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EASA AIRWORTHINESS DIRECTIVE 

 

AD No.: 2007-0242 

Date: 04 September 2007 

No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the 

requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry. 

Type Approval Holder’s Name: 

AIRBUS SAS 

Type/Model designations: 

A310 aircraft 

TCDS Number: France No 145 

Foreign AD: Not applicable 

Supersedure: None; Note: This AD supersedes the requirements of § 1.8, 1.9, 1.10, 1.13 and 1.18 of 

EASA AD 2007-0053, which has been revised. 

 

ATA 57 Wings - Outer Wings Structural Fatigue – Inspection/Modification 

 

Manufacturer: AIRBUS (formerly AIRBUS INDUSTRIE) 

Applicability: A310 aircraft, all certified models, all serial numbers. 

Note: For each of the actions required by this directive, the aircraft to which 

these actions apply are identified in each relevant "Action" paragraph of the 

Compliance-section of this Airworthiness Directive (AD). 

Reason: DGAC France Airworthiness Directive (AD) 1992-106-132(B) original issue up 

to revision 7 was issued to require a set of inspection- and modification tasks 

which addressed JAR/FAR 25-571 requirements related to damage-tolerance 

and fatigue evaluation of structure. 

Following the Extended Design Service Goal activities as part of the Structure 

Task Group for the Airbus A310 program, EASA issued AD 2007-0053 which 

replaced DGAC France AD F-1992-106-132R7. Since the issuance of that AD, 

the thresholds and the intervals of some Airbus Service Bulletins (SBs which 

address structure fatigue related areas on the wing parts), until now part of the 

requirements of AD 2007-0053, have been updated. 

For the reasons stated above, this new AD requires the accomplishment of the 

structural fatigue-related corrective actions in accordance with the latest 

revision of these SBs which have been reviewed in the context of the A310 

Extended Service Goal activities. Consequently, this new AD supersedes the 

requirements of paragraphs 1.8, 1.9, 1.10, 1.13, 1.18 of EASA AD 2007-0053, 

which has been revised accordingly. 

Effective Date: 18 September 2007 
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Compliance: Required as indicated, unless accomplished previously: 

Action No.1 Wings – Leading Edge Access Panels Landing – Lower Skin 

– Inspection for Cracks at Bolt Holes.

Applicable to A310-203 and A310-222 aircraft models, all serial numbers, 

except aircraft: 

- on which AIRBUS modification No. 05101 has been embodied in production, 

- or on which SB A310-57-2003 at any approved Revision has been embodied 

in service before the accumulation of 9 400 Flight Cycles (FC) or 18 800 

Flight hours (FH), whichever occurred first. 

Note 1: If SB A310-57-2003 at any approved Revision is embodied after the 

accumulation of 9 400 FC or 18 800 FH, whichever occurs first, the actions 

below are still required. 

(1) Not later than at the threshold defined in SB A310-57-2002 Revision 3, 

perform the required inspection and, within the tolerances and time period 

defined, apply the corrective measures in accordance with SB A310-57-

2002 Revision 3. 

 For aircraft previously inspected in accordance with SB A310-57-2002 

Revision 2, no further action is required by this paragraph (1). 

 Aircraft which have exceeded the values of the inspection threshold must 

be inspected within the delay (grace period) defined in paragraph 1.E.(2) 

of SB A310-57-2002 Revision 3, taking the effective date of this directive 

as a reference, and without exceeding the previous values quoted in the 

SB at Revision 2. 

(2) Thereafter, repeat the inspection at the intervals and according to the 

instructions defined in SB A310-57-2002 Revision 3. 

Note 2: For the first planned repeat inspection to occur after the effective date of 

this AD, a delay (grace period) can be applied, without exceeding the interval 

value quoted in SB A310-57-2002 Revision 2. 

Action No.2 Wings – Inspect Area around Overwing Refuelling Aperture 

at Ribs 13 – 14.

Applicable to A310-203, A310-204, A310-222, A310-304, A310-308, A310-

322, A310-324 and A310-325 aircraft models, all serial numbers. 

(3) Not later than at the threshold defined in SB A310-57-2006 Revision 4, 

perform the required inspection and, within the tolerances and time period 

defined, apply the corrective measures in accordance with SB A310-57-

2006 Revision 4. 

 For aircraft previously inspected in accordance with SB A310-57-2006 

Revision 3, no further action is required by this paragraph (3). 

 Aircraft which have exceeded the values of the inspection threshold must 

be inspected within the delay (grace period) defined in paragraph 1.E.(2) 

of SB A310-57-2006 Revision 4, taking the effective date of this directive 

as a reference, and without exceeding the previous values quoted in the 

SB at the Revision 2. 

(4) Thereafter, repeat the inspection at the intervals and according to the 

instructions defined in SB A310-57-2006 Revision 4. 

Note 3: For the first planned repeat inspection to occur after the effective date of 

this directive, a delay (grace period) can be applied, without exceeding the 

interval value quoted in SB A310-57-2006 Revision 3. 
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Action No.3 Wings – Upper Skin forward of Front Spar – Inspection for 

Cracks.

Applicable to A310-203 and A310-222 aircraft models, all serial numbers, 

except aircraft: 

- on which AIRBUS modification No. 05026 has been embodied in production; 

or 

- on which SB A310-57-2005 at any approved Revision has been embodied in 

service before the accumulation of 10 500 FC or 21 000FH, whichever occurs 

first. 

