EASA AD No.: 2015-0037 

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2015-0037 

Date: 02 March 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 EU 748/2012, Part 21.A.3B. In accordance 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 operate 

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): 

A330 and A340 aeroplanes

TCDS Numbers: EASA.A.004, EASA.A.015 

Foreign AD: Not applicable 

Supersedure: None 

ATA 25 Equipment / Furnishings – Cockpit Door – Modification 

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: This AD applies to: 

1. Airbus A330-201, A330-202, A330-203, A330-223, A330-243, A330-223F, 

A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-

323, A330-341, A330-342 and A330-343 aeroplanes, all manufacturer 

serial numbers (MSN), if modified in-service with Airbus Service Bulletin 

(SB) A330-25-3161, or with Airbus modification (mod) 50014 in production, 

2. Airbus A340-211, A340-212, A340-213, A340-311, A340-312, A340-313, all 

MSN, if modified in service with Airbus SB A340-25-4181, or with Airbus 

mod 50014 in production, and 

3. Airbus A340-541, A340-542, A340-642 and A340-643 aeroplanes, all MSN, 

except aeroplanes on which Airbus mod 203066, or mod 203074, or mod 

203372 has been embodied in production. 

Reason: An operator has reported chafed wiring at the upper left corner of the cockpit 

door. The investigation concluded that the affected wire bundle, which supplies 

a voltage of 115V AC, was not grounded on the cockpit door frame as part of 

the design of A330 and A340 aeroplanes. 

This condition, if not corrected, could result in injury, in case any person gets in 

contact with the door frame. 

Prompted by these findings, Airbus issued SB A330-25-3534, SB A340-25-

4349 and SB A340-25-5212 to provide instructions to modify the electrical 
EASA AD No.: 2015-0037 

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. 

bonding of the cockpit door. 

For the reasons described above, this AD requires modification of the cockpit 

door frame structure, installation of bonding-leads to the upper cockpit door 

frame and modification of the upper cockpit door plate cover. 

Effective Date: 16 March 2015 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 24 months after the effective date of this AD, modify the cockpit 

door frame structure and install bonding-leads to the upper cockpit door 

frame, in accordance with the instructions of Airbus SB A330-25-3534 

Revision 01, or SB A340-25-4349 Revision 01, or SB A340-25-5212 

Revision 01, as applicable to aeroplane type and model. 

(2) Depending on aeroplane configuration, before or concurrently with 

accomplishing the modification required by paragraph (1) of this AD, 

modify the upper cockpit door plate cover, in accordance with the 

concurrent requirement instructions of Airbus SB A330-25-3534 Revision 

01, or SB A340-25-4349 Revision 01, or SB A340-25-5212 Revision 01, 

as applicable to aeroplane type and model. 

(3) An aeroplane on which Airbus Mod 52869, or Mod 53292 has been 

embodied in production, is compliant with the requirements of paragraph 

(2) of this AD. 

Ref. Publications: Airbus SB A330-25-3534 Revision 01 dated 23 October 2014. 

Airbus SB A340-25-4349 Revision 01 dated 27 October 2014. 

Airbus SB A340-25-5212 Revision 01 dated 27 October 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 04 July 2014 as PAD 14-111 for consultation until 

01 August 2014, republished as PAD 14-111R1 on 15 July 2014 for 

consultation until 01 August 2014, and republished as PAD 14-111R2 on 

12 December 2014 until 26 December 2014. The Comment Response 

Documents can be found at http://ad.easa.europa.eu. 

3. Enquiries regarding this AD 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 – EIAL. 

E-mail: airworthiness.A330-A340@airbus.com.