Manual No.

401
61-10-01
Revision 4
January 2019

2A1 and 3A1 Series

Overhaul and Maintenance Manual

"Bantam" Models with Composite Blade

2A1-( )( )( )
3A1-( )( )( )

Hartzell Propeller Inc.

One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.
Phone: 937.778.4200
Fax: 937.778.4215
 PROPELLER MAINTENANCE MANUAL
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© 2014, 2015, 2016, 2019 - Hartzell Propeller Inc. - All rights reserved

INSIDE COVER 61-10-01 Inside Cover

Rev. 4 Jan/19
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REVISION 4 HIGHLIGHTS
Revision 4, dated January 2019, incorporates the following:

Front matter (Cover, Revision Highlights, etc.), has been revised to match this revision.

Minor language/format changes and renumbering, if applicable are marked with a revision
bar, but are not listed below.

All Hartzell Propeller Inc. de-ice and anti-icing system information is now found in
Hartzell Ice Protection System Manual 180 (30-61-80). Revised manual references
where applicable.
• INTRODUCTION
• Revised the section, "General"
• Revised the section, "Hartzell Propeller Inc. Publications"
• Revised the section, "Definitions"
• Revised the section, "Abbreviations"
• Added the section, "Contact Information"
• ASSEMBLY
• Revised the section, "General"
• Revised the section, "Bantam Assembly Procedures"
• Revised the section, "Two Blade Bantam Propeller Fork (710), Pitch Change
Rod (240), and Pitch Change Block Unit (500) Installation"
• Revised the section, "Hub Cylinder-Side Installation"
• Revised Table 7-2 and title, "Two Blade Propeller P/N 104468-( ) Stainless Steel
Bumper and P/N 105004-( ) Stainless Steel Shim Sizes"
• Added Table 7-3, "Two Blade Propeller Bumper Plus Shim Relative Sizes"
• Revised the section, "Propeller Balance"

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REVISION HIGHLIGHTS Rev. 4 Jan/19
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REVISION HIGHLIGHTS

1. Introduction

A. General
(1) This is a list of current revisions that have been issued against this manual.
Please compare to the RECORD OF REVISIONS page to make sure that all
revisions have been added to the manual.

B. Components
(1) Revision No. indicates the revisions incorporated in this manual.
(2) Issue Date is the date of revision.
(3) Comments indicates the level of the revision.
(a) New Issue is a new manual distribution. The manual is distributed in its
entirety. All the revision dates are the same and no change bars are used.
(b) Reissue is a revision to 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.
(c) Major Revision is a revision to an existing manual that includes major
content or minor format changes over a large portion of the manual. The
manual is distributed in its entirety. All the revision dates are the same, but
change bars are used to indicate the changes incorporated in the latest
revision of the manual.
(d)  Minor Revision is a revision to an existing manual that includes minor
content changes to the manual. Only the revised pages of the manual are
distributed. Each page retains the date and the change bars associated
with the last revision to that page.

Revision No. Issue Date Comments

Original Feb/14 New Issue

Revision 1 May/14 Minor Revision
Revision 2 Apr/15 Major Revision
Revision 3 Sep/16 Minor Revision
Revision 4 Jan/19 Minor Revision

REVISION HIGHLIGHTS 61-10-01 Page 2

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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

Original Feb/14 Feb/14 HPI

1 May/14 May/14 HPI

2 Apr/15 Apr/15 HPI

3 Sep/16 Sep/16 HPI

4 Jan/19 Jan/19 HPI

RECORD OF REVISIONS 61-10-01 Page 1

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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

RECORD OF REVISIONS 61-10-01 Page 2

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RECORD OF TEMPORARY REVISIONS

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

RECORD OF TEMPORARY REVISIONS 61-10-01 Page 1

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RECORD OF TEMPORARY REVISIONS

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

RECORD OF TEMPORARY REVISIONS 61-10-01 Page 2

Rev. 2 Apr/15
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SERVICE DOCUMENT LIST

CAUTION 1: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM

ALL INSPECTIONS OR WORK IN ACCORDANCE WITH THE MOST
RECENT REVISION OF THE SERVICE DOCUMENT. INFORMATION
CONTAINED IN A SERVICE DOCUMENT MAY BE SIGNIFICANTLY
CHANGED FROM EARLIER REVISIONS. FAILURE TO COMPLY WITH
INFORMATION CONTAINED IN A SERVICE DOCUMENT OR THE USE
OF OBSOLETE INFORMATION MAY CREATE AN UNSAFE CONDITION
THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR
SUBSTANTIAL PROPERTY DAMAGE.

CAUTION 2: THE INFORMATION FOR THE DOCUMENTS LISTED INDICATES THE

REVISION LEVEL AND DATE AT THE TIME THAT THE DOCUMENT
WAS INITIALLY INCORPORATED INTO THIS MANUAL. INFORMATION
CONTAINED IN A SERVICE DOCUMENT MAY BE SIGNIFICANTLY
CHANGED FROM EARLIER REVISIONS. REFER TO THE APPLICABLE
SERVICE DOCUMENT INDEX FOR THE MOST RECENT REVISION
LEVEL OF THE SERVICE DOCUMENT.

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

SERVICE DOCUMENT LIST 61-10-01 Page 2

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AIRWORTHINESS LIMITATIONS

1. Certain component parts, as well as the entire propeller, may have specific life limits
established by the FAA. Such limits require replacement of items after a specific number
of hours of use.

2. Airworthiness limitations information:

A. For single acting propellers, refer to the applicable Hartzell Propeller Inc. owner's
manual.
(1) For a list of owner's manuals, refer to the section "Required Hartzell Propeller
Inc. Publications" in the Introduction chapter of this manual.

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LIST OF EFFECTIVE PAGES

Chapter Page Rev. Level Date

Cover Cover and Inside Cover Rev. 4 Jan/19

Revision Highlights 1 and 2 Rev. 4 Jan/19
Record of Revisions 1 and 2 Rev. 2 Apr/15
Record of Temporary Revisions 1 and 2 Rev. 2 Apr/15
Service Document List 1 and 2 Rev. 2 Apr/15
Airworthiness Limitations 1 and 2 Rev. 2 Apr/15
List of Effective Pages 1 and 2 Rev. 4 Jan/19
Table of Contents 1 and 2 Rev. 2 Apr/15
Introduction 1 thru 22 Rev. 4 Jan/19
Description and Operation 1 thru 4 Rev. 2 Apr/15
Testing and Fault Isolation 1-1 thru 1-6 Rev. 2 Apr/15
Automatic Test Requirements 2-1 and 2-2 Rev. 2 Apr/15
Disassembly 3-1 thru 3-3 Rev. 2 Apr/15
Disassembly 3-4 Rev. 4 Jan/19
Disassembly 3-5 thru 3-7 Rev. 2 Apr/15
Disassembly 3-8 and 3-9 Rev. 3 Sep/16
Disassembly 3-10 and 3-11 Rev. 2 Apr/15
Disassembly 3-12 Rev. 3 Sep/16
Cleaning 4-1 thru 4-4 Rev. 2 Apr/15
Check 5-1 Rev. 4 Jan/19
Check 5-2 thru 5-4 Rev. 2 Apr/15
Check 5-5 Rev. 4 Jan/19
Check 5-6 thru 5-8 Rev. 2 Apr/15
Check 5-9 Rev. 3 Sep/16
Check 5-10 thru 5-12 Rev. 2 Apr/15
Check 5-13 Rev. 3 Sep/16
Check 5-14 thru 5-24 Rev. 2 Apr/15
Check 5-25 and 5-26 Rev. 3 Sep/16
Repair 6-1 thru 6-4 Rev. 2 Apr/15

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LIST OF EFFECTIVE PAGES

Chapter Page Rev. Level Date

Assembly 7-1 Rev. 2 Apr/15

Assembly 7-2 Rev. 4 Jan/19
Assembly 7-3 Rev. 2 Apr/15
Assembly 7-4 and 7-5 Rev. 4 Jan/19
Assembly 7-6 thru 7-14 Rev. 2 Apr/15
Assembly 7-15 Rev. 4 Jan/19
Assembly 7-16 thru 7-23 Rev. 2 Apr/15
Assembly 7-24 Rev. 4 Jan/19
Assembly 7-24.1 and 7-24.2 Rev. 4 Jan/19
Assembly 7-25 thru 7-27 Rev. 4 Jan/19
Assembly 7-28 Rev. 2 Apr/15
Assembly 7-29 Rev. 4 Jan/19
Assembly 7-30 Rev. 2 Apr/15
Assembly 7-31 Rev. 4 Jan/19
Assembly 7-32 Rev. 2 Apr/15
Assembly 7-33 Rev. 4 Jan/19
Assembly 7-34 thru 7-40 Rev. 2 Apr/15
Fits and Clearances 8-1 thru 8-8 Rev. 2 Apr/15
Special Tools, Fixtures and Equipment 9-1 and 9-6 Rev. 2 Apr/15
Illustrated Parts List 10-1 and 10-2 Rev. 4 Jan/19
Illustrated Parts List 10-3 Rev. 2 Apr/15
Illustrated Parts List 10-4 Rev. 4 Jan/19
Illustrated Parts List 10-5 thru 10-16 Rev. 2 Apr/15
Illustrated Parts List 10-17 thru 10-19 Rev. 3 Sep/16
Illustrated Parts List 10-20 Rev. 2 Apr/15
Illustrated Parts List 10-21 Rev. 3 Sep/16
Illustrated Parts List 10-22 Rev. 2 Apr/15
Illustrated Parts List 10-23 and 10-24 Rev. 3 Sep/16

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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............................................................................................................................... 6-1
ASSEMBLY......................................................................................................................... 7-1
FITS AND CLEARANCES................................................................................................... 8-1
SPECIAL TOOLING, 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.................................................................................................. 3
A. Hartzell Propeller Inc. Publications........................................................................ 3
B. References to Hartzell Propeller Inc. Publications................................................. 5
C. Vendor Publications............................................................................................... 5
3. Personnel Requirements............................................................................................. 6
A. Inspection, Repair, and Overhaul........................................................................... 6
4. Safe Handling of Paints and Chemicals...................................................................... 6
5. Calendar Limits and Long Term Storage..................................................................... 7
A. Calendar Limits...................................................................................................... 7
B. Long Term Storage................................................................................................. 7
6. Component Life and Service....................................................................................... 7
A. Overhaul................................................................................................................. 7
B. Damage.................................................................................................................. 8
C. Repair..................................................................................................................... 9
D. Component Life...................................................................................................... 9
E. Propeller Critical Parts......................................................................................... 10
7. Definitions...................................................................................................................11
8. Abbreviations............................................................................................................. 20
9. Contact Information................................................................................................... 22
A. Hartzell Propeller Inc. Product Support Department............................................ 22
B. Hartzell Propeller Inc. Technical Publications Department................................... 22

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1. Statement of Purpose

A. General
(1) This manual has been reviewed and accepted by the FAA. Additionally, this
manual contains data that has been approved in a manner acceptable to the
FAA Administrator.
(2) This manual provides maintenance and overhaul procedures for Bantam
model compact constant speed propellers manufactured by Hartzell Propeller
Inc.
(3) This manual is to be used in propeller repair stations by personnel who are
trained and experienced with Hartzell Propeller Inc. products.
(a) This manual does not provide complete information for an inexperienced
technician to attempt propeller overhaul without supervision.
(4) This manual is intended to be the primary source of maintenance and
overhaul information for Bantam propellers.
(a) The propeller models addressed in this manual may be Type Certificated
by the FAA, or may be experimental. Experimental parts must not be
installed on a type certified propeller. Always use the current illustrated
parts list for the assembly of any propeller. Always use the aircraft Type
Certificate (TC) or Supplemental Type Certificates (STC) to determine
installation eligibility of any propeller. If installation eligibility is not
identifiable, an additional installation approval, such as FAA form 337
field approval or Supplemental Type Certificate may be required. If in
doubt, contact Hartzell Propeller Inc. Product Support.
(5) This manual makes reference to other Hartzell Propeller Inc. manuals that
provide important details for procedures such as anodizing, and penetrant
inspection.
(6) Where possible, this manual is written in the format specified by
ATA iSpec 2200.

2. Required Publications

A. Hartzell Propeller Inc. Publications

(1) In addition to this manual, one or more of the following publications are
required for information regarding specific recommendations and procedures
to maintain propeller assemblies that are included in this manual.
(2) Information published in Service Bulletins, Service Letters, Service
Advisories, and Service Instructions may supersede information published
in this manual. The reader must consult active Service Bulletins, Service
Letters, Service Advisories, and Service Instructions for information that may
have not yet been incorporated into the latest revision of this manual.

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Manual No. Available at

Hartzell Propeller Inc. Manual Title
(ATA No.) www.hartzellprop.com
n/a Yes Active Hartzell Propeller Inc. Service Bulletins,
Service Letters, Service Instructions, and
Service Advisories
Manual 127 Yes Hartzell Propeller Inc. Metal Spinner
(61-16-27) Maintenance Manual
Manual 135F Hartzell Propeller Inc. Composite Propeller
(61-13-35) Blade
Maintenance Manual
Manual 148 Hartzell Propeller Inc. Composite Spinner
(61-16-48) Maintenance Manual
Manual 159 Yes Hartzell Propeller Inc. Application Guide
(61-02-59)
Manual 165A Yes Hartzell Propeller Inc. Illustrated Tool and
(61-00-65) Equipment Manual
Manual 180 Yes Hartzell Propeller Inc. Propeller Ice Protection
(30-61-80) System Manual
Manual 202A Vol. 7, Yes Hartzell Propeller Inc. Standard Practices
(61-01-02) Manual, Volumes 1 through 11
Manual 411 Yes Hartzell Propeller Inc. Propeller Owner’s
(61-00-11) Manual and Logbook for Constant Speed,
Non-counterweighted ( )(A,B)1 Series
“Bantam” Propellers with Composite Blades
HC-SL-61-61Y Yes Propeller - Overhaul Periods and Service
Life Limits for Hartzell Propeller Inc. Aviation
Components - Propellers, Governors,
Accumulators, and Propeller Damper
Assemblies

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B. References to Hartzell Propeller Inc. Publications

(1) Item references throughout the text in this manual refer to item numbers in
the Illustrated Parts List chapter of this manual. The item numbers appear in
parentheses directly following the part name. Only the item base number will
appear in the text of the manual. Item base numbers and the alpha variants
of the base numbers will appear in the illustrated parts list. There are two
reasons for the use of alpha variants:
(a) A part may be superseded, replaced, or obsoleted by another part. For
example, the pitch change block unit (104950) that is item 500 was
superseded by the pitch change block unit (104950-1) that is item 500A.
(b) An Illustrated Parts List may contain multiple configurations. Effectivity
codes are used to distinguish different part numbers within the same
list. For example, one configuration may use a piston (104256) that is
item 210, yet another configuration uses a piston (104256-1) that is item
210A. Effectivity codes are very important in the determination of parts
in a given configuration.
(2) Special tooling may be required for procedures in this manual. For further
tooling information, refer to Hartzell Propeller Inc. Illustrated Tool and
Equipment Manual 165A (61-00-65).
(a) The reference numbers for tooling appear with the prefix “TE” directly
following the tool name to which they apply. For example, a template that
is reference number 133 will appear as: template TE133.
(3) Consumable materials are referenced in certain sections throughout
this manual. Specific approved materials are listed in the Consumable
Materials chapter of Hartzell Propeller Inc. Standard Practices Manual 202A
(61‑01‑02).
(a) The reference number for consumable materials appear with the prefix
“CM” directly following the material to which they apply. For example, an
adhesive that is reference number 16 will appear as: adhesive CM16. Only
those items specified may be used.

C. Vendor Publications
None.

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3. Personnel Requirements
A. Inspection, Repair, and Overhaul
(1) Compliance to the applicable regulatory requirements established by
the Federal Aviation Administration (FAA) or international equivalent,
is mandatory for anyone performing or accepting responsibility for any
inspection and/or repair and/or overhaul of any Hartzell Propeller Inc.
product.
(2) Personnel inspecting, repairing, and overhauling Hartzell Propeller Inc.
aluminum hub propellers must have adequate training and experience.
(3) Inspection and repair of propeller parts require a high degree of skill;
therefore, personnel with inspection and supervisory responsibility are
expected to have all of the following:
(a) An FAA Propeller Repairman's Certificate or international equivalent
(b) A minimum of 18 months practical experience with Hartzell Propeller
Inc. steel hub propeller overhaul
(4) Participation in Hartzell Propeller Inc. training classes is strongly
recommended.
4. Safe Handling of Paints and Chemicals
A. Always use caution when handling or being exposed to paints and/or chemicals
during propeller overhaul and maintenance procedures.
B. Before using paint or chemicals, always read the manufacturer’s label on the
container and follow specified instructions and procedures for storage, preparation,
mixing, and application.
C. Refer to the product’s Material Safety Data Sheet (MSDS) for detailed information
about physical properties, health, and physical hazards of any chemical.

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5. Calendar Limits and Long Term Storage

A. Calendar Limits
(1) The effects of exposure to the environment over a period of time create a
need for propeller overhaul regardless of flight time.
(2) A calendar limit between overhauls is specified in Hartzell Propeller Inc.
Service Letter HC-SL-61-61Y and in the propeller owner's manual.
(3) Experience has shown that special care, such as keeping an aircraft in a
hangar, is not sufficient to permit extension of the calendar limit.
(4) The start date for the calendar limit is when the propeller is first installed on
an engine.
(5) The calendar limit is not interrupted by subsequent removal and/or storage.
(6) The start date for the calendar limit must not be confused with the warranty
start date, that is with certain exceptions, the date of installation by the first
retail customer.
B. Long Term Storage
(1) Propellers that have been in storage have additional inspection requirements
before installation. Refer to the Packaging and Storage chapter of Hartzell
Propeller Inc. Standard Practices Manual 202A (61‑01‑02).

6. Component Life and Service

WARNING: CERTAIN PROPELLER COMPONENTS USED IN NON-AVIATION

APPLICATIONS ARE MARKED WITH DIFFERENT PART NUMBERS
TO DISTINGUISH THEM FROM COMPONENTS USED IN AVIATION
APPLICATIONS. DO NOT ALTER THE PART NUMBERS SHOWN
ON PARTS DESIGNATED FOR NON-AVIATION APPLICATIONS
OR OTHERWISE APPLY THOSE PARTS FOR USE ON AVIATION
APPLICATIONS.

A. Overhaul
(1) Overhaul is the periodic disassembly, cleaning, inspecting, repairing as
necessary, reassembling, and testing in accordance with approved
standards and technical data approved by Hartzell Propeller Inc.
(2) The overhaul interval is based on hours of service, i.e., flight time, or on
calendar time.
(a) At such specified periods, the propeller hub assembly and the blade
assemblies must be completely disassembled and inspected for cracks,
wear, corrosion, and other unusual or abnormal conditions.

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(b) Parts that are not replaced at overhaul must be inspected in accordance
with the Check chapter of this manual.
1 Parts that must be replaced at overhaul are identified by a "Y" in
the O/H column of the Illustrated Parts List chapter of this manual.

WARNING: DO NOT USE OBSOLETE OR OUTDATED INFORMATION.

PERFORM ALL INSPECTIONS OR WORK IN ACCORDANCE WITH
THE MOST RECENT REVISION OF THIS MANUAL. INFORMATION
CONTAINED IN THIS MANUAL MAY BE SIGNIFICANTLY
CHANGED FROM EARLIER REVISIONS. FAILURE TO
COMPLY WITH THIS MANUAL OR THE USE OF OBSOLETE
INFORMATION MAY CREATE AN UNSAFE CONDITION THAT
MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR
SUBSTANTIAL PROPERTY DAMAGE. FOR THE MOST RECENT
REVISION LEVEL OF THIS MANUAL, REFER TO THE HARTZELL
PROPELLER INC. WEBSITE AT WWW.HARTZELLPROP.COM.
(3) Overhaul must be completed in accordance with the latest revision of the
applicable component maintenance manual and other publications applicable
to, or referenced in, the component maintenance manual.
(4) The information in this manual supersedes data in all previously published
revisions of this manual.

B. Damage
(1) Airworthy Damage
(a) Airworthy damage is a specific condition to a propeller component
identified in the Check chapter 5 of this manual that does not affect the
safety or flight characteristics of the propeller and conforms to its type
design by meeting the condition inspection criteria limitations found in this
manual.
1 The maximum limits of airworthy damage are specified in the
Check chapter 5 of this manual.
a The Check chapter 5 in this manual specifies inspection
criteria and instructions for evaluating damage to determine
continued airworthiness.
(2) Unairworthy Damage
(a) Unairworthy damage is damage that exceeds the airworthy damage
limits as specified in the Check chapter 5 of this manual.
1 Unairworthy damage can affect the safety or flight characteristics of
the propeller and does not conform to its type design.
2 This condition deems the component unairworthy, requiring
appropriate corrective action to repair or remove it from service, as
applicable.

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C. Repair
(1) Minor Repair
(a) Minor repair is that which may be done safely in the field by a certified
aircraft mechanic.
(b) For information about repair criteria for composite blades, refer to
Hartzell Propeller Inc. Composite Propeller Blade Maintenance
Manual 135F (61-13-35).
(2) Major Repair
(a) Major repair is correction of damage that cannot be done by elementary
operations.
(b) Major repair work must be accepted by an individual that is certified by
the Federal Aviation Administration (FAA) or international equivalent.
1 Preferably the individual who accepts the work also holds a Factory
Training Certificate from Hartzell Propeller Inc.
2 The repair station must meet facility, tooling, and personnel
requirements and is required to participate in Hartzell Propeller Inc.
Sample Programs as defined in the Approved Facilities chapter of
Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

D. Component Life
(1) Certain components, or in some cases an entire propeller, may be life limited.
(a) It is a regulatory requirement that a record of the time since new be
maintained for all life limited parts.
(b) Refer to the Airworthiness Limitations chapter in the applicable Hartzell
Propeller Inc. Owner's Manual for a list of life limited components.
(2) 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.
(3) Both TSN and TSO are necessary for 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).
(4) When a component or assembly undergoes an overhaul, the TSO is returned
to zero hours.
(a) Time Since New (TSN) can never be returned to zero.
(b) Repair without overhaul does not affect TSO or TSN.

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(5) Time Since New (TSN) and Time Since Overhaul (TSO) records must be
maintained in the propeller logbook.
(6) Blades and hubs are sometimes replaced while in service or at overhaul.
(a) Maintaining separate TSN and TSO histories for a replacement hub or
blade is required.
(b) Other propeller components do not require time tracking unless
specified in Hartzell Propeller Inc. service publications.
(c) Hub replacement
1 If the hub is replaced, the replacement hub serial number must be
recorded (the entry signed and dated) in the propeller logbook.
2 The propeller will be identified with the serial number of the
replacement hub.

NOTE: Propeller assembly serial numbers are impression stamped

on the hub. For stamping information, refer to the Parts
Identification and Marking chapter of Hartzell Propeller Inc.
Standard Practices Manual 202A (61-01-02).
3 The TSN and TSO of the replacement hub must be recorded and
maintained in the propeller logbook.
4 The TSN and TSO of the remaining propeller components that are
required to be tracked as defined above, are not affected by the
hub replacement and must be maintained separately.

