PUBLICATION TRANSMITTAL LETTER

FILE THIS TRANSMITTAL IN FRONT OF THE MANUAL

CHECK THAT ALL PREVIOUS TRANSMITTALS HAVE BEEN INCORPORATED

If any Transmittals have not been received, please advise Technical Publications Department, Pilatus Aircraft Ltd Page 1 of 2

PC-6

Pilatus Aircraft Ltd.

CH-6370 Stans

Switzerland

Tel 041-63 61 11

Fax 041-61 70 20

Telex 866202

Cable PILATUSAIR STANS

TO HOLDERS OF PC-6 AIRCRAFT MAINTENANCE MANUAL

PC-6 AIRCRAFT MAINTENANCE MANUAL

DOCUMENT NUMBER 01975

REVISION NO. 12

DATED MAY 14/10

HIGHLIGHTS

Pages which have been added or revised are given below together with the highlights of the revision. Remove

and insert the affected pages as listed.

Remove Insert Reason for Change

Introduction

CONT 1 and 2 1 and 2 Reference to Chapter 23 deleted.

Chapter 04- Airworthiness Limitations

04-LEP 1 and 2 1 and 2 Updated.

04-00-00 1 thru 6 1 thru 6 To correct the maintenance interval for the aileron, rudder, 

elevator and flap bellcranks and levers.

And:

To add a time limit for the flap actuator (electrical system) 

P/N 978.73.14.103.

Chapter 05 - Time Limits/Maintenance Checks

05-LEP 1 and 2 1 and 2 Updated.

05-TOC 1 and 2 1 and 2 New procedure 05-51-13 added.

05-10-10 1 thru 4

and TR 05-13

1 thru 4 TR 05-13 incorporated and maintenance of fire 

extinguisher amended.

05-10-20 1 thru 4 1 thru 4 Maintenance of fire extinguishers amended.

05-50-00 1 1 and 2 Volcanic ash inspections listed.

05-51-13 - 1 and 2 New procedure for flight through volcanic ash.
PUBLICATION TRANSMITTAL LETTER

FILE THIS TRANSMITTAL IN FRONT OF THE MANUAL

CHECK THAT ALL PREVIOUS TRANSMITTALS HAVE BEEN INCORPORATED

Page 2 of 2 If any Transmittals have not been received, please advise Technical Publications Department, Pilatus Aircraft Ltd

PC-6

Chapter 07 - Lifting and Shoring

07-LEP 1 1 and 2 Updated

07-10-00 201 thru 207 201 thru 208 Tools and equipment revised and new lifting procedures 

added.

Chapter 20 - Standard Practices

20-LEP 1 and 2 1 and 2 Updated.

20-31-00 1 thru 18 1 thru 18 Consumable materials list updated.

Chapter 24 - Electrical Power

24-LEP 1 and 2 1 and 2 Updated.

24-TOC 1 and 2 1 and 2 Unused page number deleted.

Chapter 27 - Flight Controls

27-LEP 1 and 2 1 and 2 Page dates of 27-20-00/501 corrected.

Chapter 28 - Fuel

28-LEP 1 and 2 1 and 2 Updated.

28-TOC 1 thru 4 1 thru 4 28-20-03 moved to correct the sequence.

Chapter 34 - Navigation

34-LEP 1 and 2 1 and 2 Updated.

34-21-00 501 thru 508 501 thru 508 Missing information added to Fig 502.

Correction to installation of pitot covers.

Chapter 57 - Wings

57-LEP 1 and 2 1 and 2 Page dates of Table of Contents corrected.

Chapter 79 - Oil

79-LEP 1 1 and 2 Updated.

79-TOC 1 1 and 2 New procedure added.

79-31-13 - 401 thru 404 New procedure for the removal/installation of the oil 

temperature sensor.

Record of Revisions Sheet Record incorporation of this revision and date of incorporation

Record of Temporary 

Revisions Sheet

Record the removal and removal date of TR 05-13.

Remove Insert Reason for Change
EFFECTIVITY: All

CONT Page 1

May 14/10

PC-6

MAINTENANCE MANUAL

CONTENTS

Subject Chapter

INTRODUCTION -

SERVICE BULLETIN LIST -

AIRWORTHINESS LIMITATIONS 04

TIME LIMITS / MAINTENANCE CHECKS 05

DIMENSIONS AND AREAS 06

LIFTING AND SHORING 07

LEVELLING AND WEIGHING 08

TOWING AND TAXIING 09

PARKING AND MOORING 10

PLACARDS AND MARKINGS 11

SERVICING 12

STANDARD PRACTICES 20

AIR CONDITIONING 21

ELECTRICAL POWER 24

EQUIPMENT / FURNISHINGS 25

FLIGHT CONTROLS 27

FUEL 28

ICE PROTECTION 30

INDICATING / RECORDING 31

LANDING GEAR 32

LIGHTS 33

NAVIGATION 34

OXYGEN 35

VACUUM 37

DOORS 52

FUSELAGE 53

STABILIZERS 55

WINDOWS 56

WINGS 57

PROPELLER 61

POWERPLANT 71

ENGINE FUEL AND CONTROL 73
EFFECTIVITY: All

CONT Page 2

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Subject Chapter

IGNITION 74

ENGINE CONTROLS 76

ENGINE INDICATING 77

EXHAUST 78

OIL 79

STARTING 80
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CHAPTER 04 - AIRWORTHINESS LIMITATIONS

LIST OF EFFECTIVE PAGES

Chapter

Section

Subject Pages Date

List of Effective 

Pages

1

2

May 14/10

May 14/10

Table of Contents 1 Feb 28/10

2 Feb 28/10

04-00-00 1 May 14/10

2 May 14/10

3 May 14/10

4 May 14/10

5 May 14/10

6 May 14/10
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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

(Fluorescent Dye Penetrant 

Inspection)

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

(Ref. 53-30-00. Page Block 

601)

3500 flying hours or 7 years 

(whichever comes first)

See NOTE C below

FR12A Examine

(Ref. 53-30-00. Page Block 

601)

3500 flying hours or 7 years 

(whichever comes first)

See NOTE C below

Fuselage - Wing-Strut Attachment-Brackets Examine

(Fluorescent Dye Penetrant 

Inspection)

3500 flying hours or 7 years 

(whichever comes first)

Chapter 55 - Stabilizers

Trim Actuator Attachment Examine

(Ref. 55-11-11, Page Block 

601)

3500 flying hours or 7 years 

(whichever comes first)

See NOTE C below
EFFECTIVITY: All

04-00-00 Page 2

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Chapter 57 - Wings

Left and Right Wing-Strut Fitting (All P/Ns) Examine 

(Ref. 57-00-02, Page Block 

601 - Check 1 - Visual 

Inspection)

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 (Ref. AMM, 20-

40-00, Page Block 1)

NOTE 2: For aircraft that 

operate in a moderate Corrosion 

Severity Zone (Ref. AMM, 20-

40-00, Page Block 1)

NOTE 3: For aircraft that 

operate in a mild Corrosion 

Severity Zone (Ref. AMM, 20-

40-00, Page Block 1)

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

(Ref. 57-00-02, Page Block 

601 - Check 2 - Eddy Current 

Inspection)

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

(Ref. 57-00-02, Page Block 

601 - Check 2 - Eddy Current 

Inspection)

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

(Ref. 57-00-02, Page Block 

601 - Check 2 - Eddy Current 

Inspection)

12 months

See NOTE D below

Right Wing-Strut Fitting (P/N 111.35.06.194 

or 111.35.06.195)

Examine

(Ref. 57-00-02, Page Block 

601 - Check 2 - Eddy Current 

Inspection)

12 months

See NOTE D below

Wing - Fuselage Attachments Examine

(Fluorescent Dye Penetrant 

Inspection)

7000 flying hours or 14 years 

(whichever comes first)

Item Maintenance Requirement Interval
EFFECTIVITY: All

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MAINTENANCE MANUAL

Aileron/Flap Support-Brackets Examine

(Fluorescent Dye Penetrant 

Inspection)

7000 flying hours or 14 years 

(whichever comes first)

Item Maintenance Requirement Interval
EFFECTIVITY: All

04-00-00 Page 4

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MAINTENANCE MANUAL

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)

(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

04-00-00 Page 5

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MAINTENANCE MANUAL

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

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 in accordance with an earlier 

revision of this AMM, 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 revision.

