EASA AD No : 2012-0056 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0056 

Date: 03 April 2012 

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 EC 1702/2003, Part 21A.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]. 

Type Approval Holder’s Name : 

AIRBUS 

Type/Model designation(s) : 

A310 aeroplanes 

TCDS Number : France TCDS No 145 

Foreign AD : Not applicable 

Supersedure : None 

ATA 71 Engine Mounts – Forward Engine Mount Bolts – Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus model A310-203 and A310-203C aeroplanes, all serial numbers. 

Reason: Post type-certification analyses performed in the frame of the Extended Service 

Goal (ESG) exercise, demonstrated a reduced fatigue life for the side link bolts, 

centre sway link bolts and thrust link bolts of the General Electric (GE) CF6-

80A3 forward engine mounts. 

This condition, if left uncorrected, could result in a deterioration of the structural 

integrity of the front engine mount bolts. 

For the reasons described above, this AD requires replacement of all side link 

bolts, centre sway link bolts and all thrust link bolts of GE CF6-80A3 powered 

aeroplanes.

Effective Date: 17 April 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless previously accomplished: 

(1) Within 18 months after the effective date of this AD, replace the bolts all side 

link bolts on left hand (LH) and right hand (RH) side of the engine, centre 

sway link bolts and thrust link bolts of both engines, Part Number (P/N) 

9021M88P01 (and 9021M88P02), 9205M81P01, 9021M88P03 (and 

9021M88P04) and PN 9205M82P01 with new bolts (same P/N) in 

accordance with the Accomplishment Instructions of AIRBUS Service 

Bulletin (SB) A310-71-2037 original issue. 
EASA AD No : 2012-0056 

EASA Form 110 Page 2/2 

(2) Thereafter, at intervals not exceeding 134 months, replace again all forward 

engine mount bolts of both engines in accordance with the Accomplishment 

Instructions of AIRBUS Service Bulletin (SB) A310-71-2037 original issue.

Ref. Publications: Airbus SB A310-71-2037 original issue dated 30 September 2011. 

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 15 November 2011 as PAD 11-121 for consultation 

until 13 December 2011. 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 content of the requirements in this 

AD, please contact: AIRBUS SAS – EAW (Airworthiness Office, Telephone: 

+ 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).