E. Propeller Critical Parts

(1) Procedures in this manual may involve Propeller Critical Parts (PCP).
(a) These procedures have been substantiated based on Engineering
analysis that expects this product will be operated and maintained
using the procedures and inspections provided in the Instructions for
Continued Airworthiness (ICA) for this product.
(b) Refer to the Illustrated Parts List chapter for the applicable propeller
model for the identification of Propeller Critical Parts.
(2) Numerous propeller system parts can produce an aircraft Major or Hazardous
effect, even though those parts may not be considered as Propeller Critical
Parts.
(a) The operating and maintenance procedures and inspections provided in
the ICA for this product are, therefore, expected to be accomplished for
all propeller system parts.

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7. Definitions
A basic understanding of the following terms will assist in maintaining and operating
Hartzell Propeller Inc. propeller systems.

Term ���������������������������������� Definition

Abrupt Transition ��������������� A physical difference in diameter in the pressure transition

zone of a blade shank caused by a sudden decrease in
rolling pressure during the rolling process

Alignment Bushing ������������ An alignment bushing is either a drill bushing or

manufactured steel bushing with a through bore of
0.753 ±0.001 inches (19.12 ±0.025 mm). This bushing is used
to control the concentricity of the face plate weldment shaft
to the right angle gear motor shaft during the assembly
process described in this manual.

Annealed ��������������������������� Softening of material caused by overexposure to heat

Aviation Certified ��������������� Intended for FAA or international equivalent type certificated
aircraft applications. A TC and PC number must be stamped
on the hub, and a PC number must be stamped on blades.

Aviation Experimental ������� Intended for aircraft/propeller applications not certified by

the FAA or international equivalent. Products marked with
an “X” at or near the end of the model number, part number,
or serial number are not certified by the FAA or international
equivalent and are not intended to use on certificated
aircraft.

Bantam
Composite Blades ������������� A composite blade that is used in Bantam series propellers

Beta Operation ������������������ Manual blade angle control in the beta range to select
positive blade angles for positive thrust, negative blade
angles for negative thrust, and zero blade angle for no thrust

Beta Range ����������������������� Blade angles between low pitch and maximum reverse blade
angle

Beta System ���������������������� Parts and/or equipment related to operation (manual control)
of propeller blade angle between low pitch blade angle and
full reverse blade angle

Blade Angle ����������������������� Measurement of blade airfoil location described as the angle
between the blade airfoil and the surface described by
propeller rotation

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Term ���������������������������������� Definition

Blade Pitch Axis ���������������� An imaginary reference line through the length of a blade
around which the blade rotates

Blade Station ��������������������� Refers to a location on an individual blade for blade

inspection purposes. It is a measurement from the blade
"zero" station to a location on a blade, used to apply blade
specification data in blade overhaul manuals
NOTE: Do not confuse blade station with reference blade
radius; they may not originate at the same location.

Blemish ����������������������������� An imperfection with visible attributes, but having no impact

on safety or utility

Brinelling ��������������������������� A depression caused by failure of the material in

compression

Bulge ��������������������������������� An outward curve or bend

Camber ����������������������������� The surface of the blade that is directed toward the front
of the aircraft. It is the low pressure, or suction, side of the
blade. The camber side is convex in shape over the entire
length of the blade.

Chord �������������������������������� A straight line between the leading and trailing edges of an
airfoil

Chord Line ������������������������ A straight line drawn between the leading and trailing edge
radii of the blade

Chordwise ������������������������� A direction that is generally from the leading edge to the
trailing edge of an airfoil

Co-bonded ������������������������ The act of bonding a composite laminate and simultaneously

curing it to some other prepared surface.

Cold Rolling ����������������������� Compressive rolling process for the retention area of single
shoulder blades which provides improved strength and
resistance to fatigue

Composite
Blade Traveler ������������������� A form that lists the applicable steps required for the
overhaul of a specific blade model

Composite Material ����������� Kevlar® (yellow) or graphite (black) fibers bound together
with or encapsulated within an epoxy resin

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Term ���������������������������������� Definition

Constant Force ����������������� A force which is always present in some degree when the
propeller is operating

Constant Speed ���������������� A propeller system which employs a governing device to

maintain a selected engine RPM

Corrosion (Aluminum) ������� The chemical or electrochemical attack by an acid or alkaline

that reacts with the protective oxide layer and results in
damage of the base aluminum. Part failure can occur from
corrosion due to loss of structural aluminum converted to
corrosion product, pitting, a rough etched surface finish, and
other strength reduction damage caused by corrosion.

Corrosion (Steel) ��������������� Typically, an electrochemical process that requires the

simultaneous presence of iron (component of steel),
moisture and oxygen. The iron is the reducing agent (gives
up electrons) while the oxygen is the oxidizing agent (gains
electrons). Iron or an iron alloy such as steel is oxidized
in the presence of moisture and oxygen to produce rust.
Corrosion is accelerated in the presence of salty water or
acid rain. Part failure can occur from corrosion due to loss
of structural steel converted to corrosion product, pitting,
a rough etched surface finish and other strength reduction
damage caused by corrosion.

Corrosion Product
(Aluminum)........................ A white or dull gray powdery material that has an increased
volume appearance (compared to non-corroded aluminum).
Corrosion product is not to be confused with damage left in
the base aluminum such as pits, worm holes, and etched
surface finish.

Corrosion Product
(Steel)................................When iron or an iron alloy such as steel corrode a corrosion
product known as rust is formed. Rust is an iron oxide which
is reddish in appearance and occupies approximately six
times the volume of the original material. Rust is flakey and
crumbly and has no structural integrity. Rust is permeable
to air and water, therefore the interior metallic iron (steel)
beneath a rust layer continues to corrode. Corrosion product
is not to be confused with damage left in the base steel such
as pits and etched surface finish.

Crack ��������������������������������� Irregularly shaped separation within a material, usually

visible as a narrow opening at the surface

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Term ���������������������������������� Definition

Debond ����������������������������� Separation of two materials that were originally bonded in

a separate operation

Defect �������������������������������� An imperfection that affects safety or utility

Delamination ��������������������� Internal separation of the layers of a composite material

Dent ���������������������������������� The permanent deflection of the cross section that is visible
on both sides with no visible change in cross sectional
thickness

Depression ������������������������ Surface area where the material has been compressed but
not removed

Distortion ��������������������������� Alteration of the original shape or size of a component

Dragging ��������������������������� A resistance to the roller rotation when moving on a spinning

blade. Dragging can cause blade surface damage.

Edge Alignment ����������������� Distance from the blade centerline to the leading edge of the
blade

Erosion ������������������������������ Gradual wearing away or deterioration caused by action of

the elements

Exposure ��������������������������� Leaving material open to action of the elements

Face ���������������������������������� The surface of the blade that is directed toward the rear of
the aircraft. The face side is the high pressure, or thrusting,
side of the blade. The blade airfoil sections are normally
cambered or curved such that the face side of the blade may
be flat or even concave in the midblade and tip region.

Face Alignment ����������������� Distance from the blade centerline to the highest point on the
face side perpendicular to the chord line.

Feathering ������������������������� The capability of blades to be rotated parallel to the relative

wind, thus reducing aerodynamic drag

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

Galling ������������������������������� To fret or wear away by friction

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Term ���������������������������������� Definition

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

Gouge ������������������������������� Surface area where material has been removed

Hazardous Propeller
Effect ��������������������������������� The hazardous propeller effects are defined in Title 14 CFR
section 35.15(g)(1).

Horizontal Balance ������������ Balance between the tip and the butt of the blade

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

Inboard ������������������������������ Toward the butt of the blade

Inboard Region ����������������� The inboard portion of the blade encompassing both the face
and camber sides of the blade

Inboard Trailing
Edge Region ��������������������� The inboard portion of the blade encompassing the trailing
edge

Intergranular Corrosion ����� Corrosion that attacks along the grain boundaries of metal
alloys

Jog ������������������������������������ A term used to describe movement up/down, left/right, or on/

off in short incremental motions

Laminate ��������������������������� To unite composite material by using a bonding material,

usually with pressure and heat

Legacy
Composite Blades ������������� Composite blades other than N-shank, Bantam, or Raptor

Lengthwise ������������������������ A direction that is generally parallel to the pitch axis

Loose Material ������������������ Material that is no longer fixed or fully attached

Low Pitch �������������������������� The lowest blade angle attainable by the governor for
constant speed operation

Major Propeller Effect �������� The major propeller effects are defined in Title 14 CFR
section 35.15(g)(2).

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Term ���������������������������������� Definition

Minor Deformation ������������ Deformed material not associated with a crack or missing
material less than 10 percent of the leading edge radius or
no more than 0.080 inch (2.03 mm) deep

Monocoque ����������������������� A type of construction in which the outer skin carries all or a
major part of the stresses

N-shank
Composite Blades ............. A composite blade that is used in lightweight turbine,
compact, and lightweight compact propellers

Nick ����������������������������������� Removal of paint and possibly a small amount of material

Non-Aviation Certified ������� Intended for non-aircraft application, such as Hovercraft or

Wing-In-Ground effect (WIG) applications. These products
are certificated by an authority other than FAA. The hub and
blades will be stamped with an identification different from,
but comparable to TC and PC.

Non-Aviation
Experimental ��������������������� Intended for non-aircraft application, such as Hovercraft or
Wing-In-Ground effect (WIG) applications. These products
are not certificated by any authority. There is no identification
stamp comparable to TC and PC on the hubs and blades.
Experimental parts are normally stamped with an “X” at or
near the end of the part number.

Onspeed ��������������������������� Condition in which the RPM selected by the pilot through
the propeller control/condition lever and the actual engine
(propeller) RPM are equal

Open Circuit ���������������������� Connection of high or infinite resistance between points in a

circuit which are normally lower

Outboard ��������������������������� Toward the tip of the blade

Outboard Region ��������������� The outboard portion of the blade encompassing both the
face and camber sides of the blade

Outboard Trailing
Edge Region ��������������������� The outboard portion of the blade encompassing the trailing
edge

Overhaul ���������������������������� The periodic disassembly, inspection, repair, refinish, and

reassembly of a propeller assembly

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Term ���������������������������������� Definition

Overspeed ������������������������ Condition in which the RPM of the propeller or engine

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

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

Parting Line ����������������������� The Parting line is formed where the face and camber
composite materials meet at the leading and trailing edges
of the blade. They are most visible in the shank area of the
blade.

Pitch ���������������������������������� Same as “Blade Angle”

Pitting �������������������������������� Formation of a number of small, irregularly shaped cavities

in surface material caused by corrosion or wear

Pitting (Linear) ������������������� The configuration of the majority of pits forming a pattern in
the shape of a line

Porosity ����������������������������� An aggregation of microvoids; see "Voids"

Propeller Critical Part ����������A part on the propeller whose primary failure can result in
a hazardous propeller effect, as determined by the safety
analysis required by Title 14 CFR section 35.15

Raptor
Composite Blades ������������� A composite blade that is used in Raptor series propellers

Reference Blade Radius �����Refers to the propeller reference blade radius in an

assembled propeller; e.g., 30-inch radius. A measurement
from the propeller hub centerline to a point on a blade, used
for blade angle measurement in an assembled propeller. A
yellow adhesive stripe (blade angle reference tape CM160) is
usually located at the reference blade radius location.
NOTE: Do not confuse reference blade radius with blade
station; they may not originate at the same point.

Reversing �������������������������� The capability of rotating blades to a position to generate

reverse thrust to slow the aircraft or back up.

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Term ���������������������������������� Definition

Rolling ������������������������������� Compressive rolling process for the retention area of single
shoulder blades, that provides improved strength and
resistance to fatigue

Scratch ������������������������������ Same as "Nick"

Short ��������������������������������� Connection of low resistance between points on a circuit

between which the resistance is normally much greater

Shot Peening �������������������� Process where steel shot is impinged on a surface to create
compressive surface stress, that provides improved strength
and resistance to fatigue

Single Acting ��������������������� Hydraulically actuated propeller which utilizes a single oil
supply for pitch control

Split ����������������������������������� Delamination of a composite blade extending to the blade

surface, normally found near the trailing edge or tip

Superseded ����������������������� Parts that are considered airworthy for continued flight but
may no longer be available

Synchronizing ������������������� Setting all propellers at exactly the same RPM

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

Test Bar ����������������������������� A machined round bar used to check runout and parallelism
of the chuck to the carriage. The diameter runout should not
be greater than 0.001 inch (0.025 mm).

Ticking ������������������������������� A series of parallel marks or scratches running

circumferentially around the diameter of the blade

Track ��������������������������������� In an assembled propeller, a measurement of the location

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

Trailing Edge ��������������������� The aft edge of an airfoil over which the air passes last

Trimline ����������������������������� Factory terminology referring to where the part was trimmed
to length

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Term ���������������������������������� Definition

Underspeed ���������������������� The condition in which the actual engine (propeller) RPM is
lower than the RPM selected by the pilot through the
condition lever

Unidirectional Material ������ A composite material in which the fiber are substantially
oriented in the same direction

Variable Force ������������������� A force which may be applied or removed during propeller
operation

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

Voids ��������������������������������� Air or gas that has been trapped and cured into a laminate

Windmilling ������������������������ The rotation of an aircraft propeller caused by air flowing

over it while it is not operating

Woven Fabric �������������������� A material constructed by interlacing fiber to form a fabric

pattern

Wrinkle ������������������������������ Overlap or fold within the material

Wrinkling ��������������������������� A degradation of the surface finish of a compressively

rolled blade shank where the surface has been physically
deformed by the rolling process. This results in a wavy
appearance caused by high and low material displacement.

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8. Abbreviations

Abbreviation Term

AD............................Airworthiness Directives
AMM........................Aircraft Maintenance Manual
AN............................Army-Navy
AOG.........................Aircraft On Ground
AR............................As Required
ATA..........................Air Transport Association
CSU.........................Constant Speed Unit
FAA..........................Federal Aviation Administration
FH............................Flight Hour
FM............................Flight Manual
FMS.........................Flight Manual Supplement
Ft-Lb........................Foot-Pound
HMI..........................Human Machine Interface
ICA...........................Instructions for Continued Airworthiness
ID.............................Inside Diameter
In-Lb........................Inch-Pound
IPL...........................Illustrated Parts List
IPS...........................Inches Per Second
ITAR.........................International Traffic in Arms Regulations
kPa..........................Kilopascals
Lb(s).........................Pound(s)
Max..........................Maximum
Min...........................Minimum
MIL-X-XX.................Military Specification
MPI..........................Major Periodic Inspection
MS...........................Military Standard
MSDS......................Material Safety Data Sheet
N..............................Newtons
N/A...........................Not Applicable
NAS.........................National Aircraft Standards
NASM......................National Aerospace Standards, Military
NDT.........................Nondestructive Testing
NIST.........................National Institute of Standards and Technology
N•m..........................Newton-Meter
OD...........................Outside Diameter
OPT.........................Optional
PC............................Production Certificate
PCP.........................Propeller Critical Part
PLC..........................Programmable Logic Controller
PMB.........................Plastic Media Blasting (Cleaning)
POH.........................Pilot’s Operating Handbook

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Abbreviation Term

PSI...........................Pounds per Square Inch

RF............................Reference
RPM.........................Revolutions per Minute
SAE.........................Society of Automotive Engineers
STC..........................Supplemental Type Certificate
TBO.........................Time Between Overhaul
TC............................Type Certificate
TSI...........................Time Since Inspection
TSN..........................Time Since New
TSO.........................Time Since Overhaul
UID...........................Unique Identification
WIG..........................Wing-In-Ground-Effect

NOTE: TSN/TSO is considered as the time accumulated between rotation and

landing, i.e., flight time.

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9. Contact Information

A. Hartzell Propeller Inc. Product Support Department

(1) Contact the Product Support Department of Hartzell Propeller Inc. about
any maintenance problems or to request information not included in this
publication.

NOTE: When calling from outside the United States, dial (001) before dialing
the telephone numbers below.
(a) Hartzell Propeller Inc. 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.
(b) Hartzell Propeller Inc. Product Support can also be reached by fax at
(937) 778-4215, and by e-mail at techsupport@hartzellprop.com.
(c) After business hours, you may leave a message on our 24 hour product
support line at (937) 778-4376 or at (800) 942-7767, toll free from the
United States and Canada.
1 A technical representative will contact you during normal business
hours.
2 Urgent AOG support is also available 24 hours per day, seven days
per week via this message service.
(d) Additional information is available on the Hartzell Propeller Inc. website
at www.hartzellprop.com.

B. Hartzell Propeller Inc. Technical Publications Department

(1) For Hartzell Propeller Inc. service literature and revisions, contact:
Hartzell Propeller Inc. Telephone: 937.778.4200
Attn: Technical Publications Department Fax: 937.778.4215
One Propeller Place E-mail: manuals@hartzellprop.com
Piqua, Ohio 45356-2634 U.S.A.

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DESCRIPTION AND OPERATION - CONTENTS

1. Description................................................................................................................... 3
A. General.................................................................................................................. 3
B. Components........................................................................................................... 3
2. Operation..................................................................................................................... 3
A. Bantam Constant Speed........................................................................................ 3
3. Model Designation System.......................................................................................... 4
A. Propeller Model Designation.................................................................................. 4
B. Blade Shank Designation....................................................................................... 4

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1. Description

A. General
CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY
INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST CHAPTER OF THIS MANUAL FOR THE
IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS.
(1) Hartzell Propeller Inc. Bantam propellers use composite blades mounted in
an aluminum hub. The hub is held together with bolts and contains the pitch
change mechanism. The pitch change components include the pitch change
rod, fork, and pitch change blocks.

B. Components
(1) The model designation system for propellers described in this manual is
outlined in the Hartzell Propeller Inc. Application Guide Manual 159
(61-02-59) and the applicable owner's manual, available on the Hartzell
Propeller Inc. website at www.hartzellprop.com.

2. Operation

A. Bantam Constant Speed

(1) ( )(A)1 Series Propellers with Composite Blades
(a) These propeller model series are constant speed, non-counterweighted
propellers. The propellers are capable of blade angles between a low
positive pitch (low pitch) and high positive pitch (high pitch).
(b) Centrifugal twisting moment acting on the blades moves the blades to a
low blade angle (low pitch) to increase RPM. Since the centrifugal twisting
moment is only present when the propeller is rotating, a mechanical spring
is installed within the propeller to assist movement of the blades to a lower
pitch position as RPM declines, and to reduce the propeller pitch to the
low pitch stop when the propeller is static. With the blades at low pitch, the
load on the starter when starting the engine is reduced significantly.
(c) Oil pressure opposes the spring and centrifugal twisting moment to move
the blades to a high blade angle (high pitch), reducing engine RPM.
(d) If oil pressure is lost at any time, the propeller will move to low pitch. This
occurs because the spring and blade centrifugal twisting moment are no
longer opposed by hydraulic oil pressure. The propeller will then reduce
blade pitch to the low pitch stop.

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3. Model Designation System

A. Propeller Model Designation

(1) Hartzell Propeller Inc. uses a model number designation system to identify
specific propeller and blade assemblies. An example model number would
be 3A1-TP600A1/75A01-2, with the slash mark separating the propeller
designation from the blade designation.
(2) The propeller model number is impression stamped on the propeller hub. The
blade model number is impression stamped on the butt end of the blade, as
well as ink stamped or identified by a label on the cylinder.
(3) For additional information about the model number designation system, refer
to the Hartzell Propeller Inc. Application Guide Manual 159 (61-02-59) or the
applicable owner's manual, available on the Hartzell Propeller Inc. website at
www.hartzellprop.com.

B. Blade Shank Designation

(1) For more information about blade shank designs, refer to Hartzell Propeller Inc.
Composite Propeller Blade Maintenance Manual 135F (61-13-35).

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TESTING AND FAULT ISOLATION - CONTENTS

1. Trouble-Shooting Guide............................................................................................ 1-3

A. Pitch Control Difficulty......................................................................................... 1-3
B. Friction................................................................................................................. 1-3
C. Abnormal Propeller Vibration.............................................................................. 1-3
D. Blades Not Tracking............................................................................................ 1-3
E. End-Play Movement of the Blade........................................................................ 1-4
F. In-and-Out Movement of the Blade .................................................................... 1-4
G. Fore-and-Aft Movement of the Blade.................................................................. 1-4
H. Radial Play in the Blade...................................................................................... 1-4
I. Oil Leakage......................................................................................................... 1-5
2. Lightning Strike on Hub or Blade.............................................................................. 1-5

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

Problem Probable Cause Remedy

A. Pitch Control Difficulty Excessive friction in moving parts. Refer to problem B. Friction.

Oil leaking past the piston, Disassemble the propeller and

between the pitch change rod inspect the hub-to-pitch change
and hub (engine-side), or rod O-rings and the piston
between the pitch change O-rings, as applicable. Inspect the
rod and shaft plug causing piston-to-cylinder sealing surfaces
overspeed. Hub will fill with engine and the pitch change rod sealing
oil. surfaces, as applicable. Replace
the O-ring(s).

B. Friction Propeller fork bumper shimming is Disassemble the propeller

excessive. and readjust the fork bumper
shimming.

Balls in the blade retention Replace the blade retention split

split bearing are unusually bearing assembly.
rough, corroded, or chipped.

Insufficient clearance between Check/increase the clearances

the various moving parts in the between the individual parts as
pitch change mechanism. necessary to decrease friction in
the mechanism.

C. Abnormal Propeller Bent, cracked, or damaged Refer to Hartzell Propeller Inc.

Vibration blade. Composite Blade Maintenance
Manual 135F (61-13-35).

Cracked or damaged hub. Contact the Hartzell Propeller Inc.

Product Support Department.

Refer to the Static and Dynamic

Balance chapter of Hartzell
Incorrect balance of the Propeller Inc. Standard Practices
propeller. Manual 202A (61-01-02).

D. Blades Not Tracking Foreign object strike Refer to the Special Inspections
damage. chapter of Hartzell Standard
Practices Manual 202A (61-01-02),
for inspection procedure.

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Problem Probable Cause Remedy

E. End-Play Movement of the Buildup of wear or repair Disassemble the propeller and
Blade. tolerances. reset the fork bumper shimming.
Refer to Figure 8-2 and
Table 8-2, Blade Tolerances
Blade retention bearing is worn. Inspect/Replace the blade
retention bearing.

F. In-and-Out Movement of Buildup of wear or repair Disassemble the propeller and

the Blade. tolerances. reset the fork bumper shimming.
Refer to Figure 8-2 and
Table 8-2, Blade Tolerances
Blade retention bearing is worn. Inspect/Replace the blade
retention bearing.

G. Fore-and-Aft Buildup of wear or repair Disassemble the propeller and

Movement of the Blade. tolerances. reset the fork bumper shimming.
Refer to Figure 8-2 and
Table 8-2, Blade Tolerances Blade retention bearing is worn. Inspect/replace the blade retention
bearing.

H. Radial Play in the Blade. Pitch change fork is worn. Disassemble the propeller. Inspect
Refer to Figure 8-2 and and replace parts, as required.
Table 8-2, Blade Tolerances
Pitch change block is worn. Disassemble the propeller. Inspect
and replace parts, as required.

