~PILATUS~ 12-A-AM-00-00-00-1 

UNCLASSIFIED 

Model type- PC-12, PC-12/45, PC-12/47 

Aircraft Maintenance Manual (AMM) 

Document No. 02049 

12-A-AM-00-00-00-1 

Effectivity: All 12-A-AM-00-00-00-1 

UNCLASSIFIED 

e PILATUS AIRCRAFT LTD. CH-6371 STANS. SWITZERLAND 
I 

~PILATUS~ 12-A-AM-00-00-00-1 

UNCLASSIFIED 

AMM LIST OF REVISIONS 

1 List of Revisions 

Rev No. Date of Issue 

All previous revisions incorporated. 

18 Sep 25/08 

19 Mar 01/09 

20 

21 Dec 15/09 

22 Apr 15/10 

23 Mar 30/11 

24 Dec 20/11 

25 Jan 30/12 

26 Dec 15/12 

27 Dec 15/13 

28 May 31/14 

Effectivity: ALL 

Date Inserted Signature 

Oct 16/08 Pilatus 

Mar 23/09 Pilatus 

Revision 20 issued with Revision 21 

Dec 15/09 

Apr 15/10 

Mar 30/11 

Dec 20/11 

Jan 30/12 

Dec 15/12 

Dec 15/13 

May 31/14 - -

End of data module 

UNCLASSIFIED 

Pilatus 

Pilatus 

Pilatus 

Pilatus 

Pi latus 

Pilatus 

Pilatus 

Pi latus .. 

12-A-OO-OO-OO-OOA-004A-A 

2014-05-05 Page 1 
~PILATUS~ 12-A-AM-00-00-00-1 

UNCLASSIFIED 

PC-12, PC-12/45, PC-12/47 GENERAL- AIRCRAFT MAINTENANCE MANUAL 

LIST OF EFFECTIVE CHAPTERS 

Table of Contents 

PC-12, PC-12/45, PC-12/47 GENERAL- AIRCRAFT MAINTENANCE MANUAL- LIST OF 

EFFECTIVE CHAPTERS ........................................................................................................... . 

Index of Tables 

References ............................................................................................................ . 

References 

Table 1 References 

Data modulerTechnical publication Title 

None 

Chapter Number 

00 

04 .~•a • 

05 

06 

07 

08 

09 

10 

11 

12 

20 

21 

22 

23 

24 

25 

26 

27 

28 

29 

30 

31 

32 

33 

34 

35 

52 

53 

Description 

Chapter Title 

GENERAL 

STRUCTURAL,COMPONENTAND 

MISCELLANEOUS 

TIME LIMITS/MAINTENANCE CHECKS 

DIMENSIONS AND AREAS GENERAL 

LIFTING AND SHORING 

LEVELLING AND WEIGHING 

TAXIING AND TOWING 

PARKING AND MOORING 

PLACARDS AND MARKINGS 

SERVICING 

EQUIPMENT HANDLING 

AIR CONDITIONING 

AUTO FLIGHT 

COMMUNICATIONS 

ELECTRICAL POWER 

EQUIPMENT AND FURNISHINGS 

FIRE PROTECTION 

FLIGHT CONTROLS 

FUEL SYSTEM 

HYDRAULIC POWER 

ICE AND RAIN PROTECTION 

INDICATING/RECORDING SYSTEMS 

LANDING GEAR 

LIGHTS 

NAVIGATION 

OXYGEN SYSTEM 

DOORS 

FUSELAGE 

12-A-00-00-00-00A-001 A-A 

12-A-04-00-00-00A-OOOA-A 

12-A-05-00-00-00A-018A-A 

12-A-06-00-00-00A-040A-A 

12-A-07 -OO-OO-OOA-040A-A 

12-A-08-00-00-00A-040A-A 

12-A-09-00-00-00A-040A-A 

12-A-1 O-OO-OO-OOA-040A-A 

12-A-11-00-00-00A-040A-A 

12-A-12-00-00-00A-040A-A 

12-A-20-00-00-00A-901 A-A 

12-A-21-00-00-00A-040A-A 

12-A-22-00-00-00A-040A-A 

12-A-23-00-00-00A-040A-A 

12-A-24-00-00-00A-040A-A 

12-A-25-00-00-00A-040A-A 

12-A-26-00-00-00A-040A-A 

12-A-27 -00-00-00A-040A-A 

12-A-28-00-00-00A-040A-A 

12-A-29-00-00-00A-040A-A 

12-A-30-00-00-00A-040A-A 

12-A-31-00-00-00A-040A-A 

12-A-32-00-00-00A-040A-A 

12-A-33-00-00-00A-040A-A 

12-A-34-00-00-00A-040A-A 

12-A-35-00-00-00A-040A-A 

12-A-52-00-00-00A-040A-A 

12-A-53-00-00-00A-040A-A 

Page 

Page 

Effectivity: All 12-A-OO-OO-OO-OOA-009A-A 

UNCLASSIFIED 2014-05-22 Page 1 
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Chapter Number 

55 

56 

57 

61 

71 

72 

73 

74 

76 

77 

78 

79 

80 

Effectivity: All 

Chapter Title 

STABILIZERS 

WINDOWS 

WINGS 

PROPELLER 

POWER PLANT 

ENGINE 

UNCLASSIFIED 

ENGINE FUEL AND CONTROL 

IGNITION SYSTEM (MSN 101-320, 322-

400) 

