EASA AD No : 2011-0040 

EASA Form 110 Page 1/2 

 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0040 

Date: 08 March 2011 

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 Number : EASA.A.004, EASA.A.015 

Foreign AD : Not applicable 

Supersedure : None 

ATA 32 Landing Gear – Main and Central Landing Gear Bogie Pivot 

Pins and Bushes – Inspection / Repair / Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A330 aeroplanes, models -201, -202, -203, -223, -243, -301, -302, 

-303, -321, -322, -323, -341, -342 and -343, all manufacturer serial 

numbers, except those on which Airbus modification 54500 has been 

embodied in production. 

Airbus A340 aeroplanes, models -211, -212, -213, -311, -312, -313, -541, 

-542, -642 and -643, all manufacturer serial numbers, except those on 

which Airbus modification 54500 has been embodied in production. 

Reason: During removals of A330/340 Main Landing Gear Bogie Beams and A340-

500/600 Centre Landing Gear Bogie Beams, cracks in the Bogie Pivot Pin 

(BPP) have been found. 

Investigations indicated that the main root cause is material heating due to 

friction between bogie pivot pin and bush. Consequences of that heating 

are chrome detachment and stress corrosion cracking (SCC). 

This situation, if not corrected, could result in the collapse of the main or 

central landing gear. 

As a precautionary measure, this AD requires a one-time inspection of the 

main landing gear (all types of A330 and A340) and central landing gear 

(A340-500/600 only) to detect degradation or cracking of the BPP, as 

applicable to aeroplane model, and the reporting of inspections results. 
EASA AD No : 2011-0040 

EASA Form 110 Page 2/2 

 

Effective Date: 22 March 2011 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished: 

(1) 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, perform a 

detailed visual inspection of the main landing gear and central landing 

gear bogie pivot pins and pivot pin bushes, in accordance with the 

instructions of Airbus Service Bulletin (SB) A330-32-3240 or Airbus 

SB A340-32-4281 or Airbus SB A340-32-5096 as applicable to 

aeroplane model. 

(2) If, during the inspection required by paragraph (1) of this AD, any 

bush is found cracked or damaged, before next flight, record finding 

details and do the applicable corrective actions in accordance with the 

instructions of Airbus SB A330-32-3240 or Airbus SB A340-32-4281 

or Airbus SB A340-32-5096, as applicable to aeroplane model. 

(3) If, during the inspection required by paragraph (1) of this AD, 

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

flight, record findings details and perform a Non-Destructive Test 

inspection of the affected bogie pivot pin in accordance with the 

instructions of Airbus SB A330-32-3240 or Airbus SB A340-32-4281 

or Airbus SB A340-32-5096, as applicable to aeroplane model. 

(4) If, during the Non-Destructive Test inspection required by paragraph 

(3) of this AD, the bogie pivot pin base metal is found corroded, before 

next flight, do the applicable corrective actions in accordance with the 

instructions of Airbus SB A330-32-3240 or Airbus SB A340-32-4281 

or Airbus SB A340-32-5096, as applicable to aeroplane model. 

(5) Within 90 days after accomplishment of the inspections required by 

paragraphs (1) and (3) of this AD, as applicable, report to Airbus all 

recorded inspections results (including no findings) in accordance with 

the instructions of Airbus SB A330-32-3240 or Airbus SB A340-32-

4281 or Airbus SB A340-32-5096, as applicable to aeroplane model.

Ref. Publications: Airbus SB A330-32-3240 at original issue; 

Airbus SB A340-32-4281 at original issue; 

Airbus SB A340-32-5096 at original issue. 

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 17 December 2010 as PAD 10-125 for 

consultation until 14 January 2011. The Comment Response 

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

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research 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 – EAL; 

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