aluminum blade overhaul manual - hartzell propeller · 2020. 12. 21. · hartzell propeller inc....

Hartzell Propeller Inc.One Propeller PlacePiqua, Ohio 45356-2634 U.S.A.Phone: 937.778.4200Fax: 937.778.4215

Manual No. 133C61-13-33Revision 39March 2020

ALUMINUM BLADEOVERHAUL MANUAL

61-13-33 Inside CoverRev. 39 Mar/20

ALUMINUM BLADE MANUAL 133C

© 1996, 1997, 1998, 1999, 2000, 2001, 2003, 2004, 2005, 2007, 2008, 2009, 2011, 2012, 2013, 2014, 2015, 2016, 2017, 2018, 2019, 2020 - Hartzell Propeller Inc. - All rights reserved

REVISION HIGHLIGHTS 61-13-33 Page 1Rev. 39 Mar/20

ALUMINUM BLADE OVERHAUL 133C

REVISION 39 HIGHLIGHTS

Revision 39, dated March 2020, 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.

• BLADE SHANK OVERHAUL• Revisedthesection,“CounterweightDisassembly”• Revisedthesection,“CounterweightInstallation”

• ILLUSTRATED PARTS LIST• RevisedtheBladeShankPartsListfor“D”and“E”Shank

• APPENDIX C• IncorporatedTR-094thataddedFigure11-35.2,“BladeModel8429BladeTip”and thetableforblademodel8429• RevisedFigure11-65.1title,“BladeModel9510(S)BladeTip”• Revisedthetable,“9510(S)Blade”• Addedthetable,“9782(S)Blade”toAppendixC-BladeSpecifications• Addedthetable,“9901Blade”toAppendixC-BladeSpecifications• IncorporatedTR-093thatrevisedthetableforblademodel10703(S)

• APPENDIX E• RevisedFigure13-12,“HMI”• Revisedthesection,“BasicMachineOperation”• Removedthesection,“FunctionalCheckWithoutBladeInstalled”• Revisedthesection,“RoutineMaintenanceandChecks”• Revisedthesection,“ProgramSelectionProcedure”• Revisedthesection,“RollingProcessoftheDT-1724-5RollingMachine”



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REVISIONS ISSUED

IntroductionA. 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 the revision.(3) Comments indicates the level of the revision.

1 New Issue is a new manual distribution. The manual is distributed in its entirety.Allthepagerevisiondatesarethesameandnochangebarsareused.

2 Reissueisarevisiontoanexistingmanualthatincludesmajorcontentand/ormajorformatchanges.Themanualisdistributedinitsentirety.Allthe page revision dates are the same and no change bars are used.

3 MajorRevisionisarevisiontoanexistingmanualthatincludesmajorcontent or minor format changes over a large portion of the manual. The manualisdistributedinitsentirety.Allthepagerevisiondatesarethesame, but change bars are used to indicate the changes incorporated in the latest revision of the manual.

4 MinorRevisionisarevisiontoanexistingmanualthatincludesminorcontentchangestothemanual.Onlytherevisedpagesofthemanualaredistributed. Each page retains the date and the change bars associated with the last revision to that page.

Revision No. Issue Date Comments Rev.22 Jun/07 ManualReissue Rev.23 Mar/08 MinorRevision Rev.24 Nov/08 MinorRevision Rev.25 Apr/09 MinorRevision Rev.26 Oct/09 MinorRevision Rev.27 Sep/11 MinorRevision Rev.28 Sep/12 MinorRevision Rev. 29 Nov/12 Minor Revision Rev. 30 Apr/13 Minor Revision Rev.31 Jul/14 MinorRevision Rev.32 Nov/15 MinorRevision Rev.33 Jun/16 MinorRevision

REVISION HIGHLIGHTS 61-13-33 Page4Rev. 39 Mar/20


REVISIONS ISSUED, CONTINUED Revision No. Issue Date Comments Rev.34 Jan/17 MinorRevision Rev.35 Nov/17 MinorRevision Rev.36 Jun/18 MinorRevision Rev.37 Dec/18 MinorRevision Rev.38 Apr/19 MinorRevision Rev. 39 Mar/20 Minor Revision


RECORD OF REVISIONS

This is a permanent historical record of revisions inserted into this manual. Revision 22 includes all prior revisions, up to and including Revision 21.

RECORD OF REVISIONS 61-13-33 Page 1Rev. 22 Jun/07

Revision Number

Issue Date

Date Inserted

Inserted By

22 Jun/07 Jun/07 HPI

23 Mar/08 Mar/08 HPI

24 Nov/08 Nov/08 HPI

25 Apr/09 Apr/09 HPI

26 Oct/09 Oct/09 HPI

27 Sep/11 Sep/11 HPI

28 Sep/12 Sep/12 HPI



31 Jul/14 Jul/14 HPI


33 Jul/16 Jul/16 HPI

34 Jan/17 Jan/17 HPI


36 Jun/18 Jun/18 HPI

37 Dec/18 Dec/18 HPI


39 Mar/20 Mar/20 HPI

Revision Number

Issue Date

Date Inserted

Inserted By


RECORD OF REVISIONS

This is a permanent historical record of revisions inserted into this manual. Revision 22 includes all prior revisions, up to and including Revision 21.

RECORD OF REVISIONS 61-13-33 Page 2Rev. 22 Jun/07

Revision Number

Issue Date

Date Inserted

Inserted By

Revision Number

Issue Date

Date Inserted

Inserted By


RECORD OF TEMPORARY REVISIONS Update this page to show all temporary revisions inserted into this manual.

Revision 27 includes all prior temporary revisions, up to and including TR-071.

RECORD OF TEMPORARY REVISIONS 61-13-33 Page 1Rev. 27 Sep/11

TemporaryRevision No.

Section/Page

IssueDate

InsertedBy

DateRemoved

RemovedBy

TR-072 2-24 Nov/11 HPI Sep/12 HPI

TR-073 3-52 Nov/11 HPI Sep/12 HPI

TR-074 1-151 Dec/11 HPI Sep/12 HPI

TR-075 11-84 Jun/13 HPI Jul/14 HPI

TR-076 3-40 Jun/13 HPI Oct/13 HPI

TR-077 3-40 Oct/13 HPI Jul/14 HPI



TR-080 11-134 Mar/14 HPI Apr/14 HPI

TR-081 11-260 Mar/14 HPI Jul/14 HPI

TR-082 11-134 Apr/14 HPI Jul/14 HPI

TR-083 3-25 Aug/14 HPI Nov/15 HPI

TR-084 11-82.2 Mar/15 HPI Nov/15 HPI

TR-085 2-152 Apr/15 HPI Nov/15 HPI

TR-086 11-16 Jan/16 HPI Jan/17 HPI

TR-087 7-4 Feb/16 HPI Jan/17 HPI

TR-090 2-89 Apr/17 HPI Nov/17 HPI

TR-091 11-267 Mar/18 HPI Jun/18 HPI

TR-092 11-94 Aug/18 HPI Dec/18 HPI

TR-093 11-258.4 May/19 HPI Mar/20 HPI

TR-094 11-95 May/19 HPI Mar/20 HPI

TR-095 9-3 Dec/20 HPI

RECORD OF TEMPORARY REVISIONS

Update this page to show all temporary revisions inserted into this manual. Revision 27 includes all prior temporary revisions, up to and including TR-071.

RECORD OF TEMPORARY REVISIONS 61-13-33 Page 2Rev. 27 Sep/11


TemporaryRevision No.

Section/Page

IssueDate

DateInserted

InsertedBy

DateRemoved

RemovedBy


Page 1Rev. 35 Nov/1761-13-33SERVICE DOCUMENT LIST

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.LEVEL OF THE SERVICE DOCUMENT.

Service Document Number

IncorporationRev./Date

Service Bulletins:SB118D Rev. 1 Feb/97SB131D Rev. 1 Feb/97SB136I Rev. 14 Apr/03SB146B Rev. 1 Feb/97SB154A Rev. 1 Feb/97SB178 Rev. 1 Feb/97HC-SB-61-252, R2 Rev. 29, Nov/12HC-SB-61-301 Rev. 23, Mar/08HC-SB-61-304, R1 Rev. 29, Nov/12



Service Letters:HC-SL-61-180 Rev. 4 Feb/99HC-SL-61-204 Rev. 8 Aug/00HC-SL-61-232 Rev. 27 Sep/11

HC-SL-61-245 Rev. 23 Mar/08HC-SL-30-295, R2 Rev. 27 Sep/11HC-SL-61-241 Rev. 35 Nov/17

Service Advisories:

SA75 Rev. 1 Feb/97


Page 2Rev. 35 Nov/1761-13-33SERVICE DOCUMENT LIST

SERVICE DOCUMENT LIST





AIRWORTHINESS LIMITATIONSPage 1

Rev. 27 Sep/1161-13-33

ALUMINUM BLADE MANUAL133C

AIRWORTHINESS LIMITATIONS

1. Certaincomponentparts,aswellastheentirepropeller,mayhavespecificlifelimitsestablished by the FAA. Such limits requirereplacementofitemsafteraspecificnumberofhoursofuse.

2. Forairworthinesslimitationsinformation,refertotheapplicableHartzellPropellerOwner'smanualorHartzellOverhaulmanual.

AIRWORTHINESS LIMITATIONSPage 2

Rev. 27 Sep/1161-13-33


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LIST OF EFFECTIVE PAGESPage 1

Rev. 39 Mar/2061-13-33

Chapter Page Revision Level Date

LIST OF EFFECTIVE PAGES

Cover Cover and Inside Cover Rev. 39 Mar/20Revision Highlights 1 thru 4 Rev. 39 Mar/20Record of Revisions 1 and 2 Rev. 22 Jun/07Record of Temporary Revisions 1 and 2 Rev. 27 Sep/11Service Document List 1 and 2 Rev. 35 Nov/17Airworthiness Limitations 1 and 2 Rev. 27 Sep/11List of Effective Pages 1 thru 6 Rev. 39 Mar/20Table of Contents 1 and 2 Rev. 37 Dec/18Introduction 1 thru 22 Rev. 37 Dec/18Description and Operation 1-1 and 1-2 Rev. 35 Nov/17Description and Operation 1-3 Rev. 28 Sep/12Description and Operation 1-4 Rev. 30 Apr/13Description and Operation 1-5 Rev. 37 Dec/18Description and Operation 1-6 Rev. 28 Sep/12Description and Operation 1-7 thru 1-10 Rev. 27 Sep/11Blade Shank Overhaul 2-1 Rev. 38 Apr/19Blade Shank Overhaul 2-2 Rev. 35 Nov/17Blade Shank Overhaul 2-3 and 2-4 Rev. 38 Apr/19Blade Shank Overhaul 2-5 and 2-6 Rev. 23 Mar/08Blade Shank Overhaul 2-7 Rev. 27 Sep/11Blade Shank Overhaul 2-8 Rev. 31 Jul/14Blade Shank Overhaul 2-9 Rev. 27 Sep/11Blade Shank Overhaul 2-10 and 2-11 Rev. 23 Mar/08Blade Shank Overhaul 2-12 Rev. 31 Jul/14Blade Shank Overhaul 2-13 Rev. 23 Mar/08Blade Shank Overhaul 2-14 and 2-15 Rev. 24 Nov/08Blade Shank Overhaul 2-16 and 2-17 Rev. 27 Sep/11Blade Shank Overhaul 2-18 thru 2-23 Rev. 23 Mar/08Blade Shank Overhaul 2-24 Rev. 34 Jan/17Blade Shank Overhaul 2-25 Rev. 32 Nov/15Blade Shank Overhaul 2-26 thru 2-28 Rev. 28 Sep/12Blade Shank Overhaul 2-29 thru 2-36 Rev. 23 Mar/08Blade Shank Overhaul 2-37 thru 2-39 Rev. 25 Apr/09Blade Shank Overhaul 2-40 thru 2-59 Rev. 23 Mar/08Blade Shank Overhaul 2-60 Rev. 27 Sep/11Blade Shank Overhaul 2-61 thru 2-72 Rev. 23 Mar/08Blade Shank Overhaul 2-73 Rev. 27 Sep/11Blade Shank Overhaul 2-74 Rev. 23 Mar/08Blade Shank Overhaul 2-75 Rev. 35 Nov/17



Rev. 39 Mar/2061-13-33



Blade Shank Overhaul 2-76 Rev. 34 Jan/17Blade Shank Overhaul 2-76.1 and 2.76.2 Rev. 34 Jan/17Blade Shank Overhaul 2-77 Rev. 34 Jan/17Blade Shank Overhaul 2-78 and 2-79 Rev. 29 Nov/12Blade Shank Overhaul 2-80 and 2-81 Rev. 32 Nov/15Blade Shank Overhaul 2-82 and 2-83 Rev. 23 Mar/08Blade Shank Overhaul 2-84 Rev. 25 Apr/09Blade Shank Overhaul 2-85 thru 2-87 Rev. 35 Nov/17Blade Shank Overhaul 2-88 Rev. 24 Nov/08Blade Shank Overhaul 2-89 Rev. 35 Nov/17Blade Shank Overhaul 2-90 Rev. 31 Jul/14Blade Shank Overhaul 2-90.1 and 2-90.2 Rev. 31 Jul/14Blade Shank Overhaul 2-91 and 2-92 Rev. 31 Jul/14Blade Shank Overhaul 2-93 Rev. 24 Nov/08Blade Shank Overhaul 2-94 thru 2-101 Rev. 23 Mar/08Blade Shank Overhaul 2-102 thru 2-104 Rev. 27 Sep/11Blade Shank Overhaul 2-105 Rev. 23 Mar/08Blade Shank Overhaul 2-106 Rev. 27 Sep/11Blade Shank Overhaul 2-107 thru 2-128 Rev. 23 Mar/08Blade Shank Overhaul 2-129 Rev. 28 Sep/12Blade Shank Overhaul 2-130 Rev. 25 Apr/09Blade Shank Overhaul 2-131 thru 2-134 Rev. 23 Mar/08Blade Shank Overhaul 2-135 Rev. 25 Apr/09Blade Shank Overhaul 2-136 Rev. 23 Mar/08Blade Shank Overhaul 2-137 and 2-138 Rev. 27 Sep/11Blade Shank Overhaul 2-139 Rev. 32 Nov/15Blade Shank Overhaul 2-140 Rev. 39 Mar/20Blade Shank Overhaul 2-141 and 2-142 Rev. 23 Mar/08Blade Shank Overhaul 2-143 Rev. 27 Sep/11Blade Shank Overhaul 2-144 Rev. 23 Mar/08Blade Shank Overhaul 2-145 thru 2-149 Rev. 27 Sep/11Blade Shank Overhaul 2-150 Rev. 23 Mar/08Blade Shank Overhaul 2-151 Rev. 35 Nov/17Blade Shank Overhaul 2-152 and 2-153 Rev. 39 Mar/20Blade Shank Overhaul 2-154 thru 2-158 Rev. 35 Nov/17Blade Shank Overhaul 2-159 thru 2-170 Rev. 39 Mar/20Blade Shank Overhaul 2-170.1 and 2-170.2 Rev. 39 Mar/20Blade Shank Overhaul 2-170.3 and 2-170.4 Rev. 38 Apr/19Blade Shank Overhaul 2-171 Rev. 37 Dec/18



Rev. 39 Mar/2061-13-33



Blade Shank Overhaul 2-172 thru 2-176 Rev. 35 Nov/17Blade Shank Overhaul 2-177 thru 2-184 Rev. 37 Dec/18Blade Airfoil Overhaul 3-1 and 3-2 Rev. 35 Nov/17Blade Airfoil Overhaul 3-3 Rev. 28 Sep/12Blade Airfoil Overhaul 3-4 thru 3-9 Rev. 27 Sep/11Blade Airfoil Overhaul 3-10 Rev. 23 Mar/08Blade Airfoil Overhaul 3-11 Rev. 28 Sep/12Blade Airfoil Overhaul 3-12 and 3-13 Rev. 23 Mar/08Blade Airfoil Overhaul 3-14 Rev. 28 Sep/12Blade Airfoil Overhaul 3-15 Rev. 29 Nov/12Blade Airfoil Overhaul 3-16 Rev. 35 Nov/17Blade Airfoil Overhaul 3-17 and 3-18 Rev. 27 Sep/11Blade Airfoil Overhaul 3-19 thru 3-35 Rev. 35 Nov/17Blade Airfoil Overhaul 3-36 Rev. 28 Sep/12Blade Airfoil Overhaul 3-37 Rev. 23 Mar/08Blade Airfoil Overhaul 3-38 Rev. 35 Nov/17Blade Airfoil Overhaul 3-39 and 3-40 Rev. 34 Jan/17Blade Airfoil Overhaul 3-41 Rev. 32 Nov/15Blade Airfoil Overhaul 3-42 thru 3-47 Rev. 35 Nov/17Blade Airfoil Overhaul 3-48 Rev. 32 Nov/15Blade Airfoil Overhaul 3-49 thru 3-54 Rev. 35 Nov/17Special Inspections and Procedures 4-1 and 4-2 Rev. 28 Sep/12Special Inspections and Procedures 4-3 Rev. 29 Nov/12Special Inspections and Procedures 4-4 Rev. 35 Nov/17Special Inspections and Procedures 4-5 Rev. 28 Sep/12Special Inspections and Procedures 4-6 Rev. 37 Dec/18Special Inspections and Procedures 4-7 Rev. 28 Sep/12Special Inspections and Procedures 4-8 and 4-9 Rev. 37 Dec/18Special Inspections and Procedures 4-10 thru 4-12 Rev. 28 Sep/12Special Inspections and Procedures 4-13 and 4-14 Rev. 22 Jun/07Special Inspections and Procedures 4-15 thru 4-19 Rev. 28 Sep/12Special Inspections and Procedures 4-20 Rev. 32 Nov/15Special Inspections and Procedures 4-21 and 4-22 Rev. 28 Sep/12Special Inspections and Procedures 4-23 Rev. 23 Mar/08Special Inspections and Procedures 4-24 and 4-25 Rev. 28 Sep/12Special Inspections and Procedures 4-26 Rev. 34 Jan/17Special Inspections and Procedures 4-27 Rev. 28 Sep/12Special Inspections and Procedures 4-28 and 4-29 Rev. 22 Jun/07Special Inspections and Procedures 4-30 Rev. 28 Sep/12



Rev. 39 Mar/2061-13-33



Special Inspections and Procedures 4-31 Rev. 35 Nov/17Special Inspections and Procedures 4-32 Rev. 32 Nov/15Special Inspections and Procedures 4-33 and 4-34 Rev. 28 Sep/12Special Inspections and Procedures 4-35 and 4-36 Rev. 31 Jul/14Special Inspections and Procedures 4-37 Rev. 28 Sep/12Special Inspections and Procedures 4-38 Rev. 29 Nov/12Finish 5-1 Rev. 28 Sep/12Finish 5-2 Rev. 27 Sep/11Finish 5-3 Rev. 28 Sep/12Finish 5-4 Rev. 23 Mar/08Finish 5-5 and 5-6 Rev. 28 Sep/12Finish 5-7 and 5-8 Rev. 23 Mar/08Finish 5-9 thru 5-12 Rev. 28 Sep/12De-ice Boot 6-1 and 6-2 Rev. 37 Dec/18Blade Balancing 7-1 and 7-2 Rev. 22 Jun/07Blade Balancing 7-3 Rev. 28 Sep/12Blade Balancing 7-4 Rev. 34 Jan/17Blade Balancing 7-5 and 7-6 Rev. 22 Jun/07Blade Balancing 7-7 and 7-8 Rev. 28 Sep/12Illustrated Parts List 8-1 and 8-2 Rev. 35 Nov/17Illustrated Parts List 8-3 and 8-4 Rev. 28 Sep/12Illustrated Parts List 8-5 Rev. 23 Mar/08Illustrated Parts List 8-6 Rev. 28 Sep/12Illustrated Parts List 8-7 thru 8-10 Rev. 23 Mar/08Illustrated Parts List 8-11 thru 8-14 Rev. 27 Sep/11Illustrated Parts List 8-15 Rev. 28 Sep/12Illustrated Parts List 8-16 Rev. 29 Nov/12Illustrated Parts List 8-17 Rev. 39 Mar/20Illustrated Parts List 8-18 thru 8-25 Rev. 23 Mar/08Illustrated Parts List 8-26 thru 8-28 Rev. 27 Sep/11Illustrated Parts List 8-29 and 8-30 Rev. 35 Nov/17Appendix A - Optical Comparator 9-1 thru 9-8 Rev. 35 Nov/17Appendix B - Travelers 10-1 thru 10-14 Rev. 37 Dec/18Appendix C - Blade Specification Tables 11-1 Rev. 35 Nov/17Appendix C - Blade Specification Tables 11-2 thru 11-9 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-10 and 11-11 Rev. 35 Nov/17Appendix C - Blade Specification Tables 11-12 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-13 thru 11-15 Rev. 28 Sep/12Appendix C - Blade Specification Tables 11-16 Rev. 34 Jan/17



Rev. 39 Mar/2061-13-33



Appendix C - Blade Specification Tables 11-17 thru 11-33 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-34 and 11-35 Rev. 34 Jan/17Appendix C - Blade Specification Tables 11-36 thru 11-63 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-36 thru 11-60 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-61 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-62 and 11-63 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-64 Rev. 28 Sep/12Appendix C - Blade Specification Tables 11-65 thru 11-76 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-77 Rev. 34 Jan/17Appendix C - Blade Specification Tables 11-78 thru 11-82 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-82.1 Rev. 31 Jul/14Appendix C - Blade Specification Tables 11-82.2 Rev. 32 Nov/15Appendix C - Blade Specification Tables 11-83 Rev. 32 Nov/15Appendix C - Blade Specification Tables 11-84 thru 11-92 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-92.1 and 11-92.2 Rev. 37 Dec/18Appendix C - Blade Specification Tables 11-92.3 and 11-92.4 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-93 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-94 thru 11-119 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-120 Rev. 34 Jan/17Appendix C - Blade Specification Tables 11-121 thru 11-123 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-124 Rev. 36 Jun/18Appendix C - Blade Specification Tables 11-125 Rev. 37 Dec/18Appendix C - Blade Specification Tables 11-126 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-127 Rev. 34 Jan/17Appendix C - Blade Specification Tables 11-128 thru 11-132 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-132.1 and 11-132.2 Rev. 31 Jul/14Appendix C - Blade Specification Tables 11-133 Rev. 31 Jul/14Appendix C - Blade Specification Tables 11-134 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-135 Rev. 31 Jul/14Appendix C - Blade Specification Tables 11-136 thru 11-161 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-162 and 11-163 Rev. 37 Dec/18Appendix C - Blade Specification Tables 11-164 thru 11-168 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-168.1 Rev. 31 Jul/14Appendix C - Blade Specification Tables 11-168.2 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-169 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-170 and 11-171 Rev. 29 Nov/12Appendix C - Blade Specification Tables 11-172 Rev. 30 Apr/13Appendix C - Blade Specification Tables 11-172.1 Rev. 34 Jan/17Appendix C - Blade Specification Tables 11-172.2 Rev. 29 Nov/12



Rev. 39 Mar/2061-13-33



Appendix C - Blade Specification Tables 11-173 Rev. 29 Nov/12Appendix C - Blade Specification Tables 11-174 thru 11-178 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-178.1 and 11-178.2 Rev. 30 Apr/13Appendix C - Blade Specification Tables 11-179 Rev. 30 Apr/13Appendix C - Blade Specification Tables 11-180 thru 11-182 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-182.1 and 11-182.2 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-183 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-184 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-184.1 and 11-184.2 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-185 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-186 thru 11-225 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-226 Rev. 30 Apr/13Appendix C - Blade Specification Tables 11-227 thru 11-233 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-234 and 11-235 Rev. 31 Jul/14Appendix C - Blade Specification Tables 11-236 thru 11-252 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-252.1 and 11-252.2 Rev. 32 Nov/15Appendix C - Blade Specification Tables 11-253 Rev. 32 Nov/15Appendix C - Blade Specification Tables 11-254 thru 11-256 Rev. 27 Sep/14Appendix C - Blade Specification Tables 11-257 Rev. 28 Sep/12Appendix C - Blade Specification Tables 11-258 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-258.1 and 11-258.2 Rev. 31 Jul/14Appendix C - Blade Specification Tables 11-258.3 Rev. 35 Nov/17Appendix C - Blade Specification Tables 11-258.4 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-259 Rev. 39 Mar/20Appendix C - Blade Specification Tables 11-260 thru 11-266 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-266.1 and 11-266.2 Rev. 36 Jun/18Appendix C - Blade Specification Tables 11-267 Rev. 36 Jun/18Appendix C - Blade Specification Tables 11-268 Rev. 27 Sep/11Appendix C - Blade Specification Tables 11-269 Rev. 36 Jun/18Appendix C - Blade Specification Tables 11-270 thru 11-278 Rev. 27 Sep/11Appendix D - Blade Tip Specifications 12-1 and 12-2 Rev. 27 Sep/11Appendix E - Rolling Machine 13-1 Rev. 39 Mar/20Appendix E - Rolling Machine 13-2 thru 13-30 Rev. 36 Jun/18Appendix E - Rolling Machine 13-31 Rev. 39 Mar/20Appendix E - Rolling Machine 13-32 and 13-33 Rev. 36 Jun/18Appendix E - Rolling Machine 13-34 thru 13-44 Rev. 39 Mar/20

TABLE OF CONTENTS


Page 1Rev. 37 Dec/1861-13-33

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 .......................................................................................1-1

Blade Shank Overhaul .............................................................................................2-1

Blade Airfoil Overhaul...............................................................................................3-1

Special Inspections and Procedures ........................................................................4-1

Finish........................................................................................................................5-1

De-Ice Boot ..............................................................................................................6-1

De-ice and anti-icing boot instructions have been relocated to the Hartzell Propeller Inc. Propeller Ice Protection System Manual 180 (30-61-80).

Blade Balancing .......................................................................................................7-1

Illustrated Parts List..................................................................................................8-1

Appendix A - Optical Comparator .............................................................................9-1

Appendix B - Travelers ...........................................................................................10-1

Appendix C - Blade Specification Tables ...............................................................11-1

Appendix D - Blade Tip Specifications ...................................................................12-1

Appendix E - Rolling Machine ................................................................................13-1

TABLE OF CONTENTS


Page 2Rev. 37 Dec/1861-13-33



INTRODUCTIONPage 1

Rev. 37 Dec/1861-13-33

INTRODUCTION - CONTENTS

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

A. General.............................................................................................................3

2. Reference Publications ..........................................................................................5

A. Hartzell Propeller Inc. Publications...................................................................5

B. References Contained in Hartzell Propeller Inc. Publications ..........................6

C. Vendor Publications..........................................................................................6

3. Personnel Requirements .......................................................................................6

A. Inspection, Repair, and Overhaul .....................................................................6

4. Safe Handling of Paints and Chemicals ................................................................7

5. Minimum Facility and Tooling Requirements .........................................................7

A. Tooling ..............................................................................................................7

B. Facilities ...........................................................................................................8

6. Component Life and Service .................................................................................8

A. Overhaul ...........................................................................................................8

B. Damage ............................................................................................................9

C. Repair ...............................................................................................................9

D. Life Limits .........................................................................................................9

E. Time in Service .................................................................................................9

F. Propeller Critical Parts....................................................................................10

G. Long Term Storage .........................................................................................10

7. Definitions ............................................................................................................ 11

8. Abbreviations .......................................................................................................19

9. Dimensions ..........................................................................................................20

10. Contact Information .............................................................................................21

A. Hartzell Propeller Inc. Product Support Department ......................................21

B. Hartzell Propeller Inc. Technical Publications Department .............................21


INTRODUCTIONPage 2

Rev. 37 Dec/1861-13-33



INTRODUCTIONPage 3

Rev. 37 Dec/1861-13-33

1. Statement of Purpose

A. General

(1) This manual has been reviewed and accepted by the FAA. Additionally, this manual contains data that has been approved in a manner acceptable to the FAA Administrator.

(2) This manual provides inspection, repair, and overhaul procedures for all aluminum propeller blades manufactured by Hartzell Propeller Inc. This manual assumes that the blade has been removed from the propeller assembly unless specifiedotherwise.

(3) This manual is not arranged sequentially in the steps of the overhaul process.

(a) The suggested sequence of required overhaul procedures is provided in a "traveler", but differing blade conditions as well as individual repair station requirements may dictate a need for variation in the sequence of blade overhaul.

(b) Although the sequence of events is not mandatory and may be rearranged tofitindividualrepair statiion requirements, it is essential that all steps of the overhaul process be completed during overhaul as applicable.

(4) This manual is to be used by propeller repair stations with personnel who are trained and experienced with Hartzell Propeller Inc. products.

(a) This manual does not provide complete information for an inexperienced technician to attempt aluminum blade overhaul without supervision.

(5) This manual is intended to be the primary source for aluminum blade repair and overhaul information.

(a) ThepropellermodelsaddressedinthismanualmaybeTypeCertificatedby the FAA, or may be experimental. Experimental parts must not be installedonatypecertifiedpropeller.Alwaysusethecurrentillustratedparts list for the assembly of any propeller. Always refer to the aircraft Type Certificate(TC)orSupplementalTypeCertificates(STC)todetermineinstallation eligibility of any propeller. If installation eligibility is not identifiable,anadditionalinstallationapproval,suchasFAAform337fieldapprovalorSupplementalTypeCertificatemayberequired.Ifindoubt,contact Hartzell Propeller Inc. Product Support.

(6) This manual is not a "stand alone" document. The applicable propeller manual must be consulted for information relating to the entire propeller assembly.

(7) This manual makes reference to other Hartzell Propeller Inc. manuals that provide important details for procedures such as anodizing, penetrant inspection, etc.

(8) Wherepossible,thismanualiswrittenintheformatspecifiedby ATA iSpec 2200.


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Rev. 37 Dec/1861-13-33

CAUTION: 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.

(9) The information in this manual revision supersedes data in all previously published revisions of this manual.


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Rev. 37 Dec/1861-13-33

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 forinformationregardingspecificrecommendationsandprocedurestomaintainpropeller assemblies that are included in this manual.

Manual No. (ATA No.)

Available at www.hartzellprop.com Title

n/a Yes Active Hartzell Propeller Inc. Service Bulletins, Service Letters, Service Instructions, and Service Advisories

Manual 128(61-00-28)

--- Hartzell Propeller Inc. Blade Shank Rolling Machine Maintenance Manual

Manual 159(61-02-59)

Yes Hartzell Propeller Inc. Application Guide

Manual 165A (61-00-65)

Yes Hartzell Propeller Inc. Illustrated Tool and Equipment Manual

Manual 180 (30-61-80)

Yes Hartzell Propeller Inc. Propeller Ice Protection System Manual

Manual 202A (61-01-02)

Vol. 7, Yes Hartzell Propeller Inc. Standard Practices Manual, Volumes 1 through 11


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Rev. 37 Dec/1861-13-33

B. References to Hartzell Propeller Inc. Publications

(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).

(b) The reference numbers for tooling appearwiththeprefix"TE"directlyfollowing the tool name to which they apply. For example, a template that is reference number 133 will appear as: template TE133.

(2) 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) Thereferencenumbersforconsumablematerialsappearwiththeprefix

"CM" directly following the material to which they apply. For example, an adhesive that is reference number 16 will appear as: adhesive CM16. Only thoseitemsspecifiedmaybeused.

C. Vendor Publications(1) None

3. Personnel Requirements

A. Inspection, Repair, and Overhaul

(1) Compliance to the personnel requirements established by the Federal Aviation Administration (FAA) or international equivalent, is mandatory for anyone performing or accepting responsibility for any inspection and/or repair and/or overhaul of any Hartzell Propeller Inc. product.

(2) Personnel inspecting, repairing, and overhauling Hartzell Propeller Inc. aluminum propeller blades must have adequate training and experience.

(3) Blade rework procedures such as bending/straightening and grinding/polishing requireahighdegreeofskill.Proceduresmustbeperformedbyqualifiedpersonnel at an appropriately licensed propeller repair facility.

(4) Rework and inspection of critical areas, such as blade bearing bores, demand extensive technical knowledge and familiarity with the product. Personnel with inspection and supervisory responsibility are expected to have a minimum of 18 months practical experience with Hartzell Propeller Inc. aluminum blade overhaul.

(5) Participation in Hartzell Propeller Inc. training classes is strongly recommended.


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Rev. 37 Dec/1861-13-33

4. Safe Handling of Paints and Chemicals

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

B. Before using paint or chemicals, always read the manufacturer’s label on the containerandfollowspecifiedinstructionsandproceduresforstorage,preparation,mixing, and application.

C. Refer to the product’s Material Safety Data Sheet (MSDS) for detailed information about physical properties, health, and physical hazards of any chemical.

5. Minimum Facility and Tooling Requirements

A. Tooling(1) Propeller repair stations approved to overhaul Hartzell Propeller Inc. aluminum

bladesareexpectedtopossessprecisionfixtures,tools,andbladetablesforblade inspection and rework.

(2) Exceptasspecificallyrequiredinthismanual,locallyfabricatedtoolingispermitted for most repair and inspection operations.

(3) In addition, Hartzell Propeller Inc. strongly recommends that a propeller repair facility approved to overhaul Hartzell Propeller Inc. aluminum blades own, maintain, and use the following equipment as their use may be required by certain airworthiness directives:(a) A Hartzell Propeller Inc. blade cold rolling machine, part number

DT-1724-( )

(b) An optical comparator with blade shank overlays as described in this manual

(c) Aprofilometer

(d) A “Y” shank pitch change knob shot peen cabinet, part number DST-5855-( )

(4) Some facilities may choose to subcontract some specialized processes such as cadmium plating, anodizing, cold rolling, or shot peening. Cold rolling and shot peening must only be performed by a facility approved by Hartzell Propeller Inc. For information about approved facilities, contact the Hartzell Propeller Inc. Product Support department or visit the Hartzell Propeller Inc. website at www.hartzellprop.com.


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Rev. 37 Dec/1861-13-33

B. Facilities

(1) Blade grinding, plating, and painting have the potential for health and safety hazards beyond that of other areas of a typical workshop. It is expected that such areas be in compliance with industry standards and governmental regulations concerning occupational safety and health, as well as environmental protection.

(2) Workshop areas must be segregated to prevent contamination. Separate areas must be designated for painting, plating, inspection, and blade grinding/polishing.

(3) A draft free area must be provided for static balancing operations.

6. Component Life and Service

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

A. Overhaul

(1) Overhaul is the periodic disassembly, cleaning, inspection, repairing as necessary, reassembly, 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.,flighttime,or on calendar time.

WARNING: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM ALL INSPECTIONS OR WORK IN ACCORDANCE WITH THE MOST RECENT REVISION OF THIS MANUAL. INFORMATION CONTAINED IN THIS MANUAL MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS. FAILURE TO COMPLY WITH THIS MANUAL OR THE USE OF OBSOLETE INFORMATION MAY CREATE AN UNSAFE CONDITION THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. FOR THE MOST RECENT REVISION LEVEL OF THIS MANUAL, REFER TO THE HARTZELL PROPELLER INC. WEBSITE AT WWW.HARTZELLPROP.COM.

(3) Overhaul must be completed in accordance with the latest revision of the applicable propeller maintenance manual and other publications applicable to, or referenced in, the propeller maintenance manual.

(4) The information in this manual supersedes data in all previously published revisions of this manual.


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Rev. 37 Dec/1861-13-33

B. Damage

(1) General procedures for overspeed, foreign object strike (including bent blades), andfire/heatdamagearefoundintheSpecialInspectionschapterofHartzellPropeller Inc. Standard Practices Manual 202A (61-01-02).

(2) Thebladespecificationtablesinthismanualprovidetheminimumwidthandthickness limits for aluminum blades.

(a) These are absolute minimums.

(b) Anytime widths and thicknesses are measured, if the width or thickness limits are below published minimums, retire the blade.

(c) There is no difference between in-service limits and overhaul limits.

C. Repair

(1) Repair of small nicks and scratches can generally be performed by mechanics in accordance with FAA Advisory Circular 43.13-1B without consulting this manual.

(2) Wheneversignificantamountsofmetalareremoved,whichmaybringintoquestion if the blade is below minimum width or thickness, then the propeller needs to be inspected by an approved propeller repair station to determine if it is below published minimums.

D. Life Limits

(1) Aluminum blades may be life limited. In some cases an entire propeller is life limited, but often only the blades of a propeller assembly are life limited.

(2) Airworthinesslimitations,whichincludebladelifelimits,forspecificpropellerblades are addressed in the Airworthiness Limitations section of the Owner's manual for the applicable propeller assembly.

(3) For life limits of Hartzell Propeller Inc. products, refer to the applicable Owner's manual. Refer to the "Required Publications" section of this chapter.

(4) It is a regulatory requirement that a record of the total time in service be maintained for all life limited parts.

E. Time in Service

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

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

(2) Both TSN and TSO are necessary fordefiningthelifeofthecomponent.Somepartsare"lifelimited"whichmeansthattheymustbereplacedafteraspecifiedperiod of use (TSN).


INTRODUCTIONPage 10

Rev. 37 Dec/1861-13-33

(3) 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.

(4) Time Since New (TSN) and Time Since Overhaul (TSO) records must be maintained in the propeller logbook.

(5) Blades are sometimes replaced while in service or at overhaul.

(a) Maintaining separate TSN and TSO histories for a replacement hub or blade is required.

F. Propeller Critical Parts

(1) Procedures in this manual may involve Propeller Critical Parts (PCP).

(a) These procedures have been substantiated based on Engineering analysis that expects this product will be operated and maintained using the procedures and inspections provided in the Instructions for Continued Airworthiness (ICA) for this product.

(b) Refer to the Illustrated Parts List chapter for the applicable propeller model fortheidentificationofPropellerCriticalParts.

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

G. Long Term Storage

(1) Refer to the Packaging and Storage chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02) for Long Term Storage procedures.


INTRODUCTIONPage 11

Rev. 37 Dec/1861-13-33

7. Definitions

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 certificated aircraft applications. A TC and PC number must be stamped on the hub, and a PC number must be stamped on blades.

Aviation Experimental ....... Intended for aircraft/propeller applications not certified by the FAA or international equivalent. Products marked with an “X” at or near the end of the model number or part number are not certified by the FAA or international equivalent 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 Pitch Axis ................ An imaginary reference line through the length of a blade around which the blade rotates

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

Blemish ............................. An imperfection with visible attributes, but having no impact on safety or utility

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


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Rev. 37 Dec/1861-13-33

Term DefinitionBulge ................................. 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 simultaneously curing it to some other prepared surface

Composite Material ........... Kevlar® (yellow) or graphite (black) 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 alkaline that reacts with the protective oxide layer and results in damage of the base aluminum. Part failure can occur from corrosion due to loss of structural aluminum converted to corrosion product, pitting, a rough etched surface finish, and other strength reduction damage caused by corrosion.

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


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Rev. 37 Dec/1861-13-33

Term DefinitionCorrosion Product(Aluminum) ........................ A white or dull gray powdery material that has an increased

volume appearance (compared to non-corroded aluminum). Corrosion product is not to be confused with damage left in the base aluminum such as pits, worm holes, and etched surface finish.

Corrosion Product(Steel)................................ When iron or an iron alloy such as steel corrode, a corrosion

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

Crack ................................. Irregularly shaped separation within a material, 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 visible on both sides with no visible change in cross sectional thickness

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

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

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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Rev. 37 Dec/1861-13-33

Term DefinitionFace .................................. The surface of the blade that is directed toward the rear of

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

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

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

Fraying .............................. A raveling or shredding of material

Fretting .............................. Damage that develops when relative motion of small displacement takes place between contacting parts, wearing away the surface

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

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

Hazardous PropellerEffect ................................. The hazardous propeller effects are defined in

Title 14 CFR section 35.15(g)(1)

Horizontal Balance ............ Balance between the 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

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


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Rev. 37 Dec/1861-13-33

Term DefinitionLow Pitch........................... The lowest blade angle attainable by the governor for

constant speed operation

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

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 ................................... A sharp, notch-like displacement 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 different from, but comparable to TC and PC.

Non-AviationExperimental ..................... 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 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/condition lever


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Rev. 37 Dec/1861-13-33

Term DefinitionParting Line ....................... The Parting line is formed where the face and camber

composite materials meet at the leading and trailing edges of the blade. They are most visible in the shank area of the blade.

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

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

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

Porosity ............................. An aggregation of microvoids. See “voids”

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

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

Scratch .............................. A thin, shallow cut caused by the movement of a sharp object across a surface

Short.................................. Connection of low resistance between points on a circuit between which the resistance is normally much greater

Shot Peening..................... Process where steel shot is impinged on a surface to create compressive surface stress which 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, normally found near the trailing edge or tip


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Rev. 37 Dec/1861-13-33

Term DefinitionStation 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

Ticking ............................... A series of parallel marks or scratches running circumferentially around the diameter of the blade

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

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

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

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 fiber 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

displacement


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Rev. 37 Dec/1861-13-33

Term DefinitionWrinkle(composite blade).............. Overlap or fold within the material


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Rev. 37 Dec/1861-13-33

8. Abbreviations

Abbreviation TermAD ................................Airworthiness DirectivesAMM ............................Aircraft Maintenance ManualAN ................................Army-NavyAOG .............................Aircraft On GroundAR ................................As RequiredATA ...............................Air Transport AssociationCSU .............................Constant Speed UnitFAA ..............................Federal Aviation AdministrationFH ................................Flight HourFM ................................Flight ManualFMS .............................Flight Manual SupplementFt-Lb ............................Foot-PoundHMI ..............................Human Machine InterfaceICA ...............................Instructions for Continued AirworthinessID .................................Inside DiameterIn-Lb .............................Inch-PoundIPL ................................Illustrated Parts ListIPS ...............................Inches Per SecondITAR .............................International Traffic in Arms RegulationskPa ...............................KilopascalsLb(s) .............................Pound(s)Max. .............................MaximumMin. ..............................MinimumMIL-SPEC ....................MilitarySpecificationMPI ..............................Major Periodic InspectionMS ...............................Military StandardMSDS ..........................Material Safety Data SheetN ..................................NewtonsN/A ...............................Not ApplicableNAS .............................National Aircraft StandardsNASM ..........................National Aerospace Standards, MilitaryNDT .............................Nondestructive TestingNIST .............................National Institute of Standards and TechnologyN•m ..............................Newton MeterOD ...............................Outside DiameterOPT .............................OptionalPC ................................Production CertificatePCP .............................Propeller Critical PartPLC ..............................Programmable Logic ControllerPMB .............................Plastic Media Blasting (Cleaning)POH .............................Pilot’s Operating HandbookPSI ...............................Pounds per Square Inch


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Rev. 37 Dec/1861-13-33

Abbreviation TermRF ................................ReferenceRPM .............................Revolutions per MinuteSAE ..............................Society of Automotive EngineersSTC ..............................SupplementalTypeCertificateTBO .............................Time Between OverhaulTC ................................TypeCertificateTSI ...............................Time Since InspectionTSN ..............................Time Since NewTSO .............................Time Since OverhaulUID ...............................Unique IdentificationWIG ..............................Wing-In-Ground-Effect

9. Dimensions

A. SAE units of measure are used throughout this manual. In many cases, metric equivalents are also provided.

B. When a metric unit of measure does not provide an exact conversion, the SAE unit takes precedence.

C. SAE units of measure supersede metric units of measure.


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Rev. 37 Dec/1861-13-33

10. Contact Information

A. Hartzell Propeller Inc. Product Support Department

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

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

(a) Hartzell Propeller Inc. Product Support may be reached during business hours (8:00 a.m. through 5:00 p.m., United States Eastern Time) at (937) 778-4379 or at (800) 942-7767, toll free from the United States and Canada.

(b) Hartzell Propeller Inc. Product Support can also be reached by fax at (937) 778-4215, and by e-mail at [email protected].

(c) After business hours, you may leave a message on our 24 hour product support line at (937) 778-4376 or at (800) 942-7767, toll free from the United States and Canada.

1 A technical representative will contact you during normal business hours.

2 Urgent AOG support is also available 24 hours per day, seven days per week via this message service.

(d) Additional information is available on the Hartzell Propeller Inc. website at www.hartzellprop.com.

B. Hartzell Propeller Inc. Technical Publications Department

(1) For Hartzell Propeller Inc. service literature and revisions, contact:

Hartzell Propeller Inc. Telephone: 937.778.4200 Attn: Technical Publications Department Fax: 937.778.4215 One Propeller Place E-mail: [email protected] Piqua, Ohio 45356-2634 U.S.A.


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Rev. 37 Dec/1861-13-33


DESCRIPTION AND OPERATION


61-13-33 Page 1-1Rev. 35 Nov/17

DESCRIPTION AND OPERATION - CONTENTS

1. Overview of Aluminum Blades ............................................................................1-3

A. General..........................................................................................................1-3

2. Model Designation System .................................................................................1-5

A. Propeller Model Designation .........................................................................1-5

B. Blade Model Designation ..............................................................................1-5

LIST OF FIGURES

Blade Nomenclature .................................................................. Figure 1-1 ..................1-3

Blade Shank Diagrams .............................................................. Figure 1-2 ..................1-7

LIST OF TABLES

Blade Model Designation............................................................ Table 1-1 ...................1-4

Blade Shank Specifications ........................................................ Table 1-2 ...................1-6

DESCRIPTION AND OPERATIONPage 1-2

Rev. 35 Nov/17


61-13-33




61-13-33 Page 1-3Rev. 28 Sep/12

1. Overview of Aluminum Blades

CAUTION: INFORMATION IN THIS CHAPTER INVOLVES PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS.

A. General

(1) Aluminum propeller blades are manufactured from one solid piece of aluminum that has been forged and heat treated prior to manufacture.

(2) Aluminum blades are used in both steel and aluminum hub propellers in a variety of designs which require the use of various models of blade shanks. Therefore, blades are distinguished by shank design, propeller diameter, tip configuration, and other characteristics of the blade (refer to Table 1-1).

Blade Retention RadiusBlade Butt

Shank Section

Airfoil Section

Leading Edge

Camber Side

Face Side

Trailing Edge

APS2047APS2048

Blade Nomenclature Figure 1-1


Rev. 30 Apr/13


61-13-33

Blade Model Designation Table 1-1

FJC 8475 CH-3 Q *1EXAMPLE: propeller model

Prefix of up to 3 Letters: C - counterweighted "Y" shank F - large pitch change knob "Y" shank H - right hand rotation, pusherJ - left hand rotation, tractor L - left hand rotation D,E,M,MV,P,R,T,V,W - shank design blank - standard blade, right hand rotation, tractor ("X", "Y", and "Z" shanks + few others)

The first 2 or 3 numbers indicate basic design diameter (in inches), the last 2 numbers indicate a specific model

Suffix Letters: A - Dimensional change to basic blade or "Y" shank pitch knob locationB - anti-icing or de-ice boot C - modified blade, dimensional or blade twist modification from initial blade design D - modified blade, blade twist or thickness change; for E9512D-1 blade, identical to E9512C-1

except service lifeE - de-ice boot , elliptical tip, or alternate life limitF - modified blade, dimensional modification (width/thickness) G - for 7663 and 8468 blades, a negative pitch change knob angle; for E9512G-1( ), identical to

E9512C-1( ) except service lifeH - hard alloy (7076) K - de-ice boot N - shank modification (pilot tube hole), thickness added to certain blade shanksQ - Q-tip, factory 90 degree formed tip R - specifically rounded tips S - shot peening of blade surface, or square tip (Exception: Blade model M10476 was manufactured with a shot peened surface; however, the “S” shot peen designator was not included in the model number. The “S” designator will be added to M10476 blades at overhaul.)T - twistblank - original design, no changes other letters - location of pitch change knob ("Y" shank), twist

Dash or Plus Number: Change from basic propeller diameter. There may be a letter following the dash or plus number. (Note: This basic diameter may not reflect the actual prop diameter, depending on the hub model used.)

A - slightly thinner & narrower tip fairing E - elliptical tipQ - Q-tip, factory 90 degree formed tipR - specifically rounded tipS - square tip T - specifically rounded tip

Asterisk/number - An asterisk and number to the right of the blade model number are addedwhen there is a difference in paint, de-ice, or counterweight from the “standard” blade configuration. The specific meaning applies only to an individual blade configuration and does not necessarily represent the same change(s) in blade design for other blade models.

(NOTE: This Blade Finish Table is a general guideline. There may be exceptions that are not listed.)



61-13-33 Page 1-5Rev. 37 Dec/18

2. Model Designation System

A. Propeller Model Designation(1) Hartzell Propeller Inc. uses a model designation to identify specific propeller and

blade assemblies (Table 1-1). Example: HC-B5MP-3A/M10282A+6. A slash mark separates the propeller and blade designations. The propeller model designation is impression stamped or permanently marked on the propeller hub. The blade designation is impression stamped or permanently marked on the butt end of the blade. Some blades may also be ink stamped or labeled on the camber side of the blade.

B. Blade Model Designation(1) Hartzell Propeller Inc. blades are often referred to as “D” shank, “Y” shank, etc.

NOTE: It is useful to understand the basic differences between shank types. Refer to Table 1-1 and Figure 1-2

(a) For most blades, the shank type is identified in the prefix letters of the blade model designation. For example, T10282 denotes this is a “T” shank blade.

1 There are exceptions to this rule. For example, “Y” shank blades do not use the letter “Y” in the model designation.

(2) The dash (-) or plus (+) number in the blade model designation of an aluminum blade indicates the amount of diameter change from the blade’s basic design. For example, a T10173-8 blade designates that the propeller diameter has been reduced 8 inches from its basic design.NOTE: For more information on blade model designations and reduction of the

propeller diameter, refer to paragraph 2.K. of the Blade Airfoil Overhaul chapter of this manual.

(a) An additional letter following the dash (-) number, if present, indicates alternate tip shapes.

(3) An asterisk and number to the right of the blade model number indicates that there is a difference in paint, de-ice, or counterweight from the “standard” blade configuration.

(a) The specific meaning applies only to an individual blade configuration and does not necessarily represent the same change(s) in blade design for other blade models.

(b) For specific blade paint information, refer to the Blade Finish Table in the Paint and Finish chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(c) For de-ice and/or anti-icing boot location(s), refer to Hartzell Propeller Inc. Propeller Ice Protection System Manual 180 (30-61-80).


Rev. 28 Sep/12


61-13-33

SHANK HUB TYPE RETENTION INTERNAL BEARING PITCH CHANGE

"Y" “compact” single shoulder 1 needle bearing integral knob

"D" “lightweight” single shoulder 1 needle bearing bolt-on bracket

"E" “lightweight” single shoulder 1 needle bearing bolt-on bracket

Blade Clamp

"X" steel double shoulder 1 blade bushing C-3-( )

"V" steel double shoulder1 blade bushing

and 1 needle bearing

C-3-( )

"MV" steel single shoulder1 blade bushing


D-6831-( )

"W" steel single shoulder1 blade bushing


C-1301-( )

"Z" steel single shoulder 1 blade bushing C-1301-( )

"M" steel single shoulder 2 needle bearings C-1977-( )

"P" steel single shoulder 1 blade bushing C-1977-( )

"R" steel single shoulder1 blade bushing


C-1977-( )

"T" steel single shoulder 2 needle bearings C-1301-( )

NOTE: There are other shank types that are used for composite blades such as "A", "B", "E", or "M" shank. For information about composite blades, refer to Hartzell Propeller Inc. Maintenance Manual for Composite Propeller Blades 135F (61-13-35).

Blade Shank Specifications Table 1-2


Rev. 27 Sep/11


61-13-33

"P" Shank "P" Shank Modified to "R" Shank

Blade Shank Diagrams Figure 1-2, Page 1 of 4

"R" Shank

APS0641, APS0651, APS0650, TI-133001, TI-133001

"R" Shank with "N" Modification

"P" Shank with "N" Modification


Rev. 27 Sep/11


61-13-33

"Y" Shank

"D" or "E" Shank

Blade Shank Diagrams Figure 1-2, Page 2 of 4

"M" Shank "T" Shank

"M" or "T" Shank with "N" Modification

APS0640, APS0645, APS0647, APS0655, APS0656


Rev. 27 Sep/11


61-13-33

APS0642, APS0644, TI-133001, APS0643, TI-133002

Blade Shank DiagramsFigure 1-2, Page 3 of 4

"Z" Shank "Z" Shank Modified to "W" Shank

"W" Shank"Z" Shank with "N" Modification

"W" Shank with "N" Modification


Rev. 27 Sep/11


61-13-33

Blade Shank DiagramsFigure 1-2, Page 4 of 4

"V" Shank

"X" Shank Modified to "V" Shank

"V" Shank with "N" Modification

APS0648 APS0652APS0653

"MV" Shank with "N" Modification

APS0654

"X" Shank


BLADE SHANK OVERHAUL 61-13-33 Page 2-1Rev. 38 Apr/19

BLADE SHANK OVERHAUL - CONTENTS

1. Special Inspections and Procedures ..................................................................2-5

2. Overhaul Procedures ..........................................................................................2-7

A. General..........................................................................................................2-7

B. Single Shoulder Blade Shank Inspection and Overhaul ...............................2-7

C. Double Shoulder Blade Shank Inspection and Overhaul ............................2-33

D. Pitch Change Knob Inspection and Overhaul .............................................2-49

E. Pitch Change Bracket Mounting Holes........................................................2-78

F. Blade Balance Hole Inspection and Overhaul .............................................2-86

G. Blade Bore Inspection and Overhaul...........................................................2-97

H. Blade Shank Conversion ...........................................................................2-145

I. Counterweight Disassembly ......................................................................2-151

J. Counterweight Installation .........................................................................2-156

K. Repair of Oversized 7/16-20UNF-3B Tapped Holes in "Y", "D", and "E" Shank Blade Counterweight Knob ..............................2-170.3

L. Repair of Oversized 1/2-20UNF-3B Tapped Holes in "D" and "E" Shank Blade Counterweight Knob .........................................2-173

M. B-6143-( ) Thread Insert Removal .............................................................2-175

N. Blade Counterweight Knob Threaded Insert Removal ..............................2-176

O. Blade Counterweight Knob Surface Check Criteria ..................................2-184


BLADE SHANK OVERHAULPage 2-2

Rev. 35 Nov/1761-13-33

LIST OF FIGURES

"Y", "D" and "E" Shank Dimensional Inspection ..............................Figure 2-1 .............2-6

Measuring Points for Shank Diameters ...........................................Figure 2-2 .............2-6

Rework Area for Single Shoulder Retention Radius ........................Figure 2-3 ...........2-10

"T", "W", and "Z" Shank Minimum Height ........................................Figure 2-4 ...........2-12

"P", "R", and "M" Shank Minimum Height ........................................Figure 2-5 ...........2-12

"Y", "D" and "E" Shank Minimum Height and Lip Thickness ...........Figure 2-6 ...........2-13

Bearing Retention Lip Repair Limits ................................................Figure 2-7 ...........2-13

"D", "E", and "Y" Shank Blade Shoulder Repair Area ......................Figure 2-7.1 ........2-15

"MV" Shank Minimum Height ..........................................................Figure 2-8 ...........2-19

"V" Shank Modified to "MV" Shank Dimensions ..............................Figure 2-9 ...........2-20

Electronic Profilometer TE436 and Probe Housing Component TE437 .....................................................................Figure 2-10 .........2-23

Double Shoulder Shank Diameter Dimensions ...............................Figure 2-11 .........2-30

Double Shoulder Shank Inspection .................................................Figure 2-12 .........2-34

Blade Shank Shot Peen Coverage Specifications ..........................Figure 2-13 .........2-42

Pitch Change Knob Inspection and Damage Limits ........................Figure 2-14 .........2-45

Perpendicularity of the Pitch Change Knob .....................................Figure 2-15 .........2-50

"F" Pitch Change Knob Inspection Criteria ......................................Figure 2-16 .........2-52

Non "F" Pitch Change Knob Inspection Criteria ..............................Figure 2-17 .........2-56

Almen Strip Holder (DST-5855+35) .................................................Figure 2-18 .........2-62

Angle of Incidence and Vertical Axis................................................Figure 2-19 .........2-64

Align Mark........................................................................................Figure 2-20 .........2-68

Blade Butt Mask (DST-5855+48) .....................................................Figure 2-21 .........2-70

Pitch Change Knob Location ...........................................................Figure 2-22 .........2-74

Blade Plug or Spacer Inspection Area .............................................Figure 2-22.1 ......2-86

Critical Area of the Balance Hole ....................................................Figure 2-23 .........2-90

Tool for Balance Hole Polishing .......................................................Figure 2-23.1 ...2-90.2

3M Scotch Brite® Grinding Wheel Modification ................................Figure 2-23.2 ......2-91

Shot Peening Lead Balance Hole in Blade .....................................Figure 2-24 .........2-95

Shot Peening Lead Balance Hole....................................................Figure 2-25 .........2-96

Visual Inspection Area Of Blade Bore .............................................Figure 2-26 .......2-100

"X", "X" Modified to "V", or "X" Modified to "MV" Shank ..................Figure 2-27 .......2-105


BLADE SHANK OVERHAUL 61-13-33 Page 2-3Rev. 38 Apr/19

LIST OF FIGURES, CONTINUED

"V" or "V" Modified To "MV" Shank ..................................................Figure 2-28 .......2-106

"V" and "V" Modified To "MV" With "N" Modification ........................Figure 2-29 .......2-107

"MV" Shank With "N" Modification ...................................................Figure 2-30 .......2-109

"R" or "W" Shank .............................................................................Figure 2-31 .......2-110

"P", "P" Modified to "R", "Z", or "Z" Modified to "W" Shank .............Figure 2-32 ....... 2-111

"R" or "W" Shank with "N" Modification ...........................................Figure 2-33 .......2-112

"P" and "Z" Shank with "N" Modification ..........................................Figure 2-34 .......2-114

"T" or "M" Shank ..............................................................................Figure 2-35 .......2-115

"T" or "M" Shank With "N" Modification ...........................................Figure 2-36 .......2-116

"T" or "M" Shank Rework Tolerances for Tapered "X" Area of Blade Bore .............................................................................Figure 2-37 .......2-117

"T" or "M" Shank With "N" Modification Rework Tolerances for Tapered "X" Area of Blade Bore ............................................Figure 2-38 .......2-119

"D" Shank ........................................................................................Figure 2-39 .......2-120

"Y" Shank ........................................................................................Figure 2-40 .......2-121

"E" Shank ........................................................................................Figure 2-41 .......2-122

Installing CM46 Gasket Sealant ......................................................Figure 2-42 .......2-138

Bearing Installation on "T" and "M" Shank Blades with "N" Conversion ...................................................................Figure 2-43 .......2-140

Reading Runout...............................................................................Figure 2-44 .......2-142

"X" to "V" Shank Bearing Press Tool ...............................................Figure 2-45 .......2-144

"Z" Shank Converted to "W" Shank Blade .......................................Figure 2-46 .......2-146

"P" Shank Converted to "R" Shank Blade .......................................Figure 2-47 .......2-148

Counterweight Inspection ................................................................Figure 2-48 .......2-150

Drilling the Counterweight Assembly for Spring Pin Installation ..................................................................................Figure 2-49 .......2-150

Counterweight Surface ....................................................................Figure 2-49.1 ....2-151

Counterweight Assembly .................................................................Figure 2-50 .......2-154

Counterweight Bolt Installation ........................................................Figure 2-51 .......2-154

Counterweight Spring Pin Installation..............................................Figure 2-52 .......2-157

Counterweight View .........................................................................Figure 2-52.1 ....2-159

Drilling the Dowel Pin Hole Into the Blade .......................................Figure 2-53 .......2-163



Rev. 38 Apr/1961-13-33

LIST OF FIGURES, CONTINUED

Expanding Arbor Fixture ..................................................................Figure 2-54 ....2-170.4

Blade Counterweight Knob Surface ................................................Figure 2-55 .......2-177

LIST OF TABLES

Transition Region for Anodize to Chemical Conversion Coating .......................................................................................Table 2-1 ............2-30

Transition Region for Anodize to Chemical Conversion Coating .......................................................................................Table 2-2 ............2-47

Rework Dimensions for "F" and Non-"F" Pitch Change Knobs .......Table 2-3 ............2-49

Pitch Change Knob Location (Degrees) ..........................................Table 2-4 ............2-76

Blade Plug and Spacer Inspection Criteria ......................................Table 2-4.1 .........2-85

Blades that Cannot Use the TE208( ) Reamer ................................Table 2-5 .........2-90.1

Balance Hole Shot Peen Specifications ..........................................Table 2-6 ............2-97

Bore Dimensions .............................................................................Table 2-7 ..........2-104

Blade Bushing Diameters ................................................................Table 2-8 ..........2-138

Counterweight Mounting Hardware .................................................Table 2-9 ..........2-155

Counterweight Dowel Pin Hole Requirements for Press Fit ............Table 2-10 ........2-155

Counterweight Slug Mounting Hardware Torques ...........................Table 2-11 .........2-157

Blade Counterweight Knob Surface ................................................Table 2-12 ........2-178



Rev. 23 Mar/0861-13-33

1. Special Inspections and Procedures

WARNING: THERE ARE MANDATORY INSPECTIONS AND PROCEDURES FOR SPECIFIC APPLICATIONS THAT MUST BE COMPLIED WITH IN ADDITION TO THE REQUIREMENTS OF THIS CHAPTER. A LIST OF THESE APPLICATIONS CAN BE FOUND IN THE TABLE OF CONTENTS OF THE SPECIAL INSPECTIONS AND PROCEDURES CHAPTER OF THIS MANUAL. FAILURE TO COMPLY WITH THE REQUIREMENTS WILL RESULT IN IMPROPER INSPECTION, REPAIR, AND OVERHAUL OF THE AFFECTED COMPONENT.

A. Refer to the Table of Contents of the Special Inspections and Procedures chapter of this manual for additional requirements that apply to certain assemblies.

B. If the requirements are applicable, they must be complied with in addition to those listed in this chapter.



Rev. 23 Mar/0861-13-33

Shank Diameter

Leading Edge

Trailing Edge

"Y", "D" and "E" Shank Dimensional Inspection Figure 2-1

Measuring Points for Shank Diameters Figure 2-2

DYDIMS

APS6117

B 1.375 inch(34.93 mm)

Radius Transition Area



Rev. 27 Sep/1161-13-33

2. Overhaul Procedures

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. General

(1) The following procedures are to be performed during overhaul.

(2) To determine the specific steps that apply to a particular blade model, refer to the traveler for that blade. Refer to the Appendix B - Travelers chapter of this manual.

(3) If a blade does not meet the serviceable limits, retire the blade.

B. Single Shoulder Blade Shank Inspection and Overhaul

(1) Clean Shank

(a) Using cleaning agent CM106 or plastic media cleaning, remove paint and sealant from the retention radius. Refer to the Cleaning chapter of Hartzell Standard Practices Manual 202A (61-01-02) for plastic media cleaning requirements and procedures.

(b) For "D", "E", and "Y" shank blades: Using plastic media cleaning , remove paint and epoxy resin from the retention radius. For plastic media cleaning, refer to the Cleaning chapter of Hartzell Standard Practices Manual 202A (61-01-02)

1 Remove threaded staked inserts in the counterweight knob, if required.

(c) Using a cloth dampened with solvent CM23, wipe the shank area. Permit the shank area to thoroughly dry.

(2) Inspect Outside Diameter

(a) "D", "E", and "Y" shank blades only. Refer to Figure 2-1.

1 Using a Knife Edge or Ball End Micrometer, measure the OD of the blade shank.

2 Blades that receive compression rolling of the retention radius during manufacture (all "D" and "E" shank blades and "Y" shank blades with serial number D47534 or higher) must maintain a diameter of 3.334 inches (84.69 mm) or greater in the "B" area above the bearing shoulder. Refer to Figure 2-1.



Rev. 31 Jul/1461-13-33

3 Earlier production blades that received shot peening in the retention area during manufacture (serial number D47533 or lower) must maintain a diameter of 3.344 inches (84.94 mm) or greater in the "B" area above the bearing shoulder. Refer to Figure 2-1.

4 Dimensionally inspect the shank in 45 degree increments at the area labelled "B" in Figure 2-1. Refer to Figure 2-2 for dimensional inspection points. "Undercutting" (diameter less than area "B") is not permitted in the radius.

5 If the blade is below the permitted dimensional limits, retire the blade from service.

(b) "T", "W", and "Z" Shanks Immediately Outboard of the Clamping Area

1 Inspect the blade in 45 degree increments as shown in Figure 2-2. 2 Because of their tapered shanks, "T", "W", and "Z" shanks have

special repair limits immediately outboard of the clamping area. The following limits apply to all three shanks:Distance from Shoulder Minimum Diameter

0.250 inch (6.35 mm) 3.395 (86.24 mm)

0.500 inch (12.70 mm) 3.345 (84.97 mm)

0.875 inch (22.22 mm) 3.345 (84.97 mm)

3 If the blade does not meet the permitted limits, retire the blade.(c) "M", "P", and "R" Shanks

1 Measure the shank in 45 degree increments at the area labeled OD "A" in Figure 2-5. Refer to Figure 2-2 for dimensional inspection points.

2 Measure the shank in 45 degree increments at the area labeled OD "B" in Figure 2-5. Refer to Figure 2-2 for dimensional inspection points.

3 In the area immediately outboard of the retention shoulder, a minimum of 3.538 inches (89.87 mm) outside diameter is permitted to a distance of 0.750 inch (19.05 mm) outboard from the retention shoulder to permit for repair of the blade in this area.

4 If the blade does not meet the permitted limits, retire the blade.



Rev. 27 Sep/1161-13-33

(3) Inspect Retention Radius(a) Visually inspect the retention radius for damage or corrosion. A very high

quality, smooth finish is required in the retention radius.

(b) Inspect the blade retention radius using an optical comparator. Refer to the Appendix A - Optical Comparator chapter of this manual.

1 Deviations of the radius area are not permitted regardless of shank diameter.

2 The transition between the straight surface of the blade and the area where the optical comparator inspection ends must maintain a smooth blend with no steps or irregularities.

CAUTION: DO NOT USE THE OPTICAL COMPARATOR TO INSPECT THE SHANK DIMENSIONS.

3 Use the optical comparator to inspect the retention region only, as defined in the Appendix A - Optical Comparator chapter of this manual.

(c) If the retention radius is not satisfactory, rework the radius until it meets proper optical comparator overlay shape.

(d) If the retention radius cannot be reworked to meet the optical comparator overlay shape, retire the blade from service.



Rev. 23 Mar/0861-13-33

Polish This Area on All Shank TypesSpanwise Tooling Marks are Not

Permitted in This Area

Rework Area for Single Shoulder Retention Radius Figure 2-3

NOTE: "Y" shank blade shown.

Do Not Polish This Area on "Y", "D", or "E" Shank Blades

BSK735-2

Spanwise Tooling Marks are Permitted in This Area

Spanwise Tooling Marks

(4) Rework Retention Radius as Required

CAUTION: THE MOST CRITICAL ELEMENT IN THE REWORK OF A BLADE SHANK IS TO MAINTAIN A SMOOTH, HIGH QUALITY SURFACE FINISH WITH NO SCRATCHES, PITTING, OR SIMILAR DEFECTS THAT CAN CAUSE BLADE FAILURE.

(a) Rework the retention radius to remove nicks, scratches, and corrosion found during visual inspection.

1 Rework performed must match the optical comparator overlay.2 If the retention radius cannot be reworked to meet the optical

comparator overlay shape, retire the blade from service.(b) Tooling marks are permitted outboard of the retention radius and the rolled

area.

1 Tooling marks are characterized as multiple spanwise lines, flats, or facets around all or a portion of the shank circumference that may result in a shank diameter that is not uniform. Refer to Figure 2-3.



Rev. 23 Mar/0861-13-33

(c) If there are tooling marks in the rolled area, perform rework in the rolled area. Rework in accordance with section 2.B.(6) of this chapter for the specific shank.

(d) Surface imperfections with a depth of less than 0.002 inch (0.05 mm) may be reworked by sanding with fine sandpaper (320-grit or finer).

WARNING: ROTATING A BLADE IN A LATHE IS POTENTIALLY DANGEROUS. APPROPRIATE SAFETY DEVICES AND OPERATOR TRAINING ARE REQUIRED.

(e) Blades that require rework for larger imperfections (including "Y" shank blades that were shot peened during manufacture and have never been compression rolled) must be mechanically rotated at a slow RPM to make sure that there is equal removal of material in the rework area.

1 This may be accomplished by chucking the blade in a lathe or other suitable means.

2 Using a rotating abrasive cartridge to remove the material in the rework area is recommended.

3 Rework in the flat area where the bearing race makes contact is not permitted. Refer to Figure 2-3.

4 The flat area where the bearing race makes contact may be polished to remove steps that occur in the transition from the retention radius to the bearing seat area.

5 Maintain the lip thickness and the shank height limits. Refer to Figure 2-6.

6 Sand the rough pebble grain until smooth. It is not necessary to remove all of the previous shot peening.

7 The shank must meet the optical comparator inspection requirements.

8 If the blade shank cannot be reworked to meet the optical comparator overlay shape, retire the blade from service.



Rev. 31 Jul/1461-13-33

"T", "W", and "Z" Shank Minimum Height Figure 2-4

"P", "R", and "M" Shank Minimum Height Figure 2-5

Retention Radius

APS221

0.845 Inch(21.47 mm)Minimum 4.187 Inches (106.35 mm)

or Greater OD

0.830 Inch(21.09 mm)Minimum

Retention Radius

TPI-A

PS

220

A

4.187 Inches (106.35 mm) Minimum - OD "A"

4.187 Inches (106.35 mm) Minimum - OD "A"

4.179 Inches (106.15 mm) Minimum - OD "B"

0.250 Inch (6.35 mm) Maximum

0.030 Inch (0.76 mm) R

Minimum



Rev. 23 Mar/0861-13-33

"Y", "D", and "E" Shank Minimum Height and Lip Thickness Figure 2-6

Bearing Retention Lip Repair Limits Figure 2-7

↓↑


Depthof Repair


CircumferentialLength

Lip width

APS6213APS6214 0.375 Inch

(9.53 mm) Minimum Original Material

APS222A

Retention Radius

Minimum of 0.172 Inch (4.37 mm) for "Y" and "D" Shank,0.336 Inch (8.54 mm)

for "E" Shank

Minimum of0.799 Inch (20.30 mm) for "Y" and "D" Shank,0.959 Inch (24.36 mm)

for "E" Shank



Rev. 24 Nov/0861-13-33

(5) Bearing Retention Lip Repair

(a) "D", "E" and "Y" shank blades only

1 An unlimited number of local repairs to the bearing retention lip are permitted if they fall within the limits below.

2 The maximum permitted damaged area that may be repaired is 0.050 inch (1.27 mm) deep and 1 inch (25.4 mm) in circumferential length. a The repair may extend the entire width of the bearing retention

lip. Refer to Figure 2-7.3 Two adjacent repairs must be separated by a minimum of 0.375 inch

(9.53 mm) circumferential length of original material.4 The minimum permitted lip diameter outside the local repair areas is

4.746 inches (120.55 mm). a Measure the lip diameter in four places, at 45 degree intervals. b If two or more measurements are below the minimum permitted

diameter, retire the blade from service. 5 Blend the repair(s) smoothly to the undamaged lip.

a The repaired area(s) must maintain a surface of 30 micro finish or greater.

6 If all of the above limits are not met, retire the blade.(b) After sanding, polish the area with a crocus cloth or abrasive pad CM47,

or equivalent.

(c) If rework was completed after the initial optical comparator inspection (section 2.B.[3][b] of this chapter), reinspect the blade retention radius on the optical comparator.

(d) For "D", "E", and "Y" shank blades, if rework was completed after the initial dimensional inspection (section 2.B.[2] of this chapter), repeat dimensional inspection procedures.

1 All imperfections must be repaired before the compression rolling process.



Rev. 24 Nov/0861-13-33

"D", "E", and "Y" Shank Blade Shoulder Repair Area Figure 2-7.1

APS222B

Blade Shoulder

Pitting is permitted in this area

Blade Retention Lip

Pitch Change Knob

(5.1) Blade Shoulder Repair

(a) "D", "E" and "Y" shank blades only

CAUTION 1: BE VERY CAREFUL NOT TO DAMAGE THE BLADE RETENTION LIP WHEN REPAIRING THE BLADE SHOULDER.

CAUTION 2: DO NOT UNDERCUT THE PITCH CHANGE KNOB.1 Local repairs of pitting on the surface of the blade shoulder, between

the blade retention lip and the blade butt, to a maximum depth of 0.010 inch (0.25 mm) are permitted. Refer to Figure 2-7.1.

2 There is no limit to the number of repaired areas permitted on the surface of the blade shoulder between the blade retention lip and the blade butt.



Rev. 27 Sep/1161-13-33

(6) Dimensionally Inspect Blade Shank

CAUTION: REQUIRED REPAIR AND REWORK PROCEDURES PERFORMED ON BLADE SHANK RETENTION AREAS CAN REDUCE THE OVERALL THICKNESS OF THE MATERIAL IN THE AREA BETWEEN THE BLADE BUTT AND THE SHANK RETENTION RADIUS. THIS CAN RESULT IN DIMENSIONS THAT ARE LESS THAN THE PERMITTED LIMITS, WHILE STILL MAINTAINING THE DESIRED SHAPE REQUIRED FOR ACCEPTANCE BY OPTICAL COMPARATOR INSPECTION.

(a) Put the blade on a smooth, flat surface such as a propeller buildup table.

1 Before measuring remove raised areas on the blade butt that were caused by stamping the blade after rework.

2 Permit the pitch change knob to hang over the edge of the work surface for measurement of "Y" shank blades.

(b) Inspect the Blade Butt

1 Pitting on the face of the blade butt to a maximum depth of 0.004 inch (0.10 mm) is permitted.

(c) Using a height gage graduated in thousandths of an inch (hundredths of a millimeter), dimensionally inspect the blade shank.

1 For "Z", "W", and "T" shank blades:a Measure from the blade butt to the flat just outboard of the

radius. Refer to Figure 2-4. If the measurement is less than 0.845 inch (21.47 mm), retire the blade from service.

2 For "P", "R", and "M" shank blades: a Measure from the blade butt to the outboard edge of the

shoulder just outboard of the radius. Refer to Figure 2-5. If the measurement is less than 0.830 inch (21.09 mm), retire the blade from service.



Rev. 27 Sep/1161-13-33

3 For "E" shank blades:a Measure from the blade butt to the outboard edge of the


b Measure the thickness of the lip. Refer to Figure 2-6. If the measurement is less than 0.336 inch (8.54 mm), retire the blade from service.

4 For "Y" and "D" shank blades:a Measure from the blade butt to the outboard edge of the


b Measure the thickness of the lip. Refer to Figure 2-6. If the measurement is less than 0.172 inch (4.37 mm), retire the blade from service.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

"MV" Shank Minimum Height Figure 2-8

APS6080B

RETENTIONRADIUS 0.500 INCH (12.70 mm)DIAMETER

2.000 INCHES(50.80 mm)

0.850 INCH(21.59 mm)

1.210 INCHESMINIMUM(30.74 mm)

3.940 INCHES ± 0.003 (100.08 mm ± 0.07 mm)

3.345 INCHES (84.97 mm) MINIMUM

WORK SURFACE

5 For "MV" shank blades:a Measure from the blade butt to the edge of a 0.25 inch

(6.35 mm) radius gage. lip. Refer to Figure 2-8. If the measurement is less than 1.210 inches (30.74 mm), retire the blade from service.

6 For "V" shank modified to "MV" shank blades: a Measure from the blade butt to the flat of the first blade

shoulder, adjacent to the blade butt. Refer to Figure 2-9. This measurement must be 0.515 inch (13.09 mm) or greater.

b Measure from the blade butt to the top of the "V" groove notch area. This measurement must be less than 0.950 inch (24.13 mm).

c Measure from the blade butt to the flat of the second blade retention shoulder. This measurement must be 1.210 inches (30.74 mm) or greater.

d If all of these tolerances in this section are not met, retire the blade from service.



Rev. 23 Mar/0861-13-33

"V" Shank Modified to "MV" Shank Dimensions Figure 2-9

APS6227

0.242 INCH(6.15 mm) MAXIMUM

BLADE RETENTION SHOULDER

"V" GROOVE RADIUS0.094 INCH ± 0.031 (2.38 mm ± 0.787 mm)

2.000 INCHES(50.80 mm)

3.345 INCHES (84.97 mm)MINIMUM DIAMETER

0.950 INCH(24.13 mm)MAXIMUM

1.210 INCHES(30.74 mm)MINIMUM

RETENTION RADIUS0.500 INCH (12.70 mm)DIAMETER

3.940 INCHES ± 0.003 (100.08 mm ± 0.07 mm)

3.940 INCHES ± 0.003 (100.08 mm ± 0.07 mm)

"V" GROOVE AREA

BLADE SHOULDER0.515 INCH(13.09 mm)MINIMUM

WORK SURFACE

(d) Dimensionally inspect the OD of "T", "M", "W", "Z", "P", and "R" shank blades at four positions. Refer to Figure 2-2.

1 If the OD of the shank is less than 4.187 inches (106.35 mm) at three out of the four positions, retire the blade from service. Refer to Figure 2-4 and 2-5.

(e) Dimensionally inspect the "MV" shank OD at four positions. Refer to Figure 2-2.

1 Measure up from the blade butt 0.850 inch (21.59 mm). Refer to Figure 2-8. At this point measure the diameter of the blade shank. This measurement must be 3.940 inches ± 0.003 (100.08 mm ± 0.07 mm) at three out of the four positions or the blade must be retired from service.

2 Measure up from the blade butt 2.000 inches (50.80 mm). At this point measure the diameter of the blade shank. If this measurement is less than 3.345 inches (84.97 mm) at three out of four positions, retire the blade from service.



Rev. 23 Mar/0861-13-33

(f) Dimensionally inspect the "V" shank converted to "MV" shank OD at four positions (Refer to Figure 2-2 and Figure 2-9).

1 Measure the diameter of the blade shoulder adjacent to the butt end of the blade. This measurement must be 3.940 inches ± 0.003 (100.08 mm ± 0.07 mm).

2 Measure the diameter of the blade retention shoulder farthest away from the butt end of the blade. This measurement must be 3.940 inches ± 0.003 (100.08 mm ± 0.07 mm).

3 Measure up from the blade butt 2.000 inches (50.80 mm). At this point, measure the diameter of the blade shank. This measurement must be 3.345 inches (84.96 mm) or greater at three out of four positions.

4 Measure the "V" groove radius. Refer to Figure 2-9. The radius must be 0.094 ± 0.031 inch (2.38 mm ± 0.78 mm). Measure the thickness from the flat of the "V" groove radius to the outside lip of the shank. This measurement must be 0.242 inch (6.14 mm) or less.

5 If all of these tolerances in this section are not met, retire the blade from service.

(g) For "V" shank converted to "MV" shank, the maximum depth for a local repair in the "V" groove area is 0.010 inch (0.25 mm).

1 If the damaged area exceeds this maximum depth, retire the blade from service.

(7) Chemically Etch Blade Shank

CAUTION 1: ETCHING IS AN ESSENTIAL PROCESS THAT IMPROVES THE VISIBILITY OF DEFECTS DURING PENETRANT INSPECTION. FAILURE TO CHEMICALLY ETCH BLADE SHANKS BEFORE PENETRANT INSPECTION MAY RESULT IN LACK OF DETECTION OF SMALL CRACKS.

CAUTION 2: DO NOT PERMIT CHEMICAL ETCHING SOLUTIONS TO REMAIN ON THE BLADE LONGER THAN THE RECOMMENDED TIME. CORROSIVE DESTRUCTION MAY RESULT. THOROUGHLY RINSE ALL SOLUTIONS AFTER ETCHING IS COMPLETED TO PREVENT CORROSION OF THE BLADE MATERIAL.

(a) For chemical etching procedures, refer to the Penetrant Inspection chapter of Hartzell Standard Practices Manual 202A (61-01-02).



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

Electronic Profilometer TE436 and Probe Housing Component TE437Figure 2-10

W10444

TE436 Profilometer probe Probe housing component TE437

Probe stylusStylus guard

(8) Inspect Blade Shank Using Penetrant

NOTE: During overhaul, perform a penetrant inspection of the blade, as applicable. Refer to the Blade Airfoil Overhaul chapter of this manual for instructions

(a) For required materials, penetrant application methods, and inspection and acceptance criteria, refer to the Penetrant Inspection chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(b) Penetrant inspect the blade shank a minimum of four inches (101.6 mm) outboard of the blade butt.

(c) Penetrant indications are not permitted in the blade retention radius area.

(d) Retire suspect blades from service and return them to Hartzell Propeller Inc. for evaluation.

NOTE: Previous requirements called for stamping a "P" on the butt of the blade after penetrant inspection was completed. This procedure is no longer required.



Rev. 34 Jan/1761-13-33

(9) Cold Compression Roll Blade Retention Radius

CAUTION: COMPRESSIVE ROLLING IS A CRITICAL OPERATION THAT MUST BE PERFORMED ONLY BY SHOPS APPROVED BY HARTZELL PROPELLER INC.

