Manual No.

490
61-10-90
Revision 2
November 2019

Raptor Series Reciprocating

Propeller Overhaul Manual

3C1-( )( )( )
3C4-( )( )( )
4C1-( )( )( )

Hartzell Propeller Inc.

One Propeller Place
Piqua, Ohio 45356-2634 U.S.A.
Phone: 937.778.4200
Fax: 937.778.4215
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© 2016, 2018, 2019 - Hartzell Propeller Inc. - All rights reserved

INSIDE COVER 61-10-90 Inside Cover

Rev. 2 Nov/19
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REVISION 2 HIGHLIGHTS

Revision 2, dated November 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.
DESCRIPTION AND OPERATION
• Revised the section, "General"
• Revised the section, "Operation"
TESTING AND FAULT ISOLATION
• Revised the section, "Troubleshooting Guide"
• Revised the section, "Lightning Strike on Hub or Blade"
DISASSEMBLY
• Revised the section, "Important Information"
• Revised the section, "Disassembly of ( )C1-( )( )( ) Propeller Models"
CLEANING
• Revised the section, "Cleaning Procedures"
CHECK
• Added the section, "Inspection Criteria/Procedures"
• Revised the check criteria for the Compression Spring (Item 110 and 115)
• Revised Figure 5-8, "Pitch Change Rod"
• Revised Figure 5-11, "Fork"
• Added the check criteria and Figure 5-12 for the Bumper Extension (Item 295)
• Revised the check criteria and Figure 5-19 for the Blade Seal (Item 700)
REPAIR
• Revised the section, "General Repair Requirements"
• Added the section, "Repair/Modification Procedures"
ASSEMBLY
• Revised the section, "General"
• Revised the section, "Hub Assembly Procedures", including the applicable Figures
• Revised the section, "Hydraulic Pitch Change Unit Assembly"
• Revised the section, "Adjusting the Low Pitch Stop Angle"
FITS AND CLEARANCES
• Revised Table 8-1, "Torque Values"
SPECIAL TOOLS, FIXTURES, AND EQUIPMENT
• Revised the section, "Tooling and Facility Requirements"

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REVISION 2 HIGHLIGHTS, continued

ILLUSTRATED PARTS LIST
• Revised the section, "Introduction"
• Revised the section, "Description of Columns"
• Revised the description for the blade seal (Item 700) and added the Effectivity Code
where applicable
• Added the parts list and the applicable Figures for propeller model 3C1-R430A1
• Added the parts list and the applicable Figures for propeller model 4C1-F650A1

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REVISIONS 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 Jul/16 New Issue

Revision 1 Nov/18 Minor Revision
Revision 2 Nov/19 Minor Revision

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

Revision Issue Date Inserted Revision Issue Date Inserted

Number Date Inserted By Number Date Inserted By

Orig. Jul/16 Jul/16 HPI

1 Nov/18 Nov/18 HPI

2 Nov/19 Nov/19 HPI

RECORD OF REVISIONS 61-10-90 Page 1

Jul/16
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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 61-10-90 Page 2

Jul/16
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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 61-10-90 Page 1

Jul/16
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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

Page 2
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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
HC-SB-61-377 Rev. 1, Nov/18

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SERVICE DOCUMENT LIST

Service Document Incorporation Service Document Incorporation

Number Rev./Date Number Rev./Date

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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 airworthiness limitations information, refer to Hartzell Propeller Inc. Owner's

Manual 480 (61-00-80).

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LIST OF EFFECTIVE PAGES

Chapter Page Rev. Level Date

Cover Cover and Inside Cover Rev. 2 Nov/19

Revision Highlights 1 thru 4 Rev. 2 Nov/19
Record of Revisions 1 and 2 Original Jul/16
Record of Temporary Revisions 1 and 2 Original Jul/16
Service Document List 1 and 2 Rev. 1 Nov/18
Airworthiness Limitations 1 and 2 Original Jul/16
List of Effective Pages 1 and 2 Rev. 2 Nov/19
Table of Contents 1 and 2 Original Jul/16
Introduction 1 thru 22 Rev. 2 Nov/19
Description and Operation 1 thru 4 Rev. 2 Nov/19
Testing and Fault Isolation 1-1 thru 1-3 Rev. 2 Nov/19
Testing and Fault Isolation 1-4 and 1-5 Rev. 1 Nov/18
Testing and Fault Isolation 1-6 Original Jul/16
Testing and Fault Isolation 1-7 Rev. 1 Nov/18
Testing and Fault Isolation 1-8 Original Jul/16
Testing and Fault Isolation 1-9 and 1-10 Rev. 2 Nov/19
Automatic Test Requirements 2-1 and 2-2 Original Jul/16
Disassembly 3-1 thru 3-12 Rev. 2 Nov/19
Cleaning 4-1 thru 4-4 Rev. 2 Nov/19
Check 5-1 thru 5-48 Rev. 2 Nov/19
Repair 6-1 thru 6-6 Rev. 2 Nov/19
Assembly 7-1 and 7-2 Rev. 2 Nov/19
Assembly 7-2.1 and 7-2.2 Rev. 2 Nov/19
Assembly 7-3 thru 7-44 Rev. 2 Nov/19
Fits and Clearances 8-1 thru 8-8 Rev. 2 Nov/19
Special Tools, Fixtures and Equipment 9-1 thru 9-4 Rev. 2 Nov/19
Illustrated Parts List 10-1 thru 10-44 Rev. 2 Nov/19

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LIST OF EFFECTIVE PAGES

Chapter Page Rev. Level Date

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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. General........................................................................................................................ 3
A. Statement of Purpose............................................................................................ 3
B. Item References..................................................................................................... 4
2. Reference Publications................................................................................................ 5
A. Hartzell Propeller Inc. Publications........................................................................ 5
B. Vendor Publications............................................................................................... 5
3. Personnel Requirements............................................................................................. 6
4. Special Tooling and Consumable Materials................................................................. 6
A. Special Tooling....................................................................................................... 6
B. Consumable Materials........................................................................................... 6
5. Safe Handling of Paints and Chemicals...................................................................... 7
6. Calendar Limits and Long Term Storage..................................................................... 7
A. Calendar Limits...................................................................................................... 7
B. Long Term Storage................................................................................................. 7
7. Component Life and Overhaul..................................................................................... 8
A. Component Life...................................................................................................... 8
B. Overhaul................................................................................................................. 9
8. Damage/Repair Types............................................................................................... 10
A. Airworthy/Unairworthy Damage........................................................................... 10
B. Minor/Major Repair............................................................................................... 10
9. Propeller Critical Parts................................................................................................11
10. Warranty Service........................................................................................................11
11. Hartzell Propeller Inc. Contact Information................................................................ 12
A. Product Support Department............................................................................... 12
B. Technical Publications Department...................................................................... 12
C. Recommended Facilities...................................................................................... 12
12. Definitions.................................................................................................................. 13
13. Abbreviations............................................................................................................. 20

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1. General (Rev. 1)

A. Statement of Purpose
(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 use in
propeller repair stations by personnel that 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.
(3) This manual is intended to be the primary source of maintenance and
overhaul information for the applicable Hartzell propeller/component models.
(a) 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 Certificated propeller. Always use the current
illustrated parts list for the assembly of any propeller. Always refer to the
aircraft Type Certificate (TC) or Supplemental Type Certificate (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.
(b) 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.
(4) This manual makes reference to other Hartzell Propeller Inc. manuals
that provide important details for procedures such as anodizing, penetrant
inspection, and overhaul procedures for hub units.
(5) Where possible, this manual is written in the format specified by
ATA iSpec 2200.

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B. Item References
(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 (105733) that is item 320 was
superseded by the pitch change block unit (105733-1) that is item 320A.
(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 (B-2419) that is
item 80, yet another configuration uses a piston (104256) that is
item 80A. Effectivity codes are very important in the determination of
parts in a given configuration.

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2. Reference Publications

A. Hartzell Propeller Inc. Publications

(1) 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.
(2) 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.

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 Metal Spinner Maintenance Manual

(61-16-27)

Manual 135F - Composite Propeller Blade

Maintenance Manual
(61-13-35)

Manual 159 Yes Application Guide

(61-02-59)

Manual 165A Yes Illustrated Tool and Equipment Manual

(61-00-65)

Manual 170 Yes Composite Propeller Blade Field Maintenance and

(61-13-70) Minor Repair Manual

Manual 180 Yes Propeller Ice Protection System Manual

(30-61-80)

Manual 202A Vol. 7, Yes Standard Practices Manual,

(61-01-02) Volumes 1 through 11

Manual 480 Yes Propeller Owner’s Manual and Logbook for Raptor
(61-00-80) Reciprocating Propeller Series with Composite Blades
Constant Speed, Non-counterweighted

B. Vendor Publications
None.

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3. Personnel Requirements (Rev. 1)

A. Service and Maintenance Procedures in this Manual
(1) Personnel performing the service and maintenance procedures in this
manual are expected to have the required equipment/tooling, training,
and certifications (when required by the applicable Aviation Authority) to
accomplish the work in a safe and airworthy manner.
(2) 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 the
inspection and/or repair of any Hartzell Propeller Inc. product.
(a) Maintenance records must be kept in accordance with the requirements
established by the Federal Aviation Administration (FAA) or international
equivalent.
(b) Refer to Federal Aviation Regulation (FAR) Part 43 for additional
information about general aviation maintenance requirements.

4. Special Tooling and Consumable Materials (Rev. 1)

A. Special Tooling
(1) 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) Tooling reference numbers 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.

B. Consumable Materials
(1) 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) Consumable material reference numbers 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 the material(s) specified can be used.

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5. Safe Handling of Paints and Chemicals (Rev.1)

A. Instructions for Use
(1) Always use caution when handling or being exposed to paints and/or
chemicals during propeller overhaul and/or maintenance procedures.
(2) Before using paint or chemicals, always read the manufacturer’s label on
the container(s) and follow specified instructions and procedures for storage,
preparation, mixing, and/or application.
(3) Refer to the product’s Material Safety Data Sheet (MSDS) for detailed
information about the physical properties, health, and physical hazards of
any paint or chemical.

6. Calendar Limits and Long Term Storage (Rev. 1)

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).

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7. Component Life and Overhaul (Rev. 1)

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

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

and landing, i.e., flight time.
(2) Time Since New (TSN) and Time Since Overhaul (TSO) records for the
propeller hub and blades must be maintained in the propeller logbook.
(3) Both TSN and TSO are necessary for defining the life of the component.
Certain components, or in some cases an entire propeller, may be "life
limited", which means that they must be replaced after a specified period of
use (TSN).
(a) It is a regulatory requirement that a record of the Time Since New (TSN)
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.
(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.
(5) 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) 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.

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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 If tracking any component(s) other than the hub/blades, maintain
these TSN/TSO records separately in the propeller logbook.

NOTE: Hub replacement does not affect the TSN/TSO of any other
propeller components.

B. 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) Overhaul intervals are specified in the applicable Hartzell Propeller Inc.
propeller owner's manual and Hartzell Service Letter HC-SL-61-61Y.
(b) 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.
(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.
(a) Parts that are not replaced at overhaul must be inspected in accordance
with the check criteria in the applicable Hartzell Propeller Inc.
component maintenance manual.
(b) Parts that must be replaced at overhaul are identified by a "Y" in the
O/H column of the Illustrated Parts List in the applicable Hartzell
Propeller Inc. component maintenance manual.
(4) The information in this manual supersedes data in all previously published
revisions of this manual.

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8. Damage/Repair Types (Rev. 1)

A. Airworthy/Unairworthy Damage
(1) Airworthy damage is a specific condition to a propeller component that
is within the airworthy damage limits specified in the applicable Hartzell
Propeller Inc. component maintenance manual.
(a) Airworthy damage does not affect the safety or flight characteristics of
the propeller and conforms to its type design.
(b) Airworthy damage does not require repair before further flight, but
should be repaired as soon as possible to prevent degradation of the
damage.
(2) Unairworthy damage is a specific condition to a propeller component that
exceeds the airworthy damage limits specified in the applicable Hartzell
Propeller Inc. component maintenance manual.
(a) Unairworthy damage can affect the safety or flight characteristics of the
propeller and does not conform to its type design.
(b) Unairworthy damage must be repaired before the propeller is returned
to service.

B. Minor/Major Repair
(1) Minor Repair
(a) Minor repair is that which may be done safely in the field by a certified
aircraft mechanic.
1 For serviceable limits and repair criteria for Hartzell propeller
components, refer to the applicable Hartzell Propeller Inc.
component maintenance manual.
(2) Major Repair
(a) Major repair 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 Hartzell recommends that individuals performing major repairs also
have 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).

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9. Propeller Critical Parts (Rev. 1)

A. 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 in the applicable Hartzell
Propeller Inc. maintenance manual to identify the Propeller Critical
Parts.
(2) Numerous propeller system parts can produce a propeller 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.

10. Warranty Service (Rev. 1)

A. Warranty Claims
(1) If you believe you have a warranty claim, contact the Hartzell Propeller
Inc. Product Support Department to request a Warranty Application form.
Complete this form and return it to Hartzell Product Support for evaluation
before proceeding with repair or inspection work. Upon receipt of this
form, the Hartzell Product Support Department will provide instructions on
how to proceed.
(a) For Hartzell Propeller Inc. Product Support Department contact
information, refer to the “Contact Information” section in this chapter.

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11. Hartzell Propeller Inc. Contact Information (Rev. 2)

A. 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. 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.

C. Recommended Facilities
(1) Hartzell Propeller Inc. recommends using Hartzell-approved distributors and
repair facilities for the purchase, repair, and overhaul of Hartzell propeller
assemblies or components.
(2) Information about the Hartzell Propeller Inc. worldwide network of aftermarket
distributors and approved repair facilities is available on the Hartzell website
at www.hartzellprop.com.

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12. Definitions (Rev. 3)

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

Term Definition
Annealed Softening of material due to overexposure to heat
Aviation Certified Intended for FAA or international equivalent type certifi-
cated 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 or part
number are not certified by the FAA or international equiv-
alent and are not intended to use on certificated aircraft.
Beta Operation A mode of pitch control that is directed by the pilot rather
than by the propeller governor
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
Blade Centerline 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 in-
spection 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 im-
pact on safety or utility
Brinelling A depression caused by failure of the material in compres-
sion

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Term Definition
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 distance between the leading and trailing
edges of an airfoil
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 simultane-
ously curing it to some other prepared surface
Composite Material Kevlar®, carbon, or fiberglass fibers bound together with,
or encapsulated within an epoxy resin
Compression Rolling A process that provides improved strength and resistance
to fatigue
Constant Force A force that is always present in some degree when the
propeller is operating
Constant Speed A propeller system that employs a governing device to
maintain a selected engine RPM
Corrosion (Aluminum) The chemical or electrochemical attack by an acid or alka-
line 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 con-
verted 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), mois-
ture 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.

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Term Definition
Corrosion Product A white or dull gray powdery material that has an in-
(Aluminum) creased 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 When iron or an iron alloy such as steel corrodes, a corro-
(Steel) sion product known as rust is formed. Rust is an iron oxide
which is reddish in appearance and occupies approxi-
mately 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 metal-
lic 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, sometimes
visible as a narrow opening at the surface
Debond Separation of two materials that were originally bonded
together in a separate operation
Defect An imperfection that affects safety or utility
Delamination Internal separation of the layers of composite material
Dent The permanent deflection of the cross section that is vis-
ible 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
Edge Alignment Distance from the blade centerline to the leading edge of
the blade
Erosion Gradual wearing away or deterioration due to action of the
elements
Exposure Leaving material open to action of the elements

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Term Definition
Face The surface of the blade that is directed toward the rear of
the aircraft. The face side is the high pressure, or thrust-
ing, side of the blade. The blade airfoil sections are nor-
mally 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 rela-
tive wind, thus reducing aerodynamic drag
Fraying A raveling or shredding of material
Fretting Damage that develops when relative motion of small dis-
placement takes place between contacting parts, wearing
away the surface
Galling To fret or wear away by friction
Gouge Surface area where material has been removed
Hazardous Propeller The hazardous propeller effects are defined in Title 14 CFR
Effect section 35.15(g)(1)
Horizontal Balance Balance between the blade tip and the center of the hub
Impact Damage Damage that occurs when the propeller blade or hub as-
sembly strikes, or is struck by, an object while in flight or
on the ground
Inboard Toward the butt of the blade
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
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 con-
stant speed operation

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Term Definition
Major Propeller Effect The major propeller effects are defined in Title 14 CFR
section 35.15(g)(2)
Minor Deformation Deformed material not associated with a crack or missing
material
Monocoque A type of construction in which the outer skin carries all or
a major part of the load
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 that is dif-
ferent 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. Products
marked with an “X” at or near the end of the model number
or part number are not certified by any authority and are
not intended for use on certificated craft.
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
Overhaul The periodic disassembly, inspection, repair, refinish, and
reassembly of a propeller assembly to maintain airworthi-
ness
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 propeller control/condition
lever
Pitch Same as “Blade Angle”
Pitting Formation of a number of small, irregularly shaped cavities
in surface material caused by corrosion or wear

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Term Definition
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 Parts 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
Reference Blade Radius Refers to the propeller reference blade radius in an as-
sembled 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 pro-
peller. 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
Scratch Same as “Nick”
Short Circuit 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 cre-
ate compressive surface stress, that provides improved
strength and resistance to fatigue

Single Acting Hydraulically actuated propeller that utilizes a single oil

supply for pitch control
Split Delamination of blade extending to the blade surface, nor-
mally found near the trailing edge or tip
Station Line See "Blade Station"
Synchronizing Adjusting the RPM of all the propellers of a multi-engine
aircraft to 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

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Term Definition
Ticking A series of parallel marks or scratches running circumfer-
entially 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 as-
sembly
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
Underspeed The condition in which the actual engine (propeller) RPM
is lower than the RPM selected by the pilot through the
propeller control/condition lever
Unidirectional Material A composite material in which the fibers are substantially
oriented in the same direction
Variable Force A force that may be applied or removed during propeller
operation
Vertical Balance Balance between the leading and trailing edges of a two-
blade propeller with the blades positioned vertically

Voids Air or gas that has been trapped and cured into a laminate
Windmilling The rotation of an aircraft propeller caused by air flowing
through it while the engine is not producing power
Woven Fabric A material constructed by interlacing fiber to form a fabric
pattern
Wrinkle (aluminum blade) A wavy appearance caused by high and low material dis-
placement
Wrinkle (composite blade) Overlap or fold within the material

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13. Abbreviations (Rev. 2)

Abbreviation Term
AD Airworthiness Directives
AMM Aircraft Maintenance Manual
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
kPa Kilopascals
Lb(s) Pound(s)
Max. Maximum
Min. Minimum
MIL-X-XXX Military Specification
MPI Major Periodic Inspection (Overhaul)
MS Military Standard
MSDS Material Safety Data Sheet

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Abbreviation Term
N Newtons
N/A Not Applicable
NAS National Aerospace Standards
NASM National Aerospace Standards, Military
NDT Nondestructive Testing
NIST National Institute of Standards and Technology
N•m Newton-Meters
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
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

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DESCRIPTION AND OPERATION - CONTENTS

1. General........................................................................................................................ 3
A. Propeller/Blade Model Designation........................................................................ 3
2. Operation..................................................................................................................... 3
A. ( )C1-( )( )( ) Series Propellers................................................................................ 3
B. ( )C4-( )( )( ) Series Propellers................................................................................ 4

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1. General (Rev. 1)

A. Propeller/Blade Model Designation

(1) Hartzell Propeller Inc. uses a model number designation system to identify
specific propeller and blade assemblies. The propeller model number and
blade model number are separated by a slash ( / ).
(a) Example: propeller model number / blade model number
(2) The propeller model number is impression stamped on the propeller hub.
(a) For additional information about the propeller model number designation
system, refer to the applicable Hartzell Propeller Inc. owner's manual.
(3) The blade model number is impression stamped on the butt end of the blade,
and also identified by a label on the cylinder.
(a) For additional information about the model number designation system
for composite blades, refer to Hartzell Propeller Inc. Composite Propeller
Blade Maintenance Manual 135F (61-13-35).
(b) For additional information about the model number designation system for
aluminum blades, refer to Hartzell Propeller Inc. Aluminum Blade Overhaul
Manual 133C (61-13-33).

2. Operation

A. ( )C1-( )( )( ) Series Propellers

(1) These propeller models are constant speed, single-acting, hydraulically
actuated propellers. The propellers are capable of blade angles between a low
positive pitch (low pitch) and high positive pitch (high pitch).
(2) 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.
(3) Oil pressure opposes the spring and centrifugal twisting moment to move the
blades to a high blade angle (high pitch), reducing engine RPM.
(4) 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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B. ( )C4-( )( )( ) Series Propellers

(1) These propeller model series are constant speed propellers with blade mounted
counterweights. The propellers are capable of blade angles between a low
positive pitch (low pitch) and high positive pitch (high pitch). These propellers
are generally used in aerobatic applications.
(2) The blade centrifugal twisting moment acts to move the blades to low blade
angle (low pitch), but the counterweights are large enough to neutralize
this force and produce a net increase in blade angle. Oil pressure against a
propeller mounted hydraulic piston opposes the counterweight forces to move
the blades to low pitch.
(3) The action of the counterweights tends to move the blades to a high blade
angle (high pitch), reducing engine RPM. Oil pressure toward low pitch
increases engine RPM.
(4) If oil pressure is lost at any time, the propeller will move to high pitch
to avoid overspeeding. Movement to high pitch occurs because the
blade counterweights are no longer opposed by hydraulic oil pressure.
The blade counterweights are then free to increase blade pitch toward
the high pitch stop.

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TESTING AND FAULT ISOLATION - CONTENTS

1. Troubleshooting Guide........................................................................................1-3
A. Pitch Control Difficulty....................................................................................1-3
B. Friction............................................................................................................1-3
C. Abnormal Propeller Vibration.........................................................................1-4
D. Slight Vibration...............................................................................................1-4
E. Surging RPM or Torque..................................................................................1-5
F. Oil Leakage....................................................................................................1-7
G. Grease Leakage.............................................................................................1-7
H. End-Play Movement of the Blade...................................................................1-8
I. Fore-and-Aft Movement of the Blade.............................................................1-8
J. In-and-Out Movement of the Blade................................................................1-8
K. Excessive Radial Play of the Blade (backlash)..............................................1-8
L. Blades Not Tracking.......................................................................................1-8
2. Lightning Strike on Hub or Blade.........................................................................1-9

LIST OF FIGURES
Areas of Leaking Oil or Grease.............................................Figure 1-1......................... 1-6

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1. Troubleshooting Guide

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.
The purpose of this chapter is to isolate probable causes and suggest remedies for
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 Too much friction in moving Refer to problem "Friction" in this
parts. chapter.

or Oil leaking around the piston Disassemble the propeller and

causing underspeed. Oil will leak examine the piston O-rings and
out of the low pitch stop bleeder piston-to-cylinder sealing surfaces.
hole. ( )C4- propellers only Replace the defective O-ring(s).

or Oil leaking around the piston, Using caution because the

between the pitch change rod grease/oil may be under pressure,
and hub (engine-side), or between remove a lubrication fitting from the
the pitch change rod and shaft hub and check for a dark
plug causing overspeed.Hub will grease/oil mixture leaking out of the
fill with engine oil. lubrication fitting hole.
( )C1- propellers only
Disassemble the propeller and
examine the hub-to-pitch change
rod O-rings and the piston O-rings,
as applicable.

Examine the piston-to-cylinder

sealing surfaces and the pitch
change rod sealing surfaces, as
applicable.

Replace the O-ring(s).

B. Friction Blade is shimmed too tight. Disassemble the propeller and

readjust the blade shim.

or Lack of lubrication. Add approved lubricant.

or Balls in the blade retention Replace the blade retention split

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

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Problem Probable Cause Remedy

B. Friction, continued or Not enough clearance between Examine the moving parts
the various moving parts in individually. Increase the
the pitch change mechanism. clearances between the individual
parts as necessary to decrease
friction in the mechanism.
Refer to the section, "Pitch Change
Block Button Modification" in the
Repair chapter of this manual.

or Wear strip is damaged causing Replace the damaged wear strip

too much friction on the blade and the seal O-ring.
butt seal O-ring.

