EASA AD No.: 2014-0097-E

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 1/2

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

EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2014-0097-E

Date: 23 April 2014

Note: This Emergency 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: France No. 145

Foreign AD: Not applicable

Supersedure: None

ATA 53 Fuselage – Aft Cargo Door Sill Beam Area – Inspection

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A300-600 and A310 aeroplanes, all certified models, all Manufacturer 

Serial Numbers on which Airbus modification (mod) 05438 has been embodied

in production, except those on which mod 12046 has been embodied in 

production.

Reason: During accomplishment of Maintenance Review Board Report (MRBR) task 

531625-01-1 on an A300-600 aeroplane having accumulated more than 25 000 

flight cycles (FC) since aeroplane first flight, multiple fatigue cracks were found 

on the following parts:

- Aft cargo door sill beam Part Number (P/N) A53973085210 

- Lock fitting P/N A53978239002

- Torsion box plate P/N A53973318206.

Prompted by these findings, a stress analysis was performed during which it 

was discovered that there is no dedicated scheduled maintenance task to 

inspect the affected area for fatigue damage. 

The loss of more than one lock fitting could lead to loss of the door locking 

function and, subsequently, complete loss of the cargo door in flight with 

associated risk of rapid decompression.

To address this unsafe condition, Airbus issued Alert Operators Transmission 

(AOT) A53W005-14 providing instructions for inspection of the affected area.

For the reason described above, this AD requires repetitive ultrasonic 

inspections or detailed inspections (DET) of the aft cargo door sill beam 

external area, or a one-time High Frequency Eddy Current (HFEC) inspection
EASA AD No.: 2014-0097-E

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 2/2

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

of the aft cargo door sill beam internal structure and, depending on findings,

accomplishment of corrective action(s).

This AD is considered an interim measure and further AD action may follow.

Effective Date: 25 April 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

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

applicable, and, thereafter, at intervals not to exceed 275 FC, accomplish 

an ultrasonic inspection or DET of the aft cargo door sill beam external 

area in accordance with the instructions of Airbus AOT A53W005-14.

Table 1 – Threshold for Initial Inspection

FC accumulated since 

aeroplane first flight (on the 

effective date of this AD)

Compliance Time

30 000 FC or more Within 50 FC after the effective 

date of this AD

18 000 FC or more, but less 

than 30 000 FC

Within 275 FC after the effective 

date of this AD

Less than 18 000 FC Before exceeding 18 275 FC 

since aeroplane first flight

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

cracks are found, before next flight, contact Airbus for approved repair 

instructions and accomplish those instructions accordingly.

(3) Accomplishment of a HFEC inspection in accordance with the instructions 

of Airbus AOT A53W005-14 and, depending on findings, accomplishment 

of applicable corrective action(s) before next flight after that HFEC 

inspection in accordance with approved Airbus instructions, constitutes 

terminating action for the repetitive inspections as required by paragraph 

(1) of this AD for that aeroplane.

(4) Within 30 days following the initial ultrasonic inspection or DET as required 

by paragraph (1) of this AD, report the inspection results, including no 

findings, to Airbus.

Ref. Publications: Airbus AOT A53W005-14 dated 22 April 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. The results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process.

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.