(a) Compressive rolling operations must be performed by a shop approved by Hartzell Propeller Inc.

1 A compression rolling approved facility is a facility approved by Hartzell Propeller Inc. to perform the procedures required by this manual and Service Bulletin HC-SB-61-118.

2 The approved facilities are the ONLY shops authorized by Hartzell Propeller Inc. to return compression rolled parts to service.

3 Refer to the Approved Facilities chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(b) Refer to Appendix E - Rolling Machine chapter of this manual for rolling machine specifi cations, procedures, and repair station approval information.

(c) Hartzell Propeller Inc. Process Control H-S-23 for compression rolling of single shoulder blades is an alternative method for compression rolling of the blade retention radius in accordance with Appendix E of this manual.

CAUTION: ALL SINGLE SHOULDER BLADES REQUIRE COMPRESSION ROLLING AT OVERHAUL.

(d) At overhaul, compression roll all single shoulder blades.

1 This includes older blades that received shot peening in the blade retention area at manufacture.

2 During repair or overhaul, shot peening a single shoulder blade retention radius is not permitted.

CAUTION: THE ROLLING MACHINE MUST BE TURNED OFF DURING THIS INSPECTION.

(e) After the rolling process is completed, turn off the rolling machine.

(f) Use an electronic profi lometer TE436 (Figure 2-10) or other approved alternative to measure the surface fi nish of the rolled radius and the transition area of the blade shank as defi ned in Figure 13-4 through Figure 13-8 in the Appendix E - Rolling Machine chapter of this manual.

1 Support the probe of the TE436 profi lometer using one of the following methods:a Housing component TE437, or equivalent holderb Stand adapter TE496 and drive housing adapter TE497 with

a customer procured height stand


BLADE SHANK OVERHAUL 61-13-33 Page 2-25Rev. 32 Nov/15

2 Leave the blade in the rolling machine chuck, position the blade horizontally in a holding fixture, or set the blade vertically, with the blade butt on a surface or inspection plate that has clearance for the Y-shank knob, if applicable.

3 Visually inspect the blade retention radius and transition area and make a record of any obvious discontinuities in the radius and transition areas.a Examples of unsatisfactory surface conditions are indents, pits,

ridges, or abrupt transitions. b Using an abrasive pad that has 400-grit or finer, polish

unsatisfactory conditions in accordance with the limits specified in this chapter.

c If the blade was polished after rolling, re-roll the blade retention radius. Refer to the Appendix E - Rolling Machine chapter of this manual.

4 Set up the profilometer TE436 according to the manufacturer's instructions.

5 Configure the profilometer to read "Ra" with the units in microinches or micrometers.

CAUTION: THE PROFILOMETER CALIBRATION MUST BE CHECKED AGAINST THE MANUFACTURER SUPPLIED REFERENCE STANDARD A MINIMUM OF ONCE EACH SHIFT.

6 Before performing surface finish inspections, check the profilometer calibration against the manufacturer reference standard or the roughness standard TE498, as applicable. a The profilometer "Ra" reading must be within two percent of the

"Ra" value specified by the manufacturer reference standard or the roughness standard TE498, as applicable.

b If the profilometer reading is not within the specified limits, recalibrate the profilometer in accordance with the manufacturer's instructions.

7 Profilometer setupa Set "Lt" to 0.224 inch (5.68 mm).b Set "cutoff" to 0.032 inch (0.81 mm) X 5. c Set the number of samples to 5.

8 Using a clean cloth dampened with solvent CM11, clean the blade shank.

9 Put the profilometer at the area where the most prominent of any discontinuities in the transition area of the blade is located.a Rotate the blade, if necessary.



Rev. 28 Sep/1261-13-33

10 If no discontinuities are found, the inspection may be performed anywhere within the specified area.

11 Insert the profilometer probe into the TE437 probe housing, or equivalent holder, in the vertical position so that the stylus is at the 6 o'clock ± 5 degrees position. Refer to Figure 2-10.

12 Put the TE437 probe housing on a nonslip surface or attach the probe housing to a customer procured height stand using stand adapter TE496 and drive housing adapter TE497.

CAUTION: MAKE SURE THAT THE STYLUS GUARD DOES NOT TOUCH THE BLADE.

13 Adjust the height of the probe housing legs or adjust the customer procured height stand so that the probe stylus has positive contact with the blade and is depressed approximately 0.06 inch (1.5 mm) on the transition area, so that the probe stylus can move perpendicular to the blade centerline and parallel with the surface of the blade butt.

14 Perform the surface finish inspection of the transition area in accordance with the manufacturer's instructions. a If the rolling is performed in accordance with Appendix E of this

manual, the surface finish in the transition area must be 15 Ra microinch (0.381 Ra micrometer) or smoother. If the surface finish is coarser than 15 Ra microinch (0.381 Ra micrometer), repeat steps 2.B.(2), 2.B.(4), and 2.B.(5), and steps 2.B.(9)(a) through 2.B.(9)(e)13.

b If the rolling is performed in accordance with Hartzell Process Control H-S-23 (alternative method of rolling), the surface finish in the transition area must be 10 Ra microinch (0.254 Ra micrometer) or smoother. If the surface finish is coarser than 10 Ra microinch (0.254 Ra micrometer), repeat steps 2.B.(2), 2.B.(4), and 2.B.(5), and steps 2.B.(9)(a) through 2.B.(9)(e)13.

15 Put the profilometer at the area where the most prominent of any discontinuities in the retention radius of the blade is located.a Rotate the blade, if necessary.

16 If no discontinuities are found, the inspection may be performed anywhere within the specified area.

17 If measuring the surface finish in the middle of the blade retention radius, remove and reinsert the probe into the TE437 probe housing with the button on the probe stylus in the angled slot, or position and rotate the drive unit at 45 ± 5 degrees within the drive housing adapter TE497 and the stand adapter TE496, or equivalent holder.


BLADE SHANK OVERHAUL 61-13-33 Page 2-27Rev. 28 Sep/12

18 Put the probe housing TE437 on a nonslip surface or attach the probe housing to a customer procured height stand using stand adapter TE496 and drive housing adapter TE497.

19 Adjust the height of the legs on the probe housing TE437 or adjust the customer procured height stand so that the probe stylus is in the midpoint of the radius.

CAUTION: MAKE SURE THAT THE STYLUS GUARD DOES NOT TOUCH THE BLADE.

20 Move the probe housing so that the probe stylus has positive contact with the blade and is depressed approximately 0.06 inch (1.5 mm) on the radius area, so that the probe stylus moves perpendicular to the blade centerline and parallel with the surface of the blade butt during the measurement.a If the stylus guard interferes with correct contact of the probe

stylus to the radius area, remove the guard.21 Perform the surface finish inspection in the radius area in accordance

with the manufacturer's instructions. a The surface finish in the radius area must be 10 Ra microinch

(0.254 Ra micrometer) or less. b If the surface finish is greater than 10 Ra microinch

(0.254 Ra micrometer), repeat steps 2.B.(2), 2.B.(4), and 2.B.(5), and steps 2.B.(9)(a) through 2.B.(9)(e)20.

(g) After the surface finish measurement is successfully completed, inspect the blade shank on the optical comparator. Refer to the Appendix A - Optical Comparator chapter in this manual for instructions.

1 The retention radius must be inspected at a minimum of two locations, 180 degrees apart. a More locations are required to be inspected if the retention

radius or shank shoulder appears to be non-uniform.2 If the shank does not meet the optical comparator overlay in any of

the inspected locations, rework the blade shank or remove the blade from service.

(h) For "D", "E", and "Y" shank blades only:

1 If the shank diameter was near the minimum limit before compression, measure the shank diameter in accordance with the Overhaul Procedures section of this chapter.

NOTE: Previous requirements called for stamping an "RD" on the butt of the blade after compression rolling was completed. This procedure is no longer required.



Rev. 28 Sep/1261-13-33




Rev. 23 Mar/0861-13-33

(10) Apply Chemical Conversion Coating

NOTE: This manual breaks the overhaul procedures into specific sections for simplicity, but individual shops may decide to chemically treat these areas simultaneously.

(a) At overhaul, apply a chemical conversion coating to the retention radius and the entire blade butt, including bore, balance hole, and pitch change knob, if present. Refer to the Chromic Acid Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(b) Follow the product manufacturer's instructions about storage temperature and pH level to maintain the integrity of the chemical conversion coating.

(c) Apply the chemical conversion coating in accordance with the instructions provided by the product manufacturer.

CAUTION: WHEN THE AREA TO BE CHEMICAL CONVERSION COATED HAS BEEN CLEANED, DO NOT TOUCH THE SURFACE WITH FINGERS OR ANY OILY SUBSTANCE. THIS WILL CAUSE CONTAMINATION OF THE SURFACE AND THE CHEMICAL CONVERSION COAT WILL NOT BOND TO IT.

(d) After compression rolling, clean the blade shank using a noncorrosive cleaner such as "Bon Ami", "Radiaze L.F.", or another similar cleaner that does not contain chlorine or corrosive agents.

(e) Using a grease-free and lint-free cloth such as cheese cloth CM159, apply the cleaner.

(f) Using water, rinse the shank area.

1 If the water beads on the shank area, grease is still present. 2 Repeat the cleaning process until no grease or residue is apparent.

(g) Using cheese cloth CM159 or equivalent, thoroughly dry the shank area.



Rev. 23 Mar/0861-13-33

0.250 Inch (6.35 mm)

0.250 Inch (6.35 mm)

3.450 Inches ± 0.010 (87.63 mm ± 0.25 mm)

Double Shoulder Shank Diameter Dimensions Figure 2-11

DBLSHLD

3.380 Inches ± 0.035 (85.85 mm ± 0.88 mm)

3.940 Inches ± 0.003 (100.07 mm ± 0.07 mm)

Transition Region for Anodize to Chemical Conversion Coating Table 2-1

Distance From the Blade Butt

Shank Inboard Boundary Outboard Boundary

"T", "W", "Z" 2.0 Inches (50 mm) 3.0 Inches (76 mm)"M", "P", "R" 2.0 Inches (50 mm) 3.0 Inches (76 mm)

"MV" with "N" modification 2.0 Inches (50 mm) 3.0 Inches (76 mm)"D", "E", "Y" 1.7 Inches (43 mm) 2.7 Inches (68 mm)



Rev. 23 Mar/0861-13-33

(h) At overhaul, apply a chemical conversion coating to the retention radius and to the entire blade butt, including bore, balance hole, and pitch change knob if present. Refer to the Chromic Acid Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02).

1 To make sure of proper bearing installation and corrosion protection, apply the minimum chemical conversion coating thickness necessary.

(i) The transition between the chemical conversion coating region and the anodized portion of the blade is defined in Table 2-1.

1 Overlap of the chemical conversion coating and anodize within this region is required.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

C. Double Shoulder Blade Shank Inspection and Overhaul

(1) Clean Shank

(a) Using plastic media, clean the shank area to remove paint and sealant material.

(b) Using a cloth dampened with solvent CM23, wipe the shank area.

(c) Permit the solvent to thoroughly dry.

(2) Dimensionally Inspect Shank

(a) Measure the Outside Diameter of the Blade Shank. Refer to Figure 2-11.

1 Before measuring, remove any raised area on the blade butt that is caused by stamping the blade after rework.

2 With the blade butt down, put the blade in a vertical position on a smooth, flat surface such as a propeller buildup table.

3 Measure the shank outside diameter in 45 degree increments. Refer to Figure 2-2.

4 Measure up 0.25 inch (6.3 mm) from the flat of the outboard retention radius.a At this point, measure the shank outside diameter. b The minimum permitted shank outside diameter is 3.440 inch

(87.38 mm). c If the measurement is not within the limits specified, retire the

blade from service.5 If the first measurement of the shank outside diameter is within

tolerance, measure up 0.25 inch (6.3 mm) from the first measurement (0.50 inch [12.7 mm] inch from the flat of the outboard retention radius). a At this point, measure the shank outside diameter. b The minimum permitted shank outside diameter is 3.345 inches

(84.98 mm). c If the measurement is not within the permitted limits, retire the

blade from service.6 Measure the outside diameter of the blade butt below the inboard "V"

groove retention radius. a The minimum permitted shank outside diameter is 3.937 inches

(100.00 mm). b If the measurement is not within the permitted limits, retire the

blade from service.



Rev. 23 Mar/0861-13-33

Double Shoulder Shank Inspection Figure 2-12

Total Shank Height "C"

1.337 inches (33.96 mm) minimum

APS0223A

Outboard Retention Radius

Flat of the Outboard Retention Radius

Flat of the Inboard Retention Radius

Outboard Shank Height "D" 0.801±0.001 inch

(20.34 ± 0.025 mm) minimum

Height "E"

Area "A"

Inboard "V" Groove Retention Radius



Rev. 23 Mar/0861-13-33

(b) Measure the shank height. Refer to Figure 2-12.

1 Before measuring, remove any raised area on the blade butt that is caused by stamping the blade after rework.

CAUTION: REQUIRED REPAIR AND REWORK PROCEDURES PERFORMED ON BLADE SHANK RETENTION AREAS CAN REDUCE THE OVERALL THICKNESS OF THE MATERIAL IN THE AREA BETWEEN THE BLADE BUTT AND THE SHANK RETENTION RADIUS. THIS REPAIR CAN RESULT IN DIMENSIONS THAT ARE LESS THAN SATISFACTORY LIMITS WHILE STILL MAINTAINING DESIRED SHAPE REQUIRED FOR ACCEPTANCE BY OPTICAL COMPARATOR INSPECTION.

2 With the blade butt down, put the blade in a vertical position on a smooth, flat surface such as a propeller buildup table.

3 Using a height gauge that can measure to the number of decimal places specified, dimensionally inspect the blade shank height.

4 Measure from the blade butt to the flat of the outboard retention radius. a The minimum permitted total shank height (Height "C")

measurement is 1.337 inches (33.96 mm). b If the measurement is not within the permitted limits, retire the

blade from service.



Rev. 23 Mar/0861-13-33

5 If the dimension of the total shank height "C" from step 2.C.(2)(b)4 is within the limits specified, measure from the blade butt to the flat of the inboard retention radius (Height "E").

CAUTION: MAKE SURE THAT THE MINIMUM SHANK HEIGHT IS WITHIN PERMITTED LIMITS AFTER REWORK.

a Subtract the measurement (Height "E") from the measurement of the total shank height (Height "C").

b The permitted measurement difference is 0.801 ± 0.001 inch (20.34 ± 0.02 mm).

c If the difference is less than 0.800 inch (20.32 mm), rework the inboard retention radius to meet the permitted limits.

d If the difference is greater than 0.802 inch (20.37 mm), rework the outboard retention radius by removing material from the flat of the outboard retention radius until the blade is within the permitted limits.

e The blade must have a minimum shank height of 1.337 inches (33.96 mm) at all points on the shank.



Rev. 25 Apr/0961-13-33




Rev. 25 Apr/0961-13-33

(3) Visually Inspect the Outboard Retention Radius

(a) There must be a smooth transition with no steps or irregularities where the outboard retention radius blends into the straight surface of the blade.

(b) Visually examine the outboard retention radius for damage or corrosion.

1 Damage or corrosion is not permitted.

CAUTION: MAKE SURE THAT THE REVISION LEVEL OF THE OVERLAY BEING USED IS CORRECT.

(c) Using an optical comparator TE28, perform an inspection of the outboard retention radius. Refer to Appendix A - Optical Comparator in this manual.

1 Refer to Table 9-1 for the correct revision level of the applicable overlay.

(d) If the outboard retention radius does not meet the optical comparator overlay requirements or if there is damage or corrosion, rework the radius in accordance with the "Rework of the Outboard Retention Radius" section in this chapter until it meets the correct optical comparator overlay shape.

1 If the outboard retention radius cannot be reworked to meet the correct optical comparator overlay shape, retire the blade from service.



Rev. 25 Apr/0961-13-33

(4) Visually Inspect the Inboard "V" Groove Retention Radius. Refer to Figure 2-12.

(a) Visually inspect the inboard "V" groove retention radius and area "A" for damage or corrosion.

1 Damage or corrosion is not permitted.


(b) Using an optical comparator TE28, perform an inspection of the inboard "V" groove retention radius and area "A". Refer to the Appendix A - Optical Comparator chapter in this manual.

1 Refer to Table 9-1 for the correct revision level of the applicable overlay.

(c) If the inboard "V" groove retention radius or area "A'" does not meet the optical comparator overlay requirements or there is damage or corrosion, rework in accordance with the "Rework of the Inboard "V" Groove Retention Radius" section in this chapter until it meets the correct optical comparator overlay shape.

1 If the inboard "V" groove retention radius or area "A'" cannot be reworked to meet the correct optical comparator overlay shape, retire the blade from service.

(5) Perform a Penetrant Inspection of the Outboard Retention Area and the Inboard "V" Groove Retention Area.

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

(6) Perform an Eddy Current Inspection of the Retention Area.

(a) Refer to the Eddy Current Inspection chapter of Hartzell Standard Practices Manual 202A (61-01-02).



Rev. 23 Mar/0861-13-33

(7) Rework of the Outboard Retention Radius

CAUTION: SCRATCHES, PITTING, OR SIMILAR DEFECTS ARE NOT PERMITTED, BECAUSE THESE CAN CAUSE BLADE FAILURE. A SMOOTH, HIGH QUALITY SURFACE FINISH IS THE MOST CRITICAL ELEMENT IN THE REWORK OF A BLADE SHANK.

(a) Using 320-grit or finer sandpaper, rework the outboard retention radius to remove nicks, scratches, and corrosion found during visual inspection.

1 Damage after rework is not permitted.2 Rework must be performed to match the retention radius of the

optical comparator overlay.


(b) For blades that require rework for larger imperfections, mechanically rotate the blade at a slow RPM to make sure that there is equal removal of material.

(c) One local repair is permitted in the outboard retention radius of a blade.

1 The maximum permitted depth of repair is 0.020 inch (0.50 mm).2 The maximum permitted length of repair is 0.50 inch (12.7 mm). 3 If the local repair is beyond the maximum permitted limits, retire the

blade from service.(d) If damage to the shot peened surface has a depth of more than 0.003 inch

(0.07 mm), repair the area and re-shot peen before returning the blade to service.

(e) After completion of rework, reinspect the outboard retention radius on the optical comparator.

1 If the retention radius does not match the optical comparator overlay, retire the blade from service.



Rev. 23 Mar/0861-13-33

(8) Rework of the Inboard "V" Groove Retention Radius and Area "A"

CAUTION: SCRATCHES, PITTING, OR SIMILAR DEFECTS ARE NOT PERMITTED, BECAUSE THESE CAN CAUSE BLADE FAILURE. A SMOOTH, HIGH QUALITY SURFACE FINISH IS THE MOST CRITICAL ELEMENT IN THE REWORK OF A BLADE SHANK.

(a) Using 320-grit or finer sandpaper, rework the inboard "V" groove retention radius to remove nicks, scratches, and corrosion found during visual inspection.

1 Damage after rework is not permitted. 2 Rework must be performed to match the inboard "V" groove retention

radius of the optical comparator overlay.


(b) For blades that require rework for larger imperfections, mechanically rotate the blade at a slow RPM to make sure that there is equal removal of material.

(c) Local repairs are permitted in Area "A" of the inboard "V" groove of a blade. Refer to Figure 2-12.

1 The maximum permitted depth of repair is 0.015 inch (0.38 mm).2 Blend the repair smoothly with the surrounding surface.3 If the repair extends into the inboard "V" groove retention radius,

machine the radius to remove any indication of repair. 4 If the local repair is beyond the maximum permitted limits, retire the

blade from service.(d) If damage to the shot peened surface has a depth of more than 0.003 inch

(0.07 mm), repair the area and re-shot peen before returning the blade to service.

(e) After completion of rework, reinspect the inboard "V" groove retention radius and Area "A" on the optical comparator.

1 If the retention radius or Area "A" does not match the optical comparator overlay, retire the blade from service.



Rev. 23 Mar/0861-13-33

Direction of Shot Blast, 45 degrees

1.750 ± 0.125 Inches (44.45 ± 3.18 mm)

Blade Shank Shot Peen Coverage Specifications Figure 2-13

CAUTION: ALL CUT WIRE SHOT MUST BE CONDITIONED IN ACCORDANCE WITH THE SPECIFICATIONS IN THE SHOT PEENING CHAPTER OF HARTZELL STANDARD PRACTICES MANUAL 202A (61-01-02).

Description Shot Size Almen Type IntensityDouble shoulder blade shank CW62 A 0.010 - 0.013 Inch models "X" and "V" (0.25 - 0.33 mm)

or S390 A 0.016 - 0.019 Inch (0.41 - 0.48 mm)

APS6321



Rev. 23 Mar/0861-13-33

(9) Shot Peen Shank as Required

(a) Some blades may have been shot peened outboard of the shot peen area specified in this section.

1 At overhaul, re-shot peen the blade shank within the specified area of 1.750 ± 0.125 inches (44.45 ± 3.18 mm) from the blade butt.

(b) Shot peened areas that receive repairs to damage with a depth greater than 0.003 inch (0.07 mm) must be re-shot peened at overhaul.

(c) Early production blades were not shot peened.

1 All non shot peened blades must be shot peened at overhaul. 2 Re-shot peening at subsequent overhauls is not required unless

dictated by damage or repairs.(d) For the general shot peening procedure, refer to the Shot Peening chapter

of Hartzell Standard Practices Manual 202A (61-01-02).

(e) For shops approved to do the shot peening procedure, refer to the Approved Facilities chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(f) For blade shank shot peen coverage specifications, refer to Figure 2-13.

1 Shot peen an area of 1.750 ± 0.125 inches (44.45 ± 3.18 mm) from the blade butt.

2 Apply the shot to the inboard retention shoulder at an angle 45 degrees from the pitch change axis of the blade, and toward the shank of the blade.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

Pitch Change Knob Inspection and Damage Limits Figure 2-14

APS2049

0.115R inch (2.93 mm) minimum

0.110R inch (2.80 mm) minimum

Small Diameter

Large Diameter

On some blades, the edge of the bearing bore chamfer may intersect the knob radius.



Rev. 23 Mar/0861-13-33


(a) This manual breaks the overhaul procedures into specific sections for simplicity, but individual shops may decide to chemically treat these areas simultaneously.

(b) At overhaul apply a chemical conversion coating to the retention radius and to the entire blade butt, including bore, balance hole, and pitch change knob, if present. Refer to the Chromic Acid Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(c) Follow the product manufacturer's instructions about storage temperature and pH level to maintain the integrity of the chemical conversion coating.

(d) For approved chemical conversion coating products, refer to the Chromic Acid Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02).

CAUTION: WHEN THE AREA TO BE CHEMICAL CONVERSION COATED HAS BEEN CLEANED, DO NOT TOUCH THE SURFACE WITH FINGERS OR ANY OILY SUBSTANCE. THIS WILL CAUSE CONTAMINATION OF THE SURFACE AND THE CHEMICAL CONVERSION COAT WILL NOT BOND TO IT.

(e) After rework or shot peening, clean the blade shank using a noncorrosive cleaner such as "Bon Ami", "Radiaze L.F.", or other similar cleaner that does not contain chlorine or corrosive causing agents.

(f) Using a grease-free and lint-free cloth, such as cheese cloth CM159 or equivalent, apply the cleaner.



Rev. 23 Mar/0861-13-33

Distance From the Blade Butt

Shank Inboard Boundary Outboard Boundary

"X", "V", "V" with "N" modification 2 Inches (50.8 mm) 3 Inches (76.2 mm)

Transition Region for Anodize to Chemical Conversion Coating Table 2-2

(g) Using water, rinse the shank area.

1 If the water beads on the shank area, grease is still present. 2 Repeat the cleaning process until no grease or residue is apparent.

(h) Using a lint-free cloth, such as cheese cloth CM159, thoroughly dry the shank area.

(i) Apply the chemical conversion coating in accordance with the instructions provided by the product manufacturer.

(j) Apply the chemical conversion coating to the retention radius and entire blade butt, including bore, balance hole, and pitch change knob if present.


(k) The transition between the chemical conversion coating region and the anodized portion of the blade is defined in Table 2-2.




Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

Rework Dimensions for "F" and Non-"F" Pitch Change Knobs Table 2-3

Knob/Shank Small Dia. Limit

Large Dia. Limit

Small Dia. (Mfg)

Large Dia. (Mfg)

"F" Knob 0.621 inch 0.800 inch 0.625 inch 0.812 inch("Y" and "B" shank) (15.78 mm) (20.32 mm) (15.88 mm) (20.63 mm)

Non "F" Knob 0.558 inch 0.800 inch 0.562 inch 0.812 inch("Y" shank) (14.18 mm) (20.32 mm) (14.28 mm) (20.63 mm)

After July 1971

Non "F" Knob 0.558 inch 0.740 inch 0.562 inch 0.750 inch("Y" shank) (14.18 mm) (18.80 mm) (14.28 mm) (19.05 mm)

Thru July 1971

D. Pitch Change Knob Inspection and Overhaul

(1) The pitch change knob of each Y shank aluminum propeller blade and each "B" shank composite blade must undergo the following inspections to detect and prevent pitch change knob failures.

(a) If a pitch change knob measurement is below the minimum permitted dimensions, retire the blade from service.

NOTE: The most critical location for damage to occur is at the large diameter portion of the knob in the radius adjacent to the blade butt.

(2) Non "F" knobs were manufactured with a small diameter of 0.562 inch (14.28 mm) and a large diameter of 0.750 inch (19.05 mm) through July 1971. After July of 1971, the large diameter was changed to 0.812 inch (20.63 mm).

(3) In October 1971, the "F" pitch change knob, manufactured with a small diameter of 0.625 inch (15.88 mm) and large diameter of 0.812 inch (20.63 mm) superseded the non "F" knob.

(4) Inspect and rework each pitch change knob based on the pitch change knob dimensions when manufactured. For example, a non "F" pitch change knob manufactured with a large diameter of 0.812 (20.63 mm) cannot be converted to a non "F" pitch change knob with a large diameter of 0.750 inch (19.05 mm).



Rev. 23 Mar/0861-13-33

90 degrees

Perpendicularity of the Pitch Change Knob Figure 2-15

TI-00042

(5) Compliance with the following procedures is required during each propeller overhaul and during inspection after a foreign object strike incident.

(6) Visually inspect for damage such as cracks, gouges, scratches, and corrosion pits.

(a) Repair the damage (if repairable) before the blade is returned to service.

(b) If the damage exceeds the repair limits, retire the blade.

(7) Visually inspect for possible bent knob.

(a) Check perpendicularity of knob with blade butt. Refer to Figure 2-15.

(b) If the knob is bent, retire the blade.



Rev. 23 Mar/0861-13-33

(8) Perform inspection and repair in accordance with the following guidelines:

CAUTION: DO NOT SHOT PEEN "F" PITCH CHANGE KNOBS ON COMPOSITE "B" SHANK BLADES.

(a) "F" Pitch Change Knobs ("Y" and "B" shank blades)

1 Finisha A pitch change knob that has not been shot peened must have

a smooth, high quality finish. 1) Remove all sharp corners and burrs on the knob. 2) Shot peen the knob in accordance with section 2.D.(9)

of this chapter after inspection and rework before being returned to service.

b A shot peened pitch change knob must not show wear below the shot peen pebble grain surface. 1) A shot peened pitch change knob with visible wear that

penetrates the shot peened surface must be re-shot peened in accordance to the section 2.D.(9) in this chapter after inspection and rework.

2 Large Diameter Cylindrical Surface (from blade butt to "step")a One local spot repair of the large diameter up to 0.005 inch

(0.12 mm) below the minimum diameter is permitted. b Blend smooth to 40 times the depth of the damage. c The repaired area must not exceed 25 percent of the total

surface area and must not extend more than 120 degrees around the knob.

d The minimum permitted diameter is 0.800 inch (20.32 mm). e Local spot repair of 0.005 inch (0.12 mm) below the minimum

diameter as previously described is permitted.



Rev. 23 Mar/0861-13-33

0.525 inch (13.34 mm) Min.

"F" Pitch Change Knob Inspection Criteria Figure 2-16

Location "C"

0.800 inch (20.32 mm)

0.621 inch (15.78 mm)

Location "B" must maintain the minimum "small OD" of 0.621 inch (15.78 mm)

Location "A" must maintain the minimum "large OD" of 0.800 inch (20.32 mm).

0.187 inch (4.74 mm) Max.

R 0.115 inch Min.(2.93 mm) Min.

0.156 X 0.156 inch

(3.96 mm X 3.96 mm)

Max. 0.050 inch(1.27 mm) Max.

1.322 inch(33.58 mm) Min.

TI-00040TI-00041

3 Small Diameter Cylindrical Surface (area of pitch change knob contact)

NOTE: Some early production blades were manufactured with a small beveled area on the edge of the knob. This is not cause to retire the blade. Refer to Figure 2-16.

a Repair all damage, scratches, and abrasions within 0.125 inch (3.17 mm) of the small diameter radius.

b Damage can be repaired to 0.005 inch (0.12 mm) depth. c Spot repairs must be blended so that the width of repair is a

minimum of 40 times the damage depth. d For up to 50 percent of the remaining surface area, scratches

and abrasions up to 0.003 inch (0.07 mm) in depth are permitted.

e One local spot repair of the small diameter up to 0.005 inch (0.12 mm) below the minimum diameter is permitted.

f Blend smooth to 40 times the depth of the damage. g The repaired area must not exceed 25 percent of the total

surface area and must not extend more than 120 degrees around the knob.



Rev. 23 Mar/0861-13-33

h The minimum permitted diameter is 0.621 inch (15.78 mm). i Local spot repair of 0.005 inch (0.12 mm) below the minimum

diameter as previously described is permitted.4 Large Diameter Fillet Radius:

CAUTION: DO NOT UNDERCUT THE BLADE BUTT SURFACE.a The minimum permitted radius is 0.110 inch (2.80 mm). b Rework as necessary.c Repairs in location "A" (where the cylindrical surface and

the radius meet) must maintain the minimum "large OD" of 0.800 inch (20.32 mm). Refer to Figure 2-16.

5 Small Diameter Fillet Radius: a The minimum permitted radius is 0.115 inch (2.93 mm). b Rework as necessary.c Repairs in location "B" (where the cylindrical surface and the

radius meet) must maintain the minimum "small OD" of 0.621 inch (15.78 mm). Refer to Figure 2-16.

6 If the repair enters the large diameter cylindrical surface no more than 0.050 inch (1.27 mm) and extends no more than 0.187 inch (4.74 mm), localized repair on the corner edge of the large diameter cylindrical surface as shown in location "C" is permitted.a The corner radius of the local repair must not be less than

0.115 inch (2.93 mm). Refer to Figure 2-16. b Localized repair is limited to one location and the repaired area

must not exceed 45 degrees of the knob circumference.7 Knob length is measured from the blade butt to the end of the knob.

a The minimum permitted knob length is 1.322 inches (33.58 mm).

8 The minimum distance from the blade butt to the corner of the small diameter fillet radius is 0.525 inch (13.34 mm).

9 Penetrant inspect in accordance with the Penetrant Inspection chapter of Hartzell Standard Practices Manual 202A (61-01-02).

10 "F" pitch change knobs on all aluminum blades must be shot peened in accordance with the requirements specified in section 2.D.(9) in this chapter.



Rev. 23 Mar/0861-13-33

(b) Non "F" Aluminum Blade Pitch Change Knobs

1 Finisha A smooth high quality finish is required. b Remove all sharp corners and burrs on the knob.

2 Large Diameter Cylindrical Surface (from blade butt to "step")a One local spot repair of the large diameter up to 0.005 inch

(0.12 mm) below the minimum diameter is permitted. Blend smooth to 40 times the depth of the damage.

b Repaired area must not exceed 25 percent of the total surface area and must not extend more than 120 degrees around the knob.

c Blades manufactured with a large OD of 0.812 inch (20.63 mm) repairs must maintain a minimum "large OD" of 0.800 inch (20.32 mm). Local spot repair of 0.005 inch (0.12 mm) below the minimum diameter as previously described is permitted.

d Blades manufactured with a large OD of 0.750 inch (19.05 mm) repairs must maintain a minimum "large OD" of 0.740 inch (18.80 mm). Local spot repair of 0.005 inch (0.12 mm) below the minimum diameter as previously described is permitted.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

Non "F" Pitch Change Knob Inspection Criteria Figure 2-17

0.558 inch (14.18 mm)

Location "B" must maintain the minimum "small OD" of 0.558 inch (14.18 mm)

If manufactured with a large OD of 0.812 inch (20.62 mm), location "A" must maintain the minimum large OD of 0.800 inch (20.32 mm). If manufactured with a large OD of 0.750 inch (19.05 mm), location "A" must maintain the minimum large OD of 0.740 inch (18.8 mm).

TI-00043TI-00044

Location "C"

1.322 inch(33.58 mm) Min

0.050 inch(1.27 mm) Max

R 0.110 inch(2.80 mm) Min

0.187 inch(4.74 mm) Max

0.525 inch(13.34 mm) Min

R 0.115 inch(2.93 mm) Min

0.156 X 0.156 inch

(3.96 mm X 3.96 mm)

Max. R 0.115 inch(2.93 mm) Min

3 Small Diameter Cylindrical Surface (area of pitch change knob contact)

NOTE: Some early production blades were manufactured with a small beveled area on the edge of the knob. This is not cause to retire the blade. Refer to Figure 2-17.

a Repair all damage, scratches, and abrasions within 0.125 inch (3.17 mm) of the small diameter radius. Damage can be repaired to 0.005 inch (0.12 mm) depth.

b Spot repairs must be blended so that the width of repair is a minimum of 40 times the damage depth.

c For up to 50 percent of the remaining surface area, scratches and abrasions up to 0.003 inch (0.07 mm) in depth are permitted.

d One local spot repair of the small diameter up to 0.005 inch (0.12 mm) below the minimum diameter is permitted. Blend smooth to 40 times the depth of the damage.

e The repaired area must not exceed 25 percent of the total surface area and must not extend more than 120 degrees around the knob.



Rev. 23 Mar/0861-13-33

f The minimum permitted diameter is 0.558 inch (14.18 mm). Local spot repair of 0.005 inch (0.12 mm) below the minimum diameter as previously described is permitted.

4 Large Diameter Fillet Radius:a The minimum permitted radius is 0.110 inch (2.80 mm).

CAUTION: DO NOT UNDERCUT THE BLADE BUTT SURFACE.b Rework as necessary.c Repairs in location "A" (where the cylindrical surface and

the radius meet) must maintain the minimum "large OD" in accordance with Figure 2-17 if manufactured with a large OD of 0.750 (19.05 mm).

5 Small Diameter Fillet Radius:a The minimum permitted radius is 0.115 inch (2.93 mm). b Rework as necessary. Refer to Figure 2-17.c Repairs in location "B" (where the cylindrical surface and the

radius meet) must maintain the minimum "small OD" of 0.558 inch (14.18 mm).

6 If the repair enters the large diameter cylindrical surface no more than 0.050 inch (1.27 mm) and extends no more than 0.187 inch (4.74 mm), localized repair on the corner edge of the large diameter cylindrical surface (location "C") is permitted. a The corner radius of the local repair must not be less than

0.115 inch (2.93 mm). b Localized repair is limited to one location and the repaired area

must not exceed 45 degrees of the knob circumference.7 Knob length is measured from the blade butt to the end of the knob.

The minimum permitted knob length is 1.322 inches (33.58 mm). 8 The minimum distance from the blade butt to the corner of the small

diameter fillet radius is 0.525 inch (13.34 mm).9 Penetrant inspect in accordance with the Penetrant Inspection

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

CAUTION: DO NOT SHOT PEEN NON "F" PITCH CHANGE KNOBS. IF NON "F" PITCH CHANGE KNOBS ARE SHOT PEENED THE BLADE MUST BE RETIRED FROM SERVICE.

10 If a non "F" pitch change knob is shot peened, the blade must be retired from service.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

(9) Shot Peen Requirements and Procedures

(a) Authorization to perform pitch change knob shot peening is contingent on approval from Hartzell Propeller Inc.

(b) For approved facilities and sampling program criteria, refer to the Approved Facilities chapter, Volume 9, of Hartzell Standard Practices Manual 202A (61-01-02).

(c) Almen test strips must be Almen "A" type.

(d) For information about necessary drawings and machine components to build an approved shot peen cabinet, contact the Hartzell Product Support department.

NOTE: The rolled compressive layer applied when a pitch change knob is manufactured may be compromised by damage, in service loads, rework, or wear.

(e) To reapply the compressive layer, "F" pitch change knobs must now be shot peened in accordance with the following requirements:

1 All "F" knobs on "Y" shank aluminum blades must be shot peened at next overhaul, if not previously accomplished.

2 All "F" knobs on "Y" shank aluminum blades used in aerobatic applications must be shot peened at every overhaul.

3 All "F" knobs on "Y" shank aluminum blades used in agricultural applications must be shot peened at every overhaul.

4 Damage, wear, or rework that exceeds the depth of the pebble grain surface requires that the entire knob be reshot peened before being returned to service.

5 All "F" knobs on "Y" shank aluminum blades involved in a foreign object strike requiring disassembly as defined in the Special Inspections chapter of Hartzell Standard Practices Manual 202A (61-01-02) must be shot peened before being returned to service.



Rev. 27 Sep/1161-13-33

(f) Knob Preparation

1 Using 120-grit sandpaper, break the edge on the end of the pitch change knob. a The edge break must not be greater than 0.030 inch (0.76 mm).

2 Break the edge on the corner of the large diameter cylindrical surface where it meets the small diameter radius.

NOTE 1: Breaking these edges will prevent them from expanding during shot peening.

NOTE 2: Failure to break the edge of the pitch change knob end will require additional sanding before installation of the pitch change knob bushing after shot peening.

a The edge break must not be greater than 0.020 inch (0.51 mm).3 Using solvent CM106, clean the blade shank, pitch change knob,

and blade bore in accordance with the Cleaning chapter of Hartzell Standard Practices Manual 202A (61-01-02).



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

Almen Strip Holder (DST-5855+35) Figure 2-18

almemstripholder

Almen Strip

Almen Strip Holder(DST-5855+35)



Rev. 23 Mar/0861-13-33

(g) Shot Type

1 Use S-330 Cast Steel or CW41 cut wire stainless steel, in accordance with the Shot Peening chapter, Volume 9, of Hartzell Standard Practices Manual 202A (61-01-02).

CAUTION: USE HARTZELL DST-5855(F) SHOT PEEN ASSEMBLY AND HARTZELL DST-5585-1F SHOT PEEN BLADE KNOB KIT WHEN SHOT PEENING "F" PITCH CHANGE KNOBS.

(h) Intensity Requirement

1 A process intensity of 0.012 - 0.015 inch (0.30 - 0.38 mm) Almen A is required.

2 For intensity determination and process control requirements, refer to the Shot Peening chapter, Volume 9, of Hartzell Standard Practices Manual 202A (61-01-02).

3 Fixture the Almen strips using Almen Strip Holder (DST-5855+35). Refer to Figure 2-18.

4 Because of the geometry of the feature being peened and the nature of its rotating exposure to the shot stream, it is required that peening time be measured in complete revolutions of the machine's turntable.

Example: A curve may consist of intensity measurements for 1, 2, 3, 4, 6, and 8 revolutions of the turntable.

(i) Coverage Requirement

1 Full coverage is required on both knob radii and the knob barrel between the radii.

2 Masking is required to protect the blade butt and bores from peening. Refer to Figure 2-21.

3 Partial coverage (overspray) is allowable on all knob surfaces not specified for full coverage on the blade butt area near the edges of the mask.



Rev. 23 Mar/0861-13-33

x

Angle of Incidence and Vertical Axis Figure 2-19

TI-00181

The vertical axis of the shot peen nozzle must be centered between the knob radii.

Small Diameter Fillet Radius

45 degrees

Pitch Change Knob Centerline

Shot peen nozzle

Angle

of Inc

idenc

e

Large Diameter

Fillet Radius



Rev. 23 Mar/0861-13-33

(j) Shot Peen Machine Settings

1 The following requirements must not be altered. Refer to Figure 2-19.a The angle of incidence is 45 degrees.b The vertical axis of the nozzle is a point centered between the

knob radii. Refer to Figure 2-19.c The horizontal axis for the nozzle is the centerline of the knob.d The required distance between the nozzle and shot peen

surface is 7.15 to 7.4 inches (181.7 to 188 mm).2 The following settings are recommended for the first intensity

determination curve. a To achieve the correct intensity, these settings may be adjusted

in accordance with the Troubleshooting section 2.D.(9)(j)3 of this chapter.

b The metering valve (DST-5855+24) must be open approximately 75 percent.

c The vacuum produced in the nozzle must be a minimum of 12 in. Hg (40.6 KPA).

d Clean dry air, volume greater than 50 CFM (1415 liter/min.) continuous capability with an 80 gallon (303 liter) minimum tank, must be available from the air compressor system to the shot peen cabinet.

e Adjust the regulator (DST-5855+29) until a deadhead reading of 90 PSI and continuous reading of 85 PSI, on the regulator gauge is achieved with the shot application valve (DST-5855+26) completely open.



Rev. 23 Mar/0861-13-33

3 Troubleshootinga Problem:

Pulsing or surging of shot is observed in the shot delivery tube.

Remedy:

1 If the metering valve is below 75 percent open, it can cause the flow to begin pulsing.

2 If the shot is still pulsing at 75 percent open, increase the amount that the metering valve is open.

3 Make sure that the shot is flowing through the shot delivery tube smoothly, without a visible pulsing flow.

b Problem:Vacuum pressure produced in the gun body is incorrect.

Remedy:1 Pull the shot delivery hose off the gun shot inlet. 2 Attach the vacuum gage and tube to the gun shot inlet. 3 Turn on the shot application valve. 4 Loosen the DST-5855+21 locknut.5 Adjust the DST-5855+22 air jet position until at least

12 in. Hg is achieved.c Problem:

Intensity is not in the target range after the first intensity determination curve.

CAUTION: IF INTENSITY CANNOT BE ACHIEVED, DO NOT EXCEED 110 PSI INPUT PRESSURE. VERIFY THE SHOT PEEN MACHINE SETTINGS AND MAKE SURE THAT THE CORRECT SHOT IS BEING USED.

Remedy:1 Start the intensity determination curve procedure with input

pressure at 90 PSI and raise or lower the input pressure in increments of 5 PSI.

2 Do not exceed 110 PSI. 3 After any adjustment to settings is made a new intensity

determination curve must be plotted.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

Align Mark Figure 2-20

alignmark

Alignment Mark for Approximate

Centerline of Knob



Rev. 23 Mar/0861-13-33

(k) Knob Shot Peening Procedure

CAUTION: CLEAN THE SHOT PEEN MACHINE THOROUGHLY. SHANK DAMAGE CAN RESULT IF THE BLADE IS CLAMPED INTO POSITION WHILE THERE IS LOOSE SHOT IN THE BLADE NESTING AREA.

1 Remove excess shot from any area of the machine that contacts the blade.

2 Clean and lubricate the blade butt mask (DST-5855+48).

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 BLADE.

CAUTION 2: DO NOT MARK DIRECTLY ON THE BLADE SHANK RETENTION RADIUS.

CAUTION 3: GRAPHITE (“LEAD”) PENCIL MARKS WILL CAUSE CORROSION.

3 Using a non-graphite pencil CM162 or equivalent, make a mark on the outer edge of the blade shank retention radius to indicate the approximate centerline of the pitch change knob. Refer to Figure 2-20.

NOTE: This mark will be used to position the blade when the pitch change knob cannot be seen.



Rev. 23 Mar/0861-13-33

Blade Butt Mask (DST-5855+48) Figure 2-21

Blade Butt Mask(DST-5855+48)

ButtBladeMask



Rev. 23 Mar/0861-13-33

CAUTION: TO AVOID DAMAGE TO THE BLADE BORE, WIPE AWAY ANY SHOT FROM THE GREASE USED TO LUBRICATE THE O-RING IN THE BLADE BORE MASK BEFORE INSTALLING THE NEXT BLADE.

4 Install the DST-5855+48 blade butt mask, centering the knob in the cut out. Refer to Figure 2-21.

CAUTION: DO NOT DAMAGE THE PITCH CHANGE KNOB WHEN PUTTING THE BLADE ON THE ROTATION PLATE.

5 Put the blade onto the rotation plate. 6 Position the pitch change knob so that the mark on the blade

retention area aligns with the alignment indicator on the rotation plate.7 Using the clamps, secure the blade.8 Using the rotation motor, move the timing indicator on the rotation

plate between the counter and the timing indicator on the top of the cabinet.

9 Reset the counter to "zero".

WARNING 1: CLOSE THE SHOT PEEN CABINET DOOR BEFORE USE. FAILURE TO CLOSE THE DOOR COULD CAUSE SERIOUS INJURY TO THE OPERATOR.

WARNING 2: EYE PROTECTION MUST BE WORN WHEN OPERATING THE SHOT PEEN CABINET. FAILURE TO WEAR EYE PROTECTION COULD CAUSE SERIOUS INJURY TO THE OPERATOR.

10 Turn on the rotation motor. 11 When the timing indicators are aligned, open the shot application

valve completely.

CAUTION: THE BLADE MUST ROTATE COMPLETE REVOLUTIONS. PARTIAL REVOLUTIONS ARE NOT PERMITTED.

12 The blade must rotate the number of complete revolutions as determined by the process qualification as developed per the Shot Peening chapter, Volume 9, of the Hartzell Standard Practices Manual 202A (61-01-02).

13 When the timing indicator on the rotation plate and the timing indicator on the top of the cabinet are aligned, close the shot application valve.

14 Turn off the rotation motor.



Rev. 23 Mar/0861-13-33




Rev. 27 Sep/1161-13-33

15 Unlatch the clamps that secure the blade.

CAUTION: DO NOT DAMAGE THE PITCH CHANGE KNOB WHEN REMOVING THE BLADE FROM THE ROTATION PLATE.

16 Remove the blade from the shot peen cabinet.

CAUTION: DO NOT DAMAGE THE PITCH CHANGE KNOB WHEN REMOVING THE BLADE BUTT MASK FROM THE BLADE. DO NOT PRY ON THE MASK, THIS WILL CAUSE DAMAGE TO THE BLADE.

17 Remove the blade butt mask by pulling on the short handle.(10) Inspection - After Shot Peening

(a) Using 120-grit sandpaper or a file, deburr the peened edge of the blade butt outside of the masked area.

1 A smooth, high quality finish is required.(b) Break the edge on the end of the pitch change knob as required for

installation of the pitch change knob bushing.

1 The break must not be greater than 0.030 inch (0.76 mm). 2 Removal of the pebble grain on the edge of the end of the knob is

permitted.(c) Using solvent CM106, clean the pitch change knob area and the

unmasked area to remove shot peen residue.

(d) Verify complete shot peen coverage on the surfaces required in the Coverage Requirement section, 2.D.(9)(i) of this chapter, in accordance with the Shot Peening chapter of Hartzell Standard Practices Manual 202A (61-01-02). The knob end and chamfer do not require complete coverage.

CAUTION: DO NOT USE ANODIZE IN THE BLADE RETENTION RADIUS OR THE PITCH CHANGE KNOB RADII.

(e) After inspection and rework to break the edge, apply a layer of chemical conversion coating to the pitch change knob and adjacent area.

(f) For approved conversion coating products, refer to the Chromic Acid Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02).



Rev. 23 Mar/0861-13-33

Pitch Change Knob Location Figure 2-22

3210

36° + knob angle

RIGHT HAND TRACTOR ORIENTATIONLEFT HAND TRACTOR ORIENTATION“J”

LEFT HAND PUSHER ORIENTATION“L”

RIGHT HAND PUSHER ORIENTATION“H”

36° + knob angle36° + knob angle

36° + knob angle

Trailing Edge Trailing Edge

Trailing EdgeTrailing Edge

Leading Edge Leading Edge

Leading Edge

Leading Edge



(11) Pitch Change Knob Bushing Installation

(a) For information about pitch change knob bushing installation, refer to the Special Adhesive and Bonding chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(b) Install the pitch change knob bushing, on the blade after completion of blade overhaul, or immediately before propeller assembly.

(12) Interchangeability of "Y" Shank Blades

(a) The pitch change knob of a "Y" shank blade has a defined location that depends on the blade model. Refer to Figure 2-22 and Table 2-4.

(b) All blades in a propeller assembly must have the same pitch change knob angle.

1 Matching one blade to another blade that has a different knob angle (by retwisting a blade to change a knob angle) is not permitted.

(c) Blades with shot peened knobs and blades with non-shot peened knobs are interchangeable.

(d) A propeller may contain blades with any combination of shot peened and non-shot peened knobs.

(e) Blades of one design may be reduced in length and substituted for a different design.

1 Such substitution is permitted with blades that have different knob angles (either higher or lower knob angle) as a complete set, but knob angle issues can arise that make the practice undesirable.

2 For example, an 8468A-4 (9 degree knob angle) may be reduced in length to -6S specification and used as a replacement for an 8468-6S (manufactured with a 12 degree knob angle). If a blade replacement is required in the future, there would be blade interchangeability problems that may require that all of the blades be replaced.

3 Substitution of a set of blades with different knob angles is permitted only if the low and high pitch angle limits of the propeller assembly can be established.



Rev. 34 Jan/1761-13-33

Blade Angle Blade Angle Blade AngleFC6660 10FC6660D 8FC6660DK 8FC6660K 10FC6890 9F(C)7063Q 12F(C)7068-2 11F7280 10F(C)7282 9FC7382 11F7391 9FC7391D 9F(C)7391D-3 12F7392 9F7392D 9F7392(S)-1 9F(J)C7451 12F7453 9F(J)C7453 9F(L)(C)7468 12F7468D, -2, -4 10.5F(C)7479 16FC7479-2R, -2Q 13F(C)7490 13F(C)7490D 13F7492 9F(C)7495S 10F7496(-1, -2) 10F(C)7497(D) 10F7497(D)-2 10FJC7497D 10F7498 11F7499(-1, -2) 10F7590 9F7590D(-1) 9F7663 11F7663-2(R) 11F7663-3 11F7663-4 11F7663-4Q, -6Q 11F7663-4R 11

F7663A-2(R) 9F7663A, -3, -3.5 9F7663A-4 9F7663A-6R 9F7663C 12F7663(D)-2Q 11F7663D-2R 9F7663D-3 11F7663D-4 9F7663DR 9F7663R 11F(C)7663R 11FC7663-2Q 12FC7663-4 9FC7663-4Q 11FC7663-4T 9FC7663-6 9FC7663-6Q 11FC7663-8R 12F(C)7663A-6 9FC7663D-2(R), (Q) 12FC7663D-3 11FC7663D-4, 4Q 9FC7663D-4(R) 9FC7663D-4T 9FC7663(D)-6Q 12FC7663D-8R 11FC7663DR 12FC7663E-6R 7FJ7663 11FJ7663-4 11FJ7663-6Q 11F(J)(C)7663 11F(J)C7663-2R 12F(J)C7663-4 9F(J)C7663-5R 9F(J)(C)7663D-6Q 12F(J)7663D-4,-2R 9F(J)C7663D-4Q 9FJC7663G-8 -19FL7663-2 9

FL7663-4R,-6R 9FL7663-10R 11F(L)C7663-4R 5FL7663D-2Q,-3 9FLC7663(D)F-2R 12FLC7663DG-2Q -14FLC7663F-2R 12FLC7663G-4R -14F7666 11F7666-2,-2R-4 11F7666A 10F7666A-2, -2R 10F7666A-3Q, -3R 10F7666A-4, -4Q 10F7666C-4 14FJC7666A 10F(J)C7666A-2(R) 10F(J)(C)7666A-2Q 10F(J)(C)7666A-3Q 10F(J)(L)C7666A 10F(J)(L)(C)7666A-4 10F(J)(L)(C)7666A-4(Q) 10F(J)(L)(C)7666D 10FL7666A 10FL7666A-2 10FL7666AS 10FL7666D-2 10FLC7666G-2 -14F7673-2R 9F7673DR 9FC7673DR 12F7681 11F7691 9F7691+2 9F7691D 9F7691D-3 97692(A) 10F7693(F)(-1, -2) 11F7693DF(-2) 11F7693(D)F+2 10FC7693DF(+1, +2, -2) 11

Pitch Change Knob Location (Degrees) Table 2-4


BLADE SHANK OVERHAUL 61-13-33 Page 2-76.1Rev. 34 Jan/17

Blade Angle Blade Angle Blade AngleF(J)C7666A-2(R) 10F(J)(C)7666A-2Q 10F(J)(C)7666A-3Q 10F(J)(L)C7666A 10F(J)(L)(C)7666A-4 10F(J)(L)(C)7666A-4(Q) 10F(J)(L)(C)7666D 10FL7666A 10FL7666A-2 10FL7666AS 10FL7666D-2 10FLC7666G-2 -14F7673-2R 9F7673DR 9FC7673DR 12F7681 11F7691 9F7691+2 9F7691D 9F7691D-3 97692(A) 10F7693(F)(-1, -2) 11F7693DF(-2) 11F7693(D)F+2 10FC7693DF(+1, +2, -2) 11FJC7693F(+1, +2) 11FLC7693DF(-2) 11F7694 11F7694-1 11F7694-2 11F7694-4T 15F7694D-6T 15FC7818 7F7854 9F7854-2 9F(J)C7854 9F8052 12.5F8052D 12.5F8068+2 10F8068 12F8068(D), -2 12

F8074 12F8459-2R 10F8459-4,-8R 10F8459-11Q 14F8459-18 13F8459A-4 9F8459A-4Q 10F8459A-6 9F8459A-8R 9F8459A-9R 9F8459A-11Q 9FC8459A-4 9FC8459-10R 10FC8459-12R 9FC8459-16R 9F(C)8459-18 9F(J)C8459-4,-8R 10FL8459A-10 9F8465 10F8465-2 16F8465-6 13F8465-7R, -8R 12F8465-10 10FC8465 14FC8465-6 14F8467-7R, -8R 11F(C)8467-7R 11FLC8467A-7R 15F8468 12F8468-2 12F8468-3R 12F8468-4 12F8468-5R 12F8468-6Q 5F8468-6S 12F8468-19 12F8468A(R) 9F8468A-2 9F8468A-2R 9F8468A-2R*1 9F8468A-3R 9

F8468A-4(R) 9F8468A-5R 9F8468A-6(R) 9F8468A-6Q 9F8468A-8(R) 9F8468A-8Q 9F8468A-10Q 9F8468A-12Q 9F8468AD-2R 9F8468A-6Q 9F8468AR 9F8468C 0F8468C-4 0F8468D-10R 12F8468R 12F8468T-12 12F(C)8468(R) 12F(C)8468-2R 10FC8468-3 12F(C)8468-6R,-7R 12F(C)8468-8(R),-10R 12F(C)8468-10Q 9FC8468A-6R 9FC8468A-8R 9FC8468AR 10FC8468D-6R 12FC8468D-8R 12FC8468(R) 12F(J)8468-10Q 12F(J)(C)8468-5R 12F(J)(C)8468-6Q 12F(J)(C)8468-6R 12F(J)(C)8468-7R 12F(J)C8468-8Q 12F(J)C8468-8R 12FJC8468-10Q 12F(J)C8468-10R 12F(J)(C)8468D-14 12FJC8468R 12F(L)8468-6R 12F(L)8468-10R 12

Pitch Change Knob Location (Degrees) ContinuedTable 2-4


BLADE SHANK OVERHAULPage 2-76.2

Rev. 34 Jan/1761-13-33

Blade Angle Blade Angle Blade AngleFL8468A-2R 9F(L)8468A-6(R) 9F(L)C8468-4R -14FLC8468G-2R -14FLC8468G-8Q -14F8475(R) 10F8475+2 9F8475-5Q 10F8475-6 12F8475D-2, -4, -6 10F8475F-6 9F8475T+2 12F8475FJ-4 10F8475JR 10FC8475+2 12FC8475-2 11FC8475-4 14FC8475-6 14FC8475-6R 7FC8475-8 14F(C)8475-9 14FC8475A-2,-4 11FC8475D 10FC8475E-4 8

F(C)8475F-6 9F(L)8475-4 14F(L)C8475R 14F8477 11F8477-1 11F8477-2 9F8477D-5R 11F8477(D)-6 11F(C)8477 11FC8477-2 11F(C)8477-4(R) 9FC8477-6(Q) 9FC8477-7, 8R 9FC8477A-4(Q) 11F(C)8477A-4(R) 11FC8477A-6Q 11FC8477A-7 11F(C)8477A-8R 11F8483 12F8483-2Q 12F9587A 16F9587A-7 12F9587A-10 12F9587C-13 5

F9587C-15 5F9587C-15S 5F9587C-17S 5F9587D-2 13FC9587A-18 16FC9587C-17 5FC9587D-2 5FC9587E-7 -15F(J)(C)9587A-10 12F(J)C9587A-15 9F9684 15F9684-1 15FC9684-4R -2.5FC9684C-6R 5F(J)C9684-3R 15FLC9684-12 -11FLC9684A-12 -15FC9684C-6R 5HE8218 5(H,L)E8492 5JD10541 0JE10305 -0.5LE8218 5

Pitch Change Knob Location (Degrees) ContinuedTable 2-4


BLADE SHANK OVERHAUL 61-13-33 Page 2-77Rev. 34 Jan/17




Rev. 29 Nov/1261-13-33

E. Pitch Change Bracket Mounting Holes

(1) All "D" and "E" shank aluminum blades use a removable pitch change bracket.

(2) For a four bladed propeller the pitch change bracket mounting holes are drilled on a 1.601 inch (40.66 mm) radius.

(a) Mounting holes manufactured for 1/4-28 UNF fasteners may be repaired with a Slimsert® TE410.

(b) Mounting holes that have been repaired with a Slimsert® TE410 may be repaired with a staked threaded insert (K-sert®), as necessary.

(c) Mounting holes manufactured for 5/16-24 UNF fasteners may not be repaired.

(3) For a fi ve bladed propeller the pitch change bracket mounting holes are drilled on a 1.85 inch (46.99 mm) radius.

(a) The mounting holes may be repaired with a Slimsert® TE410.

(b) Except on a (H,L)8218 blade, do not use a staked threaded insert (K-sert®).

(c) For the (H,L)8218 blade only

1 At overhaul or disassembly when the hub halves are separated, install a thin wall threaded insert (Slimsert®) TE410 in each pitch change bracket mounting hole.a Install the thin wall threaded inserts (Slimsert®) TE410 in

accordance with the instructions "Slimsert® TE410 Installation" in this section.

NOTE 1: Hartzell Propeller Inc. HE8218 blades with a serial number lower than J65603 and Hartzell Propeller Inc. LE8218 blades with a serial number lower than J65593, were manufactured without threaded inserts installed.

NOTE 2: Beginning in January, 2002, Hartzell Propeller Inc.aluminum blade model HE8218, with serial numbers J65603 and above, and Hartzell Propeller Inc. aluminum blade model LE8218, with serial numbers J65593 and above were manufactured with B-6986-258 (TE410) Slimserts® installed.

2 A staked threaded insert (K-sert®) may be used to repair a mounting hole for a (H,L)8218 blade only if it is replacing a previously installed staked threaded insert.



(4) Remove all Slimserts® and/or threaded staked inserts (K-sert®) before preforming pre-penetrant etch.

(a) Remove the existing Slimsert®, or threaded staked insert (K-sert®) in accordance with the Slimsert® Removal or Threaded Staked Insert Removal sections in the Aluminum Hub Overhaul chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).



Rev. 32 Nov/1561-13-33

(5) All pitch change bracket mounting hole repairs must be performed by qualified personnel at an appropriately licensed repair facility in accordance with the procedures listed below.

(a) Inspection

1 Accumulated thread damage exceeding one full thread in a pitch change bracket mounting hole must be repaired or the blade must be retired from service.

2 If the pitch change bracket mounting hole has a diameter greater than 0.221 inch (5.61 mm), a Slimsert® TE410 must be installed.

3 If the pitch change bracket mounting hole has a diameter greater than 0.287 inch (7.28 mm), a staked threaded insert must be installed.

4 A blade with a pitch change bracket mounting hole diameter greater than 0.339 inch (8.61 mm) must be retired from service.

(b) Slimsert® TE410 Installation

1 Modify both pitch change bracket holes in the blade.2 Make sure that the drill is concentric with the hole.3 Lock the setup in place.

CAUTION: DO NOT EXCEED 0.500 INCH (11.17 MM) DEPTH WHEN REMOVING THE EXISTING THREAD.

4 Ream a hole 0.281 +0.004/-0.001 inch (7.13 + 0.10/- 0.025 mm) diameter to a depth of 0.485 +/- .015 inch (12.32 mm).

5 Using a 5/16-24 GH-3 bottom tap, thread the hole to a minimum depth of 0.305 inch (7.750 mm).

6 Using compressed air, remove unwanted material.7 Visually inspect the tapped hole.8 Using solvent CM106, clean the tapped hole.9 Apply a layer of chemical conversion coating to the tapped holes

in accordance with the Chromic Acid Anodize chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

10 Machine off the counterbored end of the Slimsert® TE410 to remove the counterbore and the locking teeth.

11 Using a 1/4-28 UNF-3A bolt, check the fit of the Slimsert® TE410 before installation.



12 Put the modified Slimsert® TE410 on the installation tool TE314, modified end first.

13 Using Primer CM127, spray the Slimsert® TE410 and the newly tapped hole.

14 Permit a dwell time of 3 to 5 minutes before proceeding to the next step.

15 Using a clean cotton swab, apply retaining compound CM74 to the OD of the Slimsert® TE410.

16 Install the Slimsert® TE410 flush to 0.020 inch (5.1 mm) below the surface of the part.

17 Permit the repaired part to cure to fixture strength (approximately 15 minutes).

18 Using a 1/4-28 UNF-3A bolt, check the fit of the installed Slimsert®

TE410. 19 If the bolt does not fit, remove and replace the Slimsert® TE410 in

accordance with the instructions in this section.20 Permit the repaired part to cure for a minimum of twelve (12) hours at

room temperature before installing the pitch change bracket.



Rev. 23 Mar/0861-13-33

(c) Reinstalling a Slimsert® TE410

1 Remove the previously installed Slimsert® TE410 from the pitch change bracket attachment hole.a Use a locally procured "screw extractor" to remove Slimsert®

TE410.b Using a 5/16-24 GH-3 bottom tap, remove the adhesive residue.c If the adhesive residue cannot be completely removed with a

tap, use plastic media to remove the remaining adhesive.2 Using compressed air, remove unwanted material and visually

inspect the tapped hole.3 Using solvent CM106, clean the tapped hole.4 Apply a layer of chemical conversion coating to the tapped holes

in accordance with the Chromic Acid Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02).

5 Face off the counterbored end of the B-6986-258 Slimsert® TE410 to remove the counterbore and the locking teeth.

6 Using a 1/4-28 UNF-3A bolt, check the fit of the Slimsert® TE410 before installation.

7 Put the modified Slimsert® TE410 on the installation tool TE314, modified end first.

8 Using Primer CM127, spray the Slimsert® TE410 and the hole. 9 Permit a dwell time of 3 to 5 minutes before proceeding to the next

step.10 Using a clean cotton swab, apply Retaining Compound CM74 to the

OD of the Slimsert® TE410.11 Install the Slimsert® TE410 flush to 0.020 inch (5.1 mm) below the

surface of the part.12 Permit the repaired part to cure to fixture strength (approximately 15

minutes).13 Using a 1/4-28 UNF-3A bolt, check the fit of the installed Slimsert®

TE410. 14 If the bolt does not fit, remove and replace the Slimsert® TE410 in

accordance with the instructions in this section.15 Permit the repaired part to cure for a minimum of twelve (12) hours at

room temperature before installing the pitch change bracket.



Rev. 23 Mar/0861-13-33

(d) Installing a Staked Threaded Insert

1 Modify both pitch change bracket holes in the blade.

CAUTION: A B-6143-4 STAKED THREADED INSERT MAY BE USED IN A (H,L)E8218 BLADE ONLY IF IT IS REPLACING A PREVIOUSLY INSTALLED STAKED THREADED INSERT.

2 Make sure that the drill is concentric with the hole.3 Lock the setup in place.4 Drill a hole 0.323 inch (8.20 mm) +0.007 (0.17 mm), -0.002

(0.05 mm) diameter by 0.648 inch (16.45 mm) maximum depth to point of drill.

5 Ream the minor diameter 0.331 inch (8.40 mm) to 0.336 inch (8.53 mm) by 0.555 inch (14.09 mm) maximum depth. a The reamer must have a tip radius of 0.030 inch (76 mm).

6 Thread the hole to 3/8-16UNC-2B MOD, 0.430 inch (10.92 mm). a Minor diameter 0.331 (8.40 mm) to 0.336 (8.53 mm) MOD

(MOD indicates nonstandard minor diameter). b Maintain a bore corner radius of 0.030 inch (0.76 mm).

7 Chamfer to a depth of 0.390 (9.90 mm) ± 0.005 inch (0.12 mm) by 90 degrees included angle.

8 Using compressed air, remove unwanted material. 9 Inspect the tapped hole.10 Install a B-6143-4 staked threaded insert 0.010 (0.25 mm) to 0.030

inch (0.76 mm) below the blade butt surface. 11 Drive the locking keys down flush with the insert.12 Using a 1/4-28 UNF-3A bolt, check the fit of the installed staked

threaded insert.



Rev. 25 Apr/0961-13-33

(e) Reinstalling a Staked Threaded Insert

CAUTION: A B-6143-4 STAKED THREADED INSERT MAY BE USED IN A (H,L)E8218 BLADE ONLY IF IT IS REPLACING A PREVIOUSLY INSTALLED STAKED THREADED INSERT.

1 Remove the existing threaded staked insert in accordance with the Threaded Insert Removal section in the Aluminum Hub Overhaul chapter of Hartzell Standard Practices Manaul 202A (61-02-02).

2 Using compressed air, remove unwanted material.3 Visually inspect the tapped hole.4 Install a B-6143-4 staked threaded insert 0.010 to 0.030 inch

(0.25 to 0.76 mm) below the surface of the blade butt.5 Make sure that the locking keys are located in an area where keys

have not been previously installed.6 Drive the locking keys down flush with the insert.7 Using a 1/4-28 UNF-3A bolt, check the fit of the installed staked

threaded insert.



Blade Plug and Spacer Inspection Criteria Table 2-4.1

Inspect Serviceable Limits Corrective Action

Blade Plug or Spacer

(1) For a blade plug or spacer, visually examine the blade plug or spacer for corrosion and pitting.

Corrosion is not permitted. The maximum permitted depth of pitting is 0.005 inch (0.12 mm). For a blade plug, pitting is not permitted where the pitting would be in direct contact with the preload plate set screw. Pitting may not cover more than 10% of the blade plug or spacer surface.

Using glass bead cleaning, remove corrosion to a maximum depth of 0.005 inch (0.12 mm). Refer to the Cleaning chapter of Hartzell Propeller inc. Standard Practices Manual 202A (61-01-02). If the depth of the damage or cleaning is more than the permitted serviceable limits, replace the blade plug or spacer.

(2) For a blade plug, visually examine the blade plug for wear or scoring damage in the contact area of the preload plate set screw. Refer to Figure 2-22.1.

The maximum permitted depth of wear or damage is 0.004 inch (0.10 mm) beyond the surrounding undamaged surface. The surface finish in the area of contact with the preload set screw must be 30 Ra or smoother. If the blade plug is worn or damaged, measure the depth of wear or damage.

Using an abrasive pad CM47 or equivalent, polish to remove wear or damage and maintain a surface finish of 30 Ra or smoother. If wear or damage is more than the permitted serviceable limits or the repair limits, replace the blade plug. The maximum permitted depth of repair is 0.004 inch (0.10 mm) beyond the surrounding unrepaired surface.

(3) For a blade plug or spacer, visually examine the blade plug or spacer for scratches, gouges, or other damage, outside of the contact area of the preload plate set screw.

The maximum permitted depth of damage is 0.005 inch (0.12 mm). Damage must not interfere with the fit of the blade plug or spacer in the blade bore.

Using an abrasive pad CM47 or equivalent, polish pushed up material to blend with the surrounding surfaces. If damage is more than the permitted serviceable limits, replace the blade plug or spacer.

(4) For a blade plug or spacer, visually examine the blade plug or spacer for plating coverage if applicable.

Minor wear on corners and a few light random scratches are permitted; otherwise, plating must completely cover the blade plug. A steel blade plug or a steel spacer must be completely covered with cadmium plating.

If the plating coverage is less than the permitted serviceable limits, replate in accordance with the appropriate chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(5) For a spacer, visually examine the spacer for thread damage.

A-1349 Spacer: 1/2 of one thread total accumulated damage is permitted.

A-1499 Spacer: 1/2 of one thread total accumulated damage is permitted.

A-1599 Spacer: one thread total accumulated damage is permitted.

If the depth of the damage is more than the permitted serviceable limits, replace the spacer.



Rev. 35 Nov/1761-13-33

Blade Plug and Spacer Inspection AreaFigure 2-22.1

F. Blade Balance Hole Inspection and Overhaul

(1) The procedures in this section are required for all aluminum propeller blades manufactured by Hartzell Propeller Inc.

(2) Remove and discard the bearing(s) from the blade bore.

(a) Using local tooling methods or bearing puller TE102, TE103, TE104, or TE106 and a hydraulic or pneumatic press, remove the bearing(s).

(b) Remove the blade plug or spacer, as applicable.

NOTE: Shank spacer puller TE537 or TE538 are available for use when removing the blade plug or spacer. Refer to Hartzell Propeller Inc. Illustrated Tool and Equipment Manual 165A (61-00-65).

1 Inspect the blade plug or spacer in accordance with Table 2-4.1.(3) Remove Lead From Balance Hole

(a) Option 1 - Water Jet Method (Preferred)

1 Necessary requirementsa Adjustable water jet systemb The maximum permitted chloride content in the water supply

is 10 ppm.c Recycled water supplies must have sufficient filtration to remove

lead and other particulates from the water supply.

Preload Plate Set Screw Contact Area

AP

S62

84, A

1349

A-1349 Spacer

Blade Plug

Threads



CAUTION: USE ADEQUATE RESTRAINTS TO HOLD THE BLADE SECURELY DURING THE LEAD REMOVAL PROCEDURE.

2 Put the blade in a locally fabricated fixture that holds the blade horizontally at approximately the 12 and 20 inch blade stations.

CAUTION: THE WATER USED IN THE WATER JET PROCESS BECOMES A HAZARDOUS MATERIAL BECAUSE OF LEAD CONTAMINATION. USE AN APPROVED METHOD FOR DISPOSAL OF THE WATER.

3 Attach a 0 degree nozzle head to the wand of the water jet.

WARNING 1: ALWAYS WEAR PROTECTIVE CLOTHING AND EAR AND EYE PROTECTION DURING THE WATER JET PROCESS BECAUSE OF THE HIGH WATER PRESSURE AND NOISE LEVELS.

WARNING 2: DO NOT STAND IN THE PATH OF THE WATER JET NOZZLE WHEN THE SYSTEM IS OPERATING. INJURY FROM THE HIGH PRESSURE WATER COULD RESULT.

4 Put the wand in the blade bore, aimed at the balance hole.

CAUTION: DO NOT EXCEED 10,000 PSI (689.4 BARS) DURING THE WATER JET PROCESS. DAMAGE TO THE BALANCE HOLE COULD RESULT.

5 Increase the pressure on the regulating valve of the water jet system to supply just enough pressure to begin to remove the lead wool.

6 Visually inspect the balance hole to make sure that all of the lead wool has been removed.

7 If any lead wool remains in the balance hole, repeat steps 2.F.(3)(a)4 through 2.F.(3)(a)6.

8 Drain all of the water from the balance hole.9 Using clean compressed air, remove any residual water.10 Completely dry the balance hole.

(b) Option 2 - Modified Drill1 Using a radius gauge, create a 23/64 inch radius on the cutting end

of a 23/32 inch drill bit.

CAUTION: DO NOT DAMAGE THE WALLS OF THE HOLE OR DRILL INTO THE BLADE MATERIAL AT THE BOTTOM OF THE HOLE.

2 Refer to the hole depth stamped on the blade butt and use a depth gauge to monitor the depth being drilled.

3 Remove the lead by drilling into the balance hole.4 Using compressed air, blow residue from the balance hole.



Rev. 24 Nov/0861-13-33

(4) Clean Balance Hole

(a) Visually inspect the balance hole to make sure that any materials that may prevent visual inspection, such as paint or grease, have been removed.

1 Using a soft, clean cloth dampened with solvent CM22 or CM23, remove any material that may remain in the balance hole.

2 Permit the balance hole to thoroughly dry.(5) Dimensionally Inspect Balance Hole

(a) Measure the Depth

1 Using a depth gauge, measure from the blade butt to the bottom of the balance hole.

CAUTION: DO NOT CHANGE THE DIMENSION STAMPED ON THE BLADE BUTT.

a This measurement can be 0.125 inch (3.17 mm) greater than the hole depth stamped on the blade butt. For example, if the depth stamped on the butt is 5.375 inches (136.52 mm), the maximum permitted depth is 5.50 inches (139.7 mm).

b If a blade has a balance hole depth greater than the maximum permitted depth, retire the blade from service.

c Hartzell service documents previously stated that a depth of 6.50 inches (165.1 mm) was permitted on all but a few blades. Current rework of all blades is limited to 0.125 inch (3.17 mm) greater than the depth stamped on the blade butt.

(b) Measure the Diameter of the Critical Area of the Balance Hole

1 Using a micrometer, measure the diameter of the bottom 1 inch (25.4 mm) of the balance hole.a The maximum diameter for the balance hole of a blade

that cannot be reworked using reamer TE208( ) is 0.771 inch (19.58 mm).

b The maximum diameter for the balance hole of a blade that can be reworked using reamer TE208( ) is 0.786 inch (19.96 mm).

c If a blade has a balance hole diameter greater than the maximum permitted in the bottom 1 inch (25.4 mm), retire the blade from service.



(6) Inspect and Repair the Critical Area of the Balance Hole. Refer to Figure 2-23.

(a) Using a strong source of light, visually inspect the bottom 1 inch of the balance hole for corrosion, tool marks, or anodize.

1 Corrosion or anodize are not permitted.2 Tool marks, wear, or scuff marks that are below the shot peen pebble

grain surface are not permitted.a The balance hole may have a slightly different depth than

the dimension stamped on the blade butt because the manufacturing tolerance for the depth of balance holes is plus or minus 0.063 inch (1.60 mm). For example, a blade stamped 6.375 inches (161.92 mm) may actually have a depth between 6.312 and 6.438 inches (160.32 and 163.52 mm).

b Depending on the actual depth of the balance hole, the amount of material that may be removed for repair can vary significantly.

c Closely monitor the depth of the balance hole throughout the repair process.

CAUTION: DO NOT REMOVE EXCESSIVE MATERIAL FROM THE BOTTOM OF THE BALANCE HOLE.

(b) The maximum depth of the balance hole is 0.125 inch (3.17 mm) greater than the dimension stamped on the butt of the blade.

(c) If the depth of the balance hole is greater than 0.125 inch (3.17 mm) deeper than the hole depth stamped on the blade butt, retire the blade from service.

(d) If there is corrosion or damage in the bottom 1 inch (25.4 mm) of the balance hole, or if there is anodize in the balance hole:

1 Secure the blade in a drill press or lathe.

NOTE: The use of machine coolant during reaming is recommended.

2 Using the smallest reamer TE207( ) possible to achieve the desired results, ream the balance hole.

(e) If all indications of corrosion, damage, or anodize are not removed in the bottom 1 inch (25.4 mm) of the balance hole, refer to Table 2-5 to determine if use of reamer TE208( ) is permitted.

(f) Dimensionally inspect the bottom 1 inch (25.4 mm) of the balance hole in accordance with section 2.F.(5) of this chapter.

1 If use of the reamer TE208( ) is not permitted, retire the blade from service.



Rev. 31 Jul/1461-13-33

Critical Area of the Balance Hole Figure 2-23

Sco

tmod

a

0.375 inch (9.525 mm) radius

Bottom 1 inch (25.4 mm) area of the balance hole

Cylindrical portion of the balance hole, excluding the bottom 1 inch (25.4 mm) area


BLADE SHANK OVERHAUL 61-13-33 Page 2-90.1Rev. 31 Jul/14

Blades that Cannot Use the TE208( ) Reamer Table 2-5

Blade Model Serial NumberT10173 B85887 And Lower

T10173H B85887 And LowerT10176 B85887 And Lower

T10176H B85887 And Lower("Y" shank blade) 7663 B35571 And Lower

All other "Y" shank blades B93055 And Lower

(g) If use of the reamer TE208( ) is permitted:

1 Using the smallest reamer TE208( ) possible to achieve the desired results, ream the balance hole.

NOTE: The use of machine coolant during reaming is recommended.

2 If all indications of corrosion, damage, or anodize are not removed in the bottom 1 inch (25.4 mm) of the balance hole, retire the blade from service.

3 Dimensionally inspect the bottom 1 inch (25.4 mm) of the balance hole in accordance with section 2.F.(5) of this chapter.



Rev. 31 Jul/1461-13-33

Tool for Balance Hole Polishing Figure 2-23.1

The Length of the Slot is Approximately 1.5 Inches (38 mm)

The Width of the Slot is Approximately 0.125 Inch (3.17 mm)

A piece of very fine abrasive pad CM47 or equivalent, approximately 3 inches x 3 inches (76 mm x 76 mm) installed in the slot of the tool extension

Tool ExtensionTP

I-133

-101

,102


BLADE SHANK OVERHAUL 61-13-33 Page 2-91Rev. 31 Jul/14

CAUTION: USING THIS PROCEDURE FOR LOCAL REPAIR IS NOT PERMITTED.

4 Use one of the following two procedures to remove any tool marks caused by the reamers TE207( ) and TE208( ).a Procedure 1

1 Modify a tool extension to add a groove. Refer to Figure 2.23.1.

2 Cut a piece of very fine abrasive pad CM47, or equivalent, approximately 3 inches x 3 inches (76 mm x 76 mm).(a) The size of the very fine abrasive pad CM47, or

equivalent, may be adjusted for the size of the balance hole.

3 Put the very fine abrasive pad CM47, or equivalent, in the groove in the tool extension.

4 Polish the balance hole until the tool marks are removed.b Procedure 2

1 Modify a 3M Scotch Brite® medium grade 7AS 1x1x3/16 polish and grinding wheel so that it fits inside a balance hole. Refer to Figure 2-23.2.

2 Attach the modified polish and grinding wheel to a tool extension.

3 Polish the balance hole until the tool marks are removed.(h) When all indications of tool marks are removed in the bottom 1 inch

(25.4 mm) of the balance hole, dimensionally inspect that area of the balance hole in accordance with section 2.F.(5) of this chapter.

3M Scotch Brite® Grinding Wheel Modification Figure 2-23.2

Modify the Scotch Brite® grinding wheel diameter and radius to conform to the balance hole bore.

Sco

tmod

1,2



Rev. 31 Jul/1461-13-33

(7) Inspection and Repair of the Cylindrical Portion of the Balance Hole

(a) Balance hole local repair excluding the bottom 1 inch (25.4 mm) area:

CAUTION: A PORTION OF THE REPAIRED AREA MUST NOT EXTEND INTO THE BOTTOM 1 INCH (25.4 mm) AREA OF THE BALANCE HOLE.

1 Remove any corrosion or damage in the cylindrical portion of the balance hole.

2 The maximum permitted depth of local repair in the cylindrical portion of the balance hole outside of the bottom 1 inch (25.4 mm) area is 0.030 inch (0.76 mm).

3 Using a fine emery cloth or abrasive pad CM47 or equivalent, remove damage.

4 Blend the polished area with the surrounding area while removing as little material as possible.

(b) Inspect the balance hole using eddy current.

1 Perform eddy current inspection in accordance with the Eddy Current Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

2 If there is a relevant indication, retire the blade from service.(8) Shot Peen Balance Hole

(a) If a repair was performed on the balance hole, reshot peen the interior surface of the balance hole.

(b) For the general shot peening procedures, refer to the Shot Peening chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(c) For facilities approved for shot peening, refer to "Sample Program Approvals" on the Hartzell Propeller Inc. website at www.hartzellprop.com.



Rev. 24 Nov/0861-13-33

(d) Shot peen the inside of the blade balance hole in area "B", paying particular attention to the intersection of the cylindrical and semi-spherical surfaces. NOTE: Shot peen gun TE379 is available for this procedure. Refer to

Hartzell Tool and Equipment Manual 165A (61-00-65).1 For blades with shank "MV" with "N" modification, "V", "V" with "N"

modification, "V" with "MV" modification, "V" modified to "MV" with "N" modification, "X", and "X" with "V" modification, refer to Figure 2-24.

2 For blades with shank "D", "E", "M", "M" with "N" modification, "P", "P" with "N" modification, "P" modified to "R", "R", "R" with "N" modification, "T", "T" with "N" modification, "W", "W" with "N" modification, "Y", "Z", "Z" modified to "W", and "Z" with "N" modification, refer to Figure 2-25.

