EASA AD No.: 2010-0056 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0056 

Date: 29 March 2010 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States 

and of the European third countries that participate in the activities of EASA under Article 

66 of that Regulation.

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, 

the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person 

may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise 

specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 

216/2008, Article 14(4) exemption]. 

Type Approval Holder’s Name : 

AIRBUS 

Type/Model designation(s) : 

A340-500/-600 aeroplanes 

TCDS Number : EASA.A.015 

Foreign AD : Not applicable 

Supersedure : None 

ATA 57 Wings – Inner Ailerons - Inspection 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A340 aeroplanes, models -541, -542, -642 and -643, all 

manufacturer serial numbers. 

Reason: Following a Structural Repair Manual (SRM) repair strength re-evaluation, 

some Allowable Damage Limits (ADL) and Repairs of holes and 

delaminations in composite panels have been found to be no more 

compliant with certification requirements for A340-500/-600 inner aileron. 

Therefore, some Allowable Damage Limits and Repairs published in SRM 

Chapters 57-61-12 PB101 and 57-61-12 PB201 were de-validated starting 

from the SRM revision issued on January 2009. The terminology 

“De-validated SRM” used in this AD text refers to the SRM chapters 

mentioned above. 

In order to prevent complete inner aileron split due to possible failure or 

disbonding of the repairs on the inner aileron panels performed as per “devalidated SRM”, which may result in flutter coupling of the free aileron part, 

this AD requires a one time inspection of the inner aileron panels to 

identify the presence of “de-validated SRM” repairs and, if necessary, to 

apply the associated corrective actions.

Effective Date: 12 April 2010 
EASA AD No.: 2010-0056 

EASA Form 110 Page 2/2 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) In accordance with the instructions defined in Airbus Service Bulletin 

(SB) A340-57-5026, within 800 Flight Hours after the effective date of 

this AD, perform an inspection programme (tap test and visual 

inspection) or special detailed inspection (thermography inspection) of 

affected inner aileron panels at LH and RH wings in order to detect 

any previous accomplishment of “de-validated SRM” repair. 

(2) In case “de-validated SRM” repair is suspected, before next flight, 

contact Airbus to obtain the necessary approved instructions for 

corrective action and accomplish those instructions accordingly. 

 (3) A review of aeroplane maintenance records is acceptable in lieu of the 

inspection required by paragraphs (1) of this AD if the de-validated 

SRM Chapters 57-61-12 PB101 and 57-61-12 PB201 from SRM 

revisions dated before January 2009 can be conclusively identified 

from that review. 

 (4) After the effective date of this AD, do not install inner aileron panel on 

an aeroplane, unless in compliance with the requirements of this AD. 

Ref. Publications: Airbus Service Bulletin A340-57-5026 at original issue. 

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 

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

Alternative Methods of Compliance for this AD. 

2. The required actions and the risk allowance have granted the 

issuance of a Final AD with Request for Comments, postponing the 

public consultation process after publication. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, 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 – Airworthiness Office – EAL; 

E-mail: airworthiness.A330-A340@airbus.com .