# ~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 UNCLAS S IFIED @PI LATUS AIRCRAFT LTO . CH-637 1 STANS . SWITZERLAND

# I **~PILATUS~** 12-8-AM-00-00-00-1 U NCLASS I F I ED 

## AMM LIST OF REVISIONS 

## 1 Li st of Revisions Rev No. D ate 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 F UEL 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

Effectivity: All 12-8-00-00-00-00A-009A-A UNCLASSIFIED 

### 2014-05-22 Page 1

## ~PILATUS~ Chapte r N u m be r 35 4 5 46 52 53 55 56 57 61 71 

### 72 73 74 76 77 78 79 80

Effect i vity : All UNCLASSIFIED 

### Chapte r Title OXYGEN SYSTEM CENTRAL MAINTENANCE SYSTEM SYSTEMS INTEGRATION AND DISPLAY DOORS -GENERAL FUSELAGE STABILIZER S WINDOWS WINGS PROPELLER POWERPLANT ENGIN E ENGIN E FUEL AND CONTROL IGNITION S Y STEM ENGINE CO N TRO LS ENGIN E INDICATING- GENERAL EXHAUST OIL SYSTEM STARTING

End of data module UNCLASSI F IED 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-0 40A-A 12-B-53 - 00 -00-00A-040A-A 1 2-B-55-00-0 0-00A-040A-A 1 2-B -5 6-00-00 -00A-040 A -A 12-B -57 -OO-OO-OOA-040A-A 12- B -61 - 00-00-00A-04 0A-A 12- B -71 - 00-00-00A -04 0A-A 12- B -72 -00-00-00A-04 0A- A 1 2 - B -73-00-00-00A-040A- A 12-B-7 4 -00-0 0-00A-040A-A 1 2 -B-76-00-00-00A-040A -A 12-B-77-OO-OO-OOA-040A-A 12-B- 78 -00-00-00A-04 0A-A 12-B-79-00-00-00A-040A- A 12-B-80-00-00-00A-040A-A

1 2 -B-OO -OO -OO-OOA-009A-A 2014-05-2 2 Page 2

# ":5PILATUS~ UNCLASSIFIED 

## STRUCTURAL AND COMPONENT LIMITATIONS AIRWORTHINESS LIMITATIONS 

## Table of Contents Page STRUCTURAL AND COMPONENT LIMITATIONS- AIRWORTHINESS LIMITATIONS .......... 1 1 Ge neral. ................. .............. ................. . ............................ . ... . ..... . ... . ...................... 4 2 Structural Limitati ons ............... ... . ..... ................................................. ... . .. . ... . . .. ....... 5 3 Component Limitations ...... . ..... ........ . ..... ................ ..... .. . . .. .. . .............. ... ..... ... . .. .. .. ... 5 4 Miscellaneous Limitations ......... ... . .... ......... .. ..... . .. . ....... . . . . .. . .. . .. .. . ... . ..... . .... . .......... . . . 6 5 Supplemental Structural I nspection Document...... .. .. .. ......... ...................... ... . ....... 7 5 . 1 Limit of Validity. . . .................. .. .. .... ... .... ...... . ..... . ........... .. ........ . ........... . .................... 7 5 .2 Auth o ri sati on........ ................. . .. ........ .. ...... . .................. . . ... .. ... ........... . ...................... 7 5 .3 Devi ation from Type De s ign ........ . .. .. .... . .................. . . . .... ..... ................... .... ............ 7 5.4 Supplemental Corrosion Prevent i on and Con trol Program (CPCP ). ... . . ........ ... ...... 8 5 . 5 Damage Tolerance Evaluati on ........... . .................. ... . ... .. .... .. ... . ... . ........ ............ . . .. .. 8 6 Component Life.... ... . ... .. ......... . .... . .... . .. . .... .. .. . ............ . ..... .. .. . . .... .. . . . ....... ........ ...... . .. 8 7 Inspection Program....... ..... .... . .... .. ..... .. . . . . ... . .... .... ... . . ...... . ... . . . ... .. . ..... .. . .... . .. .. .. .. . . ... 9 

## Ind ex of Tab les Page 

### 1 2 

### 3 4 5 

### 6 Referen ces .............................. ..... ... . .. . .. .. . ................... . ............... . .......... . ... . .... . .. . . .. Structural Limitati ons ........ . ...... . ... ... . . .... .. .... . ... . .................. . ........ ... . .. ..... ........ ... ..... . Component Limitations .... . ...... ... .. ... .. .. . . . . .. . . . .. . ......... .. .. . ... . ........... . . .... .......... ... .. . .... . Miscellaneous Limitations . ..... .... ... . ... ... . ... .. .. ...... . ..... .. .. .. .. .......... ..... . ... . .... . ... .. .. . ... ... Component Life ... ...... .. ........ . ... .. ... .. . . .. .. .... ................ .. .. . ............................... . .. . .... .. Supplemental Structura l In spection Program .......... . ...................... . .... . ................ ..

