Hartzell HC-B3 ( )( )-2( ), ( )( )-3( ), TF-7( ), ( )( )-5( ), HC-B4 ( )( )-3( ), ( )( )-5( ), HC-B5M ( )-2( ), ( )-3( ), ( )-5( ), HC-A3 (V,MV)F-7( ) Propeller Manual

HARTZELL PROPELLER INC.

One Propeller Place

Piqua, Ohio 45356-2634 U.S.A.

Telephone: 937.778.4200

Fax: 937.778.4391

MANUAL REVISION TRANSMITTAL

Manual 139 (61-00-39)

Propeller Owner's Manual and Logbook

REVISION 13 dated June 2015

Attached is a copy of Revision 13 to Hartzell Manual 139.

Page Control Chart for Revision 13:

Remove

Page No.

Insert

Page No.

COVER/INSIDE COVER

REVISION HIGHLIGHTS pages 5 thru 8

COVER/INSIDE COVER

REVISION HIGHLIGHTS pages 5 thru 8

LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES pages 23 and 24 pages 23 and 24

TABLE OF CONTENTS pages 27 and 28 pages 31 and 32

TABLE OF CONTENTS pages 27 and 28 pages 31 and 32

INTRODUCTION INTRODUCTION pages 1-5 thru 1-14 pages 1-5 thru 1-14

INSTALLATION AND REMOVAL INSTALLATION AND REMOVAL pages 3-1 thru 3-4 pages 3-11 and 3-12 pages 3-17 thru 3-68 pages 3-1 thru 3-4 pages 3-11 and 3-12 pages 3-17 thru 3-70

INSPECTION AND CHECK pages 5-23 and 5-24

INSPECTION AND CHECK pages 5-23 and 5-24

MAINTENANCE PRACTICES MAINTENANCE PRACTICES pages 6-9 and 6-10 pages 6-9 and 6-10

This page may be discarded after proper filing of the revision.

Page 1 of 2

Page Control Chart for Revision 13, continued:

Remove

Page No.

Insert

Page No.

NOTE 1: When the manual revision has been inserted in the manual, make a record of the information required on the Record of Revisions page in this manual.

NOTE 2: Pages distributed in this revision may include pages from previous revisions if they are on the opposite side of revised page. This is done as a convenience to those users who wish to print a two-sided copy of the new revision.

Page 2 of 2

Manual No. 139

61-00-39

Revision 13

June 2015

Propeller Owner's Manual

and Logbook

Series: HC-B3( )( )-2( )

HC-B3( )( )-3( )

HC-B3( )( )-5( )

HC-B3TF-7( )

HC-B4( )( )-3( )

HC-B4( )( )-5( )

HC-B5M( )-2( )

HC-B5M( )-3( )

HC-B5M( )-5( )

HC-A3(V,MV)F-7( )

Steel Hub Turbine Propellers with Aluminum Blades

Hartzell Propeller Inc.

One Propeller Place

Piqua, OH 45356 - 2634 U.S.A.

Ph: 937 - 778 - 4200 (Hartzell Propeller Inc.)

Ph: 937-778-4379 (Product Support)

Product Support Fax: 937-778-4391


139

© 1984, 1992, 1994, 1997, 1999, 2001, 2002, 2006, 2009, 2011, 2012, 2013, 2015

Hartzell Propeller Inc. - All rights reserved

COVER

61-00-39

Page 2

Rev. 13 Jun/15


139

REVISION 13 HIGHLIGHTS

Revision 13, dated June 2015, incorporates the following:

• COVER

• Revised to match the manual revision

• REVISION HIGHLIGHTS


• LIST OF EFFECTIVE PAGES


• TABLE OF CONTENTS


• INTRODUCTION

• Revised to add the use of safety cable

• Revised the section, "Reference Publications"

• Made other language/format changes

• INSTALLATION AND REMOVAL

• Revised to add the use of safety cable, where applicable

• Revised the section, "Installing HC-B(3, 4)( )W-3( ) Propeller on the Aircraft Engine" to include compliance with GE

Aviation Service Bulletin H80-100-72-00019 on Thrush aircraft models S2R-H80 or S2RHG-H80

• Made other language/format changes

• INSPECTION AND CHECK

• Revised the illustration, "Turbine Engine Overtorque Limits"

• MAINTENANCE PRACTICES

• Revised the section, "Carbon Block Assemblies"

REVISION HIGHLIGHTS

61-00-39

Page 5

Rev. 13 Jun/15


139

(This page is intentionally blank.)


61-00-39

Page 6

Rev. 13 Jun/15


139

REVISION HIGHLIGHTS

1. Introduction

A. General

(1) This is a list of current revisions that have been issued against this manual. Please compare it 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 the revision.

(3) Comments indicates the level of the revision.

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

(b) Reissue is a revision to an existing manual that includes major content and/or major format changes.

The manual is distributed in its entirety. All the page revision dates are the same and no change bars are used.

(c) Major Revision is a revision to an existing manual that includes major content or minor content changes over a large portion of the manual. The manual is distributed in its entirety. All the page revision dates are the same, but change bars are used to indicate the changes incorporated in the latest revision of the manual.

(d) Minor Revision is a revision to an existing manual that includes minor content changes to the manual. Only the revised pages of the manual are distributed. Each page retains the date and the change bars associated with the last revision to that page.


61-00-39

Page 7

Rev. 13 Jun/15

Revision No.

Revision 5

Revision 6

Revision 7

Revision 8

Revision 9

Revision 10

Revision 11

Revision 12

Revision 13


139

Issue Date

Oct/99

Mar/01

Oct/02

Dec/06

Aug/09

Jun/11

Jul/12

Mar/13

Jun/15

Comments

Reissue

Minor Revision

Minor Revision

Minor Revision

Minor Revision

Minor Revision

Minor Revision

Minor Revision

Minor Revision


61-00-39

Page 8

Rev. 13 Jun/15


139

Chapter

LIST OF EFFECTIVE PAGES

Page Revision Date

Cover

Message

Revision Highlights

Record of Revisions

Cover and Inside Cover Rev. 13 Jun/15

1 thru 4 Rev. 6 Mar/01

5 thru 8

9 and 10

Rev. 13 Jun/15

Rev. 6 Mar/01

Record of Temporary Revisions 11 and 12

Service Documents List 13 and 14

Airworthiness Limitations

List of Effective Pages

15 thru 22

23 and 24

Rev. 6 Mar/01

Rev. 11 Jul/12

Rev. 10 Jun/11

Rev. 13 Jun/15

Table of Contents

Table of Contents

Table of Contents

Table of Contents

25 and 26

27

28 thru 31

32

Table of Contents

Introduction

33 and 34

1-1 thru 1-5

Introduction

Introduction

Description and Operation





1-14 thru 1-16

2-1

2-2

2-3

2-4

2-5

Description and Operation 2-6 thru 2-19

Rev. 12 Mar/13

Rev. 13 Jun/15

Rev. 12 Mar/13

Rev. 13 Jun/15

Rev. 12 Mar/13

Rev. 12 Mar/13

Rev. 11 Jul/12

Rev. 12 Mar/13

Rev. 11 Jul/12

Rev. 10 Jun/11

Rev. 7

Rev. 7

Oct/02

Rev. 11 Jul/12

Oct/02

Rev. 11 Jul/12 Description and Operation 2-20


Description and Operation 2-28 and 2-29

Description and Operation 2-30 and 2-31



Installation and Removal


3-1 thru 3-4

3-5




3-6 thru 3-10

3-11

3-12

Rev. 7

Rev. 7

Rev. 7

Oct/02

Rev. 11 Jul/12

Rev. 10 Jun/11

Oct/02

Rev. 12 Mar/13

Rev. 13 Jun/15

Oct/02

Rev. 11 Jul/12

Rev. 8 Dec/06

Rev. 13 Jun/15

LIST OF EFFECTIVE PAGES

61-00-39

Page 23

Rev. 13 Jun/15


139

Chapter

LIST OF EFFECTIVE PAGES

Page Revision Date









3-13 thru 3-16

3-17 and 3-18

3-19

3-20 thru 3-23

3-24 and 3-25

3-26 thru 3-29

3-30

3-31 thru 3-70

Testing and Troubleshooting 4-1 and 4-2

Testing and Troubleshooting 4-3

Testing and Troubleshooting 4-4

Testing and Troubleshooting 4-5 thru 4-10

Testing and Troubleshooting 4-11 and 4-12

Inspection and Check 5-1

Inspection and Check


5-2 thru 5-19

5-20 and 5-21

Rev. 11 Jul/12

Rev. 13 Jun/15

Rev. 11 Jul/12

Rev. 13 Jun/15

Rev. 11 Jul/12

Rev. 13 Jun/15

Rev. 11 Jul/12

Rev. 13 Jun/15

Rev. 12 Mar/13

Rev. 7 Oct/02

Rev. 12 Mar/13

Rev. 7 Oct/02

Rev. 10 Jun/11

Rev. 12 Mar/13

Rev. 11 Jul/12

Rev. 12 Mar/13




Maintenance Practices





5-22 Rev. 11 Jul/12

5-23 Rev. 13 Jun/15

5-24 thru 5-34

6-1 and 6-2

Rev. 11 Jul/12

Rev. 12 Mar/13

6-3

6-4

6-5 thru 6-8

6-9

Rev. 11 Jul/12

Rev. 6 Mar/01

Rev. 11 Jul/12

Rev. 13 Jun/15





6-10

6-11

6-12 thru 6-22

6-23 and 6-24

Anti-ice and De-ice Systems 7-1 thru 7-8

Records 8-1 thru 8-4

Rev. 11 Jul/12

Rev. 12 Mar/13

Rev. 11 Jul/12

Rev. 12 Mar/13

Rev. 12 Mar/13

Rev. 5 Oct/99

LIST OF EFFECTIVE PAGES

61-00-39

Page 24

Rev. 13 Jun/15


139

CONTENTS Page

3. Propeller Assembly Installation ..................................................3-6

A. Precautions ............................................................................3-6

B. Installing HC-B(3, 5)( )( )-2( ) Propeller on the

Aircraft Engine ......................................................................3-7

C. Installing HC-B(3,4,5)( )(A,N,P)-3( ) Propeller on the

Aircraft Engine ....................................................................3-14

D. Installing HC-B(3,4)( )W-3( ) Propeller on the

Aircraft Engine ....................................................................3-20

E. Installing HC-B(3,4)( )( )-5( ) Propeller, with a One-piece

Spinner Mounting Plate, on the Aircraft Engine ..................3-29

F. Installing HC-B(3,4,5)( )( )-5( ) Propeller, with a Two-piece


G. Installing HC-( )3( )( )-7( ) Propeller on the

Allison Engine .....................................................................3-40

