EASA AD No.: 2014-0101

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0101

Date: 02 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):

A300-600 aeroplanes

TCDS Number: France No. 145

Foreign AD: Not applicable

Supersedure: None

ATA 53 Fuselage – Forward Door Surrounding Panels – Inspection / 

Rework / Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300B4-603, A300B4-605R, A300B4-620, A300B4-622, A300B4-622R,

A300C4-605R and A300C4-620 aeroplanes, all Manufacturer Serial Numbers 

(MSN); and

Airbus A300F4-605R aeroplanes, all MSN, except those on which Airbus 

Modification No. 12699 has been embodied in production.

Reason: In the frame of the Ageing Airplane Safety Rule (AASR), all existing Structural 

Repair Manual (SRM) repairs were reviewed. 

This analysis, which consisted in new Fatigue and Damage Tolerance 

calculations, revealed that some repairs in the area surrounding the forward 

passenger/crew door and the fail safe ring are no longer adequate.

These repairs, if not reworked, could affect the structural integrity of the 

aeroplane. 

To address this potential unsafe condition, Airbus issued Service Bulletin (SB) 

A300-53-6173 (later revised), to provide instructions for the inspection of 

repairs on the left-hand (LH) and right-hand (RH) forward door surrounding 

panels.

For the reasons described above, and further to the AASR implementation, 

this AD requires a one-time inspection of the forward door surrounding panels 

to identify SRM repairs in these areas and, depending on findings, 

accomplishment of applicable corrective action(s).

Effective Date: 16 May 2014
EASA AD No.: 2014-0101

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time defined in Table 1 of this AD, accomplish a 

detailed inspection (DET) of the LH and RH forward passenger door 

surrounding panels in accordance with the instructions of Airbus SB 

A300-53-6173 Revision 01.

Table 1 – DET 

Compliance Time (whichever occurs later, A or B)

A Within 28 months after the effective date of this AD

B Before reaching the aeroplane Design Service Goal, whichever

limit is reached first, flight cycles or flight hours

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

repair is found, before next flight, identify the reworked area(s), the 

percentage of the rework and the reworks limit in accordance with the

instructions of Airbus SB A300-53-6173 Revision 01.

(3) If, during the analysis as required by paragraph (2) of this AD, any rework 

is found outside the Allowable Damage Limits of the applicable A300-600 

SRM, before next flight, report those findings to Airbus to obtain rework

approval or repair instructions, as applicable, and, in case repair is 

required, within the compliance time defined in the instructions received 

from Airbus, accomplish the repair accordingly.

(4) Actions accomplished before the effective date of this AD in accordance 

with the instructions of Airbus SB A300-53-6173 at original issue are 

acceptable to comply with the requirements of this AD.

Ref. Publications: Airbus SB A300-53-6173 original issue dated 01 August 2013 or Revision 01 

dated 28 February 2014.

The use of later approved revisions of this 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 07 October 2013 as PAD 13-156 for consultation 

until 04 November 2013, and re-published on 02 April 2014 as PAD 13-

156R1 for additional consultation until 16 April 2014.

The Comment Response Document for PAD 13-156 can be found at 

http://ad.easa.europa.eu. No comments were received during the 

consultation period of PAD 13-156R1.

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 SAS – EIAW (Airworthiness Office)

E-mail: continued.airworthiness-wb.external@airbus.com