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Problem Probable Cause Remedy

I. Oil Leakage Faulty O-ring seal between the Remove the propeller from the
engine flange and the engine and inspect the O-ring and
propeller mounting flange the sealing surface. Replace the
defective O-ring.

Engine crankshaft seal leaking Refer to the engine manufacturer's

manual for the appropriate action.

Faulty O-ring seal on the hub Disassemble the propeller and

extension plug inspect the O-rings and the sealing
surfaces. Replace the defective
O-ring(s).

Faulty seal between the low pitch Remove the low pitch stop jam nut
stop jam nut and the cylinder and replace the seal.

Oil leaking between the Disassemble the propeller and

blade and the hub inspect the hub-to-blade seal and
sealing surfaces. Replace the
defective seal.

2. Lightning Strike on Hub or Blade

A. In the event of a propeller lightning strike, an inspection is required before further

flight.
(1) A lightning strike on the propeller usually leaves arcing damage on the blade,
as evidence of where it entered or left the tip of the blade.
(2) Refer to the Special Inspections chapter of Hartzell Propeller Inc. Standard
Practices Manual 202A (61-01-02) for lightning strike inspection criteria.

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AUTOMATIC TEST REQUIREMENTS (NOT APPLICABLE)

NOTE: In accordance with ATA iSpec 2200 specification this space is reserved for
automatic test requirements. Such requirements are not applicable to the
Hartzell Propeller Inc. propellers included in this manual.

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DISASSEMBLY - CONTENTS

1. Removing the Propeller Assembly from the Aircraft................................................. 3-3

2. Marking Before Disassembly.................................................................................... 3-3
3. Removal of the Propeller Ice Protection System (if applicable)................................ 3-4
4. Two and Three Blade Propeller Disassembly........................................................... 3-6
A. Disassembly of the Propeller Pitch Change Parts.............................................. 3-6
B. Hub Disassembly................................................................................................ 3-9
C. Blade Disassembly............................................................................................ 3-11
D. Washer (260), Fork (710), and Pitch Change Rod (240) Disassembly............. 3-12

LIST OF FIGURES

Spring Compressor TE548 and Spindle TE536.................................... Figure 3-1.............. 3-5

Spring Compressor TE548 Pull Rod Threaded Into the Extension....... Figure 3-2.............. 3-7

DISASSEMBLY 61-10-01 Page 3-1

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1. Removing the Propeller Assembly from the Aircraft

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY
INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.

A. Remove the propeller in accordance with the instructions in the applicable Hartzell
Propeller Inc. Owner's manual. Refer to the Introduction chapter of this manual for a
list of the applicable publications.

B. If applicable, remove the forward bulkhead mount (960) and O-ring (950) in
accordance with the instructions in the applicable Hartzell Propeller Inc. Owner's
manual. Refer to the Introduction chapter of this manual for a list of the applicable
publications.

2. Marking Before Disassembly

WARNING: ANY PART IDENTIFIED IN THIS MANUAL AS AN EXPERIMENTAL

OR NON-AVIATION PART MUST NOT BE USED IN AN FAA OR
INTERNATIONAL EQUIVALENT TYPE CERTIFICATED PROPELLER.
A PART IDENTIFIED AS EXPERIMENTAL OR NON-AVIATION DOES
NOT HAVE FAA OR INTERNATIONAL EQUIVALENT APPROVAL.
USE ONLY THE APPROVED ILLUSTRATED PARTS LIST PROVIDED
IN THE APPLICABLE OVERHAUL MANUAL OR ADDITIONAL
PARTS APPROVED BY AN FAA ACCEPTED DOCUMENT FOR
ASSEMBLY OF A PROPELLER. THE OPERATOR ASSUMES ALL RISK
ASSOCIATED WITH THE USE OF EXPERIMENTAL PARTS. USE OF
EXPERIMENTAL PARTS ON AN AIRCRAFT MAY RESULT IN DEATH,
SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY
DAMAGE.

CAUTION 1: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY IDENTIFY

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

CAUTION 2: TO PREVENT DAMAGE TO THE PITCH CHANGE ROD, SPINDLE

TE536 AND SPRING COMPRESSOR TE548 MUST BE USED FOR
ASSEMBLY AND DISASSEMBLY OF THE PROPELLER.

A. Put the propeller assembly on the rotatable fixture TE125 on the assembly
table TE129 using spindle TE536 and spring compressor TE548.

B. Make a record of the serial number and model number of the hub, blades, and any
other serial-numbered parts and compare with the data in the propeller logbook.

DISASSEMBLY 61-10-01 Page 3-3

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CAUTION: GRAPHITE ("LEAD") PENCIL MARKS WILL CAUSE CORROSION.

ALL MARKS MADE ON PARTS MUST BE MADE WITH A CRAYON
OR SOFT, NON-GRAPHITE PENCIL SUCH AS CM162.

C. Where possible, each blade should be reinstalled in the hub socket from which it is
removed.
(1) Using a crayon or soft, non-graphite pencil such as CM162, number the blades
counterclockwise from the propeller serial number impression stamped on the
propeller hub unit.
(2) For propeller serial number location, refer to the Parts Identification and Marking
chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

D. Make a record of each blade serial number and its matching hub socket.
3. Removal of the Propeller Ice Protection System (if applicable)

A. If the propeller is equipped with an ice protection system that uses components
supplied by Hartzell Propeller Inc., applicable instructions and technical information
for the components supplied by Hartzell Propeller Inc. can be found in the following
publication available on the Hartzell Propeller Inc. website at www.hartzellprop.com:
(1) Hartzell Propeller Inc. Manual 180 (30-61-80) - Propeller Ice Protection System
Manual

B. Propeller ice protection system components not supplied by Hartzell Propeller Inc.
are controlled by the applicable TC or STC holder’s Instructions for Continued
Airworthiness (ICA).

DISASSEMBLY 61-10-01 Page 3-4

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Extension
Groove

Pull Rod
TE548-2

Extension

Extension
TE-548-1

Anti-Rotate
Hub Flange
Pin
Spindle

Compression
Spring
TE548-3
TI-401-0028
TI-401-029

Spring Compressor TE548 and Spindle TE536

Figure 3-1

DISASSEMBLY 61-10-01 Page 3-5

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4. Two and Three Blade Propeller Disassembly

WARNING: THE USE OF BLADE PADDLES TO MOVE BLADES CAN RESULT

IN THE OVERLOAD AND DAMAGE OF BLADE PITCH CHANGE
KNOBS. THIS DAMAGE IS NOT REPAIRABLE AND CAN RESULT
IN SEPARATION BETWEEN THE BLADE AND THE PITCH
CHANGE KNOB, CAUSING LOSS OF PITCH CONTROL DURING
FLIGHT.

CAUTION 1: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY

INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.

CAUTION 2: USE COMPRESSED AIR THAT HAS BEEN FILTERED FOR

MOISTURE, OR NITROGEN TO ACTUATE THE PROPELLER.

CAUTION 3: DO NOT EXCEED A PRESSURE OF 175 PSI (12.06 BARS) WHEN

ACTUATING PROPELLERS COVERED IN THIS MANUAL.

CAUTION 4: USE SUFFICENT PRESSURE TO MAKE SURE THAT THE

PROPELLER ACTUATES AGAINST EACH POSITIVE STOP.

A. Disassembly of the Propeller Pitch Change Parts

NOTE: To simplify the assembly process and minimize the effort required to set the
required blade angles, make a record of the location and orientation (where
applicable) of each part in the propeller hub assembly.
(1) Make sure that the spring compressor extension TE548-1 and anti-rotate pin
are installed in the spindle TE536. The groove in the extension must align with
the anti-rotate pin. Refer to Figure 3-1.
(2) Using nuts (910) and washers (920), install the engine-side hub half on the
propeller assembly stand.
(3) Remove and discard the low pitch stop nut (10).
(4) Remove and discard the seal washer (20) from the low pitch stop (250).
(5) Remove the low pitch stop (250) from the cylinder.
(6) Remove and discard the screws (40 and 50) and O-rings (60) that attach the
cylinder (70) to the hub (430).
(7) Remove the balance ring (90) and cylinder (70).
(8) Remove and discard the O-ring (80) from the cylinder (70).

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Pull Rod

Washer
Pitch Change Rod (240)

TI-401-0027

Spring Compressor Pull Rod TE548-2 Threaded Into the Extension

Figure 3-2

DISASSEMBLY 61-10-01 Page 3-7

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(9) Remove and discard the pitch change rod nut (200).
(10) Remove the piston (210) from the pitch change rod (240).
(11) Remove and discard the O-rings (220 and 230) from the ID and OD of the
piston.
(12) If applicable, remove the washer (260) from the pitch change rod (240).
(13) If applicable, remove the high pitch stop (75).
(14) Drain the red-dyed oil from the hub.

NOTE: The propeller hub is filled with a red-dyed oil. The red-dyed oil must
be removed before complete disassembly of the propeller.
(a) The hub has large openings to permit the red-dyed oil to drain.
(b) Flip the propeller over a large container to permit the red-dyed oil to drain.
(c) Securely balance the propeller hub over the container.
(15) Using nuts (910) and washers (920), install the engine-side hub half on the
propeller assembly stand.
(16) Put the spring compressor pull rod TE-548-2 through the pitch change
rod (240). Refer to Figure 3-1 and Figure 3-2.
(17) Thread the spring compressor TE548 pull rod into the the spring compressor
extension TE-548-1.
(18) Thread the spring compressor pull rod TE548-2 until the pull rod bottoms in the
spring compressor extension TE548-1.
(19) Remove and discard the nuts (420) and washers (410) from the hub clamping
bolts (400).
(a) If the spinner bulkhead is mounted to the propeller with the hub bolts,
remove the spinner bulkhead.
(20) Remove the hub clamping bolts (400).
(21) Using a non-metallic tool, loosen the cylinder-side hub half.
(22) Remove the cylinder-side hub half.
(23) Remove blades from the hub.
(a) Remove blade number one from the hub.
(b) Remove the pitch change block unit (500).
(c) Remove and discard the fork bumper (520).
(d) Remove the shim(s) (530).

DISASSEMBLY 61-10-01 Page 3-8

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(e) Remove and discard the bearing balls (610).

(f) Remove and discard the ball spacers (620).
(g) Remove the bearing races (630 and 640).
(h) Remove and discard the blade O-ring (600).
(i) Repeat steps 4.A.(23)(a) through 4.A.(23)(h) for each blade in the hub.
(24) Remove the spring compressor TE548 pull rod and washer from the pitch
change rod (240).
(25) Remove the pitch change rod (240) with the washer (700) and fork (710).
(26) Remove the spring (720).
(27) Remove the spring seat (730).

B. Hub Disassembly
(1) Remove and discard the O-ring (439) from the hub bushing (434).
(2) Remove and discard the mounting O-ring (930).
(3) Remove the pitch change rod bushing from the engine side of the hub.
(a) Remove and discard the internal retaining ring (437).
(b) Remove and discard the bushing (434) from the hub.
(c) Remove and discard the O-ring (432) from the bushing (434).
(4) Remove the pitch change rod bushing from the cylinder side of the hub.
(a) Remove and discard the external retaining ring (435).
(b) Remove and discard the bushing (436) from the hub.

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(5) Remove the mounting flange attachment hardware.

(a) Studs and other mounting hardware are replaced at overhaul.
(b) Procedure
1 For H, T, and Q-flange Propellers

CAUTION: DO NOT SCRATCH OR OTHERWISE DAMAGE

THE HUB WHEN SECURING THE HUB OR WHEN
USING THE STUD REMOVAL TOOL, GRINDER, OR
REAMER. ANY DAMAGE MAY CAUSE THE HUB TO
BE RETIRED.
a Secure the hub before using the stud removal tool.
b To prevent damage to the hub, place a washer over the stud,
between the stud removal tool and the propeller hub, before
using the stud removal tool.
c Using a locally procured stud removal tool, apply up to
100 ft-lb (135.6 N•m) of torque to each stud, remove as many
studs as possible.

NOTE: A taper collet-style stud removal tool, for example

Snap-on tool part number A80A, is recommended.
2 Procedure for G-flange Propellers

CAUTION: DO NOT SCRATCH OR OTHERWISE DAMAGE

THE HUB WHEN SECURING THE HUB OR WHEN
USING THE STUD REMOVAL TOOL, GRINDER, OR
REAMER. ANY DAMAGE MAY CAUSE THE HUB TO
BE RETIRED.
a Secure the hub before using the stud removal tool.
b Remove the spring pin (940) from the nut (910) and stud (900).
c To prevent damage to the hub, leave the washer (920) over
the stud, between the stud removal tool and the propeller hub,
before using the stud removal tool.
d Using a locally procured stud removal tool, apply up to
100 ft-lb (135.6 N•m) of torque to each stud (900), remove as
many studs as possible.

NOTE: A taper collet-style stud removal tool, for example

Snap-on tool part number A80A, is recommended.
e Remove the nut (910) from the stud (900).

DISASSEMBLY 61-10-01 Page 3-10

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(c) Studs that cannot be removed using the standard method require the
following additional steps.
1 Grind a flat area on one side of the exposed portion of the stud.

CAUTION: IF USING A WEDGE-STYLE REMOVAL TOOL, DO NOT

HAMMER THE WEDGE AGAINST THE STUD.
2 Using a stud removal tool, apply torque up to 100 Ft-Lb (135.6 N•m)
to remove the stud.

CAUTION: THE HUB MUST NOT BE HEATED DIRECTLY AND THE

TEMPERATURE OF THE STUD IN THE THREADED
AREA MUST NOT EXCEED 200° F (93.3° C).
3 An additional step that may be used is to heat the exposed portion of
the stud to a temperature not exceeding 200° F (93.3° C).

NOTE: A heat gun may be used to heat the stud.

4 Using a stud removal tool, apply torque up to 100 Ft-Lb (135.6 N•m)
to remove the stud.
(d) Repeat step 4.B.(5)(b) through step 4.B.(5)(c) until all the studs have been
removed.
(e) Clean all adhesive residue from the threaded holes by tapping the hole
with the appropriate thread tap.
1 Tap 7/16-20UNF GH1 bottom tap - T Flange
2 Tap 1/2-20UNF GH1 bottom tap - Q Flange
3 Tap 1/2-20UNF GH1 bottom tap - H Flange
(f) Remove all epoxy residue from the unthreaded portion of the hole.
1 For T flange, use reamer TE403-1.
2 For Q and H flange, use reamer TE403.

C. Blade Disassembly
(1) For composite blade overhaul procedures, refer to Hartzell Propeller Inc.
Composite Blade Manual 135F (61-13-35).

DISASSEMBLY 61-10-01 Page 3-11

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D. Washer (260), Fork (710), and Pitch Change Rod (240) Disassembly
(1) Refer to the Special Tooling, Equipment, and Fixtures chapter of this manual for
instruction for the Tooling for Pitch Change Rod to Fork.

NOTE: This locally fabricated tooling is the same tooling that will be used to
assemble the washer (260), fork (710), and pitch change rod (240).
(2) Put the threaded end of the pitch change rod (240) in the support with the
washer (260) firmly against the support.
(3) Put the locally fabricated tool over the unthreaded end of the pitch change
rod (240).
(4) Using a press, push on the tool until the pitch change rod (240) and
washer (260) are released from the fork (710).
(5) Remove the pitch change rod (240) and fork (710) from the press.

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CLEANING - CONTENTS

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

2. Specific Cleaning Procedures................................................................................. 4-3
A. Cleaning Steel Parts for Magnetic Particle Inspection....................................... 4-3
B. Cleaning Steel Parts for Cadmium Replating Procedures................................. 4-3
C. Cleaning Aluminum Parts for Penetrant Inspection............................................ 4-3
D. Cleaning Aluminum Parts for Chromic Acid Anodizing Procedures................... 4-3

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1. General Procedures for Cleaning Parts

A. Refer to the Cleaning chapter of Hartzell Propeller Inc. Standard Practices

Manual 202A (61-01-02).

2. Specific Cleaning Procedures

A. Cleaning Steel Parts for Magnetic Particle Inspection

(1) Refer to the Magnetic Particle Inspection chapter of Hartzell Propeller Inc.
Standard Practices Manual 202A (61-01-02).

B. Cleaning Steel Parts for Cadmium Replating Procedures

(1) Refer to the Cadmium Replating chapter of Hartzell Propeller Inc. Standard
Practices Manual 202A (61-01-02).

C. Cleaning Aluminum Parts for Penetrant Inspection

(1) Refer to the Penetrant Inspection chapter of Hartzell Propeller Inc. Standard
Practices Manual 202A (61-01-02).

D. Cleaning Aluminum Parts for Chromic Acid Anodizing Procedures

(1) Refer to the Chromic Acid Anodizing chapter of Hartzell Propeller Inc. Standard
Practices Manual 202A (61-01-02).

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CHECK - CONTENTS

1. Inspection Interval Requirements............................................................................. 5-3

2. Inspection Requirements.......................................................................................... 5-3
3. Replacement Requirements..................................................................................... 5-4
4. Repair....................................................................................................................... 5-4
5. Specific Inspection Procedures................................................................................ 5-5
6. Specific Checks........................................................................................................ 5-6
A. Cylinder (70)....................................................................................................... 5-9
B. Bearing Races (630 and 640)...........................................................................5-11
C. Pitch Change Rod (240)................................................................................... 5-13
D. Pitch Change Block Unit (500)......................................................................... 5-14
E. Spring (720)..................................................................................................... 5-15
F. Spring Seat (730)............................................................................................. 5-16
G. Hub Bolt (400).................................................................................................. 5-17
H. Piston (210)...................................................................................................... 5-19
I. Fork (710)......................................................................................................... 5-21
J. Balance Weight (840)....................................................................................... 5-22
K. Balance Ring (90)............................................................................................ 5-22
L. Set Screw (Low Pitch) (250)............................................................................ 5-23
M. High Pitch Stop (75)......................................................................................... 5-23
N. Stainless Shim (530)........................................................................................ 5-23
O. Forward Bulkhead Mount (960)........................................................................ 5-24
P. Washer (260).................................................................................................... 5-25
Q. UID Plate (431)................................................................................................ 5-26

CHECK 61-10-01 Page 5-1

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LIST OF FIGURES

Cylinder................................................................................................. Figure 5-1.............. 5-8

Bearing Races....................................................................................... Figure 5-2............ 5-10
Pitch Change Rod................................................................................. Figure 5-3............ 5-12
Pitch Change Block Unit........................................................................ Figure 5-4............ 5-14
Piston.................................................................................................... Figure 5-5............ 5-18
Fork....................................................................................................... Figure 5-6............ 5-20

LIST OF TABLES

Component Inspection Criteria.............................................................. Table 5-1............... 5-9

CHECK 61-10-01 Page 5-2

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1. Inspection Interval Requirements

A. For information about life limited components and mandatory inspections, refer to
the Airworthiness Limitations chapter of the applicable Hartzell Propeller Inc.
owner's manual.

B. For overhaul periods of Hartzell Propeller Inc. propellers, refer to Hartzell

Propeller Inc. Service Letter HC-SL-61-61Y.
(1) Hartzell Propeller Inc. Service Letter HC-SL-61-61Y is available on the
Hartzell Propeller Inc. website at www.hartzellprop.com.
2. Inspection Requirements

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY

INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.

A. Inspect the specified parts to determine if they meet the specifications in this chapter.
(1) Retire any serial-numbered part found unairworthy in accordance with the
Mandatory Parts Retirement Procedure chapter of Hartzell Propeller Inc.
Standard Practices Manual 202A (61-01-02).

B. Visual Inspection
(1) Visually examine all parts.
(a) A part that has obvious defects or damage that would affect form, fit, or
function must be removed from service.
(2) Definitions
(a) Corrosion is active electrochemical deterioration, such as rust, that can
result in pitting.
(b) Linear pitting is the configuration of the majority of pits forming a pattern
in the shape of a line.

C. Penetrant Inspection
(1) Penetrant inspect aluminum parts, as required. Refer to Table 5-1,
Component Inspection Criteria, in this chapter.
(a) For inspection of aluminum parts, use the procedures in the Penetrant
Inspection chapter of Hartzell Propeller Inc. Standard Practices
Manual 202A (61-01-02).

CHECK 61-10-01 Page 5-3

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D. Magnetic Particle Inspection

(1) Magnetic particle inspect steel parts, as required. Refer to Table 5-1,
Component Inspection Criteria, in this chapter.
(a) For inspection of steel parts, use the procedures in the Magnetic Particle
Inspection chapter of Hartzell Propeller Inc. Standard Practices
Manual 202A (61-01-02).

E. Dimensional Inspection
(1) When measuring the diameter of a part with a two point measuring
instrument, take at least two measurements unless specified differently.
(a) 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.
(b) Alternately, take eight evenly spaced measurements, unless specified
differently.
1 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).
2 This alternate method may not be used to accept a diameter that
has obvious damage beyond repairable (serviceable) limits.
(2) Inspect the part features to the number of decimal places specified. If three
decimal places are specified, inspect the part to three decimal places only.

3. Replacement Requirements

A. Replace all components that have cracks, corrosion, wear, obvious defects, or
damage found during visual inspection that do not meet serviceable limits.

B. If the component has corrosion, wear, obvious defects, or damage that is less than
the permitted serviceable limits, no further action is required.

C. If the component has cracks, corrosion, wear, obvious defects, or damage that is
greater than the permitted serviceable limits, the component must be repaired or
replaced in accordance with Corrective Action in this chapter.

4. Repair

A. Parts that can be repaired are specified in the Corrective Action section of Table 5-1,
Component Inspection Criteria, in this chapter.

B. Repair procedures are found in the Repair chapter of this manual, unless specified
differently.

CHECK 61-10-01 Page 5-4

Rev. 2 Apr/15
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5. Specific Inspection Procedures

NOTE: Specific Hartzell Propeller Inc. manuals and service documents are available
on the Hartzell website at www.hartzellprop.com. Refer to the Required
Publications section in the Introduction chapter of this manual for the
identification of these publications.

A. For daily inspection procedures of a propeller with composite blades, refer to Hartzell
Propeller Inc. Propeller Owner's Manual and Logbook 411 (61-00-11).

B. For requirements and procedures for inspecting aluminum hubs, contact the Hartzell
Propeller Inc. Product Support department.

C. For requirements and procedures for inspecting composite blades, refer to Hartzell
Propeller Inc. Composite Propeller Blade Maintenance Manual 135F (61-13-35).

D. For foreign object strike inspection procedures, refer to the Special Inspections
chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

E. If the propeller is equipped with an ice protection system that uses components
supplied by Hartzell Propeller Inc., applicable instructions and technical information
for the components supplied by Hartzell Propeller Inc. can be found in the following
publication available on the Hartzell Propeller Inc. website at www.hartzellprop.com:
(1) Hartzell Propeller Inc. Manual 180 (30-61-80) - Propeller Ice Protection
System Manual

F. Propeller ice protection system components not supplied by Hartzell Propeller Inc.
are controlled by the applicable TC or STC holder’s Instructions for Continued
Airworthiness (ICA).

