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## 12-A-04-00-00- 00A-000A-A STRUCTURAL 7 COMPONENT AND MISCELLANEOUS – AIRWORTHINESS LIMITATIONS Issue number and type: . . . . . . . . . . . . . .007 Data Module Changed - Changes are marked with revision markers. Issue Date: . . . . . . . . . . . . . . . . . . . . .2012-06-26 Language: . . . . . . . . . . . . . . . . . . . . .EN/UK Security Classification: . . . . . . . . . . . . . .UNCLASSIFIED Data Module Size:

. . . . . . . . . . . . . . . . . Responsible partner company: . . . . . . . . . .S4080 Originator: . . . . . . . . . . . . . . . . . . . . .S4080 Applicability: Model: . . . . . . . . . . . . . . . . . . . . .ALL Technical Standard: Authority Block:

. . . . . . . . . . . . . . . . Authority Exceptions: Tech Standard Notes:

. . . . . . . . . . . . . Quality Assurance Status:

. . . . . . . . . . . .This data module is an unverified draft. Reason For Update: . . . . . . . . . . . . . . . .PTS 12465 fire extinguisher life limit. PTS 11612 FCWU P/ N correction. PTS 12008 window damage limitations. 

## Table of contents Page References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 2 Structural Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 3 Component Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 4 Miscellaneous Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 5 Supplemental Structural Inspection Document . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 5.1 Limit of Validity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 5.2 Authorisation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 5.3 Deviation from Type Design . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 5.4 Supplemental Corrosion Prevention and Contro l Program (CPCP) . . . . . . . . . . . . . 8 5.5 Damage Tolerance Evaluation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 6 Component Life. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 7 Inspection Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 

## List of tables Page 1 References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2 Structural Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 3 Component Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 4 Miscellaneous Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 5 Component Life. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 6 Supplemental Structural Inspection Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

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## References

Table 1 References Data Module Title 12-A-05-20-30- 00A-280A-A SUPPLEMENTAL STRUCTURAL INSPECTION DOCUMENT – INSPECTIONS 12-A-20-40-00-00A-901A-A CORRO SION CONTROL – MAINTENANCE PRACTICES 12-A-27-00-01-00A-352A-A FLIGHT CONTROLS

j CONTROL RODS – MAGNETIC PARTICLE INSPECTION 12-A-27-00-01-00A-353A-A FLIGHT CONTROLS

jCONTROL RODS – EDDY CURRENT INSPECTION 12-A-27-10-00- 00A-310A-A AILERON CONT ROL SYSTEM – EXAMINE 12-A-27-10-0 8-00A-352B-A AILERON CONTROL SYSTEM

jFUSELAGE BELLCRANK – MAGNETIC PARTICLE INSPECTION 12-A-27-10-0 8-00A-353A-A AILERON CONTROL SYSTEM

j OUTER WING BELLCRANK – EDDY CURRENT INSPECTION 12-A-27-10-0 8-00A-353B-A AILERON CONTROL SYSTEM

jFUSELAGE BELLCRANK – EDDY CURRENT INSPECTION 12-A-27-10-0 9-00A-353A-A AILERON CONTROL SYSTEM

jFUSELAGE CABLE QUADRANT – EDDY CURRENT INSPECTION 12-A-27-20-00- 00A-310A-A RUDDER CONT ROL SYSTEM – EXAMINE 12-A-27-20-0 4-00A-353A-A RUDDER CONTROL SYSTEM

j BELLCRANK – EDDY CURRENT INSPECTION 12-A-27-20-0 5-00A-310A-A RUDDER CONTROL SYSTEM

j CABLE QUADRANT – EXAMINE 12-A-27-30-00- 00A-310A-A ELEVATOR CO NTROL SYSTEM – EXAMINE 12-A-27-30-0 5-00A-353A-A ELEVATOR CONTROL SYSTEM

j CONTROL LEVER – EDDY CURRENT INSPECTION 12-A-27-40-00-00A-903A-A HORIZONTAL STABILIZER TRIM – ADJUSTMENT"TEST 12-A-27-51-0 0-00A-310A-A FLAP DRIVE SYSTEM – EXAMINE 12-A-27-51-00- 00A-353A-A FLAP DRIVE SYSTEM – IN SITU EDDY CURRENT INSPECTION 12-A-27-51-01- 00A-353A-A FLAP DRIVE SYSTEM