3 Mask the bearing bore with the specified shot peen plug. Refer to Table 2-6.

4 To control shot peen coverage, thread the gun body through a nut and feed the gun into the bottom of the hole, if applicable.

5 Shot peen the blade balance hole using the shot size and intensity specified in Table 2-6. a Area "A" ("V" or "MV" with "N" modification only) must have full

coverage. b with the exception of Area "D", Area "B" must have full coverage.

Refer to Figure 2-25 and Figure 2-26. c Overspray is permissible in the spherical end of the balance

hole (Area "D") radiating outward from the center to 45 degrees ± 20 degrees in each direction.

d For bores that have a balance hole less than 1.50 inches (38.10 mm) in length (Area "B"), the shot peen must terminate before the inboard end of the balance hole. The shot peen may deviate from full coverage within Area "E". Refer to Figure 2-25.

e Shot peen overspray is permitted in Area "C". Refer to Figures 2-25 and 2-26.

6 Using shot peen plug removal tool TE110, or equivalent, remove the shot peen plugs, if applicable.

7 Using cleaning solvent CM23, clean the inside of the balance hole.8 Using a borescope or dental mirror, inspect the blade balance hole

after shot peening. a The bottom of the hole must be uniform and rounded, with no

corrosion, scratches, or tool marks.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

ASK1305b

For "MV" with "N" modification, "V", "V" with "N" modification, "V" with "MV" modification, "V" modified to "MV" with "N" modification, "X", and "X" with "V" modification

Shank Blades

Area "B" 1.50 ± 0.25 Inches (38.1 ± 6.3 mm)

Area "D" 45 degrees ± 20 degrees

Area "A" applies to "V" shank blades with "N" modification and "MV" shank blades with "N" modification only.

Area "A"

Area "C"

Shot Peening Lead Balance Hole in Blade Figure 2-24



Rev. 23 Mar/0861-13-33

Area "E"0.125 Inch (3.18 mm) maximum shot peen coverage deviation

Area "D" 45 degrees ± 20 degrees

Area "C"

On bores that have a balance hole less than 1.50 inches (38.1 mm) in length (Area "B"), the shot peen must terminate before the inboard end of the balance hole. The shot peen may deviate from full coverage within Area "E".

*

Area "B" 1.50 ± 0.25 inches (38.1 ± 6.3 mm)

*

Shot Peening Lead Balance Hole Figure 2-25

ASK1311A

For "D", "E", "M", "M" with "N" modification, "P", "P" with "N" modification, "P" modified to "R", "R", "R" with "N" modification, "T", "T" with "N" modification, "W", "W" with "N" modification,

"Y", "Z", "Z" modified to "W", and "Z" with "N" modification Shank Blades



Rev. 23 Mar/0861-13-33

Balance Hole Shot Peen Specifications Table 2-6

Description Shot Peen Plug Shot SizeAlmenType

Intensity

"E" shank blades TE90

Use shot media ASR 550 (Refer to

AMS-2431/1) or S-550

(Refer to [MIL] AMS-S-13165)

A

0.013 - 0.017 Inch

(0.33 - 0.43 mm)

Minimum

"W" shank blades TE91

"Y" and "D" shank blades TE87

"M" and "T" shank blades TE88

"M" and "T" shank blades with "N" modification TE89

"P", "Z", "R", "P" with "R" modification, and "Z" with "W" modification shank blades

TE92

"P", "R", "W", and "Z" shank blades with "N" modification TE458

"X", "V", "V" modified to "MV", and "X" with "V" modification shank blades

TE371

"V" and "MV" shank blades with "N" modification.

(Refer to Figure 2-24)

For area "B": TE371

For area "A": TE372

G. Blade Bore Inspection and Overhaul

(1) The procedures in this section are required for all single and double shoulder aluminum propeller blades manufactured by Hartzell Propeller Inc.

(2) Remove the needle bearing(s), blade bushing(s), and spacer(s), as applicable.

NOTE: "Y", "D", and "E" shank bearing removal was accomplished for compliance with the Blade Balance Hole Inspection and Overhaul section of this chapter.

(a) Using local tooling methods or TE101 if applicable, remove the blade bushing.



Rev. 23 Mar/0861-13-33

(b) Using local tooling methods or TE102, TE103, TE104, or TE106 and a hydraulic or pneumatic puller, remove the bearings.

1 If a shank has an inboard and an outboard bearing, pull the inboard bearing first.

2 Discard all used needle bearings.3 Discard all used blade bushings.

(c) Remove the bearing spacer.

1 Steel bearing spacers must be completely covered with cadmium plating.

2 Replate the steel bearing spacers with cadmium before reinstallation, or replace with a new bearing spacer.

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

(3) Clean Blade Bore

(a) Using solvent CM22, CM23, or CM106, clean the blade bore area of all paint, grease, and sealants.

(b) Permit the blade bore to thoroughly dry.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

Inspect this Area for Corrosion and Damage

Inspect Blade Bore Radius(Critical Area)

Visual Inspection Area Of Blade Bore Figure 2-26

SHANK6



Rev. 23 Mar/0861-13-33

(4) Inspect Blade Bore

(a) Visual Inspection

1 Using a borescope or light and mirror, inspect the blade bore for surface blemishes, tool marks, scratches, and corrosion. Refer to Figure 2-26.

2 Using a borescope or light and mirror, inspect the blade bore for anodize.

3 Rework as necessary to remove any anodize. (b) Dimensional Inspection

1 Inspect the blade bore depth. a If a blade has a bore depth more than the maximum bore depth

limits specified in Section 2.G.(5) of this chapter, retire the blade from service.

2 Inspect the blade bore diameter(s). a If a blade has a bore diameter more than the bore diameter

limits specified in Section 2.G.(5) of this chapter, retire the blade from service.



Rev. 27 Sep/1161-13-33

(5) Rework Blade Bearing/Bushing Bore

(a) Rework of damage, corrosion, or anodize removal in the critical area of the blade bore.

1 Except for blade shanks with "N" modification, the critical area extends 0.300 inch (7.62 mm) from the base of the blade bore.

CAUTION: A SMOOTH, HIGH QUALITY FINISH IS REQUIRED ON THE BLADE BORE RADIUS. MAINTAIN THE SPECIFIED RADIUS.

2 Using an abrasive cartridge or patch and a drill, remove evidence of damage and irregularities.

3 Maintain the specified radius.4 When a blade bore has damage, corrosion, or anodize that requires

rework beyond the maximum permitted depth or critical diameter, the blade must be retired from service. a For "X", "X" modified to "V", and "X" modified to "MV" without

"N" modification blade shanks, refer to Figure 2-27 and Table 2-7: 1) The maximum permitted bore depth after rework is

4.091 inches (103.91 mm). 2) The maximum permitted critical area diameter after rework

is 1.583 inches (40.20 mm). 3) If the critical area diameter is maintained, local repair in the

critical area not more than 0.010 inch (0.25 mm) at any one point is permitted.

b For "V", and "V" modified to "MV" without "N" modification blade shanks, refer to Figure 2-28 and Table 2-7: 1) The maximum permitted bore depth after rework is






Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33

Bore Dimensions Table 2-7

Blade ShankMaximum

Permitted CriticalArea Diameter

Maximum Permitted BladeBore Diameter

MaximumPermitted Center

Bore Diameter

MaximumPermitted Inboard

Bore Diameter

Maximum Permitted Blade

Bore Depth

*Critical AreaShot PeenRequired

**Maximum Permitted

(Critical Area)Repair Limit

"D" 1.5635 inches (39.712 mm)

1.5035 inches (38.188 mm) n/a n/a 1.797 inches

(45.64 mm) No 0.030 inches (0.76 mm)

"E" 1.4385 inches ( 36.538 mm)


(39.31 mm) No 0.030 inches (0.76 mm)

"M" 1.795 inches (45.59 mm)

1.7535 inches (44.538 mm) n/a 2.1278 inches

(54.046 mm)4.091 inches (103.91 mm) No 0.020 inches

(0.51 mm)

"M" with "N" mod n/a 1.7535 inches

(44.538 mm)1.800 inches (45.72 mm)

2.1278 inches (54.046 mm) n/a No 0.020 inches

(0.51 mm)

"MV" with "N" mod n/a 1.5055 inches

(38.239 mm) n/a 1.563 inches (39.70 mm) n/a Yes 0.010 inches

(0.25 mm)

"P" 1.802 inches (45.77 mm)


(103.91 mm) No 0.010 inches (0.25 mm)

"P" with "N" mod n/a 1.782 inches

(45.26 mm) n/a n/a n/a No 0.020 inches (0.51 mm)

"P" modified to "R"

1.802 inches (45.77 mm)


(103.91 mm) No 0.010 inches (0.25 mm)

"R" 1.773 inches (45.03 mm)



(0.25 mm)

"R" with "N" mod n/a 1.7535 inches

(44.538 mm)1.770 inches (44.958 mm)


(0.51 mm)

"T" 1.795 inches (45.59 mm)



(0.51 mm)

"T" with "N" mod n/a 1.7535 inches

(44.538 mm)1.800 inches (45.72 mm)


(0.51 mm)

"V" 1.583 inches (40.20 mm)



(0.25 mm)

"V" with "N" mod n/a 1.5055 inches


(0.25 mm)

"V" modified to "MV"

1.583 inches (40.20 mm)



(0.25 mm)

"V" modified to "MV"

with "N" modn/a 1.5055 inches


(0.25 mm)

"W" 1.773 inches (45.03 mm)



(0.25 mm)

"W" with "N" mod n/a 1.7535 inches

(44.538 mm)1.770 inches (44.958 mm)


(0.51 mm)

"X" 1.583 inches (40.20 mm)


(103.91 mm) No 0.010 inches (0.25 mm)

"X" modified to "V"

1.583 inches (40.20 mm)


(103.91 mm) No 0.010 inches (0.25 mm)

"X" modified to "MV"

1.583 inches (40.20 mm)

1.563 inches (39.70 mm) n/a n/a 4.091 inches (

103.91 mm) No 0.010 inches (0.25 mm)

"Y" 1.5635 inches (39.712 mm)


(45.64 mm) No 0.030 inches (0.76 mm)

"Z" 1.802 inches (45.77 mm)


(103.91 mm) No 0.010 inches (0.25 mm)

"Z" modified to "W"

1.802 inches (45.77 mm)


(103.91 mm) No 0.010 inches (0.25 mm)

"Z" with "N" Mod n/a 1.782 inches

(45.26 mm) n/a n/a n/a No 0.020 inches (0.51 mm)

*All reworked balance holes must be re-shot peened. Blades identified with “yes” in this column require re-shot peening in the critical area and balance hole if either area was reworked.

**When reworking bores to the maximum permitted critical area repair limit, the maximum permitted critical area diameter must be maintained.



Rev. 23 Mar/0861-13-33

The maximum permitted

bore depth is 4.091 inches (103.91 mm).

"X", "X" Modified to "V", or "X" Modified to "MV" Shank Figure 2-27

Remove no more than 0.010 inch (0.25 mm) at any point.

The maximum permitted bore diameter is 1.563 inches (39.70 mm). Remove no more than 0.010 inch (0.25 mm) for any localized repair.

0.094 inch (2.38 mm) minimum radius

Critical area 0.300 inch(7.62 mm)

The maximum permitted diameter for the critical area is 1.583 inches (40.20 mm).

1001



Rev. 27 Sep/1161-13-33

TI-133003

"V" or "V" Modified To "MV" Shank Figure 2-28








The maximum permitted inboard bore diameter is 1.563 inches (39.70 mm). Remove no more than 0.010 inch (0.25 mm) for any localized repair.



Rev. 23 Mar/0861-13-33


Shot Peening is required in this area.

Critical area

"V" and "V" Modified To "MV" With "N" Modification Figure 2-29




Change in bore depth is not permitted

1003



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

1004

"MV" Shank With "N" Modification Figure 2-30




Shot Peening is required in this area.


Change in bore depth is not permitted.

Critical Area



Rev. 23 Mar/0861-13-33



"R" or "W" Shank Figure 2-31





Critical area 0.300 inch (7.62 mm)

1006

No more than 0.010 inch (0.25 mm) may be removed at any point.



Rev. 23 Mar/0861-13-33



1005

"P", "P" Modified to "R", "Z", or "Z" Modified to "W" Shank Figure 2-32

No more than 0.010 inch (0.25 mm) may be removedat any point.







Rev. 23 Mar/0861-13-33

"R" or "W" Shank with "N" Modification Figure 2-33

1020

Critical Area0.865 inch (21.97 mm) minimum radius


Remove no more than 0.020 inch (0.51 mm) for any localized repair in the critical area.

The maximum permitted outboard bore diameter is 1.7535 inches (44.538 mm). Remove no more than 0.010 inch (0.25 mm) for any localized repair.

The maximum permitted center bore diameter is 1.77 inches (44.9 mm). Remove no more than 0.010 inch (0.25 mm) for any localized repair.


The transition area between the two diameters has been exaggerated on this drawing. The transition area must be smooth.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

Critical Area



Remove no more than 0.020 inch (0.51 mm) for any localized repair in critical area.

"P" and "Z" Shank with "N" Modification Figure 2-34

1019




Rev. 23 Mar/0861-13-33

"T" or "M" Shank Figure 2-35

1009

The maximum permitted bore

depth after reworkis 4.091 inches (103.91 mm).


The maximum permitted bore diameter is 1.7535 inches (44.538 mm).No more than 0.010 inch (0.25 mm) may be removed for any localized repair.

Critical area 0.300 inch(7.62 mm


The maximum permitted inboard bore diameter is 2.1278 inches (54.046 mm).

Refer to Figure 2-37 tapered bore

rework tolerances.

No more than 0.020 inch (0.50 mm) may be removed at any point.



Rev. 23 Mar/0861-13-33

"T" or "M" Shank With "N" Modification Figure 2-36

1010


The maximum permitted outboard bearing bore diameter is 1.7535 inches (44.538 mm). Remove no more than 0.010 inch (0.25 mm) for any localized repair.

Refer to Figure 2-38 for diameter limits and tapered bore rework tolerances.

Critical Area

No more than 0.020 inch (0.50 mm) may be removedfor any localized repair.





Rev. 23 Mar/0861-13-33

1011


The maximum permitted outboard bore diameter in the "X" area is 1.800 inches (45.72 mm). Remove no more than 0.020 inch (0.50 mm) for any localized repair.

0.15 inch (3.81 mm) maximum

"T" or "M" Shank Rework Tolerances for Tapered "X" Area of Blade Bore Figure 2-37

The maximum permitted inboard bore diameter in the "X" area is 2.165 inches (54.99 mm). Remove no more than 0.020 inch (0.50 mm) for any localized repair.

"X" Area Localized damage repair up to 0.020 inch (0.50 mm) is permitted.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

"T" or "M" Shank With "N" Modification Rework Tolerances for Tapered "X" Area of Blade Bore

Figure 2-38

1012


1.58 inches (40.13 mm)maximum

The transition area between the "X" area and the bearing seat area has been exaggerated on this drawing. The transition area must be smooth.

The maximum permitted center bore diameter is 1.800 inches (45.72 mm). Remove no more than 0.020 inch (0.50 mm) for any localized repair.


"X" Area Localized damage repair up to 0.020 inch (0.50 mm) is permitted.



Rev. 23 Mar/0861-13-33

"D" Shank Figure 2-39

1014

0.030 inch (0.76 mm)

The maximum permitted diameter for the critical area is 1.5635 inches (39.712 mm). Remove no more than 0.030 inch (0.76 mm) for any localized repair.


The maximum permitted bore diameter is 1.5035 inches (38.188 mm). Removeno more than 0.030 inch (0.76 mm) for any localized repair.

The maximum permitted bore depth is 1.797 inches (45.64 mm).




Rev. 23 Mar/0861-13-33

1013

"Y" Shank Figure 2-40



0.030 inch (0.76 mm)


Critical area

0.300 inch(7.62 mm)


The maximum permitted borediameter is 1.5035 inches (38.188 mm). Remove no more than 0.030 inch (0.76 mm) for any localized repair.



Rev. 23 Mar/0861-13-33

"E" Shank Figure 2-41

1014.EPS

0.030 inch (0.76 mm)


0.177 inch (4.49 mm) radius

The maximum permitted bore diameter is 1.3785 inches (35.013 mm).Remove no more than 0.030 inch (0.76 mm) for any localized repair.

The maximum permitted bore

depth is 1.548 inches (39.31 mm).Critical

area 0.300 inch(7.62 mm)



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

c For "V", "V" modified to "MV", and "MV" shank blades with "N" modifications, refer to Figures 2-28, 2-29, and Table 2-7:1) A change in bore depth is not permitted. 2) Local repair in the critical area not more than 0.010 inch

(0.25 mm) at any one point is permitted. 3) If rework performed in the critical area is more than the

depth of the shot peen pebble grain, re-shot peen the critical area and the balance hole.

d For "R" and "W" shank blades, refer to Figure 2-31 and Table 2-7: 1) The maximum permitted bore depth after rework is




e For "P", "P" modified to "R", "Z", or "Z" modified to "W" shank blades, refer to Figure 2-32 and Table 2-7: 1) The maximum permitted bore depth after rework is




f For "R" and "W" shank blades with "N" modifications, refer to Figure 2-33 and Table 2-7: 1) A change in bore depth is not permitted. 2) Local repair in the critical area not more than 0.020 inch

(0.50 mm) at any one point is permitted. g For "P" and "Z" shank blades with "N" modifications, refer to

Figure 2-34 and Table 2-7: 1) A change in bore depth is not permitted. 2) Local repair in the critical area not more than 0.020 inch

(0.50 mm) at any one point is permitted.



Rev. 23 Mar/0861-13-33

h For "T" and "M" shank blades without "N" modifications, refer to Figure 2-35 and Table 2-7: 1) The maximum permitted bore depth after rework is



critical area not exceeding 0.020 inch (0.50 mm) at any one point is permitted.

i For "T" and "M" shank blades with "N" modifications, refer to Figure 2-36 and Table 2-7: 1) Change in bore depth is not permitted. 2) Local repair in the critical area not more than 0.020 inch

(0.50 mm) at any one point is permitted. j For "D" and "Y" shank blades, refer to Figures 2-39, 2-40, and

Table 2-7:1) The maximum permitted bore depth after rework is




k For "E" shank blades, refer to Figure 2-41 and Table 2-7:1) The maximum permitted bore depth after rework is






Rev. 23 Mar/0861-13-33

(b) Rework of damage, corrosion, or anodize removal in the cylindrical portion of the blade bore (outside of the critical area, refer to Figures 2-27 through 2-41).

1 Using an abrasive cartridge or patch and a drill, remove damage, irregularities, or anodize.

2 Maintain a smooth, uninterrupted finish on all surfaces.3 Blade bore areas that require rework beyond the maximum

diameter specified in each drawing are cause for retirement of the blade.a The primary intent of the maximum diameter specification is to

make sure that there is adequate bearing fit. 1) Measurement of the diameter is only required in the portion

of the bore where the bearing contacts the blade. 2) Measurement must be made at several points. 3) Finding one location that is more than the maximum

diameter is not sufficient cause for retirement because the overall bearing fit is not significantly jeopardized with excessive diameter at only one location.

4) If over 25 percent of the bearing contact area is more than the maximum diameter limit, or if damage is more than the limits of the following paragraphs, retire the blade.

NOTE: Greater than maximum diameter limits could cause uneven loading of the bearing or in off-center installation of the bearing.

b If the diameter measurement of the blade bore is in doubt, make 10 or more micrometer measurements, equally spaced lengthwise and radially. 1) If over 25 percent of the measurements are more than the

maximum diameter, retire the blade.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

c Scratches, wear marks, and blemishes caused by normal removal or installation of the bearing do not require rework if they are less than 0.010 inch (0.25 mm) in depth.

d Light corrosion, characterized by discoloration or pitting to a depth of approximately 0.001 inch (0.025 mm) maximum, with no penetrant indications does not require rework with abrasive material.

e Extremely small (pinpoint) corrosion pits do not require rework with abrasive material even though they may have pinpoint penetrant indications (typically less than 0.063 inch [1.60 mm] diameter).

f Moderate corrosion (similar to light corrosion except for flaking, blistering, and pitting depths up to 0.010 inch [0.25 mm]), severe corrosion (flaking, blistering, and pitting depths deeper than 0.010 inch [0.25 mm]), and damage such as tool marks must be repaired. 1) Up to 25 percent of the surface area where the bearing

contacts the blade bore may be reworked. 2) Localized repairs may be reworked up to 0.010 inch

(0.25 mm) greater than the maximum diameter of the area of the bore (except for "Y", "D", and "E" shank blades which may have localized repairs reworked up to 0.030 inch [0.76 mm] greater than the maximum bore diameter).

g Some blades were manufactured in the past with a "knurled" blade bore to improve bearing fit. 1) The knurling appears as several bands of circumferential

depressions approximately 0.094 inch (2.39 mm) wide. 2) Knurling marks in the critical area of the blade bore must

be removed according to the permitted repair limits.3) Bore ID measurements taken in a knurled area must be

performed by measuring to the "peaks" of the surface.


BLADE SHANK OVERHAUL 61-13-33 Page 2-129Rev. 28 Sep/12

h Shot peen pebble grain in the cylindrical portion of the blade bore, which may have been inadvertently created during shot peening of the blade balance hole, does not require removal.

i Accidental shot peen grain located in the critical area of the blade bore must be reworked in accordance with the permitted repair dimensions. Some blades require shot peen in the critical area of the blade bore. Refer to the criteria for the critical area for a specific blade to determine repair requirements.

j Blade bore areas that contain shot peen pebble grain may also contain corrosion. Chemically etch and penetrant inspect these areas to make sure that any corrosion is within the permitted limits of 2.G.(5)(b)3f above.



Rev. 25 Apr/0961-13-33

4 Maximum Permitted Bore Diameters a For "X", "X" modified to "V", and "X" modified to "MV" without

"N" modification blade shanks, refer to Figure 2-27 and Table 2-7: 1) The maximum permitted bore diameter after rework is

1.563 inches (39.70 mm). 2) Local repair in the bore of not more than 0.010 inch

(0.25 mm) at any one point is permitted. Refer to Section 2.G.(5)(b).

b For "V", and "V" modified to "MV" without "N" modification blade shanks, refer to Figure 2-28 and Table 2-7:1) The maximum permitted bore diameter after rework is

1.5055 inches (38.239 mm). 2) The maximum permitted inboard bore diameter after

rework is 1.563 inches (39.70 mm).3) Local repair in the bore of not more than 0.010 inch


c For "V", "V" modified to "MV", and "MV" shank blades with "N" modifications, refer to Figures 2-28, 2-29 and Table 2-7: 1) The maximum permitted bore diameter after rework is


rework is 1.563 inches (39.70 mm). 3) Local repair in the bore of not more than 0.010 inch


d For "R" and "W" shank blades, refer to Figure 2-31 and Table 2-7: 1) The maximum permitted bore diameter after rework is


rework is 1.782 inches (45.26 mm). 3) Local repair in the bore of not more than 0.010 inch




Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33

e For "P", "P" modified to "R", "Z", or "Z" modified to "W" shank blades, refer to Figure 2-32 and Table 2-7: 1) The maximum permitted bore diameter after rework is

1.782 inches (45.26 mm). 2) Local repair in both bores of not more than 0.010 inch


f For all "R" and "W" shank blades with "N" modifications, refer to Figure 2-33, and Table 2-7: 1) The maximum permitted outboard bore diameter after

rework is 1.7535 inches (44.538 mm). 2) The maximum permitted center bore diameter after rework

is 1.770 inches (44.958 mm). 3) The maximum permitted inboard bore diameter after

rework is 1.782 inches (45.26 mm). 4) Local repair in all bores of not more than 0.010 inch


g For all "P" and "Z" shank blades with "N" modifications, as referenced in Figure 2-34, and Table 2-7: 1) The maximum permitted bore diameter after rework is

1.782 inches (44.26 mm).2) Local repair of not more than 0.010 inch (0.25 mm) at any

one point is permitted. Refer to Section 2.G.(5)(b).h For all "T" and "M" shank blades with or without "N"

modifications, refer to Figure 2-35, 2-36, 2-38, and Table 2-7: 1) The maximum permitted bore outboard diameter after

rework is 1.7535 inches (44.538 mm). 2) The maximum permitted inboard bore diameter after

rework is 2.1278 inches (54.046 mm).3) The maximum permitted center bore diameter for

"T" and "M" shanks with "N" modifications after rework is 1.800 inches (45.72 mm). Refer to Figure 2-38.

4) Local repair in all bores of not more than 0.010 inch (0.25 mm) at any one point is permitted. Refer to Section 2.G.(5)(b).



Rev. 23 Mar/0861-13-33

i For "D" and "Y" shank blades, refer to Figures 2-39, 2-40, and Table 2-7:1) The maximum permitted bore diameter after rework is



j For "E" shank blades, refer to Figure 2-41 and Table 2-7:1) The maximum permitted bore diameter after rework is



(c) Rework of damage, corrosion, or anodize removal in the tapered "X" area of the blade bore (applies to all "T" and "M" shanks)

1 Localized repairs may be reworked up to a depth of 0.020 inch (0.50 mm). Rework beyond that is cause for blade retirement.

2 Using an abrasive cartridge or patch and a drill, remove damage, irregularities, or anodize.

3 Maintain a smooth, uninterrupted finish on all surfaces.4 If the blade bore areas require rework beyond the maximum

diameters specified in Figures 2-37 and 2-38, retire the blade.a For all "T" and "M" shank blades with or without "N"

modifications, refer to Figures 2-37 and 2-38: 1) The maximum permitted bore diameter within the "X" area

after rework is 1.800 inches (45.72 mm). 2) The maximum permitted inboard bore diameter within the

"X" area after rework is 2.165 inches (54.99 mm). 3) Local repair within the "X" area of not more than

0.020 inch (0.50 mm) at any one point is permitted.



Rev. 23 Mar/0861-13-33

(6) Dimensionally Inspect the Blade Bore

(a) A "Two Point" micrometer is preferred for this measurement.

(b) Using a micrometer and a bore gauge, dimensionally inspect the blade bore diameter(s).

(c) If the dimensions are beyond the maximum permitted rework limits of paragraph 2.G.(5), retire the blade from service.

(7) Chemically Etch the Blade Bore

CAUTION 1: FAILURE TO CHEMICALLY ETCH BEFORE PENETRANT INSPECTION MAY RESULT IN LACK OF DETECTION OF SMALL CRACKS. ETCHING IS AN ESSENTIAL PROCESS THAT IMPROVES THE VISIBILITY OF DEFECTS DURING PENETRANT INSPECTION.


(a) Using solvent CM106 or CM23, thoroughly clean the blade bore to remove grease, oil, and dirt.

(b) Permit the blade bore to thoroughly dry.

(c) Two procedures of chemical etching exist and both are permitted, but a combination of the two procedures is also permitted.

(d) For chemical etching procedures refer to the Penetrant Inspection chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(8) Penetrant Inspect Blade Bore

(a) For required materials, penetrant application methods, and inspection and acceptance criteria, refer to the Penetrant Inspection chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(b) Inspect the entire blade bore area.

(c) Except as specified in paragraph 2.G.(5), an indication is not permitted.

(d) Using solvent CM106 or CM23, rinse the blade bore to remove all penetrant materials.



Rev. 25 Apr/0961-13-33


CAUTION: WHEN THE AREA TO BE CHEMICAL CONVERSION COATED HAS BEEN CLEANED, DO NOT TOUCH THE SURFACE WITH FINGERS OR ANY OILY SUBSTANCE. DOING SO WILL CAUSE CONTAMINATION OF THE SURFACE AND CHEMICAL CONVERSION COAT WILL NOT BOND TO IT.

(a) After penetrant inspection, clean the blade bore and balance hole with a noncorrosive cleaner such as "Bon Ami" or "Radiaze L.F." or other similar cleaner that does not contain chlorine or corrosive agents.

(b) Using a grease and lint free cloth such as cheese cloth CM159, apply the cleaner.

(c) Using water, rinse the blade bore area.

(d) If the water beads on the surface of the blade bore, grease or contaminants are still present.

(e) Repeat the cleaning process until no grease or residue is apparent.

(f) Thoroughly dry the blade bore.

(g) For approved conversion coating products, refer to the Chromic Acid Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(h) Apply a layer of chemical conversion coating to the retention radius and to the entire blade butt, including bore, balance hole, and pitch change knob if present. Refer to the Chromic Acid Anodizing chapter of Hartzell Standard Practices Manual 202A (61-01-02).


(i) Follow the product manufacturer's instructions about storage temperature and pH level to maintain the integrity of the chemical conversion coating.

(j) Apply the chemical conversion coating in accordance with the instructions provided by the product manufacturer.

(k) The transition between the chemical conversion coating region and the anodized portion of the blade is defined in Table 2-1.




Rev. 23 Mar/0861-13-33

(10) Paint Blade Bore and Balance Hole

CAUTION: PAINT IS REQUIRED IN THE BLADE BORE CRITICAL AREA AND ON AN ADDITIONAL 0.125 INCH TO 0.25 INCH (3.17 mm TO 6.35 mm) OF THE BEARING CONTACT AREA TO MINIMIZE CORROSION.

(a) Using a thin layer of mixture number 3 washer primer, paint the balance hole, the blade bore critical area, and an additional 0.125 inch to 0.25 inch (3.17 mm to 6.35 mm) of the bearing contact area adjacent to the critical area. For washer primer mixture information refer to the Paint and Finish chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(b) Permit the washer primer to dry for five minutes.

CAUTION: DO NOT APPLY PAINT TO THE ENTIRE BEARING BORE. THE DIAMETER MAY BE REDUCED ENOUGH TO CAUSE IMPROPER BEARING FIT.

(c) Using a small brush or cotton swab, paint the entire primed area with a thin, even layer of black Polane paint CM33.

1 Previous Hartzell publications called for the use of gray Polane paint CM34 in the balance hole. This is permitted, but black Polane paint CM33 provides a clearer visual indication of adequate coverage of the critical area with paint.

CAUTION: DO NOT EXCEED 200° F TEMPERATURE, IF DRYING WITH HEAT.

(d) Permit the paint to dry thoroughly before installing bearings.

1 If the temperature does not exceed 200° F (93° C), drying with heat is permitted.



Rev. 27 Sep/1161-13-33

(11) Blade Bushing Installation for All "P" and "Z" Shank Blades With or Without "N" Modifications(a) Gasket sealant CM46 must be used during A-1309 blade bushing

installations on each "P" and "Z" shank blade to prevent corrosion in the blade bore. Refer to Figure 2-42.

(b) Permit the paint in the blade bore and in the balance hole to dry for a minimum of 15 minutes before applying gasket sealant CM46.

(c) Apply a moderate layer of gasket sealant CM46 around the circumference of the blade bore between 3.50 inches (88.9 mm) and 3.75 inches (95.2 mm) from the blade butt.

(d) Make sure that there is complete coverage on the blade bore circumference.

NOTE: Applying a moderate amount of gasket sealant CM46 will minimize the amount of gasket sealant extrusion into the blade bore after installation of the blade bushing.

CAUTION: INSTALL THE BLADE BUSHING WITHIN 10 MINUTES OF APPLYING THE GASKET SEALANT CM46.

(e) Press the new blade bushing into the blade bore, flush to no more than 0.020 inch (0.50 mm) below the blade butt face.

CAUTION: DO NOT USE SOLVENT TO REMOVE EXCESS SEALANT.

(f) Wipe away excess sealant that was exposed when the blade bushing was installed.

(g) Permit the gasket sealant CM46 to cure for two hours.

(h) Ream the full length of the blade bushing in accordance with the Blade Bushing Diameters Table 2-8.



Rev. 27 Sep/1161-13-33

Sealant3

Measure 3.50 (88.9 mm) and 3.75 (95.2 mm) from the tip of the applicator. Mark the handle to use as a guide.

Installing CM46 Gasket Sealant Figure 2-42

Wipe to remove excess sealant. Do not use solvent when cleaning.

3.50 inches (88.9 mm)

3.75 inches (95.2 mm)

Blade Bushing Diameters Table 2-8

Shank Type Diameter (Inches) Diameter (mm)"X" 1.501 to 1.5025 38.13 to 38.163 "X" Modified to "V" 1.501 to 1.5025 38.13 to 38.163 "V" with "N" Modification 1.501 to 1.5025 38.13 to 38.163 "MV" with "N" Modification 1.501 to 1.5025 38.13 to 38.163 "Z" 1.7205 to 1.7220 43.701 to 43.738"Z" Modified to "W" Inboard: 1.7215 to 1.7225 Inboard: 43.726 to 43.751

Outboard: 1.7495 to 1.7505 Outboard: 44.438 to 44.462"W" 1.7215 to 1.7225 43.726 to 43.751"P" 1.7205 to 1.7220 43.701 to 43.738"P" Modified to "R" Inboard: 1.7215 to 1.7225 Inboard: 43.726 to 43.751

Outboard: 1.750 to 1.7525 Outboard: 44.45 to 44.513"R" 1.7215 to 1.7225 43.726 to 43.751



(12) Internal Bearing Installation

(a) Inspect the bearing to make sure that a smooth surface exists at the corners of the bearing.

(b) Using an abrasive pad that has 400-grit or finer, light polishing is recommended on the bearing outside diameter.

CAUTION: DO NOT USE SEALER CM49 ON "Y", "D", OR "E" SHANK BLADES.

(c) For all blades except "Y", "D", and "E" shank, apply sealer CM49 to the radiused area of the blade bore and to the radiused side of the bearing spacer.

1 Liberal use of sealer CM49 in the critical area enhances corrosion protection.

2 Do not use sealer CM49 so heavily that it extrudes into the bearing surfaces after installation.

3 Sealer CM49 is optional on "T" and "M" shank blades with "N" suffix, which use a plastic bearing spacer.

(d) Insert the bearing spacer into the blade bore.

(e) Apply a light layer of lubricant CM80 to the blade bore to permit smoother bearing installation.

(f) For all blades except "Y", "D", and "E" shank, apply sealer CM49 to the spacer end of the bearing.



Rev. 39 Mar/2061-13-33

Inboard Bearing

Outboard Bearing

Spacer

APS656

Bearing Installation on "T" and "M" Shank Blades with "N" Conversion Figure 2-43

2.645 Inches (67.18 mm)

(g) Using blade bearing press TE93 or equivalent, and local tooling methods, press the outboard bearing into place.1 Install a bearing that has open ends by pressing on the surface of the

bearing that has identification marks.2 Install a bearing that has one closed end with the closed end

outboard.3 Use Bearing Installation Tool TE64 for "T" and "M" shank blades with

"N" conversion.

NOTE: The inboard bearing may be installed using Bearing Installation Tool TE64 or previous tooling methods.

a Install the inboard bearing, outboard bearing, and spacer onto the bearing installation tool.

CAUTION: BEARING INSTALLATION TOOL TE64 MUST BE USED TO INSTALL THE OUTBOARD BEARING. PREVIOUS BEARING INSTALLATION TOOLS MAY RESULT IN IMPROPERLY LOCATING THE BEARING AND MAY DAMAGE THE PLASTIC BEARING SPACER.

b Insert the bearing installation tool TE64 into the blade bore.



Rev. 23 Mar/0861-13-33

c Using an arbor, press the bearing installation tool CM64 into the blade bore until the flange of the tool is flush with the blade butt.

d Unscrew the bearing installation tool CM64 from the spacer.e Measure the depth of the outboard bearing. f The distance from the blade butt to the inboard end of the

outboard bearing must be 2.645 ± 0.015 inches (67.18 ± 0.38 mm). Refer to Figure 2-43.

(h) Installation of Optional SCE 2020 Bearing in "Y" Shank Blade

1 The Fafnir SCE 2020 bearing is an optional, open-end bearing that may be used in "Y" shank blades.

2 Put a 0.125 inch (3.17 mm) bead of sealant CM92 around the blade bore radius.

3 Install the A2414-1 plug with the chamfer side outboard.4 Using a bearing press and local tooling methods, press the bearing

into the blade bore.



Rev. 23 Mar/0861-13-33

Reading Runout Figure 2-44

Reading the runout of the blade butt, indicate to 0.001 inch (0.025 mm) maximum Total Indicated Runout.

Reading the runout of the retention shoulder, indicate to 0.001 inch (0.025 mm) maximum Total Indicated Runout.

1005A



Rev. 27 Sep/1161-13-33

(i) Press inboard needle bearing in place (if applicable).

CAUTION 1: INSTALLATION OF A NEW BLADE BUSHING MUST BE ACCOMPLISHED BY A SKILLED LATHE OPERATOR. INSTALLATION IS CRITICAL AND BLADE AIRWORTHINESS MAY BE AFFECTED.

CAUTION 2: DO NOT RE-INSTALL A USED BLADE BUSHING.

CAUTION 3: DO NOT BORE INTO THE RADIUSED AREA AT THE BOTTOM OF THE BLADE BORE.

CAUTION 4: DO NOT PERMIT METAL SHAVINGS TO ENTER THE NEEDLE BEARING. INSTALL A PLUG IN THE LOWER END OF THE BLADE BORE.

(j) Using locally fabricated tooling, install a new blade bushing in accordance with the following procedure.

1 Press the new blade bushing into the blade bore. a The blade bushing must be flush with to no greater than

0.020 inch (0.50 mm) below the blade butt face. b For information about the correct blade bushing for a blade

shank, refer to the Illustrated Parts List of this manual.2 Mount the blade in a lathe or mill. 3 Secure the blade tip and put the blade shank in a fixed rest, if

applicable.4 Adjust the blade, as applicable, to achieve the following runout

requirements:a Reading the runout of the blade butt, indicate to 0.001 inch

(0.025 mm) maximum Total Indicated Reading. Refer to Figure 2-44.

b Reading the runout of the retention shoulder, indicate to 0.001 inch (0.025 mm) maximum Total Indicated Reading. Refer to Figure 2-44.

c Ream the blade bushing to the specified tolerance indicated in Table 2-8.



Rev. 23 Mar/0861-13-33

"X" to "V" Shank Bearing Press Tool Figure 2-45

3.5 Inches (88.9 mm)

1.485 Inches(37.71 mm)

15 degrees

0.875 Inch(22.22 mm)

1.245 Inches(31.62 mm)

APS2050



Rev. 27 Sep/1161-13-33

H. Blade Shank Conversion

(1) Conversion of "X" Shank to "V" Shank Blades

(a) Conversion of "X" shanks to "V" shanks is mandatory at blade overhaul.

(b) Dimensionally inspect the blade bushing of the "X" shank.

1 The maximum permitted ID of the blade bushing is 1.5025 inches (38.163 mm).

(c) Put a spacer in the bottom of the blade bore. Refer to paragraph 2.G.(10) of this section.

(d) Using a bearing press tool, press the needle bearing into the blade bore. Refer to Figure 2-45.

(e) Stamp a "V" before the blade model number on the blade butt. Refer to the Parts Identification and Marking chapter of Hartzell Standard Practices Manual 202A (61-01-02).



Rev. 27 Sep/1161-13-33

Spacer

Needle Bearing

A-1309-1 or Modified A-1309 Blade Bushing

1.7495 to 1.7505 Inches (44.438 to 44.462 mm)

1.7215 to 1.7225 Inches (43.727 to 43.751 mm)

1.778 to 1.779 Inches (45.17 to 45.18 mm)

Inboard Blade Bushing

ASK706

"Z" Shank Converted to "W" Shank Blade Figure 2-46

1.125 Inches (28.58 mm) ± 0.010 (0.25 mm)



Rev. 27 Sep/1161-13-33

(2) Conversion of "Z" Shank to "W" Shank Blades

CAUTION: DO NOT CONVERT A "Z" SHANK BLADE WITH AN "N" MODIFICATION TO A "W" SHANK BLADE.

(a) This conversion is optional to permit use of "Z" shank blades with "W" shank hubs.

(b) Put the blade in a lathe or mill.

(c) Chuck the tip and put the shank in a steady rest.

(d) Adjust the blade tip to achieve runout requirements:

1 Reading runout of the blade butt, indicate to 0.0005 inch (0.0127 mm) maximum Total Indicated Runout.

2 Reading runout of the blade bore, indicate to 0.002 inch (0.05 mm) maximum Total Indicated Runout.

3 Reading runout of the retention shoulder, indicate to 0.001 inch (0.025 mm) maximum Total Indicated Runout.

4 Reading runout outboard of the retention radius, indicate to 0.001 inch (0.025 mm) maximum Total Indicated Runout.


CAUTION 2: DO NOT PERMIT METAL SHAVINGS TO ENTER THE NEEDLE BEARING. INSTALL A PLUG IN THE LOWER END OF THE BLADE BORE.

(e) Insert the full length blade bushing and into the blade bore. Bore the entire length of the blade bushing to a minimum ID of 1.7495 inches (44.438 mm) and a maximum of 1.7505 inches (44.462 mm).

(f) If an A-1309 blade bushing is used, it must be modified.

1 Bore out the blade bushing to diameter of 1.778 inches (45.17 mm) to 1.779 inches (45.18 mm) at inboard 1.125 inches (28.58 mm) of blade bore. Refer to Figure 2-46.

(g) Insert the spacer and the needle bearing in accordance with paragraph 2.G.(12).

(h) Insert the inboard blade bushing.

(i) Bore the inboard blade bushing to a diameter of 1.7215 (43.727 mm) to 1.7225 inches (43.751 mm).

(j) Stamp a "W" before the blade model number on the blade butt. Refer to the Parts Identification and Marking chapter of Hartzell Standard Practices Manual 202A (61-01-02).



Rev. 27 Sep/1161-13-33

A-1309-1 Blade Bushing

ASK706

1.120 to 1.180 Inches (28.45 to 29.97 mm)

Spacer

Needle Bearing

1.7500 to 1.7525 Inches (44.45 to 44.51 mm)

A-1347 Inboard Blade Bushing

"P" Shank Converted to "R" Shank Blade Figure 2-47

1.778 to 1.779 Inches (45.17 to 45.18 mm)

1.7215 to 1.7225 Inches (43.73 to 43.75 mm)



Rev. 27 Sep/1161-13-33

(3) Conversion of "P" Shank to "R" Shank Blades

(a) Mount the blade in a lathe or mill.

(b) Chuck the tip and put the shank in a steady rest.

(c) Adjust the blade tip to achieve runout requirements:1 Reading runout of the blade butt, indicate to 0.0005 inch

(0.013 mm) maximum Total Indicated Runout.2 Reading runout of the blade bore, indicate to 0.002 inch

(0.05 mm) maximum Total Indicated Runout.3 Reading runout of the retention shoulder, indicate to 0.001 inch

(0.025 mm) maximum Total Indicated Runout.4 Reading runout outboard of the retention radius, indicate to

0.001 inch (0.025 mm) maximum Total Indicated Runout.


CAUTION 2: DO NOT PERMIT METAL SHAVINGS TO ENTER THE NEEDLE BEARING. PLUG THE LOWER END OF THE BLADE BORE.

(d) Insert an A-1309-1 blade blade bushing to a depth of 1.120 inches (28.45 mm) to 1.180 inches (29.97) into the blade bore. Refer to Figure 2-47.

(e) Bore full length of the blade bushing to minimum ID of 1.7500 inches (44.450 mm) and maximum of 1.7525 inches (44.513 mm). Refer to Figure 2-47.

(f) Insert a spacer in accordance with paragraph 2.G.(12).

(g) Insert a needle bearing in accordance with paragraph 2.G.(12).

(h) Insert an A-1347 inboard blade bushing flush with or no greater than 0.030 inch (0.76 mm) below the blade butt surface.

(i) Bore the inboard blade bushing to diameter of 1.7215 inches (43.73 mm) to 1.7225 inches (43.75 mm). Refer to Figure 2-47.

(j) Stamp an "R" before the blade model number on the blade butt.



Rev. 23 Mar/0861-13-33

Counterweight Inspection Figure 2-48

W10518

Do not rework the counterweight seat area.

Do not rework the mounting bolt bore area, or the bolt seat area.

Drilling the Counterweight Assembly for Spring Pin Installation Figure 2-49

APS2022

Blade Counterweight Knob

Counterweight



Counterweight Surface Figure 2-49.1

TPI-J

M-0

0001

4

I. Counterweight Disassembly

(1) Remove the pins from the counterweight bolts.

(2) Remove and discard the counterweight bolts.

(3) Remove the counterweights.

NOTE: The dowel pin has a tendency to remain in the blade when the counterweight is removed.

(a) If the blade will be overhauled:

1 Remove the dowel pin from the blade and discard it.a Use suitable customer procured equipment or fixtures for dowel

pin removal.b If heat is used for dowel pin removal, refer to the

Special Inspections chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02) for heat exposure limitations.

2 If there is a threaded insert in the counterweight, remove and discard it.

(b) Remove and discard the dowel pin if it is part number B-6138-6-7.

1 Dowel pin part number B-6138-6-7 is replaced by dowel pin part number B-6260.

2 Dowel pin part number B-6260 can be identified by an "S" stamped on the end of the pin.

(c) Remove and discard the dowel pin if it remains in the counterweight.

Counterweight surface to apply and remove sealant.



Rev. 39 Mar/2061-13-33


CAUTION: DO NOT USE GLASS BEAD CLEANING ON THE BLADE.

(d) Using acetone CM173, MEK CM106, or MPK CM219, remove sealant CM46, sealant CM92, and corrosion inhibitor CM352 from all surfaces of the counterweight and the blade knob.

1 Optionally, plastic media can be used in accordance with the Cleaning chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02) to remove the sealant and corrosion inhibitor.

(4) At overhaul, using a pin gauge, measure the depth of the dowel pin hole in the counterweight knob.

(a) The maximum permitted dowel pin hole depth is 1.150 inches (29.21 mm). Refer to Figure 2-53.

NOTE: The depth of the hole is measured to the shoulder of the hole, not to the point.

(b) If the hole is deeper than the permitted depth, retire the blade in accordance with the Part Retirement Procedures chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).


BLADE SHANK OVERHAUL 61-13-33 Page 2-153Rev. 39 Mar/20

(5) Examine the counterweight knob surface of each blade.

(a) Impression stamping on the knob surface is not permitted.

1 If a counterweight knob surface has been impression stamped, polish the surface to remove any raised material using an abrasive pad that has 400-grit or finer.

2 Apply chemical conversion coating in accordance with the Chromic Acid Anodizing chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(6) Make a magnetic particle inspection of the counterweight in accordance with the Magnetic Particle Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(a) Pin-point indications no greater than 0.062 inch (1.58 mm) diameter are permitted.

NOTE: Pinpoint indications can be caused by corrosion pitting or by manufacturing processes from the factory.

(7) Corrosion is not permitted.

(a) Remove corrosion using glass bead cleaning. Refer to the Cleaning chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(8) The rework limits are as follows:

WARNING: DO NOT REWORK THE MOUNTING BOLT BORE AREA, BOLT SEAT AREA, OR COUNTERWEIGHT SEAT AREA. REFER TO FIGURE 2-48.

(a) The maximum permitted depth of rework for an indication that intersects a hole is 0.020 inch (0.50 mm).

(b) The maximum permitted depth of rework for an indication that does not intersect a hole is 0.050 inch (1.27 mm).

(c) Rework the area surrounding the indication to five times the depth of the indication.

(d) Replace the counterweight if an indication is greater than the permitted rework limits.

(9) After rework, make an inspection of the counterweight in accordance with the Magnetic Particle Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(a) Replace the counterweight if a relevant indication is found.

(10) Replate the counterweight in accordance with the Cadmium Replating chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).



Rev. 35 Nov/1761-13-33

Counterweight Bolt Installation Figure 2-51

APS2008

APS2007

Counterweight

Dowel Pin


Counterweight Assembly Figure 2-50


Counterweight

Counterweight Bolts



Counterweight Mounting Hardware Table 2-9

Counterweight Part Number

Counterweight Bolt

Part Number

Dowel Pin Part

Number

1st Oversized Dowel Pin

Part Number

2nd Oversized Dowel Pin

Part Number

Spring Pin Part Number Torque

D-6021(-) B-3826 B-6260replacesB-6138-6-7

100332 104074 B-3842-0500 70 Ft-Lb (95 N•m)

B-3202(-) A-3208 A-65 A-65-1 104073 A-285 65 Ft-Lb (89 N•m)

C-329(-) B-3850-12 A-65 A-65-1 104073 B-3842-0500 65 Ft-Lb (89 N•m)

C-472(-) B-3850-12 A-65 A-65-1 104073 B-3842-0500 65 Ft-Lb (89 N•m)

101651 B-3826 B-6260 100332 104074 B-3842-0500 70 Ft-Lb (95 N•m)

Dowel Pin Part Number

Dowel Pin Size Hole Size *

A-65 0.2502 ± 0.0001 inch(6.355 ± 0.0025 mm)

0.2495 +0.0005/-0.0010 inch(6.33 +0.0127/-0.0254 mm)

A-65-1 0.2656 ±0.0001 inch(6.746 ± 0.0025 mm)

0.2649 +0.0005/-0.0010 inch(6.72 +0.0127/-0.0254 mm)

B-6260 0.3752 ± 0.0001 inch(9.530 ± 0.0025 mm)

0.3745 +0.0005/-0.0010) inch(9.512 +0.0127/-0.0254 mm)

100332 0.3912 ± 0.0001 inch(9.936 ± 0.0025 mm)

0.3905 +0.0005/-0.0010 inch(9.918 +0.0127/-0.0254 mm)

104073 0.2852 ± 0.0001 inch(7.4244 ± 0.0025 mm)

0.2845 +0.0005/-0.0010 inch(7.226 +0.0127/-0.0254 mm)

104074 0.4102 ± 0.0001 inch(10.419 ± 0.0025 mm)

0.4095 +0.0005/-0.0010 inch(10.401 +0.0127/-0.0254 mm)

* The hole may be reamed to achieve the required hole dimension.

Counterweight Dowel Pin Hole Requirements for Press Fit Table 2-10



Rev. 35 Nov/1761-13-33

J. Counterweight Installation

(1) Installation of a New Counterweight on a New Blade

(a) General

1 Counterweight knobs are found on Y, D, and E shank aluminum propeller blades.

2 New blades are not manufactured with a counterweight dowel pin hole. During the assembly process, a counterweight is bolted onto the counterweight knob (refer to Table 2-9 for counterweight mounting hardware) and a hole is drilled through a hole in the counterweight and into the blade. (Refer to Figure 2-53). This creates a matched counterweight and blade combination.

(b) Installation Procedures


CAUTION: INSTALLATION OF THE COUNTERWEIGHT AND MOUNTING BOLTS MUST BE DONE WITHIN ONE HOUR AFTER APPLYING THE SEALANT CM46.

NOTE: This procedure may be performed with the blade assembled or disassembled from the propeller assembly.

1 Apply sealant CM46 below the head and to the threads of each counterweight mounting bolt.

CAUTION: USE CARE TO NOT GET SEALANT CM46 IN THE COUNTERWEIGHT HOLES.

2 Apply sealant CM46 to the counterweight surfaces that touch the blade and to the channel between the counterweight surfaces that touch the blade. Refer to Figure 2-49.1.

3 Install the counterweight on the blade. Refer to Figure 2-50.4 Install the counterweight mounting bolts. Refer to Figure 2-51.5 Torque the counterweight mounting bolts in accordance with

Table 2-9.6 Using a clean cloth dampened with MEK CM106 or Acetone CM173,

clean sealant CM46 from the counterweight knob and around the counterweight mounting bolt head.



Counterweight Spring Pin Installation Figure 2-52

AP

S20

62

Spring Pin

Counterweight


Counterweight Bolt

Spring Pin

Counterweight Slug Mounting Hardware Torques Table 2-11

Mounting HardwarePart Number Torque Value

B-3386-(-) 36 Ft-Lb (48.8 N•m)

B-3384(-) 10 Ft-Lb (13.6 N•m)

B-3599 22 Ft-Lb (29.8 N•m)

A-2043-1 22 Ft-Lb (29.8 N•m)



Rev. 35 Nov/1761-13-33

7 Install additional slugs to the counterweight, if applicable. Refer to the Hartzell Propeller Inc. Application Guide Manual 159 (61-02-59).a Torque the counterweight slug mounting hardware in

accordance with Table 2-11.8 Using a feeler gage, inspect the four corners of the counterweight to

make sure that there is no clearance between the counterweight and the blade.

9 If there is clearance, remove the bolts and the counterweight, slightly change the alignment, and reassemble the unit until there is no clearance.

CAUTION: DO NOT PERMIT METAL SHAVINGS TO ENTER THE HUB ASSEMBLY WHEN DRILLING THE COUNTERWEIGHT. METAL SHAVINGS ENTERING THE HUB ASSEMBLY MAY DAMAGE THE BLADE SEAL.

10 If the counterweight is drilled with the blade installed in the hub, put rags tightly around the shank of the blade where the blade enters the hub.

11 Using a #42 drill bit, drill through the side of the counterweight into each bolt head to an approximate depth of 0.375 inch (9.53 mm). Refer to Figure 2-49.

12 Install a spring pin in each bolt. Refer to Figure 2-52.13 Using a drill bit of the appropriate size to get the required hole

dimension, drill through the dowel pin hole of the counterweight into the blade counterweight knob. Refer to Table 2-9, Table 2-10, and Figure 2-53.a For a Y-shank propeller blade that uses an A-65 dowel pin

and a B-3202(-) counterweight: Drill to a depth of 0.62 inch to 0.68 inch (15.8 to 17.2 mm) into the blade counterweight knob.

b For a D or E-shank propeller blade that uses an A-65 dowel pin and a C-472(-) counterweight: Drill to a depth of 0.61 inch to 0.73 inch (15.5 to 18.5 mm) into the blade counterweight knob.

c For an E-shank propeller blade that uses a B-6260 dowel pin and a C-1797(-) or D-6021(-) counterweight: Drill to a depth of 0.61 inch to 0.73 inch (15.5 to 18.5 mm) into the blade counterweight knob.

CAUTION: MAKE SURE THAT THERE IS AN INTERFERENCE FIT BETWEEN THE DOWEL PIN AND THE BLADE COUNTERWEIGHT.

14 Using a hammer and a pin punch, install the dowel pin through the dowel pin hole of the counterweight and into the blade counterweight knob.



a If the dowel pin hole depth is deeper than the recommended drill/ream hole depth and less than the maximum permitted hole depth, use caution when installing the dowel pin because it is possible to press the dowel pin so far into the blade that there will be almost no interference between the installed counterweight and the dowel pin.

15 Using a ball peen hammer, strike the surface around the dowel pin hole of the counterweight to slightly peen material over the dowel pin.

16 Using RTV CM92, fill the dowel pin hole on top of the installed dowel pin. Refer to Figure 2-52.1.

17 Using a soft clean cloth, remove any excess RTV CM92.

NOTE: RTV CM92 must be flush to the counterweight surface.

Counterweight View Figure 2-52.1

TPI-J

M-0

0014

7

Counterweight

Dowel Pin Hole

Spring Pin/Spring Pin Hole

Bolt WellBolt Head



Rev. 39 Mar/2061-13-33

CAUTION: USE CAUTION WHEN APPLYING THE CORROSION INHIBITOR CM352 AROUND DE-ICE COMPONENTS.

18 Using a soft bristled brush, apply corrosion inhibitor CM352 to the bolt heads, spring pins and bolt wells of the counterweight..a Make sure the bolt heads, spring pins, spring pin holes, and bolt

wells are completely covered by the corrosion inhibitor CM352.b Keep the corrosion inhibitor CM352 away from de-ice

components.c Optionally, apply corrosion inhibitor CM352 to all exposed

surfaces of the counterweight.19 Permit the gasket sealant CM46, RTV CM92, and corrosion inhibitor

CM352 to cure for a minimum of three hours before flight.(2) Installation of an Old Counterweight That is Matched to an Old Blade

(a) General1 "Matched" indicates that previously the counterweight and the blade

have been pinned together with a dowel pin.2 A matched counterweight and blade assembly may be disassembled

and reassembled an infinite number of times throughout the life of each component.

3 Disassembly of the counterweight from the blade is required at blade overhaul. Refer to the section "Counterweight Disassembly" in this chapter.

4 Remove the counterweight dowel pin from the blade before the anodize process of the blade.

5 When the counterweight is removed from the blade, new counterweight mounting bolts and spring pins must be used at reassembly.



(b) Reinstallation ProceduresWARNING: ADHESIVES AND SOLVENTS ARE FLAMMABLE AND

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





3 Install the counterweight on the blade. Figure 2-50.4 Install the counterweight mounting bolts. Refer to Figure 2-51.5 Torque each counterweight mounting bolt in accordance with


clean sealant CM46 from the inside of the dowel pin hole.7 Using a clean cloth dampened with MEK CM106 or Acetone CM173,

clean sealant CM46 from the counterweight knob and around the counterweight mounting bolt head.

8 Install additional slugs to the counterweight, if applicable. Refer to Hartzell Propeller Inc. Application Guide Manual 159 (61-02-59).a Torque the counterweight slug mounting hardware in






Rev. 39 Mar/2061-13-33



12 Using a #42 drill bit, drill through the existing holes in the side of the counterweight into each bolt head to an approximate depth of 0.375 inch (9.53 mm). Refer to Figure 2-49.

13 Install a spring pin in each bolt. Refer to Figure 2-52.14 Using a hammer and a pin punch, install the dowel pin through the

dowel pin hole of the counterweight and into the blade counterweight knob. Refer to Table 2-9.










CM352 to cure for a minimum of three hours before flight.



(3) Installation of an Old Counterweight on an Old Blade When the Blade Counterweight Knob Dowel Pin Hole is Expanded or Elongated

(a) General

1 Normal wear or disassembly of the counterweight from the blade can cause the dowel pin hole in the blade counterweight knob to expand or elongate so that the pin fits loosely in the hole.

2 When the standard dowel pin no longer fits in the assembly correclty, use of the oversized dowel pin is required.

(b) Installation Procedures






3 Install the counterweight on the blade. Figure 2-50.4 Install the counterweight mounting bolts. Refer to Figure 2-51.5 Torque each counterweight mounting bolt in accordance with


remove unwanted sealant CM46 from the inside of the dowel pin hole.

7 Using a clean cloth dampened with MEK CM106 or Acetone CM173, remove unwanted sealant CM46 from the counterweight knob and around the counterweight mounting bolt head.



Rev. 39 Mar/2061-13-33

Drilling the Dowel Pin Hole Into the Blade Figure 2-53

APS2009

Blade

Counterweight

Blade Counterweight

Knob

Measuring the Depth of the Dowel Pin Hole in the Blade Counterweight Knob






10 If there is a clearance, remove the bolts and the counterweight, slightly change the alignment, and reassemble the unit until there is no clearance.



12 Using a #42 drill bit, drill through the existing holes in the side of the counterweight into each bolt head to an approximate depth of 0.375 inch (9.53 mm). Refer to Figure 2-49.


dimension, drill through the dowel pin hole of the counterweight into the blade counterweight knob. Refer to Table 2-9, Table 2-10, and Figure 2-53.a For a Y-shank propeller blade that uses an A-65-1 or a 104073

dowel pin and a B-3202(-) counterweight:(1) Drill to a depth of 0.62 inch to 0.68 inch (15.8 to 17.2 mm)

into the blade counterweight knob.b For a D or E-shank propeller blade that uses an A-65-1 or

a 104073 dowel pin and a C-472(-) counterweight:(1) Drill to a depth of 0.61 inch to 0.73 inch (15.5 to 18.5 mm)

into the blade counterweight knob.c For an E-shank propeller blade that uses a 100332 or a 104074

dowel pin and a C-1797(-) or D-6021(-) counterweight:(1) Drill to a depth of 0.61 inch to 0.73 inch (15.5 to 18.5 mm)

into the blade counterweight knob.



Rev. 39 Mar/2061-13-33


15 Using a hammer and a pin punch, install the oversized dowel pin through the dowel pin hole of the counterweight and into the blade counterweight knob.a If the dowel pin hole depth is deeper than the recommended

drill/ream hole depth and less than the maximum permitted hole depth, use caution when installing the dowel pin because it is possible to press the dowel pin so far into the blade that there will be almost no interference between the installed counterweight and the dowel pin.













(4) Installation of an Unmatched New or Old Counterweight on an Old Blade(a) General

1 "Unmatched" means that the counterweight and the blade have not previously been pinned together with a dowel pin.

2 When a blade and counterweight pair are separated because of the retirement of the counterweight, a replacement counterweight may be installed on the blade.

3 Because of the unique location of each counterweight dowel pin hole, the dowel pin hole in the replacement counterweight will probably not align with the location of the existing dowel pin hole in the blade.

4 When installing a replacement counterweight on an old blade, use of the oversized dowel pin is required.

5 If the existing dowel pin hole in the blade counterweight knob does not align with the dowel pin hole in the counterweight, assembly of the two components is not permitted.

6 It is possible to “mix and match” old or new counterweights with an old blade until a counterweight is found that correctly aligns with the existing blade counterweight dowel pin hole.

(b) Installation ProceduresWARNING: ADHESIVES AND SOLVENTS ARE FLAMMABLE AND

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





3 Install the new counterweight on the blade. Refer to Figure 2-50.a If there is resistance with the applicable oversize dowel pin, the

counterweight can be installed.b If there is no resistance with the applicable oversize dowel pin,

the counterweight may not be used.



Rev. 39 Mar/2061-13-33

4 Install the counterweight mounting bolts. Refer to Figure 2-51.5 Torque the counterweight mounting bolts in accordance with


clean sealant CM46 from the inside of the dowel pin hole.7 Using a clean cloth dampened with MEK CM106 or Acetone CM173,

remove unwanted sealant CM46 from the counterweight knob and around the counterweight mounting bolt head.









dimension, drill through the dowel pin hole of the counterweight into the blade counterweight knob. Refer to Table 2-9, Table 2-10, and Figure 2-53.a For a "Y" shank blade that uses an A-65-1 or a 104073 dowel pin

and a B-3202(-) counterweight:(1) Drill to a depth of 0.62 inch to 0.68 inch (15.8 to 17.2 mm)

into the blade counterweight knob.b For a "D" or an "E" shank propeller blade that uses an A-65-1 or

a 104073 dowel pin and a C-472(-) counterweight:(1) Drill to a depth of 0.61 inch to 0.73 inch (15.5 to 18.5 mm)




c For an "E" shank lightweight turbine propeller blade that uses a 100332 or a 104074 dowel pin and a C-1797(-) or D-6021(-) counterweight:(1) Drill to a depth of 0.61 inch to 0.73 inch (15.5 to 18.5 mm)



15 Using a hammer and a pin punch, install the dowel pin through the dowel pin hole of the counterweight and into the blade counterweight knob.a If the dowel pin hole depth is deeper than the recommended














Rev. 39 Mar/2061-13-33

(5) Installation of an Old Counterweight on a New Blade(a) Counterweight Inspection

1 Using a standard dowel pin, check the dowel pin hole in the old counterweight to make sure that there is resistance.a If there is resistance with the applicable standard dowel pin, the

counterweight can be installed with a standard dowel pin.b If there is no resistance with the applicable standard dowel pin,

recheck the hole with an oversized dowel pin.2 Using an oversized dowel pin, check the dowel pin hole in the

old counterweight to make sure that there is resistance. Refer to Table 2-9.a If there is resistance with the applicable oversized dowel pin, the

counterweight can be installed with a oversized dowel pin.b If there is no resistance with the applicable oversized dowel pin,

replace the counterweight.(b) Installation Procedures



NOTE: This procedure may be performed with the blade assembled or disassembled from the propeller assembly.




3 Install the counterweight on the blade. Refer to Figure 2-50.4 Install the counterweight mounting bolts. Refer to Figure 2-51.5 Torque the counterweight mounting bolts in accordance with

Table 2-9.


BLADE SHANK OVERHAUL 61-13-33 Page 2-170.1Rev. 39 Mar/20

6 Using a clean cloth dampened with MEK CM106 or Acetone CM173, remove unwanted sealant CM46 from the counterweight knob and around the counterweight mounting bolt head.



make sure that there is no clearance between the counterweight and blade.






dimension, drill through the dowel pin hole of the counterweight into the blade counterweight knob. Refer to Table 2-9, Table 2-10, and Figure 2-53.a For a "Y" shank propeller blade that uses an A-65, an A-65-1, or

a 104073 dowel pin and a B-3202(-) counterweight:(1) Drill to a depth of 0.62 inch to 0.68 inch (15.8 to 17.2 mm)

into the blade counterweight knob.b For a "D" or an "E" shank propeller blade that uses an A-65, an

A-65-1, or a 104073 dowel pin and a C-472(-) counterweight:(1) Drill to a depth of 0.61 inch to 0.73 inch (15.5 to 18.5 mm)

into the blade counterweight knob.c For an "E" shank propeller blade that uses a B-6060,

a 100332, or a 104074 dowel pin and a C-1797(-) or a D-6021(-) counterweight:(1) Drill to a depth of 0.61 inch to 0.73 inch (15.5 to 18.5 mm)




Rev. 39 Mar/2061-13-33


14 Using a hammer and a pin punch, install the dowel pin through the dowel pin hole of the counterweight and into the blade counterweight knob.a If the dowel pin hole depth is deeper than the recommended













BLADE SHANK OVERHAUL 61-13-33 Page 2-170.3Rev. 38 Apr/19

K. Repair of Oversized 7/16-20UNF-3B Tapped Holes in "Y", "D", and "E" Shank Blade Counterweight Knob

(1) General

(a) This section contains the recommended procedures from Hartzell Propeller Inc. for repairing oversized 7/16-20UNF-3B tapped holes.

WARNING: CHROMIC ACID IS TOXIC. AVOID CONTACT WITH SKIN OR CLOTHING.

CAUTION: AT OVERHAUL, BEFORE THE THREAD INSERT IS INSTALLED, THE BLADE MUST BE CHROMIC ACID ANODIZED.

(2) At overhaul, before the thread insert is installed, chromic acid anodize the blade in accordance with the Chromic Acid Anodize chapter of Hartzell Standard Practices Manual 202A (61-01-02).

CAUTION: IF THE BLADE IS BEING REPAIRED, APPLY A CHEMICAL CONVERSION COATING TO THE OVERSIZED TAPPED HOLE WHERE THE THREAD INSERT WILL BE INSTALLED.

(3) If the blade is being repaired, before the thread insert is installed, apply a chemical conversion coating to the oversized tapped hole in accordance with the Chromic Acid Anodize chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(4) Recommended Materials List

(a) Vertical mill machine tool

(b) 0.5000 inch (12.700 mm) diameter, 4-flute end mill with 0.030 inch (0.76 mm) R. minimum corner, capable of milling to a depth of 1.020 inch (25.90 mm)



Rev. 38 Apr/1961-13-33

Y

X

Z

Expanding Arbor Fixture

Mill Table

Threaded Hole

Counterweight Knob

Blade Butt

Bearing Retention SurfaceX = 0

Expanding Arbor Fixture Figure 2-54

Aps

6232

(c) 0.5200 ± 0.0002 inch (13.208 ± 0.0050 mm) diameter reamer with 0.030 inch (0.76 mm) R. minimum corner

(d) 9/16-12UNC-2B bottom, roll tap (non-cutting)

(e) 0.625 inch (15.87 mm) diameter x 82 degree (or 90 degree) countersink (chamfer) tool

(f) 0.5156 inch (13.096 mm) diameter reamer

(g) B-6143-7 thread insert

(h) Insert tool TE68-( )

(i) Flat bottom punch

(j) Expanding arbor fixture

(k) Appropriately sized drill blanks

(l) Angle protractor

(m) Edge finder


BLADE SHANK OVERHAUL 61-13-33 Page 2-171Rev. 37 Dec/18

(5) Preparation

(a) Locally fabricate the expandable arbor fixture.

(b) Install the expandable arbor fixture to the mill table.

(c) Using an indicator, align the arbor to the chuck in the "Y" axis. Refer to Figure 2-54.

(d) Using an edge finder, locate the center of the arbor.

(e) Set the "Y" axis to zero with the arbor centered under the chuck.

(f) Install the blade to the arbor fixture. Do not tighten.

(g) Insert a drill blank that fits snugly into the hole to be repaired.

(h) Using a protractor against the drill blank, align the hole perpendicular to the mill table ("Z" axis), and tighten the blade on the arbor.

(i) Make sure that the center line of the drill blank is at a 90 degree angle to the mill table (on the "Z" axis). Refer to Figure 2-54.

(j) Using an edge finder, locate the blade bearing surface.

(k) With the blade bearing surface centered under the chuck, set the “X” axis to zero. Refer to Figure 2-54.

(6) Repair Procedure

(a) If only one hole is to be repaired, use the following procedure without moving to the second hole.

(b) In the "X" axis, X=0 is at the bearing retention surface. Refer to Figure 2-54.

1 All dimensions in the "X" axis are moving from X=0 toward the blade tip.

(c) The "Y" axis is perpendicular to the "X" axis, and parallel to the mill table. Refer to Figure 2-54.

(d) Move in the “X" axis:

1 For Y and D Shanks move to 2.900 inch (73.66 mm) dimension.2 For E shank move to either 2.900 inch (73.66 mm) or 2.736 inch

(69.49 mm) dimension.(e) Move in the “Y" axis 0.4375 inch (11.113 mm) to the first hole.

(f) Using the 0.500 inch end mill, drill 0.800-0.900 inch (20.32 - 22.86 mm) deep.

(g) Make sure that all existing thread is removed.

(h) Using compressed air, clear all of the debris from the hole.

(i) Move 0.875 inch (22.22 mm) in the “Y” axis to the second hole.



Rev. 35 Nov/1761-13-33

(j) Repeat steps 2.K.(6)(f) through 2.K.(6)(h) in this section.

(k) Using a 0.5200 inch (13.208 mm) reamer, ream the hole to the same depth attained in paragraph K.(6)(f) of this chapter.

(l) Move 0.875 inch (22.22 mm) in the “Y" axis to the first hole.

(m) Repeat step 2.K.(6)(k) in this section.

(n) Using a 0.625 inch (15.87 mm) countersink (chamfer) tool, chamfer the hole to a depth of 0.030 - 0.045 inch (0.76 - 1.14 mm) on the low side of the hole.

(o) Using compressed air, clear all of the debris from the drilled hole.

(p) Roll tap 9/16-12UNC-2B to 0.650 inch (16.51 mm) minimum depth.

(q) Using compressed air, clear all of the debris from the tapped hole.

(r) Move 0.875 inch (22.22 mm) in the “Y” axis to the second hole.

(s) Repeat steps K.(6)(p) and K.(6)(q) in this section.

(t) Using a 0.5156 inch (13.096 mm) diameter reamer, ream the thread minor diameter to 0.5150 +0.005, -0.000 inch (13.081 +0.12, - 0.00 mm).

(u) Using the applicable plug gauges, inspect the pitch diameter and the minor diameter of the thread.

(v) Install the B-6143-7 thread insert to 0.010 - 0.030 inch (0.25 - 0.76 mm) below the surface.

(w) Using insert tool TE68-( ), drive the locking pins down until the tool stops on the knob.

(x) Using a flat bottom punch, drive each pin down until it is flush with the surface of the thread insert.

(y) Remove all burrs from the each hole.

(z) Using compressed air, remove all debris from each hole.

(aa) Using a 7/16-20 UNF-3B thread gauge and a plug gauge, inspect each completed hole.

(7) Final Inspection

(a) Visually inspect the repaired blade for appearance and completeness.

(b) Reinspect the thread size and the depth of the B-6143-7 thread insert.

(c) Inspect the part identification for the serial number and the part number to make sure that they match all documentation.



L. Repair of Oversized 1/2-20UNF-3B Tapped Holes in "D" and "E" Shank Blade Counterweight Knob

(1) General

(a) This section contains the recommended procedures from Hartzell Propeller Inc. for repairing oversized 1/2-20UNF-3B tapped holes.


CAUTION: AT OVERHAUL, BEFORE THE THREAD INSERT IS INSTALLED, THE BLADE MUST BE CHROMIC ACID ANODIZED.

(2) At overhaul, before the thread insert is installed, chromic acid anodize the blade in accordance with the Chromic Acid Anodize chapter of Hartzell Standard Practices Manual 202A (61-01-02).

CAUTION: IF THE BLADE IS BEING REPAIRED, APPLY A CHEMICAL CONVERSION COATING TO THE OVERSIZED TAPPED HOLE WHERE THE THREAD INSERT WILL BE INSTALLED.

(3) If the blade is being repaired, before the thread insert is installed, apply a chemical conversion coating to the oversized tapped hole in accordance with the Chromic Acid Anodize chapter of Hartzell Standard Practices Manual 202A (61-01-02).

(4) Recommended Materials List(a) Vertical mill machine tool(b) 0.5625 inch (14.288 mm) diameter, 4-flute end mill with

0.030 inch (0.76 mm) R. minimum corner, capable of milling to a depth of 1.020 inch (25.90 mm)

(c) 0.5781 ± 0.0002 inch (14.684 ± 0.0005 mm) diameter reamer with 0.030 inch (0.76 mm) R. minimum corner

(d) 5/8-11UNC-2B bottom, roll tap (non-cutting)(e) 0.6875 inch (17.463 mm) diameter x 82 degree (or 90 degree) countersink

(chamfer) tool(f) 0.5781 inch (14.684 mm) diameter reamer(g) B-6143-8 thread insert (h) Insert tool TE68-( )(i) Flat bottom punch(j) Expanding arbor fixture (k) Appropriately sized drill blanks(l) Angle protractor(m) Edge finder



Rev. 35 Nov/1761-13-33

(5) Preparation

(a) Locally fabricate the expandable arbor fixture.

(b) Install the expandable arbor fixture to the mill table.

(c) Using an indicator, align the arbor to the chuck in the “Y” axis. Refer to Figure 2-54.

(d) Using an edge finder, locate the center of the arbor.

(e) With the arbor centered under the chuck, set the “Y” axis to zero.

(f) Install the blade to the arbor fixture. Do not tighten.

(g) Insert a drill blank that fits snugly into the hole to be repaired.

(h) Using a protractor against the drill blank, align the hole perpendicular to the mill table ("Z" axis).

(i) Tighten the blade on the arbor.

(j) Make sure that the center line of the drill blank is at a 90 degree angle to the mill table (on the "Z" axis). Refer to Figure 2-54.

(k) Using an edge finder, locate the blade bearing surface.

(l) With the blade bearing surface centered under the chuck, set the “X” axis to zero. Refer to Figure 2-54.

(6) Repair Procedure

(a) If only one hole is to be repaired, use the following procedure without moving to the second hole.

(b) In the "X" axis, X=0 is at the bearing retention surface. Refer to Figure 2-54.

1 All dimensions in the "X" axis are moving from X=0 toward the blade tip.

(c) The "Y" axis is perpendicular to the "X" axis, and parallel to the mill table.

(d) Move in the "X" axis to 2.900 inch (73.660 mm) dimension.

(e) Move in the "Y" axis 0.500 inch (12.700 mm) to the first hole.

(f) Using the 0.5625 inch end mil, drill 0.860-0.960 inch (21.844 - 24.38 mm) deep. Refer to Figure 2-54.

(g) Make sure that all existing thread is removed.

(h) Using compressed air, clear all of the debris from the hole.

(i) Move 1.000 inch (25.400 mm) in the "Y" axis to the second hole.

(j) Repeat steps 2.L.(6)(f) through 2.L.(6)(h) in this section.

(k) Using a 0.5781 inch (13.208 mm) reamer, ream the hole to the same depth attained in paragraph L.(4)(f) of this chapter.



(l) Move 1.000 inch (25.400 mm) in the "Y" axis to the first hole.

(m) Repeat step 2.L.(6)(k) in this section.

(n) Using a 0.6875 inch (17.463 mm) countersink (chamfer) tool, chamfer the hole to a depth of 0.030 - 0.045 inch (0.76 - 1.14 mm) on the low side of the hole.

(o) Using compressed air, clear all of the debris from the drilled hole.

(p) Roll tap 5/8 -11UNC-2B to 0.680 inch (17.27 mm) minimum depth.

(q) Using compressed air, remove all of the debris from the tapped hole.

(r) Move 1.000 inch (25.40 mm) in the "Y" axis to the second hole.

(s) Repeat steps 2.L.(6)(n) through 2.L.(6)(q) in this section.

(t) Using a 0.5781 inch (14.684 mm) diameter reamer, ream the thread minor diameter to 0.5770 +.005, -.000 inch (14.656 +.127, - 0.000 mm).

(u) Using the applicable plug gauges, inspect the pitch diameter and the minor diameter of the thread.

(v) Install the B-6143-8 thread insert to 0.010 - 0.030 inch (0.25 - 0.76 mm) below the surface.

(w) Using insert tool TE68-( ), drive the locking pins down until the tool stops on the knob.

(x) Using a flat bottom punch, drive each pin down until it is flush with the surface of the thread insert.

(y) Remove all burrs from each hole.

(z) Using compressed air, remove all of the debris from each hole.

(aa) Using a 1/2-20 UNF-3B thread gauge and a plug gauge, inspect each completed hole.

(7) Final Inspection

(a) Visually inspect the repaired blade for appearance and completeness.

(b) Reinspect the thread size and the depth of the B-6143-8 thread insert.

(c) Inspect the part identification for the serial number and part number to make sure that they match all documentation.

M. B-6143-( ) Thread Insert Removal

(1) For instructions about the removal of a B-6143-( ) thread insert, refer to the Aluminum Hub Overhaul chapter of Hartzell Standard Practices Manual 202A (61-01-02).



Rev. 35 Nov/1761-13-33

N. Blade Counterweight Knob Threaded Insert Removal

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS.

(1) Using the applicable threaded insert tool TE389-( ), remove the threaded insert.

(a) Discard the threaded insert after removal.

(b) For installation of threaded inserts, refer to the section, "Repair of Oversized 7/16-20UNF-3B Tapped Holes in "Y", "D", and "E" Shank Blade Counterweight Knob" or "Repair of Oversized 1/2-20UNF-3B Tapped Holes in "D" and "E" Shank Blade Counterweight Knob" in this chapter.



Blade Counterweight Knob Surface Figure 2-55

Zone 1

Dowel Pin Hole

Counterweight Attachment Holes

Zone 2

Zone 3



Rev. 37 Dec/1861-13-33


A. BLADE COUNTERWEIGHT KNOB SURFACE Top Surface, Zone 1 Refer to Figure 2-55

(1) Visually examine the counterweight knob top surface, Zone 1 for damage.

The maximum permitted depth of damage is 0.005 inch (0.12 mm).Damage must not not be greater 20% of Zone 1 surface area.

If damage is greater than the serviceable limits, remove damage by spot repair using an abrasive pad CM47, or equivalent.The maximum permitted depth of repair is 0.010 inch (0.25 mm). The maximum permitted area of repair is 20% of Zone 1 surface area.Clean the area in accordance with the Cleaning chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).If damage is greater than the serviceable limits or the corrective action limits, retire the blade in accordance with the Part Retirement procedures chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(2) Perform penetrant inspection on repaired areas.

Pin point penetrant indications are permitted.Linear pin point penetrant indications are not permitted.

If there are linear pin point penetrant indications, retire the blade in accordance with the Part Retirement procedures chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

Blade Counterweight Knob Surface Table 2-12




A. BLADE COUNTERWEIGHT KNOB SURFACE, continued Top Surface, Zone 2 Refer to Figure 2-55


The maximum permitted depth of damage is 0.005 inch (0.12 mm).Damage must not be greater than 50% of Zone 2 surface area.








Rev. 37 Dec/1861-13-33


A. BLADE COUNTERWEIGHT KNOB SURFACE, continued Top Surface, Zone 3 Refer to Figure 2-55


The maximum permitted depth of damage is 0.005 inch (0.12 mm).Damage must not be greater than 20% of Zone 3 surface area.









A. BLADE COUNTERWEIGHT KNOB SURFACE, continued Counterweight Attachments Holes Refer to Figure 2-55

(1) Visually examine the counterweight knob counter bore and chamfer surfaces for damage.

The maximum permitted depth of damage is 0.005 inch (0.12 mm).

If damage is greater than the serviceable limits, remove damage by spot repair using an abrasive pad CM47, or equivalent.The maximum permitted depth of repair is 0.010 inch (0.25 mm).Clean the area in accordance with the Cleaning chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).If damage is greater than the serviceable limits or the corrective action limits, retire the blade in accordance with the Part Retirement procedures chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(2) Visually examine the counterweight attachment hole for damaged threads.

A total accumulated damage of one thread is permitted.

If damage is greater than the serviceable limits, refer to the section, "Repair of Oversized 7/16-20UNF-3B Tapped Holes in "Y", "D", and "E" Shank Blade Counterweight Knob" or the section, "Repair of Oversized 1/2-20UNF-3B Tapped Holes in "D" and "E" Shank Blade Counterweight Knob" as appropriate for threaded insert (K-sert®) repair instructions.If preparation for a threaded insert (K-sert®) does not remove damage, retire the blade in accordance with the Part Retirement procedures chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).




