## 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 TRAN SMITTAL LETTER

FILE THIS TRANSMITTAL IN FRONT OF THE MANUAL CHECK THAT ALL PREVIOUS TRANSM ITTALS HAVE BEEN INCORPORATED If any Transmittals have not been received, please advise Technical Publicati ons Department, Pilatus Aircraft Ltd Page 2 of 2 

# 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 ChangeEFFECTIVITY: All 

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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 73EFFECTIVITY: All 

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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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INTENTIONALLY BLANKEFFECTIVITY: All 

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AIRWORTHINESS LIMITATIONS

1. General The Airworthiness Limitations section is EASA approved and variations mu st also be approved. The Airworthiness Limitations section is also FAA 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 belowEFFECTIVITY: All 

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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 IntervalEFFECTIVITY: All 

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Aileron/Flap Support-Brackets Examine (Fluorescent Dye Penetrant Inspection) 7000 flying hours or 14 years (whichever comes first) Item Maintenance Requirement IntervalEFFECTIVITY: All 

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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 (Mechanica l Trim) Overhaul 3500 flying hours Stabilizer Trim Actuator (Electrica l 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 

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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 pro peller 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 th e 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 IntervalEFFECTIVITY: 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

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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

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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

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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 V NE 05-51-04 1 All OVERSPEED - MORE THAN V FE 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 EffectivityEFFECTIVITY: All 

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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 extinguis her 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 yearsEFFECTIVITY: All 

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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 IntervalEFFECTIVITY: All 

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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 IntervalEFFECTIVITY: All 

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TIME LIMITED MAINTENANCE REQUIREMENTS

Item Maintenance Requirement Interval Chapter 24 - Electrical Power Hawker NiCad Battery (if insta lled) 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 we ight 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 yearEFFECTIVITY: All 

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Chapter 27 - Flight Controls Aileron Control Cablesand 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 IntervalEFFECTIVITY: All 

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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 IntervalEFFECTIVITY: All 

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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 CHIPcaption 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 IntervalEFFECTIVITY: All 

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UNSCHEDULED MAINTENANCE CHECKS

1. General Unscheduled maintenance checks are necessary if unusual incidents occur. These checks must be donebefore the next flight following the incident. Depending on the severity of an in cident, it may be advisable to re move 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 afte r 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 V NE 05-51-04 • Overspeed with flaps extended (V FE ) 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 inci dents 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, inaddition to P&WC EMM prescribed actions) • Lightning strike • Loss of oil pressure • Contamination by fire extinguisher agents • Flight through volcanic ash or smokeEFFECTIVITY: All 

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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 th at 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).EFFECTIVITY: All 

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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, PageBlock 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 thatthe 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 st rike (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

Chapter Section Subject Pages Date List of Effective Pages 1 2 May 14/10 May 14/10
Table of Contents 1 Jun 14/91
07-00-00 1 Jun 14/91 07-10-00 201 May 14/10 202 May 14/10 203 May 14/10 204 May 14/10 205 May 14/10 206 May 14/10 207 May 14/10 208 May 14/10
07-20-00 201 Jun 14/91

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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 barEFFECTIVITY: All 

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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 th e 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 cl ean 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 fuselageEFFECTIVITY: All 

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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 barEFFECTIVITY: All 

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(9) If necessary, remove the control-surface gust-locks. (10) Make sure that the work area is cl ean 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 CHOC KS 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 cl ean and clear of tools and other items. Part No. Description Remarks 6690.0036.01 Wheel chocks - Bottle jack - Metal bar (round)EFFECTIVITY: All 

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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 theninstalled 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 ina level attitude. Ropes attached to the wing attachment points and the fuselage tail permit the ai rcraft 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 co ntrol-surface gust-locks (Ref. 10-10-00, Pageblock 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)EFFECTIVITY: All 

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Aircraft Jack Points Figure 2016291 

# A C 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 BRACKETEFFECTIVITY: All 

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Aircraft Lifting with a Sling Figure 2026292 

