 480C, PRE SL HC-SL-61-179
480C D-6530-4R ´•HUB DHC- I 1
SUPERSEDES ITEM 4808, POST SL HC-SL-61-179
500 A-2249 GUIDE BUSHING 1

580 lA-2431 ´•BOLT 6

590 lA-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 B-3834-0632 ´•WASHER 10

610 A-2043-1 ´•NUT 10

1980 8-6588-1 LUBRICATION FITTING 4

1980A A-279 .LUBRICATION FITTING (ALTERNATE) 4

1990 8-6544 CAP, LUBRICATION FITTING 4

-2000 CRP-323 ´•DECAL 1

1010 BLADE RETENTION PARTS

3000 lA-2413 BUSHING, PITCH CHANGE KNOB -2RB(D,E) 2

3000A A-2413-2 BUSHING, PITCH CHANGE KNOB SRB(D,E)F 2

3010 1B-3883-4339 ´•SEAL, BLADE 2

3020 lA-2202-8 SPLIT BEARING, HUB SIDE RACE 2

3030 8-6144 1/2" DIAMETER STEEL BALL 50

-3030A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

3040 8-3211 ´•SPACER, BALL 2

3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 lA-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 8-2256 PRELOAD PLATE UNIT 2

3080 18-2222 PRELOAD PLATE 1

3090 18-6679 RACE, INNER BLADE BORE BEARING I I 1

3100 lA-3204 SCREW, SOCKET HEAD 1

3110 8-3368 ´•´•NUT, JAM 1

1014 F-FLANGE MOUNTING PARTS

4000 1G3317-228 ´•O-RING, FLANGE 1

4020 1A-2429-4 STUD, HUB MOUNTING 6

4030 IA-1381 ´•WASHER, HARD, STAINLESS 6

4040 lA-2044 NUT, SELF LOCKING 6

4050 8-6138-8-9 1 I .5002" X 1 1/8" DOWEL PIN 2

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2271
ITEM NOT ILLUSTRATED
(C or D)HC-C2YF-2RB(D,E)(F)

Page 1049
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

FIG.IITEM PART I AIRLINE I NOMENCLATURE I EFF IUPA

NUMBER NUMBER STOCK NUMBER I 1 2 3 4 a s 7 CODE

PROPELLER PARTS
1001 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 1 8-1938 ´•VALVE, AIR 1
50 1 A-2404-1 LOW STOP I I 1
60 1 C-3317-117 O-RING, LOW STOP 1
70 1 8-2423-1 ´•CYLINDER I I 1
-80 1 A-862-3 ´•´•BUSHING, CYLINDER 1
90 1 C-3317-427-1 ´•O-RING, CYLINDER ID
100 1 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 1 830-21 AUTO HIGH PITCH STOP UNIT 1
120 8-2406´•1 BRACKET, AUTO HIGH STOP 1
130 A-884 SPRING, AUTO HIGH STOP 4
140 A-2704-2 PIN, HIGH STOP 4
150 8-3838-3-5 COTTER PIN 4
280 1 A-3205 .SCREW 1
290 8-3837-0563 ´•WASHER I IAR
290A 8-3837-0532 ´•WASHER I IAR
300 1 A-2411-1 WASHER, FEATHER STOP 1
310 1 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 1 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST I IAR
340 1 8-3807 ´•NUT, PISTON 1
350 1 8-3683 ´•PISTON I I 1
350A 8-3237 ´•PISTON (ALTERNATE) 1
360 1 C-3317-210-1 ´•O-RING, PISTON ID 1
370 1 8-2491-3 ROD, PITCH CHANGE 1
380 1 C-3317-247 O-RING, CYLINDER MOUNTING
390 1 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER- 1
SIDE HUB HALF
400 1 8-2457-2 FORK, PITCH CHANGE -28(D,E) 1
SUPERSEDED BY ITEM 400A
400A 8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 1 A-3323 RUBBING PLATES I 1 2
430 1 8-3842-0500 SPRING PIN I 1 4
440 1 A-2217-1 BLOCK, PITCH CHANGE -28(D,E) 2
SUPERSEDED BY ITEM 4408
440A A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -PB(D,E) 2
SUPERSEDED BY ITEM 4408
4408 A-2217-4 BLOCK, PITCH CHANGE -28(D,E) 2
SUPERSEDES ITEMS 440 AND 440A
440C A-2217-3 BLOCK, PITCH CHANGE -28(D,E)F 2
450 1 A-3212 BUTTON, PITCH CHANGE BLOCK -2B(D,E) 2
450AI A-3212-1 BUTTON, PITCH CHANGE BLOCK -28(D,E)F 2
470 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
HC-CSYK-SB(D,E)(F)

Page 1050
ILLUSTRPITED PARTS LIST 61’1 0’1 7 Rev. 4May/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL illD

FIG./ITEM PART AIRLINE I NOMENCLATURE I EFF UPA

NUMBER i NUMBER STOCK NUMBER 1234567 1 CODE

480 D-2201 -2 1 I HUB 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
D-6522-1 ´•HUB 1
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
500 A-2249 GUIDE BUSHING I I 1
580 A-2431 ´•BOLT I 1 6
590 A-2432 ´•BOLT I 1 4
(WHEN USING SPINNER MOUNTING KIT, REPLACE
BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER I I 10
610 1 A-2043-1 ´•NUT I I 10
1980 1 8-6588-1 LUBRICATION FITTING 4
1980AI A-279 LUBRICATION FITTING (ALTERNATE) 4
1990 1 8-6544 CAP, LUBRICATION FITTING 4
-2000 CRP-323 I I´•DECAL 1

1010 1 I I BLADE RETENTION PARTS

3000 A-2413 BUSHING, PITCH CHANGE KNOB -2B(D,E) 2
A-2413-2 BUSHING, PITCH CHANGE KNOB QB(D,E)F 2
3010 8-3883-4339 SEAL, BLADE 2
3020 A-2202-8 SPLIT BEARING, HUB SIDE RACE 2
3030 8-6144 1/2" DIAMETER STEEL BALL I 1 50
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
3040 8-3211 SPACER, BALL 2
3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2
3060 A-2204 RING, BLADE BEARING RACE RETENTION 2
3070 8-2256 PRELOAD PLATE UNIT I 1 2
3080 8-2222 PRELOAD PLATE I I 1
3090 8-6679 RACE, INNER BLADE BORE BEARING 1
3100 A-3204 SCREW, SOCKET HEAD 1
3110 8-3368 ´•´•NUT, JAM I 1

