EASA AD No.: 2009-0204 

EASA Form 110 Page 1/2 

 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0204 

Date: 30 September 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) : 

A330 and A340-500/-600 aeroplanes 

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

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2008-0019 dated 28 January 2008. 

ATA 71 Power Plant – Engine Mount Link Pin Retention Bolts – 

Inspection / Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A330 aeroplanes, models -243, -341, -342, -343, all manufacturer 

serial numbers (MSN), 

Airbus A340 aeroplanes, models -541, -542, -642, -643, all MSN. 

Reason: It has been evidenced by test that the tightening torque settings on the 

Rolls Royce Trent 500 and Trent 700 forward (FWD) and aft (AFT) engine 

mount link pin retention bolts have always been higher than the design 

value. These bolts retain the washers that maintain the engine mount 

vertical load pins in position. 

If bolts, as a consequence of the over-torque, fail and move away, it would 

lead to loss of the vertical load pins, which could result in loss of the 

primary and/or secondary load path of the forward and/or aft engine mount 

which could potentially lead to engine separation. 

As a short term action, EASA AD 2008-0019 was issued to require a one 

time visual inspection of the impacted FWD and AFT engine mount link 

pin retention bolts in order to detect any broken or missing bolts. 

This AD, which supersedes EASA AD 2008-0019, mandates a one-time 

visual inspection of the FWD and AFT engine mount link pin retention 

bolts, in order to ensure that any over-torqued bolt is replaced. 

Effective Date: 14 October 2009 
EASA AD No.: 2009-0204 

EASA Form 110 Page 2/2 

 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated : 

(1) Unless already accomplished, perform a visual inspection of the FWD 

and AFT engine mount link pin retention bolts on all engines, in 

accordance with the instructions given in Airbus Service Bulletin (SB) 

A330-71-3022, or Airbus SB A340-71-5004, as applicable to the 

aeroplane type:

- For A330 aeroplanes identified in the applicability section, 

within 4 500 Flight Cycles (FC) after the effective date of this AD, 

- For A340 aeroplanes identified in the applicability section, 

within 2 500 FC after the effective date of this AD.

If an “X” is not marked on the bolt head, replace this bolt before next 

flight in accordance with the instructions given in Airbus SB 

A330-71-3022, or Airbus SB A340-71-5004, as applicable. 

(2) The actions defined in paragraph (1) of this AD are not required for any 

engine installed on: 

- A330 aeroplanes, from MSN 964 inclusive and subsequent, on 

which it can be demonstrated from data records that this engine has 

not been replaced or re-installed since the aeroplane original 

delivery date; 

- A340 aeroplanes, from MSN 981 inclusive and subsequent, on 

which it can be demonstrated from data records that this engine has 

not been replaced or re-installed since the aeroplane original 

delivery date. 

(3) After the effective date of this AD, no person shall install an engine on 

any aeroplane, unless in compliance with the requirements of this AD. 

Ref. Publications: Airbus Service Bulletin A330-71-3022 at Original issue, 

Airbus Service Bulletin A340-71-5004 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 10 July 2009 as PAD 09-090 for consultation 

until 10 August 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 questions concerning the technical content of the 

requirements in this AD, please contact: 

AIRBUS SAS – Airworthiness Office - EAL. Fax: +33 5 61 93 45 80. 

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