EASA AD No.: 2011-0211 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0211 

Date: 31 October 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 Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness 

Directive 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 : This AD supersedes EASA AD 2008-0223 dated 15 December 2008. 

ATA 32 Landing Gear – Main Landing Gear (MLG) Bogie Beam – 

Inspection / Repair 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

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

-301, -302, -303, - 321, -322, -323, -341, -342 and -343, all manufacturer 

serial numbers. 

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

-542, - 642 and -643, all manufacturer serial numbers. 

Reason: During a scheduled maintenance inspection on the MLG, the bogie stop pad 

was found deformed and cracked. Upon removal of the bogie stop pad for 

replacement, the bogie beam was also found cracked. 

Laboratory investigation indicates that an overload event has occurred and 

no fatigue propagation of the crack was evident. 

A second bogie beam crack has subsequently been found on another 

aeroplane, located under a bogie stop pad which only had superficial paint 

damage. 

This condition, if not detected and corrected, could result in the aeroplane 

departing the runway or to the bogie detaching from the aeroplane or gear 

collapses, which would all constitute unsafe conditions at speeds above 30 

knots. 

As a precautionary measure, EASA AD 2008-0223 required one-time detailed 

inspections under the bogie stop pad of both MLG bogie beams and, in case 

deformation or damage is detected, to apply the associated repair. 

Numerous bogie stop pad were found corroded and a few cracked as a result 
EASA AD No.: 2011-0211 

EASA Form 110 Page 2/3 

of the one-time inspection required by EASA AD 2008-0223 on A330, 

A340-200 and A340-300 aeroplanes. 

For the reasons described above, this AD, which supersedes EASA AD 

2008-0223: 

- retains the initial inspection requirement of EASA AD 2008-0223 for 

A330, A340-200 and A340-300 aeroplanes. 

- introduces a repetitive detailed visual inspection for A330, A340-200 and 

A340-300 aeroplanes. 

- retains the requirement of EASA AD 2008-0223 for A340-500 and 

A340-600 aeroplanes, for which further mandatory requirements might 

follow in future depending on the results of the one-time mandatory 

inspection in place. 

Effective Date: 14 November 2011 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the inspection threshold indicated in Table 1 of this AD, and 

depending on the MLG bogie beam condition at the effective date of 

this AD, perform detailed inspections of the left-hand (LH) and righthand (RH) bogie beams in the area of the bogie stop pad for 

detection of deformation or damage and do before further flight the 

applicable corrective actions. 

Table 1 – MLG Bogie Beam Inspection

MLG Bogie Beam 

condition at the 

effective date of this 

AD 

Inspection Threshold Required 

Instructions 

MLG bogie beams 

which have not been 

inspected in 

accordance with the 

instructions of Airbus 

Service Bulletin (SB) 

A330-32-3220, SB 

A340-32-4264, or SB 

A340-32-5087, as 

applicable to aeroplane 

model 

Upon accumulation by the 

MLG bogie beam of 2 500 

flight cycles (FC) or 22 

months, whichever occurs 

first, since its first flight on 

an aeroplane or since its 

first flight after its last 

overhaul, as applicable, but 

no later than 40 months 

since its first flight on an 

aeroplane or since its first 

flight after its last overhaul. 

Airbus SB A330-32-

3220 or SB A340-

32-4264 or SB 

A340-32-5087, as 

applicable to 

aeroplane model 

MLG bogie beams 

which have been 

inspected in 

accordance with the 

instructions of Airbus 

SB A330-32-3220, or 

SB A340-32-4264, as 

applicable to aeroplane 

model. 

a) Within 3 months after the 

effective date of this AD, 

or 

b) Within 2 500 FC or 24 

months, whichever occurs 

first, accumulated by the 

MLG bogie beam since its 

first flight after the last 

accomplishment of Airbus 

SB A330-32-3220 or A340-

32-4264, as applicable to 

aeroplane model, 

whichever occurs later 

between a) and b). 

Airbus SB A330-32-

3248 or Airbus SB 

A340-32-4286, as 

applicable to 

aeroplane model. 
EASA AD No.: 2011-0211 

EASA Form 110 Page 3/3 

(2) Thereafter, except for MLG bogie beams which have been inspected in 

accordance with the instructions of Airbus SB A340-32-5087, repeat the 

inspection required by paragraph (1) of this AD at intervals not to exceed 

2 500 FC or 24 months, whichever occurs first, from the last inspection, 

and do before further flight the applicable corrective actions in 

accordance with the instructions of Airbus SB A330-32-3248 or Airbus SB 

A340-32-4286, as applicable to aeroplane type. 

(3) Report to Airbus the results of the inspection, whatever they are, done in 

accordance with the instructions of Airbus SB A330-32-3220 or Airbus 

SB A340-32-4264 or Airbus SB A340-32-5087, as applicable to 

aeroplane model and as required by paragraph (1) of this AD, within 90 

days from the accomplishment date of the inspection. 

Ref. Publications: Airbus Service Bulletin A330-32-3220 at original issue dated 10 October 2008

Airbus Service Bulletin A340-32-4264 at original issue dated 10 October 2008

Airbus Service Bulletin A340-32-5087 at original issue dated 10 October 2008

Airbus Service Bulletin A330-32-3248 at original issue dated 05 October 2011

Airbus Service Bulletin A340-32-4286 at original issue dated 05 October 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. The required actions and the risk allowance have granted the issuance of 

a Final AD with Request for Comments, postponing the public 

consultation process after publication. 

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 questions concerning the technical content of the requirements in 

this AD, please contact: AIRBUS – Airworthiness Office – EAL 

Fax: + 33 5 61 93 45 80 or + 33 5 61 93 44 51; 

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