EASA AD No.: 2010-0205

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0205

Date: 08 October 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 partic ipate 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 airc raft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in a ccordance 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) : A330 and A340-200/-300 aeroplanes

TCDS Number : EASA.A.004, EASA.A.015
Foreign AD : Not applicable
Supersedure : None



### ATA 32 Landing Gear – Main Landing Gear (MLG) Retraction Bracket – Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330 aeroplanes, models -201, -202, -203, -223, -243, -301, -302, -303, - 321, -322, -323, -341, -342 and -343, all manufacturer serial numbers. Airbus A340 aeroplanes, models -211, -212, -213, -311, -312 and -313, all manufacturer serial numbers. This AD is not applicable to aeroplanes on which Airbus modification 54500 has been embodied in production, or on which Airbus Service Bulletin (SB) A330-32-3212 or Airbus SB A340-32-4256, as applicable to the aeroplane model, has been embodied in service.
Reason: During fatigue testing of the MLG, three failures of the retraction bracket occurred before the calculated life limitation. Further analysis has confirmed that those failures were due to fatigue initiated by fretting between the bush and lug bore. The failure of the retraction bracket, if not detected, could lead to a MLG extension with no damping resulting in MLG structural damage. Airbus carried out an investigation, demonstrating that the life limit of retraction brackets must be reduced to 19 800 Landings (LDG), which is below the life limit stated in the following A330 and A340 Airbus ALS Part 4 revisions:EASA AD No.: 2010-0205

EASA Form 110 Page 2/3 - Airbus A330 ALS Part 4 revisi on 02 approved by EASA on 16 December 2009. - Airbus A340 ALS Part 4 revisi on 01 approved by EASA on 15 December 2009. In order to maintain the structural integrity of the aeroplane, this AD requires the replacement of these MLG retraction brackets before the accumulation of 19 800 total LDG.

Effective Date: 22 October 2010
Required action(s) and Compliance Time(s): Required as indicated, unless already accomplished: (1) Before the accumulation of 19 800 total LDG* on the MLG Retraction Brackets, or within 900 Aeroplane Flight Hours after the effective date of this AD, whichever occurs later, replace the affected MLG Retraction Bracket identified in Table 1 of this AD with a serviceable part.

Table 1 Nomenclature Part Numbers – P/N 201478303 201478304 201478305 201478306 201478307 201478308 201428380 201428381 201428382 201428383 201428384 201428385 201428378 201428379 201428351 Retraction

Bracket

201428352

* Total LDG is the accumulated landings since the MLG Retraction Bracket initial entry into service on any aeroplane.

(2) Thereafter, before the accumulation of 19 800 total LDG* on any MLG Retraction Bracket identified in Table 1 of this AD, replace it with a serviceable part.

Note: The initial entry into service for the transferable systems components/items is defined as the date at which the component/item accomplishes the first flight for whic h it will undertake its intended function.EASA AD No.: 2010-0205

EASA Form 110 Page 3/3 Ref. Publications: None

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 & Re search Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the te chnical content of the requirements in this AD, please contact: AIRBUS – Airworthiness Office – EAL; E-mail: airworthiness.A330-A340@airbus.com

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