Maintenance Manual: Turboprop Gas Turbine Engine [PDF]

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MAINTENANCE MANUAL TURBOPROP GAS TURBINE ENGINE Model(s) PT6A-38/-41/-42/-42A Manual Part No. 3021442 28 February 1975 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-38/-41/-42/-42A 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

Dec 5/2008 © 1975 Pratt & Whitney Canada Corp. PRINTED IN CANADA

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

December 20, 2010

REVISION TRANSMITTAL SHEET TO:

Holders of the Pratt & Whitney Canada Maintenance Manual for PT6A-38/-41/-42/-42A Engines, Manual Part No. 3021442.

SUBJECT:

Revision No. 45, dated Dec 10/2010

Please insert the attached Revision No. 45 pages into your copy of the PT6A-38/-41/-42/-42A 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. 45 to the Record of Revisions. Any discrepancies, problems or suggestions regarding this revision should be forwarded in writing using the Pratt & Whitney Canada Customer Feedback Sheet (RSVP), and directed 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

Customer Feedback Sheets are contained with new manuals and each subsequent revision. You may also submit your feedback via our on-line RSVP form available at: www.pwc.ca/en/3_0/3_0_6/3_0_6_5_7.asp.

HIGHLIGHTS

Page 1 Dec 10/2010

Pratt & Whitney Canada Corp.

PT6A-38/-41/-42/-42A MAINTENANCE MANUAL REVISION NO. 45 HIGHLIGHTS CH/SE/SU

Description of Change

Service Bulletin List

Service Bulletin list has been updated to add SB3452. Service Bulletin list has been updated to add SB3453. Service Bulletin list has been updated to revise SB3003R23 to SB3003R24. Service Bulletin list has been updated to revise SB3430R1 to SB3430R2. Service Bulletin list has been updated to revise SB3429R0 to SB3429R1. Service Bulletin list has been updated to revise SB3428R0 to SB3428R1. Service Bulletin list has been updated to revise SB3422R0 to SB3422R1. Service Bulletin list has been updated to revise SB3417R0 to SB3417R1. Service Bulletin list has been updated to revise SB3411R0 to SB3411R1. Service Bulletin list has been updated to revise SB3404R0 to SB3404R1. Service Bulletin list has been updated to revise SB3397R0 to SB3397R1. Service Bulletin list has been updated to revise SB3394R0 to SB3394R1. Service Bulletin list has been updated to revise SB3382R0 to SB3382R1. Service Bulletin list has been updated to revise SB3364R1 to SB3364R3. Service Bulletin list has been updated to revise SB3352 to SB3352R1. Service Bulletin list has been updated to revise SB3346 to SB3346R1. Service Bulletin list has been updated to revise SB3339 to SB3339R1. Service Bulletin list has been updated to revise SB3286R1 to SB3286R2. Service Bulletin list has been updated to revise SB3290R1 to SB3290R2. Service Bulletin list has been updated to revise SB3164R1 to SB3164R2.

HIGHLIGHTS

Page 2 Dec 10/2010

Pratt & Whitney Canada Corp.

PT6A-38/-41/-42/-42A MAINTENANCE MANUAL REVISION NO. 45 HIGHLIGHTS CH/SE/SU

Description of Change Service Bulletin list has been updated to revise SB3274R2 to SB3274R3. Service Bulletin list has been updated to add SB3245R4. Service Bulletin list has been updated to revise SB3003R22 to SB3003R23. Service Bulletin list has been updated to revise SB3310 to SB3310R1. Service Bulletin list has been updated to revise SB3309 to SB3309R1. Service Bulletin list has been updated to revise SB3306 to SB3306R1. Service Bulletin list has been updated to revise SB3255R1 to SB3255R2. Service Bulletin list has been updated to revise SB3244 to SB3244R2. Service Bulletin list has been updated to revise SB3196 to SB3196R1. Service Bulletin list has been updated to revise SB3194R2 to SB3194R4. Service Bulletin list has been updated to revise SB3192 to SB3192R1. Service Bulletin list has been updated to revise SB3165R1 to SB3165R5. Service Bulletin list has been updated to revise SB3140 to SB3140R1. Service Bulletin list has been updated to revise SB3098 to SB3098R1. Service Bulletin list has been updated to revise SB3138 to SB3138R1. Service Bulletin list has been updated to revise SB3094R7 to SB3094R8. Service Bulletin list has been updated to add SB3451. Service Bulletin list has been updated to revise SB3034 to SB3034R2. Service Bulletin list has been updated to revise SB3043 to SB3043R1. Service Bulletin list has been updated to revise SB3031R2 to SB3031R3.

HIGHLIGHTS

Page 3 Dec 10/2010

Pratt & Whitney Canada Corp.

PT6A-38/-41/-42/-42A MAINTENANCE MANUAL REVISION NO. 45 HIGHLIGHTS CH/SE/SU

Description of Change Service Bulletin list has been updated to revise SB3006R2 to SB3006R5. Service Bulletin list has been updated to revise SB3003R21 to SB3003R22. Service Bulletin list has been updated to revise SB3002R24 to SB3002R25.

Introduction

Customer Service The customer service contact information has been revised to introduce customer first center mail code.

Special Tools, Fixtures and Equipment

Tool Service Bulletin PT-559 has been incorporated. Tool Service Bulletin PT-509R1 has been incorporated. Tool Service Bulletin PT-530 has been incorporated.

Consumable Materials

Service Bulletin 3452 has been incorporated.

70-00-00 Repair

Consumables The consumable materials list has been updated to add isopropyl alcohol (PWC11-014) and to remove perchlorethylene (PWC11-016). Repair of Damaged Stud Hole The repair of damaged stud hole procedure has been revised to replace consumable to isopropyl alcohol (PWC11-014) was perchlorethylene (PWC11-016).

71-00-00 Testing

Procedure

72-00-00 Fault Isolation

Engine Lubrication

72-00-00 Servicing

Oil System Flushing

72-00-00 Inspection

Periodic Inspection

The post-shutdown checks procedure has been revised to relocate the oil-to-fuel heater checks to chapter 73-10-01, maintenance practices. The engine lubrication fault isolation chart has been revised to introduce checking of breather tube for obstruction on engine and airframe side. The oil system flushing procedure has been revised to update caution. The periodic inspection table has been revised to modify the oil-to-fuel heater installation reference to 73-10-01 was 71-00-00.

HIGHLIGHTS

Page 4 Dec 10/2010

Pratt & Whitney Canada Corp.

PT6A-38/-41/-42/-42A MAINTENANCE MANUAL REVISION NO. 45 HIGHLIGHTS CH/SE/SU

Description of Change The periodic inspection table has been revised to introduce airframe zone inspection note for pneumatic system component. The periodic inspection table has been revised to introduce visual inspection note for air tubes. The periodic inspection table has been revised to introduce extension of 50 hours to 500 hours maximum interval in steps for AGB scavenge oil pump inlet screen check. General The general inspection of hot section components procedure has been updated to revise hot section inspection frequency reference to SB3003 was SB12003 and SB12103.

72-10-00 Maintenance Practices

Consumables The consumable materials list has been updated. Inspection of Oil Seal Retaining Ring, Ring Halves and Support Ring Halves The inspection of oil seal retaining ring, ring halves and support ring halves procedure has been revised to replace consumable from solvent (PWC11-022) to various other consumables.

72-20-00 Maintenance Practices

Consumables Service Bulletin 3452 has been incorporated. Installation of Air Inlet Screen Service Bulletin 3452 has been incorporated. Fits and Clearances Service Bulletin 3452 has been incorporated.

72-50-04 Maintenance Practices

Special-tools Tool Service Bulletin PT-559 has been incorporated. Tool Service Bulletin PT-530 has been incorporated. Tool Service Bulletin PT-509R1 has been incorporated. Removal of Power Turbine Tool Service Bulletin PT-559 has been incorporated. Tool Service Bulletin PT-509R1 has been incorporated. Tool Service Bulletin PT-530 has been incorporated.

73-10-01 Maintenance Practices

Adjustment/Test The adjustment/test procedure has been revised to introduce the oil-to-fuel heater installation checks.

HIGHLIGHTS

Page 5 Dec 10/2010

Pratt & Whitney Canada Corp.

PT6A-38/-41/-42/-42A MAINTENANCE MANUAL REVISION NO. 45 HIGHLIGHTS CH/SE/SU

Description of Change

73-10-07 Maintenance Practices

Consumables The consumable materials list has been updated to introduce rubber silicone sheath (PWC05-052). Repair of Damaged Silicone Rubber Sheath The repair of damaged silicone rubber sheath procedure has been revised to add consumable part no. PWC05-052 for rubber silicone sheath.

79-20-02 Maintenance Practices

Consumables The consumable materials list has been updated to delete solvent (PWC11-002). Cleaning - Electrosonically The electrosonically cleaning procedure has been revised to remove consumable solvent (PWC11-002).

HIGHLIGHTS

Page 6 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

RECORD OF REVISIONS REV NO.

ISSUE DATE

DATE INSERTED

BY

REV NO.

ISSUE DATE

DATE INSERTED

BY

1

Mar 01/76

P&WC

30

Sep 14/2001

P&WC

2

Nov 08/76

P&WC

31

Jan 25/2002

P&WC

3

Jun 30/77

P&WC

32

Jul 26/2002

P&WC

4

Apr 03/78

P&WC

33

Feb 07/2003

P&WC

5

Feb 01/79

P&WC

34

Mar 19/2004

P&WC

6

Mar 28/80

P&WC

35

Jun 11/2004

P&WC

7

Nov 02/81

P&WC

36

Sep 24/2004

P&WC

8

Sep 15/82

P&WC

37

Apr 08/2005

P&WC

9

May 26/83

P&WC

38

Oct 07/2005

P&WC

10

Jun 20/85

P&WC

39

Apr 28/2006

P&WC

11

Nov 05/85

P&WC

40

Nov 03/2006

P&WC

12

Jun 12/87

P&WC

41

Jul 11/2008

P&WC

13

Apr 26/88

P&WC

42

Dec 05/2008

P&WC

14

Jul 10/89

P&WC

43

Jun 26/2009

P&WC

15

Mar 15/91

P&WC

44

May 21/2010

P&WC

16

Feb 15/92

P&WC

45

Dec 10/2010$735//

17

Aug 15/92

P&WC

18

Feb 15/92

P&WC

19

Aug 15/93

P&WC

20

Feb 15/94

P&WC

21

Jan 15/96

P&WC

22

Dec 20/96

P&WC

23

Feb 28/97

P&WC

24

Dec 23/98

P&WC

25

Mar 26/99

P&WC

26

Sep 24/99

P&WC

27

Mar 24/2000

P&WC

28

Oct 13/2000

P&WC

29

Apr 06/2001

P&WC

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

RECORD OF REVISIONS

Feb 28/75

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

RECORD OF TEMPORARY REVISIONS TR. NO.

CH/SE/SU

PAGE NO.

ISSUE DATE

INSERTED BY

DATE REMOVED 3/9/2012

72-20

72-00-00

605

12/15/2011

ATP/RLL

72-21

72-60-00

211

1/27/2012

ATP/RLL

72-22

72-00-00

137

1/27/2012

ATP/RLL

79-3

79-20-02

219

1/27/2012

ATP/RLL

71-20

71-00-00

529

1/27/2012

ATP/RLL

72-23

72-00-00

605

2/6/2012

ATP/RLL

73-11

73-20-00

203

2/23/2012

ATP/RLL

REMOVED BY

RECORD OF TRs

ATP/RLL

Feb 28/75

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

Title Page

Dec 05/2008

Record of Revisions

Feb 28/75

Record of Temporary Revisions

Feb 28/75

LEP

1 2 blank

Dec 10/2010 Dec 10/2010

List of Chapter/ Section/Subjects

1 2 3 4 blank

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

Temporary Revision Index

1 2

Dec 05/2008 Dec 05/2008

Service Bulletin List

1 2 3 4 5 6 7 8 9 10 blank

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

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

FRONT MATTER LEP

Page 1/2 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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 Governing Standard Practices Standard Practices Power Plant Power Plant Engine Engine Power Section Power Section Reduction Gearbox Reduction Gearbox Air Inlet Section Compressor Air Inlet Case Compressor Section

72-30-00

Gas Generator Assembly

72-30-01

Center Mount Ring

72-30-02

Rear Mount Ring

72-30-04

Gas Generator Case

72-30-05

Compressor Rotor

72-40

Combustion Section

72-40-00

Combustion Chamber Assembly

72-40-01

Combustion Chamber Liner Assembly

LIST OF CHAP/SECT/SUBJ

Page 1 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CHAPTER/SECTION/SUBJECT

TITLE

72-50

Turbine Section

72-50-00

Turbine Section

72-50-01

Compressor Turbine Stator

72-50-02

Compressor Turbine

72-50-03

Power Turbine Interstage

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 Engine Fuel and Control

73-10-01

Oil-to-fuel Heater

73-10-02

Fuel Pump

73-10-03

Fuel Tubes

73-10-04

Flow Divider and Dump Valve

73-10-05

Fuel Manifold Adapters and Nozzles

73-10-06

Fuel Drain Valve

73-10-07

Compressor Delivery Air Lines

73-10-08

Governor Pneumatic Tubes

73-10-09

Torque Limiter

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

Fuel Distribution Fuel Control Unit (FCU) Ignition Ignition System Ignition Ignition Exciter

LIST OF CHAP/SECT/SUBJ

Page 2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CHAPTER/SECTION/SUBJECT

TITLE

74-20

Ignition

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

Igniters and Ignition Cables Air Air System Air Compressor Bleed Valve Engine Controls Engine Controls Engine Controls Propeller Reversing Linkage Engine Indicating

77-20-00

Engine Indicating System

77-20-01

T5 Indicating System

79-00 79-00-00 79-20

Oil Oil System Oil

79-20-00

Oil Distribution

79-20-01

External Oil Tubes

79-20-02

Oil Filter Housing

79-20-03

Thermostatic Bypass and Check Valve

LIST OF CHAP/SECT/SUBJ

Page 3/4 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TEMPORARY REVISION INDEX

T.R. No.

Filed Adjacent to

INTRO-1 Consumable Materials, Page 1 71-7 through 71-17 71-18 71-00-00, page 517 Power Plant - Adjustment/Test 71-19 71-00-00, page 517 Power Plant - Adjustment/Test 72-1 through 72-10 72-11 72-50-01, page 217 Compressor Turbine Stator Maintenance Practices 72-12 72-50-01, page 219 Compressor Turbine Stator Maintenance Practices 72-13 72-00-00, page 133 Engine, Turboprop - Fault Isolation 72-14 72-00-00, page 138 Engine, Turboprop - Fault Isolation 72-15 72-00-00, page 646 Engine, Turboprop - Inspection 72-16 72-00-00, page 604 Engine, Turboprop - Inspection 72-17 72-60-00, page 215 Accessory Gearbox - Maintenance Practices 72-18 72-00-00, page 604 Engine, Turboprop - Inspection 72-19 72-00-00, page 603 Engine, Turboprop - Inspection 73-3 through 73-7 73-8 73-10-07, page 212 Compressor Delivery Air Lines Maintenance Practices 73-9 73-10-07, page 216 Compressor Delivery Air Lines Maintenance Practices 73-10 73-10-02, page 210 Fuel Pump - Maintenance Practices 79-1 79-20-02, page 213 Oil Filter Housing - Maintenance Practices

T.R. Status Incorporated at Rev. No. 42 Incorporated at a previous revision. Incorporated at Rev. No. 19 Incorporated at Rev. No. 30 Incorporated at a previous revision.

Incorporated at Rev. No. 30

Incorporated at Rev. No. 30 Incorporated at Rev. No. 30 Incorporated at Rev. No. 31 Incorporated at Rev. No. 34 Incorporated at Rev. No. 34

Incorporated at Rev. No. 34 Incorporated at Rev. No. 41 Incorporated at Rev. No. 41 Incorporated at a previous revision.

Incorporated at Rev. No. 34

Incorporated at Rev. No. 34 Incorporated at Rev. No. 39

Incorporated at Rev. No. 31

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

TR INDEX

Page 1 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

T.R. No. 79-2

Filed Adjacent to 79-20-02, page 220 Oil Filter Housing - Maintenance Practices

T.R. Status

Incorporated at Rev. No. 31

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 restrictions on the title page.

TR INDEX

Page 2 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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. All PT6A-38/-41/-42/-42A Series engine ATA 72-Series Service Bulletins were prefixed with P/N 3026522 in lieu of a specific model identifier. New, and recently revised SBs have the prefix PT6A. For a current set of PT6A-38 bulletins only, use ordering number 3027557. For a current set of PT6A-41bulletins only, use ordering number 3026526. For a current set of PT6A -42 and -42A bulletins only, use ordering number 3020780. NOTE: Service Bulletins are being continually revised to reflect P&WC recommendations for oil, fuels, engine planned maintenance, etc., and are concurrent with incorporation of engine modifications. P&WC SB No.

ATA SB No.

3001

72-1

21

PT6A-38/-41/-42/-42A

3002

72-2

25

PT6A-38/-41/-42/-42A

3003

72-3

24

PT6A-38/-41/-42/-42A

3004 3005 3006 3007 3008 3009 3010 3011 3012 3013 3014 3015 3016 3017 3018 3019 3020 3021 3022 3023

72-4 72-5 72-24 72-7 72-14 72-10 72-15 72-6 72-23 72-25 72-11 72-9 72-13 72-17 72-12 72-18 72-31 72-27 72-8 72-33

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

Rev. No.

Engine Model Applicability

PT6A-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 Cancelled PT6A-41 Cancelled Cancelled PT6A-41 PT6A-41 PT6A-41 Cancelled PT6A-41 PT6A-41

(Ref. SB3101) (Ref. SB3066) (Ref. SB3019)

(Ref. SB3074)

Effect/Date Incorporated Apr 28/2006 (See NOTE) No effect (See NOTE) No effect (See NOTE) No effect No effect No effect No effect Feb 28/75 Feb 01/79 Feb 01/79 Feb 28/75 Mar 01/76 Feb 28/75 No effect Mar 01/76 No effect No effect Feb 01/79 No effect Mar 01/76 No effect No effect No effect

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

SB LIST

Page 1 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

P&WC SB No.

ATA SB No.

3024 3025 3026 3027 3028 3029 3030 3031 3032 3033 3034 3035 3036 3037 3038 3039 3040 3041 3042 3043 3044 3045 3046 3047 3049 3050 3052 3053 3056 3058 3059 3060 3061 3062 3063 3064 3066 3067 3068 3069 3070 3071 3073

Rev. No.

Engine Model Applicability

72-22 72-28 72-35 72-20 72-19 72-21 72-16 72-26 72-30 72-29 72-32 72-41 72-34 72-36 72-39 72-37 72-38 72-69 72-42 72-43 72-44

2 2 1 1 1 4 1 3 Orig. 2 2 1 Orig. Orig. 1 2 1 Orig. 1 1 12

PT6A-41 PT6A-41 PT6A-38/-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 PT6A-41 Cancelled (Ref. SB3066) PT6A-38/-41 PT6A-38/-41 PT6A-41 PT6A-41 PT6A-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41/-42A

72-40 72-46 72-47 72-49 72-50 72-52 72-45 72-56 72-58 72-59 72-60 72-61 72-57 72-63 72-64 72-62 72-66 72-67 72-68 72-70 72-71 72-73

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

PT6A-38/-41 Cancelled (Ref. Cancelled (Ref. PT6A-38 PT6A-38/-41 Cancelled (Ref. PT6A-38/-41 PT6A-38/-41 Cancelled (Ref. PT6A-38/-41 PT6A-38 Cancelled (Ref. PT6A-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41

SB3099) SB3083)

SB3064)

SB3093)

SB3227)

Effect/Date Incorporated Mar 01/76 Mar 28/80 Mar 01/76 Feb 28/75 No effect No effect No effect No effect Feb 28/75 No effect No effect No effect No effect Mar 01/76 No effect Mar 01/76 No effect No effect No effect No effect No Effect (See Note) Mar 01/76 No effect No effect Nov 08/76 No effect No effect No effect No effect No effect Nov 08/76 No effect No effect No effect No effect Nov 08/76 Feb 01/79 No effect Nov 08/76 No effect No effect No effect No effect

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

SB LIST

Page 2 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

Effect/Date Incorporated

3074 3075 3076 3080 3083 3084 3085 3089 3091 3092 3093 3094 3095 3097 3098 3099 3100 3101 3102 3103 3104 3105 3106 3107 3108 3109 3110 3112 3114 3115 3117 3119 3120 3121 3122 3123 3124 3126 3127 3130 3131 3132 3135 3136

72-74 72-75 72-76 72-80 72-83 72-84 72-85 72-89 72-91 72-92 72-93 72-94 72-95 72-97 72-98 72-99 72-100 72-101 72-102 72-103 72-104 72-105 72-106 72-107 72-108 72-109 72-110 72-112 72-114 72-115 72-117 72-119 72-120 72-121 72-122 72-123 72-124 72-126 72-127 72-130 72-131 72-132 72-135 72-136

1 6 1 1 1 1 Orig. 2 Orig. 1 2 8 1 3 1 2 6 1 Orig. 2 1 2 3 Orig. 2 1 Orig. Orig. 2 1 Orig. 2 Orig. 2 1 2 Orig. 1 1 3 2 1 1 1

PT6A-41 PT6A-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-41/-42 PT6A-38/-41 PT6A-38/-41 Cancelled (Ref. SB3178) PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41/-42 PT6A-38/-41 PT6A-38/-41 PT6A-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-41 PT6A-38/-41 PT6A-41 PT6A-38/-41 Cancelled Cancelled (Ref. SB3142) PT6A-38/-41 PT6A-38/-41 PT6A-38/-41 PT6A-41

Nov 02/81 Jun 12/87 No effect No effect No effect No effect No effect No effect Jun 30/77 Feb 01/79 No effect No effect No effect No effect No effect Feb 01/79 Sep 15/82 No effect No effect No effect No effect No effect Nov 02/81 No effect Jun 12/87 No effect No effect Apr 03/78 Feb 01/79 No effect No effect No effect No effect Mar 28/80 No effect Mar 28/80 Feb 01/79 No effect No effect No effect No effect No effect No effect No effect

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

SB LIST

Page 3 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

Effect/Date Incorporated

3137 3138 3139 3140 3141 3142 3143 3145 3146 3147 3148 3149 3152 3153 3154 3158 3159 3160 3162 3164 3165 3166 3167 3168 3170 3171 3172 3173 3174 3175 3176 3178 3179 3180 3183 3184 3185 3187 3188 3191 3192 3193 3194 3196

72-137 72-138 72-139 72-140 72-141 72-142 72-143 72-145 72-146 72-147 72-148 72-149 72-152 72-153 72-154 72-158 72-159 72-160 72-162 72-164 72-165 72-166 72-167 72-168 72-170 72-171 72-172 72-173 72-174 72-175 72-176 72-178 72-179 72-180 72-183 72-184 72-185 72-187 72-188 72-191 72-192 72-193 72-194 72-196

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

PT6A-38/-41 Cancelled (Ref. SB3137) PT6A-38/-41 Cancelled (Ref. SB3142) PT6A-38/-41 PT6A-41/-42 PT6A-41 Cancelled (Ref. SB3158) PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 Cancelled (Ref. SB3229) PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 Cancelled (Ref. SB3239) PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38

No effect No effect Mar 28/80 No effect No effect No effect No effect No effect Nov 02/81 No effect No effect No effect No effect Sep 15/82 No effect No effect No effect No effect No effect No Effect No effect No effect No effect No effect Nov 05/85 No effect No effect No effect No effect No effect No effect Jul 10/89 No effect No effect No effect No effect No effect No effect No effect No effect No effect No effect No effect No effect

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P&WC SB No.

ATA SB No.

Rev. No.

Engine Model Applicability

Effect/Date Incorporated

3197 3199 3200 3201 3202 3203 3204 3205 3208 3209 3211 3212 3213 3214 3215 3216 3217 3218 3219 3223 3225 3226 3227 3228 3229 3230 3231 3233 3236 3237 3238 3239 3240 3241 3242 3243 3244 3245 3246 3247 3248 3249 3250 3252

72-197 72-199 72-200 72-201 72-202 72-203 72-204 72-205 72-208 72-209 72-211 72-212 72-213 72-214 72-215 72-216 72-217 72-218 72-219 72-223 72-225 72-226 72-227 72-228 72-229 72-230 72-231 72-233 72-236 72-237 72-238 72-239 72-240 72-241 72-242 72-3243 72-244 72-245 72-246 72-247 72-248 72-249 72-250 72-252

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

PT6A-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-41/-42 Cancelled (Ref. SB3230) PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 Cancelled PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-42 PT6A-41/-42 PT6A-41/-42 Cancelled PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42

Jun 12/87 Nov 05/85 No effect No effect No effect No effect Nov 05/85 No effect Nov 05/85 No effect No effect No effect Jun 12/87 Nov 05/85 No effect No effect No effect No effect No effect Nov 05/85 No effect No effect Jun 12/87 Jun 12/87 Jun 12/87 Jun 12/87 No effect No effect Jun 12/87 No effect No effect Jun 12/87 No effect Apr 26/88 No effect No effect No Effect No Effect No effect No effect Apr 26/88 No effect Apr 26/88 No effect

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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ATA SB No.

Rev. No.

3253 3254 3255 3256 3257 3258 3259 3262 3263 3264 3265 3270 3273 3274 3275 3276 3277 3278 3279 3280 3281 3283 3284 3286 3287 3288 3290 3291 3292 3293 3294 3296 3298 3299 3301 3302 3304 3305 3306 3307 3308 3309 3310 3311

72-253 72-254 72-255 72-256 72-257 72-258 72-259 72-262 72-263 72-264 72-265 72-270 72-273 72-274 72-275 72-276 72-3277 72-278 72-279 72-280 72-281 72-283 72-284 72-286 72-287 72-288 72-3290 72-3291 72-292 72-293 72-294 72-3296 72-298 72-299 72-301 72-302 72-304 72-305 72-306 72-307 72-308 72-309 72-310 72-311

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

Engine Model Applicability

Effect/Date Incorporated

PT6A-41 PT6A-38/-41/-42 PT6A-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-41/-42 PT6A-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38 PT6A-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42

Jul 10/89 Jul 10/89 No effect No effect No effect Jul 10/89 Jul 10/89 No effect No effect No effect Apr 06/2001 Mar 15/91 No effect No Effect Apr 06/2001 Aug 15/92 Dec 05/2008 No Effect No effect No effect No effect No effect No effect No Effect No effect Feb. 13/2004 No effect No effect No effect No effect No effect No Effect No effect No effect Jan. 25/2002 No effect No effect No effect No effect No effect No effect No effect No effect No effect

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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ATA SB No.

Rev. No.

3312 3313 3314 3315 3316 3317 3318 3319 3320 3321 3322 3323 3327 3328 3329 3330 3331 3332 3334 3335 3336 3337 3338 3339 3340 3341 3342 3343 3344 3345 3346 3347 3348 3349 3350 3351 3352 3353 3354 3355 3356 3357 3358 3360

72-312 72-313 72-314 72-315 72-316 72-3317 72-3318 72-3319 72-3320 72-3321 72-3322 72-3323 72-3327 72-3328 72-3329 72-3330 72-3331 72-3332 72-3334 72-3335 72-3336 72-3337 72-3338 72-3339 72-3340 72-3341 72-3342 72-3343 72-3344 72-3345 72-3346 72-3347 72-3348 72-3349 72-3350 72-3351 72-3352 72-3353 72-3354 72-3355 72-3356 72-3357 72-3358 72-3360

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

Engine Model Applicability

Effect/Date Incorporated

PT6A-38/-41/-42 PT6A-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-41/-42 PT6A-38/-40/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-42/-42 PT6A-38/-40/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-41/-42 PT6A-41/-42 PT6A-38/-40/-41/-42 PT6A-42/-41 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42

No effect No effect No effect No effect No effect No Effect No effect No effect No effect No effect Mar 19/2004 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 No effect No effect Sep 24/99 No effect No effect No effect No effect No effect No effect No Effect No effect Feb 07/2003

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

P&WC SB No.

ATA SB No.

Rev. No.

3361 3362 3363 3364 3365 3366 3367 3368 3369 3370 3371 3372 3373 3374 3375 3376 3378 3379 3380 3381 3382 3384 3386 3387 3388 3389 3390 3391 3392 3393 3394 3395 3397 3398 3400 3401 3402 3403 3404 3405 3406 3407 3408 3409

72-3361 72-3362 72-3363 72-3364 72-3365 72-3366 72-3367 72-3368 72-3369 72-3370 72-3371 72-3372 72-3373 72-3374 72-3375 72-3376 72-3378 72-3379 72-3380 72-3381 72-3382 72-3384 72-3386 72-3387 72-3388 72-3389 72-3390 72-3391 72-3392 72-3393 72-3394 72-3395 72-3397 72-3398 72-3400 72-3401 72-3402 72-3403 72-3404 72-3405 72-3406 72-3407 72-3408 72-3409

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

Engine Model Applicability

Effect/Date Incorporated

PT6A-41/-42 PT6A-38/-41/-42 PT6A-38/-41/-42/-42A PT6A-38/-41/-42 PT6A-38/-41/-42/-42A PT6A-41/-42 PT6A-38/-41/-42 PT6A-42A PT6A-42/-42A PT6A-42/-42A PT6A-38/-41/-42/-42A PT6A-41/-42/-42A PT6A-41/-42/-42A PT6A-41/-42/-42A PT6A-38/-41/-42 PT6A-42A PT6A-38/-41/-42 PT6A-42A PT6A-38/-41 PT6A-41 PT6A-38/-41/-42/-42A PT6A-41/-42/-42A PT6A-41/-42/-42A PT6A-42A PT6A-42A PT6A-42A PT6A-42 PT6A-38/-41/-42 PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-42A PT6A-42A PT6A-41/-42/-42A PT6A-42 PT6A-41/-42 Cancelled PT6A-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42 PT6A-42A

No effect No effect No effect No effect No effect No effect No effect Sep 24/99 Mar 19/2004 Mar 19/2004 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 No effect No effect No effect No effect No effect No Effect No effect No effect No effect Mar 19/2004 No Effect No effect No effect

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

P&WC SB No.

ATA SB No.

Rev. No.

3410 3411 3412 3415 3417 3419 3421 3422 3424 3425 3426 3427 3428 3429 3430 3431 3432 3433 3436 3437 3438 3439 3440 3441 3442 3443 3444 3447 3448 3451 3452 3453

72-3410 72-3411 72-3412 72-3415 72-3417 72-3419 72-3421 72-3422 72-3424 72-3425 72-3426 72-3427 72-3428 72-3429 72-3430 72-3431 72-3432 72-3433 72-3436 72-3437 72-3438 72-3439 72-3440 72-3441 72-3442 72-3443 72-3444 72-3447 72-3448 72-3451 72-3452 72-3453

Orig. 1 Orig. 1 1 1 Orig. 1 7 Orig. 2 Orig. 1 1 2 Orig. 1 Orig. Orig. Orig. 1 Orig. Orig. Orig. 1 2 Orig. 1 Orig. Orig. Orig. Orig.

Engine Model Applicability

Effect/Date Incorporated

PT6A-42A PT6A-42A PT6A-42A PT6A-42A PT6A-41/-42 PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-42/-42A PT6A-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-38/-41/-42/-42A PT6A-42A PT6A-42 PT6A-42 PT6A-38/-41/-42/-42A PT6A-42A PT6A-42A

No effect No effect Jun 11/2004 No Effect No Effect No Effect No Effect No Effect No Effect No Effect Jul 11/2008 Dec 05/2008 No Effect No Effect No Effect Jul 11/2008 Jul 11/2008 Jul 11/2008 No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect No Effect Dec 10/2010 No Effect

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2

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Contents

1 2 blank

Dec 10/2010 Dec 10/2010

Introduction

1 2 3 4 5 6 7 8 blank

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

Special Tools Fixtures and Equipment

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26

CHAPTER SECTION Consumable Materials

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

PAGE 1 2 3 4 5 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

DATE Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 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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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

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

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INTRODUCTION LEP

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

4

9.

SPECIAL TOOLS/FIXTURES AND EQUIPMENT 1.

General

1

2.

Special Tools

1

3.

Special Equipment

23

CONSUMABLE MATERIALS 1.

General

1

2.

Consumable Materials

1

3.

Suppliers and Supplier Services

17

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

INTRODUCTION 1.

General A.

This maintenance manual contains the recommended procedures for maintaining 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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Pratt & Whitney Canada Corp. 1000 Marie-Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Attention: Customer First Center (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 Center (CFirst). Pratt & Whitney Canada Corp. 1000 Marie-Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Attention: Spare Parts Sales Department 3.

Accessories Support Accessories may be sent for repair or complete overhaul to: P&WC Accessories Services 333 rue d’Auvergne (Area 2K) Longueuil, Quebec Canada J4H 3Y3

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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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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 NOTE: 72-20 72-30 72-40 72-50 72-60

C.

Power Section Reduction Gearbox An engine that has more than one RGB, will use sequential numbers i.e., 72-11-00, 72-12 -00 etc. Air Inlet Section Compressor Section Combustion Section Turbine Section Accessory Gearbox

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.

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, DESCRIPTION AND OPERATION, 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, INSPECTION, Unscheduled Inspection).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

6.

Engine Part Nomenclature For engine areas, stations, flanges and bearings refer to Description and Operation (Ref. 72-00-00, DESCRIPTION AND OPERATION, Figure 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 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 engines should familiarize themselves with the contents of the Illustrated Parts Catalog P&WC Manual P/N 3021444, 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.

11.

Abbreviations and Symbols The following is a list of abbreviations and symbols used throughout this manual: AGB AMS AR Assy ATA

Accessory Gearbox Aerospace Material Specification As Required Assembly Air Transport Association

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

beta BRG °C CCW CG CSU CT CW del del P del T5 DELRTH Dia Dim eshp °F FCU FI FIR FOD FPI FWD (Fwd) G GGM GI Hg HP hr HSI ID Imp in. in.Hg IPC ITT (T5) kg lb. lb.in. LH LP Max.

Range of propeller blade angle between fine pitch stop and maximum reverse pitch setting Bearing Degress Celsius (Centigrade) Counterclockwise Center of Gravity Constant Speed Unit Compressor Turbine Clockwise Delta (P observed/P Standard Day) Engine Torquemeter Pressure, in. Hg T5 Temperature Trim Value Delta Root Theta Diameter Dimension Equivalent shaft horse power Degrees Fahrenheit 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 Inches of Mercury Illustrated Parts Catalog Interturbine Temperature Kilogram Pound Pound inch Left-hand Low Pressure Maximum

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

INTRODUCTION

Page 5 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

min Min. mm NA NDT Nf (NF) Ng (NG) No. Np OD Pam Para. PD P/N PP pph Psgb psi PSM PT P&WA P&WC PWC Px Py Po P1 P2 P3 °R Ref. (REF.) RGB RH RTC RTH rpm S.B. SCFM SED sfc SG shp

Minute Minimum Millimeter Not Applicable Non-Destructive Test 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 Power Section Module Power Turbine Pratt &Whitney Aircraft Pratt & Whitney Canada Corp. Special Tool Prefix Letters - Engine Control Pressure (Bleed Valve) Governor Servo Pressure Bypass Pressure Unmetered Fuel Pressure Metered Fuel Pressure Compressor Discharge Air Pressure Degrees Rankin Reference Reduction Gearbox (Propeller) Right-hand Radial Tip Clearance Root Theta Revolutions per minute Service Bulletin Standard Cubic Feet per Minute Small Exit Duct specific fuel consumption (lbs/shp/hr) Specific Gravity Shaft horse power

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

INTRODUCTION

Page 6 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

SOI SPOP tam TBA TBO theta TIG T1 T5 (ITT) UOS USA Wf

Specific Operating Instructions Service Process Operation Procedure 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 (lbs/hr)

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

INTRODUCTION

Page 7/8 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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. Special tools listed may be purchased from the following suppliers: Kell-Strom Tool Co. Inc. (CAGE 75245) 214 Church Street Wethersfield, CT 06109 USA TEL: 1-860-529-6851 or 1-860-721-0658 (24 hour service) Toll free: 1-800-851-6851 (USA & Canada) FAX: 1-860-257-9694 Website: www.kell-strom.com E-mail: [email protected] or [email protected] Rasakti Inc. (CAGE 3AD21) 148 Rue Sylvestre Saint- Germain-De-Grantham, Quebec Canada J0C 1K0 TEL: 1-819-395-1111 (regular & 24 hour service) Toll free: 1-888-RASAKTI (727-2584) (USA & Canada) FAX: 1-819-395-1100 Website: www.rasakti.com E-mail: [email protected] Pratt & Whitney, Tool Support Services (CAGE 77445) 411 Silver Lane, Mail Stop 129-20 East Hartford, CT 06118 USA TEL: 1-860-610-2675 or 1-800-565-0140 or 1-860-565-0140 (24-hour service number) Toll free: 1-800-PWA-TOOL (792-8665) (USA & Canada) FAX: 1-860-610-2670 E-mail: [email protected] When ordering special tools, include the prefix ’PWC’ as a component of the tool part number, e.g. PWC 32420, Sling. For more information, contact:

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

TOOLS/FIX/EQUIP

Page 1 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Pratt & Whitney Canada Corp. 1000 Marie-Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Attention: Manager Publications 05MS1 TABLE 1, Special Tools Maintenance Level Part No.

Name

CH/SE/SU

Line

Heavy

PWC30046-52

Puller

72-60-00

X

X

PWC30046-54

Puller

72-60-00

X

X

PWC30046-57

Puller

72-60-00

X

X

PWC30051-01

Base

72-60-00

X

PWC30051-02

Drift

72-60-00

X

PWC30052

Puller

72-60-00

X

X

PWC30075

Drift

72-60-00

X

X

PWC30114-08

Wrench

77-20-01

X

X

PWC30114-09

Wrench (Pre-SB3045)

61-20-00

X

X

PWC30114-16

Wrench (Post-SB3045)

61-20-00

X

X

PWC30122

Replaced by PWC37918

PWC30128-04

Puller

72-60-00

X

PWC30269

Mount Ring

72-00-00

X

PWC30271-100

Replaced by PWC31771

72-30-04

X

PWC30274

Base, Gearshaft (Pre-SB3121)

72-60-00

X

PWC30328

Puller (Replaced by PWC50726)

79-20-02

X

X

PWC30331

Wrench

72-50-02

X

X

PWC30335

Spreader

72-50-02

X

X

PWC30336

Protector

72-50-02

X

X

PWC30338

Replaced by PWC70652 and PWC70653

PWC30373

Puller/Pusher

72-60-00

PWC30403

Puller

72-50-02

X

X

PWC30405

Leak Test Fixture (Pre-SB3250)

73-10-05

X

X

PWC30415

Compressor

72-60-00

X

X

PWC30416

Puller (Pre-SB3250)

73-10-05

X

X

HSI

X

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

TOOLS/FIX/EQUIP

Page 2 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

Name

CH/SE/SU

Line

Heavy

X

X

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

PWC30530

Plug

73-10-05

X

X

PWC30556

Puller

79-20-02

X

X

PWC30675

Drift

72-60-00

X

PWC30800

Replaced by PWC34300

PWC30854

Adapter

72-60-00

X

PWC30855

Replaced by PWC50502

PWC31050

Wrench

72-50-04

X

PWC31515

Bar

72-50-04

X

PWC31771

Spreader

72-30-04

X

PWC32052

Replaced by PWC34752

72-00-00

X

X

PWC32062

Socket (PT6A-40/-41/-42)

73-10-09

X

X

PWC32072

Puller-Replaced by PWC57233

72-10-00

X

X

72-60-00

X

X

79-20-03

X

X

72-50-04 Replaced by PWC50767 and PWC51748

X

X

HSI

X

PWC32078

Puller, Check Valve Cover (Obsolete-replaced by PWC34532)

PWC32089

Pusher

PWC32111

Puller

72-50-03

X

PWC32120

Pusher

72-50-04

X

PWC32121

Adapter-Replaced by PWC50589

72-50-04

X

PWC32123

Puller (Obsolete - replaced by PWC50588)

72-50-04

X

PWC32125

Fixture, Bus Bar

77-20-01

PWC32136

Fixture

72-50-04

X

PWC32137

Socket

72-50-04

X

X

X

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

TOOLS/FIX/EQUIP

Page 3 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

Name

CH/SE/SU

Line

Heavy

PWC32140

Puller - Replaced by PWC50726-100

79-20-02

X

PWC32174

Base (Post-SB3121)

72-60-00

X

PWC32175

Ring

72-60-00

X

PWC32193

Crimper

72-50-04

X

PWC32209

Adapter

72-50-01

X

PWC32271

Tube, Spray

71-00-00

PWC32275

Split Plate (Pre-SB3121)

72-60-00

PWC32366

Pusher, Tubes

73-10-05

PWC32380

Gage

72-50-01

X

PWC32396

Jackscrew (Three), Accessory Gearbox

72-50-01

X

72-60-00

X

72-50-01

X

72-60-00

X

PWC32396-400

Jackscrew (Three), Gas Generator Case From Diffuser Case

X

HSI

X X

X

X

PWC32417

Replaced by PWC32380

PWC32420

Replaced by PWC50066

PWC32483

Cutter

72-30-04

X

PWC32486

Socket

72-60-00

X

PWC32505

DELETED (Replaced by PWC71392)

72-50-04

X

PWC32506

DELETED (Replaced by PWC89837)

72-50-04

X

PWC32507

Hydraulic Pump

72-50-04

X

PWC32528

Wheel, Grinding

72-50-01

X

PWC32677100or-300

Washcart , Compressor

71-00-00

X

PWC32811

Fixture

73-10-05

X

PWC32823

Puller

72-50-01

X

PWC34000

Replaced by PWC70104

PWC34060

Fixture

72-60-00

X

X

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

TOOLS/FIX/EQUIP

Page 4 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

Name

CH/SE/SU

Line

Heavy

X

X

PWC34061

Gage, Coupling Shaft (Pre-SB3277)

72-60-00

PWC34062

Puller

72-60-00

X

PWC34073

Replaced by PWC70099

PWC34128

Wheel, Shroud Grinding

72-50-01

X

PWC34161

Gage, Coupling Shaft (Post-SB3277)

72-60-00

PWC34184

Gage

72-30-04

X

PWC34258

Adapter

72-50-04

X

PWC34259

Socket (Obsolete - replaced by PWC50372)

72-50-04

X

PWC34300

Replaced by PWC51140

PWC34405

Leak Test Fixture (Post-SB3250)

73-10-05

PWC34414

Puller (Post-SB3250)

72-40-01

PWC34416

Puller (Post-SB3250)

73-10-05

PWC34522

Puller

72-50-01

PWC34525

Fixture

77-20-01

X

PWC34532

Puller Cover (Alternate to PWC32078)

79-20-03

X

X

PWC34752

Adapter

72-00-00

X

X

PWC34910-100

Borescope Assembly

72-00-00

X

PWC34910-400

Guide Tube

72-00-00

X

PWC34913

Fixture

72-00-00

X

PWC34941

Wrench

72-00-00

X

X

PWC37088-001

Drift, Seal

72-60-00

X

X

PWC37088-002

Drift, Seal

72-60-00

X

X

PWC37088-003

Drift, Seal

72-60-00

X

X

PWC37917

Dresser

72-50-01

X

PWC37918

Grinder

72-50-01

X

PWC42304

Jackscrew, Gas Generator Case From Diffuser Case Replaced by PWC32396-400

72-50-01

X

X

X

HSI

X

X X

X

X X

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

TOOLS/FIX/EQUIP

Page 5 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

Name

CH/SE/SU

Line

Heavy

PWC50042

Pad

72-50-04

PWC50060

Injector, Oil

72-50-02

X

PWC50064-100

Replaced by PWC50057

72-50-02

X

PWC50066

Replaced by PWC51861-600

PWC50372

Socket (Obsolete - replaced by PWC50442)

72-50-04

X

PWC50442

Socket (Alternate to PWC50372)

72-50-04

X

PWC50502

Compressor

72-60-00

X

PWC50588

Puller (Alternate to PWC32123)

72-50-04

X

PWC50589

Adapter

72-50-04

X

PWC50726

Puller

79-20-02

X

X

PWC50726-100

Puller

79-20-02

X

X

PWC50767

Drift

72-50-04

X

X

PWC51140

Replaced by PWC70907

72-00-00

X

X

PWC51748

DELETED - Replaced by PWC71410

72-50-04

X

X

PWC51861-600

Sling, Engine

72-00-00

X

X

PWC57233

Puller

72-10-00

X

X

72-60-00

X

X

HSI

X X

PWC64241

Pin, Aligning

72-50-01

X

X

PWC70099

Sling, PS without prop

72-00-00

X

X

PWC70104

Sling, PS with prop

72-00-00

X

X

PWC70652

Sling, PS with prop

72-00-00

X

X

PWC70653

Sling, PS with prop

72-00-00

X

X

PWC70907

Stand, Engine

72-00-00

X

X

PWC70838

Puller

72-60-00

X

X

PWC70869

Drift

72-60-00

X

X

PWC71392

Adapter, Hydraulic (Replaces PWC32505)

72-50-04

PWC71410

Rod Assembly - Replaces PWC51748

72-50-04

X

X

PWC71416

Bracket, Engine Assembly

72-00-00

X

X

X

X

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

TOOLS/FIX/EQUIP

Page 6 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Special Tools (Cont’d) Maintenance Level Part No. PWC89837

Name Cylinder, Hydraulic (Replaces PWC32506)

CH/SE/SU

Line

72-50-04

Heavy

HSI

X

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

TOOLS/FIX/EQUIP

Page 7 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC30046-52

PWC30051-01

PWC30075

PWC30046-54

PWC30051-02

PWC30114-08

PWC30046-57

PWC30052

PWC30114-09

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

TOOLS/FIX/EQUIP

Page 8 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC30114-16

PWC30269

PWC30328

PWC30122

PWC30271-100

PWC30331

PWC30128-04

PWC30274

PWC30335

Special Tool Illustrations

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

TOOLS/FIX/EQUIP

Page 9 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC30336

PWC30403

PWC30416

PWC30338

PWC30405

PWC30458

PWC30373

PWC30415

PWC30478

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

TOOLS/FIX/EQUIP

Page 10 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC30499-50

PWC30556

PWC30854

PWC30506

PWC30675

PWC30855

PWC30530

PWC30800

PWC31050

Special Tool Illustrations

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

TOOLS/FIX/EQUIP

Page 11 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC31515

PWC32062

PWC32089

PWC31771

PWC32072

PWC32111

PWC32052

PWC32078

PWC32120

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

TOOLS/FIX/EQUIP

Page 12 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC32121

PWC32136

PWC32174

PWC32123

PWC32137

PWC32175

PWC32125

PWC32140

PWC32193

Special Tool Illustrations

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

TOOLS/FIX/EQUIP

Page 13 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC32209

PWC32366

PWC32396-400

TOOL NOT ILLUSTRATED

PWC32209

PWC32271

PWC32380

PWC32417

PWC32275

PWC32396

PWC32420

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

TOOLS/FIX/EQUIP

Page 14 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC32483

PWC32506

PWC32677-100OR-300

TOOL NOT ILLUSTRATED

PWC32483

PWC32486

PWC32507

PWC32811

PWC32505

PWC32528

PWC32823

PWCxxxxx

Special Tool Illustrations

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

TOOLS/FIX/EQUIP

Page 15 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC34000

PWC34062

PWC34161

PWC34060

PWC34073

PWC34184

PWC34184

PWC34061

PWC34128

PWC34258

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

TOOLS/FIX/EQUIP

Page 16 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC34259

PWC34414

PWC34525

PWC34300

PWC34416

PWC34532

TOOL NOT ILLUSTRATED

PWC34405

PWC34522

PWC34752

Special Tool Illustrations

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

TOOLS/FIX/EQUIP

Page 17 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC34910-100

PWC34941

PWC37088-003

PWC34910-400

PWC37088-001

PWC37917

PWC37088-002

PWC37918

PWC34910−400

PWC34913

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

TOOLS/FIX/EQUIP

Page 18 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC42304

PWC50064-100

PWC50442

PWC50066

PWC50502

PWC50372

PWC50588

TOOL NOT ILLUSTRATED

PWC50042

TOOL NOT ILLUSTRATED

PWC50060

PWC50372

PWC50588

Special Tool Illustrations

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

TOOLS/FIX/EQUIP

Page 19 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC50589

PWC50767

PWC51861-600

PWC50726

PWC51140

PWC57233

TOOL NOT ILLUSTRATED

PWC50726-100

PWC51748

PWC64241

TOOL NOT ILLUSTRATED

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

TOOLS/FIX/EQUIP

Page 20 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC70099

PWC70653

TOOL NOT ILLUSTRATED

PWC70104

TOOL NOT ILLUSTRATED

PWC70907

TOOL NOT ILLUSTRATED

PWC70869

TOOL NOT ILLUSTRATED

PWC71392

TOOL NOT ILLUSTRATED

PWC70104

PWC70652

TOOL NOT ILLUSTRATED

PWC70838

TOOL NOT ILLUSTRATED

PWC71410

TOOL NOT ILLUSTRATED

Special Tool Illustrations

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

TOOLS/FIX/EQUIP

Page 21 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PWC71416

TOOL NOT ILLUSTRATED

PWC89837

TOOL NOT ILLUSTRATED

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

TOOLS/FIX/EQUIP

Page 22 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

To allow for local manufacture of basic line maintenance tools, the following fully dimensioned tool drawings are presented as a P&WC CD Publication, P/N 3054921, available free of charge to subscribers of P&WC Maintenance Manuals. PWC30046 Puller PWC30075 Puller PWC30114 Wrench PWC32072 Puller PWC32366 Pusher PWC34060 Fixture PWC34062 Puller PWC34532 Puller PWC37088 Drift PWC50272 Drift PWC50765 Scale For information and ordering, contact: Pratt & Whitney Canada Corp. 1000 Marie-Victorin Blvd. Longueuil, Quebec Canada J4G 1A1 Attention: Manager Publications 05MS1 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

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. 73-10-03)

2311F

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

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

TOOLS/FIX/EQUIP

Page 23 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Special Equipment (Cont’d) Name

Part No.

Supplier

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 HW-9 or HW-10 or Airco H20A or H35B or equivalent

Local Purchase

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

Stainless Steel Tank; 5 gallon capacity and capable of withstanding 50 psi 2 off (Ref. 71-00-00).

Local Purchase

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

Local Purchase

Adapter, threaded 0.250-28-UNJF-3B to suit pressure gage and bleed valve cover. 0.250-28 UNJF to accept tubing for shutoff valve and bleed valve cover

Local Manufacture/ Purchase

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

Local Manufacture

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

TOOLS/FIX/EQUIP

Page 24 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Special Equipment (Cont’d) Name

Part No.

Stainless Steel Container or Tray, Perforated (to suit cleaner PWC11-013) (Ref. 73-10-05) Ultrasonic Cleaner (Ref. 73-10-05)

Supplier Local Manufacture

Model T-21, (Product Code 317) or model T-14 (Product Code 311)

L & R Manufacturing Company 577 Elm Street Kearny, NJ 07032 USA or L & R Ultrasonics Ltd. 45 Clairemont Road Wealdstone, Harrow Middlesex, England HA3 7AU

In the event of non-availability of ultrasonic cleaning equipment, operators should send fuel nozzles requiring cleaning and testing to an approved overhaul facility, or to a maintenance base having suitable equipment. Blanking Plate (Ref. 73-10-05) Electrosonic, Cleaner (Ref. 79-20-02)

Local Manufacture Sonac S-2

Kel-Strom Tool Co. 213 Church St. Wethersfield, CT 06109 USA

Shut-off Valve Fluid Line (Ref. 71-00-00)

Local Purchase

Soldering Iron (100 watt)

Local Purchase

Locking Tool (Keensert) (Ref. 72-30-04)

TD1032L

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

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TOOLS/FIX/EQUIP

Page 25 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Special Equipment (Cont’d) Name Oil Filter Element Rinsing and Debris Apparatus Kit (Ref. 79-20-02)

Part No. AVL-OFRA

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

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TOOLS/FIX/EQUIP

Page 26 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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 all MSDS prior to using the consumable materials. Table 1 lists consumable materials and supplier codes used in the maintenance of the engine, and Table 2 lists supplier codes and addresses. 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, Consumable Materials

Item

Nomenclature/Specification

Supplier Code

PWC01-001

Fuel, Engine

(Ref. Approved Service Bulletins)

PWC03-001

Oil, Engine Lubricating (Ref. Approved Service Bulletins)

A0001

PWC03-002

Fluid, Calibrating Ref. Brayco 922 US MIL-PRF-7024 Type II PMC 9041

A0015

PWC04-001

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

A0001

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Page 1 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC04-004

Compound, High Temperature Ref. Plastilube No. 3 PMC 9631

1V074

PWC04-005

Grease Extreme Pressure Ref. Lubriplate 130A PMC 79919

73219, A0032, A0033, A0034, A0035

PWC05-002

Dye, Layout Ref. Micro Supreme Layout Dye PMC 4062

01058

PWC05-005A

Emulsifier Ref. Witconate P10-59B

36382, 85665

PWC05-007

Fluid Leak Check Ref. Leak Tec 372E PMC 9569

03530

PWC05-009

Ammonium Bifluoride Ref. Crystalline

A0001(s)

PWC05-011

Ammonium Nitrate Ref. Open Powder Form 1.725 Specific Gravity US MIL-A-175 PMC 1517

A0001(s)

PWC05-014

Cloth, Abrasive Ref. Scotch Brite

A0001(s), 28112

PWC05-018

Pencil, Metal Marking Ref. 21628 Silver PMC 4094

22980(m)

PWC05-18A

Pencil, Metal Marking Ref. Stock No. 02460 for Prismacolor Verithin No. 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) PMC 4059-6

70362, A0006

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Page 2 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-019

Compound, Lapping (Silicon Carbide) Ref. Clover 2A No. 400 Grit US ANSI B74.10, ANSI B74.12 PMC 3013

05972

PWC05-027

Ink, Marking Ref. Carter 21451 Black

S0089

PWC05-031

Flux, Resin Ref. No. 1545 PMC 2000

09185(m), 10178(m)

PWC05-037

Enamel, Epoxy Aluminized Ref. Enamel Base: 529K002 and Curing Solution: 910K021 PMC 1746 CPW 269

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

PWC05-038

Hydrogen Peroxide Ref. Open Commercial Grade 32.5 to 35% US Fed. A-A-53707 PMC 1602

A0001(s), 08338

PWC05-041

Dye, Layout Ref. Dykem Spray Steel Blue SP-1100 PMC 4039

98148(m)

PWC05-044

Lockwire or Safetywire Nickel Alloy (CRES) Inconel 600

A0001(s), 2Y182

PWC05-044A

Lockwire or Safetywire Nickel Alloy (CRES) Inconel 600

A0001(s)

PWC05-046A

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

S0036

PWC05-046C

Ref. PWC05-229

PWC05-048

Pen, Marking Ref. Brushpen No. 57

S0036

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Page 3 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-048A

Pen, Marking Ref. Felt Wick Pen

A0013, 30133

PWC05-048B

Ref. PWC05-331

PWC05-049

Material, Masking Ref. Brady Mask PMC 74110

A0026

PWC05-050

Nitrogen Technical Grade Ref. Minimum Purity 99% US. BB-N-411 PMC 2212

A0001(s), 0BZD7, 09563

PWC05-052

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

A0001(s), 06090

PWC05-055

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

A0001(s)

PWC05-058

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

09185(m), 10178(m)

PWC05-061

Cloth, Abrasive Coated Crocus Ref. Open US ANSI B74.18

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

PWC05-066

Tape, High Temp. (Glass Cloth) Ref. Open PMC 4273

A0001(s), 99742(m)

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Page 4 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-070

Tape, Pressure Sensitive Adhesive Filament Reinforced Ref. 3M No. 898 Type II, 2 .0 in. (50.8 mm) Wide US. ASTM D5330

A0001(s), A0083, 76381(m)

PWC05-073

Water, Distilled Deionized and Demineralized Ref. Commercial Grade PMC 1737

A0001(s)

PWC05-074

Acid, Sulfuric Ref. Commercial or Technical Grade 66 Degrees Baume PMC 1003

A0001(s)

PWC05-076

Oil, Penetrating US Fed. A-A-50493

A0001(s), 59595

PWC05-077

Oil, Preservative Ref. Grade 1010 US. MIL-PRF-6081 PMC 9852

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 Ref. Open US ANSI B74.18 No. 320 Grit

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

PWC05-105

Tape, Self-Adjusting Insulation Electrical Ref. Silicone Rubber US. Fed A-A-59163

A0001(s), 00198(s)

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Page 5 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

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 Ref. Open Alloy 51410 US AMS 5613

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)

PWC05-162

Wetting Agent Chromate Conversion Salts Ref. ARP No. 2 PMC 1632

76071, A0001(s)

PWC05-164

Welding Material Alumel/Chromel Ref. TYPE K 20 GAGE

A0066

PWC05-165

Crystals Silver Nitrate Ref. Open

A0001(s)

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Page 6 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

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 PMC 3021

75554(m), A0001(s)

PWC05-179

Wire, Filler, Welding Ref. FM69 US. AMS 5778

A0001(s), OHJT8, 2R602

PWC05-180

Wire, Filler, Welding Ref. Hastelloy X US AMS 5798

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 Fed A-A-59105 5 to 10% Solution 42% Reagent Grade 45 Degrees Baume PMC 1000

A0001(s)

PWC05-196

Acid, Hydrochloric Technical Grade Ref. Muriatic Acid US ASTM E1146 MIL-H-13528 37 % Reagent Grade 20 Degrees Baume PMC 1002

A0001(s)

PWC05-197

Acid, Chromic Flakes or Solution US Fed. A-A-55827 CR03-99.5% Min. SO4 -0.20% Max. Commercial Grade PMC 1001

A0001(s)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC05-215A

Wire, Filler, Welding (Nickel Alloy) Ref. 51410 US AMS 5776 0.035 in. (0.89 mm)

A0001(s), OHJT8, 2R602

PWC05-227

Alloy, Coating (Cobalt Base) Ref. Powder or Wire (Cast or Extruded) PWA 694

57965, 0CZB2

PWC05-229

Ink, Stamping Black (For marking on non-porous surfaces with a rubber stamp) Ref. Dykem Black KX-425 PMC 4021-1 to -3

98148 (m)

PWC05-270

Paper, Abrasive Silicon Carbide Ref. Open 120 to 600 Grit

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

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. AS 3214-01.

A0001(s), 1A053(s)

PWC05-329

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

A0123

PWC05-331

Felt Tip Marker (Rapid Drying) (Temporary Marking) Ref. PMC 4050

A0001(s)

PWC06-001

Compound, Lubricating Aerosol Spray Application Ref. DC321 Moly Spray CPW 307

71984(m)

PWC06-002

Petrolatum, White Technical Grade US Fed. AN-P-51 PMC 9609

A0001(s), 86459(m)

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Page 8 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC06-003

Compound, Antigalling Corrosion Prevention Ref. Fel-Pro C-652 PMC 79911

73165(m)

PWC06-004

Compound, Antiseize (Molybdenum Disulfide) Ref. Dow Corning G-N Metal Assembly Paste PWA 587, PMC 9549 CPW 262

71984(m), A0018(s)

PWC06-005D

Lubricant, Fluorocarbon PTFE Release Agent Ref. MS-122DF 16 oz. Aerosol Spray

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

PWC06-007

Lubricant, Dry Film Ref. Moly Dry Film Lub PMC 79910 CPW323

73165(m)

PWC06-009

Compound, Antiseize Ref. NEVER-SEEZ Pure Nickel Special PWA 36053 or PWA 36053-1 PMC 79966 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 PWA 36001 PMC 9940

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

PWC06-032

Compound, Antigalling and Anti-seize (High Temperature) Ref. Loctite C-200 Solid Film US MIL-A-907 PWA 586, PMC 79912 CPW 37

73165(m)

PWC06-033

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

71984(m)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC06-036

Compound, Anti-seize (Paste) Ref. Molykote P-37 PWC 36246 PMC 79571 CPW 571

71984(m)

PWC06-036A

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

34568

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 PWA 595-1, PMC 9748 CPW88

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

PWC07-017

Coating, Surface Sealant (Corrosion Protection) Ref. Rockhard 576-450-002 (IP 961) PMC 79964, CPW 489

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

PWC07-023

Coating, Aluminum and Zinc Ref. Serma Tel 249 PWA 548, CPW 584

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

PWC08-002

Adhesive Fluorosilicone Ref. DC RTV 730 PMC 79924 CPW 317

71984(m)

PWC08-010

Adhesive, Rubber Synthetic Ref. EC1357 CPW 324

76381(m), A0083

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Page 10 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC09-001

Sealant, Silicone Rubber Ref. DC RTV 732 PMC 1836 CPW 519-11

71984(m), K7750, D8367

PWC09-001A

Sealant, Silicone Rubber Ref. RTV 102, 103, 108, 109 CPW 519-11

01139(B)(m)

PWC09-002

Compound, Locking and Retaining Anaerobic Ref. Loctite Grade 290 US. MIL-S-22473 PWA 549-7, PMC 79900 CPW 79-290

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

PWC09-002A

Compound, Locking and Retaining Anaerobic Ref. Loctite Grade 222 US. MIL-S-22473 PWA 549-4, PMC 79897

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

PWC09-003

Compound, Sealing Silicone Ref. Dow Corning No. 4 US. MIL-S-8660 PMC 9926 CPW 326

71984(m), D8367

PWC09-005

Compound, Universal Jointing (Solvent Free) Ref. Hylomar Advanced Formulation PL 32-M ADV No. 12369 (ST490) CPW267

K3237, 60543, S0116(m)

PWC09-006

Compound, Jointing Ref. ST512 CPW 267-4

K3237, 60543, S0116

PWC09-022

Compound, Jointing (Non-curing) Ref. CA 1000 (CPW 638)

0NYS9(m)

PWC11-001

Cleaner, Alkaline (Internal Engine Washing) Ref. CLIX

20913, 56444

PWC11-001A

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

A253

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Page 11 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC11-001B

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

35502(m), 85884

PWC11-001C

Cleaner, Alkaline (Internal Engine Washing) Ref. B&B 3100 SPMC 87-4

21361

PWC11-001D

Cleaner, Alkaline (Internal Engine Washing) Ref. ECT R-MCS (Premixed P/N 4070)

N1480

PWC11-001E

Cleaner, Alkaline (Internal Engine Washing) Ref. ECT R-MC G21 (Concentrate P/N 4072)

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 SPMC 87-2

PWC11-003A

Use PWC 11-003B as an alternative. No longer available.

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

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Page 12 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC11-003B

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

A0052(s), A0121(m), 23373(s), 37127(s), 44389, K6858(m)

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 PMC 8914

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 PMC 9009

A0001(s)

PWC11-010

Alcohol, Methyl US AMS3004 O-M-232 Grade A PMC 9089

A0001(s)

PWC11-012

Acetone Ref. Open PMC 9008

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 52

02ER0

PWC11-014

Alcohol, Isopropyl US Fed. TT-I-735 Grade A PMC 9094

A0001(s)

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Page 13 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC11-015

Flakes, Cupric Sulfate Technical Grade Ref. Open

A0001(s)

PWC11-016

Perchlorethylene Ref. Vapor Degreaser Grade US ASTM D4081 ASTM D4376 PMC 9015

A0001(s)

PWC11-020

Solvent, Carbon Removing Ref. Kemsol-556 PMC 79781

35502(m)

PWC11-021

Compound, Cold Carbon Removing Ref. Turco Super Carb PMC 9047

36325(m)

PWC11-021A

Compound, Cold Carbon Removing Ref. Penetone, Formula #423 PMC 9031

56883

PWC11-021B

Compound, Cold Carbon Removing Ref. Wyandotte P-1075 PMC 9084

88375

PWC11-022

Solvent, Cleaning Methyl Ethyl Ketone (MEK) US ASTM D740 PMC 9076, CPW 79908 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 PMC 8904

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

PWC11-024

Solvent, Methylene Chloride Ref. Open

A0001(s)

PWC11-025

Solvent, Cleaning Ref. Desoclean 45 PMC 9060

0NYS9

PWC11-026

Was Solvent Trichlorethylene

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Page 14 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

NOTE: As an alternative, use perchlorethylene PWC11-016 to replace trichlorethylene solvent. PWC11-027

Solvent, Petroleum US AMS 3160 US MIL-PRF-680 Type II (NATO Code S-753) PMC 9001

A0001(s), 36131

PWC11-029

Solvent, Removing RTV Compound Ref. Chlorothene SM

A0001(s)

PWC11-031

Cleaner, Engine Ref. Tergit PMC 79783

35502(m)

PWC11-032

Solvent, Degreaser Ref. Magkleen 4 PMC 79789

35502(m)

PWC11-033

Cleaner, Aqueous Ref. Soliterj-304 PMC 71254

35502(m)

PWC11-038

Solvent, Cleaning Ref. Deoxidine No. 624

71410, A0001(s)

PWC11-048

Solvent, Cleaning (Spray-on/Wipe-off) Ref. MAG-CHEM Teksol SPMC 156

02ER0(m)

PWC11-049

Remover, Rust, Alkaline Ref. Ardrox 185 SPMC 52

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)

PWC13-001

Primer, Epoxy Base: 519 x 303; + Curing Solution: 910-357; + Solvent 020 x 324 PWA 568, PMC 1721 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)

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CONSUMABLE MATERIALS

Page 15 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

NOTE: Desiccant is supplied in one unit bags. One unit weighs one ounce. PWC15-004

Compound, Corrosion Preventative (Hard Film, Hot Application) US AMS 3075

A0001(s)

PWC15-011

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

A0133 0VJ14

PWC15-011A

Inhibitor, Rust (External Engine Cold Section) Ref. LPS-3 US MIL-C-81309

66724

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

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CONSUMABLE MATERIALS

Page 16 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 1, Consumable Materials (Cont’d) Item

Nomenclature/Specification

Supplier Code

PWC15-013J

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

23373(m), A0101(s)

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

PWC15-017

Inhibitor, Corrosion LPS Procyon PMC79138-1

66724

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)

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

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CONSUMABLE MATERIALS

Page 17 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0006

A0013

A0015

A0018(s)

A0019(s)

A0023(m)

A0026

Name/Address Dixon Ticonderoga Inc. 531 Davis Drive Newmarket, Ontario Canada L3Y 2P1 Tel.: (905) 263-4966 Fax: (905) 895-9555 Speedry Products Inc. Richmond Hill, NJ USA Tel.: Not available Fax: Not available Castrol Canada Inc. 2150 Rue Frances Hughes Ville de Laval, Quebec Canada H7S 1N7 Tel.: (514) 382-6940 Tel.: (800) 361-3837 Fax: (514) 382-1969 National Bearings Ltd. 451 Blvd. Lebeau Ville St. Laurent, Quebec Canada H4N 1S2 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.: (514) 332-3651 Fax: (514) 332-4386 Web: www.swagelok.com 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 Tel.: (800) 387-3917 Fax: Not available

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Page 18 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0030(m) A0032

A0033

A0034

A0035

A0036

A0037(s) A0038(s)

Name/Address Ref. 07218 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 Montreal, Quebec Canada H3S 1A3 Tel.: (514) 737-3755 Fax: Not available Ashburn Industries 3219 Harrisburg P.O. Box 2046 Houston, TX USA Tel.: Not available Fax: Not available Ref. H6962 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 Web: www.swagelok.com

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Page 19 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

A0040 A0042 A0052

A0065

A0066

A0083 A0084(s)

A0097(s)

Name/Address Sermatech Canada Inc. 747 Riddle Avenue Dorval, Quebec Canada H9P 1H4 Tel.: (514) 631-2240 Fax: (514) 636-6196 Ref. U7636 Ref. U4628 Trikon Technologies Inc. 3367 Rue Griffith Saint-Laurent, Quebec Canada H4T 1W5 Tel.: (514) 339-5997 Fax: Not available Turbine Support Division Chromally American Corp. 4430 Director Drive San Antonio, TX 78220 USA Tel.: (512) 333-6010 Fax: Not available Semco Instruments Inc. 25700 Rye St. Valencia, CA 91355 USA Tel.: (805) 257-2000 Fax: (805) 295-0044 Ref. 09581 Millipore Canada Ltd. 36 Antares Drive, Suite 700 Nepean, Ontario Canada K2E 7W5 Tel.: (800) 645 5476 Fax: (613) 225 9366 PRC - Desoto International 5676 Timberlea Blvd. Mississauga, Ontario Canada L4W 4M6 Tel.: (905) 629-7999 Fax: (905) 629-7009 Web: www.prc-desoto.com

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Page 20 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0099

A0100

A0101(s)

A0102

A0103(s)

A0104(s)

Name/Address 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 900400 USA Tel.: Not available Fax: Not available 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 Tel.: (800) 323-4621 Fax: (416) 674-2987 Web: www.miller-stephenson.com Loctite Canada Inc. 2225 Meadowpine Blvd. Mississauga, Ontario Canada L5N 7P2 Tel.: (905) 814-6511 Tel.: (800) 263-5043 Fax: (905) 814-5391 Web: www.loctite.com

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Page 21 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code A0105(s)

A0121(m)

A0123

A0133

A253

D2617

Name/Address 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 Canada L6T 1B7 Tel.: (905) 791-1628 Tel.: (800) 526-4473 Fax: (905) 791-1527 Fax: (908) 464-7914 Web: www.oakite.com Wahl Instruments Inc. 234 Weaverville Highway Asheville, NC 28804-1228 USA Tel.: (828) 658-3131 Tel.: (800) 421-2853 Fax: (828) 658-0728 Web: www.instrumentationgroup.com Avtech International In.c 5491 Quartermain Crescent Mississauga, Ontario L5M 5V3 Tel.: (905) 819-1637 Email: [email protected] Almon Quimico Wyandotte Corporation Rio-De-Janeiro Brazil Tel.: Not available Fax: Not available Loctite Deutschland GmbH Arabellastrasse 17 Postfach 81 05 80 8000 Munchen 81 Germany Tel.: 0899 2680 Fax: Not available Web: www.loctite.com

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Page 22 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code D8367

H6962

K1010

K3237

K3504(m)

Name/Address Dow Corning GmbH Rheingaustrasse 34 Wiesbaden Germany 65201 Tel.: 06112371 Fax: Not available Amsterdam Valve & Fitting G. Loewik B.V. (A distributor of the Swagelok Co.) P.O. Box 9050 1180 Amstelveen The Netherlands Tel.: 3120 6470231 Fax: 3120 6474267 Web: www. swagelok.com Tyco Electronics UK Ltd. (Formally Raychem Limited) Faraday Road Dorcan, Swindon United Kingdom SN3 5HH Tel.: 01 0793-572168 Fax: 01 0793-482297 Web: www.tycoelectronics.com Hylomar Ltd. Cale Lane New Springs Wigan United Kingdom WN2 1JT Tel.: 019426 17000 Fax: Not available Indestructible Paint Co. Ltd. 25 Pentos drive Sparkhill, Birmingham United Kingdom B11 3TA Tel.: (0121) 702-2485 Fax: (0121) 778-4338

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code K6858(m)

K7750

N1480

S0036

S0081 S0089 S0098(s) S0116 U0406

Name/Address Chemetall plc. (Formally Brent Europe Ltd.) Denbigh Road Bletchley, Milton Keynes United Kingdom MK1 1PB Tel.: 44-1908-649333 Fax: 44-1908-373939 Web: www.chemetall.com Dow Corning Ltd. Meriden Business Park Copse Drive Allesley, Coventry CV5 9RG United Kingdom Tel.: 01676 528000 Fax: Not available Web: www.dowcorning.com R-MC Power Recovery A/S (Formally Ivar Rivenaes A/S) Professor Hansteensg 49 Norway 5006 Tel.: 55-328800 Fax: Not Available Texrite Products Co. 10333 Shoemaker St. Detroit, MI 48213 USA Tel.: (313) 925-9002 Fax: (313) 925-9602 Ref. 0SC51 Ref. 16956 Ref. 23354 Ref. 1HHW9 Loctite UK Ltd. Watchmead Welwyn Garden City Herts United Kingdom AL7 1-B Tel.: Not available Fax: Not available Web: www.loctite.com

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Page 24 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code U4628

U7636

0BZD7

0CZB2

0HJT8

0NYS9(m) 0SC51

Name/Address ZOK International Group Ltd. Elsted Midhurst, West Sussex United Kingdom GU29 OJT Tel.: 44-1730-811920 Fax: 44-1730-811930 Web: www.zok.com Sermatech United Kingdom Ltd. High Holborn Road Codnor Gate Industrial Estate, Ripley Derbyshire United Kingdom DE5 3NW Tel.: (44) 1773-7489261 Fax: (44) 1773-512344 Liquid Air Engineering Corp. 1155 Sherbrooke St. W. Montreal, Quebec Canada H3A 1H8 Tel.: (514) 842-5431 Fax: Not available Stoody Deloro Stellite Inc. Stellite Coatings Div. 1201 Eisenhower Dr. N. Goshen, ID 46526-5396 USA Tel.: (219) 534-2585 Fax: (219) 534-3417 Airgas Northeast Inc. 325 McCausland Court Cheshire, CT 06410 USA Tel.: (203) 250-6800 Fax: (203) 250-6834 Ref. 83574 Lucas Avitron A Division of Lucas Aerospace 1 Circle West P.O. Box 120039 Stamford, CT 06912 USA Tel.: (203) 351-8400 Fax: (203) 351-8444

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Page 25 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 0VJ14

0W138

00BB6(s)

00198

01058

01139(A) (m)

Name/Address Corrosion Technologies Corp. 2638 National Drive Garland, TX 75041-2344 USA Tel.: (972) 271-7361 Fax: (972) 278-9721 Fine Organics Corp. 6935 West 62nd Street Chicago, IL 60638 USA Tel.: (312) 586-8000 Fax: Not available Indestructible Paints Inc. 66 Erna Ave. Milford, CT 06460 USA 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 Michigan Chrome & Chemical Co. 8615 Grinnel Ave. Detroit, MI 48213-1152 USA Tel.: (313) 267-5279 Fax: Not available General Electric Co. Attn: Rubber and Fluid Products Dept. Attn: Customer Support 260 Hudson River Rd. Waterford, NY 12188 USA Tel.: (518) 233-3330 Tel.: (800) 255-8886 Fax: Not available

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Page 26 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 01139(B) (m)

02ER0(m)

02258

02570(m)

03042 03530

Name/Address General Silicones General Electric Co. Silicone Sales Dept. Customer Services 260 Hudson River Road Waterford, NY 12188 USA Tel.: (518) 233-3330 Tel.: (800) 332-3390 Fax: (518) 233-3931 Web: www.gesilicones.com MAG-CHEM 190 Blvd. Industriel Boucherville Quebec J4B 2X3 Canada Tel.: (800) 363-9929 Tel.: (450) 655-1344 Fax: (450) 655-5428 Web: www.magchem.com Enthone-OMI Inc. P.O. Box 1900 West Haven, CT 06508 USA Tel.: (203) 932-8618 Fax: (203) 937-1680 Web: www.enthone-omi.com Swagelok Co. (formally Crawford Fitting Co.) 29500 Solon Road Solon, OH 44139-3449 USA Tel.: (440) 248-4600 Fax: (440) 349-5970 Web: www.swagelok.com Ref. S0089 American Gas & Chemicals Co. Ltd. 220 Pegasus Ave. Northvale, NJ 07647-1904 USA Tel.: (201) 767-7300 Tel.: (800) 288-3647 Fax: (201) 767-1741 E-mail: [email protected]

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Page 27 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 05838

05867

05972(m)

06090

07218

Name/Address Philips Elmet Corp. 1560 Lisbon Road Lewiston, ME 04240 USA Tel.: (207) 784-3591 Tel.: (800) 526-7480 Fax: Not available Fine Organics Corp. 205 Main Street P.O. Box 687 Lodi, NJ 07644-0687 USA Tel.: (201) 472-6800 Tel.: (800) 526-7480 Fax: (201) 472-6810 E-mail: [email protected] Web: www.fineorganicscorp.com Loctite Corporation 1001 Trout Brook Crossing Rock Hill, CT 06067 USA Tel.: (860) 571-5100 Fax: (860) 571-5465 Web: www.loctite.com Raychem Corp. Electronic OEM Components Division 300 Constitution Drive Menlo Park, CA 94025-1164 USA Tel.: (650) 361-3333 Tel.: (800) 260-9099 Fax: (650) 361-3485 Imperial Oil Canada 111 St. Clair Ave. W. Toronto, Ontario Canada M4V 1N5 Tel.: (416) 968-4111 Fax: (416) 968-4374

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Page 28 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 0871(m)

08338

09185(m)

09581

1A053(s)

Name/Address Millipore Corporation 80 Ashby Road Bedford MA 01730-2271 USA Tel.: (781) 275 9200 Fax: (781) 275 5550 Web: www.millipore.com 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 60018-2675 USA Tel.: (847) 297-1600 or (800) 253-7837 Fax: (847) 390-9338 or (847) 699-5548 E-mail: [email protected] Web: www.kester.com 3M Canada Inc. 1840 Oxford. St. E. P.O. Box 5757 Terminal A London, Ontario Canada N6A 4T1 Tel.: (519) 451-2500 Tel: Telex: 064-5886 Fax: (519) 452-6262 Web: www.3m.com AAA Aircraft Supply Co. 68 Shaker Rd. Enfield, CT 06083-1083 USA Tel.: (860) 749-5192 Fax: (860) 749-8836 Web: www.aaa-aircraft.com

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Page 29 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 1C394

1DD67(m)

1E473(m)

1HHW9

1V074

10178(s)

Name/Address 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 60053 USA Tel.: (847) 966-2022 or (800) 992-2424 Fax: (847) 966-8468 Web: www.miller-stephenson.com Miller-Stephenson Chemical Co. Inc. 12261 Foothill Boulevard Sylamar, CA 91342 USA Tel.: (818) 896-4714 Tel.: (800) 992-2424 Fax: (818) 896-6086 Web: www.miller-stephenson.com W. Canning Inc. 223 North Brockman St. Pasadena, TX 77506 USA Tel.: (713) 472-5081 Tel.: (800) 521-2589 Fax: (713) 472-2400 Sulflo Inc. 1158 Erie Ave. P.O. Box 285 North Tonawanda NY 14120-3507 USA Tel.: (716) 695-3585 Fax: (716) 695-0367 Litton Canada Ltd. (Kester Solder Division) 68 Prince Charles Road P.O. Box 474 Brantford, Ontario Canada N3T 5N9 Tel.: (519) 753-3425 Fax: (519) 753-0641 Web: www.kester.com

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Page 30 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 16956

18598(m)

2R128

2R602

Name/Address Dennison Mfg. Co. Idenfication Systems Div. 1 Clark Hill Farmington, MA 01701-8164 USA 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 Miller-Stephenson Chemical Co. Inc. George Washington Highway P.O. Box 905 Danbury, CT 06813 USA Tel.: (203) 743-4447 or (800) 992-2424 Fax: (203) 791-8702 Web: www.miller-stephenson.com Castrol Inc. Speciality Products Division Suite 230 16715 Van Karman Avenue Irvine, CA 92714 USA Tel.: (714) 660-9414 Tel.: (800) 458-5823, Ext. 3012 Fax: (714) 660-9374 Astrolite Alloys Div. of Astro Metallurgical 709 Via Alondra Camarillo, CA 93010-8714 USA Tel.: (805) 484-3621 Tel.: (800) 235-5935 Fax: (805) 388-0577

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Page 31 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 20913

21361

22980 (m) 23354

23373(m)

Name/Address NCH Corp. P.O. Box 152170 2727 Chemsearch Blvd. Irving, TX 75015 USA Tel.: (214) 438-0211 Fax: Not available Web: www.nch.com B & B Tritech Inc. 875 West 20th St. Hialeah, FL 33010-2310 USA Tel.: (305) 888-5247 Fax: (305) 887-4587 Ref. 86874 PRC-Desoto Internation Inc. (Formally Courtaulds AerospaceApplication Support Centre) 823 Eastgate Drive Mt. Laurel, NJ 08054 Tel.: (609) 234-1600 Fax: (609) 234-5515 Web: www.ppg.com/prc-desoto 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 or

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Page 32 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

25645

28112

28835

29372

30133

Name/Address Chemetall Oakite Canada 115 East Drive Bramalea, Ontario Canada L6T 1B7 Tel.: (800)668-4318 Tel.: (905) 791-1628 Fax: (905) 791-1527 Whitford Corp. 33 Sproul Road Frazer, PA 19355 USA Tel.: (610) 296-3200 Fax: (610) 647-4849 Minnesota Mining & Mfg. Co. 3M Company Industrial Chemical Products 3M Center St. St. Paul, MN 55144-1000 USA Tel.: (800) 364-3577 Fax: (612) 737-7117 Web: www.3m.com Hobart Bros. Co. Hobart Square 600 W. Main Street Troy, OH 45373 USA Tel.: (937) 332-4000 Fax: (937) 332-4090 Fairchild Industries Inc. Fairchild Aerospace Fastener Division 3000 West Lomita Blvd. Torrance, CA 90505-5103 USA Tel.: (310) 784-0700 Tel.: (310) 530-0963 Fax: (310) 539-6940 Ideal Stencil Machine and Tape 102 Iowa Avenue P.O. Box 305 Belleville, IL 62222-0305 USA Tel.: (618) 233-0162 Fax: Not available Web: www.idealstencil.com

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Page 33 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 33150

33333

33564(A)

33564(B)

35502 36131

36325

Name/Address Steven Industries, Inc. 39 Avenue C Bayonne, NJ 07002 USA Tel.: Not available Fax: Not available Washington Mills Electro Minerals Corp. 1801 Buffalo Avenue Niagara Falls, NY 14302 USA Tel.: (716) 278-6600 Tel.: (800) 828-1666 Fax: Not available Dexter Aerospace Materials Division 2850 Willow Pass Rd. Pittsburg, PA 94565-3299 USA Tel.: (510) 458-8000 Fax: (510) 458-8030 Dexter Aerospace Electronic Materials Division 211 Franklin Street Orlean, NY 14760 USA Tel.: (716) 372-6300 Fax: (716) 372-6864 Ref. 02ER0 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 Groulx-Robertson Ltee 190 Oneida Drive Pointe Claire, Quebec Canada H4Y 1J4 Tel.: (514) 697-7760 Fax: (514) 697-3887

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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. 255 Norman Lachine, Quebec Canada L8E 2M8 Tel.: (514) 489-8925 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 11590-2724 USA Tel.: (516) 334-1300 Fax: (516) 334-6692 Saint Gobin/Norton Industrial Ceramic Corp. 1 New Bond Street P.O. Box 15008 Worchester, MA 01606-0008 USA Tel.: (508) 795-2863 Fax: (508) 795-4466

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

CONSUMABLE MATERIALS

Page 35 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

5W425(m)

55403(m)

56444

56883

Name/Address Oakite Products Inc. (Chemetall Chemical Products Inc.) 50 Valley Road Berkeley Heights, NJ USA 07922-2712 Tel.: (800) 526-4473 Tel.: (908) 508-2214 Fax: (908) 464-7914 Web: www.oakite.com Bostik Inc. 211 Boston Street Middleton, MA 01949-2128 USA Tel.: (978) 777-0100 Fax: (978) 750-7212 Web: www.bostik.com CAIG Laboratories Inc. 12200 Thatcher Court Poway, CA 92064 USA Tel.: (858) 486-8388 Fax: (858) 486-8398 E-mail: caig123@com Web: 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 Penetone Corp. Sub. of West Chemical Products Inc. 74 Hudson Avenue Tenafly, NJ 07670-1017 USA Tel.: (201) 567-3000 Fax: (201) 569-5340 Web: www.westpenetone.com

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CONSUMABLE MATERIALS

Page 36 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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 91749 USA Tel.: (818) 968-0717 Tel.: (800) 227-9333 Fax: Not available United States Welding Corp. 3579 Hwy., 50 East #104 Carson City, NV 89701 USA Tel.: (702) 883-7878 or (800) 423-5964 Fax: (702) 883-7776 Web: www.usweldingcorp.com Sermatech International Inc. Materials Division 155 South Limerick Road Limerick, PA 19468-1603 USA Tel.: (610) 948-5100 Fax: (610) 948-5407 Web: www.sermatech.com Furon CHR Division T & F Furon Division 3660 Edison Place Rolling Meadows, IL 60008-1013 USA Tel.: (708) 392-8090 Tel.: (800) 323-1650 Fax: (708) 392-0403 Texaco Inc. 2000 Westchester Avenue White Plains, NY 10650-0001 USA Tel.: (914) 253-4000 Fax: (914) 253-7753 or Reverside Drive East Hartford, CT 06118 USA Tel.: (860) 569-8297 Fax: Not available

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CONSUMABLE MATERIALS

Page 37 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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 14120 USA Tel.: (716) 695-2100 Fax: Not available Aviall 2075 Diplomat P.O. Box 7086 Dallas, TX 75234 USA Tel.: (972) 406-2141 Tel.: (800) 284-2551 Fax: (972) 406-2043 Alox Corporation 3943 Buffalo Ave. P.O. Box 517 Niagara Falls, NY 14302 USA Tel.: Not available Fax: Not available Unifrax Corp. (The Carborundum Co.) 2351 Whirlpool St. Niagara Falls, NY 14305-2413 USA Tel.: (716) 278-3827 Tel.: Canada: (800) 635-4464 Fax: (716) 278-3904 Web: www.unifrax.com Textron Speciality Materials Sub. of Textron Inc. 2 Industrial Avenue Lowell, MA 01851-5107 USA Tel.: (978) 452-8961 Fax: (978) 454-5619 Metallurgical Technologies Inc. 14436 Max Road Route 4, Box 4752 Pearland, TX 77581-9709 USA Tel.: (281) 485-7765 Fax: (281) 485-0211

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CONSUMABLE MATERIALS

Page 38 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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 30084-5052 USA Tel.: (800) 241-8334 Fax: (770) 493-9206 Web: www.lpslabs.com Daubert Chemical Co. Inc. 4700 South central SW Chicago, IL 60638 USA Tel.: (312) 496-7350 Fax: Not available Dixon Ticonderoga Co. Sandusky Division 1706 Hayes Avenue P.O. Box 2258 Sandusky, OH 44870-4732 USA Tel.: (419) 625-9545 Tel.: (800) 824-9430 Fax: (419) 625-0719 Web: www.prang.com 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 48686-0994 USA Tel.: (517) 496-6000 Tel.: (800) 248-2481 Fax: (517) 496-6974 Ref. 05972 (m)

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CONSUMABLE MATERIALS

Page 39 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

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CONSUMABLE MATERIALS

Page 40 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

8W577(m)

80703

82682(m)

82925

83574

Name/Address Hammill and Gillespie Inc. 154 Livingstone Avenue P.O. Box 104 Livingstone, NJ 07039-3017 USA Tel.: (201) 994-3650 Fax: Not available Aerospace Specifications Metals 1384 W. McNab Rd. Ft. lauderdale, FL 33309 USA Tel.: (954) 977-0666 Fax: (954) 977-3858 Saureisen Cements Co. 160 Gamma Drive Pittsburgh, PA 15238-2920 USA Tel.: (412) 963-0303 Fax: (412) 963-7620 Tempil Inc. 2901 Hamilton Road South Plainfield, NJ 07080 USA Tel.: (800) 757-8300 Fax: (908) 757-9273 Octagon Processes, Inc. 596 River Road Edgewater, NJ 07020 USA Tel.: (201) 945-9400 Fax: Not available PRC-Desoto International (Formally Courtaulds Aerospace Inc) 5430 San Fernando Road Glendale, CA 91209 USA Tel.: (818) 549-7973 Fax: (818) 549-7595 Web: www.ppg.com/prc-desoto

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Page 41 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 85665

85884

86459(m)

86874 (m)

87889

88375

Name/Address Witco Corp. 1 American Lane Greenwich, Conn. 06831-2559 USA Tel.: (800) 494-8287 Tel.: (888) 544-3199 Fax: (203) 552-2849 Intl. Fax: (203) 552-3414 Ecolab Inc. Ecolab Center 370 Wabasha St. St. Paul, MN 55102-1307 USA Tel.: (612) 293-2570 Fax: Not available Web: www.ecolab.com Penreco 138 Petrolia St. Karns City, PA 16041 USA Tel.: (800) 245-3952 Fax: (724) 756-1050 Sanford Corporation (A Newell Co.) 2740 Washington Blvd. Bellwood, IL 60104 USA Tel.: (708) 547-6650 Tel.: (708) 649-3513 Fax: (800) 547-9208 Web: www.sanford.com The Texacone Co. 4111 Forney Rd. Mesquite, TX 75149-2722 USA Tel.: (800) 235-2727 Fax: Not available Web: www. texacone.com Wyandotte Paint Products Co. 650 Stephenson Highway P.O. Box 1196 Troy, MI 48099 USA Tel.: Not available Fax: Not available

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CONSUMABLE MATERIALS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, Supplier Codes and Addresses (Cont’d) Supplier Code 9X212

98148(m)

99742

Name/Address Shell International Trading Co. Shell Center P.O. Box 509 London, England SE1 7NA Tel.: 44-171-934-1234 Fax: 44-171-934-8060 Dykem Co. 3624 West Lake Ave. Glenview, IL 60025 USA Tel.: (800) 323-9538 Fax: (800) 323-9536 Permacel Nitto Denko Co. U.S. Highway No. 1 P.O. Box 671 New Brunswick, NJ 08903 USA Tel.: (908) 418-2400 Tel.: Telex: 6858014 PERMACEL Fax: (908) 418-2474 Web: www.permacel.com

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Sep 24/99 Sep 24/99

Contents

1 2 blank

Sep 24/99 Sep 24/99

Airworthiness Limitations

1 2 blank

Sep 24/99 Sep 24/99

AIRWORTHINESS LEP

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TABLE OF CONTENTS SUBJECT

PAGE

AIRWORTHINESS LIMITATIONS 1.

General

1

AIRWORTHINESS CONTENTS

Page 1/2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

AIRWORTHINESS LIMITATIONS 1.

General A.

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. (1)

For Rotor Component Service Life Limits refer to the latest revision of P&WC S.B. No. 3002.

AIRWORTHINESS

Page 1/2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Jul 11/2008 Jul 11/2008

Contents

1 2 blank

Jul 11/2008 Jul 11/2008

61-20-00 Description and Operation

1 2 blank

Sep 24/99 Sep 24/99

61-20-00 Maintenance Practices

201 202 203 204 205 206

Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008

61-20 LEP

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TABLE OF CONTENTS SUBJECT

PAGE

PROPELLER GOVERNOR - DESCRIPTION AND OPERATION 1.

Description and Operation

61-20-00 1

PROPELLER GOVERNING - 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.

7.

8.

9.

Cleaning/Painting

205

A.

205

Cleaning of Gasket

Inspection/Check

205

A.

Inspection of Propeller Governor and Overspeed Governor

205

B.

Inspection of Electrical Connectors and Leads

205

C.

Inspection of Propeller Governor Gasket

206

Approved Repairs

206

A.

206

Replacement of Lock Pitch Solenoid Valve (if fitted)

Adjustment/Test

206

A.

206

Procedure

61-20 CONTENTS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PROPELLER GOVERNOR - DESCRIPTION AND OPERATION 1.

Description and Operation The propeller governor is installed at the 12 o’clock position on the front case of the reduction gearbox.The propeller governor is driven by the propeller shaft through an accessory drive shaft, to control the propeller speed and pitch settings as dictated by the cockpit control settings and flight conditions. Refer to Chapter 76-00-00, or Aircraft Maintenance Manual for further details of propeller control system.

61-20-00 PROPELLER GOVERNOR - DESCRIPTION AND OPERATION

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PROPELLER GOVERNING - 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 protector caps and plugs on disconnected tubes, component openings and electrical connectors.

C.

Lockwire used shall, unless otherwise specified, comply with specification AMS5687, 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

PWC11-014

Alcohol, Isopropyl

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-SB3045 Post-SB3045

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation A.

Removal of Propeller Governor (1)

Remove electrical connector from lock pitch (shutoff) solenoid valve (4, Fig. 201).

(2)

Disconnect propeller reversing lever from Beta control valve (6).

(3)

Move reversing lever forward to clear Beta valve clevis .

(4)

Disconnect governor interconnect rod (7) from governor reset arm (Ref. 76-10-00).

(5)

Loosen power turbine control (Py) air tube coupling nut (3) (Ref. 73-10-08) at nipple (2).

(6)

Remove airframe linkage from propeller governor speed select lever (1).

61-20-00 PROPELLER GOVERNING - MAINTENANCE PRACTICES

Page 201 Jul 11/2008

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1 9

2

8

3 4 5

7

6

C815 Removal/Installation of Propeller Governor Figure 201

61-20-00 PROPELLER GOVERNING - MAINTENANCE PRACTICES

Page 202 Jul 11/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

B.

Speed Select Lever Straight Nipple Coupling Nut Lock Pitch Solenoid Valve (Optional) Self-locking Nuts and Plain Washers Beta Control Valve Interconnect Rod Front Push-pull Rod Propeller Governor

(7)

Remove self-locking nuts and washers (5), using wrench (PWC30114-09)or (PWC30114-16). Remove propeller governor (9) and gasket from mounting pad.

(8)

Remove gasket and inspect (Ref. Inspection/Check).

(9)

If governor is to be replaced, remove nipple (2) from Py port on governor and discard preformed packing.

(10)

Install suitable protective caps/covers on all openings.

(11)

Make sure all instructions (Ref. SB3146) have been complied with before installing propeller governor.

Installation of Propeller Governor (1)

If new or overhauled governor is being installed, install nipple (8 , Fig. 202): (a) Lightly lubricate new preformed packing (7) (Ref. 70-00-00) and install on nipple (8). (b) Install nipple in Py port in propeller governor. Tighten and torque nipple 65 to 75 lb. in.

(2)

Install gasket (Ref. SB3298) with raised surface up, on gearbox studs.

CAUTION: MAKE SURE DRIVE SPLINES CORRECTLY ENGAGE. (3)

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

CAUTION: DO NOT EXCEED THE TORQUE LIMITS OF 125 TO 135 LB. IN. OVER TORQUING CAN CAUSE DISTORTION AND POSSIBLE FAILURE OF THE PROPELLER GOVERNOR. (4)

Install governor with washers and nuts (5, Fig. 201). Torque the nuts 125 to 135 lb.in. using wrench (PWC30114-09) or (PWC30114-16).

(5)

Connect fork end of Beta control valve (6) to reversing lever using pin, washer and cotterpin (Ref. 76-10-00).

61-20-00 PROPELLER GOVERNING - MAINTENANCE PRACTICES

Page 203 Jul 11/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

7 8 1

2

3

4

5

6

C3920 Replacement of Lock Pitch Solenoid Figure 202

61-20-00 PROPELLER GOVERNING - MAINTENANCE PRACTICES

Page 204 Jul 11/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 202 1. 2. 3. 4. 5. 6. 7. 8.

6.

(6)

Install governor interconnect rod (7) to governor reset arm .

(7)

Connect airframe linkage to speed select lever (1) on propeller governor.

(8)

Connect coupling nut (3) of power turbine (Py) control front tube to nipple (2) on governor. Torque coupling nut 90 to 100 lb.in., and lockwire.

(9)

Install electrical connector to lock pitch solenoid valve (4) on propeller governor.

(10)

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

(11)

Check system rigging (Ref. Aircraft Maintenance Manual).

(12)

Check engine operation (Ref. Adjustment/Test).

Cleaning/Painting A.

Cleaning of Gasket (1)

7.

Screw Lock Pitch Solenoid Valve Preformed Packing (2 each) Preformed Packing Preformed Packing Propeller Governor Preformed Packing Straight Nipple

Clean with solvent (PWC11-014).

Inspection/Check A.

B.

Inspection of Propeller Governor and Overspeed Governor (1)

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

(2)

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

(3)

Examine fluid ports for damage.

Inspection of Electrical Connectors and Leads (1)

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

(2)

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

61-20-00 PROPELLER GOVERNING - MAINTENANCE PRACTICES

Page 205 Jul 11/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(3) C.

8.

Inspection of Propeller Governor Gasket (1)

Examine for tears in, and deterioration of gasket material.

(2)

Examine for breakdown of bond between asbestos/rubber material and steel plate core.

(3)

Examine mounting holes for elongation.

(4)

Examine screen for damage and looseness.

Approved Repairs A.

9.

Check leads for damage to outer covering.

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 (Ref. 70-00-00, MAINTENANCE PRACTICES), 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, torque 9 to 11 lb.in., and lockwire.

Adjustment/Test A.

Procedure (1)

Start engine (Ref. 71-00-00, ADJUSTMENT/TEST) and do checks associated with Installation/Replacement of Propeller Governor, Overspeed Governor and Automatic Feathering Valve (Ref. 71-00-00, ADJUSTMENT/TEST, Table 501).

61-20-00 PROPELLER GOVERNING - MAINTENANCE PRACTICES

Page 206 Jul 11/2008

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Dec 10/2010 Dec 10/2010

Contents

1 2 3 4

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

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

Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002 Jan 25/2002

70-00-00 Maintenance Practices

CHAPTER SECTION

PAGE

DATE

232 233 234 blank

Jan 25/2002 Jan 25/2002 Jan 25/2002

70-00-00 Removal/ Installation

401 402 403 404 405 406 blank

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

70-00-00 Inspection Check

601 602 603 604 605 606 607 608 609 610 blank

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

70-00-00 Cleaning/ Painting

701 702

Sep 24/99 Sep 24/99

70-00-00 Approved Repairs

801 802 803 804 805 806 807 808 809 810 blank

Dec 10/2010 Dec 10/2010 Dec 10/2010 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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70-00 LEP

Page 1/2 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

203

A.

General

203

B.

Torque Wrench and Extensions

203

Torque Recommendations

204

A.

Lubricated Parts

204

B.

Nuts, Bolts and Screws

204

C.

Self-locking Nuts

206

D.

Lockwire and Cotterpin Requirements

207

E.

Slotted, Steel Locknuts (Prevailing Torque Type)

207

F.

Standard and Stepped Studs

207

G. Hose, Tubing and Threaded Couplings

207

Locking Devices

207

A.

Keywashers (Tab and Cup Type)

207

B.

Retaining Rings

209

C.

Lockwire

209

6.

Identification of Hardware Material, Particularly Nuts and Bolts

210

7.

Stainless Steel Bolts with Reduced Pitch Diameters

216

8.

Debris Analysis and Material Specifications

216

A.

General

216

B.

Filter Patch Check Debris Inspection/Analysis

218

C.

Chip and Flake Analysis

218

D.

Identification of Metal Particles

219

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

70-00 CONTENTS

Page 1 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

STANDARD PRACTICES - MAINTENANCE PRACTICES (Cont’d)

9.

10.

11.

70-00-00

E.

Material Specifications

221

F.

Laboratories

227

Marking of Parts

230

A.

General

230

B.

Permanent Marking

231

C.

Temporary Marking

231

Lubrication of Preformed Packings

233

A.

General

233

Touch-up Solution

233

A.

Chrome Pickle Solution (Magnesium RGB, AGB Housings and Compressor Inlet Cases Only)

STANDARD PRACTICES - REMOVAL/INSTALLATION

233 70-00-00

1.

General

401

2.

Removal/Installation

402

A.

Replacement of Straight Nipples, Straight Adapters, Bulkhead Couplings and Tube Connector Nipples.

402

B.

Replacement of Elbows, Elbow Adapters

402

C.

Installation/Removal of Hydraulic and Pneumatic Lines

403

STANDARD PRACTICES - INSPECTION

70-00-00

1.

General

601

2.

Inspection

606

A.

General

606

B.

Gages

606

C.

Fuel, Oil and Air Filters

606

D.

Fuel, Oil and Air Tubes

607

E.

Welded Repairs

607

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70-00 CONTENTS

Page 2 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

STANDARD PRACTICES - INSPECTION (Cont’d) F.

Rotating Components

70-00-00 607

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

4.

Fixtures, Equipment and Supplier Tools

801

5.

Welding

802

A.

General

802

B.

Clean Before Welding

802

C.

Procedure

802

D.

Clean After Welding

803

E.

Local Stress Relief

803

F.

Inspection of Welding

803

6.

7.

Blend Repairs

804

A.

Repair Procedure

804

B.

Definitions

804

C.

General

804

D.

Air Gun

804

Threaded Inserts

805

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

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TABLE OF CONTENTS SUBJECT

PAGE

STANDARD PRACTICES - REPAIR (Cont’d) A. 8.

9.

Replacement of Threaded Inserts

70-00-00 805

Studs

805

A.

General

805

B.

Replacement of Studs

806

C.

Repair of Damaged Stud Hole

807

Shanknuts

808

A.

808

Replacement

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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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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 with petroleum solvent (PWC11-027) or (PWC11-031) 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)

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

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

0.112-48NF-2A

3

0.5

0.138-40NF-2A

6

0.164-36NF-2A 0.190-32UNF-3A

Mating Bolt Thread Size

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

13

2.0

0.164-32NC-2A

9

1.5

Mating Bolt Thread Size

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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) (Cont’d) Max Locking Torque

Min Breakaway Torque

Max Locking Torque

Min Breakaway Torque

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

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 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. 201). In order to arrive at the resultant required torque limits, the following formula shall be used: T - Desired torque on the part. E - Effective length of special extension or adapter. L - Effective length of torque wrench. A - Distance through which force is applied to part.

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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.

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.

CAUTION: MAKE SURE THAT ANTI-SEIZE AND ANTI-GALLING COMPOUNDS ARE APPLIED IN A THIN EVEN COAT, AND THAT EXCESS COMPOUND IS COMPLETELY REMOVED TO AVOID CONTAMINATION OF ADJACENT PARTS, PASSAGES OR SURFACES WHERE THE COMPOUND MAY CAUSE MALFUNCTIONING, OR EVEN FAILURE OF ENGINE.

B.

(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 mixed with engine oil or grease may be used. Particular applications of molybdenum disulfide are indicated in the individual text portions of this manual, as applicable. 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 torque values given in relevant assembly instruction remain constant.

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L

E A

C192A Torque Wrench and Extension Figure 201

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C.

Self-locking Nuts (1)

The locking force for self-locking nuts and helical coil inserts must be checked at assembly. The force must not be less than the values shown (Ref. Table (2)) unless otherwise specified.

(2)

When checking self-locking fasteners, make sure the fastener is not seated. This ensures that only the force necessary to overcome the friction holding the thread is measured. 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

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

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

D.