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

Vibration blade or pitch change knob. Composite Propeller Blade
Maintenance Manual 135F
(61-13-35).

or Cracked or damaged hub. Refer to the Aluminum Hub

Overhaul chapter of Hartzell
Propeller Inc. Standard Practices
Manual 202A (61-01-02).

or Broken blade retention split Replace the bearings and inspect

bearings. the other blade retention
components.

or Grease leakage. Refer to the problem, "Grease

Leakage" in this chapter.

D. Slight Vibration Blades not tracking. Refer to the problem, "Blades Not
Tracking" in this chapter.

or Static balance incorrect. Refer to the Static and Dynamic

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

or Dynamic balance incorrect. Refer to the Static and Dynamic

Balance chapter of Hartzell
Propeller Inc. Standard Practices
Manual 202A (61-01-02.

or Blade wear. Refer to Hartzell Propeller Inc.

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

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Problem Probable Cause Remedy

D. Slight Vibration, continued or Grease leakage. Refer to the problem, "Grease
Leakage" in this chapter.

or Blade-to-blade pitch variance is Disassemble the propeller and

too great. correct the blade-to-blade pitch
variance.

E. Surging RPM or Torque Too much friction in the pitch Refer to the problem, "Friction" in
change mechanism. this chapter.

or Air is trapped in the propeller After propeller installation and

actuating piston or in the engine before each flight, exercise the
shaft. propeller by changing pitch or
feathering.

The engine should have a

provision for trapped air to escape
from the system during one-half of
the pitch cycle.

or Governor problem. Refer to the airframe or the engine

manufacturer's maintenance
manual for installation instructions.

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Oil leakage from

between the set screw
and the cylinder
Grease leakage at the
seal between the cylinder
and the cylinder-side half
of the hub

Grease leakage at
the blade socket of
Grease leakage at the the hub
interface between the
halves of the hub
Grease leakage from
any lubrication fitting
TPI-490-025

Areas of Leaking Oil or Grease

Figure 1-1

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Problem Probable Cause Remedy

F. Oil Leakage Defective O-ring seal between Remove the propeller from the
(Refer to Figure 1-1) the engine flange and the engine and visually examine the
propeller mounting flange. O-ring and the sealing surface.
Replace the defective O-ring.

or Defective O-ring seal between Remove the cylinder and visually

the cylinder and the hub. examine the O-ring and the sealing
surface. Replace the defective
O-ring.

or Defective O-ring seal between Remove the cylinder and visually

the piston and the cylinder, examine the piston O-ring and
resulting in leakage between the cylinder sealing surface. Replace
pitch change rod plug and the the defective O-ring.
cylinder.

or Defective O-ring seal between Remove the lubrication fitting at

the pitch change rod and either the bottom of the hub and insert
hub half, resulting in leakage a wire. If oil runs out, then one or
from the hub and from around both O-rings are defective.
the blade shanks.
Remove the propeller from the
engine and disassemble. Visually
examine both O-rings and sealing
surfaces. Replace the defective
O-ring(s).

G. Grease Leakage Defective lubrication fitting. Replace defective lubrication

(Refer to Figure 1-1) fittings.
A new or newly overhauled
propeller can leak slightly or Defective seal at blade socket Disassemble the propeller
during the first several in the hub. and visually examine the seal
hours of operation. The and the sealing surface. Replace
leakage can be caused by defective seal.
the seating of seals and
O-rings, and the slinging
of lubricants used during
assembly. This leakage
should stop within the first
ten hours of operation.

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Problem Probable Cause Remedy

H. End-Play Movement of the Blade retention bearing is worn. Follow the Blade Retention
Blade Split Bearing Inspection and
NOTE: Refer to Table 8-2, Replacement Procedures.
"Blade Tolerances"
in the Fits and or Internal blade shim is worn. Disassemble the propeller, remove
Clearances chapter the blade shim, and inspect the
in this manual. blade shim. Replace the worn
blade shim.

I. Fore-and-Aft Movement of Blade retention bearing is worn. Follow the Blade Retention
the Blade Split Bearing Inspection and
NOTE: Refer to Table 8-2, Replacement Procedures.
"Blade Tolerances"
in the Fits and or Internal blade shim is worn. Disassemble the propeller, remove
Clearances chapter the blade, and inspect the blade
in this manual. shim. Replace the worn blade
shim.

J. In-and-Out Movement of Blade retention bearing is worn. Follow the Blade Retention
the Blade Split Bearing Inspection and
NOTE: Refer to Table 8-2, Replacement Procedures.
"Blade Tolerances"
in the Fits and
Clearances chapter
in this manual.

K. Excessive Radial Play of Pitch change fork is worn. Disassemble the propeller. Inspect
the Blade (backlash) and replace the fork, as required.
NOTE: Refer to Table 8-2,
"Blade Tolerances"
in the Fits and
Clearances
chapter in this
manual.

L. Blades Not Tracking Ground strike damage. For a composite blade, refer to
Hartzell Propeller Inc. Composite
Propeller Blade Maintenance
Manual 135F (61-13-35).

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2. Lightning Strike on Hub or Blade (Rev. 1)

A. Before Further Flight

(1) In the event of a propeller lightning strike, an inspection is required before
further flight.
(a) 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.
(b) 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. Important Information............................................................................................... 3-3
A. Removing the Propeller....................................................................................... 3-3
B. Record Serial Numbers/Blade Location Before Disassembly............................. 3-3
C. Ice Protection System......................................................................................... 3-3
2. Disassembly of ( )C1-( )( )( ) Propeller Models......................................................... 3-4
A. Hub Plug Removal: 3C1-R619A1 and 3C1-R919A1 Propellers Only................. 3-4
B. Disassembly of the Propeller Pitch Change Parts.............................................. 3-5
C. Hub Disassembly................................................................................................ 3-7
D. Disassembly of the Blade Retention Parts.......................................................... 3-8
E. Blade Disassembly.............................................................................................. 3-8
3. Disassembly of 3C4-( )( )( ) Propeller Models.......................................................... 3-9
A. Disassembly of the Propeller Pitch Change Parts.............................................. 3-9
B. Hub Disassembly.............................................................................................. 3-11
C. Disassembly of the Blade Retention Parts........................................................ 3-12
D. Blade Disassembly ........................................................................................... 3-12

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1. Important Information (Rev. 2)

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. Removing the Propeller
(1) Remove the propeller from the aircraft in accordance with the applicable
Hartzell Propeller Inc. owner's manual.
B. Record Serial Numbers/Blade Location Before Disassembly
(1) 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.
(a) For the location of the serial number on the hub, refer to the Parts
Identification and Marking chapter of Hartzell Propeller Inc. Standard
Practices Manual 202A (61-01-02).

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

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

CAUTION 2: GRAPHITE ("LEAD") PENCIL MARKS WILL CAUSE

CORROSION. ALL MARKS MADE ON PARTS MUST BE MADE
WITH a crayon or soft, non-graphite pencil such as CM162.
(2) Before disassembly, use a crayon or soft, non-graphite pencil such as CM162
to number the blades counterclockwise from the propeller serial number
impression stamped on the propeller hub unit.
(a) Make a record of each blade serial number and the hub socket/arm from
which it was removed.
C. Ice Protection System (if applicable)
(1) If the propeller is equipped with an ice protection system supplied by Hartzell,
refer to Hartzell Propeller Inc. Ice Protection System Manual 180 (30-61-80) for
technical information about the applicable ice protection system.
(2) If the propeller is equipped with an ice protection system not supplied by
Hartzell Propeller Inc., refer to the applicable TC or STC holder’s Instructions
for Continued Airworthiness (ICA) for technical information about the applicable
ice protection system.

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2. Disassembly of ( )C1-( )( )( ) Propeller Models

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 PROPELLERS.

CAUTION 3: DO NOT USE MORE THAN 175 PSI (12.06 BARS) OF PRESSURE
WHEN ACTUATING PROPELLERS INCLUDED IN THIS MANUAL.

CAUTION 4: USE ENOUGH PRESSURE TO MAKE SURE THAT THE PROPELLER

ACTUATES AGAINST EACH POSITIVE STOP.
A. Hub Plug Removal: 3C1-R619A1 and 3C1-R919A1 Propellers Only
(1) Turn the propeller over and put it on a support to get access to the propeller
mounting flange.
NOTE: A sturdy barrel or drum with the rim well padded may be used as
a support.
(2) Using puller TE98, or equivalent, remove the hub plug (370).
(a) Put the puller TE98 on the end of the pitch change rod (150).
(b) Put the pulling ends of the puller TE98 firmly in the recesses of the hub
plug (370).
(c) Tighten the puller TE98 until the hub plug (370) is removed from the bore
of the hub (220).
(3) Remove and discard the O-ring (360) from the OD of the hub plug (370).
(4) Remove and discard the O-ring (350) from the ID of the hub plug (370).
(5) Remove and discard the internal spiral retaining ring (330).

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B. Disassembly of the Propeller Pitch Change Parts

(1) To simplify the assembly process and minimize the effort to set the necessary
blade angles, make a record of the location and orientation (where applicable) of
each part in the propeller hub assembly.
(2) Attach the propeller assembly to the rotatable fixture TE125 or equivalent on
the assembly table TE129 or equivalent.
CAUTION: CYCLE THE PROPELLER BEFORE BEGINNING THE CYLINDER
REMOVAL PROCESS. FAILURE TO CYCLE THE PROPELLER
MAY CAUSE THE PITCH CHANGE ROD TO PREMATURELY
DISENGAGE FROM THE FORK.
(3) Cycle the propeller through the entire range of movement and cycle back to
no pressure or low pitch before beginning disassembly.
(4) Remove and discard the self-locking nut (10).
(5) Remove and discard the washer seal (20) from the low pitch stop
set screw (30).
(6) Remove the low pitch stop set screw (30) from the cylinder (40).
(7) Using the cylinder wrench TE153 or equivalent, remove the cylinder (40).
(8) Remove and discard the cylinder-to-hub O-ring (160).

WARNING: USE CARE WHEN REMOVING THE PISTON BECAUSE THE

PISTON IS UNDER SLIGHT FORCE.
(9) Loosen the pitch change rod (150).
(10) Remove the piston/sleeve/rod assembly from the propeller.
(11) Remove the compression spring (110).
(a) 4C1-Propellers Only: Remove compression spring (115).
(12) Remove the spring guide (140).
(13) Reinstall the piston/sleeve/rod assembly in the propeller.
(14) Remove and discard the cotter pin (50) from the piston nut (60).
(15) Remove and discard the piston nut (60) from the pitch change rod (150).
(16) Remove the piston (80) from the pitch change rod (150).
(17) Remove and discard the O-ring (70) from the OD of the piston (80).
(18) Remove and discard the O-ring (90) from the ID of the piston (80).
(19) Remove the spring seat (100).
(20) Remove the stop sleeve (120).
(21) Remove and discard the stop sleeve split keeper (130).

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(22) Remove and discard the nuts (190) and washers (200).
(23) Remove the hub bolts (210).
(a) If the spinner bulkhead is attached to the propeller with the hub
bolts (210), remove the spinner bulkhead.
(24) Using a non-metallic tool, loosen the cylinder-side half of the hub (220).
(25) Remove the cylinder-side half of the hub unit (220).
(26) Remove and discard the hub guide bushing (230).
(27) Remove blade number one from the hub (220).
(28) Remove the fork (290).
(29) Remove the fork bumpers (300).
(a) 4C1-Propellers Only: Remove four bumper extensions (295) from
the fork (290).
(30) Remove the remaining blades from the hub (220).
(31) Remove the pitch change block (320) from each pitch change knob.
(a) Make a mark to indicate the direction of the thin wall of each pitch
change block (320) to the fork (290).
(32) Remove and discard the pitch change block button (310) from each pitch
change block (320).

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C. Hub Disassembly
(1) For hub unit disassembly instructions, refer to the Aluminum Hub Overhaul
chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).
(2) Disassembly of the Cylinder-side Half of the Hub Unit
(a) Remove and discard the internal spiral retaining ring (270) from the
cylinder-side hub bushing (260).
(b) Remove and discard the cylinder-side hub bushing (260).
(3) Disassembly of the Engine-side Half of the Hub Unit
(a) Remove the engine-side half of the hub (220) from the rotatable fixture.
(b) Remove and discard the O-ring (540).
(c) Remove the pitch change rod hub bushing (280) from the engine-side half
of the hub (220).
1 Remove and discard the external retaining ring (250).
2 Remove the rod hub bushing (280) from the engine-side half of the
hub (220).
3 Remove and discard the O-ring (240) from the OD of the rod hub
bushing (280).
4 For 3C1-L675A1 propellers only, remove and discard the O-ring (340)
from the ID of the rod hub bushing (280).
(4) Disassembly of the Hub Mounting Hardware - 3C1-( )( )( ) Propellers Only:
(a) Push out the spring pin (520) from the nut (510) and the mounting
stud (500).
(b) Using a wrench, hold the mounting nut (510) and use a standard stud
removal tool to remove the mounting stud (500) from the mounting
nut (510).
(c) Discard the mounting stud (500), mounting nut (510), spring pin (520),
and washer (530).
(d) Repeat steps (4)(a) through (4)(c) for the remaining mounting studs (500).

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D. Disassembly of the Blade Retention Parts

(1) Remove and discard the blade O-ring (720).
(2) Remove the hub-side blade bearing race (660).
(3) Remove and discard the bearing balls (640).
(4) Remove and discard the ball spacer (650).
(5) Remove and discard the pitch change knob bushing (730).
(6) Remove the blade seal (700) and the blade shim (680) from the blade.
(a) To make the reassembly of the propeller easier, measure the thickness of
the blade shim (680) and make a record of the measurement.
(7) Remove and discard the O-ring (690) from the ID of the blade seal (700).
(8) Remove and discard the O-ring (710) from the OD of the blade seal (700).
(9) Remove and discard the internal spiral retaining ring (620) from the bore of
the blade.
(10) Remove the blade plug (610).
(a) Turn a screw with 8-32 UNC-3B threads into the threaded hole in the
blade plug (610).
(b) Pull the blade plug (610) from the bore of the blade.
(11) Remove and discard the O-ring (600) from the OD of the blade plug (610).
(12) Using a suitable gear puller or brass drift, remove the bearing retaining
ring (670).
(13) Remove the blade-side blade bearing race (630) of the blade retention bearing.
E. Blade Disassembly
(1) For composite blade overhaul procedures, refer to Hartzell Propeller Inc.
Composite Propeller Blade Maintenance Manual 135F (61-13-35).

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3. Disassembly of 3C4-( )( )( ) Propeller Models

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 PROPELLERS.
CAUTION 3: DO NOT USE MORE THAN 175 PSI (12.06 BARS) OF PRESSURE
WHEN ACTUATING PROPELLERS INCLUDED IN THIS MANUAL.
CAUTION 4: USE ENOUGH PRESSURE TO MAKE SURE THAT THE PROPELLER
ACTUATES AGAINST EACH POSITIVE STOP.
A. Disassembly of the Propeller Pitch Change Parts
(1) To simplify the assembly process and make it easier to set the necessary blade
angles, make a record of the location and orientation (where applicable) of each
part in the propeller hub assembly.
(2) Attach the propeller assembly to the rotatable fixture TE125 or equivalent on
the assembly table TE129 or equivalent.
CAUTION: CYCLE THE PROPELLER BEFORE BEGINNING THE
CYLINDER (40) REMOVAL PROCESS. FAILURE TO CYCLE THE
PROPELLER MAY CAUSE THE PITCH CHANGE ROD (150) TO
PREMATURELY DISENGAGE FROM THE FORK (290).
(3) Cycle the propeller through the entire range of movement and cycle back to
no pressure or low pitch before beginning disassembly.
(4) Remove and discard the self-locking nut (10).
(5) Remove and discard the washer (20) from the low pitch stop set screw (30).

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CAUTION: THE LOW PITCH STOP SCREW (30) IN AEROBATIC

PROPELLERS CAN DEFORM DUE TO CONTACT WITH THE
PITCH CHANGE ROD (150). DEFORMATION ON THE END OF
THE LOW PITCH STOP SCREW CAN DAMAGE THE THREADS
IN THE CYLINDER (40) WHEN THE LOW PITCH STOP SCREW
IS REMOVED. IF RESISTANCE INCREASES WHEN REMOVING
THE LOW PITCH STOP SCREW, REMOVE THE CYLINDER, THEN
REMOVE THE LOW PITCH STOP SCREW BY TURNING IT INTO
THE CYLINDER.
(6) Remove the low pitch stop set screw (30) from the cylinder (40).
(7) Using the cylinder wrench TE153 or equivalent, remove the cylinder (40).
(a) Remove and discard the cylinder-to-hub O-ring (160).
(8) Remove and discard the cotter pin (50) from the piston nut (60).
(9) Remove the piston nut (60) from the pitch change rod (150).
(10) Remove the piston (80) from the pitch change rod (150).
(a) Remove and discard the O-ring (70) from the OD of the piston (80).
(b) Remove and discard the O-ring (90) from the ID of the piston (80).
(11) Remove the stop collar (125).
(12) Remove and discard the split keeper (130).
(13) Remove the pitch change rod (150).
(14) Remove and discard the nuts (190) and washers (200) from the hub
bolts (210).
(15) Remove the hub bolts (210).
(a) If the spinner bulkhead is mounted to the propeller with the hub
bolts (210), remove the spinner bulkhead.
(16) Using a non-metallic tool, loosen the cylinder-side half of the hub (220).
(17) Remove the cylinder-side of the hub unit (220).
(a) Remove and discard the hub-to-pitch change rod O-ring (165) from the
cylinder-side of the hub unit (220).
(18) Remove and discard the hub guide bushing (230).
(19) Remove blade number 1 from the hub unit (220).
(20) Remove the fork (290).
(a) Remove and discard the three fork bumpers (300).
(21) Remove the remaining blades from the hub unit (220).

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(22) Remove the pitch change block (320) from each pitch change knob.
(a) Make a mark to indicate the orientation (up or down) of the thin wall of
each pitch change block (320) to the fork (290).
(b) Remove and discard the pitch change block button (310) from each pitch
change block (320).
B. Hub Disassembly
(1) For hub unit disassembly instructions, refer to the Aluminum Hub Overhaul
chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).
(2) Disassembly of the Engine-side Half of the Hub Unit
(a) Remove the engine-side half of the hub (220) from the rotatable fixture.
(b) Remove and discard the O-ring (540).
(c) Remove the pitch change rod hub bushing (280) from the engine-side half
of the hub (220).
1 Remove and discard the external retaining ring (250).
2 Remove the rod hub bushing (280) from the engine-side half of the
hub (220).
3 Remove and discard the O-ring (240) from the OD of the rod hub
bushing (280).
(3) Disassembly of the Hub Mounting Hardware
(a) Push out the spring pin (520) from the nut (510) and the mounting
stud (500).
(b) Using a wrench, hold the mounting nut (510) and use a standard stud
removal tool to remove the mounting stud (500) from the mounting
nut (510).
(c) Discard the mounting stud (500), mounting nut (510), spring pin (520),
and washer (530).
(d) Repeat steps (3)(a) through (3)(c) of this procedure for the remaining
mounting studs (500).

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C. Disassembly of the Blade Retention Parts

(1) Remove and discard the blade O-ring (720).
(2) Remove the hub-side blade bearing race (660).
(3) Remove and discard the bearing balls (640).
(4) Remove and discard the ball spacer (650).
(5) Remove and discard the pitch change knob bushing (730).
(6) Remove the blade seal (700) and the blade shim (680) from the blade.
(a) To make reassembly of the propeller easier, measure the thickness of the
blade shim (680) and make a record of the measurement.
(7) Remove and discard the O-ring (690) from the ID of the blade seal (700).
(8) Remove and discard the O-ring (710) from the OD of the blade seal (700).
(9) Remove and discard the internal spiral retaining ring (620) from the bore of
the blade.
(10) Remove the blade plug (610).
(a) Turn a screw with 8-32 UNC-3B threads into the threaded hole in the
blade plug (610).
(b) Pull the blade plug (610) from the bore of the blade.
(11) Remove and discard the O-ring (600) from the OD of the blade plug (610).
(12) Using a suitable gear puller or brass drift, remove the bearing retaining
ring (670).
(13) Remove the blade-side blade bearing race (630) of the blade retention bearing.
D. Blade Disassembly
(1) For composite blade overhaul procedures, refer to Hartzell Propeller Inc.
Composite Propeller Blade Maintenance Manual 135F (61-13-35).

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CLEANING - CONTENTS

1. Cleaning Procedures............................................................................................... 4-3

A. General Cleaning............................................................................................... 4-3
B. Cleaning Steel Parts for Magnetic Particle Inspection....................................... 4-3
C. Cleaning Steel Parts for Cadmium Replating Procedures................................. 4-3
D. Cleaning Aluminum Parts for Penetrant Inspection............................................ 4-3
E. Cleaning Aluminum Parts for Chromic Acid Anodizing Procedures................... 4-3
F. Cleaning Cylinder Threads................................................................................. 4-3

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1. Cleaning Procedures (Rev. 1)

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

B. 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).

C. 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).

D. Cleaning Aluminum Parts for Penetrant Inspection

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

E. 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).

F. Cleaning Cylinder Threads (Rev. 1)

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: DO NOT USE GLASS BEAD OR OTHER ABRASIVE CLEANING

METHODS, AS THEY MAY CAUSE EXCESSIVE DAMAGE TO THE
CYLINDER THREADS.
(1) It is preferable that the cylinder threads be cleaned only with solvent CM23;
however, removal of sealant in the threaded area can be difficult.
(2) Plastic media may be used to remove the sealant from the cylinder threads,
if minimal pressure and duration is used to minimize possible abrasion of the
aluminum threads.

