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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

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RECORD OF TEMPORARY REVISIONS

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Rev No.

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Inserted: Signature: Date Removed / Incorporated in: Signature:
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Temp 

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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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APPENDIX G 601 Jul 31/11

602 Jul 31/11

603 Jul 31/11

604 Jul 31/11

Section Pages Date Section Pages Date
TOC Page 1

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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 / Check APPENDIX A 601 All

Horizontal Trim-Actuator Bearing-Fork or Bearing Support 

Assemblies

Inspection / Check 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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DOCUMENT NO. 02334

AIRWORTHINESS LIMITATIONS

1. General

The Airworthiness Limitations section is EASA approved and variations must also be approved.

The Airworthiness Limitations section is also FAA approved 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 Attachment 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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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 (All 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 Interval
EFFECTIVITY: All

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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 propeller maintenance manuals for the applicable 

airworthiness limitations.

NOTE B: If any of the above maintenance tasks were accomplished 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 the 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 Interval
EFFECTIVITY: All

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AIRWORTHINESS LIMITATIONS

DOCUMENT NO. 02334

3. Life Limited Items

Item Maintenance Requirement 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 Replace (discard) 7000 flying hours or 14 

years (whichever comes 

first)

Stabilizer Trim Actuator (Mechanical Trim) Overhaul 3500 flying hours

Stabilizer Trim Actuator (Electrical 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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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 Replace (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 Interval
EFFECTIVITY: All

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APPENDIX A Page 601

Feb 28/10

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MAINTENANCE MANUAL

APPENDIX A

HORIZONTAL TRIM-ACTUATOR SUPPORT-BRACKET AND FRAME 12A

INSPECTION / CHECK

1. General

This procedure gives the data and instructions necessary to do an inspection of the horizontal trimactuator support-bracket and auxiliary frame 12A 

The inspection is applicable to aircraft 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 Support Assemblies (Ref. APPENDIX B).

2. Job Set Up Information

A. Operator Supplied Parts

B. Consumable Materials (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

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MAINTENANCE MANUAL

A. Preparation

CONFIG 1:

(1) Remove the horizontal stabilizer actuator.

CONFIG 2:

(2) Remove the horizontal stabilizer actuator. During this procedure 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 scrapers 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 inspections for cracks in the fitting (3) or 

connecting piece (8) and the applicable area of FR12A. No crack damage is 

permitted. You must replace:

• Cracked components (Ref. Table 601 - Component Replacement Data)

• FR12A if cracks are found
EFFECTIVITY: 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 Data
EFFECTIVITY: All

APPENDIX A Page 604

Feb 28/10

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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 and apply layers of corrosion preventative 

(Material No. P04-012) on the faying surfaces 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 and 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 holes 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 Data
EFFECTIVITY: All

APPENDIX A Page 605

Feb 28/10

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MAINTENANCE MANUAL

(3) CONFIG 2A:

(a) Obey the manufacturers instructions and apply layers of 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 the 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 instructions and apply layers of 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. Make 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 601

6708

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

6
EFFECTIVITY: 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 necessary to do an inspection of the horizontal trimactuator bearing-fork, or bearing support assemblies, installed in the horizontal stabilizer.

The inspection is applicable to aircraft 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 Frame 12A (Ref. APPENDIX A).

2. Job Set Up Information

A. Consumable Materials (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 position 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

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MAINTENANCE MANUAL

CONFIG 2:

(3) Remove the horizontal stabilizer actuator. During this procedure 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 scrapers 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 the 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 Data
EFFECTIVITY: 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.) diameter drill to remove the rivets that attach the access panel(s) 

(1) to the bottom skin of the horizontal 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 instructions and 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 instructions 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 absorbent 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 apply 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 horizontal 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 601

6709

B

A

B 1

A

1

2

1 1

CONFIG 1

AIRCRAFT WITH

ELECTRICAL TRIM

CONFIG 2

AIRCRAFT WITH

MECHANICAL TRIM

A

7 6

3

3

5

4
EFFECTIVITY: All

APPENDIX B Page 606

Feb 28/10

PC-6

MAINTENANCE MANUAL

INTENTIONALLY BLANK
EFFECTIVITY: 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) of the Wing Strut Fittings, refer to Page 607.