1.000-8

110.0

1.000-12

90.0

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

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

F.

Torque lb.in. Min

Lockwire and Cotterpin Requirements (1)

E.

Thread Size

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.

Standard and Stepped Studs (1)

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.

G. Hose, Tubing and Threaded Couplings (1)

5.

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

Locking Devices A.

Keywashers (Tab and Cup Type) (Ref. Fig. 202)

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 ENGINE. (1)

Assembly Requirements for Cupwashers:

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C1189B Examples of Lockwashers Figure 202

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(a) Examine 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 face which abuts 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 cupwasher placed against shaft slots opposite to direction of nut tightening, screw nut fingertight. (f)

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

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

B.

(i)

Repeat procedure with new cupwasher.

(j)

Stake cupwasher.

Retaining Rings CAUTION: THOROUGHLY INSPECT ALL RETAINING RINGS, INCLUDING SPIROLOX, FOR CONDITION. DISTORTED RINGS ARE NOT ACCEPTABLE AND MUST BE REPLACED. (1)

C.

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 heat and corrosion resistant steel wire of 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 vibrations if twisted too tightly. The lockwire shall be pulled taut when being twisted, but shall have minimum tension, if any when secured.

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6.

(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 203 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 204.

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. 205). 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.

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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.

C194D Lockwiring Procedure Figure 203

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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.

C195_1 Lockwiring Examples Figure 204 (Sheet 1 of 3)

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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.

C195_2 Lockwiring Examples Figure 204 (Sheet 2)

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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.

C195_3 Lockwiring Examples Figure 204 (Sheet 3)

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C196 Hardware Code Identification Figure 205

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

7.

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.

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. 206).

8.

Debris Analysis and Material Specifications A.

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.

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120 ° 0.109 0.079

REDUCED PITCH DIAMETER BOLT

STANDARD BOLT

C197B Reduced Pitch Diameter Bolt Identification Figure 206

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(3)

B.

Analysis (form, appearance, dimensions, quantity and material) of the debris captured by the filters and chip detectors 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. (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 203) is found, the operator must be advised as soon as possible by telephone and provided with a detailed written report.

Chip and Flake Analysis (1)

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

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(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) Chip detector position (Reduction Gearbox or Accessory Gearbox). (d) Reason for chip detector 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 203) is found, the operator must be advised as soon as possible by telephone and provided with a detailed written report.

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 (PWC05-165) watch glass white porcelain spot plate ammonium biflouride crystals (PWC05-008)

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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: 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 (PWC05-008A) 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 PWC05-073to 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.

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WARNING: NEVER TRY TO BURN MORE THAN A FEW PARTICLES OF METAL SUSPECTED TO BE MAGNESIUM. DUST IS EXPLOSIVE. (c) 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.

(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 (PWC05-057A) 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 203 . The common contaminants found in the oil system are listed in Tables 204 and 205.

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TABLE 203, 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

Sleeve, Prop., Oil Transfer

RGB RGB

AMS 4082, 4150

Alum. (AA6061)

Sleeve, First-stage, Carrier

AMS 4117, 4127, 4150

Alum. (AA6061)

Stator, No. 1 Brg Air Seal

GG

AMS 4214

Alum. (Alloy 355)

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

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

AMS 4439

Magnesium (ZE41E)

Compressor Inlet Case

GG

Diaphragm

AGB

Housing

AGB

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TABLE 203, Material Specification (Engine Components) (Cont’d) Specification

Material

AMS 4616

Bronze

Nomenclature

Engine Location

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

Cage, Coupling Shaft Brg

RGB RGB

AMS 5315

Steel

Sleeve, Propeller, Oil Transfer

AMS 5613

SST (51410)

No. 1 Brg Front Air Seal

GG

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 Front 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

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AGB

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TABLE 203, Material Specification (Engine Components) (Cont’d) Specification

AMS 6322

AMS 6414

Material

Steel (8740) Steel (4340)

Nomenclature

Engine Location

Coupling, Second-stage Sun Gear

RGB

Adapter, Second-stage Sun Gear

RGB

Carrier, First-stage Planet Gear

RGB

Gear, First-stage, Planet

RGB

Gear, First-stage, Sun

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

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AGB

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TABLE 203, Material Specification (Engine Components) (Cont’d) Specification

Material

AMS 6415

Steel (4340)

AMS 6440/ 6444

AMS 6490

AMS 6491

Steel (52100)

Steel (M50) Steel (M50)

Nomenclature

Engine Location

Shaft, Propeller

RGB

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, Starter Generator 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 203, 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 204, 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

Fe2O3

Rust, Non-magnetic

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

TABLE 205, Common Contaminants - Organic Material Contaminant Detected Black Fluorocarbon Rubber, Red Silicon Rubber, Blue Fluorosilicon Rubber

Source Preformed Packings, Seal Gaskets

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TABLE 205, Common Contaminants - Organic Material (Cont’d) Contaminant Detected

Source

Chloroprene Nitrile Rubber

Gaskets

Carbon

Decomposed Oil, Carbon Seals

Fibers Plastics Paint Flakes F.

Laboratories (1)

Chip and flake analysis should be done by a qualified laboratory; some of which are listed below. Air Alliance (M-50, bearing alloy ONLY) Engine Shop Supervisor 611, 6ieme Ave. Saint-Foy, Quebec Canada G2E 5W1 TEL: (418) 877-7622 FAX: (418) 872-8337 Alfa Romeo Avio Laboratory 80038 Pomigliano D’Arco Napoli Italy TEL: 39-81-8430493 FAX: 39-81-8846522 Skywatch Service of Analysts, Inc. 3075 Cornors North Court NW Norcross, GA 30071 USA TEL: (800) 241-6315 FAX: (404) 448-5918 Areco Canada Inc. 40 Camelot Drive Napean, Ontario K2G-5W6 Canada TEL: (613) 228-1145 FAX: (613) 228-1148

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Aviation Laboratories Inc. 12911 South Bublong Ave. Gardena, CA 90247 USA TEL: (213) 217-9369 Aviation Laboratories Inc. New Orleans International Airport 918 Maria Street Kenner, LA 70062 USA TEL: (504) 469-6751 FAX: (504) 469-6886 Chemical Analyst Laboratory Department of Biochemistry Trinity Collage Dublin 2 Ireland TEL: 772941, Ext: 1574 FAX: 772400 Deutsche Lufthansa AG POSTFACH 300 2000 Hamburg 63 Germany Jet-Care International Inc. 3 Saddle Road Cedar Knolls, New Jersey 07927-902 USA TEL: (201) 292-9597 FAX: (201) 292-3030 Martel Laboratory Services Inc. 1025 Cromwell Bridge Road Baltimore, MD 21204-3309 USA TEL: (301) 825-7790 FAX: (301) 821-1054 Martel Laboratory Services Inc. Aero Services Building Capital Airport Spring field, IL 62707 USA TEL: (217) 522-0009 FAX: (217) 544-2034

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Martel Laboratory Services Inc. 250 Meadowfern Suite 102 Houston, TX 77067 USA TEL: (713) 872-9100 FAX: (713) 872-7916 Materials Research Laboratories Industrial Technology Research Institute Building 77, 195 Chung Hsing Road Section 4, Chutung, Hsinchu 31015 Taiwan Metro Tech Systems Ltd. Bay 112 5621-11th Street N.E. Calgary, Alberta Canada T2E 7G9 TEL: (403) 295-8803 FAX: (403) 295-3848 PCAS (Produits Chimiques Auxiliaires et Syntheses) Zone Industrielle de la Vigne aux Loups 23 Rue Bosselet 91-161 Long-Jumeau France FAX: (1) 64-482319 Predictive Maintenance Corporation 400 Sauve Street West, Suite 101 Montreal, Quebec Canada H3L 1Z8 TEL: (514) 383-6330 FAX: (514) 383-5631 or Predictive Maintenance Corporation 206, 2723-37 Avenue NE Calgary, Alberta Canada T1Y 5R8 TEL: (403) 250-8378 FAX: (403) 286-8287

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Spectro Oil Analysis Company Ltd. Palace Gate High Street Odiham, Hampshire RG29 1NP United Kingdom TEL: 44-0-1256 704000 FAX: 44-0-1256 704006 Vernolab Zone Industrielle des Cents Sillone 27-130 Verneuil Eure France FAX: 16-32601646 Wear Check Canada Inc. 4161 Sladeview Crescent Unit 11 Mississauga, Ontario Canada L5L 5R3 TEL: (905) 569-8600 (905) 268-2131 FAX: (905) 569-8605 9.

Marking of Parts A.

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 1.160 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 0.250 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 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)

Soapstone shall not be used to mark engine parts.

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B.

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

(2)

Methods CAUTION: DO NOT ELECTROLYTICALLY ETCH ANODIZED 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. It may be used on parts harder than Rockwell C45 when specifically permitted. NOTE:

C.

Vibration peening marking method can be substituted for marking parts originally marked by diamond drag or roll marking.

Temporary Marking (1)

General (a) Temporary methods of marking are those in which the marking will identify 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 CARBURIZATION OR INTERGRANULAR ATTACK WHEN THE PART IS SUBJECTED TO INTENSE HEAT, SHALL NOT BE USED. IN THE EVENT THAT AN UNAUTHORIZED MARKING MATERIAL IS 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.

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(2)

Methods CAUTION: ANODIZED SURFACES MUST NOT BE ELECTROLYTICALLY ETCHED. (a) Electrolytic Etch - Characters are produced by electrolysis confined to area by a stencil. This is primarily a permanent marking method. However, where specified, it may also be used for temporary marking. (b) Ink Marking 1

Characters are produced by applying, by any means, an ink which does not injure the surface. Inks used in marking may have a light etching action, providing etching does not injure the surface. NOTE:

(3)

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.

Marking Materials, Hot and Cold Section Engine Parts (a) Felt Wick Pen (PWC05-048A)and Speed Dry Instant Dry Ink(PWC05-048B). (b) Marks-A-Lot Marker (PWC05-048). (c) Brushpen No. 57 (PWC05-046A) and Tex-Rite Instant Dry Ink (PWC05-046), black , red , and purple. (d) Micro Supreme Dye, Purple No. 142 (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)

Eberhard Faber Spectracolor Pemncil, Silver No. 1428,(PWC05-018) or Berol Verithin Pencil, Silver No. 753 (PWC05-018A).

Marking Materials, Cold Section Engine Parts Only Dykem Ink (PWC05-046C) KX425 (Black) or KXX122 (White). Carters Ink (PWC05-027)No. 451 (Black).

(5)

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.

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10.

Lubrication of Preformed Packings A.

General

CAUTION: APPLICATION OF LUBRICANT PLUS PROPER ASSEMBLY, WILL PREVENT DAMAGE TO PREFORMED PACKINGS. DAMAGED PREFORMED PACKINGS CAN CAUSE ENGINE MALFUNCTION. (1)

Prior to installation it is recommended that all preformed packings be coated with lubricant to the following specifications: (a) Preformed packings used in fuel and/or oil system, use engine oil (PWC03-001). (b) Preformed packings associated with Air, Water and Alcohol - Calibrating Fluid (PWC03-002).

11.

Touch-up Solution WARNING: 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. A.

Chrome Pickle Solution (Magnesium RGB, AGB Housings and Compressor Inlet Cases Only) (Ref. Table 206) (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 required amount of sodium dichromate. Stir to dissolve the sodium dichromate.

(3)

Slowly and carefully add the required amount of nitric acid. Stir to mix the solution.

(4)

Fill the remainder of the container with tap water to the specified volume required. TABLE 206, 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.

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STANDARD PRACTICES - REMOVAL/INSTALLATION 1.

General A.

During removal/disassembly, tag and mark all parts, clips, and brackets as to their location to prevent improper installation/assembly.

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. Dust caps used to protect open tubes against contamination shall always be installed over, not in the tube ends. Flow through the lines may be blocked if lines are inadvertently installed with dust caps in the tubes.

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.

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.

F.

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.

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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2.

J.

Whenever adhesive 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 this compound and accumulated foreign matter must be removed.

Removal/Installation CAUTION: 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 FASTEN TUBE ONLY WHEN IT IS INSTALLED IN POSITION WITH NO NOTICEABLE TENSION OR LOAD. A.

Replacement 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.

(3)

Lubricate new preformed packing with light film of lubricant (Ref. Standard Practices - Maintenance Procedures).

(4)

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

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

B.

(5)

Tighten fitting in boss to torque value detailed in relevant assembly instruction.

(6)

Install jam nut on flange mounted fittings and tighten to recommended torque (Ref. Table 401).

Replacement of Elbows, Elbow Adapters (Ref. Fig. 401). (1)

Remove fittings from engine lines or accessory units. NOTE:

Before removal, note angular position of fitting on engine or unit.

(2)

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

(3)

Lubricate new preformed packings, packing retainer (back-up ring) and thread of elbow fitting with light film of lubricant (Ref. Standard Practices - Maintenance Procedures).

(4)

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

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(5)

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

(6)

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

(7)

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 force.

(8)

With fitting in this position, hold jam nut stationary and turn elbow fitting into boss a further 1 1/2 turns. NOTE:

(9)

From this position the elbow fitting may be further turned inward to a maximum of one turn to facilitate alignment of fitting. 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.

With elbow fitting in correct alignment position, tighten jam nut 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. TABLE 401, Torque Values for Jam Nuts

C.

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/Removal of Hydraulic and Pneumatic Lines NOTE:

Refer to specific chapters for assembly instructions; Chapter 73 for fuel and pneumatic lines and Chapter 79 for oil lines.

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1

1

DETAIL

2

2

3

3

4

4

1

DETAIL

1

2

1

2 2 3

3 4 4 5 5 DETAIL

3

DETAIL

4

C8818A Installation of Typical Elbow Fitting Figure 401

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Key to Figure 401 1. 2. 3. 4. 5.

Elbow Fitting Jam Nut Packing Retainer Preformed Packing Boss

CAUTION: DO NOT USE FORCE TO POSITION LINE ONTO COUPLING ADATPERS. (1)

When hydraulic or pneumatic lines are installed, whether solid tubes or flexible hoses, make sure lines engage onto respective coupling adapters without tension or load.

(2)

Alignment must be obtained by adjusting the position of the adapters. Refer to Paras. A. and B. preceding 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, 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. While it is frequently possible to repair a damaged part so that it may be safely reinstalled, it is important that the cause of the damage be determined and corrected if possible. Otherwise more serious consequences may result. Some of the physical conditions most commonly encountered during inspection of engine parts are listed in Table 601. TABLE 601, Typical Physical Conditions Term

Description

Usual Causes

ABRASION

A roughened area. Varying degrees of abrasion can be described as light or heavy depending upon the extent of repair necessary to restore the surface.

Presence of fine foreign material between moving surfaces.

BEND

General distortion in structure as distinguished from a local change in conformation such as a dent, peening, etc.

Forces as defined under STRESS, or uneven application of heat.

BLISTERING

Raised areas indicating separation of the surface from the base. Usually found on plated or painted surfaces.

Imperfect bond with the base, usually aggravated by the presence of moisture.

BREAK

Complete separation by force into two or more pieces.

Fatigue; shock or overload.

BRINELLING

Indentations sometimes found on the surface of ball or roller bearing parts.

Improper assembly or disassembly e.g. removing or installing a roller or ball bearing by force on the free race.

BURNING

Injury to the surfaces by excessive heat. Evidenced by characteristic discoloration or, in severe cases, by loss or flow of material.

Excessive heat due to lack of lubrication, improper clearance.

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TABLE 601, Typical Physical Conditions (Cont’d) Term

Description

Usual Causes

BURNISHING

Mechanical smoothing of a metal surface by rubbing not accompanied by removal of material but sometimes by discoloration around the outer edges of the area.

Normal operation of parts.

BURR

A sharp projection or rough edge.

Faulty machining operations, excessive wear, peening.

CHAFING

A rubbing action between two parts having limited relative motion.

CHIPPING

Breaking out of small pieces of material.

Concentration of stress due to shock, nicks, scratches, inclusions, peening, etc., careless handling of parts.

CORROSION

Breakdown of the surface by chemical action.

Presence of corrosive agents.

CRACK

A partial fracture.

Excessive stress due to shock overloading, extension of a nick or scratch, or overheating.

DENT

Small, smoothly rounded hollow in the surface.

Concentrated overload resulting from peening or the pressure of chips between loaded surface; striking of part with dull object.

ELECTROLYTIC ACTION

Breakdown of the surface by electrolytic action between parts composed of dissimilar metals.

Galvanic action between dissimilar metals.

EROSION

Carrying away of material by the flow of grit, chemicals, or hot gasses.

Flow of corroding liquids or grit-laden oils.

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TABLE 601, Typical Physical Conditions (Cont’d) Term

Description

Usual Causes

FATIGUE

Progressive yielding of one or more local areas of weakness such as tool marks, cracks, or inclusions, under repeated stress. The progressive nature of the failure is usually indicated by several lines approximately concentric about a center, or ‘‘focus’’ which discloses the original point of failure.

Tool marks, sharp corners, nicks, cracks, inclusions, galling, corrosion, insufficient tightening of studs or bolts to obtain proper stretch.

FLAKING

Breaking away of pieces of a plated or painted surface.

Incomplete bond; excessive load, blistering.

FRETTING CORROSION

Discoloration may occur on surfaces which are pressed or bolted together under high pressure. On steel parts the color is reddish brown. On aluminum the oxide is white.

Rubbing off in fine particles of metal slight movement between parts and subsequent oxidizing of these particles.

GALLING

The transfer of metal from one surface to another.

Severe chafing or fretting action caused during engine operation by a slight relative movement of two surfaces under high contact pressure.

GLAZING

Development of a hard, glossy surface on bearing surfaces.

Combination of pressure oil and heat.

GOUGING

Displacement of material from a surface by a cutting, tearing or displacement effect.

Presence of a comparatively large foreign body between moving parts.

GROOVING

Smooth rounded furrows, such as score marks where sharp edges have been polished off.

Concentrated wear, abnormal relative motion of parts; parts out of alignment.

GUTTERING

Deep, concentrated erosion.

Enlargement of a crack or defect bu burning of an exhaust flame.

IMPERFECTION

An interruption (nonuniformity) in the normal surface condition of a part configuration which must be evaluated for acceptance to an assigned standard.

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TABLE 601, Typical Physical Conditions (Cont’d) Term

Description

Usual Causes

INCLUSION

Foreign material enclosed in the metal. Surface inclusionsare indicated by dark spots or lines.

Inherent discontinuity in the material.

NICK

A sharp indentation caused by striking of one part against another metal object.

Carelessness in handling of parts or tools during, or prior to assembly; sand or fine foreign particles in the engine during operation.

PEENING

Deformation of the surface.

Impact of foreign object, such as occurs in repeated blows of a hammer on the part.

PICK-UP

Rolling up of metal, or transfer of metal from one surface to another.

Rubbing of two surfaces without sufficient lubrication; presence of grit between surfaces under pressure during assembly; unbroken edges of press fitted parts; incipient seizure of rotating parts during operations.

PILE-UP

Displacement of particles of a surface from one point to another.

PITTING

Small, irregularly shaped cavities in a surface from which material has been removed by corrosion or chipping. Corrosive pitting is usually accompanied by a deposit formed by the action of a corrosive agent on the base material.

PROFILE

The actual contour of a surface on a section perpendicular to that surface unless some other angle is specified.

SCORING

Deep scratches made by sharp edges of foreign particles during engine operation; elongated gouges.

Corrosive pitting; breakdown of the surface by oxidation or some other chemical or electrolytic action.

Presence of chips between loaded surfaces having a relative motion.

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TABLE 601, Typical Physical Conditions (Cont’d) Term

Description

Usual Causes

SCRATCHES

Narrow, shallow marks caused by the movement of a sharp object or particles across a surface.

Carelessness in handling of parts or tools prior to, or during, assembly; sand or fine foreign particles in engine during operation.

SMOOTH

A surface that is continuously even, free of irregularities, presenting no resistance to the sliding of a finger or spherical stylus. Can be applicable to a one plane surface or transition surfaces between planes.

SPALLING

Sharply roughened area characteristic of the progressive chipping or peeling of surface material.

STRESSES

When used in describing the cause of failure of machineparts, stresses are generally divided into three groups - compression, tension and shear. These are used to describe the forces as follows:

Surface crack, inclusion or similar surface injury causing a progressive breaking away of the surface under load.

COMPRESSION - Action of two directly opposed forces which tend to squeeze a part together. TENSION - Action of two directly opposed forces which tend to pull apart. SHEAR - Action between two opposed parallel forces. SURFACE

The designed boundary, shape and extent of which is usually shown and dimensioned on an illustration

TORSION

External twisting opposed by shear stress.

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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.

Gages NOTE:

C.

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. Make sure that contacting surfaces are clean and contacting faces of part to be measured are free of dirt and burrs. When using depth gages, make sure anvil is held tight and square against part to be measured.

(2)

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

(3)

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

Fuel, Oil and Air Filters (1)

When determining the condition of engine fuel, oil lubrication and pneumatic systems, removed filters must be inspected for condition, contamination and other defects before the application of any allowable cleaning procedures. Clogged filters could be cause for downstream low pressure in systems. NOTE:

Other engine components will normally be cleaned prior to carrying out inspection procedure.

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D.

Fuel, Oil and Air Tubes NOTE:

E.

F.

The following criteria is considered standard. Specific instructions for inspection and limits where applicable will be called out in the appropriate chapter/section/unit.

(1)

Cracked tubing must be replaced. No repair is permitted.

(2)

Minor scratches having no appreciable depth are acceptable. Scratches to 0.005 inch deep must be smoothed out. Replace tubing with scratches over 0.005 inch deep.

(3)

Individual nicks to 0.062 inch long by 0.010 inch wide and 0.003 inch deep are acceptable. Nicks to a maximum 0.005 inch deep must have sharp edges removed. Replace tubing with nicks greater than 0.005 inch deep.

(4)

Round bottom dents on straight sections of tubing are permitted provided the length and depth are not greater than 10 percent of the normal outside diameter of tube. No more than one dent to maximum depth per 12 inch length of tube is acceptable. Dents on tube bends, which cause restriction by flattening and local weakening, are not acceptable.

(5)

Minor isolated pitting to 0.003 inch deep is acceptable. Clusters of pitting should be removed to maximum 0.005 inch deep. Tubing must be replaced if pitting exceeds 0.005 inch deep.

(6)

Staining on tubing and surface corrosion is acceptable if removable by light polishing with abrasive cloth and oil.

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.

(2)

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.

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.

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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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(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 3 to 4X may be used as an aid to evaluate and confirm an observed condition in detail.

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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 do the 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 chapter 72-00-00, MAINTENANCE PRACTICES. 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 chapter 72-00-00, MAINTENANCE PRACTICES.

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 PWC13-003

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

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

4.

Tool No.

Name

PWC30271-100

Spreader

Fixtures, Equipment and Supplier Tools The fixtures, equipment and supplier tools listed below are used in the following procedures. Name Welder, AC/DC with high frequency controls Torch, Linde HW-10 or equivilent with recirculating water Cups, ceramic various sizes Regulator, argon gas Flowmeters (2 off)

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

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5.

Welding CAUTION: 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. A.

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.

Clean Before Welding (1)

C.

Refer to CLEANING.

Procedure

WARNING: IF AN OXYGEN REGULATOR IS USED WITH ARGON GAS, DO NOT REINSTALL THE 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 (1)

Connect one argon gas flowmeter to torch and connect other flowmeter, if necessary, behind crack as a backup when ready to weld.

(2)

Connect torch to arc welder for straight polarity.

(3)

Insert a 1/16 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.

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

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(4)

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:

(5)

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.

(6)

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:

(7)

D.

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.

Refer to CLEANING.

Local Stress Relief (1)

F.

Test welds, using corresponding material of same thickness and joint design, should be made to determine correct gas pressure and arc welding settings.

Clean After Welding (1)

E.

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.

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)

Refer to INSPECTION.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

6.

Blend Repairs A.

Repair Procedure (1)

Blend repair using carborundum stones.

CAUTION: DO NOT POLISH WITH POWER TOOLS.

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.

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 smoothing , 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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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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: BEFORE USING INSERTS, IN ANY PART OF THE ENGINE, REFER TO THE ILLUSTRATED PARTS CATALOG FOR APPROVED LOCATIONS AND PART NUMBERS OF INSERTS. (1) (2)

Remove unserviceable insert using an approved extraction tool. Clean out hole and make sure swarf and other foreign matter is removed. NOTE:

8.

Inserts must be coated on external threads with primer (PWC13-003) prior to installation.

(3)

Install new threaded insert into threaded hole using installation tool. The insert outer thread must be between one and one-half threads below the surface of the 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.

General

CAUTION: BEFORE NEW STUDS ARE INSTALLED, REFER TO THE 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 P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

installation of a helical coil (Ref. Para. A.) or key-type insert. Consideration should, however, be given to reduction of thickness of walls or 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.

(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

0.164-36

10

30

30

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 802, Stepped Stud Torque Limits (Cont’d) Stud Thread Size (Nut End)

Minimum

Maximum Necked Down $

Maximum Plain #

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 then 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. (f)

Dry using clean, dry compressed air.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(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. A.).

Shanknuts A.

Replacement (Ref. Fig. 801) CAUTION: AVOID DAMAGE TO FLANGE. (1)

Using a suitable drill, partially remove the flared end of shanknut.

(2)

Remove shanknut body with a parallel pin punch at drilled end to shear weakened flare, and retrieve the case.

(3)

Install new shanknut (Ref. IPC) and hold against flange.

(4)

Lightly lubricate tapered portion of spreader (PWC30271-100) 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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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

SHANK NUT BEFORE INSTALLATION

SHANK NUT AFTER INSTALLATION

SPREADER

C2769B Shanknut Replacement Figure 801 P&WC Proprietary Information. Subject to the restrictions on the title page.

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Dec 10/2010 Dec 10/2010

Contents

1 2 3 4 blank

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

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

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CHAPTER SECTION

71-00-00 Cleaning/ Painting

PAGE

DATE

534 535 536 537 538 blank

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

701 702 703 704 705 706 707 708 709 710 711 712 713 blank 714 715 716 717 blank 718 719 720 721 722 blank

Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008

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TABLE OF CONTENTS SUBJECT

PAGE

POWER PLANT - ADJUSTMENT/TEST

71-00-00

1.

General

501

2.

Pre-operational Check

501

A.

501

3.

4.

5.

6.

7.

8.

9.

10.

Pre-start Checks

517

A.

517

Procedure

Dry Motoring Run

518

A.

Procedure

518

Wet Motoring Run

519

A.

519

Procedure

Engine Starting

520

A.

520

Procedure

Engine Shutdown

521

A.

521

Procedure

Post-shutdown Checks

521

A.

521

Procedure

Propeller Governor Checks

522

A.

522

Procedure

FCU Checks

523

A.

Adjust FCU Maximum Governing

523

B.

Adjust FCU Minimum Governing

525

C.

Adjust FCU Flight-idle Speed

527

D.

Manual Override System Static Check (PT6A-42A Engines where fitted)

528

Manual Override System Operational Check (PT6A-42A Engines where fitted)

528

E. 11.

Procedure

Oil Pressure Check

529

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TABLE OF CONTENTS SUBJECT

PAGE

POWER PLANT - ADJUSTMENT/TEST (Cont’d) A. 12.

13.

14.

15.

Procedure

71-00-00 529

Torque Limiter Check

531

A.

531

Procedure

Torquemeter Function Test

533

A.

533

Procedure

Engine Performance Check

534

A.

General

534

D.

Procedure

534

Acceleration Check

535

A.

535

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 Wash

702

C.

Wash Schedule

702

D.

Preparation of Solutions

703

E.

Equipment Required

705

Engine Motoring Washes

710

A.

Compressor Desalination Wash

710

B.

Compressor Performance Recovery Wash

712

C.

Compressor Turbine Desalination Wash

716

6.

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TABLE OF CONTENTS SUBJECT

PAGE

POWER PLANT - CLEANING (Cont’d) 7.

8.

71-00-00

Engine External Wash

719

A.

719

General

Fuel Nozzle In-situ Cleaning

720

A.

General

720

B.

Preparation

720

C.

Cleaning

721

D.

Post-cleaning

721

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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 integrity of installed/replaced items. Table 501 defines the specific checks and the order in which they are to be done. Table 502 defines minimum checks to be done before Fault Isolation procedures are done on an engine. Tables 503, 504, 505 and 506 define engine operating limits. Figures 501 and 502 define engine overtemperature limits and corresponding inspection requirements. Figure 503 defines inadvertent engine cut-off and relight during taxi and corresponding inspection requirements. For unscheduled inspection procedure, refer to Chap. 72-00-00, INSPECTION, Unscheduled Inspection. Figure 504 defines engine overtorque limits and corresponding inspection requirements.

2.

Pre-operational Check A.

Procedure (1)

Remove air inlet and exhaust covers (if fitted).

(2)

Open engine cowlings (Ref. Aircraft Maintenance Manual) and examine engine mounts.

(3)

Examine all linkages to engine and to accessories mounted on engine, for attachment.

(4)

Examine all fuel and oil tubes, lines and connections for attachment and leaks. No leaks are permitted except at normal seepage drains.

(5)

Examine all pneumatic line connections and filters for attachment.

WARNING: TURN ELECTRICAL POWER OFF. (6)

Examine all electrical connectors for proper attachment. Check installation of remote mounted ignition exciter.

CAUTION: DO NOT MOVE COCKPIT POWER CONTROL LEVER INTO PROPELLER REVERSE POSITION OR DAMAGE TO LINKAGE WILL RESULT. REVERSE MAY ONLY BE SELECTED WITH ENGINE RUNNING AND PROPELLER TURNING. (7)

Check cockpit controls for freedom of movement and verify full travel of control linkages on engine.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

AREA

A

1. DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE (REF. CHAP. 72−00−00, INSPECTION, UNSCHEDULED INSPECTION) 2. RECORD IN ENGINE LOG BOOK

AREA AREA

810

B C

DO HOT SECTION INSPECTION RETURN ENGINE TO OVERHAUL

AREA

C

INTER TURBINE TEMPERATURE C

800

°

780 AREA

B

760

740

AREA

A

720

NO ACTION REQUIRED 700 0

5

10

15

20

25

30

TIME − SECONDS NOTE: INTERTURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

AREA

A

1. DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE (REF. CHAP. 72−00−00, INSPECTION, UNSCHEDULED INSPECTION) 2. RECORD IN ENGINE LOG BOOK

AREA AREA

B C

DO HOT SECTION INSPECTION RETURN ENGINE TO OVERHAUL

870 AREA

C

AREA

B

AREA

A

INTER TURBINE TEMPERATURE C

850 °

830

810

790

770

750 NO ACTION REQUIRED 0

5

10

15

20

25

30

TIME − SECONDS

NOTE: INTERTURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS

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PRATT & WHITNEY CANADA

INTER TURBINE TEMPERATURE C

MAINTENANCE MANUAL MANUAL PART NO. 3021442

AREA

A

NO ACTION REQUIRED

AREA

B

1. DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE (REF. CHAP. 72−00−00, INSPECTION, UNSCHEDULED INSPECTION) 2. RECORD IN ENGINE LOG BOOK

AREA

C

AREA

D

DO HOT SECTION INSPECTION 1. RETURN ENGINE TO AN APPROVED OVERHAUL FACILITY 2. FOR AIRLINES UTILIZING THE MODULAR PROGRAM A. DO HOT SECTION INSPECTION B. RETURN POWER SECTION TO OVERHAUL C. RETURN FUEL CONTROL UNIT TO OVERHAUL D. INSPECT COMPRESSOR E. INSPECT PNEUMATIC LINE (P3) AND REPLACE P3 AIR FILTER

°

AREA 850

AREA

D

B

AREA

C

800 AREA

0

5

10

A

15

20

25

30

TIME − SECONDS

NOTE: INTER−TURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

AREA

A

NO ACTION REQUIRED.

AREA

B

1. DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE (REF. CHAP. 72−00−00, INSPECTION, UNSCHEDULED INSPECTION) 2. RECORD IN ENGINE LOG BOOK.

C AREA D

AREA

DO HOT SECTION INSPECTION. 1. RETURN ENGINE TO AN APPROVED OVERHAUL FACILITY. 2. FOR OPERATORS UTILIZING THE MODULAR PROGRAM: A. DO HOT SECTION INSPECTION. B. RETURN POWER SECTION TO OVERHAUL FACILITY. C. RETURN FUEL CONTROL UNIT TO OVERHAUL FACILITY. D. INSPECT COMPRESSOR. E. INSPECT PNEUMATIC LINE (P3) AND REPLACE P3 AIR FILTER.

900 890

AREA D

INTER TURBINE TEMP. (DEG. C)

880 870 AREA

B

860 850 AREA

AREA

C

A

800 0

5

10

15

20

25

30

TIME − SECONDS NOTE: INTERTURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A

AREA

1. DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE (REF. CHAP. 72−00−00, INSPECTION, UNSCHEDULED INSPECTION) 2. VISUAL INSPECTION THROUGH EXHAUST DUCT. 3. RECORD IN ENGINE LOG BOOK

AREA B

DO HOT SECTION INSPECTION.

C

AREA

SHIP ENGINE TO OVERHAUL.

1100 1080

INTER−TURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS.

1060 AREA

INTER−TURBINE TEMPERATURE C

1040 °

A

1020 1000 980

AREA

C

960 AREA B

940 920

AREA

A

900 880 NO ACTION REQUIRED 860 0

5

10

15

20

25

30

TIME − SECONDS

PT6A-38 and PT6A-41 Engines

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

AREA

A

1. DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE (REF. CHAP. 72−00−00, INSPECTION, UNSCHEDULED INSPECTION) 2. VISUAL INSPECTION THROUGH EXHAUST DUCT. 3. RECORD IN ENGINE LOG BOOK.

AREA B AREA

DO HOT−SECTION INSPECTION.

C

RETURN ENGINE TO OVERHAUL.

NOTE INTERTURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS.

1100 1080 1060 AREA

A

INTERTURBINE TEMPERATURE C

1040 °

1020

AREA

C

1000 980 960 940

AREA

AREA B

A

920 900 880 860 NO ACTION REQUIRED

840 0

5

10

15

20

25

30

TIME − SECONDS

PT6A-42 and PT6A-42A Engines

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A AREA B AREA

AREA

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.

C

SHIP ENGINE TO OVERHAUL.

1100 1080

INTER−TURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS.

1060

INTER−TURBINE TEMPERATURE C

1040 °

1020 1000 980

AREA

C

960 AREA B

940 920 900 880

AREA

A

860 0

5

10

15

20

25

30

TIME − SECONDS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A AREA B AREA

AREA

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.

C

SHIP ENGINE TO OVERHAUL.

NOTE INTERTURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS.

1100 1080 1060 INTERTURBINE TEMPERATURE C

1040 °

1020

AREA

C

1000 980 960 940 AREA B

AREA

920

A

900 880 860 840 0

5

10

15

20

25

30

TIME − SECONDS

PT6A-42 and -42A Engines

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AREA

A

NO ACTION REQUIRED.

AREA

B

DETERMINE AND CORRECT CAUSE OF OVERTORQUE, (REF. CHAP. 72−00−00, INSPECTION, UNSCHEDULED INSPECTION) RECORD IN ENGINE LOG BOOK.

AREA 3000

C

TORQUEMETER PRESSURE (PSIG)

RETURN ENGINE TO AN APPROVED OVERHAUL FACILITY.

90

2600 OUTPUT TORQUE LB. − FT.

85

AR

EA

C

2200

73 AREA B

64.4 AREA

A

1800 0

1 5 SECS.

2

3

4

5

TIME MINUTES

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AREA

A

NO ACTION REQUIRED.

AREA

B

DETERMINE AND CORRECT CAUSE OF OVERTORQUE, (REF. CHAP. 72−00−00, INSPECTION, UNSCHEDULED INSPECTION) RECORD IN ENGINE LOG BOOK.

AREA

C

RETURN ENGINE TO AN APPROVED OVERHAUL FACILITY. TORQUEMETER PRESSURE (PSIG)

OUTPUT TORQUE LB. − FT.

3000

2750

90

2600

85

ARE

AC

AREA B 2290

75

2230

72.95

AREA

A

2000 0 5 SECS.

1

2

3

4

5

TIME MINUTES

PT6A-41, -42 and -42A Engines

C1890E

Overtorque Limits - All Conditions Figure 504 (Sheet 2) P&WC Proprietary Information. Subject to the restrictions on the title page.

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(8)

Check engine oil level and service as necessary (Ref. 72-00-00, SERVICING). Check locking of filler cap after servicing.

(9)

Close engine cowlings (Ref. Aircraft Maintenance Manual).

(10)

Check fuel system has been serviced with proper fuel (Ref. Service Bulletin SB3044 and SB3244, Listing of Engine Fuel and Additives). TABLE 501, Checks after Component Installation/Replacement

Item Installed/Replaced Engine on Airframe Oil-to-fuel Heater Fuel Pump Fuel Lines Flow Divider and Dump Valve Fuel Manifold/Fuel Nozzles Front and Rear Fuel Drain Valves Fuel Control Unit Compressor Bleed Valve - High Pressure Compressor Bleed Valve - Low Pressure Torque Limiter (if fitted) Reversing Linkage Propeller Governor Oil Pressure System Shaft Oil Seals Scavenge Tube Oil Filter, Housing and Check Valve Oil Pressure Relief Valve

Checks Req’d (Para. No.) 2, 3, 4, 5, 6, 7, 8, 10.B, 10.C, 15, 9, 11, 12, 14, 13 3, 5, 4, 6, 7, 8, 11 5, 4, 6, 7, 8, 14 5, 4, 6, 7, 8 5, 4, 6 5, 4, 6, 14 5, 4, 6, 7 5, 4, 6, 10, 14 14 14 12 14 9, 14 11, 14 4, 5, 6, 7, 8 4, 5, 6, 7, 8 4, 5, 6, 7, 8, 11 6, 11

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 Starting Engine Shutdown

Para. No. 2. 3. 4. 5. 6. 7.

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TABLE 502, Minimum Checks Required before Troubleshooting (Cont’d) Check and Sequence Post-shutdown Check Acceleration Check

Para. No. 8. 15.

TABLE 503, PT6A-38 Engine Operating Limits Operating Conditions (2)

SHP

Torque (1) lb.ft.

Maximum Observed ITT °C

psig

Ng RPM

Np (11) %

RPM

%

Oil Press. psig (7)

Oil Temp. °C

Takeoff Max. Continuous

750

1970 64.4

705

38100

101.5 2000

91

105 to 135

10 to 99

Max. Climb and Max Cruise

750

1970 64.4

685

38100

101.5 2000

91

85 to 135

0 to 99

Min. Idle (3)

660 (8)

20000

60 Min.

-40 to 99

Starting

1000 (4)

0 to 200

-40 Min. (6)

40 to 200

99 to 104 (10)

105 to 135

0 to 99

2750 (4) 89.73

Transient Max. Reverse

700

800 (12)

38500 (5)

52

102.6

2205 (9)

100

705

NOTE: 1. Torque limit applies within range of 1600 to 2000 rpm propeller shaft; below 1600 rpm, torque is limited to 1100 lb.ft. NOTE: 2. Engine inlet condition limits for engine operation are: (a) temperature : to 57.3°C (135°F); (b) altitude: ground level to 35000 ft. (temperature lapse rate of 2°C (3.6°F) per 1000 ft. is assumed). Minimum temperature for starting is -54°C (-65°F). NOTE: 3. The minimum flight idle Ng rotor RPM is established by the airframe manufacturer. NOTE: 4. This value is time-limited to 5 seconds. Refer to Figures 502 and 503. NOTE: 5. This value is time-limited to 10 seconds. NOTE: 6. Limited by oil temperature. NOTE: 7. Normal oil pressure with gas generator speed above 72 % speed. With engine torque below 1970 lb.ft., minimum oil pressure 85 psig at normal oil temperature (60 to 70°C). Under emergency conditions to complete a flight, a lower oil pressure limit of 60 psig is permissible at reduced power level, not exceeding 1100 lb.ft. torque. NOTE: 8. Applies over gas generator speed range 20000 to 22000 rpm. NOTE: 9. May be done in an emergency condition, at all ratings, to complete a flight. NOTE: 10. Time limited to 10 minutes at any operating condition.

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TABLE 503, PT6A-38 Engine Operating Limits (Cont’d) Operating Conditions (2)

SHP

Torque (1) lb.ft.

Maximum Observed ITT °C

psig

Ng RPM

Np (11) %

RPM

Oil Press. psig (7)

Oil Temp. °C

%

NOTE: 11. In flight in the absence of a minimum 40 psig oil pressure, continuous steady state propeller rotation must be prevented by propeller feathering. On the ground, with the engine shut down, continuous propeller rotation must be prevented. NOTE: 12. This value is time limited, refer to Figure 501.

TABLE 504, PT6A-41 Engine Operating Limits Operating Conditions (2)

SHP

Torque (1) lb.ft.

Maximum Observed ITT °C

psig

Ng RPM

Np (11) %

RPM

%

Oil Press. psig (7)

Oil Temp. °C

Takeoff and Max. Continuous

850

2230 72.95

750

38100

101.7 2000

91

105 to 135

10 to 99

Max. Climb/ Max. Cruise

850

2230 72.95

725

38100

101.7 2000

91

105 to 135

0 to 99

Min. Idle (3)

750 (8)

20000

60 min.

-40 to 99

Starting

1000 (4)

0 to 200

-40 min. (6)

40 to 200

99 to 104 (10)

105 to 135

0 to 99

2750 (4) 89.73

Transient Max. Reverse

800

850 (12)

38500 (5)

53.3

102.7

2205 (9)

100

750

NOTE: 1. Torque limit applies within range of 1600 to 2000 rpm propeller shaft; below 1600 rpm, torque is limited to 1100 lb.ft. NOTE: 2. Engine inlet condition limits for engine operation are: (a) temperature : to 57.3°C (135°F); (b) altitude: ground level to 35000 ft. (temperature lapse rate of 2°C (3.6°F) per 1000 ft. is assumed). Minimum temperature for starting is -54°C (-65°F). NOTE: 3. The minimum flight idle Ng rotor RPM must be established by the airframe manufacturer. NOTE: 4. This value is time-limited to 5 seconds. Refer to Figures 502 and 503. NOTE: 5. This value is time-limited to 10 seconds. NOTE: 6. Limited by oil temperature. NOTE: 7. Normal oil pressure with gas generator speed above 72 % speed. With engine torque below 1970 lb.ft., minimum oil pressure 85 psig at normal oil temperature (60 to 70°C). Under emergency conditions to complete a flight, a lower oil pressure limit of 60 psig is permissible at reduced power level, not exceeding 1100 lb.ft. torque.

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TABLE 504, PT6A-41 Engine Operating Limits (Cont’d) Operating Conditions (2)

SHP

Torque (1)

Maximum Observed ITT °C

Ng

Np (11)

Oil Press. psig (7)

Oil Temp. °C

NOTE: 8. Applies over gas generator speed range 20000 to 22000 rpm. NOTE: 9. May be done in an emergency condition, at all ratings, to complete a flight. NOTE: 10. Time limited to 10 minutes at any operating condition. NOTE: 11. In flight in the absence of a minimum 40 psig oil pressure, continuous steady state propeller rotation must be prevented by propeller feathering. On the ground, with the engine shut down, continuous propeller rotation must be prevented. NOTE: 12. This value is time limited, refer to Figure 501.

TABLE 505, PT6A-42 Engine Operating Limits Operating Conditions (2)

SHP

Torque (1) lb.ft.

Maximum Observed ITT °C

psig

Ng RPM

Np (11) %

RPM

%

Oil Press. psig (7)

Oil Temp. °C

Takeoff

850

2230 72.95

800

38100

101.7 2000

91

100 to 135

0 to 99

Max. Continuous Max. Cruise

850

2230 72.95

800

38100

101.7 2000

91

100 to 135

0 to 99

Max. Climb

850

2230 72.95

770

38100

101.7 2000

91

100 to 135

0 to 99

Normal Cruise (PT6A-42)

850

2230 72.95

770

38100

101.7 2000

91

100 to 135

0 to 99

Min. Idle (3)

750 (8)

21000

60 min.

-40 to 99

Starting

1000 (4)

0 to 200

-40 min. (6)

40 to 200

99 to 104 (10)

100 to 135

0 to 99

2750 (4)

Transient Max. Reverse

800

850 (12)

39000 (5)

750

56.0

104.1

2205 (9)

100

NOTE: 1. Torque limit applies within range of 1600 to 2000 rpm propeller shaft; below 1600 rpm, torque is limited to 1100 lb.ft. NOTE: 2. Engine inlet condition limits for engine operation are: (a) temperature : to 57.3°C (135°F); (b) altitude: ground level to 35000 ft. (temperature lapse rate of 2°C (3.6°F) per 1000 ft. is assumed). Minimum temperature for starting is -54°C (-65°F). NOTE: 3. The minimum flight idle Ng rotor RPM must be established by the airframe manufacturer. NOTE: 4. These values are time-limited to 5 seconds. Refer to Figures 501, 502 or 503.

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TABLE 505, PT6A-42 Engine Operating Limits (Cont’d) Operating Conditions (2)

SHP

Torque (1)

Maximum Observed ITT °C

Ng

Np (11)

Oil Press. psig (7)

Oil Temp. °C

NOTE: 5. This value is time-limited to 10 seconds. NOTE: 6. Limited by oil temperature. NOTE: 7. Normal oil pressure with gas generator speed above 72 % speed. With engine torque below 1970 lb.ft., minimum oil pressure 85 psig at normal oil temperature (60 to 70°C). Under emergency conditions to complete a flight, a lower oil pressure limit of 60 psig is permissible at reduced power level, not exceeding 1100 lb.ft. torque. NOTE: 8. Applies over gas generator speed range 21000 to 23000 rpm. NOTE: 9. May be done in an emergency condition, at all ratings, to complete a flight. NOTE: 10. Time limited to 10 minutes at any operating condition. NOTE: 11. In flight in the absence of a minimum 40 psig oil pressure, continuous steady state propeller rotation must be prevented by propeller feathering. On the ground, with the engine shut down, continuous propeller rotation must be prevented. NOTE: 12. This value is time-limited. Refer to Figure 501.

TABLE 506, PT6A-42A Engine Operating Limits Operating Conditions (2)

SHP

Torque (1) lb.ft.

Maximum Observed ITT °C

psig

Ng RPM

Np (11) %

RPM

%

Oil Press. psig (7)

Oil Temp. °C

Takeoff

850

2230 72.95

800

38100

101.7 2000

91

100 to 135

0 to 99

Max. Continuous Max. Cruise

850

2230 72.95

770

38100

101.7 2000

91

100 to 135

0 to 99

Max. Climb

850

2230 72.95

770

38100

101.7 2000

91

100 to 135

0 to 99

Min. Idle (3)

750 (8)

21000

60 min.

-40 to 99

Starting

1000 (4)

0 to 200

-40 min. (6)

40 to 200

99 to 104 (10)

Transient

2750 (4)

880 (4) 850 (12)

39000 (5)

56.0

104.1

2205 (9)

100

NOTE: 1. Torque limit applies within range of 1600 to 2000 rpm propeller shaft; below 1600 rpm, torque is limited to 1100 lb.ft. NOTE: 2. Engine inlet condition limits for engine operation are: (a) temperature : to 57.3°C (135°F); (b) altitude: ground level to 35000 ft. (temperature lapse rate of 2°C (3.6°F) per 1000 ft. is assumed). Minimum temperature for starting is -54°C (-65°F). NOTE: 3. The minimum flight idle Ng rotor RPM must be established by the airframe manufacturer.

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TABLE 506, PT6A-42A Engine Operating Limits (Cont’d) Operating Conditions (2)

SHP

Torque (1)

Maximum Observed ITT °C

Ng

Np (11)

Oil Press. psig (7)

Oil Temp. °C

NOTE: 4. These values are time-limited to 5 seconds. Refer to Figures 501, 502 or 503. NOTE: 5. This value is time-limited to 10 seconds. NOTE: 6. Limited by oil temperature. NOTE: 7. Normal oil pressure with gas generator speed above 72 % speed. With engine torque below 1970 lb.ft., minimum oil pressure 85 psig at normal oil temperature (60 to 70°C). Under emergency conditions to complete a flight, a lower oil pressure limit of 60 psig is permissible at reduced power level, not exceeding 1100 lb.ft. torque. NOTE: 8. Applies over gas generator speed range 21000 to 23000 rpm. NOTE: 9. May be done in an emergency condition, at all ratings, to complete a flight. NOTE: 10. Time limited to 10 minutes at any operating condition. NOTE: 11. In flight in the absence of a minimum 40 psig oil pressure, continuous steady state propeller rotation must be prevented by propeller feathering. On the ground, with the engine shut down, continuous propeller rotation must be prevented. NOTE: 12. This value is time-limited to 20 seconds. Refer to Figure 501.

3.

Pre-start Checks WARNING: PERSONNEL, AIRCRAFT AND EQUIPMENT MUST BE KEPT CLEAR OF ENGINE DANGER ZONE. A.

Procedure NOTE:

Cockpit labels and names of controls may differ according to 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 (where fitted) - Anywhere in forward thrust operating range.

(3)

Fuel Condition Lever - OFF.

(4)

Manual Override Control Lever (where fitted) - OFF.

(5)

Engine Master Switch - ON.

(6)

Fuel System Shutoff Valve - OPEN.

(7)

Fuel Boost Pump Switch - ON.

(8)

Fuel Inlet Pressure - Five psig minimum.

(9)

Bleed Air - OFF.

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4.

Dry Motoring Run WARNING: MAKE SURE THAT PERSONNEL, OTHER AIRCRAFT AND EQUIPMENT ARE CLEAR OF DANGER ZONE NEAR ENGINE. A.

Procedure NOTE:

This procedure is used 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)

Fuel Condition Lever - OFF.

(2)

Ignition Switch - OFF.

(3)

Engine Master Switch - ON.

(4)

Fuel System Shutoff Valve - OPEN.

(5)

Fuel Boost Pump Switch - ON.

(6)

Engine Starter Switch - ON.

WARNING: SHOULD A FIRE PERSIST, AS INDICATED BY SUSTAINED T5, CLOSE FUEL SYSTEM SHUTOFF VALVE AND CONTINUE MOTORING. (7)

Maintain starter operation for the desired duration. Observe starter limits (Ref. Starter Manufacturer’s Manual).

(8)

Engine Starter Switch - OFF.

(9)

Fuel Boost Pump Switch - OFF.

(10)

Fuel System Shutoff Valve - CLOSED

(11)

Engine Master Switch - OFF. NOTE:

Allow required cooling period for starter before any further operation is attempted.

(12)

Check all oil and fuel lines and connections for leaks. No leaks are allowed except at normal seepage drains.

(13)

Check engine oil level and service as necessary (Ref. 72-00-00, SERVICING).

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5.

Wet Motoring Run WARNING: MAKE SURE PERSONNEL, OTHER AIRCRAFT AND EQUIPMENT ARE CLEAR OF DANGER ZONE NEAR ENGINE. CAUTION: THIS PROCEDURE IS USED STRICTLY FOR MAINTENANCE PURPOSES AND IS NOT PART OF NORMAL ENGINE START PROCEDURE. AFTER A WET MOTORING RUN, A DRY MOTORING RUN (REF. PARA. 4.) MUST BE DONE BEFORE AN ENGINE START IS ATTEMPTED. A.

Procedure (1)

Fuel Condition Lever - OFF.

(2)

Manual Override Control Lever (where fitted) - OFF.

(3)

Ignition Switch - OFF.

(4)

Engine Master Switch - ON.

(5)

Fuel System Shutoff Valve - OPEN.

(6)

Fuel Boost Pump Switch - ON.

(7)

Engine Starter Switch - ON. NOTE:

Observe starter motor operating limits.

(8)

After stabilized Ng and positive oil pressure, set Fuel Condition Lever to GROUND-IDLE for 10 seconds.

(9)

Fuel Condition Lever - OFF.

(10)

Engine Starter Switch - OFF.

(11)

During rundown, check that flow divider and dump valve and gas generator case drain valves are functioning.

(12)

Fuel Boost Pump Switch - OFF.

(13)

Fuel System Shutoff Valve - CLOSED.

(14)

Engine Master Switch - OFF.

(15)

Check oil lines, fuel lines and connections for leaks. No leaks are allowed except at normal seepage drains.

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6.

Engine Starting WARNING: MAKE SURE PERSONNEL, OTHER AIRCRAFT AND EQUIPMENT ARE CLEAR OF DANGER ZONE NEAR ENGINE. A.

Procedure (1)

Engine Starter Switch - ON. NOTE:

Minimum Ng to obtain satisfactory light is 12%.

(2)

Engine Oil Pressure - Check for indication.

(3)

Ignition Switch - ON.

CAUTION: WHENEVER THE GAS GENERATOR FAILS TO LIGHT UP WITHIN 10 SECONDS AFTER MOVING FUEL CONDITION LEVER TO GROUND-IDLE POSITION, SHUT OFF FUEL, STARTER AND IGNITION. ALLOW 30 SECOND FUEL DRAINING PERIOD, FOLLOWED BY 15 SECOND DRY MOTORING RUN BEFORE ATTEMPTING ANOTHER START. IF STARTER LIMITS PERMIT, IT IS NOT NECESSARY TO ALLOW RUNDOWN AFTER DRY MOTORING RUN. IF, FOR ANY REASON, A START ATTEMPT IS DISCONTINUED, ALLOW THE ENGINE TO COME TO A COMPLETE STOP AND THEN DO A DRY MOTORING RUN. REPEAT THE COMPLETE START SEQUENCE. OBSERVE STARTER LIMITS. (REF. STARTER MANUFACTURER’S MANUAL.) (4)

As the gas generator speed passes through or has stabilized above the minimum light off speed, move fuel condition lever to GROUND-IDLE position.

(5)

Check that Ng accelerates to ground-idle and that T5 starting limit is not exceeded .

(6)

When engine attains ground-idle: (a) Engine Starter Switch - OFF. (b) Ignition Switch - OFF.

CAUTION:

(7)

ON MULTI-ENGINE AIRCRAFT, TO PREVENT OVER-TEMPERATURE DURING START, MAKE SURE THE FUEL CONDITION LEVER IS ADVANCED TO FLIGHT-IDLE ON THE ENGINE SUPPLYING GENERATOR VOLTAGE.

Before proceeding to ground run, do at least two feathering cycles (if fitted with a Propeller Control Lever) to purge propeller governor and propeller hub. Retain Power Control Lever in GROUND-IDLE position.

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7.

Engine Shutdown A.

Procedure

WARNING: IF THERE IS FIRE WITHIN THE ENGINE AFTER SHUTDOWN, PROCEED IMMEDIATELY AS DESCRIBED UNDER DRY MOTORING RUN (REF. PARA. 4.). (1)

Power Control Lever - GROUND-IDLE. NOTE:

(2)

Propeller Control Lever (where fitted) - FEATHER.

(3)

Fuel Condition Lever - OFF.

(4)

Fuel Boost Pump Switch - OFF.

(5)

Fuel System Shutoff Valve - CLOSED.

(6)

Engine Master Switch - OFF. NOTE:

8.

Allow engine to stabilize for minimum of one minute at minimum obtainable T5.

During shutdown, check that the compressor (Ng) decelerates freely, and note the rundown time.

Post-shutdown Checks A.

Procedure

WARNING: MAKE SURE THAT THE ENGINE IS SHUT DOWN BEFORE ANY ADJUSTMENTS ON ENGINE-MOUNTED EQUIPMENT ARE DONE. THIS IS ESSENTIAL DUE TO THE CLOSE PROXIMITY OF PROPELLER AND EXHAUST NOZZLES. (1)

Check all engine oil lines and connections for leaks. None are allowed, except at normal seepage drains. NOTE:

Allowable oil seepage is 3 cc/hour at each accessory drive pad, and 5 cc/hour at the propeller shaft. All seal leakages shall be included in total oil consumption (Ref. Chapter 72-00-00, ENGINE DESCRIPTION AND OPERATION).

(2)

Check all engine fuel lines and connections for leaks. None are allowed.

(3)

Check engine oil level and service as necessary (Ref. Chapter 72-00-00, SERVICING, Lubricating Oil System).

(4)

Check all engine mounted and off-mounted accessories and linkages for proper mounting.

(5)

Check oil-to-fuel heater installation (Ref. 73-10-01, MAINTENANCE PRACTICES).

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9.

Propeller Governor Checks A.

Procedure

CAUTION: THE FOLLOWING INSTRUCTIONS ARE GIVEN PRIMARILY TO SATISFY SHIPPING REQUIREMENTS AND THE RESULTANT RIGGING MAY DIFFER QUITE CONSIDERABLY FROM WHAT IT SHOULD BE WHEN THE ENGINE IS INSTALLED IN THE AIRFRAME. THE FINAL RIGGING ARRANGEMENT IS PART OF THE AIRCRAFT CERTIFICATION REQUIREMENT AND IS DETAILED IN THE APPROPRIATE AIRCRAFT MAINTENANCE MANUAL. THEREFORE, WHEN AN ENGINE IS REINSTALLED IN AN AIRCRAFT AFTER OVERHAUL OR REPAIR, THE ENGINE SHOULD BE RIGGED IN ACCORDANCE WITH THE RELEVANT AIRCRAFT MAINTENANCE MANUAL AND NOT IN ACCORDANCE WITH THE APPLICABLE P&WC MAINTENANCE OR OVERHAUL MANUAL. NOTE:

Cockpit labels and names of controls may differ according to airframe manufacturer. The terminology used in this and subsequent paragraphs is that of Pratt & Whitney Canada.

CAUTION: CAP AIR PRESSURE TUBE ONLY. (1)

Disconnect and cap governor Py air pressure tube at governor.

(2)

Start engine (Ref. Para. 3. and 6.). Allow engine to warm up (oil temp. 60°C (140°F) min.).

(3)

Advance power control lever to obtain 80% Ng and perform two feathering cycles (where fitted with a Propeller Control Lever) to purge air from system and propeller hub. NOTE:

Time to feather can be reduced by turning adjustment screw (2, Fig. 505) counterclockwise. Two turns from nominal is the maximum permitted.

(4)

Set propeller control lever (where fitted) to full fine pitch position (max. rpm) with propeller governor speed set lever against stop.

(5)

Advance power control lever sufficiently for the propeller to constant speed, and mark position on cockpit quadrant. Note and record Ng.

(6)

Adjust governor maximum speed (1) as necessary to obtain 2000 rpm (max. rpm) propeller speed (Ref. NOTE). Turn screw CW to decrease, CCW to increase Np. NOTE:

Refer to Aircraft Maintenance Manual for maximum Np setting as it might be different.

(7)

Connect Py air pressure tube to governor .

(8)

Reset controls as detailed in step (4).

(9)

Note Ng and compare with value recorded in step (4). Maximum permissible Ng drop is 100 rpm. If exceeded, check linkage (5, Fig. 505) is contacting the maximum stop (3, Fig. 505). Adjust as necessary.

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CAUTION: DO NOT DISTURB ADJUSTMENT (3, Fig. 505).

10.

(10)

Reset controls as detailed in step (4) and (5) and repeat step (9).

(11)

Disconnect linkage from reset arm (5, Fig. 505) and fasten arm to minimum rear position.

(12)

With propeller control lever (where fitted) in fine pitch (max. rpm), advance power control lever sufficiently for propeller to constant speed and record Np. Check Np is 5% ± 1% below speed obtained in Step (6). Adjust pneumatic minimum adjustment (4, Fig. 505), in increments, as required.

FCU Checks CAUTION: THE MAXIMUM GOVERNING SPEED STOP IS PRESET ON ALL FUEL CONTROLS AND THE FOLLOWING PROCEDURE SHOULD NOT BE ACCOMPLISHED UNLESS ABSOLUTELY ESSENTIAL. THIS PROCEDURE WILL ONLY BE POSSIBLE AT RELATIVELY HIGH AMBIENT TEMPERATURES. CAUTION: THE FOLLOWING INSTRUCTIONS ARE GIVEN PRIMARILY TO SATISFY SHIPPING REQUIREMENTS AND THE RESULTANT RIGGING MAY DIFFER QUITE CONSIDERABLY FROM WHAT IT SHOULD BE WHEN THE ENGINE IS INSTALLED IN THE AIRFRAME. THE FINAL RIGGING ARRANGEMENT IS PART OF THE AIRCRAFT CERTIFICATION REQUIREMENT AND IS DETAILED IN THE APPROPRIATE AIRCRAFT MAINTENANCE MANUAL. THEREFORE, WHEN AN ENGINE IS REINSTALLED IN AN AIRCRAFT AFTER OVERHAUL OR REPAIR, THE ENGINE SHOULD BE RIGGED IN ACCORDANCE WITH THE RELEVANT AIRCRAFT MAINTENANCE MANUAL AND NOT IN ACCORDANCE WITH THE APPLICABLE P&WC MAINTENANCE OR OVERHAUL MANUAL. CAUTION: DURING CHECKS AND ADJUSTMENTS IT MAY BE NECESSARY TO EXCEED 97.1% Ng (36400 rpm) TO ACHIEVE MAXIMUM Ng AT ALTITUDE 101.6 % Ng (38100 rpm). CAUTION MUST BE EXERCISED DURING ADJUSTMENT AND NORMAL OPERATION TO ENSURE ENGINE OPERATING LIMITS ARE NOT EXCEEDED. NOTE:

A.

Cockpit labels and names of controls may differ according to airframe manufacturer. The terminology used in this and subsequent paragraphs is that of Pratt & Whitney Canada.

Adjust FCU Maximum Governing (Ref. Fig. 506)

CAUTION: THE MAXIMUM GOVERNING SPEED STOP IS PRESET ON ALL FUEL CONTROLS AND THE FOLLOWING PROCEDURE SHOULD NOT BE ACCOMPLISHED UNLESS ABSOLUTELY ESSENTIAL. THIS PROCEDURE WILL ONLY BE POSSIBLE AT RELATIVELY HIGH AMBIENT TEMPERATURES. (1)

Remove lockwire from attachment screw (7).

(2)

Loosen screw and rotate maximum governing set block (6) to IN-USE position.

(3)

Torque screw (7) 25 to 30 lb.in.

(4)

Start engine (Ref. Paras. 3. and 6.).

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1 2 3

CAUTION THIS SCREW NOT TO BE ADJUSTED

5

4

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Key to Figure 505 1. 2. 3. 4. 5.

Governor Maximum Speed Adjustment Feathering Adjustment Pneumatic Maximum Adjustment (DO NOT DISTURB) Pneumatic Minimum Adjustment Airbleed Link (Reset Arm - Pneumatic Section)

(5)

Gradually increase power control lever setting until maximum governing stop screw (9) contacts block (6). Do not exceed any operating limits.

(6)

Check that Ng equals 97.0%; if not, proceed as follows: (a) Remove lockwire from jam nut (8). (b) Using hexagon head key to prevent stop screw (9) from turning, break torque on jam nut (8). (c) Adjust stop screw (9) in 1⁄8 turn increments, counterclockwise to increase or clockwise to decrease Ng, until Ng equals 97.0%. (d) Torque jam nut (8) 20 to 25 lb.in. (e) Check that 97.0% Ng is maintained, if not, repeat steps (b), (c) and (d).

(7)

Shut down engine (Ref. Para.7.).

(8)

Fasten nut (8) with lockwire.

(9)

Loosen attachment screw (7), rotate maximum governing set block (6) to STOWED position.

(10) B.

With block (6) in stowed position, torque screw (7) 25 to 30 lb.in. and lockwire.

Adjust FCU Minimum Governing (Ref. Fig. 506) NOTE:

Refer to Para. C. for adjustment of idle speed on PT6A-42A Engines.

(1)

Start engine (Ref. Paras. 3. and 6.).

(2)

Set Power Control Lever - GROUND-IDLE.

(3)

Set Fuel Condition Lever - RUN.

(4)

Set propeller governor speed set lever (where fitted) - MAX

CAUTION: INDIVIDUAL AIRFRAME MANUFACTURERS MAY USE NG PERCENTAGES OF DIFFERENT VALUES TO THOSE STATED BELOW. REFER TO AIRFRAME MANUAL. (5)

Ng must be :

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2

3 SEE NOTE

4 1

10

DO NOT ADJUST

11

9 8 7 4 6 VIEW B (STOWED POSITION)

SEE NOTE

5

9 8 7 6 VIEW A (IN−USE POSITION)

DO NOT ADJUST

C922F

PT6A-38/-41/-42/-42A Fuel Control Unit Adjustment Figure 506 P&WC Proprietary Information. Subject to the restrictions on 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 Hi-idle Stop Cut-off and Hi-idle Linkage Nut (Ref. NOTE following step C.(4)) Minimum Governing Adjustment Maximum Governing Set Block Attachment Screw Nut Maximum Governing Stop Screw Minimum Fuel Flow Adjustment Screw Plug

52 % for PT6A-38 and -41 Engines 56 % for PT6A-42 Engines DELETED (6)

Adjust Ng: WARNING: SHUT DOWN ENGINE BEFORE MAKING ANY ADJUSTMENTS ON ENGINE-MOUNTED EQUIPMENT. THIS IS ESSENTIAL DUE TO CLOSE PROXIMITY OF PROPELLER AND EXHAUST NOZZLES. (a) Remove lockwire on minimum governing screw (5). (b) Prevent rotation of screw (5), break torque on jam nut. (c) Turn adjustment screw (5) in increments until Ng equals 52.0 % for PT6A-38/-41 Engines or 56.0 % for PT6A-42 Engines. NOTE:

C.

1/8 turn increments clockwise, equals 1 % Ng augmentation.

(7)

Shut down engine (Ref. Para. 7.).

(8)

Hold adjustment screw (5), torque jam nut 20 to 25 lb.in. Lockwire adjustment screw and jam nut.

Adjust FCU Flight-idle Speed (Ref. Fig. 506) (1)

Start engine (Ref. Paras. 3. and 6.).

(2)

Advance Fuel Condition Lever - FLIGHT-IDLE.

(3)

Make sure cut-off and flight idle linkage (3, Fig. 506) contacts stop (2).

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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. CAUTION: INDIVIDUAL AIRFRAME MANUFACTURERS MAY USE NG PERCENTAGES OF DIFFERENT VALUES TO THOSE STATED BELOW. REFER TO AIRFRAME MANUAL. (4)

Check that Ng is 69 to 71 % for PT6A-38, -41 and -42 Engines 63 to 65 % for PT6A-42A Engines; if not, adjust stop (2) until Ng is within limits.

(5)

If Ng is not within limits, adjust stop (2). NOTE:

D.

It is permissible to adjust nut (4, Fig. 506) for certain installations (Ref. Aircraft Maintenance Manual).

Manual Override System Static Check (PT6A-42A Engines where fitted) (Ref. Fig. 507) NOTE: (1)

Paras. 10.D. and E. apply only to engines incorporating the manual override system.

As part of the periodic inspection (Ref. 72-00-00, INSPECTION), check the static operation of the manual override system, with the engine shutdown: (a) Set cockpit Manual Override Control lever - OFF. (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 max flow stop is not reached (Ref. Fig. 507), check/adjust the airframe rigging (Ref. Aircraft Maintenance Manual). E.

Manual Override System Operational Check (PT6A-42A Engines where fitted) (Ref. Fig. 507) 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 as follows:

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TEMPORARY REVISION NO. 71-20 (PT6A-38, PT6A-41, PT6A-42, PT6A-42A) INSERT Temporary Revision 71-20 facing page 529, Chapter 71-00-00 POWER PLANT - ADJUSTMENT/TEST PURPOSE:

11.

The purpose of this temporary revision is to add a caution for recurrence of low oil pressure after adjustment during previous maintenance in PT6A-42 engines in oil pressure check procedure.

Oil Pressure Check A.

Procedure (1)

Start engine (Ref. Paras. 3. and 6.).

(2)

Run engine at some convenient gas generator speed above 72% Ng to stabilize oil temperature within the operating range.

(3)

After the instrument readings have stabilized, make sure that the oil pressure is within limits as specified .

(4)

If the oil pressure requires adjustment, shut down the engine: (a) Remove oil filter and housing (Ref. 79-20-02). (b) Remove oil pressure relief/regulating valve (Ref. 72-60-00, MAINTENANCE PRACTICES) and add or remove spacers to obtain desired oil pressure. CAUTION:

FOR PT6A-42A ENGINES: IF THE OIL PRESSURE IS ADJUSTED DURING PREVIOUS MAINTENANCE OR TROUBLESHOOTING AND LOW OIL PRESSURE OCCURS AGAIN, REFER 79-20-02, MAINTENANCE PRACTICES.

(c) With Pre-SB3106 valve: use a maximum of five class 41 (0.045 to 0.055) spacers, each affecting oil pressure by approximately 3 to 5 psi. (d) With Post-SB3106/Pre-SB3153 valve: use a maximum of nine spacers. Selections of class 31 (0.020 to 0.030) and/or class 35 (0.035 to 0.040) and/or class 41 ( 0.045 to 0.055) may be used in any combination provided 0.275 inch maximum thickness is not exceeded. (e) With Post-SB3153 valve: use a maximum of nine (0.035 to 0.040) spacers to 0.360 inch maximum thickness. (f)

After applicable adjustments are made, install oil pressure relief/regulating valve.

(g) Install housing and oil filter (Ref. 79-20-02).

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71-00-00

Page 1 of 2 POWER PLANT - ADJUSTMENT/TEST Jan 27/2012

PRINTED IN CANADA

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 71-20

(h) Check engine oil level (Ref. 72-00-00, SERVICING). Replenish if necessary. (i)

Repeat steps if required, until oil pressure range is within applicable engine specified limits .

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(a) Do the Manual Override System static check (Ref. Para. 10.D.). (b) Set Manual Override Control lever - OFF. (c) Start the engine (Ref. Paras. 3. and 6.). (d) 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 (Ref. Step (g)).

(e) Slowly increase Ng until 1350 lb.ft. of torque is obtained. This indicates proper functioning of the Manual Override System. (f)

Slowly reduce the Manual Override Control lever to OFF, keeping Ng decrease less than 4% Ng per second.

(g) Verify the Manual Override Control Lever deadband is 25 degrees at FCU Manual Override Lever before Ng increases (Ref. Fig. 507, Pickup) 11.

Oil Pressure Check A.

Procedure (1)

Start engine (Ref. Paras. 3. and 6.).

(2)

Run engine at some convenient gas generator speed above 72% Ng to stabilize oil temperature within the operating range.

(3)

After the instrument readings have stabilized, make sure that the oil pressure is within limits as specified .

(4)

If the oil pressure requires adjustment, shut down the engine: (a) Remove oil filter and housing (Ref. 79-20-02). (b) Remove oil pressure relief/regulating valve (Ref. 72-60-00) and add or remove spacers to obtain desired oil pressure. (c) With Pre-SB3106 valve: use a maximum of five class 41 (0.045 to 0.055) spacers, each affecting oil pressure by approximately 3 to 5 psi. (d) With Post-SB3106/Pre-SB3153 valve: use a maximum of nine spacers. Selections of class 31 (0.020 to 0.030) and/or class 35 (0.035 to 0.040) and/or class 41 ( 0.045 to 0.055) may be used in any combination provided 0.275 inch maximum thickness is not exceeded. (e) With Post-SB3153 valve: use a maximum of nine (0.035 to 0.040) spacers to 0.360 inch maximum thickness. (f)

After applicable adjustments are made, install oil pressure relief/regulating valve.

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Page 529 Dec 10/2010

NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

89 +− 5

0 NORMAL

+5 30 −

TOTAL TRAVEL AC TRATIVE VEL

PICK UP

MAX. FLOW

15

POSITION OF ACTUATION LEVER RELATIVE TO STOP LEVER

ON INTERNAL STOP

10

MANUAL OVERRIDE LEVER SETTING & ROTATION

C71031A

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(g) Install housing and oil filter (Ref. 79-20-02). (h) Check engine oil level (Ref. 72-00-00, SERVICING). Replenish if necessary. (i) 12.

Repeat steps if required, until oil pressure range is within applicable engine specified limits .

Torque Limiter Check (Ref. Fig. 508) CAUTION:

THE FOLLOWING INSTRUCTIONS ARE GIVEN PRIMARILY TO SATISFY SHIPPING REQUIREMENTS AND THE RESULTANT RIGGING MAY DIFFER QUITE CONSIDERABLY FROM WHAT IT SHOULD BE WHEN THE ENGINE IS INSTALLED IN THE AIRFRAME. THE FINAL RIGGING ARRANGEMENT IS PART OF THE AIRCRAFT CERTIFICATION REQUIREMENT AND IS DETAILED IN THE APPROPRIATE AIRCRAFT MAINTENANCE MANUAL. THEREFORE, WHEN AN ENGINE IS REINSTALLED IN AN AIRCRAFT AFTER OVERHAUL OR REPAIR, THE ENGINE SHOULD BE RIGGED IN ACCORDANCE WITH THE RELEVANT AIRCRAFT MAINTENANCE MANUAL AND NOT IN ACCORDANCE WITH THE APPLICABLE P&WC MAINTENANCE OR OVERHAUL MANUAL.

CAUTION:

DO NOT EXCEED ENGINE OPERATING LIMITS OF SPEED AND TEMPERATURE.

CAUTION:

DO NOT EXCEED TORQUE SETTING OR MAINTAIN MAX TORQUE CONDITION FOR MORE THAN FIVE SECONDS.

NOTE:

A.

Cockpit labels and names of controls may differ according to airframe manufacturer. The terminology used in this and subsequent paragraphs is that of Pratt & Whitney Canada.

Procedure (1)

For PT6A-42A Engines: (a) Advance power control lever to its full max travel. (b) Record torque pressure. Torque pressure should be between 1480 lb.ft. (48.43 psig) and 1500 lb.ft. (49.09 psig).

(2)

For PT6A-38/-41/-42 Engines: (a) With propeller control lever set at Max rpm, advance power control lever to takeoff power. (b) Slowly retard propeller control lever until torque pressure ceases to increase. (c) Record torque pressure. Torque pressure should be between 2370 lb.ft. (77.60 psig) and 2440 lb.ft. (80.05 psig).

(3)

If the torque pressure does not fall within the limits specified in step (1) or (2), shut down engine and adjust torque limiter (Ref. Fig. 508): (a) Slacken locknut on torque limiter adjustment screw.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

ADJUSTMENT SCREW (CLOCKWISE − INCREASE TORQUE) LOCKNUT

TORQUE LIMITER

FWD

Py AIR TUBE

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(b) Use an Allen key to turn adjusting screw clockwise to increase torque and counterclockwise to decrease torque. One half turn of screw changes torque pressure by 76 lb.ft. (2.5 psig). (c) Torque locknut 55 to 60 lb.in. and make sure that adjusting screw position is unchanged. (d) Repeat torque limiter check as in steps (1) or (2) as applicable. 13.

Torquemeter Function Test A.

Procedure (1)

Determine and record pressure altitude. NOTE:

(2)

The pressure altitude (PA) can be obtained by contacting the local flight service for uncorrected pressure reading, or by setting the altimeter to 29.92 in.Hg. The needle position indicates pressure altitude in feet. Do not use sea level pressure.

Determine and record indicated outside air temperature (Tam) in degrees Celsius. NOTE:

To make sure test is accurate, determine and record Tam immediately before engine start.

(3)

Use flight manual chart to determine target torque at which to set engine using PA and Tam recorded at step (1) and (2) respectively. Record values.

(4)

Start engine (Ref. Paras. 3. and 6.) and run for two minutes.

(5)

Place generator, bleed air and air conditioning OFF.

(6)

Check that propeller control lever (where fitted) is in high rpm.

(7)

Check that oil temperature is above 60°C.

(8)

Set Ng 500 rpm above ground-idle (Ref. Engine Operating Limits). Record the Ng, Np, and Tq readings.

(9)

Accelerate engine slowly and uniformly at a rate of 2000 rpm per second until target Tq recorded at step (3) is reached. Let engine stabilize for two minutes.

(10)

Reduce Ng slowly and uniformly at a rate of 2000 rpm per second until Ng set at step (8) is reached. Record the Ng, Np, and Tq readings.

(11)

Repeat steps (8) to (10).

(12)

Shut down engine (Ref. Para. 7.)

(13)

The engine torque indication system functions correctly when the difference between Tq recorded in steps (8), (10), and (11) is equal to or less than 150 lb.ft.

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(14)

14.

If the difference between the torque settings is more than 150 lb.ft., check aircraft indicating system. If the aircraft system is okay, the power section should be removed and sent to an approved overhaul facility and the torquemeter piston, cylinder and servo valve inspected for wear, scoring, fretting, etc.

Engine Performance Check (Ref. Fig. 509) A.

General Engine Performance Checking Chart allows engine performance to be checked on the ground over a wide range of ambient temperatures without engine overtorque or overtemperature. Engine performance checks should be done after aircraft delivery, installation of replacement engine, before and after Hot Section Inspection, and at regular intervals thereafter. Ground running, checking performance and adjusting procedures are described herein. Consult the appropriate Aircraft Maintenance Manual for detailed procedures (Charts or Tables) to do the checks. (1)

The ground performance check charts can vary between the Aircraft Maintenance Manual (AMM) and the Engine Maintenance Manual (EMM). For better consistency in results, always refer to the same chart.

B.

In addition to any in-flight condition monitoring checks that may be done (Ref. Maintenance Practices), periodic ground performance checks should be implemented, and changes in engine performance noted.

C.

All forms of engine deterioration are accompanied by an increase in T5 and Wf at a given power. Compressor deterioration is, in most cases, due to dirt deposits and causes an increase in Ng at a given power setting. This form of deterioration can be remedied by field cleaning (Ref. CLEANING).

D.

Procedure (1)

Determine engine performance parameters: (a) Obtain ambient air temperature (Tam). (b) Obtain field barometric pressure (not corrected to sea level). (c) From relevant engine performance checking chart, obtain T5, Ng , Wf and target torque for ambient conditions. Record values .

(2)

Check engine performance: (a) Do not use P3 air or power extraction for operation of aircraft ancillaries. (b) Start engine (Ref. Paras. 3. and 6.). Run at ground-idle for five minutes to stabilize operating temperatures. (c) Set propeller control lever to 91% Np 2000 rpm and power control lever to target torque setting previously determined from performance checking chart. Allow engine instrumentation to stabilize.

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(d) Record and compare observed T5, Ng and Wf with values previously recorded. (e) Value of T5, Ng and Wf should not deviate from limits on chart. NOTE:

(f)

Maintain record to monitor engine performance. NOTE:

15.

Limits on the chart cover normal engine deterioration, which should not necessarily be cause for engine rejection, until all possible troubleshooting has been completed (Ref. 72-00-00, FAULT ISOLATION).

The preceding check should not be confused with the principles and purpose of Engine Condition Trend Monitoring (Ref. 72-00-00, FAULT ISOLATION).

Acceleration Check A.

Procedure

CAUTION: DO NOT ATTEMPT ACCELERATION CHECKS WITH MANUAL OVERRIDE. (1)

If applicable, manual override control lever - OFF.

(2)

Start the engine (Ref. Paras. 3. and 6.). Operate at ground idle for five minutes to allow stabilization of temperatures.

(3)

Set Ng to FLIGHT-IDLE.

(4)

Advance the power control lever (in less than one second), to maximum setting.

(5)

Note and record time required to reach 93.5 Ng.

(6)

Immediately retard the power control lever to idle setting.

CAUTION:

(7)

IF ACCELERATION CHECK IS DONE AFTER A COMPRESSOR RUNNING WASH, CHECK THE POST-SB3012 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 acceleation adjuster dome (1, Fig. 506) one click at a time until requirement is met. Rotate 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 in either direction, replace fuel control unit (Ref. 73-20-00, Removal/Installation).

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PRATT & WHITNEY CANADA

FIELD BAROMETRIC PRESSURE (IN HG)

31.00 66

29.92

64

29.00

62

28.00

60

27.00

58

26.00

56

25.00

54

540

G)

SSURE (IN H

ETRIC PRE IELD BAROM

F

520 500

52

31.00 29.92 29.00

50

28.00 27.00

480 460 440

26.00 25.00

420

24.00

102

400

100

380

98

INTER−TURBINE TEMPERATURE T15 ( C)

96 94

°

92 800 750

CAUTION: NO INSTALLATION LOSSES, AIRBLEED OR POWER EXTRACTION

90

GAS GENERATOR SPEED − Ng (%)

ENGINE FUEL FLOW − Wf (LB/HR)

24.00

ENGINE TORQUEMETER PRESSURE (PSIG)

MAINTENANCE MANUAL MANUAL PART NO. 3021442

700 650 NOTES: 1. FOR 2000 RPM PROPELLER SPEED 2. FOR STATIC CONDITIONS 3. TORQUE (LB FT) = 30.57 X PSIG

600 550 500 −20

−10

0 10 20 30 40 ENGINE AIR INLET TEMPERATURE ( °C)

50

C931A

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PRATT & WHITNEY CANADA

540

(IN HG) IC PRESSURE

ETR

FIELD BAROM

520 500

2000 1900 1800 1700 1600

31.00

1500

29.92 29.00 28.00 27.00

480

26.00 25.00

460 440

24.00

420 400

2100

31.00 29.92 29.00 28.00 27.00 26.00 25.00 24.00

102

CAUTION: NO INSTALLATION LOSSES, AIRBLEED OR POWER EXTRACTION

100 98 96

INTER−TURBINE TEMPERATURE T5A ( C)

94 °

820

92

800

90

GAS GENERATOR SPEED Mg(%)

ENGINE FUEL FLOW − Wf (LBM/HR)

FIELD BAROMETRIC PRESSURE (IN HG)

ENGINE TORQUE (FT. − LBF)

MAINTENANCE MANUAL MANUAL PART NO. 3021442

780 760 740 720 700 680

NOTE: 1. NO LOSSES 2. STATIC CONDITIONS 3 Np = 2000 RPM

660 640 620

PT6−A42 PERFORMANCE CHECKING CURVE −20

−10

0

10 20 30 ENGINE INLET AIR TEMP

40

50

C9727

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POWER PLANT - CLEANING 1.

General A.

2.

Engine cleaning procedures describes 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

PWC05-053 PWC05-073 PWC06-036 PWC11-001 PWC11-003 PWC11-003B PWC11-014 PWC11-027 PWC11-031 PWC15-011 PWC15-015

Plastic Sheet Demineralized Water Anti-seize Compound Cleaning Agent 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

Tube, Spray Washcart, Compressor

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 Gage Adapter Test Rig Adapter

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

5.

Engine Washing A.

General Depending upon the operating environment and the types of deposits in the engine gas path, the following washes 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, TURBOPROP - INSPECTION).

B.

Types of 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 Turbine Desalination Wash: This wash is used to remove salt deposits from the compressor turbine blades and stator. The wash fluid is drinking quality water, provided minimum standards are met (Ref. Para. E.). Water is injected through a wash tube installed into the gas generator igniter boss. Ref. Para. 6. C. for the complete procedure. NOTE: When desalination washes are done in conjunction with each other it is a must that compressor wash be done first. 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 Depending on the operating environment, the nature and frequency of engine washes are recommended in accordance with Table 701.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 701, Wash Schedule Recommendations Environment

Wash

Frequency

Remarks

Continuously salt laden (See NOTE 2)

Desalination (Compressor and CT) and Engine External Wash

Daily

Strongly recommended after last flight of day.

Occasionally salt laden (See NOTE 2)

Desalination (Compressor and CT) and Engine External 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 for heavy soiling is recommended.

NOTE: 1. Multiple motoring washes should be performed to the extent permitted by starter operating limitations. Observe starter cooling period (Ref. Starter Manufacturer’s Manual). NOTE: 2. Periodic inspection of the compressor inlet case (Ref. 72-00-00) will indicate the effectiveness of the wash schedule on corrosion prevention. If corrosion is found, a more severe wash schedule is necessary. As a guide, a salt laden environment can be assumed to exist in the situation that follows: take-off and landing within 10 nautical miles of the sea or, the flight route is within 10 nautical miles or over the sea and at an altitude of less than 10,000 feet. D.

Preparation of Solutions Five liters (1.33 US gal.) of cleaning solution, and ten liters (2.66 US gal.) of rinse solution is 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 rinse .

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TABLE 702, Cleaning Solution Formulation

Ambient Temperature

Cleaning Agent ( NOTE 1)

Aviation Kerosene (NOTE 2)

Isopropyl Alcohol (PWC11-014)

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 (PWC11-014)

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. 72-00-00). 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. Use Isopropyl Alcohol (PWC11-014). Solution strength must be in accordance with manufacturer/supplier’s recommendation. Where no specific instructions are provided, proportions of agent shall be as indicated in this table. NOTE: 4. Drinking quality water is permissible for motoring wash procedures. For running wash only demineralized water is recommended. TABLE 703, Rinse Solution Formulation Ambient Temperature °C

°F

+2 up

+36 up

−25 to +2 Below −25

Water ( See NOTE)

Isopropyl Alcohol (PWC11-014)

% by vol.

% by vol.

100

-

−12 to +36

50

50

Below −12

40

60

NOTE: Drinking quality water is permitted. Refer to Equipment Required (Ref. Para. E.) for acceptance criteria. E.

Equipment Required (1)

Wash cart (PWC32677-100), or optional locally manufactured wash rig comprising the following (Ref. Fig. 701) : (a) Two stainless steel tanks. (b) Mechanical agitator, or recirculation pump with relief valve, for mixture agitation. (c) Two flow control valves for use with recirculation pump. (d) Two air delivery shut-off valves. (e) Two fluid delivery shut-off valves.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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. 3021442

(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 ID minimum.

CAUTION: DO NOT USE RESTRICTOR WHEN A MOTORING WASH IS DONE. (2)

Spray wash rings and wand . (a) Wash wand (Ref. Fig. 702). Flow rate 2 to 3 gal/minute (7.6 to 11.3 l/minute). (b) Modified wash ring (Ref. Fig. 703). Flow rate 2 to 3 gal/minute (7.6 to 11.3 l/minute).

(3)

Compressed air or nitrogen, regulated to 30 to 50 psig (207 to 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 are as follows: (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)

One pressure gage located in the air delivery line.

(7)

Two air supply valves.

(8)

Two fluid shut-off valves.

(9)

Suitable tubing to interconnect components, valve and tubing connections are to be 5/16 inch (8 mm) ID minimum.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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. 3021442

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 °

50 °

45 °

65 °

75 °

75 ° 8.640" R. (REF.)

85 °

A

90 °

A

110 °

90 °

95 ° 100°

105 °

105°

8.640" R. (REF.)

110°

115 °

130 °

80 °

85 °

95 ° 100 °

70 °

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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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(10) 6.

Two flow control valves, for use with recirculation pump (Ref. Fig. 701).

Engine Motoring Washes A.

Compressor Desalination Wash (1)

Depending on ambient temperature, fill wash tanks with appropriate solution (Ref. Table 703).Alternatively, connect suitable hose to drinking water 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.

(3)

If compressor wash rig is not available, a centrifugal pump may be used to boost drinking water pressure above 30 psig (207 kPa) .

(4)

Remove or open engine cowlings, as applicable, to expose engine inlet screen (Ref. Aircraft Maintenance Manual), and install wash wand or ring .

(5)

Connect wash wand or ring to pressurized tanks or to drinking water supply as applicable. NOTE:

To prevent the precipitation of deposits due to the use of ‘‘hard’’ water, allow engine to cool below 65 °C (150 °F). Minimum duration for cooling is 40 minutes since last operation.

CAUTION: CONTAMINATION/BLOCKAGE OF THE FCU PNEUMATIC SECTION, OR THE P3 FILTER WILL AFFECT ENGINE HANDLING. REMOVE AIR TUBE FROM ENGINE BEFORE MOTORING WASH. CAUTION: FOR PRE-SB3350 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. (6)

For Post-SB3012/Pre-SB3350 Engines: Remove forward P3 air tube from engine to prevent distortion of tube (Ref. 73-10-07). NOTE:

For Post-SB3350 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.

(7)

Switch ignition and aircraft bleed air OFF.

(8)

For Post-SB3270 Engines fitted with an exhaust duct drain: Place container under exhaust duct drain port to collect fluid and remove drain cap assembly (1, Ref. Fig. 704).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CAUTION: DO NOT MOTOR FOR MORE THAN 30 SECONDS; OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). WHEN WATER/ACOHOL SOLUTION IS USED, DO AN ADDITIONAL 30 SECOND DRY MOTORING RUN BETWEEN STEPS (12) AND (13) FOLLOWING, TO PURGE THE ENGINE OF VOLATILE FUMES. MAKE SURE THE PRESCRIBED STARTER COOLING PERIOD IS ALLOWED AFTER THIS ADDITIONAL STEP. (9)

Motor engine (starter only).

(10)

When Ng reaches 5% minimum, inject wash mixture or water into engine, as applicable.

(11)

Stop motoring after 30 seconds.

(12)

Shut off cleaning solution supply as soon as Ng falls to 5%.

(13)

Observe starter cooling period.

(14)

Remove wash wand or ring from inlet screen. Reinstall or close engine cowlings (Ref. Aircraft Maintenance Manual).

CAUTION: DO NOT BEND, TWIST OR FORCE TUBES, WHETHER RIGID OR FLEXIBLE, TO ACHIEVE ALIGNMENT WITH MATING FITTING. ADJUST FITTING TO ALIGN WITH TUBE. CLAMP AND FASTEN TUBE ONLY WHEN IT IS INSTALLED IN POSITION WITH NO NOTICEABLE TENSION OR LOAD. (15)

For Post-SB3012/Pre-SB3350 Engines: Install 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 wihtout the use of tools (fingertight) before torquing. The installation of any pipe brackets should not distort the pipe in any way.

(16)

Check that wash fluid came out of the exhaust duct drain. Remove any obstruction from the drain fitting.

(17)

For Post-SB3012 engines fitted with P3 filter: Check for zero air leakage during engine drying cycle. If satisfactory, lockwire coupling nut at nipple fitting.

(18)

For Post-SB3270 Engines (Ref. Fig. 704): (a) Apply a thin coat of anti-seize compound (PWC06-036) to nipple threads (2). (b) Install new gasket (3) on drain nipple (2) and install in bottom of exhaust duct. Torque nipple 65 to 75 lb.in. (c) Install cap assembly (1) and lockwire.

(19)

Start engine (Ref. ADJUSTMENT/TEST, Engine Starting). Run engine at 80% Ng for one minute or more to completely dry engine, and check for air leaks. Check engine acceleration.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

B.

(20)

Shut down engine (Ref. ADJUSTMENT/TEST, Engine Shutdown)

(21)

Install or close cowlings (Ref. Aircraft Maintenance Manual).

Compressor Performance Recovery Wash (1)

Depending on ambient temperature, fill wash tanks with appropriate cleaning solution (Ref. Table 702) and rinse solution (Ref. Table 703) in separate tanks.

(2)

Connect compressed air supply, 30 to 50 psig (207 to 345 kPa) to wash tanks.

(3)

Remove or open engine cowlings, as applicable, to expose engine inlet screen and install wash wand or ring.

(4)

Connect wash wand or ring, as applicable to pressure tanks. NOTE:

To prevent precipitation of deposits through inadvertent use of ‘‘hard water’’, allow engine to cool below 65°C (150°F). Minimum duration for engine cooling is 40 minutes since last operation.

(5)

Switch ignition and bleed air OFF.

(6)

For Post-SB3270 Engines fitted with an exhaust duct drain: Place container under exhaust duct drain port to collect fluid and remove drain cap assembly (1, Ref. Fig. 704).

CAUTION: CONTAMINATION/BLOCKAGE OF THE FCU PNEUMATIC SECTION, OR THE P3 FILTER WILL AFFECT ENGINE HANDLING. REMOVE AIR TUBE FROM ENGINE BEFORE MOTORING WASH. CAUTION: FOR PRE-SB3350 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. (7)

For Post-SB3012/Pre-SB3350 Engines: Remove forward P3 air tube from engine to prevent distortion of tube (Ref. 73-10-07). NOTE:

For Post-SB3350 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.

CAUTION: DO NOT MOTOR FOR MORE THAN 30 SECONDS; OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). WHEN A WATER/ALCOHOL SOLUTION IS USED, DO AN ADDITIONAL 30 SECOND DRY MOTORING RUN BETWEEN STEPS (14) AND (15) FOLLOWING, TO PURGE THE ENGNE OF VOLATILE FUMES. MAKE SURE PRESCRIBED STARTER COOLING PERIOD IS ALLOWED AFTER THIS ADDITIONAL STEP. (8) (9)

Motor engine (starter only). When Ng reaches 5%, inject cleaning solution into engine.

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THIS PAGE INTENTIONALLY LEFT BLANK

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A

3 2 1 DETAIL

A

C68245

Post-SB3270 Removal/Installation of Exhaust Duct Drain Figure 704 P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 704 1. 2. 3.

Cap Assembly (Post-SB3270) Nipple (Post-SB3270) Gasket (Post-SB3270)

(10)

Stop motoring after 30 seconds.

(11)

Shut off cleaning solution supply as soon as Ng falls to 5%.

(12)

Allow cleaning solution to soak for 15 to 30 minutes.

(13)

Motor engine. When Ng reaches 5%, inject rinse solution into engine (half quantity only).

(14)

Observe starter cooling period (Ref. Starter Manufacturer’s Manual).

(15)

Repeat step (13) observing starter limitations of starter.

(16)

Remove wash wand or ring from inlet screen.

CAUTION: DO NOT BEND, TWIST OR FORCE TUBES, WHETHER RIGID OR FLEXIBLE, TO ACHIEVE ALIGNMENT WITH MATING FITTING. ADJUST FITTING TO ALIGN WITH TUBE. CLAMP AND FASTEN TUBE ONLY WHEN IT IS INSTALLED IN POSITION WITH NO NOTICEABLE TENSION OR LOAD. (17)

For Post-SB3012/Pre-SB3350 Engines: Install 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 wihtout the use of tools (fingertight) before torquing. The installation of any pipe brackets should not distort the pipe in any way.

(18)

Check that wash fluid came out of the exhaust duct drain. Remove any obstruction from the drain fitting.

(19)

For Post-SB3270 Engines (Ref. Fig. 704): (a) Apply a thin coat of anti-seize compound (PWC06-036) to nipple threads (2). (b) Install new gasket (3) on drain nipple (2) and install in bottom of exhaust duct. Torque nipple 65 to 75 lb.in. (c) Install cap assembly (1) and lockwire.

(20)

For Post-SB3012 Engines: Check for zero air leakage during drying cycle. If satisfactory, lockwire coupling nut at nipple fitting.

(21)

Start engine (Ref. ADJUSTMENT/TEST, Engine Starting), and run at 80% Ng for one minute or more to completely dry engine, and check for zero air leaks during drying cycle. Check engine acceleration.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

C.

(22)

Shut down engine (Ref. ADJUSTMENT/TEST, Engine Shutdown).

(23)

Install or close cowlings (Ref. Aircraft Maintenance Manual).

Compressor Turbine Desalination Wash CAUTION: IF A TURBINE WASH IS TO BE DONE IN CONJUNCTION WITH A COMPRESSOR WASH, MAKE SURE THAT THE COMPRESSOR IS WASHED FIRST. (1)

Depending upon the ambient temperature, fill the wash tank with the appropriate mixture (Ref. Table 703). Alternatively, at temperatures above 2°C (36°F) use a suitable hose connected to a drinking water supply.

(2)

Connect compressed air or nitrogen supply, regulated to 30 to 50 psig (207 to 345 kPa) to wash tanks. If compressor wash rig is not available, a centrifugal pump may be used to boost drinking water pressure above 30 psig (207 kPa) .

WARNING: RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. MAKE SURE IGNITION IS SWITCHED OFF. ALWAYS DISCONNECT COUPLING NUTS AT IGNITION EXCITER FIRST. ALWAYS USE INSULATED TOOLS TO REMOVE COUPLING NUTS. DO NOT TOUCH OUTPUT CONNECTORS OR COUPLING NUTS WITH BARE HANDS. (3)

Remove the most accessible igniter (1, Fig. 705) and gasket (2). Discard gasket (Ref. 74-20-00).

(4)

Install spray tube (3) . Make sure that RGB inscribed on tang is pointing towards the reduction gearbox. Tighten fingertight.

(5)

Connect pressurized tank or drinking water supply to spray tube. NOTE:

Engine temperature must be below 65°C (150°F). Inadvertent use of hard water will result in the precipitation of deposits. The minimum cooling off period is 40 minutes since last engine operation.

(6)

Switch aircraft bleed air and ignition OFF.

(7)

For Post-SB3270 Engines fitted with an exhaust duct drain: Place container under exhaust duct drain port to collect fluid and remove drain cap assembly (1, Ref. Fig. 704).

(8)

Make sure propeller is not tethered and is free to turn.

CAUTION: DO NOT MOTOR FOR MORE THAN 30 SECONDS; OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). (9)

Do a dry motoring run.

(10)

When Ng reaches 5%, inject water or isopropyl alcohol as applicable, into engine.

(11)

Stop motoring run after 30 seconds.

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THIS PAGE INTENTIONALLY LEFT BLANK

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

2 1

A

RGB

VIEW

3

A

C41708 Compressor Turbine Wash Tube Installation Figure 705 P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 705 1. 2. 3.

Spark Igniter Gasket Tube Sprayer (PWC32271)

(12)

Shut off water or water/isopropyl alcohol as Ng decreases through 5%.

(13)

If water/alcohol solution is used, observe starter cooling period and then motor engine for 30 seconds.

(14)

Disconnect pressurized tanks or drinking water supply from wash tube and remove tube.

(15)

Install igniter (1) and new gasket (2) (Ref. 74-20-00).

(16)

Install or close engine cowlings as applicable (Ref. Aircraft Maintenance Manual).

(17)

Check that wash fluid came out of the exhaust duct drain. Remove any obstruction from the drain fitting.

(18)

For Post-SB3270 Engines (Ref. Fig. 704): (a) Apply a thin coat of anti-seize compound (PWC06-036) to nipple threads (2). (b) Install new gasket (3) on drain nipple (2) and install in bottom of exhaust duct. Torque nipple 65 to 75 lb.in. (c) Install cap assembly (1) and lockwire.

7.

(19)

Start engine (Ref. ADJUSTMENT/TEST, Engine Starting) and run at 80% Ng for one minute or more to completely dry the engine.

(20)

Shut down engine (Ref. ADJUSTMENT/TEST, Engine Shutdown) .

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.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

For engine operations in corrosive environments it is recommended to perform an external engine wash per the schedule in Table 701. NOTE: Ref. 72-00-00 for corrosion inhibitor application on external components for additional protection when operating in salt laden environments. If water wash is ineffective, a petroleum solvent, (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.

Fuel Nozzle In-situ Cleaning A.

General Cleaning should be initiated on new or recently cleaned nozzles as the procedure will not clear previous blockages. Clean every 200 hours. Adjust interval based on condition and experience. Wash cart (PWC32677-100) is required. Prior to the wash cycle, the cleaning rig must be prepared and operated in accordance with the Cleaning Rig Manual.

B.

Preparation

CAUTION: (PWC11-001G) IS AN ALKALINE THAT CAN CAUSE SKIN IRRITATION. AVOID SKIN CONTACT. (1)

Mixture ratios are: (a) At ambient temperatures above 2° C (35.5° F) mix by volume: 1 part solution (PWC11-001G) to 4 parts demineralized water. (b) At ambient temperatures below 2° C (35.5° F) mix a 50% solution of isopropyl alcohol (PWC11-014) and demineralized water (PWC05-073), then mix 4 parts of water/isopropyl alcohol (by volume) to 1 part Turco 5884.

CAUTION: MAKE SURE THAT AIR HAS BEEN RELEASED FROM RESERVOIRS. (2)

Fill reservoirs with appropriate volume of cleaning solution.

(3)

Fill rinse reservoir with appropriate volume of demineralized water or demineralized water/isopropyl 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 dump or purge valve (Ref. 73-10-04). Cap fuel inlet and elbow on flow divider and dump or purge valve.

(6)

Disconnect dump line or air inlet line from flow divider and dump or purge valve outlet elbow.

(7)

Connect wash cart fluid delivery hose to valve outlet elbow using adapter.

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POWER PLANT - CLEANING

Page 720 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(8)

Connect rig fluid delivery hose to rig ‘‘FUEL NOZZLE’’ quick disconnect.

(9)

Connect compressed air.

CAUTION: DO NOT EXCEED 120 PSIG. (10) C.

Set wash rig to 60 psig using reservoir regulator, and pulse to 70 psig using pulse regulator.

Cleaning (1)

Let engine cool for a minimum of 40 minutes after engine shutdown before cleaning fuel nozzles, and clean following Table 704. TABLE 704, Wash Cart Operating Schedule Valve Position Operation

A

B

C

Agitate detergent solution for two minutes

Agitate

Agitate

OFF

Detergent wash for three minutes

Wash

Wash

ON

Soak for 10 minutes

OFF

OFF

OFF

Detergent wash for three minutes

Wash

Wash

ON

Soak for 10 minutes

OFF

OFF

OFF

Rinse for six minutes

Rinse

Rinse

ON

Air dry for five minutes

OFF

OFF

Air Dry

Reduce both reservoir and pulse pressure to zero

OFF

OFF

OFF

D.

Post-cleaning (1)

Remove compressed air supply from wash rig.

(2)

Remove wash rig fluid delivery hose from flow divider and dump or purge valve elbow.

(3)

Reconnect dump line or air inlet line (Ref. 73-10-04).

(4)

Remove blanking cap at fuel inlet line and elbow on flow divider and dump or purge valve.

(5)

Reconnect fuel inlet line (Ref. 73-10-04).

(6)

Remove drain hoses and reinstall gas generator case drain valves (Ref. 73-10-06).

(7)

Do an engine ground run and check for leaks (Ref. ADJUSTMENT/TEST).

(8)

Clean wash rig, stow fluid delivery hoses, and bleed air pressure from reservoirs.

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 3 4 blank

Dec Dec Dec Dec

Contents

1 2 3 4 5 6

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

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72-00-00 Description and Operation

72-00-00 Fault Isolation

CHAPTER SECTION

10/2010 10/2010 10/2010 10/2010

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DATE Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 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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72-00 LEP

Page 1 Dec 10/2010

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

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DATE

72-00-00 Maintenance Practices

201 202 blank

Sep 24/99 Sep 24/99

72-00-00 Servicing

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401 402 403 404

May 21/2010 May 21/2010 May 21/2010 May 21/2010

72-00-00 Removal/ Installation

CHAPTER SECTION

72-00-00 Inspection Check

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DATE

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Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 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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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

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DATE Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 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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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

72-00-00

1.

Description and Operation

1

2.

