EASA AD No : 2012-0053

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0053

Date: 30 March 2012

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption].


### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :
A330 and A340 aeroplanes

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

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2011-0040 d ated 08 March 2011.



### ATA 32 Landing Gear – Main and Center Landing Gear Bogie P ivot Pins – Inspections

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330 aeroplanes, models 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). Airbus A340 aeroplanes, models A340-211, A340-212, A340-213, A340-311, A340-312, A340-313, A340-541, A340-542, A340-642 an d A340-643 aeroplanes, all MSN.

Reason: During removals of A330/340 Main Landing Ge ar (MLG) Bogie Beams and A340-500/600 Center Landing Gear (CLG) Bogie Beams, cracks in the bogie pivot pin were found. Investigations indicated that these findings were t he result of material heating, caused by friction between bogie pivot pin and bush , leading to chrome detachment and stress corrosion cracking. This condition, if not detected and corrected, coul d lead to collapse of the main or center landing gear, possibly resulting in damag e to the aeroplane and/or injury to occupants. As a precautionary measure, EASA issued AD 2011-004 0 to require a one-time inspection of the MLG (all types of A330 and A340 a eroplanes) and CLG (A340-500/600 aeroplanes only) to detect degradatio n or cracking of the bogie pivot pin, as applicable to aeroplane model, and th e reporting of inspections results. Following issuance of EASA AD 2011-0040, several op erators reported findingEASA AD No : 2012-0053

EASA Form 110 Page 2/3 chrome detachment or chrome dragging on bogie pivot pin. New cases of cracks were also reported. It has been confirmed as well that, due to similar design, the enhanced MLG bogie pivot pin (Airbus mo dification 54500) could also be affected by this condition. Prompted by these findings, Airbus have developed a n inspection programme consisting of repetitive inspections of the bogie p ivot pin and applicable corrective actions. For the reasons described above, this AD, which sup ersedes EASA AD 2011- 0040 and extends the applicability to all A330 and A340 aeroplanes, requires accomplishment of repetitive inspections of the MLG and CLG (for A340-500 and A340-600 aeroplanes) bogie pivot pins and pivot pin bushes, and corrective actions, depending on findings.

Effective Date: 13 April 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless already accomplished: (1) Initially within the threshold indicated in Tab le 1 of this AD and, thereafter, at intervals not to exceed 26 months, accomplish a detailed visual inspection of the bogie pivot pins on the MLG and C LG (for A340 aeroplanes only) and pivot pin bushes in accordance with the instructions of Airbus Service Bulletin (SB) A330-32-3240 Revisi on 02 or Airbus SB A340-32-4281 Revision 01 or Airbus SB A340-32-5096 Revision 01, as applicable to aeroplane model.

Table 1 – Initial Inspection
Bogie pivot pin condition Compliance time
Bogie pivot pin fitted on MLG installed on A330, A340-200 and A340-300 not having embodied: - Airbus modification 54500 in production or, - Airbus SB A330-32-3212 in service or, - Airbus SB A340-32-4256 in service. Within 26 months after 22 March 2011 [the effective date of EASA AD 2011-0040] or since the aeroplane first flight, whichever occurs later, but not before the accumulation of 12 months after the aeroplane first flight. Bogie pivot pin fitted on MLG and CLG installed on A340-500 and A340-600.

Bogie pivot pin fitted on MLG having embodied: - Airbus modification 54500 in production or, - Airbus SB A330-32-3212 in service or, Airbus SB A340-32-4256 in service. Within 26 months after the effective date of this AD or since the aeroplane first flight, whichever occurs later, but not before the accumulation of 12 months after the aeroplane first flight.
Note: Accomplishment of an overhaul of the landing gear does not substitute the accomplishment of an inspection as required by paragraph (1) of this AD. (2) If, during any inspection as required by paragr aph (1) of this AD, any bush is found cracked or damaged, before next flight, ac complish the applicable corrective actions in accordance with the instructi ons of Airbus SB A330- 32-3240 Revision 02 or Airbus SB A340-32-4281 Revis ion 01 or Airbus SB A340-32-5096 Revision 01, as applicable to aeroplan e model. (3) If, during any inspection as required by paragr aph (1) of this AD, degraded chrome plating on a bogie pivot pin is found, befor e next flight, perform a Non-Destructive Test (NDT) inspection of the affect ed bogie pivot pin inEASA AD No : 2012-0053

EASA Form 110 Page 3/3 accordance with the instructions of Airbus SB A330- 32-3240 Revision 02 or Airbus SB A340-32-4281 Revision 01 or Airbus SB A34 0-32-5096 Revision 01, as applicable to aeroplane model. (4) If, during any NDT inspection as required by pa ragraph (3) of this AD, the bogie pivot pin base metal is found corroded, befor e next flight, accomplish the applicable corrective actions in accordance wit h the instructions of Airbus SB A330-32-3240 Revision 02 or Airbus SB A34 0-32-4281 Revision 01 or Airbus SB A340-32-5096 Revision 01, as applic able to aeroplane model. (5) Accomplishment of corrective actions as require d by paragraph (2) or (4) of this AD does not constitute terminating action for the repetitive inspection requirements of paragraph (1) of this AD. (6) Inspections and corrective actions, accomplishe d before the effective date of this AD in accordance with the instructions of A irbus SB A330-32-3240 at original issue or Revision 01 or Airbus SB A340- 32-4281 at original issue or Airbus SB A340-32-5096 at original issue, as app licable to aeroplane model , are acceptable for compliance with the requirements of paragraphs (1), (2), (3) and (4) of this AD, as applicable. After the effective date of this AD, repetitive in spections and applicable corrective actions as required by this AD must be a ccomplished in accordance with the instructions of Airbus SB A330- 32-3240 Revision 02 or Airbus SB A340-32-4281 Revision 01 or Airbus SB A34 0-32-5096 Revision 01, as applicable to aeroplane model. (7) Within 90 days after accomplishment of each ins pection as required by paragraphs (1) and (3) of this AD, as applicable, r eport the inspection results (including no findings) to Airbus, in accor dance with the instructions of Airbus SB A330-32-3240 Revision 02 or Airbus SB A340-32-4281 Revision 01 or Airbus SB A340-32-5096 Revision 01, as applicable to aeroplane model.

Ref. Publications: Airbus SB A330-32-3240 Revision 02 dated 02 December 2011.
Airbus SB A340-32-4281 Revision 01 dated 02 Decembe r 2011.
Airbus SB A340-32-5096 Revision 01 dated 02 Decembe r 2011. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 16 February 2012 as PAD 12 -016 for consultation until 15 March 2012. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: Airbus – Airworthiness Off ice – EIAL; E-mail: airworthiness.A330-A340@airbus.com.