K-FLANGE MOUNTING PARTS

-4000 C-331 7-228 O-RING, FLANGE 1
-4060 A-2067 STUD, HUB MOUNTING 6
-4070 A-1381 WASHER, HARD, STAINLESS 6
-4080 A-2069 1 I NUT, HEXAGON CASTLEATED 6
-4090 8-3842-0750 SPRING PIN I 1 6

BALANCEPARTS
-9000 8-3840-( ´•SCREW I I AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

0-2271
ITEM NOT ILLUSTRATED
HC-CSYK-PB(D,E)(F)

ILLUSTRP~TED PP~RTS UST 61’1 0’1 7 Rev. 4 May/9Page 1051

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

PROPELLER PARTS
1001 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 1 8-1938 VALVE, AIR 1
50 1 A-2404-1 LOW STOP 1
A-2404-3 LOW STOP (ALTERNATE) -2CE(F) 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 1 ´•I CYLINDER I I 1
-80 A-862-3 ´•´•BUSHING, CYLINDER I I 1
90 C-331 7-427-1 O-RING, CYLINDER ID
100 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 830-30 AUTO HIGH PITCH STOP UNIT 1
120 8-2406-3 BRACKET, AUTO HIGH STOP 1
120A 8-2406-1 BRACKET, AUTO HIGH STOP (ALTERNATE) 1
130 A-884 SPRING, AUTO HIGH STOP 2
140 A-2407 PIN, HIGH STOP 2
150 8-3838-3-5 COTTER PIN 2
280 A-3205 ´•SCREW 1
290 8-3837-0563 ´•WASHER AR
290A 8-3837-0532 ´•WASHER AR
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3337-0532 WASHER, FEATHER ADJUST AR
320 1 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 1 I WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 NUT, PISTON 1
350 8-3683 PISTON 1
350A 8-3237 PISTON (ALTERNATE) 1
360 C-331 7-210-1 O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-2 FORK, PITCH CHANGE -2C(D,E) 1
SUPERSEDED BY ITEM 400A
400A 8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 A-3323 RUBBING PLATES 2
430 1 8-3842-0500 SPRING PIN 4
440 1 A-2217-1 BLOCK, PITCH CHANGE I -2C(D,E) 2
SUPERSEDED BY ITEM 4408
440A A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2C(D,E) 2
SUPERSEDED BY ITEM 4408
4408 A-2217-4 BLOCK, PITCH CHANGE -2C(D,E) 2
SUPERSEDES ITEMS 440 AND 440A
440C A-2217-3 BLOCK, PITCH CHANGE -2C(D,E)F 2
450 A-3212 BUTTON, PITCH CHANGE BLOCK QC(D,E) 2
450A A-3212-1 BUTTON, PITCH CHANGE BLOCK -2C(D,E)F 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

0-2271
ITEM NOT ILLUSTRATED
HC-CPYK-2CD(F)

ILLUSTRATED PARTS LIST 61 ’1 0’1 7 Rev. 4 May/9Page 1052

 PROPELLER MAINTENANCE MANUAL
HARTZELL ;1~tb

FIG./ITEM PART AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

480 D-2201-2 HUB 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
D-6522-1 HUB I I 1
SUPERSEDES ITEM 480, POST SL HC-SL-B1-179
500 A-2249 GUIDE BUSHING I I 1
580 A-2431 BOLT 6
590 A-2432 BOLT 4
(WHEN USING SPINNER MOUNTING KIT, REPLACE
BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10
610 A-2043-1 NUT 10
1980 8-6588-1 LUBRICATION FITTING 4
1980AI A-279 LUBRICATION FITTING (ALTERNATE) 4
1990 8-6544 CAP, LUBRICATION FITTING 4
-2000 CRP-323 DECAL I I 1

1010 BLADE RETENTION PARTS

3000 A-2413 BUSHING, PITCH CHANGE KNOB -PC(D,E) 2
A-2413-2 BUSHING, PITCH CHANGE KNOB -2C(D,E)F 2
3010 8-3883-4339 SEAL, BLADE 2
3020 A-2202-B SPLIT BEARING, HUB SIDE RACE 2
3030 8-6144 112" DIAMETER STEEL BALL 50
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
3040 8-3211 SPACER, BALL 2
3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2
3060 A-2204 RING, BLADE BEARING RACE RETENTION 2
3070 8-2256 PRELOAD PLATE UNIT 2
3080 8-2222 PRELOAD PLATE 1 I f
3090 8-6679 RACE, INNER BLADE BORE BEARING 1
3100 A-3204 SCREW, SOCKET HEAD i
3110 8-3368 ´•´•NUT, JAM i

K-FLANGE MOUNTING PARTS

-4000 C-331 7-228 O-RING, FLANGE 1

-4060 A-2067 STUD, HUB MOUNTING 6

-4070 A-1381 WASHER, HARD, STAINLESS 6
-4080 A-2069 NUT, HEXAGON CASTLEATED 6
-4090 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT I IAR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

0-2271
ITEM NOT ILLUSTRATED
HC-CPYK-ZCD(F)

ILLUSTRP~TED PP~RTS LIST ~1’1 0’1 7 Rev. 4 May/9Page 1053

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG./ITEM PART I AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

PROPELLER PARTS
1004 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-1 69-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-1 938 VALVE, AIR 1
50 A-2404-1 LOW STOP 1
50A A-2404-3 LOW STOP (ALTERNATE) 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER I I 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 O-RING, CYLINDER ID 1
100 8-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
160 8-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 160A
-160A 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 160
280 A-3205 1 I´•SCREW I I 1
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 NUT, PISTON 1
350 8-3683 PISTON 1
350A 8-3237 PISTON (ALTERNATE) 1
360 C-331 7-21 0-1 O-RING, PISTON ID I I 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-3 FORK, PITCH CHANGE 1
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN 4
440 A-2217-3 BLOCK, PITCH CHANGE 2
450 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2292
ITEM NOT ILLUSTRATED
HC-C2YK-2CDUF

ILLUSTRPITED PARTS LIST 61’1 0-1 7 Rev. 4 Mayi9Page 1054

 PROPELLER MAINTENAMCE MANUAL
HA RTZ E L L liSb:

