EASA AD No : 2012 - 00 15

EASA Form 11 0 Page 1 / 4 

## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 1 2 - 00 15

Date: 23 January 201 2 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 E uropean 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 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) exemption]. 

### Type Approval Holder’s Name : AIRBUS Type/Model designation(s) : A330 and A340 - 200/ - 300 aeroplanes TCDS Number s : EASA.A.004, EASA.A.015 F orei gn AD : Not applicable Supersedure: This AD supersedes EASA AD 2011 - 0141 dated 2 5 July 2011.



### ATA 32 Landing Gear – Main Landing Gear Bogie Beam – Inspection /

Repair / Modification 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 modif ication 58896 has been embodied in production. 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. Reason: The operator of an A330 aerop lane (which has a common bogie beam with the A340) reported a fracture of the right - hand (RH) main landing gear ( MLG ) bogie beam , which occurred while turning during low speed taxi maneuvers. The bogie fractured aft of the pivot point and remained attached to the sliding tube by the brake torque reaction rods. After this RH bogie failure, the aeroplane continued for approximately 40 meters on the forks of the sliding member before coming to rest on the taxiway. The preliminary investigations revealed that t his event was due to corrosion pitting occurring on the bore of the bogie beam. Investigations are ongoing to determine why bogie beam internal paint has been degraded, leading to a loss of cadmium plating , thereby allowing development of corrosion pitting

. This condition, if not detected and corrected, could l ead to a runway excursion event or to detachment of the bogie from the aeroplane, or to MLG collapse, possibly resulting in damage to the aeroplane and injury to the occupants.EASA AD No : 2012 - 00 15

EASA Form 11 0 Page 2 / 4 To enable early detecti on and repair of corrosion of the internal surfaces, EASA issued EASA AD 2007 - 0314 to require a one - time inspection o f all MLG bogie beam s, except Enhanced MLG bogie beam s, and the reporting of the results to Airbus. EASA AD 2007 - 0314 was revised and later superseded by EASA AD 2008 - 0093, reducing the inspection threshold. The results of subsequent investigation s showed thin paint coats and paint degradation, confirmed as well on Enhanced MLG bogie beam s. To address this additional concern, EASA issued EASA AD 2011 - 0141, retain ing the requirements of EASA AD 2008 - 0093, which was superseded, to require a one time visual inspection o f all MLG bogie beam s , includ ing a visual examination of the internal diameter for corrosion or damage to protecti ve treatments o f the bogie beam and measurement of the paint thickness on the internal bore, accomplishment of the applicable corrective actions and a modification of the MLG bogie beam to improve the coat paint application method , and application of corrosion protection

. Prompted by in - service requests, t his AD retains the requirements of EASA AD 2011 - 0141, which is superseded, and introduces repetitive inspection s of the MLG bogie beam s, which allows exten sion of the compliance time for the MLG bogie beam modification f rom 15 years to 21 years. Modification of a MLG bogie beam constitutes terminating action for the repetitive inspections for that MLG bogie beam

. Effective Date: 06 February 2012 Required A ction(s) and Compliance Time(s): Required as indicated, unless ac complished previously : (1) Within the threshold indicated in Table 1 of this AD, depending on the MLG bogie beam condition and , thereafter , at interval s indicated in Table 2 of this AD, clean the internal bore and perform a detailed visual inspection of in ternal surfaces of the LH and RH MLG bogie beams for any damage to the protective treatments or any corrosion, in accordance with instructions of Airbus SB A330 - 32 - 3225 Revision 01 or SB A340 - 32 - 4268 Revision 01, as applicable to aeroplane type

.

Table 1

– Initial Inspection MLG bogie beam c ondition Compliance time MLG bogie beams which have not embodied Airbus modification 54500 in production nor Airbus SB A330 - 32 - 3212 or Airbus SB A340 - 32 - 4256 in service, and which ha d accumulated on 03 June 2008 [the effective date of EASA AD 2008 - 0093] less than or equal to 4.5 years since their first flight on an aeroplane or since their first flight after their last overhaul, as applicable At the first convenient maintenance opportunity which occurs after the 4.5 ye ars threshold, but no later than 6 years since the LH or RH MLG bogie beam first flight on an aeroplane or since first flight after its last overhaul, as applicable MLG bogie beams which have not embodied Airbus modification 54500 in production nor Airbus SB A330 - 32 - 3212 or Airbus SB A340 - 32 - 4256 in service, and which ha d accumulated on 03 June 2008 more than 4.5 years since their first flight on an aeroplane or since their first flight after their last overhaul, as applicable At the next convenient mainte nance opportunity, or within 18 months after 04 January 2008 [the effective date of EASA AD 2007 - 0314R1], whichever occurs first and without exceeding the next bogie beam overhaul.EASA AD No : 2012 - 00 15

