EASA AD No.: 2015-0038

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0038

Date: 04 March 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):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None

ATA 71 Powerplant – Forward Engine Mount – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A319-111, A319-112, A319-113, A319-114,

A319-115, A320-211, A320-212, A320-214, A320-215, A320-216, A321-111, 

A321-112, A321-211, A321-212 and A321-213 aeroplanes, all manufacturer 

serial numbers.

Reason: During a A320 Extended Service Goal (ESG) residual fatigue test, in which new 

loads were used, taking into account the results of the 2006 fleet survey, the 

CFM56-5A/5B forward engine mount experienced a failure before reaching the 

threshold/interval for the detailed inspection of that forward engine mount, as

identified in Airbus A318/A319/A320/A321 Airworthiness Limitations Section

(ALS) Part 2 (hereafter referred to in this AD as ‘the ALS’) task 712111-01. In 

case of total loss of the primary load path, the current maintenance 

requirements do not ensure the design integrity of the remaining structure.

This condition, if not corrected, could lead to in-flight loss of an engine, possibly 

resulting in reduced control of the aeroplane and injury to persons on the 

ground. 

For the reasons described above, this AD requires implementation of a reduced

threshold and interval for the detailed inspections (DET) of the forward engine 

mount on both right hand (RH) and left hand (LH) sides, as specified in the

ALS, task 712111-01.

Once further investigations and test are completed, the threshold and interval of 

the ALS task 712111-01 will likely be modified accordingly.

Effective Date: 18 March 2015
EASA AD No.: 2015-0038

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Before exceeding 800 flight cycles (FC) since aeroplane first flight, or since

last DET in accordance with the ALS, task 712111-01, as applicable, or 

within 800 FC after the effective date of this AD, whichever occurs later,

and, thereafter, at intervals not to exceed 800 FC, accomplish a DET of the 

forward engine mount on the aeroplane, both RH and LH sides (see Note).

(2) If, during any DET as required by paragraph (1) of this AD, any 

discrepancy is detected, before next flight, replace the affected forward 

engine mount with a serviceable part (see Note).

Note: Accomplishment of a DET as required by paragraph (1) of this AD, and 

replacement of a forward engine mount as required by paragraph (2) of this AD,

in accordance with the instructions of Airbus A318/A319/A320/A321 AMM task 

712111-210-040, is an acceptable method to comply with those requirements.

(3) Replacement of a forward engine mount on an aeroplane as required by

paragraph (2) of this AD does not constitute terminating action for the 

repetitive DET as required by paragraph (1) of this AD for that aeroplane.

(4) Compliance with the requirements of this AD also constitutes compliance 

with the requirements of EASA AD 2013-0147, when related to task 

712111-01 as specified in the ALS.

Ref. Publications: Airbus A318/A319/A320/A321 ALS Part 2, Revision 03, dated 27 October 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. 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 – EIAS;

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