FIG.IITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

480 1 D-2201-2 ´•HUB 1

SUPERSEDED BY ITEM 4808, PRE SL HC-SL-61-179

480A D-2201-16 ´•HUB 1
SUF)ERSEDED BY ITEM 4808, PRE SL HC-SLB1-179
4808 D-6522-1 HUB 1

SUPERSEDES ITEM 480 AND ITEM 480A

POST SL HC-SL-61-179
500 A-2249 GUIDE BUSHING 1

580 A-2431 ´•BOLT 6

590 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10
610 A-2043-1 NUT 10
1980 A-279 LUBRICATION FITTING 4
1990 8-6544 CAP, LUBRICATION FITTING 4
-2000 CPR-41 DECAL 1

-2020 CAU002 ´•DECAL

-2030 HI-102 DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413-2 BUSHING, PITCH CHANGE KNOB 2
3010 8-3883-4339 SEAL, BLADE 2

3020 A-2202-8 SPLIT BEARING, HUB SIDE RACE 2

3030 8-6144 1/2" DIAMETER STEEL BALL 50

3030A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

3040 8-3211 SPACER, BALL 2
3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2
3060 A-2204 RING, BLADE BEARING RACE RETENTION 2
-3070 8-2256 PRELOAD PLATE UNIT 2

3080 8-2222 PRELOAD PLATE I I 1

3090 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 A-3204 SCREW, SOCKET HEAD 1

3110 8-3368 ´•´•NUT, JAM 1

I(-FLANGE MOUNTING PARTS

-4000 C-331 7-228 O-RING, FLANGE 1

-4060 A-2067 STUD, HUB MOUNTING 6

-4070 A-1381 WASHER, HARD, STAINLESS 6
-4080 A-2069 NUT, HEXAGON CASTLEATED 6
-4090 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2292
ITEM NOT ILLUSTRATED
HC-CPYK-PCDUF

1055
ILLUSTRATEO PARTS LIST 61 ’1 0’1 7 Rev. 4 Mayi9Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL li~D

FIG./ITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

PROPELLER PARTS
1001 10 1 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 1 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 1 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (AEFER TO FIG. 1013) 1
40 1 8-1938 VALVE, AIR 1
50 1 A-2404-3 LOW STOP (ALTERNATE) 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER I I 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 O-RING, CYLINDER ID
100 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 830-30 AUTO HIGH PITCH STOP UNIT 1
120 8-2406-3 BRACKET, AUTO HIGH STOP 1
120AI 8-2406-1 BRACKET, AUTO HIGH STOP (ALTERNATE) 1
130 A-884 SPRING, AUTO HIGH STOP I 1 2
140 A-2407 PIN, HIGH STOP 2
150 8-3838-3-5 COTTER PIN 2
280 A-3205 ´•SCREW 1
290 8-3837-0563 ´•WASHER AR
8-3837-0532 ´•WASHER AR
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310AI 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 NUT, PISTON 1
350 8-3683 PISTON 1
350AI 8-3237 PISTON (ALTERNATE) 1
360 C-331 7-210-1 O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING
390 1 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 1 8-2457-2 FORK, PITCH CHANGE -2CE 1
SUPERSEDED BY ITEM 400A
8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 1 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN 4
440 1 A-2217-1 BLOCK, PITCH CHANGE -2CE 2
SUPERSEDED BY ITEM 4408
A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2CE 2
SUPERSEDED BY ITEM 4408
A-2217-4 BLOCK, PITCH CHANGE -2CE 2
SUPERSEDES ITEMS 440 AND 440A
A-2217-3 BLOCK, PITCH CHANGE I -2CEF 2
450 1 A-3212 8UTTON, PITCH CHANGE BLOCK -2CE 2
A-3212-1 BUTTON, PITCH CHANGE BLOCK -2CEF 2
470 1 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
HC-CSYK-~CE(F)

ILLUSTRATED PARTS LIST 61’1 0’1 7 Rev. 4 May/9Page 1056

 PROPELLER MAINTENANCE MANUAL
HARTZELL tllbi;

FIG.IITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

480 D-2201-2 ´•HUB I I 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
D-6522-1 ´•HUB 1
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
500 A-2249 GUIDE BUSHING 1
580 A-2431 ´•BOLT 6
590 A-2432 ´•BOLT I 1 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 B-3834-0632 ´•WASHER 10
610 A-2043-1 ´•NUT I 1 10
1980 B-6588-1 LUBRICATION FITTING 4

1980AI A-279 LUBRICATION FITTING (ALTERNATE) 4

1990 B-6544 CAP, LUBRICATION FITTING 4
2000 CRP-323 ´•DECAL I I 1

1010 BLADE RETENTION PARTS

3000 A-2413 BUSHING, PITCH CHANGE KNOB -2CE 2
A-2413-2 BUSHING, PITCH CHANGE KNOB -2CEF 2
3010 B-3883-4339 SEAL, BLADE 2
3020 A-2202-B SPLIT BEARING, HUB SIDE RACE 2
3030 8-6144 1/2" DIAMETER STEEL BALL 50
B-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
3040 B-3211 SPACER, BALL 2
3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2
3060 A-2204 RING, BLADE BEARING RACE RETENTION 2
-3070 B-2256 PRELOAD PLATE UNIT 2
3080 8-2222 PRELOAD PLATE 1
3090 8-6679 RACE, INNER BLADE BORE BEARING 1
3100 A-3204 SCREW, SOCKET HEAD 1
3110 B-3368 ´•´•NUT, JAM 1

K-FLANGE MOUNTING PARTS

-4000 C-331 7-228 O-RING, FLANGE 1
-4060 A-2067 STUD, HUB MOUNTING 6
-4070 A-1381 WASHER, HARD, STAINLESS 6
-4080 1 A-2069 NUT, HEXAGON CASTLEATED 6
-4090 B-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 B-3840-( ´•SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2271
ITEM NOT ILLUSTRATED
HC-CZYK-PCE(F)

Page 1057
ILLUSTRATED PARTS LIST 61 -1 0’1 7 Rev. 4 May/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 1170

