~PILATUS:?' 12-B-AM-00-00-00-1 

UNCLASSIFIED 

Model type - PC-12/47E MSN-1 001-UP 

Aircraft Maintenance Manual (AMM) 

Document No. 02300 

12-B-AM-00-00-00-1 

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

UNCLASSIFIED 

@PI LATUS AIRCRAFT L TO. CH-6371 STANS. SWITZERLAND 
I 

~PILATUS~ 12-8-AM-00-00-00-1 

UNCLASSIFIED 

AMM LIST OF REVISIONS 

1 List of Revisions 

Rev No. Date of Issue 

1 Jan 30109 

2 Jun 01/09 

3 Oct 20/09 

4 Apr 08/10 

5 Jan 31/11 

6 Sep 30/11 

7 Dec 15/11 

8 Jan 30/12 

9 Dec 15/12 

10 Dec 08/13 

.... I 11 May 31/14 

Effectivity: ALL 

Date Inserted 

Jan 30/09 

Jun 01/09 

Oct 20/09 

Apr 08110 

Jun 30/11 

Sep 30/11 

Dec 15/11 

Jan 30/12 

Dec 15/12 

Dec 08/13 

May 31/14 

End of data module 

UNCLASSIFIED 

Signature 

Pilatus 

Pilatus 

Pilatus 

Pi latus 

Pi latus 

Pi latus 

Pi latus 

Pilatus 

Pi latus 

Pi latus 

Pilatus 

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

2014-05-05 Page 1 
~PILATUS~ 12-8-AM-00-00-00-1 

UNCLASSIFIED 

PC-12/47E GENERAL -AIRCRAFT MAINTENANCE MANUAL 

LIST OF EFFECTIVE CHAPTERS 

Table of Contents 

PC-12/47E GENERAL- AIRCRAFT MAINTENANCE MANUAL- LIST OF EFFECTIVE 

CHAPTERS ............................................................................................................................... . 

Index of Tables 

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

References 

Table 1 References 

Data module/Technical publication Title 

None 

Chapter Number 

00 

04 

05 

06 

07 

08 

09 

10 

11 

12 

20 

21 

22 

23 

24 

25 

26 

27 

28 

29 

30 

31 

32 

33 

34 

.... 