j WING

j INBOARD MECHANISM – EDDY CURRENT INSPECTION 12-A-27-51-02- 00A-353A-A FLAP DRIVE SYSTEM

jWING

j CENTER MECHANISM – EDDY CURRENT INSPECTION 12-A-27-51-03- 00A-353A-A FLAP DRIVE SYSTEM

jWING

j OUTBOARD MECHANISM – EDDY CURRENT INSPECTION 12-A-32-20-06- 00A-313A-A DRAG LINK RIGHT PART – INSPECTION " CHECK 12-A-52-10 -00-00A-310A-A PASSENGER " CREW DOOR – EXAMINE 12-A-52-20-00-00A-310A-A EMERGENCY EXIT – EXAMINE 12-A-52-30-00- 00A-310A-A CARGO DOOR – EXAMINE 12-A-53-00-00-00A-310A-A FUSELAGE – ANTENNA STRUCTURE

jEXAMINE 12-A-53-00-00-00A-353A-A FUSELAGE – ANTENNA STRUCTURE

jEDDY CURRENT INSPECTION 12-A-53-10-0 0-00A-310A-A FORWARD FUSELAGE – EXAMINE 12-A-53-10-06-01A-353A-A FORWARD FUSELAGE

j FRAME 10 LONGERONS – EDDY CURRENT INSPECTION 12-A-53-10-16-00A-310A-A FORWARD FUSELAGE

j WINDOW STRUCTURE – EXAMINE Continued

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2012-06-26 Page 3Printed by Mekon Eclipse S1000D 12-A-53-20-00-00A-310A-A CENTER FUSELAGE – EXAMINE 12-A-53-20-02-00A-310A-A CENTER FUSELAGE FRAMES

j CARRY THROUGH FRAMES – EXAMINE 12-A-53-20-02-00A-353A-A CENTER FUSELAGE FRAMES

j CARRY THROUGH FRAMES – EDDY CURRENT INSPECTION 12-A-53-30-00-00A-310A-A REAR FUSELAGE – EXAMINE 12-A-53-30-02-00A-353A-A REAR FUSELAGE FRAMES – EDDY CURRENT INSPECTION 12-A-55-00-00-00A-353A-A VERTICAL STABILIZER ATTACHMENT FITTINGS – EDDY CURRENT INSPECTION 12-A-55-20-00-00A-310A -A ELEVATORS – EXAMINE 12-A-55-20-01-00A-353A-A ELEVATOR DRIVE LEVER AND HINGE – EDDY CURRENT INSPECTION 12-A-55-30-00-00A-310A-A VER TICAL STABILIZER – EXAMINE 12-A-55-30-02-00A-353A-A VERTICAL STABILIZER

j PITCH TRIM ACTUATOR ATTACHMENT – EDDY CURRENT INSPECTION 12-A-55-30-03-00A-353A -A VERTICAL STABILIZER SPARS – EDDY CURRENT INSPECTION 12-A-55-40-00-00A-310A-A RUDDER – EXAMINE 12-A-55-40-05-00A-353A-A RUDDER HINGE – EDDY CURRENT INSPECTION 12-A-56-00-00-00A-313A -A WINDOWS – INSPECTION " CHECK 12-A-56-11-01-00A-310A-A WINDSHIELD – EXAMINE 12-A-56-11-02-00A-310A-A COCKPIT SIDE WINDOWS – EXAMINE 12-A-57-00-00-00A-3 10A-A WINGS – EXAMINE 12-A-57-00-03-00A-353A-A WING AND FUSELAGE ATTACHMENT FITTINGS – EDDY CURRENT INSPECTION 12-A-57-00-03-01A-353A-A WING AN D FUSELAGE ATTACHMENT FITTINGS

