EASA AD No.: 2015-0021

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/3

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

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0021

Date: 13 February 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: This AD supersedes EASA AD 2013-0050 dated 05 March 2013.

ATA 71 Powerplant – 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, A320-211, 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 CFM56-5A/5B engines, have been found broken.

The results of the initial investigations highlighted that two different types of 

surface finish had been applied (respectively bright and dull material finishes), 

and that dull finish 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.

This condition, if not detected and corrected, could lead to in-flight loss of an aft 

mount link, possibly resulting in damage to the aeroplane and injury to person 

on the ground.
EASA AD No.: 2015-0021

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/3

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

To address this potential unsafe condition, EASA issued AD 2013-0050 to 

require detailed inspections (DET) of the aft engine mount retainers and the 

replacement of all retainers with dull finish with retainers having a bright finish.

Since that AD was issued, inspection results have shown that the main cause 

of crack initiation remains the vibration dynamic effect that affects both 

retainers, either with "dull" or "bright" surface finishes. The non-conforming 

"dull" surface’s pitting is an aggravating factor.

For the reasons described above, this AD retains the requirements of EASA AD 

2013-0050, which is superseded, and requires repetitive DET of all aft engine 

mount retainers and, depending on findings, their replacement.

This AD is considered to be an interim action, pending development and 

availability of a final solution.

Effective Date: 27 February 2015

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Restatement of the requirements of EASA AD 2013-0050:

Note: AD 2013-0050 used the acronym DVI instead of the current DET. This 

does not constitutes a technical or requirement change.

(1) Within 3 months after the 19 March 2013 [the effective date of EASA AD

2013-0050], accomplish a DET 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 DET 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 DET as required by paragraph (1) of 

this AD and, within 50 FC after the first DET 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 the DET 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 

“bright” finish aft engine mount retainers. These aeroplanes are not 

affected by the requirements of paragraph (1) of this AD, provided it is 

determined that no engine and/or no aft engine mount retainer has been 

removed from the aeroplane since Airbus date of manufacture.

A review of aeroplane maintenance records is acceptable to make this 

determination, provided those records can be relied upon for the purpose 

of this requirement.

(5) From 19 March 2013 [the effective date of EASA AD 2013-0050], 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.

New requirements of this AD:

(6) Within the compliance time as specified in Table 1 of this AD, as 

applicable, and, thereafter, at intervals not to exceed 12 months, 

accomplish a DET of the aft engine mount retainers in accordance with the 

instructions of Airbus SB A320-71-1060, or Goodrich Aerostructures SB 

RA32071-160.
EASA AD No.: 2015-0021

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/3

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

Table 1 – Inspection Threshold

Compliance Time (A, B or C, whichever occurs later)

A

Within 12 months since Airbus date of manufacture of the 

aeroplane

B Within 12 months after installation of new retainers

C Within 9 months after the effective date of this AD

(7) If, during any DET as required by paragraph (6) of this AD, any aft engine 

mount retainer is found damaged, cracked or broken, or detected as 

missing, before next flight, replace the affected aft engine mount retainers

of the affected engine installation in accordance with the instructions of 

Airbus SB A320-71-1060.

(8) Within 30 days after any DET as required by paragraph (6) of this AD

when findings are made, report the result to Airbus.

(9) Replacement of retainers on an aeroplane, as required by paragraph (7) of 

this AD, does not constitute terminating action for the repetitive DET as 

required by paragraph (6) of this AD for that aeroplane.

Ref. Publications: Airbus AOT A71N001-12, Revision 01 dated 09 August 2012, or Revision 02 

dated 27 February 2013.

Airbus SB A320-71-1060 dated 09 October 2014.

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

Goodrich Aerostructures SB RA32071-160, original issue dated 18 September 

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. This AD was posted on 09 January 2015 as PAD 15-001 for consultation 

until 06 February 2015. 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.