Pt6a-34ag Manual de Mantenimiento [PDF]

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MAINTENANCE MANUAL TURBOPROP GAS TURBINE ENGINE Model(s) PT6A-34/-34AG/-34B/-36 Manual Part No. 3021242 15 August 1977 The contents of this manual have been examined and found acceptable to the Minister in meeting the requirements of an Engine Maintenance Manual for the Pratt & Whitney Canada PT6A-34/34AG/-34B/-36/ engine, as required by the Canadian Airworthiness Manual, Chapter 533.4 ‘‘Instructions for Continued Airworthiness’’.

WARNING - PROPRIETARY RIGHTS & EXPORT CONTROLS NOTICE This manual contains proprietary information of Pratt & Whitney Canada Corp. (″P&WC″), which P&WC provides in confidence and solely for the purposes of supporting engine certification and providing applicable information regarding the proper use, maintenance, inspection, repair, servicing and parts application of P&WC products and services, as directed therein. Neither this manual nor any information in it may be disclosed to others, or used for any other purpose, including, without limitation, to design, create, develop, reproduce, manufacture or derive any design, part, product, material, process, modification, configuration change or repair, or obtain FAA or other government approval to do so. Possession and use of this manual is also subject to the restrictions set out in P&WC’s Technical Data Agreement (a copy of which may be obtained by contacting P&WC Technical Publications). The contents of this manual may be subject to export control laws. Unauthorized export or re-export of the manual, or parts thereof, is prohibited. By accepting and possessing this manual, you agree to be bound by the foregoing terms. If a Government agency or department intends to disclose any information, written notice should be given to: VP - Legal Services, Pratt & Whitney Canada Corp., 1000 Marie-Victorin (01BE5), Longueuil, Quebec J4G 1A1.

PRATT & WHITNEY CANADA 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1

Mar 27/2017 © 1977 Pratt & Whitney Canada Corp. PRINTED IN CANADA

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

Export Control Classification (X) if Applicable Contains no Technical Data

()

Not Subject to the EAR pursuant to 15 CFR 734.7(a)(1) or Not Subject to the ITAR pursuant to 22 CFR 120.11 (NSR)

()

Jurisdiction and Classification based on Physical Location of the Item.

Location

* Additionally, refer to the classification under the local export regime where the item is located, as provided in the grid.

U.S.

Outside US*

Canada

Regulations EAR

ITAR

NSR

NSR

9E619

NSR

EIPA (ECL)

DPA (CG)

NSR

No

Pratt & Whitney Canada Corp. 1000, Marie-Victorin Longueuil, Québec, Canada J4G 1A1 Tél. 450-677-9411

July 28, 2020

REVISION TRANSMITTAL SHEET TO:

Holders of the Pratt & Whitney Canada Maintenance Manual for PT6A-34/-34AG/-36 Engines, Manual Part No. 3021242.

SUBJECT: Revision No. 63, dated Jul 20/2020

Please insert the attached Revision No. 63 pages into your copy of the PT6A-34/-34AG/-36 Maintenance Manual. Remove and destroy superseded pages. Extreme care should be exercised in updating your copy of the manual. To ensure that you do not inadvertently discard pages that should be retained, the manual should be updated in accordance with the Lists of Effective Pages. Pages supplied with the new date and revision bars but no visible change may contain coding changes transparent to the user and should be inserted as part of the revision. Please add Revision No. 63 to the Record of Revisions. The intent of Temporary Revisions 72-45 and 72-46 have been incorporated at this revision. All succeeding Temporary Revisions must be retained until incorporated. Any discrepancies, problems or suggestions regarding this revision should be sent via the Support Ticket application under the Help menu on MyP&WC Power portal at https://customer.pwc.ca You can send your comments in writing to: Pratt & Whitney Canada Corp. 1000 Marie-Victorin Longueuil, Québec Canada J4G 1A1 Attention: Email: Fax:

Manager, Technical Publications (05MS1) [email protected] (450) 468-7688

You may also submit your feedback via our on-line feedback form available at: https://customer.pwc.ca/Pages/Help/OpenNewTicket.aspx

Page 1 HIGHLIGHTS Jul 20/2020

Pratt & Whitney Canada Corp.

PT6A-34/-34AG/-36 MAINTENANCE MANUAL REVISION NO. 63 HIGHLIGHTS CH/SE/SU

Description of Change

Temporary Revision Index

The TR list has been updated.

72-00-00 Servicing

Preservation, Depreservation and Unpreserved Engines Section TR72-45 has been incorporated (Purpose: To revise the engine unpreserved procedure and to add a procedure for regular operation as alternative to preservation of inactive engines).

72-00-00 Inspection

Periodic Inspection TR72-46 has been incorporated (Purpose: To add note for inspection interval of P3 filter and P3 filter drain valve housing assembly in the periodic inspection table). Inspection of Compressor Turbine (CT) Stator Assembly The inspection procedure of compressor turbine (CT) stator assembly has been added. Inspection of Hot Section Components The HSI procedure for compressor turbine (CT) vane has been added.

73-10-07 Maintenance Practices

Check The editorial correction has been done.

Page 2 HIGHLIGHTS Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

RECORD OF REVISIONS REV NO.

ISSUE DATE

DATE INSERTED

BY

REV NO.

ISSUE DATE

DATE INSERTED

BY

1

Aug 01/78

P&WC

30

Aug 18/2000

P&WC

2

Aug 17/79

P&WC

31

Feb 02/2001

P&WC

3

Sep 10/79

P&WC

32

Aug 03/2001

P&WC

4

Jun 02/80

P&WC

33

Dec 06/2001

P&WC

5

Jun 01/81

P&WC

34

Feb 15/2002

P&WC

6

Jun 01/82

P&WC

35

Aug 16/2002

P&WC

7

Apr 26/83

P&WC

36

Jun 06/2003

P&WC

8

Feb 21/84

P&WC

37

Apr 02/2004

P&WC

9

Jan 21/85

P&WC

38

Aug 27/2004

P&WC

10

Mar 18/85

P&WC

39

Nov 26/2004

P&WC

11

Sep 16/85

P&WC

40

Jun 10/2005

P&WC

12

Jun 13/86

P&WC

41

Dec 02/2005

P&WC

13

Nov 03/87

P&WC

42

Jun 16/2006

P&WC

14

Aug 08/88

P&WC

43

Jan 05/2007

P&WC

15

Mar 07/89

P&WC

44

Apr 25/2008

P&WC

16

May 01/89

P&WC

45

Nov 21/2008

P&WC

17

Feb 15/91

P&WC

46

Apr 03/2009

P&WC

18

Nov 15/91

P&WC

47

Sep 18/2009

P&WC

19

May 15/92

P&WC

48

May 21/2010

P&WC

20

May 15/93

P&WC

49

Dec 10/2010

P&WC

21

Nov 15/93

P&WC

50

May 18/2012

P&WC

22

Mar 15/95

P&WC

51

Mar 08/2013

P&WC

23

Aug 15/95

P&WC

52

Jan 27/2014

P&WC

24

Dec 12/97

P&WC

53

Sep 15/2014

P&WC

25

Apr 03/98

P&WC

54

Mar 16/2015

P&WC

26

Oct 09/98

P&WC

55

Aug 24/2015

P&WC

27

Apr 02/99

P&WC

56

Mar 27/2017

P&WC

28

Jul 30/99

P&WC

57

Jul 10/2017

P&WC

29

Feb 11/2000

P&WC

58

Feb 19/2018

P&WC

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

RECORD OF REVISIONS

Aug 15/77

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

REV NO.

ISSUE DATE

DATE INSERTED

BY

59

Jul 23/2018

P&WC

60

Feb 18/2019

P&WC

61

Jul 22/2019

AUG 23, 2019

ATP/RLL

62

Jan 13/2020

FEB 10, 2020

ATP/LC

63

Jul 20/2020

AUG 11, 2020

ATP/PC

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

RECORD OF REVISIONS

Aug 15/77

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

RECORD OF TEMPORARY REVISIONS TR. NO.

CH/SE/SU

PAGE NO.

ISSUE DATE

INSERTED BY

72-47

72-00-00

302

8/24/2020

ATP/RLL

DATE REMOVED

REMOVED BY

RECORD OF TRs

Aug 15/77

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

Title Page

Mar 27/2017

Record of Revisions

Aug 15/77

Record of Temporary Revisions

Aug 15/77

LEP

1 2 blank

Jul 20/2020 Jul 20/2020

List of Chapter/ Section/Subjects

1 2 3 4 blank

Nov 26/2004 Nov 26/2004 Nov 26/2004 Nov 26/2004

Temporary Revision Index

1 2 3 4 5 6 blank

Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020

Service Bulletin List

1 2 3 4 5 6 7 8 9 10 blank

Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

FRONT MATTER LEP

Page 1/2 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LIST OF CHAPTER/SECTION/SUBJECTS CHAPTER/SECTION/SUBJECT

TITLE

INTRODUCTION

Introduction

AIRWORTHINESS LIMITATIONS

Airworthiness Limitations

61-20

Propeller Governing

61-20-00 70-00 70-00-00 71-00 71-00-00 72-00 72-00-00 72-01 72-01-00 72-10 72-10-00 72-20 72-20-00 72-30

Propeller Governor Standard Practices Standard Practices Power Plant Power Plant Engine Engine Turboprop Power Section Power Section Reduction Gearbox Reduction Gearbox Air Inlet Section Air Inlet Section Compressor

72-30-00

Gas Generator Assembly

72-30-01

Center Fireseal Mount Ring

72-30-02

Rear Fireseal Mount Ring

72-30-04

Gas Generator Case

72-30-05

Compressor Rotor

72-40

Combustion Section

72-40-00

Combustion Section

72-40-01

Combustion Chamber Liner Assembly

72-50

Turbine Section

LIST OF CHAP/SECT/SUBJ

Page 1 Nov 26/2004

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

CHAPTER/SECTION/SUBJECT

TITLE

72-50-00

Turbine Section

72-50-01

Compressor Turbine Stator

72-50-02

Compressor Turbine

72-50-03

Power Turbine Interstage Stator

72-50-04

Power Turbine

72-50-05

Exhaust Duct

72-60 72-60-00 73-00 73-00-00 73-10

Accessory Gearbox Accessory Gearbox Assembly Engine Fuel and Control Engine Fuel and Control Fuel Distribution

73-10-01

Oil-to-fuel Heater

73-10-02

Fuel Pump

73-10-03

Fuel Lines

73-10-04

Flow Divider and Starting Control

73-10-05

Fuel Manifold and Nozzles

73-10-06

Fuel Drain Valves

73-10-07

Pneumatic Line (P3)

73-10-08

Pneumatic Line (Py)

73-20 73-20-00 74-00 74-00-00 74-10

Fuel Control Fuel Control Unit Ignition Ignition Ignition Exciter

74-10-00

Ignition Exciter

74-10-01

Ignition Current Regulator

74-20

Ignition Cables (Spark)

LIST OF CHAP/SECT/SUBJ

Page 2 Nov 26/2004

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

CHAPTER/SECTION/SUBJECT

TITLE

74-20-00

Ignition Cables and Spark Igniters

74-20-01

Glow Plugs and Ignition Cables

74-20-02

Glow Plugs

74-20-04

Spark Igniters (Transferred to 74-20-00)

75-00 75-00-00 75-30 75-30-00 76-00 76-00-00 76-10 76-10-00 77-20

Air Air Systems Compressor Bleed Valve Compressor Bleed Valve Engine Controls Engine Controls Propeller Reversing Linkage Propeller Reversing Linkage Engine Indicating

77-20-00

Engine Indicating

77-20-01

T5 Indicating System

79-00 79-00-00 79-20

Oil Oil Oil Distribution

79-20-00

Oil Distribution

79-20-01

External Oil Tubes

79-20-02

Oil Filter and Check Valve Housing

79-20-04

Oil-to-fuel Heater Check Valve

LIST OF CHAP/SECT/SUBJ

Page 3/4 Nov 26/2004

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TEMPORARY REVISION INDEX

T.R. No.

Filed Adjacent to

T.R. Status

INTRO-1 70-1

CONSUMABLE MATERIALS, page 1 70-03-00, page 602 Standard Practices - Inspection 71-1 through 71-2 71-03-00, page 528 71-3 Power Plant - Adjustment/Test through 71-5 71-6 71-03-00, page 519 Power Plant - Adjustment/Test 71-7 71-03-00, page 521 Power Plant - Adjustment/Test 71-8 71-03-00, page 528 Power Plant - Adjustment/Test 71-9 71-03-00, page 516 Power Plant - Adjustment/Test 71-03-00, page 528 71-10 Power Plant - Adjustment/Test through 71-14 71-15 71-03-00, page 710 Power Plant - Cleaning 71-16 71-03-00, page 711 Power Plant - Cleaning 71-17 71-03-00, page 712 Power Plant - Cleaning 71-18 71-03-00, page 514A Power Plant - Adjustment/Test 71-19 71-03-00, page 506C Power Plant - Adjustment/Test 71-20 71-03-00, page 506C Power Plant - Adjustment/Test 71-21 71-03-00, page 506C Power Plant - Adjustment/Test 71-22 71-03-00, page 506C Power Plant - Adjustment/Test 71-23 71-00-00, page 507 Power Plant - Adjustment/Test 71-24 71-00-00, page 508 Power Plant - Adjustment/Test 71-25 71-00-00, page 501 Power Plant - Adjustment/Test

Incorporated at Rev. No. 45 Incorporated at Rev. No. 24 Incorporated at previous revisions.

Incorporated at Rev. No. 11 Incorporated at Rev. No. 11 Incorporated at previous revision. Incorporated at previous revision. Incorporated at Rev. No. 8

Incorporated at Rev. No. 11 Incorporated at Rev. No. 24 Incorporated at Rev. No. 24 Incorporated at Rev. No. 24 Incorporated at Rev. No. 24 Replaced by TR 71-20 Replaced by TR 71-21 Replaced by TR 71-22 Incorporated at Rev. No. 24 Incorporated at Rev. No. 25 Incorporated at Rev. No. 25 Incorporated at Rev. No. 32

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TR INDEX

Page 1 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

T.R. No.

Filed Adjacent to

T.R. Status

71-26

71-00-00, page 514 Power Plant - Adjustment/Test 71-27 71-00-00, page 514 Power Plant - Adjustment/Test 71-28 71-00-00, page 531 Power Plant - Adjustment/Test 72-1 through 72-4 72-5 72-03-00, page 608 Engine Turboprop - Inspection 72-6 72-33-01, page 201 Gas Generator Case - Maintenance Practices 72-7 72-03-00, page 601 Gas Generator Case - Maintenance Practices 72-8 72-53-01, page 206 Compressor Turbine Vane Ring, Shroud Housing Assembly and Ducts Maintenance Practices 72-9 72-03-00, page 602A Engine Turboprop - Inspection 72-10 72-03-00, page 611 Engine Turboprop - Inspection 72-11 72-33-01, page 203 Gas Generator Case - Maintenance Practices 72-12 72-53-02, page 206 Compressor Turbine - Maintenance Practices 72-13 72-03-00, page 614 Engine Turboprop - Inspection 72-14 72-03-00, page 405 Engine Turboprop - Removal/ Installation 72-15 72-03-00, page 602A Engine Turboprop - Inspection 72-16 72-03-00, page 602A Engine Turboprop - Inspection 72-17 72-53-02, page 206 Compressor Turbine - Maintenance Practices

Replaced by TR 71-27 Incorporated at Rev. No. 32 Incorporated at Rev. No. 53 Incorporated at a previous revisions. Incorporated at a previous revision.

Incorporated at a previous revision.

Incorporated at a previous revision.

Incorporated at a previous revision. Incorporated at a previous revision. Incorporated at a previous revision.

Incorporated at a previous revision.

Incorporated at a previous revision. Incorporated at a previous revision.

Incorporated at a previous revision. Incorporated at a previous revision. Incorporated at a previous revision.

Incorporated at a previous revision.

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TR INDEX

Page 2 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

T.R. No. 72-18

72-19

72-20 72-21 72-22 72-23 72-24 72-25

72-26 72-27 72-28 72-29 72-30 72-31 72-32 72-33

72-34 72-35 72-36

Filed Adjacent to

T.R. Status

72-53-02, page 207 Compressor Turbine - Maintenance Practices 72-53-01, page 206 Compressor Turbine Vane Ring, Shroud Housing Assembly and Ducts Maintenance Practices 72-03-00, page 619 Engine Turboprop - Inspection 72-03-00, page 619 Engine Turboprop - Inspection 72-03-00, page 641 Engine Turboprop - Inspection 72-03-00, page 112 Engine Turboprop - Troubleshooting 72-03-00, page 604 Engine Turboprop - Inspection 72-60-00, page 205 Accessory Gearbox - Maintenance Practices 72-00-00, page 104 Engine, Turboprop - Fault Isolation 72-00-00, page 645 Engine, Turboprop - Inspection 72-00-00, page 625 Engine, Turboprop - Inspection 72-00-00, page 626 Engine, Turboprop - Inspection 72-00-00, page 125 Engine, Turboprop - Fault Isolation 72-00-00, page 343 Engine, Turboprop - Servicing 72-00-00, page 604 Engine - Inspection 72-50-01, page 207 Compressor Turbine Stator Maintenance Practices 72-00-00, page 649 Engine - Inspection 72-00-00, page 605 Engine - Inspection 72-00-00, page 605 Engine - Inspection

Incorporated at a previous revision.

Incorporated at Rev. No. 9 Incorporated at Rev. No. 9 Incorporated at Rev. No. 9 Incorporated at Rev. No. 20 Incorporated at Rev. No. 24 Incorporated at Rev. No. 24

Incorporated at Rev. No. 32 Incorporated at Rev. No. 32 Incorporated at Rev. No. 32 Incorporated at Rev. No. 32 Incorporated at Rev. No. 32 Incorporated at Rev. No. 32 Incorporated at Rev. No. 36 Incorporated at Rev. No. 44

Incorporated at Rev. No. 44 Incorporated at Rev. No. 45 Incorporated at Rev. No. 50 Incorporated at Rev. No. 51

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TR INDEX

Page 3 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

T.R. No. 72-37 72-38 72-39 72-40

72-41

72-42 72-43 72-44

72-45 72-46 73-1

73-2

73-3

73-4

73-5

Filed Adjacent to

T.R. Status

72-00-00, page 617 Engine - Inspection 72-00-00, page 618 Engine - Inspection 72-00-00, page 605 Engine - Inspection 72-10-00, page 213 Reduction Gearbox - Maintenance Practices 72-10-00, page 215 Reduction Gearbox - Maintenance Practices 72-00-00, page 608 Engine - Inspection 72-00-00, page 644 Engine - Inspection 72-50-02, page 207 Compressor Turbine - Maintenance Practices 72-00-00, page 316 Engine, Turboprop - Servicing 72-00-00, page 608 Engine - Inspection 73-13-07, page 201 Pneumatic Line (Compressor Discharge Pressure) - Maintenance Practices 73-13-07, page 211 Pneumatic Line (Compressor Discharge Pressure) - Maintenance Practices 73-13-08, page 201 Pneumatic Line (Power Turbine Control - Nf) - Maintenance Practices 73-13-07, page 216 Pneumatic Line (Compressor Discharge Pressure) - Maintenance Practices 73-13-07, page 221 Pneumatic Line (Compressor Discharge Pressure) - Maintenance Practices

Incorporated at Rev. No. 51 Incorporated at Rev. No. 52 Incorporated at Rev. No. 53

Incorporated at Rev. No. 56

Incorporated at Rev. No. 56 Incorporated at Rev. No. 57 Incorporated at Rev. No. 57

Incorporated at Rev. No. 57 Incorporated at Rev. No. 63 Incorporated at Rev. No. 63

Incorporated at Rev. No. 24

Incorporated at Rev. No. 24

Incorporated at Rev. No. 24

Incorporated at Rev. No. 24

Incorporated at Rev. No. 24

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TR INDEX

Page 4 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

T.R. No. 73-6

73-7

73-8

73-9

73-10

73-11 73-12

73-13

79-1

Filed Adjacent to

T.R. Status

73-13-08, page 203 Pneumatic Line (Power Turbine Control - Nf) - Maintenance Practices 73-10-05, page 203 Fuel Manifold Adapter and Nozzles Maintenance Practices 73-10-05, page 203 Fuel Manifold Adapter and Nozzles Maintenance Practices 73-20-00, page 202 Fuel Control Unit - Maintenance Practices 73-20-00, page 215 Fuel Control Unit - Maintenance Practices 73-10-02, page 210 Fuel Pump - Maintenance Practices 73-20-00, page 206 Fuel Control Unit - Maintenance Practices 73-20-00, page 202 Fuel Control Unit - Maintenance Practices 79-20-02, page 214 Oil Filter, Housing and Check ValveMaintenance Practices

Incorporated at Rev. No. 24

Incorporated at Rev. No. 25

Incorporated at Rev. No. 28

Incorporated at Rev. No. 36

Incorporated at Rev. No. 36 Incorporated at Rev. No. 42

Incorporated at Rev. No. 50

Incorporated at Rev. No. 52

Incorporated at Rev. No. 33

All succeeding Temporary Revisions must be retained in your printed manual until directed otherwise by subsequent revision activity.

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TR INDEX

Page 5/6 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

SERVICE BULLETIN LIST This list identifies all Service Bulletins (SB’s) for each listed engine model. Bulletins considered to have no effect on manual have the words ‘‘No Effect’’ added; effective bulletins give the date incorporated in the manual. The incorporation of Service Bulletins on each engine is recorded in the engine log book and related documents. PT6A-34/34AG/34B/36 Series (Engine Model Group #01) engine ATA 72-Series Service Bulletins are prefixed with Part No. 3026521 in lieu of a specific model identifier. For a current set of PT6A-34 Series engine Service Bulletins only, use ordering number 3020778. For a current set of PT6A-34AG Series engine Service Bulletins only, use ordering number 3026540. For a current set of PT6A-34B Series engine Service Bulletins only, use ordering number 3020600. For a current set of PT6A-36 Series engine Service Bulletins only, use ordering number 3020599. NOTE: The referenced Service Bulletins are being continually revised to reflect P&WC recommendations for oils, fuels, engine planned maintenance, etc., and are concurrent with incorporation of engine modifications. P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

1001

72-1001

33

PT6A-34/-34AG/-34B/-36

1002

72-1002

29

PT6A-34/-34B/-36

1003

72-1003

35

PT6A-34B

1103 1116 1129 1148 1149 1165 1167 1168 1169 1170 1171 1173 1176 1178 1179 1180 1183 1184 1185 1189

72-1103 72-1116 72-1129 72-1148 72-1149 72-1165 72-1167 72-1168 72-1169 72-1170 72-1171 72-1173 72-1176 72-1178 72-1179 72-1180 72-1183 72-1184 72-1185 72-1189

2 Orig. 3 2 4 Orig. 3 Orig. 2 Orig. 1 Orig. Orig. Orig. Orig. Orig. 1 1 Orig. Orig.

PT6A-34 PT6A-34 PT6A-34/-34B/-36 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 Cancelled - Superseded by SB1287 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34 Cancelled PT6A-34 PT6A-34

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

SB LIST

Effect/Date Incorporated No Effect (See NOTE) No Effect (See NOTE) No Effect (See NOTE) No effect No effect No effect No effect No Effect Aug 15/1977 No Effect No effect No Effect No effect No Effect No Effect No effect Aug 15/1977 No effect No effect No effect No Effect Aug 15/1977 No effect

Page 1 Jan 13/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

P&WC SB No.

ATA SB No.

Rev. No.

1190 1191 1192 1193 1194 1196 1197 1199 1200 1201 1202 1203 1204 1205 1207 1209 1211 1212 1215 1216 1217 1219 1220 1221 1222 1223 1224 1225 1226 1227 1228 1229 1231 1232 1235 1236 1237 1241 1242 1244

72-1190 72-1191 72-1192 72-1193 72-1194 72-1196 72-1197 72-1199 72-1200 72-1201 72-1202 72-1203 72-1204 72-1205 72-1207 72-1209 72-1211 72-1212 72-1215 72-1216 72-1217 72-1219 72-1220 72-1221 72-1222 72-1223 72-1224 72-1225 72-1226 72-1227 72-1228 72-1229 72-1231 72-1232 72-1235 72-1236 72-1237 72-1241 72-1242 72-1244

Orig. 3 1 9 1 15 2 Orig. 1 1 Orig. Orig. 1 2 1 5 1 3 2 7 4 2 6 Orig. 2 6 2 2 1 3 2 Orig. 1 2 Orig. 4 4 2 1 28

PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34/-36 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 Cancelled - Superseded by SB1219 PT6A-34 PT6A-34 Cancelled - Superseded by SB1251 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34/-34AG PT6A-34/-34AG PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34/-34AG/-34B PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34/-34B/-36

1247 1248 1249

72-1247 72-1248 72-1249

5 2 Orig.

PT6A-34/-34AG/-34B PT6A-34 PT6A-34

Engine Model Applicability

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

SB LIST

Effect/Date Incorporated No effect No effect No effect No effect No effect May 18/2012 No effect No effect No effect No effect No effect No effect No Effect Sep 10/1979 No effect No Effect No effect No Effect Sep 10/1979 No effect Sep 10/1979 No effect Aug 15/1977 No effect No effect No effect Sep 10/1979 No effect No effect Aug 01/1978 No effect No effect No effect No effect No effect No effect No effect No effect Aug 15/1977 No Effect (See NOTE) No Effect Aug 01/1978 Aug 15/1977

Page 2 Jan 13/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

P&WC SB No.

ATA SB No.

Rev. No.

1251 1252 1253 1254 1255 1256 1258 1259 1260 1261 1263 1265 1266 1269 1270 1271 1272 1275 1276 1277 1278 1279 1280 1281 1282 1283 1284 1285 1286 1287 1288 1293 1296 1298 1299 1300 1302 1303

72-1251 72-1252 72-1253 72-1254 72-1255 72-1256 72-1258 72-1259 72-1260 72-1261 72-1263 72-1265 72-1266 72-1269 72-1270 72-1271 72-1272 72-1275 72-1276 72-1277 72-1278 72-1279 72-1280 72-1281 72-1282 72-1283 72-1284 72-1285 72-1286 72-1287 72-1288 72-1293 72-1296 72-1298 72-1299 72-1300 72-1302 17-1303

3 1 5 Orig. 4 1 4 1 1 2 2 2 Orig. 1 1 1 2 1 3 2 2 Orig. 3 2 Orig. Orig. 1 1 1 2 1 1 1 1 Orig. 1 6 10

PT6A-34/-34B PT6A-34 PT6A-34 PT6A-34/-34B PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34AG Cancelled - Superseded by SB1379 PT6A-34/-34AG/-34B/-36 Cancelled Cancelled PT6A-34/-34B PT6A-34/-34AG/-34B/-36 PT6A-34/-34B/-36 PT6A-34AG PT6A-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B PT6A-34/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34AG

1304 1306 1309 1310 1315

72-1304 72-1306 72-1309 72-1310 72-1315

Orig. 1 1 1 Orig.

PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG

Engine Model Applicability

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

SB LIST

Effect/Date Incorporated Aug 15/1977 Sep 10/1979 Sep 10/1979 Jun 01/1981 No Effect No Effect No Effect No Effect Jun 01/1981 Sep 10/1979 No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect Sep 10/1979 Sep 10/1979 Sep 10/1979 Aug 01/1978 No Effect No Effect Aug 01/1978 No Effect No Effect No Effect No Effect No Effect Sep 10/1979 No Effect Sep 10/1979 No Effect No Effect No Effect See NOTE No Effect (See NOTE) See NOTE No Effect Cancelled No Effect Sep 10/1979

Page 3 Jan 13/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

1316 1318 1320 1321 1322 1323 1324 1325 1326 1327 1329 1330 1331 1332 1334 1336 1338 1339 1343 1344

72-1316 72-1318 72-1320 72-1321 72-1322 72-1323 72-1324 72-1325 72-1326 72-1327 72-1329 72-1330 72-1331 72-1132 72-1334 72-1336 72-1338 72-1339 72-1343 72-1344

1 3 1 2 Orig. 1 3 1 Orig. 1 1 2 1 Orig. 1 1 2 2 2 12

PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG

1346 1352 1354 1356 1357 1358 1359 1361 1366 1367 1368 1370 1371 1372 1374 1377 1379 1381 1386 1387 1388 1389 1390

72-1346 72-1352 72-1354 72-1356 72-1357 72-1358 72-1359 72-1361 72-1366 72-1367 72-1368 72-1370 72-1371 72-1372 72-1374 72-1377 72-1379 72-1381 72-1386 72-1387 72-1388 72-1389 72-1390

6 Orig. 3 Orig. 3 2 Orig. Orig. Orig. 3 1 1 Orig. 5 1 3 2 7 3 Orig. 3 1 6

PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-36 PT6A-34/-34AG/-34B/-36 PT6A-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

SB LIST

Effect/Date Incorporated Jun 02/1980 No Effect Jan 21/1985 No Effect No Effect No Effect No Effect No Effect Jun 01/1982 No Effect No Effect Jun 01/1982 No Effect No Effect No Effect Cancelled No Effect No Effect Jun 01/1981 No Effect (See NOTE) No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect Feb 21/1984 No Effect No Effect Apr 26/1983 Feb 21/1984 Nov 03/1987 Feb 21/1984 No Effect No Effect Nov 03/1987 No Effect No Effect Jan 21/1985

Page 4 Jan 13/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

1391 1393 1394 1395 1396 1397 1398 1399 1403

72-1391 72-1393 72-1394 72-1395 72-1396 72-1397 72-1398 72-1399 72-1403

2 2 Orig. Orig. 2 4 Orig. Orig. 10

PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 Cancelled PT6A-34AG PT6A-34/-36

1404 1405 1407 1408 1409 1410 1411 1416 1418 1421 1422 1426 1427 1428 1430 1431 1433 1434 1439 1441 1445 1446 1447 1448 1454 1455 1457 1459 1461 1465 1466 1469 1470 1472

72-1404 72-1405 72-1407 72-1408 72-1409 72-1410 72-1411 72-1416 72-1418 72-1421 72-1422 72-1426 72-1427 72-1428 72-1430 72-1431 72-1433 72-1434 72-1439 72-1441 72-1445 72-1446 72-1447 72-1448 72-1454 72-1455 72-1457 72-1459 72-1461 72-1465 72-1466 72-1469 72-1470 72-1472

10 4 Orig. Orig. 1 2 Orig. 1 Orig. 7 5 3 2 Orig. 6 1 Orig. 6 2 2 4 6 6 6 Orig. 4 1 2 2 4 Orig. 2 2 5

PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG/-34B/-36 PT6A-34/-34AG/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-36 PT6A-34/-34B/-34AG/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-34AG/-34B/-36 PT6A-34AG

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

SB LIST

Effect/Date Incorporated No Effect No Effect Sep 16/1985 No Effect No Effect No Effect No Effect No Effect No Effect (See NOTE) No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect Nov 08/1988 No Effect No Effect No Effect No Effect No Effect Mar 07/1989 Mar 07/1989 No Effect No Effect No Effect No Effect No Effect No Effect Jan 05/2007 Jun 06/2003 No Effect No Effect Nov 15/1993 No Effect No Effect No Effect

Page 5 Jan 13/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

Effect/Date Incorporated

1473 1475 1476 1477 1478 1479 1480 1481 1483 1484 1486 1487 1488 1489 1490 1492 1493 1494 1495 1498 1499 1500 1501 1506 1508 1513 1514 1516 1518 1519 1520 1521 1522 1524 1527 1528 1534 1537 1538 1540 1544 1545 1550 1553

72-1473 72-1475 72-1476 72-1477 72-1478 72-1479 72-1480 72-1481 72-1483 72-1484 72-1486 72-1487 72-1488 72-1489 72-1490 72-1492 72-1493 72-1494 72-1495 72-1498 72-1499 72-1500 72-1501 72-1506 72-1508 72-1513 72-1514 72-1516 72-1518 72-1519 72-1520 72-1521 72-1522 72-1524 72-1527 72-1528 72-1534 72-1537 72-1538 72-1540 72-1544 72-1545 72-1550 72-1553

Orig. 2 Orig. Orig. Orig. 1 Orig. 1 Orig. 1 Orig. 1 Orig. Orig. Orig. 1 Orig. Orig. 5 1 1 Orig. Orig. 3 Orig. Orig. 1 3 1 1 2 5 Orig. Orig. Orig. 2 3 5 4 1 1 Orig. 1 Orig.

PT6A-34/-34AG/-34B/-36 PT6A-34/-34B/-34AG/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B PT6A-34/-34AG/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-34AG

No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect Feb 02/2001 No Effect No Effect No Effect No Effect Feb 02/2001 No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect Nov 21/2008 No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

SB LIST

Page 6 Jan 13/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

Effect/Date Incorporated

1554 1555 1556 1557 1558 1560 1561 1562 1563 1564 1565 1566 1567 1568 1570 1571 1572 1573 1578 1590 1591 1594 1595 1598 1599 1606 1610 1612 1613 1614 1621 1627 1628 1629 1630 1631 1637 1638 1639 1642 1645 1647 1650 1651

72-1554 72-1555 72-1556 72-1557 72-1558 72-1560 72-1561 72-1562 72-1563 72-1564 72-1565 72-1566 72-1567 72-1568 72-1570 72-1571 72-1572 72-1573 72-1578 72-1590 72-1591 72-1594 72-1595 72-1598 72-1599 72-1606 72-1610 72-1612 72-1613 72-1614 72-1621 72-1627 72-1628 72-1629 72-1630 72-1631 72-1637 72-1638 72-1639 72-1642 72-1645 72-1647 72-1650 72-1651

Orig. 5 2 1 1 4 3 Orig. 3 3 Orig. Orig. 2 8 2 2 Orig. Orig. 4 2 2 Orig. Orig. 1 Orig. Orig. 2 Orig. 1 1 Orig. Orig. Orig. Orig. 1 Orig. 1 1 Orig. 1 2 Orig. 1 Orig.

PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-36 PT6A-34/-34AG/-36 PT6A-34/-34AG/-36 PT6A-34/-34AG/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34AG PT6A-34/-34B/-34AG/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-36 PT6A-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-34AG/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-135A PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36

No Effect No Effect No Effect No Effect No Effect No Effect No Effect Jun 06/2003 No Effect No Effect No Effect Dec 06/2001 No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect Apr 25/2008 No Effect No Effect No Effect No Effect Nov 21/2008 No Effect Apr 25/2008 No Effect No Effect No Effect Nov 21/2008 No Effect No Effect

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

SB LIST

Page 7 Jan 13/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

Effect/Date Incorporated

1652 1653 1654 1655 1657 1658 1659 1661 1662 1663 1664 1665 1666 1668 1670 1672 1674 1675 1677 1678 1679 1681 1683 1684 1685 1687 1689 1690 1691 1692 1693 1694 1695 1698 1699 1700 1705 1709 1728 1747 1748 1759 1760 1761

72-1652 72-1653 72-1654 72-1655 72-1657 72-1658 72-1659 72-1661 72-1662 72-1663 72-1664 72-1665 72-1666 72-1668 72-1670 72-1672 72-1674 72-1675 72-1677 72-1678 72-1679 72-1681 72-1683 72-1684 72-1685 72-1687 72-1689 72-1690 72-1691 72-1692 72-1693 72-1694 72-1695 72-1698 72-1699 72-1700 72-1705 72-1709 72-1728 72-1747 72-1748 72-1759 72-1760 72-1761

1 Orig. 2 2 1 3 1 1 1 2 Orig. 1 1 1 3 1 Orig. Orig. Orig. Orig. Orig. 4 Orig. Orig. Orig. Orig. Orig. 4 Orig. 1 Orig. 1 Orig. 1 Orig. Orig. 1 Orig. 1 Orig. 1 1 Orig. 3

PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34 PT6A-34 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34 PT6A-34AG PT6A-34 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36

No Effect No Effect No Effect No Effect No Effect Apr 25/2008 No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect Dec 10/2010 No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

SB LIST

Page 8 Jan 13/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

Effect/Date Incorporated

1762 1763 1766 1768 1773 1781 1782 1792 1795 1796 1797 1800

72-1762 72-1763 72-1766 72-1768 72-1773 72-1781 72-1782 72-1792 72-1795 72-1796 72-1797 72-1800

1 2 Orig. 4 Orig. Orig. Orig. 2 Orig. Orig. Orig. 1

PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG PT6A-34/-34AG/-34B/-36 PT6A-34/-34AG/-34B/-36 PT6A-34AG PT6A-34AG PT6A-34 PT6A-34 PT6A-34/-34AG/-34B/-36 PT6A-34 PT6A-34/-34AG/-34B/-36

No No No No No No No Jul No No No No

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

SB LIST

Effect Effect Effect Effect Effect Effect Effect 22/2019 Effect Effect Effect Effect

Page 9/10 Jan 13/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE OF CONTENTS SUBJECT

PAGE

TITLE PAGE REVISION HIGHLIGHTS RECORD OF REVISIONS RECORD OF TEMPORARY REVISIONS LIST OF CHAPTER/SECTION/SUBJECTS TEMPORARY REVISION INDEX SERVICE BULLETIN LIST

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CONTENTS

Page 1/2 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Jul 22/2019 Jul 22/2019

Contents

1 2 blank

Jul 22/2019 Jul 22/2019

Introduction

1 2 3 4 5 6 7 8 blank

Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 deleted 20 deleted

Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019

Special Tools Fixtures and Equipment

Consumable Materials

1 2 3 4 5

CHAPTER SECTION

Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019

PAGE 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44

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INTRODUCTION LEP

DATE Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019 Jul 22/2019

Page 1/2 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE OF CONTENTS SUBJECT

PAGE

INTRODUCTION 1.

General

1

2.

Customer Service

1

3.

Accessories Support

2

4.

How to Use this Manual

2

A.

Chapter/Section/Subject Numbering

2

B.

Chapter 72

3

C.

Other Chapters

3

5.

Engine and Module Concept

3

6.

Engine Part Nomenclature

4

7.

Directional References

4

8.

Maintenance Concept

4

A.

Line Maintenance

4

B.

Heavy Maintenance

4

Supplementary Publications

4

10.

Service Bulletins

4

11.

Abbreviations and Symbols

5

9.

SPECIAL TOOLS/FIXTURES AND EQUIPMENT 1.

General

1

2.

Special Tools

1

3.

Special Equipment

16

CONSUMABLE MATERIALS 1.

General

1

2.

Consumable Materials

1

3.

Suppliers and Supplier Services

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INTRODUCTION CONTENTS

18

Page 1/2 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

INTRODUCTION 1.

General A.

This maintenance manual contains the recommended procedures for maintaining PT6A-34/-34AG/-34B/-36 series engines manufactured by Pratt & Whitney Canada. Personnel involved with engine maintenance should acquaint themselves with the contents of the following introductory paragraphs for full comprehension of the information contained in this manual.

B.

Any discrepancies, problems or suggestions regarding this publication should be forwarded in writing, using the Pratt & Whitney Canada Customer Feedback Sheet (RSVP), to: Pratt & Whitney Canada Corp. 1000 Marie-Victorin Blvd Longueuil, Quebec Canada J4G 1A1 Attention: Manager Publications Dept (05MS1) Website: www.pwc.ca E-mail: [email protected]

2.

C.

Customer Feedback Sheets are enclosed with new manuals and each subsequent revision. Additional forms may be obtained by contacting: The Supervisor, Publications Customer Services, at the above address.

D.

The on-line Customer Feedback Sheet (RSVP form) is also available on the Pratt & Whitney Canada website (www.pwc.ca).

E.

Procedures in this manual may be accomplished with the engine installed or removed from the airframe. This manual will be revised as necessary to incorporate any changes as they arise and also incorporate latest approved procedures and data. This manual is not customized to any particular airframe installation. Configurational variations that may arise as a result of installation or peculiar requirement will be dealt with in the text as they occur.

Customer Service Customer Service representatives maintain contact with operators and service activities and are available for investigation of any specific difficulty or problem. Request for assistance should be directed to: Pratt & Whitney Canada Corp. 1000 Marie-Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Attention: Customer Service Request for AOG support may also be directed to:

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INTRODUCTION

Page 1 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

Pratt & Whitney Canada Corp. 1000 Marie-Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Attention: Customer First Centre (CFirst) (01TS4) REF: CFirst (24-hour service) US and Canada: 1-800-268-8000 International: (International Access Code) -8000-268-8000 Other: 1-450-647-8000 Fax: 1-450-647-2888 Email: [email protected] Telephone or write to the manager of the Spare Parts Sales Department to get details about how to order parts. You can also get information from the Customer First Centre (CFirst). Pratt & Whitney Canada Corp. 1000 Marie-Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Attention: Spare Parts Sales Department 3.

Accessories Support Accessories can be sent for repair or full overhaul to: P&WC Accessories Services 7007, De La Savane, St-Hubert, Quebec Canada J3Y 8Y9

4.

How to Use this Manual A.

Chapter/Section/Subject Numbering Subject matter in this manual is separated into specific Chapters, Sections and Subjects in accordance with ATA Specification No. 100. Each chapter is divided into sections and each section is divided into units. These three elements are shown in large bold numbers at the lower right hand corner of each page, where applicable. Chapters are separated by tab dividers. Chapters contained in this manual are as follows: AIRWORTHINESS LIMITATIONS 61 70 71 72 73

Life Limited Parts Propeller Control Standard Practices Power Plant Engine Fuel and Control Systems

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INTRODUCTION

Page 2 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

74 75 76 77 79 B.

Ignition System Air System Engine Controls Engine Indicating System Oil System

Chapter 72 The engine chapter is further broken down into sections: 72-01 72-10

Power Section Reduction Gearbox

NOTE: An engine that has more than one RGB, will use sequential numbers i.e., 72-11-00, 72-12 -00 etc. 72-20 Air Inlet Section 72-30 Compressor Section 72-40 Combustion Section 72-50 Turbine Section 72-60 Accessory Gearbox C.

Other Chapters Chapter/Section breakdown for the other Chapters is extensive and is shown in the Table of Contents for each Chapter.

5.

Engine and Module Concept A.

For the PT6A-34 and PT6A-36, an engine comprises two modules: power section module (PSM) and gas generator module (GGM), each maintained at its own Time Between Overhaul (TBO) schedule (Ref. 72-00-00, Transport Canada Approved Service Bulletins); an approved engine modular program will define the procedures. Scheduled overhaul of a module is due when the TBO expires, and it may be shipped separately, or as a component of the complete engine (Ref. 72-00-00, SERVICING).

B.

Before shipping a power section module (PSM) or gas generator module (GGM) for overhaul, remove the classified power turbine stator assembly from the PSM and retain with the GGM as a matched unit. The classified power turbine stator assembly and GGM will form the basis for a complete engine when assembled to the new PSM (Ref. 72-50-03). Record power turbine stator assembly removal in PSM and GGM documents.

C.

An engine maintains its own TBO (Ref. 72-00-00, Transport Canada Approved Service Bulletins). When the TBO expires, the engine is due for scheduled overhaul.

D.

An engine or module with a valid TBO may be returned for unscheduled overhaul (Light Overhaul), i.e. unusual oil conditions, lightning strike, sudden stoppage, engine overspeed, etc. (Ref. 72-00-00, Unscheduled Inspection).

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INTRODUCTION

Page 3 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

6.

Engine Part Nomenclature For engine areas, bearings, stations, and flanges, refer to 72-00-00, Description and Operation, Figures 1 through 4.

7.

Directional References The terms right and left, clockwise and counterclockwise, upper and lower and similar references will apply to the engine as viewed from the rear, with the engine in a horizontal position and the accessory gearbox facing the viewer.

8.

Maintenance Concept WARNING:

PERSONNEL HANDLING ENGINES OR COMPONENTS REMOVED FROM AGRICULTURAL AIRCRAFT MUST EXERCISE EXTREME CARE TO AVOID PHYSICAL CONTACT WITH SURFACES THAT MAY BE CONTAMINATED BY HIGHLY TOXIC OR CORROSIVE CHEMICALS. USE PROTECTIVE CLOTHING AND BREATHING EQUIPMENT OR DISPOSABLE FACIAL MASKS AT ALL TIMES UNTIL COMPONENTS ARE SATISFACTORILY DECONTAMINATED BY WATER WASHING. SIMILARLY, TAKE CARE IN THE DISPOSAL OF ANY PACKAGING OR CONTAINERS FOR ENGINES OR COMPONENTS THAT MAY BE CONTAMINATED.

The maintenance functions detailed in this manual fall into two categories: Line Maintenance and Heavy Maintenance. Repairs beyond the levels detailed in this manual are not recommended as maintenance functions and should be done by an approved overhaul facility. A.

Line Maintenance The scope of line maintenance consists of removal and installation of external components and engine accessories. All procedures in this manual are to be considered line maintenance in the absence of the words ‘‘(Heavy Maintenance Only)’’ appearing with the procedure title in Maintenance Practices.

B.

Heavy Maintenance Heavy maintenance details removal, installation and repair of components or parts normally considered beyond the capabilities of the average line maintenance facility.

9.

Supplementary Publications Personnel concerned with the maintenance of the engines should familiarize themselves with the contents of the Illustrated Parts Catalog (P&WC Manual P/N 3021244) which lists and describes the saleable parts of the engines and illustrates their inter-relationships.

10.

Service Bulletins Service bulletins will be issued as required to provide information or instructions for modifying engines or parts to the latest configuration.

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

INTRODUCTION

Page 4 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

11.

Abbreviations and Symbols The following is a list of abbreviations and symbols used throughout this manual: AGB AMS Assy ATA beta BRG CCW CG CSU CT CW °C °F °R °K del del P del T5 DELRTH Dia. Dim eshp FCU FI FIR FOD FPI FWD (Fwd) G GGM GI Hg HP hr HSI ID Imp in.

Accessory Gearbox Aerospace Material Specification Assembly Air Transport Association Range of propeller blade angle between fine pitch stop and maximum reverse pitch setting Bearing Counterclockwise Center of Gravity Constant Speed Unit Compressor Turbine Clockwise Degrees Celsius (Centigrade) degrees Fahrenheit degrees Rankin degrees Kelvin delta (P observed/P Standard Day) Engine Torquemeter Pressure, in. Hg. T5 Temperature Trim Value Delta Root Theta Diameter Dimension equivalent shaft horse power Fuel Control Unit Flight Idle Full Indicator Reading Foreign Object Damage Fluorescent Penetrant Inspection Forward Gravitational Constant Gas Generator Module Ground Idle Mercury High Pressure hour Hot Section Inspection Inside Diameter Imperial inch

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INTRODUCTION

Page 5 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

in.Hg. IPC ITT (T5) kg lb. lb.in./lbf.in. LH LP Max. min Min. mm NA Nf (NF) Ng (NG) No. Np OD Pam Para. PD P/N PP pph Psgb psi psig PSM PT PTO P&WC PWC Px Py Po P1 P2 P3 (REF.) RGB RH RTD

Inches of Mercury Illustrated Parts Catalog Interturbine Temperature kilogram pound pound force inch Left-hand Low Pressure Maximum minute Minimum millimeter Not Applicable Power Turbine Speed (rpm or %) Gas Generator Speed (rpm or %) Number Propeller Speed (rpm or %) Outside Diameter Ambient Barometric Pressure Paragraph Pitch Diameter Part Number Plenum Pressure pounds per hour Reduction Gearbox Static Pressure pounds per square inch pounds per square inch gage Power Section Module Power Turbine Power Take Off Pratt & Whitney Canada Corp. Special Tool Prefix Letters - Engine Control Pressure (Bleed Valve) Governor Servo Pressure Bypass Pressure Unmetered Fuel Pressure or Intake Pressure Metered Fuel Pressure Compressor Discharge Air Pressure reference Reduction Gearbox (Propeller) Right-hand Resistance Temperature Device

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INTRODUCTION

Page 6 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

RTH rpm SB SCFM SED sfc SG shp SOI SPOP T tam TBA TBO theta TIG T1 T5 (ITT) UOS USA Wf

Root Theta revolutions per minute Service Bulletin Standard Cubic Feet per Minute Small Exit Duct specific fuel consumption (lb/shp/hr) Specific Gravity shaft horse power Specific Operating Instructions Service Process Operation Procedure Temperature Ambient Air Temperature To be advised Time Between Overhaul T observed/T standard day Tungsten Inert Gas (Welding method) Engine Inlet Temperature Inter-turbine Temperature Unless Otherwise Specified United States of America Fuel Flow (lb/hr)

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INTRODUCTION

Page 7/8 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

SPECIAL TOOLS/FIXTURES AND EQUIPMENT 1.

General This section gives data about the special tools and the fixtures and equipment required to maintain the engine.

2.

Special Tools Special tools, required to maintain the engine are listed in Table 1. Refer SIL GEN-022 for the list of tool suppliers, then send a purchase order for the special tools, listed in Table 1. When you order special tools, include the prefix ’PWC’ as a component of the tool part number, e.g. PWC32073, Sling. TABLE 1, Special Tools Maintenance Level Part No.

Name

CH/SE/SU

Line

Heavy

PWC30037

Sling - Replaced by PWC70099

72-00-00

X

X

PWC30046-52

Puller (Pre-SB1386)

72-60-00

X

X

PWC30046-54

Puller (Pre-SB1386)

72-60-00

X

X

PWC30046-57

Puller

72-10-00

X

X

PWC30051-01

Base

72-60-00

X

PWC30051-02

Drift

72-60-00

X

PWC30052

Puller

72-60-00

X

PWC30054

Drift (Pre-SB1386)

72-60-00

X

PWC30075

Drift

72-10-00

X

X

72-60-00

X

X

PWC30114-08

Wrench

77-20-01

X

X

PWC30114-09

Wrench (Pre-SB1232)

61-20-00

X

X

PWC30114-16

Wrench

61-20-00

X

X

PWC30128-04

Puller

72-60-00

X

PWC30269

Ring

72-00-00

X

X

PWC30271-100

Spreader - Replaced by PWC31771

72-30-04

X

X

PWC30274

Base

72-60-00

PWC30328

Puller (Replaced by PWC50726)

79-20-02

HSI

X X

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

X

Page 1 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Special Tools (Cont’d) Maintenance Level Part No.

Name

CH/SE/SU

Line

Heavy

PWC30331

Wrench

72-60-00

X

X

PWC30332

Wrench

72-50-02

X

X

PWC30335

Spreader

72-50-02

X

X

PWC30336

Protector

72-50-02

X

X

PWC30338

Sling - Replaced by PWC70652 and PWC70653

72-00-00

X

X

PWC30373

Puller/Pusher

72-60-00

PWC30403

Puller

72-50-02

X

X

PWC30405

Fixture

73-10-05

X

X

PWC30415

Compressor

72-60-00

X

X

PWC30416

Puller

73-10-05

X

X

PWC30425

Crimping Pliers

77-20-01

PWC30458

Squeezer

72-50-02

PWC30478

Spacer

72-50-01

PWC30499-50

Gage

72-60-00

X

X

PWC30506

Rig

73-10-05

X

X

PWC30518

Puller

79-20-04

X

X

PWC30530

Plug

73-10-05

X

X

PWC30556

Puller

79-20-02

X

X

PWC30675

Drift

72-60-00

X

X

PWC30800

Engine Stand - Replaced by PWC34300

72-00-00

X

X

PWC30854

Drift

72-60-00

X

PWC30863

Puller (Obsolete - Replaced by PWC32822)

72-50-01

X

PWC31771

Spreader

72-30-04

PWC32072

Puller - Replaced by PWC57233

72-10-00

PWC32073

Sling - Replaced by PWC34073

72-00-00

PWC32080

Pad, Engine Mount

72-00-00

X

PWC32179

Base Assembly - Replaces PWC30322

72-10-00

X

HSI

X

X X

X X

X

X X

X

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

X

Page 2 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Special Tools (Cont’d) Maintenance Level Part No.

Name

CH/SE/SU

Line

Heavy

HSI

PWC32209

Adapter

72-50-01

X

PWC32212

Alignment Pins

72-50-03

X

PWC32271

Wash Tube

71-00-00

PWC32275

Split Plate

72-60-00

X

PWC32366

Pusher

73-10-05

X

PWC32380

Radius Gage

72-50-01

X

PWC32396

Jackscrew, Accessory Gearbox

72-60-00

X

X

PWC32396-400

Jackscrew, Gas Generator Case From Diffuser Case

72-60-00

X

X

PWC32420

Sling - Replaced by PWC51861

72-00-00

PWC32483

Cutter

72-30-00

X

PWC32484

Gage

72-30-00

X

PWC32677-100

Washcart, Compressor

71-00-00

X

X

PWC32677-300

Washcart, Compressor Fuel Nozzle (In-situ cleaning)

71-00-00

X

X

PWC32811

Fixture

73-10-05

X

X

PWC32822

Puller (Obsolete - Replaced by PWC71559)

72-50-01

PWC34073

Sling - Replaced by PWC70099

72-00-00

PWC34128

Wheel, Shroud Grinding

72-50-01

PWC34300

Engine Stand - Replaced by PWC51140

72-00-00

X

PWC34752

Mount Ring Adapter

72-00-00

X

PWC34910-101

Borescope Assembly

72-00-00

X

X

PWC34910-200

Guide Tube

72-00-00

X

X

PWC34913

Holding Fixture

72-00-00

X

PWC34941

Wrench

72-00-00

X

X

PWC37088-001

Drift

72-60-00

X

X

PWC37088-002

Drift

72-60-00

X

X

PWC37088-003

Drift

72-60-00

X

X

PWC37917

Dresser

72-50-01

X

X

X

X

X X

X X

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

X

X

Page 3 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Special Tools (Cont’d) Maintenance Level Part No.

