EASA AD No.: 2015-0217

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Airworthiness Directive

AD No.: 2015-0217

Issued: 30 October 2015

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

(EC) 216/2008 on behalf of the European Union, 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 Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 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 [Regulation (EU) 1321/2014 Annex I,

Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EC) 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A300-600 aeroplanes

Effective Date: 13 November 2015

TCDS Number(s): EASA.A.0172

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2012-0103 dated 11 June 2012.

ATA 53 – Fuselage – Frame Base Fitting between Frames 41 and 46 – Inspection / 

Repair

Manufacturer(s):

Airbus (formerly Airbus Industrie)

Applicability:

Airbus A300 B4-603, A300 B4-605R, A300 B4-620, A300 B4-622, 

A300 B4-622R, A300 C4-605R variant F, A300 C4-620, A300 F4-605R, and A300 F4-622R aeroplanes, 

all manufacturer serial numbers.

Reason:

During accomplishment of Airbus Service Bulletin (SB) A300-53-6111 (EASA AD 2012-0103), 

addressing detailed visual inspections of the lower frame fittings between Frame (FR) 41 and FR46, 

a crack was detected on one A300-600 aeroplane in the area 2 of the foot of FR46 at junction radius 

level.

This frame, previously repaired due to a crack finding in the frame foot area 1, was not due to be 

inspected before reaching the post-repair inspection threshold, i.e. 45 400 flight cycles since repair 

embodiment.
EASA AD No.: 2015-0217

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Further investigation determined that the repairs specified in Airbus SB A300-53-6111 were of 

limited effect to prevent cracking in the frame foot area 2.

This condition, if not detected and corrected, could reduce the integrity of the affected structure.

As a temporary action and until an improvement of the existing repairs was made available, EASA 

issued AD 2012-0229 to require a one-time detailed inspection (DET) of the frame feet that were 

repaired in accordance with Airbus SB A300-53-6111, and the reporting of findings to Airbus.

Since that AD was issued, a detailed study was performed resulting in the development of a new 

inspection programme.

Consequently, Airbus cancelled SB A300-53-6111 and replaced it with SB A300-53-6177, introducing 

repetitive DET of the lower frame fittings between FR41 and FR46 for the entire fleet. 

In addition to this new inspection programme, Airbus designed a new frame foot which can be 

installed on aeroplanes through Airbus SB A300-53-6176.

For the reasons described above, this AD supersedes EASA AD 2012-0103, not retaining its 

requirements, and instead requires the new inspection programme for the lower frame fittings. 

This AD also introduces an optional terminating action for the repetitive inspections required by 

this AD.

Required Action(s) and Compliance Time(s):

Required as indicated, unless accomplished previously:

(1) Within the applicable compliance time (threshold and intervals) as defined in Paragraph 1.E. (2) 

of Airbus SB A300-53-6177, accomplish repetitive DET in accordance with the instructions of Airbus 

SB A300-53-6177.

(2) If, during any DET as required by paragraph (1) of this AD, any crack is found, before next flight, 

accomplish the applicable corrective action(s) in accordance with the instructions of Airbus SB 

A300-53-6177.

(3) Within 30 days after each DET, report the inspection results, including no findings, to Airbus.

(4) Modification of an aeroplane in accordance with the instructions of Airbus SB A300-53-6176 

constitutes terminating action for the repetitive DET as required by paragraph (1) of this AD for that 

aeroplane.

Ref. Publications:

Airbus SB A300-53-6177 original issue dated 20 May 2015.

Airbus SB A300-53-6176 original issue dated 20 May 2015.

The use of later approved revisions of these documents is acceptable for compliance with the 

requirements of this AD.
EASA AD No.: 2015-0217

TE.CAP.00110-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified.

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

An agency of the European Union

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Remarks:

1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance 

for this AD.

2. This AD was posted on 25 August 2015 as PAD 15-109 for consultation until 22 September 2015.

The Comment Response Document can be found at http://ad.easa.europa.eu.

3. Enquiries regarding this AD should be referred to the EASA Safety Information Section, Certification 

Directorate. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical content of the requirements in this AD, please contact:

AIRBUS – EIAW (Airworthiness Office) 

E-mail: continued.airworthiness-wb.external@airbus.com.