4. Spinner Dome Installation ........................................................3-50

5. Post-Installation Checks ...........................................................3-50

6. Spinner Dome Removal ...........................................................3-51

7. Propeller Assembly Removal ...................................................3-52

A. Removal of HC-B(3,5)( )( )-2( ) Propellers ...........................3-52

B. Removal of HC-B(3,4,5)( )(A,N,P)-3( ) Propellers ...............3-55

C. Removal of HC-B(3,4)( )W-3( ) Propellers ...........................3-59

D. Removal of HC-B(3,4,5)( )( )-5( ) Propellers ........................3-62

E. Removal of HC-( )3( )( )-7( ) Propellers ...............................3-65

F. Removal of Beta Valve Assembly for

HC-( )3( )( )-7( ) Propellers ................................................3-68

TABLE OF CONTENTS

61-00-39

Page 27

Rev. 13 Jun/15


139

CONTENTS Page

TESTING AND TROUBLESHOOTING ..........................................4-1

1. Operational Tests .......................................................................4-3

A. Initial Run-Up .........................................................................4-3

B. Post-Run Check .....................................................................4-3

C. Maximum RPM (Static) Hydraulic Low Pitch Stop Check ......4-3

D. Feathering Pitch Stop Adjustment .........................................4-4

E. Start Lock Unit Adjustment ....................................................4-4

F. Propeller Ice Protection System ............................................4-4

2. Troubleshooting .........................................................................4-4

A. Hunting and Surging ..............................................................4-4

B. Engine Speed Varies with Airspeed .......................................4-5

C. Loss of Propeller Control .......................................................4-6

D. Failure to Feather (or feathers slowly) ...................................4-6

E. Failure to Unfeather ...............................................................4-7

F. Start Lock Units Fail to Latch on Shutdown

(-2, -5 and some -3 Models) .................................................4-7

G. Vibration .................................................................................4-8

H. Propeller Overspeed ..............................................................4-9

I. Propeller Underspeed ............................................................4-9

J. Oil or Grease Leakage .............................................................4-10

INSPECTION AND CHECKS .........................................................5-1

1. Pre-Flight Checks .......................................................................5-3

2. Post-Flight Checks .....................................................................5-5

3. Operational Checks ....................................................................5-6

4. Required Periodic Inspections and Maintenance .......................5-7

A. Periodic Inspections ...............................................................5-7

B. Periodic Maintenance ............................................................5-8

C. Compliance Inspections .........................................................5-8

D. Airworthiness Limitations .....................................................5-11

E. Overhaul Periods .................................................................5-12


61-00-39

Page 28

Rev. 12 Mar/13


139

RECORDS ......................................................................................8-1

1. Introduction ................................................................................8-3

2. Record Keeping .........................................................................8-3

A. Information to be Recorded ...................................................8-3

LIST OF ILLUSTRATIONS Page

HC-B(3,5)( )( )-2( ) Propeller Assembly .......... Figure 2-1 ..............2-4

Steel Hub Unit ................................................ Figure 2-2 ..............2-5

HC-B(3,4,5)( )( )-3( ) Propeller Assembly ....... Figure 2-3 ..............2-8

Start Lock Unit on HC-B(3,4,5)( )( )-3( )

Propeller Assembly .................................. Figure 2-4 ............2-12

HC-B(3,4)( )( )-5( ) Propeller Assembly with

One-piece Spinner Mounting Plate

(Superseded Configuration) ..................... Figure 2-5 ............2-14

HC-B3( )( )-5( ) Propeller Assembly with

Two-piece Spinner Mounting Plate

(New Configuration) ................................. Figure 2-6 ............2-15

HC-B(4,5)( )( )-5( ) Propeller Assembly with

Two-piece Spinner Mounting Plate

(New Configuration) ................................. Figure 2-7 ............2-16

HC-A3VF-7( ) Propeller Assembly .................. Figure 2-8 ............2-22

HC-A3MVF-7( ) and HC-B3TF-7( )

Propeller Assembly .................................. Figure 2-9 ............2-23

Governor in Onspeed Condition .................... Figure 2-10 ...........2-32

Governor in Underspeed Condition ............... Figure 2-11 ...........2-32

Governor in Overspeed Condition ................. Figure 2-12 ...........2-32

Feathering Governor ..................................... Figure 2-13 ...........2-34

Synchronizer/Synchrophaser Governor ........ Figure 2-14 ...........2-34

Mounting Bolt and Washer ............................. Figure 3-1 ..............3-9


61-00-39

Page 31

Rev. 12 Mar/13


139

LIST OF ILLUSTRATIONS Page

Installing Propeller on Engine Flange ............. Figure 3-2 ............3-10

Diagram of Torquing Sequence for

Propeller Mounting Bolts .......................... Figure 3-3 ............3-11

Determining Torque Value When Using

Torquing Adaptor ...................................... Figure 3-4 ............3-13

Beta System Puller for Decompressing

-3 Series External Beta System ............... Figure 3-5 ............3-16

Carbon Block and Beta Ring Clearance ......... Figure 3-6 ............3-18

Carbon Block Assembly.................................. Figure 3-7 ............3-18

Hub-to-Spacer O-ring Location in the Spacer ............................................ Figure 3-8 ............3-22

Installing the HC-B(3,4)( )W-3( ) Propeller on the Engine Flange ............................... Figure 3-9 ............3-24

Installing the Washer on the Mounting Stud .. Figure 3-10 ...........3-26


Installation ............................................... Figure 3-11 ...........3-30

Beta Valve System ........................................ Figure 3-12 ...........3-38

Cross Section View of the Beta Valve

System .................................................... Figure 3-13 ...........3-39

-7( ) Propeller Assembly ................................ Figure 3-14 ...........3-42

Spring Assembly to Cylinder

Attachment Details .................................. Figure 3-15 ...........3-43

Piston to Link Arm Attachment Details........... Figure 3-16 ...........3-43

Filed Rod for Set Screw................................. Figure 3-17 ...........3-48

Checking Blade Track..................................... Figure 5-1 ............5-18

Blade Play ...................................................... Figure 5-2 ............5-18

Turbine Engine Overspeed Limits .................. Figure 5-3 ............5-22

Turbine Engine Overtorque Limits .................. Figure 5-4 ............5-23


61-00-39

Page 32

Rev. 13 Jun/15

Propeller Owner’s Manual

139

(2) Review the propeller and aircraft type certificate data sheet (TCDS), Pilot Operating Handbook (POH), and any applicable Airworthiness Directives for specific information.

5. General

A. Personnel Requirements

(1) Inspection, Repair, and Overhaul

(a) Compliance to the applicable regulatory requirements established by the Federal Aviation Administration

(FAA) or foreign equivalent is mandatory for anyone performing or accepting responsibility for any inspection and/or repair and/or overhaul of any Hartzell

Propeller Inc. product.

(b) Personnel performing maintenance on steel hub propellers are expected to have sufficient training and certifications (when required by the applicable Aviation

Authority) to accomplish the work required in a safe and airworthy manner.

B. Maintenance Practices

(1) The propeller and its components are highly vulnerable to damage while they are removed from the engine. Properly protect all components until they are reinstalled on the engine.

(2) Never attempt to move the aircraft by pulling on the propeller.

(3) Avoid the use of blade paddles. Do not place the blade paddle in the area of the de-ice boot when applying torque to a blade assembly. Place the blade paddle in the thickest area of the blade, just outside of the de-ice boot.

Use one blade paddle per blade.

(4) Use only the approved consumables, e.g., cleaning agents, lubricants, etc.

(5) Safe Handling of Paints and Chemicals

(a) Always use caution when handling or being exposed to paints and/or chemicals during propeller overhaul and maintenance procedures.

(b) Before using paint or chemicals, always read the manufacturer’s label on the container and follow specified instructions and procedures.

INTRODUCTION

61-00-39

Page 1-5

Rev. 12 Mar/13


139

(c) Refer to the product’s Material Safety Data Sheet

(MSDS) for detailed information about physical properties, health, and physical hazards of any chemical.

(6) Observe applicable torque values during maintenance.

(7) Before installing the propeller on the engine, the propeller must be statically balanced. New propellers are statically balanced at Hartzell Propeller Inc. Overhauled propellers must be statically balanced by a certified propeller repair station with the appropriate rating before return to service.

NOTE: Dynamic balance is recommended, but may be accomplished at the discretion of the operator, unless specifically required by the airframe or engine manufacturer. Dynamic balancing is to be accomplished in accordance with the procedures and limitations in

Maintenance Practices chapter of this manual.

Additional procedures may be found in the aircraft maintenance manual.

(8) As necessary, use a soft, non-graphite pencil or crayon to make identifying marks on components.

(9) As applicable, follow military standard NASMS33540 for safety wire, safety cable, and cotter pin general practices. Use 0.032 inch (0.81 mm) diameter stainless steel safety wire unless otherwise indicated.

61-00-39

Page 1-6

Rev. 13 Jun/15


139

WARNING: DO NOT USE OBSOLETE OR

OUTDATED INFORMATION. PERFORM

ALL INSPECTIONS OR WORK IN

ACCORDANCE WITH THE MOST

RECENT REVISION OF THIS MANUAL.

INFORMATION CONTAINED IN THIS

MANUAL MAY BE SIGNIFICANTLY

CHANGED FROM EARLIER REVISIONS.

FAILURE TO COMPLY WITH THIS

MANUAL OR THE USE OF OBSOLETE

INFORMATION MAY CREATE AN UNSAFE

CONDITION THAT MAY RESULT IN

DEATH, SERIOUS BODILY INJURY, AND/

OR SUBSTANTIAL PROPERTY DAMAGE.

FOR THE MOST RECENT REVISION

LEVEL OF THIS MANUAL, REFER TO THE

HARTZELL PROPELLER INC. WEBSITE AT

WWW.HARTZELLPROP.COM.

(10) The information in this manual revision supersedes data in all previous published revisions of this manual.

(11) The airframe manufacturer’s manuals should be used in addition to the information in this manual due to possible special requirements for specific aircraft applications.

(12) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller

Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the

Hartzell Propeller Inc. website at www.hartzellprop.com:

(a) Manual 180 (30-61-80) - Propeller Ice Protection

System Manual

(b) Manual 181 (30-60-81) - Propeller Ice Protection

System Component Maintenance Manual

(c) Manual 182 (61-12-82) - Propeller Electrical De-ice

Boot Removal and Installation Manual

(d) Manual 183 (61-12-83) - Propeller Anti-icing Boot

Removal and Installation Manual

INTRODUCTION

61-00-39

Page 1-7

Rev. 13 Jun/15


139

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

Airworthiness (ICA).

(14) Approved corrosion protection followed by approved paint must be applied to all aluminum blades. For information concerning the application of corrosion protection and paint, refer to the Maintenance Practices chapter of this manual. Operation of blades without the specified coatings and finishes, i.e., “polished blades”, is not permitted.