Name

CH/SE/SU

Line

Heavy

PWC37918

Grinder

72-50-01

X

PWC42034

Jackscrew - Replaced by PWC32396-400

72-60-00

X

PWC50057

Drill Kit

72-50-02

X

X

PWC50060

Injector

72-50-02

X

X

PWC50272

Drift

72-60-00

X

X

PWC50373

Bracket, Lifting

72-00-00

PWC50726

Puller

79-20-02

X

X

PWC50726-100

Puller

79-20-02

X

X

PWC50986

Puller, Check Valve

79-20-04

X

X

PWC51140

Replaced by PWC70907

72-00-00

X

X

PWC51861

Sling

72-00-00

X

X

PWC54246

Puller/Pusher, Tubes (Alternative to PWC32366)

73-10-05

X

X

PWC57233

Puller

72-10-00

PWC70099

Sling (PS - without prop)

72-00-00

PWC70334

Mounting Ring

72-00-00

X

PWC70652

Sling (PS - with prop)

72-00-00

X

PWC70653

Sling Adapter (used with PWC70652)

72-00-00

X

PWC70838

Puller, Oil Seal Carrier

72-60-00

X

X

PWC70869

Drift, Lip Seal

72-60-00

X

X

PWC70907

Stand Assembly, Engine (Obsolete - Replaced by PWC71835)

72-00-00

X

X

PWC71559

Puller (Alternate to PWC32822)

72-50-01

PWC71835

Build Stand, Engine Assembly (Alternate to PWC70907)

72-00-00

X

X

PWC90086

Spray Chamber

73-10-05

X

X

HSI X

X

X X

X

X

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TOOLS/FIX/EQUIP

Page 4 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC30037

PWC30046-57

PWC30052

PWC30046-52

PWC30051-01

PWC30054

PWC30046-54

PWC30051-02

PWC30075

Special Tool Illustrations

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 5 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC30114-08

PWC30128-04

PWC30274

PWC30114-09

PWC30269

PWC30328

PWC30114-16

PWC30271-100

PWC30331

Special Tool Illustrations P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 6 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC30332

PWC30338

PWC30405

PWC30335

PWC30373

PWC30415

PWC30336

PWC30403

PWC30416

PWC30332

Special Tool Illustrations

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 7 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC30425

PWC30499-50

PWC30530

PWC30458

PWC30506

PWC30556

PWC30478

PWC30518

PWC30675

Special Tool Illustrations P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 8 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC30800

PWC31771

PWC32080

PWC30854

PWC32072

PWC32179

TOOL NOT ILLUSTRATED

PWC30863

PWC32073

PWC32209

PWC32209

Special Tool Illustrations

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 9 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC32212

PWC32366

PWC32396-400

TOOL NOT ILLUSTRATED

PWC32271

PWC32380

PWC32420

PWC32275

PWC32396

PWC32483

PWC32483

Special Tool Illustrations P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 10 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC32484

PWC32811

PWC34128

PWC32677-100

PWC32822

PWC34300

PWC32677-300

PWC34073

PWC34752

PWC32484

Special Tool Illustrations

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 11 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC34910-101

PWC34941

PWC37088-003

PWC34910-200

PWC37088-001

PWC37917

PWC34913

PWC37088-002

PWC37918

Special Tool Illustrations P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 12 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC42034

PWC50272

TOOL NOT ILLUSTRATED

PWC50057

PWC50373

PWC50726-100

TOOL NOT ILLUSTRATED

PWC50986

TOOL NOT ILLUSTRATED

PWC50060

PWC50726

PWC51140

Special Tool Illustrations

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 13 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC51861

PWC70099

TOOL NOT ILLUSTRATED

PWC70653

TOOL NOT ILLUSTRATED

PWC51861

PWC54246

PWC70334

TOOL NOT ILLUSTRATED

PWC57233

TOOL NOT ILLUSTRATED

PWC70838

TOOL NOT ILLUSTRATED

PWC70652

TOOL NOT ILLUSTRATED

PWC70869

TOOL NOT ILLUSTRATED

Special Tool Illustrations P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 14 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PWC70907

TOOL NOT ILLUSTRATED

PWC71559

TOOL NOT ILLUSTRATED

PWC71835

TOOL NOT ILLUSTRATED

PWC90086

TOOL NOT ILLUSTRATED

Special Tool Illustrations

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 15 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

DELETED. 3.

Special Equipment Special equipment listed in Table 2 is considered as any equipment, material , fixture which is not PWC derived and is not considered a consumable material. TABLE 2, Special Equipment Name

Part No.

Supplier

Turbine Temperature Indicating System Test Set (Ref. 77-20-01, 77-20-00)

TT1000A

Barfield Instrument Corp. 4101 NW 29th St. P.O. Box 527705 Miami, FL 33152-7705 USA Tel.: (305) 871-3900

Pressure Tester (Ref. 73-10-05)

2311FA

Barfield Instrument Corp.

A.C./D.C. Arc Welding Machine; 150 amp minimum capacity with close control in 15 to 75 amp. range. (High frequency control for ease of arc starting is desirable) (Ref. 70-00-00).

P and H Model DA-300-HF-GW or equivalent

Local Purchase

Air Pressure Regulator: 100 psi input, 0 to 100 psi output. (Ref. 75-30-00)

Local Purchase

Shutoff Valve (Air Line) (Ref. 71-00-00, 75-30-00)

Local Purchase

Pressure Gage; 0 to 75 psi, accuracy ±5 percent (Ref. 71-00-00, 75-30-00)

Local Purchase

Argon Regulator (Ref. 70-00-00)

Airco 8407 or equivalent

Local Purchase

Flowmeter Block Assemblies, 2 required (Ref. 70-00-00)

Airco 830-1327 or equivalent

Local Purchase

Shielded Arc Torch; with provision for supply of inert gas (argon) and cooling water. (Ref. 70-00-00)

Linde Model HW-10 or Airco H35B or equivalent

Local Purchase

Shielded Arc Torch; with provision for supply of inert gas (argon) and cooling water. (Ref. 70-00-00)

Linde Model HW-9 or Airco H20A or equivalent

Local Purchase

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

TOOLS/FIX/EQUIP

Page 16 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Special Equipment (Cont’d) Name

Part No.

Supplier

Ground Cable; 25 feet approx.

Size 0

Local Purchase

Arc Cable, metallic; 25 feet approx.

Size 0

Local Purchase

Argon Hose; 25 feet approx.

Local Purchase

Two Stainless Steel Tanks; 6 gallon capacity and capable of withstanding 50 psi (Ref. 71-00-00).

Local Purchase

Two Stainless Steel Tanks; 5 gallon capacity and capable of withstanding 50 psi (Ref. 71-00-00).

Local Purchase

Tubing, Stainless Steel 5⁄16 inch ID, length as required (Ref. 71-00-00).

Local Purchase

Restrictor; 0.062 inch. (Ref. 71-00-00)

Local Purchase

Nitrogen or Clean Air Pressure Supply regulated to 50 psig

Local Purchase

Pressure Gage Adapter threaded to suit pressure gage (item No. 6) and bleed valve cover (0.250-28 UNJF-3B)

Local Manufacture/ Purchase

Test Rig Adapters, threaded to accept tubing for pressure regulator (item No. 4) shut-off valve (item No. 5) and bleed valve cover (0.250-28-UNJF-3B)

Local Manufacture/ Purchase

Fuel Nozzle Flushing Fixture (Ref. 73-10-05)

Local Manufacture

Stainless Steel Container or Tray, Perforated (to suit Electrosonic Cleaner) (Ref. 73-10-05)

Local Manufacture

Ultrasonic Cleaner, Esterline Angus (Ref. 73-10-05)

Model T-12, or similar (See NOTE) (Ref. 73-10-05)

Esterline Corp. P.O. Box 2400 Indianapolis, IN 26224, USA or

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TOOLS/FIX/EQUIP

Page 17 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Special Equipment (Cont’d) Name

Part No.

Supplier Instro Test Ltd. 1024 Notre Dame Lachine, Quebec, Canada

Model KS 5518 or Sonac S-2

Electrosonic, Cleaner (Ref. 79-20-02, OIL FILTER, HOUSING AND CHECK VALVE - MAINTENANCE PRACTICES and 73-10-07, PNEUMATIC LINE (P3) MAINTENANCE PRACTICES)

Kell-Strom Tool Co. 214 Church Street Wethersfield, CT 06109 USA Tel.: (860) 529-6851 or Tel.: (860) 721-0658 (AOG service) Fax: (860) 257-9694

NOTE : In the event of non-availability of ultrasonic cleaning equipment, operators should ship fuel nozzles requiring cleaning and testing to an approved overhaul facility, or to a maintenance base having suitable equipment. Local Purchase

Shut-off Valve (Fluid Line) (Ref. 72-00-00) TD1032L

Locking Tool (Keensert) (Ref. 72-30-01)

Tridair Industries 3000 West Lomita Blvd. Torrance, CA 90505, USA or Interfast Inc. 21 Constellation Court Rexdale, Ontario Canada M9W 1K4

Oil Filter Element Rinsing and Debris Apparatus Kit (Ref. 79-20-02)

AVL-OFRA

Aviation Laboratories 5401 Mitchelldale #B6 Houston, TX 77092 USA Tel.: 713-864-6677 Tel.: 800-256-6876 Fax: 713-864-6990

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TOOLS/FIX/EQUIP

Page 18 Feb 18/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

CONSUMABLE MATERIALS 1.

General This section gives data about the consumable materials listed in this manual.

2.

Consumable Materials The term ‘‘Consumable Material’’ shall be defined as an expendable substance which is not separately obtained from Pratt & Whitney Canada and which may be applied to the engine or its parts during maintenance. In many instances, products such as cleaning materials, are mentioned by their trade names to assist the operator in identifying the product types. These names are representative examples only and their inclusion does not necessarily exclude the use of other equivalent products. Specification numbers applying to consumable materials are basic numbers and shall be interpreted to include all revisions and amendments thereto. Material Safety Data Sheets (MSDS) containing information about Trade Name, Safety Hazards, Health Hazards, Reactivity, Spill or Leak Procedures, Special Protection Information, Special Precautions, and Transportation and Labelling are available from the manufacturer of the products. Read the data sheets prior to using the consumable materials. A supplier code with a (m) after the code is the manufacturer of the material and a supplier code with a (s) after the code is a supplier/distributor of the material. Table 1 describes consumable materials used in the maintenance of the engine. TABLE 1, Consumable Materials

Item

Nomenclature/Specification

Supplier Code

PWC01-001

Fuel, Engine (Ref. Approved Service Bulletins)

A0001

PWC03-001

Oil, Engine Lubricating (Ref. Approved Service Bulletins)

A0001

PWC03-002

Fluid, Calibrating US MIL-PRF-7024 Type II PMC 9041

A0015

PWC04-001

Grease, Synthetic General Purpose MIL-G-23827 QPL-23827-18 NATO G-354 PMC79671

A0001

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CONSUMABLE MATERIALS

Page 1 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-002

Dye, Layout Micro Supreme No. 142 PMC4062

01058

PWC05-003

Cloth, Abrasive Silicone Carbide

A0001(s)

PWC05-005A

Emulsifier Witconate HC-59B

36382, 85665

PWC05-007

Fluid, Leak Check Leak Tec 372 PMC9569

03530

PWC05-009

Ammonium Bifluoride Ref. Crystalline

A0001(s)

PWC05-011

Ammonium Nitrate Powder Form 1.725 Specific Gravity US MIL-A-175 PMC1517

A0001(s)

PWC05-014

Cloth, Abrasive Ref. Scotch Brite

A0001(s), 28112

PWC05-018

Pencil, Metal Marking Hard Ref. Design Spectracolor Silver 1428 PMC4094

22980(m)

PWC05-18A

Pencil, Metal Marking Hard Ref. Stock No. 02460 for Prismacolor Verithin 753 or Stock No. 03375 for Prismacolor Thick Lead 949 PMC 4059-7 (Silver)

22980(m)

PWC05-18E

Pencil, Metal Marking Hard Ref. Best No. 349 Red PMC4059-6

70362, A0006

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CONSUMABLE MATERIALS

Page 2 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-019

Compound, Lapping Silicon Carbide Clover 2A No. 400 Grit US ANSI B74.10, ANSI B74.12 PMC3013

05972

PWC05-027

Ink, Marking Ref. Carter 21451 Black

S0089

PWC05-031

Flux, Resin Ref. No. 1545 PMC2000

09185(m), 10178(m)

PWC05-037

Enamel, Epoxy Aluminized Ref. Desoto Super -Koropon 529K002 Base + 910K021 Curing Solution PMC1746, PMC1747 PWA569 (CPW269)

A0097(s), S0098(s), ONYS9(m)

PWC05-038

Hydrogen Peroxide Commercial Grade 32.5 to 35% US Fed. A-A-53707 PMC1602

A0001(s), 08338

PWC05-041

Dye, Layout Ref. Dykem Steel Blue PMC74002

98148(m)

PWC05-046A

Marker, Ink Fast Drying, No. 57 400-1 Black, 400-2 Red, 400-7 Purple

S0036

PWC05-046C

Marker, Ink Ref. Dykem KX425 or DykemKXX122

98148(m)

PWC05-048

Pen, Marking Ref. Brushpen No. 57

S0036

PWC05-048A

Pen, Marking Ref. Felt Wick Pen

A0013, 30133

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CONSUMABLE MATERIALS

Page 3 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-048B

Ref. PWC05-331

PWC05-049

Material, Masking Ref. Brady Mask PMC74110

A0026

PWC05-050

Nitrogen Technical Grade Ref. Minimum Purity 99% US. BB-N-411 PMC2212

A0001(s), 0BZD7, 09563

PWC05-052

Sheathing, Heat Shrinkable Ref. Silicone Rubber 1 in. (25.4 mm) Dia.

A0001(s), 06090

PWC05-053

Sheet, Polyethylene Ref. Open 0.002 in. (0.051 mm) thick polyethylene sheet PMC 4205

A0001(s)

PWC05-054

Bag, Polyethylene Ref. Open 0.002 in. (0.051 mm) thick with ‘‘ZIP-LOCK’’ type closure PMC 4215

A0001(s)

PWC05-055

Sodium Dichromate, (Technical Grade) Ref. Open Commercial Grade PMC 1300

A0001(s)

PWC05-058

Solder, Tin-Alloy Ref. 50/50 Mix US.ANSI J-STD-004 ANSI J-STD-005 ANSI J-STD-006

09185(m), 10178(m)

PWC05-061

Cloth, Abrasive Coated Crocus US Fed. A-A-1206,

A0001(s), 44197 (m), 61158(m)

PWC05-064

Solution, Anodize Touch-Up (for Aluminum Alloys) Ref. Alodine No. 1200S US. AMS 2473 PMC 71600

84063

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CONSUMABLE MATERIALS

Page 4 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-066

Tape, High Temp. (Glass Cloth) Ref. Permacel No. 212 PMC4273 to 4273-8

A0001(s), 99742(m)

PWC05-070

Tape, Pressure Sensitive Adhesive Filament Reinforced Ref. 3M No. 898 Type II, 2 .0 in. (50.8 mm) Wide US. Fed. PPP-T-97D

A0001(s), A0083, 76381(m)

PWC05-073

Water, Distilled Deionized and Demineralized Ref. Commercial Grade PMC1737, PMC71000

A0001(s)

PWC05-074

Acid, Sulfuric Ref. Commercial or Technical Grade 66 Degrees Baume PMC1003

A0001(s)

PWC05-075B

Grit, Abrasive Aluminum Oxide No. 60 Mesh PMC3052-1

A0001(s), 33333, 44197(m)

PWC05-076

Oil, Penetrating US Fed. A-A-50493

A0001(s), 59595

PWC05-077

Oil, Preservative Ref. Grade 1010 US. MIL-L-6081

2R128

PWC05-089

Lockwire Nickel Alloy (CRES) Ref. MS9226-03 US. AMS5687 0.025 in. (0.64 mm) Dia. (for engine external applications only, PWC05-294 may be substituted).

A0001(s), 8W577(m)

PWC05-101

Cloth, Abrasive Aluminum Oxide or Silicone Carbide US Fed. A-A-1200 No. 320 Grit

A0001(s), 44197(m), 61158(m)

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CONSUMABLE MATERIALS

Page 5 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-103

Marker, Pencil (Surface Marking) Ref. Phano No. 71 Red

70362

PWC05-105

Tape, Self-Adjusting Insulation Electrical Ref. Silicone Rubber US. MIL-I-46852

A0001(s), 00198(s)

PWC05-107

Foam, Polyurethane Ref. Open US. MIL-PRF-26514

A0001(s)

PWC05-110

Lockwire Nickel Alloy or Inconel 600 Ref. MS9226-01 US. AMS5687 0.016 in. (041 mm) Dia.

A0001(s), 8W577(m)

PWC05-118

Insert, Keensert Ref. KN 1032

29372, 39211

PWC05-145

Ref. PWC05-019

PWC05-147

Electrode 2% ThoriatedTungsten PMC5052-3 Length: 7 in. (177.8 mm) Diameter: 1/16 in. (1.587 mm)

A0001(s), 05838, 28835

PWC05-151

Wire, Filler, Welding (Inconel 625) US AMS5837

A0001(s), OHJT8, 2R602

PWC05-156

Bars, Wire, Forgings Alloy 51410 US AMS5613

A0001(s), 8W577(m)

PWC05-161

Solution, Chrome Pickle Touch-Up 1.5 pints nitric acid (PWC05-195) to 1.5 pints sodium dichromate (PWC05-055) SG of 1.42 Add to 8 pints of water. (PWC05-073)

A0001(s)

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CONSUMABLE MATERIALS

Page 6 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-162

Wetting Agent Chromate Conversion Salts Ref. ARP No. 2 PMC1632

76071, A0001(s)

PWC05-164

Welding Material Alumel Ref. TYPE K 20 GAGE

A0066

PWC05-165

Crystals Silver Nitrate Ref. Open

A0001(s)

PWC05-166

Solution, Chemical Treatment Ref. MIL-C-5541 Class 1A

A0001(s), 71410

PWC05-167

Grit, Abrasive Ref. Open No. 1200 Mesh

A0001(s)

PWC05-168

Compound, Polishing, Greaseless-Medium Ref. HD-15 Medium PMC3021

75554(m), A0001(s)

PWC05-179

Wire, Filler, Welding Ref. FM69 US. AMS5778

A0001(s), OHJT8, 2R602

PWC05-180

Wire, Filler, Welding Ref. Hastelloy X US AMS5798

A0001(s), OHJT8, 2R602

PWC05-190

Patch, Filter Ref. P/N NY6004700 Millipore 60 Micron Nylon

A0084(s), 08071(m)

PWC05-195

Acid, Nitric Technical Grade US O-N-350 5 to 10% Solution 42% Reagent Grade 45 Degrees Baume PMC1000

A0001(s)

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CONSUMABLE MATERIALS

Page 7 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-196

Acid, Hydrochloric Technical Grade Ref. Muriatic Acid US ASTM E1146 MIL-H-13528 37 % Reagent Grade 20 Degrees Baume PMC1002

A0001(s)

PWC05-197

Acid, Chromic Flakes or Solution US Fed. O-C-303 CR03-99.5% Min. SO4 -0.20% Max. Commercial Grade PMC1001

A0001(s)

PWC05-215A

Wire, Filler, Welding (Nickel Alloy) US AMS5786 0.035 in. (0.89 mm)

A0001(s), OHJT8, 2R602

PWC05-227

Alloy, Coating Cobalt Cast Rods, Pressed Sintered and Extruded or Powder Ordered

57965, 0CZB2

PWC05-273

Sleeve, Shrink Self-adhesive Ref. Raychem HTAT 48/13

K1010, 06090

PWC05-294

Lockwire or Safetywire Nickel Alloy (CRES) (for engine external applications only, may be used as a substitute for PWC05-089). Ref. AS3214-01 0.020 in. (0.500 mm) Dia.

A0001(s), 1A053(s)

PWC05-329

Temperature Recorder, Single Position (Self Adhesive) Ref. P/N 414-140F-060C 0.56 in. (14 mm) diameter

A0123

PWC05-331

Felt Tip Marker Rapid Drying Temporary Marking Ref. PMC 4050

See NOTE

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CONSUMABLE MATERIALS

Page 8 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

NOTE: For trade names and manufacturers, refer to the SPM. Remove the marking ink from the part before heat treatment process and assembly. PWC05-353

Welding Material Chromel Ref. TYPE N 20 GAGE

A0066

PWC05-367

Compound, Lapping, Silicon Carbide (Water Based) Ref. Sabreslurry W-SIC-220 220 Grit PMC 73158

A0121

PWC05-368

Compound, Lapping, Silicon Carbide (Water Based) Ref. Sabreslurry W-SIC-320 320 Grit PMC 73159

A0121

PWC06-001

Compound, Lubricating Aerosol Spray Application Ref. DC321 Moly Spray (CPW307)

71984(m)

PWC06-002

Use PWC03-001

PWC06-003

Compound, Antigalling Corrosion Prevention Ref. Fel-Pro C-652 PWA 559, PMC79911

73165(m)

PWC06-004

Compound, Antiseize (Molybdenum Disulfide) Ref. Dow Corning G-N Metal Assembly Paste US. MIL-M-7866 PWA587, PMC9549 (CPW262)

71984(m), A0018(s)

PWC06-005B+

Lubricant, Fluorocarbon (Spray Release Agent for Silicone Rubber) Ref. RCTW 9080 (Water-based) PWA 36007-3 PMC 1104

2W738

NOTE: PWC06-034 is also a water-based alternative for composite parts.

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CONSUMABLE MATERIALS

Page 9 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC06-005D

Lubricant, Fluorocarbon PTFE Release Agent Ref. MS-122DF Aerosol Spray

18598(m), 1DD67(m), 1E473(m), A0103(s)

PWC06-007

Lubricant, Dry Film Ref. Moly Dry Film Lub PMC79910 (CPW323)

73165(m)

PWC06-009

Compound, Antiseize Ref. NEVER-SEEZ Pure Nickel Special PWA36053 or PWA36053-1 PMC79966, (CPW553)

5W425(m), 75437

PWC06-012

Grease, Bearing (Long Life) Ref. FS-1292

A0001(s), 71984(m), D8367(m)

PWC06-023

Compound, Antiseize Ref. Silver Goop PWA36001 PMC9940

02570(m), A0019(s), A0037(s), A0038(s)

PWC06-032

Compound, Antigalling and Anti-seize (High Temperature) Ref. Fel-Pro C-200 US MIL-A-907 PWA586, PMC79912 (CPW37)

73165(m)

PWC06-033

Compound, Anti-seize (Paste) Ref. Dow 1000 US MIL-G-2761 Type 1

71984(m)

PWC06-036

Compound, Lubricating (Paste) Ref. Molykote P-37 PWA 36246 PMC 79571 (CPW 571)

71984(m)

PWC06-036A

Compound, Lubricating (Paste) Ref. Tiodize T8E Paste PWA 36246

34568

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CONSUMABLE MATERIALS

Page 10 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC07-002

Enamel, Glyceryl Phthalafe, Engine Gray Baking US AMS3125

A0001(s)

PWC07-008

Coating, Thermoal Insulating Ref. Flamarest BTX 1600 PMC79708, (CPW483)

63262

PWC07-012

Coating, Aluminum Heat and Corrosion Resistant Ref. SermeTel W PWA595-1, PMC9748 (CPW88)

58913(m), A0039(s), A0040(s)

PWC07-017

Coating, Surface Sealant (Corrosion Protection) Ref. Rockhard 576-450-002 (IP Araldite 961) PMC79964, CPW489

K3504(m), 00BB6(s), A0105(s)

PWC07-022

Coating, Touch-up Conversion Ref. TSD No. 1 (Air Drying Type)

A0001(s), A0065

PWC07-023

Coating, Aluminum and Zinc Ref. Serme Tel 249 PWA548 (CPW584)

58913(m), A0039(s), A0040(s)

PWC08-002

Adhesive Fluorosilicone Ref. DC RTV 730 PMC79924 (CPW317)

71984(m)

PWC08-002A

Adhesive Fluorosilicone Ref. FRV-1106 PMC79924 (CPW317)

01139 (B)

PWC08-009

Cement, Sealing, Thermocouple Ref. Sauereisen Filler No. 29 and Sauereisen Binder No. 29

80703, A0071

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CONSUMABLE MATERIALS

Page 11 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC08-010

Adhesive, Rubber Synthetic Ref. EC1357 (CPW324)

76381(m), A0083

PWC09-001

Sealant, Silicone Rubber Ref. DC RTV 732 (CPW519-11)

71984(m), K7750, D8367

PWC09-001A

Sealant, Silicone Rubber Ref. RTV 102, 103, 108, 109 (CPW519-11)

01139(B)(m)

PWC09-002

Compound, Locking and Retaining Anaerobic Ref. Loctite Grade 290 US. MIL-S-22473 PWA549-7, PMC79900 (CPW79-290)

05972(m), A0104(s), A0018, D2617, U0406

PWC09-002A

Compound, Locking and Retaining Anaerobic Ref. Loctite Grade 222 US. MIL-S-22473 PWA549-4, PMC79897

05972(m), A0104(s), A0018, D2617, U0406

PWC09-003

Compound, Sealing Silicone Ref. Dow Corning No. 4 US. MIL-S-8660 PMC9926, (CPW326)

71984(m), D8367

PWC09-005

Compound, Universal Jointing (Medium Grade) Ref. ST512 (CPW267-3)

K3237, 60543, S0116(m)

PWC09-006

Compound, Jointing Ref. ST512 (CPW267-4)

K3237, 60543, S0116

PWC11-001

Cleaner, Alkaline (Internal Engine Washing) Ref. CLIX

20913, 56444

PWC11-001A

Cleaner, Alkaline (Internal Engine Washing) Ref. Almon AL-333

A253

PWC11-001B

Cleaner, Alkaline (Internal Engine Washing) Ref. Magnus 1214

35502(m), 85884

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CONSUMABLE MATERIALS

Page 12 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC11-001C

Cleaner, Alkaline (Internal Engine Washing) Ref. B&B 3100 SPMC87-4

21361

PWC11-001D

Cleaner, Alkaline (Internal Engine Washing) Ref. R-MCS

N1480

PWC11-001E

Cleaner, Alkaline (Internal Engine Washing) Ref. R-MC G21

N1480, 58913

PWC11-001F

Cleaner, Alkaline (Internal Engine Washing) Ref. Turco 4217 Concentrate

36325(m)

PWC11-001G

Cleaner, Alkaline (Internal Engine Washing) Ref. Turco T-5884 SPMC 87-12

71410

PWC11-001H

Cleaner, Alkaline (Internal Engine Washing) Ref. Ardrox 624 Concentrate

A0052(s), 23373(s), 37127(s), K6858(m)

PWC11-001J

Cleaner, Alkaline (Internal Engine Washing) Ref. Triethanolamine

A0001(s)

PWC11-002

Was Solvent trichloroethane 1-1-1 Ref. NOTE

NOTE: Use isopropyl alcohol (PWC11-014) to replace the trichloroethane solvent. You can also use SPOP 209, refer to the SPM, Chapter 70-21-00. PWC11-003

Cleaner, Detergent (Engine Washing) Ref. Ardrox 6345 SPMC87-2

K6858(m)

PWC11-003A

Cleaner, Detergent (Engine Washing) Ref. R-MC G21

N1480, 58913

PWC11-003B

Cleaner, Detergent (Engine Washing) (Biodegradable) Ref. Ardrox 6367 (Turboclean 2)

A0052(s), 23373(s), 37127(s), A0121(m), K6858(m)

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CONSUMABLE MATERIALS

Page 13 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC11-003C

Cleaner, Detergent (Engine Washing) (Biodegradable) Ref. Ardrox 6368 (Turboclean 2 RTU) (Ready to use)

A0052(s), 23373(s), 37127(s), K6858(m)

PWC11-003D

Cleaner, Detergent (Engine Washing) (Biodegradable) Ref. ZOK 27

A0042, S0081

PWC11-005

Cleaner, Solvent Ref. Envirosolv 655 PMC8914

05867

PWC11-008

Cleaner, Contact Ref. Caeon 27

55403(m)

PWC11-009

Alcohol, Ethyl US AMS3002 MIL-A-6091 O-E-760 TYPE III MIL-STD-1201 PMC9009

A0001(s)

PWC11-010

Alcohol, Methyl US AMS3004 O-M-232 Grade A PMC9089

A0001(s)

PWC11-012

Acetone Ref. Open PMC9008

A0001(s)

PWC11-013

No longer availabe. Use alternatives PWC11-013A, PWC11-049 or PWC11-061

PWC11-013A

Compound, Carbon Removing Ref. HDP 2888 SPMC 12

02ER0(m)

PWC11-014

Alcohol, Isopropyl US Fed. TT-I-735 Grade A PMC9094

A0001(s)

PWC11-015

Flakes, Cupric Sulfate Technical Grade Ref. Open

A0001(s)

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CONSUMABLE MATERIALS

Page 14 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC11-020

Solvent, Carbon Removing Ref. Magnus 755

35502(m)

PWC11-021A

Compound, Cold Carbon Removing Ref. Penetone, Formula #423 PMC9031

56883

PWC11-021B

Compound, Cold Carbon Removing Ref. Wyandotte P-1075 PMC9084

88375

PWC11-021C

Compound, Cold Carbon Removing (Cold) Ref. Gerlach Soax No. 66

A0081

PWC11-022

Solvent, Cleaning Methyl Ethyl Ketone (MEK) US ASTM D740 PMC9076, (CPW79908) Ref. NOTE

A0001(s), 36842

NOTE: As an alternative, use the isopropyl alcohol (PWC11-014), acetone (PWC11-012), Ardrox Leeder 1064K (PWC11-023), Desoclean 45 (PWC11-025) or Envirosolv 655 (PWC11-005) to replce the MEK solvent. You can also use SPOP 209, refer to SPM, Chapter 70-21-00. PWC11-023

Solvent, Cleaning Ref. Ardrox Leeder 1064K PMC8904

A0052(s), 23373(s), 37127(s), K6858(m)

PWC11-024

Solvent, Methylene Chloride Ref. Open

A0001(s)

PWC11-025

Solvent, Cleaning Ref. Desoclean 45 PMC9060

0NYS9

PWC11-026

Was Solvent Trichlorethylene

PWC11-027

Solvent, Petroleum US AMS 3160 US Fed. P-D-680 Type II NATO code S-753 PMC9001

A0001(s), 36131

PWC11-029

Solvent, Removing RTV Compound Ref. Chlorothene SM

A0001(s)

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CONSUMABLE MATERIALS

Page 15 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC11-031

Cleaner, Engine Ref. Tergit PMC79782

35502(m)

PWC11-032

Solvent, Degreaser Ref. Magkleen 4 PMC79789

35502(m)

PWC11-033

Cleaner, Aqueous Ref. Soliterj-304 PMC71254

35502(m)

PWC11-038

Solvent, Cleaning Ref. Deoxidine No. 624

71410, A0001(s)

PWC11-049

Remover, Rust, Alkaline Ref. Ardrox 185 SPMC52

A0052(s), 23373(s), 37127(s), A0121(m), 44389, 02CA7, D1940

PWC11-061

Remover, Rust, Alkaline Ref. MAG-CHEM HDL-202 (Liquid) SPMC 129

02ER0 (m)

PWC11-074

Solvent, Non-Aqueous (Bulk or Aerosol) Ref. New ERA Degreasing Fluid, PMC 79004

A0001(s) A0141 A0142

PWC11-084

Degreaser, Water-Repellent (Inter-Treatment) Ref. HYSO 93

02ER0(m) F6892

PWC13-001

Primer, Epoxy Base: 519 x 303; + Curing Solution: 910-357; + Solvent 020 x 324 PWA568, PMC1721 PMC1722 (CPW268)

A0097(s), S0098(s), 0NYS9(m)

PWC15-001

Desiccant , Silica Gel (12 Unit Bags) US. MIL-D-3464 Grade 1 Activated

A0001(s)

NOTE: Desiccant is supplied in one unit bags. One unit weighs one ounce. PWC15-002

Indicator, Humidity Ref. MS20003-2 Humi-Spot

96043

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CONSUMABLE MATERIALS

Page 16 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC15-004

Compound, Corrosion Preventative (Hard Film, Hot Application) US AMS3075

A0001(s)

PWC15-011

Inhibitor, Rust (External Engine Cold Section) Ref. Corrosion-X US MIL-C-81309

A0133 0VJ14

PWC15-013

Inhibitor, Corrosion (Type III, Class 1) Ref. Rustlick 631 DEF II

A0099

PWC15-013A

Inhibitor, Corrosion (Type III, Class 1) Ref. ZC-015

8E913

PWC15-013B

Inhibitor, Corrosion (Type III, Class 1) Ref. Alox 2028D

60773

PWC15-013C

Inhibitor, Corrosion (Type III, Class 1) Ref. Nox Rust 211

7X108

PWC15-013D

Inhibitor, Corrosion (Type III, Class 1) Ref. 2780

0W138

PWC15-013E

Inhibitor, Corrosion (Type III, Class 1) Ref. LPS-814-BULK

66724

PWC15-013F

Inhibitor, Corrosion (Type III, Class 1) Ref. Octoil 5069

82925

PWC15-013G

Inhibitor, Corrosion (Type III, Class 1) Ref. 2028CM-3 Bulk

33150

PWC15-013H

Inhibitor, Corrosion (Type III, Class 1) Ref. Technolube FE-008

A0100

PWC15-013J

Inhibitor, Corrosion (Type III, Class 1) Ref. Ardrox 3205

23373(m), A0101(s)

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CONSUMABLE MATERIALS

Page 17 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC15-013K

Inhibitor, Corrosion (Type III, Class 1) Ref. Batco Rust Preventative

60226

PWC15-013L

Inhibitor, Corrosion (Type III, Class 1) Ref. ACF-50

A0102

PWC15-015

Compound, Corrosion Preventative (Water Displacing) Ardrox 3961

37127

PWC15-016

Compound, Corrosion Inhibitor LPS Procyon (Dry Film) PMC79138-1

A001(s) 66724(m)

3.

Suppliers and Supplier Services The names of any companies provided in Table 2, as a possible source for required services or supplies, are furnished for information purposes only. Pratt & Whitney Canada Corp. does not endorse the work performed or supplies procured from these companies. Further, Pratt & Whitney Canada Corp. does not accept responsibility, to any degree, for the selection of such companies for such work performed or supplies procured. The codes given are the Manufacturer’s Commercial Agency of Government Entity (CAGE) number. A supplier used by Pratt & Whitney Canada (P&WC) and Pratt and Whitney America (PWA), who does not have a CAGE No., is given a SXXXX code by PWA. A supplier used only by P&WC, who does not have a CAGE No., is given an AXXXX code by P&WC. TABLE 2, Supplier Codes and Addresses Supplier Code A0001(s) A0002(s)

A0006

Name/Address Local Supply Local Purchase Butterfield (Litton) 91 Cornella St. West Smith Falls, Ontario Canada K7A 4T3 Tel.: (613) 283-8001 Fax: Telex: 05-33934 Dixon Ticonderoga Inc. 531 Davis Drive Newmarket, Ontario Canada L3Y 2P1 Tel.: (905) 263-4966 Fax: (905) 895-9555

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Page 18 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0013

A0015

A0018(s)

A0019(s)

A0023(m)

A0026

A0030(m)

Name/Address Speedry Products Inc. Richmond Hill, NJ USA Tel.: Not available Fax: Not available Castrol Canada Inc. 2150 Rue Frances Hughes Chomedy, Ville de Laval, Quebec Canada H7S 1N7 Tel.: (450) 382-6940 Tel.: (900) 361-3837 Fax: Not available National Bearings Ltd. 724 Renaud Dorval, Quebec Canada H9X 1H5 Tel.: (514) 333-7000 Fax: Not available Vannes & Raccords Laurential Ltee. (A distributor of The Swagelok Co.) 2425 Halpern Ville St. Laurent, Quebec Canada H4S 1S3 Tel.: (450) 332-3651 Fax: (450) 332-4386 Whitford Plastics Ltd. Brindley 86, Astmoor Runcom, Cheshire England SK10 4NJ Tel.: 01928-571000 Fax: 01928-571010 W.H. Brady Inc. 10 Marmac Drive Rexdale, Ontario Canada M9W 1E6 Tel.: (416) 675-7111 or (800) 387-3917 Fax: Not available Imperial Oil Canada 111 St. Clair Ave. W. Toronto, Ontario Canada M5W 1K3 Tel.: (416) 968-4111 Fax: (416) 968-4374

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CONSUMABLE MATERIALS

Page 19 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0032

A0033

A0034

A0035

A0036

A0037(s)

A0038(s)

Name/Address Antwerp Marine Center, S.A. Mechelsctteenweg 43 B-2000 Antwerp Belgium Tel.: 32-3-2320084 Fax: Not available L.L. LTD. 15 Russell Garden Mews London W14 8EU England Tel.: Not available Fax: Not available Kian Seng Hardware Trading Pts. Ltd. 168 Sims Ave. Singapore Tel.: 14-3865-748-7144 Fax: Not available F. Bacon & Co. Inc. Div. De Drummond-Sullivan Co. 274 Chemin Bates Mont Royal, Quebec Canada H3S 1A3 Tel.: (514) 737-3755 Fax: Not available Ashburn Industries 3219 Harrisburg P.O. Box 2046 Houston, TX USA 77252 Tel.: Not available Fax: Not available Amsterdam Valve & Fitting G. Loewik BV (A distributor of The Swagelok Co.) P.O. Box 9050 1180 Amstelveen The Netherlands Tel.: (31) (20) 6470231 Fax: (31) (20) 6474267 Singapore Valve & Fitting (Pte) Ltd. (A distributor of The Swagelok Co.) 28 Mandai Estate Singapore 729917 Tel.: (65) 3670688 Fax: (65) 3685300 Fax: Cable : SINVAF

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CONSUMABLE MATERIALS

Page 20 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0039

A0040

A0042

A0052

A0065

A0066

A0071

Name/Address Sermatech Canada Inc. 747 Riddle Avenue Dorval, Quebec Canada H9P 1H4 Tel.: (514) 631-2240 Fax: (514) 636-6196 Sermatech United Kingdom Ltd. High Holborn Road Codnor Gate Industries Estate Ripley, Derbyshire United Kingdom DE5 3NW Tel.: (44) 1773-7489261 Fax: (44) 1773-512344 Airworthy Ltd. Elsted Midhurst, West Sussex England GU29 0JT Tel.: 730-816672 Fax: 730-815607 Trikon Technologies Inc. 6969 Trans-Canada Highway Suite 127 Saint-Laurent, Quebec Canada H4T 1V8 Tel.: (514) 339-5997 Fax: Not available Turbine Support Division Chromally American Corp. 4430 Director Drive San Antonio, TX USA 78220 Tel.: (512) 333-6010 Fax: Not available Semco Instruments Inc. 25700 Rye St. Valencia, CA USA 91355 Tel.: (805) 257-2000 Fax: (805) 295-0044 Corrosion Service Co. Ltd. 369 Rimrock Rd. Downsview, Ontario Canada M3J 3J2 Tel.: (416) 630-2600 Fax: (416) 630-2393

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CONSUMABLE MATERIALS

Page 21 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0081

A0083

A0084(s)

A0097(s)

A0099

A0100

Name/Address E.A. Gerlach Co. Eddington, PA USA Tel.: Not available Fax: Not available 3M Canada Inc. P.O. Box 5757 Oxford St. E. London, Ontario Canada N6A 4T1 Tel.: (519) 451-2500 Tel.: Telex: 064-5886 Fax: (519) 452-6262 Millipore Canada Ltd. 36 Antares Drive, Suite 700 Nepean Ontario K2E 7W5 Canada Tel.: (800) 645 5476 Fax: (613) 225 9366 Courtaulds Aerospace A Division of International Paints Canada Ltd. 5676 Timberlea Blvd. Mississauga, Ontario Canada L4W 4M6 Tel.: (905) 629-7999 Fax: (905) 629-7009 ITW Signode India Ltd. 5, SP Road Hyderabad-500016 India Tel.: Not available Fax: Not available Technolube Products 5814 East 61st Street Los Angeles, CA USA 900400 Tel.: Not available Fax: Not available

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CONSUMABLE MATERIALS

Page 22 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0101(s)

A0102

A0103(s)

A0104(s)

A0105(s)

A0121(m)

Name/Address Brent Mexicana S.A. De C.V. Tiburcio Montiel 81 Col. San Miquel Chapultepec 11850-Mexico D.F. Mexico Tel.: Not available Fax: Not available Lear Chemical Research Corp. 1285 Brittania Road East Mississauga, Ontario Canada L4W 1C7 Tel.: Not available Fax: Not available Miller-Stephenson Chemical Co. Inc. 514 Carlingview Drive Rexdale, Ontario Canada M9W 5R3 Tel.: (416) 675-3204 or (800) 323-4621 Fax: (416) 674-2987 E-mail: www.miller-stephenson.com Loctite Canada Inc. 2225 Meadowpine Blvd. Mississauga, Ontario Canada L5N 7P2 Tel: (905) 814-6511 or (800) 263-5043 Fax: (905) 814-5391 Matcon (A distributor of Indestructible Paints Ltd.) 10/2 Britto Complex 6th Cross, Victoria Layout Bangalore, India 560 047 Tel.: 9180-554-3805 Fax: 9180-544-3804 Oakite Products of Canada, Ltd. 115 East Drive Bramalea, Ontario, L6T 1B7 Canada Tel.: (800) 526-4473 Tel.: (905) 791-1628 Fax: (905) 791-1527 Fax: (908) 464-7914 URL: www.oakite.com

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CONSUMABLE MATERIALS

Page 23 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0123

A0133

A0141

A0142

A253

Name/Address Wahl Instruments Inc. 234 Weaverville Highway Asheville, NC 28804-1228 USA Tel.: (828) 658-3131 Tel.: (800) 421-2853 Fax: (828) 658-0728 E-mail: www.instrumentationgroup.com Avtech International In.c 5491 Quartermain Crescent Mississauga, Ontario L5M 5V3 Tel.: (905) 819-1637 Email: [email protected] State Chemical, State Chemical Solutions 3100 Hamilton Avenue Cleveland, OH 44114 USA TEL: (216) 861-7114 (800) 782-2436 FAX: (888) 771-9670 Website: www.statechemical.com E-mail: [email protected] Greensolv 19500 Aut. Transcanadienne Suite 200, Baie d’Urfe, QC, H9X 3S4 Canada TEL: (866) 826-8400 (514) 457-8000 FAX: (514) 457-1300 Website: www.greensolv.ca E-mail: [email protected] Almon Quimico Wyandotte Corporation Rio-De-Janeiro Brazil Tel.: Not available Fax: Not available

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Page 24 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code D2617

D8367

F6892

Name/Address Loctite Deutschland GmbH Arabellastrasse 17 Postfach 81 05 80 8000 Munchen 81 Germany Tel.: Not available Fax: Not available Dow Corning GmbH Schmierstoffe Pelkovenstrasse 152 8000 Muenchen 50 Germany Tel.: Not available Fax: Not available Socomore 1271, Ampere Suite 101 Boucherville, QC, J4B 5Z5 Canada TEL: (450) 641-8500 (855) 895-2436 FAX: (450) 655-1717 or Socomore 2901 Shamrock Ave Fort Worth, TX 76107 USA

K1010

K3237

TEL: (817) 335-1826 FAX: (817) 335-2405 Raychem Limited Faraday Road Dorcan, Swindon United Kingdom SN3 5HH Tel.: 0793-528171 Fax: 0793-482297 Marston Bentley Ltd. 9 Naylor Street Liverpool, England L3 6DS Tel.: Not available Fax: Not available

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Page 25 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code K3504(m)

K6858

K7750

N1480

S0036

S0081

Name/Address Indestructible Paint Co. Ltd. 25 Pentos drive Sparkhill, Birmingham United Kingdom B11 3TA Tel.: (0121) 702-2485 Fax: (0121) 778-4338 Brent Europe Ltd. (Brent International PLC) Denbigh RoadBletchley, Milton Keynes Buckinghamshire England MK1 1PB Tel.: 44-1753-651812 Tel.: Telex: 847693 BRENT Fax: 44-1753-652460 Dow Corning Ltd. Molykote Division NG Co. Avco House Castle Street Reading Berks, RD1 7-Z United Kingdom Tel.: Not available Fax: Not available Ivar Rivenaes A/S Damsgirds 35 N-5037 Solheimsvik Norway Tel.: 55-203390 Fax: 55-295925 Texrite Products Co. 10333 Shoemaker St. Detroit, MI USA 48213 Tel.: (313) 925-9002 Fax: (313) 925-9602 Lucas Avitron P.O. Box 120039 Stantford, CT 06912 USA Tel.: (203) 351-8400 Fax: (203) 351-8444

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Page 26 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code S0089

S0098(s)

S0116

U0406

0BZD7

Name/Address Avery Dennison Dennison Division One Clark Hill Farmington, MA USA 01701 Tel.: (508) 879-0511 Fax: (508) 383-4259 or Office Products Canada 200 Base Line Road East Bowmanville, Ontario Canada L1C 1A2 Tel.: (905) 623-6311 Fax: (905) 623-9751 ASC Philadelphia (A distributor of Courtaulds Aerospace) 823 East Gate Mt. Laurel, NJ USA 08054 Tel.: (609) 234-1600 Fax: (609) 234-5515 W. Canning Inc. 223 North Brockman St. Pasadena, TX USA 77506 Tel.: (713) 472-5081 or (800) 521-2589 Fax: (713) 472-2440 Loctite UK Ltd. Watchmead Welwyn Garden City Herts United Kingdom AL7 1-B Tel.: Not available Fax: Not available Liquid Air Engineering Corp. 1155 Sherbrooke St. W. Montreal, Quebec Canada H3A 1H8 Tel.: (514) 842-5431 Fax: Not available

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Page 27 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 0CZB2

0HJT8

0NYS9(m)

0W138

00BB6(s)

00198

Name/Address Stoody Deloro Stellite Inc. Stellite Coatings Div. 1201 Eisenhower Dr. N. Goshen, ID USA 46526-5396 Tel.: (219) 534-2585 Fax: (219) 534-3417 Airgas Northeast Inc. 325 McCausland Court Cheshire, CT USA 06410 Tel.: (203) 250-6800 Fax: (203) 250-6834 PRC-Desoto International (formally Courtaulds Aerospace, Inc.) 5430 San Fernando Road Glendale, CA 91209 USA Tel: (818) 549-7973 Fax: (818) 549-7595 www.ppg.com/prc-desoto Fine Organics Corp. 6935 West 62nd Street Chicago, IL USA 60638 Tel.: Not available Fax: Not available Indestructible Paints Inc. 66 Erna Ave. Milford, CT USA 06460 Tel.: (203) 877-9243 Fax: (203) 876-7680 Pratt & Whitney Canada Corp. Attn: Parts Support (Mail Code 01OE4) 1000 Marie Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Tel.: (450) 647-2777 Fax: (450) 647-2834

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Page 28 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 01058

01139(A)

01139(B) (m)

02ER0(m)

02258

02570(m)

03042

Name/Address Michigan Chrome & Chemical Co. 8615 Grinnel Ave. Detroit, MI USA 48213-1152 Tel.: (313) 267-5279 Fax: Not available General Electric Co. Attn: Rubber and Fluid Products Dept. Attn: Customer Support 260 HudsonRiver Rd. Waterford, NY USA 12188 Tel.: (518) 233-3330 or (800) 255-8886 Fax: Not available General Electric Co. Attn: Silicone Sales Dept. Attn: Customer Support 260 Hudson River Road Waterford, NY USA 12188 Tel.: (518) 233-3330 or (800) 255-8886 Fax: (518) 233-3931 MAG-CHEM 190 Blvd. Industriel Boucherville Quebec J4B 2X3 Canada Tel.: (800) 363 9929 Tel.: (450) 655 1344 Fax: (450) 655 5428 URL: www.magchem.com Enthone-OMI Inc. P.O. Box 1900 West Haven, CT USA 06516-4147 Tel.: (203) 934-8611 Fax: (203) 799-1513 Swagelok Co. (formally Crawford Fitting Co.) 29500 Solon Road Solon, OH USA 44139 Tel.: (440) 248-4600 Fax: (440) 349-5970 Dennison Carter (Ref. S0089)

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CONSUMABLE MATERIALS

Page 29 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 03530

05838

05867

05972(m)

06090

08071(m)

Name/Address American Gas & Chemicals Co. Ltd. 220 Pegasus Ave. Northvale, NJ USA 07647-1904 Tel.: (201) 767-7300 or (800) 288-3647 Fax: 9201) 767-1741 E-mail: [email protected] Philips Elmet Corp. 1560 Lisbon Road Lewiston, ME USA 04240 Tel.: (207) 784-3591 or (800) 526-7480 Fax: Not available Fine Organics Corp. 205 Main Street P.O. Box 687 Lodi, NJ USA 07644-0687 Tel.: (973) 472-6800 or (800) 526-7480 Fax: (973) 472-6810 E-mail: [email protected] Permatex Industrial Corp. Div. of Loctite North America Group 1001 Trout Brook Crossing Rock Hill, CT USA 06067-3910 Tel.: (860) 571-5100 Fax: (860) 571-5465 Raychem Corp. Electronic Systems Group 300 Constitution Drive Menlo Park, CA USA 94025-1111 Tel.: (650) 361-3333 Fax: (650) 361-3485 Millipore Corporation 80 Ashby Road Bedford MA 01730-2271 USA Tel.: (781) 275 9200 Fax: (781) 275 5550

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Page 30 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 08338

09185(m)

1A053(s)

1C394

1DD67(m)

1E473(m)

Name/Address Allied Chemicals Canada Ltd. Fluorine Products 201 City Centre Dr. Mississauga, Ontario Canada L5B 2T4 Tel.: (905) 276-9211 Fax: (905) 276-5711 Litton Industries. Kester Solder Division 515 E. Touhy Ave. Des Plaines, IL USA 60018-2675 Tel.: (847) 297-1600 or (800) 253-7837 Fax: (847) 390-9338 or (847) 699-5548 E-mail: [email protected] Web: www.kester.com AAA Aircraft Supply Co. 36 Suffield Street P.O. Box 411 Windsor Locks, CT 06096-1320 USA Tel.: (860) 627-0181 Fax: (860) 623-2483 Dulson Frank and Co. Ltd. 5760 Pare Street Montreal, Quebec Canada H4P 1R9 Tel.: (514) 735-4681 Fax: (514) 735-8566 Miller-Stephenson Chemical Co. Inc. 6348 Oakton Street Morton Grove, IL USA 60053 Tel.: (847) 966-2022 or (800) 992-2424 Fax: (847) 966-8468 E-mail: www.miller-stephenson.com Miller-Stephenson Chemical Co. Inc. 12261 Foothill Boulevard Sylamar, CA USA 91342 Tel.: (818) 896-4714 or (800) 992-2424 Fax: (818) 896-6086

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Page 31 Jul 22/2019

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 1V074

10178(s)

18598(m)

2R128

2R602

Name/Address Sulflo Inc. 1158 Erie Ave. P.O. Box 285 North Tonawanda NY USA 14120-3507 Tel.: (716) 695-3585 Fax: (716) 695-0367 Kester Solder Co. of Canada Ltd. 1 Prince Charles Road P.O. Box 474 Brantford, Ontario Canada N3T 5N9 Tel.: (519) 753-3425 Fax: (519) 753-0641 Web: www.kester.com Miller-Stephenson Chemical Co. Inc. George Washington Highway P.O. Box 905 Danbury, CT USA 06813 Tel.: (203) 743-4447 or (800) 992-2424 Fax: (203) 791-8702 E-mail: www.miller-stephenson.com Castrol Inc. Speciality Products Division Suite 230 16715 Van Karman Avenue Irvine, CA USA 92714 Tel.: (714) 660-9414 or (800) 458-5823, Ext. 3012 Fax: Not available Astrolite Alloys Div. of Astro Metallurgical 709 Via Alondra Camarillo, CA USA 93010-8714 Tel.: (805) 484-3621 or (800) 235-5935 Fax: (805) 388-0577

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 2W738

20913

21361

22980 (m)

23373(m)

Name/Address Chem-Trend Inc. 1445 West McPherson Park Drive P.O. Box 860 Howell, MI 48844-0860 USA Tel.: (517) 546-4520 Tel.: (800) 727-7730 Fax: For orders; (517) 546-8910 NCH Corp. P.O. Box 152170 2727 Chemsearch Blvd. Irving, TX USA 75015 Tel.: (214) 438-0211 Fax: Not available B & B Tritech Inc. 875 West 20th St. Hialeah, FL USA 33010-2310 Tel.: (305) 888-5247 Fax: (305) 887-4587 Sanford (A Newell Co.) 2711 Washington Blvd. Bellwood, IL USA 60104 Tel.: (708) 649-3513 Fax: (708) 649-3594 E-mail: www.sanfordcorp.com Brent America Inc. 16961 Knott Avenue La Mirada, CA USA 90638-6015 Tel.: (714) 739-2821 Fax: (714) 670-6480 or Brent America Inc. 921 Sherwood Dr. Lake Bluff, IL USA 90044 Tel.: (847) 295-1660 Fax: (847) 295-8748

