###  Copyright 2010 Pilatus-Aircraft Ltd. - Copyright in this manual and associated documents and drawings belongs to Pilatus-Aircraft Ltd. All rights reserved. No reproduction of all or part of this manual shall be made without the prior written consent of Pilatus-Ai rcraft Ltd. This document contains information that may be confidential. Disclosure to others of informati on contained herein requires the written consent of Pilatus-Aircraft Ltd.

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334 RECORD OF REVISIONS

Rev No. Date of Issue: Date Inserted: Signature: Rev No. Date of Issue: Date Inserted: Signature:

1 May 14/10 May 14/10 PILATUS 26
2 Jul 31/11 Jul 31/11 PILATUS 27
3 Jul 31/12 Jul 31/12 PILATUS 28
4 29 5 30 6 31
7 32 8 33 9 34 10 35 11 36 12 37 13 38 14 39 15 40 16 41 17 42 18 43 19 44 20 45 21 46 22 47 23 48 24 49 25 50

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334

INTENTIONALLY BLANK

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334 RECORD OF TEMPORARY REVISIONS

Temp Rev No. Date of Issue: Date Inserted: Signature: Date Removed / Incorporated in: Signature:

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334 Temp Rev No. Date of Issue: Date Inserted: Signature: Date Removed / Incorporated in: Signature:

# LOEP Page 1 Jul 31/12 

# PC-6 AIRWORTHINESS LIMITATIONS

DOCUMENT NO. 02334 LIST OF EFFECTIVE PAGES

Section Pages Date
Title Page 1 Jul 31/12 2 Jul 31/12
Record of Revisions 1 Feb 28/10 2 Feb 28/10 Record of Temporary Revisions 1 2 Feb 28/10 Feb 28/10 List of Effective Pages 1 Jul 31/12 2 Jul 31/12
Table of Contents 1 Jul 31/11 2 Jul 31/11
Airworthiness Limitations 1 Jul 31/12 2 Jul 31/12 3 Jul 31/12 4 Jul 31/12 5 Jul 31/12 6 Jul 31/12
APPENDIX A 601 Feb 28/10 602 Feb 28/10 603 Feb 28/10 604 Feb 28/10 605 Feb 28/10 606 Feb 28/10
APPENDIX B 601 Feb 28/10 602 Feb 28/10 603 Feb 28/10 604 Feb 28/10 605 Feb 28/10 606 Feb 28/10
APPENDIX C 601 Feb 28/10 602 Feb 28/10 603 Feb 28/10 604 Feb 28/10 605 Feb 28/10 606 Feb 28/10 607 Feb 28/10 608 Feb 28/10 APPENDIX C (Cont’d) 609 Feb 28/10 610 Feb 28/10 611 Feb 28/10 612 Feb 28/10 613 Feb 28/10 614 Feb 28/10
APPENDIX D 401 Feb 28/10 402 Feb 28/10 403 Feb 28/10 404 Feb 28/10 405 Feb 28/10 406 Feb 28/10 407 Feb 28/10 408 Feb 28/10 409 Feb 28/10 410 Feb 28/10 411 Feb 28/10 412 Feb 28/10
APPENDIX E 1 Feb 28/10 2 Feb 28/10 3 Feb 28/10 4 Feb 28/10 5 Feb 28/10 6 Feb 28/10 7 Feb 28/10 8 Feb 28/10 9 Feb 28/10 10 Feb 28/10 11 Feb 28/10 12 Feb 28/10 13 Feb 28/10 14 Feb 28/10 15 Feb 28/10 16 Feb 28/10 17 Feb 28/10 18 Feb 28/10
APPENDIX F 401 Jul 31/11 402 Jul 31/11 403 Jul 31/11 404 Jul 31/11 Section Pages Date

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# PC-6 AIRWORTHINESS LIMITATIONS

APPENDIX G 601 Jul 31/11 602 Jul 31/11 603 Jul 31/11 604 Jul 31/11 Section Pages Date Section Pages Date

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334 TABLE OF CONTENTS

Subject Page Effectivity

AIRWORTHINESS LIMITATIONS General 1 All Mandatory Structural Inspections 1 All Life Limited Items 4 All

APPENDICES Horizontal Trim-Actuator Support-Bracket and Frame 12A Inspection / Chec k APPENDIX A 601 All Horizontal Trim-Actuator Bearing-Fork or Bearing Support Assemblies Inspection / Chec k APPENDIX B 601 All Wing Strut Fitting Inspection / Check APPENDIX C 601 All Wing Strut Fitting Removal / Installation APPENDIX D 401 All Consumable Materials List General APPENDIX E 1 All Aileron / Flap Support Brackets Removal / Installation APPENDIX F 401 All Aileron / Flap Support Brackets Inspection / Check APPENDIX G 601 All

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334

INTENTIONALLY BLANKEFFECTIVITY: All 

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334 AIRWORTHINESS LIMITATIONS

1. General The Airworthiness Limitations section is EASA approved and variations mu st also be approved. The Airworthiness Limitations section is also FAA a pproved for US registered aircraft in accordance with FAR 21.29. The Airworthiness Limitations section is FAA approved and specifies maintenance required under 14 CFR 43.16 and 91.403 unless an alternate program has been FAA approved. On any PC-6, do not install the following parts: Mechanical stabilizer trim system: Connecting pieces 6232.0026.XX manufactured by Fairchild. The Fairchild part has a rivet in the center that is not on the Pilatus part (refer also to SB 53-001, Rev. 1). Electrical stabilizer trim system: Fitting 116.40.06.033 without index after part number (refer also to SB 53-001, Rev. 1). 2. Mandatory Structural Inspections
Item Maintenance Requirement Interval Chapter 27 - Flight Controls Aileron, Rudder, Elevator and Flap Bellcranks and Levers Examine (Non Destructive Inspection, see NOTES F and G below) 7000 flying hours or 14 years (whichever comes first)

Aileron Trim Screw-Actuator (Mechanical System) Check for backlash. The maximum permitted backlash is 0,3 mm (0.012 in.) 3500 flying hours or 7 years (whichever comes first)

Chapter 53 - Fuselage Stabilizer Trim Atta chment Components, FR12A Examine in accordance with APPENDIX A 3500 flying hours or 7 years (whichever comes first) See NOTE C below FR12A Examine in accordance with APPENDIX A 3500 flying hours or 7 years (whichever comes first) See NOTE C below Fuselage - Wing-Strut Attachment-Brackets Examine (Non Destructive Inspection, see NOTES F and G below) 3500 flying hours or 7 years (whichever comes first)EFFECTIVITY: All 

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334

Chapter 55 - Stabilizers Trim Actuator Attachment Examine in accordance with APPENDIX B 3500 flying hours or 7 years (whichever comes first) See NOTE C below Chapter 57 - Wings Left and Right Wing-Strut Fitting (A ll P/Ns) Examine in accordance with APPENDIX C, Check 1 Aircraft registered in the USA: 3 months All other aircraft (not operating in the USA): 3 months (See NOTE 1) 6 months (See NOTE 2) 12 months (See NOTE 3) NOTE 1: For aircraft that operate in a severe Corrosion Severity Zone NOTE 2: For aircraft that operate in a moderate Corrosion Severity Zone NOTE 3: For aircraft that operate in a mild Corrosion Severity Zone See NOTE D below Left Wing-Strut Fitting (P/N 6102.0041.00, 111.35.06.055, 111.35.06.184 or 111.35.06.185) Examine in accordance with APPENDIX C, Check 2 (Non Destructive Inspection, see NOTE G below) 1100 flying hours or 12 months (whichever comes first) See NOTE D below Right Wing-Strut Fitting (P/N 6102.0041.00, 111.35.06.056, 111.35.06.184 or 111.35.06.186) Examine in accordance with APPENDIX C, Check 2 (Non Destructive Inspection, see NOTE G below) 1100 flying hours or 12 months (whichever comes first) See NOTE D below Left Wing-Strut Fitting (P/N 111.35.06.193 or 111.35.06.195) Examine in accordance with APPENDIX C, Check 2 (Non Destructive Inspection, see NOTE G below) 12 months See NOTE D below

Right Wing-Strut Fitting (P/N 111.35.06.194 or 111.35.06.195) Examine in accordance with APPENDIX C, Check 2 (Non Destructive Inspection, see NOTE G below) 12 months See NOTE D below Item Maintenance Requirement IntervalEFFECTIVITY: All 

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334

Wing - Fuselage Attachments Examine (Non Destructive Inspection, see NOTES F and G below) 7000 flying hours or 14 years (whichever comes first)
Aileron/Flap Support-Brackets Examine in accordance with APPENDIX G (Non Destructive Inspection, see NOTES F and G below) 7000 flying hours or 14 years (whichever comes first)

NOTE A: Refer to the appropriate engine and pro peller maintenance manuals for the applicable airworthiness limitations. NOTE B: If any of the above maintenance tasks were acco mplished at a date earlier than the effective date of this document, the relevant interval starts from that date, except for items with NOTES C or D. NOTE C: If the maintenance requirement of this task was accomplished as part of SB 53-001 or superordinate ADs, the interval starts from that date. NOTE D: If the maintenance requirement of this task was accomplished as part of SB 57-005 or superordinate ADs, the interval starts from that date. NOTE E: Any maintenance task listed above for which NOTES B, C or D do not apply must be accomplished within 12 months from th e effective date of this document. NOTE F: You can do a Fluorescent Dye Penetrant Inspection or an Eddy Current Inspection. NOTE G: Only persons qualified and certified to NDT Level II (or higher) National Aerospace Standard NAS 410, European Standard EN 4179, or any other equivalent standards, shall do an Eddy Current Inspection. Pilatus recommend that persons qualified and certified to NDT Level II (or higher) National Aerospace Standard NAS 410, European Standard EN 4179, or any other equivalent standards, do a Fluorescent Dye Penetrant Inspection. Item Maintenance Requirement IntervalEFFECTIVITY: All 

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334 3. Life Limited Items

Item Maintenance Re quirement Interval Chapter 27 - Flight Controls Flight Control Chains (Mechanical Trim and Flaps) Replace (discard) 7000 flying hours or 14 years (whichever comes first) Aileron Attachment Bolts Replace (discard) 7000 flying hours or 14 years (whichever comes first) Elevator Attachment Bolts Replace (discard) 7000 flying hours or 14 years (whichever comes first) Rudder Attachment Bolts Replace (discard) 7000 flying hours or 14 years (whichever comes first) Flap Attachment Bolts Replace (discard) 7000 flying hours or 14 years (whichever comes first) Horizontal-Stabilizer Attachment-Bolts R eplace (discard) 7000 flying hours or 14 years (whichever comes first) Stabilizer Trim Actuator (Mechanica l Trim) Overhaul 3500 flying hours Stabilizer Trim Actuator (Electrica l Trim) Overhaul 3500 flying hours Flap Actuator (Electrical System) All models except P/Ns 978.73.14.101 and 978.73.14.103 (listed below) Overhaul 3500 flying hours or 7 years (whichever comes first)
Flap Actuator (Electrical System) (Electro-Metal Type 55.1-1100, P/N 978.73.14.101) Overhaul 3000 landings

Flap Actuator (Electrical System) (Electro-Metal Type 55.1-1100, Amdt. 2 P/N 978.73.14.103) Overhaul 5000 landings or 7 years (whichever comes first)
Flap Actuator Jacks (Mechanical System) Overhaul 3500 flying hours Chapter 32 - Landing Gear Main-Gear Shock-Strut Attachment-Bolts Replace (discard) 10000 landings or 7 years (whichever comes first) Tail-Gear Attachment-Bolts Replace (discard) 10000 landings or 7 years (whichever comes first)EFFECTIVITY: All 

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334

Chapter 35 - Oxygen Oxygen Cylinder (if installed) Overhaul and send to an authorized facility for hydrostatic test 5 years

Chapter 57 - Wings Wing Attachment Bolts Replace (discard) 7000 flying hours or 14 years (whichever comes first) Wing-Strut Attachment-Bolts Replace (discard) 7000 flying hours or 14 years (whichever comes first) Chapter 77 - Engine Indicating Low Pitch Warning-Switch Replac e (discard) 3500 flying hours

Approved by: Carl Thomas
EUROPEAN AVIATION SAFETY AGENCY (EASA) EASA Approval No: 10040713 Approval Signature: Signed original held on file at Pilatus Aircraft Ltd, Stans Approval Date: 25th July 2012 Item Maintenance Requirement IntervalEFFECTIVITY: All 

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# PC-6 AIRWORTHINESS LIMITATIONS DOCUMENT NO. 02334

INTENTIONALLY BLANKEFFECTIVITY: All 

# APPENDIX A Page 601 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

APPENDIX A HORIZONTAL TRIM-ACTUATOR SUPPORT-BRACKET AND FRAME 12A INSPECTION / CHECK

1. General This procedure gives the data and instructions nece ssary to do an inspection of the horizontal trimactuator support-bracket and auxiliary frame 12A The inspection is applicable to ai rcraft with electrical trim (CONFIG 1) or mechanical trim (CONFIG 2). This inspection should be done at the same time as the inspection of the Horizontal Trim-Actuator Bearing-Fork or Bearing SupportAssemblies (Re f. APPENDIX B). 2. Job Set Up Information A. Operator Supplied Parts

B. Consumable Materi als (Ref. APPENDIX E)

3. Procedures WARNING: BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS. OBEY THE MANUFACTURER’S HEALTH AND SAFETY INSTRUCTIONS. NOTE: In the procedures that follow: • CONFIG 1 refers to aircraft with electrical trim • CONFIG 2 refers to aircraft with mechanical trim and: • CONFIG 2A has 6 mm bolts installed • CONFIG 2B has 6,35 mm bolts installed Part No. Description Qty. Remarks 932.35.14.105 Bolt (NAS6604-5) 1 Oversize bolt if required. 932.35.14.109 Bolt (NAS6604-9) 1 Oversize bolt if required. 938.07.68.305 Nut (MS21046-4E) 2 Oversize nuts if required.