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CHECK - CONTENTS

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

2. Dimensional Inspection............................................................................................ 5-3
A. Diameter Measurements..................................................................................... 5-3
B. Decimal Places................................................................................................... 5-3
3. Inspection Criteria/Procedures................................................................................. 5-4
A. Propeller Components........................................................................................ 5-4
B. Hubs.................................................................................................................... 5-4
C. Blades................................................................................................................. 5-4
D. Ice Protection Systems....................................................................................... 5-4
E. Spinner Assemblies............................................................................................. 5-4
F. Special Inspections (Lightning Strike, Foreign Object Strike, etc.)..................... 5-4
4. Propeller Component Checks................................................................................... 5-5
A. SET SCREW (Item 30)........................................................................................ 5-7
B. CYLINDER (Item 40)........................................................................................... 5-9
C. PISTON (Item 80).............................................................................................. 5-11
D. SPRING SEAT (Item 100)................................................................................. 5-13
E. COMPRESSION SPRING (Item 110 and Item 115).......................................... 5-15
F. STOP SLEEVE or STOP COLLAR (Item 120 and Item 125)............................ 5-17
G. SPRING GUIDE (Item 140)............................................................................... 5-19
H. PITCH CHANGE ROD (Item 150)..................................................................... 5-21
I. HEX HEAD BOLT (Item 210)............................................................................ 5-23
J. FORK (Item 290)............................................................................................... 5-27
K. BUMPER EXTENSION (Item 295).................................................................... 5-29
L. PITCH CHANGE BLOCK (Item 320)................................................................. 5-31
M. HUB PLUG (Item 370)...................................................................................... 5-33
N. BLADE PLUG (Item 610).................................................................................. 5-35
O. RACE (Item 630 and Item 660) ........................................................................ 5-37
P. BEARING RETAINING RING (Item 670).......................................................... 5-41
Q. BLADE SHIM (Item 680)................................................................................... 5-43
R. BLADE SEAL (Item 700)................................................................................... 5-45
S. BALANCE WEIGHT (Item 810) ........................................................................ 5-47

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LIST OF FIGURES
Set Screw.......................................................................................... Figure 5-1................. 5-6
Cylinder............................................................................................. Figure 5-2................. 5-8
Piston ............................................................................................... Figure 5-3............... 5-10
Spring Seat........................................................................................ Figure 5-4............... 5-12
Compression Spring.......................................................................... Figure 5-5............... 5-14
Stop Sleeve....................................................................................... Figure 5-6............... 5-16
Spring Guide..................................................................................... Figure 5-7............... 5-18
Pitch Change Rod ............................................................................ Figure 5-8............... 5-20
Hex Head Bolt................................................................................... Figure 5-9............... 5-22
A-2043-1 Nut Modification................................................................. Figure 5-10............. 5-24
Fork................................................................................................... Figure 5-11.............. 5-26
Bumper Extension............................................................................. Figure 5-12............. 5-28
Pitch Change Block........................................................................... Figure 5-13............. 5-30
Hub Plug ........................................................................................... Figure 5-14............. 5-32
Blade Plug Inspection Area............................................................... Figure 5-15............. 5-34
Race.................................................................................................. Figure 5-16............. 5-36
Bearing Retaining Ring..................................................................... Figure 5-17............. 5-40
Blade Shim........................................................................................ Figure 5-18............. 5-42
Blade Seal......................................................................................... Figure 5-19............. 5-44
Balance Weight................................................................................. Figure 5-20............. 5-46

LIST OF TABLES

Component Inspection Criteria.......................................................... Table 5-1................... 5-7

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1. Inspection Interval Requirements (Rev. 1)

A. General
(1) For information about life limited components and mandatory inspections, refer
to the Airworthiness Limitations chapter of the applicable Hartzell Propeller Inc.
owner's manual.
(2) For overhaul periods of Hartzell Propeller Inc. propellers, refer to Hartzell
Propeller Inc. Service Letter HC-SL-61-61Y.
2. Dimensional Inspection (Rev. 1)

A. Diameter Measurements
(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) When measuring the diameter of a part with a three point measuring
instrument, take one measurement. A measurement outside the specified
tolerance is cause for retirement of the part.

B. Decimal Places
(1) 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.

CHECK 61-10-90 Page 5-3

Rev. 2 Nov/19
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3. Inspection Criteria/Procedures

A. Propeller Components (Except for those listed separately in this section)

(1) Refer to Table 5-1, "Component Inspection Criteria" in this chapter.

B. Hubs
(1) Aluminum Hubs: Refer to the Aluminum Hub Overhaul chapter of Hartzell
Propeller Inc. Standard Practices Manual 202A (61-01-02).

C. Blades
(1) Aluminum Blades: Refer to Hartzell Propeller Inc. Aluminum Blade Overhaul
Manual 133C (61-13-33).
(2) Composite Blades: Refer to Hartzell Propeller Inc. Composite Propeller Blade
Maintenance Manual 135F (61-13-35).

D. Ice Protection Systems

(1) For ice protection systems supplied by Hartzell, refer to Hartzell Propeller
Inc. Ice Protection System Manual 180 (30-61-80).
(2) For ice protection systems not supplied by Hartzell, refer to the applicable
TC or STC holder’s Instructions for Continued Airworthiness (ICA).

E. Spinner Assemblies
(1) Metal Spinners: Refer to Hartzell Propeller Inc. Metal Spinner Maintenance
Manual 127 (61-16-27).
(2) Composite Spinners: Refer to the following Hartzell Propeller Inc.
maintenance manuals:
(a) Composite Spinner Maintenance Manual 148 (61-16-48)
(b) Composite Spinner Field Maintenance and Minor Repair Manual 173
(61-10-73)

F. Special Inspections (Lightning Strike, Foreign Object Strike, etc.)

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

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Rev. 2 Nov/19
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4. Propeller Component 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.

Refer to Table 5-1, "Component Inspection Criteria" in this chapter.

CHECK 61-10-90 Page 5-5

Rev. 2 Nov/19
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Threads

102472 Set Screw

Threads
Air Bleed Hole

A-4257 Set Screw

TPI-MB-0226
TPI-102472

Set Screw
Figure 5-1

CHECK 61-10-90 Page 5-6

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

A. SET SCREW
(Item 30)
Refer to Figure 5-1

NOTE: A-4257 Set Screw (Low Pitch Stop) has an air bleed hole.
102472 Set Screw (Low Pitch Stop) does not have an air bleed hole.

(1) Visually examine the Slight damage is permitted. If the damage is greater than
pitch change rod contact Damage must not affect the the permitted serviceable limits,
surface on the set screw for performance of the set screw. replace the set screw.
damage.

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

(3) Visually examine the One damaged thread is If the damage is greater than
threads of the set screw permitted. the permitted serviceable limits,
for damage. replace the set screw.

(4) A-4257 set screw only: The air bleed hole must not be Use a piece of safety wire or
Examine the air bleed hole blocked. equivalent to clear unwanted
in the center of the set material from the air bleed hole.
screw. If the air bleed hole cannot be
cleared, replace the set screw.

(5) Visually examine the set Minor wear on corners and a If the cadmium plating coverage
screw for cadmium plating few light random scratches are is less than the permitted
coverage. permitted; otherwise cadmium serviceable limits, cadmium
plating must completely cover replate and bake the set screw
the set screw. for a minimum of 23 hours
within four hours of plating in
accordance with the Cadmium
Replating chapter of Hartzell
Propeller Inc. Standard
Practices Manual 202A
(61-01-02).

CHECK 61-10-90 Page 5-7

Rev. 2 Nov/19
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OD

Cylinder Wrench
Attachment Hole
(1 of 4)

Set Screw Hole

Threads

Cylinder Wrench
Attachment Hole
(1 of 4)

Cylinder Mounting
Threads

Cylinder-To-Hub
O-Ring Groove Wall
thickness
TPI-490-B-2428-( )-A
TPI-490-B-2428-( )

Cylinder
Figure 5-2

CHECK 61-10-90 Page 5-8

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

B. CYLINDER
(Item 40)
Refer to Figure 5-2.

(1) Visually examine the On the OD, the maximum If the damage is greater than the
anodized coating of the permitted depth of damage is permitted serviceable limits,
cylinder for wear, nicks, 0.003 inch (0.07 mm). replace the cylinder.
scratches, or other
damage. For all other surfaces, damage
is not permitted.

(2) Visually examine the If there is wear, measure If the ID is greater than the
cylinder-to-hub O-ring the ID of the cylinder-to-hub permitted serviceable limit,
groove for wear. O-ring groove. The maximum replace the cylinder.
permitted O-ring groove ID is
4.8750 inches (123.825 mm).

(3) Visually examine the If there is damage, install a If the damage is greater than
cylinder wrench 1/4-28UNF-3B screw and the permitted serviceable
attachment holes for make sure that it will tighten to limits, repair the cylinder
thread damage. attach the cylinder wrench for wrench attachment holes in
installation and removal. accordance with the section
"Repair of Damaged Cylinder
Wrench Attachment Holes"
in the Standard Repairs and
Instructions chapter of Hartzell
Propeller Inc. Standard Practices
Manual 202A (61-01-02). If a
previously repaired hole has
damage that is greater than the
permitted serviceable limits,
replace the cylinder.

(4) Visually examine the set 1/2 of one thread total If the damage is greater than
screw hole threads for accumulated damage is the permitted serviceable limits,
damage. permitted. replace the cylinder.

(5) If repaired with a threaded The minimum permitted wall If the wall thickness under the
insert, measure the wall thickness under the point point of the hole is less than
thickness under the point (center) of the hole is the permitted serviceable limits,
of the cylinder wrench 0.080 inch (2.04 mm). replace the cylinder.
attachment holes.

CHECK 61-10-90 Page 5-9

Rev. 2 Nov/19
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"E"
Diameter
"A"
Diameter

"B" "D"
Width Diameter
"C"
Diameter

Part Number "A" "B" "C" "D" "E"

Maximum Maximum Minimum Maximum Minimum
Diameter Diameter Diameter Diameter Diameter
B-2419 0.738 inch 0.270 inch 4.358 inch 0.856 inch 4.706 inch
(18.74 mm) (6.85 mm) (110.70 mm) (21.74 mm) (119.54 mm)
APS2280

Piston
Figure 5-3

CHECK 61-10-90 Page 5-10

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

C. PISTON
(Item 80)
Refer to Figure 5-3.

(1) Measure diameter "A" of Refer to Figure 5-3 for the "A" If the diameter in area "A" is
the piston. dimensional limit. greater than the serviceable
limits, replace the piston.

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

(3) Visually examine the If there is wear, measure the If the diameter in area "B" or
piston for wear in areas diameter. Refer to Figure 5-3 area "D" is greater than the
"B" and "D". for the "B" and "D" dimensional serviceable limits, replace the
limits. piston.

(4) Visually examine the If there is wear, measure the If the diameter in area "C" or
piston for wear in areas diameter. Refer to Figure 5-3 "E" is less than the serviceable
"C" and "E". for the "C" and "E" dimensional limits, replace the piston.
limits.

(5) Visually examine the Corrosion is not permitted. If Remove corrosion using glass
nut contact surface for there is corrosion, remove it in bead cleaning. Refer to the
corrosion, wear, or damage. accordance with the corrective Cleaning chapter of Hartzell
action repair limits. The Propeller Inc. Standard Practices
maximum permitted depth of Manual 202A (61-01-02). If the
wear or damage is 0.007 inch corrosion cannot be removed or
(0.17 mm). if the wear or damage is greater
than the serviceable limits,
replace the piston.

CHECK 61-10-90 Page 5-11

Rev. 2 Nov/19
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"A"

Shoulder "B"

TPI-106565

Spring Seat
Figure 5-4

CHECK 61-10-90 Page 5-12

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

D. SPRING SEAT
(Item 100)
Refer to Figure 5-4.

(1) Visually examine the spring Corrosion is not permitted. Remove corrosion using glass
seat for corrosion and If there is corrosion, remove bead cleaning. Refer to the
pitting. it in accordance with the Cleaning chapter of Hartzell
corrective action repair limits. Propeller Inc. Standard Practices
The maximum permitted Manual 202A (61-01-02). If the
depth of pitting is 0.005 inch corrosion cannot be removed
(0.12 mm). or if the pitting is greater than
the permitted serviceable limits,
replace the spring seat.

(2) Visually examine the spring The maximum permitted depth Remove material that is raised
seat for damage. of damage is 0.010 (0.25 mm) above the normal machined
surface. If the depth of damage
is greater than the permitted
serviceable limits, replace the
spring seat.

(3) Visually examine If there is wear, measure If the measurement of

diameter "A" for wear. diameter "A". The maximum diameter "A" is greater than the
permitted diameter is permitted serviceable limits,
2.045 inch (51.94 mm). replace the spring seat.

(4) Visually examine shoulder If there is wear, measure the If the thickness of shoulder "B"
"B" for wear. thickness of shoulder "B". is less than the permitted
The minimum permitted serviceable limits, replace the
thickness of shoulder "B" spring seat.
is 0.070 inch (1.78 mm).

CHECK 61-10-90 Page 5-13

Rev. 2 Nov/19
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TPI-1101330

Compression Spring
Figure 5-5

CHECK 61-10-90 Page 5-14

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

E. COMPRESSION SPRING
(Item 110 and Item 115)
Refer to Figure 5-5.

(1) Visually examine the Corrosion is not permitted. Remove corrosion using glass
compression spring for If there is corrosion, remove bead cleaning. Refer to the
wear, corrosion, or other it in accordance with the Cleaning chapter of Hartzell
damage. corrective action repair limits. Propeller Inc. Standard Practices
The maximum permitted Manual 202A (61-01-02). If the
depth of damage is 0.003 inch corrosion cannot be removed
(0.07 mm). or the damage is deeper than
the permitted serviceable limit,
replace the compression spring.

(2) Visually examine the A few random scratches are Apply a layer of zinc chromate
compression spring for zinc permitted; otherwise, complete primer to the spring in
plating or zinc chromate coverage of zinc plating or zinc accordance with the section,
primer coverage. chromate primer on all surfaces "Spring Zinc Chromate Primer
is required. Repair" in the Repair chapter of
this manual.

(3) Measure the free length of The minimum permitted free If the free length is less than
the compression spring. length is 2.875 inches the permitted serviceable limit,
(73.02 mm). replace the compression spring.

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

CAUTION: Do not strip

the zinc plating.
If the plating
is removed,
replace the
compression
spring.

CHECK 61-10-90 Page 5-15

Rev. 2 Nov/19
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TPI-101335

Stop Sleeve
Figure 5-6

CHECK 61-10-90 Page 5-16

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

F. STOP SLEEVE OR STOP COLLAR

(Item 120 and 125)
Refer to Figure 5-6.

(1) Visually examine the Corrosion is not permitted. If Remove corrosion using glass
surface of the stop sleeve there is corrosion, remove it in bead cleaning. Refer to the
or stop collar for corrosion. 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 stop sleeve or stop
collar.

(2) Visually examine the The maximum permitted depth If wear, nick, scratch, or other
surface of the stop sleeve of wear, nick, scratch, or other damage is greater than the
or stop collar for wear, damage is 0.05 inch (1.2 mm). permitted serviceable limits,
nicks, scratches, or other replace the stop sleeve or stop
damage. collar.

(3) Visually examine the stop Pushed up material may not be Blend the pushed up material
sleeve or stop collar for above or outside the machined with the surrounding area.
pushed up material that surface of the part. Refer to the section, "Aluminum
is above the surrounding and Steel Parts" in the Repair
surface. chapter of this manual for repair
procedures.

CHECK 61-10-90 Page 5-17

Rev. 2 Nov/19
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TPI-106564

Spring Guide
Figure 5-7

CHECK 61-10-90 Page 5-18

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

G. SPRING GUIDE
(Item 140)
Refer to Figure 5-7.

(1) Visually examine the spring Corrosion is not permitted. Remove corrosion using glass
guide for corrosion and If there is corrosion, remove bead cleaning. Refer to the
pitting. it in accordance with the Cleaning chapter of Hartzell
corrective action repair limits. Propeller Inc. Standard Practices
The maximum permitted area Manual 202A (61-01-02). If the
of pitting is 20% of the spring corrosion cannot be removed
guide surface. or if the pitting is greater than
the permitted serviceable limits,
replace the spring guide.

(2) Visually examine both sides If there is wear, measure the If the depth of wear is greater
of the spring guide for wear. depth of wear. The maximum than the permitted serviceable
permitted depth of wear is limits, replace the spring guide.
0.010 inch (0.25 mm). When
there is wear on both sides
of the spring guide, the total
of both wear depths must not be
greater than 0.010 inch
(0.25 mm). Wear that could
affect correct fit or function is
not permitted.

(3) Visually examine the spring Damage that extends all If the damage is greater than
guide for nicks, scratches, the way through the spring the permitted serviceable limits,
gouges, or other damage. guide is not permitted. The replace the spring guide.
maximum permitted total area
of accumulated damage for
both sides of the spring guide
is 0.5 square inch
(161 square mm). Damage
that could affect correct fit or
function is not permitted.

(4) Visually examine the spring Minor wear on corners and If the cadmium plating coverage
guide for cadmium plating random light scratches are is less than the permitted
coverage. permitted; otherwise, the spring serviceable limits, replate the
guide must have complete spring guide in accordance
cadmium plating coverage. with the Cadmium Replating
chapter of Hartzell Propeller Inc.
Standard Practices Manual
202A (61-01-02). Baking is not
required.

CHECK 61-10-90 Page 5-19

Rev. 2 Nov/19
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Threads Threads
A B
"C"

Overall Length

No chrome
0.090 inch
(2.28 mm)
No chrome maximum
0.090 inch
(2.28 mm)
Smallest diameter of the taper maximum
"C"

Part Number Overall Length (inch) Overall Length (mm)

A-2418-3 14.815 376.30
A-2418-2 8.600 218.44
A-2418-8 8.850 224.79
A-2418-14 11.815 300.10
A-2418-15 9.180 233.17
A-2418-17 9.133 231.97
aps2059

Pitch Change Rod

Figure 5-8

CHECK 61-10-90 Page 5-20

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

H. PITCH CHANGE ROD

(Item 150)
Refer to Figure 5-8.

(1) Visually examine the Except for spots of missing If there is wear below the
chrome plating of the pitch chrome around the masking chrome plating, replace the pitch
change rod for damage. areas, for example the keeper change rod.
groove or the threads, any area
worn below the chrome plating
is not permitted.

(2) At both places on the One damaged thread in each If the damage is greater than
pitch change rod, visually location is permitted. the permitted serviceable limits,
examine external threads replace the pitch change rod.
for damage.

(3) Visually examine the taper Corrosion, wear, or damage is If corrosion, wear, or damage
area "C" for corrosion, wear, not permitted at the smallest causes high spots above the
and damage. diameter of the taper. The existing surface, remove only the
remaining taper surface may high spots. If corrosion, wear,
have a maximum corrosion, or damage is greater than the
wear, or damage to a depth of serviceable limits, replace the
0.004 inch (0.10 mm) over 25% pitch change rod.
of the surface area.

(4) Measure area "A" of the The minimum permitted If the diameter in area "A" is
pitch change rod. diameter in area "A" is less than the permitted
0.732 inch (18.59 mm). serviceable limits, replace
the pitch change rod.

(5) Measure area "B" of the The minimum permitted If the diameter in area "B" is
pitch change rod. diameter in area "B" is less than the permitted
0.662 inch (16.81 mm). serviceable limits, replace
the pitch change rod.

(6) Perform a magnetic particle A relevant indication is not If there is a relevant indication,
inspection of the pitch permitted. replace the pitch change rod.
change rod in accordance
with Hartzell Propeller Inc.
Standard Practices Manual
202A (61-01-02).

(7) Visually examine the Unwanted material is not Remove all unwanted material.
oil supply bore using a permitted.
borescope or fiber-optic
flashlight.

CHECK 61-10-90 Page 5-21

Rev. 2 Nov/19
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AREA "A"
Threads

Fillet
AREA "A"

Fillet

Hex Head
TPI-143012-2

Hex Head Bolt

Figure 5-9

CHECK 61-10-90 Page 5-22

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

I. HEX HEAD BOLT

(Item 210)
Refer to Figure 5-9.

(1) Visually examine the hex Corrosion is not permitted. The Corrosion may be removed using
head bolt for corrosion and maximum permitted depth of glass bead cleaning. Refer to
pitting. pitting is 0.002 inch (0.05 mm). the Cleaning chapter of Hartzell
No more that 5% of the total Propeller Inc. Standard Practices
unthreaded surface may be Manual 202A (61-01-02). If
pitted. The maximum permitted the pitting is greater than the
diameter of an individual pit is permitted serviceable limits,
0.032 inch (0.81 mm). Pitting replace the hex head bolt.
is not permitted in the fillet
between the hex head and the
grip, Area "A". Pitting must not
affect the fit or function of the
hex head bolt.

(2) Except for the threads, The maximum permitted depth Pushed up material may be
visually examine the hex of damage or a scratch is removed with a thread file. Use
head bolt for damage or 0.002 inch (0.05 mm). of the thread file must not affect
scratches. Scratches or damage must not the fit or function of the hex head
affect the fit or function bolt. If the depth of a scratch
of the hex head bolt. Pushed-up or damage is greater than the
material is not permitted. permitted serviceable limits or if
the scratch, damage, or repair
affects the fit or function of the
hex head bolt, replace the hex
head bolt.

(3) Visually examine the hex Circumferential scoring that If the scoring is greater than the
head bolt for circumferential reduces the diameter of the hex permitted serviceable limits or if
scoring caused by head bolt is not permitted. The the OD in Area "A" is less than
installation and removal. minimum permitted OD in the permitted serviceable limits,
Area "A" is 0.370 inch replace the hex head bolt.
(9.40 mm).

(4) Visually examine the Limited damage from wrenching Remove metal movement with a
wrenching surfaces of the is permitted, but it must be file or equivalent. Only corners
head of the hex head bolt possible to torque the hex head may be repaired. Refacing
for metal movement caused bolt and metal movement must a complete surface is not
by wrenching. not interfere with the installation permitted. If metal movement
of the hex head bolt or cause is greater than the permitted
damage to the hub. serviceable limits, replace the
hex head bolt.

CHECK 61-10-90 Page 5-23

Rev. 2 Nov/19
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CAUTION: DO NOT USE MODIFIED A-2043-1 NUTS ON THE PROPELLER

ASSEMBLY. A-2043-1 NUTS THAT HAVE BEEN MODIFIED ARE
TO BE USED ONLY FOR THE HEX HEAD BOLT THREAD CHECK.

Plastic Locking Element

Nut May Be Machined To Remove The
Plastic Locking Element And Metal
Housing Or Only The Plastic Locking
Element May Be Removed
TPI-143011-1

A-2043-1 Nut Modification

Figure 5-10

CHECK 61-10-90 Page 5-24

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

I. HEX HEAD BOLT, CONTINUED

(Item 210)
Refer to Figure 5-10.

(5) Visually examine the A maximum total accumulation Limited thread file repair is
threads of the hex head bolt of 3/4 thread of damage and permitted, but must be considered
for damage and pitting. pitting is permitted. Thread as thread damage. If the damage
damage must not cause and pitting is greater than the
damage to the mating part. permitted serviceable limits,
An A-2043-1 nut with the plastic replace the hex head bolt.
locking element removed should
be able to be freely rotated by
hand on the bolt threads. For
the modification of the nut, refer
to Figure 5-10.

(6) Magnetic particle inspect A relevant indication is not If there is a relevant indication,
each bolt in accordance permitted. replace the hex head bolt.
with the Magnetic Par-
ticle Inspection chapter
of Hartzell Propeller Inc.
Standard Practices
Manual 202A (61-01-02).
NOTE: It is not necessary
to strip the
cadmium plating
from the hex
head bolt before
magnetic particle
inspection.

(7) Visually examine the hex Cadmium plating must If cadmium plating coverage
head bolt for cadmium completely cover the bolt with is less than the permitted
plating coverage. the following exceptions: A few serviceable limits, cadmium
scratches and corners with replate and bake for a minimum
cadmium plating missing, minor of 23 hours within four hours
abrading of cadmium plating on after plating the hex head bolt
the threads, or minor abrading in accordance the Cadmium
of the cadmium plating on the Replating chapter of Hartzell
hex head because of wrenching Propeller Inc. Standard Practices
are permitted. Manual 202A (61-01-02).

CHECK 61-10-90 Page 5-25

Rev. 2 Nov/19
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Three-Blade Fork Assembly

Fork Slot

Pitch Change Rod

Engagement Threads

Tapered Portion
of the Fork Bore

Four-Blade Fork Assembly

Pitch Change Rod
Fork Slot Engagement Threads

Tapered Portion
of the Fork Bore
TPI-105732, TPI-MB-0357

Fork
Figure 5-11

CHECK 61-10-90 Page 5-26

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

J. FORK
(Item 290)
Refer to Figure 5-11.

(1) Visually examine the Corrosion is not permitted. Remove corrosion using glass
cadmium plating of the If there is corrosion, remove it bead cleaning. Refer to the
fork (excluding the slots, in accordance with the Cleaning chapter of Hartzell
threaded bore, and tapered corrective action repair limits. Propeller Inc. Standard Practices
section of the bore) for The maximum permitted Manual 202A (61-01-02). If the
corrosion, pitting, wear, depth of pitting, wear, scratches, corrosion cannot be removed
scratches, or other damage. or damage is 0.003 inch or if the pitting, wear, scratches,
(0.07 mm). or damage is greater than the
permitted serviceable limits,
replace the fork.

(2) Visually examine the pitch One thread of total accumulated If the damage is greater than
change rod engagement damage in each hole is the permitted serviceable limits,
threads of the fork bore for permitted. replace the fork.
damage.

