EASA AD No.: 2014-0146

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0146

Date: 11 June 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 – Frame 24 at Stringer 17/18 – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A319-111, A319-112, A319-115, A319-132, A319-133, A320-214, 

A320-216, A320-232, A320-233, A321-211, A321-231 and A321-232

aeroplanes, manufacturer serial numbers (MSN) 5230 to 5300 inclusive, except 

MSN 5255 and 5295.

Reason: During cabin conversion of an A320 aeroplane, after removal of the cabin 

lining, an area was discovered where fasteners were missing at frame (FR) 24 

between stringer (STR) 17 and STR18. Investigation results revealed that the 

available data concerning installation on the final assembly line was insufficient 

to pinpoint the exact MSN on which the affected assemblies were installed. 

However, a ‘group’ of MSN suspected to be affected was identified. Results of 

the static analysis performed show that the structure is still able to sustain Limit 

and Ultimate loads. However, the fatigue aspects indicate that long-term effects 

can be expected.

This condition, if not corrected, could affect the structural integrity of the 

airframe.

Prompted by these findings, Airbus issued Alert Operators Transmission (AOT)

A53N006-14 and Service Bulletin (SB) A320-53-1285 to provide inspection 

instructions.

For the reasons described above, this AD requires a one-time detailed

inspection (DET) of the aeroplane structure at FR24 and, depending on 

findings, accomplishment of applicable corrective actions.

Effective Date: 25 June 2014
EASA AD No.: 2014-0146

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 60 flight cycles (FC) after the effective date of the AD, accomplish a

DET of the fasteners on the structure at FR24 between STR17 and STR18 

on the right hand side only, in accordance with the instructions of Airbus 

AOT A53N006-14.

(2) If, during the DET as required by paragraph (1) of this AD, the fasteners

are found missing, before exceeding 3 300 FC since aeroplane first flight 

or within 60 FC after the effective date of this AD, whichever occurs later, 

accomplish the inspection and, depending on findings, corrective action(s)

in accordance with the instructions of Airbus SB A320-53-1285.

(3) If, during the inspection as required by paragraph (2) of this AD, any crack 

is found, before next flight, contact Airbus for approved repair instructions 

and accomplish those instructions accordingly.

(4) Within 30 days after the DET as required by paragraph (1) of this AD, or 

after the inspection as required by paragraph (2) of this AD, as applicable, 

report the inspection results (including no findings) to Airbus.

Ref. Publications: Airbus AOT A53N006-14 original issue, dated 13 May 2014.

Airbus SB A320-53-1285 original issue, dated 29 January 2014.

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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

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.