Description 

Chapter Title 

GENERAL 

STRUCTURALANDCOMPONENT 

LIMITATIONS 

SCHEDULED/UNSCHEDULED 

MAINTENANCE 

DIMENSIONS AND ZONES- GENERAL 

LIFTING AND SHORING- GENERAL 

LEVELING AND WEIGHING- GENERAL 

HANDLING AND TAXIING- GENERAL 

PARKING, MOORING AND STORINGGENERAL 

PLACARDS AND MARKINGS- GENERAL 

SERVICING- GENERAL 

EQUIPMENT HANDLING 

AIR CONDITIONING 

AUTOMATIC FLIGHT CONTROLGENERAL 

COMMUNICATIONS 

ELECTRICAL POWER 

EQUIPMENT AND FURNISHINGS 

FIRE PROTECTION 

FLIGHT CONTROLS 

FUEL 

HYDRAULIC POWER 

ICE AND RAIN PROTECTION 

INDICATING AND RECORDING SYSTEMS 

LANDING GEAR - HYDRAULIC 

LIGHTS 

NAVIGATION 

12-8-00-00-00-00A-001 A-A 

12-8-04-00-00-00A-OOOA-A 

12-8-05-00-00-00A-018A-A 

12 -8-06-00-00-00A-040A-A 

12-8-07 -OO-OO-OOA-040A-A 

12-8-08-00-00-00A-040A-A 

12-8-09-00-00-00A-040A-A 

12-8-1 O-OO-OO-OOA-040A-A 

12-8-11-00-00-00A-040A-A 

12-8-12-00-00-00A-040A-A 

12-8-20-00-00-00A-901 A-A 

12-8-21-00-00-00A-040A-A 

12-8-22-00-00-00A-040A-A 

12-8-23-00-00-00A-040A-A 

12-8-24-00-00-00A-040A-A 

12-8-25-00-00-00A-040A-A 

12-8-26-00-00-00A-040A-A 

12-8-27 -OO-OO-OOA-040A-A 

12-8-28-00-00-00A-040A-A 

12-8-29-00-00-00A-040A-A 

12-8-30-00-00-00A-040A-A 

12-8-31-00-00-00A-040A-A 

12-8-32-00-00-00A-040A-A 

12-8-33-00-00-00A-040A-A 

12-8-34-00-00-00A-040A-A 

Page 

Page 

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Chapter Number 

35 

45 

46 

52 

53 

55 

56 

57 

61 

71 

72 

73 

74 

76 

77 

78 

79 

80 

Effectivity: All 

UNCLASSIFIED 

Chapter Title 

OXYGEN SYSTEM 

CENTRAL MAINTENANCE SYSTEM 

SYSTEMS INTEGRATION AND DISPLAY 

DOORS -GENERAL 

FUSELAGE 

STABILIZERS 

WINDOWS 

WINGS 

PROPELLER 

POWERPLANT 

ENGINE 

ENGINE FUEL AND CONTROL 

IGNITION SYSTEM 

ENGINE CONTROLS 

ENGINE INDICATING- GENERAL 

EXHAUST 

OIL SYSTEM 

STARTING 

End of data module 

UNCLASSIFIED 

12-B-AM-00-00-00-1 

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

12-B-45-00-00-00A-040A-A 

12-B-46-00-00-00A-040A-A 

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

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

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

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

12-B-57 -OO-OO-OOA-040A-A 

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

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

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

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

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

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

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

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

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

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

12 -B-OO-OO-OO-OOA-009A-A 

2014-05-22 Page 2 
":5PILATUS~ 

UNCLASSIFIED 

STRUCTURAL AND COMPONENT LIMITATIONS 

AIRWORTHINESS LIMITATIONS 

Table of Contents Page 

STRUCTURAL AND COMPONENT LIMITATIONS- AIRWORTHINESS LIMITATIONS.......... 1 

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................................................................................................ 9 

Index of Tables Page 

1 

2 

3 

4 

5 

6 

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

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

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

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

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

Supplemental Structural Inspection Program ....................................................... .. 

Data module/Technical publication 

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

12-B-20-40-00-00A-901 A-A 

12-B-21-30-00-00A-903A-A 

12-B-27 -00-01-00A-352A-A 

12-B-27 -00-01-00A-353A-A 

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

12-B-27 -1 0-08-00A-3528-t\ 

12-B-27 -1 0-08-00A-353A-t\ 

References 

Table 1 References 

Title 

SUPPLEMENTAL STRUCTURAL INSPECTION 

DOCUMENT - INSPECTION$ 

CORROSION CONTROL - MAINTENANCE 

PRACTICES 

PRESSURIZATION CONTROL - ADJUSTMENT/TEST 

FLIGHT CONTROLS- CONTROL RODS - MAGNETIC 

PARTICLE INSPECTION 

FLIGHT CONTROLS - CONTROL RODS - EDDY 

CURRENT INSPECTION 

AILERON CQNTROL SYSTEM - EXAMINE 

AILERON CONTROL SYSTEM - FUSELAGE 

BELL CRANK - MAGNETIC PARTICLE INSPECTION 

AILERON CONTROL SYSTEM - OUTER WING 

BELLCRANK - EDDY CURRENT INSPECTION 

1 

5 

5 

6 

8 

9 

Effectivity: All 12 -8-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 1 
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Data modulefTechnical publication 

