EASA AD No.: 20 15

- 0085

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 15 - 0085

Date: 13 May 2015

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 E U 1321/2014 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 [EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemp tion]. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A319 and A32 0 a eroplanes
TCDS Number: EASA.A.064
F oreign AD: Not applicable Supersedure: This AD supersedes EASA AD 2014

- 0176 dated 25 July 2014.



### ATA 53 Fuselage
– Emergency Exit Cut - O ut Area
– Modification

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 and A320

- 233 aeroplanes, all manufacturer serial numbers , except those on which Airbus modification (m od) 152637 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 at certain fastener locations on the longeron below the e mergency e xit c ut
- o uts , on the l eft

- h and (LH) and r ight

- h and (RH) s ide s of the fuselage

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

- 53

- 126 5 for in

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

. Consequently, EASA issue d AD 2014

- 0176 to require modification (cold working) of 8 fastener locations in the l ongeron area (Stringer 20A) below the e mergency e xit c ut
- o uts on the LH and RH side s

. Since that AD was issued, it w as identified that post

- mod 32208 aeroplanes, which were excluded from the Applicability o f that AD , are also affected. For the reason described above, this AD re tains the requirements of EASA AD 2014

- 0176, which is superseded, but no longer exclud es post
- mod 32208 aeroplanes from the Applicability.
Effective Date: 27 May 2015EASA AD No.: 20 15

- 0085

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 or 96 000 f light hours , whichever occurs first since aeroplane first flight, modify 8 fastener locations in the l ongeron area (Stringer 20A) below the e mergency e xit c ut
- o uts on both RH and LH side s in accordance with the instructio ns of Airbus SB A320

- 53

- 1265 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

- 1265 at original issue, is acceptable to compl y with the requirement s of paragraph (1) of this AD

. Ref. Public ations: Airbus SB A320

- 53

- 126 5 o riginal issue dated 0 2 Janua ry 2013, or Revision 01 dated 02 July 2013 , or Revision 02 dated 10 July 2014

. 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 13 April 2015 as PAD 15

- 03 9 for consultation until 11 M ay 2015

. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification 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

.