Approved by: Hamid Hampai

FEDERAL OFFICE OF CIVIL AVIATION (FOCA), SWITZERLAND

EASA Project No: 0010004781-001

Approval Signature: Signed original held on file by Pilatus Aircraft Ltd, Stans

Approval Date: May 14th 2010

Item Maintenance Requirement Interval
EFFECTIVITY: All

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CHAPTER 05 - TIME LIMITS / MAINTENANCE CHECKS

LIST OF EFFECTIVE PAGES

Chapter

Section

Subject Pages Date

List of Effective 

Pages

1

2

May 14/10

May 14/10

Table of Contents 1 May 14/10

2 May 14/10

05-00-00 1 Nov 30/03

05-10-00 1 Nov 30/03

05-10-10 1 May 14/10

2 May 14/10

3 May 14/10

4 May 14/10

05-10-20 1 May 14/10

2 May 14/10

3 May 14/10

4 May 14/10

05-20-00 1 Nov 30/03

2 Nov 30/03

3 Nov 30/03

05-21-00 1 Jun 14/91

05-21-01 1 Jun 14/91

2 Jun 14/91

3 Jun 14/91

4 Jun 14/91

05-21-02 1 Jun 14/91

05-21-03 1 Jun 14/91

2 Jun 14/91

05-22-00 1 Mar 14/95

05-22-01 1 Feb 28/10

2 Feb 28/10

3 Feb 28/10

4 Feb 28/10

5 Feb 28/10

6 Feb 28/10

05-22-01 (Cont‘d) 7 Feb 28/10

8 Feb 28/10

9 Feb 28/10

10 Feb 28/10

05-22-02 1 Jun 30/09

2 Jun 30/09

3 Jun 30/09

4 Jun 30/09

05-22-03 1 Nov 30/08

2 Nov 30/08

3 Nov 30/08

4 Nov 30/08

05-22-04 1 Mar 14/95

05-23-00 1 Nov 30/03

05-23-01 1 Nov 30/08

2 Nov 30/08

3 Nov 30/08

4 Nov 30/08

5 Nov 30/08

6 Nov 30/08

7 Nov 30/08

8 Nov 30/08

9 Nov 30/08

10 Nov 30/08

05-23-02 1 Nov 30/03

2 Nov 30/03

3 Nov 30/03

05-23-03 1 Mar 14/95

2 Mar 14/95

3 Mar 14/95

05-23-04 1 Mar 14/95

05-24-00 1 Mar 14/95

05-24-01 1 Feb 28/10

2 Feb 28/10

Chapter

Section

Subject Pages Date
05-LEP Page 2

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05-24-01 (Cont‘d) 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

05-24-02 1 Nov 30/03

2 Nov 30/03

3 Nov 30/03

05-24-03 1 Mar 14/95

2 Mar 14/95

3 Mar 14/95

05-24-04 1 Mar 14/95

05-50-00 1 May 14/10

2 May 14/10

05-51-01 1 Nov 30/03

2 Nov 30/03

05-51-02 1 Feb 28/10

2 Feb 28/10

05-51-03 1 Nov 30/03

05-51-04 1 Nov 30/03

05-51-05 1 Nov 30/03

05-51-08 1 Jun 14/91

05-51-09 1 Nov 30/03

05-51-12 1 Mar 14/95

05-51-13 1 May 14/10

2 May 14/10

05-57-01 601 Nov 30/03

602 Nov 30/03

603 Nov 30/03

Chapter

Section

Subject Pages Date

05-57-01 (Cont’d) 604 Nov 30/03

605 Nov 30/03

606 Nov 30/03

Chapter

Section

Subject Pages Date
05-TOC Page 1

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CHAPTER 05 - TIME LIMITS / MAINTENANCE CHECKS

TABLE OF CONTENTS

Subject

Chapter

Section

Subject Page Effectivity

TIME LIMITS / MAINTENANCE CHECKS 05-00-00

General 1 All

TIME LIMITS 05-10-00

General 1 All

OVERHAUL AND REPLACEMENT SCHEDULE 05-10-10 1 All

TIME LIMITED MAINTENANCE REQUIREMENTS 05-10-20 1 All

SCHEDULED MAINTENANCE CHECKS 05-20-00

General 1 All

FLIGHT MAINTENANCE CHECKS 05-21-00

General 1 All

Airframe 05-21-01 1 All

Engine 05-21-02 1 All

Electrics and Instruments 05-21-03 1 All

100 HOUR / ANNUAL INSPECTION 05-22-00

General 1 All

Airframe 05-22-01 1 All

Engine 05-22-02 1 All

Electrics and Instruments 05-22-03 1 All

Avionics 05-22-04 1 All

PARTIAL OVERHAUL 05-23-00

General 1 All

Airframe 05-23-01 1 All

Engine 05-23-02 1 All

Electrics and Instruments 05-23-03 1 All

Avionics 05-23-04 1 All

COMPLETE OVERHAUL 05-24-00

General 1 All

Airframe 05-24-01 1 All
05-TOC Page 2

May 14/10

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MAINTENANCE MANUAL

Engine 05-24-02 1 All

Electrics and Instruments 05-24-03 1 All

Avionics 05-24-04 1 All

UNSCHEDULED MAINTENANCE CHECKS 05-50-00

General 1 All

HIGH g-LOADS 05-51-01 1 All

HARD OR OVERWEIGHT LANDING 05-51-02 1 All

TAIL DOWN LANDING 05-51-03 1 All

OVERSPEED - MORE THAN VNE 05-51-04 1 All

OVERSPEED - MORE THAN VFE 

WITH FLAPS EXTENDED

05-51-05 1 All

ENGINE OVERTORQUE 05-51-08 1 All

SUDDEN PROPELLER STOPPAGE OR 

IMPACT

05-51-09 1 All

LIGHTNING STRIKE 05-51-12 1 All

FLIGHT THROUGH VOLCANIC ASH OR 

SMOKE

05-51-13 1 All

ALIGNMENT AND SYMMETRY 05-57-01 All

Inspection / Check 601 All

Subject

Chapter

Section

Subject Page Effectivity
EFFECTIVITY: All

05-10-10 Page 1

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MAINTENANCE MANUAL

OVERHAUL AND REPLACEMENT SCHEDULE

Component Maximum Life Overhaul Interval

Chapter 24 - Electrical Power

Starter-generator 1000 flying hours

Chapter 25 - Equipment and Furnishings

Safety harnesses 10 years

ELT battery (if installed) After a total of one hour of ELT 

use or as shown on the battery 

label

First aid kit (if installed) 1 year

Powder fire extinguisher P/N 959.08.01.352

(if installed)

3 years

Chapter 27 - Flight Controls

Rudder bearing 3500 flying hours or 7 years

Control column aileron/pitch trim switch 3500 flying hours or 10 years

Aileron trim actuator (electrical system) 3500 flying hours

Rudder trim actuator (electrical trim) 3500 flying hours

Chapter 28 - Fuel

Flexible hoses (P/N 115.55.06.135, 

115.55.06.136, 6538.0043.00)

10 years

Fuel filter element (Airmaze)

- cleanable type

600 flying hours

Fuel filter element (Zenith)