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

12-B-27 -1 0-09..QOA-353A-A 

12-B-27 -20-00-QOA-31 OA-A 

12-B-27 -20-04-QOA-353A-A 

12-B-27 -20-05-QOA-31 OA-A 

12-B-27 -30-00-00A-31 OA-A 

12-B-27 -30-05-00A-353A-A 

12-B-27 -40-00-QOA-903A-A 

12-B-27 -40-02-00A-920A-A 

12-B-27-51-00-00A-310A-A 

12 -B-27 -51-00-00A-313A-A 

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

12-B-27 -51-0 1-00A-353A-A 

12-B-27 -51-02-00A-353A-A 

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

12-8-32-1 0-06-00A-313A-A 

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

12-B-32-30-08-00A-903A-A 

12-B-32-30-1 O-QOA-903A-A 

12-B-52-1 0-00-00A-31 OA-A 

12-B-52-20-00-00A-31 OA-A 

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

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

12-B-53-00-00..()0A-353A-A 

Effectivity: All 

UNCLASSIFIED 

Title 

AILERON CONTROL SYSTEM- FUSELAGE 

BELLCRANK- EDDY CURRENT INSPECTION 

AILERON CONTROL SYSTEM -FUSELAGE CABLE 

QUADRANT- EDDY CURRENT INSPECTION 

RUDDER CONTROL SYSTEM - EXAMINE 

RUDDER CONTROL SYSTEM- BELLCRANK - EDDY 

CURRENT INSPECTION 

RUDDER CONTROL SYSTEM- CABLE QUADRANTEXAMINE 

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 CURRENT 

INSPECTION 

f~P DRIVE SYSTEM - WING - INBOAB._Q 

MECHANISM - EDDY CURRENT INSPECTIQ.r:l 

FLAP DRIVE SYSTEM -WING- CENTER 

MECHANISM - EDDY CURRENT INSPECTION 

FLAP DRIVE SYSTEM -WING- OUTBQARD 

MECHANISM - EDDY CURRENT INSPECTION 

MAIN GEAR AND DOORS- SPRING STRUTINSPECTION/CHECK 

DRAG LINK RIGHT PART- INSPECTION/CHECK 

LANDING GEAR RELAY UNIT- ELECTRO 

MECHANICAL LANDING GEAR -ADJUSTMENT/TEST 

EMERGENCY GEAR EXTENSION SYSTEM -

ELECTRO MECHANICAL LANDING GE;AR -

ADJUSTMENT/TEST 

PASSENGER/CREW DOOR - EXAMINE 

EMERGENCY EXIT - EXAMINE 

CARGO DOOR- EXAMINE 

FUSELAGE -ANTENNA STRUCTURE - EXAMINE 

FUSELAGE ·ANTENNA STRUCTURE - EDDY 

CURRENT INSPECTION 

12-B-04-00-00-QOA-OOOA-A 

UNCLASSIFIED 2014..()3-13 Page 2 
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Data module/Technical publication 

