EASA AD No : 2010 – 0250 

EASA Form 110 Page 1/3 

 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010 – 0250 

Date: 29 November 2010 

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 Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness 

Directive 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, A300-600 aeroplanes

TCDS Number : France No 145 

Foreign AD : None 

Supersedure : Not applicable 

ATA 57 Wings – Main Landing Gear (MLG) Attachment - Inspection 

Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE). 

Applicability: Airbus A300B4-103, B4-120, B4-203, B4-2C, C4-203 and F4-203 

aeroplane models, all serial numbers, except those where Left Hand (LH) 

and Right Hand (RH) wing MLG rib 5 forward lugs have been repaired by 

installation of oversized interference fit bushes as per Airbus Repair 

Instruction R57240221, or those where LH and RH wing have had Airbus 

Service Bulletin (SB) A300-57-0249 embodied in service. 

Airbus A300-600 aeroplanes, all models, all serial numbers, except those 

where LH and RH wing MLG rib 5 forward lugs have been repaired by 

installation of oversized interference fit bushes as per Airbus Repair 

Instruction R57240221, or those where LH and RH wing have had Airbus 

SB A300-57-6106 embodied in service. 

Reason: During routine visual inspection, a crack has been found in the wing 

MLG rib 5 aft bearing forward lug on two A310 in-service aeroplanes. 

Laboratory examination of cracked ribs confirmed that the crack was 

due to the presence of pitting corrosion in the forward lug hole. Also on 

both aeroplanes medium to heavy corrosion was found in the forward 

lugs on the opposite wing after removal of the bushes. Similarly to A310 

aeroplanes, A300 and A300-600 aeroplanes are concerned by this 

situation which, if not detected, could affect the structural integrity of the 

MLG attachment. 
EASA AD No : 2010 – 0250 

EASA Form 110 Page 2/3 

 

The aim of the Emergency Airworthiness Directive (EAD) 2006-0372-E 

was to mandate, for A300 and A300-600 aeroplanes, repetitive detailed 

visual inspections (DVI) of wing MLG rib 5 aft bearing forward lugs for 

detection of through cracks. 

Since then, in order to ensure the detection of any crack in the forward 

lug of the RH and LH MLG rib 5 aft bearing attachment at an early 

stage, Airbus has developed a new inspection by means of ultrasonic 

method. Due to the early crack detection possibility, this new means of 

inspection also enables extension of the inspection interval. 

For technical reasons, this new means of inspection is only applicable to 

A300B4, C4, and F4 and A300-600 aeroplane series (not to A300B2 

aeroplane series). 

For these reasons, this new AD, applicable to A300B4, C4, and F4 and 

A300-600 aeroplane series, retains the requirements of EASA AD 2006-

0372-E (revised to remove A300B4, C4, and F4 and A300-600 

aeroplane series from the applicability) and adds new inspection 

program requirements.

Effective Date: 13 December 2010 

Required action(s) 

and Compliance 

Time(s): 

(1) Initially, within the time indicated in Table 1 of this AD, or, for 

aeroplanes that have been previously inspected as required by EASA AD 

2006-0372-E, within 100 flight cycles (FC) after the latest detailed visual 

inspection (DVI), accomplished in accordance with the instructions of 

Airbus Alert SB A300-57A0248 or A300-57A6105, as applicable to 

aeroplane level, accomplish a DVI or an ultrasonic inspection of the LH 

and RH MLG rib 5 aft bearing forward lugs, in accordance with the 

instructions of Airbus SB A300-57-0251 or SB A300-57-6107, as 

applicable to aeroplane model. 

Table 1 

Flight cycles (FC) accumulated on 

the effective date of this AD 

Compliance time 

Less than 12 000 FC, since first flight 

or since LH or RH MLG rib 5 

replacement, as applicable 

Before accumulating 12 000 

FC 

12 000 FC or more, since first flight or 

since LH or RH MLG rib 5 

replacement, as applicable 

Within 10 days after the 

effective date of this AD 

(2) Thereafter, accomplish a DVI at intervals not to exceed 100 FC, or an 

ultrasonic inspection at intervals not to exceed 675 FC, as applicable, of 

the LH and RH MLG rib 5 aft bearing forward lugs, in accordance with the 

instructions of Airbus SB A300-57-0251 or SB A300-57-6107, as 

applicable to aeroplane model. 

(3) If, during any DVI as required by paragraph (1) or (2) of this AD, a 

crack is detected, before next flight, contact Airbus for approved repair 

instructions and accomplish those instructions accordingly. 

(4) If, during any ultrasonic inspection as required by paragraph (1) or (2) 

of this AD, a crack is detected, before next flight, report to Airbus and 

accomplish a DVI. 

(4.1) If, during the DVI as required by paragraph (4) of this AD, no crack is 

detected, repeat the DVI at intervals not exceeding 100 FC and contact 

Airbus for approved repair instructions and accomplish those instructions 

accordingly, within the time period specified in those instructions. 
EASA AD No : 2010 – 0250 

EASA Form 110 Page 3/3 

 

(4.2) If, during the DVI as required by paragraph (4) of this AD, a crack is 

detected, before next flight, contact Airbus for approved repair instructions 

and accomplish those instructions accordingly. 

(5) Within 30 days after accomplishment of the first inspection, fill-in and 

forward the SB A300-57-0251 or A300-57-6107 inspection report sheet, 

as applicable to aeroplane model, including no finding situation, to Airbus. 

(6) Modification of an aeroplane in accordance with the instructions of 

Airbus SB A300-57-0249, or SB A300-57-6106, as applicable to aeroplane 

model, constitutes terminating action for the repetitive inspection 

requirements of this AD. 

Ref. Publications: AIRBUS Service Bulletins A300-57-0251 original issue, A300-57-

6107original issue, A300-57-0249 original issue, A300-57-6106 original 

issue, Alert SB A300-57A0248, A300-57A6105 and AIRBUS Repair 

Instruction R57240221. 

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. The required actions and the risk allowance have granted the 

issuance of a Final AD with Request for Comments, postponing the 

public consultation process after publication. 

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 – Airworthiness Office – 

EAW Fax: + 33 5 61 93 44 51.