- disposable type

100 flying hours

Transfer pumps - underwing tanks 

(if installed)

7000 flying hours

Engine driven pump 3500 flying hours

Auxiliary pump 1200 flying hours 

or 7 years

Chapter 32 - Landing Gear

Flexible hoses 10 years

Main landing gear assembly 7000 flying hours 

or 14 years
EFFECTIVITY: All

05-10-10 Page 2

May 14/10

PC-6

MAINTENANCE MANUAL

Main gear shock struts 10000 landings 

or 7 years

Tail shock strut 10000 landings 

or 7 years

Tail landing gear assembly 3500 flying hours 

or 7 years

Brake master cylinder 3500 flying hours 

or 7 years

Deleted

Deleted

Brake unit 3500 flying hours 

or 7 years

Chapter 37 - Vacuum

Vacuum system air filter (D9-18-1) 500 flying hours or 1 year, 

whichever comes first

Chapter 61- Propeller

Propeller (with attachment bolts) 3000 flying hours 

or 5 years (Ref. Hartzel 

SL 61, latest revision)

Propeller overspeed governor Engine TBO + 500 hours

Chapter 71 - Power Plant

Engine 3600 flying hours 

(Ref. P&WC SB 1803)

Engine accessories (Ref. P&WC SB 1803)

Engine rotor components Refer to P&WC SB 1002

Engine hot section (HSI) 1800 flying hours

(Ref. P&WC SB 1803)

Engine shockmounts 3600 flying hours

Chapter 73 - Engine Fuel and Control

FCU drivebody inspection/bearing 

replacement 

(Ref. P&W EMM 72-00-00, Page Block 601 

/ Pilatus SL 076)

2000 flying hours 

or 6 years

Component Maximum Life Overhaul Interval
EFFECTIVITY: All

05-10-10 Page 3

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MAINTENANCE MANUAL

P3 air filter Pt No. 3029268

(cleanable type)

1000 flying hours maximum

(Ref. P&WC EMM 72-00-

00, Page Block 601)

P3 air filter Pt No. 3031781

(disposable type)

1000 flying hours

(Ref. P&WC EMM 72-00-00, 

Page Block 601)

HP fuel pump outlet filter

Pt No. 3033355

600 flying hours

(Ref. P&WC EMM 73-10-02)

Chapter 77 - Engine Indicating

Flexible hose (P/N 6501.0131.00) 10 years

Chapter 79 - Oil

Engine oil filter (permanent type)

(Post P&WC SB 1118 and Pre SB 1215)

1500 flying hours 

(Ref. P&WC EMM 72-00-

00, Page Block 601)

Engine oil filter (disposable type)

(Post P&WC SB 1215 and SB 1282)

1000 flying hours

(Ref. P&WC EMM 72-00-00, 

Page Block 601)

Oil cooler 3500 flying hours

Oil cooler shockmounts 3500 flying hours, 7 years, or 

when the cooler is removed

Flexible hoses (P/N 115.60.06.054, 

115.60.06.045, 6543.0111.00)

10 years

Component Maximum Life Overhaul Interval
EFFECTIVITY: All

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TIME LIMITED MAINTENANCE REQUIREMENTS

Item Maintenance Requirement Interval

Chapter 24 - Electrical Power

Hawker NiCad Battery (if installed) Remove and service (Ref. 

24-32-11, Page Block 401 

and Battery CMM)

300 flying hours or 3 months

Marathon NiCad Battery (if installed) Remove and service (Ref. 

24-32-11, Page Block 401 

and Battery CMM)

100 flying hours or 3 months

Hawker Lead Acid Battery (if installed) Remove and capacity test

(Ref. 24-32-11, Page Block 

401 and Battery CMM)

Initial test: 4500 flying hours or 

18 months, then:

- If the capacity is more than 

90% of the new capacity do the 

subsequent test at 1500 flying 

hours or 6 months

- If the capacity is between 81% 

and 90% of the new capacity do 

the subsequent test at 750 flying 

hours or 3 months.

Concorde Lead Acid Battery (if installed) Remove and capacity test

(Ref. 24-32-11, Page Block 

401 and Battery CMM)

Initial test: 600 flying hours or 12 

months

Subsequent tests at 200 flying 

hours or 4 months

Emergency Battery (if installed) Remove and service

(Capacity test, Ref. CMM) 

Operational test

1 year

3 months

Starter / Generator Brushes Check for wear

(Ref. 24-31-11)

200 flying hours

Chapter 25 - Equipment and Furnishings

Halon Fire Extinguisher

P/N 959.08.06.211

(if installed)

Examine

Check contents

1 year

Powder Fire Extinguisher 

P/N 959.08.01.352

(if installed)

Examine and weigh

Max permitted weight loss is 

10 grams (0.35 oz)

Check pressure

1 year

Halon Fire Extinguisher 

P/N 959.08.06.211

(if installed)

Hydrostatic test 12 years

ELT (if installed) Operational Test

(Ref. 25-63-00, Page Block 

501)

1 year
EFFECTIVITY: All

05-10-20 Page 2

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Chapter 27 - Flight Controls

Aileron Control Cables and Pulleys Examine (

Ref. 27-00-00, Page Block 

601)

3500 flying hours or 7 years

Rudder Control Cables and Pulleys Examine 

(Ref. 27-00-00, Page Block 

601)

3500 flying hours or 7 years

Elevator Control Cables and Pulleys Examine 

(Ref. 27-00-00, Page Block 

601)

3500 flying hours or 7 years

Trim Control Cables (if installed) Examine 

(Ref. 27-00-00, Page 601)

3500 flying hours or 7 years

Chapter 28 - Fuel

Fuel Filter Element

(Airmaze Pt. No. OW1702-231)

Clean (Ref. 28-21-12, Page 

Block 701)

50 flying hours

Fuel Filter Element

(Airmaze Pt. No. OW2440-231)

Clean (Ref. 28-21-12, Page 

Block 701)

100 flying hours

Engine Driven Fuel Pump Check pump drive shaft for 

backlash

(Ref. 28-20-03, Page Block 

601)

400 flying hours

Chapter 32 - Landing Gear

Main and Tailwheels Crack detect the wheel 

halves as given in the latest 

revision of ABSC CMM AP 

440

Magnetic particle inspect the 

tie bolts

At each tire replacement

Chapter 34 - Navigation

Pitot-Static System Leak check

Drain

2 years or 600 flying hours

2 years

Standby Magnetic Compass Check swing 2 year

Encoding Altimeter System (if installed) Functional test IFR flight operations:

2 years

VFR flight operations:

On condition

Item Maintenance Requirement Interval
EFFECTIVITY: All

05-10-20 Page 3

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Altimeter Functional test IFR flight operations:

2 years

VFR flight operations:

On condition

Transponder System (If installed) Functional test 2 years

Chapter 35 - Oxygen

Regulator Panels (if installed) Bench test 5 years

Chapter 51 - Structures

Complete Structure - Internal and External Look for corrosion 1 year

Chapter 53 - Fuselage

Fuselage, Seat Attachments and 

Surrounding Structure

Examine 2 years

Chapter 56 - Windows

Emergency Windows

(Aircraft without pilot/co-pilot doors)

Check operation

Lubricate seals (Material No. 

