Pratt & Whitney Canada: Overhaul Manual MANUAL PART NO. 3013243
Pratt & Whitney Canada: Overhaul Manual MANUAL PART NO. 3013243
Pratt & Whitney Canada: Overhaul Manual MANUAL PART NO. 3013243
OVERHAUL MANUAL
MANUAL PART NO. 3013243
CHAPTER CHAPTER
SECTION PAGE DATE SECTION PAGE DATE
LEP 1 Sep 10/2004 103 Nov 30/2001
2 Sep 10/2004 104 Nov 30/2001
3 Sep 10/2004 105 Nov 30/2001
4 Sep 10/2004 106 Nov 30/2001
5 Sep 10/2004 107 Nov 30/2001
6 Sep 10/2004 108 Nov 30/2001
109 Nov 30/2001
Contents 1 Sep 10/2004 110 Nov 30/2001
2 Sep 10/2004 111 Nov 30/2001
3 Sep 10/2004 112 Nov 30/2001
4 Sep 10/2004 113 Nov 30/2001
5 Sep 10/2004 114 Nov 30/2001
6 Sep 10/2004 115 Nov 30/2001
7 Sep 10/2004 116 Nov 30/2001
8 Sep 10/2004 117 Nov 30/2001
9 Sep 10/2004 118 Nov 30/2001
10 Sep 10/2004 119 Nov 30/2001
11 Sep 10/2004 120 Nov 30/2001
12 Sep 10/2004 121 Nov 30/2001
13 Sep 10/2004 122 Nov 30/2001
14 Sep 10/2004 123 Nov 30/2001
124 Nov 30/2001
72-00-00 1 Mar 05/2004 125 Nov 30/2001
Description and 2 blank Mar 05/2004 126 Nov 30/2001
Operation 3 deleted 127 Nov 30/2001
4 deleted 128 Nov 30/2001
5 deleted 129 Nov 30/2001
6 deleted 130 Nov 30/2001
7 deleted 131 Nov 30/2001
8 deleted 132 Nov 30/2001
9 deleted 133 Nov 30/2001
10 deleted 134 Nov 30/2001
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12 deleted 136 Nov 30/2001
13 deleted 137 Nov 30/2001
14 deleted 138 Nov 30/2001
15 deleted 139 Nov 30/2001
16 deleted 140 Nov 30/2001
141 Nov 30/2001
72-00-00 101 Nov 30/2001 142 Nov 30/2001
Disassembly-1 102 Jul 02/2004 143 Nov 30/2001
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CHAPTER CHAPTER
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144 Nov 30/2001 103 May 19/2000
145 Nov 30/2001 104 May 19/2000
146 Nov 30/2001 105 May 19/2000
147 Sep 10/2004 106 May 19/2000
148 Nov 30/2001 107 May 19/2000
149 Nov 30/2001 108 May 19/2000
150 Nov 30/2001 109 May 19/2000
151 Nov 30/2001 110 May 19/2000
152 Sep 10/2004 111 May 19/2000
153 Sep 10/2004 112 May 19/2000
154 blank Nov 30/2001 113 May 19/2000
114 May 19/2000
72-00-00 101 May 19/2000 115 May 19/2000
Disassembly-2 102 Jul 02/2004 116 blank May 19/2000
103 May 19/2000
104 May 19/2000 72-00-00 201 May 19/2000
105 May 19/2000 Cleaning 202 May 19/2000
106 May 19/2000 203 Feb 02/2001
107 May 19/2000 204 May 19/2000
108 May 19/2000 205 May 19/2000
109 May 19/2000 206 May 19/2000
110 May 19/2000 207 Feb 02/2001
111 May 19/2000 208 May 19/2000
112 May 19/2000
113 May 19/2000 72-00-00 301 Mar 05/2004
114 May 19/2000 Inspection 302 May 19/2000
115 May 19/2000 303 May 19/2000
116 May 19/2000 304 May 19/2000
117 May 19/2000 305 May 19/2000
118 May 19/2000 306 May 19/2000
119 May 19/2000 307 May 19/2000
120 May 19/2000 308 May 19/2000
121 May 19/2000 309 May 19/2000
122 May 19/2000 310 May 19/2000
123 May 19/2000
124 May 19/2000 72-00-00 401 Jul 02/2004
125 May 19/2000 Repair 402 Aug 16/2002
126 blank May 19/2000 403 Aug 16/2002
404 Jul 02/2004
72-00-00 101 May 19/2000 405 Aug 16/2002
Disassembly-3 102 Jul 02/2004 406 Aug 16/2002
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408 Aug 16/2002 519 Sep 10/2004
409 Aug 16/2002 520 Sep 10/2004
410 blank Aug 16/2002 521 Sep 10/2004
522 Sep 10/2004
72-00-00 501 Jul 02/2004 523 Sep 10/2004
Assembly-1 502 Jul 02/2004 524 Sep 10/2004
503 Jul 02/2004 525 Sep 10/2004
504 Jul 02/2004 526 Sep 10/2004
505 Jul 02/2004 527 Sep 10/2004
506 Jul 02/2004 528 Sep 10/2004
507 Jul 02/2004 529 Sep 10/2004
508 Jul 02/2004 530 Sep 10/2004
509 Jul 02/2004 531 Sep 10/2004
510 Jul 02/2004 532 Sep 10/2004
511 Jul 02/2004 533 Sep 10/2004
512 Jul 02/2004 534 Sep 10/2004
513 Jul 02/2004 535 Sep 10/2004
514 Jul 02/2004 536 Sep 10/2004
515 Jul 02/2004 537 Sep 10/2004
516 blank Jul 02/2004 538 Sep 10/2004
539 Sep 10/2004
72-00-00 501 Sep 10/2004 540 Sep 10/2004
Assembly-2 502 Sep 10/2004 541 Sep 10/2004
502 A deleted 542 Sep 10/2004
502 B deleted 543 Sep 10/2004
503 Sep 10/2004 544 Sep 10/2004
504 Sep 10/2004 545 Sep 10/2004
505 Sep 10/2004 546 Sep 10/2004
506 Sep 10/2004 547 Sep 10/2004
507 Sep 10/2004 548 Sep 10/2004
508 Sep 10/2004 549 Sep 10/2004
509 Sep 10/2004 550 Sep 10/2004
510 Sep 10/2004 551 Sep 10/2004
511 Sep 10/2004 552 Sep 10/2004
512 Sep 10/2004 553 Sep 10/2004
513 Sep 10/2004 554 Sep 10/2004
514 Sep 10/2004 555 Sep 10/2004
515 Sep 10/2004 556 Sep 10/2004
516 Sep 10/2004 557 Sep 10/2004
517 Sep 10/2004 558 Sep 10/2004
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CHAPTER CHAPTER
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559 Sep 10/2004 507 Jul 02/2004
560 Sep 10/2004 508 blank Jul 02/2004
561 Sep 10/2004
562 Sep 10/2004 72-00-00 601 May 23/2003
563 Sep 10/2004 Fits and 602 May 23/2003
564 Sep 10/2004 Clearances 603 May 23/2003
565 Sep 10/2004 604 May 23/2003
566 Sep 10/2004 605 May 23/2003
567 Sep 10/2004 606 May 23/2003
568 Sep 10/2004 607 May 23/2003
569 Sep 10/2004 608 May 23/2003
570 Sep 10/2004 609 May 23/2003
571 Sep 10/2004 610 May 23/2003
572 Sep 10/2004
573 Sep 10/2004 72-00-00 701 Jul 02/2004
574 Sep 10/2004 Testing 702 Jul 02/2004
575 Sep 10/2004 703 Jul 02/2004
576 Sep 10/2004 704 Jul 02/2004
577 Sep 10/2004 705 Jul 02/2004
578 Sep 10/2004 706 Jul 02/2004
579 Sep 10/2004 707 Jul 02/2004
580 Sep 10/2004 708 Jul 02/2004
581 Sep 10/2004 709 Jul 02/2004
582 Sep 10/2004 710 Jul 02/2004
583 Sep 10/2004 711 Jul 02/2004
584 Sep 10/2004 712 Jul 02/2004
585 Sep 10/2004 713 Jul 02/2004
586 Sep 10/2004 714 Jul 02/2004
587 Sep 10/2004 715 Jul 02/2004
588 Sep 10/2004 716 Jul 02/2004
589 Sep 10/2004 717 Jul 02/2004
590 Sep 10/2004 718 Jul 02/2004
591 Sep 10/2004 719 Jul 02/2004
592 blank Sep 10/2004 720 Jul 02/2004
721 Jul 02/2004
72-00-00 501 Jul 02/2004 722 Jul 02/2004
Assembly-3 502 Jul 02/2004 723 Jul 02/2004
503 Jul 02/2004 724 Jul 02/2004
504 Jul 02/2004 725 Jul 02/2004
505 Jul 02/2004 726 Jul 02/2004
506 Jul 02/2004 726 A deleted
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726 B deleted 806 Aug 03/2001
727 Jul 02/2004 807 Aug 03/2001
728 Jul 02/2004 808 Aug 03/2001
729 Jul 02/2004 809 Aug 03/2001
730 Jul 02/2004 810 Aug 03/2001
731 Jul 02/2004
732 Jul 02/2004 72-00-00 901 May 23/2003
733 Jul 02/2004 Storage 902 May 23/2003
734 Jul 02/2004 Instructions 903 May 23/2003
735 Jul 02/2004 904 May 23/2003
736 Jul 02/2004 905 May 23/2003
737 Jul 02/2004 906 May 23/2003
738 Jul 02/2004 907 May 23/2003
739 Jul 02/2004 908 May 23/2003
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757 Jul 02/2004 926 May 23/2003
758 Jul 02/2004 927 May 23/2003
759 Jul 02/2004 928 May 23/2003
760 Jul 02/2004 929 May 23/2003
930 May 23/2003
72-00-00 801 Aug 03/2001 931 May 23/2003
Troubleshooting 802 Aug 03/2001 932 May 23/2003
803 Aug 03/2001 933 May 23/2003
804 Aug 03/2001 934 May 23/2003
805 Aug 03/2001
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CHAPTER
SECTION PAGE DATE
72-00-00 1301 May 19/2000
Light Overhaul 1302 May 19/2000
1303 May 19/2000
1304 May 19/2000
1305 May 19/2000
1306 May 19/2000
1307 May 19/2000
1308 May 19/2000
1309 May 19/2000
1310 May 19/2000
1311 May 19/2000
1312 May 19/2000
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MANUAL PART NO. 3013243
TABLE OF CONTENTS
SUBJECT PAGE
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TABLE OF CONTENTS
SUBJECT PAGE
A. General 502
B. Checks 502
ENGINE - FITS AND CLEARANCES 72-00-00
1. General 601
2. Terms and Symbols 601
A. Inspection Frequency Requirement (IFR) 601
B. Dimensional Checks 601
C. Torque Limits 602
D. Index of Fits and Clearances 602
ENGINE - TESTING 72-00-00
1. General 701
2. Consumable Materials 701
3. Special Tools 701
4. Fixtures, Equipment and Supplier Tools 702
5. Engine Test Equipment 703
A. General 703
6. Engine Test Requirements 703
7. Symbols 704
8. Preparation for Test 705
A. Engine/Propeller Controls 705
B. Install Test Equipment 705
C. Removal from Assembly Stand and Install in Propeller Test
Stand 707
D. Installation of Propeller 707
E. Remove from Assembly Stand and Install on Dynamometer
Stand - (PWC32478) Mounting Arrangement 709
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SUBJECT PAGE
A. Procedure 912
9. Removal of Engine From Container 912
A. Procedure 912
B. Removal of Engine from Type I Fiberboard Container 913
C. Removal of Engine from Type II Fiberboard Container 913
D. Removal of Engine from Type III Fiberboard (reinforced)
Container 918
E. Removal of Engine from Metal Container 918
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MANUAL PART NO. 3013243
TABLE OF CONTENTS
SUBJECT PAGE
A. Procedure 1303
5. Dropped Engine 1303
A. Procedure 1303
B. General 1307
6. Unusual Oil Conditions - General 1307
A. General 1307
B. Metal Contaminants 1307
C. Particles 1307
D. Metal Chip 1307
E. Examples Of Possible Contamination 1307
F. Unusual Oil Conditions (Part A) 1307
G. Unusual Oil Conditions (Part B) 1308
H. Rectify Part A 1308
I. Rectify Part B 1309
7. Contamination by Fire Extinguishing Agents 1309
A. General 1309
B. Engines Contaminated by Fire Extinguishing Agents 1309
C. Removal of Residual Deposits and Corrosion Repair 1310
8. Power Section 1310
9. Engine Components 1310
A. General 1310
10. Accessories 1311
11. External Components 1311
A. Problems 1311
B. General 1311
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MANUAL PART NO. 3013243
Refer to applicable Engine Maintenance Manual for Engine Specifications and Leading
Particulars.
Refer to applicable Engine Maintenance Manual for Engine Stations, Flanges and Bearings.
1. General
A. Personnel engaged in the disassembly of the engine should make frequent reference to
the Introduction sections of this manual to familiarize themselves with general overhaul
procedures (Ref. INTRODUCTION, Outline of Overhaul Procedures).
B. On receipt of an engine for overhaul, remove air inlet screen and examine for foreign
object damage (F.O.D.) in compressor rotor assembly. Inspect for external damage,
burning, corrosion or signs of leakage. Record all observations made at this inspection
to provide reference during disassembly of engine, taking special notice of any
discrepancy which might not be apparent after cleaning. Tag all affected parts to identify
nature of fault. After removal from engine, submit affected parts to detailed inspection
before cleaning.
C. During inspection of engine, check that all externally mounted parts and accessories are
correctly assembled; loose and/or unattached components usually indicate these parts
have been replaced due to a previous unserviceability. Record all discrepancies and check
against data sheets received with engine for information relating to unserviceabilities
encountered during service.
D. Overhaul facilities may find it more expedient to remove certain parts before others, so
disassembly sequences given in the text need not be strictly adhered to. Instructions for
removal of some standard parts, such as loop clamps and similar attaching hardware,
may be repeated in areas hardware such parts support more than one component.
E. Cover all openings as soon as possible after removal of external parts and accessory
units. Place each component in a separate polyethylene bag, or dust-proof container,
and store on suitable racks until required for overhaul. Ensure that parts are segregated
during storage to prevent damage by impact.
G. To prevent damage to seal grooves and lands, use plastic spatulas when removing
preformed packings. Damage in these areas can cause improper seating and result
in subsequent leakage.
H. Discard all preformed packings, packing retainers, back-up rings, tabwashers, cotterpins
and gaskets immediately after removal to prevent possible reuse of these items.
2. Consumable Materials
Not Applicable
3. Special Tools
The special tools listed below are used in the following procedures.
Not Applicable
A. General
(1) Place suitable oil container and drip pan under engine.
(2) Remove oil drain plug Pre-SB1217, or cover and magnetic chip detector
Post-SB1217 (1) from bottom of propeller reduction gearbox.
(3) Pre-SB1482: Remove cotterpin (3) and straight pin (2) from bottom of compressor
inlet case. Remove drain plug 94) using puller (PWC30077).
(4) Remove drain plug (5) from 6 o’clock position on rear face of accessory gearbox.
(5) Allow all residual oil to drain from engine, then reinstall drain plugs and chip detector.
6. Removal of Externals
(1) Remove two bolts and washers, and separate front pressure oil elbow (16) from
reduction gearbox front housing and transfer tube (15). Discard preformed packing
(17).
(2) Remove two self-locking nuts, washers and Dee-head bolts securing external
coupling (13) to flange C.
(3) Separate front tube (15) from external coupling (13). Remove preformed packings
(14) from tube.
(4) Withdraw center tube (11) from rear tube (6). Remove and discard preformed
packing (12).
(5) Remove bolts and self-locking nuts that secure seal retaining plate assemblies (10)
and (5), and seals (9) and (4) to center and rear fireseal mount rings, respectively.
(6) Remove two bolts and washers that secure elbow (1) to compressor inlet case.
(7) Remove two bolts securing centre adapter flange of tube (6) to gas generator case
boss. Separate elbow from tube (6) and discard preformed packing (2).
(8) Separate adapter flange, and spacers (8), Pre-SB1169 from gas generator case
and withdraw transfer tube (6) from center and rear fireseals.
(9) Remove preformed packings (3 and 7), seal retaining plate assemblies (5 and 10),
insulation plates (18 and 19) and seals (4 and 9) from rear transfer tube (6).
(1) To improve scavenge of No. 2 bearing, an oil scavenge tube assembly of larger
diameter, together with new seals and seal retaining plates Post-SB1153 are
used. Disassemble oil tube and associated parts.
(a) Remove bolts securing front flange (3) of No. 2 bearing scavenge tube (11) to
gas generator case.
(b) Remove four bolts and self-locking nuts and seal retaining plates (4), seal
retaining plate assemblies (5 and 7) and seals (6) from tube.
(c) Remove bolts securing rear flange (10) and support bracket (8) to compressor
inlet case.
(d) Withdraw scavenge tube from bosses on gas generator and compressor inlet
cases, and remove tube rearward through hole in rear fireseal.
(e) Remove bolts and self-locking nuts, and separate support bracket (8) from rear
fireseal.
(f) Remove preformed packings (1 and 9) from flanges of scavenge tube. Remove
gasket (2) from front flange (3).
(1) Remove bolts and washers securing front elbow (5) to propeller reduction gearbox.
(2) Remove bolts, washers and self-locking nuts securing coupling (8) to flange C.
(3) Remove bolts and self-locking nuts securing seals (12), insulations (11) and retaining
plates (18) to rear fireseal mount ring.
(4) Remove bolts and self-locking nuts securing seals (14) and retaining plates (13) to
center fireseal mount ring.
(5) Withdraw front elbow (5) from short tube (2) and front tubes (7). Remove preformed
packing (3) and sleeve seal (4) from elbow.
A
C
B
2 3
4
5 VIEW B
PRE−SB1482
VIEW A
POST−SB1217
PRE−SB1217
VIEW C
1
C8577A
Location of Oil Drain Plugs and Chip Detector
Figure 101
(6) Withdraw short transfer tube (2) from reduction gearbox, and remove two preformed
packings (1) from tube.
(7) Withdraw front tubes (7) from coupling (8). Remove preformed packings (6) from
each tube.
(8) Remove coupling (8) from two rear transfer tubes (10).
(9) Remove rear tubes (10) from external scavenge pump ports, and carefully withdraw
tubes from center and rear fireseal mount rings. Remove seals, insulations and
retaining plates during withdrawal of tubes from mount rings.
(11) Disconnect coupling nut of scavenge oil hose (15) at adapter assembly on
accessory gearbox. Remove bolts and separate hose flange from accessory gearbox.
Bracket (17) supporting fuel control (PT6A-27/28 engines); will be released.
Remove preformed packing (16).
D. Removal of Electrical Connector from Heated Pneumatic Lines (Ref. Figs. 106 through
112)
(1) Remove self-locking nuts, washers, and screws (1, Fig. 105) securing electrical
connector (2) to bracket (1), and withdraw connector from bracket.
(2) Remove clamp screws (10) and separate half-clamps from bell end fitting (9).
(3) Unscrew bell end fitting (9) from flange-mounted connector shell (6) and slide fitting
and cable sleeve (13) down electrical wires. Do not allow wires to twist while
unscrewing bell end fitting and ensure that braiding is not pulled back on wires.
(4) Slide nylon sleeve (8) and rubber insulator (7) back over wires to expose soldered
connections between wires and pins (14).
(5) Using suitable soldering iron, unsolder wires from pins (14).
(6) Carefully pull wires through rubber insulator (7) and nylon sleeve (8).
(7) Remove bell end fitting (9) and cable sleeve (13) from electrical cables (4) and (5).
2
INLET CASE 3
8 3
GAS GENERATOR
1 CASE
6
5 12
REAR FIRESEAL 18
MOUNT RING
5 18
9
11
10 17
19
CENTER FIRESEAL
MOUNT RING
19
10
REDUCTION
GEARBOX
14 16
15
FLANGE C
14
13
C6980A
Pressure Oil Tubes
Figure 102
1. Elbow
2. Preformed packing
3. Preformed packing
4. Seals
5. Retaining Plates
6. Rear Tube Post-SB1169
Pre-SB1169
7. Preformed packing
8. Alignment Spacers Pre-SB1169
(Not used with Post-SB1169)
9. Seals
10. Retaining Plates
11. Center Tube Post-SB1169
12. Preformed packing
13. Coupling
14. Preformed packings
15. Front Tube
16. Elbow (Front)
17. Preformed Packing
18. Insulation Plate
19. Insulation Plate
E. Compressor Delivery Air Line Installations (Ref. Figs. 106 through 112)
(a) Remove self-locking nuts securing loop clamp (10), clamp and rubber grommet
(11) and electrical receptacle bracket (8) to studs on flange G. Withdraw
bracket and spacer (7) from studs. Tie spacer to bracket to prevent loss of part.
(b) Disconnect coupling nuts securing pneumatic insulated tube (27) and pneumatic
heated tube (6) to temperature compensator (15) or compensator body (14).
(c) Remove two nuts securing temperature compensator (15) or compensator body
(14) and two nuts and bolts (30) securing seal retaining plates (22), insulation
(23) and seals (24) to rear fireseal.
9 10
8
11
6
1 5
4 4
2
7
3 6
REAR FIRESEAL
MOUNT RING
C7463
No. 2 Bearing Scavenge Oil Tube
Figure 103
1. Preformed Packing
2. Gasket
3. Front Flange
4. Seal Retaining Plate
Pre-SB1173/Post-SB1173
5. Seal Retaining Plate Assembly
Pre-SB1153/Post-SB1153
6. Seal Pre-SB1153/Post-SB1153
7. Seal Retaining Plate Assembly
Pre-SB1153/Post-SB1153
8. Rear Fireseal Mount Ring Support Bracket
9. Preformed Packing
10. Rear Flange
11. No. 2 Bearing Scavenge Tube
Pre-SB1153/Post-SB1153
PT6A-27/28 Engines (Ref. SB1153)
PT6A-21 Engines (Basic)
(e) Disconnect coupling nut securing pneumatic heated tube (6) to metered
elbow (4) or (5) on fuel control unit. Remove pneumatic heated tube (6) and
electrical cable.
(f) Disconnect coupling nut securing pneumatic heated tube (6) to metered elbow
(4) or (5) on fuel control unit. Remove pneumatic heated tube (6) and electrical
cable.
NOTE: Angle bracket (29) supporting ignition cable (spark ignition only) will
be released at this stage.
(g) Remove straight nipple (12) and preformed packing (13) from compensator or
compensator body.
(2) Remove pneumatic tubes from PT6A-27/28 (Post-SB1123, Stnd. Mod.), and all
PT6A-21 Engines: (Ref. Fig. 107)
(a) Remove self-locking nuts securing loop clamp (1), loop clamp and rubber
grommet (12) and electrical receptacle bracket to studs on flange G.
Withdraw bracket and spacer from studs. Tie spacer to bracket to prevent loss
of part.
(b) Remove self-locking nut and bolt securing loop clamp (9) to angle bracket (10).
(c) Remove two self-locking nuts and bolts, at rear fireseal mount ring securing
seal retaining plates (3) and (6), insulations (4), seals (5) and angle bracket
(10). Remove seal retaining plate (6) (Post-SB1162).
A B C
16
17
C
15
REAR FIRESEAL
12 MOUNT RING
10
13
CENTER FIRESEAL
MOUNT RING
9
11
B
14
3
9
4
5
6
8
1
7
A 6
C7464
External Scavenge Oil Tubes
Figure 104
1. Preformed Packing
2. Transfer Tube
3. Preformed Packing
4. Sleeve Seal
5. Front Scavenge Oil Transfer Elbow
6. Preformed Packing
7. Front Transfer Tube
8. External Scavenge Oil Transfer Coupling
9. Preformed Packing
10. Rear Transfer Tubes
11. Insulation
12. Seals
13. Retaining Plates
14. Seals
15. Scavenge Oil Hose
16. Preformed Packing
17. Bracket (Support Starting Flow Control)
(PT6A-27/28 Engines)
(d) Disconnect coupling nut of pneumatic heated tube (11) at fuel control unit elbow.
Remove two bolts and separate tube flange and gasket (8) from gas generator
case.
NOTE: Angle bracket supporting ignition cable (spark ignition only) will be
released at this stage.
(e) Remove seal retaining plate (3), insulations (4) and seals (5) from tube (11).
(f) Withdraw tube assembly (11) and cable (2) from slot in rear fireseal mount ring.
(3) Remove pneumatic tubes and air filter from PT6A-27/28 (Post-SB1205) engines, as
follows: (Ref. Fig. 108).
(a) Remove self-locking nuts securing loop clamp (1), loop clamp and rubber
grommet (14) and electrical receptacle bracket to studs on flange G.
Withdraw bracket and spacer from studs. Tie spacer to bracket to prevent loss
of part.
(b) Disconnect coupling nuts of pneumatic heated tube (3) at fuel control unit
elbow and air filter (6), and remove tube with cable (2).
(c) Remove two self-locking nuts and bolts at rear fireseal mount ring, and release
seal retaining plates (7) and (10), insulations (8) and seals (9). Remove seal
retaining plate (10) (Post-SB1162).
REAR FIRESEAL
3
2
4
A
B
FLANGE G 5
A
FLANGE G
FOR ENGINE/S.B. APPLICABILITY REFER TO TABLE 101 OR 501
D A
12
6
C B
11
ELECTRICAL SCHEMATIC
11
6 7 8 9 16
12 5
14 10
13
VIEW ON ARROW B
EXPLODED
C10413
Electrical Connector for Heated Pneumatic Lines
Figure 105 (Sheet 1 of 2)
1. Screw
2. Bracket
3. Electrical Connector
4. Governor Pneumatic Heated Tube Electrical Cable
5. Compressor Delivery Pneumatic Heated Tube Electrical
Cable (Sheet 1)
Compressor Delivery Pneumatic Heated Tube Electrical
Cable and
Compressor Delivery Pneumatic Heated Center Tube
Electrical Cable (Sheet 2)
6. Connector Shell
7. Rubber Insulator
8. Nylon Sleeve
9. Bell-end Fitting
10. Clamp Screw
11. Element in Governor Pneumatic Heated Tube
12. Element in Compressor Delivery Pneumatic Heated Hose
13. Cable Sleeve
14. Pins
15. Element in Compressor Delivery Pneumatic Heated Center
Tube
16. Loop Clamp and Rubber Grommet
REAR FIRESEAL
3
2
4
B
A 5
FLANGE G
DETAIL A
FLANGE G
15
D A
12
6
C B
11
15
ELECTRICAL SCHEMATIC
12
6 7 8 9
16
10
4
11
14 13
EXPLODED VIEW ON ARROW B
C8495C
Electrical Connector for Heated Pneumatic Lines
Figure 105 (Sheet 2)
(d) Disconnect coupling nut of pneumatic insulated tube (13) at forward end of air
filter (6). Remove two bolts and separate tube flange and gasket (12) from gas
generator case.
NOTE: Angle bracket (11) supporting ignition cable (spark ignition only) will
be released at this stage.
(e) Withdraw tube assembly (13) from slot in rear fireseal mount ring and remove
seal retaining plates (7) insulations (8) and seals (9).
(f) Remove two self-locking nuts securing support bracket (5) to studs on flange G
and remove bracket (5) and air filter (6). Remove two self-locking nuts securing
support bracket (5) to studs on flange G and remove bracket (5) and air filter
(6).
(g) Remove locknut (4) securing air filter (6) to support bracket (5) and remove air
filter.
(4) Remove pneumatic tubes and bowl-type filter from PT6A-28 (Post-SB1290)
engines: (Ref. Fig. 109)
17
16
9 10 15
1 13
7 12
2 11
3
4 5 PRE−SB1123 REAR FIRESEAL
26
25
30
22
23
24
1. Preformed Packing
2. Back-up Ring
3. Locknut
4. Elbow (Pre-SB1123)
5. Metered Elbow (Post-SB1123, Alternative Mod.)
6. Compressor Delivery Pneumatic Heated Tube
7. Spacer
8. Electrical Receptacle Bracket
9. Electrical Receptacle
10. Loop Clamp
11. Loop Clamp and Rubber Grommet
12. Straight Nipple
13. Preformed Packing
14. Compensator Body
(Post-SB1123, Alternative Mod)
15. Temperature Compensator
(Pre-SB1123)
16. Insulation
17. Seal
18. Preformed packing
19. Back-up Ring
20. Locknut
21. Elbow
22. Retaining Plate
23. Insulation
24. Seal
25. Insulation
26. Retaining Plate and Insulation
27. Compressor Delivery Pneumatic Insulated Tube
28. Gasket
29. Angle Bracket (Engines with spark igniters only)
30. Bolt 0.190-32 UNJF x 0.625 inch. - Alternative: Bolt
0.190-32 IUNJF x 0.750 inch (Ref. IPC).
(a) Remove self-locking nuts (5) securing loop clamp (7) and electrical
receptacle bracket (6) to studs on flange G; withdraw spacer and bracket from
studs and tie spacer to bracket to avoid loss of part.
3
4
5 5
4 6 GAS GENERATOR 8
3 CASE
7
2
1 12
FUEL CONTROL
UNIT ELBOW
ASSY. REAR FIRESEAL
MOUNT RING
9
11 10
FLANGE G
PT6A-27/28 Engines (Post-SB1123, Stnd Mod) and all PT6A-21 Engines C7466A
Compressor Delivery Air Line Installation
Figure 107
1. Loop Clamp
2. Compressor Delivery Pneumatic Heated Tube Electrical
Cable
3. Seal Retaining Plate
4. Insulation
5. Seal
6. Seal Retaining Plate
7. Angle Bracket (engines with spark ignition only)
8. Gasket
9. Loop Clamp
10. Angle Bracket
11. Compressor Delivery Pneumatic Heated Tube
12. Loop Clamp and Rubber Grommet
(b) Remove one self-locking nut and bolt (9) to release and remove loop clamp and
rubber grommet (8) from P3 air filter (15).
(c) Disconnect heated tube (16) (Pre-SB1314or Post-SB1314) coupling nuts from
FCU elbow (17) and P3 air filter (15) elbow; remove tube with cable (2).
(d) Disconnect coupling nut of insulated tube (12) from heated air pressure tube
(1) (Pre-SB1314or Post-SB1314) at plate (10).
(e) Remove two bolts and separate tube (12) flange with gasket (13) from gas
generator case and remove tube.
NOTE: Angle bracket (14) supporting ignition cable (spark ignition only) will
be released when flange bolts are removed.
(f) Disconnect heated air pressure tube (1) (Pre-SB1314 or Post-SB1314) from
elbow on P3 air filter (5); remove locknut (11) from other end at plate (10) and
withdraw tube assembly together with cable (3).
(g) Remove remaining self-locking nut, washer and bolt (9) and separate P3 air
filter (15) from bracket (4).
(h) Remove two self-locking nuts and bracket (4), and two self-locking nuts, bolts
and plate (10).
ELECTRICAL RECEPTACLE
BRACKET
8 7
9
10
GOVERNOR AIR PRESSURE HEATED
TUBE ELECTRICAL CABLE 8 9
1
7
2
14
FUEL CONTROL
UNIT ELBOW ASSEMBLY
6
REAR FIRESEAL
5 MOUNT RING
FLANGE G
4
3
12 GAS GENERATOR
CASE
11
13
1. Loop Clamp
2. Compressor Delivery Pneumatic Heated
Tube Electrical Cable
3. Compressor Delivery Pneumatic
Heated Tube
4. Locknut
5. Support Bracket
6. Air Filter
7. Seal Retaining Plate
8. Insulation
9. Seal
10. Seal Retaining Plate
11. Angle Bracket (engines with spark ignition only)
12. Gasket
13. Compressor Delivery Insulated Tube
14. Loop Clamp and Rubber Grommet
(a) Remove self-locking nut and bolt (19) to release loop clamp and rubber grommet
from angle bracket (17) (Post-SB1330). Remove loop clamp and rubber
grommet.
(b) Disconnect tube (15) coupling nuts from FCU elbow (16) and P3 air filter (14)
elbow; remove tube with cable (3).
(c) Disconnect tube (11) coupling nut from tube (1) at plate (9).
(d) Remove two bolts and separate tube (11) flange with gasket (12) from gas
generator case and remove tube.
NOTE: Angle bracket (13) supporting ignition cable (spark ignition only) will
be released when flange bolts are removed.
(e) Disconnect heated center tube (1) from elbow on P3 air filter (14); remove
locknut (10) from other end at plate (9) and withdraw tube assembly together
with cable (2).
(f) Remove self-locking nuts, bolts (8), angle bracket (17) and washer
(Post-SB1583engines, remove self-locking nuts, washers, bolts (23), angle
bracket and washers). Separate P3 air filter (14) from bracket (4).
(g) Remove self-locking nuts (5) securing electrical receptacle bracket (6) and P3
air filter bracket (4) to studs on flange G; withdraw spacers (18) and (20) and
brackets from studs. To avoid loss tie spacer to bracket (6).
ELECTRICAL RECEPTACLE
6 BRACKET
8
9
10
11
5
2 3
1
15
17
12
16 13
14
IGNITION CABLE
(6) Remove pneumatic tubes and bowl type filter PT6A-27/28 engines
(Post-SB1343): (Ref. Fig. 111).
(a) Remove self-locking nuts (6) securing loop clamp (3) and electrical receptacle
bracket (7) to studs on flange G; withdraw spacer and bracket from studs and
tie spacer to bracket to avoid loss of part.
(b) Remove one self-locking nut, bolt (17) and washer (Post-SB1583 engines,
remove one self-locking nut, Tee bolt (21) and two washers) to release and
remove loop clamp and rubber grommet (16) from P3 air filter (18).
(c) Disconnect heated hose (19) from FCU elbow (20) and P3 air filter (18);
remove tube with cable (2).
(d) Disconnect insulated tube (10) coupling nut from tube (1) at plate (15).
(e) Remove two bolts (12) and separate tube (10) flange with gasket (11) from gas
generator case and remove tube.
NOTE: Angle bracket (13) supporting ignition cable (spark ignition only) will
be released when flange bolts are removed.
(f) Disconnect insulated center tube (1) from elbow on P3 air filter (18); remove
locknut (14) from other end at plate (15) and withdraw tube.
(g) Remove remaining self-locking nut, washer and bolt (17) (Post-SB1583
engines, remove remaining self-locking nut, Tee bolt (21) and two washers).
Separate P3 air filter (18) from bracket (4).
(h) Remove self-locking nuts (8), bolts (9) and plate (15) and self-locking nuts,
bracket (4) and spacers (5), tie spacers to bracket to avoid loss.
(7) Remove pneumatic hoses, tube and bowl type filter from PT6A-27/-28 engines
(Post-SB1448), as follows (Ref. Fig. 112):
(a) With electrical cables (14 and 15) disconnected (Ref. Para. D. preceding),
disconnect rear heated hose assembly (16) from FCU elbow (17) and P3
filter assembly (4) outer elbow (18).
(b) Disconnect center heated hose assembly from elbow (12) on rear fireseal and
P3 filter assembly (4) inner elbow (19).
(c) Loosen coupling nut on insulated tube (6) at rear fireseal mount ring and
remove bolts (8) on flange end mounted to gas generator case boss. Disconnect
coupling nut, remove tube and gasket (7). Discard gasket.
(d) Remove self-locking nuts from bolts (3) and P3 filter assembly from bracket
assembly (1) mounted on flange G.
(f) Remove self-locking nuts and bolts, tube retaining plate (10) and seal retaining
plate (9).
(1) Remove self-locking nut and loop clamp (2) from top mounting stud of fuel pump.
(2) Remove self-locking nuts and bolts at rear fireseal mount ring, and release seal
retaining plates (5 and 8), insulations (6), and seals (7); remove slotted retaining
plate (8) (Post-SB1162).
(3) Disconnect heated tube (4) from elbow (1) and coupling (9); withdraw tube
assembly and cable (3) from slot in rear fireseal mount ring.
(4) Remove self-locking nut and bolt securing loop clamp (13) to angle bracket (12) at
flange C.
(5) Disconnect coupling nuts of pneumatic front tube (11) at nipple (14) and bulkhead
coupling (9); remove tube assembly, seal retaining plates (5), insulations (6) and
seals (7).
