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

### UN CLASS IFIED



# Model type- PC-12, PC-12/45, PC-12/47 Aircraft Maintenance Manual (AMM) Document No. 02049 12-A-AM-00-00-00-1

Eff ectivity: All 12-A- AM - 00 - 00 - 00 - 1 

### UN C LA SS IFIED e PILATUS AIRCRAFT LTD . CH-6 37 1 STANS . SWITZERLAND

## I 

# ~PILATUS~ 12-A-AM-00-00-00 - 1 U NCLASSIFIED 

## AMM LIST OF REV I SIONS 

## 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

E ffectivi ty : ALL Date I nserte d Signatu r e 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 M ay 31/14 

### - -

End of data module

U N CLASSIFI E D 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 UN CLASS IFIED 

## 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- A I RCRAFT MAINTENANCE MANUAL- LIST OF EFFEC T IV E CHAPTERS............................ ..... ........ . ................... . ...... . ............................ . ... . ..... . 

## Index of Tables References .. . ........... .......... . ... . . ....... . . . . . . .. . .................. . .. . ... .. . .. . . .. .. . . . .................. .. . . . . 

## References Table 1 References 

### Data modul erTec hn ica l publi ca tion Titl e None


### C h a pter Numb e r 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 C h a pte r Titl e GE N ERAL STRUCTURAL,CO M PONENTAND MISCELLANEOUS TIME LIMITS/MAINTENANCE CHECKS D I MENS I ONS AND AREAS GENERAL LIFTING AND SHORING L EVELLING AND WEIGHING TAXIING AND TOWING PARKING AND MOORING PLACARDS AND MARKINGS SERVICING EQUIPMENT HANDLING AIR CONDIT I ONING AUTO FLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT AND FURNISHINGS FIRE PROTECTION FLIGHT CONTROLS FUEL SYSTEM HYDRAULIC POWER I CE AND RAIN PROTECTION IN D I CATI NG/R ECORDING 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 1 2 -A-12-00-00 -00A-040A-A 1 2-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 1 2-A -30-00 -00-00A -040A-A 12-A-31 -00 -00 -00A- 04 0A-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 U NCLASS IFIED 2014- 05-22 Page 1

# ~PILATUS~ Chapter Number 55 56 57 61 71 72 73 74 76 

### 77 78 79 80

Effectiv i ty : All 

### Chapter Title STABILIZERS WINDOWS WINGS PROPELLER POWER PLANT ENGINE UN C LASSIFIED



### ENGINE FUEL AND CONTROL IGNITION SYSTEM (MSN 101-320 , 322- 400) ENGINE CONTROLS ENGINE INDICATING EXHAUST ENGINE OIL SYSTEM ENGINE STARTING

End of data modu l e 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 -8 0-00 -00-00A -040A-A

12 -A-00-00- 00 -00A-009A-A 2014 - 05-22 Page 2

## ~PILATUS:;r UNCLASSIFIED 

## STRUCTURAL, COMPONENT AND MISCE L LANEOUS 

## AIRWORTHINESS LIMIT A T/ONS T ab le of Con tents Page STRUCTURAL, COMPONENT AND MISCELLANEOUS- AIRWORTHINESS LIM ITATION S . 1 

### General. ....... . .... ........ .. . ..... . ........................... . ..... . ................ .. .. ... . .... ............. .. .. ..... . 4 2 Structural Limitations ........... ............... ........... ...... . ....... .. . ......... .. ... ...... ... ...... . . .. .... . .. 5 3 Component Limitations ........ ...... . ....... ............. ........... ............... .... .................. . .. ..... 5 4 Miscellaneous limitations. . ....... . .. ........ ........ .. . ... . ........ ... ..... . . . ..... . ..... ... ... ........ .. .. . .. . 6 5 Suppl emental Structural Inspection Document..... . ...... .... .................. .......... ... ....... 7 5.1 

### Limit of Validity.. ...... .......................... ........ .............. ... . ...... ......... . . ........ .... ..... ... .. .... 7 5.2 

### Authorisation . . ........................ .... ................................................ . ........... .. ... .. .......... 7 5.3 

### Deviation from T ype De sign... .... ............ . . ...... . ........ ........... ... .. ....... ........................ 7 5.4 Supplement al Corrosion Preventio n and Control Pr ogram (C PCP). ......... .. ...... . .... 8 5.5 D a mag e Tolerance Evaluation.... ................ .. .... .... .................. .... ........ . ...... . . ........ . . 8 6 Component Life ..... .. .............. .. .......................... . ........ .......... ........... .................. . ... . 8 7 In spection Pr ogram ................ .... .................... ...... ......... . ...... ......... ......................... 8 

