EASA AD No.: 2014-0191

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0191

Date: 29 August 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 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):

A310 aeroplanes

TCDS Number: EASA.A.172

Foreign AD: Not applicable

Supersedure: None

ATA 71 Powerplant – Side Link Clevis Engine Mount Bolts – Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A310-203 aeroplanes, all manufacturer serial numbers

Reason: During fatigue analysis performed in the scope of the Extended Service Goal, 

taking into account the certification loads and the new lift-off loads, Airbus 

determined that side link clevis engine 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, Airbus 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: 12 September 2014
EASA AD No.: 2014-0191

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Within 18 months after the effective date of this AD, and, thereafter, at intervals

not to exceed 29 years, replace the side link clevis engine mount bolts, nuts

and bushings of the front engine mount on both engines and re-identify the new 

installed bolts with a cross (to differentiate them from the old ones) in 

accordance with the instructions of Airbus SB A310-71-2038.

Ref. Publications: Airbus SB A310-71-2038 original issue dated 08 April 2014.

The use 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 

this AD, please contact: AIRBUS SAS – EIAW (Airworthiness Office)

E-mail: continued.airworthiness-wb.external@airbus.com.