(3) Visually examine the If there is wear, nicks, fretting, or If wear, nicks, fretting, or
tapered portion of the damage, measure the depth of damage is greater than the
fork bore for wear, nicks, wear or damage. The maximum permitted serviceable limits,
fretting, or other damage. permitted depth of wear, nicks, replace the fork.
fretting, or damage is 0.003 inch
(0.07 mm).

(4) Visually examine the fork If there is damage, measure the If the damage is greater than the
slots for damage. depth of damage. The maximum permitted serviceable limits,
permitted depth of damage is replace the fork.
0.006 inch (0.15 mm).

(5) Perform a magnetic A relevant indication is not If a relevant indication can be

particle inspection of the permitted repaired and is within the
fork in accordance with permitted serviceable limits in
the Hartzell Propeller Inc. this section, cadmium replate
Standard Practices and bake the fork in accordance
Manual 202A (61-01-02). with the Cadmium Replating
NOTE: Remove the chapter of Hartzell Propeller Inc.
cadmium Standard Practices Manual 202A
plating (61-01-02). If the relevant
from the fork indication cannot be repaired
before within the permitted serviceable
magnetic limits, replace the fork.
particle
inspection.

CHECK 61-10-90 Page 5-27

Rev. 2 Nov/19
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Hex Area

W10228

Bumper Extension
Figure 5-12

CHECK 61-10-90 Page 5-28

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

K. BUMPER EXTENSION
(Item 295)
Refer to Figure 5-12

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

(2) Visually examine the A slight wrenching depression If the damage is greater than
bumper extension for on the outer hex area of the the permitted serviceable limits,
damage. bumper extension is permitted. replace the bumper extension.

(3) Visually examine the A maximum of 1/2 of one thread If the damage is greater than
threads of the bumper total accumulated damage is the permitted serviceable limits,
extension for damage. permitted. replace the bumper extension.

(4) Visually examine the A few random scratches and If the cadmium plate coverage
bumper extension for slight wear on the threads are is less than the permitted
cadmium plate coverage. permitted; otherwise, cadmium serviceable limits, cadmium
plating must completely cover replate in accordance with the
the spacer. Cadmium Replating chapter of
Hartzell Propeller Inc. Standard
Practices Manual 202A
(61-01-02).

CHECK 61-10-90 Page 5-29

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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C
B

Part
"A" Minimum "B" Maximum "C" Minimum
Number
0.869 inch 0.6890 inch 0.575 inch
105733
(22.08 mm) (17.500 mm) (14.61 mm)
TPI-490-002

Pitch Change Block

Figure 5-13

CHECK 61-10-90 Page 5-30

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

L. PITCH CHANGE BLOCK

(Item 320)
Refer to Figure 5-13.

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

(2) Visually examine the pitch If there is wear, measure the If the wear is greater than the
change block for wear. pitch change block. Refer to permitted serviceable limits,
Figure 5-13 for the maximum replace the pitch change block.
permitted wear dimensions.

(3) Magnetic particle inspect A relevant indication is not If there is a relevant indication,
the pitch change block in permitted. replace the pitch change block.
accordance with Hartzell
Propeller Inc. Standard
Practices Manual 202A
(61-01-02).

CHECK 61-10-90 Page 5-31

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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"C"

"A"

"B" "D"

Hub Plug Removal Feature

"A" "B" "C" "D"

Part
Minimum O-ring Maximum O-ring Minimum Plug Maximum Bore
Number
Groove OD Groove ID OD ID

2.015 inch 0.846 inch 2.246 inch 0.670 inch

A-2481
(51.18 mm) (21.48 mm) (57.05 mm) (17.01 mm)
TPI-A2481

Hub Plug
Figure 5-14

CHECK 61-10-90 Page 5-32

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

M. HUB PLUG
(Item 370)
Refer to Figure 5-14.

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

(2) Visually examine the If the hub plug O-ring groove If the hub plug O-ring groove
O-ring groove OD "A". OD "A" is worn or damaged, OD "A" is less than the permitted
measure in accordance with serviceable limits, replace the
Figure 5-14. hub plug.

(3) Visually examine the If the hub plug O-ring groove If the hub plug O-ring groove
O-ring groove ID "B". ID "B" is worn or damaged, ID "B" is greater than the
measure in accordance with permitted serviceable limits,
Figure 5-14. replace the hub plug.

(4) Visually examine the hub If the hub plug OD "C" is If the hub plug OD "C" is less
plug OD "C". worn or damaged, measure than the permitted serviceable
in accordance with Figure 5-14. limits, replace the hub plug.

(5) Visually examine the hub If the hub plug ID bore "D" is If the hub plug ID bore "D"
plug ID bore "D". worn or damaged, measure in is greater than the permitted
accordance with Figure 5-14. serviceable limits, replace the
hub plug.

(6) Visually examine the hub Slight damage is permitted. If the damage is greater than
plug removal feature for Damage must not interfere the permitted serviceable limits,
damage. with the ability to remove the replace the hub plug.
hub plug from the hub.

CHECK 61-10-90 Page 5-33

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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Threads

TPI-106048

Blade Plug Inspection Area

Figure 5-15

CHECK 61-10-90 Page 5-34

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

N. BLADE PLUG
(Item 610)
Refer to Figure 5-15.

(1) Visually examine the Corrosion is not permitted. If Remove corrosion to a maximum
blade plug for corrosion there is corrosion, remove it in depth of 0.010 inch (0.25 mm)
and pitting. accordance with the corrective using glass bead cleaning. If the
action repair limits. corrosion cannot be removed,
replace the blade plug. Refer to
The maximum permitted the Cleaning chapter of Hartzell
depth of pitting is 0.010 inch Propeller Inc. Standard Practices
(0.25 mm). The maximum Manual 202A (61-01-02). If
permitted total area of pitting is the depth or amount of pitting
20% of the blade plug surface. is greater than the permitted
serviceable limits, replace the
blade plug.

(2) Visually examine the A maximum of one thread of If the damage is greater than
threads of the blade plug total accumulated damage is the permitted serviceable limits,
for damage. permitted. replace the blade plug.

(3) Visually examine the blade The maximum permitted Using an abrasive pad CM47
plug for scratches, gouges, depth of a scratch, gouge, or or equivalent, polish pushed
or other damage. other damage is 0.010 inch up material to blend with the
(0.25 mm). Damage must not surrounding surfaces. If a
interfere with the fit of the blade scratch, gouge, or other damage
plug in the blade bore. is greater than the permitted
serviceable limits, replace the
blade plug.

CHECK 61-10-90 Page 5-35

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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Hub Contact
Surface

Hub-side Race

Radial
Depth

Ball Bearing Groove

(dashed lines)

Blade-side Race
Outer
Diameter

Blade Contact Surface

Chips Cracks

Race Mating Surface

Chips
TPI-MB-0202

Race
Figure 5-16

CHECK 61-10-90 Page 5-36

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

O. RACE
(Item 630 and Item 660)
Refer to Figure 5-16.

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

(2) Visually examine the ball The maximum permitted depth of If the pitting is greater than the
bearing groove in each pitting is 0.003 inch (0.076 mm) serviceable limits, replace the
race for pitting, wear, in the bearing ball groove. race.
fretting, and damage.
The maximum permitted
diameter of a pit is 0.032 inch
(0.81 mm).

The maximum permitted total

area of pitting in the ball bearing
groove on a complete race is
0.12 square inch
(77.4 square mm) (two races for
each bearing set). Pitting must
not interfere with bearing ball
movement or support.

If the ball bearing groove has If the wear is greater than the
wear, measure the wear. The permitted serviceable limits,
maximum permitted depth of replace the race.
wear is 0.005 inch (0.12 mm).

Fretting damage is not permitted. If there is fretting damage,

replace the race.

For damage other than pitting or If the damage is greater than

fretting, the maximum permitted the permitted serviceable limits,
depth of damage is 0.003 inch replace the race.
(0.076 mm) and must not
interfere with bearing ball
movement or support.

CHECK 61-10-90 Page 5-37

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

O. RACE, CONTINUED
(Item 630 and Item 660)
Refer to Figure 5-16.

(3) Except for the ball Corrosion is not permitted. If Remove corrosion using glass
bearing groove, visually there is corrosion, remove it in bead cleaning. For glass bead
examine all other accordance with the corrective cleaning refer to the Cleaning
surfaces of each race for action repair limits. chapter of Hartzell Propeller
corrosion. Inc. Standard Practices
Manual 202A (61-01-02). If the
corrosion cannot be removed,
replace the race.

(4) Except for the ball The maximum permitted If the pitting is greater than the
bearing groove, visually depth of pitting is 0.005 inch permitted serviceable limits,
examine all other (0.12 mm). replace the race.
surfaces of each race for
pitting, wear, fretting, and The maximum permitted
damage. diameter of a pit is 0.062 inch
(1.57 mm).

The maximum permitted

total area of pitting on all
surfaces except the ball
bearing groove of a complete
race is 0.25 square inch
(161.2 square mm) (two races for
each bearing set)..

Fretting damage is permitted on Clean the fretted area

the outer diameter of the races thoroughly using an abrasive
that interface with the bearing pad CM47 or equivalent to
retaining ring (670). Fretting must decrease fretting damage to
not loosen the tight fit with the a minimum. If the fit of the
bearing retaining ring (670). bearing retaining ring (670)
to the race is not tight, replace
the race.

Wear is not permitted. If there is wear, replace the

race.

For damage other than pitting, If the damage is greater than

the maximum permitted depth the permitted serviceable limits,
of damage is 0.005 inch replace the race.
(0.12 mm) and must not interfere
with the mating surfaces.

CHECK 61-10-90 Page 5-38

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

O. RACE, CONTINUED
(Item 630 and Item 660)
Refer to Figure 5-16.

(5) Visually examine the race Chips or cracks that are adjacent If there are chips or cracks
for chips or cracks that to the race mating surfaces are that are adjacent to the
are adjacent to the mating not permitted. mating surfaces of the race,
surfaces of the race. replace the race.

(6) Magnetic particle inspect A relevant indication is not If there is a relevant

each race in accordance permitted. indication, replace the race.
with the Magnetic Particle
Inspection chapter of
Hartzell Propeller Inc.
Standard Practices
Manual 202A (61-01-02).

CHECK 61-10-90 Page 5-39

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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Area "A"

BEARING RETAINING RING B-7071

B-7071

Bearing Retaining Ring

Figure 5-17

CHECK 61-10-90 Page 5-40

Rev. 2 Nov/19
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

P. BEARING RETAINING RING

(Item 670)
Refer to Figure 5-17.

(1) Except for Area “A”, Corrosion is not permitted. If Remove corrosion using glass
visually examine the there is corrosion, remove it in bead cleaning. Refer to the
bearing retaining ring for accordance with the corrective Cleaning chapter of Hartzell
corrosion and pitting. action repair limits. Propeller Inc. Standard Practices
Manual 202A (61-01-02). If the
The maximum permitted corrosion cannot be removed,
depth of pitting is 0.005 inch replace the bearing retaining
(0.12 mm). Pitting must not ring. If the corrosion or pitting
interfere with the ability of the is greater than the permitted
bearing retaining ring to fit serviceable limits, replace the
tightly to the blade and the bearing retaining ring.
bearing race.

(2) Visually examine the Corrosion, pitting, or wear If there is corrosion, pitting,
bearing retaining ring for through the cadmium plating in or wear through the cadmium
corrosion, pitting, or wear Area "A" is not permitted. plating, replace the bearing
in Area "A”. retaining ring.

(3) Except for Area "A", The bearing retaining ring must If wear, damage, or fretting
visually examine the fit tightly to the blade and the is greater than the permitted
bearing retaining ring for bearing race when installed serviceable limits, replace the
wear, damage, or fretting. over the blade and bearing bearing retaining ring.
race.

(4) Visually examine the entire A few random scratches If cadmium plating is not on all
bearing retaining ring for and corners with cadmium surfaces, replate the bearing
cadmium plating coverage. plating missing are permitted; retaining ring in accordance
otherwise, complete coverage with the Cadmium Replating
is required. chapter of Hartzell Propeller Inc.
Standard Practices Manual 202A
(61-01-02).

CHECK 61-10-90 Page 5-41

Rev. 2 Nov/19
PROPELLER MAINTENANCE MANUAL
490

Thickness

TPI-105758

Blade Shim
Figure 5-18

CHECK 61-10-90 Page 5-42

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

Q. BLADE SHIM
(Item 680)
Refer to Figure 5-18.

(1) Visually examine the blade Damage, missing material, If there is damage, missing
shim for damage, missing separation, or form irregularities material, separation, or form
material, separation, or are not permitted. irregularities, replace the
form irregularities as a blade shim.
continuous ring.

(2) Measure the thickness of The minimum permitted If the thickness is less than the
the blade shim. thickness of the blade shim permitted serviceable limits,
is 0.040 inch (1.02 mm). replace the blade shim.

(3) Measure the thickness The maximum permitted If the thickness variation is
variation of the blade shim thickness variation is greater than the permitted
at five equally spaced 0.005 inch (0.12 mm). serviceable limits, replace the
places on the blade shim. blade shim.

CHECK 61-10-90 Page 5-43

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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Diameter Diameter
"A" "A"

Diameter
"B"

Diameter
"E"

Width "C2"
Width "C1"
O-ring Groove
Width "F"

Thickness "D"

"A" "B" "C1" "C2" "D" "E"

MAXIMUM MAXIMUM MINIMUM MINIMUM MINIMUM MINIMUM
DIAMETER DIAMETER WIDTH WIDTH THICKNESS DIAMETER

4.550 inches 4.750 inches 0.060 inch 0.050 inch 0.065 inch 5.075 inches
(115.57 mm) (120.65 mm) (1.53 mm) (1.27 mm) (1.66 mm) (128.91 mm)
106064

Blade Seal
Figure 5-19

CHECK 61-10-90 Page 5-44

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

R. BLADE SEAL
(Item 700)
Refer to Figure 5-19

NOTE: Blade seals identified as 106117 (Rev. B or before), must be replaced with blade seals
identified as 106117 (Rev. C or later) or 107223.

(1) Visually examine the blade Corrosion is not permitted. If Using an abrasive pad CM47
seal for corrosion, pitting, there is corrosion, remove it in or equivalent, polish to remove
wear, or damage. accordance with the corrective corrosion, pitting, wear, or
action repair limits. If there damage to a maximum depth
is pitting, wear, or damage, of 0.010 inch (0.25 mm). If the
measure the depth. The depth of corrosion, pitting, wear,
maximum permitted depth of damage, or repair is greater than
pitting, wear or damage is the permitted serviceable limits
0.007 inch (0.17 mm). or the corrective action limits,
replace the blade seal.

(2) Measure the O-ring groove The maximum permitted If the O-ring groove Width "F"
Width "F". O-ring groove Width "F" is greater than the permitted
is 0.175 inch (4.44 mm). serviceable limits, replace the
blade seal.

(3) Measure the O-ring groove The maximum permitted If the width variation is greater
Width "F" for uniform width width variation is 0.015 inch than the permitted serviceable
variation. (0.38 mm). limits, replace the blade seal.

(4) Measure the blade seal The permitted limits are given If any measurement is not within
features "A", "B", "C1", in the table in Figure 5-19. the permitted serviceable limits,
"C2", "D", and "E". replace the blade seal.

CHECK 61-10-90 Page 5-45

Rev. 2 Nov/19
PROPELLER MAINTENANCE MANUAL
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A-2424

A-2424A

A-2424-1
TPI-152-027-1,-2,-3

Balance Weight
Figure 5-20

CHECK 61-10-90 Page 5-46

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

S. BALANCE WEIGHT
(Item 710)
Refer to Figure 5-20.

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

(2) For an aluminum

(gray color) balance
weight:

(a) Visually examine Corrosion is not permitted. If Remove corrosion using glass
the balance weight there is corrosion, remove it in bead cleaning. Refer to the
for corrosion. accordance with the corrective Cleaning chapter of Hartzell
action repair limits. Standard Practices Manual 202A
(61-01-02).

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

(3) For a steel (silver color)

weight:

(a) Visually examine Corrosion is not permitted. If Remove corrosion using glass
the balance weight there is corrosion, remove it in bead cleaning. Refer to the
for corrosion. accordance with the corrective Cleaning chapter of Hartzell
action repair limits. Standard Practices Manual 202A
(61-01-02).

(b) Visually examine Except for a few scratches and If the coverage is less than
the balance weight corners with cadmium plating the permitted serviceable limits,
for cadmium plating missing, complete coverage is replate the balance weight in
coverage. required. accordance with the Cadmium
Replating chapter of Hartzell
Standard Practices Manual 202A
(61-01-02).

CHECK 61-10-90 Page 5-47

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

Component Inspection Criteria

Table 5-1
Inspect Serviceable Limits Corrective Action

S. BALANCE WEIGHT, CONTINUED

(Item 810)
Refer to Figure 5-20.

(4) For a brass (gold color) Brass must be bare of any Remove applied coating using
balance weight, visually applied coating. Bare brass glass bead cleaning. Refer to
examine the balance will have a muted yellow color the Cleaning chapter of Hartzell
weight for a bare surface similar to gold. Oxidized or Standard Practices Manual 202A
(does not include oxidized tarnished brass is permitted and (61-01-02).
or tarnished surface). will appear brown to black or
blue-green.

CHECK 61-10-90 Page 5-48

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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REPAIR - CONTENTS
1. General Repair Requirements.................................................................................. 6-3
A. Shot Peening....................................................................................................... 6-3
B. Aluminum and Steel Parts................................................................................... 6-4
2. Repair/Modification Procedures............................................................................... 6-4
A. Propeller Components........................................................................................ 6-4
B. Hubs.................................................................................................................... 6-4
C. Blades................................................................................................................. 6-4
D. Spinner Assemblies............................................................................................. 6-4
E. Ice Protection Systems....................................................................................... 6-4
3. Compression Spring: Zinc Chromate Primer Repair................................................ 6-5
A. Cleaning.............................................................................................................. 6-5
B. Painting............................................................................................................... 6-5
4. Pitch Change Block Button Modification................................................................... 6-6
A. Purpose............................................................................................................... 6-6
B. Procedure............................................................................................................ 6-6

LIST OF FIGURES
Pitch Change Block Button Modification..................... Figure 6-1.................................. 6-6

REPAIR 61-10-90 Page 6-1

Rev. 2 Nov/19
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(This page is intentionally blank.)

REPAIR 61-10-90 Page 6-2

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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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 HARTZELL PROPELLER INC. 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 (Rev. 1)

A. Shot Peening

CAUTION: THE PEENING MARKS ON CERTAIN PROPELLER PARTS ARE

NOT TOOL MARKS AND SHOULD NOT BE REMOVED.
(1) Some 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).

WARNING: FAILURE TO CORRECTLY SHOT PEEN APPLICABLE

PROPELLER PARTS MAY CREATE AN UNSAFE CONDITION
THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY,
AND/OR SUBSTANTIAL PROPERTY DAMAGE. A QUALITY
SHOT PEENING PROCESS IS CRITICAL FOR FLIGHT
SAFETY. SHOT PEENING OF PROPELLER PARTS
REQUIRES SPECIAL TECHNIQUES, TRAINING, MATERIALS,
AND EQUIPMENT.
(a) Only repair stations that are properly certified by Hartzell Propeller Inc.
should shot peen Hartzell propeller parts.
1 For certification requirements, refer to the Approved Facilities chapter
of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).
2 For a list of repair stations that are certified by Hartzell Propeller Inc.
to perform shot peening on Hartzell propeller parts:
a Go to the Sample Program Approvals page on the Hartzell
Propeller Inc. website at www.hartzellprop.com
b Contact Hartzell Propeller Inc. Product Support
(1) Refer to the section, "Contact Information" in the
Introduction chapter of this manual.

REPAIR 61-10-90 Page 6-3

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
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B. Aluminum and Steel Parts

(1) Remove scratches, nicks, burrs, and other minor damage using a fine emery
cloth or abrasive pad, such as CM47.
(a) 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.
(2) After any repair, inspect the part in accordance with the applicable inspection
criteria to be sure it is within the permitted limits.

2. Repair/Modification Procedures
A. Propeller Components (Except for those listed separately in this section)
(1) For repair and modification procedures of propeller components (except for
those listed separately in this section), refer to the applicable section in this
chapter.
B. Hubs
(1) Aluminum Hubs: Refer to the Aluminum Hub Overhaul chapter of Hartzell
Propeller Inc. Standard Practices Manual 202A (61-01-02).
C. Blades
(1) Aluminum Blades: Refer to Hartzell Propeller Inc. Aluminum Blade Overhaul
Manual 133C (61-13-33).
(2) Composite Blades: Refer to Hartzell Propeller Inc. Composite Propeller Blade
Maintenance Manual 135F (61-13-35).
D. Spinner Assemblies
(1) Metal Spinners: Refer to Hartzell Propeller Inc. Metal Spinner Maintenance
Manual 127 (61-16-27).
(2) Composite Spinners: Refer to the following Hartzell Propeller Inc.
maintenance manuals:
(a) Composite Spinner Maintenance Manual 148 (61-16-48)
(b) Composite Spinner Field Maintenance and Minor Repair Manual 173
(61-10-73).
E. Ice Protection Systems
(1) For ice protection systems supplied by Hartzell, refer to Hartzell Propeller Inc.
Ice Protection System Manual 180 (30-61-80).
(2) For ice protection systems not supplied by Hartzell, refer to the applicable TC
or STC holder’s Instructions for Continued Airworthiness (ICA).

REPAIR 61-10-90 Page 6-4

Rev. 2 Nov/19
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3. Compression Spring: Zinc Chromate Primer Repair

A. Cleaning

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) For procedures for cleaning the compression spring (110, 115), refer to
Cleaning of Steel Parts in the Cleaning chapter of Hartzell Propeller Inc.
Standard Practices Manual 202A (61-01-02).
(2) Inspect the compression spring (110, 115) for scratches, corrosion, and zinc
plate coverage in accordance with the Check chapter of this manual.
(3) Using 120 grit or finer sandpaper, remove any loose material and feather the
existing coating.
(4) Using solvent CM106, clean the entire compression spring (110, 115).
(5) Permit the solvent CM106 to air dry.
B. Painting
(1) For general information about painting procedures, refer to the Paint
and Finish chapter of Hartzell Propeller Inc. Standard Practices
Manual 202A (61-01-02).
(2) Apply a layer of zinc chromate primer CM67, or equivalent, to the entire surface
of the compression spring (110, 115).
(3) Permit the primer to dry for a minimum of 24 hours before handling.
(4) Examine the compression spring (110, 115) for complete primer coverage.

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4. Pitch Change Block Button Modification

A. Purpose
(1) To improve the response rate of the propeller when going from high pitch to
low pitch, modify the pitch change block buttons (310) in accordance with the
procedure below.

B. Procedure
(1) Using an abrasive pad CM47, sandpaper, or equivalent, polish the top surface
of the pitch change block button (310) to reduce the height "A" of the button.
Refer to Figure 6-1.
(a) The minimum permitted height "A" of the pitch change block button (310)
is 0.090 inch (2.29 mm).