## Index of T a b les Page 

### 1 2 

### 3 4 

### 5 

### 6 

### References ................... . .. . ........ .... . ....... . ................. .. . ......... ............. . . ...... ......... .. . . .. S t

ructural Limitations ................ ..... ........................... . .. ....... ............ ............. .. . .. . .... . Component Li mitations ........ . ................ .... . ..... .. ........................ .... ......................... . Miscellaneous Li mitations .... . .... ............... .. .. .... ... ...... ........ . . ........... . .. ... .. . ..... .... . .... . Component Life . ............. .... . ...... ..................... ...... ................. ...... .................. . . .. . ... . Supplemental Stn1cturallnspection Program .. . ... ................ . .... .. .. .. ... . ............... ... .. 

## References Table 1 References 

### Data mo du le!Technl cal p ub lication Title 12 -A-05-20-30 -0 0A -2 80A-A 12-A-20-40-00-00A-90 1A-A **\)PPLEMENTAL** STRUCTURAL IN SPEC TION DOCUMENT - INSPECTIONS CORROSION CON TROL -MAI NTE NANCE PRACTICES 1 

### 5 

### 5 6 8 9

12-A-27-00-01 -00 A-352A -A FLIGHT CONT ROLS- C O NTROL RODS - MAGN ETIC PART I CLE INSPECTION 12 -A-27 -00 - 0 1 -0 0A-353A-A 12-A-27-1 0 -00-0 0A-31 OA-A 12-A-27-1 0-08-00A-3528-A 12-A -27- 10-08-00A-353A-A 12-A-27 -1 0-08-00A-3538-A 

### Effectivity : All FLIGHT CONTROLS- CO NTRO L RODS • EDDY CURRENT INS PECT I ON AILERON CONTROL SYST EM - EXAMINE A I LERON CO NTROL SYSTEM - FU SELAGE BELLCRANK - MAG NETIC PARTICL E INSPECTION AILERON CONTROL SYSTEM- OUTER WING BELLCRANK - EDDY CU RRENT INSPECTION AILERON CONTROL SYS TEM - FUSELAGE BELLCRANK - EDDY CURR

_ ENT I N SPECT ION 12

-A-04-00-00-00A-OOOA-A UNCLASSIFIED 2014-03-13 Page 1

# ~PILATUS::"

Data moduleffechnlca l publi catio n 12 -A-27-1 0-09-00A-353A-A 12-A-27-20-00-<lOA-31 OA-A 12-A-27 -2 0-<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-27-51-0 1-00A-353A-A 12-A-27 -51-02-0QA-353A-A 1 2-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-31OA-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 CUR RENT INSPECTION RUDDER CONTROL SYSTEM - CABLE QUADRANT - EXAMINE E LEVATOR CONTROL SYSTEM- EXAMINE ELEVATOR CONTROL SYSTEM- CONTROL LEVER

- EDDY CURRENT INSPECT I ON 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'J T

**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 IN SPECTION DRAG LINK RIGHT PART- INSPECTLQN/CHECK PASSENGER/CREW DOOR - EXAM I NE EMERGENCY EXIT - EXAMINE CARGO DOOR - EXAMINE FUSELAGE -ANTENNA STRUCTURE - EXAMINE FUSELAGE -ANTENNA STRUCTURE- EDDY CURRENT INSPECTION FORWA8D FUSELAGE - EXAMINEFORWARDFUSELAGE-FRAME10LONGERONSEDDY CURRENT IN SPECTION FORWARD FUSELAGE- _ WINDOW STRUCTURE - EXAMINE CE NTER FUSELAGE - EXAMINE CE N TER FUSELAGE FRAMES- CARRY THROUGH FRAMES - EXAMINE
12-A-04-00-00-00A-OOOA-A UNCLASSIFIED 2014-03-13 Page 2

# ~PILATUS:::"'

Data modul eiTec hnlcal 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 -02-0Q A-31 OA-A 12-A-57 -00-00-00A-31 OA-A j 2 -A-57-00-03 - 00A-3 53A-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 

