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12-B-04-00-00-00A-000A-A

STRUCTURAL AND COMPONENT LIMITATIONS – 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 corrected. PTS 12008 window damage limitations

Table of contents Page

References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

2 Structural Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

5.4 Supplemental Corrosion Prevention and Control Program (CPCP) . . . . . . . . . . . . . 8

5.5 Damage Tolerance Evaluation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

6 Component Life. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

7 Inspection Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

List of tables Page

1 References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

2 Structural Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

3 Component Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

4 Miscellaneous Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

5 Component Life. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

6 Supplemental Structural Inspection Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
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References

 Table 1 References

Data Module Title

12-B-05-20-30-00A-280A-A SUPPLEMENTAL STRUCTURAL INSPECTION 

DOCUMENT – INSPECTIONS

12-B-20-40-00-00A-901A-A CORROSION CONTROL – MAINTENANCE 

PRACTICES

12-B-21-30-00-00A-903A-A PRESSURIZATION CONTROL – ADJUSTMENT"TEST

12-B-27-00-01-00A-352A-A FLIGHT CONTROLS j CONTROL RODS – MAGNETIC 

PARTICLE INSPECTION

12-B-27-00-01-00A-353A-A FLIGHT CONTROLS j CONTROL RODS – EDDY 

CURRENT INSPECTION

12-B-27-10-00-00A-310A-A AILERON CONTROL SYSTEM – EXAMINE

12-B-27-10-08-00A-352B-A AILERON CONTROL SYSTEM j FUSELAGE 

BELLCRANK – MAGNETIC PARTICLE INSPECTION

12-B-27-10-08-00A-353A-A AILERON CONTROL SYSTEM j OUTER WING 

BELLCRANK – EDDY CURRENT INSPECTION

12-B-27-10-08-00A-353B-A AILERON CONTROL SYSTEM j FUSELAGE 

BELLCRANK – EDDY CURRENT INSPECTION

12-B-27-10-09-00A-353A-A AILERON CONTROL SYSTEM j FUSELAGE CABLE 

QUADRANT – EDDY CURRENT INSPECTION

12-B-27-20-00-00A-310A-A RUDDER CONTROL SYSTEM – EXAMINE

12-B-27-20-04-00A-353A-A RUDDER CONTROL SYSTEM j BELLCRANK – EDDY 

CURRENT INSPECTION

12-B-27-20-05-00A-310A-A RUDDER CONTROL SYSTEM j CABLE QUADRANT – 

EXAMINE

12-B-27-30-00-00A-310A-A ELEVATOR CONTROL SYSTEM – EXAMINE

12-B-27-30-05-00A-353A-A ELEVATOR CONTROL SYSTEM j CONTROL LEVER 

– EDDY CURRENT INSPECTION

12-B-27-40-00-00A-903A-A HORIZONTAL STABILIZER TRIM – 

ADJUSTMENT"TEST

12-B-27-51-00-00A-310A-A FLAP DRIVE SYSTEM – EXAMINE

12-B-27-51-00-00A-353A-A FLAP DRIVE SYSTEM – IN SITU EDDY CURRENT 

INSPECTION

12-B-27-51-01-00A-353A-A FLAP DRIVE SYSTEM j WING j INBOARD 

MECHANISM – EDDY CURRENT INSPECTION

12-B-27-51-02-00A-353A-A FLAP DRIVE SYSTEM j WING j CENTER 

MECHANISM – EDDY CURRENT INSPECTION

12-B-27-51-03-00A-353A-A FLAP DRIVE SYSTEM j WING j OUTBOARD 

MECHANISM – EDDY CURRENT INSPECTION

12-B-32-20-06-00A-313A-A DRAG LINK RIGHT PART – INSPECTION"CHECK