G. For spinner assembly inspection procedures, refer to Hartzell Propeller Inc.

Metal Spinner Assembly Maintenance Manual 127 (61-16-27), or Hartzell
Propeller Inc. Composite Spinner Maintenance Manual 148 (61-16-48).

CHECK 61-10-01 Page 5-5

Rev. 4 Jan/19
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6. Specific Checks

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY

INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.

A. For specific component checks, refer to Table 5-1, Component Inspection Criteria in
this chapter.

CHECK 61-10-01 Page 5-6

Rev. 2 Apr/15
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(This page intentionally left blank.)

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O-ring Groove Area Around

Attachment Holes

Seal Washer
Interface Surface

P/N 104577
Low Pitch Stop
P/N 104666 Threads

Area Around
Attachment Holes

Seal Washer
Interface Surface

P/N 105218
P/N 105133
Low Pitch Stop
P/N 106090 Threads
104577X_CYLINDER
TI-401-0032

O-ring Groove

Cylinder
Figure 5-1

CHECK 61-10-01 Page 5-8

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

A. CYLINDER (70)
REFER TO FIGURE 5-1

(1) Visually examine the external A crack is not permitted. If a crack is found, replace the
surfaces of the cylinder for cylinder.
cracks.

(2) Visually examine the external All external surfaces: maintain Using an abrasive pad CM47
surfaces of the cylinder for a wall thickness of 0.075 inch or equivalent, polish to blend
wear, nicks, scratches, or other (1.905 mm), repaired area out damage. High spots are not
damage. must be less than 0.5 inch permitted. If base aluminum is
(12.7 mm) in diameter, repairs exposed, chromate conversion
must be separated by a coat. If damage is greater
minimum of 0.5 inch than the permitted serviceable
(12.7 mm). limits, replace cylinder.

(3) Visually examine the threads 1/4 of one thread accumulated If damage is greater than the
of the low pitch stop hole for damage per cylinder permitted serviceable limits,
damage. attachment hole is permitted. replace the cylinder.

(4) Visually examine the anodized If wear, nicks, scratches, or If damage is greater than the
coating of the cylinder for wear, other damage is present, permitted serviceable limits,
nicks, scratches or other measure the depth of damage. replace the cylinder.
damage. On the OD, the maximum
permitted depth of damage is
0.003 inch (0.07 mm).

(5) Visually examine the O-ring If wear is present, measure the If the wear is greater than
groove for wear. diameter of the O-ring groove. the maximum permitted
The minimum permitted serviceable limit, replace the
diameter for the 104577, cylinder.
104666, 105218, and 106090
cylinder is 3.7635 inches
(95.593 mm).
The minimum permitted
diameter for the 105133 cylinder
is 3.5155 inches (89.294 mm)

(6) Visually examine the area If damage is present, measure If damage is greater than the
encircling the through holes the depth of the damage. The permitted serviceable limits,
(for attachment to the hub) maximum permitted depth of replace the cylinder.
of the cylinder for scouring damage is 0.025 inch
damage from the attaching (0.63 mm).
screws or washers.

(7) Visually examine the washer Corrosion is not permitted. If damage is greater than the
seal (20) interface surface for Pitting, scratches, gouges, or permitted serviceable limits,
corrosion, pitting, scratches, damage on the washer replace the cylinder.
gouges, or damage. seal (20) interface surface that
will permit oil to leak are not
permitted.

CHECK 61-10-01 Page 5-9

Rev. 3 Sep/16
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Ball Track
Outer Diameter

Inner Diameter

Blade Side Race Hub Side Race

105444
105421

Bearing Races
Figure 5-2

CHECK 61-10-01 Page 5-10

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

B. BEARING RACES (630 AND 640)

REFER TO FIGURE 5-2.

(1) Visually examine the ball If the ball bearing track shows If the depth of damage is
track for damage wear, measure the depth greater than the permitted
or fretting on the bearing race. of damage or fretting. The serviceable limits, replace the
maximum permitted depth of bearing race.
damage or fretting is
0.005 inch (0.12 mm).

(2) Visually examine the bearing Corrosion is not permitted. If Remove light corrosion by
race for corrosion or pitting. there is corrosion, remove it in glass media cleaning. Refer
accordance with the corrective to the Cleaning chapter
action repair limits. of Hartzell Propeller Inc.
Standard Practices Manual
If pitting is present measure 202A (61-01-02). If the
the depth of the pitting. The corrosion cannot be removed
maximum permitted depth of or if pitting is deeper than the
pitting is 0.005 inch (0.12 mm). permitted serviceable limits,
replace the bearing race.

(3) Visually examine the outer The maximum permitted depth Using an abrasive pad CM47,
diameter of the hub side of fretting is 0.005 inch or equivalent, clean the area
bearing race for fretting (0.12 mm). thoroughly to minimize fretting
damage and the inner diameter damage. If fretting is more
of the blade side bearing race. than the permitted serviceable
limits, replace the bearing
race.

(4) Magnetic particle inspect the A relevant indication is not If there is a relevant indication,
race in accordance with permitted. replace the bearing race.
the Magnetic Particle
Inspection chapter of
Hartzell Propeller Inc. Standard
Practices Manual 202A
(61-01-02).

CHECK 61-10-01 Page 5-11

Rev. 2 Apr/15
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A B

TI-401-13837

Pitch Change Rod

Figure 5-3

CHECK 61-10-01 Page 5-12

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

C. PITCH CHANGE ROD (240)

REFER TO FIGURE 5-3.

(1) Visually examine the chrome Damage below the chrome If the damage is greater than
plating of the pitch change rod for plating is not permitted. the serviceable limits, replace
damage in the area of the pitch change rod.
diameter "A".

(2) Measure the diameter of area The minimum permitted If the diameter is less than the
"A" of the pitch change rod. diameter of area "A" is serviceable limits, replace the
0.413 inch (10.49 mm). pitch change rod.

(3) Measure the diameter of area The minimum permitted If the diameter is less than the
"B" of the pitch change rod. diameter of area "B" is serviceable limits, replace the
0.557 inch (14.14 mm). pitch change rod.

(4) Measure the diameter of area The minimum permitted If the diameter is less than the
"C" of the pitch change rod. diameter of area "A" is serviceable limits, replace the
0.4379 inch (11.122 mm). pitch change rod.

(5) Visually examine the pitch Corrosion is not permitted. If there is corrosion, remove it
change rod for corrosion. using an abrasive pad CM47
or equivalent. If the corrosion
cannot be removed, replace
the pitch change rod.

(6) Visually examine the pitch Pitting or damage is not If there is pitting or damage,
change rod for pitting and permitted. replace the pitch change rod.
damage.

(7) Visually examine the pitch The rod must be straight. If the rod is not straight,
change rod for straightness. Bending is not permitted. replace the pitch change rod.

(8) Magnetic particle inspect the A relevant indication is not If there is a relevant indication,
pitch change rod. permitted. replace the pitch change rod.
NOTE: Do not strip the
chrome plating.

(9) Examine the oil supply bore Unwanted material is not Remove all unwanted material.
for unwanted material using permitted.
a borescope or fiberoptic
flashlight.

CHECK 61-10-01 Page 5-13

Rev. 3 Sep/16
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

D. PITCH CHANGE BLOCK UNIT (500)

REFER TO FIGURE 5-4. (INCLUDES BUSHING [502] AND PITCH CHANGE BLOCK [501])

(1) Visually examine the pitch If damage is present, measure If the depth of damage is
change block unit for damage. the depth of damage. The greater than the permitted
maximum permitted depth of serviceable limits, replace the
damage is 0.005 inch pitch change block unit.
(0.12 mm).

(2) Visually examine the hole in the If wear is present, measure the If the wear is greater than the
pitch change block unit for wear. diameter of the hole "C". The permitted serviceable limits,
maximum permitted diameter replace the pitch change block
for 106045( ) and 104934 is unit.
0.380 inch (9.65 mm).

(3) Measure the thickness of area The minimum permitted If the thickness is less than the
"A" of the pitch change block thickness of area "A" is serviceable limits, replace the
unit. 0.140 inch (3.56 mm). pitch change block unit.

(4) Measure the thickness of area The minimum permitted If the thickness is less than the
"B" of the pitch change block thickness of area "B" is serviceable limits, replace the
unit. 0.040 inch (1.02 mm). pitch change block unit.

B B
C
C

A A
TI-401-104955

P/N 106045 P/N 104934

Pitch Change Block Unit

Figure 5-4

CHECK 61-10-01 Page 5-14

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

E. SPRING (720)

CAUTION: DO NOT STRIP THE ZINC PLATING FROM THE SPRING. IF PLATING IS
REMOVED, REPLACE THE SPRING.

(1) Visually examine the spring Corrosion is not permitted. If If corrosion is present, replace
for wear, corrosion, or other wear or damage is present, the spring. If the wear or
damage. measure the depth of wear damage is greater than the
or damage. The maximum permitted serviceable limit,
permitted depth of wear or replace the spring.
damage is 0.003 inch
(0.07 mm).

(2) Visually examine the spring for Except for a few random Coat the spring with zinc
zinc plating coverage. scratches, the zinc plating must chromate primer in accordance
completely cover all surfaces. with the Repair chapter of this
manual.

(3) Measure the free length of the The minimum permitted free If the free length is less than
spring. length for 105282 is the permitted serviceable limit,
2.54 inches (64.6 mm) replace the spring.
The minimum permitted free
length for 103922 is
2.03 inches (51.6 mm)
The minimum permitted free
length for 106079 is
2.37 inches (60.2 mm)

(4) Magnetic particle inspect A crack is not permitted. If there is a crack, replace the
the spring in accordance spring.
with the Magnetic Particle
Inspect chapter of the Hartzell
Propeller Inc. Standard
Practices Manual 202A
(61-01-02).
NOTE: Do not strip the zinc or
cadmium plating.

CHECK 61-10-01 Page 5-15

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

F. SPRING SEAT (730)

(1) Visually examine the spring Corrosion is not permitted. If corrosion is present, replace
seat for damage, corrosion or If damage or pitting is the spring seat. If the damage
pitting. present, measure the depth or pitting is greater than the
of the damage or pitting. The permitted serviceable limit,
maximum permitted depth of replace the spring seat.
damage or pitting is 0.005 inch
(0.12 mm).

(2) Visually examine the spring If the spring seat is worn, If wear is greater than the
seat for wear. measure the depth of wear. permitted serviceable limits,
The maximum permitted depth replace the spring seat.
of wear is 0.015 inch
(0.38 mm). When there is wear
on both sides of the spring
seat, the total of both wear
depths must not be greater
than 0.015 inch (0.38 mm).
Wear that could affect correct
fit or function is not permitted.

(3) Visually examine the If nicks, scratches, gouges, If nicks, scratches, gouges,
spring seat for nicks, or other damage is present, or other damage is greater
scratches, and gouges or measure the depth of the nick, than the permitted serviceable
other damage. scratch, gouge, or damge. limits, replace the spring seat.
The maximum permitted
depth of nicks, scratches,
gouges, or other damage is
0.015 inch (0.38 mm). The
maximum permitted total area
of accumulated damage for
all surfaces combined is 0.5
square inch (322 square mm).
Damage that could affect
correct fit or function is not
permitted.

CHECK 61-10-01 Page 5-16

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

G. HUB BOLT (400)

Hub bolts that are used to bolt the hub halves together may be reused when they are inspected in
accordance with the following procedure.

(1) Visually examine each hub bolt Corrosion, scoring, thread If there is corrosion, scoring,
for corrosion, scoring, thread damage, or any other defects thread damage, or any other
damage, or other defects. are not permitted. defects, replace the hub bolt.

(2) Magnetic particle inspect A relevant indication is not If there is a relevant indication,
each bolt in accordance with permitted. replace the hub bolt.
Hartzell Propeller Inc. Standard
Practices Manual 202A
(61-01-02).
NOTE: It is not necessary
to strip the hub bolt
before magnetic
particle inspection.

(3) Visually examine the Cadmium plate must If cadmium plate does not
cadmium plate coverage completely cover the hub bolt. completely cover the hub
on the hub bolt. bolt, replate and bake the hub
bolt in accordance with the
Cadmium Replating chapter of
Hartzell Propeller Inc. Standard
Practices Manual 202A
(61-01-02).

CHECK 61-10-01 Page 5-17

Rev. 2 Apr/15
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D
A C

Piston Part "A" Dimension "B" Dimension "C" Dimension "D" Dimension
Number
104255 0.491 inch 0.296 inch 3.200 inch 3.610 inch
(12.47 mm) (7.51 mm) (81.28 mm) (91.70 mm)
106080 0.491 inch 0.296 inch 2.820 inch 3.236 inch
(12.47 mm) (7.51 mm) (71.63 mm) (82.20 mm)
TI-401-104255

Piston
Figure 5-5

CHECK 61-10-01 Page 5-18

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

H. PISTON (210)
REFER TO FIGURE 5-5.

(1) Measure the diameter of area Refer to Figure 5-5 for the If the diameter is greater than
"A" of the piston. maximum permitted diameter the serviceable limits, replace
of area "A". the piston.

(2) Visually examine the surface of If nicks, scratches, or other If nicks, scratches, or other
the piston for nicks, scratches, damage is present, measure damage is greater than the
or other damage. the depth of the nick, scratch, permitted serviceable limits,
or damage. The maximum replace the piston.
permitted depth of damage is
0.005 inch (0.12 mm).

(3) Visually examine the piston for If wear is present, measure the If wear if greater than the
wear in area "B". depth of wear. Refer to serviceable limits, replace the
Figure 5-5 for the maximum piston.
permitted diameter of area"B".

(4) Visually examine the piston for If wear is present, measure the If the diameter of area "C"
wear in areas "C" and "D". depth of wear. Refer to or area "D" is less than the
Figure 5-5 for the minimum serviceable limits, replace the
permitted diameter of area "C". piston.
Refer to Figure 5-5 for the
minimum permitted diameter of
area "D".

CHECK 61-10-01 Page 5-19

Rev. 2 Apr/15
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Part Number 104919

Part Number 105055

TI-401-104919
TI-401-105055

Fork
Figure 5-6

CHECK 61-10-01 Page 5-20

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

I. FORK (710)
REFER TO FIGURE 5-6.

(1) Visually examine the fork for If there is corrosion, wear, or Using an abrasive pad CM47
corrosion, wear, or damage. damage, measure the depth or equivalent, polish to a
of corrosion, wear or damage. maximum depth of 0.005 inch
The maximum permitted depth (0.12 mm). If repair is beyond
of corrosion, wear, or damage the serviceable limits or the
is 0.003 inch (0.07 mm). corrective action limits, replace
the fork.

(2) Measure the diameter of area The maximum permitted If the diameter is greater than
"A" of the fork. diameter of area "A" is the serviceable limits, replace
0.4378 inch (11.120 mm). the fork.

(3) For 104919 fork: Measure the The maximum permitted width If the width is greater than the
width of area "B" of the fork. of area "B" is 0.720 inch serviceable limits, replace the
(18.28 mm). fork.

(4) Visually examine the fork for Except for a few scratches and Re-plate the fork in accordance
cadmium coverage. corners with cadmium coating with the Cadium Re-Plating
missing, complete coverage is chapter of Hartzell Propeller
required. Inc. Standard Practices Manual
202A (61-01-02).

(5) Perform magnetic particle A relevant indication is not If there is a relevant indication
inspection of the fork in permitted that cannot be removed within
accordance with the Penetrant all the serviceable limits given
Inspection chapter of Hartzell for the fork in this section,
Propeller Inc. Standard replace the fork.
Practices Manual 202A
(61-01-02).

CHECK 61-10-01 Page 5-21

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

J. BALANCE WEIGHT (840)

(1) Visually examine the balance If wear corrosion, wear, or Using an abrasive pad CM47,
weights for corrosion, wear, or damage is present, measure or equivalent, polish to a
damage. the depth of corrosion, wear, maximum depth of 0.005 inch
or corrosion. The maximum (0.12 mm). If corrosion, wear,
permitted depth of corrosion, or damage is greater than
wear, or damage is 0.003 inch the serviceable limits or the
(0.07 mm). corrective action limits, replace
the balance weight.

(2) Visually examine aluminum Except for a few scratches and Re-anodize the balance weight
balance weights for anodize corners with anodize coating in accordance with the Chromic
coverage. missing, complete coverage is Acid Anodizing chapter of
required. Hartzell Propeller Inc. Standard
Practices Manual 202A
(61-01-02).

K. BALANCE RING (90)

(1) Visually examine the balance If wear corrosion, wear, or Using an abrasive pad CM47,
ring for corrosion, wear, or damage is present, measure or equivalent, polish to a
damage. the depth of corrosion, wear, maximum depth of 0.005 inch
or corrosion. The maximum (0.12 mm). If corrosion, wear,
permitted depth of corrosion, or damage is greater than
wear, or damage is 0.003 inch the serviceable limits or the
(0.07 mm). corrective action limits, replace
the balance ring.

CHECK 61-10-01 Page 5-22

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

L. SET SCREW (LOW PITCH) (250)

(1) Visually examine the set screw A corrosion, wear, or damage If corrosion, wear, or damage is
for corrosion, wear, or damage. is not permitted. found, replace the set screw.

(2) Visually examine the set screw The hole may not break out If the hole is not within the
through hole for wear and through the end or side of the serviceable limits, replace the
damage. set screw. set screw.

(3) Visually examine the set screw A maximum of 10 percent If cadmium plating coverage
for cadmium plating coverage. of the base metal visible is is less than the permitted
permitted. serviceable limits, cadmium
replate and bake the set
screw in accordance with the
Cadmium Replating chapter of
Hartzell Propeller Inc. Standard
Practices Manual 202A
(61-01-02).

M. HIGH PITCH STOP (75)

(1) Visually examine the surface If nicks, scratches, or other If nicks, scratches, or other
of the high pitch stop for nicks, damage is present, measure damage is greater than the
scratches, or other damage. the depth of the nick, scratch, permitted serviceable limits,
or damge. The maximum replace the high pitch stop.
permitted depth of damage is
0.005 inch (0.12 mm).

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

(3) Visually examine the high pitch The high pitch stop must be If the high pitch stop is not flat,
stop for flatness. flat. Bending is not permitted. replace the high pitch stop.

N. STAINLESS SHIM (530)

(1) Visually examine the stainless A torn, bent, or damaged shim If a torn, bent, or damaged
shim for tears, bending, or is not permitted. shim is greater than the
damage. permitted serviceable limits,
replace the stainless shim.

CHECK 61-10-01 Page 5-23

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

O. FORWARD BULKHEAD MOUNT (960)

(1) Visually examine the forward A crack is not permitted. If there is a crack, replace the
bulkhead mount for cracks. forward bulkhead mount.

CHECK 61-10-01 Page 5-24

Rev. 2 Apr/15
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

P. WASHER (260)

(1) Visually examine the washer for Corrosion is not permitted. If Remove corrosion using glass
corrosion and pitting. there is corrosion, remove it in bead cleaning. Refer to the
accordance with the corrective Cleaning chapter of Hartzell
action repair limits. Propeller Inc. Standard
Practices Manual 202A
(61-01-02). If the corrosion
cannot be removed, replace
the washer.

The maximum permitted depth If the pitting is greater than the

of pitting is 0.002 inch serviceable limits, replace the
(0.05 mm). washer.

The maximum permitted total

surface pitting is 5%.

The maximum permitted

diameter of an individual pit is
0.02 Inch (0.5 mm).

Pitting must not affect the fit or

function of the washer.

(2) Visually examine the washer for The maximum permitted depth If scratches are greater than
scratches. of a scratch is 0.002 inch the serviceable limits, replace
(0.05 mm). the washer.

Scratches must not affect the

fit or function of the washer.

(3) Measure the thickness of the The minimum permitted If the thickness of the washer is
washer. washer thickness is 0.052 inch less than the serviceable limits,
(1.32 mm). replace the washer.

(4) Visually examine the washer for A few random scratches are If the cadmium plating
cadmium plating coverage. permitted on the sides and coverage is less than the
inside diameter; otherwise, permitted serviceable limits,
complete coverage is required. cadmium replate and bake the
Cadmium plating must washer in accordance with the
completely cover the outside Cadmium Replating chapter of
diameter without scratches. Hartzell Propeller Inc. Standard
Slight cadmium plating loss on Practices Manual 202A
the corners between sides and (61-01-02).
outside diameter is permitted.

CHECK 61-10-01 Page 5-25

Rev. 3 Sep/16
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

Q. UID PLATE (431)

(1) Visually examine the UID plate Damage to the scan code is If damage is greater than
for damage. not permitted. The scan code the permitted serviceable
must be able to be scanned limits, replace the UID plate.
successfully. For ordering, removal, and
installation instructions, refer to
the section "Installing the UID
Plate" in the Assembly chapter
of this manual. If the UID plate
must be discarded, make the
UID plate unserviceable by one
of the following methods:
1) Cut the plate in half through
the scan code,
2) Sand the plate to remove
the scan code,
3) Use any other method
identified and/or required
by the military/government
authority that requires the use
of the UID plate.

(2) Visually examine the serial The serial number must match If the serial numbers do not
number on the UID plate. the serial number of the hub. match or if the hub must be
retired from service, replace
the UID plate. If the UID plate
must be discarded, make the
UID plate unserviceable by one
of the following methods:
1) Cut the plate in half through
the scan code,
2) Sand the plate to remove
the scan code,
3) Use any other method
identified and/or required
by the military/government
authority that requires the use
of the UID plate.

CHECK 61-10-01 Page 5-26

Rev. 3 Sep/16
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REPAIR - CONTENTS

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

A. Shot Peening....................................................................................................... 6-3
B. Aluminum and Steel Parts................................................................................... 6-3
2. Blade Repair............................................................................................................. 6-4
3. Hub Repair............................................................................................................... 6-4
4. Spinner Assembly Repair/Modification..................................................................... 6-4

REPAIR 61-10-01 Page 6-1

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(This page is intentionally blank.)

REPAIR 61-10-01 Page 6-2

Rev. 2 Apr/15
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WARNING: DO NOT ATTEMPT IN THE FIELD ANY REPAIR, REPLACEMENT,

REPLATING, RE-ANODIZING OR RE-SHOT PEENING PROCEDURE
NOT SPECIFICALLY AUTHORIZED BY HARTZELL PROPELLER INC. OR
NOT SPECIFICALLY REFERRED TO IN HARTZELL PROPELLER INC.
MANUALS. CONTACT THE FACTORY FOR GUIDANCE ABOUT THE
AIRWORTHINESS OF ANY PART WITH UNUSUAL WEAR OR DAMAGE.

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY INVOLVE

PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION
CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER
CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST IN THIS
MANUAL FOR IDENTIFICATION OF PROPELLER CRITICAL PARTS.

