E ASA AD No.: 2013
- 0167

TE. CAP.0011 0

- 003 © 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 - 0167

Date: 26 July 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 Euro pean third countries that participate in the activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with E U 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, Pa rt 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, A310 and A300

- 600 aeroplanes
TCDS Number: France TCDS No 145 F oreign AD: Not applicable Supersedure: This AD supersedes DGAC France AD 199 3
- 228
- 1 54 (B) R 3 dated 0 2 June 1999 ,

and EASA AD 2008

- 000 1 dated 03 January 2008.



### ATA 54 Nacelles / Pylons
– Pylon Lower Spar between Ribs 6 and 7
– Inspection
Manufacturer(s): Airbus (for me r ly Airbus Industrie ) Applicability: A300, A300

- 600 and A310 aeroplanes , all certified models, all manufactur e r serial numbers , except aeroplanes on which Airbus modification 10149 has been embodied in production. Reason: Cracks were found between rib s 6 and 7 in the lower spar of engine pylon s on A310, A300 and A300

- 600 aeroplanes

. T o prevent crack initiation , a first inspection programme of this area was rendered mandatory by DGAC France AD 9 3
- 228
- 1 54 ( later revised, currently at Revision 3) for A300 and A300

- 600 aeroplanes

. At a l ater date and due to new findings , a specific inspection programme for A310 aeroplanes was rendered mandatory by DGAC France AD 1999
- 23 9
- 28 7 (B) . Th at AD was later superseded by EASA AD 2008

- 000 1 , which introduced new thresho lds and intervals in the frame of the A310 extended service goal (ESG) exercise. Since DGAC France AD 199 3
- 228
- 1 54 (B) R3 and EASA AD 2008

- 000 1 w ere issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to subs tantiate the second ESG for A300

- 600 , called ESG2 exercise. The results of these analyses have shown that the inspection threshold and interval must be reduced to allow timely detection of cracks in the engine pylon l ower s par between r ibs 6 and 7

. For the reasons described above, this new AD retains the requirements of DGAC France AD 1993

- 228
- 154(B) R3 and EASA AD 2008

- 0001 , which are superseded, and requires accomplishment of the inspections and, depending on findings, corrective actions, within the new th resholds and intervals specifiedE ASA AD No.: 2013
- 0167

TE. CAP.0011 0

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

- Internet/Intranet. in Airbus S ervice B ulletin (SB) A300

- 54
- 0073 Revision 03 or SB A310

- 54
- 2017 Revision 06 or SB A300

- 54
- 6014 Revision 0 7

. Effective Date: 09 August 2013 Required A ction(s) and Compliance Time(s) : Required as indicated, unle ss accomplished previously: (1) Before exceeding the threshold and, thereafter, within the intervals as defined in paragraph E. “Compliance” of Airbus SB A300

- 54
- 0073 Revision 03 , or SB A310

- 54
- 2017 Revision 06 , or SB A300

- 54
- 6014 Revision 0 7 , as applicabl e to the aeroplane configuration and utilization, accomplish an Eddy Current or liquid penetrant inspection of the pylon lower spar between r ibs 6 and 7 in accordance with the instructions of Airbus SB A300

- 54
- 0073 Revision 03 , or SB A310

- 54
- 2017 Revision 06 , or SB A300

- 54
- 6014 Revision 0 7 , as applicable to aeroplane model. (2) For an aeroplane which, on the effective date of this AD , ha s exceeded the applicable threshold and /or interval as specified in Airbus SB A300

- 54
- 0073 Revision 03 , or SB A310

- 54
- 2017 Revision 06 , or SB A300

- 54
- 6014 Revision 0 7 , as applicable to aeroplane model, the initial compliance time ( or G race P eriod ) must be determined as defined in Airbus SB A300

- 54
- 0073 Revision 03 , or SB A310

- 54
- 2017 Revision 06 , or SB A300

- 54
- 6014 Revision 0 7 , as applicable to aeroplane model, and must be counted from the effective date of this AD

. However this n ew compliance time must not exceed the compliance time as specified in the previous issue of each of th ese SB s
. (3) If, during any inspection as requ ired by paragraph (1) of this AD, cracks are detected, before next flight, accomplish the applicable corrective actions in accordance with the instructions of Airbus SB A300

- 54
- 0073 Revision 03 , or SB A310

- 54
- 2017 Revision 06 , or SB A300

- 54
- 6014 Revision 0 7 , as applicable to aeroplane model

. (4) Corrective actions, as required by paragraph ( 3 ) of this AD , do not constitute terminating action for the repetitive inspection s as require d by paragraph (1) of this AD. (5) Inspections and corrective actions, accom plished before the effective date of this AD, in accordance with the instructions of Airbus SB A300

- 54
- 0073 at original issue up to Revision 02 , or SB A310

- 54
- 2017 at original issue up to Revision 05 , or SB A300

- 54
- 6014 at original issue up to Revision 06 , as applicable to aeroplane model , are acceptable to comply with the initial requirements of paragraphs (1) and ( 3 ) of this AD

. Ref. Public ations: Airbus SB A300

- 54
- 007 3 Revision 0 3 , dated 11 October 2012

. Airbus SB A310

- 54
- 20 17 Revision 0 6 , dated 03 Octo ber 2012

. Airbus SB A300

- 54
- 601 4 Revision 0 7 , dated 0 5 September 201 2

. 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 ap prove Alternative Methods of Compliance for this AD. 2. This AD was posted on 14 June 2013 as PAD 13
- 076 for consultation until 14 July 2013

. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Safet y 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

- EIAWA (Airworthiness Of fice) E

- mail: continued.airworthiness

- wb.external@airbus.com

.