EASA AD No.: 2014-0127

TE.CAP.00110-003 © 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.: 2014-0127

Date: 15 May 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 operate 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):

A330 and A340-200/-300 aeroplanes

TCDS Number: EASA.A.04, EASA.A.015

Foreign AD: None

Supersedure: Not applicable

ATA 25 Equipment / Furnishings – Cockpit Instrument Panel Brackets –

Inspection / Replacement

Manufacturer(s): Airbus (Formerly Airbus Industrie)

Applicability: 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) except those on which Airbus Modification 203287 has been 

embodied in production, and

Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313

aeroplanes, all MSN.

Reason: During flight tests, high stress levels have been measured on the bracket No 6 

which attaches the cockpit instrument panel to the aeroplane structure, 

apparently introduced through the nose landing gear due to bumps on the 

runway. Airbus determined that the bracket does not sustain the fatigue loads 

during the Design Service Goal (DSG).

This condition, if not detected and corrected, combined with failure of the 

horizontal beam, could lead to collapse of the cockpit panel, possibly resulting 

in reduced control of the aeroplane.

To address this potential unsafe condition, Airbus developed a program to 

inspect the condition of the affected cockpit instrument panel bracket No 6, and 

designed a stronger (reinforced titanium undrilled) bracket. The new bracket 

can be installed in-service through Airbus Service Bulletin (SB) A330-25-3548 

or SB A340-25-4354, as applicable to aeroplane type.

For the reasons described above, this AD requires repetitive inspections of the 

cockpit instrument panel bracket No 6 and, depending on findings, the 
EASA AD No.: 2014-0127

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3

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

accomplishment of applicable corrective actions. This AD also provides the 

installation of the stronger bracket as optional terminating action for the 

repetitive actions required by this AD.

Effective Date: 29 May 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Before exceeding 17 200 flight cycles (FC) since aeroplane first flight, or

before exceeding 17 200 FC by a bracket No 6 since installation on an 

aeroplane, as applicable, or within 500 FC after the effective date of this 

AD, whichever occurs later, and, thereafter, at intervals not to exceed

2 600 FC, accomplish a detailed inspection of the cockpit instrument panel 

bracket No 6 in accordance with instructions of Airbus SB A330-25-3538 or 

SB A340-25-4351, as applicable to aeroplane type.

(2) If, during any inspection as required by paragraph (1) of this AD, the 

bracket No 6 is found cracked, but both bracket lugs are not fully broken, 

within 2 600 FC after the inspection as required by paragraph (1) of this 

AD, replace the bracket No 6 with a serviceable part in accordance with 

instructions of Airbus SB A330-25-3538 or SB A340-25-4351, as 

applicable to aeroplane type.

(3) If, during any inspection as required by paragraph (1) of this AD, the 

bracket No 6 is found cracked with both bracket lugs fully broken, before 

next flight, accomplish a detailed inspection of the cockpit instrument panel 

bracket No 7 in accordance with instructions of Airbus Service Bulletin (SB) 

A330-25-3538 or SB A340-25-4351, as applicable to aeroplane type.

(4) If, during an inspection as required by paragraph (3) of this AD, the 

bracket No 7 is not found cracked, before next flight, replace the bracket 

No 6 and bracket No 7 with serviceable parts in accordance with 

instructions of Airbus SB A330-25-3538 or SB A340-25-4351, as 

applicable to aeroplane type.

(5) If, during an inspection as required by paragraph (3) of this AD, the bracket 

No 7 is found cracked, before next flight, contact Airbus for approved repair 

instructions and, within the compliance time specified in those instructions, 

accomplish the repair accordingly. If no compliance time is defined in the 

repair instructions, accomplish the repair before next flight.

(6) Replacement of bracket No 6 on an aeroplane, as required by paragraph 

(2) or (4) of this AD, does not constitute terminating action for the repetitive 

inspections as required by paragraph (1) of this AD.

(7) Modification of an aeroplane in accordance with Airbus SB A330-25-3548 

or SB A340-25-4354, as applicable to aeroplane type, constitutes 

terminating action for the repetitive inspection required by paragraphs (1) 

of this AD for that aeroplane.

Ref. Publications: Airbus SB A330-25-3538 original issue dated 13 September 2013, or

Revision 01 dated 31 January 2014.

Airbus SB A330-25-3548 original issued dated 31 October 2013.

Airbus SB A340-25-4351 original issue dated 13 September 2013, or

Revision 1 dated 31 January 2014.

Airbus SB A340-25-4354 original issued dated 31 October 2013.

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 28 March 2014 as PAD 14-059 for consultation until 
EASA AD No.: 2014-0127

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3

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

25 April 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, Executive 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.