Material No. Description Remarks P01-008 Solvent P02-016 Scotch-Brite Very fine grade P02-031 Absorbent Paper P04-012 Corrosion Preventative Mastinox 6856H P07-001 CCC Solution Alodine 1200S P07-007 Primer (Epoxy)EFFECTIVITY: All 

# APPENDIX A Page 602 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
A. Preparation CONFIG 1: (1) Remove the horizontal stabilizer actuator. CONFIG 2: (2) Remove the horizontal stab ilizer actuator. During thisprocedure use clamps (or equivalent) to make sure the cables stay in position on spools of the mechanical actuator and operating mechanism. B. Removal (Ref. Fig. 601) CONFIG 1: (1) Remove the nuts (4), the washers (2) and the bolts (1), and remove the fitting (3) from FR 12A. CONFIG 2: (2) CONFIG 2A: (a) Remove the nuts (7), the washers (6) and the bolts (5), and remove the connecting piece (8) from FR12A. Record the quantity of washers (6) installed under the lower nut (7). (3) CONFIG 2B: (a) Remove the nuts (11), the washers (6), the bolts (9) and (10), and remove the connecting piece (8) from FR12A. C. Inspection (1) Do dye-penetrant flaw detection (PFD) tests: (a) Obey the manufacturers instructions and use the solvent (Material No. P01-008), Scotch-Brite (Material No. P02-016) and/or non-metallic scrap ers to remove the layers of paint and protection from: • All surfaces of the fitting (3) or connecting piece (8) • The area of the surface of FR12A where the fitting (3) or connecting piece (8) was installed (b) Obey the manufacturers instructions and use dye flaw detection procedures (fluorescent or color contrast) to do insp ections for cracks in the fitting (3) or connecting piece (8) and the applicablearea of FR12A. No crack damage is permitted. You must replace: • Cracked components (Ref. Table 601 - Component Replacement Data) • FR12A if cracks are foundEFFECTIVITY: All 

# APPENDIX A Page 603 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
(2) Do a visual inspection of FR12A: (a) Use a X10 magnifier and a source of bright light to do an inspection of FR12A for crack damage and signs of corrosion. Crack damage is not permitted. If you find crack damage you must replace FR12A (Ref . Repair and Overhaul Manual (ROM), Chap 2). Surface corrosion is permitted if not less than 90% of the material thickness remains after the corrosion is removed (Ref. ROM, Chap 12) (3) Do a check of the attachment hole diameters: CONFIG 1: (a) Use internal vernier callipers (or equivalent) to do a check of the actuator attachment hole diameter in the fitting (3). (b) A hole diameter of more than 9,555 mm (0.3762 in.) in the fitting (3) is not permitted. Replace if necessary (Ref. Table 601 - Component Replacement Data). (c) Use internal vernier callipers (or equivalent) to do a check of the diameters of the attachment bolt holes in the fitting (3) and FR12A. Hole diameters of more than 4,85 mm (0.191 in.) are not permitted. Replace defective components as necessary (Ref. Table 601 - Component Replacement Data). CONFIG 2: (d) Use internal vernier callipers (or equivalent) to do a check of the actuator attachment hole diameter in the connecting piece (8). (e) A hole diameter of more than 16.036 mm (0.631 in.) in the connecting piece (8) is not permitted. Replace if necessary (Ref. Table 601 - Component Replacement Data). (f) Use internal vernier callipers (or equivalent) to do a check of the diameters of the attachment bolt holes in the connecting piece (8) and FR12A. If all of the hole diameters are 6,024 mm (0.23717 in.) or less, continue the procedure from Para D.(2). If one or more of the holes is more than 6, 024 mm (0.237 in.) but less than 6,35 mm (0.25 in.): (i) Use a 6,35 mm (0.25 in.) (H7) reamer to increase the diameters of all of the bolt holes in the connecting piece (8) and FR12A. Deburr the holes. (g) If one or more holes is 6,374 mm (0.251 in.) or more, replace the connecting piece (8) and/or FR12A (Ref. Table 601 - Component Replacement Data). Component Part No. Replacement FR12A (Assembly) 112.35.06.197 6201.0134 Ref. ROM, Chap 2 Table 601 - Component Replacement DataEFFECTIVITY: All 

# APPENDIX A Page 604 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

D. Installation (Ref. Fig. 601) CONFIG 1: (1) Install the fitting (3): (a) Obey the manufacturers instructions and apply layers of CCC Solution (Material No. P07-001) as necessary to the applicable components and inspection areas (Ref. ROM, Chap 12). (b) Obey the manufacturers instructions and apply layers of primer (Material No. P07- 007) and paint as necessary to the applicable components and inspection areas (Ref. ROM, Chap 12). (c) Obey the manufacturers instructions a nd apply layers of corrosion preventative (Material No. P04-012) on the faying surfac es of FR12A and the fitting (3), the nuts (4), the washers (2) and the bolts (1). (d) Put the fitting (3) in position on FR12A and install the bolts (1), the washers (2) and the nuts (4). For each bolt install one washer (2) under the head of the bolt and one washer under the nut. (e) Obey the manufacturers instructions a nd use absorbent paper (Material No. P02- 031) and solvent (Material No. P01-008) to remove unwanted corrosion preventative. CONFIG 2: (2) Install the connecting piece (8): (a) Obey the manufacturers instructions and apply layers of CCC Solution (Material No. P07-001) as necessary to the applicable components and inspection areas and the surfaces of the bolt holes (Ref. ROM, Chap 12). (b) Obey the manufacturers instructions and apply layers of primer (Material No. P07- 007) and paint as necessary to the applicable components and inspection areas (Ref. ROM, Chap 12). (c) If you increased the diameter of the hole s during the inspection, use the new bolt (9) (NAS6604-9), the new bolt (10) (NAS6604-5) and the new nuts (11) (MS21046-4E), and follow the instructions for CONFIG 2B. Fitting (CONFIG 1) 116.40.06.033 or 116.40.06.112 Ref. Para D (1)

Connecting Piece (CONFIG 2) 6232.0026 Ref. Para D (2) Component Part No. Replacement

Table 601 - Component Replacement DataEFFECTIVITY: All 

# APPENDIX A Page 605 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
(3) CONFIG 2A: (a) Obey the manufacturers in structions and apply layersof corrosion preventative (Material No. P04-012) on the faying surfaces of FR12A and the connecting piece (8), the washers (6), the bolts (5) and the nuts (7). (b) Install the connecting piece (8) with the bolts (5), washers (6) and nuts (7). Install the same quantity of washers (6) under th e lower nut (7) that you recorded in the removal procedure. (c) Obey the manufacturers instructions and use absorbent paper (Material No. P02- 031) and solvent (Material No. P01-008) to remove unwanted corrosion preventative. (4) CONFIG 2B: (a) Obey the manufacturers in structions and apply layersof corrosion preventative (Material No. P04-012) on the faying surfaces of FR12A and the connecting piece (8), the washers (6), the bolts (9) and (10) and the nuts (11). (b) Install the connecting piece (8) with the bolt (9), the bolt (10), the washers (6) and the nuts (11). (c) Obey the manufacturers instructions and use absorbent paper (Material No. P02- 031) and solvent (Material No. P01-008) to remove unwanted corrosion preventative. E. Close up (1) Remove all tools and materials. Ma ke sure the work areas are clean. (2) Install the horizontal stabilizer actuator.EFFECTIVITY: All 

# APPENDIX A Page 606 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

Horizontal Trim-Actuator Support-Bracket and FR12A - Inspection/Check Figure 6016708 CONFIG 1 AIRCRAFT WITH ELECTRICAL TRIM 

# A

A

FR12A FR12A



# A 1
2

3

2

4

CONFIG 2A AIRCRAFT WITH MECHANICAL TRIM AND 6 mm BOLTS

9
6

11 11 8

6 6 

# A

FR12A

CONFIG 2B AIRCRAFT WITH MECHANICAL TRIM AND 6.35 mm BOLTS 5
6

6 10 7 7 8

6 6EFFECTIVITY: All 

# APPENDIX B Page 601 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

APPENDIX B HORIZONTAL TRIM-ACTUATOR BEARING- FORK OR BEARING SUPPORT ASSEMBLIES INSPECTION / CHECK

1. General This procedure gives the data and instructions nece ssary to do an inspection of the horizontal trimactuator bearing-fork, or bear ing support assemblies, installed in the horizontal stabilizer. The inspection is applicable to ai rcraft with electrical trim (CONFIG 1) or mechanical trim (CONFIG 2). Aircraft with electrical trim (CONFIG 1) have a bearing fork. Aircraft with mechanical trim (CONFIG 2) have bearing support assemblies. This inspection should be done at the same time as the inspection of the Horizontal Trim-Actuator Support-Bracket and Fram e 12A (Ref. APPENDIX A). 2. Job Set Up Information A. Consumable Materi als (Ref. APPENDIX E)

3. Procedures WARNING: BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS. OBEY THE MANUFACTURER’S HEALTH AND SAFETY INSTRUCTIONS. NOTE: In the procedures that follow: • CONFIG 1 refers to aircraft with electrical trim • CONFIG 2 refers to aircraft with mechanical trim A. Preparation CONFIG 1: (1) Remove the horizontal stabilizer actuator. (2) Use applicable supports to hold the horizontal stabilizer in a po sition which gives access to the bottom surface. Material No. Description Remarks P01-008 Solvent P02-016 Scotch-Brite Very fine grade P02-031 Absorbent Paper P04-012 Corrosion Preventative Mastinox 6856H P07-001 CCC Solution Alodine 1200S P07-007 Primer (Epoxy)EFFECTIVITY: All 

# APPENDIX B Page 602 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

CONFIG 2: (3) Remove the horizontal stab ilizer actuator. During thisprocedure use clamps (or equivalent) to make sure the cables stay in position on spools of the mechanical actuator and operating mechanism. (4) Use applicable supports to hold the horizontal stabilizer in a position which gives access to the bottom surface. B. Inspection (Ref. Fig. 601) (1) Do the dye-penetrant flaw detection (PFD) tests (a) Obey the manufacturers instructions and use the solvent (Material No. P01-008), Scotch-Brite (Material No. P02-016) and/or non-metallic scrap ers to remove the layers of paint and protection from: • The surfaces of the bearing fork (4) or bearing supports (6) and (7) to which you have access (b) Obey the manufacturers instructions and use dye flaw detection procedures (fluorescent or color contrast) to do inspections for cracks in th e bearing fork (4) or bearing supports (6) and (7). No crack damage is permitted. You must replace: • Cracked components (Ref. Table 601 - Component Replacement Data) • The two bearing supports (6) and (7) if only one is found cracked

(2) If you find no crack damage: (a) Obey the manufacturers instructions and apply a layer of CCC Solution (Material No. P07-001) to all bare metal areas. (b) Obey the manufacturers instructions and apply layers of primer (Material No. P07- 007) and paint as necessary to the applicable components (Ref. ROM, Chap 12). Component Part No. Replacement Bearing Fork (CONFIG 1) 116.40.06.034 Ref. Para C Bearing Support Assembly (Left and Right) (CONFIG 2) 6304.0023 Ref. Repair and Overhaul Manual (ROM), Chap 2 Table 601 - Component Replacement DataEFFECTIVITY: All 