2. Job Set Up Information

A. Tools and Equipment

B. Expendable Parts

C. Consumable Materials (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

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 alternatives for 

P04-028 for this application.

P07-001 Alodine 1200S

P07-007 Primer Paint
EFFECTIVITY: 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, use 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 straight edge of a ruler which will indicate 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. Chap. 2 and 4) from the given fittings (1). 

This step in only applicable if you have found permitted corrosion (Ref. Step 3.B.(2).

(4) Visually examine the left and right 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 Remarks
EFFECTIVITY: 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 bearing 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. P04-028) 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, damaged, corroded, incorrectly aligned or worn 

bearings are found.

CAUTION: DO NOT USE TOO MUCH HEAT TO REMOVE THE BEARING. DO NOT EXCEED 

120°C (224°F) FOR MORE THAN 15 MINUTES.

(1) Use a hot air blower (for heat shrink sleeves) and apply heat to loosen the adhesive 

between the bearing and the fitting or the bush.

CAUTION: DO NOT USE TOO MUCH FORCE TO REMOVE 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 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).
EFFECTIVITY: All

APPENDIX C Page 604

Feb 28/10

PC-6

MAINTENANCE MANUAL

(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, 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 that are 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 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 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.

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 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 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 601

6692

A

B

A

1

CORRECT BEARING

ALIGNMENT/POSITION

1

B

2

B

NEW ORIENTATION

OLD ORIENTATION
EFFECTIVITY: 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 Materials (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 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 alternatives for 

P04-028 for this application.

P07-001 Alodine 1200S
EFFECTIVITY: 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, use 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 straight edge of a ruler which will indicate 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. Chap. 2 and 4) from the given fittings (1). 

This step in only applicable if you have found permitted corrosion (Ref. Step 3.B.(2).

(4) Visually examine the left and right 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 Remarks
EFFECTIVITY: 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 TRAINED AND APPROVED (BY THE LOCAL 

AIRWORTHINESS AUTHORITIES) CAN DO THIS PROCEDURE.

(6) Do the non destructive inspection (Eddy Current).

(a) For strut fittings 111.35.06.193, 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. P02-031) 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)2 thru 8 again 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 metal 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. P04-028) 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, damaged, corroded, incorrectly aligned or worn 

bearings are found.

CAUTION: DO NOT USE TOO MUCH HEAT TO REMOVE THE BEARING. DO NOT EXCEED 

120°C (224°F) FOR MORE THAN 15 MINUTES.

(1) Use a hot air blower (for heat shrink sleeves) and apply heat to loosen the adhesive 

between the bearing and the fitting or the bush.

CAUTION: DO NOT USE TOO MUCH FORCE TO REMOVE 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, 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 that are 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 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 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. P08-059) to the applicable surfaces 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 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 613

Feb 28/10

PC-6

MAINTENANCE MANUAL

Wing Strut Fitting - Inspection

Figure 602, Sheet 1 of 2

6693

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

D
EFFECTIVITY: All

APPENDIX C Page 614

Feb 28/10

PC-6

MAINTENANCE MANUAL

Wing Strut Fitting - Inspection

Figure 602, Sheet 2 of 2

6694

SECTION

D-D

SEALANT BEARING

SEALANT BUSH
EFFECTIVITY: 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 cracks during the inspection, or cannot remove the 

bearing (Ref. APPENDIX C). The procedure is given for replacement of the left 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 make 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 2
EFFECTIVITY: 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 Materials (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

Reamer - 8,1 mm A/R For 1st Oversize

Reamer - 8,2 mm A/R

Drill - 8,2 mm A/R

Reamer - 8,3 mm A/R For 2nd Oversize

Reamer - 8,4 mm A/R

Drill - 8,4 mm A/R

Reamer - 8,5 mm A/R For 3rd Oversize

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/R
EFFECTIVITY: All

APPENDIX D Page 403

Feb 28/10

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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 of the fitting (Ref. Fig. 401). This step is only 

applicable if there is no internal 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 also 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 opening 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 contains five 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

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MAINTENANCE MANUAL

The forward flange of the new fitting contains 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 installation 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 reamer 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 increase 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 pilot hole and drill hole (J) in forward fitting 

flange. Use the drill determined 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 the 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 sizes
EFFECTIVITY: All

APPENDIX D Page 405

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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 Step 3.B.(5)(i) and (m), in the new fitting (4) 

and the wing spar are not circular, determine 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)3 and 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 cannot 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

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MAINTENANCE MANUAL

(e) Remove the unwanted corrosion preventative (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 applicable 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 (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.

