EASA AD No.: 2013-0216

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0216

Date: 17 September 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: DGAC France TCDS No. 145

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2013-0014 dated 16 January 2013.

ATA 54 Nacelles / Pylons – Pylon Lower Spar between Ribs 9 and 10 –

Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: A300 aeroplanes, all models, all manufacturer serial numbers (MSN) on which 

Airbus modification (mod) No. 2434 has been embodied in production.

A300 aeroplane MSN 125 (on Left Hand side pylon only).

A310-221, A310-222, A310-322, A310-324 and A310-325 aeroplanes, and

A300B4-620, A300C4-620, A300B4-622R, A300B4-622 aeroplanes, all MSN, 

except aeroplanes on which Airbus mod No. 10149 has been embodied in 

production.

Reason: Cracks were found between ribs 9 and 10 in the lower pylon spar of A310 

aeroplanes equipped with Pratt & Whitney (PW) engines.

For A310, A300 and A300-600 aeroplanes and, in order to prevent crack 

initiation, the implementation of a first inspection programme of this area was 

required by DGAC France AD 1992-049-130(B), currently at Revision 4.

General Electric (GE) and PW pylons on A300 aeroplanes are also affected, 

due to similar design.

After that AD was issued, prompted by new findings, a specific inspection 

programme for A310 aeroplanes was introduced and required by DGAC 

France AD 1999-237-285(B), which was subsequently superseded by EASA 

AD 2008-0008, which introduced new thresholds and intervals in the frame of 

the A310 extended service goal exercise.

Some cracks, which were discovered after the implementation of the preventive

modification, prompted Airbus to perform a new Fatigue and Damage 
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Tolerance analysis with a refined model of the area with and without repair or 

preventive reinforcement before crack appearance. Based on the results of this 

analysis, Airbus revised the related Service Bulletins to introduce more 

restrictive thresholds and intervals for curative and preventive repair 

configuration.

EASA issued AD 2013-0014, which superseded DGAC France AD 1992-049-

130(B) and EASA AD 2008-0008, to mandate a new inspection programme.

After EASA AD 2013-0014 was issued, further analysis allowed to identify one 

A300 aeroplane model and one retrofitted A300 MSN missing in the 

applicability chapter.

For the reason described above, this AD retains the requirements of 

EASA AD 2013-0014, which is superseded, and clarifies the Applicability 

section and adds one A300 model and one A300 MSN.

Effective Date: 01 October 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Inspection pre-repair and pre-modification:

(1.1) Within the applicable threshold defined in Airbus Service Bulletin 

(SB) A300-54-0071 Revision 04, or SB A310-54-2016 Revision 05,

or SB A300-54-6011 Revision 03, as applicable to aeroplane model, 

accomplish an Eddy Current or liquid penetrant inspection of the 

pylon lower spar between Ribs 9 and 10, and depending on findings, 

accomplish the corrective actions within the time period defined in, 

and in accordance with the instructions of, Airbus SB A300-54-0071 

Revision 04, or SB A310-54-2016 Revision 05, or SB A300-54-6011 

Revision 03, as applicable to aeroplane model.

Note: For aeroplanes previously inspected in accordance with Airbus SB A300-

54-0071 Revision 02, or SB A310-54-2016 Revision 04, or SB A300-54-6011 

Revision 02, as applicable to aeroplane model, no further action is required by 

paragraph (1.1) of this AD.

(1.2) Thereafter, repeat the inspection within the intervals defined in, and 

in accordance with the instructions of, Airbus SB A300-54-0071 

Revision 04, or SB A310-54-2016 Revision 05, or SB A300-54-6011 

Revision 03, as applicable to aeroplane model and, depending on 

findings, accomplish the corrective actions within the time period 

defined in, and in accordance with the instructions of, Airbus SB 

A300-54-0071 Revision 04, or SB A310-54-2016 Revision 05, or SB 

A300-54-6011 Revision 03, as applicable to aeroplane model.

For the first planned repeat inspection to occur after the effective 

date of this AD, a compliance time can be applied, without 

exceeding the interval value quoted in SB A300-54-0071 Revision 

02, or SB A310-54-2016 Revision 04, or SB A300-54-6011 Revision 

02, as applicable to aeroplane model.

(1.3) If, during any inspection as required by paragraph (1.1) or (1.2) of 

this AD, a crack exceeding 30 mm (1.181 in.) is found, before next 

flight, contact Airbus for approved repair instructions and accomplish 

those instructions accordingly within the applicable time limits.

(1.4) In case of crack finding up to 30 mm (1.181 in.) inclusive, following

accomplishment of corrective actions (embodiment of a repair) as 

required by paragraph (1.1) or (1.2) of this AD, as applicable, refer to 

paragraph (3) of this AD for post-repair requirements.