ENGINE CONTROLS 

ENGINE INDICATING 

EXHAUST 

ENGINE OIL SYSTEM 

ENGINE STARTING 

End of data module 

UNCLASSIFIED 

12-A-AM-00-00-00-1 

12-A-55-00-00-00A-040A-A 

12-A-56-00-00-00A-040A-A 

12-A-57 -00-00-00A-040A-A 

12-A-61-00-00-00A-040A-A 

12-A-71-00-00-00A-040A-A 

12-A-72-00-00-00A-040A-A 

12-A-73-00-00-00A-040A-A 

12-A-7 4-00-00-00A-040A-A 

12-A-76-00-00-00A-040A-A 

12-A-77 -OO-OO-OOA-040A-A 

12-A-78-00-00-00A-040A-A 

12-A-79-00-00-00A-040A-A 

12-A-80-00-00-00A-040A-A 

12-A-00-00-00-00A-009A-A 

2014-05-22 Page 2 
~PILATUS:;r 

UNCLASSIFIED 

STRUCTURAL, COMPONENT AND MISCELLANEOUS 

AIRWORTHINESS LIMIT A T/ONS 

Table of Contents Page 

STRUCTURAL, COMPONENT AND MISCELLANEOUS- AIRWORTHINESS LIMITATIONS. 

1 General............................................................................................................. ...... 4 

2 Structural Limitations.............................................................................................. 5 

3 Component Limitations........................................................................................... 5 

4 Miscellaneous limitations....................................................................................... 6 

5 Supplemental Structural Inspection Document...................................................... 7 

5.1 Limit of Validity....................................................................................................... 7 

5.2 Authorisation........................................................................................................... 7 

5.3 Deviation from Type Design................................................................................... 7 

5.4 Supplemental Corrosion Prevention and Control Program (CPCP). ...................... 8 

5.5 Damage Tolerance Evaluation............................................................................... 8 

6 Component Life....... ............................................................................................... 8 

7 Inspection Program................................................................................................ 8 

Index of Tables Page 

1 

2 

3 

4 

5 

6 

References ...................... ..................................................................................... .. 

Structural Limitations ........................................................................................ ..... . 

Component Limitations .......................................................................................... . 

Miscellaneous Limitations ................................................................. .................... . 

Component Life ..................................................................................................... . 

Supplemental Stn1cturallnspection Program ....................................................... .. 

References 

Table 1 References 

Data module!Technlcal publication Title 

12-A-05-20-30-00A-280A-A 

12 -A-20-40-00-00A-90 1 A-A 

\)PPLEMENTAL STRUCTURAL INSPECTION 

DOCUMENT - INSPECTIONS 

CORROSION CONTROL -MAINTENANCE 

PRACTICES 

1 

5 

5 

6 

8 

9 

12-A-27 -00-01 -00A-352A-A FLIGHT CONTROLS- CONTROL RODS - MAGNETIC 

PARTICLE INSPECTION 

12-A-27 -00-0 1-00A-353A-A 

12-A-27-1 0-00-00A-31 OA-A 

12-A-27 -1 0-08-00A-3528-A 

12-A-27 -1 0-08-00A-353A-A 

12-A-27 -1 0-08-00A-3538-A 

Effectivity: All 

FLIGHT CONTROLS- CONTROL RODS • EDDY 

CURRENT INSPECTION 

AILERON CONTROL SYSTEM - EXAMINE 

AILERON CONTROL SYSTEM - FUSELAGE 

BELLCRANK - MAGNETIC PARTICLE INSPECTION 

AILERON CONTROL SYSTEM- OUTER WING 

BELLCRANK - EDDY CURRENT INSPECTION 

AILERON CONTROL SYSTEM - FUSELAGE 

BELLCRANK - EDDY CURR_ENT INSPECTION 

12 -A-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 1 
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Data moduleffechnlcal publication 

