FAA Approved

Manual No. 181 HARTZELL

30-60-81
Revision 3
August 2011

Propeller Ice Protection System

Component Maintenance Manual

Hartzell Propeller Inc.

One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.
Phone: 937.778.4200
Fax: 937.778.4391
© 2007, 2009, 2011 - Hartzell Propeller Inc. - All rights reserved

COVER 30-60-81 Cover Back

Rev. 3 Aug/11
 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

REVISION 3 HIGHLIGHTS

• Revised the Cover, Revision Highlights, and List of Effective Pages to match the
manual revision.
• CHECK
• Clarified De-ice Component Overhaul requirements
• Added replacement mounting screw information for the 4H2422 slip ring
assembly
• Incorporated TR-002 that added Check criteria for the MOV Bracket and Circuit
Breaker Switch
• Revised the inspection procedure for the Propeller De-ice Operational Check
(Without Engine Power)
• Revised the inspection procedure for the Propeller De-ice Operational Check
(Rotating)
• Changed the De-ice Boot Resistance Check to a De-ice Circuit Resistance
Inspection
• Added De-ice Boot Inspection for Overheating or a Short Circuit

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REVISION 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 to an existing 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.
3 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 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 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 June 2007 New Issue

Revision 1 February 2009 Minor
Revision 2 October 2009 Minor
Revision 3 August 2011 Minor

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

Revision Issue Date Inserted Revision Issue Date Inserted

Number Date Inserted By Number Date Inserted By

Orig. Jun/07 Jun/07 HPI

1 Feb/09 Feb/09 HPI

2 Oct/09 Oct/09 HPI

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

Revision Issue Date Inserted Revision Issue Date Inserted

Number Date Inserted By Number Date Inserted By

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RECORD OF TEMPORARY REVISIONS TO THIS MANUAL

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

Temporary Section/ Issue Date Inserted Date Removed
Revision No. Page Date Inserted By Removed By
TR-001 6-15 Jun/08 Jun/08 HPI Oct/09 HPI
TR-002 5-21 Sep/10 Sep/10 HPI Aug/11 HPI
TR-003 5-23 Feb/12 Feb/12 HPI

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RECORD OF TEMPORARY REVISIONS TO THIS MANUAL

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

Temporary Section/ Issue Date Inserted Date Removed

Revision No. Page Date Inserted By Removed By

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SERVICE DOCUMENT LIST

Service Document Incorporation Service Document Incorporation

Number Rev./Date Number Rev./Date

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SERVICE DOCUMENT LIST

Service Document Incorporation Service Document Incorporation

Number Rev./Date Number Rev./Date

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 PROPELLER ICE PROTECTION SYSTEM
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AIRWORTHINESS LIMITATIONS

1. Airworthiness Limitations
A. Certain ice protection system components may have specific life limits established
by the FAA. Such limits require replacement of the identified parts after a specified
number of hours of use.
B. For specific life limits of each ice protection system component, refer to the latest
version of the Hartzell Propeller Ice Protection System Manual 180 (30-61-80).

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LIST OF EFFECTIVE PAGES

Chapter Page Rev. Level Date

Cover/Cover Back Cover/Cover Back 3 Aug/11

Revision Highlights 1 and 2 3 Aug/11
Record of Revisions 1 and 2 Orig. Jun/07
Record of Temporary
Revisions 1 and 2 Orig. Jun/07
Service Document List 1 and 2 Orig. Jun/07
Airworthiness Limitations 1 and 2 Orig. Jun/07
List of Effective Pages 1 and 2 3 Aug/11
Table of Contents 1 and 2 2 Oct/09
Introduction 1 thru 10 Orig. Jun/07
Description and Operation 1 thru 4 1 Feb/09
Testing and Fault Isolation 1-1 thru 1-4 Orig. Jun/07
Automatic Test Requirements 2-1 and 2-2 Orig. Jun/07
Disassembly 3-1 thru 3-4 Orig. Jun/07
Cleaning 4-1 thru 4-4 Orig. Jun/07
Check 5-1 3 Aug/11
Check 5-2 thru 5-5 2 Oct/09
Check 5-6 3 Aug/11
Check 5-7 and 5-8 2 Oct/09
Check 5-9 thru 5-12 3 Aug/11
Check 5-13 thru 5-20 2 Oct/09
Check 5-20.1 and 5-20.2 3 Aug/11
Check 5-21 thru 5-25 2 Oct/09
Check 5-26 3 Aug/11
Check 5-27 thru 5-29 2 Oct/09
Check 5-30 3 Aug/11
Check 5-31 2 Oct/09
Check 5-32 3 Aug/11
Check 5-33 and 5-34 2 Oct/09
Check 5-35 thru 5-48 3 Aug/11
Repair/Modification 6-1 2 Oct/09
Repair/Modification 6-2 and 6-3 Orig. Jun/07
Repair/Modification 6-4 and 6-5 2 Oct/09
Repair/Modification 6-6 thru 6-10 Orig. Jun/07
Repair/Modification 6-11 and 6-12 3 Aug/11
Repair/Modification 6-13 Orig. Jun/07
Repair/Modification 6-14 thru 6-18 2 Oct/09

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LIST OF EFFECTIVE PAGES

Chapter Page Rev. Level Date

Assembly 7-1 thru 7-4 Orig. Jun/07

Assembly 7-5 1 Feb/09
Assembly 7-6 Orig. Jun/07
Fits and Clearances 8-1 thru 8-4 Orig. Jun/07
Special Tools, Fixtures
and Equipment 9-1 thru 9-4 Orig. Jun/07
Illustrated Parts List 10-1 and 10-2 Orig. Jun/07

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 PROPELLER ICE PROTECTION SYSTEM
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TABLE OF CONTENTS

REVISION HIGHLIGHTS ..................................................................................................... 1

RECORD OF REVISIONS ...................................................................................................1
RECORD OF TEMPORARY REVISIONS ............................................................................ 1
SERVICE DOCUMENT LIST ............................................................................................... 1
AIRWORTHINESS LIMITATIONS ........................................................................................ 1
LIST OF EFFECTIVE PAGES .............................................................................................. 1
TABLE OF CONTENTS........................................................................................................1
INTRODUCTION ..................................................................................................................1
DESCRIPTION AND OPERATION....................................................................................... 1
TESTING AND FAULT ISOLATION ...................................................................................1-1
AUTOMATIC TEST REQUIREMENTS..............................................................................2-1
DISASSEMBLY .................................................................................................................3-1
CLEANING ........................................................................................................................4-1
CHECK ..............................................................................................................................5-1
REPAIR/MODIFICATION ..................................................................................................6-1
ASSEMBLY .......................................................................................................................7-1
FITS AND CLEARANCES .................................................................................................8-1
SPECIAL TOOLS, FIXTURES, AND EQUIPMENT ...........................................................9-1
ILLUSTRATED PARTS LIST ...........................................................................................10-1

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INTRODUCTION - CONTENTS

1. Statement of Purpose ................................................................................................ 3

A. General .................................................................................................................3
2. Required Publications ................................................................................................ 4
A. Publications ..........................................................................................................4
B. References to Hartzell Publications .................................................................... 5
3. Personnel Requirements ........................................................................................... 5
4. Calendar Limits and Long Term Storage ................................................................... 5
5. Component Life and Service ..................................................................................... 6
A. Maintenance ......................................................................................................... 6
B. Component Life .................................................................................................... 6
6. Definitions ..................................................................................................................7
7. Abbreviations .............................................................................................................9

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1. Statement of Purpose
A. General
(1) Hartzell Propeller Inc. provides the approved Instructions for Continued
Airworthiness (ICA) for propeller mounted and airframe mounted propeller ice
protection system components supplied by Hartzell Propeller Inc. Propeller
ice protection system components not supplied by Hartzell Propeller Inc. are
controlled by the supplier's Instructions for Continued Airworthiness.

NOTE 1: Information about ice protection systems and/or components not

supplied by Hartzell Propeller Inc. must be obtained from the aircraft
TC or STC holder's ICA.
(2) Contact the Product Support Department of Hartzell Propeller Inc. concerning
any maintenance problems or to request information not covered in this
publication.
(a) 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 or at (800) 942-7767, toll free from the United States and
Canada. Hartzell Product Support can also be reached by fax at
(937) 778-4391, and e-mail at techsupport@hartzellprop.com.
(b) 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.
(c) 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 maintenance
personnel who are trained and experienced with airframe and propeller
maintenance and repair. This manual does not provide complete information
for an inexperienced technician to attempt ice protection system maintenance
without supervision.
(4) In addition to this manual, the reader must consult active Service Bulletins,
Service Letters, Service Advisories, and Service Instructions for information
concerning procedures that may have not yet been incorporated into the latest
revision of this manual.

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(5) For additional information about propeller mounted ice protection components
or airframe mounted propeller ice protection system components, refer to the
applicable manual:
1 Manual 180 - Propeller Ice Protection Systems Manual, includes:
a Illustrated Parts List and Routings
2 Manual 182 - Propeller Electrical De-ice Boot Removal and
Installation Manual, includes:
a Description and Operation - Boot only
b Electrical de-ice boot removal and installation instructions
c Electrical de-ice boot dimensions
3 Manual 183 - Propeller Anti-ice Boot Removal and Installation
Manual, includes:
a Description and Operation - Boot only
b Anti-icing boot removal and installation instructions
c Anti-icing boot dimensions
(6) Where possible, this manual is written in the format specified by
ATA iSpec 2200.

2. Required Publications
A. 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 ice protection systems.
Hartzell
Manual No. ATA No. Title
126 61-00-26 Set of active Hartzell SB, SA, SL, SI
159 61-02-59 Application Guide Manual
165A 61-00-65 Illustrated Tool and Equipment Manual
180 30-61-80 Propeller Ice Protection System Manual
182 61-12-82 Propeller Electrical De-ice Boot Removal and
Installation Manual
183 61-12-83 Propeller Anti-ice Boot Removal and Installation
Manual
202A 61-01-02 Standard Practices Manual
Aircraft TC or STC holder's ICA

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

Hartzell Propeller Inc. Telephone: 937.778.4200
Attn: Service Documents Secretary Fax: 937.778.4391
One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.
Selected information is also available on Hartzell Propeller’s website at
www.hartzellprop.com.
B. References to Hartzell Publications
(1) Item references throughout the text in this manual refer to item numbers in the
Illustrated Parts List chapter in the Hartzell Propeller Ice Protection System
Manual 180 (30-61-80). 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. A part may be superseded, replaced, or
obsoleted by another part.
(2) Special tooling may be required to install propeller mounted and airframe
mounted propeller ice protection system components. For more information
concerning tooling, refer to Hartzell Illustrated Tool and Equipment Manual
165A (61-00-65). The reference numbers for tooling appear with the prefix
“TE” directly following the tool name to which they apply.
(3) Consumable materials may be required to install propeller mounted and
airframe mounted propeller ice protection system components. Certain
instructions throughout this manual refer to consumable materials. Specific
approved materials are listed in the Consumable Materials chapter of Hartzell
Standard Practices Manual 202A (61-01-02). 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.

3. Personnel Requirements
A. Personnel performing maintenance are expected to have sufficient training and
certifications (when required by the applicable Aviation Authority) to accomplish the
work required in a safe and airworthy manner.

4. Calendar Limits and Long Term Storage

A. Propeller mounted and airframe mounted propeller ice protection system
components supplied by Hartzell Propeller Inc. that have been in storage may have
additional inspection requirements before installation. Refer to the Packaging and
Storage chapter of Hartzell Standard Practices Manual 202A (61-01-02).

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5. Component Life and Service

A. Maintenance
(1) Maintain propeller mounted and airframe mounted propeller ice protection
system components supplied by Hartzell in accordance with this manual.
B. Component Life
(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: TSN/TSO 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 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) Propeller mounted and airframe mounted propeller ice protection system
components supplied by Hartzell Propeller Inc. do not require time tracking
unless specifically required in Hartzell service publications.

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6. Definitions

Term Definition

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

De-bond .......................area that has lost adhesion from 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

Fraying .........................a raveling or shredding of material

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

displacement takes place between contacting parts,
wearing away the surface

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.

Overhaul ......................the periodic disassembly, inspection, repair, refinish, and

reassembly of a propeller assembly

Open Circuit .................connection of high or infinite resistance between points in a

circuit which are normally lower

Pitting ...........................(1) formation of a number of small, irregularly shaped cavities in

surface material caused by corrosion or wear

(2) linear pitting is the configuration of the majority of pits

forming a pattern in the shape of a line.

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Term Definition
Scratch .........................same as "Nick"

Short ............................connection of low resistance between points on a circuit

between which the resistance is normally much greater

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7. Abbreviations

Abbreviation Term

AMM . . . . . . . . . . . .Aircraft Maintenance Manual

AN . . . . . . . . . . . . . .Army-Navy
AOG . . . . . . . . . . . .Aircraft On Ground
ATA . . . . . . . . . . . . .Air Transport Association
FAA . . . . . . . . . . . . .Federal Aviation Administration
FM. . . . . . . . . . . . . .Flight Manual
FMS . . . . . . . . . . . .Flight Manual Supplement
Ft-Lb . . . . . . . . . . . .Foot-Pound
ICA . . . . . . . . . . . . .Instructions for Continued Airworthiness
ID . . . . . . . . . . . . . .Inside Diameter
In-Lb . . . . . . . . . . . .Inch-Pound
IPL . . . . . . . . . . . . .Illustrated Parts List
Lbs . . . . . . . . . . . . .Pounds
MIL-X-XXX . . . . . . .Military Specification
MS . . . . . . . . . . . . .Military Standard
NAS . . . . . . . . . . . .National Aircraft Standards
N•m . . . . . . . . . . . . .Newton-Meter
OD . . . . . . . . . . . . .Outside Diameter
POH . . . . . . . . . . . .Pilot Operating Handbook
PSI . . . . . . . . . . . . .Pounds per Square Inch
RPM . . . . . . . . . . . .Revolutions per Minute
TBO . . . . . . . . . . . .Time Between Overhaul
TSN. . . . . . . . . . . . .Time Since New
TSO . . . . . . . . . . . .Time Since Overhaul

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DESCRIPTION AND OPERATION - CONTENTS

1. Description ................................................................................................................3
2. Components Electric De-ice System ........................................................................3
A. On/Off Switch .....................................................................................................3
B. Timer or Cycling Unit ..........................................................................................3
C. Brush Block ........................................................................................................3
D. Slip Ring .............................................................................................................3
E. Slip Ring Wire Harness ......................................................................................3
F. De-ice Wire Harness ..........................................................................................3
G. De-ice Boot .........................................................................................................3
H. Ammeter .............................................................................................................4
I. Circuit Breaker or Switch ....................................................................................4
3. Components Anti-ice System
A. Anti-icing Boot ....................................................................................................4
B. Feed Tube ..........................................................................................................4
C. Fluid Tank ...........................................................................................................4
D. Pump ..................................................................................................................4
E. Slinger Ring ........................................................................................................4

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1. Description
A. A propeller de-ice system removes ice that forms on blades by electrically heating
the de-ice boots. The ice partially melts and is thrown from the blade by centrifugal
force.
B. A propeller anti-icing system is a system that prevents formation of ice on propeller
surfaces. An anti-icing system dispenses a fluid that mixes with the moisture and
decreases the temperature that will cause the moisture to freeze on the propeller
blades. The mixture may then flow off the blades before it forms ice.