Rev. 37 Dec/1861-13-33


A. BLADE COUNTERWEIGHT KNOB SURFACE, continued Counterweight Attachments Holes, continued Refer to Figure 2-55


Pin point penetrant indications are permitted on the counterweight knob counter bore and chamfer surfaces.Penetrant indications are not permitted on the counterweight attachment hole threads.Linear pin point penetrant indications are not permitted.

If there are penetrant indications on the counterweight attachment hole threads, retire the blade in accordance with the Part Retirement procedures chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).If there are linear pin point penetrant indications, retire the blade in accordance with the Part Retirement procedures chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).






A. BLADE COUNTERWEIGHT KNOB SURFACE, continued Dowel Pin Hole Refer to Figure 2-55

(1) Visually examine the dowel pin hole for damage.

The maximum permitted depth of damage is 0.005 inch (0.12 mm).The damaged area must not be greater than 25% of the dowel pin hole surface area.

If damage is greater than the serviceable limits, refer to Table 2-9 and Table 2-10 in this chapter for information on repair using oversized dowel pins.Install an oversized dowel pin to remove or decrease the damage to meet the serviceable limits.If damage remains after installation of the oversized dowel pin, retire the blade in accordance with the Part Retirement procedures chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(2) Examine the fit of the dowel pin in the blade counterweight dowel pin hole.

A tight fit is required between the dowel pin and the blade counterweight dowel pin hole sufficient to prevent movement of the dowel pin during operation of the propeller. A loose or insufficient fit is not permitted.

If the dowel pin fit is loose or insufficient, refer to Table 2-9 and Table 2-10 in this chapter for information on repair using oversized dowel pins.If the largest oversized dowel pin has been installed and the dowel pin fit is loose or insufficient, retire the blade in accordance with the Part Retirement procedures chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).






Rev. 37 Dec/1861-13-33

O. Blade Counterweight Knob Surface Check Criteria

(1) For inspection and repair limits for the blade counterweight knob surface, refer to Table 2-12.


BLADE AIRFOIL OVERHAULPage 3-1

Rev. 35 Nov/1761-13-33

BLADE AIRFOIL OVERHAUL - CONTENTS

1. Special Inspections and Procedures ..................................................................3-3

2. Overhaul Procedures ..........................................................................................3-3

A. General..........................................................................................................3-3

B. Blade Station Setup.......................................................................................3-5

C. Blade Straightening .....................................................................................3-11

D. Blade Grinding Requirements and Procedures ...........................................3-15

E. Blade Polishing Requirements and Procedures ..........................................3-19

F. Blade Final Polishing Requirements and Procedures .................................3-20

G. Chemically Etch Blade Airfoil.......................................................................3-21

H. Inspect Blade Airfoil Using Penetrant ..........................................................3-22

I. Blade Inspection Using Eddy Current .........................................................3-22

J. Dimensional Inspection of Blade Airfoil .......................................................3-23

K. Reduction in Blade Length ..........................................................................3-36

L. Shot Peened Blade Inspection and Rework ................................................3-42

M. Q Tip Blades ................................................................................................3-51

N. Lightning Strikes ..........................................................................................3-52

O. Blade Anodizing...........................................................................................3-53

P. Optional Blade Conversion..........................................................................3-54



Rev. 35 Nov/1761-13-33

LIST OF FIGURES

Measuring the Angle of a Bend on an Aluminum Blade ............ Figure 3-1 ................3-12

Leading Edge Profile ................................................................. Figure 3-2 ................3-14

Using Dowel Pins to Measure Blade Angle ............................... Figure 3-3 ................3-24

Blade Pitch Fixture TE438 ......................................................... Figure 3-4 ................3-25

Measuring Blade Angle.............................................................. Figure 3-5 ................3-25

Measuring Face Alignment ........................................................ Figure 3-6 ................3-33

Aluminum Blade Shot Peen Intensity Zone Specifications Option A Curved Trailing Edge ............................................. Figure 3-7 ................3-45

Aluminum Blade Shot Peen Intensity Zone Specifications Option B Parallel Trailing Edge ............................................ Figure 3-8 ................3-46

Shot Peening Shank Coverage ................................................. Figure 3-9 ................3-47

"Q" Tip Aluminum Propeller Blades .......................................... Figure 3-10 ...............3-50

LIST OF TABLES

Distance From Blade Butt to 0-Inch Station ............................... Table 3-1 ...................3-4

Station Setup for Aluminum Hub "Lightweight" Turbine Propeller Assembly .................................................. Table 3-2 ...................3-6

Station Setup for Aluminum Hub "Compact" ("Y" Shank) Propeller Assembly .............................................................. Table 3-3 ...................3-6

Station Setup for Steel Hub Turbine Engine Propeller Assembly .............................................................. Table 3-4 ...................3-6

Station Setup for Steel Hub Piston Engine Propeller Assembly .............................................................. Table 3-5 ...................3-7

Aluminum Blade Bend Limits ..................................................... Table 3-6 .................3-10

Dowel Pin Placement ................................................................. Table 3-7 .................3-27

Blade Twist Limits ....................................................................... Table 3-8 .................3-32

Shot Peened Aluminum Blades .................................................. Table 3-9 .................3-40



Rev. 28 Sep/1261-13-33


WARNING: THERE ARE MANDATORY INSPECTIONS AND PROCEDURES FOR SPECIFIC APPLICATIONS THAT MUST BE COMPLIED WITH IN ADDITION TO THE REQUIREMENTS OF THIS CHAPTER. A LIST OF THESE APPLICATIONS CAN BE FOUND IN THE TABLE OF CONTENTS OF THE SPECIAL INSPECTIONS AND PROCEDURES CHAPTER OF THIS MANUAL. FAILURE TO COMPLY WITH THE REQUIREMENTS WILL RESULT IN IMPROPER INSPECTION, REPAIR, AND OVERHAUL OF THE EFFECTED COMPONENT.

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

A. Refer to the Table of Contents of the Special Inspections and Procedures chapter of this manual to find additional requirements that apply to certain assemblies.

B. The applicable mandatory inspections and procedures for a specific application, must be complied with in addition to those requirements listed in this chapter.

2. Overhaul Procedures

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.

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

A. General

(1) The following procedures are to be performed during overhaul. To determine the specific procedures that apply to a particular blade model, refer to the traveler for that blade. Refer to the Appendix B - Travelers chapter of this manual.



Rev. 27 Sep/1161-13-33

Distance From Blade Butt to 0-Inch Station Table 3-1

Shank Type

Distance From Blade Butt to 0-Inch Station

"Y" 1.0 Inch (25.4 mm)*

"D" 1.0 Inch (25.4 mm)

"E" 1.0 Inch (25.4 mm)

"X" 4.150 Inches (105.41 mm)†

"V" 4.150 Inches (105.41 mm)†

"MV" 4.150 Inches (105.41 mm)†

"P" 4.512 Inches (114.60 mm)

"R" 4.512 Inches (114.60 mm)

"M" 4.512 Inches (114.60 mm)

"T" 4.512 Inches (114.60 mm)

"W" 4.512 Inches (114.60 mm)‡

"Z" 4.512 Inches (114.60 mm)‡

NOTE: These dimensions apply to all blades not in a propeller assembly. Factors such as type of hub and number of blades in the propeller assembly do not affect these dimensions.

Exceptions: * 9684 Blade is 2.0 Inches (50.8 mm)

† 8833 Blade is 4.250 Inches (108.0 mm)

‡ 8447 and 8847 Blades are 4.312 Inches (109.5 mm)



Rev. 27 Sep/1161-13-33

B. Blade Station Setup

CAUTION 1: INSTRUCTIONS AND PROCEDURES IN THIS SECTION INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS.

CAUTION 2: DO NOT CONFUSE BLADE STATION WITH REFERENCE BLADE RADIUS. BLADE STATION AND REFERENCE BLADE RADIUS OF THE SAME NUMBER MAY NOT ALWAYS INDICATE THE SAME LOCATION ON THE BLADE.

CAUTION 3: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE STRENGTH OR FUNCTION OF THE PROPELLER.


(1) Blade stations are used during the repair or overhaul process of a blade to define a blade span location for dimensional measurement.

(2) Using a non-graphite pencil CM162 or equivalent, mark blade stations within ± 0.031 inch (0.81 mm) of the specified dimensions established from the 0-inch station.

(3) Reference blade radius is measured from the center of the propeller hub to a predetermined reference location on the blade for blade angle measurement. A yellow adhesive stripe (Blade Angle Reference Tape CM160) is usually located at the reference blade radius location. Refer to the applicable overhaul manual for blade angle reference tape application instructions.

(a) Determining Blade Stations for a Bare Blade

1 Blade stations are established in reference to the center line of the propeller hub.

2 When working with a blade not installed on a hub, it is necessary to establish the location of the 0-inch station. From this reference point, all other blade stations can be established for the purpose of completing dimensional inspections.

3 Establishment of the 0-inch station is accomplished by measuring from the blade butt inboard toward the center of rotation.

4 Shank types have varying dimensions on the distance from the blade butt to the 0-inch station.

5 The dimensions to establish the 0-inch station can be found in Table 3-1 or in the blade specification tables.



Rev. 27 Sep/1161-13-33

Station Setup for Aluminum Hub "Compact" ("Y" Shank) Propeller Assembly Table 3-3

Hub Centerline to 0 Inch Station2 Blade 0.0 inch3 Blade 1.0 inch (25.4 mm)3 Blade

Model F9684 0.0 inch

4 Blade 1.875 inches (47.63 mm)

Station Setup for Steel Hub Turbine Engine Propeller Assembly Table 3-4

Hub Centerline to 0 Inch Station 3 Blade (A3VF-7[ ], A3MVF-7[ ] and B3TF-7[ ])

0.0625 Inch (1.587 mm)

3 Blade (All Others) 0.25 Inch (6.3 mm) 4 Blade 0.75 Inch (19.0 mm) 5 Blade 1.60 Inch (40.6 mm)

Station Setup for Aluminum Hub "Lightweight" Turbine Propeller AssemblyTable 3-2

Hub Centerline to 0 Inch Station3 Blade 1.50 inches (38.1 mm)4 Blade 1.875 inches (47.6 mm)5 Blade 2.875 inches (73.0 mm)6 Blade 3.703 inches (94.1 mm) (HC-A6A)6 Blade 3.750 inches (95.3 mm) (HC-E6A)



Rev. 27 Sep/1161-13-33

Station Setup for Steel Hub Piston Engine Propeller Assembly Table 3-5

Hub Centerline to0-Inch Station(8833 Blade)

Hub Centerline to0-Inch Station

(All Other Blades)

HC-12(X,V)20 -0.10 inch (-2.5 mm) 0 inch (0 mm)

HC-13(X,V)20 0.20 inch (5.0 mm) 0.30 inch (7.6 mm)

HC-D2(X,V,MV)20 0.025 inch (0.63 mm) 0.125 inch (3.17 mm)

HC-D3(X,V,MV)20 0.20 inch (5.0 mm) 0.30 inch (7.6 mm)

HC-82(X,V)20 -0.10 inch (-2.5 mm) 0 inch (0 mm)

HC-82(X,V)F,L 0 inch (0 mm) 0.10 inch (2.5 mm)


HC-83(X,V)F-1,-2 0.20 inch (5.0 mm) 0.30 inch (7.6 mm)

HC-83(X,V)F-3 0.30 inch (7.6 mm) 0.40 inch (10.16 mm)


HC-A2(X,V,MV)(F,K,L) 0.06 inch (1.5 mm) 0.16 inch (4.0 mm)

HC-A2(X,V,MV)20-1,-2,-5 0.04 inch (1.0 mm) 0.14 inch (3.5 mm)

HC-A2(X,V,MV)20-4 -0.05 inch (-1.2 mm) 0.05 inch (1.1 mm)

HC-A3(X,V,MV)(F,K,20,30,31) 0.20 inch (5.0 mm) 0.30 inch (7.6 mm)


(8447 & 8847 Blades)


(All Other Blades)

HC-92(W,Z)(F,K) 0 inch (0 mm) -0.20 inch (-5.0 mm)

HC-93Z20 0.20 inch (5.0 mm) 0 inch (0 mm)

HC-B3W(20,N) 0.398 inch (10.10 mm) 0.198 inch (5.02 mm)

HC-B3(R,W)20 0.19 inch (4.8 mm) -0.01 inch (-0.2 mm)

HC-B3(P,Z)20 0.198 inch (5.02 mm) -0.002 inch (-0.05 mm)

HC-B3(R,W)30 0.44 inch (11.1 mm) 0.24 inch (6.0 mm)

HC-B3(P,Z)30 0.448 inch (11.37 mm) 0.248 inch (6.29 mm)



Rev. 27 Sep/1161-13-33

(b) Determining Blade Stations for a Blade in a Propeller Assembly

CAUTION: BLADE STATIONS MUST BE MARKED WITHIN ± 0.032 INCH (0.81 mm) OF THE SPECIFIED DIMENSIONS ESTABLISHED FROM THE 0-INCH STATION.

1 If it is necessary to establish the blade stations for a blade that is installed on an aircraft, determine the distance from the hub centerline to the 0-inch station using Table 3-2, 3-3, 3-4, or 3-5.

a This dimension is added to (or subtracted from, if it is negative) the desired blade station to be marked.

b The sum of the two numbers is the distance from the hub centerline to the desired blade station to be marked.

c Example: A blade in an HC-B3TN-5/T10282 propeller assembly is suspected of being below minimum thickness at the 35-inch (889 mm) station. From Table 3-4, it can be determined that the distance from the hub centerline to the 0-inch station for a 3 bladed steel hub turbine propeller is +0.25 inch (6.35 mm). According to the blade specification table for the T10282 blade, the blade stations defined near the 35-inch (889 mm) station are the 30-, 36-, and 42-inch (762, 914, and 1067 mm) blade stations. If +0.25 inch (6.35 mm) is added to each of the defined stations, the result would be 30.25, 36.25, and 42.25 inches (768.35, 920.75, and 1073.15 mm). From the hub centerline, measure out 30.25, 36.25, and 42.25 inches (768.35, 920.75, and 1073.15 mm).



d Using a non-graphite pencil CM162 or equivalent, mark a line for each blade station.

2 Another method of establishing station lines is to measure inboard from the blade tip, but this method is not recommended because of the accuracy of the blade length.



Rev. 27 Sep/1161-13-33

(c) Determining the Actual Diameter of a Propeller Assembly

1 It is necessary to determine the actual diameter of a propeller assembly to make sure that it is not below the minimum diameter permitted for the aircraft it is installed on.

2 There are two methods for determining the propeller diameter.

a To determine the actual diameter of the propeller, add the distance from the hub centerline to the blade butt (refer to Table 3-1 plus applicable dimension from Table 3-2, 3-3, 3-4, or 3-5) to the actual blade length (from blade butt to blade tip, not 0-inch station to tip). Multiply the sum by two. This equals the actual propeller diameter.

2 × (Hub Centerline to Blade Butt + Blade Length) = Actual Propeller Diameter

b To determine the diameter of the propeller model because it may vary from the blade model designation, add the distance from the hub centerline to the blade 0-inch station (refer to Table 3-2, 3-3, 3-4, or 3-5) to the blade tip station (refer to the Blade Tip Drawings). Multiply the sum of these numbers by two. This equals the diameter of the propeller assembly unless it has been modified.

2 × (Hub Centerline to 0-Inch Station + Blade Tip Station) = Propeller Diameter

c For example, to determine the propeller diameter for an HC-B3TN-5K/10178-13, determine the distance from the hub centerline to the 0-inch station. Because this is an assembly for a steel hub turbine aircraft, it is necessary to use Table 3-4. This dimension is 0.25 inch (0.63 mm). According to the Blade Tip Drawing for 10178 blades, the tip station for a 10178-13 is 44 inches (1117.6 mm). Forty-four plus 0.25 inch (1117.6 plus 0.63 mm) equals 44.25 (1123.9 mm) inches. When multiplied by two, you get a total of 88.50 inches (2247.8 mm).

3 The tolerance for an assembled propeller is ± 0.1875 inch (4.76 mm).

a For example, if an aircraft type certificate states that the minimum diameter is 78 inches (1981.2 mm), the actual propeller diameter could be between 77.8125 inches and 78.1875 inches (1976.438 mm and 1985.962 mm).



Rev. 23 Mar/0861-13-33

Aluminum Blade Bend Limits Table 3-6

BladeThickness(Inches)

MaximumAngle of

Bend(Degrees)

BladeThickness(Inches)

MaximumAngle of

Bend(Degrees)

Blade Thickness(Inches)

MaximumAngle of

Bend(Degrees)

0.060 (1.52 mm) 21.9 0.410 (10.41 mm) 14.5 0.760 (19.30 mm) 7.20.070 (1.77 mm) 21.7 0.420 (10.66 mm) 14.3 0.770 (19.55 mm) 6.90.080 (2.03 mm) 21.5 0.430 (10.92 mm) 14.1 0.780 (19.81 mm) 6.70.090 (2.28 mm) 21.3 0.440 (11.17 mm) 13.9 0.790 (20.06 mm) 6.50.100 (2.54 mm) 21.1 0.450 (11.43 mm) 13.7 0.800 (20.32 mm) 6.30.110 (2.79 mm) 20.8 0.460 (11.68 mm) 13.5 0.810 (20.57 mm) 6.10.120 (3.04 mm) 20.6 0.470 (11.93 mm) 13.3 0.820 (20.82 mm) 5.90.130 (3.30 mm) 20.4 0.480 (12.19 mm) 13.1 0.830 (21.08 mm) 5.70.140 (3.55 mm) 20.2 0.490 (12.44 mm) 12.8 0.840 (21.33 mm) 5.50.150 (3.81 mm) 20.0 0.500 (12.70 mm) 12.6 0.850 (21.59 mm) 5.30.160 (4.06 mm) 19.8 0.510 (12.95 mm) 12.4 0.860 (21.84 mm) 5.10.170 (4.31 mm) 19.6 0.520 (13.20 mm) 12.2 0.870 (22.09 mm) 4.80.180 (4.57 mm) 19.4 0.530 (13.46 mm) 12.0 0.880 (22.35 mm) 4.60.190 (4.82 mm) 19.2 0.540 (13.71 mm) 11.8 0.890 (22.60 mm) 4.40.200 (5.08 mm) 18.9 0.550 (13.97 mm) 11.6 0.900 (22.86 mm) 4.20.210 (5.33 mm) 18.7 0.560 (14.22 mm) 11.4 0.910 (23.11 mm) 4.00.220 (5.58 mm) 18.5 0.570 (14.47 mm) 11.2 0.920 (23.36 mm) 3.80.230 (5.84 mm) 18.3 0.580 (14.73 mm) 10.9 0.930 (23.62 mm) 3.60.240 (6.09 mm) 18.1 0.590 (14.98 mm) 10.7 0.940 (23.87 mm) 3.40.250 (6.35 mm) 17.9 0.600 (15.24 mm) 10.5 0.950 (24.13 mm) 3.20.260 (6.60 mm) 17.7 0.610 (15.49 mm) 10.3 0.960 (24.38 mm) 2.90.270 (6.85 mm) 17.5 0.620 (15.74 mm) 10.1 0.970 (24.63 mm) 2.70.280 (7.11 mm) 17.3 0.630 (16.00 mm) 9.9 0.980 (24.89 mm) 2.50.290 (7.36 mm) 17.1 0.640 (16.25 mm) 9.7 0.990 (25.14 mm) 2.30.300 (7.62 mm) 16.8 0.650 (16.51 mm) 9.5 1.000 (25.40 mm) 2.10.310 (7.87 mm) 16.6 0.660 (16.76 mm) 9.3 1.010 (25.69 mm) 1.90.320 (8.12 mm) 16.4 0.670 (17.01 mm) 9.1 1.020 (25.90 mm) 1.70.330 (8.38 mm) 16.2 0.680 (17.27 mm) 8.8 1.030 (26.16 mm) 1.50.340 (8.63 mm) 16.0 0.690 (17.52 mm) 8.6 1.040 (26.41 mm) 1.30.350 (8.89 mm) 15.8 0.700 (17.78 mm) 8.4 1.050 (26.67 mm) 1.10.360 (9.14 mm) 15.6 0.710 (18.03 mm) 8.2 1.060 (26.92 mm) 0.80.370 (9.39 mm) 15.4 0.720 (18.28 mm) 8.0 1.070 (27.17 mm) 0.60.380 (9.65 mm) 15.2 0.730 (18.54 mm) 7.8 1.080 (27.43 mm) 0.40.390 (9.90 mm) 14.9 0.740 (18.79 mm) 7.6 1.090 (27.68 mm) 0.2

0.400 (10.16 mm) 14.7 0.750 (19.05 mm) 7.4 1.100 (27.94 mm) 0.0



Rev. 28 Sep/1261-13-33

C. Blade Straightening


(1) A bent blade may be straightened if it meets the following criteria:(a) There is no evidence of damage caused by impact on the blade butt or

retention radii.(b) There is no evidence of damage caused by impact to the blade bore.(c) The pitch change knob is not bent (if applicable).(d) The blade or blade tip bend is within the permitted bend limits specified

in the Aluminum Blade Bend Limits Table 3-6 and the Twist Allowances Table 3-8.

(2) If the blade tip is bent beyond the permitted limits, a blade may not be converted to another model or to a shorter length version of the existing model.

NOTE: In the past, blades that were bent beyond allowable limits were sometimes reduced in diameter when the shortened blade model was completely inboard of the bend. This practice is no longer permitted.

(3) If a blade does not meet the criteria specified in 2.C.(1)(a) through 2.C.(1)(d), retire the blade from service.



Rev. 23 Mar/0861-13-33

Measuring the Angle of a Bend on an Aluminum Blade Figure 3-1

Thickness of Blade at Centerline of Bend

1 inch (25.4 mm)

Angle of Bend

APS0695

(4) Determining Repairability of a Bent Blade(a) In the past, blades that were bent beyond the permitted limits were

sometimes reduced in diameter when the shortened blade model was completely inboard of the bend. This practice is no longer permitted.

(b) Using a protractor similar to the one shown in Figure 3-1, measure the angle of the bend.



1 Using a non-graphite pencil CM162 or equivalent, mark the blade 1 inch (25.4 mm) on each side of the centerline of the bend.

2 Put the protractor on the blade so that it is tangent to the blade and that there is 1 inch on each side of the centerline of the bend.

3 Make a record of the angle of the bend.



Rev. 23 Mar/0861-13-33

(c) If it is not possible to mark and locate the protractor 1 inch (25.4 mm) on each side of the bend, measure as closely as possible to the apex of the bend to achieve as accurate a measurement of the angle as possible.

(d) Measure the thickness of the blade at the centerline of the bend.(e) Using the measurement for the blade thickness established in section

2.C.(4)(d), find the maximum angle of bend in Table 3-6. 1 If the bend angle established in section 2.C.(4)(b) is less than or

equal to the maximum angle of bend, the blade may be straightened. 2 If the bend angle established in section 2.C.(4)(b) is greater than the

maximum angle of bend, retire the blade from service.(f) Blades may only be straightened by qualified personnel at an

appropriately licensed repair facility.(g) If a blade submitted for overhaul appears to have been straightened in the

field, retire the blade from service.

NOTE: The overhaul shop cannot determine if the maximum angle of bend was exceeded.



Rev. 28 Sep/1261-13-33

(5) Straightening a Bent Blade

CAUTION: STRAIGHTENING BLADES MUST ONLY BE ACCOMPLISHED BY QUALIFIED PERSONNEL AT AN APPROPRIATELY LICENSED REPAIR FACILITY. IRREPARABLE DAMAGE MAY BE DONE TO THE BLADE DURING THE STRAIGHTENING PROCESS.

(a) Straightening a blade must be accomplished before the grinding process except as follows:1 If after grinding the blade face alignment is out of tolerance, the blade

may be bent to bring it within tolerance.(b) Support the blade shank in a block under a hydraulic press. (c) Put a second block outboard of the area to be straightened.(d) Position the blade so that the press applies force approximately six inches

inboard of the bent area.

(e) Measure the blade face alignment. Refer to paragraph 2.J.(7) to determine if the blade is within tolerance.

(f) The condition of the leading and trailing edges of the blade also determines if the blade can be returned to service. Refer to Figure 3-2.

(g) Visible waves or kinks are not permitted.

(h) After the straightening process, chemical etch and penetrant inspect the blade in the area of the bend. Refer to the Penetrant Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

Leading Edge Profile Figure 3-2

LEADEDG1-4

Yes No No No



Rev. 29 Nov/1261-13-33

D. Blade Grinding Requirements and Procedures


(1) Grinding or polishing the blade airfoil is permitted for removal of paint and anodize layers.

(a) Grinding is defined as using an abrasive disc or pad that has no finer than 180-grit.

(b) Polishing is defined as using an abrasive disc or pad that has 200-grit or finer.

1 For aluminum blades, perform a penetrant inspection of the blade before polishing.

(2) The following procedures are the in-house requirements of Hartzell Propeller Inc. Industry grinding standards may be used to achieve a similar effect.

(a) Aluminum propeller blades must be ground and polished at each blade overhaul.

1 Significant dimples and irregular surfaces, although permitted for many field repairs, must be removed at overhaul.

2 Nicks, gouges, corrosion, and other damage must be removed.

3 The blade must have a smooth, even surface.

(b) Horizontally mount the blade on the work surface.

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.


(d) Using a non-graphite pencil CM162 or equivalent, mark station lines on the face of the blade in accordance with Appendix C - Blade Specification Tables.

1 Mark the blade stations within ± 0.032 inch (0.81 mm) of the specified dimensions established from the 0-inch station.

(e) Dimensionally inspect the thickness of the blade at the thickest point of each blade station.

1 If the blade thickness is below the minimum at any blade station, retire the blade from service.



Rev. 35 Nov/1761-13-33

(f) Measure the width of the blade at each blade station.

1 If the blade width is below the minimum at any blade station, retire the blade from service.

CAUTION 1: DO NOT GRIND THE RETENTION AREA OF THE BLADE. STOP GRINDING AT THE POINT WHERE THE AIRFOIL BEGINS TO FLARE TO THE CONCENTRIC PART OF THE SHANK.

CAUTION 2: MAINTAIN THE REQUIRED CONTOUR OF EACH SURFACE OF THE BLADE. THE TIP, LEAD AND TRAIL EDGE, AND FACE AND CAMBER CONTOURS ARE CRITICAL AND MAY NOT BE CHANGED BY GRINDING.

(g) Before grinding apply a small amount of a grinding lubrication composition, such as Matchless® grease, to each side of the blade.

CAUTION: BLADES CAN BE OVERHEATED BY THE GRINDING OR POLISHING PROCESS OR IF HEATED IN ORDER TO STRAIGHTEN A BLADE. REFER TO THE SPECIAL INSTRUCTIONS CHAPTER OF HARTZELL PROPELLER INC. MANUAL 202A.

(h) Grind using a grinder and an abrasive disk or pad that has no finer than 180-grit.

1 Grind chordwise or parallel to the centerline of the blade.

2 Maintain the contour of each blade surface.

3 Maintain the radius of the leading and trailing edges.

NOTE: It is recommended that blades in a set are balanced during the grinding process. This will make final balancing of the propeller assembly easier. Refer to the Blade Balancing chapter of this manual for balancing procedures.



Rev. 27 Sep/1161-13-33

CAUTION 1: DO NOT GRIND ON THE MATING SURFACE OF A BLADE COUNTERWEIGHT KNOB. ALL OTHER SURFACES OF THE COUNTERWEIGHT KNOB MAY BE LIGHTLY GROUND.

CAUTION 2: ALWAYS FILE PARALLEL TO THE CENTERLINE OF THE BLADE. FILING PERPENDICULAR TO THE CENTERLINE MAY CREATE STRESS RISERS IN THE BLADE.

(i) Using lengthwise strokes with a rasp and file, smooth out the leading edge and trailing edge and the blade tip, maintaining a radius on all edges. Refer to Figure 3-2.

1 Refer to Appendix C of this manual for tip shape details for each blade model in its new condition. The figures are provided with the intention that the repaired blade keeps the same character as the original blade.

2 The following limits apply only to blades that have a square tip shape with rounded corners. These blades have two distinct tip radii - one for the leading edge and another for the trailing edge.

a For those blades whose specified tip corner radius is less than 1 inch (25.4 mm), the repaired tip corner radius can be as much as 3X the value shown in Appendix C, but must not exceed 2 inches (50.8 mm). If the specified tip corner radius is 1 inch (25.4 mm) or greater, the repaired radius may be up to 1 inch (25.4 mm) more than that shown in Appendix C.

b In certain cases, the tip corner radii of the original blade are located sufficiently close to one another that the blade resembles one with a full radius tip shape. As the repaired blade is reduced in chord width near the tip, the corner radii will move closer together and may actually converge to form a full radius. This condition is permitted if the tip width and radius are within specified limits.

3 "Delta" or "swept" tips, which are created by removing leading edge damage near the tip while maintaining the minimum permitted diameter, are not permitted and must be retired from service.

(j) Repeat the dimensional inspections of the blade thickness and width.

1 If the dimensions are below the minimum permitted tolerances, retire the blade from service.



Rev. 27 Sep/1161-13-33




Rev. 35 Nov/1761-13-33

E. Blade Polishing Requirements and Procedures


(1) General(a) For aluminum blades, perform a penetrant inspection of the blade before

polishing.(b) The following procedures are the in-house requirements for Hartzell

Propeller Inc. Industry polishing standards may be used to achieve a similar effect.

(2) Apply masking material to the shank area during the polishing process to prevent damage to the retention radius.

(3) Apply several streaks of grinding lubrication composition to the face and camber sides of the blade before polishing.

CAUTION: BLADES CAN BE OVERHEATED BY THE GRINDING OR POLISHING PROCESS OR IF HEATED IN ORDER TO STRAIGHTEN A BLADE. REFER TO THE SPECIAL INSTRUCTIONS CHAPTER OF HARTZELL PROPELLER INC. MANUAL 202A.

(4) Using a built up polish wheel coated with 200-grit to 220-grit aluminum oxide, polish the blade to remove all grinding marks.(a) Polish parallel to the centerline of the blade.(b) Polish the leading and trailing edges and the tip area. Maintain smooth

radii.(5) Remove the masking material from the shank area.

CAUTION: DO NOT POLISH THE BLADE SHANK RETENTION RADIUS OR THE MATING SURFACE OF THE BLADE COUNTERWEIGHT KNOB.

(6) Using a sander and a 200-grit to 220-grit abrasive disk or pad, polish the shank area and the sides of the counterweight knob.

(7) Using a strip of 200-grit to 240-grit emery cloth, polish the leading and trailing edges. Run the cloth parallel to the blade centerline.(a) If necessary to remove filing marks, 120-grit to 200-grit emery cloth may

be used, followed by polishing with 200-grit to 240-grit emery cloth.(8) Make sure that the radii do not thicken near the tip.(9) The leading edge radius must be round and smoothly blended as shown in

Figure 3-2.(10) Flat spots and sharp edges are not permitted.



Rev. 35 Nov/1761-13-33


(11) Using solvent CM23, clean the blade before the blade dimensional inspection.

F. Blade Final Polishing Requirements and Procedures


CAUTION 2: BLADES CAN BE OVERHEATED BY THE GRINDING OR POLISHING PROCESS OR IF HEATED IN ORDER TO STRAIGHTEN A BLADE. REFER TO THE SPECIAL INSTRUCTIONS CHAPTER OF HARTZELL PROPELLER INC. STANDARD PRACTICES MANUAL 202A (61-01-02).

(1) The following procedures are the in-house requirements for Hartzell Propeller Inc. Industry grinding standards may be used to achieve a similar effect.

CAUTION: GLASS BEAD CLEANING OF THE SURFACE OF THE BLADE IS NOT PERMITTED.

(2) The finishing procedure is performed to create a smooth blade surface on which to apply anodize and paint.


(3) Using solvent CM23, clean the blade.(4) Apply 200-grit to 220-grit greaseless abrasive composition to a cloth flap wheel. (5) Using an abrasive pad that has 400-grit or finer, polish the face and camber

side of the blade parallel to the blade centerline.



Rev. 35 Nov/1761-13-33

CAUTION: DO NOT POLISH THE BLADE SHANK RETENTION RADIUS OR THE MATING SURFACE OF THE BLADE COUNTERWEIGHT KNOB.

(6) Using an abrasive pad that has 400-grit or finer, polish the leading and trailing edges and the sides of the counterweight knob.

(7) Optional Polishing Procedure(a) General

1 The optional polishing procedure will help clean the blade after shot peening before applying anodize or chemical conversion coating and will also improve the blade appearance.

2 If the optional polishing procedure is performed, remove only the tops of the shot peening dimples (dents); do not completely remove the shot peening dimples (dents).

(b) Procedure

CAUTION: DO NOT COMPLETELY REMOVE THE SHOT PEENING DIMPLES (DENTS) WHEN PERFORMING THE OPTIONAL POLISHING PROCEDURE.

1 After shot peening has been completed, but before applying anodize or chemical conversion coating, lightly polish over the shot peened surface using one of the following:a A red abrasive pad such as CM47 or equivalent.b CM346 200-grit to 240-grit on a cloth wheel or an equivalent

non-metallic polishing pad.

G. Chemically Etch Blade Airfoil


CAUTION 2: DO NOT APPLY CHEMICAL ETCHING SOLUTION TO THE BLADE RETENTION RADIUS. CHEMICAL ETCHING SOLUTION MAY REMOVE MATERIAL AND WOULD REQUIRE THAT THE RETENTION RADIUS BE DIMENSIONALLY REINSPECTED AND VIEWED ON THE OPTICAL COMPARATOR (REFER TO THE BLADE SHANK OVERHAUL CHAPTER OF THIS MANUAL).

CAUTION 3: ETCHING IS AN ESSENTIAL PROCESS THAT IMPROVES THE VISIBILITY OF DEFECTS DURING PENETRANT INSPECTION. FAILURE TO CHEMICALLY ETCH THE BLADE AIRFOIL BEFORE PENETRANT INSPECTION MAY RESULT IN FAILURE TO DETECT CRACKS.



Rev. 35 Nov/1761-13-33


(1) Chemically etch all surfaces of the blade airfoil from the tip to approximately four inches (101 mm) outboard of the blade retention radius.

(2) For chemical etching procedures, refer to the Penetrant Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

H. Inspect Blade Airfoil Using Penetrant


NOTE: Penetrant Inspection of the blade shank is also required during overhaul. Refer to the Blade Shank Overhaul chapter of this manual.

(1) For required materials, penetrant application methods, and inspection and acceptance criteria refer to the Penetrant Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(2) Apply penetrant to all surfaces of the blade airfoil from the tip to approximately four inches (101 mm) outboard of the blade shank retention radius.

(3) If a blades with indications defined as unsatisfactory in accordance with the Penetrant Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02), retire the blade from service.

(4) Locally repair corrosion indications in accordance with the dimensional tolerances in the applicable Blade Specification Table and paragraph 2.J. of this chapter.

I. Blade Inspection Using Eddy Current


(1) Eddy current is an optional method that may be used in addition to penetrant inspection to inspect the blade airfoil for cracks or to confirm the existence of a crack.

(2) For procedures for inspecting aluminum blades using eddy current, refer to the Eddy Current Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).



Rev. 35 Nov/1761-13-33

J. Dimensional Inspection of Blade Airfoil


(1) Arbor Setup(a) To accurately inspect the blade dimensions, the center line of the blade

must be established. The distance from the blade table to the blade center line is 7.50 inches (190.5 mm).

NOTE: (7.50 inches [190.5 mm] is standard height for Hartzell Propeller Inc. tooling; locally fabricated tools may differ).

CAUTION: DO NOT ETCH, SCRIBE, PUNCH MARK, OR SIMILARLY IDENTIFY PARTS IN ANY MANNER THAT MAY BE HARMFUL TO THE STRENGTH OR FUNCTION OF THE PROPELLER.

1 Mark blade stations within ± 0.031 inch (0.78 mm) of the specified dimensions established from the 0-inch station.

2 Secure the blade on an arbor parallel to the inspection table.

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

3 Using a non-graphite pencil CM162 or equivalent, mark station lines (refer to paragraph 2.B. of this chapter).

4 Using a square, adjust the blade so that the set up station (generally 30-inch station, refer to the Blade Specification Tables) is perpendicular to the inspection table.

5 Using a height gauge set at 7.50 inches (190.5 mm), make a line with a non-graphite pencil CM162 or equivalent, at the blade tip and at approximately the 8-inch (203.2 mm) station of the blade.

(b) Rotate the blade 180 degrees.1 Using a square, level the blade at the 30-inch (762 mm) station.

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.


2 Using a height gauge and non-graphite pencil CM162 or equivalent, make a mark at the 7.50 inch (190.5 mm) line at the tip and at approximately the 8-inch (203.2 mm) station (the marks must be on the same side of the blade).



Rev. 35 Nov/1761-13-33

3 If the marks at the tip and inboard station do not line up with the existing marks made before the blade was rotated 180 degrees, adjust the arbor to bring the marks in-line.

(2) Measure the Blade Thickness(a) Dimensionally inspect the blade thickness at each blade station.

1 If the thickness at any blade station is less than the minimum listed in the applicable Blade Specification Table, retire the blade from service.

(3) Measure the Blade Width



(a) Using a non-graphite pencil CM162 or equivalent, mark chord lines perpendicular to the blade centerline.

(b) Dimensionally inspect the blade width at each blade station.1 If the width at any blade station is less the minimum listed in the

applicable Blade Specification Table, retire the blade from service.(4) Measure the Blade Length

(a) Measure the length of each blade in the propeller assembly starting at the 0-inch blade station. Refer to Table 3-1.

(b) The length of each blade in the propeller assembly must be within ± 0.125 inch (3.17 mm) of each other.

(c) Refer to paragraph 2.K. of this chapter for additional requirements about blade length.

(5) Measure the Blade Angle



(a) Using a non-graphite pencil CM162 or equivalent, mark chord lines perpendicular to the blade centerline.

(b) Before blade face alignment, measure the blade angle and correct, if necessary.

1 Correction of the blade angle affects the face alignment.2 Correction of the face alignment does not affect the blade angle.



Rev. 35 Nov/1761-13-33

Using Dowel Pins to Measure Blade Angle Figure 3-3

NOTE: Refer to Table 3-7 for applicable dowel pin diameters, D1, and D2 distance measurements.

W10212

ProtractorFACE

Dowel Pin Diameter

CAMBERDowel Pin Diameter

TRAILING EDGED1

D2

1 Inch (25.4 mm) Maximum Length Dowel Pin

Target Station1 Inch (25.4 mm) Maximum Length Dowel Pin

Blade Airfoil



Rev. 35 Nov/1761-13-33

Blade Pitch Fixture TE438 Figure 3-4

Measuring Blade Angle Figure 3-5

Clamp Block

Thumbscrew

Slide Bar

V-notch

W10

448

Bottom of Clamp Block Surface

Top of Clamp Block Surface

CAMBERCAMBER

FACEFA

CE

LEA

D

TRA

IL

Groove on the Bottom of the Clamp Block

Blade Station Mark

Hand Held Digital Blade Angle Protractor TE97 Aligned with the Grooves on the Bottom of the Clamp Block

Clamp BlockSlide Bar

Face Side

Camber Side

NOTE: Process shown is for a tractor installation.

W10

447A

, TP

I-104

77b



Rev. 35 Nov/1761-13-33

Dowel Pin Placement Table 3-7

Station (D1) - Distance from Trailing Edge (inch)

Dowel Diameter (inch)

(D2) - Distance from Trailing Edge (inch)


(F)689018 0.750 (19.05 mm) 1/4 4.92 (124.9 mm) 1/824 1.000 (25.40 mm) 3/16 4.48 (113.7 mm) 1/829 0.500 (12.70 mm) 3/16 3.70 (93.9 mm) 1/830 0.500 (12.70 mm) 3/16 3.40 (86.3 mm) 1/833 0.600 (15.24 mm) 5/32 2.71 (68.8 mm) 1/8

(F)706818 1.000 (25.40 mm) 1/4 5.590 (141.98 mm) 1/824 0.750 (19.05 mm) 1/4 5.590 (141.98 mm) 3/1630 1.500 (38.10 mm) 1/8 4.840 (122.93 mm) 1/8

(F)728218 0.715 (18.16 mm) 1/4 5.130 (130.30 mm) 1/824 0.250 (6.35 mm) 1/4 4.750 (120.65 mm) 1/829 0.250 (6.35 mm) 1/4 3.250 (82.55 mm) 1/830 0.760 (19.30 mm) 1/4 3.270 (83.05 mm) 3/1633 0.500 (12.70 mm) 1/4 2.610 (66.29 mm) 3/1636 0.280 (7.11 mm) 1/4 2.490 (63.24 mm) 3/16

(F)738218 0.750 (19.05 mm) 3/16 4.300 (109.22 mm) 1/824 0.200 (5.08 mm) 3/16 4.560 (115.82 mm) 1/8



* The 29-inch blade station corresponds to the 30-inch reference blade radius on 3-blade, Y-shank propellers. The data provided for 29-inch stations may sometimes be useful for setting blade angles in an assembled propeller.



Rev. 35 Nov/1761-13-33

Dowel Pin Placement Table 3-7, Continued








(F)769118 0.850 (21.59 mm) 1/4 5.400 (137.16 mm) 3/1624 0.335 (8.50 mm) 1/4 4.740 (120.39 mm) 3/1629 0.250 (6.35 mm) 3/16 4.390 (111.50 mm) 1/830 1.000 (25.40 mm) 1/4 4.600 (116.84 mm) 1/433 1.036 (26.31 mm) 1/4 3.902 (99.11 mm) 1/436 0.750 (19.05 mm) 1/4 3.450 (87.63 mm) 1/4




Rev. 35 Nov/1761-13-33





D9512, A, A-5.5, AE

18 1.500 (38.10 mm) 1/4 6.580 (167.13 mm) 1/824 1.000 (25.40 mm) 1/4 6.860 (174.13 mm) 1/830 0.500 (12.70 mm) 1/4 6.650 (168.91 mm) 5/3236 0.500 (12.70 mm) 3/16 5.870 (149.09 mm) 1/842 0.500 (12.70 mm) 3/16 4.120 (104.64 mm) 5/32

E9512(C,D,G)-118 1.500 (38.10 mm) 1/4 6.580 (167.13 mm) 1/824 1.000 (25.40 mm) 1/4 6.860 (174.24 mm) 1/830 0.500 (12.70 mm) 1/4 6.650 (168.91 mm) 5/3236 0.500 (12.70 mm) 3/16 5.870 (149.09 mm) 1/842 0.500 (12.70 mm) 3/16 4.120 (104.64 mm) 5/32

Dowel Pin Placement Table 3-7, Continued




Rev. 35 Nov/1761-13-33

(c) Preset the protractor to the setup measurement indicated in the applicable blade specification table in the Appendix C - Blade Specification Tables chapter of this manual.

(d) With the blade horizontally secured with the face side up, put the protractor on the blade setup station and rotate the blade until the protractor zeroes out.

(e) Lock the blade in this position.The contour of the face side of certain blades makes it impossible to use a straight edge protractor to measure the blade angle. In those cases, use one of the following two methods to measure blade angle; or proceed to step 2.J.(5)(f).

1 Method 1 - Using dowel pins to measure the blade angle

a Tape dowel pins on the face of the blade and put the protractor on the dowel pins (Figure 3-3).

b Use Table 3-7 as a guide for measuring the angle of certain (listed) blades by taping two dowel pins of specified diameter on the face side of the blade. Refer to Figure 3-3.

c Position the dowel pins at the specified distances (D1 and D2) from the trailing edge of the blade for consistency in measurement, as the blade leading edge may be filed away.

d Dowel pins must be a maximum length of 1 inch (25.4 mm).

e Beginning at the inboard stations, put the protractor on the dowel pins and read the measurement of each angle.

f Each measurement must be within the tolerance specified in the applicable Blade Specification Table.

2 Method 2 - Using blade pitch fixture TE438 to measure the blade angle

NOTE: Previously the blade pitch fixture TE438 was manufactured without the orientation marks "LEAD", "TRAIL", "FACE", and "CAMBER" marked on it.

a If the blade pitch fixture TE438 does not have the orientation marks "LEAD", TRAIL", FACE", and "CAMBER" marked on it, add the marks as shown in Figure 3-4 in accordance with the Parts Identification and Marking chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).(1) Maximum repeatability is obtained by using blade pitch

fixture TE438 marked as shown in Figure 3-4.

b Loosen the thumbscrews on the blade pitch fixture TE438. Refer to Figure 3-4.



Rev. 35 Nov/1761-13-33

c Slide the clamp blocks out to the ends of the slide bar.

d Beginning at the inboard station, position the blade so that the leading and trailing edges are in the V-notches of the clamp blocks in accordance with the markings on the blade pitch fixture TE438. Refer to Figure 3-5.

e Align the groove on the bottom surface of each clamp block with the applicable blade station on the face side of the blade. Refer to Figure 3-5.

f Tighten the thumbscrews on the clamp blocks of fixture TE438 to attach the fixture to the blade.

g Align the hand-held protractor TE97 with the grooves on the bottom of the two clamp blocks of the fixture TE438.

h Holding the hand-held protractor TE97 firmly with the grooves on the bottom of the two clamp blocks of the fixture TE438, read the measurement of the angle. Refer to Figure 3-5.

i This measurement must be within the tolerance specified in the applicable Blade Specification Table in Appendix C of this manual.

j Proceed to step 2.J.(5)(g).

(f) Beginning at the inboard stations, put the protractor on the blade and read each angular measurement. Each measurement must be within the tolerance specified in the applicable Blade Specification Table.

(g) If a blade station is out of tolerance twist the blade to bring it back into tolerance. Refer to Blade Twisting in this section.

(h) Repeat the blade angle measurement procedure at each station specified in the applicable blade specification table in Appendix C of this manual.



Rev. 35 Nov/1761-13-33

Blade Twist Limits Table 3-8

BladeThickness*

(inches)

MaximumAngle ofTwist**

(degrees)

BladeThickness*

(inches)


(degrees)

BladeThickness*

(inches)


(degrees)0.06 (1.5 mm) 1.79 0.41 (10.4 mm) 1.19 0.76 (19.3 mm) 0.580.07 (1.7 mm) 1.77 0.42 (10.6 mm) 1.17 0.77 (19.5 mm) 0.570.08 (2.0 mm) 1.75 0.43 (10.9 mm) 1.15 0.78 (19.8 mm) 0.550.09 (2.2 mm) 1.74 0.44 (11.1 mm) 1.14 0.79 (20.0 mm) 0.530.10 (2.5 mm) 1.72 0.45 (11.4 mm) 1.12 0.80 (20.3 mm) 0.520.11 (2.7 mm) 1.70 0.46 (11.6 mm) 1.10 0.81 (20.5 mm) 0.500.12 (3.0 mm) 1.69 0.47 (11.9 mm) 1.08 0.82 (20.8 mm) 0.480.13 (3.3 mm) 1.67 0.48 (12.1 mm) 1.07 0.83 (21.0 mm) 0.460.14 (3.5 mm) 1.65 0.49 (12.4 mm) 1.05 0.84 (21.3 mm) 0.450.15 (3.5 mm) 1.63 0.50 (12.7 mm) 1.03 0.85 (21.5 mm) 0.430.16 (4.0 mm) 1.62 0.51 (12.9 mm) 1.01 0.86 (21.8 mm) 0.410.17 (4.3 mm) 1.60 0.52 (13.2 mm) 1.00 0.87 (22.0 mm) 0.400.18 (4.5 mm) 1.58 0.53 (13.4 mm) 0.98 0.88 (22.3 mm) 0.380.19 (4.8 mm) 1.57 0.54 (13.7 mm) 0.96 0.89 (22.6 mm) 0.360.20 (5.0 mm) 1.55 0.55 (13.9 mm) 0.95 0.90 (22.8 mm) 0.340.21 (5.3 mm) 1.53 0.56 (14.2 mm) 0.93 0.91 (23.1 mm) 0.330.22 (5.5 mm) 1.51 0.57 (14.4 mm) 0.91 0.92 (23.3 mm) 0.310.23 (5.8 mm) 1.50 0.58 (14.7 mm) 0.89 0.93 (23.6 mm) 0.290.24 (6.0 mm) 1.48 0.59 (14.9 mm) 0.88 0.94 (23.8 mm) 0.280.25 (6.3 mm) 1.46 0.60 (15.2 mm) 0.86 0.95 (24.1 mm) 0.260.26 (6.6 mm) 1.44 0.61 (15.4 mm) 0.84 0.96 (24.3 mm) 0.240.27 (6.8 mm) 1.43 0.62 (15.7 mm) 0.83 0.97 (24.6 mm) 0.220.28 (7.1 mm) 1.41 0.63 (16.0 mm) 0.81 0.98 (24.8 mm) 0.210.29 (7.3 mm) 1.39 0.64 (16.2 mm) 0.79 0.99 (25.1 mm) 0.190.30 (7.6 mm) 1.38 0.65 (16.5 mm) 0.77 1.00 (25.4 mm) 0.170.31 (7.8 mm) 1.36 0.66 (16.7 mm) 0.76 1.01 (25.6 mm) 0.150.32 (8.1 mm) 1.34 0.67 (17.0 mm) 0.74 1.02 (25.9 mm) 0.140.33 (8.3 mm) 1.32 0.68 (17.2 mm) 0.72 1.03 (26.1 mm) 0.120.34 (8.6 mm) 1.31 0.69 (17.5 mm) 0.71 1.04 (26.4 mm) 0.100.35 (8.8 mm) 1.29 0.70 (17.7 mm) 0.69 1.05 (26.6 mm) 0.090.36 (9.1 mm) 1.27 0.71 (18.0 mm) 0.67 1.06 (26.9 mm) 0.070.37 (9.3 mm) 1.26 0.72 (18.2 mm) 0.65 1.07 (27.1 mm) 0.050.38 (9.6 mm) 1.24 0.73 (18.5 mm) 0.64 1.08 (27.4 mm) 0.030.39 (9.9 mm) 1.22 0.74 (18.7 mm) 0.62 1.09 (27.6 mm) 0.02

0.40 (10.1 mm) 1.20 0.75 (19.0 mm) 0.60 1.10 (27.9 mm) 0.00

*Thickness at the center of a two inch (50.8 mm) span. **Maximum twist change over a two inch (50.8 mm) span.



Rev. 35 Nov/1761-13-33

(6) Blade Twisting(a) If a blade is out of blade angle tolerance twist the blade to move each

station into tolerance. Refer to the Blade Twist Limits Table 3-8.(b) If a blade requires a twist repair that is more than the maximum permitted

twist specified in Blade Twist Limits Table 3-8, retire the blade from service.

CAUTION: DO NOT USE THE PITCH CHANGE KNOB TO PREVENT THE BLADE FROM ROTATING WHEN TWISTING A "Y" SHANK BLADE. THE FORCE USED TO TWIST THE BLADE WILL DAMAGE THE PITCH CHANGE KNOB.

(c) Secure the blade in a fixture so that it cannot rotate.

CAUTION: DO NOT DAMAGE THE BLADE SURFACES WHEN TWISTING THE BLADE. KINKS IN THE LEADING OR TRAILING EDGE THAT RESULT FROM THE TWISTING PROCESS ARE NOT PERMITTED.

(d) Using a blade paddle, twist the blade.

(e) Inspect each blade angle in accordance with paragraph 2.J.(5)(c) and (d) to determine if the twisting action was enough to bring each blade station into tolerance.

(f) Repeat steps 2.J.(6)(c) through 2.J.(6)(e), as necessary to bring each station into tolerance.

Station LineFace Side

7.50 Inches(190.5 mm)

AP

S81

5

Measuring Face Alignment Figure 3-6

Height Gauge



Rev. 35 Nov/1761-13-33

(7) Measure the Blade Face Alignment

(a) With the blade horizontally secured, square the most inboard station perpendicular to the blade table.



(b) From the table, measure up 7.50 inches (190.5 mm).

(c) Using a non-graphite pencil CM162 or equivalent, make a mark across the blade station line representing the blade centerline.

(d) Repeat the squaring and marking procedure for each station.

(e) Rotate the blade so that the face side is up.

(f) Using a small bubble level, start at the most inboard station and level the blade.

(g) Secure the blade in this position.

(h) Put the pointer of a height gauge in contact with the centerline mark of the blade station. Refer to Figure 3-6.

(i) Measure the height of the pointer. Refer to Figure 3-6.

1 The tolerances listed in the Blade Specification Tables Appendix of this manual are in relation to 7.50 inches (190.5 mm).

a A positive tolerance is added to 7.50 inches (190.5 mm).

b A negative tolerance is subtracted from 7.50 inches (190.5 mm).

c For example, the 24-inch station on a 6660 blade would have a tolerance between 7.484 inches (190.09 mm) and 7.534 inches (191.36 mm).

2 If the centerline of the work fixture is not 7.50 inches (190.5 mm), adjust the final height measurement for the difference.

(j) Repeat the levelling process for each station before the height is measured.

(k) If the blades is out of tolerance, bend the blade until it is within tolerance. Refer to paragraph 2.C.(3) of this chapter.

(8) Measure the Blade Edge Alignment

(a) With the blade horizontally secured, rotate the blade so that the first flat inboard station aligns perpendicular to the blade table with the leading edge up.



Rev. 35 Nov/1761-13-33



(b) Using a non-graphite pencil CM162 or equivalent, mark a line representing each blade station on the leading edge.

(c) Using a height gauge, measure from the blade table to the highest point of the leading edge at the blade station.

(d) Repeat the above procedures for each blade station.

(e) Measure the edge alignment for each blade station of every blade in a propeller assembly.

1 At the corresponding blade stations of each blade in the blade set, the edge alignment must be within 0.120 inch (3.04 mm) from the highest edge alignment measurement to the lowest edge alignment measurement.

(9) Reference Pitch Change Knob Location

(a) For "Y" shank blades in a set, it is necessary to reference the pitch change knob of each blade in relation to the other blades.

(b) Secure the blade in a horizontal fixture.

1 Put the pitch change knob against a stop incorporated into the fixture.

2 Lock the blade in place so that it cannot rotate.

(c) Set the protractor to zero degrees.

(d) Put the protractor on the 30-inch station.

(e) Level the protractor and make a record of the measurement.

(f) Repeat the same procedures for each blade in the set.

(g) Lock each blade in the same position for the reference point to be identical.

(h) All blades in a set must be within 0.40 degree of each other.



Rev. 28 Sep/1261-13-33

K. Reduction in Blade Length


(1) Diameter Reduction for Blades that are to be Returned to Service as the Original Model Designation

(a) Propeller diameter limits are specified in the FAA Aircraft Type Certificate, Supplemental Type Certificate, or foreign equivalent.

(b) The diameter tolerance for a propeller at minimum diameter is 0.125 inches (3.17 mm).

(c) When blades in a set have had a reduction in length, remain within the type certificated diameter, and are being reinstalled on the original application, the blade model designation is not to be changed.

(d) The amount of diameter reduction beyond 0.125 inch (3.17 mm), and in 0.125 inch (3.17 mm) increments for diameter reductions thereafter, is to be impression stamped on the blade butt and ink stamped below the model designation on the camber side of the blade airfoil after the abbreviation “Dia Red.”

(e) Standard Aircraft Type Certificates permit propeller diameter reductions, but the blade model number does not specifically call out a range of blade model designations. To avoid confusion about the blade, the above procedures permit the blade model designation to remain in accordance with the Type Certificate, but require identification of the actual diameter.

(f) Older blades that were re-stamped with a modified model designation for diameter reduction must be re-stamped with their original model designation and have the amount of diameter reduction noted as outlined in the above procedures.

(g) Inspect the blades in the blade set in accordance with the applicable Blade Specification Table for the original blade model designation. Refer to the Appendix C - Blade Specifications chapter of this manual.

(h) When blade diameter reduction is necessary, maintain the same tip shape as the original blade. Refer to the Appendix C - Blade Specifications chapter of this manual.

(i) The tip shape of a blade that has a reduced diameter must have the same radii as the original blade, except that some deviation of the specified radii may be necessary to compensate for width change resulting from the diameter reduction or repairs to the leading edge.



Rev. 23 Mar/0861-13-33

(j) For most blades, stations inboard from the tip have a greater chord width than outboard stations.

(k) When reducing diameter, it is desirable to minimize the reduction of the chord width. Some deviation from the specified tip radii may be appropriate.1 Refer to section D.(2)(f) in this chapter for tip repair criteria.

CAUTION 1: DO NOT CONVERT A ROUND TIP BLADE TO A SQUARE TIP BLADE.

CAUTION 2: DO NOT REDUCE THE DIAMETER OF A SQUARE TIP BLADE TO CONVERT IT TO A ROUND TIP BLADE.

2 Certification testing/approval considers only diameter reductions that maintain the same tip shape.

3 Converting a round tip blade to a square tip blade is not permitted.4 Reducing the diameter of a square tip blade to convert it to a round

tip blade is not permitted.

NOTE: Converting a square tip blade to a round tip blade involves greater mass reduction at the blade tip and greatly affects performance and vibration characteristics.



Rev. 35 Nov/1761-13-33

(2) Diameter Reduction for Blades to be Returned to Service with a Modified Model Designation(a) In the past, blades that were bent beyond permitted limits were sometimes

reduced in diameter when the shortened blade model was completely inboard of the bend. This practice is no longer permitted.

(b) When blades in a set have had a reduction in length and are being installed on an application other than the original, the blade model designation is to be changed using the following method:1 Impression stamp a line through the original model designation dash

number.2 Impression stamp the modified model designation next to the original

model designation.

3 The blade may only be modified to a blade model defined in the Blade Tip Specifications appendix of this manual.

4 Optionally ink stamp the modified model designation on the camber side of the blade airfoil.

5 Future diameter reductions to blade sets with modified model designations are to be handled following the procedures of paragraph 2.K.(1) of this chapter.

(c) Blade modifications that result in significant diameter reductions (from one dash number to another in blade design) must consider factors such as:

1 Pitch change knob location

2 Pitch range capability

3 Interchangeability of modified blades with factory new blades

4 Tip thickness and contour

5 Airfoil width

6 Identification requirements

7 Blade modifications that cause blade-to-blade variation of these factors within a blade set are not permitted.

(d) Use the Blade Specification Table associated with the new model designation of the shortened blade.



Rev. 34 Jan/1761-13-33

(e) While reducing the length of a blade is permitted, care must be taken to avoid creating a blade configuration that is different than that which Hartzell Propeller Inc. manufactures. Refer to the examples in paragraphs K.2.(e)2 through K.2.(e)3.b.

1 Detailed descriptions of differences of all blade model designations are not given in this manual. Information about specific model interchangeability can be obtained on an individual basis from the Hartzell Propeller Inc. Product Support Department.

2 Changing an 8468-8R blade to an 8468-10R blade by reducing the diameter is permitted.

a Refer to the tip shape diagrams in Appendix C - Blade Specifications of this manual.

b Both blades have the same pitch change knob angle and it would be possible to balance the resultant blade with those manufactured by Hartzell Propeller Inc. under the same designation.

3 Changing an 8468-8R blade to an 8468D-14 blade is not permitted except by STC.

a Although both blades have the same pitch change knob angle, they have different twist distributions.

b Twisting the original blade to the new configuration will cause its pitch change knob angle to deviate from the specification and it will not match blades manufactured by Hartzell Propeller Inc.

(f) A Q-tip blade can be cut off to make a non-Q-tip blade

1 Remove material tangent to the radius of the tip and far enough inboard so that the entire Q-tip is removed.

(g) "Y" shank blades must conform to knob angle limitations. Refer to paragraph 2.D.(12) of the Blade Shank Overhaul chapter in this manual.

(h) Since complete tip data is not available in the field, physically compare blades that have significant diameter reduction to factory new blades of the same design so that widths, thickness, tip shape, and airfoil shape in the tip region can be closely matched with factory blades.

(i) Modification of a counterweighted blade to a non-counterweighted blade by removal of the counterweight knob is not permitted in the field.



Rev. 34 Jan/1761-13-33

NOTE 1: The shot peen coverage has a tolerance of + 0.125/ - 0.000 inch (+ 3.17 mm/ - 0.00 mm) within the specified shot peened area. The shot peen within these dimensions cannot be scattered or speckled, but must have complete coverage. Due to manufacturing process changes, incomplete coverage or fading of the shot peen is permitted in specific zones. Refer to Figure 3-9. Stray shot marks are not permitted outside the shot peen area.

NOTE 2: The Blade Model designation may include a "B" or "K" that indicates a de-ice or an anti-icing boot.

NOTE 3: All model M10476 blades were manufactured with a shot peened surface; however, the "S" shot peen designator was not included in the model number of all blades. All M10476 blades must be maintained as shot peened blades, and the "S" designator, if not present, must be added at overhaul.

NOTE 4: Blades may have been previously shot peened from the 4 inch station to the 26 inch station (101.6 to 660.4 mm). Pre-existing coverage between the 4 inch station and the 7 inch station is acceptable, and does not require additional shot peening.

Shot Peened Aluminum Blades Table 3-9, page 1 of 2

BLADE MODEL SHOT PEENED AREA

F7392S-1 from the 6 inch station to the 22 inch station (152.4 to 558.8 mm) F(C)7495S from the 6 inch station to the 25 inch station (152.4 to 635 mm) F7495S-1 from the 6 inch station to the 25 inch station (152.4 to 635 mm) FC7496S from the 6 inch station to the 23 inch station (152.4 to 584.2 mm) FL7666AS from the 4 inch station to the 28 inch station (101.6 to 711.2 mm) D8990S from the 7 inch station to the 30 inch station (177.8 to 762 mm) E9083S from the 7 inch station to the 26 inch station (152 to 660.4 mm) - See Note 4 M9128NS(A) from the 7 inch station to the 28 inch station (177.8 to 711.2 mm) D9290S from the 7 inch station to the 30 inch station (177.8 to 762 mm) D9390S-1R from the 7 inch station to the 26 inch station (177.8 to 660.4 mm) D9510SK from the 7 inch station to the 30 inch station (177.8 to 762 mm) D9511FAS(-2) from the 7 inch station to the 24 inch station (177.8 to 609.6 mm) D9511FS from the 7 inch station to the 24 inch station (177.8 to 609.6 mm) E9673S from the 7 inch station to the 30 inch station (177.8 to 762 mm) T10176(N)S-5 from the 7 inch station to the 22 inch station (177.8 to 558.8 mm) T10178(N)S-11R from the 7 inch station to the 30 inch station (177.8 to 762 mm) M10282A(N)S+6 from the 7 inch station to the 30 inch station (177.8 to 762 mm) LT10282(N)S-5.3R from the 7 inch station to the 30 inch station (177.8 to 762 mm) T10282(N)S from the 7 inch station to the 30 inch station (177.8 to 762 mm) T10282(H)(N)S-6R from the 7 inch station to the 30 inch station (177.8 to 762 mm) (L)T10282(N)S+4 from the 7 inch station to the 30 inch station (177.8 to 762 mm) T10290NS+2 from the 7 inch station to the 30 inch station (177.8 to 762 mm) (L)M10476(N)(S) from the 7 inch station to the 30 inch station (177.8 to 762 mm) - See Note 3 E10477S from the 7 inch station to the 30 inch station (177.8 to 762 mm) E10478S from the 7 inch station to the 30 inch station (177.8 to 762 mm)



Rev. 32 Nov/1561-13-33

Shot Peened Aluminum Blades Table 3-9, page 2 of 2

BLADE MODEL SHOT PEENED AREA

T10702NS from the 7 inch station to the 30 inch station (177.8 to 762 mm) LT10574F(N)S from the 7 inch station to the 30 inch station (177.8 to 762 mm) LT10876A(N)S-2Q from the 7 inch station to the 30 inch station (177.8 to 762 mm) M10876A(N)S from the 7 inch station to the 30 inch station (177.8 to 762 mm) T10876A(N)S-15.5 from the 7 inch station to the 30 inch station (177.8 to 762 mm) (L)M11276(N)S from the 7 inch station to the 30 inch station (177.8 to 762 mm) M11276(N)SA from the 7 inch station to the 30 inch station (177.8 to 762 mm) M11296(N)S from the 7 inch station to the 30 inch station (177.8 to 762 mm) M11691NS from the 7 inch station to the 30 inch station (177.8 to 762 mm) M11692NS from the 7 inch station to the 30 inch station (177.8 to 762 mm) M11693NS from the 7 inch station to the 30 inch station (177.8 to 762 mm)E10479S from the 7 inch station to the 30 inch station (177.8 to 762 mm)

NOTE 1: The shot peen coverage has a tolerance of + 0.125/ - 0.000 inch (+ 3.17 mm/ - 0.00 mm) within the specified shot peened area. The shot peen within these dimensions cannot be scattered or speckled, but must have complete coverage. Due to manufacturing process changes, incomplete coverage or fading of the shot peen is permitted in specific zones. Refer to Figure 3-9. Stray shot marks are not permitted outside the shot peen area.

NOTE 2: The Blade Model designation may include a "B" or "K" that indicates a de-ice or an anti-icing boot.



Rev. 35 Nov/1761-13-33

L. Shot Peened Blade Inspection and Rework


(1) General(a) Certain propeller blades are manufactured with a shot peened surface

(refer to Table 3-9 for shot peened blade models). The area shot peened typically ranges from the 7-inch blade station to the 30-inch blade station.

(b) Shot peened blades are identified by the letter "S" following the blade model number, as described in the Description and Operation chapter of this manual, and by visible shot peen pebble grain on the blade surface.

(c) All model M10476 blades were manufactured with a shot peened surface; but, the "S" shot peen designator was not included in the model number.

1 Maintain all M10476 blades as shot peened blades. At overhaul add the "S" designator, if not present.

(d) There are special repair and rework limitations for shot peened blades to make sure that the desired compressive surface stress caused by shot peening is maintained.

1 Except for the leading and trailing edges of a blade, if there is damage or repair of damage to the shot peened areas of more than 0.015 inch (0.38 mm) deep (including material removal necessary to blend out such damage) and re-shot peen the reworked area before further flight.

2 For the leading or trailing edge of a blade, if the damage to the shot peened area is farther than 0.250 inch (6.35 mm) from the blade leading edge or trailing edge, the rework limit applies.

3 For the leading or trailing edge of a blade, if the damage to the shot peened area is farther than 0.250 inch (6.35 mm) from the blade leading edge or trailing edge, re-shot peen the reworked area before further flight.



Rev. 35 Nov/1761-13-33

(2) Blade Grinding and Polishing Requirements(a) Grind and/or polish nicks, gouges, corrosion and other damage from the

entire airfoil surface, including the shot peened area.

1 If polishing is required, use an abrasive pad that has 400-grit or finer.

2 Significant dimples and irregular surfaces, although permitted for many field repairs, must be ground and polished at overhaul.

3 Blend the repairs to these areas with the blade airfoil shape and contour.

(b) If the shot peened areas of the blade do not require grinding and polishing, plastic media cleaning may be used to remove paint from shot peened surfaces. Refer to the Cleaning chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(c) Grinding and polishing of non-shot peened airfoil surfaces is required at overhaul.

(3) Blade Straightening Requirements

(a) If a shot peened blade is bent and is within repair limits for straightening, overhaul and re-shot peen the entire blade before returning the blade to service.

(b) When adjusting the face alignment or blade angle, use care not to damage the shot peened area of the blade.

(4) Blade Etching and Penetrant Inspection

(a) At overhaul, chemically etch and penetrant inspect shot peened blades after grinding. Refer to paragraphs 2.F. and 2.G. in this chapter.

(b) A local repair in the shot peened area not associated with overhaul has specific penetrant inspection requirements. Refer to paragraph 2.L.(5) of this chapter for information.



Rev. 35 Nov/1761-13-33

(5) Local Repair in the Shot Peened Area Not Associated With Overhaul

NOTE: A local repair removes a specific damage condition between overhauls. Repair of damage at overhaul is blended more smoothly with the blade shape and is not considered a local repair.

(a) All repairs must be within the tolerances specified in the applicable Blade Specification Table.

(b) If a blade is repaired beyond the permitted limits, retire the blade from service.

(c) Remove all damage before inspection and re-shot peening.

(d) Shot peening of the face and camber sides of the blade is more critical than the leading and trailing edge. Repairability limits are stricter for the face and camber surfaces.

(e) The depth of damage refers to measurements taken after rework of the effected area.

(f) Face and camber repair area is defined as between 10 percent and 80 percent of the chord width from the blade leading edge. If the damage is not deeper than the base of the shot peen pebble grain, locally repair these areas without re-shot peening.

(g) If there is damage deeper than the base of the shot peen pebble grain, re-shot peen only the surface of the blade containing the repair area. For example, if the camber side of the blade contains a repair, then only the entire camber side of the blade must be completely re-shot peened.

(h) Lead edge repair area is defined as 10 percent of the chord width back from the lead edge. Trail edge repair area is defined as 20 percent of the chord width forward from the trail edge. If the extent of the repair is less than 0.250 inch (6.35 mm) from the lead edge or trail edge of the blade, these areas may be repaired without re-shot peening.



Rev. 35 Nov/1761-13-33

1.50 inches(38.1 mm) Maximum

1.50 inches(38.1 mm) Maximum

Leading Edge(Thick Side)

Trailing Edge(Thin Side)

Face (Flat or Concave)

Camber (Curved)

CAUTION: CONDITION ALL CUT WIRE SHOT IN ACCORDANCE WITH THE SPECIFICATIONS IN THE SHOT PEENING CHAPTER OF HARTZELL PROPELLER INC. STANDARD PRACTICES MANUAL 202A (61-01-02).

For face and camber sides of the blade:Description Shot Size Almen Type IntensityTrailing edge intensity: From trailing edge to 1.50 inches CW62 A 0.008 - 0.010 Inch(38.1 mm) max outward (0.20 - 0.25 mm)Airfoil intensity: Remainder of surface that was not CW62 A 0.014 - 0.018 Inchshot peened as trailing edge (0.36 - 0.46 mm)

Aluminum Blade Shot Peen Intensity Zone Specifications Option A Curved Trailing Edge

Figure 3-7

Face

MaskShot Peen Area

(Refer to Table 3-9)Mask

AP

S63

22



Rev. 35 Nov/1761-13-33

Aluminum Blade Shot Peen Intensity Zone Specifications Option B Parallel Trailing Edge

Figure 3-8

TI-4

200



Rev. 35 Nov/1761-13-33

Shot Peening Shank CoverageFigure 3-9

Incomplete Coverage

Permissible In TheseZones

Station A, Identified on Blade Drawings

NOTE: Due to manufacturing process change, incomplete coverage or fading is permitted in specific zones as shown in this figure.

14000



Rev. 32 Nov/1561-13-33

CAUTION: IF ANY DAMAGE IN THE SHOT PEENED AREA IS DEEPER THAN THE BASE OF THE SHOT PEEN PEBBLE GRAIN, THE DAMAGED AREA MUST BE GROUND, POLISHED, CHEMICALLY ETCHED, AND PENETRANT INSPECTED BEFORE RE-SHOT PEENING.

(i) Grind the damaged area using an abrasive pad that has no finer than 180-grit and polish using an abrasive pad that has 400-grit or finer. Refer to the Blade Grinding Requirements and Procedures, Blade Polishing Requirements and Procedures, and Blade Final Polishing Requirements and Procedures sections of this chapter.

1 Repairs to the damaged area must blend with the blade airfoil shape and contour.

(j) Chemically etch the damaged area after grinding. Refer to the Penetrant Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02) for chemical etching procedures.

(k) Penetrant inspect the damaged area after chemically etching. Refer to the Penetrant Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02) for penetrant inspection procedures.

(6) Re-shot Peening Aluminum Blades

(a) A shot peened aluminum blade must be completely re-shot peened at overhaul, regardless of condition.

(b) If any single local repair area not associated with overhaul requires re-shot peening, only the surface of the blade containing the repair area must be re-shot peened. For example, if the camber side of the blade contains a repair, only the entire camber side of the blade must be completely re-shot peened.

(c) For the general shot peening procedure, refer to the Shot Peening chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(d) For facilities approved to perform shot peening, refer to the Shot Peening chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(e) For the shot peen area requirements for specific blades, refer to Table 3-9 in this manual.

(f) For aluminum blade shot peen intensity zone specifications, refer to Figure 3-7 and Figure 3-8 of this manual.

(g) For aluminum blade Almen strip and Almen strip holder locations, refer to Figure 3-9 in this manual. These locations apply for either Option A or Option B intensity zone patterns.



Rev. 35 Nov/1761-13-33

(h) Optional Polishing Procedure1 General

a The optional polishing procedure will help clean the blade after shot peening before applying anodize or chemical conversion coating and will also improve the blade appearance.

b If the optional polishing procedure is performed, remove only the tops of the shot peening dimples (dents); do not completely remove the shot peening dimples (dents).

2 Procedure

CAUTION: DO NOT COMPLETELY REMOVE THE SHOT PEENING DIMPLES (DENTS) WHEN PERFORMING THE OPTIONAL POLISHING PROCEDURE.

a After shot peening has been completed, but before applying anodize or chemical conversion coating, lightly polish over the shot peened surface using one of the following:(1) A red abrasive pad such as CM47 or equivalent(2) Jackson Lea Greaseless Abrasive Composition 200-grit

to 220-grit on a cloth wheel or an equivalent non-metallic polishing pad

(7) Shot Peening of Non-Shot Peened Blades(a) Shot peening a non-shot peened blade can be performed in accordance

with the following requirements:1 Shot peen only the non-shot peened version of blades listed in

Table 3-9.2 Stamp a non-shot peened blade that has been shot peened with

the "S" designator in accordance with the Parts Identification and Marking chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

3 If the Type Certificate Data Sheet specifies shot peened blades, do not intermix shot peened blades and non-shot peened blades in the same propeller assembly.

4 Some blade models have life limits on certain applications. These blades may not be life limited on other installations.a Time accumulated toward life limit begins when first operated on

a life limited application and continues regardless of subsequent installations.

b If a subsequent application is also life limited, the most conservative life limit is applicable.

c Shot peening of a blade removed from a life limited application does not affect the life limit. The blade must be removed from service when the life limit is reached.



Rev. 35 Nov/1761-13-33

"Q" Tip Aluminum Propeller Blades Figure 3-10

APS226AAPS489

Face Side of Blade

1.0 inch (25.4 mm)+0.0625 (1.587 mm)-0.25 (6.35 mm)

90 degrees +5 degrees-0 degrees

Maintain Standard Blade Thickness from this Point Inboard per Blade Specification Tables

0.035 inch (0.88 mm)

0.035 inch(0.88 mm)

0.090 inch(2.28 mm)

0.115 inch(2.92 mm)

0.065 inch(1.65 mm)

0.170 inch(4.31 mm)

0.143 inch(3.63 mm)

3 inchStation

2 inchStation

1 inchStation

TIP

0.065 inch (1.65 mm) Minimum Thickness

0.6875 inch(1.7462 mm)

0.50 inch(12.7 mm)

1.00 inch(25.4 mm)

0.50 inch(12.7 mm)

0.50 inch(12.7 mm)

0.50 inch(12.7 mm)

Blend Smoothly



Rev. 35 Nov/1761-13-33

M. Q Tip Blades


(1) A Q tip propeller blade is formed by bending the tip section of the blade 90 degrees toward the face side.

(2) A Q tip blade may only be formed by Hartzell Propeller Inc. on a new blade only.

(3) Bending a tip section in the field is not permitted.

(4) Field repair of a slightly deformed tip, up to 20 degrees, is permitted.

(5) Data from the Blade Specification Tables is not usable in the area of the bent tip. Refer to Figure 3-10 for tip thickness requirements.

(6) Blade width in the bend area must be sufficient to maintain the original width as reasonably as possible.

(7) Q-Tip blade repair

(a) When a Q-tip blade is manufactured, the blend (radius) of the leading and trailing edges of the tip are identical. As the leading edge of a Q-tip blade wears, the tip blend (radius) becomes distorted, while the trailing edge tip blend remains intact.

1 When repairing the leading edge of a Q-tip blade, shape the blend between the blade tip and the leading edge, as necessary, to match the shape of the trailing edge blend, using the shape of the trailing edge as a guide. A slight chord reduction may result.

2 If a repair is made to the width of the blade in the bend area, smoothly blend the repair into the most outboard, controlled blade station.

3 Repair of tip damage is permitted, if the distance from the face of the blade to the tip of the blade in the 90 degree area is at least 0.75 inch (19.05 mm).

4 If the length of the tip is reduced on one blade, the other blades in the set must also be reduced to maintain correct propeller assembly balance.



Rev. 35 Nov/1761-13-33

N. Lightning Strikes


(1) After a propeller lightning strike, an inspection of the each blade is required before further flight.

(2) Slight arcing damage to the blade surface from a lightning strike that has a maximum diameter of 0.125 inch (3.18 mm) may be repaired.

(a) Smoothly blend the damaged area and polish using an abrasive pad that has 400-grit or finer.

(b) Perform a penetrant inspection.

(3) Damage to the blade edge may be repaired in the same way as a small nick or scratch. This can generally be performed by mechanics in accordance with FAA Advisory Circular 43.13-1B.

(4) If there are larger areas of arcing damage, or if it appears that intense heat may have softened the area adjacent to the damage, retire the blade from service or return it to Hartzell Propeller Inc. Propeller for evaluation.

(5) Perform a Brinell hardness test within 0.125 inch (3.17 mm) of each damaged area. Refer to the Special Inspections chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(6) For propeller assembly inspection requirements after a lightning strike, refer to the Special Inspections chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).



Rev. 35 Nov/1761-13-33

O. Blade Anodizing


CAUTION 1: DO NOT USE ANODIC COATING (ANODIZE) IN THE ALUMINUM BLADE BORE AREA. THE USE OF ANODIC COATING (ANODIZE) IN THE BLADE SHANK BORE OF ALUMINUM BLADES MAY HAVE DETRIMENTAL EFFECTS ON BLADE FATIGUE STRENGTH.

CAUTION 2: DO NOT USE ANODIZE IN THE SHANK REGION OF THE BLADE.

CAUTION 3: IF A BLADE HAS BEEN ANODIZED IN THE SHANK REGION, REMOVE THE ANODIZE (CHEMICALLY OR MECHANICALLY), AND OVERHAUL THE SHANK, INCLUDING PENETRANT INSPECTION, DIMENSIONAL INSPECTION, AND COLD ROLLING.


(1) If the anodize solution enters the blade bore hole, rinse the blade bore hole immediately and oven dry the blade at 150° to 200° F. (66° to 92° C.) for five hours.

(2) For hard alloy blade anodizing instructions, refer to the Special Inspections and Procedures chapter of this manual.

(3) Aluminum propeller blades must be anodized at overhaul.(4) Refer to the Blade Shank Overhaul chapter of this manual for a definition of the

region of transition from anodize to chemical conversion coating.(5) For "Y", "D", and "E" shank blades

a Remove and discard the counterweight dowel pin, if applicable, before anodizing the blade.

b The counterweight dowel pin is replaced when the counterweight assembly is reinstalled.

c Remove all threaded inserts, if applicable, from the counterweight knob before anodizing the blade.

(6) Refer to Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02), for information and procedures on chromic acid anodizing.a Except on hard alloy blades, application of a chemical conversion coating

is an approved alternative to chromic acid anodize. Refer to alternative methods listed in Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

b Regardless of the method used, correct procedures must be followed to make sure that there is corrosion protection.



Rev. 35 Nov/1761-13-33

P. Optional Blade Conversion


(1) For the AT-802( ) Air Tractor Application Only

WARNING: CONVERTING AN M11276N BLADE TO AN M11276NA BLADE LIMITS THE RPM RANGE AND REQUIRES A CHANGE TO THE OPERATING RESTRICTIONS.

(a) Converting an M11276N blade to an M11276NA blade may extend the life of the blade, but limits the permitted RPM range.

1 Converting an M11276N blade to an M11276NA blade requires a change to the operating restrictions. Refer to the aircraft flight manual.

(b) To convert an M11276N blade to an M11276NA blade, add an "A" to the impression stamp on the blade shank and to the ink stamp. Refer to the Parts Identification and Marking chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

CAUTION: DO NOT CONVERT AN M11276NA BLADE TO AN M11276N BLADE.

(c) Converting an M11276NA blade to an M11276N blade is not permitted.

(2) For the AN-38-100 Antonov Application Only

(a) To convert an M11276NK-3 blade to an M11276NCK-3 blade, add a "C" to the impression stamp on the blade shank and to the ink stamp if present. Refer to the Parts Identification and Marking chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

CAUTION: THE M11276NK-3 BLADE AND THE M11276NCK-3 BLADE ARE LIFE LIMITED WHEN USED ON CERTAIN APPLICATIONS.

(b) The M11276NK-3 blade and the M11276NCK-3 blade are life limited when used on certain applications. Refer to the Airworthiness Limitations chapter of Hartzell Propeller Inc. Manual 132A (61-10-32).

CAUTION: DO NOT CONVERT AN M11276NCK-3 BLADE TO AN M11276NK-3 BLADE.

(c) Converting an M11276NCK blade to an M11276NK-3 blade is not permitted.