12-A-27 -1 0-09-00A-353A-A 

12-A-27 -20-00-<lOA-31 OA-A 

12-A-27 -20-<l4-<lOA-353A-A 

12-A-27 -20-05-0QA-31 OA-A 

12-A-27 -30-00-0QA-31 OA-A 

27 -30-05-00A-353A-A 

12-A-27 -40-00-<lOA-903A-A 

12 -A-27 -40-{)2 -OOA-920A-A 

12-A-27 -51-00-<lOA-31 OA-A 

12-A-27 -51-00-<lOA-313A-A 

12-A-27 -51-00-00A-353A-A 

12-A-27 -51-01-00A-353A-A 

12-A-27 -51-02-0QA-353A-A 

12-A-27 -51-03-00A-353A-A 

12 -A-32 -20-06-00A-313A-A 

12 -A-52 -1 0-00-00A-31 Ol\-.8 

12-A-52-20-00-QOA-31 QA-A 

12-A-52-30-00-00A-31 OA-A 

12 -A-53-00-00-00A-31 OA-A 

12-A-53-00-00-<lOA-353A-A 

12 -A-53-1 0-00-00A-31 OA-A 

12 -A-53-1 O-<l6-0 1 A-353A-A 

12 -A-53-1 0-16-00A-31 OA-A 

12-A-53-20-00-00A-31 OA-A 

12-A-53-20-02-00A-31 OA-A 

Effectivity: All 

UNCLASSIFIED 

Title 

AILERON CONTROL SYSTEM - FUSELAGE CABLE 

QUADRANT- EDDY CURRENT INSPECTION 

RUDDER CONTROL SYSTEM - EXAMINE 

RUDDER CONTROL SYSTEM - BELLCRANK - EDDY 

CURRENT INSPECTION 

RUDDER CONTROL SYSTEM - CABLE QUADRANT -

EXAMINE 

ELEVATOR CONTROL SYSTEM- EXAMINE 

ELEVATOR CONTROL SYSTEM- CONTROL LEVER 

- EDDY CURRENT INSPECTION 

HORIZONTAL STABILIZER TRIM- ADJUSTMENT/ 

TEST 

HORIZONTAL STABILIZER TRIM- TRIM ACTUATOR 

FAILSAFE PLATES- REMOVAUINSTALLATION 

FLAP DRIVE SYSTEM - EXAMINE 

FLAP DRIVE SYSTEM - IN SITU INSPECTION/CHECK 

FLAP DRIVE SYSTEM - IN SITU EDDY CURBf.t'JT 

IN SPECTIQJ~ 

FLAP DRIVE SYSTEM- WING- INBOARD 

MECHANISM - EDDY CURRENT INSPECTION 

FLAP DRIVE SYSTEM- WING - CENTE~ 

MECHANISM - EDDY CURRENT INSPECTION 

FLAP DRIVE SYSTEM -WING - OUTBOARD 

MECHANISM - EDDY CURRENT INSPECTION 

DRAG LINK RIGHT PART- INSPECTLQN/CHECK 

PASSENGER/CREW DOOR - EXAMINE 

EMERGENCY EXIT - EXAMINE 

CARGO DOOR - EXAMINE 

FUSELAGE -ANTENNA STRUCTURE - EXAMINE 

FUSELAGE -ANTENNA STRUCTURE- EDDY 

CURRENT INSPECTION 

FORWA8D FUSELAGE - EXAMINE 

FORWARDFUSELAGE-FRAME10LONGERONSEDDY CURRENT INSPECTION 

FORWARD FUSELAGE-_ WINDOW STRUCTURE -

EXAMINE 

CENTER FUSELAGE - EXAMINE 

CENTER FUSELAGE FRAMES- CARRY THROUGH 

FRAMES - EXAMINE 

12-A-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 2 
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Data moduleiTechnlcal publication 

12-A-53-20-02-00A-353A-A 

12 -A-53-30-00-00A-31 OA-A 

12-A-53-30-02-00A-353A-A 

12-A-55-00-00-00A-353A-A 

12-A-55-20-00-00A-31 OA-A 

12-A-55-20-01-00A-353A-A 

12-A-55-30-00.QOA-31 OA-A 

12-A-55-30-02-00A-353A-A 

12-A-55-30-03.QOA-353A-A 

12-A-55-40-00-00A-31 OA-A 

l2-A-55=40-Q5-QOA-353A-A 

12-A-56-00-00-QOA-313A-A 

12-A-56-11-01-QOA-310A-A 

12-A-56-11-02-0QA-31 OA-A 

12-A-57 -00-00-00A-31 OA-A 

j 2 -A-57 -00-03-00A-353A-A 

12-A-57 -00-03-01A-353A-A 

~ 2-A-57 -20-05-00A-353A-A 

12-A-57 -20-1 O-OOA-353A-A 

12-A-57 -20-1 O-OOA-353B-A 

12-A-57 -20-1 O-OOA-353C-A 

12-A-57 -20-1 O-OOA-353D-A 

12-A-57 -60-0Q..QOA-31 OA-A 

12-A-57 -60-06-00A-353A-A 

Effectivity: All 

UNCLASSIFIED 

Title 

CENTER FUSELAGE FRAMES- CARRY THROUGH 

FRAMES - EDDY CURRENT INSPECTION 

REAR FUSELAGE - EXAMINE 

REAR FUSEL:AGE FRAMES - EDDY CURRENT 

INSPECTION 

VERTICAL STABILIZER ATTACHMENT FITTINGS -

EDDY CURRENT INSPECTION 

ELEVATORS - EXAMINE 

ELEVATOR DRIVE LEVER AND HINGE- EDDY 

CURRENT INSPECTION 

VERTICAL STABILIZER- EXAMINE 

VERTICAL STABILIZER- PITCiilB.!.f¥1 ACTUATOR 

ATTACHMENT- EDDY CURRENT INSPECTION 

VERTICAL STABILIZER SPARS - EDDY CURRENT 

INSPECTION 

RUDDER - EXAMINE. 

RUDDER HINGE - EDDY CURRENT INSPECTION 

WINDOWS - INSPECTIONICHECK 

WINDSHIELD - EXAMINE 

COCKPIT SIDE WINDOWS - EXAMINE 

WINGS - EXAMINE 

WING AND FUSELAGE ATTACHMENT FITTINGSEDDY CURRENT INSPECTION 

WING AND FUSELAGE ATTACHMENT FITTINGS -

HOLLOW BOLTS - EDDY CURRENT INSPECTION 

WING STRUCTURE - RIBS - EDDY CURRENT 

INSPECTION - RIB 6 STRAP 

WING STRUCTURE- SPARS AND AUXILIARY 

STRUCTURE -MAIN SPAR - EDDY CURRENT 

INSPECTION 

WING STRUCTURE - SPARS AND AUXILIARY 

STRUCTURE - REAR SPAR - EDDY CURRENT 

INSPECTION 

WING STRUCTURE- SPARS AND AUXILIARY 

STRl.J.CTURE- REAR SPAR - EDDY CURRENT 

INSPECTION 

WING STRUCTURE- SPARS AND AUXILIARY 

STRUCTURE- MAIN SPAR- RIB 6 STRAP 

FASTENER - EDDY CURRENT INSPECTION 

AILERONS - EXAMINE 

AILERON HINGE - EDDY CURRENT INSPECTION 

12-A-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 3 
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UNCLASSIFIED 

