EASA AD No.: 2015-0036

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0036

Date: 03 March 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 EU 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 operate 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) exemption].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: None

ATA 53 Fuselage – Fuselage Skin Repairs – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A318-121, A318-122, 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.

Reason: During A320 family Extended Service Goal full scale fatigue tests, it was 

demonstrated that the inspection thresholds defined in the current Structural 

Repair Manual (SRM) for the A320 family skin repairs are insufficient to detect 

possible cracks becoming after repairs. The findings are limited to 1.2 mm 

fuselage skin and cover for all cut-out external repairs. The internal repairs are 

not affected.

This condition, if not detected and corrected, could affect the structural integrity 

of the fuselage at the repaired skin area(s).

To address this potential unsafe condition, Airbus issued Alert Operators 

Transmission (AOT) A53N007-14 to provide inspection instructions.

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

affected areas and, depending on findings, accomplishment of applicable repair 

instructions.

Effective Date: 17 March 2015
EASA AD No.: 2015-0036

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) Within the compliance time defined in Airbus AOT A53N007-14, as 

applicable, or within 350 flight cycles after the effective date of this AD, 

whichever occurs later, identify whether any fuselage external skin 

(doubler) repairs have been accomplished on fuselage sections 11, 12, 13, 

14, 16 and/or 17, and, for each of the repaired 1.2 mm fuselage skin areas, 

as applicable, accomplish an Ultrasonic (US) inspection from external, or a 

Low Frequency Eddy Current (LFEC) inspection from internal, in 

accordance with the instructions of Airbus AOT A53N007-14.

A review of aeroplane maintenance records is acceptable to make the

identification of an affected repair, provided those records can be relied 

upon for the purpose of this requirement.

(2) As an alternative to the LFEC or US inspection as required by paragraph 

(1) of this AD, a one-time High Frequency Eddy Current (HFEC) inspection 

in accordance with Non-destructive Testing Manual (NTM) Task 51-10-08 

in the cut-out surrounding fastener area (at and in front (~10-15mm) of the 

fastener row) can be accomplished, provided this is done after doubler 

removal and before new extended doubler installation, and within the 

compliance as specified in paragraph (1) of this AD.

(3) The inspection as required by paragraph (1) of this AD can be delayed,

provided that repetitive Detailed Visual Inspections (DVI), or High 

Frequency Eddy Current (HFEC) inspections are accomplished within the 

compliance times defined in, and in accordance with the instructions of,

Airbus AOT A53N007-14.

(4) If, during any US or LFEC inspection as required by paragraph (1) of this 

AD, or during the HFEC inspection as specified in paragraph (2) of this AD, 

or during any DVI or HFEC inspection as required by paragraph (3) of this 

AD, as applicable, any crack is found, before next flight, accomplish an 

applicable repair in accordance with the instructions of Airbus AOT 

A53N007-14.

Note: For an aeroplane inspected and/or repaired in accordance with the 

instructions of Airbus AOT A53N007-14, post-repair repetitive inspections as 

specified in the applicable Structural Repair Manual remain applicable for that

aeroplane. Refer to paragraph (5) of this AD for post-repair inspection 

thresholds.

(5) From the AD effective date, in case a fuselage external skin (doubler) 

repair has to be accomplished, concurrently with accomplishment of the 

repair, update the post-repair inspection threshold(s) in accordance with 

the instructions provided in paragraph 4.1.1 of Airbus AOT A53N007-14.

Ref. Publications: Airbus AOT A53N007-14 original issue, dated 22 July 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. This AD was posted on 19 December 2014 as PAD 14-177 for consultation 

until 02 January 2015 and republished as PAD 14-177R1 on 11 February 

2015 for consultation until 25 February 2015. The Comment Response 

Documents can be found at http://ad.easa.europa.eu/.

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.