### Ti t l e 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 H I NGE- 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 - INSPECTIONIC HECK WINDSHIELD - EXAMINE COCKPIT SIDE WINDOWS - EXAMINE WINGS - EXAMINE WING AND FUSELAGE ATTACHMENT FITTING SEDDY CURRENT INSPECTION WING AND FUSELAGE ATTACHMENT FITTINGS - HOLLOW BOLTS - EDDY CURRENT INSPECTION WING STR UCTUR E - R I BS - EDDY CURRENT INSPECTION - RIB 6 STRAP WING STRUCTURE- SPARS AND AUXILIARY STRUCTURE -MAIN SPAR - EDDY CURRENT INSPECTION WING STRUCTURE - SPARS AND AUXILIARY STRUCTURE - REAR S PAR - EDDY CURRENT INSPECTION WING STRUCTURE- SPARS AND AUXILIARY STRl.J.CTURE- REAR SPAR - EDDY CURRENT INSP ECTIO N 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-OOO A-A UNCLASSIFIED 20 14-03-1 3 Page 3

# ~PILATUS::" UNCLASSIFIED 

### Data m o dul e!Tec hnica l publi cat i o n Tit l e 12-A-71-00-05-00A-352A-A POWERPLANT MOUNTING FRAME - MAGNETIC PARTICLE INSPECTION 

## Description 

## 1 Genera l 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 2 1 .29. The Airworthiness Limitations section Is FAA approved and specifies maintenance required under Parts 43.16 and 91.403 of the Federal Av iation Regulations unless an alternate program has been FAA approved . Refer to the P ilot'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). 532.20.12.14 0 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 Bulleti n 32-015/016/018 ). 532.10 . 12.050 with serial numbers AM 001 thru 053 ( Ref. Pilatus Service Bulletin 32-015/016/018 ) . 5 32 . 10.12 . 077 with serial numbers AM 001 thru 229 and all without primer and painted head (Ref. Pilatus Service Bulletin 32-012/018 ) . 5 32.10.12 . 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 w ith serial numbers lower than 10000 and all Vickers Flap Actuators ( P art No's 978 . 73 . 20 . 301 , 978.73.20 . 302/303/304 and 306).

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# ~PILATUS:F' UNCLASSIFIED 

## 2 Structural Limitations Table 2 Structural Limitations Structure 

### Life Fuselage and associated structure Pre SB

**0~009** 2 0,000 flying hours or 27,000 landings. whichever comes first Post S B

**0~09** 25,000 flying hours or 30,000 l andings, whichever comes first Wing structure Pre S B

**0~009** 20,000 flying hours or 27 , 000 landing s, 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 Po st SB

**0~09** 25,000 flying hours or 30,000 landings, whichever comes first Beyond 25,000 flying hou rs or 30,000 landings (whichever comes first) refer to th e Supplementa l Structural In spection Document (SS ID ) at Para 5 and 12·A-05-20-30-00A -280A-A for s upplemental structural inspections . 

## 3 Component Limitat i ons 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 Po st S B

**0~09** 25,000 flying hours or 30,000 landing s, whichever comes first Beyond 25,000 flying hours o r 30,000 landings (wh i chever comes first) refer to the Supplemental Structural Inspection Document (SS ID ) 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 (el apsed ). 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 landing s, 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 reclin e sys tem 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 (I PC 12-20-00-07) . Refer to AMM 12-A-27-40-02-00A-920A-A for fa il safe plate removal/installation. Effectivity : All 12 -A-04- 00-00-00A-OOOA-A UNCLASSIFIED 2014-03-13 Page 5

# ~PILATUS~ UNCLASS I F I E D Compon e nt Life Nose l and ing gear torque tube ( P/ N 532.50.12.047) 1 1 ,000 fly i ng hours or 15 ,000 l and i ngs o r 1 0 years installed, whichever comes first. Note 1 : Fire extinguishe rs that are 10 years o r older must be rep l aced by 30 June 2013. 

