EASA AD No.: 2013-0232R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0232R1

Date: 02 October 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 and A300-600ST aeroplanes

TCDS Numbers: France No.145 and EASA.A.014

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2013-0232 dated 24 September 2013.

ATA 57 Wings – Top Skin at Front Spar between Ribs 1 and 7 –

Inspection / Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300-600 and A300-600ST aeroplanes, all certified models, all 

manufacturer serial numbers.

Reason: During full-scale fatigue testing conducted in the early 1990’s, cracks were 

found on the top skin of the wing between Ribs 1 and 7, starting at the front 

spar fastener holes.

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

structural integrity of the wing.

Consequently, Airbus issued Service Bulletin (SB) A300-57-6045 and DGAC 

France issued AD 97-374-238 for A300-600 aeroplanes and AD 1999-008-020 

for A300-600ST aeroplanes to require repetitive detailed inspections of the 

wing top skin and, in case of findings, an Eddy Current (EC) inspection, and, 

depending on the size of the cracks, repair.

After those ADs were issued, further cracks to the wing top skin were reported 

by operators, within an area not covered by the existing ADs. To address this 

potential unsafe condition, Airbus revised SB A300-57-6045 to extend the area 

to be inspected.

In addition, a fleet survey and updated Fatigue and Damage Tolerance 

analyses were performed in order to substantiate the second A300-600 

Extended Service Goal (ESG2) exercise. The results of these analyses have 

determined that the inspection thresholds and intervals must be reduced to 

allow timely detection of these cracks and the accomplishment of applicable 

corrective action(s).
EASA AD No.: 2013-0232R1

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As the ESG2 exercise is only applicable to A300-600 aeroplanes, A300-600ST 

aeroplanes are now addressed through new Airbus SB A300-57-9026.

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

France AD 97-374-238(B) and AD 1999-008-020(B), which are superseded, 

but requires those actions, for A300-600 aeroplanes only, within reduced 

thresholds and intervals.

This AD has been revised to correct Tables 1, 2, and 3, where the A300C4-

600R aeroplanes were inadvertently omitted.

Effective Date: 08 October 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Initially, within the compliance time defined in Table 1 of this AD, and,

thereafter, at intervals not to exceed those defined in Table 2 of this AD, 

as applicable to aeroplane configuration, accomplish a detailed inspection 

of the wing top skin between Ribs 1 to 7 in accordance with the 

instructions of Airbus SB A300-57-6045 Revision 09 or SB A300-57-9026, 

as applicable to aeroplane type.

Table 1: Inspection threshold

(whichever occurs first since aeroplane first flight) 

Aircraft Operation Compliance Time

FC FH

A300B4-600

A300B4-600R

A300C4-600

A300C4-600R

Normal Range 17 100 38 400

Short Range 17 100 38 400

A300F4-600

A300F4-600R

A300-600ST

Normal Range 22 000 49 500

Short Range 22 000 49 500

Table 2: Inspection interval

(whichever occurs first since last inspection)

Aircraft Operation Compliance Time

FC FH

A300B4-600

A300B4-600R

A300C4-600

A300C4-600R

Normal Range 5 100 11 000

Short Range 5 500 8 300

A300F4-600

A300F4-600R

A300-600ST

Normal Range 6 500 14 100

Short Range 7 000 10 600

Table 3: Grace Period

(whichever occurs later after the effective date of this AD)

Aircraft Grace Period

FC FH

A300B4-600

A300B4-600R

A300C4-600

A300C4-600R

1 000 2 200

A300F4-600R

A300-600ST 1 300 2 800
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Note: The grace period specified in Table 3 may be applied once for the initial 

or the next repetitive inspection after the effective date of this AD as required 

by paragraph (1) of this AD.

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

found in the top skin in the area forward of the front spar attachment, 

before next flight, contact Airbus for approved repair instructions and, 

within the compliance time defined in those instructions, accomplish the 

repair accordingly.

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

is found or suspected in the top skin at or aft of the spar attachment, 

before next flight, accomplish an EC inspection of the affected or 

suspected area to confirm and measure the length of the crack, in 

accordance with the instructions of Airbus SB A300-57-6045 Revision 09 

or SB A300-57-9026, as applicable to aeroplane type.

(4) If, during any EC inspection as required by paragraph (3) of this AD, a 

crack is confirmed, but less than 6 mm in length, within 50 FC or 110 FH, 

whichever occurs first after crack confirmation, and, thereafter, at intervals

not to exceed 50 FC or 110 FH, whichever occurs first, accomplish a

detailed inspection of the crack in accordance with the instructions of 

Airbus SB A300-57-6045 Revision 09 or SB A300-57-9026, as applicable 

to aeroplane type.

(5) If, during any inspection as required by paragraph (3) or (4) of this AD, as 

applicable, a crack is confirmed and is equal to or more than 6 mm but 

less than 75 mm in length, accomplish the following actions:

(5.1) Before next flight after crack confirmation, accomplish a temporary 

repair in accordance with the instructions of Airbus SB

A300-57-6045 Revision 09 or SB A300-57-9026, as applicable to 

aeroplane type.

(5.2) Within 50 FC or 110 FH, whichever occurs first, after the temporary 

repair as required by paragraph (5.1) of this AD, and, thereafter, at

intervals not to exceed 50 FC or 110 FH, whichever occurs first,

accomplish a detailed inspection in accordance with Airbus SB 

A300-57-6045 Revision 09 or SB A300-57-9026, as applicable to 

aeroplane type.

(5.3) Within 250 FC or 550 FH, whichever occurs first, after embodiment 

of the temporary repair as required by paragraph (5.1) of this AD, 

contact Airbus for approved permanent repair procedures and 

accomplish these procedures accordingly.

(5.4) Permanent repair as required by paragraph (5.3) of this AD 

constitutes terminating action for the repetitive inspections required 

by paragraph (5.2) of this AD.

(6) If, during an inspection as required by paragraph (3) or (4) of this AD, a 

crack is confirmed and is equal to or more than 75 mm in length, before 

next flight, contact Airbus for approved repair instructions and accomplish 

those instructions accordingly.

(7) Accomplishment of inspections and/or repair as required by paragraph (2), 

(3), (4), (5) or (6) of this AD, as applicable, does not constitute terminating 

action for the repetitive inspections required by paragraph (1) of this AD.

(8) Inspections and/or repair, accomplished before the effective date of this 

AD in accordance with the instructions of Airbus SB A300-57-6045 at 

original issue up to Revision 08, are acceptable to comply with the initial 

requirements of this AD. From the effective date of this AD, the actions 

required by this AD must be accomplished in accordance with Airbus SB 

A300-57-6045 Revision 09 or SB A300-57-9026, as applicable to 

aeroplane type.
EASA AD No.: 2013-0232R1

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Ref. Publications: Airbus SB A300-57-6045 Revision 09 dated 21 May 2013.

Airbus SB A300-57-9026 original issue dated 06 June 2013.

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. The original issue of this AD was posted on 16 August 2013 as PAD 

13-120 for consultation until 13 September 2013. 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)

E-mail: continued.airworthiness-wb.external@airbus.com.