EASA AD No.: 2009-0115

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009-0115

Date: 29 May 2009

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 parti cipate 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 ai rcraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in a ccordance 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):
A340-200/-300 aeroplanes

TCDS Number: EASA.A.015

Foreign AD: Not applicable

Supersedure: None



### ATA 71 Power Plant – Forward Engine Mount Thrust Links - Replacement

Manufacturer(s): Airbus (Formerly Airbus Industrie)

Applicability: Airbus A340 models -211, -212, -213, -311, -312 and -313 aeroplanes, all manufacturer serial numbers.

Reason: A recent review of the A340-2 00/300 fleet has shown that the current utilization rate of the aeroplanes is di fferent from the assumptions used at the time of A340 initial certificati on. New calculations have been performed taking into account an updated mission profile to determine the impact to the loads on the forward engine mount. Engineering analysis using the new calculated loads has shown that the structural integrity of the forwar d engine mount cannot be guaranteed after either thrust link has accumulated 15 500 Flight Cycles (FC). Consequently, this AD introduces a Limi t Of Validity (LOV) of 15 500 FC for CFM 56-5C forward engine mount thrust links Part Number (P/N) 340-7005-3 and P/N 340-7005-4. In addition, this AD requires establishing the deadline for replacement of forward engine mount thrust link asse mblies, to trace the life of these assemblies and to replace them no later than the calculated deadline.

Effective Date: 12 June 2009EASA AD No.: 2009-0115

EASA Form 110 Page 2/2 Required action(s) and Compliance Time(s): Required as indicated, unless already accomplished: From the effective date of this AD each Operator must: (1) Before 15 June 2009, establish the deadline for the replacement of all CFM 56-5C forward engine mount thrust links P/N 340-7005-3 or P/N 340-7005-4 in accordance with the calculation method provided in Airbus Service Bulletin (SB) A340-71-4006 Revision 01.
Note: P/N 340-7005-3 and P/N 340-7005-4 are the P/N for the link only, included in P/N 340-7005-503 and P/N 340-7005-504, which are the P/N for the assembly (bearing and link). If the calculation method provi ded in SB A340-71-4006 Revision 00 has been applied without taking into account the number of FC accumulated during year 2003, the re quirements of paragraph (1) of this AD are no longer required. (2) No later than the deadline established as required by paragraph (1) of this AD, replace CFM 56-5C forward engine mount thrust links P/N 340-7005-3 or P/N 340-7005-4 in accordance with the instructions of SB A340-71-4006 Revision 01. (3) Before 15 June 2009, incorporate into the approved maintenance programme:

− A LOV of 15 500 FC applicable to CFM 56-5C forward engine mount thrust links P/N 340- 7005-3 and P/N 340-7005-4,
and

− A life-tracking requirement: It is mandatory to assure traceability and monitoring of these parts in accordance with EASA Part M.A.305.

Ref. Publications: Airbus Service Bulletin A340-71-4006 Revision 01. The use of later approved revisions of this document 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 published on 30 March 2009 as PAD 09-056 for consultation until 27 April 2009. 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 & Re search Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the te chnical 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

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