12-B-52-10-00-00A-310A-A PASSENGER"CREW DOOR – EXAMINE

12-B-52-20-00-00A-310A-A EMERGENCY EXIT – EXAMINE

12-B-52-30-00-00A-310A-A CARGO DOOR – EXAMINE

12-B-53-00-00-00A-310A-A FUSELAGE – ANTENNA STRUCTURE j EXAMINE

12-B-53-00-00-00A-353A-A FUSELAGE – ANTENNA STRUCTURE j EDDY 

CURRENT INSPECTION

12-B-53-10-00-00A-310A-A FORWARD FUSELAGE – EXAMINE

12-B-53-10-06-01A-353A-A FORWARD FUSELAGE j FRAME 10 LONGERONS – 

EDDY CURRENT INSPECTION

Continued
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12-B-53-10-16-00A-310A-A FORWARD FUSELAGE j WINDOW STRUCTURE – 

EXAMINE

12-B-53-20-00-00A-310A-A CENTER FUSELAGE – EXAMINE

12-B-53-20-02-00A-310A-A CENTER FUSELAGE FRAMES j CARRY THROUGH 

FRAMES – EXAMINE

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

FRAMES – EDDY CURRENT INSPECTION

12-B-53-30-00-00A-310A-A REAR FUSELAGE – EXAMINE

12-B-53-30-02-00A-353A-A REAR FUSELAGE FRAMES – EDDY CURRENT 

INSPECTION

12-B-55-00-00-00A-353A-A VERTICAL STABILIZER ATTACHMENT FITTINGS – 

EDDY CURRENT INSPECTION

12-B-55-20-00-00A-310A-A ELEVATORS – EXAMINE

12-B-55-20-01-00A-353A-A ELEVATOR DRIVE LEVER AND HINGE – EDDY 

CURRENT INSPECTION

12-B-55-30-00-00A-310A-A VERTICAL STABILIZER – EXAMINE

12-B-55-30-02-00A-353A-A VERTICAL STABILIZER j PITCH TRIM ACTUATOR 

ATTACHMENT – EDDY CURRENT INSPECTION

12-B-55-30-03-00A-353A-A VERTICAL STABILIZER SPARS – EDDY CURRENT 

INSPECTION

12-B-55-40-00-00A-310A-A RUDDER – EXAMINE

12-B-55-40-05-00A-353A-A RUDDER HINGE – EDDY CURRENT INSPECTION

12-B-56-00-00-00A-313A-A WINDOWS – INSPECTION"CHECK

12-B-56-11-01-00A-310A-A WINDSHIELD – EXAMINE

12-B-56-11-02-00A-310A-A COCKPIT SIDE WINDOWS – EXAMINE

12-B-57-00-00-00A-310A-A WINGS – EXAMINE

12-B-57-00-03-00A-353A-A WING AND FUSELAGE ATTACHMENT FITTINGS – 

EDDY CURRENT INSPECTION

12-B-57-00-03-01A-353A-A WING AND FUSELAGE ATTACHMENT FITTINGS j

HOLLOW BOLTS – EDDY CURRENT INSPECTION

12-B-57-20-05-00A-353A-A WING STRUCTURE j RIBS – EDDY CURRENT 

INSPECTION j RIB 6 STRAP

12-B-57-20-10-00A-353A-A WING STRUCTURE j SPARS AND AUXILIARY 

STRUCTURE j MAIN SPAR – EDDY CURRENT 

INSPECTION

12-B-57-20-10-00A-353B-A WING STRUCTURE j SPARS AND AUXILIARY 

STRUCTURE j REAR SPAR – EDDY CURRENT 

INSPECTION

12-B-57-20-10-00A-353C-A WING STRUCTURE j SPARS AND AUXILIARY 

STRUCTURE j REAR SPAR – EDDY CURRENT 

INSPECTION

12-B-57-20-10-00A-353D-A WING STRUCTURE j SPARS AND AUXILIARY 

STRUCTURE j MAIN SPAR j RIB 6 STRAP 

FASTENER – EDDY CURRENT INSPECTION

12-B-57-60-00-00A-310A-A AILERONS – EXAMINE

12-B-57-60-06-00A-353A-A AILERON HINGE – EDDY CURRENT INSPECTION

12-B-71-00-00-00A-903D-A POWER PLANT TEST 3 j DC GENERATION SYSTEM 

– ADJUSTMENT"TEST

12-B-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 section is EASA approved and variations must also 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 approved 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 the PC-12/47E 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 10000 and all Vickers Flap Actuators (Part No's

978.73.20.301, 978.73.20.302/303/304 and 306).

