List of Revisions

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UNCLASSIFIED

List of Revisions

Rev No. Date of lssue Date lnserted SignatureAll previous revisions incorporated.

18 Sep 25103 Oct 16/08 Pilatus19 MarOl/09 Mar23/09 Pilatus20 Revision 20 issued with Revision 2121 Dec 15/09 Dec 15/09 Pilatus22 Apr 15/10 Apr 15/10 Pilatus23 Mar 30/1 1 Mar 30/11 Pilatus24 Dec 20/1 1 Dec 20/1 1 Pilatus25 Jan 30/12 Jan 30112 Pilatus26 Dec 15/12 Dec 15/12 Pilatus27 Dec 15/13 Dec 15/13 Pilatus28 May 31/14 May 31/14 Pilatus29 Nov 30/14 Nov 30/14 Pilatus30 Aug 31/15 Aug 31/15 Pilatus31 Nov 16/15 Nov 16/15 Pilatus

Effectivity: ALL 1 2-A-00-00-00-OOA-004A-A

End of data module

1

UNCLASSIFIED 201 5-11-10 Pagel

‘PILATUS 12-A-AM-OO-OO-OO-lUNCLASSIFIED

STRUCTURAL, COMPONENT AND MISCELLANEOUS

AIRWORTHINESS LIMITA TIONS

Table of Contents Page

STRUCTURAL, COMPONENT AND MISCELLANEOUS - AIRWORTHINESS LIMITATIONS 11 General 42 Structural Umitations 53 Component Limitations 54 Miscellaneous Limitations 65 Supplemental Structural Inspeotion Document 75,1 Limit ofValidity 75.2 Authorisation 75.3 Deviation from Type Design 85.4 Supplemental Corrosion Prevention and Control Program (CPCP) 85.5 Damage Tolerance Evaluation 86 Component Life 97 Inspection Program 9

Index of Tables Page1 References 12 Structural Limitations 53 Component Limitations 54 Miscellaneous LimitaUons 65 Component Life 96 Supplemental Structural Inspection Program 9

