EASA AD No : 2012-0176

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0176

[Correction: 20 September 2012]

Date: 07 September 2012

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].

Design Approval Holder’s Name :

AIRBUS

Type/Model designation(s) :

A300, A310, A300-600 and A300-600ST aeroplanes

TCDS Number: France TCDS N° 145 and EASA.A.014

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2006-0372R1 dated 29 November 2010, EASA AD

2007-0195 dated 19 July 2007, EASA AD 2010-0250 dated 29 November 2010

and EASA AD 2010-0251 dated 29 November 2010.

ATA 57 Wings – Main Landing Gear Rib 5 Aft Bearing Forward Lug 

Bushes – Inspection / Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: A300, A310, A300-600 and A300-600ST aeroplanes, all certified models, all 

manufacturer serial numbers.

Reason: Several cases of corrosion of the Main Landing Gear (MLG) Rib 5 aft fitting 

forward lug have been reported on A310 family aeroplanes. In some 

instances, corrosion pits caused the cracking of the forward lug. 

This condition, if not detected and corrected, may lead to the complete failure 

of the fitting and thus could affect the structural integrity of the MLG 

installation.

EASA ADs 2006-0372R1, 2007-0195, 2010-0250 and 2010-0251 were issued 

to address this condition and required a repetitive inspection programme of the 

MLG Rib 5 fitting forward lugs and, as terminating action, the embodiment of 

mandatory design change (bushes with increased interference fit).

MLG Rib 5 forward lug on A320 family aeroplanes is a similar design to the 

A300/A300-600/A310 family. Since those ADs were issued, on two A321 

aeroplanes, post modification (bushes with increased interference fit) MLG Rib

5 forward lugs were reportedly found ruptured. One other case was due to a 

sealant discrepancy that led to water ingress and consequently corrosion

initiation, leading to cracking. Subsequent investigation results have shown 

that a remaining defect, not removed during the repair, had propagated, 
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resulting in rupture of the lug.

For the reasons stated above, this new AD retains the requirements of EASA 

ADs 2006-0372R1, 2007-0195, 2010-0250 and 2010-0251, which are 

superseded, expands the applicability to all models and series of A300, A310, 

A300-600 and A300-600ST aeroplanes, and requires:

- for aeroplanes not yet modified or repaired, implementation of Modification 

Service Bulletin (SB) A300-57-0249, A310-57-2090, A300-57-6106, or 

A300-57-9019, all at Revision 3, and

- for aeroplanes which already embody that modifications, at original issue or 

revision 01 or 02 of the applicable SB, or have MLG Ribs already repaired in 

accordance with Airbus repair instruction R57240221 or R57249121, 

implementation of an additional inspection programme and associated 

corrective action(s).

This AD has been republished to correct an error in paragraph (8).

Effective Date: 21 September 2012

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

Note 1: On the effective date of this AD, the status of a MLG Rib 5 may be 

different, depending on Left Hand (LH) and Right Hand (RH) side of the 

aeroplane. Required actions applied are dependent on this status.

Paragraphs (1), (2), (3), (4), (5), (6), (7), (8) and (9) of this AD are 

applicable to aeroplanes (Group 1 aeroplanes) on which Airbus SB A300-

57-0249, A310-57-2090, A300-57-6106, or A300-57-9019, as applicable to 

aeroplane model, at original issue, Revision 01, or Revision 02, has not 

been embodied in service [Airbus modification (mod.) 

13329/13348/19619)] and to aeroplanes with MLG Ribs 5 not repaired in 

accordance with Airbus repair instruction R57240221 or R57249121.

Restatement of EASA AD 2007-0195 and EASA AD 2010-0250 requirements:

(1) For A300-600, A310 and A300B4/C4/F4 series aeroplanes, before 

accumulating 12 000 flight cycles (FC) since first flight, or since MLG Rib

5 replacement, as applicable, or within 100 FC after the latest detailed 

visual inspection (DVI), or within 675 FC (A300 aeroplanes) or 825 FC 

(A310 aeroplanes) after the latest ultrasonic inspection accomplished in 

accordance with the instructions of Airbus Alert Service Bulletin (ASB)

A300-57A0248, A310-57A2088 or A300-57A6105, at original issue, as 

applicable to aeroplane model, accomplish a Detailed Visual Inspection 

(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, A310-57-2091 or SB A300-57-6107, at original issue, as applicable 

to aeroplane model.