Pitch Change Block Button (310)

(top)

Height "A"
Minimum Height:
0.090 inch (2.29 mm)
TPI-MB-0275

Pitch Change Block Button Modification

Figure 6-1

REPAIR 61-10-90 Page 6-6

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ASSEMBLY - CONTENTS
1. General..................................................................................................................... 7-3
A. Important Information......................................................................................... 7-3
B. Ice Protection Systems...................................................................................... 7-4
C. O-rings............................................................................................................... 7-4
D. Blade Bore Plug/Bearing Installation................................................................. 7-4
E. Blade Angle Information..................................................................................... 7-4
2. Hub Assembly Procedures....................................................................................... 7-6
A. 3C1-L675A1, 3C1-R430A1, and 4C1-F650A1 Propellers Only......................... 7-6
B. 3C1-R619A1 and 3C1-R919A1 Propellers Only................................................ 7-8
C. 3C4-R430A1 Propellers Only........................................................................... 7-11
3. Blade Assembly and Installation............................................................................. 7-13
A. Blade Assembly............................................................................................... 7-13
B. Blade Installation.............................................................................................. 7-18
4. Hydraulic Pitch Change Unit Assembly.................................................................. 7-23
A. ( )C1-( )( )( ) Propeller Models.......................................................................... 7-23
B. 3C4-R( )( )( ) Propeller Models........................................................................ 7-30
5. Setting Low Blade Angle......................................................................................... 7-37
A. Low Pitch Stop Screw Installation.................................................................... 7-37
B. Adjusting the Low Pitch Stop Angle................................................................. 7-38
6. Leak Check............................................................................................................. 7-39
A. Lubrication Fitting/Plug Installation.................................................................. 7-39
B. Leak Check Procedure.................................................................................... 7-39
7. Post-Assembly Procedures.................................................................................... 7-40
A. Counterweight Installation (3C4-series Propellers Only)................................. 7-40
B. Propeller Lubrication........................................................................................ 7-40
C. Static Balance.................................................................................................. 7-40
D. Label Placement.............................................................................................. 7-40
8. Propeller Disassembled for Shipping..................................................................... 7-41
A. General............................................................................................................ 7-41
B. Preparing the Propeller for Shipping................................................................ 7-41

ASSEMBLY 61-10-90 Page 7-1

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ASSEMBLY - CONTENTS, continued

9. Reassembly of a Propeller Disassembled for Shipping.......................................... 7-43
A. Unpacking the Propeller and Blades................................................................ 7-43
B. Preparing Propeller for Reassembly................................................................ 7-43
C. Propeller Reassembly...................................................................................... 7-43

LIST OF FIGURES
Hub Assembly - 3C1-L675A1, 3C1-R430A1,
and 4C1-F650A1 Propellers........................................................ Figure 7-1................7-5
Hub Assembly - 3C1-R619A1 and 3C1-919A1 Propellers................ Figure 7-2................7-8
Hub Assembly - 3C4-R430A1 Propellers.......................................... Figure 7-3..............7-10
Blade Assembly................................................................................. Figure 7-4..............7-12
Blade Seal and Blade Shim Installation............................................ Figure 7-5..............7-14
Bearing Ball Installation..................................................................... Figure 7-6..............7-16
Hub-side Bearing Race Installation .................................................. Figure 7-7..............7-17
Installing a Blade in the Hub Socket.................................................. Figure 7-8..............7-18
Fork Installation................................................................................. Figure 7-9..............7-20
Cylinder-side Hub Half Installation ................................................... Figure 7-10............7-20
Sealing the Hub Halves..................................................................... Figure 7-11.............7-25
Piston and Compression Spring Installation...................................... Figure 7-12............7-26
Cotter Pin Installation ....................................................................... Figure 7-13............7-28
Installing the Cylinder with a Cylinder Torque Wrench
Adapter TE153............................................................................. Figure 7-14............7-29
Sealing the Hub Halves..................................................................... Figure 7-15............7-31
Split Keeper Installation..................................................................... Figure 7-16............7-33
Stop Collar Installation...................................................................... Figure 7-17............7-33
Piston Installation.............................................................................. Figure 7-18............7-34
Cotter Pin Installation........................................................................ Figure 7-19............7-35
Cylinder Installation........................................................................... Figure 7-20............7-36
Low Pitch Stop Screw Installation .................................................... Figure 7-21............7-37
Hub Leak Check ............................................................................... Figure 7-22............7-39

ASSEMBLY 61-10-90 Page 7-2

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LIST OF TABLES
Blade Shim Thickness....................................................................... Table 7-1................7-15
Stop Sleeve Heights.......................................................................... Table 7-2................7-26
Stop Collar Heights........................................................................... Table 7-3................7-32

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(This page is intentionally blank.)

ASSEMBLY 61-10-90 Page 7-2.2

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1. General (Rev. 2)

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
EVEN THOUGH IT MAY STILL SHOW AN AVIATION TC OR PC
NUMBER STAMP. 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: 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.
A. Important Information
(1) Read all assembly instructions before beginning the assembly procedures.
(2) Protect all unassembled components from damage.
(3) Use applicable torque values. Refer to Table 8-1, "Torque Values", in the Fits
and Clearances chapter of this manual.
(4) Unless specified differently, safety wire in accordance with NASM33540 using
0.032 inch (0.81 mm) safety wire.
(5) For information about additional weight slugs that may be required to be
attached to the counterweight arms of certain clamp models, refer to the
Hartzell Propeller Inc. Application Guide Manual 159 (61-02-59).

ASSEMBLY 61-10-90 Page 7-3

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CAUTION: BEFORE ASSEMBLING THE PROPELLER, DETERMINE IF AN ICE

PROTECTION SYSTEM IS REQUIRED.
B. Ice Protection Systems
(1) If installing an ice protection system supplied by Hartzell, refer to Hartzell
Propeller Inc. Ice Protection System Manual 180 (30-61-80).
(2) If installing an ice protection system not supplied by Hartzell, refer to the
applicable TC or STC holder’s Instructions for Continued Airworthiness (ICA).
C. O-rings
(1) Unless specified differently, lubricate all O-rings with lubricant CM12 before
installing them in the propeller assembly.
(2) 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.
D. Blade Bore Plug/Bearing Installation
(1) For aluminum blades, refer to Hartzell Propeller Inc. Aluminum Blade Overhaul
Manual 133C (61-13-33).
(2) For composite blades, refer to Hartzell Propeller Inc. Composite Propeller
Blade Maintenance Manual 135F (61-13-35).
E. Blade Angle Information
(1) For specific blade angle information, refer to the Hartzell Propeller Inc.
Application Guide Manual 159 (61-02-59).

ASSEMBLY 61-10-90 Page 7-4

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340
280
240
220

220

250

260
270

TPI-490-022

Hub Assembly - 3C1-L675A1, 3C1-R430A1, and 4C1-F650A1 Propellers

Figure 7-1

ASSEMBLY 61-10-90 Page 7-5

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2. Hub Assembly Procedures

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: ACTUATION OF PROPELLERS MUST BE ACCOMPLISHED USING

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

CAUTION 3: DO NOT USE A PRESSURE THAT IS GREATER THAN

175 PSI (12.06 BARS) WHEN ACTUATING PROPELLERS THAT
ARE INCLUDED IN THIS MANUAL.

CAUTION 4: USE ENOUGH PRESSURE TO MAKE SURE THAT THE PROPELLER

ACTUATES AGAINST EACH POSITIVE STOP.
A. 3C1-L675A1, 3C1-R430A1, and 4C1-F650A1 Propellers Only
(1) Hub Assembly - Refer to Figure 7-1

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) Install the propeller flange mounting hardware in accordance with the
Aluminum Hub Overhaul chapter of Hartzell Propeller Inc. Standard
Practices Manual 202A (61-01-02) before following the propeller assembly
procedures in this manual.
(b) Install the cylinder-side hub bushing (260). Refer to Figure 7-1.
1 Apply a light layer of lubricant CM12 to the cylinder-side hub
bushing (260).
2 Install the cylinder-side hub bushing (260) into the pitch change rod
bore of the cylinder-side half of the hub (220).
3 Install the internal retaining ring (270) on the cylinder-side hub
bushing (260).

ASSEMBLY 61-10-90 Page 7-6

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(c) Install the engine-side hub bushing (280). Refer to Figure 7-1.
1 Apply a light layer of lubricant CM12 to the bushing-to-hub
O-ring (240).
2 Install the O-ring (240) in the groove on the OD of the engine-side
hub bushing (280).
3 Install the bushing (280) through the flange-side of the hub (220) into
the pitch change rod bore of the engine-side of the hub (220).
4 Install the external retaining ring (250) on the engine-side hub
bushing (280).
(d) Apply a light layer of lubricant CM12 to the O-ring (340).
(e) Install the O-ring (340) in the groove on the ID of the engine-side hub
bushing (280).
(f) Apply a layer of lubricant CM12 to the flange mounting O-ring (540).
(g) Install the flange mounting O-ring (540) on the engine-side half of the
hub (220).
(h) Install the engine-side half of the hub (220) on the propeller assembly
stand.
(i) Apply a layer of lubricant CM12 to the bearing seats of the blade retention
sockets and the blade O-ring grooves.

ASSEMBLY 61-10-90 Page 7-7

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B. 3C1-R619A1 and 3C1-R919A1 Propellers Only

(1) Hub Assembly - Refer to Figure 7-2

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) Install the propeller flange mounting hardware in accordance with the
Aluminum Hub Overhaul chapter of Hartzell Propeller Inc. Standard
Practices Manual 202A (61-01-02) before following the propeller assembly
procedures in this manual.

360
370 350
330
280
240
220

220

250

260
TPI-490-021

270

Hub Assembly - 3C1-R619A1 and 3C1-R919A1 Propellers

Figure 7-2

ASSEMBLY 61-10-90 Page 7-8

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(b) Install the cylinder-side hub bushing (260). Refer to Figure 7-2.
1 Apply a light layer of lubricant CM12 to the cylinder-side hub
bushing (260).
2 Install the cylinder-side hub bushing (260) into the pitch change rod
bore of the cylinder-side half of the hub (220).
3 Install the internal retaining ring (270) on the cylinder-side hub
bushing (260).
(c) Install the engine-side hub bushing (280). Refer to Figure 7-2.
1 Apply a light layer of lubricant CM12 to the bushing-to-hub
O-ring (240).
2 Install the O-ring (240) in the groove on the OD of the engine-side
hub bushing (280).
3 Install the bushing (280) through the flange-side of the hub (220) into
the pitch change rod bore of the engine-side half of the hub (220).
4 Install the external retaining ring (250) on the engine-side hub
bushing (280).
(d) Install the engine-side hub plug (370). Refer to Figure 7-2.
1 Install the internal spiral retaining ring (330) in the groove provided
for it in the bore of the engine-side half of the hub (220).
2 Apply a light layer of lubricant CM12 to the hub plug OD O-ring (360).
3 Install the O-ring (360) in the groove on the OD of the hub plug (370).
4 Apply a light layer of lubricant CM12 to the O-ring (350).
5 Install the O-ring (350) in the groove on the ID of the hub plug (370).
(e) Apply a layer of lubricant CM12 to the flange mounting O-ring (540).
(f) Install the flange mounting O-ring (540) on the engine-side half of the
hub (220).
(g) Install the engine-side half of the hub (220) on the propeller assembly
table TE129.
(h) Apply a layer of lubricant CM12 to the bearing seats of the blade retention
sockets and the blade O-ring grooves.

ASSEMBLY 61-10-90 Page 7-9

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O-ring (540)

O-ring (240)

Hub Bushing (285)

Hub (220)
O-ring (285)

External Retaining
Ring (270)

Hub (220)

O-ring (165)
TPI-MB-0211

Hub Assembly - 3C4-R430A1 Propellers

Figure 7-3

ASSEMBLY 61-10-90 Page 7-10

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C. 3C4-R430A1 Propellers Only

(1) Hub Assembly - 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.
(a) Install the propeller flange mounting hardware in accordance with the
Aluminum Hub Overhaul chapter of Hartzell Propeller Inc. Standard
Practices Manual 202A (61-01-02) before following the propeller assembly
procedures in this manual.
(b) Cylinder-side of the hub (220) - Refer to Figure 7-3
1 Apply a light layer of lubricant CM12 to the hub-to-pitch change rod
O-ring (165).
2 Install the hub-to-pitch change rod O-ring (165) into the pitch change
rod bore of the cylinder-side half of the hub (220).
(c) Engine-side of the hub (220) - Refer to Figure 7-3
1 Apply a light layer of lubricant CM12 to the hub bushing OD
O-ring (240).
2 Install the O-ring (240) in the groove on the OD of the engine-side
hub bushing (280).
3 Install the hub bushing (280) through the flange side of the
hub (220) into the pitch change rod bore of the engine-side half
of the hub (220).
4 Install the external retaining ring (270) on the engine-side hub
bushing (280).
(d) Apply a layer of lubricant CM12 to the flange mounting O-ring (540).
(e) Install the flange mounting O-ring (540) on the engine-side half of the
hub (220).
(f) Install the engine-side half of the hub (220) on the propeller assembly
table TE129.
(g) Apply a layer of lubricant CM12 to the bearing seats of the blade retention
sockets and the blade O-ring grooves.

ASSEMBLY 61-10-90 Page 7-11

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Blade

720
730
600
610
670
620
680
660
690
640
700
650
710
630
TPI-MB-0218

Blade Assembly
Figure 7-4

ASSEMBLY 61-10-90 Page 7-12

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3. Blade Assembly and Installation

A. Blade Assembly
(1) The following procedure assumes that the blade has been inspected
and repaired and that the blade wear strip, blade side bearing race,
and bearing retaining ring are installed on each blade in accordance
with Hartzell Propeller Inc. Composite Propeller Blade Maintenance
Manual 135F (61-13-35).
(2) Install the pitch change knob bushing (730) in accordance with the
Special Adhesive and Bonding Procedures chapter of Hartzell Propeller Inc.
Standard Practices Manual 202A (61-01-02).
(3) Install the blade plug (610) in the bore of each blade. Refer to Figure 7-4.
(a) Apply a light layer of lubricant CM12 to the blade plug O-ring (600).
(b) Install the blade plug O-ring (600) on the OD of the blade plug (610).
(c) Install the blade plug (610) in the bore of the blade.
(d) Install the internal spiral retaining ring (620) in the groove provided for it
in the bore of the blade.

ASSEMBLY 61-10-90 Page 7-13

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Bearing Retaining
Ring (670) Blade Shim (680)

Blade Seal (700) Blade Butt

O-Ring (690)

O-Ring (710) Blade Shank

Wear Strip

TPI-496-17

Blade Seal and Blade Shim Installation

Figure 7-5

ASSEMBLY 61-10-90 Page 7-14

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490

(4) Install the blade O-ring (720), the blade seal (700), and the O-rings (690, 710).
Refer to Figure 7-4 and Figure 7-5.
(a) Using lubricant CM12, lubricate the blade O-ring (720).
(b) Install the blade O-ring (720) on the outboard blade wear strip on the
blade. Refer to Figure 7-4.
(c) Using lubricant CM12, lightly lubricate the O-rings (690 and 710).
(d) Install the O-ring (690) in the groove provided for it on the ID of the
blade seal (700). Refer to Figure 7-5.
(e) Install the O-ring (710) in the groove provided for it on the OD of the
blade seal (700). Refer to Figure 7-5.
1 Make sure that the O-rings (690, 710) are seated in the grooves of
the blade seal (700).
(f) Install the blade seal (700) with the blade shim (680) and the
O-rings (690, 710) on the blade. Refer to Figure 7-5.
1 The thickness of the blade shim (680) that was measured at
disassembly will help determine the thickness of the shim to be
installed.
a Use a blade shim (680) that is slightly thicker than the shim that
was removed to offset wear on the components.
Refer to Table 7-1.
2 Using lubricant CM12, lightly lubricate the O-rings (690, 710)
before installing the blade seal (700) with the blade shim (680)
and the O-rings (690, 710) on the blade.
3 Using lubricant CM12, lubricate the inboard blade shank wear strip.
4 With the blade shim (680) pointing toward the bearing retaining
ring (670), install the blade seal (700) with the blade shim (680)
and the O-rings (690, 710) on the blade as shown in Figure 7-5.

Thickness Thickness
Part Number
(inch) (mm)
105758-050 0.050 1.27
105758-055 0.055 1.39
105758-060 0.060 1.52
105758-063 0.063 1.60
105758-065 0.065 1.65
105758-067 0.067 1.70
105758-070 0.070 1.78
105758-073 0.073 1.85
105758-075 0.075 1.90
105758-077 0.077 1.95
Blade Shim Thickness
Table 7-1

ASSEMBLY 61-10-90 Page 7-15

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5 Firmly seat the blade seal (700) with the blade shim (680) and the
O-rings (690, 710) against the bearing retaining ring (670).

CAUTION: MAKE SURE THAT THE O-RINGS (690, 710)

ARE SEATED IN THE GROOVES OF THE BLADE
SEAL (700) WHEN THE BLADE SEAL (700) IS
INSTALLED ON THE BLADE.
6 Make sure that the O-rings (690, 710) are seated in the grooves of
the blade seal (700).
(5) Install the bearing balls (640) and the bearing races (630 and 660).
Refer to Figure 7-6.
(a) Using lubricant CM12, lubricate the blade-side bearing race (630).
(b) Put the ball spacer (650) on the blade-side bearing race (630).

CAUTION: ALL THE BEARING BALLS (640) IN A SINGLE BEARING

MUST BE OF THE SAME SIZE AND GAUGE. BEARING
BALLS SUPPLIED BY HARTZELL PROPELLER INC. ARE THE
SAME GAUGE.
(c) Put the bearing balls (640) in the openings of the ball spacer (650) on the
blade-side bearing race (630).

Bearing Balls (640)

Blade O-Ring (720)

Ball Spacer (650)

Blade-side Bearing Race (630)

Bearing Retaining Ring (670)

APS2002

Bearing Ball Installation

Figure 7-6

ASSEMBLY 61-10-90 Page 7-16

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CAUTION: THE BEARING RACE HALVES (630 AND 660) MUST HAVE
MATCHING SERIAL NUMBERS.
(d) Put the hub-side bearing race (660) on the bearing balls (640). Refer to
Figure 7-7.
1 Install the hub-side bearing race (660) with the parting line
perpendicular to the hub parting line when installed in the hub (220).
Refer to Figure 7-8.
(e) Repeat steps (4)(a) through (5)(d)1 of this procedure for the remaining
blades.

Blade O-ring (720)

Parting Line
Hub-side Bearing Race (660)

Bearing Balls (640)

TPI-490-027

Hub-side Bearing Race Installation

Figure 7-7

ASSEMBLY 61-10-90 Page 7-17

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B. Blade Installation

CAUTION: TO AVOID BLADE OR HUB DAMAGE, DO NOT USE FORCE TO

INSTALL THE BLADE INTO THE SOCKET.
(1) Apply a thin film of lubricant CM12 to the blade retention radii and the
O-ring grooves of the hub (220).

CAUTION: EACH BLADE MUST BE SHIMMED IN THE HUB SOCKET THAT

IT WILL OCCUPY WHEN ASSEMBLED. DO NOT SHIM ALL THE
BLADES IN THE SAME SOCKET.
(2) Install each previously constructed blade assembly using the following steps:
(a) Install a blade assembly into the socket of the engine-side half of the
hub (220).
(b) Using a feeler gage, measure the gap between the hub and the hub-side
bearing race while pushing the blade bearing down into the hub socket.
A gap of 0.002-0.004 inch (0.05-0.10 mm) is recommended.
1 If the gap is less than 0.002-0.004 inch (0.05-0.10 mm), remove
the blade and replace the blade shim (680) with a thinner blade
shim. Refer to Table 7-1.
2 If the gap is greater than 0.002-0.004 inch (0.05-0.10 mm), remove
the blade and replace the blade shim (680) with a thicker blade shim.
Refer to Table 7-1.

90 degrees Hub parting line

Parting line of the

hub-side bearing race (660)

Trailing edge
of the blade
APS0820, W10294

Installing a Blade in the Hub Socket

Figure 7-8

ASSEMBLY 61-10-90 Page 7-18

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(3) Make sure that the parting line of the hub-side bearing race (660) is
perpendicular to the hub parting line when the blade is installed in the
hub (220). Refer to Figure 7-8.
(4) When all the blades have been successfully installed in the sockets of the
hub (220), temporarily install the cylinder-side half of the hub (220).
(a) Install one bolt (210) in the hub clamping bolt hole next to the leading
edge of each blade.
(b) Install a washer (200) and a nut (190) on each hub clamping bolt (210).
(c) Tighten the nuts (190) until snug. Do not torque the nuts (190) at this time.
(5) Examine each blade for free rotation.
(a) If the blade does not rotate freely in the hub socket, make sure that the
blade O-ring (720) is seated correctly in the hub socket.
(6) Examine the blade play of each blade.
(a) If any blade is loose in the hub socket, remove the blade and replace
the blade shim (680) with a thicker blade shim (680). Refer to Table 7-1.
(7) When the blade play and rotation are satisfactory, remove the nuts (190), the
washers (200), and the hub clamping bolts (210) from the hub (220).
(8) Remove the cylinder-side half of the hub (220).
(9) 3C1-Propellers: Remove blade number one.
4C1-Propellers: Remove blade number one and blade number two.
(10) Install the pitch change fork bumpers (300) in accordance with the
applicable step(s) below:
(a) 3C1-Propellers:
1 Install the pitch change fork bumpers (300) on the pitch
change fork (290).
(b) 4C1-Propellers:
1 Apply retaining compound CM74 to the threads of each bumper
extension (295).
2 Install the four bumper extensions (295) onto the pitch change
fork (290) and torque each bumper extension in accordance with
Table 8-1, "Torque Values", in the Fits and Clearances chapter of
this manual.
3 Install a fork bumper (300) on each bumper extension (295).
(11) Install one pitch change block button (310) into each pitch change
block (320).
(12) Apply anti-seize compound CM118 to the outside of each pitch change knob
bushing (730).
(13) Apply anti-seize compound CM118 to the threads of the fork (290) and to
each pitch change block groove of the pitch change fork (290).

ASSEMBLY 61-10-90 Page 7-19

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Fork (290)

Pitch Change
Block (320)

TPI-490-014
NOTE: This Figure shows a three-blade propeller.
Fork installation for a four-blade propellers is similar.

Fork Installation
Figure 7-9

Bolt (210)

Washer (200)

Nut (190)
TI-490-020

Cylinder-side Hub Half Installation

Figure 7-10

ASSEMBLY 61-10-90 Page 7-20

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(14) With the round extension of the pitch change block (320) pointing away from
the blade, install a pitch change block (320) on each pitch change knob.
(a) When installing a new pitch change block (320), make sure that the
pitch change block (320) is installed with the thin wall pointing in the
correct direction.
1 At initial assembly, install the pitch change blocks (320) in the
fork (290) with the thin wall pointing toward the engine-side half
of the hub (220).
2 For a pitch change block (320) that has been marked during
disassembly to indicate the direction that the thin wall is pointing,
install the pitch change block (320) in accordance with the marking.
CAUTION: MAKE SURE THAT THE TAPER IN THE FORK (290) MATCHES
THE TAPER IN THE PITCH CHANGE ROD (150). IF THE PITCH
CHANGE ROD (150) IS INCORRECTLY ATTACHED TO THE
FORK (290), THE SEATING AREA OF THE PITCH CHANGE
ROD (150) WILL BE DAMAGED.
(15) Install the fork (290) on the pitch change blocks (320) of the two blades that
are installed in the hub. Refer to Figure 7-9.
(16) Install the blade(s) that were previously removed in accordance with the
step below:
(a) Put the pitch change block (320) that is installed on the blade assembly
into the fork (290), then install the blade into the socket of the engine-
side half of the hub (220).
(17) Install the cylinder-side half of the hub (220).
(18) Install one bolt (210) in the hub clamping bolt hole centered between each
blade as shown in Figure 7-10.

NOTE: On 4C1-F650A1 propellers, install the bolt (210) from the

engine-side of the hub as shown in the Illustrated Parts List chapter
of this manual.
(a) Install a washer (200) and a nut (190) on each bolt (210).
(b) Torque the nuts (190) in accordance with Table 8-1, "Torque Values",
in the Fits and Clearances chapter of this manual.

CAUTION: INCORRECT SHIMMING CAN CAUSE THE BLADES TO BE TOO

LOOSE OR TOO TIGHT IN THE HUB (220).
(19) Examine each blade for free rotation, blade end play, and fore-and-aft movement.
(a) Free rotation
1 If the blade does not rotate freely in the hub socket, make sure that
the blade O-ring (720) is seated correctly in the hub socket.
(b) Blade End play and Fore-and-Aft Movement
1 Refer to the section, "Blade Tolerances" in the Fits and Clearances
chapter of this manual for blade movement check procedures and
limits.