Propeller Blade

Propeller blade E10477K.
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2 Structural Limitations Table 2 Struct ural Limitations

3 Component Limitations Table 3 Component 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

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 Para 5 and AMM 

12-B-05-20-30-00A-280A-A for the supplemental structural inspections.

 Table 3 Component Limitations

Component Life

Engine rotor components PzWC 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 Para 5 and AMM 

12-B-05-20-30-00A-280A-A for the 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)

Cargo door lower lug fittings (Qty 3) 13,000 flying hours or 17,000 landings, 

whichever comes first

Pitch trim actuator attachment parts, fail safe 

plates and their attachment parts (IPC 12-20-

00-07) 

10,000 flying hours

Continued
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4 Miscellaneous Limitations Table 4 Miscellaneous Limitations

Nose landing gear torque tube (P/N 

532.50.12.047)

11,000 flying hours or 15,000 landings or 10 

years installed, whichever 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-B-56-00-00-00A313A-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

Generator Control Unit 

(GCU) 1 and GCU 2

Every 3,000 flying hours or at 

Annual Inspection, 

whichever comes first

Functional test of the GCU 1 and 

GCU 2 over and under-voltage trip 

protection (Refer to AMM 12-B-71-

00-00-00A-903D-A)

ECS emergency shut-off 

system

Every 3,000 flying hours or at 

Annual Inspection, 

whichever comes first

Attach a spring balance to the ECS 

EMER SHUT-OFF lever. Pull the 

lever and check that the max pull 

force to open the ram air scoop is 

22.5 lbf (100 N) and make sure that 

the ram air scoop is completely 

open.

Pressurization Dump 

switch

Every 3,000 flying hours or 

at Annual Inspection, 

whichever comes first

Operational test (refer to AMM 12-

B-21-30-00-00A-903A-A)

Horizontal stabilizer trim Every 3,000 flying hours or at 

Annual Inspection, 

whichever comes first

Functional test of Trim Runaway 

Aural Warning System (FAA CMR) 

in accordance with AMM 12-B-27-

40-00-00A-903A-A

NLG drag link right part (P/

N 532.20.12.289)

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-

B-32-20-06-00A-313A-A).

Fire extinguisher 10 years Life limit

 Table 3 Component Limitations (Continued)

Component Life

Continued
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5 Supplemental Structural Inspection Document

This section and AMM 12-B-05-20-30-00A-280A-A give the 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 Supplemental Structural Inspection 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 structure (without systems and control system structure

such as flaps and ailerons) has a lower LOV of 35,000 flying hours or 43,000 landings, whichever

comes first.

5.2 Authorisation

Only Pilatus authorised Service Centers can do the SSID as defined in Para 7 and in AMM 12-B05-20-30-00A-280A-A.

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

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. 978.73.14.202 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.

Eddy current inspection, AMM 12-

B-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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must be assessed to find out if the aircraft will be eligible for this life extension.The owner/operator

is responsible to organize these assessments well in advance of the first SSID inspection. There

must be a clear statement for the specific aircraft MSN available which states that the aircraft with

(a), (b) and (c) is eligible for this life extension.

The assessments can be done as follows for:

(a) Concessions - Only Pilatus can do this assessment. Pilatus shall be approached at least

5 months in advance. 

(b) Repairs, alterations and modifications - 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 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, provided sufficient 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 12-B-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 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 25,000 flying

hours or 30,000 landings.