(2) After the inspection as required by paragraph (1) of this AD, accomplish 

a DVI at intervals not to exceed 100 FC, or an ultrasonic inspection at 

intervals not to exceed 675 FC (A300 aeroplanes) or 825 FC (A310 

aeroplanes), 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, A310-57-2091 or SB A300-57-6107, at original issue, as applicable 

to aeroplane model.

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

this AD, a discrepancy is detected, before next flight, report the finding to 

Airbus and accomplish concurrently a one-time DVI in accordance with 

the instructions of Airbus SB A300-57-0251, A310-57-2091 or SB A300-

57-6107, at original issue ,as applicable to aeroplane model.

(4) If, during the DVI as required by paragraph (3) of this AD, crack is not 

detected, repeat the DVI at intervals not to exceed 100 FC in accordance 

with the instructions of Airbus SB A300-57-0251, A310-57-2091 or SB 
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A300-57-6107, at original issue, as applicable to aeroplane model.

(5) If, during a DVI as required by paragraph (1), (2), (3) or (4) of this AD, a 

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

instructions and accomplish those instructions accordingly, within the 

time period specified in those instructions.

Restatement of EASA AD 2006-0372R1 requirements:

(6) For A300B2 series aeroplanes, before accumulating 12 000 FC since 

first flight, or since MLG Rib 5 replacement, as applicable, or within 100

FC after the latest DVI accomplished in accordance with the instructions 

of Airbus ASB A300-57A0248, and, thereafter, at intervals not to exceed

100 FC, accomplish a DVI of the LH and RH wing MLG Rib 5 aft bearing 

forward lugs in accordance with the instructions of Airbus ASB A300-

57A0248, at original issue.

(7) If, during any DVI as required by paragraph (6) of this AD, a crack is 

detected, before next flight, contact Airbus for approved repair 

instructions and accomplish those instructions accordingly, within the 

time period specified in those instructions.

Restatement of EASA AD 2010-0251 requirements:

Note 2: Airbus SB A300-57-0249 Revision 3, SB A310-57-2090 Revision 3, 

SB A300-57-6106 Revision 3, or SB A300-57-9019 Revision 3 have been 

revised at Revision 03 to include changes to instructions for bush installation 

and paint/sealing process.

(8) For A300-600, A310, A300-600ST and A300B4/C4/F4 series 

aeroplanes, within 30 months after 13 December 2010 [the effective 

date of the EASA AD 2010-0251], install new bushes with increased 

interference fit in the gear Rib 5 aft bearing forward lug on RH and LH 

wings in accordance with the instructions of Airbus SB A300-57-0249 

Revision 3, SB A310-57-2090 Revision 3, SB A300-57-6106 Revision 3, 

or SB A300-57-9019 Revision 3, as applicable to aeroplane model.

(9) Modification of a MLG Rib 5 on an aeroplane as required by paragraph 

(8) of this AD constitutes terminating action for the inspection 

requirements of paragraphs (1), (2), (3) and (4) of this AD for that MLG

Rib 5.

(10) Repair of a MLG Rib 5 in accordance with Airbus repair instruction 

R57240425 or R57249389, as applicable to aeroplane model, constitutes 

terminating action for the inspection requirements of paragraphs (1), (2) 

, (3) and (4) of this AD for that MLG Rib 5.

(11) For A300B2 series aeroplanes, repair of a MLG Rib 5 in accordance 

with Airbus repair instruction R57240425 constitutes terminating action 

for the repetitive inspection requirements as required by paragraph (6) of 

this AD for that MLG Rib 5.

New requirements of this AD: Paragraphs (12), (13), (14), (15), (16) and (17) 

of this AD are applicable to aeroplanes (Group 2 aeroplanes) on which 

Airbus SB A300-57-0249, A310-57-2090, A300-57-6106, or A300-57-9019,

as applicable to aeroplane model, at original issue, Revision 01, or 

Revision 02, has been embodied in service, and to aeroplanes with MLG 

Rib 5 already repaired in accordance with Airbus repair instruction 

R57240221 or R57249121.

