EASA AD No : 2011-0187

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0187

Date: 27 September 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 app licable ADs. Consequently, no person may opera te an aircraft to which an AD, except in accordance with the requirement s of that AD unless otherwise specified by the Agency [EC 204 2/2003 Annex I, Part M.A.303] or agreed with the Authority of t he State of Registry [EC 216/2008, Article 14(4) exemption]. 

### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :
A310 aeroplanes

TCDS Number : France N° 145

Foreign AD : Not applicable

Supersedure : None



### ATA 57 Wings – Slats # 2 and 3, Extension Bolts at Tracks 4, 5, 6, 7 and 8 – Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: A310-203, A310-221 and A310-222 aeropl anes, all manufacturer serial numbers (MSN), except MSN 0415, 0419, 0424, 0427, 0430, 0454, 0468, 0486 and 0487.

Reason: Slat extension eccentric bolts have been re-classified as Pr incipal Structural Elements (PSE). As a result, associat ed fatigue lives will be published in the Airbus A310 Airworthiness Limitations Section (ALS) Part 1 and bolts must be replaced at or before their calculated fatigue lives. The slat extension eccentric bolt Part Number (P/N) A5786451220800 installed at slat 2, track 6 of the left hand (LH) and right hand (RH) wings is manufactured by SONACA, but some bolts with the same P/N, manufactured by FOKKER, may have been installed on A310-200 series aeroplanes and are identical in appearance. The calcul ated fatigue life of the FOKKER bolt is lower than that of the SONACA equivalent bolt.
The difference between the FOKKER and SONACA bolt cannot be distinguished by a visual inspection. To remedy this, the SONACA bolt part number was changed from P/N A5786451220800 to P/N A5784307920000. Failure to replace the bolts within the new fatigue life limits constitutes an unsafe condition. For the reasons described above, this AD requires the replacement of all slat extension eccentric bolts, P/N A5786451220800, with sl at extension eccentric bolts P/N A5784307920000 at the slat 2 tracks 4, 6 and 7 positions, as well as at the slat 3 track 8 position, on both LH and RH wings,. In addition, it is required to replace the slat extension eccentric bolt P/N A57843624200 at slat 2 track 5 with a bolt P/N A57843624202.EASA AD No : 2011-0187

EASA Form 110 Page 2/2 Effective Date: 11 October 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) At the time indicated in paragraph (1.1) or (1.2) of this AD, whichever occurs later, replace the slat extension eccentric bolts P/N A5786451220800 at slat 2 track 6 on both wings of the aeroplane with bolts P/N A5784307920000, in accordance with the Accomplishment Instructions of Airbus Service Bu lletin (SB) A310-57-2043 Revision 05. (1.1) Before accumulating 14 000 flight cycles (FC) or 19 000 flight hours (FH), whichever occurs first, or (1.2) Within 6 months after the effective date of this AD. (2) Concurrent with the replacement as required by paragraph (1) of this AD, visually inspect each removed bolt P/N A5786451220800 to detect cracks, in accordance with the Accomp lishment Instructions of Airbus SB A310-57-2043 Revision 05. (3) If a P/N A5786451220800 bolt, inspected as required by paragraph (2) of this AD, is found cracked, concurrent with the replacement of that bolt from slat 2 track 6, RH or LH, as applicable, replace the slat extension eccentric bolt P/N A57843624200 at slat 2 track 5, RH or LH, as applicable, with a bolt P/N A57843624202, in accordance with Accomplishment Instructions of Ai rbus SB A310-57-2099 original issue. (4) If a P/N A5786451220800 bolt, inspected as required by paragraph (2) of this AD, is not found cracked, before accumulating 35 900 FC or 71 800 FH, whichever occurs first, replace t he slat extension eccentric bolt P/N A57843624200 at slat 2 track 5, RH or LH, as applicable, with a bolt P/N A57843624202, in accordance with Ac complishment Instructions of Airbus SB A310-57-2099 original issue. (5) In addition to the bolt replacement actions as required by paragraphs (1), (3) and (4) of this AD, as applicable, within 30 months after the effective date of this AD, replace the slat extension eccentric bolts P/N A5786451220800 at slat 2 track 4 and tr ack 7 and slat 3 track 8 on both wings with bolts P/N A57843079200, in accordance with Accomplishment Instructions of Airbus SB A310-57-2098 original issue. (6) After modification of an aeroplane as required by this AD, do not install any slat extension eccentri c bolt P/N A5786451220800 on that aeroplane.

Ref. Publications: Airbus SB A310-57-2043 Revision 05, dated 29 September 2010; Airbus SB A310-57-2098 original issue, dated 22 July 2011; Airbus SB A310-57-2099 original issue, dated 22 July 2011. The use of later approved revisions of these documents is acceptable for compliance with 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 24 August 2011 as PAD 11-092 for consultation until 21 September 2011. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Safety Information 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).