P04-018)

300 flying hours or 1 year

Chapter 61 - Propeller

Propeller Lubricate 100 flying hours or 1 year,

Propeller Overspeed Governor Check operation

(Ref. 71-00-00, Page 501)

200 flying hours

Chapter 71 - Powerplant

Compressor Performance Recovery 

Wash 

All operations

(Ref. 71-00-00, Page 701)

100 to 200 flying hours

(Ref. P&WC EMM 71-00-00, 

Page 701)

Desalination Wash

Salt laden environment

(Ref. 71-00-00, Page 701)

Daily to weekly depending on 

operating conditions

(Ref. P&WC EMM 71-00-00, 

Page 701)

Examine for corrosion and 

erosion (Ref. P&WC EMM 

72-30-05, Page Block 201)

400 flying hours or when FOD 

damage is suspected

Item Maintenance Requirement Interval
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Turbine Wash (Ref. 71-00-00, Page 

701)

Ref. P&WC EMM 71-00-00, 

Page 701

Sand Filters (if installed) Clean (Ref. 71-12-00, Page 

701)

25 flying hours

Hot Section Examine with boroscope 

(Ref. P&WC EMM 72-00-00, 

Page Block 601)

Ref. P&WC EMM 72-00-00, 

Table 601

Chapter 73 - Engine Fuel and Control

HP Fuel Pump Inlet Screen Clean

Examine (Ref. P&WC EMM 

73-10-02)

600 flying hours

HP Fuel Pump Coupling Shaft

(If Sundstrand Fuel Pump installed)

Examine drive splines for 

fretting corrosion

(Ref. P&WC EMM 73-10-02)

600 flying hours

Fuel Manifold Adapter and Nozzle 

Assemblies

Examine (Ref. P&WC EMM 

73-10-05)

Ref. P&WC EMM 72-00-00, 

Table 601

Chapter 74 - Ignition

Spark Ignitors or Glowplugs Examine (Ref. P&WC EMM 

74-20-04 and 74-20-02)

200 flying hours

Chapter 79 - Oil

Chip Detector

(Aircraft without CHIP caption on CAWS)

Examine (Ref. P&WC EMM 

72-00-00, Page Block 601)

100 flying hours

Chip Detector

(All aircraft)

Examine (Ref. P&WC EMM 

72-00-00, Page Block 601)

600 flying hours or 1 year

Oil Separator (if installed) Drain 50 flying hours

Item Maintenance Requirement Interval
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UNSCHEDULED MAINTENANCE CHECKS

1. General

Unscheduled maintenance checks are necessary if unusual incidents occur.

These checks must be done before the next flight following the incident.

Depending on the severity of an incident, it may be advisable to remove the wings, horizontal stabilizer, 

elevator, rudder and landing gear to allow a more comprehensive inspection to be done.

If necessary contact Pilatus Aircraft Limited for further advice.

2. Unscheduled Maintenance Checks - Airframe

These checks must be done after the following incidents occur:

• High g-loads 05-51-01

• Hard or overweight landing 05-51-02

• Tail down landing 05-51-03

• Overspeed, more than VNE 05-51-04

• Overspeed with flaps extended (VFE) 05-51-05

• Engine overtorque 05-51-08

• Sudden propeller stoppage or impact 05-51-09

• Lightning strike 05-51-12

• Flight through volcanic ash or smoke 05-51-13

3. Unscheduled Maintenance Checks - Engine

These checks must be done after the following incidents occur (Ref. P&WC EMM 72-00-00, Page Block 

601):

• Engine overspeed 

(Gas generator or propeller) 

• Overtorque

• Sudden propeller stoppage

(Overhaul propeller overspeed governor, in addition to P&WC EMM prescribed actions)

• Lightning strike

• Loss of oil pressure

• Contamination by fire extinguisher agents

• Flight through volcanic ash or smoke
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FLIGHT THROUGH VOLCANIC ASH OR SMOKE - UNSCHEDULED MAINTENANCE CHECKS

1. General

Do this check before the next flight if the aircraft was flown (or you suspect it was flown) through 

volcanic ash or volcanic smoke. The purpose of the check is to find:

• Abrasion or erosion of surfaces

• Damage to the aircraft and/or engine

• Deterioration of the aircraft systems

• Quantities of collected volcanic ash

2. Procedure

A. Aircraft Exterior

(1) Do a visual examination of the areas that follow for contamination, abrasion and damage:

• The exterior surfaces of the fuselage

• All parts of the aircraft that extend into the airflow

• Stabilizers

• Wings

• Flight control surfaces

• Antennas

• Windshield, side and cabin windows

• Landing gear

• All exterior lights

B. Fuselage Interior

(1) Do a visual examination of all the aircraft compartments which have access panels or 

doors.

(2) Do a visual examination of all the aircraft compartments which have vents and/or NACA 

inlets.

C. Engine Area

(1) If the emergency shut-off valves for the air-conditioning were closed during the flight, reset 

the valves.

(2) Clean the air-inlet screens and filters for the air conditioning system.

(3) If the aircraft is equipped with a cabin ventilation system, remove and clean the filter.

(4) Clean the engine-compressor inlet-screen.

(5) If the aircraft is equipped with a sand filter installation, remove and clean the sand filters 

(Ref. 71-12-00, Page Block 701).
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(6) Examine the engine oil cooler for contamination. If necessary, clean the heat exchanger 

matrix with a soft bristle brush and/or low pressure air.

(7) Examine the propeller for contamination, abrasion and damage.

D. Pitot/Static System

(1) Disconnect the pitot/static air pipes from the:

• Vertical speed indicator

• Altimeter(s)

• Airspeed indicator

(2) Remove the pitot/static drain traps.

(3) Blow clean, dry, low pressure air through the pitot/static air pipes from the pitot head and 

static ports.

(4) Install the pitot/static drain traps.

(5) Connect the pitot/static air pipes to the:

• Vertical speed indicator

• Altimeter(s)

• Airspeed indicator

(6) Do a pitot/static system leak check (Ref. 34-11-00, Page Block 501).

E. Aircraft Cleaning

(1) Do a wash of the aircraft (Ref. 12-20-01, Page Block 701). When you do this, do a rinse of 

the engine air intake.

F. Detailed Examination/Tests

(1) Do an operational test of the flight controls to make sure that the movement is full, free and 

smooth.

(2) If the aircraft has, or is suspected to have, been struck by a coronal discharge (St. Elmo’s 

Fire), do the inspection for lightning strike (Ref. 05-51-12, Page Block 1).

(3) Examine the engine (Ref. P&WC EMM 72-00-00, Page Block 601 - Aircraft Flown through 

Volcanic Ash or Smoke).
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CHAPTER 07 - LIFTING AND SHORING

LIST OF EFFECTIVE PAGES

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205 May 14/10

206 May 14/10

207 May 14/10

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JACKING - MAINTENANCE PRACTICES

1. General

This section gives the following lifting procedures:

• Lifting and lowering the aircraft with jacks

• Lifting and lowering the aircraft on main jacks and a tail stand

• Lifting and lowering a main wheel

• Lifting the aircraft with a sling

2. Lifting and Lowering the Aircraft with Jacks

A. General (Ref. Fig. 201)

Lifting the aircraft should be done on firm and level ground. The lifting site should be protected 

from wind or, if possible, the aircraft should be lifted inside a hanger.

Jack pads are installed on the fuselage to lift the complete aircraft. Three jack pads are found at 

the following locations:

• One near each fuselage wing strut end fitting

• One at the aft end of the fuselage

B. Tools and Equipment

Part No. Description Remarks

6690.0036.01 Wheel Chocks Or equivalent

or

990.00.00.909 Wheel Chocks Or equivalent

110.85.06.006 Main Jack Or equivalent

or

968.85.81.210 Main Jack Or equivalent

or

968.85.81.213 Main Jack Or equivalent

968.85.81.215 Adapter, Main Jack For use with 968.85.81.213

- Tail Jack Minimum lifting capacity:

200 kg (450 lb)

Minimum height :

45 cm (18 in.)

Minimum lifting height:

35 cm (14 in.)

- Ballast 70 kg (150 lb)

- Ballast suspension bar
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C. Lifting the aircraft (Ref. Fig. 201)

WARNING: DO NOT LIFT THE REAR OF THE AIRCRAFT UNTIL BALLAST WEIGHTS HAVE BEEN 

INSTALLED.