Note 3: An aeroplane with the MLG Rib 5 forward lugs repaired on one wing, 

by installation of oversized interference fit bushes in accordance with Airbus 

repair Instruction R57240221 or R57249121, as applicable to aeroplane 

model, for the purposes of this AD, is a ‘Group 2’ aeroplane.

(12) For A300B4/C4/F4 series, A310, A300-600 and A300-600ST 

aeroplanes, within the threshold indicated in Table 1 of this AD, as 
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applicable, 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 A300-57-0255, A310-57-2101, A300-57-6112, 

or A300-57-9024, at original issue, as applicable to aeroplane model.

Table 1

Aeroplane Type Compliance Time – Whichever occurs 

later

A300B4/C4/F4,

A300-600 and 

A300-600ST

Within 2 500 FC after the modification or 

repair accomplishment, or

Within 550 FC after the effective date of 

this AD

A310

Within 2 500 FC after the modification or 

repair accomplishment, or

Within 775 FC after the effective date of 

this AD

(13) After the inspection as required by paragraph (12) of this AD, at intervals 

not to exceed the value specified in Table 2 of this AD, as applicable, 

accomplish a DVI or a non-destructive test inspection (NDT) of the LH 

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

instructions of Airbus SB A300-57-0255, A310-57-2101, A300-57-6112, 

or A300-57-9024, at original issue, as applicable to aeroplane model.

Table 2

Aeroplane Type DVI Interval NDT Interval

A300B4/C4/F4, A300-600 

and A300-600ST

550 FC 1 000 FC

A310 775 FC 1 300 FC

(14) If, during any NDT as required by paragraph (12) or (13) of this AD, a 

discrepancy is detected, before next flight, report to Airbus and 

accomplish concurrently a one-time DVI in accordance with the 

instructions of Airbus SB A300-57-0255, A310-57-2101, A300-57-6112, 

or A300-57-9024, as applicable to aeroplane model.

(15) If, during the DVI as required by paragraph (14) of this AD, no crack is

detected, at intervals not to exceed 100 FC, repeat the DVI in 

accordance with the instructions of Airbus SB A300-57-0255, A310-57-

2101, A300-57-6112, or A300-57-9024, at original issue, as applicable to 

aeroplane model.

(16) If, during any DVI as required by paragraph (12), (13), (14) or (15) of this 

AD, as applicable, a crack is detected, before next flight, contact Airbus 

for approved repair instructions and accomplish those instructions 

accordingly.

(17) Within 60 days after accomplishment of the inspection as required by 

paragraph (12) of this AD, report the inspection results (including no 

findings) to Airbus. For that purpose, inspection report sheet provided in 

Airbus SB A300-57-0255, A310-57-2101, A300-57-6112 or A300-57-

9024 may be used, at original issue, as applicable to aeroplane model.

Ref. Publications: Airbus ASB A300-57A0248 Original issue dated 12 December 2006,

Airbus SB A300-57-0249 Revision 3 dated 18 January 2012,

Airbus SB A300-57-0251 Original issue dated 08 August 2007, and
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Airbus SB A300-57-0255 Original issue dated 13 January 2012.

Airbus ASB A310-57A2088 Original issue dated 06 November 2006,

Airbus SB A310-57-2090 Revision 3 dated 23 January 2012,

Airbus SB A310-57-2091 Original issue dated 22 May 2007, and

Airbus SB A310-57-2101 Original issue dated 13 January 2012.

Airbus ASB A300-57A6105 Original issue dated 12 December 2006,

Airbus SB A300-57-6107 Original issue dated 08 August 2007,

Airbus SB A300-57-6106 Revision 3 dated 23 January 2012, and

Airbus SB A300-57-6112 Original issue dated 13 January 2012.

Airbus SB A300-57-9019 Revision 3 dated 18 January 2012, and

Airbus SB A300-57-9024 Original issue dated 13 January 2012

Airbus Repair Instructions R57240425 Issue A, 57249389 Issue A, 

R57240221 Issues A to G or R57249121 Issues A to G.

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 05 June 2012 as PAD 12-061 for consultation until 

03 July 2012. The Comment Response Document can be found at 

http://ad.easa.europa.eu.

3. Enquiries regarding this AD should be referred to the Safety Information

Section, Executive 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 – EIAW (Airworthiness Office,

Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).