Data module!Technical publication Title 

12-A-71-00-05-00A-352A-A POWERPLANT MOUNTING FRAME - MAGNETIC 

PARTICLE INSPECTION 

Description 

1 General 

The Airworthiness Limitations section is EASA appro~ed 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 Parts 43.16 and 

91.403 of the Federal Aviation Regulations unless an alternate program has been FAA approved. 

Refer to the Pilot's Operating Handbook/Airplane Flight Manual for the approved seats and seat limitations. 

On PC-12147 aircraft, do not install the following components: 

Nose Landing Gear 

532.20.12.038 with serial numbers AM 001 thru 054 (Ref. Pilatus Service Bulletin 32-016). 

532.20.12.039 with serial numbers AM 001 thru 054 (Ref. Pilatus Service Bulletin 32-016). 

532.20.12.140 all (Ref. Pilatus Service Bulletin 32-014). 

Main Landing Gear 

532.10.12.049 with serial numbers AM 001 thru 053 (Ref. Pi latus Service Bulletin 32-015/016/018). 

532.10.12.050 with serial numbers AM 001 thru 053 (Ref. Pilatus Service Bulletin 32-015/016/018). 

532.10.12.077 with serial numbers AM 001 thru 229 and all without primer and painted head (Ref. Pilatus Service 

Bulletin 32-012/018). 

532.10.12.110 without marl<ing "A r or "VLG" (Ref. Pi latus Service Bulletin 32-015). 

Main Landing Gear Shock Absorber 

532.10.12.175 with serial numbers AM 001 thru 107 (Ref. Pilatus Service Bulletin 32-016). 

Main Landing Gear Actuators 

960.30.01.103 with serial numbers 830E thru 881 E (Ref. Pilatus Service Bulletin 32-017). 

Flaps 

FCWU 99-3 with serial numbers lower than 10000 and all Vickers Flap Actuators (Part No's 978. 73.20.301, 

978.73.20.302/303/304 and 306). 

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2 Structural Limitations 

Table 2 Structural Limitations 

Structure Life 

Fuselage and associated structure Pre SB 0~009 20,000 flying hours or 27,000 landings. 

whichever comes first 

Post SB 0~09 25,000 flying hours or 30,000 landings, 

whichever comes first 

Wing structure Pre SB 0~009 20,000 flying hours or 27,000 landings, 

whichever comes first 

Post SB 04.()09 25,000 flying hours or 30,000 landings. 

whichever comes first 

Tail structure Pre SB 0~009 20,000 flying hours or 27,000 landings, 

whichever comes first 

Post SB 0~09 25,000 flying hours or 30,000 landings, 

whichever comes first 

Beyond 25,000 flying hours or 30,000 landings (whichever comes first) refer to the Supplemental Structural 

Inspection Document (SSID) at Para 5 and 12·A-05-20-30-00A-280A-A for supplemental structural inspections. 

3 Component Limitations 

Table 3 Component Limitations 

Component Life 

Engine rotor components P&WC SB 14002 (latest revision) 

Engine mounting frame Pre SB 0~09 20,000 flying hours or 27,000 landings, 

whichever comes first 

Post SB 0~09 25,000 flying hours or 30,000 landings, 

whichever comes first 

Beyond 25,000 flying hours or 30,000 landings (whichever comes first) refer to the Supplemental Structural 

Inspection Document (SSID) at Para 5 and 12-A-05-20-30-00A-280A-A for supplemental structural inspections. 

Engine mounting frame, replace all bolts. washers and 11 ,000 flying hours 

nuts 

Pitch trim actuator 20,000 flying hours or 27,000 landings, whichever comes 

first 

Flap actuator (Part No. 978.73.20.307, 308 and 309) 20,000 flying hours or 27,000 landings, whichever comes 

(black anodized) first 

Fire extinguisher 10 years (elapsed). See Note 1 below. 

Oxygen bottle 15 years (elapsed) 

NLG drag link right part (Part No. 532.20.12.140) (Pre 4,000 landings 

SB 32-014) 

Cargo door lower lug fittings (Qty 3) 13,000 flying hours or 17,000 landings, whichever comes 

first 

Backrest tubes on crew seats with a recline system 5,000 flying hours 

(Seat Part No's 959.30.01.111, 112, 121 and 122) 

Backrest tubes on crew seats without a recline system 10,000 flying hours 

(Seat Part No's 959.30.01 .131, 132, 133 and 134) 

Pitch trim actuator attachment parts, fail safe plates 10,000 flying hours 

and their attachment parts (IPC 12-20-00-07). Refer to 

AMM 12-A-27-40-02-00A-920A-A for fail safe plate 

removal/installation. 

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Component Life 

Nose landing gear torque tube (P/N 532.50.12.047) 11,000 flying hours or 15,000 landings or 10 years 

installed, whichever comes first. 