2. Components Electrical De-ice System

A. On/Off Switch
(1) A de-ice system consists of one or more on/off switches. The pilot controls the
operation of the de-ice system by turning on one or more switches. All de-ice
systems have a master switch, and may have another toggle switch for each
propeller. Some systems may also have a selector switch to adjust for light or
heavy icing conditions or automatic switching for icing conditions.
B. Timer or Cycling Unit
(1) The timer or cycling unit determines the sequence of which blades (or portion
thereof) are currently being de-iced, and for what length of time. The cycling
unit applies power to each de-ice boot or boot segment in a sequential or all on
order.
C. Brush Block
(1) A brush block, which is normally mounted on the engine just behind the
propeller, is used to transfer electricity to the slip ring.
D. Slip Ring
(1) The slip ring rotates with the propeller and provides a current path to the blade
de-ice boots.
E. Slip Ring Wire Harness
(1) A slip ring wire harness is used on some hub installations to electrically connect
the slip ring to the terminal strip connection screw.
F. De-ice Wire Harness
(1) A de-ice wire harness is used to electrically connect the de-ice boot to the slip
ring assembly.
G. De-ice Boot
(1) A de-ice boot contains internal heating elements or dual elements. The boot is
securely attached to the leading edge of each blade with adhesive.

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H. Ammeter
(1) An ammeter is used to indicate system current flow. The ammeter has an
internal or external shunt.
I. Circuit Breaker or Switch
(1) A switch or circuit breaker/switch is used to cut power in case of an overload.

3. Components Anti-icing System

A. Anti-icing Boot
(1) The blade anti-icing boots are channeled rubber sheets that are securely
attached to the leading edge of each blade with adhesive. The ridges in the
anti-icing boot direct the fluid out onto the blades and permit for an even
distribution of the anti-icing fluid across the blades.
B. Feed Tube
(1) Feed tubes are installed on the propeller hub and adjusted to dispense fluid
along the leading edge of the propeller anti-icing boots.
C. Fluid Tank
(1) Reservoir for anti-icing fluid.
D. Pump
(1) The pump supplies anti-icing fluid from the tank at a controlled rate. The
anti-icing fluid is delivered through a filter, a check valve, and then through
tubing to a slinger ring located at the rear of the spinner bulkhead.
E. Slinger Ring
(1) The anti-icing fluid is dispensed into the rotating slinger ring, which holds the
fluid in a curved channel by centrifugal force. The fluid then flows out of the
slinger ring through feed tubes that are connected to the slinger ring, and then
out onto the blade anti-icing boots.

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TESTING AND FAULT ISOLATION - CONTENTS

1. Testing and Fault Isolation .......................................................................................... 1-3

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TESTING AND FAULT ISOLATION

1. Testing and Fault Isolation

A. Use standard industry practices or the AMM for testing and fault isolation.
B. Repair and replace defective components as needed in accordance with the
Repair/Modification chapter or the Assembly chapter of this manual, the aircraft TC
or STC holder's ICA, and the AMM.
C. Contact Hartzell Product Support department for additional information.

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AUTOMATIC TEST REQUIREMENTS (NOT APPLICABLE)

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DISASSEMBLY - CONTENTS

1. Removal of Propeller Ice Protection Components ..............................................3-3

A. General .........................................................................................................3-3
B. Propeller Removal .........................................................................................3-3
C. Removal of Propeller Ice Protection Components .......................................3-3
D. Removal of Air Frame Mounted Propeller Ice Protection Components .........3-3
E. Removal of De-ice and Anti-icing Boots ........................................................3-3

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1. Removal of Propeller Ice Protection Components

A. General

CAUTION: USE CAUTION WHEN REMOVING ICE PROTECTION

COMPONENTS AND ICE PROTECTION ATTACHING HARDWARE
TO AVOID DAMAGING THE PROPELLER.
(1) Use the appropriate tools for removal of propeller ice protection components.
B. Propeller Removal
(1) As required, remove the propeller from the aircraft in accordance with the
applicable propeller owner's manual or the Aircraft Maintenance Manual (AMM).
C. Removal of Propeller Ice Protection Components
(1) Remove the ice protection components and attaching hardware.
(2) Discard and replace the required ice protection components and attaching
hardware in accordance with the Propeller Ice Protection System Manual 180
(30-61-80).
D. Removal of Air Frame Mounted Propeller Ice Protection Components
(1) Remove the air frame mounted propeller ice protection components in
accordance with this manual, the AMM or TC or STC holder's ICA.
E. Removal of De-ice and Anti-icing Boots

WARNING: DE-ICE AND ANTI-ICING BOOTS ARE TO BE REMOVED AND

REPLACED AT EACH PROPELLER OVERHAUL. THIS IS
REQUIRED REGARDLESS OF THE CONDITION OF THE DE-ICE
OR ANTI-ICING BOOT.
(1) Remove de-ice boots and anti-icing boots in accordance with Hartzell Propeller
Electrical De-ice Boot Removal and Installation Manual 182 (61-12-82) or
Hartzell Propeller Anti-icing Boot Removal and Installation Manual 183
(61-12-83), as applicable.

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CLEANING - CONTENTS

1. General Procedures for Cleaning Parts ..............................................................4-3

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1. General Procedures for Cleaning Parts

A. Refer to the Cleaning chapter of Hartzell Standard Practices Manual 202A
(61-01-02).

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CHECK - CONTENTS
1. Inspection Interval Requirements................................................................................ 5-3
2. Inspection Requirements............................................................................................. 5-3
A. Wear Items............................................................................................................ 5-3
B. Visual Inspection.................................................................................................... 5-3
C. Dimensional Inspection......................................................................................... 5-3
3. Replacement Requirements........................................................................................ 5-4
4. Repair.......................................................................................................................... 5-4
5. Specific Inspection Procedures.................................................................................... 5-4
A. Periodic Inspections.............................................................................................. 5-4
6. Inspection Procedures............................................................................................... 5-35
A. Propeller De-ice Operational Check (Without Engine Power)............................. 5-35
B. Propeller De-ice Operational Check (Rotating)................................................... 5-38
C. Lightning Strike.................................................................................................... 5-38
D. De-ice Slip Ring Run-out Check.......................................................................... 5-38
E. De-ice Circuit Resistance Inspection................................................................... 5-41
F. De-ice Boot and Anti-icing Boot Debond Limits................................................... 5-42
G. Terminal Mount Strap Debond Limits.................................................................. 5-43
H. Brush Measurement............................................................................................ 5-44
I. Propeller Anti-ice System Operational Check...................................................... 5-44
J. Timer Test - Hartzell 1( )( )( )( )( ) part numbers only........................................... 5-45
K. Dielectric Strength............................................................................................... 5-46
L. De-ice Boot Inspection for Overheating or a Short Circuit................................... 5-47

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LIST OF ILLUSTRATIONS
Slip Ring Run-out Check..................................................................Figure 5-1.............. 5-36
Brush Measurement ........................................................................Figure 5-2.............. 5-39

LIST OF TABLES
De-ice System 100 Hour/12 Month Inspection..................................Table 5-1................. 5-7
Anti-ice System 100 Hour/12 Month Inspection................................Table 5-2............... 5-13
Non-Rotating or Airframe Mounted Component Inspection...............Table 5-3............... 5-15
Rotating or Propeller Mounted Component Inspection.....................Table 5-4............... 5-21
Inspection at Propeller Overhaul.......................................................Table 5-5............... 5-24
Special Inspection - Lightning Strike.................................................Table 5-6............... 5-26
Special Inspection - Sudden Stoppage.............................................Table 5-7............... 5-28
Special Inspection - Fire....................................................................Table 5-8............... 5-30
Special Inspection - Foreign Object Strike........................................Table 5-9............... 5-32
De-ice Boot Resistance Values - now in the Hartzell Propeller Electrical De-ice Boot
Removal and Installation Manual 182 (61-12-82)

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1. Inspection Interval Requirements

A. Refer to the Airworthiness Limitations Chapter of this manual for information on life
limited components and mandatory inspections.

2. Inspection Requirements
A. Wear Items
(1) Inspect all wearing parts to determine if they meet the specifications in this
chapter.
(2) Any serial-numbered part found unairworthy must be retired in accordance
with the Part Retirement Procedures chapter in the Hartzell Standard Practices
Manual 202A (61-01-02).
B. Visual Inspection
(1) Visually examine all components for evidence of damage, separation of
material, de-bond, foreign object damage, erosion, corrosion, loose or missing
hardware, and any obvious defects.
C. Dimensional Inspection
(1) 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 when a minimum of two measurements are
taken.
(2) 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 when eight
measurements are taken (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 beyond the serviceable limits specified in the
50 hour/12 month Inspection and the 100 hour/12 month Inspection tables in
this chapter.
(3) 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.
(4) 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.

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3. Replacement Requirements
A. Refer to the 50 hour/12 month Inspection and the 100 hour/12 month Inspection
tables in this chapter. Replace all parts that have cracks, wear, corrosion, pitting, or
obvious defects or damage that could adversely affect the fit or function of the part
or that do not meet the serviceable limits as specified in the Check chapter of this
manual.
B. If the component has corrosion, pitting, wear, or damage less than the serviceable
limits as specified in the Check chapter of this manual, component replacement is
not required.

4. Repair
A. If the component has corrosion, pitting, wear, or damage that does not meet
serviceable limits as specified in the Check chapter of this manual, the component
may be repaired in accordance with the Corrective Action in the De-ice System
50 Hour/12 Month Inspection, De-ice System 100 Hour/12 Month Inspection, and
the Anti-ice System 100 Hour/12 Month Inspection tables in this chapter. If the
component cannot be repaired to meet the service limits as specified in the Check
chapter of this manual, the component must be replaced.
B. Repairable part features are noted in the inspection criteria in this chapter. Additional
repair procedures are found in the Repair/Modification chapter of this manual, unless
otherwise stated.

5. Specific Inspection Procedures

A. Periodic Inspections
(1) An airframe or manufacturer's maintenance program may specify time intervals
for inspection and maintenance that do not coincide with the inspection time
intervals specified by Hartzell Propeller Inc. In this situation, the airframe
manufacturer’s schedule may be applied if the inspection time intervals are less
than the intervals specified by Hartzell Propeller Inc. with the exception that the
calendar limit for the inspection interval may not exceed twelve (12) months.
If the airframe manufacturer's scheduled interval is greater than the intervals
specified by Hartzell Propeller Inc., the inspection interval may not exceed
those specified by Hartzell Propeller Inc.
(2) Refer to Inspection Procedures in this chapter or the Repair chapter in this
manual for additional possible corrective actions, and/or permitted repairs to
any discrepancies discovered as a result of the Periodic Inspections.

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(3) De-ice System 100 Hour/12 Month Inspection. Refer to Table 5-1.
(a) Perform a detailed inspection at 100 hour intervals to coincide with the
propeller 100 hour periodic inspection not to exceed twelve (12) calendar
months.
1 Perform the inspection specified in the 100 hour inspection in
Table 5-1 of this manual.
2 Procedures involved in these inspections are detailed in this chapter.
3 Perform an additional detailed inspection in accordance with the
aircraft TC or STC holder instructions for continued airworthiness.
(4) Anti-ice System 100 Hour/12 Month Inspection. Refer to Table 5-2.
(a) Perform a detailed inspection at 100 hour intervals to coincide with the
propeller 100 hour periodic inspection not to exceed twelve (12) calendar
months.
1 Perform the inspections specified in the Table 5-2 of this manual.
2 Procedures involved in these inspections are detailed in this chapter.
3 Perform an additional detailed inspection in accordance with the
aircraft TC or STC holder instructions for continued airworthiness.
(5) Non-rotating or Airframe Mounted Component Inspection. Refer to Table 5-3.
(a) Perform a detailed inspection every twelve (12) calendar months.
1 Perform the inspections specified in the Table 5-3 of this manual.
2 Perform brush block assembly inspection at 100 hour intervals to
coincide with the propeller 100 hour periodic inspection not to exceed
twelve (12) calendar months.
3 Procedures involved in these inspections are detailed in this chapter.
4 Perform an additional detailed inspection in accordance with the
aircraft TC or STC holder instructions for continued airworthiness.
(6) Rotating or Propeller Mounted Component Inspection. Refer to Table 5-4.
(a) Perform a detailed inspection at propeller overhaul.
1 Perform the inspections specified in the Table 5-4 of this manual.
2 Procedures involved in these inspections are detailed in this chapter.
3 Perform an additional detailed inspection in accordance with the
aircraft TC or STC holder instructions for continued airworthiness.

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B. De-ice Component Overhaul

(1) De-ice component overhaul must be performed at each propeller overhaul.
(2) Perform the following inspections at de-ice component overhaul:
(a) Anti-ice System 100 Hour/12 Month Inspection. Refer to Table 5-2.
1 Perform the inspections specified in the Table 5-2 of this manual.
2 Perform the inspections specified in the Table 5-5 of this manual.
3 Perform an additional detailed inspection in accordance with the
aircraft TC or STC holder instructions for continued airworthiness.
(b) Non-rotating or Airframe Mounted Component Inspection. Refer to
Table 5-3.
1 Perform the inspections specified in the Table 5-3 of this manual.
2 Perform the inspections specified in the Table 5-5 of this manual.
3 Perform an additional detailed inspection in accordance with the
aircraft TC or STC holder instructions for continued airworthiness.
(c) Rotating or Propeller Mounted Component Inspection. Refer to Table 5-4.
1 Perform the inspections specified in the Table 5-4 of this manual.
2 Perform the inspections specified in the Table 5-5 of this manual.
3 Perform an additional detailed inspection in accordance with the
aircraft TC or STC holder instructions for continued airworthiness.