# A



# A

LIFTING SLINGEFFECTIVITY: All 

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INTENTIONALLY BLANK

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CHAPTER 20 - STANDARD PRACTICES 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
20-00-00 1 Mar 14/98
201 Mar 14/98 202 Mar 14/98 203 Mar 14/98 204 Mar 14/98 205 Mar 14/98
20-10-01 201 Mar 14/98 202 Mar 14/98 203 Mar 14/98 204 Mar 14/98 205 Mar 14/98 206 Mar 14/98
20-10-02 201 Nov 30/03 202 Nov 30/03 203 Nov 30/03 204 Nov 30/03 205 Nov 30/03
20-10-03 201 Feb 28/10 202 Feb 28/10
20-10-04 701 Feb 28/10 702 Feb 28/10 20-31-00 1 May 14/10 2 May 14/10 3 May 14/10 4 May 14/10 5 May 14/10 6 May 14/10 7 May 14/10 8 May 14/10 9 May 14/10 10 May 14/10 11 May 14/10 20-31-00 (Cont’d) 12 May 14/10 13 May 14/10 14 May 14/10 15 May 14/10 16 May 14/10 17 May 14/10 18 May 14/10
20-40-00 1 Nov 30/03 2 Nov 30/03 3 Nov 30/03 4 Nov 30/03 5 Nov 30/03 6 Nov 30/03 7 Nov 30/03 8 Nov 30/03 9 Nov 30/03 10 Nov 30/03 11 Nov 30/03 12 Nov 30/03 13 Nov 30/03
201 Nov 30/03 202 Nov 30/03 203 Nov 30/03 204 Nov 30/03
801 Mar 30/08 802 Mar 30/08 20-40-10 201 Sep 30/07 202 Sep 30/07 20-50-01 201 Sep 30/07 202 Sep 30/07 203 Sep 30/07 204 Sep 30/07 Chapter Section Subject Pages Date

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

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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 -EFFECTIVITY: All 

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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 / SpecificationEFFECTIVITY: All 

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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 / SpecificationEFFECTIVITY: All 

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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 / SpecificationEFFECTIVITY: All 

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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 / SpecificationEFFECTIVITY: All 

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

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

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

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

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

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

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

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

# 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 / SpecificationEFFECTIVITY: 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 / SpecificationEFFECTIVITY: 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 50cm 3 910.42.12.128 P08-044 Resin, epoxy, Dexter Hysol AE 9395 2 part 910.42.72.169
P08-045 Sealant, sili con, translucent, RTV 907.13.13.102 MIL-A-46106
P08-046 Sealant, 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 / SpecificationEFFECTIVITY: 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/m 2917.00.11.002 WL8.4548.60 P09-032 Carbon fiber fabric Not used now P09-033 Not used now P09-034 Copper wire mesh Lightning strike protection 72 g/m 2 919.02.30.111 P09-035 Not used now P09-036 Tape adhesive 0,64 x 19 mm (0.025 x 0.75 in.) 917.40.67.312 P09-037 Spiralwrap 917.99.90.002 Material

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

# 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 / SpecificationEFFECTIVITY: 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 Aeros hell Fluid 41 (20 liters) Aeroshell Fluid 41 (5 liters) Replaces P10-003 908.14.12.017 908.14.12.018 MIL-PRF-5606 (was MIL-H-5606)
P10-018 CPC-Ardrox AV 15 Ardrox / Dinitrol AV 15 Material

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

# 20-31-00 Page 17 May 14/10 

# PC-6 MAINTENANCE MANUAL

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

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

# 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

# 24-LEP Page 1 May 14/10 

# PC-6 MAINTENANCE MANUAL

CHAPTER 24 - ELECTRICAL POWER 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
24-00-00 1 Jun 14/92
201 Jun 14/92
24-20-00 1 Jun 14/92 2 Jun 14/92
501 Jun 14/92
24-22-11 401 Jun 14/92 402 Jun 14/92 403 Jun 14/92
24-30-00 1 Jun 14/92 2 Jun 14/92 3 Jun 14/92 4 Jun 14/92 5 Jun 14/92 6 Jun 14/92 7 Jun 14/92
201 Jun 14/92 202 Jun 14/92 501 Sep 30/07 502 Sep 30/07 503 Sep 30/07 504 Sep 30/07
24-31-11 401 Jun 30/09 CONFIG 1 402 Jun 30/09 403 Jun 30/09 404 Jun 30/09
CONFIG 2 401 Jun 30/09 402 Jun 30/09 403 Jun 30/09 404 Jun 30/09 24-31-11 (Cont’d) 601 Jun 30/05 602 Jun 30/05 603 Jun 30/05 604 Jun 30/05
24-31-12 401 Jun 14/92 402 Jun 14/92 403 Jun 14/92
24-32-00 201 Dec 14/91 202 Dec 14/91
24-32-11 401 Nov 30/03 402 Nov 30/03 403 Nov 30/03
24-34-11 401 Dec 14/91
24-40-00 1 Mar 14/98 2 Mar 14/98
24-60-00 1 Jun 14/92 2 Jun 14/92 3 Jun 14/92 Chapter Section Subject Pages Date

# 24-LEP Page 2 May 14/10 

# PC-6 MAINTENANCE MANUAL

INTENTIONALLY BLANK

# 24-TOC Page 1 May 14/10 

# PC-6 MAINTENANCE MANUAL

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 24-31-11Removal / Installation CONFIG 1 401 StarterGenerator 978.91.23.101Removal / 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 

