EASA AD No : 2011–0029 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0029 

Date: 24 February 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 and A300-600 aeroplanes 

TCDS Number : France No. 145 

Foreign AD : Not applicable 

Supersedure : This AD supersedes AD 2009-0081R1, dated 30 July 2010 

ATA 57 Wings – Main Landing Gear (MLG) Rib 5 Attachment Fitting 

Lower Flange – Inspection / Repair / Modification 

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

Applicability: Airbus A300B2-1C, A300B2-203, A300B2K-3C, A300B4-103, A300B4-120, 

A300B4-203, A300B4-2C, A300C4-203 and A300F4-203 aeroplanes, all 

serial numbers, 

Airbus A300B4-601, A300B4-603, A300B4-605R, A300B4-620, A300B4-622, 

A300B4-622R, A300C4-620 and A300F4-605R aeroplanes, all serial 

numbers, 

except aeroplanes modified in production with Airbus modification 11912 or 

aeroplanes on which Airbus modification 11932 has been embodied before 

initial entry into service, or aeroplanes without Airbus modification 11912 on 

which MLG Rib 5 has been replaced in service on both the left hand (LH) and 

the right hand (RH) wings. 

Reason: Following the occurrence of cracks on the MLG Rib 5 RH and LH 

attachment fitting lower flanges, DGAC France AD 2003-318(B) was issued 

to require repetitive inspections and, as terminating action, the embodiment 

of Airbus Service Bulletins (SB) A300-57-0235 and A300-57-6088 not later 

than 31 December 2004. 

Subsequently, new cases of cracks were discovered during scheduled 

maintenance checks by operators of A300B4 and A300-600 type 

aeroplanes on which the terminating action SB’s were embodied. This 

condition, if not corrected, could affect the structural integrity of those 
EASA AD No : 2011–0029 

EASA Form 110 Page 2/3 

aeroplanes. 

To address and correct this condition, Airbus developed an inspection 

programme for aeroplanes modified in accordance with SB A300-57-0235 

or A300-57-6088. This inspection programme was required to be 

implemented by DGAC France AD F-2005-113, original issue and later 

revision 1. 

A new EASA AD 2008-0111, superseding DGAC France AD F-2005-

113R1, was issued to reduce the applicability. For aeroplanes already 

compliant with DGAC France AD F-2005-113R1, no further action was 

required. 

Since EASA AD 2008-0111 issuance, Airbus reviewed the inspection 

programmes of SB A300-57A0246 and SB A300-57A6101 to introduce 

repetitive inspections including a new inspection technique for holes 47 and 

54 and to reduce inspections threshold and intervals from 700 Flight Cycles 

(FC) to 400 FC until a revised terminating action is made available. 

For the reasons stated above, EASA AD 2009-0081 superseded EASA AD 

2008-0111 and required operators to comply with the new inspection 

programme introduced in Revisions 3 of Airbus SB A300-57A0246 and 

Airbus SB A300-57A6101. 

EASA AD 2009-0081 R1 has been published to introduce an optional 

terminating action which consisted of spot-facing the sensitive holes of the 

MLG Rib 5 (LH and RH) bottom flanges. 

Later discussions with Airbus have demonstrated the necessity to require the 

spot-facing modification as a final solution (no longer optional). This new AD 

retains the inspection requirements of EASA AD 2009-0081R1, which is 

superseded, and requires the spot-facing of sensitive holes of the MLG Rib 5 

(LH and RH) bottom flanges as terminating action.

Effective Date: 10 March 2011 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated unless accomplished previously: 

(1) Within 400 FC following embodiment of Airbus SB A300-57-0235 or 

Airbus SB A300-57-6088 (at any revision), as applicable to aeroplane 

model, 

or 

Within 400 FC or 4 months, whichever occurs first after the effective date 

of this AD, for those aeroplanes that have already exceeded 400 FC from 

embodiment of Airbus SB A300-57-0235 or Airbus SB A300-57-6088 (at 

any revision), as applicable to aeroplane model, perform a Detailed Visual 

Inspection (DVI), on both LH and RH wings, for cracks at: 

(a) the bottom flange and vertical web in the area between the wing rear 

spar/gear rib 5 attachment and the forward reaction-rod pick up lug; 

(b) on the inboard side, around the fastener holes at locations 43, 47 to 50, 

52 and 54; 

(c) on the outboard side, the lower flange, the vertical web and around the 

fastener holes at locations 43, 47 to 50, 52 and 54, 

 followed, if no crack is detected, by a Fluorescent Penetrant Inspection 

(FPI) at holes location 47 and 54, in the RH and LH MLG rib 5 attachment 

fitting lower flange, in accordance with the instructions of Airbus SB A300-

57A0246 Revision 04 or Airbus SB A300-57A6101 Revision 03, as 

applicable to aeroplane model. 

Note: A High Frequency Eddy Current inspection can be carried out as 

secondary inspection at holes location 47 and 54, in accordance with the 

instructions of Airbus SB A300-57A0246 Revision 04 or Airbus SB A300-
EASA AD No : 2011–0029 

EASA Form 110 Page 3/3 

57A6101 Revision 03 at the operator discretion. 

(2) Thereafter, at intervals not to exceed 400 FC, repeat the DVI and FPI 

inspections, in accordance with the instructions of Airbus SB A300-

57A0246 Revision 04 or Airbus SB A300-57A6101 Revision 03, as 

applicable to aeroplane model. 

(3) If any crack is detected during any of the inspections as required by 

paragraph (1), or (2) of this AD, before next flight, contact Airbus for 

approved repair solutions and repair the aeroplane accordingly. 

Note: If spot-faces of both holes 47 and 54 on a gear rib have been repaired, 

the inspection requirements of this AD are no longer required for that 

particular gear rib. 

(4) Within 30 months from the effective date of this AD, modify the spot-faces 

of all holes at locations 43, 47 to 50, 52 and 54 (except for spot-faces of 

holes which have previously been repaired) on the bottom flange MLG Rib 

5 LH and RH in accordance with the instructions of Airbus SB A300-57-

0254 or Airbus A300-57-6110, as applicable to aeroplane model. 

Note: If the bore of any hole has previously been repaired, modification of the 

spot-face is still required. 

(5) Modification of an aeroplane as required by paragraph (4) of this AD 

constitutes terminating action for the repetitive inspections required by this 

AD for that aeroplane.

Ref. Publications: Airbus Service Bulletins: 

A300-57-0235 original issue up to revision 05 

A300-57-6088 original issue up to revision 04 

A300-57A0246 Revision 04 

A300-57A6101 Revision 03 

A300-57-0254 original issue 

A300-57-6110 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 25 January 2011 as PAD 11-004 for consultation 

until 22 February 2011. No comments were received during the 

consultation period. 

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).