EASA AD No.: 2014-0177

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0177

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, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None

ATA 53 Fuselage – Rear Fuselage Clips, Shear Webs and Angles –

Replacement

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 aeroplanes, all manufacturer 

serial numbers, except those on which Airbus modification 30975 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 on the clips, shear webs and 

angles at rear fuselage section 19, on Frame (FR) 72 and FR74.

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) A320-53-1266 for 

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

For the reasons described above, this AD requires replacement of the affected 

clips, shear webs and angles at rear fuselage section 19, FR72 and FR74.

Effective Date: 08 August 2014
EASA AD No.: 2014-0177

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

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

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

whichever occurs first since aeroplane first flight, replace the clips, shear 

webs and angles at rear fuselage section 19, FR72 and FR74, in accordance 

with the instructions of Airbus SB A320-53-1266 Revision 01.

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

accordance with the instructions of Airbus SB A320-53-1266 at original 

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

AD for that aeroplane, except as specified 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 FC or

60 000 FH, whichever occurred first since aeroplane first flight, within

30 000 FC or 60 000 FH, whichever occurs first after that modification, 

repeat the replacement of the clips, shear webs and angles at rear fuselage 

section 19, FR72 and FR74 in accordance with the instructions of Airbus

SB A320-53-1266 Revision 01.

Ref. Publications: Airbus SB A320-53-1266 original issue dated 11 January 2013, or Revision 01 

dated 20 June 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 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.