j HOLLOW BOLTS – EDDY CURRENT INSPECTION 12-A-57-20-05-00A-353A-A WING STRUCTURE

jRIBS – EDDY CURRENT INSPECTION

j RIB 6 STRAP 12-A-57-20-10-00A-353A-A WING STRUCTURE

jSPARS AND AUXILIARY STRUCTURE

j MAIN SPAR – EDDY CURRENT INSPECTION 12-A-57-20-10-00A-353B-A WING STRUCTURE

jSPARS AND AUXILIARY STRUCTURE

j REAR SPAR – EDDY CURRENT INSPECTION 12-A-57-20-10-00A-353C-A WING STRUCTURE

jSPARS AND AUXILIARY STRUCTURE

j REAR SPAR – EDDY CURRENT INSPECTION 12-A-57-20-10-00A-353D-A WING STRUCTURE

jSPARS AND AUXILIARY STRUCTURE

j MAIN SPAR

j RIB 6 STRAP FASTENER – EDDY CURRENT INSPECTION 12-A-57-60-00-00A-310A -A AILERONS – EXAMINE 12-A-57-60-06-00A-353A -A AILERON HINGE – EDDY CURRENT INSPECTION 12-A-71-00-05-00A-352A-A POWERPLANT MOUNTING FRAME – MAGNETIC PARTICLE INSPECTION Table 1 References (Continued) Data Module Title

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## Description 1 General The Airworthiness Limitations se ction is EASA approved and variations mustalso be approved. The Airworthiness Limitations section is also FAA approved for US registered aircraft in accordance with FAR 21.29. The Airworthiness Limitations section is FAA a pproved and specifies maintenance required under Parts 43.16 and 91.403 of the Federal Aviation Regulations unless an alternate program has been FAA approved. Refer to the Pilot's Operating Handbook/Airplane Flight Manual for the approved seats and seat limitations. On PC-12/47 aircraft, do not install the following components: Nose Landing Gear 532.20.12.038 with serial numbers AM 001 thru 054 (Ref. Pilatus Service Bulletin 32-016). 532.20.12.039 with serial numbers AM 001 thru 054 (Ref. Pilatus Service Bulletin 32-016). 532.20.12.140 all (Ref. Pilatus Service Bulletin 32-014). Main Landing Gear 532.10.12.049 with serial numbers AM 001 thru 053 (Ref. Pilatus Service Bulletin 32-015/016/ 018). 532.10.12.050 with serial numbers AM 001 thru 053 (Ref. Pilatus Service Bulletin 32-015/016/ 018). 532.10.12.077 with serial numbers AM 001 thru 229 and all without primer and painted head (Ref. Pilatus Service Bulletin 32-012/018). 532.10.12.110 without marking "AT" or "VLG " (Ref. Pilatus Service Bulletin 32-015). Main Landing Gear Shock Absorber 532.10.12.175 with serial numbers AM 001 thru 107 (Ref. Pilatus Service Bulletin 32-016). Main Landing Gear Actuators 960.30.01.103 with serial numbers 830E thru 881E (Ref. Pilatus Service Bulletin 32-017). Flaps FCWU 99-3 with serial numbers lower than 100 00 and all Vickers Flap Actuators (Part No's 978.73.20.301, 978.73.20.302/303/304 and 306). 

## 2 Structural Limitations

Table 2 Structural Limitations Table 2 Structural Limitations Structure Life Fuselage and associated structure Pre SB 04-009 20,000 flying hours or 27,000 landings, whichever comes first Post SB 04-009 25,000 flying hours or 30,000 landings, whichever comes first Continued

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## 3 Component Limitations

Table 3 Component Limitations Wing structure Pre SB 04-009 20,000 flying hours or 27,000 landings, whichever comes first Post SB 04-009 25,000 flying hours or 30,000 landings, whichever comes first Tail structure Pre SB 04-009 20,000 flying hours or 27,000 landings, whichever comes first Post SB 04-009 25,000 flying hours or 30,000 landings, whichever comes first Beyond 25,000 flying hours or 30,000 landings (whichever comes first) refer to the Supplemental Structural Inspec tion Document (SSID) at Para 5 and 12-A-05-20-30-00A-280AA for supplemental structural inspections.

Table 3 Component Limitations Component Life Engine rotor components P z WC SB 14002 (latest revision) Engine mounting frame Pre SB 04-009 20,000 flying hours or 27,000 landings, whichever comes first Post SB 04-009 25,000 flying hours or 30,000 landings, whichever comes first Beyond 25,000 flying hours or 30,000 landings (whichever comes first) refer to the Supplemental Structural Inspec tion Document (SSID) at Para 5 and 12-A-05-20-30-00A-280AA for supplemental structural inspections. Engine mounting frame, replace all bolts, washers and nuts 11,000 flying hours 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) (black anodized) 20,000 flying hours or 27,000 landings, whichever comes first Oxygen bottle 15 years (elapsed) NLG drag link right part (Part No. 532.20.12.140) (Pre SB 32-014) 4,000 landings Cargo door lower lug fittings (Qty 3) 13 ,000 flying hours or 17,000 landings, whichever comes first Backrest tubes on crew seats with a recline system (Seat Part No's 959.30.01.111, 112, 121 and 122) 5,000 flying hours Table 2 Structural Limitations (Continued) Structure Life