Data modu l e/Technica l p u b l ication 

### 12-B-05-20-30-00A-280A-A 12-B-20-40-00-00A-901 A-A 12- B-2 1-30-00-00A-903A-A 12- B-27 -00-01-00A-352A-A 12- B-27 -00-01-00A-353A-A 1 2 - B-2 7- 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 Ta b le 1 References 

### Titl e 

### SUPPLEMENTAL STRUCTURAL INSPECTION DOCUMENT - INSPECTION$ CORROSION CONTROL - MAINTENANCE PRACTICES PRESSURIZATION CONTROL - ADJU STMENT /TEST FLIGHT CONTROLS- CONTROL RODS - MAGN ETI C PARTICLE INSPECTION FLIGHT CONTROLS - CONTROL RODS - EDDY CURRENT INSPECTION AILERON CQNTROL SYSTEM - E XAM INE AILERON CONTROL SYSTEM - FUSELAGE BELLCRANK - MAGNETIC PARTICLE INSPECTI ON AILERON CONTROL SYSTEM - OUTER WING BELLCRANK - EDDY CURRENT INSPECTION 1 

### 5 5 6 8 9

Effectivity : All 1 2-8 -0 4-00 -00-00A-OOOA-A UNCLASSIFIED 20 1 4-0 3- 13 Page 1

# ~PILATUS~

Data modulefTechnical publi ca tion 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 1 2-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-3 1OA-A 12-B-53-00-00..()0A-353A-A Effectivity : All UNCLASSIFIED
Title AILERON CONTROL SYSTEM- FUSELAGE BELLCRANK- EDDY CURRENT INSPECTION AILE RON CONTROL SYSTEM -FUSELAGE CABLE QUADRANT- EDDY CURRENT INSPECTION RUDDER CONTROL SYSTEM - EXAMINE RUDDER CONTROL SYSTEM- BELLCRANK - EDDY CURRENT INSPECTION RUDDER CONTROL SYSTEM- CABLE QUADRANTEXAM INE ELEVATOR CONTROL SYSTEM - EXAM I NE ELEVATOR CONTROL SYSTEM- CONTROL LEVER

- EDDY CURRENT INSPECTION HORIZONTAL STABILIZER TRIM- ADJUSTMENT/ TEST HORIZONTAL STAB I LIZER TRIM - TRIM ACTUATOR FA I LSAFE PLATES - REMOVAUINSTALLATI ON 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 CURREN T INSPECTI Q.r:l FLAP DRIVE SYSTEM -WI NG- CENTER MECHANISM - EDDY C URRENT IN SPECTION 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 EXTENSIO N SYSTEM - ELECTRO MECHANICAL LANDING GE;AR - ADJUSTME NT /TEST PASSENGER/CREW DOOR - EXAMINE EME RGENCY EXIT - EXAMINE CARGO DOOR- EXAMINE FUSELAGE -ANTENNA STRUCTURE - EXAMINE FUSELAGE ·ANTE NNA STRUCTURE - EDDY CURRENT INSPECTION 12-B-04-00-00-QOA-OOOA-A UNCLASSIFIED 2014..()3 - 13 Page 2

## ~PILATUS::"'

Data module/Te c hnical publi cation 12

-B-53-1 0-00 - 00A-31 OA-A 12-B-53-1 0-06-Q1A-353A-A 12

-B-53 - 10-16-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-56-11-0 1-00A-310A-A 1 2-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

Effectivi ty: All UNCLASSIFIED
Titl e FORWARD FUSELAGE - EXAMINE FORWARDFUSELAGE - FRAME 1 0LONGERONS - EDDY CURRENT INSPECTIO N FORWARD FUSELAGE- WINDOW STRUCTURE - EXAMINE CENTER FUSELAGE - EXAMINE CENTER FUSELAGE FRAMES- CARRY THROUGH FRAMES - EXAMINE CENTER FUSELAGE FRAMES - CARRY THROU GH FRAMES - EDDY CURRENT INSPECTION REAR FUSELAGE - EXAMINE REAR FUSELAGE FRAMES - EDD Y 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 VERTICA L STAB I LIZER SPARS- EDDY CURRENT INSPECTION RUDDER - EXAMINE RUDDER HINGE - EDDY CURRENT INSPECTION WINDOWS - INSPE CTION/CHECK WINDSHIELD - EXAMINE COCKPIT SIDE WINDOWS - EXAMINE WINGS -EXAMINE W I NG 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 -0 0-00A-OOOA -A UNCLASSIFIED 20 14-03-13 Page 3