C. Continued Airworthiness

(1) Operators are urged to stay informed of Airworthiness information using Hartzell Propeller Inc. Service Bulletins and Service Letters that are available from Hartzell

Propeller Inc. distributors, or from the Hartzell Propeller

Inc. factory by subscription. Selected information is also available on the Hartzell Propeller Inc. website at www.hartzellprop.com.

D. Propeller Critical Parts

(1) The following maintenance procedures may involve propeller critical parts. 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. Refer to the Illustrated Parts List chapter of the applicable maintenance manual for the applicable propeller model for the identification of specific Critical

Parts.

(2) Numerous propeller system parts can produce a propeller Major or Hazardous effect, even though those parts may not be considered as Critical Parts. 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.

61-00-39

Page 1-8

Rev. 13 Jun/15


139

6. Reference Publications

A. Hartzell Propeller Inc. Publications

NOTE: The following publications are referenced within this manual:

Active Hartzell Propeller Inc. Service Bulletins, Service

Letters, Service Instructions, and Service Advisories.

Hartzell Propeller Inc. Manual No. 118F (61-10-18) - Three and Four-Blade Steel Hub Turbine Propeller Maintenance

Manual

Hartzell Propeller Inc. Manual No. 127 (61-16-27) - Metal

Spinner Assembly Maintenance Manual - Available on the

Hartzell Propeller Inc. website at www.hartzellprop.com

Hartzell Propeller Inc. Manual No. 132A (61-10-32) -

Five-Blade Steel Hub Turbine Propellers

Hartzell Propeller Inc. Manual No. 133C (61-13-33) -

Aluminum Propeller Blade Maintenance Manual

Hartzell Propeller Inc. Manual No. 159 (61-02-59) -

Application Guide - Available on the Hartzell Propeller Inc. website at www.hartzellprop.com

Hartzell Propeller Inc. Manual 165A (61-00-65) - Illustrated

Tool and Equipment Manual - Available on the Hartzell

Propeller Inc. website at www.hartzellprop.com

Hartzell Propeller Inc. Manual No. 180 (30-61-80) - Propeller

Ice Protection System Manual - Available on the Hartzell



Ice Protection System Component Maintenance Manual -

Available on the Hartzell Propeller Inc. website at www.hartzellprop.com


Electrical De-ice Boot Removal and Installation Manual -

Available on the Hartzell Propeller Inc. website at www.hartzellprop.com


Anti-icing Boot Removal and Installation Manual - Available on the Hartzell Propeller Inc. website at www.hartzellprop.com

INTRODUCTION

61-00-39

Page 1-9

Rev. 13 Jun/15


139

Hartzell Propeller Inc. Manual No. 202A (61-01-02) -

Standard Practices Manual, Volumes 1 through 11

(Volume 7, Consumable Materials is available on the Hartzell

Propeller Inc. website at www.hartzellprop.com)

Hartzell Propeller Inc. Service Letter HC-SL-61-61Y -

Overhaul Periods and Service Life Limits for Hartzell

Propellers Inc. Aviation Components - Propellers, Governors, and Propeller Damper Assemblies - Available on the Hartzell


7. Definitions

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

Annealed . . . . . . . . . . . Softening of material due to overexposure to heat

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

Brinelling . . . . . . . . . . . . A depression caused by failure of the material in compression

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

Cold Rolling . . . . . . . . . Compressive rolling process for the retention area of single shoulder blades 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

61-00-39

Page 1-10

Rev. 13 Jun/15


139

Corrosion . . . . . . . . . . . Gradual material removal or deterioration due to chemical action

Crack . . . . . . . . . . . . . . Irregularly shaped separation within a material, sometimes visible as a narrow opening at the surface

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

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

Erosion . . . . . . . . . . . . . Gradual wearing away or deterioration due to action of the elements

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

Feathering . . . . . . . . . . The capability of blades to be rotated parallel to the relative wind, thus reducing aerodynamic drag

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

Hazardous Propeller . . . The hazardous propeller effects

Effect are defined in Title 14 CFR 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 assembly strikes, or is struck by, an object while in flight or on the ground

Major Propeller Effect . . The major propeller effects are defined in Title 14 CFR section

35.15(g)(2)

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

INTRODUCTION

61-00-39

Page 1-11

Rev. 13 Jun/15


139

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

Overhaul . . . . . . . . . . . . The periodic disassembly, inspection, repair, refinish, and reassembly of a propeller assembly to maintain airworthiness

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 lever

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

Pitch . . . . . . . . . . . . . . . Same as “Blade Angle”

Pitting . . . . . . . . . . . . . . Formation of a number of small, irregularly shaped cavities in surface material caused by corrosion or wear

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

Reversing . . . . . . . . . . . The capability of rotating blades to a position to generate reverse thrust to slow the aircraft or back up

Scratch . . . . . . . . . . . . . Same as “Nick”

61-00-39

Page 1-12

Rev. 13 Jun/15


139

Single Acting . . . . . . . . . Hydraulically actuated propeller that utilizes a single oil supply for pitch control

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

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

Track . . . . . . . . . . . . . . . In an assembled propeller, a measurement of the location of the blade tip with respect to the plane of rotation, used to verify face alignment and to compare blade tip location with respect to the locations of the other blades in the assembly

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

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

Windmilling . . . . . . . . . . The rotation of an aircraft propeller caused by air flowing through it while the engine is not producing power

INTRODUCTION

61-00-39

Page 1-13

Rev. 13 Jun/15


139

8. Abbreviations

Abbreviation Term

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

AN . . . . . . . . . . . . . . . . . Air Force-Navy (or Army-Navy)

AOG . . . . . . . . . . . . . . . Aircraft on Ground

FAA . . . . . . . . . . . . . . . . Federal Aviation Administration

FT-Lb . . . . . . . . . . . . . . Foot-Pound

ICA . . . . . . . . . . . . . . . . Instructions for Continued

Airworthiness

ID . . . . . . . . . . . . . . . . . Inside Diameter

In-Lb . . . . . . . . . . . . . . . Inch-Pound

IPS . . . . . . . . . . . . . . . . Inches Per Second

Lbs . . . . . . . . . . . . . . . . Pounds

MIL-X-XXX . . . . . . . . . . Military Specification

MPI . . . . . . . . . . . . . . . . Major Periodic Inspection (Overhaul)

MS . . . . . . . . . . . . . . . . Military Standard

MSDS . . . . . . . . . . . . . . Material Safety Data Sheet

OD . . . . . . . . . . . . . . . . Outside Diameter

NAS . . . . . . . . . . . . . . . National Aerospace Standards

NASM . . . . . . . . . . . . . . National Aerospace Standards,

Military

N•m . . . . . . . . . . . . . . . . Newton-Meters

POH . . . . . . . . . . . . . . . Pilot’s Operating Handbook

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

RPM . . . . . . . . . . . . . . . Revolutions per Minute

TBO . . . . . . . . . . . . . . . Time Between Overhaul

TC . . . . . . . . . . . . . . . . . Type Certificate

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

TSO . . . . . . . . . . . . . . . Time Since Overhaul

NOTE: TSN/TSO is considered as the time accumulated between rotation and landing, i.e., flight time.

61-00-39

Page 1-14

INTRODUCTION


139

INSTALLATION AND REMOVAL - CONTENTS

1. Tools, Consumables, and Expendables .....................................3-3

A. Tooling ..................................................................................3-3

B. Consumables ........................................................................3-4

C. Expendables .........................................................................3-4

2. Pre-Installation ...........................................................................3-5

A. Inspection of Shipping Package ...........................................3-5

B. Uncrating ..............................................................................3-5

C. Inspection after Shipment .....................................................3-5

D. Reassembly of a Propeller Disassembled for Shipment .......3-5

3. Propeller Assembly Installation ..................................................3-6

A. Precautions ...........................................................................3-6

B. Installing HC-B(3, 5)( )( )-2( ) Propeller on the

Aircraft Engine ......................................................................3-7

C. Installing HC-B(3,4,5)( )(A,N,P)-3( ) Propeller on the

Aircraft Engine ....................................................................3-14

D. Installing HC-B(3,4)( )W-3( ) Propeller on the

Aircraft Engine ....................................................................3-20





G. Installing HC-( )3( )( )-7( ) Propeller on the

Allison Engine .....................................................................3-40

4. Spinner Dome Installation ........................................................3-50

5. Post-Installation Checks ...........................................................3-50

6. Spinner Dome Removal ...........................................................3-51

7. Propeller Assembly Removal ...................................................3-52

A. Removal of HC-B(3,5)( )( )-2( ) Propellers ..........................3-52

B. Removal of HC-B(3,4,5)( )(A,N,P)-3( ) Propellers ..............3-55

C. Removal of HC-B(3,4)( )W-3( ) Propellers ..........................3-59

D. Removal of HC-B(3,4,5)( )( )-5( ) Propellers .......................3-62

E. Removal of HC-( )3( )( )-7( ) Propellers ..............................3-65


HC-( )3( )( )-7( ) Propellers ................................................3-68

INSTALLATION AND REMOVAL

61-00-39

Page 3-1

Rev. 13 Jun/15


139

INSTALLATION AND REMOVAL - FIGURES

Mounting Bolt and Washer ............................. Figure 3-1 ..............3-9

Installing Propeller on Engine Flange ............. Figure 3-2 ............3-10

Diagram of Torquing Sequence for

Propeller Mounting Bolts .......................... Figure 3-3 ............3-11

Determining Torque Value When Using

Torquing Adaptor ...................................... Figure 3-4 ............3-13

Beta System Puller for Decompressing

-3 Series External Beta System ............... Figure 3-5 ............3-16

Carbon Block and Beta Ring Clearance ......... Figure 3-6 ............3-18

Carbon Block Assembly.................................. Figure 3-7 ............3-18

Hub-to-Spacer O-ring Location in the Spacer ............................................ Figure 3-8 ............3-22

Installing the HC-B(3,4)( )W-3( ) Propeller on the Engine Flange ............................... Figure 3-9 ............3-24

Installing the Washer on the Mounting Stud .. Figure 3-10 ...........3-26


Installation ............................................... Figure 3-11 ...........3-30

Beta Valve System ........................................ Figure 3-12 ...........3-38

Cross Section View of the Beta Valve

System .................................................... Figure 3-13 ...........3-39

-7( ) Propeller Assembly ................................ Figure 3-14 ...........3-42

Spring Assembly to Cylinder

Attachment Details .................................. Figure 3-15 ...........3-43

Piston to Link Arm Attachment Details........... Figure 3-16 ...........3-43

Filed Rod for Set Screw................................. Figure 3-17 ...........3-48

INSTALLATION AND REMOVAL - TABLES

Propeller/Engine Flange O-rings ..................... Table 3-1 ...............3-8

Propeller Mounting Hardware .......................... Table 3-2 ...............3-8

Torque Table .................................................... Table 3-3 .............3-12


61-00-39

Page 3-2

Rev. 13 Jun/15


139

1. Tools, Consumables, and Expendables

The following tools, consumables, and expendables will be required for propeller removal or installation:

A. Tooling

Each propeller model requires a calibrated torque wrench, safety wire pliers (alternate: safety cable tool), and the model specific tooling listed below:

HC-B3( )(A,N,P)-2( )

• Torque wrench adaptor (Hartzell Propeller Inc.