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Inspect Serviceable Limits Corrective Action

A. Slip Ring Assembly

(1140)

(1) Visually examine for Excessive fuel or oil leak is not Correct the fuel or oil
fuel or oil leakage permitted. Wear across the leakage. For damage less
contamination wear path less than 0.007 inch than serviceable limits, clean
on the slip ring. (0.178 mm) in depth is as necessary with cleaning
Contamination may permitted. solvent CM106 or CM128
cause excess wear of and an abrasive pad, CM47.
the rings. Follow by wiping with cleaning
solvent CM106 or CM128.

(2) Visually examine for Corroded hardware is not Replace any corroded
corroded hardware. permitted. hardware.

(3) Visually examine for Minor damage, such as, nicks Replace any damaged or
damage and loose or and scratches, is permitted. missing hardware or tubing.
missing hardware. Loose or missing hardware or Tighten any loose hardware
tubing is not permitted. and safety as required.
Minor corrosion of the slip ring
plate is permitted.

(4) Visually examine Minor damage, such as, nicks Use an abrasive pad CM47
the slip ring plate for and scratches, are permitted. or equivalent, remove
corrosion. corrosion and apply a
chemical conversion coating
in accordance with Hartzell
Standard Practices Manual
202A (61-00-02). If corrosion
exceeds serviceable limits
replace the slip ring assembly.

(5) Visually examine for Damage across the wear path For damage less than
damage or excess less than 0.007 inch serviceable limits, clean using
wear of the rings. (0.178 mm) in depth is an abrasive pad CM47 or
permitted. equivalent.

De-ice System 100 Hour/12 Month Inspection

Table 5-1

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Inspect Serviceable Limits Corrective Action

(6) Visually examine Minor damage of the slip ring If damage exceeds the
the slip ring plate for plate is permitted. serviceable limits, resurface the
damage. slip ring in accordance with the
Repair/Modification chapter of
this manual.

A crack or structural damage is If the slip ring is cracked or

not permitted. damaged structurally, replace
the slip ring assembly.

If wobble is observed, perform If wobbles exceeds serviceable

(7) Visually examine the slip ring run-out check in this limits, replace the slip ring
slip ring for wobble. chapter. assembly.

Chipped, cracked, or broken If damage exceeds serviceable

(8) Visually examine the insulating compound is not limits, replace the slip ring
insulating compound permitted. assembly.
for loose or missing
compound. Separation of the copper rings If the copper rings have
from the insulating compound separated from the insulating
is not permitted. compound, replace the slip ring
assembly.

De-ice System 100 Hour/12 Month Inspection

Table 5-1 (continued)

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Inspect Serviceable Limits Corrective Action

(9) Visually examine the Obvious damage that could Terminal end replacement may
slip ring wires, studs, adversely affect proper fit or be performed in accordance
mounting screws, and function is not permitted. with industry standard
terminals. practices.
If slip ring lead wire is frayed
or broken, remove the slip ring
and replace the leadwire in
accordance with the Repair/
Modification chapter of this
manual or replace the slip ring
assembly.
If an integral wire is broken
inside the slip ring, repair is not
permitted, replace the slip ring
assembly.
If a stud is damaged or broken,
remove the slip ring and
replace the slip ring assembly.
If a mounting screw (1141) on
a 4H2422 slip ring assembly
is damaged, broken, or
missing, replace the screw in
accordance with the Repair/
Modification chapter of this
manual or replace the slip ring
assembly.
If damage to wires, studs, or
heat shrink tubing is beyond
the serviceable limits, replace
the slip ring assembly.

De-ice System 100 Hour/12 Month Inspection

Table 5-1 (continued)

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Inspect Serviceable Limits Corrective Action

B. De-Ice Boot

(1) Visually examine for Minor damage is permitted. If damage exceeds the
wrinkled, abraded, torn Damage through the serviceable limits, replace the
areas, or foreign object de-ice boot to the blade de-ice boot.
damage. Pay close is not permitted. Damage
attention to de-ice boot that exposes the de-ice
edges, blade leading boot heating element is not
edge, and where lead permitted.
straps or wires exit the
de-ice boot.

(2) Visually examine for Refer to De-ice Boot and Re-adhere debonded edges
debond. Make sure Anti-icing Boot Debond Limits as necessary. Debonded boot
of the bond at the in this chapter. edges may be re-adhered with
de-ice boot edges, in accordance with the
blade leading edge, Repair/Modification chapter of
and where lead straps this manual or replace the
or wires exit the de-ice de-ice boot.
boot.

(3) Visually examine the A short circuit is not permitted. If arcing damage, a short, or
de-ice boot lead wires an open wire is found, perform
for a short. the De-ice Boot Inspection for
Overheating or a Short Circuit
in this chapter.

C. De-Ice System

(1) Visually examine for Corrosion is not permitted. If there is corrosion, replace the
corrosion. hardware.

(2) Visually examine for Minor damage, such as, nicks Replace any damaged or
damage and loose or and scratches, is permitted. missing hardware or tubing.
missing hardware. Loose or missing hardware or Tighten any loose hardware
tubing is not permitted. and safety as required.
Minor chafing is permitted.

De-ice System 100 Hour/12 Month Inspection

Table 5-1 (continued)

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Inspect Serviceable Limits Corrective Action

(3) Visually examine the Chafing that has exposed wiring If damage exceeds the
wire harness (890 or is not permitted. serviceable limits, replace the
895) and tubing for wiring and make installation
chafing. changes to prevent future
chafing.

(4) Visually examine the Arcing damage is not permitted. If arcing damage, a short, or
wire harness (890 A short or open circuit is not an open wire is found, replace
or 895) for arcing permitted. the wire harness.
damage caused by a
short.

(5) Visually examine the Arcing damage is not permitted. If arcing damage or a short
terminal strip (170 A short or open circuit is not is found, replace the terminal
and 310) and terminal permitted. strip.
studs for arcing
damaged caused by a
short out to each other
or to the propeller hub.

(6) Visually examine the Obvious damage that could If damage exceeds serviceable
terminal strip (170 adversely affect proper function limits, replace the part.
and 310) for general is not permitted.
appearance.

(7) Visually examine the A crack is not permitted. If there is a crack, replace the
terminal strip (170 and part.
310) for cracks.

D. System Check

(1) Perform the Propeller An open or a short circuit If arcing damage, a short, or
De-ice Operational is not permitted. Readout an open wire is found, replace
Check (Without outside operational limits is not the wire harness.
Engine Power) in permitted.
accordance with the
Inspection Procedures
in this chapter.

De-ice System 100 Hour/12 Month Inspection

Table 5-1 (continued)

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Inspect Serviceable Limits Corrective Action

(2) Perform the Propeller The ammeter needle must Replace system components
De-ice Operational remain in the acceptable area, that do not meet the
Check (Rotating) in green arc, for the appropriate serviceable limits. Correct as
accordance with the cycle. necessary.
Inspection Procedures
in this chapter.

(3) Every 12 calendar De-ice boot resistance values If resistance does not meet
months, perform must be those in Hartzell the serviceable limits, replace
de-ice circuit Propeller Electrical De-ice the de-ice boot.
resistance check Boot Removal and Installation
in accordance with Manual 182 (61-12-82).
the De-ice Circuit
Resistance Inspection
section of this chapter.

E. Terminal Mount Strap

(6000)
(1) Visually examine the Refer to the Terminal Mount Re-adhere debonded edges
terminal mount strap Strap Debond Limits in this as necessary. Re-adhere
for debonding. chapter. the debonded areas in
accordance with the Hartzell
Propeller Electric De-ice Boot
Removal and Installation
Manual 182 (61-12-82).

De-ice System 100 Hour/12 Month Inspection

Table 5-1 (continued)

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Inspect Serviceable Limits Corrective Action

A. Anti-Ice System Check

(1) Examine the filter. Make sure there is free flow of If fluid flow is obstructed flow,
fluid. clean or replace the filter.

(2) Examine all travel Blockage is not permitted. Clear all blockage as
tubes and travel tube necessary. Perform Propeller
hoses for obstructions Anti-Ice Operational Check in
or blockage. The lines accordance with the Inspection
to the slinger ring and Procedures in this chapter.
from the feed tubes
(travel tubes) to the
blade anti-icing boots
are especially prone to
blockage by insects.

(3) Visually examine for Minor damage, such as, nicks Replace any damaged or
damage, and loose or and scratches, is permitted. missing hardware.
missing hardware.
Tighten any loose hardware
and safety as required.

(4) Visually examine Corrosion is not permitted. Remove the corrosion and
hardware for corrosion. repair the blade in accordance
with the appropriate Hartzell
owner's manual.

Replace corroded hardware.

(5) Visually examine all A crack is not permitted. If damage exceeds serviceable
travel tubes and travel limits, replace all travel tubes
tube hoses for cracks. and travel tube hoses.

(6) Visually examine to Safety wire and hose clamps Re-safety or tighten as
make sure the safety must securely attach the travel needed.
wire and hose clamps tube and travel tube hose.
are secure.

Anti-ice System 100 Hour/12 Month Inspection

Table 5-2

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Inspect Serviceable Limits Corrective Action

B. Anti-icing boot

(1) Visually examine the Damage that impairs the flow If damage exceeds serviceable
anti-icing boot for of the fluid is not permitted. limits, replace the anti-icing
impact damage or boot.
deterioration.

(2) Visually examine the Minor debonding is permitted. Refer to the De-ice Boot and
anti-icing boot for Anti-icing Boot Debond Limits
debonding. in this chapter.

(3) Visually examine the Corrosion is not permitted. If there is corrosion or exposed
area around the metal, the anti-icing boot must
anti-icing boot for blade be removed and the corrosion
corrosion or exposed repaired by qualified personnel
metal, especially at an appropriately licensed
corrosion that extends propeller repair facility.
beneath the anti-icing
boots.

Anti-ice System 100 Hour/12 Month Inspection

Table 5-2 (continued)

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Inspect Serviceable Limits Corrective Action

A. De-ice Split Mounting Plate

(1130)

(1) Visually examine for Obvious damage that could If damage exceeds serviceable
general appearance. adversely affect proper function limits, replace the split
is not permitted. mounting plate.

(2) Visually examine for Active corrosion is not Remove active corrosion with
corrosion. permitted. Pitting that could glass media blasting.
adversely affect proper function If corrosion exceeds
is not permitted. serviceable limits replace the
split mounting plate.

(3) Visually examine for Obvious scratches that could Stone flat any raised material.
scratches. adversely affect proper function Polishing is not permitted.
are not permitted.

B. De-ice Spacers (2530)

(1) Visually examine for Obvious damage that could If damage exceeds serviceable
general appearance. adversely affect proper function limits, replace the spacer.
is not permitted.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. spacer.

Non-rotating or Airframe Mounted Component Inspection

Table 5-3

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Inspect Serviceable Limits Corrective Action

C. Brush Block Assembly

(2010)

(1) Visually check the Obvious damage that could If damage exceeds serviceable
brush block modules for adversely affect proper function limits, replace the brush block
damage or deformation. is not permitted. module.

(2) Visually check the A crack is not permitted. If there is a crack, replace the
brush block modules for brush block module.
cracks.

(3) Visually examine for Clean with CM23 or equivalent Repair the source of leakage.
grease, fuel, and/or and a soft bristle brush, as
carbon deposits. required.

(4) Inspect brushes for free Brushes must move freely in If brushes do not move freely,
movement. each module. replace the brush block
module.

(5) Visually examine for Serviceable limits are specified Replace brushes worn
uneven wear, chipping in the Brush Measurement beyond serviceable limits in
or breakage of brushes. section in this chapter. accordance with the Repair/
Modification chapter of this
manual.

(6) Measure the brush Serviceable limits are specified Replace brushes worn
wear in accordance with in the Brush Measurement beyond serviceable limits in
the Brush Measurement section in this chapter. accordance with the Repair/
in this chapter. Modification chapter of this
manual.
D. Switch Face Plate (3030)

(1) Visually examine for Obvious damage that could If damage exceeds serviceable
general appearance. adversely affect proper function limits, replace the switch face
is not permitted. plate.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. switch face plate.

Non-rotating or Airframe Mounted Component Inspection

Table 5-3 (continued)

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Inspect Serviceable Limits Corrective Action

E. Brush Block Shim (2015)

(1) Visually examine for Obvious damage that could If damage exceeds serviceable
general appearance. adversely affect proper function limits, replace the brush block
is not permitted. shim.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. brush block shim.

F. Alignment Shim (2510)

(1) Visually examine for Obvious damage that could If damage exceeds serviceable
general appearance. adversely affect proper function limits, replace the alignment
is not permitted. shim.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. alignment shim.

Non-rotating or Airframe Mounted Component Inspection

Table 5-3 (continued)

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Inspect Serviceable Limits Corrective Action

G. Ammeter (1220)

(1) Check that the ammeter Check shunt by disconnecting If the readings from the
and shunt are correctly ammeter leads and connecting ammeter and shunt do not
matched by checking a millivoltmeter across the agree, replace whichever is
the shunt notation. shunt. Activate the defective.
Shunts with “30 amps de-icing system and check the
= 50 MV” are used millivoltmeter reading.
with 0-30 amp range If the ammeter scale is 0-50,
ammeters. Shunts with the millivoltmeter reading
“50 amps = 50 MV” are should be the same as the
used with 0-50 amp ammeter reading. If the
range ammeters. ammeter scale is 0-30, the
millivoltmeter reading should
be 1-2/3 (167%) of the
ammeter reading. Check the
ammeter by connecting a test
shunt of proper value or using
an adjustable 0-50 millivolt
source. Check for correct
reading with the deicing system
activated. If the readings from
the ammeter and shunt do not
agree, replace whichever is
defective.

Non-rotating or Airframe Mounted Component Inspection

Table 5-3 (continued)

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Inspect Serviceable Limits Corrective Action

H. Metal Oxide Varistor (MOV)

Assembly (2900)

(1) Visually examine for Minor damage, such as, nicks Replace any damaged or
damage and loose or and scratches, is permitted. missing hardware or tubing.
missing hardware. Loose or missing hardware or
tubing is not permitted. Tighten any loose hardware
and safety as required.

(2) Inspect for arcing Arcing damage is not If there is evidence of arcing,
damage caused by permitted. A short circuit is not replace or return the unit
a short or lightning permitted. to Hartzell for inspection or
surging. replace. If lightning damage is
suspected, perform additional
propeller or airframe inspection
in accordance with Hartzell
Standard Practices Manual
202A or the TC hold's ICA.

