E ASA AD No.: 2013

- 0050

TE. CAP.0011 0

- 003 © 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

. : 2 0 1 3 - 0050

Date: 0 5 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 E U 748/2012 , Part 21

. A.3B. In accordan ce 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 ope rate 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
F oreign AD: Not applicable Supersedure: None



### ATA 71 Powerplant

– CFM56 - 5/ - 5B

– 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

- 111 , 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

- 5/5B engines, have been found broken. The results of the i nvestigations 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 i nspection (DVI) of the a ft 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.E ASA AD No.: 2013

- 0050

TE. CAP.0011 0

- 003 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Effective Date: 1 9 March 2013 Required A ction(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 A irbus 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 f light c ycles (FC), repeat the DVI as required by paragraph (1) of this AD and , within 5 0 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 be en delivered by Airbus with non - affected aft engine mount retainers . T hese 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 S ervice B ulletin (SB) RA32071

- 146 , can be used to verify the correct finish of the part.
Ref. Public ations: 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 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 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 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

.