Engine Data

8

3.

Transport Canada Approved Service Bulletins

ENGINE, TURBOPROP - FAULT ISOLATION

13 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

136

F.

Engine Lubrication

137

G. Lubricating Oil Contamination

137

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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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

303

E.

Oil System Flushing

304

6.

7.

Preservation and Depreservation

305

A.

General

305

B.

Fuel Control Unit

305

C.

Preservation

305

D.

Depreservation

308

Storage and Shipping

310

A.

Fiberboard Shipping Container

310

B.

Metal Storage and Shipping Container

310

C.

Fiberboard Container Humidity Control

310

D.

Metal Container Humidity and Pressure Control

311

E.

Reactivation of Desiccant and Humidity Indicator

313

F.

Precautions - Removal / Installation of Engine in Metal Container

314

G. Precautions - Removal / Installation of Engine in Fiberboard Container

314

H.

315

Storage of Engine

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

ENGINE, TURBOPROP - SERVICING (Cont’d) I. 8.

9.

10.

Stacking Containers for Storage

72-00-00 315

Removal/Installation of Engine from/in Shipping Container

316

A.

316

Remove Engine from Fiberboard Container

B.

Remove Engine from Metal Container

317

C.

Install Engine in Fiberboard Container

319

D.

Install Engine in Metal Container

326

Removal/Installation of Engine from/in Maintenance Stand

327

A.

Removal

327

B.

Installation

329

Removal/Installation of Power Section/Power Section Module (PS/PSM) in Maintenance Stand

329

A.

Removal

329

B.

Installation

331

ENGINE, TURBOPROP - REMOVAL/INSTALLATION

72-00-00

1.

General

401

2.

Consumable Materials

401

3.

Special Tools

401

4.

Fixtures, Equipment and Supplier Tools

402

5.

Removal/Installation of Engine

402

A.

Removal of Engine from Airframe

402

B.

Installation of Engine in Airframe

402

6.

7.

Removal/Installation of Power Section/Power Section Module (PS/PSM) with Propeller Installed

403

A.

403

Procedure

Removal of Power Section/Power Section Module (PS/PSM) with Propeller Removed

407

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

ENGINE, TURBOPROP - REMOVAL/INSTALLATION (Cont’d) A. 8.

Procedure

72-00-00 407

Installation of Power Section/Power Section Module (PS/PSM)

408

A.

General

408

B.

Procedure

408

ENGINE, TURBOPROP - 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.

604

Corrosion Inhibition Procedure

7.

Control Linkage

605

8.

Periodic Inspection

605

9.

Borescope

613

A.

General

613

B.

Description

613

C.

Removal /Installation of Borescope and Accessories

613

D.

Inspection

617

E.

Fault Isolation

621

10.

In-service Inspection

621

A.

621

Hot Section Components

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

ENGINE, TURBOPROP - INSPECTION (Cont’d) B.

11.

12.

72-00-00

Removal/Installation of Power Section Module (Heavy Maintenance Only)

622

C.

Inspection of Combustion Chamber

623

D.

Inspection of CT Stator Assembly

624

E.

Inspection of CT Blades

627

F.

Inspection of CT Shroud Segments

631

G. Inspection of PT Stator

631

H.

Inspection of PT Blades

631

I.

Inspection of AGB and RGB Gears

631

Inspection of Hot Section Components

632

A.

General

632

B.

Inspection of Gas Generator Module

633

C.

Inspection of Power Section Module

633

D.

Hot Section Inspection (HSI)

635

Unscheduled Inspection

635

A.

General

635

B.

Performance Deterioration

638

C.

Overspeed

638

D.

Inadvertent Cut-off and Relight During Taxi

638

E.

Overtemperature

639

F.

Overtorque

639

G. Immersion in Water

640

H.

Dropped Engine

640

I.

Material Ingestion (e.g., ice, stones, etc)

640

J.

Bird Strike/Soft Material Ingestion (e.g., rags, plastic bags, etc.).

640

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

ENGINE, TURBOPROP - INSPECTION (Cont’d)

72-00-00

K.

Chip Detector Circuit Completion and/or Debris in Oil Filter

640

L.

Propeller Sudden Stoppage or Strike

640

M. Propeller Lightning Strike

642

N.

643

Propeller Electrical Leads Shorting

O. Heavy/Hard Landing

643

P.

644

Aircraft Flown Through Volcanic Ash or Smoke

Q. Sustained Running at Oil Temperature Outside Limits

645

R.

Loss of Oil/Oil Pressure or Low Oil Pressure

645

S.

Oil Pressure Follows Throttle

646

T.

Contamination by Fire Extinguishing Agents

646

U.

Audible Rubbing, Binding or Scraping

647

V.

Propeller Windmilling after In-flight Shutdown

647

W. Contamination of Oil with Non-metallic Foreign Material

648

X.

649

Starter-Generator Replacement

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72-00 CONTENTS

Page 6 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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 Figs. 1 and 2 for the main features of a typical engine, Fig. 3 for cross-sections and Fig. 4 for stations, flanges and bearings. 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. The engines are also equipped with a water wash ring at the compressor air inlet case 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 convert velocity to static pressure. The diffused air then passes through straightening vanes to the annulus surrounding the combustion chamber liner assembly. The annular combustion chamber liner has 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 for ease of starting, and supplied by a dual manifold consisting of primary and secondary transfer tubes and adapters. The fuel/air mixture is ignited by two 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 single-stage 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 section. The two-stage power turbine, consisting of the first-stage inlet guide vane and turbine and the second-stage inlet guide vane and turbine, drives the propeller shaft via a reduction gearbox. 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.

72-00-00 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

Page 1 Jul 26/2002

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

C44B Engine - Three Quarter View, Left Side Figure 1

72-00-00 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

Page 2 Jul 26/2002

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

C45B Engine - Three Quarter View, Right Side (Typical) Figure 2

72-00-00 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

Page 3 Jul 26/2002

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CLASSIFIED FIRST STAGE POWER TURBINE VANE RING FUEL MANIFOLD ADAPTER AND NOZZLE ASSEMBLY T5 WIRING HARNESS EXHAUST DUCT PROPELLER REDUCTION GEAR BOX PROPELLER GOVERNOR MOUNTING PAD PROPELLER SHAFT

MAGNETIC CHIP DETECTOR SECOND STAGE REDUCTION GEARING FIRST STAGE REDUCTION GEARING

POWER TURBINE SHAFT HOUSING

POWER TURBINE SHAFT

POWER TURBINES

FUEL DRAIN FUEL FLOW DIVIDER AND DUMP/PURGE VALVE

C13948_1A Engine Cross-section - Typical Figure 3 (Sheet 1 of 2)

72-00-00 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

Page 4 Jul 26/2002

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

POWER TURBINE INTERSTAGE VANE RING T5 BUS−BAR AND PROBE ASSEMBLY GAS GENERATOR CASE COMPRESSOR BLEED VALVE ASSEMBLY COMBUSTION CHAMBER LINER

DIFFUSER TUBES

COMPRESOR ROTOR ASSEMBLY

INPUT COUPLING OIL TANK ACCESSORY GEAR BOX

ACCESSORY DRIVE GEARSHAFT COMPRESSOR STUB SHAFT

FUEL DRAIN CENTRIFUGAL COMPRESSOR TURBINE IMPELLER VANE RING

AIR INLET SCREEN

COMPRESSOR INLET CASE

COMPREESOR BLEED VALVE ASSEMBLY

SINGLE STAGE COMPRESSOR TURBINE

C13948_2A Engine Cross-section - Typical Figure 3 (Sheet 2)

72-00-00 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

Page 5 Jul 26/2002

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

EXHAUST DUCT EXHAUST OUTLET

6

7

STATIONS

4

BEARINGS

3

PROPELLER SHAFT ROLLER BEARING

PROPELLER SHAFT THRUST BEARING

A

FLANGES

B

REDUCTION GEARBOX TO EXHAUST CASE REDUCTION GEARBOX REAR CASE TO POWER TURBINE HOUSING SUPPORT

C

D

EXHAUST DUCT TO GAS GENERATOR CASE EXHAUST DUCT TO POWER TURBINE VANE HOUSING

C379_1B Engine Bearings, Stations and Flanges - Typical Figure 4 (Sheet 1 of 2)

72-00-00 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

Page 6 Jul 26/2002

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR TURBINE INLET

COMBUSTION CHAMBER INLET COMPRESSOR INLET

INTERTURBINE

AIR INLET

5

3

4

1

2

2

1

ACCESSORY DRIVE ROLLER BEARING (TYPICAL)

G

E

F

SMALL EXIT DUCT TO COMPRESSOR TURBINE SHROUD HOUSING

GAS GENERATOR CASE TO COMPRESSOR INLET CASE

COMPRESSOR INLET CASE (OIL TANK) TO ACCESSORY GEARBOX HOUSING AND DIAPHRAGM

C379_2B Engine Bearings, Stations and Flanges - Typical Figure 4 (Sheet 2)

72-00-00 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

Page 7 Jul 26/2002

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Interturbine temperature (T5) is monitored by an integral bus-bar, probe and harness assembly installed between the compressor and power turbines with the probes projecting into the gas path. A terminal block mounted on the gas generator case provides a connection point to cockpit instrumentation. 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 at the center 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 US gallons and is provided with a dipstick. A chip detector, removeable for draining purposes, is installed at the bottom of the oil tank. 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). 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 comprises a single-acting hydraulic propeller that is controlled by a propeller governor, which combines 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, 2, 3, 4, 5, 6, 7, 8, 9 and 10. For the front and rear accessory drives refer to Fig. 5 and Table 11. For engine fuel and lubrication system specifications and leading particulars refer to Table 12. TABLE 1, PT6A-38 Engine Specifications (Sea Level Static Output - Standard Day) Operating Condition

ESHP

SHP

SFC (lb/eshp/hr)

Jet Thrust (lb.)

Takeoff and Max. Continuous

801

750 (1)

0.629

127

Max. Climb/Max. Cruise (3)

801

750 (2)

0.629

127

NOTE: 1. Available to 38.9 °C (102 °F) Ambient @ 2000 rpm Np NOTE: 2. Available to 27.2 °C (81°F) Ambient @ 2000 rpm Np NOTE: 3. For information only; these ratings are not Transport Canada approved.

72-00-00 ENGINE, TURBOPROP - DESCRIPTION AND OPERATION

Page 8 Jul 26/2002

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 2, PT6A-38 Engine Leading particulars Engine type Type of combustion chamber Compression ratio Propeller shaft rotation Propeller shaft coupling Propeller shaft gear ratio Engine dia. Engine length Dry weight Oil consumption (10 hour period)

Free Turbine Annular 9.0:1 Clockwise Flanged 0.0663:1 19.0 in. (483 mm) 66.9 in (1700 mm) 380 lb (172 kg) 0.2 lb/hr. (0.0907 kg/hr)

TABLE 3, PT6A-40 Engine Specifications (Sea Level Static Output - Standard Day) Operating Condition

ESHP

SHP

SFC (lb/eshp/hr)

Jet Thrust (lb.)

Takeoff (5 min.) Max. Continuous

749

700 (1)

0.646

122

Max. Climb/Normal Cruise (3)

749

700 (2)

0.646

122

Max. Cruise

749

700 (2)

0.646

122

NOTE: 1. Available to 57.2 °C (135 °F) Ambient @ 2000 rpm Np NOTE: 2. Available to 55.6 °C (132 °F) Ambient @ 2000 rpm Np NOTE: 3. For information only; these ratings are not Transport Canada approved.

TABLE 4, PT6A-40 Engine Leading particulars Engine type Type of combustion chamber Compression ratio Propeller shaft rotation Propeller shaft coupling Propeller shaft gear ratio Engine dia. Engine length

Free Turbine Annular 9.0:1 Clockwise Flanged 0.0663:1 19.0 in. (483 mm) 66.9 in (1700 mm)

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TABLE 4, PT6A-40 Engine (Cont’d) Leading particulars Dry weight Oil consumption (10 hour period)

404 lb (183.3 kg) 0.2 lb/hr. (0.0907 kg/hr)

TABLE 5, PT6A-41 Engine Specifications (Sea Level Static Output - Standard Day) Operating Condition

ESHP

SHP

SFC (lb/eshp/hr)

Jet Thrust (lb.)

Takeoff (5 min.) Max. Continuous

903

850 (1)

0.591

132

Max. Climb/Max. Cruise (3)

903

850 (2)

0.591

132

NOTE: 1. Available to 41 °C (106 °F) Ambient @ 2000 rpm Np NOTE: 2. Available to 29 °C (84 °F) Ambient @ 2000 rpm Np NOTE: 3. For information only; these ratings are not Transport Canada approved.

TABLE 6, PT6A-41 Engine Leading particulars Engine type Type of combustion chamber Compression ratio Propeller shaft rotation Propeller shaft coupling Propeller shaft gear ratio Engine dia. Engine length Dry weight Oil consumption (10 hour period)

Free Turbine Annular 9.0:1 Clockwise Flanged 0.0663:1 19.0 in. (483 mm) 66.9 in. (1700 mm) 403 lb (182.8 kg) 0.2 lb/hr. (0.0907 kg/hr)

TABLE 7, PT6A-42 Engine Specifications (Sea Level Static Output - Standard Day) Operating Condition Takeoff (5 min.) Max. Continuous

ESHP

SHP

SFC (lb/eshp/hr)

Jet Thrust (lb.)

904

850 (1)

0.601

137

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TABLE 7, PT6A-42 Engine Specifications (Sea Level Static Output - Standard Day) (Cont’d) Operating Condition Max. Climb/Max. Cruise (3)

ESHP

SHP

SFC (lb/eshp/hr)

Jet Thrust (lb.)

904

850 (2)

0.601

137

NOTE: 1. Available to 41 °C (106 °F) Ambient @ 2000 rpm Np NOTE: 2. Available to 30 °C (86 °F) Ambient @ 2000 rpm Np NOTE: 3. For information only; these ratings are not Transport Canada approved.

TABLE 8, PT6A-42 Engine Leading particulars Engine type Free Turbine Type of combustion chamber Annular Compression ratio 9.0:1 Propeller shaft rotation Clockwise Propeller shaft coupling Flanged Propeller shaft gear ratio 0.0663:1 Engine dia. 19.0 in. approx. at room temp. Engine length 66.9 in. approx. at room temp. Dry weight 434 lb. incl. optional equip. Oil consumption 0.2 lb/hr. max. in 10 hr. period

TABLE 9, PT6A-42A Engine Specifications (Sea Level Static Output - Standard Day) Operating Condition

ESHP

SHP

SFC (lb/eshp/hr)

Jet Thrust (lb.)

Takeoff (5 min.)

904

850 (1)

0.601

137

Max. Continuous Max. Climb/Max. Cruise (3)

904

850 (2)

0.601

137

NOTE: 1. Available to 41 °C (106 °F) Ambient @ 2000 rpm Np NOTE: 2. Available to 30 °C (86 °F) Ambient @ 2000 rpm Np NOTE: 3. For information only; these ratings are not Transport Canada approved.

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TABLE 10, PT6A-42A Engine Leading particulars Engine type Free Turbine Type of combustion chamber Annular Compression ratio 9.0:1 Propeller shaft rotation Clockwise Propeller shaft coupling Flanged Propeller shaft gear ratio 0.0663:1 Engine dia. 19.0 in. approx. at room temp. Engine length 67.9 in. approx. at room temp. Dry weight 434 lb. incl. optional equip. Oil consumption 0.2 lb/hr. max. in 10 hr. period

TABLE 11, Front and Rear Accessory Drives Max. Torque (in.lb.) Drive Pad

Rotation

Ratio

Continuous

Static

1

Starter-generator (NOTE: 1.)

CW

0.2931:1

170

1600

2

Fuel Pump/FCU (NOTE: 1.)

CCW

0.1670:1

-

-

3

Ng Tach Generator (NOTE: 1.)

CCW

0.1121:1

7

100

4

Optional Accessory Drive (Vacuum Air Pump) (NOTE: 1.)

CCW

0.1019:1

60

800

5

Optional Accessory Drive (NOTE: 1.)

CW

0.3208:1

135

800

6

Optional Accessory Drive (Hydraulic Pump) (NOTE: 1.)

CCW

0.2041:1

150

800

7

Propeller Governor (NOTE: 2.)

CW

0.1264:1

50

850

8

Nf Tach Generator (NOTE: 2.)

CW

0.1264:1

7

100

9

Propeller Overspeed Governor (NOTE: 2.)

CW

0.1264:1

50

850

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TABLE 11, Front and Rear Accessory Drives (Cont’d) Max. Torque (in.lb.) Drive Pad

Rotation

Ratio

Continuous

Static

NOTE: 1. Rear Accessory Drives, 100% is 37500 rpm Ng. NOTE: 2. Front Accessory Drives, 100% is 33000 rpm Nf.

TABLE 12, Fuel and Lubrication System Specifications Nomenclature Fuel Oil Oil Tank - Total Capacity Oil Tank - Expansion Space Oil Tank - Usable Quantity

3.

Specification Refer to Approved Service Bulletins Refer to Approved Service Bulletins 2.3 US gallons (1.92 Imp. gallons, 8.74 liters) 0.7 US gallons (0.58 Imp. gallons, 2.26 liters) 1.5 US gallons (1.25 Imp. gallons, 5.68 liters)

Transport Canada Approved Service Bulletins The following Service Bulletins contain data recommended by Pratt & Whitney Canada and approved by the Canadian Minister of Transport. Service Bulletin SB3001, Listing of Synthetic Oils. Service Bulletin SB3002, Rotor Components Service Life Limits. Service Bulletins SB3003, Operating Time Between Overhauls and Hot Section Inspection frequency. Service Bulletin SB3044 and SB3244, Listing of Engine Fuel and Additives.

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1 2

6 5 4

3

AS VIEWED FROM REAR

7

8 9

AS VIEWED FROM FRONT

C7819B Engine Accessory Drives Figure 5

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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 engines 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 characteristics of repeatedly producing its output at, or very close to, charted gas geneator parameter values provides the basis for the engine trend monitoring system. Thus, under known conditions of pressure altitude (PA) and indicated

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outside air temperature (IOAT), the gas generator parameter values of interturbine temperature (Tt5), gas generator speed (Ng), and fuel flow (Wf), for particular propeller speed (Np) and torques (T) 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. Abrupt changes, or gradual increased rate of change, of the normal deviations from charted parameter values are critical indicators of gas path component conditions. As such, changes are detectable before any drastic failure occurs. The monitoring system should 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 appropriate P&WC Publication SIL No. GEN-055. 6.

Fault Isolation A.

Categories To enable systematic fault isolation, engine faults are categorized. Each category consists of common related engine problems with appropriate diagnostic tests and rectification sequences. The categories of engine fault, and probable causes are detailed: (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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STARTING PROBLEMS

NO INDICATION OF RPM (SHEET 2)

INSUFFICIENT RPM (LESS THAN 12% Ng) (SHEET 3)

FAILURE TO LIGHT (SHEET 5)

WHITE SMOKE FROM EXHAUST (SHEET 7)

FLAMES FROM EXHAUST (SHEET 8)

DELAYED LIGHT−UP (SHEET 9)

HUNG START (SHEET 10)

STEP CHANGE IN ITT (SHEET 11)

EXCESSIVE RPM (GREATER THAN 25% Ng) (SHEET 4)

NOTE: ITT SPLIT (TWIN ENGINE INSTALLATION) ITTS SHOULD BE CONSIDERED ON AN INDIVIDUAL ENGINE BASIS ONLY. START ITT DOES NOT DETERMINE ENGINE SUPERIORITY. FOR SIGNIFICANT ITT CHANGE, REFER TO SHEET 11.

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STARTING PROBLEMS NO INDICATION OF ENGINE RPM IS STARTER − GENERATOR / ENGINE OPERATION AUDIBLE

YES

NO DOES ENGINE ROTATE WITH STARTER − GENERATOR OPERATION

CHECK ELECTRICAL POWER SUPPLIES AND STARTER − GENERATOR ELECTRICAL CONNECTIONS

NO

REMOVE STARTER − GENERATOR, CHECK FOR SHEARED DRIVE SHAFT AND GEARSHAFT SPLINE DAMAGE

YES

ARE ELECTRICAL POWER SUPPLIES O.K.

YES

IS STARTER − GENERATOR DRIVE SHAFT SHEARED

RECTIFY FAULT ON Ng INDICATING SYSTEM

YES

NO

RECTIFY POWER SUPPLY FAULT

NO

RETURN ENGINE TO APPROVED OVERHAUL FACILITY

REPLACE STARTER−GENERATOR (REF. AIRCRAFT MAINTENANCE MANUAL)

REPLACE STARTER − GENERATOR AND/OR DRIVESHAFT (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)

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STARTING PROBLEMS INSUFFICIENT RPM BEFORE INTRODUCTION OF FUEL (LESS THAN 12% Ng)

CHECK ELECTRICAL POWER SUPPLIES AND STARTER − GENERATOR ELECTRICAL CONNECTIONS

ARE ELECTRICAL POWER SUPPLIES O.K.

IS TURBINE TIP CLEARANCE CORRECT

YES

NO

YES

RECTIFY POWER SUPPLY FAULT

REMOVE COMPRESSOR TURBINE AND GRIND SEGMENTS (REF. 72−50−01)

DOES COMPRESSOR ROTATE FREELY WITH NO SOUND OF BLADE RUBBING YES RECTIFY FAULT ON Ng INDICATING SYSTEM

NO

NO REMOVE POWER SECTION (REF. 72−00−00) AND CHECK COMPRESSOR TURBINE TIP CLEARANCE (REF. 72−50−02)

RETURN ENGINE TO APPROVED OVERHAUL FACILITY

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STARTING PROBLEMS EXCESSIVE RPM BEFORE INTRODUCTION OF FUEL (GREATER THAN 25% Ng)

CHECK ACCESSORY GEARBOX INPUT SHAFT COUPLING FOR PROPER ENGAGEMENT. (REF. 72−60−00)

NOT OK OK RETURN ENGINE TO APPROVED OVERHAUL FACILITY RECTIFY FAULT ON Ng INDICATING SYSTEM

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STARTING PROBLEMS ENGINE FAILS TO LIGHT (SEE NOTE)

HAS THE CORRECT ENGINE STARTING PROCEDURE BEEN CARRIED OUT (REF. 71−00−00)

NO

SHUT OFF FUEL, STARTER AND IGNITION. ALLOW 30 SECOND FUEL DRAINING PERIOD FOLLOWED BY A DRY MOTORING RUN. (REF. 71−00−00)

REPEAT COMPLETE ENGINE START SEQUENCE (REF. 71−00−00)

YES

*

CARRY OUT DRY MOTORING RUN (REF. 71−00−00)

*

CHECK IGNITION SYSTEM IS FUNCTIONALLY OPERATIONAL (REF. 74−00−00)

CHECK POWER SUPPLIES TO IGNITION EXCITER, CARRY OUT ELECTRICAL INSULATION AND CONTINUITY CHECKS ON IGNITION CABLES. VISUALLY CHECK CABLES AND IGNITERS.

NOT OK

* YES

NO FAULTS FOUND ON CABLES. REPLACE IGNITION EXCITER (REF. 74−10−00)

CONT’D ON SHEET 6 *CAUTION: 1. RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. ENSURE IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE DISCONNECTING. 2. OBSERVE STARTER MOTOR LIMITS. REFER TO STARTER MANUFACTURER’S MANUAL. NOTE:

WHEN AN ENGINE FAILS TO LIGHT, IT IS USUALLY DUE TO: 1. NO FUEL TO THE NOZZLES 2. NO SPARK AT THE IGNITERS. 3. INCORRECT AIR/FUEL RATIO.

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STARTING PROBLEMS CONT’D FROM SHEET 5

YES IS FUEL AVAILABLE AT FLOW DIVIDER INLET

CHECK FLOW DIVIDER (REF. 73−10−04) AND FUEL NOZZLES (REF. 73−10−05)

NO NO

IS FUEL AVAILABLE AT FCU INLET

NOT OK

OK

YES IS FUEL AVAILABLE AT FUEL PUMP INLET NO YES

REPLACE FCU (REF. 73−20−11) REPLACE AS NECESSARY

REPLACE FUEL PUMP (REF. 73−10−02)

ENSURE FUEL IS FREE OF ICE, WATER AND CONTAMINATION. RECTIFY AS NECESSARY.

IF FUEL IS FREE OF ICE, WATER AND CONTAMINATION, REFER TO THE AIRCRAFT MAINTENANCE MANUAL.

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STARTING PROBLEMS WHITE SMOKE FROM EXHAUST (SEE NOTE)

DOES THE ENGINE LIGHT

* NO

DO DRY MOTORING RUN (REF. 71−00−00)

IS THE Ng RPM AT FUEL INTRODUCTION GREATER THAN 16%

YES

NO *

CHECK FLOW DIVIDER AND DUMP OR PURGE VALVE OPERATION, RECTIFY AS NECESSARY. (REF. 73−10−04)

CHECK IGNITION SYSTEM IS FUNCTIONALLY OPERATIONAL (REF. 74−00−00)

YES

OK

TRY FUEL INTRODUCTION AS THE GG ACCELERATES THROUGH 16%

NOT OK 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

*

NO FAULTS FOUND ON CABLES. REPLACE IGNITION EXCITER (REF. 74−10−00)

CHECK FUEL NOZZLES AND FLOW DIVIDER (REF. 73−10−05) NOT OK

OK

RETURN ENGINE TO APPROVED OVERHAUL FACILITY

REPLACE AS NECESSARY

*CAUTION:

1. RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. ENSURE IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE DISCONNECTING. 2. OBSERVE STARTER MOTOR LIMITS. REFER TO STARTER MANUFACTURER’S MANUAL. NOTE: 1. WHITE SMOKE IS AN INDICATION THAT FUEL IS IN THE ENGINE AND IS BEING VAPORIZED. 2. SMOKY STARTS MAY BE ALLEVIATED BY REPLACEMENT OF FLOW DIVIDER AND PURGE VALVE (REF. 73−10−04)

C35289A Engine Starting Fault Isolation Chart Figure 101 (Sheet 7) P&WC Proprietary Information. Subject to the restrictions on the title page.

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STARTING PROBLEMS FLAMES FROM EXHAUST (SEE NOTE)

*

REPLACE AS NECESSARY

NOT OK

CARRY OUT DRY MOTORING RUN (REF. 71−00−00)

CHECK FLOW DIVIDER (REF. 73−10−04) AND FUEL NOZZLES (REF. 73−10−05)

OK

CHECK DUMP OR PURGE VALVE OPERATION. RECTIFY OR REPLACE AS NECESSARY. (REF. 73−10−04)

* CAUTION: OBSERVE STARTER MOTOR LIMITS. REFER TO STARTER MANUFACTURER’S MANUAL. NOTE: FLAMES IN THE EXHAUST STUBS ARE OFTEN AN INDICATION THAT FUEL HAS COLLECTED IN THE BOTTOM OF THE ENGINE FROM THE PREVIOUS SHUTDOWN OR ATTEMPTED START.

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STARTING PROBLEMS DELAYED LIGHT UP, MORE THAN 5 SECS.

NO

CHECK FLOW DIVIDER AND DUMP OR PURGE VALVE OPERATION. RECTIFY OR REPLACE AS NECESSARY (REF. 73−10−04)

HAS THE CORRECT ENGINE STARTING PROCEDURE BEEN CARRIED OUT (REF. 71−00−00) YES

* SHUT OFF FUEL, STARTER AND IGNITION. ALLOW 30 SECOND FUEL DRAINING PERIOD FOLLOWED BY A DRY MOTORING RUN. (REF. 71−00−00)

*

REPEAT COMPLETE ENGINE START SEQUENCE (REF. 71−00−00)

CHECK IGNITION SYSTEM IS FUNCTIONALLY OPERATIONAL (REF. 74−00−00)

OK

NOT OK 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

*

NO FAULTS FOUND ON CABLES. REPLACE IGNITION EXCITER (REF. 74−10−00)

CHECK POSITION OF FUEL MANIFOLD ADAPTERS. ENSURE PRIMARY NOZZLES ARE POSITIONED AS DETAILED IN 73−10−05

CHECK FUEL NOZZLES FOR RESTRICTIONS. FUNCTION CHECK NOZZLES (REF. 73−10−05)

*CAUTION: 1. RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. ENSURE IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE DISCONNECTING. 2. OBSERVE STARTER MOTOR LIMITS. REFER TO STARTER MANUFACTURER’S MANUAL.

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STARTING PROBLEMS HUNG START, I.E. ENGINE DOES NOT, OR IS SLOW TO ACCELERATE TO IDLE SPEED (Ng)

CHECK FOR LEAKS ON PROP GOVERNOR PNEUMATIC LINE. RECTIFY AS NECESSARY. (REF. 73−10−08)

CHECK FOR POSSIBLE LEAKS OR RESTRICTIONS ON FCU PNEUMATIC SYSTEM. RECTIFY AS NECESSARY (REF. 73−10−07)

CHECK FUEL PUMP FILTERS FOR BLOCKAGE. RECTIFY AS NECESSARY.

REPLACE FCU (REF. 73−20−00)

NOT OK

CHECK FCU FOR CONTAMINATION OR CORROSION. (REF. 73−20−00)

OK

CHECK FLOW DIVIDER AND DUMP OR PURGE VALVE OPERATION. RECTIFY AS NECESSARY. (REF. 73−10−04)

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STARTING PROBLEMS STEP CHANGE IN STARTING ITT (SEE NOTE)

STEP INCREASE

NO

CHECK AND CORRECT ITT INDICATING SYSTEM

YES

SEE 71−00−00 FIG. 502 FOR CORRECTIVE ACTION

YES IS START ITT > 1000 DEG. C NO IS THE INCREASE IN START ITT ACCOMPANIED BY A SIMILAR INCREASE IN ITT AT CRUISE SHP

NO CONT’D ON SHEET 12

YES CHECK THE ENGINE ITT INDICATING SYSTEM

NOT OK RECTIFY AS NECESSARY

OK CHECK THE AIRCRAFT ITT INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

OK

DEPENDING ON THE RESULT OF THE BORESCOPE INSPECTION, EITHER PERFORM AN HSI (REF. 72−00−00) OR RETURN THE ENGINE TO AN APPROVED FACILITY FOR REPAIR

PERFORM A BORESCOPE INSPECTION OF THE HOT SECTION AND COMPRESSOR SECTION. (REF. 72−00−00)

NOT OK RECTIFY AS NECESSARY

NOTE: THE ITT ON STARTING IS AN INDICATION OF THE TRANSIENT GAS TEMPERATURE AND IS NOT NECESSARILY REPRESENTATIVE OF ANY ENGINE COMPONENT TEMPERATURE.

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STARTING PROBLEMS CONT’D FROM SHEET 11 NO HAS THE CORRECT ENGINE STARTING PROCEDURE BEEN CARRIED OUT (REF. 71−00−00) YES SHUT OFF FUEL, STARTER AND IGNITION. ALLOW 30 SECOND FUEL DRAINING PERIOD FOLLOWED BY A DRY MOTORING RUN. (REF. 71−00−00)

CHECK FOR LOW POWER SUPPLIES AND POOR CONNECTIONS ON POWER INPUT LINES AND STARTER − GENERATOR CONNECTIONS

OK

NOT OK

*

RECTIFY POWER SUPPLY OR CABLE FAULT

*

REPEAT COMPLETE ENGINE START SEQUENCE (REF. 71−00−00)

CHECK IGNITION SYSTEM IS FUNCTIONALLY OPERATIONAL (REF. 74−00−00)

CONT’D ON SHEET 13

* CAUTION: 1. RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. ENSURE IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE DISCONNECTING. 2. OBSERVE STARTER MOTOR LIMITS. REFER TO STARTER MANUFACTURER’S MANUAL.

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STARTING PROBLEMS CONT’D FROM SHEET 12

YES

NO

IGNITION SYSTEM FOUND O.K.

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.

CHECK P3 BLEED AIR SYSTEM FOR LEAKS. ENSURE ALL APPROPRIATE AIRCRAFT SERVICES ARE SELECTED OFF. RECTIFY AS NECESSARY.

CHECK ENGINE CONTROL LINKAGE RIGGING MIN FLOW & ACCELERATION CHECK (REF. 76−00−00)

NOT OK

NO FAULTS FOUND ON CABLES. REPLACE IGNITER EXCITER (REF. 74−10−00)

*

OK CHECK FLOW DIVIDER AND DUMP OR PURGE VALVE OPERATION, RECTIFY OR REPLACE AS NECESSARY (REF. 73−10−04)

CARRY OUT CONTROL LINKAGE RIGGING ADJUSTMENTS (REF. 76−10−00)

CHECK POSITION OF FUEL MANIFOLD ADAPTERS. ENSURE PRIMARY NOZZLES ARE POSITIONED AS DETAILED IN 73−10−05

CHECK FUEL NOZZLES FOR RESTRICTIONS. FUNCTION CHECK NOZZLES (REF. 73−10−05)

CAUTION: RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. ENSURE IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE DISCONNECTING.

C35295A Engine Starting Fault Isolation Chart Figure 101 (Sheet 13) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Cont’d on Sheet 2 HOOTING OR HUMMING SOUND

FORWARD

CHECK OPERATION OF COMPRESSOR BLEED VALVE

BLEED VALVE O.K.

INCORRECT RPM (Np) HIGH − LOW

PROPELLER SLOW TO FEATHER AND UNFEATHER

CHECK PROPELLER GOVERNOR CONTROL SETTINGS. ADJUST AS NECESSARY

NO

REVERSE

CHECK SPEED SELECT LEVER WILL CONTACT MAX STOP

CHECK GOVERNOR RESET ARM RIGGING (REF. AIRCRAFT MAINTENTANCE MANUAL)

ADJUST MAX RPM STOP ON PROPELLER GOVERNOR

ADJUST Nf RESET SPEED ADJUSTMENT ON PROPELLER GOVERNOR

YES REPLACE VALVE

NO ACTION NECESSARY IF CONDITION OCCURS BELOW 60% Ng AND INTERMITTENTLY, SUCH AS DURING ACCELERATION TO IDLE OR DURING A CHANGE OF SPEED. IF CONDITION PERSISTS, OR OCCURS ABOVE 60% Ng, DISASSEMBLE AND CHECK C/T DISK FOR BLADE SHIFT. REPAIR AS NECESSARY. IF NO BLADE SHIFT, REBALANCE OR REPLACE C/T DISK. IF CONDITION PERSISTS AFTER REPLACEMENT OF DISK, SHIP ENGINE TO AN OVERHAUL FACILITY.

REPLACE PROPELLER GOVERNOR HAVE NECESSARY GOVERNOR ADJUSTMENTS BEEN MADE

NO

YES IF FAULT IS STILL APPARENT, POSSIBLE LEAK DUE TO WORN OR DAMAGED PREFORMED PACKING AT PROPELLER SHAFT OR OIL TRANSFER TUBE

IF GOVERNOR ADJUSTMENTS ARE INEFFECTIVE REPLACE GOVERNOR

SHIP ENGINE OR POWER SECTION TO APPROVED OVERHAUL FACILITY

C65605 Engine Operating Fault Isolation Chart Figure 102 (Sheet 1 of 10) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Cont’d on Sheet 3

Cont’d from Sheet 1 FAILURE TO DECELERATE

UNCONTROLLED ACCELERATION

OVERSPEED (Ng)

CHECK ENGINE Ng INDICATING SYSTEM. RECTIFY AS NECESSARY

CHECK FCU TO FUEL PUMP INTERFACE FOR POSSIBLE SHEARED OR WORN DRIVE SPLINE COUPLING CHECK LINKAGE HANGUP IN CAMBOX YES REPLACE FCU AND/OR COUPLING

DRIVE SPLINE COUPLING SHEARED OR WORN NO CHECK FCU FOR CONTAMINATION AND/OR CORROSION

REPLACE FCU

C65606 Engine Operating Fault Isolation Chart Figure 102 (Sheet 2) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CONTINUED ON SHEET 4

CONTINUED FROM SHEET 2

SLOW TO ACCELERATE

SURGE DURING ACCELERATION

CHECK Py AIR BLEED TUBE AND P3 AIR DELIVERY TUBE FOR POSSIBLE LEAKS OR RESTRICTIONS. RECTIFY AS NECESSARY

DO COMPRESSOR WASH PROCEDURE CHECK OPERATION OF HIGH AND LOW COMPRESSOR BLEED VALVES AND CONDITION OF DIAPHRAGM

CHECK P3 AIR FILTER. REPLACE IF NECESSARY

IS BLEED VALVE OPERATION O.K.

NO

YES

VERIFY FUEL HEATER FOR HIGH OPERATING TEMPERATURE (REF. 71−00−00, ADJ/TEST) REPLACE IF NECESSARY

CHECK FCU ACCELERATION ADJUSTMENT AND PROP GOVERNOR REPLACE FCU OR PROP GOVERNOR AS APPLICABLE

CHECK FCU METERING ORIFACE AT COMPRESSOR DELIVERY AIR INLET ELBOW FOR RESTRICTION OR LEAKS. RECTIFY AS NECESSARY

REPLACE APPROPRIATE DIAPHRAGM OR DEFECTIVE BLEED VALVE

REMOVE INLET SCREEN. EXAMINE 1ST STAGE COMPRESSOR BLADES FOR FOREIGN OBJECT DAMAGE (FOD) COMPRESSOR BLADES FOUND O.K.

NO

YES

SHIP ENGINE TO APPROVED OVERHAUL FACILITY

REPLACE FCU

C65607A Engine Operating Fault Isolation Chart Figure 102 (Sheet 3) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Cont’d on Sheet 5

Cont’d from Sheet 3 FUEL LEAKAGE AT FCU VENT

OVER TEMPERATURE (MAX ALLOWABLE TEMP HAS BEEN EXCEEDED) Cont’d on Sheet 5

REMOVE FCU AND CHECK PREFORMED PACKING AT BYPASS PORT. IS PACKING LEAKAGE SUSPECTED NO

CHECK OPERATION OF TEMPERATURE INDICATING SYSTEM. IF FAULTY RECTIFY IF O.K.

CHECK ENGINE OVERTEMPERATURE CHART ENGINE REMOVAL

YES

REPLACE PREFORMED PACKING AND FCU

NO REMOVE ENGINE. INSPECT PROCEED AS NOTED ON OVERTEMP CHART

CHECK FOR LEAKAGE AT FUEL PUMP SHAFT CARBON SEAL FRONT AND REAR NO REPLACE BOTH FCU AND FUEL PUMP

YES

CHECK TORQUE INDICATING SYSTEM. IF FAULTY, RECTIFY

YES REPLACE FUEL PUMP

CHECK AIR INLET AND COMPRESSOR FOR CONTAMINATION BUILD−UP

COMPRESSOR DIRTY

YES

Cont’d on Sheet 5 NO CHECK FOR EXCESSIVE AIRFRAME ACCESSORY POWER LOADING NOTE: ON TWIN AND MULTI−ENGINED AIRCRAFT, CROSS−GENERATOR STARTS MAY RESULT IN HIGH T5 TEMPERATURE INDICATIONS

WASH COMPRESSOR

C65608 Engine Operating Fault Isolation Chart Figure 102 (Sheet 4) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Cont’d from Sheet 4

CHECK FOR EVIDENCE OF FUEL CONTAMINATION OF FCU DRIVE SHAFT BEARING AREA

YES

NO

RETURN FCU TO SERVICE

REPLACE FCU

C65609 Engine Operating Fault Isolation Chart Figure 102 (Sheet 5) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Cont’d from Sheet 5

Cont’d on Sheet 7 VIBRATION

TEMPERATURE LIMITED

REFER TO "HIGH T5 TEMPERATURE" ON PERFORMANCE CHECK CHART (FIGURE 103, SHEET 2)

PROPELLER DAMAGED OR BLADE ANGLE SLIPPED. ADJUST AND/OR REPLACE AS NECESSARY (REF. AIRCRAFT MAINTENANCE MANUAL)

INSPECT ENGINE FOR LOOSE MOUNTING BRACKETS

CHECK THROUGH EXHAUST PORTS FOR POWER TURBINE DAMAGE

REMOVE AIR INLET SCREEN AND INSPECT 1ST STAGE COMPRESSOR FOR SIGNS OF DAMAGE

NO

TURBINE AND COMPRESSOR CHECKS O.K. YES

SHIP ENGINE TO APPROVED OVERHAUL FACILITY

CHECK HIGH PRESSURE COMPRESSOR BLEED AIR VALVE OPERATION

C65610 Engine Operating Fault Isolation Chart Figure 102 (Sheet 6) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CONTINUED FROM SHEET 6

CONTINUED ON SHEET 8 FLAME OUT CHECK AIRFRAME INSTALLATION FUEL SUPPLY SOURCE. ENSURE FREE OF ICE OR WATER CONTAMINATION IF AIRFRAME FUEL SOURCE IS SATISFACTORY, LOOSEN INLET TUBE AT FCU AND CHECK FOR FUEL FLOW WHILST MOTORING ENGINE. NO FLOW APPARENT, REPLACE FUEL PUMP IF FUEL SUPPLY CHECKS ARE O.K., DEFECT DUE TO POSSIBLE AIR LOCK. RESTART ENGINE TO CARRY OUT SELF BLEEDING OPERATION CHECK ACCELERATION TIME OF ENGINE YES

ACCELERATION TIME O.K. NO

NO

CHECK FCU FOR CONTAMINATION OR CORROSION. FCU CONTAMINATED YES REPLACE FCU

INSPECT ENGINE FOR "FOD" OR TURBINE DAMAGE

CHECK MANIFOLD ADAPTERS AND FUEL NOZZLES

VERIFY FUEL HEATER FOR HIGH OPERATING TEMPERATURE (REF. 71−00−00, ADJ/TEST) REPLACE IF NECESSARY

C65611A Engine Operating Fault Isolation Chart Figure 102 (Sheet 7) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CONTINUED FROM SHEET 7 LOW POWER (ALL PARAMETERS LOW)

SQUEAL NOISE AT DECELERATION OR DURING MOTORING

CHECK OPERATING OF INDICATING SYSTEM. RECTIFY AS NECESSARY

WERE OPERATING PROCEDURES PROPERLY CARRIED OUT

CHECK FOR INCORRECT ADJUSTMENT OR DISCONNECTED CONTROL LINKAGES

CHECK FUEL PUMP. IF PUMP IS SOURCE CONTINUE IN SERVICE

SUNSTRAND FUEL PUMP PRESSURE PLATES NORMALLY SQUEAK AT LOW Ng.

IF CONTROL LINKAGES ARE SATISFACTORY, CARRY OUT CHACKS ON PROPELLER GOVERNOR. (PNEUMATIC SECTION Nf). IF DEFECTIVE, REPLACE GOVERNOR

CHECK FOR LEAKS OR RESTRICTIONS IN FCU PNEUMATIC SYSTEM. RECTIFY AS NECESSARY

NO LEAKS OR RESTRICTIONS IN FCU PNEUMATIC LINE. CHECK ADJUSTMENT OF FCU MAX SPEED SETTING

IF FCU MAX SETTING IS SATISFACTORY, CHECK FUEL NOZZLES FOR RESTRICTIONS

IF FUEL NOZZLES ARE SATISFACTORY, POSSIBLE FAULT DUE TO CONTAMINATED FCU. CHECK AND REPLACE AS NECESSARY

VERIFY FUEL HEATER FOR HIGH OPERATING TEMPERATURE (REF. 71−00−00, ADJ/TEST) REPLACE IF NECESSARY

C65612A Engine Operating Fault Isolation Chart Figure 102 (Sheet 8) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 8

IDLE SPEED INCORRECT

MISMATCH IN TWIN ENGINE INSTALLATION (RAPID ACCELERATION OF ONE ENGINE)

CHECK FOR INCORRECT CONTROL LINKAGE RIGGING. RE−ADJUST AS NECESSARY

CHECK Px METERING ORIFACE IS INSTALLED IN ELBOW IN FCU

CARRY OUT PROPELLER GOVERNOR CHECKS

INSPECT FCU PNEUMATIC SYSTEM TUBES FOR LEAKS. RECTIFY AS NECESSARY

IDLE SPEED SETTING OF FCU INCORRECT. RE−ADJUST AS NECESSARY

IF ADJUSTMENTS FAIL TO CORRECT PROBLEM, REPLACE FCU Cont’d on Sheet 10

C65613 Engine Operating Fault Isolation Chart Figure 102 (Sheet 9) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 9 Px METERING O.K. CHECK SETTING OF FCU ACCELERATION DOME. ADJUST AS NECESSARY

CHECK HP AND LP COMPRESSOR BLEED VALVE OPERATION AND CONDITIONS OR DIAPHRAGMS

IS COMPRESSOR BLEED VALVE OPERATION O.K.

NO

YES DO COMPRESSOR WASH PROCEDURE

REPLACE APPROPRIATE DIAPHRAGM OR COMPRESSOR BLEED VALVE

DO ENGINE RUN AND CHECK FOR AIR LEAKS AT ENGINE FLANGES. RECTIFY AS NECESSARY

IF FCU ACCELERATION SETTING AND BLEED VALVE OPERATION ARE O.K., REPLACE FCU

C65614 Engine Operating Fault Isolation Chart Figure 102 (Sheet 10) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

IS ENGINE ON ECTM PROGRAM

NO Cont’d on Sheet 7

YES IS PARAMETER SHIFT CONSIDERED NORMAL FOR ENGINE RUNNING TIME (REF. NOTES 1 AND 6)

YES

DO PREVENTIVE MAINTENANCE (REF. NOTE 3)

NO IF MULTI−ENGINE INSTALLATION, ANALYZE ECTM PLOTS FOR EACH ENGINE. ARE PARAMETER SHIFTS SIMILAR

YES

NO ITT (RAPID) SHIFT AND NO Ng/Wf SHIFT (REF. NOTES 2,5)

CHECK AIRCRAFT OAT, ALTITUDE AND AIR SPEED INDICATING SYSTEMS. A DEFECT IN THESE SYSTEMS WILL CAUSE SIMILAR ECTM SHIFT ON BOTH ENGINES

YES

NO Ng (RAPID) SHIFT AND NO ITT/Wf SHIFT (REF. NOTE 2)

YES

NO WF (RAPID) SHIFT AND NO ITT/Ng SHIFT (REF. NOTE 2)

YES

CHECK ENGINE/AIRFRAME INDICATING SYSTEM

REPAIR

Cont’d on Sheet 3

NO Cont’d on Sheet 2

C36844A Engine Performance Fault Isolation Chart Figure 103 (Sheet 1 of 10) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 1

ITT, Ng AND Wf DECREASED?

YES

NO CHECK ENGINE/AIRFRAME TORQUE AND Np INDICATING SYSTEMS. OK?

REPAIR

NO YES

NO ITT, Ng, Wf INCREASED?

YES CHECK ENGINE/AIRFRAME TORQUE AND Np INDICATING SYSTEMS. OK?

NO

YES INSPECT ENGINE INLET. CHECK BYPASS DOOR/ICE VANE RIGGING. OK?

NO

YES INSPECT COMPRESSOR. FOD/EROSION/RUB?

YES

YES DAMAGE ACCEPTABLE/REPAIRABLE

REPAIR

Cont’d on Sheet 3 "A"

NO NO

COMPRESSOR DIRTY?

SHIP ENGINE/GGM TO AN APPROVED OVERHAUL FACILITY YES

DO A COMPRESSOR WASH OR POWER RECOVERY WASH

NO Cont’d on Sheet 3

C36845 Engine Performance Fault Isolation Chart Figure 103 (Sheet 2) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 2 NO DO ENGINE BLEED VALVE CHECK. OK? YES NO

LEAK CHECK P2.5 AIRFRAME BLEED PIPE. OK?

REPAIR

YES CHECK HOT STARTS, A HOT START MAY CAUSE ALL PARAMETERS TO INCREASE SUDDENLY

NO

INSPECT ENGINE HOT SECTION COMPONENTS AS REQUIRED

YES From Sheets 1 and 2 "A"

YES

DO ENGINE PERFORMANCE CHECK. COMPARE WITH CHECK DONE AT ENGINE INSTALLATION OR LATER (AS AVAILABLE). RECORD DIFFERENCES (SHIFT) IN PARAMETERS

SIGNIFICANT DIFFERENCE BETWEEN ECTM AND ENGINE PERFORMANCE CHECK PARAMETERS RECORDED (REF. NOTE 4)

YES

IS THE INITIAL SHIFT REDUCED/ELIMINATED BY THE PREVIOUS MAINTENANCE ACTION

NO

YES

NO

SYSTEM NORMAL

Cont’d on Sheet 5

CHECK ENGINE FIREWALL AND INLET SEAL CONDITIONS. OK? (REF. NOTE 8) NO

YES

REPAIR

Cont’d on Sheet 4

C36846A Engine Performance Fault Isolation Chart Figure 103 (Sheet 3) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 3

AIR BLEED SYSTEM PRESSURE REGULATING VALVE OK? (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

YES AIR BLEED SYSTEM SHUTOFF VALVE OK? (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

YES NO AIR BLEED SYSTEM DUCTING OK? (REF. AIRCRAFT MAINTENANCE MANUAL)

REPAIR

YES CONTACT AIRCRAFT MANUFACTURER

REPEAT ENGINE PERFORMANCE CHECK. HAS PERFORMANCE IMPROVED? NO

YES

Cont’d on Sheet 5

SYSTEM NORMAL

C36847 Engine Performance Fault Isolation Chart Figure 103 (Sheet 4) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheets 3 and 4 ITT AND Wf INCREASE AND Ng DECREASE? NO

YES INSPECT CT STATOR, BLADES AND SHROUD SEGMENTS. DEFECTS FOUND? YES

ARE DEFECTS UNACCEPTABLE OR COULD THEY CAUSE THE PERFORMANCE DETERIORATION? NO

NO

YES DO AN HSI

DO A PERFORMANCE RECOVERY WASH

ITT AND Wf INCREASE WITH Ng CONSTANT? YES CHECK GAS GENERATOR CASE DRAIN VALVES, FUEL NOZZLE GASKETS, "C" FLANGE AND T5 HARNESS SEAL FOR LEAKS. OK?

NO

YES NO LEAK CHECK P3 BLEED (AIRFRAME) PIPE AND ADAPTER. OK? YES NO INSPECT COMPRESSOR AND HOT SECTION. OK? (REF. NOTE 7)

REPAIR

REPEAT ENGINE PERFORMANCE CHECK. HAS PERFORMANCE IMPROVED? YES SYSTEM NORMAL

NO Cont’d on Sheet 6

C36848 Engine Performance Fault Isolation Chart Figure 103 (Sheet 5) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheets 5 and 9

NO

REPEAT ENGINE PERFORMANCE CHECK WITH BLEED AIR PORTS BLANKED OFF. HAS ENGINE PERFORMANCE IMPROVED (REF. NOTE 10) YES

NO

SYSTEM NORMAL

DO AN HSI

C36849 Engine Performance Fault Isolation Chart Figure 103 (Sheet 6) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 1

ENGINE PERFORMANCE CHECK AFFECTED ENGINE IS SATISFACTORY (REF. NOTE 5)

CHECK ENGINE FIREWALL AND INLET SEAL CONDITION. OK? (REF. NOTE 8)

YES

NO

NO

YES AIR BLEED SYSTEM PRESSURE REGULATING VALVE. OK? (REF. AIRCRAFT MAINTENANCE MANUAL)

COMPARE ENGINE PERFORMANCE CHECK WITH CHECK DONE AT ENGINE INSTALLATION OR LATER (AS AVAILABLE). RECORD DIFFERENCES IN PARAMETERS (REF. NOTE 3)

NO

YES AIR BLEED SYSTEM SHUTOFF VALVE. OK? (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

YES CHECK AIR BLEED SYSTEM DUCTING (REF. AIRCRAFT MAINTENANCE MANUAL) ITT SHIFT AND NO Ng SHIFT (REF. NOTES 6, 9)

NO

YES

NO Ng SHIFT AND NO ITT SHIFT?

YES

NO CHECK ENGINE/AIRFRAME INDICATING SYSTEM Cont’d on Sheet 8

REPAIR

Cont’d on Sheet 9 "C"

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 7 NO

ITT AND Ng CHANGE

CONT’D ON SHEET 9

YES YES

ITT INCREASE AND Ng DECREASE ?

CONT’D ON SHEET 9 "D"

NO CHECK TORQUE AND Np INDICATING SYSTEMS (AIRFRAME/ENGINE). OK?

NO

YES INSPECT ENGINE INLET. CHECK BYPASS DOOR/ICE VANE RIGGING. OK?

NO

REPAIR

YES YES

INSPECT COMPRESSOR. FOD/EROSION/RUB?

DAMAGE ACCEPTABLE/REPAIRABLE

YES

REPAIR

NO

NO

SHIP ENGINE/GGM TO AN APPROVED OVERHAUL FACILITY

COMPRESSOR DIRTY?

YES

CONT’D ON SHEET 9 "C"

DO A COMPRESSOR WASH OR POWER RECOVERY WASH

NO CHECK ENGINE BLEED VALVE. OK?

NO

YES

REPAIR

LEAK CHECK P2.5 AIRFRAME BLEED PIPE. OK? YES

NO

CHECK FOR HOT STARTS. A HOT START MAY CAUSE ALL PARAMETERS TO INCREASE SUDDENLY

INSPECT HOT SECTION COMPONENTS AS REQUIRED

NO

YES CONT’D ON SHEET 9 "C"

C36851B Engine Performance Fault Isolation Chart Figure 103 (Sheet 8) P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

FROM SHEET 8 "D" ( IF AT IDLE ) CHECK FUEL HEATER. OK ?

CHANGE FUEL HEATER

NO

YES ARE DEFECTS UNACCEPTABLE OR COULD THEY CAUSE THE PERFORMANCE DETERIORATION ?

INSPECT CT VANE, BLADES AND SHROUD SEGMENTS. DEFECTS FOUND? YES FROM SHEET 8

NO

NO

YES DO AN HSI

DO A PERFORMANCE RECOVERY WASH

ITT AND Wf INCREASE WITH Ng CONSTANT? YES CHECK GAS GENERATOR CASE DRAIN VALVES, FUEL NOZZLE GASKETS, "C" FLANGE AND T5 HARNESS SEAL FOR LEAKS. OK?

NO

YES NO LEAK CHECK P3 BLEED (AIRFRAME) PIPE AND ADAPTER. OK? YES NO INSPECT COMPRERSSOR AND HOT SECTION. OK? (REF. NOTE 7)

FROM SHEET 7 AND 8

"C"

REPAIR

REPEAT ENGINE PERFORMANCE CHECK. HAS PERFORMANCE IMPROVED ?

YES SYSTEM NORMAL

NO CONT’D ON SHEET 6

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

E.

Engine Condition Trend Monitoring Shift (1)

To diagnose and rectify engine condition trend monitoring shift, refer to ECTM Shift Fault Isolation Chart (Ref. Table 101) . TABLE 101, ECTM Shift Fault Isolation Chart

Engine Parameters All parameters UP

Probable Cause

Action Req’d

Remarks

Engine/Airframe indicating systems

Inspect

Repair as req’d

Air inlet door blocked

Inspect

Repair as req’d

Bypass door or ice vane misrigged.

Inspect

Repair as req’d

Compressor FOD, rub, erosion

Inspect and/or repair

Remove engine if damage limits are exceeded

Compressor contaminated/dirty

Wash compressor

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 DOWN

Engine/Airframe indicating system

Inspect

Repair as req’d

T5 UP or DOWN, Ng, Wf Constant

Engine/Airframe indicating system (NOTE 1)

Inspect . If applicable, do on-wing T5 system trim.

Repair as req’d. T5 usually decreases when probes are unserviceable.

Fuel nozzle deterioration

Inspect

Clean as req’d

Ng UP or DOWN, T5, Wf Constant.

Engine/Airframe indicating system

Inspect

Repair as req’d.

Wf UP or DOWN, T5, Ng Constant.

Engine/Airframe indicating system

Inspect

Repair as req’d.

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

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Page 136 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TEMPORARY REVISION NO. 72-22 (PT6A-38, PT6A-41, PT6A-42, PT6A-42A) INSERT Temporary Revision 72-22 facing page 137, Chapter 72-00-00 ENGINE, TURBOPROP - FAULT ISOLATION PURPOSE:

F.

The purpose of this temporary revision is to revise the engine lubrication fault isolation chart to add necessity of PRV spacer for PT6A-42 engine model and to introduce a check of the AGB internal scavenge pump inlet screen for blockage in the event of an inlet case oil leak following multiple motoring cycles or propeller wind milling in flight.

Engine Lubrication (1)

To diagnose and rectify engine lubrication problems, refer to Engine Lubrication Fault Isolation Chart (Ref. Fig. 104).

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

ENGINE, TURBOPROP - FAULT ISOLATION PRINTED IN CANADA

Page 1 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-22

Cont’d on Sheet 3

HIGH OIL PRESSURE

LOW OIL PRESSURE

CHECK OIL PRESSURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

INSUFFICIENT OIL. CHECK OIL LEVEL (REF. 70−00−00)

OIL LEVEL O.K. CHECK OIL PRESSURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

INDICATING SYSTEM O.K. YES

NO

NO

INDICATING SYSTEM O.K.

YES

YES RECTIFY FAULT ON INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

FOR PT6A−42A PIPER MERIDIAN, REFER TO CHAP. 79−20−02, MAINTENANCE PRACTICES, PARA. 8.E.

FOR PT6A−38/41/42 INSPECT OIL FILTER. CLEAN OR REPLACE AS NECESSARY

CHECK EXTERNAL OIL LINES AND OIL COOLER FOR LEAKS. RECTIFY AS NECESSARY Cont’d on Sheet 2 Cont’d on Sheet 2

C36853B Engine Lubrication Fault Isolation Chart Figure 104 (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.

72-00-00

ENGINE, TURBOPROP - FAULT ISOLATION

Page 2 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-22

From Sheet 1

From Sheet 1

PRV MALFUNCTION. REMOVE, CLEAN AND INSPECT

PRESSURE RELIEF REGULATING VALVE (PRV) MALFUNCTION. REMOVE, CLEAN AND INSPECT

NO

NO

PRV O.K.

PRV O.K.

YES YES REMOVE PRV SPACER(S) AS NECESSARY

REPLACE PRV

ADD PRV SPACER(S) AS NECESSARY. CAUTION: FOR PT6A−42A ENGINES: IF THE OIL PRESSURE IS ADJUSTED DURING PREVIOUS MAINTENANCE OR TROUBLESHOOTING AND LOW OIL PRESSURE REOCCURS, REFER TO 79−20−02, MAINTENANCE PRACTICES.

C184916 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.

72-00-00

ENGINE, TURBOPROP - FAULT ISOLATION

Page 3 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-22 Cont’d on Sheet 4

From Sheet 1

FLUCTUATING OIL PRESSURE

INSUFFICIENT OR EXCESS OIL. CHECK OIL LEVEL

OIL LEVEL O.K. CHECK OIL PRESSURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

RECTIFY FAULT ON INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

INDICATING SYSTEM O.K. YES

INSPECT OIL FILTER. CLEAN OR REPLACE AS NECESSARY

OIL FILTER INSPECTION O.K.POSSIBLE PRESSURE RELIEF VALVE MALFUNCTION. CLEAN AND INSPECT

REPLACE PRV AS NECESSARY

C36855 Engine Lubrication Fault Isolation Chart Figure 104 (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.

72-00-00

ENGINE, TURBOPROP - FAULT ISOLATION

Page 4 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-22

Cont’d on Sheet 6

From Sheet 3

*

HIGH OIL TEMPERATURE

INSUFFICIENT OIL. CHECK OIL LEVEL.

OIL LEVEL O.K. CHECK OIL TEMPERATURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

RECTIFY FAULT ON INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

INDICATING SYSTEM O.K. YES

* NOTE: EXCESSIVE IDLING IN FEATHER COULD CAUSE OVERHEATING INDICATION. RESTRICT IDLING TIME IN FEATHER

IF HIGH OIL TEMPERATURE DURING GROUND OPERATION, (AIRCRAFT STATIONARY) VERIFY PROPELLER RIGGING/ADJUSTMENT, (PRIMARY BLADE ANGLE) (REF. AIRCRAFT MAINTENANCE MANUAL)

Cont’d on Sheet 5

C36856 Engine Lubrication Fault Isolation Chart Figure 104 (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.

72-00-00

ENGINE, TURBOPROP - FAULT ISOLATION

Page 5 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-22

From Sheet 4

CHECK AIRFRAME OIL COOLER SYSTEM FOR RESTRICTIONS OR MALFUNCTIONS (REF. AIRCRAFT MAINTENANCE MANUAL)

RECTIFY FAULT ON OIL COOLER SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

OIL COOLER SYSTEM O.K. YES

PT6A−38

PT6A−41

INSPECT AND RECTIFY THERMOSTATIC BYPASS VALVE ON OIL−TO−FUEL HEATER. IF NECESSARY, REPLACE THERMOSTATIC BYPASS VALVE

THERMOSTATIC BYPASS VALVE INSPECTION O.K.

HEAT SHIELD FAILURE. RETURN ENGINE TO APPROVED OVERHAUL FACILITY

C65599 Engine Lubrication Fault Isolation Chart Figure 104 (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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ENGINE, TURBOPROP - FAULT ISOLATION

Page 6 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-22 FROM SHEET 3

CONT’D ON SHEET 8

CHECK THE BREATHER TUBE FOR OBSTRUCTION ON ENGINE SIDE AND AIRFRAME SIDE

OIL LEVEL DECREASE IN STATIC CONDITION BY ONE QUARTER OR MORE

OIL LEAK FROM COMPRESSOR INLET CASE

YES

CHECK OIL TANK LEVEL FOR OVERSERVICED CONDITION. LEVEL OK?

INLET CASE OIL LEAK FOLLOWING MULTIPLE MOTORING CYCLES OR PROPELLER WINDMILLING IN FLIGHT?

NO YES

CHECK OIL TANK DRAIN PLUG FOR LEAKAGE

VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE−SB3066). RECTIFY AND DO STATIC TEST CHECK

NO

YES CHECK FOR OIL LEAKAGE AT PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING

CHECK AGB INTERNAL NO SCAVENGE PUMP INLET SCREEN FOR BLOCKAGE. OK?

NO PREFORMED PACKING AND PLASTIC RING O.K.

YES

LAP CHECK VALVE (PRE−SB3066). RENEW PREFORMED PACKING (POST−SB3066). LAP CHECK VALVE AND SEAT (POST−SB3178) DO STATIC LEAK TEST

YES

CLEAN INLET SCREEN

NO

CLEAN ENGINE AND RETURN TO SERVICE

CHECK FOR OIL LEAKAGE AT FILTER BYPASS AND CHECK VALVE PREFORMED PACKINGS, PACKINGS O.K. YES

CHECK OIL FILTER BYPASS AND CHECK VALVE SEALS WHEN FULLY CLOSED. VALVE O.K.

NO

CLEAN OR REPLACE VALVE AS NECESSARY

REPLACE PREFORMED PACKINGS OR PLASTIC RINGS AS NECESSARY Cont’d on Sheet 7

C166451 Engine Lubrication Fault Isolation Chart Figure 104 (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.

72-00-00

ENGINE, TURBOPROP - FAULT ISOLATION

Page 7 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-22

From Sheet 6

EXCESSIVE OIL CONSUMPTION

EXCESSIVE DISCHARGE FROM OVERBOARD BREATHER

EXCESS OF OIL. CHECK TANK LEVEL FOR OVER−SERVICED CONDITION EXCESS OF OIL. CHECK TANK LEVEL FOR OVER−SERVICED CONDITION

CHECK THE BREATHER TUBE FOR OBSTRUCTION ON ENGINE SIDE AND AIRFRAME SIDE

CHECK FOR LEAKAGE OR RESTRICTIONS IN PRESSURE OR SCAVENGE OIL TUBES

OIL LEVEL INSPECTION O.K. CHECK FOR OIL LEAKAGE DUE TO DEFECTIVE PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING

PREFORMED PACKING AND PLASTIC RING O.K.

NO

SCAVENGE OR OIL TUBES O.K. CHECK FOR LEAKAGE AT PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING NO

PREFORMED PACKING AND PLASTIC RING O.K.

YES

YES REPLACE PREFORMED PACKING AND/OR PLASTIC RING AS NECESSARY

VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE−SB3066). RECTIFY IF NECESSARY AND DO STATIC LEAK CHECK

CHECK CONDITION OF CHECK VALVE SEAT (PRE−SB3066) OR PREFORMED PACKING (POST− SB3066). CHECK OK. NO

VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE−SB3066). RECTIFY IF NECESSARY AND DO STATIC LEAK CHECK

YES

CONT’D ON SHEET 9

LAP CHECK VALVE (PRE−SB3066). RENEW PREFORMED PACKING (POST−SB3066). LAP CHECK VALVE AND SEAT (POST−SB3178). DO STATIC LEAK TEST

CONT’D ON SHEET 9

C170347 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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ENGINE, TURBOPROP - FAULT ISOLATION

Page 8 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-22

From Sheet 6 YES

REMOVE OIL FILTER HOUSING. CHECK FOR LEAKAGE FROM EITHER EXPANSION PLUG IN INLET CASE WALL. PLUGS O.K.

NO

SHIP GGM TO APPROVED OVERHAUL FACILITY FOR REPAIR

YES

CHECK FOR LEAKAGE AT PREFORMED PACKINGS ON ACCESSORY GEARBOX. RECTIFY AS NECESSARY

C36859 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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Page 9 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-22

From Sheet 8

From Sheet 8

EXCESSIVE BACK PRESSURE IN SCAVENGE SYSTEM. CHECK FOR RESTRICTIONS IN OIL SCAVENGE TUBES, PUMP SCREEN AND OIL−TO−FUEL HEATER TUBES. RECTIFY AS NECESSARY YES

SCAVENGE OIL SYSTEM O.K. CHECK FOR DEFECTIVE OR COCKED CENTRIFUGAL BREATHER CARBON SEAL. REPLACE AS NECESSARY

REMOVE POWER OUTPUT SECTION. CHECK POWER TURBINE AND COMPRESSOR TURBINE AREAS FOR TRACES OF OIL

CHECK EXHAUST AREA FOR TRACES OF OIL. IS OIL VISIBLE NO POSSIBLE FAULT DUE TO INTERNAL LEAKAGE IN OIL−TO−FUEL HEATER. REPLACE OIL−TO−FUEL HEATER

FAULT STILL APPARENT. CHECK FOR DEFECTIVE OR COCKED CENTRIFUGAL BREATHER CARBON SEAL. REPLACE AS NECESSARY

IF EVIDENT IN POWER AREA, SHIP POWER SECTION TO APPROVED OVERHAUL FACILITY

IF EVIDENT IN COMPRESSOR AREA, REMOVE TURBINE DISK, ASSEMBLY OF VANE RING AND LARGE EXIT DUCT. INSPECT NO. 2 BEARING STATOR AIR SEAL GASKET. REPLACE AS NECESSARY. CHECK AIR PRESSURIZING HOLES AT REAR OF MOUNTING FLANGE OF EXIT DUCTS FOR BLOCKAGE. CLEAR AS NECESSARY

CARBON SEAL SATISFACTORY. CHECK PREFORMED PACKINGS ON ACCESSORY GEARBOX. RECTIFY AS NECESSARY

SHIP ENGINE TO APPROVED OVERHAUL FACILITY

C36861 Engine Lubrication Fault Isolation Chart Figure 104 (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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Page 10 of 10 Jan 27/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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.

If limits exceeded, do an HSI.

Normal hot section deterioration

Do an HSI if T5 limit exceeded.

P3 leaks from engine/airframe 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.

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. F.

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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Page 137 Dec 10/2010

NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Cont’d on Sheet 3

HIGH OIL PRESSURE

LOW OIL PRESSURE

CHECK OIL PRESSURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

INSUFFICIENT OIL. CHECK OIL LEVEL (REF. 70−00−00)

OIL LEVEL O.K. CHECK OIL PRESSURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

INDICATING SYSTEM O.K. YES

NO

NO

INDICATING SYSTEM O.K.

YES

YES RECTIFY FAULT ON INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

FOR PT6A−42A PIPER MERIDIAN, REFER TO CHAP. 79−20−02, MAINTENANCE PRACTICES, PARA. 8.E.

FOR PT6A−38/41/42 INSPECT OIL FILTER. CLEAN OR REPLACE AS NECESSARY

CHECK EXTERNAL OIL LINES AND OIL COOLER FOR LEAKS. RECTIFY AS NECESSARY Cont’d on Sheet 2 Cont’d on Sheet 2

C36853B Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 1 of 9) P&WC Proprietary Information. Subject to the restrictions on the title page.

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Page 138 Dec 10/2010

NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 1

From Sheet 1

PRV MALFUNCTION. REMOVE, CLEAN AND INSPECT

PRESSURE RELIEF REGULATING VALVE (PRV) MALFUNCTION. REMOVE, CLEAN AND INSPECT

NO

NO

PRV O.K.

PRV O.K.

YES

YES REMOVE PRV SPACER(S) AS NECESSARY

ADD PRV SPACER (S) AS NECESSARY

REPLACE PRV

C36854 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 2) P&WC Proprietary Information. Subject to the restrictions on the title page.

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Page 139 Dec 10/2010

NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Cont’d on Sheet 4

From Sheet 1

FLUCTUATING OIL PRESSURE

INSUFFICIENT OR EXCESS OIL. CHECK OIL LEVEL

OIL LEVEL O.K. CHECK OIL PRESSURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

RECTIFY FAULT ON INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

INDICATING SYSTEM O.K. YES

INSPECT OIL FILTER. CLEAN OR REPLACE AS NECESSARY

OIL FILTER INSPECTION O.K.POSSIBLE PRESSURE RELIEF VALVE MALFUNCTION. CLEAN AND INSPECT

REPLACE PRV AS NECESSARY

C36855 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 3) P&WC Proprietary Information. Subject to the restrictions on the title page.

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Page 140 Dec 10/2010

NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Cont’d on Sheet 6

From Sheet 3

*

HIGH OIL TEMPERATURE

INSUFFICIENT OIL. CHECK OIL LEVEL.

OIL LEVEL O.K. CHECK OIL TEMPERATURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

RECTIFY FAULT ON INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

INDICATING SYSTEM O.K. YES

* NOTE: EXCESSIVE IDLING IN FEATHER COULD CAUSE OVERHEATING INDICATION. RESTRICT IDLING TIME IN FEATHER

IF HIGH OIL TEMPERATURE DURING GROUND OPERATION, (AIRCRAFT STATIONARY) VERIFY PROPELLER RIGGING/ADJUSTMENT, (PRIMARY BLADE ANGLE) (REF. AIRCRAFT MAINTENANCE MANUAL)

Cont’d on Sheet 5

C36856 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 4) P&WC Proprietary Information. Subject to the restrictions on the title page.

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Page 141 Dec 10/2010

NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 4

CHECK AIRFRAME OIL COOLER SYSTEM FOR RESTRICTIONS OR MALFUNCTIONS (REF. AIRCRAFT MAINTENANCE MANUAL)

RECTIFY FAULT ON OIL COOLER SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)

NO

OIL COOLER SYSTEM O.K. YES

PT6A−38

PT6A−41

INSPECT AND RECTIFY THERMOSTATIC BYPASS VALVE ON OIL−TO−FUEL HEATER. IF NECESSARY, REPLACE THERMOSTATIC BYPASS VALVE

THERMOSTATIC BYPASS VALVE INSPECTION O.K.

HEAT SHIELD FAILURE. RETURN ENGINE TO APPROVED OVERHAUL FACILITY

C65599 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 5) P&WC Proprietary Information. Subject to the restrictions on the title page.

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Page 142 Dec 10/2010

NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

FROM SHEET 3

CONT’D ON SHEET 8

CHECK THE BREATHER TUBE FOR OBSTRUCTION ON ENGINE SIDE AND AIRFRAME SIDE

OIL LEVEL DECREASE IN STATIC CONDITION BY ONE QUARTER OR MORE

OIL LEAK FROM COMPRESSOR INLET CASE

YES

CHECK OIL TANK LEVEL FOR OVERSERVICED CONDITION LEVEL O.K.

INLET CASE OIL LEAK FOLLOWED MULTIPLE MOTORING CYCLES

NO YES

YES

CLEAN AND RETURN TO SERVICE

CHECK OIL TANK DRAIN PLUG FOR LEAKAGE

VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE−SB3066). RECTIFY AND DO STATIC TEST CHECK

NO CHECK FOR OIL LEAKAGE AT PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING

NO

LAP CHECK VALVE (PRE−SB3066). RENEW PREFORMED PACKING (POST−SB3066). LAP CHECK VALVE AND SEAT (POST−SB3178) DO STATIC LEAK TEST

PREFORMED PACKING AND PLASTIC RING O.K. YES

NO

CHECK FOR OIL LEAKAGE AT FILTER BYPASS AND CHECK VALVE PREFORMED PACKINGS, PACKINGS O.K. YES

REPLACE PREFORMED PACKINGS OR PLASTIC RINGS AS NECESSARY

CHECK OIL FILTER BYPASS AND CHECK VALVE SEALS WHEN FULLY CLOSED. VALVE O.K.

NO

CLEAN OR REPLACE VALVE AS NECESSARY

Cont’d on Sheet 7

C65602B Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 6) P&WC Proprietary Information. Subject to the restrictions on the title page.

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Page 143 Dec 10/2010

NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 6

EXCESSIVE OIL CONSUMPTION

EXCESSIVE DISCHARGE FROM OVERBOARD BREATHER

EXCESS OF OIL. CHECK TANK LEVEL FOR OVER−SERVICED CONDITION EXCESS OF OIL. CHECK TANK LEVEL FOR OVER−SERVICED CONDITION

OIL LEVEL INSPECTION O.K. CHECK FOR OIL LEAKAGE DUE TO DEFECTIVE PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING

PREFORMED PACKING AND PLASTIC RING O.K.

NO

CHECK THE BREATHER TUBE FOR OBSTRUCTION ON ENGINE SIDE AND AIRFRAME SIDE

CHECK FOR LEAKAGE OR RESTRICTIONS IN PRESSURE OR SCAVENGE OIL TUBES SCAVENGE OR OIL TUBES O.K. CHECK FOR LEAKAGE AT PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING NO

PREFORMED PACKING AND PLASTIC RING O.K.

YES

YES REPLACE PREFORMED PACKING AND/OR PLASTIC RING AS NECESSARY

VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE−SB3066). RECTIFY IF NECESSARY AND DO STATIC LEAK CHECK

CHECK CONDITION OF CHECK VALVE SEAT (PRE−SB3066) OR PREFORMED PACKING (POST− SB3066). CHECK OK. NO

VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE−SB3066). RECTIFY IF NECESSARY AND DO STATIC LEAK CHECK

YES

CONT’D ON SHEET 9

LAP CHECK VALVE (PRE−SB3066). RENEW PREFORMED PACKING (POST−SB3066). LAP CHECK VALVE AND SEAT (POST−SB3178). DO STATIC LEAK TEST

CONT’D ON SHEET 9

C170347 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 7) P&WC Proprietary Information. Subject to the restrictions on the title page.

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NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 6 YES

REMOVE OIL FILTER HOUSING. CHECK FOR LEAKAGE FROM EITHER EXPANSION PLUG IN INLET CASE WALL. PLUGS O.K.

NO

SHIP GGM TO APPROVED OVERHAUL FACILITY FOR REPAIR

YES

CHECK FOR LEAKAGE AT PREFORMED PACKINGS ON ACCESSORY GEARBOX. RECTIFY AS NECESSARY

C36859 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 8) P&WC Proprietary Information. Subject to the restrictions on the title page.

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NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

From Sheet 8

From Sheet 8

EXCESSIVE BACK PRESSURE IN SCAVENGE SYSTEM. CHECK FOR RESTRICTIONS IN OIL SCAVENGE TUBES, PUMP SCREEN AND OIL−TO−FUEL HEATER TUBES. RECTIFY AS NECESSARY YES

SCAVENGE OIL SYSTEM O.K. CHECK FOR DEFECTIVE OR COCKED CENTRIFUGAL BREATHER CARBON SEAL. REPLACE AS NECESSARY

REMOVE POWER OUTPUT SECTION. CHECK POWER TURBINE AND COMPRESSOR TURBINE AREAS FOR TRACES OF OIL

CHECK EXHAUST AREA FOR TRACES OF OIL. IS OIL VISIBLE NO POSSIBLE FAULT DUE TO INTERNAL LEAKAGE IN OIL−TO−FUEL HEATER. REPLACE OIL−TO−FUEL HEATER

FAULT STILL APPARENT. CHECK FOR DEFECTIVE OR COCKED CENTRIFUGAL BREATHER CARBON SEAL. REPLACE AS NECESSARY

IF EVIDENT IN POWER AREA, SHIP POWER SECTION TO APPROVED OVERHAUL FACILITY

IF EVIDENT IN COMPRESSOR AREA, REMOVE TURBINE DISK, ASSEMBLY OF VANE RING AND LARGE EXIT DUCT. INSPECT NO. 2 BEARING STATOR AIR SEAL GASKET. REPLACE AS NECESSARY. CHECK AIR PRESSURIZING HOLES AT REAR OF MOUNTING FLANGE OF EXIT DUCTS FOR BLOCKAGE. CLEAR AS NECESSARY

CARBON SEAL SATISFACTORY. CHECK PREFORMED PACKINGS ON ACCESSORY GEARBOX. RECTIFY AS NECESSARY

SHIP ENGINE TO APPROVED OVERHAUL FACILITY

C36861 Engine Lubrication Fault Isolation Chart Figure 104 (Sheet 9) P&WC Proprietary Information. Subject to the restrictions on the title page.

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NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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 restrictions on the title page.

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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 RGB 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 RGB MODULE

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

C36863 Engine Lubricating Oil Contamination Fault Isolation Chart Figure 105 (Sheet 2) P&WC Proprietary Information. Subject to the restrictions on the title page.

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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

NO

REMOVE ENGINE

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

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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 WAS DEBRIS ALLOWABLE

CONTINUE IN SERVICE

NO

WAS DEBRIS GEAR MATERIAL?

NO

REPLACE ENGINE

INSPECT MODULE AS REQUIRED USING BORESCOPE (LABORATORY ANALYSED DEBRIS)

YES

NO WAS MATERIAL AIR SEAL AMS4117, AMS4127, AMS4150, AMS5613, AMS5671, MOLY

YES

ENGINE MAY REMAIN IN SERVICE. CARRY OUT A CHIP DETECTOR AND FILTER CHECK AFTER 10 HOURS AND PROVIDING NO DEBRIS IS FOUND, AFTER 50 HOURS (REF. NOTE 2)

WAS DEBRIS BRONZE CATEGORY 2 MATERIAL YES

IS MODULE IN ACCEPTABLE CONDITION

NO CONTINUE IN SERVICE

YES

CARRY OUT 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 MODULE

IS LAB SEAL OR BRONZE MATERIAL FOUND (MAJOR OR MINOR CONTAMINANT) YES REMOVE MODULE

NO RETURN TO SERVICE

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(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 prior to 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. NOTE: 6. Bearing inner and outer rings as well as rolling elements are made of steel AMS6440/6444 (52100) or AMS6490/6491 (M50). Bearing cages are made of steel AMS6414/6415 (4340) or bronze AMS4616, silver plated per AMS2412. 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.

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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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ENGINE, TURBOPROP - SERVICING 1.

2.

General A.

The following information and procedures are necessary for storage, preservation and depreservation of an engine or power section/power section module (PS/PSM).

B.

For engine installation in airframe, refer to REMOVAL/INSTALLATION.

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

3.

Item No.

Name

PWC03-001 PWC05-070 PWC05-077 PWC06-012 PWC07-005 PWC07-005A PWC09-003 PWC13-002

Oil, Engine Lubricating Tape, Pressure Sensitive Oil, Preservative Grease, Bearing Paint, Enamel Paint, Enamel Compound, Sealing Coating, Primer

Special Tools The special tools listed below are used in the following procedures. Tool No.

Name

PWC30269 PWC30800

Mount Ring, Stand Stand, Engine (Replaced by PWC34300) DELETED Sling, Power Section without prop. (Replaced by PWC70099) Stand, Engine Adapter, Engine Mount DELETED DELETED Sling, Engine Sling, Power Section without prop. DELETED

PWC32420 PWC34073

PWC34300 PWC34752 PWC50066 PWC51140 PWC51861-600 PWC70099 PWC70907

Application

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4.

Tool No.

Name

Application

PWC71416

Bracket, Engine Assembly

Replaces PWC32000

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 (Ref. 72-00-00, DESCRIPTION AND OPERATION, Approved Service Bulletins) 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.

B.

Oil Level Check To avoid overservicing 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 dipstick with clean lint free cloth

CAUTION: WHEN FILLER CAP ASSEMBLY IS INSTALLED AND LOCKED, NO MOVEMENT IS ALLOWED. (3)

Install cap/dipstick and lock.

(4)

Remove cap/dipstick

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CAUTION: DO NOT MIX DIFFERENT TYPES OF OIL SINCE THEIR DIFFERENT CHEMICAL STRUCTURES MAY MAKE THEM INCOMPATIBLE. IF DIFFERENT TYPES OF OIL BECOME MIXED, DRAIN AND FLUSH SYSTEM AND REFILL WITH NEW OIL. (5)

Check oil tank contents against marking on dipstick and service as required. Normal oil level is one US quart (0.83 Imp. quart, 0.95 liters) below maximum level, with engine in horizontal attitude. NOTE:

(6)

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.

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. CAUTION: WHEN FILLER CAP ASSEMBLY IS INSTALLED AND LOCKED, NO MOVEMENT IS ALLOWED. (b) Install filler cap and 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) thru (6) preceding). (e) Check main oil filter (Ref. 79-20-02).

D.

Oil Servicing NOTE:

For oil change recommendations, refer to SB3001.

(1)

Place suitable containers under engine.

(2)

Remove chip detector and valve housing located at 6 o’clock position on front case of reduction gearbox and oil drain plug on accessory gearbox housing.

(3)

Remove drain plug on oil-to-fuel heater (Ref. 73-10-01).

(4)

Discard all preformed packings.

(5)

Install new preformed packings on drain plugs, chip detector and valve housing.

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E.

(6)

Install drain plugs on accessory gearbox housing. Tighten plugs 215 to 240 lb.in. and lockwire.

(7)

Install chip detector into threaded boss in RGB . Tighten detector body 45 to 55 lb.in. and lockwire.

(8)

Install drain plug on oil-to-fuel heater. Tighten plug 65 to 75 lb.in. and lockwire.

(9)

Fill oil tank (Ref. Subpara. C.).

Oil System Flushing

CAUTION: IF THE ENGINE OIL SYSTEM HAS BEEN FILLED WITH AN UNAPPROVED OIL TYPE OR IF THE OIL SYSTEM HAS BEEN CONTAMINATED BY OTHER THAN METALLIC MATTER, THE SYSTEM MUST BE FLUSHED AND FILLED AGAIN WITH THE ORIGINAL OIL TYPE OR AN APPROVED OIL TYPE. (1)

Place suitable containers under engine.

(2)

Remove chip detector from reduction gearbox front case, and oil drain plugs from accessory gearbox housing and oil-to-fuel heater.

CAUTION: LIMIT ENGINE ROTATION TO MINIMUM TIME REQUIRED TO DRAIN OIL. ALSO OBSERVE STARTER OPERATING LIMITATIONS. (3)

With drains open, place fuel condition lever to CUT-OFF and ignition switch OFF, motor engine with starter only and allow scavenge pumps to clear all lubricating oil.

(4)

Install chip detector and drain plugs.

(5)

Fill engine oil tank (Ref. Subpara. C.).

(6)

Start engine and run at GROUND-IDLE (Ref. 71-00-00, ADJUSTMENT/TEST) for a minimum of two minutes.

(7)

Feather propeller.

(8)

Shut down engine (Ref. 71-00-00, ADJUSTMENT/TEST).

(9)

Repeat steps (1) through (3), preceding.

(10)

Remove main oil filter and clean, or replace with new one, (Ref. 79-20-02) according to type. Reinstall oil filter.

(11)

Remove reduction gearbox oil strainer and clean (Ref. 72-10-00). Reinstall strainer.

(12)

Reinstall engine chip detector and drain plugs, tighten and lockwire (Ref. Subpara. D.).

(13)

Repeat steps (5) through (8), preceding.

(14)

Check oil level and replenish, as necessary (Ref. Subpara. C.).

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6.

Preservation and Depreservation A.

General Preservation of engines in service depends on the period of inactivity and whether or not the engine may be rotated during the inactive period. An engine is considered inactive when it has not been operated either on the ground, or in flight for a minimum of ten minutes after the oil temperature has stabilized. The expected period of inactivity should be established and reference made to the Engine Preservation Procedures following. The preservation done should be recorded in the engine log book and on tags fastened to the engine. For an engine inactive in a severe environment such as extreme temperature changes, high humidity, dusty, polluted or salt laden atmosphere, it is recommended that the engine be preserved to the next higher schedule or the engine started and run for minimum of ten minutes more frequently. If an engine has been preserved to a certain schedule, (91 days to 1 year) and now the engine will be inactive for more than 1 year, the engine should be depreserved, inspected and tested according to the 91 days to 1 year instructions, and the engine removed and stored in an engine container.

B.

Fuel Control Unit (1)

Preservation of a fuel control unit depends on the period of inactivity and whether or not the FCU is operated during the inactive period. (a) A FCU is considered active if an engine is involved in normal flight operations or if an engine is wet motored or run during preservation periods. (b) A FCU is not considered active if an engine is not wet motored or run during aircraft inactive periods.

C.

(2)

For fuel control units that remain on inactive engines in long term container storage (off wing), the time accumulated in the container begins at the time of packaging.

(3)

For units that have been removed from the engine and are in storage three years or more, refer to 73-20-00, Maintenance Practices, Storage, Three Year Requirement.

(4)

For units that have been removed from the engine and are in storage more than six years, refer to 73-20-00, Maintenance Practices, Storage, Six Year Requirement.

(5)

For units on engines that are inactive for more than six months and that are not preserved, refer to 73-20-00, Maintenance Practices, Storage, Six Year Requirement.

Preservation (1)

Engines inactive 0 to 7 days. (a) If the engine was operated in a salt laden environment, do a compressor and CT desalination wash

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(b) Engine may remain inactive with no preservation protection provided engine is sheltered, humidity is not excessively high and there is not extreme temperature changes that may produce condensation (c) Install inlet and exhaust covers. (2)

Engines inactive 8 to 28 days. (a) Do 0 to 7 days procedures. (b) Place desiccant bags and humidity indicator (Ref. IPC) on wooden racks in engine exhaust duct only. (c) Seal off all engine openings. Make sure exhaust cover has suitable window to monitor humidity indicators. (d) Check relative humidity every two weeks if engine is stored outside, and every 28 days if engine is stored inside. Relative humidity should be maintained at 40 %. If humidity indicator turns pink, replace desiccant bags and indicator.

(3)

Engines inactive 29 to 90 days. (a) Do 0 to 7 days, and 8 to 28 days procedures. (b) Wash engine externally. (c) Do a compressor performance recovery/desalination wash and a CT rinse. (d) Examine all engine external protective coating, and touch-up/repair as necessary. (e) Lubricate all linkages (f)

Disconnect fuel inlet line to oil-to-fuel heater and connect suitable oil supply line to oil-to-fuel heater fuel inlet. Blank off disconnected fuel supply line.

(g) Disconnect fuel line at flow divider inlet to prevent oil from entering fuel manifold, and loosen line as required to permit drainage into a suitable container. CAUTION: UNDER NO CIRCUMSTANCES PERMIT PRESERVATIVE OIL TO ENTER ENGINE WHERE IT MAY COME INTO CONTACT WITH THERMOCOUPLE PROBE ASSEMBLY. OIL CONTAMINATION OF PROBES MAY CAUSE COMPLETE FAILURE OF THERMOCOUPLE SYSTEM. (h) Supply preserving oil (PWC05-077) at 5 to 25 psig at least 16°C (60°F). CAUTION: OBSERVE STARTER MOTOR OPERATING LIMITS (REF. STARTER MANUFACTURER’S MANUAL). (i)

With ignition system OFF, fuel condition lever to GROUND-IDLE and power control lever to TAKE-OFF, carry out normal motoring run until all preservative oil is displaced from system.

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(j)

After motoring run check to see if preservative oil is coming from opened fuel line. If not, repeat motoring cycle until preservative oil flows from opened fuel line.

(k) Return power control lever to GROUND-IDLE and fuel condition lever to OFF. Reconnect fuel supply to oil-to-fuel heater and fuel line to flow divider inlet. (l) (4)

Install caps, covers and plugs as necessary to prevent entry of foreign material and accumulation of moisture (Ref. Fig. 304).

Engines inactive for periods exceeding 90 days. (a) Do 0 to 7, 8 to 28 and 29 to 90 days procedures. CAUTION: OBSERVE STARTER MOTOR OPERATING LIMITS (REF. STARTER MANUFACTURER’S MANUAL). (b) Close normal fuel supply shutoff valve and motor engine with starter until oil pressure and Ng are indicated. Disengage starter. (c) Drain engine oil (Ref. SERVICING) (d) With drains open, motor engine (Ref. 71-00-00, ADJUSTMENT/TEST) to permit scavenge pumps to clear engine, indicated by stoppage of steady stream of oil from drains. To prevent excessive operation with limited lubrication, limit rotation to shortest possible time to accomplish complete draining. (e) Remove oil filter element (Ref. 79-20-02) and allow to drain. (f)

Let oil to drain to a slow drip, approximately one drip per half hour, then install oil filter and close drains.

(g) Remove covers from accessory drive pads and spray exposed surfaces and gearshafts with engine oil (PWC03-001). Replace cover plates. CAUTION: COMPOUND MUST NOT TO BE APPLIED TO ANY BOLT THREADS USED TO RETAIN ACCESSORIES. THESE THREADS MUST BE COATED WITH REGULAR ENGINE OIL AS REQUIRED BY NORMAL TIGHTENING PROCEDURES. UNDER NO CIRCUMSTANCES MUST THE COMPOUND BE USED IN, OR PERMITTED TO ENTER ANY AREA WHERE IT COULD CONTAMINATE THE ENGINE LUBRICATION SYSTEM (h) Coat all external flanges, bolts, and studs with compound (PWC09-003). In particular, pay special attention to the RGB and compressor inlet case flanges. (i)

Install caps, covers and plugs, as necessary to prevent entry of foreign material and accumulation of moisture (Ref. Fig. 304).

(j)

Tag oil filler cap with date of preservation and enter date and type of preservation in engine log book.

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(k) Install humidity indicator in air inlet and exhaust of engine compartment. Cover with suitable airtight moisture barrier. Provide inspection windows at each end for observation of humidity indicators. NOTE:

(5)

Inspection of a preserved unit should be carried out every two weeks if aircraft is stored outside, or every 30 days if aircraft is stored inside. If relative humidity, as indicated on humidity indicator, is less than 40 percent, no further action is required. If humidity indicated exceeds 40 percent, desiccant bags must be replaced or reactivated (Ref. Para. 7., E.).

Engines inactive for periods exceeding one year: (a) Do 0 to 7, 8 to 28, 29 to 90, and 91 days and over procedures. (b) Remove the engine, and store in storage container.

D.

Depreservation (1)

0 to 7 days: (a) No depreservation required.

(2)

8 to 28 days: (a) Remove covers from inlet and exhaust openings, and moisture barriers

(3)

(b)

Make sure all engine openings are clear and unobstructed.

(c)

Remove desiccant bags and racks if applicable.

29 to 90 days: (a) Do 8 to 28 days procedure. (b) Fill engine oil tank (Ref. SERVICING). CAUTION: UNDER NO CIRCUMSTANCES PERMIT PRESERVATIVE OIL TO ENTER ENGINE WHERE IT MAY COME INTO CONTACT WITH THERMOCOUPLE PROBE ASSEMBLY. OIL CONTAMINATION OF PROBES MAY CAUSE COMPLETE FAILURE OF INDICATING SYSTEM. (c) Disconnect fuel line at flow divider inlet to permit drainage into suitable container. (d) Connect aircraft fuel supply. (e) With ignition OFF, place power control lever to TAKEOFF and fuel condition lever to GROUND-IDLE.

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CAUTION: OBSERVE STARTER MOTOR OPERATING LIMITS (REF. STARTER MANUFACTURER’S MANUAL). (f)

Do a normal 30 second motoring run, during which time move power control lever to GROUND-IDLE and return to TAKEOFF, fuel condition lever to OFF and return to GROUND-IDLE until clean fuel flows from line.

(g) Connect fuel inlet line to flow divider, tighten all coupling nuts 90 to 100 lb.in. and lockwire. (h) Return power control lever to GROUND-IDLE and fuel condition lever to OFF. (4)

91 days and over: (a) Do 8 to 28 days procedure. (b) Examine all external cases for corrosion, and protective coating for wear. Repair as necessary. (c) Remove compressor inlet screen, and examine case and visible flanges for corrosion. If corrosion is found examine internals of AGB and RGB with borescope. (d) Slowly rotate the propeller by hand , and check for stiffness, audible scraping, binding or rubbing (Ref. Unscheduled Inspection). (e) Do 29 to 90 days procedures. (f)

Start the engine (Ref. 71-00-00, ADJUSTMENT/TEST), and do the following: Pre-operational Check Pre-start Check Wet Motoring Run Dry Motoring Run Engine Start FCU Checks Oil Pressure Check Engine Performance Check Acceleration Check Shutdown Checks Post-shutdown Checks NOTE:

During motoring, check for stiffness, audible scraping, binding and/or rubbing.

(g) After engine run, and completion of all checks, examine all drain valves for oil. If oil is found, send engine to an overhaul facility. (h) Examine fuel filters and clean or replace as necessary.

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(i)

7.

Examine oil filter, RGB oil strainer, and RGB and AGB chip detectors as applicable. If contamination is found, and the engine has no previous contamination history, send engine to an approved overhaul facility . Otherwise, refer to Chapter 79-20-02.

Storage and Shipping A.

Fiberboard Shipping Container The fiberboard shipping container, either engine, or PSM as applicable, comprises a wooden skid base, to which is fastened a metal cradle, with a fiberboard inner and outer sleeve forming the sides of the containers, and a fiberboard cover. Plywood sheeting provides additional support to the container sides and cover. The base, plywood supports, cradle and associated hardware are reusable; the fiberboard sleeve and cover are disposable. The container is intended for shipment in a closed conveyance on the North American continent, or overseas shipment by air and is not intended for shipment by sea. To avoid possible bearing damage such as brinelling, use of shipping container /skid with shock mounts is required for all transportation The fiberboard container is weather resistant only and should not be exposed to climatic conditions for more than seven days and must not be used for outdoor storage. It also offers protection against corrosion for a period of up to six months, provided that the container is correctly sealed and sheltered indoors in relatively dry areas and the color of humidity indicator is monitored every 15 days. For fiberboard engine shipping container data refer to Table 301.

B.

Metal Storage and Shipping Container The metal storage and shipping container is of steel construction, manufactured in two halves and joined at the horizontal centerline with a gasket between upper and lower halves to form a hermetic seal. The container is reusable and may be used for long term indoor and outdoor storage, provided humidity within is frequently checked, desiccant replenished as required and the engine preserved in accordance with the applicable preservation schedule. The metal container is not pressurized and an automatic, pressure activated, two-way breather valve serves to maintain pressure within the container, at or near prevailing ambient pressure. The breather valve operates whenever internal pressure exceeds ambient pressure by plus 2.0 to 2.5 psi or minus 1.0 to 1.5 psi. The service receptacle and cover can be removed (Ref. Fig. 301) to provide access to the desiccant cage for desiccant replenishment (Ref.IPC). At the other end of container, a rectangular recess is provided for storage of the engine log book, shipping instructions and other documents. For metal storage and shipping container data, refer to Table 302.

C.

Fiberboard Container Humidity Control To maintain internal conditions within the protective envelope at a safe humidity level for storage, a specific quantity of desiccant material is placed in the protective envelope. Each desiccant bag (Ref.IPC) contains eight units (one unit weighing one ounce (28.34 g)).

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A humidity indicator (Ref.IPC) is installed within the protective envelope and is visible through a window in the fiberboard casing. The moisture level can thus be checked without disturbing the container or its contents. At a safe humidity level (up to 40 percent relative humidity) the indicator color is blue. As humidity increases the color gradually changes to pink. An all pink color indicates that an unsafe moisture condition has been reached; the desiccant must then be replaced with freshly activated bags (Ref. Para. E. following). Twelve bags of desiccant are used in an engine fiberboard container, and eight bags in an engine metal container. NOTE: Humidity indicators have a reversible element allowing them to be reactivated and reused, provided the original all-blue color is evident. Indicators need not be replaced unless damaged. TABLE 301, Engine Fiberboard Shipping Container Data Description Length Width Height Weight

Data 81 inches (2057 mm) 29.5 inches (750 mm) 32.5 inches (826 mm) 312 lb. (142 kg)

TABLE 302, Metal Storage and Shipping Container Data Description

Data 90.8 inches (2305 mm) 34 inches (864 mm) 39 inches (965 mm) 400 lb. (181.4 kg) 10 psig SAE 1010=1020 (PWC13-002) (PWC07-005) or (PWC07-005A)

Length Width Height Weight Pressure Tested at Material Specification (Skin) Paint Primer (One Coat as per) Paint (Two Coats Enamal as per) D.

Metal Container Humidity and Pressure Control To maintain humidity within the metal container at a safe level for storage, a specific quantity of desiccant material is placed in the desiccant cage. Each desiccant bag contains 8 one-ounce units. A humidity indicator is installed in the service end of the cover, enabling the humidity level to be checked without disturbing the cover. Two viewing windows are provided adjacent to the humidity indicator.

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1 26

25

24

2

23 21

A

4

22

3 20 4

19 18 6

17

5

9 10 11 12 13

8

7

14 16

15 VIEW

A

C3921A Metal Storage and Shipping Container Components Figure 301 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 301 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25.

Top Cover Lifting Points Container Top Cover Container Base Engine Mount Pins Log Book Recess Cover Butterfly Nuts Container Gasket Drain Plug Nut Washer Preformed Packing Service Receptacle Collar Stud Square Headed Plug Service Receptacle Cover Nut and Washer Breather Valve Bolt Nuts Lockwashers Locating Pins Desiccant Cage Bolt Humidity Indicator Observation Window

A drain plug is located in the container base just below the service receptacle cover. At a safe humidity level (up to 40 percent humidity), indicator color is blue. As humidity increases, the color gradually changes to pink. An all pink color indicates that an unsafe humidity level exists. Replace the desiccant bags with freshly activated bags (Ref. Subpara. E.). Retain the desiccant bags for reactivation. E.

Reactivation of Desiccant and Humidity Indicator (1)

Place bags of desiccant and humidity indicator (Ref.IPC) in a suitable oven controlled at 121°C (250°F). The humidity indicator may be removed when an all blue color has been attained. The desiccant bags should remain in the oven for two hours minimum.

(2)

Allow oven to cool to room temperature (approximately 22°C (72°F)), and then remove bags and indicator as applicable.

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(3)

Immediately place desiccant bags in airtight polyethylene envelopes. Exclude all air and heat seal envelopes. NOTE: 1. Desiccant bags must be removed from plastic bags prior to installation in shipping/storage container. NOTE: 2. Do not place desiccant bags on or near the compressor inlet to avoid possible ingestion of desiccant particles by the engine.

F.

Precautions - Removal / Installation of Engine in Metal Container (1)

When an assembly is to be removed from, or installed in a shipping container, the following precautions must be taken. (a)

Before removing an engine from a metal container, slowly loosen square headed plug (14, Fig. 301) in the service receptacle to allow the pressure to equalize.

(b) Make sure a hoist of sufficient lifting capacity, plus safety factor, is available to lift loads as follows: 1

A load of 475 lb. (215 kg) when lifting engine only.

2

A load of 800 lb. (363 kg) when lifting engine loaded in a fiberboard engine shipping container.

3

A load of 1000 lb. (455 kg) when lifting engine loaded in a metal engine shipping container.

(c) Place container or assembly correctly on floor, directly beneath hoist. (d) Allow free overhead space of at least 6 feet (2 meters), exclusive of distance from the top of the container or assembly to the hook. G. Precautions - Removal / Installation of Engine in Fiberboard Container (1)

When an assembly is to be removed from, or installed in a shipping container, the following precautions must be taken.

(2)

Ensure a hoist of sufficient lifting capacity plus safety factor is available to lift the following loads: (a) 475 lb (215 kg) engine only. (b) 800 lb (363 kg) engine loaded in fiberboard container.

(3)

Ensure container is correctly positioned on floor directly beneath hoist.

(4)

Ensure that a clear overhead space of at least eight feet, not including distance from top of container to hoist hook, is available.

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H.

Storage of Engine (1)

Fiberboard Container: (a) An engine can be stored in a fiberboard container, under dry conditions, for up to six months. A periodic check must be carried out at least once every seven days to determine if humidity is reaching an unsafe level. When the indicator changes to a partially pink color, remove engine from container and protective envelope (Ref. Para 8. A.). (b) Replace old desiccant with bags of freshly activated desiccant, and reinstall engine in container (Ref. Para 8. C.).

(2)

Metal Container: (a) When an engine is stored in a metal container, the color of the humidity indicator should be checked every seven to fifteen days, depending upon the ambient relative humidity. For removal of defective humidity indicator, refer Para 8. B. and for installation of humidity indicator, refer Para 8. D.

I.

Stacking Containers for Storage (1)

Instructions outlined in Table 303 and 304 must be followed when stacking empty containers or engines in containers or power section/power section modules. TABLE 303, Stacking Limitations - Engine Shipping Container METAL CONTAINER

FIBERBOARD CONTAINER

Limits

Precautions

Limits

Precautions

Engine in Container Three high max.

Make sure that containers are sound and in undamaged condition.

Engine in container Two high Max. (Static Storage) One high Max. (Shipping/ Transporting)

Replace used sleeve with new sleeve and cover.

Empty Container Four high Max.

Only static (no impact) and superimposed stacking recommended. Avoid dropping containers over each other.

Empty container Four high Max.

Make sure wooden side stiffeners (where fitted) are sound and undamaged. Only static (no impact) and superimposed stacking is recommended. Avoid dropping containers over each other.

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TABLE 304, Power Section/PSM Shipping Container Stacking Limitations Container

8.

Limits

Precautions

with PS/PSM

Two high Max. (Static Storage) One high Max. (Shipping/Transporting)

without PS/PSM

Four high Max.

Only static (no impact) and superimposed stacking is recommended. Avoid dropping containers over each other.