Note 1: Fire extinguishers that are 10 years or older must be replaced by 30 June 2013. 

4 Miscellaneous Limitations 

Table 4 Misceffaneous Umitations 

Component Limitation Procedure 

Inboard flap drive arms Every 150 flying hours or Annual In-situ Inspection/Check, AMM 

Inspection (whichever comes first) 12A27510000A313AA I 

Cockpit outer side, DV windows If cracked or stress crazing can be Replace 

and cabin windows felt 

Cockpit inner and outer side, DV If chipped, cracked (only for inner Refer toAMM 

windows and cabin windows side windows), scratche<l, bubbles or 12-A-~6:S.)O-OO-OOA-31~A-A for limitations 

delaminated 

Windshield LH and RH If cracked in inner lamination Replace 

If cracked in outer lamination Only unpressurized flight is permitted up 

to the next scheduled inspection 

providing it does not cause visual 

problems 

Horizontal stabilizer trim Every 3,000 flying hours or at Annual Functional test of Trim Runaway Aural 

Inspection, whichever comes first Warning System (FAA CMR) in 

accordance with AMM 

12-A-27 -4Q-OO-OOA-903A-A 

NLG drag link right part (P/N Initially 2,000 flying hours or 2,500 Inspection/check (refer to AMM 

532.20.12.289 or 532.20.12.140) landings (installed) whichever comes 12-A 32-20-06-00A-~ 13A-A). 

first, then every 300 flying hours or 

400 landings, whichever comes first. 

Oxygen bottle Refer to AVOX Service Information Hydrostatic test 

Letter SIL-35-114 latest revision 

Refer to AVOX Service Information Letter (www.avoxsys.com). SIL-35-1141atest revision 

(www.avoxsys.com). 

Pitch trim actuator (Part No. 1,500 flying hours Overhaul 

978.73.14.201) 

Pitch trim actuator (Part No. 5,000 flying hours or 5 years Overhaul 

978.73.14.202 and (installed) whichever comes first. 

978. 73.14.203) 

Wing Main Spar Fastener Holes Threshold 16000 wing flying hours or Eddy current inspection, AMM 

Strap Rib 6 22500 wing landings, whichever 12 A-~7 -20-1 O-OOA-353D-A 

comes first. 

No cracks are permitted. If you find 

All wings with no landing records cracks contact Pilatus Aircraft for advice. 

must apply a calculated applicable 

landings equal to 2 x flying hours. 

See Notes 1 and 2 below. 

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The inspection is applicable to all aircraft except MSN 170, 222, 233, 234, 237, 240, 244, 250 and 324 which 

have performed the inspection as part of a fleet leader inspection suNey and aircraft that have performed 

SeNice Bulletin 04-009 Revision 1 or later. 

Wings with more than 15500 flying hours or 22000 landings, whichever comes first, must perform the inspection 

within the next 500 flying hours or 500 landings, whichever comes first. 

5 Supplemental Structural Inspection Document 

This section and AMM 12-A-05-20-30-00A-280A-A give the additional structural and component life limits and the 

supplemental inspections needed for aircraft that have 25,000 flying hours or 30,000 landings or more and forms 

the Supplemental Structural Inspection Document (SSID) needed to increase the life of the airframe. 

SeNice Bulletin 04-009 must be accomplished to allow an aircraft to be operated up to 25,000 flying hours or 

30,000 landings, whichever comes first. 

Only authorised Pilatus SeNice Centers can do the SSID, see Para 5.2. 

5.1 Limit of Validity 

The limit of validity (LOV) of the SSID is 50.000 flying hours or 60,000 landings, whichever comes first. The part of 

the SSID for the wing structure (without systems and control system structure such as flaps and ailerons) has a 

lower LOV of 35,000 flying hours or 43,000 landings, whichever comes first. 

5.2 Authorisation 

Only Pilatus authorised SeNice Centers can do the SSID as defined in Para 7 and in AMM 

12 -A-05-20-30-00A-280A-A. 

5.3 Deviation from Type Design 

Deviations from the Type Design in critical locations could make the aircraft ineligible for this life extension. 

Therefore: 

(a) all concessions, 

(b) all repairs, alterations and modifications, 

(c) all STC installations 

must be assessed to find out if the aircraft will be eligible for this life extension. The owner/operator is responsible to 

organize these assessments well in advance of the first SSID inspection. There must be a clear statement for the 

specific aircraft MSN available which states that the aircraft with (a), (b) and (c) is eligible for this life extension. 

The assessments can be done as follows for: 

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UNCLASSIFIED 

(a) Concessions- Only Pilatus can do this assessment. Pilatus shall be approached at least 5 months in 

advance. 

(b) Repairs, alterations and modifications - Any Authority approved Design Organization or equivalent can do 

this assessment. 

(c) For the aircraft modifications of the STC any Authority approved Design Organization or equivalent can do 

this assessment. For the part of the STC itself the STC holder(s) only must do this assessment 

On request, Pilatus can do the assessments for items (b) and the first part of (c) in addition to (a) above, provided 

sufficient information is given. 

5.4 Supplemental Corrosion Prevention and Control Program (CPCP) 

The maximum corrosion level to be maintained is Corrosion Level1. Refer to AMM 12-A-20-40-00-00A-901A-A for 

Corrosion Control Maintenance Practices. 