(1) Put the aircraft on to level and firm ground.

(2) Make sure that there are no obstructions around or above the aircraft.

(3) Put the wheel chocks in position.

(4) Put the main jacks below the forward fuselage jack pads.

(5) Put the tail jack below the tail jack pad.

(6) Install the ballast suspension bar through the rear fuselage and install ballast.

(7) Operate the jacks slowly and evenly until the main wheels and tail wheel are clear of the 

ground.

D. Lowering the aircraft (Ref. Fig. 201)

(1) Make sure there are no obstructions around or below the aircraft.

(2) Operate the jacks to lower the aircraft until the main wheels and tail wheel touch the 

ground.

(3) Put the wheel chocks in position.

(4) Remove the jacks from the aircraft.

(5) Remove the tail ballast and the ballast suspension bar.

(6) Make sure that the work area is clean and clear of tools and other items.

3. Lifting and Lowering the Aircraft on Main Jacks and a Tail Stand

A. General (Ref. Fig. 201)

Lifting the aircraft should be done on firm and level ground. The lifting site should be protected 

from wind or, if possible, the aircraft should be lifted inside a hanger.

Jack pads are installed on the fuselage to lift the complete aircraft. Three jack pads are found at 

the following locations:

• One near each fuselage wing strut end fitting

• One at the aft end of the fuselage
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B. Tools and Equipment

C. Lifting the aircraft (Ref. Fig. 201)

(1) Lift the aircraft with a sling (Ref. Para. 5).

(2) Put the main jacks below the forward fuselage jack pads.

(3) Put the tail stand below the tail jack pad.

(4) Lower the aircraft on to the jacks and tail stand.

(5) Adjust the jacks and tail stand as necessary until the aircraft is level.

(6) Make sure that the tail stand lock device locks around the tail jack pad and that the stand 

legs are firmly in contact with the ground.

(7) Install the ballast suspension bar through the rear fuselage and install the ballast.

(8) Remove the sling and the ropes.

D. Lowering the aircraft 

(1) Prepare to lift the aircraft with a sling (Ref. Para. 5).

(2) Remove the tail ballast and the ballast suspension bar.

(3) Lift the aircraft off the jacks and tail stand with the sling (Ref. Para. 5).

(4) Remove the jacks and the tail stand from the aircraft.

(5) Make sure there are no obstructions around or below the aircraft.

(6) Lower the aircraft to the ground.

(7) Put the wheel chocks in position.

(8) Remove the sling and the ropes.

Part No. Description Remarks

6690.0036.01 Wheel Chocks Or equivalent

or

990.00.00.909 Wheel Chocks Or equivalent

110.85.06.006 Main Jack Or equivalent

or

968.85.81.210 Main Jack Or equivalent

or

968.85.81.213 Main Jack Or equivalent

968.85.81.215 Adapter, Main Jack For use with 968.85.81.213

110.85.06.007 Tail Stand Or equivalent

- Ballast 70 kg (150 lb)

- Ballast suspension bar
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(9) If necessary, remove the control-surface gust-locks.

(10) Make sure that the work area is clean and clear of tools and other items.

4. Lifting and Lowering a Main Wheel

A. General (Ref. Fig. 201)

The aircraft main wheels can be lifted at the ski attachment brackets with a suitable round metal 

bar installed through the holes in the bracket and a hydraulic bottle jack used to lift the aircraft.

The lifted wheel should be lifted no more than is necessary to obtain ground clearance. 

B. Tools and Equipment

C. Lifting a Main Wheel (Ref. Fig. 201)

WARNING: BEFORE LIFTING, THE WHEEL CHOCKS MUST BE INSTALLED TO STOP 

ACCIDENTAL MOVEMENT OF THE AIRCRAFT.

(1) Put the aircraft on to level and firm ground.

(2) Make sure that there are no obstructions around or above the aircraft.

(3) Apply the park brake.

(4) Put the wheel chocks in position.

(5) Install the round metal bar through the holes in the ski attachment bracket.

(6) Put the jack below the jack point to be lifted.

(7) Operate the jack until the wheel is clear of the ground.

D. Lowering a Main Wheel

(1) Make sure that there are no obstructions around or below the wheel to be lowered.

(2) Operate the jack to lower the aircraft until the main wheel touches the ground.

(3) Remove the round metal bar from the ski attachment bracket and the jack from the aircraft.

(4) Make sure that the work area is clean and clear of tools and other items.

Part No. Description Remarks

6690.0036.01 Wheel chocks

- Bottle jack

- Metal bar (round)
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5. Lifting the Aircraft with a Sling

A. General (Ref. Fig. 202)

Two tapped holes are located on the top of the fuselage adjacent to the wing attachment fittings. 

A sling with lifting lugs is then installed to lift the aircraft.

The complete aircraft can be lifted with a lifting sling and a hoist or a mobile crane. The total 

weight of the aircraft must not be more than 1500 kg (3300 lb).

When the aircraft is lifted it must remain in a level attitude. Ropes attached to the wing 

attachment points and the fuselage tail permit the aircraft to be maneuvered in a stable attitude.

B. Tools and Equipment

C. Procedure (Ref. Fig. 202)

(1) Make sure that there are no obstructions around or above the aircraft.

(2) Put the wheel chocks in position.

(3) Defuel the aircraft (Ref. 12-11-28, Page block 301).

(4) If necessary, install the control-surface gust-locks (Ref. 10-10-00, Page block 201).

(5) Make sure that all the doors are closed and that no equipment will become loose when 

lifting the aircraft.

(6) Install the sling to the attachment points at the top of the fuselage. Make sure that the 

attachment screws are fully screwed down.

(7) Attach ropes to the wing and to the tail tie down attachment points.

(8) With personnel positioned at each rope and a supervisor co-ordinating the lifting 

operation, slowly lift the aircraft off the ground. Make sure the aircraft is kept in a level 

attitude when the aircraft is lifted.

Part No. Description Remarks

6690.0018.00 Sling

- Rope

- Lifting equipment Minimum capacity 2250 kg 

(5000 lb)
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Aircraft Jack Points

Figure 201

6291

C A

B

C

B

A

B

C HOLE THROUGH FUSELAGE FOR

BALLAST SUSPENSION BAR

REAR END

OF FUSELAGE

TAIL JACK PAD

WING STRUT

END FITTING

FORWARD FUSELAGE

JACK PAD

SKI ATTACHMENT

BRACKET
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Aircraft Lifting with a Sling

Figure 202

6292

A

A

LIFTING SLING
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CHAPTER 20 - STANDARD PRACTICES

LIST OF EFFECTIVE PAGES

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205 Mar 14/98

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205 Nov 30/03

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702 Feb 28/10

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4 Nov 30/03

5 Nov 30/03

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9 Nov 30/03

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13 Nov 30/03

201 Nov 30/03

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801 Mar 30/08

802 Mar 30/08

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202 Sep 30/07

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202 Sep 30/07

203 Sep 30/07

204 Sep 30/07

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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.
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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

-
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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
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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
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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

20-31-00 Page 6

May 14/10

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

20-31-00 Page 7

May 14/10

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

20-31-00 Page 8

May 14/10

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

20-31-00 Page 9

May 14/10

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

20-31-00 Page 10

May 14/10

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

20-31-00 Page 11

May 14/10

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

20-31-00 Page 12

May 14/10

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

20-31-00 Page 13

May 14/10

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

P08-066 Honeycomb core ECA 3.2-48-3mm thick 917.00.25.220

P08-067 Honeycomb core ECA 3.2-48 6mm thick 917.00.25.223

P08-068 Honeycomb core ECA 3.2-80 9.5mm thick 917.00.25.206

Material 

No. Material Name Notes Pilatus Part 

No.

