EASA AD No.: 2014-0258

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0258

Date: 28 November 2014

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 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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A319 and A320 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None

ATA 71 Power Plant – Aft Engine Mount Bolts – Re-Torque

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A319-113, A319-114, A320-211 and A320-212 aeroplanes, all 

manufacturer serial numbers.

Reason: In the Aircraft Maintenance Manual (AMM) revision dated May 2013, a wrong 

torque value was added in AMM task 71-00-00-400-040-A01 “Installation of the 

power plant with Engine Positioner TWW75E”. Temporary Revisions (TR) 

dated March 2014 were published by Airbus to correct the information and with

AMM revision dated May 2014, Task 71-00-00-400-040-A01 was corrected to 

include the correct values. Notwithstanding those actions, static and fatigue 

analyses have concluded that this under-torque scenario negatively impacts the 

assembly performance, reducing the aft mount capability.

This condition, if not corrected and if combined with any maintenance damage,

could lead to aft engine mount failure, possibly resulting in engine detachment

and consequent reduced control of the aeroplane.

For the reasons described above, this AD requires identification of CFM56-5

engines (those listed in TCDS EASA.E.067) that were installed by using the 

wrong torque data of AMM instructions mentioned above and re-torque of the 

four aft mount pylon bolts of those engines.

Effective Date: 12 December 2014
EASA AD No.: 2014-0258

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 6 months or 1 500 flight cycles, whichever occurs first

after the effective date of this AD, accomplish the following actions in 

accordance with the instructions of Airbus Service Bulletin (SB)

A320-71-1063, as required by paragraphs (1.1) and (1.2) of this AD.

(1.1) Determine whether an engine has been installed on the aeroplane 

by reference to instructions of AMM task 71-00-00-400-040-A01 

dated May 2013 or later (except as specified in paragraph (2) of this 

AD) during which a wrong torque value was applied to the aft engine 

mount bolts.

A review of the aeroplane maintenance records is acceptable to 

make this determination, provided those records can be relied upon 

for the purpose of this requirement.

(1.2) For each engine installation, determined as required by paragraph 

(1.1) of this AD, apply a re-torque of the aft engine mount bolts to 

the correct value as published in AMM revision dated May 2014 or 

later revision, and in AMM TR dated March 2014.

(2) From the effective date of this AD, it is allowed to install a CFM56-5 engine 

on an aeroplane, provided this is done in accordance with the instructions 

as specified in an AMM TR dated March 2014, or an AMM revision dated

May 2014, or a later revision.

Ref. Publications: Airbus SB A320-71-1063 original issue dated 13 August 2014.

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 posted on 28 October 2014 as PAD 14-158 for consultation 

until 25 November 2014. 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 – EIAS;

Fax +33 5 61 93 44 51; E-mail: account.airworth-eas@airbus.com.