EASA AD No : 2011-0086

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0086

Date: 12 May 2011

Note: This Airworthiness Directive (AD) is i ssued 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 EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft s hall be ensured by accomplishing any applicable ADs. Consequently, no person may opera te 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]. 

### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :
A300, A310 and A300-600 aeroplanes

TCDS Number : France No. 145

Foreign AD : Not applicable

Supersedure : None



### ATA 53 Fuselage – Cross Beam at Junction with Lower Cargo Door Actuator Beam – Inspection / Modification

Manufacturer(s): Airbus (formerly Airbus Industrie).

Applicability: - A300 and A310 aeroplanes, all certified models, all serial numbers; - A300B4-601, A300B4-603, A300B4-620, A300B4-622, A300C4-620, A300B4- 605R and A300B4-622R aeroplanes, all serial numbers, except aeroplanes on which AIRBUS Se rvice Bulletin (SB) A300-53-0389 or A310-53-2133 or A300-53-6166 (AIRBUS m odification 13434), as applicable to the aeroplane model, has been embodied in service.
Note : Modification of an aeroplane from passenger configuration to freighter configuration (e.g. by STC) does not e xclude that aeroplane from the applicability of this AD. Reason: Some operators have reported cracked crossbeams at the junction with the lower deck cargo door actuator beam. T he investigation results indicate that these cracks initiated in the fastener hol e, propagated in vertical direction and were due to fatigue. This condition, if not corrected, could lead, in case of cracks propagation in a crossbeam (upper and lower web), to the floor grid being unable to withstand ultimate load condition. For the reasons described above, this AD requires repetitive inspections of certain crossbeams including those previous ly repaired by the Structure Repair Manual (SRM) or Repair Approval Sheet (RAS).

Effective Date: 26 May 2011EASA AD No : 2011-0086

EASA Form 110 Page 2/2 

### Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Aeroplanes with crossbeams FR22/23 a nd FR61/62 not repaired previously according to SRM or by RAS (1) Within 10 000 Flight Cycles (FC) accumulated since the aeroplane first flight or 600 FC after the effective date of this AD, whichever occurs later, and thereafter, at intervals not exceeding 600 FC, perform a High Frequency Eddy Current (HFEC) inspection of the crossbeam Fuselage Frame Stations (FR) FR22/23 and FR61/62 in accordance with the instructions of Airbus Service Bulletin (SB) A300- 53-0390 original issue, A310-53-2134 original issue, A300-53-6168 original issue, as applicable to aeroplane model. (2) If, during any inspection as required in paragraph (1) of this AD, no crack has been detected, the modification of the crossbeams at FR22/FR23 and FR61/FR62 in accordance with the instructions of SB A300-53-0389 or A310-53- 2133 or A300-53-6166, as applicable to aeroplane model, performed within 600 FC after the last inspection, constitutes terminating action for the repetitive inspection requirements of this AD. (3) If, during any inspection as required by paragraph (1) of this AD, any crack is detected and the crack length is : - less than 7.0 mm (0.28 in.), within 50 FC after the identification of the crack, contact Airbus to obtain the necessary approved instructions for corrective action and accomplish those instructions accordingly,

or, - equal or more than 7.0 mm (0.28 in.), before the next flight, contact Airbus to obtain the necessary approved instructions for corrective action and accomplish those instructions accordingly. (4) All aeroplanes modified in accordance with these instructions provided by AIRBUS are no longer concerned by the inspections required by paragraph (1) of this AD. Aeroplanes with crossbeams FR22/23 and FR61/62 previously repaired according to SRM or by RAS (5) Within 10 000 FC accumulated since the aeroplane first flight or 600 FC after the effective date of this AD, whichever occurs later, contact AIRBUS and follow their instructions.



### Ref. Publications: AIRBUS Service Bulletins: A300-53-0389 original issue, A310-53-2133 original issue, A300-53-6166 original issue, A300-53-0390 original issue, A310-53-2134 original issue and A300-53-6168 original issue. 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. This AD was posted on 11 March 2011 as PAD 11-014 for consultation until 08 April 2011. The Comment Response Documents can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Research 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 – EAW (Airworthiness Office, Telephone: + 33 5 61 18 41 39, Fax:+ 33 5 61 93 44 51).