E ASA AD No.: 20 13

- 0286

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 13 - 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 ope rate an aircraft to which an AD applies, except in accordance with the requ irements 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

- 60 0 ST aeroplanes

TCDS Number s : France No

. 145, EASA.A.014

F oreign AD: Not applicable
Supersedure: None



### ATA 54 Nacelles and Pylon s – Rib 5 L ower A rea – Inspection / Replacement

Manufacturer(s): Airbus ( f ormerly Airbus Industrie ) Applicability: Airbus A300

- 600 aeroplanes, all certified m odels, 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 A300 F4

- 60 8 ST 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 program me to detect the cracks and associated actions to correct them. For the reasons described above, this AD requires repetitive inspection s 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 2013E ASA AD No.: 20 13

- 0286

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 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 accomplished previously: (1) Before accumulating 15 000 f light h ours (FH) since aeroplane first flight , or within 6 000 FH after the effective date of this AD, whichever occurs later , and , t hereafter, at interval s no t to exceed 15 000 FH , accomplish a High Frequency Eddy Current (HFEC) inspection on the lower area of rib 5 on th e 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 th os e instructions accordingly. ( 3 ) R eplacement 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

- 603 1, constitutes terminating action for the repetitive HFEC inspection s 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 0 1 or original issue , are acceptable to compl y with the initial requirements of paragraph (1) of this AD.
Ref. Public ations: Airbus SB A300

- 54

- 6031 original issue dated 30 May 1996

. Airbus SB A300

- 54

- 6034 R evision 02 dated 26 August 2013

. Airbus SB A300

- 54

- 900 5 original issue dated 26 June 2013

. The u se 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 conte nt of the requirements in this AD, please contact: AIRBUS SAS

– E IAW (Airworthiness Office) E

- mail: continued.airworthiness

- wb.external@airbus.com



### .