1. General Repair Requirements

A. Shot Peening

CAUTION: THE PEENING MARKS ON CERTAIN PROPELLER PARTS ARE

NOT TOOL MARKS AND SHOULD NOT BE REMOVED.
(1) Certain surfaces of propeller assembly parts have been shot peened at Hartzell
Propeller Inc. to improve fatigue strength.
(2) Shot peened surfaces may require re-shot peening because of rust, corrosion,
fretting, or nicks. For shot peening procedures, refer to the Shot Peening
chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).
(a) Re-shot peening must be performed only by a repair station that is
certified by Hartzell Propeller Inc.
1 A list of the repair stations that are formally certified to perform shot
peening and the expiration dates of the sample approvals may be
found by:
a Referring to Sample Program Approvals on the Hartzell
Propeller Inc. website at www.hartzellprop.com
b Contacting Hartzell Propeller Inc. Product Support by telephone
at (937) 778-4379, or at (800) 942-7767 toll free from the
United States and Canada.
c E-mail request to techsupport@hartzellprop.com.
B. Aluminum and Steel Parts
(1) Eliminate all evidence of scratches, nicks, burrs, and other minor damage by
using a fine emery cloth or abrasive pad, such as CM47.
(a) Make sure to blend the polished area in with the surrounding area.
(b) Use extreme care to completely remove the damage while removing as
little material as possible.

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(2) Make sure that the part is still within tolerance after any type of repair. Refer to
the Check chapter and the Fits and Clearances chapter of this manual.

2. Blade Repair
A. For composite blade repair, replacement, and modification instructions, refer to
Hartzell Propeller Inc. Composite Propeller Blade Maintenance Manual 135F
(61-13-35).

3. Hub Repair
A. Contact Hartzell Propeller Inc. Product Support department for the requirements and
procedures for repairing aluminum hub units.

4. Spinner Assembly Repair/Modification

A. For requirements and procedures for repairing or modifying spinner assemblies, refer
to Hartzell Propeller Inc. Metal Spinner Maintenance Assembly Manual 127 (61-16-27)
or Hartzell Propeller Inc. Composite Spinner Maintenance Manual 148 (61-16-48).

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ASSEMBLY - CONTENTS

1. General.....................................................................................................................7-3
2. Bantam Assembly Procedures.................................................................................7-5
A. General............................................................................................................... 7-5
3. Two and Three Blade Bantam Assembly Procedures..............................................7-7
A. Hub Assembly..................................................................................................... 7-7
B. Pitch Change Rod (240) and Fork (710) Assembly........................................... 7-12
C. Two Blade Bantam Propeller Fork (710), Pitch Change Rod (240), and
Pitch Change Block Unit (500) Installation........................................................ 7-15
D. Three Blade Bantam Propeller Fork (710), Pitch Change Rod (240), and
Pitch Change Block Unit (500) Installation........................................................ 7-18
E. Installation of the Blade Bearing Race and Balls.............................................. 7-21
F. Hub Cylinder-Side Installation........................................................................... 7-24
G. Propeller Balance.............................................................................................. 7-31
H. Sealant Cure..................................................................................................... 7-31
I. Leak Check the Hub.......................................................................................... 7-31
J. Cylinder Installation .......................................................................................... 7-36
4. Propeller Disassembled for Shipping.....................................................................7-37
A. General............................................................................................................. 7-37
B. Preparing the Propeller for Shipping................................................................. 7-38
5. Reassembly of a Propeller Disassembled for Shipping..........................................7-39
A. Unpacking the Propeller and Blades................................................................. 7-39
B. Preparing Propeller for Reassembly................................................................. 7-39
C. Propeller Reassembly....................................................................................... 7-39

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LIST OF FIGURES
Hub Assembly....................................................................................... Figure 7-1.............. 7-6
Installation of the Fork on the Pitch Change Rod.................................. Figure 7-2............ 7-10
Installation of the Washer on the Pitch Change Rod............................. Figure 7-3............ 7-11
Two Blade Propeller - Installation of the Fork and the Pitch Change
Rod in the Hub................................................................................. Figure 7-4............ 7-14
Installation of a Shim for a Two Blade Bantam Propeller Fork.............. Figure 7-5............ 7-15
Three Blade Bantam Propeller - Installation of the Fork and the
Pitch Change Rod in the Hub.......................................................... Figure 7-6............ 7-16
Two and Three Blade Bantam Propellers - Fork at the Hub
Parting Line...................................................................................... Figure 7-7............ 7-17
Installation of Balls, Spacers, and Races on Blade .............................. Figure 7-8............ 7-20
Installation of the Blade in the Hub ....................................................... Figure 7-9............ 7-22
Three Blade Bantam Propeller- Determining Stainless Steel
Shim Thickness............................................................................... Figure 7-10........... 7-23
Application of Sealant on the Cylinder-Side Hub Half.......................... Figure 7-11........... 7-28
Installation of the 104506 Plug Assembly............................................. Figure 7-12........... 7-30
Leak Check ......................................................................................... Figure 7-13........... 7-32
Piston Installation................................................................................. Figure 7-14........... 7-34
Low Pitch Stop Installation................................................................... Figure 7-15........... 7-35

LIST OF TABLES

Three Blade Propeller P/N 104940-( ) Stainless Steel Shim Sizes........ Table 7-1............ 7-24
Two Blade Propeller P/N 104468-( ) Stainless Steel Bumper and
P/N 105004-( ) Stainless Steel Shim Sizes.......................................Table 7-2............ 7-24
Two Blade Propeller Bumper Plus Shim Relative Sizes.........................Table 7-3......... 7-24.1

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1. General

WARNING 1: ANY PART IDENTIFIED IN THIS MANUAL AS AN EXPERIMENTAL

OR NON-AVIATION PART MUST NOT BE USED IN AN FAA OR
INTERNATIONAL EQUIVALENT TYPE CERTIFICATED PROPELLER.
A PART IDENTIFIED AS EXPERIMENTAL OR NON-AVIATION DOES
NOT HAVE FAA OR INTERNATIONAL EQUIVALENT APPROVAL.
USE ONLY THE APPROVED ILLUSTRATED PARTS LIST PROVIDED
IN THE APPLICABLE OVERHAUL MANUAL OR ADDITIONAL
PARTS APPROVED BY AN FAA ACCEPTED DOCUMENT FOR
ASSEMBLY OF A PROPELLER. THE OPERATOR ASSUMES ALL RISK
ASSOCIATED WITH THE USE OF EXPERIMENTAL PARTS. USE OF
EXPERIMENTAL PARTS ON AN AIRCRAFT MAY RESULT IN DEATH,
SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY
DAMAGE.

WARNING 2: DO NOT USE FORMS PROVIDED BY THE FAA OR INTERNATIONAL

EQUIVALENT FOR RECORDING INFORMATION FOR
EXPERIMENTAL OR NON-AVIATION PROPELLERS. FORMS
PROVIDED BY THE FAA OR INTERNATIONAL EQUIVALENT ARE
CONTROLLED BY THE CERTIFICATION AUTHORITY AND ARE FOR
USE WITH TYPE CERTIFICATED PROPELLERS.

CAUTION 1: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY

INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.

CAUTION 2: THE USE OF BLADE PADDLES TO MOVE BLADES OR ROTATE

PRELOAD PLATES CAN RESULT IN OVERLOAD AND DAMAGE
OF BLADE PITCH CHANGE KNOBS. THIS DAMAGE IS NOT
REPAIRABLE AND CAN RESULT IN SEPARATION BETWEEN THE
BLADE AND THE PITCH CHANGE KNOB, CAUSING LOSS OF PITCH
CONTROL DURING FLIGHT.

NOTE: Specific Hartzell Propeller Inc. manuals and service documents are available
on the Hartzell website at www.hartzellprop.com. Refer to the Required
Publications section in the Introduction chapter of this manual for the
identification of these publications.

A. In preparation for assembling and installing a Hartzell Propeller Inc. propeller, make
sure that all preliminary procedures have been followed.

B. Read all assembly instructions before beginning the assembly procedures.

ASSEMBLY 61-10-01 Page 7-3

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C. For blade bore plug and blade bore bearing installation procedures for a composite
blade, refer to Hartzell Propeller Inc. Composite Propeller Blade Maintenance
Manual 135F (61-13-35).

D. To make sure the installation of a spinner assembly is correct, refer to the applicable
aircraft type certificate data sheet or Hartzell Propeller Inc. Application Guide
Manual 159 (61-02-59).

E. For specific blade angle information, refer to the Hartzell Propeller Inc. Application
Guide Manual 159 (61-02-59).

F. Protect all unassembled components from damage.

G. Unless specified differently, lubricate all O-rings with lubricant CM12 before installing
them in the propeller assembly.

H. Hartzell Propeller Inc. recommends that the lot number and cure date for each O-ring
be recorded with all work orders when an O-ring is installed in any propeller assembly.

I. Use applicable torque values. Refer to Table 8-1, Torque Values, in the Fits and
Clearances chapter of this manual.

J. Unless specified differently, safety wire in accordance with NASM33540 using

0.032 inch (0.81 mm) safety wire.
K. Before beginning the assembly of the propeller, determine if an ice protection system
is required.
(1) If the propeller is equipped with an ice protection system that uses
components supplied by Hartzell Propeller Inc., applicable instructions and
technical information for the components supplied by Hartzell Propeller Inc.
can be found in the following publication available on the Hartzell Propeller Inc.
website at www.hartzellprop.com:
(a) Hartzell Propeller Inc. Manual 180 (30-61-80) - Propeller Ice Protection
System Manual
(2) Propeller ice protection system components not supplied by Hartzell
Propeller Inc. are controlled by the applicable TC or STC holder’s
Instructions for Continued Airworthiness (ICA).

ASSEMBLY 61-10-01 Page 7-4

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CAUTION 1: ACTUATION OF PROPELLERS IS TO BE ACCOMPLISHED USING

COMPRESSED AIR THAT HAS BEEN FILTERED FOR MOISTURE, OR
NITROGEN.

CAUTION 2: DO NOT EXCEED A PRESSURE OF 175 PSI (12.06 BARS) WHEN

ACTUATING PROPELLERS COVERED IN THIS MANUAL.

CAUTION 3: USE SUFFICIENT PRESSURE TO MAKE SURE THAT THE

PROPELLER ACTUATES AGAINST EACH POSITIVE STOP.

2. Bantam Assembly Procedures

A. General

NOTE: Specific Hartzell Propeller Inc. manuals and service documents are
available on the Hartzell website at www.hartzellprop.com. Refer to the
Required Publications section in the Introduction chapter of this manual for
the identification of these publications.
(1) If required, make sure that the spinner and bulkhead assembly installation
procedures are completed before beginning assembly of the hub. Use the
alternate hub assembly nuts and bolts that are supplied with a spinner mounting
kit, if applicable.
(2) If the propeller is equipped with an ice protection system, applicable
instructions and technical information can be found in Hartzell Propeller Inc.
Propeller Ice Protection System Manual 180 (30-61-80) for those system
components supplied by Hartzell Propeller Inc. Propeller ice protection system
components not supplied by Hartzell Propeller Inc. are controlled by the
applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).

CAUTION: TO PREVENT DAMAGE TO THE PITCH CHANGE ROD (240), THE

HUB FLANGE SPINDLE TE536, AND SPRING COMPRESSOR
TE548 MUST BE USED FOR ASSEMBLY OF THE PROPELLER.
(3) Install the propeller assembly on the rotatable fixture TE125 on the assembly
table TE129 using hub flange spindle TE536 and spring compressor TE548.
(4) Use protractor TE96, TE97, or equivalent when measuring a blade angle.
(5) If applicable, the hub assembly will have a UID plate (431).
(a) Put the UID plate (431) aside until final balance.
(b) The UID plate is installed on the balance ring (90) during the static balance
procedure.

ASSEMBLY 61-10-01 Page 7-5

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910
920

900
430

437
432

434
435

436 104950 hub

NOTE: Three Blade Hub Shown for Reference

Hub Assembly
Figure 7-1

ASSEMBLY 61-10-01 Page 7-6

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3. Two and Three Blade Bantam Assembly Procedures

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY

INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.

A. Hub Assembly - Refer to Figure 7-1

(1) Mounting Stud (900) Installation Procedure for H, T, and Q-flange Propellers

WARNING: ADHESIVES AND SOLVENTS ARE FLAMMABLE AND TOXIC

TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND
EYE PROTECTION ARE REQUIRED. AVOID PROLONGED
CONTACT AND BREATHING OF VAPORS. USE SOLVENT
RESISTANT GLOVES TO MINIMIZE SKIN CONTACT AND
WEAR SAFETY GLASSES FOR EYE PROTECTION. USE
IN A WELL VENTILATED AREA AWAY FROM SPARKS AND
FLAME. READ AND OBSERVE ALL WARNING LABELS.
(a) Using solvent CM106 (MEK) or CM219 (MPK), clean the studs (900)
and hub mounting hole threads to make sure that all oil, grease, and
unwanted material have been removed.
(b) Apply adhesive CM16 to the threads of the stud (900) and threads of the
hub mounting hole or the threads of the insert.
(c) Verify the stud (900) extension from the hub:
1 The stud (900) P/N 100041 must extend 1.020 - 1.080 inches
(25.91 - 27.43 mm) from the flange of the hub.
2 The stud (900) P/N A-2429-3 must extend 1.140 - 1.160 inches
(28.96 - 29.46 mm) from the flange of the hub.
(d) Using solvent CM106 (MEK) or CM219 (MPK), remove any excess
adhesive CM16.
(e) Install a stud curing fixture to make sure that the studs (900) are set
perpendicular to the hub flange.

NOTE: Stud curing fixtures are locally manufactured tools. They are
typically engine flanges that have been removed from damaged
crankshafts.
(f) Permit the adhesive to cure 24 hours at 77° F (25° C) or 2 hours
at 140° F (60° C).
(g) Remove the stud curing fixture.

ASSEMBLY 61-10-01 Page 7-7

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(h) Attach a stud installation tool TE404 to the stud (900) and apply a
torque to the stud. The stud should not rotate when the torque is
applied.
1 For the stud (900) P/N 100041 in a T flange, apply a torque of
12 Ft-Lbs (16.2 N•m) to the stud.
2 For the stud (900) P/N A-2429-3 in an H flange or Q flange, apply a
torque of 25 Ft-Lbs (33.9 N•m) to the stud.
3 If the newly installed stud (900) fails the torque test, continue with
the following steps:
a Remove the stud (900) and discard the stud.
b Using solvent CM106 (MPK) or CM219 (MPK), clean the hub
stud (900) hole threads or insert threads to make sure all oil,
grease, residual adhesive, and foreign material have been
removed.

CAUTION: DO NOT INSTALL A STUD (900) THAT HAS BEEN

USED TO INSTALL A PROPELLER ON AN AIRCRAFT.
c Install a new stud (900) in accordance with steps in 3.b.(1).
(2) Mounting Stud (900) Installation Procedure for G-flange Propellers
(a) Using solvent CM106, or equivalent, clean the mounting stud (900)
threads, to ensure all oil, grease, and foreign material have been
removed.
(b) Coat the mounting stud (900) with thread locking primer CM127. Follow
the thread locking primer manufacturer's instructions.
(c) Coat the mounting stud (900) with thread locking compound CM74.
Follow the thread locking compound manufacturer's instructions.
(d) Insert the end of the stud (900) with a hole in it into the hub flange.
(e) Install the washer (920) and the nut (910) onto the stud (900). The top of the
nut should be flush with the end of the stud and a slot in the nut should align
with the hole in the stud.
(f) Install the spring pin (940) through the nut (910) and stud (900).
1 Grease the spring pin (940) with lubricant CM12 to prevent the
thread locking compound CM74 from filling the spring pin hole.
A safety wire will be inserted through the spring pin hole during
propeller installation.
2 Install the spring pin (940) with the slot toward the hub or away
from the hub. Orienting the spring pin in this manner will prevent
the safety wire from being caught in the spring pin slot during
propeller installation.

ASSEMBLY 61-10-01 Page 7-8

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(g) Using a clean dry cloth, remove any residual thread locking
compound CM74 and primer CM127 from the stud (900).
(3) Install the cylinder side hub bushing (436).
(a) Apply a light layer of lubricant CM12 to the cylinder side hub
bushing (436).
(b) Install the cylinder side hub bushing (436) into the pitch change rod bore
of the cylinder side of the hub.
(c) Install the external retaining ring (435) on the cylinder side hub
bushing (436).
(4) Install the engine side hub bushing (434).
(a) Apply a light layer of lubricant CM12 to the bushing to hub
O-ring (432).
(b) Install the O-ring (432) in the groove on the engine side hub
bushing (434).
(c) Install the bushing (434) through the flange side of the hub into the pitch
change rod bore of the engine side of the hub.
(d) Install the internal retaining ring (437) on the engine side hub bushing (434).
(5) Install the flange mounting O-ring (930) on the engine-side hub half.
(6) Install the pitch change rod O-ring (439) in the engine-side hub half.
(7) Make sure the spring compressor spring TE-548-3 is installed in the spring
compressor extension TE-548-1.
(8) Insert the spring compressor extension TE548-1 over the pitch change
rod (240). Refer to Figure 3-1, Spring Compressor TE548 and
Spindle TE536, in the Disassembly chapter of this manual.
(9) Make sure that the spring compressor extension TE548-1 and anti-rotate pin
are installed in the spindle TE536. The groove in the extension must align
with the anti-rotate pin.
(10) Using nuts (910) and washers (920), install the engine-side hub half on the
propeller assembly stand.
(11) Using lubricant CM12, apply a layer on the bearing seats of the blade
retention sockets.
(12) Using lubricant CM12, apply a layer in the grooves in each blade.

ASSEMBLY 61-10-01 Page 7-9

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Press

Locally Fabricated Tooling

Pitch Change Rod (240) to Prevent Damage to the
Threaded End of the Pitch
Change Rod (240)

Fork (710)

Locally Fabricated Tooling to

Support the Fork (710)

TI-401-0005

NOTE: Three Blade Fork Shown for Reference

Installation of the Fork on the Pitch Change Rod

Figure 7-2

ASSEMBLY 61-10-01 Page 7-10

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Washer (260)

Loctite CM74

Pitch Change Rod (240)

Fork (710)

Washer (700)

Unthreaded End of the Pitch

Change Rod (240)
TI-401-0006
TI-401-0020

NOTE: Three Blade Fork Shown for Reference

Installation of the Washer on the Pitch Change Rod

Figure 7-3

ASSEMBLY 61-10-01 Page 7-11

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B. Pitch Change Rod (240) and Fork (710) Assembly

(1) Refer to the Special Tooling, Equipment, and Fixtures chapter of this manual
for instructions for the Tooling for Pitch Change Rod (240) to Fork (710).

NOTE: This locally fabricated tooling is the same tooling that will be used to
assemble the washer (260), fork (710), and pitch change rod (240).
(2) Put the fork (710) on the support. Refer to Figure 7-2.
(3) If applicable, install the washer (260) on the unthreaded end of the pitch
change rod (240). Refer to Figure 7-3.

WARNING: ADHESIVES AND SOLVENTS ARE FLAMMABLE AND TOXIC TO

THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE
PROTECTION ARE REQUIRED. AVOID PROLONGED CONTACT
AND BREATHING OF VAPORS. USE SOLVENT RESISTANT
GLOVES TO MINIMIZE SKIN CONTACT AND WEAR SAFETY
GLASSES FOR EYE PROTECTION. USE IN A WELL VENTILATED
AREA AWAY FROM SPARKS AND FLAME. READ AND OBSERVE
ALL WARNING LABELS.
(4) Using solvent CM44 or CM106, clean the area of the pitch change rod (240)
that will be pressed into the fork (710).
(5) Permit the solvent CM44 or CM106 to dry.
(6) Apply retaining compound CM74 to the step in the pitch change rod (240) and
the bore in the fork (710) where the fork will seat. Refer to Figure 7-3.

CAUTION: DO NOT PERMIT THE UNTHREADED END OF THE PITCH

CHANGE ROD (240) TO CONTACT THE PRESS. THE SUPPORT
FOR THE FORK (710) MUST BE HIGH ENOUGH THAT WHEN THE
PITCH CHANGE ROD IS INSTALLED IN THE FORK THE PITCH
CHANGE ROD CANNOT CONTACT THE PRESS.
(7) Install the unthreaded end of the pitch change rod (240) with the washer
(260) through the fork (710). Refer to Figure 7-3
(8) Make sure that the unthreaded end of the pitch change rod (240) cannot
contact the surface of the press.
(9) Put the locally fabricated tool on the threaded end of the pitch change
rod (240).
(10) Using a press, push on the tool until the pitch change rod (240) and
washer (260) are seated in the fork (710). Refer to Figure 7-2.
(11) Remove the pitch change rod (240) and fork (710) from the press.
(12) Make sure that the washer (260) is not distorted and is firmly seated in the
fork (710).

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(This page intentionally blank.)

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Unthreaded End of the Pitch

Change Rod (240)

Fork Bumper (520) Spring (720)

and
Shim (530)

Washer (700)

Fork (710)
TI-401-0039

Two Blade Propeller - Installation of the Fork and the Pitch Change Rod in the Hub
Figure 7-4

ASSEMBLY 61-10-01 Page 7-14

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C. Two Blade Bantam Propeller Fork (710), Pitch Change Rod (240), and Pitch Change
Block Unit (500) Installation
(1) Apply a thin layer of lubricant CM12 to the spring seat (730).
(2) With the chamfer side to the hub, put the spring seat (730), over the pitch
change rod bore in the engine side hub half. Refer to Figure 7-4.
(3) Apply a thin layer of lubricant CM12 to the unthreaded end of the pitch
change rod (240).
(4) Apply lubricant CM12 in the slots in the fork (710) for the fork bumpers (520)
and shims (530).
(5) Apply lubricant CM12 in the slots in the fork (710) for the pitch change block
units (500).
(6) Install a shim (530) in the shim location of the fork (710) specified in
Figure 7-5.
(7) Install a fork bumper (520) on top of the shim (530) in the fork (710). Refer to
Figure 7-5.
(8) Put the spring (720) on the spring seat (730) in the hub.
(9) Insert the assembled pitch change rod (240)/fork (710) through the
spring (720) and the spring seat (730) into the engine side hub bushing (439).
Refer to Figure 7-4.

Fork Bumper (520)

Unthreaded End
Shim (530) of the
Piston Rod (240)

Shim Location

Fork (710)

Pitch Change
Block Location
Piston Rod (240)
TI-401-0037

Washer (700)

Installation of a Shim for a Two Blade Bantam Propeller Fork

Figure 7-5

ASSEMBLY 61-10-01 Page 7-15

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Pull Rod

Pitch Change Rod (240)

Fork (710)

Bumper (520)

Pitch Change
Block Unit (500)

Spring (720)

TI-401-0030

Spring Seat (730)

Three Blade Bantam Propeller - Installation of the Fork and the

Pitch Change Rod in the Hub
Figure 7-6

ASSEMBLY 61-10-01 Page 7-16

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Two Blade Bantam Propeller

Fork (710)
centered
at the hub
parting line

Fork (710)
centered
at the hub
parting line

Three Blade Bantam Propeller

TI-401-0031
TI-401-0042

Two and Three Blade Bantam Propellers - Fork at the Hub Parting Line
Figure 7-7

ASSEMBLY 61-10-01 Page 7-17

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(10) Insert the spring compressor pull rod TE548-2 in the pitch change
rod (240). Refer to Figure 3-1, Spring Compressor TE548 and
Spindle TE536, in the Disassembly chapter of this manual.
(11) Turn the spring compressor pull rod TE548-2 into the spring compressor
extension TE548-2.