Alternative Product /

Specification
EFFECTIVITY: All

20-31-00 Page 14

May 14/10

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

20-31-00 Page 15

May 14/10

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

P09-053 Glass fiber fabric 280g/m2 917.00.11.003

P09-054 Carbon fiber fabric 200g/m2 917.00.12.123

P09-055 Peel ply 51789 Natural -

Material 

No. Material Name Notes Pilatus Part 

No.

Alternative Product /

Specification
EFFECTIVITY: All

20-31-00 Page 16

May 14/10

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

20-31-00 Page 17

May 14/10

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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

20-31-00 Page 18

May 14/10

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
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CHAPTER 24 - ELECTRICAL POWER

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2 Mar 14/98

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2 Jun 14/92

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INTENTIONALLY BLANK
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CHAPTER 24 - ELECTRICAL POWER

TABLE OF CONTENTS

Subject

Chapter

Section

Subject Page Effectivity

ELECTRICAL POWER 24-00-00

Description and Operation 1 All

Maintenance Practices 201 All

AC GENERATION 24-20-00

Description and Operation 1 All

Adjustment / Test 501 Aircraft with AC 

power systems

STATIC INVERTERS 24-22-11

Removal / Installation 401 Aircraft with AC 

power systems

DC GENERATION 24-30-00

Description and Operation 1 All

Maintenance Practices 201 All

Adjustment / Test 501 All

STARTER-GENERATOR 24-31-11

Removal / Installation CONFIG 1 401 StarterGenerator 

978.91.23.101

Removal / Installation CONFIG 2 401 StarterGenerator 

978.91.23.201

Inspection / Check 601 All

VOLTAGE REGULATOR 24-31-12

Removal / Installation 401 All

BATTERY 24-32-00

Maintenance Practices 201 All

MAIN BATTERY 24-32-11

Removal / Installation 401 All

VOLT - AMMETER 24-34-11

Removal / Installation 401 All
24-TOC Page 2

May 14/10

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MAINTENANCE MANUAL

EXTERNAL POWER 24-40-00

Description and Operation 1 All

DC ELECTRICAL POWER DISTRIBUTION 24-60-00

Description and Operation 1 All

Subject

Chapter

Section

Subject Page Effectivity
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MAINTENANCE MANUAL

CHAPTER 27 - FLIGHT CONTROLS

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503 Jun 30/05

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CONFIG 1 502 Dec 14/91

503 Jun 14/92

504 Dec 14/91

Chapter

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CONFIG 2 502 Dec 14/91

503 Jun 14/92

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404 Mar 30/08

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506 Nov 30/03

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403 Jun 14/92

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502 Mar 14/98

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2 Nov 30/03

3 Nov 30/03

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502 Nov 30/03

503 Nov 30/03

504 Nov 30/03

505 Nov 30/03

CONFIG 2 501 Nov 30/03

502 Nov 30/03

503 Nov 30/03

504 Nov 30/03

505 Nov 30/03

506 Nov 30/03

27-45-01 201 Nov 30/03

CONFIG 2 202 Nov 30/03

203 Nov 30/03

Chapter

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CONFIG 1 402 Jun 14/92

CONFIG 2 401 Jun 14/92

402 Jun 14/92

403 Jun 14/92

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402 Jun 14/92

403 Jun 14/92

404 Jun 14/92

405 Jun 14/92

27-50-00 1 Mar 14/95

2 Mar 14/95

3 Mar 14/95

4 Mar 14/95

CONFIG 1 501 Mar 14/95

502 Mar 14/95

503 Mar 14/95

504 Mar 14/95

505 Mar 14/95

506 Mar 14/95

507 Mar 14/95

508 Mar 14/95

509 Mar 14/95

510 Mar 14/95

CONFIG 2 501 Mar 14/95

502 Mar 14/95

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402 Jun 14/92

403 Jun 14/92

404 Jun 14/92

27-52-12 601 Nov 30/08

602 Nov 30/08

603 Nov 30/08

604 Nov 30/08

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402 Jun 14/92

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CHAPTER 28 - FUEL

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702 Nov 30/08

CONFIG 2 701 Nov 30/08

702 Nov 30/08

703 Nov 30/08

704 Nov 30/08

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503 Sep 30/07

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402 Jun 14/91

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404 Jun 14/91

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404 Mar 14/98

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404 Sep 30/07

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402 Mar 14/98

403 Mar 14/98

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CONFIG 1 402 Nov 30/08

403 Nov 30/08

404 Nov 30/08

CONFIG 2 401 Nov 30/08

402 Nov 30/08

403 Nov 30/08

404 Nov 30/08

28-40-00 501 Sep 30/07

502 Sep 30/07

503 Sep 30/07

504 Sep 30/07

28-41-11 401 Mar 14/98

402 Mar 14/98

403 Mar 14/98

28-41-12 401 Jun 14/91

Chapter

Section

Subject Pages Date
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PC-6

MAINTENANCE MANUAL

CHAPTER 28 - FUEL

TABLE OF CONTENTS

Subject

Chapter

Section

Subject Page Effectivity

FUEL 28-00-00

Description and Operation 1 All

Maintenance Practices 201 All

FUEL TANK 28-10-00

Inspection / Check 601 All

Repair 801 All

INWARD VENT-VALVE FLOAT 28-10-11

Removal / Installation 401 All

UNDERWING FUEL SYSTEM 28-15-00

Description and Operation 1 Aircraft with u/w 

fuel system

UNDERWING FUEL SYSTEM - 

FUEL PUMP FILTER

28-15-00

Cleaning / Painting CONFIG 1 701 Aircraft with u/w 

fuel system and 

fuel transfer 

pump P/N 

968.84.30.301 

or

968.84.30.307

Cleaning / Painting CONFIG 2 701 Aircraft with u/w 

fuel system and 

fuel transfer 

pump P/N 

115.55.06.443

UNDERWING TANK 28-15-11

Removal / Installation 401 Aircraft with u/w 

fuel system

UNDERWING FUEL TANK PYLON 28-15-12

Removal / Installation 401 Aircraft with u/w 

fuel system

UNDERWING TANK FILTER 28-15-13

Removal / Installation 401 Aircraft with u/w 

fuel system
28-TOC Page 2

May 14/10

PC-6

MAINTENANCE MANUAL

UNDERWING FUEL-SYSTEM VENT-VALVE 

FLOAT

28-15-14

Removal / Installation 401 Aircraft with u/w 

fuel system

DISTRIBUTION 28-20-00

Adjustment / Test 501 All

ENGINE DRIVEN PUMP 28-20-03

Removal / Installation 401 All

Inspection / Check 601 All

FUEL FILTER ASSEMBLY 28-21-11

Removal / Installation 401 All

FUEL FILTER ELEMENT 28-21-12

Removal / Installation 401 All

Cleaning / Painting 701 Aircraft with SB 

126 (Air maze 

fuel filter)

FUEL SHUT-OFF VALVE 28-22-11

Removal / Installation 401 All

COLLECTOR TANK 28-23-11

Removal / Installation 401 All

AUXILIARY FUEL PUMP 28-23-12

Removal / Installation 401 All

WATER COLLECTOR TANK 28-23-13

Removal / Installation 401 All

FUEL TRANSFER PUMP 28-25-11

Removal / Installation CONFIG 1 401 Aircraft with u/w 

fuel system and 

fuel transfer 

pump P/N 

968.84.30.301 

or

968.84.30.307

Removal / Installation CONFIG 2 401 Aircraft with u/w 

fuel system and 

fuel transfer 

pump P/N 

115.55.06.443

Subject

Chapter

Section

Subject Page Effectivity
28-TOC Page 3

May 14/10

PC-6

MAINTENANCE MANUAL

INDICATING 28-40-00

Adjustment / Test 501 All

FUEL QUANTITY TRANSMITTER 28-41-11

Removal / Installation 401 All

FUEL QUANTITY INDICATOR 28-41-12

Removal / Installation 401 All

Subject

Chapter

Section

Subject Page Effectivity
28-TOC Page 4

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CHAPTER 34 - NAVIGATION

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504 May 14/10

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507 May 14/10

508 May 14/10
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STANDBY MAGNETIC COMPASS - ADJUSTMENT/TEST

1. General

A compass swing must be done when:

• the standby magnetic compass is replaced

• the deviation recorded on a previous compass swing is not the same on a check swing

• every two years (VFR operation)

• every year (IFR operation)

A check swing must be done when:

• a modification, repair or major replacement of magnetic material is done

• the aircraft has been struck by lightning

• the aircraft has been subject to magnetic crack detection examination

• an important change is made to the electrical or avionics installation circuits near the compass

• the aircraft has been in long term storage

• you think the system is not accurate

The procedure must be done on an approved compass calibration area using either a compass rose or 

datum compass to give the aircraft heading. 

