EASA AD No.: 20 12

- 0 1 9 4

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

. : 20 12 - 0 1 9 4

Date: 2 5 September 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 i ssued in accordance with EC 748/2012 , Part 21

. A.3B. In accordan ce 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 ope rate 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 : A IRBUS Type/Model designation(s) : A300

- 600 aeroplanes

TCDS Number: France No.145

F oreign AD: Not applicable
Supersedure: This AD supersedes DGAC France AD 2003

- 29 0(B) R1 dated 01 October 2003.



### ATA 57 Wings

– Centre Spar Sealing Angles A djacent to Pylon Rear

Attachment F ittings

– Inspection / Repair

Manufacturer(s): Airbus ( f orme r ly Airbus Industrie) Applicability: Airbus A300

- 600 aeroplanes, all certified models, all manufacturer serial numbers, except aeroplanes on which Airbus modification (Mod) 8608 has been embodied in production.
Reason: Fatigue testing applied to a test airframe confirmed the initiation of cracks on the sealing angles of the centre spar, adjacent to rib 8, which could lead to the rupture of the sealing angles and the subsequent crack initiation in the bottom skin of the wing. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this unsafe condition, DGAC France issued AD 91

- 253

- 128(B) to require inspection of centre spar sealing angles adjac ent to pylon rear attachment fittings of Left Hand (LH) and Right Hand (RH) wings. Early cracks reported on an in

- service aeroplane prompted Airbus to conduct additional investigations. Based on the results, DGAC France issued AD 2003

- 290 ( later revised), which superseded DGAC France AD 91

- 253

- 128(B) , to require modification of the affected aeroplanes as specified in Airbus Service Bulletin (SB) A300

- 57

- 6033 (Airbus Mod 8609) , as well as post

- modification repetitive inspections

. Since DGAC France AD 2003

- 29 0(B)R1 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)EASA AD No.: 20 12

- 0 1 9 4

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. exercise. The results of these analyses have shown that the inspection thresho ld and interval must be reduced to allow timely detection of cracks on the sealing angles of the centre spar, adjacent to rib 8. For the reasons described above, this new AD retains the requirements of DGAC France AD 2003

- 290(B) R1, which is superseded, and requires the accomplishment instructions at the new thresholds and intervals given by Revision 07 of Airbus Service Bulletin (SB) A300

- 57

- 6027.
Effec tive Date: 09 October 2012 Required A ction(s) and Compliance Time(s) : Required as indicated, unless previously accomplished: (1) Within the compliance time indicated in Table 1 or Table 2 of Airbus SB A300

- 57

- 6027 Revision 7 , as applicable to the aeroplane configuration and aeroplane utilization, accomplish the following actions concurrently : (1.1) Do a High Frequency Eddy Current (HFEC) inspection of the centre spar sealing angles adjacent to the pylon rear attachment fittin g in accordance with the instructions of Airbus SB A300

- 57

- 6027 Revision 07, and (1.2) Unless already accomplished, modify the aeroplane by cold expansion of the centre spar sealing angles outboard of Rib 8 adjacent to the pylon rear attachment fitting in accordance with the instructions of Airbus SB A300

- 57

- 6033 Revision 02

. (1.3) Aeroplanes that have already been modified, before the effective date of this AD, in accordance with the instructions of Airbus SB A300

- 57

- 6033 at original issue or Revision 01 are compliant with the requirement of paragraph (1.2) of this AD. (2) Thereafter, repeat the HFEC inspection as required by paragraph (1.1) of this AD at intervals not to exceed the values defined in Table 1 or Table 2 of Airbus SB A300

- 57

- 6027 Revision 7, as applicable to the aeroplane configuration and aeroplane utilization. (3) If, during any inspection as required by paragraph (1.1) or (2) of this AD, discrepancies are detected, before next flight, accomplish the applicable corrective actions in accordance with the instructions of Airbus SB A300

- 57

- 6027 Revision 07

. (4) Corrective actions, as required by paragraph (3) of this AD, do not constitute terminating action for the repetitive inspections as required by paragraph (2) of this AD. (5) Inspections and corrective actions , accomplished before the effective date of this AD in accordance with Airbus SB A300

- 57

- 6027 at original issue up to Revision 06 , are acceptable to comply with the initial requirements of paragraphs (1.1) and (2) of this AD (initial and repetitive inspection s ). After the effective date of this AD, repetitive inspections and corrective actions must be accomplished in accordance with the instructions of Airbus SB A300

- 57

- 6027 at Revision 07. (6) After modification of an aeroplane in accordance with the instructions of Airbus Repair R571 50404, within 3 months after the effective date of this AD, or after modification, whichever occurs later, contact Airbus in order to get appro ved instructions for post

- repair repetitive inspections and corrective actions and , thereafter, within the intervals and compliance time(s) specified, accomplish th ose instructions accordingly

. Ref. Public ations: Airbus SB A300

- 57

- 6033 original issue date d 31 March 1993 , Revision 01 dated 18 December 2003 , or Revision 02 dated 19 September 2011. Airbus SB A300

- 57

- 6027 Revision 07 dated 06 June 2011. The use of later approved revisions of these documents is acceptable forEASA AD No.: 20 12

- 0 1 9 4

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. compliance with the requirements of this AD. Airbus Repair R571 50404

. Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 24 August 2012 as PAD 12

- 114 for consultation until 21 September 2012

. No comments were received during the consultation period

. 3. Enquiries regarding this A D 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.