CAUTION: DO NOT PERMIT THE CENTER OF THE PITCH CHANGE BLOCK

SLOT OF THE FORK (710) TO GO BELOW THE PARTING LINE
OF THE HUB. TURNING THE SPRING COMPRESSOR PULL ROD
TE548-2 TOO FAR MAY DAMAGE THE SPRING (720).
(12) Turn the spring compressor pull rod TE548-2 until the center of the
fork (710) is centered at the hub parting line. Refer to Figure 7-7.
(13) Installation of the pitch change block unit (500).
(a) Measure the wall thickness of the side of the pitch change block
unit (500) to verify the orientation of the pitch change block unit.

CAUTION: GRAPHITE ("LEAD") PENCIL MARKS WILL CAUSE

CORROSION. ALL MARKS MADE ON PARTS MUST BE
MADE WITH A CRAYON OR SOFT, NON-GRAPHITE
PENCIL SUCH AS CM162.
(b) Using a crayon or soft, non-graphite pencil such as CM162, make a mark
on the pitch change block unit (500) for orientation during assembly.
(c) With the thin side of the pitch change block unit (500) facing the engine
side hub half, install the pitch change block unit in the fork (710).
1 Pitch change block units (500) marked for orientation during
disassembly should be reassembled in accordance with those
markings.

D. Three Blade Bantam Propeller Fork (710), Pitch Change Rod (240), and Pitch
Change Block Unit (500) Installation
(1) Apply a thin layer of lubricant CM12 to the spring seat (730).
(2) Put the spring seat (730) with the chamfer side to the hub, over the pitch
change rod bore in the engine side hub half. Refer to Figure 7-6.
(3) Install the spring (720) on the unthreaded end of the pitch change rod (240).
(4) Seat the spring (720) in the recess of the fork (710).
(5) Using lubricant CM12, apply a thin layer to the unthreaded end of the pitch
change rod (240).

ASSEMBLY 61-10-01 Page 7-18

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(6) Insert the pitch change rod into the engine side hub bushing and into
the spring compressor extension TE548-1. Refer to Figure 3-1, Spring
Compressor TE548 and Spindle TE536, in the Disassembly chapter of this
manual and Figure 7-6.
(7) Put the spring compressor pull rod TE548-2 through the pitch change
rod (240). Refer to Figure 7-6.
(8) Thread the spring compressor pull rod TE548-2 into the spring compressor
extension TE548-2.

CAUTION: DO NOT PERMIT THE CENTER OF THE FORK (710) TO GO

BELOW THE HUB PARTING LINE. TURNING THE SPRING
COMPRESSOR PULL ROD TE548-2 TOO FAR MAY DAMAGE THE
SPRING (720).
(9) Turn the spring compressor pull rod TE548-2 until the center of the
fork (710) is centered at the hub parting line. Refer to Figure 7-7.
(10) Apply lubricant CM12 in the slots in the fork (710) for the fork bumpers (520)
and shims (530).
(11) Apply lubricant CM12 in the slots in the fork (710) for the pitch change block
units (500).
(12) Install a shim (530) in each slot in the fork (710).
(a) Both shims for each blade socket must have the same part number.
(b) The shims from one blade socket to another blade socket may be
different part numbers.
1 Installation of a P/N 104940-15, 104940-18, or 104940-20 shim (530)
is recommended at the initial assembly. The shim may require
replacement after inspection for loose blades.
(13) Install a fork bumper (520) on top of the shim (530) in each slot in the
fork (710). Refer to Figure 7-6.
(14) Installation of the pitch change block units (500).
(a) Measure the wall thickness of the side of the pitch change block
units (500) with the tab.
(b) Mark the pitch change block units (500) for orientation during assembly.
(c) Install the pitch change block units (500) in the fork (710) with the thin
side of the pitch change block units facing the engine side hub half.
1 Pitch change block units (500) marked for orientation during
disassembly should be reassembled following those markings.

ASSEMBLY 61-10-01 Page 7-19

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Blade O-Ring (600)

Hub Bearing
Race (630)

Bearing Ball (610)

Ball Spacer (620)

Blade Bearing Race (640)
TI-401-0018

TE504

Installation of Balls, Spacers, and Races on Blade

Figure 7-8

ASSEMBLY 61-10-01 Page 7-20

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E. Installation of the Blade Bearing Race and Balls

(1) Apply a thin layer of lubricant CM12 to the blade O-ring (600).
(2) Install the blade O-ring (600) on the blade.
(3) Install the hub bearing race (630) on the blade.
(4) Apply a thin layer of lubricant CM12 to the blade retention radius and the
teflon.
(5) Using bearing assembly tool TE504, install the split blade bearing
races (640), ball spacers (620), and the balls (610). Refer to Figure 7-8.

CAUTION: THE SPLIT BEARING RACES MUST HAVE MATCHING

SERIAL NUMBERS.
(a) Install the blade split bearing race (640) on the blade retention radius.
There is no specified position for the split bearing race on the blade
retention radius.
(b) Hold the hub bearing race (630) inboard of the teflon.
(c) Install the ball spacers (620) and bearing balls (610) on the blade
bearing race (640).

CAUTION: ALL THE BEARING BALLS IN A SINGLE BEARING MUST

BE OF THE SAME SIZE AND GAUGE. ALL BEARING BALLS
SUPPLIED BY HARTZELL PROPELLER INC. ARE THE SAME
GAUGE.
(d) Alternate the bearing balls (610) and the ball spacers (620) on the blade
bearing race (640).
(e) Put the hub bearing race (630) on the balls (610).
(f) Put the blade O-ring (600) on the blade teflon.

ASSEMBLY 61-10-01 Page 7-21

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Blade O-Ring (600)

Bearing Ball (610)
Hub Bearing Race (630)

Ball Spacer (620)

Blade Teflon Strip Blade Bearing Race (640)
TI-401-0004

Blade

Installation of the Blade in the Hub

Figure 7-9

ASSEMBLY 61-10-01 Page 7-22

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Feeler Gauge

Cylinder Side Hub

Fork (710)

Fork Bumper (520)

TI-401-0008

Three Blade Bantam Propeller- Determining Stainless Steel Shim Thickness

Figure 7-10

ASSEMBLY 61-10-01 Page 7-23

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(g) Install the number one blade assembly into the socket of the
engine-side hub half. Refer to Figure 7-9.
1 Firmly holding the hub bearing race (630) over the balls (610) and
ball spacers (620), install the blade in the hub.
2 Install the pitch change knob in the pitch change block unit (500).
3 Rotate the blade into the blade socket.
4 Make sure that the blade O-ring (600) is evenly seated around the
blade and in the hub O-ring groove in the hub.
(h) Repeat section 3.E.(5), "Installation of the Blade Bearing Race and
Balls" for each blade.

F. Hub Cylinder-Side Installation

(1) Put the hub guide bushing (433) in the engine side hub half.
(2) Install the cylinder-side hub half.
(3) Make sure the blade O-ring (600) is in the O-ring groove of the hub.
(4) Install bolts (400), washers (410), and nuts (420) in the hub on opposite
sides of the blade.
(a) For a two blade hub:
1 Install 2 bolts (400), 4 washers (410), and 2 nuts (420)
(b) For a three blade hub:
1 Install 3 bolts (400), 6 washers (410), and 3 nuts (420)

P/N 104940-( ) Shim (530) Sizes Feeler Gauge Check Resulting Value
104940-12 (0.012 inch [0.304 mm]) Value between 0 and 2.5
104940-15 (0.015 inch [0.381 mm]) Value between 0 and 2.5
104940-18 (0.018 inch [0.457 mm]) Value between 2.6 and 4.5
104940-20 (0.020 inch [0.508 mm]) Value between 4.6 and 7.5
104940-23 (0.023 inch [0.584 mm]) Value between 7.6 and 9.5
104940-25 (0.025 inch [0.635 mm]) Value between 9.6 and 10.5

Three Blade Propeller P/N 104940-( ) Stainless Steel Shim Sizes

Table 7-1
P/N 104468-( ) Bumper (520) Sizes P/N 105004-( ) Shim (530) Sizes
104468-1 (0.3550 inch [9.014 mm]) 105004-13 (0.013 inch [0.330 mm])
104468-2 (0.3350 inch [8.509 mm]) 105004-15 (0.015 inch [0.381 mm])
104468-3 (0.3750 inch [9.525 mm])

Two Blade Propeller P/N 104468-( ) Stainless Steel Bumper

and P/N 105004-( ) Stainless Steel Shim Sizes
Table 7-2

ASSEMBLY 61-10-01 Page 7-24

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Space Between Fork Pocket & Shank Bumper(s) + Shim(s)

0.3350 104468-2
0.3375
0.3400
0.3425
0.3450
0.3475 104468-2 +105004-013
0.3500 104468-2 +105004-015
0.3525
0.3550 104468-1
0.3575
0.3600 104468-2 +105004-013 +105004-013
0.3625 104468-2 +105004-013 +105004-015
0.3650 104468-2 +105004-015 +105004-015
0.3675 104468-1+105004-013
0.3700 104468-1+105004-015
0.3725 104468-2 +105004-013 +105004-013 +105004-013
0.3750 104468-3
0.3775 104468-2 +105004-013 +105004-015 +105004-015
0.3800 104468-1+105004-013 +105004-013
0.3825 104468-1+105004-013 +105004-015
0.3850 104468-1+105004-015 +105004-015
0.3875 104468-3 +105004-013
0.3900 104468-3 +105004-015
0.3925 104468-1+105004-013 +105004-013 +105004-013
0.3950 104468-1+105004-013 +105004-013 +105004-015
0.3975 104468-1+105004-013 +105004-015 +105004-015
0.4000 104468-3 +105004-013 +105004-013
0.4025 104468-3 +105004-013 +105004-015
0.4050 104468-3 +105004-015 +105004-015
0.4075
0.4100
0.4125 104468-3 +105004-013 +105004-013 +105004-013
0.4150 104468-3 +105004-013 +105004-013 +105004-015
0.4175 104468-3 +105004-013 +105004-015 +105004-015
0.4200 104468-3 +105004-015 +105004-015 +105004-015

Two Blade Propeller Bumper Plus Shim Relative Sizes

Table 7-3

ASSEMBLY 61-10-01 Page 7-24.1

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(This page intentionally blank.)

ASSEMBLY 61-10-01 Page 7-24.2

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(5) Tighten the nuts (420) until snug. Do not torque the nuts (420) at this time.
(6) Three Blade Bantam Propeller Determination of Shimming of the Fork
Bumpers (520) Only
(a) Using the spring compressor TE548, position the fork (710) in the center
of the hub parting line.
(b) Do not apply pressure on the blades.
(c) Using a feeler gauge, insert the feeler gauge through the holes in the
cylinder-side hub half and insert the feeler gauge between the fork
bumper (520) and the blade butt. Refer to Figure 7-10.
(d) Make a note of the thickest feeler gauge that will fit.
(e) Shim accordingly to produce a thickness value of 0.003 inch (0.076 mm)
to 0.005 inch (0.12 inch) for the proper blade response.
1 Refer to Table 7-1 for the appropriate shim (530) size.

NOTE: Table 7-1 is for reference only. Tolerances may require a

dash number shim (530) that does not correspond with the
tables.
(f) Blade play should meet the appropriate blade tolerances. Refer to
Table 8-2, Blade Tolerances in the Fits and Clearances chapter of this
manual.
(g) If blade play cannot be achieved within the permitted limits, contact the
Hartzell Propeller Inc. Product Support Department
(h) Repeat the procedure to determine the correct shim (530) for each blade.
(7) Blade Angle Check
(a) Using the spring compressor TE548, turn the pull rod TE-548-2 until the
blade angle is at the low pitch blade angle specified for the propeller
assembly.
(b) Using blade pitch fixture TE438, measure the blade angles at the
30 inch (762 mm) radius of all of the blades.
(c) If the blade angle differs more than 0.2 degree between blades, make
note of the position of the blade that does not meet the specified limits.
(d) If required, correct any blade angle split when shimming the fork
bumpers (520).
(8) Shimming of the Fork Bumpers (520) and Blade Angle Correction
(a) Remove the bolts (400), washers (410), and nuts (420) that attach the
cylinder-side hub half.
(b) While firmly holding the outer bearing race (640) over the balls (610)
and ball spacers (620), remove each blade.

ASSEMBLY 61-10-01 Page 7-25

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(c) Remove each fork bumper (520).

CAUTION: SHIMMING TOO TIGHT CAN CAUSE INCORRECT PITCH

CHANGE OF THE PROPELLER.
(d) Install the correct shim (530) thickness in the fork bumper slot in the
fork (710).
1 Refer to Table 7-1, Table 7-2, and Table 7-3 for the appropriate
shim (530) size.

NOTE: Table 7-1, Table 7-2, and Table 7-3 are for reference only.
Tolerances may require a dash number shim (530) that
does not correspond with the tables.
2 For a three blade Bantam propeller only:
a Both shims (530) for each blade socket must be the same part
number.
b The shims (530) from one blade socket to another blade
socket may be different part numbers.
(e) Blade play should meet the appropriate blade tolerances. Refer to
Table 8-2, Blade Tolerances in the Fits and Clearances chapter of this
manual.
(f) If blade play cannot be achieved within the permitted limits, contact the
Hartzell Propeller Inc. Product Support Department
(g) Repeat the procedure to determine the correct shim (530) for each blade.
(h) Install each fork bumper (520) in the fork bumper slot in the fork (710).
(i) If the blade angle differs more than 0.2 degree between blades, rotate
one or more of the pitch change block units (500).
1 Pitch change block units (500) must be installed in the fork (710) with
the thin wall toward the engine-side hub half during initial assembly.
2 Rotating the pitch change block unit (500) 180 degrees will
decrease the pitch of the corresponding blade 0.3 to 0.4 degree on
a tractor propeller.
3 Rotating the pitch change block unit (500) 180 degrees will
increase the pitch of the corresponding blade 0.3 to 0.4 degree on
a pusher propeller.
(j) Firmly holding the outer bearing race (630) over the balls (610) and ball
spacers (620), install the blade in the hub.
1 Install the number one blade assembly into the socket of the
engine-side hub half.
2 Install the pitch change knob in the pitch change block unit (500).

ASSEMBLY 61-10-01 Page 7-26

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3 Rotate the blade into the blade socket.

4 Make sure that the blade O-ring (600) is evenly seated around the
blade and in the hub O-ring groove.
(k) Install the cylinder-side hub half.
(l) Install bolts (400), washers (410), and nuts (420) in the hub on opposite
sides of the blade.
1 For a two blade hub:
a Install 2 bolts (400), 4 washers (410), and 2 nuts (420)
2 For a three blade hub:
a Install 3 bolts (400), 6 washers (410), and 3 nuts (420)
(m) Tighten the nuts (420) until snug. Do not torque the nuts at this time.
(9) Make sure that the blades rotate freely.
(a) If the blades do not rotate freely, check the blade O-rings (600) for
friction or binding.
(10) Repeat section 3.F.(6), "Three Blade Bantam Propeller Determination of
Shimming of the Fork Bumpers (520) Only".
(11) Repeat the Blade Angle Check
(a) If there is more than 0.2 degree difference between blades that cannot
be corrected, contact the Hartzell Propeller Inc. Product Support
Department.
(12) Perform a Blade Play Check
(a) Using light pressure, check blade end-play. Make sure that the
maximum permitted blade end-play is within the limits specified in
Table 8-2, Blade Tolerances in the Fits and Clearances chapter of this
manual. Refer to Figure 8-2, Blade Play in the Fits and Clearances
chapter of this manual.
(b) Using light pressure, check blade fore-and-aft play. Make sure that the
maximum permitted blade fore-and-aft play is within the limits specified
in Table 8-2, Blade Tolerances in the Fits and Clearances chapter of this
manual.
(c) Check the blade track. Refer to the Fits and Clearances chapter in this
manual for blade track limits.
(d) If blade end-play, fore-and-aft play, or blade track is greater than
the limits specified in Table 8-2, Blade Tolerances in the Fits and
Clearances chapter of this manual, perform the steps in section 3.F.(8),
"Shimming of the Fork Bumpers (520) and Blade Angle Correction"
using the next thickest shim (530).

ASSEMBLY 61-10-01 Page 7-27

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Cylinder Side Hub Sealant CM257

TI-401-0015

NOTE: Three Blade Hub Shown for Reference

Application of Sealant on the Cylinder-Side Hub Half

Figure 7-11

ASSEMBLY 61-10-01 Page 7-28

Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
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(e) Repeat until blade end-play, fore-and-aft play, or blade track is within
the permitted limits.
(f) If blade end-play, fore-and-aft play, or blade track cannot be achieved
within the permitted limits, contact the Hartzell Propeller Inc. Product
Support Department.
(13) Installation of the Cylinder-Side Hub Half - Refer to Figure 7-11.

WARNING: ADHESIVES AND SOLVENTS ARE FLAMMABLE AND TOXIC

TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND
EYE PROTECTION ARE REQUIRED. AVOID PROLONGED
CONTACT AND BREATHING OF VAPORS. USE SOLVENT
RESISTANT GLOVES TO MINIMIZE SKIN CONTACT AND
WEAR SAFETY GLASSES FOR EYE PROTECTION. USE
IN A WELL VENTILATED AREA AWAY FROM SPARKS AND
FLAME. READ AND OBSERVE ALL WARNING LABELS.

CAUTION: HUB MATING SURFACES MUST BE CLEAN AND FREE OF

ALL CONTAMINANTS TO PERMIT SEALING OF THE HUB
PARTING LINE.
(a) Using solvent CM106 or CM11, clean the cylinder-side and engine-side
hub mating surfaces.
(b) Permit the solvent CM106 or CM11 to dry.

CAUTION: SEALANT CM257 HAS A TACK TIME OF SIX (6) MINUTES.

(c) Apply sealant CM257 to the cylinder-side and engine-side hub mating
surfaces.
1 Spread the sealant CM257 to achieve complete coverage of the
cylinder-side and engine-side hub mating surfaces.
2 The sealant CM257 must be a smooth, thin, even layer over the
entire cylinder-side and engine-side hub mating surfaces.
3 Do not permit the sealant CM257 to enter any of the hub clamping
bolt holes.
4 Do not permit excess sealant CM257 to enter the blade O-ring
groove.
(d) Within six (6) minutes of applying the sealant CM257, use the six hub
clamping bolts (400), six nuts (420), and six washers (410) to attach the
cylinder-side hub half to the engine-side hub half.
(e) Using an alternating sequence, torque the hub clamping bolts (400) in
accordance with the Table 8-1, Torque Values in the Fits and Clearances
chapter of this manual.
(f) Cycle the propeller from low pitch to high pitch 2 or 3 cycles to seat all
O-rings.

ASSEMBLY 61-10-01 Page 7-29

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TE510

Pitch Change Rod

(240)

TI-401-0016

NOTE: Three Blade Hub Shown for Reference

Installation of the 104506 Plug Assembly

Figure 7-12

ASSEMBLY 61-10-01 Page 7-30

Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
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G. Propeller Balance

NOTE: Specific Hartzell Propeller Inc. manuals and service documents are
available on the Hartzell website at www.hartzellprop.com. Refer to the
Required Publications section in the Introduction chapter of this manual for
the identification of these publications.
(1) Put the cylinder (70) on the hub (430).
(2) Install the balance ring (90) on the cylinder (70).
(3) Using lubricant CM12, lightly lubricate the O-rings (60).
(4) Install an O-ring (60) on each screw (50).
(5) Using screws (50) with O-rings (60) installed in the through drilled holes,
install the cylinder (70) on the cylinder-side hub half.
(6) Tighten but do not torque the screws (50)
(7) Install the set screw low pitch stop (250) in the cylinder (70).
(8) Using the set screw low pitch stop (250), set the approximate low pitch
specified in Hartzell Propeller Inc. Application Guide 159 (61-00-59).
(9) Tighten the set screw low pitch stop (250) but do not torque at this time.
(10) Perform static balance of the propeller in accordance with the Static and
Dynamic Balance chapter of Hartzell Propeller Inc. Standard Practices
Manual 202A (61-01-02).

H. Sealant Cure

WARNING: ADHESIVES AND SOLVENTS ARE FLAMMABLE AND TOXIC TO

THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE
PROTECTION ARE REQUIRED. AVOID PROLONGED CONTACT
AND BREATHING OF VAPORS. USE SOLVENT RESISTANT
GLOVES TO MINIMIZE SKIN CONTACT AND WEAR SAFETY
GLASSES FOR EYE PROTECTION. USE IN A WELL VENTILATED
AREA AWAY FROM SPARKS AND FLAME. READ AND OBSERVE
ALL WARNING LABELS.
(1) Permit the sealant CM257 to cure for a minimum of 12 hours.

I. Leak Check the Hub

(1) Apply an index mark on the cylinder (70), balance ring (90), and hub (430).
(2) Remove the set screw low pitch stop (250) from the cylinder (70).
(3) Remove and retain the screws (50) with the O-rings (60).
(4) Remove the cylinder (70) and balance ring (90) from the hub (430).

ASSEMBLY 61-10-01 Page 7-31

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NOTE: Three Blade Hub

Shown for Reference

TE506

Oil Level Check

Screw (50) with
O-ring (60)

TE507

TI-401-0017

Leak Check
Figure 7-13

ASSEMBLY 61-10-01 Page 7-32

Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
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(5) Put the spring compressor pull rod TE548-2 through the pitch change
rod (240).
(6) Turn the spring compressor pull rod TE548-2 into the spring compressor
extension TE548-2.
(7) Using the spring compressor pull rod TE548-2, cycle the propeller from low
pitch to high pitch for two or three cycles.
(8) Remove the spring compressor pull rod TE548-2.
(9) Make sure that the O-ring C-3317-006 is installed on the plug assembly
TE510.
(10) Using lubricant CM12, lightly lubricate the O-ring C-3317-006 on the plug.
(11) Install the plug assembly TE510 in the pitch change rod (240). Refer to
Figure 7-12.
(12) Using lubricant CM12, lightly lubricate the O-ring (80).
(13) Install the O-ring (80) on the cylinder (70).
(14) Put the cylinder (70) on the hub (430).
(15) Align the index mark on the balance ring (90) to the cylinder (70) and the
cylinder-side hub half.
(16) Using three screws (50) with O-rings (60) installed in the through drilled
holes, install the cylinder (70) on the cylinder-side hub half.
(17) Tighten but do not torque the screws (50).
(18) Install the leak check manifold TE506 with adapter TE507 to the cylinder (70)
as shown in Figure 7-13.
(19) Apply 50 - 55 PSI (3.44 - 3.79 Bar) air pressure through the leak check
manifold TE506.
(20) Permit the pressure to stabilize.
(21) After air pressure has stabilized, a maximum drop of 3 PSI (0.21 Bar) is
permitted in a two minute period.
(22) If the pressure drops more than 3 PSI (0.21 Bar), reapply air pressure and
using leak detector CM122 troubleshoot the leak.
(23) If the pressure drops less than 3 PSI (0.21 Bar), remove the leak check
manifold TE506 and adapter TE507.
(24) Remove and retain the screws (50) with the O-rings (60) installed.
(25) Remove the cylinder (70) with O-ring (80) and the balance ring (90).
(26) Remove the plug assembly TE510 from the pitch change rod (240).