EASA Form 11 0 Page 3 / 4 Table 2

– Repe a t Inspection N o later than 6 years , but no t earlier than 4 years since its first flight after the MLG bogie beam overhaul which occurs after the last inspection (1.1) If , during any of the inspection s as required by paragraph (1) of this AD, no damage and no corrosion is found, before next flight, apply the p rotective treatments of the bogie beam in accordance with the instructions of Airbus SB A330 - 32 - 3225 Revision 01 or SB A340 - 32 - 4268 Revision 01, as applicable to aeroplane type

. (1.2) If , during any of the inspection s as required by paragraph (1) of this A D, damage or corrosion is found, before next flight, record the findings and apply the applicable corrective actions and accomplish the repair in accordance with the instructions of Airbus SB A330 - 32 - 3225 Revision 01 or SB A340 - 32 - 4268 Revision 01, as app licable to aeroplane type

. (2) Accomplishment of the inspection and corrective actions , in accordance with the instructions of Messier - Dowty SB N° A33/34 - 32 - 271 or in accordance with the instructions of Messier - Dowty SB N° A33/34 - 32 - 272, as applicable, is an acceptable method to comply with the requirements of paragraph (1) of this AD. (3) MLG bogie beams that have been inspected and corrected, before the effective date of this AD, in accordance with the instructions of Airbus SB A330 - 32 - 3225 at original i ssue or Airbus SB A340 - 32 - 4268 at original issue, as applicable to the aeroplane type , are compliant with the requirements of paragraph (1) of this AD. The repetitive inspection s as required by paragraph (1) of this AD remain applicable. (4) Before a MLG b ogie beam accumulates 21 years since its first flight on an aeroplane, accomplish the following actions concurrently: (4.1) Visually inspect the internal bores of the MLG bogie beam in accordance with the instructions of Airbus SB A330 - 32 - 3237 or Airbus SB A340 - 32 - 4279, as applicable to aeroplane type and, in case damage or corrosion is found, apply the corrective actions and accomplish the repair in accordance with the instructions of Airbus SB A330 - 32 - 3237 or SB A340 - 32 - 4279, as applicable to aeroplane type, and (4.2) Modify and/or re - identify, as applicable, the MLG bogie beam in accordance with the instructions of Airbus SB A330 - 32 - 3237 or Airbus SB A340 - 32 - 4279, as applicable to aeroplane type. (4. 3 ) The inspection requirements of paragraph (4.1) of this AD and the modification requirements only of paragraph (4.2) do not apply to a MLG bogie beam whose serial number is listed in Appendix A of Messier - Dowty SB N° A33/34 - 32 - 283 or Messier - Dowty SB N° A33/34 - 32 - 284, as applicable. (5) Within 90 days after accomplishment of each inspection as required by paragraph (1) or paragraph (4) of this AD , as applicable, report the results, including no findings, to Airbus. (6) Accomplishment of inspections and corrective actions in accordance with the instructi ons of Messier - Dowty SB N° A33/34 - 32 - 278 is an acceptable alternative method to comply with the requirements of paragraph (4.1) of this AD

. (7) Modification of a MLG bogie beam in accordance with the instructions of Messier - Dowty SB N° A33/34 - 32 - 283 or Mes sier - Dowty SB N° A33/34 - 32 - 284, as applicable, is an acceptable alternative method to comply with the requirements of paragraph (4.2) of this AD for that MLG bogie beam.EASA AD No : 2012 - 00 15

EASA Form 11 0 Page 4 / 4 (8) Modification of a MLG bogie beam as required by paragraph (4) of this AD , or as sp ecified in paragraphs (6) and (7) of this AD, constitutes terminating action for the repetitive inspections require d by paragraph (1) of this AD for that MLG bogie beam

. (9) From the effective date of this AD, do not install any MLG bogie beam on an aeropl ane, unless it is in compliance with the requirements and thresholds of this AD. Ref. Public ations : Airbus SB A330 - 32 - 3225 original issue dated 21 November 2007, or Revision 01 dated 30 October 2008. Airbus SB A340 - 32 - 4268 original issue dated 21 Novembe r 2007, or Revision 01 dated 30 October 2008. Messier - Dowty SB N° A33/34 - 32 - 271 original issue dated 13 September 2007. Messier - Dowty SB N° A33/34 - 32 - 272 original issue original issue dated 16 November 2007, or Revision 1 dated 22 September 2008. Messier - D owty SB N° A33/34 - 32 - 278 original issue dated 17 February 2010. Messier - Dowty SB N° A33/34 - 32 - 283 original issue dated 11 May 2010. Messier - Dowty SB N° A33/34 - 32 - 284 original issue dated 11 May 2010. Airbus SB A330 - 32 - 3237 original issue dated 18 January 2 011. Airbus SB A340 - 32 - 4279 original issue dated 18 January 2011. 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 approv e Alternative Methods of Compliance for this AD. 2. This AD was posted on 2 2 Dec ember 2011 as PAD 11 - 1 35 for consultation until 19 January 2012

. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this A D should be refe rred to the Safety Information Section , Executive 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 SAS

– Airwor thiness Office

– E I AL, E - mail: airworthiness.A330 - A340@airbus.com

.