EASA AD No.: 2012-0092

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 1/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0092 [Correction: 04 June 2012]

Date: 25 May 2012

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, 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 F-20 04-159 (EASA approval 2004-9779)

dated 29 September 2004.



### ATA 57 Wings – Center Wing Box Frame 47 Angle Fittings – I nspection /

Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300B4-603, A300B4-620, A300B 4-605R, A300B4-622, A300B4-622R, A300C4-605R/F, A300C4-620 and A300F4-605R aeroplane s, all serial numbers, except for aeroplanes on which AIRBUS modi fication No. 12171 or No. 12249 has been embodied in production, or on wh ich Airbus Service Bulletin (SB) A300-57-6069 has been embodied in ser vice.

Reason: Prompted by cracks found on the Frame 47 an gle fitting, DGAC France published AD 2000-533-328 to require repetitive ins pection programme for fuselage frame 47. If not detected and corrected, t hese cracks could affect the structural integrity of the Centre Wing Box (CWB) o f the aeroplane. Subsequent to the publication of a new repetitive i nspection programme for fuselage frame 47 at certain fasteners of the CWB a ngle fitting, DGAC France issued AD F-2004-159, superseding AD 2000-533-328.
After DGAC France AD F-2004-159 was issued, cracks were reportedly found on the horizontal flange of the Frame 47 internal c orner angle fitting during accomplishment of routine maintenance structural in spection and modification in accordance with Airbus SB A300-57-6050. Prompted by these findings, Airbus reviewed and ame nded the inspection programme for the internal lower angle fitting flan ge (horizontal face). The inspection programme for the lower angle fitting we b (vertical face) related to SB A300-57-6049 and internal lower angle fitting mo dification programme related to SB A300-57-6050 remain unchanged.EASA AD No.: 2012-0092

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 2/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. For the reasons explained above, this new AD retain s the requirements of DGAC France AD F-2004-159, which is superseded, and requires additional repetitive inspections of the CWB lower panel throu gh the ultrasonic method and, depending on findings, re-installation of remo ved fasteners in transition fit instead of interference.
This AD has been republished to correct a typograph ical error in paragraph (1.1).

Effective Date: 08 June 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: Re-statement of requirements of DGAC France F-2004- 159: (1) Inspection programme for the internal lower ang le fitting web (vertical face)
(1.1) At the threshold and in accordance with the A ccomplishment Instructions defined in Airbus SB A300-57-6049 Revi sion 7, perform an inspection of holes H, I, K, L, M, N, U, V, W, X and Y, and of the rear spar and bottom panel at junction with the fus elage. (1.2) According to the results of the previous insp ection and the corrective actions undertaken, thereafter, at intervals define d in Airbus SB A300-57-6049 Revision 7, repeat the inspection in a ccordance with the Accomplishment Instructions of Airbus SB A300-5 7-6049 Revision 7. (2) Inspection programme for the internal lower ang le fitting flange (horizontal face): (2.1) At the threshold defined in Airbus SB A300-57 -6086 or within 1 500 flight cycles (FC) after 06 January 2001 [the effec tive date of AD 2000-533-328], whichever occurs later, perform an i nspection of the holes A, B, C, D, E, F, G, P,Q, S and T (adjacent t o the hole G) at the LH and RH internal angle of the CWB in accordan ce with the Accomplishment Instructions defined in Airbus SB A3 00-57-6086. Aeroplanes which had exceeded the predefined thres hold value by more than 2 000 FC on 06 January 2001 [the effectiv e date of AD 2000-533-328] must have been inspected within 750 F C following 06 January 2001. (2.2) According to the results of the previous insp ection and the corrective actions undertaken, thereafter, at intervals define d in Airbus SB A300-57-6086 , repeat the inspection in accordance with the Accomplishment Instructions of Airbus SB A300-57-60 86. (3) Internal lower angle fitting modification progr amme: (3.1) Within 15 100 FC or 38 900 flight hours (FH) accumulated since the aeroplane first flight, whichever occurs first, mod ify the angle fitting attachment holes by cold expansion in accordance wi th the Accomplishment Instructions of Airbus SB A300-57-60 50 Revision 3