P/N AST-2877)

• 5/8 inch deep well socket

• 1-7/16 inch crowfoot wrench

HC-B(3,4,5)( )(A,N,P)-3( )


P/N AST-2877)



• Feeler gage

• Beta system puller (Hartzell Propeller Inc. P/N CST-2987)

HC-B(3,4)( )W-3( )


P/N AST-3175)

• Torque check tool (Hartzell Propeller Inc. P/N AST-2968-1)

• Feeler gage

• Beta system puller (Hartzell Propeller Inc. P/N CST-2987)



HC-B5M( )-2

HC-B(3,4,5)( )-5( )


P/N AST-2877)

• One inch deep well socket



61-00-39

Page 3-3

Rev. 13 Jun/15


139

HC-( )3( )F-7( )


P/N AST-2917)



B. Consumables

• Quick Dry Stoddard Solvent or Methyl-Ethyl-Ketone (MEK)

• Anti-Seize Compound (MIL-PRF-83483)

C. Expendables

• 0.032 inch (0.81 mm) Stainless Steel Aircraft Safety Wire

(Alternate: 0.032 inch [0.81 mm] aircraft safety cable and

associated hardware)

• O-ring, propeller flange (see Table 3-1)

• O-ring, for HC-B(3,4)( )W-3( ) spacer (see Table 3-1)


61-00-39

Page 3-4

Rev. 13 Jun/15


139

A Flange

W10107C

W10107B

W10108C

W10109C

W10109B

SEQUENCE A SEQUENCE B

Use Sequence A for steps one and two.

Use Sequence B for step three.

Step 1 - Torque all bolts to 40 ft-lbs (54 N•m). Step 3 - Torque all bolts to

Step 2 - Torque all bolts to 80 ft-lbs (108 N•m). Table 3-3.

F Flange

Step 1 - Torque all bolts to 40 ft-lbs (54 N•m).

Step 2 - Torque all bolts to Table 3-3.

N, P or W Flange

SEQUENCE A SEQUENCE B

Use Sequence A for steps one and two.

Use Sequence B for step three.

Step 1 - Torque all bolts to 40 ft-lbs (54 N•m). Step 3 - Torque all bolts to

Step 2 - Torque all bolts to 80 ft-lbs (108 N•m). Table 3-3.

Diagram of Torquing Sequence for Propeller Mounting Bolts

Figure 3-3


61-00-39

Page 3-11

Rev. 8 Dec/06


139

(7) Install the mounting bolts with washers through the engine flange and into the propeller hub flange. Refer to

Figure 3-2.

(8) Use a torque wrench and the specified torque wrench adaptor (see paragraph 1.A. Tooling in this chapter) to torque all mounting bolts in sequences and steps shown in Figure 3-3. Refer to Table 3-3 and Figure 3-4 to determine the proper torque value.

(9) Safety all mounting bolts with 0.032 inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two bolts per safety.)

CAUTION: TO FACILITATE BOXING AND SHIPPING

OF PROPELLERS, THE PISTON NUT

(A-880-1) ON HC-B3( )( )-2( ) STEEL HUB

TURBINE PROPELLERS MAY HAVE BEEN

REMOVED TO ALLOW ROTATING OF THE

BLADES BEFORE PACKAGING.

A flange mounting bolts

F flange mounting bolts

N/P flange mounting bolts

W flange mounting nuts

Spinner mounting bolts

Piston nut (lock nut)

Guide rod jam nuts

Lubrication Fitting

100-105 Ft-Lbs (136-142 N•m) wet

80-90 Ft-Lbs (108-122 N•m)

100-105 Ft-Lbs (136-142 N•m) wet

120-125 Ft-Lbs (163-170 N•m)

30-40 Ft-Lbs (41-54 N•m)

120 Ft-Lbs (163 N•m)*

10 Ft-Lbs (14 N•m)*

4 Ft-Lbs (5 N•m)*

Check Nut (beta valve assembly) 9-11 Ft-Lbs (12-15 N•m)

* Torque tolerance is ± 10 percent unless otherwise noted.

NOTE 1: Torque values are based on non-lubricated threads, unless otherwise specified.

NOTE 2: Wet torque values denote the use of anti-seize compound MIL-PRF-83483.

Torque Table

Table 3-3


61-00-39

Page 3-12

Rev. 13 Jun/15


139

CAUTION: ID CHAMFER OF THE WASHER MUST

BE FACING TOWARD THE BOLT HEAD.

WASHERS WITHOUT CHAMFER MUST

BE INSTALLED WITH ROLLED EDGES

TOWARD THE BOLT HEAD. (REFER TO

FIGURE 3-1).

(8) Install mounting bolts with washers through the engine flange and into the propeller hub flange. Refer to

Figure 3-2.


(10) Safety all mounting bolts with 0.032 inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two bolts per safety).

(11) Decompress the external beta system and remove the beta system puller.

CAUTION: THE BETA RING MUST NOT CONTACT ANY

ENGINE COMPONENT OR MOUNTING BOLT

SAFETY WIRE. THE BETA SYSTEM COULD

BE DAMAGED IF IT CONTACTS ANY STATIC

ENGINE COMPONENT WHILE ROTATING.

(12) Examine the beta ring to make sure that it is not in contact with any engine component or mounting bolt safety wire.

(a) If there is contact between the beta ring and any engine component or mounting bolt safety wire, consult qualified personnel at an appropriately licensed propeller repair facility.

(13) Install the carbon block into the beta linkage lever in accordance with the airframe manufacturer’s instructions.


61-00-39

Page 3-17

Rev. 13 Jun/15


139

Snap Ring

Carbon Block

Assembly

Side clearance 0.001 to 0.010 inch (0.03 to 0.25 mm) upon installation.

Beta Ring

Carbon Block and Beta Ring Clearance

Figure 3-6

Snap Ring

Yoke Unit

Cotter Pin

Beta Lever

Clevis Pin

Block Unit

Carbon Block Assembly

Figure 3-7


61-00-39

Page 3-18

Rev. 13 Jun/15


139

CAUTION 1: FIT THE BLOCK IN THE BETA RING WITH

A MINIMUM SIDE CLEARANCE OF 0.001

INCH (0.03 mm). REFER TO FIGURE 3-6.

CAUTION 2: MAXIMUM SIDE CLEARANCE

PERMITTED IS 0.010 INCH (0.25 mm)

IN ACCORDANCE WITH THE CARBON

BLOCK ASSEMBLIES SECTION IN THE

MAINTENANCE PRACTICES CHAPTER

OF THIS MANUAL.

(14) Install the carbon block assembly (Figure 3-7) into the beta ring.

(15) Install, adjust and safety the beta linkage per the airframe manufacturer’s instructions.



MAY HAVE BEEN REMOVED TO ALLOW

ROTATING OF THE BLADES BEFORE

PACKAGING.

(16) Procedure for reinstallation of piston nut, if applicable.

(a) Following the installation of the propeller, use a breaker bar and a 5/8 inch deep well socket to hold the pitch change rod.

(b) Using a 1-7/16 inch crowfoot wrench and torque wrench, torque the A-880-1 piston nut. Refer to

Table 3-3 and Figure 3-4 for the proper torque value.

NOTE: The removal and subsequent reinstallation of the piston nut does not require that the propeller blade angles be re-checked.

(17)If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller




System Manual


61-00-39

Page 3-19

Rev. 11 Jul/12


139









D. Installing HC-B(3,4)( )W-3( ) Propeller on the Aircraft Engine

CAUTION 1: INSTRUCTIONS AND PROCEDURES IN

THIS SECTION MAY INVOLVE CRITICAL

PARTS. REFER TO THE INTRODUCTION

CHAPTER OF THIS MANUAL FOR

INFORMATION ABOUT PROPELLER

CRITICAL PARTS. REFER TO THE

ILLUSTRATED PARTS LIST CHAPTER

OF THE APPLICABLE OVERHAUL

MANUAL(S) FOR THE IDENTIFICATION

OF SPECIFIC PROPELLER CRITICAL

PARTS.

CAUTION 2: WHEN INSTALLING THE

HC-B4TW-3/T10282N PROPELLER ON

THRUSH AIRCRAFT MODELS S2R-H80

OR S2RHG-H80, COMPLIANCE WITH

GE AVIATION SERVICE BULLETIN

H80-100-72-00019 IS REQUIRED.

(1) Use a beta system puller CST-2987 (Figure 3-5) to compress the beta system and pull the beta ring forward to allow access to the propeller mounting flange.


61-00-39

Page 3-20

Rev. 13 Jun/15


139

WARNING: MAKE SURE THE SLING IS RATED UP

TO 800 LBS (363 KG) TO SUPPORT THE

WEIGHT OF THE PROPELLER ASSEMBLY

DURING INSTALLATION.

CAUTION:

(2) With a suitable crane hoist and sling, carefully move the propeller assembly to the aircraft engine mounting flange.

CAUTION:

WHEN INSTALLING THE PROPELLER

ON THE AIRCRAFT, DO NOT DAMAGE

THE ICE PROTECTION SYSTEM

COMPONENTS, IF APPLICABLE.

IF THE PROPELLER IS REMOVED

BETWEEN OVERHAUL INTERVALS, A

TORQUE CHECK OF THE MOUNTING

STUDS MUST BE PERFORMED.

(3) Unless this is the first installation of a new, or newly overhauled propeller, perform a torque check of the propeller mounting studs as follows:

(a) Thread the torque check tool AST-2968-1 onto each propeller mounting stud and torque to 35 ft-lbs

(47.6 N•m).

(b) Visually inspect each stud for evidence of movement.

(c) Remove the torque check tool AST-2968-1 while visually inspecting each stud for evidence of movement.

(d) If any stud rotates due to either the tightening or removal of the torque check tool, all studs must be replaced. Refer to Hartzell Propeller Inc. Standard

Practices Manual 202A (ATA 61-01-02) for stud replacement procedures.

(4) Make sure the propeller hub flange and the engine flange mating surfaces are clean.

(5) Install the specified O-ring on the engine flange. Refer to

Table 3-1.

(6) If the C-7364-2 spacer is attached to the propeller hub with screws, proceed to step 3.D.(8).