The datum compass must be approximately 25 meters (75 feet) from the aircraft and aligned with the 

aircraft's longitudinal axis at each heading. The compass reading is then compared with the datum 

compass reading.

When you use a datum compass it is not necessary for the aircraft to be exactly on the applicable swing 

heading. Sightings taken within ± 2° of the heading are acceptable.

NOTE: When you use a datum compass you must remember to make allowance for the direction you 

are facing when you calculate the datum heading. Depending on the type of datum compass 

in use it may indicate 180° if you are facing the nose of the aircraft when it is positioned on a 

heading of 000°.

NOTE: A worked example of how to complete a compass swing data sheet and calculate the 

coefficients is given at Fig. 502.
EFFECTIVITY: All

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2. Compass Swing

A. Tools and Equipment

B. Procedure

(1) Put the aircraft in position on the compass calibration area.

(2) Remove the pitot tube cover.

(3) In the cockpit:

(a) Make sure the ANTI ICE switch is set to off.

(b) Make a note of the standby compass heading.

(c) Place a metallic object, e.g. a screwdriver, close to the standby compass and make 

the heading shown deflect by 30°.

(d) Wait 30 seconds and remove the metallic object.

(e) Wait until the standby compass has settled and make sure the heading shown is 

within ± 3° of the heading previously noted.

(4) Do this procedure again, deflecting the compass in the opposite direction.

(5) If the compass does not return to its original heading ± 3° it must be replaced.

(6) Start the engine (Ref. 71-00-00, Page Block 201).

(7) Set these systems to on:

• generator

• inverter (if installed)

• communications and navigation systems

• navigation lights and strobe or anti-collision beacons

CAUTION: DO NOT SET THE ANTI-ICE SWITCH TO ON FOR MORE THAN 30 SECONDS. 

LET THE COMPONENTS GET COLD BEFORE YOU REPEAT THE OPERATION.

(8) Position the aircraft on magnetic heading 000°, wait 10 seconds then:

(a) Set the ANTI ICE switch to on.

Part No. Description Remarks

E2/84/02 Corrector key or equivalent non-magnetic 

screwdriver

- Compass rose or

- Datum compass
EFFECTIVITY: All

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MAINTENANCE MANUAL

(b) Make a note of the heading shown on the compass and the datum heading.

(c) Set the ANTI ICE switch to off.

(d) Set the INSTR LIGHTS switch to on.

(e) Turn the INSTR LIGHTS through its full range and make sure the compass does not 

deflect. Set the INSTR LIGHTS switch to off.

(f) Do this procedure again on magnetic headings 090° and 180°.

(9) Calculate these values:

• the deviation on heading 000° (North)(compass heading minus datum heading)

• the deviation on heading 180° (South)(compass heading minus datum heading)

• the coefficient ‘C’ (deviation North minus deviation South divided by 2, sign 

changed, e.g. plus becomes minus)

• the ‘Corrected Compass Heading’ (compass heading South plus coefficient ‘C’)

(10) If the calculated coefficient is more than 2°:

(a) Adjust the ‘C’ corrector with the corrector key (or equivalent non-magnetic 

screwdriver) until the compass shows the ‘Make Compass Read’ value’.

(11) Position the aircraft on magnetic heading 270°, wait 10 seconds then:

(a) Set the ANTI ICE switch to on.

(b) Make a note of the heading shown on the compass and the datum heading.

(c) Set the ANTI ICE switch to off.

(d) Set the INSTR LIGHTS switch to on.

(e) Turn the INSTR LIGHTS through its full range and make sure the compass does not 

deflect. Set the INSTR LIGHTS switch to off.

(12) Calculate these values:

• the compass deviation on heading 090° (East)(compass heading minus datum 

heading)

• the compass deviation on heading 270° (West)(compass heading minus datum 

heading)

• the coefficient ‘B’ (deviation East minus deviation West divided by 2, sign changed)

• the ‘Corrected Compass Heading’ value (compass heading West plus 

coefficient ‘B’)

(13) If the calculated coefficient is more than 2°:

(a) Adjust the ‘B’ corrector with the corrector key (or equivalent non-magnetic 

screwdriver) until the compass shows the Corrected Compass Heading value.
EFFECTIVITY: All

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(14) Do a calibration swing as follows:

(a) Position the aircraft on each of the following headings, 000° (N), 090° (E), 180° (S), 

270° (W) and at each heading wait 10 seconds then:

(i) Set the ANTI ICE switch to on.

(ii) Make a note of the heading shown on the compass and the datum heading.

(iii) Set the ANTI ICE switch to off.

(b) Calculate the coefficient ‘A’ (deviation North + South + East + West divided by 4). If 

the error is more than 3° do the following procedure:

(i) Loosen the standby compass securing screws.

(ii) Slowly turn the compass to cancel the average error.

NOTE: If the average error is sign plus, rotate the unit to move the vertical 

lubber line right. If the average error is sign minus, rotate the unit to 

move the vertical lubber line left.

(iii) Tighten the compass securing screws.

(15) Repeat the procedure and make sure that the coefficient ‘A’ is less than 3°. If the 

coefficient ‘A’ cannot be made less than 3°, the compass must be replaced.

(16) Position the aircraft on magnetic heading 000°, wait 10 seconds then:

(a) Set the ANTI ICE switch to on.

(b) Make a note of the heading shown on the compass in the 'Steer' column of the 

deviation card (Ref. Fig. 501).

(c) Set the ANTI ICE switch to off.

(d) Do this procedure again on these headings:

• 030°, 060°, 090°, 120°, 150°, 180°, 210°, 240°, 270°, 300° and 330°.

(17) Shut down the engine (Ref. 71-00-00, Page Block 201).

(18) Remove the aircraft from the compass calibration area.

(19) Record the compass swing data in the aircraft log book.

CAUTION: LET THE PITOT TUBE BECOME COOL BEFORE YOU INSTALLTHE 

PROTECTIVE COVER.

(20) Install the pitot tube cover.
EFFECTIVITY: All

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MAINTENANCE MANUAL

3. Check Swing

A. General

A check swing consists of placing the aircraft on four headings 90° apart and comparing the 

deviations with those recorded on the deviation card. If there is any difference between these 

deviations a full compass swing must be done.

B. Tools and Equipment

C. Procedure

(1) Put the aircraft in position on the compass calibration area.

(2) Remove the pitot tube cover.

(3) In the cockpit, make sure the ANTI ICE switch is off.

(4) Start the engine (Ref. 71-00-00, Page Block 201).