ReferencesTable 1 References

Data module/Technical publication Title

12-A-05-20-30-OOA-280A-A SUPPLEMENTAL STRUCTURAL INSPECTIONDOCUMENT - INSPECTIONS

12-A-2040-D0-OOA-901A-A CORROSION CONTROL - MAINTENANCEPRACTICES

12-A-27-0O-01-OOA-352A-A FLIGHT CONTROLS — CONTROL RODS - MAGNETICPARTICLE INSPECTION

12-A-27-0O-Ol-OOA-353A-A FLIGHT CONTROLS — CONTROL RODS - EDDYCURRENT INSPECTION

1 2-A-27-l 0-O0-OOA-31 OA-A AILERON CONTROL SYSTEM - EXAMINE

1 2-A-27-l 0-08-OOA-352B-A AILERON CONTROL SYSTEM — FUSELAGEBELLCRANK - MAGNETIC PARTICLE INSPECTION

12-A-27-l0-08-OOA-353A-A AILERON CONTROL SYSTEM — OUTER WINGSELLCRANK - EDDY CURRENT INSPECTION

12-A-27-lO-08-OOA-3538-A AILERQN CONTROL SYSTEM — FUSELAGESELLCRANK - EDDY CURRENT INSPECTION


UNCLASSIFTED 2015-09-26 Pagel

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UNCLASSIFIED

Data modulerrechnical publication

1 2-A-27-1 O-09-OOA-353A-A

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

1 2-A-27-20-04-OOA-353A-A

1 2-A-27-20-05-OOA-31 OA-A

1 2-A-27-30-00-OOA-31 OA-A

1 2-A-27-30-05-OOA-353A-A

1 2-A-2740-O0-00A-903A-A

1 2-A-2740-02-OOA-920A-A

1 2-A-27-51 -00-OOA-31 OA-A

1 2-A-27-51 -O0-OOA-31 3A-A

1 2-A-27-51 -00-OOA-353A-A

1 2-A-27-51 -01-OOA-353A-A

1 2-A-27-51 -02-OOA-353A-A

1 2-A-27-51 -03-OOA-353A-A

1 2-A-32-1 0-00-OOA-31 OA-A

1 2-A-32-20-06-OOA-31 3A-A

1 2-A-52-1 0-O0-OOA-31 OA-A

1 2-A-52-20-00-OOA-31 OA-A

1 2-A-52-30-0O-OOA-31 OA-A

1 2-A-53-00-00-00A-31 OA-A

1 2-A-53-D0-00-00A-353A-A

1 2-A-53-1 0-00-OOA-31 OA-A

1 2-A-53-1 0-06-01A-353A-A

1 2-A-53-1 0-1 6-OOA-31 OA-A

1 2-A-53-20-00-OOA-31 OA-A

1 2-A-53-20-02-OOA-31 OA-A

Title

AILERON CONTROL SYSTEM — FUSELAGE CABLEQUADRANT - EDDY CURRENT INSPECTION

RUDDER CONTROL SYSTEM - EXAMINE

RUDDER CONTROL SYSTEM — BELLCRANK - EDDYCURRENT INSPECTION

RUDDER CONTROL SYSTEM — CABLE QUADRANT -

EXAMINE

ELEVATOR CONTROL SYSTEM - EXAMINE

ELEVATOR CONTROL SYSTEM — CONTROL LEVER- EDDY CURRENT INSPECTION

HORIZONTAL STABILIZER TRIM - ADJUSTMENT/TEST

HORIZONTAL STABILIZER TRIM —TRIM ACTUATORFAILSAFE PLATES - REMOVAUINSTALLATION

FLAP DRIVE SYSTEM - EXAMINE

FLAP DRIVE SYSTEM - IN SITU INSPECTION/CHECK

FLAP DRIVE SYSTEM - IN SITU EDDY CURRENTINSPECTION

FLAP DRIVE SYSTEM — WING — INBOARDMECHANISM - EDDY CURRENT INSPECTION

FLAP DRIVE SYSTEM — WNG — CENTERMECHANISM - EDDY CURRENT INSPECTIQN

FLAP DRIVE SYSTEM — WNG — OUTBOARDMECHANISM - EDDY CURRENT INSPECTION

MLG AssembIv Baits aand Nuts - Examine

DRRG LINK RIGHT PART - INSPECTIONICHECK

PASSENGERICREW DOOR - EXAMINE

EMERGENCY EXIT - EXAMINE

CARGO DOOR - EXAMINE

FUSELAGE - ANTENNA STRUCTURE — EXAMINE

FUSELAGE - ANTENNA STRUCTURE — EDDYCURRENT INSPECTION

FORWARD FUSELAGE - EXAMINE

FORWARD FUSELAGE — FRAME 10 LONGERONS -

EDDY CURRENT INSPECTION

FORWARD FUSELAGE — WINDOW STRUCTURE -

EXAM IN E

CENTER FUSELAGE - EXAMINE

CENTER FUSELAGE FRAMES — CARRY THROUGHFRAMES - EXAMINE


UNCLASSIFIED 2015-09-28 Page 2

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Data module/Technical publication