61-00-39

Page 3-21

Rev. 13 Jun/15


139

(7) If the C-7364-2 spacer is not already installed on the propeller hub perform the following installation procedures:

(a) If the hub flange does not have two 8-32 threaded holes to attach the spacer or, if two attachment screws were not provided, perform the following steps:

1 Coat the hub-to-spacer O-ring with grease.

Refer to Table 3-1.

2 Install the hub-to-spacer O-ring in the groove in the spacer that interfaces with the face of the hub flange. Refer to Figure 3-8.

3 Align the mounting studs and dowel pin holes in the propeller hub flange with the mounting holes and dowel pins in the spacer.

W10409

W10410

Attachment screw hole

Dowel pin

Engine

Side

Dowel pin

O-ring groove

Propeller

Side

Engine

Side

Attachment screw hole

Dowel pin

Hub-to-Spacer O-ring Location in the Spacer

Figure 3-8

Dowel pin


61-00-39

Page 3-22

Rev. 13 Jun/15


139

CAUTION: MAKE SURE THE HUB-TO-SPACER

O-RING STAYS IN THE GROOVE

IN THE SPACER. IF THE O-RING

IS TWISTED OR PINCHED, OIL

LEAKAGE WILL RESULT WHEN

THE PROPELLER IS OPERATED

ON THE AIRCRAFT.

4 Slide the spacer onto the mounting studs and against the hub flange.

NOTE: If the propeller installation will be delayed, the spacer and O-ring should be installed and temporarily held in place with non-self locking nuts and a sufficient number of washers on at least two mounting studs. Remove the nuts and washers before installation.

(b) If the hub flange has two 8-32 threaded holes and two MS24693-S2 flat-head screws

(HPI P/N B-3868-S52) are provided to attach the

C-7364-2 spacer, perform the following steps:

1 Coat the hub-to-spacer O-ring with grease.

Refer to Table 3-1.

2 Install the hub-to-spacer O-ring in the groove in the spacer that interfaces with the face of the hub flange. Refer to Figure 3-8.

3 Align the spacer attachment holes with the two

8-32 threaded holes in the hub flange.

CAUTION: MAKE SURE THE HUB-TO-SPACER

O-RING STAYS IN THE GROOVE

IN THE SPACER. IF THE O-RING

IS TWISTED OR PINCHED, OIL

LEAKAGE WILL RESULT WHEN

THE PROPELLER IS OPERATED

ON THE AIRCRAFT.

4 Slide the spacer onto the mounting studs and against the hub flange.


61-00-39

Page 3-23

Rev. 13 Jun/15


139

APS6160C.TIF

E-7373i.PLT,

W10079

Torque Wrench

Washer

Hub-to-Engine

O-ring

Propeller

Flange

Hub-to-Spacer

O-ring

Torque Wrench

Adaptor*

Nut

Engine Flange

Screw

*Note: If torque wrench adaptor is used, use the calculation in Figure 3-4 to determine correct torque wrench setting.

W

Propeller Flange

Spinner Mounting Plate

Attachment Holes (10)

(Threaded)

Dowel Pin Holes (4)

(Unthreaded)

Mounting

Studs (8)

Spacer Attachment

Holes (2) (Threaded),

If Present

Installing the HC-B(3,4)( )W-3( ) Propeller on the Engine Flange

Figure 3-9


61-00-39

Page 3-24

Rev. 11 Jul/12


139

5 Insert supplied flat-head screw through each screw hole in the spacer and into the 8-32 threaded holes in the hub flange. Refer to

Figure 3-9.

CAUTION: MAKE SURE THE FLAT-HEAD

ATTACHMENT SCREWS DO NOT

PROTRUDE ABOVE THE ENGINE-

SIDE SURFACE OF THE SPACER.

6 Tighten the flat-head screw until snug.

7 If after the flat-head screws are tightened, one or both are protrude above the engine side surface of the spacer, perform the following steps: a Remove both flat-head screws and the spacer.

b Rotate the spacer 180 degrees, aligning the screw holes in the spacer with the 8-32 threaded holes in the hub flange.

CAUTION: MAKE SURE THE FLAT-HEAD

ATTACHMENT SCREWS DO NOT

PROTRUDE ABOVE THE ENGINE-

SIDE SURFACE OF THE SPACER.

c Slide the spacer onto the mounting studs and against the hub flange.

d Insert a flat-head screw through each screw hole in the spacer and into the 8-32 threaded holes in the hub flange. Refer to

Figure 3-9.

e Tighten the flat-head screw until snug.

f If after the flat-head screws are tightened, one or both are protrude above the engine side surface of the spacer, remove the screws.

NOTE: If the propeller installation will be delayed, the spacer and

O-ring should be installed and temporarily held in place with nonself locking nuts and a sufficient number of washers on at least two mounting studs. Remove the nuts and washers before installation.


61-00-39

Page 3-25

Rev. 11 Jul/12


139

CAUTION 1: MAKE SURE THAT COMPLETE AND TRUE

SURFACE CONTACT IS ESTABLISHED

BETWEEN THE SPACER AND THE

ENGINE FLANGE.

CAUTION 2: IF THE C-7364-2 SPACER IS NOT

ATTACHED TO THE HUB, MAKE SURE

THE HUB-TO-SPACER O-RING STAYS

IN THE GROOVE IN THE SPACER. IF

THE O-RING IS TWISTED OR PINCHED,

OIL LEAKAGE WILL RESULT WHEN THE

PROPELLER IS OPERATED ON THE

AIRCRAFT.

(8) Slide the propeller onto the engine flange.

Engine Flange

OD Chamfer

Washer

Stud

Engine Shaft

Fillet

Installing the Washer on the Mounting Stud

Figure 3-10


61-00-39

Page 3-26

Rev. 13 Jun/15


139

CAUTION 1: NEW PROPELLER MOUNTING NUTS

MUST BE USED WHEN INITIALLY

INSTALLING A NEW OR OVERHAULED

PROPELLER.

CAUTION 2: THE SIDE OF THE WASHER WITH THE

OD CHAMFER MUST BE AGAINST THE

ENGINE FLANGE. REFER TO FIGURE 3-10.

(9) Install self locking mounting nuts with washers onto the propeller mounting studs. Refer to Table 3-2 for appropriate mounting hardware. Refer to Figure 3-10.

NOTE 1: The OD chamfer on the washer is for clearance of the engine flange fillet. Refer to

Figure 3-10.

NOTE 2: If the propeller is removed between overhaul intervals, mounting nuts and washers may be reused if they are not damaged or corroded.

(10) Use a torque wrench and the specified torque wrench adaptor (see paragraph 1.A. Tooling in this chapter) to torque all mounting nuts in the sequences and steps shown in Figure 3-3. Refer to Table 3-3 and Figure 3-4 to determine the proper torque value.

(11) Safety all propeller mounting studs with 0.032 inch

(0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware

(two bolts per safety.)

(12) Decompress the external beta system and remove the beta system puller.

CAUTION: THE BETA RING MUST NOT CONTACT ANY

ENGINE COMPONENT OR MOUNTING BOLT

SAFETY WIRE. THE BETA SYSTEM COULD

BE DAMAGED IF IT CONTACTS ANY STATIC

ENGINE COMPONENT WHILE ROTATING.

(13) Examine the beta ring to make sure that it is not in contact with any engine components or mounting bolt safety wire.


61-00-39

Page 3-27

Rev. 13 Jun/15


139

(a) If there is contact between the beta ring and any engine components or mounting bolt safety wire, consult qualified personnel at an appropriately licensed propeller service facility.

(14) Install the carbon block into the beta linkage lever per the airframe manufacturer’s instructions.

CAUTION 1: FIT THE BLOCK IN THE BETA RING WITH

A SIDE CLEARANCE OF 0.001 INCH

(0.03 mm). REFER TO FIGURE 3-6.

CAUTION 2: MAXIMUM SIDE CLEARANCE

PERMITTED IS 0.010 INCH (0.25 mm)

IN ACCORDANCE WITH THE CARBON

BLOCK ASSEMBLIES SECTION IN THE

MAINTENANCE PRACTICES CHAPTER

OF THIS MANUAL.

(15) Install the carbon block assembly (Figure 3-7) into the beta ring.

(16) Install, adjust and safety the beta linkage per the airframe manufacturer’s instructions.


OF THE PROPELLER, THE PISTON NUT

MAY HAVE BEEN REMOVED TO ALLOW

ROTATING OF THE BLADES BEFORE

PACKAGING.

(17) Procedure for reinstallation of the piston nut, if applicable.

(a) Following the installation of the propeller, use a breaker bar and a 5/8 inch deep well socket to hold the pitch change rod.





61-00-39

Page 3-28

Rev. 13 Jun/15


139





System Manual










61-00-39

Page 3-29

Rev. 13 Jun/15


139

SPINNER MOUNTING PLA


PROPELLER HUB FLANGE


SPINNER BULKHEAD AND ST


61-00-39

Page 3-30

Rev. 11 Jul/12


139


Spinner Mounting Plate, on the Aircraft Engine

CAUTION: INSTRUCTIONS AND PROCEDURES IN










PARTS.

NOTE: Some -5 propellers were previously manufactured with a one-piece spinner mounting plate. The spinner bulkhead, which has start locks mounted on it, is attached to the spinner mounting plate.

The spinner mounting plate is installed in a cutaway portion of the propeller hub flange and is

“pinched” between the propeller hub flange and the engine flange. Refer to Figure 3-11.





CAUTION: WHEN INSTALLING THE PROPELLER





(2) Make sure the propeller hub flange and engine flange mating surfaces are clean.


Table 3-1.


61-00-39

Page 3-31

Rev. 13 Jun/15


139

(4) Retract each start lock pin and hold into place with a heavy wire inserted into the hole in each auto high pitch housing.

(5) Slide the assembled one-piece spinner mounting plate, spinner bulkhead and start lock onto the propeller hub flange.

(a) The start locks must face toward the propeller.

(6) Align the clearance “scallops” in the spinner mounting plate with the holes in the propeller hub flange. Refer to

Figure 3-11.

NOTE: This will insure that the spinner mounting plate does not interfere with the mounting bolts and dowel pins.

(7) Align the start locks with each blade and clamp mounted stop plate.

NOTE: The start locks are attached to the spinner bulkhead.

(8) Align mounting and dowel pin holes in the propeller hub flange with the mounting holes and dowel pins in the engine flange.

CAUTION: MAKE SURE THAT COMPLETE AND TRUE


BETWEEN THE PROPELLER HUB

FLANGE AND THE ENGINE FLANGE.

(9) Slide the propeller flange onto the engine flange.

CAUTION: NEW PROPELLER MOUNTING BOLTS



PROPELLER.

(10) Apply MIL-PRF-83483 anti-seize compound to the threaded surfaces of the mounting bolts. Refer to Table

3-2 for appropriate mounting hardware.