5.5 Damage Tolerance Evaluation

The entire aircraft structure is subject to Damage Tolerance Evaluation when modified or repaired,

except for life limited components as listed in Table 3 and Table 5, which remain as safe-life.

6 Component Life Table 5 Component Life

 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 - Life Limit (discard) 25,000 30,000
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7 Inspection Program

Only Pilatus authorised Service Centers can do this SSID:

 Table 6 Supplemental Structural Inspection Program

 Table 6 Supplemental Structural Inspection Program

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

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 Trailing 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-B-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-B-52-20-00-00A-310A-A

32,500 42,000 12,500 15,000 6

52-30/350 Cargo door - Examine all 

structural elements

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

Inspection kit P/N 500.60.12.034

32,500 42,000 12,500 15,000 6

Continued
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53-00/353 Fuselage Frames 16 to 36 - 

Examine all structural elements

AMM 12-B-53-20-00-00A-310A-A

Inspection kit P/N 500.60.12.042

32,500 42,000 12,500 15,000 6

53-00/354 Fuselage Frames 36 to 43 - 

Examine all structural elements

AMM 12-B-53-30-00-00A-310A-A

32,500 42,000 12,500 15,000 6

53-00/355 Antenna Structure - Examine

AMM 12-B-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-B-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-B-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-B-53-20-02-00A-310A-A

Inspection kit P/N 500.50.12.327

30,000 39,000 10,000 12,000 6

53-00/359 Frames 21 and 24 Wing 

Attachments - Eddy Current 

Inspection

AMM 12-B-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-B-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-B-53-30-02-00A-353A-A

or

AMM 12-B-55-30-03-00A-353A-A

32,500 42,000 12,500 15,000 -

 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-B/AMP-04

Effectivity: All

UNCLASSIFIED

12-B-04-00-00-00A-000A-A

2012-06-26 Page 11

Printed by Mekon Eclipse S1000D

55-20/362 Elevator - Examine

AMM 12-B-55-20-00-00A-310A-A

32,500 42,000 12,500 15,000 6

27-30/363 Elevator - Control System - 

Examine

AMM 12-B-27-30-00-00A-310A-A

Inspection kit P/N 500.60.12.019

32,500 42,000 12,500 15,000 6

27-30/364 Elevator Control Rods - Eddy 

Current Inspection

AMM 12-B-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-B-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-B-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-B-55-20-01-00A-353A-A

32,500 42,000 12,500 15,000 -

55-20/368 Elevator Hinges - Eddy Current 

Inspection

AMM 12-B-55-20-01-00A-353A-A

32,500 42,000 12,500 15,000 -

55-30/369 Vertical Stabilizer - Examine

AMM 12-B-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 Stabilizer Main and Rear 

Spar Attachment to Fuselage - 

Eddy Current Inspection

AMM 12-B-53-30-02-00A-353A-A

or

AMM 12-B-55-30-03-00A-353A-A

32,500 42,000 12,500 15,000 -

 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-B/AMP-04

Effectivity: All

UNCLASSIFIED

12-B-04-00-00-00A-000A-A

2012-06-26 Page 12

Printed by Mekon Eclipse S1000D

55-30/371 Vertical Stabilizer Main 

Attachment to Horizontal 

Stabilizer - Eddy Current 

Inspection

AMM 12-B-55-00-00-00A-353A-A

32,500 42,000 12,500 15,000 -

55-30/372 Vertical Stabilizer Pitch Trim 

Actuator Fitting and Attachment - 

Eddy Current Inspection

AMM 12-B-55-30-02-00A-353A-A

32,500 42,000 12,500 15,000 -

55-40/373 Rudder - Examine

AMM 12-B-55-40-00-00A-310A-A

32,500 42,000 12,500 15,000 6

27-20/374 Rudder Control System - Examine

AMM 12-B-27-20-00-00A-310A-A

Inspection kit P/N 500.60.12.018

32,500 42,000 12,500 15,000 6

27-20/375 Rudder Bellcranks - Eddy Current 

Inspection

AMM 12-B-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-B-27-20-05-00A-310A-A

