EASA AD No.: 2013-0013R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0013R1

Date: 20 February 2013

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):

A300-600 aeroplanes

TCDS Number: France No.145

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2013-0013 dated 15 January 2013, which 

superseded DGAC France AD 1997-375-239(B)R3 dated 12 July 2000.

ATA 57 Wings – Rear Spar Build Slot between Ribs 1 and 2 – Inspection

Manufacturer(s): Airbus (Formerly Airbus Industries)

Applicability: Airbus A300B4-601, A300B4-603, A300B4-605R, A300B4-620, A300B4-

622, A300B4-622R, A300C4-605R/F, A300C4-620, and A300F4-605R

aeroplanes, all manufacturer serial numbers.

Reason: Wing fatigue tests carried out by Airbus revealed cracks on the vertical web 

of the rear spar between Ribs 1 and 2. Similar cracks in the same area were 

reportedly found by A300 aeroplane operators. In all cases, the cracks ran 

from the tip of the build slot to the nearest adjacent bolt hole.

This condition, if not detected and corrected, could affect the structural 

integrity of the aeroplane.

To address this unsafe condition, DGAC France issued AD 1997-375-239

(later revised, now at Revision 3) to require an eddy current inspection of the 

aft face of the wing rear spar in the area adjacent to the build slot on Left 

Hand (LH) and Right Hand (RH) wings.

Since that AD was issued, a fleet survey and updated fatigue and damage 

tolerance analysis were performed in order to substantiate the second A300-

600 Extended Service Goal (ESG2) exercise. The results of the survey and

analysis showed that the inspection threshold and interval must be reduced 

to allow timely detection of cracks and accomplishment of an applicable 

corrective action.

Prompted by these findings, Airbus issued Airbus Service Bulletin (SB) 

A300-57-6059 Revision 04.
EASA AD No.: 2013-0013R1

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

For the reasons described above, this AD retains the requirements of DGAC 

France AD 1997-375-239(B)R3, which is superseded, but redefines the 

thresholds and intervals. This AD also expands the applicability to 

aeroplanes on which Airbus modification (mod) 12102 has been embodied 

in production and to aeroplanes on which Airbus SB A300-57-6063 (Airbus 

mod 11130) has been embodied in service.

This AD is re-published for clarification of the inspection thresholds and 

intervals.

Effective Date: Revision 1: 06 March 2013

Original issue: 29 January 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance times (thresholds and intervals, flight hours or 

flight cycles, whichever occurs first) defined in Table 1, Table 2, Table 3 

and Table 4 of Airbus SB A300-57-6059 Revision 4, as applicable to the 

aeroplane configuration and aeroplane utilization, accomplish repetitive 

eddy current inspections of the aft face of the wing rear spar web in the 

area adjacent to the build slot in accordance with the instructions of

Airbus SB A300-57-6059 Revision 04.

(2) If, during any inspection as required by paragraph (1) of this AD, 

discrepancies are detected, before next flight, accomplish the 

applicable corrective actions in accordance with the instructions of 

Airbus SB A300-57-6059 Revision 04.

(3) Corrective actions, as required by paragraph (2) of this AD do not 

constitute terminating action for the repetitive inspection requirements 

of paragraph (1) of this AD.

(4) Inspections and corrective actions, accomplished before the effective 

date of this AD, in accordance with the instructions of Airbus SB A300-

57-6059 at original issue up to Revision 03, are acceptable to comply 

with the initial requirements of paragraphs (1) and (2) of this AD (initial 

and repetitive inspections). After the effective date of this AD, repetitive 

inspections and, depending on findings, corrective actions must be 

accomplished in accordance with the instructions of Airbus SB A340-

57-6059 at Revision 04.

Ref. Publications: Airbus SB A300-57-6059 Revision 04 dated 22 February 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. The original issue of this AD was posted on 26 November 2012 as PAD 

12-148 for consultation until 24 December 2012. 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), 

Telephone: + 33 (0)5 6118-4139, Fax: + 33 (0)5 6193-4451.