ASSEMBLY 61-10-90 Page 7-21

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(20) If any blade does not rotate freely in the hub socket, or if blade movement
for any blade is greater than the limits specified in the "Blade Tolerances"
section in the Fits and Clearances chapter of this manual:
(a) Remove the cylinder-side half of the hub (220).
(b) Remove the blade.
(c) Remove the blade seal (700) and O-rings (690, 710).
(d) Remove the blade shim (680).
(e) Replace the blade shim (680) with the next thinner or next thicker blade
shim (680), as necessary. Refer to Table 7-1.
(f) Install the blade shim (680) in the recess of the blade seal (700).
(g) Using lubricant CM12, lightly lubricate O-rings (690, 710) before
installation of the blade shim (680) and blade seal (700) with
O-rings (690, 710) on the blade.
(h) With the blade shim (680) pointing toward the bearing retaining ring
(670),
install the blade shim (680) and blade seal (700) with O-rings (690, 710)
on the blade.
(i) Firmly seat the blade seal (700) against the blade shim (680).

CAUTION: MAKE SURE THAT THE O-RINGS (690, 710) ARE SEATED
IN THE GROOVES OF THE BLADE SEAL (700) WHEN THE
BLADE SEAL (700) IS INSTALLED ON THE BLADE.
(j) Make sure that the O-rings (690, 710) are seated in the grooves of the
blade seal (700).
(k) Install the cylinder-side half of the hub (220).
(l) Install the hub clamping bolts (210) in the hub clamping bolt holes that
are next to the leading edge of each blade.

NOTE: On 4C1-F650A1 propellers, install the bolt (210) from the

engine-side of the hub as shown in the Illustrated Parts List
chapter of this manual.
1 Install a washer (200) and a nut (190) on each hub clamping
bolt (210).
2 Tighten the nuts (190) until snug. Do not torque the nuts at this time.
(m) Examine each blade for free rotation.
(21) Repeat steps (19) through (20)(m) of this procedure until all blades rotate
freely in the hub (220) and the maximum permitted blade end play and fore-
and-aft movement is within the limits specified in the "Blade Tolerances"
section in the Fits and Clearances chapter of this manual.

ASSEMBLY 61-10-90 Page 7-22

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4. Hydraulic Pitch Change Unit Assembly

A. ( )C1-( )( )( ) Propeller Models
(1) Insert the pitch change rod (150) through the cylinder-side half of the hub (220)
and into the fork (290).
(2) Torque the pitch change rod (150) in accordance with Table 8-1, "Torque Values",
in the Fits and Clearances chapter of this manual.
(3) Blade Angle Check:
(a) Install the cylinder (40) hand tight on the cylinder-side half of the hub (220).
(b) Install the low pitch stop screw (30) into the cylinder (40).
1 The low pitch stop screw (30) does not have to be set to the
applicable low pitch angle.
2 The cylinder (40) and low pitch stop screw (30) only provide a contact
point for the pitch change rod (150) while checking for 0.2 degrees
tolerance between blades.
(c) Rotate the blades until the pitch change rod (150) touches the low pitch
stop screw (30) and measure the blade angles at the 30 inch radius of all
of the blades.
(d) If there is more than 0.2 degree blade angle difference between blades,
turn one or more of the pitch change blocks (320).
1 To turn the pitch change blocks (320), remove the cylinder (40) and
the cylinder-side half of the hub (220).
2 Make the necessary adjustments to the pitch change blocks (320).
a Pitch change blocks (320) should be installed in the fork (290)
with the thin wall pointing toward the engine-side half of the
hub (220) during initial assembly.
b Rotating the pitch change block (320) 180 degrees will decrease
the pitch of the corresponding blade 0.3 to 0.4 degree on a
tractor propeller.
c Rotating the pitch change block (320) 180 degrees will increase
the pitch of the corresponding blade 0.3 to 0.4 degree on a pusher
propeller.
3 Reassemble the propeller and follow steps (3) through (3)(d)2 of this
procedure to measure the blade angle tolerance between blades.

ASSEMBLY 61-10-90 Page 7-23

Rev. 2 Nov/19
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490

(4) Cylinder-side Hub Half Installation:

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: THE MATING SURFACES OF THE HUB (220) MUST BE

CLEAN AND FREE OF ALL UNWANTED MATERIAL TO
PERMIT SEALING OF THE HUB PARTING LINE.
(a) Remove the low pitch stop screw (30) from the cylinder (40).
(b) Remove the cylinder (40).
(c) Remove the pitch change rod (150).
(d) Using solvent MEK CM106 or MPK CM219, clean the cylinder-side and
engine-side mating surfaces of the hub (220) to make sure that all oil,
grease, and unwanted material have been removed.
(e) Permit the solvent MEK CM106 or MPK CM219 to dry.
(f) Install the hub guide bushing (230) in the hole provided for it in the
engine-side half of the hub (220).

ASSEMBLY 61-10-90 Page 7-24

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(g) Apply a bead of sealant CM92 to the mating surfaces on the cylinder-side
and engine-side of the hub (220) in accordance with Figure 7-11.
1 The quantity of sealant applied to the mating surfaces must be
sufficient to permit a small amount to be squeezed out along the
entire parting surface when the hub bolts are correctly torqued.
2 Do not permit the sealant CM92 to enter any of the hub clamping
bolt holes.
3 Do not permit the sealant CM92 to enter the blade O-ring groove.
(h) Install the cylinder-side half of the hub (220).
(i) Install all bolts (210), washers (200), and nuts (190). Refer to Figure 7-10.

NOTE: On 4C1-F650A1 propellers, install the bolt (210) from the

engine-side of the hub as shown in the Illustrated Parts List
chapter of this manual.
1 When the propeller is assembled without the bulkhead,
additional washers can be used to help with clamping the halves
of the hub (220) during the cure of the sealant CM92.
(j) Torque the nuts (190) in accordance with Table 8-1, "Torque Values", in the
Fits and Clearances chapter of this manual.

Apply Sealant CM92 in accordance

with the dashed line

TPI-MB-0325

Sealing the Hub Halves

Figure 7-11

ASSEMBLY 61-10-90 Page 7-25

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Nut (60) Cotter Pin (50)

Piston (80)
O-ring (70)

Stop Sleeve (120)

Spring Seat (100)
Compression Spring (110)

Pitch Change Rod (150)

O-ring (160) Spring Guide (140)

Hub (220)

TPI-490-017
Piston and Compression Spring Installation
Figure 7-12

Part Number Height (inch) Height (mm)

101335-9 1.270 32.26
101335-8 1.240 31.50
101335-7 1.210 30.73
101335-6 1.180 29.97
101335-5 1.150 29.21
101335-4 1.120 28.45
101335-3 1.090 27.69
101335-2 1.060 26.92
101335-1 1.030 26.16
Stop Sleeve Heights
Table 7-2

ASSEMBLY 61-10-90 Page 7-26

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(5) Piston and Cylinder Installation:

(a) Using lubricant CM12, lightly lubricate the spring guide (140) and put it on
the hub (220) over the pitch change rod bore hole.
(b) Install the stop sleeve split keeper (130) on the pitch change rod (150)
groove.
(c) Install the stop sleeve (120) over the pitch change rod (150) and stop
sleeve split keeper (130). Refer to Figure 7-12.
1 Use the correct stop sleeve (120) to get the necessary high pitch
stop angle. Refer to Table 7-2, "Stop Sleeve Heights" for dimensions
and part numbers.

NOTE: A 1/32 (0.031) inch (0.79 mm) change in height yields

approximately one degree of change in blade angle.
(d) Measure the blade high pitch stop angle.
1 Move the blades into a low pitch position, and then, while pushing
down on the stop sleeve (120), move the blades into high pitch.
(e) Using lubricant CM12, lubricate the O-ring (90).
(f) Install the O-ring (90) over the pitch change rod (150) down onto the
stop sleeve (120).
(g) Using lubricant CM12, lubricate the spring seat (100).
(h) Put the spring seat (100) over the pitch change rod (150) and seat it on
the stop sleeve (120).
(i) With the ID O-ring groove of the piston (80) toward the stop
sleeve (120), put the piston (80) onto the pitch change rod (150) as
shown in Figure 7-12.
(j) Install the nut (60) on the pitch change rod (150).

CAUTION: DO NOT TORQUE THE NUT (60) MORE THAN

55 FT-LBS (74 N•m).
(k) Torque the nut (60) to the minimum torque value in accordance with
Table 8-1, "Torque Values", in the Fits and Clearances chapter of this
manual.
(l) If the hole in the pitch change rod (150) and the slot in the nut (60) do not
align, do the following:
1 Set the torque wrench to 55 Ft-Lbs (74 N•m).
2 Slowly torque the nut (60) until a slot in the nut (60) aligns with the
nearest hole in the pitch change rod (150).

ASSEMBLY 61-10-90 Page 7-27

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CAUTION: DO NOT PERMIT THE COTTER PIN (50) TABS TO BE BENT

OVER THE END OF THE PITCH CHANGE ROD (150). COTTER
PIN (50) TABS BENT OVER THE END OF THE PITCH
CHANGE ROD (150) INTERFERE WITH THE LOW PITCH
STOP SCREW (30).
(m) Safety the nut (60) with the cotter pin (50) as shown in Figure 7-13.

CAUTION: DO NOT REMOVE THE ASSEMBLED PITCH CHANGE

ROD/PISTON BY ATTACHING A WRENCH TO THE
COTTER-PINNED NUT (60); USE THE END OF THE PITCH
CHANGE ROD (150).
(n) Unthread the assembled pitch change rod/piston from the fork (290) and
remove the pitch change rod/piston and the spring seat (100) from the
hub (220).
(o) Apply lubricant CM12 to each end of the compression spring (110),
then put the compression spring onto the spring guide (140) as shown in
Figure 7-12.
(p) 4C1-Propellers Only: Apply lubricant CM12 to each end of the
compression spring (115), then put the compression spring onto the
spring guide (140) inside of the compression spring (110).

NOTE: The compression spring (115) is not shown in Figure 7-12.

(q) Put the spring seat (100) over the compression spring (110).
(r) Move the blades to low pitch position.

Cotter Pin (50)

Nut (60)

Pitch Change Rod (150)

APS2015

Cotter Pin Installation

Figure 7-13

ASSEMBLY 61-10-90 Page 7-28

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490

CAUTION: DO NOT INSTALL THE ASSEMBLED PITCH CHANGE

ROD/PISTON BY ATTACHING A WRENCH TO THE
COTTER-PINNED NUT (60); USE THE END OF THE PITCH
CHANGE ROD (150).
(s) Insert the assembled pitch change rod/piston through the compression
spring(s) (110 and 115 if applicable), and the spring guide (140) into
the cylinder-side half of the hub (220) and the fork (290) as shown in
Figure 7-12.

NOTE: The compression spring(s) will be compressed when the pitch

change rod/piston is turned into the fork (290).
(t) Torque the pitch change rod (150) in accordance with Table 8-1, "Torque
Values", in the Fits and Clearances chapter of this manual.
(u) Using lubricant CM12, lubricate the piston OD O-ring (70).
(v) Install the piston OD O-ring (70) in the O-ring groove of the piston (80) as
shown in Figure 7-12.
(w) Using lubricant CM12, lubricate the O-ring (160).
(x) Install the cylinder O-ring (160) in the groove at the base of the cylinder
attachment threads in the cylinder-side half of the hub (220) as shown
in Figure 7-12.
(y) Using lubricant CM12, lightly lubricate the attachment threads of the
cylinder (40).
(z) Install the cylinder (40) onto the hub (220).
(aa) Using four 1/4-28UNF-3B bolts or screws, attach the cylinder torque
wrench adapter TE153 to the cylinder (40). Refer to Figure 7-14.
(ab) Torque the cylinder (40) in accordance with Table 8-1, "Torque Values", in
the Fits and Clearances chapter of this manual.

Cylinder Torque
Wrench Adapter TE153

Cylinder (40)
TPI-490-018

Installing the Cylinder with a Cylinder Torque Wrench Adapter TE153

Figure 7-14

ASSEMBLY 61-10-90 Page 7-29

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B. 3C4-R( )( )( ) Propeller Models

(1) Insert the pitch change rod (150) through the cylinder-side half of the hub (220)
and into the fork (290).
(2) Torque the pitch change rod (150) in accordance with Table 8-1, "Torque Values",
in the Fits and Clearances chapter of this manual.
(3) Blade Angle Check:
(a) Install the split keeper (130) into the groove on the pitch change rod (150).
(b) Put the stop collar (125) over the pitch change rod (150) and split
keeper (130).
(c) Turn the nut (60) onto the pitch change rod (150) until it is finger-tight.
(d) Rotate the blades toward high pitch until the nut (60) touches the stop
collar (125).
(e) Measure the blade angle at the 30 inch radius on each blade.
(f) If there is more than 0.2 degree blade angle difference between blades,
turn one or more of the pitch change blocks (320).
1 To turn the pitch change blocks (320), remove the nut (60),
stop collar (125), split keeper (130), and the cylinder-side half of
the hub (220).
2 Make the necessary adjustments to the pitch change blocks (320).
a Pitch change blocks (320) should be installed in the fork (290)
with the thin wall pointing toward the engine-side half of the
hub (220) during initial assembly.
b Rotating the pitch change block (320) 180 degrees will decrease
the pitch of the corresponding blade 0.3 to 0.4 degree on a
tractor propeller.
c Rotating the pitch change block (320) 180 degrees will increase
the pitch of the corresponding blade 0.3 to 0.4 degree on a pusher
propeller.
3 Reassemble the propeller and follow steps (3)(a) through (3)(f)2
of this procedure to measure the blade angle tolerance beween the
blades.

ASSEMBLY 61-10-90 Page 7-30

Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

(4) Cylinder-side Hub Half Installation:

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: THE MATING SURFACES OF THE HUB (220) MUST BE

CLEAN AND FREE OF ALL UNWANTED MATERIAL TO
PERMIT SEALING OF THE HUB PARTING LINE.
(a) Remove the pitch change rod (150).
(b) Using solvent MEK CM106 or MPK CM219, clean the cylinder-side and
engine-side mating surfaces of the hub (220) to make sure that all oil,
grease, and unwanted material have been removed.
(c) Permit the solvent MEK CM106 or MPK CM219 to dry.
(d) Install the hub guide bushing (230) in the hole provided for it in the
engine-side half of the hub (220).

Apply Sealant CM92 in accordance

with the dashed line

TPI-MB-0325

Sealing the Hub Halves

Figure 7-15

ASSEMBLY 61-10-90 Page 7-31

Rev. 2 Nov/19
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490

(e) Apply a bead of sealant CM92 to the mating surfaces on the cylinder-side
and engine-side of the hub (220) in accordance with Figure 7-15.
1 The quantity of sealant applied to the mating surfaces must be
sufficient to permit a small amount to be squeezed out along the
entire parting surface when the hub bolts are correctly torqued.
2 Do not permit the sealant CM92 to enter any of the hub clamping
bolt holes.
3 Do not permit the sealant CM92 to enter the blade O-ring groove.
(h) Install the cylinder-side half of the hub (220).
(i) Install all bolts (210), washers (200), and nuts (190). Refer to Figure 7-10.
1 When the propeller is assembled without the bulkhead,
additional washers can be used to help with clamping the halves
of the hub (220) during the cure of the sealant CM92.
(j) Torque the nuts (190) in accordance with Table 8-1, "Torque Values", in the
Fits and Clearances chapter of this manual.

Height Height Height Height

Part Number Part Number
(inch) (mm) (inch) (mm)
A-2420-42 0.730 18.54 A-2420-27 1.180 29.97
A-2420-41 0.760 19.30 A-2420-26 1.201 30.73
A-2420-40 0.790 20.06 A-2420-25 1.240 31.49
A-2420-39 0.820 20.82 A-2420-24 1.270 32.25
A-2420-38 0.850 21.59 A-2420-23 1.300 33.02
A-2420-37 0.880 22.35 A-2420-22 1.330 33.78
A-2420-36 0.910 23.11 A-2420-21 1.360 34.54
A-2420-35 0.940 23.87 A-2420-20 1.390 35.30
A-2420-34 0.970 24.63 A-2420-19 1.420 36.06
A-2420-33 1.000 25.40 A-2420-18 1.450 36.83
A-2420-32 1.030 26.16 A-2420-17 1.480 37.59
A-2420-31 1.060 26.92 A-2420-15 1.510 38.35
A-2420-30 1.090 27.68 A-2420-14 1.540 39.11
A-2420-29 1.120 28.44 A-2420-13 1.570 39.87
A-2420-28 1.150 29.21

Stop Collar Heights

Table 7-3

ASSEMBLY 61-10-90 Page 7-32

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Split Keeper (130)

TPI-APS2028
Split Keeper Installation
Figure 7-16

O-ring (90)
Pitch Change Rod (150)

Stop Collar (125)

O-ring (160)
TPI-APS2011

Stop Collar Installation

Figure 7-17

ASSEMBLY 61-10-90 Page 7-33

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490

(5) Piston and Cylinder Installation:

(a) Install the split keeper (130) into the groove on the pitch change rod (150)
as shown in Figure 7-16.
(b) Put the stop collar (125) over the pitch change rod (150) and split
keeper (130) as shown in Figure 7-17.
a Use the correct stop collar (125) to get the necessary high pitch
stop angle. Refer to Table 7-3 for stop collar dimensions and part
numbers.

NOTE: A change in height of 1/32 inch (0.79 mm) yields

approximately one degree change in blade angle.
(c) Do a preliminary check of the blade high pitch stop angle.
a Move the blades to low pitch position and then move the blades into
high pitch by pushing down on the stop collar (125).
(d) Install the O-ring (90) on the pitch change rod (150) as shown
in Figure 7-17.
(e) Put the piston (80) onto the pitch change rod (150) with the ID O-ring
groove in the piston turned toward the stop collar (125).
Refer to Figure 7-18.

Piston (80)
Nut (60)

O-ring (70)

Stop Collar (125)

TPI-APS2014b

Piston Installation
Figure 7-18

ASSEMBLY 61-10-90 Page 7-34

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(f) Install the nut (60) onto the pitch change rod (150).

CAUTION: DO NOT TORQUE THE NUT (60) TO MORE THAN

55 FT-LBS(74 N•m).
a Torque the nut (60) to the minimum torque listed in Table 8-1,
"Torque Values", in the Fits and Clearances chapter of this manual.
(g) If the hole in the pitch change rod (150) and the slot in the nut (60)
do not align:
a Set the torque wrench to 55 Ft-Lbs (74 N•m).
b Slowly torque the nut (60) until a slot in the nut aligns with the
nearest hole in the pitch change rod (150).
(h) Safety the nut (60) with the cotter pin (50) as shown in Figure 7-19.
(i) Install the O-ring (70) in the OD groove on the piston (80) as shown in
Figure 7-18.
(j) Install the cylinder O-ring (160) on the cylinder-side of the hub (220) as
shown in Figure 7-17.

Cotter Pin (50)

Pitch Change Rod (150)

Nut (60)

TPI-APS2015

Cotter Pin Installation

Figure 7-19

ASSEMBLY 61-10-90 Page 7-35

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(k) Apply a bead of sealant CM92 on the O-ring (160) where the cylinder (40)
will touch the hub (220).
(l) Apply lubricant CM12 to the threads of the cylinder (40).
(m) Install the cylinder (40) onto the hub (220).
1 Attach the cylinder torque wrench adapter TE153 to the cylinder (40)
as shown in Figure 7-20.
2 Torque the cylinder (40) in accordance with Table 8-1,
"Torque Values", in the Fits and Clearances chapter of this manual.

Cylinder Torque
Wrench Adapter TE153

Cylinder (40) TPI-490-018

Cylinder Installation
Figure 7-20

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5. Setting Low Blade Angle

A. Low Pitch Stop Screw Installation

WARNING: 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) Using solvent MEK CM106 or MPK CM219, clean the threads of the low pitch
stop screw (30) to make sure that all oil, grease, and unwanted material have
been removed.
(2) Apply threadlocker CM21 to the threads of the low pitch stop screw (30).
(3) Install the low pitch stop screw (30) in the cylinder (40). Refer to Figure 7-21.

Nut (10)

Washer (20)

Set Screw (30)

Cylinder (40)

TPI-W10215

Low Pitch Stop Screw Installation

Figure 7-21

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B. Adjusting the Low Pitch Stop Angle

(1) Measure the low pitch stop angle.
(a) With the blades at the low pitch position, set the propeller pitch in
accordance with the aircraft Type Certificate Data Sheet.
(b) Adjust the low pitch angle with the low pitch stop screw (30).
1 To increase pitch, turn the low pitch stop screw (30) clockwise.
2 To decrease pitch, turn the low pitch stop screw (30)
counterclockwise.
(2) Install the washer (20) and the hex nut (10) on the low pitch stop screw (30) as
shown in Figure 7-21.
(3) Torque the hex nut (10) in accordance with Table 8-1, "Torque Values", in the
Fits and Clearances chapter of this manual.
(a) Holding the low pitch stop screw (30) with an allen wrench, apply torque to
the low pitch stop jam nut (10).
(4) ( )C1-( )( )( ) propellers only - Examine for air leakage around the
washer seal (20) on the low pitch stop screw (30).
(a) If there is no air leakage, go to step (5) of this procedure.
(b) If there is air leakage, replace the washer seal (20) on the low pitch stop
screw (30).
1 Repeat the check for air leakage and replace the washer seal (20)
on the low pitch stop screw (30) if necessary, until the check for air
leakage is satisfactory.
2 When the check for air leakage is satisfactory, continue to the next
step.
(5) Measure the final low pitch angle.
(6) Measure the blade track.
(a) Refer to the section, "Blade Tolerances" in the Fits and Clearances
chapter of this manual for blade track limits.

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6. Leak Check
A. Lubrication Fitting/Lubrication Hole Plug Installation
(1) For information about the location of lubrication fittings (180) and
lubrication hole plugs (181), refer to the Propeller Lubrication chapter of
Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).
(2) Install the lubrication fittings (180) and lubrication hole plugs (181) in
the lubrication holes in the hub (220).
(a) Leave one lubrication hole in the cylinder-side half of the hub (220) open
for the leak check.
(3) Tighten each lubrication fitting (180) and lubrication hole plug (181) until
finger-tight, then tighten one additional 360 degree turn.
B. Leak Check Procedure
(1) While the hub (220) is installed on the propeller test stand, actuate the propeller
to high pitch to purge air trapped in the hub (220).
(2) Apply soap solution CM122 to the hole where the lubrication fitting (180) or the
lubrication hole plug (181) was removed. Refer to Figure 7-22.
(3) If there is any indication of air exiting the hub (220), perform troubleshooting of
the propeller assembly to identify and correct the cause.
(4) After a satisfactory leak check, install the remaining lubrication fitting (180) or
lubrication plug (181) in the hub (220).
(a) Tighten the lubrication fitting (180) or lubrication plug (181) until
finger-tight, then tighten one additional 360 degree turn.

Soap Solution CM122

TPI-490-011

Hub Leak Check

Figure 7-22

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7. Post-Assembly Procedures
A. Counterweight Installation (3C4-series Propellers Only)
(1) For the correct counterweight (2000) for the propeller, refer to the Hartzell
Propeller Inc. Application Guide Manual (61-02-59).
(2) For installation of a counterweight (2000) on a composite blade, refer to
Hartzell Propeller Inc. Composite Propeller Blade Maintenance Manual 135F
(61-13-35).
B. Propeller Lubrication
(1) Lubricate the propeller in accordance with the Propeller Lubrication chapter
of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).
C. Static Balance
(1) 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).
D. Label Placement
(1) For installation of labels, refer to the Parts Identification and Marking chapter
of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02) or to
Hartzell Propeller Inc. Composite Blade Manual 135F (61-13-35).