(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) (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) Install the two screws (P/N 935.13.16.018) that you kept at Para. 3.B.(1).
EFFECTIVITY: All

APPENDIX D Page 407

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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 marks for the rivet holes with a 

2,4 mm (0.1 in.) diameter drill. 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 the bare metal surfaces of the 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

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MAINTENANCE MANUAL

C. Close up

(1) Remove all tools and materials. Make sure 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

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MAINTENANCE MANUAL

 Access Openings and Covers - Installation (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 26 mm

(1.02 in.)

R 35 m

(1.3

m

8 in.)

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 42 m

(1.6

m

5 in.)

B

FWD

INBOARD

43 mm

(1.69 in.)

97 mm

(3.82 in.)

=== ==

== = = = =

B

C
EFFECTIVITY: All

APPENDIX D Page 410

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MAINTENANCE MANUAL

 Access Openings and Covers - Installation (Left Shown, Right Similar)

Figure 401(Sheet 2 of 2)

SB1640

FWD

C

 Ø 155 mm

(6.10 in.)

R 67.5 mm

(2.66 in.)

R 60 mm

(2.36 in.)

= =

=

=

2

R 67.5 mm

(2.66 in.)
EFFECTIVITY: All

APPENDIX D Page 411

Feb 28/10

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MAINTENANCE MANUAL

Fitting - Replacement (Left Shown, Right Similar)

Figure 403

SB1569

A

A

1

2

3

4

SHOWN WITHOUT

SKIN FOR CLARITY

A

B

D

E C

G

F

H

J

K
EFFECTIVITY: All

APPENDIX D Page 412

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INTENTIONALLY BLANK
EFFECTIVITY: All

APPENDIX E Page 1

Feb 28/10

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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 - Bonding, 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 about the trade name, safety hazards, reactions, spill 

and leak procedures, special protection data, special 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

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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

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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 /

Specification
EFFECTIVITY: All

APPENDIX E Page 4

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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 /

Specification
EFFECTIVITY: 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 /

Specification
EFFECTIVITY: 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 lubricant, 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 /

Specification
EFFECTIVITY: 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 /

Specification
EFFECTIVITY: 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 /

Specification
EFFECTIVITY: 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 /

Specification
EFFECTIVITY: 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 /

Specification
EFFECTIVITY: 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 /

Specification
EFFECTIVITY: 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 microspheres, 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 /

Specification
EFFECTIVITY: 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 50cm3 910.42.12.128

P08-044 Resin, epoxy,

Dexter Hysol AE 9395 

2 part 910.42.72.169

P08-045 Sealant, silicon, translucent, 

RTV

907.13.13.102 MIL-A-46106

P08-046 Sealant, electrically 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 Thickness 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 /

Specification
EFFECTIVITY: 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/m2 917.00.11.002 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/m2 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 /

Specification
EFFECTIVITY: 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 /

Specification
EFFECTIVITY: 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 Aeroshell 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 /

Specification
EFFECTIVITY: 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 /

Specification
EFFECTIVITY: 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 /

Specification
EFFECTIVITY: 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 Materials (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 Solution
EFFECTIVITY: All

APPENDIX F Page 402

Jul 31/11

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(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

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Support Bracket - Removal / Installation

Figure 401

6721

A

B

B

A

A

B

B

1

2

3
EFFECTIVITY: All

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EFFECTIVITY: All

APPENDIX G Page 601

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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 where 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 equivalent 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 Materials (Ref. APPENDIX E): 

3. Procedures

A. Job Set Up

(1) Remove the ailerons and flaps.

(2) Remove the support brackets (Ref. APPENDIX F).

B. Inspection (Ref. Fig. 601)

WARNING: OBEY THE MANUFACTURERS HEALTH AND SAFETY INSTRUCTIONS 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 Developer
EFFECTIVITY: All

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(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 this on 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

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Support Brackets - Inspection / Check

Figure 601

6722

A

B

A

A

B

B

WING LOWER

SURFACE

B

C

C

INSPECTION AREAS
EFFECTIVITY: All

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