E ASA AD No.: 20 13 - 02 1 6

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 13 - 02 1 6

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 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]

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### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A300, A310 and A300 - 600 aeroplanes TCDS Number: DGAC France TCDS No

. 145 F oreign 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 m odification (mod) No. 2434 has been embodied in production. A300 aeroplane MSN 125 (on Left Han d side pylon only). A 310 - 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 whic h 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 19 92 - 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 introduc ed 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 DamageE ASA AD No.: 20 13 - 02 1 6

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 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 curativ e 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 program m e . After EASA AD 2013 - 0014 was issued , further analysis allow ed 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 A pplicability section an d adds one A300 model and one A300 MSN. Effective Date: 01 October 2013 Required A ction(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 0 5 , or SB A300 - 54 - 6011 Revision 0 3 , as applicable to aeroplane model, accomplish an Eddy Current or liquid penetrant inspection of the p ylon 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 0 5 , or SB A30 0 - 54 - 6011 Revision 0 3 , 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 0 4 , or SB A300 - 54 - 6011 Revision 0 2 , as applicable to aero plane 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 accord a n ce with the instructions of, Airbus SB A300 - 54 - 0071 Revision 04 , or SB A310 - 54 - 2016 Revision 0 5 , or SB A300 - 54 - 6011 Revision 0 3 , 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 R evision 0 5 , or SB A300 - 54 - 6011 Revision 0 3 , as applicable to aeroplane model. For the first plan n ed 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 0 4 , or SB A300 - 54 - 6011 Revision 0 2 , 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 action s ( 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 require ments

. Accomplishment of a repair on an aeroplane , as required by paragraph (1. 1 ) or (1.2) of this AD, as applicable, constitute s terminating action for the repetitive inspections required byE ASA AD No.: 20 13 - 02 1 6

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 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 . R efer to paragraph ( 4 ) of this AD for post modification 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 0 5 , or SB A300 - 54 - 6011 Revision 0 3 , as applicable to aeroplane model, accomplish an Eddy Current or liquid penetrant inspection of the pylon l ower 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 - 007 1 Revision 04 , or SB A310 - 54 - 2016 Revision 0 5 , or SB A300 - 54 - 6011 Revision 0 3 , as applicable to aeroplane model , taking the effective date of this AD as a starting date, and without exceeding the previous ly applicable value quoted in Airbus SB A300 - 54 - 0071 Revision 02, or SB A310 - 54 - 2016 Revision 0 4 , or SB A300 - 54 - 6011 Revision 0 2 , as applicable to aeroplane model

. ( 3 .2) Thereafter, repeat the inspection within the intervals defined in , and in accord a n ce with the instructions of, Airbus SB A300 - 54 - 0071 Revision 04 , or SB A310 - 54 - 2016 Revision 0 5 , or SB A300 - 54 - 6011 Revision 0 3 , 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 fl ight, contact Airbus for approved repair instructions and accomplish those instructions accordingly within the applicable time limits. ( 4 ) Po st - modification ( SB A300 - 54 - 0079 , SB A310 - 54 - 2022 or SB A300 - 54 - 6019 ) Inspection s: ( 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 0 5 , or SB A300 - 54 - 6011 Revision 0 3 , as applicable to aeroplane model, accomplish an Eddy Current or liquid penetrant inspection of the pylon l ower 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 0 5 , or SB A300 - 54 - 6011 Revision 0 3 , as applicable to aeroplane model , taking the effective date of this AD as a starting date, and without exceeding the previous ly applicable value quoted in Airbus SB A300 - 54 - 0071 Revision 02, or SB A310 - 54 - 2016 Revision 0 4 , or SB A300 - 54 - 6011 Revision 0 2 , 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 0 5 , or SB A300 - 54 - 6011 Revision 0 3 , 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 instructionsE ASA AD No.: 20 13 - 02 1 6

TE. CAP.0011 0 - 00 3 © European Aviation Safety Agency. All rights reserved. 4 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 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, constitute s 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 program me dedicated to each affe cted aeroplane. Ref. Public ations: AIRBUS SB A300 - 54 - 0071 Revision 04 dated 11 April 2013. AIRBUS SB A310 - 54 - 2016 Revision 0 5 dated 05 October 2012. AIRBUS SB A300 - 54 - 6011 Revision 0 3 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 conte nt of the requirements in this AD, please contact: AIRBUS SAS

– EIAW (Airworthiness Office) , E - mail: continued.airworthiness - wb.external@airbus.com

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