Continued

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## 4 Miscellaneous Limitations

Table 4 Misc ellaneous Li mitations Backrest tubes on crew seats without a recline system (Seat Part No's 959.30.01.131, 132, 133 and 134) 10,000 flying hours

Pitch trim actuator atta chment parts, fail safe plates and their attachment parts (IPC 12-20- 00-07) 10,000 flying hours

Nose landing gear torque tube (P/N 532.50.12.047) 11,000 flying hours or 15,000 landings or 10 years installed, wh ichever comes first.

Table 4 Miscellaneous Limitations Component Limitation Procedure Cockpit outer side, DV windows and cabin windows If cracked or stress crazing can be felt Replace

Cockpit inner and outer side, DV windows and cabin windows If chipped, cracked (only for inner side windows), scratched, bubbles or delaminated Refer to AMM 12-A-56-00-00- 00A-313A-A for limitations

Windshield LH and RH If cracked in inner lamination Replace If cracked in outer lamination Only unpressurized flight is permitted up to the next scheduled inspection providing it does not cause visual problems Horizontal stabilizer trim Ev ery 3,000 flying hours or at Annual Inspection, whichever comes first Functional test of Trim Runaway Aural Warning System (FAA CMR) in accord ance with AMM 12-A-27-40-00-00A-903A-A NLG drag link right part (P/ N 532.20.12.289 or 532.20.12.140) Initially 2,000 flying hours or 2,500 landings (installed) whichever comes first, then every 300 flying hours or 400 landings, whichever comes first. Inspection/check (refer to AMM 12-A-32-20-06-00A-313A-A).

Fire extinguisher 10 years Life limit Oxygen bottle Refer to AVOX Service Information Letter SIL-35-114 latest revision (www.avoxsys.com). Hydrostatic test. Refer to AVOX Service Information Letter SIL-35-114 latest revision (www.avoxsys.com). Pitch trim actuator (Part No. 978.73.14.201) 1,500 flying hours Overhaul Table 3 Component Limitations (Continued) Component Life

Continued

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2012-06-26 Page 7Printed by Mekon Eclipse S1000D Note 1 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 pa rt of a fleet leader inspection survey and aircraft that have performed Service Bulletin 04-009 Revision 1 or later.
Note 2 Wings with more than 15500 flying hours or 22000 landings, whichever comes first, must perform the inspection within the next 500 flying hours or 500 landings, whichever comes first. 

## 5 Supplemental Structura l Inspection Document This section and AMM 12-A-05-20-30-00A-280A-A gi ve the additional structural and component life limits and the supplemental inspections neede d for aircraft that have 25,000 flying hours or 30,000 landings or more and forms the Supple mental Structural Insp ection Document (SSID) needed to increase the life of the airframe. Service Bulletin 04-009 must be accomplished to allow an aircraft to be operated up to 25,000 flying hours or 30,000 landings, whichever comes first. Only authorised Pilatus Service Centers can do the SSID, see Para 5.2. 

### 5.1 Limit of Validity The limit of validity (LOV) of the SSID is 50,000 flying hours or 60,000 landings, whichever comes first. The part of the SSID for the wing structur e (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 Service Centers can do the SSID as defined in Para 7 and in AMM 12-A05-20-30-00A-280A-A.

Pitch trim actuator (Part No. 978.73.14.202 and 978.73.14.203) 5,000 flying hours or 5 years (installed) whichever comes first. Overhaul

Wing Main Spar Fastener Holes Strap Rib 6 Threshold 16000 wing flying hours or 22500 wing landings, whichever comes first. All wings with no landing records must apply a calculated applicable landings equal to 2 x flying hours. See Notes 1 and 2 below. Eddy current inspection, AMM 12- A-57-20-10-00A-353D-A No cracks are permitted. If you find cracks contact Pilatus Aircraft for advice. Table 4 Miscellaneous Limitations (Continued) Component Limitation Procedure

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### 5.3 Deviation from Type Design Deviations from the Type Design in critical locati ons 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 find out if the aircraft will be eligible for this life ex tension.The ow ner/operator is responsible to organize these assessments we ll in advance of the first SSID inspection. There must be a clear statement for the specific aircraft MSN available wh ich states that the aircraft with (a), (b) and (c) is eligib le for this life extension. The assessments can be done as follows for: (a) Concessions - Only Pilatus can do this asse ssment. Pilatus shall be approached at least 5 months in advance. (b) Repairs, alterations and modifications - An y Authority approved Design Organization or equivalent can do this assessment. (c) For the aircraft modifications of the STC any Authority approved Design Organization or equivalent can do this assessment. For the part of the STC itself th e STC holder(s) only must do this assessment. On request, Pilatus can do the assessments for item s (b) and the first part of(c) in addition to (a) above, provided sufficient information is given. 