(6) Remove locknut (10) and separate coupling (9) from center fireseal mount ring.
G. Fuel Tubes and Flexible Hoses (PT6A-21 Engines) (Ref. Fig. 114)
(1) Disconnect coupling nuts at each end of flexible fuel hose (2) from oil-to-fuel heater
and fuel pump. Remove tube and cap all openings.
(2) Disconnect coupling nuts at each end of flexible fuel hose (1) from fuel pump and
fuel control unit (FCU). Remove tube and cap all openings.
(3) For Pre-SB1471 Engines: Disconnect coupling nuts at each end of fuel tube (3)
from FCU and bulkhead coupling (6) at fuel pressure tube bracket (5). Remove
tube and cap all openings.
(a) Disconnect coupling nuts at each end of fuel tube (3) from FCU and tube
assembly (24) or fuel flowmeter (25) (if fitted).
(b) Remove nut (26) and bolt (27) which secures loop clamp (28) to bracket (29).
(d) Separate tube assembly (24) or fuel flowmeter (25) from tube assembly (30).
(5) Remove jam nut (4) which secures fuel pressure tube bracket (5) to rear fireseal
mount ring.
(6) Remove self-locking nuts (11) from bolts (10) at rear fireseal mount ring, and
remove fuel line seals (9), retaining plates (7) and insulation (8) from tube.
(7) Remove self-locking nuts (19) from bolts (18) at center fireseal mount ring, and
remove fuel line seals (17), retaining plates (15) and insulation (16) from tube.
(8) Disconnect coupling nuts at each end of fuel tube (20) from bulkhead coupling (6)
at fuel pressure tube bracket (5) and elbow fitting on flow divider valve.
(9) Remove self-locking nut (13) and bolt (14) securing loop clamp (12) and washer
(21) to support bracket (22) at rear of fuel drain valve.
(10) Remove nuts and bolts securing fuel line loop clamp (12) to similar loop clamp on
ignition cable and loop clamp (23) (glow plug ignition only).
H. Fuel Tubes and Flexible Hoses (PT6A-27/-28 Engines) (Ref. Fig. 115)
(1) Disconnect coupling nuts of fuel hose (6) at elbow (5) and straight nipple (7);
remove hose.
18 7
6 8
A
5 14
19
20
7 8
17
POST−SB1378
4
14
TO FUEL 10
CONTROL 16 9
12
15
1 3
2
11 13
22
22
21
22
4
14
DETAIL A 23
POST−SB1583
(2) Disconnect coupling nuts of fuel hose (9) at straight nipple (8) and elbow (10); remove
hose.
NOTE: Item (9) is not fitted (i.e. airframe-supplied) on some PT6A-28 engine
models.
(3) Disconnect coupling nuts of fuel bypass tube (3) at connector (1), and tee (11);
remove tube.
(4) Disconnect fuel pressure tube (4) at adapter (2) and elbow (14), and remove tube
assembly.
(5) Remove self-locking nuts and bolts (four places) on both center and rear fireseal
mount rings, and release seal retaining plates (15), insulations (16) and seals (17).
(6) Remove two self-locking nuts and bolts to release backing plate (25) and loop clamps
(24) on fuel tube (20) and (21) and ignition cables.
(7) On engines with glow plug ignition (Pre-SB1196), remove two self-locking nuts and
bolts to release loop clamps (26) on fuel tubes (20 and 21) and ignition cables.
6 9
2
8
5
4
1 A
PRE−SB1583
14
15
17
16
19 18 11
12
4
13
21 10
IGNITION CABLE
22
16
FLANGE G
18 22 23
DETAIL A
POST−SB1583
(8) Remove two self-locking nuts, bolts and spacing washers (if fitted), to release
loop clamps (18) and (19) from support bracket attached to rear drain valve on
gas generator case.
(9) Disconnect fuel pressure tube (20) at straight nipple (12) and elbow (22).
(10) Withdraw tube (20) through center and rear fireseal mount rings and remove seal
retaining plates, insulations and seals.
(11) Disconnect fuel pressure tube (21) at nipple (13) and elbow (23).
(12) Withdraw tube through center and rear fireseal mount rings, and remove seal
retaining plates, insulations and seals.
(1) Remove glow plug ignition cables (Pre-SB1196) (Ref. Fig. 116):
FLANGE G
1
19
7
18
3
6
17 9 5
4
16
8
15
REAR FIRESEAL
14 MOUNT RING
11
12 10
13
1. Bracket Assembly
2. Electrical Connector
3. Bolt
4. P3 Air Filter Assembly
5. Locknut
6. Insulated Tube
7. Gasket
8. Bolt
9. Plate, Seal Retaining
10. Plate, Tube Retaining
11. Washer
12. Elbow
13. Center Heated Hose Assembly
14. Electrical Cable, Center Hose
15. Electrical Cable, Rear Hose
16. Rear Heated Hose Assembly
17. Elbow, FCU
18. Outer Elbow
19. Inner Elbow
(b) Remove self-locking nuts and bolts securing loop clamps (4) to angle brackets
(2) on center fireseal mount ring (14) and integral brackets on gas generator
case (Ref. Details A and B).
(c) Remove self-locking nuts and bolts securing cable flanges (8) to center fireseal
mount ring (14) (Details A and B).
(d) Remove self-locking nuts and bolts securing loop clamps (9) to brackets (12)
(Ref. Detail C).
NOTE: Self-locking nuts and bolts securing loop clamps (9) to loop clamps
(10) on fuel tubes, have been removed (Ref. Para. G.).
(e) Remove self-locking nuts and bolts securing cable flanges (8) to rear fireseal
mount ring (13) (Ref. Detail C).
NOTE: Mount ring support bracket (7) has been previously removed (Ref.
Para. B., preceding).
13
14
TO PROPELLER 12
GOVERNOR
11 FLANGE C
CENTER FIRESEAL 4
MOUNT RING
9
10
11
2
REAR FIRESEAL 6 5
MOUNT RING 7
6 7 8
5
3
C7469A
Propeller Governor Pneumatic Tubes
Figure 113
(f) Remove self-locking nuts and bolts securing loop clamps (6) to angle
brackets (5) (Detail D).
(b) Referring to Detail A: Remove self-locking nuts and bolts, separate loop clamps
(1) and (5) from ignition cables (6) and angle brackets (2) and (3) on center
fireseal (4).
(c) Remove self-locking nuts and bolts to release cable (6) flanges from center
fireseal. Remove two brackets (3) from center fireseal.
(d) Detail B: Remove self-locking nut and bolt and separate clamps (7) and (8)
from each other and from cables (6).
(e) Detail C: Remove self-locking nut, bolt and bracket (19) and separate loop
clamp (18) from ignition cable.
NOTE: Bolt and washer retaining bracket (19) and flange of compressor
delivery tube (17) were previously removed (Ref. Para. E.).
FUEL
CONTROL
UNIT A
1 B
3
VIEW A
30
27
PRE−SB1471 29 24
FLOW DIVIDER AND
DUMP VALVE
28
25 15
26 16 19
POST−SB1471 17 20
18
3
22
23
21 CENTER FIRESEAL
MOUNT RING
14 15 16
20 12
12 13
2
8
OIL−TO−FUEL HEATER
7 11
10
7
8
9
6 VIEW B
5
4
(f) Detail D, Pre-SB1482): Remove self-locking nuts and bolts and separate
loop clamps (10) and (13) from brackets (11) and (15) at front of rear fireseal
mount ring (14). Remove clamps from cables (6).
(g) Remove self-locking nut and bolt. Separate loop clamp (9) from ignition cable
(6) and bracket (22) on air inlet screen bolting flange. As nut and bolt were
previously removed (Ref. Para. G.), separate loop clamp (16) from ignition cable
(6).
8
OIL−TO−FUEL HEATER
FCU 7
FUEL
PUMP
5 FUEL PUMP 9
1 10
2
11
3 13
16 12
17 15
14 STARTING CONTROL
FUEL MANIFOLD
CENTER FIRESEAL INLET ADAPTER
REAR FIRESEAL ASSEMBLY
MOUNT RINGS
15 17
16
DETAIL A 20
TYP. 4 PLACES A
TUBE SEALING 18 22
A 19
23
A
21
A
B
R/H IGNITION CABLE
25 19 26
19
21
18 20 24 25
24
26
18
PT6A−27/28 ENGINES L/H IGNITION CABLE
(PRE−SB1196)
VIEW B PT6A−27/28 ENGINES (POST−SB1196)
(h) Detail E, Post-SB1482: Remove bolt and nut and separate loop clamp (16)
from clamp on rear fuel pressure tube (20). Remove clamps.
(i) Remove bolt and nut and separate loop clamp (9) from bracket (22).
(j) Remove bolt, nut, bracket (22) and washer from bracket (21).
(k) Detail F, Post-SB1482: Rremove self-locking nuts and bolts and separate loop
clamps (10, 13) from brackets (11, 15) at rear fireseal mount ring (14). Remove
clamps from cables (6).
(1) Remove glow plug ignition cable (Pre-SB1196) (Ref. Fig. 118):
(b) Remove self-locking nuts and bolts securing loop clamps (4) to angle brackets
(5) on center fireseal mount ring, and integral brackets (6) on gas generator
case (Ref. Detail A).
(c) Remove self-locking nuts and bolts securing cable flanges (7) to center fireseal
mount ring (Ref. Detail B).
NOTE: 1. Self-locking nuts and bolts securing loop clamps (8) to loop clamps
(9) on fuel tubes have been removed previously (Ref. Para. G.).
NOTE: 2. Self-locking nuts, bolts and backplate (11) securing loop clamps (10)
and (12) to loop clamps (13) on fuel tubes have been removed
previously (Ref. Para. G. and Detail D, Fig. 118).
(d) Remove self-locking nuts and bolts securing cable flanges (14) to rear fireseal
mount ring (Ref. Detail E).
NOTE: Mount ring support bracket (15) has been removed previously (Ref.
Para. B.).
(e) Remove self-locking nuts and bolts securing loop clamps (17) and (18) to angle
brackets (16) at flange E (Ref. Detail F).
(f) Withdraw ignition cables (2) and (3) through fireseal mount rings.
DETAIL D
DETAIL A
2
1
1
4
6 3
14 8
3
5
A
C D
B
14 13 7
8
9
10
2 12
1
11 3
14 9 13
10
4
8
3
9
DETAIL C
DETAIL B
1. Connector
2. Bracket
3. Ignition Cable
4. Loop Clamp
5. Bracket
6. Loop Clamp
7. Mount Ring Support Bracket
8. Cable Flanges
9. Loop Clamp
10. Loop Clamp
11. Fuel Line Support Bracket
12. Bracket
13. Rear Fireseal Mount Ring
14. Center Fireseal Mount Ring
(b) Remove self-locking nuts and bolts and separate loop clamps (4), angle
brackets (5) and (6), from integral brackets (7) on gas generator case (Ref. Detail
A).
(c) Remove self-locking nuts and bolts securing loop clamps (9) to angle brackets
(8) (Ref. Detail B).
(d) Remove self-locking nuts and bolts securing cable flanges (10) and angle
brackets (8) to center fireseal mount ring.
(e) Remove self-locking nut and bolt securing loop clamp (11) to angle bracket
(12).
NOTE: 1. Bolt and washer securing angle bracket (12) to flange of compressor
delivery pneumatic tube at gas generator case have been removed
previously (Ref. Para. E. and Detail C, Fig. 119).
NOTE: 2. Self-locking nuts, bolts and lockplate (14) securing loop clamps (13)
and (15) to loop clamps (16) on fuel tubes have been removed
previously (Ref. Para. G. and Detail D, Fig. 119).
(f) Remove self-locking nuts and bolts securing loop clamps (17 and 19) to angle
brackets (20) (Ref. Detail E).
1 6
3 7
8
4
DETAIL B
DETAIL A
5
A
B
POST−SB1337
ALTERNATIVE
LOCATION
D
C
A
PRE−SB1482 CONFIGURATION SHOWN
10
9
11 12
13
18
17
14
19 22
15
16
DETAIL C DETAIL D
1. Loop Clamp
2. Bracket
3. Bracket
4. Center Fireseal Mount Ring
5. Loop Clamp
6. Ignition Cables
7. Loop Clamp
8. Loop Clamp
9. Loop Clamp
10. Loop Clamp
11. Bracket
12. Mount Ring Support Bracket
13. Loop Clamp
14. Rear Fireseal Mount Ring
15. Bracket
16. Loop Clamp
17. Insulated Tube
18. Loop Clamp
19. Bracket
20. Rear Fuel Pressure Tube (Ref)
21. Bracket
22. Bracket
E F
POST−SB1482
9 6
15
22 20
21 10
13
11
16
6
14
DETAIL E DETAIL F
(g) Remove self-locking nuts and bolts securing cable flanges (18) and angle
brackets (20) to rear fireseal mount ring (Ref. Detail E).
NOTE: Mount ring support bracket (21) has been removed previously (Ref.
Para. B.).
(h) Remove self-locking nut and bolt securing loop clamp (22) to loop clamp (23)
on igniter cables (Ref. Detail F).
(1) Remove cotterpins (5), castellated nuts (15), washers (14) and bolts (7) securing
rod assembly (16) to fuel control unit arm (18) and fuel control lever (29) (Ref.
View A and B.) Note and record position of bolt (7) in hole of fuel control lever.
(2) On PT6A-27/28 engines, remove upper and lower cotterpins (5), castellated nuts
(15), washers (14), spacer sleeves (20), (24) and (25) plus bolts (21), and separate
upper and lower interconnect rod assembly (23) from FCU control lever (19) and
start control lever (26)
(3) Remove cotterpin (5) and washer (6) and separate pin (9) from rear push-pull
control rod end clevis (10) and propeller control cam (8). Note and record
position of pin in hole of control cam.
(4) Remove bolt (2) securing angle bracket (1) to control lever mounting bracket (4).
(5) Remove two bolts (3) securing angle bracket (1) and flange cover (12) to accessory
gearbox housing; separate bracket and temporarily reinstall bolts (3) to retain cover.
(6) Remove two self-locking nuts (13) and separate control lever mounting bracket (4)
from flange G; temporarily reinstall nuts (13) to prevent loss of parts.
(1) Remove cotterpin (8), washer (2) and pin (13) securing propeller lever (15) to Beta
valve plunger (14) (Ref. Detail C).
(2) Remove cotterpin (8), castellated nut (1) and bolt (12), and separate push-pull
control rod (10) from lever (15) (Ref. Detail B).
(3) Remove lever (15) and separate sleeve spacer (11) and sleeve bushing (16) (Ref.
Details B and C). Retain spacer and bushing with lever.
(4) Remove cotterpin (8), castellated nut (1) and washers (2) securing forward rod end
connector (3) of rod assembly (7) to wire rope clamp (9) (Ref.Detail A).
DETAIL A DETAIL F
17
CENTER FIRESEAL
MOUNT RING
4
5
DETAIL E 18
16
6 DETAIL B 8
GAS GENERATOR
CASE DETAIL C
7
B F
C D E
B C FLANGE E
1
A
3
10
11
14
12
15
13
REAR FIRESEAL
FUEL TUBES MOUNT RING
14
DETAIL D DETAIL E
1. Glow Plug
2. Ignition Cable (L.H.)
3. Ignition Cable (R.H.)
4. Loop Clamp
5. Angle Bracket
6. Bracket
7. Cable Flange
8. Loop Clamp
9. Loop Clamp
10. Loop Clamp
11. Backplate
12. Loop Clamp
13. Loop Clamp
14. Cable Flange
15. Mount Ring Support Bracket
16. Angle Bracket
17. Loop Clamp
18. Loop Clamp
(5) Remove cotterpin (8), castellated nut (1), washer (2) and bolt (5) securing rear
rod end connector (3) of rod assembly (7) to propelelr governor air bleed link (4)
(Ref. Detail A); remove rod.
(6) Remove two self-locking nuts (18) and washers (19) and separate guide pin
bracket (17) from propeller thrust bearing cover (Ref. Detail D). Temporarily install
washers and nuts to prevent loss of parts.
(1) Slacken self-locking nut (15) securing wire rope clamp (1) and unscrew wire rope
terminal assembly (2) from wire rope (5) (Ref. Detail D).
(2) Unscrew casing nut (6) from casing swivel joint (3).
(3) Slacken rear nut (4) securing casing swivel joint (3) to rea fireseal mount ring.
Unscrew and remove swivel joint and nuts from mount ring and bracket (28).
(4) Remove self-locking nut (15), bolt (17) and spacer (9), and separate loop clamp (8)
from loop clamp (10) on T5 trim wiring harness (11) (Ref. Detail C). Place parts
removed in a plastic bag and secure to harness for subsequent overhaul (Ref.
77-20-01).
(5) Remove self-locking nut (15), washer (16) and bolt (17), and separate loop clamp
(8) from angle bracket (18) forward of center fireseal mount ring.
5 10 12
6 REAR FIRESEAL 9
MOUNT RING
7
CENTER FIRESEAL
GAS GENERATOR MOUNT RING
CASE 1 PT6A−28
2 POST−SB1337
G ALTERNATIVE
LOCATION
A B D E F DETAIL G
B C
2
A
3
1
3 IGNITION
EXCITER
14 DETAIL G
13 18
15 17
22
16 21
REAR FIRESEAL
20 MOUNT RING 23
18
FUEL TUBES 19 20
DETAIL D DETAIL E DETAIL F
1. Spark Igniter
2. Igniter Cable (L.H.)
3. Ignition Cable (R.H.)
4. Loop Clamp
5. Angle Bracket
6. Angle Bracket
7. Bracket
8. Angle Bracket
9. Loop Clamp
10. Cable Flange
11. Loop Clamp
12. Angle Bracket
13. Loop Clamp
14. Bookplate
15. Loop Clamp
16. Loop Clamp
17. Loop Clamp
18. Cable Flange
19. Loop Clamp
20. Angle Bracket
21. Mount Ring Support Bracket
22. Loop Clamp
23. Loop Clamp
(6) Remove two self-locking nuts (15) and bolts (17) securing seal retaining plates
(12), insulation (13), seals (14) and bracket (18) to center fireseal mount ring.
Remove insulation, seals and bracket.
(7) Remove self-locking nut (15) and bolt (17) and separate loop clamp (8) from angle
bracket (25) at flange C (Ref. Detail B). Remove self-locking nut (27) and D-head
bolt Pre-SB1528 or tee bolt Post-SB1528 (26) and separate bracket from flange C.
Temporarily install D-head bolt and nut to flange C to prevent loss of parts.
(8) Slacken self-locking nut (15) securing wire rope clamp (19) and unscrew wire rope
terminal assembly (20) from wire rope (5) (Ref. Detail A).
NOTE: Wire rope terminal assembly will remain in place inside adjuster and
swivel joint assembly.
29 A 7 9
29 11
8 10
5 8
6
B
REAR FIRESEAL
3 MOUNT RING
15
17 14
2 G
13 4 12 FLANGE
23
1
VIEW A 5
18
16
15 14 18
5 17
7
C 16
PT6A−27/28 ENGINES 19
5
15
14
28 20 22 21
29 VIEW B
8
A
5
15
14
B
23
22
16 27 26
17 25
24
VIEW C 21
PT6A−21 ENGINES
18
C11796
Interconnect Linkage Group - Rear
Figure 120
1. Angle Bracket
2. Bolt
3. Bolt
4. Control Lever Mounting Bracket
5. Cotterpin
6. Washer
7. Bolt
8. Propeller Control Cam
9. Pin
10. Push-pull Rod End Clevis
11. Push-pull Wire Rope Clevis
12. Flange Cover
13. Self-locking Nut
14. Washer
15. Castellated Nut
16. Rod Assembly
17. Fuel Control Arm Extension
18. Fuel Control Unit Arm
19. FCU Lever Assembly
20. Spacer Sleeve (PT6A-27/28 Engines)
21. Bolt (PT6A-27/28 Engines)
22. Jam Nut (PT6A-27/28 Engines)
23. Upper and Lower Rod Assembly (PT6A-27/28 Engines)
24. Spacer Sleeve (PT6A-27/28 Engines)
25. Spacer Sleeve (PT6A-27/28 Engines)
26. Starting Control Lever (PT6A-27/28 Engines)
27. Starting Control (PT6A-27/28 Engines)
28. Fuel Control Unit (FCU - Typical) (PT6A-27/28 Engines)
29. Fuel Control lever
(10) Unscrew nut (4) from adjuster and swivel joint assembly (21) and remove
assembly from mounting bracket (23).
(11) Remove two self-locking nuts (15) and bolts (24) and separate retaining plate (22)
from bracket (23).
(12) Withdraw casing and rope assembly forward through center fireseal mount ring,
removing nuts (4) and seal retaining plate (12).
(13) Securely tape casing and rope assembly to a stiff board for protection. Retain parts
such as nuts, washers and bolts etc. in a bag.
10
15
A
B
AIRBLEED
LINK
C 7 14
D
15
THRUST
BEARING 17
COVER
1 18
2
8 3
2 9
10 12
DETAIL D
7
5 11
1
6 8
DETAIL B
6
13 16
8
DETAIL A
DETAIL C
4
3
2 2
1 14
8
17
15
C9450A
Interconnect Linkage Group - Front
Figure 121
1. Castellated Nut
2. Washer
3. Rod End Connector
4. Propeller Governor Air Bleed Link
5. Bolt
6. Nut
7. Rod Assembly
8. Cotterpin
9. Wire Rope Clamp
10. Push-pull Control Rod
11. Sleeve Spacer
12. Bolt
13. Pin
14. Beta Valve Plunger
15. Propeller Lever
16. Sleeve Bushing
17. Guide Pin Bracket
18. Self-locking Nut
19. Washer
15 8 25 17
POST−SB1528
A
FLANGE C
REAR FIRESEAL
D
28 4
B 4
3
2
1
REAR FIRESEAL C
MOUNT RING DETAIL D
SUPPORT BRACKET
11 15 25
FLANGE C
CENTER FIRESEAL
MOUNT RING
10 15
17 15
9
17 8 17
26 27 8
17 12 16 7
8 DETAIL B
15 15
5 PRE−SB1528
18
12
13 19
14
13 29
DETAIL C 7
17 4
6
5
15
20
15 21
5
22
23
7 6 24 DETAIL A
C9445E
Interconnect Linkage Group - Push-pull Control
Figure 122
1. General
A. Personnel disassembling the engine or modules should read the Introduction Sections of
this manual to familiarize themselves with general overhaul procedures (Ref.
INTRODUCTION, Outline of Overhaul Procedures).
B. When the engine is received for overhaul, remove the air inlet screen and inspect first
stage of compressor rotor for foreign object damage (FOD). Inspect engine for external
damage, burning, corrosion, and signs of leakage. Record all observations made at
this inspection for reference during disassembly of engine, taking special notice of any
discrepancy that might not be apparent after cleaning. Tag all affected parts to identify
nature of fault. After removal from engine, submit affected parts to detailed inspection
before cleaning.
C. During inspection of engine, check that all externally mounted parts and accessories are
correctly fitted. Loose or unattached components usually indicate that they have been
replaced because of previous unserviceability. Record all discrepancies and check against
data sheets received with engine for information relating to unserviceabilities
encountered during service.
D. Overhaul facilities may find it more expedient to remove certain parts before others, so
disassembly sequences given in the text need not be strictly adhered to. Instructions for
removal of some standard parts, such as loop clamps and similar attaching hardware,
may be repeated in areas where such parts support more than one component.
F. Seal all openings as soon as possible after removal of external parts and accessory
units. Place each component in a separate polyethylene bag or dust-proof container,
and store on suitable racks until required for overhaul. Segregate parts during storage to
prevent impact damage.
H. To prevent damaging seal grooves and lands, use plastic spatulas for removing
preformed packings. Damage in these areas can cause leaks due to improper seating.
I. Discard all preformed packings, tabwashers, cotterpins and gaskets immediately after
removal, to prevent possible reuse.
2. Consumable Materials
Not Applicable
3. Special Tools
The special tools listed below are used in the following procedures.
Not Applicable
5. Removal of Accessories
(1) Remove four self-locking nuts (4) and washers (5) using wrench (PWC30114-09) or
(PWC30114-16), as required.
(2) Separate propeller governor (1) from mounting pad (7), remove and discard gasket
(6).
(3) Remove straight nipple (3), and discard preformed packing (2).
NOTE: Record part and serial number of propeller governor to ensure correct
governor is installed at Final Assembly.
(1) Remove oil tube assembly (9) from elbow (7) on oil-to-fuel heater (8) and elbow
(10) on adapter (15) of check valve assembly.
(2) Remove bolts and retaining plate (3) from oil return adapter (1).
(3) Remove self-locking nuts and washers securing oil-to-fuel heater (8) to studs at
flange G.
(4) Withdraw oil-to-fuel heater and check valve assembly (4) from studs at flange G
and adapter (1) on compressor inlet case.
(5) Withdraw check valve assembly from port in oil-to-fuel heater. Remove and discard
preformed packings (2 and 5).
(6) Overhaul check valve assembly, oil-to-fuel heater and attaching parts (Ref.
73-10-01).
(1) Loosen nut (11) and remove elbow (10) from adapter (15) on compressor inlet
case. Remove preformed packing (13) and back-up ring (12).
(2) Remove bolts, and separate mount ring support bracket (14) and adapter (15) from
compressor inlet case.
(3) Withdraw adapter (15) from compressor inlet case, and remove preformed packing
(16).
(4) Remove retaining ring (17) from check valve sleeve (22), and withdraw check valve
spring seat (18), valve spring (20) and check valve (21) from check valve sleeve
(22). Remove preformed packing (19) from spring seat.
(5) Withdraw check valve housing (24) and check valve sleeve (22) from compressor
inlet case using puller (PWC30518).
(6) Withdraw check valve sleeve (22) from check valve housing (24). Remove
preformed packings (25) and (26) from housing and preformed packing (23) from
sleeve.
(1) For disconnection of fuel inlet hose, fuel pressure line, Py air pressure tube and
propeller reversing linkage controls, refer to preceding paragraphs. Remove FCU
(Ref. Fig. 103).
NOTE: It may be more convenient to remove FCU and fuel pump together and
separate units on a bench.
(a) Support fuel control unit (1) and remove four self-locking nuts (2) and washers
(3).
(b) Withdraw unit from studs on fuel pump (6), and remove and discard splined
coupling (5).
(c) Remove preformed packing (7) from recess on face of fuel pump (6).
(d) Do not remove fuel control arm (9), extension (8) and serrated spacer (4) from
fuel control unit at this stage.
(e) Overhaul fuel control unit and associated parts (Ref. 73-20-00).
1
2
3
C7199
Propeller Governor
Figure 101
(1) For disconnection of fuel inlet flexible hose, fuel pressure line, Py air pressure tube,
P3 air pressure tube and propeller reversing linkage control rod, refer to preceding
paragraphs. Remove FCU, as follows: (Ref. Fig. 104)
NOTE: It may be more convenient to remove fuel control unit and fuel pump
together, and separate units on bench.
(a) Extract two cotterpins and remove castellated nuts (9), washers (8) and bolts
(6). Remove interconnecting rod (10) and spacers (7), (11) and (12) from fuel
control unit arm and starting control arm.
NOTE: Items (6) thru (12) are not used on some PT6A-27 engine models.
(b) Support fuel control unit (1) and remove four self-locking nuts (2) and washers
(3).
(c) Withdraw unit from studs on fuel pump, and remove and discard splined
coupling (4).
(e) Do not remove fuel control arm (14), extension (15) and serrated spacer (13)
from fuel control unit (1) at this stage.
(f) Overhaul fuel control unit and associated parts (Ref. 72-20-00).
(1) Support fuel pump (1), and remove self-locking nuts (2) and washers (3).
(2) Withdraw pump from studs on accessory gearbox (5). Discard gasket (4).
G. Remove Starting Control (Dual Line Fuel System) (Ref. Fig. 106)
1 2 3
4 5
COMPRESSOR INLET
CASE 7
6 8 9
10
FLANGE G 9
11
12
13
14
15
16
23 17
24 18
19
25 20
26 21
COMPRESSOR INLET 22
CASE
C7477A
Oil-to-Fuel Heater and Check Valves
Figure 102
(1) Remove bolt (1) that secures starting control (5) to mounting bracket (2) on accessory
gearbox.
(2) Support starting control (3), and remove self-locking nuts and washers (2).
(1) Remove four self-locking nuts and washers securing oil filter cover (7) to compressor
inlet case (1).
(2) Remove cover (7) complete with stepped spacer (6) from case (1). Discard
preformed packing (5).
6
1 5
4
9
8
3
2
C7203A
Fuel Control Unit (PT6A-21 Engines)
Figure 103
(b) Screw rod (11) into collet assembly (12), until enlarged end of rod clears collet
teeth.
(c) Install puller (9) over filter housing (8) so that end of housing rests in
counterbore of puller.
(d) Push rod inward until collet teeth engage behind inner bore of filter element
end cover.
(g) Remove puller (9) and element (3) from housing (8); remove element from
puller.
(1) Withdraw oil filter housing assembly (3) from compressor inlet case (1) using puller
(PWC30328) as follows:
(b) Pull open halves of head (6) at threaded end and insert opposite end of head
into oil filter housing (3); release head so that it engages behind shoulder of
housing.
9 8
1 2 3
4
FUEL PUMP
13
15
10 14
6
STARTING FLOW
CONTROL
9
8 10
C7478B
Fuel Control Unit (PT6A-27/28 Engines)
Figure 104
(d) Operate sliding weight (8) along rod (9) to extract housing (3).
(e) Remove puller from housing (3). Discard preformed packings (2) and (5).
(3) Withdraw trim harness (3) through center fireseal mount ring.
(1) Support ignition regulator (1), and remove three bolts (3) and washers (2).
3 4 5
2
C7173
Fuel Pump
Figure 105
1. Fuel Pump
2. Self-locking Nut
3. Washer
4. Gasket
5. Accessory Gearbox
(1) Support ignition exciter (3), and remove self-locking nuts (5), washers (4) and bolts
(1) (Pre-SB1422). Alternatively, remove nuts (8), washers (9), bolts (12) and
sleeves (11) (Post-SB1422).
(3) Support mounting bracket (2), and remove three bolts (6) and washers (7).
(5) Remove vibration absorber mounts (10) (Post-SB1422) from bracket (2).
3 4
FLANGE G
2
5
C7479
Starting Control
Figure 106
1. Bolt
2. Mounting Bracket (Ref.)
3. Self-locking Nut
4. Washer
5. Starting Control
4
8
5
6
1
3
9
10
11
2 12
4
8
C9280
Oil Filter Element Removal
Figure 107
2 3 4 5 1
6 7 8 9
C9281A
Oil Filter Housing Assembly Removal
Figure 108
CENTER FIRESEAL 7
MOUNT RING
2 3 4
TERMINAL BLOCK
8
9
10
PROPELLER REVERSING
CABLE HOUSING
GAS GENERATOR
CASE
C7480C
T5 Trim Wiring Harness
Figure 109
1. Loop Clamp
2. Loop Clamp
3. T5 Trim Harness
4. Bolt
5. Angle Bracket
6. Loop Clamp
7. Self-locking Nut
8. Bolt (Alumel Terminal)
9. Bolt (Chromel Terminal)
10. Spacer
1
ACCESSORY GEARBOX
2
3
2
3
C7481
Ignition Regulator
Figure 110
1. Ignition Regulator
2. Washer
3. Bolt
3
1
4 5
7 6
ACCESSORY GEARBOX
2 POST−SB1337
1
3
4 5
7 6
POST−SB1422
ACCESSORY GEARBOX
2
9 3
8 11
10 9
12
7 6
C8496B
Ignition Exciter Installation
Figure 111
1. Bolt Pre-SB1422
2. Mounting Bracket
3. Ignition Exciter
4. Washer Pre-SB1422
5. Nut Pre-SB1422
6. Bolt
7. Washer
8. Nut Post-SB1422
9. Washer Post-SB1422
10. Vibration Absorber Mount Post-SB1422
11. Flanged Sleeve Post-SB1422
12. Bolt Post-SB1422
1. General
A. Personnel disassembling the engine or modules should read the Introduction Sections of
this manual to familiarize themselves with general overhaul procedures (Ref.
INTRODUCTION, Outline of Overhaul Procedures).
B. This chapter contains overhaul procedures for a complete engine, and when applicable,
overhaul procedures for approved engine modules. Overhaul procedures for an engine
module program will be defined in Special Instructions (SIs).
C. On receipt of an engine or gas generator module (GGM) for overhaul, remove air inlet
screen and examine for foreign object damage (FOD) in compressor rotor assembly.
Inspect externally for damage, burning, corrosion, and signs of leakage. Record all
observations made at this inspection to provide reference during disassembly of
engine; special notice is to be made of any discrepancy which might not be apparent
after cleaning. All affected parts must be tagged to identify nature of fault and, after
removal from engine, these parts subjected to detailed inspection before cleaning.
D. During inspection of engine, check that all externally mounted parts and accessories are
correctly fitted. Loose or unattached components usually indicate that they have been
replaced because of previous unserviceability. Record all discrepancies and check against
data sheets received with engine for information relating to unserviceabilities
encountered during service.
E. Overhaul facilities may find it more expedient to remove certain parts before others, so
disassembly sequences given in the text need not be strictly adhered to. Instructions for
removal of some standard parts, such as loop clamps and similar attaching hardware,
may be repeated in areas where such parts support more than one component.
G. Seal all openings as soon as possible after removal of external parts and accessory
units. Place each component in a separate polyethylene bag or dust-proof container,
and store on suitable racks until required for overhaul. Segregate parts during storage to
prevent impact damage.
I. Use plastic spatulas when removing preformed packings to prevent possibility of scores
and scratches on seal grooves and lands; damage in these areas can produce improper
seating and result in leakage.
J. Discard all preformed packings, tabwashers, cotterpins and gaskets immediately after
removal, to prevent possible reuse.
2. Consumable Materials
Not Applicable
3. Special Tools
The special tools listed below are used in the following procedures.
Not Applicable
5. Removal of Fireseals
A. Center Fireseals
(a) Remove self-locking nuts and washers (6) and bolts (7) securing top (1) and
bottom (4) center fireseal mount ring support brackets (5) to integral support
brackets (8) on gas generator case. Remove nuts, bolts and brackets (5) from
fireseal.
(b) Remove self-locking nuts (2) and bolts (3) and separate top center fireseal
mount ring and bottom center fireseal mount ring from gas generator case.
(1) Remove fireseal from engines without compressor wash ring (Ref. Fig. 101).
NOTE: Bracket (18) and attachment nuts and bolts were previously removed.
(b) Remove two self-locking nuts (13), washers (14) and bolts (12), and separate
support bracket (15) from rear fireseal (16).
(c) Remove self-locking nuts (17) and bolts (19) from each side of upper and lower
fireseal brackets, and separate both halves of fireseal (16) and (23) from air
inlet case.
(1) Remove fireseal from engines with compressor wash ring installed (Ref. IPC) (Ref.
Fig. 101):
NOTE: Bracket (18) and attachment nuts and bolts were previously removed.
(b) Remove two self-locking nuts (13), washers (14) and bolts (12), and separate
support bracket (15) from rear fireseal (16).
(c) Remove two self-locking nuts (13), washers (14) and bolts (12), and separate
support bracket (15) from rear fireseal (16).
(d) Remove two self-locking nuts (17) and bolts (19) from each side of upper and
lower fireseal brackets, and separate both halves of fireseal (16) and (23) from
air inlet case.
(1) Place suitable oil container below propeller reduction gearbox (7), remove oil drain
plug (8) (Pre-SB1217) or magnetic chip detector (8) (Post-SB1217) and allow
residual oil to drain from gearbox.
(2) Install power section sling (PWC30037) on propeller reduction gearbox (7).
(a) Position mounting plate of sling (1) over propeller mounting flange on reduction
gearbox (7), and engage dowels on flange with corresponding holes in plate.
(b) Secure sling (1) to propeller mounting flange with four socket-head cap screws
(17), installed from rear of mounting flange. Tighten screws and torque 700 to
770 lb.in.
10 16 15 13
11 14
1 12
18
17
23
8
A
2
GAS
GENERATOR 3
CASE
IGNITION CABLES
22 19
8 20
7
17
4
24
5
19
6
3
DETAIL A
C41544
Center and Rear Fireseal Mount Rings and Compressor Wash Ring
Figure 101
(c) Attach hoist to lifting lug on sling (1), and take up slack on hoist to support weight
of power section.