# APPENDIX B Page 603 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
C. Replacement (Ref. Fig. 601) (1) Remove the horizontal stabilizer. (2) Use a 3,2 mm (0.126 in.) diam eter drill to remove the rivets t hat attach the access panel(s) (1) to the bottom skin of the horizo ntal stabilizer. (Ref. ROM, Chap 2). NOTE: Some horizontal stabilizers have two access panels (1). CONFIG 1: (3) Replace the bearing fork if necessary: (a) Remove the bearing fork (4). (i) Remove the nuts (5), the washers (3) and the bolts (2) then remove and discard the bearing fork (4). (ii) Obey the manufacturers instructionsand apply layers of CCC Solution (Material No. P07-001) as necessary in the rivet holes and on all bare metal surfaces. (b) Install the new bearing fork (4). (i) Obey the manufacturers instructio ns and apply layers of corrosion preventative (Material No. P04-012) on the faying surfaces of the bearing fork (4) and the adjacent structure. Also do this on the applicable surfaces of the nuts (5), the washers (3) and the bolts (2). (ii) Put the bearing fork (4) in position and install the bolts (2), washers (3) and the nuts (5). (iii) Obey the manufacturers instructions and use abso rbent paper (Material No. P02-031) and solvent (Material No. P01-008) to remove unwanted corrosion preventative. CONFIG 2: (4) Replace the bearing supports (6) and (7) if necessary (Ref. ROM, Chap 2). CONFIGS 1 and 2: (5) Obey the manufacturers instructions and appl y layers of corrosion preventative (Material No. P04-012) as necessary) on the faying surfaces of the access panel (1). (6) Put the access panel (1) in position and install rivets (CR3223-4-2) (Ref. ROM, Chap 2). (7) Install the horizontal stabilizer.EFFECTIVITY: All 

# APPENDIX B Page 604 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
D. Close up (1) Remove all tools and materials. Make sure the work areas are clean. (2) Install the horizonta l stabilizer actuator.EFFECTIVITY: All 

# APPENDIX B Page 605 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

Horizontal Trim-Actuator Bearing-Fork or Bearing Support Assembly - Inspection/Check Figure 6016709 

# B A



# B 1 

# A

1

2

1 1 CONFIG 1 AIRCRAFT WITH ELECTRICAL TRIM

CONFIG 2 AIRCRAFT WITH MECHANICAL TRIM 

# A

6 7 3

3 5

4EFFECTIVITY: All 

# APPENDIX B Page 606 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

INTENTIONALLY BLANKEFFECTIVITY: All 

# APPENDIX C Page 601 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

APPENDIX C WING STRUT FITTING - INSPECTION / CHECK CHECK 1 - VISUAL INSPECTION 1. General This procedure gives the data for the Visual Inspection (Check 1) of the Wing Strut Fittings and is applicable to both the LH and RH wing strut fittings. For the Eddy Current Inspection (Check 2) ofthe Wing Strut Fittin gs, refer to Page 607. 2. Job Set Up Information A. Tools and Equipment

B. Expendable Parts

C. Consumable Materi als (Ref. APPENDIX E) Part No. Descr iption Remarks - Torque wrench 0 to 85 Nm (0 to 750 lb. in.) - X10 magnifier Local Supply - Source of Bright Light Local Supply

IPC Ref. Description Remarks 57-21-01, Fig. 01 Cotter pin 57-26-01, Fig. 01 Bearing If necessary

Material No. Description Remarks P01-010 Solvent Or an Approved Alternative P02-031 Absorbent Paper P02-016 Scotch-Brite CAUTION: DO NOT MIX DIFFERENT TYPES OF GREASE. IF THE ORIGINAL GREASE IS TO BE REPLACED WITH A NEW TYPE OF GREASE, MAKE SURE THE BEARINGS ARE COMPLETELY CLEAN BEFORE PACKING WITH THE NEW GREASE.

P04-028 Grease P04-001, P04-004 and P04-031 are suitable alte rnatives for P04-028 for this application. P07-001 Alodine 1200S P07-007 Primer PaintEFFECTIVITY: All 

# APPENDIX C Page 602 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

3. Procedures A. Job Set Up Remove the left and right wing struts. B. Inspection (Ref. Fig. 601) (1) Remove loose paint if necessary, then, us e absorbent paper (Mat. No. P02-031) and the solvent (Mat. No. P01-010) to clean the left and right wing strut fittings (1). (2) Visually examine the left and right fittings (1) for signs of corrosion. Do this with a X10 magnifier and a source of bright light. NOTE: You can also use the straightedge of a ruler which will in dicate distortion caused by corrosion. Minor surface corrosion is permitted (Ref. ROM. Chap. 2 and 4). All other corrosion is not permitted and you must replace the defective fitting (Ref. APPENDIX D). (3) Remove minor surface corrosion (Ref. ROM. Ch ap. 2 and 4) from the given fittings (1). This step in only applicable if you have fo und permitted corrosion (Ref. Step 3.B.(2). (4) Visually examine the left and ri ght wing strut fittings (1) for signs of cracks. Do this with a X10 magnifier and a source of bright light. No cracks are permitted. If you find a crack, you must replace the fitting before next flight (Ref. APPENDIX D). (5) Examine the bearing (2). Make sure: • The bearing ball is free to rotate by hand. If necessary, you can use the attachment bolt as a lever. • The bearing ball and housing are not corroded. Remove superficial corrosion with the absorbent paper (Mat. No. P02-031) and the solvent (Mat. No. P01-010). No remaining corrosion is permitted. • The bearing housing is not loose in the wing strut fitting (1) • The bearing housing is aligned (as shown in Detail B) • The bearing ball and housing are not worn. No measurable gap is permitted. P08-059 Adhesive P08-052 or P08-060 are suitable alternatives for P08-059 for this application. Material No. Description RemarksEFFECTIVITY: All 

# APPENDIX C Page 603 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
If necessary: • Remove the bearing (Ref. Para. 3.C.) • Examine the bearing and replace if necessary (Ref. Para. 3.C.) • Install the bearing (Ref. Para. 3.D.). NOTE: If you must replace the bearing, do not install the new bearing until you have done the Eddy Current Inspection. (6) Apply layers of Alodine 1200S (Mat. No. P07-001), the primer (Mat. No. P07-007) and the applicable paint on all bare metal surfaces except the bearin g housing interfaces. (7) Lubricate the bearing (2). (a) Remove the bearing ball:
1 Rotate the bearing ball out of the bearing housing by 90 degrees.
2 Turn it until it aligns with the cut-outs in the bearing housing.
3 Remove the bearing ball.
4 Use absorbent paper (Mat. No. P02-031) and the solvent (Mat. No. P01-010) to clean the bearing and the bearing housing.
5 Apply a layer of the grease (Mat. No. P0 4-028) to the mating surfaces of the bearing and the bearing housing. (b) Install the bearing ball:
1 Align the bearing ball with the cut-outs in the bearing housing.
2 Install the bearing ball.
3 Turn the bearing by 90 degrees until it is flush in the bearing housing. C. Removal of the Bearing (Ref. Fig. 601) NOTE: This procedure is applicable if loose, dam aged, corroded, incorrectly aligned or worn bearings are found. CAUTION: DO NOT USE TOO MUCH HEAT TO RE MOVE THE BEARING. DO NOT EXCEED 120°C (224°F) FOR MORE THAN 15 MINUTES. (1) Use a hot air blower (for heat shrink sl eeves) and apply heat to loosen the adhesive between the bearing and the fitting or the bush. CAUTION: DO NOT USE TOO MUCH FORCE TOREMOVE THE BEARING. YOU CAN DAMAGE THE WING STRUT FITTING IF YOU USE TOO MUCH FORCE. (2) Use a press or applicable diameter drift to remove the bearing (2) from the bore in the fitting or the bush. If you cannot removethe bearing (2), replace the fitting (Ref. APPENDIX D). NOTE: The bearing (2) is removed from the top (wing side) of the wing strut fitting (1).EFFECTIVITY: All 

# APPENDIX C Page 604 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
(3) Use the solvent (Mat. No. P01-010) to removethe unwanted adhesive from the hole in the fitting or the bush. (4) Use the Scotch-Brite (Mat. No. P02-016) to polish the hole in the fitting or the bush. (5) Use the absorbent paper (Mat. No. P02-031) made moist with the solvent (Mat. No. P01-010) and clean the hole in the fitting or the bush. (6) For wing strut-fittings P/N 6102.0041.00, 111.35.06.055, 111.35.06.056, 111.35.06.184, 111.35.06.185 and 111.35.06.186: (a) Do a visual inspection of the bearing hole in the fitting for wear. No wear is permitted. Replace wing strut fittings thatare worn before the next flight (Ref. APPENDIX D). (b) Apply a layer of alodine (Mat. No. P07-0 01) to the surface of the hole and facing. Install the replacement bearing (2) in the alodined hole in less than 72 hours. (7) For wing strut-fittings P/N 111.35.06 .193, 111.35.06.194 and 111.35.06.195: Do a visual inspection of the bearing hole in the fitting for wear and corrosion. No corrosion is permitted. Remove all the corrosion and measure the inner diameter of the bush. The maximum permitted diameter is 32.24 mm (1.27 in.). If the inner diameter of the bush is more than the maximum permitted diamet er, replace the fitting (Ref. APPENDIX D). (8) Examine the bearing (2). Make sure: • The bearing ball is free to rotate by hand. If necessary, you can use the attachment bolt as a lever. • The bearing ball and housing are not corroded. Remove superficial corrosion with the absorbent paper (Mat. No. P02-031) and the solvent (Mat. No. P01-010). No remaining corrosion is permitted. • The bearing ball and housing are not worn. No measurable gap is permitted. (9) If necessary, discard the old bearing and use a new bearing. D. Installation of the Bearing (Ref. Fig. 601)
(1) Use the absorbent paper (Mat. No. P02-031) made moist with the solvent (Mat. No. P01-010) and clean the bonding face of the bearing (2). (2) Use the Scotch-Brite (Mat. No. P02-016) to polish the bonding face of the bearing (2). (3) Use the absorbent paper (Mat. No. P02-031) made moist with the solvent (Mat. No. P01-010) and clean the bonding face of the bearing (2). (4) Put the bearing (2) in position in the hole. Make sure it can be installed easily. Remove the bearing (2). NOTE: Put the bearing (2) in the hole as shown in Detail B, NEW ORIENTATION. (5) Mix the two parts of the adhesive (Mat. No. P08-059).EFFECTIVITY: All 

# APPENDIX C Page 605 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
(6) Apply a layer of the adhesive (Mat. No. P08-059) to the applicable surfaces of the bearing (2) and the hole. Make sure there is suffici ent adhesive to give a full bond when the parts are assembled. (7) Put the bearing (2) in position in the hole. Make sure the bearing (2) is correctly aligned (Ref. Detail B, NEW ORIENTATION) and push t he bearing (2) firmly into the hole to make sure it is tightly against the flange face. (8) Remove the unwanted adhesive (Mat. No. P08-059). CAUTION: DO NOT USE TOO MUCH HEAT. DO NOT EXCEED 120°C (224°F) FOR MORE THAN 15 MINUTES. (9) Let the adhesive (Mat. No. P08-059) cure for 5 to 7 days at room temperature or 2 hours at 65 +5°C (136 +8°F). E. Close up (1) Remove all tools and materials. Make sure that the work areas are clean. (2) Install the wing struts.EFFECTIVITY: All 

# APPENDIX C Page 606 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

Wing Strut Fitting - Visual Inspection Figure 6016692 

# A

B 

# A

1

CORRECT BEARING ALIGNMENT/POSITION 1



# B 2 

# B NEW ORIENTATION OLD ORIENTATIONEFFECTIVITY: All 

# APPENDIX C Page 607 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

CHECK 2 - EDDY CURRENT INSPECTION 1. General This procedure gives the data for the Eddy Current Inspection (Check 2) of the Wing Strut Fittings and is applicable to both the LH and RH wing strut fittings. 2. Job Set Up Information A. Tools and Equipment

B. Expendable Parts

C. Consumable Materi als (Ref. APPENDIX E) Part No. Description Remarks - Torque wrench 0 to 85 Nm (0 to 750 lb. in.) - X10 magnifier Local Supply - Source of Bright Light Local Supply - Eddy Current NDT Equipment NORTEC 2000 Eddy Current Instrument or equivalent - Shielded Probe and Lead Combination 3 mm Diameter, 500 KHz, 90-degree
- Calibration Standard 7075 Aluminum, 2124 Aluminum or 2024 Aluminum with an EDM slot 0.5 mm deep

IPC Ref. Description Remarks 57-21-01, Fig. 01 Cotter pin 57-26-01, Fig. 01 Bearing If necessary

Material No. Description Remarks P01-010 Solvent Or an Approved Alternative P02-031 Absorbent Paper P02-016 Scotch-Brite CAUTION: DO NOT MIX DIFFERENT TYPES OF GR EASE. IF THE ORIGINAL GREASE IS TO BE REPLACED WITH A NEW TYPE OF GREASE, MAKE SURE THE BEARINGS ARE COMPLETELY CLEAN BEFORE PACKING WITH THE NEW GREASE.