1 2-A-53-20-02-00A-353A-A

1 2-A-53-30-0O-OOA-31 OA-A

1 2-A-53-30-02-OOA-353A-A

1 2-A-55-00-0O-OOA-353A-A

1 2-A-55-20-0O-OOA-31 OA-A

1 2-A-55-20-O1-OOA-353A-A

1 2-A-55-30-00-OOA-31 OA-A

1 2-A-55-30-02-OOA-353A-A

1 2-A-55-30-03-OOA-353A-A

12-A-5540-00-OOA-31 OA-A

1 2-A-55-40-05-OOA-353A-A

1 2-A-56-00-OO-OOA-31 3A-A

1 2-A-56-1 1 -01-OOA-31 OA-A

1 2-A-56-1 1 -02-OOA-31 OA-A

1 2-A-57-00-O0-OOA-31 OA-A

1 2-A-57-00-03-OOA-353A-A

1 2-A-57-0O-03-O1A-353A-A

1 2-A-57-20-05-00A-353A-A

1 2-A-57-20-1 D-00A-353A-A

1 2-A-57-20-1 0-OOA-353B-A

1 2-A-57-20-1 0-OOA-353C-A

1 2-A-57-20-1 O-00A-353D-A

1 2-A-57-60-0O-OOA-31 0A-A

1 2-A-57-60-06-OOA-353A-A

Title

CENTER FUSELAGE FRAMES — CARRY THROUGHFRAMES - EDDY CURRENT INSPECTION

REAR FUSELAGE - EXAMINE

REAR FUSELAGE FRAMES - EDDY CURRENTINSPECTION

VERTICAL STABILIZER AHACHMENT FIHINGS -


ELEVATORS - EXAMINE

ELEVATOR DRIVE LEVER AND HINGE - EDDYCURRENT INSPECTION

VERTICAL STABILIZER - EXAMINE

VERTICAL STABILIZER — PITCH TRIM ACTUATORAHACHMENT - EDDY CURRENT INSPECTION

VERTICAL STABILIZER SPARS - EDDY CURRENTINSPECTION

RUDDER - EXAMINE

RUDDER HINGE - EDDY CURRENT INSPECTION

WINDOWS - INSPECTION!CHECK

WNDSHIELD - EXAMINE

COCKPIT SIDE WiNDOWS - EXAMINE

WINGS - EXAMINE

WING AND FUSELAGE ATACHMENT FIHINGS -


WING AND FUSELAGE AHACHMENT FIHINGS —

HOLLOW BOLTS - EDDY CURRENT INSPECTION

WING STRUCTURE — RIBS - EDDY CURRENTINSPECTION — RIB 6 STRAP

WING STRUCTURE — SPARS AND AUXILIARYSTRUCTURE — MAIN SPAR - EDDY CURRENTINSPECTION

WING STRUCTURE — SPARS AND AUXILIARYSTRUCTURE — REAR SPAR - EDDY CURRENTINSPECTION

WING STRUCTURE — SPARS AND AUXILIARYSTRUCTURE — REAR SPAR - EDDY CURRENTINSPECTION

WING STRUCTURE — SPARS AND AUXILIARYSTRUCTURE — MAIN SPAR — RIB 6 STRAPFASTENER - EDDY CURRENT INSPECTION

AILERONS - EXAMINE

AILERON HINGE - EDDY CURRENT INSPECTION



‘PILATUS 12-A-AM-00-00-00-lUNCLASSIFIED

Data moduleffechnical publication Title

1 2-A-71 -00-05-OOA-352A-A POWERPLANT MOUNTING FRAME - MAGNETICPARTICLE INSPECTION

Description

1 General

The Airworthiness Limitations section is FASA approved and variaUons must also be approved.

The Aiiworthiness Limitations section is also FM approved for US registered aircraft in accordance with FAR21.29.

The Airworthiness Limitations section is FAR approved and specWies maintenance required under Parts 43.16 and91.403 of the Federal Aviation Regulations unless an alternate program has been FA approved.

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

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

Nose Landing Gear

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

532.2012039 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

5321012.049 with senat numbers AM 001 thru 053 (Ref. Pilatus Service Bulletin 32-015/016/018).

532.1012050 with senial numbers AM 001 thru 053 (Ref. Pilatus Service Bulletin 32-015/016/018).

532.10.12.077 willi senial numbers AM 001 thw 229 and all without pdmer and painted head (Ref. Pilatus ServiceBulletin 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 001 thru 107 (Ref. Pilatus Service Bulletin 32-016).

Main Landing Gean Actuators

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

Flaps

FCWU 99-3 with serial numbers lower than 10000 and all Vickers Flap Actuatons (P/N‘s 978.73.20.301,978.73.20.302/303/304 and 306).


UNCLASSIFIED 201 5-09-28 Page 4

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2 Structural Limitations

TaUe 2 Structur& UmitationsStructure UteFuselage and associated structure Pre SB 04-009 20,000 flying hours Dr 27,000 landings,

whichever comes firstPost SB 04-009 25000 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 firstPost SB 04-009 25,000 flying hours or 30,000 landings,whichever comes first

Tau structure Pre SB 04-009 20,000 flying hours or 27,000 landings,whichever comes firstPost 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 the Suppiemental Structurallnspection Document (SSID) at Para Sand 1 2-A-05-20-30-OOA-280A-A for supplemental structural inspections.