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

12-B-53-1 0-06-Q1A-353A-A 

12 -B-53-1 0-16-QQA-31 OA-A 

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

12-B-53-20-02-QOA-31 OA-A 

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

12-B-5.3-30-00-00A-31 OA-A 

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

12-B-55-00-00-QOA-353A-A 

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

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

12-B-55-30-00-00A-31 OA-A 

12 -B-55-30-02 -OOA-353A-A 

1 2-B-55-30-03-00A-353A-A 

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

12-B-55-40-05-00A-353A-A 

12-B-56-QO-QQ-QOA-313A-A 

12-B-56-11-01-00A-310A-A 

12-B-56-11-02-00A-31 OA-A 

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

12-B-57 -00-03-00A-353A-A 

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

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

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

Effectivity: All 

UNCLASSIFIED 

Title 

FORWARD FUSELAGE - EXAMINE 

FORWARDFUSELAGE - FRAME 10LONGERONS -

EDDY CURRENT INSPECTION 

FORWARD FUSELAGE- WINDOW STRUCTURE -

EXAMINE 

CENTER FUSELAGE - EXAMINE 

CENTER FUSELAGE FRAMES- CARRY THROUGH 

FRAMES - EXAMINE 

CENTER FUSELAGE FRAMES - CARRY THROUGH 

FRAMES - EDDY CURRENT INSPECTION 

REAR FUSELAGE - EXAMINE 

REAR FUSELAGE FRAMES - EDDY CURRENT 

INSPECTION 

VERTICAL STABILIZER ATTACHMENT FITTINGSEDDY CURRENT INSPECTION 

ELEVATORS- EXAMINE 

ELEVATOR DRIVE LEVER AND HINGE- EDDY 

CURRENT INSPECTION 

VERTICAL STABILIZER- EXAMINE 

VERTICAL STABILIZER- PITCH TRIM ACTUATOR 

ATTACHMENT- EDDY CURRENT INSPECTION 

VERTICAL STABILIZER SPARS- EDDY CURRENT 

INSPECTION 

RUDDER - EXAMINE 

RUDDER HINGE - EDDY CURRENT INSPECTION 

WINDOWS - INSPECTION/CHECK 

WINDSHIELD - EXAMINE 

COCKPIT SIDE WINDOWS - EXAMINE 

WINGS -EXAMINE 

WING AND FUSELAGE ATTACHMENT FITTINGSEDDY CURRENT INSPECTION 

WING AND FUSELAGI; ATTACHMENT FITTINGS -

HOLLOW BOLTS - EDDY CURRENT INSPECTION 

WING STRUCTURE - RIBS - EDD.Y CURRENT 

INSPECTION- RIB 6 STRAP 

WING STRUCTURE- SPARS AND AUXILIARY 

STRUCTURE- MAIN SPAR - EDDY CURRENT 

INSPECTION 

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

UNCLASSIFIED 2014-03-13 Page 3 
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Data modulefTechnical publication 

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

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

12-B-57 -20-10-00A-353D-A 

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

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

12-B-71-00-00-00A-903D-A 

12-B-71-00-05-00A-352A-A 

1 General 

UNCLASSIFIED 

Title 

WING STRUCTURE SPARS AND AUXILIARY 

STRUCTURE- REAR SPAR- EDDY CURRENT 

INSPECTION 

WING STRUCTURE- SPARS AND AUXILIARY 

STRUCTURE- 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 

POWER PLANT TEST 3 -DC GENERATION SYSTEM 

- ADJUSTMENT/TEST 

POWERPLANT MOUNTING FRAME - MAGNETIC 

PARTICLE INSPECTION 

Description 

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

The Airworthiness Limitations section is also FAA approved for US registered aircraft in accordance with FAR 

21 .29. 

The Airworthiness Limitations section is FAA approved and specifies maintenance required under Parts 43.16 and 

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

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

On the PC-12/47E 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. Pilatus 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 marking "AT" or "VLG" (Ref. Pilatus Service Bulletin 32-015). 

Main Landing Gear Shock Absorber 

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

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

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Main Landing Gear Actuators 

960.30.01.103 with serial numbers 830E thru 881E (Ref. Pilatus SeNice 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). 

Propeller Blade 

Propeller blade E10477K. 

2 Structural Limitations 

Table 2 Structural Limitations 

Structure Life 

Fuselage and associated structure Pre SB 04-009 20,000 flying hours or 27,000 landings. 

whichever comes first 

Post SB 04.009 25,000 flying hours or 30,000 landings, 

whichever comes first 

Wing structure Pre SB 04-009 20,000 flying hours or 27,000 landings, 

whichever comes first 

Post SB 04-009 25,000 flying hours or 30,000 landings, 

whichever comes first 

Tail structure Pre SB 04-009 20,000 flying hours or 27,000 landings, 

whichever comes first 

Post SB 04-009 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 Para 5 and AMM 12-

B-05-20-30-00A-280A-A for the 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 04-009 20,000 flying hours or 27,000 landings, 

whichever comes first 

Post SB 04-009 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 Para 5 and AMM 12-

B-05-20-30-00A-280A-A for the 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) 

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UNCLASSIFIED 

Component Life 

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

first 

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-B-27-40-02-00A-920A-A for fail safe plates 

removal/installation. 

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

installed, whichever comes first. 