(3) Remove interturbine temperature thermocouple (T5) terminal block retaining bolts
and push terminal block and gasket into gas generator case.
(4) Remove self-locking nuts (2) and bolts (4) securing exhaust duct (3) to gas
generator case (5) at flange C.
(5) Separate and withdraw power section from gas generator case.
(6) Install mount ring (PWC30269) and two engine stand adapters (PWC30712) on
power section.
(a) Place mount ring (9) on flange of exhaust duct. Position mount ring with set of
three holes at each side of horizontal plane, and secure with bolts (11) and
self-locking nuts (12).
(b) Secure one adapter (10) to each set of three holes in mount ring (9) with two
hexagon-head machine screws (13).
C7207
Removal of Power Section
Figure 102
(7) Lower power section into stand (PWC30800), and secure adapters (10) to
mounting disks on stand with bolts (14), washers (15) and nuts (16). Tighten nuts
securely.
(1) Remove oil drain plug (12) and allow residual oil to drain from accessory gearbox.
Reinstall oil drain plug to prevent loss of part.
(2) Using accessory gearbox transfer tube puller (PWC30128-04), withdraw oil transfer
tube (21) from elbow boss inside accessory gearbox, and remove tube from bottom
of compressor inlet case (22). Remove and discard preformed packings (20).
(3) Remove plug (8) from center boss in rear face of accessory gearbox and discard
preformed packing (7).
(4) Determine location of coupling shaft lock ball, at compressor rear hub coupling, by
viewing through the hole in the center boss. Rotate compressor until notch in
washer at rear hub is at 3 o’clock position. This will ensure the lock ball is at the
12 o’clock position on the splined end of the rear hub; preventing the ball from
dropping out of position (Ref. Fig. 103).
4
2
5
6
10
9
A 7 8
23
11
12
22
14
20
21 13
6
1 14
19
15
16
17
18 VIEW A
C7483B
Removal of Accessory Gearbox
Figure 103 (Sheet 1 of 2)
1. Coupling Shaft
2. Preformed Packing
3. Washer
4. Engine Lifting Bracket
5. Self-locking Nut
6. Accessory Gearbox Housing
7. Preformed Packing
8. Plug
9. Starter-generator Overboard Drain Adapter (Ref)
10. Drain Adapter Cap (Ref)
11. Preformed Packing
12. Accessory Gearbox Oil Drain Plug
13. Adapter (Engines with vacuum pump drive)
Tee (Engines without vacuum pump drive)
14. Diaphragm
15. Compressor Hub Coupling Shaft
16. Preformed Packing
17. Oil Tank Center Tube
18. Preformed Packing
19. Lock Ball
20. Preformed Packing
21. Oil Transfer Tube
22. Compressor Inlet Case
23. Spacers
24. Screw
25. Nut
26. Body
24
25
26 B
24
25
26
DETAIL B
1
19
A
DETAIL A
15 LOCK−BALL ARRANGEMENT
C13622
Removal of Accessory Gearbox
Figure 103 (Sheet 2)
NOTE: Two self-locking nuts and washers securing oil-to-fuel heater, engine
lifting bracket (4) and accessory gearbox to studs on compressor inlet
case have previously been removed.
(6) Remove remaining self-locking nut (5) and lifting bracket (4).
(9) Withdraw accessory gearbox from compressor inlet case and remove preformed
packing (2) from accessory gearbox (6) at flange G.
NOTE: If lock ball (19) drops out of locking position between compressor hub
coupling shaft (15) and coupling shaft (1) during removal of accessory
gearbox, retrieve ball from No. 1 bearing housing area, or from oil scavenge
passage in compressor inlet case (22), as applicable.
(11) If oil tank center tube (17) and two oil transfer tubes are withdrawn with accessory
gearbox, remove tubes from gearbox, discard preformed packings and retain tubes
with compressor inlet case (22) for subsequent overhaul of these parts.
(13) Enclose plug (8) and lock ball (19) in a protective bag and tie to accessory
gearbox.
7. Unscheduled Removal of Power Section from Gas Generator Assembly (Ref. Fig. 104)
(1) Install power section sling (3) (PWC30037) on propeller reduction gearbox (15), and
remove power section as follows:
(2) Place suitable oil container under reduction gearbox (15), and remove oil drain plug
(14) or magnetic chip detector (14), as applicable; allow residual oil to drain from
gearbox.
(3) Disconnect coupling nut of propeller governor pneumatic (Py) line (9) at bulkhead
coupling (11) on center fireseal mount ring. Cap lines.
(4) Remove cotterpin, nut, bolt and spacer (25) securing front rod end clevis (1) to
propeller reversing lever (17).
(5) Remove cotterpin, nut, bolt and washer (26) securing propeller governor interconnect
rod end (2) to air bleed link (27) on propeller governor (6).
(6) Remove self-locking nut and bolt from support bracket of wire rope casing (8) at
flange C.
(7) Disconnect propeller reversing linkage from bracket (7) (Pre-SB1185) on PT6A-27/28
engines, as follows:
(a) Remove cotterpin, washer and straight pin (18) securing rear rod end clevis
(20) to propeller control cam (19).
(b) Loosen nut on rear clamping bolt. Disengage terminal (21) and assembly of rod
end clevis (20) from wire rope (22) by turning counterclockwise to free rope
from internal thread of clamping bolt.
(c) Disconnect wire rope casing (8) from rear of front swivel joint (4) at engine
lifting bracket (7).
CAUTION: HANDLE WIRE ROPE WITH CARE. STORE IN A PLASTIC BAG FOR
PROTECTION AGAINST CONTAMINATION AND POSSIBLE
DAMAGE.
(d) Remove locknut (5) from front swivel joint (4), and withdraw link assembly and
wire rope forward, and free of engine lifting bracket (7).
(8) Disconnect propeller reversing linkage from bracket (7) PT6A-27/28 (Post-SB1185)
and all PT6A-21 engines.
(a) Loosen locknut (5) at rear of engine lifting bracket (7), that secures front swivel
joint (4) to lifting bracket.
(b) Remove inner nut (28) and bolt (30), and release outer nut and bolt securing
swivel joint retaining plate (29) to front lifting bracket (7). Swing retaining plate
out of engagement, and lift propeller reversing linkage front end clear of
slot in lifting bracket (7). Suitably support linkage.
(9) Remove bolts securing T5 trim harness leads to terminal posts on terminal block
(10) on gas generator assembly.
(10) Remove two retaining bolts securing T5 thermocouple terminal block (10) to gas
generator assembly. Release terminal block and gasket into gas generator
assembly.
(11) Attach hoist to lifting lug on sling (3); take up slack on hoist to support weight of
power section.
(13) Cap all oil transfer tubes (12) and install caps on couplings (13).
(14) Withdraw power section from gas generator assembly and install in stand (Ref.
Para. 6.,A., preceding).
7 28
8 22
21
POST−SB1185 20
7 6 19
8 5 4
1 30 29
23
SPACER SLEEVE 18
REAR FIRESEAL
25
INPUT LEVER
22 24
17 CONTROL LEVER
MOUNTING BRACKET
27 26
FCU CONTROL ROD
2
CENTER FIRESEAL VIEW B
MOUNT RING
VIEW A 11
B
3 7 8
1 6
2 10 9
17
16 15 13
14
FLANGE C 12
C7484
Unscheduled Removal of Power Section from Gas Generator Assembly
Figure 104
ENGINE - CLEANING
1. General
B. General cleaning procedures in this chapter and specific cleaning procedures in each of
the other chapters should be used in conjunction with cleaning procedures described in
P&WA Standard Practices Manual P/N 585005.
C. Certain cleaning procedures used in the manual will refer to the letter prefix SPOP, an
abbreviation for Service Process Operation Procedure, followed by a control number,
e.g., SPOP 209. Whenever any normal SPOP cleaning method is specified, reference
should be made to P&WA Standard Practices Manual for detailed information.
F. All engine parts, other than standard replacement parts such as gaskets and preformed
packings not detailed in respective tables, should be cleaned in accordance with
SPOP 209. Tubes in this category must be blown through with clean, dry compressed
air and examined to ensure they are unobstructed. Cap all tubes immediately after
cleaning to prevent the entry of contaminants which could affect engine operation.
H. Segregate bearings from other engine parts and handle carefully (Ref. 70-21, P&WA
Standard Practices Manual). Clean bearings as specified in table of applicable
chapter/section.
2. Consumable Materials
The consumable materials listed below are used in the following procedures.
For alternate products, suppliers and suppliers addresses refer to Consumables Material List
P/N 3043340.
Not Applicable
Not Applicable
5. Cleaning
A. General
(1) The importance of engine cleaning cannot be overstated for the following reasons:
(b) Removes deposits which adversely affect the efficient functioning of engine
components.
(c) Prepares surfaces for repair and salvage processes such as plating, welding
and painting.
(d) Removes various organic or inorganic coatings that require replacement, either
for inspecction of the underlaying surfaces, or to remove deteriorated coatings
unsuitable for further service.
B. General Precautions
(1) Since one reason for cleaning is to prepare parts for adequate inspection,
excessive cleaning should be avoided and the following points kept in mind:
(a) In general, parts that will be subjected to visual inspection only or to magnetic
particle inspection, do not require the high degree of cleanliness necessary for
parts that will be subjected to fluorescent-penetrant inspection.
(b) Stains on cadmium or nickel-cadmium plated parts need not be removed since
they do not impair magnetic-particle inspection. Scrubbing such stains may
remove the plate and necessitate replating.
(c) Oxide coatings need not be removed unless critical penetrant inspection is
called for.
(d) Paints and varnishes on non-ferrous parts need not be stripped, unless
subsequent fluorescent-penetrant inspection indicates that they cause a
fluorescence which interferes with crack detection, or the condition is such that
paint or varnish requires replacement.
(e) If Hylomar (PWC09-005A) has previously been used on mating surfaces, and
cleaning is not effective with applicable SPOP, a nylon brush should be used in
these areas.
C. Cleaning Precautions
(1) To avoid possible damage to costly engine parts, the following points should be
noted:
(a) Always refer to the appropriate table before cleaning any engine part. Some
parts can be seriously damaged if an unsuitable cleaning process is used.
(b) Make sure that process requirements are met, by frequently checking
temperature of solutions, strength of solutions and immersion time in solutions.
(d) After cleaning parts that contain recesses, passageways or enclosed areas, care
must be taken to ensure these areas have been thoroughly cleaned out.
Damage may result from hydraulic action of residual oil, grease, preservation
compound or other liquids trapped in blind holes into which studs, bolts, inserts or
similar fittings will be screwed or press-fitted.
(e) Acid-cleaning methods shall not be used where there is any possibility of the
cleaning agent becoming entrapped, or not completely removed, during
cleaning.
(b) Glass bead clean corroded areas only per SPOP 16. Corrosion areas not
accessible by blasting may be cleaned by rotary file.
(c) Remove masking and remove any remaining residue per SPOP 208.
(d) Pressure flush all passages and internal surfaces using varsol filtered through
10 micron filter.
(1) In a stainless steel container, soak filter element in carbon removing solvent (SPMC
U0024) for 30 to 60 minutes at room temperature.
(2) Immerse element in cleaning solvent (SPMC U0021) in an ultrasonic cleaner (with
backflushing adapter and flush filter of 3 to 5 microns) for 1 to 3 minutes at 48 °C
(118°F).
(3) Simultaneously backflush and ultrasonic clean (SPMC U0021) the element at a flow
rate of 1 to 3 gal/min at 30 psig. and at an ultrasonic frequency 25 kHz minimum
for 1 to 3 minutes at 38°C (100 °F).
(4) Rotate the element 180 degrees. Continue to backflush and ultrasonic clean
simultaneously (SPMC U0021) at a flow rate 1 to 3 gal/min at 30 psig. for 1 to 3
minutes at 38°C (100°F) .
(5) Hold element in vapors below water jacket level for 1 to 5 minutes at 48°C (118°F).
(SPMC U0021)
NOTE: Cooling water should be flowing in a constant stream through water jacket,
at not more than 27°C (80°F), otherwise unnecessary losses of highly
volatile solvent (SPMC U0021) will occur. Continue to run water through
cooling system at least 30 minutes after ultrasonic cleaner is switched off.
(7) Use clean, dry compressed air to dry the element for 1 to 3 minutes.
(9) Use clean, dry compressed air and/or plastic or wooden spatula to remove any lint
deposits.
(10) Remove any remaining lint deposits by soaking the element in lint dissolving
solution (SPS U0020) for 60 minutes at room temperature. (Ref. Table 201).
(11) Flush the element in hot water 66 to 93 °C (150 to 200 °F) for 1 to 5 minutes to
remove any remaining lint residue.
(12) Use clean, dry compressed air to dry the element for 1 to 3 minutes.
(13) Swab element end caps with 5 to 10% nitric acid solution (SPMC U1000) to
remove any copper deposits.
(14) Pressure flush the element with cold water at room temperature.
(15) Use clean, dry compressed air to dry the element for 1 to 3 minutes.
(16) Use a 10 power magnification glass to inspect the element for broken wires. Reject
the element if broken wires are found. Sharp and deep dents, if otherwise
acceptable, should not be straightened.
(17) Do a bubble point test with the element submerged 1/2 inch below the surface of
cleaning solvent (SPMC U0021) at 22 °C (72 °F). Rotate the element slowly and
smoothly until first air bubble emerges. Reject the element if the bubble point value
is less than 3.00 inches - water gage (40 micron filter).
NOTE: Slowly increase the air pressure without creating ambient vibrations.
(18) Use clean, dry compressed air to dry the element for 1 to 3 minutes.
(1) In a stainless steel container, soak filter element in carbon removing solvent
(PWC11-020) for 15 to 30 minutes at room temperature.
(2) Dip rinse element in hot water 66° to 93°C (150° to 200 °F) .
(4) Simultaneously backflush and ultrasonic clean the element at a flow rate of 1 to 3
gal/min at 30 psig. and at an ultrasonic frequency 25 kHz minimum for 1 to 3
minutes at 38 °C (100°F).
(5) Rotate the element 180 degrees. Continue to backflush and ultrasonic clean
simultaneously at a flow rate 1 to 3 gal/min at 30 psig. for 1 to 3 minutes at 38°C
(100°F).
(6) Hold element in vapors below water jacket level for 1 to 5 minutes at 48°C (118°F).
NOTE: Cooling water should be flowing in a constant stream through water jacket,
at not more than 27°C (80°F), otherwise unnecessary losses of highly
volatile solvent (PWC11-014) or (PWC11-032) will occur. Continue to run
water through cooling system at least 30 minutes after ultrasonic cleaner is
switched off.
(8) Use clean, dry compressed air to dry the element for 1 to 3 minutes.
(10) Use clean, dry compressed air and/or plastic or wooden spatula to remove any lint
deposits.
(11) Remove any remaining lint deposits by soaking the element in lint dissolving
solution for 60 minutes at room temperature. (Ref. Table 201).
(12) Flush the element in hot water 66 to 93°C (150 to 200°F) for 1 to 5 minutes to
remove any remaining lint residue.
(13) Use clean, dry compressed air to dry the element for 1 to 3 minutes.
(14) Swab element end caps with 5 to 10% nitric acid solution (PWC05-195) to remove
any copper deposits.
(15) Pressure flush the element with cold water at room temperature.
(16) Use clean, dry compressed air to dry the element for 1 to 3 minutes.
(17) Use a 10 power magnification glass to inspect the element for broken wires. Reject
the element if broken wires are found. Sharp and deep dents, if otherwise
acceptable, should not be straightened.
(18) Do a bubble point test with the element submerged 1/2 inch below the surface of
cleaning solvent (PWC11-014) or (PWC11-032) at 22°C (72°F). Rotate the element
slowly and smoothly until first air bubble emerges. Reject the element if the
bubble point value is less than 8 inches - water gage.
NOTE: Slowly increase the air pressure without creating ambient vibrations.
(19) Use clean, dry compressed air to dry the element for 1 to 3 minutes.
G. Vapor Honing
ENGINE - INSPECTION
1. General
A. Personnel engaged on overhaul of the engine should acquaint themselves with the
INTRODUCTION section of this manual (Ref. Outline of Manual Overhaul
Procedures). Certain inspection procedures will refer to the P&WA Standard Practices
Manual P/N 585005 (Ref. 70-30, INSPECTION).
B. Inspection procedures within this manual may refer to the letter prefix SPOP, an
abbreviation for Service Process Operation Procedure, which is followed by a control
number, e.g., SPOP 62, STANDARD FLUORESCENT PENETRANT INSPECTION. For all
SPOP inspection methods, refer to P&WA Standard Practices Manual P/N 585005.
D. Each component must be carefully inspected by trained specialists who are capable of
deciding, when no limits are specified, whether the part is suitable for further service,
requires repair, or must be replaced. In addition to visual inspection for surface fault
conditions, magnetic-particle or fluorescent-penetrant inspection must be carried out
on specific parts to assist detection of cracks or material defects. If no limits are specified,
cracks in any component are cause for its rejection. Where limits for wear or damage
are given, it must be borne in mind that these are maximum limits. At the conclusion of
magnetic-particle inspection, each component must be demagnetized.
E. Surface damage in the form of nicks, dents or scratches, which does not exceed the
limits specified, shall be removed with a fine stone or abrasive cloth. Local smoothing
must extend over an area at least fifteen times the depth of damage. The sharper the
damage, the more desirable it is to have the affected area smoothed. Surface finish
of all repairs must be as smooth as, or smoother than the original finish, and finish marks
must follow the pattern of original machining.
2. Consumable Materials
Not Applicable
3. Special Tools
Not Applicable
Not Applicable
5. Self-locking Fasteners
Engine assembly torque limits are provided in text, or referred to in Table 601 of the
appropriate Chapter/Section for self-locking fasteners i.e., locknuts, helical coil inserts and
self-locking bolts and screws.
TABLE 301, Minimum Acceptable Locking Torque for Self-locking Nuts and Self-locking Helical
Coil Inserts
TORQUE (LB.IN.) TORQUE (LB.IN.)
THREAD SIZE MIN. MAX. THREAD SIZE MIN. MAX.
0.112-40 0.5 3 0.4375-14 16.5 100
0.112-48 0.5 3 0.4375-20 14.0 100
0.138-32 1.0 6 0.500-13 24 150
0.138-40 1.0 6 0.500-20 18 150
0.164-32 1.5 9 0.5625-12 30 200
0.164-36 1.5 9 0.5625-128 24 200
0.190-24 2.0 13 0.625-11 40 300
0.190-32 2.0 13 0.625-18 32 300
0.250-20 4.5 30 0.750-10 60 400
0.250-28 3.5 30 0.750-106 50 400
0.3125-18 7.5 60 0.875-9 82 600
0.3125-24 6.5 60 0.875-14 70 600
0.375-16 12.0 80 1.000-8 110 800
0.375-24 9.5 80 1.000-12 90 800
Self-locking fasteners are reused at overhaul, if limits specified in Table 301 can be obtained
with mating parts identical to those used on the engine.
Or, where necessary, torque can be verified at reassembly with the locking feature fully
engaged and the fastener unseated (not in contact with any other part), so that only the
frictional hold on the screw thread is measured.
Unless otherwise specified, apply thread lubricant to all parts to be torqued, using engine oil
(Ref. SB1001), or equivalent.
Torque required to overcome static friction shall not be less than the value given in the
minimum breakaway torque column, Table 301.
Torque required to overcome kinetic friction shall not be greater than the value given in the
maximum locking torque column, Table 301.
(a) The total operating hours (accumulated) of certain engine parts are required for
record or warranty purposes. Engine parts in this category are marked at
manufacture with a serial number placed on a convenient and, whenever
possible, plainly visible surface.
(b) Serialized engine parts include: combustion chamber liner, main antifriction
bearings, etc.
(c) Serialized engine accessories include: engine-driven pump, fuel control unit,
compressor bleed valve, ignition exciter, etc.
(a) The engine-logged service time between each overhaul in hours and cycles
shall be marked on each life-limited rotor component part listed (Ref.
05-10-00 and SB1002).
(1) Although engine main bearings Nos. 1 through 4 and the propeller reduction
gearbox bearings are retired on condition only, it is considered beneficial to maintain
a record of their accumulated hours in either of the following ways:
A. Standard Instructions
(1) Tubing
C41344
Specimen Inspection Record Sheet
Figure 301
(a) Circumferential scratches in tubes are acceptable provided they do not exceed
a 45 degree segment on circumference. Any number of scratches is permissible;
these may be blended out provided depth of blend does not exceed 0.005
inch.
(b) Longitudinal scratches in tubes must not exceed one-half inch in length. Any
number of scratches is permissible.
(c) Nicks and chafing marks in tubes are acceptable and may be blended provided
they do not exceed 0.005 inch in depth. Each blended area must not exceed
one-half square inch.
(d) Dents in tubes are of limited acceptability, provided there are no restrictions to
flow caused by sharp edges or corners. Dents are unacceptable within one
inch of ferrule scarf-welds, or in a blended area.
(e) Minor isolated pitting is acceptable if not greater than 0.003 inch in depth.
Clusters of pits should be blended out to a maximum depth of 0.005 inch.
(f) Rust and stains on tubes are acceptable if they can be removed by light
polishing with a very mild abrasive.
(h) Examine coupling and threaded fittings for cracks or damaged threads.
(2) Hoses
(a) High pressure hoses that operate at pressures above 150 psig must be
rejected if any crimps or buckles are evident.
(a) Hoses with cuts in metal braid, having more than three broken wires per plait,
or more than six broken wires per linear foot, must be replaced.
(b) Replace flexible hoses where braid wires have chafed or worn to inner liner.
(a) Test high pressure hoses with hydraulic fluid at 3,000 psig. Maintain pressure
for a minimum of two minutes.
A. Inspection Procedures
B. Bearing Repairs
No bearing repairs are permitted other than the repairs contained in P&WC approved
manuals or the Anti-Friction Bearing Visual Inspection Standard P/N 3039731.
(b) To ensure correct readings, use a dial bore gage, or a similar gage operating
on the air-gap principle; both types of instrument have to be capable of
measuring accurately within 0.0001 inch with a gage force not exceeding four
ounces.
(c) Reject any bearing assembly having I.D. or O.D. dimensions outside the limits
specified in Table 302, for the particular bearing.
NOTE: The following general inspection procedures should be used for all gears and
gearshafts except where more specific inspection procedures/data are detailed in
the relevant chapters of this manual.
(2) Surface Pitting: Accept pitting damage up to 0.005 inch deep and 0.010 inch
diameter, provided no more than five pits are found in 0.250 inch diameter area.
(4) Localized Nicks, Dents or Scratches: Remove sharp edges and blend damage up
to 0.003 inch deep and 0.010 inch wide, provided a minimum 80% of total tooth
surface contact pattern remains. Polish to restore original surface finish and maintain
tooth profile.
(5) Uneven Tooth Surface Contact Pattern: Damage up to 0.003 inch deep is
acceptable, provided a minimum of 80% of the total tooth surface contact pattern
remains. Polish to restore original surface finish and maintain tooth profile.
(1) Inspect gears and gearshafts using appropriate SPOP (Refer to relevant chapter for
specific SPOP callout).
(1) Localized Nicks, Dents or Scratches: Damage up to 0.002 inch deep without high
spots and not extending across more than 50% of sealing face is acceptable. Lap
face if damage exceeds limits.
(2) Runout: Runout must be 0.001 inch FIR in relation to datums unless otherwise
stated.
(3) Flatness: Flatness must be within two helium light bands. Lap face (Ref. Repair) if
flatness exceeds limits.
D. Inspect Splines
(1) Surface Pitting: Accepts pitting damage up to 0.005 inch deep by 0.015 inch
diameter, provided no more than five pits are found in 0.250 inch diameter area.
(3) Localized Nicks, Dents or Scratches: Remove sharp edges and blend damage up
to 0.005 inch deep and 0.010 inch wide, provided a minimum 80% of total spline
surface contact pattern remains. Polish to restore original surface finish and maintain
spline profile.
(4) Galling: Remove damage up to 0.005 inch deep by polishing to restore original
surface finish. Maintain original spline profile.
(5) Wear, Uneven Spline Surface Contact Pattern: Damage up to 0.005 inch deep is
acceptable, provided a minimum of 80% of the total spline surface contact pattern
remains. Polish to restore original surface finish and maintain spline profile.
E. Inspect Threads
(1) Surface Pitting: Accept pitting damage up to 0.003 inch deep by 0.010 inch
diameter, provided no more than three pits are found in 0.250 inch length.
(3) Localized Nicks, Dents or Scratches: Remove sharp edges and blend damage up
to 0.005 inch deep and 0.010 inch wide, provided a minimum 90% of total thread
contact pattern remains. Polish to restore original surface finish and maintain original
thread profile.
(4) Galling: Remove damage up to 0.005 inch deep by polishing to restore original
surface finish. Maintain original thread profile.
(1) Surface Pitting: Accept pitting damage up to 0.005 inch deep by 0.015 inch
diameter, provided no more than five pits are found in 0.250 inch diameter area.
(3) Localized Nicks, Dents or Scratches: Remove sharp edges and blend damage up
to 0.005 inch deep and 0.010 inch wide. Polish to restore original surface finish.
NOTE: The following inspection is for damage on bearing diameters having direct
contact with balls/rollers of bearing.
(3) Localized Nicks, Dents or Scratches: Remove sharp edges and blend damage up
to 0.005 inch deep and 0.010 inch wide, provided damage is 0.050 inch minimum
apart. Polish to restore original surface finish and maintain geometric tolerances.
(4) Scratches or Scoring: Remove sharp edges and blend damage up to 0.005 inch
deep and 0.010 inch wide, provided damage is 0.050 inch minimum apart. Polish
to restore original surface finish and maintain geometric tolerances.
(1) Surface Pitting: Accept minor pitting damage up to 0.005 inch deep by 0.015 inch
diameter, provided no more than five pits are found in 0.250 inch diameter area.
(3) Localized Nicks, Dents or Scratches: Remove sharp edges and blend damage up
to 0.010 inch deep and 0.010 inch wide. Polish to restore original surface finish and
maintain geometric tolerances.
(1) Remove surface stains, corrosion deposits up to 0.001 inch deep using SPOP 16 .
Prior to wet glass bead blasting, mask the following areas:
ENGINE - REPAIR
1. General
A. Personnel engaged in overhaul of the engine should acquaint themselves with the
INTRODUCTION section of this manual to familiarize themselves with general overhaul
procedures (Ref. Outline of Overhaul Procedures).
B. Specific repairs are provided in certain chapters of the manual; repairs common in many
areas of the engine are described in this chapter, e.g., helical coil inserts, oversize stud
holes, etc. Standard repairs should be used where specified (Ref. P&WA Standard
Practices Manual P/N 585005).
C. Many repair procedures refer to the letter prefix SPOP, an abbreviation for Service
Process Operation Procedure, which is followed by a control number, e.g., SPOP 21,
CADMIUM PLATE. Whenever any repair SPOP method is required, refer to P&WA
Standard Practices Manual P/N 585005 for detailed information.
D. These instructions have been written with the understanding that all components have
been cleaned, inspected and tagged to indicate suitability for further service, require
repair or must be replaced.
2. Consumable Materials
The consumable materials listed below are used in the following procedures.
For alternate products, suppliers and suppliers addresses refer to Consumables Material List
P/N 3043340.
Not Applicable
Not Applicable
(3) If local spots persist on component, mask as required, and remove by dry
plastic blast per SPOP 19.
(3) Mask studs, pins, helical coil inserts, jacking inserts and internal sleeves per
SPOP 36.
(4) Bake for 20 minutes minimum at 143° to 154 °C (290° to 310 °F).
(5) Cool down to room temperature and make sure that masking is still in place.
NOTE: Use thinner (PWC07-016) as required to obtain proper viscosity for the
spray gun.
(6) Apply, as soon as possible, surface sealant (PWC07-017) to make sure that
moisture is not absorbed.
NOTE: Mix per manufacturer’s recommendations and apply coat (total thickness
of 0.00025 to 0.00045 inch).
(7) Air dry for 15 to 30 minutes at room temperature in a dust free atmosphere.
(8) Cure first coat for 15 minutes at 195° to 200 °C (385° to 400 °F).
(9) Bake final coat for 45 to 60 minutes at 195° to 200 °C (385 to 400 °F).
(10) Restore epoxy primer and aluminized enamel paint per SPOP 148 except, bake
enamel paint for 45 minutes at 143° to 149 °C (290° to 300 °F).
(1) Degrease component per SPOP 209 or locally degrease reworked area per
SPOP 208.
(3) Mask studs, pins, helical coil inserts, jacking inserts and internal sleeves per
SPOP 36.
(4) Prepare two-part epoxy coating (PWC07-037) by mixing one part by volume of
resin with one part by volume of catalyst.
NOTE: Coating may be applied by either a brush or spray gun. Use thinner
(PWC07-016) as required to obtain proper viscosity for the spray gun.
(5) Bake for 20 minutes minimum at 143° to 154 °C (290° to 310 °F).
(9) Bake for one hour at 93° to 121 °C (200° to 250 °F).
(10) Locally restore epoxy primer and aluminized enamel paint on reworked areas per
SPOP 148 except, bake enamel paint for 45 minutes at 143° to 149 °C (290° to
300 °F).
6. General Procedures
A. Oversize studs are installed as replacements for those parts which are stretched, loose
or have damaged threads. Should a stud that is already oversize require replacement,
use the next oversize stud. Use the correct stud drivers to insert new studs and torque to
values given (Ref. 70-52, P&WA Standard Practices Manual). The Illustrated Parts
Catalog for the engine contains part numbers and location of studs.
B. When threads of a stud hole are damaged beyond dimensions suitable for a maximum
oversized stud, they may be repaired using a helical coil insert (Ref. Para. 7., following).
The Parts Catalog may provide part numbers and locations of suitable helical coil
inserts. Before other methods of replacing studs are attempted, e.g., standard insert or
solid inserts, ensure sufficient material remains around the repair so as not to impair
the integrity of cavity walls, etc.
9. Weld Repair
A. Welding Procedures
B. Weld Repairs
(1) Unless otherwise directed, stress relief after welding is not required.
(2) A new weld shall not be applied over an existing weld repair.
(3) Weld beads shall be dressed to within 0.005 inch of adjacent parent metal. No
undercutting is permissible
(4) The width of weld bead shall not exceed 0.150 inch at any point.
(1) Soften cement between grommet and clamp with cleaning solvent (PWC11-023),
and remove grommet and all residual cement from clamp.
(2) Roll new grommet around suitable rod to obtain required inside diameter (dia. A).
Exercise care when forming loop to avoid damaging grommet.
(3) Wipe mating surfaces of clamp and grommet with a clean, lint-free cloth moistened
in cleaning solvent (PWC11-023), to ensure clean and dry contact areas for
application of cement.
(4) Apply a thin film of cement (PWC09-004) to designated areas on loop clamp and
grommet.
(5) Position grommet in loop clamp, align as shown and press cemented surfaces
together. Allow cement to cure for 24 hours at room temperature.
(6) Check adhesion of grommet to loop clamp. If unsatisfactory, repeat steps (1)
through (5).
For copper plating (PS 304) and service process solutions refer to Standard Practices
Manual 70-44-02.
GROMMET
DIA. A
LOOP CLAMP
A
VIEW A−A
C13462
Replacement of Loop Clamp Grommet
Figure 401
(1) Stainless steel oil tubes with round-bottom dents found in Area a can be repaired
as follows.
(2) Insert a brass rod of the appropriate size into the tube damaged area and secure
the other end of the brass rod in a vise or other suitable holder. The brass rod
should be the largest diameter that will fit into the tube without damaging the ferrule.
(3) Use a suitable smooth-faced hammer to lightly tap the tube outer wall surface to
re-shape the tube to its original shape. Rework the damaged areas of the tube in
small increments with light hammer blows. Attempts to rework large areas with single
hammer blows could result in the tube being rejected.
(4) Make sure that the ferrule or other areas of the tube were not damaged during
rework.
WARNING: COMPRESSED AIR CAN CAUSE SERIOUS INJURY. MAKE SURE THE
TUBE IS TESTED IN A MANNER SO THAT PERSONNEL ARE
PROTECTED IN THE EVENT OF A TUBE FRACTURE OR FAILURE.
(6) Pressure test the tube at 150 to 200 psi. No leakage is permitted.
B. Repair Oil Tubes With Damaged Ferrules Or Dents (Area b, Fig. 402)
(1) Stainless steel oil tubes dented within 0.750 inch from the ferrule (Area b), can be
repaired without removing the ferrule, provided that the ferrule is not damaged. If
the ferrule is not damaged, rework the tube to remove dents in Area b, (Ref. Para. A.,
steps (2) to (6)).
(a) Locally heat the ferrule until able to remove it from the tube. Discard the
damaged ferrule or retain undamaged ferrule.
(c) Rework the damaged tube to remove dents in Area b (Ref. Para. A., steps (2)
to (5).
(d) Prepare ferrule and tube for brazing according to AMS 2664:
(e) Install new or undamaged ferrule on the tube in its original position.
(f) Support the assembled tube in its required length and alignment.
(g) Braze the ferrule on the tube according to AMS 2664 using torch-braze (neutral
flame) with brazing rod (PWC08-005).
(i) Inspect brazed area for continuity of braze all around the ferrule.
(3) Clean the tube assembly (Ref. Chapter 79-20-01 or 79-20-04, CLEANING).
BRAZE FERRULE
0.750 0.750
b a b
C80605
Repair of Stainless Steel Oil Tube (Typical)
Figure 402
1. General
A. Personnel engaged in final assembly of the engine should refer to the INTRODUCTION
section of this manual to familiarize themselves with general overhaul procedures (Ref.
Outline of Manual Overhaul Procedures).
B. Final assembly is divided into three sections: FINAL ASSEMBLY-1 through FINAL
ASSEMBLY-3.
ENGINE FINAL ASSEMBLY-1: ENGINE ASSEMBLY
ENGINE FINAL ASSEMBLY-2 : ACCESSORY AND EXTERNAL COMPONENTS
ENGINE FINAL ASSEMBLY-3 : FINAL CHECKS
D. Do not allow loop clamps to move cables from their natural contour when tightening
attachment bolts, as chafing of cable will result.
2. Consumable Materials
The consumable materials listed below are used in the following procedures.
For alternate products, suppliers and suppliers addresses refer to Consumables Material List
P/N 3043340.
The special tools listed below are used in the following procedures.
Not Applicable
A. Installation of Accessory Gearbox Assembly to Gas Generator Assembly (Ref. Fig. 503)
(1) With accessory gearbox assembly and gas generator assembly assembled to
standard detailed in Chapters 72-60-00 and 72-30-00 respectively, and with gas
generator assembly mounted in stand (Ref. 72-30-00), proceed as follows:
(a) Remove storage protection or sealing materials from rear face of gas generator
assembly and front face of accessory gearbox, in preparation for assembly.
(b) Ensure that transfer tubes and associated preformed packings are installed
correctly on rear face of inlet case and have not been disturbed since
assembly of gas generator assembly.
(c) Make sure that ball-lock spring, plug and associated parts are in position in
compressor hub coupling shaft (15).
(d) Slowly rotate compressor until hole in compressor hub coupling shaft (15) is at
12 o’clock position. Place lock ball (19) in hole, and pack with petrolatum
(PWC06-002)) to retain ball during following assembly (Ref. Fig. 503, Sheet 2).
(e) Install preformed packings (16) and (18) on oil tank center tube (17), and insert
tube into centerbore of inlet case.
(f) Install preformed packing (2) on spigot of accessory gearbox diaphragm (14).
(g) Lift gearbox onto gas generator assembly, aligning dowel in diaphragm with hole
in compressor inlet case (22). Locate gearbox on inlet case studs and align
coupling shaft, oil transfer tubes and oil tank center tube, taking care not to
damage preformed packings.
(h) Insert pusher tool (PWC30373) through rear of gearbox housing at plug (8)
location. Engage threaded end of pusher with threaded drive gearshaft,
connected to input coupling shaft (1), and screw body of pusher into gearbox
housing. Back-off nut on pusher sufficiently to allow full forward travel of pusher
for engagement of coupling shaft (1) with lock ball (19) on compressor rear
hub coupling (15).