## 4 Miscellaneous Limitati o ns Table 4 Mis ceffaneous Umita t ions C omp o n e n t Limit ation Procedure Inboa rd flap drive arms Every 150 flying hours o r Annual In -si tu Inspection/Check , AMM I nspectio n (w hichever comes fir st) 12A27510000A313AA 

# I Cockpit outer side, DV windows If cracked or stress crazing ca n be Rep l ace and cabin w i ndows felt Cockpit inner and outer side, DV If chipped , cracked (only for inner R efer toAMM windows and cabin windows s ide windows), scratche<l, bubbles or

**12-A-~6:S.)O-OO-OOA-31~A-A** for l i mitations delaminated Windshield LH and RH If c racked i n inner l amination Rep lace If c racked in outer lamination Only unpressurized flight is permitted up to the next schedu l ed inspection providing it does not cause visual problems Horizontal stabilizer trim Every 3,000 fly ing hours or at An n ual F unctional test of Trim R unaw ay Aura l Inspectio n , w hichever comes first Warning System ( FAA CMR) in accordance with AMM 12-A-27-4Q-OO-OOA-903A -A NLG drag link right pa rt ( P/ N I n i tially 2,000 flying hours or 2 , 500 I nspection/check (refer to AMM 532.20.12.289 or 532.20.12.140) l andings (installed) whichever comes

**12-A 32-20**  **-06-00A-**

**~** 13A-A). firs t , then every 300 flying hours o r 400 landings, whichever comes first. Oxygen bottle R efer to AVOX Service Information Hydrostati c test L etter SIL-35-114 latest r evision Refer to AVOX Service Information Letter (www .avoxsys . com) . S I L- 35- 1141atest revision (www. avoxsys. c om ) . Pitch trim actuator (Part No . 1,500 flying hou r s Ove rh au l 978.73.14 . 20 1) Pitch t rim actuator ( Part No . 5 , 000 fly i ng hours or 5 years Overhaul 978.73.14.202 and (ins talled) whichever comes first. 978. 73. 14.203) Wing M ain Spar Fastener Ho les Threshold 16000 wing flying h ours or Eddy c urrent inspection, AMM Strap Rib 6 22500 wing landing s, whi c hever

**12 A-**  **~7** - 20 - 1O-OOA-353D-A comes first. No c rac ks a r e perm i tted . I f you find All wings with no landin g records cracks con ta ct P ilatus Aircraft for advice . mus t apply a calculated applicable land i ngs equal to 2 x flying hours. See Notes 1 and 2 below.

Effectivity: All 12 -A-04-00-00-00A-OOOA-A UNCLASSIF IED 2 014 -03 - 13 Pag e 6

## ~PILATUS:;r UNCLASSIFIED

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 B ulletin 04-009 Revision 1 or later. Wings w ith more than 15500 flying hours or 22000 landings, whichever comes first, must perform the inspection wi t hin the next 500 flying hours or 500 landings, wh ich ever 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 sup plemental inspections needed for aircraft that have 25,000 flying hours or 30,000 landings or more and forms the Supplemental Structural In spection Document (SS I D) needed to increase th e 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 SS I D is 50.000 flying hours or 60,000 landings, whichever comes first. The p art 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 SeN ice Centers can do the SSID as defined in Para 7 and in AMM 12

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

## 5.3 D eviation fro m Type Design Dev iations from the Type Design in critical locations could make the aircraft ineligible for th is life extension . Therefore: (a) all concessions, (b) all repairs, alteration s and modifications, (c) all STC installations must be assessed to find out if the aircraft will be eligible for th is li fe extension.The owner /operator is responsible to organi ze 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 :

Effectivity: All 12-A-04-00-00-00A-OOOA -A UNC LA SSIFIED 2014-03-13 Page 7

# ~PILATUS:?"' UNCLASSIFIED (a) Concess i ons- Only Pilatus can do this assessment. Pilatus sha ll be approached at least 5 months in advance. (b) Repairs, al terations and modifications - Any Authority approved Design Organ i zation or equivalent can do this assessment. (c) For th e aircraft modifications of the STC any Authority approved Design Organization or equivalent can do th is assessment. For the part of the STC itself the STC holder(s) only must do this assessmen t On request, Pilatus can do the assessments for ite m s (b) and the first part of (c) in addition to (a) above, provided sufficien t information is g i ven . 

## 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 Ma intenance Practices . The supplemental CPCP inspection tasks a r e identified in the column where a calendar time interval is given. The following additional threshold inspection requirement is applicable for all those CPCP i nspection tasks: the CPCP inspection task must be accomplished 6 years after Service Bulletin 04-009 has been accomplished the CPC P 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 l ife limited components as listed in Table 3 and Table 5 , which remain as safe-li fe. 