Electro-mechanical landing gear actuators 1000 landings 

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

4 Miscellaneous Limitations 

Table 4 Miscellaneous Limitations 

Component Limitation Procedure 

Inboard flap drive arms Every 150 flying hours or at Annual In-situ lnspection/CheckAMM 

Inspection, whichever comes first 12-B-27 -51-00-00A-313A-A 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 to AMM 12-B-56-00-00-00A-313A-A 

windows and cabin windows side windows), scratched, bubbles for limitations 

or delaminated 

Windshield LH and RH If cracked in inner lamination Replace 

If cracked in outer lamination Only unpressurized Hight is permitted up to 

the next scheduled inspection providing it 

does not cause visual problems 

Generator Control Unit (GCU) 1 Every 3,000 flying hours or at Functional test of the GCU 1 and GCU 2 

and GCU 2 Annual Inspection, whichever over and under-voltage trip protection 

comes first (Refer to AMM 

12-B-71-00-00-00A-903D-A) 

ECS emergency shut-off system Every 3,000 flying hours or at Attach a spring balance to the ECS EMER 

Annual Inspection, whichever SHUT-OFF lever. Pull the lever and check 

comes first that the max pull force to open the ram air 

scoop is 22.51bf (100 N) and make sure 

that the ram air scoop is completely open. 

Pressurization Dump switch Every 3,000 flying hours or at Operational test (refer to AMM 

Annual Inspection, whichever 12-8-21-30-00-00A-9Q3A-A) 

comes first 

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

Annual Inspection, whichever Warning System (FAA CMR) in 

comes first accordance with AMM 

12-!2-27 -40-00-00A-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) landings (installed) whichever 12 -B-32 -2Q-02-0Q8-313A-A). 

comes first, then every 300 flying 

hours or 400 landings, whichever 

comes first. 

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UNCLASSIFIED 2014-03-13 Page 6 
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UNCLASSIFIED 

Component Limitation Procedure 

Emergency gear extension 2000 flying hours or at Annual Operational test, 

system Inspection, whichever comes first AMM12-B-~2-30-10-00A-903A-A 

Electro mechanical landing gear 

Main landing gear spring strut 2000 flying hours or at Annual Loosen and move the spring strut cover to 

Electro mechanical landing gear Inspection, whichever comes first examine the springs, AMM 

1 Z-B-32-1 O-Q6-00A-31 ~A-A 

Time delay relays and power 2000 flying hours or at Annual Functional test, AMM 

contactors Inspection, whichever comes first 12-B-32 -30-08-00A-903A-A 

Electro mechanical landing gear 

Oxygen bottle Refer to AVOX Service Information Hydrostatic test. 

Letter SIL-35-114 1atest revision 

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

(www.avoxsys.com). 

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 Eddy current inspection, AMM 

Strap Rib 6 or 22500 wing landings, whichever 12-B-57 -2Q-1 0-00A-3530-A 

comes first. 

No cracks are permitted. If you find cracks 

All wings with no landing records contact Pi latus Aircraft for advice. 

must apply a calculated applicable 

landings equal to 2 x flying hours. 

5 Supplemental Structural Inspection Document 

This section and AMM 12-B-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. 

Service 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 Service 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 naps and ailerons) has a 

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

5.2 Authorisation 

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

12-B-OQ-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: 

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

UNCLASSIFIED 2014-03-13 Page 7 
~PILATUS~ 

(a) all concessions, 

(b) all repairs, alterations and modifications, 

(c) all STC installations 

UNCLASSIFIED 

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: 

(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 Level 1. Refer to AMM 12-B-20-40-00-QOA-901 A-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 Life 

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- Life Limit (discard) 25,000 30,000 

32-20/416 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 

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

UNCLASSIFIED 2014-03-13 Page 8 
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UNCLASSIFIED 

7 Inspection Program 

Only Pilatus authorised Service Centers can do this SSID: 

Table 6 Supplemental Structural Inspection Program 

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM 

Task No lnspectlonfReference 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 