(j) Install spacers, brackets and plain washers (Ref. Figs. 501 and 502). Install a
self-locking nut on each of 16 studs. Tighten nuts in a diametric sequence and
torque 32 to 36 lb.in.
(l) Install preformed packing (7, Fig. 503) on plug (8). Install plug and torque 150
to 160 lb.in.
(m) Install preformed packings (20) on oil transfer tube (21); insert assembly in
boss at 7 o’clock position at bottom of inlet case.
6. Power Section
(1) With power section and gas generator assembly assembled to standard detailed in
Chapters 72-01-00 and 72-30-00 respectively, and gas generator assembly
mounted in a vertical position in stand (Ref. 72-30-00), proceed as follows:
(a) Place overhauled power section in stand (Ref. 72-01-00, SUB-ASSEMBLY) into
a vertical position.
(b) Locate sling (2) (PWC30037) on propeller mounting flange, and engage dowels
in flange bolt holes. Secure sling to flange with four socket-head cap screws
(1).
(c) Attach hoist to nose ring on sling to take weight of power section, and remove
bolts securing mount ring to exhaust duct.
(e) Ensure that protective covers installed during overhaul of power section and
gas generator assembly are removed.
(f) Check that gas generator case flange C, and power section exhaust duct
flange C, are clean, free from nicks, scratches, dents and other damage
likely to affect sealing efficiency. Smear a thin layer of compound (PWC09-022)
on exhaust flange before assembly.
1 Two ring Pre-SB1218; install so that ring gaps are diametrically opposite
each other, one gap at TDC.
(h) Rotate gas generator assembly (6) in stand so that flange C is uppermost.
12
14
SCAVENGE OIL 38
VIEW OF FLANGE A COUPLING 37
36
(LOOKING FORWARD)
28 27
PRESSURE OIL
NO. 31 COUPLING
MOUNTING HOLES FOR OIL−TO−FUEL VIEW OF FLANGE C
HEATER. WASHER REQUIRED (LOOKING FORWARD)
ENGINE LIFTING BRACKET
MOUNTING HOLES FOR PROPELLER
REVERSING LINKAGE
16
SPACER REQUIRED 15 1
2 ELECTRICAL RECEPTACLE
14 BRACKET
13 3
SPACER REQUIRED
❉
12 4
❉
SPACER REQUIRED
11 5
C8512C
Bracket Location on Flanges - PT6A-21 Pre-SB1330 Engines
Figure 501
(i) Lower power section onto gas generator case until mating flanges are six
inches apart.
(j) Install new gasket on terminal block (4) of T5 thermocouple wiring harness.
Insert block through gas generator case; ensure that gasket is correctly
positioned and secure with two bolts. Tighten bolts, torque 36 to 40 lb.in. and
lockwire.
NOTE: If bolts securing terminal block have been removed, ensure they are
reinstalled as described in preceding step.
(l) Perform loop and ground resistance checks of T5 system (Ref. 72-01-00,
SUB-ASSEMBLY).
(m) During insertion of Dee-headed bolts (5) through mating flanges of power
section and gas generator case, assemble propeller governor pneumatic
(Py) tube bracket, reversing control wire rope casing bracket, and scavenge
and pressure oil couplings at locations shown on Figures 501 and 502. Install
self-locking nuts (3) on each bolt and torque nuts 36 to 40 lb.in.
7. Installation of Fireseals
A. Center Fireseal
(a) Place top center fireseal mount ring (1) on engine, and secure support brackets
(5) to fireseal with bolts and nuts, and to integral support brackets (8) with bolts
(7), washers and self-locking nuts (6), fingertight.
(b) Place bottom center fireseal mount ring (4) on engine, and secure support
brackets (5) to fireseal with bolts and nuts, and to integral support brackets
(8) with bolts (7), washers and self-locking nuts (6), fingertight.
(c) Attach top mount ring (1) to bottom mount ring (4) with bolts (3) inserted from
bottom on left side and from top on right side, and secure with self-locking nuts
(2); torque nuts 36 to 48 lb. in.
(d) Tighten and torque nuts fitted in step (a) and (b), 36 to 40 lb. in.
2
35 36 1
5
12
14
38
37
36
VIEW OF FLANGE A
28 27
(LOOKING FORWARD)
MOUNTING HOLES FOR OIL−TO−FUEL SCAVENGE OIL
COUPLING NO. 31 PRESSURE OIL
HEATER. WASHER REQUIRED
VIEW OF FLANGE C COUPLING
ENGINE LIFTING (LOOKING FORWARD)
BRACKET
16 MOUNTING HOLES FOR PROPELLER
SPACER 15 1 REVERSING LINKAGE
REQUIRED 14 2 ELECTRICAL RECEPTACLE BRACKET
12 4
LOOP CLAMP SUPPORTING ELECTRICAL
❉
C8475C
Bracket Location on Flanges - PT6A-27/-28 Pre-SB1330/Post-SB1343 Engines
Figure 502 (Sheet 1 of 2)
ENGINE LIFTING
BRACKET
16
SPACER 15 1 MOUNTING HOLES FOR PROPELLER
REQUIRED 14 2 REVERSING LINKAGE
13 3
❉
12 4
SPACER P3 FILTER BRACKET
❉
REQUIRED 11 ❉ 5
FUEL PRESSURE TUBE
10 6 MOUNTING BRACKET
ANGLE
BRACKETS 9 7
8
NOTE
DIAPHRAGM TO HOUSING ATTACHMENT SCREWS
❉
ARE FITTED AT POSITIONS MARKED THUS AND
WASHER REQUIRED SPACER ARE ONLY TO BE LOOSENED OR TIGHTENED WHEN
REQUIRED DISMANTLING GEARBOX ASSEMBLY.
VIEW OF FLANGE G
(LOOKING FORWARD)
MOUNTING HOLES FOR OIL−TO−FUEL
HEATER. WASHER REQUIRED
ENGINE LIFTING
BRACKET
16
SPACER 15 1 MOUNTING HOLES FOR PROPELLER
REQUIRED 14 2 REVERSING LINKAGE
13 3
❉
❉
12 4 P3 FILTER BRACKET
SPACER
❉
C10252
Bracket Location on Flanges - PT6A-27/-28 Pre-SB1330/Post-SB1343 Engines
Figure 502 (Sheet 2)
4
2
5
6
10
9
A 7 8
23
11
12
22
14
20
21 13
6
1 14
19
15
16
17
18 VIEW A
C7483B
Installation of Accessory Gearbox
Figure 503 (Sheet 1 of 2)
1. Coupling Shaft
2. Preformed Packing
3. Washer
4. Engine Lifting Bracket
5. Self-locking Nut
6. Accessory Gearbox Housing
7. Preformed Packing
8. Plug
9. Starter-generator Overboard Drain Adapter (Ref.)
10. Drain Adapter Cap (Ref.)
11. Preformed Packing
12. Accessory Gearbox Oil Drain Plug
13. Adapter (Typical) (Engines with vacuum pump drive), or Tee
(Engines without vacuum pump drive)
14. Diaphragm
15. Compressor Hub Coupling Shaft
16. Preformed Packing
17. Oil Tank Center Tube
18. Preformed Packing
19. Lock Ball
20. Preformed Packing
21. Oil Transfer Tube
22. Compressor Inlet Case
23. Spacers
24. Screw
25. Nut
26. Body
24
25
26 B
24
25
26
DETAIL B
1
19
A
DETAIL A
15 LOCK−BALL ARRANGEMENT
C13622
Installation of Accessory Gearbox
Figure 503 (Sheet 2)
(e) Install external lines and components passing through center fireseal mount
ring.
B. Rear Fireseal and Compressor Wash Ring (if fitted) (Ref. Fig. 505)
(1) The following procedure should be adapted to suit the installation if engine does not
incorporate compressor wash ring option.
(a) Remove protective material and air inlet screen from compressor inlet case
(Ref. 72-30-00, DISASSEMBLY).
(b) Locate top and bottom rear fireseal sections (16) and (23) around inlet case
and secure together with two bolts (19) and nuts (17), fingertight.
(c) Align holes in upper support bracket (15) with holes in top half of fireseal and
secure together with bolts (12), washers (14) and nuts (13), fingertight.
(d) Secure lower support bracket (18) to bottom half fireseal (23) with bolts (22)
and nuts (21), fingertight.
NOTE: Nuts and bolts securing lower support bracket will be tightened and
torqued during installation of ignition cables at a later stage.
(f) Install air inlet screen and protective material (Ref. 72-30-00, SUB-ASSEMBLY)
on compressor inlet case.
(1) On engines fitted with compressor wash ring (Ref. IPC), install with rear fireseal as
follows (Ref. Fig. 505):
(a) Remove protective material and air inlet screen from compressor inlet case
(Ref. 72-30-00, DISASSEMBLY).
(b) Locate top and bottom rear fireseal sections (16) and (23) around inlet case
and secure together with two bolts (19) and nuts (17), fingertight.
2
8
3
FLANGE C 4
C7214
Installation of Power Section on Gas Generator Case
Figure 504
(c) Position compressor wash ring (20), with its bracket holes aligned with holes
in top half of fireseal (16) and upper support bracket (15), and secure together
with two bolts (12), washers (14) and nuts (13), fingertight.
(d) Place compressor wash ring (9), complete with tee (11) and cap (10), on
compressor inlet case, and connect coupling nut of tube (20) to tee.
(e) Correctly align top and bottom fireseal sections (16) and (23) and wash rings
(9) and (20); tighten nuts (13) and (17) and torque 36 to 40 lb.in.
(f) Install air inlet screen and protective material (Ref. 72-30-00, SUB-ASSEMBLY)
on compressor inlet case.
(g) Tighten tube (20) coupling nut to tee (11), torque 270 to 300 lb.in. and lockwire.
(h) Secure lower support bracket (18) to bottom half fireseal (23) with bolts (22)
and nuts (21), fingertight.
NOTE: Nuts and bolts securing lower support bracket will be tightened and
torqued during installation of ignition cables at a later stage.
10 16 15 13
11 14
1 12
18
17
23
8
A
2
GAS
GENERATOR 3
CASE
IGNITION CABLES
22 19
8 20
7
17
4
24
5
19
6
3
DETAIL A
C41544
Center and Rear Fireseals
Figure 505
1. General
A. Personnel engaged in the final assembly of the engine should read the Introduction
sections of this manual to familiarize themselves with general overhaul procedures
(Ref. INTRODUCTION, Outline of Overhaul Procedures).
B. Final assembly is divided into three sections: FINAL ASSEMBLY-1 through FINAL
ASSEMBLY-3.
ENGINE FINAL ASSEMBLY-1: ENGINE ASSEMBLY
ENGINE FINAL ASSEMBLY-2: ACCESSORY AND EXTERNAL COMPONENTS
ENGINE FINAL ASSEMBLY-3: FINAL CHECKS
C. The type of lockwire (safety wire) used during assembly shall comply with Specification
AMS5687 which, unless otherwise specified, is 0.025 inch diameter, heat and corrosion
resistant steel wire (PWC05-089) and will not be specified in assembly instructions.
D. Do not allow loop clamps to move cables from their natural contour, when tightening
attachment bolts, as chafing of cable will result.
E. Refer to Final Assembly-1 and Figure 501 for bracket location before finally making any
flange joint.
G. Where aluminum foil seal retaining plates are installed on external tubes at fireseals, the
plates must be installed so that the aluminum foil faces the fireseal mount ring.
2. Consumable Materials
The consumable materials listed below are used in the following procedures.
For alternate products, suppliers, and suppliers addresses, refer to Consumable Materials
List P/N 3043340.
The special tools listed below are used in the following procedures.
Not Applicable
A. Oil Filter Element, Filter Housing and Check Valve Assembly (Ref. Fig. 501)
(a) Install new preformed packing (12) in groove at inner end of oil filter housing
(1).
(b) Install packing retainer (11) (Pre-SB1127), or plastic ring (11) (Post-SB1127),
on inner section of groove at center of housing.
(c) Assemble preformed packing (10) SB1127 in outer section of groove, against
packing retainer or plastic ring (11).
NOTE: When incorporating Post-SB1127, the existing oil filter housing (1),
preformed packing (10) and packing retainers (11) are replaced within
new items of an improved configuration.
(d) Insert oil filter housing and check valve assembly (1) into compressor inlet case
and, using hand pressure, push assembly in until firmly seated.
NOTE: Do not apply side loads on housing while being pressed into inlet
case.
(e) Assemble new preformed packings (2) Post-SB1118 and (4) on filter element
(3).
(f) Install filter element (3) (perforated flanged end first) into filter housing (1) in
compressor inlet case.
NOTE: Ensure teflon spacer (6) is in position and secure on lugs of filter
cover.
(h) Install filter cover on compressor inlet case mounting (13), and secure with four
plain washers (9) and self-locking nuts (8). Tighten nuts and torque 32 to
36 lb.in.
(b) Install starting control (5) on mounting studs on flange G (Ref. Final Assembly-1,
Fig. 502). Secure with two washers (4, Fig. 502) and self-locking nuts (3).
Tighten nuts and torque 32 to 36 lb.in.
(c) Secure bracket (2) to starting control (5) with bolt (1); torque 32 to 36 lb.in. and
lockwire (PWC05-089).
NOTE: It may be more convenient to pre-assemble fuel pump to fuel control unit
(Ref. Paras. D. and E. following) on the bench, then install units together
on engine.
(a) Remove protective caps from inlet and outlet ports of pump and drain off any
preservation fluid.
(b) Install gasket (4) on mounting pad studs of accessory gearbox (5).
1
2
B 3
4
5 A
6
13 7
VIEW A
12 9
1 8
11
10
13
PRE−SB1247
VIEW B
12
1
11
10
POST−SB1247
VIEW B
C7855
Installation of Oil Filter Element, Housing and Check Valve Assembly
Figure 501
(e) Functional check of pump will be conducted at engine testing (Ref. Testing).
3 4
FLANGE G
2
5
C7479
Installation of Starting Control
Figure 502
1. Bolt
2. Mounting Bracket
3. Self-locking Nut
4. Washer
5. Starting Control
(a) Remove blanking caps and drain preservation fluid from fuel control unit.
(d) Install fuel control unit (1) on fuel pump and engage with splined coupling (5).
Carefully place FCU on studs of pump and secure with washers (3) and
self-locking nuts (2). Tighten nuts and torque 75 to 85 lb.in.
(e) Serrated spacer (4), fuel control arm (9) and arm extension (8) remain loosely
assembled at this stage. For final adjustment, refer to appropriate procedure of
Paragraph 6., following.
(a) Remove blanking caps and drain preservation fluid from fuel control unit.
(d) Install fuel control unit (1) on fuel pump and engage with splined coupling (4).
Carefully place FCU on studs of pump and secure with washers (3) and
self-locking nuts (2). Tighten nuts and torque 75 to 85 lb.in.
(e) Serrated spacer (13), fuel control arm (14) and arm extension (15) remain
loosely assembled at this stage. For final adjustment, refer to appropriate
procedure of Paragraph 5., following:
3 4 5
2
C7173
Installation of Fuel Pump
Figure 503
1. Fuel Pump
2. Self-locking Nut
3. Washer
4. Gasket
5. Accessory Gearbox Mounting Boss
(f) Locate interconnect rod (10) between arm on fuel control unit and arm on starting
control. Temporarily secure upper rod end connector with bolt (6), spacer (7),
washer (8) and castellated nut (9), and lower rod end connector with bolt (6),
spacers (11) and (12), washer (8) and castellated nut (9).
NOTE: Castellated nuts will be torqued and locked with cotterpins after final
adjustment of interconnect rod.
(1) With oil-to-fuel heater and oil return check valve overhauled to Chapter 73-10-01:
(a) Remove blanking caps and drain preservation fluid from oil and fuel ports of
oil-to-fuel heater.
(b) Remove blanking caps from oil return check valve assembly (4), and install
preformed packings (2) and (5) in their respective grooves.
(c) Locate check valve (4) in oil-to-fuel heater port, and insert large end of valve
through hole in lifting bracket (6) to engage with adapter (1) and studs at
flange G.
(d) Secure oil-to-fuel heater to studs with two washers and self-locking nuts; torque
nuts 32 to 36 lb.in.
(e) Retain check valve assembly (4) to adapter (1) with retaining plate (3) and two
bolts. Torque bolts 32 to 36 lb.in. and lockwire .
(a) Install new preformed packing (19) on spigot of check valve spring seat (18).
(b) Insert check valve (21), valve spring (20) and check valve seat (18) into check
valve sleeve (22), and secure with retaining ring (17).
(c) Install three new preformed packings (23) on check valve sleeve (22) and
insert into check valve housing (24).
6
1
5
2 3 4
(d) Install new preformed packings (25) and (26) on check valve housing (24),
and insert check valve housing into port at 2 o’clock position on compressor
inlet case.
(f) Install adapter (15) and rear fireseal mount ring support bracket (14) on check
valve housing (24) and secure to compressor inlet case with two bolts. Tighten
and torque bolts 36 to 40 lb.in. and lockwire (PWC05-089).
(g) Assemble nut (11), backup ring (12) and new preformed packing (13) on elbow
(10).
(h) Install elbow (10) in adapter (15) and position at angle noted on original
installation (Ref. INTRODUCTION for elbow assembly procedures).
(i) Install oil tube assembly (9) between elbow on check valve assembly and
elbow on oil-to-fuel heater (8). Tighten and torque coupling nuts 90 to
100 lb.in.
(a) Lightly lubricate new preformed packing (2) and install on nipple (3).
(b) Screw nipple (3) into governor Py port and torque 65 to 75 lb.in.
(c) Place new gasket (6) on gearbox mounting pad, raised surface uppermost.
1 2 3
6 5
4
FUEL PUMP
13
14
15
7
8
10
10
6
(d) Install governor (1) over studs and engage drive splines. If necessary, rotate
propeller shaft to assist drive engagement. Ensure governor flange is fully
seated on gasket and install washers (5) and nuts (4). Tighten and torque nuts
(REF. NO. 186, Table 601) using wrench (Ref. PWC30114-09 or
PWC30114-16), as appropriate.
NOTE: The ignition regulator is associated with engines that incorporate the glow
plug ignition system.
(a) Locate regulator (1) on three mounting bosses of the accessory gearbox at the
8 o’clock position.
(b) Secure regulator with three washers (2) and bolts (3); tighten and torque bolts
36 to 40 lb.in. and lockwire (PWC05-089).
NOTE: The ignition exciter is associated with engines that incorporate the spark
igniter ignition system.
(a) Locate mounting bracket (2) on three mounting bosses of the accessory
gearbox at the 8 o’clock position.
1 2 3 4
5
COMPRESSOR
INLET CASE 7
6 8 9
10
FLANGE G
9
11
12
3
14
15
16
23 17
24 18
25 19
26 20
21
22
COMPRESSOR
INLET CASE
C7477
Installation of Oil-to-fuel Heater and Check Valves
Figure 506
(b) Secure bracket with three washers (7) and bolts (6); tighten and torque bolts 36
to 40 lb.in. and lockwire (PWC05-089).
(c) Install vibration absorber mounts (10) Post-SB1422 in holes in bracket (2) and
insert sleeves (11) into mounts.
(e) Secure exciter with four bolts (1), washers (4) and self-locking nuts (5)
Pre-SB1422; torque nuts 36 to 40 lb.in. Alternatively, secure exciter with bolts
(12), washers (9) and nuts (8) Post-SB1422; torque nuts 36 to 40 lb.in.
1
2
3
C7199
Installation of Propeller Governor
Figure 507
6. Installation of Externals
A. Fuel Delivery Tubes and Flexible Hoses (PT6A-21 Engines) (Ref. Fig. 510)
(1) Secure coupling nuts of flexible hose (1) to straight nipple on fuel pump and elbow
on FCU. Torque coupling nuts 170 to 200 lb.in. and lockwire.
NOTE: Make sure hose fits snugly between FCU and fuel pump fittings without
forcing or twisting.
(2) Secure coupling nuts of flexible hose (2) to elbow on fuel pump and straight nipple
on oil-to-fuel heater. Tighten coupling nuts, torque 450 to 500 lb.in., and lockwire.
(3) Insert coupling (6) into bracket (5) of flange G. Secure coupling with jam nut (4)
and torque nut 38 to 42 lb.in.
(4) Slide tube seals (17) over fuel pressure tube (20) on each side of centre fireseal
mount ring. Butt seals against mount ring. Position insulations (16) next to seals
and retaining plates (15) next to insulations.
(5) Slide tube seals (9) over fuel pressure tube (20) on each side of rear fireseal mount
ring. Butt seals against mount ring. Position insulations (8) next to seals and
retaining plates (7) next to insulations.
(7) Secure loop clamps (12 and 23) to fuel pressure tube (20).
(8) Secure loop clamp (12) to support bracket (22) to rear of fuel drain valve on gas
generator case with washer(s) (21), nut (13) and bolt (14). Tighten nut and torque
36 to 40 lb.in.
NOTE: To align front fuel tube, a maximum of two spacing washers may be
positioned between loop clamps and support bracket.
1
ACCESSORY GEARBOX
2
3
2
3
C7481
Installation of Ignition Current Regulator
Figure 508
1. Ignition Regulator
2. Washer
3. Bolt
(9) Secure coupling nuts of tube (20) to bulkhead coupling (6) and elbow on flow divider
and dump valve. Torque coupling nuts 90 to 100 lb.in., and lockwire.
(10) For Pre-SB1471 Engines: Connect rear fuel pressure tube (3) between bulkhead
coupling (6) and connector on fuel control unit. Tighten tube coupling nut, torque
270 to 300 lb.in. and lockwire.
(a) Remove existing bolt and use to secure bracket (29) to boss of reduction
gearbox housing assembly.
(b) Secure loop clamp (28) to tube assembly (3) and install to bracket (29) with nut
(26) and bolt (27). Torque nut 36. to 40 lb.in.
(c) Install tube assembly (24) or fuel flowmeter (25) if fitted, to rear fuel pressure
tube (3) and tube assembly (30). Torque coupling nuts 90 to 100 lb.in. and
lockwire.
(d) Install tube assembly (30) to bulkhead coupling (6). Torque coupling nut 90 to
100 lb.in. and lockwire.
(e) Connect rear fuel pressure tube (3) to connector on fuel control unit. Tighten
and torque coupling nut 270 to 300 lb.in. and lockwire.
B. Fuel Delivery Tubes and Flexible Hoses (PT6A-27/-28 Engines) (Ref. Fig. 511)
(1) Connect flexible hose (6) to straight nipple (7) and FCU elbow (5); tighten and torque
coupling nuts 170 to 200 lb.in. and lockwire.
(2) Connect flexible hose (9) to straight nipple (8) and elbow (10) on fuel pump; tighten
and torque coupling nuts 450 to 500 lb.in. and lockwire.
NOTE: Flexible hose (9) is not used on some installed PT6A-28 engine models.
Component is airframe supplied. Slave hose must be provided for engine
test.
(3) Connect fuel bypass tube (3) between connector (1) on fuel control unit and tee
(11) on starting control. Torque coupling nuts 90 to 100 lb.in. and lockwire.
3
1
4 5
7 6
ACCESSORY GEARBOX
2 POST−SB1337
1
3
4 5
7 6
POST−SB1422
ACCESSORY GEARBOX
2
9 3
8 11
10 9
12
7 6
C8496B
Installation of Ignition Exciter
Figure 509
1. Bolt (Pre-SB1422)
2. Mounting Bracket
3. Ignition Exciter
4. Washer (Pre-SB1422)
5. Nut (Pre-SB1422)
6. Bolt
7. Washer
8. Nut (Post-SB1422)
9. Washer (Post-SB1422)
10. Vibration Absorber Mount (Post-SB1422)
11. Flanged Sleeve (Post-SB1422)
12. Bolt (Post-SB1422)
CAUTION: WHEN INSTALLING FUEL TUBE (4) ENSURE THAT SHORTER END IS
CONNECTED TO FUEL CONTROL UNIT. INCORRECT INSTALLATION
MAY RESULT IN CHAFING BETWEEN TUBE AND ADJACENT AIRFRAME
EQUIPMENT.
(4) Connect fuel pressure tube (4) between adapter (2) on fuel control unit and elbow
(14) on starting control. Torque coupling nuts 90 to 100 lb.in., and lockwire.
(5) Place one (rear) seal retaining plate (15) over rear coupling nut on fuel pressure
tube (20), insert tube forward through rear fireseal mount ring and place two
center seal retaining plates (15) over tube.
(6) Insert tube (20) forward through center fireseal mount ring, and place one (forward)
seal retaining plate (15) over tube.
(7) Secure coupling nuts of tube (20) to elbow (22) and straight nipple (12). Torque
coupling nuts 90 to 100 lb.in. and lockwire .
(8) Place one (rear) seal retaining plate (15) over rear of fuel pressure tube (21), insert
tube forward through rear fireseal and place two (center) seal retaining plates (15)
over tube.
(9) Insert tube (21) forward through center fireseal, and place one (forward) seal
retaining plate (15) over tube.
(10) Secure coupling nuts of tube (21) to elbow (23) on fuel manifold inlet adapter
assembly and straight nipple (13) on starting control. Torque coupling nuts 90 to
100 lb.in. and lockwire .
(11) Place insulations (16) and seals (17), with slits diametrically opposite, on tubes (20)
and (21) at each side of center and rear fireseal. Position retaining plates (15)
(already on tubes) next to insulation (16), with aluminized side of insulation facing
mount rings (eight locations).
FUEL
CONTROL
UNIT A
1 B
3
VIEW A
30
27
PRE−SB1471 29 24
FLOW DIVIDER AND
DUMP VALVE
28
25 15
26 16 19
POST−SB1471 17 20
18
3
22
23
21 CENTER FIRESEAL
MOUNT RING
14 15 16
20 12
12 13
2
8
OIL−TO−FUEL HEATER
7 11
10
7
8
9
6 VIEW B
5
4
(13) Install loop clamps (18) and (19) on their respective fuel pressure tube (20) and
(21). Locate spacing washers (if required for alignment) between clamps and
secure with two nuts and bolts to support bracket attached to rear drain valve on
gas generator case. Tighten nuts and torque 36 to 40 lb.in.
NOTE: To align fuel pressure tubes, a maximum of two spacing washers can be
used between each loop clamp and the support bracket.
(14) Install one loop clamp (24) on each tube (20) and (21) and, on engines with glow
plug ignition system, install one additional loop clamp (26) on each tube.
(15) Check lines for leaks during engine test (Ref. Testing).
(a) Install preformed packings (14) on both ends of front transfer tube (15), and
preformed packing (17) in groove of elbow (16).
(b) Place elbow (16) on one end of tube (15) and insert other end into external
coupling (13) on flange C.
NOTE: External coupling was installed after assembly of power section to gas
generator assembly.
(c) Position elbow (16) on reduction gearbox and secure with two bolts and
washers; torque bolts 36 to 40 lb.in. and safety wire.
(d) Install preformed packing (12) on forward end of center transfer tube (11), and
insert tube into coupling (13).
(e) Place one (center) seal retaining plate assembly (5) and seal (4) over rear of
rear transfer tube (6), and slide toward center of tube.
NOTE: On later configuration, install insulation between plates (5) and seals
(4) (Ref. IPC).
(f) Place one (center) seal retaining plate assembly (10) and seal (9) over forward
end of transfer tube (6), and slide toward center of tube.
NOTE: On later configuration, install insulation between plates (10) and seals
(9) (Ref. IPC).
(g) Install preformed packings (3) on each end of transfer tube (6) and preformed
packing (7) on adapter.
NOTE: Alignment spacers (8) are used on adapter of rear tube (Pre-SB1169
only).
(h) Insert rear end of transfer tube (6) through rear fireseal mount ring and forward
end of tube through center fireseal mount ring.
(i) Place one (forward) seal (9), insulation (19) and seal retaining plate assembly
(10) over forward end of tube (6).
NOTE: On later configuration, install insulation between plates (10) and seals
(9) (Ref. IPC).
(j) Place one (rear) seal (4), insulation (18) and seal retaining plate assembly (5)
over rear end of tube (6).
NOTE: 1. On later configuration, install insulation between plates (5) and seals
(4) (Ref. IPC).
(k) Install preformed packing (2) on elbow (1), and place elbow on rear end of
transfer tube (6).
(l) Insert forward end of transfer tube (6) into rear end of transfer tube (11),
adapter into boss on gas generator case, and locate elbow (1) on inlet case.
(m) Install elbow (1) with bolts and washers. Torque bolts 36 to 40 lb.in. and safety
wire.
(n) Secure flange of adapter to gas generator case with two bolts. Tighten, torque
bolts 36 to 40 lb.in. and lockwire.
(p) Check for oil leaks during engine test (Ref. Testing).
(1) Install preformed packings (1) and (9) on front and rear flanges (3) and (10) of
No. 2 bearing scavenge tube (11). Install gasket (2) on front flange.
(2) Pass front end of scavenge tube through rear fireseal mount ring, and locate
flanges on respective bosses on gas generator and compressor inlet cases.
(3) Locate rear fireseal mount ring support bracket (8) (already installed on fireseal) on
front hole of scavenge tube rear flange (10). Secure tube rear flange (10) and
bracket to boss with two bolts. Tighten bolts, torque 36 to 40 lb.in. and lockwire.
8
OIL−TO−FUEL HEATER
FCU 7
FUEL
PUMP
5 FUEL PUMP 9
1 10
2
11
3 13
16 12
17 15
14 STARTING CONTROL
FUEL MANIFOLD
CENTER FIRESEAL INLET ADAPTER
REAR FIRESEAL ASSEMBLY
MOUNT RINGS
15 17
16
DETAIL A 20
TYP. 4 PLACES A
TUBE SEALING 18 22
A 19
23
A
21
A
B
R/H IGNITION CABLE
25 19 26
19
21
18 20 24 25
24
26
18
PT6A−27/28 ENGINES L/H IGNITION CABLE
(PRE−SB1196)
VIEW B PT6A−27/28 ENGINES (POST−SB1196)
(4) Secure front flange (3) to gas generator case with two bolts. Tighten bolts, torque 36
to 40 lb.in. and lockwire.
(5) Install seals (6) and seal retaining plate assemblies (5) and (7) (foil side facing
seal) on scavenge tube. Secure assemblies and seals to rear fireseal mount ring
with two retaining plates (4), four bolts (heads located on compressor air inlet side of
mount ring) and self-locking nuts. Tighten nuts and torque (REF. NO. 549, Table
601).
2
INLET CASE 3
8 3
GAS GENERATOR
1 CASE
6
5 12
REAR FIRESEAL 18
MOUNT RING
5 18
9
11
10 17
19
CENTER FIRESEAL
MOUNT RING
19
10
REDUCTION
GEARBOX
14 16
15
FLANGE C
14
13
C6980A
Installation of Pressure Oil Transfer Tubes
Figure 512
1. Elbow (Rear)
2. Preformed Packing
3. Preformed Packing
4. Seals
5. Retaining Plates
6. Rear Tube Post-SB1169
Rear Tube Pre-SB1169
7. Preformed Packing
8. Alignment Spacers (Pre-SB1169 only, ref)
9. Seals
10. Retaining Plates
11. Center Tube Post-SB1169
Center Tube Pre-SB1169
12. Preformed Packing
13. Coupling
14. Preformed Packing
15. Front Tube
16. Elbow (Front)
17. Preformed Packing
18. Insulation Plate
19. Insulation Plate
(1) If the intent of SB1087 is embodied, ensure that seal retaining plates (11 and 13),
inner seals (12) and (14) and rear transfer tubes (10) are of the correct part
numbers, as these parts to Pre-SB1087and Post-SB1087 standard are not
interchangeable. Center and rear fireseal lower mounting rings are also modified to
accommodate this service bulletin.
(a) Install preformed packings (9) on each end of rear transfer tubes (10).
(b) Place inner seals (12) and (14) and inner retaining plates (11) and (13) in the
center of both rear transfer tubes (10).
(c) Insert transfer tubes (10) through center and rear fireseals, and locate outer
seals (12) and (14) and outer retaining plates (11) and (13) over ends of
tubes.
(d) Remove transfer coupling (8), installed during initial assembly, from flange C.
(e) Connect rear ends of transfer tubes (10) to ports of external scavenge pump.
(f) Assemble transfer coupling (8) over ends of tubes (10); mount coupling on flange
C, engaging dowel of coupling in flange hole.
9 10
8
11
6
1 5
4 4
2
7
3 6
REAR FIRESEAL
MOUNT RING
C7463
Installation of No. 2 Bearing Scavenge Oil Tube
Figure 513
1. Preformed Packing
2. Gasket
3. Front Flange
4. Seal Retaining Plate
5. Seal Retaining Plate Assembly
6. Seal
7. Seal Retaining Plate Assembly
8. Rear Fireseal Mount Ring Support Bracket
9. Preformed Packing
10. Rear Flange
11. No. 2 Bearing Scavenge Tube
(g) Loosely secure coupling with three Dee-headed bolts, washers and
self-locking nuts.
(h) Install preformed packings (1) on short transfer tube (2) and insert tube into
boss on reduction gearbox.
(i) Assemble sleeve seal (4) and preformed packing (3) in No. 3 and 4 bearing
scavenge port of front transfer elbow (5).
(j) Install preformed packings (6) on both ends of front transfer tubes (7). Insert
tubes into respective ports on transfer elbow (5).
(k) Place oil transfer elbow (5) and tubes under reduction gearbox. Insert short
transfer tube (2) into port on transfer elbow (5), and rear end of transfer
tubes (7) into respective ports on transfer coupling (8).
(l) Locate oil transfer elbow on mounting boss of reduction gearbox, making sure
that preformed packing (3) and sleeve seal (4) mate with corresponding hole in
boss. Secure elbow (5) with three bolts and plain washers. Tighten bolts,
torque 36 to 40 lb.in. and lockwire.
(m) Torque self-locking nuts, that secure oil transfer coupling (8) to flange C, 36 to
40 lb.in.
(n) Tighten self-locking nuts and torque (REF. NO. 549, Table 601).
(o) Install preformed packing (16) on flanged end of scavenge oil hose (15), and
insert into boss on accessory gearbox. Align bolt holes on flange with
corresponding holes in accessory gearbox and bracket (17) on starting control
(PT6A-27/-28 engines) and secure with two bolts. Torque bolts 36 to 40 lb.in.
and lockwire.
(p) Secure coupling nut of hose (15) to adapter or tee, as applicable, on scavenge
pump housing. Tighten coupling nut, torque 400 to 500 lb.in. and lockwire.
(1) Install glow plug ignition cables Pre-SB1196 (Ref. Fig. 515):
(a) Insert both ignition cables (3) through rear fireseal (13) and center fireseal (14)
apertures.
(b) Position flanges (8) of each cable on rear and center fireseal (13) and (14) and
secure with four bolts and self-locking nuts. Two top bolts also secure mount
ring support bracket (7). Tighten nuts and torque 36 to 40 lb.in.
NOTE: Heads of bolts securing flanges to center and rear fireseal mount
rings must be located on compressor air inlet side of respective mount
ring.
(e) Tighten and torque coupling nut connectors to glow plugs (REF. NO. 566, Table
601) and ignition regulator (REF. NO. 561, Table 601). Lockwire coupling nut at
ignition regulator end.
(f) Assemble one loop clamp (4) on each cable (3) (Ref. Details A and B); secure
to bracket (2) on center fireseal (14) and integral bracket on gas generator
case with bolts and self-locking nuts. Tighten nuts and torque 36 to 40 lb.in.
(g) Assemble four loop clamps (9) on ignition cable (3) (Ref. Detail C).
(h) Secure two of these loop clamps to loop clamps (10) on fuel tube with bolts
and self-locking nuts.
(i) Secure third loop clamp to bracket (12) on air inlet screen with bolt and
self-locking nut.
(j) Secure fourth loop clamp to fuel line and ignition support bracket (11) with bolt
and self-locking nut.
(l) Assemble four loop clamps (6) on ignition cable (3) (Ref. Detail D), and secure
in pairs to brackets (5) on flange E with bolts and self-locking nuts. Tighten
nuts and torque 36 to 40 lb.in.
(a) Insert both ignition cables (6) through rear fireseal (14) and center fireseal (4)
apertures.
(b) Position flanges of each cable (6) (Ref. Detail A) on center fireseal (4) with
brackets (3) located on rear face of upper hole. Secure together at each
cable flange position with two bolts and self-locking nuts. Tighten nuts and torque
36 to 40 lb.in.