Removal/Installation of Engine from/in Shipping Container A.

Remove Engine from Fiberboard Container

CAUTION: IF ENGINE IS DROPPED, IN CONTAINER OR OTHERWISE, SHIP ENGINE TO AN OVERHAUL FACILITY. (1)

Remove strapping (3, Fig. 302) from around fiberboard container. Retain reinforcing corners (2). Remove tape, cover (1), support (14), and sleeves (5 and 7) with plywood supports (4) from base (9).

(2)

Cut protective envelope (11) and expose top of engine.

CAUTION: DO NOT USE SLING AND LIFTING BRACKETS TO LIFT ENGINE ATTACHED TO SKID BASE. (3)

Install sling (1,PWC51861-100, Fig. 303) on hoist with lifting eye of sling adjusted to enable horizontal engine lift.

(4)

Attach sling to engine lifting brackets (2 and 3) at flanges A and G respectively.

(5)

Observe caution preceding step (3), take weight of engine on sling, and remove engine mount pins (5).

(6)

Maintain engine horizontal and raise until clear of cradle; remove engine front mount brackets (7) and engine rear mount bracket (10) together with associated hardware from engine.

(7)

Install engine front mount brackets (7) and engine rear mount bracket (10) on cradle with pins (5). NOTE:

Retain associated hardware, place in bag and fasten to cradle. Retain cradle, skid base and associated hardware for reuse.

(8)

Remove ignition exciter, complete in protective envelope (11), from container and retain with engine.

(9)

Remove desiccant bags from engine and retain for reactivation and reuse. NOTE:

Retain desiccant bag in ignition exciter protective envelope until unit is required for use. When unit is removed, desiccant bag should be reactivated for reuse (Ref. Para. 7. E.).

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B.

(10)

Remove envelopes containing shipping and engine documents from box attached to skid base.

(11)

Remove all shipping caps, covers and plugs from engine (Ref. Fig. 304).

(12)

Retain moisture barrier/protective wrapping on engine air-inlet screen until engine is installed in airframe.

Remove Engine from Metal Container CAUTION: IF THE ENGINE IS DROPPED, IN THE CONTAINER OR OTHERWISE, RETURN THE ENGINE TO AN OVERHAUL FACILITY. (1)

Remove nuts and washer (16, Fig. 301) attaching the service receptacle cover (15) to the service receptacle (12) and remove the cover.

(2)

Slowly loosen the square headed plug (14) on service receptacle (12) to equalize the air pressure. Make sure air pressure is equalized before proceeding.

(3)

Remove 40 nuts (19), lockwashers (20) and bolts (24) attaching the container top cover (2) to the container base (3).

(4)

Lift the container top cover (2) vertically to clear the locating pins (21) with the hoist attached to the lifting points (1). Rest the container top on clean wooden blocks.

(5)

Attach the sling (2, Fig. 305) to the engine lifting brackets (1 and 3) at flanges A and G.

CAUTION: DO NOT USE THE ENGINE SLING AND HOIST FITTINGS TO LIFT THE ENGINE ATTACHED TO THE METAL CONTAINER BASE. (6)

Take the engine weight on the sling and remove the pins (4) from the engine front mounting brackets (15).

(7)

Raise the engine slowly from the container; make sure the engine remains horizontal and is not permitted to swing.

(8)

Remove the two engine front mount brackets (15), rear mount bracket (5), bolts and washers from the engine mount pads. Retain the brackets and bolts in a suitable cloth or polyethylene envelope and attach to the cradle.

(9)

Remove desiccant bags from the desiccant cage and retain for reactivation and reuse.

(10)

Remove the butterfly nuts (6, Fig. 301) and cover (5). Withdraw the engine log book and documents from the receptacle. Replace the cover and nuts.

(11)

Remove bolts and nuts (8, Fig. 305) attaching ignition exciter (12) to cradle (11); remove ignition exciter and retain with engine. Retain nuts and bolts in a suitable cloth or polyethylene envelope and attach to the cradle.

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1 2

3 14 13 12

4 5

5

6

7

8 9

11 10

C13935 Engine Shipping Container Figure 302 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 302 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14.

C.

Container Cover Reinforcing Corner Strapping (PWC05-063) Plywood Sleeve Support Sleeve (inner) Envelope Gasket Sleeve (outer) Cradle Skid Base Ignition Exciter and Mounting Base Protective Envelope Humidity Indicator Pressure Sensitive Tape (PWC05-070) Plywood Support (cover)

(12)

Remove all shipping covers, caps, plugs and the T5 trim lead tiedown strap from the engine. Retain the covers, caps, plugs and the T5 trim tiedown strap in a suitable cloth or polyethylene envelope and attach to the cradle.

(13)

Clean the interior of the container.

(14)

Replace the container top and attach with 40 nuts, lockwashers and bolts.

(15)

Coat all exposed hardware with preservative compound (PWC06-012).

(16)

Retain the moisture barrier/protective wrapping on the engine air inlet screen until the engine is installed in the airframe.

Install Engine in Fiberboard Container CAUTION: MAKE SURE OIL HAS BEEN COMPLETELY DRAINED FROM ENGINE. (1)

With engine mounted in stand (Ref. Para. 9.) and engine preservation completed (Ref. Para. 6.), fit all blanking covers, plugs and caps (Ref. Fig. 304).

(2)

Install moisture barrier/protective cover on air-inlet screen with pressure sensitive tape (PWC05-070). NOTE:

Moisture barrier/protective cover may be of polyethylene sheet, aluminum foil, cotton-backed material or waxed paper.

(3)

Make sure cradle and skid base are serviceable and new or serviceable fiberboard sleeve and lid are available.

(4)

Remove engine from stand (Ref. Para. 9.).

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1

2

3

4 9 5

7

6

8

10 5

9 6

11

C811B Removal/Installation of Engine from/in Fiberboard Container Figure 303 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 303 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11.

Sling (PWC51861-600) Engine Front Lifting Bracket Engine Rear Lifting Bracket Protective Envelope Engine Mount Pins (lanyard attached) Bolts Engine Front Mounting Brackets Container Cradle Washer Engine Rear Mounting Bracket Ignition Exciter and Protective Envelope

CAUTION: DO NOT USE STANDARD COMMERCIAL HARDWARE TO FASTEN ENGINE SUPPORT BRACKETS TO ENGINE OR CONTAINER. USE OF HARDWARE OF LOWER STRENGTH THAN SPECIFIED COULD CAUSE SERIOUS ENGINE DAMAGE DURING SHIPPING. (5)

Remove ignition exciter, if applicable, and fasten ignition cables to engine with adjustable tiedown straps. Make sure cable and protective caps are fastened with pressure sensitive tape (PWC05-070).

(6)

Make sure interior of protective envelope is free of dirt, oil, water or other contaminants.

(7)

Install engine in new protective envelope (4, Fig. 303) aligning gaskets with lower engine mounting pads on each side of engine and accessory gearbox mounting pad.

(8)

Attach engine front mount brackets (7) to lower engine mounting pads on each side of gas generator case with bolts (6) and washers (9). Tighten bolts and torque 225 to 250 lb.in.

(9)

Attach engine rear mount bracket (10) to mounting pad at 6 o’clock position on accessory gearbox, with bolts (6) and washers (9). Tighten bolts and torque 50 to 70 lb.in.

(10)

Place engine log book, log sheets and other relevant documents to be shipped with engine, in a waterproof envelope and seal with pressure sensitive tape (PWC05-070). Insert envelope in box fastened to skid base and seal box.

CAUTION: MAKE SURE THAT ENGINE SHIPPING CONTAINER HAS BEEN MODIFIED (POST-SB3032) TO ACCOMODATE ENGINES WITH P3 AIR FILTER (POST-SB3012). (11)

Lower engine to cradle (8, Fig. 303) and fasten engine front and rear mount brackets (7 and 10) to clevis on cradle with three (lanyard attached) engine mount pins (5).

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6

7

8

9

11 12

10

13

41 42 43

2 3 4 16

5

46 44

17

18

19

13

14 15

21 22 23

20

24 18

25

27

28

26

33 34

35 36

37 38

29 30 31 32 45

39 40

C67242 Shipping Caps, Covers and Plugs (Typical) Figure 304 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 304 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25.

Engine Shipping Container (Ref. Fig. 302) Propeller Shaft Shipping Cover Bolt Washer Nut Overspeed Governor Drive Cover Exhaust Port Shipping Cover Bolt Washer Nut Engine Center Mount Shipping Cover Bolt Oil-to-cooler and Oil Return Shipping Cap Protective Cap Adjustable Tie-down Strap Case Drain Shipping Caps Tachometer-Generator Shipping Cover Torque Transmitter Boss Shipping Plug Torquemeter Oil and Dump Valve Drain Shipping Cap Starter-generator Mount Shipping Cover Oil Vent Shipping Cover Bolt Washer Electrical Connector Shipping Cover Oil Temperature and Fuel Vent Shipping Plug

26. 27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40. 41. 42. * 43. 44. 45. 46. *

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Oil-to-fuel Heater Shipping Plug Desiccant (8 unit bags) Container Assembly (Ref. Fig. 302) Box Shipping Data Envelope Engine Log Book Engine Log Book Envelope Packing Instruction Envelope Shipping Container Instructions Bolt Lockwasher Electrical Connector Shipping Cap Desiccant (4 unit bag) Bolt Washer Cabin Air Outlet Cover Bolt Cabin Bleed Air Adapter Cover Compressor Inlet Screen Cover Gasket (For use with customer adapter) Compressor Bleed Valve Cover Used instead of item 41 and 42 if engine is shipped with cabin bleed air adapter fitted.

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3 1

4 5

15

4

14 10

11 12

6

13

7

13

8 9

C3922B Removal/Installation of Engine in Metal Container (Typical) Figure 305 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 305 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15.

Engine Front Lifting Bracket Engine Sling Engine Rear Lifting Bracket Engine Mount Pins (lanyard attached) Engine Rear Mount Bracket Bolts and Washers Engine Rear Support Bolt, Washer and Nuts Service Cover Desiccant Cage Cradle Ignition Exciter Engine Side Support Bolts and Washers Engine Front Mount Brackets

(12)

Install humidity indicator (Ref. IPC) in protective envelope, in correct position to be visible through fiberboard sleeve window.

(13)

Remove sling and hoist from engine.

CAUTION: REMOVE DESICCANT BAGS FROM THEIR PROTECTIVE ENVELOPES BEFORE INSTALLATION. CAUTION: DO NOT PLACE DESICCANT BAGS ON OR NEAR THE COMPRESSOR AIR INLET TO AVOID POSSIBLE INGESTION OF DESICCANT PARTICLES BY THE ENGINE. (14)

Tie freshly activated desiccant bags (Ref. IPC) to engine, evenly disposed over engine length, six on each side.

(15)

Heat seal along top of envelope, using suitable hand-held sealing iron, leaving one corner open to evacuate air. Evacuate air, fold corner and seal.

(16)

Place ignition exciter, with shipping caps installed, in protective envelope. Insert one 4-unit desiccant bag in envelope. Seal envelope leaving one corner open, evacuate air from envelope, fold corner and complete heat sealing. Secure exciter and envelope to skid base with tape.

(17)

Install fiberboard sleeves (5 and 7) and plywood supports (4) over engine and fit in position on skid base (9) (Ref. Fig. 302).

(18)

Fold engine envelope and make sure humidity indicator aligns with window in sleeve. Fasten envelope folds with pressure sensitive tape (13).

(19)

Close flaps of sleeve and seal with pressure sensitive tape (13).

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D.

(20)

Place plywood support (14) and cover (1) on sleeve, fold flaps down and seal at each corner with pressure sensitive tape (13).

(21)

Install cover horizontally with strap (3) and four metal reinforcing corners (2).

(22)

Install cover and sleeve to skid base with straps (3) and reinforcing corners (2).

Install Engine in Metal Container CAUTION: MAKE SURE OIL HAS BEEN COMPLETELY DRAINED FROM ENGINE. (1)

With engine mounted in stand and engine preservation completed (Ref. Para. 6.), fit all blanking covers, plugs and caps (Ref. Fig. 304).

(2)

Locate the moisture barrier/protective cover around the air-inlet screen, making sure there is adequate overlap and full coverage of the screen. Secure the cover with pressure-sensitive tape (PWC05-070). NOTE:

The moisture barrier/protective cover may be made of polyethylene sheet, aluminized cotton-backed material or waxed paper.

(3)

Install moisture barrier/protective cover over compressor bleed valve exhaust housing. Secure with pressure sensitive tape.

(4)

Make sure the interior and exterior of the metal container top and bottom halves are clean, dry and free of damage. Make sure a new gasket (7, Fig. 301) is available.

(5)

Install ignition exciter (12, Fig. 305) with flanged mount pad on cradle (11) structure; secure with bolts, washers and nuts (8) and torque 32 to 36 lb.in.

(6)

Attach sling to hoist and adjust sling lifting eye to provide horizontal engine lift.

(7)

Secure sling legs to engine lifting bracket (2 and 15, Fig. 306).

(8)

Remove the engine from the stand (Ref. Para. 9.).

(9)

Install center mount shipping covers ( (11, Ref. Fig. 304)) to engine upper center mount pad each side of engine and secure covers with four bolts.

CAUTION: DO NOT USE STANDARD COMMERCIAL HARDWARE TO SECURE THE ENGINE SUPPORT BRACKETS TO THE ENGINE OR CONTAINER. USE OF HARDWARE OF LOWER STRENGTH THAN SPECIFIED COULD CAUSE SERIOUS DAMAGE DURING SHIPPING. (10)

Remove the two engine front mount brackets (15, Fig. 305) from the container and secure the brackets to the engine front lower mount pads on each side of the engine with eight bolts (14) and washers. Torque the bolts 225 to 250 lb.in.

(11)

Remove the engine rear mount bracket (5) from the cradle and secure the bracket to the engine rear mount pad with three bolts (6) and washers. Torque the bolts 50 to 70 lb.in.

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(12)

Carefully lower the engine onto the cradle (11); secure the front and rear mount brackets to the cradle with pins (4).

CAUTION: WHEN REACTIVATED DESICCANT BAGS ARE USED, REMOVE THE BAGS FROM THE PROTECTIVE ENVELOPES.

9.

(13)

Insert desiccant into the desiccant cage and secure door with lockwire. Install the cover and secure. Reuse of the humidity indicator (25, Fig. 301) should be satisfactory, since the element is reversible. Replace only if necessary (Ref. IPC).

(14)

Liberally coat the new gasket (7) with anti-sticking compound (PWC09-003) and install the gasket in position on the mating flange of container base.

(15)

Lift the top cover of the container into position using the hoist and sling from the lifting points (1). Lower the top cover over the locating pins (21).

(16)

Secure the top cover to the container base using 40 bolts (24), lockwashers (20) and nuts (19). Torque bolts 270 to 300 lb.in.

(17)

Coat all exposed hardware with preservative compound (PWC06-012).

(18)

Place the engine log book and relevant shipping documents in rectangular recess in container base. Install the cover (5) secure with nuts (6) and lockwire.

(19)

Stencil the engine model, serial number, rubber cure date and pertinent preservation and inspection dates on the white panel adjacent to the humidity indicator.

(20)

Make sure the service receptacle cover (1) is secure, lockwired and lead sealed.

Removal/Installation of Engine from/in Maintenance Stand A.

Removal (1)

Attach sling (1,PWC51861-600, Fig. 306) to engine lifting brackets (2 and 3) and take up slack on hoist. NOTE:

Adjust lifting eye on sling to maintain engine horizontal during lifting operations.

(2)

Remove bolts (8), washer (9) and engine mounting brackets (7 and 11, PWC71416) from stand adapter (12, PWC34752).

(3)

Carefully lift engine clear of stand (5, PWC34300).

(4)

Remove bolts (4) and engine mounting brackets (7 and 11, PWC71416) from engine.

(5)

Stow brackets, adapters and bolts on stand.

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14

13

11

12

9

8 1

10 3 VIEW

A

2

A

4

7

5

6

C161263 Removal/Installation of Engine from/in Stand Figure 306 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 306 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. B.

10.

Engine Sling (PWC51861-600) Front Lifting Bracket Rear Lifting Bracket Bolt Engine Stand (PWC34300) Engine Mount Disc Engine Mount Bracket (PWC71416) Bolt Washer Bolt Engine Mount Bracket (PWC71416) Engine Mount Adapter (PWC34752) Washer Nut

Installation (1)

Coat threads of bolts (4, Fig. 306) with oil (PWC03-001), and install mount brackets (7 and 11, PWC71416) to engine mounting pads, with bolts (4). Tighten 275 to 300 lb.in.

(2)

Install adapter (12, PWC34752) to inner face of each mounting disk (6) on stand (5, PWC34300) with bolts (10), washers (13) and nuts (14), so that extension on adapter lies in horizontal plane. Tighten nuts and bolts with standard torque values (Ref. 70-00-00, STANDARD PRACTICES, Standard Torques).

(3)

Position stand (5, PWC34300) directly under engine, and carefully lower engine into stand. Install brackets 7 and 11, (PWC71416), with first and third holes to adapters (12, PWC34752), with bolts (8) and washers (9). Tighten bolts with standard torque values (Ref. 70-00-00, STANDARD PRACTICES, Standard Torques).

(4)

Remove the sling (1, PWC51861-600) from the engine.

Removal/Installation of Power Section/Power Section Module (PS/PSM) in Maintenance Stand A.

Removal (1)

Locate sling mounting plate (10, Fig. 307) on propeller mounting flange (9). Align two dowels on flange with corresponding holes in plate, and install four screws (11) from rear of mounting flange.

(2)

Attach hoist (1) to lifting eye (2) on sling (18, PWC37073 or PWC70099), and take up slack on hoist to support weight of PS.

(3)

Remove 12 nuts (4) and bolts (5) attaching power section to mount ring (3).

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14

15

8

16

VIEW

A 1 2

A

12

3

18

5

4

7 6 10

9 11

8

17 13

C160098 Removal/Installation - Power Section from/in Stand (Typical) Figure 307 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 307 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. (4) B.

Hoist Lifting Eye Mount Ring (PWC30269) Nut Bolt Washer Screw Adapter (PWC34752) Propeller Mounting Flange Mounting Plate Screws Power Section/Power Section Module Stand (PWC34300) Nut Washer Bolt Reduction Gearbox Sling (PWC37073 or PWC70099)

Carefully withdraw power section (17) from mount ring (3).

Installation (1)

Remove Py tubing (Ref. 73-10-08), pressure and scavenge oil tubing (Ref. 79-20-01), and propeller reversing linkage (Ref. 76-10-00), to allow attachment of mount ring (4, Fig. 307).

(2)

Install adapters (8, PWC34752, 307) to stand (13, PWC34300) with four bolts (16), washers (15) and nuts (14). Tighten the nuts.

(3)

Position mount ring (3, PWC30269) in stand (13, PWC34300) with front face against rear face of adapters (8, PWC34752). Align and attach mount ring (3) to bracket with three washers (6) and screws (7). Tighten the screws.

(4)

Lower power section to align flange C with cutout in mount ring (3). Carefully position power section so that flange C is in contact with mount ring.

(5)

Attach power section (12) to mount ring (3) with 12 nuts (4) and bolts (5)..

(6)

Lower hoist to transfer power section weight to stand (13). Remove sling (18, PWC37073 or PWC70099) from propeller shaft flange.

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ENGINE, TURBOPROP - REMOVAL/INSTALLATION 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire, unless otherwise specified, shall comply with specification AMS5687, 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

PWC09-005 PWC11-002 PWC11-014

Compound, Jointing (Use PWC11-014) Alcohol, Isopropyl

Special Tools The special tools listed below are used in the following procedures. Tool No.

Name

PWC30800 PWC30269

DELETED Mount Ring, Engine Stand Sling

PWC30338 PWC32052 PWC32420 PWC34000 PWC34073 PWC34300 PWC34752 PWC50066 PWC51140 PWC51861-600 PWC70099

Adapter, Mount Ring DELETED Sling, Power Section with prop Sling, Power Section without prop Stand, Engine Adapter Sling, Engine DELETED Sling, Engine Sling, Power Section without prop

Application

Replaced by PWC70652 and PWC70653 Replaced by PWC34752 Replaced by PWC70104 Replaced by PWC70099

Replaced by PWC51861-600

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Tool No.

Name

PWC70104

Sling, Power Section with prop Sling, Power Section with prop Sling, Power Section with prop DELETED

PWC70652 PWC70653 PWC70907 4.

Application

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation of Engine A.

Removal of Engine from Airframe

CAUTION: IF ENGINE IS DROPPED, IN CONTAINER OR OTHERWISE, SHIP ENGINE TO AN APPROVED OVERHAUL FACILITY. (1)

Remove propeller and engine-mounted airframe-supplied accessories from engine (Ref. Aircraft Maintenance Manual).

CAUTION: ON AIRFRAMES WHERE IGNITION EXCITER IS MOUNTED ON ENGINE MOUNT STRUCTURE, THE EXCITER MUST BE REMOVED WITH THE ENGINE AND NOT LEFT CONNECTED TO AIRFRAME INPUT LEADS. (2)

Remove engine from airframe (Ref. Aircraft Maintenance Manual) with sling (PWC51861-600) and suitable hoist. NOTE:

B.

After removal of engine from airframe, install correctly in shipping container if engine is to be shipped to an overhaul facility, or in engine stand if heavy maintenance is to be done (Ref. SERVICING).

Installation of Engine in Airframe (1)

Install engine-mounted airframe-supplied accessories (Ref. Aircraft Maintenance Manual).

(2)

Install engine in airframe (Ref. Aircraft Maintenance Manual), with sling (PWC51861-600) and suitable hoist. NOTE:

(3)

Where ignition exciter is airframe mounted, install unit in accordance with Aircraft Maintenance Manual.

Install propeller on engine (Ref. Aircraft Maintenance Manual).

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6.

Removal/Installation of Power Section/Power Section Module (PS/PSM) with Propeller Installed A.

Procedure CAUTION: PS/PSM MUST NOT BE LEFT IN SLING OVERNIGHT OR FOR LONGER PERIOD. REMOVE PROPELLER AND INSTALL PS/PSM IN STAND (REF. SERVICING). (1)

Drain oil (Ref. SERVICING).

(2)

Disconnect coupling nut of governor air tube (5, Fig. 401) from bulkhead coupling (9).

(3)

Disconnect electrical connections to engine-mounted accessories on reduction gearbox, as necessary (Ref. Aircraft Maintenance Manual).

(4)

Remove cotterpin, nut, bolt and spacer fastening clevis end of push-pull terminal (3) to propeller reversing lever (17).

(5)

Remove cotterpin, nut, washers, spacer and bolt fastening propeller governor interconnect rod (4) to reset arm on propeller governor (1).

(6)

Release locknut (7) fastening front swivel joint (6) of propeller reversing linkage to front lifting bracket.

(7)

Remove inner nut and bolt and slacken outer nut and bolt fastening swivel joint retaining plate to front lifting bracket. Swing retaining plate and lift forward end of propeller reversing linkage clear of front lifting bracket. Suitably support linkage.

(8)

Remove alumel and chromel bolts (Pre-SB3114) or nuts (Post-SB3114) fastening T5 trim thermocouple wiring harness to T5 thermocouple terminal block at flange C. Remove wiring harness lugs. Temporarily fasten T5 trim harness and airframe leads to terminal block.

(9)

Attach sling (PWC34000) or (PWC70104) or (PWC30338) or (PWC70652 and PWC70653) to center line hole on front lifting bracket with ball-lock pin. Take up slack on hoist. NOTE:

(10)

Figure 401 shows different sling attached to propeller flange as for removal without propeller installed.

Remove nuts and bolts at flange C and separate PS/PSM from gas generator module (GGM). Using sling, partially withdraw PS/PSM.

CAUTION: DO NOT ROTATE OR DISTURB INTERSTAGE SEALING RINGS ON COMPRESSOR TURBINE STATOR HOUSING UNLESS REMOVING FOR INSPECTION (REF. 72-50-01). (11)

Cap all tubes (12) and install plugs on couplings (13).

(12)

Withdraw PS/PSM from GGM and retain in sling or install in maintenance stand, as applicable.

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3

2

6

4

7

8

9

10

5

1

11

12 17

16

15

14

18 13

C384B Removal/Installation of Power Section/Power Section Module (PS/PSM) Figure 401 (Sheet 1 of 2) P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 401 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18.

Propeller Governor Sling (Propeller-not-installed type shown) Reversing Linkage Front Clevis Governor Interconnect Rod Coupling Nut Swivel Joint Locknut Flange C Bulkhead Coupling Center Fireseal Engine Stand (PWC34300) Oil Transfer Tubes (Scavenge/Pressure) Flange C External Couplings (Scavenge/Pressure) Drain Plug Reduction Gearbox Sling Mounting Bolts Propeller Reversing Lever Sealing Ring

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

750 POUNDS−MAXIMUM LIFT INCLUDING PROPELLER

EYE ASSEMBLY

SLING ASSEMBLY SLEEVE

BALL−LOC PIN ENGINE FRONT LIFTING BRACKET

C41030 Removal/Installation of Power Section/Power Section Module (PS/PSM) Figure 401 (Sheet 2) P&WC Proprietary Information. Subject to the restrictions on the title page.

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7.

(13)

For Pre-SB3337 Engines: Remove sealing compound residue, if used, from flanges of gas generator case and exhaust duct with solvent (PWC11-002) or (PWC11-014).

(14)

For PT6A-42A and Post-SB3337 Engines: Remove and discard gas generator/power section sealing ring (18).

(15)

Install suitable protective cover over GGM and PSM openings.

Removal of Power Section/Power Section Module (PS/PSM) with Propeller Removed A.

Procedure (Ref. Fig. 401) (1)

Drain oil (Ref. SERVICING).

(2)

Disconnect coupling nut of governor air tube (5) from bulkhead coupling (9) (Ref. 73-10-08) and cap coupling and line.

(3)

Disconnect electrical connections to engine-mounted accessories on reduction gearbox, as necessary .

(4)

Remove cotterpin, nut, bolt and spacer fastening clevis end of push-pull terminal (3) to propeller reversing lever (17).

(5)

Remove cotterpin, nut, washers, spacer and bolt fastening propeller governor interconnect rod (4) to reset arm on propeller governor (1) (Ref.76-10-00).

(6)

Release locknut (7) fastening front swivel joint (6) of propeller reversing linkage to front lifting bracket.

(7)

Remove inner nut and bolt and slacken outer nut and bolt fastening swivel joint retaining plate to front lifting bracket. Swing retaining plate and lift forward end of propeller reversing linkage clear of front lifting bracket. Suitably support linkage.

(8)

Remove alumel and chromel bolts (Pre-SB3114)s or nuts (Post-SB3114) fastening T5 trim thermocouple wiring harness to T5 thermocouple on gas generator case. Remove wiring harness lugs. Temporarily fasten trim harness and airframe wiring to T5 terminal block.

(9)

Locate sling (2 PWC34073 or PWC70099) on propeller mounting flange and engage four dowels in flange bolt holes. Attach sling to flange A to prevent PS/PSM rotation.

(10)

Remove nuts and bolts from flange C (8) and using sling, partially withdraw PS/PSM from gas generator module (GGM).

(11)

Cap all tubes (12) and install plugs on couplings (13).

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CAUTION: DO NOT ROTATE OR DISTURB INTERSTAGE SEALING RINGS ON CT STATOR HOUSING UNLESS THEY ARE TO BE REMOVED FOR INSPECTION (REF. 72-50-01). (12)

Withdraw PS/PSM from GGM and retain in sling or install in maintenance stand, as applicable. NOTE:

8.

When removing PS/PSM from engine mounted in airframe, PS/PSM should be mounted in engine stand (PWC34300), with mount ring (PWC30269) and adapters (PWC32052) or (PWC34752) (Ref. SERVICING).

(13)

Remove sealing compound residue, if used, from flanges of gas generator case and exhaust duct using solvent (PWC11-002) or (PWC11-014).

(14)

Install suitable protective cover over GGM and PSM openings.

Installation of Power Section/Power Section Module (PS/PSM) A.

General Whenever a replacement power section is installed on an engine at maintenance, the original power turbine vane and interstage baffle assembly should be retained and installed on the new power section whenever possible. This is to maintain vane throat area match between compressor turbine and power turbine vanes, which can affect operating parameters of the engine if altered.

B.

Procedure (1)

Install appropriate sling (2, Fig. 401) on PS/PSM; using hoist take weight of PS/PSM and remove from stand (10).

(2)

Remove caps from pressure and scavenge oil tubes (12) and install new preformed packings on tubes.

(3)

Remove plugs from couplings (13) at flange C on PS/PSM.

(4)

Examine mating areas of GGM and PS/PSM for cleanliness and security of parts; remove any protective covers installed during maintenance period.

(5)

Check and centralize a new interstage sealing ring on compressor turbine stator housing; this may be accomplished by inserting a piece of beeswax of suitable size, in groove at 12 o’clock position in housing to prevent ring dropping to bottom of groove. Ensure ring is in same position noted at disassembly.

(6)

For Pre-SB3337 Engines: Apply light film of jointing compound (PWC09-005) to mating flanges of gas generator case and exhaust duct.

(7)

For PT6A-42A and Post-SB3337 Engines: Install a new sealing ring (18) in gas generator flange C (8) locating diameter. NOTE:

The seal ring is a crush type ring and should not be used twice.

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CAUTION: CHECK FLANGE C OF GGM AND EXHAUST DUCT ARE PARALLEL AND AXIALLY ALIGNED. IF ASSEMBLIES DO NOT MATE FREELY, DO NOT USE FORCE. WITHDRAW PS/PSM AND CHECK FOR CAUSE OF INTERFERENCE. (8)

Using hoist, move PS/PSM carefully into position on GGM. Align pressure and scavenge oil tube couplings with respective tubes at rear of engine, and mate PS/PSM and GGM at flange C. NOTE:

(9)

Make sure SB3013 is complied with.

Install bolts, through mating flanges with bolt heads rear. Fit T5 thermocouple wiring harness loop clamps, governor pneumatic tube clamp bracket to flange C (Ref. Fig. 402 and IPC). Install clamps and bolts with self-locking nuts. Tighten nuts in diametric sequence 36 to 40 lb.in. Wipe off excess sealant and allow joint to set for minimum of two hours or as defined by sealant manufacturer’s instructions.

(10)

Remove sling from propeller mounting flange or front lifting bracket, as applicable.

(11)

Remove bolts (Pre-SB3114) or self-locking nuts (Post-SB3114) temporarily securing T5 trim harness and airframe thermocouple lead to T5 thermocouple terminal. Connect terminal lugs of T5 thermocouple wiring harness, T5 trim harness and airframe thermocouple lead to appropriate terminal posts on the terminal and secure with bolts or nuts. (a) For Pre-SB3114 Engines: tighten and torque bolt at alumel terminal 25 to 30 lb.in. and bolt at chromel terminal 20 to 25 lb.in. (b) For Post-SB3114 Engines: tighten and torque nut at alumel terminal 10 to 15 lb.in. and nut at chromel terminal 8 to 12 lb.in. (Ref. 77-20-01)(Ref. 77-20-01).

(12)

Connect coupling nut (5, Fig. 401) at rear end of governor pneumatic tube to bulkhead fitting (9) at center fireseal mount ring (10) (Ref.73-10-08). Tighten coupling nut 90 to 100 lb.in., and lockwire.

(13)

Install front swivel joint (6) of propeller reversing linkage in slot of front lifting bracket. Swing retaining plate over swivel joint and install inner bolt and nut (Ref.76-10-00). Tighten inner and outer nuts 32 to 36 lb.in. Tighten front swivel joint locknut (7) 200 to 225 lb.in., and lockwire.

(14)

Install spacer sleeve in propeller reversing lever (17) and locate clevis end of push-pull terminal (3) on propeller reversing lever with bolt and castellated nut. Tighten nut 24 to 36 lb.in., and install cotterpin.

(15)

Locate governor interconnect rod (4) on airbleed link of propeller governor (1) with bolt, washer and castellated nut. Tighten nut 24 to 36 lb.in., and install cotterpin.

(16)

Install, tighten and lockwire airframe electrical connections as required (Ref. Aircraft Maintenance Manual).

(17)

Install new preformed packing on chip detector (14) and install detector in reduction gearbox drain boss. Tighten detector and torque 45 to 55 lb.in. and lockwire.

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GOVERNOR AIR TUBE SUPPORT BRACKETS (NOT REQUIRED ON SOME ENGINE MODELS)

SUPPORT BRACKET PT6A−41 (POST−SB3112)

ENGINE LIFTING BRACKET

GOVERNOR AIR TUBE SUPPORT BRACKETS (NOT REQUIRED ON SOME ENGINE MODELS)

35 36 1

57

1

CLAMPS FOR T5 WIRING HARNESS

5

5

8

38

37 36

SCAVENGE OIL COUPLING

NO. 19 VIEW ON FLANGE A (LOOKING FORWARD)

NO. 31 VIEW ON FLANGE C (LOOKING FORWARD)

NOTE: DIAPHRAGM TO HOUSING ATTACHMENT SCREWS ARE FITTED AT POSITIONS MARKED THUS ❉ AND ARE ONLY TO BE LOOSENED OR TIGHTENED WHEN DISMANTLING GEARBOX ASSEMBLY

16

1 2

14

A 3

13 ❉

❉

12

4 ❉

❉

11

5

8

ELECTRICAL CONNECTOR BRACKET (PRE−SB3369) CLAMPS FOR ELECTRICAL LEADS (PT6A−38 ENGINES ONLY)

7 MOUNTING HOLES FOR OIL−TO−FUEL HEATER

NO. 9

DETAIL A (POST−SB3369)

MOUNTING HOLES FOR PROPELLER REVERSING LINKAGE. SPACERS REQUIRED (PT6A−40, −41 AND −42)

6

10 4

PRESSURE OIL COUPLING

ENGINE LIFTING BRACKET

15 SPACER REQUIRED AT LOCATIONS 4, 5, 11, 12, 13 AND 14 (ALL ENGINES)

28 27

VIEW ON FLANGE G (LOOKING FORWARD)

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(18)

Do power section/power section module checks (Ref. 71-00-00, ADJUSTMENT/TEST, Table 501).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

ENGINE, TURBOPROP - INSPECTION 1.

2.

General A.

The inspection criteria for the various sections of the engine are summarized in Table 601. Detailed inspection procedures are provided, where applicable, in the relevant INSPECTION/CHECK sections of subject chapters in this manual.

B.

The inspection procedures detailed are considered a normal function of operating organizations and are intended as a guide for minimum inspection and maintenance requirements.

C.

ROUTINE inspection coincides with the daily or preflight airframe inspection. MINOR inspection is coincidental with a typical airframe zone inspection. The intervals at which these inspections are performed may be altered by the aircraft manufacturers maintenance program and approved by the operators local airworthiness authority.

D.

Engines maintained in compliance with the aircraft manufacturer’s approved maintenance program shall be inspected as required by Condition Monitoring in accordance with the Operator/Local Authority agreed plan. Engines operating in sandy or dusty environments or in smog or salt-laden atmospheres should be subjected to additional inspections for corrosion and compressor erosion.

E.

Hot section inspection frequencies are outlined in the applicable service bulletin (Ref. Approved Service Bulletins) and will be updated periodically as dictated by service experience and time-between-overhauls (TBO). If, in the light of experience, it becomes necessary to modify procedures, these will be included in subsequent revisions to this manual.

F.

Retaining rings (spirolox, etc.) used throughout the engine are to be inspected for distortion and general condition. Distorted rings are not acceptable and must be replaced (Ref. 70-00-00, MAINTENANCE PRACTICES).

Consumable Materials The consumable materials listed below are used in the following procedures. Item No.

Name

PWC04-001 PWC11-027 PWC11-031 PWC15-011 PWC15-015 PWC15-017

Grease Solvent, Petroleum Cleaner, Engine Inhibitor, Rust Corrosion Preventative, Compound Inhibitor, Rust

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3.

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

4.

Tool No.

Name

PWC34910-100 PWC34910-400 PWC34913 PWC34941

Borescope Assembly Guide Tube Holding Fixture Wrench

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Corrosion A.

High temperature alloy corrosion High temperature alloy corrosion may be identified as metal loss or pitting, but more usually appears as local swelling or buildup due to greater volume occupied by nickel oxides. These corrosion products vary in color from black to green and in the advanced state there will be cracking and flaking, referred to as exfoliation. Care should be taken to distinguish between corrosion buildup and possible light brown or rust colored deposits which are essentially harmless combustion by-products. The latter are usually more widespread over hot section components and while possibly affecting performance will not directly affect compressor turbine mechanical integrity.

B.

Sulphidation Sulphidation is a common name for a type of hot corrosion which can affect turbine area components of gas turbine engines. Sulphates form at engine operating temperatures with sodium and sulphur present. Most aviation turbine fuels contain sulphur in sufficient amounts for sulphidation. Common sources of sodium are seawater, atmospheric pollutants and volcanic discharges. Sulphidation attack most often affects the compressor turbine blades, but sulphidation of power turbine blades and of non-rotating parts such as shroud segments is not uncommon. Turbine blades are coated with a protective layer. Sulphidation will first degrade this coating and eventually lead to some loss of base alloy material. Post coating strip inspection of attacked blades may reveal that they are not suitable for repair by recoating. In-service sulphidation may be characterized through the following four stages: Stage 1 - Light Sulphidation (Initial Coating Deterioration): Slight roughening of the surface and localized breakdown of the protective surface layer. Substrate is not yet affected.

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Stage 2 - Failure of the protective layer (Initial Substrate Corrosion): Roughness of surface is more marked as protective layer breakdown exposes the substrate to attack. Mechanical integrity is not yet affected. Stage 3 - Severe sulphidation: Base material is attacked to significant depth, as evidenced by obvious buildup scale and some blistering. Progression to Stage 4 would accelerate. Integrity is now affected and parts are no longer serviceable. Stage 4 - Catastrophic attack: Deep penetration of attack with large blisters of scale. Loss of structural material will lead to eventual component failure. All stages of attack may be encountered, although stages 3 and 4 will normally be limited to those engines which are directly exposed to salt water. Desalination wash using plain water with an antifreeze agent, if required, minimizes attack. During stages 1 and 2 the wash will dissolve and carry away sulfates on component surface. Water used for washing must be free from contamination, in most cases drinking water is acceptable. Otherwise demineralized water should be used. Wash frequency depends on the amount of contamination. Washing weekly is probably the minimum acceptable. Maritime areas may require washing daily or before each flight. Recommended wash frequency is based on operators estimate of corrosion environment or refer to Chapter 71-00-00, CLEANING. An alternative method of establishing wash frequency is to monitor blade condition using a borescope. Wash schedule should be adjusted according to results. If sulphidated blades continue in service, a borescope inspection program should be started. This program should continue until a reliable progression rate for the particular circumstances can be established and a blade life limit determined. The recommended inspection interval is 200 hours. Blade lives established this way should be reviewed periodically to account for possible changes in the factors affecting sulphidation. Two points are important to consider when evaluating sulphidated blades: Stage of corrosion attack. Estimate of progression rate to stage 3. At stage 3 mechanical integrity is jeopardized and blades should be removed from service. When estimating progression beyond stage 1 or 2 exposure to contamination and improvements in wash programs should be taken into account.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

6.

Corrosion Inhibition A.

Corrosion Inhibition Procedure NOTE: 1. For engines operating in corrosive environments, it may be necessary to do more frequent periodic preventative maintenance including the application of corrosion inhibitors to the Accessory Gearbox Housing, Reduction Gearbox Housing (Front and Rear) and the Compressor Inlet Case. NOTE: 2. As the corrosion inhibitor starts to evaporate or is washed away in service, reapply as required to determine the optimum period between applications. NOTE: 3. Discontinue the use of (PWC09-003) if using a corrosion inhibitor. NOTE: 4. Continue to follow the recommended external and internal engine wash schedule (Ref. Chap. 71-00-00) after use of corrosion inhibitors. (1)

Do a compressor desalination wash followed by a compressor turbine desalination wash (Ref. 71-00-00, Cleaning).

(2)

Do an external engine wash (Ref. 71-00-00, Cleaning).

(3)

For components listed below, remove corrosion in accordance with applicable Approved Repairs procedure: v AGB Housing (Ref. 72-60-00, Approved Repairs) v RGB Front and Rear Housings (Ref. 72-10-00, Approved Repairs) v Compressor Inlet Case (Ref. 72-20-00, Approved Repairs)

WARNING: ALLOW THE ENGINE TO COOL COMPLETELY BEFORE APPLYING CORROSION INHIBITOR. IF CORROSION INHIBITOR IS SPRAYED ONTO A HOT SURFACE, THE CARRIER SOLVENT WILL RAPIDLY EVAPORATE AND WILL EASILY IGNITE IF AN IGNITION SOURCE IS PRESENT. WARNING: DO NOT APPLY CORROSION INHIBITOR ON CONNECTORS, WIRING HARNESS, PROBES, RUBBER MATERIAL, ELECTRICAL EQUIPMENT OR ON HOT SECTION OF ENGINE. WARNING: REFER TO THE MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR INFORMATION SUCH AS HAZARDOUS INGREDIENTS, PHYSICAL/CHEMICAL CHARACTERISTICS, FIRE, EXPLOSION, REACTIVITY, HEALTH HAZARD DATA, PRECAUTIONS FOR SAFE HANDLING, USE AND CONTROL MEASURES. (4)

Apply corrosion inhibitor (PWC15-011), (PWC15-015), (PWC15-017) or equivalent onto the painted surfaces using a spray or brush per the manufacturer’s instructions.

(5)

Check to make sure that the surface is completely coated.

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72-00-00

ENGINE, TURBOPROP - INSPECTION

Page 604 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TEMPORARY REVISION NO. 72-23 (PT6A-38, PT6A-41, PT6A-42, PT6A-42A) REMOVE Temporary Revision 72-20 and INSERT Temporary Revision 72-23 facing page 605, Chapter 72-00-00 ENGINE, TURBOPROP - INSPECTION PURPOSE:

The purpose of this temporary revision is to add an inspection for cracks and damages in the pneumatic system components and a note to inspect the accessible lockwire and safety cable of engine external components. The FCU drive shaft periodic inspection interval limits has been revised. TABLE 601, Periodic Inspection

Component 1.

Inspection

Interval

Engine Externals A.

Clamps, Brackets, Tubes/Lines, Linkages

(1)

All accessible connections, clamps and brackets for attachment.

MINOR

NOTE: Inspect accessible lockwire and safety cable for security and installation. (2)

Chafing, cracks and corrosion.

MINOR

NOTE: Visually inspect insulated air tubes for sign of swelling, cracking, bulging of rubber sheath material. Refer to repair section and SB3451. Replace as necessary. (3)

Fuel and oil lines for leaks.

ROUTINE

(4)

Depending on operating conditions and environment, examine linkages at regular intervals. Pay particular attention to rear linkage cam box, fuel control unit arm, telescopic rod and rod end fittings. Disconnect rod ends and clean using solvent (PWC11-027) or (PWC11-031). Examine the rod ball for corrosion, roughness in rotation, side play and radial play. Lubricate with light grease (PWC04-001) after engine external wash. Examine rod end for corrosion, roughness in rotation, side play and radial play. Check free movement of linkage.

MINOR (See NOTE)

NOTE: Inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results but not to exceed 200 hours.

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72-00-00

Page 1 of 8 ENGINE, TURBOPROP - INSPECTION Feb 06/2012

PRINTED IN CANADA

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-23

TABLE 601, Periodic Inspection (Cont’d) Component

Inspection (5)

Interval

After lubrication, reinstall rod ends and torque to specified value (Ref. 76-10-00).

NOTE: With the exception of rod end fittings, linkages generally will operate satisfactorily without lubrication. While lubrication will be effective in some instances, it must be realized that grease and oil attracts dirt and foreign matter. Depending on local conditions, operators should take these facts into consideration before deciding to lubricate components or do otherwise. Mandatory lubrication of all engine control linkages is required after every engine wash. B.

Air Inlet

(1)

Inspect air inlet screen for cleanliness (Ref. 72-20-00, Inspection/Check).

MINOR

(2)

Inspect inlet surface areas, with screen removed, inspect overall surface area and struts for corrosion (Ref. 72-20-00, Inspection/Check).

MINOR

C.

Gas Generator Case

External surfaces, and fireseal mount ring brackets for cracks, distortion, and corrosion (Ref. 72-30-04, Inspection/Check).

MINOR

D.

Fireseal Mount Rings

Cracks and attachment of brackets and seals.

MINOR

E.

Exhaust Duct

Cracks and distortion (Ref. 72-50-05, Inspection/Check).

MINOR

F.

Propeller Shaft Seal

Check for oil leaks (Ref. 72-10-00).

ROUTINE

G.

Accessories

Attachment and linkages, air, oil and fuel lines.

MINOR

(1)

NOTE: Visually inspect insulated air tubes for sign of swelling, cracking, bulging of rubber sheath material. Refer to repair section and SB3451. Replace as necessary.

2.

(2)

Security of pneumatic lines (Ref. 73-10-07 and 73-10-08).

MINOR

(3)

Oil and fuel leaks as applicable.

ROUTINE

(4)

Starter-generator gearshaft splines for wear (at starter-generator removal/replacement only) (Ref. 72-60-00).

Engine Internals

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-23

TABLE 601, Periodic Inspection (Cont’d) Component A.

3.

Hot Section

Inspection

Interval

Examine with borescope (Ref. Para. 9.).

In conjunction with periodic fuel nozzle leak and function tests (Ref. 3.B.(11)).

(1)

Check oil level (Ref. 72-00-00, SERVICING).

ROUTINE

(2)

Check condition and locking of oil filler cap (Ref. 72-60-00).

ROUTINE

(3)

Examine oil filter. Elements must be inspected and cleaned. Light traces of sediment only may be removed from the main filter screen . All other contamination requires replacement of filter element. Any foreign material found in main oil filter or on chip detector, should be identified before further inspection/operation (Ref. 79-20-02).

MINOR (See NOTES)

Systems A.

Oil System

NOTE 1: Inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results but not to exceed 200 hours. NOTE 2: If carbon like deposits are found, drain accessory gearbox oil into a clean container and examine debris. Varnish flakes are non metallic and are usually dark on one side and shiny, similar to bronze, on the other side. They are hard and will not form into paste when rubbed between fingers (Ref. step (10)). (4)

For engines operating in an agricultural environment: Elements must be discarded after 1000 hours or after heavy contamination.

(5)

For engine NOT operating in an agricultural environment: (a) For Pre-SB3018 PT6A-41 Engines: Check filter every 1500 operating hours and ship to an overhaul facility for cleaning and inspection. After cleaning and inspection, the element may be used for a further 1500 hours or 30 month period maintaining the same inspection and cleaning schedule.

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Page 3 of 8 ENGINE, TURBOPROP - INSPECTION Feb 06/2012

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-23

TABLE 601, Periodic Inspection (Cont’d) Component

Inspection

Interval

(b) For Post-SB3018 PT6A-41 Engines and PT6A-38/-40/-42/-42A Engines: Remove and inspect filter for foreign matter. Clean in accordance with Chapter 79-20-02. Discard after 1000 operating hours. (6)

Check magnetic chip detector(s) for continuity; open circuit must exist indicating no contamination at pole tips. If continuity exists, remove and inspect for contamination. Any foreign material found on the chip detector or in the main oil filter should be identified before further inspection/operation (Ref. 79-20-02, INSPECTION/CHECK).

Every 100 hours (See NOTES)

NOTE 1: If the chip detector is connected to a cockpit indicating system, inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results, but not to exceed 200 hours. NOTE 2: While the chip detector is removed, inspect with both poles bridged (Ref. Check (7)). With poles unbridged, inspect for continuity. If continuity exists, replace the chip detector.

(7)

NOTE 3: For aircraft equipped with a cockpit indicating system, use a suitable ohmmeter to check completely as stated in step (6) above.

Every 100 hours, with extension to 400 hours maximum, based on inspection results.

Bridge chip detector magnetic poles with suitable metallic jumper and use a suitable ohmmeter to check for continuity between connector pins. Any foreign material found on either chip detector or in main oil filter should be identified before further inspection/operation (Ref. Chapter 79-20-02, INSPECTION/CHECK). Replace chip detector if continuity does not exist.

600 hours or 12 months, whichever comes first.

NOTE: For aircraft equipped with an airframe supplied indicating device, the integrity of the complete indicating system can be checked by re-attaching the electrical connector to the removed chip detector and check for chip indication when magnetic poles are bridged. Closed circuit condition must exist.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-23

TABLE 601, Periodic Inspection (Cont’d) Component

Inspection

Interval

(8)

Check scavenge pump housing for leaks.

ROUTINE

(9)

Check AGB internal scavenge oil pump inlet screen (Ref. Chapter 72-60-00 Cleaning/ Inspection). Collect drained oil. Use a mirror and a flashlight to inspect the scavenge oil pump inlet screen. Any foreign material found blocking the screen or contained in the oil should be identified before further operation (Ref. Unscheduled Inspection).

200 hours or 6 months (at operator’s option) for engines operating in high relative humidity/ tropical environment (above 70% for most of the year). Extension in steps of 50 hours to 500 hours maximum, based on operator experience. 1000 hours for engines NOT operating in high relative humidity/ tropical environment.

B.

Fuel System

(1)

Check for water contamination.

ROUTINE

(2)

Check fuel pump for installation and leaks (Ref. 73-10-02).

MINOR

NOTE: If airframe fuel boost pump fails or is inadvertently left off for an accumulative time in excess of 10 hours, the engine driven fuel pump must be removed and replaced. The removed pump should be sent to an approved overhaul facility for inspection/repair in accordance with pump manufacturers instructions.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-23

TABLE 601, Periodic Inspection (Cont’d) Component (3)

Inspection

Interval

Check fuel pump inlet screen for foreign matter or distortion, clean and reinstall, or install new screen (Ref. 73-10-02).

600 hours (Non Agricultural) 300 hours (Agricultural)

CAUTION: ON NEW AIRCRAFT, CHECK FILTER AFTER EACH FLIGHT UNTIL NO CONTAMINATION IS EVIDENT; CHECK AFTE FIRST FLIGHT OR GROUND RUN WHENEVER ANY COMPONENT UPSTREAM OR FILTER IS REPLACED. (4)

Check fuel pump outlet filter for foreign matter or distortion (Ref. 73-10-02). Install new filter as service conditions dictate, not to exceed 600 hours and when fuel system contamination is suspected.

(5)

If Sundstrand fuel pump is installed:

MINOR

Check fuel pump coupling in-situ for fretting and corrosion (Ref. 73-10-02).

Every 600 hours

Remove fuel pump and inspect the drive coupling and cover (accessory gearbox side) for signs of reddish-brown (iron oxide) stains. If stains are observed, return the fuel pump to an approved overhaul facility (Ref. 73-10-02).

Every 1800 hours

(6)

Check drain valve(s) for installation and leaks (Ref. 73-10-06).

MINOR

(7)

Check FCU for installation, linkages and pneumatic lines (Ref. 73-20-00). Evidence of FCU bearing washout indicated by traces of blue dye effluent is caused by a mixture of bearing grease and fuel.

MINOR

(8)

(a) PT6A-38/-41/-42: FCU drivebody inspection/driveshaft bearing replacement. Route to a qualified shop for detailed inspection and driveshaft bearing replacement.

3000 hours See NOTE

(b) PT6A-42A: FCU drivebody inspection/ driveshaft bearing replacement. Route to a qualified shop for detailed inspection and driveshaft bearing replacement.

3000 hours or 6 years whichever comes first. See NOTE

NOTE: This limit is calculated from the time the unit has entered service or the last overhaul of the FCU.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-23

TABLE 601, Periodic Inspection (Cont’d) Component

Inspection

(9)

Interval

(b) Remove FCU and sent for overhaul.

Ref. SB3003.

Check flow divider/ dump valve for installation and leaks (Ref. 73-10-04).

MINOR

(10) For engines fitted with a manual override on the fuel control, check FCU Manual Override System for static operation (Ref. 71-00-00, ADJUSTMENT/TEST).

Every 100 hours.

(11) Leak test and function test fuel manifold adapter and nozzle assemblies (Ref. 73-10-05).

See NOTES

NOTE 1: Do the periodic borescope inspection of the hot section components in conjunction with these tests (Ref. 2.A.). NOTE 2: For improved hot section durability, it is recommended that fuel nozzle assemblies be inspected on a routine basis according to: (a) Engines ON nozzle in-situ cleaning program (Ref. 71-00-00, CLEANING).

See NOTES

NOTE 1: Test fuel nozzles and refurbish as necessary. NOTE 2: Where fuel quality may be questionable, and for operators new to PT6A operation, inspection is recommended at 400 hr. initially, with extension of 200 hr. based on inspection results. NOTE 3: For other operators, remove nozzle and inspect at 600 hour intervals initially, with extensions of 200 hours based on inspection results. (b) Engines NOT ON fuel nozzle in-situ cleaning program (Ref. Chapter 73-10-05, Fuel Manifold, Cleaning/Painting).

See NOTES

NOTE 1: Test fuel manifold adapter assemblies (Ref. Chapter 73-10-05). NOTE 2: Where fuel quality may be questionable, and for operators new to PT6A operation, cleaning/inspection is recommended at 200 hr. initially, with extension based on inspection results. NOTE 3: For other operators, inspection is recommended at 400 hour intervals initially, with extension based on inspection results. (12) Check oil-to-fuel heater installation (Ref. 73-10-01, MAINTENANCE PRACTICES).

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72-00-00

MINOR

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-23

TABLE 601, Periodic Inspection (Cont’d) Component C.

Ignition System

Inspection

Interval

(1)

Check ignition exciter for installation and condition (Ref. 74-10-00).

MINOR

(2)

Check ignition cables for chafing, wear and installation (Ref. 74-20-00).

MINOR

(3)

Check spark igniters for cleanliness and erosion. Check function (Ref. 74-20-02).

MINOR (See NOTE)

NOTE: Inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results but not to exceed 200 hours. D.

Pneumatic System

(1)

Check P3 filter for installation (Ref. 73-10-07, Inspection/Check).

MINOR

(2)

Inspect pneumatic tubes and lines for cracks and damages especially at the end fittings and joints.

MINOR

(3)

Clean filter dependent on condition, service experience or environment (Ref. 73-10-07).

See NOTE 2

(4)

Clean and inspect Post-SB3350 P3 filter drain valve housing assembly (Ref. 73-10-07).

See NOTE 2

NOTE 1: Filter contamination is greatly influenced by particular operating conditions and environment, inspection intervals may be modified accordingly. NOTE 2: Inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results, but not to exceed 200 hours. (5)

Replace disposable filter based on condition, service experience or environment.

Every 1000 hours

(6)

Clean or replace permanent filter based on condition, service experience or environment. Ship to an approved overhaul facility for ultrasonic cleaning.

Every 1000 hours

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

7.

Control Linkage Inspect all engine controls for correct operation. Ensure that the linkage from cockpit controls to engine control levers are connected to permit full and free movement. Ensure that controls are adjusted to permit over-travel of power control lever to ensure full operation of engine and that the linkage can be operated without interference. Also investigate and eliminate any slack in the control system. Lubricate and adjust all controls. (Ref. Aircraft Maintenance Manual.)

8.

Periodic Inspection NOTE: The following tolerance is established for maintenance scheduling convenience only and must be approved by the governing civil aviation authority. Unless otherwise stated, the tolerance for periodic inspections is ten percent (10%), or up to a maximum of 100 hours operating time, whichever is less. The tolerance for scheduled inspections is ten percent (10%), or up to a maximum of 30 days calendar time, whichever is less. Subsequent intervals will be adjusted to re-establish the original schedule. When an inspection is done more than 10% early, subsequent inspections will be advanced as required to not exceed the maximum tolerance. Concurrence and final approval of the inspection interval tolerance by the governing civil aviation authority is the responsibility of the owner/operator. For inspection items and intervals, refer to Table 601. TABLE 601, Periodic Inspection Component

1.

Inspection

Interval

Engine Externals A.

Clamps, Brackets, Tubes/Lines, Linkages

(1)

All accessible connections, clamps and brackets for attachment.

MINOR

(2)

Chafing, cracks and corrosion.

MINOR

NOTE: Visually inspect insulated air tubes for sign of swelling, cracking, bulging of rubber sheath material. Refer to repair section and SB3451. Replace as necessary. (3)

Fuel and oil lines for leaks.

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ROUTINE

72-00-00

ENGINE, TURBOPROP - INSPECTION

Page 605 Dec 10/2010

NOTE: Please see the TEMPORARY REVISION that revises this page

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 601, Periodic Inspection (Cont’d) Component

Inspection (4)

Depending on operating conditions and environment, examine linkages at regular intervals. Pay particular attention to rear linkage cam box, fuel control unit arm, telescopic rod and rod end fittings. Disconnect rod ends and clean using solvent (PWC11-027) or (PWC11-031). Examine the rod ball for corrosion, roughness in rotation, side play and radial play. Lubricate with light grease (PWC04-001) after engine external wash. Examine rod end for corrosion, roughness in rotation, side play and radial play. Check free movement of linkage.

Interval MINOR (See NOTE)

NOTE: Inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results but not to exceed 200 hours. (5)

After lubrication, reinstall rod ends and torque to specified value (Ref. 76-10-00).

NOTE: With the exception of rod end fittings, linkages generally will operate satisfactorily without lubrication. While lubrication will be effective in some instances, it must be realized that grease and oil attracts dirt and foreign matter. Depending on local conditions, operators should take these facts into consideration before deciding to lubricate components or do otherwise. Mandatory lubrication of all engine control linkages is required after every engine wash. B.

Air Inlet

(1)

Inspect air inlet screen for cleanliness (Ref. 72-20-00, Inspection/Check).

MINOR

(2)

Inspect inlet surface areas, with screen removed, inspect overall surface area and struts for corrosion (Ref. 72-20-00, Inspection/Check).

MINOR

C.

Gas Generator Case

External surfaces, and fireseal mount ring brackets for cracks, distortion, and corrosion (Ref. 72-30-04, Inspection/Check).

MINOR

D.

Fireseal Mount Rings

Cracks and attachment of brackets and seals.

MINOR

E.

Exhaust Duct

Cracks and distortion (Ref. 72-50-05, Inspection/Check).

MINOR

F.

Propeller Shaft Seal

Check for oil leaks (Ref. 72-10-00).

ROUTINE

G.

Accessories

Attachment and linkages, air, oil and fuel lines.

MINOR

(1)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 601, Periodic Inspection (Cont’d) Component

Inspection

Interval

NOTE: Visually inspect insulated air tubes for sign of swelling, cracking, bulging of rubber sheath material. Refer to repair section and SB3451. Replace as necessary.

2.

Security of pneumatic lines (Ref. 73-10-07 and 73-10-08).

MINOR

(3)

Oil and fuel leaks as applicable.

ROUTINE

(4)

Starter-generator gearshaft splines for wear (at starter-generator removal/replacement only) (Ref. 72-60-00).

Engine Internals A.

3.

(2)

Hot Section

Examine with borescope (Ref. Para. 9.).

In conjunction with periodic fuel nozzle leak and function tests (Ref. 3.B.(11)).

(1)

Check oil level (Ref. 72-00-00, SERVICING).

ROUTINE

(2)

Check condition and locking of oil filler cap (Ref. 72-60-00).

ROUTINE

(3)

Examine oil filter. Elements must be inspected and cleaned. Light traces of sediment only may be removed from the main filter screen . All other contamination requires replacement of filter element. Any foreign material found in main oil filter or on chip detector, should be identified before further inspection/operation (Ref. 79-20-02).

MINOR (See NOTES)

Systems A.

Oil System

NOTE 1: Inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results but not to exceed 200 hours. NOTE 2: If carbon like deposits are found, drain accessory gearbox oil into a clean container and examine debris. Varnish flakes are non metallic and are usually dark on one side and shiny, similar to bronze, on the other side. They are hard and will not form into paste when rubbed between fingers (Ref. step (10)). (4)

For engines operating in an agricultural environment: Elements must be discarded after 1000 hours or after heavy contamination.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 601, Periodic Inspection (Cont’d) Component

Inspection (5)

Interval

For engine NOT operating in an agricultural environment: (a) For Pre-SB3018 PT6A-41 Engines: Check filter every 1500 operating hours and ship to an overhaul facility for cleaning and inspection. After cleaning and inspection, the element may be used for a further 1500 hours or 30 month period maintaining the same inspection and cleaning schedule. (b) For Post-SB3018 PT6A-41 Engines and PT6A-38/-40/-42/-42A Engines: Remove and inspect filter for foreign matter. Clean in accordance with Chapter 79-20-02. Discard after 1000 operating hours.

(6)

Check magnetic chip detector(s) for continuity; open circuit must exist indicating no contamination at pole tips. If continuity exists, remove and inspect for contamination. Any foreign material found on the chip detector or in the main oil filter should be identified before further inspection/operation (Ref. 79-20-02, INSPECTION/CHECK).

Every 100 hours (See NOTES)

NOTE 1: If the chip detector is connected to a cockpit indicating system, inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results, but not to exceed 200 hours. NOTE 2: While the chip detector is removed, inspect with both poles bridged (Ref. Check (7)). With poles unbridged, inspect for continuity. If continuity exists, replace the chip detector. NOTE 3: For aircraft equipped with a cockpit indicating system, use a suitable ohmmeter to check completely as stated in step (6) above.

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Every 100 hours, with extension to 400 hours maximum, based on inspection results.

Page 608 Dec 10/2010

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 601, Periodic Inspection (Cont’d) Component (7)

Inspection

Interval

Bridge chip detector magnetic poles with suitable metallic jumper and use a suitable ohmmeter to check for continuity between connector pins. Any foreign material found on either chip detector or in main oil filter should be identified before further inspection/operation (Ref. Chapter 79-20-02, INSPECTION/CHECK). Replace chip detector if continuity does not exist.

600 hours or 12 months, whichever comes first.

NOTE: For aircraft equipped with an airframe supplied indicating device, the integrity of the complete indicating system can be checked by re-attaching the electrical connector to the removed chip detector and check for chip indication when magnetic poles are bridged. Closed circuit condition must exist. (8)

Check scavenge pump housing for leaks.

ROUTINE

(9)

Check AGB internal scavenge oil pump inlet screen (Ref. Chapter 72-60-00 Cleaning/ Inspection). Collect drained oil. Use a mirror and a flashlight to inspect the scavenge oil pump inlet screen. Any foreign material found blocking the screen or contained in the oil should be identified before further operation (Ref. Unscheduled Inspection).

200 hours or 6 months (at operator’s option) for engines operating in high relative humidity/ tropical environment (above 70% for most of the year). Extension in steps of 50 hours to 500 hours maximum, based on operator experience.

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TABLE 601, Periodic Inspection (Cont’d) Component

Inspection

Interval 1000 hours for engines NOT operating in high relative humidity/ tropical environment.

B.

Fuel System

(1)

Check for water contamination.

ROUTINE

(2)

Check fuel pump for installation and leaks (Ref. 73-10-02).

MINOR

NOTE: If airframe fuel boost pump fails or is inadvertently left off for an accumulative time in excess of 10 hours, the engine driven fuel pump must be removed and replaced. The removed pump should be sent to an approved overhaul facility for inspection/repair in accordance with pump manufacturers instructions. (3)

Check fuel pump inlet screen for foreign matter or distortion, clean and reinstall, or install new screen (Ref. 73-10-02).

600 hours (Non Agricultural) 300 hours (Agricultural)

CAUTION: ON NEW AIRCRAFT, CHECK FILTER AFTER EACH FLIGHT UNTIL NO CONTAMINATION IS EVIDENT; CHECK AFTE FIRST FLIGHT OR GROUND RUN WHENEVER ANY COMPONENT UPSTREAM OR FILTER IS REPLACED. (4)

Check fuel pump outlet filter for foreign matter or distortion (Ref. 73-10-02). Install new filter as service conditions dictate, not to exceed 600 hours and when fuel system contamination is suspected.

(5)

If Sundstrand fuel pump is installed:

(6)

MINOR

Check fuel pump coupling in-situ for fretting and corrosion (Ref. 73-10-02).

Every 600 hours

Remove fuel pump and inspect the drive coupling and cover (accessory gearbox side) for signs of reddish-brown (iron oxide) stains. If stains are observed, return the fuel pump to an approved overhaul facility (Ref. 73-10-02).

Every 1800 hours

Check drain valve(s) for installation and leaks (Ref. 73-10-06).

MINOR

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TABLE 601, Periodic Inspection (Cont’d) Component

Inspection

Interval

(7)

Check FCU for installation, linkages and pneumatic lines (Ref. 73-20-00). Evidence of FCU bearing washout indicated by traces of blue dye effluent is caused by a mixture of bearing grease and fuel.

MINOR

(8)

(a) Remove FCU for Drivebody Inspection/ Driveshaft Bearing Replacement.

3000 hours See NOTE

NOTE: This limit is calculated from the time the unit has entered service or the last overhaul of the FCU.

(9)

(b) Remove FCU and sent for overhaul.

Ref. SB3003.

Check flow divider/ dump valve for installation and leaks (Ref. 73-10-04).

MINOR

(10) For engines fitted with a manual override on the fuel control, check FCU Manual Override System for static operation (Ref. 71-00-00, ADJUSTMENT/TEST).

Every 100 hours.

(11) Leak test and function test fuel manifold adapter and nozzle assemblies (Ref. 73-10-05).

See NOTES

NOTE 1: Do the periodic borescope inspection of the hot section components in conjunction with these tests (Ref. 2.A.). NOTE 2: For improved hot section durability, it is recommended that fuel nozzle assemblies be inspected on a routine basis according to: (a) Engines ON nozzle in-situ cleaning program (Ref. 71-00-00, CLEANING).

See NOTES

NOTE 1: Test fuel nozzles and refurbish as necessary. NOTE 2: Where fuel quality may be questionable, and for operators new to PT6A operation, inspection is recommended at 400 hr. initially, with extension of 200 hr. based on inspection results. NOTE 3: For other operators, remove nozzle and inspect at 600 hour intervals initially, with extensions of 200 hours based on inspection results. (b) Engines NOT ON fuel nozzle in-situ cleaning program (Ref. Chapter 73-10-05, Fuel Manifold, Cleaning/Painting).

See NOTES

NOTE 1: Test fuel manifold adapter assemblies (Ref. Chapter 73-10-05).

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TABLE 601, Periodic Inspection (Cont’d) Component

Inspection

Interval

NOTE 2: Where fuel quality may be questionable, and for operators new to PT6A operation, cleaning/inspection is recommended at 200 hr. initially, with extension based on inspection results. NOTE 3: For other operators, inspection is recommended at 400 hour intervals initially, with extension based on inspection results.

C.

Ignition System

(12) Check oil-to-fuel heater installation (Ref. 73-10-01, MAINTENANCE PRACTICES).

MINOR

(1)

Check ignition exciter for installation and condition (Ref. 74-10-00).

MINOR

(2)

Check ignition cables for chafing, wear and installation (Ref. 74-20-00).

MINOR

(3)

Check spark igniters for cleanliness and erosion. Check function (Ref. 74-20-02).

MINOR (See NOTE)

NOTE: Inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results but not to exceed 200 hours. D.

Pneumatic System

(1)

Check P3 filter for installation (Ref. 73-10-07, Inspection/Check).

MINOR

(2)

Clean filter dependent on condition, service experience or environment (Ref. 73-10-07).

See NOTE 2

(3)

Clean and inspect Post-SB3350 P3 filter drain valve housing assembly (Ref. 73-10-07).

See NOTE 2

NOTE 1: Filter contamination is greatly influenced by particular operating conditions and environment, inspection intervals may be modified accordingly. NOTE 2: Inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results, but not to exceed 200 hours. (4)

Replace disposable filter based on condition, service experience or environment.

Every 1000 hours

(5)

Clean or replace permanent filter based on condition, service experience or environment. Ship to an approved overhaul facility for ultrasonic cleaning.

Every 1000 hours

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

9.

Borescope NOTE:

A.

The borescope inspection is not intended to replace or diminish the importance of doing an HSI, but is intended to monitor the internal components of the engine to help reduce the cost of future repairs/refurbishments.

General The borescope is an optical device which lets an operator examine internal areas of the engine without removal or disassembly of the engine. Access is through ports or openings created by removal of engine components. Personnel doing inspection should be qualified to use borescope and analyze results. The borescope is a delicate device vulnerable to shocks, twisting and pinching. Use care and attention when handling/using tool. Examine the borescope assembly and it’s accessories (Ref. Fig. 601), and study the following procedures. NOTE:

B.

As an alternative, delete the Removal/Installation of Power Section Module (Heavy Maintenance only) (Ref. Para. 10. B.).

Description The borescope assembly comprises a pattern controlled rigid guide tube, a direct viewing flexible fibrescope, light source, side viewing adapter, and other accessories. An operator can do on-wing inspections of the CT stator assembly, combustion chamber liners, including cooling rings and dome, and AGB and RGB gears.

C.

Removal /Installation of Borescope and Accessories (1)

Side viewing adapter (Ref. Fig. 602) (a) Installation 1

Hold fiberscope as close as possible to distal end, and remove protective ring.

CAUTION: INSTALL SIDE-VIEWING ADAPTER CAREFULLY. IF NOT INSTALLED AND TIGHTENED CORRECTLY, ADAPTER COULD FALL INTO ENGINE. OVERTIGHTENING COULD DAMAGE DISTAL. 2

Hold fiberscope as close as possible to distal end, and install adapter with indexing slot and lug aligned. Tighten adapter fingertight.

(b) Removal 1

Hold fiberscope as close as possible to distal end, and remove side-viewing adapter.

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CAMERA AND LENS CAMERA ADAPTER EYEPIECE GUIDE TUBE HOLDING FIXTURE

FLANGE

FIBERSCOPE WRENCH

C

LIGHT SOURCE

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BORESCOPE DISTAL END

PROTECTIVE RING DIRECTION OF ROTATION FOR RING REMOVAL

RING REMOVAL

PRISM BODY INDEXING LUG INDEXING SLOT BORESCOPE DISTAL END

SIDE VIEWING ADAPTER THREADED RING DIRECTION OF ROTATION FOR RING REMOVAL

ADAPTER INSTALLATION

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CAUTION: INSTALL PROTECTIVE RING CAREFULLY. IF NOT INSTALLED AND TIGHTENED CORRECTLY, RING COULD FALL INTO ENGINE. OVERTIGHTENING COULD DAMAGE DISTAL. 2 (2)

Hold fiberscope as close as possible to distal end, and install protective ring.

Light source NOTE:

Specify power requirement when purchasing borescope.

(a) A halogen lamp, with either 110 V 60 Hz, or a 220 V 50 Hz power supply. (b) Remove top cover from light source to replace lamp. (c) Set intensity knob at maximum for best results. (d) Before light source is installed, refer to manufacturer’s instructions. (3)

Camera (a) A camera may be used to record internal engine components. It must be equipped with a 50 mm F1.8 lens. (b) Installation CAUTION: DO NOT USE COMPRESSED AIR TO CLEAN CAMERA, BORESCOPE, OR ASSOCIATED EQUIPMENT 1

Clean camera viewfinder, reflex mirror, focusing screen, and lens.

2

Install endoscopic focusing screen in camera.

3

Install lens.

4

Install adapter (CAII) on lens.

5

Install film in camera (Ref. Camera Handbook).

6

Set camera film speed to suit film , and set exposure to −2 (Ref. Camera Handbook).

7

Align bayonet slots of adapter and install camera on borescope eyepiece pins. NOTE:

Make sure distal is not moved while taking photographs.

(c) Removal 1

Turn outer ring of camera adapter to disengage locking mechanism and remove camera.

2

Remove camera adapter from lens.

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3

Remove film from camera and add following data: Engine S/N Date and area photographed. Engine TSN/TSO or cycles since last overhaul Reason for inspection.

(4)

Guide Tube (Ref. Fig. 603) (a) Installation 1

Remove appropriate fuel manifold adapter(s) (Ref. 73-10-05).

2

Ease guide tube (PWC34910-400) through manifold adapter opening into combustion chamber and exit duct area turning guide tube three-quarters of a turn CCW. NOTE:

3

The rigid, pattern controlled guide tube must be inserted freely with NO force.

The guide tube end locates between vane of CT stator, while the supporting flange is attached to the adapter boss.

(b) Removal

D.

1

Loosen knurled screw to release guide tube supporting flange.

2

Withdraw guide tube, turning CW.

3

Install fuel manifold adapter(s) (Ref. 73-10-05).

Inspection (1)

CT blades and shroud segments (a) Install guide tube (Ref. Para. C. step (4)). (b) Fasten holding fixture (PWC34913) to Flange C (Ref. Fig. 601). CAUTION: MAKE SURE ENGINE TEMPERATURE IS BELOW 60°C (140° F). (c) Insert fiberscope into guide tube while looking through eyepiece. Stop inserting when distal reaches end of guide tube. NOTE:

Make sure distal actuating lever is in neutral position when installing/removing fiberscope.

(d) Remove starter-generator (Ref. Aircraft Maintenance Manual). (e) Install wrench (PWC34941) in AGB splined gearshaft. (f)

Loosen knurled knob on holding fixture.

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FUEL MANIFOLD ADAPTER PORT FLANGE

C

RIGID GUIDE TUBE

POINT OF ENTRY (REF.)

FIBERSCOPE TIP 125 °

VANE RING DISTAL TIP RELATION BETWEEN POINT OF ENTRY AND DISTAL TIP VIEW TOWARD AIR INLET CASE

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CAUTION: MAKE SURE DISTAL TIP IS NOT BETWEEN CT BLADES BEFORE TURNING COMPRESSOR. (g) Examine CT blades, and shroud segments while turning compressor. (h) Retract fiberscope into guide tube. (i)

Remove wrench from splined gearshaft, and install starter-generator (Ref. Aircraft Maintenance Manual).

(j)

Remove fiberscope from guide tube.

(k) Remove borescope and holding fixture. (l) (2)

Remove guide tube (Ref. Para. C. step (4)).

CT Stator Assembly (a) Install guide tube (Ref. Para. C. step (4)). (b) Fasten holding fixture (PWC34913) to Flange C , install borescope, and attach light source (Ref. Fig. 601) CAUTION: MAKE SURE ENGINE TEMPERATURE IS BELOW 60°C (140 °F). (c) Insert fiberscope into guide tube. NOTE:

The side-viewing adapter will add to inspection capability.

(d) Examine CT stator assembly. (e) Remove light source, borescope and holding fixture. (f) (3)

Remove guide tube (Ref. Para. C. step (4)).

Combustion Chamber Liner CAUTION: MAKE SURE ENGINE TEMPERATURE IS BELOW 60°C (140 °F). (a) Remove fuel manifold adapter as necessary (Ref. 73-10-05). (b) Fasten holding fixture (PWC34913) to flange C, insert fiberscope into opening, fasten eyepiece to fixture, and attach light source. (c) Inspect combustion chamber liner. (d) Remove fiberscope, light source, and fixture. (e) Install fuel manifold adapter (Ref. 73-10-05).

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(4)

Accessory Gearbox NOTE:

When the AGB inspection is done at the same time as the first-stage compressor rotor, the AGB gears can be turned by the first-stage rotor. Do not use bare hands.

(a) Remove oil filler cap/ gage assembly and filler tube from accessory gearbox housing (Ref. 72-60-00). (b) Remove starter-generator (Ref. Aircraft Maintenance Manual). (c) Insert wrench (PWC34941) into splined gearshaft. (d) Clamp holding fixture (PWC34913) to engine rear lifting bracket, fasten eyepiece to holding fixture, and connect light source. CAUTION: MAKE SURE END OF FIBERSCOPE DOES NOT TOUCH GEARS. (e) Insert fiberscope into oil filler hole and examine gear teeth, while second operator rotates geartrain using the wrench. (f)

Remove wrench, light source, fiberscope, eyepiece and holding fixture.

(g) Install starter-generator (Ref. Aircraft Maintenance Manual). (h) Install oil filler tube, filler cap and gage assembly (Ref. 72-60-00). (5)

Reduction Gearbox (a) Remove scavenge oil strainer (Ref. 72-10-00). (b) Fasten holding fixture (PWC34913) to Flange A, attach eyepiece to fixture, and connect light source (Ref. Fig. 601). CAUTION: MAKE SURE END OF FIBERSCOPE DOES NOT TOUCH GEARS. (c) Insert fiberscope into the oil strainer access along the lower passage until the first-stage planet gears can be seen. To view the second-stage gears insert fiberscope in an upward direction. Examine gears. (d) Manipulate fiberscope while second person rotates geartrain by turning the propeller by hand. (e) Inspect internal casing for corrosion, pay particular attention to flange area at six o’clock position. (f)

Remove wrench, light source, fiberscope, eyepiece and holding fixture.

(g) Install scavenge oil strainer (Ref. 72-10-00).

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E.

Fault Isolation (1)

The possible sources of, and remedies for problems encountered when using borescope are shown in Table 602. TABLE 602, Fault Isolation

Problem Poor illumination

Poor definition

Fiberscope distal does not move when control knob is turned 10.

Source

Remedy

Oil or dirt on distal tip, or side-viewing adapter prism

Clean using lens cleaner and tissue

Light source intensity switch set at LOW

Set switch to HIGH

Defective lamp.

Replace lamp

Damaged borescope light tube

Return to manufacturer.

Defective transformer.

Return to manufacturer.

Poor illumination.

Return to manufacturer.

Diopter ring not adjusted correctly.

Adjust to suit eyes.

Damaged fibers in fiberscope, (seen as black dots through viewer).

Return to manufacturer

Damaged control wires.

Return to manufacturer.

In-service Inspection A.

Hot Section Components In-service inspection is used to determine performance deterioration. Parts can be inspected using a borescope (Ref. Para. 9.) or by removing the power section (Ref. Subpara. B.) following. Refer to Chapter 72-00-00, FAULT ISOLATION for areas to be inspected. Using a borescope is more practical for this inspection. Removal and installation of the power section, components/assemblies may result in damage to parts and/or distortion of sealing surfaces causing gas leaks and performance loss. Acceptable damage must be documented and progression monitored. Record engine/ module TSN/TSO and cycles, fuel nozzle ports used, if found by borescope, component, description, location and dimensions of defect. If rotating components are found with unacceptable damage during inspection, an HSI must be done before next flight. If damaged non-rotating components are found, except when holes are burnt through the combustion chamber or the CT vane ring trailing edge defects are beyond limits (Ref. Inspection), the HSI may be delayed, providing an engine performance/ground power check is done.

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An additional engine performance check and inspection of the affected area must be done after 50 hours. If further extensions are required, subsequent inspections and engine performance check intervals will depend on the progression and level of deterioration. Keeping an engine in service after components have deteriorated may substantially increase the cost of future repairs/refurbishments. Gas path components downstream of components having material missing must be inspected for secondary damage. Pay special attention to rotating components. CT stator vanes burned through at trailing edge (pressure and suction sides) may mean replacement of the complete set of CT blades, depending on the area of the surface burned through. The ability of an engine to produce the TO power required by the flight manual for the actual Tam/Pa is the only engine airworthiness requirement. The engine performance check may be used to confirm TO power is produced within operating limits over the complete range of Tam and Pa for which the engine/aircraft is certified. If, at an anticipated high ambient temperature and/or altitude, T5 and Ng will approach or exceed the maximum limits, an HSI is recommended before the actual conditions occur. When T5 and Ng approach, or are anticipated to approach or exceed the maximum limits, troubleshoot the engine/installation before doing an HSI. Carbon accumulation inside fuel nozzle passages is the principle cause of spray pattern degradation resulting in non-uniform combustion and local high temperature peaks. Exposure to these peaks contributes to premature hot section deterioration. Carbon accumulation is progressive and can affect all nozzles. Therefore, inspect all nozzles , to minimize premature deterioration occurring at other locations. If component deterioration exceeds limits, either replace the individual component or do an HSI, depending on the general condition of the hot section and engine performance. The inspections are recommended concurrent with scheduled engine maintenance checks applicable to individual aircraft installation. B.

Removal/Installation of Power Section Module (Heavy Maintenance Only) NOTE: (1)

This is an alternative to using borescope.

Removal (a) Remove power section (Ref. SERVICING). (b) Remove CT disk assembly (Ref. 72-50-02, Removal/Installation). (c) Remove combustion chamber inner liner (Ref. 72-40-01, Removal/Installation). (d) Remove CT stator assembly, shroud housing and small exit duct (Ref. 72-50-01, Removal/Installation). NOTE:

Do not separate parts unless CT stator damage exceeds limits.

(e) Inspect hot section components (Ref. Subpara. C.). (2)

Installation

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(a) Install CT stator assembly, shroud housing and small exit duct (Ref. 72-50-01, Removal/Installation). (b) Install CT disk assembly (Ref. 72-50-02, Removal/Installation). (c) Install combustion chamber inner liner (Ref. 72-40-01, Removal/Installation). (d) Install power section (Ref. SERVICING). C.

Inspection of Combustion Chamber (1)

Combustion chamber liner cracks may be repairable, and an HSI is recommended before component replacement is required. Converging cracks in the inner and outer liner walls which do not meet are acceptable. (a) Inspect affected area at 100 hours. Subsequent inspections must not exceed 400 hours.

(2)

Plasma top coating (ceramic) loss revealing undercoat (diffused aluminide) on inner and outer liners is acceptable, providing base metal is not burnt or eroded.

(3)

Small areas (approximately 1 sq.in.) bulging and/or hot spots on inner or outer liner walls may be repairable, and an HSI is recommended. Inspect the affected area at intervals not exceeding 400 hours. NOTE:

Engine may remain in service, providing the associated fuel nozzle(s) are inspected and replaced if not within limits.

(4)

Holes in the inner and outer liner walls are unacceptable. An HSI must be done to replace the affected component, and the associated fuel nozzle(s) inspected and replaced if not within limits.

(5)

Cracked or distorted cooling rings on liners may be repairable. An HSI is recommended before cooling rings are burned through and pieces enter the gas stream. NOTE:

(a) (6)

Engine may remain in service if it is understood that cooling air flow is changed, and the rate at which the combustion chamber deteriorates may increase. Therefore, if an HSI is not done, combustion chamber liner with distorted cooling rings or converging cracks must have the associated fuel nozzle(s) inspected and replaced if not within limits.

Inspect damage at 100 hours. Subsequent inspections must not exceed 400 hours.

Excessive carbon deposits inside combustion chamber could be result of poor fuel atomization by the fuel nozzles (indicated by deposits around fuel nozzle bosses). Distortion of combustion chamber liner cooling rings may produce carbon deposits in the dome area downstream of the affected cooling ring. If excessive carbon deposits are found, flow check fuel nozzles .

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(a)

If the nozzles are serviceable, the combustion chamber liner is the probable cause of the deposits. Inspect the CT blades, as erosion by carbon particles (some carbon particles remain in the gas stream and are not deposited in the combustion area) may damage and cause CT blade replacement.

(b)

If CT blades are eroded, refer to step E. If CT blades are not eroded, engine may remain in service and the CT blades and combustion chamber liners inspected within 100 hours. Subsequent inspections must not exceed 400 hours.

(7)

As the structural integrity of the small exit duct is not affected, cracks and open radial cracks extending from the inner to the outer diameter are acceptable (length not limited), and an unlimited amount of coating loss is acceptable.

(8)

Holes less than 0.500 in. in diameter in the outer wall are acceptable.

(9)

If holes or open cracks are found, an HSI is recommended. NOTE:

D.

The engine may remain in service, and HSI delayed, providing it is understood that the CT stator cooling air flow is affected, increasing the rate of deterioration.

(10)

When damage is found, inspect the CT stator and associated fuel nozzle.

(11)

Inspect damage at 100 hours. Subsequent inspections must not exceed 400 hours.

(12)

If deterioration exceeds the above limits, an HSI is recommended.

Inspection of CT Stator Assembly CAUTION: IF ANY CT STATOR VANE EXHIBITS TRAILING EDGE BURN THROUGH AS SHOWN (Ref. Fig. 604) THE CT BLADES MUST BE DISCARDED. (1)

Burned areas on vanes increase flow area which accelerates downstream component deterioration, decreases Ng and increases T5.

(2)

Cracks (Ref. Fig. 605) are repairable. Keep the engine in service and monitor deterioration. Do an HSI before crack progression makes the CT stator unrepairable. This will increase the cost of the subsequent HSI. Inspect stator having the defects shown (Ref. Fig. 605) within 100 hours. Subsequent inspections must not exceed 400 hours.

(3)

If defects have progressed beyond repair limits (Ref. Fig. 605), engine may remain in service, providing a ground power check (Ref. Aircraft Maintenance Manual) is done, and the airfoil trailing edge damage does not exceed limits shown (Ref. Fig. 604). An HSI is recommended if the vane trailing edge defects are beyond the limits shown or downstream components are affected by the CT vane distress or engine performance is unacceptable. NOTE:

Refer to Subpara. A. for additional recommendations.

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NOTE: TRAILING EDGE DEFECTS EXCEEDING THESE LIMITS ARE NOT ACCEPTABLE. DIMENSIONS CANNOT BE ACCURATELY MEASURED WHEN USING A BORESCOPE THEREFORE THE EXTENT OF THE DAMAGE MAY BE ESTIMATED AS A PERCENTAGE OF AIRFOIL LEADING EDGE HEIGHT (1.130 APPROX.)

0.230

1.130 APPROX. 0.230

LEADING EDGE OPEN CRACK TRAILING EDGE SURFACE MISSING (BURNT MATERIAL) CRACKS IN THE OUTER RING EXTENDING INTO THE FILLET RADIUS OR ON THE AIRFOIL BURNT AREA ON INNER/OUTER RING

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AIRFOIL CRACKS ON PRESSURE AND SUCTION SIDES

LEADING EDGE CRACK TRAILING EDGE PARALLEL CRACKS

INNER/OUTER RING CRACKS NOT EXTENDING INTO FILLET RADIUS

NOTE: THE ABOVE DEFECTS ARE ACCEPTABLE FOR FURTHER SERVICE. THE EXTENT OF THE DEFECT(S) MUST BE RECORDED AND MONITORED BY ADDITIONAL INSPECTIONS. THE ASSOCIATED FUEL NOZZLE MUST BE INSPECTED AND REPLACED IF NOT WITHIN SPECIFIED LIMITS.

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E.

Inspection of CT Blades (Ref. Figs. 606, 607 and 608) (1)

While performing compression turbine blade inspection, operators might notice surface anomalies that could be mistaken for sulphidation. In fact, these surface anomalies are a result of the blade manufacturing process and do not affect turbine performance. The following points of inspection will help operators determine if the blades are serviceable: v No loss of coating. v No change in color. v No evidence of sulphidation on adjacent blades. v Geometrical deviations do not exceed 0.005 inches deep or 0.005 inches high. There is no width limitation (Ref. Fig. 606).

(2)

The conditions of blades and tips is critical to obtain rated power. Most significant blade tip defects (rubs and oxidation) increase interturbine temperature (T5). Even if T5 is below maximum, an HSI may be recommended if damage is beyond the limits shown (Ref. Fig. 607). Defects shown are acceptable, providing their condition is monitored by further inspections and engine ground power checks. Subsequent inspections must not exceed 400 hours. Cracks 0.050 in. long in the upper 1/3 of the trailing edge are acceptable providing the complete set of blades is removed within 100 hours and overhauled. If defects are beyond those shown (Ref. Fig. 608), an HSI is recommended. NOTE:

(3)

Refer to Subpara. A. for additional HSI recommendations.

Check blades for axial shift. Normally, with components within assembly tolerances, the blade platforms are approximately inline. When a blade shifts, the blade moves axially and can be seen as having moved in relation to the adjacent platform. NOTE: 1. Checking, each blade TE platform alignment with a borescope, is quite difficult. The recommended method is to look at the leading edge (LE) mismatch while rotating the CT disk. When a mismatch is observed (one of the airfoil LE is shifted), check blade trailing edge platform. Maximum shift is 0.020 inch. NOTE: 2. The amount of blade shift may be estimated by using a 0.020 in. thick wire wrapped tightly around the tip of borescope and held by tape. The free end should be positioned within the field of view of the borescope. When estimating the amount of shift, position the free end of the wire adjacent to the platform being checked.

(4)

If blade shift in excess of the limit is observed, an HSI is recommended.

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0.005 IN

0.005 IN

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HEAVY RUBBING AND BURNT MATERIAL IS ACCEPTABLE PROVIDING ENGINE PERFORMANCE IS WITHIN LIMITS. EROSION

CRACK

0.050 TYPICAL

0.050 TYPICAL

CRACK 1/3 h

0.050 TYPICAL

h

TRAILING EDGE

COATING LOSS

0.970 (REF.) LEADING EDGE COATING LOSS (CHANGE IN COLOUR)

THE ABOVE DEFECTS ARE ACCEPTABLE FOR FURTHER SERVICE. THE EXTENT OF THE DEFECT(S) MUST BE RECORDED AND MONITORED BY ADDITIONAL INSPECTIONS.

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BLADE TIP

EROSION

OPEN CRACK

ORIGINAL CONTOUR VIEW ON ARROW A

BURNT OR MISSING MATERIAL EROSION BURNT MATERIAL OR FOREIGN OBJECT DAMAGE (FOD)

A

TRAILING EDGE SULFIDATION (COATING BLISTERING WITH SOME BLISTERS BURST)

LEADING EDGE

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F.

Inspection of CT Shroud Segments (1)

Heavy rubbing and oxidation are acceptable, providing T5 is within limits. Operating the engine with burned shroud segments may cause damage to the CT shroud housing (cracking and burning of the attachment rim), and an HSI is recommended. A damaged shroud housing must be replaced at the next HSI or refurbishment. NOTE:

Refer to Subpara. A. for additional HSI recommendations.

G. Inspection of PT Stator NOTE: 1. Inspection of the PT stator is recommended when upstream component damage does not explain performance loss or when secondary damage is suspected. NOTE: 2. Damage on the vanes may produce an increase in flow area which will increase Ng and T5.

H.

(1)

Cracks on the inner and outer rings and vanes are repairable. Keeping the engine in service, the defects will progress until the stator becomes unrepairable. This will increase the cost of the subsequent HSI. Inspect the damaged area within 100 hours. Subsequent inspections must not exceed 400 hours.

(2)

An HSI is recommended when the defects are still repairable.

(3)

If the defects are not repairable, replace PT stator at the next power section repair. Providing Ng and T5 are within limits, there is no need for power section repair and PT stator change, regardless of the amount of damage, unless structural integrity of the vanes are affected (e.g. wide open cracks, excessive foreign object damage (FOD) and missing or burnt material are unacceptable).

Inspection of PT Blades (1)

I.

Increased tip clearance of PT blades increases T5 . If T5 is within limits, there is no need to change the PT assembly, regardless of the amount of damage, providing structural integrity of the components is not affected. Cracks, missing material, excessive FOD, heavy sulphidation or blade distortion are unacceptable.

Inspection of AGB and RGB Gears (1)

The following inspection criteria should be used when inspecting the accessory and the reduction gearboxes using a borescope.

(2)

This inspection may be done at the operator’s discretion if gearbox distress is suspected or as a troubleshooting aid as required.

(3)

Acceptable Defects on Tooth Contact Faces (a) Small clusters of spalling at one extremity of the tooth width or in a narrow band on less than 1/2 tooth length.

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(b) Light shallow scoring where the scratches cannot be detected with a 0.040 in. radius scriber. Scoring usually indicates poor lubrication and the associated oil nozzle is recommended to be overhauled. (c) Heat discoloration usually indicates poor lubrication which may lead to scoring, then spalling. The associated oil nozzle is recommended to be overhauled. (d) Ideal tooth contact is a centrally-located strip on face of tooth. Any deviation indicates incorrect tooth contact. (e) Wear pattern starting at the end of the tooth denotes end loading. A minor amount of end loading is not considered detrimental. (f)

Incorrect tooth contact may result in spalling because the torque transmitted by the gear is transmitted by a smaller tooth surface resulting in increased contact pressure and local overloading.

(g) Components having acceptable defects may remain in service providing an inspection of the affected area is carried out at an interval not exceeding 400 hours. Subsequent inspections should be done at intervals depending upon the rate of progression and level of deterioration seen. In addition, special attention must be paid to the scheduled oil filter and chip detector inspections required by the regular maintenance program. (4)

Non-acceptable Defects NOTE:

Replace affected module or component if any non-acceptable condition is evident.

(a) Spalling in a narrow band along whole width of tooth or dispersed throughout contact area. (b) Deep scoring (root/tip direction) across tooth contact surface. NOTE:

Deep scoring is defined as scoring where the scratches can be felt with 0.040 in. radius scriber.

(c) Rough tooth contact surface due to excessive wear, with raised material at tooth extremities. 11.

Inspection of Hot Section Components A.

General For Hot Section Inspection Frequency, refer to SB3003. For description of tasks, refer to Para. D. Ground power check (Ref. 71-00-00, ADJUSTMENTS/TEST, Ground Power Check) before and after inspection is recommended and is important in determining the status of hot section parts and ascertain performance recovery. For inspection of the hot section parts, refer to SB3003 (PT6A-38/41/42/42A) and to Para. D..

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The following information (Ref. Para. B. and C.) is offered as a guide to improved engine performance/handling. B.

Inspection of Gas Generator Module (1)

To monitor the condition of the Hot Section Components, a borescope may be used to inspect them (Ref. Para. 9.).

(2)

Maintain CT blade radial tip clearance within prescribed limits (Ref. 72-50-01).

(3)

Improve CT blade tip clearance by maintaining lug and slot joint geometry (Ref. 72-50-01) and minimizing side clearance of lugs.

(4)

Interstage sealing rings must be in satisfactory condition.

(5)

Compressor bleed valve must be functioning correctly.

(6)

No air leaks are permitted in gas generator assembly area (e.g. cabin bleed air adapter, fuel nozzle adapter, igniter plug, P3 filter cover and adjoining lines including ecology system if fitted).

(7)

Cracks in the CT vane ring are acceptable provided they do not exceed acceptable limits (Ref. 72-50-01) or destroy lug and slot joint free movement and flat surface sealing.

(8)

The following affected parts condition; sealing faces and interference fits may be maintained by rework. (a) Sealing faces: CT vane ring to small exit duct; shroud housing and lock plate (Ref. 72-50-01). (b) Lugs/slot Fit: CT vane ring to shroud housing and No. 2 bearing flange (Ref. 72-50-01).

C.

Inspection of Power Section Module NOTE:

If the PT stator assembly needs to be replaced, refer to Chap. 72-50-03, Table 201.

(1)

Cracks in PT first-stage vane ring are acceptable provided they do not exceed limits (Ref. 72-50-03) or destroy lug and slot joints free movement and flat surface sealing.

(2)

Free sliding fit should exist between PT lugs of first-stage vane ring and slots of stator housing. Stone lugs or deburr slots as necessary (Ref. 72-50-03).

(3)

The following affected parts condition sealing surfaces and interference fits may be maintained by rework. (a) Sealing Surface: PT first-stage vane ring to interstage stator (Ref. 72-50-03). (b) Lugs/Slot Fits: PT first-stage vane ring to stator housing (Ref. 72-50-03). (c) Sliding Fit: PT first-stage vane ring to stator housing (Ref. 72-50-03).

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(4)

Inspection criteria is found in Table 603 following. TABLE 603, Hot Section Inspection

Component Gas Generator Case (Ref. 72-30-04) Combustion Chamber Liner, (Ref. 72-40-01) Combustion Chamber Large and Small Exit Ducts (Ref. 72-50-01)

C T Vane Ring and Shroud Housing (Ref. 72-50-01)

C T Shroud Segments (Ref. 72-50-01) C T Disk Assembly (Ref. 72-50-01)

Sealing Ring(s) (Ref. 72-50-01) Fuel Nozzles (Ref. 73-10-05) Fuel Nozzle Sheaths (Ref. 73-10-05) Compressor Inlet (Ref. 72-20-00) PT Stator Housing (Ref. 72-50-01) P T Disk Assembly (Ref. 72-50-04) P T Vane Ring and Interstage Baffle (Ref. 72-50-03) T5 Trim Thermocouple (Ref. 77-20-01) T5 Temperature Sensing System (Ref. 77-20-01)

Nature of Inspection Cracks, distortion, overheating and corrosion. Cracks, distortion, burning, fretting wear and hot spots. Cracks, distortion, burning, fretting wear and hot spots. Any amount of coating loss is acceptable provided burning of parent metal has not occurred . Verify the cooling ring gaps. Cracks, coating loss, erosion of parent metal or impact damage. Examine vane cooling air inlet and outlet ports for signs of blockage. Cracks, distortion, erosion and metal build-up. Measure radial tip clearance . Examine blades for tip rub, erosion, impact damage, coating loss, cracks, shift and circumferential movement. Examine blade retaining rivets for condition. Wear, fretting and distortion. Dissimilarity of carbon build-up. Do a functional test. Fretting wear, erosion and carbon build-up. Remove air inlet screen, examine inlet area and struts, first-stage blades and vanes for dirt deposits, corrosion and cracks. Cracks, none permitted. Check for proper sealing with interstage sealing rings. Blades for impact damage, erosion and cracks. Cracks, erosion and impact damage . Check attachment of lugs and leads. Do an operational check . Attachment, wiring harness and lugs. Check operation.

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TABLE 603, Hot Section Inspection (Cont’d) Component

Nature of Inspection Cracks and distortion.

Exhaust Duct (Ref. 72-50-05) RGB Oil Strainer (Ref. 72-10-00) Chip Detector (Ref. 72-10-00) D.

Hot Section Inspection (HSI) (Ref. Fig. 609) (1)

For a normally scheduled HSI, do a ground performance run (Ref. 71-00-00 or AMM).

(2)

Remove the RGB strainer, the main oil filter and the chip detector(s). Verify the debris (Ref. 79-20-02).

(3)

Verify Compressor for FOD (Ref. 72-30-00).

(4)

Remove power section/power section module (Ref. Para. 10. B.).

(5)

Measure the radial CT blade tip clearance and remove compressor turbine disk and blade assembly (Ref. 72-50-02, Removal / Installation).

(6)

Remove combustion chamber liner (Ref. 72-40-01, Removal/Installation). NOTE:

Should it be necessary, during HSI, to make a more detailed inspection of components which remain installed, those components should be removed as detailed in 72-50-01, Inspection/Check.

(7)

Verify components as per Table. 603.

(8)

If HSI is done due to over temperature remove PT stator housing (Ref. 72-50-03).

(9)

Calibrate aircraft instrumentation (Ref. AMM).

(10) 12.

Remove and examine assembly for foreign matter . Remove and examine chip detector for metal deposits.

Do a ground performance run (Ref. 71-00-00, ADJUSTMENT/TEST).

Unscheduled Inspection NOTE:

A.

If complete engine or accessory gearbox assembly is sent to an overhaul shop for repair, it is recommended to incorporate SB3358 at this time if not previously incorporated.

General (1)

Unscheduled inspection is done when the engine is subjected to unusual stress or operating conditions, or exceeds operating limitations or gives unsatisfactory performance.

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ELIMINATE HANG−UP

SMALL EXIT DUCT AND SHROUD HOUSING ASSEMBLY 0.030 IN. MAX. AXIAL MOVEMENT

A LUG AND SLOT JOINTS MUST BE FREE

COMPRESSOR TURBINE TIP CLEARANCE (REF. NO. 318)

ELIMINATE LEAKS

TWELVE COOLING AIR HOLES

COOLING AIR GAP

COOLING AIR GAP MIN. 0.005

LAP BOTH FACES

IDEAL LAPPING PATTERN (BOTH FACES) VIEW

MAX. 0.075

LAP BOTH FACES

ACCEPTABLE LAPPING PATTERN (BOTH FACES)

A

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LOADED SIDE OF LUGS (STONE OFF UNEVEN WEAR)

SHROUD HOUSING

C.T. VANE RING

NO.2 BEARING COVER FLANGE

UNLOADED SIDE OF LUGS (REMOVE GALL MARKS TO ENSURE FREEDOM OF MOVEMENT OVER SHROUD HOUSING AND FLANGE GROOVES)

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B.

(2)

If as a result of the inspection, engine removal is required, a written report stating cause of removal in detail (e.g. overspeed, overtemperature, etc.) must be sent with the engine to an approved overhaul/repair facility.

(3)

Refer to the applicable accessories manual for disposition of external components or, if applicable, send component along with the removed engine or module to an approved overhaul facility.

(4)

Several types of events call for rotating the propeller by hand as part of the inspection of the power section. On some engines, the power turbine may rub immediately after shutdown. This is not an indication of distress providing the rubbing/noise disappears after engine cool down.

Performance Deterioration (1)

C.

Refer to FAULT ISOLATION.

Overspeed (1)

Check engine/aircraft indicating system. If satisfactory, do the following: (a) When Ng exceeds 102.6 % (PT6A-38/-41) or 104 % (PT6A-40/-42/-42A), ship engine to an approved overhaul facility for Light Overhaul, Engine Overspeed, indicating Ng observed. (b) If observed Ng exceeds 101.5 %, except for transient conditions, ship engine to an approved overhaul facility for Light Overhaul, Engine Overspeed, indicating Ng observed. (c) When observed Np exceeds 100 % (all conditions except transient), ship engine or power section to an approved overhaul facility for Light Overhaul, Engine Overspeed, indicating Np observed. (d) If Ng exceeded 102.6 % (PT6A-38/-41) or 104 % (PT6A-40/-42/-42A) or Np exceeded 110%, determine and rectify cause of overspeed. Send gas generator or power section to an approved overhaul facility for Light Overhaul, Engine Overspeed, indicating Ng or Np observed.

D.

Inadvertent Cut-off and Relight During Taxi NOTE:

An inadvertent cut-off and relight happens when the operator moves the fuel condition lever from Low Idle to Cut-off and immediately back to Low Idle. This may result in a short-term sub-idle overtemperature.

(1) For operators WITH an engine monitor and have obtained a detailed recording of the overtemperature event: Refer to Chap. 71-00-00, ADJUSTMENT/TEST, Inadvertent Cut-off and Relight During Taxi figure. (2) For operators WITHOUT an engine monitor: Return the compressor turbine blade and disk assembly to an overhaul shop facility for stretch check, fluorescent penetrant inspection and a metallurgical analysis (cut-up) of two blades.

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E.

Overtemperature (1)

Check engine/aircraft indicating system. If satisfactory, refer to Chapter 71-00-00, ADJUSTMENT/TEST for required action.

(2)

When an overtemperature has occurred, and the maximum temperature reached and/or its duration cannot be established, or whenever an overtemperature is suspected to have occurred, send the engine to an overhaul facility for Light Overhaul. Indicate ‘‘Unkown Overtemperature’’. NOTE:

(3) F.

