EASA AD No.: 20 14

- 0178

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 - 0178

Date: 25 Ju ly 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 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: None



### ATA 53 Fuselage
– Pa ssenger Door G irt B ar F ittings
– 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, A320

- 233, A321

- 111, A321

- 112, A321

- 131, A321

- 211, A321

- 212, A321

- 213, A321

- 2 31 and A321

- 232 aeroplanes, all manufacturer serial numbers , except tho se on which Airbus modification 154966 has been embodied in production

. Reason: During final as sembly line process, several AFT passenger door lower fitting gap s were found excessive and out of tolerance between two parts of the girt bar fittings. The gap contributes to the correct locking of the girt bar during the door lifting movement , ensuring the retention of the girt bar when the loads applied on the girt by the slide are directed f r o m the outside to the inside. If the gap is too large, there is a risk that the girt bar, when subjected to these loads, will detach from one of the girt bar fittings. This condition, if not detected and corrected , could lead to the separation of the slide/slide

- raft from the fuselage, making the emergency exit inoperative and, consequently, significant ly reducin g the safety margin for the occupants during an evacuation

. For the reason describe d above, this AD requires a detai led inspection (DET) to check the gap between the two parts of the girt bar fittings , on AFT passenger door s , left

- hand (LH) and right

- hand (RH) side s , and, depending on findings, accomplishment of the applicable corrective actions

. Effective Date: 08 August 2014EASA AD No.: 20 14

- 0178

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 36 months after the effective date of this AD, accomplish a DET of the girt bar fitting s of the AFT passenger door s, LH and RH side s , and , before next flight after the DET , depending on findings, accomplish all applicable corrective actions in accordance with the instruction s of Airbus Service Bulletin (SB) A320

- 53

- 1289

. (2) For an aeroplane that has been modified to a configuration where the LH and/or RH AFT passenger door is permanently inoperative and/or deactivate d , the DET and, depending on findings, corrective action(s) as specified in paragraph (1) of this AD must be accomplished before next flight after reactivation of the affected AFT passenger door (s) on that aeroplane

. Ref. Public ations: Airbus SB A320

- 53

- 1289 o riginal issue , dated 28 May 2014

. The use 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. This AD was posted on 12 June 2014 as PAD 14

- 098 for consultation until 10 July 2014. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the S afety 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: AIRBUS

– Airworthiness Office

– EIAS; Fax +33 5 61 93 44 51; E

- mail: account.airworth

- eas@airbus.com

.