CMM 02099 

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 

CMM 02099 

52-10/348 Passenger/crew door - Examine all 32,500 42,000 12,500 15,000 6 

structural elements 

AMM 12-B-52-10-00-00A-310A-A 

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

elements 

AMM 12-B-52-20-00-00A ~1 OA-8 

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

elements 

AMM 12-B-52-30-00-00A-310A-A 

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

Current Inspection 

AMM 12-B-5~-10-06-01A-353A-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 6 

structural elements 

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

Inspection kit P/N 500.60.12.034 

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

structural elements 

AMM 12-B ~-2Q-QQ :QOA-3108 A 

Inspection kit P/N 500.60.12.042 

53-00/354 Fuselage Frames 36 to 43 - Examine all 32,500 42,000 12,500 15,000 E 

structural elements 

AMM 12-B-53-30-00-00A-310A-A 

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

UNCLASSIFIED 2014-03-13 Page 9 
~PILATUS~ 

UNCLASSIFIED 

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM 

Task No Inspect ion/Reference Threshold Repeated Interval (whichever 

(whichever comas comas first) 

first) 

Flying Landings Flying Landings Years 

Hours Hours 

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

AMM 12-B-53-00-0Q-OOA-31 OA-A 

53-00/356 Antenna - Bottom fuselage skin - Eddy 28,300 37,000 8,300 10,000 

Current Inspection 

AMM 12-B-53-00-QQ-QOA-353A-A 

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

Current Inspection 

AMM 12-B-53:::QO-QO-OOA-353A-A 

53-00/358 Upper Flange Carry Through Frames 21 30,000 39,000 10,000 12,000 € 

and 24 - Examine 

AMM 12-B-53-2Q-Q2-00A-310A-A 

Inspection kit P/N 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-B-53-20-Q,-OOA-353A-A 

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

Attachments - Eddy Current Inspection 

AMM 12-B-5~·2Q Q2 QOA-353A-A 

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

Eddy Current Inspection 

AMM 12-B-~3-~0-02-00A-353A-A 

or 

AMM 12-B-~~-30-Q3-00A-353A-8 

55-20/362 Elevator - Examine 32,500 42.000 12,500 15,000 6 

AMM 12-B-55-20-QQ-OOA-310A-A 

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

AMM 12-B-27-~Q-QQ-OOA-310A-A 

Inspection kit P/N 500.60.12.019 

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

Inspection 

AMM 12-B-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-B-27-Q0-01-00A-352A-A 

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

Inspection 

AMM 12-B-27 -30-05-00A-353A-A 

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

UNCLASSIFIED 2014-03-13 Page 10 
"':SPILATUS~ 

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 j 2-B-55-20-01-00A-35~A-~ 

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

Inspection 

AMM 12-B-55-2Q-Q1::QOA-353A-8 

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

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

Inspection kit P/N 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 12-8-53-30-02-00A-353A-A 

or 

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

55-30/37.1 Vertical Stabilizer Main Attachment to 32,500 42,000 12,500 15,000 

Horizontal Stabilizer - Eddy Current 

Inspection 

AMM 12-8-55-00-00-00A-~53A-8 

55-30/372 Vertical Stabilizer Pitch Trim Actuator 32,500 42.000 12,500 15,000 

Fitting and Attachment - Eddy Current 

Inspection 

AMM 12-8-55-30-02-00A-353A-A 

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

AMM 12-[~-5~·40-00-00A-31QA-A 

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

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

Inspection kit PIN 500.60.12.018 

27-20/375 Rudder Bellcranks - Eddy Current 32,500 42,000 12.500 15,000 

Inspection 

AMM 12-8-27 -2Q-04-00A-353A-A 

27-20/376 Rudder Cable Quadrant Shear Spigot - 32,500 42,000 12,500 15,000 € 

Examine 

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

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

AMM 12-B-55-40-05-00A-353A-A 

Effectivity: All 12-8-04-00-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 11 
~PILATUS~ 

