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 i ssued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communi ty, its Member States and of t he 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 a ccomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with the re quirements 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 perf ormed in the frame of the Extended Service Goal (ESG) exercise, demonstrated a reduc ed 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 re sult 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 thru st 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 dat e 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 Bulle tin (SB) A310-71-2037 original issue.

Ref. Publications: Airbus SB A310-71-2037 or iginal 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 subs tantiated, 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 technica l 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).