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 25645

28112

28835

29372

30133

33150

Name/Address Whitford Corp. 33 Sproul Road Frazer, PA USA 19355 Tel.: (610) 296-3200 Fax: (610) 647-4849 Minnesota Mining & Mfg. Co. 3M Company Industrial Chemical Products 3M Center St. St. Paul, MN USA 55144-1000 Tel.: (800) 364-3577 Fax: (612) 737-7117 Hobart Bros. Co. Hobart Square 600 W. Main Street Troy, OH USA 45373 Tel.: (937) 332-4000 Fax: (937) 332-4090 Fairchild Industries Inc. Fairchild Aerospace Fastener Division 3000 West Lomita Blvd. Torrance, CA USA 90505-5103 Tel.: (310) 784-0700 or (310) 530-0963 Fax: (310) 539-6940 Ideal Stencil Machine and Tape 102 Iowa Avenue P.O. Box 305 Belleville, IL USA 62222-0305 Tel.: (618) 233-0162 Fax: Not available Steven Industries, Inc. 39 Avenue C Bayonne, NJ USA 07002 Tel.: Not available Fax: Not available

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 33333

33564(A)

33564(B)

35502

36131

36325

Name/Address Washington Mills Electro Minerals Corp. 1801 Buffalo Avenue Niagara Falls NY USA 14302 Tel.: (716) 278-6600 or (800) 828-1666 Fax: Not available Dexter Aerospace Materials Division 2850 Willow Pass Rd. Pittsburg, PA USA 94565-3299 Tel.: (510) 458-8000 Fax: (510) 458-8030 Dexter Aerospace Electronic Materials Division 211 Franklin Street Orlean, NY USA 14760 Tel.: (716) 372-6300 Fax: (716) 372-6864 Magna Chemical Ltd. 190 Blvd. Industriel Boucherville, Quebec Canada J4B 2X3 Tel: (450) 655-1344 Fax: (450) 655-5428 Shell Canada Products Limited 400 4th Ave. SW P.O. Box 100 Station M Calgary, Alberta Canada T2P 2H5 Tel.: (403) 691-3111 Fax: (403) 691-3777 Deane & Co. Div. of Groulx-Robertson Ltee./Ltd. 190 Oneida Drive Pointe Claire, Quebec Canada H9R 1A8 Tel.: (514) 697-3730 Fax: (514) 697-3887

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 36382

36842

37127(m)

39211

39918

44197 (m)

Name/Address Witco Canada 565 Coronation Drive West Hill, Ontario Canada M1E 2K3 Tel.: (416)284-1661 Fax: (416) 284-4316 Anachemia Canada Inc. 500 2nd Avenue Ville St. Pierre, Quebec Canada H8R 1M3 Tel.: (514) 489-5711 Fax: (514) 363-5281 Brent Canada Ltd. 363 Arvin Avenue Stoney Creek, Ontario Canada L8E 2M8 Tel.: (905) 662-8046 Fax: (905) 662-5966 Interfast Inc. 21 Constellation Court P.O. Box 6984 Toronto, Ontario Canada M9W 1K4 Tel.: (416) 674-0770 Fax: (416) 674-5804 Sulzer Metco (Westbury) Inc. 1101 Prospect Ave. Westbury, Long Island, NY USA 11590-2724 Tel.: (516) 334-1300 Fax: (516) 338-2486 Norton Co. (Export Sales) 1 New Bond Street P.O. Box 15008 Worchester, MA USA 01606-0008 Tel.: (508) 795-5307 or (800) 446-1119 Fax: (508) 795-4130

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 44389

5W425(m)

55403(m)

56444

55596

56883

Name/Address Oakite Products Inc. (Chemetall Chemical Products Inc.) 50 Valley Road Berkeley Heights, NJ 07922-2712 USA Tel.: (800) 526-4473 Tel.: (908) 508-2214 Fax: (908) 464-7914 URL: www.oakite.com Emhart Corp. Bostik Division Boston Street Middleton, MA USA 01949 Tel.: (978) 777-0100 Fax: (978) 750-7212 Caig Laboratories Inc. 12200 Thatcher Court Poway, CA USA 92064 Tel.: (858) 486-8388 Fax: (858) 486-8398 E-mail: [email protected] Website:http//www.caig.com National Chemsearch 245 Orenda Road Bramalea, Ontario Canada L6T 1E7 Tel.: (416) 457-5220 or (800) 268-0804 Fax: (416) 457-5220 Polymet Corp. 10073 Commerce Park Drive Cincinnati, OH USA 45246 Tel.: (513) 874-3586 Fax: (513) 874-2880 Penetone Corp. Sub. of West Chemical Products Inc. 74 Hudson Avenue Tenafly, NJ USA 07670-1017 Tel.: (201) 567-3000 Fax: (201) 569-5340

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 57965

58401(m)

58913 (m)

58933

59595

Name/Address Stoody Deloro Stellite Welding Rods & Wires Division 16425 Gale Avenue Industry, CA USA 91749 Tel.: (818) 968-0717 or (800) 227-9333 Fax: Not available United States Welding Corp. 3579 Hwy., 50 East #104 Carson City, NV USA 89701 Tel.: (702) 883-7878 or (800) 423-5964 Fax: (702) 883-7776 E-mail: www.usweldingcorp.com Sermatech International Inc. Materials Division 155 South Limerick Road Limerick, PA USA 19468-1603 Tel.: (610) 948-5100 Fax: (610) 948-5407 Furon CHR Division T & F Furon Division 3660 Edison Place Rolling Meadows, IL USA 60008-1013 Tel.: (708) 392-8090 or (800) 323-1650 Fax: (708) 392-0403 Texaco Inc. 2000 Westchester Avenue White Plains, NY USA 10650 Tel.: (914) 253-4000 Fax: (914) 253-7753 or Reverside Drive East Hartford, CT USA 06118 Tel.: (860) 569-8297 Fax: Not available

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 60226

60543

60773

61158(m)

63262

63726

Name/Address Battenfield Grease & Oil Corp. of New York 1174 Erie Avenue P.O. Box 728 North Tonawanda, NY USA 14120 Tel.: (716) 695-2100 Fax: Not available Ryder-Aviall 2075 Diplomat P.O. Box 7086 Dallas, TX USA 75234 Tel.: (214) 406-2000 Fax: Not available Alox Corporation 3943 Buffalo Ave. P.O. Box 517 Niagara Falls, NY USA 14302 Tel.: Not available Fax: Not available Unifrax Corp. (The Carborundum Co.) 2351 Whirlpool St. Niagara Falls, NY USA 14305-2413 Tel.: (716) 278-3827 Tel.: Canada: (800) 635-4464 Fax: (716) 278-3904 E-mail: www.unifrax.com Textron Speciality Materials Sub. of Textron Inc. 2 Industrial Avenue Lowell, MA USA 01851-5107 Tel.: (978) 452-8961 Fax: (978) 454-5619 Metallurgical Technologies Inc. 14436 Max Road Route 4, Box 4752 Pearland, TX USA 77581-9709 Tel.: (281) 485-7765 Fax: (281) 485-0211

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 66724 (m)

7X108

70362

71410

71984(m)

73165

Name/Address LPS Laboratories Division of Holt Lloyd Corp. P.O. Box 105052 4647 Hugh Howell Road Tucker, GA USA 30084-5052 Tel.: (800) 241-8334 Fax: (770) 493-9206 E-mail: [email protected] Daubert Chemical Co. Inc. 4700 South central SW Chicago, IL USA 60638 Tel.: (312) 496-7350 Fax: Not available Dixon Ticonderoga Co. Sandusky Division 1706 Hayes Avenue P.O. Box 2258 Sandusky, OH USA 44870-4732 Tel.: (419) 625-9545 or (800) 824-9430 Fax: (419) 625-0719 Parker & Amchem Division of Henkel Corp. 32100 Stephenson Hwy. Madison Heights, MI USA 48071 Tel.: (248) 583-9300 Fax: (248) 583-2896 Dow Corning Corp. 2200 West Salzburg Rd. P.O. Box 994 Midland, MI USA 48686-0994 Tel.: (517) 496-6000 or (800) 248-2481 Fax: (517) 496-6974 Fel-Pro Inc. Div. of Felt Products Mfg. Co. 7450 North McCormick Blvd. P.O. Box 1103 Skokie, IL USA 60076-8103 Tel.: (847) 674-7700 or (800) 323-4356 Fax: (847) 674-0019

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 73219

75437

75554

76071

76381(m)

8E913

Name/Address Fiske Brothers Refining Co. 129 Lockwood Street Newark, NJ USA 07105-4720 Tel.: (973) 589-9150 Fax: (973) 589-4432 EOE Inc. 585 Fourth Street P.O. Box 177 Troy, Ny USA 12181 Tel.: (518) 272-6922 Fax: (518) 272-2182 Jackson Lea A unit of Jackson Inc. 75 Progress Lane P.O. Box 71 Waterbury, CT USA 06705 Tel.: (203) 753-5118 Fax: (203) 754-3770 Macdermid Inc. 245 Freight Street Waterbury, CT USA 06702 Tel.: (203) 575-5700 or (800) 325-4158 Fax: Domestic: (203) 575-5630 Fax: International: (203) 575-7900 3M Company 3M Center St. Paul, MN USA 55144-1000 Tel.: (612) 737-6501 or (800) 364-3577 Fax: (612) 737-7117 Zip-chem Products A division of ANDPAK-EMA, Inc. 1860 Dobbin Drive San Jose, CA USA 95133 Tel.: (408) 729-0291 Fax: (408) 272-8062

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 8R378

8W577(m)

80703

82682(m)

82925

85665

85884

Name/Address Hammill and Gillespie Inc. 154 Livingstone Avenue P.O. Box 104 Livingstone, NJ USA 07039-3017 Tel.: (201) 994-3650 Fax: Not available Aerospace Specifications Metals 1384 W. McNab Rd. Ft. lauderdale, FL USA 33309 Tel.: (954) 977-0666 Fax: (954) 977-3858 Saureisen Cements Co. 160 Gamma Drive Pittsburgh, PA USA 15238-2920 Tel.: (412) 963-0303 Fax: (412) 963-7620 Tempil Inc. 2901 Hamilton Road South Plainfield, NJ USA 07080 Tel.: (800) 757-8300 Fax: (908) 757-9273 Octagon Processes, Inc. 596 River Road Edgewater, NJ USA 07020 Tel.: (201) 945-9400 Fax: Not available Witco Corp. 1 American Lane Greenwich, Conn. USA 06831-2559 Tel.: 1-800-494-8287 Fax: (203) 552-2849 Intl. Fax: (203) 552-3414 Ecolab Inc. Ecolab Center 370 Wabasha St. St. Paul, MN USA 55102-1307 Tel.: (612) 293-2570 Fax: Not available

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 86459(m)

87889

88375

9X212

96043

98148(m)

Name/Address Penreco 138 Petrolia St. Karns City, PA USA 16041 Tel.: (800) 245-3952 Fax: (724) 756-1050 The Texacone Co. 4111 Forney Rd. Mesquite, TX USA 75149-2722 Tel.: (800) 235-2727 Fax: Not available Wyandotte Paint Products Co. 650 Stephenson Highway P.O. Box 1196 Troy, MI USA 48099 Tel.: Not available Fax: Not available Shell International Petroleum Co. Shell Center London, SE1 7NA England Tel.: 44-171-934-1234 Fax: 44-171-934-8060 Driaire 26 Fitch St. P.O. Box 569 South Norwalk, CT USA 06856 Tel.: Not available Fax: Not available Dykem Co. 3624 West Lake Ave. Glenview, IL USA 60025 Tel.: (800) 323-9538 Fax: (800) 323-9536

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 99742

Name/Address Permacel Div. of Nitto Penko America U.S. Highway No. 1 P.O. Box 671 New Brunswick, NJ USA 08903 Tel.: (732) 418-2400 Tel.: Telex: 6858014 PERMACEL Fax: (732) 418-2739

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Mar 08/2013 Mar 08/2013

Contents

1 2 blank

Mar 08/2013 Mar 08/2013

Airworthiness Limitations

1 2

Mar 08/2013 Mar 08/2013

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AIRWORTHINESS LEP

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE OF CONTENTS SUBJECT

PAGE

AIRWORTHINESS LIMITATIONS 1.

General

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AIRWORTHINESS CONTENTS

2

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

AIRWORTHINESS LIMITATIONS

The Airworthiness Limitations section is FAA approved and specifies maintenance required under Sections 43.16 and 91.403 of title 14 of the Code of Federal Aviation Regulations unless an alternative program has been FAA approved.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

...................... 1.

General The Airworthiness Limitations section specifies mandatory Rotor Component Service Life Limits required for type certification. The Airworthiness Limitations section is approved by the Canadian Minister of Transport and specifies maintenance required by any applicable airworthiness or operational rule unless an alternative program has been approved by the Canadian Minister of Transport. For Rotor Component Service Life Limits refer to the latest revision of P&WC S.B. No.1002 for PT6A-34/-34B/-36 and P&WC S.B. No. 1302 for PT6A-34AG.

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AIRWORTHINESS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Apr 25/2008 Apr 25/2008

Contents

1 2 blank

Apr 25/2008 Apr 25/2008

61-20-00 Description and Operation

1 2 blank

Feb 11/2000 Feb 11/2000

201 202 203 204 205 206 blank

Apr 25/2008 Apr 25/2008 Apr 25/2008 Apr 25/2008 Apr 25/2008 Apr 25/2008

61-20-00 Maintenance Practices

61-20 LEP

Page 1/2 Apr 25/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE OF CONTENTS SUBJECT

PAGE

PROPELLER GOVERNOR - DESCRIPTION AND OPERATION

61-20-00

1.

General

1

2.

Fault Isolation

1

PROPELLER GOVERNOR - MAINTENANCE PRACTICES

61-20-00

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation

201

A.

Removal of Propeller Governor

201

B.

Installation of Propeller Governor

203

6.

Inspection/Check

204

A.

Propeller Governor

204

B.

Electrical Connectors and Leads

204

C.

Governor Gasket

204

7.

Adjustment/Test

205

8.

Approved Repairs

205

A.

205

Replacement of Lock Pitch Solenoid Valve (if fitted)

61-20 CONTENTS

Page 1/2 Apr 25/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PROPELLER GOVERNOR - DESCRIPTION AND OPERATION 1.

General The propeller governor is installed at the 12 o’clock position on the front case of the reduction gearbox and is driven by the propeller shaft through an accessory driveshaft. The propeller governor controls the propeller speed and pitch settings as dictated by the cockpit control settings and flight conditions. Refer to Chapter 76-00-00 for further details of propeller control system. Refer also to the Airframe Manufacturer’s Maintenance Manual, Chapter 61.

2.

Fault Isolation For detailed fault isolation of the propeller governor, refer to Chapter 72-00-00, FAULT ISOLATION.

61-20-00 PROPELLER GOVERNOR - DESCRIPTION AND OPERATION

Page 1/2 Feb 11/2000

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PROPELLER GOVERNOR - MAINTENANCE PRACTICES 1.

2.

General A.

Maintenance personnel should make reference to the INTRODUCTION section and Chapter 70-00-00, STANDARD PRACTICES of this manual to familiarize themselves with general procedures.

B.

Install protective caps and plugs on disconnected tubes, component openings and electrical connectors.

C.

Lockwire used shall, unless otherwise specified, comply with specification AMS 5687, heat and corrosion resistant steel wire MS9226-03, which is 0.025 inch diameter, and will not be specified in instructions.

Consumable Materials The consumable materials listed below are used in the following procedures.

3.

Item No.

Name

PWC03-001

Oil, Engine

Special Tools The special tools listed below are used in the following procedures.

4.

Tool No.

Name

Application

PWC30114-09 PWC30114-16

Wrench Wrench

Pre-SB1232 Post-SB1232

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation A.

Removal of Propeller Governor (Ref. Fig. 201) (1)

Remove the electrical connectors from the governor and/or propeller speed synchronizer (Ref. Aircraft Maintenance Manual).

(2)

Remove the propeller reversing lever from the Beta control valve (Ref. 76-10-00).

(3)

Remove the propeller governor interconnect rod from the propeller governor airbleed link (reset lever) (Ref. 76-10-00, Removal/Installation).

(4)

Remove the coupling nut of the pneumatic (Py) front tube (9) from the propeller governor straight nipple (8).

(5)

Remove the airframe linkage from the propeller governor speed select lever.

61-20-00 PROPELLER GOVERNOR - MAINTENANCE PRACTICES

Page 201 Apr 25/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

7 8 9 6 4

5 10

3 1 2

11

C3809A Removal/Installation of Propeller Governor Figure 201

61-20-00 PROPELLER GOVERNOR - MAINTENANCE PRACTICES

Page 202 Apr 25/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

Key to Figure 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11.

B.

Screw Lock Pitch (Shutoff) Solenoid Valve (if fitted) Preformed Packing (two) Preformed Packing Preformed Packing Propeller Governor Preformed Packing Straight Nipple Pneumatic Tube (Py) Self-locking Nut and Washer Gasket

(6)

Using the appropriate propeller governor retaining nut wrench (PWC30114-09), Pre-SB1232 or (PWC30114-16), Post-SB1232, remove the four self-locking nuts and plain washers (10) securing the propeller governor to the reduction gearbox. Withdraw the propeller governor (6) and the gasket (11) from the mounting pad.

(7)

If the propeller governor is to be replaced by a new or overhauled unit, remove the straight nipple (8) from the Py port on the governor (6) and discard the preformed packing (7); retain the nipple for reuse on the replacement unit.

Installation of Propeller Governor (Ref. Fig. 201)

CAUTION:

MAKE SURE DRIVE SPLINES ARE CORRECTLY ENGAGED BY CHECKING THAT FLANGE OF GOVERNOR RESTS ON GASKET SQUARELY WITH NO GAP. ROTATE PROPELLER TO ASSIST ENGAGEMENT, IF NECESSARY.

CAUTION:

MAKE SURE CORRECT PROPELLER GOVERNOR IS INSTALLED (IDENTIFIED BY UNIT PART NUMBER). REFER TO THE ILLUSTRATED PARTS CATALOG.

CAUTION:

AFTER MAJOR TURBINE BLADE FRACTURE, THE PROPELLER GOVERNOR ON ENGINES WITH PROPELLER REVERSING MUST BE SENT TO AN APPROVED OVERHAUL FACILITY FOR INSPECTION PRIOR TO RETURNING THE UNIT TO SERVICE.

(1)

If a new or overhauled governor (6) is being installed, install the straight nipple (8): (a) Lightly lubricate the new preformed packing (7) with engine oil (PWC03-001) and install on the nipple. (b) Install the nipple in the Py port in the propeller governor. Tighten the nipple 65 to 75 lb.in.

(2)

Install a new gasket (11) over the studs of the propeller governor mounting pad, making sure the raised side of the gasket faces upward.

61-20-00 PROPELLER GOVERNOR - MAINTENANCE PRACTICES

Page 203 Apr 25/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

(3)

Install the governor over the studs onto the gasket. Rotate the propeller shaft slightly to engage the governor drive splines. Make sure the governor and the gasket are mounted flush.

CAUTION:

(4)

Secure the governor with washers and self-locking nuts (10) using the retaining nut wrench (PWC30114-16). Tighten the nuts 125 to 135 lb.in.

(5)

Install the reversing lever to the Beta valve using the clevis pin, washer and the cotterpin (Ref. 76-10-00).

(6)

Install the propeller governor interconnect rod to the governor airbleed link (Ref. 76-10-00).

(7)

Connect the airframe linkage to the speed select lever on the propeller governor.

(8)

Install the Py air tube (9) to the nipple. Tighten the coupling nut 90 to 100 lb.in., and fasten with lockwire.

(9)

Install the electrical connector to the lock pitch solenoid valve (2) if fitted on the propeller governor, and also, if applicable, the propeller speed synchronizer.

(10) 6.

DO NOT EXCEED THE TORQUE LIMITS OF 125 TO 135 LB. IN. FOR PROPELLER GOVERNOR INSTALLATION. OVER-TORQUE CAN LEAD TO DISTORTION OF THE PROPELLER GOVERNOR AND POSSIBLE SEIZURE OF THE INTERNAL PUMP WHICH DELIVERS OIL TO THE PROPELLER.

Pressure test the pneumatic system (Ref. 73-10-07).

Inspection/Check A.

B.

C.

Propeller Governor (1)

Examine the mounting flange and the body for cracks and other defects. Cracks are not acceptable.

(2)

Examine for broken or damaged lockwire. If broken, have the unit bench-checked for tightness of connections and re-lockwired before placing unit in service.

(3)

Examine the fluid ports for damage.

Electrical Connectors and Leads (1)

Examine the threads for damage. Chase the threads to remove minor damage. Replace the governor if threads are badly damaged or crossed.

(2)

Check the output terminal pins; replace the governor if pins are loose or bent.

(3)

Check the leads for damage to the outer covering.

Governor Gasket (1)

Examine for tears in, and deterioration of the gasket material.

61-20-00 PROPELLER GOVERNOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

7.

(2)

Examine for breakdown of the bond between the non-metallic material and the steel plate core.

(3)

Examine the mounting holes for elongation.

(4)

Examine the screen for damage and looseness.

Adjustment/Test After the installation of a new or overhauled propeller governor, adjust and test as detailed in Chapter 71-00-00, ADJUSTMENT/TEST.

8.

Approved Repairs A.

Replacement of Lock Pitch Solenoid Valve (if fitted) (1)

Disconnect the electrical lead from the connector on the solenoid valve (2) (if fitted).

(2)

Remove the four screws (1) and washers securing the solenoid valve to the propeller governor (6) and remove the solenoid valve.

(3)

Remove and discard the preformed packings (3), (4) and (5) from the recesses in the valve mating flange.

(4)

Lightly lubricate the new preformed packings (3), (4) and (5) with engine oil (PWC03-001), and install the packings in the appropriate recesses on the mating flange of the solenoid valve (2).

(5)

Install the solenoid valve on the mating flange of the propeller governor (6) and secure with four washers and screws (1). Tighten the screws 9 to 11 lb.in., and fasten with lockwire.

61-20-00 PROPELLER GOVERNOR - MAINTENANCE PRACTICES

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Jan 13/2020 Jan 13/2020

Contents

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Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020

201 202 203 204 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220 221 222 223 224 225 226 227 228 229 230 231 232 233

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70-00-00 Maintenance Practices

CHAPTER SECTION

PAGE

DATE

234 235 236 237 238 239 240 241 242 243 244 245 246 247 248 blank

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70-00-00 Removal/ Installation

401 402 403 404 405 406 blank

Feb 11/2000 Feb 11/2000 Feb 11/2000 Feb 11/2000 Feb 11/2000 Feb 11/2000

70-00-00 Inspection Check

601 602 603 604 605 606

Feb 11/2000 Feb 11/2000 Feb 11/2000 Feb 11/2000 Feb 11/2000 Feb 11/2000

70-00-00 Cleaning/ Painting

701 702

Feb 11/2000 Feb 11/2000

70-00-00 Approved Repairs

801 802 803 804 805 806 807

Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010

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CHAPTER SECTION

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DATE Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010

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TABLE OF CONTENTS SUBJECT

PAGE

STANDARD PRACTICES - MAINTENANCE PRACTICES

70-00-00

1.

General

201

2.

Standard Torques

202

A.

202

3.

4.

5.

General

Torque Indicating Devices

204

A.

General

204

B.

Torque Wrench and Extensions

204

Torque Recommendations

205

A.

Lubricated Parts

205

B.

Nuts, Bolts and Screws

205

C.

Self-locking Nuts

207

D.

Power Torque Wrench

208

E.

Lockwire and Cotterpin Requirements

209

F.

Slotted, Steel Locknuts (Prevailing Torque Type)

209

G. Standard and Stepped Studs

209

H.

209

Hose, Tubing and Threaded Couplings

Locking Devices

210

A.

Keywashers (Tab and Cup Type)

210

B.

Retaining Rings

212

C.

Lockwire

212

D.

Safety Cable

217

6.

Identification of Hardware Material, Particularly Nuts and Bolts

229

7.

Stainless Steel Bolts with Reduced Pitch Diameters

231

8.

Debris Analysis and Material Specifications

231

A.

General

231

B.

Filter Patch Check Debris Inspection/Analysis

231

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TABLE OF CONTENTS SUBJECT

PAGE

STANDARD PRACTICES - MAINTENANCE PRACTICES (Cont’d) C.

9.

10.

11.

70-00-00

Inspection/Analysis of Debris Collected on Chip Detector or Magnetic Pulse Pick-up Sensors

233

D.

Identification of Metal Particles

234

E.

Material Specifications

236

F.

Laboratories

242

Marking of Parts

242

A.

General

242

B.

Permanent Marking

242

C.

Temporary Marking

243

Lubrication of Preformed Packings

244

A.

General

244

Touch-up Solution

245

A.

Chrome Pickle Solution (PWC05-161) (Magnesium RGB and AGB Housings)

245

B.

Chromate Repair of Magnesium Casings - Method A

245

C.

Chromate Repair of Magnesium Casings - Method B

246

D.

Repair of Protective Coating on Painted Surfaces

247

STANDARD PRACTICES - REMOVAL/INSTALLATION

70-00-00

1.

General

401

2.

Consumable Materials

402

3.

Special Tools

402

4.

Fixtures, Equipment and Supplier Tools

402

5.

Removal/Installation

402

A. B.

Removal of Straight Nipples, Straight Adapters, Bulkhead Couplings and Tube Connector Nipples

402

Removal of Tube-to-Boss Elbows, Elbow Adapters and Elbow Assemblies

402

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TABLE OF CONTENTS SUBJECT

PAGE

STANDARD PRACTICES - REMOVAL/INSTALLATION (Cont’d) C. D. E.

70-00-00

Installation of Straight Nipples, Straight Adapters, Bulkhead Couplings and Tube Connector Nipples

403

Installation of Tube-to-Boss Elbows, Elbow Adapters and Elbow Assemblies

403

Installation/Removal of Hydraulic, Oil and Pneumatic Lines

405

STANDARD PRACTICES - INSPECTION

70-00-00

1.

General

601

2.

Inspection

601

A.

General

601

B.

Inspection Terms

601

C.

Inspection Gages

603

D.

Magnetic Particle Inspection

604

E.

Fluorescent Penetrant Inspection

604

F.

Inspection of Fuel, Oil and Air Tubes

604

G. Inspection of Welded Repairs

604

H.

605

Inspection of Rotating Components

STANDARD PRACTICES - CLEANING

70-00-00

1.

General

701

2.

Cleaning

701

A.

General

701

B.

Precautions

701

C.

Cleaning Before Welding

702

STANDARD PRACTICES - REPAIR

70-00-00

1.

General

801

2.

Consumable Materials

801

3.

Special Tools

801

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TABLE OF CONTENTS SUBJECT

PAGE

STANDARD PRACTICES - REPAIR (Cont’d)

70-00-00

4.

Fixtures, Equipment and Supplier Tools

801

5.

Welding

802

A.

General

802

B.

Cleaning Before Welding

802

C.

Welding Procedures

802

D.

Cleaning After Welding

803

E.

Local Stress Relief

803

F.

Inspection of Welding

803

6.

7.

8.

9.

Blend Repairs

804

A.

Repair Procedure

804

B.

Definitions

804

C.

General

804

D.

Air Gun

804

Threaded Inserts

805

A.

805

Replacement of Threaded Inserts

Studs

805

A.

Replacement of Studs

805

B.

Replacement of Studs

806

C.

Repair of Damaged Stud Hole

807

Shanknuts

808

A.

808

Replacement of Shanknuts

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STANDARD PRACTICES - MAINTENANCE PRACTICES 1.

General A.

During disassembly, tag and mark all parts, clips, and brackets as to their location and position to prevent incorrect installation.

B.

During removal of tubes or engine parts look for indications of scoring, burning or other undesirable conditions. Tag unserviceable parts and units for investigation and possible repair.

C.

Extreme care shall be taken to prevent dust, dirt, lockwire, nuts, washers or other foreign matter from entering the engine. It cannot be overemphasized that this precaution applies whenever work is done on the engine either on the wing or off the wing. Suitable plugs, caps, and other covering shall be used to protect all openings as they are exposed. Dust caps used to protect open tubes against contamination shall always be installed over tube ends and not in the tube. Flow through the lines may be blocked if lines are inadvertently installed with dust caps in the tube ends.

D.

If at any time items are dropped into the engine, the assembly process must stop until the dropped articles are located, even though this may require a considerable amount of time and labor. Before assembling or installing any part, be sure it is thoroughly clean.

E.

Lockwire, lockwashers, tablocks, tabwashers, or cotterpins must never be reused. All lockwire and cotterpins must fit snugly in holes drilled in studs and bolts for locking purposes. Install a cotterpin so that the head fits into the castellation of the nut, and unless otherwise specified, bend one end of the pin back over the stud or bolt and the other end down flat against the nut. Only lockwire and cotterpins made of corrosion resistant steel shall be used. Bushing plugs shall be lockwired to the assembly boss or case; do not lockwire the plug to the bushing.

F.

Replace all gaskets, packings, and rubber parts at reassembly. Make sure that new nonmetallic parts to be installed (such as an oil seal) show no sign of having deteriorated in storage.

G. To protect critical areas of engine parts (such as compressor and turbine disks) against scratches and nicks, tool surfaces contacting these areas must be covered with protective material. H.

During replacement of components, note condition of any removed preformed packings. Pieces accidentally torn or cut from packings must be retrieved, regardless of size, even if this entails a systematic disassembly and cleaning of the system. Make sure that new packings are free of cuts, flashings and deformities which may be sheared off at installation.

I.

When installing engine parts that require the use of a hammer to facilitate assembly or installation, use only a plastic or rawhide hammer.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

2.

J.

Whenever pressure sensitive tape has been applied to any part, the tape must be removed and the part thoroughly cleaned of all tape residue prior to being subjected to high temperature during engine run. Test results indicate that all tapes are capable of causing surface attack and/or reduction in tensile ductility as temperature increases. Do not leave tape or tape residue on engine parts.

K.

If any part has been coated with corrosion preventive compounds, all traces of the compound and accumulated foreign matter must be removed.

Standard Torques A.

General (1)

Torque values given in the manual are to be interpreted: (a) Pound-inches at room temperature. (b) Angle of turn, in degrees. (c) Stretch values in inches.

(2)

Unless otherwise specified, thread lubricant shall be engine oil and shall be applied to parts which are to be tightened.

(3)

If the part to be tightened is hot, allow sufficient time for the part to reach temperature equilibrium with the surrounding area before final torquing.

(4)

Flange bolts shall be drawn up evenly. This can be achieved by having two mechanics working simultaneously 180 degrees apart.

(5)

Tightening applications should be done slowly and evenly for consistency and the best possible accuracy. Check for adequate torque of self-locking fasteners before reuse. Discard fastener if locking capability is impaired. Do not repair self-locking fasteners.

(6)

Six-point crowfoot adapters are recommended for applying torque values above 110 lbf.in. to tube fittings (Ref. Fig. 201).

(7)

Self-locking nuts, self-locking bolts, and self-locking helical coil inserts shall be capable of meeting the torque requirements in Table 201.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

C118249A Six-Point Crowfoot Adapter Figure 201 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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STANDARD PRACTICES - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 201, Torque Check for Reuse of Self-Locking Nuts, Bolts and Helical Coil Inserts (Pound-inches at Room Temperature and Lubricated With Engine Oil) Max Locking Torque

Min Breakaway Torque

0.112-40NC-2A

3

0.5

1.0

0.125-40NC-2A

4

1.0

9

1.5

0.138-32NC-2A

6

1.0

0.190-32UNF-3A

13

2.0

0.164-32NC-2A

9

1.5

0.250-28UNF-3A

30

3.5

0.190-24UNC-3A

13

2.0

0.3125-24UNF-3A

60

6.5

0.250-20UNC-3A

30

4.5

0.375-24UNF-3A

80

9.5

0.3125-18UNC-3A

60

7.5

0.4375-20UNF-3A

100

14.0

0.375-16UNC-3A

80

12.0

0.500-20UNF-3A

150

18.0

0.4375-14UNC-3A

100

16.5

0.5625-18UNF-3A

200

24.0

0.500-14UNC-3A

150

24.0

0.625-18UNF-3A

300

32.0

0.5625-12UNC-3A

200

30.0

0.750-16UNF-3A

400

50.0

0.625-11UNC-3A

300

40.0

0.875-14UNF-3A

600

70.0

0.750-10UNC-3A

400

60.0

Max Locking Torque

Min Breakaway Torque

0.112-48NF-2A

3

0.5

0.138-40NF-2A

6

0.164-36NF-2A

Mating Bolt Thread Size

Mating Bolt Thread Size

NOTE: The breakaway torque specified is the minimum torque required to overcome static friction, and applies at installation or removal. The locking torque specified is the maximum torque required to overcome kinetic friction and applies at installation or removal. NOTE: Use the listed bolt sizes for torque testing cadmium plated nuts, carbon steel nuts, alloy steel nuts, and aluminum nuts. 3.

Torque Indicating Devices A.

General (1)

B.

Check torque indicating devices before using, and calibrate them by means of weights and a measured lever arm to make sure that there are no inaccuracies. Checking one torque wrench against another is not sufficient. Some wrenches are quite sensitive to the way they are supported during a tightening operation, and every effort must be made to adhere to the instructions furnished by the respective manufacturers.

Torque Wrench and Extensions (1)

Occasionally, it is necessary to use a special extension, or adapter wrench together with a standard torque wrench (Ref. Fig. 202). In order to arrive at the resultant required torque limits, the following formula shall be used: T - Desired torque on the part.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

E - Effective length of special extension or adapter. L - Effective length of torque wrench. A - Distance through which force is applied to part. R - Reading on scale or dial of torque wrench. R=

LT A

=

LT L+E

Example: A torque of 1440 lb.in. is desired on a part, using special extension having a length of three inches from center to center of its holes, and a torque wrench measuring 15 inches from center of handle or handle swivel pin to center of its square adapter. Then: LT

R=L+E= (2)

4.

15 X 1440 15 + 3

= 1200 lb.in.

With the axis of the extension or adapter and the torque wrench in a straight line, tightening to a wrench reading of 1200 lb.in. will provide the desired torque of 1440 lb.in. on the part.

Torque Recommendations A.

B.

Lubricated Parts (1)

All nut, bolt and screw torques should be obtained using a thread lubricant. The lubricant should be engine oil, or equivalent, unless otherwise specified. Torque requirements for interference fit application, such as studs and pipe plugs, may be obtained with or without lubrication, unless otherwise specified.

(2)

Antigalling compound should be applied to all loose-fit spline drives which are external to the engine and have no other means of lubrication. For certain assembly procedures, molybdenum disulfide in either paste or powder form mixed with engine oil or grease may be used. Particular applications of molybdenum disulfide are indicated in the individual text portions of this manual. Make sure antiseize and antigalling compounds are applied in a thin even coat, and that excess is completely removed to avoid contamination of adjacent parts, passages or surfaces where the compound may cause malfunctioning, or failure, of engine.

(3)

The torque values given within the text apply to nuts where the height of the nut is approximately equal to the major diameter of the thread. For jam nuts refer to REMOVAL/INSTALLATION. Torque values do not apply to hollow bolts and screws.

Nuts, Bolts and Screws (1)

Bolts and nuts on flanges with metal tubular gaskets must be initially torqued to the required torque and then retorqued until the torque value given in the relevant assembly instruction remains constant.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

E

L A

C2178 Torque Wrench and Extension Figure 202 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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STANDARD PRACTICES - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

C.

Self-locking Nuts (1)

The locking torque for self-locking nuts and helical coil inserts must be checked at assembly. The locking torque must not be less than the values shown (Ref. Table 202) unless otherwise specified.

(2)

When checking self-locking torque, care must be taken to ensure the fastener is not seated. This ensures that only the torque necessary to overcome the friction holding the thread is measured. NOTE: Self-locking nuts should be checked for effectivity of self-locking feature before reinstallation. Reject suspect nuts as necessary.

(3)

For each item, note the torque necessary to turn nut on bolt before seating the nut.

(4)

Add this torque to the value detailed in the assembly instructions for the application. Use this new value as the total applied torque. TABLE 202, Locking Torque for Self-locking Nuts and Helical Coil Inserts Thread Size

Torque lb.in. Min

0.112-40

0.5

0.112-48

0.5

0.138-32

1.0

0.164-32

1.5

0.164-36

1.5

0.190-24

2.0

0.190-32

2.0

0.2500-20

4.5

0.2500-28

3.5

0.3125-18

7.5

0.3125-24

6.5

0.3750-16

12.0

0.3750-24

9.5

0.4375-14

16.5

0.4375-20

14.0

0.5000-13

24.0

0.5000-20

18.0

0.5625-12

30.0

0.5625-18

24.0

0.6250-11

40.0

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 202, Locking Torque for Self-locking Nuts and Helical Coil Inserts (Cont’d)

D.

Thread Size

Torque lb.in. Min

0.6250-18

32.0

0.750-10

60.0

0.750-16

50.0

0.875-9

82.0

0.875-14

70.0

1.000-8

110.0

1.000-12

90.0

Power Torque Wrench (1)

The retaining nut for the power turbines is removed and installed with a power torque wrench and appropriate adapter, supplied with the engine overhaul kit.

(2)

The power torque wrench employs a high ratio geartrain operated by a handcrank (supplied with the tool) or a pneumatic ratchet drive tool. A 3⁄4-inch square drive bar (also supplied with the tool) transmits the output torque of the geartrain to the socket wrench on the nut being turned. Two 1⁄2-inch diameter pins on each space adapter transmit the counteracting load. Input and output shafts of the wrench rotate in the same direction.

(3)

It must be emphasized that when using a countertorque adapter attached to the nut, the direction of the input drive is opposite to that normally required on the nut being turned, i.e., when tightening a nut, the input drive must be turned counterclockwise; when loosening, the reverse rotation applies.

(4)

To tighten a nut, using the power torque wrench and appropriate countertorque adapter: (a) Install socket wrench on nut. (b) Install appropriate countertorque adapter on part being assembled. NOTE: Observe instructions marked on adapter denoting direction of rotation required when torquing and untorquing. (c) Install power torque wrench on adapter, and engage both pins. (d) Insert 3/4-inch output drive bar into wrench output shaft, and turn until bar engages socket wrench. (e) Turn ratchet (located on front face of power wrench) in same direction as that required to turn output driveshaft. (f)

Insert input drive source (handle or power-operated wrench) in input shaft, and turn in same direction as that required for output shaft.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

(g) Continue turning until torque indicator reaches required reading on scale. NOTE: Since the torque indicator is calibrated in pounds-feet, the appropriate conversion must be made when torquing to values specified in pounds-inches. (h) To remove power wrench, reverse direction of rotation of input drive until indicator returns to zero (green band); this removes the holding pressure on the wrench, allowing it to be withdrawn from the adapter. (i) (5) E.

To untorque, repeat the preceding steps (a) through (i), except for rotational direction of ratchet and input shaft, which must be reversed.

Lockwire and Cotterpin Requirements (1)

F.

Remove power wrench, adapter and socket wrench.

When tightening a castellated nut, alignment of the slot must be obtained without exceeding the maximum torque. If this is not possible, replace the nut with another one. After tightening the nut to the recommended torque, the nut must not be loosened to permit insertion of lockwire or cotterpin. If the slot in the nut or the lockwire hole in the bolt or screw is not correctly aligned at the minimum torque value given, the nut, screw or bolt should be further tightened to the next alignment position, but the maximum torque value given must not be exceeded. Should the alignment still be impossible without exceeding the maximum torque, back off the nut, screw or bolt one-half turn and retorque.

Slotted, Steel Locknuts (Prevailing Torque Type) (1)

Effective locking of slotted, steel locknuts on bolts or studs requires full engagement of all locknut threads. The chamfered section of the locknut ID does not exert force on the bolt or stud; therefore, it is not necessary that the bolt or stud be flush with, or protrude from, the outer face of the locknut.

G. Standard and Stepped Studs (1)

H.

When the torque required to drive a stud to the correct protrusion does not reach the minimum value given, or exceeds the maximum value given, a new stud must be selected.

Hose, Tubing and Threaded Couplings (1)

If leakage occurs at a coupling, do not attempt to correct by overtorquing. Disassemble the fitting and check for nicks, burrs and/or foreign matter. Use new parts, as required, to rectify fault.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

5.

Locking Devices A.

Keywashers (Tab and Cup Type) (Ref. Fig. 203)

CAUTION:

KEYWASHERS ARE TO BE USED ONCE ONLY. INSTALL NEW KEYWASHER(S) AT EACH ASSEMBLY.

CAUTION:

DO NOT USE SHARP EDGED TOOLS TO BEND OR SET KEYWASHER TABS. TAB DETACHMENT MAY OCCUR WITH SUBSEQUENT DAMAGE TO THE ENGINE.

(1)

The terms keywasher, tabwasher and cupwasher are interchangeable, as used in this manual.

(2)

When bending or setting the tabs on these washers, do not use sharp-pointed tools. Use of such tools can lead to subsequent failure of the locking tabs which, on becoming detached, can pass through the engine causing extensive damage.

(3)

Key and tab washers typically have an anti turn tang that inserts into the engine part accepting the bolt. During torquing of bolt, it is important to make sure this tang is loaded in a counter clockwise direction within its hole so that the bolt and washer do not turn during operation.

(4)

Assembly requirements for cupwashers: (a) Examine the cupwasher for freedom from deep drawing score marks (especially in undercut adjacent to tangs) and for freedom from prior assembly/handling damage, i.e. bent tangs or prior stake marks. (b) Examine contact surfaces for excessive roughness, burrs, or scores that may cause the washer to bend on the nut. (c) Examine the nut for burrs, nicks or scratches on the face adjacent to the cupwasher that could cause the nut to pick up on the washer. (d) The cupwasher must be lubricated on the nut side only, the opposite face must be clean and dry. (e) With the cupwasher placed against the shaft slots opposite to direction of nut tightening, screw the nut fingertight. (f)

With an approved silver pencil, make an alignment mark on the cupwasher outside diameter and the component immediately adjacent to cupwasher.

(g) Tighten the nut in the normal manner. (h) If the alignment mark has moved, remove and discard the cupwasher. (i)

Repeat the procedure with a new cupwasher.

(j)

Stake the cupwasher.

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B.

Retaining Rings CAUTION:

(1)

C.

THOROUGHLY INSPECT ALL RETAINING RINGS, INCLUDING SPIROLOX, FOR CONDITION. DISTORTED RINGS ARE NOT ACCEPTABLE AND MUST BE REPLACED.

Retaining rings must be installed using approved retaining ring pliers. Internal type rings must not be compressed beyond the point where the ends of the ring meet. External type rings must be expanded just enough to allow installation without becoming bent. After installation, make sure that each ring is completely seated, without looseness or distortion in its groove.

Lockwire (1)

Except where otherwise specified, the wire is made of heat and corrosion resistant steel wire 0.025 inch diameter.

(2)

Lockwire must be tight after installation to prevent failure due to rubbing or vibration.

(3)

Lockwire must be installed in a manner that tends to tighten and keep a part locked in place thus counteracting the natural tendency of the part to loosen.

(4)

Lockwire must never be overstressed. It will break under vibration if twisted too tightly. The lockwire shall be pulled taut when being twisted, but shall have minimum tension, if any when secured.

(5)

Lockwire ends must be bent toward the engine, or part, to avoid sharp or projecting ends which might present a safety hazard or vibrate in the air stream.

(6)

Internal wiring must not cross over or obstruct a flow passage when an alternate method can be used.

(7)

Check the units to be lockwired to make sure they have been correctly torqued and that the wiring holes are properly positioned in relation to each other. When there are two or more units, it is desirable that the holes in the units be in the same relationship to each other. Never overtorque or loosen units to obtain proper alignment of the holes. It should be possible to align the wiring holes when the units are torqued within the specified limits. However, if it is impossible to obtain a proper alignment of the holes without either over or under torquing, select another unit which will permit proper alignment within the specified torque limits.

(8)

To prevent mutilations of the twisted section of the wire when using pliers, grasp the wire at the ends or at a point that will not be twisted. Lockwire must not be nicked, kinked, or mutilated. Never twist the wire ends off with the pliers and when cutting off ends, leave at least three complete turns after the loop, exercising extreme care to prevent the wire ends from falling into the engine. The strength of the lockwire holes is marginal; never twist the wire off with pliers. Cut the lockwire close to the hole, exercising extreme care.

(9)

Figure 204 illustrates a typical lockwiring procedure. Although there are numerous lockwiring operations performed on these engines, practically all are derived from the basic examples shown in Figure 205.

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10:30 O’CLOCK

4:30 O’CLOCK

POSITION THE HOLES

INSERT THE UPPERMOST WIRE, WHICH POINTS TOWARDS THE SECOND BOLT, THROUGH THE HOLE WHICH LIES BETWEEN THE NINE AND TWELVE O’CLOCK POSITIONS. GRASP THE END OF THE WIRE WITH A PAIR OF PLIERS AND PULL THE WIRE TIGHT.

INSERT PROPER GAGE WIRE

BRING THE FREE END OF THE WIRE AROUND THE BOLT HEAD IN A COUNTERCLOCKWISE DIRECTION AND UNDER THE END PROTRUDING FROM THE BOLT HOLE. TWIST THE WIRE IN A COUNTERCLOCK− WISE DIRECTION.

GRASP UPPER END OF THE WIRE AND BEND IT AROUND THE HEAD OF THE BOLT, THEN UNDER THE OTHER END OF THE WIRE. BE SURE WIRE IS TIGHT AROUND HEAD.

GRASP THE WIRE BEYOND THE TWISTED PORTION AND TWIST THE WIRE ENDS COUNTER− CLOCKWISE UNTIL TIGHT.

TWIST WIRE UNTIL WIRE IS JUST SHORT OF HOLE IN THE SECOND BOLT.

DURING THE FINAL TWISTING MOTION OF THE PLIERS, BEND THE WIRE DOWN AND UNDER THE HEAD OF THE BOLT.

KEEPING WIRE UNDER TENSION, TWIST IN A CLOCKWISE DIRECTION UNTIL THE WIRE IS TIGHT. WHEN TIGHTENED THE WIRE SHALL HAVE APPROXIMATELY 7 TO 10 TWISTS PER INCH.

CUT OFF EXCESS WIRE WITH DIAGNOL CUTTERS.

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EXAMPLE 1

EXAMPLE 2

EXAMPLE 3

EXAMPLE 4

EXAMPLES 1,2,3 AND 4 APPLY TO ALL TYPES OF BOLTS, FILLISTER HEAD SCREWS, SQUARE HEAD PLUGS, AND OTHER SIMILAR PARTS WHICH ARE WIRED SO THAT THE LOOSENING TENDENCY OF EITHER PART IS COUNTERACTED BY TIGHTENING OF THE OTHER PART. THE DIRECTION OF TWIST, FROM THE SECOND TO THE THIRD UNIT, IS COUNTER−CLOCKWISE TO KEEP THE LOOP IN POSITION AGAINST THE HEAD OF THE BOLT. THE WIRE ENTERING THE HOLE IN THE THIRD UNIT WILL BE THE LOWER WIRE AND BY MAKING A COUNTER−CLOCKWISE TWIST AFTER IT LEAVES THE HOLE, THE LOOP WILL BE SECURED IN PLACE AROUND THE HEAD OF THAT BOLT.

EXAMPLE 5

EXAMPLE 6

EXAMPLE 7

EXAMPLE 8

EXAMPLES 5,6,7 AND 8 SHOW METHODS FOR WIRING VARIOUS STANDARD ITEMS. WIRE MAY BE WRAPPED OVER THE UNIT RATHER THAN AROUND IT WHEN WIRING CASTELLATED NUTS OR ON OTHER ITEMS WHEN THERE IS A CLEARANCE PROBLEM.

EXAMPLE 9

EXAMPLE 10

EXAMPLE 9 SHOWS THE METHOD FOR WIRING BOLTS IN DIFFERENT PLANES. NOTE THAT WIRE SHOULD ALWAYS BE APPLIED SO THAT TENSION IS IN THE TIGHTENING DIRECTION.

EXAMPLE 10 SHOWS HOLLOW HEAD PLUGS WIRED WITH THE TAB BENT INSIDE THE HOLE TO AVOID SNAGS AND POSSIBLE INJURY TO PERSONNEL WORKING ON THE ENGINE.

EXAMPLE 11 EXAMPLE 11 SHOWS CORRECT APPLICATION OF SINGLE WIRE TO CLOSELY SPACED MULTIPLE GROUP.

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EXAMPLE 12

EXAMPLE 13

EXAMPLES 12 AND 13 SHOW METHODS FOR ATTACHING LEAD SEAL TO PROTECT CRITICAL ADJUSTMENTS.

EXAMPLE 14

EXAMPLE 15

EXAMPLE 14 SHOWS BOLT WIRED TO A RIGHT ANGLE BRACKET WITH THE WIRE WRAPPED AROUND THE BRACKET.

EXAMPLE 15 SHOWS CORRECT METHOD FOR WIRING ADJUSTABLE CONNECTING ROD.

EXAMPLE 17

EXAMPLE 18

EXAMPLE 19

EXAMPLE 16 EXAMPLE 16 SHOWS CORRECT METHOD FOR WIRING THE COUPLING NUT ON FLEXIBLE LINE TO THE STRAIGHT CONNECTOR BRAZED ON RIGID TUBE.

EXAMPLE 20

FITTINGS INCORPORATING WIRE LUGS SHALL BE WIRED AS SHOWN IN EXAMPLES 17 AND 18. WHERE NO LOCKWIRE LUG IS PROVIDED, WIRE SHOULD BE APPLIED AS SHOWN IN EXAMPLES 19 AND 20 WITH CAUTION BEING EXERTED TO ENSURE THAT WIRE IS WRAPPED TIGHTLY AROUND THE FITTING.

EXAMPLE 21 SMALL SIZE COUPLING NUTS SHALL BE WIRED BY WRAPPING THE WIRE AROUND THE NUT AND INSERTING IT THROUGH THE HOLES AS SHOWN.

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EXAMPLE 22

EXAMPLE 23

COUPLING NUTS ATTACHED TO STRAIGHT CONNECTORS SHALL BE WIRED AS SHOWN WHEN HEX IS AN INTEGRAL PART OF THE CONNECTOR.

EXAMPLE 24 COUPLING NUTS ON A TEE SHALL BE WIRED AS SHOWN ABOVE SO THAT TENSION IS ALWAYS IN THE TIGHTENING DIRECTION.

EXAMPLE 25 STRAIGHT CONNECTOR (BULKHEAD TYPE)

EXAMPLE 26

EXAMPLE 27

EXAMPLE 28

EXAMPLES 26, 27 AND 28 SHOW THE VARIOUS STANDARD FITTINGS WITH CHECK NUT WIRED SO THAT IT NEED NOT BE DISTURBED WHEN REMOVING THE COUPLING NUT.

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D.

Safety Cable (Ref. Figs. 206 and 207) (1)

General: (a) Safety cable is installed through two or more parts in such a way that as the fastener loosens the safety cable will tighten. By tightening, the safety cable will not permit the fastener to loosen or turn. The safety cable system is made up of two components: the safety cable/ferrule kit (PWC05-344) and a crimping tool (PWC90025) (Ref. Fig. 206). (b) The safety cable is available in one size, 0.032 inch (0.81 mm) diameter, and is made of stainless steel material. One end of the cable will have a cable end fitting swaged to it. The cable end fitting is made of stainless steel material. The strands of the cable on the opposite end of the cable are fused together to prevent the cable from fraying. (c) The ferrules are made of stainless steel material and are purchased in a spring-loaded, disposable cartridge. When the safety cable is installed the ferrule will be crimped on the open end of the cable. (d) The hand operated crimping tool comes in two different lengths. The crimping pressure of the tool is set by the manufacturer. The primary parts of the crimping tool are the nose assembly and the tool body. This tool is used to crimp the ferrule on the end of the safety cable. The crimping tool will cut the safety cable even with the ferrule at the same time the ferrule is crimped. (e) Where safety cable is specified, it may be replaced with lockwire. Use lockwire as specified in Table 203. TABLE 203, Safety Cable Substitution

Nominal Safety Cable Diameter

Lockwire Substitution

0.032 inch (0.815 mm)

AS3214-02 or MS9226-04

NOTE: Lockwire AS3214 may be used in engine external applications only.

(2)

Basic Installation Rules: (a) It is not permissible to re-use safety cable or a ferrule. The safety cable and ferrule must be new for every application. (b) Unless specified differently in assembly procedure, safety cable should be installed in double- or triple-bolt patterns. The double-bolt pattern is preferred when you apply safety cable to an even number of fasteners. (c) The maximum allowable span of safety cable between two end points is 6 inches (152.4 mm), unless otherwise specified. (d) Any damages (such as fray, nicks, kink or any damage to the safety cable) to any portion of the safety cable prior to, during or after installation is not permitted.

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SAFETY CABLE

FERRULE FERRULE CARTRIDGE

TOOL BODY

HANDLE NOSE ASSEMBLY

CABLE ENTRANCE

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STANDARD HARDWARE

COUPLINGS

OTHER APPLICATIONS

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CAUTION:

DO NOT USE SAFETY CABLE IF THE HOLES ARE MORE THAN 0.100 INCH (2.54 mm) DIAMETER. THE FERRULES ON THE END OF THE CABLE ARE 0.106 - 0.108 INCH (2.69 - 2.74 mm) DIAMETER AND WILL FALL THROUGH HOLES LARGER THAN THIS.

