E ASA AD No.: 2013

- 0147

TE. CAP.0011 0

- 003 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 3 - 0 147

Date: 16 Jul y 201 3

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 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): A318 , A319 , A320 and A321 aeroplanes
TCDS Number: EASA.A.064

F oreign AD: Not applicable Supersedure: This AD supersedes EASA AD 2010

- 0071 R1 dated 28 May 2010 , and EASA AD

2011

- 0231 dated 09 December 2011

.



### ATA 05 Time Limits and Maintenance Checks

– Damage Tolerant

Airworthiness Limitation Items
– ALS Part 2

– Amendment

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

- 111, 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: The airworthiness limitations for Airbus A320 family aeroplanes are currently included in Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) document

. The airworthiness limitations applicable to the Damage Tolerant Airworthiness Limitation Items (DT ALI) are currently given in Airbus ALS Part 2 , which is approved by EASA

. Previously, EASA issued AD 2010

- 0071 R1 , which require d the implementation of the DT ALI maintenance instructions as specified in Airbus A318/A319/A320 / A321 ALI Document ref

. AI/SE

- M4/95A.0252/96 issue 10 and Airbus A319 Corporate Jet ALI Document ref. AI/SE

- M2/95A.1038/99. The new Airbus A318/A319/A320/A321 ALS Part 2 Revision 0 2 , which include s also Airbus A319 Corporate Jet , introduce s more restrictive DT ALI maintenance instructions . Failure to comply with these instructions could result in an unsafe condition. A pplication of new DT ALI tasks 531129

- 02

- 2 and 531129

- 02

- 3 introduce s initial and repetitive inspections of the windshield central lower node continui ty fittings , replac ing the one time inspection for that subject, previously required by EASA AD 2011

- 0231.E ASA AD No.: 2013

- 0147

TE. CAP.0011 0

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

- Internet/Intranet. For the reasons described above, t his AD retains the requirements of EASA AD 2010

- 0071R 1 and those of EASA AD 2011

- 0231 , which are superseded, and requires compliance with all maintenance task s as described in Airbus A318/A319/A320/A321 ALS Part 2 at Revision 0 2.
Effective Date: 30 July 2013 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) After the effective date of this AD, within the compliance times defined in the Record of Revisions (ROR ) pages of the Airbus A318/A319/A320/A321 ALS Part 2 Revision 0 2 , accomplish al l applicable maintenance tasks , depending on aeroplane configuration, as specified in Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 2 Revision 0 2

. (2) I f, during accomplishment of any task as required by paragraph (1) of this AD, discrepancies are detected, wi thin the applicable compliance time specified in the Airbus maintenance documentation, accomplish the applicable corrective action ( s ) in accordance with instructions specified (or incorporated by reference) in the applicable Airbus maintenance documentatio n. If no compliance time is identified in the Airbus maintenance documentation, before next flight, accomplish the corrective action ( s ) or contact Airbus for approved instructions and within the compliance time specified therein , accomplish those instructions accordingly

. If any of the discrepancies , detected during accomplishment of any task as required by paragraph (1) of this AD , is not defined in the Airbus maintenance documentation, before next flight, contact Airbus for app roved instructions and accomplish those instructions accordingly. (3) Compliance with the requir ements of paragraph (1) of this AD can be demonstrated by: (3.1) Revising as follows, the approved Aircraft Maintenance Programme (AMP) on the basis of which the operator or the owner ensures the continuing airworthiness of each operated aeroplane: Incorporate all DT ALI maintenance instructions specified in Airbus A318/A319/A320/A321 ALS Part 2 Revision 0 2.
a nd (3.2) Complying with the approved AMP described in paragraph ( 3. 1) of this AD.
Ref. Public ations: Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 2 Revision 0 2, approved by EASA on 28 May 2013

. The use of later approved variations or revisions of th i s 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 0 5 February 2013 as PAD 13

- 028 for consultation until 05 March 2013. 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, F ax +33 5 61 93 44 51, E

- mail: account.airworth

- eas@airbus.com

.