EASA AD No.: 2014-0119

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0119

Date: 13 May 2014

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

Supersedure: This AD supersedes DGAC France AD 94-069-158(B) dated 09 April 1994.

ATA 57 Wings – Wing Bottom Skin Adjacent To The Aft Pylon Attachment 

Fitting – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300B4-601, A300B4-603, A300B4-605R, A300B4-620, A300B4-622, 

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

A300F4-622R aeroplanes, all manufacturer serial numbers.

Reason: Full-scale fatigue tests carried out on the A300-600 test specimen by Airbus

revealed crack initiation in the bottom skin adjacent to the aft pylon attachment 

fitting.

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

of the aeroplane.

To address this unsafe condition, DGAC France issued AD 94-069-158(B) to

require repetitive detailed visual inspections (DVI) of the wing bottom skin in the 

area of the cut-out for the pylon rear attachment fitting on Left Hand (LH) and 

Right Hand (RH) wings.

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

Tolerance analyses have been performed in order to substantiate the second 

A300-600 Extended Service Goal (ESG2) exercise. As a result, it was revealed 

that the inspection threshold and interval must be reduced to allow timely 

detection of cracks and the accomplishment of an applicable corrective action.

Prompted by these findings, Airbus issued Revision 07 of Service Bulletin (SB) 

A300-57-6028.

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

France AD 94-069-158(B), which is superseded, but reduces the inspection 

thresholds and intervals.
EASA AD No.: 2014-0119

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Effective Date: 27 May 2014

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance times (threshold and intervals) indicated in Table 1 

or Table 2 of Appendix 1 of this AD, as applicable to the aeroplane model 

and aeroplane utilization, accomplish repetitive DVI of the wing bottom skin 

in the area of the cut-out for the pylon rear attachment fitting on LH and RH 

wings in accordance with the instructions of Airbus SB A300-57-6028 

Revision 07.

Note: For the purpose of this AD, the Average Flight Time shall be established 

as follows for the determination of: 

- The inspection threshold (TH), as the total accumulated flight hours (FH), 

counted from take-off to touch-down, divided by the total accumulated flight 

cycles (FC) at the effective date of this AD. 

- The first inspection interval (INT), as the total accumulated FH divided by the 

total accumulated FC at the time of the TH inspection. 

- The second inspection INT onwards, as the FH divided by the FC 

accumulated between the last two inspections.

(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-

57-6028 Revision 07.

(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 A300-57-6028 

at original issue up to Revision 06, are acceptable to comply with the initial 

requirements of paragraphs (1) and (2) of this AD. 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 A300-57-6028 Revision 07.

Ref. Publications: Airbus SB A300-57-6028 Revision 07 dated 06 June 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. This AD was posted on 14 September 2012 as PAD 12-119 for consultation 

until 12 October 2012. The Comment Response Document can be found at 

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

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), 

Email: continued.airworthiness-wb.external@airbus.com.
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Appendix 1

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 1: Inspection Threshold and Interval for Normal Range Operations

Aeroplane models Compliance time 

(whichever occurs later between A and B) Interval (whichever 

occurs first)

A (whichever occurs first) B (whichever occurs first)

A300F4-605R and 

A300F4-622R

24 000 Flight Cycles (FC) 

or 51 800 Flight Hours 

(FH) since aeroplane first 

flight

2 000 FC or 4 300 FH 

after the effective date of 

this AD

9 000 FC or 19 400 FH

A300B4-600 and 

A300C4-600 series 

19 100 FC or 41 200 FH 

since aeroplane first flight

1 500 FC or 3 200 FH 

after the effective date of 

this AD

7 100 FC or 15 300 FH

Table 2: Inspection Threshold and Interval for Short Range Operations

Aeroplane models Compliance time 

(whichever occurs later between A and B) Interval (whichever 

occurs first)

A (whichever occurs first) B (whichever occurs first)

A300F4-605R and 

A300F4-622R

25 900 FC or 38 800 FH

since aeroplane first flight

2 100 FC or 3 200 FH 

after the effective date of 

this AD

9 700 FC or 14 500 FH

A300B4-600 and 

A300C4-600 series 

20 600 FC or 30 900 FH 

since aeroplane first flight

1 600 FC or 2 400 FH 

after the effective date of 

this AD

7 600 FC or 11 500 FH