## ~PILATUS:::"'

Data modulefTech ni ca l pub li cation 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 Gen e ral UNCLASSIFIED
Tit l e 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 A I LERONS -EXAMINE AILERON HINGE - EDDY CURRENT INSPECTION POWER PLANT TEST 3 -DC GENERATION SYSTEM

- ADJUSTMENT/TEST POWERPLANT MOUNTING FRAME - MAGNETIC PARTICLE INSPECTION 

## Descript ion

The Airworthiness Limitations section is EASA approved and variations must also be approved. The Airworthiness Limitations section i s also FAA approved for US registered aircraft in accorda nce 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 compo nents: 

### Nose L and ing Gea r 532.20.12.038 with serial numbers AM 001 thru 054 ( Ref. Pilatus Service Bu lleti n 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 Landi n g 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). 532.1 0 . 12 . 077 with serial number s AM 001 thru 229 and all without primer and painted head (Ref. P il atus Service Bullet in 32-012/018). 532.10.12.110 without marking "AT" or "VLG" (Ref. Pilatus Servi ce Bulletin 32-015). 

### Main Landing Gear S h ock Abso r ber 532.10.12.175 with serial numbers AM 001thru 107 (Ref. Pilatus Service Bull etin 32-016}. Effectivity: All 12- B-04-00-00 -00A-OOOA-A UNCLASSIFIED 2014-03-13 Page 4

# ~PILATUS~ UNCLASSIFIED

Main L a nding Gear Actu at ors 960.30.01.103 with serial numbers 830 E thru 881E (Ref . Pilatus SeNice Bulletin 32-017). F la p s 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). Pro p e ller Blade Propeller b l ade E10477K. 

## 2 Structural Limitations Table 2 Structural Limi t ations Structure Life Fuselage and associated structure Pre SB 04-009 20,000 flying hours or 27,000 landings. whichever comes first Po st SB 04.0 09 25,000 flying hours or 30,000 landings, whichever comes first Wing structure Pre S B 04-00 9 20,000 flying hours or 27 , 000 landings , whichever comes first Po st SB 04-0 09 25,000 flying hours or 30,000 land i ngs, whichever comes first Tail struct ure Pre SB 04-0 09 20,000 flying hours or 27 , 000 landings, whichever comes first P ost SB 04-0 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 Para 5 and AMM 12- B-05-20-30-00A-280A-A for the supplemental structural inspections . 

## 3 Component Limitations T

able 3 Component Limitations Component Life E n gine rotor co m pone n ts P &WC SB 14002 (latest revision) Engine mounting frame Pre SB 04-009 20,000 fl ying hours o r 27,000 landings, w hichever comes first Post SB 04-00 9 25,000 fl ying 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 supple m ental structural inspections . Engine mounting frame, replace all bolts. wash e rs and 11,000 flying hours nuts Pitch trim actuator 20,000 fly i ng 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)

Effec tivi ty: A ll 12-8- 04-00-00-00A-OOOA-A
U N CLASSIFIED 2014-03-13 Page 5

# ~PILATUS~ 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 M isce ll aneo us Li mitati o ns Table 4 Miscellaneous Limitations Component Li mitation Procedu re 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 inne r 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.

Effectivity: All 12-B-04-00-00-00A-OOOA-A
UNCLASSIFIED 2014-03-13 Page 6

# ~PILATUS::" UNCLASSIFIED Compon e nt Lim i tati o n Proce d u re 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 mech anical 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 exa mine the spri ngs, AMM 1 Z-B-32-1 O-Q6-00A-31

**~A-A** Time delay relays and powe r 2000 flying hours or at Annua l Functio n al test, A M M contactors Inspection, whichever comes first 12-B-32-30-08-00A-903A-A Electro mechanica l landing gear Oxygen bottle Refer to AVOX Service Information Hydrostatic test. Letter S I L-35 - 114 1 atest revision Refer to AVOX Service Information Letter (www.avoxsys.com ) . Sll-35-1141atest revision (www.avoxsys.com). Pitch trim actuato r (Part No. 5 , 000 flying h ours or 5 years Overhaul 978.73 . 14.202 and (insta ll ed) whicheve r comes first 978. 73.14 . 203) Wing Main Spar Fa stener Holes Thresho ld 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 la n ding records contact Pi latus Aircraft for advice. must apply a calculated applicable landings equal to 2 x flying hours. 

