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 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 operate 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]. 

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 supersedes 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, A300B4-103, A300B4-120, A300B4-203, A300C4-203 

and A300F4-203 aeroplanes, all serial numbers, if modified preventively inservice (without crack finding) in accordance with Airbus Service Bulletin (SB) 

A300-53-0297 (Airbus Modification (Mod.)10453), at any revision. 

AIRBUS A300B4-601, A300B4-603, A300B4-605R, A300B4-620, A300B4-622, 

A300B4-622R and A300C4-620 aeroplanes, all serial numbers, if modified 

preventively in-service (without crack finding) 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 action (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 found 
EASA 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, this 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 corrective action. Passing the EC or liquid 

penetrant inspection constitutes terminating 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 instructions 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 exceeding 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 effective 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 inspections 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 substantiated, EASA can approve Alternative 

Methods of Compliance for this AD. 

2. The required actions and the risk allowance 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 technical 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).