E ASA AD No.: 20 14

- 0 191

TE. CAP.0011 0

- 00 4 © 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

. : 20 14 - 0 1 9 1

Date: 2 9 A ugust 2014

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 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 ope rate an aircraft to which an AD applies, except in accordance with the requ irements 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): A310 aeroplanes

TCDS Number: EASA.A.172

F oreign AD: Not applicable
Supersedure: None



### ATA 71 Powerplant

– Side L ink C levis E ngine M ount B olts

– Re placement

Manufacturer(s): Airbus ( f ormerly Airbus Industrie)
Applicability: Airbus A310

- 203 aeroplanes, all manufacturer serial numbers

Reason: During fatigue analysis performed in the scope of the Extended Service G oal , taking in to account the certification loads and the new lift

- off loads , Airbus determined that side link clevis engin e mount bolts do not meet the Design Service Goal (DSG) requirements on aeroplanes equipped with CF6

- 80A3 engines. This condition, if not corrected, could lead to failure of the front engine mount , possibly resulting in

- flight separation of the engine from the aeroplane

. To address this potential unsafe condition, A irbus issued Service Bulletin (SB) A310

- 71

- 2038 to introduce a life limit on the side link clevis engine mount bolts. For the reason described above, this AD requires implementation of the new life limit and replacement of all side link clevis engine mount bolts that have exceeded the new limit.
Effective Date: 1 2 September 2014E ASA AD No.: 20 14

- 0 191

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: W ithin 18 months after the effective date of this AD , and , thereafter , at interval s not to exceed 29 years, replace the side link clevis engine mount bolts, nut s and bushing s of the front engine mount on both engines and r e - identify the new installed bolts with a cross ( to differentiate them from the old ones ) in accordance with the instruction s of Airbus SB A310

- 71

- 2038

. Ref. Public ations: Airbus SB A310

- 71

- 2038 o riginal issue dated 08 April 2014

. The u se 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. This AD was posted on 23 July 2014 as PAD 14

- 120 for consultation until 20 August 2014

. No comments were received during the consultation period

. 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 t his AD, please contact: AIRBUS SAS

– E I AW (Airworthiness Office ) E

- mail: continued.airworthine ss - wb.external@airbus.com

.