(e) Always install safety cable through the safety cable holes provided on the fastener. (f)

Do not decrease or increase the torque on the parts to correctly align the holes for the cable.

(g) Install safety cable so that any tendency for a fastener to loosen is counteracted by more tension on the cable. (h) It is recommended that there be no sharp turns more than 90° when the cable is passed through a fastener. Installation of safety cable should be with either a positive or neutral pull. (i)

Cable flex limits are specified in Figure 210. These values are the maximum flex limits between the end points when light finger pressure of approximately 2 pound (8.9 N) is applied at midspan.

(j)

Cut off excess cable from crimped ferrule after installation of safety cable.

(k) Maximum length of cable beyond crimped ferrule is 0.031 inch (0.787 mm). (l)

Where specified, apply and crimp an aluminum seal to the load bearing portion of the safety cable.

(m) After installing the seal, make sure that it is snug on the cable and that it cannot be moved without showing evidence of tampering. (n) After installing the seal, an inspection stamp or other means of identification shall be applied to the seal. (3)

Installation (Ref. Fig. 208): (a) Install ferrule cartridge into crimper tool body (PWC90025). (b) Do a visual inspection of the holes to be used to find all damage. If the hole is damaged, replace the part or, if possible, use another hole to install safety cable. NOTE: Keep the safety cable as straight as possible when you locking the fasteners or parts together. (c) Insert the free end of the safety cable (PWC05-344) into the hole of the part. Pull the cable through the hole until the cable end fitting is against the part. NOTE: On a double-bolt pattern, do not safety cable in a negative pull direction. Make sure the safety cable has a positive or neutral pull.

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FERRULE CARTRIDGE BOLT B BOLT B

BOLT A BOLT A

BOLT A

90

BOLT B

BOLT B

NOSE ASSEMBLY

BOLT A BOLT A

BOLT B

BOLT B

FERRULE

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(d) Install the end of the cable through the second part. Choose the hole in the part that permits the cable to be as straight as possible. Pull the cable through the second part. If three parts must be safety cabled, do the same procedure for the third part. (e) The nose can be changed to four different positions at 90° increments. To select the position, push the nose in towards the tool, rotate to the desired position, and release the nose. If the nose does not lock into the indexed position, turn it slightly until it does (Ref. Fig. 209). (f)

Install the free end of the safety cable through a ferrule (PWC05-344). Use the safety cable to pull the ferrule out of the ferrule cartridge.

(g) Put the end of the safety cable through the crimping head of the crimping tool. Make sure the large hole in the crimping head is on the same side as the ferrule. Move the crimping tool along the safety cable until the crimping head is against the part. Make sure the ferrule goes inside the hole in the crimping head. (h) Install the free end of the cable into the cable entrance. Continue to push the cable into the cavity. When the free end of the cable appears at the bottom of the tool, grab the cable and pull the slack from the cable until resistance is felt. NOTE: Grip the cable as close to the free end as possible during insertion to prevent buckling of the cable. (i)

When all slack is removed from the cable, make sure the tool is snugly against the fastener by using several short strokes of the handle. Release the handle to the full open position and fully close the handle to affect crimping and cutting.

CAUTION:

(j)

IT IS IMPORTANT ON THIS FINAL STROKE TO HOLD THE TOOL AS STEADY AND PERPENDICULAR TO THE CABLE AS POSSIBLE WHILE ENSURING THAT A FULL STROKE IS USED TO MAINTAIN A CONSISTENT TENSIONING OF THE CABLE.

After crimping and cutting, release the tool handle and slide the tool off the crimped ferrule. Pull the excess cable from the tool.

(k) Remove and discard unused safety cable from the bottom of the crimping tool. (4)

Verification (Ref. Fig. 210): (a) Push against the safety cable with light finger pressure halfway between the locked parts. If the cable feels loose, do a dimensional check to make sure the safety cable is serviceable as follows: 1 Measure the distance between the locked parts. Write this measurement down as Dimension A. If three parts are locked together, measure the distance between each of the parts and add the two measurements together to get Dimension A.

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PU INDSH TO EX

2 1

3

4

90

I TYP

CA

NOTE: THE NOSE ASSEMBLY CAN BE ADJUSTED TO 4 POSITIONS IN 90 INCREMENTS. TO SELECT THE POSITION, PUSH THE NOSE ASSEMBLY IN AND ROTATE TO THE DESIRED POSITION.

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L

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

DIM. A

DIM. B DIM. C

DIM. D

FOR TRIPLE BOLT PATTERNS DIM. A = DIM. D + DIM. E

DIM. E

DIM. A

0.5 IN. 1.0 IN. 2.0 IN. 3.0 IN. 4.0 IN. 5.0 IN. 6.0 IN.

(12.7 mm) (25.4 mm) (50.8 mm) (76.2 mm) (101.6 mm) (127.0 mm) (152.4 mm)

DIM. B

0.125 IN. 0.250 IN. 0.375 IN. 0.375 IN. 0.500 IN. 0.500 IN. 0.625 IN.

(3.18 mm) (6.35 mm) (9.52 mm) (9.52 mm) (12.70 mm) (12.70 mm) (15.88 mm)

DIM. C

0.062 IN. 0.125 IN. 0.188 IN. 0.188 IN. 0.250 IN. 0.250 IN. 0.312 IN.

(1.59 mm) (3.18 mm) (4.76 mm) (4.76 mm) (6.35 mm) (6.35 mm) (7.94 mm)

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2 Push against the safety cable with light finger pressure halfway between the two locked parts. Measure the distance the safety cable moves laterally. Writes this measurement down as Dimension C. 3 Compare the dimensions written down to the limits given. CAUTION:

DO NOT TRY TO BREAK THE SAFETY CABLE. IF THE SAFETY CABLE MUST BE REMOVED, CUT THE SAFETY CABLE TO AVOID DAMAGE TO THE HOLES OF THE PART.

(b) If the safety cable is not within limits, cut the safety cable with wire cutters and remove the safety cable. Install new safety cable. (c) Check that cable was installed through bolts correctly (Ref. Step (3)). (d) Verify that cable was cut flush at the end of the ferrule with no strand extending more than 1/32 inch from the end of the ferrule. (e) Visually inspect safety cable for kinks, frayed wires, or improper crimps. Remove and replace safety cable if problem exists. (5)

Indenter Adjustment (Ref. Fig. 211): (a) Remove the nose assembly by removing the two socket head cap screws. CAUTION:

DO NOT ADJUST THE PUSHROD MORE THAN A QUARTER OF A TURN AT A TIME. SEVERE ADJUSTMENTS MAY DAMAGE THE TOOL.

(b) Adjust the pushrod adjustment screw using a 0.25 inch (6.4 mm) straight edge screw driver. Rotate the pushrod adjustment screw clockwise to loosen the crimp (enlarge the gaging dimension). Rotate the adjustment screw counterclockwise to tighten the crimp (reduce gaging dimension). (c) Replace the nose assembly and the two socket head cap screws. Rotate each screw a small amount until tight to prevent binding. CAUTION:

TIGHTENING THE CRIMP INCREASES REQUIRED HAND FORCES DURING APPLICATION AND INCREASES CABLE ASSEMBLY TENSILE VALUES. LOOSENING THE CRIMP DECREASES REQUIRED HAND FORCES DURING APPLICATION AND DECREASES CABLE ASSEMBLY TENSILE VALUES.

(d) Check calibration as described in (Ref. Step. (6)). (6)

Indenter Calibration (Ref. Fig. 212): NOTE: 1. Indenter calibration should be checked periodically and must be checked after the nose assembly has been removed or interchanged. NOTE: 2. Do a pull-off load test as often as necessary to make sure the crimp done by the crimping tool meets the necessary requirements. (a) Set up test block (PWC90026).

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NOSE ASSEMBLY

A

NOSE ADAPTER 8−32 SOCKET HEAD CAP SCREWS

PUSHROD ADJUSTMENT SCREW

VIEW A

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TEST DIRECTION

TORQUE WRENCH (ib. in.) 80 90

75 85 95

MOUNTING HOLES

TEST

12 PT SCREW

AREA

LEVER

SWIVEL

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(b) Thread the cable into the 12 point screw and through the swivel, holding the lever in the home position. If the lever is not kept in the home position the results may be adversely affected. Cut the cable by making sure to close the handles completely. (c) Apply approximately 2 lbs. force to the cable with your finger at the line marked test area. If the cable touches either the side or bottom surface of the test area then remove the cable from the test block and use another cable as described (Ref. Step. (6) (b)). (d) Place a 3/8 inch drive torque wrench into the square drive hole, orientating the test block and torque wrench on a flat surface. Apply the proper pull-off load as shown in Table 204. Release torque when minimum pull-off load is achieved. NOTE: Do not apply additional tension to safety cable than that is required to achieve minimum pull-off load. (e) If the cable did not break or pull out of the ferrule after applying proper torque, remove the torque wrench and apply approximately 2 lbs. force to the cable with your finger at the line marked test area. (f)

If the cable breaks, touches either the side or bottom surface of the test area or pulls out of the ferrule, then the crimp is unacceptable and the tool indenter should be adjusted (Ref. Step. (5)).

TABLE 204, Safety Cable Minimum Crimp Requirements (Pull-off Load)

(7)

Nominal Cable Diameter

Minimum Pull-off Load

0.032 Inch (0.81 mm)

70 Inch-Pounds (7.909 Nm)

Maintenance of Crimp Cavity: (a) Debris can accumulate in the crimp cavity during use. This debris must be removed and the cavity oiled periodically depending upon use and environment. NOTE: Ferrule sticking can occur if this procedure is not followed. (b) Remove debris by gently scraping or brushing the crimp cavity. (c) Blow any remaining debris from the cavity with air. (d) Coat the cavity with a light film of any lightweight synthetic or petroleum based oil after the cavity has been thoroughly cleaned.

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6.

Identification of Hardware Material, Particularly Nuts and Bolts A.

A permanent type of material code designation has been adopted for use in these engines. Correct engine reassembly procedures require that particular attention be paid to the material requirements for nuts and bolts used in the hot section of the engine. In these areas, where parts must be of material which is resistant to high operating temperatures, special heat resistant alloys are employed. It is imperative, that at reassembly of the engine or its components, the properly coded part be reassembled in its original location, if serviceable.

B.

The code system employs the use of a letter ‘‘C’’ for corrosion resistant steel for normal application and ‘‘H’’ for heat resistant alloys in hot section application. The stamped or embossed letter will be followed by a number of one or more digits, such as C1, C8, H3, and H12. Bolt code identification will usually appear on the top of the head and nut identification on one side of the hex (Ref. Fig. 213). When the application is an AN or MS six digit part number, the code identification ‘‘C’’ or ‘‘H’’ will be preceded by the letter ‘‘E’’ as in EC3 or EH10. NOTE: All AN or MS six digit part numbers, when manufactured of material in the common temperature range (such as cadmium plated, low alloy steel parts), are also coded ‘‘E’’ to indicate, in part, close material quality control.

CAUTION:

NEVER ASSEMBLE A MATERIAL CODED PART WITH A ‘‘C’’ IDENTIFICATION IN A LOCATION WHICH REQUIRES AN ‘‘H’’ CODED PART AND VICE-VERSA. NEVER USE CADMIUM PLATED NUTS, BOLTS OR ANY OTHER CADMIUM PLATED PART IN THE HOT SECTION OF THE ENGINE.

C.

The adoption of this program will make it possible for service activities to avoid the assembly of parts, with similar physical appearance, in locations which require high heat resistant parts. In this regard, it is required, at time of disassembly (removal), that all similarly coded parts be segregated so that two, or more, physically similar parts with different code numbers will not be scrambled; and so that, at subsequent reassembly (installation), the properly coded parts are replaced in their proper locations.

D.

Parts from several engines should not be scrambled at disassembly (removal) and cleaning, because, at the time of engine manufacture, production requirements may necessitate one or more material substitutions in a block of engines. Subsequent engine reassembly with indiscriminate scrambling of hardware, may result in unnecessary confusion in sorting these parts for proper reassembly.

CAUTION:

E.

IT IS IMPORTANT THAT ‘‘J’’ THREADED HARDWARE BE CAREFULLY SEGREGATED AND MARKED AT DISASSEMBLY (REMOVAL) TO PREVENT MIXING WITH NON ‘‘J’’ THREADED PARTS.

Unified Controlled Radius Root ‘‘J’’ Threaded Bolts feature full root radius for external threads with increased minor internal threaded diameter. ‘‘J’’ threads ensure greater fatigue life, improved stress relaxation characteristics and show improvement in tensile strength over previous designs. This thread form is used extensively throughout engines. Engine bolts having ‘‘J’’ threads appear just like items threaded with conventional threads.

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7.

Stainless Steel Bolts with Reduced Pitch Diameters At engine manufacture, it is the practice to provide bolts with reduced pitch diameter for use in the hot sections of engines. This will minimize the possibility of bolt and nut seizure and is standard practice for locations where the parts are subjected to elevated temperatures (Ref. Fig. 214).

8.

Debris Analysis and Material Specifications A.

B.

General (1)

Debris analysis monitors wear of oil-wetted engine parts. This procedure improves aircraft serviceability and dispatch reliability and reduces engine repair costs. This is achieved by identifying potential engine problems at the earliest possible stage, thus minimizing the possibility of in-flight shutdowns, away-from-base engine changes and secondary damage.

(2)

Rapid wear or surface fatigue (e.g. on gear teeth contact surfaces, bearing raceways, rolling elements, housing bearing bores, etc.) or interference between rotating and fixed components (e.g. oil pump pinions, associated housings and labyrinth seals, etc.) produces debris. Magnetic debris over 100 microns in diameter is usually captured by the chip detectors. Magnetic and non-magnetic debris over 10 microns in diameter is usually captured by the oil system filters. For engine equipped with such devices, it is also possible to find debris on the magnetic pulse pick-up sensors.

(3)

Analysis (form, appearance, dimensions, quantity and material) of the debris generated by oil wetted parts is necessary to provide the information needed to facilitate locating the source of the debris and determining any preventive maintenance action required.

Filter Patch Check Debris Inspection/Analysis (1)

The analysis should be done by a qualified laboratory (Ref. Para . F.). Operators may send the contaminated filter or the debris to the laboratory for the filter patch check and/or analysis and provide the following information: (a) Engine model and serial number. (b) Engine time since new (TSN) or time since overhaul or refurbishment (TSO or TSR). (c) Time since last filter inspection. (d) Filter location. (e) Reason for filter removal, inspection and debris analysis.

(2)

Reports supplied by the laboratory to the operator containing the results of the analysis must include: (a) Information provided by the operator with the filter or debris.

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120 ° 0.109 0.079

REDUCED PITCH DIAMETER BOLT

STANDARD BOLT

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(b) Total weight of debris. (c) Material and amount of non-magnetic debris when classified as major (Ref. NOTE). (d) Material, appearance, shape and amount of non-magnetic metallic debris. (e) Material, appearance, shape and amount of metallic debris. NOTE: The amount of individual constituents in the debris should be classified as: v Major - when the weight of the constituent is more than 50% of the total debris weight. v Minor - when the weight of the constituent is less than 50% of the total debris weight. v Traces - when the weight of the constituent is less than 5% of the total debris weight. (3) C.

If bearing material (Ref. Table 205) is found, the operator must be advised as soon as possible by telephone and provided with a detailed written report.

Inspection/Analysis of Debris Collected on Chip Detector or Magnetic Pulse Pick-up Sensors (1)

The analysis should be done by a qualified laboratory (Ref. Para . F.).

(2)

The operator must provide the laboratory with the following information: (a) Engine model and serial number. (b) Engine time since new (TSN) or time since overhaul or refurbishment (TSO or TSR). (c) Locations where debris were found. (d) Reason for inspection (scheduled or unscheduled).

(3)

Reports supplied by the laboratory to the operator containing the results of the analysis must include: (a) Information provided by the operator when submitting the material for analysis. (b) Type(s) of material found. (c) Shape and appearance of the material. (d) If bearing material (Ref. Table 205) is found, the operator must be advised as soon as possible by telephone and provided with a detailed written report.

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D.

Identification of Metal Particles (1)

General (a) When unidentified particles of metal are found, they may be either steel, tin, aluminum, magnesium, silver, bronze, titanium, or cadmium. In some cases the type of metal may be determined by the color and hardness of the pieces. However, when the particles cannot be positively identified by visual inspection and knowledge of the exact character of the metal is desired as an aid to troubleshooting, a few simple tests will determine the kind of metal present. WARNING:

USE EXTREME CARE IN HANDLING ACIDS.

(b) The following equipment and chemicals are required to make these tests: a source of open flame permanent magnet two ounces of solution containing ten percent ammonium nitrate(PWC05-011) and water electrical soldering iron two ounces each of 50 percent by volume hydrochloric acid (PWC05-196) or (PWC05-196A) and concentrated nitric acid (PWC05-195) sodium hydroxide pellets (PWC05-056) watch glass white porcelain spot plate ammonium biflouride crystals (PWC05-009) 5 to 10 percent hydrofluoric acid (PWC05-004) or concentrated sulfuric acid (PWC05-074) 3 to 10 percent hydrogen peroxide (PWC05-038) concentrated phosphoric acid (PWC05-006) (2)

Procedure NOTE: The following test procedure is recommended for determining the character of unknown metal particles. For best results, follow the steps as outlined: (a) Steel - the particles of many steels can be isolated by means of the permanent magnet. Magnetic steel or iron is attracted by the magnet. (b) Titanium:

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WARNING:

THE FOLLOWING CHEMICALS ARE HAZARDOUS AND REQUIRE SPECIAL HANDLING. IT IS RECOMMENDED THE FOLLOWING TESTS BE DONE BY QUALIFIED LABORATORY PERSONNEL.

1 Place a piece, or pieces of the metal to be identified, on a white porcelain spot plate. A piece of titanium or titanium-bearing metal should be placed on another spot plate to observe and verify the results obtained. 2 Add several crystals of ammonium bifluoride (PWC05-009) and 5 to 10 drops of water to the metal particles. (Two or three drops of a 5 to 10 percent hydrofluoric acid solution PWC05-004 can be used instead). NOTE: Solid ammonium bifluoride is crystalline and can be conveniently stored in a dry area and used as required. 3 Let stand 20 to 30 minutes, or until the solution becomes slightly discolored. 4 Add two or three drops of 1:1 sulfuric acid (one part demineralized water PWC05-073 to one part concentrated acid PWC05-074). 5 Let stand 20 to 30 minutes, or until solution becomes more discolored. 6 Add three to four drops of 3 to 10 percent hydrogen peroxide (PWC05-038). Solution must not be too old. 7 If titanium is present, a yellowish color will develop. This yellow color will become progressively darker with time, if allowed to set. 8 Add two to three drops of concentrated phosphoric acid (PWC05-006), and stir to discharge any yellow color due to the possible presence of iron. 9 Any light yellow to orange coloration indicates the presence of titanium. WARNING: (c)

NEVER TRY TO BURN MORE THAN A FEW PARTICLES OF METAL SUSPECTED TO BE MAGNESIUM. DUST IS EXPLOSIVE.

Magnesium - a simple test for these particles is burning. Magnesium will burn with a bright white flash.

(d) Cadmium - place the remaining particles in the solution of water and ammonium nitrate(PWC05-011). If all or any of the particles dissolve in this solution, they are cadmium. After this test, rinse and dry any remaining particles. (e) Tin - the tin particles can be distinguished by their low melting point. With a clean soldering iron, heated to 260°C (500°F) and tinned with 50-50 solder (50 percent tin - 50 percent lead), a tin particle dropped on the iron will melt and fuse with the solder. (f)

Aluminum - when a particle of aluminum is placed in hydrochloric acid (PWC05-196), 50 percent by volume, it will fizz with rapid emission of gas bubbles and gradually disintegrate and form a black residue (aluminum chloride). Silver and bronze do not noticeably react with hydrochloric acid.

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(g) Aluminum Paint - use this procedure to determine whether or not the material is aluminum silicone paint, aluminum chips, or silver particles. 1 Make a solution by adding one pellet of sodium hydroxide (PWC05-056) to three ccs of water. 2 Place several drops of this solution on a watch glass and drop in the suspected particles. 3 If the particles are aluminum silicone paint, there will be a mild reaction in the form of gas bubbles and some visible gas as the particles change to sodium aluminate. 4 If the particles are aluminum chips, the reaction will be much more active with many more gas bubbles forming and more visible gas. 5 If the particles are silver, there will be no reaction. (h) Silver - when a silver particle is placed in nitric acid, it reacts rather slowly, producing a whitish fog in the acid. (i) E.

Bronze - when a bronze (or copper) particle is placed in nitric acid, a bright green cloud is produced.

Material Specifications (1)

To facilitate the identification of components which are the source of debris found in the oil system, the material specifications are listed in Table 205 . The common contaminants found in the oil system are listed in Tables 206 and 207. TABLE 205, Material Specification (Engine Components)

Specification

Material

AMS 2412

Silver Plating

Nomenclature

Engine Location

Cage, No. 1 Brg

GG

Cage, No. 2 Brg

GG

Cage, No. 3 Brg

PT

Cage, No. 4 Brig

PT

Cage, No. 5 Brg

RGB

Cage, No. 6 Brg

RGB

Cage, No. 7 Brg

RGB

Cage, FCU Drive Brg

AGB

Cage, Start-Gen Drive Brg

AGB RGB

AMS 4082, 4150

Alum (AA6061)

Sleeve, First-stage, Carrier

AMS 4117, 4127, 4150

Alum (AA6061)

Stator, No. 1 Brg Air Seal

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TABLE 205, Material Specification (Engine Components) (Cont’d) Specification

Material

AMS 4214

Alum (Alloy 355)

Nomenclature

Engine Location

Breather, Impeller

AGB

Body, Main Scavenge Oil Pump

AGB

Housing, Main Scavenge Oil Pump

AGB

Cover, Main Scavenge Oil Pump

AGB

Housing , External Scavenge Oil Pump

AGB

Spacer, External Scavenge Oil Pump

AGB

Cover Housing, Scavenge Oil Pump

AGB

AMS 4260

Alum. (Alloy 356)

Cover, Main Oil Pressure Pump

AGB

AMS 4275

Alum. (Alloy 750)

Brgs, Main Oil Pump Gear

AGB

Sleeve, Accessory Drive Gears

RGB

Housing, Front

RGB

Housing, Rear

RGB

Housing, Main Oil Pressure Pump

RGB

Diaphragm

AGB

Housing

AGB

AMS 4439

Magnesium (ZE41E)

AMS 4212

Alum (Alloy 355)

Compressor Inlet Case

GG

AMS 4616

Bronze

Cage, FCU Drive Brgs

AGB

Cage, Start- Gen Drive Brg

AGB

Cage, Vacuum Pump Drive Brg

AGB

Cage, External Scavenge Oil Pump Drive Brg

AGB

Coupling Shaft Brg

RGB RGB

AMS 5315

Steel

Sleeve, Propeller, Oil Transfer

AMS 5613

SST (X51410)

No. 1 Brg Front Air Seal

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TABLE 205, Material Specification (Engine Components) (Cont’d) Specification

Material

Nomenclature

Engine Location

No. 2 Brg Front Stator, Air Stator

GG

No. 2 Brg Front Rotor Air Seal

GG

No. 2 Brg Rear Stator Air Seal

GG

No. 2 Brg Rear Rotor Air Seal

GG

No. 3 Brg Stator Air Seal ,

PT

AMS 5645, 5646

SST (30321)

Sleeve, AGB Coupling Shaft Brg

AMS 5671

SST (Inconel X750)

Seal, No. 3 Brg, Front Labyrinth, Air

PT

AMS 5732

SST (A286)

Housing, No. 1 Brg, Outer

GG

AMS 6260

Steel (9310)

Gear, Main Oil Scavenge Pump

AGB

AMS 6265

Steel (9310)

Gear, Accessory Drive, Front

RGB

Gear, Second-stage Planet

RGB

Carrier, Second-stage Planet Gear

RGB

Shaft, Second-stage Planet Gear

RGB

Gear, Ng Tacho Drive

RGB

Gear, Propeller and O/S Governor Drive

RGB

Coupling, Propeller Governor Drive

RGB

Gear, Second-stage, Ring

RGB

Gear, First-stage, Ring

RGB

Gear, Second-stage, Sun

RGB

Coupling, Second-stage Sun Gear

RGB

Adapter, Second-stage Sun Gear

RGB

Carrier, First-stage Planet Gear

RGB

Gear, First-stage, Planet

RGB

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TABLE 205, Material Specification (Engine Components) (Cont’d) Specification

Material

Nomenclature

Engine Location

Gear, First-stage, Sun

AMS 6322

AMS 6414

AMS 6415

Steel (8740) Steel (4340)

Steel (4340)

RGB

Coupling, AGB Drive

GG

Coupling, First-stage Sun Gear

PT

Shaft, AGB Coupling

AGB

Gear, FCU, Drive

AGB

Gear, Start- Gen Drive

AGB

Gear, Vacuum Pump Drive

AGB

Gear, Hydraulic Pump Drive

AGB

Gear, Main Oil Pump Drive

AGB

Gear, External Scavenge Pump Drive

AGB

Gear, Oil Pressure Pump

AGB

Gear, External Oil Scavenge Pump

AGB

Gear, Scavenge Oil Pump

AGB

Shaft, Vacuum Pump Drive

AGB

Shaft, External Scavenge Pump Drive,

AGB

Coupling, Oil Pump Drive

AGB

Sleeve, Second-stage Sun Gear

RGB

Shaft, First-stage Planet Gear

RGB

Cage, No. 7 Roller Brg

RGB

Torque Piston

RGB

Inner Housing No. 1 Brg

GG

Cage, No. 1 Brg

GG

Cage, No. 2 Brg

GG

Cage, No. 3 Brg

PT

Cage, No. 4 Brg

PT

Coupling, Main Oil Pump Drive Gear

AGB

Shaft, Propeller

RGB

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TABLE 205, Material Specification (Engine Components) (Cont’d) Specification

AMS 6440/ 6444

AMS 6490

AMS 6491

Material

Steel (52100)

Steel (M50) Steel (M50)

Nomenclature

Engine Location

Cage, No. 6 Brg

RGB

Cage, No. 5 Brg

RGB

Locating Pin, Second-stage Planet Gear Carrier,

RGB

Torque Cylinder,

RGB

Shaft, Impeller

GG

Roller, AGB Coupling Shaft Brg

AGB

Roller, Start-Gen Drive Brg

AGB

Roller, Hydraulic Pump Drive Brg

AGB

Roller, Vacuum Pump Drive Brg

AGB

Roller, External Scavenge Pump Drive Brg

AGB

No. 7 Brg, Roller and Rings

RGB

No. 6 Brg, Ball and Rings

RGB

No. 5 Brg, Roller and Rings

RGB

First-stage Planet Gearshaft

RGB

Rings, AGB Coupling Shaft Brg

AGB

Rings, FCU Drive Brg

AGB

Rings, Start-Gen Drive Brg

AGB

Rings, Hydraulic Pump Drive Brg

AGB

Rings, Vacuum Pump Drive Brg

AGB

Rings, External Scavenge Pump Drive Brg

AGB

No. 2 Brg, Rings and Rollers

GG

No. 3 Brg Rings and Rollers

PT

No. 1 Brg Rings and Balls,

GG

PT Shaft

PT

PT Shaft Coupling

PT

No. 4 Brg Rings and Balls,

PT

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TABLE 205, Material Specification (Engine Components) (Cont’d) Specification

Material

AMS6265/ 6444

Steel

AMS 4928

Titanium Alloy

Molybdenum

Nomenclature

Engine Location

Shaft, Second-stage Planet Gear

RGB

Shaft, First-stage Planet Gear

RGB

Compressor, First-stage

GG

Stubshaft, First-stage Compressor

GG

Coating, No. 2 Brg, Labyrinth, Seals, Air

GG

TABLE 206, Common Contaminants - Non-organic Material Contaminant Detected

Main Elements

Cause of Contaminants

Alumina

Al203

Manufacturing

Black Magnetic

Fe304

Anaerobic decomposition of shaft material, can look like carbon is a corrosive product.

Calcium Oxide

CaO

Environment

Rust, Non-magnetic

Fe2O3

Rust

Sand

SiO2

Manufacturing/Environment

Silicon Carbide (Black, Shiny, Angular)

SiC

Manufacturing/Blasting

Zirconia

ZrSiO4

Manufacturing

Mo52

Common as a trace, could combine with Fe (Iron) to indicate bearing alloy. Usually found in new or overhauled engines.

Calcium Chloride (Salt)

CaCl2

Environment

Sodium Chloride (Salt)

NaCl

Environment

Calcium Sulphate (Salt)

CaSO4

Environment

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TABLE 207, Common Contaminants - Organic Material Contaminant Detected

Source

Black Fluorocarbon Rubber, Red Silicon Rubber, Blue Fluorosilicon Rubber

Preformed Packings, Seal Gaskets

Chloroprene Nitrile Rubber

Gaskets

Carbon

Decomposed Oil, Carbon Seals

Fibers Plastics Paint Flakes F.

Laboratories (1)

9.

Chip and flake analysis must be done by approved laboratories; refer to Service Information Letter No. GEN-123 for the list of approved oil laboratories.

Marking of Parts A.

B.

General (1)

Marking of engine parts, assemblies, or weldments shall be applied so as to ensure maximum legibility and durability of mark but in a manner that will not affect function or serviceability of part. Only applicable Pratt & Whitney Canada marking methods shall be used.

(2)

Except where otherwise specified, reidentification of parts shall be accomplished adjacent to, or in a location similar to that of, original marking.

(3)

All marking characters, unless otherwise specified, shall be 0.060 to 0.160 inch high. In special cases, when marking area is governed by size or configuration of part, characters not less than 0.016 inch nor more than 0.200 inch in height are permitted.

(4)

Electric-arc scribing, particularly hand arc scribing, whereby characters are produced by the action of an electric arc between the surface and an the electrode (scriber), has been found unsuitable for jet engine parts and must not be used.

(5)

Acid etching, whereby characters are formed by action of an acid on the surface of the part, is not recommended because of its possible corrosive effect.

(6)

Do not use Soapstone to mark the engine parts.

Permanent Marking (1)

General (a) Marking should be done as close to original marking as possible. Permanent methods of marking are those in which marking is legible during entire service life of part.

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(b) Permanent markings shall not extend onto any radius, chamfer, sharp edge, or fillet adjoining designated marking surface. (2)

Approved Marking Methods CAUTION:

DO NOT USE ELECTROLYTIC ETCH METHOD OF MARKING ON ANODIZED ALUMINUM SURFACES.

(a) Electrolytic Etch - Characters are produced by electrolysis confined to area of characters by a stencil. This technique is sometimes used as a temporary method. Do not confuse it with electric-arc scribing. (b) Vibration Peening - Characters are produced by a vibrating, radius-tipped, conical tool. Manual - tool is hand-guided and has a single tip. Mechanical - tool is mechanically guided and has a single tip, or has multiple tips producing one or more complete characters simultaneously. This method is not usually permitted if hardness of part at time of marking is higher than Rockwell C45 or equivalent. NOTE: Vibration peening marking method can be substituted for marking parts originally marked by diamond drag or roll marking. C.

Temporary Marking (1)

General (a) Temporary methods of marking are those in which the marking will identify the parts during ordinary handling, and storage, and final assembly. CAUTION:

LEAD AND/OR METALLIC PENCILS, OR ANY TEMPORARY MARKING METHOD LEAVING A DETRIMENTAL DEPOSIT OF CARBON, ZINC, COPPER, LEAD, OR SIMILAR RESIDUE WHICH MAY CAUSE A REDUCTION IN FATIGUE STRENGTH AS A RESULT OF CARBONIZATION OR INTERGRANULAR ATTACK WHEN THE PART IS SUBJECTED TO INTENSE HEAT, SHALL NOT BE USED. THE MARK MUST BE THOROUGHLY REMOVED BY A PROCEDURE DICTATED BY THE MARKING METHOD AND THE PART MATERIAL.

(b) When using a marking pencil, marks shall not be applied to carbon seal plate surfaces or to mating surfaces of finished machined parts. Heavy deposits of marking material could adversely affect clearance and runout. (2)

Approved Marking Methods CAUTION:

DO NOT USE ELECTROLYTIC ETCH METHOD OF MARKING ON ANODIZED ALUMINUM SURFACES.

(a) Electrolytic Etch - Characters are produced by electrolysis confined to area of the characters by a stencil. This is primarily a permanent marking method. However, where specified, it may also be used for temporary marking.

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(b) Ink Marking 1 An ink that does not damage the surface is used to produce the characters. Inks used in marking may have a light etching action, but does not damage the surface. NOTE: Ordinarily, ink stamping and electrolytic etching, when used as a temporary marking method, may be applied to any surface which, after assembly, does not move relative to a contacting surface. (3)

Marking Materials, Hot and Cold Section Engine Parts (a) Felt Wick Pen (PWC05-048A) and Instant Dry Ink (PWC05-046). (b) Marks-A-Lot Marker(PWC05-048B) (c) Brushpen No. 57 (PWC05-048) and Fast Drying Ink (PWC05-046A), black, red and purple. (d) Micro Supreme Dye, No. 142 (Purple) (PWC05-002). (e) Berol Verithin Pencil, Red No. 750 (PWC05-018F). May be used on parts which are not directly exposed to the gas path. This type of mark is easily obliterated and, therefore, less durable. (f)

(4)

Design Spectracolor Pencil, Silver No. 1428 (PWC05-018), or Verithin Pencil, Silver No. 753 (PWC05-018A).

Marking Materials, Cold Section Engine Parts Only Dykem Ink (PWC05-046C)KX425 (Black) or (PWC05-332)KXX122 (White). Carters Ink (PWC05-027) KX451 (Black).

(5)

10.

Marking Materials, Hot Section Engine Parts Only. Use layout dye (PWC05-041) (lightly applied) to mark parts which are directly exposed to engine gas path such as turbine blades and disks, turbine vanes, and combustion chamber liner.

Lubrication of Preformed Packings A.

General

CAUTION:

(1)

APPLICATION OF LUBRICANT PLUS PROPER ASSEMBLY, WILL PREVENT DAMAGE TO PREFORMED PACKINGS. DAMAGED PREFORMED PACKINGS CAN CAUSE ENGINE MALFUNCTION.

Prior to installation, it is recommended that all preformed packings be coated with lubricant to the following specifications: (a) Preformed packings used in the fuel and/or oil system, use engine oil (PWC03-001).

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11.

Touch-up Solution WARNING:

A.

REFER TO THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS FOR INFORMATION SUCH AS HAZARDOUS INGREDIENTS, PHYSICAL/CHEMICAL CHARACTERISTICS, FIRE, EXPLOSION, REACTIVITY, HEALTH HAZARD DATA, PRECAUTIONS FOR SAFE HANDLING, USE AND CONTROL MEASURES. SOME OF THESE MATERIALS CAN BE DANGEROUS. YOU CAN GET THE DATA SHEETS FROM THE MANUFACTURERS OR THE SUPPLIERS OF THESE MATERIALS.

Chrome Pickle Solution (PWC05-161) (Magnesium RGB and AGB Housings) (Ref. Table 208) (1)

Fill a suitable container with tap water to no more than 1⁄2 of the volume of the solution required.

(2)

Slowly and carefully add the necessary quantity of sodium dichromate (PWC05-055). Mix to dissolve the sodium dichromate.

(3)

Slowly and carefully add the necessary quantity of nitric acid (PWC05-195). Mix the solution.

(4)

Fill the remainder of the container with tap water to the specified volume required. TABLE 208, Chrome Pickle Solution

MATERIAL

PROPORTION

PROPORTIONAL LIMITS

Sodium Dichromate (PWC05-055)

1.5 lbs.

1.0 to 1.5 lbs.

Nitric Acid (PWC05-195)

1.5 pints

1.0 to 1.5 pints

NOTE: The figures that are given are per gallon of solution required. B.

Chromate Repair of Magnesium Casings - Method A

WARNING:

(1)

REFER TO THE MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION. IT GIVES INFORMATION ABOUT HAZARDOUS INGREDIENTS, PHYSICAL/CHEMICAL PROPERTIES, FIRE, EXPLOSION, REACTIVITY, HEALTH HAZARD DATA, PRECAUTIONS FOR SAFE HANDLING, USE AND CONTROL MEASURES.

Prepare chromate conversion solution (PWC11-019) (Ref. Table 209): (a) Fill an applicable container to 3/4 level with tap water. (b) Slowly and carefully add necessary quantity of chromate conversion salts (PWC05-198). (c) Slowly and carefully add necessary quantity of hydrochloric acid (PWC05-196). Mix the solution.

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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(d) Slowly and carefully add necessary quantity of wetting agent (PWC05-162). Mix the solution. (e) Fill the container to operating level. Mix the solution. (f)

Add hydrochloric acid (PWC05-196) or a combination of sodium hydroxide solution (PWC05-057) and 16 oz of distilled water (PWC05-073) to adjust pH as necessary. Mix the solution. TABLE 209, Chromate Conversion Solution (PWC11-019) Material

Make-up

Operating Limits

Chromate conversion salts (PWC05-198)

5 oz. wt/gal

4.5 - 5.5 oz. wt/gal

Hydrochloric acid (PWC05-196)

2 fl oz/gal

1 - 3 fl oz/gal

Wetting agent (PWC05-162)

1 ml/gal

Sodium hydroxide solution (PWC05-196) and 16 oz distilled water (PWC05-073)

Add as necessary to increase pH to operating range.

pH = 0.6 - 1.1

NOTE: To maintain wetting agent (PWC05-162), add 0.5 ml for each 5 oz of chromate conversion salts (PWC05-198) added. C.

Chromate Repair of Magnesium Casings - Method B (1)

Put an applicable cover or debris collector to the necessary area to prevent the entry of debris into the compressor or into other openings. Attach a lanyard to the debris collector or cover so it will not fall into the compressor cavity.

(2)

Clean the surface of the magnesium casing with one of the methods that follow: v A swab soaked in isopropyl alcohol (PWC11-014B) v A coated abrasive crocus cloth (PWC05-061) v An isopropyl alcohol hand-wipe or other applicable hand-wipe chemical

(3)

Remove the corrosion with one of the materials that follow: v A small non-metallic wire brush v A stainless steel or aluminum brush v A coated abrasive crocus cloth (PWC05-061) v An abrasive cloth with aluminum oxide or glass grit. Do not use silicon carbide abrasive. v For better results, you can use a swab soaked in a chromic acid solution (PWC05-197) that has a temperature of 122.5 ± 40.5 °C (252.5 ± 72.5 °F).

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(4)

Flush with clean water at room temperature.

(5)

Flush with clean water at a temperature of 60 °C (140 °F) minimum.

(6)

Dry with clean low pressure compressed air at 200 kPa (29 psig).

(7)

Apply chromate conversion solution (PWC11-019) or chrome pickle solution (PWC05-161) at a temperature of 23 ± 6 °C (74 ± 11 °F) for 30 to 45 seconds to the prepared surface with a swab or brush. Apply again frequently to make sure that the surface is wet with solution during the treatment.

(8)

You can use the materials that follow as an alternative to chromate conversion solution (PWC11-019) or chrome pickle solution (PWC05-161): (a) Touch-up conversion coating (PWC05-418) - pen applicator for non-hexavalent chromium based solution. (b) Touch-up conversion coating applicator (Alodine) (Magnesium Treatment Kit) (PWC05-419).

(9) (10) D.

Swab area with clean water until swabs are no longer stained yellow. Dry the part in an oven or locally with a heat gun for 20 to 30 minutes at 131 ± 46 °C (267.5 ± 82.5 °F).

Repair of Protective Coating on Painted Surfaces NOTE: The instructions that follow are not applicable for flanges, engine mount pads or accessories mount pads. (1)

Touch-up exposed metal (Ref. Para. 11.A., B. and C.).

(2)

Mask the area where painting is not necessary.

(3)

Apply two layers of epoxy primer (PWC13-001). Wait one hour before you apply second layer. Let the part dry at room temperature for 8 hours minimum after the second layer.

(4)

Apply three layers of aluminized epoxy enamel (PWC05-037). Wait 15 to 30 minutes before you apply next layer. Let the last coat dry at room temperature for 24 hours minimum.

(5)

Remove the masking. Make sure that the exposed area is fully covered.

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STANDARD PRACTICES - REMOVAL/INSTALLATION 1.

General A.

To ensure proper reinstallation, tag and mark all parts, clips, and brackets as to their location.

B.

During removal of tubes or engine parts look for indications of scoring, burning or other undesirable conditions. To facilitate reinstallation, observe the location of each part during removal. Tag unserviceable parts and units for investigation and possible repair.

C.

Extreme care shall be taken to prevent dust, dirt, lockwire, nuts, washers or other foreign matter from entering the engine. It cannot be overemphasized that this precaution applies whenever work is done on the engine either on the wing or off the wing. Suitable plugs, caps, and other covering shall be used to protect all openings as they are exposed.

CAUTION:

DUST CAPS USED TO PROTECT OPEN TUBES AGAINST CONTAMINATION SHALL ALWAYS BE INSTALLED OVER THE TUBE ENDS AND NOT IN THE TUBE ENDS. FLOW THROUGH THE LINES MAY BE BLOCKED OFF IF LINES ARE INADVERTENTLY INSTALLED WITH DUST CAPS IN THE TUBE ENDS.

D.

If at any time items are dropped into the engine, the assembly process must stop until the dropped articles are located, even though this may require a considerable amount of time and labor. Before assembling or installing any part, be sure it is thoroughly clean.

E.

Lockwire, lockwashers, tablocks, tabwashers, or cotterpins must never be reused. All lockwire and cotterpins must fit snugly in holes drilled in studs and bolts for locking purposes. Install a cotterpin so that the head fits into the castellation of the nut, and unless otherwise specified, bend one end of the pin back over the stud or bolt and the other end down flat against the nut. Only lockwire and cotterpins made of corrosion resistant steel shall be used. Bushing plugs shall be lockwired to the assembly boss or case. Do not lockwire the plug to the bushing.

F.

Replace all gaskets, packings, and rubber parts at reassembly. Make sure that new nonmetallic parts to be installed (such as an oil seal) show no sign of having deteriorated in storage.

CAUTION:

TOOL SURFACES WHICH MAY CONTACT ENGINE CRITICAL AREAS MUST BE ADEQUATELY COVERED WITH A PROTECTIVE MATERIAL.

G. To protect critical areas of engine parts (such as compressor and turbine disks) against scratches and nicks, tool surfaces contacting these areas must be covered with protective material. H.

During replacement of components, note condition of any removed preformed packings. Pieces accidentally torn or cut from packings must be retrieved, regardless of size, even if this entails a systematic disassembly and cleaning of the system. Ensure that new packings are free of cuts, flashings and deformities which may be sheared off at installation.

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2.

I.

When installing engine parts that require the use of a hammer to facilitate assembly or installation, use only a plastic or rawhide hammer.

J.

Whenever adhesive tape has been applied to any part, the tape must be removed and the part thoroughly cleaned of all tape residue with petroleum solvent prior to being subjected to high temperature during engine run. Test results indicate that all tapes are capable of causing surface attack and/or reduction in tensile ductility as temperature increases. Do not leave tape or tape residue on engine parts.

K.

If any part has been coated with corrosion preventive compounds, all traces of this compound and accumulated foreign matter must be removed.

Consumable Materials The consumable materials listed below are used in the following procedures.

3.

Item No.

Name

PWC03-001 PWC06-002

Oil, Engine Lubricating Petrolatum, White

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation CAUTION:

A.

B.

DO NOT BEND, TWIST OR FORCE HYDRAULIC AND PNEUMATIC TUBES, WHETHER RIGID OR FLEXIBLE, TO ACHIEVE ALIGNMENT WITH MATING FITTING. ADJUST FITTING TO ALIGN WITH TUBE. CLAMP AND SECURE TUBE ONLY WHEN IT IS INSTALLED IN POSITION WITH NO NOTICEABLE TENSION OR LOAD.

Removal of Straight Nipples, Straight Adapters, Bulkhead Couplings and Tube Connector Nipples (1)

Remove fittings from engine lines or accessory units.

(2)

Remove preformed packings from fittings and discard.

Removal of Tube-to-Boss Elbows, Elbow Adapters and Elbow Assemblies (1)

Remove fittings from engine lines or accessory units. NOTE: Before removal, mark angular position of fitting on engine or unit.

(2)

Remove preformed packings, packing retainers (back-up rings) and discard. Discard jam nuts from fittings.

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C.

Installation of Straight Nipples, Straight Adapters, Bulkhead Couplings and Tube Connector Nipples (1)

Lubricate new preformed packing with light film of engine oil (PWC03-001) or fluid to be used in line.

(2)

Install preformed packing on fitting and screw fitting in boss or flange, as applicable.

CAUTION: (3) (4)

EXCESSIVE TIGHTENING WILL RESULT IN DAMAGE TO THREADS OF MATING PARTS.

Tighten fitting in boss and torque to value detailed in relevant assembly instruction. Install jam nut on flange mounted fittings and torque jam nut to recommended value (Ref. Table 401). TABLE 401, Torque Values for Jam Nuts

D.

THREAD SIZE

TORQUE (lb.in.)

0.250 -28

14 to 16

0.3125-24

22 to 24

0.375 -24

28 to 32

0.4375-20

38 to 42

0.500 -20

58 to 62

0.5625-18

70 to 80

0.625 -18

95 to 105

0.750 -16

145 to 155

0.8125-16

165 to 185

Installation of Tube-to-Boss Elbows, Elbow Adapters and Elbow Assemblies (Ref. Fig. 401) (1)

Lubricate new preformed packings, packing retainer (back-up ring) and thread of elbow fitting with light film of petrolatum (PWC06-002) or fluid to be used in the line.

(2)

Assemble jam nut, new packing retainer and preformed packing on elbow fitting, pressing packing retainer into counterbore of jam nut.

(3)

Turn jam nut down elbow fitting until preformed packing is seated in non-threaded annulus of fitting.

(4)

Turn jam nut outward until preformed packing is pushed firmly against first lower thread of fitting.

(5)

Install elbow fitting into boss on unit, allowing jam nut to turn with fitting until preformed packing contacts boss mating face. This point will be recognized by increase in torque.

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1 1

2 2 3 3 4

4

1

2 3 4

C3146A Installation of Typical Elbow Fitting Figure 401

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Key to Figure 401 1. 2. 3. 4. (6)

Elbow Fitting Jam Nut Packing Retainer Preformed Packing

With fitting in this position, hold jam nut stationary and turn elbow fitting into boss a further 1 1/2 turns. NOTE: From this position the elbow fitting may be further turned inward to a maximum of one turn to facilitate alignment of fitting (Ref. Para. 1.B). Should the fitting tighten in the jam nut before completion of initial 1 1/2 turns or during final alignment, the jam nut may be allowed to turn with the fitting for the remainder of the distance.

(7)

With elbow fitting in correct alignment position, tighten jam nut and torque to recommended torque (Ref. Table 401). NOTE: Metal-to-metal contact between jam nut and boss must be obtained without exceeding recommended torque and there must be no extrusion of preformed packing or packing retainer.

E.

Installation/Removal of Hydraulic, Oil and Pneumatic Lines

CAUTION:

DO NOT USE FORCE TO POSITION LINE ON TO COUPLING ADAPTERS.

NOTE: Refer to specific chapter for assembly instructions; Chapter 73 for fuel and pneumatic lines, Chapter 79 for oil lines. (1)

When installing hydraulic, oil or pneumatic lines, whether dolid tubes or flexible hoses, ensure lines engage on to respective coupling adapters without tension or load.

(2)

Alignment must be obtained by adjusting the position of the adapters. Refer to paragraphs C and D preceeding, for instructions pertaining to the installation of adapters.

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STANDARD PRACTICES - INSPECTION 1.

General A close and complete inspection is important to prolong engine life and give maximum performance. Check for loose or missing parts and inspect any engine part or component that has been worn or damaged. Damage to engine parts may result from improper clearance, lack of lubrication, undesired movement of parts which are bolted or pressed together, overloaded, uneven load distribution, heat, shock, extension of minor damage such as scratches, tool marks, grinding cracks, nicks, etc. Damage to engine parts may also result from presence of foreign matter such as grit, chips, moisture, chemicals, etc., or from incorrect techniques during removal and installation. All inspection procedures should be done in a well lighted, clean and dust-free area. Benches should be clean to keep previously cleaned parts free of dirt and dust. All parts shall be suitably tagged to indicate necessary repair or replacement. Although most parts will require only a visual inspection, a certain number will require use of gages and other measuring equipment. Some damage may only be detected by magnetic particle or fluorescent penetrant inspection methods. Methods of inspection for specific parts and components are detailed in relevant sections of this manual.

2.

Inspection A.

General (1)

Examine parts for alignment, distortion, foreign matter, looseness, out-of-roundness, sharp edges, scratches, taper, warping and wear. Additionally, check the following: (a) Holes in cases, manifolds, pipes and tubes for obstructions. (b) Gear teeth and splines for contact patterns. (c) Magnesium parts for corrosion. (d) Mounting pads, parting and seating surfaces, for smoothness and flatness. Use pencil carbon paper whenever a smear-type indication of surface smoothness is required. (e) Plugs for tightness. (f)

Studs, dowels, and similar protruding parts for alignment and projection length.

(g) Protective surface coatings for completeness. (h) Threads for condition. B.

Inspection Terms (1)

For definitions of the inspection terms used throughout this manual, refer to Table 601.

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TABLE 601, Inspection Terms Term Abrasion Blister Buckling

Burning Burr Chafing Corrosion

Crack Dent Distortion Flaking Frosting

Galling Gouging Grooving Inclusion Metallization Nick Peening

Definition Wearing away of small amounts of metal as a result of friction between parts. The raised portion of surfaces caused by separation of layers of material. Large deformation from original shape. Usually caused by pressure or impact of a foreign object, unusual structural stresses, excessive heat, or any combination of these conditions. Loss of material from excessive heat. A sharp projection or rough edge. Wear caused by friction. A surface chemical action resulting in surface discoloration, a layer of oxide, or, in advanced stages, the removal of surface material. Pressure break in material A smooth, round-bottomed depression. Change from the original shape. Loose particles of surface material. An initial stage of scoring caused by irregularities or high points of metal welding together with minute particles of metal transferring to the mating surface, giving a frosted appearance. Fretting, and wearing away by friction. Removal of surface material, typified by rough and deep depressions. Smooth, rounded indentations caused by concentrated wear. Foreign material enclosed in metal. Coating by molten metal particles sprayed through the engine. Sharp bottomed depression with rough outer edges. Flattening or displacing of material by repeated blows. A surface may be peened by continuous impact of foreign objects, or loose parts.

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TABLE 601, Inspection Terms (Cont’d) Term Pitting

Scoring

Scratches

Scuff Seizure Spalling

Stressfailure Tear Unbalance

Wear

C.

Definition Surface condition characterized by minute holes or cavities which occur on overstressed areas. The pits may occur in such profusion as to resemble spalling. Form of wear characterized by a scratched, scuffed, or dragged appearance, with markings in the direction of sliding. Narrow shallow marks or lines resulting from the movement of a metallic particle or pointed object across a surface. Dull or moderate wear of a surface resulting from slight rubbing. Welding or binding of two adjacent surfaces, preventing further movement. Surface or sub-surface damage characterized by chips of parent metal that spall or flake out of material leaving cavities of varying sizes and depths. Metal failure due to compression forces, tension, shear, torsion, or shock. Parent metal torn by excessive vibration or other stresses. Condition created in a rotating body by an unequal distribution of weight about its axis. Will result in vibration. Condition resulting from a relatively slow removal of parent material. Frequently not visible to the unaided eye.

Inspection Gages NOTE: When an inspection procedure requires a very accurate measurement, a micrometer, vernier caliper or a dial indicator must be used. (1)

If a micrometer or vernier is to be used, check gage for accuracy before making measurement. Be sure that contacting surfaces are clean and contacting faces of part to be measured are free of dirt and burrs. When using depth gages, ensure anvil is held tight and square against part to be measured.

(2)

If a dial indicator is used, ensure indicator base is anchored firmly and that any swivel connections are tightened securely.

(3)

When taking measurements with feeler gages, ensure final size of feeler is a reasonably snug fit.

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D.

Magnetic Particle Inspection (1)

E.

Fluorescent Penetrant Inspection (1)

F.

The magnetic particle inspection is a nondestructive test procedure which detects cracks, voids, pits, subsurface holes and other imperfections. This method is applicable to ferromagnetic steel and has no effect on nonferrous materials.

Fluorescent penetrant inspection is a nondestructive means of inspecting nonferrous or nonmagnetic materials for cracks, cold shuts, porosity and other defects having surface openings. This method may be used on ferromagnetic parts of complex structure which could give false indications when checked by the magnetic particle inspection methods.

Inspection of Fuel, Oil and Air Tubes NOTE: The following inspection criteria are a standard instruction. Specific instructions for tubing inspection, where applicable, will be described in the appropriate chapter within the manual. (1)

Circumferential scratches in tubes are acceptable, provided they do not exceed a 45 degree segment on circumference. Any number of scratches is permissible; these may be blended out, provided depth of blend does not exceed 0.005 inch.

(2)

Longitudinal scratches in tubes must not exceed one-half inch in length. Any number of scratches is permissible.

(3)

Nicks and chafing marks in tubes are acceptable and may be blended provided they do not exceed 0.005 inch in depth. Each blended area must not exceed one-half square inch.

