EASA AD No.: 201 5

- 0026

TE. CAP.0011 0

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

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 201 5

- 0026

Date : 1 9 February 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 E U 748/2012 , Part 21

. A.3B. In accordan ce 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 ope rate 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):

A319 and A320 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Note applicable

Supersedure : This AD supersedes EASA AD 2014

- 0270 R1 dated 15 December 2014

.



### ATA 57 Wings

– Wing Bottom Skin at Main Landing Gear Rib 5

– Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A319

- 115, A319

- 132, A319

- 133, A320

- 214, A320

- 216, A320

- 232 and A320

- 233 aeroplane s, manufacturer serial numbers (MSN) 5817, 5826, 5837, 5848, 5855, 5864, 5875, 5886, 5896 and 5910, and MSN 5918 and up

.

Reason: During production of wings

, a number of taperlok fasteners w ere found failed after installation. The fasteners in question are located at the bottom skin of the Main Landing Gear ( MLG ) reinforcing plate, wing skin and Gear Support Rib 5 lower flange

. Based on the results of the preliminary investigation, this affects only certain A319 and A320 aeroplanes delivered since January 2014. This condition, if not detected and corrected could reduce the design safety margin of the structur e. Prompted by these findings

, EASA issued Emergency AD 2014

- 0270

- E (later revised) to require repetitive detailed inspection s (DET) of the bottom skin taperlok fasteners at the MLG Rib 5 footprint location and, depending on findings, accomplishment of app licable corrective action(s)

. Since EASA AD 2014

- 0270R1 was issued, based on in service feedback and further investigation, Airbus issued Revision 01 of Alert Operators Transmission (AOT) A57N006

- 14 to extend the original 8 calendar days inspection interval to 60 calendar days for the external area and for the internal inboard side

. In addition, it w as identified that the model A319

- 132 was missing from the AD applicability.

For the reason s described above, this AD retains the requirements of EASA ADEASA AD No.: 201 5

- 0026

TE. CAP.0011 0

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

- Internet/Intranet. 2014

- 0270R1

, which is superseded, to amend the Applicability and to require those actions within the new thresholds and intervals

. This AD is still considered to be an interim action and further AD action may follow.

Effective Date: 2 6 February 2015

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 60 calendar days after 15 December 2014 [ the effective date of EASA AD 2014

- 0270

- E ]

, or 60 calendar days after the aeroplane date of manufacture (see Note 1)

, or before next flight (see Note 2 )

, whichever occurs later

, and

, thereafter

, at interval s not to exceed 60 calendar days or before each flight (see Note 2 ) , whichever occurs later

, accomplish the actions specified in paragraph s (1.1) and (1.2) of this AD in accordance with the instructions of Airbus AOT A57N006

- 14

. (1.1) A ccomplish a DET of the extern al surface of the Left Hand (LH) and Right Hand (RH) lower skin surface to detect missing or migrating fasteners

. (1.2) A ccomplish a DET of the inboard MLG support rib lower flange to detect broken fastener tai l s /nuts

. Note 1: For the purpose of this AD, the d ate of manufacture is the date of t ransfer o f t itle

, which is referenced in Airbus documentation at the time of first delivery to an operator.

Note 2 : In case an aeroplane is not operated for more than 60 days, the next inspection is to be performed on that aeroplane before next flight. (2) Within 4 months after 15 December 2014 [ the effective date of EASA AD 2014

- 0270

- E]

, or after the aeroplane date of manufacture (see Note 1)

, or before next flight (see Note 3 ) whichever occurs later , and

, thereafter

, at interval s not to exceed 120 calendar days or before each flight (see Note 3 ), whichever occurs later , accomplish a DET of the outboard MLG support rib lower flange fasteners and nuts in accordance with the instructions of Airbus AOT A57N006

- 14.

Note 3 : In case an aeroplane is not operated for more than 4 months ( 120 calendar days ) , the next inspection is to be performed on that aeroplane before next flight

. (3) If, during any DET as required by paragraph (1) or (2) of this AD, as applicable, any discrepancy ( missing, migrated or damaged fastener ; or missing nut) is detected, before next flight, accomplish the applicable corrective actions in accordance with the instructions of Airbus AOT A57N006

- 14. (4) Replacement of fasteners or nuts on an aeroplane, as required by paragraph (3) of this AD , does not constitute terminating action for the repetitive inspections as required by this AD for that aeroplane

.

Ref. Public ations: AOT A57N006

- 14 original issue dated 04 December 2014

, or Revision 01 dated 16 February 2015

. The u se of later approved 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. 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

.EASA AD No.: 201 5

- 0026

TE. CAP.0011 0

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

- Internet/Intranet. 3. Enquiries regarding this A D 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

.