EASA AD No.: 2013-0167

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0167

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 

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, A310 and A300-600 aeroplanes

TCDS Number: France TCDS No 145

Foreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD 1993-228-154(B) R3 dated 02 June 1999,

and EASA AD 2008-0001 dated 03 January 2008.

ATA 54 Nacelles / Pylons – Pylon Lower Spar between Ribs 6 and 7 –

Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: A300, A300-600 and A310 aeroplanes, all certified models, all manufacturer 

serial numbers, except aeroplanes on which Airbus modification 10149 has 

been embodied in production.

Reason: Cracks were found between ribs 6 and 7 in the lower spar of engine pylons on 

A310, A300 and A300-600 aeroplanes. To prevent crack initiation, a first 

inspection programme of this area was rendered mandatory by DGAC France 

AD 93-228-154 (later revised, currently at Revision 3) for A300 and A300-600 

aeroplanes.

At a later date and due to new findings, a specific inspection programme for 

A310 aeroplanes was rendered mandatory by DGAC France AD 1999-239-

287(B). That AD was later superseded by EASA AD 2008-0001, which 

introduced new thresholds and intervals in the frame of the A310 extended 

service goal (ESG) exercise.

Since DGAC France AD 1993-228-154(B)R3 and EASA AD 2008-0001 were 

issued, a fleet survey and updated Fatigue and Damage Tolerance analyses 

have been performed in order to substantiate 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 lower spar between ribs 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 thresholds and intervals specified 
EASA AD No.: 2013-0167

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in Airbus Service Bulletin (SB) A300-54-0073 Revision 03 or SB A310-54-2017 

Revision 06 or SB A300-54-6014 Revision 07.

Effective Date: 09 August 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless 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 07, as 

applicable to the aeroplane configuration and utilization, accomplish an

Eddy Current or liquid penetrant inspection of the pylon lower spar 

between ribs 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 07, as applicable to aeroplane model.

(2) For an aeroplane which, on the effective date of this AD, has 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 07, as applicable to aeroplane model, the initial compliance time 

(or Grace Period) 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 07, as applicable to aeroplane model, and must be counted from 

the effective date of this AD. However this new compliance time must not 

exceed the compliance time as specified in the previous issue of each of 

these SBs.

(3) If, during any inspection as required 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 07, as applicable to aeroplane model.

(4) Corrective actions, as required by paragraph (3) of this AD, do not 

constitute terminating action for the repetitive inspections as required by 

paragraph (1) of this AD.

(5) Inspections and corrective actions, accomplished 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. Publications: Airbus SB A300-54-0073 Revision 03, dated 11 October 2012.

Airbus SB A310-54-2017 Revision 06, dated 03 October 2012.

Airbus SB A300-54-6014 Revision 07, dated 05 September 2012.

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 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 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 - EIAWA (Airworthiness Office)

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