EASA AD No.: 2012-0138

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0138

Date: 26 July 2012

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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A300-600 aeroplanes

TCDS Number: France No.145

Foreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD 94-208-169(B)R2 dated 08 October 1997.

ATA 57 Wings – Front and Rear Spar Lower Boom at Rib 9 – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300-600 aeroplanes, all certified models, all manufacturer serial 

numbers, except aeroplanes on which Airbus modification 10161 has been 

embodied in production.

Reason: Full fatigue tests carried out by the manufacturer revealed crack initiation from 

the bolts holes at inboard and outboard of rib 9, on the front and rear spar 

bottom booms. Similar cracks at the same area were reported by A300-600 

aeroplane operators.

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

of the aeroplane.

To address this unsafe condition, DGAC France issued AD 94-208-169(B)R2 to

require an ultrasonic inspection of holes inboard and outboard of rib 9 on the 

front and rear spar bottom booms on Left Hand and Right Hand wings.

Since that AD was issued, a fleet survey and updated Fatigue and Damage 

Tolerance analysis have been performed in order to substantiate the second 

A300-600 Extended Service Goal (ESG2) exercise. The results of these 

analyses have shown that the risk for these aeroplanes is higher than initially 

determined and that, consequently, the inspection threshold and interval must 

be reduced to allow timely detection of cracks and the accomplishment of an 

applicable corrective action.

For the reasons explained above, this new AD retains the requirements of 

DGAC France AD 94-208-169(B)R2, which is superseded, and requires the 

accomplishment instructions within the new thresholds and intervals specified 
EASA AD No.: 2012-0138

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in Revision 04 of Airbus Service Bulletin (SB) A300-57-6037.

Effective Date: 09 August 2012

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the threshold defined in Table 1 of this AD, as applicable, and 

thereafter at intervals not to exceed the compliance time(s) indicated in 

Table 2 of this AD, as applicable, depending on aeroplane utilization,

accomplish an ultrasonic inspection of the lower boom of the front and rear 

spar inboard and outboard of rib 9 in accordance with the instructions of 

Airbus SB A300-57-6037 Revision 04.

Table 1: Inspection thresholds, whichever occurs later, A or B:

Operations

(see Note)

A: whichever occurs first since 

aeroplane first flight or since 

aeroplane modification in 

accordance with the instructions 

of Airbus SB A300-57-6039 (at 

any revision), as applicable

B: Whichever occurs 

first after the effective 

date of this AD

Normal range

14 100 Flight Cycles (FC) or 

30 400 Flight Hours (FH) 1 600 FC or 3 400 FH

Short range 15 200 FC or 22 800 FH 1 700 FC or 2 500 FH

Note: The short range is applicable for aeroplanes with an average flight time 

lower than 1,5 FH, and the normal range is applicable for aeroplanes with an 

average flight time equal or higher than 1,5 FH.

Table 2: Inspection intervals

Operations Compliance time, whichever occurs first

Normal range 3 900 FC or 8 400 FH

Short range 4 200 FC or 6 300 FH

(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-

57-6037 Revision 04.

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

constitute terminating action for the repetitive inspections as required by 

paragraph (1) of this AD.

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

of this AD in accordance with Airbus SB A300-57-6037 at original issue or 

Revision 01, or Revision 02, or Revision 03 are acceptable to comply with 

the initial requirements of paragraph (1) of this AD. After the effective date 

of this AD, all repetitive inspections and corrective actions must be 

accomplished in accordance with the instructions of Airbus SB A300-57-

6037 Revision 04.

Ref. Publications: Airbus SB A300-57-6037 Original issue dated 01 August 1994, or Revision 1 

dated 31 August 1995, or Revision 2 dated 9 January 2001, or Revision 3 

dated 11 January 2002, or Revision 4 dated 24 February 2011.

Airbus SB A300-57-6039 Original issue dated 01 August 1994, or Revision 1 

dated 26 October 2011.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.
EASA AD No.: 2012-0138

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Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 14 May 2012 as PAD 12-044 for consultation until 

11 June 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.