(4)

Dents in tubes are of limited acceptability, provided there are no restrictions to flow caused by sharp edges or corners. Dents are unacceptable within one inch of ferrule scarf-welds, or in a blended area.

(5)

Minor isolated pitting is acceptable if not greater than 0.003 inch in depth. Clusters of pits should be blended out to a maximum depth of 0.005 inch.

(6)

Rust and stains on tubes are acceptable if they can be removed by light polishing with very mild abrasive.

(7)

Examine tubes for cracks, especially at brazed joints.

(8)

Examine coupling and threaded fittings for cracks or damaged threads.

(9)

Check tube bores for obstructions.

G. Inspection of Welded Repairs (1)

Inspect weld repair for quality, uniformity, undercutting, cracking and flux removal. Welds must be blended into adjacent metal in gradual, smooth curves. Welds must be sound, clean, free from foreign material, and from internal and external defects which would adversely affect strength of weld.

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(2)

H.

Nominal welds (those not requiring finishing) must exhibit bead conditions as shown in Figure 601, detail A. Finished welds must exhibit bead conditions as shown in detail B.

Inspection of Rotating Components (1)

Life limited (critical) rotating components exhibiting cracks are unserviceable and shall not be repaired.

(2)

Handle rotating components with extreme care to prevent damage or contamination of the material.

(3)

Wear lint free gloves when touching rotating components.

(4)

Make sure close attention is paid to areas such as counterweight holes and blade slots where imperfections are difficult to find.

(5)

Use suitable clean, protective containers for storing and transporting components

(6)

Inspect components in accordance with the criteria specified in the relevant Chapter/Section/Subject.

(7)

Any observed conditions not defined in this manual are not acceptable for repair.

(8)

Evaluation of the surface should take into consideration the need for repairs and the limits to which repairs may be made to determine the suitability for continued use of the component.

(9)

Unrepairable components shall be quarantined to prevent further use.

(10)

It is important to have suitable lighting. The minimum recommended illumination for close and difficult inspection is 100 foot-candles measured at the inspection table top.

(11)

Unless otherwise specified, magnification shall not be used. A magnification of 3X to 4X may be used as an aid to evaluate and confirm an observed condition in detail.

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BEAD MUST NOT EXCEED T MAX. 0.05

T

MAX.

T

BEAD MUST NOT EXCEED 0.5 T MAX. MINIMUM MATERIAL CONDITION

MAXIMUM MATERIAL CONDITION

A − NOMINAL WELD − NO FINISHING REQUIRED

0.010 MAX.

T

T

0.010 MAX.

MAXIMUM MATERIAL CONDITION

MIN.

MINIMUM MATERIAL CONDITION

B − FINISHED WELD − DIMENSIONS AFTER DRESSING

C2589 Weld Repair - Inspection Figure 601

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STANDARD PRACTICES - CLEANING 1.

2.

General A.

Gas turbine cleaning can be categorized into two broad areas, namely specific parts cleaning and field cleaning (i.e., compressor washing).

B.

Specific parts cleaning is primarily to remove contaminants which might conceal minor cracks and other defects which, if not detected, could eventually lead to failure of a component or part. Engine components or parts should be cleaned only as necessary to perform required inspection and repair. Overcleaning of components or parts is unnecessary and should be avoided. The cleaning methods given in the following text are adequate for all maintenance levels. For compressor washing methods, refer to Chapter 71-00-00, CLEANING.

Cleaning A.

B.

General (1)

Prior to engine disassembly, ensure that the work area is clean.

(2)

Benches on which engine parts are placed must be clean and free from grit, metal filings, etc., which may contaminate engine oil systems, fuel systems or hardware.

(3)

Clean plastic bags should be available in which oil system and fuel system parts may be stored until ready for reassembly.

(4)

Clean plastic caps or covers should be used to protect exposed tubes or bearing areas.

(5)

At reassembly make sure that all parts are clean and new packings installed.

Precautions NOTE: The choice of cleaning agents should be limited to the consumables listed in CONSUMABLE MATERIALS section. The toxicity of cleansing agent will, however, depend on the type of contamination encountered on part to be cleaned. CAUTION:

TAKE PARTICULAR CARE IN SELECTING CLEANING METHOD TO MAKE SURE THAT ANODIZING AND OTHER PROTECTIVE COATINGS ARE NOT REMOVED FROM PARENT METAL. DO NOT USE ALKALIES ON ALUMINUM, MAGNESIUM, ALUMINIZED AND PAINTED AREAS.

(1)

Wear rubber gloves, apron or coveralls and face shield or goggles, when working with solvents.

(2)

Use the least toxic of available cleaning materials which will satisfactorily accomplish work.

(3)

Do all cleaning operations in a well ventilated work area.

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C.

(4)

Make sure that adequate and usable fire fighting and safety equipment is conveniently located and available to all personnel.

(5)

Do not smoke or expose a flame within 50 feet of cleaning area.

(6)

Make sure that all degreasing agents are thoroughly removed from all parts after cleaning.

(7)

Do not use steel brushes for any cleaning operation except when specifically detailed within this manual. Use a stiff bristle fiber brush.

Cleaning Before Welding (1)

Surface to be welded must be free from protective coatings, dirt, grease, oil and other contaminants, and as free as practicable from oxide formation. Wire brushes and abrasives may be used to remove protective coatings and oxides, except that the final step in removing oxides from aluminum alloys preferably should consist of chemical treatment immediately prior to welding. Wire brushes, when used for cleaning corrosion-resistant alloy, must have bristles of austenitic, corrosion-resistant steel. No undesirable deposit or residue must remain on surface to be welded after cleaning operation.

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STANDARD PRACTICES - REPAIR 1.

General A.

2.

The primary purpose of repair is to enable a component or engine part to be reworked to a condition which will provide safe operation. Approved repair schemes are detailed in the relevant sections of this manual using the various consumables listed in CONSUMABLE MATERIALS section.

Consumable Materials The consumable materials listed below are used in the following procedures.

3.

Item No.

Name

PWC03-001 PWC05-061 PWC05-147 PWC05-161 PWC05-197 PWC11-014 PWC11-016

Oil, Engine Lubricating Cloth, Abrasive Electrode, Welding Solution, Touch-up Acid, Chromic Alcohol, Isopropyl DELETED

Special Tools The special tools listed below are used in the following procedures.

4.

Tool No.

Name

Application

PWC30271-100

Spreader, Nut

PWC31771

Spreader, Nut

Obsolete - replaced by PWC31771 Alternate to PWC30271-100

Fixtures, Equipment and Supplier Tools The fixtures, equipment and supplier tools listed below are used in the following procedures. Name

Remarks

Welder Torch

AC/DC with high frequency controls Linde HW-10 or equivalent with recirculating water Argon gas (2 off)

Regulator Flowmeters

P&WC Proprietary Information. Subject to the restrictions on the title page.

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5.

Welding CAUTION:

A.

WELDING MUST BE DONE BY QUALIFIED PERSONNEL ONLY, USING SAFE WELDING PRACTICES, ADEQUATE VENTILATION, AND PROTECTIVE EQUIPMENT. DO NOT WELD IN CONFINED AREAS WITHOUT PROPER VENTILATION.

General The following procedures apply to components that have been removed from the engine. Weld repair of components still installed on the engine, is not permitted under any circumstance. A tungsten inert gas fusion welding process must be used when repairing cracks in engine parts. Argon or helium gas may be used in inert gas welding; however, argon is preferred by Pratt & Whitney Canada because its greater density reduces its rate of diffusion with the atmosphere. Inert gas welding is a gas arc welding process which uses inert gas to protect the weld area from the surrounding atmosphere. The heat necessary for welding is provided by a very intense electric arc which is struck between a non-consumable thoriated tungsten (tungsten and thorium alloy) electrode and the metal part. On repairs where a filler material is required, a welding rod, of appropriate material, is fed into the weld area and melted with the base metal in the same manner as in conventional gas welding.

B.

Cleaning Before Welding (1)

C.

Refer to CLEANING.

Welding Procedures

WARNING:

(1)

IF AN OXYGEN REGULATOR IS USED WITH ARGON GAS, DO NOT REINSTALL REGULATOR ON AN OXYGEN CYLINDER. ARGON GAS CONTAINS OIL AND THE POSSIBILITY EXISTS OF AN EXPLOSION DUE TO THE PRESENCE OF OIL IN THE REGULATOR.

Welding must be done only by certified personnel. (a) Connect one argon gas flowmeter to torch and connect other flowmeter, if necessary, behind crack as a backup when ready to weld. (b) Connect torch to arc welder for straight polarity. (c) Insert a 1⁄6 inch diameter thoriated tungsten electrode (PWC05-147) into torch, allowing approximately 5⁄16 inch of electrode to protrude from ceramic cup. The ceramic cup used must not be smaller than a No. 6 for the HW-10 torch, in order to provide a sufficient amount of inert gas to the weld area where cleanliness of the surface beader is important. NOTE: A plain tungsten electrode may be used, but a needle point must be maintained on the electrode for more positive starting of arc. Where possible, the electrode must be kept clean of material pickup.

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(d) If it is necessary to protect underside of weld from contamination, possible weld porosity, or poor surface finish, attach argon gas line behind crack to be welded. This may be accomplished by fabrication of small box-like fixtures having edges shaped to fit contours of part to be welded and using a suitable connection to secure gas line. Seal fixture to part in order to conserve gas leakage to minimum. NOTE: The amount of gas pressure to provide sufficient backup must be determined. This pressure should not allow the gas to stir the weld puddle. Do not use flux when welding in an inert atmosphere. (e) When high frequency controls are used, it is not necessary to strike an arc. Hold torch vertically to work so that the shielding gas (argon) forms a protective envelope around the weld. It is preferable to have area to be welded in a horizontal position. (f)

When high frequency controls are not used, strike arc and hold electrode tip approximately 1⁄8 to 1⁄4 inch above surface to be welded until a puddle is formed. Add welding rod, as applicable, and proceed as in conventional gas welding. NOTE: Test welds, using corresponding material of same thickness and joint design, should be made to determine correct gas pressure and arc welding settings.

(g) Because a high percentage of steel parts used in the engine are fabricated from 12 percent chromium corrosion-resistant steels, which are characterized by their susceptibility to air hardening, field repair of cracks by fusion welding is a special problem. The high temperature at which fusion weld repairs are made and the subsequent air cooling of the part, or parts, from these temperatures usually results in an increase in material hardness and a loss in ductility. Parts on which fusion weld repairs have been made have a tendency to crack because the steel structure becomes unstable, brittle and highly stressed. The structure of the material can be improved by reheating the parts and controlling the cooling rate. D.

Cleaning After Welding (1)

E.

Local Stress Relief (1)

F.

Refer to CLEANING.

Components which are not highly stressed may be repaired by fusion welding. It is possible to partially restore the original properties of such welded parts through use of local heat treatment. The localized heat may be applied by neutral flame of an oxyacetylene torch. Extend the stress relief one inch minimum beyond the welded area. After the desired heat has been applied to the part for the correct length of time, reduce temperature of part gradually.

Inspection of Welding (1)

Inspect repair area (Ref. INSPECTION).

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6.

Blend Repairs A.

Repair Procedure (1)

Blend repair using carborundum stone.

CAUTION:

B.

(2)

Polish blended area using crocus cloth (PWC05-061).

(3)

Blend all repairs and finish smoothly.

(4)

Lines, scratches or sharp edges which may cause a concentration of stress are not permitted.

Definitions BLENDING

GRINDING POLISHING C.

DO NOT POLISH WITH POWER TOOLS.

An operation that removes an irregularity or imperfection from a surface and results in restoring the surface to a smooth acceptable condition. An operation that removes material by the use of an abrasive material to produce a predetermined size. A finishing operation which produces a smooth surface finish.

General Repairs are defined as freehand blending, deburring and/or polishing. It does not include machining or machine grinding. Repair only defined damage within the limits specified in the relevant Chapter/Section/Unit. Undefined damage shall render the component unserviceable. Do repairs in a direction so that the finishing marks follow the lay of the original manufacturing machining marks. Restore surface finish of repaired area to the original manufacturing finish. Make sure repaired area conforms to the original manufacturing shapes, profiles, contours and radii. Make sure local repairs extend over an area 10 times the depth of damage. Maintain a smooth transition between repaired areas and adjacent areas. Make sure repaired area is 1/3 deeper than the damage to ensure removal of damage. Examine all repaired components.

D.

Air Gun The air gun is hand held, with an adjustable spindle speed and drives a suitable mandrel.

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Use a piece of abrasive cloth, rotary file, abrasive disk or wheel of appropriate shape, dimensions and grit size for hand grinding rotating components. Adjust the rotation of the hand blending wheel to obtain the required surface finish. Do not allow the wheel to exceed 2000 RPM to prevent local overheating of the material. Adjust the applied pressure of the wheel to produce a maximum of 0.0005 inch of material removal in each pass. A light, equal pressure on the wheel gives the best results as it permits the abrasive to cut easily without loading up and overheating. 7.

Threaded Inserts A.

Replacement of Threaded Inserts CAUTION:

(1)

8.

BEFORE USING INSERTS, IN ANY PART OF ENGINE, REFER TO ILLUSTRATED PARTS CATALOG FOR APPROVED LOCATIONS AND PART NUMBER OF INSERT.

Remove unserviceable insert using an approved extraction tool.

(2)

Clean out hole and make sure swarf and other foreign matter is removed.

(3)

Install new threaded insert into threaded hole using installation tool. Insert outer thread must be between one and one-half threads below surface of hole or counterbore, whichever applies.

(4)

Cut off driving tang at notch using approved tang removal tool and remove tang from holes.

(5)

Inspect repaired hole.

Studs A.

Replacement of Studs

CAUTION:

BEFORE INSTALLING NEW STUDS, REFER TO ILLUSTRATED PARTS CATALOG FOR APPROVED LOCATIONS AND PART NUMBERS.

When necessary, oversize studs are to be installed in place of those which are broken, stretched, loose or have damaged external threads. Whenever a stud which is already oversize requires replacement, install the next oversize stud. Use correct stud drivers to install new studs and torque to appropriate value (Ref. Tables 801 or 802, as applicable). Before installing new studs, refer to associated Illustrated Parts Catalog, for approved locations and part numbers. When threads of a stud hole are damaged beyond dimensions suitable for fitting a maximum oversize stud, it is usually possible to do repairs by the

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installation of a helical coil (Ref. Subpara. A.) or key-type insert. Consideration should, however, be given to reduction of thickness of walls of parent metal around insert and the required strength. Specific problems should be referred to P&WC Service Department (Ref. INTRODUCTION). B.

Replacement of Studs (1)

Remove damaged stud using an approved method.

CAUTION:

BEFORE INSTALLING NEW STUDS, REFER TO ILLUSTRATED PARTS CATALOG FOR APPROVED LOCATIONS AND PART NUMBERS.

(2)

Examine stud hole for condition; on worn stud holes use oversize studs.

(3)

Install stud using an approved stud driver to correct protrusion height; make sure torque limits (Ref. Tables 801 or 802, as applicable) are not exceeded. TABLE 801, Standard Stud Torque Limits

Stud Thread Size (Drive End)

Minimum

Maximum Necked Down $

Maximum Plain #

0.112-40

4

-

8

0.138-32

8

-

14

0.164-32

10

30

30

0.190-24

15

40

45

0.216-24

20

65

70

0.250-20

40

95

105

0.3125-18

85

210

230

0.375-16

160

375

425

0.4375-14

200

600

675

0.500-13

250

950

1050

NOTE: 1. Symbol $: These limits apply where the unthreaded diameter of the stud is less than the minimum minor diameter of the coarse pitch thread (drive end). NOTE: 2. Symbol #: These limits apply where the unthreaded diameter of the stud is equal to or greater than the minimum minor diameter of the coarse pitch thread (drive end).

TABLE 802, Stepped Stud Torque Limits Stud Thread Size (Nut End)

Minimum

Maximum Necked Down $

Maximum Plain #

0.138-40

8

-

18

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TABLE 802, Stepped Stud Torque Limits (Cont’d) Stud Thread Size (Nut End)

Minimum

Maximum Necked Down $

Maximum Plain #

0.164-36

10

30

30

0.190-32

15

45

50

0.216-28

20

65

75

0.250-28

40

115

125

0.3125-24

85

240

260

0.375-24

160

450

500

0.4375-20

200

700

800

0.500-20

250

1150

1300

NOTE: 1. Symbol $: These limits apply where the unthreaded diameter of the stud is less than the minimum minor diameter of the fine pitch thread (nut end). NOTE: 2. Symbol #: These limits apply where the unthreaded diameter of the stud is equal to or greater than the minimum minor diameter of the fine pitch thread (nut end). C.

Repair of Damaged Stud Hole (1)

Make sure damaged hole is suitable for repair (Ref. Subpara. B. preceding).

(2)

Measure core depth of existing hole.

(3)

Select relevant size drill and drill hole to measured depth (Ref. Step (2), preceding).

(4)

Using relevant special tap, thread hole one thread deeper than insert to be fitted.

(5)

Where applicable, counterbore hole to required angle and depth.

(6)

Clean out hole and ensure freedom from metal chippings and other foreign matter.

(7)

If part being repaired is magnesium, treat tapped hole with chrome pickle touch-up solution (PWC05-161): (a) Clean area to be treated with abrasive cloth (PWC05-061) and/or cloth impregnated with isopropyl alcohol (PWC11-014). (b) On rough surfaces, remove corrosion using wire brush or abrasive paper. (c) On finished surfaces, remove corrosion using swab or brush impregnated with solution (PWC05-197) at 85° to 93°C (180° to 200°F). (d) Rinse with clean, cold water. (e) Rinse with clean, hot water.

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(f)

Dry using clean, dry compressed air.

(g) Apply solution (PWC05-197) to area to be treated using a clean cloth. Repeat swabbing at frequent intervals to make sure treated area is maintained wet with solution during treatment. (h) Thoroughly rinse touched up area by swabbing several times with clean cloth moistened with water. (i) (8) 9.

Dry using clean, dry compressed air.

Using appropriate size threaded insert, install insert into repaired stud hole (Ref. Para. B.).

Shanknuts A.

Replacement of Shanknuts (Ref. Fig. 801) CAUTION: (1)

AVOID DAMAGE TO FLANGE.

Using a suitable drill, partially remove the flared end of shanknut.

(2)

Remove shanknut body using a parallel pin punch at drilled end to shear weakened flare, and retrieve the shanknut case.

(3)

Install new shanknut (Ref. IPC) and hold against flange.

(4)

Lightly lubricate tapered portion of spreader (1) (PWC30271-100) or (2) (PWC31771) with oil (PWC03-001) and screw into shanknut until shank end is flared against flange.

(5)

Remove spreader and examine flared end of shanknut for correct forming with no evidence of deformation or cracks.

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THIS PAGE INTENTIONALLY LEFT BLANK

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SHANK NUT BEFORE INSTALLATION

SHANK NUT AFTER INSTALLATION

1

SHANK NUT BEFORE INSTALLATION

2

SHANK NUT AFTER INSTALLATION

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Key to Figure 801 1. 2.

Spreader (PWC30271-100) Spreader (PWC31771)

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Jan 13/2020 Jan 13/2020

Contents

1 2 3 4 blank

Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020

71-00-00 Adjustment/ Test

501 502 503 504 505 506 507 508 509 510 511 512 513 514 515 516 517 518 519 520 521 522 523 524 525 526 527 528 529 530 531 532 533

Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020 Jan 13/2020

CHAPTER SECTION

71-00-00 Cleaning/ Painting

PAGE

DATE

534 blank 535 536 blank 537 538 blank 539 540 541 542 543 544 545 546 547 548 549 550

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701 702 703 704 705 706 707 708 709 710 711 712 713 714 715 716 717 718 719 720 blank

Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019 Feb 18/2019

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TABLE OF CONTENTS SUBJECT

PAGE

POWER PLANT - ADJUSTMENT/TEST

71-00-00

1.

General

501

2.

Engine Overtorque and Overtemperature Limits

505

3.

Engine Pre-operational Check

505

A.

505

4.

5.

6.

7.

8.

9.

Pre-start Checks

511

A.

511

11.

Engine Control and Switch Position

Dry Motoring Run

511

A.

Procedure

511

Wet Motoring Run

512

A.

512

Procedure

Engine Starting

513

A.

513

Procedure

Engine Shutdown

514

A.

514

Procedure

Post-Shutdown Checks A.

10.

Procedure

515

Procedure

515

Propeller Governor Checks

515

A.

515

Procedure

Fuel Control Unit Checks A.

518

Fuel Control Unit (FCU) Maximum Gas Generator Speed Setting (PT6A-34, -34B, -36)

518

Fuel Control Unit (FCU) Gas Generator Speed Adjustment (PT6A-34AG)

519

C.

Fuel Control Unit (FCU) Idle Speed Adjustments

521

D.

Manual Override System Static Check (PT6A-34/-34AG)

524

E.

Manual Override System Operational Check (PT6A-34/-34AG)

524

B.

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TABLE OF CONTENTS SUBJECT

PAGE

POWER PLANT - ADJUSTMENT/TEST (Cont’d) F. 12.

13.

14.

15.

16.

Deceleration Check

71-00-00 529

Oil Pressure Check

531

A.

531

Procedure

Engine Performance Check

531

A.

General

531

B.

Procedure

531

Acceleration Adjustments

545

A.

545

Procedure

Torquemeter Function Test

545

A.

545

Procedure

Bleed Valve Closing Check (Post-SB1683)

546

A.

546

Procedure

POWER PLANT - CLEANING

71-00-00

1.

General

701

2.

Consumable Materials

701

3.

Special Tools

701

4.

Fixtures, Equipment and Supplier Tools

701

5.

Engine Washing

702

A.

General

702

B.

Types of Internal Wash

702

C.

6.

Wash Schedule Recommendations

702

D.

Preparation of Solutions

703

E.

Equipment Required

705

Engine Motoring Washes

709

A.

709

Compressor Desalination Wash

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TABLE OF CONTENTS SUBJECT

PAGE

POWER PLANT - CLEANING (Cont’d) B. 7.

8.

9.

10.

71-00-00

Compressor Performance Recovery Wash

711

Engine External Wash

713

A.

713

General

Compressor Turbine Wash

715

A.

General

715

B.

Equipment

715

C.

Compressor Turbine Wash Method

715

Fuel Nozzle In-situ Cleaning

717

A.

General

717

B.

Preparation

717

C.

Cleaning

718

Inhibition of Engine Corrosion

719

A.

719

Optional Application of Engine Corrosion-inhibiting Solution

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POWER PLANT - ADJUSTMENT/TEST 1.

General This section contains information for engine ground running and for checks and adjustment/test procedures to verify the integrity of installed/replaced items. Before making any control adjustments/checks, the engine should be run for ten minutes minimum and all parameters stabilized. NOTE: 1. Although generalized procedures for ground testing are described in the following paragraphs, the appropriate Aircraft Manufacturer’s Manual must be consulted for detailed procedures, reference curves and/or tables required to do the tests. NOTE: 2. For PT6A-34AG engines, in ‘‘converted’’ airframes only, customized operating information document compiled by the engine manufacturer is to be used, when available, in lieu of an original-equipment Aircraft Manufacturers Manual. PT6A-34AG installed at new by airframe constructors will use manufacturers data as in NOTE 1. A.

Specific checks and the order in which they are to be done after installation or replacement of components are defined in Table 501. TABLE 501, Checks after Component Installation/Replacement

Item Installed/Replaced Compressor Bleed Valve Engine on Airframe Scavenge Oil Tubes Starting Flow Control Unit/Flow Divider Fuel Control Unit Fuel Drain Valves (Front and Rear) Fuel Lines Fuel Manifold/Fuel Nozzles Fuel Pump Shaft Oil Seals Oil Filter, Filter Housing and Check Valve Oil Pressure Relief Valve Oil-to-Fuel Heater Pressure Oil System Propeller Governor P3 (Compressor) Air Filter (when fitted) Reversing Linkage B.

Check Req’d (Para. No.) 4.7.13.8.9. 3.5.6.4.7.11.14.10.12.13.8.9. 4.7.8.9. 6.5.4.7.8.9. 6.5.4.7.11.13.8.9. 6.5.4.7.8.9. 6.5.4.7.8.9. 6.5.4.7.13.8.9. 6.5.4.7.8.9. 4.7.8.9. 5.6.4.7.8.9. 4.7.12.8. 6.5.4.7.8.9. 4.7.12.8.9. 4.7.10.13.8.9. 4.7.8.9. 13.

Minimum checks to be done before fault isolation procedures are initiated and done on an engine are defined in Table 502.

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TABLE 502, Minimum Checks Required before Troubleshooting Check and Sequence Engine Pre-operational Check Engine Pre-start Check Dry Motoring Run Wet Motoring Run Engine Start Engine Shutdown Post-Shutdown C.

Para. No. 3. 4. 5. 6. 7. 8. 9.

Engine operating limits are defined in Table 503 and 504. TABLE 503, PT6A-34/-34B/-34AG Engine Operating Limits

Power Setting

Ng (100%= 37,500 rpm)

Max. Torque SHP

lb.ft.

psi

Takeoff and Max. Cont.) Enroute) Emergency

750 31.0°C (87°F)

Max. Climb

For For -34/-34B -34/-34B engines engines 1970 64.5 For For 700 -34AG -34AG 28.3°C engines engines (83°F) 1840 60.2

Max. Cruise

700 19.4°C (67°F)

1970

1840

64.5

60.2

Idle

790

765

%

38100 101.6

38,100 101.6

740

38,100 101.6

685 (5)

19,750 Typ.

RPM

2200

2200

2200

%

Oil Press. psig (2)

Oil Temp. °C (8)

100

85 to 105

10 to 99 (50° to 210°F)

100

85 to 105

0 to 99 (32° to 210°F)

100

85 to 105

0 to 99 (32° to 210°F)

40 (Min.)

-40 to 99 (-40° to 210°F)

52.6 Typ.

1090 (4) (7)

Starting 2100 (10)

Transient Max. Reverse (6)

Max. Observed ITT °C RPM

Np (100%= 2200 rpm)

750

1970

68.4 (10)

64.5

850 (4)

790

-40 (Min.) 38,500 102.6 (4) (4)

38,100 101.6

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2420 (9)

110 (9)

85 to 105

0 to 99 (32° to 210°F)

2100

95 ±1%

85 to 105

0 to 99 (32° to 210°F)

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TABLE 503, PT6A-34/-34B/-34AG Engine Operating Limits (Cont’d)

Power Setting

Ng (100%= 37,500 rpm)

Max. Torque SHP

lb.ft.

psi

Max. Observed ITT °C RPM

%

Np (100%= 2200 rpm) RPM

%

Oil Press. psig (2)

Oil Temp. °C (8)

GENERAL NOTE: The operating parameters in this Table are individual limits for each engine parameter and do not apply simultaneously. NOTE: 1. All limits are based on sea level and ambient temperatures as specified. NOTE: 2. Minimum oil pressure above 27,000 Ng is 85 psig. NOTE: 3. For overtemperature and overtorque action, refer to Figures 501, 502 and 503, and to Chapter 72-00-00, Unscheduled Inspection. NOTE: 4. These values are time limited to two (2) seconds. NOTE: 5. Increase Ng to keep within this limit. NOTE: 6. If maximum torque is used, Np must be set so as not to exceed power limitations. Reverse power operation is limited to one (1) minute. NOTE: 7. Starting temperatures above 850°C (1562°F) should be investigated for cause. NOTE: 8. For increased oil service life, an oil temperature below 80°C (176°F) is recommended. NOTE: 9. In the event of failure of the propeller governor toward overspeed, it is permissible to complete a flight with propeller control via the overspeed governor (on engines so equipped) providing this limit is not exceeded. NOTE: 10. These values are time limited to twenty (20) seconds.

TABLE 504, PT6A-36 Engine Operating Limits

Power Setting

Max. Torque SHP

lb.ft.

psi

Takeoff and Max. Cont.) Enroute) Emergency

750 36.1°C (97°F) 1970 64.5

Takeoff Wet

750 47.8°C (118°F) 1970 64.5

Max. Observed ITT °C

805

805

Ng (100%= 37,500 rpm) RPM

38,100

38,100

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Np (100%= 2200 rpm) %

RPM

101.6 2200

101.6 2200

%

Oil Press. psig (2)

Oil Temp. °C (8)

100

85 to 105

10 to 99 (50° to 210°F)

100

85 to 105

10 to 99 (50° to 210°F)

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TABLE 504, PT6A-36 Engine Operating Limits (Cont’d)

Power Setting

Max. Torque SHP

lb.ft.

psi

Max. Climb

700 28.3°C (83°F) 1970 64.5

Max. Cruise

700 19.4°C (67°F) 1840 60.2

Idle

765

RPM

38,100

740

38,100

685 (5)

19,750 Typ.

Np (100%= 2200 rpm) %

RPM

101.6 2200

101.6 2200

%

Oil Press. psig (2)

Oil Temp. °C (8)

100

85 to 105

0 to 99 (32° to 210°F)

100

85 to 105

0 to 99 (32°to 210°F)

40 (Min.)

-40 to 99 (-40° to 210°F)

52.6 Typ.

1090 (4)(7)

Starting 2100 68.4 (11) (11)

Transient Max. Reverse (6)

Max. Observed ITT °C

Ng (100%= 37,500 rpm)

750

1970 64.5

865 (4)

805

-40 (Min.) 38,500 (4)

102.6 2420 110 (4) (10) (10)

85 to 105

0 to 99 (32° to 210°F)

38,100

95 101.6 2100 (±1%)

85 to 105

0 to 99 (32° to 210°F)

GENERAL NOTE: The operating parameters in this Table are individual limits for each engine parameter and do not apply simultaneously. NOTE: 1. All limits are based on sea level and ambient temperatures as specified. NOTE: 2. Minimum oil pressure above 27,000 Ng is 85 psig. NOTE: 3. For overtemperature and overtorque action, refer to Figures 501, 502 and 504, and to Chapter 72-00-00, Unscheduled Inspection. NOTE: 4. These values are time limited to two (2) seconds. NOTE: 5. Increase Ng to keep within this limit. NOTE: 6. If maximum torque is used, Np must be set so as not to exceed power limitations. Reverse power operation is limited to one (1) minute. NOTE: 7. Starting temperatures above 850°C (1562°F) should be investigated for cause. NOTE: 8. For increased oil service life, an oil temperature below 80°C (176°F) is recommended. NOTE: 9. These values are for engines equipped with water/methanol injection Power Augmentation. NOTE: 10. In the event of failure of the propeller governor toward overspeed, it is permissible to complete a flight with propeller control via the overspeed governor (on engines so equipped) providing this limit is not exceeded. NOTE: 11. These values are time limited to twenty (20) seconds.

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2.

Engine Overtorque and Overtemperature Limits Refer to Figure 501 and Figure 502 for engine overtemperature limits and corresponding inspection requirements. Refer to Figure 503 for engine inadvertent cut-off and relight during taxi and corresponding inspection requirements. For unscheduled inspection procedure, refer to Chap. 72-00-00, INSPECTION, Unscheduled Inspection. Refer to Figure 504 for engine overtorque limits and corresponding maintenance actions.

3.

Engine Pre-operational Check A.

Procedure (1)

Remove the air inlet and exhaust covers (if fitted). Do not permit the propeller to windmill if a restraining device is secured to the exhaust covers.

(2)

Open engine cowlings (Ref. Aircraft Manufacturer’s Manual) and inspect the engine mounts and air inlet screen, and spray ring, if fitted.

(3)

Examine all linkages to the engine and to the accessories mounted on the engine, for attachment.

(4)

Examine all fuel and oil tubes, lines and connections for security and for leaks. No leaks are permitted except at normal seepage drains.

(5)

Examine all pneumatic line connections and filters for security.

WARNING: (6)

Examine all electrical connectors for proper installation.

CAUTION:

(7)

MAKE SURE THE ELECTRICAL POWER IS OFF.

DO NOT MOVE THE COCKPIT POWER CONTROL LEVER INTO PROPELLER REVERSE POSITION, AS DAMAGE TO THE LINKAGE WILL RESULT. REVERSE MAY ONLY BE SELECTED WITH THE ENGINE RUNNING AND THE PROPELLER TURNING.

Check the cockpit engine controls for freedom of movement and verify full travel of engine control linkages. NOTE: Individual airframe installations may prevent full application of this check with the electrical power off and engine not running. Refer to individual aircraft operating instructions.

(8)

Check engine oil level and that oil system has been properly serviced (Ref. 72-00-00, SERVICING). Check locking of the filler cap after servicing.

(9)

Close engine cowlings (Ref. Aircraft Manufacturer’s Manual).

(10)

Make sure that fuel system has been serviced with proper fuel (Ref. Service Bulletin SB1244, Approved Listing of Engine Fuel and Additives).

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AREA

A

1. DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE. 2. PERFORM VISUAL INSPECTION. 3. RECORD IN ENGINE LOG BOOK.

AREA B

C

1. PERFORM HOT SECTION INSPECTION. 2. RETURN COMPRESSOR TURBINE DISK AND BLADE ASSEMBLY TO AN OVERHAUL FACILITY FOR STRETCH AND FLOURESCENT PENETRANT INSPECTION. IF TEMPERATURE EXCEEDS THIS VALUE FOR 2 SECONDS RETURN ENGINE TO AN OVERHAUL FACILITY. COMPRESSOR AND POWER TURBINE BLADES MUST BE DISCARDED AND BOTH TURBINE DISKS SUBJECTED TO STRETCH CHECK AND FLOURESCENT PENETRANT INSPECTION.

❉

❉

AREA

1. PERFORM HOT SECTION INSPECTION.

INTER−TURBINE TEMPERATURE C

850

°

840

RE

TU

AREA

RN

C

EN

GIN

ET

830

OA

NO

VE

RH

AU

L FACILITY

AREA B 810 AREA

A

790 NO ACTION REQUIRED 2

10

20

30

40

50

60

70

80

90

TIME − SECONDS

C1244D

PT6A-34/-34B/-34AG Overtemperature Limits (All Conditions Except Starting) Figure 501 (Sheet 1 of 2) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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AREA

A

1. DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE. 2. PERFORM VISUAL INSPECTION. 3. RECORD IN ENGINE LOG BOOK. 1. PERFORM HOT SECTION INSPECTION.

AREA B

C

1. PERFORM HOT SECTION INSPECTION. 2. RETURN COMPRESSOR TURBINE DISK AND BLADE ASSEMBLY TO AN OVERHAUL FACILITY FOR STRETCH CHECK AND FLOURESCENT PENETRANT INSPECTION.

INTER−TURBINE TEMPERATURE C

865

°

❉

❉

AREA

RE

855

IF TEMPERATURE EXCEEDS THIS VALUE FOR 2 SECONDS RETURN ENGINE TO AN OVERHAUL FACILITY. COMPRESSOR AND POWER TURBINE BLADES MUST BE DISCARDED AND BOTH TURBINE FISKS SUBJECTED TO STRETCH CHECK AND FLOURESCENT PENETRANT INSPECTION.

TU

AREA

RN

EN

GIN

ET

C

OA

NO

VE

845

RH

AU

LF

AC

ILIT

Y

AREA B 825 AREA

A

805 NO ACTION REQUIRED 2

10

20

30

40

50

60

70

80

90

TIME − SECONDS

C5975B

PT6A-36 Overtemperature Limits (All Conditions Except Starting) Figure 501 (Sheet 2) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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A AREA B AREA

NO ACTION REQUIRED VISUAL INSPECTION AND RECORD IN ENGINE LOG BOOK

C

AREA

1. PERFORM HOT SECTION INSPECTION 2. RETURN COMPRESSOR TURBINE BLADE AND DISK ASSEMBLY TO AN OVERHAUL FACILITY FOR STRECTH CHECK AND FLOURESCENT PENETRANT INSPECTION.

❉

NOTE INTER−TURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS. BUT DO ALLOW FOR SOME TYPICAL INSTRUMENT LAG.

❉

1090

IF TEMPERATURE EXCEEDS THIS VALUE FOR TWO SECONDS RETURN ENGINE TO AN OVERHAUL FACILITY. COMPRESSOR AND POWER TURBINE BLADES MUST BE DISCARDED AND BOTH TURBINE DISKS SUBJECTED TO STRETCH CHECK AND FLOURESCENT PENETRANT INSPECTION.

RN VE

NO

OA

ET

GIN

EN LF

AU

C

RH AC

980

ILIT

B

Y

INTER−TURBINE TEMPERATURE C

TU

RE

° 1035

A 925 1 1 2

5

10

15

20

30

TIME − SECONDS

C233F Overtemperature Limits (Starting Conditions Only) Figure 502 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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A AREA B AREA

AREA

C

RECORD OCCURRENCE IN ENGINE LOG BOOK. 1. DO HOT SECTION INSPECTION. 2. RETURN COMPRESSOR TURBINE BLADE AND DISK ASSEMBLY TO AN OVERHAUL FACILITY FOR STRETCH CHECK, FLUORESCENT PENETRANT INSPECTION AND A METALLURGICAL ANALYSIS (CUT−UP) OF TWO BLADES. RETURN ENGINE TO AN OVERHAUL FACILITY. NOTE: INTERTURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS. BUT DO ALLOW FOR SOME TYPICAL INSTRUMENT LAG.

INTERTURBINE TEMPERATURE C

1090

°

1035

AREA

C

AREA B

980

AREA

A

925

0

2

5

10

15

20

25

30

TIME SECONDS

C94193 Inadvertent Cut-off and Relight During Taxi Figure 503 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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TORQUE LB−FT (PSI) : NO MAINTENANCE ACTION IS REQUIRED.

AREA

A B

AREA

C

: RETURN THE ENGINE TO AN APPROVED OVERHAUL FACILITY.

AREA

2,100 (68.7)

: FIND AND CORRECT THE CAUSE OF OVERTORQUE. DO A VISUAL INSPECTION. RECORD THE EVENT IN THE ENGINE LOG BOOK. (REF. 72−00−00, ENGINE − INSPECTION)

2,065 (67.5) AREA

C

AREA B 1,970 (64.4)

AREA 0 20 SECONDS

1

A 2

3

4

5

TIME − MINUTES

C192508

PT6A-34/-34B/-34AG/-36 Overtorque Limits (All Conditions) Figure 504 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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(11)

4.

If the engine is not to be started immediately, refit the air inlet and exhaust covers. If the engine is to be started, remove the propeller restraining device. Check that the area is clear for engine motoring.

Pre-start Checks A.

Engine Control and Switch Position NOTE: Cockpit labels and names of controls tend to differ according to the airframe manufacturer. The terminology used in this and subsequent paragraphs is that of Pratt & Whitney Canada. (1)

Power Control Lever - GROUND IDLE.

(2)

Propeller Control Lever - FEATHER. NOTE: Engines incorporating the non-P&WC reversing cam, select Fine Pitch at ambient temperatures below +50°F (+10°C) and feather the propeller at higher ambient temperatures.

(3)

Starting Control Lever - CUT-OFF.

(4)

Fuel Condition Lever - OFF.

WARNING: (5)

MAKE SURE PERSONNEL, EQUIPMENT AND OTHER AIRCRAFT ARE CLEAR OF DANGER ZONE NEAR ENGINE.

If proceeding to a start: (a) Engine Master Switch - ON. (b) Fuel System Shut-off Switch - ON. (c) Fuel Boost Pump Switch - ON. (d) Fuel Inlet Pressure Indicator - Check 5 psig minimum (if aircraft is equipped with gage or light, to make sure that fuel is being delivered to the engine fuel inlet).

5.

Dry Motoring Run A.

Procedure NOTE: This procedure is used at any time it is deemed necessary to remove internally trapped fuel and vapor, or if there is evidence of a fire within the engine gas path. Air passing through the engine serves to purge fuel, vapor or fire from the combustion section, compressor turbine, power turbines, and exhaust system. (1)

Power Control Lever - GROUND-IDLE.

(2)

Starting Control Lever - CUTOFF/Fuel Condition Lever - OFF (as applicable).

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(3)

Ignition Switch - OFF.

(4)

Engine Master Switch - ON.

(5)

Fuel System Shut-off Switch - ON.

(6)

Fuel Boost Pump Switch - ON.

(7)

Engine Starter Switch - ON.

WARNING:

SHOULD THE FIRE PERSIST, AS INDICATED BY SUSTAINED T5, CLOSE THE FUEL SYSTEM SHUTOFF SWITCH AT THIS TIME AND CONTINUE MOTORING.

(8)

Maintain the starter operation for the desired duration, observing appropriate starter limits (Ref. Starter Manufacturer’s Manual).

(9)

Engine Starter Switch - OFF.

(10)

Fuel Boost Pump Switch - OFF.

(11)

Fuel System Shut-off Switch - OFF.

(12)

Engine Master Switch - OFF. NOTE: Allow the required cooling period for the starter before any further operation is attempted.

6.

(13)

Check all oil and fuel lines and connections for leaks. None are allowed.

(14)

Check engine oil level and service as necessary (Ref. 72-00-00, SERVICING).

Wet Motoring Run CAUTION:

A.

THIS PROCEDURE IS USED STRICTLY FOR MAINTENANCE PURPOSES AND IS NOT PART OF THE NORMAL START PROCEDURE. AFTER A WET MOTORING RUN, A DRY MOTORING RUN (REF. PARA. 5.) MUST BE ACCOMPLISHED BEFORE ANY START IS ATTEMPTED.

Procedure (1)

Starting Control Lever - CUTOFF/Fuel Condition Lever - OFF (as applicable).

(2)

Ignition Switch - OFF.

(3)

Engine Master Switch - ON.

(4)

Fuel System Shutoff Switch - ON.

(5)

Fuel Boost Pump Switch - ON.

(6)

Engine Starter Switch - ON. NOTE: Observe starter limits.

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(7)

After the gas generator has reached stabilized speed, Starting Control Lever to GROUND-IDLE for 10 seconds.

(8)

Starting Control Lever - CUTOFF/Fuel Condition Lever - OFF (as applicable)

(9)

7.

Engine Starter Switch - OFF.

(10)

During rundown, check that the starting control drain is draining and that both gas generator case drain valves are likewise functioning.

(11)

Fuel Boost Pump Switch - OFF.

(12)

Fuel System Shutoff Switch - OFF.

(13)

Engine Master Switch - OFF.

(14)

Check all engine fuel lines and connections for leaks. None are allowed.

(15)

Allow the starter cooling period, then follow with a dry motoring run (Ref. Para. 5.).

Engine Starting A.

Procedure

CAUTION:

WHEN STARTING ENGINES INCORPORATING A MANUAL OVERRIDE SYSTEM, MAKE SURE THE COCKPIT MANUAL OVERRIDE CONTROL IS IN THE OFF POSITION.

(1)

Do the pre-start procedure (Ref. Para. 4.).

(2)

Engine Starter Switch - ON. NOTE: Minimum speed to obtain satisfactory light is 4500 rpm (12% Ng).

(3)

Engine Oil Pressure - Check for indication.

(4)

Ignition Switch - ON.

(5)

After the gas generator speed passes through or has stabilized above the minimum light-off speed, advance the Starting Control lever to the IDLE position.

(6)

Make sure that the engine accelerates to IDLE rpm and that the maximum allowable ITT is not exceeded.

(7)

For engines equipped with spark ignition, after attaining stabilized gas generator speed, move the Starting Control (Fuel Condition) lever to LO-IDLE position.

(8)

For engines equipped with glow-plug igntion, wait for five seconds (approximately) to allow the gas generator speed to stabilize, then move the Starting Control (Fuel Condition) lever to the LO-IDLE position.

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CAUTION:

(9)

WHENEVER THE GAS GENERATOR FAILS TO LIGHT UP WITHIN 10 SECONDS AFTER MOVING THE STARTING CONTROL LEVER TO THE RUN POSITION, SHUT OFF FUEL, STARTER AND IGNITION. ALLOW A 30 SECOND FUEL DRAINING PERIOD, FOLLOWED BY A 15 SECOND DRY MOTORING RUN BEFORE ATTEMPTING ANOTHER START. IF THE STARTER LIMITS PERMIT, IT IS NOT NECESSARY TO ALLOW RUNDOWN AFTER A DRY MOTORING RUN. IF, FOR ANY REASON, THE STARTING ATTEMPT IS DISCONTINUED, ALLOW THE ENGINE TO COME TO A COMPLETE STOP AND THEN ACCOMPLISH A DRY MOTORING RUN. REPEAT THE COMPLETE STARTING SEQUENCE. OBSERVE STARTER LIMITS (REF. APPLICABLE STARTER MANUFACTURER’S MANUAL).

When the engine attains idle rpm: (a) Engine Starter Switch - OFF. (b) Ignition Switch - OFF.

CAUTION:

(10) 8.

ON MULTI-ENGINED AIRCRAFT, TO PRECLUDE OVERTEMPERATURE DURING A START, MAKE SURE THAT THE STARTING CONTROL LEVER IS ADVANCED TO IDLE ON THE ENGINE SUPPLYING GENERATOR VOLTAGE.

Before proceeding to ground run, carry out at least two feathering cycles to purge propeller governor and propeller hub.

Engine Shutdown A.

Procedure

WARNING:

IF THERE IS ANY EVIDENCE OF FIRE WITHIN THE ENGINE AFTER SHUTDOWN, PROCEED IMMEDIATELY AS DESCRIBED UNDER THE DRY MOTORING RUN (REF. PARA. 5.).

WARNING:

MAKE SURE THE ENGINE IS SHUT DOWN BEFORE PERFORMING ANY ADJUSTMENTS ON ENGINE-MOUNTED EQUIPMENT. THIS IS ESSENTIAL DUE TO THE CLOSE PROXIMITY OF THE PROPELLER AND EXHAUST NOZZLES.

(1)

Power Control Lever - GROUND-IDLE. NOTE: Allow the engine to stabilize for a minimum of one minute at the minimum obtainable ITT.

(2)

Propeller Control Lever - FEATHER.

(3)

Starting Control Lever - CUTOFF/Fuel Condition Lever - OFF (as applicable).

(4)

Fuel Boost Pump Switch - OFF.

(5)

Fuel System Shutoff Switch - OFF.

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(6)

Engine Master Switch - OFF. NOTE: Make sure that the compressor decelerates freely. The compressor rundown time must not be less than 20 seconds from ground idle.

9.

Post-Shutdown Checks A.

Procedure (1)

Check all engine oil lines and connections for leaks. None are allowed, except at normal seepage drains as specified in Table 505. TABLE 505, Engine Oil and Fuel Permissible Leakage

MAXIMUM LEAKAGE DURING LOCATION OF DRAIN OPERATION Engine Breather 15 cc/hr Fuel Pump 0.55 cc/min Fuel Control Unit Zero Start Control or Flow Divider and Dump 0.2 cc/min Valve (as applicable) Starter Oil Seal Cavity 3.0 cc/hr Gas Generator Drain Valves Zero Propeller Nose Seal 5 cc/hr Oil Consumption 0.2 lb/hr (100 cc/hr) or 1 liter in 10 hours Oil Filter Housing Check Valve 0.50 cc/hr NOTE: When a specific seal leakage is not specified, the seal leakage shall not exceed 3 cc per hour per individual seal. All seal leakages shall be included in total oil consumption (Ref. Chapter 72-00-00, Engine Description and Operation).

10.

(2)

Check engine oil level and service as necessary (Ref. Chapter 72-00-00, SERVICING).

(3)

Check all engine-mounted accessories and linkages for security for mounting.

(4)

Check oil-to-fuel heater installation (Ref. 73-10-01, MAINTENANCE PRACTICES).

Propeller Governor Checks (Ref. Fig. 505) A.

Procedure CAUTION:

MAKE SURE THAT THE Py TUBE IS BLANKED. ALSO BLANK THE FITTING ON THE GOVERNOR TO STOP OIL FROM SEEPING OUT DURING ENGINE RUN.

(1)

With the engine shut down, disconnect and cap the governor Py air pressure tube at the governor (Ref. 73-10-08).

(2)

Do the pre-start checks (Ref. Para. 4.).

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1

7

2

8 3

4

6

5

C620C Propeller Governor Adjustments Figure 505 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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Key to Figure 505 1. 2. 3. 4. 5. 6. 7. 8.

Pneumatic Maximum Adjuster (Not for Field use) Governor Maximum Speed Adjuster Feathering Adjuster Pneumatic Minimum Eccentric Adjuster Airbleed Link Reset Lever Interconnect Rod Push-pull Control Speed Adjusting Lever

(3)

Start the engine and operate for five minutes at ground idle to permit warm-up of the engine oil to 75°C (167°F) minimum.

(4)

Advance the power control lever to obtain 80% Ng, and perform two feathering cycles to purge air from the system and propeller hub. NOTE: Reduce feathering time by turning the adjustment screw (3) in a counterclockwise direction. Two turns from the nominal is the maximum permissible adjustment.

(5)

Set the propeller control lever to the full fine pitch position. Advance the power control lever sufficiently for the propeller to reach constant speed, and mark the position on the cockpit quadrant. Note and record the Ng.

(6)

Adjust the governor maximum speed adjustment (2) as required to obtain the desired propeller speed (Np). An adjustment counterclockwise increases speed. NOTE: Maximum Np may vary with different installations and according to the model. Consult the Aircraft Manufacturer’s Manual for the correct setting.

(7)

Reconnect the governor Py air pressure tube to governor (Ref. 73-10-08).

(8)

Set the propeller control to a full fine pitch position, and the power control lever to the quadrant position marked in step (5).

(9)

Note the Ng and compare it with value recorded in step (5). The maximum permissible Ng drop is 100 rpm. If exceeded, check the linkage to make sure the reset arm is in contact with the maximum stop. Adjust if necessary.

CAUTION:

DO NOT, UNDER ANY CIRCUMSTANCES, DISTURB ADJUSTMENT (1).

(10)

Repeat steps (8) and (9). If not satisfactory, change the propeller governor.

(11)

Disconnect the interconnect rod (6) from the airbleed link reset lever (5) and secure the lever to the minimum rear position.

(12)

With the propeller control lever in fine pitch, move power control lever to the maximum stop and record the propeller shaft speed (Np). Make sure that the Np is 5 ± 1% less than the speed recorded in Step (6). Adjust the pneumatic minimum adjustment (4) in increments to get the necessary propeller shaft speed (Np).

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11.

Fuel Control Unit Checks A.

Fuel Control Unit (FCU) Maximum Gas Generator Speed Setting (PT6A-34, -34B, -36) (1)

Although fuel control units are calibrated for maximum governing during a bench check (overhaul), the maximum gas generator speed setting should be checked after engine installation or component replacement. The part power trim stop (8, Fig. 506) is a movable spacer placed between the maximum Ng stop and the power lever anvil, and represents 1,700 rpm Ng speed decrement. This enables setting of the max. gas generator speed over a wide range of ambient conditions without exceeding engine limitations. After adjustments have been completed, the part power trim stop is returned to the stowed position on the FCU.

CAUTION:

DURING ADJUSTMENTS AND NORMAL OPERATION, MAKE SURE THAT ENGINE OPERATING LIMITS, AS SPECIFIED IN TABLES 503 AND 504 FOR ENGINE GROUND OPERATION, ARE NOT EXCEEDED.

CAUTION:

ON TWIN ENGINE INSTALLATIONS, COMPLIANCE WITH SB1368 OR SB1374, AS APPLICABLE, SHOULD BE DONE ON BOTH ENGINES SIMULTANEOUSLY, AS THE ALTERED POWER LEVER ANGLE/GAS GENERATOR SPEED RELATIONSHIP WILL OTHERWISE RESULT IN EXCESSIVE PLAY STAGGER.

(2)

Carry out the pre-start check (Ref. Para. 4.).

(3)

Position the part power trim stop (8) so as to limit power control lever travel.

(4)

Carry out satisfactory start (Ref. Para. 7.).

(5)

Advance the power control lever to the part power trim stop. Allow the engine to stabilize for a minimum of two minutes.

(6)

Check that the maximum gas generator speed (Ng) is 97.1% and adjust the gas generator speed stop (3) as required . (a) To adjust the Ng speed, proceed as follows: 1 Hold the speed stop (3) using a suitable Allen key to prevent screw turning. 2 Unlock the locknut (10). 3 Turn the speed stop (3) in increments of 1⁄8-turn, counterclockwise to increase or clockwise to decrease the Ng speed. 4 Holding the speed stop (3), tighten the locknut (10), 20 to 25 lb.in. 5 Recheck that the Ng is still within limits; repeat the adjustment as necessary.

(7)

Shut down the engine (Ref. Paras. 8. and 9.).

(8)

Stow the trim stop (8) and fasten the attachment screw (11) with lockwire.

(9)

Fasten the maximum speed stop screw (3) and locknut (10) with lockwire.

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B.

Fuel Control Unit (FCU) Gas Generator Speed Adjustment (PT6A-34AG) (Ref. Fig. 507) (1)

Although fuel control units are calibrated for maximum flow during a bench check (overhaul), the maximum Ng speed should be adjusted after engine installation or component replacement. The part power trim stop (8, Fig. 506) is a movable spacer placed between the maximum Ng stop and the power lever anvil, and represents a 1,700 rpm Ng speed increment. After adjustments have been completed, the part power trim stop is returned to the stowed position on the FCU. NOTE: The following checks should be done in conjunction with the procedure and charts detailed in the relevant aircraft maintenance manual.