Two compressor turbine blades must be sent for metallurgical analysis (cut-up) to determine the extent of any damage to the engine.

If the engine was subject to an inadvertent cut-off and relight during taxi, refer to Para. D. above.

Overtorque (1)

Check the engine/aircraft indicating system. If satisfactory, refer to Chapter71-00-00, ADJUSTMENT/TEST and do the following: (a) If the overtorque is in Area B: 1

Remove and inspect RGB chip detector, oil strainer and main oil filter (Ref. 72-10-00, 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

2

Turn the propeller by hand and listen for unusual noises coming from the reduction gearbox or PT bearings (Ref. Para. A.(4)). For unusual noises, slow propeller acceleration on start or abrupt deceleration on shutdown, send power section to an approved overhaul facility for Light Overhaul. Indicate torque observed and duration.

3

Run at 80 % TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum).

4

Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals.

(b) If the overtorque is in Area C, send PSM to an approved overhaul facility for Light Overhaul. Indicate torque observed and duration. (2)

Refer to the Aircraft Maintenance Manual for related aircraft checks. NOTE:

Providing RBG chip detector, strainer and main oil filter element inspections are done and the results are found satisfactory, a ferry flight may be done under the authorization of the responsible regulatory agency to bring the aircraft to a maintenance base capable of power section module change.

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G. Immersion in Water (1) H.

Dropped Engine (1)

I.

J.

K.

Send the engine or component to an approved overhaul facility for Light Overhaul. Indicate dropped engine or component, the type of surface the engine struck and from what height.

Material Ingestion (e.g., ice, stones, etc) (1)

Check compressor first-stage blades for damage (Ref. 72-30-05, Inspection/Check).

(2)

Do an engine performance/ground power check (Ref. 71-00-00, ADJUSTMENT/ TEST, Engine Performance Check) or ground power check (Ref. 71-00-00, ADJUSTMENT/TEST, Ground Power Check).

Bird Strike/Soft Material Ingestion (e.g., rags, plastic bags, etc.). (1)

Remains on compressor first-stage blades confirm if bird or soft material has passed through the engine and possibly contaminated the gas path and CT vane cooling air passages. If contamination occurred, remove the power section and inspect hot section components (Ref. In-service Inspection). Evidence of possible contamination of the compressor turbine vane cooling passages necessitates an approved overhaul level inspection of the vane.

(2)

If the engine remains in service, do a performance recovery wash (Ref. POWER PLANT - CLEANING, Internal Washing) and a performance (Ref. 71-00-00, ADJUSTMENT/TEST, Engine Performance Check) or ground power check as applicable (Ref. 71-00-00, ADJUSTMENT/TEST, Ground Power Check).

Chip Detector Circuit Completion and/or Debris in Oil Filter (1)

L.

Send engine to an approved overhaul facility for Light Overhaul. Indicate immersion in water.

Refer to FAULT ISOLATION.

Propeller Sudden Stoppage or Strike NOTE: 1. Propeller sudden stoppage occurs when propeller rotation stops due to contact (propeller strike) with a hard object (e.g., ground, ground service equipment, etc.). NOTE: 2. The term propeller strike is used when either a rotating propeller hits an object which causes a speed variation (no stoppage) and blade damage or a stationary propeller is hit by a moving object which causes blade damage. (1)

For Propeller sudden stoppage, propeller strike causing blade structural damage (eg. bent blade, or blade tip missing or bent over 1 in. (over 5 in. for composite blade)), propeller strike on a power line, or propeller strike at power above FLIGHT-IDLE (Ng above 82 %) do the following:

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(a) Send power section to an approved overhaul facility for Light Overhaul. Indicate propeller strike, sudden stoppage as applicable, propeller speed and power at event, and extent of propeller damage. (b) Inspect remainder of engine:

(2)

1

Remove and inspect the main oil filter(Ref. 79-20-02). If metallic debris if found, refer to FAULT ISOLATION.

2

Inspect for cracks or distortion at all engine casings and housings, especially at or near the flanges. Remove the starter-generator and check all AGB pads and AGB mounted engine and airframe components. Look for shearing, cracks, distortion or mis-alignment, and loose/pulled fasteners. Similarly, inspect all engine mounts.

3

Inspect fireseals for warping or buckling, and all external tubes for damage and/or fluid leaks.

4

Check all airframe/engine connections, including fuel inlet and oil cooler lines, air system, electrical, ignition and indicating systems, control linkages, and drains.

5

For propeller strike on a power line (power utility line - does not include guide/support wires, telephone or telecommunications lines), check for evidence of electrical discharge (localized burn marks) at the C-flange or at the compressor turbine.

6

Rotate the compressor by hand and listen for rubbing, scraping, interference of rotating components with stationary parts, or rapid/abrupt deceleration. Check for rear accessory case mounted accessory drag. Check for compressor turbine tip rub (Ref. 72-50-02, Inspection/Check).

7

For casing or accessories damage, evidence of electrical discharge, unusual noises that could indicate damage to the gears, bearings, seals or rotors, slow compressor acceleration on start or abrupt deceleration on shutdown, send the complete engine to an approved overhaul facility for Light Overhaul. Indicate propeller strike/sudden stoppage as applicable, propeller speed and power at event, and extent of propeller damage.

8

After installation of a repaired/replacement power section on the serviceable gas generator, run at 80% TO power for ten minutes. Remove and inspect the main oil filter (Ref. 79-20-02). If no metallic debris is found, return the engine to service.

9

Inspect main oil filter after one week (25 hours minimum, 65 hours maximum). If no metallic debris is found, return to standard inspection schedule.

For Propeller strike causing minor blade damage (eg. delamination, indentation, blade tip bent slightly, etc.) with engine at or below FLIGHT-IDLE power or while engine was shut down do the following:

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(a) Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref. 72-10-00 and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION. (b) Turn the propeller by hand and listen for unusual noises coming from the reduction gearbox or PT bearings (Ref. Para. A.(4)). For unusual noises, slow propeller acceleration on start or abrupt deceleration on shutdown, send power section to an approved overhaul facility for Light Overhaul. Indicate what the propeller hit and at what speed and power, and extent of damage. (c) Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum). (d) Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals. M. Propeller Lightning Strike (1)

If signs of arcing are found on the propeller blades, the propeller shaft and flange must be checked for magnetism. NOTE:

(2)

Refer to the applicable accessories manual for disposition of external components.

Check for magnetism, using one of the following methods: (a) Check propeller shaft, especially flange, using a magnetometer to make sure residual magnetism is within ± 3 gauss or 3 oersted of 2.38 A/cm. If reading is above limits, replace power section.

(3)

If the propeller shaft or flange are found magnetized: (a) Ship the power section to an approved overhaul facility for Light Overhaul. Indicate a lightning strike. (b) On the gas generator, check for evidence of electrical discharge (localized burn marks) at the C-flange or at the compressor turbine. Evidence of discharge requires sending the complete engine to an approved overhaul facility. (c) Inspect the main oil filter (Ref. 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

(4)

If the propeller shaft or flange are not magnetized: (a) Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

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(b) Turn the propeller by hand and listen for unusual noises from the reduction gearbox or PT bearings (Ref. Para. A.(4)). For unusual noises, slow propeller acceleration on start or abrupt deceleration on shutdown, send power section to an approved overhaul facility for Light Overhaul. Indicate a lightning strike. (c) Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return the engine to service and check RGB chip detector daily for one week (25 hours minimum). (d) Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals. N.

Propeller Electrical Leads Shorting (1)

If signs of arcing between de-icer leads and the propeller spinner, bulkhead or hub assembly have been found, check propeller de-icing system (Ref. Aircraft Maintenance Manual) and rectify.

(2)

Inspect engine: (a) Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION. (b) Turn the propeller by hand and listen for unusual noises coming from the reduction gearbox or PT bearings (Ref. Para. A.(4)). For unusual noises, slow propeller acceleration on start or abrupt deceleration on shutdown, send power section to an approved overhaul facility for Light Overhaul. Indicate propeller electrical leads short and any discrepancy noted. Otherwise, run engine at 80% TO power for ten minutes. (c) Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum). (d) Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals.

O. Heavy/Hard Landing NOTE: 1. Do the following checks in the event of a suspected heavy or hard landing. A landing must be considered hard if the aircraft incurred any airframe or landing gear damage. NOTE: 2. If the heavy/hard landing involved a windmilling (inoperative) engine, send the complete engine to an approved overhaul facility for Light Overhaul. Indicate heavy/hard landing of inoperative engine. Otherwise, proceed as follows: (1)

Inspect for cracks or distortion at all engine casings and housings, especially at or near the flanges.

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P.

(2)

Remove the starter-generator and check all AGB pads and AGB mounted engine and airframe components. Look for shearing, cracks, distortion or mis-alignment, and loose/pulled fasteners. Similarly, inspect all other accessories and engine mounts.

(3)

Inspect fireseals for warping or buckling, and all external tubes for damage and/or fluid leaks.

(4)

Check all airframe/engine connections, including fuel inlet and oil cooler lines, air system, electrical, ignition and indicating systems, control linkages, and drains.

(5)

Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

(6)

Rotate the compressor by hand and listen for rubbing, scraping, interference of rotating components with stationary parts, or rapid/abrupt deceleration. Check for rear accessory case mounted accessory drag. Check for compressor turbine tip rub (Ref. 72-50-02, Inspection/Check). Rotate the propeller by hand and listen for any interference of rotating components with stationary parts or any other unusual noises coming from the gearbox or turbines (Ref. Para. A.(4)). Examine PT disk assembly and exhaust area through exhaust ports for evidence of distress. If damage is found, inspect (Ref. 72-50-04, Inspection/Check).

(7)

For casing or accessories damage, unusual noises that could indicate damage to the gears, bearings, seals or rotors, slow propeller acceleration on start or abrupt deceleration of compressor or power section on shutdown, send the complete engine to an approved overhaul facility for Light Overhaul. Indicate heavy landing and discrepancies observed.

(8)

Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum).

(9)

Inspect main oil filter after one week (25 hours minimum, 65 hours maximum). If no metallic debris is found, return to standard inspection schedule.

Aircraft Flown Through Volcanic Ash or Smoke (1)

Wash compressor and turbine (Ref. 71-00-00, POWER PLANT - CLEANING, Internal Washing).

(2)

Drain and refill oil system with new oil (Ref. SERVICING, Lubricating Oil System).

(3)

Clean or change main oil filter (Ref. 79-20-02, Cleaning).

(4)

Examine compressor (Ref. INSPECTION/CHECK, Borescope).

(5)

Return engine to service if no defects are found.

(6)

Drain and refill oil system with new oil (Ref. SERVICING, Lubricating Oil System) 50 ± 10 flight hours after original oil change done in step (2).

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Q. Sustained Running at Oil Temperature Outside Limits

R.

(1)

Check aircraft/engine indicating system and correct cause of high oil temperature (Ref. FAULT ISOLATION).

(2)

Rotate the compressor rotor and check for indications of AGB or bearing distress.

(3)

Turn the propeller by hand and listen for unusual noises coming from the reduction gearbox or PT bearings (Ref. Para. A.(4)).

(4)

For any presence of unusual noise, send the complete engine to an approved overhaul facility for Light Overhaul. Indicate the oil temperature that the engine was operated at, the engine power and the duration.

(5)

Drain and discard oil (Ref. SERVICING, Lubricating Oil System).

(6)

Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref. 72-10-00 and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

(7)

Fill oil system(Ref. SERVICING, Lubricating Oil System).

(8)

Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref. 72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum).

(9)

Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals.

Loss of Oil/Oil Pressure or Low Oil Pressure NOTE:

(1)

Low oil pressure is defined as oil pressure below limits (Ref. 71-00-00, ADJUSTMENT/TEST, Pre-Operational Check). If oil pressure was fluctuating (such as a result of loss of oil) or transient, refer to the transient limits.

If the engine oil pressure dropped below 60 psi, or, if the engine oil pressure dropped between 60 to 90 psi with engine power above 1100 lb.ft., or if the transient low oil pressure limits were exceeded: (a) Check oil pressure indicating system. If correct, ship the engine to an approved overhaul facility for Light Overhaul. Indicate oil pressure the engine was run at, the engine power, and duration.

(2)

If the engine lost 6 qt. or more oil and the oil pressure or torquemeter indication fluctuated without exceeding transient limits, or if the engine ran at an oil pressure of 60 to 90 psi, at power less than 1100 lb.ft torque for a period longer than the transient limit: (a) Check oil pressure indicating system. If correct, remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION.

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(b) Rotate the compressor rotor and check for indications of AGB or bearing distress. (c) Turn the propeller by hand and listen for unusual noises coming from the reduction gearbox or PT bearings (Ref. Para. A.(4)). For unusual noises, slow starts or abrupt deceleration on shutdown, send the engine to an approved overhaul facility for Light Overhaul. Indicate oil pressure the engine was run at, the engine power, and duration. (d) Run the engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref. 72-10-00 and 79-20-02). If no metallic debris is found, return the engine to service and check RGB chip detector daily for one week (25 hours minimum). (e) Inspect main oil filter after one week (25 hours minimum, 65 hours maximum (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals. S.

Oil Pressure Follows Throttle NOTE:

T.

Under normal operating conditions, oil pressure indication is stable. Malfunction of the pressure relief valve or oil leakage can cause indication to increase as throttle is advanced, or drop when throttle is retarded.

(1)

Check external lines for breaks and leakage. Remove pressure relief valve and check for sticking, scoring, etc. (Ref. 72-60-00).

(2)

Remove accessory gearbox. Check oil pump housing for cracks(Ref. 72-60-00).

(3)

Remove relief valve and housing. Examine housing for wear resulting from relief valve rotation. Replace housing if necessary (Ref. 79-20-03).

Contamination by Fire Extinguishing Agents (1)

Foam, powder or other chemical extinguishers: (a) If only engine externals are exposed, then wash (Ref. 71-00-00, CLEANING, Engine External Wash) using drinkable quality water only and monitor for corrosion. (b) In the event of internal contamination, return engine to an approved overhaul facility for Light Overhaul. Indicate the agent ingested by the engine. Depending on the agent, and at the option of the operator, an attempt may be made at cleaning the contaminating agent prior to shipping: 1

Do a dry motoring run (Ref. 71-00-00, ADJUSTMENT/TEST, Dry Motoring Run) to blow out any residual deposits.

2

Wash engine externally (Ref. 71-00-00, CLEANING) using drinkable quality water only.

3

Do an engine performance recovery wash (Ref. 71-00-00, CLEANING) followed by two dry motoring runs.

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(2)

Halon: (a) No engine maintenance required.

U.

Audible Rubbing, Binding or Scraping NOTE: (1)

Any unusual (internal) engine noises (e.g. rubbing, scraping and/or squealing, etc.) require immediate investigation.

Rotate compressor rotor and listen for any interference of rotating components with stationary parts and/or check for rapid deceleration on shutdown. (a) Check for rear accessory case mounted accessory drag. (b) Check for compressor turbine tip rub (Ref. 72-50-02, Inspection/Check). (c) Indications of compressor rub or bearing or AGB distress. Send engine to an approved overhaul facility for Light Overhaul.

(2)

Rotate the propeller and listen for any interference of rotating components with stationary parts (Ref. Para. A.(4)). If power turbine rotor rattles, or if there is rubbing or scraping, slow propeller acceleration on start or abrupt deceleration on shutdown: (a) Examine PT disk assembly and exhaust area through exhaust ports for evidence of distress. (b) If damage is found, inspect (Ref. 72-50-04, Inspection/Check). (c) Slow or stiff propeller rotation. Send power section to an approved overhaul facility for Light Overhaul. Indicate rubbing.

(3)

If the suspected problem cannot be repeated or confirmed: (a) Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If metallic debris is found, refer to FAULT ISOLATION. (b) Run engine at 80% TO power for ten minutes. Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02). If no metallic debris is found, return engine to service and check RGB chip detector daily for one week (25 hours minimum). (c) Inspect main oil filter after one week (25 hours minimum, 65 hours maximum) (Ref. 79-20-02). If no metallic debris is found, return to standard inspection intervals.

V.

Propeller Windmilling after In-flight Shutdown (1)

Investigate cause of shutdown. If suspected of being attributed to an engine or accessory problem, send engine or accessory to an approved overhaul facility for Light Overhaul. Indicate engine shutdown and the events and conditions at the time.

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(2)

With shutdown not related to an engine problem (serviceable engine): (a) With stabilized windmilling Np not more than 20 rpm and less than 6 qt. of oil required to bring oil level to MAX on dipstick, no further action is necessary. (b) With an unknown (not recorded) Np or stabilized windmilling Np greater than 20 rpm or if 6 qt. or more of oil is required to bring oil level to MAX on dipstick: 1

Remove and inspect RGB chip detector, oil strainer, and main oil filter (Ref.72-10-00 and 79-20-02) . If metallic debris is found, refer to FAULT ISOLATION.

2

Rotate the compressor rotor and check for indications of AGB or bearing distress.

W. Contamination of Oil with Non-metallic Foreign Material NOTE: 1. AGB/RGB internal protective coatings may be released within the engine and appear as flakes 1/64 inch to 3/8 inch in diameter, usually shiny, yellow, brown or green in color, and may or may not be transparent. NOTE: 2. Inspect chip detector, main oil filter and AGB scavenge pump screen after approximately 10 hours. If no debris is found, inspect at 50 hours. NOTE: 3. If no debris is found at 50 hours, refer to the standard periodic inspection interval for oil filter and chip detector (Ref. Table 601). NOTE: 4. If these flakes are found, immediately contact your local P&WC customer support representative. Send engine to an approved overhaul facility for light overhaul. Indicate oil contamination from released AGB/RGB internal protective coatings. (1)

Remove chip detector from reduction gearbox front housing (Ref. SERVICING, Oil Change) and scrub scavenge oil strainer sleeve with a brush to remove any foreign material blocking the screen.

(2)

Remove accessory gearbox drain plug(s).

(3)

Flush oil system (Ref. SERVICING, Oil System Flushing).

(4)

Reinstall chip detector and plug(s) and tighten. Refill engine oil tank. NOTE:

Do not lockwire chip detector and drain plug(s) at this time.

(5)

Remove chip detector and inspect scavenge oil strainer sleeve for residual foreign material accumulated after system flush (Ref. NOTE 1).

(6)

Repeat steps (2) thru (5), if required.

(7)

Reinstall chip detector. Tighten all plugs and chip detector and lockwire.

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X.

Starter-Generator Replacement (1)

If there is an engine starting fault or an electrical generation defect, do the following inspections: (a) Inspect the starter-generator drive splines: 1

Inspect per Aircraft Maintenance Manual (AMM).

2

If there is no inspection procedure in the AMM, clean the starter-generator splines and inspect for evidence of electrical arcing damage (in the form of pitting) using a 10X magnifying glass. NOTE: 1. If there is any evidence of electrical arching, return engine to an approved overhaul facility for Electrical Discharge Damage (EDD) repair. NOTE: 2. If there is NO evidence of electrical arching, inspect the main oil filter (Ref. Step (b)).

3

If cause of pitting can not be determined, metallurgical analysis may be required. Contact the Aircraft OEM.

(b) Inspect the main oil filter: 1

Do a main oil filter patch check (Ref. 79-20-02). The results of the filter patch analysis should be reviewed within the next 25 flight hours. If non allowable debris is found, follow the recommended maintenance actions (Ref. 79-20-02).

2

Regardless of the results of the patch analysis, repeat step 1 every 100 hours, for the next 700 flight hours.

3

If bearing material (AMS 6440/6444 or AMS 6490/6491, (Ref. 79-20-02) is found, remove the engine/gas generator module and send to an approved overhaul facility for repair.

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

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DATE

LEP

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Contents

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TABLE OF CONTENTS SUBJECT

PAGE

POWER SECTION - DESCRIPTION AND OPERATION 1.

Description and Operation

72-01-00 1

72-01 CONTENTS

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POWER SECTION - DESCRIPTION AND OPERATION 1.

Description and Operation (Ref. Fig. 1) The power section is essentially a two-stage rotor and shaft assembly coupled to a reduction gearbox and propeller shaft. The turbine shaft housing and shrouds enclosing the rotor and stator assemblies are contained within the twin-ported exhaust duct attached to the reduction gearbox casing. First and second-stage turbine disks are coupled together and secured on the rear end of the power turbine shaft by a special nut and slotted washer. A splined coupling, connected to the second-stage turbine disk, transmits the drive to the shaft. The power turbine shaft is supported at the front end by a ball bearing (No 4), and at the rear end by a roller bearing (No. 3). Both bearings are carried in the shaft housing, which is attached to the rear half of the reduction gearbox casing. The sun gear set, which is a combination gear, shaft and splined coupling, connects the forward end of the turbine shaft to the first-stage reduction geartrain. The first-stage stator assembly, comprising a vane ring, first-stage shroud, interstage baffle and stator air seal, is situated between compressor and power turbines. An interstage stator, between the first and second-stage power turbines, carries the second-stage stator vanes and interstage stator air seal. Both stators and second-stage shroud are interlocked and secured by a shroud housing attached to rear flange of the exhaust duct. This housing supports part of the T5 system, either a thermocouple bas-bar and integral probe assembly or two bus-abars with individual thermocouples. An insulating blanket, sandwiched between the inner side of the exhaust duct and the outer casing of the rear-half reduction gearbox and shaft housing, shields the shaft assembly and bearings from the high temperatures prevailing in the exhaust duct. After driving the compressor turbine, the gas stream enters the power section where it passes through the power turbine stators, impinging in turn on the blades of the first and second-stage turbines. Leaving the second-stage power turbine, the exhaust gas stream discharges to atmosphere through the twin-ported exhaust duct. Driving power is transmitted from the coupled turbine rotors through a common shaft and sun gear coupling to a two-stage planetary reduction gear and propeller shaft. Two oil tubes carried in the shaft housing circulate lubricating oil in the shaft bearing areas. The upper tube receives oil from the pressure side of the engine lubrication system, and directs it onto Nos. 3 and 4 bearings through three spray jets. The lower tube conducts scavenge oil from the housing to the tank return line. The turbine disks and shaft are cooled by a flow of air entering the compressor/power turbine interstage area from the compressor discharge through the bore of the compressor turbine. From this point, a portion of the air flow is directed by metering disks on the interstage baffle to the rear face of the first-stage power turbine. The remainder of the air flow is directed through holes in the disk hub to the power turbine interstage area. Some of the remaining flow is allowed to bleed through the interstage stator air seal and across the disk faces, while the balance passes through holes in the second-stage turbine disk to pressurize the No. 3 bearing air seal. Air entering the shaft housing through the air seal is exhausted through the oil scavenge tube to the accessory gearbox, where it vents to atmosphere after undergoing oil separation in the centrifugal breather.

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T5 HARNESS AND THERMOCOUPLE BUSBAR POWER TURBINE SHAFT HOUSING

INSULATING BLANKET

SECOND−STAGE POWER TURBINE SHROUD

REDUCTION GEARBOX REAR HOUSING SECOND−STAGE STATOR VANE SHROUD HOUSING PROPELLER SHAFT

THERMOCOUPLE PROBE

INTERSTAGE BAFFLE

FIRST−STAGE STATOR AND SHROUD ASSEMBLY EXHAUST DUCT REDUCTION GEARBOX FRONT HOUSING

SUN GEAR SET

POWER TURBINE SHAFT

FIRST−STAGE POWER TURBINE

NO. 3 BEARING

NO. 4 BEARING

SECOND−STAGE POWER TURBINE

C3986 Cross-section of Power Section (Typical) Figure 1

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The interturbine temperature (T5) is monitored by thermocouple probes projecting into the annular space between compressor turbine and first-stage power turbine.

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

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Contents

1 2

Dec 10/2010 Dec 10/2010

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TABLE OF CONTENTS SUBJECT

PAGE

REDUCTION GEARBOX - DESCRIPTION AND OPERATION 1.

Description and Operation

72-10-00 1

REDUCTION GEARBOX - MAINTENANCE PRACTICES

72-10-00

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

202

5.

Removal/Installation

202

A.

Removal of Propeller Shaft Oil Seal (Post-SB3026)

202

B.

Removal of Propeller Shaft Oil Seal (Post-SB3239, Post-SB3278 and Post-SB3427)

202

C.

Removal of Chip Detector

203

D.

Removal of Oil Strainer

203

E.

Installation of Propeller Shaft Oil Seal (Post-SB3026)

203

F.

Installation of Propeller Shaft Oil Seal (Post-SB3239, Post-SB3278 and Post-SB3427)

205

6.

7.

G. Installation of Chip Detector

209

H.

209

Installation of Oil Strainer

Cleaning/Painting

209

A.

Cleaning of Scavenge Oil Strainer Assembly

209

B.

Cleaning of Magnetic Chip Detector

209

Inspection/Check

211

A.

Inspection of Propeller Thrust Bearing Cover Assembly

211

B.

Inspection of Oil Seal Retaining Ring, Ring Halves and Support Ring Halves

211

C.

Inspection of Oil Seal Runner

213

D.

Inspection of Scavenge Oil Strainer Assembly

213

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TABLE OF CONTENTS SUBJECT

PAGE

REDUCTION GEARBOX - MAINTENANCE PRACTICES (Cont’d)

8.

72-10-00

E.

Inspection of Chip Detector

213

F.

Inspection of Propeller Shaft Oil Seal

215

Approved Repairs

215

A.

Replacement of Accessory Drive Seal

215

B.

Repair of Thrust Bearing Cover (Corroded Seal Cavity)

215

C.

Propeller Shaft - On Wing Repair of Coating (Post-SB3362)

215

D.

Propeller Shaft Anti-corrosion Treatment (Alternate Method)

217

E.

Repair of Corrosion - Front and Rear Reduction Gearbox Housing

218

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REDUCTION GEARBOX - DESCRIPTION AND OPERATION 1.

Description and Operation (Ref. Figs. 1 and 2) The propeller gearbox assembly is located at the front of the engine and consists of two alloy housings, front and rear, bolted together at flange A of the exhaust duct. The gearbox contains a two-stage planetary geartrain, accessory drives, torquemeter and propeller shaft. The first-stage reduction gear and torquemeter are contained in the rear case, while the second-stage reduction gear, accessory drives and propeller shaft are in the front case. Torque from the power turbine section is transmitted through the power turbine shaft and turbine coupling to the first-stage sun gear. The first-stage reduction geartrain is driven by the sun gear which consists of a short hollow steel shaft with an integral spur gear at the front and external splines on the rear. The external splines engage with the internal splines of the turbine coupling on the power turbine shaft. Axial float between the sun gear and turbine coupling is controlled by a thrust washer retained within the coupling by a retaining ring. A spigot installed at the rear of the sun gear centerbore locates in the power turbine shaft and serves to centralize the gear relative to the shaft. Lubrication to the coupling is provided through radial holes in the spigot. An oil dam is located in the sun gear at the front to make sure adequate oil is available for lubrication of the number 4 bearing and the sun gear splines. The first-stage of the reduction geartrain consists of three planet gear assemblies in a rotating carrier balancing assembly and a non rotating ring gear. The ring gear is located in helical splines in the rear case. The torque developed by the power turbine is transmitted through the sun gear and planet gears to the ring gear which is opposed by the helical splines. This opposition causes the planet gear carrier to rotate. The ring gear, although held radially by the helical splines, is allowed to move axially between the case and retaining plates fastened to the case. The axial movement is used in the torquemeter application. The second-stage of reduction is housed in the front case of the reduction gearbox. The first-stage planet carrier is attached to the second-stage sun gear by a flexible coupling which also acts to dampen any vibrations between the two rotating masses. The second-stage sun gear drives five planet gears mounted in the second-stage carrier. A second-stage ring gear is located by splines in the front case of the reduction gearbox by retaining plates. The second-stage carrier is in turn splined to the propeller shaft and held by a keywasher and nut. A flanged roller bearing supports the second-stage carrier and the rear of the propeller shaft. The inner race of the bearing is located on the machined circumference of the second-stage carrier extension, while the flanged outer race is bolted to a web in the front case. A propeller oil transfer tube adapter and a nozzle assembly are coupled together by a retaining ring and located within the centerbore of the propeller shaft. The adapter provides the necessary separation of pressure oil for propeller actuation, and pressure oil for lubrication of propeller thrust and gearbox front roller bearings. The nozzle assembly and transfer tube conduct pressure oil for lubrication of the No. 4 bearing area, second-stage planetary gears and sungear coupling. Pressure oil is applied to the oil transfer tube via oil transfer sleeve installed on the OD of the propeller shaft. The sleeve is supplied by two

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independent oil sources via two transfer tubes. Engine oil is supplied to the rear section of the sleeve for direction to the centerbore transfer tube adapter. Propeller governor oil is supplied to the front section of the sleeve to provide hydraulic pressure for the propeller pitch servo system. The accessories located on the front reduction gearbox are driven by a bevel drive gear mounted at the rear of the propeller shaft thrust bearing assembly. Drive shafts from the bevel drive gear transmit rotational power to the three pads on the front case of the reduction gearbox. The pads are located at the 12, 2, and 9 o’clock positions. Propeller thrust loads are absorbed by the ball bearing assembly (No. 6), located on the front section of the propeller shaft. The ball bearing is mounted in conjunction with and behind a shaft support roller bearing (No. 7), the outer flange of which is secured to the front case of the gearbox.The bevel drive gear adjusting spacer, thrust bearing and roller bearing and seal runner are stacked and secured to the propeller shaft by a keywasher and spanner nut. A thrust bearing cover assembly is secured by nuts and washers at the front flange of the reduction gearbox front case. The cover assembly encloses a propeller shaft oil seal, retained by a bolted ring plate. A cavity in the rear face of the cover collects bearing lubrication oil, which is returned to the gearbox sump via a transfer tube. Oil seepage past the propeller shaft oil seal is allowed to drain overboard via an airframe connection to the thrust bearing cover assembly. Both bearings are lubricated with pressure oil through drillings in the walls of the propeller shaft and via the front annular cavity formed by the propeller shaft centerbore oil transfer tube adapter. The torquemeter (Ref. Fig. 2) is a hydro-mechanical torque-measuring device, installed at the rear of the first-stage reduction gear in the rear case of the reduction gearbox. The torquemeter provides an accurate indication of engine power output and consists of a cylinder, piston, seal rings, valve plunger and spring. Rotation of the ring gear is resisted by the helical splines, which impart an axial movement to the ring gear and to the torquemeter piston. Movement of the piston moves a valve plunger against the spring, opening a metering orifice and allowing an increased flow of pressure oil into the torquemeter chamber. Piston movement continues until oil pressure in the torquemeter chamber is proportional to torque being absorbed by the ring gear. Any change in engine power recycles the sequence until a state of equilibrium is again reached. Hydraulic locks are prevented by allowing oil to bleed continuously from the torquemeter chamber into the reduction gear sump through a small bleed orifice at the top of the torquemeter cylinder. Because the external ambient pressure and the pressure within the reduction gearbox may vary and affect the total pressure on the torquemeter piston, internal pressure is measured. The difference between the torquemeter pressure and reduction gear internal pressure accurately indicates the torque being produced. The two pressures are internally routed to bosses at the top of the reduction gear front case where connections can be made to suit individual airframe instrumentation requirements. A chip detector is installed at the 6 o’clock position on the front case of the reduction gearbox. The chip detector provides an indication of the presence of ferrous particles in the lubrication system when a continuity check is done. Provisions exist for airframe wiring to provide in-flight indication of contamination (Ref. Aircraft Maintenance Manual).

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FLANGE GOVERNOR DRIVE SHAFT GEAR

A SECOND−STAGE SUN GEAR FLEXIBLE COUPLING

FRONT HOUSING ASSEMBLY OIL TRANSFER GALLERY

REAR HOUSING ASSEMBLY NO. 4 BEARING OIL NOZZLE

BEVEL GEAR

FIRST−STAGE PLANET GEAR

OIL SEAL PROPELLER SHAFT

SHAFT SPIGOT SPLINE ADAPTER

FWD

FLANGE

B

THRUST BEARING

TORQUEMETER CYLINDER AND PISTON

THRUST BEARING COVER PROPELLER OIL TRANSFER SLEEVE

EXHAUST DUCT (REF.)

ROLLER BEARING FIRST−STAGE RING GEAR

MAGNETIC CHIP DETECTOR

SECOND−STAGE RING GEAR SECOND−STAGE PLANET GEAR

C47B Cross-section of Propeller Gearbox Assembly Figure 1

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12

13

11

1 2

10 9

3 4

8

5

7

6

14

CONSTANT POWER

POWER INCREASED

C351A Torquemeter - Schematic (Typical) Figure 2

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Key to Figure 2 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14.

Gearbox Oil Pressure Torquemeter Pressure Valve Plunger Spring Metering Orifice Torquemeter Piston Torquemeter Chamber First-stage Planet Gear First-stage Ring Gear Helical Splines Rear Case Torquemeter Cylinder Bleed Orifice Engine Oil Pressure

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REDUCTION GEARBOX - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire, unless otherwise specified, shall comply with specification AMS5687, heat and corrosion resistant steel wire MS9226-03, 0.025 inch in 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 PWC05-037 PWC05-061 PWC05-101 PWC05-166 PWC05-270 PWC07-006 PWC07-023 PWC08-002 PWC08-006 PWC09-001 PWC11-005+ PWC11-012 PWC11-014 PWC11-022 PWC11-023+ PWC11-025+ PWC11-027 PWC11-031 PWC13-001

Oil, Engine Lubricating Enamel, Epoxy Cloth, Abrasive Coated Crocus Cloth, Abrasive Solution, Chemical Treatment Paper, Abrasive Paint, Modified Silicone Coating, Aluminium and Zinc Adhesive, Sealant Adhesive, Epoxy Sealant, Silicone Rubber Envirosolv 655 Acetone Alcohol, Isopropyl DELETED Ardrox Leeder 1064K Desoclean 45 Solvent, Petroleum Cleaner, Engine Primer, Epoxy

Special Tools The special tools listed below are used in the following procedures. Tool No.

Name

Application

PWC57233

Puller

Replaces PWC32072

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4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation A.

Removal of Propeller Shaft Oil Seal (Post-SB3026) (Ref. Fig. 201) (1)

Remove propeller (Ref. Aircraft Maintenance Manual).

(2)

Place suitable container under front end of reduction gearbox and disconnect airframe drain line from nipple at bottom of thrust bearing cover (5). Allow any residual oil to drain into container.

(3)

Remove eight bolts (8) and washers (7) that secure the oil seal retaining ring (1) to thrust bearing cover. Move retaining ring forward to be flush against flange of propeller shaft. Remove gasket (6) and discard.

(4)

If oil seal support ring halves (2, Post-SB3204/Pre-SB3239) are fitted, note split line location then identify top and bottom segments and remove from propeller shaft. NOTE:

(5)

Work out seal element (3) from cavity, taking care not to damage bore of thrust bearing cover or surface of oil seal runner.

(6)

Remove garter spring from inside diameter rear face of seal. Unwind spring and remove from propeller shaft. Remove seal by stretching over retaining ring and propeller shaft flange. NOTE:

(7) B.

Propeller shaft oil seal support ring halves are not used on Post-SB3239 configurations.

Seal may be cut to remove it. Protect surface of propeller shaft from possibility of nicks or scratches caused by cutting instrument.

Clean off gasket mating surfaces with a suitable non-metallic scraper.

Removal of Propeller Shaft Oil Seal (Post-SB3239, Post-SB3278 and Post-SB3427) (Ref. Fig. 202) (1)

Remove propeller (Ref. Aircraft Maintenance Manual).

(2)

Remove eight bolts (6) and washers (7) which secure the oil seal retaining ring halves (1) to the propeller thrust bearing cover assembly (3). Remove the ring halves.

(3)

Work out seal (4) from cavity, taking care not to damage the bore of the thrust bearing cover assembly or surface of the oil seal runner (5).

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(4)

Remove garter spring from inside diameter rear face of seal. Unwind spring and remove from propeller shaft. remove seal by stretching over retaining ring and propeller shaft flange. NOTE:

(5) C.

D.

E.

Seal may be cut to remove it. Protect surface of propeller shaft from possibility of nicks or scratches caused by cutting instrument.

Clean off retaining ring halves and thrust bearing cover mating surfaces with suitable non-metallic scraper.

Removal of Chip Detector (Ref. Fig. 203) (1)

Remove airframe calbe connector from chip detector at 6 o’clock position on reduction gearbox front case.

(2)

Remove lockwire from chip detector (3).

(3)

Remove chip detector and allow oil in reduction gearbox sump to drain into a suitable container.

(4)

Remove preformed packing (2) from chip detector.

Removal of Oil Strainer (Ref. Fig. 204) (1)

Remove bolt (2) and washer (3) which secure the scavenge oil strainer plug (4) to reduction gearbox (1). Withdraw strainer plug with puller (PWC57233) and remove preformed packing (5)

(2)

Remove sleeve strainer (6) from cored passage in gearbox.

Installation of Propeller Shaft Oil Seal (Post-SB3026) (Ref. Fig. 201)

CAUTION: HANDLE SEAL WITH CARE TO PREVENT DAMAGE. AVOID APPLYING LOADS LOCALLY TO LIP OF SEAL AS SEAL IS SOFT AND HAS LOW TEAR RESISTANCE. (1)

Moisten new seal element (3) in engine oil (PWC03-001) and install over flange of propeller shaft and retaining ring (1) with Vee-side of seal facing thrust bearing cover assembly (5). (a) To facilitate installation of the seal, do the following: 1

Tape a strip of plastic material to flange of propeller and retaining ring and liberally coat with engine oil. This will enable seal to be slipped over flange without undue stretching.

2

Heat the seal in engine oil (PWC03-001) at approsimately 93 °C (200 °F) maximum for 20 minutes.

(2)

Install garter spring in Vee-section of seal (Ref. Fig. 205).

(3)

Gently press seal into cavity in thrust bearing cover (5) ensuring seal is well lubricated and correctly seated.

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2

3

1

5 1 4

6 8

A

7

5 2 6

FOR FIELD MAINTENANCE, CUT GASKET AT LOCATION SHOWN

FOR FIELD MAINTENANCE, CUT GASKET AT LOCATION SHOWN

GARTER SPRING 2 3

GARTER SPRING

1 1

3

6

POST−SB3026/PRE−SB3204

6

VIEW A (ALTERNATE CONFIGURATIONS)

2 POST−SB3204

C13522A

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Key to Figure 201 1. 2. 3. 4. 5. 6. 7. 8. (4)

Retaining Ring Oil Seal Support Ring Halves (Post-SB3204) Seal Element Seal Runner Thrust Bearing Cover Gasket Washer Bolt

If oil seal support ring halves (2, Post-SB3204) are to be installed, position segments with split line as noted at disassembly and with top and bottom halves properly located against seal element (3).

CAUTION: GASKET IS BRITTLE AND SHOULD NOT BE OVER-STRESSED WHEN INSTALLED. MAKE SURE FACE OF RETAINING RING IS CLEAN. (5)

Cut (split) new gasket (6) midway between two holes at right angle to vertical centerline, then carefully install on propeller shaft.

(6)

Remove plastic sheet from propeller flange and align groove in retaining ring (1) and corresponding cut-out in gasket with drain spigot in thrust bearing cover assembly.

(7)

Make sure retaining ring (1), gasket (6) and support ring halves (2) mounting holes are aligned before they are secured with bolts (8) and washers (7) to thrust bearing cover (5).

(8)

Tighten bolts in a diametric sequence. Torque 36 to 40 lb.in. and lockwire in parts.

(9)

Install propeller (Ref. Aircraft Maintenance Manual).

(10) F.

Connect airframe drain line to nipple at bottom of thrust bearing cover (Ref. Aircraft Maintenance Manual).

Installation of Propeller Shaft Oil Seal (Post-SB3239, Post-SB3278 and Post-SB3427) (Ref. Fig. 202)

CAUTION: HANDLE SEAL WITH CARE TO PREVENT DAMAGE. AVOID APPLYING LOADS LOCALLY TO LIP OF SEAL AS SEAL IS SOFT AND HAS LOW TEAR RESISTANCE. (1)

Moisten new seal element (4) in engine oil (PWC03-001) and install over flange of propeller shaft with Vee-side of seal facing thrust bearing cover assembly (3). (a) To facilitate installation of the seal, do the following: 1

Tape a strip of plastic material to flange of propeller and retaining ring and liberally coat with engine oil. This will enable seal to be slipped over flange without undue stretching.

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3

3 2

2

1

4

1

4

8

5

5

3 2 1

6

A

7

GARTER SPRING

GARTER SPRING

4

4

8 1

1

2

2

VIEW A (POST−SB3239)

VIEW A (POST−SB3278) (POST−SB3427)

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Key to Figure 202 1.

Oil Seal Retaining Ring Halves (Post-SB3239, Post-SB3278 and Post-SB3427) Gasket Propeller Thrust Bearing Cover Seal and Garter Spring Seal Runner Bolts Washers Felt Strip Insert (Post-SB3278 and Post-SB3427)

2. 3. 4. 5. 6. 7. 8. 2

Heat the seal in engine oil (PWC03-001) at approximately 93 °C (200 °F) maximum for 20 minutes.

(2)

Install garter spring in Vee-section of seal (Ref. Fig. 205).

(3)

Gently press seal assembly (4, Fig. 202) into cavity formed by bore of thrust bearing cover (3) and oil seal runner (5). Work seal into cavity with thumbs until seal is fully seated in cavity.

CAUTION: GASKET IS BRITTLE AND SHOULD NOT BE OVER-STRESSED WHEN INSTALLED. MAKE SURE FACE OF RETAINING RING IS CLEAN. (4)

Open gasket (2) at split and carefully install on propeller shaft.

(5)

For Post-SB3278/Post-SB3427 Engines: Moist felt strips (8) on oil seal retaining ring halves (1) with engine oil (PWC03-001).

(6)

Locate oil seal retaining ring halves (1) and gasket (2) forward of seal and garter spring (4). Make sure gap between retaining halves is approximately at horizontal center line and if applicable, felt strips (8, Post-SB3278/Post-SB3427) engage lip of oil seal runner (5).

(7)

Make sure retaining ring halves (1), gasket (2), oil drain hole and mounting holes are aligned before they are secured with bolts (6) and washers (7) to thrust bearing cover (3).

(8)

Tighten bolts (6) in a diametric sequence. Torque 36 to 40 lb.in. and lockwire in parts.

(9)

Install propeller (Ref. Aircraft Maintenance Manual).

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PROPELLER REDUCTION GEARBOX

A

A

1 4 0.750−16 UNJF−3A 2 THREE LACQUER STRIPES EQUISPACED 4 D.750−20 UNEF−2A 3

SECTION

A−A

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Key to Figure 203 1. 2. 3. 4.

Lockwire Securing Lug Preformed Packing Magnetic Chip Detector Magnetic Poles

G. Installation of Chip Detector (Ref. Fig. 203) CAUTION: IN VIEW OF SIZE OF WRENCH THAT WOULD NORMALLY BE USED FOR CHIP DETECTOR BODY, OVERTIGHTENING CAN EASILY OCCUR. THEREFORE, USE OF TORQUE WRENCH TO AVOID OVERTIGHTENING IS RECOMMENDED TO PREVENT FRACTURE OF CHIP DETECTOR BODY.

H.

6.

(1)

Install new preformed packing (2) on chip detector (3).

(2)

Lubricate thread of chip detector and insert into threaded boss in reduction gearbox. Torque 45 to 55 lb.in.

(3)

Lock hexagon flats to securing lug (1) with lockwire.

Installation of Oil Strainer (Ref. Fig. 204) (1)

Locate sleeve strainer (6) in cored passage at front of reductiong gearbox (1). Make sure strainer is pressed fully home.

(2)

Moisten preformed packing (5) in engine oil (PWC03-001) and isntal in recess on boss of strainer plug (4).

(3)

Install strainer plug on reduction gearbox and secure with bolt (2) and washer (1). Torque bolt 36 to 40 lb.in. and lockwire.

Cleaning/Painting A.

B.

Cleaning of Scavenge Oil Strainer Assembly (1)

Soak scavenge oil strainer assembly in clean solvent (PWC11-027) or (PWC11-031). Remove oil sludge and examine for evidence of metallic particles. Open up blocked holes using non-metallic scraper.

(2)

Wipe clean with lint-free cloth and dry with clean, dry compressed air.

Cleaning of Magnetic Chip Detector CAUTION: DO NOT SOAK DETECTOR IN SOLVENT. (1) (2)

Seal electrical receptacle. Clean with solvent (PWC11-027) or (PWC11-031) and a medium stiff-bristle brush or spray.

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1

3 2 6 5 4

C352 Removal/Installation of Reduction Gearbox Oil Strainer Figure 204 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 204 1. 2. 3. 4. 5. 6. (3) 7.

Reduction Gearbox Bolt Washer Scavenge Oil Strainer Plug Preformed Packing Sleeve Strainer Assembly

Make sure magnets are free of metal particles, and store detector in sealable container until ready for use.

Inspection/Check A.

Inspection of Propeller Thrust Bearing Cover Assembly (1)

B.

Examine thrust bearing cover seal cavity for burrs, nicks and other surface damage. Light stoning of damaged surfaces is acceptable. Corrosion may be removed (Ref. Para. 8.).

Inspection of Oil Seal Retaining Ring, Ring Halves and Support Ring Halves (1)

Examine for nicks, burrs and similar surface damage. Light stoning of damaged surfaces is acceptable.

(2)

Check integrity of felt strip inserts (8, Fig. 202) on oil seal retaining ring halves (Post-SB3278/Post-SB3427). If loose, worn or damaged, replace felt strip inserts: (a) Remove remaining worn or damaged felt strip insert from retaining ring half by carefully scraping slot area. Clean with acetone (PWC11-012) isopropyl alcohol (PWC11-014) or ardrox leeder 1064K (PWC11-023+) or desoclean 45 (PWC11-025+) envirosolv 655 (PWC11-005+). Discard remainder of felt strip. (b) If anodizing has been damaged, apply touch-up (PWC05-166). (c) Cut portions of felt strip insert to suit slot in retaining ring half. Make sure felt strip protrudes 0.020 to 0.040 inch for Post-SB3278 engines and 0.040 inch maximum for Post-SB3427 engines at each end of ring half. (d) For Post-SB3278 Engines: Apply adhesive (PWC08-006) per manufacturer’s instructions and cure at temperature not exceeding 93 °C (200 °F) for 30 minutes minimum. (e) For Post-SB3427 Engines: Bond felt strip into the groove of the retaining ring by applying adhesive (PWC08-006) to the black colored surface of the strip following the adhesive manufacturers instructions.

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GRASP SPRING SUCH THAT NARROW END IS IN RIGHT HAND. STRAIGHT END IN LEFT. HOLDING LEFT END FIRMLY ROTATE NARROW END TWO TURNS IN A COUNTER−CLOCKWISE DIRECTION (SPRING HELIX IS RIGHT−HANDED).

INSERT NARROW END (RIGHT HAND) INTO OTHER END

SPRING IS ASSEMBLED WHEN THE NARROW END IS ROTATED TWO TURNS CLOCKWISE TO SECURE ENDS TOGETHER

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C.

Inspection of Oil Seal Runner (1)

Examine visible area of seal runner for nicks, burrs and other surface damage caused by tools during removal of seal. No repair is acceptable. Send power output section of engine to an approved overhaul facility for replacement of defective seal runner. NOTE:

(2)

Examine visible area of oil seal contact area on seal runner for wear (grooving). If concentrated wear is present, installation of Post-SB3276 alternate offset propeller shaft oil seal (Ref. IPC) should be considered. This lets the alternate propeller shaft oil seal to contact oil seal runner at different location. NOTE:

D.

E.

If applicable, check sealant (PWC08-002) between oil seal runner and propeller shaft. Replace if necessary.

Post-SB3276 oil seal not to be installed with upper and lower spacers P/N 3113779-01.

Inspection of Scavenge Oil Strainer Assembly (1)

Examine for blocked passages. Clean as necessary (Ref. Cleaning/Painting).

(2)

Examine seating surfaces for nicks, burrs and other surface damage caused during removal and installation. Light stoning of damaged surfaces is acceptable.

(3)

Examine threads of nut and, if plug is removed, internal threads for deformation. Chase threads using suitable die or tap as appropriate. Remove all metal chips.

Inspection of Chip Detector NOTE: 1. Whenever a reduction gearbox chip detector is inspected, the main oil filter and air inlet chip detector should also be inspected. Any foreign material found on the chip detectors in the main oil filter should be identified before further inspection/operation. NOTE: 2. For detailed debris analysis refer to Chapter 70-00-00, MAINTENANCE PRACTICES.

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CAUTION: WHEN AN ENGINE IS REMOVED DUE TO METAL CONTAMINATION OF THE OIL SYSTEM AND TO AVOID CONTAMINATION OF A NEWLY INSTALLED ENGINE, ALL AIRFRAME COMPONENTS ASSOCIATED WITH THE ENGINE OIL SYSTEM - INCLUDING PROPELLER, PROPELLER GOVERNORS, TUBES AND HOSES - SHOULD BE FLUSHED ACCORDING TO AIRFRAME MANUFACTURERS INSPECTION. AIRFRAME OIL COOLERS SHOULD BE REPLACED BY NEW COMPONENTS. ORIGINAL ENGINE EQUIPMENT SUCH AS OIL-TO-FUEL HEATERS AND GOVERNORS SHOULD BE RETURNED WITH THE ENGINE. (1)

If only a small quantity of slivers or fuzz type material or non-magnetic material is found, clean chip detector and continue operation. Recheck both chip detectors and oil filter within the next 15 flight hours. NOTE:

Clean poles on chip detector by wiping with a lint-free cloth; discard cloth after cleaning.

(2)

When a quantity of material is substantially larger than that needed to form a single chain bridging the magnet poles or if nugget shaped pieces of various sizes are found, send engine to an approved overhaul facility for inspection.

(3)

Examine threads for damage. Chase threads as required. Replace detector if threads are badly damaged or crossed. NOTE:

(4)

Any rejection of one part is cause for rejection of the other since the two parts of the chip detector are not individually procurable. Component parts of chip detectors should remain in sets and not mixed.

If valve housing remains installed in the gearbox, examine for excessive oil leakage indicating internal preformed packing valve seat is deteriorated or non-metallic valve has not seated properly. NOTE:

After draining oil from reduction gearbox, the valve housing may be removed and preformed packings may be replaced. If non-metallic valve functioning indicates sticking, or broken spring, replace complete chip detector.

(5)

Connect ohmmeter across detector output terminals and place suitable steel bar across magnet poles. Circuit continuity must exist.

(6)

Check output terminal pins and condition of potting compound. If pins are loose or if compound is cracked, reject complete detector.

(7)

Inspect witness stripes on chip detector body and connector. If stripes are displaced, reject chip detector. If stripes are not apparent, paint (PWC07-006) three stripes equispaced on body and connector. Threads of connector must be free of paint. NOTE:

Chip detectors P/N 3029199, change letter B and subsequent, incorporate an internal splined locking arrangement that prevents movement; therefore, witness stripes are not required.

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F.

Inspection of Propeller Shaft Oil Seal (1)

Examine visible area of oil seal contact area for damage and wear. If oil leakage at the OD of the seal is suspected, replace oil seal as follows: (a) Remove old seal element (Ref. Para. 5.A. and B.). (b) Clean seal cavity of thrust bearing cover using solvent (PWC11-027). (c) Apply adhesive (PWC08-002) or (PWC09-001) in seal cavity. (d) Install new seal element (Ref. Para. 5.E.and F.). Remove excess adhesive and cure per manufacturer’s instructions.

8.

Approved Repairs A.

B.

Replacement of Accessory Drive Seal (1)

Remove accessory unit, if applicable, from mounting pad on reduction gearbox.

(2)

Remove seal and seal carrier (Ref. 72-60-00, Ng tachometer-generator).

(3)

Install replacement seal (Ref. 72-60-00, Ng tachometer-generator).

(4)

Reinstall accessory unit, as applicable.

Repair of Thrust Bearing Cover (Corroded Seal Cavity) NOTE:

C.

Mask bearing and propeller shaft, to prevent ingress of debris.

(1)

Remove corrosion from seal cavity contact surface using abrasive cloth (PWC05-061).

(2)

Clean area with solvent (PWC11-027).

(3)

Apply adhesive (PWC08-002) at corroded surface following manufacturer’s instructions. Remove excess adhesive.

(4)

Install new seal element (Ref. Para. 5.E. and F.).

(5)

Allow adhesive to cure following manufacturer’s instructions.

Propeller Shaft - On Wing Repair of Coating (Post-SB3362) (Ref. Fig. 206) (1)

Remove the propeller shaft seal half plates (Ref. Removal/Installation). NOTE:

(2)

Keep the seal in position to prevent contamination of the RGB internal components.

Mask the seal, the propeller mounting face and all areas marked NP per SPOP 19 to protect them from damage and overspray.

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A

A AFTER PIN INSTALLATION

NP

NP IN BOLT HOLES

VIEW

A

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CAUTION: DO NOT REMOVE TIN FLASH FROM BOLT HOLES. (3)

Remove all traces of tin flash from Area A with an abrasive pad (Ref. Fig. 206).

(4)

Roughen Area A with 240 Grit abrasive paper (PWC05-270).

(5)

Clean Area A with isopropyl alcohol (PWC11-014).

(6)

Coat the propeller shaft, Area A, as follows: (a) Apply one coat of epoxy primer (PWC13-001) using SPOP 148 to a dry film thickness between 0.0005 to 0.0010 inch. (b) Allow the primer to dry at room temperature for a minimum of one hour in a clean dust free environment. (c) Apply two coats of aluminum epoxy enamel (PWC05-037) using SPOP 148 to a total dry film thickness of 0.002 to 0.004 inch. NOTE:

D.

Allow the enamel to dry 24 hours at room temperature between coats.

(7)

Remove the masking from the propeller shaft and propeller shaft seal.

(8)

Inspect the propeller shaft seal. Replace the seal if it is damaged.

(9)

Install the propeller shaft seal half plates (Ref. Removal/Installation).

Propeller Shaft Anti-corrosion Treatment (Alternate Method) (1)

Touch-up existing coated areas: (a) If required, remove the propeller shaft seal retaining rings. CAUTION: INSTALL PROTECTIVE COVERS TO PROTECT THE SHAFT FLANGE AND GEARBOX DURING THE CLEANING AND COATING PROCEDURES. (b) Mask the bore containing the propeller shaft seal and the propeller shaft flange bolt holes. (c) Use abrasive cloth (PWC05-061) to remove any corrosion and/or stains on the propeller shaft. (d) Use a swab dipped in acetone (PWC11-012) or isopropyl alcohol (PWC11-014) to clean the surface to be coated. (e) Apply coating (PWC07-023): CAUTION: THOROUGHLY MIX THE ALUMINUM AND ZINC COATING PAINT (PWC07-023) BEFORE USE. TO PRODUCE A CONSTANT COATING, THE MIXTURE MUST BE CONTINUALLY STIRRED, DUE TO THE HIGH DENSITY OF THE PIGMENT. 1

Use a fine brush to apply a thin, even coat of paint.

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2

Allow the coating to dry for a minimum of four hours. NOTE:

3

E.

Immediately clean the brush in warm water.

Apply a second coat. a

The second coat can be handled after 30 minutes and will be completely dry in 28 to 48 hours, or air dry for 10 minutes and use a heat gun to cure for 30 minutes minimum.

b

Use a nylon pad to polish the touch-up area.

Repair of Corrosion - Front and Rear Reduction Gearbox Housing NOTE:

Corrosion must not be deeper than 0.010 in. and must not cover an area greater than 30 percent of the total surface of the front and rear RGB housing.

(1)

Apply a suitable covering material around the area to be repaired.

(2)

Clean the surface of the area to be repaired with a swab soaked in isopropyl alcohol (PWC11-014) and crocus cloth (PWC05-061).

(3)

Remove all traces of corrosion (magnesium oxide) using a suitable steel brush, crocus cloth (PWC05-061), abrasive cloth (PWC05-101), file or grit paper. Remove all traces of debris using a vacuum cleaner.

(4)

Flush the area with clean water at room temperature.

(5)

Dry the area with clean compressed air at 29 psig.

WARNING: 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. (6)

Prepare a chrome pickle solution (Ref. Chap. 70-00-00, MAINTENANCE PRACTICES, Touch-Up Solution).

(7)

Using a swab or brush, apply the chrome pickle solution, at a temperature of 17° to 29°C (55° to 85°F), to the prepared surface for 30 to 45 seconds. NOTE:

Repeat the application frequently to make sure that the affected surface is continually wet with the solution.

(8)

Swab the area with clean water until successive swabs are no longer stained yellow.

(9)

Dry the area with local heating (air dry or a heat gun at a low setting).

(10)

Clean the affected area with a rag soaked in clean water.

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(11)

Dry the area with clean, compressed air at 29 psig.

(12)

Apply two coats of primer (PWC13-001). NOTE:

The primer can be diluted with 10% solvent.

(13)

Allow the primer to air dry for eight hours before applying enamel paint. Use compressed air at 29 psig to accelerate the drying time.

(14)

Apply three to four coats of enamel (PWC05-037) to the primed surface. Allow the surface of the enamel to become tacky (approximately 15 minutes) between each coat. The final coat of enamel must dry for 24 hours before returning the engine to service. NOTE:

Drying time for the primer and paint can be reduced with the use of a heat gun at a low setting. Refer to the manufacturer’s instructions.

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Dec 10/2010 Dec 10/2010

Contents

1 2

Dec 10/2010 Dec 10/2010

72-20-00 Description and Operation

1 2

Sep 24/99 Sep 24/99

72-20-00 Maintenance Practices

201 202 203 204 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220

Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 Dec 10/2010 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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TABLE OF CONTENTS SUBJECT

PAGE

COMPRESSOR AIR INLET CASE - DESCRIPTION AND OPERATION

72-20-00

1.

General

1

2.

Description and Operation

1

A.

Compressor Inlet Case

1

B.

Air Inlet Screen

1

C.

Oil Level Sight Glass (Post-SB3368, PT6A-42A Engines)

1

COMPRESSOR AIR INLET CASE - MAINTENANCE PRACTICES

72-20-00

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation

202

A.

Removal of Air Inlet Screen

202

B.

Removal of Oil Level Sight Glass (Post-SB3368, PT6A-42A)

202

C.

Removal of Oil Tank Pressurizing Valve (Pre-SB3412, PT6A-42A)

202

Removal of Oil Tank Pressurizing Valve (Post-SB3412, PT6A-42A)

202

E.

Installation of Air Inlet Screen

203

F.

Installation of Oil Level Sight Glass (Post-SB3368, PT6A-42A)

205

D.

G. Installation of Oil Tank Pressurizing Valve (Pre-SB3412, PT6A-42A) H. 6.

Installation of Oil Tank Pressurizing Valve (Post-SB3412, PT6A-42A)

205 205

Cleaning/Painting

205

A.

Cleaning of Air Inlet Screen

205

B.

Cleaning of Oil Level Sight Glass (Post-SB3368, PT6A-42A)

207

C.

Cleaning of Oil Tank Pressurizing Valve (PT6A-42A only)

207

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

COMPRESSOR AIR INLET CASE - MAINTENANCE PRACTICES (Cont’d) 7.

8.

9.

72-20-00

Inspection/Check

207

A.

Inspection of Air Inlet Screen

207

B.

Inspection of Compressor Inlet Case Expansion Plugs

207

C.

Inspection of Oil Level Sight Glass (Post-SB3368, PT6A-42A)

207

D.

Inspection of Compressor Air Inlet Surfaces

209

E.

Inspection of Oil Tank Pressurizing Valve (PT6A-42A only)

209

Approved Repairs

212

A.

212

Repair of Air Inlet Screen Edge

B.

Repair of Air Inlet Screen (P/N 3023044) Spacer Bonding

212

C.

Repair of Corrosion - Compressor Inlet Case

212

D.

Repair of Oil Tank Pressurizing Valve (Heavy Maintenance Only) (PT6A-42A)

215

Fits and Clearances

218

A.

General

218

B.

Dimensional Checks

218

C.

Torque Limits

218

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72-20 CONTENTS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR AIR INLET CASE - DESCRIPTION AND OPERATION 1.

General A.

2.

The compressor inlet case is a component of the engine gas generator assembly and directs incoming air to the compressor rotor assembly. An air inlet screen prevents debris entering the compressor inlet.

Description and Operation (Ref. Fig. 1) A.

Compressor Inlet Case The compressor inlet case is a circular alloy casting that forms an annular plenum chamber for the passage of air to the compressor rotor. Two mounting flanges are incorporated; Flange F at the front provides mounting for the gas generator case while Flange G at the rear, provides mounting for the accessory gearbox. The inlet case also forms a compartment for the forward face of the integral oil tank. Housed in the inlet case is the No. 1 bearing assembly with its associated rotor and stator seals and the No. 1 bearing oil jet. The bearing outer housing and rear stator air seal are secured to the centerbore flange by four bolts. The No. 1 bearing outer race is secured within the bearing inner housing by an externally threaded retaining ring and locking rivet, while the inner housing is secured to the outer housing by four bolts and nuts at the rear. A calibrated oil nozzle, installed at the end of a cored passage in the compressor inlet case at approximately the 5 o’clock position, provides lubrication for the No. 1 bearing. A cored outlet port at the 6 o’clock position allows scavenge oil to flow to the accessory gearbox, via a transfer tube in the oil tank and port in the accessory gearbox diaphragm. Compressor interstage air is applied to the center of the rear stator air seal to prevent oil from the No. 1 bearing area flowing into the compressor section. Part of the air, at the center of the seal, vents forward and into the inlet air stream while the remainder vents to the rear and into the accessory gearbox via the oil tank center tube. The oil filter, oil filter housing, check and bypass valve assembly is installed at the 3 o’clock position on the inlet case with the check valve located in the outlet port of the oil pump. A cover plate, with a teflon spacer, bolted to the inlet case retains the oil filter and housing. A tube, with preformed packings, is installed between the centerbore of the inlet case and the accessory gearbox diaphragm to provide a passage for the accessory drive coupling shaft.

B.

Air Inlet Screen The air inlet screen is an open mesh screen wrapped around the periphery of the inlet case to prevent entry of large objects that may bypass the airframe cowling inertial separator vanes.

C.

Oil Level Sight Glass (Post-SB3368, PT6A-42A Engines) An oil level sight glass is located on the side of the air inlet case at the 10 o’clock position.

72-20-00 COMPRESSOR AIR INLET CASE - DESCRIPTION AND OPERATION

Page 1 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR AIR INLET SCREEN

COMPRESSOR INLET CASE FLANGE

G

ACCESSORY GEARBOX (REF.) FLANGE

F BREATHER TUBE

NO. 1 BEARING STATOR AIR SEAL

OIL TANK CENTER TUBE

NO. 1 BEARING

FWD ACCESSORY GEARBOX INPUT COUPLING SHAFT (REF.)

NO. 1 BEARING SUPPORT HOUSING PRESSURE OIL CORED PASSAGE

NO. 1 BEARING OIL NOZZLE

NO. 1 BEARING SCAVENGE OIL CORED PASSAGE TRANSFER TUBE

OIL PUMP

NO. 2 BEARING SCAVENGE OIL

C48A Compressor Inlet Case and Air Inlet Screen Installation Figure 1

72-20-00 COMPRESSOR AIR INLET CASE - DESCRIPTION AND OPERATION

Page 2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR AIR INLET CASE - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire, unless otherwise specified, shall comply with specification AMS5687, heat and corrosion resistant steel wire MS9226-03, 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

PWC04-004 PWC04-005 PWC05-019 PWC05-037 PWC05-061 PWC05-064 PWC05-101 PWC05-145 PWC06-002 PWC08-002 PWC09-022 PWC11-012 PWC11-014 PWC11-027 PWC11-031 PWC13-001

Grease, High Temperature Grease, Exterior (Extreme) Pressure Compound, Lapping Enamel, Aluminized Cloth, Coated Abrasive Solution, Anodize Touch-Up Cloth, Abrasive Compound, Lapping (Silicon Carbide) Petrolatum, White Adhesive, Fluorosilicone Compound, Jointing (Non-curing) Acetone, Methyl Alcohol, Isopropyl Solvent, Petroleum Cleaner, Engine Primer, Epoxy

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

5.

Removal/Installation A.

Removal of Air Inlet Screen (Ref. Fig. 201)

CAUTION: KEEP COMPRESSOR INLET AREA CLEAR OF ALL FOREIGN OBJECTS THAT COULD BE INGESTED BY ENGINE DURING SUBSEQUENT OPERATION. (1) For PT6A-38/-41/-42A Engines: Remove self-locking nuts (2), washers (3, Pre-SB3406 only) and bolts (4) fastening air inlet screen (1) flanges at 4 o’clock position. (2) For PT6A-42 Engines: Remove self-locking nuts (2), washers (3, Pre-SB3406 only) and bolts (4) fastening air inlet screen (1) flanges at 3 o’clock position. (3)

Carefully open screen and withdraw from around compressor inlet case.

CAUTION: IF ANY OBJECT FALLS INTO ENGINE COMPRESSOR INLET, ALL WORK MUST CEASE UNTIL OBJECT IS RECOVERED. (4) B.

C.

D.

To protect compressor inlet area from foreign object ingress, cover entire inlet area with suitable polyethylene or similar sheeting.

Removal of Oil Level Sight Glass (Post-SB3368, PT6A-42A) (Ref. Fig. 202) (1)

Drain engine oil (Ref. 72-00-00, SERVICING, Lubricating Oil System).

(2)

Remove bolts (1) and washers (2) which fasten the oil level sight glass (3) to the air inlet case.

(3)

Remove the oil level sight glass (3) and preformed packings (4). Discard preformed packings.

Removal of Oil Tank Pressurizing Valve (Pre-SB3412, PT6A-42A) (Ref. Fig. 203) (1)

Remove nuts (1) and bolts (3) fastening bracket (4) to rear fireseal mount ring.

(2)

Remove bolts (2) and washer (5) fastening bracket (4), cover (6) and gasket (7) to compressor inlet case.

(3)

Withdraw transfer tube (8) from compressor inlet case and breather tube. Remove and discard preformed packing (9).

(4)

Install suitable protective cover to compressor inlet case.

Removal of Oil Tank Pressurizing Valve (Post-SB3412, PT6A-42A) (Ref. Fig. 203) (1)

Remove nuts (1) and bolts (3) fastening bracket (4) to rear fireseal mount ring.

(2)

Remove bolts (2) and washer (5) fastening bracket (4), cover (10) and gasket (7) to compressor inlet case.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

E.

(3)

Withdraw valve assembly (16) from compressor inlet case and internal breather tube. Remove and discard preformed packing (9).

(4)

Install suitable protective cover to compressor inlet case.

Installation of Air Inlet Screen (Ref. Fig. 201)

CAUTION: IF ANY OBJECT FALLS INTO ENGINE COMPRESSOR INLET, ALL WORK MUST CEASE UNTIL OBJECT IS RECOVERED. (1)

Remove any protective covering from compressor inlet area, and make sure area is free of foreign material or loose components.

(2)

PT6A-38/-41/-42 Engines: Apply compound (PWC04-004) or (PWC04-005) to inner circumference of rubber rims of air inlet screen.

(3)

PT6A-42A Engines: (a) Pre-SB3452: Apply compound (PWC06-002) to inner circumference of rubber rims of air inlet screen. (b) Post-SB3452: Apply compound (PWC09-022) sparingly to circumferential mating surfaces of screen prior to assembly on engine (REF. NO. 1334, Fits & Clearances).

(4)

For PT6A-38/-41 Engines: Carefully install air inlet screen (1) over compressor inlet case, inserting screen between case and external fittings and lines. Locate flange mating faces at 4 o’clock position, midway between ends of liquid injection spray ring on rear mount ring.

(5)

For PT6A-42A Engines: Carefully install air inlet screen (1) over compressor inlet case, inserting screen between case and external fittings and lines. Locate flange mating faces at 11 o’clock position, midway between ends of liquid injection spray ring on rear mount ring.

(6)

For PT6A-42 Engines: Carefully install air inlet screen (1) over compressor inlet case, inserting screen between case and external fittings and lines. Locate flange mating faces at 3 o’clock position, midway between ends of liquid injection spray ring on rear mount ring.

(7)

Insert bolts (4) through screen flanges, and install self-locking nuts (2) and washers (3, Pre-SB3406 only). Tighten self-locking nuts fingertight only.

(8)

On air inlet screen P/N 3023044 only: Measure unstressed gap between two flanges (Ref. Fig. 201, Detail A and Fig. 205). If gap between flanges is between 0.000 and 0.150 inch, do next step. If gap between flanges exceeds 0.151 inch, refer to Para. 8.B.. NOTE:

(9)

Air inlet screens (P/Ns 3023043 and 3023695) have controlled inside diameters and do not require gap measurement on installation.

Torque flange self-locking nuts 12 to 15 lb. in.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

5

DETAIL

4

A

PRE−SB3406 3 2

1

A

C388B Removal/Installation of Air Inlet Screen Figure 201 P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 201 1. 2. 3. 4. 5. F.

Air Inlet Screen Self-locking Nut Washer (Pre-SB3406 only) Bolt Spacer(s) (Used with screen P/N 3023044 only)

Installation of Oil Level Sight Glass (Post-SB3368, PT6A-42A) (Ref. Fig. 202) (1)

Make sure that the mating face of the compressor air inlet case is smooth and clean.

(2)

Install new lubricated preformed packings (4) and oil level sight glass (3) to compressor air inlet case with washers (2) and bolts (1). Torque bolts in a diametric sequence 24 to 36 lb.in. and lockwire.

(3)

Refill engine oil system (Ref. 72-00-00, SERVICING, Lubricating Oil System) and test run engine (Ref. 71-00-00, ADJUSTMENT/TEST, General). Check for oil leaks.

G. Installation of Oil Tank Pressurizing Valve (Pre-SB3412, PT6A-42A) (Ref. Fig. 203)

H.

6.

(1)

Install new lubricated preformed packing (9) on transfer tube (8) and insert through compressor inlet case into internal breather tube.

(2)

Install new gasket (7), cover (6) and support bracket (4) to compressor inlet case with bolts (2) and washer (5). Tighten bolts 36 to 40 lb.in. and lockwire.

(3)

Install support bracket (4) to rear fireseal mount ring with bolts (3) and nuts (1). Torque nuts 36 to 40 lb.in.

Installation of Oil Tank Pressurizing Valve (Post-SB3412, PT6A-42A) (Ref. Fig. 203) (1)

Install new lubricated preformed packing (9) on valve assembly (16) and insert through compressor inlet case into internal breather tube.

(2)

Install new gasket (7), cover (10) and support bracket (4) to compressor inlet case with bolts (2) and washer (5). Tighten bolts 36 to 40 lb.in. and lockwire.

(3)

Install support bracket (4) to rear fireseal mount ring with bolts (3) and nuts (1). Torque nuts 36 to 40 lb.in.

Cleaning/Painting A.

Cleaning of Air Inlet Screen (1)

Clean wire mesh using solvent (PWC11-027) or (PWC11-031). Dry with clean, dry compressed air.

(2)

Clean sealing rim and flange of air inlet screen (Location X, Fig. 205) with acetone (PWC11-012) or isopropyl alcohol (PWC11-014).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A

4 3

2 1

VIEW

A C69528

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 202 1. 2. 3. 4. (3) B.

Clean with warm, soapy water and soft nylon brush.

Cleaning of Oil Tank Pressurizing Valve (PT6A-42A only) (1)

7.

When new spacer(s) are installed (on air inlet screen P/N 3023044 only), clean flange of inlet screen and mating face(s) of spacer(s) (Ref. Para. 8.B.).

Cleaning of Oil Level Sight Glass (Post-SB3368, PT6A-42A) (1)

C.

Bolts (Post-SB3368) Washers (Post-SB3368) Oil Level Sight Glass (Post-SB3368) Preformed Packings (Post-SB3368)

Clean components by flushing or spraying with solvent (PWC11-027) or (PWC11-031). Make sure bores are clean and free of obstructions. Dry components with clean, dry, compressed air.

Inspection/Check A.

B.

C.

Inspection of Air Inlet Screen (1)

Inspect air inlet screen wire mesh for cleanliness and damage. Screens with broken wire mesh must be replaced. Clean undamaged screens (Ref. Para. 6.A.).

(2)

Inspect rubber sealing rims for security and condition. Screens with detached wire mesh/sealing rim bond must be replaced. Sealing rim unbonding at screen flanges (Location X, Fig. 205) should be repaired (Ref. Para. 8.B.).

(3)

On air inlet screen P/N 3023044, inspect flange spacer(s) if fitted, for security and condition. Damaged or loose spacer(s) should be replaced (Ref. Para. 8.B.).

Inspection of Compressor Inlet Case Expansion Plugs (1)

Drain oil from engine (Ref. 70-00-00, SERVICING).

(2)

Remove oil filter housing (Ref. 79-20-02, MAINTENANCE PRACTICES, Removal/Installation).

(3)

Insert a suitable mirror through oil filter housing bore and with a strong light source, locate the upper and lower expansion plugs on the compressor inlet case. Check for liberation of either or both plugs.

(4)

If either or both plugs are loose, ship engine to an approved overhaul facility.

Inspection of Oil Level Sight Glass (Post-SB3368, PT6A-42A) (1)

Examine sealing and mating surfaces for scratches, scoring and other surface damage.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

2

1

NO WASHER THIS LOCATION

3

REAR FIRESEAL (REF.) 4

2 5

10

2

7 5 11 6 PRE−SB3412

12 7

16

13

POST−SB3412

14

8

15 9

C96257

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Key to Figure 203 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. (2) D.

Nut (Ref.) Bolt Bolt (Ref.) Bracket Washer Cap (Pre-SB3412) Gasket Transfer Tube (Pre-SB3412) Packing Cover (Post-SB3412) Pin (Post-SB3412) Seat (Post-SB3412) Piston (Post-SB3412) Spring (Post-SB3412) Housing (Post-SB3412) Valve Assembly (Post-SB3412)

Check sealing of lens preformed packings with gage frame for possible leakage. Replace preformed packings are required.

Inspection of Compressor Air Inlet Surfaces (1)

Remove the inlet screen (Ref. Para. 5.A.).

(2)

Use a suitable mirror or flash light to inspect the inlet throat area, struts, radii and mating surfaces for corrosion.

(3)

If any corrosion is found, then repair the damaged area (Ref. Para. 8.C.). (a) If corrosion is within repairable limits the engine can be returned to service for a maximum of 10 hours for the purpose of scheduling for the repair in accordance with Para. 8.C. It is recommended to perform a compressor and compressor turbine desalination wash prior to the next flight (Ref. 71-00-00).

E.

Inspection of Oil Tank Pressurizing Valve (PT6A-42A only) (1)

Examine for wear or corrosion.

(2)

Valve seats must be free of scoring and/or pitting.

(3)

Repair as required (Ref. Para. 8.).

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PLUGS CAN BE VIEWED THROUGH OIL FILTER HOUSING BORE

A

VIEW OF COMPRESSOR INLET CASE WITH ACCESSORY GEARBOX OMITTED FOR CLARITY

UPPER EXPANSION PLUG

LOWER EXPANSION PLUG

VIEW ON ARROW A

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BOND AIR INLET SCREEN SPACER TO EITHER ONE OF SCREEN RETAINING FLANGES

SCREEN RETAINING BOLTS CHAFING STRIPS

X AIR INLET SCREEN

UNSTRESSED FLANGE GAP CLEARANCE

X X

X

AIR INLET SCREEN SPACER (TYPICAL)

CHECK FLANGE GAP DIMENSION WITH RETAINING BOLTS INSTALLED AND NUTS TIGHTENED FINGER TIGHT ONLY

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8.

Approved Repairs A.

Repair of Air Inlet Screen Edge (Ref. Fig. 205) (1)

Apply adhesive/sealant (PWC08-002) to mating surfaces of sealing rim and screen flange (Location X, Fig. 204).

(2)

Press bonded surfaces together and hold in position with suitable clamp or weights.

(3)

Allow adhesive to cure for a minimum of two hours at room temperature before installing screen. NOTE:

B.

Repair of Air Inlet Screen (P/N 3023044) Spacer Bonding (Ref. Fig. 205) (1)

Select appropriate spacer (Ref. IPC) as determined at initial assembly.

(2)

Clean mating surfaces of flange and spacer(s) (Ref. Para. 6.A.(3)).

(3)

Apply a thin coat of adhesive sealant (PWC08-002) to mating face of flange and spacer(s).

(4)

Press bonded surfaces together and install bolts, washers and self-locking nuts. Tighten nuts fingertight only.

(5)

Allow adhesive to cure for a minimum of two hours at room temperature. NOTE:

C.

A total of 72 elapsed hours are needed to fully cure bond. Placing screen into service before sufficient time has elapsed, and exerting pressure, will cause adhesive to exude and weaken bond.

A total of 72 elapsed hours are needed to fully cure bond. Placing screen into service before sufficient time has elapsed, and exerting pressure, will cause adhesive to exude and weaken bond.

Repair of Corrosion - Compressor Inlet Case (1)

For PT6A-38/-41/-42 engines with aluminum compressor air inlet cases only: (a) Allowable limits of corrosion 1

Corrosion must not be deeper than 0.010 in. on the inlet struts and adjacent radii.

2

Local wall thinning (in all areas, except for struts) up to 0.025 in. Max. locally within a 1 in. sq. area and must not exceed 10 percent of the total surface of the inlet case.

3

If corrosion exceeds depth of 0.025 in. on casing, remove Gas Generator Module (Ref. 72-00-00, REMOVAL AND INSTALLATION) and send to an approved P&WC overhaul facility.

(b) Apply a suitable covering material over the compressor section.

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(c) Clean the surface of the area to be repaired with a swab soaked in isopropyl alcohol (PWC11-014) and crocus cloth (PWC05-061). (d) Remove all traces of corrosion (aluminum oxide) using a suitable steel brush, crocus cloth (PWC05-061), abrasive cloth (PWC05-101), file or grit paper. Remove all traces of debris using a vacuum cleaner. (e) Flush the area with clean water at room temperature. (f)

Locally clean the repaired surface and surrounding area using a swab soaked in acetone (PWC11-012) or isopropyl alcohol (PWC11-014) and a crocus cloth (PWC05-061). Remove all debris using a vacuum cleaner.

(g) Apply anodize touch-up solution (PWC05-064) using a swab or brush for three to four minutes. NOTE: 1. Repeat the application frequently to make sure that the affected surface is continually wet with the solution. NOTE: 2. If the solution does not wet the surface, remove the solution with a clean cloth and repeat Step (d). Also, clean the first-stage compressor if the solution has been inadvertently applied. (h) Allow the surface to air dry or wipe off solution with a cloth soaked in clean water. (i)

Examine the coating and make sure that the repair surface is completely covered. Reapply the treatment again as necessary. NOTE:

(j)

After the successful completion of Step (i), the engine may be returned to service for the next 100 hours.

For a more durable repair, do the following: 1

Do Steps (c) through (g) again.

2

Dry the affected area thoroughly.

3

Apply two coats of primer (PWC13-001). NOTE:

The primer can be diluted with 10% solvent.

4

Allow the primer to air dry for eight hours before applying enamel paint. Use compressed air at 29 psig to accelerate the drying time.

5

Apply three to four coats of enamel (PWC05-037) to the primed surface. Allow the surface of the enamel to become tacky (approximately 15 minutes) between each coat. Allow a final coat of enamel paint to dry for 24 hours before returning the engine to service. NOTE:

Drying time can be reduced with the use of a heat gun at a low setting. Refer to the manufacturers instructions.

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(k) If the corrosion repair is more than the maximum permitted limits, inspect the repaired area again, at intervals not exceeding 10 flight hours. The engine must be returned to an approved overhaul facility within 50 flight hours for a repair to be done. (2)

For P/N 3113749-01 and PT6A-42A engines with magnesium compressor air inlet cases only (Ref. Fig. 206): (a) Repairable limits of corrosion except for specific areas (Ref. Fig. 206): 1

Corrosion must not be deeper than 0.010 in. on the inlet struts and adjacent radii.

2

Local wall thinning (in all areas, except for struts) up to 0.025 in. Max. locally within a 1 in. sq. area and must not exceed 10 percent of the total surface of the inlet case.

3

If corrosion exceeds repairable limits, remove Gas Generator Module (Ref. 72-00-00, REMOVAL AND INSTALLATION) and send to an approved P&WC overhaul facility.

(b) Apply a suitable covering material over the compressor section. (c) Clean the surface of the area to be repaired with a swab soaked in isopropyl alcohol (PWC11-014) and crocus cloth (PWC05-061). (d) Remove all traces of corrosion (magnesium oxide) using a suitable steel brush, crocus cloth (PWC05-061), abrasive cloth (PWC05-101), file or grit paper. Remove all traces of debris using a vacuum cleaner. (e) Flush the area with clean water at room temperature. (f)

Dry the area with clean compressed air at 29 psig.

WARNING: 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. (g) Prepare a chrome pickle solution (Ref. Chap. 70-00-00, MAINTENANCE PRACTICES, Touch-Up Solution). (h) Using a swab or a brush, apply the chrome pickle solution, at a temperature of 17° to 29°C (55° to 85°F), to the prepared surface, for 30 to 45 seconds. NOTE:

Repeat the application frequently to make sure that the affected surface is continually wet with the solution.

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72-20-00

COMPRESSOR AIR INLET CASE - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(i)

Swab the area with clean water until successive swabs are no longer stained yellow.

(j)

Dry the area with local heating (air dry or a heat gun at a low setting).

(k) Clean the affected area with a rag soaked in clean water. (l)

Dry the area with clean, compressed air at 29 psig.

(m) Apply two coats of primer (PWC13-001). NOTE:

The primer can be diluted with 10% solvent.

(n) Allow the primer to air dry for eight hours before applying enamel paint. Use compressed air at 29 psig to accelerate the drying time. (o) Apply three to four coats of enamel (PWC05-037) to the primed surface. Allow the surface of the enamel to become tacky (approximately 15 minutes) between each coat. The final coat of enamel must dry for 24 hours before returning the engine to service. NOTE:

Drying time for the primer and paint can be reduced with the use of a heat gun at a low setting. Refer to the manufacturers instructions.

(p) If the corrosion repair is more than the maximum permitted limits, inspect the repaired area again, at intervals not exceeding 10 flight hours. The engine must be returned to an approved overhaul facility within 50 flight hours for a repair to be done. D.

Repair of Oil Tank Pressurizing Valve (Heavy Maintenance Only) (PT6A-42A) (Ref. Fig. 203) (1)

Remove pin (11) fastening valve seat (12), piston (13) and spring (14) in valve housing (16).

(2)

Clean valve components (Ref. Para. 6.).

(3)

Lap valve seat (12) to give 360 degree surface contact using compound (PWC05-019) or (PWC05-145).

(4)

Thoroughly clean the valve seat (Ref. Para. 6.).

(5)

Insert spring (14) and piston (13) into housing (15). Screw valve seat (12) in until travel stops, to compress spring to minimum height.

(6)

Back off valve seat (12) 2.5 turns (0.104 in.).

(7)

Fasten the valve components into housing (15)with spring (14).

(8)

Install the valve assembly into the compressor inlet case (Ref. Para. 5.).

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

72-20-00

COMPRESSOR AIR INLET CASE - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

SEE DETAIL

A

SEE DETAIL

B

P/N 3113749-01 and PT6A-42A Engines Only

C79512

Repair of Corrosion - Compressor Inlet Case (Typical) Figure 206 (Sheet 1 of 2) P&WC Proprietary Information. Subject to the restrictions on the title page.

72-20-00

COMPRESSOR AIR INLET CASE - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

MAXIMUM CIRCUMFERENTIAL ALLOWABLE LENGTH = 5.000 IN. INLET CASE

.250

.500

EXTENT OF TOUCH−UP REPAIR

COMPRESSOR SHROUD

EXTENT OF TOUCH−UP REPAIR

DETAIL

A

DETAIL

B

.060

P/N 3113749-01 and PT6A-42A Engines Only

C79513

Repair of Corrosion - Compressor Inlet Case (Typical) Figure 206 (Sheet 2) P&WC Proprietary Information. Subject to the restrictions on the title page.

72-20-00

COMPRESSOR AIR INLET CASE - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

9.

Fits and Clearances A.

General The following provide the fits and clearances, torques, spring pressures, special assembly, and backlash checks where applicable. The REF. NO. should be used in conjunction with Figure 207.

B.

Dimensional Checks The DIMENSIONS FOR REF. column indicates minimum and maximum manufacturing dimensions of two mating parts. These dimensions are provided for information only. The LIMITS column indicates the desired minimum and maximum fits and clearances between new parts, and also the allowable limit to which these parts may wear before replacement is necessary. The letter T indicates a tight fit; L or no letter, a loose fit. BY SELECTION means parts must be matched by selection to provide a required fit. FIT TO means a fitting operation may be required at assembly to obtain the required fit. An asterisk (*) indicates part(s) should be replaced if any looseness is evident. Unless otherwise stated, all fits are diametrical. Spline fits are calculated from chordal dimensions.

C.

Torque Limits Unless otherwise stated, apply thread lubricant to all parts that are to be torque-loaded. Use engine lubricating oil or equivalent, unless otherwise specified. Where torque limits for castle nuts are provided in the MINIMUM column only, these nuts should be tightened to the designated torque and then further tightened, if necessary, to properly align the locking slots and holes. Where MINIMUM and MAXIMUM values are given, the alignment of the locking slot must be obtained without loosening the nut and without exceeding the maximum limit. If this is not possible, back-off the nut half a turn, then retighten. If alignment cannot be accomplished, select another nut. Torque requirements for interference fit applications, such as studs, may be obtained with or without lubrication, unless otherwise specified. TABLE 201, Fits and Clearances

REF. NO.

Dim. for Ref. (inches) Name

Min.

Max.

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

Limits (inches) Min.

Max.

72-20-00

COMPRESSOR AIR INLET CASE - MAINTENANCE PRACTICES

Replace

Page 218 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 202, Torque and Stretch Limits REF. NO.

Name

Min.

Max.

TABLE 203, Spring Pressures Limits REF. NO.

Name

Min.

Max.

Not Applicable

TABLE 204, Special Assembly Procedures Limits REF. NO. 1334

Name

Min.

Max.

Post-SB3452 (1)

Apply compound (PWC09-022) sparingly to circumferential mating surfaces of screen prior to assembly on engine (For PT6A-42A only).

TABLE 205, Backlash Limits REF. NO.

Name

Min.

Max.

Not Applicable

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

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

1334

C171726 Fits and Clearances Figure 207 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-20-00

COMPRESSOR AIR INLET CASE - MAINTENANCE PRACTICES

Page 220 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Dec 05/2008 Dec 05/2008

Contents

1 2 3 4

Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008

72-30-00 Description and Operation

1 2 blank

Sep 24/99 Sep 24/99

72-30-01 Description and Operation

1 2 blank

Sep 24/99 Sep 24/99

201 202 203 204 blank

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

1 2 blank

Sep 24/99 Sep 24/99

201 202 203 204 205 206 207 208 blank

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

1 2 blank 3 4 blank

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

72-30-01 Maintenance Practices

72-30-02 Description and Operation 72-30-02 Maintenance Practices

72-30-04 Description and Operation

CHAPTER SECTION

PAGE

72-30-04 Maintenance Practices

72-30-05 Description and Operation

72-30-05 Maintenance Practices

201 202 203 204 205 206 207 208 209 210 211 212 213 blank 214 215 216 blank 1 2 3 4 blank 201 202 203 204 205 206 207 208 209 210 211 212 blank

DATE Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/2004 Sep 24/2004 Sep 24/2004 Sep 24/2004 Sep 24/2004 Sep 24/2004 Sep 24/2004 Sep 24/2004 Sep 24/2004 Sep 24/2004 Sep 24/2004 Sep 24/2004

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

72-30 LEP

Page 1/2 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

GAS GENERATOR ASSEMBLY - DESCRIPTION AND OPERATION 1.

Description and Operation

1

CENTER FIRESEAL MOUNT RING - DESCRIPTION AND OPERATION 1.

72-30-00

Description and Operation

72-30-01 1

CENTER MOUNT RING - MAINTENANCE PRACTICES

72-30-01

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation

201

6.

Cleaning/Painting

201

A.

201

7.

8.

Cleaning of Center Mount Ring

Inspection/Check

201

A.

201

Inspection of Center Mount Ring

Approved Repairs

202

A.

202

Repair of Mount Ring Insulating Strips )

REAR MOUNT RING - DESCRIPTION AND OPERATION 1.

Description and Operation

72-30-02 1

REAR MOUNT RING - MAINTENANCE PRACTICES

72-30-02

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 Compressor Wash Ring

201

B.

Installation of Compressor Wash Ring

204

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72-30 CONTENTS

Page 1 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

REAR MOUNT RING - MAINTENANCE PRACTICES (Cont’d) 6.

7.

8.

72-30-02

Cleaning/Painting

204

A.

Cleaning of Mount Ring

204

B.

Cleaning of Wash Ring

204

Inspection/Check

205

A.

Inspection of Mount Rings

205

B.

Inspection of Compressor Wash Ring

205

Approved Repairs

206

A.

206

Repair Mount Ring Insulating Strips

GAS GENERATOR CASE - DESCRIPTION AND OPERATION

72-30-04

1.

General

1

2.

Description and Operation )

1

GAS GENERATOR CASE - MAINTENANCE PRACTICES

72-30-04

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation

202

A.

Removal of Gas Generator Assembly (Heavy Maintenance)

202

B.

Installation of Gas Generator Assembly

202

6.

7.

8.

Cleaning/Painting

202

A.

202

Cleaning of Gas Generator Case

Inspection/Check

203

A.

203

Inspection of Gas Generator Case

Approved Repairs

206

A.

206

Corrosion Removal

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

72-30 CONTENTS

Page 2 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

GAS GENERATOR CASE - MAINTENANCE PRACTICES (Cont’d)

72-30-04

B.

Repair of Protective Coating (conversion-coat only)

206

C.

Repair of Igniter Boss Threads

208

D.

Repair of Bleed Valve Mount Pad and/or Fuel Nozzle Pad Rear Threaded Holes

208

Replacement of Bleed Valve Mount and/or Fuel Nozzle Pad Damaged Threaded Inserts

208

Repair of Fuel Nozzle Pad Front Threaded Hole

208

G. Replacement of Shanknut (Heavy Maintenance Only)

209

H.

Repair of Diffuser Exit Ducts (Heavy Maintenance Only)

209

I.

Replacement of Diffuser Exit Ducts (Heavy Maintenance Only)

212

E. F.

COMPRESSOR ROTOR - DESCRIPTION AND OPERATION

72-30-05

1.

General

1

2.

Description and Operation )

1

COMPRESSOR ROTOR - MAINTENANCE PRACTICES

72-30-05

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Inspection/Check - (First-stage Compressor Rotor)

201

A.

General

201

B.

Documenting Damage

202

C.

Acceptable Damage Limits

202

D.

Acceptable Erosion Limits

204

E.

Unacceptable Damage

204

6.

Approved Repairs

208

A.

208

Repair of Leading Edge

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72-30 CONTENTS

Page 3 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

COMPRESSOR ROTOR - MAINTENANCE PRACTICES (Cont’d) B.

Repair of Trailing Edge

72-30-05 209

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

72-30 CONTENTS

Page 4 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

GAS GENERATOR ASSEMBLY - DESCRIPTION AND OPERATION 1.

Description and Operation The gas generator section of the engine consists basically of a coupled turbine and rotor assembly mounted within two concentric cylindrical casings, also containing a vane ring/shroud assembly, exit ducting, combustion chamber and plenum chamber. This assembly forms the main body of the engine and provides the external attachment points for installation in the airframe or assembly stand. A flange at the front end of the gas generator casing forms the attachment point for the power section, and studs at the rear of the inlet case carry the accessory gearbox. The combined single-stage turbine and multi-stage compressor rotor assembly is supported on two anti-friction bearings; a roller bearing (No. 2) housed in the gas generator case, and a ball thrust bearing (No. 1) contained in a flexible housing assembly attached to the air inlet case. An external flange on the forward end of the impeller housing attaches to a mating flange on the inner casing of the gas generator structure. At the rear end, a lip on the first-stage stator housing locates in an annular recess in the air inlet case. The combustion chamber, surrounding the compressor turbine, consists of an annular liner located in the inner and outer exit ducts attached to the turbine vane ring. Protruding into, and supporting the domed end of the combustion chamber liner, are two igniters, designed to provide continuous ignition, and fourteen fuel manifold nozzle assemblies. A wire mesh screen around the annular plenum chamber of the ai rinlet case prevents the entry of foreign objects and debris into the inlet zone of the engine. The compressor bleed valve assemblies are proted from two mounting faces horizontally opposed on each side of the gas generator case. The low pressure valve is installed on the left side and high pressure valve on the right side. The fuel manifold assembly is attached around the external side of the gas generator case in the combustion zone and consists of fuel nozzle adapters interconnected by transfer tubes. Attached to the base of the fuel manifold assembly is a flow divider and dump/purge valve unti which allows residual fuel to drain on engine shutdown.

72-30-00 GAS GENERATOR ASSEMBLY - DESCRIPTION AND OPERATION

Page 1/2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CENTER FIRESEAL MOUNT RING - DESCRIPTION AND OPERATION 1.

Description and Operation The center fireseal mount ring which forms a bulkhead between the compressor air inlet zone and the front of the engine, consists of upper and lower halves with bolting flanges. Each half is manufactured from stainless steel sheet with the outer circumference contoured to suit airframe nacelle requirements. Holes for external piping and attaching parts are provided at appropriate locations in the upper and lower halves. An insulating strip is bonded to the inner circumference to provide a seal between the fireseal and the gas generator case. The upper and lower halves are bolted together to form a complete ring which is fastened to the gas generator case by mounting brackets attached to the assembly.

72-30-01 CENTER FIRESEAL MOUNT RING - DESCRIPTION AND OPERATION

Page 1/2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CENTER MOUNT RING - MAINTENANCE PRACTICES 1.

General A.

2.

It is not a necessary practice to remove the mount ring during maintenance of the engine. Removal should be dictated by the extent of repair necessary as determined during inspection. Refer to the relevant chapters in this manual for the removal/installation of lines/tubes and components passing through the rings.

Consumable Materials The consumable materials listed below are used in the following procedures. For alternate products, suppliers, and supplier addresses, refer to 72-00-00, MAINTENANCE PRACTICES.

3.

Item No.

Name

PWC08-002 PWC11-027 PWC11-029 PWC11-031

Adhesive, Fluorosilicone Solvent, Petroleum Solvent, Removing Cleaner, Engine

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation Refer to the relevant chapters in this manual for the removal/installation of lines/tubes and components passing through the mount ring.

6.

Cleaning/Painting A.

Cleaning of Center Mount Ring (1)

7.

Clean with solvent (PWC11-027) or (PWC11-031). Dry with clean, dry, compressed air.

Inspection/Check A.

Inspection of Center Mount Ring (1)

Examine mount ring halves for attachment, damage and condition. NOTE:

For external tubes/lines passing through mount rings, refer to relevant chapters in this manual.

72-30-01 CENTER MOUNT RING - MAINTENANCE PRACTICES

Page 201 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(2) 8.

Examine circumferential insulating strips for attachment. Loose strip may be rebonded (Ref. Repair).

Approved Repairs A.

Repair of Mount Ring Insulating Strips (Ref. Fig. 201) (1)

Remove old adhesive from mount ring and insulating strip with solvent (PWC11-029).

(2)

Clean surfaces (Ref. Cleaning/Painting).

(3)

Bond insulating strip to mount ring halves with adhesive sealant (PWC08-002).

(4)

Allow sealant to cure at room temperature for approximately 72 hours.

(5)

Trim insulating strip to dimensions shown. NOTE:

Seventy two hours is normal curing time of bond. Ring half may be returned to service after two to four hours, but avoid exerting pressure that would cause sealant to exude and weaken bond.

72-30-01 CENTER MOUNT RING - MAINTENANCE PRACTICES

Page 202 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A

0.060 0.000

VIEW

A

C390 Mount Ring Half- Insulating Strip Replacement Figure 201

72-30-01 CENTER MOUNT RING - MAINTENANCE PRACTICES

Page 203/204 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

REAR MOUNT RING - DESCRIPTION AND OPERATION 1.

Description and Operation A.

The rear fireseal mount ring which forms a bulkhead between the compressor air inlet zone and the accessory gearbox, consists of upper and lower halves with bolting flanges. Construction is similar to the center fireseal mount ring except for the outer circumference contours. The upper and lower halves are bolted together and secured to the compressor inlet case by mounting brackets attached to the assembly.

B.

The rear fireseal provides positioning for the compressor wash spray ring (when fitted) around the air inlet. The spray ring is supported by clips trapped under the rear edge of the air inlet screen.

72-30-02 REAR MOUNT RING - DESCRIPTION AND OPERATION

Page 1/2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

REAR MOUNT RING - MAINTENANCE PRACTICES 1.

General A.

2.

It is not a necessary practice to remove the rear fireseal mount ring during maintenance of the engine. Removal should be dictated by the extent of repair necessary as determined during inspection. Refer to the relevant chapters in this manual for the removal/installation of lines/tubes and components passing through the rings.

Consumable Materials The consumable materials listed below are identified in procedural text. For alternate products, suppliers, supplier addresses, refer to 72-00-00, MAINTENANCE PRACTICES.

3.

Item No.

Name

PWC03-001 PWC05-004 PWC05-070 PWC08-010 PWC11-014 PWC11-027 PWC11-029 PWC11-031 PWC11-032

Oil, Engine Lubricating Acid, Hydrofluoric Tape, Pressure Sensitive Adhesive Adhesive, Rubber Alcohol, Isopropyl Solvent, Petroleum Solvent, Removing Cleaner, Engine Solvent, Degreaser

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation Refer to the relevant chapters in this manual for the removal/installation of lines/tubes and components passing through the mount ring. NOTE: A.

On Post-SB3258 Engines: a maximum of four washers, two per side, may be used as spacers between top and bottom mount ring assemblies.

Removal of Compressor Wash Ring (Ref. Fig. 201) CAUTION: COVER AIR INLET SCREEN TO PREVENT OBJECTS FALLING INTO INLET. IF ANY OBJECT PASSES THROUGH SCREEN, ALL WORK MUST CEASE UNTIL OBJECT IS RECOVERED. (1)

On forward face of rear fireseal, disconnect coupling nut (4) on upper spray tube assembly (6) from water inlet tee (3).

72-30-02 REAR MOUNT RING - MAINTENANCE PRACTICES

Page 201 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

1

6

7

SECTION

A−A 6

4

VIEW

8

B

3 14

9

2

❉

5 13

A A ❉ FWD

❉ ENGRAVING ON TUBE: DELUGE WASH RING − DO NOT USE TO AUGMENT POWER

B 10 11

B

12

C9123 Removal/Installation of Compressor Wash Ring Figure 201

72-30-02 REAR MOUNT RING - MAINTENANCE PRACTICES

Page 202 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. (2)

Washers Jam nut Inlet Tee Coupling Nut Bolt Upper Tube Assembly Rivet Preformed Packing Plug Lower Tube Assembly Jam Nut Plug Coupling Nut (Lower Tube) Plug

Remove two bolts (5) that secure tube assembly brackets to fireseal mount ring, then remove upper spray tube assembly in a circular motion to clear end at reversing linkage push-pull casing. NOTE:

Two packing washers (1) are fitted between each spray tube mounting bracket and face of fireseal. These are required to position spray tube over lip of air inlet screen.

(3)

Remove plugs (12 and 14) from tee fittings (10 and 3) respectively.

(4)

Remove jam nut (11) that secures tee section of lower spray tube (10) to rear fireseal mount ring.

(5)

Disconnect coupling nut (13) of lower spray tube assembly (10) from water inlet tee (3).

(6)

Remove one bolt and two washers that secure lower spray tube (10) to rear fireseal mount ring and remove tube assembly. NOTE:

(7)

Because of restricted space between engine casing, scavenge oil tubes and ignition cables, move spray tube forward over air inlet screen until assembly is at narrow coned section of gas generator case before attempting to manoeuvre it out. Remove compressor bleed valve if necessary.

Remove jam nut (2) that secures water inlet tee (3) to rear fireseal mount ring.

72-30-02 REAR MOUNT RING - MAINTENANCE PRACTICES

Page 203 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

B.

Installation of Compressor Wash Ring (Ref. Fig. 201) CAUTION: COVER AIR INLET SCREEN TO PREVENT OBJECTS FALLING INTO INLET. IF ANY OBJECT PASSES THROUGH SCREEN, ALL WORK MUST CEASE UNTIL OBJECT IS RECOVERED. (1)

Manoeuvre lower spray tube (1) into position around narrower cone section of gas generator case, then move assembly rearward over air inlet screen and align with holes in rear fireseal mount ring. NOTE:

6.

Reinstall compressor bleed valve if removed at disassembly.

(2)

Insert two washers (1) between mounting bracket on lower spray tube and mount ring, then isntall single bolt. Tighten bolt and torque 36 to 40 lb.in.

(3)

Install jam nut (11) on tee section of spray tube, tighten and torque 38 to 42 lb.in. Install plug (12) on tee section, tighten and torque 90 to 100 lb.in. and lockwire jam nut and clip on fireseal mount ring.

(4)

Install water inlet tee (3) and secure with jam nut (2). Tighten and torque nut fingertight only.

(5)

Install upper spray tube (6) on rear fireseal mount ring. Insert two washers (1) between each mounting bracket and mount ring and secure with two bolts (5). Tighten bolts and torque 36 to 40 lb.in.

(6)

Connect coupling nuts (4 and 13) of upper and lower spray tubes to water inlet tee, aligning tee fitting as necessary. Tighten coupling nuts and torque 270 to 300 lb.in. and lockwire to clips on fireseal mount ring.

(7)

Tighten jam nut (2) and torque 70 to 80 lb.in. Install plug (14) on water inlet tee. Tighten plug and torque 110 to 120 lb.in. and lockwire to jam nut (2) and clip on mount ring.

Cleaning/Painting A.

Cleaning of Mount Ring (1)

B.

Clean with solvent (PWC11-027) or (PWC11-031). Dry with clean, dry, compressed air.

Cleaning of Wash Ring (1)

Clean tee, elbow, and plugs with solvent (PWC11-027) or (PWC11-031). Dry with clean, dry, compressed air. NOTE:

If necessary, pressure flush tee to make sure all ports are clear.

(2)

Clean exterior of spray tubes with soft cloth moistened in solvent (PWC11-027) or (PWC11-031).