ASSEMBLY 61-10-01 Page 7-33

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NOTE: Three Blade Hub Shown for Reference

Piston (210)

Piston Nut (200)

TI-401-0009

Piston Installation
Figure 7-14

ASSEMBLY 61-10-01 Page 7-34

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NOTE: Three Blade Hub Shown for Reference

Low Pitch Stop (250)

Low Pitch Stop
Jam Nut (10)

Cylinder (70)

TI-401-0014

Low Pitch Stop Installation

Figure 7-15

ASSEMBLY 61-10-01 Page 7-35

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J. Cylinder Installation
(1) If applicable, install the high pitch stop (75) on the pitch change rod, on the
cylinder side hub half with the ID chamfer to the hub.
(2) If applicable, install the washer (260) on the pitch change rod (240).

WARNING: ADHESIVES AND SOLVENTS ARE FLAMMABLE AND TOXIC TO

THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE
PROTECTION ARE REQUIRED. AVOID PROLONGED CONTACT
AND BREATHING OF VAPORS. USE SOLVENT RESISTANT
GLOVES TO MINIMIZE SKIN CONTACT AND WEAR SAFETY
GLASSES FOR EYE PROTECTION. USE IN A WELL VENTILATED
AREA AWAY FROM SPARKS AND FLAME. READ AND OBSERVE
ALL WARNING LABELS.
(3) The Bantam propeller is an oil-filled design. The propeller hub contains a
red-dyed oil.
(a) For a two blade Bantam propeller:
(1) Mix 1.6 ml of red dye CM210 with 250 ml oil CM302.
(b) For a three blade Bantam propeller:
(1) Mix 1.6 ml of red dye CM210 with 200 ml oil CM302.
(c) Pour red-dyed oil through the holes in the cylinder-side hub half.
(4) Using lubricant CM12, lightly lubricate the ID piston O-ring (230).
(5) Install the ID piston O-ring (230) in the piston (210) O-ring groove.
(6) Using lubricant CM12, lightly lubricate the OD piston O-ring (220).
(7) Install the OD piston O-ring (230) in the piston (210) O-ring groove.
(8) Install the piston (210) on the pitch change rod (240). Refer to Figure 7-14.
(9) Install the piston nut (200) on the pitch change rod (240). Refer to
Figure 7-14.
(10) Torque the nut (200) in accordance with the Table 8-1, Torque Values, in the
Fits and Clearances chapter of this manual.
(11) Using lubricant CM12, lubricate the O-ring (80) that is on the cylinder (70).
(12) Install the cylinder (70) with O-ring (80) onto the cylinder-side hub half. Refer
to Figure 7-15.
(13) Align the index mark on the balance ring (90) to the cylinder (70) and the
cylinder-side hub half and install the balance ring on the cylinder.
(14) Apply threadlocker CM116 to the threads of the three oil level screws (50).
(15) Install the three oil level check screws (50) with O-rings (60) in the through
drilled holes to attach the balance ring (90) and cylinder (70).

ASSEMBLY 61-10-01 Page 7-36

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(16) Install six screws (40) in the blind holes to attach the balance ring (90) and
cylinder (70).
(17) Torque the screws (40 and 50) in an alternating sequence in accordance with
Table 8-1, Torque Values, in the Fits and Clearances chapter of this manual.
(18) Apply adhesive CM21 to the threads of the set screw low pitch stop (250).
(19) Install the set screw low pitch stop (250) in the cylinder (70).
(20) Install the seal washer (20) on the low pitch stop (250).
(21) Install the low pitch jam stop nut (10) on the set screw low pitch stop (250).
Refer to Figure 7-15.
(22) Verify the low pitch stop angle.
(a) Rotate the blades to the low pitch position and set the propeller pitch in
accordance with the aircraft Type Certificate Data Sheet.
(b) Adjust the low pitch blade angle with the low pitch stop screw (250).

NOTE: To increase pitch, turn the low pitch stop clockwise. To decrease
pitch, turn the low pitch stop counterclockwise.
(23) Holding the low pitch stop screw (250) in place with an Allen wrench, torque
the low pitch stop jam nut (10) in accordance with Table 8-1, Torque Values.
(24) Perform final check of the low pitch blade angle.
(25) If applicable, install the O-ring (950) and forward bulkhead mount (960)
in accordance with the instructions in the applicable Hartzell Propeller Inc.
Owner's manual. Refer to the Introduction chapter of this manual for a list of
the applicable publications.

4. Propeller Disassembled for Shipping

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY

INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.

A. General
(1) A propeller disassembled for shipping has had one or more blades removed
from the propeller after assembly. The propeller was fully assembled,
inspected, and statically balanced before blade removal and shipping.
(2) A propeller disassembled for shipping must be assembled by properly
rated personnel trained in accordance with Hartzell Propeller Inc. propeller
manuals.

ASSEMBLY 61-10-01 Page 7-37

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(3) For additional general assembly information, refer to the General section at
the beginning of this chapter.

B. Preparing the Propeller for Shipping

NOTE 1: New hardware was installed during propeller assembly for shipping. When
disassembling a propeller for shipping, it is not necessary to discard
hardware that would require replacement at overhaul.

NOTE 2: New O-rings have been installed during propeller assembly for shipping.
During propeller disassembly for shipping, it is not necessary to replace
O-rings unless damaged during component installation or removal.
(1) Before removal, make a mark to indicate alignment of each blade assembly
to hub, fork unit to hub, spinner bulkhead to hub, cylinder to hub, balance
ring to cylinder, and balance weight location on the balance ring. Refer to
the Marking Before Disassembly section in the Disassembly chapter of this
manual.
(2) Before removal, make a mark to indicate position and orientation of each
pitch change block unit (500) in the pitch change fork unit.
(3) Remove all balance weight screws (800), nuts (820), washers (830), and
balance weights (840) from the balance ring (90).
(4) Disconnect the electric de-ice lead wires from the hub and bulkhead, if
applicable.
(5) Disassemble the propeller to the point of blade removal. Refer to the
Propeller Disassembly section in the Disassembly chapter of this manual.
(6) Propeller Reassembly with Blades Removed for Shipping
(a) When reassembling the propeller with the blades removed, do not
accomplish procedures related to blade installation or setting of blade
angles.

NOTE: The pitch change block units (500) may be taped in place in the
pitch change fork (710).
(b) Reassemble the propeller without the blade assemblies. Refer to the
Assembly section in this chapter.
(c) Perform leak check in accordance with this chapter.
(7) Packing the Propeller and Blades for Shipping
(a) Refer to the Packaging and Storage chapter of Hartzell Propeller
Standard Practices Manual 202A (61-01-02), for packing the propeller
and blades for shipping.
(b) Pack the propeller without blades for shipping.

ASSEMBLY 61-10-01 Page 7-38

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(c) Pack the blades for shipping with the blade O-ring (600) and grease on
each blade shank.

5. Reassembly of a Propeller Disassembled for Shipping

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY

INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.

A. Unpacking the Propeller and Blades

(1) Carefully unpack the propeller and blades from shipping.
(2) Visually inspect each propeller component for shipping damage.
(a) If damage is found, refer to the Check chapter of this manual for the
inspection, serviceable limits, and corrective action criteria for the
specific component.
(b) If damage is found to a blade, refer to Hartzell Propeller Inc. Composite
Blade Manual 135F (61-13-35).

B. Preparing Propeller for Reassembly

NOTE 1: New hardware was installed during propeller assembly for shipping. When
disassembling a propeller from shipping, it is not be necessary to discard
hardware that would require replacement at overhaul.

NOTE 2: New O-rings have been installed during propeller assembly for shipping.
During propeller disassembly from shipping, it is not necessary to replace
O-rings, unless they were damaged during component installation or
removal.
(1) Make sure that the alignment marks have been made for each blade
assembly to hub, fork unit to hub, spinner bulkhead to hub, cylinder to hub,
balance ring to cylinder, and balance weight location on the balance ring.
(2) Remove all balance weight screws (800), nuts (820), and balance
weights (810).

C. Propeller Reassembly
(1) Reassemble the propeller in accordance with the Assembly instructions in
this chapter.
(2) Reconnect the electric de-ice lead wires to the bulkhead, if applicable.

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FITS AND CLEARANCES -CONTENTS

1. Torque Values........................................................................................................... 8-4

LIST OF FIGURES
Determining Torque Value of a Standard
Torque Wrench with Adaptor............................................................ Figure 8-1.............. 8-3
Blade Play............................................................................................. Figure 8-2.............. 8-6

LIST OF TABLES
Torque Values.........................................................................................Table 8-1.............. 8-5
Blade Tolerances....................................................................................Table 8-2.............. 8-7

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APS0212B

Torquing Adapter
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 adapter)
actual torque

EXAMPLE:
reading on torque
100 Ft-Lb (136 N•m) x 1 ft (304.8 mm) = 66.7 Ft-Lb wrench with 6-inch
1 ft (304.8 mm) + 0.50 ft (152.4 mm) (90.1 N•m) (152.4 mm) adapter
for actual torque of
100 Ft-Lb (136 N•m)

The correction shown is for an adapter that is aligned with the centerline of the
torque wrench. If the adapter is angled 90 degrees relative to the torque wrench
centerline, the torque wrench reading and actual torque applied will be equal.

Determining Torque Value of a Standard Torque Wrench with Adaptor

Figure 8-1

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1. Torque Values

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY

INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.

A. Threaded fasteners and hardware are the weakest components in an assembly.

(1) Vibration can cause an incorrectly tightened fastener to fail in a matter of
minutes.
(2) Correct tension in a fastener depends on a variety of known load factors and
can influence fastener service life.
(3) Correct tension is achieved by application of measured torque.

B. Use accurate wrenches and professional procedures to make sure of correct

tensioning.

C. For the torque values to use when assembling a Hartzell Propeller Inc. propeller,
refer to Table 8-1, Torque Values in this chapter.

D. When an adapter is used with a torque wrench, use the equation in Figure 8-1 to
determine the correct torque value.

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CAUTION 1: TORQUE VALUES ARE BASED ON NON-LUBRICATED THREADS,

UNLESS SPECIFIED IN TABLE 8-1.

CAUTION 2: FOR TORQUE READING WHEN USING A TORQUE WRENCH ADAPTER,

REFER TO FIGURE 8-1.

NOTE: Torque tolerance is ± 10 percent unless otherwise noted.

Item Part Description Torque Ft-Lb Torque In-Lb Torque N•m

No. Number

10 A-2043-1 Low Pitch Stop Nut 15 20.3

40 A-2626-2 Screw, Balance Ring Attaching 60 6.7

50 104578 Screw, Oil Level Check 60 6.7

200 A-1373 Nut/Piston Rod 20 27.11

420 A-2043-1 Hub clamping nut 30 41

Torque Values
Table 8-1

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NOTE: Refer to Table 8-2, Blade Tolerances

Fore and Aft Play

In and Out Play

Radial Play

Blade End Play

TI-411-026

Blade Play
Figure 8-2

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Tolerances Affecting the Blades

In-and-Out Blade Play None permitted

End Play (leading edge to trailing edge) ± 0.09 inch (2.28 mm)
0.19 inch (4.82 mm) total

Fore-and-Aft (Face to camber)

± 0.19 inch (4.82 mm)
0.38 inch (9.65 mm) total

Radial Play (pitch change) ± 0.5 degree (1 degree total)
measured at reference station

Blade Track - Composite Blades ± 0.125 inch (3.18 mm)

or 0.250 inch (6.35 mm) total

Blade Pitch Setting Tolerance 0.2 degree

Between Blades at Low Pitch

NOTE: Blades are intended to be tight in the

propeller; however, slight movement is
acceptable. Blades with excessive movement
should be referred to a certified propeller
repair station with the appropriate rating.

Blade Tolerances
Table 8-2

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SPECIAL TOOLS, 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. General............................................................................................................... 9-3
B. Special Tools....................................................................................................... 9-5

LIST OF FIGURES

Tooling for Pitch Change Rod to Fork................................................... Figure 9-1.............. 9-4

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1. Minimum Facility and Tooling Requirements

A. Tooling
(1) Propeller repair stations certified by the FAA or international equivalent to
overhaul Hartzell Propeller Inc. propellers are expected to possess precision
fixtures, tools, and blade tables for blade inspection and repair.
(a) Except as specifically required in this manual, locally fabricated tooling
is acceptable for most repair and inspection operations.

B. Facilities
(1) Grinding, plating, and painting of propeller components have the potential for
health and safety hazards beyond that of other areas of a typical workshop.
(a) It is expected that such areas be in compliance with industry standards
and governmental regulations concerning occupational safety and
health, as well as environmental protection.
(2) Workshop areas need to be segregated to prevent contamination.
(a) Separate areas should be designated for cleaning, inspection, painting,
plating, and assembly.
(b) Propeller balancing must be performed in a draft free area.

2. Special Tools

A. General

NOTE: Specific Hartzell Propeller Inc. manuals and service documents are
available on the Hartzell website at www.hartzellprop.com. Refer to the
Required Publications section in the Introduction chapter of this manual for
the identification of these publications.
(1) While Hartzell Propeller Inc. does not maintain an exact list of standard tools
used in repair or servicing of our propellers, Hartzell Propeller Inc. frequently
requires the use of special tools during servicing, repair, or overhaul.
(a) The applicable overhaul manual and Hartzell Propeller Inc. Illustrated
Tool and Equipment Manual 165A (61-00-65) provide this necessary
tooling information.
(b) It is the responsibility of the repair station or the technician performing
the repair or servicing to use these special tools as required.

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Press
Locally Fabricated Tooling to
Prevent Damage to End of
Pitch Change Rod

Larger diameter than 0.75

inches (19.05 mm)

Flat on both sides

Locally Fabricated
Pitch Change Rod (240) Tooling to Support the
Fork (710)

Minimum length of
4.0 inches (101.9 mm)

Minimum OD of
0.750 inch (19.05 mm)
Fork (710) diameter

Maximum OD of
1.20 inches (30.48 mm)

Minimum ID of 0.60 inch

(15.24 mm)

TI-401-0005

Tooling for Pitch Change Rod to Fork

Figure 9-1

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B. Special Tools

NOTE: Specific Hartzell Propeller Inc. manuals and service documents are
available on the Hartzell website at www.hartzellprop.com. Refer to the
Required Publications section in the Introduction chapter of this manual for
the identification of these publications.
(1) Hartzell Propeller Inc. Illustrated Tool and Equipment Manual 165A (61-00-65)
contains a listing of special tools.
(2) Tooling for Pitch Change Rod (240) to Fork (710)
(a) This locally fabricated tooling is the same tooling that will be used to
assemble the washer (260), fork (710), and pitch change rod (240).
(b) Locally fabricate tooling to support the fork (710) and to protect the ends
of the pitch change rod (240).
1 The support for the fork (710) must be a minimum length of
4.0 inches (101.9 mm).
2 The support for the fork (710) must have a minimum ID of 0.60 inch
(15.24 mm) diameter.
3 The support for the fork (710) must have a minimum OD of
0.750 inch (19.05 mm) diameter and a maximum OD of 1.20 inches
(30.48 mm).
4 The support for the fork (710) must be stable enough to support the
fork (710) parallel to the surface of the press.
(c) The tooling to press the pitch change rod (240) must have a diameter
larger than 0.75 inch (19.05 mm) and flat on both sides.

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ILLUSTRATED PARTS LIST - CONTENTS

1. Introduction...........................................................................................................10-3
2. The Illustrated Parts List.......................................................................................10-5
A. Detailed Parts List........................................................................................... 10-5
B. Revisions......................................................................................................... 10-7
C. Vendors........................................................................................................... 10-8

LIST OF FIGURES

Two Blade Propeller Exploded View............................................Figure 10-1.................. 10-9

Three Blade Propeller Exploded View,
Except 3A1-G353A2(L)X( )....................................................Figure 10-2................ 10-10
Three Blade Propeller Exploded View,
3A1-G353A2(L)X( )................................................................Figure 10-3................ 10-11
Blade Retention System Exploded View.....................................Figure 10-4................ 10-12
Two Blade Hub Assembly Exploded View...................................Figure 10-5................ 10-13
Three Blade Hub Assembly Exploded View,
Except 3A1-G353A2(L)X( )....................................................Figure 10-6................ 10-14
Three Blade Hub Assembly Exploded View
3A1-G353A2(L)X( )................................................................Figure 10-7................ 10-15

TWO BLADED PROPELLER PARTS

2A1-HP275A1............................................................................................................... 10-16

THREE BLADED PROPELLER PARTS

3A1-G353A2(L)X( )....................................................................................................... 10-18
3A1-QP460A4X( )......................................................................................................... 10-20
3A1-TP724A1................................................................................................................ 10-22

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1. Introduction

WARNING: ANY PART IDENTIFIED IN THIS MANUAL AS AN EXPERIMENTAL

OR NON-AVIATION PART MUST NOT BE USED IN AN FAA OR
INTERNATIONAL EQUIVALENT TYPE CERTIFICATED PROPELLER.
A PART IDENTIFIED AS EXPERIMENTAL OR NON-AVIATION DOES
NOT HAVE FAA OR INTERNATIONAL EQUIVALENT APPROVAL.
USE ONLY THE APPROVED ILLUSTRATED PARTS LIST PROVIDED
IN THE APPLICABLE OVERHAUL MANUAL OR ADDITIONAL
PARTS APPROVED BY AN FAA ACCEPTED DOCUMENT FOR
ASSEMBLY OF A PROPELLER. THE OPERATOR ASSUMES ALL RISK
ASSOCIATED WITH THE USE OF EXPERIMENTAL PARTS. USE OF
EXPERIMENTAL PARTS ON AN AIRCRAFT MAY RESULT IN DEATH,
SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY
DAMAGE.

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS CHAPTER MAY

INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE
INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION
ABOUT PROPELLER CRITICAL PARTS. REFER TO THE
ILLUSTRATED PARTS LIST IN THIS MANUAL FOR IDENTIFICATION
OF PROPELLER CRITICAL PARTS.
A. This manual is intended to be the primary source of maintenance and overhaul
information for the Bantam propeller models. The propeller models addressed in this
manual may be Type Certificated by the FAA, or may be experimental. Always use
the current illustrated parts list for the assembly of any propeller. Always refer to the
aircraft Type Certificate (TC) or Supplemental Type Certificates (STC) to determine
installation eligibility of any propeller. If installation eligibility is not identifiable, an
additional installation approval, such as FAA form 337 field approval or Supplemental
Type Certificate may be required. If in doubt, contact the Hartzell Propeller Inc.
Product Support Department.
B. General
(1) This Illustrated Parts List contains all of the current configurations for the
specified propellers manufactured by Hartzell Propeller Inc. included in this
manual and supersedes any prints that may have previously been supplied for
part and assembly information. The parts lists contained within the Illustrated
Parts List are to be used to make sure of the configuration of propeller models
and ordering parts.

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CAUTION: ILLUSTRATIONS IN THE ILLUSTRATED PARTS LIST ARE TO BE

USED FOR IDENTIFYING PARTS AND SHOULD NOT BE USED AS
A MAINTENANCE REFERENCE FOR ASSEMBLY.
(2) Figures are for reference only. The figures provide general views of parts.
For ease of illustration, typical views of some parts were created and shown
in multiple figures. For this reason, illustrated parts may not exactly reflect
parts contained in some propeller assemblies.
C. Using the Illustrated Parts List
(1) Every effort has been made to include all of the applicable propellers and
configurations manufactured by Hartzell Propeller Inc. If a repair station has
questions about a propeller configuration as stated in the Illustrated Parts List,
contact the Hartzell Propeller Inc. Product Support Department.
(2) Basic Propeller Parts: Refers to all of the propeller components that may be
unique to a particular propeller model.
(3) ( )-Flange Parts: Refers to the type of flange parts used on a particular
propeller model.
(4) Balance Parts: These components are common to all Bantam propellers.
D. Propeller Assemblies Configured with an Ice Protection System
(1) If the propeller is equipped with an ice protection system that uses components
supplied by Hartzell Propeller Inc., applicable instructions and technical
information for the components supplied by Hartzell Propeller Inc. can be found
in the following publication available on the Hartzell Propeller Inc. website at
www.hartzellprop.com:
(a) Hartzell Propeller Inc. Manual 180 (30-61-80) - Propeller Ice Protection
System Manual
(2) Propeller ice protection system components not supplied by Hartzell Propeller
Inc. are controlled by the applicable TC or STC holder’s Instructions for
Continued Airworthiness (ICA).

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2. The Illustrated Parts List

A. Detailed Parts List
(1) The Detailed Parts List consists of the Figure/Item Number (Fig./Item Number),
Part Number, Description, Effectivity Code (EFF Code), Units Per Assembly
(UPA), Overhaul (O/H), and Propeller Critical Parts (PCP). Space is reserved
for the Airline Stock Number (Airline Stock No.). The following is an explanation
of each column.
(a) Fig/Item Number
1 Figure Number refers to the illustration where items appear. Item
Numbers are assigned in broken sequence to allow the insertion
of subsequent additional parts. Items listed but not illustrated are
identified by a dash to the left of the item number.
2 Alpha variants will be used to add additional items. There are two
reasons for the use of alpha variants:
a A part may have an alternate, or may be superseded, replaced,
or obsoleted by another part. For example, the self locking nut
(A-2043) that is item 10 was superseded by the self locking nut
(A-2043-1) that is item 10A.
b An Illustrated Parts List may contain multiple configurations.
Effectivity codes are used to distinguish different part numbers
within the same list. For example, one configuration may use
a propeller mounting bolt (A-2429-3) that is item 900, yet
another configuration uses a propeller mounting bolt (B-3347)
that is item 900A. Effectivity codes are very important in the
determination of parts in a given configuration.
(b) Part Number
1 Use the Hartzell Propeller Inc. part number when ordering the part
from Hartzell Propeller Inc. or a Hartzell Propeller Inc. approved
distributor. Digits of Hartzell Propeller Inc. Part Numbers have no
significance other than to identify a part.
(c) Airline Stock Number
1 Space is reserved for the Airline Stock Number.

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(d) Description
1 This column identifies the item. The relationship of parts to the
assembly is indicated by the use of indentations. The description in
this column may also contain a Propeller Critical Parts prefix “PCP:”
or a vendor CAGE code, as applicable. Information regarding part
alternative, supersedure, replacement, or obsolecence may also be
found in this column. Refer to Revisions, in this section, for further
information regarding alternate, superseded, replaced, or obsoleted
parts.
(e) Effectivity Code (EFF CODE)
1 The effectivity column shows the prefix and/or suffix of the propeller
model to which the parts apply. In some cases, the specific engine or
aircraft manufacturer may be called out. Effectivity codes assigned
apply only to the figure/listing in which they appear. Parts common to
all end items show no code.
(f) Units Per Assembly (UPA)
1 Designates the total quantity of an item required for the next higher
assembly or subassembly.
(g) Overhaul (O/H)
1 Designates the parts to be replaced at overhaul. A “Y” identifies the
parts that must be replaced at overhaul.