(c) Position flanges of each cable (6) on front of rear fireseal (14) (Pre-SB1482,
Ref. Detail D) or rear of rear fireseal (14) (Post-SB1482, Ref. Detail F) with
brackets (11) and (15) positioned over one hole in cable flange. Secure together
at each cable flange location with two bolts and self-locking nuts. Tighten
nuts and torque 36 to 40 lb.in.
(f) Attach bracket (2) (Ref. Detail A) to angle bracket on center fireseal (4) (two
places) with bolts and self-locking nuts. Tighten nuts and torque 36 to 40 lb.in.
A B C
16
17
C
15
REAR FIRESEAL
12 MOUNT RING
10
13
CENTER FIRESEAL
MOUNT RING
9
11
B
14
3
9
4
5
6
8
1
7
A 6
C7464
Installation of External Dual Scavenge Oil Tubes
Figure 514
1. Preformed Packings
2. Transfer Tube
3. Preformed Packing
4. Sleeve Seal
5. Front Scavenge Oil Transfer Tube
6. Preformed Packing
7. Front Transfer Tubes
8. External Scavenge Oil Transfer Coupling
9. Preformed Packings
10. Rear Transfer Tubes
11. Seal Retaining Plates
12. Seals
13. Seal Retaining Plates
14. Seals
15. Scavenge Oil Hose
16. Preformed Packing
17. Support Bracket (Starting Flow Control, PT6A-27/-28
Engines)
(g) Assemble loop clamps (1) and (5) on both ignition cables (Ref. Detail A) and
secure to angle brackets (2) and (3) (already installed) with bolts and
self-locking nuts. Tighten nuts and torque 36 to 40 lb.in.
1 Pre-SB1482; Assemble loop clamp (9) on ignition cable (6). Secure clamp
to bracket (22) on air inlet screen. Tighten nuts and torque 36 to 40 lb.in.
(Ref. Detail D).
2 Post-SB1482; Assemble loop clamp (9) on ignition cable (6). Secure clamp
to bracket (22) with bolt and self locking nut, and bracket (22) to bracket
(21) using bolt, washer and self-locking nut. Tighten nuts and torque 36 to
40 lb.in. (Ref. Detail E).
(i) Assemble loop clamps (10) and (13) on ignition cables (6) (Ref. Detail D or F)
and secure to brackets (11) and (15) (already installed) with bolts and
self-locking nuts. Tighten nuts and torque 36 to 40 lb.in.
(j) Assemble loop clamp (18) (Ref. Detail C) on ignition cable (6) and secure to
angle bracket (19) with bolt and self-locking nut fingertight.
(k) Assemble loop clamps (7) and (8) on ignition cables (6) (Ref. Detail B) and
secure together with bolt and self-locking nut. Tighten nut and torque 36 to
40 lb.in.
(1) Install glow plug ignition cables (Pre-SB1196), as follows: (Ref. Fig. 517)
(a) Install overhauled ignition cables (2) and (3) between center and rear fireseal
mount rings, passing cable ends through respective holes in mount rings.
(b) Install cable flanges (7) on center fireseal mount ring (Ref. Detail B) and secure
with bolts and self-locking nuts. Tighten nuts and torque 36 to 40 lb.in.
NOTE: Heads of bolts securing flanges to center and rear fireseal mount
rings must be located on compressor air inlet side of respective mount
ring.
(c) Install cable flanges (14) on rear fireseal mount ring (Ref. Detail E) and secure
with four bolts and self-locking nuts. Two top bolts also secure mount ring
support bracket (15). Tighten nuts and torque 36 to 40 lb.in.
(f) Tighten coupling nuts (REF. NO. 566, Table 601) at glow plugs, and (REF. NO.
561, Table 601) at ignition regulator. Lockwire coupling nuts at ignition regulator
end .
(g) Secure loop clamps (4) (Ref. Detail A) on cables (2) and (3) to angle brackets
(5) on center fireseal mount ring, and integral brackets (6) on gas generator
case, with bolts and self-locking nuts. Tighten nuts and torque 36 to 40 lb.in.
(h) Secure loop clamps (8) (Ref. Detail C) on cables (2) and (3) to loop clamps (9)
on fuel tubes with bolts and self-locking nuts. Tighten nuts and torque 36 to
40 lb.in.
(i) Secure loop clamps (10) and (12) (Ref. Detail D) on cables (2) and (3) to loop
clamps (13) on fuel tubes, with backplate (11), bolts and self-locking nuts.
Tighten nuts and torque 36 to 40 lb.in.
(j) Secure loop clamps (17) and (18) (Ref. Detail F) to angle brackets (16) on
flange E with bolts and self-locking nuts; torque nuts 36 to 40 lb.in.
(2) Install spark ignition cables (Post-SB1196), as follows: (Ref. Fig. 518)
(a) Install overhauled ignition cables (2, and 3) (Ref. 74-20-00) between center and
rear fireseal mount rings, passing cable ends through respective holes in
mount rings.
(b) Locate cable flanges (10) (Ref. Detail B) on center fireseal mount ring and
position bracket (8) on rear face of flange. Secure with bolts and self-locking
nuts and torque 36 to 40 lb.in.
NOTE: Heads of bolts securing flanges to center and rear fireseal mount
rings must be located on compressor air inlet side of respective mount
ring.
(c) Install cable flanges (18) (Ref. Detail E) on rear fireseal mount ring and position
angle brackets (20) on front face of each flange upper hole position. Secure
with four bolts and self-locking nuts. Top two bolts also secure mount ring support
bracket (21). Tighten nuts and torque 36 to 40 lb.in.
DETAIL D
DETAIL A
2
1
1
4
6 3
14 8
3
5
A
C D
B
14 13 7
8
9
10
2 12
1
11 3
14 9 13
10
4
8
3
9
DETAIL C
DETAIL B
Pre-SB1196 C8489
Installation of PT6A-21 Engine Ignition Cables
Figure 515
(f) Secure two brackets (6) to bracket (7) with one bolt and self-locking nut.
Tighten nut and torque 36 to 40 lb.in.
(g) Secure one angle bracket (5) (Ref. Detail A) to angle bracket (6) and center
fireseal mount ring (two places) with bolts and self-locking nuts. Tighten nuts
and torque 36 to 40 lb.in.
(h) Secure one loop clamp (4) on each cable (2) and (3) to angle brackets (5) with
bolts and self-locking nuts. Tighten nuts and torque 36 to 40 lb.in.
(i) Secure loop clamps (9) (Ref. Detail B) on cables (2) and (3) to angle brackets
(8), on center fireseal mount ring, with bolts and self-locking nuts. Tighten nut
and torque 36 to 40 lb.in.
(j) Secure one loop clamp (11) (Ref. Detail C) on cable (3) to angle bracket (12)
with bolt and self-locking nut. Tighten nut fingertight.
NOTE: Angle bracket (12) (Ref. Detail C) will be secured during subsequent
installation of compressor delivery pneumatic tubes.
1 6
3 7
8
4
DETAIL B
DETAIL A
5
A
B
POST−SB1337
ALTERNATIVE
LOCATION
D
C
A
PRE−SB1482 CONFIGURATION SHOWN
10
9
11 12
13
18
17
14
19 22
15
16
DETAIL C DETAIL D
Post-SB1196 C8490C
Installation of PT6A-21 Engine Ignition Cables
Figure 516 (Sheet 1 of 2)
1. Loop Clamp
2. Bracket
3. Bracket
4. Center Fireseal Mount Ring
5. Loop Clamp
6. Ignition Cables
7. Loop Clamp
8. Loop Clamp
9. Loop Clamp
10. Loop Clamp
11. Bracket
12. Mount Ring Support Bracket
13. Loop Clamp
14. Rear Fireseal mount Ring
15. Bracket
16. Loop Clamp
17. Insulated Tube
18. Loop Clamp
19. Bracket
20. Rear Fuel Pressure
21. Bracket
22. Bracket
E F
POST−SB1482
9 6
15
22 20
21 10
13
11
16
6
14
DETAIL E DETAIL F
C22988A
Installation of PT6A-21 Engine Ignition Cables
Figure 516 (Sheet 2)
(k) Secure loop clamps (13) and (15) (Ref. Detail D) on cables (2) and (3) to loop
clamps (16) on fuel tubes with backplate (14), bolts and self-locking nuts.
Tighten nuts and torque 36 to 40 lb.in.
(l) Secure loop clamps (17) and (19) (Ref. Detail E) on cables (2) and (3) to angle
brackets (20), on rear fireseal mount ring, with bolts and self-locking nuts.
Tighten nuts and torque 36 to 40 lb.in.
(m) Secure loop clamp (22) (Ref. Detail F) on cable (2) to loop clamp (23) on cable
(3) with bolt and self-locking nut. Tighten nut and torque 36 to 40 lb.in.
(1) Remove protective material from overhauled linkage (Ref. 76-10-00); lubricate all
bearings by rotating outward and applying grease (PWC04-001).
(2) The assembly procedure provides for installation of the complete propeller
reversing linkage when a test cell facility acceptable to the reversing propeller
configuration is available.
(3) Where test facilities are of a non-reversing propeller configuration, such as when
testing against a dynamometer or when engine-testing without using the propeller
reversing function, the procedures described in paragraphs 6. to 7. inclusive should
not be implemented until after engine final acceptance test, and prior to shipment
of engine.
(4) These instructions are given primarily for shipping purposes and the resultant
rigging may differ considerably from that required when the engine is installed
in the airframe.
(5) At engine installation by the airframe manufacturer, the linkage is adjusted to suit a
particular airframe requirement. Adjustment may include altering rod lengths,
moving clevis pins to different holes and, if necessary, selecting a different cam to
obtain the necessary power response characteristics.
(6) The final rigging arrangement is part of the aircraft certification requirement,
detailed in the Aircraft Maintenance Manual. Therefore, when an engine is reinstalled
in the aircraft after overhaul or repair, the engine should be rigged in accordance
with the Aircraft Maintenance Manual and not in accordance with the P&WC Engine
Maintenance or Overhaul Manual.
(a) Install swivel joint retaining plate (22) on engine front lifting bracket (23) and
secure with two bolts (24) and self-locking nuts (15). Tighten nuts and torque
36 to 40 lb.in.
(b) Insert adjuster and swivel joint assembly (21) into lifting bracket assembly (23)
and secure with nut (4) (Ref. Detail A). Tighten nut and torque 95 to 105 lb.in.
and lockwire.
DETAIL A DETAIL F
17
CENTER FIRESEAL
MOUNT RING
4
5
DETAIL E 18
16
6 DETAIL B 8
GAS GENERATOR
CASE DETAIL C
7
B F
C D E
B C FLANGE E
1
A
3
10
11
14
12
15
13
REAR FIRESEAL
FUEL TUBES MOUNT RING
14
DETAIL D DETAIL E
Pre-SB1196 C8487
Installation of PT6A-27/-28 Engine Ignition Cables
Figure 517
1. Glow Plug
2. Ignition Cable (LH)
3. Ignition Cable (RH)
4. Loop Clamp
5. Angle Bracket
6. Bracket
7. Cable Flange
8. Loop Clamp
9. Loop Clamp
10. Loop Clamp
11. Backplate
12. Loop Clamp
13. Loop Clamp
14. Cable Flange
15. Mount Ring Support Bracket
16. Angle Bracket
17. Loop Clamp
18. Loop Clamp
(c) Insert flexible shaft casing (7) rearward through center fireseal mount ring,
and locate seal retaining plate (12) and nut (4) on casing behind mount ring.
Move casing rearward into hole in rear fireseal mount ring and install plate (12)
on casing forward of center mount ring.
(e) Align hole in wire rope clamp (19) to receive wire rope (5). Push wire rope
forward from rear end and, at the same time, turn wire rope terminal assembly
(20) until wire rope is fully engaged in clamp and terminal. Secure clamp (19) with
spacer (29) and self-locking nut (15), and torque nut (REF. NO. 581, Fits and
Clearances). Ensure wire rope is in safety by inserting the end of a piece of
lockwire in terminal safety hole. Rope is in safety when lockwire will not pass
through hole.
(f) Locate nut (4) mid-way on casing swivel joint (3). Insert swivel joint through
rear fireseal mount ring and connect wire rope (5) and casing (7). Secure
casing to swivel joint with nut (6) fingertight (Ref. Detail C).
5 10 12
6 REAR FIRESEAL 9
MOUNT RING
7
CENTER FIRESEAL
GAS GENERATOR MOUNT RING
CASE 1 PT6A−28
2 POST−SB1337
G ALTERNATIVE
LOCATION
A B D E F DETAIL G
B C
2
A
3
1
3 IGNITION
EXCITER
14 DETAIL G
13 18
15 17
22
16 21
REAR FIRESEAL
20 MOUNT RING 23
18
FUEL TUBES 19 20
DETAIL D DETAIL E DETAIL F
Post-SB1196 C8488A
Installation of PT6A-27/-28 Engine Ignition Cables
Figure 518
1. Spark Igniter
2. Ignition Cable (Left-hand)
3. Ignition Cable (Right-hand)
4. Loop Clamp
5. Angle Bracket
6. Angle Bracket
7. Bracket
8. Angle Bracket
9. Loop Clamp
10. Cable Flange
11. Loop Clamp
12. Angle Bracket
13. Loop Clamp
14. Backplate
15. Loop Clamp
16. Loop Clamp
17. Loop Clamp
18. Cable Flange
19. Loop Clamp
20. Angle Bracket
21. Mount Ring Support Bracket
22. Loop Clamp
23. Loop Clamp
NOTE: Installation of nuts (4) also secures mount ring to mounting bracket
(28).
(h) Assemble loop clamp (8) on casing (7) and secure to angle bracket (25) on
flange C with bolt (17) and self-locking nut (15). Tighten nut and torque 36 to
40 lb.in. (Ref. Detail B).
NOTE: Installation of bracket (25) was previously carried out during assembly
of power output section to gas generator assembly.
(i) Place two seals (14) on casing (7), one each side of center fireseal mount ring.
(j) Place two insulations (13) on casing (7), one on outside of each seal (14), with
aluminized side of each insulation facing mount ring, and slits in insulations
and seals diametrically opposite.
(k) Secure two plates (12), insulations (13), seals (14) and angle bracket (18) to
center fireseal mount ring with two bolts (17) and self-locking nuts (15), and
torque (REF. NO. 549, Fits and Clearances), (Ref. Detail C).
(l) Assemble loop clamp (8) on casing (7) forward of center fireseal mount ring
and secure clamp to bracket (18) with bolt (17), washer (16) and self-locking
nut (15). Tighten nut and torque 36 to 40 lb.in. (Ref. Detail C).
NOTE: The T5 trim harness (11) will be secured to casing (7) with loop
clamps (8) and (10), bolt (17), spacer (9) and self-locking nut (15)
when harness is installed after engine test.
(a) Remove two self-locking nuts (18) and washer (19) securing propeller thrust
bearing cover assembly at the 1 and 2 o’clock positions (Ref. Detail D).
(b) Place guide pin bracket (17) on studs and secure with nuts (18) (Ref. Detail D),
and torque (REF. NO. 188, Table 601).
(c) Locate sleeve spacer (11) in upper hole in propeller lever (15) and locate lever
end in clevis of push-pull control rod front terminal (10). Insert bolt (12) through
clevis and lever, and secure with castellated nut (1). Torque nut 25 to
35 lb.in. and lock with cotterpin (8) (Ref. Detail B).
(d) Install sleeve bushing (16) in center hole of lever (15); locate lever in fork of
Beta valve plunger (14) and secure with pin (13), washer (2) and cotterpin
(8).
(e) Assemble washer (2), rod assembly connector (3) and second washer (2) on
wire rope clamp (9) and secure with castellated nut (1). Tighten nut, torque 25
to 35 lb.in. and lock with cotterpin (8) (Ref. Detail A).
(f) Position interconnect linkage fully forward against low pitch stop, and air bleed
link (4) fully forward against maximum stop. Align rear connector (3) with
airbleed link (4); check that center of connector hole is approximately 1/32 inch
to rear of center of outer hole in link. If necessary, adjust length of rod
assembly (7).
(g) Check that both connectors (3) are in safety in rod assembly (7) by inserting a
piece of lockwire in rod safety holes. Connectors are in safety if lockwire will
not pass through holes. Secure connectors (3) and nuts (6) to rod (7). Torque
nuts (6) 12 to 18 lb. in. and lockwire (PWC05-089) connectors (3) and nuts
(6) to rod (7).
(h) Secure rear connector (3) to airbleed link (4) with bolt (5), washer (2) and
castellated nut (1). Torque nut 24 to 36 lb. in. and lock with cotterpin (8)
(Ref. Detail A).
NOTE: Final adjustment of the low pitch stop position and rod assembly
length can only be achieved with a propeller installed.
(a) Remove two bolts (3) securing flange cover (12) to accessory gearbox housing.
(b) Remove two self-locking nuts (13) securing accessory gearbox to air inlet
case at flange G. Locate cambox assembly (4) on two accessory gearbox
studs, followed by an electrical connector bracket (Ref. Final Assembly-1).
Secure bracket and cambox with self-locking nuts (13). Tighten nuts and torque
32 to 36 lb.in.
(c) Locate angle bracket (1) on accessory gearbox raised boss and cover (12);
secure with two bolts (3) fingertight. Insert remaining bolt (2) in top hole of
bracket and screw into control lever mounting bracket (4). Torque each bolt 36
to 40 lb.in. and lockwire.
(d) Set FCU by rotating control arm (18) fully counterclockwise, then slowly rotate
arm clockwise until FCU governor cam pick-up point is felt. Set arm
counterclockwise just clear of pick-up point, and retain in this position.
(e) Position of arm (18) should be approximately 16 degrees below horizontal with
arm pointing rearwards.
(f) If necessary, reset arm (18) by slackening FCU arm extension (17) and rotating
arm on serrated spacer. Tighten arm extension (17), torque (REF. NO. 598,
Table 601) and lockwire.
(g) Rotate shaft of cambox (4) until shoulder pin of follower lever is at track point
in propeller control cam (8).
NOTE: Track point of cam slot is at the rear end of arc-shaped slot where an
abrupt change in cam profile occurs.
(h) To ensure that rod assembly (16) is assembled to correct length, rod is
measured from center of one connector to center of the other, and recorded (Ref.
76-10-00). If, during installation of rod assembly (16), connectors fail to align
with holes in FCU lever (29) and FCU arm (18), readjust in accordance with
assembly procedures (Ref. 76-10-00).
(i) Align holes in FCU lever (29) and FCU arm (18) with holes in connectors of rod
assembly (16) and install bolts (7) at each end.
(j) Check each connector for safety by inserting a piece of lockwire in safety holes
in rod. When lockwire will not pass through holes, connectors are in safety.
(k) Lock bolts (7), previously installed, with washer (14) and castellated nut (15).
Tighten nut and torque (REF. NO. 585, Table 601) and lock with cotterpin (5).
(l) On engines with starting control, set FCU arm (18) to 16 degrees below
horizontal (Ref. step (d) preceding). Insert rig pin (Rod 0.120 inch dia.)
through hole in starting control lever (26) and into detent plate rigging slot of
starting control (27) (RUN position is normally 72 degrees).
(n) The following substeps are provided for their informational value:
1 The RUN position (Ref. Fig. 522) on the starting control may be at 45° or
72°, depending on the airframe installation, and is defined by detents or
rigging slots in the plate behind the lever. Movement from 45° to 90° has no
effect on starting control operation and is provided only to actuate the
FCU control arm via the telescopic rod and introduce the hi-idle function.
2 Most installations incorporating this function use the 72° RUN position. With
the rod adjusted as above, movement of the start control lever from 72° to
90° will provide approximately the correct hi-idle speed, final adjustment
being made by the starting control maximum stop.
3 However, for installations using the 45° RUN position, movement of the
start control lever from 45° to 90° will provide a hi-idle speed considerably
higher than required. This must be compensated for by increasing the gap at
the lower end of the rod as required to obtain the desired rpm or,
alternatively, limiting movement of the cockpit starting control lever when
selecting HI-IDLE.
(o) Tighten rod assembly (23) jam nuts (22, Fig. 521), torque 32 to 36 lb.in. and
lockwire (PWC05-089).
(p) Apply a light film of grease (PWC04-001) to ball end fitting of control rod
assembly (23).
(q) Secure upper end of rod assembly (23), to FCU lever (19) with bolt (21),
spacer sleeve (20), washer (14) and castellated nut (15). Tighten nut, torque 12
to 18 lb.in. and lock with cotterpin (5).
(r) Secure lower end of rod assembly (23) to start control lever (26) with bolt (21),
spacer sleeves (24) and (25), washer (14) and castellated nut (15). Tighten nut,
torque 12 to 18 lb.in. and lock with cotterpin (5).
(t) Align slot in head of wire rope clamp (1, Fig. 519) in push-pull terminal (2)
along length of terminal. Locate terminal over wire rope (5) and casing
swivel joint (3); wind terminal onto wire rope until fully engaged with clamp (1).
Secure wire rope (5) to clamp (1) with washer (30) and self-locking nut (15)
and torque (REF. NO. 581, Table 601). Check that wire rope is in safety by
inserting lockwire in safety hole in terminal. Rope is in safety when lockwire
will not pass through hole.
(u) Set follower lever pin to track point in cam (Ref. step (g) preceding). Apply
slight pressure on terminal (2, Fig. 519) toward propeller control cam (8,
Fig. 521).
(v) Adjust rod end clevis on rear terminal (11) until hole in clevis aligns with middle
hole of cam (8); unscrew clevis one complete turn. Tighten jam nut (10) and
torque 38 to 42 lb.in. Check that terminal thread is in safety by inserting lockwire
in clevis safety hole. Terminal is in safety when lockwire will not pass through
hole.
(w) Secure clevis of terminal (11) to cam (8) with pin (9), washer (6) and cotterpin
(5).
(11) After complete assembly of controls, operate and check controls for full and free
movement in the correct sense.
(12) Check reversing system components are in safety and all locking devices are
correctly secured.
(1) Remove all protective material applied on completion of overhaul (Ref. 73-10-08).
(2) Insert bulkhead coupling (9) in center fireseal mount ring (from rear side) and secure
with jam nut (10). Torque nut 38 to 42 lb.in
(3) Install one seal retaining plate (5) on front end of tube (4) and slide toward rear
end. Place tube loosely in slot of rear fireseal and install second plate (5).
15 8 25 17
POST−SB1528
A
FLANGE C
REAR FIRESEAL
D
28 4
B 4
3
2
1
REAR FIRESEAL C
MOUNT RING DETAIL D
SUPPORT BRACKET
11 15 25
FLANGE C
CENTER FIRESEAL
MOUNT RING
10 15
17 15
9
17 8 17
26 27 8
17 12 16 7
8 DETAIL B
15 15
5 PRE−SB1528
18
12
13 19
14
13 29
DETAIL C 7
17 4
6
5
15
20
15 21
5
22
23
7 6 24 DETAIL A
C9445E
Interconnect Linkage Group - Push-pull
Figure 519
10
15
A
B
AIRBLEED
LINK
C 7 14
D
15
THRUST
BEARING 17
COVER
1 18
2
8 3
2 9
10 12
DETAIL D
7
5 11
1
6 8
DETAIL B
6
13 16
8
DETAIL A
DETAIL C
4
3
2 2
1 14
8
17
15
C9450A
Interconnect Linkage Group - Front Components
Figure 520
1. Castellated Nut
2. Washer
3. Rod End Connector
4. Propeller Governor Airbleed Link
5. Bolt
6. Nut
7. Rod Assembly
8. Cotterpin
9. Wire Rope Clamp
10. Push-pull Control Rod Terminal
11. Sleeve Spacer
12. Bolt
13. Pin
14. Beta Valve Plunger
15. Propeller Lever
16. Sleeve Bushing
17. Guide Pin Bracket
18. Self-locking Nut
(4) Place insulations (6) and seals (7) (slit diametrically opposite) on pneumatic tube (4)
each side of rear fireseal mount ring. Position retaining plates (5) next to insulation
(6) with aluminized side of insulation facing mount ring.
(5) Connect tube (4) coupling nuts to coupling (9) and elbow (1); torque both coupling
nuts 90 to 100 lb.in.
(6) Install seal retaining plate (8) between mount ring and forward seal (7); ensure
joggled portion of plate slots into fireseal.
(8) Route electrical cable (3) across accessory gearbox and secure with loop clamp (2)
to top mounting stud of fuel pump, with washer and self-locking nut. Tighten nut
and torque 75 to 85 lb.in.
(9) Connect electrical cable (3) to electrical connector flange G, as described for
heated pneumatic tubes (Ref. Para. K., following).
(10) Connect both ends of tube (11) to coupling (9) and nipple (14) on propeller
governor; tighten tube nuts and torque 90 to 100 lb.in.
29 A 7 9
29 11
8 10
5 8
6
B
REAR FIRESEAL
3 MOUNT RING
15
17 14
2 G
13 4 12 FLANGE
23
1
VIEW A 5
18
16
15 14 18
5 17
7
C 16
PT6A−27/28 ENGINES 19
5
15
14
28 20 22 21
29 VIEW B
8
A
5
15
14
B
23
22
16 27 26
17 25
24
VIEW C 21
PT6A−21 ENGINES
18
C11796
Interconnect Linkage Group - Rear Components
Figure 521
1. Angle Bracket
2. Bolt
3. Bolt
4. Control Lever Mounting Bracket
5. Cotterpin
6. Washer
7. Bolt
8. Propeller Control Cam
9. Pin
10. Jam Nut
11. Push-pull Wire Rope Rear Terminal
12. Flange Cover
13. Self-locking Nut
14. Washer
15. Castellated Nut
16. Rod Assembly
17. Fuel Control Arm Extension
18. Fuel Control Arm
19. FCU Lever Assembly
20. Spacer Sleeve (For PT6A-27-28 Engines)
21. Bolt (For PT6A-27-28 Engines)
22. Jam Nut (For PT6A-27-28 Engines)
23. Rod Assembly (For PT6A-27-28 Engines)
24. Spacer Sleeve (For PT6A-27-28 Engines)
25. Spacer Sleeve (For PT6A-27-28 Engines)
26. Starting Control Lever (For PT6A-27-28 Engines)
27. Starting Control (For PT6A-27-28 Engines)
28. Fuel Control Unit (FCU) (Typical) (For PT6A-27-28 Engines)
29. Fuel Control Lever
(11) Secure loop clamp (13) to angle bracket (12) with bolt and self-locking nut, and torque
nut 36 to 40 lb.in.
(12) Lockwire all tube couplings and bulkhead connector after pressure test of
pneumatic tubes (Ref. Para. L., following).
HI−IDLE
F.C.U. DETAIL
HI−IDLE
TAKE−OFF
(REF.) F.C.U. DETAIL
90 °
72° LOW IDLE
(RUN)
IF GAP IS TILL SET TO 0.030 WHEN
USING 45 ° RUN POSITION, MOVEMENT
TO 90 ° WILL GIVE EXCESSIVELY HIGH
HI−IDLE, GAP MUST BE PRE−SET TO 0°
OBTAIN DESIRED SPEED OR COCKPIT
LEVER MOVEMENT MUST BE RESTRICTED HI−IDLE STARTING
CONTROL
DETAIL
PRE−SET GAP FOR 45° 45 °
RUN POSITION 90 ° RUN POSITION
MOVEMENT MOVEMENT
45°
CUT−OFF AND
DUMP STOP
(0 ° REF.) 0°
C9216
Adjustment of Starting Control Telescopic Linkage
Figure 522
(b) Install straight nipple (12) with preformed packing (13) in compensator (15) or
compensator body (14). Tighten nipple and torque to 65 to 75 lb.in.
(c) Install elbow (21) with preformed packing (18), back-up ring (19) and locknut
(20). Tighten locknut, torque 38 to 42 lb.in. and lockwire.
(d) Install seal (17) and insulation (16), aluminized side facing fireseal on studs of
compensator (15) or compensator body (14). Install seal (24), insulation (23),
aluminized side facing fireseal, and retaining plate (22) on elbow (21).
(e) Install compensator (15) or compensator body (14) on rear face of rear fireseal
and install seal (25) and retaining plate (26) over protruding ends of compensator
(15) or studs of body (14).
(f) Install seal (24), insulation (23), aluminized side facing fireseal, and retaining
plate (22) over protruding elbow (21).
(h) Connect compressor delivery pneumatic heated tube (6) to nipple (12) on
compensator (15) or compensator body (14), and to elbow (4) on fuel
control unit. Tighten locknut (3) and torque 38 to 42 lb.in., at the same time
holding elbow (5) in position. Tighten tube coupling nuts and torque to 90 to
100 lb.in.
(a) Remove all protective material applied on completion of overhaul (Ref. 73-10-07).
(b) Install one seal retaining plate (3) over heated tube (11) and slide rearward
to center of tube. Position tube loosely in slot of rear fireseal mount ring, and
install second seal retaining plate (3).
(c) Place insulations (4) and seals (5) (slits diametrically opposite) on tube (11),
each side of rear fireseal. Position retaining plates (3) next to insulation (4),
aluminized side of insulation facing fireseal.
13
14
TO PROPELLER 12
GOVERNOR
11 FLANGE C
CENTER FIRESEAL 4
MOUNT RING
9
10
11
2
REAR FIRESEAL 6 5
MOUNT RING 7
6 7 8
5
3
C7469A
Installation of Propeller Governor Pneumatic Tubes
Figure 523
(3) Install pneumatic tubes and air filter on PT6A-27/-28 Post-SB1205 engines, as
follows (Ref. Fig. 527):
(b) Secure support bracket (5) to studs on flange G with three self-locking nuts.
Tighten two lower nuts and torque 36 to 40 lb.in.
(c) Install air filter (6) (arrow on filter pointing toward rear of engine) on bracket (5)
and secure with locknut (4). Tighten nut and torque 38 to 42 lb.in.
(d) Assemble heated tube (3) on elbow of fuel control unit and air filter (6). Torque
both coupling nuts 90 to 100 lb.in.
(e) Connect electrical cable (2) to electrical connector at flange G, as described for
installation of heated pneumatic tubes (Ref. Para. K. following).
(f) Install one seal retaining plate (7) over insulated tube (13) and slide rearward
to first bend in tube. Position tube loosely in slot of rear fireseal mount ring,
and install second seal retaining plate (7).
(g) Place insulations (8) and seals (9) (slits diametrically opposite) on tube (13) at
each side of rear fireseal. Position retaining plates (7) next to insulation (8),
aluminized side of insulation facing fireseal.
REAR FIRESEAL
3
2
4
A
B
FLANGE G 5
A
FLANGE G
FOR ENGINE/S.B. APPLICABILITY REFER TO TABLE 101 OR 501
D A
12
6
C B
11
ELECTRICAL SCHEMATIC
11
6 7 8 9 16
12 5
14 10
13
VIEW ON ARROW B
EXPLODED
C10413
Installation of Electrical Connector for Heated Pneumatic Tubes
Figure 524 (Sheet 1 of 2)
1. Screw
2. Bracket
3. Electrical Connector
4. Governor Pneumatic Heated Tube Electrical Cable
5. Compressor Delivery Pneumatic Heated Tube Electrical
Cable (Sheet 1) Compressor Delivery Pneumatic Heated
Tube Electrical Cable and Compressor Delivery Pneumatic
Heated Center Tube Electrical Cable (Sheet 2)
6. Connector Shell
7. Rubber Insulator
8. Nylon Sleeve
9. Bell-end Fitting
10. Clamp Screw
11 Element in Governor Pneumatic Heated Tube
12. Element in Compressor Delivery Pneumatic Heated Tube
13. Cable Sleeve
14. Pins
15. Element in Compressor Delivery Pneumatic Heated Center
Tube
16. Loop Clamp and Rubber Grommet
REAR FIRESEAL 3
2
B
A 5
FLANGE G
DETAIL A
FLANGE G
15
D A 12
6
C B
11
15
ELECTRICAL SCHEMATIC
11
16
6 8 9
7 10
4
D
A
C
B 5
12
14 13
C8495B
Installation of Electrical Connector for Heated Pneumatic Tubes
Figure 524 (Sheet 2)
(4) Install pneumatic tubes and bowl-type filter on PT6A-28 Post-SB1290 engines, as
follows (Ref. Fig. 528):
(a) Install bracket (4) on flange G (Ref. Final Assembly-1, Fig. 502) and secure
with two self-locking nuts (5). Tighten nuts and torque 32 to 36 lb.in.
(b) Install P3 filter assembly (15) on bracket (4) and, with loop clamp (8) located
on electrical cable, secure clamp and filter assembly with bolts (9), washer
and self-locking nuts to bracket (4). Tighten nuts and torque 36 to 40 lb.in.
(c) Attach one end of heated hose (16) to elbow (17) on FCU and the other end to
elbow on P3 filter assembly (15). Tighten both coupling nuts, torque 90 to
100 lb.in.
(d) Assemble plate (10) on rear fireseal (forward side) at slot location; secure with
two bolts and self-locking nuts and torque 32 to 36 lb.in.
(e) Insert nipple end of heated center tube (1) forward through plate (10) and
secure with locknut (11); secure coupling nut at other end of center tube to
elbow on P3 air filter assembly (15).
(f) Tighten center tube coupling nut at one end and torque 90 to 100 lb.in; tighten
locknut (11) at the other end and torque 38 to 42 lb.in.
(g) Connect electrical cables (2) and (3) to electrical connector at flange G (Ref.
Para. K., following).
(a) Install bracket (4) on flange G (Ref. Final Assembly-1, Fig. 502) and secure
with nut on lower stud.
(b) Install spacers (20) and (18) and bracket (6). Fit self-locking nuts (5), tighten
and torque 32 to 36 lb.in.
(c) Install P3 filter assembly (14) on bracket (4) and, with one washer, one angle
bracket (17) (Post-SB1330 only), two bolts (8) and self-locking nuts, secure
angle bracket and filter assembly to bracket (4). Tighten nuts and torque 36 to
40 lb.in.
(d) On Post-SB1583 engines, install P3 filter assembly (14) on bracket (4) and,
with four washers, one angle bracket (17) (Post-SB1330 only), two bolts (23)
and self-locking nuts, secure angle bracket and filter assembly to bracket (4).
Tighten nuts and torque 36 to 40 lb.in.
(e) Assemble plate (9) on fireseal (forward side) at slot location; secure with two
bolts and self-locking nuts and torque 36 to 40 lb.in.
(f) Insert nipple end of heated tube (1) forward through plate (9) and secure with
locknut (10); secure coupling nut at other end of tube to elbow on P3 air filter
assembly (14).
(g) Tighten tube locknut (10) and torque 38 to 42 lb.in.; tighten coupling nut at
other end of tube and torque 90 to 100 lb.in.
(h) Attach one end of heated tube (15) to elbow (16) on FCU and the other end to
elbow on P3 filter assembly (14). Tighten both coupling nuts and torque 90 to
100 lb.in.
(i) Connect electrical cables (2) and (3) to electrical connector at flange G (Ref.
Para. K., following).
(6) Install pneumatic tubes and bowl-type filter (PT6A-27/-28 Engines Post-SB1343) as
follows (Ref. Fig. 530):
(a) Install spacers (5) and bracket (4) on flange G (Ref. Final Assembly-1, Fig.
502) with two self-locking nuts. Torque nuts 36 to 40 lb.in.
(b) Install P3 filter assembly (18) on bracket (4) and, with loop clamp (16) located
on electrical cable, with bolts (17), washers and self-locking nuts. Torque nuts
32 to 36 lb.in.
(c) On Post-SB1583 engines, install P3 filter assembly (18) on bracket (4) and,
with loop clamp (16) located on electrical cable, with Tee bolts (21), four
washers and self-locking nuts. Torque nuts 32 to 36 lb.in.
(d) Attach one end of heated hose (19) to elbow (20) on FCU and the other end to
P3 air filter assembly (18). Torque both coupling nuts 90 to 100 lb.in.
(e) Assemble plate (15) on rear of rear fireseal mount ring at slot location with two
bolts (9) and self-locking nuts. Torque 32 to 36 lb.in.
(f) Insert nipple end of center insulated tube (1) forward through plate (15) with
locknut (14); attach coupling nut at other end of tube to elbow on P3 air filter
assembly (18).
