EASA AD No: 2011-0163

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0163

Date: 30 August 2011

Note: This Airworthiness Directive (AD) is i ssued 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 opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agenc y [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]. 

### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :
A300 and A300-600 aeroplanes

TCDS Number: France N° 145

Foreign AD: Not applicable
Supersedure: This AD super sedes EASA AD 2009-0094 dated 21 April 2009, including the Correction dated 29 May 2009.



### ATA 53, 57 Fuselage / Wings – Frame 40 Forward Fitting between Stringers 32 and 33 – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: AIRBUS A300B4-2C, A300B4-1 03, A300B4-120, A300B4-203, A300C4-203and A300F4-203 aeroplanes, all serial numbers, if modified preventively inservice (without crack finding) in accord ance with Airbus Service Bulletin (SB) A300-53-0297 (Airbus Modification (M od.)10453), at any revision. AIRBUS A300B4-601, A300B4-603, A300 B4-605R, A300B4-620, A300B4-622, A300B4-622R and A300C4-620 aeroplanes, all serial numbers, if modified preventively in-service (without crack fi nding) in accordance with Airbus SB A300-57-6053 (Mod.10453), at any revision. Note: This AD does not apply to aeroplanes having incorporated Airbus SB A300-53-0297 or SB A300-57-6053 (Mod. 10453 ) at any revision, as applicable to aeroplane model, as a corrective ac tion (repair following crack finding).

Reason: One A300-600 aeroplane operator reported that, during a routine inspection, a crack was found in the right hand frame (FR) 40 forward fitting between stringer 32 and stringer 33. The subject aeroplane had previously been modified in accordance with Airbus SB A300-57-6053 (Mod. 10453). Therefore and pending completion of the full analysis using a refined Finite Element Model, EASA issued AD 2009- 0094 to require a one-time Detailed Visual Inspection (DVI) of the post- SB A300-57-6053 A300-600 aeroplanes and post-SB A300-53-0297 A300 aeroplanes in order to ensure the structural integrity of frame 40. During a recent maintenance check, on two aeroplanes (one A300B4 and one A300-600), cracks were found in the FR 40 forward fitting. These new crack findings are considered as unexpected, since they were foundEASA AD No: 2011-0163

EASA Form 110 Page 2/2 after: - application of modification SB A300-57-6053 or SB A300-53-0297 which

cancels the inspection programme, and - accomplishment of EASA AD 2009-0094. For the reasons described above, th is new AD, which supersedes EASA AD 2009-0094, requires repetitive DVI of the FR 40 forward fitting (without nut removal), accomplishment of a one time Eddy Current (EC) inspection or liquid penetrant inspection of this area (with nut removal) and, depending on findings, the accomplishment of associated corr ective action. Passing the EC or liquid penetrant inspection constitutes termin ating action for the repetitive DVI.

Effective Date: 13 September 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Repetitive Detailed Visual Inspections: (1) Within 300 flight cycles (FC) after the effective date of this AD, perform a DVI of the forward fitting at FR 40 without nut removal on both sides of the aeroplane, in accordance with the instru ctions of Airbus All Operator Telex (AOT) A300-53A0391 original issue, or Airbus AOT A300-57A6111 original issue, as applicable to the aeroplane model. (2) Thereafter, at intervals not exceed ing 300 FC, repeat the DVI as required by paragraph (1) of this AD. One Time Non Destructive Test (NDT): (3) Within 36 months from the effect ive date of this AD, perform an EC inspection or a liquid penetrant inspection of the forward fitting at FR 40 with nut removal on both sides of the aeroplane, in accordance with the instructions of Airbus AOT A300-53A0391 original issue, or Airbus AOT A300-57A6111 original issue, as applicable to the aeroplane model. (4) If, during any inspection as required by paragraphs (1), (2) or (3) of this AD, discrepancies are detected, before next flight, contact Airbus to get approved repair instructions and accomplish those instructions accordingly. (5) Within 30 days after each inspection as required by this AD, report the results, including no findings, to Airbus. (6) Accomplishment of the one time NDT inspection as required by paragraph (3) of this AD, including corrective action(s), depending on findings, constitutes termination action for the in spections as required by paragraphs (1) and (2) of this AD.
Ref. Publications: Airbus AOT A300-53A0391 original issue dated 09 August 2011. Airbus AOT A300-57A6111 original issue dated 09 August 2011. The use of later approved revisions of these documents is acceptable for compliance with requirements of this AD.

Remarks : 1. If requested and appropriately subs tantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The required actions and the risk a llowance have granted the issuance of a Final AD with Request for Comments, postponing the public consultation process after publication. 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 tec hnical content of the requirements in this AD, please contact: AIRBUS SAS – EAW (Airworthiness Office, Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).