EASA AD No.: 2015-0079

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0079

Date: 07 May 2015

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 EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 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 [EU 

1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].

Design 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 2014-0066 dated 14 March 2014, including its

Correction dated 20 March 2014.

ATA 32 Landing Gear – Main Landing Gear Side Stay Upper Cardan Pin –

Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: This AD applies to:

1. 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), and

2. Airbus A340-211, A340-212, A340-213, A340-311, A340-312, A340-313, 

A340-541, A340-542, A340-642 and A340-643 aeroplanes, all MSN,

except aeroplanes on which an upper cardan pin on a Main Landing Gear 

(MLG) has never been replaced or re-installed since first entry into service of 

the aeroplane.

Reason: An A330 aeroplane equipped with Basic MLG was rolling out after landing 

when it experienced a nose wheel steering fault (unrelated to the safety subject 

addressed by this AD), which resulted in the crew stopping the aeroplane on 

the taxiway after vacating the runway. The subsequent investigation revealed 

that the right-hand MLG sidestay upper cardan pin had migrated out of position. 

The sidestay upper cardan nut and retainer had detached from the upper 

cardan pin and were found, still bolted together, in the landing gear bay.

Prompted by these findings, Airbus published Alert Operators Transmission 

(AOT) A32L003-14, providing inspection instructions and, as an interim 

solution, EASA issued AD 2014-0066 to require repetitive detailed inspections 
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(DET) of the MLG upper cardan pin, nut and retainer. That AD also required

accomplishment of a one-time gap check between wing rear spar fitting lugs 

and the bush flanges and, depending on findings, corrective action(s). The gap 

check (including corrections, as necessary) terminated the repetitive DET.

Since that AD was issued, further investigation concluded that the reported 

MLG sidestay upper cardan pin migration event had been caused by corrosion, 

due to lack of jointing compound and inadequate sealant application during 

MLG installation. Therefore, this issue affects any MLG that had an upper 

cardan pin replacement or re-installation, irrespective of MLG overhaul. Any 

corrosion on the upper cardan pin and nut threads would not have been 

detected during the previously required DET.

This condition, if not detected and corrected, could lead to a complete migration 

of the sidestay upper cardan pin and a disconnection of the sidestay upper arm 

from the aeroplane structure, possibly resulting in MLG collapse with 

consequent damage to the aeroplane and injury to occupants.

To address this potential unsafe condition, Airbus published Service Bulletin 

(SB) A330-32-3269, SB A340-32-4301 and SB A340-32-5115 providing 

inspection instructions. In addition, to prevent any improper re-installation of an 

upper cardan pin on a MLG, Airbus amended the applicable Aircraft

Maintenance Manual (AMM) on 01 October 2014.

For the reasons described above, this AD supersedes EASA 2014-0066 and 

requires a one-time DET of the MLG upper cardan pin and nut threads to check 

for corrosion or damage on the upper cardan pin and nut threads, and, 

depending on findings, replacement of the damaged part(s).

As this unsafe condition could also develop on A330 freighters and A340-500/-

600 aeroplanes, this AD also applies to those aeroplanes.

Effective Date: 21 May 2015

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

For the purpose of this AD, an upper cardan pin on a MLG is affected if it has 

been installed as replacement part, or re-installed since first entry into service 

of the aeroplane AND if this action was accomplished using the applicable 

Airbus AMM at a revision dated prior to 01 October 2014.

(1) For an affected upper cardan pin on an MLG, before exceeding 96 months

since its latest installation on an aeroplane, or within 12 months after the 

effective date of this AD, whichever occurs later, accomplish a DET of the

upper cardan pin and nut threads, in accordance with the instructions of 

Airbus SB A330-32-3269, or SB A340-32-4301, or SB A340-32-5115, as 

applicable to aeroplane type and model.

(2) If, during the DET as required by paragraph (1) of this AD, any corrosion, 

pitting or thread damage is detected, before next flight, replace the upper 

cardan pin and/or nut, as applicable, in accordance with the instructions of 

Airbus SB A330-32-3269, or SB A340-32-4301, or SB A340-32-5115, as 

applicable to aeroplane type and model.

Ref. Publications: Airbus SB A330-32-3269 at original issue dated 17 February 2015.

Airbus SB A340-32-4301 at original issue dated 17 February 2015.

Airbus SB A340-32-5115 at original issue dated 17 February 2015.

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 27 February 2015 as PAD 15-018 for consultation 
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until 13 March 2015. 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, 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 – EIAL,

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