EASA AD No.: 20 14

- 0259

TE. CAP.0011 0

- 00 4 © 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 14 - 0 2 5 9

Date: 05 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 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]

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### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A318, A319 and A320 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not applicable
Supersedure: None



### ATA 53 Fuselage

– External Fuselage Skin

– Inspection

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

- 211, A320

- 212, A320

- 214, A320

- 215, A320

- 216, A320

- 231, A320

- 232 and A320

- 233 aeroplane s , all manufacturer serial numbers , except those on which Airbus m odification (mod) 37878 has been embodied in production , or Airbus S ervice B ulletin (SB) A320

- 53

- 1281 in service

. Reason: An operator reported finding chaf ing damage on the fuselage skin at the bottom of frame (FR) 34 junction between stringer (STR) 43 left hand (LH) side and right hand (RH) side on several aeroplane s, underneath the fairing structure. After investigation, a contact between the fairing nut plate and the fuselage was identified, causing damage to the fuselage. This con dition , if not detected and corrected , could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage

. For the reason describe d above, this AD requires repetitive detail ed inspection s (DET) of the fuselage at FR 34 and provides an optional terminating action to the repetitive inspections required by this AD.
Effective Date: 1 9 December 2014EASA AD No.: 20 14

- 0259

TE. CAP.0011 0

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

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within the threshold as defined in the table 1 of this AD and, thereafter at interval s not exceeding 12 000 f light c ycles (FC) or 24 000 f light h ours (FH), whichever occurs first, accomplish a DET on the fuselage skin at FR34 between ST R 43 both LH and RH side , in accordance with the instruction s of Airbus SB A320

- 53

- 1287

. Table 1

– DET Threshold Compliance T ime ( whichever occurs later, A or B )
A Before exceeding 12 000 FC or 24 000FH, whichever occurs first since aeroplane first flight
B Within 5 000 FC or 10 000 FH, whichever occurs first after the effective date of this AD

(2) If, during any DET as required by paragraph (1) of this AD, damage is detected, before next flight, accomplish the applicable corrective action (s) in accordance with the instructions of Airbus SB A320

- 53

- 1287 or , i n case the detected damage exceeds the limits specified in that SB, contact Airbus for approved repair instructions and accomplish those instructions accordingly

. (3) Accomplishment of a repair o n an aeroplane, as required by paragraph (2) of this AD , does not constitute terminating action for the repetitive DET as required by paragraph (1) of this AD, unless the approved repair indicates otherwise. ( 4 ) Modification of an aeroplane in accordance with the instructions of Airbus SB A320

- 53

- 1281 constitutes terminating action for the repetitive DET as required by paragraph (1) of this AD for that aeroplane.
Ref. Public ations: Airbus SB A320

- 53

- 1287 o riginal issue dated 29 July 2014

. Airbus SB A320

- 53

- 1281 o riginal issue dated 29 July 2014

. The use of later approved revisions of these documents 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 13 October 2014 as PAD 1 4

- 147 for consultation until 1 0 November 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, Certification Dir ectorate, 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

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