NOTE: If the propeller is removed between overhaul intervals, mounting bolts and washers may be reused if they are not damaged or corroded.


61-00-39

Page 3-32

Rev. 13 Jun/15


139





TOWARD THE BOLT HEAD (FIGURE 3-1).


Figure 3-2.



(14) Remove the heavy wire from the start lock housings to free the start lock pins.

(15) Refer to the airframe manufacturer’s instructions to seat the start lock plates on the start locks.

NOTE: The start lock plates interface with the start lock pins and are attached to the inboard surface of each blade clamp.



(A-880-2) ON -5 STEEL HUB TURBINE

PROPELLERS MAY HAVE BEEN




(a) Following the installation of the propeller, use a breaker bar and a one inch deep well socket to hold the pitch change rod.


61-00-39

Page 3-33

Rev. 13 Jun/15


139




(17) Install the beta tube per airframe and/or engine manufacturer’s instructions.

NOTE 1: Follow the airframe manufacturer’s instructions for adjusting the beta tube to obtain the correct low pitch (flight idle blade angle).

NOTE 2: Refer to the Aircraft Type Certificate Data

Sheet for the low pitch blade angle setting.





System Manual










61-00-39

Page 3-34

Rev. 13 Jun/15


139


Spinner Mounting Plate, on the Aircraft Engine











PARTS.

NOTE: Some -5 propellers are manufactured with a two-piece spinner mounting plate which is bolted on the propeller hub flange. On four and five-blade propellers (see Figure 2-7) the bulkhead and start locks are attached to the spinner mounting plate.

On three-bladed propellers (see Figure 2-6) the start locks are attached to the guide collar (between the hub and cylinder); although the bulkhead is attached to the spinner mounting plate.





CAUTION: WHEN INSTALLING THE PROPELLER





(a) If the propeller is equipped with a de-ice system, refer to the General Maintenance Practices section in the Introduction chapter of this manual.


61-00-39

Page 3-35

Rev. 13 Jun/15


139



Table 3-1.

(4) Align the mounting and dowel pin holes in the propeller hub flange with the mounting holes and dowel pins in the engine flange.





(5) Slide the propeller flange onto the engine flange.

CAUTION: NEW PROPELLER MOUNTING BOLTS



PROPELLER.

(6) Apply MIL-PRF-83483 anti-seize compound to the threaded surfaces of the mounting bolts. Refer to

Table 3-2 for appropriate mounting hardware.








Figure 3-2.

(8) Use a torque wrench and the specified torque wrench adaptor (see paragraph 1.A. Tooling) to torque all mounting bolts in sequences and steps shown in

Figure 3-3. Refer to Table 3-3 and Figure 3-4 to determine the proper torque value.


61-00-39

Page 3-36

Rev. 13 Jun/15


139




(A-880-2) ON -5 STEEL HUB TURBINE

PROPELLERS MAY HAVE BEEN




(a) Following the installation of the propeller, use a breaker bar and a one inch deep well socket to hold the pitch change rod.




(11) Install the beta tube per airframe and/or engine manufacturer’s instructions.

(a) Follow the airframe manufacturer’s instructions for adjusting the beta tube to obtain the correct low pitch

(flight idle blade angle).

(b) Refer to the Aircraft Type Certificate Data Sheet for the low pitch blade angle setting.





System Manual




61-00-39

Page 3-37

Rev. 13 Jun/15


139

ROD END CAP

ROD END FITTING

PUSH ROD SPOOL

COVER PLA

O-RINGS (SUPPLIED BY

ENGINE SHAFT ADAPT

SPRING RET

PITCH CHANGE ROD

SELF LOCKING NUT


61-00-39

Page 3-38

Rev. 13 Jun/15


139

SPRING RET

OUTER SPRING

INNER SPRING

PUSH ROD SPOOL

COVER PLA

ROD END FITTING

ROD END CAP

C-3317-006 O-RING


61-00-39

Page 3-39

Rev. 13 Jun/15


139







G. Installing HC-( )3( )( )-7( ) Propeller on the Allison Engine











PARTS.

This propeller incorporates a beta valve assembly

(Figures 3-12 and 3-13), which is installed inside of the propeller shaft and extends from the rear of the engine to the front of the propeller piston. This assembly is installed in the engine shaft before the propeller is installed.

(1) Make sure that the shaft adaptor (see Figure 3-13) is installed in the engine shaft.

(2) Install the C-3317-116 O-rings in the two grooves

(see Figure 3-13) of the shaft adaptor.

(3) Remove the cover plate from the rear of engine case.

Refer to Figures 3-12 and 3-13.

(4) Prepare the beta valve.

NOTE: The beta valve should be preassembled as shown in Figure 3-12 less the pitch change rod, engine shaft adaptor, engine supplied o-rings and cover plate when new or from overhaul.


61-00-39

Page 3-40

Rev. 13 Jun/15


139

Refer to Figures 3-12 and 3-13.

(a) If the beta valve is supplied preassembled, remove the self locking nut, spacer, rod end cap, rod end fitting, bushing and check nut.

(b) If the beta valve is supplied disassembled, assemble as follows:

1 Slide the push rod spool onto the pin and into the sleeve with the threaded end facing away from the sleeve.

2 Slide the inner and outer springs onto the rod up to and against the shoulder of the sleeve.

3 Install the spring retainer onto the rod with the recessed center section facing toward the two springs.

(5) Slide the partially assembled beta valve into the engine shaft from the front, allowing the push rod spool to extend out the rear of the engine.

(a) The shoulder of the sleeve should be against the shaft adaptor.

(6) Compress the springs with spring retainer and install the retaining ring that is furnished with the engine to secure the spring retainer.

NOTE: A locator button on the spring retainer will fit into a recess in the engine shaft/flange.

(7) Install the ID and OD O-rings on the engine cover, per the airframe or engine manufacturer’s instructions.

(8) Install the engine cover on the rear of the engine gear box encircling the beta valve push rod spool, per airframe or engine manufacturer’s instructions.

NOTE: Cover plate fasteners are supplied by the engine manufacturer.


61-00-39

Page 3-41

Rev. 13 Jun/15

SPRING ASSEMBL


139

SELF LOCKING NUT

PITCH CHANGE ROD


61-00-39

Page 3-42

Rev. 13 Jun/15

W10139

W10136


139

SPRING

RETAINER

RING RETENTION

PLATE

SPLIT

RETAINER

RING RETENTION

PLATE SCREW

CYLINDER

Spring Assembly to Cylinder Attachment Details

Figure 3-15

W10137

PISTON

LINK PIN UNIT

SAFETY SCREW

PISTON SLOT

SAFETY WIRE

LINK ARM

Piston to Link Arm Attachment Details

Figure 3-16


61-00-39

Page 3-43

Rev. 13 Jun/15


139

(9) Prepare the propeller for installation (see Figures 3-14 through 3-16 ).

(a) Piston removal

1 Remove the flexlock nut with a 1-7/16 inch wrench, if installed.

2 Remove the safety wire from the three link pin units.

3 Remove the safety screws from the link pin units.

4 Remove the link pin units.

5 Mark the piston and link pins with a felt tip pen or equivalent, so the piston can be reinstalled in the same position.

6 Slide the link arms out of the piston slots.

7 Remove the socket head cap screw, jam nut, and washer from each piston guide rod.

8 Slide the piston off the cylinder.

(b) Spring assembly removal.

1 Remove the ring retention plate screw safety wire.

2 Remove the ring retention plate screws.

3 Remove the retention plate.

4 Remove the split retainer.

5 Remove the spring assembly from the cylinder.


61-00-39

Page 3-44

Rev. 13 Jun/15


139




DURING REMOVAL.

CAUTION: INSERT THE DOWEL PINS INTO

THE PROPELLER FLANGE USING A

BRASS HAMMER OR EQUIVALENT

TOOL TO PREVENT DAMAGE TO THE

DOWEL PINS. THE DOWEL PINS ARE

AN INTERFERENCE FIT WITH THE

PROPELLER FLANGE.

(10) Insert two dowel pins (Table 3-1) through the threadless holes in the propeller flange, flush with the propeller side of the hub flange. The dowel pins will protrude from the engine side of the hub flange to engage the engine flange.


NOTE: If the propeller is equipped with a de-ice system, refer to the General Maintenance

Practices section in the Introduction chapter of this manual.



Table 3-1.

CAUTION: DO NOT ALLOW THE PROPELLER

ASSEMBLY TO HIT OR REST ON THE

BETA FEEDBACK ROD. THIS COULD

BEND OR OTHERWISE DAMAGE THE

FEEDBACK ROD.

(14) Slide the propeller over the beta valve assembly.

(15) Align the mounting holes and dowel pins in the propeller hub flange with the mounting holes and dowel pin holes in the engine flange.


61-00-39

Page 3-45

Rev. 13 Jun/15


139





(16) Slide the propeller hub flange onto the engine flange.

CAUTION 1: ID CHAMFER OF THE WASHER MUST





CAUTION 2: NEW PROPELLER MOUNTING BOLTS



PROPELLER.

(17) Install the propeller mounting bolts and washers through the engine flange and into the propeller hub flange.

Refer to Table 3-2 for appropriate mounting hardware.


(18)Use a torque wrench and the specified torque wrench adaptor (see paragraph 1.A. Tooling in this chapter) to torque all mounting bolts in sequences and steps shown in Figure 3-3. Refer to Table 3-3 and Figure 3-4 to determine the proper torque value.


(20) Reinstall the spring assembly (see Figures 3-14 and

3-15).

(a) Slide the spring assembly into the cylinder and around the beta valve rod.

(b) Install split retainer between the cylinder and front spring retainer. Slide retainer into the recess in the cylinder.


61-00-39

Page 3-46

Rev. 13 Jun/15


139

(c) Pull the spring retainer tight against the split retainer.

(d) Install the ring retention plate.

(e) Install the ring retention plate screws and tighten until snug.

(f) Safety screws with 0.032 inch (0.81 mm) minimum diameter stainless steel safety wire or equivalent aircraft safety cable and associated hardware (two bolts per safety.)

(21) Install the C-3317-012-2 O-ring in the front inside cavity of the pitch change rod. (See Figure 3-14.)

(22) Reinstall the piston on the cylinder and pitch change rod in the same position it was before disassembly. Refer to

Figures 3-14 and 3-16.

(a) Reconnect the link arms to the piston.

(b) Install the link pin units.

(c) Install the link pin unit safety screws.

(d) Safety the link pin screws with 0.032 inch (0.81 mm) minimum diameter stainless steel safety wire (see

Figure 3-16).

(e) Hand tighten the A-880-1 piston nut on the pitch change rod.

(f) Position a breaker bar and a 5/8 inch deep well socket on the pitch change rod.