## 5 Suppl e mental Structura l Inspe ction Document This section and AMM 12-B-05-20-30-00A-280A -A give th e 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 Supp l emen t al Structural Inspection Document (SS I D) needed to increase the life of the airfram e. 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 Cen ters can do the SS I D, see Para 5.2. 

## 5 . 1 Limit of Va l idity The limit of validity (LOV) of the SSID is 50,000 flying hours or 60,000 landings, whicheve r comes first. The part of the SS I D for the w i ng structure (without systems and con t ro l 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 inelig i ble for this life extension. Therefore: Effectivity: All 12-B-04-00-00-00A-OOOA-A UNCLASSIFIED 2014-03-13 P age 7

# ~PILATUS~

(a) all co nces sions, (b) all repairs, alterations and modifications, (c) all STC installations U NCLASSIFIED

must be assessed to find out if the ai r craft will be eligible for this life extension.The owner/operator is responsible to organi ze these assessments well in advance of the fi r st 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 mod ifi cations - 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 itsel f 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 i s 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-20-40-0 0-QOA-90 1 A-A for Corrosion Control Maintenance Practices. The su pplemental CPCP inspection tasks are id entified in the column where a calendar time interval is given. The following additional threshold inspection requi rement is applicable for all those CPCP inspection ta sks: the C P CP inspection task must be accomplished 6 years after Service Bulletin 04=009 has been accomplished the C P CP inspection task must not be accomplished before the aircraft reaches 25,000 flying hours or 30 , 000 landings. 

## 5 . 5 Damage Tolerance Evaluat io n The en ti re ai rcraft structure is subject to Dam age To le rance Evalua tion when modified or repa i red, except for li fe limited components as l isted in Table 3 and Table 5, which remain as safe-li fe . 

## 6 

## Component Life Table 5 Component Life Ta sk No. Component 

### Life (whi cheve r comes first) Flying Landing s Ho urs 27-50/4 1 4 F l aps- Life Limit (discard) 25,000 30,000 55-10/4 15 Horizontal Stabilizer- Li fe Limit (disca rd) 25,000 30,000 32-20/416 NLG Drag Link - Life Limit (discard) 25,000 30,000 32-30/4 17 MLG Actuator- Life Limit {discard) 25,000 30,000 29-10/418 Nitrogen accumulator - Life Limit (disca rd) 25,000 30,000
Effectivity: All 12- B-04-00-00-QOA-OOOA-A UNCLASS I FIED 2014-03-13 Page 8

## ~PILATUS::r UNCLASS I F I ED 

## 7 I n specti o n Program Only Pilatus authorised Service Centers can do th i s SSID: 

### Table 6 Supplemental Structural Inspection Program SUPPLEMENTAL STRU CTURAL I NSPE CTION P ROGRAM T ask No lns pectlonf R ef e ren ce Thres h o l d Rep eat ed I n te rv a l (whi c h eve r (wh icheve r co m es c o m es fi r st) first ) F ly ing L a nd in gs Fl y ing Land ing s Years Ho ur s H o u rs 32-10/345 Main landing gea r - Overhaul 25,000 30,000 8,300 10,000 

### 6 CMM 02099 Inspection kit P/N 500.60. 1 2.027 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 I nspection 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 1 5 ,000 

### € ele m ents AMM

**12-B-52-20-00-00A**

**~1** OA-8 52-30/350 Cargo door - Exam i ne all structural 32 , 500 42,000 12 , 500 1 5, 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 I nspection 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 1 5, 000 6 structural elements AMM 12- B-53- 1 0-00-00A-310A-A Inspectio n kit P/N 500.60.12 .034 53-00/353 F uselage Frames 16 to 36- Examine all 32,500 42 , 000 12,500 15 , 000 

### 6 structural elemen ts AMM

**12-B**

**~- 2Q-**  **QQ :QOA-3108** 

**A** Inspection kit P/ N 500.60.12.042 53-00/354 F uselage Frames 36 to 43 - Examine all 32,500 42,000 12,500 15,000 

### E structura l eleme nts AMM 12-B-53-30-00-00A-310A-A Effecti vity: All 12-B-04- 00 -0 0-0 0A-O OOA -A UNCLASSIFIED 2 014-03-13 P ag e 9

