E ASA AD No : 20 12
- 0176

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- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No
. : 20 12 - 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 Communit y, 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 ope rate 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) exempt ion]. 

### 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
F oreign 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 d ated 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
- 600 ST 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 lu g. This condition, i f 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 AD s 2006
- 0372R1, 2007
- 0195, 2010
- 0250 and 2010
- 0251 were issued to address this condition and required a repetitive inspection program me 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 i s a similar de sign to the A300/A300
- 600/A310 f amily. Since those ADs were issued, o n two A321 aeroplane s , 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 ha ve shown that a remaining defect , not removed during the repair , had propagated,E ASA AD No : 20 12
- 0176

CA P.00110
- 001 © European Aviation Safety Agency. All rights reserved. 2 / 5 Proprietary docu ment. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. resulting in rupture of the lug. For the r eason s stated above , this new AD retains the requirements of EASA AD s 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
- 600 ST aeroplanes , and requires:

- for aeroplanes not yet modified or repaired, implementation of M odification Service Bulletin ( SB ) A300
- 57
- 0249, A310
- 57
- 2090, A300
- 57
- 6106, or A300
- 57
- 9019 , all at Revision 3 , and

- for aeroplane s which already embody that modification s , at original issue o r revision 0 1 or 0 2 of the applicable SB , or have ML G Rib s already repaired in accordance with Airbus repair instruction R57240221 or R572 49121 , implementation of an additional inspection programme and associated corrective action (s)

. This AD has been republish ed to c orrect 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 depend ent on this status. P ar agraphs (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 - 2 090 , A300 - 57 - 6106, or A300 - 57 - 9019 , as applicable to aeroplane model, at original issue , R evision 0 1 , or R evision 0 2 , has not been embodied in service [Airbus modification (mod.) 13329/13348/19619)] and to aeroplanes with MLG Rib s 5 not repaired in accorda nce 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 , b efore accumulating 12 000 f light c ycles (FC) since first flight , or since MLG Rib 5 replacement , as applicable , or w ithin 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 instru ctions 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) A fter the inspection as required by paragraph (1) of this AD , accomplish a DVI at interval s 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 Airbu s a nd 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 SBE ASA AD No : 20 12
- 0176

CA P.00110
- 001 © European Aviation Safety Agency. All rights reserved. 3 / 5 Proprietary docu ment. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. A300
- 57
- 6107, at original issue, as applicable to aeroplane model

. ( 5 ) I f, 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 EAS A 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 w ithin 100 FC after the latest DVI accomplished in accordance with the instructions of Airb us 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 201 0
- 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/sealin g process
. ( 8 ) For A300 - 600, A310 , A300 - 600ST and A300B4/C4/F4 series aeroplanes , w ithin 30 months after 13 December 2010 [the effective date of the EASA AD 2010
- 0251] , install new bushes with increased interference fit in t he gear Rib 5 aft bearing forward lug on RH and LH wing s in accordance with the instructions of Airbus SB A300
- 57
- 0249 R evision 3 , SB A310
- 57
- 2090 R evision 3, SB A300
- 57
- 6106 R evision 3, or SB A300
- 57
- 9019 R evision 3 , as applicable to aeroplane model. ( 9 ) Modification of a MLG Rib 5 o n 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

. (1 0 ) Repair of a MLG Rib 5 in accordance w ith Airbus repair instruction R57240425 or R 57249389 , 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

. (1 1 ) For A300B2 series aeroplanes , r epair 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: P aragraphs (12), ( 13 ), ( 14 ), ( 15 ), ( 16 ) and (1 7 ) 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 , R evision 0 1 , or R evision 0 2 , ha s been embodied in service , and to aeroplane s with ML G Rib 5 already repaired in accordance with Airbus repair instruction R57240221 or R57249121
. Note 3 : A n aeroplane with the MLG Rib 5 forward lugs repaired on one wing, by installation of oversized inte rference 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. ( 1 2 ) For A300B4/C4/F4 series , A310, A300 - 600 and A300 - 600ST aeroplanes , w ithin the threshold indicated in T able 1 of this AD , asE ASA AD No : 20 12
- 0176

CA P.00110
- 001 © European Aviation Safety Agency. All rights reserved. 4 / 5 Proprietary docu ment. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. applicable, accomplish a DVI or an ultrasonic inspection of the LH and RH MLG Rib 5 aft bearing forward lugs in accordance with the instruc tions of Airbus SB A300
- 57
- 0255 , A310
- 57
- 2101 , A300
- 57
- 6112, or A3 00
- 57
- 9024 , at original issue, as applicable to aeroplane model.

Table 1 A eroplane Type Compliance Time
– Whichever occurs later A300B4/C4/F4, A300
- 600 and A300
- 600ST Within 2 500 FC after the modification or repair accomplishment, o r Within 550 FC aft er the effective date of this AD

A310 Within 2 500 FC after the modification or repair accomplishment, o r Within 775 FC after the effective date of this AD
( 1 3 ) A fter the inspection as required by paragraph ( 1 2 ) of this AD , at intervals not to exceed th e 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
- 611 2, or A300
- 57
- 9024 , at original issue, as applicable to aeroplane model. Table 2 A eroplane Type DVI Interval NDT Interval A300B4/C 4 /F4, A300
- 600 and A300
- 600ST 550 FC 1 000 FC
A310 775 FC 1 300 FC
(1 4 ) If, during any NDT as required by paragraph ( 1 2 ) o r (1 3 ) 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 aerop lane model

. (1 5 ) If, during the DVI as required by paragraph ( 1 4 ) 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

. (1 6 ) If, during any DVI as required by paragraph ( 12 ) , (1 3 ), ( 1 4 ) or (1 5 ) of this AD, as applicable, a crack is detected, before next flight, contact Airbus for approved repair instructions and accompl ish those instructions accordingly. ( 1 7 ) W ithin 6 0 days after accomplishment of the inspection as required by paragraph ( 1 2 ) of this AD , report the inspection results (including no finding s ) 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 O riginal issue dated 12 Dec ember 2006 , Airbus SB A300
- 57
- 0249 Revision 3 dated 18 January 2012, Airbus SB A300
- 57
- 0251 O riginal issue dated 08 August 2007, andE ASA AD No : 20 12
- 0176

CA P.00110
- 001 © European Aviation Safety Agency. All rights reserved. 5 / 5 Proprietary docu ment. Copies are not controlled. Confirm revision status through the EASA
- Internet/Intranet. Airbus SB A300
- 57
- 0255 O riginal issue dated 13 January 2012. Airbus ASB A310
- 57A2088 O riginal 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 O riginal issue dated 12 December 2006 , Airbus SB A300
- 57
- 6107 Original issue dated 08 August 2007 , Airbu s SB A300
- 57
- 6106 Revision 3 dated 23 January 2012 , and Airbus SB A30 0
- 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 Inst ructions R57240425 Issue A , 57249389 Issue A , R57240221 Issue s A to G or R57249121 Issue s 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 appropriatel y 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 regardi ng 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 conte nt of the requirements in this AD, please con tact: AIRBUS SAS

– E I AW (Airworthiness Office, Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).