EASA AD No.: 2014

- 0119

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 201 4
- 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 Europ ean 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 a ircraft 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 Age ncy [EC 2042/2003 Annex I, Par t 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:
A IRBUS Type/Model designation(s):
A300

- 600 aeroplanes

TCDS Number: France No.145

F oreign AD: Not applicable
Supers edure: 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 ( f orme r ly Airbus Industrie)
Applicability: Airbus A300B4

- 60 1, A300B4

- 6 03, A300B4

- 605R, A300B4

- 620, A300B4

- 622, A300B4

- 622R, A300C4

- 605R/F, A300C4

- 620 , A300F4

- 605R and A300F4

- 622R aeroplanes, all manufacturer serial numbers

. Reason: F ull

- scale fatigue tests carried out on the A300

- 600 test specimen by Airbus revea led 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 inspection s (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 a nd Damage Tolerance analyse s have been performed in order to substantiate the second A300

- 600 Extended Service Goal (ESG2) exerci se. 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 issu ed Revision 0 7 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)
, whic h is superseded, but red uces the inspection t hresholds and intervals.EASA AD No.: 2014

- 0119

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Effective Date: 27 May 2014
Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) W ithin the compliance time s (threshold and intervals) ind icated 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), counte d 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 befor e the effective date of this AD in accordance with the instructions of Airbus SB A30 0

- 57

- 6028 at original issue up to Revision 06 , are acceptable to compl y with the initial requirements of paragraph s (1) and (2) of this AD

. After the effective date of this AD, repetitive inspection s and, depending on findings , corrective actions must be accomplished in accordance with t he instructions of Airbus SB A30 0

- 57

- 6028 Revision 07.

Ref. Public ati ons: 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 Alterna tive Methods of Compliance for this AD.
2. This AD was posted on 14 September 2012 as PAD 12

- 1 19 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 (Airworth iness Office), Email: continued.airworthiness

- wb.external@airbus.com

.EASA AD No.: 2014

- 0119

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 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 O perations
Aeroplane models Compliance time ( whichever occurs later between A and B) Inter val ( 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 0 00 FC or 4 3 00 FH after the effective date of this AD 9 000 FC or 19 4 00 FH

A300B4

- 600 and A300C4

- 600 series 19 100 FC or 41 200 FH since aeroplane first flight 1 5 00 FC or 3 2 00 FH after the effective date of this AD 7 100 FC or 15 3 00 FH

Table 2 : Inspection Threshold and Interval for Short Range O perat ions
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 1 0 0 FC or 3 2 00 FH after the effective date of this AD 9 700 FC or 14 5 00 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