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8. Propeller Disassembled for Shipping

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION 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, tested,
inspected, lubricated, and statically balanced before blade removal and
shipping.
(2) A propeller disassembled for shipping must be assembled by trained personnel
in accordance with Hartzell Propeller Inc. manuals.
(3) For additional general assembly information, refer to the section, "General" at
the beginning of this chapter.
B. Preparing the Propeller for Shipping
(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.
(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.
(3) Before removal, make a mark to indicate alignment of each blade assembly,
fork unit, spinner bulkhead, and balance weight location with the hub unit.
Refer to the section, "Marking Before Disassembly" in the Disassembly chapter
of this manual.
(a) Before removal of the pitch change block (320), make a mark to indicate
position and orientation to the pitch change fork unit.
1 The pitch change blocks may be taped in place in the pitch
change fork.
(4) Remove all balance weight screws (800) and balance weights (810).
(5) Disconnect the electric de-ice lead wires from the hub and bulkhead, if
applicable.
(6) Disassemble the propeller to the point of blade removal. Refer to the section,
"Propeller Disassembly" in the Disassembly chapter of this manual.

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(7) Propeller Reassembly with Blades Removed for Shipping

(a) Reassemble the propeller without the blade assemblies in accordance
with the applicable assembly instructions in this chapter.
1 The pitch change blocks (320) can be taped in position in the pitch
change fork (290).
(8) Packing the Propeller and Blades for Shipping
(a) Refer to the Packaging and Storage chapter of Hartzell Propeller Inc.
Standard Practices Manual 202A (61-01-02), for packing the propeller
and blades for shipping.
(b) Pack the propeller without blades for shipping.
(c) Pack the blades for shipping with the blade seal (700), blade bearings,
and lubricant on each blade shank.

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9. Reassembly of a Propeller Disassembled for Shipping

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION 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 examine 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. 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 for shipping, it is not necessary to replace
O-rings, unless they were damaged during component installation or
removal.
(1) Make sure that each blade assembly, the fork unit (290), and each balance
weight (810) has been marked for alignment with the hub (220).
(2) Remove all balance weight screws (800) and balance weights (810), if
necessary.
C. Propeller Reassembly
(1) Reassemble the propeller in accordance with the applicable 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
Calculating Torque When Using a Torque Wrench Adapter.......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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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
= (152.4 mm) adapter
1 ft (304.8 mm) + 0.50 ft (152.4 mm) (90.1 N•m)
for actual torque of
100 Ft-Lb (136 N•m)

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.
APS212

Calculating Torque When Using a Torque Wrench Adapter

Figure 8-1

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1. Torque Values (Rev. 1)

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. Important Information
(1) The structural integrity of joints in the propeller that are held together with
threaded fasteners is dependent upon proper torque application.
(a) Vibration can cause an incorrectly tightened fastener to fail in a matter of
minutes.
(b) Correct tension in a fastener depends on a variety of known load factors
and can influence fastener service life.
(c) Correct tension is achieved by application of measured torque.
(2) Use accurate wrenches and professional procedures to make sure of correct
tensioning.
(3) For the torque values to use when assembling a Hartzell Propeller Inc.
propeller, refer to Table 8-1, "Torque Values" in this chapter.
(4) 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.

Item Part Description Torque

No. Number
Ft-Lb In-Lb N•m
10 A-2043-1 Nut, 3/8-24, Hex, Self-Locking 15 180 21

B-3807 Nut, 5/8-18, Hex, Self-Locking 30 360 41

40 B-2428-( ) Cylinder 120-150 wet 1440-1800 wet 163-203 wet

40 minimum 480 minimum 55 minimum

60 A-2211 Nut, .718-20, Castelled, Thin
Refer to NOTE 2 Refer to NOTE 2 Refer to NOTE 2

150 A-2418-( ) Rod, Pitch Change 40 wet 480 wet 55 wet

190 A-2043-1 Nut, 3/8-24, Hex, Self-Locking 24-26 288-312 33-35

295 B-468-2 Extension, Bumper - 60-72 7-8

NOTE 1: Torque tolerance is + 10 percent unless otherwise noted.

NOTE 2: Refer to the text in the Assembly chapter of this manual for the
maximum value.

Torque Values
Table 8-1

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Fore-and-Aft
Movement

In-and-Out
Movement

Radial Play

End Play

TPI-MB-0027b

Blade Play
Figure 8-2

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2. Blade Tolerances

Tolerances Affecting the Blades - Refer to Figure 8-2

In-and-Out Blade Play 0.020 inch (0.50 mm)

End Play (leading edge to trailing edge) ± 0.05 inch (1.27 mm)
0.100 inch (2.54 mm) total

Fore-and-Aft (Face to camber)

± 0.05 inch (1.27 mm)
0.100 inch (2.54 mm) total

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

Blade Track ± 0.125 inch (3.17 mm)

or 0.25 inch (6.3 mm) total

Blade Pitch Setting Tolerance 0.2 degree
Between Blades at Low Pitch

NOTE: Hartzell Propeller Inc. Raptor-series propellers use specially

designed spacers within the propeller to achieve the required
blade fit. The blades may feel loose in the hub when compared
to Hartzell Compact-series propellers. During propeller
rotation, the blade fit within the propeller is the same as other
Hartzell propeller models.

Blade Tolerances
Table 8-2

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SPECIAL TOOLS, FIXTURES, AND EQUIPMENT - CONTENTS

1. Tooling and Facility Requirements.......................................................................9-3
A. Standard Tooling............................................................................................9-3
B. Special Tooling...............................................................................................9-3
C. Facilities.........................................................................................................9-3

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1. Tooling and Facility Requirements (Rev. 1)

A. Standard 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. Special Tooling
(1) 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) Tooling reference numbers 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.
(b) It is the responsibility of the repair station or the technician performing the
repair or servicing to use these special tools as required.
C. Facilities
(1) Grinding, plating, and painting of propeller components can create health
and safety hazards beyond that of other areas of a typical workshop.
(a) Areas where grinding, plating, and painting are performed should comply
with governmental regulations for occupational safety and health, industry
standards, and environmental regulations.
(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.

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ILLUSTRATED PARTS LIST - CONTENTS

1. Introduction...........................................................................................................10-3
A. General........................................................................................................... 10-3
B. Counterweight/Slugs/Mounting Hardware....................................................... 10-3
C. Spinner Assemblies/Mounting Hardware........................................................ 10-3
D. Ice Protection System Components................................................................ 10-4
2. Description of Columns........................................................................................10-4
A. Fig./Item Number............................................................................................. 10-4
B. Part Number.................................................................................................... 10-4
C. Airline Stock Number...................................................................................... 10-4
D. Description...................................................................................................... 10-5
E. Effectivity Code (EFF CODE).......................................................................... 10-5
F. Units Per Assembly (UPA)............................................................................... 10-5
G. Overhaul (O/H)................................................................................................ 10-6
H. Propeller Critical Part (PCP)............................................................................ 10-6
3. Description of Terms.............................................................................................10-6
A. Alternate.......................................................................................................... 10-6
B. Supersedure.................................................................................................... 10-6
C. Replacement................................................................................................... 10-6
D. Obsolete.......................................................................................................... 10-6
4. Vendor Supplied Hardware...................................................................................10-7

PROPELLER ASSEMBLIES
Propeller Model 3C1-L675A1 .................................................................................... 10-9
Propeller Model 3C1-R430A1.................................................................................. 10-15
Propeller Model 3C1-R619A1.................................................................................. 10-21
Propeller Model 3C1-R919A1.................................................................................. 10-27
Propeller Model 3C4-R430A1.................................................................................. 10-33
Propeller Model 4C1-F650A1.................................................................................. 10-39

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LIST OF FIGURES
Propeller Model 3C1-L675A1 ................................................Figure 10-1.................. 10-8
 Blade Retention Parts........................................................Figure 10-2................ 10-12
Propeller Model 3C1-R430A1 ...............................................Figure 10-3................ 10-14
  Blade Retention Parts........................................................Figure 10-4................ 10-17
Propeller Model 3C1-R619A1 ...............................................Figure 10-5................ 10-20
 Blade Retention Parts........................................................Figure 10-6................ 10-24
Propeller Model 3C1-R919A1 ...............................................Figure 10-7................ 10-26
 Blade Retention Parts........................................................Figure 10-8................ 10-30
Propeller Model 3C4-R430A1................................................Figure 10-9................ 10-32
 Blade Retention Parts......................................................Figure 10-10................ 10-36
Propeller Model 4C1-F650A1.............................................. Figure 10-11................ 10-38
 F-Flange Mounting Parts..................................................Figure 10-12................ 10-40
 Blade Retention Parts......................................................Figure 10-13................ 10-42

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1. Introduction (Rev. 1)

WARNING: ANY PART IDENTIFIED 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
EVEN THOUGH IT MAY STILL SHOW AN AVIATION TC OR PC
NUMBER STAMP. 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.
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 IN THIS MANUAL FOR
IDENTIFICATION OF PROPELLER CRITICAL PARTS.
(1) This chapter includes the parts lists and applicable illustrations for the propeller
models included in this manual.

CAUTION: THE ILLUSTRATIONS IN THIS CHAPTER ARE PROVIDED

FOR PART IDENTIFICATION AND LOCATION REFERENCE
ONLY. THEY SHOULD NOT BE USED FOR ASSEMBLY.
(a) The illustrations in this chapter use some general views of parts that may
not exactly depict every propeller part configuration.
B. Counterweights/Slugs/Mounting Hardware
(1) Counterweights, counterweight slugs, and the applicable mounting hardware
are application specific. Refer to Hartzell Propeller Inc. Application Guide
Manual 159 (61-02-59).
C. Spinner Assemblies/Mounting Hardware
(1) Spinner assemblies and the applicable mounting hardware are application
specific. Refer to Hartzell Propeller Inc. Application Guide Manual 159
(61-02-59).

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D. Ice Protection System Components

(1) Ice protection systems are application specific. Refer to Hartzell Propeller Inc.
Application Guide Manual 159 (61-02-59).
(a) For components of ice protection systems supplied by Hartzell, refer to
Hartzell Propeller Inc. Ice Protection System Manual 180 (30-61-80).
(b) For components of ice protection systems not supplied by Hartzell, refer to
the applicable TC or STC holder’s Instructions for Continued Airworthiness
(ICA).

2. Description of Columns (Rev. 1)

A. Fig./Item Number
(1) Figure Number refers to the illustration where items appear.
Item Numbers refer to the specific part callout in the applicable illustration.
(a) Item Numbers that are listed but not shown in the illustration are identified
by a dash to the left of the item number. (example: "-800")
(b) Alpha variants will be used to add additional items. There are two reasons
for the use of alpha variants:
1 A part may have an alternate, or may be superseded, replaced, or
obsoleted by another part.
a For example, the self-locking nut (A-2043) that is item 20 was
superseded by the self-locking nut (A-2043-1) that is item 20A.
2 An Illustrated Parts List may contain multiple configurations.
Effectivity codes are used to distinguish different part numbers within
the same list.
a For example, one propeller configuration may use a mounting
bolt (B-3339-1) that is item 30, yet another propeller
configuration uses a mounting bolt (B-3347) that is item 30A.
Effectivity codes are very important in the determination of parts
in a given configuration.
B. Part Number
(1) The Part Number is the Hartzell Propeller Inc. identification number for the part.
(2) Use the Hartzell Propeller Inc. part number when ordering the part from Hartzell
or a Hartzell-approved distributor.
C. Airline Stock Number
(1) This column is reserved for the Airline Stock Number.

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D. Description
(1) This column provides the Hartzell Propeller Inc. description of the part.
(2) Bullets and indentations are used to indicate parts that are components of a
sub-assembly.
(a) For example, a Fork Assembly that is part of a HC-C2YR-1 propeller
assembly will have one bullet ( • ) before the description. This indicates
that the Fork Assembly is part of the propeller assembly.
1 A Fork Bumper that is part of the Fork Assembly will appear
directly below the Fork Assembly with two bullets ( • • ) before the
description. This indicates that the Fork Bumper is part of the Fork
Assembly - that is part of the Propeller Assembly.
a Example: HC-C2YR-1
• Fork Assembly
• • Fork Bumper
(3) If the description in this column includes a "PCP:" prefix, the part is classified as
a Propeller Critical Part.
(4) If applicable, information regarding part alternatives, supersedures,
replacements, or obsolescence will appear in the Description column.
(a) Refer to the section, "Description of Terms" in this chapter for definitions
and requirements for part "alternates", "supersedures", etc.
(b) When part alternatives, supersedures, replacements, etc. are listed, the
service document number related to the change may be included for
reference.
(5) If applicable, vendor CAGE codes will be listed in the Description column.
E. Effectivity Code (EFF CODE)
(1) This column is used when additional information about a part is required.
(a) Effectivity codes can be used to identify parts that are only used on a
particular model, or to direct the user to additional information in the
"Effectivity" box at the bottom of the page.
(b) Whenever an effectivity code is present, refer to the "Effectivity" box at the
bottom of the page for the applicable information.
(2) Parts common to all assembly models on the page show no effectivity code.
F. Units Per Assembly (UPA)
(1) Designates the total quantity of an item required for the next higher assembly or
subassembly.

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 PROPELLER MAINTENANCE MANUAL
490

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 (PCP) that are contained in
each propeller model.
(a) Refer to the Introduction chapter of this manual for the definition of
Propeller Critical Parts (PCP).

3. Description of Terms (Rev. 1)

A. Alternate
(1) 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 number may be used interchangeably when ordering/stocking
new parts.
B. Supersedure
(1) 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.
C. Replacement
(1) 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.
D. Obsolete
(1) Obsolete parts are identified by "OBS” in the Units Per Assembly (UPA)
column. Obsolete items are considered unairworthy for continued flight.

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4. Vendor Supplied Hardware (Rev. 1)

A. Important Information
(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 part numbers have been assigned to all O-rings, fasteners, and
hardware. Part shipments from Hartzell Propeller Inc. will specify only the
Hartzell part numbers.
(2) Some O-rings, fasteners, and hardware manufactured in accordance with
established industry specifications (certain AN, MS, NAS items) are acceptable
for use in Hartzell Propeller Inc. products without additional standards imposed
by Hartzell.
(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 part number item and AN, MS, NAS,
and other specified vendor number items can be used interchangeably.
(c) The Hartzell part number must be used when ordering these parts from
Hartzell Propeller Inc.

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490

80 90
70

60
40

30 50
20
140
10

150
130

120 540
110 340
190 280
100 200
240
220

310

320
300
220 500
290 180
210
170
250 530
230
510 520
181

260
TPI-490-006_EXPLODED-675W-BUSH

270

160

Propeller Model 3C1-L675A1

Figure 10-1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-1 3C1-L675A1 PROPELLER ASSEMBLY PARTS

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

20 B-6747 • SEAL, WASHER 1 Y
30 102472 • SCREW, SET, 3/8-24 1
40 B-2428-3 • CYLINDER 1
50 B-3838-3-5 • COTTER PIN 1 Y
60 A-2211 • NUT, .718-20, CASTELLATED, THIN 1 Y
70 C-3317-348-1 • O-RING (PISTON OD) 1 Y
80 B-2419 • PISTON 1
90 C-3317-018 • O-RING (PISTON ID) 1 Y
100 106565 • SPRING SEAT 1
110 106563 • SPRING, COMPRESSION 1
120 101335-( ) • SLEEVE, STOP 1
130 A-867 • PCP: KEEPER, SPLIT (STOP SLEEVE) 1 Y PCP
140 106564 • GUIDE, SPRING 1
150 A-2418-15 • ROD, PITCH CHANGE 1
160 C-3317-247 • O-RING (CYLINDER) 1 Y
170 B-6544 • CAP, FITTING, LUBRICATION A 3 Y
180 A-279 • FITTING, LUBRICATION (ENGINE-SIDE OF HUB) A 3 Y
181 106545 • PLUG, LUBRICATION (CYLINDER-SIDE OF HUB) A 3 Y
190 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 3 Y
200 B-3834-0632 • WASHER 3 Y
210 A-2432 • BOLT, 3/8-24, HEX HEAD 9
220 106153 • PCP: HUB UNIT, 3C1-L675A1 1 PCP
230 A-2249 • • HUB BUSHING, GUIDE 1 Y
240 C-3317-021-1 • • O-RING (BUSHING TO HUB) 1 Y
250 A-6153-87 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
260 A-2245-2 • • HUB BUSHING, ROD (CYLINDER SIDE) 1 Y
270 A-5839-87 • • RING, RETAINING, INTERNAL SPIRAL 1 Y
280 103434-2 • • HUB BUSHING, ROD (ENGINE SIDE) 1
290 105732 • FORK, THREE BLADE ASSEMBLY 1
300 A-3256 • • BUMPER, FORK 3 Y
310 106136 • BUTTON, BLOCK, PITCH CHANGE 3 Y
320 105733 • BLOCK, PITCH CHANGE 3
340 C-3317-115-1 • O-RING 1 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

A REFER TO THE PROPELLER LUBRICATION

CHAPTER OF HARTZELL PROPELLER INC.
STANDARD PRACTICES MANUAL 202A (61-01-02).

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-L675A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-1 3C1-L675A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

L-FLANGE MOUNTING PARTS

500 A-2247-1 • STUD, MOUNTING, 7/16-20, DRILLED 6 Y
510 A-2498 • NUT, 7/16-20, CASTELLATED 6 Y
520 B-3842-0625 • SPRING PIN, 3/32", CRES 6 Y
530 A-2482 • WASHER, MOUNTING 6 Y
540 C-3317-228 • O-RING, MOUNTING 1 Y

BALANCE PARTS

-800 B-3840-( ) • SCREW A/R Y

-810 A-2424-( ) • BALANCE WEIGHT A/R

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) OR COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48).

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-L675A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
PROPELLER MAINTENANCE MANUAL
490

(This page is intentionally blank.)

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

Blade

720

730
600 670
610
620 680

690
660
700
640
710
650

630
TPI-490-008_BLADE-JM

Blade Retention Parts

Figure 10-2

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-1 3C1-L675A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

10-2 BLADE RETENTION PARTS

600 C-3317-028 • O-RING (BLADE PLUG) 3 Y

610 106048 • PLUG, BLADE 3
620 A-5839-156 RING, RETAINING, INTERNAL SPIRAL (BLADE
• 3 Y
PLUG)
630 C-792-B • RACE, BLADE SIDE 3
640 B-6144-1 • BALL, BEARING, 3/8" DIA 99 Y
650 B-793 • BALL SPACER 3 Y
660 C-792-A • RACE, HUB SIDE 3
670 101512 • RING, RETAINING, BEARING 3
680 105758-( ) • SHIM, BLADE 3
690 C-3317-246 • O-RING (BLADE SEAL ID) 3 Y
700 106117 • SEAL, BLADE B 3
REPLACED BY ITEM 700A, PRE HC-SB-61-377
700A 106117 • SEAL, BLADE C 3
REPLACES ITEM 700, POST HC-SB-61-377
700B 107223 • SEAL, BLADE 3
ALTERNATE FOR ITEM 700A, POST HC-SB-61-377
710 C-3317-158 • O-RING (BLADE SEAL OD) 3 Y
720 C-3317-341-8 • O-RING 3 Y
730 105731 • BUSHING, KNOB, PITCH CHANGE 3 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

B 106117 BLADE SEALS IDENTIFIED AS C 106117 BLADE SEALS IDENTIFIED AS

"REV. B" OR BEFORE "REV. C" OR LATER

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-L675A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

80 90
70

60
40

50
30
20
140
10

150

130

120
110
100 540
190
200 280
240
220
310
320 340
300
500
220 290

210 180

530 170
250
510
230 520

181
260
270

160
TPI-MB-0398

Propeller Model 3C1-R430A1

Figure 10-3

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-3 3C1-R430A1 PROPELLER ASSEMBLY PARTS

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

20 B-6747 • SEAL, WASHER 1 Y
30 102472 • SCREW, SET, 3/8-24 1
40 B-2428-3 • CYLINDER 1
50 B-3838-3-5 • COTTER PIN 1 Y
60 A-2211 • NUT, .718-20, CASTELLATED, THIN 1 Y
70 C-3317-348-1 • O-RING (PISTON OD) 1 Y
80 B-2419 • PISTON 1
90 C-3317-018 • O-RING (PISTON ID) 1 Y
100 106565 • SPRING SEAT 1
110 106563 • SPRING, COMPRESSION 1
120 101335-( ) • SLEEVE, STOP 1
130 A-867 • PCP: KEEPER, SPLIT (STOP SLEEVE) 1 Y PCP
140 106564 • GUIDE, SPRING 1
150 A-2418-2 • ROD, PITCH CHANGE 1
160 C-3317-247 • O-RING (CYLINDER) 1 Y
170 B-6544 • CAP, FITTING, LUBRICATION A 3 Y
180 A-279 • FITTING, LUBRICATION (ENGINE-SIDE OF HUB) A 3 Y
181 106545 • PLUG, LUBRICATION (CYLINDER-SIDE OF HUB) A 3 Y
190 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 9 Y
200 B-3834-0632 • WASHER 9 Y
210 A-2432 • BOLT, 3/8-24, HEX HEAD 9
220 105726-1 • PCP: HUB UNIT, 3C1-R430A1 1 PCP
230 A-2249 • • HUB BUSHING, GUIDE 1 Y
240 C-3317-021-1 • • O-RING (BUSHING TO HUB) 1 Y
250 A-6153-87 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
260 A-2245-2 • • HUB BUSHING, ROD (CYLINDER SIDE) 1 Y
270 A-5839-87 • • RING, RETAINING, INTERNAL SPIRAL 1 Y
280 103434-2 • • HUB BUSHING, ROD (ENGINE SIDE) 1
290 105732 • FORK, THREE BLADE ASSEMBLY 1
300 A-3256 • • BUMPER, FORK 3 Y
310 106136 • BUTTON, BLOCK, PITCH CHANGE 3 Y
320 105733 • BLOCK, PITCH CHANGE 3
340 C-3317-115-1 • O-RING 1 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

A REFER TO THE PROPELLER LUBRICATION

CHAPTER OF HARTZELL PROPELLER INC.
STANDARD PRACTICES MANUAL 202A (61-01-02).
- ITEM NOT ILLUSTRATED

Propeller Model 3C1-R430A1

61-10-90
Page 10-15
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-3 3C1-R430A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

R-FLANGE MOUNTING PARTS

500 A-2067 • STUD, MOUNTING, 1/2-20 6 Y
510 A-2069 • NUT, MOUNTING, CASTELLATED 6 Y
520 B-3842-0750 • SPRING PIN, 3/32", CRES 6 Y
530 A-1381 • WASHER, 1/2" CRES 6 Y
540 C-3317-228 • O-RING (MOUNTING) 1 Y

BALANCE PARTS
-800 B-3840-( ) • SCREW A/R Y
-810 A-2424-( ) • BALANCE WEIGHT A/R

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) OR COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48).

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-R430A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

720

730
600 670
610
620 680

690
660
700
640
710
650

630
TPI-490-008_BLADE-JM

Blade Retention Parts

Figure 10-4

61-10-90
Page 10-17
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

3C1-R430A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

10-4 BLADE RETENTION PARTS

600 C-3317-028 • O-RING (BLADE PLUG) 3 Y

610 106048 • PLUG, BLADE 3
620 A-5839-156 RING, RETAINING, INTERNAL SPIRAL (BLADE
• 3 Y
PLUG)
630 C-792-B • RACE, BLADE SIDE 3
640 B-6144-1 • BALL, BEARING, 3/8" DIA 99 Y
650 B-793 • BALL SPACER 3 Y
660 C-792-A • RACE, HUB SIDE 3
670 101512 • RING, RETAINING, BEARING 3
680 105758-( ) • SHIM, BLADE 3
690 C-3317-246 • O-RING (BLADE SEAL ID) 3 Y
700 106117 • SEAL, BLADE C 3
700A 107223 • SEAL, BLADE 3
ALTERNATE FOR ITEM 700, POST HC-SB-61-377
710 C-3317-158 • O-RING (BLADE SEAL OD) 3 Y
720 C-3317-341-8 • O-RING 3 Y
730 105731 • BUSHING, KNOB, PITCH CHANGE 3 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

C 106117 BLADE SEALS IDENTIFIED AS

"REV. C" OR LATER

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-R430A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
PROPELLER MAINTENANCE MANUAL
490

(This page is intentionally blank.)

