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 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) : 

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 revision 02 approved by EASA on 16 December 

2009. 

- Airbus A340 ALS Part 4 revision 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 which 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 & 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 .