(g) Use 1-7/16 inch crowfoot wrench and torque wrench to torque the A-880-1 piston nut. Refer to Table 3-3 and Figure 3-4 for the proper torque value.


(h) Install a socket head screw, washer and jam nut onto each piston guide rod. Refer to Figure 3-14.

(i) Torque the jam nuts on the piston guide rods as indicated in Table 3-3.


61-00-39

Page 3-47

Rev. 13 Jun/15

W10138


139

CAUTION: THE ROD END CAP MUST BOTTOM

ON THE PUSH ROD SPOOL WHEN

INSTALLED.

(23) Install the rod end cap onto the threaded end of the push rod spool.

NOTE: Do not tighten the set screw in the rod end cap.

(a) Mark the location of the set screw on the rod and then remove the end cap unit.

(b) File a flat, tangent to the rod, no deeper than the depth of the threads at the marked location of the set screw. Refer to Figure 3-17.

(24) Install the check nut onto the threaded end of the push rod spool.

(25) Install the bushing onto the threaded end of the push rod spool.

(26)Install the rod end fitting onto the threaded end of the push rod spool.

(27) Install the C-3317-006 O-ring in the cavity at the rear end of the push rod spool.

FILED FLAT

PUSH ROD SPOOL

Filed Rod for Set Screw

Figure 3-17


61-00-39

Page 3-48

Rev. 13 Jun/15


139

(28) Install the rod end cap onto the threaded end of the push rod spool.

NOTE: Make sure the rod end cap is bottomed on the end of the push rod spool.

(a) Apply Loctite

®

272 to the set screw threads.

(b) Tighten the set screw.

(29) Apply Loctite

®

272 to the push rod threads where the check nut will be located on the push rod spool next to the bushing.

(30) Tighten the check nut against the bushing to torque indicated in Table 3-3.

(31) Attach engine mounted beta system control hardware to rod end fitting and adjust per airframe or engine manufacturer’s instructions.

(32) Install the beta light switch against the pin per airframe manufacturer’s instructions.

(33) Install the spacer and self-locking nut onto the front of the rod that protrudes through the front of the pitch change rod and piston.

(a) Follow the airframe manufacturer’s instructions for making pitch control adjustments.





System Manual








61-00-39

Page 3-49

Rev. 13 Jun/15


139



4. Spinner Dome Installation

CAUTION 1: INSTRUCTIONS AND PROCEDURES IN THIS

SECTION MAY INVOLVE CRITICAL PARTS.

REFER TO THE INTRODUCTION CHAPTER

OF THIS MANUAL FOR INFORMATION ABOUT

PROPELLER CRITICAL PARTS. REFER TO

THE ILLUSTRATED PARTS LIST CHAPTER

OF THE APPLICABLE OVERHAUL MANUAL(S)

FOR THE IDENTIFICATION OF SPECIFIC

PROPELLER CRITICAL PARTS.

CAUTION 2: TO PREVENT DAMAGE TO THE BLADE AND

BLADE PAINT, WRAP THE BLADE SHANKS IN

SEVERAL LAYERS OF MASKING OR DUCT

TAPE BEFORE INSTALLING THE SPINNER

DOME. REMOVE THE TAPE AFTER THE

SPINNER IS INSTALLED.

CAUTION 3: SPINNER DOME WILL WOBBLE IF NOT

ALIGNED PROPERLY, AND MAY AFFECT

DYNAMIC BALANCE OF PROPELLER.

A. Carefully slide the spinner dome over the reassembled propeller.

B. Secure the spinner dome to the spinner bulkhead with the supplied screws and washers.

5. Post-Installation Checks

A. Refer to the airframe manufacturer’s instructions for

post-installation checks.

B. Perform a maximum RPM (Static) hydraulic low pitch stop check in accordance with the Testing and Troubleshooting chapter of this manual.


61-00-39

Page 3-50

Rev. 13 Jun/15


139

6. Spinner Dome Removal

CAUTION 1: INSTRUCTIONS AND PROCEDURES IN THIS









CAUTION 2: TO PREVENT DAMAGING THE BLADE AND

BLADE PAINT, WRAP THE BLADE SHANKS IN

SEVERAL LAYERS OF MASKING OR DUCT

TAPE BEFORE REMOVING THE SPINNER

DOME.

A. Remove the screws and washers that secure the spinner to the spinner bulkhead.

B. Remove the spinner dome.


61-00-39

Page 3-51

Rev. 13 Jun/15


139

7. Propeller Assembly Removal

A. Removal of HC-B(3,5)( )( )-2( ) Propellers

WARNING: FOR SAFETY REASONS, THE

PROPELLER MUST BE PUT IN FEATHER

POSITION BEFORE IT IS REMOVED

FROM THE AIRCRAFT.











PARTS.

(1) Remove the spinner dome in accordance with the procedure in the Spinner Dome Removal section of this chapter.

(a) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell

Propeller Inc., applicable instructions and technical information for the components supplied by

Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at www.hartzellprop.com:

1 Manual 180 (30-61-80) - Propeller Ice Protection

System Manual



3 Manual 182 (61-12-82) - Propeller Electrical

De-ice Boot Removal and Installation Manual

4 Manual 183 (61-12-83) - Propeller Anti-icing



61-00-39

Page 3-52

Rev. 13 Jun/15


139

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

Continued Airworthiness (ICA).

WARNING 1: DURING ENGINE INSTALLATION OR

REMOVAL, USING THE PROPELLER TO

SUPPORT THE WEIGHT OF THE ENGINE

IS NOT AUTHORIZED. UNAPPROVED

INSTALLATION AND REMOVAL

TECHNIQUES MAY CAUSE DAMAGE TO

THE PROPELLER THAT MAY LEAD TO

FAILURE AND RESULT IN AN AIRCRAFT

ACCIDENT.

WARNING 2: DURING PROPELLER REMOVAL,

AIRFRAME MANUFACTURER’S

MANUALS AND PROCEDURES MUST

BE FOLLOWED BECAUSE THEY MAY

CONTAIN ISSUES VITAL TO AIRCRAFT

SAFETY THAT ARE NOT CONTAINED

IN THIS MANUAL OR THE HARTZELL

PROPELLER INC. OVERHAUL MANUALS

118F (61-10-18) AND 132A (61-10-32).

WARNING 3: MAKE SURE THE SLING IS RATED UP



DURING REMOVAL.

(2) Cut and remove the safety wire on the propeller mounting bolts.


61-00-39

Page 3-53

Rev. 13 Jun/15


139

(3) Support the propeller assembly with a sling.

NOTE 1: Supporting the propeller with the sling may be delayed until all but two mounting bolts and washers have been removed to allow rotating the propeller for ease of bolt removal.

NOTE 2: If the propeller will be reinstalled, and it has been dynamically balanced, make an identifying mark on the propeller hub and a matching mark on the engine flange to ensure proper orientation during re-installation to prevent dynamic imbalance.

CAUTION:

(4) Remove the propeller mounting bolts and washers.


CAUTION:

DISCARD THE PROPELLER MOUNTING

BOLTS IF THEY ARE DAMAGED OR

CORRODED, OR WHEN THE PROPELLER

IS REMOVED FOR OVERHAUL.

USE ADEQUATE PRECAUTIONS TO

PROTECT THE PROPELLER ASSEMBLY

FROM DAMAGE WHEN IT IS REMOVED

FROM THE AIRCRAFT ENGINE AND

WHEN IT IS STORED.

(5) Using the support sling, lift the propeller from the mounting flange.

(6) Remove and discard the propeller mounting O-ring.

(7) Place the propeller on a suitable cart for transportation.


61-00-39

Page 3-54

Rev. 13 Jun/15


139

B. Removal of HC-B(3,4,5)( )(A,N,P)-3( ) Propellers




FROM THE AIRCRAFT, IF THE BLADES

ARE AT A STARTING BLADE ANGLE DUE

TO START LOCKS.











PARTS.






System Manual








61-00-39

Page 3-55

Rev. 13 Jun/15


139



(2) Disconnect the engine beta linkage and carbon block assembly from the beta ring per the airframe manufacturer’s instructions. Refer to Figure 3-7.

(a) If the carbon block must be removed, perform the following procedures:

1 Remove the snap ring that retains the carbon block assembly to the beta linkage.

2 Remove the carbon block assembly.

CAUTION: MAKE SURE THAT THE BETA

LINKAGE IS DISCONNECTED BEFORE

COMPRESSING THE BETA SYSTEM.

(3) Use the beta system puller, Hartzell Propeller Inc.

P/N CST-2987, to compress the beta system and pull the beta ring forward to expose the propeller mounting bolts and washers. Refer to Figure 3-5.


61-00-39

Page 3-56

Rev. 13 Jun/15


139









ACCIDENT.









118F (61-10-18) AND 132A (61-10-32).




DURING REMOVAL.






61-00-39

Page 3-57

Rev. 13 Jun/15


139

CAUTION:



CAUTION:









WHEN IT IS STORED.



(9) Decompress and remove the beta system puller.



61-00-39

Page 3-58

Rev. 13 Jun/15


139

C. Removal of HC-B(3,4)( )W-3( ) Propellers











PARTS.






System Manual









(2) Disconnect the engine beta linkage and carbon block assembly from the beta ring per the airframe manufacturer’s instructions. Refer to Figure 3-7.


61-00-39

Page 3-59

Rev. 13 Jun/15


139

(a) If the carbon block must be removed, perform the following procedures:

1 Remove the snap ring that retains the carbon block assembly to the beta linkage.

2 Remove the carbon block assembly.

CAUTION: MAKE SURE THAT THE BETA

LINKAGE IS DISCONNECTED BEFORE

COMPRESSING THE BETA SYSTEM.

(3) Use the beta system puller, Hartzell Propeller Inc.

P/N CST-2987, to compress the beta system and pull the beta ring forward to expose the propeller mounting nuts and washers. Refer to Figure 3-5.









ACCIDENT.









118F (61-10-18) AND 132A (61-10-32).




DURING REMOVAL.

(4) Cut and remove the safety wire on the propeller mounting studs.


61-00-39

Page 3-60

Rev. 13 Jun/15


139


NOTE 1: Supporting the propeller with the sling may be delayed until all but two mounting nuts and washers have been removed to allow rotating the propeller for ease of nut removal.


CAUTION:

(6) Remove the propeller mounting nuts and washers.

NOTE: If the propeller is removed between overhaul intervals, mounting nuts and washers may be reused if they are not damaged or corroded.

CAUTION:


NUTS AND/OR WASHERS IF THEY ARE

DAMAGED OR CORRODED, OR WHEN

THE PROPELLER IS REMOVED FOR

OVERHAUL.





WHEN IT IS STORED.


(8) Remove and discard the engine flange-to-spacer O-ring.

