EASA AD No : 2011-0113 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0113 

Date: 17 June 2011 

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 Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Directive 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, A300-600 and A300-600ST aeroplanes 

TCDS Number : France N° 145 and EASA.A.014 

Foreign AD : Not applicable 

Supersedure : None 

ATA 74 Ignition – Ignition Starting and Continuous Relight – Auto-Relight 

Function Implementation for CF6-80C2 Engines 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus model A310-204, A310-304, A310-308, A300B4-601, A300B4-603, 

A300B4-605R, A300C4-605R and A300F4-605R aeroplanes, all serial 

numbers, which are powered by General Electric (GE) CF6-80C2 series 

engines, and 

Airbus model A300F4-608ST aeroplanes, all serial numbers. 

Reason: Two single flame out events attributed to inclement weather occurred on Wide 

Body (WB) aeroplanes powered with GE CF6-80C2 engines. 

On WB aeroplanes, no auto-relight function is embodied. To avoid long engine 

restart sequence after a non selection of continuous relight by the crew and a 

flame out event of both engines, resulting in strongly reduced control of the 

aeroplane especially at low altitude, the manufacturer Airbus designed a 

modification by introducing auto-relight function for aeroplanes powered by GE 

CF6-80C2 engines. 

For the reason described above, this EASA AD requires the installation on the 

aeroplane of an auto-relight function as a precaution and to increase restart 

capability without crew action. 

Effective Date: 01 July 2011 
EASA AD No : 2011-0113 

EASA Form 110 Page 2/2 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Within 6 000 Flight Hours or 30 months after the effective date of this AD, 

whichever occurs later, modify the aeroplane by introducing auto-relight 

function in accordance with the Accomplishment Instructions of Airbus Service 

Bulletin (SB) A310-74-2003 Revision 01 or A300-74-6003 Revision 01 or 

A300-74-9001 Revision 02, as applicable to aeroplane model. 

Ref. Publications: Airbus SB A310-74-2003 Revision 01, 

Airbus SB A300-74-6003 Revision 01, 

Airbus SB A300-74-9001 Revision 02. 

The use of later approved revisions of these documents 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 13 May 2011 as PAD 11-053 for consultation until 

10 June 2011. The Comment Response Documents can be found at 

http://ad.easa.europa.eu/.

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

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).