I. Brush Block Bracket (2500)

(1) Visually examine for Obvious damage that could If damage exceeds serviceable
general appearance. adversely affect proper function limits, replace the brush block
is not permitted. bracket.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. brush block bracket.

(3) Visually examine for Pitting in excess of 0.062 inch If pitting exceeds serviceable
corrosion. (1.575 mm) diameter and 0.010 limits, replace the brush block
inch (0.254 mm) deep is not bracket.
permitted.

Active corrosion is not Using glass media blasting,

permitted. remove active corrosion.

Non-rotating or Airframe Mounted Component Inspection

Table 5-3 (continued)

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Inspect Serviceable Limits Corrective Action

J. De-ice Timers

(1) Visually examine for Obvious damage that could If damage exceeds
general appearance. adversely affect proper function serviceable limits, replace the
is not permitted. timer.

(2) Visually examine for a A crack is not permitted. If there is a crack, replace the
crack. timer.

(3) Visually examine for Corrosion is not permitted. If pitting exceeds serviceable
corrosion and pitting. Pitting in excess of 0.062 inch limits, replace the timer.
(1.575 mm) diameter and Use glass media to remove
0.010 inch (0.254 mm) deep is corrosion.
not permitted.

Non-rotating or Airframe Mounted Component Inspection

Table 5-3 (continued)

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Inspect Serviceable Limits Corrective Action

K. MOV Bracket (2820)

(1) Visually examine for Obvious damage that could If damage exceeds
general appearance. adversely affect proper serviceable limits, replace the
function is not permitted. MOV bracket.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. MOV bracket.

(3) Visually examine for Corrosion is not permitted. Remove active corrosion
corrosion and pitting. using glass media. Refer
to the Cleaning chapter of
Hartzel Standard Practices
Manual 202A (61-0-02). If
damage is more than the
permitted serviceable limits,
replace the MOV bracket.

Pitting in excess of 0.062 inch If pitting is grreater than the

(1.575 mm) diameter and serviceable limits, replace the
0.010 inch (0.254 mm) deep is MOV bracket.
not permitted.

L. Circuit Breaker Switch

(3020)

(1) Visually examine for Obvious damage that could If damage exceeds
general appearance. adversely affect proper serviceable limits, replace the
function is not permitted. circuit breaker switch.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. circuit breaker switch.

30-60-81
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Inspect Serviceable Limits Corrective Action

A. Terminal Strip Spacer

(340)

(1) Visually examine for Obvious damage that could If damage exceeds
general appearance. adversely affect proper function serviceable limits, replace the
is not permitted. Using CM128 terminal strip spacer.
and a soft bristle brush to
remove comtaminants.

(2) Visually examine A crack or arcing damge is not If there is a crack or arcing
for cracks or arcing permitted. damage, replace the terminal
damage. strip spacer.

B. Lead Strap Clip (360)

(1) Visually examine for Obvious damage that could If damage exceeds
general appearance. adversely affect proper function serviceable limits, replace the
is not permitted. lead strap clip.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. lead strap clip.

C. Terminal Clamp Assembly

(700)

Obvious damage that could If damage exceeds

(1) Visually examine for
adversely affect proper function serviceable limits, replace the
general appearance.
is not permitted. terminal clamp assembly.

A crack is not permitted. If there is a crack, replace the

(2) Visually examine for
terminal clamp assembly.
cracks.

Pitting in excess of 0.062 inch If pitting exceeds serviceable

(3) Visually examine for
(1.575 mm) diameter and limits, replace the terminal
corrosion.
0.010 inch (0.254 mm) deep is clamp assembly.
not permitted.
Using glass media blasting,
Active corrosion is not remove active corrosion.
permitted.

Rotating or Propeller Mounted Component Inspection

Table 5-4

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Inspect Serviceable Limits Corrective Action

(4) Inspect for loose studs. Obvious damage that could If a stud is loose, replace the
adversely affect proper function terminal clamp assembly.
is not permitted.
D. Insulating Bushing (290)

(1) Visually examine for Obvious damage that could If damage exceeds serviceable
general appearance. adversely affect proper function limits, replace the insulating
is not permitted. bushing.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. insulating bushing.

E. Terminal Strip (170 and

310)

(1) Visually examine for Obvious damage that could If damage exceeds serviceable
general appearance. adversely affect proper function limits, replace the terminal
is not permitted. strip.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks damage. terminal strip.

(3) Visually examine the Arcing damage is not If arcing damage or a short
terminal strip and permitted. A short or open is found, replace the terminal
terminal studs for arcing circuit is not permitted. strip.
damaged caused by a
short out to each other
or to the propeller hub.

Rotating or Propeller Mounted Component Inspection

Table 5-4 (continued)

30-60-81
Page 5-22
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 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

TEMPORARY REVISION NO. 003

To Manual 30-60-81
This Temporary Revision is now considered a part
of Hartzell Propeller Ice Protection System Component Maintenance Manual 181.

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 5-22 (Rev. 2 Oct/09).

Reason for issue: Remove the requirement to inspect and replace the rubber spacer if
cracked.

NOTE: See page 1 of this Temporary Revision.

© 2012 - Hartzell Propeller Inc. - All rights reserved

CHECK TR-003 Page 2 of 2

Feb/12
 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

Inspect Serviceable Limits Corrective Action

F. Terminal Clamp Assembly

(700)

(1) Visually examine for Obvious damage that could If damage exceeds
general appearance. adversely affect proper function serviceable limits, replace the
is not permitted. part.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. part.

(3) Visually examine for Pitting in excess of 0.062 inch If pitting exceeds serviceable
corrosion. (1.575 mm) diameter and 0.010 limits, replace the part.
inch (0.254 mm) deep is not
permitted.

Active corrosion is not permitted. Using glass media blasting,

remove active corrosion.

(4) Inspect for loose studs. A loose stud is not permitted. If a stud is loose, replace the
part.

G. Synchrophaser Target Obvious damage that could If damage exceeds

(1150) adversely affect proper function serviceable limits, replace the
is not permitted. part.

H. Rubber Spacer
(820)

(1) Visually examine for Obvious damage that could If damage exceeds
general appearance. adversely affect proper function serviceable limits, replace the
is not permitted. part.

Rotating or Propeller Mounted Component Inspection

Table 5-4 (continued)

CHECK TR-003 Page 1 of 2

Feb/12
 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

Inspect Serviceable Limits Corrective Action

F. Terminal Clamp Assembly

(700)

(1) Visually examine for Obvious damage that could If damage exceeds
general appearance. adversely affect proper function serviceable limits, replace the
is not permitted. part.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. part.

(3) Visually examine for Pitting in excess of 0.062 inch If pitting exceeds serviceable
corrosion. (1.575 mm) diameter and 0.010 limits, replace the part.
inch (0.254 mm) deep is not
permitted.
D -
A LI Using glass media blasting,
Active corrosion is not permitted.

R V RYremove active corrosion.

(4) Inspect for loose studs. A loose studG
E permitted.
R A If a stud is loose, replace the
N PO
is not

O part.
L EMthat could If damage exceeds
G. Synchrophaser Target
N O Taffect proper function serviceable limits, replace the
Obvious damage
(1150)
X T is not O
T permitted.
adversely

E
T FE ON R part.

RE VISI
H. Rubber Spacer
(820)

(1) Visually examineR

E Obvious damage that could If damage exceeds
for
general appearance. adversely affect proper function serviceable limits, replace the
is not permitted. part.

(2) Visually examine for A crack is not permitted. If there is a crack, replace the
cracks. part.

Rotating or Propeller Mounted Component Inspection

Table 5-4 (continued)

30-60-81
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 PROPELLER ICE PROTECTION SYSTEM
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Inspect Serviceable Limits Corrective Action

A. De-ice Split Mounting Plate

(1130)

(1) Perform penetrant A crack is not permitted. If damage exceeds serviceable

inspection in limits, replace the split mounting
accordance with the plate.
Penetrant Inspection
chapter of Hartzell
Standard Practices
Manual 202A
(61-01-02).

B. Slinger Ring Assembly

(5000)
(1) Visually examine the A crack is not permitted. If damage exceeds serviceable
slinger ring assembly limits, replace the slinger ring
for cracks. assemlby.

(2) Visually examine the A crack or separation is not If damage exceeds serviceable
welds for cracks or permitted. limits, replace the slinger ring
separation. assemlby.

(3) Visually examine the Obvious damage that could If damage exceeds serviceable
slinger ring assembly adversely affect proper function limits, replace the slinger ring
for damage. is not permitted. assemlby.

(4) Visually examine the Minor wear on corners and If the coverage is less than the
cadmium plating for random light scratches are permitted serviceable limits,
coverage. permitted; otherwise, complete cadmium replate the slinger
coverage is required. ring assembly in accordance
with the Cadmium Re-plating
chapter of the Hartzell Standard
Practices Manual 202A
(61-01-02).

Inspection at Propeller Overhaul

Table 5-5

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Inspect Serviceable Limits Corrective Action

(5) Magnetic particle No indications are permitted. None. Replace the slinger ring
inspect the slinger assembly.
ring assembly in
accordance with the
Magnetic Particle
Inspection chapter
of Hartzell Standard
Practices Manual 202A
(61-01-02). Cadmium
plating does not need
to be removed.

Inspection at Propeller Overhaul

Table 5-5 (continued)

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 PROPELLER ICE PROTECTION SYSTEM
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Lightning Strike Inspections

Component Procedure

A. De-ice Boots Visually examine the de-ice boot in accordance

with the De-ice System 100 Hour/12 Month
Inspection, Table 5-1, in this chapter.

Perform resistance check in accordance

with section 6.E. De-ice Circuit Resistance
Inspection in this chapter.

For graphite composite blades: Perform the section 6.K. Dielectric Strength test
in this chapter.

B. De-ice boot wire harness, slip ring wire Visually examine the de-ice boot in accordance
harness, and all de-ice attaching hardware. with the De-ice System 100 Hour/12 Month
Inspection, Table 5-1, and the Rotating or
Propeller Mounted Component Inspection,
Table 5-4, in this chapter.

All steel parts must be checked for magnetism.

Refer to the Demagnetization section of the
Magnetic Particle Inspection chapter of Hartzell
Standard Practices Manual 202A
(61-01-02), Volume 2.

C. Slip Ring Assembly Visually examine the slip ring assembly in

accordance with the De-ice System 100
Hour/12 Month Inspection, Table 5-1, in this
chapter.

Perform resistance check in accordance with

section 6.E. Slip Ring Resistance Check in this
chapter.

Special Inspections - Lightning Strike

Table 5-6

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 PROPELLER ICE PROTECTION SYSTEM
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Lightning Strike Inspections

Component Procedure

D. De-ice Brush Block Assembly Visually examine the de-ice brushes in

accordance with the Non-Rotating or Airframe
Mounted Component Inspection, Table 5-3, in
this chapter.

Visually examine the de-ice brush block

assembly in accordance with the Non-Rotating
or Airframe Mounted Component Inspection,
Table 5-3, in this chapter.

E. Timer or MOV Assembly Visually examine the timer and MOV assembly
in accordance with the Non-Rotating or
Airframe Mounted Component Inspection,
Table 5-3, in this chapter.

Perform the section 6.J. Timer Test in this

chapter.

F. Slinger Ring Assembly Visually examine the slinger ring assembly in

accordance with the Anti-ice System
100 Hour/12 Month Inspection, Table 5-2, in
this chapter.

Special Inspections - Lightning Strike

Table 5-6

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 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

Sudden Stoppage Inspections

Component Procedure

A. De-ice Boots Visually examine the de-ice boot in accordance

with the De-ice System 100 Hour/12 Month
Inspection, Table 5-1, in this chapter.

B. De-ice boot wire harness, slip ring wire Visually examine the components in
harness, and all de-ice attaching hardware. accordance with the De-ice System 100
Hour/12 Month Inspection, Table 5-1, and the
Rotating or Propeller Mounted Component
Inspection, Table 5-4, in this chapter.

C. Slip Ring Assembly Visually examine the slip ring assembly in

accordance with the De-ice System
100 Hour/12 Month Inspection, Table 5-1, in
this chapter.
D. De-ice Brush Block Assembly
Visually examine the de-ice brushes in
accordance with the Non-Rotating or Airframe
Mounted Component Inspection, Table 5-3, in
this chapter.

Visually examine the de-ice brush block

assembly in accordance with the Non-Rotating
or Airframe Mounted Component Inspection,
Table 5-3, in this chapter.
E. Timer or MOV Assembly
Visually examine the timer and MOV assembly
in accordance with the Non-Rotating or
Airframe Mounted Component Inspection,
Table 5-3, in this chapter.
F. Slinger Ring Assembly
Visually examine the slinger ring assemlby in
accordance with Anti-ice System
100 Hour/12 Month Inspection, Table 5-2, in
this chapter.

Special Inspections - Sudden Stoppage

Table 5-7

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Fire Inspections

Component Procedure

A. De-ice Boots Visually examine the de-ice boot in

accordance with the De-ice System 100
Hour/12 Month Inspection, Table 5-1, in this
chapter.

Perform resistance check in accordance

with section 6.E. De-ice Circuit Resistance
Inspection in this chapter.

B. De-ice boot wire harness, slip ring wire Visually examine the de-ice boot in
harness, and all de-ice attaching hardware. accordance with the De-ice System
100 Hour /12 Month Inspection, Table 5-1, and
the Rotating or Propeller Mounted Component
Inspection, Table 5-4, in this chapter.

C. Slip Ring Assembly Visually examine the slip ring assembly in

accordance with the De-ice System 100
Hour/12 Month Inspection, Table 5-1, in this
chapter.

Perform resistance check in accordance with

section 6.E. Slip Ring Resistance Check in
this chapter.

D. De-ice Brush Block Assembly Visually examine the de-ice brushes in

accordance with the Non-Rotating or Airframe
Mounted Component Inspection, Table 5-3, in
this chapter.

Visually examine the de-ice brushblock

assembly in accordance with Non-Rotating
or Airframe Mounted Component Inspection,
Table 5-3, in this chapter.

Special Inspections - Fire

Table 5-8

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 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

Fire Inspections

Component Procedure

E. Timer or MOV Assembly Visually examine the timer and MOV assembly
in accordance with the Non-Rotating or
Airframe Mounted Component Inspection,
Table 5-3, in this chapter.