### 5.4 Supplemental Corrosion Preventi on and Control Program (CPCP) The maximum corrosion level to be maintained is Corrosion Level 1. Refer to AMM 12-A-20-40- 00-00A-901A-A for Corrosion Control Maintenance Practices. The supplemental CPCP inspection tasks are identified in the column where a calendar time interval is given. The following additional thres hold inspection requirement is applicable for all those CPCP inspection tasks: – the CPCP inspection task must be accomplis hed 6 years after Service Bulletin 04-009 has been accomplished – the CPCP inspection task must not be accomplis hed before the aircraft reaches 25,000 flying hours or 30,000 landings. 

### 5.5 Damage Tolerance Evaluation The entire aircraft structure is subject to Dam age Tolerance Evaluation when modified or repaired, except for life limited 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



## 7 Inspection Program Only Pilatus authorised Servic e Centers can do this SSID:

Table 6 Supplemental Structural Inspection Program Table 5 Component Life Task No. Component Life (whichever comes first) Flying Hours Landing s 27-50/414 Flaps - Life Limit (discard) 25,000 30,000 55-10/415 Horizontal Stabilizer - Life Limit (discard) 25,000 30,000 32-20/416 NLG Drag Link - Life Limit (discard) 25,000 30,000 32-30/417 MLG Actuator - Life Limit (discard) 25,000 30,000 29-10/418 Nitrogen accumulator - Li fe Limit (discard) 25,000 30,000

Table 6 Supplemental Structural Inspection Program SUPPLEMENTAL STRUCTURA L INSPECTION PROGRAM Task No Inspection/Reference Threshold (whichever comes first) Repeated Interval (whichever comes first) Flying Hours Landin gs Flying Hours Landin gs Years 32-10/345 Main landing gear - Overhaul CMM 02099 Inspection kit P/N 500.60.12.027 25,000 30,000 8,300 10,000 6

32-10/346 MLG Yoke fitting lugs - Eddy Current Inspection CMM 02099 25,000 30,000 8,300 10,000 -

32-10/347 MLG Tr ailing Link - Eddy Current Inspection CMM 02099 25,000 30,000 8,300 10,000 -

52-10/348 Passenger/crew door - Examine all structural elements AMM 12-A-52-10-00-00A-310A-A 32,500 42,000 12,500 15,000 6

52-20/349 Emergency door - Examine all structural elements AMM 12-A-52-20-00-00A-310A-A 32,500 42,000 12,500 15,000 6

Continued

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2012-06-26 Page 10Printed by Mekon Eclipse S1000D 52-30/350 Cargo door - Examine all structural elements AMM 12-A-52-30-00-00A-310A-A 32,500 42,000 12,500 15,000 6

53-00/351 Upper Longerons Frame 10 - Eddy Current Inspection AMM 12-A-53-10-06-01A-353A-A Inspection kit P/N 500.60.12.032 25,000 30,000 12,500 15,000 -

53-00/352 Fuselage Frames 10 to 16 - Examine all structural elements AMM 12-A-53-10-00-00A-310A-A Inspection kit P/N 500.60.12.033 32,500 42,000 12,500 15,000 6

53-00/353 Fuselage Frames 16 to 36 - Examine all structural elements AMM 12-A-53-20-00-00A-310A-A Inspection kit P/N 500.60.12.041 32,500 42,000 12,500 15,000 6

53-00/354 Fuselage Frames 36 to 43 - Examine all structural elements AMM 12-A-53-30-00-00A-310A-A 32,500 42,000 12,500 15,000 6

53-00/355 Antenna Structure - Examine AMM 12-A-53-00-00-00A-310A-A 32,500 42,000 12,500 15,000 6
53-00/356 Antenna - Bottom fuselage skin - Eddy Current Inspection AMM 12-A-53-00-00-00A-353A-A 28,300 37,000 8,300 10,000 -