CAUTION:

DURING ADJUSTMENTS AND NORMAL OPERATION, MAKE SURE THAT THE ENGINE OPERATING LIMITS ARE NOT EXCEEDED (REF. TABLE 503; OPERATING LIMITS FOR ENGINE GROUND OPERATION).

(2)

Using the correct values for ambient air temperatures and field barometric pressure (not corrected to sea level), determine the referenced torquemeter pressure (psi) from the chart (Ref. Fig. 507).

(3)

If the FCU has been replaced, or the fuel system lines disturbed, carry out a wet motoring run, followed immediately by a dry motoring run, to check the fuel system for leaks.

(4)

Unlock and slacken the part power trim stop attachment screw (11, Fig. 506). Move the part power trim stop (8) to the ‘‘in-use’’ position and secure by tightening the screw (11), 25 to 30 lb.in.

(5)

Start the engine and warm to operating temperatures (Ref. Para. 7.).

(6)

Gradually advance the power control lever as far as the part power trim stop. Allow the engine to stabilize at this setting for approximately five minutes with the propeller in fine pitch. NOTE: To reduce the noise level, the propeller pitch setting may be increased provided the torque limit is not exceeded. Engine stabilization is essential to avoid erroneous instrument readings.

(7)

Check that the maximum Ng speed is set at 97.1%, the ITT is not exceeded, and the torquemeter pressure is equal to or above the referenced pressure (Ref. (2)). If the ITT limit is exceeded, or the torquemeter pressure is below the referenced pressure at 97.1%, rectification is necessary prior to further flight.

(8)

To adjust the Ng speed, proceed as follows: (a) Hold the speed stop (3) using a suitable Allen key to prevent screw turning. (b) Unlock the locknut (10). (c) Turn the speed stop (3) in increments of 1⁄8-turn, counterclockwise to increase or clockwise to decrease the Ng speed. (d) While holding the speed stop (3), tighten the locknut (10), 20 to 25 lb.in.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

5

4

3 1

2

B

A

8 7 6 9 3 10 11 8 DETAIL

B DETAIL

A

C1315D Fuel Control Unit Adjustment Figure 506 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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Key to Figure 506 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11.

Acceleration Adjuster Dome Minimum Governing Speed Adjuster Maximum Ng Speed Stop (For breakdown, see Detail A) Idle Deadband Adjuster Rod End Clevis Fuel Bypass Bleed to Tank Starting Control - Interconnect Rod Part Power Trim Stop Staring Control Flight-Idle Adjustment Stop Locknut Attachment Screw (Part power trim stop)

(e) Recheck that the Ng is still within limits; repeat the adjustment as necessary. (9) (10) C.

Fasten the locknut (10) with lockwire. Slacken the screw (11), and return the part power trim stop (8) to its ‘‘stowed’’ position. Tighten the screw 25 to 30 lb.in., and fasten with lockwire.

Fuel Control Unit (FCU) Idle Speed Adjustments (1)

General (a) At barometric pressures equivalent to altitudes less than 3500 feet above sea level, the fuel flow is metered to maintain idle speed at a constant value, and is referred to as the minimum governing speed. However, since the fuel flow required to maintain a constant idle speed decreases with increasing altitude, a point is reached where the fuel flow does not decrease further, this point being the minimum fuel flow setting. At altitudes higher than this point, the gas generator speed increases proportionally with altitude. (b) Usually, the minimum fuel flow setting will be lower than the minimum governing speed. However, under marginal conditions, that is, when the altitude is close to or slightly higher than 3500 feet and/or barometric pressure is close to or slightly less than 25.2 in. Hg, the two speeds may coincide, or the Ng at minimum fuel flow may be higher than that at minimum governing. (c) From the preceding, it will be seen that idle speed adjustments should only be done at conditions of low altitude and/or high barometric pressure.

(2)

Minimum Governing (Idle) Speed Check (Ref. Fig. 506). CAUTION:

DO NOT PERFORM CHECKS AT BAROMETRIC PRESSURES BELOW 25.2 IN. Hg OR ALTITUDES IN EXCESS OF 3500 FT. CHECKS MUST BE DONE WITH ZERO POWER EXTRACTION.

(a) Carry out pre-start check (Ref. Para. 4.).

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Np = 2200 R.P.M., EXHAUST AREA = 88 IN.2 EFF.

60.0

BAR

OM

ETE

R3

1.0

29.9

2

INC

HES

28.0

OF

50.0

HG

26.0 24.0

40.0

22.0 20.0

30.0

18.0

TORQUE METER PRESSURE P.S.I.

TORQUE SETTING

70.0

20.0

10.0 760 I.T.T. C

NOT ACCEPTABLE °

740 720 ACCEPTABLE

700 −20

−10

0

10

20

30

40

50

O.A.T. ° C

C7967

PT6A-34AG Installed Engine Trim Chart Figure 507 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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(b) Carry out satisfactory start (Ref. Para. 7.). CAUTION:

IF INTERTURBINE TEMPERATURE (T5) RISES ABNORMALLY AT ANY TIME DURING IDLE SPEED, SHUT DOWN ENGINE IMMEDIATELY.

(c) Allow the engine to warm to operating temperatures, and instruments to stabilize at idle rpm. NOTE: Adjustments must be done under conditions representative of normal operation as instructed in relevant Aircraft Maintenance Manual (i.e., specified loads). (d) With the propeller in fine pitch and oil temperature at 38°C (100°F) minimum, observe the idle Ng. (e) If the Ng is 52.5% +1%, -0%, no further action is necessary. (f)

If the Ng is less than 52.5%, adjust the speed adjustment (2, Fig. 506) in a clockwise direction, as required, to achieve 52.5%, +1%, -0%.

(g) If Ng is more than 53.5%, adjust the speed adjustment (2, Fig. 506) in a counterclockwise direction, as required, to achieve 52.5%, +1%, -0%. (h) If there is no response to the adjustment made in (f) or (g) preceding, the fuel control unit must be replaced. (3)

Final Adjustments (a) Consult the applicable Aircraft Manufacturer’s Manual for specific instructions on final adjustments; in the absence of such instructions, carry out final checks and adjustments as follows: 1 Carry out a pre-start check (Ref. Para. 4.). 2 Carry out a satisfactory start (Ref. Para. 7.). 3 Allow the engine to warm up to operating temperature and stabilize to idle rpm.

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WARNING:

SHUT DOWN ENGINE BEFORE MAKING ANY ADJUSTMENTS ON ENGINE-MOUNTED EQUIPMENT. THIS IS ESSENTIAL DUE TO CLOSE PROXIMITY OF PROPELLER AND EXHAUST NOZZLES.

4 Advance the starting control lever slowly to flight idle position and check that the speed is within the required range. If the speed is incorrect, adjust the starting control flight idle max. stop (9) (Ref. Fig. 506 and Fig. 1, Chapter 73-10-04), as required. NOTE: 1. Adjust the stop counterclockwise to increase speed. NOTE: 2. It is permissible to adjust nut (4, Fig. 508) (Ref. Aircraft Maintenance Manual). D.

Manual Override System Static Check (PT6A-34/-34AG) (Ref. Fig. 509) NOTE: Para. 11.D. and E. apply only to engines incorporating the manual override system. (1)

As part of the periodic inspection (Ref. 72-00-00, INSPECTION, Periodic Inspection), check the static operation of the manual override system, with the engine shutdown: (a) Set cockpit Manual Override Control lever - OFF. Make sure the Manual Override lever on the FCU is in the OFF position (hard against its internal stop). (b) Set cockpit Manual Override Control lever to the maximum forward position. Make sure the cockpit Manual Override Control lever does not bind and the Manual Override Lever on the FCU contacts the stop at the MAXIMUM FLOW position. NOTE: Some resistance to movement of the cockpit Manual Override Control lever is normal. (c) If either stop is not reached, check/adjust the airframe rigging (Ref. Aircraft Maintenance Manual).

E.

Manual Override System Operational Check (PT6A-34/-34AG) CAUTION:

OTHER THAN THE FOLLOWING CHECK, USE OF THE MANUAL OVERRIDE SYSTEM IS RESTRICTED FOR EMERGENCIES ONLY.

CAUTION:

WHEN USING THE MANUAL OVERRIDE SYSTEM, THE ENGINE RESPONSE MAY BE MORE RAPID THAN WHEN USING THE POWER LEVER. A RAPID INCREASE IN MANUAL OVERRIDE LEVER POSITION TOWARDS MAXIMUM IS TO BE AVOIDED, AS THIS CAN CAUSE ENGINE SURGE, ENGINE OVER-TEMPERATURE, Ng OVER-SPEED OR OVER-TORQUE.

(1)

Following an FCU or engine change (Ref. 71-00-00, ADJUSTMENT/TEST, Table 501) or as part of an annual airframe zone inspection (Ref. Aircraft Maintenance Manual), check the serviceability of the manual override system:

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3

2

4

1

5

C71128 Fuel Control Unit Adjustment (Engines with Flow Divider Valve) Figure 508 (Sheet 1 of 2) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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Key to Figure 508 1. 2. 3. 4. 5.

Acceleration Adjuster Dome Flight-Idle Stop Cut-off and Flight-Idle Linkage Nut (ADJUSTABLE per Aircraft Maintenance Manual) Nut (NOT ADJUSTABLE)

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3

2 4 1

5

C80260 Fuel Control Unit Adjustment (Engines with Flow Divider Valve) Figure 508 (Sheet 2) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

1

2

CAUTION DO NOT ADJUST THIS SCREW

3 4

EACH SERRATION INDEXING OF LEVER EQUALS 15°

MAX. FLOW

30 °

60 ° 69 ° 30 ° ± 5 °

ACTIVE RANGE

99 ° ± 5 °

0 ° NORMAL FLOW

TOTAL TRAVEL PICK−UP POINT

NOTE FCU BELLOWS ACTUAL INEFFECTUAL THROUGHOUT THIS RANGE OF LEVER MOVEMENT

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Key to Figure 509 1. 2. 3. 4.

Stop Screw - Maximum Speed Shaft Stop Lever - Manual Override Control

(a) Do the Manual Override System static check (Ref. Subpara. D.). (b) Set Manual Override Control lever - OFF. (c) Start the engine (Ref. Para. 4. and 7.). (d) Fuel Condition lever - GROUND-IDLE. (e) Power Control lever - GROUND-IDLE. (f)

Slowly advance Manual Override Control lever observing ITT, torque and Ng at all times. Keep Ng maximum increase under 4% per second. NOTE: Some movement of the Manual Override Control lever, resulting in no increase in engine power, is normal.

(g) Slowly increase Ng until a 15% increase above ground-idle speed is obtained. This indicates proper functioning of the Manual Override System. (h) Slowly reduce the Manual Override Control lever to OFF, keeping Ng decrease less than 4% Ng per second. F.

Deceleration Check (Ref. Fig. 510) (1)

Do a check for ground idle speed (Ref. Para. 11.C.) and record in logbook.

(2)

With the engine still running, set to min. idle and let instruments stabilize for one minute minimum.

(3)

If equipped, make sure that the cockpit Manual Override Control lever is to the OFF position.

(4)

Set engine Ng speed to 85% and propeller speed to MAX and stabilize engine for ten seconds.

(5)

Slam decel the power control lever in less than one second to ground idle speed.

(6)

Note and record in logbook time to reach Ng of 60% or low idle speed, whichever comes first.

(7)

If deceleration time is more than the limit, contact P&WC.

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14

DECELERATION TIME (SEC.)

12 10 8 6 4 2 0 0 OR BELOW

2

4

6

8 ALTITUDE (kFt)

10

12

14

16

C228856 Deceleration Check Figure 510 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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12.

Oil Pressure Check A.

Procedure (1)

Start engine (Ref. Paras. 4. and 7.).

(2)

Run the engine at some convenient gas generator speed above 72% to stabilize the oil temperature within the operating range.

(3)

After instrument readings have stabilized, check that the oil pressure is within the limits specified in Tables 503, 504; operating limits for engine ground operation. If not, it may be necessary to adjust the quantity of spacers in the oil pressure relief valve (Ref. 72-60-00). NOTE: Do not exceed the maximum permitted quantity of six spacers.

13.

(4)

Shut down the engine (Ref. Para. 8.).

(5)

Adjust the oil pressure relief valve, if necessary, and repeat steps (1) through (4).

Engine Performance Check (Ref. Fig. 511) A.

General Engine Performance Checking Curve, Figure 511, enables engine performance to be checked, on the ground, over a wide range of ambient temperatures without overtorquing or overtemperaturing the engine. In addition to any in-flight condition monitoring checks that may be done, periodic ground performance checks should be done and changes in engine performance noted. All forms of engine deterioration are accompanied by an increase in interturbine temperature and fuel flow at a given power. Compressor deterioration is, in most cases, due to dirt deposits and causes an increase in gas generator speed at a given power setting. This form of deterioration can be remedied by field cleaning (Ref. CLEANING). NOTE: When checking performance, the information and figures given in the Aircraft Maintenance Manual for the particular power plant must be observed.

B.

Procedure (1)

Determine engine performance check parameters: (a) Obtain ambient air temperature in degrees Celsius. (b) Obtain field barometric pressure (not corrected to sea level) or field pressure altitude from the aircraft altimeter (set at 29.92 in.Hg). (c) From the appropriate engine performance checking chart (Ref. Aircraft Maintenance Manual), obtain the gas generator speed, maximum interturbine temperature, fuel flow and target torque pressure for ambient conditions. Record the values of these parameters.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PT6A-34AG (Gulfstream American G-164D)

C8472

Engine Performance Checking Curve Figure 511 (Sheet 1 of 9) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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* STATIC, INSTALLED, PROP SPEED = 2200 RPM THIS GRAPH IS NOT TO BE USED TO ACCEPT OR REJECT AN ENGINE REFERENCE ENGINE TORQUE

FIELD BARO

1500

PRESSURE (IN. HG)

31 29.92 29 28 27

1400 1300 1200

26 25

F U E L F L O W P P H

1100

24

REFERENCE ENGINE FUEL FLOW

31 29.92 29 28 27 26 25 24

400 350

F T * L B 105

300 REFERENCE GAS GENERATOR SPEED

100 95

750

N G %

90

800

D E G C

T O R Q U E

1000

450

100% NG = 37468 RPM

I T T

E N G I N E

REFERENCE INTERTURBINE TEMPERATURE

700 650 INSTALLATION LOSS ASSUMPTIONS CHARGE HEATING = 4.3 DEG. C INTAKE LOSS = 0.0007 SEC2/LB2 HP EXTRACTION = 1.3 HP EXHAUST AREA = 88 SQ. IN.

600

30P11863

−20

−10

0

10 20 30 40 OUTSIDE AIR TEMPERATURE DEG. C

50

PT6A-34AG (Air Tractor AT402B and AT502B)

60

C80525

Engine Performance Checking Curve Figure 511 (Sheet 2) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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C8474A1

PT6A-34 (I.A.I Arava) Engine Performance Checking Curve Figure 511 (Sheet 3) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OAT °C

C8474A2

PT6A-34 (I.A.I. Arava) Engine Performance Checking Curve Figure 511 (Sheet 4) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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STATIC − INSTALLED − NP = 2200 RPM 1800 SEA

TORQUE LB FT

1600

LEV

200 0 4000 Ft F 6000 t 8000 Ft 1000 Ft 0 12000 Ft Ft

1400 1200 1000

EL

800 600 500

WF − LB / HR

SEA 2000

LEVE

L

Ft

4000 Ft 6000 Ft 8000 F t 10000 Ft 12000 F T

400

300

200 − 40

− 30

− 20

− 10

0

10

20

30

40

50

60

OAT − ° C

CAUTION : THIS CHART NOT TO BE USED FOR FLIGHT POWER SETTINGS . CONSULT APPROPRIATE AIRCRAFT OPERATING MANUAL .

C10556A1

PT6A-36 (Beech C-99) Engine Performance Checking Curve Figure 511 (Sheet 5) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

12000 Ft 102 NG − %

100 98

0 Ft

1000

8000

Ft

SEA LEVEL TO 12000 Ft

Ft 6000 Ft 4000 t F 2000 VEL LE SEA

96 94 92

− INSTALLED − STATIC − Np=2200 RPM

90 12000 Ft 810 790

0 00

Ft

SEA LEVEL TO 12000 Ft

10

770

0 00

750

Ft

8

t

ITT − C

730 °

0F

0 60

710

t

0F

0 40

690

t

0F

0 20

670

A

SE

650

EL

V LE

CAUTION : THIS CHART NOT TO BE USED FOR FLIGHT POWER SETTINGS . CONSULT APPROPRIATE AIRCRAFT OPERATING MANUAL .

630 610 590 570 − 40

− 30

− 20

− 10

0

10

20

30

40

50

60

OAT − ° C

C10556A2

PT6A-36 (Beech C-99) Engine Performance Checking Curve Figure 511 (Sheet 6) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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C10979

PT6A-36 (I.A.I. Arava) Engine Performance Checking Curve Figure 511 (Sheet 7) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PT6A-34 (Frakes Turbo-Mallard)

C13415A1

Engine Performance Checking Curve Figure 511 (Sheet 8) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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STATIC INSTALLED − NPROP = 2200 rpm − PRESSURE ALTITUDE IN FEET 102

00

120

0

1000

100 NG (%)

98

92

8000 6000 4000 2000

90

SEA

790 780

12000

96 94

EL

LEV

760

0

00

740

10

720 ITT ( C)

700 °

00

80

680

00

660

60

640

00

620

40

600

20

00

THIS CHART NOT TO BE USED FOR FLIGHT POWER SETTINGS. CONSULT APPROPRIATE AIRCRAFT OPERATING MANUAL.

EL

580

A

SE

560 −40

V LE

−30

−20

−10

0

10

20

30

40

50

60

AMBIENT TEMPERATURE ( ° C)

PT6A-34 (Frakes Turbo-Mallard)

C13415A2

Engine Performance Checking Curve Figure 511 (Sheet 9) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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(2)

Check engine performance: (a) This check should be done without bleed air or power extraction for operation of aircraft ancillary. (b) Pre-start check (Ref. Para. 4.). (c) Implement a satisfactory engine start (Ref. Para. 7.). (d) Run at ground idle speed for 5 minutes to warm up engine. (e) Set the propeller control lever to the output speed as stated on the checking curve (Ref. Fig. 511) and the power control lever to the target torque setting previously determined from the performance checking curve. Allow sufficient warm-up time for engine instrumentation to stabilize. (f)

Record and compare the observed fuel flow, gas generator speed and interturbine temperature with the values previously recorded (Ref. Step (1)(c)).

(g) Make sure that the values observed during the engine performance check are within the following limits: 1 +15 lb/hr fuel flow. If fuel flow is more than 75 lb/hr below the chart value, check instrumentation. 2 Maximum interturbine temperature line is not exceeded. If the temperature is more than 75°C (167°F) below the target temperature, check instrumentation. NOTE: The limits shown on the curve are for normal engine deterioration, but deviations should not necessarily be the basis for engine rejection until all possible troubleshooting has been completed (Ref. 72-00-00). (h) It is desirable to keep records of the preceding checks and thus monitor engine performance. NOTE: 1. The preceding check should not be confused with the principles and purpose of Engine Condition Trend Monitoring System (Ref. 72-00-00, MAINTENANCE PRACTICES). NOTE: 2. The following applications to Figure 511, have been allocated to specific airframe installations. Other applications will be assigned when required. 1 PT6A-34AG (Gulfstream American G-164D) 2 PT6A-34AG (Air Tractor AT402B and AT502B) 3 PT6A-34 (I.A.I. Arava) 4 PT6A-36 (Beech C-99)

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5 PT6A-36 (I.A.I. Arava) 6 PT6A-34 (Frakes Turbo-Mallard) 14.

Acceleration Adjustments A.

Procedure (Ref. Fig. 506) CAUTION: (1)

Manual Override Control Lever - OFF .

(2)

Start the engine (Ref. Paras. 4.and 7.). Operate at ground idle for five minutes to allow stabilization of temperatures.

(3)

Set the Ng to High Idle.

(4)

Rapidly (in less than one second), move the power control lever to maximum.

(5)

Note and record time required for the Ng to reach 93.5%.

(6)

Immediately when the Ng passes through 93.5%, retard the power control lever to an idle setting.

CAUTION:

(7)

15.

DO NOT USE MANUAL OVERRIDE TO CHECK ACCELERATION.

IF AN ACCELERATION CHECK IS DONE AFTER A COMPRESSOR RUNNING WASH, CHECK THE P3 FILTER/FORWARD AIR TUBE FOR CONTAMINATION/BLOCKAGE. DO NOT ADJUST THE FCU.

Acceleration time should be 2.5 to 4.0 seconds. If not, rotate the acceleration adjuster dome (1, Fig. 506) one click at a time until requirement is met. Rotate the dome clockwise to reduce acceleration time (faster acceleration), or counterclockwise to increase acceleration time (slower acceleration). If requirement cannot be met within a maximum of three clicks, replace the fuel control unit (Ref. 73-20-00).

Torquemeter Function Test A.

Procedure (1)

Determine and record field barometric pressure (pressure altitude (ft)). NOTE: Pressure altitude (PA) can be obtained by contacting local flight service for uncorrected pressure reading, or by setting altimeter to 29.92 Hg. Position of needle indicates pressure altitude in feet. Do not use sea level pressure.

(2)

Determine and record indicated outside air temperature (IOAT) in degrees Celsius. NOTE: To make sure result of torquemeter function test is accurate, determine and record IOAT immediately before engine start. Use IOAT value recorded to determine take-off torque (Ref. Step (3)).

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16.

(3)

Use the flight manual chart to determine the take-off torque (target torque) at which to set the engine using pressure altitude (ft) and IOAT recorded at step (1) and step (2) respectively. Record the value.

(4)

Start the engine.

(5)

Switch off the generator, bleed air and the air conditioning.

(6)

Check propeller control lever is in high rpm.

(7)

Check oil temperature is above 60 °C.

(8)

Set Ng 500 rpm above GROUND-IDLE (Ref. Operating Limitations).

(9)

Record Ng, Np and engine torque (Tq).

(10)

Accelerate engine slowly and uniformly at a rate of 2000 rpm per second until target torque recorded at step (3) is reached.

(11)

Allow engine to stabilize for two minutes.

(12)

Reduce Ng slowly and uniformly at a rate of 2000 rpm per second to Ng set at Step (8).

(13)

Record Ng, Np and Tq.

(14)

Repeat steps (10) to (13).

(15)

Reduce Ng to GROUND-IDLE.

(16)

Shutdown engine (Ref. Para. 8.).

(17)

The engine torque indication system functions correctly when the difference between Tq recorded in steps (9), (13) and (14) is equal to or less than 150 lb.ft.

(18)

If the difference between the torque readings is in excess of 150 lb.ft. , check the aircraft indication system. If the aircraft indicating system check is satisfactory, the power section is recommended to be removed and the torquemeter piston, cylinder and servo valve inspected at an authorized facility for excessive wear, scoring, fretting, etc.

Bleed Valve Closing Check (Post-SB1683) A.

Procedure (Ref. Fig. 512 and 513) CAUTION: (1)

MAKE SURE THAT THE BOV CAN OPERATE WITHOUT INTERFERENCE FROM THE PROBE.

Install thermocouple (PWC50933-02) or (PWC50933-04) (1) on the BOV. NOTE: It is recommended to remove the ‘‘L’’ shaped bracket from the thermocouple and to attach the thermocouple to the BOV with the clamp provided with thermocouple.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

(2)

Connect the thermocouple connector to a multimeter which has a 50 mV full scale deflection, or to Fluke temperature readout or to a Barfield tester.

(3)

Set the cabin bleed air switch to OFF.

(4)

Start the engine (Ref. Para. 7.) and slowly increase power up to MAX. NOTE: Make sure that the multimeter shows a reading, which gradually decreases and becomes stable as full power is applied.

(5)

Slowly reduce power until the multimeter or the temperature indicator just begins to indicate an increase in voltage or in temperature (BOV closing point).

(6)

Record the values of Ng and OAT at this point.

(7)

Reduce power to IDLE and shut down the engine (Ref. Para. 8.).

(8)

Plot the value of Ng at measured OAT as recorded in the above step (6) (Ref. Fig. 513).

(9)

Adjust the BOV closing point, as required and repeat steps (3) thru (8), in order that Ng at BOV closing point falls within the guide lines (Ref. Fig. 513). (a) Loosen lock screw (3). (b) Turn the adjustment screw (4) until Ng falls within the guide lines shown (Ref. Fig. 513). NOTE: The closing point is adjusted by rotation of the adjustment screw (4) (Ref. Fig. 512). A 60 degree clockwise rotation (i.e. one flat of the hexagonal adjustment screw) leads to an increase of Ng closing point of approximately 2%. (c) Lock the variable orifice by torque the small self locking screw (3) to 5 to 6 lb.in. (Size 3/32 in.).

(10)

When bleed valve closing point is within limits, check engine performance.

(11)

Remove the thermocouple (PWC50933-02) or (PWC50933-04) (1) from the BOV.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

1

2

THERMOC0UPLE AND BOV INSTALLATION

3

4

BOV ADJUSTMENT

C173054

(PT6A-34) Thermocouple-BOV Installation and BOV Adjustment Figure 512 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

Key to Figure 512 1. 2. 3. 4.

Thermocouple (PWC50933-02 or PWC50933-04) Compressor Bleed Valve Locking Screw BOV Adjustment Screw

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

100

98

96

Ng (%)

94

92

90

88 WH

EN

J AD

US

T

ING

BO

V,

T SE

WI

T

HIN

TH

I

A SB

ND

86

84

82

−20

0

20

40

60

80

100

120

OUTSIDE AIR TEMPERATURE (DEG. F)

C69738

(PT6A-34) Compressor Bleed Valve Closing Point (Post-SB1683) Figure 513 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

POWER PLANT - CLEANING 1.

General A.

2.

Engine cleaning procedures describe the compressor desalination wash, compressor performance recovery wash, compressor turbine desalination wash, fuel nozzle cleaning, and engine external wash.

Consumable Materials The consumable materials listed below are used in the following procedures.

3.

Item No.

Name

PWC05-005 PWC05-053 PWC05-073 PWC11-001 PWC11-003 PWC11-003B PWC11-014 PWC11-027 PWC11-031 PWC15-011 PWC15-015

Emulsifier Plastic Sheet Water, Demineralized Cleaning Alkaline Cleaner, Detergent Cleaner, Detergent Alcohol, Isopropyl Solvent, Petroleum Cleaner, Engine Corrosion-Inhibiting Solution Corrosion-Inhibiting Solution

Special Tools The special tools listed below are used in the following procedures.

4.

Tool No.

Name

PWC32271 PWC32677-100 PWC32677-300

Tube, Spray Washcart, Compressor Washcart, Compressor/Fuel Nozzles

Fixtures, Equipment and Supplier Tools The fixtures, equipment and supplier tools listed below are used in the following procedures. Name Shut off Valve Pressure Gauge Steel Tank Steel Tubing Nitrogen or Compressed Air Pressure Gauge Adapter Test Rig Adapter

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Name Shut off Valve 5.

Engine Washing A.

General

CAUTION:

MAKE SURE THE P3 LINE TO THE FILTER AND FCU IS DISCONNECTED BEFORE PERFORMING A MOTORING COMPRESSOR WASH TO AVOID CONTAMINATION. CONTAMINATION MAY HAVE AN ADVERSE EFFECT ON ENGINE POWER AND HANDLING.

Depending on the operating environment and the types of deposits in the engine gas path, the following methods can be used to remove salt or dirt and other baked-on deposits that accumulate over a period of time and cause engine performance deterioration and as well as corrosion or sulphidation (Ref. 72-00-00, ENGINE - INSPECTION). B.

Types of Internal Wash NOTE: Internal Engine washes must be done during motoring. They are done at 10 to 25% Ng and water or cleaning mixture, depending on ambient temperature (Ref. Table. 702), is injected into engine intake at a rate of 2 to 3 gal/minute (7.6 to 11.3 l/minute). Washing during a motoring cycle makes sure emulsion fluid remains in liquid form. Compressor Desalination Wash: This wash is used to remove salt deposits. Light dirt deposits may also be removed by this wash. The wash fluid is drinking quality water, provided minimum standards are met (Ref. Para. E.). Use either an installed compressor wash ring or a hand held wash wand to inject water into the engine intake. Ref. Para. 6. A. for the complete procedure. Compressor Performance Recovery Wash: This wash is used to remove more stubborn deposits which cannot be removed during normal desalination washes. The wash fluid includes approved chemical additives (Ref. Table. 702). This wash must only be done when engine performance loss is noticeable or trend monitoring dictates. Ref. Para. 6. B. for the complete procedure. External Engine Wash: This wash is used as an effective method of tracing oil leaks and as well as removing salt and other environmental contaminants from the engine external surfaces. The wash fluid is drinking quality water, provided minimum standards are met (Ref. Para. E.). Ref. Para. 7. for the complete procedure.

C.

Wash Schedule Recommendations Depending on the operating environment, the nature and frequency of engine washes are recommended in accordance with Table 701.

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TABLE 701, Wash Schedule Recommendations Environment

Wash

Frequency

Remarks

Continuously salt laden

Desalination (Compressor and CT) and External Engine Wash

Daily

Strongly recommended after last flight of day.

Occasionally operated in salt-laden or harsh environment

Desalination (Compressor and CT) and External Engine Wash

Weekly

Strongly recommended. Adjust interval to suit engine condition.

All

Performance Recovery (Compressor only)

As required

Strongly recommended. Performance recovery washes are required less frequently. Adjust frequency to suit engine operating conditions as indicated by ECTM. Motoring wash for light soiling and multiple motoring washes for heavy soiling is recommended.

NOTE: 1. Multiple motoring washes should be done to the extent permitted by starter operating limitations. Observe starter cooling period (Ref. Starter Manufacturer’s Manual). NOTE: 2. This Table covers the normal requirements of general aviation and does not specifically consider the peculiar frequency requirements of engines operating in an agricultural environment. NOTE: 3. Harsh environment includes dusty, sandy or heavy polluted environments such as those near to the industrial smog or active volcanoes. NOTE: 4. Continually salt-laden or harsh environment also includes salt flats. D.

Preparation of Solutions Five liters (1.33 U.S. gal.) of cleaning mixture and ten liters (2.66 U.S. gal.) of rinse solution are required. The solution formulation is dependent upon prevailing ambient temperature and must be prepared in accordance with Table 702 for cleaning, and Table 703 for rinsing .

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TABLE 702, Cleaning Solution Formulation

Ambient Temperature

Cleaning Agent ( NOTE 1)

Aviation Kerosene (NOTE 2)

Isopropyl Alcohol

Water (NOTE 3)

°C

% by vol.

% by vol.

% by vol.

% by vol.

°F

Typical mixture proportions using B & B 3100 (PWC11-001C) or TC-100 (PWC11-003E), at amb. temp. of -25°C to +2°C: (Similar proportions for Magnus 1214 (PWC11-001B), R-MCS (PWC11-001D), R-MC G21 (PWC11-001E), ALMON AL-333 (PWC11-001A), TURCO 5884 (PWC11-001G) and CLIX (PWC11-001). +2 Up

+36 Up

25

Nil

Nil

75

-25 to +2

-12 to +36

25

15

20

40

Below -25

Below -12

25

15

40

20

Example 1. (at +2°C): B & B 3100 25% by vol. = 1250 ml in 5 liters (1.33 US Gallons) Kerosene 15% by vol. = 750 ml Isopropyl Alcohol 20% by vol. = 1000 ml Water 40% by vol. = 2000 ml Total 100% by vol. = 5000 ml or 5 liters (1.33 US Gallons) Typical mixture proportions using Turco 4217 (PWC11-001F) or Ardrox 624 (PWC11-001H). +2 Up

+36 Up

4

40

Nil

56

-25 to +2

-12 to +36

4

40

20

36

Below -25

Below -12

4

40

36

20

Example 2. (at +2°C): Turco 4217 4% by vol. = 200 ml in 5 liters (1.33 US Gallons) Kerosene 40% by vol. = 2000 ml Isopropyl Alcohol 0% by vol. = 0 ml Water 56% by vol. = 2800 ml Total 100% by vol. = 5000 ml or 5 liters (1.33 US Gallons) Typical mixture proportions using Ardrox 6345 (PWC11-003) or Ardrox 6367 (PWC11-003B), Turboclean 2 (PWC11-003C) and ZOK 27 (PWC11-003D) +5 Up

+41 Up

20

Nil

Nil

80

-5 to +5

+23 to +41

20

Nil

20

60

-21 to -5

-6 to +23

20

Nil

30

50

Below -21

Below -6

20

Nil

40

40

Example 3. (at +5°C): Zok 27 20% by vol. = 1000 ml in 5 liters (1.33 US Gallons)

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TABLE 702, Cleaning Solution Formulation (Cont’d)

Ambient Temperature

Cleaning Agent ( NOTE 1)

Aviation Kerosene (NOTE 2)

Isopropyl Alcohol

Water (NOTE 3)

°C

% by vol.

% by vol.

% by vol.

% by vol.

°F

Isopropyl Alcohol 0% by vol. = 0 ml Water 80% by vol. = 4000 ml Total 100% by vol. = 5000 ml or 5 liters (1.33 US Gallons) NOTE: 1. Use any cleaning agent listed (Ref. CONSUMABLE MATERIALS). Solution strength must be in accordance with manufacturer/supplier’s recommendations. Where no specific instructions are provided, proportion of cleaning agent should be as indicated. NOTE: 2. Use of emulsifying agent (PWC05-005A), 3% by vol. or 150 ml in 5 liters is highly recommended to prevent possibility of kerosene separation. NOTE: 3. Drinking quality water is permissible for motoring wash procedures. TABLE 703, Rinse Solution Formulation Ambient Temperature °C

°F

+2 up

+36 up

-25 to +2 Below -25

Water ( See NOTE)

Isopropyl Alcohol

% by vol.

% by vol.

100

-

-12 to +36

50

50

Below -12

40

60

NOTE: 1. Drinking quality water is permitted. Refer to Equipment Required for acceptance criteria. E.

Equipment Required (Ref. Figs. 701, 702 and 703)

CAUTION:

DO NOT USE ANY RESTRICTOR WHEN THE MOTORING WASH IS DONE.

NOTE: Some engines have a built-in, 50-hole, deluge washing ring as standard installation feature. (1)

Wash wand (Ref. Fig. 702) or wash ring (Ref. Fig. 703). Flow rate 2 to 3 gpm (U.S.) (7.57 to 11.33 l/min).

(2)

Wash cart (PWC32677-100)or (PWC32677-300), optional locally manufactured wash rig (Ref. Fig. 701) comprising the following: (a) Two stainless steel tanks, 5 gallon (U.S.) (19 liters) capacity, each capable of withstanding up to 50 psig (345 kPa) working pressure. (b) Mechanical agitator, or recirculation pump with relief valve, for mixture agitation.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

MECHANICAL AGITATOR

PRESSURE GAGE

CLEANING SOLUTIONS/STEEL TANK 5 U.S. GALS. (19 LITERS) CAPACITY WORKING PR. 50 P.S.I. (345 kPa)

AIR SUPPLY VALVE

VALVE

SHUT−OFF VALVE

VALVE RELIEF VALVE TO SPRAY RING OR WASH WAND CONNECTION

AIR / NITROGEN PRESSURE SOURCE REGULATED UP TO 50 P.S.I. (345 kPa)

RECIRCULATION PUMP

AIR SUPPLY VALVE

RINSE SOLUTION TANK 5 U.S. GALS. (19 LITERS) CAPACITY WORKING PR. 50 P.S.I. (345 kPa) S/STEEL

SHUT−OFF VALVE

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

FWD 17 HOLES 1/16 DIA. DRILL, EQUALLY SPACED

LENGTH AND ANGLE OF THIS PORTION TO BE DETERMINED BY AIRCRAFT INSTALLATION

10° SECTION A−A

SOLDER

SOLDER

SOLDER

SOLDER

STD. 1/2 DIA. FEMALE HOSE CONNECTION

6

A

DIMENSIONS ARE IN INCHES

3

A

SOLDER DIRECTION OF SPRAY

12 10°

ALL FITTINGS ARE STD. 1/2 DIA. TEES, ELBOWS & CAPS MATERIAL 1/2 DIA. HARD DRAWN COPPER PIPE

STANDARD 1/2 DIA. HOSE CONNECTION

B B

STANDARD 1/2 CAP

45°

5

17 HOLES 1/16 DIA. EQUALLY SPACED TO SPRAY RADIALLY INWARD

16"

8.5 R. TO FIT SCREEN

SECTION

ALTERNATE CONFIGURATION

B−B

DIMENSIONS ARE IN INCHES MATERIAL: 1/2 DIA. SOFT COPPER WATER PIPE

NOTE : THIS SKETCH IS INTENDED AS A GUIDE ONLY. ALL DIMENSIONS ARE APPROXIMATE AND ALTERNATE MATERIALS MAY BE USED AS AVAILABLE.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

MS 24402−6 TEE DO NOT USE RESTRICTOR 30 ° 40 ° 35 °

50 °

20 °

20 ° 25 °

14°

14°

30 ° 40 °

25 °

35 °

45 °

55 °

55 °

65 °

70 ° 80 °

65 °

75 °

A

90 °

8.640" R. (REF.)

A

95 °

110 °

80 °

85 °

90 °

95 ° 100°

105 °

105°

8.640" R. (REF.)

110°

115 °

130 °

70 °

75 °

85 °

100 °

50 °

45 °

115°

135 ° 140 °

135° 145 °

130°

145° 140°

150 °

150° 0.052−0.057 DIA. 50 HOLES LOC. WITHIN 0.030 R. OF TRUE POS.

EXISTING 6 HOLES ADDITIONAL 44 HOLES DO NOT BREAK SHARP EDGES UNSCREW RING−HALVES AT TEE, FLUSH TO REMOVE SWARF, AND REASSEMBLE. SECTION

20 °

A−A C5383

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(c) Two flow control valves, for use with recirculation pump. (d) Two air supply shut-off valves. (e) Two fluid delivery shut-off valves. (f)

One pressure gage located in air delivery line.

(g) Suitable tubing to interconnect components. NOTE: Valve and tubing connections are to be 5/16-inch (8 mm) ID minimum (Ref. TOOLS/FIX/EQUIP). (3)

Compressed air or nitrogen supply, regulated up to 50 psig (345 kPa).

(4)

A source of demineralized water (PWC05-073) to the following specifications: (a) Appearance: free of suspended solids. (b) Total solids: 10 ppm (mg/l) Max. (c) Specific conductance: 11 micro-mho/cm Max. (d) Silica content: 3 ppm (mg/l) Max. (e) pH value: 5.0 to 7.5 inclusive. (f)

(5)

Intake filter not coarser than 10 microns.

Drinking quality water criteria: (a) Appearance: free of visible extraneous impurities. (b) Total solids: 175 ppm (mg/l) Max. (c) pH value: 6.0 to 8.0 inclusive. (d) Chlorides: 15 ppm (mg/l) Max. (e) Sulfates: 10 ppm (mg/l) Max. NOTE: Drinking water quality varies according to location and season; these specifications are provided as a guide only.

6.

Engine Motoring Washes A.

Compressor Desalination Wash NOTE: P&WC recommends to do a compressor turbine desalination wash after the compressor desalination wash for salt-laden or harsh environment, since the compressor desalination wash will transfer salt deposits into the turbine (Ref. SIL No. PT6A - 206).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

(1)

Depending on the ambient temperature, fill wash tanks with the appropriate solution (Ref. Table 702). Alternatively, connect suitable hose to drinking water tap for ambient temperature above +2°C (+36°F).

(2)

Connect compressed air regulated to 30 to 50 psig (207 to 345 kPa) to wash tanks. If tap water is used, connect through centrifugal pump if water pressure is below 30 psig (207 kPa).

(3)

Remove or open engine cowlings, as applicable, to expose the engine inlet screen and install the wash wand or modified wash ring (Ref. Figs. 702 and 703).

(4)

Connect the wash ring or wand to the pressurized tanks, or to the drinking water tap as applicable. NOTE: To prevent the precipitation of deposits due to the use of ‘‘hard’’ water, allow the engine to cool below 65°C (150°F). The minimum duration for engine cooling is 40 minutes since the last operation.

CAUTION:

CONTAMINATION/BLOCKAGE OF THE FCU PNEUMATIC SECTION, OR THE P3 FILTER WILL AFFECT ENGINE HANDLING. REMOVE THE AIR TUBE FROM THE ENGINE BEFORE PERFORMING A MOTORING WASH IF SB1495 IS NOT INSTALLED.

CAUTION:

FOR PRE-SB1495 ENGINES: SPECIAL CARE SHOULD BE TAKEN WHEN A COMPRESSOR WASH IS DONE TO MAKE SURE THAT THE P3 LINE IS COMPLETELY REMOVED TO AVOID BENDING STRESS OF ONE COUPLING.

(5)

For Pre-SB1495 Engines: Remove forward P3 air tube (Ref. 73-10-07) from engine to prevent distortion of tube. NOTE: For Post-SB1495 Engines: Removal of the forward P3 air tube is not required as the drain valve installed in the P3 filter cover will drain remaining fluids.

(6)

Make sure the ignition switch and aircraft bleed air are OFF.

CAUTION:

(7)

Motor engine (starter only).

CAUTION:

(8)

DO NOT MOTOR FOR MORE THAN 30 SECONDS; OBSERVE THE STARTER COOLING PERIOD (REF. STARTER MANUFACTURERS MANUAL). WHEN USING A WATER/ALCOHOL SOLUTION, PERFORM AN ADDITIONAL 30-SECOND DRY MOTORING RUN BETWEEN STEPS (10) AND (11) FOLLOWING, TO PURGE THE ENGINE OF VOLATILE FUMES. MAKE SURE THE PRESCRIBED STARTER COOLING PERIOD IS ALLOWED FOLLOWING THIS ADDITIONAL STEP.

DO NOT SPRAY WASH MIXTURE OR WATER INTO THE ENGINE INTAKE AT A RATE MORE THAN THREE GALLON/MINUTE (11.3 LITER/MINUTE) TO PREVENT FCU CONTAMINATION.

When the Ng reaches 5% minimum, inject the wash mixture or water into the engine at a rate of two to three gallon/minute (7.6 - 11.3 liter/minute).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

(9)

Stop motoring after 30 seconds.

(10)

Shut off the cleaning solution supply as soon as the Ng falls to 5%.

(11)

Observe the starter cooling period (Ref. Starter Manufacturers Manual).

(12)

Remove the wash wand or ring from the inlet screen. Reinstall or close the engine cowlings.

(13)

For Pre-SB1495 Engines: Install the front air tube (Ref. 73-10-07). NOTE: It is important to make sure all solid P3 lines are properly and correctly fitted before the coupling nuts are tightened. The coupling nuts should be seated without the use of tools (finger tight) before torquing. The installation of any pipe brackets should not distort the pipe in any way.

B.

(14)

Start the engine (Ref. ADJUSTMENT/TEST). Run the engine at 80% Ng for one minute or more to completely dry the engine and check for zero air leakage at the reinstalled coupling nuts on the P3 forward air tube. Check engine acceleration (Ref. ADJUSTMENT/TEST).

(15)

Shut down the engine (Ref. ADJUSTMENT/TEST).

Compressor Performance Recovery Wash (Ref. Fig. 701) NOTE: P&WC recommends to do a compressor turbine desalination wash after the compressor performance recovery wash for salt laden environment, since the compressor performance recovery wash will transfer salt deposits into the turbine (Ref. SIL No. PT6A - 206). (1)

Depending on the ambient temperature, fill the wash tanks with the appropriate cleaning solution (Ref. Table 702) and rinse solution (Ref. Table 703) in separate tanks.

(2)

Connect the compressed air supply, 30 to 50 psig (207 to 345 kPa), to wash tanks.

(3)

Remove or open the engine cowlings, as applicable, to expose the engine inlet screen and install the wash ring or wand.

(4)

Connect the wash ring or wand, as applicable, to the pressure tanks. NOTE: To prevent the precipitation of deposits due to the use of ‘‘hard’’ water, allow the engine to cool below 65 °C (150 °F). The minimum duration for engine cooling is 40 minutes since the last operation.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

CAUTION:

CONTAMINATION/BLOCKAGE OF THE FCU PNEUMATIC SECTION, OR THE P3 FILTER WILL AFFECT ENGINE HANDLING. REMOVE THE AIR TUBE FROM THE ENGINE BEFORE PERFORMING A MOTORING WASH IF SB1495 IS NOT INSTALLED.

CAUTION:

FOR PRE-SB1495 ENGINES: SPECIAL CARE SHOULD BE TAKEN WHEN A COMPRESSOR WASH IS DONE TO MAKE SURE THAT THE P3 LINE IS COMPLETELY REMOVED TO AVOID BENDING STRESS OF ONE COUPLING.

(5)

For Pre-SB1495 Engines: Remove forward P3 air tube (Ref. 73-10-07) from engine to prevent distortion of tube. NOTE: For Post-SB1495 Engines: Removal of the forward P3 air tube is not required as the drain valve installed in the P3 filter cover will drain remaining fluids.

(6)

Make sure the ignition and aircraft bleed air are OFF.

CAUTION:

(7)

DO NOT MOTOR FOR MORE THAN 30 SECONDS; OBSERVE THE STARTER COOLING PERIOD (REF. STARTER MANUFACTURERS MANUAL). WHEN USING A WATER/ALCOHOL SOLUTION, PERFORM AN ADDITIONAL 30-SECOND DRY MOTORING RUN BETWEEN STEPS (13) AND (14) FOLLOWING, TO PURGE THE ENGINE OF VOLATILE FUMES. MAKE SURE THE PRESCRIBED STARTER COOLING PERIOD IS ALLOWED FOLLOWING THIS ADDITIONAL STEP.

Motor the engine (starter only).

CAUTION:

AGITATE THE SOLUTION THOROUGHLY PRIOR TO INGESTION AND DURING THE WASH CYCLE, THUS PREVENTING SEPARATION OF THE KEROSENE. PREFERABLY, THE USE OF WITCONATE AS AN EMULSIFYING AGENT, OR ALTERNATIVELY, THE USE OF A MECHANICAL AGITATOR OR RECIRCULATION PUMP WITH A RELIEF VALVE (REF. FIG. 701) IS STRONGLY RECOMMENDED.

CAUTION:

DO NOT SPRAY CLEANING SOLUTION INTO THE ENGINE INTAKE AT A RATE MORE THAN THREE GALLON/MINUTE (11.3 LITER/MINUTE) TO PREVENT FCU CONTAMINATION.

(8)

When the Ng reaches 5%, inject the cleaning solution into the engine at a rate of two to three gallon/minute (7.6 - 11.3 liter/minute).

(9)

Stop motoring after 30 seconds.

(10)

Shut off the cleaning solution supply as soon as the Ng falls to 5%.

(11)

Allow the cleaning solution to soak for 15 to 30 minutes.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

CAUTION:

DO NOT SPRAY RINSE SOLUTION INTO THE ENGINE INTAKE AT A RATE MORE THAN THREE GALLON/MINUTE (11.3 LITER/MINUTE) TO PREVENT FCU CONTAMINATION.

(12)

Motor the engine. When the Ng reaches 5%, inject the rinse solution into the engine (half quantity only) at a rate of two to three gallon/minute (7.6 - 11.3 liter/minute).

(13)

Observe the starter cooling period. (Ref. Starter Manufacturers Manual).

(14)

Repeat step (12) observing the starter limitations.

(15)

Remove the wash ring or wand from the inlet screen.

(16)

For Pre-SB1495 Engines: Install the front air tube (Ref. 73-10-07). NOTE: It is important to make sure all solid P3 lines are properly and correctly fitted before the coupling nuts are tightened. The coupling nuts should be seated without the use of tools (finger tight) before torquing. The installation of any pipe brackets should not distort the pipe in any way.

7.

(17)

Switch the ignition ON and start the engine (Ref. ADJUSTMENT/TEST). Run the engine at 80% Ng for one minute or more to completely dry the engine. Check for zero air leakage during the drying cycle. Check engine acceleration.

(18)

Shut down the engine (Ref. ADJUSTMENT/TEST).

(19)

Install or close the cowling (Ref. Aircraft Maintenance Manual).

Engine External Wash A.

General

CAUTION:

DO NOT USE GASOLINE OR SIMILAR TOXIC SUBSTANCES FOR EXTERNAL ENGINE CLEANING.

CAUTION:

DO NOT ATTEMPT TO WASH AN ENGINE THAT IS STILL HOT OR RUNNING. LET ENGINE COOL FOR A MINIMUM OF 40 MINUTES AFTER SHUTDOWN.

Fresh water external washing is very effective in tracing possible origin of external oil leakage, and is recommended when the engine is contaminated with salt or corrosive chemicals such as those found in industrial smog. Demineralized water is not necessary. The engine should never be left in a contaminated condition overnight, or longer. For engine operations in corrosive environments it is recommended to perform an external engine wash per the schedule in Table .701 . NOTE: When you operate the engine in salt-laden or harsh environment, apply corrosion inhibitor on the external components for more protection (Ref. 72-00-00, ENGINE - INSPECTION).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

2 1

A

RGB

VIEW

3

A

C41708 Removal/Installation Compressor Turbine Wash Tube Connection (Typical) Figure 704 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

Key to Figure 704 1. 2. 3.

Igniter/Glow Plug Gasket Tube Sprayer (PWC32271)

If water wash is ineffective, a petroleum solvent (varsol/water emulsion), (PWC11-027) or (PWC11-031), may be used to remove oil and grime. Thoroughly rinse with water to remove all traces of cleaning fluid. Completely dry the engine using clean, dry compressed air. 8.

Compressor Turbine Wash A.

General This is a method for washing compressor turbine blades, while installed in the engine, to alleviate sulphidation attack and salt deposits. Water or water/alcohol, depending upon ambient temperatures (Ref. Table 702), is used to wash the compressor turbines. Depending on the operating environment, the nature and frequency of wash carried out are recommended to be in accordance with Table 701 . Approximately 1.90 liters (0.5 U.S. gallon) will pass through the compressor turbine during a 30-second motoring wash cycle.

B.

Equipment For equipment required for a motoring wash, reference Para. E.. The wash tube assembly (PWC32271) is designed to introduce the wash solution directly to the compressor turbine blades.

C.

Compressor Turbine Wash Method (1)

Depending on the ambient temperature, fill the wash tank with the appropriate mixture (Ref. Table 702). Alternatively, at temperatures above 2°C (36°F) use a suitable hose connected to a drinking water supply.

(2)

Connect the compressed air or nitrogen supply, regulated to 30 to 50 psig (207 to 345 kPa) to the wash tanks. If drinking water is used, connect through a centrifugal pump if water pressure is below 30 psig (207 kPa).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

WARNING:

RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. MAKE SURE THAT THE IGNITION IS SWITCHED OFF. ALWAYS DISCONNECT THE COUPLING NUTS AT THE IGNITION EXCITER FIRST. ALWAYS USE INSULATED TOOLS TO REMOVE THE COUPLING NUTS. DO NOT TOUCH THE OUTPUT CONNECTORS OR COUPLING NUTS WITH BARE HANDS.

(3)

Remove the most accessible igniter (1, Fig. 704) and the gasket (2) (Ref. 74-20-00, IGNITION CABLES AND SPARK IGNITERS - MAINTENANCE PRACTICES) or the glow plug and the gasket (Ref. 74-20-02, GLOW PLUGS MAINTENANCE PRACTICES).

(4)

Install the compressor turbine wash tube assembly (3) fingertight in the igniter port. Make sure the arrow and ‘‘RGB’’ on the tang point toward the reduction gearbox and the tang is parallel with the engine centerline.

CAUTION: (5)

SUPPORT THE DELIVERY HOSE TO PREVENT DAMAGE TO THE SPRAY TUBE.

Connect the pressurized tank or drinking water supply to the wash tube assembly. NOTE: A minimum cool-down period of 40 minutes should be observed after the engine run. Engine temperature must be below 65 °C (150 °F) to make sure that inadvertent use of hard water does not result in the precipitation of deposits.

(6)

Make sure the ignition and aircraft bleed air are OFF.

CAUTION:

(7)

DO NOT MOTOR THE ENGINE FOR MORE THAN 30 SECONDS; OBSERVE THE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL).

Do a dry motoring run (Ref. ADJUSTMENT/TEST).

CAUTION:

WHEN USING A WATER/ALCOHOL SOLUTION, DO AN ADDITIONAL DRY MOTORING RUN TO PURGE THE ENGINE. OBSERVE THE STARTER LIMITS.

(8)

When the Ng reaches 5%, inject the water or water/alcohol as applicable, into the engine.

(9)

Stop the motoring run after 30 seconds.

(10)

Shut off the water or water/alcohol as the Ng decreases through 5%.

CAUTION:

OBSERVE THE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL).

(11)

Repeat the washing cycles as necessary to remove contaminants from the turbines.

(12)

Disconnect the pressurized tanks or drinking water supply from the wash tube assembly (3, Fig. 704) and remove the assembly from the igniter port.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

(13)

Install the igniter (1) with the gasket (2) (Ref. 74-20-00, IGNITION CABLES AND SPARK IGNITERS - MAINTENANCE PRACTICES) or the glow plug with the gasket (Ref. 74-20-02, GLOW PLUGS - MAINTENANCE PRACTICES) into the igniter port.

CAUTION:

9.

OBSERVE THE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL).

(14)

Do an additional 30 second dry motoring run if the water/alcohol has been used.

(15)

Start the engine (Ref. ADJUSTMENT/TEST) and run at 80% Ng for one minute or more to completely dry the engine.