Perform the section 6.J. Timer Test in this

chapter.

F. Slinger Ring Assembly Visually examine the slinger ring assemlby in

accordance with the Anti-ice System
100 Hour/12 Month Inspection, Table 5-2, in
this chapter.

Special Inspections - Fire

Table 5-8

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 PROPELLER ICE PROTECTION SYSTEM
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Foreign Object Strike Inspections

Component Procedure

A. De-ice Boots Visually examine the de-ice boot in

accordance with the De-ice System
100 Hour/12 Month Inspection, Table 5-1, in
this chapter.

Perform resistance check in accordance

with section 6.E. De-ice Circuit Resistance
Inspection in this chapter.

B. De-ice boot wire harness, slip ring wire Visually examine the de-ice boot in
harness, and all de-ice attaching hardware. accordance with the De-ice System
100 Hour/12 Month Inspection, Table 5-1, and
the Rotating or Propeller Mounted Component
Inspection, Table 5-4, in this chapter.

C. Slip Ring Assembly Visually examine the slip ring assembly in

accordance with the De-ice System
100 Hour/12 Month Inspection, Table 5-1, in
this chapter.

Perform resistance check in accordance with

section 6.E. Slip Ring Resistance Check in this
chapter.

D. De-ice Brush Block Assembly Visually examine the de-ice brushes in

accordance with the Non-Rotating or Airframe
Mounted Component Inspection, Table 5-3, in
this chapter.

Visually examine the de-ice brush block

assembly in accordance with the Non-Rotating
or Airframe Mounted Component Inspection,
Table 5-3, in this chapter.

Special Inspections - Foreign Object Strike

Table 5-9

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 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

Foreign Object Strike Inspections

Component Procedure

E. Timer or MOV Assembly Visually examine the timer and MOV assembly
in accordance with the Non-Rotating or
Airframe Mounted Component Inspection,
Table 5-3, in this chapter.

F. Slinger Ring Assembly Visually examine the slinger ring assemlby

in accordance with the Anti-ice System 100
Hour/12 Month Inspection, Table 5-2, in this
chapter.

Special Inspections - Foreign Object Strike

Table 5-9

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6. Inspection Procedures

CAUTION 1: FOR AN ALUMINUM BLADE: DO NOT OPERATE THE DE-ICE BOOTS

FOR MORE THAN ONE CYCLE . OVERHEATING OF THE
DE-ICE BOOT CAN CAUSE DAMAGE TO THE PROPELLER BLADES.
PERMIT BLADES TO COOL COMPLETELY BEFORE REPEATING
THE TEST.

CAUTION 2: FOR A COMPOSITE BLADE: DO NOT OPERATE THE DE-ICE BOOTS

FOR MORE THAN 10 SECONDS. OVERHEATING OF THE
DE-ICE BOOT CAN CAUSE DAMAGE TO THE PROPELLER BLADES.
PERMIT BLADES TO COOL COMPLETELY BEFORE REPEATING
THE TEST.

CAUTION 3: TO PREVENT ARCING DAMAGE TO THE SLIP RING WHEN

PERFORMING THE PROPELLER DE-ICE OPERATIONAL CHECK
(WITHOUT ENGINE POWER), SLOWLY ROTATE THE PROPELLER
BY HAND.

NOTE: An auxiliary power supply (APU) may be used when checking the de-ice
system.
A. Propeller De-ice Operational Check (Without Engine Power)
(1) On a multi-engine application only, isolate the de-ice system on the non-test
propeller.
(a) Using a non-conductive material, isolate the brushes from the slip ring
assembly to prevent contact of the brushes with the slip ring.
(2) Slowly rotate the test propeller by hand.
(3) Activate the de-ice system

NOTE: The timer output can be cycled through each phase by cycling the
timer off for 1 to 5 seconds and then back on. Cycling a timer off for
more than 7 seconds may reset the timer to the first cycle.
(4) Visually confirm that the ammeter(s) or annunciator(s) indication for the test
propeller is within acceptable limits for each phase.
(a) If the indication is not within acceptable limits, proceed to De-ice Circuit
Resistance Inspection.
(b) If the indication is not within acceptable limits and the De-ice Circuit
Resistance Inspection has no fault found, refer to the aircraft TC or STC
holder's Instructions for Continued Airworthiness.

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 PROPELLER ICE PROTECTION SYSTEM
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Slip Ring Assembly

Dial Indicator
Direction of Propeller
Rotation

Copper Rings

Slip Ring Run-out Check

Figure 5-1

30-60-81
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 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

(5) If applicable, repeat the test for the other propeller assemblies.
(6) Perform the de-ice boot heat test:
(a) Slowly rotate the test propeller by hand.
(b) Activate the de-ice system for an aluminum blade a maximum of 3 minutes
and for a composite blade a maximum of 10 seconds. Permit the blade to
cool between heating cycles.

NOTE: The timer output can be cycled through each phase by cycling the
timer off for 1 to 5 seconds and then back on. Cycling a timer off for
more than 7 seconds may reset the timer to the first cycle.

WARNING: ON SPECIFIC AIRCRAFT THE DE-ICE SYSTEM MAY

OPERATE UP TO 200 VAC WHICH CAN CAUSE SERIOUS OR
FATAL INJURY. USE EXTREME CAUTION WHEN OPERATING
PROPELLER DE-ICE SYSTEM WHILE AIRCRAFT IS STATIC.
VISUALLY INSPECT BOOTS FOR CRACKS OR EXPOSED
HEATING ELEMENTS.
(c) Touch the de-ice boot area on each blade that should be heated during
each phase of the de-ice cycle.
Example: De-ice systems have several cycling methods.
1. All inboard areas will heat at the same time and then all
outboard areas will heat at the same time.
2. All boots will heat at the same time and are off at the same
time.
3. On some four bladed propellers, blades 1 and 3 will heat
and then blades 2 and 4.
1 If the heating is not correct, refer to Hartzell Propeller Ice Protection
System Manual 180 (30-61-80) or refer to the aircraft TC or STC
holder's Instructions for Continued Airworthiness to verify that the
propeller de-ice wiring is correct.

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B. Propeller De-ice Operational Check (Rotating)

(1) Lock the brakes and operate the engine at a high RPM setting.
(2) Activate the de-ice system in accordance with the aircraft TC or STC holder's
ICA and observe the ammeter or annunciator for approximately two cycles for
the appropriate installation.
(3) The ammeter needle should remain in the acceptable area for the complete
phase of each cycle and the annunciator reading is correct.

NOTE: Some ammeter needles may flicker outside shaded area as timer
cycles to each phase.
(a) If the indication is not within acceptable limits, proceed to De-ice Circuit
Resistance Inspection.
(4) Repeat as needed
C. Lightning Strike
(1) In the event of a propeller lightning strike, an inspection of the de-ice
components is required before further flight.
(2) Perform the De-ice System 100 hour/12 Month Inspection requirements
specified in Table 5-1 of this chapter.
(3) In de-icing systems with Metal Oxide Varistor (MOV) assemblies, replace MOV
assemblies in all cases of lightning strike.
(4) After above inspection and replacement of MOV assemblies (if applicable),
perform a functional test of the system to assure proper cycling of timer and
correct current draw per system design.
D. De-ice Slip Ring Run-out Check

CAUTION: SEVERE ARCING AND BRUSH WEAR OFTEN OCCUR WHEN

THERE IS "WOBBLE" IN THE SLIP RING ASSEMBLY (1140).
WOBBLE OCCURS BECAUSE THE SLIP RINGS DO NOT RUN IN
A PLANE PERPENDICULAR TO THE CENTER LINE OF ROTATION
OF THE PROPELLER SHAFT. SLIP RING WOBBLE WILL CAUSE
RAPID DETERIORATION OF THE SLIP RING/BRUSH BLOCK
CONTACT SURFACES AND EVENTUAL FAILURE OF THE DE-ICE
SYSTEM.
(1) Perform slip ring run-out check at each slip ring installation, whenever brush
block assembly is replaced, or as needed to trouble-shoot a suspected system
fault.
(2) Perform a slip ring assembly (1140) run-out check:
(a) Attach a dial indicator gauge to the engine or assembly stand.
(b) Hold the propeller blade and rotate the propeller slowly.

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 PROPELLER ICE PROTECTION SYSTEM
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Brush exposure at inspection

0.0625 inch (1.587 mm)

Measuring Tool

Brush Rod Hole

0.359 inch
(0.912 mm)
Maximum

Brush Measurement
Figure 5-2

30-60-81
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 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

(c) Place the pointer on the copper ring. Refer to Figure 5-1.
(d) Measure the slip ring indicated run-out.
(3) Use uniform push or pull on the propeller to make sure the slip ring run-out
measurement is accurate.
(4) The maximum permitted total indicated run-out (TIR) is 0.005 inch
(0.127 mm) for piston engines, or 0.008 inch (0.2032 mm) for turbine engines.
Total indicated run-out (TIR) measurement must not exceed 0.0020 inch
(0.0508 mm) within any 4.0 inch (101.5 mm) arc of slip ring travel.

CAUTION: DO NOT VARY THE TORQUE OF THE PROPELLER

ATTACHMENT BOLTS. VARY THE TORQUE ONLY ON THE
SLIP RING MOUNTING BOLTS.
(a) For steel hub and compact propeller installed using a belleville washer,
the belleville washer arrangement that permits proper slip ring adjustment
by varying the torque applied to attaching hardware.
1 If the slip ring run-out measurement exceeds serviceable limits, vary
the torque on the slip ring attachment bolts within the limits specified
below or in accordance with the TC or STC holder's ICA, or within
standard limits for bolts used.
a 96 - 120 in-lbs. (10.8 - 13.5 N•m) for 1/4-28 bolts or screws
b 21 - 32 in-lbs. (2.3 - 3.6 N•m) for 10-32 screws or bolts
c 40 - 120 in-lbs. (4.5 - 13.5 N•m) if Belleville washers are used
(b) If the run-out still exceeds serviceable limits:
1 Remove the slip ring assembly (1140) and clean.
2 Make sure of the flatness and structural integrity of the mounting
surface.
3 Put the slip ring assembly on a flat surface and measure the slip ring
run-out (flatness to mounting surface).
4 If necessary, resurface the slip ring in accordance with the
De-Ice Slip Ring Resurfacing section in the Repair/Modification
chapter of this manual.
5 Reinstall the slip ring assembly (1140) on the propeller.
6 Perform the slip ring run-out check.
7 If the run-out still exceeds serviceable limits, replace the slip ring
assembly (1140) with a serviceable part.

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E. De-ice Circuit Resistance Inspection

NOTE 1: The De-ice Circuit Resistance Inspection is only required at 12 month

intervals except as required by Paragraph 6.A. Propeller De-ice
Operational Check (Without Engine Power)

NOTE 2: A de-ice boot circuit includes the de-ice boot, de-ice wire harness, de-ice
terminal strips, slip ring wire harness, and all other components that permit
the de-ice system to work.
(1) Isolate the slip ring assembly from the brush block brushes.
(a) Isolate the brushes from the slip ring assembly using a non-conductive
material to prevent contact by a brush to the slip ring.
(2) Using a megohm meter, with the 2000 megohm at 500 volts (DC) range
selected, attach it to any point on the de-ice circuit and to a hub clamping bolt.
(3) Dielectric Reading Inspection
(a) If the dielectric reading is less than 8 megohms, remove grease, oil, or
other contaminates from the slip ring surface or other connection parts that
could lead to a faulty reading and repeat the resistance check.
(b) If the dielectric reading remains less than 8 megohms, isolate each
component and perform resistance check until the fault is found. Clean,
replace, or repair the affected component(s).
(c) A dielectric reading greater than 8 megohms is acceptable.
(4) Perform the following electrical resistance inspection on each blade in the
propeller assembly:
(a) Refer to Hartzell Propeller Electrical De-ice Boot Removal and Installation
Manual 182 (61-12-82) for the correct resistance values for the de-ice boot
installed on the blade.
(b) Disconnect the de-ice boot circuit for each blade at the closest connection
to the slip ring assembly to isolate the de-ice boot circuit for each blade.
(c) Using a megohm meter, note the resistance reading and compare the
results to the resistance values.
(d) Flex and probe each component on the de-ice boot circuit while monitoring
the resistance readings.
1 If the resistance reading fluctuates, clean, repair, or replace any
affected component.

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2 Read the resistance of the de-ice boot circuit and compare the results
to the resistance values specified in Hartzell Propeller Electrical
De-ice Boot Removal and Installation Manual 182 (61-12-82).
a If the resistance value is not correct, isolate the de-ice boot and
perform resistance check on the boot.
b If the resistance value of the de-ice boot reading is not correct,
replace the de-ice boot in accordance with Hartzell Propeller
Electrical De-ice Boot Removal and Installation Manual 182
(61-12-82).
c If the resistance value of the de-ice boot reading is correct,
isolate each component and perform resistance check
until the fault is found. Clean, Replace, repair the affected
component(s).
(5) When the resistance value of the de-ice circuit is correct, repeat the inspection
specified in paragraph 6.A. Propeller De-ice Operational Check (Without
Engine Power).
F. De-ice Boot or Anti-icing Boot Debond Limits
(1) For the 4H3064-1 and the 7931-4E3064-1 de-ice boot installed on the
HC-B5MA-2( ) propeller:
(a) The maximum allowable debond is 6.50 square inches
(4193.54 square mm) over the entire de-ice boot surface, face side and
camber side combined.
(b) If debond exceeds the allowable limit, the de-ice boot must be replaced.
(2) For the B-6442 de-ice boot installed on the HD-E6C-3( ) propeller:
(a) The maximum permitted debond is 30.00 square inches (19354 sq/mm)
over the entire de-ice boot surface, face side, and camber side combined.
(b) If debond exceeds the permitted limit, the de-ice boot must be replaced at
the next A-check or within 300 flight hours, whichever occurs first.
(c) A de-ice boot with debonded areas that exceed 35.0 square inches
(22580 sq/mm) must be replaced before further flight, except as noted
below.
1 If visual inspection shows no evidence of premature de-ice boot
failure, the de-ice boot may remain in service for up to 10 flight hours,
to permit maintenance scheduling.
(d) A debond may not extend to the edge of the de-ice boot.
1 Loose de-ice boot edges at the outboard end of the de-ice boot,
within 0.25 inch (6.35 mm) of the leading edge, are permitted.

