EASA AD No : 2011-0212

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0212

Date: 31 October 2011

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 parti cipate 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 Airworthiness Directive app lies, except in accordance with the requirements of that Airworthiness Directive 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 aeroplanes

TCDS Number : EASA.A.004

Foreign AD : Not applicable

Supersedure : None



### ATA 32 Landing Gear – Main Landing Gear (MLG) Bogie Beam – Life Limit

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202 , A330-203, A330-223, A330-243, A330-301, A330-302, A330-303, A330-321, A3 30-322, A330-323, A330-341, A330- 342 and A330-343 aeroplanes, all manufacturer serial numbers.
Reason: During ground load test cycles on an A340-600 aeroplane, the MLG bogie beam has prematurely fractured. The results of the investigation identif ied that this premature fracture was due to high tensile standing stress, resulting from dry fit axle assembly method. Improvement has been introduc ed subsequently with a grease fit axle assembly method. Fatigue and damage tolerance analyses were performed, whose results demonstrated that the current life lim it of certain MLG bogie beams with dry fit axles installed on A330 aeropl anes only must be reduced compared to the life limit stated in the A330 Ai rworthiness Limitations Section (ALS) Part 1- Safe Life Airworthiness Limitation Items revision 05 approved by EASA on 29 July 2010. Failure to comply with the reduced life limit of the MLG bogie beam with dry fit axle might jeopardize the MLG structural integrity. For the reasons described above, this AD requires the replacement of the affected MLG bogie beams before reaching the new reduced life limit.EASA AD No : 2011-0212

EASA Form 110 Page 2/3 Effective Date: 14 November 2011

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: For the purpose of this AD, an affected MLG Bogie Beam is defined as a MLG Bogie Beam having a Part Number (P/N) listed in table 1 of this AD, and whose serial number is not identified as ‘S2A’, ‘S2B’ and ‘S2C’ in Messier-Dowty Service Letter A33-34 A20 revision 05. Table 1 – Affected MLG bogie beam P/N
Affected MLG bogie beam P/N

201485300 or 201485301, or 201272302, or 201272304, or 201272306, or 201272307
(1) Within the compliance time specified in paragraph (1.1) or (1.2) of this AD, whichever occurs later, replace the affected MLG bogie beam by a serviceable part. (1.1) Before the accumulation of the flight hours (FH) or landings (LDG), whichever occurs first, as defined in Table 2 of this AD, as applicable to aeroplane type, model and Weight Variant (WV), or (1.2) within 6 months after the effective date of this AD.

Table 2 - MLG bogie beam life limit

Affected aeroplanes Life Limit to be counted from the MLG bogie beam first installation on an aeroplane
A330-201/-202/- 203/-223/-243 WV02x, WV05x (except WV058), and WV06x series 50 000 LDG or 72 300 FH

A330-201/-202/- 203/-223/-243 WV058 50 000 LDG or 57 900 FH

A330-301/ -302/ - 303/-321/-322/-323/- 341/-342/-343 WV00x, WV01x, WV02x, WV05x series 46 000 LDG or 75000 FH

(2) After the effective date of this AD, a MLG bogie beam having a P/N identified in Table 1 of this AD can be installed on an aeroplane, provided its life has not exceeded t he life limit defined in Table 2 of this AD and it is replaced with a serviceable part before reaching the life limit defined in Table 2 of this AD.

Note 1: Table 2 of this AD provides the applicable life limits only when the P/N installation is valid for the given aeroplane model and weight variant. Note 2: The reduced MLG bogie beam life limits are expected to be incorporated in the subsequent revision of the A330 ALS Part 1.EASA AD No : 2011-0212

EASA Form 110 Page 3/3 Ref. Publications : Airbus A330 ALS Part 1 revision 05, approved on 29 July 2010; Messier-Dowty Service Letter A33-34 A20 revision 05 dated 31 July 2009.

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 Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

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

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