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 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 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 -201, -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 the 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 integrity 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 2011 
EASA 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 months since its first flight on an 

aeroplane or since its first flight after its 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 Bulletin 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 & 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.