list of revisions
TRANSCRIPT
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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
Effectivity: ALL 1 2-A-04-00-00-OOA-000A-A
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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
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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 -
EDDY CURRENT INSPECTION
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 -
EDDY CURRENT INSPECTION
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
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‘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).
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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.
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3
Engine mounting frame
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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)
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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.
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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.
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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
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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
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SUPPLEMENTAL STRUCTURAL INSPEGTION PROGRAMTask No InspectionlReference Threshold Repeated Interval (whichever
(whichever comes comes ffrst)first)
Flying Landings Flying Landings YearsHours Hours
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
Effectivity: ALL 1 2-A-04-00-00-OOA-000A-A
UNCLASSIFIED 2015-09-28 Page 11
‘Pl LATUSW 1 2-A-AM-00-00-00-IUNC LASS IFIED
SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAMTask No Inspeetion/Reference Threshold Repeated Interval (whichever
(whichever comes comes first)first)
Flying Landings Flying Landings YearsHours Hours
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
Effectivity: ALL 1 2-A-04-00-00-OOA-000A-A
UNCLASSIFIED 2015-09-28 Page 12
Pl LATUS 1 2-A-AM-00-00-00-IUNCLASSIFIED
SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAMTask No InspectionlReference Threshold Repeated Interval (whichever
(whichever comes comes first)first)
Flying Landings Flying Landings YearsHours Hours
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
lnspection kit P/N 500.60.12.031
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
lnspection kit P/N 500.60.12.021
lnspection kit P/N 500.60.12.022
lnspection kit P/N 500.60.12.023
lnspection kit P/N 500.60.12.024
lnspection kit P/N 500.60.12.025
Effectivity: ALL 12-A-04-00-00-OOA-000A-A
UNCLASSIFIED 2015-09-28 Page 13
Pl LATUS W 2-A-AM-00-00-00-IUNCLASSIFIED
SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAMTask No InspectionlReference Threshold Repeated Interval (whichever
(whichever comes comes first)first)
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
Effectivity: ALL 1 2-A-04-00-00-OOA-000A-A
UNCLASSIFIED 2015-09-28 Page 14
— _.. — n ——.. . —_. • • W 1 2-A-AM-00-00-00-I
UNCLASSIFIED
SUPPLEMNTAL STRUCTURAL INSPECTION PROGRAMTask No InspeetionlReference Threshold Repeated Interval (whichever
(whichever comes comes first)first)
Flying Landings Flying Landings YearsHours Hours
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
lnspection kit P/N 500.50.12.315
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
lnspection kit P/N 500.60.12.006
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)
Effectivity: ALL 1 2-A-04-00-00-OOA-000A-A
UNCLASSIFIED 2015-09-28 Page 15