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 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 EC 1702/2003, Part 21A.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]. 

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 Service Bulletin (SB) A300-53-0389 or 

A310-53-2133 or A300-53-6166 (AIRBUS modification 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 exclude 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. The investigation results indicate that 

these cracks initiated in the fastener hole, 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 previously repaired by the Structure Repair 

Manual (SRM) or Repair Approval Sheet (RAS). 

Effective Date: 26 May 2011 
EASA 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 and 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).