EASA AD No.: 20 14 - 0222

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 14 - 0222

Date: 06 Octo ber 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 accordan ce 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 ope rate 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]

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### Design Approval Holder’s Name : AIRBUS Type/Model designation(s) : A330 and A340 aeroplanes TCDS Number s : EASA.A.004 and EASA.A.015 F oreign AD: Not applicable Supersedure : None

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### 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 ma nufacturer serial numbers (MSN) , except those on which Airbus modif ication 58896 has been embodied in production or embodied in service through Airbus Service Bulletin (SB) A330 - 32 - 3237

. Airbus A340 - 211, A340 - 21 2, 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 ha ve 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 configuration s . For the reasons described above, this AD requires identification of the MLGEASA AD No.: 20 14 - 0222

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 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 A ction(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, d etermine 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 b ogie p ivot pin and the b ogie b eam 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 t o compl y 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 t his AD , as applicable, or, prior to installation , the MLG unit passes the inspection as required by paragraph (1) of this AD

. Ref. Public ations: 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 document s is acceptable forEASA AD No.: 20 14 - 0222

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. compliance with the requirements of this AD. M - D SB A33/34 - 32 - 285 dated 09 July 201 0 , 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 201 4

. 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 - 1 4 1 for consultation until 26 September 2014. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this A D 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

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