Component Limitations

Ta Mc 3 Component LimitationsComponent Life LimitEngine rotor components P&WC SB 14002 (latest revision)

Pre SBO4-00920,000 flying hours or 27,000 landings,whichever comes firstPost SB 04-009 25,000 fiying hours or 30,000 landings,whichever comes first

Beyond 25,000 flying hours or 30,000 landings (whichever comes first) refer to the Supplemental StwcturalInspection Document (SSID) at Para Sand 12-A-0S20-30-OOA-280A-A for supplemental structural inspections.Engine mounting frame. replace all bolts. washers and 1 1,000 flying hoursnutsPitch tdm actuator 20,000 flying hours or 27,000 landings, whichever comes

firstFlap actuator (PIN 978.73.20.307, 308 and 309) 20,000 flying hours or 27,000 landings, whichever comes(black anodized) firstFire extinguisher 10 years (elapsed). See Note 1 below.Oxygen boftle 15 years (elapsed)NLG upper right hand drag link (PIN 532.20.12.140) 4,000 landings(Pre SB 32—014)Cargo door lower lug fittings (Qty 3) 13,000 flying hours or 17,000 landings, whichever comes

tirstBackrest tubes on crew seats with a rechne system 5,000 flying hours(Seat PIN‘s 959.30.01.111, 112, 121 and 122)Backrest tubes on crew seats without a rechne system 10,000 flying hours(Seat P/N‘s 959.30.01.131, 132, 133 and 134)Pitoh trim actuator attachment parts, fail safe plates 10,000 flying hoursand their attachment parts (IPC 12-20-00-07). Refer toAMM 1 2-A-27-40-02-OOA-920A-A for fail safe plateremovah/installation.


3

Engine mounting frame

1

UNCLASSIFIED 201 5-09-28 Page 5

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UNCLASSIFIED

Component Life LimitNase landing gear torque tube (PIN 532.50.12.047) 11,000 flying hours er 15000 landings cr10 years

installed, whichever cames first.Note 1

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

4 Miscellaneous Limitations

Table 4 Miscellaneous LimitationsComponent Limitation Procedurelnboard flap drive arms Every 150 flying hours er Annual ln-situ lnspection/Check, AMM j.

Inspection (whichever comes first) A-27-51-00-OOA-31 3A-ACockpit outer side, DV windows If cracked Replaceand cabin windowsCockpit inner and outer side, DV If chipped, cracked (only für inner Refer to AMM 1 2-A-56-00-00-OOA-31 3A-windows and cabin windows side windows). crazing, scratched, a for limitations

bubbies er delaminatedWindshield LH and RH If cracked in inner lamination Replace

If cracked in outer lamination OnIy unpressurized flight is permitted upto the next scheduled inspectionproviding it does not cause visualproblems

Horizontal stabilizer trim Every 3,000 fiying hours or at Annual Functional test of Trim Runaway AuralInspection, whichever comes first Waming System (FAA CMR) in

accordance with AMM 12-A-27-40-00-OOA-903A-A

Main landing gear leg forward 6 years Examine (refer to AMM jattachment bolt and rear A-32-10-00-OOA-310A-A)attachment bolt and nut See Note 3 below

Main landing gear actuator top 6 years Examine (refer to AMM j.and bottam affachment bolts and A-32-10-00-OOA-310A-A)nuts See Note 3 below

Main landing gear shock At Annual lnspection Examine (refer to AMM jabsorber top and bottom A-32-1 0-00-OOA-31 OA-A)attachment bolts and nutsNLG upper right hand drag link lnitially 2,000 flying hours or 2,500 lnspectionfcheck (refer to AMM 12(P/N 5322012.289 or landings (installed) whichever comes A-32-20-06-ODA-313A-A).532.20.12.140) first, then every 300 flying hours or

400 landings, whichever comes firstOxygen bottle Refer to AVOX Service Information Hydrostatic test.

Letter SIL-35-1 14 latest revision(www.avoxsys.com) Refer to AVOX Service Information Letter

SIL-35-114 latest revision(www.avoxsys.com).

Pitch trim actuator (PJN 1500 flying hours Overhaul978.73.14.20 1)


11

1111


PILATUS‘UNCLASSIFIED

Component Limitation ProcedurePitch trim actuator (P/N 5,000 flying hours cr5 years Overhaul978.7314202 and (installed) whichever comes fcrst978.7314203)

er

4,200 flying hours er 6 years(instafled) whichever comes first

or

3,400 flying hours er 7 years(installed) whichever comes first

Wng Main Spar Fastener Holes Threshold 16,000 wing flying hours Eddy current inspection, AMM 12-Strap Rib 6 or 22,500 wing landings, whichever A-57-20-10-OOA-353D-A

comes first.No cracks are permitted. If you find

All wings with ne landing records cracks contact Pilatus Aircraft for advice.must apply a calculated applicablelandings equal to 2 x flying hours.

