EASA AD No.: 2012

- 0103

CAP.00110

- 001 © 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

. : 2012

- 0103 [Correction: 1 9 June 2012]

Date: 11 June 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 ope rate an aircraft to which an AD applies, except in accordance wi th 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) :

A30 0

- 600 aeroplanes

TCDS Number: France N° 145

F oreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage

– Frame Base Fitting between Frames 41 and 46

– Inspection / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300B4

- 603, A300B4

- 605R, A300B4

- 620, A300B4

- 622, A300B4

- 622R and A300C4

- 605R/F, A300C4

- 620, A300F4

- 605R and A300F4

- 622R aeroplane s , all serial numbers.

Reason: During maintenance checks, cracks were discovered by A300 and A300

- 600 operators in the frame feet fittings, connecting the frame lower positions to the centre wing box. These occurrences were followed by a dedicated sampling inspection programme carried out by Airbus. During this sampling programme, 22 A300

- 600 aeroplanes we re found with cracks on the lower fittings of frame 44 to frame 46 left hand (LH) and right hand (RH) side.
This condition, if not detected and corrected, could affect the structural integrity of the fuselage of all aeroplane s operated up to the extended service goal (ESG).
For the reasons described above, this AD requires repetitive detailed visual inspections of the lower frame fittings between frame 41 and frame 46 and, depending on findings, accomplishment of a repair.
This AD has been republished to correct Note 2 in Appendix 1.

Effective Date: 25 June 2012EASA AD No.: 2012

- 0103

CAP.00110

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

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless previously accomplished: (1) Initially, within the compliance time specified in Appendix 1 of this AD, as applicable, perform a detailed visual inspection (DVI) of the base fitting of LH and RH frames 41 to 46 of the fuselage in accordance with the instructions of Airbus Service Bulletin (SB) A300

- 53

- 6111 Revision 04. (2) Thereafter, at the intervals specified in the plan ning information paragraph 1.E (2) of A irbus SB A300

- 53

- 6111 Revision 0 4, repeat the DVI as specified in paragraph (1) of this AD.
(3) If, during any DVI as required by paragraph (1) or (2) of this AD, discrepancies are detected, within the compliance time specified in Airbus SB A300

- 53

- 6111 Revision 04, as applicable, and in accordance with the instructions of Airbus SB A300

- 53

- 6111 Revision 04, accomplish the applicable corrective action(s).
(4) Within 30 days after an y inspection as required by this AD w here discrepancies are detected , report all inspection results to Airbus.
(5) Accomplishment of corrective action(s) as required by paragraph (3) of this AD does not constitute terminating action for the repetitive inspections required by paragraph (2) of this AD.

Ref. Public ations: Airbus SB A300

- 5 3

- 6 111 Revision 04 dated 25 August 2011.
The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD.
Airbus Repair Instructions R53810322

, R53810323

, R 53 810329

, R53810330

, R53810331 and R53810332.

Remarks: 1. If requested and appropriately substantiated

, EASA can approve Alternative Methods of Compliance for this AD.

2. This AD was posted on 10 April 2012 as PAD 12

- 028 for consultation until 08 May 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 conte nt of the requirements in this AD, please contact: AIRBUS SAS

– EIAW (Airworthiness Office, Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).EASA AD No.: 2012

- 0103

CAP.00110

- 001 © 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 1: For the purpose of this AD, the Average Flight Time (AFT) is defined as a computation of the number of flight hours (FH) divided by the number of flight cycles (FC) accumulated since last inspection, or since aeroplane first flight, as applicable.

Frame configuration and aeroplane utilization C ompliance time

, A or B

, whichever occurs later

A B

Frame(s) without any repair accomplished Aeroplanes operated with AFT more than 1,5 h ours Within 5 000 f light c ycles (FC) or 10 800 f light h ours (FH)

, whichever occurs first since aeroplane first flight

1 000 FC after the effective date of this AD Aeroplanes operated with AFT equal to or less than 1,5 Hours Within 5 400 FC or 8 100 FH

, whichever occurs first since aeroplane first flight

Frame(s) with repair accomplished (see Note 2) Aeroplanes operated with AFT more than 1,5 Hours Within 45 400 FC or 98 000 FH

, whichever occurs first since frame repair embodiment
Aeroplanes operated with AFT equal to or less than 1,5 Hours Within 49 000 FC or 73 500 FH

, whichever occurs first since frame repair embodiment

Note 2: Affected repairs are R53810322

, R53810323, R53810329, R53810330, R53810331 and R53810332 , as well as repairs accomplished in accordance with Airbus SB A300

- 5 3

- 6 111 (at any revision).