EASA AD No.: 2014-0176

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0176

Date: 25 July 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 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):

A319 and A320 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None

ATA 53 Fuselage – Longeron below Emergency Exit Cut-Outs –

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 (mod) 152637 or mod 

32208 has been embodied in production.

Reason: During the A320 fatigue test campaign for Extended Service Goal (ESG), it was 

determined that fatigue damage could appear at certain fastener locations on 

the longeron below the emergency exit cut-outs, on the left-hand (LH) and

right-hand (RH) sides 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) A320-53-1265

for in-service application to allow aeroplanes to operate up to the new ESG 

limit.

For the reasons described above, this AD requires modification (cold working) 

of 8 fastener locations in the Longeron area (Stringer 20A) below the 

emergency exit cut-outs on the LH and RH sides.

Effective Date: 08 August 2014
EASA AD No.: 2014-0176

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Before exceeding 48 000 flight cycles or 96 000 flight hours, whichever 

occurs first since aeroplane first flight, modify 8 fastener locations in

the Longeron area (Stringer 20A) below the emergency exit cut-outs on 

both RH and LH sides in accordance with the instructions of Airbus SB 

A320-53-1265 Revision 01.

(2) Modification of an aeroplane, before the effective date of this AD, in 

accordance with the instructions of Airbus SB A320-53-1265 at original 

issue, is acceptable to comply with the requirements of paragraph (1) of 

this AD.

Ref. Publications: Airbus SB A320-53-1265 original issue dated 02 January 2013, or Revision 01 

dated 02 July 2013.

The use of later approved revisions of this 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 12 June 2014 as PAD 14-097 for consultation until 

10 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.