P04-028 Grease P04-001, P04-004 and P04-031 are suitable alte rnatives for P04-028 for this application. P07-001 Alodine 1200SEFFECTIVITY: All 

# APPENDIX C Page 608 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

3. Procedures A. Job Set Up Remove the left and right wing struts. B. Inspection (Ref. Fig. 602) (1) Remove loose paint if necessary, then, us e absorbent paper (Mat. No. P02-031) and the solvent (Mat. No. P01-010) to clean the left and right wing strut fittings (1). (2) Visually examine the left and right fittings (1) for signs of corrosion. Do this with a X10 magnifier and a source of bright light. NOTE: You can also use the straightedge of a ruler which will in dicate distortion caused by corrosion. Minor surface corrosion is permitted (Ref. ROM. Chap. 2 and 4). All other corrosion is not permitted and you must replace the defective fitting (Ref. APPENDIX D). (3) Remove minor surface corrosion (Ref. ROM. Ch ap. 2 and 4) from the given fittings (1). This step in only applicable if you have fo und permitted corrosion (Ref. Step 3.B.(2). (4) Visually examine the left and ri ght wing strut fittings (1) for signs of cracks. Do this with a X10 magnifier and a source of bright light. No cracks are permitted. If you find a crack, you must replace the fitting before next flight (Ref. APPENDIX D). (5) Examine the bearing (2). Make sure: • The bearing ball is free to rotate by hand. If necessary, you can use the attachment bolt as a lever. • The bearing ball and housing are not corroded. Remove superficial corrosion with the absorbent paper (Mat. No. P02-031) and the solvent (Mat. No. P01-010). No remaining corrosion is permitted. • The bearing housing is not loose in the wing strut fitting (1) • The bearing housing is aligned (as shown in Detail B) • The bearing ball and housing are not worn. No measurable gap is permitted. P07-007 Primer Paint
P08-018 Sealant For strut fittings 111.35.06.193, 111.35.06.194 and 111.35.06.195

P08-059 Adhesive P08-052 or P08-060 are suitable alternatives for P08-059 for this application. Material No. Description RemarksEFFECTIVITY: All 

# APPENDIX C Page 609 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
If necessary: • Remove the bearing (Ref. Para. 3.C.) • Examine the bearing and replace if necessary (Ref. Para. 3.C.) • Install the bearing (Ref. Para. 3.D.). NOTE: If you must replace the bearing, do not install the new bearing until you have done the Eddy current inspection (Ref. Para. 3.B.(6)). CAUTION: ONLY PERSONNEL THAT ARE TRAINE D AND APPROVED (BY THE LOCAL AIRWORTHINESS AUTHOR ITIES) CAN DO THIS PROCEDURE. (6) Do the non destructive inspection (Eddy Current). (a) For strut fittings 111.35.06.19 3, 111.35.06.194 and 111.35.06.195:
1 Use a non-metallic scraper and remove the bead of sealant (Mat. No. P08-018) from between the bush and the fitting (Ref. Sheet 2).
2 Use the absorbent paper (Mat. No. P 02-031) and the solvent (Mat. No. P01-010) to clean the area where the sealant was applied. (b) Calibrate the Eddy Current Instrument as follows: • Frequency 300 - 500 KHz • Probe selection Absolute • Refer to the manufacturer‘s handbook and calibrate the instrument for an 80% upscale deflection from the 0.5 mm EDM slot of the calibration standard. (c) Inspection of the fittings NOTE 1: Use a non-metallic object to guide the probe as close as possible to all the edges. NOTE 2: Specially inspect the areas shown on Figure 602, Detail B.
1 Do the procedure as given in the manufacturer‘s handbook.
2 Put the probe on the lower face of the left fitting.
3 Move the probe across the lower face. Make sure you get as close as possible to the outer edges of the fitting and as close as possible to the edges of the bearing (Ref. Detail B).
4 Put the probe on the upper face of the left fitting.
5 Move the probe across the upper face. Make sure you get as close as possible to the outer edges of the fitting and as close as possible to the edges of the bearing (Ref. Detail B).
6 Put the probe on the face of the edge of the left fitting.
7 Move the probe across the face of the edge. Make sure you get as close as possible to the outer edges (Ref. Detail C).EFFECTIVITY: All 

# APPENDIX C Page 610 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

8 If the bearing is removed: • Put the probe on the inner face of the bearing hole of the left fitting • Move the probe across the face and around the hole. Make sure you get as close as possible to the outer edges of the hole. 9 Do Para. 3.B.(6)(b)2thru 8again for the right fitting.
10 If you find a crack, you must replace the fitting before next flight (Ref. APPENDIX D). (d) Apply layers of Alodine 1200S (Mat. No. P07-001), the primer (Mat. No. P07-007) and the applicable paint on all bare me tal surfaces except the bearing housing interfaces. (e) For strut fittings 111.35.06.193, 111.35.06.194 and 111.35.06.195:
1 Use the absorbent paper (Mat. No. P02-031) and the solvent (Mat. No. P01-010) and clean the area between the bush and the fitting. where the sealant will be applied (Ref. Sheet 2).
2 Apply a bead of sealant (Mat. No. P08-018) between the bush and the fitting (Ref. Sheet 2). (7) Lubricate the bearing (2). (a) Remove the bearing ball:
1 Rotate the bearing ball out of the bearing housing by 90 degrees.
2 Turn it until it aligns with the cut-outs in the bearing housing.
3 Remove the bearing ball.
4 Use absorbent paper (Mat. No. P02-031) and the solvent (Mat. No. P01-010) to clean the bearing and the bearing housing.
5 Apply a layer of the grease (Mat. No. P 04-028) to the mating surfaces of the bearing and the bearing housing. (b) Install the bearing ball:
1 Align the bearing ball with the cut-outs in the bearing housing.
2 Install the bearing ball.
3 Turn the bearing by 90 degrees until it is flush in the bearing housing.EFFECTIVITY: All 

# APPENDIX C Page 611 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
C. Removal of the Bearing (Ref. Fig. 602) NOTE: This procedure is applicable if loose, dam aged, corroded, incorrectly aligned or worn bearings are found. CAUTION: DO NOT USE TOO MUCH HEAT TO RE MOVE THE BEARING. DO NOT EXCEED 120°C (224°F) FOR MORE THAN 15 MINUTES. (1) Use a hot air blower (for heat shrink sl eeves) and apply heat to loosen the adhesive between the bearing and the fitting or the bush. CAUTION: DO NOT USE TOO MUCH FORCE TOREMOVE THE BEARING. YOU CAN DAMAGE THE WING STRUT FITTING IF YOU USE TOO MUCH FORCE. (2) Use a press or applicable diameter drift to remove the bearing (2) from the bore in the fitting. If you cannot remove the bearing (2), replace the fitting (Ref. APPENDIX D). NOTE: The bearing (2) is removed from the top (wing side) of the wing strut fitting (1). (3) Use the solvent (Mat. No. P01-010) to remove the unwanted adhesive from the hole in the fitting or the bush. (4) Use the Scotch-Brite (Mat. No. P02-016) to polish the hole in the fitting or the bush. (5) Use the absorbent paper (Mat. No. P02-031) made moist with the solvent (Mat. No. P01- 010) and clean the hole in the fitting or the bush. (6) For wing strut-fittings P/N 6102.0041.00, 11 1.35.06.055, 111.35.0 6.056, 111.35.06.184, 111.35.06.185 and 111.35.06.186: (a) Do a visual inspection of the bearing hole in the fitting for wear. No wear is permitted. Replace wing strut fittings thatare worn before the next flight (Ref. APPENDIX D). (b) Apply a layer of alodine (Mat. No. P07-001) to the surface of the hole and facing. Install the replacement bearing (2) in the alodined hole in less than 72 hours. (7) For wing strut-fittings P/N 111.35.06.193, 111.35.06.194 and 111.35.06.195: Do a visual inspection of the bearing hole in the fitting for wear and corrosion. No corrosion is permitted. Remove all the corrosion and me asure the inner diameter of the bush. The maximum permitted diameter is 32.24 mm (1.27 in .). If the inner diameter of the bush is more than the maximum permitted diameter, replace the fitting (Ref. APPENDIX D). (8) Examine the bearing (2). Make sure: • The bearing ball is free to rotate by hand. If necessary, you can use the attachment bolt as a lever. • The bearing ball and housing are not corroded. Remove superficial corrosion with the absorbent paper (Mat. No. P02-031) and the solvent (Mat. No. P01-010). No remaining corrosion is permitted. • The bearing ball and housing are not worn. No measurable gap is permitted. (9) If necessary, discard the old bearing and use a new bearing.EFFECTIVITY: All 

# APPENDIX C Page 612 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
D. Installation of the Bearing (Ref. Fig. 602)
(1) Use the absorbent paper (Mat. No. P02-031) made moist with the solvent (Mat. No. P01- 010) and clean the bonding face of the bearing (2). (2) Use the Scotch-Brite (Mat. No. P02-016) to polish the bonding face of the bearing (2). (3) Use the absorbent paper (Mat. No. P02-031) made moist with the solvent (Mat. No. P01- 010) and clean the bonding face of the bearing (2). (4) Put the bearing (2) in position in the hole. Make sure it can be installed easily. Remove the bearing (2). NOTE: Put the bearing (2) in the hole as shown in Detail B, NEW ORIENTATION. (5) Mix the two parts of the adhesive (Mat. No. P08-059). (6) Apply a layer of the adhesive (Mat. No. P08-0 59) to the applicable su rfaces of the bearing (2) and the hole. Make sure there is sufficient adhesive to give a full bond when the parts are assembled. (7) Put the bearing (2) in position in the hole. Make sure the bearing (2) is correctly aligned (Ref. Detail B, NEW ORIENTATION) and push the bearing (2) firmly intothe hole to make sure it is tightly against the flange face. (8) Remove the unwanted adhesive (Mat. No. P08-059). CAUTION: DO NOT USE TOO MUCH HEAT. DO NO T EXCEED 120°C (224°F) FOR MORE THAN 15 MINUTES. (9) Let the adhesive (Mat. No. P08-059) cure for 5 to 7 days at room temperature or 2 hours at 65 +5°C (136 +8°F). E. Close up (1) Remove all tools and materials. Makesure that the work areas are clean. (2) Install the wing struts.EFFECTIVITY: All 

# APPENDIX C Page 613 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

Wing Strut Fitting - Inspection Figure 602, Sheet 1 of 26693 

# A

B 

# A

1

CORRECT BEARING ALIGNMENT/POSITION 1 MOVE PROBE AS CLOSE AS POSSIBLE TO THE OUTER AND INNER EDGES AS INDICATED ON BOTH SIDES OF THE FITTING



# B 2 SPECIALLY INSPECT THESE AREAS OF THE UPPER AND LOWER SURFACES 

# B

C 

# C 1 NEW ORIENTATION OLD ORIENTATION



## D DEFFECTIVITY: All 

# APPENDIX C Page 614 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

Wing Strut Fitting - Inspection Figure 602, Sheet 2 of 26694 SECTION



## D-D

SEALANT BEARING

BUSH SEALANTEFFECTIVITY: All 

# APPENDIX D Page 401 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

APPENDIX D WING STRUT FITTING - REMOVAL/INSTALLATION

1. General This procedure is only applicable if you found cra cks during the inspection, or cannot remove the bearing (Ref. APPENDIX C). Th e procedure is given fo r replacement of the le ft fitting but is also applicable for the right fitting. NOTE: Not all aircraft have the applicable openings for internal access to the fittings. This procedure gives the data and instructions to ma ke new access panels if necessary. 2. Job Set Up Information A. Operator Supplied Parts (1) The parts listed below are necessary for the replacement of one wing strut fitting (left or right). Operators must order the parts from PILATUS as necessary: New Part No. Description Old Part No. Qty Fig. Item 111.35.06.057 111.35.06.191 111.35.06.192 Bolt (8.2 mm Dia 1st Oversize) Bolt (8.4 mm Dia 2nd Oversize) Bolt (8.6 mm Dia 3rd Oversize) 932.53.47.286 932.53.46.436 111.35.06.057 111.35.06.191 5 403 1

111.35.06.193 Left Wing Strut-Fitting 6102.0041.00 111.35.06.055 111.35.06.184 111.35.06.185 111.35.06.193 111.35.06.195 1 403 4

111.35.06.194 Right Wing Strut-Fitting 6102.0041.00 111.35.06.056 111.35.06.184 111.35.06.186 111.35.06.194 111.35.06.195 1 N/A N/A