See Notes 1 and 2 below

Note 1

The inspection is applicable to all aircraft except MSN 170, 222, 233, 234, 237, 240, 244, 250 and 324 which haveperformed the inspection as part of a fleet leader inspection survey and aircraft that have performed ServiceBulletin 04-009 Revision 1 or later.

Note 2

Wings with more than 15,500 flying heurs or 22.000 landings, whichever cames first, must perform the inspectionwithin the next 500 flying hours er 500 landings, whichever comes first.

1 Note 3

1 Aircraft with aftachment bolts and nuts that are 6 years or older must be examined by 30 June 2016.

5 Supplemental Structural Inspection Document

This section and AMM 1 2-A-05-20-30-OOA-280A-A give the additional structural and component life limits and thesupplemental inspections needed for aircraft that have 25,000 flying hours er 30,000 landings er mere and formsthe Supplemental Structural lnspection Decument (SSID) needed te increase the life of the airframe.

Service Bulletin 04-009 must be accomplished le allow an aircraft tobe operated up to 25,000 flying heurs er30,000 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 er 60,000 landings, whichever comes first. The part ofthe SSID fer the wing structure (without systems and centrel system structure such as flaps and ailerons) has alewer LOV ef 35,000 fiying haurs er 43,000 landings, whichever comes first.

5.2 Authorisation

Only Pilatus autharised Service Centers can da the SSID as defined in Para 7 and in AMM jA-05-20-30-OOA-280A-A.



PILATUSr 12-A-M-00-O0-O0-IUNC LASS IFIED

5.3 Deviation from Type Design

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

(a) all concessions,

(b) all repairs, alterations and modifications,

(c) all STC installations

must be assessed to lind out if the aircraft will be eligible for this life extension. The owner/operator is responsibleto organize these assessments weIl in advance of the first SSID inspection. There rnust be a clear statement forthe 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 inadvance.

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

(c) For the aircraft modifications of the STC any Authority approved Design Organization or equivalent can dothis 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, providedsufficient 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 1 2-A-20-40-00-OOA-901A-A forCorrosion Control Maintenance Practices.

The supplemental CPCP inspection tasks are identifled in the column where a calendar time interval is given. Thefollowing 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 25000 flying hours or 30000landings.

5.5 Damage Tolerance Evaluation

The entire aircraft structure is subject to Damage Tolerance Evaluation when modified or repaired, except for lifelimited components as listed in Table 3 and Table 5, which remain as safe-life.

Effectivity: ALL 1 2-A-04-00-O0-OOA-000A-A


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UNCLASSIFIED

6 Component Life

Table 5 Component Life

Task No. Component Life (whlchever comesfirst)

Flying LandingsHo urs

27-50/414 Flaps - Life Limit (discard) 25000 3000055-10/415 Horizontal Stabilizer- Life Limit (discard) 25000 3000032-20/416 NLG Upper Right Hand Drag Link (except for PIN 532.20.12140) - 25000 30,000

Life_Limit_(discard)32-30/417 MLG Actuator - Life Limit (discard) 25,000 30,00029-10/418 Nitrogen accumulator- Life Limit (discard) 25,000 30,000

7 Inspection Program

Only Pilatus authorised Service Centers can do this SSID:

Table 6 Supplemental Shvctural Inspection PmgramSUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM

Task Na lnspectionlReference Tflreshold Repeated Interval (whichever(whichever comes comes first)

fast)Flying Landings Flying Landings VearsHours Hours

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

CMM 02099

lnspection kit P/N 500.60.12.02732-10/346 MLG Yoke fitting lugs - Eddy Current 25,000 30000 8,300 10,000

1 nspection

CMM 0209932-10/347 MLG Trailing Link - Eddy Current 25,000 30,000 8,300 10,000

lnspection

CMM 0209952-10/348 Passengedcrew door - Examine all 32,500 42,000 12,500 15,000 6

structural elements

AMM 1 2-A-52-1 0-00-OOA-31 OA-A52-20/349 Emergency door - Exarnine all structural 32,500 42,000 12,500 15,000 6

elements

AMM 1 2-A-52-20-00-OOA-31 OA-A52-30/350 Cargo door - Examine all structural 32,500 42,000 12,500 15,000 6

elements

AMM 1 2-A-52-30-00-OOA-31 OA-A


1


PlLATUS 1 2-A-AM-00-00-00-lUNCLASSIFIED

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAMTask Na lnspectionlReference Threshold Repeated Interval (whichever