The supplemental CPCP inspection tasks are identified in the column where a calendar time interval is given. The 

following additional threshold inspection requirement is applicable for all those CPCP inspection tasks: 

the CPCP inspection task must be accomplished 6 years after Service Bulletin 04-009 has been accomplished 

the CPCP inspection task must not be accomplished before the aircraft reaches 25,000 flying hours or 30,000 

landings. 

5.5 Damage Tolerance Evaluation 

The entire aircraft structure is subject to Damage Tolerance Evaluation when modified or repaired, except for life 

limited components as listed in Table 3 and Table 5, which remain as safe-life. 

6 Component Life 

Table 5 Component Ufe 

Task No. Component Life (whichever comes 

first) 

Flying Landings 

Hours 

27-50/414 Flaps - Life Limit {discard) 25,000 30,000 

55-10/415 Horizontal Stabilizer- Ufe Limit (discard) 25,000 30,000 

32-20/41 6 NLG Drag Link- Life Limit (discard) 25,000 30,000 

32-30/417 MLG Actuator - Life Limit (discard) 25,000 30,000 

29-10/418 Nitrogen accumulator- Life Limit {discard) 25,000 30,000 

7 Inspection Program 

Only Pilatus authorised Service Centers can do this SSID: 

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UNCLASSIFIED 

Table 6 Supplemental Structural Inspection Program 

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM 

Task No lnspectionfReference Threshold Repeated Interval (whichever 

(whichever comes comes first) 

first) 

Flying Landings Flying Landings Years 

Hours Hours 

32-10/345 Main landing gear - Overhaul 25,000 30,000 8,300 10,000 6 

CMM02099 

Inspection kit P/N 500.60.12.027 

32-10/346 MLG Yoke fitting lugs - Eddy Current 25,000 30.000 8,300 10,000 

Inspection 

CMM 02099 

32-10/347 MLG Trailing Link- Eddy Current 25,000 30,000 8,300 10,000 

Inspection 

CMM02099 

52-10/348 Passenger/crew door- Examine all 32.500 42,000 12,500 15,000 6 

structural elements 

AMM 12-A-~2-10-00-00A-310A-A 

52-20/349 Emergency door - Examine all structural 32,500 42,000 12,500 15,000 6 

elements 

AMM 12-A-52-20-00-00A-310A-A 

52-30/350 Cargo door - Examine all structural 32,500 42,000 12,500 15,000 E 

elements 

AMM 12-A-52-30-00..QOA-310A-A 

53-00/351 Upper Longerons Frame 10 - Eddy 25,000 30,000 12,500 15,000 

Current Inspection 

AMM 12-A-~~-10-06-01A-35;}A-A 

inspection kit P/N 500.60.12.032 

53-00/352 Fuselage Frames 10 to 16 - Examine all 32,500 42,000 12,500 15,000 € 

structural elements 

AMM 12-A-53-10-00-00A-310A-A 

Inspection kit PIN 500.60.12.033 

53-00/353 Fuselage Frames 16 to 36 - Examine all 32,500 42,000 12,500 15,000 6 

structural elements 

AMM 12-A-5;2-2Q-OO-OOA-31 OA-~ 

Inspection kit PIN 500.60.12.041 

53-00/354 Fuselage Frames 36 to 43 - Examine all 32,500 42,000 12,500 15.000 € 

structural elements 

AMM 12-A-53-30-00..QOA-310A-A 

53-00/355 Antenna Structure - Examine 32,500 42,000 12,500 15,000 6 

AMM 2-~·23-00-00-00A-~10A-A 

Effectivity: All 12 -A-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 9 
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UNCLASSIFIED 

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM 

Task No Inspection/Reference Threshold Repeated Interval (whichever 

(whichever comes comes first) 

first) 

Flying Landings Flying Landings Years 

Hours Hours 

53-00/356 Antenna - Bottom fuselage skin - Eddy 28,300 37,000 8.300 10,000 

Current Inspection 

AMM 12-A-§3-0Q-QO-OOA-353A-A 

53-00/357 Antenna - Upper fuselage skin - Eddy 32,500 42,000 12,500 15,000 

Current Inspection 

AMM 12-A-53-00-QQ-OQA-353A-A 

53-00/358 Upper Flange Carry Through Frames 21 30,000 3g,ooo 10,000 12,000 6 

and 24 - Examine 

AMM 12-A-53-2Q-Q2:QQA-310A-A 

Inspection kit PIN 500.50.12.327 

53-00/359 Frames 21 and 24 Wing Attachments - 30,000 39,000 10,000 12,000 

Eddy Current Inspection 

AMM 12-A-53-20-02-00A-~53A-A 

53-00/360 Frames 21 and 24 Side Frame 30,000 39,000 10,000 12,000 

Attachments - Eddy Current Inspection 

AMM 12-A-53-2Q-Q2:QQA-353A-A 

53-00/361 Frames 41 and 43 Stabilizer Attachment - 32,500 42,000 12,500 15,000 

Eddy Current Inspection 

AMM 12-A-53-;lQ·Q~·QQA-353A-A 

or 

AMM 12-A-55-30-03-00A-353A-A 

55-20/362 Elevator - Examine 32,500 42,000 12,500 15,000 6 

AMM 12-A-55-20-00-00A-310A-A 

27-30/363 Elevator - Control System - Examine 32,500 42,000 12,500 15,000 6 

AMM 12-A-27-~Q OQ:.QOA 310A-A 

Inspection kit P/N 500.50.12.319 

27-30/364 Elevator Control Rods - Eddy Current 32,500 42,000 12,500 15,000 

Inspection 

AMM 12-A-27-00-01-00A-353A-A 

27-30/365 Elevator Control Rods - Magnetic Particle 32,500 42,000 12,500 15,000 

Inspection 

AMM 12-A-27-00-Q 1-00A-3~2A-A 

27-30/366 Elevator Control Lever · Eddy Current 32,500 42,000 12,500 15,000 

Inspection 

AMM 12-A-27-3~-00A-353A-A 

Effectivity: All 12-A-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 10 
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UNCLASSIFIED 