938.07.31.124 Nut 938.07.34.104 938.07.65.105 938.07.31.108 938.07.31.124 5 403 3

938.78.11.206 Washer 938.71.51.108 938.78.11.106 938.78.11.206 5 403 2EFFECTIVITY: All 

# APPENDIX D Page 402 Feb 28/10 

# PC-6 MAINTENANCE MANUAL (2) The parts listed below are necessary if the aircraft has no access panels:

B. Tools and Equipment

C. Consumable Mate rials (APPENDIX E): Part No. Description Qty each Wing 916.16.35.110 Aluminium Alloy Sheet Size 224 x 84 mm (8.8 x 3.3 in.) 939.19.86.102 Rivet 34 916.16.35.110

or 6102.0125.02 Aluminium Alloy Sheet

Panel Size 155 x 155 mm (6.1 x 6.1 in.)
1

Part No. Description Qty Remarks Drill - 8,0 mm A/R For 1st Oversize Reamer - 8,1 mm A/R Reamer - 8,2 mm A/R Drill - 8,2 mm A/R For 2nd Oversize Reamer - 8,3 mm A/R Reamer - 8,4 mm A/R Drill - 8,4 mm A/R For 3rd Oversize Reamer - 8,5 mm A/R Reamer - 8,6 mm A/R

Mat. No. Description Qty Remarks P01-010 Solvent A/R Or Approved Alternative P02-031 Absorbent Paper A/R P04-012 Corrosion Preventative A/R P07-001 Alodine 1200S A/R P07-007 Epoxy Primer A/R Required for a new access panel P10-013 Corrosion Preventative A/REFFECTIVITY: All 

# APPENDIX D Page 403 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

3. Procedures WARNING: OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS WHEN YOU USE THE CONSUMABLE MATERIALS. CAUTION: OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU APPLY THE CONSUMABLE MATERIALS. A. Preparation (1) Remove the left and right wing struts. B. Fittings - Replacement (Ref. Fig. 401 and 402) (1) Remove the access panels LB10 and/or RB9. Keep two of the screws (P/N 935.13.16.018) from the access panel. Discard the unwanted panel and screws. (2) Make an access opening in the skin, forward ofthe fitting (Ref. Fig. 401). This step is only applicable if there is no in ternal access to the forward flange of the fitting assembly. NOTE: The new opening is at the same location (and is the same width) as the circular (inspection) opening LB10 (left) or RB9 (right). The forward and aft anchor nuts for the access covers LB10 or RB9 will al so be used for the cover of the new opening. (a) Make marks to show the contours of the opening on the skin. Do this at the location shown and to the given dimensions (192 x 52 mm (7.6 x 2.0 in.) with 26 mm (1.0 in.) radii at each end). (b) Cut the opening in the skin to the contour marks with the applicable cutting tools. Make sure that there are no sharp edges. Do not remove the forward and aft anchor nuts for the access covers LB10 or RB9. (3) If necessary make a new access openi ng in the skin aft of the fitting. (a) Make marks to show an intersection of center lines and the contours of a circular opening 120 mm (4.7 in.) in diameter. Do this on the skin at the location shown. (b) Cut the opening in the skin to the contour marks with the applicable cutting tools. Make sure that there are no sharp edges. (4) Remove the defective fitting(s) (Ref. Fig. 402). (a) Remove the nuts (3), the washers (2) and the bolts (1). Keep two of the bolts (1), the washers (2) and the nuts (3). (b) Disassemble and remove the fitting (4) from the wing structure. (5) Make the bolt holes for the new fitting (Ref. Fig. 402). NOTE: The rear flange of the new fitting containsfive 8.0 mm diameter holes (A thru E). These holes are pilot, positioning and alignment holes for the new fitting which align with the holes of the wing spar.EFFECTIVITY: All 

# APPENDIX D Page 404 Feb 28/10 

# PC-6 MAINTENANCE MANUAL The forward flange of the new fitting contai ns only one hole (F). This hole serves as an alignment hole. The remaining four holes (G, H J and K) in the forward flange are drilled during insta llation of the new fitting. All holes in the new fitting are reamed to the final diameter together with the wing spar holes for the tight fit bolt installation. All bolts must have the same diameter. If the fitting was replaced before, the diameter of the existing holes in the new fitting must be increased to match the wing spar hole diameter first. (a) Measure the diameter of one removed bolt (1). (b) Determine the drill and re amer sizes necessary (Ref. Table 1) for the diameter measured in Step 3.B.(5)(a).

(c) If the measured diameter from Step 3.B. (5)(a) is larger than 8.0 mm, use the drill determined in Step 3.B.(5)(b) to increa se the fitting holes (A) thru (E) and (F). (d) Put the new fitting (4) in position and temporarily install one of the used bolts (1), one of the used washers (2) and one of the used nuts (3) thru the holes (A) and (F). Tighten the nut (3). (e) Install the other used bolt (1) thru the rear flange hole (E) into wing spar hole to align the fitting (4). (f) Use the fitting rear flange hole (D) as p ilot hole and drill hole (J) in forward fitting flange. Use the drill determin ed in Step 3.B.(5 )(b). Do not damage the wing spar holes. (g) Remove the bolt (1), installed in Step 3.B. (5)(e), and install the bolt (1), the other used washer (2) and the other used nut (3) thru the holes (D) and (J). Tighten the nut (3). (h) Use the fitting rear flange holes (B), (C) and (E) as pilot holes and drill the holes (G), (H) and (K) in the fitting forward flange. Do not damage the wing spar holes. (i) Increase the diameter of th e holes (B-G), (C-H) and (E-K) to the next oversize. Use the two reamers determined in Step 3.B.(5)(b)

. (j) Temporarily install the new oversized bolts (1), the new washers (2) and the new nuts (3) at the holes (B-G) and (E-K), and tighten nuts.

Old Bolt Dia Diameter of Drill Required for New Fitting Diameter of Reamer Required P/N of New Bolt Required 8.0 mm 8.0 mm 8.1 and 8.2 mm 111.35.06.057 (1st Oversize) 8.2 mm 8.2 mm 8.3 and 8.4 mm 111.35.06.191 (2nd Oversize) 8.4 mm 8.4 mm 8.5 and 8.6 mm 111.35.06.192(3rd and Maximum Oversize) Table 1: Drill and Reamer sizesEFFECTIVITY: All 

# APPENDIX D Page 405 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
(k) Remove the used bolts (1), the used washer (2) and the used nut (3) installed in Step 3.B.(5)(d) and (g). (l) Discard all five used bolts (1), washers (2) and nuts (3). (m) Increase the diameter of the holes (A-F) and (D-J) to the next oversize. Use the two reamers determined in Step 3.B.(5)(b)

. (n) Remove the new bolts (1), the new washers (2) and the new nuts (3) installed in Step 3.B.(5)(j) and remove the new fitting (4) from the wing spar. (o) If one or more of the holes, reamed in St ep 3.B.(5)(i) and (m), in the new fitting (4) and the wing spar are not circular, dete rmine the next oversize diameter reamers (Ref. Table 1) and: 1 Temporarily install the fitting (4). Use the bolts (1), the washers (2) and the nuts (3) used in Step 3.B.(5)(j) to attach the fitting (4) in holes (A-F) and (E-K). 2 Increase the diameter of the holes (B-G), (C-H) and (D-J) to the next oversize. Use the two reamers determined in Step 3.B.(5)(o)

. 3 Temporarily install the next oversize bolts (1), the washers (2) and the nuts (3) at the holes (B-G) and (D-J), and tighten nuts. 4 Remove the bolts (1), the washers (2) and the nuts (3) installed in Step 3.B.(5)(o)1

. 5 Increase the diameter of the holes (A-F) and (E-K) to the next oversize. Use the two reamers determined in Step 3.B.(5)(o)

. 6 Remove the bolts (1), the washer (2) and the nuts (3) installed in Step 3.B.(5)(o)3and remove the new fitting (4) from the wing spar. (p) If one or more of the holes, reamed in Step 3.B.(5)(o), in the new fitting (4) and the wing spar are not circular, determine the next oversize diameter reamers (Ref. Table 1) and repeat Step 3.B.(5)(o). If you cann ot get the holes circular and the holes are at the maximum of 8.6 mm, contact Pilatus. (q) Deburr the holes (A thru H, J and K) in the new fitting and wing spar. (r) Apply layers of Alodine 1200S (Material No.P07-001). Do this on the bare metal surfaces of the holes in the wing structure and the fitting (4). (6) Install the replacement fitting. (a) Apply layers of the corrosion preventative (Material No. P04-012) on the faying surfaces of new bolts (1), the washers (2) and the nuts (3). (b) Put the fitting (4) in position in the wing and align the holes. (c) Install the new bolts (1), the washers (2) and the nuts (3). Make sure that the heads of the bolts point forward. (d) Torque the nuts (3) to between 18 and 24 Nm (159.3 and 212.4 lbf in.).EFFECTIVITY: All 

# APPENDIX D Page 406 Feb 28/10 

# PC-6 MAINTENANCE MANUAL (e) Remove the unwanted corrosion preven tative (Material No. P04-012) with the solvent (Material No. P01-010). (f) Apply layers of the corrosion preventative(Material No. P10-013) on the bolts (1), the washers (2), the nuts (3) and the fitting (4). (7) Make the cover for the forward access opening (Ref. Fig. 401). (a) Make marks to show the center line and contours of the cover on the piece of aluminium alloy sheet (P/N 916.16.35.110). Do this to the given dimensions (224 x 84 mm (8.8 x 3.3 in.) with 42 mm (1.7 in.) radii at each end). (b) Cut the aluminium alloy sheet (P/N 916 .16.35.110) at the contour marks with the applicable cutting tools to make the cover (1). Make sure that there are no sharp edges. (c) Make marks to show the locations of the rivet and screw holes around the edges of the cover (1). Do this at the pitch dimensions shown. (d) Make the rivet holes at the applicable marks on the cover (1) with a 3,3 mm (0.13 in.) diameter drill. Deburr the holes. (e) Make the screw holes at the applicab le marks on the cover (1) with a 4,0 mm (0.16 in.) diameter drill. Deburr the holes. (f) Apply layers of the Alodine 1200S (Mater ial No. P07-001) and the primer (Material No. P07-007). Do this on the bare metal surfaces of the cover (1) and the edges of the opening in the skin. (8) Make the rivet holes for the cover for the forward access opening in the skin. (a) Put the cover (1) in position on the skin, align the center lines and hold. (b) Make the rivet and screw holes in the skin with a 3,3 mm (0.13 in.) and 4,0 mm (0.16 in.) diameter drill. (c) Remove the cover and deburr the rivet holes. (d) Apply layers of the Alodine 1200S (Material No. P07-001) and the primer (Material No. P07-007). Do this on the bare metal surfaces of the cover (1) and the edges of the opening in the skin. (9) Install the cover for the forward access opening. (a) Apply layers of the sealant (Material No. P08-057) on the faying surfaces of the cover (1) and the skin. (b) Put the cover (1) in position on the skin and hold with gripper pins. (c) Install the rivets (P/N 939.19.86.102) (R ef. ROM. Chap. 2). Apply a layer of the sealant (Material No. P08-057) on each rivet before you install it. (d) Remove the unwanted sealant (Material No. P08-057) with the solvent (Material No. P01-010). (e) Install the two screws (P/N 935.13.16 .018) that you keptat Para. 3.B.(1).EFFECTIVITY: All 

# APPENDIX D Page 407 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
(f) Apply layers of the primer (Material No. P07-007) and the applicable paint on the rivet and screw heads and the exterior surface of the cover (1). (10) Make the new cover for the aft access opening or use the procured panel (P/N 6102.0125.02). NOTE: The steps that follow are only necessary if you do not use the procured panel (P/N 6102.0125.02). (a) Make marks to show an intersection of center lines and the contours of a 155 mm (6.1 in.) diameter circular cover. Do this on a piece of the aluminium alloy sheet (P/N 916.16.35.110). (b) Cut the aluminium alloy sheet (P/N 916. 16.35.110) at the contour marks with the applicable cutting tools to make the cover (2). Make sure that there are no sharp edges. (c) Make marks to show the locations of the 16 rivet holes around the edges of the cover (2). Make sure that the holes are of equal pitch, at a diameter of 135 mm (5.32 in.). (d) Make pilot holes in the cover (2). Do this at the ma rks for the rivet holes with a 2,4 mm (0.1 in.) diameterdrill. deburr the holes. (11) Make the rivet holes for the cover for the aft access opening. (a) Put the cover (2) in position on the skin, align the center lines and hold. (b) Make the rivet holes in the cover (2) and the skin. Do this through the pilot holes with a 3,3 mm (0.13 in.) drill. (c) Remove the cover (2) and deburr the rivet holes. (d) Apply layers of the Alodine 1200S (Material No. P07-001) and the primer (Material No. P07-007). Do this on th e bare metal surfaces of th e cover (2) and the edges of the opening in the skin. (12) Install the cover for the aft access opening cover. (a) Apply layers of the sealant (Material No . P08-057) on the faying surfaces of the cover (2) and the skin. (b) Put the cover (2) in position the skin and hold with gripper pins. (c) Install the rivets (P/N 939.19.86.102) (Ref. ROM. Chap. 2). Apply a layer of the sealant (Material No. P08-057) on each rivet before you install it. (d) Remove the unwanted sealant (Material No . P08-057) with the solvent (Material No. P01-010). (e) Apply layers of the primer (Material No. P07-007) and the applicable paint on the rivet heads and the exterior surface of the cover (2). (13) If necessary do Steps (1) thru (12) again to make the access openings and replace the fitting (4) in the remaining wing.EFFECTIVITY: All 

# APPENDIX D Page 408 Feb 28/10 

# PC-6 MAINTENANCE MANUAL C. Close up (1) Remove all tools and materials. Makesure that the work areas are clean. (2) Install the access panels LB10 and RB9 as applicable. (3) Install the wing struts.EFFECTIVITY: All 

# APPENDIX D Page 409 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

Access Openings and Covers - Insta llation (Left Shown, Right Similar) Figure 401(Sheet 1 of 2)SB1568 

# A 

# A

LEFTSIDE SHOWN RIGHT OPPOSITE

1 45° 45° 45° 45° =

45° 45° 45° 45°

R

2

6

mm (1.02 i n.) R 3

5 m

m ( 1

. 3

8 i n .)