(3)

Pressure flush each spray tube:

72-30-02 REAR MOUNT RING - MAINTENANCE PRACTICES

Page 204 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(a) With a suitable flexible, coiled, non-metallic brush, and lots of solvent (PWC11-027) or (PWC11-031) thoroughly scrub interior of each tube. (b) Temporarily cover all tube spray holes with pressure sensitive tape (PWC05-070). (c) Fit suitable tubing over plug end of tube and provide a suitable container for spillage. (d) Pressure flush tubes from coupling nut end with solvent (PWC11-027) or (PWC11-031), and remove tubing. (e) Remove tape from each tube, and remove adhesive residue with solvent (PWC11-027) or (PWC11-031). (f)

Install suitable slave plugs in plug ends of tubes.

(g) Pressure flush tubes with solvent (PWC11-027) or (PWC11-031). Make sure all spray holes are clear. (h) Remove slave plugs and dry each tube with clean dry compressed air. 7.

Inspection/Check A.

Inspection of Mount Rings (1)

Examine rear fireseal mount ring halves for attachment, damage and condition. NOTE:

(2) B.

For external tubes/lines passing through mount rings, refer to relevant chapters in this manual.

Examine circumferential insulating strips for attachment. Loose strip may be rebonded (Ref. Repair).

Inspection of Compressor Wash Ring (1)

Examine tee, elbow and cap for condition/damage. Repair damaged threads with suitable chaser/die.

(2)

Examine plugs for condition/damage. Replace plugs as required.

(3)

Check spray holes in each tube. Clear holes of any foreign matter with a 0.052 to 0.057 in. drill bit. DO NOT break sharp edges.

(4)

Examine brazed joints in area of coupling nuts and plugs. Cracks are not acceptable.

(5)

Examine locating brackets and support clips for proper attachment. Cracks are not acceptable.

(6)

Dents in area of holes,which could alter spray pattern, are not acceptable.

(7)

Examine tubes as follows:

72-30-02 REAR MOUNT RING - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(a) Scratches with no appreciable depth are acceptable. Scratches to 0.005 in. deep should be smoothed out (Ref. 70-00-00, REPAIR). Replace tube(s) if scratch(es) exceed 0.005 in. (b) Nicks 0.0625 in. long, by 0.010 in. wide and 0.003 in. deep are acceptable. Nicks to 0.005 in. should be smoothed out to remove sharp edges (Ref. 70-00-00, REPAIR) (c) Dents are acceptable provided they are round bottomed and length or depth does not exceed 10 percent of tube OD. No more than one dent,to maximum depth, per 12 inch length, is acceptable. (d) Minor isolated pitting to 0.003 in. deep is acceptable. Clusters should be removed and smoothed to 0.005 in. max. deep. (e) Corrosion, rust or stains are acceptable if they can be removed by light polishing with abrasive cloth (PWC05-004) and oil (PWC03-001). 8.

Approved Repairs A.

Repair Mount Ring Insulating Strips (1)

Remove old adhesive from mount ring and insulating strip with solvent (PWC11-029).

(2)

Clean surfaces using solvent (PWC11-014) or (PWC11-032).

(3)

Bond insulating strip to mount ring halves using adhesive sealant (PWC08-010) (Ref. Fig. 202).

(4)

Allow sealant to cure at room temperature for approximately 72 hours.

(5)

Trim insulating strip to dimensions shown. NOTE:

(6)

Seventy two hours is the normal curing time of bond. Ring half may be returned to service after two to four hours, but avoid exerting pressure that would cause sealant to exude and weaken bond.

Repairs to compressor wash rings are confined to replacement of loose or missing countersunk head rivets at plate nuts on spray tube mounting brackets. Plate nut must be located to maintain float of 0.020 inch radius from center of bolt hole.

72-30-02 REAR MOUNT RING - MAINTENANCE PRACTICES

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METALLIC SURFACE THIS SIDE

VIEW

A

A

C391 Fireseal/Insulating Strip Repair Figure 202

72-30-02 REAR MOUNT RING - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

GAS GENERATOR CASE - DESCRIPTION AND OPERATION 1.

General The gas generator case comprises the components necessary for the compression of the incoming air, and the mixing and combustion of fuel and air. It also provides the main attachment points for mounting the engine in the airframe.

2.

Description and Operation (Ref. Fig. 1) The gas generator case is located between the compressor inlet case at the rear and the exhaust duct at the front. The case consists of two stainless steel sections fabricated into a single structure, and may be coated with a diffused aluminide process treatment for increased resistance to corrosion attack. The rear inner section provides a housing for the compressor rotor and stator assembly. Bleed ports for the low and high compressor bleed valves are located at the 9 and 3 o’clock positions on the conical outer section of the case. The No. 2 bearing, with compressor and compressor turbine stator air seals, is located in the case centerbore. The compressor double labyrinth stator air seal is secured in the centerbore by a double coil retaining ring, while the compressor turbine stator air seal is secured to the front flange at the centerbore by eight bolts. Diffuser tubes, brazed inside the center section of the case, increase the static pressure of the compressor discharge air and direct it through straightening vanes to the combustion area. Compressor discharge air (P3) is piped from a diffuser tube at approximately the 4 o’clock position to a boss on the case to provide controlling pressure for the fuel control system. A boss and bleed air adapter secured at the 9 o’clock position on the case provides P3 air for airframe services; the boss is connected via a direct passage to supply P3 air from behind the diffuser tube. The adapter may be of plain or venturi-type depending on airframe requirements. P3 air for the compressor bleed valves is obtained from a tee fitting which projects from the diffuser pipe at the 12 o’clock position. The fitting connects two separated tubes on the compressor side of the gas generator case to their respective bleed valve. Pressure oil to lubricate the No. 2 bearing is applied to the bearing area from a inlet port at the 5 o’clock position on the gas generator case, an internal pressure tube and a cored passage in the centerbore of the case. A dual nozzle assembly at the 2 o’clock position on the cored passage applies oil to the front and rear faces of the bearing. Scavenge oil from the bearing area is returned to the accessory gearbox through an internal tube installed at the 6 o’clock position in the bearing area to a boss at the 5 o’clock position on the gas generator case. An external transfer tube connects the boss to a similar boss on the accessory gearbox. The front section of the gas generator case forms the outer housing for the combustion chamber liner. The case is circular in section, with mounting bosses for the 14 fuel manifold adapters, the front and rear drain valves and the two spark igniters. The drain valves are located at the 6 o’clock position while the spark igniter bosses are at the 4 and 9 o’clock positions. The spark igniters and the fuel nozzles and sheaths of the manifold adapters pass through the case and outer liner of the combustion chamber to protrude into the combustion area. The fuel nozzle sheaths are utilized to support the front of the combustion chamber outer liner. Four pads are provided on the gas generator case at the 2, 4, 8, and 10 o’clock positions for engine mounting in the airframe.

72-30-04 GAS GENERATOR CASE - DESCRIPTION AND OPERATION

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

FLANGE

FUEL MANIFOLD ADAPTER

C

GAS GENERATOR LARGE CASE EXIT DUCT

HIGH PRESSURE COMPRESSOR BLEED VALVE

EXHAUST HOUSING

COMPRESSOR INLET SCREEN (REF)

COMPRESSOR INLET CASE (REF) NO. 2 BEARING

COMPRESSOR SECTION COMPRESSOR TURBINE NO. 1 BEARING ROTOR AIR SEAL

FWD

NO. 1 BEARING

NO. 1 BEARING STATOR AIR SEAL

NO. 1 BEARING OIL NOZZLE (REF)

1ST AND 2ND STAGE (POWER) TURBINES (REF)

COMPRESSOR REAR DISK AND HUB EXHAUST DUCT (REF)

SMALL EXIT DUCT AND COMPRESSOR TURBINE INLET GUIDE VANE

FRONT FUEL DRAIN VALVE FUEL INLET MANIFOLD ADAPTER, FUEL FLOW DIVIDER AND DUMP VALVE ASSEMBLY

COMBUSTION CHAMBER LINER

NO. 1 BEARING SCAVENGE OIL (REF) EXHAUST HOUSING ASSEMBLY REAR FUEL DRAIN VALVE

C49B Gas Generator Case Installation - Cross-section Figure 1

72-30-04 GAS GENERATOR CASE - DESCRIPTION AND OPERATION

Page 3/4 Sep 24/99

LOW PRESSURE COMPRESSOR BLEED VALVE

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

GAS GENERATOR CASE - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire 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 PWC05-003 PWC05-014 PWC05-118 PWC09-002 PWC11-014 PWC15-013

Oil, Engine Lubricating Cloth, Abrasive Cloth, Abrasive, Scotch Brite Insert, Threaded Sealant, Adhesive Alcohol, Isopropyl Inhibitor, Rust

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

4.

Tool No.

Name

Application

PWC30271-100 PWC31771 PWC32483 PWC34184

Spreader, Shanknuts Spreader Cutter, Diffuser Pipe Gage

Replaced by PWC31771

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

Remarks

Locking Tool (Keensert)

TD1032L

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5.

Removal/Installation A.

B.

6.

Removal of Gas Generator Assembly (Heavy Maintenance) (1)

Remove engine from airframe and install in stand (Ref. 72-00-00, REMOVAL/INSTALLATION).

(2)

Remove power section/power section module (PS/PSM) from gas generator assembly and install in stand (Ref. 72-00-00, SERVICING).

(3)

Remove CT disk and blade assembly (Ref. 72-50-02, Removal/Installation).

(4)

Remove combustion chamber inner liner (Ref. 72-40-01, Removal/Installation).

(5)

Remove CT stator assembly, stator housing assembly and exit ducts (Ref. 72-50-01, Removal/Installation).

Installation of Gas Generator Assembly (1)

Install exit ducts, stator housing assembly and CT stator assembly (Ref. 72-50-01, Removal/Installation).

(2)

Install combustion chamber inner liner (Ref. 72-40-01, Removal/Installation).

(3)

Install CT disk and blade assembly (Ref. 72-50-02, Removal/Installation).

(4)

Remove PS/PSM from stand, and install on gas generator assembly (Ref. 72-00-00, SERVICING).

(5)

Install engine in airframe (Ref. 72-00-00, REMOVAL/INSTALLATION).

Cleaning/Painting A.

Cleaning of Gas Generator Case (1)

Wash salt and smog deposits from gas generator case with clean water. Dry with clean, dry compressed air.

(2)

Clean corrosion buildup with non-metallic brush. NOTE:

(3)

On engines with the diffused aluminide conversion-coated gas generator cases, corrosion products (sacrificial) may become visually apparent. Coloring will be reddish brown to rust, which may give the impression that premature attack has occurred on the base material. Light brushing with a soft bristle brush will show that apparent ‘‘rust’’ is superficial. Conversion coating color may vary from green to gray and surface finish should be glaze-like in appearance. Diffused intermetallic coating should be matte gray to brown. Damaged coating should be touch-up repaired (Ref. Para. 8.).

Make sure area around diffuser block cooling air holes at No. 2 bearing housing is thoroughly cleaned and cooling holes are clear (Ref. Para. 7.).

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7.

Inspection/Check A.

Inspection of Gas Generator Case (1)

External: (a) Examine for general condition, including cracks, distortion, corrosion and evidence of overheating. (b) Examine protective coating for loss or deterioration. Repair as necessary (Ref. Para. 8.). (c) Minor corrosion on exposed surface of gas generator case may be removed (Ref. Para. 8.). NOTE:

1

If condition of gas generator case indicates further inspection is required, remove fuel manifold adapters (Ref. 73-10-05, Removal/Installation) and spark igniters (Ref. 74-20-00, Removal/ Installation).

Machined surfaces (bosses and pads) with corrosion pitting less than 0.010 inch deep and less than 75 percent of the surface is acceptable without repair.

(d) On engines INSTALLED in airframe, inspect engine mounts for attachment and condition (Ref. Aircraft Maintenance Manual). (e) On engines NOT INSTALLED in airframe, inspect condition of mounting pads and threaded holes. Damage to threaded holes may be repaired (Ref. Para. 8.). (f)

Examine center mount ring mounting brackets for damage to the following limits : 1

Cracks in legs must be stop drilled using a 0.0625 (1⁄16) inch drill bit.

2

Crack through one leg is acceptable. Remove sharp edges.

3

Cracks through both legs is acceptable on two brackets provided brackets are 180° apart. Remove sharp edges. NOTE:

4 (2)

Cracks may be an indication of vibration, or misalignment. Check for sources of vibration ( propeller, starter, etc.) and fit of airframe firewall(s) and cowling(s).

Replace damaged brackets at next overhaul.

Internal (Heavy Maintenance Only): (a) Make sure diffuser block cooling air holes at No. 2 bearing housing are clear. Insert No. 40 (0.098 in.) drill in each hole and rotate by hand.

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7

11

6

10

PRE−SB3093 3

2 1

12 POST−SB3093

5 9

8

7

4

6

C3895B Repair of Gas Generator Case Figure 201 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12.

Gas Generator Case Shanknut Shanknut Rear Mounting Flange Front Mounting Flange Gasket No. 2 Bearing Stator Air Seal No. 2 Bearing Cover Flange No. 2 Bearing Cover Large Exit Duct Vane Ring Baffle

(b) Examine shanknuts on flanges in area of No. 2 bearing. Loose or damaged nuts may be replaced (Ref. Para. 8.). (c) Examine straightening vanes for cracks and missing material. A maximum of seven vanes with one side broken off is acceptable provided no more than two are adjacent and sharp edges are removed to prevent detachment of material. (d) Examine diffuser exit ducts (Ref. Fig. 202): 1

Cracks of any length on inner surface of any number of ducts are acceptable provided cracks will not converge and allow metal to become detached (Ref. Details A, B and C). Cracks must be stop drilled (Ref. Para. 8.).

2

Cracks ending in weld are acceptable and require no repair.

3

Loss of material is acceptable on a maximum of four ducts, provided detached material is removed from engine and hole size is within the limits shown (Ref. Details A and B). Remove sharp edges (Ref. Para. 8.).

4

Cracks in duct outer face are acceptable. Cracks must be stop drilled (Ref. Para. 8.).

5

Fretting wear on outer face and edge adjacent to next duct is acceptable provided such wear is repaired (Ref. Para. 8.).

6

Cracks in fretted areas are acceptable provided such cracks are stop drilled (Ref. Para. 8.).

7

Examine for 0.020 inch minimum clearance at the following locations: a

Between adjacent ducts.

b

Between ducts and adjacent straightening vanes.

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c

Between ducts and inner wall of gas generator case.

8

If any of the above limits are exceeded the duct(s) must be replaced (Ref. Para. 8.).

9

Reject engine if two adjacent ducts are missing, or if more than two non-adjacent ducts are missing.

10

An engine with two non-adjacent ducts missing may remain in service until removal for repair or overhaul provided all other ducts are within allowable limits, allowable repairs have been done, and engine performance is acceptable and surge free. Remove debris, and sharp edges. NOTE:

11 8.

Operating with missing diffuser exits ducts may lead to accelerated hot section deterioration. If engine is kept in service, do a borescope inspection of hot section and combustion chamber 250 hours after discovery of loss and subsequently at a 400 hour interval.

Cracking of ducts may be associated with vibration. The source of vibration should be identified, and corrective action taken to reduce it.

Approved Repairs A.

Corrosion Removal (1)

Remove all visible corrosion with coarse abrasive cloth (PWC05-003) exposing bare metal. Use pad (PWC05-014) or a soft bristle brush to provide a clean surface. NOTE:

B.

Do not use power tools for corrosion removal.

(2)

Restore protective coating (Ref. Para. B.).

(3)

Mask all areas that are to remain free of corrosion inhibitor (PWC15-013).

(4)

Apply inhibitor in accordance with manufacturer’s instructions.

Repair of Protective Coating (conversion-coat only) (1)

Restore localized areas of conversion coating loss as follows:

(2)

Clean the affected area by lightly brushing with ‘‘Scotch Brite’’ (PWC05-014) cloth or a soft stainless steel bristle brush to provide a clean surface. NOTE:

Casing should be cool to touch.

(3)

Apply two or three brush, spray or damp-sponge coats of the conversion coating touch-up per SPOP 144. Excess coating must be wiped off carefully.

(4)

Allow the conversion coating touch-up to air dry for 10 minutes after applying each coat.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

DAMAGE ON INNER SURFACE

DAMAGE ON OUTER SURFACE

0.300 MAX. PERMISSIBLE

0.500 MAX. PERMISSIBLE

0.800 MAX. PERMISSIBLE

A

B

DAMAGE ON INNER SURFACE

DAMAGE ON OUTER SURFACE

FRETTED AREA

C

D

C347D Inspection of Diffuser Exit Ducts Figure 202 P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

C.

Repair of Igniter Boss Threads (1)

D.

Dress damaged threads using a 0.5625-18 UNF tap.

Repair of Bleed Valve Mount Pad and/or Fuel Nozzle Pad Rear Threaded Holes (1)

Mask gas generator openings to prevent ingress of swarf.

(2)

Open up damaged hole(s) with a 9⁄32 (0.281) inch drill bit . Chamfer 0.323 to 0.333 inch x 90 ± 5 degrees included angle.

(3)

Tap hole using 0.3125-18 UNC-2B tap.

(4)

Install threaded insert (PWC05-118) fingertight: (a) Fuel nozzle inserts 0.010 to 0.015 inch above surface with keys aligned. (b) Bleed valve inserts 0.010 to 0.015 inch below surface . (c) Drive keys down with locking tool and hammer.

(5) E.

F.

Remove all masking material.

Replacement of Bleed Valve Mount and/or Fuel Nozzle Pad Damaged Threaded Inserts (1)

Remove insert material between keys and thread to 5⁄32 ( 0.157) inch deep maximum with a 7⁄32 (0.219) inch drill.

(2)

Deflect keys inward, break off using suitable pin punch.

(3)

Remove insert with suitable extraction tool.

(4)

Install new insert (Ref. Para. D.).

Repair of Fuel Nozzle Pad Front Threaded Hole NOTE:

This is a temporary (field level) repair. Holes repaired using these instructions will require removal of the threaded insert at overhaul.

(1)

Remove power section (Ref. 72-00-00, REMOVAL/INSTALLATION).

(2)

Remove fuel manifold adapter(s) (Ref. 73-10-05, Removal/Installation).

(3)

Remove combustion chamber liner (Ref. 72-40-01, Removal/Installation).

(4)

Mask gas generator openings to prevent ingress of debris.

(5)

Open up damaged front hole with a 0.203 (13/64) inch drill bit.

(6)

Chamfer hole 0.220 - 0.250 inch diameter X 120 degrees ± 5 degrees.

(7)

Tap hole and install helical insert (MS124655 or equivalent). NOTE:

The insert must be installed 3⁄4 to one thread pitch below surface.

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(8)

Break and remove driving tangs.

(9)

Remove all masking material.

(10)

Clean inside gas generator case with suitable suction cleaner.

(11)

Install combustion chamber liner (Ref. 72-40-01, Removal/Installation).

(12)

Install fuel manifold adapter(s) (Ref. 73-10-05, Removal/Installation).

(13)

Install power section (Ref. 72-00-00, REMOVAL/INSTALLATION).

G. Replacement of Shanknut (Heavy Maintenance Only) (1)

Using a suitable drill, partially remove the flared end of shanknut (2 or 3, as applicable), (Ref. Fig. 203). NOTE:

H.

Do not drill through to contact flange.

(2)

Remove shanknut using a parallel pin punch at drilled end to shear weakened flare, and retrieve from case.

(3)

Install new shanknut and hold against flange (Ref. Fig. 203).

(4)

Apply oil (PWC03-001) to tapered portion of spreader (PWC30271-100) or (PWC31771) 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.

Repair of Diffuser Exit Ducts (Heavy Maintenance Only) (Ref. Fig. 204) (1)

Stop drill cracks with a 1⁄16 (0.0625) inch drill (Ref. Details A, B and D).

(2)

Smooth out areas where material has become detached (Ref. Details A and B).

(3)

Cracks on edges of duct, which may join and cause sections to become detached, must be smoothed (Ref. Detail C).

(4)

Cracks in outer wall of ducts may be reached by drilling access holes in inner walls with a 1⁄4 (0.250) inch drill, then stop drill crack in outer wall with a 1⁄16 (0.0625) inch drill. Access holes are acceptable without repair (Ref. Detail D).

(5)

Fretting wear at exit of duct should be carefully smoothed.

(6)

Cracks in fretted areas should be stop drilled with a 1⁄16 (0.0625) inch drill.

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SHANKNUT AFTER INSTALLATION

SPREADER

SHANKNUT BEFORE INSTALLATION

TYPICAL CROSS−SECTION AREA AND APPLICATION

C1997A Shanknut Replacement Figure 203 P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

STOP−DRILL AND SMOOTH OUT HOLE

STOP−DRILL AND SMOOTH OUT HOLE

A

B STOP−DRILL THROUGH WINDOW ON INNER WALL

STOP−DRILL, REMOVE METAL AND BLEND OUT HOLE 0.800 MAX. 0.400 MAX. 0.500 MAX.

0.250 MAX.

0.800 MAX.

C

D

C348C Diffuser Exit Duct Repair Figure 204 P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

I.

Replacement of Diffuser Exit Ducts (Heavy Maintenance Only)

CAUTION: PRIOR TO HEAT TREATMENT EXCEEDING 344°C (650°F) REMOVE AND DISCARD ALL BOLTS ON DIFFUSER EXIT DUCTS. RETAIN CLAMPS AND DUCTS FOR REUSE. CAUTION: MASK ALL OPENINGS IN VICINITY OF DUCTS TO PREVENT INGRESS OF METAL PARTICLES INTO ENGINE. (1)

Place suitable protective shim, brass of steel, between gas generator case and duct, and carefully remove damaged duct with suitable tool.

(2)

Machine remaining duct stub (4, Fig. 205) to dimensions shown with cutter (PWC32483), and gage (PWC34184). Break sharp edges (Ref. Detail C).

(3)

Open clamp (5) to permit insertion of ferrule end of duct assembly (3). Coat OD of stub (4) with adhesive (PWC09-002), and with clamp open, install over stub (4).

(4)

Butt ferrule and stub together, and progressively tighten clamp bolt (2), 60 to 65 lb.in., and lockwire. NOTE:

(5)

Some minor deformation of bolt after tightening is acceptable. However, if bolt is removed for any reason, it must be discarded.

Clean area with suitable suction device. Remove all masking, and clean tape residue with solvent (PWC11-014).

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THIS PAGE INTENTIONALLY LEFT BLANK

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1

5

2

BREAK EDGE 0.000−0.003

DETAIL

C

0.587 DIA. (REF.)

0.012 MIN.

4

3

ENLARGED SECTION OF CLAMPED JOINT (SHOWN IN NORMAL POSITION) VIEW

0.530 0.480 (PART OFF)

0.420 0.400 (FACE)

DETAIL

A

A−A

C

A 0.020 MIN. BOTH ENDS

THIS DIM. BOTH ENDS MUST BE EQUAL WITHIN 0.040 BUT MUST NOT EXCEED 0.080

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Key to Figure 205 1. 2. 3. 4. 5.

Washer Bolt Diffuser Exit Duct (Replacement) Stub (After machining) Clamp

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COMPRESSOR ROTOR - DESCRIPTION AND OPERATION 1.

General The compressor rotor is housed in the gas generator case and is driven by the compressor turbine. It compresses incoming air for delivery to the combustion chamber.

2.

Description and Operation (Ref. Fig. 1) The compressor rotor balancing assembly is located in the rear section of the gas generator case. The rotor assembly consists of three axial stages, three interstage spacers and a single-stage centrifugal impeller. First-stage rotor blades are of titanium, while second-and third-stage rotor blades are cadmium-plated stainless steel. The rotor blades fit into dovetail grooves machined in the rims of respective disks. The limited clearance between the blade roots and grooves produces the characteristic clicking heard during compressor run-down. Axial movement of the blades is limited by interstage spacers installed between the rotor disks. The airfoil section of the first-stage blades differs from that of the second-and third-stage blades. The OD of the first-, second-, and third-stage disk and blade assemblies remains nearly constant while the disk diameters increase progressively from first to third stage. The first-stage rotor has 18 blades (PT6A-38/-41) or 16 blades (PT6A-40/-42/-42A) while the second- and third-stage rotors each have 36 blades. The centrifugal impeller is bolted to the three axial stages and associated spacers by six numbered tie rods to form an integral unit. The first-stage compressor stator assembly has 53 vanes in early engines and 39 in all later models, the second stage has 43 vanes and the third stage has 39 vanes. The vanes in each stage are of stainless steel. Each set of vanes is held in position by its respective compressor stator assembly through which the outer ends of the vanes protrude and to which the vane ends are brazed. The third-stage stator assembly also provides a housing for the centrifugal impeller. The first- and third-stage stator assemblies are bolted together, while the second-stage stator assembly is retained between flanges in the centerbores of the firstand third-stage stator assemblies. Rotation is prevented by slots and lugs in the mating flanges. Interstage pressure (P2.5) is vented to the compressor bleed valve chamber in the gas generator case through slots in the third-stage stator assembly. The compressor stubshaft, centrifugal impeller and third-stage compressor stator assembly are positioned, in that order from front to rear, followed by the third-stage disk spacer and rotor assembly, the second-stage stator assembly, second-stage disk spacer and rotor assembly, the first-stage stator assembly, first-stage disk spacer and compressor rear hub (first-stage disk and blade assembly). The third-stage stator and impeller housing assembly is secured to the gas generator case by 12 bolts while the first-stage stator assembly is retained within a flange on the front face of the compressor inlet case. Sealing is accomplished by a preformed packing at the interface. The compressor front stubshaft is a hollow steel forging, machined to accommodate the compressor air seal rotor and the number 2 bearing assembly. The number 2 bearing is a roller-type and supports the stubshaft and forward end of the compressor rotor assembly in the gas generator case. The compressor turbine rotor air seal is fitted on the stubshaft forward of the number 2 bearing.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

The compressor rear hub is an integral part of the first-stage compressor rotor disk. The hub consists of a hollow forging machined to accommodate the number 1 bearing rotor air seal, the oil slinger and the number 1 bearing. The number 1 bearing is a ball-type and supports the compressor rear hub and the rear end of the compressor assembly in the compressor inlet case. A short, hollow, steel coupling, externally splined at the rear end, is secured in the hollow end of the rear hub by a transverse pin which passes through the hub and coupling. A hollow steel coupling shaft, internally splined at its forward end and incorporating a pinion at its rear end, extends the compressor drive rearward to drive the accessory gearbox. The front end is secured by a ball-lock arrangement while the rear end is supported by a single roller-type bearing which is secured to the gearbox housing. The number 1 and 2 bearings support the compressor assembly in the rear section of the gas generator case. The number 1 bearing outer race is held in a flexible housing assembly by an externally threaded ring which is locked by a single rivet. The flexible housing assembly consists of an inner housing and an outer housing, the latter being bolted to the compressor inlet case. The split inner race of the number 1 bearing, an oil slinger and rotor air seal are stacked against a shoulder on the rear hub and secured by a keywasher and spanner nut. A puller groove embodied in the OD of the rear half of the inner race facilitates removal. The flange of the number 2 bearing outer race is secured to the center bore of the gas generator case by four bolts and tablock washers. The inner race of the number 2 bearing is interposed between compressor rotor air seal and the compressor turbine rotor air seal with the compressor rotor air seal bearing against a shoulder on the stubshaft. The bearing and rotor air seals are retained by the compressor turbine disk.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

NO. 2 BEARING PRESSURE OIL TUBE AND NOZZLE

2ND STAGE COMPRESSOR STATOR ASSEMBLY DIFFUSER TUBES

TIE RODS

2ND STAGE COMPRESSOR BLADES

COMPRESSOR INLET CASE (REF.)

NO. 2 BEARING COMPRESSOR FRONT STUB SHAFT

FLEXIBLE HOUSING NO. 1 BEARING

FWD ACCESSORY GEARBOX INPUT COUPLING SHAFT COMPRESSOR TURBINE (REF.)

COMPRESSOR REAR AIR SEAL

1ST STAGE COMPRESSOR COMPRESSOR 3RD STAGE COMPRESSOR BLADES COMPRESSOR REAR HUB FRONT AIR SEAL BLADES NO. 2 BEARING 3RD STAGE SCAVENGE TUBE 1ST STAGE COMPRESSOR CENTRIFUGAL COMPRESSOR STATOR AND IMPELLER IMPELLER HOUSING STATOR ASSEMBLY ASSEMBLY

C50B Compressor Rotor Cross-section Figure 1

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR ROTOR - MAINTENANCE PRACTICES 1.

General A.

2.

Maintenance of the compressor rotor is restricted to inspection and repair of the first-stage rotor.

Consumable Materials Not Applicable

3.

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Inspection/Check - (First-stage Compressor Rotor) A.

General

CAUTION: KEEP COMPRESSOR INLET AREA CLEAR OF ALL FOREIGN OBJECTS THAT COULD BE INGESTED BY ENGINE AND CAUSE SERIOUS DAMAGE DURING SUBSEQUENT OPERATION. NOTE:

(1)

The following inspection should be done whenever the air inlet screen is removed (Ref. 72-20-00). Due to limited access, the use of a mirror is recommended.

The limits stated under ’Acceptable Damage Limits’ and ’Acceptable Erosion Limits’ are considered acceptable without repair. The actual damage must be documented and additional inspections scheduled to assess the rate of defect progression. NOTE:

(2)

Continued operation of a compressor with FOD, either accepted as-is or blended is dependent on satisfactory engine performance (Ref. Table 201). NOTE:

(3)

If acceptable limits are exceeded, the blades may still be repaired (Ref. Approved Repairs).

When assessing damage, it should be understood that continued operation with a large number of blades damaged or eroded at or near maximum acceptable limits may result in reduction of compressor efficiency and engine performance.

Acceptable damage limits are based primarily on structural integrity considerations. Rotors with damage exceeding ’Acceptable Damage Limits’ cannot remain in service unless damage can be removed by blending (Ref. Approved Repairs):

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TABLE 201, Example of FOD (Ref. Fig. 202, Sheet 1) Type of Damage A nick, 0.020 inch deep by 0.025 inch wide, in blade root.

NOTE:

B.

C.

Disposition Engines may not continue in operation with damage in blade root. However, if the damage can be removed by performing a leading edge cutback (Ref. Approved Repairs) the engine can return to service provided performance is satisfactory.

Remove the minimum material required to remove the damage. Document the damage (Ref. Subpara. B.).

(4)

If damaged blade is within acceptable limits and is not reworked, inspect area at 100 hours. Subsequent inspections are at the discretion of the operator but must not exceed 400 hours.

(5)

If damage to the blades is acceptable, and/or after blending, engine performance is within acceptable limits, inspection of the subsequent stages, (rotors, stators and impeller) is not required. Under these conditions, the engine is considered acceptable for service.

(6)

If damage exceeds limits and cannot be removed by blending or engine performance is unsatisfactory after repair, the engine or gas generator must be removed from service.

Documenting Damage (1)

Defects/damage should be documented (i.e., engine module TSN/TSO, cycles, component description, location and dimensions, if obtainable).

(2)

If the blade is repaired document the amount of material removed, (i.e. if the blade was cut back, the amount of cutback should be documented).

Acceptable Damage Limits (Ref. Fig. 201)

CAUTION: NICKS IN LEADING AND TRAILING EDGES BECOME INCREASINGLY CRITICAL TOWARD ROOT. DAMAGE IS NOT PERMITTED WITHIN 0.050 INCH OF BLADE ROOT FILLET RADIUS. THE ENGINE MAY REMAIN IN SERVICE PROVIDED THE DAMAGE IS COMPLETELY REMOVED BY LEADING EDGE CUTBACK. NOTE: (1)

For multiple leading edge defects closer than 0.200 inch, the entire leading edge may be blended.

Leading or trailing edge nicks 0.100 inch deep maximum. Two per blade on any number of blades. NOTE:

(2)

A nick is considered to be a sharp surface indentation caused by impact resulting in loss of parent material.

Leading or trailing edge dents 0.100 inch deep by 0.100 inch long. Two per blade on any number of blades.

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LEADING EDGE

ORIGINAL CONTOUR

C22548A Compressor First-stage Blades Inspection Figure 201

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(3)

Leading or trailing edge tip curl, without tearing, maximum is 0.100 inch deformation on one edge, up to four blades.

(4)

Leading edge nicks 0.030 to 0.050 inch deep by 0.080 inch wide, more than 0.200 inch apart, and more than 0.250 inch from blade tip, on any number of blades, are acceptable provided there are no tears and/or cracks.

(5)

Trailing edge dents and nicks, maximum of four (4) per blade, 0.030 to 0.050 inch deep by 0.080 inch wide, more than 0.200 inch apart, and more than 0.250 inch from blade tip, on any number of blades, are acceptable provided there are no tears or cracks.

(6)

Blade tip rub is acceptable providing there is no rolled over material and an engine performance/ground power check is acceptable.

(7)

Area a and c; (a) Corrosion pitting, nicks and dents 0.005 in. deep are acceptable.

(8)

Area b; (a) Corrosion pitting, nicks and dents 0.010 in. deep are acceptable.

(9)

Area d; (a) Corrosion pitting 0.002 in. deep is acceptable.

D.

Acceptable Erosion Limits (Ref. Fig. 203) (1)

Erosion at the root is acceptable providing the chord is not reduced by more than 0.250 in. and there is no feathered (i.e. sharp) edge(s). NOTE:

(2)

E.

The chord of an airfoil section is the shortest distance between the leading and trailing edges.

Feathered edges must be removed (Ref. Para. 6.) or the engine or gas generator module removed from service. The original airfoil chord of the repaired section must not be reduced by more than 0.250 in. and the original leading edge profile must be restored.

Unacceptable Damage (Ref. Fig. 202) (1)

Tears and cracks due to deformation of leading or trailing edges and cracks on any blade surface are not acceptable. The blade must be repaired if the defect is within repairable limits (Ref. Approved Repairs), or the engine or gas generator module removed from service.

(2)

Tip curl more than 0.100 in. is unacceptable. Rework corner 0.250 in. maximum along tip and 0.400 in. maximum down leading edge (Ref. Approved Repairs).

(3)

Sharp corners must be smoothed to 0.100 in. radius minimum, and 0.050 in. deep and maximum width. Tip corner radius must not exceed 0.100 in. Maintain trailing edge profile.

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0.050 in. MAXIMUM BLEND LIMIT

0.020 in.

LEADING EDGE

LEADING EDGE

0.025 in.

LEADING EDGE

0.020 in. DETAIL

A

DETAIL

A

DETAIL A REMOVE MINIMUM MATERIAL TO REMOVE DAMAGE

MATERIAL AVAILABLE FOR FUTURE REPAIR IF REQUIRED. MAXIMUM MATERIAL REMOVAL ALLOWED

C60975 Example of Damage Removal Figure 202 (Sheet 1 of 3)

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0.080

0.280

0.080

0.120

0.120 0.375

LEADING EDGE

LEADING EDGE

DETAIL D TYPICAL BLADE TIP OVAL (LE OR TE)

LEADING EDGE

DETAIL D MAXIMUM BLEND LIMITS (LE OR TE)

DETAIL D REMOVE MINIMUM MATERIAL TO REMOVE DAMAGE

MATERIAL AVAILABLE FOR FUTURE REPAIR IF REQUIRED. MAXIMUM MATERIAL REMOVAL ALLOWED

C60976 Example of Damage Removal Figure 202 (Sheet 2)

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0.165

0.020

0.220 MIN

0.220 MIN

0.300

0.075

LEADING EDGE

LEADING EDGE

DETAIL C LE DAMAGE

0.020

DETAIL C MAXIMUM LE BLEND LIMITS

0.220 MIN

0.075

LEADING EDGE

DETAIL C REMOVE MINIMUM MATERIAL TO REMOVE DAMAGE MATERIAL AVAILABLE FOR FUTURE REPAIR IF REQUIRED. MAXIMUM MATERIAL REMOVAL ALLOWED

C60977 Example of Damage Removal Figure 202 (Sheet 3)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

6.

Approved Repairs A.

Repair of Leading Edge (Ref. Fig. 203) CAUTION: KEEP COMPRESSOR INLET AREA CLEAR OF ALL FOREIGN MATERIAL AND OBJECTS WHICH COULD BE INGESTED BY ENGINE AND CAUSE DAMAGE DURING OPERATION. (1)

Repair the first-stage blade leading edge within the following limits with fine hand files and stones.

(2)

Suitably mask entire first-stage compressor area to prevent contamination of compressor.

WARNING: AN ACCUMULATION OF TITANIUM DUST IS A FIRE HAZARD. CLEAN UP TITANIUM DUST ON COMPLETION OF REPAIR AND DO NOT ALLOW DUST TO ACCUMULATE ON CLOTHING. (3)

In case of multiple leading edge defects situated closer than 0.200 in., the entire leading edge of an unlimited number of blades may be cut back 0.025 in. maximum (Ref. Detail A). Maintain leading edge profile and fillet radius as close as possible to original. NOTE: 1. If cutting back the leading edge by 0.025 in. does noteliminate or make defects acceptable, the blade cutbacks may be extended to 0.050 in. maximum, providing engine performance is within limits. This is acceptable to permit the engine to remain in service; however, the affected components may have to be replaced at the next overhaul. NOTE: 2. If any blade is cut back to the maximum limits, the blade 180 degrees opposite must be cut back by the same amount to prevent compressor rotor imbalance.

(4)

Nicks and tears may be smoothed to 0.150 in. wide maximum by 0.100 in. deep maximum, provided the end of repaired area is 0.125 in. minimum from blade tip (Ref. Detail C). NOTE: 1. If repairing the airfoil within the above limits does noteliminate the defects or make them acceptable, individual defects may be smoothed to 0.300 in. wide maximum and 0.165 in. deep maximum, providing repair area is 0.220 in. minimum from blade tip and engine performance is within limits. However, the affected components may have to be replaced at next overhaul. NOTE: 2. If any blade is smoothed to the maximum limit, the blade 180 degrees opposite must be smoothed to the same shape to prevent compressor rotor imbalance.

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(5)

Bent or torn leading edge blade tips may be smoothed to maximum 0.175 in. deep by maximum 0.200 in. wide (Ref. Detail D). NOTE: 1. If repairing the airfoil within the above limits does noteliminate the defects or make them acceptable, individual defects may be smoothed to 0.375 in. wide maximum and 0.280 in. deep maximum, providing engine performance is within limits. However, the affected components may have to be replaced at next overhaul. NOTE: 2. If any blade is smoothed to the maximum limits, the blade 180 degrees opposite must be smoothed to the same shape to prevent compressor rotor imbalance.

B.

(6)

If any blade is smoothed to the maximum limits, the blade 180 degrees opposite must be smoothed to the same shape to prevent compressor rotor imbalance.

(7)

Remove sharp edge at leading edge root eroded area. Restore as near as possible the original radius and smoothness (Detail E). After the repair, make sure the original airfoil chort at the repair area was not reduced by more than 0.250 in.

(8)

Clean inlet area with a suitable suction cleaner. Remove all masking material and repeat cleaning. Make sure all residue is removed from inlet area and first-stage blades.

Repair of Trailing Edge (1)

Dents and nicks up to 0.050 in. deep and wide, not less than 0.200 in. apart and not within 0.250 in. of blade tip, are acceptable (maximum 4 per blade), providing there are no tears or cracks.

(2)

Sharp corners must be smoothed to an approximate radius of 0.050 in. and a maximum of 0.050 in. deep and wide. Tip corner radius must not exceed 0.100 in.

CAUTION: KEEP COMPRESSOR INLET AREA CLEAR OF ALL FOREIGN OBJECTS WHICHCOULD BE INGESTED BY ENGINE AND CAUSE DAMAGE DURING ENGINE OPERATION. (3)

Use a suitable suction cleaner to thoroughly clean entire compressor inlet area. Remove all masking material and repeat cleaning. Make sure all filing residue is removed from inlet area and first-stage compressor blades.

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0.100 DEEP MAX

0.025 MAX CUT BACK AREA 0.125 MIN 0.150 MAX MAINTAIN LEADING EDGE RADIUS AVOID SHARP EDGES OR FLAT AREAS

B

ENLARGED VIEW

C

DETAIL

B 0.175 DEEP MAX

0.025 MAX

0.200 MAX

DETAIL

A

DETAIL

D

C22550D First-stage Compressor Repair Limits Figure 203 (Sheet 1 of 2)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

ORIGINAL CHORD LENGTH 0.250 IN. MAX. BLENDING

MAINTAIN LEADING EDGE RADIUS, AVOID SHARP EDGES OR FLAT AREAS ENLARGED SECTION

F−F

NOTE: THE MAXIMUM PERMITTED MATERIAL REMOVAL IS SHOWN. ONLY REMOVE THE MINIMUM MATERIAL NECESSARY TO BLEND OUT DAMAGE.

F

F DETAIL

E

C22549C First-stage Compressor Repair Limits Figure 203 (Sheet 2)

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Apr 08/2005 Apr 08/2005

Contents

1 2 blank

Apr 08/2005 Apr 08/2005

72-40-00 Description and Operation

1 2 blank

Sep 24/99 Sep 24/99

72-40-01 Description and Operation

1 2 3 4 blank

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

72-40-01 Maintenance Practices

201 202 203 204 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220 221 222 223 224 224 A 224 B blank

CHAPTER SECTION

PAGE 225 226

DATE Feb 07/2003 Feb 07/2003

Apr 08/2005 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Apr 08/2005 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Apr 08/2005 Feb 07/2003 Feb 07/2003 Feb 07/2003 Feb 07/2003 Apr 08/2005 Apr 08/2005

72-40 LEP

Page 1/2 Apr 08/2005

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

COMBUSTION CHAMBER ASSEMBLY- DESCRIPTION AND OPERATION 1.

General

1

COMBUSTION CHAMBER LINER ASSEMBLY- DESCRIPTION AND OPERATION 1.

72-40-00

Description and Operation

72-40-01 1

COMBUSTION CHAMBER LINER ASSEMBLY - MAINTENANCE PRACTICES

72-40-01

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 Combustion Chamber Liner (Pre-SB3250)

201

B.

Removal of Combustion Chamber Liner (Post-SB3250)

203

C.

Installation of Combustion Chamber Liner (Pre-SB3250)

203

D.

Installation of Combustion Chamber Liner (Post-SB3250)

205

6.

7.

Inspection/Check

205

A.

General

205

B.

Inspection of Combustion Liners

205

Approved Repairs

220

A.

220

Repair of Cracks

72-40 CONTENTS

Page 1/2 Apr 08/2005

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMBUSTION CHAMBER ASSEMBLY- DESCRIPTION AND OPERATION 1.

General The combustion section of the engine is contained in the front part of the gas generator case, and consists of the combustion chamber liner and large exit duct (Pre-SB3250), or inner and outer combustion chamber liners (Post-SB3250) and small exit duct. Compressor delivery air from the diffuser section discharges into the combustion section. The air enters the liner through straight and plunged holes, mixes with the fuel from the manifold, and is ignited. The expanding gases flow to the rear and into the exit duct zone, where the gas flow is turned 180 degrees inward to flow forward through the compressor turbine stator to the compressor turbine.

72-40-00 COMBUSTION CHAMBER ASSEMBLY- DESCRIPTION AND OPERATION

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMBUSTION CHAMBER LINER ASSEMBLY- DESCRIPTION AND OPERATION 1.

Description and Operation (Ref. Fig. 1) The Pre-SB3250 combustion chamber liner is an annular, heat-resistant steel liner, open at the rear end and domed at the front end. The Post-SB3250 combustion chamber assembly is made up of two heat-resistant steel liners bolted together at the front (domed) end to create an annular space open to the rear. The outer liner extends rearward to form the large exit duct, incorporates a bolting flange by which it is fastened to the gas generator case at the compressor stator assembly mounting flange. The inner liner has a sliding joint at the rear to engage the outer diameter of the small exit duct. Igniter sleeves and fuel manifold adapter ports and support collars are located in the front of the outer liner. A series of straight and shielded holes let P3 air to enter the combustion zone of the liner assembly. The shape, size and locations of the holes and shields, as well as the locations of the igniter sleeves, provide the best fuel/air ratios for starting and sustaining combustion, and form efficient primary and secondary zones within the combustion zone. Primary air introduces near the fuel manifold adapter ports, supports combustion. Secondary air provides a layer of cooling air over the inner walls of the liners, which also prevents the flame from touching the liner walls, cools the gases leaving the combustion zone to a temperature the compressor turbine can tolerate, and provides air for combustion. The domed end of the combustion chamber liner assembly is supported inside the front section of the gas generator case by the fuel manifold adapter sheaths and is located by the spark igniter. The rear of the assembly is supported at the small exit duct and compressor turbine stator assembly interface. On the PT6A-40 and some PT6A-41/42 engines, the combustion chamber liner is modified to include a machined ring on the inner wrapper, with altered sealing arrangements at the small exit duct interface. Together with a different outer wrapper and corrugated ring, the liner durability is improved. To ensure optimum air cooling of the combustion chamber, fourteen additional air holes are incorporated in the liner.

72-40-01 COMBUSTION CHAMBER LINER ASSEMBLY- DESCRIPTION AND OPERATION

Page 1 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COOLING RINGS

LOUVERED COOLING RING COOLING RING

COOLING RINGS

FUEL MANIFOLD SUPPORT COLLAR

C51B

Pre-SB3250 Combustion Chamber Liner Figure 1 (Sheet 1 of 2)

72-40-01 COMBUSTION CHAMBER LINER ASSEMBLY- DESCRIPTION AND OPERATION

Page 2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

LOUVERED COOLING RING

OUTER LINER COOLING RING

INNER LINER

SEALING RING

COOLING RING

SEALING RING

BOLTING FLANGE FUEL MANIFOLD SUPPORT COLLAR

SPARK IGNITER SUPPORT COLLAR

C10219C

Post-SB3250 Combustion Chamber Liner Figure 1 (Sheet 2)

72-40-01 COMBUSTION CHAMBER LINER ASSEMBLY- DESCRIPTION AND OPERATION

Page 3/4 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMBUSTION CHAMBER LINER ASSEMBLY - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire used, unless otherwise specified, shall comply with specification AMS5687, 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

PWC05-151 PWC05-180 PWC11-014

Wire, Filler Wire, Filler Alcohol, Isopropyl

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

4.

Tool No.

Name

PWC34414

Puller

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation A.

Removal of Combustion Chamber Liner (Pre-SB3250) (Ref. Fig. 201) (1)

Remove the power section/power section module (Ref. 72-00-00, SERVICING).

(2)

Remove the fuel manifold adapter assemblies (Ref. 73-10-05).

(3)

Remove the spark igniters (Ref. 74-20-00).

72-40-01 COMBUSTION CHAMBER LINER ASSEMBLY - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

1

2

3

4

C392A

Pre-SB3250 Removal/Installation of Combustion Chamber Liner Figure 201

72-40-01 COMBUSTION CHAMBER LINER ASSEMBLY - MAINTENANCE PRACTICES

Page 202 Feb 07/2003

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 201 1. 2. 3. 4.

Combustion Chamber Liner Gas Generator Assembly Gas Generator Case Igniter Bosses Spark Igniter Bosses

CAUTION: DO NOT ATTEMPT TO PRY THE LINER LOOSE WITH SHARP EDGED OR POINTED TOOLS. (4)

Withdraw the combustion chamber liner (1, Fig. 201) from the gas generator assembly (2). NOTE:

B.

If difficulty is experienced in withdrawing the liner from the gas generator assembly, strike the inside wall of the liner with the palm of your hand to dislodge the liner from the small and large exit duct joints.

Removal of Combustion Chamber Liner (Post-SB3250) (Ref. Fig. 202) (1)

Remove power section/power section module (Ref. 72-00-00, SERVICING).

(2)

Remove bolts (1, Fig. 202).

CAUTION: DO NOT ATTEMPT TO PRY LINER LOOSE WITH SHARP EDGED OR POINTED TOOLS. (3)

Withdraw combustion chamber inner liner (2) from combustion chamber outer liner (3) using puller (PWC34414). NOTE:

(4) C.

If it is difficult separating inner and outer liner, strike inside wall of inner liner with palm of hand to dislodge it from small exit duct joint.

If it is necessary to remove the combustion chamber outer liner (3) from the gas generator case (4) (Ref. 72-50-01, Removal/Installation).

Installation of Combustion Chamber Liner (Pre-SB3250) (Ref. Fig. 201) NOTE:

Refer to IPC and applicable service bulletin for combustion chamber liner configuration.

(1)

Install the combustion chamber liner (1, Fig. 201) in the gas generator case (2), aligning spark igniter bosses (3) in the outer wall of the liner with the corresponding bosses (4) on the gas generator case.

(2)

Install the spark igniters (Ref. 74-20-00).

(3)

Install the fuel manifold adapter assemblies (Ref. 73-10-05).

(4)

Install the power section/ power section module on the gas generator assembly (Ref. 72-00-00).

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4 3

2 1

C10193

Post-SB3250 Removal/Installation of Combustion Chamber Inner Liner Figure 202

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Key to Figure 202 1. 2. 3. 4. D.

6.

Bolt Combustion Chamber Inner Liner Combustion Chamber Outer Liner Gas Generator Case

Installation of Combustion Chamber Liner (Post-SB3250) (Ref. Fig. 202) (1)

Install combustion chamber outer liner (3, Fig. 202) in gas generator case (4), if removed (Ref. 72-50-01).

(2)

Install combustion chamber inner liner (2) in combustion chamber outer liner (3) engage flange of small exit duct with sealing ring on rear of inner liner.

(3)

Align bolting flanges on inner liner (2) with flanges on outer liner (3), and install bolts (1). Tighten bolts 36 to 40 lb.in.

(4)

Install power section/power section module (Ref. 72-00-00).

Inspection/Check A.

General Make sure cooling holes are not blocked as a result of weld repair or plasma overspray. Use suitable drill to check hole size, drill must rotate freely by hand (Ref. Fig. 208 or 210). Examine combustion chamber liners for cracks, buckling and burning. Cracks in the liner surface are usually of a stress relieving nature and are usually not serious as rate of growth decreases as crack lengthens. Thermal stresses, in effect, relieve original stress conditions. It is normal to observe a given type of deterioration repeated from liner to liner in the same engine, or engines of the same model. Typical liner distress consists of buckling and cracking of cooling rings and cracking at inner wall of the exit duct section of the outer liner Post-SB3250.

B.

Inspection of Combustion Liners (1)

Acceptable Conditions, Repair Unnecessary: (a) Localized buckling and/or burning of cooling rings, except louvered type, accompanied by cracking is acceptable provided cracks do not extend into the seam weld (Ref. Fig. 203 or 204, Detail B). (b) Cracks in louvered type cooling ring (Detail A) are acceptable provided that circumferential cracks in the seam weld (Ref. Fig. 205) not exceeding 0.300 inch in length are stop drilled using a 1⁄16 (0.0625) inch drill. (c) Straight line cracks between two adjacent cooling holes.

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A B

DETAIL A LOUVERED TYPE

CRACK MUST NOT EXTEND INTO SEAM WELD DETAIL B NON−LOUVERED TYPE

C41431

Pre-SB3250 Acceptable Buckling and Cracking in Cooling Rings Figure 203

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A

B

LOUVERED TYPE DETAIL

A CRACK MUST NOT EXTEND INTO SEAM WELD

NON−LOUVERED TYPE DETAIL

B

C13627A

Post-SB3250 Acceptable Buckling and Cracking in Cooling Rings Figure 204

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CRACKS OF THIS NATURE ARE ACCEPTABLE, PROVIDED THEY DO NOT EXCEED 0.300 INCH IN LENGTH AND ARE STOP−DRILLED USING 1/16 DRILL.

C225B Acceptable Cracks in Louvered Cooling Ring Seam Weld Figure 205

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PRE−SB3250

TYPICAL CRACK ADJACENT TO WELD SEAMS

FUEL MANIFOLD SUPPORT COLLAR WELDS

POST−SB3250 POST−SB3296

TYPICAL CRACK NEXT TO SEAM WELD

FUEL MANIFOLD SUPPORT COLLAR WELDS

Post-SB3250 and Post-SB3296

C41438B

Cracks in Combustion Chamber Liner Figure 206

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CAUTION: CRACKS RUNNING IN SAME DIRECTION, AND WHICH COULD ULTIMATELY JOIN, ARE NOT ACCEPTABLE UNLESS THEY ARE SEPARATED BY AT LEAST THREE INCHES OF PARENT METAL. (d) Maximum seven cracks, each crack not exceeding one inch long, is acceptable in the inner wall next to the domed end (Ref. Fig. 207 or 208, Detail A). (e) For PT6A-41 (Post-SB3074) and PT6A-40/-42/-42A Engines: Cracks from holes betweenf uel manifold support collars in inner portion of double skin are acceptable provided they run in a front to rearward manner. (f)

For PT6A-41 (Post-SB3074) and PT6A-40/-42/-42A Engines: Cracks along or adjacent to outer portion of double skin weld seam (Ref. Fig. 206) are acceptable provided there are not more than seven and they are not nearer than one-half inch to the fuel manifold support collar weld.

(g) Localized areas that have been heated to an extent as to cause buckling of the liner are considered acceptable provided the buckling is shallow, and it is not associated with burning, which would reduce the wall thickness and weaken the structure (Ref. Fig. 209 or 210, Detail A). (h) Cracks along, or next to, outer liner flange to wrapper seam weld (Post-SB3250 and Post-SB3296) (Ref. Fig. 206) are acceptable provided there are not more than seven and they are no nearer than one-half inch to the fuel manifold support collar. (i)

Cracks up to 1.00 inch long in the large exit duct section (Post-SB3250 and Post-SB3296) inner wall are acceptable provided they are stop drilled using a 1⁄16 (0.0625) inch drill.

(j)

Coating loss of any amount is acceptable on large exit duct section (Post-SB3250 and Post-SB3296) provided there is no evidence of burning or erosion of parent metal.

(k) For Pre-SB3250 liner dome configurations only: Localized areas that have been heated so as to cause bulging of the liner dome are considered acceptable provided there is no crack and the bulging is not associated with excessive burning, which would reduce the wall thickness and weaken the structure. The dome bulging is often associated with cooling ring buckling and reduction of cooling ring gap. Repair of the gap is necessary (Ref. Step (2) and Figure 211). (2)

Acceptable Conditions, Repair Necessary: (a) Buckled cooling rings where the gap has been eliminated must be reworked. Use a suitable bar to restore a uniform gap to dimensions shown (Ref. Figs. 212, 213, 214 or 215). (b) Cracks not exceeding two inches in length must be repaired (Ref. Approved Repairs).

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C88A

Pre-SB3250 Combustion Chamber Liner Figure 207

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

LINE OF COOLING HOLES AFFECTED BY EXCESS PLASMA SPRAY CHECK BY INSERTING SUITABLE SIZE DRILL

A

DETAIL

A

Post-SB3250 and Post-SB3296

C10277B

Combustion Chamber Inner Liner Figure 208

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

C89A

Pre-SB3250 Acceptable Buckling in Liner Figure 209

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

B

A LINE OF COOLING HOLES AFFECTED BY REPAIR. CHECK BY INSERTING SUITABLE SIZE DRILL.

THREE LARGE HOLES

FUEL MANIFOLD BOSS ALTERNATE CONFIGURATIONS DETAIL DETAIL

B

A

Post-SB3250 and Post-SB3296

C10278C

Acceptable Buckling and Inspection of Cooling Holes Figure 210

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TYPICAL

C25837 Acceptable Bulging in Liner Dome Figure 211

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0.060 0.040

DOME TO OUTER LINER SEAM WELD

0.050 0.030

0.010 0.000

TYPICAL VIEWS ON ARROWS 0.080 0.060

0.080 0.060

B

0.050 0.030

B LINER DOME LOUVERED COOLING RING

DOME TO INNER LINER SEAM WELD

B

0.080 0.060

0.080 0.060

0.080 0.060

C3706A

PT6A-41 (Pre-SB3021) Combustion Chamber Liner Seam Weld and Cooling Ring Gaps Figure 212

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PRE−SB3074

DOME TO OUTER LINER SEAM WELD

0.050 0.030

0.050 0.030

0.080 0.060

0.080 0.060

SUPPORT STRIP

0.050 0.030

POST−SB3074

A B

LINER DOME LOUVERED COOLING RINGS

DOME TO INNER LINER SEAM WELD

B 0.010 0.000

0.080 0.060 0.060 0.040

0.080 0.060

0.080 0.060 OUTER WRAPPER OF COMBUSTION CHAMBER LINER

TYPICAL VIEW ON ARROWS OUTER WRAPPER OF COMBUSTION CHAMBER LINER

SUPPORT STRIP 0.025 0.020

B

0.025 0.020 MIN. 0.022

SEAM WELD THIS AREA MISMATCH IN EITHER DIRECTION PERMISSIBLE

SEAM WELD THIS AREA

15.325 AVERAGE DIA. 15.300

DETAIL

A

PRE−SB 3100

SUPPORT STRIP ASSEMBLY DETAIL

A

POST−SB 3100

PT6A-41 (Post-SB3021, Pre-SB3170) and PT6A-38/-42 (Pre-SB3170)

C3933D

Combustion Chamber Liner Seam Weld and Cooling Ring Gaps Figure 213

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

DOME TO OUTER LINER SEAM WELD

0.050 0.030

POST−SB3236

0.080 0.060

0.080 0.060

A

0.050 0.030 LOUVERED COOILING RING

0.050 0.030

LINER DOME

DOME TO INNER LINER SEAM WELD 0.080 0.060

0.080 0.060

0.080 0.060

0.050 0.030

SUPPORT STRIP ALTERNATE CONFIGURATION PRE−SB3236

0.050 0.030

DETAIL

A

PT6A-40/-41/-42 (Pre-SB3250)

C9250C

Combustion Chamber Liner Seam Weld and Cooling Ring Gaps Figure 214

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FLANGE TO WRAPPER SEAM WELD

0.040 0.030

C 0.070 0.060

A

0.060 0.040

POST−SB3250 PRE−SB3296

0.060 0.050

LOUVERED COOLING RING

0.080 0.070

D

0.070 0.060

POST−SB3296

B

0.865 0.825

0.056 0.046

B VIEW

0.060 0.050

A

SECTION

B−B VIEW

FLANGE TO NOSE LINER SEAM WELD

0.060 0.040

0.010 0.000

0.080 0.060

0.060 0.040

C

0.060 0.040

TYPICAL VIEW ON ARROW

0.040 0.030

0.060 0.040 NOSE LINER TO WRAPPER SEAM WELD

C41434A

Post-SB3250 Combustion Chamber Liner Seam Weld and Cooling Ring Gaps Figure 215

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Page 219 Feb 07/2003

D

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(c) Circumferential cracks next to seam welds must be repaired (Ref. Approved Repairs). NOTE:

Combustion chamber liners with crack openings in excess of 0.030 inch are not field repairable. Send liner to an approved overhaul facility for possible restoration to a serviceable condition.

(d) When cracks progress from a free edge so that their meeting is imminent, and could subsequently allow a piece of liner material to break loose, they must be repaired by welding (Ref. Approved Repairs). (e) Make sure that cooling holes are not blocked as a result of welding or plasma overspray. Use a suitable drill to check pattern and size of holes adjacent to repair area (Ref. Figs. 208 and 210, Detail B). (3)

Unacceptable Conditions, No Repair Permitted: NOTE:

Rejected combustion chamber liners removed during maintenance activities should be returned to an overhaul facility for possible restoration to a usable condition. It is recommended that ‘‘run’’ inner and outer liners be kept together in pairs, if possible.

(a) Multiple cracks that are not repairable (Ref. Fig. 216 or 217). (b) Severe buckling causing kinked metal (Ref. Fig. 218 or 219). (c) Cracks exceeding two inches in length, except where otherwise stated. (d) Circumferential cracks which are opened more than 0.030 inch and are next to seam welds. 7.

Approved Repairs A.

Repair of Cracks CAUTION: HOLES THAT BECOME PLUGGED AS A RESULT OF WELDING MUST BE REDRILLED TO ORIGINAL SIZE AND THEN DEBURRED. CHECK PATTERN AND SIZE OF ADJACENT HOLES USING SUITABLE DRILL GAGE. LOOSE WELD MATERIAL MUST BE REMOVED. (1)

Stop drill ends of crack with a1⁄16 (0.0625) inch drill. Vee out crack using a suitable abrasive wheel.

(2)

Thoroughly wire brush area and swab with (PWC11-014).

(3)

Repair prepared area with tungsten inert gas (TIG) equipment (Ref. 70-00-00, REPAIR) and small diameter filler rod (PWC05-151) or (PWC05-180) (Ref. Table 201) to minimize weld bead size. Stress relief after welding is not necessary. NOTE:

Use copper back-up plate to reduce distortion, with addition of argon gas backup, if available.

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C91A

Pre-SB3250 Unacceptable Multiple Cracks in Liner Figure 216

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A

DETAIL

A

Post-SB3250 and Post-SB3296

C10280A

Unacceptable Multiple Cracks in Liner Figure 217

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

C90A

Pre-SB3250 Unacceptable Buckling in Liner Figure 218

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A

DETAIL

A

Post-SB3250 and Post-SB3296

C10279A

Unacceptable Buckling in Liner Figure 219

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(4)

If outer liner (Post-SB3250) heat shield is repaired in Area B (Ref. Fig. 220), smooth weld bead flush to parent metal. To make sure adequate dome cooling, remove ceramic coating from Area C of inner liner.

72-40-01

Page 224A/224B

COMBUSTION CHAMBER LINER ASSEMBLY - MAINTENANCE PRACTICES

Apr 08/2005

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 201, Weld Fillter Rods Combustion Chamber Liner Part Number

Filler Material

3022392

PWC05-180

3024282

PWC05-151

3028316

PWC05-151

3029559

PWC05-151

3030307

PWC05-151

3101341-02

PWC05-151

3103775-01

PWC05-151

3110188-01 (Outer)

PWC05-151

3110179-01 (Inner)

PWC05-151

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OUTER LINER

B HEATSHIELD AREA

INNER LINER

C VIEW

A

TYPICAL HAIRLINE CRACKS

A

TYPICAL EROSION

Post-SB3250 and Post-SB3296

C41329B

Outer Liner Flange Heat Shield Inspection Figure 220

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2

Dec 10/2010 Dec 10/2010

Contents

1 2 3 4

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

72-50-00 Description and Operation

1 2

Sep 24/99 Sep 24/99

72-50-01 Description and Operation

1 2 blank

Sep 24/99 Sep 24/99

72-50-01 Maintenance Practices

201 202 203 204 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220 221 222 223

Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008

CHAPTER SECTION

PAGE

72-50-02 Description and Operation 72-50-02 Maintenance Practices

DATE

224 225 226 227 228 229 230 231 232 233 234 235 236 237 238 239 240 241 242 243 244 245 246 247 deleted 248 deleted

Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008

1 2 blank

Sep 24/99 Sep 24/99

201 202 203 204 205 206 207 208 209

Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008

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

72-50 LEP

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LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE 210 211 212 213 214 blank

72-50-03 Description and Operation 72-50-03 Maintenance Practices

72-50-04 Description and Operation 72-50-04 Maintenance Practices

1 2 blank

201 202 203 204 205 206 207 208 209 210 1 2

201 202 203 204 205 206 207 208 209 210 211 212 213 214 215 216

DATE Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Sep 24/99 Sep 24/99

CHAPTER SECTION

PAGE

72-50-05 Description and Operation 72-50-05 Maintenance Practices

DATE

1 2

Sep 24/99 Sep 24/99

201 202

Sep 24/99 Sep 24/99

Jun 26/2009 Jun 26/2009 Jun 26/2009 Jun 26/2009 Jun 26/2009 Jun 26/2009 Jun 26/2009 Jun 26/2009 Jun 26/2009 Jun 26/2009 Sep 24/99 Sep 24/99

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

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

72-50 LEP

Page 2 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

TURBINE SECTION- DESCRIPTION AND OPERATION

72-50-00

1.

General

1

2.

Description and Operation

1

COMPRESSOR TURBINE STATOR - DESCRIPTION AND OPERATION 1.

Description and Operation

72-50-01 1

COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

72-50-01

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation (Heavy Maintenance Only)

202

A.

Removal of CT Vane Ring, PT6A-41 (Pre-SB3020)

202

B.

Removal of CT Vane Ring, PT6A-41 (Post-SB3020) and PT6A-40/-41/-42/-42A,

202

C.

Installation of CT Vane Ring, PT6A-41 (Pre-SB3020)

203

D.

Installation of CT Vane Ring (Post-SB3020)

209

6.

7.

Inspection/Check

217

A.

Inspection of CT Vane Ring

217

B.

Inspection of CT Shroud Housing and Shroud Segments

219

C.

Inspection of Small and Large Exit Ducts

219

D.

Compressor Turbine Shroud Locating Ring (Pre-SB3208)

220

E.

Inspection of Shroud Segment Retaining Ring

220

Approved Repairs (Heavy Maintenance Only)

220

A.

Replacement of Shroud Segments, PT6A-41 (Pre-SB3020),

220

B.

Replacement of Shroud Segments, PT6A-41 (Post-SB3020) and PT6A-38/-42/-42A,

221

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

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TABLE OF CONTENTS SUBJECT

PAGE

COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES (Cont’d)

8.

C.

Grinding of Compressor Turbine Shroud Segments

225

D.

Lapping of Hot Section Parts

233

E.

Fitting of Hot Section Parts

235

Fits and Clearances

239

A.

General

239

B.

Dimensional Checks

239

C.

Torque Limits

239

COMPRESSOR TURBINE - DESCRIPTION AND OPERATION 1.

72-50-01

Description and Operation

72-50-02 1

COMPRESSOR TURBINE - MAINTENANCE PRACTICES

72-50-02

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation

202

A.

Removal of CT Assembly

202

B.

Installation of CT Assembly

205

6.

Inspection/Check

207

A.

Compressor Turbine Blade Tip Clearance

207

B.

Inspection of CT Blades

207

C.

Compressor Turbine Stubshaft Bolt (Post-SB3254)

212

D.

Inspection of CT Disk

213

POWER TURBINE INTERSTAGE - DESCRIPTION AND OPERATION 1.

Description and Operation

72-50-03 1

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

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TABLE OF CONTENTS SUBJECT

PAGE

POWER TURBINE INTERSTAGE - MAINTENANCE PRACTICES

72-50-03

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation (Heavy Maintenance only)

201

A.

Removal of Power Turbine Stator

201

B.

Installation of Power Turbine Stator

203

6.

7.

Inspection/Check

204

A.

204

Inspection of Power Turbine Stator Assembly

Approved Repairs

208

A.

Replacement of Interstage Baffle Rivets

208

B.

Repair of Sealing Surfaces

208

POWER TURBINE - DESCRIPTION AND OPERATION 1.

Description and Operation

72-50-04 1

POWER TURBINE - MAINTENANCE PRACTICES

72-50-04

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

202

5.

Removal/Installation (Heavy Maintenance Only)

202

A.

Removal of Power Turbine

202

B.

Installation of Power Turbine

203

6.

Inspection/Check (Heavy Maintenance Only)

205

A.

Inspection of Power Turbine Installation

205

B.

Inspection of Power Turbine Disk

207

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

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TABLE OF CONTENTS SUBJECT

PAGE

EXHAUST DUCT - DESCRIPTION AND OPERATION 1.

Description and Operation

72-50-05 1

EXHAUST DUCT - MAINTENANCE PRACTICES

72-50-05

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Cleaning/Painting

201

A.

201

6.

7.

Cleaning of Exhaust Duct

Inspection/Check

201

A.

201

Inspection of Exhaust Duct

Approved Repairs

202

A.

202

Replacement of Shanknut (Heavy Maintenance Only)

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

72-50 CONTENTS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TURBINE SECTION- DESCRIPTION AND OPERATION 1.

General The engine incorporates two turbines, one for the compressor section and the other for the power output section. The compressor turbine is a single-stage assembly splined to the compressor front stubshaft, while the power turbine is a dual-stage (first- and second-stages) assembly splined to the power turbine shaft, which, in turn, drives the reduction gearbox.

2.

Description and Operation (Ref. Fig. 1) Each turbine stage is preceded by an inlet guide vane assembly which directs the gas flow onto its associated turbine at the most efficient angle. The inlet guide vanes on PT6A-38 engines are of the solid variety, while the vanes on PT6A-41 and PT6A-42 engines are provided with cored cooling air passages. The compressor turbine rotates within a shroud housing which incorporates nine shroud segments. The segments are ground to provide the necessary blade tip clearance. The power turbine guide vanes and interstage baffle, which form part of the first-stage power turbine inlet guide vane assembly, are contained within the power turbine stator housing which is bolted, at its front end, to the exhaust duct. The gas flow from the combustion chamber liner is directed into the engine turbine area via the annular passage between the small and large exit ducts. This passage changes the gas flow 180 degrees to provide a forward flow through the compressor turbine and power turbine.

72-50-00 TURBINE SECTION- DESCRIPTION AND OPERATION

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

GAS GENERATOR CASE (REF) T5 BUS BAR AND PROBE ASSEMBLY

FLANGE C (REF)

T5 WIRING HARNESS EXHAUST DUCT (REF)

POWER TURBINE 1ST STAGE TURBINE

FLANGE

B

LARGE EXIT DUCT (REF) INTERSTAGE SEALING RINGS SMALL EXIT DUCT

NO. 4 BEARING

POWER TURBINE 2ND STAGE TURBINE POWER TURBINE SHAFT

SHAFT COUPLING SHAFT SPIGOT

COMPRESSOR TURBINE VANE RINGS NO. 2 BEARING COVER NO. 2 BEARING CENTER BOLT

FWD

NO. 4 BEARING OIL NOZZLE (REF)

NO. 2 BEARING AIR SEAL NO. 3 BEARING NO. 3 BEARING AIR SEAL

SUN GEAR NO. 3 AND NO. 4 BEARING SCAVENGE OIL TUBE

COMPRESSOR TURBINE COMPRESSOR TURBINE SHROUD HOUSING

POWER TURBINE SHAFT HOUSING

SHROUD HOUSING 2ND STAGE POWER TURBINE

POWER TURBINE 1ST STAGE STATOR GUIDE VANE AND INTERSTAGE BAFFLE

STATOR GUIDE VANE 2ND STAGE POWER TURBINE

POWER TURBINE STATOR HOUSING

C52B Compressor Turbine and Power Turbine - Cross-section Figure 1

72-50-00 TURBINE SECTION- DESCRIPTION AND OPERATION

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR TURBINE STATOR - DESCRIPTION AND OPERATION 1.

Description and Operation (Ref. 72-50-00, Fig. 1) The compressor turbine classified guide vane ring consists of 14 vanes, cast integrally and located between inner and outer rings. The vane ring is of the ‘‘dihedral angle’’ type; that is, the leading (rear) edge of each vane lies at an angle between the inner and outer rings, whereas the trailing (forward) edge is approximately perpendicular between the rings. The airfoil section of the vanes directs the expanding gases from the combustion chamber liner to the compressor turbine blades at the optimum angle for maximum drive and efficiency. The inner ring is cast with an extended rearward platform and internal flange. Lugs on the flange engage with slots in the number 2 bearing cover flange. An annular lockplate and 16 bolts secure the vane ring, number 2 bearing cover, number 2 bearing cover flange and large exit duct to the gas generator case. The outer ring locates the compressor turbine shroud housing and small exit duct. An air baffle attached to the forward edge of the No. 2 bearing cover fills the annular space at the ID of the vane inner ring. The compressor turbine shroud housing extends forward towards the power section. The extension provides two features: the outer diameter incorporates a circumferential groove which accommodates two (inner and outer) interstage sealing rings while the inner diameter is machined to accommodate the classified compressor turbine shroud segments. The segments are held in position by a retaining ring seated in a circumferential groove inside the shroud housing. Segments are additionally positioned by a circular locating plate (Pre-SB3208) with notches to engage each segment and tangs at the rear that engage the outer ring flange of the guide vane ring. The shroud segments act as a seal and provide running clearance for the compressor turbine. The interstage sealing rings seal the mechanical separation between the combustion section and the interturbine area. The large exit duct (Pre-SB3250), or combustion chamber outer liner (Post-SB3250), is located adjacent to the diffuser in the front section of the gas generator case. The large exit duct, or rear section of the outer liner, forms the outer section of an envelope which changes the direction of gas flow 180 degrees and directs it to the compressor turbine guide vanes. The duct or outer liner, is fabricated from nickel alloy and incorporates a heatshield at the rear; compressor discharge air (P3) is routed into the space formed by the heatshield to cool the duct. The outer flange of the large exit duct incorporates a ‘‘wiggle strip’’ which provides a mating flange for the outer wall of the combustion chamber liner (Pre-SB3250) and ports for the passage of cooling air over the duct wall. The inner section of the duct, or outer liner, incorporates a bolting flange for mounting at the gas generator case centerbore. The small exit duct locates in the rear of the combustion chamber liner via a sliding joint and slotted seal ring and attaches to the compressor turbine guide vane ring. The duct forms the inner section of an envelope that changes the direction of gas flow 180 degrees and directs it to the compressor turbine inlet guide vanes. The duct is fabricated from nickel alloy and incorporates a heatshield and mounting flange at the front. Holes in the heatshield allow cooling air to be routed through the space between the duct wall and heatshield; the air then passes out of the space and into the gas stream at the ID of the duct wall. On the PT6A-40/-41/-42 engines, air entry ports are incorporated in the mounting flange to enable P3 cooling air to be directed into the cored passages in the compressor inlet guide vanes.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR TURBINE STATOR - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire used, unless otherwise specified, shall comply with specification AMS5687, heat and corrosion resistant steel wire MS9226-03, 0.025 inch diameter, and will not be called out in instructions.

Consumable Materials The consumable materials listed below are used in the following procedures. Item No.

Name

PWC05-018 PWC05-145 PWC09-002

Pencil, Metal Marking Compound, Lapping Compound, Locking and Retaining Solvent, Petroleum Cleaner, Engine

PWC11-027 PWC11-031 3.

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

4.

Tool No.

Name

PWC30478 PWC32209 PWC32380 PWC32396-400 PWC32528 PWC32823 PWC34128 PWC34522 PWC37917 PWC37918 PWC42034 PWC64241

Spacer Adapter Gage, radius Jackscrew, three req’d Wheel, Grinding Puller Wheel, Grinding Puller Dresser Grinder Jackscrew Pin, Aligning

Application

Replaced by PWC32396-400

Fixtures, Equipment and Supplier Tools Not Applicable

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

5.

Removal/Installation (Heavy Maintenance Only) A.

Removal of CT Vane Ring, PT6A-41 (Pre-SB3020) (Ref. Figs. 201 and 202) (1)

Remove power section (Ref. 72-00-00).

(2)

Remove compressor turbine disk and blade assembly (Ref. 72-50-02).

(3)

Remove bolts (10), tabwashers and lockplate (12) securing compressor turbine vane ring (4) and shroud housing assembly (2), and No. 2 bearing cover assembly (9) to gas generator case (15).

CAUTION: BEFORE REMOVING CT VANE RING, MARK LOCATION RELATIVE TO NO. 2 BEARING COVER FLANGE WITH AN APPROVED MARKER (PWC05-018)(REF. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts) TO ENSURE CORRECT ALIGNMENT OF MATING SURFACES ON REASSEMBLY. (4)

Withdraw compressor turbine vane ring, shroud housing and small exit duct assembly (14) from gas generator case.

(5)

Remove No. 2 bearing cover assembly (9) and large exit duct from gas generator case (15).

(6)

Inspect vane ring, small exit duct and shroud housing assembly for index ‘‘X’’ mark identification (Ref. Fig. 202). If marks are not legible, mark adjacent to offset hole using an approved marking pencil (PWC05-018).

(7)

Remove 14 bolts (7) securing vane ring (4) and shroud housing (2) to small exit duct (6).

(8)

Remove four plug bolts (16) from jacking holes in shroud housing.

(9)

Use an approved marker (Ref. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts), to mark position of interstage sealing ring gaps on shroud housing. Remove two interstage sealing rings (1) from shroud housing.

(10)

Separate vane ring (4) from shroud housing (2) and small exit duct (6), using four jack screws, if necessary. Tag parts for identification. NOTE:

B.

Should shroud segments require replacement, remove and install new segments as detailed under Approved Repairs (Ref. Para. 7.).

Removal of CT Vane Ring, PT6A-41 (Post-SB3020) and PT6A-40/-41/-42/-42A, (Ref. Figs. 203 and 204) (1)

Install engine in stand (Ref. 72-00-00).

(2)

Separate power section/power section module (PS/PSM) from gas generator module and install PS/PSM in stand (Ref. 72-00-00, SERVICING).

(3)

Remove CT disk and blade assembly (1, Ref. Fig. 203 or 204) (Ref. 72-50-02, Removal/Installation).

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(4)

Remove combustion chamber liner (3) (Pre-SB3250) or inner liner (3) (Post-SB3250) (Ref. 72-40-01, Removal/Installation).

(5)

Remove bolts, washers and baffle plate (14) from gas generator case central mount position.

(6)

Remove No. 2 bearing cover (13) using puller (PWC34522). Post-SB3301: Remove shims (17). NOTE:

Make sure compressor stator air seal (15) and gasket (16) are not disturbed when removing No. 2 bearing cover (13). If air seal and gasket are inadvertently disturbed, install new gasket during assembly.

CAUTION: BEFORE REMOVING CT VANE RING, MARK LOCATION RELATIVE TO NO. 2 BEARING COVER FLANGE WITH AN APPROVED MARKER (REF. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts) TO ENSURE CORRECT ALIGNMENT OF MATING SURFACES ON REASSEMBLY. (7)

Remove bolts and keywashers and separate lockplate (12) from gas generator case central mount position.

CAUTION: HANDLE SMALL EXIT DUCT WITH CARE. IMPACT WITH HARD OBJECT MAY CAUSE DEFECT IN CERAMIC COATING. (8)

Remove No. 2 bearing cover flange (9) (Pre-SB3042), using puller (PWC32823). Remove No. 2 bearing cover flange (9) (Post-SB3042), using jackscrews (PWC42034) or (PWC32396-400).

(9)

Remove large exit duct (8) (Pre-SB3250), or combustion chamber outer liner (8) (Post-SB3250), from gas generator case. NOTE:

(10)

Removal of outer liner (8) (Post-SB3250) involves removal of fuel manifold and adapters (Ref. 73-10-05) and igniter plugs (Ref. 74-20-00).

Remove bolts, stator assembly (11), and shroud housing (4) from small exit duct (10). NOTE:

If necessary, remove bolts from jacking holes in shroud housing and use jackscrews (PWC42034) or (PWC32396-400) to separate components.

CAUTION: BEFORE REMOVING INTERSTAGE SEALING RING, MARK GAPS ON SHROUD HOUSING WITH AN APPROVED MARKER (REF. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts). (11)

Remove sealing rings (2) from groove in shroud housing, if necessary. NOTE:

C.

Should shroud segments require replacement, remove and install segments as detailed in Approved Repairs.

Installation of CT Vane Ring, PT6A-41 (Pre-SB3020) (Ref. Figs. 201, 202 and 205) (1)

Inspect shroud housing slots (3) and rear face of vane ring (4) for vibropeened index ‘‘X’’ marks. Align index marks.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

12

8

11

OFFSET HOLE 9

10

13

15

6

JACKING LOCATIONS

7

5

4 3 2 1

16 14

7

C664B

PT6A-41 (Pre-SB3020)

Removal/Installation of Compressor Turbine Vane Ring, Shroud Housing and Small Exit Duct Figure 201

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. (2)

Interstage Sealing Rings Compressor Turbine Shroud Housing Shroud Housing Slots Compressor Turbine Vane Ring Vane Rig Lugs (Outer) Small Exit Duct Bolt (14 each) No. 2 Bearing Cover Slots No. 2 Bearing Housing Cover Bolt (16 each) Tabwasher (16 each) Lockplate Vane Ring Lugs (Inner) Vane Ring, Shroud Housing and Small Exit Duct Assembly Gas Generator Case Plug Bolt

If replacement vane ring and/or shroud housing are to be installed: (a) Assemble vane ring (4) to shroud housing (2) in each of fourteen positions in order to establish the location most free of interference. (b) When optimum position is established as in step (a), check clearance between shroud housing slots (3) and vane ring outer lugs (5) on same side of each lug as shown in Figure 202. (c) Lightly stone each lug as necessary to obtain 0.001 to 0.002 clearance at each location. (d) When clearance has been established, align and suitably mark index ’X’ marks for future alignment (Ref. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts).

(3)

Assemble shroud housing (3) and vane ring (4) to small exit duct (6) and secure with bolts (7). Tighten bolts and torque 15 to 20 lb.in. Do not lockwire at this stage.

(4)

Install four plug bolts (16) in flange of shroud housing. Tighten bolts and torque 15 to 20 lb.in. Lockwire bolts (7) and (16) in pairs.

(5)

Use an approved marking method (Ref. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts) to mark offset hole in flange of large exit duct, number 2 bearing housing cover (9) and lockplate (13). Make sure all markings are visible during assembly of parts.

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR TURBINE SHROUD HOUSING

SHROUD HOUSING SLOTS

E

CHECK CLEARANCE (14 LOCATIONS)

SHROUD HOUSING

VANE RING

LOCATION MARKS (X)

E

C1324A Removal/Installation of Compressor Turbine Vane Ring, Shroud Housing and Small Exit Duct (Typical) Identification Figure 202

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(6)

Position large exit duct in gas generator case (15) and align offset hole in duct with corresponding offset hole in gas generator case flange. Offset hole in located to right of 12 o’clock position, as viewed looking into case. When a new vane ring or No. 2 bearing cover is to be installed, the optimum fit of the vane ring lugs to the No. 2 bearing cover slots must be obtained, and the lugs must not be pinched by the lockplate. To obtain correct fit: (a) Place No. 2 bearing cover on bench with flange face down. (b) Lower vane ring assembly over cover until lugs on vane ring engage with slots in cover flange. Do not use force. (c) If interference is encountered, rotate vane ring by one slot and repeat step (b). Repeat in each of remaining slot positions until best location is determined. (d) If interference is found in all possible locations, locate the offending lug(s) and lightly stone until free, hand fit is obtained. There should be no rotational movement. (e) Measure thickness of No. 2 bearing cover flange and vane ring inner flange. The thickness of No. 2 bearing cover flange should be equal to or greater than the vane ring inner flange. (f)

Rectification may be achieved by selection of vane rings, No. 2 bearing covers or lockplates, or by lapping the lockplate to the vane ring inner flange.

(7)

Install number 2 bearing housing cover (9) over large exit duct flange and align offset holes.

(8)

Locate lockplate (12) into centerbore of vane ring, and make sure chamfered face of lockplate is located at interface.

(9)

Install vane ring, shroud housing and small exit duct assembly (14) in gas generator case, aligning pencil index marks on vane ring and No. 2 bearing cover. Maintain alignment of offset holes while engaging lugs (13) of vane ring with corresponding slots (8) in No. 2 bearing cover.

(10)

Secure assembly (14), large exit duct, No. 2 bearing housing cover (9) and lockplate (12) to gas generator case flange with bolts (10) and tabwashers (11). Tighten bolts, torque 36 to 40 lb.in., and lock tabwashers.

(11)

Check that complete assembly has no rotational movement.

(12)

Install two interstage sealing rings (1) in groove in OD of shroud housing (2). Make sure that gaps in rings are positioned 180 degrees apart and that they align with marks on shroud housing (Ref. Para. A., step (9)).

(13)

Install compressor turbine disk and blade assembly (Ref. 72-50-02).

(14)

Check compressor turbine tip clearance (Ref. 72-50-02).

(15)

Install combustion chamber liner (Ref. 72-40-01).

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

2

3

4

5

6

7

8 INTERNAL PORTION OF GAS GENERATOR CASE 1 9 10 11 12

14

13

15

16 INSTALL GASKET WITH PROUD SIDE (BUMP) FACING THE NO. 2 BEARING

PT6A-38/-41 (Post-SB3020/ Pre-SB3250), PT6A-40/-42 (Pre-SB3250)

C3908E

Removal/Installation of CT Vane Ring Assembly Figure 203

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 203 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. (16) D.

CT Assembly Interstage Seal Rings Combustion Chamber Liner Shroud Housing Shroud Segments Retaining Ring Shroud Locating Ring (Pre-SB3208) Large Exit Duct No. 2 Bearing Cover Flange Small Exit Duct CT Vane Ring Lockplate No. 2 Bearing Cover CT Air Baffle No. 2 Bearing Stator Air Seal Gasket

Install power section (Ref. 72-00-00).

Installation of CT Vane Ring (Post-SB3020) (Ref. Figs. 203 and 204) (1)

Make sure vane ring assembly, shroud housing and lockplate have been lapped and lug-to-slot clearances have been checked (Ref. Approved Repairs). Make sure cooling air holes in diffuser block around No. 2 bearing housing are clear.

(2)

Align index marks, and assemble shroud housing (4, Ref. Fig. 203 or 204) and stator assembly (11) to small exit duct (10). Install bolts. Tighten bolts 15 to 20 lb.in., and lockwire.

(3)

If removed, install bolts in jacking holes in flange of shroud housing, tighten 15 to 20 lb. in. and lockwire.

(4)

Install large exit duct (8) (Pre-SB3250) or combustion chamber outer liner (8) (Post-SB3250) in gas generator case, aligning offset holes, fuel manifold adapter holes and igniter plug holes. Install fuel manifold adapters (Ref. 73-10-05, Removal/Installation) and igniter plugs (Ref. 74-20-00, Removal/Installation).

(5)

Locate No. 2 bearing cover flange (9) in large exit duct or combustion chamber outer liner. Align offset holes. NOTE:

Due to relative tolerances, tightness may be encountered when fitting flange on gas generator case. When these conditions prevail, use of a soft-faced hammer is permissible.

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

4

2

1

5

7

6

3

INTERNAL PORTION OF GAS GENERATOR CASING 8 9

17 10 POST−SB3301

11 12

13

14 15

16 INSTALL GASKET WITH PROUD SIDE (BUMP) FACING THE NO. 2 BEARING

PT6A-40/-41/-42 (Post-SB3250)

C41428C

Removal/Installation of CT Vane Ring Assembly Figure 204

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 204 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. (6)

CT Assembly Interstage Seal Rings Combustion Chamber Inner Liner Shroud Housing Shroud Segments Retaining Ring Shroud Locating Ring (Pre-SB3208) Combustion Chamber Outer Liner No. 2 Bearing Cover Flange Small Exit Duct CT Vane Ring Lockplate No. 2 Bearing Cover CT Air Baffle Compressor Rear Stator Air Seal Gasket Shims (Post-SB3301)

Install assembled vane ring and shroud housing assembly in gas generator case, engaging compressor turbine stator inner lugs with corresponding slots on No. 2 bearing cover flange, in original position as previously marked. NOTE:

If new parts are being installed, no index marks will be found. Parts should be rotated/fitted until best fit is obtained.

(7)

Position lockplate (12) into center of CT stator. Make sure chamfered face of lockplate is located at interface. Install lockplate, CT stator and shroud housing to large exit duct or, combustion chamber liner, and gas generator case with bolts and keywashers. Tighten bolts 36 to 40 lb. in. and lock keywashers.

(8)

Make sure assembly does not rotate. NOTE:

(9)

Due to tolerances involved, a slight axial movement may be evident (REF. NO. 489, Fits & Clearances).

If removed, install interstage sealing rings (2). Make sure index marks are aligned with gaps 180 degrees apart, in circumferential groove of shroud housing (4). NOTE:

Check pressure side of sealing ring (marked on ring) is facing mating flange of small exit duct to CT shroud housing.

(a) Alternatively, install inner ring in shroud housing and mount outer ring on inner ring with chamfered face positioned away from gas generator case and gaps in each ring 180° apart

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

CRACK OF THIS NATURE ACCEPTABLE

VANE TRAILING EDGE COATING LOSS AND EROSION ACCEPTABLE

POCKET SCOOPS

OUTER RIM FILLET AREA

LEADING EDGE

VANE LEADING EDGE AND AIRFOIL LOSS OF COATING ACCEPTABLE

AIR FLOW

B

C

TRAILING EDGE

A

FILLET AREA

INNER RIM

VANE RING CROSS−SECTION

C5327B Inspection of Compressor Turbine Vane Ring - Typical Figure 205

72-50-01 COMPRESSOR TURBINE STATOR - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(10)

If the air seal (15) and gasket (16) have been accidently disturbed (Ref. Step (6)), install two guidepins (PWC64241) into the gas generator case.

(11)

Install a new gasket (16) (with the proud side towards the No. 2 bearing), the air seal (15) and the No. 2 bearing cover (13) over the guidepins and the protruding centerbore of the No. 2 bearing cover flange. Light tapping with a soft faced hammer is permitted. NOTE:

When fitting a new No.2 bearing cover (13), the correct gap between the bearing cover and the compressor turbine disk (1) must be kept. Measure the new bearing cover inner diameter, then subtract the measured diameter of the compressor turbine balancing rim and record the result. Divide the result by two to calculate the radial clearance (REF. NO. 261, Fits & Clearances).

(12)

Put the CT air seal baffle (14), over the guide pins on the No.2 bearing cover. Make sure the bolt holes are aligned.

(13)

Install the CT stator air seal baffle and No.2 bearing cover on the gas generator case with bolts and keywashers . Remove the guide pins and install the remaining bolts. Tighten the bolts 36 to 40 lb. in. Pre-SB3301: Lock the keywashers. Post-SB3301: Determine shim (17) thickness required (Ref. step (14)).

(14)

For Post-SB3301 Engines: Determine number of shims required to obtain setting Dimension Z (Ref. Fig. 206): (a) Torque bolts (1) 36 to 40 lb.in. but do not lock keywashers (2). (b) Place straightedge across flange C, measure and record Dimension A and Dimension B. (c) Remove bolts (1), baffle (3) and No. 2 bearing housing cover (4). (d) Calculate shim thickness = Dim. B - Dim. A (e) Select shims to obtain Dimension Z (+0.00 / -0.010 inch). NOTE: (f)

Total shim thickness must not exceed 0.090 inch. Each shim is 0.0075 to 0.0085 inch thick.

Install shims, No. 2 bearing housing cover, compressor turbine air baffle, bolts and washers. Torque bolts 36 to 40 lb.in. but do not lock keywashers.

(g) Repeat step (b), and verify setting Dimension Z (REF. NO. 366, Fits & Clearances) is within limits. (h) Make sure clearances between vane ring and outer diameter of baffle, and between No. 2 bearing housing cover and inner diameter of baffle, are within limits (REF. NO. 229, 261, Fits & Clearances). (i)

Lock keywashers on baffle retaining bolts.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

6 3 CLEARANCE TO BE MAINTAINED BETWEEN VANE RING AND BAFFLE FLANGE

VIEW E

C

7

6

DIM. B

E 4 DIM. A

3 1

2

ENGINE CENTERLINE

5

SHIM THICKNESS = DIM. B

DIM. A

C41984B

Post-SB3301 Shim Thickness Determination (Typical) Figure 206 (Sheet 1 of 2)

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A

B

3 6

2

0.025 MIN.

SHIMS

1

0.005 0.000 3

4 5

DETAIL

A

SETTING DIMENSION 0.010 0.000

Z DETAIL B (SHIMS INSTALLED)

C28318A

Post-SB3301 Shim Thickness Determination (Typical) Figure 206 (Sheet 2)

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Key to Figure 206 1. 2. 3. 4. 5. 6. 7.

Bolt Keywasher Baffle No. 2 Bearing Housing Cover Shims Compressor Turbine Vane Ring Gas Generator Case

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6.

(15)

Install compressor turbine disk and blade assembly (Ref. 72-50-02, Removal/Installation).

(16)

Check compressor turbine blade tip clearances (Ref. 72-50-02, Inspection/Check).

(17)

Install Pre-SB3250 combustion chamber or Post-SB3250 combustion chamber inner liner (Ref. 72-40-01, Removal/Installation).

(18)

Install power section/power section module (PS/PSM) in gas generator assembly (Ref. 72-00-00, SERVICING).

(19)

Remove engine from stand (Ref. 72-00-00).

Inspection/Check A.

Inspection of CT Vane Ring (1)

Examine vanes, inner, and outer rings (Ref. Table 201 and Fig. 205).

(2)

For PT6A-40/-41 and PT6A-42/-42A Engines: Inspect vane ring at cooling air inlet and outlet ports for damage and blockage. TABLE 201, Compressor Turbine Vane Ring Inspection Max. Serviceable

Max. Repairable

Corrective Action

Vanes

Any amount provided parent metal erosion is within limits.

**

*

Outer ring

Complete loss of coating

**

*

Inner ring

Complete loss of coating

**

*

Vane trailing edges

Multiple hairline cracks not exceeding 0.100 inch long are acceptable.

**

*

Inner ring

Cracks through part or entire length of inner ring are acceptable provided no two cracks converge in such a manner that would allow a piece to become detached. Cracks open not more than 0.020 inch wide are acceptable.

**

*

Outer ring

Cracks through wall of outer ring are acceptable provided there is no burning. Outer ring cracks which extend into the vane airfoil are acceptable provided no two cracks converge in such a manner that would allow a piece to become detached.

**

*

Inspection COATING LOSS

CRACKS

EROSION

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TABLE 201, Compressor Turbine Vane Ring Inspection (Cont’d) Max. Serviceable

Max. Repairable

Corrective Action

Vanes

0.010 inch deep on any airfoil surface on any number of vanes. When a compressor turbine stator examination reveals that stator trailing edge burning has resulted in a loss of airfoil area of 0.125 sq.in., (ie. length 0.350 x width 0.350 = 0.1225 sq.in.) or more, on any one vane, and burnt area can be seen from the leading edge of the stator vane when viewed parallel to longitudinal axis of the engine, the entire set of compressor turbine blades must be scrapped (Ref. 72-50-02).

**

*

Outer and Inner rings

Any amount.

Inspection

NOTE: 1. Acceptance criteria is based on structural integrity considerations and apply only if engine performance was satisfactory prior to an HSI. Replace the vane ring if its condition appears to be the cause for loss of performance. NOTE: 2. * A vane ring exhibiting defects in excess of Maximum Serviceable limits must be replaced. NOTE: 3. When compressor tubine vane ring is to be replaced, a vane ring of the same class, or within ± 0.03 variation of the class from the last test cell performance run, is recommended for installation. NOTE: 4. If a vane ring class is unknown, refer to the last test cell performance run (log book), or contact your local P&WC Customer Support Representative. NOTE: 5. If distressed vanes are encountered, check fuel nozzles functioning.

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TABLE 201, Compressor Turbine Vane Ring Inspection (Cont’d) Inspection

Max. Serviceable

Max. Repairable

Corrective Action

NOTE: 6. **Vane rings considered unacceptable for continued service may be sent to P&WC or following vendors for possible repair. Pratt & Whitney Canada 7007 de la Savane St. Hubert, Quebec Canada J3Y 3X7 Attention: Recieving Area No. 9 Vac-Hyd, Dallas, Blade and Vane Division 1177 Great Southwest Parkway Grand Prairie, TX 75050 USA Howmet Turbine Components Corp. 555 Benston Rd. Whitehall, MI 49461 USA Attention: Thermatech Division Sifco Turbine Component 2430 Winnetka Avenue North Minneapolis, MN 55427 USA B.

C.

Inspection of CT Shroud Housing and Shroud Segments (1)

Inspect shroud housing for signs of distortion and fretting wear in interstage sealing ring groove. Minor fretting wear is acceptable provided high spots are removed by light hand stoning. Reject housing for possible repair if heavy fretting wear or distortion which would impair interstage sealing is present.

(2)

Inspect shroud housing for cracks. Any number of cracks in shroud segment downstream retaining lip are acceptable provided have not penetrated to outside of housing. Reject housing for possible repair if cracked beyond limits.

(3)

Examine interstage sealing rings for condition.

(4)

Examine shroud segments (Ref. 72-50-02, Inspection/Check).

Inspection of Small and Large Exit Ducts (1)

Examine small exit duct for fretting wear at duct flange which contacts combustion chamber inner liner. Wear to 0.015 inch deep is acceptable. If wear is in excess of 0.015 inch, duct should be sent to an approved overhaul facility for possible repair.

(2)

Radial cracks to 1.00 inch long in small exit duct outer wall are acceptable provided they are stop-drilled with a 1⁄16 (0.0625) inch drill.

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D.

E.

(3)

Examine Pre-SB3250 large exit duct for fretting wear along the area which contacts the combustion chamber liner. Wear up to 50 percent of the material thickness is acceptable. If the wear is in excess of 50 percent, the duct should be returned to an approved overhaul facility for possible repair.

(4)

Cracks up to 1.00 inch long in the large exit duct inner wall are acceptable provided they are stop-drilled using a 1⁄16 (0.0625) inch drill.

(5)

Coating loss of any amount is acceptable provided there is no evidence of burning or erosion of parent metal.

Compressor Turbine Shroud Locating Ring (Pre-SB3208) (1)

Visually inspect locating ring. Cracks, distortion and buckling are not acceptable.

(2)

Worn slots are acceptable to a maximum width of 0.750 inch and a maximum depth of 0.110 inch.

(3)

Worn lugs are acceptable to a minimum width of 0.500 inch and a maximum length of 0.065 inch.

Inspection of Shroud Segment Retaining Ring (1)

Examine retaining ring for distortion and function.

(2)

Examine free state end gap: For Pre-SB3248 Engines: 0.065 to 0.100 inch For Post-SB3248 Engines: 0.170 to 0.220 inch

(3) 7.

Replace retaining ring if gap is out of limits or excessive fretting is evident.

Approved Repairs (Heavy Maintenance Only) A.

Replacement of Shroud Segments, PT6A-41 (Pre-SB3020), (Ref. Figs. 207 and 208) (1)

Disassembly of Shroud Housing Assembly (Ref. Fig. 207): (a) Before removing retaining ring (3) from shroud housing (1), ensure that position of gap is marked on shroud housing using an approved marker (Ref. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts). (b) Remove manufactured heads of rivets (2) on inner face of shroud housing using a suitable air-operated drill and grinding wheel (PWC32528). CAUTION: WHEN REMOVING RIVETS, ENSURE RIVET HOLES IN SHROUD HOUSING AND RETAINING RING ARE NOT ENLARGED OR DEFORMED BY PUNCH. DAMAGED RETAINING RINGS MUST BE REPLACED. (c) Carefully punch out rivets (2) with suitable punches and remove retaining ring.

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(d) Place shroud housing on work bench, with flange down, and remove shroud segments (4) using a fiber drift. Lightly tap each segment to free segment from inside housing. (2)

Assembly of Shroud Housing Assembly (Ref. Figs. 207, 208 and 209) (a) Select shroud segment class (Ref. Table 202) to provide specified radial tip clearance (REF. NO. 318, Table 204). NOTE:

It may be necessary to grind inside diameter of shroud segment to obtain required clearance (Ref. Para. C.).

(b) Apply compound (PWC09-002) to the inner and outer surfaces of the front locating lip of one shroud segment. (c) Install one segment (4, Fig. 207) in locating grooves of shroud housing (1), positioning end of segment 1.00 inch minimum distance from previously marked location of retaining ring gap, and 0.250 inch minimum from nearest cooling hole (Dimension A-A, Fig. 208). (d) Apply compound (Ref. Step (b), above) and install remaining eight shroud segments in shroud housing, equalizing gaps between segments. Use suitable shim stock between gaps to facilitate gap equalization. Remove shim stock when segments are firmly located in shroud housing grooves. (e) Position retaining ring (3) on shroud housing (1) with ring gap at previously marked location. (f)

Insert 0.013 inch shim stock between each segment and retaining ring to ensure a clearance of 0.010 to 0.015 inch is maintained between segments and ring.

(g) Adjust compressor turbine shroud riveter, as required, to create an upset head on each rivet to dimensions shown on Figure 207, by inserting shim stock under head of anvil. (h) Connect an air supply, regulated at 85 to 95 psig., to riveter. Rivet retaining ring to shroud housing with rivets (2). NOTE:

B.

Install rivets with manufactured heads on ID of retaining ring.

(i)

Inspect rivets for cracks, deformity of heads and incorrect seating. Replace defective rivets.

(j)

Remove shim stock positioned between shroud segments and retaining ring. Check clearances at all locations. If clearance is not within limits, remove, reposition and reinstall retaining ring. Install new retaining ring, if necessary.

Replacement of Shroud Segments, PT6A-41 (Post-SB3020) and PT6A-38/-42/-42A, (Ref. Figs. 209 and 210) (1)

Disassembly of Shroud Housing Assembly (Ref. Fig. 209):

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SEGMENT GAP TO BE A SHROUD 0.250 IN. FROM COOLING HOLE

0.156 IN. 0.188 IN. 1

A 0.062 IN. 0.109 IN. AREA

B 0.010 IN. 0.015 IN.

3

2

4

C3306B

PT6A-41 (Pre-SB3020) Shroud Housing Assembly Figure 207

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Key to Figure 207 1. 2. 3. 4.

Shroud Housing Retaining Rivet (Manufactured head) Retaining Ring Shroud Segments (9 each)

(a) Use an approved marker (Ref. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts), to mark position of gap in shroud retaining ring (3) on shroud housing (1). Remove retaining ring. (b) Place shroud housing on work bench, with flange end down, and remove shroud segments (2) using a fiber drift. Lightly tap each segment to free segment from counterbore in housing. (2)

Assembly of Shroud Housing Assembly (Ref. Figs. 209 and 210): (a) Select shroud segment class (Ref. Table 202) to provide specified radial tip clearance (REF. NO. 318, Table 204). NOTE: 1. It may be necessary to grind ID of shroud segment to obtain required compressor turbine clearance (Ref. Para. C.). NOTE: 2. For Post-SB3275 Engines: Shroud Segments have no anti-rotation slots and are used in conjuction with Post-SB3265 shroud housing with tightened tolerances on segment locating features. (Ref. Fits and Clearances, Ref. No. 487+488). (b) Apply compound (PWC09-002) to the inner and outer surfaces of the front locating lip of one shroud segment. (c) Install one segment (2) in locating grooves of shroud housing (1) positioning end of segment 1.00 inch minimum distance from previously marked location of retaining ring gap and 0.250 inch minimum from nearest cooling hole (Section A-A, Fig. 210). (d) Apply compound (Ref. step (b) above) and install remaining eight segments in shroud housing, equalizing gaps between segments. Use suitable shim stock between gaps (Section B-B) to facilitate gap equalization. Remove shim stock when segments are firmly located in housing. (e) Install shroud retaining ring (3), as applicable, in groove of shroud housing, aligning gap in ring with index mark on housing. (f)

Check gap between each segment and retaining ring (Ref. Fits and Clearances, Table 204, REF. NO. 675).

