EASA AD No.: 2014

- 0097

- E

TE. CAP.0011 1

- 00 3 © 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 E U 748/2012 , Part 2 1

. 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 ope rate an aircraft to which an AD applies, except in accordance wi th 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

F oreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage

– Aft Cargo Door Sill Bea m 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 o n 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 do or 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 maint enance 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) A53W00 5

- 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

, o r a one

- time High Frequency Eddy Current (HFEC) inspectionEASA AD No.: 2014

- 0097

- E

TE. CAP.0011 1

- 00 3 © 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 A ction(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

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

area in accordance with the instructions of Airbus AOT A53W00 5

- 14

.

Table 1

– Threshold for Initial Inspection

FC accumulate d since aeroplane first flight (on the effective date of this AD ) Compliance T ime

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. Public ations: Airbus AOT A53W00 5

- 14 dated 22 April 2014.

The u se 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 ha ve indicated the need for immediate publication and notification , without the full public consultation process

. 3. Enquiries regarding this A D 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

.