. (3.2) Aeroplanes which were near to, or which had e xceeded, the predefined value on 06 January 2001 [the effective date of AD 2000- 533-328], must have been modified within the grace periods defined in paragraphs 1.B.(4).(a) and (b) of SB A300-57-605 0 Revision 3 (the effective date of AD 2000-533-328 being then t aken as reference).

New requirements of this AD: (4) Inspection programme for the aft bottom panel:EASA AD No.: 2012-0092

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 3/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. (4.1) As per SB A300-57-6086 Revision 5, the CONF 0 01 is valid for aeroplanes on which SB A300-57-6050 is not embodied or on which Mod. No. 10155 (Serial Solution) is embodied. Within 13 400 FC or 34 600 FH from the first fligh t of the aeroplane, whichever occurs first, or

within 650 FC or 8 months whichever occurs first a fter the effective date of this AD, for those aeroplanes that have alr eady exceeded 13 400 FC or 34 600 FH from the first flight of the aeroplane, perform an ultrasonic inspection of the LH and RH aft bottom panel of the CWB in accordance with the Accomplishment In structions of Airbus SB A300-57-6086 Revision 05. (4.2) As per SB A300-57-6086 Revision 5, the CONF 0 02 is valid for aircraft on which SB A300-57-6050 is embodied. Within 13 400 FC or 34 600 FH following embodiment of Airbus SB A300-57-6050 (at any revision), whichever occurs fi rst, or
within 650 FC or 8 months, whichever occurs first after the effective date of this AD, for those aeroplanes that have alr eady exceeded 13 400 FC or 34 600 FH from embodiment of Airbus SB A300-57- 6050 (at any revision),
perform an ultrasonic inspection of the LH and RH aft bottom panel of the CWB, in accordance with the Accomplishment I nstructions of Airbus SB A300-57-6086 Revision 05.
(4.3) Thereafter, at intervals defined in Table 1 o f this AD and depending on the value of the Average Flight Time (AFT) which must be determined by the operator, repeat the ultrasonic i nspection, in accordance with the Accomplishment Instructions of Airbus SB A300-57-6086 Revision 05.

Table 1 - Ultrasonic Inspection

Average Flight Time (AFT) Interval, whichever occur s first

AFT > 1.5 FH/FC 1 260 FC or 2 720 FH

AFT < 1.5 FH/FC 1 360 FC or 2 200 FH

(4.4) Depending on the results of each inspection a s required by paragraph (4.1), (4.2) or (4.3) of this AD, as appl icable, before next flight, contact Airbus for the required corrective actions and apply them accordingly. (5) Within 30 days after each inspection as require d by paragraph (4) of this AD, report all inspection results (including no fin ding) to AIRBUS. For that purpose, the Inspection report of SB A300-57-6086 R evision 05 may be used. (6) Accomplishment of corrective action(s) as requi red by paragraph (4.4) of this AD does not constitute terminating action for the repetitive inspections required by paragraph (4.3) of this AD.

Ref. Publications: Airbus SB A300-57-6049 Revision 7 dated 22 December 2006. Airbus SB A300-57-6050 Revision 3 dated 31 May 2001

. Airbus SB A300-57-6086 Revision 5 dated 30 January 2012. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approveEASA AD No.: 2012-0092

CAP.00110-001 © European Aviation Safety Agency. Al l rights reserved. 4/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Alternative Methods of Compliance for this AD.
2. This AD was posted on 28 March 2012 as PAD 12-02 4 for consultation until 25 April 2012. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical conten t of the requirements in this AD, please contact: AIRBUS SAS – EIAW (Airwort hiness Office, Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).