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(3) For the 4H4072-(1, 2) de-ice boot installed on the HC-E5A-2( ) propeller:
(a) The maximum permitted debond is 9.00 square inches (228.6 mm) over
the entire de-ice boot surface, face and camber side combined.
(b) If debond exceeds the allowable limit, the de-ice boot must be replaced.
(4) For all other de-ice boots or anti-icing boots:
(a) The maximum permitted debond is 3.00 square inches
(1935.48 square mm) over the entire de-ice boot surface, face side and
camber side combined.
(b) If debond exceeds the permitted limit, the de-ice boot must be replaced.
(5) For all de-ice boots or anti-icing boots:
(a) A raised area of a debond must not have signs of accelerated erosion,
tearing, punctures, or other unusual wear or damage that could lead to
premature failure of the de-ice boot.
(b) A de-ice boot or an anti-icing boot that has significantly raised areas of
debond that would obviously affect the function must be replaced before
further flight.
(6) Re-adhering de-ice boot or anti-icing boot debond:
(a) Re-adhere de-ice boot or anti-icing boot in accordance with the installation
procedures in Hartzell Propeller Electrical De-ice Boot Removal and
Installation Manual 182 (61-12-82) or Hartzell Propeller Anti-icing Boot
Removal and Installation Manual 183 (61-12-83).
G. Terminal Mount Strap Debond Limits
(1) The terminal mount strap may be debonded from the blade up to 70 percent of
the total strap width, when applying a 6 pound force to the wire harness toward
the tip of the blade.
(a) Apply the load to the wire harness midway between the adel clamp,
securing the harness to the terminal mount strap and the de-ice harness
bracket that is attached to the hub.
(2) Puckers and wrinkles of the terminal mount strap are permitted if they do not
adversely affect the proper fit or function and the edges are sealed to the blade.
(3) Re-adhere the terminal mount strap in accordance with the installation
procedures in Hartzell Propeller Electrical De-ice Boot Removal and Installation
Manual 182 (61-12-82).

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H. Brush Measurement
(1) Brush Modules with Rods
(a) Measure brush wear to determine requirement to replace brushes.
1 Refer to Figure 5-2 how to measure brush wear. Compress brush
into the module so that 0.0625 inch (1.587 mm) of the brush extends
from the brush module.
2 Use a toothpick, small diameter wire, or equivalent as a measuring
tool. Slide the measuring tool into the opening above the brush rod in
the module until the tool touches the end of the rod.
3 Mark or indicate on the measuring tool the location where it aligns
with the outside edge of the module.
4 Remove the measuring tool from the module and measure the
amount of the measuring tool that extended into the module.
5 When the measured amount is 0.359 inch (9.118 mm) or greater,
replace the brush.
(2) Replace the brush as necessary in accordance with the Repair/Modification
chapter of this manual.
I. Propeller Anti-Ice System Operational Check
(1) Attach a hose to the tubing between the pump and the slinger ring. Place the
other end of the hose in a container that is marked for measuring fluid.
(2) Refer to the aircraft TC or STC holder's ICA or the propeller owner's manual
for anti-ice system flow rate information. For example, the owners manual may
state that “with the rheostat in the MAX position, fluid is dispensed at a rate of
approximately one quart every four minutes.”
(3) Operate the system as suggested in the aircraft TC or STC holder's ICA or
propeller owner’s manual. The container that is marked for measuring fluid
should contain the amount of anti-ice fluid specified by the aircraft TC or STC
holder's ICA or propeller owner’s manual at the end of the test.
(4) If the expected results are not achieved at the conclusion of the test:
(a) No fluid flow to all blades on all propellers (if applicable).
1 The tank is empty.
2 The tank siphon tube is blocked. Clean the tube and reinstall.
3 The filter is clogged. Clean or replace the filter and reinstall.
4 The pump is inoperative. Loosen the output fitting at the pump
and the operating system and measure the fluid flow at the pump.
Replace the pump if necessary.

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(b) No fluid flow to one propeller (all blades).

1 The tank is empty.
2 The tank siphon tube is blocked. Clean the tube and reinstall.
3 The filter is clogged. Clean or replace the filter and reinstall.
4 The pump is inoperative. Loosen the output fitting at the pump
and the operating system and measure the fluid flow at the pump.
Replace the pump if necessary.
5 The check valve is clogged or stuck closed. Remove the obstruction
or replace the valve as necessary.
6 The feed tube to the slinger ring is clogged. Remove the obstruction.
(c) No fluid flow to one or more blades.
1 Clogged slinger ring tube(s). Remove the obstruction.
(d) Fluid supply decreases - system not in use.
1 There is evaporation. Alcohol systems are especially prone to fluid
loss through evaporation.
2 There is a system leak. Check the tank and lines for leaks. Repair or
replace components as necessary.
3 There is a marked fluid loss after flight. There is a defective check
valve. Replace the check valve as necessary.
(e) Flow rate slows or stops as system is operated.
1 The tank vent is blocked or inoperative. Clear the blockage or replace
the vent as necessary.
J. Timer Test - Hartzell 1( )( )( )( )( ) part numbers only

NOTE: Timer test is required only when de-ice boot heat test or abnormal current
annunciation indicates system malfunction.
(1) Use APU with 24 to 32 VDC output or a system battery capable of supplying
40 amps DC at 24 volts.
(2) Measure voltage from aircraft ground to Pin E. System voltage should be
present.
(3) Measure from aircraft ground to outputs, Pin D and Pin F. Each output should
have a system voltage for 90 seconds each +/- 5% alternating between outputs.
(4) With cockpit switch de-ice "on", measure control voltage to Pin B. System
voltage should be present.
(5) Measure annunciator output Pin G (positive) and Pin I (negative). Voltage
should measure 3.6 - 4.0 volts.

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(6) If the readings are not within serviceable limit, contact Hartzell Propeller Inc.
K. Dielectric Strength

CAUTION: DO NOT ATTEMPT THIS TEST UNLESS ALL REATTACHMENT

PROCEDURES ARE COMPLETE, INCLUDING TOTAL CURING OF
THE ADHESIVE.
(1) Using an Associated Research Meg-Check, Model 2026D, or Model 1026, or
equivalent, with the 2000 megohm at 500 volts (DC) range selected, check the
dielectric strength of each de-ice boot on the propeller assembly.
(a) Disconnect the de-ice lead wires to isolate the individual de-ice boot.
Connect the positive (red) lead of the test unit to a lead wire on one blade
de-ice boot.
(b) Connect the negative (black) lead to an exposed section of the erosion
shield.

WARNING: DO NOT TOUCH ANY PART OF THE BLADE WHILE THE

FOLLOWING TEST EQUIPMENT IS TURNED ON.
(c) Turn the power switch to the “ON” position for one minute while observing
the resistance reading. The resistance measurement must be 8 Megohm
or more.
(d) If the resistance is less than 8 Megohm, the de-ice boot must be replaced.
(2) If resistance is greater than or less than the serviceable limits specified in the
De-ice Boot Resistance Check section of Hartzell Propeller Electrical De-ice
Boot Removal and Installation Manual 182 (61-12-82), as required, replace the
de-ice boot.

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L. De-ice Boot Inspection for Overheating or a Short Circuit

CAUTION: DO NOT OPERATE THE DE-ICE BOOTS ON AN ALUMINUM

BLADE FOR MORE THAN ONE CYCLE WHEN THE AMBIENT
TEMPERATURE IS ABOVE 100°F (38°C). OVERHEATING OF THE
DE-ICE BOOT CAN CAUSE DAMAGE TO THE PROPELLER BLADES.
ALLOW BLADES TO COOL COMPLETELY BEFORE REPEATING THE
TEST.
(1) For an aluminum blade:
(a) If the de-ice boot indicates evidence of damage, burning, or short circuits,
or has experienced or is suspected of overheating because of operation in
a non-rotating environment, inspect the de-ice boot for a debond condition
in accordance with section the De-ice Boot and Anti-icing Boot Debond
Limits in this chapter.
1 If the debond is greater than the limits permitted:
a Remove and replace the de-ice boot in accordance with Hartzell
Propeller Electrical De-ice Boot Removal and Installation
Manual 182 (61-12-82).
b Inspect the blade in the area where the de-ice boot is installed in
accordance with the Check chapter of Hartzell Aluminum Blade
Overhaul Manual 133C (61-13-33).
c Contact Hartzell Product Support department if the blade
exhibits arcing damage or evidence of overheating.
2 If a debond condition is not found, the propeller may be returned to
service.

CAUTION: FOR A COMPOSITE BLADE: DO NOT OPERATE THE DE-ICE BOOTS

FOR MORE THAN 10 SECONDS. OVERHEATING OF THE
DE-ICE BOOT CAN CAUSE DAMAGE TO THE PROPELLER BLADES.
PERMIT BLADES TO COOL COMPLETELY BEFORE REPEATING THE
TEST.
(1) For a composite blade:
(a) If the de-ice boot has experienced or is suspected of overheating because
of operation in a non-rotating environment, inspect the de-ice boot for a
debond condition in accordance with section De-ice Boot and Anti-icing
Boot Debond Limits in this chapter.
1 If the debond is greater than the limits permitted:
a Remove and replace the de-ice boot in accordance with Hartzell
Propeller Electrical De-ice Boot Removal and Installation
Manual 182 (61-12-82).

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b Perform a visual and a coin tap inspection of the blade in the

area where the de-ice boot is installed in accordance with the
Check chapter of Hartzell Composite Blade Overhaul Manual
135F (61-13-35).
c Contact Hartzell Product Support department if a blade exhibits
arching damage or evidence of overheating.
2 If a debond condition is not found, the propeller may be returned to
service.

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REPAIR/MODIFICATION - CONTENTS

1. General Repair Requirements ............................................................................6-3

A. Aluminum and Steel Parts .............................................................................6-3
B. Copper Parts .................................................................................................6-3
2. Specific Repair Requirements ............................................................................6-3
A. De-ice Slip Ring Resurfacing except 4E2811-( ) ...........................................6-3
B. De-ice Slip Ring Resurfacing for 4E2811-( ) .................................................6-9
C. De-ice Slip Ring Assembly Resistance Checks ............................................6-9
D. Slip Ring Lead Wire Replacement ..............................................................6-10
E. Brush Replacement .....................................................................................6-12
F. Brush Module Replacement ........................................................................6-14
G. Slip Ring Interchangeability .........................................................................6-15
H. 4H2422 Slip Ring Mounting Screw (1141) Replacement ............................6-16
I. Alternate Configuration for De-ice Kit 7931-65-025-1
with Spinner Bulkhead P/N D-3437-1(P) ....................................................6-16

LIST OF FIGURES

De-ice Slip Ring Minimum Dimension

except 4E2811-( ) ..............................................................Figure 6-1 ................6-6
De-ice Slip Ring Minimum Dimension
for 4E2811-( ) .....................................................................Figure 6-2 ................6-7
Installation of New Brush in Module .......................................Figure 6-3 .............. 6-11
Brush Module Assembly Stacking ..........................................Figure 6-4 ..............6-13
Alternate Configuration for De-ice Kit 7931-65-025-1
with Spinner Bulkhead P/N D-3437-1(P) ..........................Figure 6-5 ..............6-17

LIST OF TABLES

Slip Ring Minimum Dimension ...............................................Table 6-1 .................6-4

REPAIR/MODIFICATION 30-60-81 Page 6-1

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WARNING: DO NOT ATTEMPT IN THE FIELD ANY REPAIR, REPLACEMENT,

REWORK, REPLATING, OR RE-ANODIZING NOT SPECIFICALLY
AUTHORIZED BY HARTZELL PROPELLER INC. OR SPECIFIED IN A
HARTZELL MANUAL. CONTACT HARTZELL PROPELLER INC. FOR
GUIDANCE ABOUT THE AIRWORTHINESS OF ANY PART WITH
UNUSUAL WEAR OR DAMAGE.

1. General Repair Requirements

A. Aluminum and Steel Parts
(1) Eliminate all scratches, nicks, burrs, and other minor damage by using a fine
emery cloth or abrasive pad CM47 or equivalent. Make 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 sure the part is still within serviceable limits after any type of repair. Refer
to the Check chapter and the Fits and Clearances chapter of this manual.
B. Copper Parts
(1) Rework and repair copper rings in accordance with the De-ice Slip Ring
Resurfacing section of this chapter.

2. Specific Repair Requirements

A. De-ice Slip Ring Resurfacing except 4E2811-( )
(1) Using solvent CM106 or CM128, clean the slip ring assembly (1140) before
machining.
(2) Install the slip ring assembly (1140) on a lathe.
(a) The slip ring assembly (1140) must be centered and installed on a
locally manufactured plate. The plate must be sufficiently rigid and flat
within 0.002 inch (0.051 mm) or less to prevent deflection of the slip
ring assembly (1140) during machining. The plate must permit the slip
ring (1140) to be securely mounted to prevent chatter when cutting the
surfaces of the copper rings. If bolts are used as the attachment method
to the plate, torque the bolts (1160/1170) in accordance with Table 8-1.

NOTE: Mounting the slip ring through the slip ring attachment holes
provides the best probability of achieving slip ring run out
requirements after installation.

