EASA AD No.: 2013-0286

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0286

Date: 04 December 2013

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 EU 748/2012, Part 21.A.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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A300-600 and A300-600ST aeroplanes

TCDS Numbers: France No. 145, EASA.A.014

Foreign AD: Not applicable

Supersedure: None

ATA 54 Nacelles and Pylons – Rib 5 Lower Area – Inspection / 

Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300-600 aeroplanes, all certified models, all Manufacturer Serial 

Numbers (MSN), except those on which Airbus modification 11110 has been 

embodied in production, or which have been modified in service in accordance 

with the instructions of Airbus Service Bulletin (SB) A300-54-6031.

Airbus A300F4-608ST aeroplanes, MSN 0655, 0751 and 0765.

Reason: Cracks were found on the lower side of rib 5 in the pylon box on A300 

aeroplanes powered with General Electric engines.

Investigations revealed that these cracks were due to the stresses resulting 

from the pressure applied by the thrust reverser cowl bumpers.

This condition, if not detected and corrected, could affect the structural integrity 

of the aeroplane.

Airbus developed an inspection programme to detect the cracks and associated

actions to correct them.

For the reasons described above, this AD requires repetitive inspections of the 

pylon rib 5 on the left hand side (LH) and right hand (RH) side and, when

cracks are detected, replacement of the affected structural part(s).

Effective Date: 18 December 2013
EASA AD No.: 2013-0286

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Before accumulating 15 000 flight hours (FH) since aeroplane first flight,

or within 6 000 FH after the effective date of this AD, whichever occurs 

later, and, thereafter, at intervals not to exceed 15 000 FH, accomplish a 

High Frequency Eddy Current (HFEC) inspection on the lower area of rib 

5 on the LH side and RH side pylon in accordance with the instructions of 

Airbus SB A300-54-6034 Revision 02, or Airbus SB A300-54-9005, as 

applicable to aeroplane model.

(2) If, during any inspection as required by paragraph (1) of this AD, any 

crack is found, for A300-600 aeroplanes, within 250 FH, replace all the 

fittings with new standard fittings in accordance with the instructions of 

Airbus SB A300-54-6031 or, for A300F4-608ST aeroplanes, before next 

flight, contact Airbus for approved instructions and accomplish those 

instructions accordingly.

(3) Replacement of all the fittings on an aeroplane as required by paragraph 

(2) of this AD, or voluntary modification of an A300-600 aeroplane in 

accordance with the instructions of Airbus SB A300-54-6031, constitutes 

terminating action for the repetitive HFEC inspections required by 

paragraph (1) of this AD for that aeroplane.

(4) Inspections, accomplished before the effective date of this AD in 

accordance with the instructions of Airbus SB A300-54-6034 at Revision 

01 or original issue, are acceptable to comply with the initial requirements 

of paragraph (1) of this AD.

Ref. Publications: Airbus SB A300-54-6031 original issue dated 30 May 1996.

Airbus SB A300-54-6034 Revision 02 dated 26 August 2013.

Airbus SB A300-54-9005 original issue dated 26 June 2013.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 24 October 2013 as PAD 13-160 for consultation 

until 21 November 2013. No comments were received during the 

consultation period.

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 – EIAW (Airworthiness Office)

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