EASA AD No.: 2015-0082

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0082

Date: 11 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: None

ATA 71 Power Plant – Aft and Forward Engine Mount Bolts – Torque Check

/ Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: 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, and

Airbus A340-541, A340-542, A340-642 and A340-643 aeroplanes, 

from manufacturer serial number (MSN) 0715 to MSN 1507 inclusive, and MSN 

1509, except aeroplanes on which all engines have been removed and/or 

replaced since Airbus date of manufacture.

Reason: In 2013, during a pre-delivery test on an A330 aeroplane fitted with Pratt & 

Whitney (PW) PW4170 engines, an issue with N1 vibrations level on ENG1 

was identified. While performing an engine removal, one forward engine mount 

bolt was found improperly torqued. The investigation concluded this was due to 

a production line engine installation quality issue. Further analysis showed that 

some aeroplanes, delivered between June 2006 and January 2014, may have 

had the rear (AFT) and forward (FWD) engine mount bolts improperly torqued.

This condition, if not detected and corrected, could ultimately lead to an in-flight 

detachment of the engine from the aeroplane, possibly resulting in damage to 

the aeroplane and/or injury to persons on the ground.

Prompted by these findings, Airbus issued four Alert Operators Transmissions

(AOT) A71L004-14 (for A330 aeroplanes fitted Pratt & Whitney (PW) engines),

AOT A71L006-14 (for A330 aeroplanes fitted with General Electric (GE) 

engines), AOT A71L005-14 (for A330 aeroplanes fitted with Rolls Royce (RR) 
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Trent 700 engines) and AOT A71L008-14 (for A340 aeroplanes fitted with RR 

Trent 500 engines) to provide torque check instructions.

For the reasons described above, this AD requires a one-time torque check of 

the FWD and AFT engine mount bolts and, depending on findings, re-torque of 

the affected bolt(s) and/or replacement of all four bolts and associated nuts. 

Effective Date: 25 May 2015

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

For the purpose of this AD, an affected engine is an engine that has never been 

removed and/or replaced since Airbus date of manufacture.

For A330 aeroplanes fitted with PW engines:

(1) Within 2 000 flight hours (FH), or during accomplishment of Airbus Service 

Bulletin (SB) A330-71-3028, whichever occurs first after the effective date 

of this AD, accomplish a torque check of FWD and AFT engine mount bolts 

on each affected engine, at the locations as specified in, and in 

accordance with the instructions of Airbus AOT A71L004-14 Revision 01.

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

discrepancy is detected, within the compliance time defined in Airbus AOT

A71L004-14 Revision 01, depending on aeroplane configuration and flight 

cycles (FC) / FH accumulated by the aeroplane since aeroplane first flight, 

accomplish the applicable corrective actions (re-torque of each affected 

bolt and/or replacement of all four bolts and associated nuts) in 

accordance with the instructions of Airbus AOT A71L004-14 Revision 01.

For A330 aeroplanes fitted with GE engines:

(3) Within 2 000 FH after the effective date of this AD, accomplish a torque 

check of FWD and AFT engine mount bolts on each affected engine, at the 

locations as specified in, and in accordance with the instructions of Airbus 

AOT A71L006-14.

(4) If, during the torque check as required by paragraph (3) of this AD, any 

discrepancy is detected, within the compliance time defined in Airbus AOT 

A71L006-14, depending on FC / FH accumulated by the aeroplane since 

aeroplane first flight, accomplish the applicable corrective actions (retorque of each affected bolt and/or replacement of all bolts and associated 

nuts) in accordance with the instructions of Airbus AOT A71L006-14.

For A330 aeroplanes fitted with RR Trent 700 engines:

(5) Within 2 000 FH after the effective date of this AD, accomplish a torque 

check of FWD and AFT engine mount bolts on each affected engine, at the 

locations as specified in, and in accordance with the instructions of Airbus 

AOT A71L005-14 Revision 01.

(6) If, during the torque check as required by paragraph (5) of this AD, any 

discrepancy is detected, within the compliance time defined in Airbus AOT 

A71L005-14 Revision 01, accomplish the applicable corrective actions (retorque of each affected bolt and/or replacement of all four bolts and 

associated nuts/washers) in accordance with the instructions of Airbus 

AOT 

A71L005-14 Revision 01.

For A340 aeroplanes fitted with RR Trent 500 engines:

(7) Within 2 000 FH after the effective date of this AD, accomplish a torque 

check of FWD and AFT engine mount bolts on each affected engine, at the 

locations as specified in, and in accordance with the instructions of Airbus 

AOT A71L008-14 Revision 01.

(8) If, during the torque check as required by paragraph (7) of this AD, any 

discrepancy is detected, within the compliance time defined in Airbus AOT 
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A71L008-14 Revision 01, accomplish the applicable corrective actions (retorque of each affected bolt and/or replacement of all four bolts and 

associated nuts/washers) in accordance with the instructions of Airbus 

AOT A71L008-14 Revision 01.

For all A330 aeroplanes and A340-500/-600 aeroplanes:

(9) A torque check of all FWD and AFT engine mount bolts of each affected 

engine on an aeroplane, accomplished before the effective date of this AD, 

in accordance with the instructions of Airbus AOT A71L004-14 or AOT 

A71L005-14 or A71L008-14 at original issue, as applicable, is an 

acceptable method to comply with the requirements of paragraphs (1), (5) 

and (7) of this AD, as applicable, for that aeroplane, provided that no 

discrepancy was detected during the torque check.

(10) Within 30 days after the torque check as required by this AD, or within 30 

days after the effective date of this AD, whichever occurs later, report the 

results of this check (including no discrepancies) to Airbus.

Ref. Publications: Airbus AOT A71L004-14 dated 01 April 2014, or Revision 01 dated 07 April 

2014.

Airbus AOT A71L006-14 dated 22 July 2014.

Airbus AOT A71L005-14 dated 29 September 2014, or Revision 01 dated 11 

December 2014.

Airbus AOT A71L008-14 dated 29 September 2014, or Revision 01 dated 18 

December 2014.

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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

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.