(g) Torque center tube coupling nut at filter 90 to 100 lb.in., torque locknut (14) 38
to 42 lb.in.
(h) Connect electrical cable (2) to electrical connector at flange G (Ref. Para. K.).
(7) Install pneumatic hoses, tube and bowl type filter (PT6A-27/-28 engines,
Post-SB1448) as follows (Ref. Fig. 531):
(a) Assemble, at rear fireseal mount ring slot location, tube retaining plate (10) on
rear and seal retaining plate (9) on front with bolts and self-locking nuts. Torque
nuts 32 to 36 lb.in.
(b) Install washer (11) on elbow (12), insert elbow through retaining plates (10
and 9) on rear fireseal mount ring with locknut (5). Torque nut 38 to 42 lb.in.
(c) Install P3 filter assembly (4) on bracket assembly (1) mounted on flange G,
with bolts (3) and self-locking nuts. Torque nuts 32 to 36 lb.in.
(d) Attach center heated hose (13) with electric cable (14) to elbow (12) on rear
fireseal mount ring and other end to P3 filter assembly (4) inner elbow (19).
Torque coupling nuts 90 to 100 lb.in.
(e) Attach rear heated hose (16) with electric cable (15) to P3 filter assembly (4)
outer elbow (18) and other end to elbow (17) on FCU. Torque coupling nuts 90
to 100 lb.in.
(f) Install electrical connector (2) to bracket assembly (1) (Ref. Para. K.).
(g) Attach insulated tube (6) coupling nut to elbow (12) on rear fireseal mount ring.
Align gasket (7) between flange end of tube and gas generator case boss,
insert bolts (8) through flange and gasket into boss and tighten.
K. Installation of Electrical Connector from Heated Pneumatic Tube (Ref. Fig. 524)
(1) After installation of pneumatic heated tubes, route leads to electrical connector and
solder as follows:
(a) Insert leads through loop clamp and rubber grommet (16), cable sleeve (13),
bell-end fitting (9), nylon sleeve (8) and relevant holes in rubber insulator (7).
NOTE: Electrical leads from element (11) in Py heated tube connect to pins A
and C, and leads from element (12) in P3 heated tube connect to pins
B and D. Leads from element (15) (Ref. Fig. 524, Sheet 2) connect
to pins B and D also.
(b) Using a suitable soldering iron, solder leads to connector pin (14) solder
buckets, using solder (PWC05-205) and resin flux (PWC05-031).
(c) Slide rubber insulator (7) and nylon sleeve (8) over solder connections, position
bell-end fitting (9) over sleeve and secure to connector (6), fingertight.
17
16
9 10 15
1 13
7 12
2 11
3
4 5 PRE−SB1123 REAR FIRESEAL
26
25
30
22
23
24
C8484A
Installation of Compressor Delivery Air Line - PT6A-27/-28 Pre-SB1123/Post-SB1123 Alternative
Mod.) Engines
Figure 525
1. Preformed Packing
2. Back-up Ring
3. Locknut
4. ElbowPre-SB 1123 or Elbow Post-SB1123
5. Metered Elbow ( Post-SB1123, Alternative Mod.)
6. Compressor Delivery Pneumatic Heated Tube
7. Spacer
8. Electrical Receptacle Bracket
9. Electrical Receptacle
10. Loop Clamp
11. Loop Clamp and Rubber Grommet
12. Straight Nipple
13. Preformed Packing
14. Compensator Body (Post-SB1123, Part B)
15. Temperature Compensator (Pre-SB1123 Alternative Mod.)
16. Insulation
17. Seal
18. Preformed Packing
19. Back-up Ring
20. Locknut
21. Elbow
22. Retaining Plate
23. Insulation
24. Seal
25. Insulation
26. Retaining Plate and Insulation
27. Compressor Delivery Pneumatic Insulated Tube
28. Gasket Pre-SB1276 or Corrugated Steel Gasket
Post-SB1276
29. Angle BracketPost-SB1196
30. Bolt 0.190-32 UNJF x 0.625 inch Alternative; Bolt 0.190-32
UNJF x 0.750 inch
(e) Install connector assembly (3) in bracket (2), with four screws (1), washers and
self-locking nuts; torque nuts 7 to 8 lb.in. Install loop clamp (16) to bracket (2)
Post-SB1330 or angle bracket Post-SB1330 with bolt and self-locking nut.
Torque nut 36 to 42 lb.in.
6 5 4 3
8
5 GAS GENERATOR
4 CASE
3 7
2
1 12
REAR FIRESEAL
MOUNT RING
9
10
11
FLANGE G
FUEL CONTROL
UNIT ELBOW ASSY
C7466
Installation of Compressor Delivery Air Line - PT6A-27/-28 (Post-SB1123, Stnd. Mod.) Engines
and all PT6A-21 Engines
Figure 526
1. Loop Clamp
2. Compressor Delivery Pneumatic Heated Tube Electrical
Cable
3. Seal Retaining Plate
4. Insulation
5. Seal
6. Seal Retaining Plate Post-SB1162
7. Angle Bracket (engines with spark ignition system)
8. Gasket Pre-SB1276 or Corrugated Steel Gasket
Post-SB1276
9. Loop Clamp
10. Angle Bracket (engines with spark ignition only)
11. Compressor Delivery Pneumatic Heated Tube
12. Loop Clamp and Rubber Grommet
NOTE: Because leads of rear and center heated tubes are soldered to the
same connector pins, both tube heater elements are checked
together, (their resistance values must be combined for the purpose of
the above checks). Refer to Table 502 for individual tube assembly
resistance values.
ELECTRICAL RECEPTACLE
BRACKET
8 7
9
10
GOVERNOR AIR PRESSURE HEATED
TUBE ELECTRICAL CABLE 8 9
1
7
2
14
FUEL CONTROL
UNIT ELBOW ASSEMBLY
6
REAR FIRESEAL
5 MOUNT RING
FLANGE G
4
3
12 GAS GENERATOR
CASE
11
13
C8508
Installation of Compressor Delivery Air Line - PT6A-27/-28 (Post-SB1205) Engines
Figure 527
1. Loop Clamp
2. Compressor Delivery Pneumatic Heated Tube Electrical
Cable
3. Compressor Delivery Pneumatic Heated Tube
4. Locknut
5. Support Bracket
6. Air Filter
7. Seal Retaining Plate
8. Insulation
9. Seal
10. Seal Retaining Post-SB1162
11. Angle Bracket (engines with spark ignition only)
12. Gasket Pre-SB1276 or Corrugated Steel Gasket
Post-SB1276
13. Compressor Delivery Insulated Tube
14. Loop Clamp and Rubber Grommet
ELECTRICAL RECEPTACLE
6 BRACKET
8
9
10
11
5
2 3
1
15
17
12
16 13
14
IGNITION CABLE
C8485
Installation of Compressor Delivery Air Line - PT6A-28 Post-SB1290 Engines
Figure 528
18 7
6 8
A
5 14
19
20
7 8
17
POST−SB1378
4
14
TO FUEL 10
CONTROL 16 9
12
15
1 3
2
11 13
22
22
21
22
4
14
DETAIL A 23
POST−SB1583
C79904
Installation of Compressor Delivery Air Line Post-SB1330/Post-SB1378
Figure 529
(d) When pressure test is satisfactory, wipe off all traces of leak detecting fluid.
(f) Install applicable gasket (28) under flange of insulated tube (27), and locate
tube between elbow connector on compensator (15) or compensator body
(14).
6 9
2
8
5
4
1 A
PRE−SB1583
14
15
17
16
19 18 11
12
4
13
21 10
IGNITION CABLE
22
16
FLANGE G
18 22 23
DETAIL A
POST−SB1583
C10264A
Installation of Compressor Delivery Air Line - PT6A-27/-28 Post-SB1343 Engines
Figure 530
(g) Secure tube flange and gasket to gas generator case with two bolts. Place angle
bracket (29) (engines with spark ignition only) under head of lower bolt. Tighten
bolts and torque (REF. NO. 592, Table 601).
(h) Connect coupling nut at rear end of tube to elbow connector on compensator
(15) or compensator body (14); tighten and torque coupling nut 90 to 100 lb.in.
(a) Connect a supply of clean dry compressed air at 80 ± 5 psig to elbow on fuel
control unit.
FLANGE G
1
19
7
18
3
6
17 9 5
4
16
8
15
REAR FIRESEAL
14 MOUNT RING
11
12 10
13
C42271
Installation of Compressor Delivery Air Lines -PT6A-27/28 Post-SB1448 Engines
Figure 531
1. Bracket Assembly
2. Electrical Connector
3. Bolt
4. P3 Air Filter Assembly
5. Locknut
6. Insulated Tube
7. Gasket
8. Bolt
9. Plate, Seal Retaining
10. Plate, Tube Retaining
11. Washer
12. Elbow
13. Center Heated Hose Assembly
14. Electrical Cable, Center hose
15. Electrical Cable, Rear Hose
16. Rear Heated Hose Assembly
17. Elbow, FCU
18. Outer Elbow
19. Inner Elbow
(d) When pressure test is satisfactory, wipe off all traces of leak detecting fluid.
(f) Install gasket (8) Pre-SB1276, or corrugated steel gasket (8) Post-SB1276
under flange of heated tube (11), and locate tube between elbow on fuel
control unit and boss on gas generator case.
(g) Secure tube flange and gasket to gas generator case with two bolts. On
engines with spark ignition system, place angle bracket (7) under head of lower
bolt. Tighten bolts and torque (REF. NO. 592, Table 601).
(h) Connect coupling nut at rear end of tube to elbow on fuel control unit, tighten
and torque coupling nut 90 to 100 lb.in.
(j) Assemble loop clamp (9) on heated tube (11) and secure to bracket (10) with
bolt and self-locking nut. Tighten nut and torque 36 to 40 lb.in.
(k) Position loop clamp (12) and loop clamp and rubber grommet (1) on electrical
cable (2) and secure to studs on flange G with self-locking nuts. Tighten and
torque nuts 32 to 36 lb.in.
(3) Pressure test pneumatic lines and air filter on PT6A-27/-28 Post-SB1205 engines,
as follows (Ref. Fig. 527):
(d) When pressure test is satisfactory, wipe off all traces of leak detection fluid.
(g) Secure tube flange and gasket to gas generator case with two bolts. Place
angle bracket (11) (engines with spark ignition system) under head of lower
bolt. Tighten bolts and torque (REF. NO. 592, Table 601).
(h) Connect coupling nut at rear end of tube to connector on air filter, tighten and
torque coupling nut 90 to 100 lb.in., and lockwire.
(j) Remove lower nut securing electrical connector bracket and upper nut securing
air filter support bracket (5) to flange G. Position loop clamp (1) and loop clamp
and rubber grommet (14) on cable (2) and secure to studs at flange G with
self-locking nuts. Tighten and torque nuts 32 to 36 lb.in.
NOTE: The upper loop clamp also secures the governor air pressure tube
electrical cable to the lower mounting studs of the electrical receptacle
bracket.
(4) Pressure test pneumatic lines and bowl-type filter on Post-SB1330 engine or
PT6A-28 (Post-SB1290) engines as follows (Ref. Figs.528 and 529):
(d) When pressure test is satisfactory, wipe off all traces of leak detection fluid.
(f) Install Pre-SB1276 gasket (13) or Post-SB1276 corrugated steel gasket (13)
under flange of insulated tube (12) and locate tube between nipple on tube (1)
and boss on gas generator case.
(g) Secure tube flange with gasket to gas generator case with two bolts, placing
angle bracket (14) (engines with spark ignition system) under head of lower
bolt. Tighten bolts and torque (REF. NO. 592, Table 601).
(h) Connect coupling nut of tube (12) to tube (1) and torque 90 to 100 lb.in.
(5) Pressure test pneumatic lines and bowl-type filter on PT6A-27/-28 Post-SB1343
engines as follows (Ref. Fig. 530):
(d) When pressure test is satisfactory, wipe off all traces of leak detection fluid.
(f) Install Pre-SB1276 gasket (11) or Post-SB1276 corrugated steel gasket (11)
under flange of insulated tube (10) and locate tube between nipple on tube
(1) and boss on gas generator case.
(g) Secure tube flange with gasket to gas generator case with two bolts (12),
placing angle bracket (13) (engines with spark ignition system) under head
of lower bolt. Tighten bolts and torque 32 to 36 lb.in.
(h) Connect coupling nut of tube (10) to tube (1) and torque 90 to 100 lb.in.
NOTE: Loop clamp (3) also secures the governor air pressure tube electrical
cable to the lower mounting stud of the electrical receptacle bracket.
(d) When pressure test is satisfactory, wipe off all traces of leak detection fluid.
(f) If insulated tube (6) was removed, attach coupling nut to elbow (12). Align
gasket (7) between flanged end of tube and gas generator boss, insert bolt
(8) through flange and gasket into boss, torque 32 to 36 lb.in. and safety wire.
Torque coupling nut 90 to 100 lb.in. and safety wire.
(g) If insulated tube (6) is in place, attach coupling nut to elbow (12) and torque 90
to 100 lb.in. Torque bolts (8) attaching flange end 32 to 36 lb.in. Safety wire
coupling nut and bolts.
1 Remove lower nut (5) attaching electrical receptacle bracket (6) and P3
filter mounting bracket (4) to flange G.
2 Remove rear self-locking nut and bolt attaching P3 filter, loop clamp and
rubber grommet (8) to mounting bracket (4).
3 Assemble loop clamp (7), loop clamp and rubber grommet (8) on cables (2
and 3). Install loop clamp (7) on stud at flange G with nut. Torque nut 32 to
36 lb.in.
NOTE: Loop clamp (7) also attaches governor air pressure tube electrical
cable to lower mounting stud of electrical receptacle bracket.
(b) Safety wire all coupling nuts in pneumatic system, leaving flange bolts
(Pre-SB1276 only) unlocked. Retorque and lock these bolts after engine test with
safety wire.
(1) Install class of trim thermocouple, determined from data established during engine
testing, as follows:
(a) Install probe of harness (3) through center fireseal mount ring, with bolts (4)
(from air inlet side) and self-locking nuts (7). Torque nuts 36 to 40 lb.in.
(b) Install one loop clamp (2), separated by spacer on probe and second clamp (1)
on reversing cable housing with bolt and self-locking nut, torqued 36 to 40 lb.in.
A. Procedure
(a) Remove caps from pressure and scavenge oil transfer tubes (12) and install
new preformed packings on transfer tubes.
(c) Remove protective covers installed after light overhaul. Make sure that gas
generator case and power section exhaust duct flanges C, are clean, free
from nicks, scratches, dents and defects likely to damage seals. Smear thin layer
of compound (PWC09-005A) on exhaust duct flange before assembly.
(d) Check and centralize two interstage sealing rings (Pre-SB1218) or one sealing
ring (Post-SB1218) on power turbine stator housing to ensure smooth entry
onto mating surface of compressor turbine shroud housing. Interstage sealing
rings (Pre-SB1218) are positioned with gaps 180 ± 20 degrees apart with
one gap at TDC. Interstage sealing ring (Post-SB1218) is positioned so that
side marked ‘‘PRESS’’ is facing rear of engine.
(e) Using hoist, carefully move power section into position until mating flanges are
six inches apart.
(f) Install gasket on T5 thermocouple wiring terminal block (10) of harness. Insert
block through gas generator case, with gasket correctly positioned, and secure
block with two bolts. Torque bolts 36 to 40 lb.in. and lockwire .
(g) Align locating grooves in edges on flange C of exhaust duct and gas generator
case at 12 o’clock position.
(i) Implement loop and ground resistance checks of T5 system (Ref. 72-01-00,
SUB-ASSEMBLY).
(j) Install Dee-head bolts (heads face rear) through mounting flanges, and locate
governor pneumatic tube clamp bracket and interconnect linkage casing clamp
bracket on flange C (Ref. Final Assembly-1, Figs. 501 and 502, View on
Flange C). Secure all bolts with self-locking nuts, tighten in diametric sequence
and torque 36 to 40 lb.in.
(k) Temporarily remove bolts (8) and (9) (Ref. Fig. 532) secured to posts on T5
terminal block. Connect lugs of T5 trim harness to appropriate post on
terminal block. Reinstall bolts (8) and (9); torque bolt (8) (REF. NO. 961, Table
601) and bolt (9) (REF. NO. 962).
(l) Connect coupling nut of tube (9, Fig. 533) to coupling (11) at center fireseal,
torque 90 to 100 lb.in. and lockwire .
(a) Install locknut (5) on wire rope casing (8) at rear of front lifting bracket (7).
(b) Insert wire rope (22) through front lifting bracket into forward end of wire rope
casing (8), and feed rearward until wire rope emerges at rear swivel joint (23).
Locate front swivel joint assembly (4) in front lifting bracket (7).
(c) Screw locknut (5) onto threaded casing of front swivel joint (4); torque locknut
95 to 105 lb.in. and lockwire.
(d) Connect wire rope casing coupling nut (24) to rear of front swivel joint (4).
Tighten nut, torque (REF. NO. 582, Table 601) and lockwire.
(e) Install spacer sleeve in propeller reversing lever (17), and connect front clevis
(1) to lever with bolt, washer and castellated nut (25). Tighten nut and torque
12 to 18 lb.in.;secure nut with cotterpin
(f) Attach lower end of governor interconnecting rod (2) to air bleed link (27) on
propeller governor (6) with bolt, washer and castellated nut (26). Tighten nut,
torque nut 12 to 18 lb.in. and secure with cotterpin.
(g) Install rear wire rope terminal (21) and rod-end clevis (20) on end of wire rope
(22) by screwing assembly clockwise until wire rope bottoms. Ensure wire rope
is in safety by inserting a piece of lockwire through inspection hole in
terminal. When wire rope is in safety, lockwire will not pass through hole.
Tighten nut on clamping bolt and torque (REF. NO. 581, Table 601).
(h) Attach rear rod-end clevis (20) to propeller control cam (19) with straight
headed pin (18). Install washer on pin and lock with cotterpin.
(3) For PT6A-27/-28 (Post-SB1185) and all PT6A-21 Engines: Reconnect propeller
reversing linkage:
CENTER FIRESEAL 7
MOUNT RING
2 3 4
TERMINAL BLOCK
8
9
10
PROPELLER REVERSING
CABLE HOUSING
GAS GENERATOR
CASE
C7480C
Installation of T5 Trim Wiring Harness
Figure 532
1. Loop Clamp
2. Loop Clamp
3. T5 Trim Harness
4. Bolt
5. Angle Bracket
6. Loop Clamp
7. Self-locking Nut
8. Bolt (Alumel Terminal)
9. Bolt (Chromel Terminal)
10. Flat Spacer
(a) Install front swivel joint (4) in slot of front lifting bracket (7). Pivot retaining
plate (29) over swivel joint and secure with bolt (30) and nut (28). Tighten
both nuts (28) and torque 36 to 40 lb.in. Tighten locknut (5), torque 95 to
105 lb.in. and lockwire.
(b) Install spacer sleeve in reversing lever (17) and secure rod-end clevis (1) to
lever with bolt and castellated nut (25). Tighten nut, torque 12 to 18 lb.in. and
lock with cotterpin.
(c) Attach lower end of interconnecting rod (2) to air bleed link (27) with bolt,
washer and castellated nut (26), torque 12 to 18 lb.in. and lock with cotterpin.
(5) Install new preformed packing on oil drain plug (14) or magnetic chip detector, as
applicable, and install in boss on reduction gearbox (15). Tighten and torque oil
drain plug (REF. NO. 184, Table 601) or magnetic chip detector (REF. NO. 200) and
lockwire .
7 28
8 22
21
POST−SB1185 20
7 6 19
8 5 4
1 30 29
23
SPACER SLEEVE 18
REAR FIRESEAL
25
INPUT LEVER
22 24
17 CONTROL LEVER
MOUNTING BRACKET
27 26
FCU CONTROL ROD
2
CENTER FIRESEAL VIEW B
MOUNT RING
VIEW A 11
B
3 7 8
1 6
2 10 9
17
16 15 13
14
FLANGE C 12
C7484
Installation of Power Section on Gas Generator
Figure 533
1. General
A. Personnel engaged in final assembly of the engine should refer to the INTRODUCTION
section of this manual to familiarize themselves with general overhaul procedures (Ref.
Outline of Manual Overhaul Procedures).
B. Final assembly is divided into three sections: FINAL ASSEMBLY-1 through FINAL
ASSEMBLY-3.
ENGINE FINAL ASSEMBLY-1: ENGINE ASSEMBLY
ENGINE FINAL ASSEMBLY-2 : ACCESSORY AND EXTERNAL COMPONENTS
ENGINE FINAL ASSEMBLY-3 : FINAL CHECKS
C. The type of lockwire used during assembly shall comply, unless otherwise specified, with
Specification AMS5687 which is 0.025 inch diameter heat and corrosion resistant steel
wire (PWC05-089) and will not be specified in assembly instructions.
D. Do not allow loop clamps to move cables from their natural contour when tightening
attachment bolts, as chafing of cable will result.
E. Where aluminum foil seal retaining plates are installed on external tubes at fireseals, the
plates must be installed so that the aluminum foil faces the fireseal mount ring.
2. Consumable Materials
The consumable materials listed below are used in the following procedures.
For alternate products, suppliers, and suppliers addresses, refer to Consumable Materials
List P/N 3043340.
Not Applicable
Not Applicable
A. General
(1) Immediately after satisfactory engine test, the following checks must be implemented
to ensure integrity of all external components of engine assembly.
(3) Where necessary, reference will be made to paragraphs within this chapter, or to
other chapters for specific information on torque values, etc.
B. Checks
(1) Examine exhaust duct, gas generator case, center and rear fireseal mount rings,
inlet area and screen as follows:
(a) Examine exhaust duct, mount rings and gas generator case for damage or
dents. Check for security at attachment flanges.
(b) Remove air inlet screen (Ref. 72-30-00, DISASSEMBLY), and conduct a
thorough examination for foreign object damage (F.O.D.) within inlet case area.
Replace inlet screen (Ref. 72-30-00, SUB-ASSEMBLY), and cover with a
strip of waxed paper or other suitable material to exclude foreign matter from
compressor.
(a) Inspect scavenge oil pump for leakage. Check for security to accessory
gearbox
(b) Examine oil-to-fuel heater for leakage. Check attachment nuts for security.
(c) Ensure main oil filter element is the original item installed during assembly.
NOTE: A slave oil filter element used during engine testing must be
removed after testing is completed and the original oil filter element
installed.
(d) Inspect No. 2 bearing scavenge oil tube for damage and security; ensure
retaining bolts are wirelocked.
(e) Inspect oil pressure tubes from accessory gearbox to propeller reduction
gearbox for damage. Check torque values on tube flange, coupling and
elbow-retaining bolts, and wirelock (Ref. Para. 6, FINAL ASSEMBLY-2).
(f) Inspect dual oil scavenge tubes for damage. Check torque values of elbow and
seal-retaining plates, retaining bolts, and wirelock (Ref. Para. 6, FINAL
ASSEMBLY-2).
(h) Check magnetic chip detector or oil drain plug in propeller reduction gearbox
for correct torque value (Ref. FINAL ASSEMBLY-2).
(b) Check bleed valve retaining bolts for correct torque values, and wirelock (Ref.
72-30-00, SUB-ASSEMBLY).
(c) Inspect compressor delivery air tubes for damage, paying particular attention to
tube insulation. Check torque values on tube nuts, nipple, adapter retaining nut,
P3 filter (if fitted), and wirelock (Ref. Para. 6, FINAL ASSEMBLY-2).
(d) Inspect governor pneumatic tubes from fuel control unit to propeller governor
for damage. Check torque values, and wirelock (Ref. Para. 6, FINAL
ASSEMBLY-2).
(e) Connect propeller reversing linkage, and wirelock (Ref. Para. 6, FINAL
ASSEMBLY-2).
(a) Examine fuel pump for security to accessory gearbox and tightness of hose
and line connections. Check wirelocking.
(b) Examine fuel control unit for security to fuel pump, and tightness of hose and
line connections. Check wirelocking.
(c) Examine starting control (PT6A-27/28 engines) for security to flange G; check
tightness of line connections and wirelocking.
(d) Inspect flow divider and dump valve (PT6A-21 engines); check torque values of
retaining bolts and wirelocking.
(f) Check fuel drain valves for correct torque value, and wirelock (Ref. 72-30-00,
SUB-ASSEMBLY).
(a) Check T5 wiring harness terminal bolts for correct torque values and lockwire
(Ref. Para. 6, FINAL ASSEMBLY-2).
(b) Inspect ignition cables for security to spark igniters/glow plug and ignition
exciter/ignition regulator.
(c) Recheck torque values of each spark igniter/glow plug and lockwire to ignition
cables.
(6) Install Trim Data Plate after Test (Ref. Fig. 501)
(a) On completion of engine test, and prior to engine shipment, ensure that trim
data from engine test log sheet is properly stamped on trim data plate; install
as follows:
1 Place engine data plate (1) on mounting boss (2) on inlet case and secure
with bolts (4) in the two top attachment holes.
2 Locate trim data plate (5) over two lower holes in data plate (1) and secure
with two lockwashers (3) and bolts (4). Tighten all bolts and torque 36 to
40 lb.in.
1
INLET CASE
VIEW A
5
3
4
C7485A
Installation of Trim Data Plate after Test
Figure 501
1. General
A comprehensive table of fits and clearances is provided in each applicable chapter with
illustrated views of the engine showing the location of the various fits and limits, indicated by
reference number (REF. NO.). All REF. NOs. from these tables are listed in numerical
sequence with respective chapter number in Table 601 following, to provide a reference index
for all chapters. A plus (+) symbol preceding the REF. NO. indicates one that is used in
this chapter (72-00-00). These NOs. are repeated in Table 602 with appropriate torque limits
and assembly procedures.
In order to maintain consistency throughout the manual, all tables of fits and clearances are
located in Pageblock 601 in each applicable chapter.
The term Inspection Frequency Requirement (IFR) is a system by which each fit, or
clearance receives an inspection frequency rating (Ref. P&WA Standard Practices Manual,
P/N 58005).
The letters A, B, C and D appearing in the IFR column indicate the recommended
frequency of inspection.
(a) A - Measure each component, fit or clearance at each overhaul or whenever
affected parts are disassembled regardless of physical condition. Make a
record of the results.
(b) B - Make sure that the fit, clearance, torque or other special assembly
requirement is correct at assembly, during every engine build.
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.
FIT TO means a fitting operation may be required at assembly to obtain the required fit.
Unless otherwise stated, all fits are diametrical. Spline fits are calculated from chordal
dimensions.
The figures in the MINIMUM, MAXIMUM and REPLACE columns shall be interpreted:
(a) Dimensions in inches.
(b) Torque in pound-inches.
(c) Spring pressures in pounds and ounces.
(d) Vane areas in square inches.
(e) Vane class figures correspond to a determined geometric area.
NOTE: When the REPLACE Column is left blank, the MIN. or MAX. limits
apply, as required.
C. Torque Limits
Unless otherwise stated, apply thread lubricant to all parts that are to be torque-loaded.
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.
(1) Refer to Tables 601 and 602 for chapter and REF. NOs. used in this manual.
585
598
584
669
VIEW A VIEW C
ASSEMBLY PROCEDURE
585
SECTION B−B
FLANGE B FLANGE C FLANGE A
B 582 582 C
A
B
581
566
549 592 549 TYPE FOR ALL RUBBER
TYPE FOR ALL RUBBER
MTD TUBE SEALS MTD TUBE SEALS
577 561
577
PT6A−27/28 ENGINES 577
PT6A−21 ENGINES ASSEMBLY INSTRUCTIONS
ASSEMBLY INSTRUCTIONS 566
C8476C
Engine Assembly - Fits and Clearances
Figure 601 (Sheet 1 of 2)
186
184
200
199
VIEW A
A
184
961
962
C8477A
Engine Assembly - Fits and Clearances
Figure 601 (Sheet 2)
ENGINE - TESTING
1. General
A. The purpose of these instructions is to make sure that engines will produce rated power
within required limits after repair, or normal scheduled overhaul.
B. The classified first-stage power turbine stator returned with a gas generator module
undergoing scheduled overhaul is (already) installed on the slave power section and
the engine tested in accordance with instructions in this chapter.
D. All wet line pressure systems should be calibrated at the appropriate engine height.
F. The type of lockwire (safety wire) used during testing shall comply, unless otherwise
specified, with Specification AMS5687 which is 0.025 inch diameter heat and corrosion
resistant steel wire (PWC05-089) and will not be specified in testing instructions.
2. Consumable Materials
The consumable materials listed below are used in the following procedures.
For alternate products, suppliers and suppliers addresses refer to Consumable Materials List
P/N 3043340.
The special tools listed below are used in the following procedures.
The special tools listed below are used in the following procedures.
Name Remarks
Analyzer Tec Aces Model 1700, P/N 10-100-0464
RAM Procedure Card Tec Aces PT6, P/N 11-100-0048
Charge Converter Box Integrator Model 510-02, P/N 10-100-1502
Cable 80 ft., P/N 10-320-0131
Cable Tachometer Generator, 80 ft., P/N
10-320-0132
Tachometer Matching box Model 516, P/N 10-100-1516
Name Remarks
Cable Microdot, 3 ft., P/N 75-200-0032
Cable Interface, P/N 10-320-0133
5. Engine Test Equipment
A. General
(1) The equipment required for testing PT6A-21,-27 and -28 engines is listed in Paras.
3. and 4. and are referred to in text.
(2) Engine testing shall be conducted on a suitably correlated test stand. Requirements
for accomplishing overhaul test stand correlation may be obtained by contacting
Pratt & Whitney Canada, Customer Support Department. A condensed description of
test cell correlation procedures and requirements is also contained in the P&WC
Facility Equipment and Planning Manual, P/N 3040878.
7. Symbols
Symbols designated for various stations within the engine and working variables used in
engine testing, are as follows. Capitalized symbols in parenthesis are used interchangeably
with those immediately adjoining, (e.g. Ng = NG) to provide similarity to appearance on
computerized calculations.
A. Engine/Propeller Controls
(1) Because reverse power is not used during engine test, controls associated with
reverse power feature, i.e., FCU interconnect rod and propeller reversing lever,
are not installed until test is completed (Ref. Final Assembly).
(2) Push Beta valve fully in, and place reset lever in the fully forward position.
(3) Secure valve and lever in these positions with a suitable tension spring (5, Fig.
702) attached to each of the components.
(2) Install breather adapter fitting (PWC30199) on accessory gearbox and secure with
two bolts; torque 32 to 36 lb.in.
(3) Install overspeed governor (PWC32101-101) with gasket on studs at left-hand side
of reduction gearbox and secure with four nuts and washers; torque 150 to
170 lb.in.
(4) Install exhaust nozzles (PWC30434) on engine and secure each with six bolts and
nuts; torque 65 to 75 lb.in.
(d) Secure with nuts and washers to housing, and torque 75 to 85 lb.in.
(6) Install main oil pressure fitting (PWC32107) on right-hand side of accessory
gearbox housing. Torque fitting 375 to 425 lb.in.
(8) Install torquemeter static fitting (PWC32112) on left-hand side of reduction gearbox.
Secure fitting with two bolts; torque bolts 32 to 36 lb.in.
(9) Install reduction gearbox oil pressure fitting (PWC30314) PT6A-27/-28 engines
Pre-SB1223 or (PWC32105) PT6A-27/-28 engines Post-SB1223 and all PT6A-21
engines.
NOTE: Reduction gearbox oil pressure fitting need be installed only if reduction
gearbox pressure reading is required during engine test.
(10) Install propeller oil pressure measurement adapter (PWC50391) on left-hand side of
reduction gearbox. Make sure hole of adapter is aligned to permit oil flow . Torque
nuts 150 to 170 lb.in.
(11) Install accessory spur drive plug (PWC51336) inside gearshaft located in AGP pad
at the 10 o’clock position.
(13) Install oil drain collector (PWC50384) on starter generator drain. Torque fitting 38 to
42 lb.in.
(14) Install oil drain collectors (PWC50385), one on fuel pump drain and one on
propeller shaft drain. Torque fittings 38 to 42 lb.in.
(15) Install fuel dump collector (PWC50385) on fuel divider. Torque fittings 38 to 42 lb.in.
(16) Remove one fuel nozzle retaining bolt from gas generator case; install Ps3
adapter (PWC30136) through flange of fuel nozzle into bolt hole. Torque adapter 25
to 30 lb.in.
(17) Install oil inlet temperature thermocouple probe (PWC30814) in boss on right hand
side of engine accessory gearbox. Torque 65 to 75 lb.in.
(20) On some PT6A-28 engines, with an airframe-supplied flexible fuel hose, install a
slave hose between oil-to-fuel heater and fuel pump. Torque hose coupling nuts
450 to 500 lb.in. (Ref. Final Assembly-2).
(21) Remove two bolts, washers and nuts from flange A of propeller reduction gearbox
at the 6 o’clock position. Install vibration bracket pickup assembly (PWC32082-100)
at the rear of flange A and secure with two bolts, washers and nuts. Torque 36 to
40 lb.in.
(22) Remove nuts from flange G at 3 o’clock position. Install AGB vibration bracket
(PWC80503) at the rear of flange G. Secure with nuts and torque 32 to 36 lb.in.
(24) For a permanent record of vibration survey, attach printer and printer cable to
ACES Analyzer.
(1) Attach hoist and lifting eye (PWC32117) to mount ring on assembly stand. Take up
slack on hoist chain.
(2) Remove bolts and washers securing mount ring to adapters on stand (Ref. Storage
Instructions).
(3) Make sure that mount pads (PWC32080) are installed on mount ring (PWC32081)
and secured to gas generator case. Torque 365 to 390 lb.in. and 225 to 250 lb.in.
respectively.
(4) Hoist engine, complete with mount ring, and secure to test stand with three bolts
and nuts. Torque nuts 800 to 900 lb.in. and lock with cotterpins.
D. Installation of Propeller
(2) Torque retaining bolts 660 to 730 lb.in and lockwire with single strand of lockwire.
3 4
2 5
1
9
8 10 6
7
C11321A
Test Cell Configuration - Left-hand Front View
Figure 701
1. Propeller Governor
2. Propeller Control
3. Torque Static Pressure Fitting
4. Mount Ring Bracket
5. Mount Ring
6. Overspeed Governor
7. Reset Solenoid and Lead
8. Magnetic Chip Detector Lead
9. Torquemeter Static Line
10. Vibration Bracket Assembly
(1) Remove 22 bolts, washers and nuts from flange A of propeller reduction gearbox.
Install engine mount ring (2) (PWC32083) in front of flange A and secure with 22
slave bolts MS9518-20 and nuts (P/N3012675). Tighten nuts diametrically opposite
in sequence and torque 36 to 40 lb.in.
(2) Remove nut (7), washer (6) and bolt (11) from bracket assembly (4) (PWC30591).
Secure bracket (5) to accessory gearbox mount pad with three washers (8) and
bolts (9). Tighten bolts, torque 140 lb.in., and lockwire.
(3) Attach hoist and lifting eye (PWC32117) to mount ring on assembly stand. Take up
slack on hoist chain.
(4) Remove bolts and washers securing mount ring to adapters on stand (Ref. Storage
Instructions).
(5) Lubricate preformed packing (19) (MS9388-328) and install on plug (18)
(PWC32236), and insert plug into propeller shaft.
(7) Secure engine rear support bracket (5) to struts (10) with bolt (11), washer (6) and
nut (7); torque nut 500 lb.in.
(8) Secure engine mount ring (2) to left side mount (3) (PWC32305-100) and to right
side mount (1) (PWC32304-100) with bolts (12), spacers (13 and 14) and nuts (15).
Torque nuts 4000 lb.in.
(9) Connect coupling shaft to propeller shaft flange and secure with eight bolts (21)
and nuts (20); torque nuts 1500 lb.in.
(1) Attach hoist and lifting bracket (PWC50373) to mount ring (PWC70330) on assembly
stand. Take up slack on hoist chain.
1 2 3
8
4
5
9 7
C8114A
Test Cell Configuration - Right-hand Front View
Figure 702
(2) Remove bolts and washers securing engine mount ring to adapters on assembly
stand (Ref. Storage Instructions).
(3) Make sure that mount pads are installed to mount ring (PWC70330) and secure to
gas generator case. Torque 350 to 400 lb. in. and 225 to 300 lb. in. respectively.