OPENING FOR LB10/RB9 DO NOT REMOVE

NUT PLATES

43 mm (1.69 in.) 97 mm (3.82 in.) 224 mm (8.82 in.)

84 mm (3.3 in.) SCREW HOLE R 4

2 m

m ( 1

. 6

5 i

n .) 

# BFWD INBOARD 43 mm (1.69 in.) 97 mm (3.82 in.)

=== ==

== = = = = 

# B

CEFFECTIVITY: All 

# APPENDIX D Page 410 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

Access Openings and Covers - Installation (Left Shown, Right Similar) Figure 401(Sheet 2 of 2)SB1640FWD 

# C

Ø 155 mm

(6.10 in.) R

6 7

.5

m

m ( 2

.6

6

i n

. ) R 6

0 m

m ( 2

.3

6

i n

. )

= = =

=

2

R

6 7.

5m m ( 2 .

6 6

i n . )EFFECTIVITY: All 

# APPENDIX D Page 411 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

Fitting - Replacement (Left Shown, Right Similar) Figure 403SB1569 

# A



# A

1

2 3

4 SHOWN WITHOUT SKIN FOR CLARITY

A B D E C G F

H J KEFFECTIVITY: All 

# APPENDIX D Page 412 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

INTENTIONALLY BLANKEFFECTIVITY: All 

# APPENDIX E Page 1 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

APPENDIX E CONSUMABLE MATERIALS LIST

1. General This section gives the data for the consumable materials which are recommended for the maintenance of all Pilatus aircraft types. The materials are put into groups to show the type of material. The groups used in this section are: P01 - Processing and Cleaning P07 - Paints, Varnishes and Thinners P02 - Processing Sundries P08 - Bondin g, Adhesives, Fillers and Sealers P03 - Welding and Metal P09 - General Stores P04 - Jointing Compounds and Greases P10 - Oils and Fluids P05 - Polishing P11 - Fuels P06 - Inspecting P12 - Packing Each material is also given an item number which comes after the group number. The groups of materials are shown in tables, each table has these columns: • Material No. • Material Name • Notes • Pilatus Part No. • Alternative Product / Specification. The Material No., Material Name, Notes and Pilatus Part No. columns give the products recommended by Pilatus. The Alternative Product / Specification column is to show alternative products or the specifications for alternative products, when known. The section gives the consumable materials necessary for each procedure for this aircraft. You can use alternative materials, but if no alternative products are given in the tables then you must only use the recommended product. Material Safety Data Sheets (MSDS) contain data ab out the trade name, safety hazards, reactions, spill and leak procedures, special protection data, spec ial precautions, transport and labels are available from the manufacturer of the products. Before you use any consumable materials, read all MSDS. Changes to items in the tables are shown by revision bars. The Page Date will identify the latest issue.EFFECTIVITY: All 

# APPENDIX E Page 2 Feb 28/10 

# PC-6 MAINTENANCE MANUAL
2. Consumable Materials List

Material

No. Material Name Notes Pilatus Part No. Alternative Product / Specification P01 - Processing and Cleaning P01-001 Alkaline cleaner, Turco 5884 910.21.31.008 MIL-PRF-85704 Almon AL-333 Ardrox 624 B & B 3100 Carbitol CLIX Magnus 1214 Rivenaes R-MCS Rivenaes R-MC G21 Turco 5884 P01-002 Triethanolamine P01-003 Emulsifier, Witco HC-59B or P10-59B P01-004 Superseded by P01-015 P01-005 Soap solution, Aero-Klene No. 299 910.21.21.120
P01-006 Cleaner Refer to P05-003 P01-007 Non leaded gasoline, Petroleum 908.62.11.101 MIL-G-5572F, ASTM-D910 P01-008 White spirit, EXXSOL D40 908.63.81.101 P01-009 Solvent, Methanol (Methyl- alcohol) 908.44.52.003 AMS 3004, O-M-232K, PWC011-010 P01-010 Solvent, Methyl-Ethyl-Ketone (MEK) 910.21.61.015 ASTM D740, MIL-M-13999, O-C-265 P01-011 Solvent alcohol, Isopropyl (Isoproponol) 908.44.52.005 TT-I-735 GRADE A, PWC011-014 P01-012 Liquid detergent, Teepol MIL-D-16791 P01-013 Solvent, Toluene 910.33.90.270 TT-T-548 P01-014 Cleaner, detergent, Turboclean 2 MIL-PRF-85704 P01-015 Ethanol (Ethyl alcohol) 908.44.52.006 AMS3002, MIL-A-6091, O-E-760 type III,PWC011-009 P01-016 Acetone 910.21.21.001 O-A-51, ASTM D329-95 P01-017 Electrical contact protector, Progold G5S-6 908.24.32.024 P01-018 Superseded by P01-020 P01-019 Cleaning fluid, Kontakt 60 908.18.12.094 P01-020 Electrical contact enhancer, Stabilant 22 908.24.32.026 P01-021 Corrosion remover Phos-Klene 1 Super 908.40.32.155 P01-022 Corrosion remover Turco 4409 908.40.32.154 P01-023 Paint remover Turco 6776 LO WOD 910.10.00.003 P01-024 Heavy duty cleaner Ardrox 1900C Do not use on canopies - P01-025 Heavy duty cleaner Zip-Chem Calla 800 Do not use on canopies - MIL-PRF-87937D Type II
P01-026 Disinfectant Virkon S, Antec International -EFFECTIVITY: All 