(whichever comes comes first)first)

Flying Landings Flying Landings YearsHours Hours

53-00/351 Upper Longerons Frame 10- Eddy 25000 30000 12,500 15,000Current Inspeotion

AMM 1 2-A-53-1 0-06-01 A-353A-A

Inspeetion kit P/N 500.60.12.03253-00/352 Fuselage Frames 10 to 16- Examine all 32,500 42,000 12,500 15,000 6

stmctural elements

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

lnspection kit P/N 500.60.12.03353-00/353 Fuselage Frames 16 to 36- Examine all 32,500 42,000 12,500 15,000 6

structural elements

AMM 1 2-A-53-20-00-OOA-31 OA-A

lnspection kit P/N 500.60.12.04153-00(354 Fuselage Frames 36 to 43- Examine all 32,500 42,000 12,500 15,000 6

structural elements

AMM 1 2-A-53-30-00-OOA-31 OA-A53-00(355 Antenna Structure - Examine 32,500 42,000 12,500 15,000 6

AMM 12-A-53-00-00-OOA-31 OA-A53-00/356 Antenna - Boffom fuselage skin - Eddy 28,300 37,000 8,300 10,000

Current lnspection

AMM 1 2-A-53-00-00-OOA-353A-A53-00/357 Antenna - Upper fuselage skin - Eddy 32,500 42,000 12,500 15,000

Current lnspection

AMM 1 2-A-53-00-00-OOA-353A-A53-00/358 Upper Flange Cany Through Frames 21 30,000 39,000 10,000 12,000 €

and 24 - Examine

AMM 12-A-53-20-02-OOA-31 OA-A

lnspection kit P/N 500.50.12.32753-00/359 Frames 21 and 24 Wing Attachments - 30,000 39,000 10,000 12,000

Eddy Current lnspection

AMM 1 2-A-53-20-02-OOA-353A-A53-00/360 Frames 21 and 24 Side Frame 30,000 39,000 10,000 12,000

Attachments - Eddy Current lnspection

AMM 1 2-A-53-20-02-OOA-353A-A



flas a — a sfl—II I. II—• .n. w 12-A-AM-00-00-00-I

UNCLASSIFIED

SUPPLEMENTAL STRUCTURAL INSPEGTION PROGRAMTask No InspectionlReference Threshold Repeated Interval (whichever

(whichever comes comes ffrst)first)


53-00/361 Frames 41 and 43 Stabilizer Attachment - 32,500 42000 12,500 1 5000Eddy Current Inspection

AMM 1 2-A-53-30-02-00A-353A-A

or

AMM 1 2-A-55-30-03-OOA-353A-A55-20/362 Elevator- Examine 32,500 42,000 12,500 15,000

AMM 1 2-A-55-20-00-OOA-31 OA-A27-30/363 Elevator- Control System - Examine 32,500 42,000 12,500 15,000

AMM 12-A-27-30-00-OOA-31 OA-A

Inspection kit P/N 500.50.1231927-30/364 Elevator Control Rods - Eddy Current 32,500 42,000 12,500 15,000

Inspection

AMM 1 2-A-27-00-01 -OOA-353A-A27-301365 Elevator Control Rads - Magnetic Partiele 32,500 42,000 12,500 15,000

Inspection

AMM 1 2-A-27-00-01 -OOA-352A-A27-30/366 ElevatorControl Lever- EddyCurrent 32,500 42,000 12,500 15,000

Inspection

AMM 1 2-A-27-30-05-OOA-353A-A55-20/367 Elevator Drive Lever- Eddy Current 32,500 42,000 12,500 15,000

Inspection

AMM 1 2-A-55-20-01-OOA-353A-A55-20/368 Elevator Hinges - Eddy Current 32,500 42,000 12,500 15,000

Inspection

AMM 1 2-A-55-20-01-OOA-353A-A55-30/369 Vertical Stabilizer- Examine 32,500 42,000 12,500 15,000 6