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"X" Dimension "X" Dimension

Refer to Figure 6-1 Refer to Figure 6-1
Part Number Inches mm Part Number Inches mm
4H1526-1 0.475 12.06 4H1964-4 0.975 24.76
7931-4E1526-1 0.475 12.06 7931-4E1964-4 0.975 24.76
4H1526-4 0.475 12.06 4H1988-1 0.320 8.13
7931-4E1526-4 0.945 24.00 7931-4E1988-1 0.320 8.13
4H1555-1 0.220 5.58 4H2267-1 0.295 7.49
7931-4E1555-1 0.220 5.58 7931-4E2267-1 0.295 7.49
4H1555-2 0.220 5.58 4H2267-2 0.295 7.49
7931-4E1555-2 0.220 5.58 7931-4E2267-2 0.295 7.49
4H1555-3 0.220 5.58 4H2350-1 0.980 24.89
7931-4E1555-3 0.220 5.58 7931-4E2350-1 0.980 24.89
7931-4E1614-2 0.265 6.73 4H2377-1 0.650 16.51
7931-4E1614-3 0.945 24.00 7931-4E2377-1 0.650 16.51
7931-4E1676-1 0.187 4.74 4H2422 0.295 7.49
7931-4E1676-2 0.187 4.74 7931-4E2422 0.295 7.49
7931-4E1676-3 0.187 4.74 4H2442-1 0.187 4.74
7931-4E1676-6 0.187 4.74 7931-4E2442-1 0.187 4.74
7931-4E1731-1 1.160 29.46 4H2444-1 0.205 5.21
7931-4E1865-1 0.475 12.06 7931-4E2444-1 0.205 5.21
4H1865-2 0.945 24.00 4H2448-1 0.980 24.89
7931-4E1865-2 0.945 24.00 7931-4E2448-1 0.980 24.89
4H1924-1 0.295 7.49 7931-4E2459 0.285 7.23
7931-4E1924-1 0.295 7.49 4H2459-2 0.295 7.49
4H1924-3 0.295 7.49 7931-4E2459-2 0.295 7.49
7931-4E1924-3 0.295 7.49 7931-4E2468 0.310 7.87
7931-4E1926-1 0.235 5.96 4H2511 0.320 8.13
7931-4E1933-1 0.480 12.19 7931-4E2511 0.320 8.13
7931-4E1933-4 0.480 12.19 4H2551-1 0.200 5.08
7931-4E1933-6 0.945 24.00 7931-4E2551-1 0.200 5.08
4H1933-7 0.945 24.00 7931-4E2624-1 0.187 4.74
7931-4E1933-7 0.945 24.00 4H2661-1 0.275 6.98
7931-4E1948-1 0.315 8.00 7931-4E2661-1 0.275 6.98
7931-4E1964-1 0.480 12.19 7931-4E2661-2 0.275 6.98
4H1964-2 0.945 24.00 7931-4E2661-3 0.275 6.98
7931-4E1964-2 0.945 24.00 4H2661-4 0.275 6.98
4H1964-3 0.945 24.00 7931-4E2661-4 0.275 6.98
7931-4E1964-3 0.975 24.76 4H2662-1 0.275 6.98
7931-4E2662-1 0.275 6.98

Slip Ring Minimum Dimension

Table 6-1

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 PROPELLER ICE PROTECTION SYSTEM
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"X" Dimension "X" Dimension

Refer to Figure 6-1 Refer to Figure 6-1
Part Number Inches mm Part Number Inches mm
4H2674-1 0.275 6.98 NOTE: 4E2811-( ) slip rings are integral to the
7931-4E2674-1 0.275 6.98 composite bulkhead D-5313-( ). Machining
is permitted up to but not including composite
4H2674-2 0.300 7.62 materials. Refer to Figure 6-2.
7931-4E2674-2 0.300 7.62
4H2714-1 0.328 8.33
7931-4E2714-1 0.328 8.33
7931-4E2761-2 0.285 7.23
7931-4E2811-1 See Note
4H2811-2 See Note
7931-4E2811-2 See Note
4H2863 0.714 18.13
7931-4E2863 0.714 18.13
7931-4E2955-1 0.480 12.19
4H3000-1 0.490 12.44
7931-4E3000-1 0.490 12.44
4H3008-1 0.610 15.49
7931-4E3008-1 0.610 15.49
4H3060-1 0.714 18.13
7931-4E3060-1 0.714 18.13
4H3062-1 0.610 15.49
7931-4E3062-1 0.610 15.49
4H3094-1 0.480 12.19
7931-4E3094-1 0.480 12.19
4H3099-1 0.187 4.74
7931-4E3099-1 0.187 4.74
7931-4E3236-1 0.305 7.74
7931-4E3236-2 0.320 8.12
4H3422-1 0.260 6.60
7931-4E3422-1 0.260 6.60
4H4015-1 0.480 12.19
7931-4E4015-1 0.480 12.19
4H4069-1 0.500 12.70
7931-4E4069-1 0.500 12.70
101896 1.420
104249 0.735

Slip Ring Minimum Dimension

Table 6-1 (Continued)

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Slip Ring
Assembly Copper Rings
Aluminum
Holder

X
Mounting
Surface

Potting Compound

De-ice Slip Ring Minimum Dimension except 4E2811-( )

Figure 6-1

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Slip Ring
Assembly Copper Rings
Aluminum
Holder

Y
X

Mounting
Surface

Potting Compound

NOTE: Machining to the surface of the aluminum holder is permitted.

De-ice Slip Ring Minimum Dimension for 4E2811-( )

Figure 6-2

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COMPONENT MAINTENANCE MANUAL 181

(3) Using a dial indicator, measure the run-out of the inside diameter of the
aluminum holder of the slip ring assembly (1140) mounting surface. The holder
run-out reading must not exceed 0.0020 inch (0.0508 mm) over 360 degrees of
rotation.

CAUTION: WHEN MACHINING, DO NOT PERMIT THE TEMPERATURE OF

THE SLIP RINGS TO EXCEED 200° F (93°C).
(4) Set the rotation speed of the lathe at 600-900 RPM. The feed rate should not
exceed 0.005 - 0.008 inch (0.13 - 0.20 mm) per revolution.

CAUTION: DO NOT MACHINE THE OUTER EDGE OF A SLIP RING HOLDER

THAT HAS SYNCHROPHASER TARGETS.
(5) A diamond edge tool with 0.0156 - 0.0313 inch (0.396 - 0.795 mm) radius is
recommended. Alternately, a carbide insert tool with a TIN (Titanium nitride)
coated insert with a 0.0156 - 0.0313 inch (0.396 - 0.795 mm) radius may be
used.

CAUTION 1: EXCESSIVE HEAT BUILD-UP IN THE COPPER SLIP RINGS

CAN RESULT IN DEBONDING OF THE RING FROM THE EPOXY
POTTING. A CONTINUOUS APPLICATION OF KEROSENE
OR TAPMATIC DUAL ACTION PLUS #2 FLUID IS STRONGLY
RECOMMENDED TO AID IN CUTTING, TO PREVENT TOOL
CHATTER, AND REDUCE HEAT BUILD-UP. DO NOT USE
CUTTING FLUIDS OR COOLANTS OTHER THAN KEROSENE OR
TAPMATIC DUAL ACTION PLUS #2 FLUID, AS THEY MAY REACT
WITH THE COPPER SLIP RINGS, CAUSING DISCOLORATION
AND/OR LEAVING A CONTAMINATING RESIDUE. IF KEROSENE
OR TAPMATIC DUAL ACTION PLUS #2 FLUID IS NOT AVAILABLE,
MACHINE THE SLIP RING DRY.

CAUTION 2: DO NOT MACHINE THE COPPER SLIP RINGS, INSULATING

COMPOUND, OR SLIP RING HOLDER EDGES BELOW THE
MINIMUM "X" DIMENSION SPECIFIED IN TABLE 6-1.

CAUTION 3: NO UNDERCUT OF THE INSULATING COMPOUND BETWEEN

COPPER SLIP RINGS IS REQUIRED. THE HEIGHT OF THE
INSULATING COMPOUND MAY NOT EXCEED THE HEIGHT OF
THE COPPER SLIP RINGS.
(6) Make a light cut at a depth of no greater than 0.002 - 0.004 inch (0.05 - 0.10
mm) per pass at the specified feed rate and RPM. Cut no deeper than
necessary to remove surface damage. The copper ring surface and slip ring
holder must be cut as shown in Figure 6-1.
(7) The final surface finish must be 32 micro inches or better.

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(8) The surface of the copper rings and slip ring holder edges must be parallel to
the mounting surface within 0.005 inch (0.12 mm) over 360 degrees of rotation.
Run-out of the contact surfaces must be within 0.002 inch (0.05 mm) over a 4.0
inch (101 mm) arc.
(9) Use abrasive pad CM47 and deburr the edges and surfaces as necessary.
(10) Using approved solvent CM128 or CM106, thoroughly clean the copper rings.

CAUTION: COPPER RING SURFACES MUST BE FREE OF ANY CHEMICAL

CONVERSION COATING.
(11) Apply a chemical conversion coating to any exposed aluminum surfaces on
the slip ring holder in accordance with the Chromic Acid Anodizing chapter of
Hartzell Standard Practices Manual 202A (61-01-02).
(12) Measure the continuity after the resurfacing in accordance with the De-ice Slip
Ring Assembly Resistance Checks in this chapter.
B. De-ice Slip Ring Resurfacing for 4E2811-( )
(1) Determine minimum dimension. Refer to Figure 6-2.
(a) Measure the copper ring height "X".
(b) Measure the depth of the wear groove, "Y".
(c) If "Y" is equal or greater than "X", replace the slip ring assembly.
(d) If "Y" is less than "X", resurface the copper rings in accordance with the
Paragraph 2.A.
C. De-ice Slip Ring Assembly Resistance Checks

WARNING: CM128 AND CM106 ARE FLAMMABLE AND TOXIC TO THE SKIN,
EYES, AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION
ARE REQUIRED. AVOID PROLONGED CONTACT. USE IN A WELL
VENTILATED AREA.
(1) Using CM128 or CM106, thoroughly clean the copper rings.
(2) Set the micro-ohmmeter TE355 on an appropriate scale to measure 0.20 ohms.
Refer to the manufacturer’s instructions for zeroing and meter setup.
(3) Measure the resistance from each copper slip ring and to the aluminum holder.
Repeat for each slip ring in the assembly.
(4) Measure the resistance from each copper slip ring and the applicable ring
terminal. Repeat for each slip ring in the assembly.

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 PROPELLER ICE PROTECTION SYSTEM
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(5) Resistance must measure < 0.20 ohms open circuit between the copper ring
and at least one bonding area.
(6) If the slip ring resistance check is not within limits, replace the slip ring
assembly.

WARNING: THE FOLLOWING TEST REQUIRES THE USE OF A MEGOHM

METER UTILIZING HIGH VOLTAGE POTENTIAL. USE EXTREME
CAUTION AND FOLLOW MANUFACTURERS RECOMMENDED
SAFETY PROCEDURES. TESTING MUST BE PERFORMED
BY QUALIFIED PERSONNEL FAMILIAR WITH THE USE OF
ELECTRICAL TEST EQUIPMENT.
(7) Put the assembly on a non-conductive surface.
(8) Using a Megohm meter TE354, measure the insulation resistance by
measuring between each of the copper rings and the slip ring mounting
surface.
(9) Also measure the insulation resistance ring to ring.
(10) Apply 500 VDC. The resistance must be a minimum of 5 megohms after
30 seconds.
(11) If this check is not within limits, replace with a serviceable part.
D. Slip Ring Lead Wire Replacement
(1) There is a frayed or broken wire.
(a) Repair or replace the wire with a wire of equivalent length, gauge, and
quality.
(2) There is a wire broken at the stud.
(a) Put the assembly ring side down on a metal surface.

CAUTION: THE TEMPERATURE OF THE ASSEMBLY SHOULD NOT

RISE ABOVE 200°F (93°C) ANYWHERE EXCEPT AT THE
STUD. AVOID EXCESSIVE HEATING OF THE ASSEMBLY
OR THE STUDS WHEN REPAIRS ARE PERFORMED. USE A
HIGH WATTAGE SOLDERING GUN AND WORK AS QUICKLY
AS POSSIBLE.
(b) Using a high amperage soldering iron, heat the stud enough to melt the
solder to remove the broken wire.
(c) Remove the broken wire and solder from the stud.
(d) Using core solder CM195-2, solder a new wire of equivalent length,
gauge, and quality in place.
(e) Using solvent CM106 or CM128, clean area around the stud and the stud.
(f) Replace the shrink tubing and terminal ends with suitable type.

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 PROPELLER ICE PROTECTION SYSTEM
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Step 1
Form the Replacement
Brush Leadwire

2380

Step 2
Thread the Leadwire
through the Exit Hole

Step 3
Secure the Brush with
a Rubber Band

Bushing (2310)
Terminal End (2320)
Washer (2340)
Step 4
Attach the Terminal and
Leadwire to Module

Tubing (2330) Screw (2350)

Marker (2360)

Installation of New Brush in Module

Figure 6-3

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 PROPELLER ICE PROTECTION SYSTEM
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(g) Using an ohmmeter, measure the continuity after the wire replacement in
accordance with the De-ice Slip Ring Assembly Resistance Checks in this
chapter.
E. Brush Replacement

CAUTION: MAKE NOTE OF THE BRUSH WIRE MARKER. THE WIRE

MARKER WILL BE A, B, OR C.
(1) Make a record of the brush identification.
(2) Remove and keep the screw (2350), washers (2340), and spacers (2310), if
applicable, attaching the ring terminal to the brush module. Refer to Figure 6-3.
(3) Remove and discard the ring terminal (2320) from the brush leadwire.
(4) Remove and discard the brush (2380) and tubing (2330) through the slot in the
module.
(5) Inspect the brush slot for uneven wear and replace if there is uneven wear has
occurred.
(6) Inspect the inside of the brush module assembly for unwanted material.
Remove any unwanted material.

WARNING: THE BRUSH MODULE ASSEMBLY IS BONDED TOGETHER. DO

NOT SEPARATE THE BASE FROM THE LID.
(7) Using cleaning solvent CM118, CM23 or equivalent and a soft bristle brush,
clean the inside and outside of the brush module assembly to remove carbon
deposits, as required.
(8) Install new insulation tubing (2330) over the leadwire of the new brush (2380)
so that the end of the tubing almost contacts the brush.

NOTE: Use cleaning solvent CM23, CM118, or equivalent, soak the tubing
(2330) in solvent until pliable to ease installation. Install tubing
(2330) over the brush lead (2380).
(9) Slightly bend the brush leadwire into an arc as shown in Figure 6-3.
(10) Insert the brush and leadwire into the brush slot of the brush module assembly,
until the leadwire comes out of the leadwire hole as shown in Figure 6-3.
(11) Compress the brush and pull the maximum amount of the leadwire out of the
hole in the brush module assembly.
(12) Secure the compressed brush (2380) in the brush module assembly with a
rubber band or equivalent as shown in Figure 6-3.
(13) Slide the insulation tubing (2330) to within 0.187 inch (4.749 mm) of the end of
the leadwire.

