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 participat e 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 aircra ft 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, A300B2-20 3, 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 Bulle tins (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 affe ct the structural integrity of thoseEASA 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, supers eding 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, Ai rbus 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 publis hed to introduce an optional terminating action which consisted of s pot-facing the sensitive holes of the MLG Rib 5 (LH and RH) bottom flanges.
Later discussions with Airbus have dem onstrated 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 fast ener 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 t he 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, bef ore 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 previous ly 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 r epetitive 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 & Re search Section, Certification Directorate, EASA E-mail: ADs@easa.europa.eu

. 4. For any question concerning the tec hnical 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).