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 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): 

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 A340-200/300 fleet has shown that the current 

utilization rate of the aeroplanes is different from the assumptions used at 

the time of A340 initial certification. 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 forward engine mount cannot be guaranteed after 

either thrust link has accumulated 15 500 Flight Cycles (FC). 

Consequently, this AD introduces a Limit 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 assemblies, to trace the life of these 

assemblies and to replace them no later than the calculated deadline. 

Effective Date: 12 June 2009 
EASA 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 provided in SB A340-71-4006 Revision 00 

has been applied without taking into account the number of FC 

accumulated during year 2003, the requirements 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 & 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, 

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

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