32,500 42,000 12,500 15,000 6

55-40-377 Rudder Hinges - Eddy Current 

Inspection

AMM 12-B-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-B-56-11-01-00A-310A-A

and

AMM 12-B-56-11-02-00A-310A-A

and

AMM 12-B-53-10-16-00A-310A-A

Inspection kit P/N 500.50.12.326

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-B/AMP-04

Effectivity: All

UNCLASSIFIED

12-B-04-00-00-00A-000A-A

2012-06-26 Page 13

Printed by Mekon Eclipse S1000D

57-00/379 Wing - Examine all structural 

elements Rib 1 to Rib 20

AMM 12-B-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-B-57-00-03-00A-353A-A

and

AMM 12-B-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-B-57-20-10-00A-353C-A

25,000 30,000 12,500 15,000 -

57-00/383 Wing Main Spar Fastener Holes 

Rib 1 thru Rib 6 - Eddy Current 

Inspection

AMM 12-B-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-B-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 -

 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-B/AMP-04

Effectivity: All

UNCLASSIFIED

12-B-04-00-00-00A-000A-A

2012-06-26 Page 14

Printed by Mekon Eclipse S1000D

57-00/385 Wing Rear Spar Fastener Holes 

Rib 2 thru Rib 3 - Eddy Current 

Inspection

AMM 12-B-57-20-10-00A-353B-A

25,000 30,000 12,500 15,000 -

27-50/386 Flap Mechanism - Examine

AMM 12-B-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-B-27-51-00-00A-353A-A

25,000 30,000 2,500 3,000 -

27-50/388 Flap Drive Arm (removed) - Eddy 

Current 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

30,000 39,000 10,000 12,000 -

27-50/389 Flap Support Arm - Eddy Current 

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

30,000 39,000 10,000 12,000 -

27-50/390 Flap Cove Rib FIttings - Eddy 

Current 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

30,000 39,000 10,000 12,000 -

 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-B/AMP-04

Effectivity: All

UNCLASSIFIED

12-B-04-00-00-00A-000A-A

2012-06-26 Page 15

Printed by Mekon Eclipse S1000D

27-50-391 Flap Aft Links - Eddy Current 

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

30,000 39,000 10,000 12,000 -

27-50/392 Flap Bellcranks - Eddy Current 

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

30,000 39,000 10,000 12,000 -

57-60/393 Aileron - Examine

AMM 12-B-57-60-00-00A-310A-A

32,500 42,000 12,500 15,000 6

27-10/394 Aileron Control System - Examine

AMM 12-B-27-10-00-00A-310A-A

Inspection kit P/N 500.50.12.314

Inspection kit P/N 500.60.12.035

Inspection kit P/N 500.60.12.016 

32,500 42,000 12,500 15,000 6

27-10/395 Aileron Cable Segment - Eddy 

Current Inspection

AMM 12-B-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-B-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-B-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-B-27-10-08-00A-353A-A

AMM 12-B-27-10-08-00A-353B-A

AMM 12-B-27-10-08-00A-352B-A

32,500 42,000 12,500 15,000 -

 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-B/AMP-04

Effectivity: All

UNCLASSIFIED

12-B-04-00-00-00A-000A-A

2012-06-26 Page 16

Printed by Mekon Eclipse S1000D

The Airworthiness Limitations Section is EASA Approved under Approval Number:

Approval Date:- 

27-30/400 Aileron Hinge Points - Eddy 

Current Inspection

AMM 12-B-57-60-06-00A-353A-A

32,500 42,000 12,500 15,000 -

71-00/401 Engine Mount - Magnetic Particle 

Inspection

AMM 12-B-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

End of data module