FIG.IITEM PART AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

PROPELLER PARTS
1004 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 1k169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-1938 VALVE, AIR 1
50 A-2404-1 LOW STOP 1
50A A-2404-3 LOW STOP (ALTERNATE) 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 O-RING, CYLINDER ID 1
100 8-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
160 8-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 160A
160AI 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 160
280 A-3205 ´•SCREW 1
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 NUT, PISTON 1
350 8-3683 PISTON 1
350A 8-3237 PISTON (ALTERNATE) 1
360 C-331 7-210-1 O-RING, PISTON ID 1
370 8-2491-3 1 I ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-3 FORK, PITCH CHANGE 1
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN 4
440 A-2217-3 BLOCK, PITCH CHANGE 2
450 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2292
ITEM NOT ILLUSTRATED
HC-C2YK-2CEUF EXCEPT PIPER PA44-180

ILLUSTRPITED P~RTS LIST 61 -1 0’17 1058

 PROPELLER MAINTENANCE MANUAL
HARTZELL

FIG.IITEM I PART AIRLINE I NOMENCLATURE EFF UPA

NUMBER NUMBER STOCKNUMBER 1234567 CODE

480 D-2201-2 HUB 1

SUPERSEDED BY ITEM 4808, PRE SL HC-SL-61-179
480A D-2201-16 HUB 1
SUPERSEDED BY ITEM 4808, PRE SL HC-SL-61-179
48081 D-6522-1 HUB i
SUPERSEDES ITEM 480 AND ITEM 480A
POST SL HC-SL-61-179
500 1 A-2249 GUIDE BUSHING 1
580 1 A-2431 ´•BOLT 6
590 1 A-2432 ´•BOLT I 1 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER I r 10
610 1 A-2043-1 NUT I 1 10
1980 A-279 LUBRICATION FITTING I i 4
1990 8-6544 CAP, LUBRICATION FITTING 4
2000 CPR-41 DECAL I
2020 CAUOO2 DECAL I I 1

-2030 HI-102 DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413-2 BUSHING, PITCH CHANGE KNOB 2
3010 8-3883-4339 SEAL, BLADE 2
3020 A-2202-8 SPLIT BEARING, HUB SIDE RACE 2
3030 8-6144 112" DIAMETER STEEL BALL 50
-3030A 8-6144-650 112" DIAMETER STEEL BALL (650 PIECE BOX) RF
3040 8-3211 SPACER, BALL 2
3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2
3060 A-2204 RING, BLADE BEARING RACE RETENTION 2
-3070 8-2256 PRELOAD PLATE UNIT 2
3080 8-2222 PRELOAD PLATE 1

3090 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 A-3204 SCREW, SOCKET HEAD 1

3110 8-3368 ´•´•NUT, JAM 1

K-FLANGE MOUNTING PARTS

-4000 C-331 7-228 O-RING, FLANGE 1

-4060 1 A-2067 STUD, HUB MOUNTING 6

-4070 A-1381 WASHER, HARD, STAINLESS 6
-4080 1 A-2069 NUT, HEXAGON CASTLEATED 6
-4090 1 8-3842-0750 SPRING PIN 6

BALANCE PARTS
9000 8-3840-( ´•SCREW AR
9020 A-2424(A)-( BALANCE WEIGHT I IAR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D2292
ITEM NOT ILLUSTRATED
HC-C2YK-2CEUF EXCEPT PIPER PA44-180

1 059
ILLUSTRATED PARTS LIST ~1’1 0’17 Rev. 4 May/9Page
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG./ITEM PART AIRLINE NOMENCLATURE EFF IUPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

PROPELLER PARTS
1004 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 1 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-l 938 VALVE, AIR 1
50 1 A-2404-1 LOW STOP 1
60 1 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 1 I CYLINDER 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 O-RING, CYLINDER ID 1
100 8-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
160 8-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 1608
-160AI 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 1608
-16081 B-l 106 1 I SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEMS 1GOAND160A
280 1 A-3205 ´•SCREW 1
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310AI 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 NUT, PISTON I I 1
350 8-3683 PISTON I I 1
8-3237 PISTON (ALTERNATE) 1
360 C-331 7-210-1 1 I O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-3 FORK, PITCH CHANGE 1
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN I 1 4
440 A-2217-3 BLOCK, PITCH CHANGE I 1 2
450 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2292
ITEM NOT ILLUSTRATED
HC-CPYK-2CEUF PIPER PA44-180

61-10-17 1060
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117[)

FIG./ITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCKNUMBER 1234567 CODE

480 D-2201-2 ´•HUB 1

SUPERSEDED BY ITEM 4808, PRE SL HC-SL-61-179
480A D-2201-16 HUB 1
SUPERSEDED BY ITEM 4808, PRE SL HC-SL-61-179
4808 D-6522-1 ´•HUB 1
SUPERSEDES ITEM 480 AND ITEM 480A
POST SL HC-SL-61-179
500 1 A-2249 GUIDE BUSHING 1

580 1 A-2431 ´•BOLT 6

590 1 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10
610 A-2043-1 ´•NUT 10
1980 A-279 LUBRICATION FI~ING 4
1990 8-6544 GAP, LUBRICATION FITTING 4
-2000 CPR-41 ´•DECAL 1

-2020 CAU002 ´•DECAL 1

2030 HI-102 ´•DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413-2 BUSHING, PITCH CHANGE KNOB 2
3010 8-3883-4339 SEAL, BLADE 2
3020 A-2202-B SPLIT BEARING, HUB SIDE RACE 2
3030 8-6144 112" DIAMETER STEEL BALL I 1 50
-3030A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
3040 8-3211 SPACER, BALL 2
3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 A-2204 RING, BLADE BEARING RACE RETENTION 2

3070 8-2256 1 I PRELOAD PLATE UNIT 2
3080 8-2222 PRELOAD PLATE I 1

3090 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 A-3204 SCREW, SOCKET HEAD t

3110 8-3368 ´•´•NUT, JAM 1

K-FLANGE MOUNTING PARTS

-4000 C-331 7-228 O-RING, FLANGE i

-4060 A-2067 STUD, HUB MOUNTING 6

-4070 A-1381 WASHER, HARD, STAINLESS 6
-4080 A-2069 NUT, HEXAGON CASTLEATED 6
-4090 8-3842-0750 SPRING PIN I 1 6

BALANCE PARTS
9000 8-3340-( ´•SCREW I IAR
9020 A-2424(A)-( BALANCE WEIGHT I IAR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2292
ITEM NOT ILLUSTRATED
HC-C2YK-2CEUF PIPER PA44-180