(9) If the C-7364-2 spacer is not attached with flat-head screws, perform the following procedures:

(a) Remove the spacer from the hub.

(b) Remove and discard the hub-to-spacer O-ring.

(10) If the C-7364-2 spacer is attached to the hub with flathead screws, perform the following procedures if the

O-ring must be replaced due to oil leakage.

(a) Remove the spacer attachment screws, if applicable.


61-00-39

Page 3-61

Rev. 13 Jun/15


139

(b) Remove the C-7364-2 spacer.

(c) Remove and discard the propeller hub-to-spacer

O-ring.

(11) Decompress and remove the beta system puller.


D. Removal of HC-B(3,4,5)( )( )-5( ) Propellers




FROM THE AIRCRAFT.











PARTS.






System Manual






61-00-39

Page 3-62

Rev. 13 Jun/15


139





CAUTION: THE BETA TUBE MUST BE REMOVED

BEFORE THE PROPELLER ASSEMBLY IS

REMOVED FROM THE AIRCRAFT. REFER

TO THE AIRCRAFT MAINTENANCE

INSTRUCTION MANUAL.

(2) Remove the beta tube.









ACCIDENT.









118F (61-10-18) AND 132A (61-10-32).




DURING REMOVAL.



61-00-39

Page 3-63

Rev. 13 Jun/15


139




CAUTION:



CAUTION:









WHEN IT IS STORED.


(7) If the propeller has a two-piece spinner mounting plate, proceed to paragraph 9.C.(9).

(8) Propellers with the one-piece spinner mounting plate only (refer to Figure 3-11):

(a) Remove the spinner mounting plate, spinner bulkhead and start locks, as a unit, from the propeller hub flange.

(9) Remove and discard propeller mounting O-ring.



61-00-39

Page 3-64

Rev. 13 Jun/15


139

E. Removal of HC-( )3( )( )-7( ) Propellers











PARTS.

NOTE: Refer to Figures 3-12 through 3-16 for the Beta

Valve System.






System Manual










61-00-39

Page 3-65

Rev. 13 Jun/15


139

(2) Remove the self-locking nut and spacer from the beta system rod that protrudes from the pitch change rod and piston.

(3) Prepare the propeller for removal (see Figures 3-14 through 3-16).

(a) Piston Removal

1 Remove the flexlock nut with Hartzell Propeller

Inc. P/N AST-2917 or a 1 7/16 inch wrench, if installed.

2 Remove the safety wire from the three link pin units.

3 Remove the safety screws from the link pin units.

4 Remove the link pin units.

5 Mark the piston and link pins with a felt tip pen or equivalent, so the piston can be reinstalled in the same position.

6 Slide the link arms out of the piston slots.

7 Remove the socket head cap screw, jam nut, and washer from each piston guide rod.

8 Slide the piston off the cylinder.

(b) Spring assembly removal.

1 Remove the ring retention plate screw safety wire.

2 Remove the ring retention plate screws.

3 Remove the retention plate.

4 Remove the split retainer.

5 Remove the spring assembly from the cylinder.


61-00-39

Page 3-66

Rev. 13 Jun/15


139









ACCIDENT.









118F (61-10-18) AND 132A (61-10-32).




DURING REMOVAL.






61-00-39

Page 3-67

Rev. 13 Jun/15


139

CAUTION: DISCARD THE PROPELLER MOUNTING






CAUTION 1: DO NOT ALLOW THE PROPELLER

ASSEMBLY TO HIT OR REST ON THE

BETA FEEDBACK ROD. THIS COULD

BEND OR OTHERWISE DAMAGE THE

ROD.

CAUTION 2: USE ADEQUATE PRECAUTIONS TO




WHEN IT IS STORED.





HC-( )3( )( )-7( ) Propellers

(1) Remove the beta light switch from the beta valve pin per airframe manufacturer’s instructions.

(2) Remove the engine mounted beta system control hardware from the beta valve rod end fitting, per the airframe/engine manufacturer’s instructions.

(3) Loosen the check nut on the push rod spool from the bushing to break the Loctite

®

bond.

(4) Loosen the set screw to clear the threads of the push rod spool and to allow removal of the rod end cap.

(5) Loosen the rod end cap to break the Loctite

®

bond and remove the rod end cap from the push rod spool.


61-00-39

Page 3-68

Rev. 13 Jun/15


139

(6) Remove the rod end fitting from the push rod spool.

(7) Remove the bushing from the push rod spool.

(8) Remove the check nut from the push rod spool.

(9) Remove the O-ring from the cavity at the rear of the threaded end of the push rod spool.

(10) Remove the engine cover from the rear of the engine gear box encircling the beta valve push rod spool per the airframe or engine manufacturer’s instructions.

(11) Remove and discard the ID and OD O-rings from the engine cover.

WARNING: TO AVOID INJURY, SPRINGS IN THE

ENGINE SHAFT ARE PRELOADED AND

MUST BE PROPERLY CONTROLLED

WHEN RELEASING THE SPRING

RETAINER.

(12) Secure the spring retainer and remove the retaining ring that holds the spring retainer in place.

(13) Remove the spring retainer from the engine shaft and beta valve.

(14) Remove the inner and outer springs from the engine shaft and beta valve.

(15) Slide the beta valve’s remaining assembly and push rod spool out of the engine shaft toward where the propeller had been mounted.

(16) Place all beta valve parts together, including the self locking nut and spacer that were removed to allow the removal of the propeller assembly.


61-00-39

Page 3-69

Rev. 13 Jun/15


139

(This page is intentionally blank.)


61-00-39

Page 3-70

Rev. 13 Jun/15


139

Percent Overtorque -- Turbine Engines Only

INSPECTION AND CHECK

61-00-39

Page 5-23

Rev. 13 Jun/15


139

B. Propeller Ground Idle Operating Restrictions

WARNING: STABILIZED GROUND OPERATION

WITHIN THE PROPELLER RESTRICTED

RPM RANGE CAN GENERATE

HIGH PROPELLER STRESSES AND

RESULT IN FATIGUE DAMAGE TO THE

PROPELLER. THIS DAMAGE CAN LEAD

TO A REDUCED PROPELLER FATIGUE

LIFE, PROPELLER FAILURE, AND LOSS

OF CONTROL OF THE AIRCRAFT. THE

PROPELLER RESTRICTED RPM RANGE

IS DEFINED IN THE AIRPLANE FLIGHT

MANUAL.

(1) General

(a) The information in this section applies only to the four and five bladed propeller models that are addressed in this manual.

(b) The information in this section is intended to emphasize the critical importance of correct propeller ground idle RPM on certain turboprop installations.

It also defines the appropriate corrective action required when a propeller has been operated within this restricted RPM region.

(c) If the propeller is operated within a restricted RPM range or below a minimum idle RPM restriction for an extended period of time, the propeller blades and hub can become unairworthy because of fatigue.

A failed blade or hub has the potential to cause a catastrophic blade separation.

(d) Four, five and six blade propellers operating on turbine engines can be sensitive to operation within restricted RPM ranges. These restricted ranges are usually in the lower RPM ranges, requiring that ground idle RPM be set above a critical minimum value.

INSPECTION AND CHECK

61-00-39

Page 5-24

Rev. 11 Jul/12


139

3. Carbon Block Assemblies

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS









A. Inspection

The clearance between the yoke pin and the corresponding linkage (beta lever bushing) can become too close due to a buildup of plating and foreign particles between the two pieces. This can cause a binding action, resulting in excessive wear to the carbon block, beta ring, and beta linkage.

(1) Inspect the beta lever and carbon block interface for free movement. If there is binding, do the following:

(a) Disconnect the beta linkage and remove the carbon block assemblies from the beta ring.

(b) Using an abrasive pad, lightly polish the yoke pin to provide adequate clearance and eliminate binding.

(c) Reinstall the carbon block assembly into the beta ring.

(d) Install, adjust and safety the beta linkage per the airframe manufacturer's instructions.

B. Replacement of A-3026 Carbon Block Unit in the A-3044

Carbon Block Assembly

Replace an A-3026 carbon block unit if the side clearance between the beta ring and carbon block exceeds 0.010 inch

(0.25 mm).

(1) Remove the cotter pin from the end of the clevis pin.

(2) Slide the pin from the assembly and remove and discard the carbon block unit.

(3) Inspect the yoke for wear or cracks. Replace the yoke if necessary.

MAINTENANCE PRACTICES

61-00-39

Page 6-9

Rev. 13 Jun/15


139

(4) Install a new carbon block unit and slide a new clevis pin into place.

(5) Secure the clevis pin with a T-head cotter pin

(Figure 3-7).

(6) Refit the carbon block (Figure 3-6).

(a) Establish the required clearance by sanding the sides of the carbon block as needed.

C. Installation of the A-3044 Carbon Block Assembly

Refer to Installation and Removal Chapter of this manual for installation instructions.

MAINTENANCE PRACTICES

61-00-39

Page 6-10

Rev. 11 Jul/12

Hartzell HC-B3 ( )( )-2( ), ( )( )-3( ), TF-7( ), ( )( )-5( ), HC-B4 ( )( )-3( ), ( )( )-5( ), HC-B5M ( )-2( ), ( )-3( ), ( )-5( ), HC-A3 (V,MV)F-7( ) Propeller Manual

Assistant Bot

Propeller Owner's Manual

and Logbook

Key Features

Frequently Answers and Questions

What types of aircraft can these propellers be used on?

How often does the propeller need to be overhauled?

What are the airworthiness limitations for these propellers?

What type of maintenance procedures are required for these propellers?

What are the requirements for personnel performing propeller maintenance?

What documents are referenced in this manual?

Related manuals

Hartzell HC-B3 ( )( )-2( ), ( )( )-3( ), TF-7( ), ( )( )-5( ), HC-B4 ( )( )-3( ), ( )( )-5( ), HC-B5M ( )-2( ), ( )-3( ), ( )-5( ), HC-A3 (V,MV)F-7( ) Propeller Manual

Assistant Bot

Propeller Owner's Manual

and Logbook

Key Features

Frequently Answers and Questions

What types of aircraft can these propellers be used on?

How often does the propeller need to be overhauled?

What are the airworthiness limitations for these propellers?

What type of maintenance procedures are required for these propellers?

What are the requirements for personnel performing propeller maintenance?

What documents are referenced in this manual?

Related manuals

Beta

2250-O

Hartzell

HC-A2 (B)HC-A2(MV,V)(F,K,L)-1

Hartzell

HC-D3MV20 8D

Hartzell

Propeller De-ice Boot

Hartzell

HC-D3MV20-6L Series

Hartzell

N-shank NG8301

Cirrus

SR20

Hartzell

Propeller Ice Protection System

Cirrus

SR20

Hartzell

HC-E5A-31 Series

Hartzell Propeller

HC-A3 (V,MV)F-7

Hartzell Propeller

Propeller