53-00/357 Antenna - Upper fuselage skin - Eddy Current Inspection AMM 12-A-53-00-00-00A-353A-A 32,500 42,000 12,500 15,000 -

53-00/358 Upper Flange Carry Through Frames 21 and 24 - Examine AMM 12-A-53-20-02-00A-310A-A Inspection kit P/N 500.50.12.327 30,000 39,000 10,000 12,000 6 Table 6 Supplemental Structural Inspection Program (Continued) SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM Task No Inspection/Reference Threshold (whichever comes first) Repeated Interval (whichever comes first) Flying Hours Landin gs Flying Hours Landin gs Years

Continued

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2012-06-26 Page 11Printed by Mekon Eclipse S1000D 53-00/359 Frames 21 and 24 Wing Attachments - Eddy Current Inspection AMM 12-A-53-20-02-00A-353A-A 30,000 39,000 10,000 12,000 -

53-00/360 Frames 21 and 24 Side Frame Attachments - Eddy Current Inspection AMM 12-A-53-20-02-00A-353A-A 30,000 39,000 10,000 12,000 -

53-00/361 Frames 41 and 43 Stabilizer Attachment - Eddy Current Inspection AMM 12-A-53-30-02-00A-353A-A
or AMM 12-A-55-30-03-00A-353A-A 32,500 42,000 12,500 15,000 -

55-20/362 Elevator - Examine AMM 12-A-55-20-00-00A-310A-A 32,500 42,000 12,500 15,000 6
27-30/363 Elevator - Control System - Examine AMM 12-A-27-30-00-00A-310A-A Inspection kit P/N 500.50.12.319 32,500 42,000 12,500 15,000 6

27-30/364 Elevator Control Rods - Eddy Current Inspection AMM 12-A-27-00-01-00A-353A-A 32,500 42,000 12,500 15,000 -

27-30/365 Elevator Control Rods - Magnetic Particle Inspection AMM 12-A-27-00-01-00A-352A-A 32,500 42,000 12,500 15,000 -

27-30/366 Elevator Control Lever - Eddy Current Inspection AMM 12-A-27-30-05-00A-353A-A 32,500 42,000 12,500 15,000 -

55-20/367 Elevator Drive Lever - Eddy Current Inspection AMM 12-A-55-20-01-00A-353A-A 32,500 42,000 12,500 15,000 - Table 6 Supplemental Structural Inspection Program (Continued) SUPPLEMENTAL STRUCTURA L INSPECTION PROGRAM Task No Inspection/Reference Threshold (whichever comes first) Repeated Interval (whichever comes first) Flying Hours Landin gs Flying Hours Landin gs Years

Continued

### UNCLASSIFIED 12-A/AMP-04

Effectivity: All



### UNCLASSIFIED 12-A-04-00-00-00A-000A-A
2012-06-26 Page 12Printed by Mekon Eclipse S1000D 55-20/368 Elevator Hinges - Eddy Current Inspection AMM 12-A-55-20-01-00A-353A-A 32,500 42,000 12,500 15,000 -

55-30/369 Vertical St abilizer - Examine AMM 12-A-55-30-00-00A-310A-A Inspection kit P/N 500.50.12.325 32,500 42,000 12,500 15,000 6

55-30/370 Vertical Stab ilizer Main and Rear Spar Attachment to Fuselage - Eddy Current Inspection AMM 12-A-53-30-02-00A-353A-A
or AMM 12-A-55-30-03-00A-353A-A 32,500 42,000 12,500 15,000 -

55-30/371 Vertical Stabilizer Main Attachment to Horizontal Stabilizer - Eddy Current Inspection AMM 12-A-55-00-00-00A-353A-A 32,500 42,000 12,500 15,000 -

55-30/372 Vertical St abilizer Pitch Trim Actuator Fitting and Attachment - Eddy Current Inspection AMM 12-A-55-30-02-00A-353A-A 32,500 42,000 12,500 15,000 -

55-40/373 Rudder - Examine AMM 12-A-55-40-00-00A-310A-A 32,500 42,000 12,500 15,000 6
27-20/374 Rudder Control System - Examine AMM 12-A-27-20-00-00A-310A-A Inspection kit P/N 500.50.12.318 32,500 42,000 12,500 15,000 6