1061
ILLUSTRATED PARTS LIST 61 ’1 0’1 7 Rev. 4 May/9 Page
 PROPELLER MAINTENANCE MANUAL
HARTZ ELL 117D

FIG./ITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCKNUMBER 1234567 CODE

PROPELLER PARTS
1001 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 1 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 1 8-1938 VALVE, AIR 1
50 1 A-2404-3 LOW STOP 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 O-RING, CYLINDER ID
100 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 830-30 AUTO HIGH PITCH STOP UNIT 1
120 8-2406-3 BRACKET, AUTO HIGH STOP 1
120A 8-2406-1 BRACKET, AUTO HIGH STOP (ALTERNATE) 1
130 A-884 SPRING, AUTO HIGH STOP 2
140 A-2407 PIN, HIGH STOP 2
150 8-3838-3-5 COTTER PIN 2
280 A-3205 ´•SCREW 1
290 8-3837-0563 ´•WASHER AR
290A 8-3837-0532 ´•WASHER AR
300 A-2411-1 WASHER, FEATHER STOP 1
310 1 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 NUT, PISTON 1
350 8-3683 PISTON 1
350A 8-3237 PISTON (ALTERNATE) 1
360 C-331 7-210-1 O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER- 1
SIDE HUB HALF
400 8-2457-2 FORK, PITCH CHANGE I -2CG 1
SUPERSEDED BY ITEM 400A
400A 8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN 4
440 A-2217-1 BLOCK, PITCH CHANGE I -2CG 2
SUPERSEDED BY ITEM 4408
440A A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2CG 2
SUPERSEDED BY ITEM 4408
4408 A-2217-4 BLOCK, PITCH CHANGE -2CG 1 2
SUPERSEDES ITEMS 440 AND 440A
440C A-2217-3 BLOCK, PITCH CHANGE I -2CGF 2
450 A-3212 BUTTON, PITCH CHANGE BLOCK -2CG 1 2
450A A-3212-1 BUTTON, PITCH CHANGE BLOCK -2CGF 12
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
HC-CPYK-PCG(F)

61-10-17 1062
 PROPELLER MAINTENANCE MANUAL
HARTZELL IliD

FIG.IITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

480 D-2201-2 HUB I I

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
D-6522-1 HUB 1
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
500 A-2249 GUIDE BUSHING 1

580 A-2431 ´•BOLT 6

590 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING t(lT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 B-3834-0632 ´•WASHER 10

610 A-2043-1 NUT 10

-900 C-1576 DAMPER ASSEMBLY 1

-910 A-1579 HEX HEAD SPACER TUBES 8

-920 A-1 580 ´•´•SPRING, DAMPER 8

-930 1 8-3851-0732 ´•´•WASHER 8

-940 A-1865-2 ´•´•WASHER 8
-950 C-l 567-1 1 I´•´•WEIGHT, DAMPER 1

960 A-1581 SILICONE GROMMET 8

-970 C-1568-1 FRICTION DISC 1

-980 C-1566-1 ´•´•PLATE, SUPPORT 1

-990 A-1 578 ´•´•SCREW 8

1980 8-6588-1 LUBRICATION FITTING 4

1980AI A-279 LUBRICATION FITTING (ALTERNATE) 4

1990 8-6544 1 I CAP, LUBRICATION FITTING 4

-2000 CRP-323 DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413 BUSHING, PITCH CHANGE KNOB I -2CG 2
A-2413-2 BUSHING, PITCH CHANGE KNOB 1 -2CGF 2

3010 8-3883-4339 SEAL, BLADE 2

3020 A-2202-8 SPLIT BEARING, HUB SIDE RACE I 1 2

3030 8-6144 1/2" DIAMETER STEEL BALL 50

8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

3040 8-3211 SPACER, BALL 2

3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 A-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 8-2256 PRELOAD PLATE UNIT 2

3080 8-2222 PRELOAD PLATE 1

3090 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 A-3204 1 I SCREW, SOCKET HEAD 1

3110 8-3368 ´•´•NUT, JAM 1

K´•FLANGE MOUNTING PARTS

-4000 1 C-3317-228 ´•O-RING, FLANGE 1

-4060 A-2067 STUD, HUB MOUNTING 6

-4070 A-1381 WASHER, HARD, STAINLESS 6

-4080 A-2069 NUT, HEXAGON CASTLEATED 6

-4090 8-3842-0750 SPRING PIN 6

BALANCE PARTS
SCREW AR
-9000 8-3840-(
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2271
ITEM NOT ILLUSTRATED
HC-CPYK-PCG(F)

1063
ILLUSTRATED PARTS LIST ~1 -1 O’i 7 Rev. 4 May/9Page
 PROPELLER
HARTZELL D711LAUN~M

FIG./ITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

PROPELLER PARTS
1001 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 B-1 938 VALVE, AIR 1
50 1 A-2404-1 LOW STOP 1
A-2404-3 LOW STOP (ALTERNATE) 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 O-RING, CYLINDER ID
100 1 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 1 830-30 AUTO HIGH PITCH STOP UNIT 1
120 8-2406-3 1 I BRACKET, AUTO HIGH STOP 1
120A 8-2406-1 BRACKET, AUTO HIGH STOP (ALTERNATE) 1
130 1 A-884 SPRING, AUTO HIGH STOP 2
140 A-2407 PIN, HIGH STOP 2
150 8-3838-3-5 COTTER PIN 2
280 A-3205 ´•SCREW 1
290 8-3837-0563 ´•WASHER AR
290A 8-3837-0532 ´•WASHER AR
300 A-2411-1 WASHER, FEATHER STOP 1
310 1 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 NUT, PISTON 1
350 8-3683 PISTON 1
350A 8-3237 PISTON (ALTERNATE) 1
360 C-331 7-21 0-1 O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE I I 1
380 C-3317-247 O-RING, CYLINDER MOUNTING
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-2 FORK, PITCH CHANGE -2CLE i 1
SUPERSEDED BY ITEM 400A
400A 8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN 4
440 A-2217-1 BLOCK, PITCH CHANGE -2CLE 2
SUPERSEDED BY ITEM 4408
440A A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -PCLE 2
SUPERSEDED BY ITEM 4408
44081 A-2217-4 BLOCK, PITCH CHANGE I -2CLE 2
SUPERSEDES ITEMS 440 AND 440A
440C A-2217-3 BLOCK, PITCH CHANGE I -2CLEF 2
450 A-3212 BUTTON, PITCH CHANGE BLOCK -2CLE 2
450AI A-3212-1 BUTTON, PITCH CHANGE BLOCK -PCLEF 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2271
ITEM NOT ILLUSTRATED
HC-C2YK-2CLE(F)