(16)

Shut down the engine.

Fuel Nozzle In-situ Cleaning A.

General Wash cart (PWC32677-300) is required. Prior to the wash cycle, the cleaning rig must be prepared and operated in accordance with the Cleaning Rig Manual. Cleaning should be initiated on new or recently cleaned nozzles as the procedure will not clear previous blockages. Clean every 200 hours. Adjust the interval based on condition and experience.

B.

Preparation

CAUTION: (1)

CLEANING AGENT IS AN ALKALINE SUBSTANCE THAT CAN CAUSE SKIN IRRITATION. AVOID SKIN CONTACT.

Mixture ratios: (a) At ambient temperatures above 2°C (36°F) mix by volume: 1 part cleaner (PWC11-001G) to 4 parts demineralized water (PWC05-073). (b) At ambient temperatures below 2°C (36°F) mix a 50% solution of alcohol(PWC11-014) and demineralized water (PWC05-073), then mix 4 parts of water/alcohol (by volume) to 1 part cleaner (PWC11-001G).

CAUTION:

MAKE SURE THAT AIR HAS BEEN RELEASED FROM RESERVOIRS.

(2)

Fill reservoirs with an appropriate volume of cleaning solution.

(3)

Fill rinse reservoir with appropriate volume of demineralized water or demineralized water/alcohol mixture according to ambient temperature.

(4)

Remove two gas generator drain valves from engine (Ref. 73-10-06). Install suitable drain hoses.

(5)

Disconnect fuel inlet line from flow divider and purge valve outlet elbow (Ref. 73-10-04).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

(6)

Connect wash rig fluid delivery hose to valve outlet elbow using adapter (0.4375-20 UNJF).

(7)

Connect rig fluid delivery hose to rig ‘‘FUEL NOZZLE’’ quick disconnect.

(8)

Connect compressed air.

CAUTION: (9) C.

DO NOT EXCEED 120 PSIG.

Set wash rig to 60 psig using reservoir regulator, and pulse to 70 psig using pulse regulator.

Cleaning (1)

Let the engine cool for a minimum of 40 minutes after engine shutdown before cleaning the fuel nozzles.

(2)

Place valve A and B to AGITATE and valve C OFF, and agitate detergent solution for two minutes.

(3)

Place valve A and B to WASH and valve C ON, and detergent wash for three minutes.

(4)

Place all valves OFF and let soak for ten minutes.

(5)

Place valve A and B to WASH and valve C ON, and detergent wash for three minutes.

(6)

Place all valves OFF and let soak for ten minutes.

(7)

Place valve A and B to RINSE and valve C ON, and rinse for five minutes.

(8)

Place valve A and B OFF and valve C to AIR DRY, and dry for five minutes.

(9)

Place valves OFF and reduce both reservoir and pulse pressure to zero.

(10)

Remove compressed air supply from wash rig.

(11)

Remove wash rig fluid delivery hose from flow divider elbow.

(12)

Reconnect dump line or air inlet line (Ref. 73-10-04).

(13)

Remove blanking cap at fuel inlet line and elbow on flow divider and dump or purge valve.

(14)

Reconnect fuel inlet line (Ref. 73-10-04).

(15)

Remove drain hoses and reinstall gas generator case drain valves (Ref. 73-10-06).

(16)

Do an engine ground run and check for leaks (Ref. ADJUSTMENT/TEST).

(17)

Clean wash rig, stow fluid delivery hoses, and bleed the air pressure from the reservoirs.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

10.

Inhibition of Engine Corrosion A.

Optional Application of Engine Corrosion-inhibiting Solution (1)

Information relocated to Chapter 72-00-00, Inspection.

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DATE Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020 Jul 20/2020

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE OF CONTENTS SUBJECT

PAGE

ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

72-00-00

1.

Description and Operation

1

2.

Engine Data

9

3.

Approved Service Bulletins

14

ENGINE, TURBOPROP - FAULT ISOLATION

72-00-00

1.

General

101

2.

Consumable Materials

101

3.

Special Tools

101

4.

Fixtures, Equipment and Supplier Tools

101

5.

Engine Condition Trend Monitoring System

101

A.

101

6.

General

Fault Isolation

102

A.

Categories

102

B.

Engine Starting

102

C.

Engine Operating

102

D.

Engine Performance

102

E.

Engine Condition Trend Monitoring Shift

103

F.

Engine Lubrication

103

G. Lubricating Oil Contamination

103

ENGINE, TURBOPROP - MAINTENANCE PRACTICES

72-00-00

1.

General

201

2.

Special Tools

201

3.

Special Equipment

201

4.

Consumable Materials

201

5.

Suppliers and Supplier Services

201

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TABLE OF CONTENTS SUBJECT

PAGE

ENGINE, TURBOPROP - SERVICING

72-00-00

1.

General

301

2.

Consumable Materials

301

3.

Special Tools

301

4.

Fixtures, Equipment and Supplier Tools

302

5.

Lubricating Oil System

302

A.

Lubricating Oil

302

B.

Oil Level Check

302

C.

Procedure

302

D.

Oil Servicing

304

E.

Oil System Flushing

305

F.

Procedure After Oil System Flushing

308

6.

7.

G. Oil Level Check and Replenishment following Multiple Motoring Runs or Wind-Milling of a Shutdown Engine in Flight

308

Preservation, Depreservation and Unpreserved Engines Section

309

A.

General

309

B.

Engine Preservation Procedure

309

C.

Engine Depreservation Procedure

314

D.

Preservation of Power Section (P/S)

316

E.

Engine Unpreserved Procedure

316

F.

Regular Operation as Alternative to Preservation of Inactive Engines

321

G. Accessories, Preservation, Storage and Depreservation

321

Storage and Shipping

323

A.

General

323

B.

Shipping/Storage Container

323

C.

Humidity Control

324

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TABLE OF CONTENTS SUBJECT

PAGE

ENGINE, TURBOPROP - SERVICING (Cont’d)

8.

9.

10.

11.

D.

Reactivation of Desiccant and Humidity Indicator

324

E.

Precautions

324

F.

Metal Storage and Shipping Container

325

G. Humidity and Pressure Control

327

H.

Precautions

328

I.

Engine Storage in Metal Container

328

J.

Stacking Containers for Storage

330

Removal/Installation of Engine from/in Fiberboard Container

330

A.

Removal

330

B.

Installation

331

C.

Engine Removal from Reinforced Fiberboard Container

334

D.

Engine Installation in Reinforced Fiberboard Container

335

E.

Engine Removal from Metal Container

338

F.

Engine Installation in Metal Container

339

Removal/Installation of Engine from/in Maintenance Stand

341

A.

Removal

341

B.

Installation

343

Removal/Installation of Power Section (P/S) from/in Container

345

A.

Removal

346

B.

Installation

347

Removal/Installation of Power Section from/in Maintenance Stand

351

A.

Removal

351

B.

Installation

351

ENGINE, TURBOPROP - REMOVAL/INSTALLATION 1.

72-00-00

General

72-00-00 401

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TABLE OF CONTENTS SUBJECT

PAGE

ENGINE, TURBOPROP - REMOVAL/INSTALLATION (Cont’d)

72-00-00

2.

Consumable Materials

401

3.

Special Tools

401

4.

Fixtures, Equipment and Supplier Tools

401

5.

Removal/Installation of Engine

402

A.

Removal of Engine from Airframe

402

B.

Installation of Engine in Airframe

402

6.

Removal/Installation of Power Section (P/S) from Gas Generator Assembly

402

A.

Removal

402

B.

Installation

407

ENGINE - INSPECTION

72-00-00

1.

General

601

2.

Consumable Materials

601

3.

Special Tools

602

4.

Fixtures, Equipment and Supplier Tools

602

5.

Corrosion

602

A.

High Temperature Alloy Corrosion

602

B.

Sulphidation

602

6.

Corrosion Inhibition

604

A.

Corrosion Inhibition Procedure

604

B.

Air Inlet Case Corrosion Prevention

605

7.

Control Linkage

608

8.

Periodic Inspection

608

9.

Borescope

623

A.

623

General

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TABLE OF CONTENTS SUBJECT

PAGE

ENGINE - INSPECTION (Cont’d)

10.

11.

12.

72-00-00

B.

Description

623

C.

Removal/Installation of Borescope and Accessories

623

D.

Inspection

627

E.

Fault Isolation

632

In-service Inspection

633

A.

Hot Section Components

633

B.

Removal/Installation of Power Section (Heavy Maintenance Only)

634

C.

Inspection of Combustion Chamber

634

D.

Inspection of Compressor Turbine (CT) Stator Assembly

636

E.

Inspection of CT Blades

643

F.

Inspection of CT Shroud Segments

652

G. Inspection of Power Turbine (PT) Stator

652

H.

Inspection of PT Blades

653

I.

Inspection of Accessory Gearbox (AGB) and Reduction Gearbox (RGB) Gears

653

Inspection of Hot Section Components

654

A.

General

654

B.

Gas Generator Module

654

C.

Power Section

655

D.

Hot Section Inspection

659

E.

Hot Section Inspection of Compressor Turbine (CT) Vane

660

Unscheduled Inspection

665

A.

General

670

B.

Performance Deterioration

670

C.

Engine Overspeed

670

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE OF CONTENTS SUBJECT

PAGE

ENGINE - INSPECTION (Cont’d)

72-00-00

D.

Inadvertent Cut-off and Relight During Taxi

671

E.

Overtemperature

671

F.

Overtorque

672

G. Immersion in Water

672

H.

Dropped Engine or Component

672

I.

Material Ingestion (e.g., ice, stones, etc.)

673

J.

Bird Strike/Soft Material Ingestion (e.g., rags, plastic bags, etc.)

673

K.

Chip Detector Circuit Completion and/or Debris in Oil Filter

673

L.

Propeller Sudden Stoppage or Strike

673

M. Propeller Lightning Strike

676

N.

677

Propeller Electrical Leads Shorting

O. Heavy/Hard Landing

677

P.

678

Aircraft Flown Through Volcanic Ash or Smoke

Q. Sustained Running at Oil Temperature Outside Limits

679

R.

Loss of Oil/Oil Pressure or Low Oil Pressure

679

S.

Oil Pressure Follows Throttle

681

T.

Contamination by Fire Extinguishing Agents

681

U.

Audible Rubbing, Binding or Scraping

681

V.

Propeller Windmilling after In-flight Shutdown

682

W. Contamination of Oil with Non-metallic Foreign Material

683

X.

Inspection of Main Oil Filter Secondary Screen

683

Y.

Starter-Generator Replacement

685

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72-00 CONTENTS

Page 6 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

ENGINE, TURBOPROP - DESCRIPTION AND OPERATION 1.

Description and Operation The PT6A Series power plant is a lightweight free turbine engine. The engine utilizes two independent turbine sections: one driving the compressor in the gas generator section and the second (two-stage power turbine) driving the propeller shaft through a reduction gearbox. The engine is self-sufficient since its gas generator driven oil system provides lubrication for all areas of the engine, pressure for the torquemeter and power for propeller pitch control. Refer to Fig. 1 and Fig. 2 for the main features of a typical engine, Fig. 3 for the engine cross-section and Fig. 4 for engine stations, flanges and bearings. The inlet air enters the engine through an annular plenum chamber, formed by the compressor inlet case, where it is directed forward to the compressor. The compressor consists of three axial stages combined with a single centrifugal stage, assembled as an integral unit. A row of stator vanes, located between each stage of compression, diffuses the air, raises its static pressure and directs it to the next stage of compression. The compressed air passes through diffuser tubes which turn the air through ninety degrees in direction and converts velocity to static pressure. The diffused air then passes through straightening vanes to the annulus surrounding the combustion chamber liner. The combustion chamber liner consists of an annular weldment having perforations of various sizes that allow entry of compressor delivery air. The flow of air changes direction 180 degrees as it enters and mixes with fuel. The fuel/air mixture is ignited and the resultant expanding gases are directed to the turbines. The location of the liner eliminates the need for a long shaft between the compressor and the compressor turbine, thus reducing the overall length and weight of the engine. Fuel is injected into the combustion chamber liner through 14 simplex nozzles arranged in two sets of seven for ease of starting. Fuel is supplied by a dual manifold consisting of primary and secondary transfer tubes and adapters. The fuel/air mixture is ignited by two glow plugs or spark igniters which protrude into the liner. The resultant gases expand from the liner, reverse direction in the exit duct zone and pass through the compressor turbine inlet guide vanes to the compressor turbine. The guide vanes ensure that the expanding gases impinge on the turbine blades at the correct angle, with minimum loss of energy. The still expanding gases are then directed forward to drive the power turbine. The compressor and power turbines are located in the approximate center of the engine with their respective shafts extending in opposite directions. This feature provides for simplified installation and inspection procedures. The exhaust gas from the power turbine is directed through an annular exhaust plenum to atmosphere via twin opposed exhaust ports provided in the exhaust duct. Interturbine temperature (T5) is monitored by a cold junction thermocouple system comprising a bus-bar, probes and harness assembly installed between the compressor and power turbines with the probes projecting into the gas path. A terminal block mounted in the gas generator case provides a connection point to cockpit instrumentation and to a T5 trim thermocouple mounted externally in the air inlet zone.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

C1206A Engine - Right Rear View (Typical) Figure 1 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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Page 2 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION Sep 15/2014

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

C1207A Engine - Left Front View Figure 2 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

PROPELLER GOVERNOR MOUNTING PAD

FUEL MANIFOLD ADAPTER AND NOZZLE ASSEMBLY

EXHAUST DUCT T5 WIRING HARNESS

FIRST−STAGE REDUCTION

PROPELLER SHAFT

PROPELLER REDUCTION GEARBOX

MAGNETIC CHIP DETECTOR

SECOND−STAGE REDUCTION

POWER TURBINE SHAFT HOUSING

COMPRESSOR TURBINE VANE RING

COMPRESSOR ASSEMBLY

COMPRESSOR IMPELLER

COMPRESSOR TURBINE

COMPRESSOR INLET CASE

ACCESSORY GEARBOX

AIR INLET SCREEN

POWER TURBINE SHAFT POWER TURBINE

COMBUSTION CHAMBER LINER

FLOW DIVIDER AND DUMP VALVE

C13613 Engine Cross-Section (Typical) Figure 3 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

T5 BUS−BAR AND PROBE ASSEMBLY

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Page 5/6 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION Sep 15/2014

GAS GENERATOR CASE

CLASSIFIED POWER TURBINE VANE RING

OIL TANK FUEL DRAIN VALVE DIFFUSER TUBE

COMPRESSOR BLEED VALVE

GEARBOX INPUT DRIVE GEARSHAFT GEARBOX INPUT COUPLING SHAFT

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

COMPRESSOR TURBINE INLET EXHAUST OUTLET

INTERTURBINE

EXHAUST DUCT

STATIONS

7

ENGINE INLET

6

BEARINGS

4

COMBUSTION CHAMBER INLET COMPRESSOR INLET

5

3

4

3

2

1

2

1

PROPELLER SHAFT ROLLER BEARING PROPELLER SHAFT THRUST BEARING

FLANGES

ACCESSORY DRIVE ROLLER BEARING TYPICAL

A

B

C

D

REDUCTION GEARBOX TO EXHAUST CASE REDUCTION GEARBOX REAR CASE TO POWER TURBINE HOUSING SUPPORT EXHAUST DUCT TO GAS GENERATOR CASE

EXHAUST DUCT TO POWER TURBINE VANE HOUSING

Engine Bearings, Stations and Flanges Figure 4

72-00-00

F SMALL EXIT DUCT TO COMPRESSOR TURBINE SHROUD HOUSING

C1268D

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E

Page 7/8 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION Sep 15/2014

G OIL TANK TO ACCESSORY GEARBOX DIAPHRAGM GAS GENERATOR CASE TO COMPRESSOR INLET CASE

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

All engine-driven accessories, with the exception of the propeller governor, Nf overspeed governor and Nf tachometer-generator are mounted on the accessory gearbox at the rear of the engine. These components are driven by the compressor by means of a coupling shaft which extends the drive through a conical tube in the center section of the oil tank. The rear location of accessories provides for a clean engine and simplifies maintenance procedures. The engine oil supply is contained in an integral oil tank which forms the rear section of the compressor inlet case. The tank has a total capacity of 2.3 U.S. gallons and is provided with a dipstick. Fuel supplied to the engine from an external source is further pressurized by an engine-driven fuel pump and its flow to the fuel manifold is controlled by the fuel control unit (FCU) and a starting flow control unit or a flow divider and dump valve according to engine model requirements. The power turbine drives a propeller through a two-stage planetary reduction gearbox located at the front of the engine. The gearbox embodies an integral torquemeter device which is instrumented to provide an accurate indication of engine power. The propeller reversing installation consists of a single-acting hydraulic propeller controlled by a propeller governor, combining the functions of a normal constant speed unit (CSU), a reversing valve and a power turbine (Nf) governor. A mechanical linkage between the propeller governor Beta control valve and the air bleed link enables the FCU and the propeller governor to modify engine power to maintain power turbine speed at a speed slightly less than the selected rpm when operating in the Beta control range. 2.

Engine Data For engine specifications and leading particulars, refer to Tables 1 and 2 for the PT6A-34/-34B/-34AG Engines, and Tables 3 and 4 for the PT6A-36 Engines. For the front and rear accessory drives-leading particulars, refer to Fig. 5 and Table 5. For engine fuel and lubrication system specifications and leading particulars, refer to Table 6.

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Page 9 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION Sep 15/2014

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

1 2

6 5 4

3

AS VIEWED FROM REAR

7

8 9

AS VIEWED FROM FRONT

C7819B Engine Accessory Drives Figure 5 P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 1, PT6A-34/-34B/-34AG Engine Specifications (Sea Level Static Output - Standard Day)

OPERATING CONDITION

ESHP

SHP

JP-4 FUEL CONSUMPTION (lb/eshp/hr) at 15°C (59°F)

Takeoff

783 (1)

750 (2)

0.595

82

Max. Continuous

783 (1)

750 (2)

0.595

82

Max. Climb (5)

731 (1)

700 (3)

0.604

77

Max. Cruise (5)

731 (1)

700 (4)

0.604

77

JET THRUST (lb.)

(1) Ratings are for 2200 propeller rpm. (2) Available to 31°C (87°F) ambient. (3) Available to 28.3°C (83°F) ambient. (4) Available to 19.4°C (67°F) ambient. (5) For information only; these ratings not DOT approved.

TABLE 2, PT6A-34/-34B/-34AG Engine Leading Particulars LEADING PARTICULARS Engine type Free turbine Type of combustion chamber Annular Compression ratio 7.0:1 Propeller shaft rotation Clockwise (looking FWD) Propeller shaft configuration Flanged Propeller shaft gear ratio 0.0664:1 Engine diameter 19.0 in. (combustion case approx. at room temp.) (483 mm) Engine length 62.0 in. (approx. at room temp.) (1575 mm) Oil consumption 0.2 lb/hr (90 cc/hr) or 0.90 liter/10 hr Dry weight, PT6A-34 331 lb. (Incl. standard equip.) (150 kg) Dry weight, PT6A-34AG 331 lb. (Incl. standard equip.) (150 kg) Dry weight, PT6A-34B 344 lb. (Incl. standard equip.) (156 kg)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 3, PT6A-36 Engine Specifications (Sea Level Static Output - Standard Day)

OPERATING CONDITION

ESHP

SHP

JP-4 FUEL CONSUMPTION (lb/eshp/hr) at 15°C (59°F)

Takeoff

786 (1)

750 (2)

0.590

90

Max. Continuous

786 (1)

750 (2)

0.590

90

Takeoff Wet

786 (1)

750 ( 5)

0.590

90

Max. Climb (6)

735 (1)

700 (3)

0.601

87

Max. Cruise (6)

735 (1)

700 (4)

0.601

87

JET THRUST (lb.)

(1) Ratings are for 2200 propeller rpm. (2) Available to 36.1°C (97°F). (3) Available to 28.3°C (83°F). (4) Available to 19.4°C (67°F). (5)Available to 47.8°C (118°F) (Water/Meth). (6) For information only; these ratings not DOT approved.

TABLE 4, PT6A-36 Engine Leading Particulars LEADING PARTICULARS Engine type

Free Turbine

Type of combustion chamber

Annular

Compression ratio

7.0:1

Propeller shaft rotation (looking FWD)

Clockwise

Propeller shaft configuration

Flanged

Propeller shaft gear ratio

0.0664:1

Engine diameter (combustion case approx. at room temp.)

19.0 in. (483 mm)

Engine length (approx. at room temp.)

62.0 in. (1575 mm)

Oil consumption

0.2 lb/hr (90 cc/hr) or 0.90 liter/10 hr

Dry weight (incl. standard equip.)

331 lb. (150 kg)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 5, Accessory Drives - Leading Particulars Max. Torque (in.lb.) Drive Pad

Rotation

Ratio

Continuous

Static

Max. Speed (RPM)

1

Starter-generator (1)

CW

0.2931:1

170

-

10,991

2.

Fuel Pump/FCU (1)

CCW

0.1670:1

-

-

6,262

3.

Ng Tach Generator (1)

CCW

0.1121:1

7

100

4,203

4.

Vacuum Air Pump (Optional) (1)

CCW

0.1019:1

60

800

3,821

5.

Optional Accessory Drive (1)

CW

0.3208:1

135

800

12,028

6.

Optional Accessory Drive (Hydraulic Pump) (1)

CCW

0.2041:1

150

800

7,654

7.

Propeller Governor (2)

CW

0.1264:1

50

850

-

8.

Nf Tach Generator (2)

CW

0.1264:1

7

100

-

9.

Propeller OverspeedGovernor (2)

CW

0.1264:1

50

850

-

NOTE: 1. Rear Accessory Drives: 100% is 37,500 rpm Ng. NOTE: 2. Front Accessory Drives: 100% is 33,000 rpm Nf.

TABLE 6, Fuel and Lubrication System Specifications Nomenclature Fuel Specification

Specification Ref. P&WC SB1244 for PT6A-34/-34B/-36 and SB1344 for PT6A-34AG (Ref. NOTE 1) Oil Specification Ref. P&WC SB1001 (Ref. NOTE 1) Oil Tank - Total Capacity 2.3 US gallons (1.92 Imp. gallons, 8.74 liters) Oil Tank - Expansion Space 0.7 US gallons (0.58 Imp. gallons, 2.64 liters) Oil Tank - Usable Quantity 1.5 US gallons (1.25 Imp. gallons, 5.68 liters) NOTE: 1. Ref. Service Bulletin List for further details.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

3.

Approved Service Bulletins The following Service Bulletins contain data recommended by Pratt & Whitney Canada and approved by the Canadian Minister of Transport. SB1001: Approved Listing of Synthetic Oils. SB1003, SB1303 or SB1403: Operating Time Between Overhauls. SB1244 for the PT6A-34/-34B/-36 Engines or SB1344 for the PT6A-34AG Engines: Requirements and Approved Listing of Engine Fuel And Additives.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

ENGINE, TURBOPROP - FAULT ISOLATION 1.

2.

General A.

For details on recommended procedures for engine system fault isolation, reference should be made to the Fault Isolation Charts (Figures 101 through 105 and Table 101).

B.

The charts comprise a series of diagnostic tests and rectification sequences which will assist an operator in discovering, isolating and correcting various faults that may arise in the basic engine or any of its related systems during service.

C.

Engine faults can be either obvious or hidden. If hidden faults are not detected, serious and considerable damage may occur to the engine. Therefore, it is essential to have a thorough knowledge of correct turbine gas temperature and other important details of engine operation. Before attempting to locate a fault or difficulty, or to work on an engine which has been malfunctioning during flight, consult flight log and any other available data that could help in diagnosing the fault.

D.

To correctly isolate a fault, check all previous information of engine faults, if any, and work that has been performed on the engine. Check each probable source of fault by use of relevant diagnostic test sequences until defect has been isolated. Systematic checking, essential for thorough fault isolation, will save time and extend engine life.

Consumable Materials Not Applicable

3.

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Engine Condition Trend Monitoring System A.

General Gas turbine/turboprop engine maintenance practices frequently include in-flight engine performance monitoring as a means of detecting mechanical deterioration in engine gas paths. A simple system, requiring almost no arithmetic calculation, has been devised for the PT6A engine to aid in early planning of indicated rectifications, and thus reduce the potential costs of primary and secondary damage resulting from fully developed failures, or from the risks of in-flight shutdowns, and flight cancellations. The turbine engine characteristic of repeatedly producing its output at, or very close to, charted gas generator parameter values provides the basis for the engine condition trend monitoring system. Thus, under known conditions of pressure altitude (PA) and

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

indicated outside air temperature (IOAT), the gas generator parameter values of interturbine temperature (ITT), compressor speed (Ng), and fuel flow (Wf), for particular propeller shaft speeds (Np) and torques are predictable within reasonable limits. New engines operate within a tolerance band, either above or below charted parameter values, and tend to deviate more from these values with time and deterioration of gas path components. Sudden changes or gradually increased rate of change of the normal deviations from charted parameter values are very important indicators of gas path component conditions. As such, you can find the changes before some distress occurs. The monitoring system must be introduced when engines are new or newly overhauled. This enables establishment of a performance base line before any deterioration takes place in the engine. For procedure refer to P&WC Publication SIL No. GEN-055. 6.

Fault Isolation A.

Categories To enable systematic fault isolation, engine faults are categorized into classes. Each class consists of common related engine problems with appropriate diagnostic tests and rectification sequences. The classes of engine fault and probable causes are detailed as follows: (a) Engine Starting (Ref. Subpara. B.) (b) Engine Operating (Ref. Subpara. C.) (c) Engine Performance (Ref. Subpara. D.) (d) Engine Condition Trend Monitoring Shift (Ref. Subpara. E.) (e) Engine Lubrication (Ref. Subpara. F.) (f)

B.

Engine Starting (1)

C.

To diagnose and rectify engine starting problems, refer to Engine Starting Fault Isolation Chart (Ref. Fig. 101).

Engine Operating (1)

D.

Engine Lubrication Oil Contamination (Ref. Subpara. G.)

To diagnose and rectify engine operating problems, refer to Engine Operating Fault Isolation Chart (Ref. Fig. 102).

Engine Performance (1)

To diagnose and rectify engine performance problems, refer to Engine Performance Fault Isolation Chart (Ref. Fig. 103).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

E.

Engine Condition Trend Monitoring Shift (1)

F.

To diagnose and rectify engine condition trend monitoring shift, refer to ECTM Shift Fault Isolation Chart (Ref. Table 101) .

Engine Lubrication (1)

To diagnose and rectify engine lubrication problems, refer to Engine Lubrication Fault Isolation Chart (Ref. Fig. 104).

G. Lubricating Oil Contamination (1)

To diagnose and rectify engine lubricating oil contamination, refer to Engine Lubricating Oil Contamination Fault Isolation Chart (Ref. Fig. 105).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

STARTING PROBLEMS

NO INDICATION OF ENGINE RPM

IS STARTER − GENERATOR OPERATION AUDIBLE

CONT’D ON SHEET 3

INSUFFICIENT RPM

EXCESSIVE RPM

CHECK ACCESSORY GEARBOX INPUT SHAFT COUPLING FOR PROPER ENGAGEMENT. INSPECT ACCESSORY GEAR DRIVES, BEARINGS AND COMPRESSOR REAR HUB SPLINES (REF. 72−60−00)

NO

CHECK ELECTRICAL POWER SUPPLIES AND STARTER − GENERATOR ELECTRICAL CONNECTIONS

YES

RECTIFY POWER SUPPLY FAULT

NO

ARE ELECTRICAL POWER SUPPLIES O.K. ANY EVIDENCE OF DAMAGE, RETURN ENGINE TO APPROVED OVERHAUL FACILITY

YES REPLACE STARTER−GENERATOR (REF. AIRCRAFT MAINTENANCE MANUAL)

IF ANY STARTER−GENERATOR BEARING DISTRESS AND/OR SHORTED ARMATURE TO THE STARTER−GENERATOR SHAFT IS SUSPECTED, PERFORM INSPECTION OF MAIN OIL FILTER AFTER STARTER−GENERATOR REPLACEMENT (REF. UNSCHEDULED INSPECTION, 72−00−00)

DOES ENGINE ROTATE WITH STARTER − GENERATOR OPERATION

YES

REMOVE Ng TACHOMETER − GENERATOR AND ATTEMPT TO ROTATE COMPRESSOR AT TACHOMETER DRIVE

NO CONT’D ON SHEET 2

CONT’D ON SHEET 2

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

STARTING PROBLEMS FROM SHEET 1

FROM SHEET 1

RECTIFY FAULT ON Ng TACHOMETER INDICATING SYSTEM

YES

NO

REMOVE STARTER − GENERATOR. CHECK FOR SHEARED DRIVE SHAFT AND GEARSHAFT SPLINE DAMAGE

IS STARTER − GENERATOR DRIVE SHAFT SHEARED

REMOVE POWER SECTION (REF. 72−00−00) CHECK COMPRESSOR TURBINE TIP CLEARANCE (REF. 72−50−02) NO IS TURBINE TIP CLEARANCE CORRECT

YES ARE SPLINES ON GEARSHAFT O.K.

DOES COMPRESSOR ROTATE FREELY WITH NO SOUND OF TURBINE BLADE SCRAPING

NO

NO YES

YES REPLACE STARTER − GENERATOR AND/OR DRIVESHAFT (REF. AIRCRAFT MAINTENANCE MANUAL)

RETURN ENGINE TO APPROVED OVERHAUL FACILITY

REMOVE COMPRESSOR TURBINE AND GRIND SEGMENTS (REF. 72−50−01)

IF ANY STARTER−GENERATOR BEARING DISTRESS AND/OR SHORTED ARMATURE TO THE STARTER−GENERATOR SHAFT IS SUSPECTED, PERFORM INSPECTION OF MAIN OIL FILTER AFTER STARTER−GENERATOR REPLACEMENT (REF. UNSCHEDULED INSPECTION, 72−00−00)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

FROM SHEET 1

STARTING PROBLEMS

CONTINUED ON SHEET 5

ENGINE FAILS TO LIGHT UP

CHECK RIGGING OF THE START CONTROL VALVE (REF. 73−10−04 AND AMM)

HAS ENGINE STARTING PROCEDURE (REF. 71−00−00) BEEN CARRIED OUT

SET STARTING CONTROL / FCU LEVER TO CUT−OFF AND DUMP POSITION. ALLOW 30 SECONDS FUEL DRAINING PERIOD AND CARRY OUT DRY MOTORING RUN (REF. 71−00−00)

NO

YES CARRY OUT DRY MOTORING RUN ON ENGINE (REF. 71−00−00)

REPEAT COMPLETE ENGINE START SEQUENCE (REF. 71−00−00) CAUTION: OBSERVE STARTER MOTOR LIMITS

CAUTION: ON IGNITER SYSTEM (ALTERNATE) APPLICATION, RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. MAKE SURE IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE DISCONNECTING.

OPERATIONALLY CHECK IGNITION SYSTEM (REF. 74−00−00) CHECK GLOW PLUGS AND BALLAST TUBES. REPLACE AS NECESSARY. CHECK FOR CORRECT TUBES (REF. 74−10−01)

NO

IGNITION SYSTEM FOUND O.K.

NO

(ALTERNATE INSTALLATION) CHECK POWER SUPPLIES TO IGNITION EXCITER. CARRY OUT ELECTRICAL INSULATION AND CONTINUITY CHECKS ON IGNITION CABLES AND VISUALLY CHECK CABLES AND IGNITERS. RECTIFY AS NECESSARY (REF. 74−20−00)

YES CONTINUED ON SHEET 4

CONTINUED ON SHEET 4

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

STARTING PROBLEMS FROM SHEET 3

ON AIRFRAME INSTALLATION, CHECK OPERATION OF BOOSTER PUMP, IF FITTED, AND MAKE SURE FUEL SOURCE IS FREE OF ICE OR WATER CONTAMINATION

NO

FROM SHEET 3

IS AIRFRAME FUEL SUPPLY TO ENGINE O.K.

NO FAULTS FOUND ON IGNITERS OR CABLES. REPLACE IGNITION EXCITER (REF. 74−10−00)

YES LOOSEN INLET TUBE FROM PUMP TO FCU. CHECK FOR FUEL FLOW. FLOW EVIDENT

NO

REPLACE PUMP (REF. 73−10−02)

YES FAULT POSSIBLE DUE TO AIR LOCK IN FUEL CONTROL UNIT. IF FUEL SYSTEM HAS BEEN DISCONNECTED, MAKE SURE BYPASS FUEL TO TANK IS UNRESTRICTED AND RESTART ENGINE TO CARRY OUT SELF BLEEDING OPERATION

CHECK BYPASS VALVE OPERATION IN FCU

NO

LOOSEN OUTLET TUBE FROM FCU TO STARTING CONTROL. CHECK FOR FUEL FLOW WHILE MOTORING. FLOW EVIDENT. YES

NO

REPLACE STARTING CONTROL (REF. 73−10−04)

LOOSEN PRIMARY TUBE AT STARTING CONTROL. CHECK FOR FUEL FLOW WHILE MOTORING. FLOW EVIDENT. YES

CHECK POSITION OF FUEL MANIFOLD ADAPTERS. MAKE SURE PRIMARY NOZZLES ARE POSITIONED AS DETAILED (REF. 73−10−05) CHECK FUEL NOZZLES FOR RESTRICTION. FUNCTION CHECK NOZZLES (REF. 73−10−05)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

STARTING PROBLEMS FROM SHEET 3

CONTINUED FROM SHEET 6

ENGINE FAILS OR IS SLOW TO ACCELERATE TO IDLE SPEED

CHECK RIGGING OF THE START CONTROL VALVE (REF. 73−10−04 AND AMM)

CHECK P3 BLEED AIR DELIVERY TUBES INCLUDING THE P3 ELBOW AT THE FCU FOR POSSIBLE LEAKS AND RESTRICTIONS. FOR ENGINES FITTED WITH P3 AIR FILTER, CHECK THE FILTER BOWL FOR POSSBILE LEAKS AND P3 AIR FILTER FOR RESTRICTIONS AND CONTAMINATION (OIL, WATER, DIRT, ETC). RECTIFY AS NECESSARY (REF. 73−10−07)

IF DELIVERY TUBES ARE O.K., CHECK PNEUMATIC SECTION OF PROPELLER GOVERNOR. RECTIFY AS NECESSARY (REF. 61−20−00)

CHECK FLOW DIVIDER AND DUMP VALVE OPERATION. RECTIFY OR REPLACE AS NECESSARY (REF. 73−10−04)

IF PREVIOUS CHECKS ARE O.K., POSSIBLE FAULT DUE TO CONTAMINATION IN FCU. CHECK AND REPLACE AS NECESSARY (REF. 73−20−00)

C220575 Engine Starting Fault Isolation Chart Figure 101 (Sheet 5) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

STARTING PROBLEMS CONTINUED FROM SHEET 5

CONTINUED ON SHEET 8

DELAYED LIGHT UP

HOT START

HAS ENGINE STARTING PROCEDURE BEEN CARRIED OUT (REF. 71−00−00)

NO

NO

HAS ENGINE STARTING PROCEDURE BEEN CARRIED OUT (REF. 71−00−00)

YES

YES

CHECK FOR LOW POWER SUPPLIES AND LOOSE CONNECTIONS ON POWER INPUT LINES AND STARTER−GENERATOR CONNECTION (REF. INSPECTION) ARE ELECTRICAL SUPPLIES O.K? NO

SET STARTING CONTROL LEVER / FCU TO CUT−OFF AND DUMP POSITION. ALLOW 30 SECONDS FUEL DRAINING PERIOD AND CARRY OUT DRY MOTORING RUN (REF. 71−00−00)

YES DO COMPLETE ENGINE START AGAIN (REF. 71−00−00). CAUTION: MONITOR STATER MOTOR LIMITS.

CORRECT POWER SUPPLY OR CABLE FAULT

DO AN OPERATIONAL CHECK OF IGNITION SYSTEM (REF. 74−20−00) CAUTION: ON IGNITER SYSTEM (ALTERNATE) APPLICATION, RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. MAKE SURE IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE DISCONNECTING.

DO AN OPERATIONAL CHECK OF IGNITION SYSTEM (REF. 74−20−00)

CONTINUED ON SHEET 7 CONTINUED ON SHEET 7

C225290 Engine Starting Fault Isolation Chart Figure 101 (Sheet 6) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

STARTING PROBLEMS FROM SHEET 6

FROM SHEET 6 IGNITION SYSTEM FOUND O.K.

NO

NO

IGNITION SYSTEM FOUND O.K.

YES

YES

CHECK P3 BLEED AIR SYSTEM FOR AIRCRAFT SERVICES. MAKE SURE ALL SERVICES ARE SELECTED OFF. RECTIFY AS NECESSARY

CHECK GLOW PLUGS AND BALLAST TUBES. REPLACE AS NECESSARY. CHECK FOR CORRECT TUBES (REF. 74−20−01)

(ALTERNATE INSTALLATION) CHECK POWER SUPPLIED TO IGNITION EXCITER. DO ELECTRICAL INSULATION AND CONTINUITY CHECKS ON IGNITION CABLE AND VISUALLY CHECK CABLES AND IGNITERS. RECTIFY AS NECESSARY (REF.74−20−01 / 74−20−04)

CHECK ENGINE CONTROL LINKAGE RIGGING (REF. 76−10−00) NO

IS ENGINE CONTROL LINKAGE O.K.

NO FAULTS FOUND ON IGNITER OF CABLES. REPLACE IGNITION EXCITER (REF. 74−10−00)

YES DO CONTROL LINKAGE RIGGING ADJUSTMENTS (REF. 76−10−00)

CHECK FLOW TO FLOW DIVIDER AND DUMP / PURGE VALVE

CHECK POSITION OF FUEL MANIFOLD ADAPTERS. MAKE SURE PRIMARY NOZZLES ARE POSITIONED AS DETAILED (REF. 73−10−05)

CHECK MINIMUM FLOW SETTING ON FCU. IF TOO LOW, ADJUST (REF. 71−00−00, ADJUSTMENT / TEST)

CHECK TRANSFER VALVE IN STARTING CONTROL. IF STUCK, REPLACE STARTING CONTROL (REF. 73−10−04)

CHECK FUEL NOZZLES FOR RESTRICTION. FUNCTION CHECK NOZZLES. RECTIFY AS NECESSARY (REF. 73−10−05)

C29849A Engine Starting Fault Isolation Chart Figure 101 (Sheet 7) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

CONTINUED FROM SHEET 6

IS THE Ng RPM AT YES FUEL INTRODUCTION GREATER THAN 16% ?

WHITE SMOKE FROM EXHAUST (SEE NOTE)

NO DOES THE ENGINE LIGHT?

* DO A DRY MOTORING RUN (REF. 71−00−00)

NO

TRY FUEL INTRODUCTION AS THE GAS GENERATOR ACCELERATES THROUGH 16% OK?

YES CHECK FLOW DIVIDER AND DUMP OR PURGE VALVE OPERATION. CORRECT AS NECESSARY (REF. 73−10−04)

* DO AN OPERATIONAL CHECK OF YES IGNITION SYSTEM (REF. 74−20−00) OK? NO CHECK POWER SUPPLIES TO IGNITION EXCITER. CARRY OUT ELECTRICAL INSULATION AND CONTINUITY CHECKS ON IGNITION CABLES AND VISUALLY CHECK CABLES AND IGNITERS. CORRECT AS NECESSARY (REF. 74−20−00). * NO FAULTS FOUND ON CABLES. REPLACE IGNITION EXCITER (REF. 74−10−00)

NO CHECK FUEL NOZZLES AND FLOW DIVIDER (REF. 73−10−05 AND 73−10−04) OK? NO

YES

YES

SEND BACK ENGINE TO SERVICE

REPLACE AS NECESSARY (REF. 73−10−05 AND 73−10−04)

SEND ENGINE TO AN APPROVED P&WC OVERHAUL FACILITY

* CAUTION: 1. RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. MAKE SURE THAT THE IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE YOU DISCONNECT. 2. MONITOR STARTER MOTOR LIMITS. REFER TO STARTER MOTOR MANUFACTURER’S MANUAL. NOTE: 1. WHITE SMOKE FROM THE EXHAUST IS AN INDICATION THAT FUEL IS IN THE ENGINE AND BECAME A GAS ON START. 2. SMOKY STARTS CAN BE PREVENTED BY REPLACEMENT OF FLOW DIVIDER AND PURGE VALVE (REF. 73−10−04).

C225293 Engine Starting Fault Isolation Chart Figure 101 (Sheet 8) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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OPERATING PROBLEMS CONTINUED ON SHEET 2

PROPELLER SLOW TO FEATHER AND UNFEATHER/PROPELLER SPEED VARIATION

HOOTING OR HUMMING SOUND

CHECK OPERATION OF COMPRESSOR BLEED VALVE AND CONDITION OF DIAPHRAGM (REF. 75−30−00)

COMPRESSOR BLEED VALVE O.K.

NO

CHECK FRONT END PROPELLER REVERSING LINKAGE. ADJUST AS NECESSARY

CHECK PROPELLER GOVERNOR CONTROL SETTINGS, ADJUST AS NECESSARY (REF. 71−00−00)

REPLACE COMPRESSOR BLEED VALVE

YES

IF GOVERNOR ADJUSTMENTS ARE INEFFECTIVE, REPLACE GOVERNOR (REF.61−20−00)

IF THERE ARE NO PARAMETER FLUCTUATIONS AND SOUND DISAPPEARS ABOVE 60% Ng, NO ACTION NECESSARY. IF THERE ARE PARAMETER FLUCTUATIONS AND CONDITION PERSISTS ABOVE 60% Ng, DISASSEMBLE AND CHECK C.T. DISK FOR BLADE SHIFT. REMEDY AS NECESSARY. IF NO BLADE SHIFT, REBALANCE OR REPLACE C.T. DISK. IF CONDITION PERSISTS WITH REPLACEMENT OF C.T. DISK, RETURN ENGINE TO OVERHAUL FACILITY

IF FAULT IS STILL APPARENT, NO CHECK FOR HIGH OIL TEMPERATURE (REF. 71−00−00) YES REFER ENGINE LUBRICATION FAULT ISOLATION CHART

ADJUST OIL PRESSURE (REF. 71−00−00)

YES

IF FAULT IS STILL APPARENT, CHECK FOR LOW OIL PRESSURE (REF. 71−00−00) NO IF FAULT IS STILL APPARENT, POSSIBLE LEAK DUE TO WORN OR DAMAGED PREFORMED PACKING AT PROPELLER SHAFT OIL TRANSFER TUBE

SHIP ENGINE OR POWER SECTION TO A P&WC APPROVED OVERHAUL FACILITY

C220375 Engine Operating Fault Isolation Chart Figure 102 (Sheet 1 of 13) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING PROBLEMS CONT’D ON SHEET 3

FROM SHEET 1

INCORRECT RPM (Np) HIGH − LOW FORWARD

CHECK SPEED SELECT LEVER WILL CONTACT MAX STOP

REVERSE

CHECK AIR BLEED LINK (RESET ARM) RIGGING (REF. AIRFRAME MANUAL)

ADJUST MAX RPM STOP ON PROPELLER GOVERNOR (REF. AIRFRAME MANUAL)

ADJUST Nf RESET SPEED ADJUSTMENT ON PROPELLER GOVERNOR (REF. AIRFRAME MANUAL)

REPLACE PROPELLER GOVERNOR (REF. 61−20−00)

C29851 Engine Operating Fault Isolation Chart Figure 102 (Sheet 2) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING PROBLEMS CONTINUED FROM SHEET 2

CONTINUED ON SHEET 4

FAILURE TO DECELERATE

EXAMINE ENGINE CONTROL LINKAGE RIGGING. RIG AGAIN IF NECESSARY (REF. 76−10−00)

EXAMINE ENGINE Ng INDICATING SYSTEM. RECTIFY AS NECESSARY

EXAMINE FCU TO FUEL PUMP INTERFACE FOR POSSIBLE SHEARED OR WORN DRIVE SPLINE COUPING (REF. 73−10−02)

YES

DRIVE SPLINE COUPLING SHEARED OR WORN NO

REPLACE FCU AND / OR COUPLING (REF. 73−20−00)

UNCONTROLLED ACCELERATION

OVERSPEED (Ng)

EXAMINE ENGINE OPERATING LIMITS (REF. 71−00−00, ADJUSTMENT/TEST). DID AN OVERSPEED OR OVERTORQUE CONDITION OCCUR?

NO

YES

EXAMINE FCU FOR CONTAMINATION AND / OR CORROSION

REPLACE FCU (REF. 73−20−00)

DO AN UNSCHEDULED INSPECTION FOR OVERSPEED OR OVERTORQUE (REF. INSPECTION)

CONTINUE NORMAL ENGINE OPERATION

C226355 Engine Operating Fault Isolation Chart Figure 102 (Sheet 3) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

FROM SHEET 3

OPERATING PROBLEMS

CONTINUED FROM SHEET 5

SLOW TO ACCELERATE

CHECK RIGGING OF THE START CONTROL VALVE (REF. 73−10−04 AND AMM)

CHECK Py AIR BLEED TUBE AND P3 BLEED AIR DELIVERY TUBES INCLUDING THE P3 ELBOW AT THE FCU FOR POSSIBLE LEAKS AND RESTRICTIONS. FOR ENGINES FITTED WITH P3 AIR FILTER, CHECK THE FILTER BOWL FOR POSSBILE LEAKS AND P3 AIR FILTER FOR RESTRICTIONS AND CONTAMINATION (OIL, WATER, DIRT, ETC). RECTIFY AS NECESSARY (REF. 73−10−07)

ARE P3 TUBE AND FILTER O.K.?

NO

YES

RECTIFY OR REPLACE AS APPLICABLE (REF. 73−10−07)

VERIFY FUEL HEATER FOR HIGH OPERATING TEMPERATURE (REF. 71−00−00, ADJUSTMENT/TEST) REPLACE IF NECESSARY

OTHER PT6A: CHECK FCU ACCELERATION ADJUSTMENT OR PROPELLER GOVERNOR (REF. 71−00−00)

REPLACE FCU (REF. 73−20−00) OR PROPELLER GOVERNOR (REF. 61−20−00) AS APPLICABLE

C220576 Engine Operating Fault Isolation Chart Figure 102 (Sheet 4) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

NOTES: 1. LARGE BENT AIRFOIL WILL GIVE A HIGH PITCH NOISE AND POSSIBLE VIBRATION DAMAGE TO DOWNSTREAM COMPONENTS. 2. BORESCOPE MAY BE USED TO AVOID REMOVAL OF INLET SCREEN.

OPERATING PROBLEMS

FROM SHEET 4

HIGH PITCH NOISE FROM COMPRESSOR AREA. (EXAMPLE−WHINNING OR WHISTLING NOISE)

EXAMINE FIRST−STAGE COMPRESSOR BLADES FOR FOREIGN OBJECT DAMAGE (FOD) (REF.72−30−05) (REF. NOTES 1 AND 2)

SURGE DURING ACCELERATION

DO A CHECK FOR OPERATION OF COMPRESSOR BLEED VALVE AND CONDITION OF DIAPHRAGM (REF.75−30−00)

COMPRESSOR BLADES OK (REF.72−30−05). NO

CONTACT P&WC

REPAIR & RETURN TO SERVICE

REMOVE FCU. EXAMINE PREOFRMED PACKING AT BYPASS PORT DO YOU SEE SOME LEAKAGE?

YES NO DO A CHECK FOR LEAKAGE AT FUEL PUMP SHAFT CARBON SEAL FRONT AND BACK (REF. 73−10−02).

BLEED VALVE OPERATION OK.

NO

YES REPLACE DIAPHRAGM OR BLEED VALVE (REF. 75−30−00)

REPLACE PREFORMED PACKING AND FCU (REF. 73−23−01)

REPLACE BOTH FCU AND FUEL PUMP (REF. 73−20−00 / 73−10−02) YES

IS DAMAGE WITHIN REPAIR −ABLE LIMIT? (REF.72−30−05). YES

FUEL LEAKAGE AT FCU / FUEL PUMP FLANGE

DO THE COMPRESSOR WASH PROCEDURE (REF. 71−00−00)

NO

YES

CONTINUED ON SHEET 6

EXAMINE FCU METERING ORIFICE AT COMPRESSOR DELIVERY AIR INLET ELBOW FOR BLOCKAGE OR LEAKAGES. CORRECT AS NECESSARY.

REPLACE FUEL PUMP (REF. 73−10−02). DO A CHECK FOR INDICATION OF FCU BEARING FUEL CONTAMINATION.

YES

NO SEND ENGINE TO AN APPROVED P&WC OVERHAUL FACILITY FOR LIGHT OVERHAUL.

REPLACE FCU (REF. 73−20−00)

NO RETURN FCU TO SERVICE

CONTINUED ON SHEET 6

ICN-00198-G000008730-001-01 Engine Operating Fault Isolation Chart Figure 102 (Sheet 5) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

CONTINUED ON SHEET 7

CONTINUED FROM SHEET 5

EXAMINE FIRST−STAGE COMPRESSOR BLADES FOR FOREIGN OBJECT DAMAGE (FOD) (REF. 72−30−05 MAINTENANCE PRACTICES) (REF. NOTE 2)

COMPRESSOR BLADES OK YES

NO

EXAMINE THE FUEL PUMP DISCHARGE FILTER FOR CONTAMINATION (REF. 73−10−02 MAINTENANCE PRACTICES) IS THERE ANY CONTAMINATION? NO

SEND ENGINE TO A P&WC APPROVED OVERHAUL FACILITY.

YES

REPLACE THE FUEL PUMP DISCHARGE FILTER (REF. 73−10−02 MAINTENANCE PRACTICES) AND RETURN TO SERVICE.

REPLACE FCU (REF. 73−20−00).

ICN-00198-G000008731-001-01 Engine Operating Fault Isolation Chart Figure 102 (Sheet 6) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING PROBLEMS CONTINUED ON SHEET 8

CONTINUED FROM SHEET 6

OVERTEMPERATURE (MAX ALLOWABLE TEMPERATURE HAS BEEN EXCEEDED)

*

CHECK TEMPERATURE INDICATING SYSTEM. RECTIFY AS NECESSARY

YES

CHECK ENGINE OVERTEMPERATURE CHART (REF. 71−00−00). INSPECT AND REMOVE ENGINE AS APPLICABLE ENGINE REMOVED

PROCEED AS NOTED ON OVERTEMPERATURE CHART (REF. 71−00−00)

NO

TURBINE INSPECTION O.K.

* NOTE: ON TWIN AND MULTI − ENGINED AIRCRAFT, CROSS GENERATOR STARTS MAY RESULT IN HIGH T5 TEMPERATURE INDICATIONS

CHECK TORQUE INDICATING SYSTEM. RECTIFY AS NECESSARY

CONTINUED ON SHEET 8

ICN-00198-G000008732-001-01 Engine Operating Fault Isolation Chart Figure 102 (Sheet 7) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING PROBLEMS

CONTINUED FROM SHEET 7

CHECK AIR INLET AND COMPRESSOR FOR CONTAMINATION BUILD−UP

CARRY OUT COMPRESSOR WASH PROCEDURE (REF. 71−00−00)

YES COMPRESSOR DIRTY NO

CHECK FOR EXCESSIVE AIRFRAME ACCESSORY POWER LOADING (REF. AIRFRAME MANUAL)

ICN-00198-G000008733-001-01 Engine Operating Fault Isolation Chart Figure 102 (Sheet 8) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING PROBLEMS CONTINUED FROM SHEET 8

CONTINUED ON SHEET 10

TEMPERATURE LIMITED

FLAMEOUT

VIBRATION

CHECK AIRFRAME INSTALLATION FUEL SUPPLY SOURCE. MAKE SURE FREE OF ICE OR WATER CONTAMINATION

PROPELLER DAMAGED OR BLADE ANGLE SLIPPED. ADJUST AND/OR REPLACE AS NECESSARY (REF. AIRFRAME MANUAL)

REFER TO "HIGH T5 TEMPERATURE" ON PERFORMANCE CHECK CHART

IF AIRFRAME FUEL SOURCE IS SATISFACTORY, LOOSEN INLET TUBE AT FCU AND CHECK FOR FUEL FLOW DURING MOTORING ENGINE. NO FLOW APPARENT, REPLACE FUEL PUMP

INSPECT ENGINE FOR LOOSE MOUNTING BRACKETS CHECK THROUGH EXHAUST PORTS FOR POWER TURBINE DAMAGE

REMOVE AIR INLET SCREEN (REF. 72−20−00) AND INSPECT 1ST STAGE COMPRESSOR FOR SIGNS OF DAMAGE

NO

RETURN ENGINE TO APPROVED OVERHAUL FACILITY

TURBINE AND COMPRESSOR CHECKS O.K. YES CHECK COMPRESSOR AIR BLEED VALVE OPERATION (REF. 75−30−00)

IF FUEL SUPPLY CHECKS ARE O.K., DEFECT DUE TO POSSIBLE AIR LOCK. RESTART ENGINE TO CARRY OUT SELF−BLEEDING OPERATION

CONTINUED ON SHEET 10

ICN-00198-G000008734-001-01 Engine Operating Fault Isolation Chart Figure 102 (Sheet 9) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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OPERATING PROBLEMS CONTINUED FROM SHEET 9

CHECK ACCELERATION TIME OF ENGINE (REF. 71−00−00)

YES ACCELERATION TIME O.K. NO

NO

INSPECT ENGINE FOR "FOD" OR TURBINE DAMAGE

CHECK FCU FOR CONTAMINATION OR CORROSION. FCU CONTAMINATION YES REPLACE FCU (REF. 73−20−00)

CHECK FUEL MANIFOLD ADAPTERS AND NOZZLES

VERIFY FUEL HEATER FOR HIGH OPERATING TEMPERATURE (REF. 71−00−00, ADJUSTMENT/TEST) REPLACE IF NECESSARY

ICN-00198-G000008735-001-01 Engine Operating Fault Isolation Chart Figure 102 (Sheet 10) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING PROBLEMS CONTINUED ON SHEET 12

CONTINUED FROM SHEET 10

SQUEAL NOISE AT DECELERATION OR DURING MOTORING

LOW POWER (ALL PARAMETERS LOW)

CHECK OPERATION OF INDICATING SYSTEM. RECTIFY AS NECESSARY

MAKE SURE OPERATING PROCEDURES WERE PROPERLY CARRIED OUT

CHECK FUEL PUMP. IF PUMP IS SOURCE CONTINUE IN SERVICE * * SUNSTRAND FUEL PUMP PRESSURE PLATES NORMALLY SQUEAL AT LOW Ng.

