EASA AD No.: 2014

- 0270 R1

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

. : 2014

- 0270 R1

Date : 1 5 December 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 E U 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 requ irements 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 and A320 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Note applicable

Revision : This AD revises EASA Emergency AD 2014

- 0270

- E dated 11 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

- 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

. This condition, if not detected and corrected could reduce the design margin of the structure.

Based on the results of the preliminary investigation, this affects only certain A319 and A320 aeroplane Model s delivered since January 2014. A321 aeroplanes are not affected

, as the wing assembly is done using parallel fasteners

. A318 aeroplanes are not affected, since none have been delivered since January 2014.
Prompted by these findings

, EASA issued Emergency AD 2014

- 0270

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

. Since that AD was issu ed, operator comments have indicated the need for clarification, as well as correction.EASA AD No.: 2014

- 0270 R1

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. For the reason described above , this AD is revised to add Note s for information and to correct paragraph s (1) and (2) of the AD.

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

Effective Date: Revision 1: 2 2 December 2014 Original issue: 15 December 2014

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously:
(1) Within 8 calendar days after 15 December 2014 [ the effective date of the original issue of this AD ]

, or 8 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 8 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 Alert Operators Transmission (AOT) A57N006

- 14

. (1.1) A ccomplish a Detail ed Visual Inspection (DVI) 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 DVI of the inboard MLG support rib lower flange to detect broken nut s or/and fastener tai l s

. 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 8 days, the next inspection is to be performed on that aeroplane before next flight.
(2) Within 4 months after the effective date of this AD

, 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 4 months or before each flight (see Note 3 ), whichever occurs later , accomplish a DVI 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 , the next inspection is to be performed on that aeroplane before next flight

. (3) If, during any DVI as required by paragraph (1) or (2) of this AD, as applicable, a ny 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

. 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. The results of the safety assessment ha ve indicated the need for immediate publication and notification , without the full public consultation process

.EASA AD No.: 2014

- 0270 R1

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

.