SPECIAL INSPECTIONS AND PROCEDURES 61-13-33 Page 4-1Rev. 28 Sep/12

SPECIAL INSPECTIONS AND PROCEDURES - CONTENTS

1. Special Inspections and Procedures ......................................................................4-5

A. General..............................................................................................................4-5

2. Overhaul and Maintenance Procedures for Hard Alloy Blades ..............................4-5

A. General Requirements ......................................................................................4-5

B. Overhaul Requirements ....................................................................................4-6

3. Additional Inspection, Overhaul, and Maintenance Requirements for Hard Alloy Blades Installed on Turbine-Powered Aircraft .........................................................4-7

A. Effectivity ...........................................................................................................4-7

B. General..............................................................................................................4-8

C. Check ................................................................................................................4-8

D. Rework ..............................................................................................................4-8

4. Required Eddy Current Inspection On Hard Alloy Blades ....................................4-10

A. Effectivity .........................................................................................................4-10

B. Check ..............................................................................................................4-10

5. Hard Alloy Blade Airfoil Anodizing .........................................................................4-11

6. Hard Alloy Blade Straightening .............................................................................4-12

A. Effectivity .........................................................................................................4-12

B. Discussion .......................................................................................................4-12

7. Replacement of Hard Alloy Blades With Standard Alloy Blades ...........................4-12

A. Effectivity .........................................................................................................4-12

B. Discussion .......................................................................................................4-12

8. Modification of Double Shoulder 7636D-( ), 8433( ), 8833( ), 9333C( ), and 10133D-( ) Blades..........................................................................................4-15

A. Effectivity .........................................................................................................4-15

B. Discussion .......................................................................................................4-15


SPECIAL INSPECTIONS AND PROCEDURESPage 4-2

Rev. 28 Sep/1261-13-33

SPECIAL INSPECTIONS AND PROCEDURES - CONTENTS, CONTINUED

9. Additional Inspection Requirements for Propellers Installed on Nord 262 Aircraft ...................................................................................................4-15

A. Effectivity .........................................................................................................4-15

B. Discussion .......................................................................................................4-16

C. Check ..............................................................................................................4-16

D. Compliance .....................................................................................................4-16

10. Inspection Requirements for HC-B3TN-5( )( )/T10282H(B)..................................4-17

A. Effectivity .........................................................................................................4-17

B. Discussion .......................................................................................................4-17

C. Check ..............................................................................................................4-17

11. Inspection Requirements for HC-B3TN-5( )L/LT10282( )( )+4 ..............................4-18

A. Effectivity .........................................................................................................4-18

B. Discussion .......................................................................................................4-18

C. Check ..............................................................................................................4-18

12. Replacement of LT10282( )( )+4 Blades ...............................................................4-18

A. Effectivity .........................................................................................................4-18

B. Discussion .......................................................................................................4-19

C. Procedure ........................................................................................................4-19

13. Counterweight Requirements for the BHC-L2YF-4F/FC8468AR Propeller ..........4-19

A. Effectivity .........................................................................................................4-19

B. Discussion .......................................................................................................4-19

C. Procedure ........................................................................................................4-19

14. Inspection of T10176 Propeller Blade Shanks ......................................................4-21

A. Effectivity .........................................................................................................4-21

B. Discussion .......................................................................................................4-21

C. Check ..............................................................................................................4-21

D. Compliance .....................................................................................................4-22

15. New "T" and "M" Shank Propeller Blades .............................................................4-22

A. General............................................................................................................4-22

B. Interchangeability Between Old and New Blades ...........................................4-23


SPECIAL INSPECTIONS AND PROCEDURES 61-13-33 Page 4-3Rev. 29 Nov/12

16. Compatibility of C7479-2R Propeller Blades ........................................................4-24A. Effectivity .........................................................................................................4-24B. Discussion .......................................................................................................4-24

17. Use of Oversize Internal Blade Needle Bearing ...................................................4-2618. Retirement of Blades in Propeller Assembly

HC-B4TN-5(D,G,J)L/LT10282(N)(B,K)-5.3R ........................................................4-27A. Effectivity .........................................................................................................4-27B. Requirements ..................................................................................................4-27

19. Modification of Blade Model LT10574(A)(S)(B) to LT10574F(N)S(B) ...................4-30A. Effectivity .........................................................................................................4-30B. Discussion .......................................................................................................4-30C. Requirements ..................................................................................................4-30

20. Retirement of Certain Blade Models Installed on Propeller Model HC-12X20 .....4-31A. General............................................................................................................4-31B. Procedure ........................................................................................................4-31

21. Replacement of Non-Counterweighted Blade Models 8475-( ) and 8477-( ) .......4-31A. General............................................................................................................4-31B. Procedure ........................................................................................................4-32

22. Additional Blade Shank Inspection for T9212, 10172( ), 10173( ) and 10176( ) Blades .............................................................................................4-32A. Effectivity .........................................................................................................4-32B. Discussion .......................................................................................................4-32C. Procedure ........................................................................................................4-32

23. Replacement Blade for M10876K Installed on Shorts SD3-60 Aircraft ................4-3324. Replacement of Hartzite Blades ...........................................................................4-3325. Replacement of 7663-4 Blades with Serial Numbers Below B35571 ...................4-3326. Interchangeability of "P", "R", "W", and "Z" Shank Blades with "N" Modification ..4-34

A. Effectivity .........................................................................................................4-34B. Discussion .......................................................................................................4-34

27. Modification of Counterweight D-6021-1 for Use with De-ice Kit 103253 .............4-3528. Replacement of T10173F(N)(B,K)-12.5 blades with T10173AN(B,K)-12.5 Blades ... 4-38

29. Replacement of "Y" Shank Blades Used in Propeller Models ( )HC-( )( )Y( )-( ) ..4-38

SPECIAL INSPECTIONS AND PROCEDURES - CONTENTS, CONTINUED



Rev. 35 Nov/1761-13-33

LIST OF FIGURES

"V" Shank Modification .................................................Figure 4-1 ..................................4-14

TE131 Blade Inspection Tool ........................................Figure 4-2 ..................................4-20

10574F(S)(B) Blade Modification Template ..................Figure 4-3 ..................................4-29

Modification of Counterweight for Terminal Strip and Spring Pin Attaching Holes...............................Figure 4-4 ..................................4-36

Modification of Counterweight for Tie Mount Attaching Hole .........................................................Figure 4-5 ..................................4-37

LIST OF TABLES

Hard Alloy Blades Requiring Eddy Current Inspection .Table 4-1 ...................................4-10

Blade Changes for "V" with "N" Modification Shanks ...Table 4-2 ...................................4-14

Inspection Requirements for M10282A(B)+6 Blades ...Table 4-3 ...................................4-16

Counterweight Parts Removed From BHC-L2YF-4F/FC8468AR Propellers .....................Table 4-4 ...................................4-19

Non-Standard C7479-2R Aluminum Propeller Blades..Table 4-5 ...................................4-24

10574F(S)(B) Blade Conversion .................................Table 4-6 ...................................4-28



WARNING: FAILURE TO COMPLY WITH THE REQUIREMENTS OF THIS CHAPTER WILL RESULT IN IMPROPER INSPECTION, REPAIR, AND OVERHAUL OF THE COMPONENT.



A. General

(1) The data in this chapter is required for those applications to which it applies. These requirements must be met in addition to all other requirements of this manual.

2. Overhaul and Maintenance Procedures for Hard Alloy Blades


NOTE: Hard alloy blades are identified by the letter "H" immediately following the blade design number, e.g., T10282HB or T10178H-11R; hard alloy blades are also stamped with the number "76" on the blade butt.

A. General Requirements

(1) The following procedures are to be incorporated into the aircraft's daily and periodic inspection practices:

NOTE: Particular attention must be given to aircraft operated in salt water conditions.

(a) Visually inspect for the possible beginning of intergranular corrosion.(b) Visually inspect for erosion of the blade surface and leading edge.

(2) Corrosion Control

(a) If evidence of surface corrosion is found, the area must be reworked to remove all traces of corrosion. This can be accomplished in the field and with the propeller on the aircraft wing; however, if the corrosion has advanced to the point where considerable material must be removed, the propeller must be removed and an overhaul completed for all of the blades.

(b) The blade must be cleaned following rework in order to prepare the blade for the application of primer and paint.



Rev. 37 Dec/1861-13-33

(3) Erosion Repair

(a) If evidence of erosion is found, the surface must be adequately sanded to remove all paint and surface defects in the affected area.

(b) The blade must be cleaned using solvent (CM23) following rework in order to prepare the blade for the application of primer and paint.

B. Overhaul Requirements

NOTE: The following requirements are to be performed in addition to those established in the Blade Airfoil Overhaul chapter of this manual.

(1) Remove the de-ice or anti-icing boot from each blade.

(a) For instructions about removal of a de-ice boot and/or an anti-icing boot, refer to Hartzell Propeller Inc. Propeller Ice Protection System Manual 180 (30-61-80).

(2) Remove all paint.

(a) The recommended method for paint removal, other than removal during the grinding process, is plastic media cleaning.

(b) For plastic media cleaning guidelines, refer to Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(3) Dimensionally inspect the width and thickness of the blade to determine if the blade is within the tolerances specified in the Blade Specification Tables located in Appendix C of this manual.

(a) If the blade is under the minimum width or thickness measurement specified in the Blade Specification Table in Appendix C of this manual, retire the blade from service.

(b) If the blade, from the 9 inch station out to the 24 inch station, is less than 0.020 inch (0.51 mm) over the minimum allowable width or thickness specified in the Blade Specification Table in Appendix C of this manual, retire the blade from service.

(4) Remove 0.010 inch (0.25 mm) of material from the face and camber sides of the blade from the 9 inch station out to the 24 inch station.

(5) Dimensionally inspect the width and thickness of the blade from the nine inch station out to the 24 inch station to verify that it is still within the tolerances specified in the Blade Specification Tables located in Appendix C of this manual.

(a) If the blade is under the minimum width or thickness measurement specified in the Blade Specification Table in Appendix C of this manual, retire the blade from service.



CAUTION: THE CORRECT AERODYNAMIC BLEND MUST BE MAINTAINED AT ALL POINTS ON THE BLADE.

(6) If more than 0.010 inch (0.25 mm) of material must be removed from a blade to remove all damage or nicks, it may be necessary to remove the same amount of material from all blades in the propeller assembly to maintain static and dynamic balance.

NOTE: It may be necessary to grind the thickest blades down to the dimension of the thinnest blade to correct balance.

(7) Outboard of the 24 inch station, remove material on an as needed basis to remove all traces of corrosion. All nicks and scratches must be removed or blended during the rework process.

(8) Visually examine the blade to make sure all intergranular corrosion and discontinuities have been removed.

(a) Inspect the blade using dye penetrant in accordance with Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(b) Eddy Current inspection is an optional method that may be performed in addition to dye penetrant inspection to verify the existence of a crack; however, a crack is only detected when the depth is greater than 0.006 inch (152 mm) and it runs through the blade in a straight line. For information about eddy current inspection, refer to Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).1 Eddy current is not acceptable for corrosion detection, primarily

because of the irregularity of the depth of corrosion.

3. Additional Inspection, Overhaul, and Maintenance Requirements for Hard Alloy Blades Installed on Turbine-Powered Aircraft


NOTE: This information was obtained from Hartzell Propeller Inc. Service Bulletin 138.

A. Effectivity

(1) All Hartzell Propeller Inc. turboprop aircraft propeller blades manufactured from hard alloy aluminum.

NOTE: Hard alloy blades are identified by the letter "H" immediately following the blade design number, e.g., T10282HB or T10178H-11R; hard alloy blades are also stamped with the number "76" on the blade butt.



Rev. 37 Dec/1861-13-33

B. General(1) Hard alloy aluminum (7076-T61) was developed to improve the water and sand

erosion characteristics of propeller blades.(a) The impact resistance of hard alloy aluminum to stone nicks and dents is

also superior to the standard aluminum alloy.(b) Hard alloy aluminum can be susceptible to intergranular corrosion,

particularly if corrosion is not thoroughly removed before blade surface protection, or if corrosive material is trapped between the unprotected bare metal and paint or a de-ice or anti-icing boot.

C. Check

WARNING: FAILURE TO ADHERE TO THESE CORROSION REMOVAL AND CONTROL PROCEDURES MAY LEAD TO IN-FLIGHT BLADE FAILURES.

(1) In addition to the normal aircraft daily inspection procedures:(a) Visually examine the propeller blades in the area from the blade clamp to

six inches outboard of the de-ice or anti-icing boot for scratches, dents, nicks, or other signs of exposed bare metal where surface corrosion could initiate.

(b) Visually examine the paint coating for signs of deterioration such as cracks, chips, bubbles, flaking, and blisters which might indicate the presence of corrosion underneath the paint.

(c) Visually examine the blade de-ice or anti-icing boot in accordance with Hartzell Propeller Inc. Ice Protection System Manual 180 (30-61-80).

D. Rework(1) If the presence of bare metal or corrosion is observed or suspected to exist

under a deteriorated paint coating on any blade, accomplish the following to make sure that there are no cracks in the blade:

WARNING: RETIRE FROM SERVICE ANY BLADE THAT HAS A CRACK. BEFORE THE NEXT FLIGHT, OVERHAUL THE ENTIRE PROPELLER ASSEMBLY FROM WHICH THE CRACKED BLADE WAS REMOVED.

(a) Penetrant inspect the area before the next flight. Refer to the Penetrant Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).1 If the corrosion area is adjacent to the de-ice or anti-icing boot,

remove the de-ice or anti-icing boot and penetrant inspect the area under the de-ice or anti-icing boot.a For instructions about removal of a de-ice and/or an anti-icing

boot, refer to Hartzell Propeller Inc. Propeller Ice Protection System Manual 180 (30-61-80).


SPECIAL INSPECTIONS AND PROCEDURES 61-13-33 Page 4-9Rev. 37 Dec/18

(b) Within the next 25 hours of operation and each succeeding 25 hours of operation, eddy current inspect the entire area. Refer to the Eddy Current Inspection chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(c) Remove and overhaul the propeller within the next 100 hours of operation following the first indication of bare metal or corrosion.

(2) Any propeller that has a blade with a loose, bubbled, or detached de-ice or anti-icing boot must be removed and overhauled before the next flight, or all de-ice or anti-icing boots must be removed and the blades inspected and reworked in accordance with steps 3.D.(1)(a) through 3.D.(1)(c) in this chapter.

(a) For instructions about removal and installation of a de-ice and/or an anti-icing boot, refer to Hartzell Propeller Inc. Propeller Ice Protection System Manual 180 (30-61-80).



Rev. 28 Sep/1261-13-33

4. Required Eddy Current Inspection On Hard Alloy Blades


NOTE: Refer to Airworthiness Directive 74-14-01.

A. Effectivity

(1) Blades T10282H( )-( ), T10173H( )-( ), T10176H( )-( ), and T10178H( )-( ) are affected when installed on the hub models with serial numbers earlier than those listed below (see Table 4-1):

(2) Blades that are a part of the above applications are affected if they have less than 1000 hours of service. Blades with more than 1000 hours of service are not affected.

(3) This inspection is to be completed as soon as possible and within the next 50 hours of operation.

B. Check

(1) Inspect the entire blade in accordance with the eddy current procedures in Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

Hard Alloy Blades Requiring Eddy Current InspectionTable 4-1

Hub Model Serial Numbers

HC-B3TN Below BU 4624

HC-B3TN-5 Below BV 2216 (except BV 2210, BV 2213, BV 2214)

HC-B3TN-7 Below CV 7

HC-B4TN-5 Below CD 62

HC-B4TN-3A Below EA 255

HC-B3TF-7 Below EX 3

HC-B3TN-2 Below AG 275



5. Hard Alloy Blade Airfoil Anodizing


CAUTION 2: THE USE OF ANODIC COATING (ANODIZE) IN THE BLADE SHANK BORE OF ALUMINUM BLADES MAY HAVE DETRIMENTAL EFFECTS ON BLADE FATIGUE STRENGTH. ANODIZE IS NOT PERMITTED IN THE ALUMINUM BLADE BORE AREA. IF ANODIZE SOLUTION ENTERS THE HOLE, IT MUST BE RINSED OUT IMMEDIATELY AND THE BLADE MUST BE OVEN DRIED AT 150° TO 200° F. FOR FIVE HOURS.

CAUTION 3: IF A BLADE HAS BEEN ANODIZED IN THE SHANK REGION, THE ANODIZE MUST BE REMOVED (CHEMICALLY OR MECHANICALLY), AND OVERHAUL OF THE SHANK MUST BE PERFORMED, INCLUDING NDT, DIMENSIONAL INSPECTION, AND COLD ROLLING.

CAUTION 4: USE OF ANODIZE IN THE SHANK REGION OF THE BLADE IS NOT AUTHORIZED.

A. Anodize all hard alloy propeller blades at overhaul.

CAUTION: APPLICATION OF A CHEMICAL CONVERSION COATING AS AN ALTERNATIVE TO CHROMIC ACID ANODIZE IS NOT PERMITTED ON HARD ALLOY BLADES.

(1) Refer to the Blade Shank Overhaul chapter of this manual for a definition of the region of transition from anodize of the blade airfoil to chemical conversion coating of the blade shank.

(2) Refer to the Chromic Acid Anodizing chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02), for information and procedures for chromic acid anodizing.

(a) The counterweight dowel pin and all threaded inserts, if applicable, must be removed from the counterweight knob of a Y, D, and E shank blade before anodizing the blade.

(b) Replace the dowel pin when the counterweight assembly is reinstalled.(3) After anodizing, perform an inspection in accordance with the procedures in the

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



Rev. 28 Sep/1261-13-33

6. Hard Alloy Blade Straightening


A. Effectivity

(1) This requirement applies to all hard alloy blades.

B. Discussion

(1) A substantial amount of over-twisting and bending is required for straightening hard alloy blades.

(2) Hartzell Propeller Inc. has established the requirement that no hard alloy blade twisting or bending is allowed to be attempted in the field. Hartzell Propeller Inc. will attempt to straighten blades returned for repair.

7. Replacement of Hard Alloy Blades With Standard Alloy Blades


A. Effectivity

(1) This requirement applies to all hard alloy blades.

B. Discussion

(1) Blades of hard and standard alloy that have the same blade model designation are interchangeable when applied to aircraft powered by turboprop engines.

(2) Intermixing propellers with alternate alloy configurations on twin engine aircraft is permitted, in other words one propeller assembly can contain all hard alloy blades and the other propeller assembly can contain all standard alloy blades.

(3) Intermixing alloy configurations in a single propeller assembly is not permitted (for example, a three blade propeller assembly cannot have two hard alloy blades and one standard alloy blade).



Rev. 22 Jun/0761-13-33




Rev. 22 Jun/0761-13-33

"V" Shank "V" Shank with "N" Modification

APS0652

APS0653

"V" Shank ModificationFigure 4-1

Blade Changes for "V" with "N" Modification ShanksTable 4-2

New Design No. Modification

V7636N .050 inch per side added in thickness at the nine inch station

V8433N Same as above

V8833N Same as above

V9333N No changes made to the blade thickness

V10133N No changes made to the blade thickness



8. Modification of Double Shoulder 7636D-( ), 8433( ), 8833( ), 9333C( ), and 10133D-( ) Blades


CAUTION 2: MODIFICATION OF HARD ALLOY BLADES IS NOT PERMITTED.

A. Effectivity

(1) Double shoulder blades with model numbers 7636D( ), 8433( ), 8833( ), 9333C( ), and 10133D-( ).

B. Discussion

(1) All new blades of the type mentioned above are manufactured with improved designs (see Figure 4-1). They are all V type pilot tube bores and are identified with an "N" following the model number to identify the improved design. For example, a blade formerly manufactured as V7636 is now manufactured and identified as V7636N; a blade formerly manufactured as V10133D is now V10133N.

NOTE: The effected blades were originally manufactured with "X" or "V" shanks.

(2) Additional modifications to the blade designs are included (see Table 4-2).

(3) All effected blade models that are replaced must be replaced using the same design. Do not intermix blade designs in an assembly.

9. Additional Inspection Requirements for Propellers Installed on Nord 262 Aircraft



A. Effectivity

(1) All HC-B5MP-3A/M10282A(B)+6 propellers installed on Nord 262 (Frakes conversion) aircraft with Pratt and Whitney PT6A-45 series engines are affected.

(2) M10282A(B)+6( ) blades used on the Nord 262 aircraft must follow the inspection criteria of this section.

NOTE: Blade M10282AN(B)+6( ) is exempt from and not affected by the following requirements due to improved design in the internal bearing radius and additional thickness added to the inboard stations.



Rev. 28 Sep/1261-13-33

Inspection Requirements for M10282A(B)+6 BladesTable 4-3

Propeller Blade Time in Service Inspection Compliance

Initial Inspection Less than or equal to 400 hours since new or since last inspection

Prior to the accumulation of 500 hours since inspection or since new

Greater than 400 hours since new or since last inspection for compliance, or if time since inspection or total time is unknown

Within 100 hours of operation

Repetitive Inspection After initial inspection Perform inspection at intervals not

to exceed 500 hours of operation

B. Discussion

(1) The purpose of this inspection is to identify fatigue cracks that may occur at the smaller internal bearing bore on effected blades.

C. Check

(1) In accordance with the Blade Shank Overhaul chapter of this manual, inspect the radius end of the blade bearing bore.

(2) Perform rework procedures if necessary.

NOTE: This includes all evidence of scratches, tool marks, and corrosion, as well as etching and dye penetrant inspection of the critical areas of the blade bore.

(3) All blades showing evidence of cracks or other unairworthy conditions must be replaced prior to further flight.

(4) Report all incidents of cracks or linear crack indications to the Product Support Department of Hartzell Propeller Inc.

D. Compliance

(1) All effected blades must be repetitively inspected after the initial inspection. The repetitive inspection is based on time in service of the blade (see Table 4-3).

NOTE: The repetitive requirements of this inspection are terminated when all blades installed in a propeller assembly have been replaced by "N" modification blades.



10. Inspection Requirements for HC-B3TN-5( )( )/T10282H(B)


NOTE: This information was obtained from Hartzell Propeller Inc. Service Bulletin 146B.

A. Effectivity

(1) This inspection is required for propeller model HC-B3TN-5( )( )/T10282H(B) installed on Fairchild SA226T, SA226TC, SA226AT, Metro aircraft with Garrett Engine model TPE-331-3U-303G, TPE-331-3UW-303G, and those aircraft above modified with model TPE-331-10UA-501G or -511G engines.

B. Discussion

(1) This inspection is required to detect cracks that may begin on the blade trailing edge and progress in a chordwise direction toward the leading edge. The cracks occur in an area between two and 24 inches from the tip and are generally observed from 1/2 to 1 1/2 inches in length.

(2) Blade tip stall, with the associated high noise levels which occur in the reverse blade angle range, may contribute to this cracking condition.

NOTE: Incidents of blade cracking have also occurred on installations with no known tip stall occurrences.

C. Check

(1) Cracks associated with this installation are visible with the naked eye and give advance warning of possible tip failure if the following recommended actions are taken:

(a) Visually inspect the blade for cracks in the area between two and 24 inches from the blade tip on the trailing edge.

(b) Inspect the blade utilizing a 10X magnifying glass every 100 hours (maximum) after the initial inspection. Inspect the blade surface in the same area described in 9.C.(1) above.

NOTE: The blade must be adequately illuminated to insure accurate inspection.

(c) Evidence of cracking requires further inspection by dye penetrant or eddy current inspections in accordance with Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(d) Blades showing any confirmed indications of cracking must be retired from service before further operation.



Rev. 28 Sep/1261-13-33

11. Inspection Requirements for HC-B3TN-5( )L/LT10282( )( )+4



A. Effectivity

(1) Applies to all propeller models HC-B3TN-5( )L/LT10282( )( )+4 installed on the Gulfstream American (formerly Rockwell International) Aero Commander 690( ) aircraft.

B. Discussion

(1) An audible blade stall may occur if high reverse blade angles are used during high speed landings. This condition may cause high stress concentrations at blade stations approximately five to 15 inches from the blade tip. The high stress concentration can cause a fatigue crack, particularly if the blade has been damaged in this area, such as from a stone nick.

C. Check

(1) Prior to the next and each subsequent flight, visually inspect the blade for indications of a crack in areas five to 15 inches from the blade tip on the camber and face surfaces.

(2) Within the next 10 hours and at each 100 hour interval, inspect blades in the suspect area utilizing an acceptable NDT procedure. See Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(3) All blades showing evidence of a crack must be retired from service.

NOTE: Compliance with Rockwell International Service Bulletin No. 174B, dated August 29, 1980, satisfies the requirements of this inspection.

12. Replacement of LT10282( )( )+4 Blades


NOTE: This information was obtained from Hartzell Propeller Inc. Service Bulletin 131D.

A. Effectivity

(1) All blades, model LT10282( )( )+4, installed on the Gulfstream American (formerly Rockwell International) Aero Commander 690( ) aircraft.



Part Number Description Quantity Removed

A-890-15 Weight 1

A-890 Weight 1

AN4H710A Bolt 2

AN4H7A Bolt 2

AN960-416 Washer 4

Counterweight Parts Removed From BHC-L2YF-4F/FC8468AR PropellersTable 4-4

B. Discussion

(1) Requirements have been developed to exceed the inspection procedures listed in paragraph 10. above for effected blades.

C. Procedure

(1) At next overhaul, replace all effected blades with blade model LT10673.

NOTE: Blade model LT10673 is exempt from inspection requirements listed in paragraph 10. above and Rockwell International Service Bulletin No. 174B.

13. Counterweight Requirements for the BHC-L2YF-4F/FC8468AR Propeller


A. Effectivity

(1) All BHC-L2YF-4F/FC8468AR propellers installed on the Beech T-34A aircraft with the Continental IO-470-N engine.

B. Discussion

(1) To avoid possible overload and failure of the pitch change knob, a change in the amount of counterweight installed is required.

C. Procedure

(1) Remove the counterweights that are attached to the main counterweight with AN hardware. See Table 4-4 for specific parts that are to be removed.

NOTE: Do not remove the main counterweight.



Rev. 32 Nov/1561-13-33

3.750 ± .002 ½ ¾

.878 ± .00290°

"B"

"C"1"

4.1

Camber Side Up

AP

S48

8

"A"

"A"

1/16 - 1/8 Inch Metal Plate

TE131 Blade Inspection ToolFigure 4-2

TE131



14. Inspection of T10176 Propeller Blade Shanks



A. Effectivity

(1) All T10176 and T10176H non-category 2 blades installed in HC-B3TN-5C propeller hubs installed on turboprop aircraft.

B. Discussion

(1) This inspection is required to discover possible fatigue cracks originating at the inside of the pilot tube bore.

C. Check

(1) For propellers that have accumulated 700 hours or more, complete the following procedures within 50 hours:

(a) Using penetrant inspection (refer to the Blade Bore Inspection and Overhaul section of the Blade Shank Overhaul chapter of this manual), visually inspect the inside of the blade pilot tube bore for cracks.

(b) If a crack is found, remove the blade from service.(c) Using an appropriate light source, an inspection mirror, and a sharp

non-graphite pencil CM162, or equivalent as a probe, inspect the bore in the area of minimum wall thickness for scratches or tool marks.

(d) Inspect the surface in the radius area. (e) If any scratches or tool marks penetrate the blade bore surface, rework the

blade in accordance with the Blade Shank Overhaul chapter of this manual.(f) Using TE131, inspect the blade for minimum wall thickness at the

8.25 inch (209.5 mm) station.1 Put the blade on a table with the camber side up. 2 Fit the template to the blade with the 1 inch (25.4 mm) leg contacting

the butt of the blade along axis "A-A," as shown in Figure 4-2. The 0.75 inch (19.0 mm) leg must touch the blade flange at "C."

3 With the template pivoted at axis "A-A," move the 0.50 inch (12.7 mm) leg back and forth until it touches the surface of the blade at "B." Repeat this for several angular positions of the axis "A-A" to find the thinnest part of the blade.

4 Position the template at the thinnest part of the blade. 5 If the template does not touch the blade at "B", retire the blade from

service.



Rev. 28 Sep/1261-13-33

D. Compliance

(1) After the initial inspection, repeat the inspection of the T10176 blade shanks at 1500 hour intervals.

15. New "T" and "M" Shank Propeller Blades


A. General

(1) All new "T" and "M" shank aluminum propeller blades are now being manufactured with "N" design changes that incorporate significant design improvements in the internal bearing radius. On 10282N series blades, thickness has been added in the area of the inboard blade stations.

(2) "N" blades are identified by the suffix letter "N" in the blade model designation that is impression stamped on the blade butt and ink stamped or labeled on the blade airfoil.

(3) Installation of an "N" Blade in the Propeller Assembly

(a) If all of the blades installed in the propeller assembly are "N" blades, make an entry in the propeller logbook about the propeller blade model designation.

Example: HC-B4TN-5C/T10173FB-12.5 is changed to HC-B4TN-5C/T10173FNB-12.5.

(b) If all of the blades installed in the propeller assembly are not "N" blades, do not make an entry in the propeller logbook about the propeller blade model designation.

(4) The "N" design change requires the use of a new internal bearing spacer.



Rev. 23 Mar/0861-13-33

B. Interchangeability Between Old and New Blades

CAUTION 1: DO NOT MIX A NEW "N" BLADE WITH AN OLD, HARD ALLOY BLADE, SUCH AS T10173H, IN A PROPELLER ASSEMBLY.

CAUTION 2: DO NOT MIX A CATEGORY II AND A NON-CATEGORY II BLADE IN A PROPELLER ASSEMBLY.

(1) New T10173N and T10176N blades can be mixed with "Category II" blades (identified "Cat. II" on the blade butt), but cannot be mixed with early production non-category II blades.

NOTE: A Category II blade is thicker than a Non-Category II blade at the 8, 12, and 18 inch stations. Refer to Appendix C, Blade Specification Tables for thickness specifications.

(2) If the propeller or aircraft was type certified with an "N" blade only an "N" blade can only be replaced with an "N" blade.

CAUTION: MIXING OF "N" AND NON-"N" BLADES IS NOT PERMITTED FOR "V" AND "MV" SHANK BLADES.

(a) Replace "V" shank blades (double shoulder) and "MV" shank blades with "N" modification only in sets.

(b) Mixing "N" and Non-"N" "T" and "M" shank blades is permitted in the same hub.

(c) Although T10282 and LT10282 series “N” blades have additional thickness on the inboard stations, interchangeability or mixing of old and new blades is not affected if static balance can be achieved.

(d) There are different overhaul repair specifications for "N" and non-"N" blades. Refer to the Blade Specification Tables for applicable blade station dimensions.



Rev. 28 Sep/1261-13-33

Non-Standard C7479-2R Aluminum Propeller BladesTable 4-5

Serial Number Serial Number Serial Number

A84521 B6298 B10810 through B10820

A92509 B6299 B10822

A94705 B6302 B10823

A94710 B6303 B10905 through B10913

B4663 B6304 B10915

B4665 B6306 B11790 through B11796

B4670 B6307 B11798

B4671 B6322 B11800

B4672 B6324 B11801

B4679 B6326 B11803

B6292 B6330 B11808 through B11811

B6294 B6333 B11814

B6295 B8160 through B8174

B6297 B10800 through B10806

16. Compatibility of C7479-2R Propeller Blades


A. Effectivity

(1) Certain C7479-2R propeller blades used in HC-F3YR-2 propeller assembly installed on Beech 60 and A60 aircraft. Refer to Table 4-5 for effected blades by serial number.

B. Discussion

(1) C7479-2R blades were manufactured with two different pitch change knob locations.

(a) Blades listed in Table 4-5 were manufactured with a pitch change knob location with different blade angles inboard of the 30-inch blade station. 1 The blade angle outboard of the 30-inch station is the same as other

blades of this model.



7479-2R Blade "Y" Shank

Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align.

Min Max Min Max

18 26.0 27.0 0.098 0.162

24 18.0 18.6 -0.032 0.032

30 13.5 Set Up -0.152 -0.088

33 11.7 12.1 -0.222 -0.158

(2) Because of varying pitch change knob locations and the resulting difference in the counterweight knob locations, propeller assemblies may not mix blades listed in Table 4-5 with blades not listed in Table 4-5.

(3) Blade angle and face alignment requirements for the blades listed in Table 4-5 are listed below.

NOTE: This blade data is only applicable to the blades listed in Table 4-5. For blade specifications of other C7479-2R blades, refer to the Blade Specification Table Appendix of this manual.



Rev. 34 Jan/1761-13-33

17. Use of Oversize Internal Blade Needle Bearing


A. When a blade bearing bore is reworked to the permitted limits, it can be difficult to get a blade needle bearing that will have an acceptable interference fit.

B. Oversize blade needle bearings have been made to accommodate the repair limits for the blade bore specified in the Blade Shank Overhaul chapter of this manual.

(1) Oversize Blade Needle Bearing C-6252

(a) The C-6252 blade needle bearing is an approved alternative to the B-6684 or B-6685 blade needle bearing in the "R", P" modified to "R", "W", "T", "M", and "M" or "T" with "N" modification shank aluminum propeller blades.

NOTE: Current production "R" and "W" shank blades have the 1.7535 inch (44.539 mm) diameter constraint; however, older "R" and "W" shank blades can have a larger diameter because of an internal blade bushing. Refer to the Blade Shank Overhaul chapter of this manual.

(b) The C-6252 blade bearing is slightly larger in diameter than the standard blade needle bearing. This needle bearing is recommended for use in blades that are near the maximum bore diameter limits (1.7520 to 1.7535 inches [44.500 to 44.539 mm]).

(c) Special or additional procedures are not necessary for removal or installation of the oversize C-6252 blade needle bearing.

(2) Oversize Blade Needle Bearing B-7283

(a) The B-7283 blade needle bearing is an approved alternative to the B-6681 blade needle bearing in the "MV" with "N" modification, "V" with "N" modification, and "V" shank aluminum propeller blades.

(b) The B-7283 blade needle bearing is slightly larger in diameter than the standard blade needle bearing. This bearing is recommended for use in blades that are near the maximum bore diameter limits (1.5025 to 1.5055 inches [38.164 to 38.239 mm]).

(c) Special or additional procedures are not necessary for removal or installation of the oversize B-7283 blade needle bearing.



18. Retirement of Blades in Propeller Assembly HC-B4TN-5(D,G,J)L/LT10282(N)(B,K)-5.3R


A. Effectivity

(1) All HC-B4TN-5(D,G,J)L/LT10282(N)(B,K)-5.3R propeller assemblies installed on Mitsubishi MU-2B-26A, MU-2B-36A, MU-2B-40, and MU-2B-60 aircraft or other MU-2 aircraft modified by installation of the propeller model listed above.

B. Requirements

(1) In accordance with Airworthiness Directive 95-01-02 and Hartzell Propeller Inc. Service Bulletin A188, blade replacement or rework requirements exist. Refer to the indicated documents for additional information.



Rev. 22 Jun/0761-13-33

10574F(S)(B) Blade Conversion Table 4-6

Station 30EdgeWidthThicknessFaceAngle 0 degrees -Set Up

Station 36Edge 2.980 inches to 3.060 inchesWidth 6.940 inches to 7.020 inchesThickness 0.555 inches to 0.585 inchesFace 7.070 inches to 7.110 inchesAngle 23.9 degrees to 24.3 degrees





Rev. 22 Jun/0761-13-33

10574F(S)(B) Blade Modification Template Figure 4-3

Bla

de le

adin

g ed

ge

1057

4(A

)(S

)(B

)

1057

4(F)

(S)(

B)

Tip

tem

plat

e en

ds a

t 42"

sta

tion

The

tip p

rofil

e m

ust b

e bl

ende

d sm

ooth

ly

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een

the

30" a

nd 4

2" s

tatio

n.

APS257

42"

4

8"

36"

30

"



Rev. 28 Sep/1261-13-33

19. Modification of Blade Model LT10574(A)(S)(B) to LT10574F(N)S(B)


A. Effectivity

(1) Dornier DO-228 series aircraft with Hartzell Propeller Inc. propeller assembly HC-B4TN-5( )L/LT10574(A)(S)(B)

B. Discussion

(1) There have been intermittent occurrences of blade tip stalling and associated high propeller noise levels on this installation. This condition, if it occurs, is usually apparent during the landing maneuver when the propeller blade angle is close to ground idle blade angle i.e., "beta" range.

(2) This condition is capable of producing abnormally high stresses on the blades in the propeller assembly.

C. Requirements

(1) Each LT10574(B) blade must be replaced at overhaul.

(2) Each LT10574A(S)(B) blade must be modified to blade model LT10574FS(B) at next overhaul.

(3) Modification instructions are as follows:

(a) Place the blade on a blade inspection arbor. Set the arbor for a 7.5 inch blade centerline in accordance with section 2.J. of the Blade Airfoil Overhaul chapter of this manual.

(b) Using a non-graphite pencil such as CM162 or equivalent, identify each blade station listed in 10574F(S)(B) Blade Conversion Table 4-6. Refer to section 2.J. of the Blade Airfoil Overhaul chapter for station identification techniques.

(c) Record the dimensions of each blade station.(d) As shown in Figure 4-3, make a template for the 10574F(S)(B) tip shape,

and transfer the shape to the blade surface.(e) Compare the blade station dimensions to the station dimensions defined

in 10574F(S)(B) Blade Conversion Table 4-6. Reshape the airfoil and tip profile to the new specifications. Make sure there is smooth transition between each blade station and a smooth transition to the new tip profile.

(f) Inspect each blade in accordance with section 2.J. of the Blade Airfoil Overhaul chapter. If the blade does not meet inspection criteria, rework and recheck the blade.


SPECIAL INSPECTIONS AND PROCEDURES 61-13-33 Page 4-31Rev. 35 Nov/17

(g) Shot peen the blade as required from the 7 to 30 inch stations in accordance with the Shot Peening chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(h) Inspect the shot peened surfaces in accordance with section 2.L. of the Blade Airfoil chapter of this manual.

(i) Using a round bottom stamp or vibra-engraver, re-identify the new model number on the blade butt.

(j) Optionally, re-identify the blade model number with an ink stamp or a label on the camber side of the blade.

20. Retirement of Certain Blade Models Installed on Propeller Model HC-12X20


A. General

(1) In order to increase the fatigue limit of the blade shank on aluminum blades, a change was made in the radius at the inner flange retention shoulder on September 1, 1952.

(2) Blades manufactured prior to this change and installed on Lycoming O-435 engines were subject to cracks in the radius. These blades will not pass optical comparator inspection and rework of these blades is no longer authorized.

B. Procedure

(1) Blades with serial numbers below 75,000 which were manufactured before September 1, 1952, and installed on Lycoming O-435 engines (propeller model HC-12X20) must be retired from service.

21. Replacement of Non-Counterweighted Blade Models 8475-( ) and 8477-( )


NOTE: This information was obtained from Hartzell Propeller Inc. Service Bulletin 101D.

A. General

(1) A strengthened pitch change knob was incorporated into Y shank blade models that were manufactured after August of 1971. These blades are identified with the letter "F" preceding the blade model number.



Rev. 32 Nov/1561-13-33

B. Procedure

(1) All 8475-( ) and 8477-( ) propeller blades with over 1000 hours of service that are non-counterweighted and do not have a letter "F" preceeding the blade model number must be replaced with blades incorporating the strengthened pitch change knob (identified by the letter "F" preceding the blade model number). This must be accomplished within the next 200 hours of service.

22. Additional Blade Shank Inspection for T9212, 10172( ), 10173( ) and 10176( ) Blades


A. Effectivity

(1) All T9212, non-category II 10172( ) and 10173( ) (excludes 10173D), and category II 10173( ) and 10176( ) blades.

B. Discussion

(1) When the above blades are at extreme shank thickness or face alignment limits, it is possible to violate the minimum wall thickness of the blade shank at the end of the pilot tube bore. This condition may result in fatigue cracks in the critical radius of the blade bore.

C. Procedure

(1) For the 10172( ) and 10173( ) non-category II blades, use TE131 (refer to Figure 4-2) to complete the inspection at each overhaul. Complete the inspection procedures in accordance with paragraph 14.C.(1)(f) of this chapter.

(2) For T9212 and category II 10173( ) and 10176( ) blades, a new tool similar to that shown in Figure 4-2 must be created by changing the "B" dimension to 0.798 ± 0.002 inch. Complete the inspection procedures of paragraph 14.C.(1)(f) of this chapter at each overhaul.

NOTE: The tool for these blades can be created by purchasing a new TE131 and modifying it, or by fabricating a new tool according to the dimensions in Figure 4-2 with the exception of the alternate "B" dimension.

(3) If the leg shown as section "B" does not contact the blade at the thinnest position located on the shank, the blade must be retired from service.



23. Replacement Blade for M10876K Installed on Shorts SD3-60 Aircraft


A. All blades with this design number must be retired from service and replaced with blade design number M10876ASK.

24. Replacement of Hartzite Blades


A. A Hartzite blade cannot be repaired, overhauled, or converted to a “V” or "MV" shank blade. To determine if a Hartzite blade can be replaced by an aluminum blade, consult the aircraft Type Certificate (TC) or Supplemental Type Certificate (STC).

25. Replacement of 7663-4 Blades with Serial Numbers Below B35571


NOTE: This information was obtained from Hartzell Propeller Inc. Service Bulletin HC-SB-61-96A.

A. All 7663-4 blades with serial numbers below B35571 must be retired from service and replaced with F7663-4 blades.



Rev. 28 Sep/1261-13-33

26. Interchangeability of "P", "R", "W", and "Z" Shank Blades with "N" Modification


A. Effectivity

(1) All "P", "R", "W", or "Z" shank blades are affected.

(2) All "P", "R", "W", and "Z" shank aluminum blades are now being manufactured with the "N" modification that incorporates significant design improvements to the internal blade bore.

(3) The propeller Type Certificate Data Sheet has been revised to permit use of "N" modification and non-"N" modification blades on installations originally certified with non-"N" modification blades.

(4) Non-"N" modification blades are not permitted on an installation that originally was certified with "N" modification blades.

B. Discussion

(1) Mixing "N" and non-"N" blades is permitted in the same propeller assembly provided propeller static balance can be achieved.

CAUTION: DO NOT REPLACE AN "N" MODIFICATION BLADE WITH A NON-"N" MODIFICATION BLADE.

(2) Replacing an "N" modification blade with a non-"N" modification blade is not permitted.

(3) For "R" and "W" shank aluminum blades, the design change requires the use of a new internal bearing spacer.

(4) "N" modification blades are identified with the suffix letter "N" in the blade model.

(a) This suffix letter is impression stamped on the blade butt, ink stamped or labeled on the blade airfoil. NOTE: Example: LW10151-3 will change to LW10151N-3

1 Optionally, at overhaul the blade model may also be ink stamped or a label applied on the blade airfoil.

(5) Rework of the blade bore to the "N" modification is not permitted.

(6) When all blades in the assembly are the "N" design, make an entry in the propeller logbook about the change to the blade model designation.

(a) If any blade in the assembly is a non-"N" design, the entry in the logbook should not be made.


SPECIAL INSPECTIONS AND PROCEDURES 61-13-33 Page 4-35Rev. 31 Jul/14

27. Modification of Counterweight D-6021-1 for Use with De-ice Kit 103253


A. Modify the counterweight for use with the wire harness and de-ice boot.

(1) Modify the counterweight to incorporate the mounting holes for the terminal strip, the attachment hole for the tie mount, and the spring pin, in accordance with Figure 4-4 and Figure 4-5.

(2) If the 6-32 UNC-3B threaded hole is damaged, a threaded insert may be installed.

(a) Using a 6-32 true position indicator or a thread tap to locate off of the thread pitch diameter, determine the center of the threaded hole. 1 Optionally, the largest drill blank that will fit into the minor diameter

of the threaded hole may also be used to determine the center of the hole.

(b) Bore the hole to a diameter 0.1495 (#25 drill) a minimum of 0.539 inch (13.70 mm) deep.

(c) Deburr the edges of the hole.(d) Using Heli-Coil® STI Tap part number 06CBB, or equivalent, tap the newly

bored hole a minimum of 0.414 deep.(e) Using a Heli-Coil® thread gauge part number 3688-06, or equivalent,

make an inspection of the tapped hole. 1 The "GO" thread end must install freely. 2 Retap the hole until the inspection of the tapped hole is satisfactory.

(f) Using installation tool Heli-Coil® part number 7551-36, or equivalent, install the Heli-Coil® part number 1185-06CN-0414 in the threaded hole a minimum of 1/4 pitch below the mounting surface.

(g) Make a visual inspection of the threads of the installed Heli-Coil®.(h) Verify that a 6/32 threaded fastener will install correctly.

(3) If the spring pin hole was machined too large, it may be repaired by enlarging the hole and installing an oversize spring pin.

(a) Drill the spring pin hole to the oversize diameter listed in Figure 4-4.(b) Install the oversize spring pin B-6378-7 as a replacement for the

spring pin B-3842-0500 identified in the de-ice kit 103253.



Rev. 31 Jul/1461-13-33

Terminal Strip HolesTap hole 6-32 UNC-3B Thread depth (minimum) 0.375 inch (9.52 mm)Minor dia. 0.104 - 0.114 inch (2.64 - 2.89 mm)Depth 0.60 inch (15.2 mm)

Existing Threaded Hole

Modification of Counterweight for Terminal Strip and Spring Pin Attaching HolesFigure 4-4

1.3 inch (33.0 mm)

0.75 inch (19.0 mm)

0.275 inch (7.0 mm)

View shows trailing edge side of the counterweight.

0.32 inch(8.1 mm)

Spring Pin HoleStandard Diameter: 0.094 - 0.097 inch (2.39 - 2.46 mm)Oversize Diameter: 0.125 - 0.129 inch (3.17 - 3.27 mm)Depth 0.30 - 0.36 inch (7.6 - 8.4 mm)

0.38 inch(9.6 mm)



2.0 inch (50 mm)

0.5 inch(12 mm)

Tap hole 8-32 UNC-3B Thread depth 0.25 inch (6.3 mm) minimum.Minor dia. 0.1300-0.1389 inch (3.3-3.5 mm)Depth 0.438 inch (11.12 mm)

Existing Threaded Hole

Modification of Counterweight for Tie Mount Attaching HoleFigure 4-5

View shows leading edge side of the counterweight.



Rev. 29 Nov/1261-13-33

28. Replacement of T10173F(N)(B,K)-12.5 blades with T10173AN(B,K)-12.5 Blades


A. Effectivity

(1) Hawker Beechcraft King Air B100 aircraft with Hartzell Propeller Inc. steel hub propeller HC-B4TN-5(C,F)/T10173F(N)(B,K)-12.5 are affected.

B. Discussion

(1) There have been sporadic reports of blade flutter during landing while using propeller reversing. An investigation identified a greater likelihood for this occurrence with blades nearing dimensional minimums.

(a) This same occurrence of blade flutter is also possible with blades near original manufacturing specifications.

(b) This condition can cause cracked and/or failed blades.C. Requirements

(1) Replace all affected blades with the improved T10173AN(B,K)-12.5 blades in accordance with Hartzell Propeller Inc. STC SA02539CH-D and Hartzell Propeller Inc. Service Bulletin HC-SB-61-304.

29. Replacement of "Y" Shank Blades Used in Propeller Models ( )HC-( )( )Y( )-( )


A. Effectivity

(1) Hartzell Propeller Inc. compact propeller models ( )HC-( )( )Y( )-( ) with "Y" shank, aluminum blades that have a serial number that is listed in Hartzell Propeller Inc. Alert Service Bulletin HC-ASB-61-322.

B. Discussion

(1) During dye penetrant inspection at overhaul, one blade was found to have an indication in the blade bearing bore. This indication was determined to be caused by a unique condition in the aluminum forging from the vendor.

(2) All blades machined from the same forging lot may have this condition.

B. Requirements

(1) Replace blades as necessary in accordance with the instructions in Hartzell Propeller Inc. Alert Service Bulletin HC-ASB-61-322.


FINISHPage 5-1

Rev. 28 Sep/1261-13-33

FINISH - CONTENTS

1. Finish ..................................................................................................................5-3

A. Blade Painting ...............................................................................................5-3

B. Application of Teflon® Tape on "Y", "D", and "E" Shank Blades .....................5-5

C. Application of Hard Coating on Shank Radius ..............................................5-9

D. Installation of Blade Retention Split Bearing Race and Bearing Retaining Ring onto "Y", "D", and "E" Shank Blades ...........................................................5-10

E. Application of Lubricant to the Blade Bore ..................................................5-12

FINISH - LIST OF FIGURES

Blade Shank Teflon® Tape ......................................................... Figure 5-1 ..................5-4

Blade Shank Teflon® Tape Location ........................................... Figure 5-2 ..................5-4

Application of CM49 on Aluminum Blade Shanks ..................... Figure 5-3 ..................5-8

Application of Approved Lubricant Within the Blade Bore ......... Figure 5-4 ................5-11


FINISHPage 5-2

Rev. 27 Sep/1161-13-33



FINISHPage 5-3

Rev. 28 Sep/1261-13-33

1. Finish



A. Blade Painting


(1) Approved corrosion protection followed by approved paint must be applied and maintained on all aluminum blades.

(a) For information about the application of corrosion protection and paint, refer to the Chromic Acid Anodizing and Paint and Finish chapters of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(b) Operation of blades without the specified coatings and finishes, i.e., “polished blades”, is not permitted.

(2) Blade paint schemes, e.g., finish, color, tip stripe patterns, and colors, are defined by the blade configuration.

(a) To determine the correct paint scheme for a specific blade configuration, refer to the Blade Finish Table in the Paint and Finish chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(b) An aluminum blade can be refinished using any aluminum blade paint scheme specified in Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02). The Blade Finish Table in the Paint and Finish chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02) describes manufacturing paint schemes used by Hartzell Propeller Inc.

(3) For instructions, recommendations, equipment, mixture proportions, tip patterns, label and stamp locations, and other finish related information, refer to the Paint and Finish chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).


FINISHPage 5-4

Rev. 23 Mar/0861-13-33

Blade Shank Teflon® Tape LocationFigure 5-2

NOTE: "D" shank blade shown, others similar.

Blade Shank Teflon® Tape Figure 5-1

B4256

NOTE: Use 1/2-inch (12.7 mm) CM155 or 3/4-inch (19.05 mm) CM156 Teflon® tape, cut to the length shown.

45 degrees 45 degrees

"X" Blade Shank Teflon® Tape

C2890

Shank Type "X" Dimension (Inches) For 1/2-inch (12.7 mm) Tape

"X" Dimension (Inches) For 3/4-inch ( 19.1 mm) Tape

"Y" SHANK 0.875 ± 0.031 Inches N/A(22.23 ± 0.78 mm)

"D" SHANK 0.875 ± 0.031 N/A(22.23 ± 0.78 mm)

"E" SHANK IN 4 BLADE PROPELLER 0.710 ± 0.030 0.650 ± 0.030(18.03 ± 0.76 mm) (16.51 ± 0.76 mm)

"E" SHANK IN 5 BLADE PROPELLER 0.90 ± 0.030 0.650 ± 0.030(22.86 ± 0.76 mm) (16.51 ± 0.76 mm)

10.620 Inch (269.75 mm)


FINISHPage 5-5

Rev. 28 Sep/1261-13-33

B. Application of Teflon® Tape on "Y", "D", and "E" Shank Blades


The blade shank Teflon® tape, CM155 or CM156 is applied to the hub seal mating surface of "Y", "D" and "E" shank blades. This is applied to prevent the O-ring or quad ring, which seals between the hub and the blade, from wearing into the shank of the blade.

(1) Use 0.50 inch (12.7 mm) wide tape CM155 on "Y" and "D" shank blades.

(2) Use 0.50 inch (12.7 mm) wide tape CM155 or 0.75 inch (19.0 mm) wide tape CM156 on "E" shank blades.

NOTE: Both tapes are available in longer length rolls, which may be cut to the proper size. Refer to Figures 5-1 and 5-2.

(3) Permit the paint to dry for one hour or dry to the touch.

(4) Using a non-graphite pencil CM162 or equivalent, mark the location where the Teflon® tape CM155 or CM156 is to be placed around the blade OD. Refer to Figure 5-2.

(5) Cut Teflon® strip CM155 or CM156. Refer to Figure 5-1.

(6) Mix epoxy CM68 in accordance with the manufacturer's directions.

(7) Using a 0.50 inch (12.7 mm) brush, apply epoxy CM68 around the shank OD.

(a) If 0.50 inch (12.7 mm) Teflon® tape CM155 is used, apply a smooth, even layer 0.125 inch (3.2 mm) inboard of the layout line and 0.75 inch (19.0 mm) wide.

(b) If 0.75 inch (19.0 mm) Teflon® tape CM156 is used, apply a smooth even layer 0.125 inch (3.2 mm) inboard of the layout line and 1 inch (25.4 mm) wide.

CAUTION: Do not overlap the ends of the Teflon® tape CM155 or CM156.(8) Start applying the Teflon® tape CM155 or CM156, as applicable, on the face

side of the blade.

(a) Apply the Teflon® tape CM155 or CM156, as applicable, so that the split is located on the camber side of the blade.

(b) The maximum permitted seam gap width between the ends of the Teflon®

tape CM155 or CM156, as applicable is 0.031 inch (0.78 mm).

(c) Fill the gap with epoxy.

(9) Apply 1.5 inch (38 mm) wide masking tape tightly over the Teflon® tape CM155 or CM156.


FINISHPage 5-6

Rev. 28 Sep/1261-13-33

(10) When the epoxy starts to set, remove the masking tape from the blade.(11) Using 240-grit emery cloth, sand the seam of the Teflon® tape CM155 or

CM156 to remove any rough edges. (12) Using 400-grit sandpaper, sand the seam of the Teflon® tape CM155 or CM156

to a smooth finish. (13) Make an inspection of the Teflon® tape CM155 or CM156 installation.

(a) The maximum permitted seam gap width is 0.031 inch (0.78 mm).

1 If the gap width is more than the maximum permitted, remove the Teflon® tape CM155 or CM156 and install a new piece of Teflon® tape CM155 or CM156, as applicable.

(b) The seam gap is filled with adhesive CM68.

(c) Air bubbles larger than 0.031 inch (0.79 mm) diameter are not permitted.

NOTE: Air bubbles can be distinguished from tape blemishes because the tape can be indented with pressure leaving a depression.

1 If there is an air bubble larger than the maximum permitted, remove the Teflon® tape CM155 or CM156 and install a new piece of Teflon® tape CM155 or CM156, as applicable.

(d) All masking tape used during the Teflon® tape CM155 or CM156 installation is removed.

(e) Examine the location of the Teflon® tape CM155 or CM156. Refer to Figure 502.

1 If the location is incorrect, remove the Teflon® tape CM155 or CM156 and install a new piece of Teflon® tape CM155 or CM156, as applicable.

2 If the location is correct, continue to the next step.

(f) Wrinkles, bumps, depressions, or ridges that are detectable by touch on the surface of the Teflon® tape CM155 or CM156 are not permitted.

1 If there is a wrinkle, bump, depression, or ridge, remove the Teflon® tape CM155 or CM156 and install a new piece of Teflon® tape CM155 or CM156, as applicable.

(g) Excess adhesive inboard or outboard of the Teflon® tape CM155 or CM156 must be flush or below the surface of the Teflon® tape CM155 or CM156.


FINISHPage 5-7

Rev. 23 Mar/0861-13-33



FINISHPage 5-8

Rev. 23 Mar/0861-13-33

Application of CM49 on Aluminum Blade Shanks Figure 5-3

APS2052SHANK5

Approximately0.50 Inch

(12.7 mm)

Coat the entire "V"

Approximately0.50 Inch(12.7 mm)


FINISHPage 5-9

Rev. 28 Sep/1261-13-33

C. Application of Hard Coating on Shank Radius


(1) General

(a) This procedure does not apply to "Y", "D", or "E" shank blades.

(b) Application of sealer CM49 provides a hard, fuel resistant layer on the blade shank radius.

(2) Procedure

(a) Using a 0.50 inch (12.7 mm) brush, apply a thin layer of sealer CM49 to the retention area of all double shoulder and all single shoulder blades, except those noted above. Refer to Figure 5-3.

(3) Permit the sealer CM49 to air dry.


FINISHPage 5-10

Rev. 28 Sep/1261-13-33

D. Installation of Blade Retention Split Bearing Race and Bearing Retaining Ring onto "Y", "D", and "E" Shank Blades


CAUTION 2: LUBRICANT APPLIED TO THE BLADE RETENTION RADIUS BEFORE INSTALLATION OF THE SPLIT BEARING RACE AND RETAINING RINGS IS EXTREMELY CRITICAL. THE ADHESIVE FILLS IN ANY VOIDS BETWEEN THE SPLIT BEARING RACE AND THE RADIUS OF THE BLADE SHANK. IF LUBRICANT IS NOT PUT AROUND THE BLADE RETENTION RADIUS, THE ADHESIVE WILL BOND THE SPLIT BEARING RACE TO THE BLADE SHANK.

CAUTION 3: VERIFY MATCHING BEARING RACE HALVES BY SERIAL NUMBER AND BY FIT. UNMATCHED BEARING HALVES WILL CAUSE IMPROPER FIT AND PREMATURE BEARING FAILURE.

NOTE: This procedure is to be completed after final blade balancing.

(1) Apply a light film of lubricant CM12 to the surface of the blade retention radius that will contact the bearing race.

(2) Apply adhesive CM16 to the lubricated area of the blade shank.

(3) Install the blade retention split bearing race on the blade shank.

(a) Align the split between the two halves of the bearing with the inboard portion of the leading and trailing edges of the blade.

(4) Put the blade shank in a fixture.

(5) Using a blade bearing press TE93, press the split bearing race retaining ring over the split bearing.

(6) Keep a force of 6000 to 8000 lb (2722 to 3628 kg) for at least 45 seconds.


FINISHPage 5-11

Rev. 28 Sep/1261-13-33

Application of Approved Lubricant Within the Blade Bore Figure 5-4

Fill to Top of Needle Bearing

ASK1314

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.

CAUTION: DO NOT APPLY SOLVENT TO UNCURED BLADE PAINT. APPLYING SOLVENT TO BLADE PAINT THAT IS NOT CURED MAY CAUSE THE BLADE PAINT TO SOFTEN.

(7) Using a clean, dry cloth, wipe the excess adhesive from the split bearing race and blade shank.

(a) Optionally, use a clean cloth dampened with solvent MEK CM106, MPK CM219, or toluene CM41.


FINISHPage 5-12

Rev. 28 Sep/1261-13-33

E. Application of Lubricant to the Blade Bore


(1) After a blade completes the final balancing process, apply lubricant CM12 in accordance with the following:

(a) For "Y", "D", or "E" shank blades, apply a small amount of lubricant CM12 to the needle bearing.

(b) For all except "Y", "D", or "E" shank blades, fill the blade bore with lubricant CM12.

NOTE: When filling the blade bore with lubricant CM12, make sure that no air pockets form within the balance hole or blade bore because it can affect propeller balance.

1 For blades that have a needle bearing in the bottom of the blade bore, fill the balance hole and the blade bore to the top of the needle bearing. Refer to Figure 5-4.

2 For blades that have only a bronze bushing, fill the balance hole and the blade bore to approximately 1 inch (25.4 mm) from the butt of the blade.

(2) If the blade is to be stored before propeller assembly buildup, cover the blade shank with a plastic bag secured with a rubber band.

DE-ICE BOOTPage 6-1

Rev. 37 Dec/1861-13-33


DE-ICE BOOT - CONTENTS

De-ice and anti-icing boot instructions have been relocated to the Hartzell Propeller Inc.Propeller Ice Protection System Manual 180 (30-61-80).

DE-ICE BOOTPage 6-2

Rev. 37 Dec/1861-13-33


(This page intentionally blank.)


BLADE BALANCINGPage 7-1

Rev. 22 Jun/0761-13-33

CONTENTS - BLADE BALANCING

1. Static Balance of Aluminum Propeller Blades.........................................................7-3

A. Static-Horizontal Balancing of Blade Sets .........................................................7-3

B. Static-Vertical Balancing of Blade Sets .............................................................7-7

LIST OF FIGURES - BLADE BALANCING

Blade Balancing, Horizontal Position............................Figure 7-1 ....................................7-3

Blade Balancing, Vertical Position ................................Figure 7-2 ....................................7-6



Rev. 22 Jun/0761-13-33




Rev. 28 Sep/1261-13-33

Adjustable weight

Blade on balance stand with leading edge up

APS2071

Blade Balancing, Horizontal Position Figure 7-1

1. Static Balance of Aluminum Propeller Blades

A. Static-Horizontal Balancing of Blade Sets


NOTE: Static-horizontal blade balancing is required at overhaul for aluminum blades in a blade set. Local tooling may differ and alternate procedures may be used to achieve similar results.

(1) Place the proper shank adapter for the blade type to be balanced on the balance stand.

(2) Place an adjusting weight on the balance stand (refer to Figure 7-1).

(3) Place a blade on the balance stand with the leading edge up.

(4) Adjust the weight on the balance stand until the blade is balanced in the horizontal position.

NOTE: The blade is considered balanced when it remains in the horizontal position with no tendency to rotate.



Rev. 34 Jan/1761-13-33

(5) Without adjusting the weight, put each of the remaining blades from the set on the balance stand so that the heaviest blade in the set may be determined.

(6) Put the heaviest blade in the set on the balance stand with the leading edge up.

(a) Adjust the weight until the blade is balanced in the horizontal position.

(7) Individually put the lighter blades in the set on the balance stand.

(a) Do not adjust the weight.

(b) In order to get each of these blades in the horizontal position, it is necessary to put lead wool in the blade balance hole.

(1) To find the amount of lead wool needed to balance the blade, put lead wool on the shank area, a distance equal to the depth of the blade balance hole (this dimension is stamped on the butt of the blade), until the blade is horizontally balanced.

(8) For "Y", "D", and "E" shank blades that use a closed-end bearing, remove the bearing before putting lead in the blade bore.

WARNING: ALUMINUM BLADES ARE LIMITED TO A MAXIMUM TEMPERATURE OF 200° F (93° C). USE ONLY ROOM TEMPERATURE LEAD WOOL TO BALANCE THE BLADE. UNDER NO CIRCUMSTANCE IS MELTED LEAD TO BE POURED INTO THE BALANCE BORE.

(9) Put the lead wool used to balance the blade in the blade balance hole.

(10) Using an applicable sized tool, tamp the lead wool until it is compressed in the bottom of the balance hole.

CAUTION: DO NOT PUT LEAD WOOL IN THE BLADE PILOT TUBE BORE.

(a) The amount of lead wool used to bring a blade into horizontal balance must only fill the blade balance hole.

(b) Small amounts of lead can move around in the lead hole after it is tamped into position. Sealant CM9 can be used to hold small amounts of lead in the bottom of the balance hole.

(11) Put the blade on the balance stand.

(a) The blade must stay in the horizontal position with no tendency to rotate.

(b) Add or remove lead, as necessary, to achieve proper balance.

(12) Complete steps 1.A.(7) through 1.A.(11)(b) for each of the remaining blades in the set.



Rev. 22 Jun/0761-13-33




Rev. 22 Jun/0761-13-33

Weights for adjusting vertical balance of heaviest blade

Top View Detail

Blade Balancing, Vertical Position Figure 7-2

APS2070APS2070A

Add weight, as required, five inches from the centerline of the balance arbor in either direction.



Rev. 28 Sep/1261-13-33

B. Static-Vertical Balancing of Blade Sets


NOTE: Static-vertical blade balancing is not a required overhaul procedure because experience has shown that matching blade edge alignment (see paragraph 2.J.(8) of the Blade Airfoil Overhaul chapter) is adequate for correcting most vertical imbalance problems. It is a recommended technique for identifying vibration or balance problems that have been encountered with a propeller assembly and cannot be attributed to any other cause. Local tooling may differ and alternate procedures may be used to achieve similar results.

(1) Blades in a set are vertically balanced during the blade grinding process. The vertical and horizontal balance of blades in a set should be tested before grinding, after initial grinding to remove all stone nicks and damage, and at the end of the grinding process.

(2) Vertical balance is complete when all blades in a set are within the allowable range (refer to paragraph 1.A.(2)(c)1 and 2. Horizontal balance is completed after the application of paint and de-icer boots (refer to paragraph 1.B. of this chapter).

(a) Using a balance stand incorporating the proper shank adapter, determine which blade is lightest in the horizontal position. Horizontal balance between blades in a set can be achieved by grinding the heavier blades in areas where the greatest amount of material exists (refer to the Blade Airfoil Overhaul chapter, paragraph 2.D.), keeping in mind the requirements for vertical balance.

(b) Place the lightest blade in the vertical position (see Figure 7-2) on the balance stand so that the leading and trailing edges are in-line with the adjusting weights at the blade setup station (refer to the Blade Specification Tables Appendix). Adjust the weights until the blade does not have a tendency to rotate.



Rev. 28 Sep/1261-13-33

(c) Check the vertical balance of all other blades in the set against the lightest blade (allow the blades to rotate; do not adjust the weights). Determine the difference between the heaviest blade in the set and all others by placing weight on the arm of the lighter side of the blade five inches from the centerline of the balance arbor (refer to Figure 7-2, Top View Detail). Record the amount needed to bring each blade into vertical balance. The total difference in weight between the blades in vertical balance must be established to determine if additional grinding is necessary. The maximum weight variation between all blades in the blade set is 0.0625 lbs. (1 ounce) at the five inch position on the balance arbor.

(d) If the total weight used to bring the blades in vertical balance exceeds 0.0625 lbs. (1.0 ounce), the vertical balance of the blades should be corrected by concentrating the grinding action on the heavy side of the heavier blade(s).


ILLUSTRATED PARTS LISTPage 8-1

Rev. 35 Nov/1761-13-33

ILLUSTRATED PARTS LIST- CONTENTS

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

A. General..........................................................................................................8-3

2. The Illustrated Parts List .....................................................................................8-3

A. Detailed Parts List .........................................................................................8-3

B. Revisions .......................................................................................................8-5

C. Vendors .........................................................................................................8-6

Blade Shank Parts List

"P" Shank ...........................................................................................................8-7

"P" Shank Modified to "R" Shank ........................................................................8-8

"R" Shank ..........................................................................................................8-9

"M" Shank .........................................................................................................8-11

"T" Shank .........................................................................................................8-12

"M" or "T" Shank with "N" Modification .............................................................8-13

"Y" Shank .........................................................................................................8-15

"D" and "E" Shank ............................................................................................8-17

"Z" Shank .........................................................................................................8-18

"Z" Shank Modified to "W" Shank .....................................................................8-19

"W" Shank ........................................................................................................8-20

"X" Shank ..........................................................................................................8-21

"X" Shank Modified to "V" Shank ......................................................................8-23

"V" Shank ..........................................................................................................8-24

"V" Shank with "N" Modification ........................................................................8-25

"MV" Shank with "N" Modification .....................................................................8-26

"P" or "Z" Shank with "N" Modification ..............................................................8-27

"R" or "W" Shank with "N" Modification ............................................................8-28

Miscellaneous Blade Parts .....................................................................................8-29



Rev. 35 Nov/1761-13-33

LIST OF FIGURES

"P" Shank ................................................................................Figure 8-1 .....................8-7

"P" Shank Modified to "R" Shank ............................................Figure 8-2 .....................8-8

"R" Shank ................................................................................Figure 8-3 .....................8-9

"M" Shank ................................................................................Figure 8-4 ...................8-11

"T" Shank .................................................................................Figure 8-5 ...................8-12

"M" or "T" Shank with "N" Modification ....................................Figure 8-6 ...................8-13

"Y" Shank ................................................................................Figure 8-7 ...................8-15

"D" and "E" Shank ..................................................................Figure 8-8 ...................8-16

"Z" Shank .................................................................................Figure 8-9 ...................8-18

"Z" Shank Modified to "W" Shank ............................................Figure 8-10 .................8-19

"W" Shank ...............................................................................Figure 8-11 .................8-20

"X" Shank ................................................................................Figure 8-12 .................8-21

"X" Shank Modified to "V" Shank .............................................Figure 8-13 .................8-23

"V" Shank ................................................................................Figure 8-14 .................8-24

"V" Shank with "N" Modification ...............................................Figure 8-15 .................8-25

"MV" Shank with "N" Modification ............................................Figure 8-16 .................8-26

"P" or "Z" Shank with "N" Modification .....................................Figure 8-17 .................8-27

"R" or "W" Shank with "N" Modification ...................................Figure 8-18 .................8-28

Miscellaneous Blade Parts ......................................................Figure 8-19 .................8-29



Rev. 28 Sep/1261-13-33

1. Introduction


A. General

(1) This Illustrated Parts List contains all of the current configurations for the specified propeller blades manufactured by Hartzell Propeller Inc. and supersedes any prints that may have previously been supplied for part and assembly information. Use the parts lists contained within the Illustrated Parts List for verifying the configuration of propeller blade models and ordering parts.

CAUTION: ILLUSTRATIONS IN THE ILLUSTRATED PARTS LIST ARE TO BE USED FOR IDENTIFYING PARTS AND SHOULD NOT BE USED AS A MAINTENANCE REFERENCE FOR ASSEMBLY.

(2) Figures are for reference only. The figures provide general views of parts. For ease of illustration, typical views of some parts were created and shown in multiple figures. For this reason, illustrated parts may not exactly reflect parts contained in some propeller blade assemblies.

(3) Parts are numbered to correspond with the Item numbers listed in the IPL.

2. The Illustrated Parts List

A. Detailed Parts List

(1) The Detailed Parts List consists of the Figure/Item Number, Part Number, Nomenclature, Effectivity Code, Units Per Assembly, and Overhaul. Space is reserved for the Airline Stock Number. The following is an explanation of each column.

(2) Fig/Item Number

(a) Figure Number refers to the illustration where items appear. Item Numbers are assigned in broken sequence to allow the insertion of subsequent additional parts. Items listed but not illustrated are identified by a dash to the left of the item number.

(b) Alpha variants will be used to add additional items. There are two reasons for the use of alpha variants:

1 A part may have an alternate, or may be superseded, replaced, or obsoleted by another part.

2 An Illustrated Parts List may contain multiple configurations. Effectivity codes are used to distinguish different part numbers within the same list. Effectivity codes are very important in the determination of parts in a given configuration.



Rev. 28 Sep/1261-13-33

(3) Part Number

(a) Use the Hartzell Propeller Inc. part number when ordering the part from Hartzell Propeller Inc. or a Hartzell Propeller Inc. approved distributor. Digits of Hartzell Part Numbers have no significance other than to identify a part.

(4) Airline Stock Number

(a) Space is reserved for the Airline Stock Number.

(5) Nomenclature

(a) This column identifies the item. The relationship of parts to assembly are indicated by the use of indentations. This column may also contain vendor CAGE codes, as applicable. Information regarding part alternative, supersedure, replacement, or obsolescence may also be found in this column. Refer to Revisions, below, for further information regarding alternate, superseded, replaced, or obsoleted parts.

(6) Effectivity Code (EFF CODE)

(a) The effectivity column shows the prefix and/or suffix of the propeller model to which the parts apply. In some cases, the specific engine or aircraft manufacturer may be called out. Effectivity codes assigned apply only to the figure/listing in which they appear. Parts common to all end items show no code.

(7) Units Per Assembly (UPA)

(a) Designates the total quantity of an item required for the next higher assembly or subassembly.

(8) Overhaul (O/H)

(a) Designates the parts that require replacement at overhaul. A "Y" will identify which parts are replaced at overhaul.



Rev. 23 Mar/0861-13-33

B. Revisions

(1) Alternate

(a) Alternate parts are identified by the term "ALTERNATE" in the Description column. Alternate items are considered airworthy for continued flight and existing stock of parts may be used for maintenance and/or repair. The new or alternate part numbers may be used interchangeably when ordering/stocking new parts.

(2) Supersedure

(a) Part changes are identified by the terms "SUPERSEDES ITEM _____" or "SUPERSEDED BY ITEM _____" in the Description column. Superseded items are considered airworthy for continued flight and existing stock of superseded parts may be used for maintenance and/or repair. Once the superseding part has been incorporated/installed into an assembly, the original superseded part may no longer be used. Superseded parts may no longer be available, and the new part number must be used when ordering/stocking new parts.

(3) Replacement

(a) Part changes identified by the terms "REPLACES ITEM _____" or "REPLACED BY ITEM _____" in the Description column are considered airworthy for continued flight, but must be replaced with a part with the new part number at overhaul. Existing stock of replaced parts may not used for maintenance and/or repair of effected assemblies. Replaced parts may no longer be available, and the new part number must be used when ordering/stocking new parts.

(4) Obsolescence

(a) Obsolete parts are identified by "OBS" in the Units Per Assembly (UPA) column. Obsolete items are considered unairworthy for continued flight.



Rev. 28 Sep/1261-13-33

(5) Service Documents and Airworthiness Directives

(a) In the event of modification or rework of an existing part, the supersedure, replacement, or obsolescence of a part, or the addition of parts installed by a Service Bulletin (SB) or Service Letter (SL), the SB or SL number will appear in the Description column as "SB_____", or "SL_____" after the description.

(b) When a SB has a relationship to an Airworthiness Directive (AD), the AD will be shown in parentheses after the SB number as SB_____ (AD____).

C. Vendors

(1) Many O-rings, fasteners, and other vendor supplied hardware listed in Hartzell manuals have previously been specified with AN, MS, NAS or vendor part number. To provide internal controls and procurement flexibility, Hartzell Propeller Inc. has made engineering changes to provide all O-rings, fasteners, and hardware with a Hartzell Propeller Inc. part number. Parts shipments from Hartzell Propeller Inc. will specify only the Hartzell Propeller Inc. part numbers.

(2) Some O-rings, fasteners, and hardware manufactured in accordance with established industry specifications (certain AN, MS, NAS items) are permitted for use in Hartzell Propeller Inc. products without additional standards imposed by Hartzell Propeller Inc.; however, Hartzell Propeller Inc. does impose restrictions on certain AN, MS, and NAS vendor parts, which must be procured directly from Hartzell Propeller Inc.. Refer to the Vendor Cross Reference chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02) for a listing of part number interchangeability. Where allowable, both the Hartzell Propeller Inc. part number item and AN, MS, NAS, and other specified vendor numbers items can be used interchangeably. The Hartzell Propeller Inc. part number must be used when ordering these parts from Hartzell Propeller Inc.



Rev. 23 Mar/0861-13-33

FIG./ITEM PART AIRLINE NOMENCLATURE EFF UPA O/H NUMBER NUMBER STOCK NUMBER 1 2 3 4 5 6 7 CODE

"P" Shank

8-1 "P" SHANK 4 A-1309 • BUSHING, BLADE 1 Y

OIL GROOVE IS OPTIONAL

4

"P" Shank Figure 8-1

APS-0641



Rev. 23 Mar/0861-13-33


"P" Shank Modified to "R" Shank

8-2 "P" SHANK MODIFIED TO "R" SHANK 2 A-1349 • SPACER 1 3 B-6684 • BEARING, NEEDLE 1 Y 3A C-6252 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y

REFER TO USE OF OVERSIZE INTERNAL BLADE BEARING IN THE SPECIAL INSPECTIONS AND PROCEDURES CHAPTER OF THIS MANUAL.

4 A-1309 • BUSHING, BLADE 1 Y 4A A-1309-1 • BUSHING, BLADE, ALTERNATE 1 Y 5 A-1347 • BUSHING, BLADE 1 Y

2345

"P" Shank Modified to "R" Shank Figure 8-2

APS0651



Rev. 23 Mar/0861-13-33


"R" Shank

8-3 "R" SHANK 2 A-1349 • SPACER 1 3 B-6684 • BEARING, NEEDLE 1 Y 3A C-6252 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y


5 A-1347 • BUSHING, BLADE 1 Y

23

5

"R" Shank Figure 8-3

APS0650



Rev. 23 Mar/0861-13-33



Page 8-11Rev. 27 Sep/1161-13-33ILLUSTRATED PARTS LIST


8-4 "M" SHANK 2 A-1349 • SPACER 1 3 B-6684 • BEARING, NEEDLE 1 Y 3A B-6685 • BEARING, NEEDLE, ALTERNATE 1 Y 3B C-6252 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y 6 B-6682 • BEARING, NEEDLE 1 Y


6A B-6683 • BEARING, NEEDLE, ALTERNATE 1 Y

"M" Shank

236

"M" Shank Figure 8-4

APS0645




8-5 "T" SHANK 2 A-1349 • SPACER 1 3 B-6684 • BEARING, NEEDLE 1 Y 3A B-6685 • BEARING, NEEDLE, ALTERNATE 1 Y 3B C-6252 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y


6 B-6682 • BEARING, NEEDLE 1 Y 6A B-6683 • BEARING, NEEDLE, ALTERNATE 1 Y

"T" Shank

APS0647

62

3

"T" Shank Figure 8-5




8-6 "M" OR "T" SHANK WITH "N" MODIFICATION 2 A-385 • SPACER 1 Y 3 B-6684 • BEARING, NEEDLE 1 Y 3A B-6685 • BEARING, NEEDLE, ALTERNATE 1 Y 3B C-6252 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y


6 B-6682 • BEARING, NEEDLE 1 Y 6A B-6683 • BEARING, NEEDLE, ALTERNATE 1 Y

"M" or "T" Shank with "N" Modification

236

APS0656

"M" or "T" Shank with "N" Modification Figure 8-6



Rev. 27 Sep/1161-13-33





"Y" Shank

APS06408

7

109

13

"Y" Shank Figure 8-7

8-7 "Y" SHANK, REFER TO NOTE 1

1 A-2414 • PLUG, BLADE 1 3 B-6680 • BEARING, NEEDLE, CLOSED END 1 Y 8 A-2413( ) • BUSHING, KNOB, PITCH CHANGE 1 Y (“F” KNOB BLADES, WITHOUT SHOT PEEN) 8A C-7645-( ) • BUSHING, KNOB, PITCH CHANGE, ALTERNATE 1 Y (“F” KNOB BLADES, WITH SHOT PEEN) 8B A-2413 • BUSHING, KNOB, PITCH CHANGE, ALTERNATE 1 Y (NON “F” KNOB BLADES) 7 CM155 • TEFLON® TAPE AR 9 A-2202 • BEARING, RETENTION, BLADE 1 10 A-2204 • RING, RETAINING, BEARING 1

NOTE 1: COUNTERWEIGHT SLUGS AND COUNTERWEIGHT SLUG MOUNTING HARDWARE ARE APPLICATION SPECIFIC. COUNTERWEIGHT SLUG MOUNTING HARDWARE MUST BE REPLACED AT OVERHAUL. REFER TO HARTZELL PROPELLER INC. APPLICATION GUIDE MANUAL 159 (61-02-59).



Rev. 29 Nov/1261-13-33

31

910

7

APS-0655

"D" and "E" Shank Figure 8-8



Rev. 39 Mar/2061-13-33

"D" and "E" Shank

8-8 "D" SHANK, REFER TO NOTE 1 1 A-2414 • PLUG, BLADE 1 3 B-6680 • BEARING, NEEDLE, CLOSED END 1 Y 7 CM155 • TEFLON® TAPE AR 9 A-2202 • BEARING, RETENTION, BLADE 1 10 A-2204 • RING, RETAINING, BEARING 1 PRE HC-SL-61-241, R3 SUPERSEDED BY ITEMS 10A, 11, 12 10A 102158 • RING, RETAINING, BEARING 1 POST HC-SL-61-241, R3 SUPERSEDES ITEM 10 11 B-7726 • SEAL, BLADE, POST HC-SL-61-241, R3 4 USE WITH ITEMS 10A AND 12 12 C-3317-045 • O-RING, POST HC-SL-61-241, R3 4 USE WITH ITEMS 10A AND 11

8-8 "E" SHANK, REFER TO NOTE 1 1 A-665 • PLUG, BLADE 1 3 A-1271 • BEARING, NEEDLE, CLOSED END 1 Y 7 CM155 • TEFLON® TAPE AR 9 C-792-( ) • BEARING, RETENTION, BLADE 1 10 B-1041 • RING, RETAINING, BEARING C 1 PRE HC-SL-61-241 SUPERSEDED BY ITEMS 10B, 11, 12 10A B-7071 • RING, RETAINING, BEARING C 1 POST HC-SL-61-241 SUPERSEDES ITEM 10A 11 B-7726 • SEAL, BLADE, POST HC-SL-61-241, R3 C 4 USE WITH ITEMS 10A AND 12 12 C-3317-045 • O-RING, POST HC-SL-61-241, R3 C 4 USE WITH ITEMS 10A AND 11 -13 B-6986-258M • INSERT, THREAD, THIN WALL (TE410) A 2 Y POST HC-SB-61-252

NOTE 1: REFER TO THE APPLICABLE PROPELLER ASSEMBLY MANUAL FOR PARTS INFORMATION REGARDING PITCH CHANGE KNOBS AND BLADE RETENTION BEARINGS FOR "D" AND "E" SHANK BLADES.