AMM 1 2-A-55-30-00-OOA-31 OA-A

Inspection kit P/N 500.50.12.32555-30/370 Vertical Stabilizer Main and Rear Spar 32,500 42,000 12,500 15,000

Attachment to Fuselage - Eddy CurrentInspection

AMM 1 2-A-53-30-02-OOA-353A-A

or

AMM 1 2-A-55-30-03-OOA-353A-A



‘Pl LATUSW 1 2-A-AM-00-00-00-IUNC LASS IFIED

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAMTask No Inspeetion/Reference Threshold Repeated Interval (whichever



55-30/371 Vertical StabilizerMainAffachmentto 32,500 42000 12,500 15,000Horizontal Stabilizer - Eddy CurrentInspection

AMM 1 2-A-55-00-O0-OOA-353A-A55-30/372 Vertical Stabilizer Pitch Trim Actuator 32,500 42,000 12,600 15,000

Fitting and Attachment - Eddy Currentlnspection

AMM 1 2-A-55-30-02-OOA-353A-A55-40/373 Rudder- Examine 32,500 42,000 12,500 15,000 6

AMM 1 2-A-55-40-00-OOA-31 OA-A27-20/374 Rudder Control System - Examine 32,500 42,000 12,500 15,000 6

AMM 1 2-A-27-20-00-OOA-31 OA-A

lnspection kit P/N 500.50.12.31827-20/375 Rudder Bellcranks - Eddy Current 32,500 42,000 12,500 15,000

lnspection

AMM 1 2-A-27-20-04-OOA-353A-A27-20/376 Rudder Cable Quadrant Shear Spigot - 32,500 42,000 12,500 15,000 6

Examine

AMM 1 2-A-27-20-05-OOA-31 OA-A55-40-377 Rudder Hinges - Eddy Current lnspection 32,500 42,000 12,500 15,000

AMM 1 2-A-55-40-05-OOA-353A-A56-11/378 Windshield LH and RH and Cockpit Side 32,500 42,000 12,500 15,000 6

Windows - Examine with windshield andside windows removed

AMM 1 2-A-56-1 1 -01 -OOA-31 OA-A

and

AMM 1 2-A-56-1 1 -02-OOA-31 OA-A

and

AMM 1 2-A-53-1 0-1 6-OOA-31 OA-A

lnspection kit P/N 50050.12.32657-00/379 Wng - Examine all structural elements 30,000 39,000 10,000 12,000 6

Rib 1 to Rib 20

AMM 1 2-A-57-00-00-OOA-31 OA-A



Pl LATUS 1 2-A-AM-00-00-00-IUNCLASSIFIED

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAMTask No InspectionlReference Threshold Repeated Interval (whichever



57-00/380 Wing Main and RearSparto Fuselage 30000 39000 10000 12000Attachment - Eddy Current Inspeotion

AMM 1 2-A-57-00-03-00A-353A-A

and

AMM 1 2-A-57-00-03-OIA-353A-A

lnspection kit P/N 500.60.12.004 wingaffachment

lnspection kit P/N 500.60.12.007 doublebush

57-00/382 Wing Rear Spar at Rib 8 FIap Arm 25,000 30,000 12,500 15,000Attachment - Eddy Current lnspection

AMM 1 2-A-57-20-1 0-00A-353C-A57-00/383 Wing Main Spar Fastener Holes Rib 1 25,000 30,000 3300 4,000

thru Rib 6 - Eddy Current lnspection

AMM 1 2-A-57-20-1 0-OOA-353A-A

lnspection kit P/N 500.60.12.030

or

lnspection kit P/N 500.60.12.02057-00/384 Wng Main Spar Fastener Holes Strap Rib 25,000 30,000 3,300 4,000

6- Eddy Current lnspection

AMM 1 2-A-57-20-05-OOA-353A-A


or

lnspection kit P/N 500.60.12.04357-00/385 Wing Rear Spar Fastener Holes Rib 2 25,000 30,000 12,500 15,000

thru Rib 3 - Eddy Current lnspection

AMM 1 2-A-57-20-1 0-OOA-353B-A27-50/386 Flap Mechanism - Examine 30,000 39,000 10,000 12,000 6

AMM 1 2-A-27-51 -00-OOA-31 OA-A






Effectivity: ALL 12-A-04-00-00-OOA-000A-A


Pl LATUS W 2-A-AM-00-00-00-IUNCLASSIFIED

SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAMTask No InspectionlReference Threshold Repeated Interval (whichever