## ~PILATUS~ UNCLASS I FIED SUPPLEMENTAL STRU CTURAL INSPECTION PROGRAM Task No I ns p ec t ion/Refe rence Th res h o l d Re p eated I nterva l (w h ichever (whichever comas comas fi r st) 

### first) Fl y ing L a nd i n gs F l ying L a ndi ngs Years Ho ur s Ho urs 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 F r ames 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**

**-0 2-00A-353A-A**  or AMM

**12-B-~~-30 -Q3-00**  **A-353A-8** 55-20/362 Elevato r - 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 - Examin e 32,500 42 , 000 12,500 15 ,0 00 6 AMM

**12-B-27-~Q-**

**QQ -OOA-310A-A**  Inspecti on kit P/N 500.60.12. 019 27-30/364 E l evator Contro l 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 ,0 00 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 I nspection 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 In s p e ction/Reference Threshold Re p eated Interval (which ev e r (wh i chever comes co mes firs t ) fir st) Fly i ng Land i ng s Fl y in g L and in g s Years H o urs Ho u rs 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 AM M 12-B-55-2Q-Q1::QO A- 353 A-8 55-30/369 Vertical Stab i l izer - Exa mine 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 A M M 12-B-55-30-03-00A -353A-A 55-30/37.1 Vertical Stabi l izer Main Attachment to 32,500 42,000 12,500 1 5,000 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 R udde r - Exam i ne 32 , 500 42,000 1 2 .500 15,000 

### E AMM

**12-[~-5~·40-00-00A-31QA-A** 27-20/374 Rudder Control System - E xamine 32,500 42,000 12 ,5 00 15,000 

### € AMM 12-B-27-20-00-00A-31 OA-A Inspection kit PIN 500.60 . 12 .0 18 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 Quadran t Shear Spigot - 32 ,500 42 , 000 12 ,50 0 15,000 

### € Examine AMM 12- B-27-20-05-00A-310A-A 55-40-377 Rudder Hinges - Eddy Current Inspection 32,500 42 ,0 00 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 ST RUCTURAL IN SP E CTI ON PROGRAM Task No I nspection/Refer ence 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 ,50 0 15,000 6 Windows - Examine with windshield and side windows removed AMM

**12-B-56-11**

**-0 :QQA-~l0**  **A-A** and AMM 12-B-56-11 -02-0QA-3 10A-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-31Q A-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-3 53A-A Inspection ki t 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 Ins pection AMM

**12-B-57 20-Q~·QQA-353A-A**  Inspection kit P/N 500.60.12.031 or Inspection kit PI N 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 I nspection/Reference Th r eshold Repeated I nterval (whichever (whichever comes comes first) 

### first) Flying landings Flying Landing s Yea r s Hour s Hours 57 -00/3 85 Wing Rear Spar Faste ner Ho les R ib 2 25,000 30,000 12,500 15 , 000 thru Rib 3 - Eddy Current Inspection AMM 12- B-57-20-10-00A-353 8-A 27-50/386 Flap Me chanis m - 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 Inspectio n kit P/N 500.60.12.022 Inspection kit P/N 500.60.12.023 Inspection kit PI N 500.60 . 12.024 Inspection ki t 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 Curren t 30,000 39 , 000 10,000 12,000 Insp ection 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 - E ddy 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 27-50/3 90 F lap Cove Rib Fittings - Eddy Current 30,000 39 ,0 00 10,000 12,000 I nspecti on 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 2 7 -50-391 Flap Aft Links - Eddy Current Inspection 30,000 39 , 000 10 , 000 12 , 000 AMM 1 2- 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 1 3

# ~PILATUS~ UNCLASSIFIED SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM Task No Inspection/Reference Thresho ld Repeated Interval (whichever (whichever comes comes first) first) Fly ing 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-27-5 1-03::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 I nspection kit P/N 500.50.12.314 Inspe ction kit PIN 500 . 60.12.035 Inspection ki t PIN 500 . 60.12 . 016 27-10 /395 Aileron Cable Segment - Eddy Current 32,500 42,000 12 ,500 15,000 Inspection AMM 1 2-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 1 2,500 15,000 Inspection AMM 12-B-27-00-01-QQ A-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 H inge 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 Effe c ti vity : All End of dala module UNCLASSIFIED 1 2-B-Q4-00 -Q O-QOA-QOOA-A 2014-Q3-13 Page 14 

## I I