(5) Hoist engine, complete with mount ring and secure to mount ring adapter
(PWC70327). Torque bolts to 750 lb. in. and lockwire.
(6) Mate engine propeller shaft to adapter flange (PWC70329-01). Torque bolts to 600
to 650 lb. in. and lockwire.
(1) Connect test stand power control to FCU power control lever.
(2) On PT6A-27/-28 engines connect test stand condition (start control) lever to starting
control adapter plate (PWC32444) installed on engine starting control lever.
(3) Connect test stand propeller speed control to speed control lever of engine
propeller governor.
(4) Check for full and free movement of controls. Adjust test stand linkage as
necessary.
(1) For location of test cell connections, refer to Figures 701 through 705 and Para. B.,
preceding.
(2) Install oil scavenge-to-cooler elbow (PWC32113) between engine scavenge pump
outlet and oil cooler inlet line.
(3) Connect test cell oil cooler return oil line at 12 o’clock position on compressor inlet
case. Torque 900 to 1000 lb.in.
3
2
1
11 5
10
9
7
8 6
C8113
Test Cell Configuration - Left-hand Rear View
Figure 703
(4) Connect engine breather tube to breather adapter on accessory gearbox using
worm-drive hose clamp.
(5) Connect fuel inlet line (incorporating fuel inlet thermocouple) (PWC30814) to
oil-to-fuel heater. Torque 450 to 500 lb.in.
(6) Connect engine ignition leads to ignition exciter (or current regulator). Tighten
fingertight plus 45 degrees.
1 2 3
PT6A-21 C8112
Test Cell Configuration - Right-hand Rear View
Figure 704
(h) Reduction gearbox oil pressure sensing line, if required (Ref. Para. B. (9)).
(11) Remove engine oil filter element and replace with slave-filter element of identical
part number (Ref. Disassembly).
(12) Make sure filter, Tt7 measurement thermocouple (PWC32449), and test cell static
pressure probe (PWC34297) are correctly installed.
(1) Unlock filler cap on accessory gearbox housing and withdraw dipstick from filler
tube.
2 3 4
1
8
7
6 10 5
PT6A-27/-28 C8111B
Test Cell Configuration - Right-hand Rear View
Figure 705
CAUTION: FUEL SYSTEMS PRESERVED WITH OIL FOR STORAGE PURPOSES MUST
BE PURGED PRIOR TO MOTORING CYCLE.
(1) On PT6A-21 engines disconnect fuel line at flow divider and dump valve inlet for
drainage into suitable container.
(2) On PT6A-27/-28 engines disconnect fuel lines at outlet side of starting flow control
valve. Cap the bypass, dump and No.1 manifold outlets, allowing drainage from
No.2 manifold outlet into a suitable container.
(3) Open test cell fuel valve and switch fuel pump ON.
(5) Place propeller control lever at FEATHER. Power control lever at IDLE. On
PT6A-27/-28 engines place start control lever at RUN.
(7) Position power control lever to FUEL CUT-OFF, switch fuel supply pump OFF and
close test cell fuel valve.
(8) Reconnect fuel line to flow divider and dump valve and secure line attachment
points.
(9) On PT6A-27/-28 engines remove caps from the bypass, dump and No.1 manifold
outlets and reconnect all fuel lines to starting control unit.
4 5 6 12
3
13
2 TO TEST CELL
SPEED SYST.
1
11 10 9
C39205
AGB Vibration Survey - ACES Analyzer
Figure 706
A. Prestart Checks
(1) Make sure that the engine test installation is clear of all loose nuts, bolts, tools or
other foreign objects.
(c) Fuel supply pump switch ON. Confirm fuel inlet pressure is not less than 5
psig.
2
A
1 B
C
B
4
2 FLANGE A 3
2
16
17
12
13
DETAIL A
15 14
DETAIL B
(TYPICAL)
19 11 5
18
COUPLING SHAFT
(REF.)
6
9
PROPELLER 7
SHAFT FLANGE 20 10
DETAIL D
21
DETAIL C
C8890
Engine Installation in Dynamometer Test Stand - (PWC32478) Mounting Arrangement
Figure 707
(3) Advance power control lever fully (PT6A-21 engines) or start control lever to RUN
(PT6A-27/-28 engines), for maximum of 10 seconds.
(4) Record fuel flow rate which must be 70 to 100 pph before start attempt is made. If
not within this range, reject the fuel control unit.
(5) Retard power control lever (PT6A-21 engines), or start control lever (PT6A-27/-28
engines) to CUT-OFF.
(7) During engine rundown, check operation of dump valve and gas generator case
drain valves. Listen for unusual noises such as scraping or rubbing sounds. If any
such noise is heard, determine location and possible cause; rectify (Ref. Light
Overhaul).
(9) Close fuel valve and place fuel pump switch OFF.
NOTE: This procedure is used to remove internally trapped fuel and fuel vapor, or if
there is evidence of fire within the engine. Air passing through the engine
serves to purge fuel/fuel vapor from the combustion section, power turbine and
exhaust system.
(5) Start control lever (PT6A-27/-28 engines) or power control lever (PT6A-21 engines)
at CUT-OFF.
(6) Place starter switch ON and motor engine for maximum of 10 seconds to expel fuel
and fuel vapors. Switch starter OFF; when engine stops rotating, close fuel valve
and place fuel supply pump switch to OFF.
(7) Check engine oil level (Ref. Para. 8.) and replenish tank to MAX. COLD level.
(f) Fuel supply switch ON. Confirm that fuel inlet pressure is not less than 5 psig.
NOTE: On glow plug ignition systems allow Ng to stabilize at a speed above 4500
rpm for five seconds.
(3) Observe that engine lights, then return ignition and starter switches to OFF after
engine has accelerated smoothly to idle speed, 19750 ± 500 rpm.
(g) Fuel supply switch ON. Fuel inlet pressure is 5 psig minimum.
NOTE: On glow plug ignition systems allow Ng to stabilize at a speed above 4500
rpm for five seconds.
(3) Observe that engine lights, then return ignition and starter switches to OFF after
engine has accelerated smoothly to idle speed.
F. Unsatisfactory Start
NOTE: If one or more of the following conditions occur during engine starting, shut
down engine immediately; anticipatory action is to be taken, whenever
possible, to prevent engine temperature limitations being exceeded.
(1) Engine fails to light up within 10 seconds of advancing power control lever to
minimum idling speed.
(2) False or hung start: After light-up, engine fails to reach idling speed.
(3) Hot start: Tt5 exceeds starting temperature limits. This condition may be preceded
by false or hung start.
G. Shutdown
(3) Move start control lever (PT6A-27/-28 engines) or power control lever (PT6A-21
engines) to CUT-OFF. Note rundown time and record.
(4) Shut off test cell fuel supply and switch fuel supply OFF.
(1) All operating limits quoted in Table 702 are observed during all phases of test
procedure.
(2) Test cell instrument readings taken during test run are recorded in engine test log
(Ref. Fig. 708).
(1) Fuel pressure at the engine inlet shall be 5 to 20 psig at all times including
transient conditions.
(2) Oil temperature limit for all running with exception of transients shall be 140° to
160°F.
(3) Scavenge oil back pressure at the engine outlet shall be 20 psig min. to 50 psig
max.
(6) Maximum torque at idle is 10 in.Hg. Engine torquemeter system shall be purged
prior to oil level check at acceptance calibration.
(7) Maximum acceptance limit for vibration shall not exceed 100 ‘‘G’’.
Ng Speed ± 50 rpm
100% Ng = 37468 rpm
Speed
Nf Speed ± 100 rpm
100% Nf = 33000 rpm (PT6A-21 Engines)
Speed
100% Nf = 33235 rpm (PT6A-27/28 Engines)
Speed
δP torque ± 1.5 in. Hg
Tt5 ± 5°F
temperature
C. Run-in Procedure
(1) Do a wet motoring run followed with a dry motoring run (Ref. Para. 9. preceding).
(2) With propeller lever in feather position, start engine and run at ground-idle 19750 ±
500 rpm Ng (propeller testing) or rotate dynamometer controller to obtain 5000 rpm
Nf or maximum available (dynamometer testing) for 5 minutes.
(3) Record Ng, Nf, Tt1, Tt5, del P, oil pressures and oil temperatures.
(4) Unfeather propeller and run at ground-idle with propeller in fine pitch (propeller
testing) or rotate dynamometer controller to obtain 15000 rpm Nf or maximum
available (dynamometer testing) for 5 minutes.
(5) Record Ng, Nf, Tt1, Tt5, del P, oil pressure and oil temperatures.
(6) Carry out two feathering cycles to check propeller governor and propeller systems.
D. Preliminary Checks
(b) If required Nf cannot be obtained, shut down engine and reset propeller
maximum speed adjustment (Ref. Para. 11.B. following).
(a) With propeller control lever in the maximum position, set power control lever to
obtain 30000 ± 1000 rpm Ng and lock stop on console. Move propeller control
lever to feather position until lever is hard against stop (propeller testing).
(b) Record Ng before and after feather condition. A change of more than 100 rpm
Ng requires CSU to be changed.
(c) With propeller control lever in the maximum position, set power control lever to
obtain 24000 ± 500 rpm Ng and rotate dynamometer controller to obtain 5000
± 500 rpm Nf and lock stop on console. Retard propeller control lever from
maximum to feather stop position (dynamometer testing).
(e) A change of more than 100 rpm Ng requires CSU to be changed. Propeller oil
pressure should be less than 20 psig.
(3) With oil temperature controlled at 140° to 160°F, make sure oil pressure is 85 to 95
psig at 27000 Ng and above, and not less than 40 psig at ground-idle. If necessary,
adjust as follows:
(c) Remove oil filter cover, using puller (PWC30556) extract filter element. Remove
filter housing from inlet case (Ref. Disassembly) with puller (PWC30328).
(d) With compressor tool (PWC30415), remove retaining ring and relief valve from
inlet case.
(g) Install relief valve through aperture in air inlet case into oil pressure pump
housing and using compressor tool (PWC30415) secure relief valve with
retaining ring (Ref. Final Assembly).
(h) Install check valve assembly, oil filter element and cover (Ref. Final Assembly).
NOTE: 1. The vibration survey requirement applies only to engines being tested
following overhaul or repair requiring balancing of the compressor rotor
assembly.
NOTE: 2. Do the vibration survey using the following procedures and the ACES
Operator’s Manual. Personnel must be familiar with the Analyzer prior to
performing these operations.
(1) Install the ACES PT6 RAM procedure card (11-100-0048) in the analyzer. Select
the analyzer power on, and load the procedure.
(2) Select ‘‘PT6A 1ENg Survey Engine Model’’ from the operation options menu.
NOTE: Vibration survey is common for all PT6A engines, engine model selection
is for survey records (hardcopy).
(5) Start engine (Ref. Para. 9.). Let engine stabilize and oil temperature to reach a
minimum of 51°C (125°F).
(6) Select ‘‘Start Engine Survey’’ from the menu on the analyzer.
(8) Select the Vibration Sensor as a BK4505/TEC, and set the input range to 1.0.
(d) Ng Sweep:
(10) When survey is completed, review and record peak amplitude by using the cursor
keys to locate the peak.
(a) To magnify or reduce vertical scale use vertical arrow keys tagged ‘‘Point.’’
(b) To magnify horizontal scale between point ‘‘A’’ and ‘‘B’’, select point ‘‘A’’ with
cursor and press ‘‘MARK.’’ Select Point ‘‘B’’ with cursor and press ‘‘EXP.’’
(c) To return to original screen, select Point ‘‘A’’ and press ‘‘MARK,’’ and then
select Point ‘‘B’’ and press ‘‘CLR.’’
(d) For a hard copy, press and hold the ‘‘0’’ key on the ACES Analyzer. The printer
will copy the displayed screen.
(b) Select ‘‘Shutdown Survey’’ from the menu on the ACES Analyzer.
(c) Press ‘‘Enter’’ on the ACES Analyzer to start recording. Shut down engine from
idle.
(d) End vibration survey after engine reaches 0 rpm and a sync error appears on
the ACES Analyzer; then press ‘‘Enter’’ on the ACES Analyzer to stop
recording.
(a) From the plots produced above, ensure that 1ENg vibration level does not
exceed the following limits:
GROUND-IDLE to max Ng ; 0.5 cm/sec
Shutdown from GROUND-IDLE to 5000 rpm Ng; 0.5 cm/sec
(1) If engine response is sluggish, or acceleration rate is too slow, check P3 and fuel
system pneumatic control tubes and connectors for leakage or obstruction, before
any fuel control adjustments are made (Ref. Troubleshooting).
(2) Position power control lever maximum stop on console to limit torque to 86.3 in.Hg.
(PT6A-21 engines) or 108.6 in.Hg. (PT6A-27/-28 engines) or maximum obtainable,
without exceeding engine operating limits (Ref. Table 702). Lock stop on console.
(3) Set propeller control lever or rotate dynamometer controller to give 32000 rpm Nf.
(5) Decrease power control lever to flight-idle 23600 ± 100 rpm Ng.
(6) Slam accelerate from flight-idle to T.O. timed to 97.5% of take-off Ng. Slam
decelerate to ground-idle (19750 ± 500).
NOTE: The time taken to move power control lever in checks (5) through (6) must
not exceed 1.0 second, engine should respond smoothly during acceleration
and deceleration.
(7) Acceleration time must fall within range specified (Ref. Fig. 709).
(a) Rotate FCU acceleration dome three detents clockwise to increase fuel flow.
(b) Run engine for not less than one minute at maximum stop (Ref. step (2)
preceding) to achieve stabilization; slam decelerate to 32000 Ng, then without
dwelling at lower speed, slam accelerate to maximum stop. Repeat to
26000 Ng; again slam to maximum stop. Reduce Ng to GI.
NOTE: For sequential bodie checks, dwell time at each power setting should
be minimum required for engine to stabilize.
(c) If engine is stall and surge free on completion of bodie checks, reset acceleration
dome to original position (three detents counterclockwise).
(d) If engine stall or surge is experienced during checks, rotate acceleration dome
one detent counterclockwise and repeat bodie check.
(f) If bleed valve is functioning correctly, the dome may be reset a further two
detents, a bodie check being implemented after each detent adjustment.
(g) When surge is eliminated, reset dome three detents counter clockwise from
surge-free setting.
(10) Following acceptable acceleration and bodie checks, if scribe marks do not align,
remove seal and lockwire on FCU acceleration dome. Holding adjusting screw with
an Allen wrench, loosen adjuster locknut. Turn dome to re-align scribe marks,
then tighten locknut, lockwire and seal. lockwire dome tab.
(11) Reset propeller control lever stop on console to permit 33000 Nf selection.
(1) Start engine, and advance power control and propeller control levers (propeller
testing) or rotate dynamometer controller until engine is operating at observed
power of 550 ± 10 SHP/DELRTH (PT6A-21 engines) or 680 ± 10 SHP/DELRTH
(PT6A-27/-28 engines) or maximum power obtainable without exceeding engine
operating limits (Ref. Table 702) and at an Nf/RTH equal to 33000 rpm but not
to exceed 34200 rpm (observed).
(2) Run engine for 5 minutes at this power setting to obtain stabilization. Annotate log
sheet; Tt5 Trim Determination and record set of readings.
Nf
Ng
Pam or Baro
Psn or P1000
Ps3
δP
SG
Tf
Tsg
Tt1
Tt5
Tt7
Wf
(3) Determine trim value from readings in step (2), preceding. Process Data with
Program 30P10230 or PWC83020.
(a) With results obtained in step (3) preceding, calculate trim to suppress TT5/TH
to a value T5D/TH - 60° ± 10 F° (PT6A-21/-27/-28 engines) or T5D/TH - 65° ±
5 F° (PT6A-28 Piper engines only).
(c) Trim value obtained in step (a) preceding is for a 59°F day. To trim engine, this
value should be denormalized as follows:
(4) Select appropriate class of trim harness (P/N 3013604 or P/N 3031417) (Ref. Table
703).
(5) Install selected trim harness (Ref. Final Assembly), and record class in log sheet.
(6) Start engine and run at take-off power (Ref. step (1), preceding).
(7) After allowing for stabilization of readings, make sure that selected trim reduces Tt5
by the required value. If you are using program PWC83020, check the T5 trim
check box and the output screen will state if the trim is good or not. Should it be
necessary, install another class of trim and recheck.
(8) Annotate log sheet; Tt5 TRIM CHECK POINT TRIMMED in remarks column.
H. Acceptance Checks
(2) Record readings in Subpara G. step (2) preceding, for each of the power setting
points.
(5) From readings obtained in steps (3) or (4) preceding, process data with program
30P10230 or PWC83020. Plot the best straight line across the normalized values
of Wf, Tt5 and Ng against shp on engine performance graph (Ref. Fig. 710).
I. Acceptance Values
(1) Enter curve at 550 shp (PT6A-21 engines) or 680 shp (PT6A-27/-28 engines) and
record corresponding values for SFC, Tt5 and Ng for take-off power in corrected
engine performance block. SFC = Wf/DELRTH ÷ SHP/DELRTH.
(2) Check parameters determined in step (1) against required parameters (Ref. Table
704).
(3) Enter curve at 549 shp (PT6A-27/-28 engines) and record corresponding Ng value
as data plate speed rpm. Express this rpm as a percentage of 37500 rpm (100%
Ng) and record in space provided. Stamp engine trim plate accordingly and install on
lower end of engine data plate (Ref. Final Assembly).
(2) With the starting flow control in the RUN position and no interference from the idle
linkage, adjust to correct idling speed (19750 Ng ± 500) by unlocking minimum
governing screw on FCU (Ref. Fig. 715 or 716).
NOTE: Build Specification BS392 and BS954 are applicable to DHC6 installation and
BS673 is applicable to Metro IIIA installation.
(a) With propeller control lever in maximum position, advance power control lever
slowly until Nf ceases to increase.
(b) Record Nf, torque, MOT and MOP. Nf should be between 32700 and 33300
rpm (PT6A-21) at 550 SHP ±50 SHP with MOT of 140 to 210 °F or 32935
and 33535 rpm (PT6A-27/-28) or 31353 to 31953 rpm (PT6A-27 BS392, BS 954
and BS673) at 680 SHP ±50 SHP with MOT of 140 to 210 °F.
NOTE: For BS392, BS954 and BS673 operation Max. NG adjustment (Ref.
Para. 11. D.) should be carried out prior to maximum speed
adjustment (Ref. Para. 11.B.).
(d) Repeat procedures in step (a)thru (c) until correct Nf is obtained. Nf oscillation
should not exceed 100 rpm.
(a) With the propeller control lever in maximum position, set dynamometer
controller for an Nf speed of 32000 ±500 rpm (PT6A-21/-27/-28) or 30500 ± 500
rpm (PT6A-27 BS 392, BS954 and BS673 only).
(b) Advance power control lever slowly until 550 ± 50 shp (PT6A-21) or 680 ± 50
shp (PT6A-27/-28).
(d) Using the dynamometer controller increase Nf slowly until POP drops to 250 ±
50 psig.
(e) Record Nf, torque MOT, MOP and POP. Nf should be between 32700
and 33300 rpm (PT6A-21) or 32935 and 33535 rpm (PT6A-27/-28) or 31353 to
31953 rpm (PT6A-27 BS392, BS954 and BS673).
C4947C
Log of Engine Test - Sample Form
Figure 708
5.0
FOR ENGINES TESTED AT AN ALTITUDE OF 3000 FEET,
4.8 ADD THE FOLLOWING TIME TO THE COMPUTED LIMITS.
INLET TIME TO
4.6 TEMPERATURE ADD
(DEG. F) (SECONDS)
4.4 −20 .25
0 .26
4.2 20 .27
40 .28
59 .31
4.0 80 .35
100 .41
3.8 120 .48
ACCELERATION TIME (SECONDS)
3.6
3.4
3.2
3.0
2.8
2.6
2.4
2.2
2.0
1.8
1.6
1.4
−20 −10 0 10 20 30 40 50 60 70 80 90 100 110 120
C64961A
Acceleration Time vs Ambient Temperature
Figure 709
37000
36000
35000
34000 2200
33000 2100
32000 2000
CORRECTED Tt5 ( R)
1900 °
500 1800
CORRECTED FUEL FLOW LB/HR
1700
450
1600
400
1500
350
1400
300
250
C7821A
Engine Performance Curve - Sample Form
Figure 710
(1) Disconnect slave tension spring, positioned between propeller governor reset arm
and beta valve, from reset arm (Ref. Fig. 702) and attach to front lifting bracket to
maintain beta valve in fully rearward position. Move reset arm to minimum
(rear) position and secure with lockwire.
(2) Run engine, and with propeller control lever in the maximum position (propeller or
dynamometer testing) (make sure dynamometer load is not excessive) gradually
advance control lever to contact maximum Ng stop (Ref. Fig. 715 or 716, as
applicable).
(3) Record Nf which should be 31020 to 31680 rpm (PT6A-21 engines) or 31241 to
31905 rpm (PT6A-27 and PT6A-28 engines) or 29869 to 30269 rpm (PT6A-27
engines, DHC BS392, BS954 and Metro BS673 application only).
(5) After satisfactory completion of check, unlock reset arm, move to forward position
and reconnect slave tension spring.
D. Maximum Ng Adjustment
NOTE: In cold weather (below 15°F) maximum torque limit may be exceeded up
to a limit of 127 in.Hg for this adjustment.
(2) Start engine; with propeller control lever at maximum rpm position, advance power
control lever to contact part power trim stop.
(4) With engine running at trim stop power confirm that Ng oscillation does not exceed
50 rpm. Record Ng and Tt1.
(5) Reposition part power trim stop to its stowed position and lockwire.
(2) Set power control lever at ground idle and record Ng.
(3) Check gas generator speed (Ng) is correct (± 300 rpm) for ambient temperature
and pressure altitude as indicated (Ref. Fig. 717).
(4) If adjustment is necessary on engines with flow divider and dump valve (Ref. Fig.
716):
(b) Hold nut (8) with wrench and carefully loosen nut (9) counterclockwise.
(d) When specified Ng rpm has been obtained (Ref. Fig. 717), tighten nut (9)
while holding screw (10), torque 20 to 25 lb.in. and lockwire.
(e) Shut down engine, reconnect Nf governor line to FCU and lockwire.
(5) If adjustment is necessary on engines with start control unit (Ref. Fig. 715):
(c) When specified Ng rpm has been obtained (Ref. Fig. 717), shut down engine.
1640
1635
1630
1625
1620
MAXIMUM TT5/TH R AT 550 SHP/DELRTH (TRIMMED)
1615
1610
1605
1600
°
1595
1590
1585
1580
1575
1570
0 10 20 30 40 50 60 70 80 90 100
PERCENTAGE OF TBO LOGGED AGAINST ENGINE
PT6A-21 C4969C
Tt5 Limits - Repair Category
Figure 711 (Sheet 1 of 3)
1760
1755
1750
MAXIMUM TT5/TH R AT 680 SHP/DELRTH (TRIMMED)
1745
1740
1735
1730
1725
1720
1715
1710
1705
1700
0 10 20 30 40 50 60 70 80 90 100
PT6A-27 C728D
Tt5 Limits - Repair Category
Figure 711 (Sheet 2)
1740
1735
1730
1725
MAXIMUM TT5/TH R AT 680 SHP/DELRTH (TRIMMED)
1720
1715
1710
° 1705
1700
1695
1690
1685
1680
0 10 20 30 40 50 60 70 80 90 100
PERCENTAGE OF TBO LOGGED AGAINST ENGINE
36250
36150
NG / RTH MAX. (RPM)
36050
35950
35850
0% 10% 20% 30% 40% 50% 60% 70% 80% 90% 100%
% TBO
PT6A-21 C84984
NG/RTH Limits
Figure 712 (Sheet 1 of 3)
37400
37300
NG / RTH MAX. (RPM)
37200
37100
37000
0% 10% 20% 30% 40% 50% 60% 70% 80% 90% 100%
% TBO
PT6A-27 C84985
NG/RTH Limits
Figure 712 (Sheet 2)
37100
37000
NG/RTH (RPM)
36900
36800
36700
0 10 20 30 40 50 60 70 80 90 100
PERCENTAGE OF TBO LOGGED AGAINST ENGINE
(1) Run engine to obtain oil temperature range of 140° to 160°F. Shut down engine
and, after one minute, check oil level and record.
(2) The difference between oil levels recorded in Para.8.I. and step (1) preceding,
should not exceed 0.2 lb/hr maximum.
(3) Inspect engine for external oil and fuel static leakage. Remove slave oil filter from
compressor inlet case, wipe out oil residue inside oil filter housing, and let engine
stand for two hours.
(a) Check oil level is at maximum mark, or not more than two inches below
maximum.
(b) Remove drain plug from 6 o’clock position on rear face of accessory gearbox
and allow oil to drain.
(c) Check oil level after minimum of two hours has elapsed. Level must be same
as recorded in step (a), drain rate from accessory gearbox drain should not
exceed one drop per minute.
(5) Remove magnetic chip detector, if applicable, from propeller reduction gearbox.
Examine chip detector and slave oil filter for contamination or metal particles.
0.686
0.684
0.682
SFC (lb.shp.hr.) MAX.
0.68
0.678
0.676
0.674
0.672
0.67
0% 10% 20% 30% 40% 50% 60% 70% 80% 90% 100%
% TBO
PT6A-21 C84986
SFC Limits
Figure 713 (Sheet 1 of 2)
0.648
0.647
0.646
0.645
0.644
0.643
0.642
0.641
SFC (lb/shp/hr)
0.640
0.639
0.638
0.637
0.636
0.635
0.634
0.633
0.632
0.631
0 10 20 30 40 50 60 70 80 90 100
PERCENTAGE OF TBO LOGGED AGAINST ENGINE
PT6A-27/-28 C74811A
SFC Limits
Figure 713 (Sheet 2)
3
2
1
4
10
6
9
8
C7387A
Propeller Governor Adjustments
Figure 714
NOTE: When a specific seal leakage is not specified, the seal leakage shall not exceed 3 cc
per hour per individual seal. All seal leakages shall be included in total oil consumption.
(2) Install new identified oil filter element in place of test slave element (Ref. Final
Assembly).
A 3
6
5
2
1
VIEW A
STOWED POSITION
OPERATING POSITION
PT6A-27/-28 C7932C
Fuel Control Unit Adjustments
Figure 715
(11) With oil temperature controlled at 140°F to 160°F, check that oil pressure is 85 to
95 psig at 27,000 Ng and above, and not less than 40 psig at ground idle. If
necessary, adjust oil pressure:
(c) Remove oil filter cover, element housing and check valve assembly from inlet
case (Ref. Disassembly).
(d) Using compressor tool ( PWC30415), remove retaining ring and relief valve
from inlet case.
NOTE: Each additional spacer will increase oil pressure approximately three
to five psig.
2 3
10
1
4
VIEW A
6 7
5
PT6A-21 C8110B
Fuel Control Unit Adjustments
Figure 716
(h) Install relief valve through inlet case aperture into oil pressure pump housing;
secure relief valve with retaining ring, using tool (Ref. PWC30415).
(i) Install check valve, new oil filter element and cover (Ref. Final Assembly).
(13) Remove main oil filter and chip detector and check for metal particle contamination.
(14) If heavy contamination is evident, return engine to overhaul shop for unusual oil
condition examination and inspection (Ref. Light Overhaul).
(16) Should an engine sustain propeller shaft seizure on test using a slave propeller
governor, recall governor from test cell and conduct light overhaul (Ref. 61-20-00,
LIGHT OVERHAUL).
14. Preservation
(1) Refer to Para. 8. for physical location of test cell connections and plumbing.
Remove interconnect drain pipes and instrumentation harness.
(2) Fit blanking caps/covers to open-ended pipes and ports of engine and test facility.
T. FT .
URE AL
PRESS 10000
23000
22000 8000
GAS GENERATOR SPEED (NG) − RPM
21000
6000
20000
4000
19000
2000
18000
EL
SEA LEV
17000
16000
−20 −10 0 10 20 30 40 50 60 70 80 90 100
C13733
Ng Corrected for Temperature and Altitude
Figure 717
750
700
650
600
SHP/DEL
550
500
450
400
−20 0 20 40 60 80 100 120
Tt1 AMBIENT TEMPERATURE F °
C30945A
Reduced Power Trim Curve SHP Corrected for Temperature
Figure 718
A. Remove Engine From Propeller Test Stand And Install In Assembly Stand
(1) Attach hoist to lifting eye (PWC32117) on mount ring. Take up slack on hoist chain.
(2) Unlock and remove bolts and nuts securing mount ring to test stand.
(3) Lift engine and mount ring and install in assembly stand (Ref. Storage Instructions).
B. Remove Engine from Dynamometer Stand and Install in Assembly Stand (Ref. Fig. 707)
(2) Remove eight nuts (20) and bolts (21) securing coupling shaft to propeller shaft
flange.
(3) Attach hoist to lifting eye (PWC32081) on engine center mount ring. Take up slack
on hoist.
(4) Remove nuts (15), spacers (14 and 13), and bolts (12) securing left- and right-side
mounts (3 and 1) to mount ring (2).
(5) Remove nut (7), washer (6) and bolt (11) securing bracket (5) to struts (10).
(7) Remove propeller shaft plug (18); remove and discard preformed packing (19).
(8) Remove three bolts (9) and washers (8) securing bracket (5) to accessory gearbox.
Remove bracket.
(10) Remove slave nuts (16) and bolts (17) in flange A and remove mount ring (2);
reinstall bolts and nuts to secure flange (Ref. 72-10-00, SUB-ASSEMBLY).
A. Remove test accessories and slave equipment (Ref. Para. 8. for item location).
Return the engine to the assembly bay (overhaul shop) for security check of parts and
components, torque values and lockwiring (Ref. Final Assembly).
NOTE: The on-wing run-in is for a power section specifically returned for unscheduled
repair (LIGHT OVERHAUL), when new sleeve bearings have been installed in
first-stage planet gears, or when three or more new sleeve bearings are installed in
second-stage planet gears in propeller reduction gearbox.
A. Incremental Run-in
(1) Conduct pre-start and engine motoring checks with propeller feathered (refer to
appropriate airframe manual).
(2) Start engine with propeller feathered (refer to appropriate airframe manual).
(4) Unfeather propeller and run engine at IDLE for 10 minutes with propeller in fine
pitch.
(5) Increase power gradually to obtain the following Np% maximum speeds in
sequence. Dwell at each speed for five minutes:
Np (percent) RPM
67 1470
73 1600
79 1700
85 1870
88 1940
91 2000
96 2140
100 2200
(6) Hold Np at 100% and increase torque in increments. Dwell at each torque level for
10 minutes:
PSI LB.FT.
31 957
34 1050
39 1204
42.5 1315
(b) PT6A-27/-28 engines:
PSI LB.FT.
31 957
39 1192
47 1422
50 1529
53 1620
(7) Shut down engine
(8) Examine oil filter and magnetic chip detector for metal particles.
ENGINE - TROUBLESHOOTING
1. General
Figure 801 should be used as a guide during engine test to trace and rectify any problem
that may arise after scheduled or unscheduled overhaul. In some instances, the problem may
be resolved in the test cell, otherwise the engine must be returned to the overhaul shop
for unscheduled overhaul.
To facilitate troubleshooting, common engine problems are divided into four categories, each
of which contains probable symptoms of defects or malfunction in the System(s) related
to that category. Diagnostic and corrective action required to isolate and rectify the various
problems are linked in logic form to each of the symptoms.
2. Troubleshooting
CONT’D SHEET 2
C7589A_1
Troubleshooting - Starting Problems
Figure 801 (Sheet 1 of 2)
FROM SHEET 1
C7589A_2
Troubleshooting - Starting Problems
Figure 801 (Sheet 2)
CONT’D SHEET 2
C7588B_1
Troubleshooting - Operating Problems
Figure 802 (Sheet 1 of 3)
C7588B_2
Troubleshooting - Operating Problems
Figure 802 (Sheet 2)
FROM SHEET 2
C7588B_3
Troubleshooting - Operating Problems
Figure 802 (Sheet 3)
CONT’D SHEET 2
C7587A_1
Troubleshooting - Lubricating System Problems
Figure 803 (Sheet 1 of 2)
C7587A_2
Troubleshooting - Lubricating System Problems
Figure 803 (Sheet 2)
C7586A
Troubleshooting - Unacceptable Performance Parameters
Figure 804
ENGINE - STORAGE
1. General
A. Special handling, packing, storage and preservation procedures for individual components
or sub-assemblies are described, where necessary, in Storage Instructions of the
appropriate Chapter.
B. This section provides information and procedures necessary for storage, preservation
and depreservation of the complete engine, and includes handling instructions for
removing or installing the engine in its fiberboard container, metal container or stand.
Two different fiberboard storage and shipping containers are in general use; Type I, made
to meet the initial requirement for shipping and storage of PT6A-27/-28 engines, Type
II, a container redesigned to smaller dimensions for use with PT6A-21/-27/-28 engines,
and Type III, a reinforced fiberboard container for use with PT6A-28 engines. A
reusable metal shipping container is also available, and can be used with all engine
models.
2. Consumable Materials
The consumable materials listed below are used in the following procedures.
The special tools listed below are used in the following procedures.
Not Applicable
5. Engine Storage
(2) The fiberboard container, which must not be used for outdoor storage, or be
exposed to climatic conditions for more than one week, is intended for domestic
shipment in a closed conveyance on the North American continent, or for overseas
shipment by air.
(3) For engine shipping container leading particulars, refer to Table 901.
(1) The fiberboard shipping container is a flat-sided case consisting of a skid base, a
rectangular sleeve and a cover. A metal frame, bolted to the upper side of the base,
carries a rubber-mounted steel cradle that holds and supports the engine assembly
during transit and storage. For internal protection against the effects of moisture, the
engine is enclosed in an evacuated, sealed plastic envelope containing a specific
quantity of dehydrating material (desiccant). Cover, sleeve and base are firmly
secured after closure by five steel straps. Both the fiberboard cover and sleeve
are disposable, but the base and cradle assembly may be reused, subject to
condition.
(2) The fiberboard container, which must not be used for outdoor storage, or be
exposed to climatic conditions for more than one week, is intended for domestic
shipment in a closed conveyance on the North American continent, or for overseas
shipment by air.
(3) For engine shipping container leading particulars, refer to Table 901.
(1) The reinforced fiberboard shipping container is available for PT6A-28 engines and
is similar in construction to the Type II, with the addition of plywood reinforced sides
and cover and modified engine support.
(2) The fiberboard container, which must not be used for outdoor storage, or be
exposed to climatic conditions for more than one week, is intended for domestic
shipment in a closed conveyance on the North American continent, or for overseas
shipment by air.
(3) For engine shipping container leading particulars, refer to Table 901.
(1) The metal storage and shipping container is of steel construction; manufactured in
two halves and joined at the horizontal center line. A gasket between the upper and
lower halves forms a hermetic seal. The metal container is reusable and may be
used for long term indoor and outdoor storage, provided the humidity level within the
container is frequently checked, the desiccant replenished as required, and the
engine preserved in accordance with the preservation schedule (Ref. Para. 7.).
(2) The metal container is pressurized. An air filler valve and a relief valve are fitted in
the service receptacle to maintain the pressure within the container to equal 5 psi
at 16°C (60°F). The service receptacle cover and service receptacle can be removed
to provide access to the desiccant cage for desiccant replacement. Removal of
the record receptacle cover will allow access to the record receptacle that provides
storage for the engine log book, shipping instructions and other documents.
(3) For metal storage and shipping container data, refer to Table 902.
E. Humidity Control
(1) To maintain internal moisture conditions at a safe level for storage, a specific
quantity of dehydrating material (desiccant) (Ref. IPC) is stowed in each type of
container. The desiccant is packed in individual bags, each containing eight units
(one unit weighs one ounce (28.34 g)).
(2) Each container has a humidity indicator to show the moisture level within the
container without disturbing the container or the contents. At a safe moisture level (up
to 40 percent relative humidity) the indicator color is blue.
(3) If the internal humidity increases, the color gradually changes to pink. An all-pink
color indicates an unsafe moisture condition, and the desiccant must be replaced
with freshly activated material.
(4) Twelve bags of desiccant are used in the fiberboard container, and eight bags in
the metal container.