27-20/375 Rudder Bellcranks - Eddy Current Inspection AMM 12-A-27-20-04-00A-353A-A 32,500 42,000 12,500 15,000 -

27-20/376 Rudder Cable Quadrant Shear Spigot - Examine AMM 12-A-27-20-05-00A-310A-A 32,500 42,000 12,500 15,000 6 Table 6 Supplemental Structural Inspection Program (Continued) SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM Task No Inspection/Reference Threshold (whichever comes first) Repeated Interval (whichever comes first) Flying Hours Landin gs Flying Hours Landin gs Years

Continued

### UNCLASSIFIED 12-A/AMP-04

Effectivity: All



### UNCLASSIFIED 12-A-04-00-00-00A-000A-A
2012-06-26 Page 13Printed by Mekon Eclipse S1000D 55-40-377 Rudder Hinges - Eddy Current Inspection AMM 12-A-55-40-05-00A-353A-A 32,500 42,000 12,500 15,000 -

56-11/378 Windshield LH and RH and Cockpit Side Windows - Examine with windshield and side windows removed AMM 12-A-56-11-01-00A-310A-A and AMM 12-A-56-11-02-00A-310A-A and AMM 12-A-53-10-16-00A-310A-A Inspection kit P/N 500.50.12.326 32,500 42,000 12,500 15,000 6

57-00/379 Wing - Examine all structural elements Rib 1 to Rib 20 AMM 12-A-57-00-00-00A-310A-A 30,000 39,000 10,000 12,000 6

57-00/380 Wing Main and Rear Spar to Fuselage Attachment - Eddy Current Inspection AMM 12-A-57-00-03-00A-353A-A and AMM 12-A-57-00-03-01A-353A-A Inspection kit P/N 500.60.12.004 wing attachment Inspection kit P/N 500.60.12.007 double bush 30,000 39,000 10,000 12,000 -

57-00/382 Wing Rear Spar at Rib 8 Flap Arm Attachment - Eddy Current Inspection AMM 12-A-57-20-10-00A-353C-A 25,000 30,000 12,500 15,000 - Table 6 Supplemental Structural Inspection Program (Continued) SUPPLEMENTAL STRUCTURA L INSPECTION PROGRAM Task No Inspection/Reference Threshold (whichever comes first) Repeated Interval (whichever comes first) Flying Hours Landin gs Flying Hours Landin gs Years

Continued

### UNCLASSIFIED 12-A/AMP-04

Effectivity: All



### UNCLASSIFIED 12-A-04-00-00-00A-000A-A
2012-06-26 Page 14Printed by Mekon Eclipse S1000D 57-00/383 Wing Main Spar Fastener Holes Rib 1 thru Rib 6 - Eddy Current Inspection AMM 12-A-57-20-10-00A-353A-A Inspection kit P/N 500.60.12.030
or Inspection kit P/N 500.60.12.020 25,000 30,000 3,300 4,000 -

57-00/384 Wing Main Spar Fastener Holes Strap Rib 6 - Eddy Current Inspection AMM 12-A-57-20-05-00A-353A-A Inspection kit P/N 500.60.12.031 or Inspection kit P/N 500.60.12.043 25,000 30,000 3,300 4,000 -

57-00/385 Wing Rear Spar Fastener Holes Rib 2 thru Rib 3 - Eddy Current Inspection AMM 12-A-57-20-10-00A-353B-A 25,000 30,000 12,500 15,000 -

27-50/386 Flap Mechanism - Examine AMM 12-A-27-51-00-00A-310A-A Inspection kit P/N 500.60.12.021 Inspection kit P/N 500.60.12.022 Inspection kit P/N 500.60.12.023 Inspection kit P/N 500.60.12.024 Inspection kit P/N 500.60.12.025 30,000 39,000 10,000 12,000 6

27-50/387 Flap Drive Arm (not removed) - Eddy Current Inspection AMM 12-A-27-51-00-00A-353A-A 25,000 30,000 2,500 3,000 - Table 6 Supplemental Structural Inspection Program (Continued) SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM Task No Inspection/Reference Threshold (whichever comes first) Repeated Interval (whichever comes first) Flying Hours Landin gs Flying Hours Landin gs Years