## 6 Component Life Table 5 Component Ufe Task No . Compon e nt Life (w hichever comes first) Flying Landing s Hour s 27-50/414 Flaps - Life Limit {discard) 25,000 30,000 55- 1 0/415 Horizontal S tabilizer- 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 N itrogen accumulator- Life Limit {discard) 25,000 30 , 000 

## 7 Inspection Program Only Pilat us authorised Service Centers can do this SS ID :

Effectivity : All 12-A-04-00-00-00A-OOOA-A
U N CLASSIFIED 2014-03-13 Page 8

# ~PILATUS::r UNCLASSIFIED Table 6 Supplemental Structural Inspection Program SUPP L EM E NTA L STRUCTURAL INSPECTION PROGRAM Ta sk No l n s pectionf Reference Threshold Repeated I nterval (whichever (whicheve r comes co mes first) first) Flying Landings Flying L andings Years Hours Hours 32-10/345 Ma in land i ng gear - Overhaul 25,000 30,000 8,300 10 ,000 6 CMM02099 Inspe ction kit P/ N 500.60.12 . 027 32-10/346 MLG Yoke fitting lugs - Eddy Current 25,000 30.000 8,300 10,000 Insp ection CMM 02099 32-10/347 MLG Trailing Link- Eddy Curren t 25,000 30 , 000 8 ,300 10 ,00 0 Inspection CMM02099 52-10/348 Passe nger/crew door- Examine a ll 32.500 42,000 12,500 15 ,00 0 

### 6 stru ctural e lements AMM

**12-A-~2 -10-0**  **0-00A-310A-A** 52-20/349 Emerg ency 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 - Exa mine all stru ctural 32,500 42,000 12,500 15,000 

### E element s AMM 12-A-52-30-00..QOA-310A-A 53-00/351 Upp er 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 F uselage Frames 10 to 16 - Examine all 32,500 42,00 0 12 ,500 1 5 ,0 00 

### € structural e l eme nts AMM 12-A-53-10-00-00A-3 1 0A-A Inspection kit PIN 500.60.12.033 53-00/353 Fuse lage Frames 16 to 36 - Exam ine all 32,500 42,000 12,500 15 ,000 

### 6 structural e lements AMM 12-A-5;2-2Q -OO-OOA-31

**OA- ~**  Inspection kit PIN 500.60.12 . 04 1 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-3 1 0A-A 53-00/355 Antenn a Structure - Exam ine 32,500 42,000 12 , 500 15 ,00 0 

### 6 AMM

**2-~·23-00-0 0-00A-**  **~10A-A** Effect ivity: All 12-A-04-00-00-00A-OOOA-A U N C LASS IFI ED 2014-03 - 13 Page 9

# ~PILATUS::" UNCLASSIFIED SUPPLEMENTAL STRUCTURAL I NSPECTION PROGRAM Ta sk No Inspect io n/ Reference Thre shold Repeated Interval (w h ichever (whichever comes co me s first) first) F l ying Landing s Flyi n g Landing s Years Hours Hour s 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 ski n - 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 Fram es 21 30,000 3g,ooo 10,000 12 ,0 00 

### 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 1 2-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 27-30/36 4 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 E l evator 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

# ~PILATUS:::r UNCLASSIFIED SUPPLEM ENTAL STRUCTURAL IN S PECTION PROGRAM Tas k No In spection/Reference Thresho ld Repeated In terval (whichever (whichever comes comes first) first) Flying Landings Fly ing L andings Years Hours Hours 55-20/367 E levator Drive Lever- Eddy Current 32,500 42 ,000 12,500 1 5,000 Inspection AMM

**12- A-**  **~~-2Q Q1:QQ**  **-3~3 A-A**  55-20/368 E levator Hinges - Eddy Current 32,500 42,000 12,500 15,000 I nsp ection AMM

**12 -5**  **5-20-01 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 Stabili zer Main and Rear Spar 32,500 42,000 12,500 15,000 Attachment to Fuselage - Ed dy Curren t Inspection AMM 12 -A-53-30-02-00A-353A-A o r AMM

**12 -A-55-3** 

**03 00A-35**  **A-A** 55-30/371 Vertical Stabilizer Main Attachm en t to 32,500 42,000 12,500 15 ,000 Horizontal S tabilize r - Eddy Current Inspection AMM 12-A-55-00-00-00A- 353A-A 55-30/372 V e rtical Sta bilizer Pi tch Trim Actuator 32,500 42,000 1 2.500 15,000 Fitting and Attach ment - 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 ,00 0 12,500 1 5,000 