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM 

Task No Inspection/Reference Threshold Repeated Interval (whichever 

(whichever comes comes first) 

first) 

Flying Landings Flying Landings Years 

Hours Hours 

55-20/367 Elevator Drive Lever- Eddy Current 32,500 42,000 12,500 15,000 

Inspection 

AMM 12-A-~~-2Q Q1:QQ -3~3A-A 

55-20/368 Elevator Hinges - Eddy Current 32,500 42,000 12,500 15,000 

Inspection 

AMM 12 -55-20-01 00A-~~~t:\-t:\ 

55-30/369 Vertical Stabilizer - Examine 32,500 42,000 12,500 15,000 6 

AMM 12-A-55-30-00-00A-310A-A 

Inspection kit PIN 500.50.12.325 

55-30/370 Vertical Stabilizer Main and Rear Spar 32,500 42,000 12,500 15,000 

Attachment to Fuselage - Eddy Current 

Inspection 

AMM 12-A-53-30-02-00A-353A-A 

or 

AMM 12-A-55-3 03 00A-35 A-A 

55-30/371 Vertical Stabilizer Main Attachment to 32,500 42,000 12,500 15,000 

Horizontal Stabilizer - Eddy Current 

Inspection 

AMM 12-A-55-00-00-00A-353A-A 

55-30/372 Vertical Stabilizer Pitch Trim Actuator 32,500 42,000 12.500 15,000 

Fitting and Attachment - Eddy Current 

Inspection 

AMM 12-t:\-~5-;2Q-Q2-00A-353A-A 

55-40/373 Rudder - Examine 32,500 42,000 12.500 15,000 6 

AMM 12-A-55-40-QO:QOA-~1 OA-A 

27-20/374 Rudder Control System - Examine 32,500 42,000 12,500 15,000 6 

AMM 12-A-27 -20-00-00A-31 OA-A 

Inspection kit P/N 500.50.12.318 

27-20/375 Rudder Bellcranks - Eddy Current 32,500 42,000 12,500 15,000 

Inspection 

AMM 12-A-27 20 04-00A-353A-~ 

27-20/376 Rudder Cable Quadrant Shear Spigot - 32,500 42.000 12,500 15,000 e 

Examine 

AMM 12-A-27-20-05-00A-310A-A 

55-40-377 Rudder Hinges - Eddy Current Inspection 32,500 42,000 12,500 15,000 

AMM 12-A-~~-40-05-00A 353A-A 

Effectivity: All 12-A-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 11 
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UNCLASSIFIED 

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM 

Task No Ins paction/Reference Threshold Repeated Interval (whichever 

(whichever comes comes first) 

first) 

Flying Landings Flying Landings Years 

Hours Hours 

56-11/378 Windshield LH and RH and Cockpit Side 32,500 42,000 12,500 15,000 € 

Windows - Examine with windshield and 

side windows removed 

AMM 12-A-~6 11-01-00A-310A-A 

and 

AMM 12-A-~6- 11 -02-00A-310A-A 

and 

AMM 12-A-53-10-1!HlQA-310A-A 

Inspection kit PIN 500.50.12.326 

57-00/379 Wing - Examine ail structural elements 30,000 39,000 10,000 12,000 f 

Rib 1 to Rib 20 

AMM 12-A-~7-QQ OO-OOA-310A-A 

57-00/380 Wing Main and Rear Spar to Fuselage 30,000 39,000 10,000 12,000 

Attachment - Eddy Current Inspection 

AMM 12 57-00-Q;l:QQA-~~;2A-A 

and 

AMM 12-A-~7-QQ Q3-01A-353A-A 

Inspection kit P/N 500.60.12.004 wing 

attachment 

Inspection kit P/N 500.60.12.007 double 

bush 

57-00/382 Wing Rear Spar at Rib 8 Flap Arm 25,000 30,000 12,500 15,000 

Attachment - Eddy Current Inspection 

AMM jk[\-57 -20-10-00A-3~~C-A 

57-00/383 Wing Main Spar Fastener Holes Rib 1 25,000 30,000 3,300 4,000 

thru Rib 6 - Eddy Current Inspection 

AMM 12-A-27 -20-10-00A-353A-A 

Inspection kit P/N 500.60.12.030 

or 

inspection kit PIN 500.60.12.020 

57-00/384 Wing Main Spar Fastener Holes Strap Rib 25,000 30,000 3,300 4,000 

6 - Eddy Current Inspection 

AMM 12-A-57-20-05-00A-353A-A 

Inspection kit PIN 500.60.12.031 or 

Inspection kit P/N 500.60.12.043 

Effectivity: All 12-A-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 12 
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UNCLASSIFIED 

