EASA AD No.: 2014-0222

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0222

Date: 06 October 2014

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 EU 748/2012, Part 21.A.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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A330 and A340 aeroplanes

TCDS Numbers: EASA.A.004 and EASA.A.015

Foreign AD: Not applicable

Supersedure: None.

ATA 32 Landing Gear – Main Landing Gear Bogie Beam Bore – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, 

A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, 

A330-341, A330-342 and A330-343 aeroplanes, all manufacturer serial 

numbers (MSN), except those on which Airbus modification 58896 has been 

embodied in production or embodied in service through Airbus Service Bulletin 

(SB) A330-32-3237.

Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313

aeroplanes, all MSN, except those on which Airbus modification 58896 has 

been embodied in production or embodied in service through Airbus SB 

A340-32-4279.

Reason: From in-service experience, it was found that the inner bore of some bogie 

beams had been insufficiently re-protected against corrosion after inspection 

and/or possible maintenance actions accomplished in this area (absence of 

corrosion inhibitor and damage to paint have been found in some specific 

areas).

This condition, if not detected and corrected, could lead to corrosion on the 

bore of the bogie beam, potentially resulting in Main Landing Gear (MLG) 

collapse, ultimately resulting in damage to the aeroplane and injury to the 

occupants.

To address this potential unsafe condition, Airbus issued Alert Operators 

Transmission (AOT) A32L004-14, providing inspection instructions for some 

aeroplane configurations.

For the reasons described above, this AD requires identification of the MLG
EASA AD No.: 2014-0222

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units that are possibly affected, inspection of the MLG Bogie Beam bore and, 

depending on findings, accomplishment of the applicable corrective actions.

This AD also prohibits the installation of MLG units that have been overhauled 

by using instructions from an earlier Components Maintenance Manual (CMM)

revision.

Effective date: 20 October 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 12 months after the effective date of this AD, for each Part Number 

(P/N) 201252 series and P/N 201490 series MLG unit, determine the CMM 

revision which was used to accomplish the latest overhaul and, for each

MLG having been overhauled by using a CMM as specified in Table 1 of 

this AD, as applicable, clean and inspect the area around the interface 

between the bogie pivot pin and the bogie beam bore of the MLG in 

accordance with the instructions of Airbus AOT A32L004-14.

Table 1

MLG P/N CMM which was used during latest overhaul

201252 series CMM 32-11-74 Rev.25 or an earlier revision

201490 series CMM 32-12-05 Rev.20 or an earlier revision

(2) If, during the inspection as required by paragraph (1) of this AD, the paint is 

found to be missing or damaged locally, before next flight, inspect the 

Cadmium plate / base metal in accordance with the instructions of Airbus 

AOT A32L004-14.

(3) If, during the inspection as required by paragraph (2) of this AD, any 

discrepancy is identified as specified in Airbus AOT A32L004-14, before 

next flight, accomplish the applicable corrective actions in accordance with 

the instructions of Airbus AOT A32L004-14.

(4) Within 90 days after accomplishment of the inspection as required by 

paragraph (1) of this AD, report the inspection results (including no 

findings) to Airbus.

(5) Inspection and, depending on findings, correction of a MLG Bogie in

accordance with the instructions of Messier-Dowty (M-D) SB 

A33/34-32-272 is an acceptable method to comply with the requirements of 

paragraphs (1), (2) and (3) of this AD for that MLG, unless M-D SB

A33/34-32-285 at Revision 4 or earlier, is (or was) accomplished after 

accomplishment of M-D SB A33/34-32-272 on that MLG.

Note: Inspections in accordance with the instructions of M-D SB A33/34-32-285 

at Revision 5 and later approved revisions, do not affect an inspection in 

accordance with the instructions of M-D SB A33/34-32-272.

(6) From the effective date of this AD, installation on an aeroplane of an 

overhauled MLG P/N 201252 series or an overhauled MLG P/N 201490 

series is allowed, provided it is determined that the latest MLG overhaul 

was not accomplished by using a CMM as identified in Table 1 of this AD, 

as applicable, or, prior to installation, the MLG unit passes the inspection 

as required by paragraph (1) of this AD.

Ref. Publications: Airbus AOT A32L004-14 dated 28 July 2014.

M-D SB A33/34-32-272 dated 16 November 2007, or Revision 1 dated

22 September 2008.

M-D SB A33/34-32-285 Revision 5 dated 14 August 2014.

The use of later approved revisions of these documents is acceptable for 
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compliance with the requirements of this AD.

M-D SB A33/34-32-285 dated 09 July 2010, or Revision 1 dated 04 October 

2011 or Revision 2 dated 04 October 2012 or Revision 3 dated 11 September 

2013, or Revision 4 dated 23 January 2014.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative 

Methods of Compliance for this AD.

2. This AD was posted on 12 September 2014 as PAD 14-141 for consultation 

until 26 September 2014. The Comment Response Document can be found 

at http://ad.easa.europa.eu/.

3. Enquiries regarding this AD should be referred to the Safety Information 

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 – EIAL;

E-mail: airworthiness.A330-A340@airbus.com.