### 6 AMM 1 2-A-27-20-00-00A-31 OA-A Inspection kit P/N 500.50 . 12.318 27-20/375 Rudder Be llc ranks - Eddy Current 32,500 42,000 1 2,500 15 , 000 Inspection AMM 12 -A-27

**20 04-00A-353A-~**  27-20/3 76 Rudder Cable Quadrant Shear Spigot - 32,500 42.000 1 2,500 15,000 

# e Examine AMM 12 -A-27-20 -05 -00A-310A-A 55-40 -377 R udder H inges - Eddy Current Inspection 32,500 42,000 12 , 500 15 ,00 0 AMM

**12-A-~~-40 -05**  **-00A 353A-A**  Effectivity: All 12-A-04-00-00-00A-OOOA-A UNCLASSIFIED 2014-03-13 Pag e 11

# ~PILATUS~ UNCLASSIF I ED SUPPLEMENTA L ST RUCTURAL INSPECTI ON PROGRAM Ta s k No In s p action/Ref erence Th r esho l d Rep eated Int erva l (w h i chever (w hi cheve r comes comes first) first) Flying Landings Flying La nding s Years Hours H o urs 56-11 /378 Windshield LH and RH and Cockpit Side 32 , 500 42,000 12 , 500 15 , 000 

### € Windows - Examine wi th w i ndsh ield 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! Hl QA-310A-A Inspection kit PI N 500 . 50.12.326 57-00/379 Wing - Examine ail structura l 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 Fu selage 30,000 39,000 10,000 12,000 Attachment - Edd y Current Inspection AMM

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

### and AMM

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

### Inspecti on ki t P / N 500 . 60.12 . 004 w i ng attachment Inspection kit P / N 500 .60 . 12.007 double bush 57- 00/382 Wing Rear Spar a t Rib 8 Flap 

### Arm 25,000 30,000 12 , 500 15,000 Attachment - Eddy Current Inspecti on 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-2 7-20-10-00A-353A-A Inspection kit P / N 500 . 60.12.030 or in spection kit PIN 500 . 60.12.020 57-00/384 Wing Main Spa r Fa ste ner Holes Strap Rib 25,000 30,00 0 3,300 4 , 000 6 - Eddy Current Inspec tion AMM 12-A-57-20-05-00A-353A-A I nspection kit PI N 500 . 60 . 12 . 031 or Inspection kit P / N 500 . 60 . 12.043 Effectivity: All 12 -A-04 -00-00-00A-OOOA-A UNCLASSIFIED 2 014 -03 - 13 P ag e 12

# ~PILATUS:F UNCLASSIFIED SUPPLEMENTAL STRU CTURAL IN S PE CT I O N PROGRAM T ask N o In s p ecti on/Ref eren ce Thres h o ld R epeate d I nterva l (wh ic h ever (whichever co m es comes first) first) 

### Fl yi n g L an ding s F l yin g La n din g s Years Ho ur s H o ur s 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 Mechan is m - 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 P IN 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 I nspection 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-5 1-02-00A-353A-A AMM

**12-A-27 -51-03-0**  **0A-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

# ~PILATUS:F' UNCLASS I FIED S UP P L E M EN TAL S TRU CTURA L INS PE CTION P ROGRAM T ask N o Inspectio n /Refere n ce Th reshold Repeated Interval (w h ichever (wh ic h eve r comes comes first) first) F lying l andings F lying l andings Years H o ur s Ho urs 27-50/392 Flap Belicranks - Eddy Current inspection 30,000 39,000 10,000 12,000 AMM 1 2-A-27-51-01-00A-353A-A AMM 12-A-27-5j-02-00A-353A-A AMM

**12-A-27-51 -0~::QO**  **A-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 Ai l eron Cab l e 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 Be licranks - Eddy Current and 32 , 500 42,000 12,500 15 ,000 Magnetic Parti cle 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 2 0 14-03-1 3 Page 14

# ~PILATUS::r UNCLASSIFIED



### The Airworthiness Limitations Section Is EASA Approved under Approval Number : 

## I 10048310 

## I Approval Date : - 27 February 2014

Effec t ivity: All 

### End of data module UNCLASS IFI ED 12-A -04-00-00-00A-OOOA-A

2014-03- 1 3 Page 15

# ~PILATUS:::"

Effectivity: All UNCLASSIFIED

I n ten t ionall y l eft b l a n k

End of data module

UNCLASS I FIED 12 -A-04-00-{)0 -00A-OOOA-A
2014-03-13 Page 1 6