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A

0.080 INCH 0.000 INCH GAP

A

B JACKSCREW LOCATIONS

B

AA

0.250 INCH MINIMUM DISTANCE FROM ANY ADJACENT COOLING HOLE

BB

SHROUD SEGMENT GAPS MUST BE EQUAL

C3307B

PT6A-41 (Pre-SB3020) Compressor Turbine Shroud Segment Location Figure 208

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TABLE 202, Compressor Turbine Shroud Segment Classification Recommended Shroud Segment Dim. A (in.) Min. Max.

Shroud ID Before Grinding (in.) Min. Max.

CT Disk OD (in.)

Class

8.556 Max.

4

0.043

0.045

8.570

8.574

8.550

5

0.045

0.047

8.566

8.570

8.546

6

0.047

0.049

8.562

8.566

8.542

7

0.049

0.051

8.558

8.562

8.538

8

0.051

0.053

8.554

8.558

8.534

9

0.053

0.055

8.550

8.554

8.530

10

0.055

0.057

8.546

8.550

8.526

11

0.057

0.059

8.542

8.546

8.522

12

0.059

0.061

8.538

8.542

8.518

13

0.061

0.063

8.534

8.538

8.514

14

0.063

0.065

8.530

8.534

8.510

15

0.065

0.067

8.526

8.530

8.506

16

0.067

0.069

8.522

8.526

8.502

17

0.069

0.071

8.518

8.522

8.498

18

0.071

0.073

8.514

8.518

8.494

19

0.073

0.075

8.510

8.514

8.490 Min.

20

0.075

0.077

8.506

8.510

NOTE: If compressor turbine blade tip clearance exceeds specified limits after removing eccentricity on shroud segments, select next class (thicker) of segments and grind as necessary. C.

Grinding of Compressor Turbine Shroud Segments (Ref. Figs. 211 and 212) (1)

General (a) Replacement of compressor turbine shroud segments may entail localized grinding to remove high spots and/or any slight eccentricity of segments to obtain correct turbine blade tip clearance. If tip clearance exceeds specified limits (REF. NO. 318, Table 204; PT6A-41 (Pre-SB3020) or REF. NO. 318, Table 204, PT6A-41 (Post-SB3020) and PT6A-38/-42/-42A) after removal of high spots and/or eccentricity, select next higher class of shroud segments (Ref. Table 202); install and grind as necessary.

(2)

Determine Shroud Segment Concentricity and Diameter (Ref. Fig. 211). (a) Install adapter (6, PWC32209) on compressor stubshaft with bolts (5).

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B

B

A A

5 3 2 1

POST−SB3275

PRE−SB3360

PRE−SB3275

4

PRE−SB3248

POST−SB3248 SECTION

4

4

B−B 2

1 LOCTITE

3 ALTERNATE ARRANGEMENT

2

SECTION A−A ASSEMBLED

LOCTITE

PT6A-41 (Post-SB3020) and PT6A-38/-42/-42A

C3909E

Shroud Housing Assembly Figure 209

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Key to Figure 209 1. 2. 3. 4. 5.

Shroud Housing Shroud Segments (9) Pre-SB3275 Shroud Segment Retaining Ring Pre-SB3360 Interstage Sealing Rings Shroud Segments (9) Post-SB3275

(b) Install four spacers (11, Fig. 212) under small exit duct. Set spacers approximately 90 degrees apart. (c) Select contact point (3, Fig. 211) for radius to be measured and fasten to radius gage tip (2). NOTE:

Radius gage and gage master are common to all PT6 engines. The gage is supplied with four contact points of different lengths, while the gage master has four ‘‘steps’’ of different radius. These variables allow the gage and master to be used on all PT6 engine models.

(d) Install radius gage (9) on adapter (6) with bolts (7). Tighten bolts 20 to 30 lb.in. Check for correct mounting by trying to insert 0.001 inch shim stock between gage and adapter. (e) Position contact point (3) at center of segment (4) using adjuster (1). (f)

Take four readings, 90 degrees apart around shroud segments. Adjust spacers (11, Fig. 212) as necessary to obtain concentricity.

(g) Remove radius gage from adapter (6, Fig. 211) and install in gage master (8). Set dial indicator (10) to zero. (h) Remove radius gage from master (8). Make sure dial indicator setting is not disturbed. (i)

Install radius gage on adapter (6) with bolts (7). Tighten bolts 20 to 30 lb.in. Check 0.001 inch shim stock will not fit between gage and adapter.

(j)

Rotate gage and record high and low readings. Adjust gage in and out to determine segment taper. Low reading and/or segment taper will determine whether segments are suitable for further use or if replacement is required.

(k) Use an eight to nine inch micrometer to measure the compressor turbine disk and blade assembly at several locations and record the largest diameter (REF. NO. 509, Table 204). (3)

Calculate grinding or replacement of shroud segments as shown in following typical examples: A = True radius as stamped on gage master. B = Radius of bladed disk, 1⁄2 OD, as measured with micrometer. C = Dial indicator reading on shroud segments.

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COOLING HOLE COMPRESSOR TURBINE SHROUD HOUSING

C

C

B

B

SHROUD SEGMENT GAPS MUST BE EQUAL (9PLACES)

B−B C−C

SHROUD SEGMENT GAPS MUST BE EQUAL 0.008 TO 0.016 INCH SHROUD SEGMENT END TO RETAINING RING GAP 1.00 INCH MIN.

PT6A-41 (Post-SB3020) and PT6A-38/-42/-42A

C67241

Compressor Turbine Shroud Segment Location Figure 210

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D = Radius of shroud segments. E = Existing blade tip clearance, before grinding. EXAMPLE 1: A = 4.282 inches B = 4.266 inches C = 0.013 inch clockwise reading on minus side of gage zero datum D = A minus C = 4.282 inches minus 0.013 inch = 4.269 inches E = D minus B = 4.269 inches minus 4.266 inches = 0.003 inch In this example, 0.009 inch must be ground from existing shroud segments to provide minimum blade tip clearance of 0.012 inch. (REF. NO. 318, Table 204). EXAMPLE 2: A = 4.282 inches B = 4.266 inches C = 0.012 inch counterclockwise reading on plus side of gage zero datum D = A plus C = 4.282 inches plus 0.012 inch = 4.294 inches E = D minus B = 4.294 inches minus 4.266 inches = 0.028 inch In this example, existing blade tip clearance exceeds the maximum permissible limit of 0.014 inch (REF. NO. 318, Table 204). EXAMPLE 3: A = 4.282 inches B = 4.266 inches C = 0.0020 inch, clockwise on minus side of gage zero datum. D = A minus C = 4.282 inches minus 0.002 inch = 4.280 inches E = D minus B = 4.280 inches minus 4.266 inches = 0.014 inch In this example, existing blade radial tip clearance is within limits (Ref. Table 204) and therefore no grinding of shroud segments is required except for removal of local high spots. (4)

Grinding (Ref. Fig. 212) (a) Use suitable material (3, 10 and 12, Fig. 212) to blank off cavities around large exit duct (Pre-SB3250) or combustion chamber outer liner (Post-SB3250) and compressor turbine vane ring. (b) Install dresser (14), grinding wheel (1) on grinder (7), and install grinder (7) on adapter with bolts (13). Tighten bolts 20 to 30 lb.in. Check 0.001 inch shim stock will not fit between grinder and adapter. NOTE:

Dressing of wheel may be done before or after installation of grinder on adapter, or during grinding operation.

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3 4

2

1 5 11 7

8

6

10

DIM. A 1

4

9

C41928 Compressor Turbine Shroud Segments - Blade Tip Clearance Check Figure 211

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Key to Figure 211 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11.

Axial Adjuster Tip Contact Point Shroud Segment Bolt Adapter (PWC32209) Bolt (3 off) Gage Master Gage Body (PWC32380) Dial Indicator Rotor Air Seal

(c) Position wheel (1) in line with and slightly overlapping segments, using axial adjustment (6). Allow wheel to touch compressor turbine stator. Back off adjustment (6) one turn and lock using screw (8). (d) Rotate grinder around segments, adjusting radial adjustment (9) until wheel (1) contacts high spots. Back off one turn. (e) Connect grinder air line (4) to shop air of 90 psig with a flow rate of 36 scfm. (f)

Operate grinder. Adjust wheel (1) with radial adjustment (9) until wheel contacts segments, and grind upper half of segment ID to required dimension. NOTE:

When grinding upper half of segments, do not load grinder to compensate for any compressor rotor bearing play. Support grinder when grinding lower segment half to prevent taper grinding.

(g) Loosen radial adjuster until grinding wheel contacts high spot on lower segments. Continue grinding, using complete revolutions, until required dimension is obtained on lower segments. (h) Disconnect air hose (4) and remove grinder from adapter. (i)

Install radius gage and recheck shroud segment diameter. Check segment taper by running contact point across width of segments.

(j)

Remove radius gage and return to gage master. Remove adapter.

(k) Remove all grinding residue from gas generator case with suitable suction cleaner. (l)

Remove all blanking material and repeat step (k).

(m) Remove all masking adhesive residue with solvent (PWC11-027) or (PWC11-031).

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2

3 1 14 13 4 12

7

5

6

8 11

10

9

C41203 Compressor Turbine Shroud Segment Grinding Figure 212

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Key to Figure 212 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. D.

Grinding Wheel (PWC34128) Bolt (Shroud Housing) Blanking Material (Exit Duct) Air Hose Gas Generator Case Axial Vernier Adjust Grinder (PWC37918) Axial Adjustment Lockscrew Radial Vernier Adjust Blanking Material (Stator Assembly) Spacer (PWC30478) Blanking Disk Bolt Diamond Dresser (PWC37917)

Lapping of Hot Section Parts (Ref. Figs. 213, 214, 215 and 216) (1)

Before installing a vane ring, small exit duct, or lockplate, the mating faces should be lapped to a surface finish better than 16 A.A. and surface waviness maximum 0.0008 to obtain 100 percent contact for gas tightness.

(2)

After lapping, each part must be index marked to its mating part.

(3)

Lap face (5, Figs. 213and 214) of small exit duct (4) until a 100 percent lapped finish of the contacting area is achieved.

(4)

Lap face (6) of compressor turbine vane ring (1) until a 100 percent lapped surface is achieved.

(5)

Lap vane ring (2) to previously lapped face (5) of small exit duct, using compound (PWC05-145), (Ref. View A).

(6)

Secure lockplate (2, Fig. 215) and No. 2 bearing cover flange (1) to suitable backup plate with 16 bolts and washers (5). Tighten bolts evenly and progressively, and torque 36 to 40 lb.in.

(7)

Lap face of lockplate (2) until a 100 percent lapped surface is achieved. Disassemble lockplate, No. 2 bearing cover flange and backup ring after lapping.

(8)

Thoroughly clean all lapped surfaces to ensure that all traces of lapping compound are removed. Clean parts using petroleum solvent (PWC11-027) or (PWC11-031)and allow to dry.

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1. COMPRESSOR TURBINE VANE RING 2. VANE RING LUGS 3. LUB CONTACT SURFACE 4. SMALL EXIT DUCT 5. DUCT CONTACT SURFACE 6. LOCKING PLATE MATING SURFACE 7. AIR EXIT LUG

4 2 3 1

5

6

LAP THESE FACES TO OBTAIN 100% SURFACE CONTACT BETWEEN DUCT AND VANE ASSEMBLY LUGS

4

4 LAP THIS FACE TO OBTAIN 100% CONTACT 5 5

A 2 VANE RING LUG 100% CONTACT TO THIS POINT MUST BE OBTAINED

3 6 VIEW

LAP THIS FACE TO OBTAIN 100% SURFACE CONTACT

A

C3443A

PT6A-41 (Pre-SB3020) Compressor Turbine Vane Ring and Small Exit Duct - Lapping Mating Surfaces Figure 213

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Key to Figure 213 1. 2. 3. 4. 5. 6. 7. E.

Compressor Turbine Vane Ring Vane Ring Lug Contact Surface Small Exit Duct Duct Contact Surface Lockplate Mating Surface Cooling Air Exit Ports

Fitting of Hot Section Parts (Ref. Fig. 216 and Table 203) NOTE:

(1)

If new part is to be fitted, no index marks will be found; thus it will not be possible to align index marks as described following. New part should be indexed (rotated) until best fit is obtained, and then marked.

Place shroud housing assembly (1) on bench with slotted flange uppermost and temporarily install compressor turbine vane ring assembly (3) in shroud housing to previously marked indexed position. NOTE:

The term ‘‘loaded side’’ is used to define which side of vane ring lugs are in contact with wall of mating slots, due to action of compressor air. As air flows through stator it tends to turn or ‘‘load’’ stator in a clockwise direction until restricted by slots in mating parts.

(2)

Hold vane ring so that loaded sides of outer lugs (4) are touching side of shroud housing slots, then, using feeler gages, measure clearance at both loaded and unloaded sides of lugs. Clearance at loaded side of each lug should be 0.001 to 0.002 inch. Clearance at unloaded side of each lug should be 0.001 to 0.007 inch. The rotational motion (play) should not exceed 0.004 inch when measured at the outer lugs.

(3)

If lug-to-slot fit is not within limits, rotate vane ring assembly (3) into another position; recheck and repeat if necessary until suitable fit is obtained.

(4)

It is permissible to remove offending part and stone lug(s) and/or slot(s) to obtain required fit. After stoning, lug or slot width must not exceed minimum or maximum dimensions, as applicable (Ref. Table 203).

(5)

When required fit is obtained, remove previous index mark from repositioned part and re-mark for subsequent assembly, using an approved temporary marker (Ref. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts). Remove stator assembly (3) from shroud housing. NOTE:

If clearance(s) at lug-to-slot is/are found to exceed limits (Ref step (2) preceding), or lug or slot widths exceed limits (Ref. Table 203), the offending part(s) must be sent to an approved overhaul facility for repair.

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MAX. 0.075

2

1

3

ACCEPTABLE LAPPING PATTERN 2

6

MIN. 0.005 3

IDEAL LAPPING PATTERN

VIEW C ON LOCKPLATE

LAP THESE FACES TO OBTAIN 100% SURFACE CONTACT BETWEEN DUCT AND VANE RING

POST−SB3105

LAP THESE FACES TO OBTAIN 100% SURFACE CONTACT BETWEEN DUCT AND VANE RING

VIEW B

B

4 5 5

PRE−SB3105 PRE−SB3165

C A

C VIEW A POST−SB3165

6 LAP THIS FACE TO OBTAIN 100% SURFACE CONTACT

C7863B

PT6A-41 (Post-SB3020) and PT6A-38/-40/-42/-42A Compressor Turbine Vane Ring and Small Exit Duct - Lapping Mating Surfaces Figure 214

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Key to Figure 214 1. 2. 3. 4. 5. 6.

Compressor Turbine Vane Ring Vane Ring Lug Contact Surface Small Exit Duct Duct Contact Surface Lockplate Mating Surface

(6)

Place CT vane ring assembly (3) on bench with inner lugs uppermost, and temporarily install No. 2 bearing cover flange (5) on vane ring to previously marked indexed position. Hold No. 2 bearing cover flange (5) so that loaded side of inner lugs (2) are touching side of No. 2 bearing cover flange slots; then, using feeler gages measure clearance at both loaded and unloaded side of lugs. Clearance at loaded side of each lug should be 0.000 to 0.002 inch. Clearance at unloaded side of each lug should be 0.000 to 0.005 inch. There should be no rotational motion.

(7)

If lug-to-slot fit is not within limits, rotate No. 2 bearing cover flange (5) into another position, recheck and, if necessary, repeat until suitable fit is obtained.

(8)

It is permissible to remove offending part and stone lug(s) and/or slot(s) to obtain required fit. After stoning, lug or slot width must not exceed minimum or maximum dimensions, as applicable (Ref. Table 203).

(9)

When required fit is obtained, remove previous index mark from repositioned part and re-mark for subsequent assembly, using an approved temporary marker (Ref. 70-00-00, MAINTENANCE PRACTICES, Marking of Parts). Remove No. 2 bearing cover flange (5) from vane ring assembly (3). NOTE:

If clearances at lug-to-slot are found to exceed limits (Ref. step (6) preceeding), or lug(s) or slot(s) exceed minimum or maximum limits (Ref. Table 203), offending parts must be sent to an approved overhaul facility for rework. TABLE 203, Lug and Slot Widths No.2 Bearing Cover Flange

CT Stator Inner Lug Min. Width

Outer Lug Min. Width

0.249

0.395

C T Shroud Housing

Slot Maximum Width 0.255

0.402

CAUTION: HANDLE SMALL EXIT DUCT WITH CARE. IMPACT WITH HARD OBJECT CAN DAMAGE CERAMIC COATING. (10)

Position small exit duct, flange uppermost, on protective surface on bench. Align index marks and fit shroud housing in position on small exit duct. A tight fit is required (Ref. FIT NO. 250).

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LAP THIS FACE TO OBTAIN 100 PER CENT SURFACE CONTACT

1 5

2

4 3

PT6A-41 (Post-SB3020) and PT6A-38/-40/-42/-42A

C6525

Compressor Turbine Vane Ring Lockplate - Lapping Contact Surface Figure 215

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Key to Figure 215 1. 2. 3. 4. 5. 8.

No. 2 Bearing Cover Flange Lockplate Backup Ring Lapping Ring Bolt and Washer

Fits and Clearances A.

General The following provide the fits and clearances, torques, spring pressures, special assembly, and backlash checks where applicable. The REF. NO. should be used in conjunction with Figure 217.

B.

Dimensional Checks The DIMENSIONS FOR REF. column indicates minimum and maximum manufacturing dimensions of two mating parts. These dimensions are provided for information only. The LIMITS column indicates the desired minimum and maximum fits and clearances between new parts, and also the allowable limit to which these parts may wear before replacement is necessary. The letter T indicates a tight fit; L or no letter, a loose fit. BY SELECTION means parts must be matched by selection to provide a required fit. FIT TO means a fitting operation may be required at assembly to obtain the required fit. An asterisk (*) indicates part(s) should be replaced if any looseness is evident. Unless otherwise stated, all fits are diametrical. Spline fits are calculated from chordal dimensions.

C.

Torque Limits Unless otherwise stated, apply thread lubricant to all parts that are to be torque-loaded. Use engine lubricating oil or equivalent, unless otherwise specified. Where torque limits for castle nuts are provided in the MINIMUM column only, these nuts should be tightened to the designated torque and then further tightened, if necessary, to properly align the locking slots and holes. Where MINIMUM and MAXIMUM values are given, the alignment of the locking slot must be obtained without loosening the nut and without exceeding the maximum limit. If this is not possible, back-off the nut half a turn, then retighten. If alignment cannot be accomplished, select another nut.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

UNLOADED SIDE OF LUGS LOADED SIDE OF LUGS

1

2 3 4

5

C7660 Shroud Housing Assembly Slots and Vane Ring Lugs - Checking Clearance Figure 216

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Key to Figure 216 1. 2. 3. 4. 5.

Shroud Housing Assembly Vane Ring Inner Lugs Vane Ring Assembly Vane Ring Outer Lugs No. 2 Bearing Cover Flange

Torque requirements for interference fit applications, such as studs, may be obtained with or without lubrication, unless otherwise specified. TABLE 204, Fits and Clearances REF. NO. 229

229

250

260

261

261

Dim. for Ref. (inches) Name

Min.

Max.

Flange, No. 2 Brg. Housing Cover

5.259

5.261

Cover, No. 2 Brg. Housing Assembly

5.259

5.261

Post-SB3301 Flange, No. 2 Brg. Housing Cover

5.168

5.170

Cover, No. 2 Brg. Housing Assembly

5.166

5.168

Housing, CT Shroud

10.654

10.656

Exit Duct, Small

10.650

10.652

Lockplate, CT Stator

5.309

5.313

Cover, No. 2 Brg. Housing Assembly

5.298

5.304

CT Disk

3.197

3.201

Cover, No. 2 Brg. Housing Assembly

3.246

3.254

Post-SB3301 CT Disk

3.197

3.201

Cover, No. 2 Brg. Housing Assembly

3.294

Limits (inches) Min.

Max.

Replace

0.002 0.002T

0.000 0.004

3.304

0.002T 0.006T

0.005 0.015

0.0225 0.0285 RADIAL

0.0465 0.0535 RADIAL

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TABLE 204, Fits and Clearances (Cont’d) REF. NO. 263

318

Dim. for Ref. (inches) Name

Min.

Max.

Cover, No. 2 Brg. Housing Assembly

5.302

5.304

Case, Gas Generator Assembly

5.300

5.303

For PT6A-38 and Pre-SB3296 PT6A-41/-42 Engines: Compressor Turbine Blade, Radial Tip Clearance

Limits (inches) Min.

Max.

Replace

0.004T 0.001

0.010 0.012 (New Segment)

0.009 0.014 (Run Segment)

NOTE: 318

Refer to Table 207 for special assembly procedures.

For Post-SB3296 PT6A-41/-42 and PT6A-42A Engines: Compressor Turbine Blade, Radial Tip Clearance

0.018 0.020 (New Segment)

0.017 0.022 (Run Segment)

366

NOTE:

For a limited quantity of Post-SB3296 engines, the Compressor Turbine Radial Tip limits can be 0.013 to 0.015 (new segments) and 0.012 to 0.017 (run segments). Refer to SB3348 for details.

NOTE:

Refer to Table 207 for special assembly instructions.

Post-SB3301 Vane Ring Turbine Baffle, Air Compressor Turbine

0.000 0.010

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TABLE 204, Fits and Clearances (Cont’d) REF. NO. 487

487

488

488

488

489

Dim. for Ref. (inches) Name

Min.

Max.

Post-SB3020 Pre-SB3265 Shroud Segment

0.055

0.059

Shroud Housing

0.060

0.063

Post-SB3265 Shroud Segment

0.058

0.060

Shroud Housing

0.061

0.063

Pre-SB3020 Shroud Segment

9.093

9.101

Shroud Housing

9.098

9.106

Post-SB3020 Pre-SB3265 Shroud Segment

0.064

0.068

Shroud Housing

0.070

0.073

Post-SB3265 Shroud Segment

0.068

0.070

Shroud Housing

0.071

0.073

Vane Ring Assembly

0.123

0.126

Flange, No. 2 Brg Cover

0.126

0.128

Limits (inches) Min.

Max.

0.001 0.008

0.001 0.005

0.003T 0.013

0.002 0.009

0.001 0.005

0.000 0.005

504

For PT6A-38 Engines: CT Disk - Vane Ring

0.140 0.150 Axial Clearance

504

For PT6A-41/-42 (Pre-SB3164) Engines: CT Disk - Vane Ring

0.070 0.080 Axial Clearance

For PT6A-40/-41/-42/42A Engines: CT Disk - Vane Ring

0.050 0.060 Axial Clearance

504

Replace

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TABLE 204, Fits and Clearances (Cont’d) REF. NO.

Dim. for Ref. (inches) Name

509

CT Bladed Disk, (Diameter)

675

Pre-SB3020 Shroud Retaining

Min.

Limits (inches)

Max.

Min.

8.546 8.556

Replace 8.490

0.010 0.015

Ring - Shroud Segments 675

Max.

Post-SB3020, Pre-SB3248 Shroud Retaining Ring

0.004 0.016

Shroud Segments 675

Post-SB3248/PreSB3360 Shroud Retaining Ring

0.005 0.016

Shroud Segments 675

Post-SB3360 Not Applicable

TABLE 205, Torque and Stretch Limits REF. NO. 541

Name

Min.

Max.

Compressor Turbine Stubshaft Center Bolt (1)

For Pre-SB3254 Engines: Torque 600 to 650 lb.in. Loosen to zero. Retorque 420 to 460 lb.in.

(2)

For Post-SB3254 Engines: Torque 600 to 650 lb.in. Loosen to zero. Retorque 500 to 550 lb.in.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 206, Spring Pressures Limits REF. NO.

Name

Min.

Max.

Not Applicable

TABLE 207, Special Assembly Procedures Limits REF. NO. 318

Name

Min.

Max.

Compressor Turbine Radial Tip Clearance (1)

With the CT disk and CT vane removed, measure the CT disk OD (measure at the blade trailing edge) and the CT vane assembly shroud ID. Calculated clearances must be within limits. If not, then grind or replace the shrouds.

(2)

With the CT vane assembly mounted in the gas generator, measure the shroud ID at four places, approximately mid segment position. The ID of the shroud segments should be within 0.003 (new segments) or 0.005 (run segments) F.I.R. If necessary, machine the shrouds to get the correct clearance.

(3)

With the CT disk installed, measure the CT blade tip clearance with wire or tapered feeler gages, at several locations, at the blade trailing edge. Load the disk 180 degrees in the opposite direction of the clearance being checked and correct the results for bearing play. Machine the shroud segments or replace them if necessary to produce clearances within the final build limits.

TABLE 208, Backlash Limits REF. NO.

Name

Min.

Max.

Not Applicable

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

B

366 DETAIL B (POST−SB72−301)

C3928J Fits and Clearances Figure 217

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR TURBINE - DESCRIPTION AND OPERATION 1.

Description and Operation (Ref. 72-50-00, Fig. 1) The compressor turbine installation consists of a two-plane balanced turbine disk with an integral shaft extension, turbine blades, and classified weights. The assembly is an independently balanced unit which can be replaced by another balanced unit without affecting the compressor rotor assembly balance. The turbine drives the compressor rotor assembly in a counterclockwise direction through the shaft extension, which is externally splined to fit into the internally splined compressor stubshaft. A master spline ensures positive location of the turbine assembly to retain original balance. A center bolt and keywasher secure the turbine assembly to the compressor rotor assembly. The blades are inserted in fir tree serrations machined in the disk circumference and retained in position by rivets. Classified trim weights are riveted, as necessary, to the front and rear balancing rims during balancing of the bladed, balanced disk and compressor rotor assembly. The trim weights allow the bladed disk to be replaced in the field.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

COMPRESSOR TURBINE - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire used which unless otherwise specified, shall comply with specification AMS 5687, heat and corrosion resistant steel wire MS9226-03, 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. For alternate products, suppliers, and supplier addresses, refer to 72-00-00, MAINTENANCE PRACTICES.

3.

Item No.

Name

PWC06-004

Compound, Antiseize

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

4.

Tool No.

Name

PWC30331 PWC30335 PWC30336 PWC30403 PWC30458 PWC50057 PWC50060 PWC50064-100

Wrench Spreader Protector Puller Squeezer Drill Kit Oil Injector DELETED

Application

CT Bolt Replaced by PWC50057

Fixtures, Equipment and Supplier Tools Not Applicable

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

5.

Removal/Installation A.

Removal of CT Assembly (1)

Remove power section/power section module (Ref. 72-00-00, SERVICING). NOTE:

(2)

When necessary, check CT blade radial tip clearance (Ref. Inspection/Check) before proceeding.

Using wire or tapered feeler gages, measure the clearance of each blade at the 6 o’clock position and determine the longest blade. Put a mark on the longest blade with marker (PWC05-103). NOTE:

Measure the tip clearance at the blade trailing edge.

(3)

Using wire or tapered feeler gages, measure and record the tip clearances between the longest blade and the center and butt ends of each shroud segment. Load the disk 180 degrees in the opposite direction of the clearance being checked and correct the results for bearing play.

(4)

Check that tip clearances are within acceptable limits (REF. NO. 318, 72-50-01, Fits & Clearances). If the tip clearances are not within limits, length of longest blade must be calculated and one or more shroud segments may require replacement or grinding (Ref. 72-50-01, Approved Repairs).

(5)

Install holding wrench (2, Fig. 201) on flange C (1) of gas generator case. Make sure slots are correctly seated on turbine disk balancing rim lugs (4). Install protector (3). NOTE:

The wrench prevents disk rotation during removal of center bolt and keywasher.

(6)

Insert spreader (6) into centerbore over CT disk center bolt. Uncrimp keywasher locking center bolt. Remove spreader.

(7)

Remove bolt, cupwasher, wrench, and protector.

CAUTION: DO NOT EXCEED 150 LB.FT. TORQUE ON BOLT. (8)

With wrench held firmly in position, break torque (50 to 100 lb.ft.) on stubshaft bolt using standard socket and wrench.

(9)

If Pre-SB3254 bolt is seized (Ref. Fig. 202): (a) Install drill bit (part of kit PWC50057) in suitable hand drill. (b) Install stop on drill bit 4.270 inches from tip. (c) Install bushing into CT bolt hole fingertight. (d) Use oil, and drill bolt slowly until drill stop contacts bushing. Remove debris at regular intervals.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(e) Remove bushing from CT bolt, and clean surrounding area. (f)

Fill oil injector (PWC50060): 1

Turn knob clockwise until plunger bottoms.

2

Place injector tip in penetrating oil (50% kerosene, 50% engine oil is suitable).

3

Turn knob counterclockwise to draw in oil.

(g) Install injector in CT bolt. Make sure packing seals between injector and bolt head. (h) Turn injector knob clockwise fingertight to empty injector and to flood stubshaft cavity. Maintain pressure in cavity by tightening knob at regular intervals for 5 minutes minimum.

(10)

(i)

Remove injector , and loosen bolt.

(j)

If bolt does not move, repeat steps (f) thru (i) until bolt is removed.

If Post-SB3254 bolt is seized: (a) Apply sufficient penetrating oil (50% kerosene, 50% engine oil is suitable) into bolt center hole to flood stubshaft cavity. (b) Rotate CT several times to let oil reach slots in bolt thread, and let soak for 20 minutes minimum. (c) Break torque on bolt (50 to 100 lb. ft.). If bolt does not move, apply sufficient tightening force to move bolt, then loosen. Repeat tightening/loosening until bolt is free and can be removed. NOTE:

If force required to move bolt does not decrease, DO NOT exceed 150 lb. ft. This indicates permanent seizure, and the bolt must be removed by drilling. Remove in two stages. DO NOT exceed minor thread dia. of 0.5538 inch.

CAUTION: CONTINUED OPERATION OF PULLER DURING REMOVAL OF DISK MAY DAMAGE BLADE TRAILING EDGES IF SHROUD HOUSING IS CONTACTED. (11)

Insert puller (PWC30403) into centerbore of turbine disk and release turbine disk snap diameters. Withdraw compressor turbine assembly from gas generator case. NOTE:

A drop of the disk or freedom of puller operation will be observed when the disk snap diameters are released.

CAUTION: HANDLE COMPRESSOR TURBINE ASSEMBLY WITH CARE. (12)

Place compressor turbine assembly on clean bench and remove puller. Install assembly in a suitable container.

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5 4 3

2

1

6

C1241 Removal/Installation of Compressor Turbine Assembly Figure 201

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Key to Figure 201 1. 2. 3. 4. 5. 6. B.

Flange C CT Disk Wrench (PWC30331) Protector (PWC30336) Lugs CT Disk Assembly Keywasher Spreader (PWC30335)

Installation of CT Assembly CAUTION: HANDLE COMPRESSOR TURBINE ASSEMBLY WITH CARE. (1)

Apply light film of compound (PWC06-004) to splines of compressor turbine disk (5, Fig. 201).

(2)

Align master splines and install compressor turbine on compressor front stubshaft.

(3)

Check that new keywasher is dry and free from burrs and other surface damage. Apply light film of compound (PWC06-004) to inside of washer, to shoulder and to threads of CT bolt. Make sure bolt, lubricating axial hole and slots in threads are free of compound.

(4)

Install keywasher and bolt into center of CT disk (5).

(5)

Install holding wrench (2) on flange C (1) of gas generator case. Make sure slots are correctly seated on turbine disk balancing rim lugs (4). Install protector (3). NOTE:

The holding wrench prevents CT disk rotation during installation and tightening of CT bolt.

(6)

Tighten CT bolt (Ref. 72-50-01,Table 205, REF. NO. 541).

(7)

Remove protector and wrench from gas generator case.

(8)

Check CT blade radial tip clearance (Ref. 72-50-01, Fits & Clearances, REF. NO. 318)

(9)

Make sure cooling air gap between CT disk and stator is maintained (Ref. 72-50-01, Table 204, REF. NO. 504).

(10)

Make sure cooling air gap between CT disk and No. 2 bearing housing cover is maintained (Ref. 72-50-01, Table 204, REF. NO. 261).

(11)

Install squeezer (PWC30458) in centerbore of disk, and lock keywasher. Remove squeezer carefully from disk.

(12)

Install power section (Ref. 72-00-00, SERVICING).

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4.270

DRILL STOP

DRILL BIT C T BOLT

BUSHING

OIL INJECTOR PREFORMED PACKING

C T BOLT

C25663 Removal of CT Bolt Figure 202

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

6.

Inspection/Check A.

Compressor Turbine Blade Tip Clearance NOTE:

Turbine blade tip clearance should be measured after installation of the compressor turbine disk and blade assembly and whenever engine performance is unsatisfactory (Ref. to 72-00-00, FAULT ISOLATION).

(1)

Measure and record the blade radial tip clearance (Ref. Removal/Installation).

(2)

The clearance at any one location should not normally exceed 0.021 inch or be less than 0.008 inch. However, if clearance does exceed 0.021 inch at one location only, continue shroud segments in service provided engine performance has been satisfactory.

(3)

If the tip clearances are less than 0.008 inch due to a high spot in a shroud segment, the segment may be ground locally, as required, over a length not exceeding one inch on any one segment. NOTE:

(4) B.

For grinding procedure refer to 72-50-01.

Inspect turbine shroud segments for evidence of metal build-up and cracks (Ref. Fig. 203 and204).

Inspection of CT Blades (Ref. Figs. 205 and 206 and Table 201) (1)

The entire set of compressor turbine blades must be scrapped when a compressor turbine vane ring inspection reveals that vane trailing edge burning has resulted in loss of airfoil area of 0.125 sq.in. or more, on any one vane and burnt area can be seen from the leading edge of vane ring when viewed parallel to longitudinal axis of engine (Ref. 72-50-01).

(2)

Inspect blade airfoil surfaces, particularly concave surface for corrosion and loss of coating using 10 power magnification. Assess stage of deterioration and accept or reject bladed disk: Stage 1 - Initial Coating Deterioration (Sulfidation) Evidenced by slight color change of part of coating area. May be rust colored or dark gray. Coating has deteriorated but is probably still intact. Blades are acceptable for further service. Stage 2 - Initial Corrosion Evidenced by apparent rise of sulfidated coating over surrounding surface, with small, scattered blisters appearing in coating. Corrosion of base material has started. Accept or reject disk, at discretion of operator, based on previous experience. If blades are to remain in service, operator must increase desalination washes and schedule regular borescope inspection of blades every 200 hours.

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HEAVY RUB − WHERE FUSION OF METAL FROM COMPRESOR TURBINE BLADE SQUEALER TIPS HAS OCCURED. GRIND SEGMENT UNTIL FLUSH WITH CONTOUR. INSPECT COMPRESSOR TURBINE BLADES FOR 0.008 IN. MINIMUM SQUEALER TIP HEIGHT.

LIGHT TIP RUB OF THIS NATURE IS ACCEPTABLE

PT6A-38 and PT6A-41 (Pre-SB3075)

C1262B

Metal Buildup on CT Shroud Segments (Typical) Figure 203

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HEAVY RUB − WHERE FUSION OF METAL FROM COMPRESSOR TURBINE BLADE TIPS HAS OCCURED GRIND SEGMENT UNTIL FLUSH WITH CONTOUR

LIGHT TIP RUB OF THIS NATURE IS ACCEPTABLE

PT6A-41 (Post-SB3075) and PT6A-40/-41AG/-42

C6565

Metal Buildup on CT Shroud Segments (Typical) Figure 204

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0.100 TRAILING EDGE

❉

0.100 LEADING EDGE

0.200

LEADING EDGE

A

❉

0.100

PROVIDED ENGINE PERFORMANCE IS SATISFACTORY

FILLET AREA B

TIP RADIUS EROSION LIMITS

BLADES HAVING THINNED OR FEATHERED LEADING EDGES DUE TO EROSION ARE NOT ACCEPTABLE

C3112E

PT6A-38 and PT6A-41 Compressor Turbine Blade Inspection Figure 205

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❉

0.100

PROVIDED ENGINE PERFORMANCE IS SATISFACTORY

❉

0.100

0.200 RADIUS MAX. PERMISSIBLE

A LEADING EDGE

B

LEADING EDGE (REF.)

TRAILING EDGE

0.100

TIP RADIUS EROSION LIMITS

BLADES HAVING FEATHERED LEADING EDGES DUE TO EROSION ARE NOT ACCEPTABLE

C6344B

Pt6A-40/-41AG/-42 Compressor Turbine Blade Inspection Figure 206

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Stage 3 - Advanced Corrosion Evidenced by clusters of ruptured blisters exposing bare material. Craters so formed progressively deepen and crater surfaces darken with glazed appearance. Reject disk for blade replacement at overhaul facility; scrap blades. TABLE 201, Compressor Turbine Blade Inspection Max. Serviceable

Inspection

Max. Repairable

Action

CORROSION (Ref. 72-00-00, INSPECTION)

Not Acceptable.

Not repairable

*

BLADE SHIFT

Protrusion of blade root beyond disk rim must be equal within 0.016 inch on either side of disk

Not repairable

*

CIRCUMFERENTIAL MOVEMENT

Max. 0.030 inch acceptable at blade tip

AXIAL MOVEMENT

None permitted.

Not repairable

*

Nicks, dents and pits

Three 0.003 inch deep per blade.

Not repairable

*

Cracks

Not acceptable

Not repairable

#

Nicks, dents and pits

One 0.005 inch deep per blade.

Not repairable

*

Cracks

Not acceptable

Not repairable

#

Nicks, dents and pits

One 0.020 inch deep per blade.

Not repairable

*

Cracks

Not acceptable

Not repairable

#

Radius 0.200 inch max.

Not repairable

*

AREA A

AREA B (FILLET)

LEADING AND TRAILING EDGES

LEADING EDGE TIP Erosion

* Send bladed disk assembly to an approved overhaul facility. # If any blade is found to be cracked , ship bladed disk assembly to an approved overhaul facility for replacement of complete set of blades. C.

Compressor Turbine Stubshaft Bolt (Post-SB3254) (1)

Inspect bolt lubrication axial hole and two slots in threads to make sure areas are clear of compound and debris.

72-50-02 COMPRESSOR TURBINE - MAINTENANCE PRACTICES

Page 212 Jul 11/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

D.

Inspection of CT Disk (1)

Nicks, scratches and dents in any area of the disk is acceptable to maximum 0.005 inch deep. Damage exceeding limit must be repaired by an approved overhaul facility.

72-50-02 COMPRESSOR TURBINE - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

POWER TURBINE INTERSTAGE - DESCRIPTION AND OPERATION 1.

Description and Operation (Ref. 72-50-00, Fig. 1) The power turbine stator housing consists of a stepped conical casting, machined with open ends to accommodate the power turbine stator and interstage stator assemblies. A flange at the front of the housing is attached to the rear inner flange of the exhaust duct, while a machined inner diameter on the housing rear extension fits over the interstage sealing rings and provides a mechanical joint and seal between the compressor and power turbines. Eight Pre-SB3197 or ten Post-SB3197 equi-spaced thermocouple bosses are provided on the rear of the housing for the temperature sensing system bus-bar and probe assembly. Clips are welded on the outer face of the housing for location and safety wiring of the thermocouple wiring harness. The interstage baffle assembly is between the compressor turbine assembly and the first-stage power turbine, and forms part of the first-stage power turbine stator assembly. The baffle prevents dissipation of turbine gases and consequent transmission of heat to the turbine disk faces. The center section of the baffle incorporates lipped flanges on the front and rear faces. The flanges fit over corresponding rotor seal flanges on the turbine disks to provide control of cooling air flow through the bore of the compressor turbine and a hole in the center of the baffle. Cooling air is allowed to bleed through the seal and flange interface to cool the front and rear faces of the compressor and first-stage power turbine disks respectively; cooling air is then exhausted into the gas stream at the turbine blade roots. The stator assembly consists of an inner and outer ring with forward extension acting as the first-stage power turbine shroud. Integrally cast vanes between the rings direct the compressor turbine discharge gases onto the first-stage power turbine blades at the most efficient angle and velocity. The outer ring is located within the power turbine stator housing by a flange at the rear of the extension and by lugs at the front end that engage with a mating flange and slots. The interstage baffle assembly is secured to a flange in the center of the inner ring by locating lugs and rivets.

72-50-03 POWER TURBINE INTERSTAGE - DESCRIPTION AND OPERATION

Page 1/2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

POWER TURBINE INTERSTAGE - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire used, unless otherwise specified, shall comply with specification AMS5687, heat and corrosion resistant steel wire MS9226-03, 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

PWC05-145 PWC11-027 PWC11-031

Compound, Lapping Silicon Carbide Solvent, Petroleum Cleaner, Engine

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

4.

Tool No.

Name

PWC32111

Puller

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation (Heavy Maintenance only) NOTE:

A.

The classified first-stage power turbine stator vane ring and compressor turbine stator throat areas are matched during initial engine build. When replacing power section module, it is recommended that the power turbine stator assembly be transferred from power section/power section module being removed to power section being installed to maintain optimum engine match.

Removal of Power Turbine Stator (1)

Remove power section (Ref. 72-00-00, SERVICING).

(2)

Remove T5 thermocouple wiring harness (2) from T5 bus-bar and probe assembly (Ref. 77-20-01).

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

72-50-03

POWER TURBINE INTERSTAGE - MAINTENANCE PRACTICES

Page 201 Jun 26/2009

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

5

1 3

4

2

6

7 9

8

C10283B Removal/Installation of Power Turbine Stator Figure 201 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-03

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Page 202 Jun 26/2009

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

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

Exhaust Duct T5 Wiring Harness Power Turbine Stator Assembly Retaining Ring Power Turbine Stator Housing T5 Bus Bar and Probe Assembly Bolt Shanknut Sealing Ring (PT6A-42A and Post-SB3337)

(3)

Remove wire fastening wiring harness sleeves to clips on stator housing. Tie back harness to prevent damage during further disassembly.

(4)

Remove bolts (7) from inner flange on exhaust duct (1).

CAUTION: DO NOT ROTATE STATOR HOUSING DURING REMOVAL. ROTATION MAY DAMAGE T5 PROBES WHICH PASS THROUGH SLOTS IN VANE RING. USE EXTREME CARE TO AVOID DROPPING STATOR ASSEMBLY.

B.

(5)

Carefully withdraw stator housing from power section using puller (PWC32111).

(6)

For PT6A-42A and Post-SB3337: Remove and discard seal ring (9).

(7)

Remove stator assembly (3, Fig. 201) from power section. Withdraw assembly axially to avoid damaging power turbine first-stage turbine blades.

(8)

For PT6A-41 (Post-SB3092) and PT6A-40/-42/-42A Engines: Remove retaining ring (4) from central flange on stator assembly.

Installation of Power Turbine Stator (1)

Prior to assembly: (a) Check for free sliding fit between the 1st stage power turbine vane ring lugs and the power turbine stator housing slots. (b) If required, it is permissible to stone the lugs or the slots to the following dimensions in order to obtain a 0.001 to 0.002 inch clearance where there is interference: 1

Lugs to 0.0294 in. wide minimum

2

Slots to 0.317 in. wide maximum NOTE:

(2)

The clearance can be greater than 0.002 in. at other locations.

Locate power turbine stator assembly (3, Fig. 201) on power section with index mark at 12 o’clock position. Align assembly axially to avoid damaging PT first-stage blades.

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

72-50-03

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

6.

(3)

For PT6A-41 (Post-SB3092) and PT6A-40/-42/-42A Engines: Install retaining ring (4) on central flange of stator (3); make sure dimples on retaining ring provide a snug fit.

(4)

Carefully install power turbine stator housing (5) over interstage stator. Make sure probes fit into slots at rear face of vane ring.

(5)

For PT6A-42A and Post-SB3337: Install new seal ring (9) in exhaust duct.

(6)

With bolt holes at front flange of stator housing (5) and inner flange of exhaust duct (1) aligned, install stator housing on inner flange of exhaust duct with bolts (7) and shanknuts (8). Tighten bolts 36 to 40 lb.in.

(7)

Install thermocouple wiring harness on bus-bar and probe assembly (6) (Ref. 77-20-01).

(8)

Fasten wiring harness sleeves to clips on stator housing with lockwire (Ref. 77-20-01).

(9)

Install power section on gas generator case (Ref. 72-00-00).

Inspection/Check A.

Inspection of Power Turbine Stator Assembly (1)

Examine power turbine stator assembly (Ref. Table 201 and Fig. 202).

(2)

Install power turbine stator assembly carefully over first-stage turbine. Locate flange concentrically with interstage stator assembly and align lugs.

(3)

Apply axial force to hold assembly in firm contact and check sealing Faces A and B (Ref. Fig. 203) all around with 0.001 inch feeler gage. If gage enters more than 90 degrees cumulative, rectify sealing faces by lapping (Ref. Para. 7. B.).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TRAILING EDGE TYPICAL REWORKED VANE

OUTER RING

INNER RING

CRACKS SHOWN ARE TYPICAL FOR LEADING EDGE AND TRAILING EDGE

C1867A Inspection of Power Turbine Stator Assembly Figure 202 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-03

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

F F C C

6

3

5

4

2 1

A

B

2

AXIAL FORCE

3

SECTION

C−C D

E

5

6

COMPRESSOR TURBINE SHROUD HOUSING REF. SECTION

F−F C113682

Power Turbine Section Sealing Surfaces (Typical) Figure 203 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-03

POWER TURBINE INTERSTAGE - MAINTENANCE PRACTICES

Page 206 Jun 26/2009

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 203 1. 2. 3. 4. 5. 6.

Exhaust Duct Power Turbine Interstage Stator Assembly (Ref.) Power Turbine Stator Assembly Retaining Ring Power Turbine Stator Housing Interstage Sealing Ring(s) (Ref.)

TABLE 201, Power Turbine Stator Assembly Inspection Max. Serviceable

Item VANE RING

INTERSTAGE BAFFLE

Action

Cracks up to 0.400 in. long on any number of vanes, leading and/or trailing edges.

*

One crack through entire length, of outer ring, provided crack is not open more than 0.050 in. and sealing faces do not exhibit any distortion.

*

One crack through entire length of inner ring, provided crack is not open more than 0.020 inch.

*

Any number of hairline cracks, inner or outer rings, provided no two converge in such a manner that would allow material to become detached.

*

Erosion or pitting, 0.250 sq.in. by 0.010 in. deep on any airfoil surface, any number of vanes. Stators which have been reworked by vane trailing edge material removal are acceptable.

*

Loss of anti-rotation lugs is not acceptable

*

Examine for correct attachment, integrity.

Replace loose rivets.

* Replace PT stator vane ring with like class. When PT stator assembly is to be replaced a stator assembly of same class as original is recomended. Flow area of replacement must be within ± 0.1 of original. .If class unknown, refer to engine log book for last test cell run matching figures or contact P&WC Customer Support (Ref. INTRODUCTION). Acceptance criteria outlined herein is based on structural integrity considerations and apply only if engine performance /handling was satisfactory prior to HSI. Replace stator assembly if its condition appears to be the cause for loss of performance.

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72-50-03

POWER TURBINE INTERSTAGE - MAINTENANCE PRACTICES

Page 207 Jun 26/2009

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE 201, Power Turbine Stator Assembly Inspection (Cont’d) Max. Serviceable

Item

Action

Stator assemblies considered unacceptable for continued service may be sent to the following facility for possible repair. Pratt & Whitney Canada Corp. 1000 Marie-Victorin Longueuil, Quebec Canada J4G 1A1 Attention: Customer Support 7.

Approved Repairs A.

Replacement of Interstage Baffle Rivets NOTE:

Replace loose rivets. Baffle could be removed and reinstalled if loose rivets are not accessible.

(1)

Remove the 16 rivet heads at the baffle assembly by grinding or drilling, and carefully punch out the rivet stems with a parallel pin punch.

(2)

Remove the sealing plate and the two interstage air seals from the baffle on the vane ring,

(3)

Remove the six rivet heads and carefully press out the rivet stems with a parallel pin punch. Remove the baffle assembly and retaining plates from the vane ring.

(4)

Install the baffle on the vane ring with three retaining plates and six rivets. Maintain the dimensions indicated.

(5)

Locate the two interstage air seals on the baffle, and position the sealing plate relative to the dimension indicated, relative to the vane ring.

(6)

Fasten the baffle assembly on the vane ring with 16 rivets. NOTE:

B.

Use care when riveting to avoid distortion of the sealing plate or the baffle assembly.

Repair of Sealing Surfaces (1)

Lap Face B of power turbine stator assembly (Ref. Fig. 203) on a lapping table until a 100% lapped surface is achieved.

CAUTION: CARE MUST BE TAKEN WHEN APPLYING LAPPING COMPOUND TO FACE OF INTERSTAGE STATOR TO MAKE SURE NONE FALLS INTO ENGINE. (2)

Carefully apply compound (PWC05-145) to Face A of interstage stator. Lap Face A to Face B until a 100% lapped finish of the contacting area is achieved.

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

72-50-03

POWER TURBINE INTERSTAGE - MAINTENANCE PRACTICES

Page 208 Jun 26/2009

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

VANE RING (REF.)

0.020 INCH MAX 0.033 INCH MAX RETAINING PLATES (3)

BAFFLE ASSEMBLY SEALING PLATE

RIVETS 6 REQUIRED

AIR SEALS (PART OF BAFFLE ASSEMBLY)

RIVETS 16 REQUIRED

NO MACHINING REQUIRED AFTER BAFFLE ASSEMBLY REPLACEMENT

C8087A Replacement of Interstage Baffle Rivets Figure 204 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-03

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(3)

Thoroughly clean all lapped surfaces to remove all traces of compound. Clean parts with solvent (PWC11-027) or (PWC11-031) and let air dry.

(4)

Recheck sealing surfaces (Ref. Para. 6.).

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

72-50-03

POWER TURBINE INTERSTAGE - MAINTENANCE PRACTICES

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

POWER TURBINE - DESCRIPTION AND OPERATION 1.

Description and Operation (Ref. 72-50-00, Fig. 1) The power turbine installation consists of first and second-stage disk and blade assemblies which are mounted on the balanced power turbine shaft assembly and retained by a spanner nut and slotted washer. A rotor air seal mounted between the two disk and blade assemblies provides a running face for the interstage air seal. The first and second-stage disk and blade assemblies incorporate 47 and 43 blades respectively. The blades differ from those of the compressor turbine blades in that they are forged with notched and shrouded tips. Each blade is located in a fir tree serration in the circumference of the turbine disk and retained by a rivet. The first and second-stage disk and blade assemblies rotate within shrouds machined in the first and second-stage vane ring assemblies respectively. Each power turbine disk incorporates a flange for disk balancing. The required number of classified weights and rivets is determined during assembly balancing procedures. The power turbine interstage stator installation, comprising second-stage vane ring and interstage seal, is installed between the first and second-stage power turbine disk and blade assemblies. The vane ring consists of an outer ring, with integral vanes, and an inner ring. The interstage seal consists of an abradable element installed in the interstage seal housing and fastened by the seal retaining plate bolted to the housing. The housing is secured to the inner vane ring with the turbine vane ring clamping ring. The rotor air seal mounted between the first and second-stage turbine disks provides the running clearance between the rotating parts and the abradable seal element. Lugs on the outer circumference of the vane ring, immediately forward of the vanes, locate in slots in the bore of the power turbine stator housing. The front extension of the outer ring provides the running clearance for the second-stage power turbine. The front face of the vane ring is located on the rear inner flange of the exhaust duct and retained by bolts passing through power turbine stator housing and exhaust duct (flange D). The power turbine shaft assembly, mounted in the centerbore of the shaft housing, consists of the shaft, turbine coupling, rear rotor air seal, No. 3 bearing inner race and rollers, No. 4 bearing inner race and balls, and the power turbine shaft coupling. The rear rotor air seal is installed on the outer circumference of the turbine coupling rear extension. The centerbore of the rear extension is splined to accommodate the second-stage turbine disk. A machined circumference on the turbine coupling forward of the extension is provided for the No. 3 bearing inner race which is secured by a spacer, keywasher and spanner nut. The split inner races of the No. 4 bearing are located on a machined circumference at the front end of the shaft, while the power turbine shaft coupling is splined onto the shaft forward of the bearing. The bearing and coupling are secured on the shaft by a keywasher and spanner nut. The power turbine shaft housing consists of a fabricated steel cylindrical housing with a mounting flange at the front end. The housing is secured to studs on the rear face of the reduction gearbox rear case. The housing provides a support for the power turbine shaft assembly and the outer races of the No. 3 and No. 4 bearings. A stator air seal, located and secured in the rear centerbore of the housing by a dowel pin and retaining ring, prevents oil leakage from the bearing area into the turbine section.

72-50-04 POWER TURBINE - DESCRIPTION AND OPERATION

Page 1 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A No. 3 bearing heatshield assembly, surrounds the rear end of the housing. The outer races of the No. 3 and No. 4 bearings are bolted to internal flanges in the housing. Two oil transfer tubes are incorporated in the housing; one tube provides pressure oil via four nozzles to the front and rear faces of the No. 3 roller bearing and to the front and rear face of the No. 4 ball bearing. The tube, which contains a strainer element, is coupled to a port in the rear case of the reduction gearbox by a short transfer tube, and is secured and positioned by one of the No. 3 bearing upper retaining bolts. The second tube, in the bottom of the housing, transfers scavenge oil from the vicinity of the air seal and No. 3 bearing to the reduction gearbox via a cored passage in the rear case.

72-50-04 POWER TURBINE - DESCRIPTION AND OPERATION

Page 2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

POWER TURBINE - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire used, unless otherwise specified, shall comply with specification AMS5687, heat and corrosion resistant steel wire MS9226-03, 0.025 inch diameter, and will not be called out 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. Tool No.

Name

PWC31050 PWC31515 PWC32089

Wrench Bar Pusher

PWC32120 PWC32121 PWC32123

Pusher Adapter Puller

PWC32136 PWC32137 PWC32193 PWC32505 PWC32506 PWC32507 PWC34258 PWC34259

Fixture Socket Crimper DELETED DELETED Hydraulic Pump Adapter Socket

PWC50042 PWC50372

Pad Socket

Application

Replaced by PWC50767 and PWC51748 Replaced by PWC50589 Obsolete - replaced by PWC50588

Replaced by PWC71392 Replaced by PWC89837

Obsolete - replaced by PWC50372 Obsolete - replaced by PWC50442

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

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Page 201 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

4.

Tool No.

Name

Application

PWC50442 PWC50588 PWC50589 PWC50767 PWC51748 PWC71392 PWC71410 PWC89837

Socket Puller Adapter Drift DELETED Adapter, Hydraulic Rod Assembly Cylinder, Hydraulic

Alternate to PWC50372 Alternate to PWC32123

Replaced by PWC71410 Replaces PWC32505 Replaces PWC51748 Replaces PWC32506

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation (Heavy Maintenance Only) A.

Removal of Power Turbine (1)

Remove power turbine stator housing and power turbine stator assembly (Ref. 72-50-03, Removal/Installation).

(2)

Uncrimp power turbine retaining nut slotted washer (2, Fig. 201).

(3)

Use socket (1, Fig. 202), wrench (2), bar (3) and adapter (4), and turn handle of wrench counterclockwise, to remove power turbine retaining nut and slotted washer. Discard nut and washer.

(4)

If retaining nut (1) has seized, use the following alternate method: NOTE: 1. Use of oil is recommended during drilling operation. NOTE: 2. Drills are specially prepared for this operation; do not resharpen. (a) Use fixture (PWC32136)to drill two holes in power turbine retaining nut (1) to the depth limited by stop on drill. (b) Use socket (PWC34259 or PWC50372 or PWC50442) (1), wrench (PWC31050) (2), bar (PWC31515) (3) and adapter (PWC34258) (4), remove power turbine retaining nut and slotted washer from shaft. Discard nut and washer.

(5)

Withdraw power turbine first-stage disk (3, Fig. 201) from shaft with puller (PWC32123) (1, Fig. 204) or puller (PWC50588), cylinder (PWC89837), adapter (PWC71392), pump (PWC32507) and pad (PWC50042). Place power turbine disk carefully into a suitable protective container. NOTE:

If both turbine disks withdraw together, separate them on bench using pusher (1, Fig. 203) in conjunction with puller (3) and adapter (2).

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(6)

Remove interstage stator assembly. NOTE:

B.

Do not remove interstage rotor air seal from power turbine second-stage disk.

Installation of Power Turbine (1)

Clean all parts prior to re-assembly (Ref. Cleaning/Painting).

(2)

If both turbine disks were withdrawn together at removal, lightly coat snap diameters of PT second-stage disk (6, Fig. 201) with oil (PWC03-001). Install second-stage disk on power turbine shaft, pushing disk firmly by hand only onto shaft coupling.

(3)

Install interstage stator assembly (4).

(4)

Lightly coat snap diameters of first-stage disk (3) with oil (PWC03-001), install against second-stage disk (6), aligning large lug with corresponding slot. Check ’X’ marks on disk hub and end of shaft are aligned.

(5)

Using pusher (1, Fig. 205), push power turbine disks fully into shaft coupling. Remove pusher.

(6)

Install new slotted washer (2, Fig. 201) on power turbine shaft.

(7)

Lightly coat PT shaft thread, retaining nut thread and washer-to-nut interface with oil (PWC03-001). Install new nut (1), hand tight.

(8)

Using wrench (2, Fig. 202), adapter (4), socket (1) and bar (3), turn handle of wrench clockwise, and tighten nut (1, Fig. 201) 2400 lb.in. Loosen and remove nut. Repeat step (7).

(9)

Tighten nut 300 lb.in., increase force until nut turns 50 degrees ± 2 . DO NOT exceed 3000 lb.in. Record final value. Loosen and remove nut. Repeat step (7).

(10)

Retighten nut to 300 lb.in., then increase force until nut turns 50 degrees ± 2 as previous. DO NOT exceed 3000 lb.in. Record final value.

(11)

If second value exceeds first value, loosen nut and repeat steps (7) thru (10) until final value is LESS THAN, but WITHIN 10 percent of previously recorded value.

(12)

Remove wrench, adapter, bar and socket.

(13)

Crimp keywasher into nut scallops at two locations 180 degrees apart using (PWC32193).

(14)

Install power turbine stator and stator housing (Ref. 72-50-03) and T5 wiring harness (Ref. 77-20-01).

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

72-50-04

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

1 2

3

5

4

6

C13890 Power Turbine and Interstage Stator Figure 201 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-04

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Page 204 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 201 1. 2. 3. 4. 5. 6. 6.

Power Turbine Retaining Nut Slotted Washer Power Turbine First-stage Disk and Blades Power Turbine Interstage (Second-stage) Stator Assembly Interstage Rotor Air Seal Power Turbine Second-stage Disk and Blades

Inspection/Check (Heavy Maintenance Only) NOTE:

A.

The power turbine second-stage disk and blades, and vane ring vanes should be inspected as detailed in the following section only when the first-stage power turbine, first-stage vane ring and power turbine stator housing have been removed (Ref. 72-50-03).

Inspection of Power Turbine Installation (1)

Examine power turbine blades (Ref. Figs. 206, 207 and Table 201).

(2)

Inspect power turbine second-stage vane ring (Ref. 72-50-03, Table 201 and Fig. 202).

(3)

Examine second-stage turbine for condition and signs of damage. Inspection of rear face can be done by viewing through ports in exhaust duct if second-stage turbine is not removed.

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

72-50-04

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Page 205 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

1 REMOVAL

INSTALLATION

3

4

2

C10271 Removal/Installation of Power Turbine Nut Figure 202 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-04

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 202 1. 2. 3. 4.

Socket (PWC32137) for Removal, or (PWC34259 or PWC50372 or PWC50442) for Installation) Power Torque Wrench (PWC31050) Torque Wrench Bar (PWC31515) Adapter (PWC34258) TABLE 201, Power Turbine Blade Inspection

Inspection

Max. Serviceable

Action

BLADE SHIFT

Protrusion of any blade root must be equal within 0.005 in. either side of disk

*

CIRCUMFERENTIAL MOVEMENT

0.030 in. max. at tip

*

AXIAL MOVEMENT

None permitted.

*

Nicks

Three max., 0.015 in. long by 0.005 in. deep max.

*

Dents and pits

Three max., 0.010 in. deep max.

*

Cracks

Not acceptable.

*

One max., 0.020 in. deep max.

*

Nicks, dents and pits

One max., 0.020 in. deep max.

*

Cracks

Not acceptable

*

AREA A:

AREA B: Nicks, dents and pits LEADING AND TRAILING EDGES

* Return power section for overhaul. B.

Inspection of Power Turbine Disk (Ref. Fig. 208) Examine power turbine disk for wear.

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

72-50-04

POWER TURBINE - MAINTENANCE PRACTICES

Page 207 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

2 1 4

5 3

C10225A First and Second-stage Power Turbine Disks Figure 203 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-04

POWER TURBINE - MAINTENANCE PRACTICES

Page 208 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 203 1. 2. 3. 4. 5.

Pusher (PWC32089) or (PWC50767) and (PWC71410) Second-stage Power Turbine Adapter (PWC32121) or (PWC50589) Puller (PWC32123) or (PWC50588) First-stage Power Turbine Disk (Ref.) Second-stage Power Turbine Disk (Ref.)

Light score marks due to rubbing along seal baffle clearance diameter up to 0.003 in. deep are acceptable. The score marks must be 0.100 in. from the fillet radius (Ref. Detail A). If there is evidence that the disk has already been blended due to rubbing with the seal baffle, a minimum thickiness of 0.045 in. is required (Ref. Detail A). Power turbine disks considered unacceptable for continued service may be sent to P&WC for possible repair: Pratt & Whitney Canada Inc. 7007 Rue de la Savanne St-Hubert, Québec Canada J3Y 3X7 Attention: Service Centre Receiving Area 5-1

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

72-50-04

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Page 209 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A

A

1

C10191 Power Turbine Figure 204 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-04

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Page 210 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 204 1.

First-stage Power Turbine Puller (PWC32123) or (PWC50588)

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

72-50-04

POWER TURBINE - MAINTENANCE PRACTICES

Page 211 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

A

A

1

C10192 Installation of Power Turbine Figure 205 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-04

POWER TURBINE - MAINTENANCE PRACTICES

Page 212 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 205 1.

Pusher (PWC32120)

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

72-50-04

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

POWER TURBINE 1. BLADE PLATFORM END 2. TURBINE DISK 1

NOTE: PROTRUSION OF BLADE MAY BE MEASURED FROM EITHER SIDE OF DISK

2

REFER TO TABLE 201

C1868 Power Turbine First-stage Blade Shift Figure 206 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-04

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Page 214 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

0.125 FILLET AREA 0.250

TRAILING EDGE

B

A

0.125

0.125

0.125

LEADING EDGE

B

0.250

FILLET AREA CRITICAL NO DAMAGE PERMITTED

NOTE: 1. RIPPLING OF TRAILING EDGE IS NOT ACCEPTABLE

C748B Power Turbine Second-stage Blade Inspection Figure 207 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-04

POWER TURBINE - MAINTENANCE PRACTICES

Page 215 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

0.045 IN. THICKNESS MINIMUM

A

0.060 0.050 REF.

0.109 0.078 R 0.100 IN. FROM FILLET RADIUS

25 ° ± 0 ° 30’

0.420 0.410 REF. DETAIL

A C100864A

Inspection of Power Turbine Disk Figure 208 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-50-04

POWER TURBINE - MAINTENANCE PRACTICES

Page 216 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

EXHAUST DUCT - DESCRIPTION AND OPERATION 1.

Description and Operation (Ref. Fig. 1) The exhaust duct installation comprises an exhaust duct assembly and a shaped insulation blanket. The exhaust duct assembly consists of a heat-resistant nickel-alloy sheet, truncated cone fabrication with twin opposed exhaust ports and an annular sheet metal inlet. The exhaust port flanges provide the mounting for the airframe-supplied exhaust nozzles. Exhaust gases from the power turbine area enter a bifurcated tube which carries the exhaust gases to the exhaust ports. The front flange of the duct (flange A) provides the support and mounting flange for the reduction gearbox. Two flanges are provided at the rear of the duct; the inner flange (flange D) shank nuts provide the mounting for the power turbine stator housing, while the outer flange (flange C) forms the major dividing flange between the gas generator assembly and the power section/power section module. A sealed tube in the exhaust duct assembly provides a passageway and mounting flange for the T5 lead-out wiring harness. The two piece texturized stainless steel/ceramic fiber laminated insulation blanket is laced together and installed between the bifurcated tubes of the duct and the power turbine shaft housing to minimize transfer of heat from the exhaust gases to the power turbine shaft bearings and rear section of the reduction gearbox.

72-50-05 EXHAUST DUCT - DESCRIPTION AND OPERATION

Page 1 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

PT6A−40/42 ENGINES

SHANK NUT

EXHAUST DUCT INSULATION BLANKET

GAS GENERATOR CASE (REF.) FLANGE

A

FLANGE

C

PT6A−38/41 ENGINES

C7978A Exhaust Duct and Insulation Blanket Figure 1

72-50-05 EXHAUST DUCT - DESCRIPTION AND OPERATION

Page 2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

EXHAUST DUCT - MAINTENANCE PRACTICES 1.

General A.

2.

Maintenance practices for the exhaust duct is restricted to Inspection/Check, Cleaning/Painting, and Approved Repairs.

Consumable Materials Not Applicable

3.

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Cleaning/Painting A.

6.

Cleaning of Exhaust Duct (1)

Remove salt and smog deposits from outer surface of with clean water. Dry with clean, dry compressed air.

(2)

Clean light surface corrosion build-up with with non-metallic brush.

Inspection/Check A.

Inspection of Exhaust Duct NOTE:

For periodic, hot section, or unscheduled inspections such as engine sudden-stoppage (Ref. 72-00-00, INSPECTION) or suspected aircraft heavy landing, examine exhaust duct critically for evidence of the following:

(1)

Examine outer surface condition for buckling, ripples or similar distortion.

(2)

Examine outer surface, particularly in vicinity of flanges A and C and exhaust ports, for cracking in metal skin, welds or flange bolt holes.

(3)

Inspect exhaust port flanges for cracking. Cracks not exceeding 0.500 inch in length and do not progress into the stitch weld or cracks in a tangential direction not exceeding 1.000 inch long are acceptable provided they are stop drilled with a 1/16 (0.0625 inch) drill.

(4)

Check for integrity of internal structure through exhaust ports. NOTE:

(5)

Refer to Aircraft Maintenance Manual for removal/installation of exhaust stubs.

Using suitable lighting or borescope, examine internal structure as far as possible for cracks, looseness and distortion.

72-50-05 EXHAUST DUCT - MAINTENANCE PRACTICES

Page 201 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

7.

(6)

Inspect for sever corrosion or overheating, both internally and externally. Check particularly for corrosion caused by possible rainwater or condensation buildup inside bottom center of duct at flange C if engine has been exposed for prolonged periods without proper preservation.

(7)

Examine Post-SB3270 drain forward of flange C . Drain must be clear and unobstrcted

Approved Repairs A.

Replacement of Shanknut (Heavy Maintenance Only) (1)

Replace unserviceable shanknuts on flange D (Ref. 72-30-04, Approved Repairs). NOTE:

Other repairs that may be deemed necessary are considered beyond the capability of field level maintenance. Send power section/power section module, or complete engine if desired, to an approved overhaul facility.

72-50-05 EXHAUST DUCT - MAINTENANCE PRACTICES

Page 202 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

DATE

LEP

1 2 blank

Dec 05/2008 Dec 05/2008

Contents

1 2

Dec 05/2008 Dec 05/2008

72-60-00 Description and Operation

1 2 3 4 blank

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

72-60-00 Maintenance Practices

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

CHAPTER SECTION

Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008

PAGE 231 blank 232 233 234 235 236 237 238 239 blank 240 241 242 243 244 245 246 247 248 blank

DATE Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008 Dec 05/2008

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

72-60 LEP

Page 1/2 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

ACCESSORY GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION 1.

Description and Operation )

72-60-00 1

ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES

72-60-00

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

202

5.

Removal/Installation

202

A.

Removal of Accessory Drive Seals

202

B.

Installation of Accessory Drive Seals

207

C.

Removal of Dipstick and Filler Cap

209

D.

Removal of Oil Pressure Relief/Regulating Valve

209

E.

Installation of Oil Pressure Relief/Regulating Valve

211

F.

Removal of Accessory Gearbox (Heavy Maintenance Only)

214

G. Removal of External Scavenge Pump

221

H.

Installation of Accessory Gearbox

223

I.

Installation of External Scavenge Oil Pump (With a Vacuum Pump Drive)

227

Installation of External Scavenge Oil Pump (Without a Vacuum Pump Drive)

228

Installation of Dipstick and Filler Cap

228

J. K. 6.

7.

Cleaning

229

A.

Oil Pressure Relief/Regulating Valve

229

B.

Cleaning of Scavenge Oil Pump Inlet Screen

229

Inspection/Check

229

A.

229

Inspection of Accessory Gearshaft Spline (Typical)

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

72-60 CONTENTS

Page 1 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES (Cont’d)

8.

72-60-00

B.

Checking of AGB Coupling Shaft Axial Position

233

C.

Inspection of Dipstick/Gage and Filler Cap

235

D.

Inspection of Oil Pressure Relief/Regulating Valve

236

E.

Inspection of Compressor Rear Hub Coupling

236

F.

Inspection of Scavenge Pump Inlet Screen

236

Approved Repairs

238

A.

Replacement of Dipstick

238

B.

Replacement of Oil Pump Drive Seal

238

C. D. E.

Replacement of Starter-generator Gearshaft Carbon Seal

238

Replacement of Starter-generator Gearshaft Centrifugal Breather

241

Repair of Corrosion - Accessory Gearbox Housing

243

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

72-60 CONTENTS

Page 2 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

ACCESSORY GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION 1.

Description and Operation (Ref. Fig. 1) The accessory gearbox assembly, located at the rear of the engine, consists of two alloy castings, bolted together at their outer flanges and installed on flange G of the compressor air inlet case. The accessory gearbox, located at the rear of the engine, consists of two magnesium alloy castings, bolted together at their outer flanges and secured to studs on flange G of the compressor inlet case (Ref. 72-20-00). The front casting, provided with preformed packings at the front and rear mating faces, forms an oil tight diaphragm between the oil tank compartment in the compressor inlet case and the accessory gearing. The diaphragm also provides the support for the oil pump and pressure relief/regulating valve assembly, which is secured to the front face by four bolts, and the accessory drive gear front bearings and seals. The centerbore of the diaphragm is sealed from the oil tank by the inlet case center tube (Ref. 72-20-00). The diaphragm is secured to the gearbox rear casting by four countersunk head screws and self-locking nuts located at the 4th, 8th, 14th and 18th positions in clockwise rotation, assuming the 1st to be at the 12 o’clock position. The rear casing forms the gearbox housing and provides support bosses for the accessory drive gear rear bearings and seals. A roller bearing secured to a boss at the center provides the rear support for the input gearshaft. The input gearshaft incorporates an internal spline at its front end for mating with the compressor rear hub coupling external spline; positive engagement is obtained by a ball-lock in the spline coupling arrangement. The engine oil supply system is pressurized by a main pressure pump mounted internally in the oil tank. The pressure is regulated by a plunger-type pressure relief/regulating valve located and secured to a boss at the top of the oil pump housing. This valve is adjusted during engine assembly to the required oil pressure by inserting spacers under the spring. Under normal conditions, this setting will require no further adjustment. All oil in excess of regulated pressure is returned directly into the oil tank. The internal scavenge oil pump, consisting of front and rear elements, is mounted at the bottom of the gearbox compartment and driven by the number 3 drive. Each element consists of twin gears operating in a ported housing; the front element scavenges the number 2 bearing area and dumps the oil into the gearbox sump, the rear element scavenges the gearbox sump and returns the oil directly to the oil tank through the oil-to-fuel heater and thermostatic bypass/check valve (if fitted) when oil temperature is less than 72 °C (160 °F), or to the oil tank through the oil-to-fuel heater, thermostatic bypass/check valve and airframe-mounted oil cooler when oil temperature is more than 72 °C (160 °F). The external scavenge oil pump, consisting of front and rear elements, is secured to an external pad on the gearbox housing and driven by the number 4 drive. The pump is similar to the internal pump; however, the housings of each element incorporate large input elbows which accommodate their respective external scavenge tubes. The front element scavenges the number 3 and 4 bearing area and dumps the oil into the gearbox sump, while the rear element scavenges the reduction gearbox and directs the oil through an airframe-mounted cooler and then to tank.

72-60-00 ACCESSORY GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION

Page 1 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

All accessory drives are supported on identical roller bearings. With the exception of the front bearing of the starter-generator gearshaft, which has a carbon face seal, all drives are fitted with garter-type oil seals. An oil tray is incorporated in the lower section of the gearbox adjacent to the scavenge pump drive gears (drives 3 and 4), to minimize oil foaming during engine operation. A centrifugal oil separator, installed on the starter- front end of the gearshaft and within the cored breather air passage precludes oil leakage through the bearing assembly. Mounting pads, complete with studs, are incorporated on the external face of the gearbox housing for the fuel control unit/fuel pump, airframe-supplied starter generator and Ng tachometer-generator. Two additional pads are incorporated on the left side of the housing, plus a third on the rear face of the external scavenge pump, and these are available for additional airframe-supplied equipment. An access plug, located below the starter-generator pad, provides access for a puller tool which must be used to disengage the ball-locked input gearshaft and compressor rear hub coupling shaft during disassembly. A combined dipstick (gage) and filler cap assembly is installed at the 11 o’clock position on the accessory gearbox housing. The assembly is secured to a removable housing by a quick-release and locking arrangement. The housing projects forward and downward through the accessory gearbox and diaphragm and into the oil tank to form a seal between the tank and gearbox. The dipstick is calibrated in U.S. quarts and indicates the quantity required to fill the tank to maximum oil level.

72-60-00 ACCESSORY GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

FLANGE

G

ACCESSORY GEARBOX HOUSING ACCESSORY GEARBOX DIAPHRAGM

ROLLER BEARINGS (TYPICAL)

COMPRESSOR INLET CASE (REF.)

STARTER−GENERATOR GEARSHAFT

CARBON FACE SEAL OIL TANK CENTER TUBE

CENTRIFUGAL IMPELLER STARTER−GENERATOR SEAL CAVITY DRAIN

BALL LOCK

CENTER BOLT OIL PUMP DRIVEGEAR

FLEXIBLE INPUT COUPLING SHAFT

INTERNAL SCAVENGE PUMP (2 ELEMENT) PRESSURE OIL TRANSFER TUBE OIL SEAL (TYPICAL)

OIL PUMP GEAR OIL PUMP HOUSING

SEAL CARRIER (TYPICAL)

OIL PUMP INLET SCREEN NO. 2 BEARING SCAVENGE OIL TRANSFER TUBE

NO. 2 BEARING SCAVENGE OIL TRANSFER TUBE AND BYPASS VALVE

C53B Accessory Gearbox Assembly - Cross-section Figure 1

72-60-00 ACCESSORY GEARBOX ASSEMBLY - DESCRIPTION AND OPERATION

Page 3/4 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

ACCESSORY GEARBOX ASSEMBLY - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire unless otherwise specified shall comply with specification AMS5687, 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 PWC04-001 PWC05-037 PWC05-061 PWC05-101 PWC11-014 PWC11-027 PWC11-031 PWC13-001

Oil, Engine Lubricating Grease, Synthetic Enamel, Epoxy Cloth, Abrasive Coated Crocus Cloth, Abrasive Alcohol, Isopropyl Solvent, Petroleum Cleaner, Engine Primer, Epoxy

Special Tools The special tools listed below are used in the following procedures. Tool No.

Name

PWC30046-52 PWC30046-54 PWC30046-57 PWC30051-01 PWC30051-02 PWC30052 PWC30075 PWC30128-04 PWC30274 PWC30373 PWC30415 PWC30499-50

Puller Puller Puller Base Drift Puller Drift Puller Base Pusher/Puller Compressor Gage

Application

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

72-60-00

ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES

Page 201 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

4.

Tool No.

Name

Application

PWC30675 PWC30854 PWC32140

Drift Adapter Puller

PWC32174 PWC32175 PWC32275 PWC32396-400 PWC32486 PWC34060 PWC34061 PWC34062 PWC34161 PWC37088-001 PWC37088-002 PWC37088-003 PWC42034

Base Ring Plate Jackscrew Socket Fixture Gage Puller Gage Drive Seal Drift Drive Seal Drift Drive Seal Drift Jackscrew

PWC50502 PWC50726-100 PWC70838 PWC70869

Compressor Puller Puller Drift

Obsolete - replaced by PWC50726-100

Alternate to PWC42034

Obsolete - replaced by PWC32396-400 Alternate to PWC32140

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation A.

Removal of Accessory Drive Seals (Ref. Fig. 201 and 202) (1)

Remove the retaining ring (9, Fig. 201) from the fuel control unit mounting pad.

(2)

Remove the oil seal carriers (10, 13 and 19), and the seal retainer (16) with the applicable pullers, as follows:

(3)

Carrier/Retainer (Ref. Fig. 201)

Location

Puller

10 13 16 19

Fuel Pump Tacho-Generator Vacuum Pump Hi- and Lo-speed Optional Gearshafts

(PWC30046-52) (PWC30046-57) (PWC30046-52) (PWC30046-52)

Remove and discard the seals (12, 15, 18 and 21), and the preformed packings (11, 14, 17 and 20).

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

72-60-00

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Page 202 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

THIS PAGE INTENTIONALLY LEFT BLANK

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ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES

Page 203 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

35

33

31

45 32 POST−SB3420

37 42

36

OR

33

47

49

43

34 35 46

48

PRE−SB3420

22

36

8

23

7

6

5

24

11

12

10

9 26

27

25 2

1

38 39

21

4

20 19

3

28

41

29

18

30 17

15

14

16 43

13

40

44

42

C11616H Accessory Gearbox Externals Figure 201 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-60-00

ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES

Page 204 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27.

Cap Drain Adapter Plug (Pre-SB3274) Preformed Packing Retaining Ring Oil Seal Carrier (Pre-SB3420) Preformed Packing (Pre-SB3420) Seal (Pre-SB3420) Retaining Ring Oil Seal Carrier Preformed Packing Seal Oil Seal Carrier Preformed Packing Seal Oil Seal Retainer Preformed Packing Seal Oil Seal Carrier Preformed Packing Seal Bolt Flanged Cover Preformed Packing Bolt Oil Temperature Bulb Adapter (PT6A-38, -41 and Pre-SB3288 -42 Engines) Preformed Packing

28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38.

39. 40. 41. 42. 43. 44. 45. 46. 47. 48. 49.

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

Drain Plug Preformed Packing Cap Oil Filler Cap and Gage Assembly (Post-SB3166/Pre-SB3378) Preformed Packing Retaining Ring Filler Tube (Pre-SB3378) Preformed Packing Preformed Packing Oil Filler Cap and Dipstick Assembly (Pre-SB3166) Oil Temperature Bulb and Pressure Sensing Tee (PT6A-41, Post-SB3288 -42 and -42A Engines) Bolt Oil Jet Nozzle (Post-SB3274) Preformed Packing (Post-SB3274) Oil Filler Tube (Post-SB3378/Pre-SB3433) Oil Filler Cap and Gage Assembly (Post-SB3378) Oil Nozzle (Post-SB3317) Oil Filler Tube (Post-SB3433) Plastic Ball (Post-SB3433) Retaining Ring (Post-SB3433) Lip Seal (Post-SB3420) Preformed Packing (Post-SB3420)

72-60-00

ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES

Page 205 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

NOTE: DETAIL

A

RETAINING RINGS AT FCU AND STARTER−GENERATOR GEARSHAFT NOT SHOWN

C502B Removal of Oil Seal and Oil Seal Retainer (Typical) Figure 202 P&WC Proprietary Information. Subject to the restrictions on the title page.

72-60-00

ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES

Page 206 Dec 05/2008

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(4)

For Pre-SB3420 engines, remove the starter-generator oil seal carrier (6) as follows; (a) Remove the retaining ring (5) from the starter-generator mounting pad. Remove the seal carrier (6) from the starter-generator mounting pad with the puller (PWC30046-54). (b) Remove and discard the seal (8) and the preformed packing (7).

(5)

For Post-SB3420 engines, remove the starter-generator lip seal (48) as follows; (a) Remove the retaining ring (5) from the starter-generator mounting pad. Remove the lip seal (48) from the starter-generator mounting pad with the puller (PWC70838). (b) Remove and discard the lip seal (48) and the preformed packing (49).

B.

Installation of Accessory Drive Seals (Ref. Fig. 201 and 203) (1)

Heat the oil seal carriers (10, Fig. 201), (13) and (19) to 141°C (285°F) in an oven.

(2)

Moist the oil seals (12), (15) and (21) with engine oil (PWC03-001).

(3)

Remove the oil seal carriers from the oven.

(4)

Install each oil seal in their oil seal carrier with the drift (PWC37088-001), (PWC37088-002) or (PWC37088-003). NOTE:

Retainer (16), preformed packing (17) and seal (18) will be installed after installation of external scavenge pump.

(5)

Moist the preformed packings (11), (14) and (20) with engine oil (PWC03-001). Assemble each preformed packing on the outside diameter of each oil seal carrier.

(6)

Put the oil seal carriers in their boss (Ref. Fig. 203). Carefully install each oil seal carrier into their boss with the drift (PWC30075).

(7)

For Pre-SB3420 engines, install the starter-generator oil seal carrier (6, Fig. 201) as follows; (a) Heat the oil seal carrier (6) to 141°C (285°F) in an oven. (b) Moist the oil seal (8) with engine oil (PWC03-001). (c) Remove the oil seal carrier (6) from the oven. (d) Install the oil seal (8) in the oil seal carrier (6) with the drift (PWC37088-001) or (PWC37088-002) or (PWC37088-003). (e) Moist the preformed packing (7) with engine oil (PWC03-001). Assemble the preformed packing on the outside diameter of oil seal carrier (6).

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FWD

SEAL CARRIER

SEAL

DRIFT

C3848 Installation of Gearshaft Oil Seal - Typical Figure 203 P&WC Proprietary Information. Subject to the restrictions on the title page.

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(f) (8)

Carefully install the oil seal carrier (6) in its boss with the drift (PWC30075) (Ref. Fig. 203).

For Post-SB3420 engines, install the starter-generator lip seal (50, Fig. 201) as follows; NOTE:

The lip seal (50) is supplied with a mandrel for installation. Do not remove the mandrel from the lip seal before installation.

(a) Moist the preformed packing (51) with engine oil (PWC03-001). (b) Install the preformed packing (51) on the lip seal (50). (c) Align the mandrel of the lip seal, against the shaft in the boss of the gearbox housing. (d) Push the lip seal (50) into the shaft with the drift (PWC70869). (e) Discard the mandrel. (9)

C.

D.

Secure the starter-generator carrier assembly (Pre-SB3420) or the lip seal assembly (Post-SB3420) with the retaining ring (5), and the fuel control drive carrier assembly with the retaining ring (9).

(10)

Check for oil leakage (Ref. Chapter 71-00-00, ADJUSTMENT/TEST).

(11)

Check for oil leakage after 5 to 10 hours of operation (Ref. Chapter 71-00-00, ADJUSTMENT/TEST, Post-Shutdown Check).

Removal of Dipstick and Filler Cap (Ref. Fig. 204) (1)

Unlock and remove the oil filler cap and gage assembly (1 or 2) from the oil filler tube (9, 12 or 13). Remove the preformed packing (7).

(2)

Disengage the retaining ring (8) that attaches the oil filler tube (9, 12 or 13) to the accessory gearbox housing (11). Remove the oil filler tube (9, 12 or 13) from the accessory gearbox housing (11). Remove and discard the preformed packings (10). If the retaining ring (8) is unserviceable, remove it from the oil filler tube (9, 12 or 13).

(3)

For Post-SB3433 Engines: Remove the retaining ring (15) and the plastic ball (14) from the oil filler tube (13).

Removal of Oil Pressure Relief/Regulating Valve (Ref. Fig. 205) (1)

Remove oil filter element and housing (Ref. 79-20-02).

(2)

Insert compressor (PWC30415), as applicable, through oil filter housing port to collapse retaining ring (1) securing relief/regulating valve in internal bore of relief/regulating valve housing (Ref. Fig. 205).

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4 10 12

13

3

8

8

16 2

5

10

4

IMPERIAL QUARTS 0.833

MAX. COLD

7

LITERS

1

15

0.95

2

14

1.90

3

6

2.85

5 US QUARTS 4

6

MAX. HOT

1

3.80

8 9

1.66

10 2.49

11

3.32

4.15

4.75

DETAIL OF DIPSTICK ASSEMBLY (TYPICAL)

C11353C Removal/Installation of Filler Cap and Dipstick Figure 204 P&WC Proprietary Information. Subject to the restrictions on the title page.

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TEMPORARY REVISION NO. 72-21 (PT6A-38, PT6A-41, PT6A-42, PT6A-42A) INSERT Temporary Revision 72-21 facing page 211, Chapter 72-60-00 ACCESSORY GEARBOX ASSEMBLY - MAINTENANCE PRACTICES PURPOSE:

E.

The purpose of this temporary revision is to add a caution for recurrence of low oil pressure after adjustment during previous maintenance in PT6A-42 engines in the installation procedure of oil pressure relief/regulating valve.

Installation of Oil Pressure Relief/Regulating Valve (Ref. Fig. 205) (1)

Install preformed packings (10 and 11) (Pre-SB3106) onto sleeve (8). Slide relief valve piston (7) into sleeve (8), followed by guide (6), spacer(s) (5), spring (4), and spring seat (3). Secure spring seat in sleeve (8) with retaining ring (2). (a) A maximum of five class 41 spacers (5) may be used to make sure desired oil pressure (Ref. 71-00-00, Adjustment/Test). Lapping of the valve is not recommended.

CAUTION:

(2)

FOR PT6A-42A ENGINES: IF THE OIL PRESSURE IS ADJUSTED DURING PREVIOUS MAINTENANCE OR TROUBLESHOOTING AND LOW OIL PRESSURE OCCURS AGAIN, REFER 79-20-02, MAINTENANCE PRACTICES.

Slide relief valve piston (7) (Post-SB3106/Pre-SB3153) into sleeve (8), followed by preformed packing (9) and guide (6), spacer(s) (5), spring (4), and spring seat (3). Attach spring seat (3) in sleeve (8) with retaining ring (2). (a) On some configurations (Post-SB3106), the pressure relief valve is to be fitted in lieu of items 6, 7 and 9; assemble accordingly. (b) A maximum of nine (Post-SB3106/Pre-SB3153) class 31 and/or class 35 and/or class 41 spacers may be used and mixed as necessary, to make sure necessary oil pressure (Ref. 71-00-00, Adjustment/Test).

(3)

Assemble regulating valve (Post-SB3153): (a) Slide piston (12) over piston seat (13) and insert seat into sleeve (8); check for free movement in both directions. (b) Insert spring (4) into sleeve (8) until seated on flange of piston (12). (c) Install spacers (5) (same number as recorded during disassembly), on spigot of spring seat (3) and insert spring seat into sleeve (8). NOTE:

A maximum of nine spacers (Post-SB3153) may be used to establish desired oil pressure (Ref. Adjustment/ Test).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TR 72-21

(d) Apply pressure on spring seat to compress spring, and secure with retaining ring (2). (e)

Install preformed packings (10 and 11) on sleeve (8).

(4)

Fit retaining ring (1) into exterior groove on sleeve (8).

(5)

Install oil relief valve compressor or puller into threaded spring seat (3).

CAUTION:

WHEN INSTALLING COMPRESSOR (PULLER) ON VALVE, ALIGN GAPIN RETAINING RING MIDWAY BETWEEN ANY TWO COMPRESSOR FINGERS. FAILURE TO DO SO WILL MAKE SUBSEQUENT VALVE REMOVAL DIFFICULT.

(6)

Insert relief/regulating valve, mounted on valve compressor (Ref. Fig. 205), through filter housing port into relief/ regulating valve housing; ensure full insertion.

(7)

Slide compressor body outward to release retaining ring (1). Pull shaft of compressor outward until retaining ring snaps into place. Unscrew compressor shaft from spring seat (3) and remove compressor.

(8)

Install filter housing and filter element (Ref. 79-20-04).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 204 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. (3)

Screw shaft of compressor into spring seat (3) to compress retaining ring (1). When compressor shaft bottoms, pull on shaft to extract relief/regulating valve cartridge from housing.

(4)

Remove retaining ring (2) (Pre-SB3106), and preformed packings (10 and 11) from sleeve (8). Extract spring seat (3), spring (4), spacer(s) (5), guide (6), and relief valve piston (7) from sleeve.

(5)

Remove retaining ring (2) (Post-SB3106/Pre-SB3153) and preformed packings (10 and 11) from sleeve (8). Extract spring seat (3), spring (4), spacer(s) (5), guide (6), preformed packing (9), and relief valve piston (7) from sleeve (8). NOTE:

(6)

On some configurations (Post-SB3106, the pressure relief valve is fitted in lieu of items 6, 7 and 9; disassemble accordingly.

Remove retaining ring (2) (Post-SB3153), preformed packings (10 and 11) from sleeve (8). Extract spring seat (3), spacer(s) (5), spring (4), piston (12) and piston seat (13) from bore of sleeve. NOTE:

E.

Oil Filler Cap and Gage Assembly (Post-SB3166) Oil Filler Cap and Gage Assembly (Post-SB3378) Washer (Pre-SB3431) Oil Filler Cap Spindle Locknut Dipstick Preformed Packing Retaining Ring Oil Filler Tube Assembly (Pre-SB3378) Preformed Packing Accessory Gearbox Housing Oil Filler Tube Assembly (Post-SB3378/Pre-SB3433) Oil Filler Tube Assembly (Post-SB3433) Plastic Ball (Post-SB3433) Retaining Ring (Post-SB3433) Keywasher (Post-SB3431)

Record number of spacers (5) removed.

Installation of Oil Pressure Relief/Regulating Valve (Ref. Fig. 205) (1)

Install preformed packings (10 and 11) (Pre-SB3106) onto sleeve (8). Slide relief valve piston (7) into sleeve (8), followed by guide (6), spacer(s) (5), spring (4), and spring seat (3). Secure spring seat in sleeve (8) with retaining ring (2). (a) A maximum of five class 41 spacers (5) may be used to establish desired oil pressure (Ref. 71-00-00, Adjustment/Test). Lapping of the valve is not recommended.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

RELIEF/REGULATING VALVE HOUSING

11 COMPRESSOR (TYPICAL)

8 10

7 11

11

6

8

8

5 10

10

4

9

12 POST−SB3153

PRE−SB3106

7

13

3

6

2

5

4

14

5

1

4 3 2

3

1

2

POST−SB3106

1

C3925D Removal/Installation of Oil Pressure Relief/Regulating Valve Figure 205 P&WC Proprietary Information. Subject to the restrictions on the title page.

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 205 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14.

(2)

Retaining Ring Retaining Ring Spring Seat Spring Spacers (5 max, Pre-SB3106) (9 max, Post-SB3106/3153) Guide Relief Valve Piston Sleeve Preformed Packing (Post-SB3106) Preformed Packing (Post-SB3066) Preformed Packing (Post-SB3066) Regulating Valve Piston (Post-SB3153) Piston Seat (Post-SB3153) Pressure Relief Valve (alternative to callouts 6, 7 and 9, Post-SB3106)

Slide relief valve piston (7) (Post-SB3106/Pre-SB3153) into sleeve (8), followed by preformed packing (9) and guide (6), spacer(s) (5), spring (4), and spring seat (3). Secure spring seat in sleeve (8) with retaining ring (2). (a) On some configurations (Post-SB3106), the pressure relief valve is to be fitted in lieu of items 6, 7 and 9; assemble accordingly. (b)

(3)

A maximum of nine (Post-SB3106/Pre-SB3153) class 31 and/or class 35 and/or class 41 spacers may be used and mixed as necessary to establish desired oil pressure (Ref. 71-00-00, Adjustment/ Test).

Assemble regulating valve (Post-SB3153): (a) Slide piston (12) over piston seat (13) and insert seat into sleeve (8); check for free movement in both directions. (b) Insert spring (4) into sleeve (8) until seated on flange of piston (12). (c) Install spacers (5) (same number as recorded during disassembly), on spigot of spring seat (3) and insert spring seat into sleeve (8). NOTE:

A maximum of nine spacers (Post-SB3153) may be used to establish desired oil pressure (Ref. Adjustment/ Test).

(d) Apply pressure on spring seat to compress spring, and secure with retaining ring (2). (e) (4)

Install preformed packings (10 and 11) on sleeve (8).

Fit retaining ring (1) into exterior groove on sleeve (8).

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(5)

Install oil relief valve compressor or puller into threaded spring seat (3).

CAUTION:

F.

WHEN INSTALLING COMPRESSOR (PULLER) ON VALVE, ALIGN GAPIN RETAINING RING MIDWAY BETWEEN ANY TWO COMPRESSOR FINGERS. FAILURE TO DO SO WILL MAKE SUBSEQUENT VALVE REMOVAL DIFFICULT.

(6)

Insert relief/regulating valve, mounted on valve compressor (Ref. Fig. 205), through filter housing port into relief/ regulating valve housing; ensure full insertion.

(7)

Slide compressor body outward to release retaining ring (1). Pull shaft of compressor outward until retaining ring snaps into place. Unscrew compressor shaft from spring seat (3) and remove compressor.

(8)

Install filter housing and filter element (Ref. 79-20-04).

Removal of Accessory Gearbox (Heavy Maintenance Only) (Ref. Figs. 206 and 207) NOTE:

Depending on airframe type and installation clearances, the ability to remove accessory gearbox as a complete entity, without removal of engine from airframe, would override the ‘‘Heavy Maintenance Only’’ statement. Primary reasons for gearbox removal are for replacement of centrifugal breather carbon seal or center oil tube preformed packing.

(1)

Drain oil (Ref. 72-00-00, SERVICING).

(2)

If engine is installed in airframe and access permits, disconnect the following and remove as necessary (Ref. Aircraft Maintenance Manual). (a) Connection to heated pneumatic tube electrical receptacle at flange G. (b) Connection to overboard breather line. (c) Connections to oil pressure and temperature sensors, and Ng tachometer-generator. (d) Connection to starter-generator seal cavity drain. (e) Connections to oil-to-fuel heater, and spill valve and seepage drains at FCU and fuel pump. (f)

Connections to fuel flowmeter transmitter and/or fuel temperature sensing transmitter if applicable.

(g) Mechanical linkage connections to FCU and reversing linkage. (h) Starter-generator and such accessories as may be installed on optional power takeoff mount pads. (i) (3)

Connections to airframe oil cooler.

Remove oil-to-fuel heater (Ref. 73-10-01) and oil tube between thermostatic bypass and check valve and scavenge oil tee (Ref. 79-20-01).

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THIS PAGE INTENTIONALLY LEFT BLANK

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20

3

2 1

5

4

34

11

33

7

32

8

A

5 6

22

ALTERNATE CONFIGURATIONS 9

21

10

19 17 18 17

11

PRE−SB3277/PT6A−42A

25

26

27

25

24

23

1 21

16 12

14

13

31

30

29

28

15 VIEW A (ENLARGED)

POST−SB3277

C3702G Removal/Installation of Accessory Gearbox Assembly Figure 206 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 206 1. 2. 3. 4. 5. 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.

Coupling Shaft Transfer Tube Preformed Packing Rear Lifting Bracket Self-locking Nut Preformed Packings Access Plug (Pre-SB3274) Drain Adapter Plug Preformed Packing Drain Plug Accessory Gearbox Housing Compressor Rear Hub Coupling Preformed Packing Center Tube Preformed Packing Lockball (Pre-SB3277/PT6A-42A) Preformed Packing Transfer Tube Compressor Inlet Case Washer Accessory Gearbox Diaphragm Spacers Coupling Shaft Spacer (Post-SB3259/Pre-SB3277/PT6A42A) Retaining Ring (Pre-SB3277/PT6A-42A) Washers (Pre-SB3277/PT6A-42A) Expander Spring (Pre-SB3277/PT6A-42A ) Key, Ball Thrust Spring (Pre-SB3277/PT6A-42A) Spring Lock Insert (Post-SB3277/Post-SB3317) Expander Spring (Post-SB3277/Post-SB3317) Lockpin (Post-SB3277/Post-SB3317) Sleeve (Post-SB3277/Post-SB3317) Oi Nozzle (Post-SB3274) Preformed Packing (Post-SB3274) Oil Jet Nozzle Assembly (Post-SB3317)

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14

14 15

15 13

13

3

3

12

12 11

11

16 10

9 4

PRE−SB3121

10

3

16

9

POST−SB3121 SECTION

8

A−A

10 2 7 4 5

6 10 2 9 1

9

PRE−SB3286 5

1 POST−SB3286

C7866C Removal/Installation of Accessory Gearbox Diaphragm Figure 207 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 207 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. (4)

Accessory Gearbox Housing Center Flanged Transfer Tube Starter-generator Gearshaft and Centrifugal Impeller Transfer Tube and Preformed Packing Transfer Tube and Preformed Packing No. 2 Scavenge Tube and Relief Valve Housing Locating Dowels Accessory Gearbox Diaphragm Bolts and Tabwashers (Typical) Flanged Roller Bearing (Typical) Preformed Packing Seal Carrier Carbon Seal and Carrier Preformed Packing Preformed Packing Retaining Ring

Remove FCU and fuel pump as a complete assembly (Ref. 73-20-00). NOTE:

It is not necessary to separate FCU from fuel pump.

(5)

Disconnect rear lifting bracket (3, Fig. 206, propeller reversing linkage at flange G and electrical connector bracket (Ref. 76-10-00).

(6)

Disconnect and remove air line at rear of coupling adapter or P3 air filter housing, as applicable (Ref. 73-10-07).

(7)

Remove propeller governor Py air tube and electrical cable at rear of center mount ring (Ref. 73-10-08).

(8)

Remove fuel tubes between FCU and rear mount ring (Ref. 73-10-03), including fuel flowmeter transmitter, if fitted.

(9)

Disconnect loop clamps fastening ignition cables to No. 2 bearing scavenge oil tube (Ref. 74-20-00).

(10)

Remove No. 2 bearing scavenge oil tube (Ref. 79-20-01) and remove short oil transfer tube (28) from accessory gearbox diaphragm using puller (PWC30128-04).

(11)

Remove oil filler cap and gage assembly, and oil filler tube from accessory gearbox housing (Ref. Approved Repairs).

(12)

Remove oil filter and oil filter housing from compressor inlet case (Ref. 79-20-02).

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(13)

Remove self-locking nuts (4), spacers (22), washers (20) and rear lifting bracket (3) from accessory gearbox assembly at flange G. NOTE:

Accessory gearbox diaphragm is fastened to accessory gearbox housing by four countersunk screws and self-locking nuts. Assuming nut at 12 o’clock position to be No. 1, these nuts are 4th, 8th, 14th and 18th in clockwise rotation and must not be removed at this stage.

(14)

Remove starter-generator seal cavity drain plug (8) from accessory gearbox housing.

(15)

Remove parts from center boxx in rear face of accessory gearbox: (a) For Pre-SB3274 Engines: Remove access plug (6). Remove and discard preformed packing (5). (b) For Post-SB3274 Engines: Remove oil jet nozzle (32). Remove and discard preformed packings (5 and 33). (c) For Post-SB3317 Engines: Remove oil jet nozzle assembly (34). Remove and discard preformed packings (5 and 33).

(16)

For Pre-SB3277/PT6A-42A Engines: Determine location of lockball (16) at compressor rear hub coupling (12) by viewing through hole in center boss. Rotate compressor until notch in washer at rear hub is at 3 o’clock position. This will position lockball at 12 o’clock position on splined end of rear hub coupling.

(17)

For Post-SB3277 Engines: Insert fixture (PWC34060) into coupling shaft (1), and engage tangs of fixture with slots in spring lock insert (28), insert puller (PWC34062) into fixture, and screw into spring lock insert. Remove insert, puller and fixture.

(18)

Put puller/pusher (PWC30373), through center boss in rear face of accessory gearbox and screw into coupling shaft (1). Turn the knurled body into center boss. do not rotate puller/pusher T-handle once tool is fastened. Pull on T-handle until lockball (16, Pre-SB3277/PT6A-42A) or lockpin (30, Post-SB3277) is fully disengaged. Tighten puller/pusher nut to remove any slackness along coupling shaft with your hands. NOTE:

(19)

Use of puller/pusher is to make sure coupling shaft does not slide out of AGB during handling.

Install four jackscrews (PWC42034) or (PWC32396-400) in relevant locations on flange G and carefully separate accessory gearbox assembly from studs on compressor inlet case. Remove and discard preformed packing (2) from diaphragm/inlet case flange. Remove oil tank center tube (14) with puller (PWC32140) or (PWC50726-100). Remove and discard preformed packings (13 and 15). NOTE:

If lockball (16, Pre-SB3277/PT6A-42A) drops out of locking arrangement during removal of AGB, retrieve it from the No. 1 bearing housing area or oil scavenge passage in compressor inlet case.

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(20)

For Pre-SB3277/PT6A-42A Engines: Remove lockball (16), retaining ring (24), washer (25), key (27), and expander spring (26) from inside compressor rear hub coupling (12). Remove lockball (16) from hole on top of rear hub coupling. Discard expander spring and lockball. Check compressor rear hub lockball hole for elongation (Ref. Inspection/Check).

(21)

For Post-SB3277 Engines:Lift tang on expander spring (29) from hole in sleeve (31), remove and discard expander spring. If lockpin (30) drops from locking arrangement, remove and retain. NOTE: 1. If lockpin (30) has dropped out during removal ofexpander spring, retrieve and retain for re-assembly. NOTE: 2. Three short oil transfer tubes installed in thecompressor inlet case at the 4 o’clock, 7 o’clock and 11 o’clock positions should not be removed.

(22)

Support accessory gearbox assembly on suitable wooden blocks with diaphragm down (Ref. Fig. 207).

(23)

Provide support under coupling shaft, then unscrew puller/pusher. Remove four self-locking nuts, washers and screws fastening housing to diaphragm. Lift housing from diaphragm; use a soft-faced hammer to separate flanges, if necessary. Remove and discard preformed packing from mating flange.

(24)

Remove transfer tube (2) with puller (PWC30128-04)and tubes (4) and (5) remove and discard preformed packings from tubes. Remove preformed packing(s), as applicable from No. 2 bearing scavenge tube and relief valve housing assembly (6).