ILLUSTRATED PARTS LIST 61’1 0’1 7 Rev. 4 May/9Page 1064

 PROPELLER MAINTENANCE MANUAL
HARTZ E LL

PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER I 1 2 3 4 5 a 7 CODE

480 D-2201-2 1 I´•HUB I I 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL-61-179
480A D-6522-1 ´•HUB I I 1
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
500 A-2249 GUIDE BUSHING 1

580 A-2431 ´•BOLT 6

590 A-2432 ´•BOLT I 1 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 1B-3834-0632 ´•WASHER 10
610 A-2043-1 ´•NUT I 1 10
1980 8-6588-1 LUBRICATION FITTING 4

1980A A-279 LUBRICATION FITTING (ALTERNATE) 4

1990 8-6544 CAP, LUBRICATION FITTING 4

-2000 CRP-323 ´•DECAL I I 1

1010 BLADE RETENTION PARTS

3000 A-2413 BUSHING, PITCH CHANGE KNOB I -2CLE 2
3000A A-2413-2 BUSHING, PITCH CHANGE KNOB -2CLEF 2
3010 8-3883-4339 SEAL, BLADE 2
3020 A-2202-8 SPLIT BEARING, HUB SIDE RACE 2
3030 8-6144 1/2" DIAMETER STEEL BALL 50
-3030A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
3040 8-3211 SPACER, BALL 2
3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2
3060 A-2204 RING, BLADE BEARING RACE RETENTION 2
-3070 8-2256 PRELOAD PLATE UNIT 2
3080 8-2222 PRELOAD PLATE 1

3090 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 A-3204 SCREW, SOCKET HEAD 1

3110 8-3368 ´•´•NUT, JAM 1

K-FLANGE MOUNTING PARTS

-4000 C-331 7-228 O-RING, FLANGE 1
-4060 A-2067 STUD, HUB MOUNTING 6
-4070 IA-1381 WASHER, HARD, STAINLESS 6
-4080 A-2069 NUT, HEXAGON CASTLEATED 6
-4090 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

0-2271
ITEM NOT ILLUSTRATED
HC-CSYK-SCLE(F)

Page 1065
ILLUSTRATED PARTS LIST 61’1 0’1 7 Rev. 4May/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG./ITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCKNUMBER 1234567 CODE

PROPELLER PARTS
1004 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 8-1938 VALVE, AIR 1
50 A-2404-1 LOW STOP 1
50A A-2404-3 LOW STOP (ALTERNATE) 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 1 I´•CYLINDER 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 O-RING, CYLINDER ID 1
100 8-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
-160 8-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 160A
-160A 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 160
280 lA-3205 ´•SCREW 1
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGHPITCH ADJUST AR
340 8-3807 NUT, PISTON 1
350 8-3683 PISTON 1
350A 8-3237 PISTON (ALTERNATE) 1
360 C-331 7-210-1 O-RING, PISTON ID I I 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 lC-3317-247 O-RING, CYLINDER MOUNTING 1
390 lC-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-3 FORK, PITCH CHANGE 1
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN 4
440 A-2217-3 BLOCK, PITCH CHANGE 2
450 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2292
ITEM NOT ILLUSTRATED
HC-C2YK-2CLEUF EXCEPT PIPER PA44-180

ILLUSTRATED PARTS LIST ~1 -1 0-1 7 Rev. 4 May/9Page 1 966

 PROPELLER MAINTENANCE MANUAL
HARTZELL Hib

FIG./ITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234557 CODE

480 D-2201-2 ´•HUB I I 1

SUPERSEDED BY ITEM 4808, PRE SL HC-SL-61-179

480A D-2201-16 HUB 1
SUPERSEDED BY ITEM 4808, PRE SL HC-SL-61-179
4808 D-6522-1 HUB 1
SUPERSEDES ITEM 480 AND ITEM 480A
POST SL HC-SLdl-179
500 A-2249 GUIDE BUSHING
580 A-2431 1 I´•BOLT 6
590 A-2432 ´•BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10
610 A-2043-1 ´•NUT 10

1980 A-279 LUBRICATION FITTING 4

1990 8-6544 CAP, LUBRICATION FITTING 4

-2000 CPR-41 DECAL 1

-2020 CAU002 DECAL 1

-2030 HI-102 DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413-2 BUSHING, PITCH CHANGE KNOB 2

3010 8-3883-4339 SEAL, BLADE 2

3020 A-2202-B SPLIT BEARING, HUB SIDE RACE 2

3030 8-6144 1/2" DIAMETER STEEL BALL I 1 50
-3030A 8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF
3040 8-3211 ´•SPACER, BALL 2

3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 A-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 8-2256 PRELOAD PLATE UNIT 2

3080 8-2222 PRELOAD PLATE 1

3090 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 A-3204 SCREW, SOCKET HEAD 1

3110 8-3368 ´•´•NUT, JAM 1

K-FLANOE MOUNTING PARTS

-4000 C-331 7-228 O-RING, FLANGE 1

-4060 1 A-2067 STUD, HUB MOUNTING 6

-4070 A-1381 WASHER, HARD, STAINLESS 6
-4080 A-2069 NUT, HEXAGON CASTLEATED 6
-4090 8-3842-0750 SPRING PIN 6

BALANCE PARTS
-9000 8-3840-( ´•SCREW AR
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2292
ITEM NOT ILLUSTRATED
HCIC2YK-2CLEUF EXCEPT PIPER PA44-180

Page 1067
ILLUSTRATED PARTS LIST 61-10-17 Rev. 4May/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG./ITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

