EASA AD No : 2008-0187 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2008-0187 

Date: 10 October 2008 

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 SAS

Type/Model designation(s) : 

A310 aircraft 

TCDS Number : France No 145 

Foreign AD : Not applicable 

Supersedure : This AD supersedes DGAC France AD F-2005-001, EASA approval 2004-12541. 

ATA 57 Wings – Centre Wing Rear Spar Internal Angle & Tee Fitting – 

Inspection / Modification 

Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE). 

Applicability: AIRBUS A310 aircraft, all certified models, all serial numbers. 

Reason: 

Analysis performed in the frame of the Extended Service Goal has led Airbus to 

modify the inspection programme [modification of thresholds, intervals and 

associated configurations] which is currently required by DGAC France AD 

F-2005-001. 

This modified inspection programme is necessary to detect and prevent damage 

associated with a structural fatigue phenomenon of the rear spar internal angle 

and the tee fitting located in the centre wing box. This condition, if not corrected, 

could affect the structural integrity of the centre wing box. 

For the reason stated above, this new EASA AD retains the requirements of 

DGAC France AD F-2005-001, which is superseded, and refers to the latest 

revision of Airbus Service Bulletin (SB) A310-57-2047. 

Effective Date: 24 October 2008 
EASA AD No : 2008-0187 

EASA Form 110 Page 2/3 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

1. Rear spar internal angle inspection 

1.1 At the threshold defined in Airbus SB A310-57-2047 Revision 07, 

accomplish the inspection, and apply the corrective action if necessary, 

of the holes in the rear spar internal angle located in the centre wing 

box in accordance with the instructions of Airbus SB A310-57-2047 

Revision 07. 

1.2 According to the results of the previous inspection and the corrective 

action taken, repeat the inspection and the corrective action, if 

necessary, at the intervals defined in, and in accordance with the 

instructions of Airbus SB A310-57-2047 Revision 07. 

 Aircraft which, on the effective date of this AD, have already exceeded 

the values of the inspection threshold or the inspection interval must be 

inspected at the earliest of the times specified after Table 2 of Airbus 

SB A310-57-2047 revision 07, to be calculated from the effective date 

of this AD, and without exceeding the previous values quoted in Airbus 

SB A310-57-2047 Revision 06. 

2. Tee fitting inspection 

2.1 At the threshold defined in Airbus SB A310-57-2047 Revision 07, 

accomplish the inspection and, if necessary, apply the corrective action 

of the tee fitting, LH side and RH side in accordance with the 

instructions of Airbus SB A310-57-2047 Revision 07. 

 Aircraft which, on the effective date of this AD, have already exceeded 

the values of the inspection threshold must be inspected at the earliest 

of the times specified after Table 3 of Airbus SB A310-57-2047 

Revision 07, to be calculated from the effective date of this AD, and 

without exceeding the previous values quoted in Airbus SB A310-57-

2047 Revision 06. 

2.2 According to the results of the previous inspection and the corrective 

action taken, repeat the inspection and the corrective action, if 

necessary, at the intervals defined in, and in accordance with the 

instructions of Airbus SB A310-57-2047 Revision 07. 

3. Credit for previously accomplished tasks 

 Any inspections (initial or repetitive) accomplished prior to the effective date 

of this AD in accordance with Airbus SB A310-57-2047 Revision 03 or 04 or 

05 or 06 are acceptable for compliance with the requirements of this AD. 

After the effective date of this AD, repetitive inspections and corrective 

actions must be accomplished in accordance with Airbus SB A310-57-2047 

at Revision 07. 

4. Modification of Angle and Tee Fitting 

 Within 5 years after 15 January 2005 [effective date of AD F-2005-001], 

modify the holes in the angle and in the tee fitting in accordance with the 

instructions of Airbus SB A310-57-2035 Revision 10. 

 This modification requirement does not apply to aircraft that have 

incorporated Airbus modifications 06672, 06673 and 07387, and aircraft 

modified in-service in accordance with Airbus SB A310-57-2035 at original 

issue or any later approved revisions. 

Incorporation of Airbus modifications 06672, 06673 and 07387, or 

accomplishment in-service of Airbus SB A310-57-2035, at original issue or 

any later approved revisions, does not exempt the aircraft from the inspection 

requirements of paragraphs 1 and 2 of this AD. 
EASA AD No : 2008-0187 

EASA Form 110 Page 3/3 

Ref. Publications: 

AIRBUS SB A310-57-2047 Revision 07 

AIRBUS SB A310-57-2035 Revision 10 

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 03 September 2008 as PAD 08-101 for consultation 

until 24 September 2008. No comments were received during the 

consultation period. 

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 93 36 96, Fax: + 33 5 61 93 44 51).