G. Removal of External Scavenge Pump (Ref. Fig. 208) (1)

Remove nuts (10), washers (9) and bolts (23 and 6), fastening pump rear housing (11) and spacer (8) to front housing (24). Withdraw pump assembly from front housing.

(2)

Straighten tabs of keywashers (21) and remove nuts (20) with socket (PWC32486). Remove nuts (5) and washers (4). Remove front housing (24) from mounting pad studs.

(3)

Remove oil deflector (1) and shaft (2).

(4)

Remove and discard preformed packings (3 and 22).

(5)

Withdraw front spur gears (19).

(6)

For engines with a vacuum pump drive: Remove two half collars (15) from shaft (13).

(7)

For engines without a vacuum pump drive: Remove four half collars (15 and 26) from shafts (25 and 27) respectively.

(8)

Withdraw shafts (13) or (25 and 27), as applicable.

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11 10

9 7

2

3

4

5

VACUUM PUMP DRIVE

8

6

1 13 12 15

14

16

20

19

18

17

21 23

22 8

24 25

15

NO VACUUM PUMP DRIVE 27

26

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Key to Figure 208 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27.

(9)

Remove spacer (8) and discard preformed packings (18). NOTE:

H.

Oil Deflector Coupling (Vacuum Pump Drive Installed) Preformed Packing Plain Washer Self-locking Nut Bolt Dowel (2 req’d) Spacer Plain Washer Self-locking Nut Scavenge Pump Housing (Rear) Bolt Drive Shaft (Vacuum Pump Drive Installed) Adapter Assembly Scavenge Oil Rear Half-collars Preformed Packing Spur Gear (Rear) Preformed Packing Spur Gear (Front) Plain Nut (Pre/Post-SB3358) Keywasher (Pre/Post-SB3358) Preformed Packing Bolt Scavenge Pump Housing (Front) Coupling Shaft (No Vacuum Pump Drive Installed) Half-collars (No Vacuum Pump Drive Installed) Scavenge Pump Drive Shaft (No Vacuum Pump Drive Installed)

Two locating dowels (7) fitted in spacer (8) are an interference fit, and should not be removed.

(10)

Withdraw rear spur gears (17).

(11)

Remove bolts (12) and adapter assembly (14). Remove and discard preformed packing (16).

Installation of Accessory Gearbox (Ref. Figs. 206 and 207) (1)

Install new lubricated preformed packings on transfer tubes (2, 4 and 5, Fig. 207) and insert into respective bosses on accessory gearbox housing (1).

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(2)

Install new lubricated preformed packing(s), as applicable, on No. 2 bearing scavenge tube and relief valve housing assembly (6). Make sure serviceable spacer (23, Post-SB3259/Pre-SB3277/PT6A-42A, Fig. 206), if fitted, is fully inserted in coupling shaft.

(3)

For Pre-SB3277/PT6A-42A Engines: Install in compressor hub coupling (12), one washer (25) slot up, new expander spring (26) opening down, key (27) with lip forward over spring to engage washer. Position second washer (25) to engage key and install retaining ring (24).

(4)

For Post-SB3277 Engines: Install sleeve (31) into rear hub coupling (12), make sure that the slot in sleeve aligns with hole in coupling. Position lock pin (30) into slot and install new expander spring (29) to hold lock pin. Make sure tang on expander spring is located in opposite sleeve slot.

(5)

Install new lubricated preformed packing on rear flange of accessory gearbox diaphragm (8, Fig. 207), and position housing (1) over diaphragm. Lead-in chamfer on gearshafts permits easy entry into respective bearings and oil seals. NOTE:

Make sure flanged transfer tube (2) is properly installed in center boss of housing, with flat aligned with center bearing flange before assembling onto diaphragm.

CAUTION: FOR POST-SB3420 ENGINES, IF THE AGB HOUSING IS SEPARATED FROM THE DIAPHRAGM WITHOUT REMOVING THE LIP SEAL ON THE STARTER-GENERATOR MOUNTING PAD, THE LIP SEAL MUST BE REMOVED AND DISCARDED BEFORE INSTALLING THE HOUSING ON THE DIAPHRAGM. IT IS NOT POSSIBLE TO RE-MATE THE AGB WITH THE LIP SEAL INSTALLED. FOR INSTALLATION OF NEW LIP SEAL, REFER PARA. B.. (6)

Seat housing (1) on diaphragm (8). Make sure proper engagement of locating dowels (7) without forcing.

(7)

Install countersunk screws, washers and self-locking nuts at 4th, 8th, 14th and 18th positions from top center in clockwise direction. Tighten nuts 32 to 36 lb.in.

(8)

Install pusher/puller (PWC30373) through center boss of housing to engage thread of coupling shaft. Screw body into housing to prevent shaft falling out through center tube. NOTE:

Check IPC for correct coupling shaft configuration.

(9)

Check that Post-SB3259 spacer (23, Fig. 206) is fully seated in coupling shaft (1).

(10)

Install new lubricated preformed packing (2) on front flange of diaphragm (21) and install oil tank center tube (14) with new lubricated preformed packings (13 and 15) into boss at centerbore of diaphragm.

(11)

For Pre-SB3277/PT6A-42A Engines: Slowly rotate compressor rotor in engine, until hole in splined end of rear hub coupling (12) is at 12 o’clock position. Coat new lockball (16) with grease (PWC04-001) and install in hole.

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(12)

Loosen nut on puller/pusher sufficiently to allow full forward travel of pusher for engagement of coupling shaft (13) with lockball (16, Pre-SB3277/PT6A-42A) or lockpin (30 Post-SB3277), as applicable.

(13)

Position accessory gearbox assembly on studs of compressor inlet case (19). Align coupling shaft (1) with compressor rear hub coupling (12). NOTE:

Make sure oil tank center tube mates with corresponding boss in inlet case, and that

(14)

Check that lockball (16, Pre-SB3277/PT6A-42A) or lockpin (30, Post-SB3277) is seated in hub coupling (12). Apply hand pressure only to puller/pusher to engage lockball. Remove puller/pusher.

(15)

For Post-SB3277/3317 Engines: Install locking fixture (PWC34060) over insert puller (PWC34062) and thread into lock spring insert (28). Insert through coupling shaft. Engage insert into hub coupling and remove fixture and puller.

(16)

Do coupling shaft engagement check (Ref. Inspection/Check).

(17)

Install parts in the accessory gearbox housing: (a) For Pre-SB3274 Engines: Lubricate and install preformed packing (5) on access plug (6). Torque plug 150 to 160 lb.in. (b) For Post-SB3274 Engines: Lubricate and install preformed packings (5 and 33) on oil nozzle plug (32). Torque oil nozzle plug 150 to 160 lb.in. NOTE:

Check oil passages are free of debris and oil jet nozzle is not blocked.

(c) For Post-SB3317 Engines: Lubricate and install preformed packings (5 and 33) on oil jet nozzle assembly (34). Torque oil jet nozzle assembly 150 to 160 lb.in. (18)

Install rear lifting bracket (3) on studs at 12 o’clock position and secure with single self-locking nut (4, Fig. 206). Install single washers (20) over short studs and spacers (22) over long studs, at flange G and secure with self-locking nuts. Torque nuts 32 to 36 lb.in.

(19)

Apply light coat of sealing compound on tapered threads of drain adapter (7) and install adapter in boss at base of starter-generator mount pad. Torque adapter 30 to 40 lb.in.

CAUTION: DO NOT OVER-TIGHTEN ADAPTER. OVERTIGHTENING MAY STRIP THREADS ON AGB HOUSING. (20)

Install starter-generator seal cavity drain adapter (7) and plug (8) on drain adapter boss at bottom of mounting pad. Torque adapter and plug 30 to 40 lb.in. Lockwire adapter (7), plug (8) and access plug (6) to gearbox housing.

(21)

Install oil filter and oil filter housing (Ref. 79-20-02).

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CAUTION: WHEN FILLER CAP AND GAGE ASSEMBLY IS INSTALLED AND LOCKED, NO MOVEMENT IS ALLOWED. (22)

Install oil filler cap and gage assembly in accessory gearbox housing (Ref. Approved Repairs).

(23)

Install new lubricated preformed packings (17) on short oil transfer tube (18), install in compressor inlet case and connect No. 2 bearing scavenge oil tube to boss on case (Ref. 79-20-01).

(24)

Fasten ignition cable loop clamps to similar loop clamps on No. 2 bearing scavenge oil tube with bolt and self-locking nut (Ref. 74-20-00). Tighten nuts 36 to 40 lb.in.

(25)

Connect rear section of power turbine governor Py pneumatic line to rear of bulkhead coupling at center fireseal mount ring (Ref. 73-10-08).

(26)

Connect rear section of compressor discharge pressure pneumatic line to coupling adapter or P3 air filter housing, as applicable (Ref. 73-10-07), and connect leads to electrical receptacle on Flange G bracket.

(27)

Locate rear section of reversing linkage mechanism (Ref. 76-10-00) on studs at rear of accessory gearbox housing. Install electrical connector and bracket assembly over lower lug of reversing lever bracket and stud below bracket. Install brackets and three self-locking nuts and single spacer (22). Torque nuts 32 to 36 lb.in.

(28)

Install fuel control unit and fuel pump as complete assembly on pump mount pad (Ref. 73-20-00).

(29)

Install oil-to-fuel heater and fuel temperature transmitter, if fitted, (Ref. 73-10-01) and oil tube between thermostatic bypass and check valve and scavenge oil tee (Ref. 79-20-01).

(30)

Connect fuel tubes between FCU and rear mount ring, including fuel flowmeter transmitter, if fitted (Ref. 73-10-03).

(31)

Install new lubricated preformed packing on accessory gearbox drain plug (10) and install in boss at 6 o’clock position on gearbox assembly. Tighten plug 215 to 240 lb.in., and lockwire.

(32)

Fill oil tank (Ref. 72-00-00, SERVICING).

(33)

Pressure test pneumatic system (Ref. 73-10-08).

(34)

Install and connect the following as necessary (Ref. Aircraft Maintenance Manual) : (a) Connections to airframe oil cooler. (b) Starter-generator and accessories on optional power takeoff mount pads. (c) Mechanical linkage to FCU and propeller reversing linkage cambox. (d) Electrical connections to fuel flowmeter and fuel temperature sensing transmitters if applicable.

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(e) Connections to fuel input at oil-to-fuel heater and spill valve and seepage drains at FCU and fuel pump. (f)

Connections to starter-generator seal cavity drain.

(g) Connections to oil pressure and temperature sensors, and Ng tachometer. (h) Connection to overboard breather line.

(35) I.

(i)

Connection to heated pneumatic tube electrical receptacle at flange G.

(j)

Connection to remote-mounted oil-to-fuel heater.

Do engine test (Ref. 71-00-00, ADJUSTMENT/TEST).

Installation of External Scavenge Oil Pump (With a Vacuum Pump Drive) (Ref. Fig. 208) (1)

Install oil deflector (1) in cavity of No. 4 mounting pad on gearbox housing.

(2)

Install preformed packing (3) on spigot of pump front housing (24).

(3)

Install preformed packings (22) in two lower holes (countersunk) in mounting flange of pump front housing (24).

(4)

Install bolts (6) and one bolt (23) in pump front housing (24) flange.

(5)

Position front housing (24) on No. 4 mount pad studs, and secure with washers (4), self-locking nuts (5), keywashers (21) and nuts (20). Torque self-locking nuts 75 to 85 lb.in. Torque plain nuts 32 to 36 lb.in. with socket (PWC32486). Lock keywashers (21).

(6)

Install two spur gears (17) in pump rear housing (11). Rotate gear and check for correct meshing.

(7)

Install preformed packings (18) on spacer (8). With dowels (7) in spacer aligned with pump rear housing (11), press firmly together.

(8)

Insert vacuum pump drive shaft (13) through rear housing (11) into upper spur gear (17), with front splines of drive shaft protruding through spacer.

(9)

Install two half-collars (15) in groove of drive shaft (13). Locate upper spur gear (19) on drive shaft and half-collars, and check for correct engagement.

(10)

Install lower spur gear (19) in lower hole of spacer (8). Check for correct engagement and meshing of gears.

(11)

Install assembled pump rear housing assembly to pump front housing (24) (already mounted on gearbox housing) and check scavenge pump drive shaft (13) engages coupling (2).

(12)

Secure pump rear housing to pump front housing with four washers (9) and nuts (10) to previously installed bolts (6 and 23). Torque nuts 75 to 85 lb.in.

(13)

Install preformed packing (16) on adapter (14), and secure to rear housing (11) with bolts (12). Torque bolts 36 to 40 lb.in. and lockwire.

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J.

Installation of External Scavenge Oil Pump (Without a Vacuum Pump Drive) (Ref. Fig. 208) (1)

Install oil deflector (1) in cavity of No. 4 mounting pad on gearbox housing.

CAUTION: ON EXTERNAL SCAVENGE PUMPS WITHOUT VACUUM PUMP DRIVE, COUPLING (2) IS NOT USED.

K.

(2)

Install preformed packing (3) on spigot of pump front housing (24).

(3)

Install preformed packing (22) in two lower holes (countersunk) in pump front housing (24).

(4)

Install bolts (6) and bolt (23) in pump front housing (24) flange.

(5)

Position front housing (24) on No. 4 mount pad studs, and secure with washers (4), nuts (5), keywashers (21) and nuts (20). Torque nuts 75 to 85 lb.in., plain nuts 24 to 36 lb.in. and lock keywashers.

(6)

Install two spur gears (17) in pump rear housing (11). Rotate gear and check for correct meshing.

(7)

Install preformed packings (18) on spacer (8). With dowels (7) in spacer aligned with pump rear housing (11), press firmly together.

(8)

Install two half-collars (15) on coupling shaft (25). Assemble upper spur gear (19) on coupling shaft, and over half-collars.

(9)

Insert coupling shaft (25) into engagement with upper spur gear (17). Check for correct engagement.

(10)

Install two half-collars (26) on drive shaft (27). Assemble lower spur gear (19) on drive shaft and over half-collars. Insert drive shaft into engagement with lower spur gear (17).

(11)

On both installations, check for correct engagement and meshing of all spur gears.

(12)

Install assembled pump rear housing assembly to pump front housing (24) (already mounted on gearbox housing) and check that pump drive coupling shaft (25) engages scavenge pump drive gearshaft.

(13)

Secure pump rear housing to pump front housing with washer (9) and nuts (10) to previously installed bolts (6 and 23). Torque nuts 75 to 85 lb.in.

(14)

Install preformed packing (16) on adapter (14), and secure to pump rear housing (11) with bolts (12). Torque bolts 36 to 40 lb.in. and lockwire.

Installation of Dipstick and Filler Cap (Ref. Fig. 204) (1)

For Post-SB3433 Engines: Install the plastic ball (14) and the retaining ring (15) in the oil filler tube (13).

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(2)

Install the retaining ring (8) and the new lubricated preformed packings (10) on the oil filler tube (9, 12 or 13).

(3)

Insert the oil filler tube (9, 12 or 13) into the accessory gearbox housing (11) aligning the notch in the flange of the tube with the dowel pin on the boss of the housing. Attach the oil filler tube (9, 12 or 13) with the retaining ring (8).

(4)

Install the new lubricated preformed packing (7) on the oil filler cap and gage assembly (1 or 2) and insert into the oil filler tube (9, 12 or 13). With the oil filler cap correctly positioned and locked, no movement is allowed. (a) If movement occurs, remove the cap and gage assembly (1 or 2) and tighten the self-locking nut which fastens the gage to the filler cap, 8 to 11 lb.in. Check the force required to depress/lift the lock tab (Ref. Inspection/Check).

6.

Cleaning A.

B.

Oil Pressure Relief/Regulating Valve (1)

Clean all parts of pressure relief/regulating valve with solvent (PWC11-027) or (PWC11-031).

(2)

Dry parts with clean, dry compressed air.

Cleaning of Scavenge Oil Pump Inlet Screen (Ref. Fig. 209) (1)

If carbon is present on the screen mesh, loosen with a suitable small plastic scraper or similar nonmetallic scraper. Do not deform the screen mesh.

(2)

Flush any carbon residue from the AGB as follows: (a) Remove the oil filler cap (Ref. Removal/Installation). (b) Remove the retaining ring and the oil filler tube (Ref. Removal/Installation) (c) Place a suitable container under the AGB drain, and pour approximately 34 fluid ounces (one liter) of new engine oil (PWC03-001) heated to 122°F (50°C), into the AGB filler tube opening. Make sure oil does not enter oil tank. (d) Let oil drain. Examine inlet screen and surrounding area to make sure carbon residue is removed. If not, repeat flushing procedure above.

7.

(3)

Install oil filler tube (Ref. Removal/Installation).

(4)

Refill oil tank (Ref. Chapter 72-00-00, SERVICING)

Inspection/Check A.

Inspection of Accessory Gearshaft Spline (Typical) (Ref. Fig. 210) NOTE:

Gearshaft should be checked for spline wear at associated component removal/installation.

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OIL FILLER CAP AND CAGE ASSEMBLY

A

A DRAIN PLUG OR MAGNETIC CHIP DETECTOR

B

PUMP INLET SCREEN

PUMP INLET SCREEN

SECTION A−A (DRAIN PLUG REMOVED)

VIEW B (TYPICAL VIEW ON DRAIN BOSS)

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THIS PAGE INTENTIONALLY LEFT BLANK

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3

1

A 2

5

ALLOW GAGE TO SUPPORT ITSELF

3

DIM.

4

1

A 4 DETAIL

A

C1539B Accessory Gearshaft Inspection Figure 210 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 210 1. 2. 3. 4. 5.

B.

Gearshaft Spline Wear Gage (PWC30499-50) Gearshaft Splines Gage Clamp Screw Ball and Screw Assemblies Mount Pad (Typical)

(1)

Release clamp screw (3) of gage (1) and adjust screw assemblies (4) to obtain a 0.660 inch (Dim. A) over ball ends. Tighten clamp screws and recheck dimension.

(2)

Tilt gage (1, PWC30499-50), outer end uppermost, and insert into shaft centerbore until ball ends are approximately midway along vertically opposite splines.

(3)

Gradually release gage, allowing it to support itself in shaft. If gage is self supporting, gearshaft is considered serviceable. If gage extension falls below horizontal, gearshaft must be replaced (Ref. Approved Repairs).

Checking of AGB Coupling Shaft Axial Position (Ref. Fig. 211) (1)

For Pre-SB3259 Engines: (a) Install coupling gage (PWC34061), with gage plunger (4, Fig. 211) fully forward in gage pilot(s). Make sure Face A of gage plunger (4) and legs of gage pilot contact end of compressor hub coupling (1). NOTE:

Check end of plunger (4). It must be below gage pilot. If it is not, it indicates coupling shaft spacer (6) is installed. Proceed to Post-SB3259 and engines following.

(b) Slide gage sleeve (3) forward until Face B contacts rear of coupling shaft (2). (c) Check that Face C of gage sleeve (3) is located within STEP of gage pilot (5), indicating proper engagement of small lockball and coupling shaft (2). (d) If Face C of gage sleeve is outside of STEP, the coupling shaft must be repositioned, and check must then be repeated. (e) Remove coupling gage from coupling shaft (2). (2)

For Post-SB3259/Pre-SB3277/PT6A-42A Engines: (a) Install coupling gage (PWC34061)in coupling shaft (2, Fig. 211) with gage plunger (4) fully forward in gage pilot (5). Make sure Face A of gage plunger is seated on coupling shaft spacer (6) and legs of gage pilot pass through scallops in coupling spacer, which may require rotation of coupling gage , to contact compressor rear hub coupling (1). NOTE:

Check end of plunger (4). It must be below gage pilot. If it is not, it indicates coupling shaft spacer (6) is not installed.

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1

2 A B STEP

3 4

5

C

PRE−SB3259

1

2

A

B STEP

3 C

4

5

6

POST−SB3259/ PRE−SB3277/PT6A−42A 2

1

A B STEP

3 7

C 4

POST−SB3277/ PRE−SB3317

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Key to Figure 211 1. 2. 3. 4. 5. 6. 7.

Compressor Rear Hub Coupling Coupling Shaft Gage Sleeve Gage Plunger Gage Pilot (Pre-SB3277/PT6A-42A) Spacer (Post-SB3259/Pre-SB3277/PT6A-42A) Springlock Insert (Post-SB3277)

(b) Slide gage sleeve (3) forward until Face B of sleeve contacts rear of coupling shaft (2). (c) Check that Face C of gage sleeve (3) is located within STEP of gage pilot (5), indicating proper engagement of small lockball and coupling shaft. (d) If Face C of gage sleeve is outside of STEP, the coupling shaft must be repositioned, and check must then be repeated (Ref. preceding step). (e) Remove coupling gage from coupling shaft (2). (f) (3)

Install access plug or oil nozzle as applicable.

For Post-SB3277/Pre-SB3317/PT6A-42A Engines: (a) Install coupling gage (PWC34161) in coupling shaft and make sure Face A of gage plunger (4) contacts end of spring lock insert (7). (b) Slide gage sleeve (3) forward until Face B of sleeve contacts end of coupling shaft. (c) Check Face C of gage sleeve, if located within step of gage plunger indicates proper engagement of lock pin and coupling shaft. Remove coupling gage from shaft. If Face C is outside step, coupling shaft must be repositioned and preceding steps (a) and (b) must be repeated.

(4)

C.

Install new preformed packing (5, Fig. 204, Pre-SB3274) or packings (5, Post-SB3274) on access plug (6). Screw plug into position in center of accessory gearbox housing (11), torque 150 to 160 lb.in. and lockwire.

Inspection of Dipstick/Gage and Filler Cap (1)

Examine filler cap and dipstick assembly or filler cap and gage assembly, and oil filler tube for corrosion and signs of damage.

(2)

Check spring-loaded locking feature of cap for serviceability. If force required to depress/lift handle is outside limit 8 to 11 lbs, remove cap and tighten/loosen self-locking nut to meet required limits.

(3)

Check dipstick blade for security and visible damage.

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(4) D.

E.

F.

Make sure there is no movement of the filler cap and gage assembly when installed and locked in position (Ref. Installation).

Inspection of Oil Pressure Relief/Regulating Valve (1)

Examine all parts of oil pressure relief/regulating valve for pitting, nicks, scoring and deformation. Replace parts as necessary.

(2)

Check operation of valve during next engine run (Ref.71-00-00, TESTING).

Inspection of Compressor Rear Hub Coupling (Ref. Fig. 212) (1)

Remove AGB (Ref. Removal /Installation).

(2)

Measure and record distance from rear of hole, including elongation, to rear face of coupling shaft, Dim. A (Ref. Fig. 212).

(3)

Rear hub is acceptable provided that Dim. A is not less than 0.180 inch.

(4)

If Dim. A is less than 0.180 inch, send gas generator or engine to an approved overhaul facility for hub coupling replacement.

Inspection of Scavenge Pump Inlet Screen (1)

Remove oil drain plug located on the AGB housing (Ref. Chap. 72-00-00, SERVICING). NOTE:

For engine equipped with an AGB chip detector, remove the chip detector.

(2)

Collect drained oil in a clean container and check for any debris (Ref. Chap. 79-20-02, MAINTENANCE PRACTICES).

(3)

Use a mirror and suitable light source (or borescope) and inspect the scavenge oil pump inlet screen for carbon or debris (Ref. Chap. 79-20-02, MAINTENANCE PRACTICES). NOTE:

Any foreign material found blocking the screen or contained in the oil should be identified. Look especially for paint flakes approximately 1/8 inch to 1/2 inch in diameter (Ref. Chap. 79-20-02, MAINTENANCE PRACTICES).

(4)

If carbon or debris is present, clean the inlet screen (Ref. Cleaning/Painting, Fig. 209).

(5)

Install the drain plug on the AGB housing (Ref. Chapter 72-00-00, SERVICING). NOTE:

(6)

For engine equipped with an AGB chip detector, install the chip detector.

Replenish the drained oil (if not contaminated by foreign material) in oil tank (Ref. Chapter 72-00-00, SERVICING).

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8.

Approved Repairs A.

Replacement of Dipstick (Ref. Fig. 204) (1)

Remove locknut (5) and Pre-SB3431 washer (3) or Post-SB3431 keywasher (16) that attaches dipstick (6) to underside of oil filler cap body and remove dipstick.

(2)

Fit new dipstick (6) on oil filler cap spindle (4) and attach with Pre-SB3431 washer (3) or Post-SB3431 keywasher (16) and locknut (5). Torque locknut 6 to 11 lb.in.

(3)

For Post-SB3431 Engines: Safety keywasher (16). NOTE:

B.

Replacement of Oil Pump Drive Seal (Ref. Fig. 213) (1)

Remove accessory gearbox assembly from engine.

(2)

Remove and install replacement oil pump oil seal (Ref. Removal/Installation). NOTE:

(3) C.

Oil filler cap and gage assembly (1 or 2) are not repairable and should be shipped to an approved overhaul facility.

Oil seal is fitted from non-pressure side.

After installation of oil pump (5) on gearbox diaphragm, torque four attachment bolts 32 to 36 lb.in., and lockwire.

Replacement of Starter-generator Gearshaft Carbon Seal (Ref. Figs. 207 and 214) (1)

Remove accessory gearbox assembly from engine and separate housing from diaphragm (Ref. Removal/Installation).

(2)

Remove starter-generator gearshaft (3, Fig. 207) from gearbox housing (1).

(3)

Remove bolts and keywashers (9) fastening flanged bearing (10) to diaphragm. Remove bearing.

(4)

Withdraw seal and seal carrier (2, Fig. 214) using puller (1, PWC30052). Remove and discard preformed packing (4).

(5)

Remove seal and casing (3) from carrier (2) using base (PWC30051-01) and drift (PWC30051-02) .

(6)

Immerse new carbon seal in engine oil (PWC03-001) and move seal in and out within seal casing to check freedom of movement.

(7)

Immerse seal carrier in oil (PWC03-001) heated to 80° to 90°C (176° to 194°F) for a few minutes.

(8)

Remove carrier from engine oil, press replacement carbon seal into carrier (Ref. Fig. 214) with drift (PWC30675).

(9)

Install new lubricated preformed packing (4) on seal carrier and press carrier into boss on diaphragm, with drift (PWC30075).

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

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8

1

2

FWD 3

7

6

5 4

C1873 Installation of Oil Pump Drive Seal Figure 213 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 213 1. 2. 3. 4. 5. 6. 7. 8.

Accessory Gearbox Diaphragm Oil Tank Center Tube Oil Pump Driveshaft Oil Seal and Carrier Oil Pump Preformed Packing Oil Seal Carrier Oil Seal

(10)

Install flanged bearing (10, Fig. 207) on boss with bolts and keywashers (9). Tighten bolts 36 to 40 lb.in., and lock keywashers.

(11)

Install starter-generator/centrifugal breather gearshaft (3) in gearbox housing.

CAUTION: IF, FOR ANY REASON, OTHER ACCESSORY DRIVES WERE REMOVED DURING PROCEDURE, USE CARE NOT TO INTERCHANGE THE EXTERNAL SCAVENGE PUMP GEARSHAFT (NO. 4) WITH THE HYDRAULIC PUMP GEARSHAFT (NO. 6). THESE GEARSHAFTS ARE SIMILAR IN APPEARANCE AND MUST BE IDENTIFIED BY PART NUMBER. (12) (13) D.

Install accessory gearbox housing on diaphragm. Install accessory gearbox assembly on engine (Ref. Removal/Installation)

Replacement of Starter-generator Gearshaft Centrifugal Breather (Ref. Figs. 215 and 216) (1)

Remove accessory gearbox assembly from engine and separate housing from diaphragm (Ref. Removal/Installation).

(2)

Remove starter-generator/centrifugal breather gearshaft (3, Fig. 207) from gearbox diaphragm (8).

(3)

For Pre-SB3121 Engines: (a) Locate split plate (3, Fig. 215) between centrifugal impeller (5) and gearshaft (6). (b) Position gearshaft/impeller assembly on base (4). (c) Install compressor (1) on impeller (5) and mate lugs of compressor with corresponding slots in impeller. (d)

Using adapter (2) inserted in compressor (1), separate assemblies.

(e) Remove split plate (3) from impeller, and gearshaft (6) from base (4). (4)

For Post-SB3121 Engines:

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1

2

3

4

C1874 Replacement of Starter-generator Gearshaft Carbon Seal Figure 214 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 214 1. 2. 3. 4.

Carbon Seal Carrier Puller (PWC30046-54) Carbon Seal Carrier Carbon Seal and Casing Preformed Packing

CAUTION: DO NOT USE SPLIT PLATE ON POST-SB3121 IMPELLER. (a) Place ring (5, Fig. 216) on base (6). (b) Position gearshaft/impeller assembly on ring (5). Make sure pins (7) align with shouldered pins (9). (c) Install compressor (2) on impeller (4) and mate lugs of compressor with corresponding slots in impeller. CAUTION: SEPARATION OF GEARSHAFT AND IMPELLER SHOULD NOT REQUIRE EXCESSIVE FORCE. IF DIFFICULTY IS EXPERIENCED, CHECK THAT RETAINING RING IS CLEAR OF GROOVE IN IMPELLER. (d)

Using drift (1) inserted in compressor (2), separate assemblies.

(e) Fully disengage gearshaft (8) from three shoulder pins installed in impeller (4). Remove gearshaft from impeller. (5)

Remove retaining ring (16, Fig. 207), remove and discard preformed packings (14 and 15).

(6)

Install new lubricated preformed packing (14) on OD of impeller.

(7)

Install new lubricated preformed packing (15) on starter-generator gearshaft.

(8)

Install retaining ring (16) in groove in gearshaft. NOTE:

(9)

E.

Check integrity of shoulder pins before mating parts.

Position impeller on gearshaft; align shoulder pins in impeller with holes in gearshaft and press parts firmly together by hand to engage retaining ring. Make sure parts are locked together.

(10)

Install starter-generator/centrifugal breather gearshaft on diaphragm (8) by mating with related gearshafts.

(11)

Install accessory gearbox housing on diaphragm and install accessory gearbox assembly on engine (Ref. Removal/Installation).

Repair of Corrosion - Accessory Gearbox Housing NOTE:

Corrosion must not be deeper than 0.010 in. and must not cover an area greater than 10 percent of the total surface of the AGB housing.

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

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2

1 3

5

6

7

4

C7867

Pre-SB3121 Replacement of Starter-generator Gearshaft Figure 215 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 215 1. 2. 3. 4. 5. 6. 7.

Compressor (PWC50502) Drift (PWC30854) Split Plate (PWC32275) Base (PWC30274) Centrifugal Impeller Starter-generator Gearshaft Retaining Ring

(1)

Apply a suitable covering material over all the accessories, linkages, compressor section and around the area to be repaired.

(2)

Clean the surface of the area to be repaired with a swab soaked in isopropyl alcohol (PWC11-014) and crocus cloth (PWC05-061).

(3)

Remove all traces of corrosion (magnesium oxide) using a suitable steel brush, crocus cloth (PWC05-061), abrasive cloth (PWC05-101), file or grit paper. Remove all traces of debris using a vacuum cleaner.

(4)

Flush the area with clean water at room temperature.

(5)

Dry the area with clean compressed air at 29 psig.

WARNING: 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. (6)

Prepare a chrome pickle solution (Ref. Chap. 70-00-00, MAINTENANCE PRACTICES, Touch-Up Solution).

(7)

Using a swab or brush, apply the chrome pickle solution, at a temperature of 17° to 29°C (55° to 85°F), to the prepared surface for 30 to 45 seconds. NOTE:

Repeat the application frequently to make sure that the affected surface is continually wet with the solution.

(8)

Swab the area with clean water until successive swabs are no longer stained yellow.

(9)

Dry the area with local heating (air dry or a heat gun at a low setting).

(10)

Clean the affected area with a rag soaked in clean water.

(11)

Dry the area with clean, compressed air at 29 psig.

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

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1

2

3

9

4

8

7 5

6

C7868A

Post-SB3121 Replacement of Starter-generator Gearshaft Figure 216 P&WC Proprietary Information. Subject to the restrictions on the title page.

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Key to Figure 216 1. 2. 3. 4. 5. 6. 7. 8. 9. (12)

Adapter (PWC30854) Compressor (PWC50502) Retaining Ring Impeller Ring (PWC32175) Base (PWC32174) Pin Gearshaft Shouldered Pin

Apply two coats of primer (PWC13-001). NOTE:

The primer can be diluted with 10% solvent.

(13)

Allow the primer to air dry for eight hours before applying enamel paint. Use compressed air at 29 psig to accelerate the drying time.

(14)

Apply three to four coats of enamel (PWC05-037) to the primed surface. Allow the surface of the enamel to become tacky (approximately 15 minutes) between each coat. The final coat of enamel must dry for 24 hours before returning the engine to service. NOTE:

Drying time for the primer and paint can be reduced with the use of a heat gun at a low setting. Refer to the manufacturer’s instructions.

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

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Contents

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73-00-00 Description and Operation

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TABLE OF CONTENTS SUBJECT

PAGE

ENGINE FUEL AND CONTROL - DESCRIPTION AND OPERATION

73-00-00

1.

Description

1

2.

Operation

1

A.

Engine Starting (PT6A-38/-41/-42/-42A)

1

B.

Engine Starting (PT6A-40)

9

C.

Acceleration

9

D.

Governing

10

E.

Altitude Compensation

10

F.

Deceleration

10

3.

G. Reverse Thrust

10

H.

Power Turbine Limiting

11

I.

Manual Metering (PT6A-40/-42A)

11

J.

Engine Shutdown

11

Fault Isolation

11

73-00 CONTENTS

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ENGINE FUEL AND CONTROL - DESCRIPTION AND OPERATION 1.

Description (Ref. Fig. 1) The fuel control system consists of an oil-to-fuel heater, fuel pump, fuel control unit, flow divider and dump valve, dual fuel manifold with 14 simplex nozzles, and fuel drain valves. For purposes of description and operation, the system also includes the power turbine governor and torque limiter (optional), although further information relating to these components is contained in Chapter 61. The fuel pump delivers fuel to the FCU, which component determines the correct fuel schedule for engine steady-state operation and acceleration. The flow divider supplies the metered fuel flow to the primary or to both primary and secondary manifolds as required. Full propeller control during forward and reverse thrust operation is provided by a governor which incor porates a propeller governor (CSU) section, a reversing valve and a power turbine governor (Nf) section. The Nf governor section provides power turbine overspeed protection during normal operation. During reverse thrust operation, the propeller governor section is inoperative and control of power turbine speed is accomplished by the Nf section. A torque limiter, when fitted, senses the torquemeter pressure and controls the maximum torque by progressively bleeding off pressure from the pneumatic computing section in the FCU through an orifice. Opening the orifice repositions the metering valve and reduces fuel metered to the engine and thereby limits propeller torque. In the following text, references to various control levers and cockpit quadrant markings are generalized since there is no pattern of consistency among various airframe manufacturers. For instance, ‘‘fuel condition lever’’ may be called ‘‘fuel shutoff lever’’, or ’IDLE’ may be labelled ’MINIMUM GOVERNING SPEED’. For individual engine operating procedures, markings and item names on specific airframe installations, refer to the aircraft operating manual.

2.

Operation A.

Engine Starting (PT6A-38/-41/-42/-42A) The engine starting cycle is initiated with the power control lever placed in the IDLE position and the fuel condition lever in CUT-OFF. The ignition and starter are switched on and, when minimum ignition speed is attained, the fuel shutoff lever is advanced to RUN position. Following ignition the engine accelerates to idle speed. For particular engine starting procedures on specific aircraft installations, refer to relevant Aircraft Operating Manual. During the starting sequence, the metering valve in the FCU is in a low flow position, and some of the fuel flow is diverted back to the fuel pump via the spill valve. As the compressor accelerates, the discharge pressure (P3) increases. This creates an increase in Px pressure, which is modified P3 acting on one side of the bellows assembly, and Py, which is modified Px, on the opposite side. Py is the governing pressure and acts on a greater surface area of the bellows. The increase is pressure sensed by the bellows causes the metering valve to move in an opening direction. As P3 pressure increases, the spill valve progressively closes the bypass port allowing full metered fuel flow to pass to the engine. Excess fuel supplied by the fuel pump will pass via the spill valve back to tank. When Ng approaches idle speed, the centrifugal force of the Ng

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TORQUE LIMITER (IF FITTED)

RETURN TO FUEL TANK

Px

F.C.U. CUT−OFF STOP

HIGH IDLE STOP FLOW DIVIDER

SPILL VALVE

CUT−OFF VALVE TORQUEMETER OIL PRESSURE

ACCEL. ADJUSTMENT MINIMUM PRESSURIZING VALVE

P0 P2 Py

GOVERNOR BELLOWS

METERING HEAD REGULATOR BYPASS VALVE

Py

CUT−OFF

VIEW OF CUT−OFF AND IDLE RESEST LINKAGE

PRESSURE RELIEF VALVE ACCEL. BELLOWS (EVACUATED)

Px

FUEL PUMP FILTER BYPASS VALVE

FILTER TORQUE TUBE

RESET ARM (AIRBLEED LINK)

10 MICRON FILTER

P1

MAX. FLOW STOP

IDLE SPEED ADJUSTMENT

INPUT COUPLING

Pa

N f GOVERNOR

Pa AMBIENT AIR Px ACCELERATION PRESSURE Px

Py GOVERNOR SERVO PRESSURE P0 BYPASS FUEL PRESSURE

OUTPUT COUPLING

DRAIN

P1 UNMETERED FUEL PRESSURE

N g GOVERNOR

P2 METERED FUEL PRESSURE P3 COMPRESSOR DISCHARGE PRESSURE

P3 AIR

C54C

PT6A-38 and PT6A-41 Fuel Control System Schematic Figure 1 (Sheet 1 of 3)

73-00-00 ENGINE FUEL AND CONTROL - DESCRIPTION AND OPERATION

P0

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REGULATING VALVE 74 MICRON STRAINER

FUEL INLET

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

FUEL FLOWMETER FLOW DIVIDER

FUEL CONTROL UNIT

CUT−OFF VALVE METERING VALVE MIN. FLOW STOP ACCELERATION (SPECIFIC GRAVITY) METERING ADJUSTMENT VALVE DISK GROUP (BIMETALLIC)

MINIMUM PRESSURIZING VALVE

PROPELLER GOVERNOR (N f GOVERNOR SECTION)

MANUAL METERING ACTUATING PROPELLER SPEED SHAFT MAX. STOP OPERATING PIN GOVERNOR Py BELLOWS

P2

METERING HEAD REGULATOR BYPASS VALVE

CUT−OFF STOP HIGH IDLE STOP

CUT−OFF

BLEED RETURN TO TANK

VIEW OF CUT−OFF AND IDLE RESET LINKAGE

RELIEF VALVE

N f GOVERNOR AIR BLEED LINK ACCELERATION BELLOWS (RESET ARM) (EVACUATED)

MAX. FLOW STOP

TORQUE TUBE

P1

Po

Py

MAXIMUM STOP

FCU BYPASS RETURN TO PUMP (INTERNAL)

Px

UNDERSPEED FUEL GOVERNING SPEED ADJUSTMENT

GEAR TYPE FUEL PUMP (WITH INTEGRAL MICRO−SCREEN ELEMENT)

GAS GENERATOR SPEED SCHEDULING CAM

10 MICRON FILTER

IDLE SPEED STOP

Pa

Pa AMBIENT AIR P x ACCELERATION PRESSURE P y GOVERNOR SERVO PRESSURE Po BYPASS FUEL PRESSURE P1 UNMETERED FUEL PRESSURE P 2 METERED FUEL PRESSURE P 3 COMPRESSOR DISCHARGE PRESSURE

FILTER BYPASS VALVE

INPUT COUPLING

Px Py DRAIN

N g GOVERNOR

GOVERNOR VALVE

P x METERING ORIFICE COMPRESSOR PRESSURE

PUMP GEAR AND SHAFT GEAR

OUTPUT COUPLING

Po REGULATING VALVE 74 MICRON SCREEN ELEMENT

P 3 AIR P 3 FILTER

WATER DRAIN/VENT

C11351

PT6A-40 and PT6A-42A Fuel Control System Schematic Figure 1 (Sheet 2)

73-00-00 ENGINE FUEL AND CONTROL - DESCRIPTION AND OPERATION

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FUEL INLET (FROM OIL−TO−FUEL HEATER)

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TORQUE LIMITER (IF FITTED)

Px

RETURN TO FUEL TANK

F.C.U. CUT−OFF STOP

FLOW DIVIDER SPILL VALVE

CUT−OFF VALVE TORQUEMETER OIL PRESSURE

HIGH IDLE STOP

ACCEL. ADJUSTMENT

MINIMUM PRESSURIZING VALVE

Po P2

BYPASS VALVE

Py

GOVERNOR BELLOWS

Py

VIEW OF CUT−OFF AND IDLE RESET LINKAGE

PRESSURE RELIER VALVE ACCEL. BELLOWS (EVACUATED) RESET ARM (AIRBLEED LINK)

CUT−OFF

METERING HEAD REGULATOR

Px

10 MICRON FILTER

FUEL PUMP FILTER BYPASS VALVE

FILTER TORQUE TUBE

MAX. FLOW STOP

P1 IDLE SPEED ADJUSTMENT

INPUT COUPLING

Pa

N f GOVERNOR

Px Pa AMBIENT AIR P x ACCELERATION PRESSURE P y GOVERNOR SERVO PRESSURE Po BYPASS FUEL PRESSURE P1 UNMETERED FUEL PRESSURE P 2 METERED FUEL PRESSURE P 3 COMPRESSOR DISCHARGE PRESSURE

OUTPUT COUPLING DRAIN

N g GOVERNOR

Po REGULATING VALVE 74 MICRON STRAINER

P 3 AIR

C7979A

PT6A-42 Fuel Control System Schematic Figure 1 (Sheet 3)

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FUEL INLET (FROM OIL−TO−FUEL HEATER)

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

governor flyweights begins to overcome the governor spring force and opens the governor valve, bleeding off Py pressure. This creates a Px-Py differential which causes the metering valve to move in a closing direction until the required-to-run idle speed fuel flow is obtained. Any variation in engine speed from the selected (idle) speed will be sensed by the Ng governor flyweights and will result in increased or decreased weight force. This change will cause movement of the governor valve which will then be reflected by a differing Px to Py relationship and cause the metering valve to move to re-establish the correct fuel flow, and hence Ng speed. B.

Engine Starting (PT6A-40) The engine starting cycle is initiated with the power control lever placed in the IDLE position and the fuel condition lever in CUTOFF. The ignition and starter are switched ON and when minimum ignition speed is attained, the fuel condition lever is advanced to RUN position. Following ignition the engine accelerates to IDLE speed. For particular engine starting procedures on specific aircraft installations, refer to relevant Aircraft Operating Manual. During the starting sequence, the metering valve in the FCU is in a low flow position. As the compressor accelerates, the discharge pressure (P3) increases. This creates an increase in Px pressure, which is modified P3 acting on one side of the bellows assembly, and PY which is modified Px, on the opposite side. Py is the governing pressure and acts on a greater surface area of the bellows. The increase in pressure sensed by the bellows causes the metering valve to move in an opening direction. Excess fuel supplied by the fuel pump will pass via the bypass valve back to tank. When Ng approaches idle speed, the centrifugal force of the Ng governor flyweights begins to overcome the governor spring force and open the governor valve, bleeding off Py pressure. This creates a Px-Py differential which causes the metering valve to move in a closing direction until the required-to-run idle speed fuel flow is obtained. Any variation in engine speed from the selected (idle) speed will be sensed by the Ng governor flyweights and will result in increased or decreased weight force. This change will cause movement of the governor valve which will then be reflected by a differing Px to Py relationship and cause the metering valve to move to re-establish the correct fuel flow, and hence Ng speed.

C.

Acceleration As the power control lever is advanced above idle setting, the speed scheduling cam is repositioned, moving the cam follower lever to increase the governor spring force. The governor spring then overcomes the flyweights and moves the lever closing the governor valve. Px and Py pressures immediately increase, causing the metering valve to move in an opening direction. Acceleration is then a function of increasing Px (Px = Py). As Ng and consequently Nf increase, the propeller governor increases the pitch of the propeller blades to control Nf at the selected speed and applies the increased power as additional thrust. Acceleration is completed when the centrifugal force of the governor flyweight again overcomes the governor spring and opens the governor valve.

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D.

Governing Once the acceleration cycle has been established, any variation in engine speed from the selected speed will be sensed by the Ng governor flyweights and will result in increased or decreased weight force. This change in weight force will cause the governor valve to either open or close; this will then be reflected by the change in fuel flow necessary to re-establish the selected speed. When the FCU is governing, the governor valve will be maintained in a regulating, or floating, position.

E.

Altitude Compensation Altitude compensation is automatic, since the acceleration bellows assembly in the FCU computing section is evacuated and affords an absolute pressure reference. Compressor discharge air (P3) is a measurement of engine speed and air density. Px is proportional to P3, so it will decrease with a decrease in air density. This is sensed by the acceleration bellows which acts to reduce fuel flow on acceleration at altitude.

F.

Deceleration When the power control lever is retarded, the speed scheduling cam is rotated to a lower point on the cam rise. This reduces the governor spring force and allows the governor valve to move in an opening direction. The resulting drop in Py pressure moves the metering valve in a closing direction until it contacts the Wf minimum flow stop. This stop ensures sufficient metered fuel flow to engine to prevent flameout. The engine continues to decelerate until the governor flyweight force decreases to balance the governor spring force at the set governing position.

G. Reverse Thrust Reverse thrust can be obtained at any propeller speed above 1800 rpm provided that the forward speed of the aircraft after landing or during taxiing is not high enough to cause propeller windmilling at speeds near the selected rpm. The idle reset has two settings; low idle and high idle. The high idle setting permits acceleration to maximum rpm to be accomplished in minimum time. The idle setting and fuel cut-off is controlled by the fuel condition lever in the cockpit. The power lever linkage is used only to increase or decrease power. The FCU speed scheduling cam has a single contoured lobe operated through a cam box which permits the scheduling of full power at each end of the power lever travel. When the power control lever is moved to the REVERSE THRUST position, the propeller pitch control and the FCU are integrated. Increased power control lever movement toward FULL REVERSE position will increase compressor turbine speed (Ng) and propeller (reverse) pitch. The propeller governor is maintained in an underspeeding condition in the reverse thrust range by controlling propeller speed with the Nf governing section of the propeller governor. If Nf exceeds the desired speed the Nf governing orifice will open to decrease Py pressure in the computing section of the FCU and cause a reduction in fuel flow and Nf speed, thereby limiting the propeller speed and maintaining the CSU in an underspeed condition.

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H.

Power Turbine Limiting The Nf governing section of the propeller governor senses Py pressure via an external line from the computing section of the FCU. If a power turbine overspeed should occur during forward thrust operation, the Nf governing orifice will be opened, under the influence of the governor flyweights and lever movement, to bleed off Py pressure. This causes a decrease in Py pressure at the FCU computing section causing the metering valve to move in a closing direction, thus reducing fuel flow and consequently Ng and Nf speed.

I.

Manual Metering (PT6A-40/-42A) The manual metering system provides a means for manually adjusting the fuel flow to the engine if a control malfunction occurs. This system may also be used to provide the enrichment necessary for certain starting conditions. To increase the fuel flow, the pilot rotates a lever in the cockpit, which is connected through a series of linkages, to an actuating shaft on the FCU. When the lever is rotated, the actuating shaft rotates, applying a force to manually compress the governor bellows and open the metering valve. When the lever is in the OFF position, the actuating shaft operating pin acts as the governor bellows travel stop.

J.

Engine Shutdown The integral cut-off valve in the FCU provides a positive means of shutting off fuel flow to the engine. During normal engine operation the valve is fully open and offers no restriction to the metered fuel flow to the engine. The engine is shut down by moving the fuel condition lever in the cockpit to CUT-OFF. Fuel is returned to the fuel pump inlet via the internal bypass passages and ports in the FCU and pump. Fuel in the primary and secondary manifolds is drained overboard/ flushed into the combustion chamber via the dump/purge valve ports in the flow divider.

3.

Fault Isolation For detailed procedures refer to Chapter 72-00-00, FAULT ISOLATION.

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DATE Apr 28/2006 Apr 28/2006 Apr 28/2006 Apr 28/2006 Apr 28/2006 Apr 28/2006 Apr 28/2006 Apr 28/2006 Apr 28/2006 Sep 24/99 Sep 24/99

Mar 19/2004 Mar 19/2004 Sep 24/99 Mar 19/2004 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 14/2001 Sep 14/2001

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73-10 LEP

Page 1 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

73-10-05 Maintenance Practices

73-10-06 Description and Operation 73-10-06 Maintenance Practices

73-10-07 Description and Operation

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 blank 1 2 blank

201 202 203 204 1 2 blank

DATE

CHAPTER SECTION

Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008 Jul 11/2008

73-10-07 Maintenance Practices

Sep 24/99 Sep 24/99

73-10-08 Maintenance Practices

PAGE

73-10-08 Description and Operation

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

DATE

201 202 203 204 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220 221 222 blank

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

1 2 blank

Oct 13/2000 Oct 13/2000

201 202 203 204 205 206 207 208 209 210 211 212

Mar 19/2004 Mar 19/2004 Mar 19/2004 Mar 19/2004 Mar 19/2004 Mar 19/2004 Mar 19/2004 Mar 19/2004 Mar 19/2004 Mar 19/2004 Mar 19/2004 Mar 19/2004

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Page 2 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

LIST OF EFFECTIVE PAGES

CHAPTER SECTION

PAGE

73-10-09 Description and Operation 73-10-09 Maintenance Practices

DATE

1 2 blank

Sep 24/99 Sep 24/99

201 202 203 204 blank

Sep 24/99 Sep 24/99 Sep 24/99 Sep 24/99

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

OIL-TO-FUEL HEATER - DESCRIPTION AND OPERATION

73-10-01

1.

Description

1

2.

Operation

1

OIL-TO-FUEL HEATER - MAINTENANCE PRACTICES

73-10-01

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 Oil-to-Fuel Heater

201

B.

Installation of Oil-to-Fuel Heater

204

6.

7.

8.

9.

Cleaning/Painting

206

A.

Insulation

206

B.

Insulating Coating

206

C.

Flushing of Unit

206

D.

Cleaning of Oil-to-Fuel Heater

206

Inspection/Check

206

A.

General

206

B.

Insulation

207

C.

Insulating Coating (Flame Retardant)

207

Approved Repairs

207

A.

General

207

B.

Repair of Molded Insulation

207

C.

Application of Anodic Surface Treatment

208

D.

Insulating Coating Repairs

208

Adjustment/Test

209

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73-10 CONTENTS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

OIL-TO-FUEL HEATER - MAINTENANCE PRACTICES (Cont’d) A.

Oil-To-Fuel Heater

73-10-01 209

FUEL PUMP - DESCRIPTION AND OPERATION

73-10-02

1.

Description

1

2.

Operation

1

FUEL PUMP - MAINTENANCE PRACTICES

73-10-02

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Servicing

201

A.

Removal of Filters

202

B.

Installation of Filters

202

6.

7.

8.

9.

Removal/Installation

203

A.

Removal of Fuel Pump

203

B.

Installation of Fuel Pump

207

Cleaning/Painting

209

A.

General

209

B.

Cleaning of Inlet Filter Element

209

Inspection/Check

209

A.

General

209

B.

Inspection of Filter Elements

210

C.

Sundstrand Fuel Pump In-Situ Inspection

210

Approved Repairs

211

A.

General

211

B.

Removal of Corrosion

213

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

FUEL PUMP - MAINTENANCE PRACTICES (Cont’d) C. 10.

Application of Surface Treatment

213

Adjustment/Test

214

A.

214

Procedure

FUEL TUBES - DESCRIPTION AND OPERATION 1.

73-10-02

Description and Operation

73-10-03 1

FUEL TUBES - MAINTENANCE PRACTICES

73-10-03

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 Fuel Lines

201

B.

Installation of Fuel Lines

206

6.

7.

8.

Cleaning/Painting

208

A.

208

Cleaning of Interconnect Hose and Fuel Tubes

Inspection/Check

208

A.

Inspection of Interconnect Hose

208

B.

Inspection of Fuel Tube Assemblies

208

Adjustment/Test

209

A.

209

Procedure

FLOW DIVIDER AND DUMP VALVE - DESCRIPTION AND OPERATION

73-10-04

1.

Description

1

2.

Operation

1

A.

1

Flow Divider and Dump Valve (Pre-SB3199)

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73-10 CONTENTS

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

FLOW DIVIDER AND DUMP VALVE - DESCRIPTION AND OPERATION (Cont’d) B.

Flow Divider and Purge Valve (Post-SB3199)

FLOW DIVIDER AND DUMP VALVE - MAINTENANCE PRACTICES

73-10-04 1 73-10-04

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation

202

A.

Removal of Flow Divider

202

B.

Installation of Flow Divider

202

6.

7.

8.

9.

Cleaning/Painting

203

A.

203

Cleaning of Flow Divider

Inspection/Check

203

A.

203

Inspection of Flow Divider and Dump Valve

Approved Repairs

205

A.

General

205

B.

Removal of Corrosion

206

C.

Application of Anodic Surface Treatment

206

Adjustment/Test

206

A.

206

Procedure

FUEL MANIFOLD ADAPTERS AND NOZZLES - DESCRIPTION AND OPERATION 1.

73-10-05

Description and Operation

1

A.

Fuel Manifold

1

B.

Fuel Manifold Adapter Assemblies

1

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

FUEL MANIFOLD ADAPTERS AND NOZZLES - MAINTENANCE PRACTICES

73-10-05

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

202

5.

Removal/Installation

202

A.

Procedure Before Removal

202

B.

Removal of Fuel Manifold Adapters

202

C.

Installation of Fuel Manifold Adapters

204

6.

Cleaning/Painting

210

A.

Cleaning of Fuel Manifold Adapter Assemblies

210

B.

Cleaning of Fuel Nozzles (Removed from Fuel Manifold Adapter)

211

Cleaning of Fuel Manifold Adapter (Nozzles Removed) and Adapter Sheaths

214

C. 7.

8.

9.

Inspection/Check

214

A.

Inspection of Nozzle Sheath

214

B.

Inspection of Manifold Adapter

214

C.

Inspection of Nozzle Assembly

214

Approved Repairs

215

A.

215

Procedure

Adjustment/Test

215

A.

General

215

B.

Leakage Test of Fuel Manifold Adapters

217

C.

Function Test of Fuel Manifold Adapters

219

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Page 5 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

FUEL DRAIN VALVE - DESCRIPTION AND OPERATION 1.

Description and Operation

73-10-06 1

FUEL DRAIN VALVE - MAINTENANCE PRACTICES

73-10-06

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 Drain Valve(s)

201

B.

Installation of Drain Valve(s)

201

6.

7.

8.

9.

Cleaning/Painting

203

A.

203

Procedure

Inspection/Check

203

A.

Inspection of Drain Valve

203

B.

Inspection of Spring

204

Approved Repairs

204

A.

General

204

Adjustment/Test

204

A.

Operation

204

B.

Procedure after Test

204

COMPRESSOR DELIVERY AIR LINES - DESCRIPTION AND OPERATION 1.

73-10-07

Description and Operation

1

A.

For the PT6A-38 Engines:

1

B.

For the PT6A-40, PT6A-41, PT6A-42 and PT6A-42A Engines:

1

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73-10 CONTENTS

Page 6 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

COMPRESSOR DELIVERY AIR LINES - MAINTENANCE PRACTICES

73-10-07

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Servicing

202

A.

General

202

B.

Replacement of P3 Air Filter

202

6.

7.

Removal/Installation

203

A.

Removal of Electrical Connector Leads (P3 or Py)

203

B.

Removal of Tube Assemblies, Adapter Assemblies and P3 Air Filter

205

C.

Installation of Electrical Connector Leads

207

D.

Installation of Tube Assemblies, Adapter Assemblies and P3 Air Filter

211

E.

Removal of Post-SB3350 Air Filter Housing Drain Valve

212

F.

Installation of Post-SB3350 Air Filter Housing Drain Valve

212

Cleaning/Painting

213

A.

Cleaning of P3 Air Filter

213

B.

Cleaning of Post-SB3350 Air Filter Housing Drain Valve Adapter

213

Cleaning of Air Tubes

213

C. 8.

Inspection/Check

215

A.

Inspection of Air Tubes

215

B.

Inspection of Air Filter Element

215

C.

Inspection of Heated Tubes

215

D.

Heated Tube Checks

216

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

COMPRESSOR DELIVERY AIR LINES - MAINTENANCE PRACTICES (Cont’d) E. 9.

10.

Inspection of Post-SB3350 Air Filter Housing Drain Valve Assembly

216

Approved Repairs

217

A.

Repair of Cuts in Tube Insulation

217

B.

Repair of Damaged Silicone Rubber Sheath

217

Adjustment/Test

217

A.

217

Testing of Fuel Control Pneumatic System

GOVERNOR PNEUMATIC TUBES - DESCRIPTION AND OPERATION 1.

73-10-07

Description and Operation

73-10-08 1

GOVERNOR PNEUMATIC TUBES - MAINTENANCE PRACTICES

73-10-08

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation

201

A.

Removal (Standard Configuration)

201

B.

Removal (Alternative Configuration)

207

C.

Installation (Standard Configuration)

208

D.

Installation (Alternative Configuration)

210

6.

7.

8.

Cleaning/Painting

211

A.

211

Cleaning of Air Tubes

Inspection/Check

211

A.

211

Inspection of Air Tubes

Approved Repairs

212

A.

212

Procedure

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PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

TABLE OF CONTENTS SUBJECT

PAGE

GOVERNOR PNEUMATIC TUBES - MAINTENANCE PRACTICES (Cont’d) 9.

Adjustment/Test

212

A.

212

Procedure

TORQUE LIMITER - DESCRIPTION AND OPERATION 1.

73-10-08

Description and Operation

73-10-09 1

TORQUE LIMITER - MAINTENANCE PRACTICES

73-10-09

1.

General

201

2.

Consumable Materials

201

3.

Special Tools

201

4.

Fixtures, Equipment and Supplier Tools

201

5.

Removal/Installation

201

A.

Removal

201

B.

Installation

203

6.

Adjustment/Test

203

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73-10 CONTENTS

Page 9/10 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

OIL-TO-FUEL HEATER - DESCRIPTION AND OPERATION 1.

Description (Ref. Fig. 1) The oil-to-fuel heater, mounted below the fuel pump at the rear of the engine and bolted to flange G, is essentially a heat exchanger which utilizes heat from the engine lubricating oil system to preheat the fuel in the fuel system. The heater incorporates a honeycomb two-pass oil circuit and a two-pass fuel circuit. A fuel temperature-sensing oil bypass valve regulates the fuel temperature by either allowing oil to flow through the heater circuit, or bypass it to the engine oil tank.

2.

Operation The temperature-sensing oil bypass (thermal element) valve consists of a highly expansive material sealed in a metallic chamber. The expansion force is transmitted through a diaphragm and plunger to a piston. Since the element only exerts an expansive force, it is counterbalanced by a return spring which provides a contracting force during decreases in temperature. The element senses the temperature of the outlet fuel and, at temperatures above 21°C (70°F), starts to close the core valve and simultaneously opens the bypass valve. At 32°C (90°F), the core valve is completely closed and oil bypasses the heater core.

73-10-01 OIL-TO-FUEL HEATER - DESCRIPTION AND OPERATION

Page 1 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

BYPASS PASSAGE VALVE SLEEVE

PUSH ROD FUEL OUT

OIL IN

THERMAL ELEMENT

OIL OUT ROD GUIDE SPRING DISCHARGE PASSAGE FUEL IN

HEAT EXCHANGER CORE

C55B Oil-to-Fuel Heater Schematic Figure 1

73-10-01 OIL-TO-FUEL HEATER - DESCRIPTION AND OPERATION

Page 2 Sep 24/99

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

OIL-TO-FUEL HEATER - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire unless otherwise specified shall comply with specification AMS5687, heat and corrosion resistant steel wire MS9226-03, 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

PWC01-001 PWC03-001 PWC05-061 PWC05-166 PWC07-008 PWC09-001A PWC11-012 PWC11-014 PWC11-016 PWC11-024 PWC11-027 PWC11-031 PWC11-038

Fuel, Engine Oil, Engine Lubricating Cloth, Abrasive Solution, Chemical Treatment Coating, Thermal Insulating Sealant, Silicone Rubber Acetone Alcohol, Isopropyl DELETED Solvent, Methylene Chloride Solvent, Petroleum Cleaner, Engine Solvent, Cleaning

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation A.

Removal of Oil-to-Fuel Heater (Ref. Fig. 201) (1)

Drain oil tank (Ref. 70-00-00, SERVICING).

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73-10-01

OIL-TO-FUEL HEATER - MAINTENANCE PRACTICES

Page 201 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

10

13

11

9

7

12

THERMOSTATIC BYPASS / CHECK VALVE FITTED

5

8 6 14

15

4

1

5

15

2

3

20 16 17 16

19

BYPASS / CHECK VALVE NOT FITTED

18

C3916B Removal/Installation of Oil-to-Fuel Heater Figure 201 P&WC Proprietary Information. Subject to the restrictions on the title page.

73-10-01

OIL-TO-FUEL HEATER - MAINTENANCE PRACTICES

Page 202 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

Key to Figure 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. (2)

Oil-to-fuel Heater Fuel Inlet Connection Drain Plug Oil Transfer Tube Bolt Retaining Plate Bolt Retaining Plate Fuel Transfer Tube Oil Transfer Tube Bracket Bolts Oil Transfer Tube Preformed Packing Preformed Packing Preformed Packing Oil Outlet Transfer Tube Bolt Elbow Preformed Packing

If oil-to-fuel heater (1) is being removed with engine installed, disconnect fuel line from connection (2) on heater. Suitably cap end of fuel line and heater connection. NOTE:

To prevent contamination of work area, use a container to catch spillage when disconnecting fuel line.

(3)

Remove drain plug (3), drain oil-to-fuel heater (1), and reinstall plug.

(4)

On engines not fitted with thermostatic bypass/check valve, remove two bolts (18) and washers to release oil return elbow at boss on compressor inlet case.

(5)

On engines fitted with thermostatic bypass/check valve, remove two bolts (5) securing oil transfer tube retaining plate (6) to thermostatic bypass/check valve assembly. Disengage plate from groove in transfer tube (4) and remove plate. Move transfer tube forward into cavity in valve assembly until rear end of tube disengages from oil-to-fuel heater boss.

(6)

Remove two bolts (7) securing retaining plate (8) to oil-to-fuel heater. Disengage plate from groove in fuel transfer tube (9) and remove plate.

(7)

Remove bolt (10) and washer securing bracket (11) to oil-to-fuel heater. Swivel bracket away from heater.

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73-10-01

OIL-TO-FUEL HEATER - MAINTENANCE PRACTICES

Page 203 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(8)

Supporting oil-to-fuel heater, remove two bolts (12) and washers securing heater to flange G of accessory gearbox housing. Remove oil-to-fuel heater in a downward direction. NOTE:

B.

Oil transfer tube (13) and fuel transfer tube (9) will remain attached to accessory gearbox and fuel pump respectively as oil-to-fuel heater is removed. On engines (Pre-SB3009) oil outlet transfer tube and elbow fitting will be removed with heater.

(9)

On engines not fitted with thermostatic bypass/check valve, withdraw transfer tube (17) from outlet boss on oil-to-fuel heater and remove elbow fitting (19) from transfer tube (17).

(10)

Remove all preformed packings from transfer tubes. Cap all lines and openings to prevent ingress of foreign material.

Installation of Oil-to-Fuel Heater (Ref. Fig. 201) (1)

When a replacement oil-to-fuel heater (1) is being installed, carry out depreservation prior to installation as follows: NOTE:

Depreservation is not required when original oil-to-fuel heater is being installed.

(a) Remove shipping plugs from oil ports and flush oil circuit of heater with engine oil (PWC03-001). Drain off surplus oil and reinstall shipping plugs until heater is ready for installation. (b) Remove shipping plugs from fuel ports and flush fuel circuit of heater with fuel (PWC01-001). Drain off surplus fuel and reinstall shipping plugs until heater is required for installation. (2)

Remove blanking caps from transfer tubes (9) and (13); ensure bore of each tube is clean. Fit new preformed packings (14) in grooves on transfer tubes.

(3)

On engines not fitted with thermostatic bypass/check valve, remove blanking caps from oil transfer tube (17) and elbow fitting (19). Fit new preformed packings (16) and (20) on tube and elbow fitting.

(4)

On engines fitted with thermostatic bypass/check valve, remove blanking cap from oil transfer tube in bypass/check and diverter valve. Fit new preformed packing (15) on transfer tubes.

(5)

Remove blanking plug from oil outlet boss on oil-to-fuel heater (1).

(6)

On engines not fitted with thermostatic bypass/check valve, install one end of oil transfer tube (17) into elbow fitting (19) and insert other end of transfer tube into boss on oil-to-fuel heater. NOTE:

(7)

Preformed packings must not be displaced from seal grooves of tube during this operation.

Remove blanking plugs from oil and fuel inlet bosses on oil-to-fuel heater.

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73-10-01

OIL-TO-FUEL HEATER - MAINTENANCE PRACTICES

Page 204 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

(8)

Raise oil-to-fuel heater to engage transfer tubes (9 and 13) with bosses on heater. On engines not fitted with thermostatic bypass/check valve, align boss on elbow fitting (19) with corresponding boss on compressor inlet case, and push fitting into position.

(9)

Align holes in oil-to-fuel heater flange with corresponding holes in flange G of accessory gearbox housing. Secure heater to housing with two bolts (12) and washers. Tighten bolts, torque 36 to 40 lb.in. and lockwire.

(10)

Swivel bracket (11) into position on oil-to-fuel heater and secure with bolt (10). Tighten bolts, torque 32 to 36 lb.in. and lockwire to hole in bracket.

(11)

Position retaining plate (8) in groove on transfer tube (9) and secure with two bolts (7). Tighten bolts torque 32 to 36 lb.in. and lockwire to hole in plate.

(12)

On engines not fitted with thermostatic bypass/check valve, secure elbow fitting (19) to compressor inlet case with two bolts (18) and washers. Tighten bolts, torque 36 to 40 lb.in., and lockwire.

(13)

On engines fitted with thermostatic bypass/check valve, withdraw oil transfer tube (4) from thermostatic bypass/check valve and insert rear end of tube into boss on oil-to-fuel heater. Locate retaining plate (6) in groove at front end of transfer tube and secure to thermostatic bypass/check valve with two bolts. Tighten bolts, torque 32 to 36 lb.in. and lockwire to hole in plate.

(14)

Check installation of drain plug (3): (a) If plug is correctly lockwired on a replacement oil-to-fuel heater (1), it may be assumed that plug is correctly assembled. (b) If plug is not lockwired and loose, remove plug and assemble new preformed packing. Install plug, tighten and torque 65 to 75 lb.in., and lockwire to hole in boss on oil-to-fuel heater (1).

(15)

If installation of oil-to-fuel heater (1) has been done with engine installed: (a) Remove blanking caps from fuel inlet port on heater and from fuel inlet line. (b) Connect inlet line to connection (2) on oil-to-fuel heater. (c) Tighten line connection to torque value recommended in appropriate aircraft maintenance manual and lockwire to holes in boss of heater.

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73-10-01

OIL-TO-FUEL HEATER - MAINTENANCE PRACTICES

Page 205 Dec 10/2010

PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3021442

6.

Cleaning/Painting A.

Insulation

WARNING: DO NOT ATTEMPT TO CLEAN EXTERIOR OF OIL-TO-FUEL HEATER WITHTRICHLORETHYLENE, OR SIMILAR CLEANING AGENTS, AS THESE MATERIALS HAVE A HARMFUL EFFECT ON INSULATION MOLDED AROUND UNIT. WASH OFF SOLVENT, IF INADVERTENTLY SPLASHED ON INSULATION, USING SOAP AND WATER. ENSURE THAT ALL PORTS ARE CAPPED DURING WASHING TO PREVENT SOAP AND WATER ENTERING UNIT.

B.

(1)

Clean exterior of oil-to-fuel heater by washing insulation with soap and water.

(2)

Use a soft bristle brush and/or lint-free cloths and acetone (PWC11-012) or isopropyl alcohol (PWC11-014) to remove contamination from oil and fuel ports.

Insulating Coating (1)

C.

Flushing of Unit (1)

D.

Clean external parts of heater with cleaning solvent (PWC11-027) or (PWC11-031). Dry parts with dry, filtered compressed air.

If flushing of unit is required, the complete assembly must be shipped to an approved overhaul facility for back flushing in accordance with Overhaul Manual.

Cleaning of Oil-to-Fuel Heater CAUTION: DO NOT CLEAN EXTERIOR OF UNIT WITH SOLVENTS. THESE MATERIALS CAN DAMAGE INSULATION MOLDED AROUND UNIT. WASH OFF ANY SOLVENT INADVERTENTLY SPLASHED ON INSULATION USING SOAP AND WATER. CAP ALL PORTS TO PREVENT SOAP AND WATER ENTERING UNIT.

7.

(1)

Clean exterior with soap and water.

(2)

Use a soft bristle brush and/or lint-free cloths and acetone (PWC11-012) or isopropyl alcohol (PWC11-014) to remove contamination from oil and fuel ports.

(3)

If flushing of unit is required, the complete assembly must be sent to an approved overhaul facility for back flushing .

Inspection/Check A.

General (1)

Visually inspect mounting lugs for cracks and other defects. Cracks are not permissible; minor defects may be repaired.

(2)

Inspect bores of oil inlet and outlet ports and fuel outlet port for damage on sealing surfaces.

(3)

Inspect fuel inlet port for damage to threads.

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

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B.

C.

(4)

Check for security damage and correct installation of helical coil inserts located at fuel outlet port and boss adjacent to oil inlet port.

(5)

Check for security of identification plate.

Insulation (1)

Examine insulating material for general surface condition. Deterioration of surface is cause for rejection of oil-to-fuel heater which must be returned to manufacturer for molding of new insulation.

(2)

Inspect surface of insulating material for cracks, gouges, chips and other defects. Minor damage which does not penetrate to metal body may be repaired. When damage is severe and penetrates to metal, reject oil-to-fuel heater and return to manufacturer for molding of new insulation.

Insulating Coating (Flame Retardant) (1)

8.

Inspect surface of insulating material for cracks, gouges, chips and other defects. Minor damage which does not penetrate metal body may be repaired (Ref. Para 8.D.). When damage is severe and penetrates metal, reject oil-to-fuel heater and return to manufacturer for possible repair.

Approved Repairs A.

General NOTE:

B.

Make sure that all areas are cleaned and corrosion-preventive treatment applied to aluminum surfaces out minor repairs are done.

(1)

Minor damage such as burrs, scores, scratches, nicks and other similar defects on sealing surfaces in oil and fuel ports may be cleaned up with a abrasive cloth (PWC05-061). Remove all high spots .

(2)

Smooth minor surface defects on mounting lugs and other metal surfaces with a fine stone or swiss file.

(3)

Clean up minor thread damage in fuel inlet port or chase threads 7/8-14 UNJF-3B.

(4)

Replace damaged or loose helical coil inserts (Ref. 70-00-00, REPAIR).

Repair of Molded Insulation (1)

Remove loose particles of insulating material from gouged or torn area and blow out with a low pressure air blast.

(2)

Fill repair area with silicone adhesive (PWC09-001A).

(3)

Using a suitable spatula, press adhesive into repair and smooth out to blend with surrounding insulating material.

(4)

Allow adhesive to cure for approximately 24 hours or until completely set.

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

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C.

Application of Anodic Surface Treatment (1)

The anodic anti-corrosion finish on exposed aluminum surfaces of oil-to-fuel heater may be repaired by local application of chemical treatment solution (PWC05-166). This treatment must be used on areas where minor repairs have been carried out by blending and/or polishingand on repaired threads. To apply treatment, proceed as follows: WARNING: ALODINE SOLUTION IS EXTREMELY DANGEROUS. IT CONTAINS AN OXIDIZING INGREDIENT WHICH CAN CAUSE AN EXPLOSION IF IT COMES IN CONTACT WITH COMBUSTIBLE MATERIALS SUCH AS PAINTS AND SOLVENTS. (a)

Prepare surface by cleaning with solvent (PWC11-038). Keep surface wetted with cleaning agent for one to five minutes.

(b) Rinse with clean water to remove all traces of solvent. (c) Apply chemical treatment solution (PWC05-166) to prepared surface by brush, swab or spray method and allow three to five minutes setting time. (d) Rinse with clean water to remove all traces of excess chemical treatment solution and allow surface to air dry. (e) Examine treated surface to make sure that repair area is completely covered. Reapply treatment as necessary. D.

Insulating Coating Repairs (1)

The flame retardant, insulating coating on heaters not covered with insulating material, may be touched up with paint (PWC07-008). Apply treatment, as follows: (a) Clean surface with methylene chloride (PWC11-024). (b) Mix epoxy base paint, component A, with catalyst, component B, in a 10:1 ratio (PWC07-008). Mixing shall be performed in an open container and only sufficient quantity for one application. Apply with a brush to exposed areas. Three coats should be applied with one hour drying time between coats. NOTE:

Once catalyzed, the epoxy coating has a usable life of 45 to 60 minutes. Brushes and containers should be cleaned with methylene chloride (PWC11-024) within 60 to 90 minutes after initial contact.

(c) Examine treated surface to make sure that repair area is completely covered. Reapply treatment as necessary. (d) Units shall be allowed to air dry at room temperature for an additional minimum 12 hour period before further handling.

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

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9.

Adjustment/Test A.

Oil-To-Fuel Heater (1)

Start engine (Ref. 71-00-00, ADJUSTMENT/TEST, Engine Starting) and do checks associated with Installation/Replacement of Oil-to-fuel Heater (Ref. 71-00-00, ADJUSTMENT/TEST, Table 501). NOTE:

(2)

Run engine above 72 % (Ng) until oil temperature stabilizes

Check the oil-to-fuel heater within 15 min. after engine shutdown for a high operating temperature. A heater fuel outlet or a fuel pump filter cover having a temperature above 140°F. (60°C.) after shutdown shows a heater that does not correctly operate. To measure the temperature of the oil-to-fuel heater, do one of the following procedures: WARNING: MAKE SURE PROTECTIVE CLOTHING IS PUT ON WHEN MANUALLY CHECKING THE TEMPERATURE OF THE HEATER FUEL OUTLET OR THE FUEL PUMP FILTER COVER. THE OIL-TO-FUEL HEATER CAN GET HOT. THIS WILL PREVENT POSSIBLE INJURY TO PERSONNEL. (a) Carefully feel the heater fuel outlet or the fuel pump filter cover. 1

If the temperature of the heater fuel outlet or the fuel pump filter cover feels unusually hot, replace the oil-to-fuel heater.

2

If a high temperature is not felt, remove the protective clothing and carefully check the heater fuel outlet or the fuel pump filter cover again. If the oil-to-fuel heater is operating correctly, the heater fuel outlet and the fuel pump filter cover should be comfortable to touch.

CAUTION: A NEW TEMPERATURE RECORDER MUST BE USED FOR EACH INSPECTION. (b) Put a temperature recorder on the heater fuel outlet or the fuel pump filter cover. If the temperature recorder shows a temperature above 140°F. (60°C.), replace the oil-to-fuel heater. NOTE:

A temp-plate temperature recorder (PWC05-329) or similar can be used.

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

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FUEL PUMP - DESCRIPTION AND OPERATION 1.

Description The engine-driven fuel pump installation comprises a positive displacement gear-type pump and related parts, mounted on a pad at the 2 o’clock position on the rear face of the accessory gearbox. The pump incorporates spring and pressure loaded bushings and is shaft-driven off the accessory gearbox train. A splined coupling is used to transmit the geartrain drive to the pump gears; the coupling splines are lubricated by oil mist from the gearbox via a hole in the associated gearshaft. Another coupling, on the other side of the pump gears, is used to transmit a speed signal to the fuel control unit (FCU).

2.

Operation (Ref. Fig. 1) Fuel from the oil-to-fuel heater enters the fuel pump chamber through a 74-micron (200-mesh) inlet screen. The inlet screen is spring-loaded and should it become blocked, the increase in differential pressure will overcome the spring and allow unfiltered fuel to flow into the pump chamber. The pump gears increase the fuel pressure and deliver it to the FCU via a 10-micron filter in the pump outlet. A bypass valve and cored passages in the pump body enables unfiltered high pressure fuel to flow to the FCU in the event of the outlet filter becoming blocked. An internal passage originating at the mating face of the FCU returns bypass fuel from the FCU metering valve directly into the pump gears. A pressure regulating valve in the bypass line serves to pressurize the bearings and direct excess bypass fuel to the pump fuel inlet downstream of the inlet screen. The fuel pump is sized for starting requirements and has excess capacity for all steady running conditions.

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FUEL OUTLET (TO F.C.U.)

10 MICRON FILTER

FILTER BYPASS VALVE

INPUT COUPLING F.C.U. COUPLING DRIVE SPLINES

RETAINING RING F.C.U. BYPASS FUEL

74 MICRON STRAINER

BYPASS REGULATING VALVE

FUEL INLET (FROM OIL−TO−FUEL HEATER)

C3885B Fuel Pump Figure 1

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FUEL PUMP - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

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

Consumable Materials The consumable materials listed below are used in the following procedures. For alternate products, suppliers, and supplier addresses, refer to 72-00-00, MAINTENANCE PRACTICES.

3.

Item No.

Name

PWC01-001 PWC03-001 PWC05-061 PWC05-101 PWC05-166 PWC05-167 PWC11-027 PWC11-031 PWC11-038 PWC13-003

Fuel, Engine Oil, Engine Lubricating Cloth, Abrasive Cloth, Abrasive Solution, Chemical Treatment Grit, Abrasive Solvent, Petroleum Cleaner, Engine Solvent, cleaning Primer Coating, Zinc Chromate

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Servicing NOTE:

Fuel pump can be either Sundstrand or Argo-Tech manufacture (Ref. IPC).

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A.

Removal of Filters (Ref. Fig. 201) (1)

Unscrew discharge filter cover (2) and remove from fuel pump (1). Withdraw filter element (3) and preformed packing (4) and discard packing. At life limit, withdraw element and packing and discard both items.

CAUTION: THE DISCHARGE FILTER ELEMENT IS DISPOSABLE AND MUST BE DISCARDED. DO NOT CLEAN. (2)

Remove preformed packing (5) from cover (2) and discard.

(3)

Sundstrand pump inlet filter removal: (a) Remove inlet filter cover (6) and attached filter element (7) from fuel pump (1). Do not disassemble parts. (b) Remove and discard preformed packings (8 and 9) from inlet cover (6).

(4)

Argo-Tech pump inlet filter removal: (a) Using 3/8-inch Allen wrench, remove inlet filter cover (13) with attached filter assembly (11). Do not disassemble parts. (b) Remove and discard preformed packing (12) form inlet cover (13).

B.

Installation of Filters (Ref. Fig. 201) NOTE: (1)

Lubricate all preformed packings with a light film of engine oil (PWC03-001) prior to assembly.

Sundstrand pump: (a) Make sure inlet filter element (7) is clean and install:

(2)

1

Assemble new preformed packings (8 and 9) under head of inlet filter cover (6) and in groove of filter.

2

Insert assembled inlet filter element and cover into fuel pump (1) and screw cover into pump. Tighten cover (6), torque 180 to 220 lb.in., and lockwire.

Argo Tech pump:

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CAUTION: WHEN INSTALLING INLET SCREEN ASSEMBLY INTO ARGO-TECH PUMP HOUSING ASSEMBLY, MAKE SURE THE SCREEN SEAT CONTACTS SEAT MACHINED IN HOUSING PRIOR TO COMPRESSING SPRING AND ENGAGING INLET SCREEN COVER THREADS. VERIFY PROPER INSTALLATION BY VISUALLY DETERMINING THAT UPPER EDGE OF SCREEN IS BELOW THREADS MACHINED IN PUMP HOUSING ASSEMBLY. IF NOT INSTALLED PROPERLY, THE SCREEN CAN HANG UP ON THE SCREEN CENTERING LUGS AND THE UPPER EDGE OF THE SCREEN WOULD PROTRUDE INTO THE THREADED PORTION OF THE HOUSING. (a) Install inlet filter assembly (11) into pump housing (1). (b) Install new preformed packing (12) in groove on inlet filter cover (13). (c) Position cover (13) over spring, and thread cover into pump housing. Tighten cover above run-in torque required to compress preformed packing (12), then torque cover 30 to 50 lb.in. (3)

Install new discharge filter element (3): NOTE:

Two service kits are available from the engine manufacturer for the discharge filter. One kit covers consumable parts needed during discharge filter replacement; the other at discharge filter visual inspection (Ref. IPC).

(a) Assemble new preformed packing (5) in seal groove around discharge filter cover (2). (b) Assemble new preformed packing (4) in seal groove of filter element (3). (c) Insert element into fuel pump (1). (d) Install cover (2): 1

Argo-Tech pump: a

2

Sundstrand pump: a

6.

Position cover (2) over end of filter element (3) and screw cover into pump (1). Tighten cover above run-in torque required to compress preformed packing (5), then torque cover 30 to 50 lb.in. and lockwire.

Position cover (2) over end of filter element (3) and screw cover into fuel pump (1). Torque cover 180 to 220 lb.in. and lockwire.

Removal/Installation A.

Removal of Fuel Pump (Ref. Fig. 202) (1)

Remove oil-to-fuel heater (Ref. 73-10-01).

(2)

Remove fuel control unit (Ref. 73-20-00).

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1 AREA TO BE OBSERVED

11 12

4

13

10

3 6 7 8

9

5

2

C13018A Fuel Pump Filters Figure 201

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Key to Figure 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13.

Fuel Pump Discharge Filter Cover Discharge Filter Element Preformed Packing Preformed Packing Inlet Filter Cover (Sundstrand Fuel Pump Assembly) Inlet Filter Element (Sundstrand Fuel Pump Assembly) Preformed Packing (Sundstrand Fuel Pump Assembly) Preformed Packing (Sundstrand Fuel Pump Assembly) Coupling Shaft Inlet Filter Assembly (Argo-Tech Fuel Pump Assembly) Preformed Packing (Argo-Tech Fuel Pump Assembly) Inlet Filter Cover (Argo-Tech Fuel Pump Assembly)

(3)

If fuel pump (1) is being removed with engine installed, disconnect line from fitting installed in seal drain port (2). Suitably cap line connection and pump fitting.

(4)

Remove bolts (3) and release plate (4) from fuel transfer tube (5).

(5)

Withdraw transfer tube (5) from inlet port of fuel pump (1) and remove preformed packing (6). Suitably blank off inlet port of pump.

(6)

Disconnect and remove fuel outlet hose (7) and suitably cap hose connections and nipple (12) in fuel pump (1).

(7)

Support fuel pump (1) and remove nuts (8) and washers (9) which secure pump to accessory gearbox (11). Remove pump and gasket (10).

(8)

If fuel pump is being replaced, remove parts for reassembly on replacement pump: (a) Remove nipple (12) and preformed packing (13) from outlet port of fuel pump (1). Install blanking plug in outlet port. (b) Remove fitting and preformed packing from seal drain port (2) of fuel pump (1) and install blanking plug in drain port. If fitting is an elbow, note angular position before removal.

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8

9

11

10

1 12

13

7

2 15

14 6

4 3

5

C809 Removal/Installation of Fuel Pump Figure 202

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Key to Figure 202 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. B.

Fuel Pump Seal Drain Port Bolt Plate Fuel Transfer Tube Preformed Packing Fuel Outlet Hose Nut Washer Gasket Accessory Gearbox Nipple Preformed Packing Discharge Filter Cover Inlet Filter Cover

Installation of Fuel Pump (Ref. Fig. 202)

CAUTION: ALL TRACES OF GREASE MUST BE REMOVED FROM PUMP COUPLING SPLINES. ONLY ENGINE OIL IS TO BE USED AS A LUBRICANT. (1)

If a new fuel pump (1) is being installed, do an engine depreservation (Ref. Chap. 72-00-00, SERVICING): NOTE: 1. Depreservation is not required if removed fuel pump is being re-installed. NOTE: 2. Post-SB3148 fuel pump incorporates a new spur geardrive with longer splined shaft providing greater positive locking action between the coupling clip and gearshaft. (a) Remove blanking plugs from inlet and outlet ports of fuel pump (1). (b) Connect a supply of filtered fuel (PWC01-001), at an inlet pressure of 5 to 15 psig, to inlet port of pump. (c) Using a suitable turning device, rotate drive shaft of pump for approximately one minute until clear fuel is ejected from outlet port. (d) Remove rotation device, disconnect fuel supply from inlet port and blank off this port. (e) Assemble preformed packing (13) on nipple (12) and install nipple in fuel outlet port. Tighten nipple and torque 110 to 120 lb.in. Install suitable blanking cap.

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(f)

Assemble preformed packing on fitting retained from previous pump and install fitting in seal drain port (2) of fuel pump (1). Tighten fitting and torque to value recommended in appropriate aircraft maintenance manual. If fitting is an elbow, position at same angle noted during removal (Ref. 70-00-00, REMOVAL/INSTALLATION). Install suitable blanking cap.

(2)

Remove all traces of grease from gearshaft bore and pump coupling. Make sure that oil mist lubrication hole in gearshaft restrictor is clear (check diameter is 0.050 to 0.055 in. using No. 55 drill bit) and teflon insert is installed, then lubricate splines with engine oil.

(3)

Place gasket (10) on studs of accessory gearbox (11).

CAUTION: ENSURE DRIVE COUPLING (PRE-SB3139) IS CORRECTLY SECURED ON PUMP INTERNAL SPLINES BY LIGHTLY PULLING AND PUSHING BY HAND. COUPLING SHOULD BE SLIGHTLY LOOSE, BUT SHOULD NOT MOVE IN OR OUT. DO NOT REMOVE COUPLING FROM PUMP. CHECK PROTRUSION OF COUPLING FROM MOUNTING FACE OF PUMP; MEASUREMENT SHOULD BE 1.00 TO 1.12 INCHES. ENSURE COUPLING IS NOT DISPLACED DURING ASSEMBLY TO GEARBOX. PUMP COUPLINGS (POST-SB3139) FEATURE A STOP FLANGE AND MORE POSITIVE RETENTION; THERE SHOULD BE NO AXIAL MOVEMENT. (4)

Support fuel pump (1) and position on studs of accessory gearbox (11). As pump is pushed on, carefully engage splines of driveshaft with corresponding splines on gearshaft in accessory gearbox. Secure pump to gearbox with washers (9) and nuts (8). Tighten nuts and torque 85 to 95 lb.in.

(5)

Assembly preformed packing (6) in seal groove of fuel transfer tube (5).

(6)

Remove blanking plug from inlet port of fuel pump (1) and insert end of transfer tube (5). Make sure that preformed packing (6) is not displaced from seal groove of tube.

(7)

Position plate (4) around transfer tube (5) and secure to inlet port boss of fuel pump (1) with bolts (3). Tighten bolts and torque 36 to 40 lb.in. and lockwire each bolt, separately, through hole in plate.

(8)

Remove blanking caps from connection on fuel outlet hose (7) and from nipple (12). Connect hose to nipple but do not tighten until fuel control unit is installed; refer to step (10), following.

(9)

If installation of fuel pump (1) has been done with engine installed: (a) Remove blanking caps from seal drain line and from fitting in seal drain port (2) of fuel pump (1). (b) Connect line to drain fitting and tighten union to torque value recommended in appropriate aircraft maintenance manual.

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7.

(10)

Install fuel control unit (Ref. 73-20-00). Ensure interconnect hose which connects fuel pump outlet with fuel control unit inlet is installed correctly without twisting, then torque connection at each end 270 to 300 lb.in.

(11)

Install oil-to-fuel heater (Ref. 73-10-01).

Cleaning/Painting A.

B.

General (1)

Clean exterior surfaces of fuel pump with solvent (PWC11-027) or (PWC11-031). To prevent cleaning agent from entering unit, do not remove blanking caps and/or plugs.

(2)

Wipe surfaces dry with clean, lint-free cloths and/or compressed air to remove all residual solvent and contamination.

Cleaning of Inlet Filter Element (1)

Supply solvent (PWC11-027) or (PWC11-031), through a 10-micron filter at 30 psig, to outside of screen mesh. Rotate element during cleaning to ensure all areas of mesh screen are flushed. NOTE:

8.

Contaminants will usually collect inside screen mesh at area of cone section where attachment bolt head is located.

(2)

Reverse flush inlet filter element with solvent (PWC11-027) or (PWC11-031) to remove all contamination from screen mesh.

(3)

Remove residual contaminants and dry screen mesh using a blast of dry, clean, low-pressure air.

(4)

Examine filter element for cleanliness and, if necessary, repeat cleaning and reverse flushing operations until satisfactory.

Inspection/Check A.

General (1)

Examine mounting lugs for cracks and other defects. Cracks are not permissible; minor surface damage may be repaired.

(2)

Examine machined mounting faces for gouges, nicks, scores, scratches and similar surface defects which can damage gasket between pump and accessory gearbox and/or prevent correct mating of fuel control unit to pump. Particular attention should be paid to seal groove at bypass port between studs in mounting face for fuel control unit.

(3)

Examine bore of inlet port for damage on sealing surface.

(4)

Check studs for security and for damage to threads.

(5)

Examine helical coil inserts located in boss for fuel inlet for security and damage.

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(6)

Inspect seal drain port and fuel outlet port nipple for damage to threads.

(7)

Examine for leakage from seal drain port: (a) Coupling drive oil leaks from fuel pump drain should not exceed 3 cc per hour. If limits are exceeded, replace plain seal on accessory gearbox pad (Ref. 72-60-00, Removal/Installation). If leaks are still present and exceed limits, ship unit for overhaul. (b) Fuel leaks should not exceed 20 cc per hour. If limits are exceeded, send fuel pump to supplier. NOTE:

(8)

If limit is exceeded, inspect FCU driveshaft bearing area for fuel contamination (Ref. 73-20-00).

Check Pre-SB3139 drive coupling for security. If coupling can be pulled easily from pump, internal retaining ring is unserviceable . Replace retaining ring as follows: (a) Pull drive coupling from drive gear splines. Remove and discard retaining ring. (b) Install new retaining ring in drive coupling. Make sure ring is pressed in with closed end first to prevent distortion and loss of retention ability. (c) Snap drive coupling over splines of drive gear and engage retaining ring. Pull on drive coupling to check that retaining ring is fully engaged.

(9)

B.

C.

Check installation of drive coupling Post-SB3139. Drive coupling features a stop flange and retaining ring to prevent pump decoupling; there should be no axial movement.

(10)

Examine splines on drive coupling for nicks, gouges and chips. Remove any sharp/raised edges.

(11)

Examine external surfaces of pump for corrosion and for general condition of anodic treatment.

(12)

Check for signs of leakage from joint between pump cover and pump housing. If leakage is evident, return for overhaul.

(13)

Check attachment of identification plate.

Inspection of Filter Elements (1)

Examine inlet filter element for damage and/or breaks in screen mesh.

(2)

Outlet filter is disposable and should be subjected only to examination for defects if life on part has not expired (Ref. 72-00-00, INSPECTION, Periodic Inspection).

Sundstrand Fuel Pump In-Situ Inspection (1)

Remove drain line and fitting from fuel pump drain port (Ref. Fig. 202).

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CAUTION: IF A COTTON SWAB OR SIMILAR DEVICE IS USED FOR THE FOLLOWING INSPECTION, CARE MUST BE TAKEN TO MAKE SURE NO FOREIGN MATTER REMAINS IN THE DRAIN PORT OR ASSOCIATED FITTINGS AND LINES. (2)

Insert a cotton swab, or equivalent, 1.0 to 1.5 in. deep into the drain port of the fuel pump (Ref. Fig. 203).

(3)

Angle the cotton swab (Ref. Fig. 203) and roll it inside the drain port to collect evidence of a possible reddish-brown deposit (iron oxide).

(4)

If no reddish-brown (iron oxide) stain is evident, the fuel pump may remain in service.

(5)

If a reddish-brown (iron oxide) stain is evident: (a) Remove fuel pump (Ref. Para. 6.). (b) Examine the input coupling shaft area of the pump face (Ref. Fig. 201) for residue from fretting corrosion (iron oxide deposit). If none is present, the pump may remain in service. (c) Evidence of corrosion residue indicates possible spline wear. Return the fuel pump to an approved overhaul facility. (d) Install a replacement fuel pump (Ref. Para. 6.).

9.

Approved Repairs A.

General (1)

Minor damage such as burrs, scores, scratches, nicks and similar surface defects may be removed with a fine stone and/or abrasive cloth (PWC05-061). Remove all sharp edges and high spots.

(2)

Clean up minor thread damage in seal drain port, and in fuel outlet port when adapter is removed, with a suitable Swiss file, or a 0.4375-20 UNJF-3B tap for drain port and 0.5625-18 UNJF-3B tap for outlet port.

(3)

Clean up minor thread damage on studs with a suitable Swiss file, or chase threads using a 0.250-28 UNF-3A die.

(4)

Blend out minor chips and nicks in edges of splines, using a hard Arkansas stone, to remove rough edges and high spots that could damage mating splines and prevent correct meshing.

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FUEL PUMP OUTLET FILTER

CAVITY TO BE INSPECTED

DRAIN PORT (DRAIN FITTING REMOVED)

C107468 Fuel Pump In-situ Inspection Figure 203

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(5)

Replace damaged or loose helical coil inserts, located in boss for fuel inlet, in accordance with Specification MS33537. Inserts must be coated on external threads with zinc chromate primer (PWC13-003) prior to installation. Remove tang of insert after installation. NOTE:

B.

Make sure that all areas are cleaned and corrosion-preventive treatment applied to aluminum surfaces after carrying out minor repairs. Do not allow filings to enter unit.

Removal of Corrosion (1)

Light surface corrosion may be removed from pump housing and cover using one of the two methods outlined in following text. Severe corrosion, indicated by surface etching, is cause for rejection of pump, which must be sent for overhaul. (a) Remove corrosion deposits by vapor blasting with abrasive grit (PWC05-167) or finer. Make sure areas adjacent to corrosion are masked to prevent damage. (b) Remove corrosion deposits using abrasive cloth (PWC05-101) and (PWC05-061). Remove as little base metal as possible to remove corrosion. (c) Apply anti-corrosion treatment to repaired area (Ref. Subpara. C.).

C.

Application of Surface Treatment (1)

The anti-corrosion finish on pump housing and cover may be repaired by a local application of chemical treatment solution (PWC05-166). This treatment must be used on areas where minor repairs have been done. Apply treatment, as follows: (a) Prepare surface by cleaning with solution (PWC11-038). Keep surface wetted with cleaning solution for one to five minutes. (b) Rinse with clean water to remove all traces of solution. WARNING: ALODINE SOLUTION IS EXTREMELY DANGEROUS. IT CONTAINS AN OXIDIZING INGREDIENT WHICH CAN CAUSE AN EXPLOSION IF IT COMES IN CONTACT WITH COMBUSTIBLE MATERIALS SUCH AS PAINTS AND SOLVENTS. (c) Apply solution (PWC05-166) to prepared surface by brush, swab or spray, and allow three to five minutes setting time. (d) Rinse with clean water to remove all traces of excess solution and allow surface to air dry. (e) Examine treated surface and check that repair area is completely covered. Reapply treatment as necessary.

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10.

Adjustment/Test A.

Procedure (1)

Do checks associated with Installation/Replacement of Fuel Pump (Ref. 71-00-00, ADJUSTMENT/TEST, Table 501).

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FUEL TUBES - DESCRIPTION AND OPERATION 1.

Description and Operation The fuel supply to the engine is directed from the fuel pump to the fuel control unit (FCU) through a flexible hose, while the metered fuel from the FCU to the flow divider and dump or purge valve is directed through stainless steel lines. The fuel hose assembly consists of a fluorocarbon plastic inner core with a stainless steel braiding and a fiberglass and synthetic rubber outer covering. The latter acts as a fireshield. Each end of the assembly is fitted with stainless steel fittings and coupling nuts. The two stainless steel delivery tube assemblies each consist of a preformed seamless tube with stainless steel end fittings. The front tube assembly has a coupling nut at the front end for connection to the flow divider and dump or purge valve and a bulkhead fitting at the rear end for attachment to the rear fireseal. The assembly is supported by loop clamps. The rear tube assembly has coupling nuts at each end for connection to the FCU at the rear and the bulkhead coupling of the front tube assembly at the front.

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FUEL TUBES - 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 suitable protective caps/covers over all disconnected tubes/lines and component openings.

C.

Lockwire unless otherwise specified shall comply with specification AMS5687, heat and corrosion resistant steel wire MS9226-03, 0.025 inch diameter, and will not be called out in instructions.

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

3.

Item No.

Name

PWC01-001 PWC11-027 PWC11-031

Oil, Engine Lubricating Solvent, Petroleum Cleaner, Engine

Special Tools Not Applicable

4.

Fixtures, Equipment and Supplier Tools Not Applicable

5.

Removal/Installation A.

Removal of Fuel Lines (Ref. Fig. 201) (1)

Interconnecting Hose - Fuel Pump to Fuel Control Unit (FCU). (a) Disconnect coupling nuts at each end of interconnecting flexible hose (2) and remove hose.

(2)

Fuel Pressure Primary Line - FCU to Flow Divider (No Transmitter). NOTE:

The following procedure describes line removal on an engine not equipped with a fuel flowmeter transmitter. Refer to step (3) for removal of airframe-supplied transmitter.

(a) Disconnect coupling nuts (1 and 4) connecting fuel pressure rear tube (3) to elbow fitting at FCU and bulkhead coupling (6) on rear fireseal. Remove tube.

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4

FUEL CONTROL UNIT 3

2 1

7

8

CENTER FIRESEAL

12

9

6

10

5

11

11

10

12

13 REAR FIRESEAL

14

PT6A-38, A-41 and A-42 (Pre-SB3288)

C1885

Removal/Installation of Fuel Lines (Without Transmitter) Figure 201

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Key to Figure 201 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14.

Coupling Nut Interconnecting Hose - FCU to Fuel Pump Fuel Pressure Rear Tube Coupling Nut Bulkhead Coupling Nut Bulkhead Coupling Fuel Pressure Front Tube Loop Clamp Loop Clamp Seal Retaining Plate Seal Retaining Plate Insulator Fuel Tube Seal Coupling Nut Fuel Flow Divider

(b) Remove self-locking nuts and bolts securing loop clamps (8 and 9) on fuel line to loop clamps on ignition lead. Move ignition lead away from fuel pressure front tube (7). Allow clamps to remain on tube. (c) Remove jam nut (5) securing bulkhead coupling (6) to rear fireseal. (d) Remove two self-locking nuts and bolts securing seal retaining plates (10), retaining plate insulation (11) and tube seals (12) to center fireseal. Remove split insulation and seals from tube. (e) Disconnect coupling nut (13) from elbow on flow divider and dump or purge valve (14). (f)

Remove front seal retaining plate (10) from tube over coupling nut (13).

(g) Withdraw bulkhead coupling (6) on front tube (7) from rear fireseal, manoeuvre and remove front tube rearward to clear center fireseal. (h) Remove rear seal retaining plate (10) from tube over coupling nut (14). (i) (3)

Cap exposed connections on FCU and flow divider valve.

Fuel Pressure Primary Line - FCU to Flow Divider (With Transmitter) (Ref. Fig. 202) NOTE:

The following procedure describes line removal on an engine equipped with an airframe-supplied fuel flowmeter transmitter, or with dummy spacer tube in lieu of transmitter.

(a) If engine is installed in airframe, make that electrical power is shut off. Remove electrical leads from fuel flowmeter transmitter (1).

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FUEL CONTROL UNIT

5 6 8 10

2 9

1

7

3 4

18

15

16

17

16

17

18

12

20

19

14 11 13

PT6A-41, A-42 (Post-SB3288) and A-42A

C6495B

Removal/Installation of Fuel Lines (With Transmitter) Figure 202

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Key to Figure 202 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20.

Fuel Flowmeter Transmitter (Airframe-supplied) Coupling Nut Coupling Nut Fuel Pressure Rear Tube Spacer Tube (Alternate to item 1.) Bolt Loop Clamp Fuel Pressure Center Tube Coupling Nut Coupling Nut Bulkhead Coupling Bolts Loop Clamps Fuel Pressure Front Tube Bolts Seal Retaining Plates Retaining Plate Insulation Tube Seals Coupling Nut Flow Divider and Dump or Purge Valve

(b) Note angular positioning of flowmeter transmitter for subsequent reassembly. NOTE:

A spacer tube (5) may be installed in lieu of transmitter.

(c) Disconnect coupling nuts (2) and (3) connecting fuel pressure rear tube (4) to FCU straight adapter and flowmeter transmitter (1) or spacer tube (5). Remove rear tube. (d) Remove bolt (6) and self-locking nut securing loop clamp (7) on fuel pressure center tube (8) at accessory gearbox oil temperature sensor boss. (e) Disconnect coupling nut (10) connecting fuel pressure center tube (8) to bulkhead coupling (11) on rear fireseal. (f)

Remove fuel pressure center tube (8) with flowmeter transmitter (1), or spacer tube (5), still attached. Disconnect coupling nut (9) on tube from transmitter or spacer tube on the bench.

(g) Remove self-locking nuts and bolts (12) securing loop clamps (13) on fuel line to loop clamp, on ignition lead and to straight coupling front tube (14). Allow clamps to remain on tube. (h) Remove jam nut securing bulkhead coupling (11) to rear fireseal.

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(i)

Remove two self-locking nuts and bolts (15) securing seal retaining plates (16), retaining plate insulation (17) and tube seals (18) to center fireseal. Remove split insulation and seals from tube.

(j)

Disconnect coupling nut (19) from elbow on flow divider and dump or purge valve (20).

(k) Remove front seal retaining plate (16) from tube over coupling nut (19). (l)

Withdraw bulkhead coupling (11) from rear fireseal, manoeuvre and remove front tube (14) rearward to clear center fireseal.

(m) Remove rear seal retaining plate (16) from tube over coupling nut (19). (n) Cap exposed connections on FCU and flow divider and dump/purge valve. B.

Installation of Fuel Lines (Ref. Fig. 201) (1)

Interconnecting Hose - Fuel Pump to FCU (a) Secure coupling nuts at each end of flexible hose (2) to fuel pump and FCU. Tighten coupling nuts, torque 170 to 200 lb.in. and lockwire. NOTE:

(2)

Check that hose fits snugly between FCU and fuel pump fittings without forcing or twisting, and that adequate clearances exist between hose and reve