# PC-6 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

# 27-LEP Page 1 May 14/10 

# PC-6 MAINTENANCE MANUAL

CHAPTER 27 - FLIGHT CONTROLS 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 Jun 30/09 2 Jun 30/09 3 Jun 30/09 4 Jun 30/09
27-00-00 1 Jun 14/92 2 Jun 14/91 201 Sep 30/07 202 Sep 30/07 203 Sep 30/07 204 Sep 30/07 205 Sep 30/07 206 Sep 30/07 207 Sep 30/07 208 Sep 30/07
601 Mar 30/08 602 Mar 30/08 603 Mar 30/08 604 Mar 30/08
27-05-00 401 Jun 30/09 402 Jun 30/09 403 Jun 30/09 404 Jun 30/09 405 Jun 30/09 406 Jun 30/09 407 Jun 30/09 408 Jun 30/09
501 Jun 30/09 502 Jun 30/09 503 Jun 30/09 504 Jun 30/09
27-10-00 1 Jun 14/92 2 Jun 14/92
501 Mar 14/98 502 Mar 14/98 27-10-00 (Cont’d) 503 Mar 14/98 504 Mar 14/98 505 Mar 14/98 506 Mar 14/98
27-12-11 401 Jun 14/92 402 Jun 14/92 403 Jun 14/92 404 Jun 14/92 405 Jun 14/92 27-14-11 401 Sep 30/07 402 Sep 30/07 403 Sep 30/07 404 Sep 30/07 501 Sep 30/07 502 Sep 30/07
27-15-00 501 Feb 28/10 502 Feb 28/10 503 Feb 28/10 504 Feb 28/10 27-15-13 401 Sep 30/07 402 Sep 30/07
27-20-00 1 Jun 14/92 2 Jun 14/92
501 Jun 30/05 502 Jun 30/05 503 Jun 30/05 504 Jun 30/05 505 Jun 30/05
27-22-11 401 Jun 14/92 402 Jun 14/92 403 Jun 14/92
27-25-00 501 Dec 14/91 CONFIG 1 502 Dec 14/91 503 Jun 14/92 504 Dec 14/91 Chapter Section Subject Pages Date

# 27-LEP Page 2 May 14/10 

# PC-6 MAINTENANCE MANUAL

27-25-00 (Cont’d) 501 Dec 14/91 CONFIG 2 502 Dec 14/91 503 Jun 14/92
27-25-13 401 Mar 30/08 402 Mar 30/08 403 Mar 30/08 404 Mar 30/08
27-30-00 1 Jun 14/92 2 Jun 14/92
501 Nov 30/03 502 Nov 30/03 503 Nov 30/03 504 Nov 30/03 505 Nov 30/03 506 Nov 30/03
27-31-11 401 Jun 14/92 402 Jun 14/92 403 Jun 14/92
27-32-00 501 Mar 14/98 502 Mar 14/98
27-40-00 1 Nov 30/03 2 Nov 30/03 3 Nov 30/03
CONFIG 1 501 Nov 30/03 502 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 Section Subject Pages Date 27-45-11 401 Jun 14/92 CONFIG 1 402 Jun 14/92
CONFIG 2 401 Jun 14/92 402 Jun 14/92 403 Jun 14/92
27-45-12 401 Jun 14/92 402 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
27-52-11 401 Jun 14/92 402 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
27-53-11 401 Jun 14/92 402 Jun 14/92 Chapter Section Subject Pages Date

# 28-LEP Page 1 May 14/10 

# PC-6 MAINTENANCE MANUAL

CHAPTER 28 - FUEL 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 3 May 14/10 4 May 14/10
28-00-00 1 Nov 30/02 2 Nov 30/02 3 Nov 30/02 4 Nov 30/02 5 Nov 30/02
201 Jun 14/91 202 Jun 14/91
28-10-00 601 Dec 14/91 602 Dec 14/91
801 Mar 14/95 802 Mar 14/95 803 Mar 14/95
28-10-11 401 Jun 30/09 402 Jun 30/09 403 Jun 30/09 404 Jun 30/09
28-15-00 1 Mar 14/95 2 Mar 14/95 3 Mar 14/95 4 Mar 14/95
CONFIG 1 701 Nov 30/08 702 Nov 30/08
CONFIG 2 701 Nov 30/08 702 Nov 30/08 703 Nov 30/08 704 Nov 30/08
28-15-11 401 Jun 14/91 402 Jun 14/91 28-15-11 (Cont’d) 403 Jun 14/91
28-15-12 401 Jun 14/91 402 Jun 14/91 403 Jun 14/91
28-15-13 401 Mar 14/98 402 Mar 14/98
28-15-14 401 Feb 28/10 402 Feb 28/10 403 Feb 28/10 404 Feb 28/10 28-20-00 501 Sep 30/07 502 Sep 30/07 503 Sep 30/07 504 Sep 30/07
28-20-03 401 Nov 30/03 402 Nov 30/03 403 Nov 30/03 404 Nov 30/03
601 Nov 30/03
28-21-11 401 Jun 14/91 402 Jun 14/91 403 Jun 14/91 404 Jun 14/91
28-21-12 401 Mar 14/98 402 Mar 14/98 403 Mar 14/98 404 Mar 14/98 405 Mar 14/98
701 Mar 14/95
28-22-11 401 Jun 14/91 402 Jun 14/91 403 Jun 14/91 404 Jun 14/91 Chapter Section Subject Pages Date