# APPENDIX E Page 3 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P02 - Processing Sundries P02-001 Lockwire (standard), diameter 0,8 mm (0.032 in.) 919.01.11.104 NASM20995 (was MS20995C-32) P02-002 Aluminum wool 904.48.83.103 P02-003 Cleaning cloth Superseded by P02-031 904.49.73.004 P02-004 Chamois leather 904.49.74.204 P02-005 Sponge 904.49.75.303 P02-006 Lockwire (heat resistant), diameter 0,6 mm (0.025 in.) 919.01.11.203 MS 9226-03 P02-007 Lockwire (standard), diameter 0,6 mm (0.025 in.) 919.01.11.103 NASM20995 (was MS20995C-25) P02-008 Lockwire (heat resistant), diameter 1,0 mm (0.04 in.) 919.01.11.107 MS 9226-05
P02-009 Abrasive cloth, Grade 120 1913 Siawat FC 904.47.22.210 P02-010 Abrasive cloth, Grade 180 1913 Siawat FC 904.47.22.213 P02-011 Abrasive cloth, Grade 240 1913 Siawat FC 904.47.22.216 P02-012 Abrasive cloth, Grade 280 1913 Siawat FC 904.47.22.218 P02-013 Abrasive cloth, Grade 320 1913 Siawat FC 904.47.22.220 P02-014 Abrasive cloth, Grade 400 1913 Siawat FC 904.47.22.222 P02-015 Lockwire (heat resistant), diameter 0,8 mm (0.032 in.) 919.01.11.105 MS 9226-04 P02-016 Scotch-Brite, Very fine grade 904.48.85.107 P02-017 Lockwire (standard), diameter 1,0 mm (0.04 in.) 919.01.11.106 NASM20995 (was MS20995C-41) P02-018 Abrasive cloth, Grade 80 904.47.23.176 P02-019 Cloth, cotton 904.49.71.203 P02-020 Scotch-Brite, Regular Grade P02-021 Lockwire (brass), diameter 0,5 mm (0.02 in.) 919.01.11.117 P02-022 Lockwire (special), diameter 0,4 mm (0.016 in.) 919.01.11.101 MS 9226-01 P02-023 Superseded by P02-024 P02-024 Abrasive cloth, Grade 600 1913 Siawat FC 904.47.22.223 P02-025 Cotton wadding Pure cotton wool 904.49.73.006 P02-026 Abrasive cloth, Grade 1500 907.71.22.703 P02-027 Abrasive cloth, Grade 1800 907.71.22.704 P02-028 Abrasive cloth, Grade 2400 907.71.22.705 P02-029 Abrasive cloth, Grade 3200 907.71.22.706 P02-030 Abrasive cloth, Grade 4000 907.71.22.707 P02-031 Absorbent paper 904.49.73.004 P02-032 Abrasive paper 3M Trizact P3000 D32 MM 907.71.22.791 P02-033 Lamb wool pad Polishing pad 904.49.76.362 P02-034 Polish pad Mirror polish - black 904.49.76.341 P02-035 Polish pad small Finesse it Buff pad 904.49.76.321 P02-036 Polish hood Off Polish Hood of Micro Fiber white 904.49.76.361 P02-037 Micro Fiber cloth Micro Power Cloth - Terrycloth 904.49.76.381 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 4 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P02-038 Cleaning Modelling Material Magic Smooth and Clean, yellow 904.49.76.121 P02-039 All Purpose Cleaner All Purpose Cleaner PLUS Concentrate D-12 904.49.76.141 P02-040 Lockwire (heat resistant), diameter 0,5 mm (0.02 in.) Inconel 919.01.11.102 MS9226-02 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 5 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P03 - Welding and Metal P03-001 Welding Rod, Filler rod 347 Diameter 0,8 mm (0.032 in.) 907.83.32.501 AMS 5680 Diameter 1,0 mm (0.039 in.) 907.83.32.502 Diameter 1,14 mm (0.045 in.) 907.83.32.503 Diameter 1,6 mm (0.064 in.) 907.83.32.505 P03-002 Welding Rod, Filler rod (1.7734.2) Diameter 1,5 mm (0.06 in.) 907.83.31.911 Diameter 2,0 mm (0.08 in.) 907.83.31.912 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 6 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P04 - Jointing Compounds and Greases P04-001 Grease, Aeroshell Grease 5 Do not use Superseded by P04-031 908.21.52.003 MIL-PRF-81322F, G-395, DOD-G-24508 P04-002 Grease, Aeroshell Grease 7 908.20.02.063 MIL-PRF-23827 Type II P04-003 Grease, Aeroshell Grease 22 908.20.02.064 MIL-PRF-81322F G-395, DOD-G-24508 P04-004 Grease, Plastilube 3 908.25.71.501 PWC04-004 P04-005 Superseded by P04-030 P04-006 Grease, Aeroshell Grease 17 Superseded by P04-037 908.25.71.803 MIL-G-21164, G-353 P04-007 Superseded by P04-030 P04-008 Wellseal Superseded by P04-017 907.13.11.923 P04-009 Anti-seize compound 908.25.71.802 MIL-PRF-83483 P04-010 Anti-seize compound, Aeroshell Compound 08 908.20.02.102 SAE-AMS2518, Def Stan 80-80 grade ZX-1 P04-011 Spray lubr icant, Molyslip ADF301 908.10.09.002 P04-012 Corrosion preventative, Mastinox 6856H 910.31.20.040 MIL-PRF-8116 Mastinox 6856K P04-013 Superseded by P04-003 P04-014 Heat conducting paste, V5004 907.13.11.998 P04-015 Anti-seize compound, Molykote 1000 908.24.02.004
P04-016 Grease, Aeroshell Grease 6 908.25.71.111 MIL-G-24139, G-382, G-450 P04-017 Jointing compound, Hylomar SQ 32M Purchased as Hylomar M 907.13.11.903 P04-018 Silicon grease, MS4 908.20.02.093 SAE AS8660, S-736 (was MIL-S-8660) P04-019 Not used now P04-020 Superseded by P04-004 P04-021 Superseded by P04-029 P04-022 Grease, Molykote G Rapid Plus Nato-No.9150-0-200-0097 P04-023 Propeller grease, Gulfflex 2 908.25.71.101 P04-024 Grease, MolySlip liquid grease 908.10.09.013 P04-025 Compound, anti-seize, Never Seez PWC06-009 P04-026 Compound, anti-seize, Silver Goop PWC06-023 P04-027 Grease, Mobil Special 908.21.42.110 P04-028 Grease, Aeroshell Grease 33 908.20.02.065 MIL-PRF-23827 Type I Def Stan 91-53 Nato G-354 Mobil Grease 27 P04-029 Paste, installation, Duotempi PMY45 60 g tube 600 g tin 908.24.02.001 908.24.02.002 P04-030 Grease, Vaselinum, 26-7500-1 908.20.02.101 VV-236A, Def Stan 91-38, Grade PX-7, MIL-C-11796 P04-031 Grease, MAG SHC 100 908.20.02.066 P04-032 Grease, Isoflex Topas NCA 51 908.21.42.115 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 7 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P04-033 Oxygen paste, Oxygenoex FF250 Superseded by P04-038 908.25.71.700 908.25.71.701 MIL-T-5542
P04-034 Lubricant ULTRA-PLUS EXTRA 908.40.01.002 P04-035 Anti-seize compound, Molykote P-37 908.24.02.003 P04-036 Heat conducting paste, Dow Corning 340 Supersedes P04-014 907.13.11.997
P04-037 Grease, Aeroshell Grease 33MS Supersedes P04-006 908.25.71.804 MIL-G-21164, G-353 P04-038 Grease, Krytox 240AC Supersedes P04-033 908.25.71.702 MIL-PRF-27617 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 8 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P05 - Polishing P05-001 Not used now See Note P05-002 Plastic / Acrylic Cleaner (paste) MGH No. 17 908.64.22.203
P05-003 Plastic / Acrylic Cleaner (liquid), Aero-Klene 910.21.21.120 MIL-D-16791 Type I
Plastic / Acrylic Cleaner (liquid), MGH No. 18 908.64.22.202 Novus No. 1
P05-004 Plastic / Acrylic Polish (fine), Altuglas No. 2 907.71.22.702
P05-005 Plastic / Acrylic Polish (heavy), Altuglas No. 1 907.71.22.701 Novus No. 3
P05-006 Plastic / Acrylic Polish (Medium), MGH No. 10 908.64.22.201 Novus No. 2 P05-007 Grinding polish Diamant Grinding polish M-85 904.49.76.261 P05-008 Polish Cleaner Cleaning and Mirror Polish M-83 904.49.76.241 P05-009 Sealing Polymer Sealing M-20 904.49.76.221 P05-010 Fine Cleaner Last Touch Detailing D-155 904.49.76.165 NOTE: The procedure that used the P05-001 is deleted. Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 9 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P06 - Inspecting P06-001 Penetrant Aerosol 908.68.12.105 AMS-2644, ASTM-E1417, MIL-STD-2132, ASTM-E-165 P06-002 Remover Aerosol 908.68.12.106 AMS-2644, ASTM-E1417, MIL-STD-2132, ASTM-E-165 P06-003 Developer Aerosol 908.68.12.107 AMS-2644, ASTM-E1417, MIL-STD-2132, ASTM-E-165 P06-004 Leak detector spray 907.12.11.004 MIL-PRF-25567 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 10 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P07 - Paints, Varnishes and Thinners P07-001 Alodine 1200S CCC Solution 908.40.32.251 P07-002 Zinc chromate primer Superseded by P07-003 P07-003 Epoxy primer Superseded by P07-007 P07-004 Primer 8010-0-100-012P P07-005 Thinner 8010-0-100-0143 P07-006 Paint, cockpit, grey 8010-0-100-0144 P07-007 Epoxy primer, yellow, Akzo-Nobel Primer 910.02.05.031
Hardener 910.02.05.032 Thinners 910.09.00.101 P07-008 Paint, marking, red, Enictol 234183-125 Enictol 910.33.82.150
P07-009 Paint, anti-erosion, Celoflex 95 Paint 910.04.04.504 Hardener 910.04.04.505 Thinners 910.09.00.057 P07-010 Paint, black 910.07.05.102 Paint, white 910.07.05.103 Paint, red 910.07.05.104 Paint, hardener 910.07.05.101 Paint, thinners 910.09.00.508 Paint, retarder 910.09.00.904 P07-011 Deleted Refer to P07-010 910.07.05.102 P07-012 Deleted Refer to P07-010 910.07.05.103 P07-013 Deleted Refer to P07-010 910.07.05.104 P07-014 Deleted Refer to P07-010 910.09.00.508 P07-015 Deleted Refer to P07-010 910.09.00.904 P07-016 Primer, barrier white 37045 Primer 910.02.05.030 Hardener 910.04.04.316 P07-017 Paint, white Aviox finish 90075 Paint 910.04.04.515 Hardener 910.04.04.502 P07-018 Paint, snow-white anti-chafe, Celogliss 5456 / 1238 Paint 910.07.09.012 Paint, grey anti-chafe, Celogliss 5456 / 1238 Paint 910.07.09.015 Hardener for Celogliss 5456 910.07.09.014 Thinners for Celogliss 5456 910.07.09.013 P07-019 Paint, top coat, Nuvovern ACR Enamel, Aluminum Paint 910.04.04.022
PUR Hardener 910.04.04.050 Thinners 910.09.00.005 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 11 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P07-020 Paint, white Aerodur finish, C21 / 100 UVR 910.04.04.320 Paint, black Aerodur finish, C21/100 UVR 910.04.04.416 Paint, red Aerodur finish, C21/100 UVR 910.04.04.317 Paint, hardener 910.04.04.316 Paint, thinners or 910.09.00.101 Paint, thinners 910.09.00.102 P07-021 Alodine 1132 Touch-N-Prep Pen 908.40.32.252 P07-022 Snow white, ECL-G-1678 Eclipse HS PUR topcoat paint 910.04.04.517 Snow white 702112 Light grey, ECL-G-11018 Eclipse HS PUR topcoat paint 910.04.04.521 RAL 7035 Gray, ECL-G-11017 Eclipse HS PUR topcoat paint 910.04.04.522 RAL 7040 Black, ECL-G-92 Eclipse HS PUR topcoat paint 910.04.04.523 RAL 9005 Blue, ECL-G-2843 Eclipse HS PUR topcoat paint 910.04.04.524 RAL 5017 White, ECL-G-1681 Eclipse HS PUR topcoat paint 910.04.04.525 RAL 9003 Traffic red, ECL-G-3637 Eclipse HS PUR topcoat paint 910.04.04.531 RAL 3020 White, ECL-G-1670 Eclipse HS PUR topcoat paint 910.04.04.532 RAL 9010 White, ECL-G-10 BAC 7067 Eclipse HS PUR topcoat paint 910.04.04.534 FSB 17925 Red 715045, ECL-G-3701 Eclipse HS PUR topcoat paint 910.04.04.535 FSB 11350 UK, ECL-G-3818 Eclipse HS PUR topcoat paint 910.04.04.538 CM410A5, orange ECL-G-6663 Eclipse HS PUR topcoat paint 910.04.04.540 RAL 2009, orange 71740 Hardener 910.04.04.536 Activator 910.04.04.529 P07-023 ECL-G-7 Eclipse HS PUR clearcoat paint 910.04.04.537 Hardener 910.04.04.536 Activator 910.04.04.529 P07-024 Varnish, RD 1177 Blue 8010-0-100-0143 910.42.72.701. P07-025 Spray Filler (AKZO Autocryl Multi-use HS) Base Hardener (Autocryl P25) Thinner (Sikkens Plus Reducer Fast) 910.08.06.010 910.08.06.013 917.00.40.019 P07-026 Wash Primer (ANAC Metaflex FCR) Base Hardener (Metaflex FCR) Thinner (C25/90S) 910.02.09.005 910.02.09.006 910.09.00.101 P07-027 Conductive Coating (Pyroflex 7 D 713. Base Hardener (0651) Thinner (C25/90S) 910.04.04.334 910.04.04.335 910.09.00.101 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 12 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P08 - Bonding, Adhesives, Fillers and Sealers P08-001 Caulking Putty 3M body caulking 907.13.13.092 P08-002 Silicon Sealant, Loctite 5368 910.42.12.126 P08-003 Sealant Superseded by P08-018 P08-004 Sealant Superseded by P08-020 P08-005 Sealant, Pro-seal 890 A2 907.13.13.022 P08-006 Coating, Laminar X-500 Superseded by P08-024 P08-007 Coating, PR 1560 Superseded by P08-024 P08-008 Adhesive BALCO-ME 910.42.22.372 P08-009 Adhesive 3M Fastbond 10 910.42.22.037 MIL-A-21366, A-A-1936 P08-010 Thinners 3M Fastbond 10 910.42.22.038 P08-011 Contact adhesive Superseded by P08-009 P08-012 Thinner Superseded by P08-010 P08-013 Sealant Superseded by P08-018 P08-014 Sealant Superseded by P08-056 P08-015 Adhesive, Acrylic, Tensol No.6 910.42.22.393 P08-016 Edge sealer Superseded by P08-041 P08-017 Adhesive, Loctite Grade 241 Adhesive, Loctite Grade 243 Adhesive, Loctite Grade 641 moved to P08-065 910.42.12.123 910.42.12.128 P08-018 Sealant, PR 1422B-2 1,0 liter 907.10.11.232 DMS 2082 P08-019 Sealant, RTV 123 907.13.11.931 P08-020 Sealant, PR 1422A-2 1,5 liters 907.10.11.222 P08-021 Loctite, Grade 542 910.42.12.121 P08-022 Sealant, Permatex, Form-a-Gasket No. 1 907.12.11.203 MIL-S-45180D P08-023 Adhesive Superseded by P08-059 P08-024 Coating, PR 1005-L 907.10.02.001 AMS-S-4383 P08-025 Thinner, BALCO ME 910.42.22.375 P08-026 Adhesive, Bostik M890 910.42.72.111 P08-027 Coating, Age Master No. 1 908.41.01.001 P08-028 Fuel Protective Coating, BFG A-851-B 907.13.13.041 P08-029 Adhesive, Scotchgrip 1300L 910.42.22.051 MIL-A-21366, A-A-1936 P08-030 Filler, Scotchseal EC-801 P08-031 Conductive sealant, BFG A-56-B 910.07.19.012 P08-032 Sealant Superseded by P08-057 P08-033 Sealant Superseded by P08-058 P08-034 Adhesive, Araldite rapid 910.42.62.002 P08-035 Plastic sealant, Loctite AVX 957.30.00.049 P08-036 Resin, epoxy, Dexter Hysol AE 9396 2 part 910.42.72.170 P08-037 Glass microsphere s, Cap-o-Sil 910.82.20.910 P08-038 Adhesive, epoxy , Araldite 2 component, 50 g 910.42.62.000 P08-039 Sealant, Loctite Grade 307 8010-0-000-0021 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 13 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P08-040 Sealant Superseded by P08-056 P08-041 Clear sealer, 3M 08551 Not available now Superseded by P08-056 907.13.13.093
P08-042 Sealant, Sikaflex-221 907.13.13.201 P08-043 Loctite, Grade 243, blue 50cm 3 910.42.12.128 P08-044 Resin, epoxy, Dexter Hysol AE 9395 2 part 910.42.72.169
P08-045 Sealant, sili con, translucent, RTV 907.13.13.102 MIL-A-46106
P08-046 Sealant, electr ically conductive, PR 1764 Class B 907.10.11.271 P08-047 Superseded by P04-029 P08-048 Resin, epoxy, Hysol 9394 A /B 2 part 907.10.11.272 MMM-A-132 P08-049 Honeycomb core, Nomex 3.2-80 Thickness 14 mm (0.55 in.) 917.00.25.210 P08-050 Honeycomb core, Nomex 3.2-48 Thickness 12 mm (0.50 in.) 917.00.25.227 P08-051 Foam core, PMI Rohazell 51WF T hickness 35 mm (1.37 in.) 917.33.14.146 P08-052 Adhesive, epoxy, 3M DP490 910.42.72.205 P08-053 Filler, spray, Filler 2K UP 910.08.06.004 P08-054 Resin, epoxy, Araldite 5052 917.00.40.001 P08-055 Ceramic adhesive, Resbond 907GF 907.10.11.273 MMS3500-11
P08-056 Sealant, PR 1829, B1 / 2 Sealant, PR 1829, B2, Black Pot life 30 minutes Pot life 120 minutes 907.10.11.262 907.10.11.263 P08-057 Sealant, PS 892 C12 907.10.11.244 P08-058 Sealant, PS 892 C24 907.10.11.243 P08-059 Adhesive, epoxy, SW9323 910.42.72.204 P08-060 Adhesive, epoxy, EC1614B/ A Superseded by P08-059 910.42.72.203 P08-061 Adhesive, epoxy, DP-100FR 2 part 910.42.62.003 P08-062 Insulkleber 1000 910.42.22.351 P08-063 Adhesive, Acrylic, Tensol No.70 910.42.72.112 P08-064 Adhesive, epoxy, Raychem S1005 910.42.72.206
P08-065 Adhesive, Loctite Grade 641 910.42.12.120 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 14 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P09 - General Stores P09-001 Tape, PTFE 01.1040.1212 917.47.71.103 P09-002 French chalk, Talcum powder 908.44.12.203 P09-003 Fabric strip 50 mm (2.0 in.) wide 918.71.62.032 P09-004 Koroseal binding P09-005 Cable ties 119 x 3,6 mm (4.69 x 0.14 in.) 971.32.51.105 MS3367-5-9, PA66, SAE-AS3367I P09-006 Thread, red indicating 918.71.03.121 P09-007 Glass fiber tape, 3M-386 25 mm (1.0 in.) wide 917.40.80.006 FAR 25.853(a) P09-008 Cable ties 69 x 2,5 mm (2.72 x 0.10 in.) 971.32.51.104 MS3367-4-9, PA66, SAE-AS33671 P09-009 Superseded by P09-024 P09-010 Rubber band 178 x 16 mm (7.00 x 0.63 in.) 944.85.82.112 P09-011 Lead seal 8,0 x 5,0 mm (0.32 x 0.20 in.) 911.21.91.005 P09-012 Tape Aluminum, Scotch 425 50 mm (2.0 in.) wide 917.40.91.005 FAR25.853(a), L-T-80, MIL-T-23397, TO 1-1-8 P09-013 Tape, Armaflex Band 50 mm (2.0 in.) wide 957.30.00.046 P09-014 Cable ties 160 x 4,8 mm (6.30 x 0.20 in.) 971.32.51.101 MS3397-1-9, PA66, SAE-AS3367I P09-015 Protective tape BAS185-GS3-0.6 in 946.33.21.296 P09-016 Superseded by P09-046 P09-017 Cable tie, heat-resistant 180 x 6,0 mm (7.10 x 0.24 in.) 971.32.51.206 P09-018 Soldering Sleeve, D142-50 971.19.26.104 NAS1745-14 P09-019 Soldering Sleeve, D142-51 971.19.26.105 NAS1745-15 P09-020 Glass fiber tape, 3M-361 19 mm (0.75 in.) wide 917.40.80.004 FAR25.853(a) P09-021 Superseded by P09-045 P09-022 Thread 917.54.16.203 P09-023 Lead seal 5,5 x 3,5 mm (0.22 x 0.14 in.) 911.21.91.002 P09-024 Rope, polyester, white 3,0 mm (0.12 in.) diameter 917.54.26.520 P09-025 Polyethylene foil, 3M-5423 19 (0 .75) wide x 1000 mm (39.40 in.) long 917.40.69.019 P09-026 Tape adhesive, 3M-8561 0,35 x 20 mm (0.014 x 0.80 in.) 917.40.68.001 P09-027 Superseded by P09-044 P09-028 Ident sleeve 20 mm (0.80 in.) wide 942.94.51.106 P09-029 String 918.71.03.071 MIL-T-43435B, A-A-52080B, A-A-52081B, A-A-52082B, A-A-52083B, A-A-52084B P09-030 Heat shrink sleeve 3/ 16 inch diameter 917.99.88.605 P09-031 Glass fiber fabric 163 g/m 2917.00.11.002 WL8.4548.60 P09-032 Carbon fiber fabric Not used now P09-033 Not used now P09-034 Copper wire mesh Lightning strike protection 72 g/m 2 919.02.30.111 P09-035 Not used now P09-036 Tape adhesive 0,64 x 19 mm (0.025 x 0.75 in.) 917.40.67.312 P09-037 Spiralwrap 917.99.90.002 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 15 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P09-038 Superseded by P09-043 P09-039 Masking Paper Masking paper, 300 mm (11.80 in.) width 905.20.10.003 Permafix 045 P09-040 Masking Paper Masking paper, 600 mm (23.60 in.) width 905.20.10.006 Permafix 045 P09-041 Masking Paper Masking paper, 900 mm (35.43 in.) width P09-042 Masking Paper Masking paper, 1500 mm (59.10 in.) width 905.20.10.015 Permafix 045 P09-043 Tape adhesive, transparency 0,35 x 40 mm (0.014 x 1.575 in.) 917.40.20.703 P09-044 Heat shrink sleeve 3/8 in. diameter 917.99.88.607 P09-045 Heat shrink sleeve 1 / 4 in. diameter 917.99.88.606 P09-046 Heat shrink sleeve 25,4 mm (1.0 in.) diameter 917.99.88.610 P09-047 Tape, adhesive 25,4 mm (1.0 in) width 917.40.61.108 P09-048 Tape, adhesive 76,2 mm (3.0 in) width 917.40.61.113 P09-049 Tape, Adhesive 0.36*305 3M-8673 917.40.69.152 P09-050 Tape, Lead 12 mm 917.40.91.011 P09-051 Tape, Lead 12 mm 917.40.91.012 P09-052 Tape Aluminum, Scotch 425 25 mm (1.0 in.) wide 917.40.91.003 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 16 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P10 - Oils and Fluids P10-001 CPC-temporary (Supersedes P10-001B & C) Lear Chemical ACF-50 Lear Chemical ACF-50, aerosol 908.18.12.087 908.18.12.088 MIL-C-81309 Type III P10-002 Superseded by P10-005 P10-003 Hydraulic Fluid Castrol Aero 585B Replaced by P10-017 908.14.12.015 MIL-H-5606 P10-004 Engine oil Refer to the applicable P&WC SB: 1001, 13001, 14001 P10-005 CPC-light (Supersedes P10-001A, P10- 002 and P10-005A & B) Ardrox / Dinitrol AV 8 Ardrox / Dinitrol AV 8, aerosol 908.18.12.081 908.18.12.083 MIL-PRF-16173 Grade 1 & 4