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM 

Task No Inspection/Reference Threshold Repeated Interval (whichever 

(whichever comes comes first) 

first) 

Flying Landings Flying Landings Years 

Hours Hours 

57-00/385 Wing Rear Spar Fastener Holes Rib 2 25,000 30,000 12,500 15,000 

thru Rib 3 - Eddy Current Inspection 

AMM 12-A-57-20-10-00A-3538-A 

27-501386 Flap Mechanism - Examine 30,000 39,000 10,000 12,000 e 

AMM 12-A-27-51-00-00A-310A-A 

Inspection kit PIN 500.60.12.021 

Inspection kit PIN 500.60.12.022 

Inspection kit PIN 500.60.12.023 

Inspection kit PIN 500.60.12.024 

Inspection kit P/N 500.60.12.025 

27-501387 Flap Drive Arm (not removed) - Eddy 25,000 30,000 2,500 3,000 

Current Inspection 

AMM 12-A-27 -51-00-00A-~~~A-A 

27-50/388 Flap Drive Arm (removed)- Eddy Current 30,000 39,000 10,000 12,000 

Inspection 

AMM 12-A-27-Q1-01-00A-3538-A 

AMM 12-8-2Z-51-02-00A-353A-A 

AMM 12-A-27-51-03-00A-35~A-A 

27-501389 Flap Support Arm - Eddy Current 30,000 39,000 10,000 12,000 

Inspection 

AMM 12-A-27 -51-01-00A-~5~A-A 

AMM 12-A-27-Q1-02-00A-353A-8 

AMM 12-A-27-51-03-00A-~:2~A-A 

27-50/390 Flap Cove Rib Fittings- Eddy Current 30,000 39,000 10,000 12,000 

Inspection 

AMM 12-A-27-~1-01-00A-~5~A-A 

AMM 12-A-~Z-51-02-00A-353A-A 

AMM 12-A-27-51-03-QQ8-~:23A-A 

27-50-391 Flap Aft Links - Eddy Current Inspection 30,000 39,000 10,000 12,000 

AMM 12-8-27-51-01:!)QA-353A-A 

AMM 1 ~ -A-27 -51-02 -OOA-353A-A 

AMM 12-A-27-Qj-03-00A-~5~8-A 

Effectivity: All 12-A-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 13 
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UNCLASSIFIED 

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM 

Task No Inspection/Reference Threshold Repeated Interval (whichever 

(whichever comes comes first) 

first) 

Flying l andings Flying l andings Years 

Hours Hours 

27-50/392 Flap Belicranks - Eddy Current inspection 30,000 39,000 10,000 12,000 

AMM 12-A-27-51-01-00A-353A-A 

AMM 12-A-27-5j-02-00A-353A-A 

AMM 12-A-27-51 -0~::QOA-353A-A 

57-60/393 Aileron - Examine 32,500 42,000 12,500 15,000 6 

AMM 12-A-57 -60-00-00A-31 OA-A 

27-10/394 Aileron Control System - Examine 32,500 42,000 12,500 15,000 6 

AMM 12-A-27 -1 0-00::QQA-~1 OA-A 

inspection kit P/N 500.50.12.314 

Inspection kit P/N 500.50.12.315 

Inspection kit P/N 500.50.12.316 

Inspection kit PIN 500.60.12.015 (MSN 

684- 999) 

Inspection kit P/N 500.60.12.016 (MSN 

684 -999) 

27-10/395 Aileron Cable Segment - Eddy Current 32,500 42,000 12,500 15,000 

Inspection 

AMM 12-A-27 -1 0-09-00A-353A-A 

27-10/396 Aileron Control Rods - Eddy Current 32,500 42.000 12,500 15.000 

Inspection 

AMM 12-A-27 -QO-Q1 -00A-353A-A 

27-10/397 Aileron Control Rods - Magnetic Particle 32,500 42,000 12,500 15,000 

Inspection 

AMM 12-A-27-00::Q1-00A-352A-A 

27-10/398 Aileron Belicranks - Eddy Current and 32,500 42,000 12,500 15,000 

Magnetic Particle Inspections 

AMM 12-A-27-10-Q8::QQA-353A-A 

AMM 12-A-27 -1 Q-Q~::QOA-~~38-A 

AMM 12-A-27 -1 0-Qf!-00~-3528-A 

27-30/400 Aileron Hinge Points - Eddy Current 32,500 42,000 12,500 15,000 

Inspection 

AMM 12-A-57:§0-06-00A-353A-A 

71-00/401 Engine Mount - Magnetic Particle 26,600 35,000 6,600 8,000 

Inspection 

AMM 12 -A-71-QQ-Q5-QOA-352A-A 

Inspection kit PIN 500.60.12.006 

Effectivity: All 12-A-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-1 3 Page 14 
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UNCLASSIFIED 

The Airworthiness Limitations Section Is EASA Approved under Approval Number: 

I 10048310 

I Approval Date:- 27 February 2014 

Effectivity: All 

End of data module 

UNCLASSIFIED 

12-A-04-00-00-00A-OOOA-A 

2014-03-13 Page 15 
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Effectivity: All 

UNCLASSIFIED 

Intentionally left blank 

End of data module 

UNCLASSIFIED 

12-A-04-00-{)0-00A-OOOA-A 

2014-03-13 Page 16