EASA AD No.: 2014-0081

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0081

Date: 31 March 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 – Potable Water and Waste Water Service Panels –

Reinforcement

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 (mod) 160055 or

Airbus mod 160056 have been embodied in production.

Reason: During the full scale fatigue test on A320-200, it has been noticed that, due to 

fatigue, cracks could be initiated at the waste water service panel area and the 

potable water service panel area.

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

of the aeroplane.

Prompted by these findings, ALS Part 2 tasks have been introduced for the 

affected A320 family aeroplanes. Since those actions were taken, Airbus 

developed production mod 160055 and mod 160056 to embody reinforcements 

(cold working on certain rivet rows) of the potable water and waste water 

service panels, and published associated Airbus Service Bulletin (SB)

A320-53-1272 (retrofit mod 153074) and SB A320-53-1267 (retrofit mod

153073) for in-service embodiment. 

Following complementary Design Office studies, it appears that the Sharklet

installations on certain aeroplanes have a significant impact on the aeroplane 

structure (particularly, A319 and A320 post-mod 160001, and A321 post-mod 

160021), leading to different compliance times, depending on aeroplane 

configuration.
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For the reasons described above, this AD requires reinforcement of the potable 

water and waste water service panels. Accomplishment of these modifications

cancels the need for the related ALS Part 2 Tasks.

Effective Date: 14 April 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Before exceeding the compliance time as specified in Table 1 of this AD, 

as applicable, modify the potable water service panel in accordance with 

the instructions of Airbus SB A320-53-1272 Revision 01.

Table 1 – Potable Water Service Panel Reinforcement

Affected aeroplanes Compliance time

(Flight cycles (FC) or flight hours 

(FH), whichever occurs first since 

aeroplane first flight)

A319 pre-mod 160001 48 500 FC or 97 000 FH

A319 post-mod 160001 46 000 FC or 92 000 FH

A320 pre-mod 160001 54 200 FC or 108 400 FH

A320 post-mod 160001 36 000 FC or 72 000 FH

A321 60 000 FC or 120 000 FH

(2) Before exceeding the compliance time as specified in Table 2 or Table 3 of 

this AD, as applicable, modify the waste water service panel in accordance 

with the instructions of Airbus SB A320-53-1267 Revision 01.

Table 2 – Waste Water Service Panel Reinforcement

Affected aeroplanes Compliance time

(FC or FH, whichever occurs first 

since aeroplane first flight)

A319 pre-mod 160001 44 400 FC or 88 800 FH

A319 post-mod 160001 43 600 FC or 87 200 FH

A320 pre-mod 160001 see Table 3

A320 post-mod 160001 39 200 FC or 78 400 FH

A321 pre-mod 160021 51 600 FC or 103 200 FH 

A321 post-mod 160021 51 200 FC or 102 400 FH 

Table 3 – Waste Water Service Panel Reinforcement for

A320 pre-mod 160001 aeroplanes

Compliance Time (whichever occurs later, A or B)

A

Before exceeding 46 400 FC or 92 800 FH, whichever occurs 

first since aeroplane first flight 

B

Within 2 300 FC or 4 600 FH, whichever occurs first since last 

accomplishment of ALS Part 2 Task No. 534126-01-3 (except 

as required by paragraph (3) of this AD) without exceeding

48 000 FC or 96 000 FH, whichever occurs first since aeroplane

first flight
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(3) For pre-mod 160001 A320 aeroplanes having exceeded 46 400 FC or

92 800 FH, whichever occurred first since aeroplane first flight, if cracks 

are found during accomplishment of ALS Part 2 Task 534126-01-3, before 

next flight, contact Airbus for corrective action and accomplish those 

actions accordingly.

(4) Modification of an aeroplane, prior to the effective date of this AD in 

accordance with the instructions of Airbus SB A320-53-1272 at original 

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

this AD for that aeroplane.

Modification of an aeroplane, prior to the effective date of this AD in 

accordance with the instructions of Airbus SB A320-53-1267 at original 

issue, is acceptable to comply with the requirements of paragraph (2) of 

this AD for that aeroplane.

(5) Modification of an aeroplane as required by paragraph (1) of this AD 

cancels the need to accomplish the ALS Part 2 task for that aeroplane as 

specified in Table 4 of this AD, as applicable.

Table 4 – ALS Part 2 Task terminated after

Potable Water Service Panel reinforcement

Affected aeroplanes ALS Part 2 Task No.

A319 pre-mod 160001 534125-01-2

A319 post-mod 160001 534125-01-5

A320 pre-mod 160001 534125-01-3

A320 post-mod 160001 534125-01-6

A321 pre-mod 160021 534125-01-4

A321 post-mod 160021 534125-01-7

(6) Modification of an aeroplane as required by paragraph (2) or (3) of this AD 

cancels the need to accomplish the ALS Part 2 task for that aeroplane as 

specified in Table 5 of this AD, as applicable.

Table 5 – ALS Part 2 Task terminated after

Waste Water Service Panel reinforcement

Affected aeroplanes ALS Part 2 Task No.

A319 pre-mod 160001 534126-01-2

A319 post-mod 160001 534126-01-5

A320 pre-mod 160001 534126-01-3

A320 post-mod 160001 534126-01-6

A321 pre-mod 160021 534126-01-4

A321 post-mod 160021 534126-01-7

Ref. Publications: Airbus SB A320-53-1267 original issue dated 24 June 2013, or Revision 01 

dated 02 October 2013.

Airbus SB A320-53-1272 original issue dated 10 January 2013, or Revision 01 

dated 06 August 2013.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.
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Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 23 January 2014 as PAD 14-018 for consultation 

until 20 February 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.