EASA AD No.: 2013-0050

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0050

Date: 05 March 2013

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):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None

ATA 71 Powerplant – CFM56-5/-5B – Aft Engine Mount Retainers –

Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industries)

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

A319-115, A320-111, 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 in-service inspections, several aft engine mount retainers, fitted on 

aeroplanes equipped with CFM56-5/5B engines, have been found broken.

The results of the investigations highlight that two different types of surface 

finish have been applied (respectively bright and dull material finishes), and that 

dull finish adversely affects the strength of the retainer with regard to fatigue 

properties of the part.

The pins which attach the engine link to the aft mount are secured by two nuts, 

which do not have a self-locking feature; this function is provided by the retainer 

brackets. In case of failure of the retainer bracket, the locking feature of the 

nuts of the inner and outer pins is lost; as a result, these nuts could 

subsequently become loose.

In case of full loss of the nuts, there is the potential to also lose the pins, in 

which case the aft mount link will no longer be secured to the aft engine mount.

The same locking feature is used for the three link assemblies of the aft mount.

For the reasons described above, this AD requires a one-time detailed visual

inspection (DVI) of the aft engine mount to identify the affected dull finish 

retainers and replace these with serviceable retainers. This AD also prohibits 

installation of any dull finish aft engine mount retainers.
EASA AD No.: 2013-0050

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

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Effective Date: 19 March 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 3 months after the effective date of this AD, accomplish a DVI of the 

aft engine mount retainers in accordance with the instructions of Airbus 

Alert Operators Transmission (AOT) A71N001-12 Revision 01.

(2) If, during the DVI as required by paragraph (1) of this AD, any installed dull 

finish aft engine mount retainer is found without cracks and not failed, 

within 25 flight cycles (FC), repeat the DVI as required by paragraph (1) of 

this AD and, within 50 FC after the first DVI as required by paragraph (1) of 

this AD, replace all dull finish retainers in accordance with the instructions 

of Airbus AOT A71N001-12 Revision 01.

(3) If, during any DVI as required by paragraph (1) of this AD, any installed aft 

engine mount retainer is found cracked or failed, before next flight, replace 

all affected aft engine mount retainers in accordance with the instructions 

of Airbus AOT A71N001-12 Revision 01.

(4) Aeroplanes from MSN 4942 and higher have been delivered by Airbus with 

non-affected aft engine mount retainers. These aeroplanes are not affected 

by the requirements of paragraph (1) of this AD, provided that no engines 

and/or no aft engine mount retainers have been removed since first flight.

(5) From the effective date of this AD, do not install any dull finish aft engine 

mount retainer on an aeroplane. The instructions of Airbus AOT A71N001-

12, or those of Goodrich Service Bulletin (SB) RA32071-146, can be used 

to verify the correct finish of the part.

Ref. Publications: Airbus AOT A71N001-12 Revision 01 dated 09 August 2012.

Goodrich SB RA32071-146 Revision 2, dated 26 July 2012.

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 21 December 2012 as PAD 12-161 for consultation 

until 18 January 2013. 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, Executive 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.