EASA AD No.: 20 14

- 0177

TE. CAP.0011 0

- 00 4 © 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 14 - 0177

Date : 25 Ju ly 2014

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 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): A319, A320 and A32 1 a eroplanes

TCDS Number: EASA.A.064

F oreign AD: Not applicable Supersedure: None



### ATA 53 Fuselage
– Rear Fuselage Clips, Shear W ebs and Angles
–

Re p lacement

Manufacturer(s): Airbus (formerly Airbus Industrie) Applicability: Airbus A319

- 111, A319

- 112, A319

- 113, A319

- 114, A319

- 115, A319

- 131, A319

- 132, A319

- 133, A320

- 211, A320

- 212, A320

- 214, A320

- 215, A320

- 216, A320

- 231, A320

- 232, A320

- 233, A321

- 111, A321

- 112, A321

- 131, A321

- 211, A321

- 212, A321

- 213, A321

- 231 and A321

- 232 aeroplane s , al l manufacturer serial numbers , except those on which Air bus modification 30975 ha s been embodied in production

. Reason: During the A320 fatigue test campaign for Extended Service Goal (ESG) , it w as determined that fatigue damage could appear on the clips, shear webs and angles at rear fuselage section 19 , on Frame (FR) 72 and FR 74

. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus developed a modi fication , which has been published through Airbus Service Bulletin (SB) A320

- 53

- 126 6 for in

- service application to allow aeroplanes to operate up to the new ESG limit

. For the reasons describe d above, this AD requires replacement of the affected clips, shear webs and angles at rear fuselage section 19 , FR72 and FR 74.
Effective Date: 08 August 2014EASA AD No.: 20 14

- 0177

TE. CAP.0011 0

- 00 4 © 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 exceeding 48 000 f light cycles (FC) or 96 000 f light hours (FH) , whichever occurs first since aeroplane first flight, rep l a ce the clips, sh ear webs and angles at rear fuselage section 19 , FR72 and FR74 , in accordance with the instructio ns of Airbus SB A320

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- 126 6 Revision 01. (2) Modification of an a eroplane , before the effective date of this AD, in accordance with the instructio ns of Airbus SB A320

- 53

- 126 6 at original issue, is acceptable to compl y with the requirement s of paragraph (1) of this AD for that aeroplane , except as spe cified in paragraph (3) of this AD

. (3) For aeroplanes modified in accordance with the instructions of Airbus SB A320

- 53

- 1266 ( at any revision) before accumulating 30 000 F C or 60 000 F H , whichever occurred first since aeroplane first flight , within 30 000 F C or 60 000 FH , whichever occur s first after that modification, repeat the replace ment of the clips, shear webs and angles at rear fuselage section 19, FR72 and FR74 in accordance with the instructions of Airbus SB A320

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- 1266 Revision 01. Ref. Public a tions: Airbus SB A320

- 53

- 126 6 o riginal issue dated 11 Janua ry 2013, or Revision 01 dated 2 0 Ju ne 2013

. The u se of later approved revisions of th i s document 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 11 June 2014 as PAD 14

- 096 and republished on 16 June 2014 as PAD 14

- 096R1 for consultation until 09 July 2014. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 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

– Airworthiness Office

– EIAS; Fax +33 5 61 93 44 51; E

- mail: account.airworth

- eas@airbus.com

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