(5) Set normal flight conditions with exception of the ANTI ICE switch:

• generator on-line

• inverter on (if installed)

• communications and navigation systems on

• navigation lights and strobe or anti-collision beacons on

CAUTION: DO NOT SET THE ANTI ICE SWITCH TO ON FOR LONGER THAN 30 

SECONDS. LET THE COMPONENTS GET COLD BEFORE YOU REPEAT THE 

OPERATION.

(6) Position the aircraft on magnetic heading 000° (N), wait 10 seconds then:

(a) Set the ANTI ICE switch to on.

(b) Make a note of the heading shown on the compass.

(c) Set the ANTI ICE switch to off.

(d) Do this procedure again on these headings 090° (E), 180° (S) and 270° (W).

(7) Compare the compass headings with the 'Steer' figure on the existing deviation card. If 

there is more than ± 3° difference on any heading a full compass swing must be done.

(8) Switch off the inverter, communications and navigation systems.

(9) Shut down the engine (Ref. 71-00-00, Page Block 201).

Part No. Description Remarks

- Compass rose or

- Datum compass
EFFECTIVITY: All

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MAINTENANCE MANUAL

(10) Remove the aircraft from the compass calibration area.

WARNING: LET THE PITOT TUBE BECOME COOL BEFORE YOU INSTALL THE 

PROTECTIVE COVER.

(11) Install the pitot tube cover.
EFFECTIVITY: All

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MAINTENANCE MANUAL

Compass Swing Data Sheet and Deviation Card

Figure 501

COMPASS SWING DATA SHEET

A/C TYPE ......................................................

SERIAL No. .......................................................

DATE .........................................................

PLACE .........................................................

STANDBY COMPASS SERIAL No

TRADESMAN

CORRECTION SWING (COEFFICIENTS C AND B)

APPROX. 

HEADING

DATUM

HEADING

(a)

COMPASS

HEADING

(b)

DEVIATION

+ OR -

(a) - (b)

TOTAL 

DEVIATION

COEFFICIENT=

TOTAL 

DEVIATION  2

CORRECTED

COMPASS 

HEADING

000 N C = 

180 S

090 E B =

270 W

CALIBRATION SWING (COEFFICIENT A)

APPROX. 

HEADING

DATUM

HEADING

(d)

COMPASS

HEADING

(e)

DEVIATION

+ OR -

(d) - (e)

TOTAL

DEVIATION

COEFFICIENT=

TOTAL 

DEVIATION  4

CORRECTED

HEADING

000 N

090 E A =

180 S

270 W

For N 30 60 E 120 150

Steer

For S 210 240 W 300 330

Steer

DATE
EFFECTIVITY: All

34-21-00 Page 508

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MAINTENANCE MANUAL

Compass Swing Data Sheet - Worked Example

Figure 502

COMPASS SWING DATA SHEET

A/C TYPE ................PC-6..........................

SERIAL No. ................HB-ABC............................

DATE .........14 March 95.........................................

PLACE ..................Stans...................................

STANDBY COMPASS SERIAL No. XXXXSC - 123

TRADESMAN XXXXXI Wood 

CORRECTION SWING (COEFFICIENTS C AND B)

APPROX. 

HEADING

DATUM

HEADING

(a)

COMPASS

HEADING

(b)

DEVIATION

+ OR -

(a) - (b)

TOTAL 

DEVIATION

COEFFICIENT=

TOTAL 

DEVIATION  2

CORRECTED

COMPASS 

HEADING

000 N 001 359 + 2

4

C =

XXX2 176

180 S 176 178 - 2

090 E 091 092 - 1

3

B =

XXX1.5 271.5

270 W 272 270 + 2

CALIBRATION SWING (COEFFICIENT A)

APPROX. 

HEADING

DATUM

HEADING

(d)

COMPASS

HEADING

(e)

DEVIATION

+ OR -

(d) - (e)

TOTAL

DEVIATION

COEFFICIENT=

TOTAL 

DEVIATION  4

CORRECTED

HEADING

000 N 0 359 + 1

XXX0

A =

XXXX0

359

090 E 090 091 - 1 091

180 S 178 179 - 1 179

270 W 272 271 + 1 271
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MAINTENANCE MANUAL

CHAPTER 57 - WINGS

LIST OF EFFECTIVE PAGES

Chapter

Section

Subject Pages Date

List of Effective 

Pages

1

2

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May 14/10

Table of Contents 1 Nov 30/08

2 Nov 30/08

57-00-00 1 Nov 30/03

401 Sep 30/07

402 Sep 30/07

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57-00-01 401 Jun 30/05

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57-00-02 401 Nov 30/08

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57-00-02 (Cont’d) 801 Nov 30/08

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57-51-11 401 Dec 14/91

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57-61-11 401 Jun 14/92

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57-62-11 401 Jun 14/92

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CHAPTER 79 - OIL

LIST OF EFFECTIVE PAGES

1.Chapter

Section

Subject Pages Date

List of Effective 

Pages

1

2

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402 Jun 14/92

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CHAPTER 79 - OIL

TABLE OF CONTENTS

Subject

Chapter

Section

Subject Page Effectivity

OIL 79-00-00

STORAGE

OIL COOLER 79-11-11

Removal / Installation 401 All

OIL FILTER 79-21-11

Removal / Installation 401 All

Cleaning / Painting 701 All

INDICATING

MAGNETIC CHIP DETECTOR 79-31-11

Removal / Installation 401 All

Adjustment / Test 501 All

OIL TEMPERATURE SENSOR 79-31-13

Removal / Installation 401 All
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EFFECTIVITY: All

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OIL TEMPERATURE SENSOR - REMOVAL/INSTALLATION

1. Job Set Up Information

A. Tools and Equipment

B. Expendable Parts

C. Consumable Materials (Ref. 20-31-00)

2. Procedures

A. Preparation

(1) Open and install a safety clip to the circuit breaker:

START GEN (Battery Bus CB panel)

(2) Drain the oil from the engine (Ref. 79-00-00, Page Block 301).

(3) Open the engine cowl PR1 (Ref. 71-10-00, Page Block 201).

B. Removal (Ref. Fig. 401)

(1) Disconnect the electrical plug (3) from the oil temperature sensor.

(2) Cut and remove the lockwire from the oil temperature sensor (2).

(3) Remove the oil temperature sensor (2).

(4) Remove and discard the O-ring (1).

(5) Install a blank to the opening.

C. Installation (Ref. Fig. 401)

(1) Remove the blank from the opening.

(2) Lubricate the new O-ring with clean engine oil (Material No. P10-004).

Part No. Description Remarks

110.88.07.065 Safety clip Circuit breaker hold open

IPC Ref. Description Remarks

79-31-09, Fig. 01 O-ring Qty 1

Material No. Description Remarks

P02-006 Lockwire Heat resistant

P10-004 Engine oil
EFFECTIVITY: All

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(3) Install the new O-ring (1) to the oil temperature sensor.

(4) Install the oil temperature sensor (2).

(5) Safety the oil temperature sensor (2) to the adjacent support bracket with lockwire 

(Material No. P02-006).

(6) Connect the electrical plug (3) to the oil temperature sensor (2).

D. Close-Up

(1) Fill the engine with oil to the correct level (Ref. 79-00-00, Page Block 301).

(2) Remove the safety clip and close the circuit breaker:

START GEN (Battery Bus CB panel)

(3) Make sure that the work area is clean and clear of tools and other items.

(4) Close the engine cowl PR1 (Ref. 71-10-00, Page Block 201).

(5) Do an engine ground run and make sure the engine oil temperature indicator operates 

(Ref. 71-00-00, Page Block 201).

(6) Make sure there are no oil leaks from the oil temperature sensor (2).
EFFECTIVITY: All

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Oil Temperature Sensor - Removal/Installation

Figure 401

6710

1

A

A

2

3
EFFECTIVITY: All

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