E ASA AD No.: 20 14

- 0081

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 14 - 00 8 1

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 accordan ce 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 ope rate 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
F oreign AD: Not applicable Supersedure: None



### ATA 53 Fuselage
– Potable Water and Waste W ater S ervice P anel s – Reinforcement

Manufacturer(s): Airbus (formerly Airbus Industrie ) Applicability: Airbus A 319

- 111 , A319

- 112 , A319

- 113 , A319

- 114 , A319

- 115 , A319

- 131 , A319

- 132 , A319

- 133 , A320

- 211, A320

- 212, A320

- 214, A320

- 215 , A32 0

- 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 , al l manufacturer serial numbers , except those on which Airbus modification (mod ) 160055 or Airbus m od 160056 have been embodied in production

. Reason: During the full scale fatigue test on A320

- 200, it has been notic ed that , due to fatigue, cracks could be initiated at the w aste 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 h ave been introduced for the affected A320 family aeroplanes

. Since those actions were taken , Airbus developed production m od 160055 and m od 160056 to embody reinforcements (cold working on certain rivet rows) of the p otable w ater and w aste w ater service panel s , 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 S harklet installations on certain aeroplanes have a significant impact on the aeroplane structure ( particularly, A319 and A320 post
- mod 160001 , and A321 post

- mod 1600 2 1 ) , leading to different compliance time s, depending o n aeroplane configuration

.E ASA AD No.: 20 14

- 0081

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. For the reason s describe d above, this AD requires reinforcement of the potable water and waste water service panel s

. Accomplishment of these m odification s cancel s the need for the related ALS Part 2 Task s

. Effective Date: 1 4 April 2014 Required A ction(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

- 127 2 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 - m od 160001 48 500 F C 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 Reinforce ment 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 s ee 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 T ime (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 flightE ASA AD No.: 20 14

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TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. (3) For pre

- mod 160001 A320 aeroplanes having exceeded 46 400 FC or 92 800 FH, whichever occur red first since aeroplane first flight, if cracks are found during accomplishment of ALS P art 2 Task 534126

- 01

- 3 , before next flight, contact Airbus for corrective action and accomplish those actions accordingly

. (4) Modification of a n 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 compl y with the requirements of paragraphs (1) of this AD for that aeroplane

. Modification of a n aeroplane, prior to the effective date of this AD in accordance with the instructions of Airbus SB A320

- 53

- 12 67 at original issue, is acceptable to compl y 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. Public ations: 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.E ASA AD No.: 20 14

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TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 4 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 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

- 0 18 for consultation until 2 0 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 conte nt of the requirements in this AD, please contact: AI RBUS

- Airworthiness Office

- EIAS, Fax +33 5 61 93 44 51. E

- mail: account.airworth

- eas@airbus.com

.