NOTE 2: COUNTERWEIGHT SLUGS AND COUNTERWEIGHT SLUG MOUNTING HARDWARE ARE APPLICATION SPECIFIC. COUNTERWEIGHT SLUG MOUNTING HARDWARE MUST BE REPLACED AT OVERHAUL. REFER TO HARTZELL PROPELLER INC.APPLICATION GUIDE MANUAL 159 (61-02-59).

A (H,L)E8218 C "E" SHANKS ONLY

FIG./ITEM PART AIRLINE NOMENCLATURE EFF. UPA O/H NUMBER NUMBER STOCK NUMBER 1 2 3 4 5 6 7 CODE

EFFECTIVITY MODEL EFFECTIVITY MODEL



Rev. 23 Mar/0861-13-33


APS0642

4

"Z" Shank Figure 8-9

"Z" Shank

8-9 "Z" SHANK 4 A-1309 • BUSHING, BLADE 1 Y




Rev. 23 Mar/0861-13-33


"Z" Shank Modified to "W" Shank Figure 8-10

APS0644

8-10 "Z" SHANK MODIFIED TO "W" SHANK 2 A-1349 • SPACER 1 3 B-6684 • BEARING, NEEDLE 1 Y 4 A-1309-1 • BUSHING, BLADE 1 Y 4A A-1309 • BUSHING, BLADE, ALTERNATE 1 Y 5 A-1347 • BUSHING, BLADE 1 Y

234

5

"Z" Shank Modified to "W" Shank



Rev. 23 Mar/0861-13-33


APS0643

235

"W" Shank Figure 8-11

8-11 "W" SHANK 2 A-1349 • SPACER 1 3 B-6684 • BEARING, NEEDLE 1 Y 3A C-6252 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y



"W" Shank



Rev. 23 Mar/0861-13-33


5

(Oil grooves)

PART NO. BLADE BORE Ø AFTER REWORK

A-127 1.5590 to 1.5610 Inches (39.599 to 39.649 mm) Has flange; oil grooves optional

A-127-1 1.5590 to 1.5610 Inches (39.599 to 39.649 mm)

A-127-4 1.5611 to 1.5630 Inches (39.652 to 39.700 mm) Has flange; oil grooves optional

A-127-5 1.5611 to 1.5630 Inches (39.652 to 39.700 mm)

APS0649

"X" Shank Figure 8-12

"X" Shank

8-12 "X" SHANK 5 A-127 • BUSHING, BLADE, REFER TO NOTE 1 1 5A A-127-1 • BUSHING, BLADE, REFER TO NOTE 1 1 5B A-127-4 • BUSHING, BLADE, REFER TO NOTE 1 1 5C A-127-5 • BUSHING, BLADE, REFER TO NOTE 1 1

NOTE 1: FOR THE CORRECT BUSHING SELECTION, MEASURE THE BLADE BORE DIAMETER AFTER REWORK AND IF OIL GROOVE IS PRESENT. REFER TO THE CHART IN FIGURE 8-12.



Rev. 23 Mar/0861-13-33




Rev. 23 Mar/0861-13-33


"X" Shank Modified to "V" Shank Figure 8-13

235

APS0648


A-127 1.5590 to 1.5610 Inches (39.599 to 39.649 mm)

Has flange; oil grooves optional

A-127-1 1.5590 to 1.5610 Inches (39.599 to 39.649 mm)

A-127-4 1.5611 to 1.5630 Inches (39.652 to 39.700 mm)

Has flange; oil grooves optional

A-127-5 1.5611 to 1.5630 Inches (39.652 to 39.700 mm)

"X" Shank Modified to "V" Shank

8-13 "X" SHANK MODIFIED TO "V" SHANK 2 A-1499 • STEEL SPACER 1 3 B-6681 • BEARING, NEEDLE 1 Y 5 A-127 • BUSHING, BLADE, REFER TO NOTE 1 1 5A A-127-1 • BUSHING, BLADE, REFER TO NOTE 1 1 5B A-127-4 • BUSHING, BLADE, REFER TO NOTE 1 1 5C A-127-5 • BUSHING, BLADE, REFER TO NOTE 1 1




Rev. 23 Mar/0861-13-33


APS0652


A-1497 1.5590 to 1.5610 Inches (39.599 to 39.649 mm)

A-1497-1 1.5611 to 1.5630 Inches (39.652 to 39.700 mm)

235

"V" Shank Figure 8-14

"V" Shank

8-14 "V" SHANK 2 A-1499 • STEEL SPACER 1 3 B-6681 • BEARING, NEEDLE 1 Y 3A B-7283 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y


5 A-1497 • BUSHING, BLADE, REFER TO NOTE 1 1 Y 5A A-1497-1 • BUSHING, BLADE, REFER TO NOTE 1 1 Y




Rev. 23 Mar/0861-13-33


"V" Shank with "N" Modification Figure 8-15

APS0653

235

"V" Shank with "N" Modification

8-15 "V" SHANK WITH "N" MODIFICATION 2 A-1599 • SPACER 3 B-6681 • BEARING, NEEDLE 3A B-7283 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y





A-1497 1.5590 to 1.5610 Inches (39.599 to 39.649 mm)

A-1497-1 1.5611 to 1.5630 Inches (39.652 to 39.700 mm)




235

APS6129

"MV" Shank with "N" Modification Figure 8-16

"MV" Shank with "N" Modification

8-16 "MV" SHANK WITH "N" MODIFICATION 2 A-1599 • SPACER 1 3 B-6681 • BEARING, NEEDLE 1 Y 3A B-7283 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y

REFER TO "USE OF OVERSIZE INTERNAL BLADE BEARING" IN THE SPECIAL INSPECTIONS AND PROCEDURES CHAPTER OF THIS MANUAL.




A-1497 1.5590 to 1.5610 Inches (39.599 to 39.649 mm)

A-1497-1 1.5611 to 1.5630 Inches (39.652 to 39.700 mm)




4

TI-133001

"P" or "Z" Shank with "N" Modification Figure 8-17

"P" or "Z" Shank with "N" Modification

8-17 "P" OR "Z" SHANK WITH "N" MODIFICATION 4 A-1309 • BUSHING, BLADE 1 Y





8-18 "R" OR "W" SHANK WIITH "N" MODIFICATION 2 A-385 • SPACER 1 3 B-6684 • BEARING, NEEDLE 1 Y 3A C-6252 • BEARING, NEEDLE, OVERSIZE, ALTERNATE 1 Y



"R" or "W" Shank with "N" Modification Figure 8-18

"R" or "W" Shank with "N" Modification

23

5

TI-133002

Incorporate SL232PCR-105839


Page 8-29Rev. 35 Nov/1761-13-33ILLUSTRATED PARTS LIST


- ITEM NOT ILLUSTRATED

Miscellaneous Blade Parts

Miscellaneous Blade Parts Figure 8-19

8-19 MISCELLANEOUS BLADE PARTS -100 A-6741-244 LEAD WOOL, 50 LB. BAG 1 200 79980-HPI-LO HPI OVAL; HARTZELL BLADE DECAL 1 200A 106947 BLADE DECAL, HPI OVAL, ALTERNATE FOR 1 ITEM 200



Rev. 35 Nov/1761-13-33



APPENDIX A - OPTICAL COMPARATOR 61-13-33 Page 9-1Rev. 35 Nov/17

APPENDIX A - OPTICAL COMPARATOR - CONTENTS

1. Optical Comparator General Information ............................................................9-3

2. Approved Optical Comparators ..........................................................................9-4

3. Optical Comparator Overlays .............................................................................9-6

4. Optical Comparator Procedures .........................................................................9-7

A. General..........................................................................................................9-7

B. Alignment of an Overlay on the Screen.........................................................9-7

C. Alignment of the Blade Shank Image on the Overlay....................................9-8

D. Blade Shank Serviceability and Repairability ................................................9-8

LIST OF FIGURES

Sample Optical Comparator (S-T Industries, Inc.) .................... Figure 9-1 ..................9-6

LIST OF TABLES

Optical Comparator Overlays .................................................... Table 9-1 ...................9-6


APPENDIX A - OPTICAL COMPARATORPage 9-2

Rev. 35 Nov/1761-13-33


of 4Dec/20

TEMPORARY REVISION NO. 095To Manual 61-13-33

This Temporary Revision is now considered a part of Hartzell Propeller Inc. Aluminum Blade Overhaul Manual 133C.

NOTE: Record the incorporation of this temporary revision on the RECORD OF TEMPORARY REVISIONS sheet at the front of the manual.

Insert this Temporary Revision in the APPENDIX A - OPTICAL COMPARATOR chapter with this transmittal page facing page 9-2 (Rev. 35 Nov/17).

Reason for issue: To revise Appendix A - Optical Comparator.

NOTE: See page 1 of this Temporary Revision.

© 2020 - Hartzell Propeller Inc. - All rights reserved


TR-095APPENDIX A - OPTICAL COMPARATOR

of 4Dec/20




D. Optical Comparator Procedures

NOTE 1: For all shanks except E-shanks, the outboard limit for inspection of the blade shank is at the transition between the blade shank diameter and the retention radius.

NOTE 2: For E-shanks only, the outboard limit for inspection of the blade shank is at the transition between the blade shank diameter and the 8 degree taper outboard of the retention radius.

NOTE 3: The transition point where the optical comparator inspection area meets the straight surface of the blade, must maintain a smooth blend with no steps or irregularities on all blade shanks.

(1) Alignment of the Overlay on the Optical Comparator Screen(a) Set the magnification on the optical comparator TE28 to match the

optical comparator overlay TE18-( ).(b) Put the optical comparator overlay TE18-( ) on the screen of the optical

comparator TE28 in approximately the final position.(c) Clip the optical comparator overlay TE18-( ) in place so that the overlay

can be shifted for exact alignment.(d) Adjust the stage on the optical comparator TE28 so that an image of the

stage surface appears halfway up on the screen.(e) Adjust the optical comparator overlay TE18-( ) on the screen so that the

horizontal surface of the overlay aligns with the stage surface.(2) Alignment of the Blade Shank Image on the Overlay

(a) Put the blade vertically on the stage of the optical comparator TE28.

NOTE: The pitch change knob on the blade must be permitted to overhang the edge of the stage, if applicable.

(b) Adjust the horizontal position of the blade so that the largest outside diameter of the blade shank aligns with the "SET 1" line indicated on the overlay.

(c) Adjust the vertical position of the blade so that the projected retention radius contacts the radius on the optical comparator overlay TE18-( ).

(d) Serviceability/repairability may now be determined by comparing the projected image with the optical comparator overlay TE18-( )1 The projected image must be between the maximum new

production line on the overlay and the minimum repair line on the overlay.

Page 2 of 4Dec/20



of 4Dec/20

1. Optical Comparator

A. General Information(1) Repair procedures performed on the blade shank retention area can alter

the shape of this highly stressed area. Improper repairs can reduce fatigue strength and could lead to blade failure.

(2) An optical comparator TE28 and optical comparator overlay TE18-( ) are devices used to verify the accuracy of repair work performed on the blade shank retention area.

(3) The optical comparator TE28 projects a magnified profile image of the blade shank onto a screen. The image is compared to the optical comparator overlay TE18-( ) that has the required blade shank shape imprinted on its surface.(a) The optical comparator overlay TE18-( ) is used to inspect the shape of

the retention radius, not the shank dimension. (b) Measure the shank dimensions using a micrometer in accordance with

the applicable chapter of this manual.(4) Following any repair or compression rolling in the blade shank retention area,

use a Hartzell-approved optical comparator TE28 with the applicable optical comparator overlay TE18-( ) to verify that the shape of the blade shank retention area is within the permitted limits.(a) If the blade shank retention area is below the repair line on the

comparator overlay TE18-( ), the blade is unairworthy and must be retired from service in accordance with Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

B. Approved Optical Comparators(1) For specifications and vendor information for Hartzell-approved optical

comparators TE28, refer to Hartzell Tool and Equipment Manual 165A (61-00-65).

C. Optical Comparator Overlay(1) For optical comparator overlays that are available from Hartzell

Propeller Inc., refer to Hartzell Tool and Equipment Manual 165A (61-00-65).





1. Optical Comparator General Information


A. Required repair and rework procedures performed on an aluminum blade shank retention area can alter the shape of this highly stressed area. This alteration, if made without adequate guidance, can result in a reduction of fatigue strength that could lead to blade failure.

B. To make sure of the accuracy in the repair and rework procedures performed on blade shank retention areas, the use of an inspection device known as an "optical comparator" TE28 is required.

C. Anopticalcomparatorisadevicethatprojectsamagnifiedprofileimageoftheobject (blade shank) onto a screen. The image is then compared to an overlay.

(1) An overlay is a clear plastic sheet that has the blade shank shape and lines representing the required shape of the retention radius imprinted on its surface.


(2) Refer to Table 9-1 for the correct revision level of the applicable overlay.

(3) An overlay is used only to inspect the retention radius, not the shank dimension.

(a) When using an overlay, inspect only the radius area shape.

(b) Using a micrometer, measure the shank dimension in accordance with the Blade Shank Overhaul chapter of this manual.

D. An optical comparator inspection is required after any repair, rework, or compression rolling in the blade shank retention area.

(1) Using a 10 power optical comparator with the applicable Hartzell overlay, verify the accuracy and acceptability of the shape of the blade shank retention area.

E. If a blade shank retention area is below the repair line on the comparator overlay, the blade is considered unairworthy and must be retired from service in accordance with the established procedures in the Part Retirement Procedures chapter of Hartzell Standard Practices Manual 202A (61-01-02).

TEXT NO LO

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REFER TO TEMPORARY REVISIO

N



Rev. 35 Nov/1761-13-33

2. Approved Optical Comparators


A. The following companies produce a comparator that is considered acceptable for inspecting a blade shank retention area. Machines manufactured by other companies may also be acceptable.

NOTE: A10xlensmustbespecifiedwhenordering.

Company Comparator Part No.

S-T Industries, Inc. 14-8000-SP - (Superseded by part no. 20-3500-07) 301 Armstrong Blvd. N. 20-3500-07 - (Supersedes part no. 14-8000-SP) St. James, MN 56081, USA 20-3500-08 - (Supersedes part no. 20-3500-07) Phone: 507-375-3211 20-4000-00 - (Mini Comparator) (discontinued) Fax: 507-375-4503 20-4100-00 - (Mini Comparator) (discontinued) Web: www.stindustries.com/ 20-4200-00 - (Mini Comparator) (discontinued)

Micro-Vu Corp. H-14 7909 Conde Lane Windsor, CA 92492, USA Phone: 707-838-6272 Fax: 707-838-3985

Eastman Kodak Company 314 Commercial Imaging Group 343 State Street Rochester, NY 14650, USA Phone: 585-724-4000

J & L Metrology Division PC-14 Vermont Precision Machine Services P.O. Box 10 280 Clinton Street Springfield, VT 05156, USA Phone: 802-885-8291 Fax: 802-885-2404 Web: www.jlmetrology.com/

TEXT NO LO

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N



Company Comparator Part No.

Baty International R14 Baty Precision Measuring Instruments 45 Victoria Road Burgess Hill West Sussex RH15 9LR, U.K. Web: [email protected]

Mitutoyo PH-A14 965 Corporate Blvd Aurora, IL 60502, USA Phone: 888-648-8869 Fax: 630-978-3501 Web: www.mitutoyo.com/

TEXT NO LO

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N



Rev. 35 Nov/1761-13-33

3. Optical Comparator Overlays


A. For optical comparator overlays that are available from Hartzell Propeller Inc., refer to Table 9-1.(a) All of the revision levels listed in Table 1 are permitted.

NOTE: Minor changes were made to the drawings that do not affect the inspection requirements.

Sample Optical Comparator (S-T Industries, Inc.) Figure 9-1

Tool Number Blade Shank Overlay Number Revision Level

TE18 D, Y CST-2923 Revision B or C or D

TE19 X,V,VwithNmodification CST-2924 Revision C or D or E

TE20 Z, W, T, S CST-2925 Revision B or C or D

TE21 M, R, P CST-2926 Revision B or C or D

TE22 E CST-2989 Revision B or C or D

TE373 MVwithNmodification CST-10050 New or A or B

Optical Comparator OverlaysTable 9-1

Front View Side View

AP

S61

16

TEXT NO LO

NGER VALID -


N



4. Optical Comparator Procedures


A. General

The clear overlays are used only to inspect the retention region of the blade as definedbelow.Shankdiametersmustbeinspectedusingamicrometer,asdescribedin Blade Shank Overhaul chapter of this manual.

(1) E shanks

(a) The outboard limit for inspection of the blade shank using the optical comparator overlay is at the transition between the blade shank diameter and the 8 degree taper outboard of the retention radius.

(b) The transition point between the area where the optical comparator inspection ends and the straight surface of the blade must maintain a smooth blend with no steps or irregularities of any kind.

(2) All other shanks

(a) The outboard limit for inspection of the blade shank using the optical comparator overlay is at the transition between the blade shank diameter and the retention radius.

(b) The transition point between the area where the optical comparator inspection ends and the straight surface of the blade must maintain a smooth blend with no steps or irregularities of any kind.

B. Alignment of an Overlay on the Screen

(1) Settheopticalcomparatorforthemagnificationthatcorrectlymatchestheoverlay.

(2) Putanoverlayonthescreeninapproximatelythefinalposition.

(3) Lightly clip the overlay in place lightly so that overlay can be shifted for exact alignment.

(4) Adjust the stage so that an image of the stage surface appears halfway up the screen.

(5) Adjust the overlay on the screen so that the horizontal reference points on the overlay align with the stage surface.

TEXT NO LO

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N



Rev. 35 Nov/1761-13-33

C. Alignment of the Blade Shank Image on the Overlay

(1) Put the blade vertically on the stage.

NOTE: The pitch change knob on "Y" shank blades must be permitted to overhang the edge of the stage.

(2) Adjust the horizontal position of the blade so that the largest blade shank outside diameter aligns with the "SET 1" line indicated on the overlay.

(3) Adjust the vertical position of the blade so that the projected retention radius contacts the overlay radius.

(a) For a "Y" shank blade, align the image of the bearing race seating surface with the line on the overlay that represents this surface.

(b) Because of the large surface area of the shoulder on "D" and "Y" shank blades, an unclear image may appear at the bearing race seating surface. For correct alignment with the overlay easier, put a B-2202 bearing race on the blade shoulder and use the straight line shape of the contact surface of the bearing race to line up the shank overlay.

D. Blade Shank Serviceability and Repairability

(1) Detemine the serviceability and repairability of the blade shank by comparing the projected image with the overlay.

(a) The projected image must fall between the maximum new production line on the overlay and the minimum repair line as indicated on the overlay.

(b) An overlay is used only to inspect the retention radius, not the shank dimension.

1 When using an overlay, inspect only the radius area shape.

2 Using a micrometer, measure the shank dimension in accordance with the Blade Shank Overhaul chapter of this manual.

a Bladeshankretentionradiusinspectionlocationsarespecifiedin the Blade Shank Overhaul chapter of this manual.

TEXT NO LO

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N


Page 10-1Rev. 37 Dec/1861-13-33APPENDIX B - TRAVELERS

APPENDIX B - TRAVELERS - CONTENTS

1. Aluminum Blade Overhaul Travelers ................................................................10-3

A. General........................................................................................................10-3

LIST OF FIGURES

Blade Overhaul Traveler D, E, or Y Shank Blade ........................................................10-5

D, E, or Y Shank Blade Dimensional Traveler .............................................................10-6

Blade Overhaul Traveler M, P, R, T, W, or Z Shank Blade ..........................................10-7

M, P, or R Shank Blade Dimensional Traveler .............................................................10-8

T, W, or Z Shank Blade Dimensional Traveler .............................................................10-9

Blade Overhaul Traveler MV Shank Blade ................................................................10-10

MV Shank Blade Dimensional Traveler .....................................................................10-11

Blade Overhaul Traveler X and V Shank Blade.........................................................10-12

X and V Shank Blade Dimensional Traveler..............................................................10-13

V Shank with N Modification Blade Dimensional Traveler .........................................10-14



1. Aluminum Blade Overhaul Travelers


A. General

(1) Each aluminum blade shank design has overhaul requirements. Each requirement may be unique to a certain type of shank or may be applicable to all shanks. The requirements are in the form of a "traveler" for quick reference.

WARNING: THERE ARE REQUIREMENTS IN THE SPECIAL INSPECTIONS AND PROCEDURES CHAPTER OF THIS MANUAL THAT ARE NOT DOCUMENTED ON THE TRAVELERS IN THIS CHAPTER. THE TRAVELERS IN THIS CHAPTER PROVIDE MINIMUM OVERHAUL REQUIREMENTS THAT ALL BLADES MUST MEET. SOME BLADE MODELS MAY REQUIRE ADDITIONAL OVERHAUL INSPECTIONS OR REWORK.

(2) Travelers list the minimum procedures necessary to complete an aluminum blade overhaul. Procedures listed on the traveler are detailed in various chapters of this manual.

(3) Differing blade conditions, as well as individual shop requirements, may dictate a need for variation in the sequence of blade overhaul. The sequence of the procedures is not mandatory except where indicated and may be rearranged to fit individual blade or shop requirements. All steps of the procedure on the traveler must be completed during overhaul. The travelers in this chapter provide an example of the recommended sequence for aluminum blade overhaul.

(a) Some procedures are designed to be performed sequentially. For example, chemical etching of a component must be completed before penetrant inspection. In this instance, sequence of procedures is mandatory.

(4) It is recommended that a traveler be filled out in its entirety for each blade being overhauled.

(a) The completed traveler should be kept on file for a minimum of seven years.

(b) Any accompanying inspection sheets should be signed by the person performing the task being completed.

(5) This appendix provides samples of travelers for six blade groups. Copies of these travelers are the responsibility of each individual shop.

5Rev. 37 Dec/1861-13-33APPENDIX B - TRAVELERS

Blade Overhaul Traveler D, E, or Y Shank BladeCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # TSO

Prop Serial # TSNManual Revision TR's

All work will be done in accordance with Hartzell Manuals 133C

NOTE: (1) Stripping of anodize/chemical conversion coatings and all rework procedures must be performed before the etch process. (2) The etch process must be performed before penetrant inspection. (3) Strip and etch must be performed as separate processes. (4) Chromic Acid Anodize may not be used on the blade shank or bores.

180

202A, Vol. 1

202A, Vol. 2

202A, Vol. 10

Work Description Reference Technician Crew Chief/QC

Date

1 Remove De-Icer Boot: P/N: 180

2 Remove counterweight and dowel pin 133C

3 Inspect counterweight 133C

4 Remove bearing, and clean shank, remove paint and lead. 133C

5 Preliminary dimensional inspection of shank, bore, and blade airfoil 133C

6 Check edge alignment of blade set (within 0.120 inch) 133C

7 Check knob variance between set (0.4 degrees) 133C

8 Strip anodize/alodine 202A Vol. 2

9 Dimensionally inspect pitch change knob and rework knob 133C

10 Rework & inspect bore and balance hole 133C

11 Eddy current balance hole 133C

12 Final inspect bore and balance hole 133C

13 Inspect and rework blade shank 133C

14 Dimensionally inspect blade airfoil, and shank 133C

15 Comparator inspect shank 133C

16 Grind and polish blade 133C

17 Etch blade, bore, and shank 133C / 202A, Vol. 2

18 Dry Blade: Chose 1 procedure1) 150 degrees for 30 minutes - start time ________ end time ________ 2) Air dry 24 for hours - start time ________ end time ________

202A, Vol. 2

19 Penetrant inspect blade, bore and shank 133C / 202A, Vol. 2

20 Shot peen knob ["Y" Shank] 133C

21 Roll blade shank 133C

22 Shot Peen Blade Airfoil 133C / 202A, Vol. 9

23 Profilometer inspection [Attach print out] 133C

24 Final comparator inspect shank 133C

25 Final dimensional inspect blade and shank 133C

26 Anodize/chemical conversion coat and inspect blade for indications 202A, Vol. 10

27 Chemical conversion coat bore, balance hole, shank and knob 133C / 202A, Vol. 10

28 Paint blade, bore and balance hole [Note: Cure Blade for 12 hours] 133C / 202A, Vol. 1

29 Install de-ice or anti-ice boot and perform electrical check 180

30 Install pitch change knob bushing [Y Shank] 133C

31 Install teflon and counterweight 133C

32 Balance blade and install bearings. 133C

33 Final inspect blade 133C

NOTE: This document was created using all available resources. However, there is a possibility that the information may not be complete. The applicable overhaul manuals and all service document must be referenced to ensure compliance with all required tasks. Failure to perform the required inspections and procedures may result in death, serious bodily injury, and/or substantial property damage.


D, E, or Y Shank Blade Dimensional TravelerCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # Distance to "0" Station

Prop Serial # Blade Length from centerline Min:TSO TSN

Manual Revision TR's

All work will be done in accordance with Hartzell Manuals133C

159

Edge Align: Station 1)______ 2)______ 3)______ 4)______ 5)______ 6)______ 7)______ 8)______ 9)______ 10)______

Shank O.D.: Min:_______ Pre:_______ Final: _______ Lip Thickness: Min:________ Pre:_______ Final:_______

Shank Height: Min:________ Pre:________ Final:________

Bore I.D. Max:________ Pre:_________ Final:________ Critical Area:Max:________ Pre:________ Final:________

Balance Hole: Depth (Stamped + 1/8") Max:________ Pre:________ Final:__________

Balance Hole Dia. Max:___________ Pre: __________ Final:__________

Station Minimum Width

Before O/H Width

After O/H Width

Minimum Thickness

Before O/H Thickness

After O/H Thickness

Face Alignment

Angles

Notes:

Ground By: ____________________ Date: __________ Inspected By: ____________________

Checked By: ____________________ Date: __________ Date: _________



Blade Overhaul Traveler M, P, R, T, W, or Z Shank BladeCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # TSO




180

202A, Vol. 1

202A, Vol. 2

202A, Vol. 10


Date















202A, Vol. 2


16 Shot Peen Blade Airfoil 133C / 202A, Vol. 9













M, P, or R Shank Blade Dimensional TravelerCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # Distance to "0" Station

Prop Serial # Blade Length Min:TSO TSN



159


Shank O.D.: Min:_______ Pre:_______ Final: _______ at 0.750": Min:________ Pre:_______ Final:_______


Bore I.D. Max Outer:________ Pre:_________ Final:________ Max Inner:________ Pre:________ Final:________

Bore Critical Area Max:________ Pre:_________ Final:________ Depth Max:________ Pre:________ Final:________


Balance Hole Diameter Max:___________ Pre: __________ Final:__________


Before O/H Width

After O/H Width

Minimum Thickness


After O/H Thickness

Face Alignment

Angles

Notes:





T, W, or Z Shank Blade Dimensional TravelerCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # Distance to "0" Station




159



at 0.500": Min:________ Pre:_______ Final:_______ at 0.875": Min:________ Pre:_______ Final:_______



Bore Critical Area Max:________ Pre:_________ Final:________ Flange Thick: Pre:________ Final:________




Before O/H Width

After O/H Width

Minimum Thickness


After O/H Thickness

Face Alignment

Angles

Notes:





Blade Overhaul Traveler MV Shank BladeCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # TSO




180

202A, Vol. 1

202A, Vol. 2

202A, Vol. 10


Date















202A, Vol. 2








22 Install bushing and machine to size 133C







MV Shank Blade Dimensional TravelerCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # Distance to "0" Station




159


Shank O.D. at 0.850": Min:_______ Pre:_______ Final: _______ at 2.0": Min:________ Pre:_______ Final:_______

Flange Thick: Min:________ Pre:________ Final:________


Bore Critical Area Max:________ Pre:_________ Final:________ Depth Max:________ Pre:________ Final:________




Before O/H Width

After O/H Width

Minimum Thickness


After O/H Thickness

Face Alignment

Angles

Notes:





Blade Overhaul Traveler X and V Shank BladeCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # TSO




180

202A, Vol. 1

202A, Vol. 2

202A, Vol. 10


Date











11 Eddy current inpect shank 202A, Vol. 2





202A, Vol. 2


17 Shot peen blade shank 133C





22 Install bushing and machine to size 133C







X and V Shank Blade Dimensional TravelerCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # Distance to "0" Station




159



at 0.500": Min:________ Pre:_______ Final:_______ Height Min:________ Pre:_______ Final:_______

Bore I.D. Max Outer:________ Pre:_________ Final:________ Bore Critical Area Max:_______ Pre:_______ Final:_______

Shoulder Height Variance (0.801 ±0.001) Pre:_________ Final:________




Before O/H Width

After O/H Width

Minimum Thickness


After O/H Thickness

Face Alignment

Angles

Notes:





V Shank with N Modification Blade Dimensional TravelerCustomer: Customer PO #:Date: Work Order #:Description Blade Part #:Manufacturer Blade Serial #:Prop Part # Distance to "0" Station




159



at 0.500": Min:________ Pre:_______ Final:_______ Height: Min:________ Pre:________ Final:________


Shoulder Height Variance (0.801 ±0.001) Pre:_________ Final:________




Before O/H Width

After O/H Width

Minimum Thickness


After O/H Thickness

Face Alignment

Angles

Notes:





APPENDIX C - BLADE SPECIFICATIONSPage 11-1

Rev. 35 Nov/1761-13-33

APPENDIX C - BLADE SPECIFICATIONS - CONTENTS

1. General ...........................................................................................................11-13

2. BladeSpecificationTables ..............................................................................11-13

A. UsingtheBladeSpecificationTables ........................................................11-13

B. Ruleof0.030-InchThicknessforBladesinFour,Five, andSixBladePropellers ...........................................................................11-14

3. BladeTipSpecifications..................................................................................11-16

A. UsingtheBladeTipSpecifications ............................................................11-16

LIST OF FIGURES

Blade Model 6660 Blade Tip.....................................................Figure 11-1 ..............11-18








BladeModels7392(D),7392(S)-1,7392-2BladeTip ..............Figure 11-9 ..............11-34

Blade Model 7451 Blade Tip.....................................................Figure 11-10 ............11-36

Blade Model 7453 Blade Tip.....................................................Figure 11-11 .............11-38

BladeModels7468(D),7468D-2,7468D-4BladeTip ..............Figure 11-12 ............11-40

Blade Model 7479-2R Blade Tip ...............................................Figure 11-13 ............11-42




BladeModels7497(D),7497(D)-1,7497(D)-2BladeTip .........Figure 11-17 ............11-50








Rev. 39 Mar/2061-13-33

LISTOFFIGURES,CONTINUEDBlade Model 7673 Blade Tip.....................................................Figure 11-23 ............11-68BladeModel7691(D)BladeTip................................................Figure 11-24 ............11-70Blade Model 7692 Blade Tip.....................................................Figure 11-25 ............11-72BladeModels7693(D),7693(D)-1,7693(D)-2,

7693(D)+2BladeTip ...........................................................Figure 11-26 ............11-74BladeModels7693(D)F,7693F-1,7693(D)F-2,7693(D)F+1,

7693(D)F+2BladeTip .........................................................Figure 11-27 ............11-76BladeModels7694,7694-1,7694-2,7694-4T,

7694-6T Blade Tip ...............................................................Figure 11-28 ............11-78Blade Model 7818 Blade Tip.....................................................Figure 11-29 ............11-80Blade Model 7854 Blade Tip.....................................................Figure 11-30 ............11-82Blade Model 7894 Blade Tip.....................................................Figure 11-30.1 ......11-82.2Blade Model 8052 Blade Tip.....................................................Figure 11-31 ............11-84Blade Model 8068 Blade Tip.....................................................Figure 11-32 ............11-86Blade Model 8074 Blade Tip.....................................................Figure 11-33 ............11-88Blade Model 8218 Blade Tip.....................................................Figure 11-34 ............11-90Blade Model 8292 Blade Tip.....................................................Figure 11-35 ............11-92Blade Model 8295 Blade Tip.....................................................Figure 11-35.1 ......11-92.2Blade Model 8429 Blade Tip.....................................................Figure 11-35.2 ......11-92.4Blade Model 8433 Blade Tip.....................................................Figure 11-36 ............11-94Blade Model 8447 Blade Tip.....................................................Figure 11-37 ..........11-100Blade Model 8459 Blade Tip.....................................................Figure 11-38 ..........11-104BladeModels8459-8Q,8459-8R,8459-9R,

8459-10R Blade Tip ............................................................Figure 11-39 ..........11-106BladeModels8465,8465-2,8465-4,8465-6,

8465-10 Blade Tip ...............................................................Figure 11-40 ..........11-108BladeModels8465-7R,8465-8RBladeTip .............................Figure 11-41 .......... 11-110BladeModels8467,8467SBladeTip ......................................Figure 11-42 .......... 11-112BladeModels8467-7R,8467-8RBladeTip .............................Figure 11-43 .......... 11-114Blade Model 8468 Blade Tip.....................................................Figure 11-44 .......... 11-116Blade Model 8475 Blade Tip.....................................................Figure 11-45 ..........11-124Blade Model 8477 Blade Tip.....................................................Figure 11-46 ..........11-128Blade Model 8483 Blade Tip.....................................................Figure 11-47 ..........11-132Blade Model 8492 Blade Tip.....................................................Figure 11-47.1 ....11-132.2



Rev. 39 Mar/2061-13-33

LISTOFFIGURES,CONTINUEDBlade Model 8501 Blade Tip.....................................................Figure 11-48 ..........11-134BladeModels8833,8833-2BladeTip......................................Figure 11-49 ..........11-136Blade Model 8833-4 Blade Tip .................................................Figure 11-50 ..........11-138BladeModels8847,8847-2BladeTip......................................Figure 11-51 ..........11-140Blade Model 8990 Blade Tip.....................................................Figure 11-52 ..........11-142Blade Model 9083 Blade Tip.....................................................Figure 11-53 ..........11-144Blade Model 9128 Blade Tip.....................................................Figure 11-54 ..........11-146Blade Model 9212 Blade Tip.....................................................Figure 11-55 ..........11-148Blade Model 9216 Blade Tip.....................................................Figure 11-56 ..........11-150Blade Model 9290 Blade Tip.....................................................Figure 11-57 ..........11-152Blade Model 9290CR Blade Tip ...............................................Figure 11-58 ..........11-154Blade Model 9327 Blade Tip.....................................................Figure 11-59 ..........11-156Blade Model 9333 Blade Tip.....................................................Figure 11-60 ..........11-158Blade Model 9349 Blade Tip.....................................................Figure 11-61 ..........11-160Blade Model 9350 Blade Tip.....................................................Figure 11-62 ..........11-162Blade Model 9383 Blade Tip.....................................................Figure 11-63 ..........11-164Blade Model 9390 Blade Tip.....................................................Figure 11-64 ..........11-166Blade Model 9391 Blade Tip.....................................................Figure 11-65 ..........11-168Blade Model 9510(S) Blade Tip ................................................Figure 11-65.1 ....11-168.2BladeModel9511F(A)BladeTip ..............................................Figure 11-66 ..........11-170Blade Model 9512 Blade Tip.....................................................Figure 11-67 ..........11-172Blade Model 9515 Blade Tip.....................................................Figure 11-67.1 ....11-172.2Blade Model 9587 Blade Tip.....................................................Figure 11-68 ..........11-174Blade Model 9612 Blade Tip.....................................................Figure 11-69 ..........11-178Blade Model 9673 Blade Tip.....................................................Figure 11-69.1 ....11-178.2Blade Model 9684 Blade Tip.....................................................Figure 11-70 ..........11-180Blade Model 9690 Blade Tip.....................................................Figure 11-71 ..........11-182BladeModel9782(S)BladeTip ................................................Figure 11-71.1 ....11-182.2Blade Model 9900 Blade Tip.....................................................Figure 11-72 ..........11-184Blade Model 9901 Blade Tip.....................................................Figure 11-72.1 ....11-184.2Blade Model 9990N Blade Tip ..................................................Figure 11-73 ..........11-186Blade Model 10133 Blade Tip...................................................Figure 11-74 ..........11-188Blade Model 10151 Blade Tip...................................................Figure 11-75 ..........11-190



Rev. 39 Mar/2061-13-33

LISTOFFIGURES,CONTINUEDBlade Model 10152 Blade Tip...................................................Figure 11-76 ..........11-192Blade Model 10160 Blade Tip...................................................Figure 11-77 ..........11-194BladeModels10160-6.5R,10160-8.5RBladeTip ...................Figure 11-78 ..........11-196Blade Model 10160-12E Blade Tip ...........................................Figure 11-79 ..........11-198Blade Model 10172 Blade Tip...................................................Figure 11-80 ..........11-200Blade Model 10173A Blade Tip ................................................Figure 11-81 ..........11-202Blade Model 10173D Blade Tip ................................................Figure 11-82 ..........11-206Blade Model 10173F Blade Tip ................................................Figure 11-83 ..........11-208BladeModel(T)10173BladeTip ..............................................Figure 11-84 ..........11-212Blade Model 10176 Blade Tip...................................................Figure 11-85 ..........11-222Blade Model 10178 Blade Tip...................................................Figure 11-86 ..........11-226Blade Model 10282 Blade Tip...................................................Figure 11-87 ..........11-234BladeModel10282(A)BladeTip ..............................................Figure 11-88 ..........11-240Blade Model 10290 Blade Tip...................................................Figure 11-89 ..........11-244Blade Model 10305 Blade Tip...................................................Figure 11-90 ..........11-246Blade Model 10476 Blade Tip...................................................Figure 11-91 ..........11-248Blade Model 10477 Blade Tip...................................................Figure 11-92 ..........11-250Blade Model 10478S Blade Tip ................................................Figure 11-93 ..........11-252Blade Model 10479S Blade Tip ................................................Figure 11-93.1 ....11-252.2Blade Model 10541 Blade Tip...................................................Figure 11-94 ..........11-254Blade Model 10574F Blade Tip ................................................Figure 11-95 ..........11-256Blade Model 10673 Blade Tip...................................................Figure 11-96 ..........11-258Blade Model 10702 Blade Tip...................................................Figure 11-96.1 ....11-258.2Blade Model 10703(S) Blade Tip ..............................................Figure 11-96.2 ....11-258.4Blade Model 10876 Blade Tip...................................................Figure 11-97 ..........11-260BladeModels10890,10890()-2BladeTip ..............................Figure 11-98 ..........11-264Blade Model 10891N Blade Tip ................................................Figure 11-99 ..........11-266Blade Model 10991 Blade Tip...................................................Figure 11-99.1 ....11-266.2Blade Model 11276 Blade Tip ...................................................Figure 11-100 ........11-268Blade Model 11296 Blade Tip ...................................................Figure 11-101 ........11-270Blade Model 11691 Blade Tip ...................................................Figure 11-102 ........11-272Blade Model 11692 Blade Tip ...................................................Figure 11-103 ........11-274BladeModel11693N(S)BladeTip ...........................................Figure 11-104 ........11-276



Rev. 39 Mar/2061-13-33

LIST OF TABLES6660 Blade ..................................................................................................................... 11-196660D Blade ................................................................................................................... 11-196890 Blade ..................................................................................................................... 11-217023 Blade ..................................................................................................................... 11-237063QBlade................................................................................................................... 11-257068-2 Blade .................................................................................................................. 11-277282 Blade ..................................................................................................................... 11-297382 Blade ..................................................................................................................... 11-317391,-3Blade ................................................................................................................ 11-337391D,-3Blade.............................................................................................................. 11-337392,7392(S)-1,7392-2Blade ...................................................................................... 11-357392D Blade ................................................................................................................... 11-357451 Blade ..................................................................................................................... 11-377453 Blade ..................................................................................................................... 11-397468 Blade ..................................................................................................................... 11-417468D,-2,-4Blade ........................................................................................................ 11-417479-2R Blade................................................................................................................ 11-437490 Blade ..................................................................................................................... 11-457495 Blade ..................................................................................................................... 11-477496,-1,-2Blade ........................................................................................................... 11-497497D,7497D-1,7497D-2Blade ................................................................................... 11-517497,7497-1,7497-2Blade ........................................................................................... 11-517498 Blade ..................................................................................................................... 11-537590 Blade ..................................................................................................................... 11-557590D Blade ................................................................................................................... 11-557636D,-2,-4Blade ........................................................................................................ 11-577636N-2Q*Blade .......................................................................................................... 11-577636N,-2,-4Blade ........................................................................................................ 11-587663,-4(T),7663A-(4)Blade.......................................................................................... 11-617663R,7663-2R,7663-2QBlade ................................................................................... 11-617663-5(R),-6(R)Blade ................................................................................................... 11-627663DR Blade ................................................................................................................ 11-627663-4Q,-6QBlade ....................................................................................................... 11-63



Rev. 39 Mar/2061-13-33

LISTOFTABLES,CONTINUED7663D-2,-2R,-2QBlade ................................................................................................ 11-637663D-6QBlade ............................................................................................................. 11-647663D-3,-4Blade .......................................................................................................... 11-647666(A),-2(Q,R),-3(Q,R),-4(Q)Blade .......................................................................... 11-677666C,-3R,-4Blade ...................................................................................................... 11-677673D Blade ................................................................................................................... 11-697691,+2Blade ............................................................................................................... 11-717691D,-1,-3Blade ........................................................................................................ 11-717692 Blade ..................................................................................................................... 11-737693,-1,-2,+2Blade ..................................................................................................... 11-757693DF,-2,+2Blade ...................................................................................................... 11-777693F,-1,-2,+1,+2Blade ............................................................................................. 11-777694,-1,-2,-4TBlade ...................................................................................................... 11-797694D-6T Blade ............................................................................................................. 11-797818 Blade ..................................................................................................................... 11-817854 Blade .................................................................................................................. 11-82.17894,7894-1.5,7894-4Blade ........................................................................................ 11-838052 Blade ..................................................................................................................... 11-858068,-2,+2Blade .......................................................................................................... 11-878068D,-2,+2Blade ....................................................................................................... 11-878074 Blade ..................................................................................................................... 11-898218 Blade ..................................................................................................................... 11-918292*,-2,-4Blade...................................................................................................... 11-92.18295(B)Blade.............................................................................................................. 11-92.38429 Blade ..................................................................................................................... 11-938433(A)(S),-2,2R,-4,4RBlade .................................................................................... 11-968433(A)-6,-7,-10,-12Blade .......................................................................................... 11-968433N,-2,-4Blade ........................................................................................................ 11-978433N-6Q* Blade ........................................................................................................... 11-978433N-6,-7,-10,-12Blade ............................................................................................ 11-988447(A)Blade............................................................................................................... 11-1018447A-8 Blade .............................................................................................................. 11-1018447A-8Q*Blade.......................................................................................................... 11-102



Rev. 39 Mar/2061-13-33

LISTOFTABLES,CONTINUED8447(A)-12ABlade ....................................................................................................... 11-1028459(A),-4,-6Blade .................................................................................................... 11-1058459-18 Blade .............................................................................................................. 11-1058459(A)-8RBlade ......................................................................................................... 11-1078459-11QBlade ............................................................................................................ 11-1078465 Blade ................................................................................................................... 11-1098465-6 Blade ................................................................................................................ 11-1098465-7R,8465-8RBlade ...............................................................................................11-1118467 Blade ....................................................................................................................11-1138467-7R,-8RBlade .......................................................................................................11-1158468(A)(-2)(R)Blade .....................................................................................................11-1198468(A)-3(R),-4(R)Blade .............................................................................................11-1198468(A)-5R,-6R,-6Blade ............................................................................................ 11-1208468(A)-8R,-10RBlade ............................................................................................... 11-1208468D-6R Blade ........................................................................................................... 11-1218468D-8R Blade ........................................................................................................... 11-1218468D-14 Blade............................................................................................................ 11-1228468T-12 Blade ............................................................................................................ 11-1228468-8Q,-10QBlade ................................................................................................... 11-1238475+2Blade ............................................................................................................... 11-1258475-5Q,-6Blade ......................................................................................................... 11-1258475-8,-9Blade ............................................................................................................ 11-1258475F-6 Blade .............................................................................................................. 11-1268475J-4 Blade .............................................................................................................. 11-1268475R,8475(D)-2,-4Blade ......................................................................................... 11-1278475T+2Blade ............................................................................................................. 11-1278477(A),-2,-4Blade .................................................................................................... 11-1298477(A)-6(Q*)Blade ..................................................................................................... 11-1298477(A)-7,8477(A)-8RBlade ....................................................................................... 11-1308477D-5R,8477D-6Blade ........................................................................................... 11-1308483 Blade ................................................................................................................ 11-132.18492 Blade ................................................................................................................... 11-1338501*Blade .................................................................................................................. 11-135



Rev. 39 Mar/2061-13-33

8501-3.5*Blade ............................................................................................................ 11-1358833(H),-2Blade ......................................................................................................... 11-137

8833(H)N,-2Blade....................................................................................................... 11-1378833(H)-4Blade ........................................................................................................... 11-1398833(H)N-4Blade......................................................................................................... 11-1398847 Blade ................................................................................................................... 11-1418990*Blade .................................................................................................................. 11-1439083*Blade .................................................................................................................. 11-1459128(A)NBlade ............................................................................................................ 11-1479212*Blade .................................................................................................................. 11-1499212-2,-4Blade ........................................................................................................... 11-1499216(N)*Blade ............................................................................................................. 11-1519290*Blade .................................................................................................................. 11-1539290CR*Blade ............................................................................................................. 11-1559327*Blade .................................................................................................................. 11-1579333(C,N)-3,-4,-5,-6,-6Q*,-7Q*Blade .................................................................... 11-1599349,+1/2Blade .......................................................................................................... 11-1619349-4.6,-6.5Blade ..................................................................................................... 11-1619350,-4.6Blade ........................................................................................................... 11-1639383*Blade .................................................................................................................. 11-1659390*Blade .................................................................................................................. 11-1679390-1R*Blade ............................................................................................................ 11-1679391*Blade ............................................................................................................... 11-168.19510(S)Blade............................................................................................................... 11-1699511F(A),-2*Blade ..................................................................................................... 11-1719511F(A)-4Blade ......................................................................................................... 11-1719511F(A)-11Blade ........................................................................................................ 11-1719512(A,AE,AF,C,D)-1*Blade ................................................................................ 11-172.19515 Blade ................................................................................................................... 11-1739587A Blade ................................................................................................................. 11-1759587A-10 Blade ............................................................................................................ 11-1759587D-2 Blade.............................................................................................................. 11-176

LISTOFTABLES,CONTINUED



Rev. 39 Mar/2061-13-33

LISTOFTABLES,CONTINUED9587D-7 Blade.............................................................................................................. 11-1769587C-15(S)Blade ....................................................................................................... 11-1779587C-17S Blade ......................................................................................................... 11-1779612*Blade ............................................................................................................... 11-178.1

9673*Blade .................................................................................................................. 11-179

9684,-3RBlade............................................................................................................ 11-181

9684-12 Blade .............................................................................................................. 11-181

9690*Blade ............................................................................................................... 11-182.1

9782(S)Blade............................................................................................................... 11-183

9900*Blade ............................................................................................................... 11-184.1

9901*Blade .................................................................................................................. 11-185

9990N*Blade ............................................................................................................... 11-187

10133D,-3Blade.......................................................................................................... 11-189

10133N,-3Blade.......................................................................................................... 11-189

10133D-11 Blade .......................................................................................................... 11-189

10133N-11 Blade .......................................................................................................... 11-189

10151-8(R)Blade ......................................................................................................... 11-191

10151-10(R)Blade ....................................................................................................... 11-191

10151C-5 Blade............................................................................................................ 11-191

10152-5.5 Blade ........................................................................................................... 11-193

10160-1,-3Blade ......................................................................................................... 11-195

10160-6 Blade .............................................................................................................. 11-195

10160-8.5R Blade......................................................................................................... 11-197

10160-12E Blade .......................................................................................................... 11-199

10172 Blade ................................................................................................................. 11-201

10172C Blade ............................................................................................................... 11-201

10173A(N)Blade .......................................................................................................... 11-203

10173A(N)-6,-6Q*Blade ............................................................................................. 11-203

10173AN-12.5*Blade ................................................................................................... 11-204

10173D(N)-6Q*Blade .................................................................................................. 11-207

10173F(N)-10.5*,-11RBladeand ................................................................................ 11-209



Rev. 35 Nov/1761-13-33

10173F(N)-12.5*onallaircraftexceptBeechA100 ..................................................... 11-209

10173F(N)-12.5*BladeonBeechA100applicationsonly ........................................... 11-209

10173F(N)-21RBlade .................................................................................................. 11-210

10173and+1Blade ..................................................................................................... 11-213

10173(N)and+1Blade ................................................................................................ 11-213

10173(N)-3Blade ......................................................................................................... 11-214

10173-3 Blade .............................................................................................................. 11-214

10173-8(R)Blade ......................................................................................................... 11-215

10173(N)-8(R),-9Blade ............................................................................................... 11-215

10173-11 Blade ............................................................................................................ 11-216

10173(N)-11(R)Blade .................................................................................................. 11-216

10173(N)-13Q*Blade ................................................................................................... 11-217

10173(N)-15Blade ....................................................................................................... 11-217

10173(N)-17RBlade..................................................................................................... 11-218

10173(N)-18Blade ....................................................................................................... 11-218

10173(N)-21RBlade..................................................................................................... 11-219

10173(N)-25RBlade..................................................................................................... 11-219

10173Cand+1Blade ................................................................................................... 11-220

10173C(N)and+1Blade .............................................................................................. 11-220

10173C(N)-8Blade....................................................................................................... 11-221

10176(H)(S)-6,-5Blade ............................................................................................... 11-223

10176(H)(N)(S)-6,-5,-8Blade ..................................................................................... 11-223

10176and+1&-3Blade .............................................................................................. 11-224

10176Cand+1Blade ................................................................................................... 11-224

10176(N)and+1&-3Blade ......................................................................................... 11-225

10178(H)(N)(R)Blade .................................................................................................. 11-227

10178C(H)(N)(R),+1Blade .......................................................................................... 11-227

10178(H)(N)-3RBlade.................................................................................................. 11-228

10178(H)(N)-5and-6Blade ......................................................................................... 11-228

10178(H)(N)-5RBlade.................................................................................................. 11-229

10178(H)(N)-4RBlade.................................................................................................. 11-229




Rev. 35 Nov/1761-13-33

10178(H)(N)-8RBlade.................................................................................................. 11-230

10178(H)(N)-10Q*Blade .............................................................................................. 11-230

10178(H)(N)-11Blade .................................................................................................. 11-231

10178(H)(N)-11RBlade ................................................................................................ 11-231

10178(H)(N)-13RBlade................................................................................................ 11-232

10178(N)-5Q,-7QBlade .............................................................................................. 11-232

10178(N)-13QBlade .................................................................................................... 11-233

10178(N)-15Blade ....................................................................................................... 11-233

10282(N)+4Blade ........................................................................................................ 11-235

10282(N)-4P,-4RBlade ............................................................................................... 11-235

10282(N)RBlade .......................................................................................................... 11-236

10282(N)+6Blade ........................................................................................................ 11-236

10282(N)-6RBlade....................................................................................................... 11-237

10282D(N)Blade .......................................................................................................... 11-237

10282D(N)-4RBlade .................................................................................................... 11-238

10282(N)Blade ............................................................................................................ 11-238

10282NS-5.3R*Blade .................................................................................................. 11-239

10282(N)-9.5RBlade.................................................................................................... 11-239

10282A(N)+2.5*Blade ................................................................................................. 11-241

10282A(N)+4*Blade .................................................................................................... 11-241

10282A(N)+6*Blade .................................................................................................... 11-242

10290N,+2Blade ......................................................................................................... 11-245

10305 Blade ................................................................................................................. 11-247

10476(N)S*Blade......................................................................................................... 11-249

10477(A)(S)*Blade ...................................................................................................... 11-251

10478S Blade ............................................................................................................ 11-252.1

E10479S Blade............................................................................................................. 11-253

10541*Blade ................................................................................................................ 11-255

10574*Blade ................................................................................................................ 11-257

10574A(S)*Blade ......................................................................................................... 11-257

10574F(N)S*Blade ...................................................................................................... 11-257




Rev. 39 Mar/2061-13-33

10673(N),-2Q*Blade ................................................................................................ 11-258.1

10702(N)(S)* ............................................................................................................. 11-258.3

10703(S) Blade............................................................................................................. 11-259

10876(N)*Blade ........................................................................................................... 11-261

10876A(N)(S)*Blade .................................................................................................... 11-261

10876A(N)(S)-2QBlade ............................................................................................... 11-262

10890N*Blade ............................................................................................................. 11-265

10890CN-2 Blade ......................................................................................................... 11-265

10891N*Blade .......................................................................................................... 11-266.1

10991 Blade ................................................................................................................. 11-267

11276N(S)*Blade ......................................................................................................... 11-269

11276(C)N-3*Blade** ................................................................................................... 11-269

11276NSA Blade .......................................................................................................... 11-269

11296N*Blade .............................................................................................................. 11-271

11691N(S)*Blade ......................................................................................................... 11-273

11692N*Blade .............................................................................................................. 11-275

11693N(S)*Blade ......................................................................................................... 11-277




Rev. 28 Sep/1261-13-33

1. General

CAUTION: ALLBLADEMODELSLISTEDINTHISCHAPTERHAVEBEENDETERMINEDTOBEPROPELLERCRITICALPARTS.REFERTOTHEINTRODUCTIONCHAPTEROFTHISMANUALFORINFORMATIONABOUTPROPELLERCRITICALPARTS.

A. ThebladetipspecificationfigureshavebeenmovedfromAppendixDandincorporatedinthisAppendixCofthismanual.

B. Bladestationsareusedduringtherepairoroverhaulprocessofabladetodefineabladespanlocationfordimensionalmeasurement.

C. Referencebladeradiusismeasuredfromthecenterofthepropellerhubtoapredeterminedreferencelocationonthebladeforbladeanglemeasurement.

(1) Ayellowadhesivestripe(BladeAngleReferenceTapeCM160)isusuallylocatedatthereferencebladeradiuslocation.Refertotheapplicableoverhaulmanualforbladeanglereferencetapeapplicationinstructions.

2. BladeSpecificationTables

CAUTION1: ALLBLADEMODELSLISTEDINTHISSECTIONHAVEBEENDETERMINEDTOBEPROPELLERCRITICALPARTS.REFERTOTHEINTRODUCTIONCHAPTEROFTHISMANUALFORINFORMATIONABOUTPROPELLERCRITICALPARTS.

CAUTION2: DONOTCONFUSEBLADESTATIONWITHREFERENCEBLADERADIUS.BLADESTATIONANDREFERENCEBLADERADIUSOFTHESAMENUMBERMAYNOTALWAYSINDICATETHESAMELOCATIONONTHEBLADE.

A. UsingtheBladeSpecificationTables

NOTE: Ifadditionalormissinginformationisneeded,contacttheHartzellPropellerInc.ProductSupportdepartment.

(1) Bladespecificationdataareprovidedformeasurementandinspectionofabareblade.Blademeasurementsaremadeatspecificstationlines.Stationlinesaremeasuredfroma"0"referencestation(refertotheBladeAirfoilOverhaulchapterofthismanual).

(2) Inthefollowingtables,theprefixandsuffixlettersofablademodeldesignationhavebeenomittedwheresuchlettersarenotrelatedtothebladedimensions.

(a) Prefixletterssuchas"F"inaFJC7663("Y"shankbladewithalargepitchchangeknob)or"B"ina10173B(de-icebootinstalled)areunrelatedtospecificationtabledata.



Rev. 28 Sep/1261-13-33

(3) Suffixlettersmayhavedifferentmeaningsfromonebladedesigntoanother.

(a) Forexample,the8468A-2bladeissimilartoa8468-2exceptfordifferentknobanglelocations,whichisunrelatedtothebladespecificationtabledata.Ontheotherhand,a10173Abladeissimilartoa10173bladeexceptforthickness.Thisresultsintwodifferentbladespecificationtablesforthe10173and10173Ablades.

(4) Parenthesesinablademodeldesignationindicatealetterthatmayormaynotbepresentforusewithagivenspecificationtable.

(5) Bladespecificationdataareoccasionallyrevisedorsuperseded.

(a) Olddatamaydifferfromneworreviseddata.Insomeinstances,theolddatamayhavepermittedabladetoreturntoservice,whereasthenewdatawouldrequirereplacementoftheblade.Inthesecases(unlessotherwiserequiredbyservicedocumentation),abladeoverhauledbeforepublicationofthelaterspecificationsremainsairworthy.

(b) Duringanysubsequentoverhaulorotherinspectionbyapropellerrepairstation,theblademustbeinspectedinstrictaccordancewiththespecificationsineffectatthattime.

(6) Bladespecificationtabledatadoesnotapplyto"Q"tippropellerbladesintheareaofthebenttip.RefertotheBladeAirfoilOverhaulchapterofthismanual.

B. Ruleof0.030InchThicknessforBladesinFour,Five,andSixBladePropellers

(1) General

(a) Propellerswithfourormorebladesaresusceptibletoatypeofvibrationcalleda“reactionlessmode”thatisexcitedbyoperatingincrosswindswhileontheground.

1 Thistypeofvibrationcannotbefeltbytheflightcreworpassengerseventhoughtheresultingstressescanbedamagingtothebladesandotherpropellercomponents.

2 Becauseitisnotpracticaltoavoidoperatingincrosswinds,mostpropellerswithfourormorebladeshaverestrictionsprohibitingoperatingintheRPMrangewherethereactionlessmodeislikely tooccur.

(b) Bladeerosion,wearandimpactdamageismorelikelytooccurinthetipregionwherethevelocityishighestandthegroundclearanceisleast.

1 Asthebladewearsandisrepairedinthetipregion,thelossofbladetipweightcausestheRPMatwhichthereactionlessmodeoccurstorise.Inanextremecase,theRPMofthereactionlessmodecouldrisesufficientlytomoveoutsideoftherestrictedoperatingrange.



Rev. 28 Sep/1261-13-33

(c) To avoid the possibility of vibration occuring outside of the restricted RPM range, Hartzell Propeller Inc. has devised a repair scheme to keep the reactionless mode within its original RPM boundaries.

1 As the blade tip is repaired, the “0.030 inch rule” requires that a certain amount of thickness be removed from the inboard sections of the blade to maintain a balance between the weight and stiffness of the blade.

CAUTION: THE RULE OF 0.030 INCH THICKNESS DOES NOT APPLY TO SECTIONS OF THE BLADE FROM THE 8-INCH STATION INBOARD.

(2) The following requirement is only applicable to certain blade models identifi ed in the Blade Specifi cation Tables.

(a) When applying the rule of 0.030-inch (0.76 mm) thickness by removing inboard thickness material, only the maximum face alignment must be maintained at the inboardmost station for face alignment as specifi ed in the blade specifi cation table.

(b) At all other specifi ed face alignment stations, both the minimum and the maximum dimensions must be maintained.

(c) This face alignment exception to the blade specifi cation tables applies to "D", "E", "T" and "M" shank blade types identifi ed in this section.

(3) For All "T" and "M" Shank Blades, Except for (L)M9990N and LT10282NS-5.3R

(a) If any thickness outboard of, but not including, the 27-inch station is within 0.030 inch (0.76 mm) of the minimum allowed thickness*, then all blade stations from the next control station outboard of the 12-inch station, through and including the 27-inch station, must be reduced in thickness to no more than 0.030 inch (0.76 mm) above the minimum permitted thickness.

1 *This thickness check applies only to the airfoil section of the blade and does not apply to the tip of the blade.

(4) For (L)M9990N Blades Only

(a) For (L)M9990N blades, if any thickness from the next control station outboard of the 12-inch station, through and including the 27-inch station, is within 0.030 inch (0.76 mm) of the minimum permitted thickness, then the blade thickness of all stations outboard of the 27-inch station* must be reduced to within 0.030 inch (0.76 mm) of their minimum permitted thickness.

1 *This rule applies only to the airfoil section of the blade and does not apply to the tip of the blade.



Rev. 34 Jan/1761-13-33

(5) For LT10282NS-5.3R Blades Only

(a) For LT10282NS-5.3R blades, refer to the applicable blade specifi cation table in this chapter for the thickness requirements.

1 Because blade model LT10282NS-5.3R has specifi c thickness requirements that are given in the applicable blade specifi cation table, the rule of 0.030 inch thickness does not apply.

(6) For All "D" and "E" Shank Blades

(a) If any thickness outboard of, but not including, the 27-inch station is within 0.030 inch (0.76 mm) of the minimum permitted thickness*, then all blade stations from the 27-inch station inboard up to, but not including, the 8-inch station must be reduced in thickness to no more than 0.030 inch (0.76 mm) above the minimum permitted thickness.

1 *This thickness check applies only to the airfoil section of the blade and does not apply to the tip of the blade.

(7) To reduce thickness at the stations affected by the 0.030 inch rule, the airfoil (thickness) profi le between one inch from the lead edge and one inch from the trail edge must be proportionately reduced the same amount as at the point of maximum thickness.

(a) The material must be equally removed from both the face and camber sides of the blade, particularly for the inboard blade stations.

3. Blade Tip Specifi cations

CAUTION: ALL BLADE MODELS LISTED IN THIS SECTION HAVE BEEN DETERMINED TO BE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS.

A. Using the Blade Tip Specifi cations

(1) Blade tip rework and diameter reduction must be performed within the requirements of the blade tip specifi cations.

(2) The specifi cations shown are for new production blades.

(3) Refer to the Blade Airfoil Overhaul chapter of this manual for requirements about maintaining blade tip radii.

(4) All dimensions are in inches.



Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33

Blade Model 6660(D) Blade Tip Figure 11-1

6660

2.125R

0.21875R

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

33.125

3024

illustrationchecked-OK


APPENDIX C - BLADE SPECIFICATIONSPage11-19

Rev. 27 Sep/1161-13-33

6660 Blade "Y" SHANKRefertoFigure11-1Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.450 1.47512 ---- ---- ---- ---- 6.200 1.07018 21.7 22.3 0.184 0.234 7.100 0.72524 13.8 14.2 -0.016 0.034 7.350 0.53030 9.0 SetUp -0.121 -0.071 7.390 0.53032 ---- ---- -0.228 -0.182 ---- 0.365

6660D Blade "Y" SHANKRefertoFigure11-1Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.450 1.47512 ---- ---- ---- ---- 6.200 1.07018 21.7 22.3 0.184 0.234 7.100 0.72524 13.8 14.2 -0.016 0.034 7.350 0.53030 6.9 SetUp -0.121 -0.071 7.390 0.53032 ---- ---- -0.228 -0.182 ---- 0.365



Rev. 27 Sep/1161-13-33

Blade Model 6890 Blade Tip Figure 11-2

6890

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

0.710

0.500R

0.375R

3033

34




Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.557 1.50512 ---- ---- ---- ---- 5.356 1.18018 26.5 26.9 0.279 0.334 5.608 0.80024 20.0 20.4 0.098 0.153 5.049 0.50530 14.6 SetUp -0.034 0.021 3.779 0.33533 11.8 12.0 -0.154 -0.099 2.885 0.185tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33


33.5

30

27

R. 35

7023

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S




Rev. 27 Sep/1161-13-33

7023 Blade “D” SHANKRefertoFigure11-3Distancefrombladebuttto“0”station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min7* —— —— —— —— 3.344 1.5529* —— —— —— —— 3.344 1.16012* —— —— —— —— 4.450 0.80015* —— —— —— —— 6.280 0.52518 33.3 33.7 .005 .060 7.073 0.41521 31.2 31.6 -.055 0.00 7.177 0.41524 29.8 30.2 -.105 -.050 7.151 0.43027 28.6 28.8 -.145 -.090 7.118 0.46530 28.0 SetUp -.185 -.130 7.074 0.50033.5 — — -.225 -.170 — 0.555*dimensionsareformetalblade,notcuff.



Rev. 27 Sep/1161-13-33


7063


7063Q



Rev. 27 Sep/1161-13-33

7063Q Blade “Y” SHANKRefertoFigure11-4Distancefrombladebuttto“0”station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 —— —— —— —— 3.987 1.44012 —— —— —— —— 4.096 0.96518 15.0 15.6 .175 .255 3.937 0.69524 8.10 8.50 .000 .075 3.666 0.49030 3.90 SetUp -.110 -.035 2.900 0.35034 2.10 2.30 -.200 -.145 2.223 ——**seeparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual



Rev. 27 Sep/1161-13-33


LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

3033

34

7068-22.

75 R

0.37

5 R7068A




Rev. 27 Sep/1161-13-33

7068-2 Blade "Y" SHANKRefertoFigure11-5Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.521 1.68512 ---- ---- ---- ---- 5.564 1.36018 20.7 21.1 0.382 0.437 6.285 0.96024 13.7 14.1 0.209 0.264 6.111 0.72530 8.0 SetUp 0.016 0.071 5.160 0.44532 ---- ---- ---- ---- ---- 0.27533 ---- ---- ---- ---- ---- 0.165tip ---- ---- ---- ---- ---- 0.055



Rev. 27 Sep/1161-13-33


7282a

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S0.085

0.938 R

3336

3534

30




Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- ---- ---- ---- 3.378 1.54512 ---- ---- ---- ---- 5.124 0.87518 18.9 19.3 .222 .287 5.447 0.67524 14.1 14.5 .118 .173 5.047 0.57030 10.4 SetUp -.008 .047 3.505 0.42533 8.80 9.00 -.112 -.057 2.563 0.26734 ---- ---- ---- ---- 2.234 ----35 ---- ---- -.243 -.188 ---- ----Tip --- --- --- --- --- 0.055



Rev. 27 Sep/1161-13-33


3033

36.5

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

7382

1.25

R

7382A




Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.559 1.44512 ---- ---- ---- ---- 5.417 0.79018 26.5 26.9 .122 .187 5.471 0.63024 20.0 20.4 -.050 .005 5.140 0.48530 14.6 SetUp -.238 -.183 4.210 0.32033 11.80 12.00 -.350 -.295 3.150 0.230tip ---- ---- ---- ---- ---- 0.105



Rev. 27 Sep/1161-13-33

Blade Models 7391 Blade Tip Figure 11-8

7391

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

R. 0.25

1.55

0.91

35

34

30

24

36.5

7391( )-3

R. 1.00

R. 1.50

7391( )




Rev. 27 Sep/1161-13-33

7391, -3 Blade "Y" SHANKRefer to Figure 11-8Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.676 1.40212 ---- ---- ---- ---- 6.432 0.90118 40.1 40.5 0.206 0.271 6.860 0.62724 34.5 34.9 0.082 0.137 5.962 0.46530 30.0 Set Up -.049 0.006 4.597 0.31634 27.1 27.3 -.154 -.099 3.318 0.195Tip ---- ---- ---- ---- ---- 0.075

7391D, -3 Blade Y" SHANKRefer to Figure 11-8Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.676 1.40212 ---- ---- ---- ---- 6.432 0.90118 41.4 41.8 0.206 0.271 6.860 0.62724 34.5 34.9 0.082 0.137 5.962 0.46530 30.0 Set Up -.049 0.006 4.597 0.31634 27.7 27.9 -.154 -.099 3.318 0.195Tip ---- ---- ---- ---- ---- 0.075



Rev. 34 Jan/1761-13-33

Blade Models 7392(D), 7392(S)-1, 7392-2 Blade TipFigure 11-9

739224

3034

36.5 7392(D)

7392(S)-17392-2

LEA

DIN

G E

DG

E



Rev. 34 Jan/1761-13-33

7392, 7392(S)-1, 7392-2 Blade “Y” SHANKRefer to Figure 11-9Distance from blade butt to “0” station = 1.000”

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.148 1.32512 ---- ---- ---- ---- 5.076 0.98018 39.0 39.4 0.244 0.289 5.588 0.67024 33.8 34.2 0.076 0.131 5.250 0.46530 30.0 Set Up -.044 0.011 4.201 0.32034 28.0 28.2 -.165 -.110 2.944 0.165tip ---- ---- ---- ---- ---- 0.050

7392D Blade "Y" SHANKRefer to Figure 11-9Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.148 1.32512 ---- ---- ---- ---- 5.076 0.98018 36.8 37.2 0.244 0.289 5.588 0.67024 29.9 30.3 0.076 0.131 5.250 0.46530 24.9 Set Up -.044 0.011 4.201 0.32034 22.4 22.6 -.165 -.110 2.944 0.165tip ---- ---- ---- ---- ---- 0.050



Rev. 27 Sep/1161-13-33


7451

1.0

R

3037

ROTA

TIO

NA

L A

XIS

LEA

DIN

G E

DG

E

35



Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 5.915 1.71612 ---- ---- ---- ---- 6.620 0.98518 42.0 42.6 .265 .315 6.520 0.62624 35.1 35.5 .115 .165 5.900 0.41030 30.0 SetUp .035 .075 5.030 0.27635 27.7 28.1 -.053 -.013 3.570 0.175



Rev. 27 Sep/1161-13-33


7453

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

3037

35

1.00

R

.077

24




Rev. 27 Sep/1161-13-33

7453 Blade "Y" SHANK RefertoFigure11-11 Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.590 1.68012 ---- ---- ---- ---- 5.780 1.01218 30.5 30.9 0.195 0.260 5.990 0.63124 23.5 23.9 0.054 0.109 5.610 0.44330 18.7 SetUp -0.064 -0.009 4.809 0.29635 15.3 15.5 -0.170 -0.115 3.258 0.145



Rev. 27 Sep/1161-13-33

Blade Models 7468(D), 7468D-2, 7468D-4 Blade Tip Figure 11-12

7468

7468(D)

7468D-2

2XR

2.25

ROTATIONALAXIS

LEADINGEDGE

3330

2XR

2.50

7468D-4

3635

37

1.375R




Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.520 1.62512 ---- ---- ---- ---- 5.564 1.08518 21.7 22.1 0.150 0.215 6.289 0.69024 18.1 18.5 -0.035 0.020 6.073 0.51530 14.1 SetUp -0.225 -0.170 5.291 0.35233 12.3 12.5 -0.335 -0.280 4.323 0.235Tip ---- ---- ----- --- ---- 0.055

7468D, -2, -4 Blade "Y" SHANKRefertoFigure11-12Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.520 1.62512 ---- ---- ---- ---- 5.564 1.08518 37.6 38.0 0.150 0.215 6.289 0.69024 33.1 33.5 -0.035 0.020 6.073 0.51530 30.0 SetUp -0.225 -0.170 5.291 0.35233 28.7 28.9 -0.335 -0.280 4.323 0.235Tip ---- ---- ---- ---- ---- 0.055



Rev. 27 Sep/1161-13-33

Blade Model 7479-2R Blade Tip Figure 11-13

7479

0.50

0.09

Lead

ing

Edge

7479-2R33

3036

1.25"R. 1.25"R.




Rev. 27 Sep/1161-13-33

7479-2R Blade "Y" SHANKRefertoFigure11-13Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.580 1.02018 22.9 23.9 .098 .162 6.310 0.64724 17.4 17.9 -.032 .032 6.470 0.47730 13.5 SetUp -.152 -.088 5.764 0.32133 11.7 12.1 -.222 -.158 4.480 0.215

NOTE: RefertotheSpecialInspectionsandProcedureschapterofthismanualforexceptionsto7479-2Rblades.



Rev. 27 Sep/1161-13-33


7490

0.375R

0.750

0.500R

37

LEADINGEDGE

ROTATIONALAXIS

3630




Rev. 27 Sep/1161-13-33

7490 Blade “Y” SHANKRefertoFigure11-14Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.275 1.11512 ---- ---- ---- ---- 5.184 0.80018 30.7 31.1 0.184 0.249 5.628 0.58024 23.2 23.6 0.100 0.155 5.467 0.50530 16.2 SetUp 0.026 0.081 4.661 0.46536 11.0 11.2 -0.188 -0.133 3.174 0.165tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33


7495A


2.18

0

7495( )37

34

24

R 0

.375

30

0.91

1

R 0

.125

LEADINGEDGE

ROTATIONALAXIS



Rev. 27 Sep/1161-13-33





Rev. 27 Sep/1161-13-33


7496

7496( )7496( )-17496( )-2

3736.5

34

24

36R

0.3

75

30

0.91

1

R 0

.125

2.18

0




Rev. 27 Sep/1161-13-33

7496, -1, -2 Blade “Y” SHANKRefertoFigure11-16Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.420 1.84112 ---- ---- ---- ---- 5.566 1.32718 40.3 40.8 0.222 0.287 6.263 0.91324 34.4 34.8 0.001 0.056 5.944 0.64030 30.0 SetUp -0.182 -0.127 4.663 0.48734 27.7 27.9 -0.281 -0.226 2.994 0.316Tip ---- ---- ---- ---- ---- 0.045



Rev. 27 Sep/1161-13-33

Blade Models 7497(D), 7497(D)-1, 7497(D)-2 Blade Tip Figure 11-17

7497-1

2430

3437

2430

3436

36.5

R0.125R0.375

0.911

LEADINGEDGE

ROTATIONALAXIS

2.180

7497(D)7497(D)-17497(D)-2




Rev. 27 Sep/1161-13-33

7497, 7497-1, 7497-2 Blade "Y" SHANKRefertoFigure11-17Distancefrombladebuttto"0"station=1.000"


7497D, 7497D-1, 7497D-2 Blade "Y" SHANKRefertoFigure11-17Distancefrombladebuttto"0"station=1.000"




Rev. 27 Sep/1161-13-33


7498

34

R 0

.375

30

R 0

.750

37




Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ----- ----- 4.363 1.24512 ---- ---- ----- ----- 5.379 0.80018 40.5 40.9 0.131 0.196 5.832 0.50024 34.0 34.4 0.047 0.102 5.602 0.44230 29.1 SetUp -0.040 0.015 4.494 0.34234 25.7 25.9 -0.152 -0.097 3.113 0.175tip ---- ---- ----- ----- ----- 0.035



Rev. 27 Sep/1161-13-33


7590




Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. WidthThickness Min Max Min Max Min Min7.5 ---- ---- ---- ---- 4.127 1.3029.5 ---- ---- ---- ---- 5.652 ----12 ---- ---- ---- ---- 6.121 0.84014 ---- ---- ---- ---- 6.408 ----16 ---- ---- ---- ---- 5.572 ----18 17.9 18.3 0.188 0.253 5.629 0.59024 13.5 13.9 0.103 0.158 5.471 0.51030 9.6 SetUp 0.009 0.064 4.685 0.43036 5.6 5.8 -0.170 -0.115 3.212 0.195tip ---- ---- ---- ---- ---- 0.075

7590D Blade “Y” SHANKRefertoFigure11-19Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. WidthThickness Min Max Min Max Min Min7.5 ---- ---- ---- ---- 4.127 1.3029.5 ---- ---- ---- ---- 5.675 ----12 ---- ---- ---- ---- 5.184 0.84018 17.9 18.3 0.188 0.253 5.629 0.59024 12.1 12.5 0.103 0.158 5.471 0.51030 7.6 SetUp 0.009 0.064 4.685 0.43036 3.6 3.8 -0.170 -0.115 3.212 0.195tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33


7636




Rev. 27 Sep/1161-13-33

7636N -2Q* Blade “MV”, “V” SHANKRefertoFigure11-20Distancefrombladebuttto“0”station=4.150”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min 9 ---- ---- ---- ---- 4.700 2.08012 ---- ---- ---- ---- 5.572 1.09518 41.0 42.0 0.138 0.202 5.702 0.66624 37.0 37.6 -0.072 -0.008 5.312 0.44930 33.2 SetUp -0.192 -0.128 4.450 0.319*Seeparagraph2sectionM.oftheBladeAirfoilOverhaulchapter ofthismanual

7636D, -2, -4 Blade “MV”, “V”, “X” SHANKRefertoFigure11-20Distancefrombladebuttto“0”station=4.150”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9 ---- ---- ---- ---- 4.700 1.98012 ---- ---- ---- ---- 5.572 1.09518 41.0 42.0 0.138 0.202 5.702 0.66624 37.0 37.6 -0.072 -0.008 5.312 0.44930 33.2 SetUp -0.192 -0.128 4.450 0.31936 29.8* 30.2* -0.242*-0.178*NL NL*notapplicableto-4blades



Rev. 27 Sep/1161-13-33

7636N, -2, -4 Blade “MV”, “X”, “V” SHANKRefertoFigure11-20Distancefrombladebuttto“0”station=4.150”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min 9 ---- ---- ---- ---- 4.700 2.08012 ---- ---- ---- ---- 5.572 1.09518 41.0 42.0 0.138 0.202 5.702 0.66624 37.0 37.6 -0.072 -0.008 5.312 0.44930 33.2 SetUp -0.192 -0.128 4.450 0.31936 29.8* 30.2* -0.242*-0.178*NL NL*notapplicableto-4blades



Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33


7663




Rev. 39 Mar/2061-13-33

7663, -4(T), 7663A-(4) Blade “Y” SHANKRefertoFigure11-21Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- --- ---- ---- 3.840 1.963*12 ---- ---- ---- ---- 5.280 1.02618 22.9 23.9 0.138 0.202 5.700 0.66624 18.3 18.7 -0.072 -0.008 5.315 0.44930 15.0 SetUp -0.192 -0.128 4.450 0.31935 ---- ---- ---- ---- 3.020**0.169**36 12.4** 12.8** -0.242**-0.178**NL NL*notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.748thicknessatthe6.5inchstation.**notapplicableto-4blades

7663R, 7663-2R, 7663-2Q Blade “Y” SHANKRefertoFigure11-21Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- --- ---- ---- 3.840 1.963*12 ---- ---- ---- ---- 5.280 1.02618 22.9 23.9 0.138 0.202 5.700 0.66624 18.3 18.7 -0.072 -0.008 5.315 0.44930 15.0 SetUp -0.192 -0.128 4.450 0.31935 ---- ---- ---- ---- 3.020**0.169**36 12.4 12.8 -0.242 -0.178 NL** NL***notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.748thicknessatthe6.5inchstation.**R,-2Ronly;for-2Qseeparagraph2.M.oftheBladeAirfoil chapterofthismanual.



Rev. 27 Sep/1161-13-33

7663DR Blade "Y" SHANKRefertoFigure11-21Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- --- ---- ---- 3.840 1.963*12 ---- ---- ---- ---- 5.280 1.02618 15.8 16.8 0.138 0.202 5.700 0.66624 9.40 9.90 -0.072 -0.008 5.315 0.44930 4.10 SetUp -0.192 -0.128 4.450 0.31935 ---- ---- ---- ---- 3.020 0.16936 -0.10 0.30 -0.242 -0 .178 NL NLTip ---- ---- ---- ---- ---- 0.050*notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.748thicknessatthe6.5inch station.

7663-5(R), -6(R) Blade "Y" SHANKRefertoFigure11-21Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- --- ---- ---- 3.840 1.963*12 ---- ---- ---- ---- 5.280 1.02618 22.9 23.9 0.138 0.202 5.700 0.66624 18.3 18.7 -0.072 -0.008 5.315 0.44930 15.0 SetUp -0.192 -0.128 4.445 0.321Tip ---- ---- ---- ---- ---- 0.050***notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.748thicknessatthe6.5inch station.**ForRtiponly.Otherwiseuse0.075



Rev. 27 Sep/1161-13-33

7663-4Q, -6Q Blade “Y” SHANKRefertoFigure11-21Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- ---- ---- ---- 3.840 1.963*12 ---- ---- ---- ---- 5.280 1.02618 22.9 23.9 0.138 0.202 5.700 0.66624 18.3 18.7 -0.072 -0.008 5.315 0.44930 15.0 SetUp -0.192 -0.128 4.445 0.32133 ---- ---- ---- ---- 3.400 ----***notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.748thicknessatthe6.5inchstation.**seeparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual

7663D-2, -2R, -2Q Blade "Y" SHANKRefertoFigure11-21Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- --- ---- ---- 3.840 1.963*12 ---- ---- ---- ---- 5.280 1.02618 15.8 16.8 0.138 0.202 5.700 0.66624 9.40 9.90 -0.072 -0.008 5.315 0.44930 4.10 SetUp -0.192 -0.128 4.450 0.31935 ---- ---- ---- ---- 3.020**0.169**36 -0.10 0.30 -0.242 -0.178 NL** NL**Tip ---- ---- ---- ---- ---- 0.050****notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.748thicknessatthe6.5inch station.**-2,-2Ronly;for-2Qseeparagraph2.M.oftheBladeAirfoil Overhaulchapterofthismanual

***For-2Ronly.Use0.075for-2



Rev. 28 Sep/1261-13-33

7663D-3, -4(T) Blade "Y" SHANKRefertoFigure11-21Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- --- ---- ---- 3.840 1.963*12 ---- ---- ---- ---- 5.280 1.02618 15.8 16.8 0.138 0.202 5.700 0.66624 9.40 9.90 -0.072 -0.008 5.315 0.44930 4.10 SetUp -0.192 -0.128 4.450 0.31935 0.6 1.0 -0.232 -0.168 3.020 0.169Tip ---- ---- ---- ---- ---- 0.075*notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.748thicknessatthe6.5inch station.

7663D-6Q Blade "Y" SHANKRefertoFigure11-21Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- ---- ---- ---- 3.840 1.963*12 ---- ---- ---- ---- 5.280 1.02618 15.8 16.8 0.138 0.202 5.700 0.66624 9.35 9.85 -0.072 -0.008 5.315 0.44930 4.10 SetUp -0.192 -0.128 4.445 0.32133 ---- ---- ---- ---- 3.400 ----***notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.748thicknessatthe6.5inch station.**seeparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual



Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33


7666

7666C

RO

TATI

ON

AL

AX

IS

7 666A

7666A-2

1 R.

1 R.

.25 R

..25

R.