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 PROPELLER ICE PROTECTION SYSTEM
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Nut (2080)
Washer (2085)
Washer (2075)
Brush Module "A" ( 2020)
Spacer (2090)
Brush Module "B" (2030)
Spacer (2090)
Brush Module "C" (2040)
Spacer (2095)

Screw (2070)

Standard Stacking
Configuration

Alternate Stacking
Configuration

Brush Module Assembly Stacking

Figure 6-4

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 PROPELLER ICE PROTECTION SYSTEM
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(14) Install a new ring terminal (2320) so that the end of the insulation tubing (2330)
is inside the jacket of the ring terminal and no bare leadwire is exposed.
(15) Using crimping tool AMP 47387 or equivalent, crimp the ring terminal (2320) in
place.
(16) Replace the screw (2350), washer (2340), and spacer(s) (2310).
(17) Remove the rubber band and carefully pull the brush (2370 or 2380) until all
slack in the leadwire is encased in the brush module assembly. Compress and
release the brush to make sure that it does not bind or hang up inside the brush
module assembly.
F. Brush Module Replacement
(1) Remove the modular brush block assembly from the aircraft in accordance with
the TC or STC holder's ICA.
(2) Remove the nuts (2080) and washers (2075, 2085) that secure the brush
module assemblies together. Keep the nuts (2080) and discard the washers
(2075, 2085).
(3) Remove and keep the assembly screws (2070) and separate the brush module
assemblies (2020, 2030, 2040) and spacers (2090, 2095). Keep the spacers
(2090, 2095) and serviceable brush module assemblies (2020, 2030, 2040).
(4) Replace the worn brush module assembly (2020, 2030, 2040) with the
appropriate replacement brush module assembly.
(a) The part number of each brush module assembly is etched on the lid.
(b) Replace the brush module assembly with the appropriate part number in
accordance with the Hartzell Propeller Ice Protection System Manual 180
(30-61-80) or the universal replacement brush module assembly Goodrich
P/N 3E2011-10, appropriately configured.
(c) A brush worn below minimum specifications may be replaced in
accordance with the instructions in this chapter.
(5) Assemble the brush module assemblies (2020, 2030, 2040) and spacers (2090,
2095) in accordance with the Hartzell Propeller Ice Protection System
Manual 180 (30-61-80).
(a) If there is interference between the adjacent ring terminals, adjust the
center brush module assembly as shown in Figure 6-4, Alternate Stacking
Arrangement.
(6) Install the flat washer (2075) between the module (2020, 2030, 2040) and the
lock washer (2085).
(7) Install the brush module assemblies (2020, 2030, 2040) and spacers (2090,
2095). Make sure the brush module assembly is squarely positioned and
tighten the screws (2070). Use care to not overtighten.

REPAIR/MODIFICATION 30-60-81 Page 6-14

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 PROPELLER ICE PROTECTION SYSTEM
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(8) Install the modular brush block assembly on the aircraft in accordance with the
TC or STC holder's ICA.
(9) Align the brushes to the slip ring assembly in accordance with the Assembly
chapter of this manual.
G. Slip Ring Interchangeability
(1) The Hartzell 4H1964-3 slip ring assembly and 4E1964-4 slip ring assembly are
drilled with one hole for installation of a synchrophaser target.
(2) The Hartzell 4H1964-3 slip ring assembly has a synchrophaser target installed
in the hole.
(3) The Hartzell 4H1964-4 slip ring assembly does not have a synchrophaser
target installed in the hole.
(4) A 2H1377 synchrophaser target may be installed in the hole on the 4H1964-4
slip ring assembly and the slip ring will become an 4H1964-3 slip ring assembly.
(5) Modification of a Hartzell 4H1964-3 slip ring assembly to a Hartzell 4H1964-4
slip ring assembly.
(a) Remove the 2H1377 synchrophaser target.
(b) Re-identify the slip ring assembly as an 4H1964-4 slip ring assembly in
accordance with Hartzell Standard Practices Manual 202A (61-01-02).
(6) Modification of a Hartzell 4H1964-4 slip ring assembly to a Hartzell 4H1964-3
slip ring assembly.
(a) Install an 2H1377 synchrophaser target as required in the hole on the
4H1964-4 slip ring assembly.
1 Apply sealant CM74 on the threads of the 2H1377 synchrophaser
target.
2 Install the 2H1377 synchrophaser target in the slip ring assembly.
The 2H1377 synchrophaser target must sit firmly against the slip ring
assembly after installation.
3 Torque the synchrophaser target 2 - 3 in-Lbs. (0.23 - 0.34 N•m).
4 Permit sealant CM74 to dry.
(b) Re-identify the slip ring assembly as an 4H1964-3 slip ring assembly in
accordance with Hartzell Standard Practices Manual 202A (61-01-02).

REPAIR/MODIFICATION 30-60-81 Page 6-15

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 PROPELLER ICE PROTECTION SYSTEM
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H. 4H2422 Slip Ring Mounting Screw (1141) Replacement

(1) As required, remove the slip ring mounting screw (1141).
(2) Using an approved solvent (CM11, CM21, CM41, or CM106), thoroughly clean
the threads and external surface of the slip ring assembly (1140) to remove
retaining compound (CM 74).
(3) Apply retaining compound (CM 74) to the threads of the slip ring assembly
(1140).
(4) Install the slip ring mounting screws (1141), as required.
(5) Torque the slip ring mounting screw (1141) 3 - 5 ft. lbs. (4.06 - 6.77 N•m).
(6) Allow to cure a minimum of eight hours before propeller installation.
I. Alternate Configuration For De-ice Kit 7931-65-025-1 With Spinner Bulkhead P/N
D-3437-1(P)
(1) The D-3437-1(P) spinner bulkhead incorporates B-7333-120 Rivnuts and
B-3893-12H screws to attach the 1H1150-2 or the 7931-1E1150-2 terminal
strips (170) to the bulkhead.

CAUTION: MAKE SURE THE PROPELLER MOUNTING HARDWARE DOES

NOT INTERFERE WITH THE RIVNUTS AND SCREWS USED TO
ATTACH THE TERMINAL STRIP TO THE BULKHEAD.
(2) When installed on the aircraft, aircraft mounted hardware may interfere with the
rivnuts and screws. Damage may result to the rivnuts and screws.
(3) To correct the interference, the bulkhead may be reworked to remove the
rivnuts.
(4) Removal of the rivnuts requires alternate hardware to attach the terminal strip
(170) to the bulkhead.
(5) Alternate Configuration:
(a) Remove the rivnuts using standard maintenance practices.
(b) Refer to Figure 6-5 for installation.

REPAIR/MODIFICATION 30-60-81 Page 6-16

Rev. 2 Oct/09
 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

Configuration AT

190

200

170

Bulkhead

200

220*

* Torque until snug.

Alternate Configuration for De-ice Kit 7931-65-025-1

with Spinner Bulkhead P/N D-3437-1(P)
Figure 6-5

REPAIR/MODIFICATION 30-60-81 Page 6-17

Rev. 2 Oct/09
 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

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ASSEMBLY - CONTENTS

1. Ice Protection Assembly and Installation ............................................................7-3

A. General ..........................................................................................................7-3
B. De-ice Boot Installation..................................................................................7-3
C. Anti-icing Boot Installation .............................................................................7-3
D. Brush Alignment to Slip Ring .........................................................................7-3

LIST OF ILLUSTRATIONS

Brush Alignment to Slip Ring Assembly .....................................Figure 7-1 ............... 7-4

Brush Alignment Template .........................................................Figure 7-2 ............... 7-5

Page 7-1
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Page 7-2
ASSEMBLY 30-60-81 Jun/07
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COMPONENT MAINTENANCE MANUAL 181

1. Ice Protection Assembly and Installation

A. General
(1) Installation instructions and applicable illustrations are not available for all
ice protection kits. Refer to the Hartzell Propeller Ice Protection Manual 180
(30-61-80) for additional installation instructions and applicable illustrations.
Additional installation instructions and applicable illustrations will be provided
in this manual as they become available. Where installation instructions or an
applicable illustration does not exist in this manual or the Hartzell Propeller Ice
Protection Manual 180 (30-61-80), refer to the applicable TC or STC holder's
ICA for the installation configuration.
(2) Information provided in this chapter is for initial installation of an ice protection
system. The instructions provided may not be applicable for replacement
of components or installation of conversion kits. Installation instruction for
systems or components not supplied by Hartzell Propeller Inc. must be
obtained from the aircraft TC or STC holder's ICA.
(3) Ice protection system installation affects the weight and balance of the
propeller. Refer to the aircraft TC or STC holder's ICA for specific weight and
balance information or calculate before proceeding.
(4) General information about component modification/removal necessary to install
ice protection system components is provided. Refer to the Check chapter
or the Repair/Modification chapter of this manual, or the aircraft TC or STC
holder's ICA for specific details.
(5) Unless specified, hardware is tightened until snug. Refer to Table 8-1 for
specified torque requirements.
B. De-ice Boot Installation
(1) Install a de-ice boot in accordance with the Hartzell Propeller Electrical De-ice
Boot Removal and Installation Manual 182 (61-12-82).
C. Anti-icing Boot Installation
(1) Install an anti-icing boot in accordance with the Hartzell Propeller
Anti-icing Boot Removal and Installation Manual 183 (61-12-83).
D. Brush Alignment to Slip Ring
(1) Reconnect the aircraft wire harness, matching the A, B, C, terminals.
NOTE: Make sure that adjacent ring terminals do not touch.
(2) Install the assembly on the aircraft in accordance with the TC or STC holder's
ICA.
(3) Radial alignment of the modular brush assembly to the slip assembly (1140) is
important to de-ice system operation.

Page 7-3
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TI-18001
Brush rides off the
edge of the slip ring Lip forms on brush
Slip Ring Assembly from improper
Brush Assembly alignment

100 percent of brush face

surface must contact the
slip ring surface

Correct Radial Alignment Incorrect Radial Alignment

Slip Ring
Rotation

2 degrees

0.0625 +/- 0.0312 inch

Spring pressure (1.587 +/- 0.794 mm)
on brush
Brush Assembly
Correct Fore and Aft Alignment

Angle of brush Too great a distance

block assembly is between brush module
too great. and slip ring.

Incorrect Fore and Aft Alignment

Brush Alignment to Slip Ring Assembly

Figure 7-1

Page 7-4
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COMPONENT MAINTENANCE MANUAL 181

TI-18005

Min. 0.250 inch

(6.35 mm)

1.375 inch
0.0625 inch (34.925 mm)
(1.587 mm)

0.250 inch
(6.35 mm)

Use this area

as a handle

Brush Alignment Template

Figure 7-2

Page 7-5
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 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

(4) The full face surface of the brushes must contact the slip rings throughout 360
degrees of slip ring rotation.
(5) Angular fore and aft alignment prevents side loading and premature wear of
the brushes and brush modules. Figure 7-1 illustrates the correct and incorrect
alignment.
(6) To facilitate alignment a template can be devised. Refer to Figure 7-2. Only
the critical dimensions are shown. The portion of the template within the dotted
circle serves as a handle to grasp the template. This area can be fabricated to
the shape and dimensions desired for ease of use.
(7) Adjust the brush projection and angle by holding the brushes in the desired
location while tightening the self locking nut. Slotted holes are provided for this
purpose.
(8) The brush projection must be such that the distance between the brush block
and the slip ring is 0.0312 to 0.0937 inch (0.794 - 2.38 mm). See Figure 7-1.
NOTE: Brush assembly is not to be cocked.
(9) Face alignment of the brushes is accomplished by inserting shims between the
brush block and the bracket to obtain proper radial alignment.
(10) The shims are made of 0.003 inch (0.0762 mm) thick layers of metal laminated
together to obtain an overall thickness of approximately 0.020 inch
(0.508 mm). Individual layers of shim may be peeled off in order to obtain the
desired thickness.
NOTE: Shims may be manufactured locally, if desired.

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FITS AND CLEARANCES - CONTENTS

1. Torque Values .....................................................................................................8-3

LIST OF ILLUSTRATIONS
Determining Torque Value
of a Standard Torque Wrench with Adaptor ....................... Figure 8-1................8-3

LIST OF TABLES
Torque Values ........................................................................ Table 8-1 .................8-4

FITS AND CLEARANCES 30-60-81 Page 8-1

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 PROPELLER ICE PROTECTION SYSTEM
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1. Torque Values
A. 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. 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.
B. Accurate wrenches and professional procedures will result in precision
tensioning.
C. When an adaptor is used with a torque wrench, use the equation in Figure 8-1 to
determine the torque value.

APS212

Torquing Adaptor
Standard Torque Wrench

1.00 foot 0.50 foot

(304.8 mm) (152.4 mm)

(actual torque required) x (torque wrench length) torque wrench reading

= to achieve required
(torque wrench length) + (length of adaptor)
actual torque

EXAMPLE:
reading on torque
100 Ft-Lb (136 N•m) x 1 ft (304.8 mm) wrench with 6-inch
= 66.7 Ft-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 AND CLEARANCES 30-60-81 Page 8-3

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 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

CAUTION: TORQUE VALUES ARE BASED ON NON-LUBRICATED THREADS,

UNLESS OTHERWISE STATED IN TABLE 8-1.
NOTE: Torque tolerance is + 10 percent unless otherwise noted. Refer to the
assembly chapter of this manual when wet torque is designated.

NOTE: Where applicable, torque value includes run on torque of self locking
fasteners.
Item Part Torque Torque Torque
No. Number Description Ft-Lb In-Lb N•m

Refer to the appropriate propeller overhaul

manual for torque values for slip ring
attaching bolts.

Torque Values
Table 8-1

FITS AND CLEARANCES 30-60-81 Page 8-4

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SPECIAL TOOLING, FIXTURES, AND EQUIPMENT - CONTENTS

1. Minimum Facility and Tooling Requirements ......................................................9-3
A. Tooling ...........................................................................................................9-3
B. Facilities ........................................................................................................9-3
2. Special Tools.......................................................................................................9-3
A. Special Tools .................................................................................................9-3
B. Listings ..........................................................................................................9-3

30-60-81
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1. Minimum Facility and Tooling Requirements

A. Tooling
Repair stations approved to repair Hartzell ice protection system components are
expected to possess appropriate fixtures and tools inspection and rework. Except as
specifically required in this manual, locally fabricated tooling is acceptable for most
repair and inspection operations.
B. Facilities
(1) Repair of ice protection system components has 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 must be segregated to prevent contamination. Separate areas
should be designated for cleaning, inspection, and assembly.

2. Special Tools

NOTE: It is the responsibility of the repair station to determine the special tooling
required.
A. Special Tools
Hartzell Tool and Equipment Manual 165A (61-00-65) 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 Hartzell Tool and Equipment Manual 165A (61-00-65)
provides information about what is included in the listings and how to quickly locate
tools.

30-60-81
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COMPONENT MAINTENANCE MANUAL 181

ILLUSTRATED PARTS LIST - CONTENTS

Refer to the Hartzell Propeller Ice Protection System Manual 180 (30-61-80) for an Illus-
trated Parts List.

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 PROPELLER ICE PROTECTION SYSTEM
COMPONENT MAINTENANCE MANUAL 181

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ILLUSTRATED PARTS LIST 30-60-81 Jun/07