PROPELLER PARTS
1004 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 1 I NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 8-1938 VALVE, AIR 1
50 A-2404-1 LOW STOP 1
50A A-2404-3 LOW STOP (ALTERNATE) 1
60 1C3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER 1
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 O-RINGI CYLINDER ID 1
100 8-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
-160 8-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 160A
-160A 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 160
1608 8-1106 SPRING ASSEMBLY
(REFER TO FIGURE 1011) 1
SUPERSEDES ITEMS 160 AND 160A
280 A-3205 ´•SCREW 1
300 A-2411-1 WASHER, FEATHER STOP 1
310 8-3837-0563 WASHER, FEATHER ADJUST AR
310A 8-3837-0532 WASHER, FEATHER ADJUST AR
320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
330A A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 NUT, PISTON 1
350 8-3683 PISTON 1
350A 8-3237 i PISTON (ALTERNATE) 1
360 C-331 7-21 0-1 O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 1 C-3317-247 O-RING, CYLINDER MOUNTING 1
390 C-3317-210-1 O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-3 FORK, PITCH CHANGE 1
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 1 I SPRING PIN 4
440 A-2217-3 BLOCK, PITCH CHANGE 2
450 A-3212-1 BUTTON, PITCH CHANGE BLOCK 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

D-2292
ITEM NOT ILLUSTRATED
HC-C2YK-2CLEUF PIPER PA44-180

61-10-17 1068
 PROPELLER MAINTENANCE MANUAL
HARTZELL 170

FIG./ITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

480 1 D-2201-2 HUB 1

SUPERSEDED BY ITEM 480B, PRE SL HC-SL-61-179
480A D-2201-16 HUB 1
SUPERSEDED BY ITEM 4808, PRE SL HC-SL-61-179
4808 D-6522-1 HUB
SUPERSEDES ITEM 480 AND ITEM 480A
POST SL HC-SL-61-179
500 A-2249 GUIDE BUSHING 1

580 A-2431 ´•BOLT 6

590 A-2432 BOLT 4

(WHEN USING SPINNER MOUNTING KIT, REPLACE

BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
600 8-3834-0632 ´•WASHER 10

610 A-2043-1 ´•NUT 10

1980 A-279 LUBRICATION FITTING 4

1990 8-6544 CAP, LUBRICATION FITTING 4

-2000 CPR-41 DECAL 1

-2020 CAU002 DECAL 1

-2030 HI-102 DECAL 1

1010 BLADE RETENTION PARTS

3000 A-2413-2 BUSHING, PITCH CHANGE KNOB 2

3010 1B-3883-4339 SEAL, BLADE 2

3020 IA-2202-B SPLIT BEARING, HUB SIDE RACE 2

3030 8-6144 112" DIAMETER STEEL BALL 50

-3030A 8-6144-650 112" DIAMETER STEEL BALL (650 PIECE BOX) RF
3040 8-3211 SPACER, BALL 2

3050 A-2202-A SPLIT BEARING, BLADE SIDE RACE 2

3060 A-2204 RING, BLADE BEARING RACE RETENTION 2

-3070 8-2256 PRELOAD PLATE UNIT 2

3080 8-2222 PRELOAD PLATE 1

3090 8-6679 RACE, INNER BLADE BORE BEARING 1

3100 A-3204 SCREW, SOCKET HEAD 1

3110 8-3368 ´•´•NUT, JAM 1

K-FLANGE MOUNTING PARTS

-4000 1 C-3317-228 O-RING, FLANGE 1

-4060 1 A-2067 STUD, HUB MOUNTING 6

-4070 A-i 381 WASHER, HARD, STAINLESS 6
-4080 A-2069 NUT, HEXAGON CASTLEATED 6
-4090 8-3842-0750 SPRING PIN 6

BALANCE PARTS
´•SCREW AR
-9000 8-3840-(
-9020 A-2424(A)-( BALANCE WEIGHT AR

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2292
ITEM NOT ILLUSTRATED
HC-CPYK-PCLEUF PIPER PA44-180

Page 1069
ILLUSTRATED PARTS LIST 61 -1 0’1 7 Rev. 4May/99
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART AIRLINE NOMENCLATURE EFF UPA

NUMBER NUMBER STOCK NUMBER 123/1567 CODE

PROPELLER PARTS
1001 10 A-2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 A-169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 A-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 8-1938 VALVE, AIR 1
50 A-2404-3 LOW STOP 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER
-80 A-862-3 ´•´•BUSHING, CYLINDER 1
90 C-331 7-427-1 O-RING, CYLINDER ID
100 8-3841-10 SCREW, HIGH PITCH STOP BRACKET 4
-110 830-30 AUTO HIGH PITCH STOP UNIT 1
120 8-2406-3 BRACKET, AUTO HIGH STOP 1
120AI 8-2406-1 BRACKET, AUTO HIGH STOP (ALTERNATE) 1
130 A-884 SPRING, AUTO HIGH STOP 2
140 A-2407 PIN, HIGH STOP 2
150 8-3838-3-5 COTTER PIN 2
280 A-3205 ´•SCREW 1
290 8-3837-0563 ´•WASHER AR
8-3837-0532 ´•WASHER AR
300 A-2411-1 WASHER, FEATHER STOP 1
310 1 8-3837-0563 WASHER, FEATHER ADJUST AR
310AI 8-3837-0532 WASHER, FEATHER ADJUST AR
.320 A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 A-2435 WASHER, HIGH PITCH ADJUST AR
A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 NUT, PISTON 1
350 8-3683 ´•PISTON 1
8-3237 PISTON (ALTERNATE) 1
360 C-331 7-210-1 O-RING, PISTON ID 1
370 8-2491-3 ROD, PITCH CHANGE 1
380 C-3317-247 O-RING, CYLINDER MOUNTING
390 C-3317-210-1 1 I O-RING, PITCH CHANGE ROD, CYLINDER-SIDE 1
HUB HALF
400 8-2457-2 FORK, PITCH CHANGE -2CLG 1
SUPERSEDED BY ITEM 400A
8-2457-3 FORK, PITCH CHANGE 1
SUPERSEDES ITEM 400
420 A-3323 RUBBING PLATES 2
430 8-3842-0500 SPRING PIN 4
440 A-2217-1 BLOCK, PITCH CHANGE -2CLG 2
SUPERSEDED BY ITEM 4408
A-2217-2 BLOCK, PITCH CHANGE (ALTERNATE) -2CLG 2
SUPERSEDED BY ITEM 4408
A-2217-4 BLOCK, PITCH CHANGE -2CLG 2
SUPERSEDES ITEMS 440 AND 440A
A-2217-3 BLOCK, PITCH CHANGE -2CLGF 2
450 A-3212 BUTTON, f>lTCH CHANGE BLOCK -2CLG 2
A-3212-1 BUTTON, PITCH CHANGE BLOCK I 4CLGF 2
470 C-3317-115-1 O-RING, PITCH CHANGE ROD, ENGINE-SIDE 1
HUB HALF