Accomplishment of a repair on an aeroplane, as required by 

paragraph (1.1) or (1.2) of this AD, as applicable, constitutes

terminating action for the repetitive inspections required by 
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paragraph (1.2) of this AD for that aeroplane.

(2) In case no cracks are found, modification of an aeroplane in accordance 

with the instructions of Airbus SB A300-54-0079, or SB A310-54-2022, or 

SB A300-54-6019, as applicable to aeroplane model, constitutes 

terminating action for the repetitive inspections as required by paragraph 

(1) of this AD for that aeroplane. Refer to paragraph (4) of this AD for postmodification inspection requirements.

(3) Inspection post-repair - installation of doubler in case of crack 

< 30 mm (1.181 in):

(3.1) From the repair embodiment date, within the applicable threshold 

defined in, and in accordance with the instructions of, Airbus SB 

A300-54-0071 Revision 04, or SB A310-54-2016 Revision 05, or SB 

A300-54-6011 Revision 03, as applicable to aeroplane model, 

accomplish an Eddy Current or liquid penetrant inspection of the 

pylon lower spar between Ribs 9 and 10.

Aeroplanes which have exceeded the value of the applicable 

inspection threshold must be inspected within the compliance time 

defined in SB A300-54-0071 Revision 04, or SB A310-54-2016 

Revision 05, or SB A300-54-6011 Revision 03, as applicable to 

aeroplane model, taking the effective date of this AD as a starting 

date, and without exceeding the previously applicable value quoted 

in Airbus SB A300-54-0071 Revision 02, or SB A310-54-2016 

Revision 04, or SB A300-54-6011 Revision 02, as applicable to 

aeroplane model.

(3.2) Thereafter, repeat the inspection within the intervals defined in, and 

in accordance with the instructions of, Airbus SB A300-54-0071 

Revision 04, or SB A310-54-2016 Revision 05, or SB A300-54-6011 

Revision 03, as applicable to aeroplane model. 

(3.3) If, during any inspection as required by paragraph (3.1) or (3.2) of 

this AD, a crack is found, before next flight, contact Airbus for 

approved repair instructions and accomplish those instructions

accordingly within the applicable time limits.

(4) Post-modification (SB A300-54-0079, SB A310-54-2022 or SB A300-54-

6019) Inspections:

(4.1) From the modification embodiment date, within the applicable 

threshold defined in, and in accordance with the instructions of, 

Airbus SB A300-54-0071 Revision 04, or SB A310-54-2016 Revision 

05, or SB A300-54-6011 Revision 03, as applicable to aeroplane

model, accomplish an Eddy Current or liquid penetrant inspection of 

the pylon lower spar between Ribs 9 and 10.

Aeroplanes which have exceeded the value of the applicable 

inspection threshold must be inspected within the compliance time 

defined in Airbus SB A300-54-0071 Revision 04, or SB A310-54-

2016 Revision 05, or SB A300-54-6011 Revision 03, as applicable to 

aeroplane model, taking the effective date of this AD as a starting 

date, and without exceeding the previously applicable value quoted 

in Airbus SB A300-54-0071 Revision 02, or SB A310-54-2016 

Revision 04, or SB A300-54-6011 Revision 02, as applicable to 

aeroplane model.

(4.2) Thereafter, repeat the inspection within the intervals defined in, and 

in accordance with the instructions of, Airbus SB A300-54-0071 

Revision 04, or SB A310-54-2016 Revision 05, or SB A300-54-6011 

Revision 03, as applicable to aeroplane model. 

(4.3) If, during any inspection as required by paragraph (4.1) or (4.2) of 

this AD, a crack is found, before next flight, contact Airbus for 

approved repair instructions and accomplish those instructions
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accordingly within the applicable time limits.

(5) Repair of an aeroplane, as required by paragraph (1.3), (3.3) or (4.3) of 

this AD, as applicable, constitutes terminating action for the repetitive 

inspections required by, respectively, paragraph (1.2), (3.2) or (4.2) of this 

AD for that aeroplane. However, the Airbus Repair Approval Sheet will 

define a new post-repair inspection programme dedicated to each affected 

aeroplane.

Ref. Publications: AIRBUS SB A300-54-0071 Revision 04 dated 11 April 2013.

AIRBUS SB A310-54-2016 Revision 05 dated 05 October 2012.

AIRBUS SB A300-54-6011 Revision 03 dated 23 June 2011.

AIRBUS SB A300-54-0079 Revision 01 dated 09 July 2002.

AIRBUS SB A310-54-2022 Revision 02 dated 09 July 2002.

AIRBUS SB A300-54-6019 Revision 02 dated 07 April 2003.

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 15 August 2013 as PAD 13-119 for consultation 

until 12 September 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.