P10-006 Hydraulic fluid Aeroshell Fluid 31 908.14.12.016 MIL-PRF-83282 (was MIL-H-83282) P10-007 Compressor oil, BVM 100N Tamoil Tamfrost 100 Supersedes P10-007A, B, C & D 908.12.22.101 957.30.00.050 P10-008 Refrigerant R12, Freon, Fresan 957.30.00.058 P10-009 Cold air unit oil Esso ETO 2380, 908.11.02.105 MIL-PRF-23699 (was MIL-L-23699) P10-010 Refrigerant R134A 957.30.00.063 P10-011 Compressor oil, Castrol Icematic SW32 Supersedes P10-011A, B & C 957.30.00.051
P10-012 Oil, Hellerine 248 ml 908.20.02.047 P10-013 CPC-Ardrox AV 40 Ardrox / Dinitrol AV 40 908.18.12.086 P10-014 CPC Remover Ardrox / Dinitrol AV 980, aerosol 908.18.12.089 P10-015 CPC-Ardrox AV 30 (Supersedes P10-005C) Ardrox / Dinitrol AV 30, 20 liter Ardrox / Dinitrol AV 30, aerosol 908.18.12.080 908.18.12.085 MIL-PRF-16173 Grade 1 & 4 AMS 3077 P10-016 CPC-Ardrox AV 25 (Supersedes P10-005D) Ardrox / Dinitrol AV 25, aerosol 908.18.12.084 MIL-PRF-16173 Grade 3 AMS 3066 P10-017 Hydraulic fluid Aeros hell Fluid 41 (20 liters) Aeroshell Fluid 41 (5 liters) Replaces P10-003 908.14.12.017 908.14.12.018 MIL-PRF-5606 (was MIL-H-5606)
P10-018 CPC-Ardrox AV 15 Ardrox / Dinitrol AV 15 Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 17 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P11 - Fuels P11-001 Fuel For fuel specifications refer to P&WC EMM Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX E Page 18 Feb 28/10 

# PC-6 MAINTENANCE MANUAL

P12 - Packing There are no Pilatus Recommended Materials in this section. Material

No. Material Name Notes Pilatus Part No. Alternative Product / SpecificationEFFECTIVITY: All 

# APPENDIX F Page 401 Jul 31/11 

# PC-6 MAINTENANCE MANUAL

APPENDIX F AILERON/FLAP SUPPORT-BRACKETS- REMOVAL/INSTALLATION

1. General This procedure is applicable to the LH and RH support brackets. There are three support brackets on each wing. 2. Job Set Up Information
A. Consumable Material s (Ref. APPENDIX E):

3. Procedures WARNING: OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS WHEN YOU USE THE CONSUMABLE MATERIALS. CAUTION: OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU APPLY THE CONSUMABLE MATERIALS. A. Job Set Up (1) Remove the aileron and/or flap as necessary to remove the damaged support bracket: B. Removal (Ref. Fig. 401) (1) Cut and remove the lockwire from the bolts (3). (2) Remove the bolts (3), washers (2) and the support bracket (1). C. Installation (Ref. Fig. 401) (1) Hold the support bracket (1) in position on the wing and align the holes. (2) Temporarily install the bolts (3) to make sure the bolt holes align. (3) If you can not install the bolts (3) because of misalignment of the bolt holes: (a) Remove the bolts (3) and the support bracket (1). (b) You can file a small amount of material from three of the four bolt holes in the support bracket (1) to make the holes align. Material No. Description Remarks P01-008 Solvent Or Approved Alternative P02-007 Lockwire P02-031 Absorbent Paper P04-012 Corrosion Preventative P07-001 CCC SolutionEFFECTIVITY: All 

# APPENDIX F Page 402 Jul 31/11 

# PC-6 MAINTENANCE MANUAL (c) Apply a layer of CCC solution (Material No. P07-001) to the filed areas. (4) Apply corrosion preventative (Material No. P04-012) on the faying surfaces of the support bracket (1), the bolts (3) and the washers (2). (5) Install the support bracket (1) with the washers (2) and bolts (3). (6) Torque the nuts (3) to between 5,65 and 7,90 Nm (50 and 70 lbf in.). (7) Remove the unwanted corrosion preventative (Material No. P04-012) with the absorbent paper (Material No. P02-031) made moist with the solvent (Material No. P01-008). (8) Safety the bolts (3) with lockwire (Material No. P02-007). D. Close up (1) Install the removed aileron and/or flap, as necessary:EFFECTIVITY: All 

# APPENDIX F Page 403 Jul 31/11 

# PC-6 MAINTENANCE MANUAL

Support Bracket - Removal / Installation Figure 4016721 

# A

B



# B A A

B
B

1

2

3EFFECTIVITY: All 

# APPENDIX F Page 404 Jul 31/11 

# PC-6 MAINTENANCE MANUAL

INTENTIONALLY BLANKEFFECTIVITY: All 

# APPENDIX G Page 601 Jul 31/11 

# PC-6 MAINTENANCE MANUAL

APPENDIX G AILERON/FLAP SUPPORT-BRACKETS - INSPECTION/CHECK

1. General This procedure gives the data to do a fluorescent dye penetrant inspection on the support brackets, and visually examine the wing surface wh ere the support brackets attach. As an option, you can do an eddy current inspection on the support brackets. Only persons qualified and certified to Eddy Current Inspection Level II (or higher) National Aerospace Standard NAS 410, European Standard EN 4179, or any other equivalen t standards, shall do the eddy current inspection There are three support brackets on each wing. You must do the inspection on all six support brackets. 2. Job Set Up Information A. Tools and Equipment

B. Consumable Material s (Ref. APPENDIX E):

3. Procedures A. Job Set Up (1) Remove the ailerons and flaps. (2) Remove the s upport brackets (Ref. APPENDIX F). B. Inspection (Ref. Fig. 601) WARNING: OBEY THE MANUFACTURERS HEALTH AND SAFETY INST RUCTIONS WHEN YOU USE THE CONSUMABLE MATERIALS. (1) Use the absorbent paper (Material No. P02-031) made moist with solvent (Material No. P01-008) to clean the support bracket and the mating surface of the wing lower skin. Part No. Description Remarks - Bright light source - x10 magnifier

Material No. Description Remarks P01-008 Solvent Or approved alternative P02-031 Absorbent Paper P06-001 Penetrant P06-002 Remover P06-003 DeveloperEFFECTIVITY: All 

# APPENDIX G Page 602 Jul 31/11 

# PC-6 MAINTENANCE MANUAL (2) Use a bright light source and x10 magnifier to visually examine the mating surface of the wing lower skin for cracks. If you find a crack(s) contact Pilatus Aircraft Ltd for repair information. (3) Use the dye penetrant (Material No’s P06-002, P06-002 and P06-003) to do an inspection of the support bracket for cracks. Do thison the areas shown shaded on Fig. 601. (4) If you find a crack(s), replace the support bracket. (5) If you find no crack(s): (a) Use the absorbent paper (Material No. P02-031) made moist with solvent (Material No. P01-008) to clean the support bracket and the bore of the bush. C. Close up (1) Install the support brackets (Ref. APPENDIX F). (2) Install the ailerons and flaps.EFFECTIVITY: All 

# APPENDIX G Page 603 Jul 31/11 

# PC-6 MAINTENANCE MANUAL

Support Brackets - Inspection / Check Figure 6016722 

# A

B 

# A A

B
B

WING LOWER SURFACE 

# B

C C

INSPECTION AREASEFFECTIVITY: All 

# APPENDIX G Page 604 Jul 31/11 

# PC-6 MAINTENANCE MANUAL

INTENTIONALLY BLANK