NOTE: An overhaul kit may not contain all the parts identified with
a "Y" for a particular model propeller. An example of parts
that may not be included in the overhaul kit is spinner
mounting parts.
(h) Propeller Critical Part (PCP)
1 This column identifies the Propeller Critical Parts that are contained
in each propeller model. A critical part on the propeller is one
whose primary failure can result in a hazardous propeller effect,
as determined by the safety analysis required by Title 14 CFR
Sec. 35.15. Maintenance and Repair procedures that apply to the
propeller models in this manual have been substantiated based on
Engineering analysis that expects this product will be operated and
maintained using the procedures and inspections provided in the ICA
for this product.

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B. Revisions
(1) Alternate
(a) Alternate parts are identified by the term "ALTERNATE" in the Description
column. Alternate items are considered airworthy for continued flight
and existing stock of parts may be used for maintenance and/or repair.
The new or alternate part numbers may be used interchangeably when
ordering/stocking new parts.
(2) Supersedure
(a) Part changes are identified by the terms “SUPERSEDES ITEM _____” or
­“SUPERSEDED BY ITEM _____” in the Description column. Superseded
items are considered airworthy for continued flight and existing stock of
superseded parts may be used for maintenance and/or repair. Once the
superseding part has been incorporated/installed into an assembly, the
original superseded part may no longer be used. Superseded parts may
no longer be available, and the new part number must be used when
ordering/stocking new parts.
(3) Replacement
(a) Part changes identified by the terms "REPLACES ITEM _____” or
“REPLACED BY ITEM _____” in the Description column are considered
airworthy for continued flight, but must be replaced with a part with the
new part number at overhaul. Existing stock of replaced parts may not
be used for maintenance and/or repair of effected assemblies. Replaced
parts may no longer be available, and the new part number must be used
when ordering/stocking new parts.
(4) Obsolescence
(a) Obsolete parts are identified by "OBS” in the Units Per Assembly (UPA)
column. Obsolete items are considered unairworthy for continued flight.
(5) Service Documents and Airworthiness Directives
(a) In the event of modification or repair of an existing part, the supersedure,
replacement, or obsolescence of a part, or the addition of parts installed
by a Service Bulletin (SB) or Service Letter (SL), the SB or SL number will
appear in the Description column as “SB_____”, or "SL_____” after the
description.

61-10-01
Page 10-7
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

C. Vendors
(1) Many O-rings, fasteners, and other vendor supplied hardware listed in Hartzell
Propeller Inc. manuals have previously been specified with AN, MS, NAS or
vendor part number. To provide internal controls and procurement flexibility,
Hartzell Propeller Inc. has made engineering changes to provide all O-rings,
fasteners, and hardware with a Hartzell Propeller Inc. part number. Parts
shipments from Hartzell Propeller Inc. will specify only the Hartzell Propeller Inc.
part numbers.
(2) Some O-rings, fasteners, and hardware manufactured in accordance with
established industry specifications (certain AN, MS, NAS items) are acceptable
for use in Hartzell Propeller Inc. products without additional standards imposed
by Hartzell Propeller Inc.
(a) For a listing of part number interchangeability, refer to the Vendor
Cross Reference chapter of Hartzell Propeller Inc. Standard Practices
Manual 202A (61-01-02).
(b) Where permitted, both the Hartzell Propeller Inc. part number item and
AN, MS, NAS, and other specified vendor numbers items can be used
interchangeably.
(c) The Hartzell Propeller Inc. part number must be used when ordering these
parts from Hartzell Propeller Inc.

61-10-01
Page 10-8
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

210

200 220
70
240 80
90 230
250
820
830
40

840
900 930
20 430
10
433

60 520 730 910

800 50 920
530
420

410
439
720

710
700

410
400
TI-401-0035

Two Blade Propeller Exploded View

Figure 10-1

61-10-01
Page 10-9
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

220 260
200
240 80
70
820
830
40 250
230
840 210

300
20
310
10

800 60 90
433
50
730 930
720
710
700 420
410

439

430
520

530
TI-401-0027
TI-401-0028

410
400

Three Blade Propeller Exploded View, Except 3A1-G353A2(L)X( )

Figure 10-2

61-10-01
Page 10-10
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

220 260
200
70 240 80
820
830
40 250
230
840 210
800
20

10
420
60 90
410
50
950 960

439 930

720
710
410 700
400

730
430
433
520

530
TI-401-0041
TI-401-0040

Three Blade Propeller Exploded View, 3A1-G353A2(L)X( )

Figure 10-3

61-10-01
Page 10-11
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

600

630

610
620

640

500
TI-401-0029

Blade Retention System Exploded View

Figure 10-4

61-10-01
Page 10-12
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

910
920

900
430 434

437

432

435

433

436 TI-401-0034

Two Blade Hub Assembly Exploded View

Figure 10-5

61-10-01
Page 10-13
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

910
920

900
430

437 432

434

435

433

436
TI-401-0033

Three Blade Hub Assembly Exploded View, Except 3A1-G353A2(L)X( )

Figure 10-6

61-10-01
Page 10-14
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

432
434

430

437

900

435
920

940 910

433

436
TI-401-0038

Three Blade Hub Assembly Exploded View 3A1-G353A2(L)X( )

Figure 10-7

61-10-01
Page 10-15
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

FIG./ITEM PART AIRLINE DESCRIPTION EFF UPA O/H PCP

NUMBER NUMBER STOCK NO. 1 2 3 4 5 6 7 CODE

10-1 2A1-HP275A1( )
10-4
10-5

10 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 1 Y

20 B-6747 • SEAL, WASHER 1 Y
40 A-2626-2 • SCREW, 10-32, CAP 6 Y
50 104578 • SCREW, OIL LEVEL CHECK 2 Y
60 C-3317-002 • O-RING 2 Y
70 105133 • CYLINDER 1
-75 105130-( ) • STOP, HIGH PITCH 1
80 C-3317-153 • O-RING 1 Y
90 105132 • RING, BALANCE 1
200 A-1373 • NUT, 7/16-20, HEX, SELF-LOCKING 1 Y
210 106080 • PISTON 1
220 C-3317-336-1 • O-RING, PISTON OD 1 Y
230 C-3317-112 • O-RING, PISTON ID 1 Y
240 103837-( ) • ROD, PITCH CHANGE 1
250 102472 • SCREW, SET, 3/8-24 (LOW PITCH STOP) 1
400 A-2431 • BOLT, 3/8-24, HEX HEAD 6
410 B-3834-0663 • WASHER 12 Y
420 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 6 Y
430 105021 • PCP:HUB UNIT, 2A1-HP275A1 1 PCP
432 C-3317-021-1 • • O-RING, BUSHING TO HUB 1 Y
433 A-2249 • • HUB BUSHING, GUIDE 1 Y
434 103920 • • HUB BUSHING, ROD ENGINE SIDE 1 Y
435 A-6153-62 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
436 103846 • • HUB BUSHING, ROD CYLINDER SIDE 1 Y
437 A-5839-71 • • RING, RETAINING, INTERNAL SPIRAL 1 Y
-438 B-6142 • • INSERT, 1/4-28, CRES, COILED 4 Y
439 C-3317-111-1 • O-RING, ROD TO BUSHING 1 Y
500 106045 • PITCH CHANGE BLOCK ASSEMBLY 2
-501 106044 • • BLOCK, PITCH CHANGE 1
-502 104954 • • BUSHING 1

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

2A1-HP275A1( )

61-10-01
Page 10-16
ILLUSTRATED PARTS LIST Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

FIG./ITEM PART AIRLINE DESCRIPTION EFF UPA O/H PCP

NUMBER NUMBER STOCK NO. 123 45 6 7 CODE

10-1 2A1-HP275A1( )
10-4
10-5

520 104468-( ) • BUMPER, FORK 2 Y

530 105004-( ) • SHIM, STAINLESS STEEL A/R
600 C-3317-338-8 • O-RING 2 Y
610 B-6144-1 • BALL, BEARING, 3/8" DIA 48 Y
620 104949 • BALL SPACER 48 Y
630 105421 • RACE, HUB SIDE 2
640 105444 • RACE, BEARING, BLADE SIDE 2
700 A-965 • WASHER, 7/16, CRES 1 Y
710 105055 • FORK, TWO BLADE 1
720 103922 • SPRING, COMPRESSION 1
730 103933 • SPRING SEAT 1
800 B-3840-( ) • SCREW, 10-32, FILLISTER HEAD AR Y
820 B-3808-3 • NUT, HEX, SELF-LOCKING AR Y
830 B-3851-0363 • WASHER AR Y
840 104547 • WEIGHT, BALANCE AR
900 A-2429-3 • STUD, MOUNTING, 1/2-20 6 Y
910 A-2044 • NUT, 1/2-20, HEX, SELF-LOCKING, MOUNTING 6 Y
920 A-1381 • WASHER, 1/2" CRES, MOUNTING 6 Y
930 C-3317-225-1 • O-RING, MOUNTING 1 Y
950 C-3317-129 • O-RING, CYLINDER/SPINNER DOME 1 Y

NOTE: SPINNER ASSEMBLIES AND SPINNER

MOUNTING HARDWARE ARE APPLICATION
SPECIFIC. REFER TO HARTZELL
PROPELLER INC. APPLICATION GUIDE
MANUAL 159 (61-02-59) AND HARTZELL
PROPELLER INC. METAL SPINNER
ASSEMBLY MAINTENANCE MANUAL 127
(61-16-27), COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48).

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

2A1-HP275A1( )

Page 10-17
ILLUSTRATED PARTS LIST 61-10-01 Rev. 3 Sep/16
 PROPELLER MAINTENANCE MANUAL
401

FIG./ITEM PART AIRLINE DESCRIPTION EFF UPA O/H PCP

NUMBER NUMBER STOCK NO. 123 45 6 7 CODE

10-3 3A1-G353A2(L)X( )
10-4
10-7

10 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 1 Y

10A B-3359 • NUT, 3/8-24, HEX, SELF-LOCKING 1 Y
ALTERNATE FOR ITEM 10
20 B-6747 • SEAL, WASHER 1 Y
40 A-2626-2 • SCREW, 10-32, CAP 6 Y
50 104578 • SCREW, OIL LEVEL CHECK 3 Y
60 C-3317-002 • O-RING 3 Y
70 104666 • CYLINDER 1
-75 106017-( ) • STOP, HIGH PITCH 1
80 C-3317-154 • O-RING 1 Y
90 104546 • RING, BALANCE 1
200 A-1373 • NUT, 7/16-20, HEX, SELF-LOCKING 1 Y
210 106080 • PISTON 1
220 C-3317-336-1 • O-RING, PISTON OD 1 Y
230 C-3317-112 • O-RING, PISTON ID 1 Y
240 103837 • ROD, PITCH CHANGE 1
250 102472 • SCREW, SET, 3/8-24 (LOW PITCH STOP) 1
260 103906 • WASHER 1
400 A-2431 • BOLT, 3/8-24, HEX HEAD 6
410 B-3834-0663 • WASHER 12 Y
420 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 6 Y
430 104661X • PCP:HUB UNIT, 3A1-G353-A1X 1 PCP
-431 104582 • • PLATE, UID-BLANK 1
432 C-3317-021-1 • • O-RING, BUSHING TO HUB 1 Y
433 A-2249 • • HUB BUSHING, GUIDE 1 Y
434 103844 • • HUB BUSHING, ROD ENGINE SIDE 1 Y
435 A-6153-81 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
436 103846 • • HUB BUSHING, ROD CYLINDER SIDE 1 Y
437 A-5839-71 • • RING, RETAINING, INTERNAL SPIRAL 1 Y
-438 B-6142 • • INSERT, 1/4-28, CRES, COILED 6 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

3A1-G353A2(L)X( )

Page 10-18
ILLUSTRATED PARTS LIST 61-10-01 Rev. 3 Sep/16
 PROPELLER MAINTENANCE MANUAL
401

FIG./ITEM PART AIRLINE DESCRIPTION EFF UPA O/H PCP

NUMBER NUMBER STOCK NO. 123 45 6 7 CODE

10-3 3A1-G353A2(L)X( )
10-4
10-7
439 C-3317-111-1 • O-RING, ROD TO BUSHING 1 Y
500 104955 • PITCH CHANGE BLOCK UNIT 3
-501 104934 • • BLOCK, PITCH CHANGE 1
-502 104954 • • BUSHING 1
520 104763 • BUMPER, FORK 6 Y
530 104940-( ) • SHIM, STAINLESS STEEL A/R
600 C-3317-338-8 • O-RING 3 Y
610 B-6144-1 • BALL, BEARING, 3/8" DIA 72 Y
620 104949 • BALL SPACER 72 Y
630 105421 • RACE, HUB SIDE 3
640 105444 • RACE, BEARING, BLADE SIDE 3
700 A-965 • WASHER, 7/16, CRES 1 Y
710 104919 • FORK, THREE BLADE 1
720 105282 • SPRING, COMPRESSION 1
730 103881 • SEAT, SPRING 1
800 B-3840-( ) • SCREW, 10-32, FILLISTER HEAD 6 Y
820 B-3808-3 • NUT, HEX, SELF-LOCKING 6 Y
840 104547 • WEIGHT, BALANCE 2
900 104606( ) • STUD, MOUNTING, M8 - 1.25 6 Y
910 104339 • NUT, M8 X1.25 MTG, CASTELLATED 6 Y
920 B-3851-0563 • WASHER, MOUNTING 6 Y
930 C-3317-225-1 • O-RING, MOUNTING 1 Y
940 B-3842-0500 • SPRING PIN, 3/32" CRES. 6 Y
950 C-3317-129 • O-RING, CYLINDER/SPINNER DOME 1 Y
960 105330 • MOUNT, FORWARD BULKHEAD 1

NOTE: SPINNER ASSEMBLIES AND SPINNER

MOUNTING HARDWARE ARE APPLICATION
SPECIFIC. REFER TO HARTZELL
PROPELLER INC. APPLICATION GUIDE
MANUAL 159 (61-02-59) AND HARTZELL
PROPELLER INC. METAL SPINNER
ASSEMBLY MAINTENANCE MANUAL 127
(61-16-27) AND COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48)..

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

3A1-G353A2(L)X( )

Page 10-19
ILLUSTRATED PARTS LIST 61-10-01 Rev. 3 Sep/16
 PROPELLER MAINTENANCE MANUAL
401

FIG./ITEM PART AIRLINE DESCRIPTION EFF UPA O/H PCP

NUMBER NUMBER STOCK NO. 123 45 6 7 CODE

10-2 3A1-QP460A4X( )
10-4
10-6

10 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 1 Y

20 B-6747 • SEAL, WASHER 1 Y
40 A-2626-2 • SCREW, 10-32, CAP 6 Y
50 104578 • SCREW, OIL LEVEL CHECK 3 Y
60 C-3317-002 • O-RING 3 Y
70 104577 • CYLINDER 1
80 C-3317-154 • O-RING 1 Y
90 104546 • RING, BALANCE 1
200 A-1373 • NUT, 7/16-20, HEX, SELF-LOCKING 1 Y
210 104255 • PISTON 1
220 C-3317-339-1 • O-RING, PISTON OD 1 Y
230 C-3317-112 • O-RING, PISTON ID 1 Y
240 103837 • ROD, PITCH CHANGE 1
250 102472 • SCREW, SET, 3/8-24 (LOW PITCH STOP) 1
260 103906 • WASHER 1
400 A-2431 • BOLT, 3/8-24, HEX HEAD 6
410 B-3834-0663 • WASHER 12 Y
420 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 6 Y
430 104545X • PCP:HUB UNIT, 3A1-QP460-A1 1 PCP
-431 104582 • • PLATE, UID-BLANK 1
432 C-3317-021-1 • • O-RING, BUSHING TO HUB 1 Y
433 A-2249 • • HUB BUSHING, GUIDE 1 Y
434 103844 • • HUB BUSHING, ROD ENGINE SIDE 1 Y
435 A-6153-81 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
436 103846 • • HUB BUSHING, ROD CYLINDER SIDE 1 Y
437 A-5839-71 • • RING, RETAINING, INTERNAL SPIRAL 1 Y
-438 B-6142 • • INSERT, 1/4-28, CRES, COILED 6 Y
439 C-3317-111-1 • O-RING, ROD TO BUSHING 1 Y
500 104955 • PITCH CHANGE BLOCK UNIT 3
-501 104934 • • BLOCK, PITCH CHANGE 1
-502 104954 • • BUSHING 1

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

3A1-QP460A4X( )

Page 10-20
ILLUSTRATED PARTS LIST 61-10-01 Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

FIG./ITEM PART AIRLINE DESCRIPTION EFF UPA O/H PCP

NUMBER NUMBER STOCK NO. 123 45 6 7 CODE

10-2 3A1-QP460A4X( )
10-4
10-6
520 104763 • BUMPER, FORK 6 Y
530 104940-( ) • SHIM, STAINLESS A/R
600 C-3317-338-8 • O-RING 3 Y
610 B-6144-1 • BALL, BEARING, 3/8" DIA 72 Y
620 104949 • BALL SPACER 72 Y
630 105421 • RACE, HUB SIDE 3
640 105444 • RACE, BEARING, BLADE SIDE 3
700 A-965 • WASHER, 7/16, CRES 1 Y
710 104919 • FORK, THREE BLADE 1
720 105282 • SPRING, COMPRESSION 1
730 103881 • SEAT, SPRING 1
800 B-3840-( ) • SCREW, 10-32, FILLISTER HEAD 6 Y
820 B-3808-3 • NUT, HEX, SELF-LOCKING 6 Y
830 B-3851-0363 • WASHER 6 Y
840 104547 • WEIGHT, BALANCE 2
900 A-2429-3 • STUD, MOUNTING, 1/2-20 6 Y
910 A-2044 • NUT, 1/2-20, HEX, SELF-LOCKING, MOUNTING 6 Y
920 103555 • WASHER, MOUNTING 6 Y
930 C-3317-225-1 • O-RING, MOUNTING 1 Y

NOTE: SPINNER ASSEMBLIES AND SPINNER

MOUNTING HARDWARE ARE APPLICATION
SPECIFIC. REFER TO HARTZELL
PROPELLER INC. APPLICATION GUIDE
MANUAL 159 (61-02-59) AND HARTZELL
PROPELLER INC. METAL SPINNER
ASSEMBLY MAINTENANCE MANUAL 127
(61-16-27), AND COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48).

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

3A1-QP460A4X( )

Page 10-21
ILLUSTRATED PARTS LIST 61-10-01 Rev. 3 Sep/16
 PROPELLER MAINTENANCE MANUAL
401

FIG./ITEM PART AIRLINE DESCRIPTION EFF UPA O/H PCP

NUMBER NUMBER STOCK NO. 123 45 6 7 CODE

10-2 3A1-TP724A1
10-4
10-6
10 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 1 Y
20 B-6747 • SEAL, WASHER 1 Y
40 A-2626-2 • SCREW, 10-32, CAP 6 Y
50 104578 • SCREW, OIL LEVEL CHECK 3 Y
60 C-3317-002 • O-RING 3 Y
70 105218 • CYLINDER 1
-75 105412-( ) • STOP, HIGH PITCH 1
80 C-3317-154 • O-RING 1 Y
90 104546 • RING, BALANCE 1
200 A-1373 • NUT, 7/16-20, HEX, SELF-LOCKING 1 Y
210 104255 • PISTON 1
220 C-3317-339-1 • O-RING, PISTON OD 1 Y
230 C-3317-112 • O-RING, PISTON ID 1 Y
240 103837 • ROD, PITCH CHANGE 1
250 102472 • SCREW, SET, 3/8-24 (LOW PITCH STOP) 1
260 103906 • WASHER 1
300 B-3384-1H • BOLT, 1/4-28, HEX HEAD 6 Y
310 B-3837-0432 • WASHER 6 Y
400 A-2431 • BOLT, 3/8-24, HEX HEAD 6
410 B-3837-0432 • WASHER 12 Y
420 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 6 Y
430 104826 • PCP:HUB UNIT, 3A1-TP724A1 1 PCP
432 C-3317-021-1 • • O-RING, BUSHING TO HUB 1 Y
433 A-2249 • • HUB BUSHING, GUIDE 1 Y
434 103844 • • HUB BUSHING, ROD ENGINE SIDE 1 Y
435 A-6153-81 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
436 103846 • • HUB BUSHING, ROD CYLINDER SIDE 1 Y
437 A-5839-71 • • RING, RETAINING, INTERNAL SPIRAL 1 Y
-438 B-6142 • • INSERT, 1/4-28, CRES, COILED 6 Y
439 C-3317-111-1 • O-RING, ROD TO BUSHING 1 Y
500 104955 • PITCH CHANGE BLOCK UNIT 3
104934 • • BLOCK, PITCH CHANGE 1
104954 • • BUSHING 1

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

3A1-TP724A1

Page 10-22
ILLUSTRATED PARTS LIST 61-10-01 Rev. 2 Apr/15
 PROPELLER MAINTENANCE MANUAL
401

FIG./ITEM PART AIRLINE DESCRIPTION EFF UPA O/H PCP

NUMBER NUMBER STOCK NO. 123 45 6 7 CODE

10-2 3A1-TP724A1
10-4
10-6

520 104763 • BUMPER, FORK 6 Y

530 104940-( ) • SHIM, STAINLESS A/R
600 C-3317-338-8 • O-RING 3 Y
610 B-6144-1 • BALL, BEARING, 3/8" DIA 72 Y
620 104949 • BALL SPACER 72 Y
630 105421 • RACE, HUB SIDE 3
640 105444 • RACE, BEARING, BLADE SIDE 3
700 A-965 • WASHER, 7/16, CRES 1 Y
710 104919 • FORK, THREE BLADE 1
720 105282 • SPRING, COMPRESSION 1
730 103881 • SEAT, SPRING 1
800 B-3840-6 • SCREW, 100-32, FILLISTER HEAD 6 Y
820 B-3808-3 • NUT, HEX, SELF-LOCKING 6 Y
830 B-3851-0363 • WASHER 6 Y
840 104547 • WEIGHT, BALANCE 2
900 100041 • STUD, MOUNTING, 7/16-20 6 Y
910 A-1373 • NUT, MOUNTING 6 Y
920 A-965 • WASHER, MOUNTING 6 Y
930 C-3317-225-1 • O-RING, MOUNTING 1 Y
950 C-3317-129 • O-RING, CYLINDER/SPINNER DOME 1 Y

NOTE: SPINNER ASSEMBLIES AND SPINNER

MOUNTING HARDWARE ARE APPLICATION
SPECIFIC. REFER TO HARTZELL
PROPELLER INC. APPLICATION GUIDE
MANUAL 159 (61-02-59) AND HARTZELL
PROPELLER INC. METAL SPINNER
ASSEMBLY MAINTENANCE MANUAL 127
(61-16-27), AND COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48).

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

3A1-TP724A1

Page 10-23
ILLUSTRATED PARTS LIST 61-10-01 Rev. 3 Sep/16
PROPELLER MAINTENANCE MANUAL
401

(This page intentionally blank.)

Page 10-24
ILLUSTRATED PARTS LIST 61-10-01 Rev. 3 Sep/16