EASA AD No : 2011-0032

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0032

Date: 01 March 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 participate in th e 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 opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Age ncy [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) exemptio n]. 

### Type Approval Holder’s Name :
AIRBUS Type/Model designation(s) : A330 and A340 aeroplanes

TCDS Number : EASA.A.004, EASA.A.015

Foreign AD : Not applicable

Supersedure : None



### ATA 32 Landing Gear – Nose Landing Gear (NLG) – NLG Main Fitting – Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330 aeroplanes, models -2 01, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342 and -343, all manufacturer serial numbers, except aeroplanes on which Airbus modification 200616 has been embodied in production. Airbus A340 aeroplanes, models -211, - 212, -213, -311, -312, and -313, all manufacturer serial numbers, except aeroplanes on which Airbus modification 200616 has been embodied in production.
Reason: Corrosion has been found on the main fitting of the NLG leg in the vicinity of the dowel pin bushes retaining t he lower steering flange on A330/A340 aeroplanes. The majority of parts have been reworked and returned to service.
This corrosion, if not avoided, could lead to the NLG main fitting rupture, possibly resulting in a NLG collapse, which would constitute an unsafe condition.
In order to maintain the structural inte grity of the NLG, this AD requires the accomplishment of a modification which consists in adding primer paint to the cadmium around the dowel bush holes on the main fitting, in order to provide further protection against cadmium degradation.

Effective Date: 15 March 2011EASA AD No : 2011-0032

EASA Form 110 Page 2/2 Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Before the NLG has accumulated 60 m onths since its first flight on an aeroplane or since its first flight after it s last overhaul, as applicable, or within 24 months after the effective date of this AD, whichever occurs later: Modify the NLG main fitting by adding primer paint to the cadmium around the dowel bush holes, in accordance with the instructions of Airbus Service Bulletin (SB) A330-32-3241 or Airbus SB A340-32-4282, as applicable to aeroplane type.

Ref. Publications: Airbus Service Bulle tin A330-32-3241 at original issue. Airbus Service Bulletin A340-32-4282 at original issue. The use of later approved revisions of these documents 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. This AD was posted on 26 January 2011 as PAD 11-006 for consultation until 23 February 2011. No comments were received during the consultation period. 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 tec hnical content of the requirements in this AD, please contact: AIRBUS – Airworthiness Office – EAL; E-mail: airworthiness.A330-A340@airbus.com

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