# 28-LEP Page 2 May 14/10 

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28-23-11 401 Mar 14/98 402 Mar 14/98 403 Mar 14/98 404 Mar 14/98 28-23-12 401 Sep 30/07 402 Sep 30/07 403 Sep 30/07 404 Sep 30/07
28-23-13 401 Mar 14/98 402 Mar 14/98 403 Mar 14/98
28-25-11 401 Nov 30/08 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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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 Operat ion 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

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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

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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

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CHAPTER 34 - NAVIGATION 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 Mar 14/95
34-11-00 1 Mar 14/95 2 Mar 14/95
34-11-00 501 Feb 28/10 502 Feb 28/10 34-21-00 501 May 14/10 502 May 14/10 503 May 14/10 504 May 14/10 505 May 14/10 506 May 14/10 507 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 oravionics 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. Th e 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 co mpass 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 screwdrive r, close to the standby compass and make the heading shown deflect by 30°. (d) Wait 30 seconds and re move 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 an d strobe or anti-collision beacons CAUTION: DO NOT SET THE ANTI-ICE SWITCH TOON 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 compassEFFECTIVITY: All 

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(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 mi nus 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 followin g 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 No rth + 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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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 cond itions 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 SWITCHTO ON FOR LONGER THAN 30 SECONDS. LET THE COMPONENTS GE T 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, comm unications and navigation systems. (9) Shut down the engine (Ref. 71-00-00, Page Block 201).

Part No. Description Remarks - Compass rose or - Datum compassEFFECTIVITY: All 

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(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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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 DATEEFFECTIVITY: All 

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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. XXXX 

### SC - 123
TRADESMAN XXXXX

### I 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 = 

### XXX 2 176 180 S 

### 176 178 - 2

090 E 

### 091 092 - 1 3 B = 

### XXX 1.5 271.5 270 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 = XXXX

### 0 359

090 E 

### 090 091 - 1 091

180 S 

### 178 179 - 1 179

270 W 

### 272 271 + 1 271

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CHAPTER 57 - WINGS 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 Nov 30/08 2 Nov 30/08
57-00-00 1 Nov 30/03 401 Sep 30/07 402 Sep 30/07 403 Sep 30/07 404 Sep 30/07 405 Sep 30/07 406 Sep 30/07 407 Sep 30/07 408 Sep 30/07
57-00-01 401 Jun 30/05 402 Jun 30/05 403 Jun 30/05
601 Jun 30/05 602 Jun 30/05
57-00-02 401 Nov 30/08 402 Nov 30/08 403 Nov 30/08 404 Nov 30/08 405 Nov 30/08 406 Nov 30/08
601 Nov 30/08 602 Nov 30/08 603 Nov 30/08 604 Nov 30/08 605 Nov 30/08 606 Nov 30/08 607 Nov 30/08 608 Nov 30/08 609 Nov 30/08 610 Nov 30/08 611 Nov 30/08 612 Nov 30/08 613 Nov 30/08 614 Nov 30/08 57-00-02 (Cont’d) 801 Nov 30/08 802 Nov 30/08 803 Nov 30/08 804 Nov 30/08 805 Nov 30/08 806 Nov 30/08
57-51-11 401 Dec 14/91 402 Dec 14/91 403 Dec 14/91
57-61-11 401 Jun 14/92 402 Jun 14/92 403 Jun 14/92 404 Jun 14/92 405 Jun 14/92
57-62-11 401 Jun 14/92 402 Jun 14/92 Chapter Section Subject Pages Date

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CHAPTER 79 - OIL LIST OF EFFECTIVE PAGES

1. 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
79-11-11 401 Jun 14/92 402 Jun 14/92 403 Jun 14/92
79-21-11 401 Mar 14/98 402 Mar 14/98 403 Mar 14/98
701 Dec 14/91 702 Dec 14/91
79-31-11 401 Mar 14/98 402 Mar 14/98 403 Mar 14/98
501 Mar 14/98 502 Mar 14/98 79-31-13 401 May 14/10 402 May 14/10 403 May 14/10 404 May 14/10

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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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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 oilEFFECTIVITY: 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) tothe 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 cl ean 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 4016710 1 

# A



# A

2

3EFFECTIVITY: All 

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