E ASA AD No.: 20 1 5

- 0021

TE. CAP.0011 0

- 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

. : 20 1 5

- 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 accordan ce 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 ope rate 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) exempt ion].


### Design Approval Holder’s Name:
AIRBUS Type/Model designation(s): A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2013

- 0050 dated 05 March 2013

.



### ATA 71 Powerplant

– Aft Engine Mount Retainer s – 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

- 11 1, A321

- 112, A321

- 211, A321

- 212 and A321

- 213 aeroplanes , all manufacturer serial numbers

.
Reason: During in

- service inspections, s everal a ft engine mount retainers
, fitted on aeroplanes equipped with CFM 56

- 5 A /5B engines, have been found broken. The results of the initial i nvestigations highlight ed that two different types of surface finish ha d 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.E ASA AD No.: 20 1 5

- 0021

TE. CAP.0011 0

- 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 detail ed inspection s ( 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 issu ed, inspection result s have shown that the main cause of crack initiation remains the vibration dynamic effect that affects both
r etainers , either with " d ull" or " b right" surface finishes. The non

- conforming

" d ull" 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 a ft engine mount ret ainers 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 A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: Restatement of the requirement s 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 1 9 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 f light c ycles (FC), repeat the DET as required by paragraph (1) of this AD and , within 5 0 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 ha s been removed from the aeroplane since Airbus date of manufacture

. A review of aeroplane maintenance records is acceptable to ma ke this de term i n ation, 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 interval s 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 Aero structures SB RA32071

- 16 0

.E ASA AD No.: 20 1 5

- 0021

TE. CAP.0011 0

- 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 retainer s 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 whe n findings are made, report the result to Airbus. ( 9 ) Replacement of retainers on an aeroplane , as required by paragraph ( 7 ) of this AD
, do es not constitute terminating action for the repetitive DET as require d by paragraph ( 6 ) of this AD for that aeroplane

.
Ref. Public ations: Airbus AOT A71N001

- 12
, Revision 01 dated 09 August 2012
, or Revision 02 dated 27 February 2013

. Airbus SB A320

- 71

- 1060 dated 09 Octob er 2014

. Goodrich Aerostructures SB RA32071

- 1 4 6, Revision 2 dated 26 July 2012

. Goodrich Aerostructures SB RA32071

- 160, original issue dated 18 September 2014

. The use of later approved revisions of th e s e document s 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 1 5

- 00 1 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 conte nt of the requirements in this AD, please contact: AIRBUS

- Airworthiness Office

– E I AS
, Fax +33 5 61 93 44 51, E

- mail: account.airworth

- eas@airbus.com

.