F. Re-activation of Desiccant
(1) Place bags of used desiccant and a pink humidity indicator in a suitable oven
controlled at 121°C (250°F), until humidity indicator turns blue.
(2) Allow oven to cool to room temperature approximately 22°C (72°F), then remove
bags and indicator.
G. Storage of Engine
(b) Replace old desiccant with bags of freshly activated desiccant and reinstall
engine in container (Ref. Para. 12.).
(a) Long term storage of engine must be accomplished in a metal container, when
stored indoors or outdoors.
(b) All precautions must be observed to eliminate loss of pressure and to prevent
humidity reaching an unsafe level.
(c) The humidity indicator and pressure must be checked once every 30 days and
rectified as necessary. Refer to Figure 907 and Table 903 Preservation
Schedule for Engine in Metal Container.
(1) Refer to instructions in Table 904 for stacking containers with or without engine.
(1) Because the engine stand (PWC30800) can be used for engine disassembly,
assembly and preparation for testing, it is necessary to select correct type of
mounting brackets, as follows:
NOTE: It is more expedient to use the above brackets for engine assembly,
when engine testing in a test cell follows:
(2) Installation procedure for each type of mounting bracket is described in following
paragraph.
B. Installation of Engine for Disassembly, Assembly and/or Testing (Ref. Fig. 901)
(a) With engine suspended from sling (8), install three non-flexible mounting
brackets (12) on engine mounting pads of gas generator case. Secure each
bracket with four bolts (13). Torque bolts 225 to 300 lb.in. and lockwire .
(a) With engine suspended from sling (8), install three mount brackets (21)(part of
flexible mounting brackets) (Ref. View C) on gas generator case mounting
pads. Secure each bracket with four bolts (13). Torque bolts 225 to 300 lb.in.
and lockwire.
(b) Assemble rubber mount pads (20) with sleeve, to each bracket (21) and secure
with four bolts and nuts (19)(Ref. View C). Ensure offset hole in each mount
pad is correctly located (Ref. View B). Tighten nuts, torque 75 to 85 lb.in. and
lockwire.
(3) Locate large section of mount ring (11) on left-hand side of engine and secure
mount ring pads (14) to brackets at 12 o’clock and 8 o’clock positions with bolts,
washers and castellated nuts. Do not tighten or lock nuts at this stage.
(4) Locate small section of mount ring (11) on right-hand side of engine, and secure
mount ring pad (14) to bracket at 4 o’clock position with bolt, washer and castellated
nut. Do not tighten or lock nut at this stage.
(5) Install two lockplates (15) on small and large sections of mount ring (11), and
secure each lockplate with eight screws. Tighten screws, torque 225 to 300 lb.in.
and lockwire.
(6) Tighten three nuts on bolts (mount ring to bracket attachment, installed in steps (3)
and (4)), torque to 50 lb.in. and install cotterpins.
(7) Secure one engine mount adapter (3) to inner face of each mounting disk (16) on
engine stand (18) with three bolts (4), washers (2) and nuts (1). Tighten nuts and
torque 600 to 650 lb.in. Ensure hub locking pin (17) is fully engaged.
(8) Position stand under suspended engine and carefully lower engine until two holes
in lug of each adapter (3) are aligned with holes in mount ring. Secure each
adapter to mount ring with two washers (6) and bolts (7) (Ref. View A). Tighten
bolts and torque 250 to 270 lb.in.
7. Preservation/Depreservation of Engine
A. Depreservation of Engine
(1) Depreservation is a preliminary step before engine check run and, when necessary,
before disassembly and overhaul.
(a) Fill oil tank with approved engine oil (Ref. Testing).
(c) Disconnect fuel line to fuel manifold at flow divider and dump valve.
(e) Open test cell fuel valve and switch fuel pump ON.
(g) Position propeller control lever at FEATHER and power control lever at TAKE
OFF (fully open).
(i) Position power control lever at CUTOFF, switch fuel supply pump OFF and
close test cell fuel valve.
(j) Reconnect fuel line to flow divider and dump valve and secure line attachment
points.
(a) Fill oil tank with approved engine oil (Ref. Testing).
(c) Disconnect fuel lines at outlet side of starting flow control valve. Cap the
bypass, dump and No. 1 manifold outlets, allowing drainage from No. 2 manifold
outlet into a suitable container.
1 2 8
3
4
14 12 13
15 10
16
9
7
6 B
5
A
11
VIEW A 16
17
14 11
DIRECTION OF OFFSET HOLE
20
21
20
MOUNT
PADS
19
OFFSET HOLE
13
VIEW B
ENGINE MOUNT PAD OFFSET HOLE
LOCATIONS AS VIEWED FROM REAR VIEW C
(ALTERNATE FLEXIBLE
MOUNT BRACKET)
C7521C
Removal/Installation of Engine from Stand
Figure 901
1. Nut
2. Washer
3. Engine Mount Adapter
4. Bolt
5. Mount Ring (Ref)
6. Washer
7. Bolt
8. Engine Sling
9. Front Lifting Bracket
10. Rear Lifting Bracket
11. Mount Ring
12. Non-flexible Mounting Bracket
13. Bolt
14. Mount Ring Pads
15. Lockplates
16. Engine Mount Disk
17. Hub Locking Pin
18. Engine Stand
19. Bolt and Nut
20. Rubber Mount Pad
21. Mounting Bracket
(f) Place propeller control lever at FEATHER, power control lever at IDLE and
start control lever at RUN positions.
(g) Motor engine until clean fuel flows from open line.
(h) Reposition start control lever at CUTOFF. Close test cell fuel supply and switch
fuel supply pump OFF.
(i) Remove caps from the bypass, dump and No. 1 manifold outlets and reconnect
all fuel lines to starting control unit.
B. Preservation of Engine
(1) The engine fuel and oil systems are preserved preparatory to storage in containers,
subject to the condition detailed in Paragraph 5.. The procedures are described in
Subparagraphs C., D. and E. following.
(2) Disconnect fuel line at inlet to flow divider valve to prevent oil from entering fuel
manifold; loosen line as required to permit drainage into a suitable container.
(5) Position propeller control lever at FEATHER and power control lever at TAKE-OFF.
(7) After motoring run, check preservation oil is flowing from open fuel line. If not,
repeat step (6) until oil flow appears.
(9) Reconnect fuel line to flow divider valve, and secure line attachment points.
(10) Disconnect oil supply line to oil-to-fuel heater inlet and fit blanking cap to inlet.
(2) Disconnect fuel lines at outlet side of starter flow control valve. Cap bypass, dump
and No. 1 manifold outlets, allowing drainage from No. 2 manifold outlet into a
suitable container.
(5) Move power control lever to TAKE-OFF and starting control lever to RUN positions.
(7) After motoring run, check preservative oil is flowing from No. 2 manifold outlet of
the starting control valve. If not, repeat step (6) until oil flow appears.
(8) Return power control lever to IDLE and starting control lever to CUT-OFF.
(9) Remove caps from the bypass, dump and No. 1 manifold outlets, and reconnect all
fuel lines to starting control valve.
(10) Disconnect oil supply line to oil-to-fuel heater inlet and fit blanking cap to inlet.
(2) Place suitable container under engine. Remove magnetic chip detector or oil drain
plug, as applicable, from propeller reduction gearbox, and drain plugs from
compressor inlet case and accessory gearbox.
(5) Allow oil to drain from engine until oil drip is slow and intermittent (approximately
one-half hour); then install oil filter, and close drains.
(6) Remove cover plates from pads of accessory drives, and spray exposed surfaces
and gearshaft with engine lubricating oil (PWC03-004). Replace cover plates.
(7) Install plugs, caps and covers to all engine openings to prevent moisture
accumulation and entry of foreign material (Ref. Fig. 902)
A. Procedure
(1) Attach sling (PWC50066) or (PWC51861-600) to engine lifting points (9) and (10),
and take up slack on hoist.
(2) Remove bolts (7) and washers (6) securing mount ring (11) to both engine mount
adapters (3).
(4) Remove eight screws securing each lockplate (15) to small and large sections of
mount ring (11). Remove lockplates.
(5) Remove cotterpins, castellated nuts and bolts from mount ring pads (14) on large
section of mount ring (11), and separate from brackets at 12 o’clock and 8 o’clock
positions.
(6) Support small section of mount ring (11) and remove cotterpin, castellated nut and
bolt securing mount ring pad (14) of mount ring to mounting bracket at 4 o’clock
position on engine.
NOTE: After removal, retain all nuts, bolts, washers and both lockplates in a
suitable bag, and attach to stand.
(7) Remove bolts (13) and separate three mount brackets (12) or (21) from gas
generator case. Retain brackets with stand.
A. Procedure
(1) When an engine is to be removed from, or installed in, a container, the following
precautions must be taken.
(a) Ensure that a hoist of sufficient lifting capacity and safety factor is available to
lift the following loads:
(c) A free overhead space of approximately six feet (approx. two meters) from the
floor to the hoist hook is required to remove the engine from the container.
(1) Cut and remove steel strapping (15) from around fiberboard container. Retain
reinforcing corners (16).
(2) Cut sealing tape and fold back flaps on top of container.
(5) Take weight of engine on sling and remove eight bolts (18) and lockwashers (19)
securing cradle to mounting brackets (14).
(6) Slowly lift engine and cradle assembly; ensure that engine remains level and is not
permitted to swing.
(7) Transfer engine to clear area and remove cradle from engine by removing
quick-release pins (21) from engine mount brackets (11) and (12).
(8) Remove 11 bolts and washers securing two engine front mount brackets (11) and
one engine rear mount bracket (12). Replace mount brackets (11) and (12) on
cradle (13) and secure with quick- release pins (21). Place bolts and washers in cloth
or polyethylene bag and secure to cradle.
(9) Retain cradle (13), wooden pallet (8) and associated hardware for reuse. Discard
non-reusable items.
(11) Remove 12 desiccant bags from engine and retain for re-activation and reuse.
(12) Remove shipping data envelope and envelope containing engine log books from
bottom of containers.
(1) Cut and remove steel strapping (3) and (10) from around fiberboard container.
Retain reinforcing corners (2) and (9). Remove cover (1) and sleeve (5) from
skid base (17).
17
14 15 16
3 4 18
5
2 6 19
13 20
7
21
8
12
9
36
11 37
1 23 22
38
1 12 24
26 12 25
FRONT VIEW REAR VIEW
10
39
POST−SB1482
OIL−FUEL−HEATER
VIEW A
31
30
32
29
33
28
VIEW A
27
34
UNDERSIDE VIEW 35 A
C8515A
Location of Shipping Covers and Plugs
Figure 902
9
20
16
15
10 21
11 21 11
12 21 18
13 19
14
17
5
3
3 7
1
5
4
22 3
2
8
6
C8514
Fiberboard Container Components - Type I
Figure 903
1. Inner Stiffener
2. Bolt
3. Plain Washer
4. Outer Stiffener
5. Self-locking Nut
6. Reinforcing Plate
7. Sheat Mount
8. Pallet
9. Engine Protective Envelope
10. Gaskets
11. Engine Mount Forward Brackets
12. Engine Mount Rear Bracket
13. Cradle
14. Mounting Bracket
15. Steel Strapping
16. Reinforcing Corners
17. Screw
18. Bolt
19. Lockwasher
20. Humidity Indicator
21. Quck-release Pins
22. Slotted Box
(4) Take weight of engine on sling, remove quick-release pins (11) and (13) securing
engine mount brackets (12) and (14) to cradle (15).
(6) Remove 11 bolts and washers securing two engine front mount brackets (12) and
one engine rear mount bracket (14) to engine. Replace mount brackets (12) and
(14) on cradle and secure with quick-release pins (11) and (13). Place bolts and
washers in cloth or polyethylene bag and secure to cradle.
(7) Retain cradle, skid base and associated hardware for reuse. Remove protective
envelope (7).
(8) Remove 12 desiccant bags from engine and retain for re-activation and reuse.
(9) Remove shipping data envelope and envelope containing engine log book from box
glued to skid base.
D. Removal of Engine from Type III Fiberboard (reinforced) Container (Ref. Fig. 905)
(1) Cut and remove steel strapping (4) from around fiberboard container. Retain
reinforcing corners (24). Remove cover (1) and sleeve (10) from skid base (12).
Retain plywood panels (3), (5) and (6) if condition permits.
(4) Take weight of engine on sling and remove eight nuts (14) and bolts (16) securing
engine support (22) to cradle mounting (13). Retain all hardware.
(5) Slowly lift engine and support; ensure that engine remains level and is not
permitted to swing.
(6) Remove nuts (26), bolts (15) securing engine support (22) to lower mount brackets
(25).
(7) Remove quick-release pin (17) from upper mount bracket (27) and lift support (22)
away from engine. Secure support (22) to cradle mounting (13) with bolts (16) and
nuts (14).
(8) Remove bolts and washers securing lower mount brackets (25) and upper mount
bracket (27) to engine. Secure brackets (25) and (27) to support (22) with bolts
(15), nuts (26) and pin (17) respectively.
(10) Remove 12 desiccant bags from engine and retain for re-activation and reuse.
(11) Remove shipping data envelope and envelope containing engine log books from
bottom of containers.
(12) Remove box containing ignition exciter (if applicable) taped to bottom of container.
(2) Remove service receptable cover (1) by removing two nuts and lockwashers.
(4) Remove 36 nuts, washers and bolts securing container top cover to container base.
(5) With hoist attached to container lifting points (8), lift container top cover vertically
to clear locating pin (6). Rest container top cover on clean, wooden blocks.
(6) Attach engine sling (PWC50066) or (PWC51861-600) to front and rear lifting
brackets at flanges A and G. Adjust lifting eye of sling to obtain level lift.
(8) If difficulty is experienced when attempting to remove quick- release pins (9), use
the following alternative method for removing engine:
(a) Remove eight bolts, washers and nuts securing mounting cradle (11) to
container.
(b) Slowly raise engine, together with mounting cradle from container.
(9) Raise engine slowly from container. Ensure that engine remains horizontal and
does not swing.
(10) Remove 11 bolts and washers securing two front mount brackets and one rear
mount bracket to engine. Replace mount brackets on cradle (11) and secure with
quick-release pins (9). Place bolts and washers in cloth or polyethylene bag and
secure to cradle.
(11) Remove four nuts and lockwashers, two studs and two bolts, and withdraw service
receptacle (3) from container base.
(12) Remove eight desiccant bags from desiccant case, and retain them for re-activation
and reuse (Ref. Para. 5.E.).
(13) Remove record receptacle cover by removing two nuts, washers and bolts.
(14) Withdraw engine log book and any other documents from record receptacle (5).
Replace cover, bolts, washers and nuts.
(15) Remove all shipping covers, caps and plugs from engine, place in suitable bag and
secure to cradle.
(17) Replace top cover and secure with 36 bolts, washers and nuts.
C3868B
Fiberboard Container Components - Type II
Figure 904
1. Cover
2. Reinforcing Corners
3. Steel Strap
4. Pressure Sensitive Tape
5. Sleeve
6. Humidity Indicator
7. Protective Envelope
8. Gaskets
9. Reinforcing Corners
10. Steel Strap
11. Quick-release Pin
12. Front Mount Brackets
13. Quick-release Pin
14. Rear Mount Bracket
15. Cradle
16. Shear Mounts
17. Skid Base
(19) Retain moisture barrier/protective wrapping on engine, air inlet screen until
disassembly of engine.
A. Preparation
(2) With engine mounted in stand (PWC30800) and engine preservation accomplished
(Ref. Para. 7..B.), fit all shipping covers and plugs (Ref. Fig. 902).
(3) Enclose air inlet screen with shipping cover (35, Fig. 902).
(4) Ensure all reusable container parts are serviceable, and all non- reusable parts
have been replaced with new parts.
(5) Remove the ignition exciter (if applicable) and tape the ignition cables to the engine
using pressure-sensitive tape (PWC05-070).
(1) Open container slotted box (22) and fold bottom end flaps inwards, followed by side
flaps.
2
1
11
4
10
7
9
18 19 6
20
21
8 17
5 25 27
22
16 23
26
15
14
13
24
12
C13572
Fiberboard Container Components - Type III
Figure 905
1. Cover
2. Corner, Reinforcing
3. Top, Plywood
4. Seal, Strapping
5. End, Plywood
6. Side, Plywood
7. Gaskets
8. Protective Envelope
9. Humidity Indicator
10. Sleeve, Fiberboard
11. Tape
12. Skid Base
13. Cradle Mounting
14. Nut
15. Bolt
16. Bolt
17. Quick-release Pin and Lanyard
18. Bolt
19. Swivel Mount
20. Washer
21. Split Pin
22. Engine Support
23. Strapping
24. Corner, Reinforcing
25. Bracket, Mounting - Lower
26. Nut
27. Bracket, Mounting - Upper
(3) Resting inner stiffener (1) on bottom of container (inside) as template, drill or punch
six 0.437 inch holes.
(5) Install two bolts (2) with two plain washers (3) in upper holes of outer stiffener (4)
and attach to outside of container box (22). Install inner stiffener over bolts from
inside container and loosely attach with plain washers (3) and self-locking nuts (5).
(6) In each lower pair of holes, install bolts through reinforcing plate (6) and container
box (22). Install shear mounts (7) over protruding ends of bolts and loosely secure
with plain washers (3) and self-locking nuts (5).
11
4
2
10
C1186C
Metal Shipping Container Components
Figure 906
(7) Repeat steps (5) and (6) on opposite side. Tighten all 12 bolts and torque 80 to
90 lb.in.
(8) Install four mounting brackets (14) to shear mounts (7) using screws (17).
(10) Attach sling (PWC50066) or (PWC51861-600) to engine lifting points and take up
slack on hoist.
(11) Remove engine from stand as described in Paragraph 8.. Ensure mounting
brackets have been removed from gas generator case and attached to stand.
(12) Check that interior of protective envelope is free of dirt, oil, water and other
contaminants.
(13) Install new, protective envelope (9) under engine, aligning gaskets (10) with lower
engine mounting pads on each side of engine, and accessory gearbox mounting
pad.
(15) Attach container rear mount bracket (12) to mounting pad at 6 o’clock position on
accessory gearbox with three bolts and lockwashers. Tighten bolts and torque 50 to
70 lb.in.
(16) Retain engine log book and relevant papers in waterproof envelopes and seal with
pressure-sensitive tape (PWC05-070). Insert envelopes in suitable box and secure
to bottom of engine container.
(17) Attach cradle (13) to engine mount brackets (previously installed) with quick-release
pins (21).
(19) Lower engine and cradle assembly carefully into container; align upward locating
pins protruding from four mounting brackets (14) with four holes in cradle.
(20) Secure cradle to mounting brackets with eight bolts (18) and lockwashers (19).
(21) Tie 12 (eight-ounce) freshly activated desiccant bags to engine; evenly dispose over
engine length, six top and bottom.
(22) Heat seal along top of envelope using suitable hand soldering iron, leaving one
corner open. Evacuate air, fold corner and heat seal.
(23) Fold protective envelope and check that humidity indicator aligns with window in
container. Tape envelope folds with pressure-sensitive tape (PWC05-070).
(24) First fold end flaps of container inward, then fold side flaps.
(25) Using pressure-sensitive tape (PWC05-070), seal middle seam and overlap ends
and extend around sides approximately 8 inches. Tape edges at both ends and
extend around side approximately 12 inches.
(26) Secure container to pallet with five sets of 3/4 inch commercial steel strapping (15)
over 10 reinforcing corners (16).
(27) Stencil engine model and serial number, inspection, preservation and packaging
dates on both ends of container.
(1) Attach sling (PWC50066) or (PWC51861-600) to engine lifting points and take up
slack on hoist.
(2) Remove engine from stand (Ref. Para. 8., preceding). Ensure mounting brackets
have been removed from gas generator case and attached to stand.
(3) Check that interior of protective envelope is free of dirt, oil, water and other
contaminants.
(4) Install new, protective envelope (7) under engine, aligning gaskets (8) with lower
engine mounting pads on each side of engine and accessory gearbox mounting
pad.
(6) Attach container rear mount bracket (14) to mounting pad at 6 o’clock position on
accessory gearbox with three bolts and lockwashers. Tighten bolts and torque 50 to
70 lb.in.
(7) Place engine log book and relevant papers in waterproof envelopes and seal with
pressure-sensitive tape (PWC05-070). Insert envelopes in box glued to bottom of
skid base, and seal box.
(8) Lower engine into cradle (15) on skid base (17), and secure mount brackets (12)
and (14) to cradle with three quick-release pins (11) and (13).
(11) Tie 12 (eight-ounce) freshly activated desiccant bags to engine; evenly dispose over
engine length, six top and bottom.
(12) Heat seal along top of envelope using suitable hand soldering iron, leaving one
corner open. Evacuate air, fold corner and heat seal.
(13) Install fiberboard sleeve (5) over engine and fit in position on skid base (17).
(14) Fold protective envelope, and check that humidity indicator (6) aligns with window
in sleeve. Tape envelope folds with pressure-sensitive tape (PWC05-070).
(15) Close flaps of sleeve and seal with pressure-sensitive tape (4).
(16) Place cover (1) on sleeve, fold flaps down and seal at each corner with
pressure-sensitive tape (4).
(17) Secure cover horizontally with 3/4-inch commercial steel strapping (3) and four
reinforcing corners (2).
(18) Secure cover and sleeve to skid base with 3/4-inch steel strapping (10) and 16
reinforcing corners (9).
(19) Stencil engine model and serial number, inspection, preservation and packaging
dates on both ends of container.
D. Installation of Engine in Type III Fiberboard (reinforced) Container (Ref. Fig. 905):
(1) Attach sling (PWC50066) or (PWC51861-600) to engine lifting points and take up
slack on hoist.
(2) Remove engine from stand (Ref. Para. 6, preceding). Ensure mounting brackets
have been removed from gas generator case and attached to stand.
(3) Check that interior of protective envelope (8) is free of dirt, oil, water and other
contaminants.
(4) Install protective envelope around engine, align mount gaskets (7) with lower and
upper engine mount pads.
(6) Place engine support (22) over engine. Insert quick-release pin (17) through upper
bracket (27) and secure lower brackets (25) with bolts (15) washers and nuts (26).
Tighten bolts and torque 675 to 750 lb.in.
(7) Place engine log book and relevant papers in waterproof envelopes and seal with
pressure-sensitive tape (PWC05-070). Insert envelopes in box glued to bottom of
skid base, and seal box.
(8) Place ignition exciter (if applicable) in protective envelope along with one four-unit
desiccant bag. Heat seal envelope, leaving one corner open, evacuate air and seal
corner. Place envelope in box and secure with tape (PWC05-070) to container
floor.
(9) Lower engine onto cradle mounting (13), align engine support (22) with location
dowels and secure using bolts (16) and nuts (14). Tighten and torque bolts 275 to
300 lb.in.
(12) Tie 12 (eight-ounce) freshly activated desiccant bags to engine; evenly dispose
over engine length, six top and bottom.
(13) Heat seal along top of envelope (8) using suitable hand soldering iron, leaving one
corner open. Evacuate air, fold corner and heat seal.
(14) Install fiberboard sleeve (10) complete with plywood panels (5) and (6) over engine
and fit in position on skid base (12).
(15) Fold protective envelope, and check that humidity indicator (9) aligns with window
in sleeve. Tape envelope folds with pressure-sensitive tape (PWC05-070).
(16) Close flaps of sleeve and seal with pressure-sensitive tape (11).
(17) Place cover (1) complete with plywood top panel (3) on sleeve, fold flaps down and
seal at each corner with pressure-sensitive tape (11).
(18) Secure cover horizontally with 3/4-inch commercial steel strapping (23) and four
reinforcing corners (2).
(19) Secure cover and sleeve to skid base with 3/4-inch commercial steel strapping (23)
and 16 reinforcing corners (24).
(20) Secure cover and sleeve to skid base with 3/4-inch commercial steel strapping (23)
and 16 reinforcing corners (24).
(21) Stencil engine model and serial number, inspection, preservation and packaging
dates on both ends of container.
A. Procedure
(2) With engine mounted in stand (Ref. Para. 6.) and engine preservation procedure
accomplished (Ref. Para. 7.), install all shipping covers and plugs (Ref. Fig. 902).
(4) Top and bottom interior halves of metal container must be clean and dry.
(5) Mating flanges of top and bottom halves of metal container must be clean and free
of damage. A new gasket (10, Fig. 906) must be used on container.
(6) Attach sling (PWC50066) or (PWC51861-600) to engine lifting points and take up
slack on hoist.
(7) Remove engine from stand (Ref. Para. 8.). Ensure mounting brackets have been
removed from gas generator case and attach to stand.
(9) Use three bolts and lockwashers, and attach container rear mount bracket to
mounting pad at 6 o’clock position on accessory gearbox. Tighten bolts and torque 50
to 70 lb.in.
(10) Carefully lower engine into container base. Secure mount brackets to cradle (11)
with three quick-release pins (9).
(11) If cradle has been removed from container for engine installation, proceed as
follows:
(a) Install cradle (11) on engine and secure mounting brackets with three
quick-release pins (9).
(b) Lower engine, together with mounting cradle (11), into container base.
(c) Secure cradle to container with eight bolts, washers and nuts. Tighten and
torque nuts 150 to 170 lb.in.
(12) Insert eight bags of desiccant (64 units total) into cage at front end of container
base. Reverse condition and reuse humidity indicator (if serviceable), otherwise
install new indicator.
NOTE: Make sure desiccant bags are removed from protective polyethylene
containers.
(13) Liberally coat new gasket (10) with anti-sticking compound (PWC09-003) and install
gasket in position on mating flange of container base.
(14) Lift top cover into position using hoist and sling at lifting points (8). Lower cover
over locating pin (6) on container base forward flange.
(15) Secure top cover to container base using 36 bolts, washers and nuts. Tighten nuts
and torque progressively to 250 to 270 lb.in.
(17) Retain engine log book and relevant papers in waterproof envelope and seal with
pressure-sensitive tape (PWC05-070). Insert envelopes in record receptacle (5),
replace cover and secure with two bolts, washers and nuts. Torque nuts 135 to
150 lb.in.
(18) Replace service receptacle (3) and secure with two studs and bolts, four lockwashers
and nuts. Tighten nuts and torque 250 to 270 lb.in.
(19) Introduce dry, clean air through air filler valve (2) until internal air pressure equals
recommended value for prevailing ambient temperature (Ref. Fig. 907). Replace
valve cap.
(20) Check container for pressure leaks using leak checking fluid (PWC05-007). Seal
any leaks immediately.
(21) Replace service receptacle cover (1) and secure with two lockwashers and nuts.
Tighten and torque nuts 250 to 270 lb.in.
A. Procedure
(1) When humidity indicator shows an unsafe condition (Ref. Table 903), renew
desiccant as follows (Ref. Fig. 906):
(a) Remove two nuts and lockwashers, and service receptacle cover (1).
(b) Release air through air filler valve (2) to depressurize container.
(d) Take eight desiccant bags from desiccant cage and retain them for re-activation
and reuse (Ref. Para . 5. E.).
(e) Insert eight bags of freshly activated desiccant (64 units total) into cage.
NOTE: Make sure desiccant bags are removed from protective polyethylene
containers.
(f) Replace service receptacle (3) and secure with two studs and bolts for
lockwashers and nuts. Tighten nuts and torque 250 to 270 lb.in.
(g) Introduce clean, dry air through air filler valve (2) until internal air pressure
equals recommended value for prevailing ambient temperature (Ref. Fig.
907). Replace valve cap.
(h) Check container for pressure leaks with leak checking fluid (PWC05-007). Any
leaks must be sealed immediately.
(i) Replace service receptacle cover (1), and secure with two lockwashers and
nuts. Tighten and torque nuts 250 to 270 lb.in.
5
PRESSURE PSIG
EXAMPLE:
CONTAINER INTERNAL PRESSURE/ WITH AN AMBIENT
AMBIENT TEMPERATURE RELATIONSHIP TEMPERATURE OF
4 65 ° F (18 ° C)
CONTAINER PRESSURE
SHOULD BE 5.2 PSIG
C9160
Metal Container Pressure/Ambient Temperature Relationship
Figure 907
1. General
Depending on the nature of the problem or defect and the assembly or component(s)
involved, the scope of light overhaul can vary considerably from normal scheduled overhaul,
especially when diagnostic capabilities are required for inspection purposes. Because of
this, procedures covering disassembly, cleaning, inspection, repair or replacement, and
assembly, are included in the LIGHT OVERHAUL Section .
To avoid repetition, normal overhaul procedures which apply (in whole or in part) to light
overhaul are cross-referenced in all Chapters dealing with light overhaul.
Hot section inspection can be implemented without engine disassembly, using the borescope
equipment (Ref. INTRODUCTION).
2. Light Overhaul
(1) Overtorque
(3) Overtemperature
(4) Overspeed
(11) Loss of all power turbine blades (not associated with loss of compressor turbine
blades).
(12) Damaged ring gear, first and second-stage sun gears or power turbine shaft
coupling.
A. General
(1) The problem and defects are diagnosed and the engine is separated into three
major sub-assemblies as follows:
(2) Each major sub-assembly is further separated into minor assemblies, which are
subject to unscheduled overhaul procedures in their appropriate chapter, to
resolve and rectify the problem or defect. Refer to Light Overhaul in the relevant
Chapter of this manual (Ref. Table 1301) and also the following paragraphs.
TABLE 1301, Light Overhaul Reference for Unscheduled Removal - Engine (Cont’d)
Reason for Unscheduled Removal 72-01-00 72-30-00 72-60-00
Loss of All Power Turbine Blades (not *
associated with loss of compressor
turbine blades)
High Oil Consumption (Smoky Starts) * *
Damaged Ring Gear, First and Second *
Stage Sun Gears or Power Turbine
Shaft Coupling
Decoupled Accessory Gearbox * * *
High Oil Consumption (smoky starts) *
Fire Extinquishing Agent Contamination * * *
4. Overtemperature
A. Procedure
(a) When overtemperature conditions fall within area A (Ref. Fig. 1301), conduct a
hot section inspection of the power section (Ref. 72-01-00, LIGHT OVERHAUL)
and gas generator assembly (Ref. 72-30-00, LIGHT OVERHAUL).
(b) When overtemperature conditions fall within area B (Ref. Fig. 1301), conduct
an overtemperature inspection of power section (Ref. 72-01-00, LIGHT
OVERHAUL), and gas generator assembly (Ref. 72-30-00, LIGHT OVERHAUL).
5. Dropped Engine
A. Procedure
(1) When an engine has been dropped during handling, or in a P&WC shipping
container, conduct an external inspection of the engine as follows:
(c) Inspect exhaust duct and gas generator case for buckling, distortion and
cracks.
(d) Inspect tubing, sense lines, brackets and sheet metal parts for distortion.
(e) Check for security of attachment and integrity of mounting flanges of all
accessories.
°F °C
2015 1100
1995 1090
INTERTURBINE TEMPERATURE
B
1895 1035
1795 980
NO ACTION REQUIRED
1695 925
1 2 5 10 15 20 30
TIME SECONDS
STARTING CONDITIONS ONLY
°F °C
1565 850
1455 790
B
1435 780
1415 770
A
1395 760
1380 750
NO ACTION REQUIRED
2 10 20 30 40 50 60 70 80 90
TIME IN SECONDS ALL
CONDITIONS EXCEPT STARTING
°F °C
1515 825
1410 765
B
INTER−TURBINE TEMPERATURE
1390 755
1375 745 A
1355 735
1340 725
NO ACTION REQUIRED
2 10 20 30 40 50 60 70 80 90
TIME IN SECONDS
ALL CONDITIONS EXCEPT STARTING
B. General
Separate power section from gas generator assembly (Ref. Disassembly) and conduct
an inspection of these assemblies (Ref. 72-01-00 , 72-30-00 and 72-60-00, LIGHT
OVERHAUL).
A. General
B. Metal Contaminants
When metal contaminants are evident, consideration must be given to particle/flake size,
shape and engine operating history.
C. Particles
D. Metal Chip
A flake is a metal chip having immeasurable thickness, but large enough to become
entrapped on the main oil filter surface.
(1) Small flakes of non-ferrous metal normally originate from plain bearings or bushings
of Babbitt, tin, bronze or silver.
(2) Small flakes of ferrous metal normally originate from spalled anti-friction bearings,
gear teeth or from fretting.
(3) Slivers of steel normally originate from interference between steel parts or from
heavy scoring.
(4) Fuzz or powdered material is cast iron and originates from propeller shaft oil
transfer sleeve.
(5) If a fire extinguisher has been used on an engine, consideration must be given to
the possibility of extinguishing agent entering oil system.
(2) Pressure dropped below 100 psi but remained above 40 psi. No metal particles
found in main oil filter or on chip detector.
(2) Pressure dropped below 40 psi. Metal particles found in main oil filter or on chip
detector.
(3) Any magnetic particles or more than 40 non-magnetic particles found in main oil
filter.
(1) Separate engine into three engine major sub-assemblies (Ref. Disassembly).
(2) Remove power section and accessory gearbox from engine (Ref. Disassembly).
(3) Remove propeller reduction gearbox from power seciton (Ref. 72-01-00, LIGHT
OVERHAUL).
(4) Pressure flush accessory gearbox and main oil tank (Ref. 72-60-00, LIGHT
OVERHAUL).
(7) Rectify external oil system components subjected to unusual oil conditions; when
necessary, refer to Table 1301 for chapter reference.
I. Rectify Part B
(1) Refer to Table 1303 for chapter reference and rectification of external oil system
components.
(2) Separate engine into three engine major sub-assemblies (Ref. Disassembly).
(3) Disassemble power section (Ref. Disassembly); rectify for unusual oil conditions on
all assemblies removed (72-10-00, LIGHT OVERHAUL, Table 1301).
(4) Disassemble gas generator assembly (Ref. Disassembly); rectify for unusual oil
conditions on all assemblies removed (Ref. 72-30-00, LIGHT OVERHAUL, Table
1301).
(5) Disassemble accessory gearbox (Ref. Disassembly), rectify for unusual oil
conditions on all assemblies removed (Ref. 72-60-00, LIGHT OVERHAUL, Table
1301).
A. General
(1) Where fires have been external, or have been confined to burner and turbine gas
path, and overtemperature limits have not been exceeded, carry out light overhaul
procedures following.
(2) Where overtemperature limits have been exceeded and fire extinguishing agent
contamination is present, carry out light overhaul procedures Subpara. 4. and
following.
(2) Remove externals from engine and separate into following major subassemblies
(Ref. Disassembly).
(6) Conduct light overhaul for contamination by fire extinguishing agents on each
subassembly as outlines in appropriate chapter.
(7) If oil system contamination is suspected, treat as for unusual oil conditions (Ref.
Subpara. E. preceding).
8. Power Section
9. Engine Components
A. General
If any of the following engine components are returned to an overhaul facility after
unscheduled removal, refer to LIGHT OVERHAUL in Chapter 72-30-00 and those listed
in Table 1302.
TABLE 1302, Light Overhaul Reference for Unscheduled Removal - Engine Components
Component Chapter
Compressor Turbine (Blade Shift) 72-50-02
Combustion Chamber Exit Duct (Small) 72-50-01
Combustion Chamber Exit Duct (Large) 72-50-01
Combustion Chamber Liner 72-40-01
10. Accessories
NOTE: Where light overhaul is not specified, refer to normal scheduled overhaul
instructions in the relevant manual.
A. Problems
B. General
Refer to Light Overhaul in the specified chapter of this manual (Ref. Table 1303).
TABLE 1303, Light Overhaul Reference for Unscheduled Removal - External Components
REASON FOR UNSCHEDULED REMOVAL
CHAPTER
1 2 3 4 5 6 7 REFERENCE
* * * * * * * 61-20-00
* * * 72-30-01
* * * 72-30-02
* * * * * 73-10-01
* * * * 73-10-02
* * * 73-10-03
* * * * 73-10-04
* * * * 73-10-05
* * * 73-10-06
* * * * 73-10-07
* * * 73-10-08
* * * * 73-20-00
* * * * 74-10-01
* * * * 74-10-00
* * 74-20-01
* * 74-20-00
12. Testing
After completing light overhaul, engine must be tested in accordance with procedures
described in Testing Section of this chapter.
After completing light overhaul of power sections, install in a slave gas generator assembly
(Ref. Final Assembly) and test (Ref. Testing).