EASA AD No.: 2014-0272

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0272

Date: 12 December 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, A300-600 and A300-600ST aeroplanes

TCDS Numbers: EASA.A.172 and EASA.A.014

Foreign AD: Not applicable

Supersedure: None

ATA 57 Wings – Frame 40 Lower Junction Fastener Holes – Inspection / 

Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300 and A300-600 aeroplanes, all models, all Manufacturer Serial 

Numbers (MSN), and

Airbus A300-600ST aeroplanes, all MSN.

Reason: Following the A300-600 Extended Service Goal (ESG2) exercise, specific 

inspections for cracks were performed in fittings of frame (FR) 40, in areas not 

covered by any existing task.

Findings were identified on an A300-600 aeroplane withdrawn from service in 

the lower tension bolt area at rib one junction (both sides).

This condition, if not detected and corrected, could lead to crack initiation, 

affecting the structural integrity of the aeroplane.

To address this potential unsafe condition, an inspection programme was 

developed for the fitting around the fastener holes located at FR40 lower wing 

junction, left hand (LH) and right hand (RH) sides.

For the reasons described above, this AD requires repetitive High Frequency 

Eddy Current (HFEC) inspections and rototest inspections of the fitting around 

the fastener holes located at FR40 lower wing junction and, depending on 

findings, accomplishment of a repair.

Effective Date: 29 December 2014
EASA AD No.: 2014-0272

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 1 000 flight hours (FH) after the effective date of this AD, and,

thereafter, at intervals not to exceed 1 000 FH, accomplish a HFEC 

inspection of fasteners 1 to 3 at FR 40 lower junction, LH and RH sides,

and of the fitting around the fastener holes in accordance with the 

instructions of Airbus Service Bulletin (SB) A300-57-0257, SB A300-57-

6115 or SB A300-57-9030, as applicable to aeroplane model.

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

any crack is found, before next flight, contact Airbus for approved repair 

instructions and accomplish those instructions accordingly.

(3) Within 36 months after the effective date of this AD, remove fasteners 1 to 

3 at FR40 lower junction, LH and RH sides, measure the diameter of the 

fastener holes and, before next flight, accomplish the actions specified in 

Table 1 of this AD, as applicable depending on measurement results, in 

accordance with the instructions of Airbus SB A300-57-0257, 

SB A300-57-6115 or SB A300-57-9030: 

Table 1: Actions following Measurement of Fastener Holes

Measurement Results Corrective Actions

One or more hole diameters are 

outside the tolerance of the 

nominal diameter and are outside 

the tolerance of the first and 

second oversize.

Contact Airbus for approved repair 

instructions and accomplish those 

instructions accordingly.

All hole diameters are within the 

tolerance of the nominal diameter

or the first or second oversize.

Accomplish a rototest inspection of 

the fastener holes at FR40 lower 

junction, LH and RH sides.

(4) Accomplishment of a rototest inspection on an aeroplane, as required by 

paragraph (3) of this AD, constitutes terminating action for the repetitive 

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

aeroplane.

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

any crack is found, before next flight, contact Airbus for approved repair 

instructions and accomplish those instructions accordingly.

(6) If, during the rototest inspection as required by paragraph (3) of this AD, 

no crack is found, before next flight, install new fasteners of the same 

diameter in special clearance fit for fasteners 1 to 3 at FR40 lower junction, 

LH and RH sides, and, thereafter, at intervals not to exceed 7 000 flight 

cycles, repeat the rototest inspection in accordance with the instructions of 

Airbus SB A300-57-0257, SB A300-57-6115 or SB A300-57-9030.

(7) If, during any rototest inspection as required by paragraph (6) of this AD, 

any crack is found, before next flight, contact Airbus for approved repair 

instructions and accomplish those instructions accordingly.

Ref. Publications: Airbus SB A300-57-0257 original issue, dated 04 April 2014.

Airbus SB A300-57-6115 original issue, dated 04 April 2014.

Airbus SB A300-57-9030 original issue, dated 31 March 2014.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.
EASA AD No.: 2014-0272

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Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 30 April 2014 as PAD 14-077 for consultation until 

28 May 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.