EASA AD No : 2009-0081R1 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0081R1 

Date: 30 July 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 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 

Revision : This AD revises AD 2009-0081, dated 06 April 2009. 

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

Flange – Inspection / Repair 

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. 

In addition, the requirements of this AD do not apply to: 

- aeroplanes without Airbus modification 11912 on which MLG ribs 5 have 

been replaced in service on both the left hand (LH) and the right hand (RH) 

wings. 

- aeroplanes that have had the holes 47 and 54 on both the LH and RH wings 

repaired in accordance with repair drawing R57240226. 

Note: If a new MLG rib 5 has been installed on one wing only, or if repair 

drawing R57240226 has been performed on one wing only, then the 

mandatory actions specified in this AD are still required on the MLG rib 5 

installed on the other wing. 
EASA AD No : 2009-0081R1 

EASA Form 110 Page 2/3 

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 

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, 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. 

This AD is revised to introduce an optional terminating action which consists 

of spot-facing the sensitive holes of the MLG Rib 5 (LH and RH) bottom 

flanges. 

Effective Date: Revision 1 : 13 August 2010 

Original issue: 20 April 2009 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated: 

(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 at original issue, 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) 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 is crack detected, by a Fluorescent Penetrant Inspection 

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

attachment fitting lower flange, in accordance with the instructions of 

Airbus SB A300-57A0246 Revision 03 or Airbus SB A300-57A6101 

Revision 03, as applicable to aeroplane model. 

Actions performed prior to the effective date of this AD at original issue in 
EASA AD No : 2009-0081R1 

EASA Form 110 Page 3/3 

accordance with the instructions of any previous issues of Airbus SB A300-

57-0246 or Airbus SB A300-57-6101 are acceptable for compliance with 

the corresponding paragraph (1)(a), (1)(b) or (1)(c) of this AD, as long as 

the inspected areas and the methods used are equivalent to the ones 

specified in Airbus SB A300-57A0246 Revision 03 or Airbus SB A300-

57A6101 Revision 03, as applicable to aeroplane model, and paragraph 

(1) of this AD. 

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 03 or Airbus SB A300-

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

applicable to aeroplane model. 

(3) If any cracks are 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. 

OPTIONAL TERMINATING ACTION:

(4) After modification of an aeroplane by spot-facing of the sensitive holes 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, the inspections of this AD are no longer 

required 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 03 

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. 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 – EAW (Airworthiness Office, 

Telephone: + 33 5 61 93 36 96, Fax:+ 33 5 61 93 44 51).