0-2271
ITEM NOT ILLUSTRATED
HC-C2YK-2CLG(F)

ILLUSTRATED PARTS LIST 61’1 0’1 7 Rev. 4 May/9Page 1070

 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

I rjOMENCLATURE
1

FIG.IITEM PART AIRLINE EFF UPA

NUMBER NUMBER STOCK NUMBER 1234567 CODE

480 1 D-2201-2 .HUB 1

SUPERSEDED BY ITEM 480A, PRE SL HC-SL61-179
´•HUB 1
0-6522-1
SUPERSEDES ITEM 480, POST SL HC-SL-61-179
GUIDE BUSHING 1
500 1 A-2249
A-2431 ´•BOLT 6
580
.BOLT 4
590 A-2432
(WHEN USING SPINNER MOUNTING KIT, REPLACE
BOLTS (590) WITH BOLTS IN KIT, IF APPLICABLE)
1 8-3834-0632 ´•WASHER 10
600
.NUT 10
610 1 A-2043-1
DAMPER ASSEMBLY 1
-900 C-1576
HEX HEAD SPACER TUBES 8
-910 1 A-1579
´•´•SPRING, DAMPER 8
-920 1 A-1580
8-3851-0732 ´•´•WASHER 8
-930
´•´•WASHER 8
-940 1 A-1865-2
C-l 567-1 ´•´•WEIGHT, DAMPER 1
-950
SILICONE GROMMET 8
-960 1 A-1581
C-1568-1 FRICTION DISC 1
-970
C-l 566-1 PLATE, SUPPORT 1
-980
´•´•SCREW 8
-990 1 A-1578
´•´•SCREW (ALTERNATE) 8
-990AI A-2038-6
1980 1 8-6588-1 LUBRICATION FITTING 4
LUBRICATION FITTING (ALTERNATE) 4
1980AI A-279
CAP, LUBRICATION FITTING 4
1990 1 8-6544
´•DECAL 1
-2000 1 CRP-323

1010 BLADE RETENTION PARTS

BUSHING, PITCH CHANGE KNOB QCLG 2
3000 A-2413
A-2413-2 BUSHING, PITCH CHANGE KNOB -2CLGF 2

´•SEAL, BLADE 2
3010 1 8-3883-4339
SPLIT BEARING, HUB SIDE RACE 2
3020 1 A-2202-8
1/2" DIAMETER STEEL BALL 50
3030 1 8-6144
8-6144-650 1/2" DIAMETER STEEL BALL (650 PIECE BOX) RF

8-3211 ´•SPACER, BALL 2

3040
SPLIT BEARING, BLADE SIDE RACE 2
3050 1 A-2202-A
RING, BLADE BEARING RACE RETENTION 2
3060 1 A-2204
PRELOAD PLATE UNIT 2
-3070 1 8-2256
PRELOAD PLATE 1
3080 1 8-2222
RACE, INNER BLADE BORE BEARING 1
3090 1 8-6679
A-3204 SCREW, SOCKET HEAD 1
3100
´•´•NUT, JAM 1
3110 8-3368

K-FLANGE MOUNTING PARTS

´•O-RING, FLANGE 1
-4000 1 C-3317-228
STUD, HUB MOUNTING 6
-4060 1 A-2067
´•WASHER, HARD, STAINLESS 6
-4070 1 A-1381
A-2069 NUT, HEXAGON CASTLEATED 6
-4080
SPRING PIN 6
-4090 1 8-3842-0750

BALANCE PARTS
.SCREW AR
-9000 8-3840-(
BALANCE WEIGHT AR
-9020 A-2424(A)-(

SPINNER PARTS APPLICATION SPECIFIC

REFER TO HARTZELL APPLICATION GUIDE

D-2271
ITEM NOT ILLUSTRATED
HC-CPYK-2CLG(F)

Page 1071
ILLUSTRATED PARTS LIST 61-10-17 Rev. 6 Apr/GO
 PROPELLER MAINTENANCE MANUAL
HARTZELL 117D

FIG.IITEM PART AIRLINE NOMENCLATURE EFF IUPA

NUMBER I NUMBER STOCK NUMBER 1234587 1 CODE

PROPELLER PARTS
1004 10 1k2405-2 NUT, SPINNER, CAP-SIDE (REFER TO FIGURE 1013) 1
20 1A169-7 SPACER, SPINNER (REFER TO FIGURE 1013) AR
30 lA-2405-3 NUT, SPINNER, CYLINDER-SIDE (REFER TO FIG. 1013) 1
40 1B-1938 ´•VALVE, AIR 1
50 lA-2404-3 LOW STOP 1
60 C-3317-117 O-RING, LOW STOP 1
70 8-2423-1 ´•CYLINDER I I i
-80 lA-862-3 ´•´•BUSHING, CYLINDER 1
90 1(=-3317-427-1 .O-RING, CYLINDER ID 1
100 1B-3841-8 SCREW, HIGH PITCH STOP BRACKET 4
-160 1B-1589 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACED BY ITEM 160A
-160AI 8-1589-2 SPRING ASSEMBLY (REFER TO FIGURE 1011) 1
REPLACES ITEM 160
280 lA-3205 ´•SCREW I I 1
300 A-2411-1 WASHER, FEATHER STOP 1
310 1B-3837-0563 WASHER, FEATHER ADJUST AR
310AI 8-3837-0532 WASHER, FEATHER ADJUST AR
320 1A-2499-10 SLEEVE, HIGH PITCH STOP 1
330 lA-2435 WASHER, HIGH PITCH ADJUST AR
330AI A-2435-1 WASHER, HIGH PITCH ADJUST AR
340 8-3807 ´•NUT, PISTON 1
350 8-3683 ´•PISTON 1
350AI 8-3237 ´•PISTON (ALTERNATE) 1
360 C-331 7-21 0-1 ´•O-RING, PISTON ID 1
370 18-2491-3 ROD, PITCH CHANGE 1
380 lC-3317-247 O-RING, CYLINDER MOUNTING 1
390 lC-3317-210-1 O-RING, PITCH CHANGE ROD, CYLI