1.75

R.

1.75

R.

1.92

R.

1.92

R.

.25 R

.

.25 R.

7666A-2R

7666( )-4

7666( )-3R

36

3837

36.5

34

LEA

DIN

G E

DG

E




Rev. 27 Sep/1161-13-33

7666C, -3R, -4 Blade "Y" SHANKRefertoFigure11-22Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.538 1.78712 ---- ---- ---- ---- 5.574 1.30418 22.7 23.7 0.208 0.272 6.300 0.88524 17.1 18.1 -0.032 0.032 6.084 0.51630 13.5 SetUp -0.152 -0.088 5.168 0.35234 11.0* 12.0* -0.202 -0.138 3.656 0.225*notapplicableto-4blades

7666(A), -2(Q,R), -3(Q,R), -4(Q) Blade "Y" SHANKRefertoFigure11-22Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.538 1.78712 ---- ---- ---- ---- 5.574 1.30418 21.0 22.0 0.208 0.272 6.300 0.88524 16.7 17.1 -0.032 0.032 6.084 0.51630 13.5 SetUp -0.152 -0.088 5.168 0.35234 12.0* 12.4* -0.202 -0.138 3.656 0.225***notapplicableto-4blades**seeparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual



Rev. 27 Sep/1161-13-33


7673


LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S



Rev. 27 Sep/1161-13-33

7673D Blade "Y" SHANKRefertoFigure11-23Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- ---- ---- ---- 3.828 1.963*12 ---- ---- ---- ---- 5.266 1.09618 15.8 16.8 0.168 0.232 5.687 0.71524 9.40 9.90 -0.032 0.032 5.298 0.51630 4.10 SetUp -0.172 -0.108 4.423 0.36236 -0.10 0.30 -0.242 -0.178 2.923 0.141*notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.759thicknessatthe 6.5inchstation.



Rev. 27 Sep/1161-13-33

Blade Model 7691(D) Blade Tip Figure 11-24

7691

36

0.750 0.500R.

0.375R.

7691(D)-1

7691(D)-2

7691(D)-3

ROTATIONALAXIS

LEADINGEDGE

37.5

3738

36.5

7691()+2

2.000R.

39


3330



Rev. 27 Sep/1161-13-33

7691, +2 Blade "Y" SHANKRefertoFigure11-24Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.276 1.11512 ---- ---- ---- ---- 5.184 0.80018 17.9 18.3 0.183 0.248 5.629 0.58024 13.5 13.9 0.078 0.133 5.471 0.46030 9.6 SetUp -0.011 0.044 4.685 0.39033 7.5 7.7 -0.076 -0.021 4.002 0.33936 5.6 5.8 -0.162 -0.107 3.248 0.215tip* ---- ---- ---- ---- ---- 0.075tip** ---- ---- ---- ---- ---- 0.045*Appliesto7691only**Appliesto7691+2only

7691D, -1, -3 Blade "Y" SHANKRefertoFigure11-24Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.276 1.11512 ---- ---- ---- ---- 5.184 0.80018 17.9 18.3 0.183 0.248 5.629 0.58024 12.1 12.5 0.078 0.133 5.471 0.46030 7.6 SetUp -0.011 0.044 4.685 0.39033 5.4 5.6 -0.076 -0.021 4.002 0.33936* 3.6 3.8 -0.162 -0.107 3.248 0.215tip ---- ---- ---- ---- ---- 0.035*Appliestofulllengthbladesonly



Rev. 27 Sep/1161-13-33


7692


38

37

36

34

30



Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.525 1.78712 ---- ---- ---- ---- 5.560 1.32018 21.0 22.0 .303 .367 5.405 0.95624 16.6 17.1 .073 .137 4.970 0.72830 13.5 SetUp -.132 -.068 3.945 0.52534 11.0 11.4 -.297 -.233 2.800 0.31736 9.90 10.3 -.402 -.338 NL NL



Rev. 27 Sep/1161-13-33

R1.75

7693(D)

R1.50

R0.75

R0.375

R0.50

7693(D)

3034

37.5

LEADINGEDGE

7693(D)-1

7693(D)-2

3837

39

7693(D)+2

Blade Models 7693(D), 7693(D)-1, 7693(D)-2, 7693(D)+2 Blade Tip Figure 11-26




Rev. 27 Sep/1161-13-33

7693, -1, -2, +2 Blade "Y" SHANKRefertoFigure11-26Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.246 1.39512 ---- ---- ---- ---- 5.419 0.95018 37.7 38.1 0.156 0.221 6.078 0.60024 32.9 33.3 0.047 0.102 5.938 0.45530 30.0 SetUp -0.028 0.027 4.967 0.36534 28.2 28.4 -0.122 -0.067 3.648 0.235tip ---- ---- ---- ---- ---- 0.035



Rev. 27 Sep/1161-13-33

Blade Models 7693(D)F, 7693F-1, 7693(D)F-2, 7693(D)F+1, 7693(D)F+2 Blade Tip Figure 11-27

7693(D)F

R1.75

R1.50

R0.75

R0.375

R0.50

7693(D)F

3034

37.5

LEADINGEDGE

7693F-17693(D)F-2

3837

39

7693(D)F+27693(D)F+1

38.5




Rev. 34 Jan/1761-13-33

7693DF, -2, +2 Blade "Y" SHANKRefer to Figure 11-27Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.246 1.39512 ---- ---- ---- ---- 5.419 0.95018 40.8 41.2 0.181 0.246 6.078 0.60024 34.1 34.5 0.057 0.112 5.938 0.45530 30.0 Set Up -0.027 0.028 4.967 0.36534 27.5 27.7 -0.122 -0.067 3.648 0.235TIP ---- ---- ---- ---- ---- 0.035

NOTE: The use of a Blade Pitch Fixture TE438 is required when checking blade angle.

7693F, -1, -2, +1, +2 Blade "Y" SHANKRefer to Figure 11-27Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.246 1.39512 ---- ---- ---- ---- 5.419 0.95018 37.7 38.1 0.181 0.246 6.078 0.60024 32.9 33.3 0.057 0.112 5.938 0.455 30 30.0 Set Up -0.027 0.028 4.967 0.36534 28.2 28.4 -0.122 -0.067 3.648 0.235TIP ---- ---- ---- ---- ---- 0.035

NOTE: The use of a Blade Pitch Fixture TE438 is required when checking blade angle.



Rev. 27 Sep/1161-13-33

Blade Models 7694, 7694-1, 7694-2, 7694-4T, 7694-6T Blade Tip Figure 11-28

1.00

R

0.50

R

76947694-17694-2

7694-4T

2.75

R

2430

3436

3738

7694-6T

LEA

DIN

G E

DG

E

37.5

RO

TATI

ON

AL

AXI

S

7694

3.5R 0.81

21.

44

35



Rev. 27 Sep/1161-13-33

7694D-6T Blade "Y" SHANKRefertoFigure11-28Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.129 1.34512 ---- ---- ---- ---- 5.076 0.90018 37.1 37.5 0.186 0.251 5.877 0.59024 30.5 30.9 0.083 0.138 5.958 0.47530 24.4 SetUp -0.022 0.033 5.025 0.365Tip ---- ---- ---- ---- ---- 0.075

7694,-1,-2, -4T Blade "Y" SHANKRefertoFigure11-28Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.131 1.34512 ---- ---- ---- ---- 5.079 0.90018 38.5 38.9 0.186 0.251 5.886 0.59024 32.8 33.2 0.083 0.138 5.991 0.47530 28.4 SetUp -0.022 0.033 5.212 0.36534 26.0 26.2 -0.132 -0.077 3.796 0.215Tip ---- ---- -0.257*-0.202*---- 0.035*Appliestofulllengthbladeonly



Rev. 27 Sep/1161-13-33


7818

3.50R

LEADINGEDGE




Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.456 1.88112 ---- ---- ---- ---- 6.421 0.99418 24.5 24.9 0.076 0.141 7.159 0.53424 18.5 18.9 -0.106 -0.051 7.439 0.37330 15.0 SetUp -0.237 -0.182 7.251 0.32133 12.8 13.0 -0.295 -0.240 6.734 0.31136 10.0 10.2 -0.378 -0.323 5.921 0.252Tip ---- ---- ---- ---- ---- 0.105



Rev. 27 Sep/1161-13-33


7854



APPENDIX C - BLADE SPECIFICATIONSPage 11-82.1

Rev. 31 Jul/1461-13-33

7854 Blade "Y" SHANK RefertoFigure11-30Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- ---- ---- ---- 3.933 2.150*8 ---- ---- ---- ---- 5.310 1.45012 ---- ---- ---- ---- 6.560 0.96018 39.9 40.5 .201 .251 6.940 0.65024 34.3 34.7 .084 .134 6.640 0.48030 30.0 SetUp -.034 .017 5.830 0.39336 26.9 27.1 -.080-.040 4.380 0.215*Notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.901thicknessatthe6.5inch station.



Rev.32Nov/1561-13-33

Blade Model 7894 Blade Tip Figure 11-30.1

38.25 ()7894-1.5

()7894

()7894-2

()7894-4

3839

3630

2437

R1.00 R.25



Rev.32Nov/1561-13-33

7894, 7894-1.5, 7894-4 Blade "Y" SHANKRefertoFigure11-30.1Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.248 1.72512 ---- ---- ---- ---- 5.421 1.22518 39.4 39.8 0.274 0.339 6.181 0.80824 33.9 34.3 0.083 0.138 5.950 0.54530 30.0 SetUp -0.021 0.034 5.096 0.44536 27.0 27.2 -0.141 -0.086 3.392 0.280TIP ---- ---- ---- ---- ---- 0.045



Rev. 27 Sep/1161-13-33


8052

3036

40

1.75

0 R

.

1.75

0 R

.

0.87

5

0.41

0

LEA

DIN

G E

DG

E

TRA

ILIN

G E

DG

E


RO

TATI

ON

AL

AXI

S



Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.450 1.62012 ---- ---- ---- ---- 6.362 0.95018 36.9 37.5 .186 .236 6.432 0.64524 32.1 32.5 .076 .126 6.084 0.51030 27.9 SetUp -.007 .043 5.550 0.40836 24.6 24.8 -.165 -.125 4.800 0.29037 ---- ---- ---- ---- 4.620 0.22038 ---- ---- -.195 -.236 4.275 0.160TIP ---- ---- ---- ---- ---- 0.045



Rev. 27 Sep/1161-13-33


8068

3936

40

ROTATIONALAXIS

LEADINGEDGE

R 2

.00

R 1

.50

R 0

.50

8068(D)-2

8068(D)

2.39

R 0

.25

0.90

5

41

8068(D)+2

R 0

.75




Rev. 27 Sep/1161-13-33

8068, -2, +2 Blade "Y" SHANKRefertoFigure11-32Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.521 1.62512 ---- ---- ---- ---- 5.557 1.08018 38.0 38.4 0.189 0.254 6.297 0.69024 33.4 33.8 0.020 0.075 6.088 0.51030 30.0 SetUp -0.145 -0.090 5.408 0.35236 27.3 27.5 -0.315 -0.260 3.874 0.177TIP ---- ---- -0.442*-0.387*---- 0.035*Appliestofulllengthbladeonly

8068D, -2, +2 Blade "Y" SHANKRefertoFigure11-32Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.521 1.62512 ---- ---- ---- ---- 5.557 1.08018 42.1 42.5 0.189 0.254 6.297 0.69024 35.1 35.5 0.020 0.075 6.088 0.51030 30.0 SetUp -0.145 -0.090 5.408 0.35236 26.1 26.3 -0.315 -0.260 3.874 0.177TIP ---- ---- -0.442*-0.387*---- 0.035*Appliestofulllengthbladeonly



Rev. 27 Sep/1161-13-33


8074




Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min7 ---- ---- ---- ---- 3.807 ----8 ---- ---- ---- ---- 4.637 1.61510 ---- ---- ---- ---- 5.781 ----12 ---- ---- ---- ---- 6.290 0.94518 38.1 38.5 .110 .185 7.064 0.64024 32.6 33.0 -.055 .010 7.241 0.50030 27.5 SetUp -.215 -.150 6.555 0.41136 22.7 22.9 -.365 -.300 4.846 0.29038 ---- ---- ---- ---- 4.214 ----Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33


8218

3630

39.625

ROTATIONALAXIS

LEADINGEDGE

1.0

R

1.0

R




Rev. 27 Sep/1161-13-33

8218 Blade "E" SHANKRefertoFigure11-34Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 5.204 1.45512 ---- ---- ---- ---- 6.380 1.11018 29.5 29.9 0.100 0.165 7.091 0.72024 23.7 24.1 -0.195 -0.140 7.603 0.41530 19.2 SetUp -0.410 -0.355 7.861 0.29036 14.3 14.5 -0.600 -0.545 7.622 0.20038 ---- ---- ---- ---- ---- 0.148Tip ---- ---- ---- ---- ---- 0.105*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


8292

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

30

39.375

38.375

36

37.375

R. 0

.630

R. 1

.00

8292( )-4

8292( )-2

8292




Rev. 37 Dec/1861-13-33

8292* , -2, -4 Blade "D" SHANKRefertoFigure11-35Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.586 1.18012 ---- ---- ---- ---- 6.302 0.65018 42.5 42.9 0.056 0.121 6.934 0.43024 35.5 35.9 -0.043 0.012 6.954 0.38530 30.0 SetUp -0.123 -0.068 6.279 0.37536 25.6 25.8 -0.228 -0.173 4.409 0.295Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.Bofthischapter



Rev. 37 Dec/1861-13-33

TP

I-JM

-000

092


LEA

DIN

G E

DG

E

8295(B)-2

RO

TATI

ON

AL

AXI

S

38.3

75

39.3

75

R 1.00

3630

2418

R 0.25



Rev. 39 Mar/2061-13-33

8295(B), -2 Blade "D" SHANKRefertoFigure11-35.1Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.586 1.18012 ---- ---- ---- ---- 6.302 0.65018 21.4 21.8 0.047 0.112 6.934 0.43024 14.4 14.8 -0.054 0.001 6.954 0.38530 8.9 SET UP -0.125 -0.070 6.279 0.37536 4.5 4.7 -0.227 -0.172 4.409 0.295TIP ---- ---- ---- ---- ---- 0.075



Rev. 39 Mar/2061-13-33


R. 1

.50

R. 0

.25

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

TP

I-JM

-000

141

4236

3930

24



Rev. 39 Mar/2061-13-33

8429 Blade "Y"ShankRefertoFigure11-35.2Distancefrombladebuttto“0”station=1.000”

Sta Angle Min

Angle Max

Face Min

Align Max

Width Min

Thickness Min

8 45.4 47.4 0.642 0.717 4.273 1.34512 42.0 43.0 0.307 0.382 5.315 0.82018 37.2 37.6 0.096 0.161 6.243 0.60024 33.0 33.4 -0.059 -0.004 6.244 0.49030 30.0 SET UP -0.221 -0.166 5.401 0.39036 27.6 27.8 -0.401 -0.346 3.976 0.23539 26.6 26.8 -0.485 -0.430 3.165 0.155Tip ---- ---- -0.579 -0.524 ---- 0.055 *Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33

Blade Model 8433 Blade Tip Figure 11-36, page 1 of 2

8433-1



Rev. 27 Sep/1161-13-33

Blade Model 8433 Blade Tip Figure 11-36, Page 2 of 2

8433-2




Rev. 27 Sep/1161-13-33

8433(A)(S), -2, -2R, -4, -4R Blade "MV","X","V" SHANKRefertoFigure11-36Distancefrombladebuttto"0"station=4.150"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9 ---- ---- ---- ---- 4.700 1.98012 ---- ---- ---- ---- 5.720 1.09518 41.0 42.0 .138 .202 6.200 0.62524 37.0 37.6 -.072 -.008 6.000 0.47330 33.2 SetUp -.192 -.128 5.460 0.34136 29.8 30.2 -.242 -.178 4.200 0.234

8433(A)-6, -7, -10, -12 Blade "MV", "X", "V" SHANKRefertoFigure11-36Distancefrombladebuttto"0"station=4.150"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9 ---- ---- ---- ---- 4.700 1.98012 ---- ---- ---- ---- 5.720 1.09518 41.0 42.0 .138 .202 6.200 0.62524 37.0 37.6 -.072 -.008 5.985 0.47130 33.2 SetUp -.192 -.128 5.380 0.33736 29.8 30.2 -.242 -.178 NL NL



Rev. 27 Sep/1161-13-33

8433N, -2, -4 Blade "MV","V" SHANKRefertoFigure11-36Distancefrombladebuttto"0"station=4.150"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9 ---- ---- ---- ---- 4.700 2.08012 ---- ---- ---- ---- 5.720 1.09518 41.0 42.0 .138 .202 6.200 0.62524 37.0 37.6 -.072 -.008 6.000 0.47330 33.2 SetUp -.192 -.128 5.460 0.34136 29.8 30.2 -.242 -.178 4.200 0.234

8433N-6Q* Blade "MV", "V" SHANKRefertoFigure11-36Distancefrombladebuttto"0"station=4.150"


*Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapterofthis manual.



Rev. 27 Sep/1161-13-33

8433N-6, -7, -10, -12 Blade "MV", "V" SHANKRefertoFigure11-36Distancefrombladebuttto"0"station=4.150"




Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33


8447




Rev. 27 Sep/1161-13-33

8447(A) Blade “W” SHANKRefertoFigure11-37Distancefrombladebuttto“0”station=4.312”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.052 2.64912 ---- ---- ---- ---- 5.587 1.30418 31.1 32.1 .158 .222 6.340 0.79924 25.7 26.3 -.032 .032 6.123 0.51830 21.9 SetUp-.152 -.088 5.462 0.35536 18.8 19.2 -.232 -.168 4.203 0.26340 16.9 17.3 -.341 -.279 3.270 0.165

8447A-8 Blade “W” SHANKRefertoFigure11-37Distancefrombladebuttto“0”station=4.312”




Rev. 27 Sep/1161-13-33

8447(A)-12A Blade "W" SHANKRefertoFigure11-37Distancefrombladebuttto"0"station=4.312"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.052 2.64912 ---- ---- ---- ---- 5.587 1.30418 31.1 32.1 .158 .222 6.340 0.79924 25.7 26.3 -.032 .032 6.123 0.51830 21.9 SetUp-.152 -.088 5.462 0.355Tip ---- ---- ---- ---- NL NL

8447A-8Q* Blade "W" SHANKRefertoFigure11-37Distancefrombladebuttto"0"station=4.312"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.052 2.64912 ---- ---- ---- ---- 5.587 1.30418 31.1 32.1 .158 .222 6.340 0.79924 25.7 26.3 -.032 .032 6.123 0.51830 21.9 SetUp -.152 -.088 5.462 0.35536 18.8 19.2 -.232 -.168 4.203 0.170*Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual



Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33


8459

42

30

33

34

36

37

41 8459-2R

8459S8459-2

8459-12R

8459-4

8459A-10

8459-16R

8459-18

LEADINGEDGE

ROTATIONALAXIS

0.5R 0.5R

0.5R

0.5R

1.75R

1.75R

1.5R

1.5R

2.5R2.5R

1.5R

1.5R

2.5R

2.5R

2.75R




Rev. 27 Sep/1161-13-33

8459(A), -4, -6 Blade "Y" SHANKRefertoFigure11-38Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- ---- ---- ---- 3.845 1.936*10 ---- ---- ---- ---- 5.090 1.09016 30.2 31.2 .138 .202 6.007 0.68024 23.2 23.7 -.072 -.008 6.080 0.45830 20.0 SetUp -.192 -.128 5.466 0.32736 17.4 17.8 -.242 -.178 4.200 0.234tip ---- ---- ---- ---- ---- 0.065*Notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.696thicknessatthe6.5inchstation.


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- ---- ---- ---- 3.824 1.936*10 ---- ---- ---- ---- 5.066 1.09016 30.2 31.2 0.138 0.202 5.976 0.68024 23.2 23.7 -0.072 -0.008 6.017 0.45830 20.0 SetUp -0.235 -0.177 5.256 0.235*Notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.696thicknessatthe6.5inchstation.



Rev. 27 Sep/1161-13-33

Blade Models 8459-8Q, 8459-8R, 8459-9R, 8459-10R Blade Tip Figure 11-39

8459-8_9_10

LEADINGEDGE

ROTATIONALAXIS

37

30

33

34

36

388459-9R

8459-8Q

8459-10R

1.5R

1.5R

2.0R

37.5

8459-8R




Rev. 27 Sep/1161-13-33

8459-11Q Blade "Y" SHANKRefertoFigure11-39Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- ---- ---- ---- 3.824 1.936*10 ---- ---- ---- ---- 5.066 1.09016 30.2 31.2 .138 .202 5.976 0.68024 23.2 23.7 -.072 -.008 6.017 0.45830 20.0 SetUp -.192 -.128 5.256 0.32736 17.4 17.8 NL NL 3.698 **tip ---- ---- ---- ---- ---- 0.065*Notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.696thicknessatthe6.5inchstation.**Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual.

8459(A)-8R Blade "Y" SHANKRefertoFigure11-39Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min6 ---- ---- ---- ---- 3.845 1.936*10 ---- ---- ---- ---- 5.090 1.09016 30.2 31.2 .138 .202 6.007 0.68024 23.2 23.7 -.072 -.008 5.950 0.45830 20.0 SetUp -.192 -.128 5.380 0.32736 17.4 17.8 -.242 -.178 NL NLtip ---- ---- ---- ---- ---- 0.065*Notapplicableforbladeswithcounterweightknobs.Forbladeswithcounterweightknobs,checkfor1.696thicknessatthe6.5inchstation.

thereisnodrawingwith8459-11Qbladeonit



Rev. 27 Sep/1161-13-33

Blade Models 8465, 8465-2, 8465-4, 8465-6, 8465-10 Blade Tip Figure 11-40

8465

2.0

R

2.0

R

RO

TATI

ON

AL A

XIS

LEAD

ING

ED

GE

1.75

R

1.75

R

2.25

R

2.25

R

2.5

R

2.5

R2.

0 R 2.0

R

3036

3738

3940

4142

8465

8465-2

8465-4

8465-6

8465-10




Rev. 27 Sep/1161-13-33







Rev. 27 Sep/1161-13-33

8465-01

Blade Models 8465-7R, 8465-8R Blade Tip Figure 11-41

RO

TATI

ON

AL A

XIS

LEAD

ING

ED

GE

1.5

R

1.5

R

1.5

R

3036

3738

38.5

1.5

R

8465-8R

8465-7R




Rev. 27 Sep/1161-13-33

8465-7R, 8465-8R Blade "Y" SHANKRefertoFigure11-41Distancefrombladebuttto"0"station=1.000"




Rev. 27 Sep/1161-13-33

Blade Models 8467, 8467S Blade Tip Figure 11-42

8467_S

8467S

8467

1.5R

LEADINGEDGE

ROTATIONALAXIS

1.5R

3642

3830




Rev. 27 Sep/1161-13-33





Rev. 27 Sep/1161-13-33

Blade Models 8467-7R, 8467-8R Blade Tip Figure 11-43

8467_7R_8R


36

38.5

38

30

8467-7R

8467-8R

LEADINGEDGE

ROTATIONALAXIS

1.06R

1.06R1.06R

1.06R



Rev. 27 Sep/1161-13-33

8467-7R, -8R Blade "Y" SHANKRefertoFigure11-43Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.538 1.78712 ---- ---- ---- ---- 5.580 1.30418 21.0 22.0 .208 .272 6.312 0.88624 16.7 17.1 -.032 .032 6.096 0.51730 13.5 SetUp -.152 -.088 5.393 0.38236 10.9 11.3 -.227 -.163 NL NL



Rev. 27 Sep/1161-13-33


TR-063

PCR-107439

8468-1A

8468,8468A

8468-2,8468A-2

8468-4R,8468A-4R

8468-6S

8468()-8R

8468-10R,8468A-10R

8468T-12

8468T-18



Rev. 27 Sep/1161-13-33


8468-2A



Rev. 27 Sep/1161-13-33


8468-3A



Rev. 27 Sep/1161-13-33

8468(A)(-2)(R) Blade "Y" SHANKRefer to Figure 11-44Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.570 1.08418 21.0 22.0 .098 .162 6.305 0.69624 16.7 17.2 -.032 .032 6.105 0.51830 13.5 Set Up -.152 -.088 5.460 0.35536 10.9 11.3 -.227 -.163 4.200 0.263

8468(A)-3(R), -4(R) Blade "Y" SHANKRefer to Figure 11-44Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.620 12 ---- ---- ---- ---- 5.570 1.084 18 21.0 22.0 .098 .162 6.305 0.696 24 16.7 17.2 -.032 .032 6.105 0.518 30 13.5 Set Up -.152 -.088 5.460 0.355 36 10.9 11.3 -.227 -.163 4.200 0.199



Rev. 34 Jan/1761-13-33

8468(A)-5R, -6R, -6 Blade "Y" SHANKRefer to Figure 11-44Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.620 12 ---- ---- ---- ---- 5.570 1.084 18 21.0 22.0 .098 .162 6.305 0.696 24 16.7 17.2 -.032 .032 6.080 0.517 30 13.5 Set Up -.152 -.088 5.370 0.352 36 10.9 11.3 -.227 -.163 4.000* 0.179* *for -5R and -6 blade min. width 4.100", min. thickness 0.264"

8468(A)-8R, -10R Blade "Y" SHANK Refer to Figure 11-44Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.620 12 ---- ---- ---- ---- 5.570 1.084 18 21.0 22.0 .098 .162 6.305 0.696 24 16.7 17.2 -.032 .032 6.080 0.517 30 13.5 Set Up -.152 -.088 5.370 0.352 33 12.0 12.4 -.192 -.128 4.710* 0.244*36 10.9 11.3 -.227 -.163 3.300** 0.145***For -10R width 4.430", thickness 0.225" **For -10R width and thickness NL



Rev. 27 Sep/1161-13-33

8468D-6R Blade "Y" SHANKRefertoFigure11-44Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.570 1.08418 20.9 21.3 0.098 0.162 6.305 0.69624 13.8 14.2 -0.032 0.032 6.080 0.51730 9.5 SetUp -0.152 -0.088 5.370 0.35236 4.3 4.7 -0.227 -0.163 4.000 0.179

8468D-8R Blade "Y" SHANKRefertoFigure11-44Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.570 1.08418 20.9 21.3 0.098 0.162 6.305 0.69624 13.8 14.2 -0.032 0.032 6.080 0.51730 9.5 SetUp -0.152 -0.088 5.370 0.35236 4.3 4.7 -0.227 -0.163 3.300 0.145Tip --- --- --- --- --- 0.065



Rev. 27 Sep/1161-13-33

8468D-14 Blade "Y" SHANK RefertoFigure11-44Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.570 1.08418 20.9 21.3 .098 .162 6.305 0.69624 13.8 14.2 -.032 .032 6.080 0.51730 9.5 SetUp -.152 -.088 5.370 0.352

8468T-12 Blade "Y" SHANK RefertoFigure11-44Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.570 1.08418 22.9 23.9 .070 .160 6.305 0.69624 15.05 15.55 -.060 .030 6.080 0.51730 9.4 SetUp -.180 -.090 5.370 0.35234 5.7 6.1 -.220 -.130 3.48 NL



Rev. 27 Sep/1161-13-33

8468-8Q, -10Q Blade "Y" SHANK RefertoFigure11-44Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.570 1.08418 21.0 22.0 .076 .160 6.305 0.69624 16.65 17.15 -.052 .030 6.080 0.51730 13.5 SetUp -.173 -.090 5.370 0.35236 10.9 11.3 -.220 -.165 3.650* 0.170***3.100for-10Q;**0.145for10Q***Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapterof thismanual



Rev. 36 Jun/1861-13-33


TPI-8

475


37.5 8475-9




Rev. 37 Dec/1861-13-33

8475+2 Blade "Y" SHANKRefertoFigure11-45Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.580 1.08518 22.9 23.9 .098 .162 6.310 0.69624 17.4 17.9 -.032 .032 6.510 0.51830 13.5 SetUp -.152 -.088 6.300 0.38236 10.9 11.3 -.227 -.163 5.250 0.28640 9.6 10.0 -.302 -.238 3.945 0.188

8475-5Q*, -6 Blade "Y" SHANKRefertoFigure11-45Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.580 1.08518 22.9 23.9 .098 .162 6.310 0.69624 17.4 17.9 -.032 .032 6.510 0.51830 13.5 SetUp -.152 -.088 6.200 0.37736 10.9 11.3 -.227 -.163 5.100 0.276*Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapter ofthismanual.

8475-8, -9, -10 Blade "Y" SHANKRefertoFigure11-45Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.580 1.08518 22.9 23.9 .098 .162 6.310 0.69624 17.4 17.9 -.032 .032 6.510 0.51830 13.5 SetUp -.152 -.088 6.200 0.37734 11.6 12.0 -.197 -.133 5.510 0.260TIP ---- ---- ---- ---- ---- 0.085



Rev. 27 Sep/1161-13-33

8475J-4 Blade "Y" SHANKRefertoFigure11-45Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.580 1.08518 27.2 28.2 .077 .162 6.310 0.69624 19.15 19.65 -.052 .032 6.510 0.51830 13.5 SetUp -.173 -.088 6.300 0.38236 8.30 8.7 -.253 -.163 5.250 0.28638 ---- ---- ---- ---- 4.402 ----

8475F-6 Blade "Y" SHANKRefertoFigure11-45Distancefrombladebuttto"0"station=1.000"




Rev. 34 Jan/1761-13-33

8475R Blade "Y" SHANK8475(D)-2, -4 BladeRefer to Figure 11-45Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.580 1.08518 22.9 23.9 0.098 0.162 6.310 0.69624 17.4 17.9 -0.032 0.032 6.510 0.51830 13.5 Set Up -0.152 -0.088 6.300 0.38236 10.9 11.3 -0.227 -0.163 5.250 0.286

8475T+2 Blade "Y" SHANKRefer to Figure 11-45Distance from blade butt to "0" station = 1.000"

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.535 1.62012 ---- ---- ---- ---- 5.580 1.08518 23.7 24.7 0.098 0.162 6.310 0.69624 18.25 18.75 -0.032 0.032 6.510 0.51830 14.9 Set Up -0.152 -0.088 6.300 0.38236 11.7 12.1 -0.227 -0.163 5.250 0.28640 10.2 10.6 -0.302 -0.238 3.945 0.188



Rev. 27 Sep/1161-13-33

Blade Model 8477 Blade TipFigure 11-46

8477



Rev. 27 Sep/1161-13-33

8477(A), -2, -4 Blade "Y" SHANKRefertoFigure11-46Distancefrombladebuttto"0"station=1.000"


8477(A)-6(Q*) Blade "Y" SHANKRefertoFigure11-46Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.538 1.78712 ---- ---- ---- ---- 5.580 1.30418 21.0 22.0 0.218 0.282 6.312 0.92024 16.7 17.2 -0.032 0.032 6.110 0.57730 13.5 SetUp -0.152 -0.088 5.460 0.41536 11.0 11.2 -0.225 -0.170 3.966 0.304Tip** ---- ---- ---- ---- ---- 0.105*Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual.**Doesnotapplyto-6Q.



Rev. 27 Sep/1161-13-33

8477(A)-7, 8477(A)-8R Blade "Y" SHANKRefertoFigure11-46Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.538 1.78712 ---- ---- ---- ---- 5.580 1.30418 21.0 22.0 0.218 0.282 6.312 0.92024 16.7 17.2 -0.032 0.032 6.110 0.57730 13.5 SetUp -0.152 -0.088 5.460 0.41536 10.9 11.3 -0.222 -0.158 NL NL

8477D-5R, 8477D-6 Blade Y" SHANKRefertoFigure11-46Distancefrombladebuttto"0"station=1.000"




Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33


8483

ROTATIONALAXIS

LEADINGEDGE

0.14

0

1.00

R



APPENDIX C - BLADE SPECIFICATIONSPage 11-132.1Rev. 31 Jul/1461-13-33

8483 Blade "Y"SHANKRefertoFigure11-47Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.547 1.56512 ---- ---- ---- ---- 5.723 1.04518 22.0 22.4 0.240 0.305 6.688 0.75524 18.3 18.7 0.065 0.120 6.876 0.55030 15.0 SetUp -0.075 -0.020 6.596 0.41036 11.8 12.0 -0.215 -0.160 5.543 0.32039 10.3 10.5 -0.325 -0.270 4.275 0.200Tip ---- ---- ---- ---- ---- 0.045




R1.00 R1.0040

.375

3630

24

TPI-8492



Rev. 31 Jul/1461-13-33

8492* Blade "E" SHANKRefertoFigure11-47.1Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 5.243 1.51512 ---- ---- ---- ---- 7.038 1.10518 31.7 32.1 0.112 0.177 7.853 0.72024 25.5 25.9 -0.104 -0.049 8.173 0.45030 20.5 SetUp -0.237 -0.182 8.055 0.35536 16.2 16.4 -0.352 -0.297 7.250 0.305Tip ---- ---- ---- ---- ---- 0.112*Refertoparagraph2.B.ofthischapter.



Rev. 27 Sep/1161-13-33


8501

3.75R

2XR3.50LE

ADINGEDGE

E8501-3.5

41.125

39.375

3936

30

ROTATIONALAXIS



Rev. 31 Jul/1461-13-33

8501* Blade "E" SHANKRefertoFigure11-48Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.576 1.31512 ---- ---- ---- ---- 6.351 0.74518 42.3 42.7 0.072 0.137 7.271 0.55024 35.8 36.2 -0.099 -0.044 7.710 0.40330 30.3 SetUp -0.210 -0.155 7.971 0.39536 25.1 25.3 -0.348 -0.293 7.878 0.32339 ---- ---- -0.447 -0.392 ---- 0.223TIP ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter

8501-3.5* Blade "E" SHANKRefertoFigure11-48Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.576 1.31512 ---- ---- ---- ---- 6.351 0.74518 42.3 42.7 0.072 0.137 7.271 0.55024 35.8 36.2 -0.099 -0.044 7.710 0.40330 30.3 SetUp -0.210 -0.155 7.971 0.39536 25.1 25.3 -0.348 -0.293 7.878 0.323TIP ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33

Blade Models 8833, 8833-2 Blade Tip Figure 11-49

CPS0566

32

LEADINGEDGE

ROTATIONALAXIS

0.5R

0.5R

3840

4142

4344

0.5R

0.5R

8833-2

8833

1.5R

0.1088

33-S

1.5R



Rev. 27 Sep/1161-13-33

8833(H), -2 Blade "MV","X","V" SHANKRefertoFigure11-49Distancefrombladebuttto"0"station=4.250"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9 ---- ---- ---- ---- 4.570 1.98012 ---- ---- ---- ---- 5.717 1.09518 31.1 32.1 0.103 0.167 6.310 0.69226 24.0 24.6 -0.082 -0.018 6.070 0.47232 20.0 SetUp -0.164 -0.098 5.450 0.34038 16.8 17.2 -0.242 -0.178 4.190 0.233

8833(H)N, -2 Blade "MV","V" SHANK RefertoFigure11-49Distancefrombladebuttto"0"station=4.250"


PCR-106979



Rev. 27 Sep/1161-13-33

Blade Model 8833-4 Blade Tip Figure 11-50

CPS0566-1

32

LEADINGEDGE

ROTATIONALAXIS

3840

4142

1.5R 1.5R

8833-4



Rev. 27 Sep/1161-13-33

8833(H)N-4 Blade "MV","V" SHANK RefertoFigure11-50Distancefrombladebuttto"0"station=4.250"


8833(H)-4 Blade "MV","X","V" SHANKRefertoFigure11-50Distancefrombladebuttto"0"station=4.250"




Rev. 27 Sep/1161-13-33

Blade Models 8847, 8847-2 Blade Tip Figure 11-51

CPS0572

3238

4041

42

LEADINGEDGE

ROTATIONALAXIS

1.5R

1.5R

4344

8847

8847-2

0.75R

0.75R



Rev. 27 Sep/1161-13-33

8847 Blade "Z","W" SHANKRefertoFigure11-51Distancefrombladebuttto"0"station=4.312"




Rev. 27 Sep/1161-13-33


8990

3.000R

0.025R

0.305R

3.000R

4036

3043

.125




Rev. 27 Sep/1161-13-33

8990* Blade "D" SHANKRefertoFigure11-52Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.439 1.41512 ---- ---- ---- ---- 5.635 0.97518 32.0 32.4 0.167 0.232 6.580 0.55024 24.3 24.7 0.030 0.085 6.741 0.36030 18.4 SetUp -0.032 0.023 6.571 0.34536 13.3 13.5 -0.089 -0.034 6.282 0.33540 10.5 10.7 -0.164 -0.109 6.022 0.255Tip ---- ---- ---- ---- ---- 0.055*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


9083




Rev. 27 Sep/1161-13-33

9083* Blade "D", "E" SHANKRefertoFigure11-53Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.576 1.72512 ---- ---- ---- ---- 6.351 1.08518 42.0 42.4 0.100 0.165 7.276 0.60024 35.5 35.9 -0.075 -0.020 7.718 0.43330 30.0 SetUp -0.205 -0.150 7.986 0.39536 24.8 25.0 -0.315 -0.260 7.906 0.37539 22.7 22.9 -0.375 -0.320 7.586 0.36242 ---- ---- -0.455 -0.400 5.575 0.312tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


9128

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

R. 0.50

45.4

42

36




Rev. 27 Sep/1161-13-33

9128(A)N* Blade "M" SHANK RefertoFigure11-54Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9 ---- ---- ---- ---- 4.510 2.49112 ---- ---- ---- ---- 5.723 1.43418 44.9 45.5 0.240 0.305 6.961 0.84924 37.0 37.4 -0.045 0.010 7.540 0.57630 31.2 SetUp -0.270 -0.215 7.852 0.43836 26.0 26.2 -0.458 -0.403 7.429 0.37942 21.1 21.3 -0.661 -0.606 5.519 0.286Tip ---- ---- ---- ---- ---- 0.136*RefertoParagraph2.B.ofthischapter

PCR-107014



Rev. 27 Sep/1161-13-33


W10321

1.5 R.

1.5 R

.1.5

R.

1.5 R

.

1.5 R

.

1.5 R

.

1.5

R.

LEA

DIN

G E

DG

E

TRA

ILIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

3036

41.2

543

.75

44.7

545

.75

9212-9

9212-4

9212-2

1.5

R.




Rev. 27 Sep/1161-13-33

9212* Blade "T" SHANK RefertoFigure11-55Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.24 2.77110 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.49 1.19218 40.7 41.3 0.102 0.167 6.80 0.62524 33.6 34.0 -0.025 0.040 7.33 0.43030 28.0 SetUp -0.154 -0.089 7.25 0.35036 23.2 23.6 -0.231 -0.175 6.69 0.33042 20.2 20.6 -0.345 -0.290 5.89 0.275Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter

9212-2, -4 Blade "T" SHANK RefertoFigure11-55Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.24 2.77110 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.49 1.19218 40.7 41.3 0.102 0.167 6.80 0.62524 33.6 34.0 -0.025 0.040 7.33 0.43030 28.0 SetUp -0.154 -0.089 7.25 0.35036 23.2 23.6 -0.231 -0.175 6.69 0.33042 20.2 20.6 -0.345 -0.290 5.89 0.275Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33


9216

3036

42

RO

TATI

ON

AL A

XIS

LEAD

ING

ED

GE

45.7

5

1.50

R

1.50

R

9216ThisbladehasnoitemlistinginAxalant,onlymodel!!




Rev. 27 Sep/1161-13-33

9216(N)* Blade “T” SHANK RefertoFigure11-56Distancefrombladebuttto“0”station=4.512”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.865 2.77012 ---- ---- ---- ---- 5.49 1.43218 42.6 43.2 0.318 0.383 6.80 0.93524 35.4 35.8 0.071 0.136 7.33 0.62230 30.0 SetUp -0.097 -0.032 7.25 0.44436 25.8 26.2 -0.229 -0.174 6.69 0.34042 22.1 22.5 -0.345 -0.290 5.89 0.255Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter

9216ThisbladehasnoitemlistinginAxalant,onlymodel!!



Rev. 27 Sep/1161-13-33


9290

44.625

36

2.401.

5 R

30

400.

22 1.5

R

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S




Rev. 27 Sep/1161-13-33

9290* Blade “D” SHANK RefertoFigure11-57Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.510 1.72512 ---- ---- ---- ---- 5.827 1.08518 39.1 39.5 0.140 0.205 6.948 0.60024 31.5 31.9 -0.040 0.015 7.278 0.40330 26.0 SetUp-0.160 -0.105 7.100 0.34536 21.4 21.6 -0.230 -0.175 6.433 0.33542 17.2 17.4 -0.326 -0.271 5.558 0.295Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33

Blade Model 9290CR Blade Tip Figure 11-58

2.75

R.

Lead

ing

Edge

Rot

atio

nal A

xis

1.42

9290CR

42

36

44.625

30




Rev. 27 Sep/1161-13-33

9290CR* Blade “D” SHANK RefertoFigure11-58Distancefrombladebuttto“0”station=1.000”




Rev. 27 Sep/1161-13-33


CPS0602

Lead

ing

Edge

Rot

atio

nal A

xis

3.27 R

42

36

45.125

30

.31




Rev. 27 Sep/1161-13-33

9327* Blade “D” SHANK RefertoFigure11-59Distancefrombladebuttto“0”station=1.000”




Rev. 27 Sep/1161-13-33


9333


93339333-R

9333-3

9333-4

9333-5

9333-5R

9333-3R

9333-6

46.5

4645

4444

.5

43.5

.5 R.

2.85 .5

R.

.5 R. 2 R

.

2 R.

.5 R..5

R..5

R.

.5 R.

.5 R. 2

R.

.5 R.

.5 R.

40

34

RO

TATI

ON

AL

AXI

S

LEA

DIN

G E

DG

E



Rev. 27 Sep/1161-13-33

9333(C,N) -3, -4, -5, -6, “MV”,”X”,”V” SHANK -6Q*, -7Q* BladeRefertoFigure11-60Distancefrombladebuttto“0”station=4.150”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9.5 ---- ---- ---- ---- 4.704 1.98013 ---- ---- ---- ---- 5.720 1.09520 41.0 42.0 -.122 -.058 6.307 0.69328 36.5 37.1 -.472 -.408 6.070 0.47234 33.2 SetUp -.682 -.618 5.450 0.37640 29.8 30.2 -.832 -.768 4.200 0.286*Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual.



Rev. 27 Sep/1161-13-33


9349A

NOTE:WHEN9349-4.6ISUSEDINA2BLADEASSEMBLYITBECOMES 88INCHDIAMETER.

9349-4.6

9349-6.5


47

RO

TATI

ON

AL

AXI

S

LEA

DIN

G E

DG

E

46.5

9349+1/2

43.2

5

4644

.243

0.5 R0.5 R

0.5 R 0.5 R

1.5 R1.5 R

0.5 R0.5 R

9349



Rev. 27 Sep/1161-13-33

9349, +1/2 Blade "Z", "W" SHANKRefertoFigure11-61Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.045 2.87013 ---- ---- ---- ---- 5.720 1.09520 41.0 42.0 -0.122 -0.058 6.310 0.69328 36.5 37.1 -0.472 -0.408 6.097 0.47234 33.2 SetUp -0.682 -0.618 5.450 0.37640 29.8 30.2 -0.832 -0.768 4.200 0.28643 28.7 29.1 -0.932 -0.868 3.273 0.228Tip ---- ---- ---- ---- ---- 0.075

9349-4.6, -6.5 Blade "W" SHANKRefertoFigure11-61Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.045 2.87013 ---- ---- ---- ---- 5.720 1.09520 41.0 42.0 -0.122 -0.058 6.310 0.69328 36.5 37.1 -0.472 -0.408 6.070 0.47134 33.2 SetUp -0.682 -0.618 5.395 0.37340 29.8 30.2 -0.832 -0.768 3.960 0.276Tip ---- ---- ---- ---- ---- 0.080



Rev. 37 Dec/1861-13-33


CPS0610

NOTE:WHEN9350IS USED IN A 2 BLADEASSEMBLYITBECOMES 88INCHDIAMETER.

9350

9350-3

9350()-4.69350-5

9350-9

0.5

0.5

0.5

0.5

0.5

0.5

0.5

0.5

0.5

0.5



Rev. 37 Dec/1861-13-33

9350-4.6 Blade "Z","W" SHANKRefertoFigure11-62Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.045 2.87013 ---- ---- ---- ---- 5.720 1.09520 41.0 42.0 0.108 0.172 6.310 0.69328 36.5 37.1 -0.122 -0.058 6.097 0.47234 33.2 SetUp -0.222 -0.158 5.450 0.37640 29.8 30.2 -0.262 -0.198 4.200 0.28643 28.6 30.0 -0.218 -0.282 ---- ----Tip ---- ---- ---- ---- ---- 0.080

9350-9 Blade "Z","W" SHANKRefertoFigure11-62Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.045 2.87013 ---- ---- ---- ---- 5.720 1.09520 41.0 42.0 0.108 0.172 6.310 0.69328 36.5 37.1 -0.122 -0.058 6.097 0.47234 33.2 SetUp -0.222 -0.158 5.450 0.37640 29.8 30.2 -0.262 -0.198 4.200 0.286Tip ---- ---- ---- ---- ---- 0.080



Rev. 27 Sep/1161-13-33


CPS0603

TRA

ILIN

G E

DG

E

3.95 R.

42

36

45.125

30

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

.24



Rev. 27 Sep/1161-13-33

9383* Blade "D" SHANKRefertoFigure11-63Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.720 1.62012 ---- ---- ---- ---- 6.025 1.34518 42.5 43.1 0.260 0.320 7.185 0.86524 34.5 34.9 -0.010 0.050 7.730 0.46530 28.9 SetUp -0.150 -0.090 8.000 0.37036 24.5 24.7 -0.260 -0.200 7.930 0.35042 20.9 21.1 -0.370 -0.310 7.350 0.330Tip ---- ---- ---- ---- ---- 0.045*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


9390


9390-1R

9390



Rev. 27 Sep/1161-13-33

9390* Blade "E" SHANKRefertoFigure11-64Distancefrombladebuttto"0"station=1.000"


9390-1R* Blade "D" SHANKRefertoFigure11-64Distancefrombladebuttto"0"station=1.000"




Rev. 27 Sep/1161-13-33


9391

3036

42

RO

TATI

ON

AL

AX

IS

LEA

DIN

G E

DG

E

45.1

25

3.00

R. T

YP.




9391* Blade “D” SHANKRefertoFigure11-65Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min7.5 ---- ---- ---- ---- 4.528 1.81512 ---- ---- ---- ---- 6.341 1.31518 37.6 38.2 0.074 0.139 7.053 0.77021 33.5 33.9 -0.118 -0.053 7.285 0.52524 30.3 30.7 -0.232 -0.177 7.468 0.36030 24.6 SetUp -0.321 -0.266 7.698 0.32536 19.4 19.6 -0.362 -0.307 7.725 0.38542 15.5 15.7 -0.453 -0.398 7.239 0.345Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter


APPENDIX C - BLADE SPECIFICATIONSPage 11-168.2Rev. 39 Mar/2061-13-33

Blade Model 9510(S) Blade Tip Figure 11-65.1

9510

R 0.25R 1.500

46.125

42

36

30

24



Rev. 39 Mar/2061-13-33

9510(S) Blade "D" SHANKRefertoFigure11-64.1Distancefrombladebuttto"0"station=1.000"




Rev. 29 Nov/1261-13-33

Blade Model 9511F(A) Blade Tip Figure 11-66

9511F_a

46.125

45.125

42

36

41

44.5

R2.

0

R2.

0

2.6 FULL RADIUS

2.9 FULL RADIUS

9511F(A)-2

9511F(A)-4

9511F(A)-11

9511F(A)



Rev.29Nov/1261-13-33

9511F(A), -2 * Blade “D”SHANKRefertoFigure11-66Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.547 1.47512 ---- ---- ---- ---- 5.664 1.03518 40.9 41.5 0.100 0.165 6.809 0.59024 33.8 34.2 -0.110 -0.055 7.226 0.36530 29.7 SetUp -0.225 -0.170 7.274 0.34536 26.1 26.3 -0.344 -0.289 7.076 0.31542 23.7 23.9 -0.489 -0.434 5.550 0.235Tip ---- ---- ---- ---- ---- 0.080*Refertoparagraph2.B.ofthischapter

9511F(A)-4 Blade “D”SHANKRefertoFigure11-66Distancefrombladebuttto“0”station=1.000”


9511F(A)-11 Blade “D”SHANKRefertoFigure11-66Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.541 1.47512 ---- ---- ---- ---- 5.646 1.03518 40.9 41.5 0.100 0.165 6.767 0.59024 33.8 34.2 -0.110 -0.055 7.158 0.36530 29.7 SetUp -0.225 -0.170 7.114 0.34536 26.1 26.3 -0.344 -0.289 6.502 0.315Tip ---- ---- ---- ---- ---- 0.180



Rev.30Apr/1361-13-33

Blade Model 9512( ) Blade Tip Figure 11-67

9512


46.1

2545

.625

4236

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

2.06

R.

9512-1


APPENDIX C - BLADE SPECIFICATIONSPage 11-172.1Rev. 34 Jan/1761-13-33

9512 (A, AE, AF, C, D, G), -1* Blade “D”, “E” SHANK Refer to Figure 11-67Distance from blade butt to “0” station = 1.000”

Sta Angle Face Align. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.510 1.88512 ---- ---- ---- ---- 5.800 1.41518 42.3 42.9 0.265 0.330 6.910 0.97024 35.5 35.9 0.010 0.075 7.230 0.68030 30.0 Set Up -0.190 -0.125 7.010 0.49536 25.6 26.0 -0.355 -0.300 5.940 0.36542 23.1 23.3 -0.505 -0.450 3.990 0.21543 ---- ---- ---- ---- ---- 0.17544 ---- ---- ---- ---- ---- 0.13045** ---- ---- ---- ---- ---- 0.080Tip ---- ---- ---- ---- ---- 0.045*Refer to paragraph 2.B. of this chapter** Does not apply to -1 blade



Rev. 29 Nov/1261-13-33

Blade Model 9515 Blade TipFigure 11-67.1

9515

46.1

2542

36

R3.00 R0.25

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S



Rev.29Nov/1261-13-33

9515 Blade “D”SHANK RefertoFigure11-67.1Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.807 1.76112 ---- ---- ---- ---- 6.239 1.33918 39.8 40.4 0.199 0.264 7.302 0.80424 32.2 32.6 -0.093 -0.038 7.711 0.41030 26.5 SetUp -0.241 -0.186 7.537 0.32336 22.1 22.4 -0.312 -0.257 7.115 0.37642 17.8 18 -0.448 -0.393 5.739 0.351Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


9587


LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

47.5

46.5

44.5

4442

.542

4039

3832

.51" R. 1" R.

2" R.

2" R. 2" R.

2.5" R. 2.5" R.

1" R. 1" R.

1" R. 1" R.

9587A

9587D-2

9587A-7

9587A-10

9587C-15S

9587C-17S



Rev. 27 Sep/1161-13-33

9587A Blade “Y” SHANKRefertoFigure11-68Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.5 ---- ---- ---- ---- 5.225 1.40514.5 ---- ---- ---- ---- 6.235 0.86520.5 35.25 35.75 0.038 0.102 6.660 0.53026.5 29.75 30.25 -0.122 -0.058 6.690 0.40132.5 25.5 SetUp -0.240 -0.176 6.390 0.33838.5 22.1 22.5 -0.358 -0.294 5.455 0.25344.5 19.4 19.8 -0.476 -0.412 3.560 0.172Tip ---- ---- ---- ---- ---- 0.035

9587A-10 Blade “Y” SHANKRefertoFigure11-68Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.5 ---- ---- ---- ---- 5.225 1.40514.5 ---- ---- ---- ---- 6.235 0.86520.5 35.25 35.75 0.038 0.102 6.660 0.53026.5 29.75 30.25 -0.122 -0.058 6.690 0.40132.5 25.5 SetUp -0.240 -0.176 6.354 0.33038.5 22.1 22.5 -0.358 -0.294 5.262 0.245Tip ---- ---- ---- ---- ---- 0.035



Rev. 27 Sep/1161-13-33

9587D-2 Blade “Y” SHANKRefertoFigure11-68Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.5 ---- ---- ---- ---- 5.225 1.40514.5 ---- ---- ---- ---- 6.235 0.86520.5 37.55 38.05 0.038 0.102 6.660 0.53026.5 30.45 30.95 -0.122 -0.058 6.690 0.40132.5 25.5 SetUp -0.240 -0.176 6.390 0.33038.5 21.8 22.2 -0.358 -0.294 5.455 0.24544.5 18.8 19.2 -0.476 -0.412 3.560 0.167Tip ---- ---- ---- ---- ---- 0.035

9587D-7 Blade “Y” SHANKRefertoFigure11-68Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.5 ---- ---- ---- ---- 5.225 1.40514.5 ---- ---- ---- ---- 6.235 0.86520.5 37.55 38.05 0.038 0.102 6.660 0.53026.5 30.45 30.95 -0.122 -0.058 6.690 0.40132.5 25.5 SetUp -0.240 -0.176 6.354 0.33038.5 21.8 22.2 -0.358 -0.294 5.262 0.245Tip ---- ---- ---- ---- -------- 0.035



Rev. 27 Sep/1161-13-33

9587C-15(S) Blade “Y” SHANKRefertoFigure11-68Distancefrombladebuttto“0”station=1.000”


9587C-17S Blade “Y” SHANKRefertoFigure11-68Distancefrombladebuttto“0”station=1.000”




Rev. 27 Sep/1161-13-33


W10095

.50

R. T

YP.



APPENDIX C - BLADE SPECIFICATIONSPage 11-178.1Rev.30Apr/1361-13-33

9612* Blade “E” SHANKRefertoFigure11-69Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.0 ---- ---- ---- ---- 4.540 1.93512.0 ---- ---- ---- ---- 5.820 1.44518.0 41.3 41.9 0.313 0.378 6.910 1.02024.0 34.5 34.9 0.070 0.125 7.230 0.72030.0 29.0 SetUp -0.149 -0.094 7.010 0.49536.0 23.9 24.1 -0.321 -0.266 5.940 0.36542.0 21.1 21.3 -0.491 -0.436 4.350 0.24545.0 ---- ---- ---- ---- 3.400 0.140Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter


APPENDIX C - BLADE SPECIFICATIONSPage 11-178.2Rev.30Apr/1361-13-33

Blade Model 9673( ) Blade Tip Figure 11-69.1

46.6

2542

36

2 X R1.00

9673



Rev.30Apr/1361-13-33

9673* Blade “E” SHANKRefertoFigure11-69.1Distancefrombladebuttto“0”station=1.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.0 58.3 60.3 0.924 0.999 4.552 1.93512.0 48.8 49.8 0.643 0.718 5.792 1.44518.0 42.5 43.1 0.183 0.248 6.957 1.02024.0 35.9 36.3 -0.075 -0.020 7.539 0.72030.0 30.3 SetUp -0.303 -0.248 7.604 0.49536.0 25.4 25.6 -0.484 -0.429 7.117 0.36542.0 21.1 21.3 -0.582 -0.527 6.066 0.245Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


9684




Rev. 27 Sep/1161-13-33

9684, -3R Blade “Y” SHANKRefertoFigure11-70Distancefrombladebuttto“0”station=2.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9.5 ---- ---- ---- ---- 5.164 1.69515.5 ---- ---- ---- ---- 6.062 1.22021.5 32.7 33.7 .080 .140 6.285 0.79027.5 29.15 29.65 -.120 -.060 6.186 0.56833.5 25.8 SetUp -.240 -.180 5.676 0.42539.5 22.6 23.0 -.365 -.305 4.638 0.29542.5 21.3 21.7 -.460 -.400 3.762 0.220Tip ---- ---- ---- ---- ---- 0.055

9684-12 Blade “Y” SHANKRefertoFigure11-70Distancefrombladebuttto“0”station=2.000”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9.5 ---- ---- ---- ---- 5.167 1.69515.5 ---- ---- ---- ---- 6.064 1.22021.5 32.7 33.7 .080 .140 6.286 0.79027.5 29.15 29.65 -.120 -.060 6.152 0.56833.5 25.8 SetUp -.240 -.180 5.560 0.42539.5 22.6 23.0 -.365 -.305 4.261 0.295Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33


9690

0.11

50.25

52.

125

R.

2.12

5 R

.

46.6

2542

36

LEA

DIN

G E

DG

E





Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.542 1.73512 ---- ---- ---- ---- 5.805 1.31518 43.1 43.7 0.233 0.298 6.892 0.80024 35.1 35.5 0.029 0.084 7.425 0.53030 30.0 SetUp -0.063 -0.008 7.623 0.50536 26.4 26.6 -0.145 -0.090 7.052 0.49542 23.4 23.6 -0.279 -0.224 5.021 0.375Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter




TPI-J

M-0

0024

4

R. 2

.000

R. 0

.25

46.9

7542

3630

24

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S



Rev. 39 Mar/2061-13-33

9782(S) Blade "E"ShankRefertoFigure11-71.1Distancefrombladebuttto“0”station=1.000”

Sta Angle Min

Angle Max

Face Min

Align Max

Width Min

Thickness Min

8 ---- ---- ---- ---- 4.010 2.24512 ---- ---- ---- ---- 5.319 1.24518 41.7 42.3 0.231 0.296 6.705 0.86424 34.1 34.5 0.006 0.061 7.236 0.61230 29.2 SET UP -0.165 -0.110 7.208 0.48636 25.5 25.7 -0.304 -0.249 6.782 0.41442 22.7 22.9 -0.444 -0.389 6.018 0.324Tip ---- ---- ---- ---- ---- 0.075 *Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


R 1

.50

R 1

.00

48.1

2545

4236

30

9900




Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.488 1.63512 ---- ---- ---- ---- 5.664 1.27518 40.5 41.1 0.172 0.237 6.811 0.75024 32.4 32.8 -0.106 -0.041 7.533 0.40030 27.0 SetUp -0.206 -0.151 7.827 0.31536 22.1 22.5 -0.205 -0.150 7.766 0.35542 18.4 18.6 -0.206 -0.151 6.727 0.36545 16.9 17.1 -0.247 -0.192 5.528 0.295Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter




R. 0

.25

R. 0

.25

48.1

25

4236

3048

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

TPI-J

M-0

0023

3



Rev. 39 Mar/2061-13-33

9901 Blade "D"ShankRefertoFigure11-72.1Distancefrombladebuttto“0”station=1.000”

Sta Angle Min

Angle Max

Face Min

Align Max

Width Min

Thickness Min

8 ---- ---- ---- ---- 4.547 1.47512 ---- ---- ---- ---- 5.664 1.03518 38.5 39.1 0.100 0.165 6.811 0.59024 33.8 34.2 -0.116 -0.051 7.289 0.36530 31.4 SetUp -0.229 -0.174 7.165 0.34536 29.2 29.6 -0.346 -0.291 6.681 0.31542 27.1 27.3 -0.489 -0.434 5.785 0.235Tip ---- ---- ---- ---- ---- 0.140 *Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33

R 1.82

Blade Model 9990N Blade Tip Figure 11-73

9990

49.2

542

36

LEA

DIN

G E

DG

E

46



Rev. 27 Sep/1161-13-33

9990N* Blade “M” SHANKRefertoFigure11-73Distancefrombladebuttto“0”station=4.512”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.5 ---- ---- ---- ---- 3.682 3.08510.5 ---- ---- ---- ---- 4.335 2.18512.0 ---- ---- ---- ---- 4.919 1.87518.0 40.8 41.4 0.527 0.592 6.409 1.33024.0 32.5 32.9 0.247 0.312 7.253 0.97030.0 26.6 SetUp 0.020 0.075 7.689 0.71536.0 21.4 21.8 -0.192 -0.137 7.451 0.49542.0 17.3 17.5 -0.398 -0.343 5.937 0.28546.0 14.9 15.1 -0.529 -0.474 4.027 0.155Tip ---- ---- ---- ---- ---- 0.045*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33

CPS0568





Rev. 27 Sep/1161-13-33

10133D, -3 Blade "MV","X", "V" SHANK10133N, -3 BladeRefertoFigure11-74Distancefrombladebuttto"0"station=4.15"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9.5 ---- ---- ---- ---- 4.690 1.98312 ---- ---- ---- ---- 5.340 1.50118 39.1 40.1 .293 .357 6.060 0.92224 32.9 33.5 .038 .102 6.290 0.69130 29.4 SetUp -.122 -.058 6.160 0.51836 25.6 26.0 -.242 -.178 5.670 0.42542 22.6 23.0 -.357 -.293 4.620 0.31748 19.9 20.3 -.532 -.468 NL NL

10133D-11 Blade "MV","X","V" SHANK10133N-11 BladeRefertoFigure11-74Distancefrombladebuttto"0"station=4.15"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min9.5 ---- ---- ---- ---- 4.690 1.98312 ---- ---- ---- ---- 5.335 1.50018 39.1 40.1 .293 .357 6.050 0.92124 32.9 33.5 .038 .102 6.275 0.68930 29.4 SetUp -.122 -.058 6.115 0.51536 25.6 26.0 -.242 -.178 5.535 0.41542 22.6 23.0 -.357 -.293 4.290 0.197



Rev. 27 Sep/1161-13-33



10151

10151(C)-5

10151-8

10151-8R10151-10

10151-10R

.5R

.TYP

.5R

.TYP

2 R.2 R.

2 R.2 R.

.5R..5R.



Rev. 27 Sep/1161-13-33

10151-8(R) Blade "Z","W" SHANK10151-10(R) BladeRefertoFigure11-75Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.043 2.85412 ---- ---- ---- ---- 5.355 1.50118 ---- ---- .293 .357 6.071 0.92224 32.9 33.5 .038 .102 6.306 0.69030 29.4 SetUp -.122 -.058 6.175 0.51636 25.6 26.0 -.242 -.178 5.655 0.42242 22.6 23.0 -.357 -.293 NL NL

10151C-5 Blade "Z","W" SHANKRefertoFigure11-75Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.043 2.85412 ---- ---- ---- ---- 5.355 1.50118 ---- ---- .293 .357 6.071 0.92224 32.9 33.5 .038 .102 6.306 0.69030 29.4 SetUp -.122 -.058 6.175 0.51636 26.3 26.7 -.242 -.178 5.655 0.42242 24.5 24.9 -.357 -.293 4.514 0.308



Rev. 27 Sep/1161-13-33


10152


10152-5.5

.44 R. .44 R

.



Rev. 27 Sep/1161-13-33

10152-5.5 Blade "Z", "W", "P", "R" SHANK RefertoFigure11-76Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.870 2.89012 ---- ---- ---- ---- 4.825 1.61018 ---- ---- .393 .457 5.500 1.12024 32.9 33.5 .088 .152 5.816 0.80230 29.3 SetUp -.122 -.058 5.982 0.58036 25.8 26.2 -.242 -.178 5.655 0.43042 23.3 23.7 -.357 -.293 4.514 0.33043.5 ---- ---- ---- ---- ---- 0.31544.5 ---- ---- ---- ---- ---- 0.28545.5 ---- ---- ---- ---- ---- 0.24746.5 ---- ---- ---- ---- ---- 0.208



Rev. 27 Sep/1161-13-33


CPS0612

LEA

DIN

G E

DG

E

47.5

4642

4745

4436

4348

4950

RO

TATI

ON

AL

AXI

S

10160-3

10160-1

10160-6

45.5


0.44 R. 0.44 R

.



Rev. 27 Sep/1161-13-33

10160-1, -3 Blade "Z", "W", "P", "R" SHANKRefertoFigure11-77Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.859 3.04512 ---- ---- ---- ---- 4.812 1.77018 38.4 39.4 0.429 0.491 5.492 1.19324 32.9 33.5 0.089 0.151 5.811 0.80530 29.3 SetUp -0.091 -0.029 5.970 0.62536 25.8 26.2 -0.216 -0.154 5.636 0.46142 23.3 23.7 -0.346 -0.284 4.467 0.35048 21.4 21.8 -0.466 -0.404 2.960 0.231

10160-6 Blade "Z", "W", "P", "R" SHANKRefertoFigure11-77Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.870 2.89012 ---- ---- ---- ---- 4.825 1.77518 ---- ---- .428 .492 5.500 1.19824 32.9 33.5 .088 .152 5.816 0.81230 29.3 SetUp -.092 -.028 5.982 0.63036 25.8 26.2 -.217 -.153 5.666 0.47642 23.3 23.7 -.347 -.283 4.532 0.36543.5 ---- ---- ---- ----- ---- 0.34544.5 ---- ---- ---- ---- ---- 0.30845.5 ---- ---- ---- ---- ---- 0.26146 ---- ---- ---- ---- ---- 0.225



Rev. 27 Sep/1161-13-33

Blade Models 10160-6.5R, 10160-8.5R Blade Tip Figure 11-78

CPS0612-1

LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AXI

S

47.2

546

.25

4336

46

4442

47

45

2.25 R

.

2.25 R

.2.25

R.

2.25 R

.10160-8.5R

10160-6.5R




Rev. 27 Sep/1161-13-33

10160-8.5R Blade "Z" SHANKRefertoFigure11-78Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.870 2.89012 ---- ---- ---- ---- 4.825 1.77518 ---- ---- .428 .492 5.500 1.19824 32.9 33.5 .088 .152 5.816 0.81230 29.3 SetUp -.092 -.028 5.982 0.63036 25.8 26.2 -.217 -.153 5.666 0.47642 23.3 23.5 -.347 -.283 4.375 0.31043.25 ---- ---- ---- ---- ---- 0.27044.25 ---- ---- ---- ---- ---- 0.21045.25 ---- ---- ---- ---- ---- 0.160



Rev. 27 Sep/1161-13-33

Blade Model 10160-12E Blade Tip Figure 11-79

10160-12E

LEA

DIN

G E

DG

E

10160-12E

42

44.5

4436

RO

TATI

ON

AL

AXI

S




Rev. 27 Sep/1161-13-33

10160-12E Blade "P","R" SHANKRefertoFigure11-79Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.870 2.89012 ---- ---- ---- ---- 4.825 1.77518 ---- ---- .428 .492 5.500 1.19824 32.9 33.5 .088 .152 5.816 0.81230 29.3 SetUp -.092 -.028 5.890 0.63036 25.8 26.2 -.217 -.153 5.390 0.47642 23.3 23.7 -.347 -.283 3.770 0.310



Rev. 27 Sep/1161-13-33


10172


noiteminaxalant,onlymodel

3642

46.5

4850

.5

1" R

.1" R.

AXI

S O

F R

OTA

TIO

N

LEA

DIN

G E

DG

E

10172



Rev. 27 Sep/1161-13-33

10172 Blade "T" SHANKRefertoFigure11-80Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.055 2.56512 ---- ---- ---- ---- 5.367 1.19518 39.1 40.1 .228 .292 6.083 0.73224 33.0 33.5 .038 .102 6.306 0.54630 29.4 SetUp -.122 -.058 6.187 0.41736 25.6 26.0 -.240 -.176 5.702 0.33842 22.6 23.0 -.358 -.294 4.644 0.25348 19.9 20.3 -.476 -.412 2.930 0.172

10172C Blade "T" SHANKRefertoFigure11-80Distancefrombladebuttto"0"station=4.512"


noiteminaxalant,onlymodel



Rev. 27 Sep/1161-13-33

Blade Model 10173A Blade Tip Figure 11-81

10173A-1


10173A

10173A-410173A-6Q

10173AN-12.5

50.5

48.5

48.2

4536

44.2

5

1"R1"R

1"R 1"R

2"R2"R

2.5"R 2.5"R

42



Rev. 27 Sep/1161-13-33

10173A(N) Blade "T" SHANK RefertoFigure11-81Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74110 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.40518 43.1 44.1 .289 .351 6.237 0.85424 35.5 35.8 .038 .102 6.655 0.59530 30.0 SetUp -.122 -.058 6.682 0.46536 25.2 25.6 -.240 -.176 6.380 0.39242 20.9 21.3 -.358 -.294 5.450 0.29948 17.6 18.0 -.476 -.412 3.560 0.217

10173A(N)-6, -6Q* Blade "T" SHANK RefertoFigure11-81Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74110 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.40518 43.1 44.1 .289 .351 6.237 0.85424 35.5 35.8 .038 .102 6.655 0.59530 30.0 SetUp -.122 -.058 6.670 0.46436 25.2 25.6 -.240 -.176 6.330 0.38942 20.9 21.3 -.358 -.294 5.290 0.291*Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual



Rev. 27 Sep/1161-13-33

10173AN-12.5* Blade "T" SHANK RefertoFigure11-81Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74110 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.40718 43.1 44.1 .289 .351 6.235 0.84524 35.5 35.8 .038 .102 6.645 0.58230 30.0 SetUp -.122 -.058 6.660 0.45136 25.3 25.5 -.240 -.176 6.230 0.38042 21.0 21.2 -.358 -.294 5.155 0.295Tip ---- ---- ---- ---- ---- 0.070*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33

Blade Model 10173D Blade Tip Figure 11-82

10173D




Rev. 27 Sep/1161-13-33

10173D(N)-6Q* Blade "T" SHANK RefertoFigure11-82Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.91612 ---- ---- ---- ---- 5.300 1.54318 43.1 44.1 .244 .306 6.237 0.94424 35.3 35.8 -.042 .022 6.655 0.63830 30.0 SetUp -.242 -.178 6.670 0.49836 25.2 25.6 -.405 -.341 6.330 0.43442 20.9 21.3 -.578 -.514 5.290 0.321*Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapter ofthismanual



Rev. 27 Sep/1161-13-33

Blade Model 10173F Blade Tip Figure 11-83

T10173F

4236

3045

LEA

DIN

G E

DG

E

R1.00

R1.00

4850

.545

.25

44.2

540

R2.50

R3.35

R2.94

R2.50

R2.50

R2.50

10173FB-10.5

10173F-11,-11R

10173F-12.5

10173F-21R




Rev. 27 Sep/1161-13-33

10173F(N)-10.5*, -11R Blade and10173F(N)-12.5* on all aircraft except Beech A100 "T" SHANK RefertoFigure11-83Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.75010 ---- ---- ---- ---- ---- 1.87012 ---- ---- ---- ---- 5.300 1.20518 43.1 44.1 .178 .242 6.235 0.64424 35.25 35.75 .038 .102 6.645 0.47130 30.0 SetUp -.122 -.058 6.660 0.40836 25.2 25.6 -.240 -.176 6.230 0.34542 20.9 21.3 -.358 -.294 5.155 0.251Tip ---- ---- ---- ---- ---- 0.070*Refertoparagraph2.B.ofthischapter

10173F(N)-12.5* Blade on Beech A100 applications only "T" SHANKRefertoFigure11-83Distancefrombladebuttto"0"station=4.512"

Angle FaceAlign. Width ThicknessSta Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.75010 ---- ---- ---- ---- ---- 1.87012 ---- ---- ---- ---- 5.300 1.20518 43.1 44.1 .178 .242 6.235 0.64424 35.25 35.75 .038 .102 6.645 0.47130 30.0 SetUp -.122 -.058 6.734 0.40836 25.2 25.6 -.240 -.176 6.456 0.34542 20.9 21.3 -.358 -.294 5.619 0.255Tip ---- ---- ---- ---- ---- 0.070*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33

10173F(N)-21R Blade "T" SHANK RefertoFigure11-83Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.75010 ---- ---- ---- ---- ---- 1.87012 ---- ---- ---- ---- 5.334 1.20518 43.1 44.1 .178 .242 6.231 0.64424 35.25 35.75 .038 .102 6.623 0.47130 30.0 SetUp -.122 -.058 6.571 0.40836 25.2 25.6 -.240 -.176 5.851 0.345Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33

Blade Model (T)10173 Blade Tip Figure 11-84

T10173




Rev. 27 Sep/1161-13-33

10173 and +1 Blade "T" SHANKRefertoFigure11-84Distancefrombladebuttto"0"station=4.512"


10173(N) and +1 Blade "T" SHANK Category 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"




Rev. 27 Sep/1161-13-33

10173-3 Blade "T" SHANK RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.58512 ---- ---- ---- ---- 5.300 1.19518 43.1 44.1 0.228 0.292 6.192 0.73224 35.25 35.75 0.038 0.102 6.615 0.54730 30.0 SetUp -0.122 -0.058 6.670 0.41736 25.2 25.6 -0.240 -0.176 6.370 0.34242 20.9 21.3 -0.358 -0.294 5.450 0.25348 17.6 18.0 -0.476 -0.412 ---- ----Tip ---- ---- ---- ---- ---- 0.075

10173(N)-3 Blade "T" SHANKCategory 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74510 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.36018 43.1 44.1 0.289 0.351 6.192 0.83024 35.25 35.75 0.038 0.102 6.615 0.54730 30.0 SetUp -0.122 -0.058 6.670 0.41736 25.2 25.6 -0.240 -0.176 6.370 0.34242 20.9 21.3 -0.358 -0.294 5.450 0.25348 17.6 18.0 -0.476 -0.412 ---- ----Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33

10173-8(R) Blade "T" SHANKRefertoFigure11-84Distancefrombladebuttto"0"station=4.512"


10173(N)-8(R), -9 Blade "T" SHANKCategory 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74510 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.36018 43.1 44.1 0.289 0.351 6.192 0.83024 35.25 35.75 0.038 0.102 6.615 0.54630 30.0 SetUp -0.122 -0.058 6.648 0.41536 25.2 25.6 -0.240 -0.176 6.257 0.33842 20.9 21.3 -0.358 -0.294 5.185 0.242Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33

10173-11 Blade "T" SHANKRefertoFigure11-84Distancefrombladebuttto"0"station=4.512"


10173(N)-11(R) Blade "T" SHANKCategory 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74510 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.36018 43.1 44.1 0.289 0.351 6.186 0.83024 35.25 35.75 0.038 0.102 6.608 0.54630 30.0 SetUp -0.122 -0.058 6.640 0.41536 25.2 25.6 -0.240 -0.176 6.230 0.33642 20.9 21.3 -0.358 -0.294 5.155 0.241Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33

10173(N)-13Q* Blade "T" SHANKCategory 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74510 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.36018 43.1 44.1 .228 .292 6.186 0.83024 35.25 35.75 .038 .102 6.608 0.54630 30.0 SetUp -.122 -.058 6.640 0.41536 25.2 25.6 -.240 -.176 6.230 0.33642 20.9 21.3 -.358 -.294 5.155 0.170*seeparagraph2.M.oftheBladeAirfoilOverhaulchapterofthismanual

10173(N)-15 Blade "T" SHANKCategory 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74510 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.36018 43.1 44.1 .228 .292 6.186 0.83024 35.25 35.75 .038 .102 6.608 0.54630 30.0 SetUp -.122 -.058 6.640 0.41536 25.2 25.6 -.240 -.176 6.230 0.33642 20.9 21.3 -.358 -.294 3.760 0.112Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33

10173(N)-17R Blade "T" SHANKCategory 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74510 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.36018 43.1 44.1 0.289 0.351 6.186 0.83024 35.25 35.75 0.038 0.102 6.608 0.54630 30.0 SetUp -0.122 -0.058 6.640 0.41536 25.2 25.6 -0.240 -0.176 5.999 0.33639 ---- ---- ---- ---- 5.026 0.295Tip ---- ---- ---- ---- ---- 0.075

10173(N)-18 Blade "T" SHANK Category 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74510 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.36018 43.1 44.1 0.289 0.351 6.186 0.83024 35.25 35.75 0.038 0.102 6.608 0.54630 30.0 SetUp -0.122 -0.058 6.640 0.41536 25.2 25.6 -0.240 -0.176 5.999 0.33639 ---- ---- ---- ---- 5.369 0.295Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33

10173(N)-21R Blade "T" SHANK Category 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.020 2.77010 ---- ---- ---- ---- ---- 1.925x12 ---- ---- ---- ---- 5.325 1.38218 43.1 44.1 0.289 0.351 6.213 0.82024 35.25 35.75 0.038 0.102 6.589 0.53230 30.0 SetUp -0.122 -0.058 6.468 0.40136 25.2 25.6 -0.240 -0.176 5.974 0.323

10173(N)-25R Blade "T" SHANK Category 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.02 2.77010 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.325 1.38218 43.1 44.1 0.27 0.35 6.213 0.82024 35.25 35.75 0.02 0.10 6.589 0.53230 30.0 SetUp -0.14 -0.06 6.468 0.40134 26.7 27.1 -0.22 -0.14 5.974 0.34535 ---- ---- ---- ---- 5.761 ----36 25.2 25.6 -0.26 -0.18 5.160 0.23037 ---- ---- ---- ---- 3.891 ----Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33

10173C(N) and +1 Blade "T" SHANKCategory 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"


10173C and +1 Blade "T" SHANKRefertoFigure11-84Distancefrombladebuttto"0"station=4.512"




Rev. 27 Sep/1161-13-33

10173C(N)-8 Blade "T" SHANKCategory 2RefertoFigure11-84Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74510 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.36018 43.1 44.1 .289 .351 6.192 0.83024 35.25 35.75 .038 .102 6.615 0.54630 30.0 SetUp -.122 -.058 6.648 0.41536 26.8 27.2 -.240 -.176 6.257 0.33842 24.7 25.1 -.358 -.294 5.185 0.242



Rev. 27 Sep/1161-13-33


10176



Rev. 27 Sep/1161-13-33

10176(H)(S)-6, -5 Blade "T" SHANK RefertoFigure11-85Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.58512 ---- ---- --- ---- 5.300 1.19518 43.1 44.1 .228 .292 6.192 0.73224 35.25 35.75 .038 .102 6.615 0.54730 30.0 SetUp -.122 -.058 6.670 0.44136 25.2 25.6 -.240 -.176 6.325 0.36042 20.9 21.3 -.358 -.294 5.290 0.285Tip ---- ---- ---- ---- ---- 0.075

10176(H)(N)(S)-6, -5, -8 Blade "T" SHANK Category 2 RefertoFigure11-85Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.990 2.74510 ---- ---- ---- ---- ---- 1.92512 ---- ---- ---- ---- 5.300 1.36018 43.1 44.1 .289 .351 6.192 0.83024 35.25 35.75 .038 .102 6.615 0.54730 30.0 SetUp -.122 -.058 6.670 0.44136 25.2 25.6 -.240 -.176 6.325 0.36042 20.9 21.3 -.358 -.294 5.290 0.285Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33


10176C and +1 Blade "T" SHANKRefertoFigure11-85Distancefrombladebuttto"0"station=4.512"


10176 and +1 & -3 Blade "T" SHANKRefertoFigure11-85Distancefrombladebuttto"0"station=4.512"




Rev. 27 Sep/1161-13-33

10176(N) and +1 & -3 Blade "T" SHANKCategory 2RefertoFigure11-85Distancefrombladebuttto"0"station=4.512"




Rev.30Apr/1361-13-33


10178A



Rev. 27 Sep/1161-13-33

10178(H)(N)(R) Blade "T" SHANKRefertoFigure11-86Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.435 0.94224 35.25 35.75 .089 .151 7.090 0.65530 30.0 SetUp -.081 -.019 7.345 0.50536 25.2 25.6 -.231 -.169 7.400 0.36442 20.9 21.3 -.351 -.289 7.130 0.25348 17.6 18.0 -.461 -.399 6.250* 0.153tip ---- ---- ---- ---- ---- 0.075*5.450for10178(R)blade

10178C(H)(N)(R), +1 Blade "T" SHANKRefertoFigure11-86Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.435 0.94224 35.25 35.75 .089 .151 7.090 0.65530 30.0 SetUp -.081 -.019 7.345 0.50536 26.8 27.2 -.231 -.169 7.400 0.36442 24.7 25.1 -.351 -.289 7.130 0.25348 22.8 23.2 -.461 -.399 6.250* 0.153tip ---- ---- ---- ---- ---- 0.075*5.450for10178CRblade



Rev. 27 Sep/1161-13-33

10178(H)(N)-5 and -6 Blade "T" SHANKRefertoFigure11-86Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.435 0.94224 35.25 35.75 .089 .151 7.090 0.65730 30.0 SetUp -.081 -.019 7.345 0.50736 25.2 25.6 -.231 -.169 7.380 0.36542 20.9 21.3 -.351 -.289 6.915 0.24748 17.6 18.0 -.461 -.399 ---- ----

10178(H)(N)-3R Blade "T" SHANKRefertoFigure11-86Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.435 0.94224 35.25 35.75 .089 .151 7.090 0.65730 30.0 SetUp -.081 -.019 7.345 0.51536 25.2 25.6 -.231 -.169 7.400 0.37542 20.9 21.3 -.351 -.289 7.050 0.26544 ---- ---- ---- ---- ---- 0.23046 ---- ---- ---- ---- ---- 0.19548 17.6 18.0 -.461 -.399 NL NL



Rev. 27 Sep/1161-13-33


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.435 0.94224 35.25 35.75 .089 .151 7.090 0.65730 30.0 SetUp -.081 -.019 7.345 0.50736 25.2 25.6 -.231 -.169 7.380 0.36542 20.9 21.3 -.351 -.289 6.350 0.24748 17.6 18.0 -.461 -.399 ---- ----


Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 0.319 0.381 6.435 0.94224 35.25 35.75 0.089 0.151 7.090 0.65730 30.0 SetUp -0.081 -0.019 7.345 0.50736 25.2 25.6 -0.231 -0.169 7.390 0.36542 20.9 21.3 -0.351 -0.289 6.700 0.24748 17.6 18.0 -0.461 -0.399 NL 0.060



Rev. 27 Sep/1161-13-33



Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 0.319 0.381 6.435 0.94224 35.25 35.75 0.089 0.151 7.090 0.65730 30.0 SetUp -0.081 -0.019 7.325 0.50636 25.2 25.6 -0.231 -0.169 7.270 0.36242 20.9 21.3 -0.401 -0.339 5.850 0.154

10178(H)(N)-10Q* Blade "T" SHANKRefertoFigure11-86Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.430 0.94224 35.25 35.75 .089 .151 7.080 0.65530 30.0 SetUp -.081 -.019 7.315 0.50536 25.2 25.6 -.231 -.169 7.250 0.36442 20.9 21.3 -.351 -.289 6.800 0.241*Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapter ofthismanual



Rev. 27 Sep/1161-13-33

10178(H)(N)-11 Blade "W", "T" SHANKRefertoFigure11-86Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.430 0.94224 35.25 35.75 .089 .151 7.080 0.65530 30.0 SetUp -.081 -.019 7.315 0.50536 25.2 25.6 -.231 -.169 7.250 0.36442 20.9 21.3 -.351 -.289 6.800 0.241





Rev. 27 Sep/1161-13-33



10178(N)-5Q, -7Q Blade "T" SHANKRefertoFigure11-86Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913 12 ---- ---- ---- ---- 5.165 1.541 18 43.1 44.1 .319 .381 6.435 0.94224 35.25 35.75 .089 .151 7.090 0.65730 30.0 SetUp -.081 -.019 7.345 0.50736 25.2 25.6 -.231 -.169 7.380 0.36542 20.9 21.3 -.351 -.289 6.915 0.24745 ---- ---- ---- ---- 6.450 ----**Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapter ofthismanual



Rev. 27 Sep/1161-13-33

10178(N)-13Q Blade "T" SHANKRefertoFigure11-86Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913 12 ---- ---- ---- ---- 5.165 1.541 18 43.1 44.1 .319 .381 6.430 0.94224 35.25 35.75 .089 .151 7.080 0.65530 30.0 SetUp -.081 -.019 7.315 0.50536 25.2 25.6 -.231 -.169 7.250 0.36442 20.9 21.3 -.351 -.289 6.800 ----**Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapter ofthismanual

10178(N)-15 Blade "T" SHANKRefertoFigure11-86Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.91312 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 0.319 0.381 6.430 0.94224 35.25 35.75 0.089 0.151 7.080 0.65530 30.0 SetUp -0.081 -0.019 7.290 0.50336 25.2 25.6 -0.281 -0.219 6.800 0.31042 20.9 21.3 -0.401 -0.339 ---- 0.136tip ---- ---- ---- ---- ---- 0.075



Rev. 31 Jul/1461-13-33


TPI-10282-1



Rev. 31 Jul/1461-13-33

10282(N)+4 Blade "T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913*9 ---- ---- ---- ---- ---- 2.790**12 ---- ---- ---- ---- 5.201 1.54118 43.1 44.1 0.319 0.381 6.435 0.94224 35.25 35.75 0.089 0.151 7.090 0.65730 30.0 SetUp -0.081 -0.019 7.345 0.50836 26.0 26.4 -0.261 -0.199 7.400 0.36742 23.1 23.5 -0.431 -0.369 7.130 0.25348 20.9 21.3 -0.571 -0.509 6.250 0.15351.625 ---- ---- ---- ---- ---- 0.109tip ---- ---- ---- ---- ---- 0.050*Minimumthicknessfor"N"bladesis3.170inch**Station9specificationsapplyto"N"bladesonly

10282(N)-4P, -4R Blade "T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913*9 ---- ---- ---- ---- ---- 2.790**12 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 0.319 0.381 6.435 0.94224 35.25 35.75 0.089 0.151 7.090 0.65730 30.0 SetUp -0.081 -0.019 7.345 0.50836 26.0 26.4 -0.261 -0.199 7.400 0.36542 23.1 23.5 -0.431 -0.369 7.130 0.25348 20.9 21.3 -0.571 -0.509 tip ---- ---- ---- ---- ---- 0.050*Minimumthicknessfor"N"bladesis3.170inch**Station9specificationsapplyto"N"bladesonly



Rev. 27 Sep/1161-13-33

10282(N)R Blade "T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913*9 ---- ---- ---- ---- ---- 2.790**12 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.435 0.94224 35.25 35.75 .089 .151 7.090 0.65730 30.0 SetUp -.081 -.019 7.345 0.50836 26.0 26.4 -.261 -.199 7.400 0.36742 23.1 23.5 -.431 -.369 7.130 0.25348 20.9 21.3 -.571 -.509 5.650 0.153tip ---- ---- ---- ---- ---- 0.070*Minimumthicknessfor"N"bladesis3.170inch**Station9specificationsapplyto"N"bladesonly

10282(N)+6 Blade "M","T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913*9 ---- ---- ---- ---- ---- 2.790**12 ---- ---- ---- ---- 5.201 1.54118 43.1 44.1 .319 .381 6.469 0.94224 35.25 35.75 .089 .151 7.164 0.65730 30.0 SetUp -.081 -.019 7.435 0.51436 26.0 26.4 -.261 -.199 7.543 0.36742 23.1 23.5 -.431 -.369 7.503 0.25348 20.9 21.3 -.571 -.509 6.872 0.15352.5 19.5 19.9 -.591 -.529 4.380 0.109tip ---- ---- ---- ---- ---- 0.050*Minimumthicknessfor"N"bladesis3.170inch*Station9specificationsapplyto"N"bladesonly



Rev. 27 Sep/1161-13-33

10282D(N) Blade "T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913*9 ---- ---- ---- ---- ---- 2.790**12 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.435 0.94224 35.25 35.75 .089 .151 7.090 0.65730 30.0 SetUp -.081 -.019 7.345 0.50836 25.2 25.6 -.261 -.199 7.400 0.36742 20.9 21.3 -.431 -.369 7.130 0.25348 17.6 18.0 -.571 -.509 5.979 0.153tip ---- ---- ---- ---- ---- 0.070*Minimumthicknessfor"N"bladesis3.170inch**Station9specificationsapplyto"N"bladesonly

10282(N) -6R Blade "T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913*9 ---- ---- ---- ---- ---- 2.790**12 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 0.319 0.381 6.435 0.94224 35.25 35.75 0.089 0.151 7.090 0.65730 30.0 SetUp -0.081 -0.019 7.345 0.50536 26.0 26.4 -0.261 -0.199 7.400 0.36542 23.1 23.5 -0.431 -0.369 7.083 0.253tip ---- ---- ---- ---- ---- 0.035*Minimumthicknessfor"N"bladesis3.170inch**Station9specificationsapplyto"N"bladesonly



Rev. 27 Sep/1161-13-33


10282(N) Blade "T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512" Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913*9 ---- ---- ---- ---- ---- 2.790**12 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 0.319 0.381 6.435 0.94224 35.25 35.75 0.089 0.151 7.090 0.65730 30.0 SetUp -0.081 -0.019 7.345 0.50836 26.0 26.4 -0.261 -0.199 7.400 0.36742 23.1 23.5 -0.431 -0.369 7.130 0.25348 20.9 21.3 -0.571 -0.509 5.979 0.153tip ---- ---- ---- ---- ---- 0.070*Minimumthicknessfor"N"bladesis3.170inch**Station9specificationsapplyto"N"bladesonly ***Refertoparagraph2.B.ofthischapterforbladesusedin a4bladedpropeller

10282D(N)-4R Blade "T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913*9 ---- ---- ---- ---- ---- 2.790**12 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 .319 .381 6.435 0.94224 35.25 35.75 .089 .151 7.090 0.65730 30.0 SetUp -.081 -.019 7.345 0.50836 25.2 25.6 -.261 -.199 7.400 0.36542 20.9 21.3 -.431 -.369 7.130 0.25348 17.6 18.0 -.571 -.509 NL NLtip ---- ---- ---- ---- ---- 0.050*Minimumthicknessfor"N"bladesis3.170inch**Station9specificationsapplyto"N"bladesonly



Rev. 27 Sep/1161-13-33

10282NS-5.3R* Blade "T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512"

Angle FaceAlign. WidthThicknessSta Min Max Min Max Min Min A B8 ---- ---- ---- ---- 3.861 3.175 ---- ----9 ---- ---- ---- ---- ---- 2.790 ---- ----12 ---- ---- ---- ---- 5.213 1.550 ---- 1.57518 43.1 44.1 .319 .381 6.518 0.940 ---- 0.96524 35.25 35.75 .089 .151 7.173 0.650 ---- 0.67530 30.0 SetUp -.081 -.019 7.430 0.500 ---- 0.52536 26.0 26.4 -.261 -.199 7.516 0.365 0.395 ----42 23.1 23.5 -.431 -.369 7.459 0.255 0.285 ----44 ---- ---- ---- ---- 7.089 0.212 0.242 ----46.5 ---- ---- ---- ---- 5.162 0.162 0.192 ----Tip ---- ---- ---- ---- ---- 0.070 0.100 ----*Ifanythicknessesfromthe36-inchstationtothetiparelessthanthatincolumnA(butaboveminimums),thenfromthe 12-inchstationthroughthe30-inchstationtheblademustbereducedinthicknesstonomorethanthefiguresincolumnB. Toreducethicknessatthesestations,theairfoil(thickness)profilebetweenoneinchfromtheleadedgeandoneinchfromthetrailedgemustbereducedthesameamountasthemaximumthickness.