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 

56-111378 Windshield LH and RH and Cockpit Side 32,500 42,000 12,500 15,000 6 

Windows - Examine with windshield and 

side windows removed 

AMM 12-B-56-11 -0 :QQA-~l0A-A 

and 

AMM 12-B-56-11-02-0QA-310A-A 

and 

AMM 2-B-5~-1Q- §-00A-3 10A-A 

Inspection kit PIN 500.50.12.326 

57-001379 Wing - Examine all structural elements 30,000 39,000 10,000 12,000 E 

Rib 1 to Rib 20 

AMM 12-B-57-00-00-00A-31QA-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-B-57 -QQ:Q~-OOA-353A-A 

and 

AMM 12-B-57-00-03-01A-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 12-B-57-2Q-1Q-QQA-353C-A 

57-001383 Wing Main Spar Fastener Holes Rib 1 25,000 30,000 3,300 4,000 

thru Rib 6 - Eddy Current Inspection 

AMM 12-B-57-2Q-10:QOA-353A-A 

Inspection kit PIN 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-B-57 20-Q~·QQA-353A-A 

Inspection kit P/N 500.60.12.031 or 

Inspection kit PIN 500.60.12.043 

Effectivity: All 12 -B-04-0Q-00-00A-OOOA-A 

UNCLASSIFIED 2014-03-13 Page 12 
~PILATUS::" 

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-B-57-20-10-00A-3538-A 

27-50/386 Flap Mechanism - Examine 30,000 39,000 10,000 12,000 E 

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

Inspection kit P/N 500.60.12.021 

Inspection kit P/N 500.60.12.022 

Inspection kit P/N 500.60.12.023 

Inspection kit PIN 500.60.12.024 

Inspection kit PIN 500.60.12.025 

27-50/387 Flap Drive Arm (not removed) - Eddy 25,000 30,000 2,500 3,000 

Current Inspection 

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

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

Inspection 

AMM 2-B-27-51-01-00A-~:2~A A 

AMM 12-B-27-51-02-00A-353A-A 

AMM 12-B-27-51-03-00A ~53A-A 

27-50/389 Flap Support Arm - Eddy Current 30,000 39,000 10,000 12,000 

Inspection 

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

AMM 12-B-27 -51-02-00A-353A-A 

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

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

Inspection 

AMM 12-B-27 -~ 1 :Q1 :QOA-353A-A 

AMM 12-B-27-51-02-00A-353A-A 

AMM 12-B-27 -51 :Q3-00A-353A-A 

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

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

AMM 12-B-27-~1-02-00A-3~3A-~ 

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

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

UNCLASSIFIED 2014-03-13 Page 13 
~PILATUS~ 

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 

27-50/392 Flap Bellcranks - Eddy Current Inspection 30,000 39,000 10,000 12,000 

AMM l2-B-27-51-01::QQ~-353A-A 

AMM 1~-B-27-51-02::QOA-353A-A 

AMM 12-B-27 -51-03::QQA-353A-A 

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

AMM 12-B-57-60-QQ-QOA-310A-A 

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

AMM 12-B-27-10-QO-QOA-310A-A 

Inspection kit P/N 500.50.12.314 

Inspection kit PIN 500.60.12.035 

Inspection kit PIN 500.60.12.016 

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

Inspection 

AMM 12-B-27 -1 0-09-QOA-~:2~A-A 

27-10/396 Aileron Control Rods - Eddy Current 32,500 42,000 12,500 15.000 

Inspection 

AMM 12-8-27-00-01 ;:QQA-~53A-A 

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

Inspection 

AMM 12-B-27-00-01-QQA-352A-A 

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

Magnetic Particle Inspections 

AMM 12-B-27-10-08-QOA-353A-A 

AMM 12-B-27-10-08-QOA-3538-A 

AMM 12-B-27-10-0~-QOA-3528-A 

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

Inspection 

AMM 12-B-:27 -6Q-Q6::QQA-;lQ;lA-A 

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

Inspection 

AMM 12-B-71-00-05-00A-352A-A 

Inspection kit P/N 500.60.12.006 

The Airworthiness Limitations Section is EASA Approved under Approval Number: 

10048310 

Approval Date:- 27 February 2014 

Effectivity: All 

End of dala module 

UNCLASSIFIED 

12-B-Q4-00-QO-QOA-QOOA-A 

2014-Q3-13 Page 14 

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