61-10-90
Page 10-19
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

80 90
70

60
40

30 50
20
140
10

150

130

120 540
110 360
100 330
190
200 280
220 240
310 350
320 370
300
220 500
290
210 180

170
250 530
510
230 520

181
260
270

160
TPI-MB-0227

Propeller Model 3C1-R619A1

Figure 10-5

61-10-90
Page 10-20
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-5 3C1-R619A1 PROPELLER ASSEMBLY PARTS

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

20 B-6747 • SEAL, WASHER 1 Y
30 102472 • SCREW, SET, 3/8-24 1
40 B-2428-3 • CYLINDER 1
50 B-3838-3-5 • COTTER PIN 1 Y
60 A-2211 • NUT, .718-20, CASTELLATED, THIN 1 Y
70 C-3317-348-1 • O-RING (PISTON OD) 1 Y
80 B-2419 • PISTON 1
90 C-3317-018 • O-RING (PISTON ID) 1 Y
100 106565 • SPRING SEAT 1
110 106563 • SPRING, COMPRESSION 1
120 101335-( ) • SLEEVE, STOP 1
130 A-867 • PCP: KEEPER, SPLIT (STOP SLEEVE) 1 Y PCP
140 106564 • GUIDE, SPRING 1
150 A-2418-14 • ROD, PITCH CHANGE 1
160 C-3317-247 • O-RING (CYLINDER) 1 Y
170 B-6544 • CAP, FITTING, LUBRICATION A 3 Y
180 A-279 • FITTING, LUBRICATION (ENGINE-SIDE OF HUB) A 3 Y
181 106545 • PLUG, LUBRICATION (CYLINDER-SIDE OF HUB) A 3 Y
190 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 9 Y
200 B-3834-0632 • WASHER 9 Y
210 A-2432 • BOLT, 3/8-24, HEX HEAD 9
220 105726-2 • PCP: HUB UNIT, 3C1-R619A1 1 PCP
230 A-2249 • • HUB BUSHING, GUIDE 1 Y
240 C-3317-021-1 • • O-RING (BUSHING TO HUB) 1 Y
250 A-6153-87 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
260 A-2245-2 • • HUB BUSHING, ROD (CYLINDER SIDE) 1 Y
270 A-5839-87 • • RING, RETAINING, INTERNAL SPIRAL 1 Y
280 105870 • • HUB BUSHING, ROD (ENGINE SIDE) 1
290 105732 • FORK, THREE BLADE ASSEMBLY 1
300 A-3256 • • BUMPER, FORK 3 Y
310 106136 • BUTTON, BLOCK, PITCH CHANGE 3 Y
320 105733 • BLOCK, PITCH CHANGE 3

EFFECTIVITY MODEL EFFECTIVITY MODEL

A REFER TO THE PROPELLER LUBRICATION

CHAPTER OF HARTZELL PROPELLER INC.
STANDARD PRACTICES MANUAL 202A (61-01-02).

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-R619A1

61-10-90
Page 10-21
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-5 3C1-R619A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

330 A-5839-225 • RING, RETAINING, INTERNAL SPIRAL 1 Y

350 C-3317-115-1 • O-RING (HUB PLUG, ID) 1 Y
360 C-3317-226 • O-RING (HUB PLUG, OD) 1 Y
370 A-2481 • PLUG, HUB 1

R-FLANGE MOUNTING PARTS

500 A-2067 • STUD, MOUNTING, 1/2-20 6 Y
510 A-2069 • NUT, MOUNTING, CASTELLATED 6 Y
520 B-3842-0750 • SPRING PIN, 3/32", CRES 6 Y
530 A-1381 • WASHER, 1/2" CRES 6 Y
540 C-3317-228 • O-RING (MOUNTING) 1 Y

BALANCE PARTS
-800 B-3840-( ) • SCREW A/R Y
-810 A-2424-( ) • BALANCE WEIGHT A/R

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) OR COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48).

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-R619A1

61-10-90
Page 10-22
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
PROPELLER MAINTENANCE MANUAL
490

(This page is intentionally blank.)

61-10-90
Page 10-23
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

Blade

720

730
600 670
610
620 680

690
660
700
640
710
650

630
TPI-490-008_BLADE-JM

Blade Retention Parts

Figure 10-6

61-10-90
Page 10-24
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

3C1-R619A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

10-6 BLADE RETENTION PARTS

600 C-3317-028 • O-RING (BLADE PLUG) 3 Y

610 106048 • PLUG, BLADE 3
620 A-5839-156 RING, RETAINING, INTERNAL SPIRAL (BLADE
• 3 Y
PLUG)
630 C-792-B • RACE, BLADE SIDE 3
640 B-6144-1 • BALL, BEARING, 3/8" DIA 99 Y
650 B-793 • BALL SPACER 3 Y
660 C-792-A • RACE, HUB SIDE 3
670 101512 • RING, RETAINING, BEARING 3
680 105758-( ) • SHIM, BLADE 3
690 C-3317-246 • O-RING (BLADE SEAL ID) 3 Y
700 106117 • SEAL, BLADE B 3
REPLACED BY ITEM 700A, PRE HC-SB-61-377
700A 106117 • SEAL, BLADE C 3
REPLACES ITEM 700, POST HC-SB-61-377
700B 107223 • SEAL, BLADE 3
ALTERNATE FOR ITEM 700A, POST HC-SB-61-377
710 C-3317-158 • O-RING (BLADE SEAL OD) 3 Y
720 C-3317-341-8 • O-RING 3 Y
730 105731 • BUSHING, KNOB, PITCH CHANGE 3 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

B 106117 BLADE SEALS IDENTIFIED AS C 106117 BLADE SEALS IDENTIFIED AS

"REV. B" OR BEFORE "REV. C" OR LATER

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-R619A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

80 90
70

60
40

30 50
20
140
10

150
130
540
120 360
110
100 330
190 280
200
240
220
350
310
370
320
300 500
220
290 180
210
170
530
250
510
230 520

181
260
270
TPI-490-023_EXPLODED-919EC

160

Propeller Model 3C1-R919A1

Figure 10-7

61-10-90
Page 10-26
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-7 3C1-R919A1 PROPELLER ASSEMBLY PARTS

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

20 B-6747 • SEAL, WASHER 1 Y
30 102472 • SCREW, SET, 3/8-24 1
40 B-2428-3 • CYLINDER 1
50 B-3838-3-5 • COTTER PIN 1 Y
60 A-2211 • NUT, .718-20, CASTELLATED, THIN 1 Y
70 C-3317-348-1 • O-RING (PISTON OD) 1 Y
80 B-2419 • PISTON 1
90 C-3317-018 • O-RING (PISTON ID) 1 Y
100 106565 • SPRING SEAT 1
110 106563 • SPRING, COMPRESSION 1
120 101335-( ) • SLEEVE, STOP 1
130 A-867 • PCP: KEEPER, SPLIT (STOP SLEEVE) 1 Y PCP
140 106564 • GUIDE, SPRING 1
150 A-2418-3 • ROD, PITCH CHANGE 1
160 C-3317-247 • O-RING (CYLINDER) 1 Y
170 B-6544 • CAP, FITTING, LUBRICATION A 3 Y
180 A-279 • FITTING, LUBRICATION (ENGINE-SIDE OF HUB) A 3 Y
181 106545 • PLUG, LUBRICATION (CYLINDER-SIDE OF HUB) A 3 Y
190 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 9 Y
200 B-3834-0632 • WASHER 9 Y
210 A-2432 • BOLT, 3/8-24, HEX HEAD 9
220 105726 • PCP: HUB UNIT, 3C1-R919A1 1 PCP
230 A-2249 • • HUB BUSHING, GUIDE 1 Y
240 C-3317-021-1 • • O-RING (BUSHING TO HUB) 1 Y
250 A-6153-87 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
260 A-2245-2 • • HUB BUSHING, ROD (CYLINDER SIDE) 1 Y
270 A-5839-87 • • RING, RETAINING, INTERNAL SPIRAL 1 Y
280 105870 • • HUB BUSHING, ROD (ENGINE SIDE) 1
290 105732 • FORK, THREE BLADE ASSEMBLY 1
300 A-3256 • • BUMPER, FORK 3 Y
310 106136 • BUTTON, BLOCK, PITCH CHANGE 3 Y
320 105733 • BLOCK, PITCH CHANGE 3
330 A-5839-225 • RING, RETAINING, INTERNAL SPIRAL 1 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

A REFER TO THE PROPELLER LUBRICATION

CHAPTER OF HARTZELL PROPELLER INC.
STANDARD PRACTICES MANUAL 202A (61-01-02).

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-R919A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-7 3C1-R919A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

350 C-3317-115-1 • O-RING (HUB PLUG, ID) 1 Y

360 C-3317-226 • O-RING (HUB PLUG, OD) 1 Y
370 A-2481 • PLUG, HUB 1

R-FLANGE MOUNTING PARTS

500 A-2067 • STUD, MOUNTING, 1/2-20 6 Y
510 A-2069 • NUT, MOUNTING, CASTELLATED 6 Y
520 B-3842-0750 • SPRING PIN, 3/32", CRES 6 Y
530 A-1381 • WASHER, 1/2" CRES 6 Y
540 C-3317-228 • O-RING (MOUNTING) 1 Y

BALANCE PARTS
-800 B-3840-( ) • SCREW A/R Y
-810 A-2424-( ) • BALANCE WEIGHT A/R

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) OR COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48).

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-R919A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
PROPELLER MAINTENANCE MANUAL
490

(This page is intentionally blank.)

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

Blade

720

730
600 670
610
620 680

690
660
700
640
710
650

630
TPI-490-008_BLADE-JM

Blade Retention Parts

Figure 10-8

61-10-90
Page 10-30
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-8 3C1-R919A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

10-6 BLADE RETENTION PARTS

600 C-3317-028 • O-RING (BLADE PLUG) 3 Y

610 106048 • PLUG, BLADE 3
620 A-5839-156 RING, RETAINING, INTERNAL SPIRAL (BLADE
• 3 Y
PLUG)
630 C-792-B • RACE, BLADE SIDE 3
640 B-6144-1 • BALL, BEARING, 3/8" DIA 99 Y
650 B-793 • BALL SPACER 3 Y
660 C-792-A • RACE, HUB SIDE 3
670 101512 • RING, RETAINING, BEARING 3
680 105758-( ) • SHIM, BLADE 3
690 C-3317-246 • O-RING (BLADE SEAL ID) 3 Y
700 106117 • SEAL, BLADE B 3
REPLACED BY ITEM 700A, PRE HC-SB-61-377
700A 106117 • SEAL, BLADE C 3
REPLACES ITEM 700, POST HC-SB-61-377
700B 107223 • SEAL, BLADE 3
ALTERNATE FOR ITEM 700A, POST HC-SB-61-377
710 C-3317-158 • O-RING (BLADE SEAL OD) 3 Y
720 C-3317-341-8 • O-RING 3 Y
730 105731 • BUSHING, KNOB, PITCH CHANGE 3 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

B 106117 BLADE SEALS IDENTIFIED AS C 106117 BLADE SEALS IDENTIFIED AS

"REV. B" OR BEFORE "REV. C" OR LATER

- ITEM NOT ILLUSTRATED

Propeller Model 3C1-R919A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

80 90
70

60
40

30 50
20
10

150
130

125 190 540

200 240
220 280
250
320 285
300 500
290 170
220
180
210
530
510
520
310 230

181
165
160
TPI-MB-0210

Propeller Model 3C4-R430A1

Figure 10-9

61-10-90
Page 10-32
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-9 3C4-R430A1 PROPELLER ASSEMBLY PARTS

10 B-3807 • NUT, 5/8-18, HEX, SELF-LOCKING 1 Y

20 B-3851-1032 • WASHER 1 Y
30 A-4257 • SCREW, SET, 5/8-18, DRILLED 1
40 B-2428-2 • CYLINDER 1
50 B-3838-3-5 • COTTER PIN 1 Y
60 A-2211 • NUT, .718-20, CASTELLATED, THIN 1 Y
70 C-3317-348-1 • O-RING (PISTON OD) 1 Y
80 B-2419 • PISTON 1
90 C-3317-018 • O-RING (PISTON ID) 1 Y
125 A-2420-( ) • COLLAR, STOP 1
130 A-867 • PCP: KEEPER, SPLIT (STOP COLLAR) 1 Y PCP
150 A-2418-8 • ROD, PITCH CHANGE 1
160 C-3317-247 • O-RING (CYLINDER) 1 Y
165 C-3317-210-1 • • O-RING (HUB TO PITCH CHANGE ROD) 1 Y
170 B-6544 • CAP, FITTING, LUBRICATION A 3 Y
180 A-279 • FITTING, LUBRICATION (ENGINE-SIDE OF HUB) A 3 Y
181 106545 • PLUG, LUBRICATION (CYLINDER-SIDE OF HUB) A 3 Y
190 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 9 Y
200 B-3834-0632 • WASHER 9 Y
210 A-2432 • BOLT, 3/8-24, HEX HEAD 9
220 106546 • PCP: HUB UNIT, 3C4-R430( )A( ) 1 PCP
230 A-2249 • • HUB BUSHING, GUIDE 1 Y
240 C-3317-021-1 • • O-RING (GUIDE BUSHING OD) 1 Y
250 A-6153-87 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
280 103434-2 • • HUB BUSHING, ROD (ENGINE SIDE) 1
285 C-3317-115-1 • • O-RING (GUIDE BUSHING ID) 1 Y
290 105732 • FORK, THREE BLADE ASSEMBLY 1
300 A-3256 • • BUMPER, FORK 3 Y
310 106136 • BUTTON, BLOCK, PITCH CHANGE 3 Y
320 105733 • BLOCK, PITCH CHANGE 3

EFFECTIVITY MODEL EFFECTIVITY MODEL

A REFER TO THE PROPELLER LUBRICATION

CHAPTER OF HARTZELL PROPELLER INC.
STANDARD PRACTICES MANUAL 202A (61-01-02).

- ITEM NOT ILLUSTRATED

Propeller Model 3C4-R430A1

61-10-90
Page 10-33
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-9 3C4-R430A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

R-FLANGE MOUNTING PARTS

500 A-2067 • STUD, MOUNTING, 1/2-20 6 Y
510 A-2069 • NUT, MOUNTING, CASTELLATED 6 Y
520 B-3842-0750 • SPRING PIN, 3/32", CRES 6 Y
530 A-1381 • WASHER, 1/2" CRES 6 Y
540 C-3317-228 • O-RING (MOUNTING) 1 Y

BALANCE PARTS
-800 B-3840-( ) • SCREW A/R Y
-810 A-2424-( ) • BALANCE WEIGHT A/R

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

Propeller Model 3C4-R430A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

3C4-R430A1 PROPELLER ASSEMBLY PARTS,

CONTINUED
COUNTERWEIGHTS AND COUNTERWEIGHT SLUGS
-2000 • COUNTERWEIGHT PCP
APPLICATION SPECIFIC
REFER TO HARTZELL PROPELLER INC.
APPLICATION GUIDE MANUAL 159 (61-02-59) FOR
PART NUMBER AND PROPELLER CRITICAL PART
(PCP) IDENTIFICATION
-2010 • COUNTERWEIGHT SLUG
APPLICATION SPECIFIC
REFER TO HARTZELL PROPELLER INC.
APPLICATION GUIDE MANUAL 159 (61-02-59) FOR
PART NUMBER AND PROPELLER CRITICAL PART
(PCP) IDENTIFICATION

COUNTERWEIGHT SLUG MOUNTING HARDWARE

-2020 • BOLT Y
APPLICATION SPECIFIC
REFER TO HARTZELL PROPELLER INC.
APPLICATION GUIDE MANUAL 159 (61-02-59) FOR
PART NUMBER AND PROPELLER CRITICAL PART
(PCP) IDENTIFICATION
-2030 • NUT Y
APPLICATION SPECIFIC
REFER TO HARTZELL PROPELLER INC.
APPLICATION GUIDE MANUAL 159 (61-02-59) FOR
PART NUMBER AND PROPELLER CRITICAL PART
(PCP) IDENTIFICATION

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) OR COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48).

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

Propeller Model 3C4-R430A1

61-10-90
Page 10-35
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

Blade

720
730
600
610
670
620
680
660
690
640
700
650
710
630
TPI-MB-0218

Blade Retention Parts

Figure 10-10

61-10-90
Page 10-36
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

3C4-R430A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

10-10 BLADE RETENTION PARTS

600 C-3317-028 • O-RING (BLADE PLUG) 3 Y

610 106048 • PLUG, BLADE 3
620 A-5839-156 • RING, RETAINING, INTERNAL SPIRAL
3 Y
(BLADE PLUG)
630 C-792-B • RACE, BLADE SIDE 3
640 B-6144-1 • BALL, BEARING, 3/8" DIA 99 Y
650 B-793 • BALL SPACER 3 Y
660 C-792-A • RACE, HUB SIDE 3
670 101512 • RING, RETAINING, BEARING 3
680 105758-( ) • SHIM, BLADE 3
690 C-3317-246 • O-RING (BLADE SEAL ID) 3 Y
700 106117 • SEAL, BLADE C 3
700A 107223 • SEAL, BLADE 3
ALTERNATE FOR ITEM 700
710 C-3317-158 • O-RING (BLADE SEAL OD) 3 Y
720 C-3317-341-8 • O-RING 3 Y
730 105731 • BUSHING, KNOB, PITCH CHANGE 3 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

C 106117 BLADE SEALS IDENTIFIED AS

"REV. C" OR LATER

- ITEM NOT ILLUSTRATED

Propeller Model 3C4-R430A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

80 90
70

60
40

50
30
20 140
10
150
130

120
115
110 210
100 340
220 280

310
320 540
240
290
220
200 180
170
250
190
230
295 300

E
181
260
270
160
TPI-MB-0356

Propeller Model 4C1-F650A1

Figure 10-11

61-10-90
Page 10-38
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-11 4C1-F650A1 PROPELLER ASSEMBLY PARTS

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

20 B-6747 • SEAL, WASHER 1 Y
30 102472 • SCREW, SET, 3/8-24 1
40 B-2428-3 • CYLINDER 1
50 B-3838-3-5 • COTTER PIN 1 Y
60 A-2211 • NUT, .718-20, CASTELLATED, THIN 1 Y
70 C-3317-348-1 • O-RING (PISTON OD) 1 Y
80 B-2419 • PISTON 1
90 C-3317-018 • O-RING (PISTON ID) 1 Y
100 106565 • SPRING SEAT 1
110 106563 • SPRING, COMPRESSION 1
115 107426 • SPRING, COMPRESSION 1
120 101335-( ) • SLEEVE, STOP 1
130 A-867 • PCP: KEEPER, SPLIT (STOP SLEEVE) 1 Y PCP
140 106564 • GUIDE, SPRING 1
150 A-2418-17 • ROD, PITCH CHANGE 1
160 C-3317-247 • O-RING (CYLINDER) 1 Y
170 B-6544 • CAP, FITTING, LUBRICATION A 4 Y
180 A-279 • FITTING, LUBRICATION (ENGINE-SIDE OF HUB) A 4 Y
181 106545 • PLUG, LUBRICATION (CYLINDER-SIDE OF HUB) A 4 Y
190 A-2043-1 • NUT, 3/8-24, HEX, SELF-LOCKING 12 Y
200 B-3834-0632 • WASHER 12 Y
210 A-2432 • BOLT, 3/8-24, HEX HEAD 12
220 107402-1 • PCP: HUB UNIT, 4C1-F650A1 1 PCP
230 A-2249 • • HUB BUSHING, GUIDE 1 Y
240 C-3317-021-1 • • O-RING (BUSHING TO HUB) 1 Y
250 A-6153-87 • • RING, RETAINING, EXTERNAL SPIRAL 1 Y
260 A-2245-2 • • HUB BUSHING, ROD (CYLINDER SIDE) 1 Y
270 A-5839-87 • • RING, RETAINING, INTERNAL SPIRAL 1 Y
280 103434-2 • • HUB BUSHING, ROD (ENGINE SIDE) 1
290 107378 • FORK, FOUR BLADE ASSEMBLY 1
295 B-468-2 • • EXTENSION, BUMPER 4
300 A-3256 • • BUMPER, FORK 4 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

A REFER TO THE PROPELLER LUBRICATION

CHAPTER OF HARTZELL PROPELLER INC.
STANDARD PRACTICES MANUAL 202A (61-01-02).

- ITEM NOT ILLUSTRATED

Propeller Model 4C1-F650A1

61-10-90
Page 10-39
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

Propeller Flange

550
500

540
Engine Flange

530

510
TPI-F-FLANGE1-1

F-Flange Mounting Parts

Figure 10-12

61-10-90
Page 10-40
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

10-11 4C1-F650A1 PROPELLER ASSEMBLY PARTS,

CONTINUED
310 106136 • BUTTON, BLOCK, PITCH CHANGE 4 Y
320 105733 • BLOCK, PITCH CHANGE 4
340 C-3317-115-1 • O-RING (HUB PLUG, ID) 1 Y

10-12 F-FLANGE MOUNTING PARTS

500 A-2429-4 • STUD, MOUNTING, 1/2-20 6 Y
510 A-2044 • NUT, 1/2-20, HEX, SELF-LOCKING 6 Y
530 A-1381 • WASHER, 1/2" CRES 6 Y
540 C-3317-228 • O-RING (MOUNTING) 1 Y
550 B-6138-8-9 • DOWEL PIN 2 Y

BALANCE PARTS
-800 B-3840-( ) • SCREW A/R Y
-810 A-2424-( ) • BALANCE WEIGHT A/R

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) OR COMPOSITE SPINNER
MAINTENANCE MANUAL 148 (61-16-48).

EFFECTIVITY MODEL EFFECTIVITY MODEL

- ITEM NOT ILLUSTRATED

Propeller Model 4C1-F650A1

61-10-90
Page 10-41
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

Blade

720

730
600 670
610
620 680

690
660
700
640
710
650

630
TPI-490-008_BLADE-JM

Blade Retention Parts

Figure 10-13

61-10-90
Page 10-42
ILLUSTRATED PARTS LIST Rev. 2 Nov/19
 PROPELLER MAINTENANCE MANUAL
490

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

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

4C1-F650A1 PROPELLER ASSEMBLY PARTS,

CONTINUED

10-13 BLADE RETENTION PARTS

600 C-3317-028 • O-RING (BLADE PLUG) 4 Y

610 106048 • PLUG, BLADE 4
620 A-5839-156 RING, RETAINING, INTERNAL SPIRAL (BLADE
• 4 Y
PLUG)
630 C-792-B • RACE, BLADE SIDE 4
640 B-6144-1 • BALL, BEARING, 3/8" DIA 132 Y
650 B-793 • BALL SPACER 4 Y
660 C-792-A • RACE, HUB SIDE 4
670 101512 • RING, RETAINING, BEARING 4
680 105758-( ) • SHIM, BLADE 4
690 C-3317-246 • O-RING (BLADE SEAL ID) 4 Y
700 106117 • SEAL, BLADE C 4
700A 107223 • SEAL, BLADE 4
ALTERNATE FOR ITEM 700
710 C-3317-158 • O-RING (BLADE SEAL OD) 4 Y
720 C-3317-341-8 • O-RING 4 Y
730 105731 • BUSHING, KNOB, PITCH CHANGE 4 Y

EFFECTIVITY MODEL EFFECTIVITY MODEL

C 106117 BLADE SEALS IDENTIFIED AS

"REV. C" OR LATER

- ITEM NOT ILLUSTRATED

Propeller Model 4C1-F650A1

61-10-90
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ILLUSTRATED PARTS LIST Rev. 2 Nov/19
PROPELLER MAINTENANCE MANUAL
490

(This page is intentionally blank.)

61-10-90
Page 10-44
ILLUSTRATED PARTS LIST Rev. 2 Nov/19