10282(N)-9.5R Blade "T" SHANKRefertoFigure11-87Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.830 2.913*9 ---- ---- ---- ---- ---- 2.790**12 ---- ---- ---- ---- 5.165 1.54118 43.1 44.1 0.319 0.381 6.435 0.94224 35.25 35.75 0.089 0.151 7.090 0.65730 30.0 SetUp -0.081 -0.019 7.345 0.50836 26.0 26.4 -0.261 -0.199 7.400 0.36542 23.1 23.5 -0.431 -0.369 7.000 0.253tip ---- ---- ---- ---- ---- 0.070*Minimumthicknessfor"N"bladesis3.170inch**Station9specificationsapplyto"N"bladesonly



Rev. 27 Sep/1161-13-33

Blade Model 10282(A) Blade Tip Figure 11-88

10282A



Rev. 27 Sep/1161-13-33

10282A(N)+2.5* Blade "T" SHANK RefertoFigure11-88Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.855 2.91312 ---- ---- ---- ---- 5.201 1.54118 43.1 44.1 .319 .381 6.495 0.92724 35.25 35.75 .089 .151 7.215 0.64530 30.0 SetUp -.081 -.019 7.530 0.50436 26.0 26.4 -.231 -.169 7.620 0.39642 23.1 23.5 -.351 -.289 7.620 0.34248 20.9 21.3 -.431 -.369 6.486 0.24750.25 20.1 20.5 -.460 -.399 ---- 0.181tip ---- ---- ---- ---- ---- 0.090*Refertoparagraph2.B.ofthischapter

10282A(N)+4* Blade "T" SHANK RefertoFigure11-88Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.855 2.91312 ---- ---- ---- ---- 5.201 1.54118 43.1 44.1 .319 .381 6.495 0.92724 35.25 35.75 .089 .151 7.215 0.64530 30.0 SetUp -.081 -.019 7.530 0.50436 26.0 26.4 -.231 -.169 7.620 0.39642 23.1 23.5 -.351 -.289 7.620 0.34248 20.9 21.3 -.431 -.369 7.010 0.24750.25 20.1 20.5 -.460 -.399 ---- 0.181tip ---- ---- ---- ---- ---- 0.050* Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33

10282A(N)+6* Blade "M","T" SHANKRefertoFigure11-88Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.855 2.91312 ---- ---- ---- ---- 5.201 1.54118 43.1 44.1 .319 .381 6.495 0.92724 35.25 35.75 .089 .151 7.215 0.64530 30.0 SetUp -.081 -.019 7.530 0.50436 26.0 26.4 -.231 -.169 7.620 0.39642 23.1 23.5 -.351 -.289 7.620 0.34248 20.9 21.3 -.431 -.369 7.010 0.24750.25 20.1 20.5 -.461 -.399 6.600 0.18152.5 19.5 19.9 -.501 -.439 5.000 0.109tip ---- ---- ---- ---- ---- 0.050* Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33


10290



Rev. 27 Sep/1161-13-33

10290N, +2 Blade "T" SHANKRefertoFigure11-89Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.879 3.17012 ---- ---- ---- ---- 5.332 1.56518 43.0 43.6 0.299 0.364 6.617 0.97524 35.7 36.1 0.027 0.092 7.396 0.65030 30.6 31.0 -0.132 -0.077 7.745 0.52536 27.7 28.1 -0.270 -0.215 7.721 0.45542 25.8 SetUp -0.422 -0.367 7.017 0.35548 23.6 23.8 -0.590 -0.535 5.052 0.220Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33



TI-4137

50.125

4642

LEADINGEDGE

2X4.00



Rev. 27 Sep/1161-13-33

10305 Blade "E" SHANK RefertoFigure11-90Distancefrombladebuttto"0"station=1.000"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.724 1.85512 ---- ---- ---- ---- 6.017 1.34518 42.5 43.1 0.228 0.293 7.096 0.86024 35.4 35.8 0.030 0.095 7.586 0.67030 29.5 29.9 -0.058 -0.003 7.844 0.69036 24.7 25.1 -0.182 -0.127 7.903 0.65542 21.0 SetUp -0.353 -0.298 7.804 0.52046 18.7 18.9 -0.504 -0.449 7.628 0.355Tip ---- ---- ---- ---- ---- 0.075 *Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33



CPS0604



Rev. 27 Sep/1161-13-33

10476(N)S* Blade "M" SHANK RefertoFigure11-91Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.860 2.94512 ---- ---- ---- ---- 5.341 1.69518 41.6 42.2 0.200 0.265 6.646 0.88824 35.3 35.7 -0.030 0.035 7.435 0.63530 30.0 SetUp -0.165 -0.110 7.802 0.55836 25.0 25.4 -0.285 -0.230 7.826 0.51042 20.8 21.0 -0.415 -0.360 7.297 0.44548 16.9 17.1 -0.577 -0.522 5.642 0.305Tip ---- ---- ---- ---- ---- 0.050*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


RO

TATI

ON

AL A

XIS

LEAD

ING

ED

GE


10477

1.75R50

.625

4236

47



Rev. 27 Sep/1161-13-33

10477(A)(S)* Blade “E” SHANK RefertoFigure11-92Distancefrombladebuttto“0”station=1.0”

Sta Angle FaceAlign. Width ThicknessMin Min Max Min Max Min Min8 ---- ---- ---- ---- 4.250 1.75512 ---- ---- ---- ---- 5.674 1.18518 40.3 40.9 0.167 0.232 6.818 0.72024 34.2 34.6 -0.025 0.040 7.494 0.54030 29.0 SetUp -0.137 -0.082 7.769 0.51536 24.2 24.6 -0.259 -0.204 7.647 0.48542 20.0 20.2 -0.391 -0.336 6.768 0.43047 16.8 17.0 -0.547 -0.492 4.995 0.295Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33



10478

50.6

2542

3648

LEADINGEDGE

ROTATIONALAXIS

+

2.00R.

0.880


APPENDIX C - BLADE SPECIFICATIONSPage11-252.1Rev.32Nov/1561-13-33

10478S Blade “E” SHANK RefertoFigure11-93Distancefrombladebuttto“0”station=1.0”

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.292 2.61912 ---- ---- ---- ---- 5.659 1.45218 40.9 40.3 0.200 0.135 6.827 0.80824 34.6 34.2 0.007 -0.058 7.533 0.61530 SetUp 29.0 -0.132 -0.187 7.835 0.54836 24.6 24.2 -0.254 -0.309 7.775 0.50342 20.2 20.0 -0.380 -0.435 7.119 0.43248 16.4 16.2 -0.577 -0.632 5.051 0.240Tip ---- ---- ---- ---- ---- 0.050 *Refertoparagraph2.B.ofthischapter


APPENDIX C - BLADE SPECIFICATIONSPage11-252.2Rev.32Nov/1561-13-33

0

10479

Blade Model 10479S Blade Tip Figure 11-93.1

50.6

2548

4236

LEADINGEDGE



Rev.32Nov/1561-13-33

E10479S Blade "E" SHANKRefertoFigure11-93.1Distancefrombladebuttto"0"station=1.000"




Rev. 27 Sep/1161-13-33



10541

3.00R



Rev. 27 Sep/1161-13-33

10541* Blade "D" SHANK RefertoFigure11-94Distancefrombladebuttto"0"station=1.000"




Rev. 27 Sep/1161-13-33

Blade Model 10574F Blade Tip Figure 11-95

CPS0605



Rev. 28 Sep/1261-13-33

10574* Blade "T" SHANK

NOTE: 10574*Bladeisobsoleteandhasbeenreplacedby 10574FSperAD87-15-05andHartzellPropellerInc. ServiceBulletin140().

10574A(S)* Blade "T" SHANK

NOTE: 10574A(S)*Bladeisobsoleteandhasbeenreplaced by10574FSperAD87-15-05andHartzellPropellerInc. ServiceBulletin140()

10574F(N)S* Blade "T" SHANKRefertoFigure11-95Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.840 2.94512 ---- ---- ---- ---- 4.944 1.44518 42.2 42.8 0.215 0.280 5.845 0.81524 36.3 36.7 -0.005 0.060 6.422 0.69030 30.0 SetUp -0..220 -0.165 6.780 0.59036 23.9 24.3 -0.430 -0.375 6.670 0.52542 19.2 19.4 -0.660 -0.605 6.080 0.47548 16.2 16.4 -0.900 -0.845 4.830 0.375Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33



10673


APPENDIX C - BLADE SPECIFICATIONSPage11-258.1Rev. 31 Jul/1461-13-33

10673(N), -2Q* Blade "T" SHANK RefertoFigure11-96Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.840 2.94512 ---- ---- ---- ---- 5.107 1.74518 42.0 43.0 0.190 0.265 5.954 0.94324 36.25 36.75 -0.010 0.055 6.386 0.72930 30.0 SetUp -0.245 -0.190 6.781 0.56136 23.9 24.3 -0.455 -0.400 6.871 0.44542 19.1 19.5 -0.685 -0.630 6.449 0.33548 16.1 16.5 -0.905 -0.850 5.301 0.205Tip ---- ---- ---- ---- ---- 0.060***Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapter ofthismanual**Appliesonlytothe10673(N)blade


APPENDIX C - BLADE SPECIFICATIONSPage11-258.2Rev. 31 Jul/1461-13-33


R2.70

53.2

548

4236

TPI-10702

LEADINGEDGE

ROTATIONALAXIS



Rev. 35 Nov/1761-13-33

10702(N)(S)* Blade "T" SHANKRefertoFigure11-96.1Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.761 3.17012 ---- ---- ---- ---- 4.931 1.54518 52.1 52.7 0.154 0.219 6.300 0.90024 48.1 48.5 -0.147 -0.082 7.165 0.60030 44.8 SetUp -0.357 -0.302 7.538 0.48036 41.9 42.3 -0.571 -0.516 7.437 0.36542 40.0 40.2 -0.781 -0.726 6.840 0.25548 38.7 38.9 -0.986 -0.931 5.764 0.155Tip ---- ---- ---- ---- ---- 0.045*Refertoparagraph2.B.ofthischapter.




LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AX

IS

52.1

2548

4236

30

R. 5

R 1

.500

TPI-J

M-0

0001

0



Rev. 39 Mar/2061-13-33

10703(S) Blade "E" SHANKRefertoFigure11-96.2

Angle FaceAlign. Width ThicknessSta Min Max Min Max Min Min8 - - - - - - - - - - - - - - - - 4.105 2.24512 - - - - - - - - - - - - - - - - 5.222 1.24518 51.3 51.9 0.198 0.263 6.501 0.80024 47.3 47.7 -0.024 0.041 7.269 0.56630 44.2 SET UP-0.180 -0.125 7.553 0.45736 41.5 41.9 -0.344 -0.289 7.360 0.34542 39.7 39.9 -0.499 -0.444 6.674 0.23548 38.6 38.8 -0.634 -0.579 5.502 0.142Tip - - - - - - - - - - - - - - - - - - - - 0.045*Refertoparagraph2.B.ofthischapter.



Rev. 27 Sep/1161-13-33


10876

10876AS-2Q

10876A(S)

10876A(N, S)-2Q



Rev. 27 Sep/1161-13-33

10876(N)* Blade "M" SHANKRefertoFigure11-97Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.86 2.68512 ---- ---- ---- ---- 5.34 1.37018 43.0. 43.6 0.185 0.250 6.65 0.82524 35.7 36.1 -0.045 0.020 7.44 0.60530 30.0 SetUp -0.189 -0.124 7.81 0.54036 25.2 25.6 -0.308 -0.253 7.83 0.48542 22.0 22.2 -0.435 -0.380 7.31 0.42548 19.4 19.6 -0.595 -0.540 5.67 0.28552 17.8 18.0 -0.726 -0.671 3.85 0.145Tip ---- ---- ---- ---- ---- 0.070*Refertoparagraph2.B.ofthischapter

10876A(N)(S)* Blade "M" SHANKRefertoFigure11-97Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.86 3.04512 ---- ---- ---- ---- 5.34 1.37018 43.0 43.6 0.175 0.250 6.64 0.82524 35.7 36.1 -0.055 0.020 7.44 0.60530 30.0 SetUp -0.194 -0.129 7.81 0.54036 25.2 25.6 -0.316 -0.253 7.83 0.48542 22.0 22.2 -0.443 -0.380 7.31 0.42548 19.4 19.6 -0.603 -0.540 5.67 0.28552 17.8 18.0 -0.734 -0.671 3.85 0.145Tip ---- ---- ---- ---- ---- 0.070*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


10876A(N)(S) -2Q Blade "T" SHANKRefertoFigure11-97Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.86 3.04512 ---- ---- ---- ---- 5.33 1.37018 43.0 43.6 0.175 0.250 6.62 0.82524 35.7 36.1 -0.055 0.020 7.40 0.60530 30.0 SetUp -0.194 -0.129 7.75 0.54036 25.2 25.6 -0.316 -0.253 7.74 0.48542 22.0 22.2 -0.443 -0.380 7.10 0.42548 19.4 19.6 -0.603 -0.540 5.20 0.28552 17.8 18.0 -0.799 -0.671 3.36 ----**Refertoparagraph2.M.oftheBladeAirfoilOverhaulchapter ofthismanual



Rev. 27 Sep/1161-13-33




Rev. 27 Sep/1161-13-33


Blade Models 10890, 10890( )-2 Blade Tip Figure 11-98

10890

3.00R.TY

P.

2XR

.3.75

5152.75

4842

54

10890()-2

10890

LEADINGEDGE



Rev. 27 Sep/1161-13-33

10890N* Blade "T" SHANKRefertoFigure11-98Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.5 ---- ---- ---- ---- 3.999 3.08510.5 ---- ---- ---- ---- ---- 2.15512 ---- ---- ---- ---- 5.341 1.69518 40.0 40.6 0.354 0.419 6.646 0.98024 33.4 33.8 0.117 0.182 7.440 0.71030 29.1 SetUp -0.053 0.002 7.788 0.56536 25.3 25.7 -0.200 -0.145 7.885 0.48542 22.3 22.5 -0.344 -0.289 7.746 0.40548 19.7 19.9 -0.501 -0.446 7.420 0.29551 18.5 18.7 -0.601 -0.546 7.175 0.195Tip ---- ---- ---- ---- ---- 0.045*Refertoparagraph2.B.ofthischapter

10890CN-2 Blade "T" SHANKRefertoFigure11-98Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.5 ---- ---- ---- ---- 3.996 3.08510.5 ---- ---- ---- ---- ---- 2.15512 ---- ---- ---- ---- 5.333 1.69518 38.3 38.9 0.354 0.419 6.618 0.98024 33.4 33.8 0.117 0.182 7.398 0.71030 29.1 SetUp -0.053 0.002 7.730 0.56536 25.3 25.7 -0.200 -0.145 7.783 0.48542 22.3 22.5 -0.344 -0.289 7.486 0.40548 19.7 19.9 -0.501 -0.446 6.706 0.29551 18.5 18.7 -0.601 -0.546 ---- 0.195Tip ---- ---- ---- ---- ---- 0.075



Rev. 27 Sep/1161-13-33

Blade Model 10891N Blade Tip Figure 11-99

10891

54

51

48

42

LEADINGEDGE


APPENDIX C - BLADE SPECIFICATIONSPage 11-266.1Rev. 36 Jun/1861-13-33

10891N* Blade "T" SHANKRefertoFigure11-99Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8.5 ---- ---- ---- ---- 3.999 2.88610.5 ---- ---- ---- ---- ---- 1.99312 ---- ---- ---- ---- 5.341 1.63118 41.2 41.8 0.368 0.433 6.646 1.01024 34.5 34.9 0.097 0.162 7.440 0.67030 29.8 30.2 -0.048 0.007 7.788 0.57736 26.5 26.9 -0.169 -0.114 7.885 0.54942 24.3 SetUp -0.296 -0.241 7.615 0.50248 22.2 22.4 -0.476 -0.421 6.715 0.34351 21.1 21.3 -0.595 -0.540 5.728 0.203Tip ---- ---- ---- ---- ---- 0.045*Refertoparagraph2.B.ofthischapter


APPENDIX C - BLADE SPECIFICATIONSPage 11-266.2Rev. 36 Jun/1861-13-33


LEA

DIN

G E

DG

E

RO

TATI

ON

AL

AX

IS

4852

.875

R2.

94

R2.

94

4236

3051

TPI-J

M-0

0004

6



Rev. 36 Jun/1861-13-33

10991 Blade "E" SHANKRefertoFigure11-99.1

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 4.258 2.24512 ---- ---- ---- ---- 5.660 1.34518 39.7 40.3 0.257 0.322 6.833 0.92524 33.5 33.9 0.011 0.076 7.535 0.63630 29.3 SETUP -0.123 -0.068 7.826 0.56736 26.0 26.4 -0.242 -0.187 7.865 0.54342 23.8 24.0 -0.375 -0.320 7.505 0.48148 21.8 22.0 -0.569 -0.514 6.413 0.295Tip ---- ---- ---- ---- ---- 0.045*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


11276

3.25 R

3.50 R

4.00 R

5154

.548

4254

11276-4

RO

TATI

ON

AL

AX

IS

LEA

DIN

G E

DG

E11276-3

56



Rev. 36 Jun/1861-13-33

11276N(S)* Blade "M" SHANK11276(C)N-3* Blade**RefertoFigure11-100Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.881 3.04512 ---- ---- ---- ---- 5.341 1.64518 43.0 43.6 0.260 0.320 6.646 0.98024 35.8 36.0 -0.090 -0.030 7.441 0.69030 29.9 30.1 -0.240 -0.180 7.810 0.58536 25.1 25.3 -0.380 -0.320 7.891 0.51542 21.5 SetUp -0.510 -0.450 7.611 0.45548 18.4 18.6 -0.630 -0.570 6.938 0.38551** 17.0 17.2 -0.720 -0.660 6.349 0.30254** 15.7 15.9 -0.840 -0.780 5.411 0.175Tip ---- ---- ---- ---- ---- 0.070*Refertoparagraph2.B.ofthischapter **Doesnotapplytoblade11276(C)N-3

11276NSA Blade "M" SHANKRefertoFigure11-100Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.879 3.04512 ---- ---- ---- ---- 5.332 1.64518 43.0 43.6 0.245 0.310 6.619 0.98024 35.7 36.1 -0.096 -0.031 7.401 0.69030 29.8 30.2 -0.250 -0.195 7.759 0.58536 25.0 25.4 -0.387 -0.332 7.810 0.51542 21.5 SetUp -0.517 -0.462 7.443 0.45548 18.4 18.6 -0.640 -0.585 6.498 0.38551 17.0 17.2 -0.727 -0.675 5.742 0.30254 15.7 15.9 -0.845 -0.790 4.720 0.175Tip ---- ---- ---- ---- ---- 0.070*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33


11296

3.25 R56

4842

54

RO

TATI

ON

AL

AX

IS

LEA

DIN

G E

DG

E



Rev. 27 Sep/1161-13-33

11296N* Blade "M" SHANKRefertoFigure11-101Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.763 3.04512 ---- ---- ---- ---- 4.763 1.64518 42.5 43.1 0.245 0.310 5.832 0.98024 35.2 35.6 -0.096 -0.031 7.196 0.69030 29.8 SetUp -0.250 -0.195 7.810 0.58536 25.7 26.1 -0.387 -0.332 7.891 0.51542 22.6 23.0 -0.517 -0.462 7.611 0.45548 19.6 19.8 -0.640 -0.585 6.938 0.38554 17.4 17.6 -0.845 -0.790 5.411 0.175tip ---- ---- ---- ---- ---- 0.070*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33



11691



Rev. 27 Sep/1161-13-33

11691N(S)* Blade "M" SHANKRefertoFigure11-102Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.577 3.38512 ---- ---- ---- ---- 4.929 2.04518 42.5 43.1 0.402 0.467 6.439 1.08024 37.4 37.8 0.140 0.205 7.306 0.76030 33.0 33.4 -0.013 0.042 7.764 0.65036 29.1 29.5 -0.154 -0.099 7.770 0.58042 26.1 SetUp -0.297 -0.242 7.358 0.50048 23.3 23.5 -0.446 -0.391 6.526 0.40554 21.2 21.4 -0.635 -0.580 4.861 0.225Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33



11692



Rev. 27 Sep/1161-13-33

11692N* Blade "M" SHANKRefertoFigure11-103Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.577 3.38512 ---- ---- ---- ---- 4.929 2.04518 42.5 43.1 0.407 0.472 6.439 1.09024 37.4 37.8 0.173 0.238 7.306 0.82630 33.0 33.4 0.052 0.107 7.764 0.78236 29.1 29.5 -0.072 -0.017 7.770 0.74542 26.1 SetUp -0.215 -0.160 7.358 0.66548 23.3 23.5 -0.397 -0.342 6.526 0.50554 21.2 21.4 -0.621 -0.566 4.861 0.255Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33

Blade Model 11693N(S) Blade Tip Figure 11-104

11693

ROTATIONALAXIS

LEADINGEDGE



Rev. 27 Sep/1161-13-33

11693N(S)* Blade "M" SHANKRefertoFigure11-104Distancefrombladebuttto"0"station=4.512"

Sta Angle FaceAlign. Width Thickness Min Max Min Max Min Min8 ---- ---- ---- ---- 3.577 3.38512 ---- ---- ---- ---- 4.929 2.04518 42.5 43.1 0.398 0.463 6.439 1.09024 37.4 37.8 0.156 0.221 7.306 0.82630 33.0 33.4 0.026 0.081 7.764 0.78236 29.1 29.5 -0.107 -0.052 7.906 0.74542 26.1 SetUp -0.260 -0.205 7.697 0.66548 23.3 23.5 -0.449 -0.394 7.123 0.50554 21.2 21.4 -0.681 -0.626 5.862 0.255Tip ---- ---- ---- ---- ---- 0.075*Refertoparagraph2.B.ofthischapter



Rev. 27 Sep/1161-13-33




APPENDIX D - BLADE TIP SPECIFICATIONSPage 12-1

Rev. 27 Sep/1161-13-33

1. BladeTipSpecifications...........................................................................Relocated

NOTE: ThebladetipspecificationsinformationhasbeenrelocatedtoAppendixCofthismanual.

CONTENTS-APPENDIXD-BLADETIPSPECIFICATIONS


APPENDIX D - BLADE TIP SPECIFICATIONSPage 12-2

Rev. 27 Sep/1161-13-33



APPENDIX E - ROLLING MACHINEPage 13-1

Rev. 39 Mar/2061-13-33

APPENDIX E - ROLLING MACHINE - CONTENTS

1. General Information ..........................................................................................13-32. Principles of Operation .....................................................................................13-3

A. DT-1724, DT-1724-1, and DT-1724-2..........................................................13-3

B. DT-1724-3( ) ................................................................................................13-4

C. DT-1724-5 ...................................................................................................13-53. DT-1724-3( ) Rolling Machine ...........................................................................13-9

A. Electrical Switch Operations........................................................................13-9B. Assembly After Receipt of New or Exchanged Units.................................13-10C. Routine Maintenance and Checks ............................................................13-11D. Functional Check Without Blade Installed .................................................13-13E. Roller Assembly Setup Procedures ...........................................................13-21F. Blade Inspection ........................................................................................13-27G. Rolling Process of the DT-1724-3( ) Rolling Machine ...............................13-27H. Sample Program .......................................................................................13-29

4. DT-1724-5 Rolling Machine ............................................................................13-34

A. Basic Machine Operation ..........................................................................13-34B. Assembly After Receipt of New or Exchanged Units.................................13-35C. Routine Maintenance and Checks ............................................................13-36D. Program Selection Procedure ...................................................................13-38E. Blade Inspection ........................................................................................13-38F. Rolling Process of the DT-1724-5 Rolling Machine ...................................13-39G. Sample Program .......................................................................................13-41H. Blade Data Printing ...................................................................................13-42



Rev. 36 Jun/1861-13-33

LIST OF FIGURES

Rolling Machine DT-1724-3( )..........................................................Figure 13-1 .........13-6

Rolling Machine DT-1724-3( ) Roller Head Assembly .....................Figure 13-2 .........13-7

Rolling Machine DT-1724-3( ) Carriage Traverse Motor..................Figure 13-3 .........13-8

"M", "P", and "R" Shank Rolling Characteristics ..............................Figure 13-4 .......13-14

"T", "W", and "Z" Shank Rolling Characteristics ..............................Figure 13-5 .......13-15

"D" and "Y" Shank Rolling Characteristics .....................................Figure 13-6 .......13-16

"E" Shank Metal Blade Rolling Characteristics ...............................Figure 13-7 .......13-17

"MV" Shank Rolling Characteristics .................................................Figure 13-8 .......13-18

"C" Shank Rolling Characteristics ...................................................Figure 13-9 .......13-19

DT-1724+34 Blade Holding Fixture Modification .............................Figure 13-10 .....13-22

DT-1724-5 Automated Rolling Machine - Front View ......................Figure 13-11 .....13-30

HMI ..................................................................................................Figure 13-12 .....13-31

DT-1724-5 Automated Rolling Machine - Without Cage ..................Figure 13-13 .....13-32

DT-1724-5 Automated Rolling Machine - Rear View .......................Figure 13-14 .....13-33

LIST OF TABLES

Rolling Machine DT-1724-3( ) Spacer, Expansion Sleeve, and Clamp Applications .............................................................Table 13-1 ........13-20



Rev. 36 Jun/1861-13-33

1. General Information


A. The DT-1724-( ) rolling machine has been provided in five basic design configurations, beginning with the DT-1724 (no dash number). Improvements have been incorporated into the design of the unit throughout the years. Each subsequent design change raised the dash number by one (that is, DT-1724-1, DT-1724-2, etc.).

B. The current new design configuration number is DT-1724-5. DT-1724-( ) machines certified after August 1987 are issued certificates and are permitted to operate in accordance with the "Requirements for Certification" listed in the Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02). Only machines overhauled by Hartzell Propller Inc. will be recertified and approved for field use.

C. Compressive rolling of Hartzell Propeller Inc. aluminum blades must be performed only with DT-1724-3( ) or DT-1724-5 rolling machines that have been manufactured by Hartzell Propeller Inc. and are on the Cold Compression Rolling Approval Listing in the Sample Program Approvals on the Hartzell Propeller Inc. website.

2. Principles of Operation

CAUTION: ROLLING MACHINE MODELS DT-1724, DT-1724-1, AND DT-1724-2 ARE OBSOLETE AND MUST NOT BE USED TO ROLL BLADES.

A. DT-1724, DT-1724-1, and DT-1724-2

(1) These units are obsolete and are no longer approved for use. These models shall not be rebuilt or upgraded to a DT-1724-3( ) or DT-1724-5 configuration.



Rev. 36 Jun/1861-13-33

B. DT-1724-3( )

(1) The function of the DT-1724-3( ) rolling machine is to provide a controlled process of compression rolling the radius of the retention shoulder of Hartzell Propeller Inc. "C" (non-counterweighted only), "D", "E", "M", "MV", "P", "R", "T", "W", "Y", and "Z" shank single shoulder aluminum propeller blades. The equipment rotates the blade, using a geared motor-transmission combination with a face plate and collet to retain the blade. The initial rotation of this assembly is controlled by a microswitch activated by the carriage motion. The DT-1724-3( ) rolling machine can be upgraded to a DT-1724-5 at the Hartzell Propeller Inc. factory.

NOTE 1: A separate conversion kit is required to roll non-countereweighted "C" shank blades. The DT-1724-3( ) Rolling Machine cannot roll "C" shank blades with counterweights. Refer to Setup Procedure for "C" Shank Blades in this chapter.

NOTE 2: A separate mounting kit and a modification to the blade holding fixture are required to roll "E" shank blades. Refer to Setup Procedure for "E" Shank Metal Blades in this chapter.

(2) The roller portion of the unit consists of a roller head that rotates to follow the blade retention radius. This unit is mounted on a carriage that moves parallel to the blade centerline to extend the rolled area beyond the radius.

(3) The roller assembly uses a small reversible motor to drive a geared wheel to which the roller head is attached. As this wheel rotates, it rotates the roller head through the required radius. The movement of the roller is controlled by a microswitch placed at each end of the travel.

(4) The carriage movement is controlled automatically by an electric motor. The rolling operation begins with the carriage full forward (nearest the blade butt). Once the roller head has proceeded through the radius portion of the rolling process, the carriage will begin to move toward the tip of the blade (aft), parallel to the blade centerline. The roller pressure is gradually decreased to zero. The reduction of roller pressure is accomplished by releasing the hydraulic pressure, which is automatically controlled by an air-ball check valve installed in the air line.

(5) The carriage traverse motor controls the forward and aft movement of the carriage. Start and stop action is controlled by microswitches located at the stops at either end of the carriage travel. The forward switch activates the rolling action when the carriage has reached the full forward position. The aft switch stops the carriage movement at the home position.



Rev. 36 Jun/1861-13-33

C. DT-1724-5

(1) The function of the DT-1724-5 rolling machine is to provide a controlled process of compression rolling the radius of the retention shoulder of Hartzell Propeller Inc. "C", "D", "E", "M", "MV", "P", "R", "T", "W", "Y", and "Z" shank single shoulder aluminum propeller blades. The equipment rotates the blade, using a geared motor-transmission combination with a face plate to retain the blade. The initial rotation of this assembly is controlled by a Programmable Logic Controller (PLC) and a library of blade shank specific recipes.

(2) The roller portion of the unit consists of a roller head that rotates to follow the blade retention radius. This unit is mounted on a carriage that moves parallel to the blade centerline to extend the rolled area beyond the radius.

(3) The roller assembly uses a small reversible stepper motor to drive a 90 degree gearbox to which the roller head is attached. As the stepper motor rotates, it rotates the roller head through the required radius. The movement of the roller angle is controlled by the PLC.

(4) The carriage movement is controlled automatically by an electric motor. The rolling operation begins with the carriage in the lowest position, nearest to the blade butt. Once the roller head has proceeded through the radius portion of the rolling process, the carriage will begin to move toward the tip of the blade, parallel to the blade centerline. The roller pressure is gradually decreased to zero. The reduction of the pressure is accomplished by releasing the hydraulic pressure of the air-to-oil booster, through the PLC controlled air pressure regulator.

(5) The carriage traverse motor controls the vertical movement of the carriage. The motor drives a linear actuator that moves the carriage up or down. Start and stop action is controlled by the PLC and determined by the applicable blade recipe.

(6) The roller portion of the machine can be driven to or away from the blade to set diameter spacing. This automatic action eliminates the need for diameter spacers as found in the previous versions of the DT-1724-( ) Machine. Once the machine automatically positions this axis, the PLC activates an electromagnetic brake to hold position during the roll cycle. Diameter spacing positions are controlled by the PLC and determined by the applicable blade recipe.



Rev. 36 Jun/1861-13-33

Rolling Machine DT-1724-3( ) Figure 13-1

Start Cycle Switch

aps0

925

F.R.L. Unit

Blade Drive Motor

Main Power SwitchBlade Drive Motor Switch

Carriage Aft Stop Switch

CarriageFORWARD DIRECTION AFT DIRECTION



Rev. 36 Jun/1861-13-33

Rolling Machine DT-1724-3( ) Roller Head AssemblyFigure 13-2

Carriage Return Switch

CarriageBlade Drive Motor

Switch

Roller Motor Limit Switch

Roller Support

Arm

Carriage

Blade Drive Motor Switch

Roller Motor Aft Direction Limit Switch

Roller Head Drive Motor

W10

376



Rev. 36 Jun/1861-13-33

Rolling Machine DT-1724-3( ) Carriage Traverse MotorFigure 13-3

Carriage Traverse Motor

Worm Gear

Drive Gear

W10

375



Rev. 36 Jun/1861-13-33

3. DT-1724-3( ) Rolling Machine

A. Electrical Switch Operations

Refer to Figures 13-1 through 13-3

(1) Main Power Switch

(a) Supplies power to all circuits.

(2) Start Cycle Switch

(a) Starts the rolling machine cycle.

(3) Carriage Aft Stop Switch

(a) Supplies power to the carriage traverse motor.

(b) Stops aft (farthest from blade butt) movement of the carriage.

(4) Blade Drive Motor Switch

(a) Stops the blade drive motor when the carriage moves aft, opening the blade drive motor switch to stop the carriage before possible contact with the blade counterweight.

(5) Carriage Forward Stop Switch (not shown)

(a) Stops forward movement of the carriage.

(b) Provides power to the roller head drive motor.

(c) Trips the contact relays, which in turn starts the blade drive motor and allows pressure to be applied.

(6) Roller Motor Forward Direction Limit Switch (under head cover)

(a) Limits travel of the roller head in reverse direction.

NOTE: Reverse direction is the direction in which the roller head moves at the beginning of the rolling cycle.

(7) Carriage Return Switch

(a) The carriage return switch is positioned on the roller support arm and is activated when the roller body makes contact, closing the switch.

(b) When the switch is closed, power is provided to the carriage traverse motor, starting the carriage return.

(8) Roller Motor Aft Direction Limit Switch (under head cover)

(a) As the roller completes its arc, the roller motor aft direction switch limits and stops the travel of the roller head by cutting power to the roller head drive motor.



Rev. 36 Jun/1861-13-33

B. Assembly After Receipt of New or Exchanged Units

Refer to Figure 13-1.

(1) Documentation

(a) Make sure that the information on the rolling machine certificate is correct.

(2) Accessory Parts

(a) The following accessory parts are packaged separately from the rolling machine. Make sure that all of these parts have been received, before beginning assembly of the machine.

PART NUMBER DESCRIPTION

AST-2867 Spacer - (Stamp Serial Number and arrow)

AST-2867-1 Spacer - (Stamp Serial Number and arrow)



AST-2865 Spacer 0.2500 Radius

AST-2865-1 Spacer 0.3750 Radius

BST-2866 Expansion Sleeve

BST-2866-1 Expansion Sleeve

BST-2869 Spacer

Standard Lock Screw - (Paint red)

DT-1724+88 Handle

(3) Supply 110 volts to the master switch box located adjacent to the blade drive motor. This is the only power connection required.

NOTE: Unless otherwise stated at the time of order, all machines are shipped with 110 volt 60 cycle systems. Conversion units are available for foreign use with step down transformers, which are designated by a letter “F” following the machine part number (e.g., DT-1724-3F - foreign). Units with 110 volt 60 cycle systems are designated by a letter “D” following the machine part number (e.g., DT-1724-3D - domestic).

(4) Remove the electrical supply cord, if a step down transformer is used and a permanent supply connection is provided.

(5) The main power switch is fused to act as a protective device. Push down on the master switch to reset it, if required.

(6) Connect the air line to the F.R.L. unit.

NOTE: Air line pressure must be 90-130 psi (6.20-8.96 bar).



Rev. 36 Jun/1861-13-33

C. Routine Maintenance and Checks

NOTE: For additional information about the maintenance, repair, and troubleshooting of the DT-1724-3( ) rolling machine, refer to Hartzell Propeller Inc. Blade Shank Rolling Machine Manual 128 (61-00-28).

(1) Cleaning


CAUTION 1: DISCONNECT ALL ELECTRIC AND AIR SUPPLIES BEFORE CLEANING.

CAUTION 2: COVERING THE MACHINE WHEN NOT IN USE IS RECOMMENDED.

(a) Clean all machine components as indicated. Depending on the condition of the machine, certain cleaning methods may or may not be required. The order in which components are cleaned may vary.

1 An abrasive pad CM47 and solvent CM23 may be used as necessary to clean parts.

2 Clean motors and other painted surfaces with a mild solvent, such as CM23, that will not remove the paint.

3 Using a putty knife, scrape excess grime and grease from accessible areas.

CAUTION: USE CARE NOT TO BEND THE ARMS OR ALTER THE ORIGINAL POSITIONS OF THE LIMIT SWITCHES. THE LIMIT SWITCHES PLAY A KEY ROLE IN THE FUNCTION OF THE MACHINE.

4 Keep all limit switches clean and free of dust, contaminants, and corrosion.

(2) Lubrication

CAUTION: USE OF AIRCRAFT HYDRAULIC FLUID (MIL-H-5606) IS NOT PERMITTED.

(a) Refill the lubricator in the F.R.L. unit with the specified oil, as necessary. For oil specifications, refer to the section "Oil Specifications" in this chapter.



Rev. 36 Jun/1861-13-33

1 If the lubricator is not using oil, or is using more than the required amount of oil, make the necessary adjustments in accordance with the Machine Setup and Testing chapter of Hartzell Propeller Inc. Blade Shank Rolling Machine Manual 128 (61-00-28).

2 Drain the water separator as necessary to keep the rolling machine free of moisture.

(b) Before each use, check the level of hydraulic oil in the booster.1 To fill the reservoir of the booster:

a Remove the reservoir cap.b Fill the reservoir to the applicable level with hydraulic oil, such

as Mobil DTE 24, Shell TELLUS 23, Chevron EP22, Pro-Cool AW 46, or automatic transmission fluid.

2 A low level of hydraulic oil in the booster with no evidence of external leakage may be an indication of internal oil leakage in the booster. Refer to the Troubleshooting chapter of Hartzell Propeller Inc. Blade Shank Rolling Machine Maintenance Manual 128 (61-00-28).

(3) Roller Wheel Inspection(a) Before each use, inspect the roller wheel for the following conditions:

nicks, excessive wear, flat spots in the radius, corrosion pitting, or tearing of the material.1 If conditions exist, replace the roller wheel in accordance with the

Repair and Replace chapter of Hartzell Propeller Inc. Blade Shank Rolling Machine Manual 128 (61-00-28).

NOTE: The condition of the roller wheel surface and the roller wheel bearing have the greatest impact on the surface finish and appearance of the rolled surface.

(4) Pressure Gauge Inspection(a) If the pressure gauge does not function correctly, refer to the

Troubleshooting and Repair and Replace chapters of Hartzell Blade Shank Rolling Machine Manual 128 (61-00-28).

NOTE: A pressure gauge purchased separately through Hartzell Propeller Inc. is not certified when shipped.

(5) Oil Requirements(a) The oil used in the F.R.L. unit lubricator must be non-detergent oil and

must have a kinematic viscosity rating that meets one of the following three requirements:1 SAE 10 or SAE 10W (Society of Automotive Engineers)2 150 SUS (Saybolt Universal Second [often SUS or SSU] at

210° F [98° C] degrees in accordance with ASTM D156-02)



Rev. 36 Jun/1861-13-33

3 ISO VG32 (International Standardization Organization viscosity grading system for lubricants of 32 cSt (centistokes) at 40 deg C.)

(b) An additional feature (not required) that also prolongs the life of the air contact components is that the lubricant have a capability to absorb up to 10 percent of its weight in water to avoid rust or corrosion.

D. Functional Check Without Blade Installed Refer to Figures 13-1 through 13-3.

(1) With air and electrical connections complete, the carriage will be in the aft position (farthest from blade butt). All units are shipped with the carriage in the full aft position.

WARNING: BE SURE THE COLLET DRAW BAR HAS BEEN REMOVED BEFORE STARTING THE MACHINE.

(2) Turn the main power switch to the ON position.

WARNING: USE EXTREME CAUTION WHEN ACTIVATING THE START CYCLE SWITCH. AS THE BLADE DRIVE MOTOR IS ACTIVATED, THE BLADE DRIVE WILL ROTATE WITHOUT WARNING, AND COULD CAUSE INJURY.

(3) Push the START cycle switch. When the carriage moves full forward, the blade drive motor will be activated and the blade drive assembly will begin to rotate. The forward motion will also close the ball-check valve, permitting the accumulated hydraulic pressure to get to the pressure recorded on the 100885 label located on the booster output pressure gauge in accordance with Hartzell Propeller Inc. Blade Shank Rolling Machine Maintenance Manual 128 (61-00-28).

(4) When the carriage forward movement begins, the carriage forward stop switch will activate the roller head assembly, beginning its aft rotational movement.

(5) When the roller head is perpendicular to the blade centerline, the roller arm will contact the carriage return switch, activating the carriage traverse motor. The carriage will begin to move aft (toward the blade tip).

(6) As the carriage moves aft, the ball-check valve will open, and the hydraulic pressure will start to bleed off.

CAUTION: PRESSURE BLEED-OFF MUST BE ACCOMPLISHED IN A MINIMUM OF 60 TO 80 SECONDS TO ASSURE A SMOOTH TRANSITION AREA IN THE ROLLING SURFACE.

(7) Using a stop watch, verify that the pressure bleed-off time is between 60 and 80 seconds.

(8) As the carriage continues to move aft, the blade drive motor switch will be deactivated and the blade drive assembly will stop.

(9) After the carriage traverse motor has completed its cycle, turn off the main power switch.



Rev. 36 Jun/1861-13-33

"M", "P", and "R" Shank Rolling Characteristics Figure 13-4

* Pressure must bleed to zero PSI before the blade stops rotating.

AP

S05

10B

Rolled at full pressure

Pressure must flare out to zero compression in this zone*

Pressure transition zone

18 +3/-0 Degrees Roller Angle Start

Critical Area 0.3735 Inch (9.487 mm) Radius

0.500 ± 0.060 Inch (12.70 ± 1.5 mm) 0.220

Inch (5.59 mm) Min.




Rev. 36 Jun/1861-13-33

"T", "W", and "Z" Shank Rolling Characteristics Figure 13-5

Rolled at full pressure0.375 ± 0.075 Inch (9.53 ± 1.91 mm)

Critical Area 0.250 Inch (6.35 mm) Radius

18 +3/-0 Degrees Roller angle start

AP

S05

07B

0.220 Inch (5.59 mm) Min.


Pressure must flare out to zero compression within this zone *





Rev. 36 Jun/1861-13-33

"D" and "Y" Shank Rolling Characteristics Figure 13-6


AP

S05

08B

Critical area 0.415 Inch (10.54 mm) Radius

Pressure must flare out to zero compression within this zone *


Rolled at full pressure 0.540 ± 0.075 Inch (13.72 ± 1.91 mm)

0.220 Inch (5.59 mm) Min.





Rev. 36 Jun/1861-13-33

"E" Shank Metal Blade Rolling Characteristics Figure 13-7

AP

S05

09A



Critical area0.437 Inch (11.10 mm)

Pressure must flare out to zero compression within this zone*

0.570 Inch (14.48 mm) MaximumRolled at full pressure

0.562 ± 0.075 Inch (14.27 ± 1.91 mm) 0.220

Inch (5.59 mm) Min.




Rev. 36 Jun/1861-13-33

"MV" Shank Rolling CharacteristicsFigure 13-8



Critical area 0.250 Inch (6.35 mm) radius


0.220 Inch (5.59 mm) Min.

0.375 ± 0.075 Inch (9.53 ± 1.91 mm) Pressure must flare out

to zero compression within this zone *

Rolled at full pressure


W10

097



Rev. 36 Jun/1861-13-33


Pressure Transition Zone

Pressure must flare out to zero compression

within this zone *

Critical area rolled at full pressure

0.562 ± 0.075 Inch (14.27 ±

1.91 mm)

0.220 Inch (5.59 mm)Min.

0.432 Inch (10.97 mm)

Radius


"C" Shank Rolling CharacteristicsFigure 13-9

TPI-1

33-0

48



Rev. 36 Jun/1861-13-33

Rolling Machine DT-1724-3( ) Spacer, Expansion Sleeve, and Clamp ApplicationsTable 13-1

Rolling Machine Adaptor Usage

Shank

BS

T-2866B

ST-2866-1

AS

T-2865A

ST-2865-1

BS

T-2872B

ST-2869

AS

T-2867-1A

ST-2867-2

AS

T-2867-3A

ST-2867

DT-1724+160

DT-1724+161

DT-1724+162

DT-1724+164

DT-1724+31

DT-1724+33

DT-1724+34

DT-1724+171

DT-1724+172

DT-1724+173

BS

T-2869-1

"E" x x x x x x x x

"C" x x x x x x

"D" x x x x x

"M" x x x x x x x x

"MV" x x x x x x

"P" x x x x x x x x

"R" x x x x x x x x

"T" x x x x x x x

"W" x x x x x x x

"Y" x x x x x

"Z" x x x x x x x



Rev. 36 Jun/1861-13-33

E. Roller Assembly Setup Procedures

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.

NOTE: Refer to Table 13-1 to determine the correct spacers and expansion sleeve for the type of blade to be rolled. Dimensional characteristics of the different blade types are shown in Figures 13-4 through 13-9.

(1) Setup Procedure for “D” and “Y” Shank Blades

NOTE: No special expansion sleeves are required.

(a) Loosen the adjustment screws and move the rolling head assembly to allow installation of the AST-2867 spacer.

(b) Place AST-2867 spacer between rolling head assembly and AST-2868 plate.

(c) Reposition rolling head assembly against spacer and tighten adjustment screws.

(d) Remove BST-2869 sleeve from roller limit pin, if installed.

(e) Install the BST-2872 spacer on the roller arm, opposite plunger “P”.

NOTE: When installing or removing a counterweighted blade, always do so with the counterweight knob away from the roller arm.

(f) Install the blade on the fixture, tighten the collet with a draw bar, then remove the draw bar.

NOTE: If the blade does not completely tighten, adjust the Allen head screw in the end of the blade mounting collet.



Rev. 36 Jun/1861-13-33

(2) Setup Procedure for “T” Shank Blades

Refer to Table 13-1.

(a) Install the AST-2865 spacer and the BST-2866 expansion sleeve over the collet.

(b) Loosen the adjustment screws (7) and move the rolling head assembly to allow installation of the AST-2867-2 spacer.

(c) Place the AST-2867-2 spacer between the rolling head assembly and the AST-2868 plate.

(d) Reposition the rolling head assembly against the spacer and tighten the adjustment screws.

(e) Install the BST-2869 sleeve onto the roller limit pin.

(f) Remove the BST-2872 spacer from roller arm, if installed.

(g) Install the blade on the fixture, tighten the collet with a draw bar, then remove the draw bar.

NOTE: If the blade does not completely tighten, adjust the Allen head screw in the end of the blade mounting fixture.

DT-1724+34 Blade Holding Fixture Modification Figure 13-10

0.250 Inch (6.35 mm)

Remove this area

AP

S06

59



Rev. 36 Jun/1861-13-33

(3) Setup Procedure for “W” and “Z” Shank BladesRefer to Table 13-1.(a) Install the AST-2865 spacer and the BST-2866-1 sleeve over the collet.(b) Loosen the adjustment screws and move the rolling head assembly to

allow installation of the AST-2867-2 spacer.(c) Place the AST-2867-2 spacer between the rolling head assembly and the

AST-2868 plate.(d) Reposition the rolling head assembly against the spacer and tighten the

adjustment screws.(e) Install the BST-2869 sleeve onto roller limit pin.(f) Remove the BST-2872 spacer from roller arm, if installed.(g) Install the blade on the fixture, tighten the collet with a draw bar, then

remove the draw bar.

NOTE: If the blade does not completely tighten, adjust the Allen head screw in the end of blade mounting fixture.

(4) Setup Procedure for “M” Shank BladesRefer to Table 13-1.(a) Install the AST-2865-1 spacer and BST-2866 expansion sleeve over the

collet.(b) Loosen the adjustment screws and move the rolling head assembly to

allow installation of the AST-2867-1 spacer.(c) Place the AST-2867-1 spacer between the rolling head assembly and the

AST-2868 plate.(d) Reposition the rolling head assembly against the spacer and tighten the

adjustment screws.(e) Install the BST-2869 sleeve onto the roller limit pin.(f) Install the BST-2872 spacer onto the roller arm, opposite plunger “P”.


NOTE: If the blade does not completely tighten, adjust the Allen head screw in the end of blade mounting collet.



Rev. 36 Jun/1861-13-33

(5) Setup Procedure for “P” and “R” Shank Blades


(a) Install the AST-2865-1 spacer and the BST-2866-1 expansion sleeve over the collet.

(b) Loosen the adjustment screws and move the rolling head assembly to allow installation of the AST-2867-1 spacer.

(c) Place the AST-2867-1 spacer between the rolling head assembly and the AST-2868 plate.

(d) Reposition the rolling head assembly against the spacer and tighten the adjustment screws.

(e) Install the BST-2869 sleeve onto the roller limit pin.

(f) Install the BST-2872 spacer onto the roller arm, opposite plunger “P”.


NOTE: If the blade does not completely tighten, adjust the Allen head screw in the end of blade mounting collet.

(6) Setup Procedure for “E” Shank Metal Blades


NOTE 1: DT-1724-3( ) rolling machines manufactured after July 1996 require no new provisions to roll "E" shank blades. Overhauled DT-1724-3( ) machines will have "E" shank capacity.

NOTE 2: DT-1724-3( ) machines manufactured before July 1996, or machines that have not been overhauled since July 1996 will need to be modified or adapted to roll "E" shank blades, according to the following procedure.

(a) Change the existing DT-1724+34 Blade Holding Fixture (one time only). This modification will not require any changes in the setup procedures for other styles of blades.

1 Using a surface grinder, remove 0.250 inch (6.35 mm) from the end of the DT-1724+34 Blade Holding Fixture (Refer to Figure 13-10).

2 Using black oxide coat or other suitable method, corrosion protect the exposed area of the Blade Holding Fixture after material removal (optional).



Rev. 36 Jun/1861-13-33

(b) Acquire the necessary parts for changing each DT-1724-3( ) rolling machine:

Part Number Keyword Quantity

DT-1724+160 collet screw 1/machine

DT-1724+161 "E" shank collet 1/machine

DT-1724+162 "E" shank spacer 1/machine

(c) Remove the collet screw, collet, and spacer DT-1724+33 if applicable, from the rolling machine.

(d) Install the DT-1724+162 spacer and DT-1724+161 collet.

(e) Tighten the collet with DT-1724+160 collet screw.

NOTE: The DT-1724+160 collet screw is special and is necessary only for the DT-1724+161 collet. The standard collet screw is used for all other blade applications.

(f) Loosen the adjustment screws and move the rolling head assembly to allow installation of the AST-2867-1 spacer.

(g) Place the AST-2867-1 spacer between the rolling head and AST-2868 plate.

(h) Reposition the rolling head assembly against the spacer, and tighten the adjustment screws.

(i) Install the BST-2872 spacer on the roller arm, opposite the plunger "P".

(j) Install the blade on the fixture, tighten the collet with the draw bar, then remove the draw bar.

1 If the blade does not completely tighten, adjust the Allen head screw in the end of the blade mounting collet.

(7) Setup Procedure for “MV” Shank Blades


(a) Remove the collet screw, collet, and DT-1724+33 spacer.

(b) Install the DT-1724+164 spacer, collet, and collet screw.

(c) Loosen the adjustment screws and move the rolling head assembly to allow installation of the AST-2867-2 spacer.

(d) Place the AST-2867-2 spacer between the rolling head assembly and the AST-2868 plate.

(e) Reposition the rolling head assembly against the spacer, and tighten the adjustment screws.

(f) Install the BST-2869 sleeve onto the roller limit pin.



Rev. 36 Jun/1861-13-33

(g) Remove the BST-2872 spacer from the roller arm, if installed.

(h) Install the blade on the fixture, tighten the collet with a draw bar, then remove the draw bar.

NOTE: If the blade does not completely tighten, adjust the Allen head screw in the end of the blade mounting fixture.

(8) Setup Procedure for "C" Shank Blades


NOTE: Refer to the Blade Shank Rolling Machine Maintenance Manual 128 (61-00-28), Machine Setup and Testing for instructions on calibrating the rolling machine baseline for a "Y" shank test specimen and one-time machine setup instructions for "C" shank blades.

(a) Loosen the adjustment screws and move the rolling head assembly to permit installation of the AST-2867-3 spacer.

(b) Replace the installed AST-2867(-) spacer with the AST-2867-3 spacer between the rolling head assembly and the AST-2868 plate.

(c) Reposition the rolling head assembly against the AST-2867-3 spacer and tighten the adjustment screws.

(d) Replace the installed BST-2869 sleeve from the roller limit pin with the BST-2869-1 sleeve.

(e) Install the BST-2872 spacer on the roller arm, opposite plunger “P”.

CAUTION: WHEN INSTALLING OR REMOVING A COUNTERWEIGHTED BLADE, ALWAYS DO SO WITH THE COUNTERWEIGHT KNOB AWAY FROM THE ROLLER ARM.

(f) Remove the collet fixture from the spindle face plate by removing the two 1/2-13 bolts.

(g) Install the "C" shank rolling conversion kit to the face plate by aligning the dowel pins.

1 Install the 1/2-13 bolts in the "C" shank rolling conversion kit.

2 Torque the 1/2-13 bolts to 35-45 Ft-Lb (47.45-61.01 N•m).

(h) Install the blade on the "C" shank rolling conversion kit.

CAUTION: DO NOT TIGHTEN THE CLAMPING BOLTS MORE THAN 70 IN-LBS (7.90 N•M).

(i) Tighten the 1/4-28 clamping bolts to 35-70 In-Lbs (3.95-7.90 N•m).



Rev. 36 Jun/1861-13-33

F. Blade Inspection


(1) Before the cold rolling process, the blade must be measured, cleaned, and free of any nicks, scratches, or marks. Refer to the Blade Shank Overhaul chapter of this manual.

(2) After the rolling process, inspect the blade shank in accordance with the Blade Shank Overhaul chapter of this manual.

G. Rolling Process of the DT-1724-3( ) Rolling Machine


NOTE: “D”, “E”, and “Y” shank blades are rolled without the needle bearings installed. “M”, “P”, “R”, “T”, “W”, “Z”, and “MV” shanks are rolled with needle bearings or blade bushings installed. (The rolled surface is the blade retention radius/shoulder.)

(1) The supply air pressure to the air regulator must be maintained at 90-130 psi (6.20-8.96 bar).

(2) When the ball-check valve is depressed, the booster pressure must read the pressure recorded on the 100885 label located on the booster output pressure gauge in accordance with Hartzell Propeller Inc. Blade Shank Rolling Machine Maintenance Manual 128 (61-00-28). This will supply 240-260 pound force (1067.57-1156.53 N) to the roller wheel when operating.

NOTE 1: The booster pressure is controlled by the air regulator in the line ahead of the ball-check valve.

NOTE 2: The gauge on the booster has been calibrated and certified.

(3) Adjust the booster pressure to 1950-2000 psi (134.44-137.89 bar), regardless of the pressure on the regulator gauge.

(4) With the carriage in the aft position, lock the face plate to the support block by tightening the anti-rotation screw in place.

(5) Install the blade to be rolled on the fixture located on the face plate.

(6) For “D,” “E”, “M”, “P”, “R”, “T”, “W”, “Y”, “Z”, and “MV” shanks

(a) Make sure that the blade is as far forward as possible before tightening the collet.

(b) When the draw bar is tight, remove and store the handle.



Rev. 36 Jun/1861-13-33

(7) For “C” shanks(a) Make sure that the blade is as far forward as possible before tightening

the clamping bolts.(8) Remove the anti-rotation screw between the face plate and support block.

WARNING 1: USE EXTREME CAUTION WHEN ACTIVATING ANY SWITCH ON THE ROLLING MACHINE. WHEN CERTAIN MOTORS ARE ACTIVATED, MACHINE PARTS WILL AUTOMATICALLY MOVE OR ROTATE WITHOUT WARNING AND COULD CAUSE INJURY.

WARNING 2: FOR “D,” “E”, “M”, “P”, “R”, “T”, “W”, “Y”, “Z”, AND “MV” SHANKS, MAKE SURE THE COLLET DRAW BAR HAS BEEN REMOVED BEFORE STARTING THE MACHINE.

(9) Turn the power switch ON.

CAUTION: THE CARRIAGE MUST BE IN THE FULL AFT POSITION BEFORE BEGINNING THE ROLLING PROCESS.

(10) With the roller head in the aft position, the machine is ready to operate.


(11) Using a clean soft cloth soaked in CM106 or other equivalent solvent, clean the roller wheel and blade shank.

(12) Sparingly apply a vegetable-based oil or non-fluid lubricator to the radius area.(13) Depress the start cycle button momentarily.(14) As the carriage moves forward, the rolling cycle will begin.(15) When the carriage reaches the start position, the accumulated booster pressure

must read the pressure recorded on the 100885 label located on the booster output pressure gauge in accordance with Hartzell Propeller Inc. Blade Shank Rolling Machine Maintenance Manual 128 (61-00-28), adjusted in accordance with step 3.F.(2). in this section.

(16) As the roller progresses through the radius, it will contact the carriage return switch on the roller support arm, reversing the carriage travel.

(17) As the carriage travels aft, the ball-check valve begins to release the accumulated pressure and the pressure transition zone begins.



Rev. 36 Jun/1861-13-33

(18) The roller pressure will decrease to zero (0) and the rolling process will be completed.

(a) For time cycle information, refer to the section, "Functional Check Without Blade Installed" in this chapter.

(19) The carriage will return to the full aft position and stop.

(20) Turn the main power switch to the OFF position.

(21) Install the anti-rotation screw in the support block, locking the face plate.

(22) For “D,” “E”, “M”, “P”, “R”, “T”, “W”, “Y”, “Z”, and “MV” shanks

(a) Release the tension on the blade retention collet.

(23) For “C” shanks

(a) Loosen the C-shank rolling conversion kit screws.

CAUTION: WHEN INSTALLING OR REMOVING A COUNTERWEIGHTED BLADE, ALWAYS DO SO WITH THE COUNTERWEIGHT KNOB AWAY FROM THE ROLLER ARM.

(24) Remove the blade.


(25) Using a clean soft cloth soaked in CM106 or equivalent solvent, wipe the blade shank.

(26) Continue the blade shank overhaul procedures in accordance with the Blade Shank Overhaul chapter of this manual.

H. Sample Program

(1) Compression Rolling

(a) For information about how a facility can be approved to perform compressive rolling, refer to the Approved Facilities chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

DT-1724-5 Automated Rolling Machine - Front View Figure 13-11

Main Power Switch

HMI



Rev. 36 Jun/1861-13-33

TPI-J

M-0

0005

2



Rev. 39 Mar/2061-13-33

TPI-J

M-0

0005

2E-stop Button

Fault Reset Button and

Light

Power/Reset Button

and Light

Cycle Start Button

HMI Figure 13-12



Rev. 36 Jun/1861-13-33

TPI-J

M-0

0004

9

DT-1724-5 Automated Rolling Machine - Without Cage Figure 13-13

B-axis Drive

Y-axis Drive

X-axis Drive



Rev. 36 Jun/1861-13-33

TPI-J

M-0

0007

7

DT-1724-5 Automated Rolling Machine - Rear View Figure 13-14

Air Supply Lines



Rev. 39 Mar/2061-13-33

4. DT-1724-5 Rolling Machine

A. Basic Machine OperationRefer to Figures 13-11 through 13-14(1) Main Power Disconnect Switch (On/Off)

(a) Supplies power to all circuits:1 Main electrical enclosure

a Power Supply: 5 Volts DCb Power Supply: 24 Volts DCc Power Supply: 48 Volts DCd X-axis Drive (vertical)e Y-axis Drive (horizontal)f B-axis Drive (roller angle)g Programmable Logic Controller (PLC)

2 HMI Consolea Cycle Start Button

(1) Starts the chosen blade recipe to begin the rolling processb Fault Reset Button

(1) Resets the fault indicator lightc Power/Reset Button

(1) Powers on the drives

(2) Puts the machine in a standby status(3) Resets system fault warnings when flashing

d E-stop Button

(1) Emergency button that provides an immediate power off of the rolling machine

(2) After using the E-stop Button, the system resets to the Main Menu

3 Transformer(2) Blade Holding Fixture

(a) Blades are retained on the machine using a 6-jaw scroll chuck that uses custom jaws and is approved for use on all current and applicable blade shank designs.



Rev. 39 Mar/2061-13-33

B. Assembly After Receipt of New or Exchanged Units

(1) Documentation

(a) Make sure that the information on the rolling machine certificate is correct.

(b) Make sure there is a Certificate of Calibration for the pressure sensor. Refer to the Approved Facilities chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(c) Make sure there is a Certificate of Calibration for the force gauge TE638. Refer to the Approved Facilities chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).

(2) Electrical Power Supply

(a) Refer to the Hartzell Propeller Inc. DT-1724-5 Blade Shank Rolling Machine Maintenance Manual 178 (61-00-78) for electrical power supply requirements and instructions.

(3) Air Supply

(a) Connect the machine to an air supply of 90-130 psi (6.20-8.96 bar) through the airline connector located on the back of the machine, near the lower right. Refer to Figure 13-14.

(4) Required Accessories

(a) USB Flash Drive

1 Plug a locally procured USB flash drive into a USB port located on the bottom of the HMI console to record blade rolling data.

2 It is recommended the USB flash drive is 16GB or greater.

NOTE: Data logs are for user records. Single blade data logs are required for annual recertification. Refer to the "Requirements for Certification" section in the Approved Facilities chapter of Hartzell Propeller Inc. Standard Practices Manual 202A for data log details.

(5) Optional Accessories

(a) Keyboard

1 A locally procured standard English keyboard can be plugged into a USB port located on the bottom of the HMI console and used for data entry.

(b) USB Scanner

1 A locally procured standard barcode scanner can be plugged into a USB port located on the bottom of the HMI console and used for data entry.

2 The barcode scanner can be used in conjunction with a keyboard through a USB splitter or a keyboard with an auxiliary USB port.



Rev. 39 Mar/2061-13-33

(c) USB Mouse

1 A locally procured standard USB mouse can be plugged into a USB port located on the bottom of the HMI console and used for HMI screen navigation, command selection, and data entry.

2 The USB mouse can be used in conjunction with a keyboard through a USB splitter or a keyboard with an auxiliary USB port.

C. Routine Maintenance and Checks

NOTE: For additional information about the maintenance, repair, and troubleshooting of the DT-1724-5 rolling machine, refer to the Hartzell Propeller Inc. DT-1724-5 Blade Shank Rolling Machine Maintenance Manual 178 (61-00-78).

(1) 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 PROTCTION. USE IN A WELL VENTILATED AREA AWAY FROM SPARKS AND FLAME. READ AND OBSERVE ALL WARNING LABELS.

CAUTION 1: DISCONNECT ALL ELECTRIC AND AIR SUPPLIES BEFORE CLEANING.

CAUTION 2: COVERING THE MACHINE WHEN NOT IN USE IS RECOMMENDED.

(a) Clean all machine components daily as necessary. Depending on the condition of the machine, certain cleaning methods could be required.

1 An abrasive pad CM47 and solvent CM23 can be used as necessary to clean parts.

2 Clean motors and other painted surfaces with a mild solvent, such as CM23, that will not remove the paint.

3 Using a putty knife, scrape excess grime and grease from accessible areas.



Rev. 39 Mar/2061-13-33

(2) Lubrication

CAUTION: USE OF AIRCRAFT HYDRAULIC FLUID (MIL-H-5606) IS NOT PERMITTED.

(a) Before each use, check the level of hydraulic oil in the air/oil booster.

1 To fill the reservoir of the air/oil booster:

a Remove the reservoir cap.

b Fill the reservoir to the applicable level with hydraulic oil, such as Mobil DTE 24, Shell Tellus 23, Chevron EP22, Pro-Cool AW 46, or Automatic Transmission fluid (ATF).

2 A low level of hydraulic oil in the air/oil booster with no evidence of external leakage can be an indication of internal oil leakage in the air/oil booster. Refer to the Troubleshooting chapter of the Hartzell Propeller Inc. DT-1724-5 Blade Shank Rolling Machine Maintenance Manual 178 (61-00-78).

(3) Roller Wheel Inspection(a) Before each use, inspect the roller wheel for nicks, excessive wear, flat

spots in the radius, pitting, or tearing of the material.

1 If there is a nick, excessive wear, flat spot in the radius, pitting, or tearing of the material, replace the roller wheel in accordance with the Repair and Replace chapter of the Hartzell Propeller Inc. DT-1724-5 Blade Shank Rolling Machine Maintenance Manual 178 (61-00-78).

NOTE: The condition of the roller wheel surface and the roller wheel bearing have the greatest effect on the surface finish and appearance of the rolled surface.

(4) Pressure Sensor Inspection(a) If the pressure sensor does not function correctly, refer to the

Troubleshooting, and the Repair and Replace chapters of Hartzell Propeller Inc. DT-1724-5 Blade Shank Rolling Machine Maintenance Manual 178 (61-00-78).

NOTE: A pressure sensor purchased separately through Hartzell Propeller Inc. is not certified when shipped.



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D. Program Selection Procedure

NOTE 1: Refer to the Hartzell Propeller Inc. DT-1724-5 Blade Shank Rolling Machine Maintenance Manual 178 (61-00-78) for HMI screen function and details.

NOTE 2: No mechanical setup is necessary for the DT-1724-5 machine. Setup performed through a touch screen as described in this section.

(1) From the "Blade Select Menu", select and load the applicable correlating program with the blade design intended to be rolled.(a) Search and select the recipe from the library for the correlating program of

the blade to be rolled.(b) Push “Load” to load the recipe values to the HMI.

1 Make sure the loaded "Active Shank Design" field agrees with the library name to show the program loaded correctly.

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 (PCP).

E. Blade Inspection

(1) Before the cold rolling process, the blade must be measured, cleaned, and free of any nicks, scratches, or marks. Refer to the Blade Shank Overhaul chapter of this manual.

(2) After the rolling process, inspect the blade shank in accordance with the Blade Shank Overhaul chapter of this manual.



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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 (PCP).

F. Rolling Process of the DT-1724-5 Rolling Machine

(1) The air pressure supply to the machine must be kept at 90-130 psi (6.20-8.96 bar).

(2) When the rolling machine is in operation, the air/oil booster pressure will automatically populate to the "Set PSI" value that is entered on the "Applied Force Set" screen. 240-260 pound force (1067.57-1156.53 N) is supplied to the roller wheel when the rolling machine is operating. Refer to the section, "Applied Force Calibration (Applied Force Set)" of Hartzell Propeller Inc. DT-1724-5 Blade Shank Rolling Machine Maintenance Manual 178 (61-00-78) for frequency of calibration requirements.

NOTE 1: The air/oil booster pressure is controlled by the air pressure regulator found below the machines base cover. A Proportional Integral Derivative (PID) loop in the PLC programming constantly monitors and adjusts the regulator output during operation to agree with the command pressure input. The pressure ramp is also controlled by the PLC and air pressure regulator as part of the blade recipe.

NOTE 2: The pressure transducer on the air/oil booster has been calibrated and certified and must be in accordance with requirements of Hartzell Propeller Inc. Standard Practices Manual 202A, Volume 9 (61-01-02) and Hartzell Propeller Inc. DT-1724-5 Blade Shank Rolling Machine Maintenance Manual 178 (61-00-78).

(3) With the rolling machine in the load/home position, install the blade to be rolled on the fixture found on the face plate weldment.

NOTE: Make sure the pitch change knob of the blade is located between two jaws of the chuck.

(a) Tighten the fixture using the torque wrench adaptor (TE641) and a calibrated 1/2 inch torque wrench to 60 Ft-Lbs ±6 Ft-Lbs (81.3 N•m ±8.1N•m).

(b) Make sure that the blade is correctly seated in the fixture before tightening.

(c) When the fixture is tight, remove and store the torque wrench and adaptor.



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WARNING: MAKE SURE THE TORQUE WRENCH ADAPTOR IS REMOVED AND STORED AWAY FROM THE AUTOMATED ROLLING MACHINE BEFORE STARTING THE AUTOMATED ROLLING MACHINE PROCESS.

CAUTION: THE DT-1724-5 AUTOMATED ROLLING MACHINE MUST MEET MINIMUM AND ON CONDITION CALIBRATION REQUIREMENTS GIVEN IN THE HARTZELL PROPELLER INC. DT-1724-5 BLADE SHANK ROLLING MACHINE MAINTENANCE MANUAL 178 (61-00-78) BEFORE PROCESSING ANY BLADES. FAILURE TO DO SO CAN RESULT IN INCORECT START, STOP, AND RAMP LOCATIONS, IMPROPER ROLLING FORCE, OR DAMAGE TO THE BLADE OR MACHINE.

(4) The rolling machine is ready to operate.

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 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.

(5) Using a clean soft cloth soaked in CM106 or other equivalent solvent, clean the roller wheel and blade shank.

(6) Sparingly apply a vegetable-based oil or air tool lubricator to the radius area.

(7) Close the rolling machine door.

(8) Push the cycle start button.

(a) The rolling machine will activate a data input screen.

1 Enter the operator name or initials

2 Enter the blade serial number

3 Enter the blade part number

4 Enter the work order number

(9) Push OK to begin the rolling process.

(a) Push CANCEL to return to the previous window.

(10) The rolling machine will automatically lock the door, and perform a rapid traverse to the starting location and begin rolling.

(11) When the carriage reaches the start position, the accumulated air/oil booster pressure will automatically adjust to the value input from the Applied Force Set screen.



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(12) Once complete, the machine will return to the home position, in a standby condition and the door will automatically unlock.

(13) Loosen the blade fixture with the torque wrench adaptor by turning it counterclockwise until the blade removes freely from the fixture.

(14) Remove the blade.

(15) Using a clean soft cloth soaked in methyl-ethyl-ketone (MEK) CM106 or equivalent solvent, wipe the processed blade shank clean.

(16) Continue the blade shank overhaul procedures in accordance with the Blade Shank Overhaul chapter of this manual.

G. Sample Program

(1) Compression Rolling

(a) For information about how a facility can be approved to perform compressive rolling, refer to the Approved Facilities chapter of Hartzell Propeller Inc. Standard Practices Manual 202A (61-01-02).



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H. Blade Data Printing

(1) Description:

(a) During a rolling cycle, the HMI collects the machine setting, input, and operational data at multiple steps of the process and collects this data into a .csv file.

1 The .csv file is saved to a customer supplied USB flash drive.

(b) Hartzell Propeller Inc. recommends printing blade data reports, but is not necessary.

(c) To print specific blade reports, contact Hartzell Propeller Inc. Product Support for the current DT-1724-5 Blade Report Microsoft Excel template.

1 Templates can be changed and re-formatted to meet the needs of the user.

(2) Extract .csv files from the flash drive.

(a) After processing the applicable blades, remove the flash drive.

CAUTION: DO NOT OPERATE THE ROLLING MACHINE WITHOUT THE USB FLASH DRIVE PLUGGED INTO THE HMI CONSOLE. DATA WILL NOT TRANSFER WITHOUT THE USB FLASH DRIVE INSTALLED.

(b) Plug the USB flash drive into a Windows PC with a version of Microsoft Excel.

(c) Open the datafile.csv Excel file.

1 Highlight column A.

(d) Go to the DATA tab (top tab bar), and choose Text to Columns.

1 Choose the Deliminated radial button and click Next.

2 Choose the Semicolon radial box and click Next.

3 Click Finish.

(3) Choose a cell within the table, and push (Ctrl+Shift+L)

(a) This action permits the user to perform a search query within the table. Using the drop down cells in Line 1, search for a blade ran by date, operator, work number, blade type, etc.

(4) Search by work order number (Work #), to create a report for that propeller.

(a) Choose the Work # drop down,

(b) Search for the necessary workorder number,

(c) Click OK.



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(5) Highlight and Copy the data below line 1.

(a) Click the cell directly below A1 (Date/Time), and push (Ctrl+Shift+End).

(b) With all the populated cells below row 1 highlighted, push (Ctrl+C) to copy.

(6) Choose the "File data (copy_paste)" sheet tab (bottom of Excel file) within the Hartzell Propeller Inc. Printable Data Template.

(7) Choose the A2 cell and paste (Ctrl+V) the data to the sheet.

(8) Choose the "Print Report" sheet tab (bottom of Excel file).

(9) Print the report (File tab>Print>Print or Ctrl+P).

(10) Once the necessary reports are printed, safely remove the USB flash drive and plug it back into the HMI console's USB port.



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