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

Foreign AD: Not applicable 

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

ATA 32 Landing Gear – Main and Center Landing Gear Bogie Pivot 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 and A340-643 

aeroplanes, all MSN. 

Reason: During removals of A330/340 Main Landing Gear (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 the 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, could lead to collapse of the main 

or center landing gear, possibly resulting in damage to the aeroplane and/or 

injury to occupants. 

As a precautionary measure, EASA issued AD 2011-0040 to require a one-time 

inspection of the MLG (all types of A330 and A340 aeroplanes) and CLG 

(A340-500/600 aeroplanes only) to detect degradation or cracking of the bogie 

pivot pin, as applicable to aeroplane model, and the reporting of inspections 

results. 

Following issuance of EASA AD 2011-0040, several operators reported finding 
EASA 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 modification 54500) could 

also be affected by this condition. 

Prompted by these findings, Airbus have developed an inspection programme 

consisting of repetitive inspections of the bogie pivot pin and applicable 

corrective actions. 

For the reasons described above, this AD, which supersedes 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 Table 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 CLG (for A340 

aeroplanes only) and pivot pin bushes in accordance with the instructions 

of Airbus Service Bulletin (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. 

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 

Bogie pivot pin fitted on MLG and CLG flight. 

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 paragraph (1) of this AD, any bush 

is found cracked or damaged, before next flight, accomplish the applicable 

corrective actions in accordance 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. 

(3) If, during any inspection as required by paragraph (1) of this AD, degraded 

chrome plating on a bogie pivot pin is found, before next flight, perform a 

Non-Destructive Test (NDT) inspection of the affected bogie pivot pin in 
EASA 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 A340-32-5096 Revision 

01, as applicable to aeroplane model. 

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

bogie pivot pin base metal is found corroded, before next flight, accomplish 

the applicable corrective actions in accordance 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. 

(5) Accomplishment of corrective actions as required 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, accomplished before the effective date 

of this AD in accordance with the instructions of Airbus 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 applicable 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 inspections and applicable 

corrective actions as required by this AD must be accomplished in 

accordance 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. 

(7) Within 90 days after accomplishment of each inspection as required by 

paragraphs (1) and (3) of this AD, as applicable, report the inspection 

results (including no findings) to Airbus, in accordance 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 December 2011. 

Airbus SB A340-32-5096 Revision 01 dated 02 December 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 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 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 – Airworthiness Office – EIAL; 

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