FIying Landings FIying Landings YearsHours Hours

27-50/387 FIap Drive Arm (not removed) - Eddy 25000 30000 2,500 3000Current Inspection

AMM 1 2-A-27-51-00-OOA-353A-A27-50/386 FIap Dhve Arm (removed) - Eddy Current 30,000 39,000 10000 12,000

Inspection

AMM 1 2-A-27-51-01-OOA-353A-A

AMM 1 2-A-27-51 -02-aOA-353A-A

AMM 1 2-A-27-51 -03-OOA-353A-A27-50/389 FlapSupportArm-EddyCurrent 30,000 39,000 10000 12000

lnspection

AMM 1 2-A-27-51 -01 -OOA-353A-A

AMM 1 2-A-27-51 -02-OOA-353A-A

AMM 1 2-A-27-51-03-OOA-353A-A27-50/390 FIap Cove Rib Fittings - Eddy Current 30,000 39,000 10,000 12,000

Inspection

AMM 1 2-A-27-51-01 -OOA-353A-A

AMM 1 2-A-27-51-02-OOA-353A-A

AMM 1 2-A-27-51 -03-OOA-353A-A27-50-391 FIap Aft Links - Eddy Current Inspection 30,000 39,000 10,000 12,000

AMM 1 2-A-27-51-01-OOA-353A-A

AMM 1 2-A-27-51 -02-OOA-353A-A

AMM 1 2-A-27-51-03-OOA-353A-A27-50/392 FIap Bellcranks - Eddy Curvent Inspeution 30,000 39,000 10,000 12,000

AMM 1 2-A-27-51 -01-OOA-353A-A

AMM 1 2-A-27-51 -02-OOA-353A-A

AMM 1 2-A-27-51 -03-OOA-353A-A57-60/393 Aileron - Examine 32,500 42,000 12,500 15,000 6

AMM 1 2-A-57-60-00-OOA-31 OA-A



— _.. — n ——.. . —_. • • W 1 2-A-AM-00-00-00-I

UNCLASSIFIED

SUPPLEMNTAL STRUCTURAL INSPECTION PROGRAMTask No InspeetionlReference Threshold Repeated Interval (whichever



27-10/394 Aileron Control System - Examine 32500 42,000 12,500 15,000 6

AMM 1 2-A-27-10-00-00A-310A-A

Inspectian kit P/N 500.50.12.314


Inspectian kit P/N 500.50.12.316

lnspection kit P/N 500.60.12.015 (MSN684 - 999)

lnspection kit P/N 500.60.12.016 (MSN684 -999)

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

AMM 1 2-A-27-1 0-09-OOA-353A-A27-10/396 Aileron Control Rads - Eddy Current 32,500 42,000 12,500 15,000

Inspection

AMM 1 2-A-27-00-01-OOA-353A-A27-10/397 Aileron Control Rads - Magnetic Particle 32,500 42,000 12,500 15,000

lnspection

AMM 1 2-A-27-00-01-OOA-352A-A27-10/398 Aileron BeUcranks - Eddy Current and 32,500 42,000 12,500 15,000

Magnetic Partide lnspections

AMM 1 2-A-27-1 0-08-OOA-353A-A

AMM 1 2-A-27-1 0-08-OOA-353B-A

AMM 1 2-A-27-1 0-08-OOA-3526-A27-30/400 Aileron Hinge Points - Eddy Current 32,500 42,000 12,500 15,000

Inspeetion

AMM 1 2-A-57-60-06-OOA-353A-A71-00/401 Engine Mount - Magnetic Particle 26,600 35,000 6,600 8,000

lnspection

AMM 1 2-A-71-00-05-OOA-352A-A


The Airworthiness Limitations Section is EASA1 Actuator TBQ)

1 Approval Date:- 07 July 2015

Approved under Approval Number: 10053969 (Pitch Trim

I The Airworthiness Limitations Section is EASA Approved underApproval Number: 10054802 (MLG Boltsand CockpiUCabin Wndow lnspection)



PILATUSr 12-A-AM-ao-oo-oo-UNCLASSIFIED

Approval Date:- 18September2015

Effectivity: ALL 1 2-A-04-0O-0O-OOA-000A-A

End of data module


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