Continued

### UNCLASSIFIED 12-A/AMP-04

Effectivity: All



### UNCLASSIFIED 12-A-04-00-00-00A-000A-A
2012-06-26 Page 15Printed by Mekon Eclipse S1000D 27-50/388 Flap Drive Arm (removed) - Eddy Current Inspection AMM 12-A-27-51-01-00A-353A-A AMM 12-A-27-51-02-00A-353A-A AMM 12-A-27-51-03-00A-353A-A 30,000 39,000 10,000 12,000 -

27-50/389 Flap Support Arm - Eddy Current Inspection AMM 12-A-27-51-01-00A-353A-A AMM 12-A-27-51-02-00A-353A-A AMM 12-A-27-51-03-00A-353A-A 30,000 39,000 10,000 12,000 -

27-50/390 Flap Cove Rib FIttings - Eddy Current Inspection AMM 12-A-27-51-01-00A-353A-A AMM 12-A-27-51-02-00A-353A-A AMM 12-A-27-51-03-00A-353A-A 30,000 39,000 10,000 12,000 -

27-50-391 Flap Aft Links - Eddy Current Inspection AMM 12-A-27-51-01-00A-353A-A AMM 12-A-27-51-02-00A-353A-A AMM 12-A-27-51-03-00A-353A-A 30,000 39,000 10,000 12,000 -

27-50/392 Flap Bellcranks - Eddy Current Inspection AMM 12-A-27-51-01-00A-353A-A AMM 12-A-27-51-02-00A-353A-A AMM 12-A-27-51-03-00A-353A-A 30,000 39,000 10,000 12,000 -

57-60/393 Aileron - Examine AMM 12-A-57-60-00-00A-310A-A 32,500 42,000 12,500 15,000 6 Table 6 Supplemental Structural Inspection Program (Continued) SUPPLEMENTAL STRUCTURA L INSPECTION PROGRAM Task No Inspection/Reference Threshold (whichever comes first) Repeated Interval (whichever comes first) Flying Hours Landin gs Flying Hours Landin gs Years

Continued

### UNCLASSIFIED 12-A/AMP-04

Effectivity: All



### UNCLASSIFIED 12-A-04-00-00-00A-000A-A
2012-06-26 Page 16Printed by Mekon Eclipse S1000D 27-10/394 Aileron Control System - Examine AMM 12-A-27-10-00-00A-310A-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 P/N 500.60.12.015 (MSN 684 - 999) Inspection kit P/N 500.60.12.016 (MSN 684 -999) 32,500 42,000 12,500 15,000 6

27-10/395 Aileron Cable Segment - Eddy Current Inspection AMM 12-A-27-10-09-00A-353A-A 32,500 42,000 12,500 15,000 -

27-10/396 Aileron Control Rods - Eddy Current Inspection AMM 12-A-27-00-01-00A-353A-A 32,500 42,000 12,500 15,000 -

27-10/397 Aileron Control Rods - Magnetic Particle Inspection AMM 12-A-27-00-01-00A-352A-A 32,500 42,000 12,500 15,000 -

27-10/398 Aileron Bellcranks - Eddy Current and Magnetic Particle Inspections AMM 12-A-27-10-08-00A-353A-A AMM 12-A-27-10-08-00A-353B-A AMM 12-A-27-10-08-00A-352B-A 32,500 42,000 12,500 15,000 -

27-30/400 Aileron Hinge Points - Eddy Current Inspection AMM 12-A-57-60-06-00A-353A-A 32,500 42,000 12,500 15,000 -

71-00/401 Engine Mount - Magnetic Particle Inspection AMM 12-A-71-00-05-00A-352A-A Inspection kit P/N 500.60.12.006 26,600 35,000 6,600 8,000 - Table 6 Supplemental Structural Inspection Program (Continued) SUPPLEMENTAL STRUCTURAL INSPECTION PROGRAM Task No Inspection/Reference Threshold (whichever comes first) Repeated Interval (whichever comes first) Flying Hours Landin gs Flying Hours Landin gs Years

### UNCLASSIFIED 12-A/AMP-04

Effectivity: All



### UNCLASSIFIED 12-A-04-00-00-00A-000A-A
2012-06-26 Page 17Printed by Mekon Eclipse S1000D The Airworthiness Limitation s Section is EASA Approved under Approval Number:
Approval Date:-

### UNCLASSIFIED 12-A/AMP-04

Effectivity: All



### UNCLASSIFIED 12-A-04-00-00-00A-000A-A
2012-06-26 Page 18Printed by Mekon Eclipse S1000D Intentionally Blank



### End of data module