EASA AD No.: 2014-0202R1

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0202R1

Date: 19 September 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 and A310 aeroplanes

TCDS Number: EASA.A.172

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2014-0202 dated 11 September 2014.

ATA 53 Fuselage – Door Frames Holes – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300B4-603, A300B4-605R, A300B4-622R, A310-304, A310-308, 

A310-324 and A310-325 aeroplanes, all manufacturer serial numbers in postmodification (MOD) 06924 configuration, except MSN 464, 477, 479, 481,482, 

483, 484 and 488. 

Note: MSN 464, 477,479, 481, 482, 483, 484 and 488 partially embodied MOD

06924 by means of modification proposal D05902. 

Reason: During the preparation phase for conversion of an A300-600 aeroplane from 

passenger to freighter configuration, a crack was detected on door frame (FR) 

73A, between stringer (STRG) 24 and STRG 25.

DGAC France had issued AD 1999-013-276R1 to require inspections at 

FR 73A in accordance with the instructions of Airbus Service Bulletin (SB) 

A310-53-2107 or SB A300-53-6116, as applicable. However, the new crack was 

found in an area not covered by the existing inspection and is therefore 

addressed by this new AD. (DGAC France AD 1999-013-276R1 remains in 

place).

Further investigations identified that, on A300-600 aeroplanes, the areas at

FR 56A and FR 57A have the same design and material as at FR 73A. 

This condition, if not detected and corrected, could affect the structural integrity 

of the airframe.

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

rivet heads of the seal retainer run out holes to detect cracks and, depending on 

findings, accomplishment of corrective actions.
EASA AD No.: 2014-0202R1

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.

Even though no crack has been identified at FR 56A and FR 57A, as a 

preventive measure, the inspection is extended to these areas. On A310 

aeroplanes, only the area at FR 73A needs to be inspected.

This AD is revised to reduce the applicability to aeroplanes in post-MOD 06924

configuration.

Effective Date: 25 September 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time as defined in Table 1 of this AD, as applicable,

and, thereafter, at intervals not to exceed 7 500 flight cycles (FC), 

accomplish a High Frequency Eddy Current (HFEC) inspection around the 

rivet heads of the seal retainer run out holes on A300-600 aeroplanes at 

FR 56A, FR 57A and FR 73A, left-hand (LH) and right-hand (RH) sides, and 

on A310 aeroplanes at FR 73A, LH and RH sides, in accordance with the 

instructions of Airbus SB A310-53-2138 or Airbus SB A300-53-6175, as 

applicable.

Table 1 – Compliance Time for Inspection

Compliance Time (whichever occurs later, A or B)

A Before exceeding 32 000 FC since aeroplane first flight

B

Within 36 months after the effective date of this AD, without 

exceeding 36 000 FC since aeroplane first flight

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

found, before next flight, contact Airbus to obtain a Repair Design Approval 

Sheet (RDAS) and accomplish that repair accordingly, including post-repair 

follow-on action(s), if any are specified in that RDAS.

(3) Accomplishment of a repair on an aeroplane, as required by paragraph (2) 

of this AD, does not constitute terminating action for the repetitive 

inspections as required by paragraph (1) of this AD for that aeroplane, 

unless the RDAS indicates otherwise.

Ref. Publications: Airbus SB A310-53-2138 original issue dated 28 May 2014.

Airbus SB A300-53-6175 original issue dated 28 May 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. The original issue of this AD was posted on 30 July 2014 as PAD 14-124 for 

consultation until 27 August 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 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.