EASA AD No : 2012-0042

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0042

Date: 10 April 2012

Note: This Airworthiness Directive (AD) is i ssued 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 t he 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 a ccomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Directiv e 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 [E C 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 – Slat Extension Eccentric Bolts – Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)
Applicability: A310-204, A310-222, A310-304, A310-322 and A310-324 aeroplanes, having received in production Airbus modification 04809 without Airbus modification 06243 or 13596.

Reason: Slat extension eccentric bolts have been reclassified as Principal Structural Elements (PSE). As a result, associat ed fatigue lives will be published in the Airbus A310 Airworthiness Limitation Section (ALS) Part 1 and bolts must be replaced at or before their calculated fatigue lives. Failure to replace the bolts within the new fatigue life limits constitutes an unsafe condition. For the reasons explained above, this AD requires: - for A310-300 aeroplanes, the replacem ent of slat extension eccentric bolts, Part Number (P/N) A57844015200, with slat extension eccentric bolts P/N A57844015204 at the slat 2 tracks 4 and 7 and slat 3 track 8 positions on both Left Hand (LH) and Right Hand (RH) wings, and - for A310-300 and A310-200 aeroplanes t hat incorporate Airbus modification 04809, the replacement of slat ex tension eccentric bolts, P/N A57843624200 and associated washers P/N A57844016200, wi th slat extension eccentric bolts P/N A57843624202 and washers P/N A5784 4391200 at the slat 2 track 5 position, on both LH and RH wings.
Effective Date: 24 April 2012EASA AD No : 2012-0042

EASA Form 110 Page 2/2 Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within the compliance time indicated in Table 2 of this AD, as applicable, accomplish the replacement actions as specified in Table 1 of this AD, as applicable, in accordance with the inst ructions of Airbus Service Bulletin (SB) A310-57-2100 Revision 1. Table 1 – Actions and Applicability Aeroplane applicability Require d Action(s) on both Wings A310-300 aeroplanes Replace t he slat extension eccentric bolts P/N A57844015200 at the slat 2 tracks 4 and 7 and slat 3 track 8 positions with bolts P/N A57844015204 A310-300 aeroplanes and A310-200 aeroplanes that have incorporated Airbus modification 04809 Replace the slat ex tension eccentric bolts P/N A57843624200 at the slat 2 track 5 position with bolts P/N A57843624202 Replace the associ ated washers of eccentric bolts P/N A57844016200 at the slat 2 track 5 position with washers P/N A57844391200 Table 2 – Compliance time Affected aeroplanes Compliance time since aeroplane first flight (whichever occurs first) A310-300 aeroplanes operated with an average flight time (AFT) less than 4 hours 66 000 flight hours (FH) or 40 000 flight cycles (FC)

A310-300 aeroplanes operated with an AFT of 4 hours or more 66 000 FH or 31 400 FC

A310-200 aeroplanes with Airbus modification 04809 71 800 FH or 35 900 FC

Note: To establish the AFT, take the accu mulated flight time (counted from the take-off up to the landing) and divide it by the number of accumulated flight cycles. This gives the averag e flight time per flight cycle. (2) After modification of an aeroplane as required by this AD, do not install any slat extension eccentric bolt P/N A57844015200 or P/N A57843624200 with associated washer A57844016200 on that aeroplane.
Ref. Publications: Airbus SB A310-57-2100 Revision 1, dated 03 February 2012. The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately subs tantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 10 February 2012 as PAD 12-011 for consultation until 09 March 2012. No comments were received during the consultation period. 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 tec hnical content of the requirements in this PAD, please contact: AIRBUS SAS – EIAW (Airworthiness Office, Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).