CHECK FOR INCORRECT ADJUSTMENT OR DISCONNECTED CONTROL LINKAGES (REF. 76−00−00 OR AIRFRAME MANUAL)

IF CONTROL LINKAGES ARE SATISFACTORY, CARRY OUT CHECKS ON PROPELLER GOVERNOR (PNEUMATIC SECTION). IF DEFECTIVE, REPLACE GOVERNOR (REF. 61−20−00)

CHECK P3 AIR BLEED DELIVERY TUBES UP TO P3 TUBE FCU ELBOW FOR POSSIBLE LEAKS OR RESTRICTIONS. FOR POST−SB1205 OR SB1253, REPLACE AIR FILTER IF NECESSARY (REF. 73−10−07)

CONTINUED ON SHEET 12

ICN-00198-G000008736-001-01 Engine Operating Fault Isolation Chart Figure 102 (Sheet 11) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING PROBLEMS

CONTINUED FROM SHEET 11

CHECK FCU MAX SPEED SETTING (REF. 71−00−00)

IF FCU CHECKS ARE O.K., CHECK FUEL NOZZLES FOR POSSIBLE RESTRICTIONS (REF. 73−10−05)

IF FUEL NOZZLES ARE O.K., POSSIBLE FAULT DUE TO CONTAMINATED FCU. CHECK AND REPLACE AS NECESSARY

VERIFY FUEL HEATER FOR HIGH OPERATING TEMPERATURE (REF. 71−00−00, ADJUSTMENT/TEST) REPLACE IF NECESSARY

ICN-00198-G000008737-001-01 Engine Operating Fault Isolation Chart Figure 102 (Sheet 12) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING PROBLEMS CONTINUED FROM SHEET 11 UNUSUAL NOISES ENGINE INTERNAL RUBBING OR SCRAPING NOISES. COMPRESSOR OR TURBINE ROTORS DO NOT ROTATE FREELY, DECELERATE OR RUN DOWN EASILY ON ENGINE SHUT DOWN.

T5 TOO HIGH AT SHUT DOWN

CHECK COMPRESSOR FOR SHORT AND ABRUPT DECELERATION OR RUN DOWN TIME.

RESTRAIN PROPELLER AND MOMENTARILY ROTATE COMPRESSOR WITH STARTER. CHECK FOR EVIDENCE OF COMPRESSOR TURBINE RUB, IF ONLY LIGHT RUBBING AUDIBLE, RESTART ENGINE AND ALLOW NORMAL PERIOD OF COOLING AT GROUND IDLE PRIOR TO SHUT DOWN.

CHECK REAR MOUNTED ACCESSORIES FOR DRAG OR INTERFERENCE OF ROTATING COMPONENTS.

ON START UP, SLOW PROPELLER ACCELERATION, ABRUPT DECELERATION ON SHUT DOWN OR PROPELLER STIFF TO TURN.

ROTATE PROPELLER. CHECK FOR RUBS AND SCRAPING. INSPECT POWER TURBINE ROTOR AND EXHAUST AREAS FOR EVIDENCE OF DISTRESS (REF. 72−50−04) REMOVE POWER SECTION AND INSPECT FOR COMPRESSOR TURBINE BLADE TIP TO SHROUD RUB (REF. 72−50−02)

INSPECT THROUGH EXHAUST PORTS, EXHAUST AREAS AND POWER TURBINE FOR EVIDENCE OF DISTRESS. POSSIBLE PROPELLER SHAFT OIL TRANSFER HOUSING SEIZURE

LOOSE OR WORN NO. 3 BEARING COVER (PRE−SB1430)

RETURN TO OVERHAUL FACILITY FOR REPAIR

INSPECT AND REPLACE AS NECESSARY (REF. 72−50−04)

ICN-00198-G000008738-001-01 Engine Operating Fault Isolation Chart Figure 102 (Sheet 13) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING & PERFORMANCE CHECK PROBLEMS CONT’D ON SHEET 2

IDLE SPEED INCORRECT

HIGH Ng

CHECK INDICATING SYSTEM. RECTIFY AS NECESSARY

CHECK FOR INCORRECT CONTROL LINKAGE RIGGING. RE−ADJUST (REF. 76−00−00)

CARRY OUT COMPRESSOR WASH PROCEDURE (REF. 71−00−00) CARRY OUT PROPELLER GOVERNOR CHECKS (REF. 71−00−00)

IF RIGGING AND CONTROL CHECKS ARE O.K., CHECK P3 AIR DELIVERY TUBES UP TO P3 TUBE FCU ELBOW FOR POSSIBLE LEAKS OR RESTRICTIONS. RECTIFY OR REPLACE AS NECESSARY.

IF FAULT STILL APPARENT, CHECK OPERATION OF COMPRESSOR BLEED VALVE AND CONDITION OF DIAPHRAGM (REF. 75−30−00) REPLACE DIAPHRAGM OR BLEED VALVE (REF. 75−30−00)

NO

COMPRESSOR BLEED VALVE OPERATION O.K. YES CARRY OUT ENGINE RUN AND CHECK FOR AIR LEAKS AT ENGINE FLANGES. RECTIFY AS NECESSARY

CHECK IDLE SPEED SETTING ON FCU (REF. 71−00−00). ADJUST AS NECESSARY OR REPLACE FCU (REF. 73−20−00)

INSPECT ENGINE FOR "FOD" OR TURBINE DAMAGE (REF. 71−00−00)

CARRY OUT HOT SECTION INSPECTION (REF. 72−00−00) HIGH Ng WITH T5 AND FUEL FLOW WITHIN ACCEPTABLE LIMITS. REPLACE POWER TURBINE VANE RING WITH ONE HAVING SMALLER CLASS AVERAGE.

C184187 Engine Performance Fault Isolation Chart Figure 103 (Sheet 1 of 9) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING & PERFORMANCE CHECK PROBLEMS FROM SHEET 1

CONT’D ON SHEET 3 HIGH FUEL FLOW AT ALTITUDE

MISMATCH IN TWIN ENGINE INSTALLATION (RAPID ACCELERATION OF ONE ENGINE)

CHECK FUEL INDICATING SYSTEM AND AIRFRAME FUEL TANK BLEED (REF. AIRFRAME MANUAL)

CHECK ENGINE RIGGING CHECK AND MAKE SURE Px METERING ORIFICE IS INSTALLED IN ELBOW OF FCU Px METERING O.K. CHECK SETTING OF FCU ACCELERATION DOME. ADJUST AS NECESSARY (REF. 71−00−00) IDLE SPEED SETTING INCORRECT. RE−ADJUST AS NECESSARY

INDICATING AND AIRFRAME FUEL SYSTEM O.K. CHECK COMPRESSOR BLEED VALVE OPERATION AND CONDITION OF DIAPHRAGM (REF. 75−30−00)

REPLACE DIAPHRAGM OR BLEED VALVE (REF. 75−30−00)

NO

COMPRESSOR BLEED VALVE OPERATION O.K. YES

CARRY OUT COMPRESSOR WASH PROCEDURE (REF. 71−00−00) IF ADJUSTMENTS FAIL TO CORRECT PROBLEM, REPLACE FCU (REF. 73−20−00)

CARRY OUT ENGINE RUN AND CHECK FOR AIR LEAKS AT ENGINE FLANGES. RECTIFY AS NECESSARY

C29865 Engine Performance Fault Isolation Chart Figure 103 (Sheet 2) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING & PERFORMANCE CHECK PROBLEMS CONT’D ON SHEET 5

FROM SHEET 2

HIGH T5 TEMPERATURE INDICATIONS

HIGH FUEL FLOW

CHECK INSTRUMENTATION OPERATION (REF. AIRFRAME MANUAL)

IF INSTRUMENTATION AND OPERATING PROCEDURES ARE O.K., CARRY OUT COMPRESSOR WASH PROCEDURE (REF. 71−00−00)

AT IDLE SPEED, WITH Ng DECREASING

YES

CHECK FUEL HEATER. OK? NO

CHECK FOR EXCESSIVE AIRFRAME ACCESSORY POWER LOADING OR BLEED AIR LEAKS IN AIRFRAME SYSTEM. RECTIFY AS NECESSARY (REF. AIRFRAME MANUAL)

CHANGE FUEL HEATER.

IF AIRFRAME ACCESSORY LOADINGS ARE O.K., CHECK COMPRESSOR BLEED VALVE OPERATION AND CONDITION OF DIAPHRAGM (REF. 75−30−00)

CONT’D ON SHEET 4

C29866A Engine Performance Fault Isolation Chart Figure 103 (Sheet 3) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING & PERFORMANCE CHECK PROBLEMS FROM SHEET 3

NO

COMPRESSOR BLEED VALVE OPERATION O.K. YES

REPLACE DIAPHRAGM OR BLEED VALVE (REF. 75−30−00)

CARRY OUT ENGINE RUN AND CHECK FOR AIR LEAKS AT ENGINE FLANGES. RECTIFY AS NECESSARY

NO LEAKS APPARENT AT ENGINE FLANGES. CARRY OUT HOT SECTION INSPECTION (REF. 72−00−00)

CHECK T5 SENSING SYSTEM. REPAIR OR REPLACE COMPONENTS AS NECESSARY (REF. 77−20−00)

HIGH T5 WITH Ng AND FUEL FLOW WITHIN ACCEPTABLE LIMITS. REPLACE POWER TURBINE VANE RING WITH ONE HAVING LARGER CLASS AVERAGE (REF. 72−50−03)

C29867 Engine Performance Fault Isolation Chart Figure 103 (Sheet 4) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING & PERFORMANCE CHECK PROBLEMS FROM SHEET 3

FLUCTUATING ENGINE PARAMETERS (FUEL FLOW, Ng, T5, Nf, TORQUE)

CHECK INDICATING SYSTEMS YES

YES

CONT’D ON SHEET 6

FLUCTUATIONS CONTINUE YES Np FLUCTUATIONS

CHECK PROPELLER GOVERNOR. ADJUST OR REPLACE AS NECESSARY (REF. 71−00−00 / 61−20−00)

T5 FLUCTUATIONS

TORQUE FLUCTUATIONS

CHECK FOR INTERMITTENT CONTACT OR GROUNDING IN T5 SYSTEM (REF. AIRFRAME MANUAL)

CHECK MAIN OIL FILTER FOR METAL (POSSIBLE GEARBOX PROBLEM)

CHECK PROPELLER OVERSPEED GOVERNOR SETTING. ADJUST AS NECESSARY. REPLACE IF UNABLE TO ADJUST (REF. AIRFRAME MANUAL)

CHECK FOR STICKING OF BETA VALVE MECHANISM. CHECK PROPELLER FEEDBACK RING FOR RUNOUT, AND RODS FOR FULL AND FREE TRAVEL CHECK FOR CORRECT PROPELLER LOW BLADE ANGLE PICKUP REPLACE PROPELLER GOVERNOR IF FLUCTUATIONS PERSIST (REF. 61−20−00)

C29868 Engine Performance Fault Isolation Chart Figure 103 (Sheet 5) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING & PERFORMANCE CHECK PROBLEMS FROM SHEET 5

FUEL FLOW AND/OR Ng FLUCTUATIONS (WITH OR WITHOUT Np AND/OR TORQUE) LEAK CHECK FUEL CONTROL SYSTEM PNEUMATIC SYSTEM. RECTIFY ANY LEAKS AS NECESSARY (REF. AIRCRAFT MAINTENANCE MANUAL)

DISCONNECT Py LINE AT FCU, AND BLANK BOTH Py LINE AND FCU CONNECTION

FLUCTUATIONS CONTINUE? NO

YES

REPLACE PROPELLER GOVERNOR (REF. 61−20−00)

CHECK AIRFRAME SIDE OF FUEL DELIVERY SYSTEM

POSSIBLE STICKING OF THERMOSTATIC ELEMENT IN OIL−TO−FUEL HEATER CAUSING VAPOR LOCKS. REPLACE UNIT AS NECESSARY (REF. 73−10−01)

CHECK FOR BLUE DYE OR OTHER EVIDENCE OF FUEL LEAKAGE FROM VENT HOLE ON UNDERSIDE OF FCU (REF. 73−20−00, INSPECTION/CHECK) CONT’D ON SHEET 7

C29869 Engine Performance Fault Isolation Chart Figure 103 (Sheet 6) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING & PERFORMANCE CHECK PROBLEMS FROM SHEET 6 NO

YES

LEAKAGE EVIDENT

REPLACE FCU (REF. 73−20−00)

REMOVE FCU (REF. 73−20−00) MARKING RELATIVE POSITION OF FCU DRIVE AND FUEL PUMP SPLINES

CHECK FOR WORN COUPLING AND FCU DRIVE SPLINE WEAR

NO

CHECK FOR LEAKAGE AT FUEL PUMP PREFORMED PACKING

LEAKAGE FOUND

WEAR FOUND

YES

REPLACE COUPLING AND/OR FCU (REF. 73−20−00)

YES

NO

REPLACE PREFORMED PACKING AT FCU/PUMP INTERFACE (REF. 73−20−00)

CHECK FOR LEAKAGE AT FUEL PUMP SHAFT CARBON SEAL, FRONT AND BACK

CONT’D ON SHEET 8

C29870 Engine Performance Fault Isolation Chart Figure 103 (Sheet 7) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

OPERATING & PERFORMANCE CHECK PROBLEMS FROM SHEET 7

YES

LEAKAGE FOUND NO

REPLACE FUEL PUMP (REF. 73−10−02). CHECK FCU BEARING FOR EVIDENCE OF FUEL CONTAMINATION

NO

REPLACE FCU (REF. 73−20−00)

YES

EVIDENCE OF FCU DRIVE BEARING WASHOUT AND/OR WEAR NO

REPLACE FCU (REF. 73−20−00)

CHECK FOR FREEDOM FROM RESTRICTION AND CORRECT INSTALLATION OF FUEL PUMP DRAIN

REFIT EXISTING FCU (REF. 73−20−00) WITH FCU SPLINES INDEXED 90 DEGREES FROM ORIGINAL LOCATION WITH RESPECT TO FUEL PUMP SPLINES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

NOTE: 1.

Review ECTM data, pilot reports and maintenance log book entries and troubleshooting for the last 6 months. Hot section components and performance gradually deteriorate as running time accumulates. The deterioration rate varies according to operating conditions (environment and type of operation) and for different engine modification standards. If engine performance apparently improves T5 decrease without maintenance action, check indicating systems (usually T5 system is at fault).

NOTE: 2.

A rapid shift in engine parameters is usually the result of an indicating system defect.

NOTE: 3.

To extend hot section life, the following preventive maintenance, based on the increase in T5 from the values established at engine installation (engine performance/ground power check or ECTM), is recommended: For a 10 C (20 F) increase in T5, do a performance recovery wash. In addition, indicating system and engine performance/ground power checks are recommended to ensure reliable engine performance data. Also, test spray pattern or refurbish fuel nozzles. For a 15 C (27 F) increase in T5 or a 1 to 1.5% decrease in Ng, do a borescope inspection of the combustion chamber, small exit duct, CT stator vanes and CT blades. In addition, do the maintenance recommended above.

NOTE: 4.

A significant difference between ECTM and engine performance/ground power check parameters indicate that the defect is within the aircraft air bleed system on the affected engine (air bleed is off during an engine performance/ground power check). An alternative method is to do an engine performance/ground power check with air bleed ON then OFF. Compare the shift parameters for the engines on the same aircraft. A significant difference indicates bleed sharing problems. For single engine installations, contact P&WC for typical parameter shift recommendations.

NOTE: 5.

When an engine is temperature limited on climb or cruise and the engine performance/ground power check is satisfactory, the defect is within the aircraft bleed system of the affected engine.

NOTE: 6.

An increase in temperature without other parameter shifts may be the result of defective fuel nozzles or a deteriorated combustion liner altering combustion profile and changing the temperature distribution.

NOTE: 7.

Compressor deterioration (which increases Ng) and hot section normal deterioration (which reduces Ng) may balance each other and the effect deterioration has on Ng will be very small or zero (i.e. Ng will remain constant).

NOTE: 8.

When the engine is running on the ground, inlet plenum air pressure is lower than ambient air pressure. Therefore, if the inlet or firewall seals are damaged, hot air from around the engine may be ingested causing a temperature increase. Similarly, if the wind direction is from the rear, exhaust gas may be ingested and temperature increased.

NOTE: 9.

The relationship between T5 and the temperature in front of CT stator may change due to hot section component deterioration altering combustion profile and/or gas path temperature distribution. This may affect the T5 trim and the indicated T5 and the relationship between T5 and the temperature in front of the CT vane used for engine certification. A T5 trim verification on the wing or in the test cell will confirm a shift in the indicated temperature.

NOTE: 10.

To remove doubts, a T5 system check (including individual thermocouple checks) is recommended before doing a complete HSI.

C65318 Engine Performance Fault Isolation Chart Figure 103 (Sheet 9) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 101, ECTM Shift Fault Isolation Chart ENGINE PARAMETERS All parameters UP

PROBABLE CAUSE

ACTION REQ’D

REMARKS

AC/ engine indicating systems

Inspect

Repair as req’d

Air inlet door blocked

Inspect

Repair as req’d

Bypass door or ice vane mis-rigged.

Inspect

Repair as req’d

Compressor FOD, rub, erosion

Inspect and/or repair

Remove engine if limits are exceeded

Compressor contaminated/dirty

Compressor performance recovery wash

Bleed valve open

Inspect

Repair as req’d

P2.5 air leaks from engine/airframe system

Inspect

Repair as req’d

PT stator vanes burned/flow area increased. PT blade tip oxidation/rub.

Inspect

Repair as req’d

Hot start

Inspect hot section and check log book

Do applicable overtemperature inspection

All parameters variable

AC/engine torque and Np indicating system

Inspect

Repair as req’d

T5 UP or DOWN, Ng, Wf constant

AC/engine indicating system (Ref. Note 1)

Inspect . If applicable, do on-wing system trim.

Repair as req’d. T5 usually decreases when probes are unserviceable.

Fuel nozzle deterioration

Inspect (Ref. NOTE 1)

Clean as req’d

Ng UP or DOWN, T5, Wf Constant.

AC/engine Ng indicating system

Inspect

Repair as req’d.

Wf UP or DOWN, T5, Ng, constant.

AC/engine indicating system

Inspect

Repair as req’d.

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TABLE 101, ECTM Shift Fault Isolation Chart (Cont’d) ENGINE PARAMETERS Wf, T5 UP, Ng down

Wf, T5 UP, Ng constant

PROBABLE CAUSE

ACTION REQ’D

REMARKS

CT stator vanes burned/flow area increased. CT blade tip oxidation/rub.

Inspect CT stator, and CT blades.

Normal hot section time related deterioration

Do an HSI if T5 limit exceeded.

P3 leaks from AC/engine system

Inspect

Repair as req’d

Gas generator case cracked at fuel nozzle or P3 bleed pads. Diffuser exit ducts cracked or loose.

Inspect

Replace engine if defect confirmed.

Leaking gas generator drain valves, C flange, fuel nozzle gasket, or T5 harness seal.

Inspect

Replace engine if defect confirmed.

Concurrent hot section and compressor deterioration

Inspect CT stator and CT blades, and compressor.

Do an HSI or send engine for overhaul.

If limits exceeded, do an HSI.

NOTE: 1. An increase in T5 without other parameter shifts may be the result of defective fuel nozzles or a deteriorating combustion chamber liner altering combustion profile and gas path temperature distribution. NOTE: 2. The relationship between T5 and the temperature in front of the CT stator may change due to hot section component deterioration altering combustion profile and/or gas path temperature distribution. This may affect the T5 trim and the indicated T5, and the relationship between T5 and the temperature in front of the CT stator used for engine certification. A T5 trim verification on-wing or in a test cell will confirm a shift in the indicated temperature.

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

CONTINUED ON SHEET 3

LUBRICATION PROBLEMS NOTE 1: OIL PRESSURE LOWER THAN USUAL BY APPROXIMATELY 24 PSID SHOWS THAT THE MAIN OIL FILTER IS BYPASSED. NOTE 2: EXAMINE THE COARSE HAT−TYPE SCREEN ATTACHED TO THE INNER END OF THE FILTER FOR CONTAMINATION. IF YOU FIND DEBRIS, IT CAN BE CONSIDERED THAT A BYPASS HAS OCCURRED.

LOW OIL PRESSURE AND/OR OIL FILTER BYPASS (REF. NOTE 1) INSUFFICIENT OIL. DO AN OIL LEVEL CHECK (REF. SERVICING).

HIGH OIL PRESSURE

IF OIL LEVEL IS OK, DO A CHECK OF OIL PRESSURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL).

DO A CHECK OF OIL PRESSURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL).

IS INDICATING SYSTEM OK?

NO

NO

IS INDICATING SYSTEM OK? YES

YES CORRECT FAULT ON INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL).

DO AN INSPECTION OF THE CHIP DETECTOR AND THE STRAINER FOR METALLIC DEBRIS.

NO

REMOVE AND DO AN INSPECTION OIL FILTER (REF. 79−20−02) (REF. NOTE 2). DO THE FILTER PATCH CHECK DEBRIS ANALYSIS (REF. 70−00−00). IS CARBON DEBRIS AMOUNT CLASSIFIED AS MAJOR?

NO

IS THERE METALLIC YES DEBRIS?

REFER TO FIGURE 105 SHEET 1

REPLACE THE OIL FILTER (REF. 79−20−02).

YES THE ENGINE HAS A RECENT HISTORY NO (NOT MORE THAN 200 FLIGHT HOURS) OF GENERATING CARBON DEBRIS? YES DO AN OIL FILTER PERIODIC INSPECTION AT 100 HOURS. REPLACE FILTER ELEMENT AT 300 HOURS INTERVAL (REF. 79−20−02). CONTACT P&WC FOR MORE ACTION TO START OIL FILTER INSPECTION/REPLACEMENT INTERVALS.

DO A CHECK OF OIL PRESSURE (REF. 71−00−00).

IF OK, SEND THE ENGINE BACK TO SERVICE.

IF NOT OK, DO A CHECK OF EXTERNAL OIL TUBES AND OIL COOLER FOR LEAKS. CORRECT AS NECESSARY.

CONTINUED ON SHEET 2

ICN-00198-G000025183-001-01 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 1 of 8) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LUBRICATION PROBLEMS FROM SHEET 1

FROM SHEET 1

PRESSURE RELIEF VALVE MALFUNCTION. REMOVE, CLEAN AND INSPECT (REF. 72−60−00)

PRESSURE RELIEF VALVE MALFUNCTION. REMOVE, CLEAN AND INSPECT (REF. 72−60−00)

RELIEF VALVE O.K.

NO

NO

YES

RELIEF VALVE O.K.

YES

REMOVE SPACER(S) FROM VALVE AS NECESSARY

REPLACE OIL PRESSURE RELIEF VALVE (REF. 72−60−00)

ADD SPACER(S) TO VALVE AS NECESSARY

C29873 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 2) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LUBRICATION PROBLEMS CONT’D ON SHEET 4

FROM SHEET 1

CHECK THE BREATHER TUBE FOR OBSTRUCTION ON ENGINE SIDE AND AIRFRAME SIDE SMOKE IN COCKPIT

OIL LEAK FROM COMPRESSOR INLET CASE OR INTO EXHAUST DUCT (ENGINE SIGNIFICANTLY NOSE DOWN)

CHECK FOR OIL LEAKAGE DUE TO DEFECTIVE PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING

CHECK OIL TANK LEVEL FOR OVERSERVICED CONDITION. LEVEL OK?

PREFORMED YES PACKING AND PLASTIC RING O.K. NO

INLET CASE OIL LEAK FOLLOWING MULTIPLE MOTORING CYCLES OR PROPELLER WINDMILLING IN FLIGHT? NO YES REPLACE PREFORMED PACKING AND/OR PLASTIC RING

VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE−SB1247), REPAIR IF NECESSARY AND PERFORM STATIC LEAK TEST

LAP CHECK VALVE (PRE−SB1247). RENEW PREFORMED PACKING (POST−SB1247). LAP CHECK VALVE AND SEAT (POST−SB1379). PERFORM STATIC LEAK TEST

LEAKAGE PERSISTS

CHECK AGB INTERNAL SCAVENGE PUMP NO INLET SCREEN FOR BLOCKAGE. OK?

CHECK FOR LEAKAGE AT PREFORMED PACKING ON ACCESSORY GEARBOX. RECTIFY AS NECESSARY

YES

CLEAN ENGINE AND RETURN TO SERVICE

CLEAN INLET SCREEN

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LUBRICATION PROBLEMS CONT’D ON SHEET 5

FROM SHEET 3

FLUCTUATING OIL PRESSURE

OIL PRESSURE FOLLOWS POWER LEVER AND WILL NOT RESPOND TO ADDITION OF SHIMS

INSUFFICIENT OR EXCESS OIL. CHECK OIL LEVEL

OIL LEVEL O.K. CHECK OIL PRESSURE INDICATING SYSTEM (REF. AIRFRAME MANUAL) RECTIFY FAULT ON INDICATING SYSTEM (REF. AIRFRAME MANUAL)

NO

INDICATING SYSTEM O.K.

OIL FILTER INSPECTION O.K. POSSIBLE PRESSURE RELIEF VALVE MALFUNCTION. CLEAN AND INSPECT

YES INSPECT OIL FILTER. CLEAN OR REPLACE AS NECESSARY

OIL FILTER INSPECTION O.K. POSSIBLE PRESSURE RELIEF VALVE MALFUNCTION. CLEAN AND INSPECT

REPLACE PRESSURE RELIEF VALVE AS NECESSARY

REPLACE PRESSURE RELIEF VALVE AS NECESSARY

REMOVE ACCESSORY GEARBOX AND CHECK OIL PUMP HOUSING FOR CRACKS

REPLACE OIL PUMP HOUSING

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LUBRICATION PROBLEMS

NOTES:

1. FOR GROUND OPERATION DECREASE IDLING IN FEATHER. 2. VERIFY PROPELLER RIGGING (CHECK PRIMARY BLADE ANGLE) (REF. AIRCRAFT MAINTENANCE MANUAL). 3. IF THE ENGINE HAS BEEN OPERATED FOR AN EXTENDED PERIOD (REF. 71−00−00, POWER PLANT − ADJUSTMENT/TEST FOR TIME LIMIT) ABOVE OIL TEMPERATURE LIMITS, THEN DO AN UNSCHEDULED INSPECTION FOR SUSTAINED RUNNING AT OIL TEMPERATURE OUTSIDE LIMITS (REF. INSPECTION).

CONTINUED FROM SHEET 4

CONTINUED ON SHEET 6

HIGH OIL TEMPERATURE (REF. NOTES 1 AND 2)

NO

CHECK OIL LEVEL. OIL LEVEL OK?

REPLENISH OIL (REF. SERVICING)

YES CORRECT FAULT ON INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

CHECK OIL TEMPERATURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL). OK? YES

CHECK AIRFRAME OIL COOLER SYSTEM FOR RESTRICTIONS OR MALFUNCTIONS (REF. AIRCRAFT MAINTENANCE MANUAL)

CORRECT FAULT ON OIL COOLER SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

OIL COOLER SYSTEM OK? YES HEAT SHIELD FAILURE. SEND ENGINE TO AN APPROVED P&WC OVERHAUL FACILITY.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LUBRICATION PROBLEMS FROM SHEET 5

EXCESSIVE OIL CONSUMPTION

INSUFFICIENT OR EXCESS OIL. CHECK OIL LEVEL (REF. 72−00−00)

EXCESS OIL. CHECK OIL TANK LEVEL FOR OVER−SERVICED CONDITION (REF. 72−00−00)

OIL LEVEL INSPECTION O.K. CHECK FOR OIL LEAKAGE DUE TO DEFECTIVE PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING (REF. 79−20−02)

EXCESS OIL. CHECK OIL TANK LEVEL FOR OVER−SERVICED CONDITION (REF. 72−00−00)

CHECK THE BREATHER TUBE FOR OBSTRUCTION ON ENGINE SIDE AND AIRFRAME SIDE

VISUALLY CHECK FOR EVIDENCE OF LEAKAGE OR RESTRICTIONS IN PRESSURE OR SCAVENGE OIL TUBES (REF. 79−20−00 / 79−20−01)

SCAVENGE OR OIL TUBES O.K. CHECK FOR LEAKAGE AT PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING (REF. 79−20−02)

CONT’D ON SHEET 7

CONT’D ON SHEET 7

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LUBRICATION PROBLEMS FROM SHEET 6

FROM SHEET 6

PREFORMED PACKING AND PLASTIC RING O.K.

NO

NO

YES

REPLACE PREFORMED PACKING AND/OR PLASTIC RING AS NECESSARY (REF. 79−20−02)

VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE−SB1247), REPAIR IF NECESSARY AND PERFORM STATIC LEAK TEST (REF. 79−20−02)

CONDITION OF CHECK VALVE SEAT (PRE−SB1247) OR PREFORMED PACKING (POST−SB1247) O.K. YES

NO

PREFORMED PACKING AND PLASTIC RING O.K. YES

VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE−SB1247), REPAIR IF NECESSARY AND PERFORM STATIC LEAK TEST (REF. 79−20−02)

LAP CHECK VALVE CONDITION OF CHECK VALVE NO (PRE−SB1247). RENEW SEAT (PRE−SB1247) OR PREFORMED PACKING PREFORMED PACKING (POST−SB1247). LAP CHECK (POST−SB1247) O.K. VALVE AND SEAT (POST−SB1379) (REF. 79−20−02) YES PERFORM STATIC LEAK TEST (REF. 79−20−02)

EXCESSIVE BACK PRESSURE IN SCAVENGE SYSTEM. CHECK FOR RESTRICTIONS IN OIL SCAVENGE TUBES, PUMP SCREEN AND OIL−TO−FUEL HEATER TUBES. RECTIFY AS NECESSARY. REPLACE PRESSURE RELIEF VALVE AS NECESSARY (REF. 72−60−00) CONT’D ON SHEET 8

C29879 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 7) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

LUBRICATION PROBLEMS FROM SHEET 7

YES

CHECK EXHAUST AREA FOR TRACES OF OIL. IS OIL VISIBLE NO

REMOVE POWER SECTION (REF. 72−00−00). CHECK POWER TURBINE AND COMPRESSOR TURBINE AREAS FOR TRACES OF OIL

IF EVIDENT IN POWER TURBINE AREA, RETURN POWER SECTION TO APPROVED OVERHAUL FACILITY

IF EVIDENT IN COMPRESSOR TURBINE AREA, REMOVE DISK, ASSEMBLY OF VANE RING AND LARGE EXIT DUCT. INSPECT NO. 2 BEARING STATOR AIRSEAL GASKET. REPLACE AS NECESSARY. CHECK AIR PRESSURIZING HOLES AT REAR OF MOUNTING FLANGE OR EXIT DUCTS FOR BLOCKAGE. CLEAR AS NECESSARY

POSSIBLE FAULT DUE TO INTERNAL LEAKAGE IN OIL−TO−FUEL HEATER. REPLACE OIL−TO−FUEL HEATER (REF. 73−10−01)

FAULT STILL APPARENT. CHECK FOR DEFECTIVE OR COCKED CENTRIFUGAL BREATHER CARBON SEAL. REPLACE AS NECESSARY (REF. 72−60−01)

CARBON SEAL SATISFACTORY. CHECK PREFORMED PACKINGS ON ACCESSORY GEARBOX. RECTIFY AS NECESSARY (REF. 72−60−00)

RETURN ENGINE TO APPROVED OVERHAUL FACILITY

C29881 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 8) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

CHIP DETECTOR CIRCUIT COMPLETION

REMOVE AND INSPECT CHIP DETECTOR (REF. 79−20−02)

REMOVE AND INSPECT ASSOCIATED STRAINER AND MAIN OIL FILTER (REF. 79−20−02)

Cont’d on Sheet 4

CLASSIFY DEBRIS (REF. 79−20−02)

CLEAN AND RE−INSTALL OIL FILTER, STRAINER AND CHIP DETECTOR. RETURN ENGINE TO SERVICE

YES IS DEBRIS ALLOWABLE?

RECORD CATEGORY, TYPE AND ORIGIN OF DEBRIS

Cont’d on Sheet 4

NO IS DEBRIS NON−ALLOWABLE CATEGORY 1 ?

YES

RECORD CATEGORY AND TYPE OF DEBRIS AND REMOVE MODULE/ENGINE (REF. NOTE 1)

NO IS MAGNETIC DEBRIS NON−ALLOWABLE CATEGOR 2 OR 3 ?

YES

NO IS DEBRIS CATEGORY 2 BRONZE (I.E., IT ORIGINATES IN RGB ?)

NO

RECORD ENGINE TIME CATEGORY, TYPE AND ORIGIN OF DEBRIS

YES RECORD MODULE TIME CATEGORY, TYPE AND ORIGIN OF DEBRIS

Cont’d on Sheet 3

Cont’d on Sheet 2

C23263C Engine Lubricating Oil Contamination Fault Isolation Chart Figure 105 (Sheet 1 of 4) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

Cont’d from Sheet 1 NON−ALLOWABLE CATEGORY 2 BRONZE DEBRIS ORIGINATING IN RGB

HAS RGB GENERATED DEBRIS WITHIN LAST 400 HOURS (REF. NOTE 3) NO

YES

CLEAN AND INSTALL OIL FILTER, CHIP DETECTOR AND STRAINERS

HAS QUANTITY OF CURRENT DEBRIS INCREASED OR IS GEARBOX CONSISTENTLY GENERATING DEBRIS? YES

NO

SCHEDULE ENGINE REMOVAL WITHIN 10 FLIGHT HOURS OF CURRENTLY REPORTED DEBRIS

RUN ENGINE AT 80% T.O. POWER FOR 10 MINUTES (REF. ADJUSTMENT/TEST)

CLEAN AND INSTALL CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS

REMOVE AND INSPECT CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS. IS DEBRIS CATEGORY 2 BRONZE FOUND? YES NO DRAIN AND FLUSH OIL SYSTEM CLEAN AND INSTALL MAIN OIL FILTER, CHIP DETECTOR AND STRAINERS. FILL UP OIL SYSTEM

RUN ENGINE AT 80% FOR 10 MINUTES

REMOVE AND INSPECT OIL FILTER, CHIP DETECTOR AND STRAINERS. CATEGORY 2 BRONZE DEBRIS GENERATED? NO

YES

REMOVE ENGINE

CLEAN AND INSTALL CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS RETURN ENGINE TO SERVICE AND CHECK CHIP DETECTOR AND MAIN OIL FILTER AFTER 10 HOURS AND PROVIDING NO DEBRIS IS FOUND, AFTER 50 HOURS (REF. NOTE 2). IF DEBRIS IS FOUND, SEND TO LABORATORY FOR ANALYSIS

Cont’d on Sheet 4

C36863A Engine Lubricating Oil Contamination Fault Isolation Chart Figure 105 (Sheet 2) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

Cont’d from Sheet 1 NON−ALLOWABLE CATEGORY 2 OR 3 DEBRIS OTHER THAN BRONZE

HAS ENGINE GENERATED DEBRIS WITHIN 400 HOURS (REF. NOTE 3) NO

YES WERE THE RESULTS OF THE LAST LABORATORY ANALYSIS BEARING MATERIAL (REF. NOTE 4)

CLEAN AND INSTALL CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS

YES

NO

RUN ENGINE AT 80% FOR 10 MINUTES REMOVE ENGINE REMOVE AND INSPECT CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS. IS CATEGORY 2 OR 3 DEBRIS FOUND YES

NO

NO

IS THE QUANTITY OF DEBRIS SAME OR INCREASED OR IS ENGINE CONSISTENTLY GENERATING DEBRIS YES

DRAIN AND FLUSH OIL SYSTEM. CLEAN AND INSTALL CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS. FILL UP OIL SYSTEM

REMOVE ENGINE AT FIRST OPPORTUNITY OR WITHIN 10 HOURS

RUN ENGINE AT 80% FOR 10 MINUTES CLEAN AND INSTALL CHIP DETECTOR. MAIN OIL FILTER AND STRAINERS REMOVE AND INSPECT CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS. IS CATEGORY 2 OR 3 DEBRIS FOUND YES REMOVE ENGINE

NO RETURN ENGINE TO SERVICE AND CHECK CHIP DETECTOR AND MAIN OIL FILTER AND STRAINERS AFTER 10 HOURS AND PROVIDING NO DEBRIS IS FOUND, AFTER 50 HOURS (REF. NOTE 2). IF DEBRIS IS FOUND, SEND TO LABORATORY FOR ANALYSIS

Cont’d on Sheet 4

C36864B Engine Lubricating Oil Contamination Fault Isolation Chart Figure 105 (Sheet 3) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

Cont’d from Sheets 1, 2 and 3 DEBRIS ANALYSED AT LAB

WAS THE ENGINE GENERATING DEBRIS (REF. NOTE 5)

YES IS DEBRIS BEARING MATERIAL AMS6440/6444 (52100) OR AMS6490/6491 (M50) (SEE NOTE 6)

NO

YES

ENGINE MAY REMAIN IN SER− VICE. DO A CHIP DETECTOR AND FILTER CHECK AFTER 10 HOURS AND PROVIDING NO DEBRIS IS FOUND, AFTER 50 HOURS (REF. NOTE 2)

NO

REMOVE ENGINE YES

IS DEBRIS ALLOWABLE

INSPECT USING BORESCOPE (LABORATORY ANALYSED DEBRIS)

NO WAS MATERIAL AIR SEAL AMS4117, AMS4127, AMS4150, AMS5613, AMS5671, MOLY

WAS DEBRIS BRONZE CATEGORY 2 MATERIAL YES

IS ENGINE IN ACCEPTABLE CONDITION

NO CONTINUE IN SERVICE

YES

DO AN ADDITIONAL FILTER PATCH CHECK AFTER 10 HOURS AND PROVIDING NO DEBRIS IS FOUND, AFTER 50 HOURS (REF. NOTE 2)

NO

YES

ENGINE MAY REMAIN IN SERVICE. CHECK CHIP DETECTOR AND MAIN OIL FILTER STRAINER AFTER 10 HOURS AND IF NO DEBRIS IS FOUND AFTER 50 HOURS (REF. NOTE 2)

REMOVE ENGINE

IS LAB SEAL OR BRONZE MATERIAL FOUND (MAJOR OR MINOR CONTAMINANT) YES REMOVE ENGINE

NO RETURN ENGINE TO SERVICE

C36865B Engine Lubricating Oil Contamination Fault Isolation Chart Figure 105 (Sheet 4) P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

(2)

The following NOTES are referred to in Figure 105: NOTE: 1. Depending where the debris was found (i.e., strainer, main oil filter or chip detector) and the shape (i.e., tooth part, locking washer part etc.) a decision could be made concerning the removal of the affected module. Alternatively, remove engine. NOTE: 2. If no debris is found at the 50-hour check, return the oil filter and chip detector inspections to operator’s standard maintenance program intervals. NOTE: 3. Results of previous laboratory analysis and origin of debris should be determined within 50 hours of original detection of debris. NOTE: 4. Results of last sample must be known prior to continuing. NOTE: 5. It should have already been determined that the engine and not RGB mounted accessories are generating the debris. If propeller governor or O/S governor failure occurred before the original debris detection and the material could be identified as a propeller or O/S governor material then the engine may not be generating the debris and therefore could remain in service, if the components of the propeller governor or O/S governor are accounted for. NOTE: 6. Bearing inner and outer rings as well as rolling elements are made of steel AMS 6440/6444 (52100) or AMS 6490/6491 (M50). Bearing cages are made of steel AMS 6414/6415 (4340) or bronze AMS 4616, silver plated per AMS 2412. When only bearing cage material is generated (major or minor filter contaminant), this may indicate cage wear due to lack of lubrication and/or bearing damage causing rolling element instability.

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

ENGINE, TURBOPROP - MAINTENANCE PRACTICES 1.

General DELETED.

2.

Special Tools Information moved to TOOLS/FIX/EQUIP section.

3.

Special Equipment Information moved to TOOLS/FIX/EQUIP section.

4.

Consumable Materials Information moved to CONSUMABLE MATERIALS section.

5.

Suppliers and Supplier Services Information moved to CONSUMABLE MATERIALS section.

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Page 201/202 Feb 11/2000

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

ENGINE, TURBOPROP - SERVICING 1.

General A.

The following information and procedures are necessary for storage, preservation and depreservation of an engine or power section, and removal and installation in an appropriate fiberboard/reinforced fiberboard container, metal container or stand.

CAUTION:

TO PREVENT THE POSSIBLE BEARING DAMAGE SUCH AS BRINELLING, USE OF SHIPPING/STORAGE CONTAINER/SKID WITH SHOCK MOUNTS IS NECESSARY FOR ALL TRANSPORTATION OF AN ENGINE.

NOTE: For engine installation in airframe, refer to REMOVAL/INSTALLATION. 2.

Consumable Materials The consumable materials listed below are used in the following procedures.

3.

Item No.

Name

PWC03-001 PWC05-053 PWC05-054 PWC05-070 PWC05-077 PWC05-107 PWC06-007 PWC09-003 PWC09-005 or -006 PWC11-002 or -014

Oil, Engine Lubricating Polyethylene Sheet Bag, Polyethylene Tape, Pressure Sensitive Oil, Preservative Foam, Polyurethane Lubricant, Dry Film Compound, Sealing Sealant, Jointing Solvent, Cleaning

Special Tools The special tools listed below are used in the following procedures. Tool No.

Name

Application

PWC30077 PWC30128-4 PWC30269 PWC32080 PWC34300 PWC34752

Puller Puller Ring, Mounting Pad, Engine Mount Stand, Engine Adapter, Engine Mount Bracket, Lifting Stand Assembly, Engine Sling, Engine

Replaced by PWC30128-4 Replaces PWC30077

PWC50373 PWC51140 PWC51861-600

Obsolete - Replaced by PWC70907

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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Page 301 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

Tool No.

Name

PWC70099

Sling, Power Section (without prop.) Mounting Ring Adapter Stand Assembly, Engine Build Stand, Engine Assembly

PWC70334 PWC70792 PWC70907 PWC71835 4.

Application

Obsolete - Replaced by PWC71835 Alternate to PWC70907

Fixtures, Equipment and Supplier Tools Not Applicable

5. Lubricating Oil System A.

Lubricating Oil The lubricating oils specified for use in PT6A turboprop engines are detailed in Pratt & Whitney Canada, (P&WC) Service Bulletin 1001 and will be revised periodically to include recently approved oils. All oils listed in the bulletin are for use in commercially operated engines, and are approved for flight operation. In cases when oils approved by P&WC are not available and other oils have to be substituted, an operator must obtain prior approval or recommendations for use of such oil from: Pratt & Whitney Canada Corp. Att. Customer Support Services 1000 Marie-Victorin Longueuil, Quebec Canada J4G 1A1

B.

Oil Level Check To avoid overfilling of oil tank, and high oil consumption, an oil level check is recommended within 30 minutes after engine shutdown. Ideal interval is 15 to 20 minutes. If more than 30 minutes has passed, and the dipstick indicates that oil is needed, start the engine and run at ground-idle for five minutes, and recheck oil level as follows:

C.

Procedure (1)

Unlock filler cap and dipstick from filler neck at 11 o’clock position on accessory gearbox and remove filler cap.

(2)

Wipe the dipstick with clean lint free cloth.

CAUTION: WHEN THE FILLER CAP AND DIPSTICK/GAGE ASSEMBLY IS INSTALLED AND LOCKED, NO MOVEMENT IS ALLOWED. (3)

Install the cap/dipstick and lock.

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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Page 302 Jul 20/2020

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

t~l\nPORARY REVISl°GlfiJ( NO. _72-47 II

(PT6A-34, PT6A-34AG, PT6A-34B, PT6A-36)

INSERT Temporary Revision 72-47 facing page 302, Chapter 72-00-00 ENGINE, TURBOPROP - SERVICING PURPOSE: C.

The purpose of this temporary revision is to add oil analysis technology sampling procedure.

Procedure (1)

Unlock filler cap and dipstick from filler neck at 11 o'clock position on accessory gearbox and remove filler cap.

(2)

Wipe the dipstick with clean lint free cloth.

CAUTION:

WHEN THE FILLER CAP AND DIPSTICK/GAGE ASSEMBLY IS INSTALLED AND LOCKED, NO MOVEMENT IS ALLOWED.

(3)

Install the cap/dipstick and lock.

(4)

Remove the cap/dipstick.

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II

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I

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I

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I I

-

I

- -I

...

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-

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P&WC Proprietary Information. Subject to the restriction on the liHe page. The export control dassificalion with respect to this document is contained on the back of the tilie page.

72

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PRINTED IN CANADA Export Control Classifications: Canada· EIPA = NSR Canada - DPA = N Outside U.S.· EAR= Contains 10-25% 9E991 U.S. - EAR= 9E619.a.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TR 72-47

(5)

Check the oil tank contents against the markings on dipstick (markings correspond to U.S. quarts) and service as required. NOTE: 1. Pre-SB1249: Graduations on the dipstick indicate the oil level in U.S. quarts below maximum capacity of the oil tank. Normal cold oil level is one U.S. quart (0.83 Imp. quart, 0.95 liters) below the maximum (MAX) mark on dipstick; e.g. a dipstick reading of 3 will indicate the system requires two U.S. quarts to replenish to normal level if the oil is cold and three U.S. quarts if the oil is hot. NOTE: 2. Post-SB1249: Graduations on the dipstick indicate oil level in U.S. quarts below the maximum capacity of oil tank. Normal cold oil level is the MAX COLD mark on the dipstick. Normal hot oil level is the MAX HOT mark on the dipstick. A dipstick reading of 3 will indicate the system requires two U.S. quarts to replenish to normal level if the oil is cold and three U.S. quarts if the oil is hot. NOTE: 3. If the engine is nose high or nose low, compensation must be made to avoid over or under servicing. NOTE: 4. Filling the oil to the maximum level may result in high consumption rate, with the oil exiting through the AGB breather. On some engines, this may also occur with the oil level at one or two US quarts below the maximum level. In such cases, operators are advised to service the oil to the level that results in acceptable consumption, down to 3 quarts below the maximum, if necessary. For engines with an oil sight gauge, keep the level within the green band. This practice is acceptable, due to the large usable oil quantity, and providing the oil level is monitored using the engine maintenance manual, making sure the consumption allowance and operation are within the recommended oil temperature and pressure.

(6)

If oil level is too low to register on dipstick due to possible excessive consumption, or if low or fluctuating pressures have been recorded, refer to Fault Isolation, Engine Lubrication, for action to be taken, then proceed as follows: (a) Fill oil tank to normal level and record quantity of oil added. NOTE:

CAUTION:

If oil overflows during replenishing, verify the sight gage for oil level. For engines without an oil sight gage and with an oil filler ball valve, inspect ball valve for freedom of movement. Replace the oil filler and ball valve if required (Ref. 72-60-00, ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES). WHEN FILLER CAP ASSEMBLY IS INSTALLED AND LOCKED, NO MOVEMENT IS ALLOWED.

(b) Install filler cap/dipstick, make sure cap is locked. (c) Run engine at ground-idle for approximately five minutes (Ref. 71-00-00, ADJUSTMENT/TEST). (d) Check oil level (Ref. Steps (1) through (6) preceding).

P&WC Proprietary lnfonnation. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

72 00 00

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Export Control Classifications: Canada· EI PA = NSR Canada- DPA = N Outside U.S. · EAR= Contains 10-25% 9 E991 U.S. - EAR = 9E6 19:a.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

D.

TR 72-47

P&WC's Oil Analysis Technology Sampling Procedure (1)

General: (a) This procedure is to provide instructions for collection of oil samples for the P&WC's Oil Analysis Technology program. NOTE: 1. P&WC's Oil Analysis Technology is an optional task. It can be done at the discretion of the operator.

I

I

NOTE: 2. The oil sampling kits are available through P&WC Customer Portal. Refer to P&WC SIL-GEN-153 or contact P&WC for more information.

.

NOTE: 3. P&WC's Oil Analysis Technology is complementary to oil filter/chip analysis, it is not replacing it. You can do the oil filter debris and chip analysis in any independent laboratory approved by P&WC per SIL GEN-123. Do chip/filter analysis during scheduled maintenance (filter and chip inspection) or in an unscheduled maintenance activity.

(b) Oil sampling is recommended within 15 to 30 minutes after engine shutdown. If the time after engine shutdown is more than 30 minutes, start the engine and operate at ground-idle for 5 minutes or until oil temperature is stable. (c) Collect the oil sample before you do the engine oil service. (d) After an engine oil system flush, a minimum of 20 hours of engine operation is recommended before you take an oil sample. (2)

Recommended Interval: (a) For operators enrolled in the P&WC's Oil Analysis Technology program, it is recommended to take oil samples at aircraft MINOR interval, or annually, whichever occurs first. NOTE:

In order to be valid, oil sampling must be done in accordance with the engine oil system oil analysis procedure (Ref. Step (3)).

(b) Based on oil analysis results, P&WC can recommend a different sampling interval for a specific engine. (c) In case of an unplanned removal for an oil system related issue, take an oil sample before removal if possible. (3)

Oil Sampling Procedure: CAUTION:

MAKE SURE THE AREA IS CLEAN IN ORDER TO PREVENT CONTAMINATION OF THE ENGINE OIL SYSTEM AND OIL SAMPLE. MAKE SURE THAT THE CONTAINER AND TOOLING ARE FREE OF DEBRIS AND CONTAMINANTS . .

(a) Shut down the engine (Ref. 71-00-00, POWER PLANT - ADJUSTMENT/TEST).

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

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Export Control Classifications: Canada· EIPA

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•

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=NSR Canada· DPA =N Outside U.S.· EAR= Contains 10-25% 9E991 U.S. - EAR= 9E619.a.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

TR 72-47

(b) Unlock the filler cap and dipstick from the filler neck at the 11 o'clock position on the accessory gearbox. Remove the filler cap. (c) Make sure that the plastic bottle is clean and dry. NOTE:

You can clean the plastic bottle with water and dry with compressed air.

(d) Record the applicable information on the bottle label and attach it on the bottle. (e) Collect a sample of 60 ml (2 oz.) engine oil through the filler neck with the syringe and the flexible tube. (f)

Put the oil sample collected with the syringe into the plastic bottle. NOTE:

Do not use syringe and flexible tubes more than one time. Discard the used syringe.

(g) Make sure that the plastic bottle is sealed correctly and put it in a separate plastic bag supplied with the oil sampling kit. (h) Fill the oil analysis sampling form P&WC 11914 or 12233 supplied in the oil sampling kit. NOTE:

E.

Use one form for each engine sample.

(i)

Put the sealed plastic bag with the oil sample bottle and the completed oil analysis sampling form into the shipping envelope and send in accordance with P&WC SIL-GEN-153.

(j)

Do a check for the engine oil level and fill as necessary (Ref. Paras. 5.B. and 5.C.).

Oil Servicing (Ref. Fig. 301)

CAUTION:

NOTE:

DO NOT MIX DIFFERENT VISCOSITIES OR SPECIFICATIONS OF OIL AS THEIR DIFFERENT CHEMICAL STRUCTURE CAN MAKE THEM INCOMPATIBLE. For oil change recommendations, refer to SB1001 .

(1)

Place suitable containers or drip pan under the engine.

(2)

Remove the cotterpin (6) and oil drain plug lockpin (5, Fig. 301) from the lugs on the compressor inlet case and withdraw the drain plug (8) using the puller (9). Discard the preformed packing (7).

(3)

PT6A-34AG/348/36 and PT6A-34 (Pre-S81792): Remove the drain plug (2) from the 6 o'clock position on the rear face of the accessory gearbox housing. Remove and discard the preformed packing (3) from the plug (2) (Ref. 72-60-00).

P&WC Proprietary Information. Subject to the restriction on the title page. The export control classification with respect to this document is contained on the back of the title page.

72 00 00

of g 4 ENGINE, TURBOPROP - SERVICING Aug 24/2020 •

Export Control Classifications: Canada - EIPA = NSR Canada - DPA = N Outside U.S. - EAR= Contains 10-25% 9E991 U.S. - EAR= 9E619.a.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021242

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TR 72-47

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:a

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IMPERIAL QUARTS

9

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LITERS

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