Note 4: If SB A310-57-2005 at any approved Revision is embodied after the 

accumulation of 10 500 FC or 21 000 FH, whichever occurs first, the actions 

below are still required. 

(5) Not later than at the threshold defined in SB A310-57-2032 Revision 4, 

perform the required inspection and, within the tolerances and time period 

defined, apply the corrective measures in accordance with SB A310-57-

2032 Revision 4. 

 For aircraft previously inspected in accordance with SB A310-57-2032 

Revision 3, no further action is required by this paragraph (5). 

 Aircraft which have exceeded the values of the inspection threshold must 

be inspected in the delay (grace period) defined in paragraph 1.E.(2) of 

SB A310-57-2032 Revision 4, taking the effective date of this directive as 

a reference, and without exceeding the previous values quoted in the SB 

at the Revision 3. 

(6) Thereafter, repeat the inspection at the intervals and according to the 

instructions defined in SB A310-57-2032 Revision 4. 

Note 5: For the first planned repeat inspection to occur after the effective date of 

this directive, a delay (grace period) can be applied, without exceeding the 

interval value quoted in SB A310-57-2032 Revision 3.

Action No.4 Wings – Stringer Flanges at Rib 14 Wing Bottom Skin –

Inspect for Cracks.

Applicable to A310-203 and A310-222 aircraft models, all serial numbers, 

except aircraft on which AIRBUS modification No. 04987 has been embodied 

in production. 

(7) Not later than at the threshold defined in SB A310-57-2038 Revision 4, 

perform the required inspection and, within the tolerances and time period 

defined, apply the corrective measures in accordance with SB A310-57-

2038 Revision 4. 

 For aircraft previously inspected in accordance with SB A310-57-2038 

Revision 3, no further action is required by this paragraph (7). 

 Aircraft which have exceeded the values of the inspection threshold must 

be inspected within the delay (grace period) defined in paragraph 1.E.(2) 

of SB A310-57-2038 Revision 4, taking the effective date of this directive 

as a reference, and without exceeding the previous values quoted in the 

SB at the Revision 3. 

(8) Thereafter, repeat the inspection at the intervals and according to the 

instructions defined in SB A310-57-2038 Revision 4. 

Note 6: For the first planned repeat inspection to occur after the effective date of 

this directive, a delay (grace period) can be applied, without exceeding the 

interval value quoted in SB A310-57-2038 Revision 3. 
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Action No 5 Wings – inspection of rear spar at selected bolt locations for 

attachment of Main landing gear forward pick-up fitting.

Applicable to A310-203, A310-204, A310-222, A310-304, A310-308, A310-

322, and A310-324 aircraft models, all serial numbers, except aircraft on which 

AIRBUS modification No 07601 has been embodied in production. 

(9) Not later than at the threshold defined in SB A310-57-2046 Revision 8, 

perform the required inspection and, within the tolerances and time period 

defined, apply the corrective measures in accordance with SB A310-57-

2046 Revision 8. 

 For aircraft previously inspected in accordance with SB A310-57-2046 

Revision 7, no further action is required by this paragraph (9). 

 Aircraft which have exceeded the values of the inspection threshold must 

be inspected within the delay (grace period) defined in paragraph 1.E.(2) 

of SB A310-57-2046 Revision 8, taking the effective date of this AD as a 

reference, and without exceeding the previous values quoted in the SB at 

the Revision 7. 

(10) Thereafter, repeat the inspection at the intervals and according to the 

instructions defined in SB A310-57-2046 Revision 8. 

Note 7: For the first planned repeat inspection to occur after the effective date of 

this AD, a delay (grace period) can be applied, without exceeding the interval 

value quoted in SB A310-57-2046 Revision 7.

Note 8: For A310-300 series aircraft post modification 07601, inspections are 

detailed in the Structure Significant Item (SSI) 57.21.16 of the Maintenance 

Review Board Document (MRBD). 

(11) Accomplishment of any corrective measures in accordance with any of the 

Airbus SBs detailed in the Ref. Publications section does not constitute 

terminating action for the inspection requirements of this directive. 

Ref. Publications: AIRBUS Service Bulletins : 

A310-57-2002 Revision 2 or Revision 3; 

A310-57-2003 Original issue up to Revision 3; 

A310-57-2005 Original issue up to Revision 3; 

A310-57-2006 Revision 3 or Revision 4; 

A310-57-2032 Revision 3 or Revision 4; 

A310-57-2038 Revision 3 or Revision 4; 

A310-57-2046 Revision 7 or Revision 8; or 

later approved revisions of these documents. 

Remarks : 1. If requested and appropriately substantiated, EASA can accept Alternative 

Methods of Compliance for this AD. 

2. This AD was posted on 06 August 2007 as PAD 07-131 for consultation until 

03 September 2007. No comments were received during the consultation 

period. 

3. Enquiries regarding this AD should be referred to the AD Focal Point - 

Certification Directorate, EASA. E-mail: ADs@easa.europa.eu . 

4. For any question concerning the technical content of the requirements in 

this AD, please contact AIRBUS SAS – EAW (Airworthiness Office, 

Ph. :+ 33 5 61 93 36 96, Fax :+ 33 5 61 93 44 51).