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 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 Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Directive 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) : 

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, associated 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 replacement 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 that incorporate Airbus modification 

04809, the replacement of slat extension eccentric bolts, P/N A57843624200 

and associated washers P/N A57844016200, with slat extension eccentric bolts 

P/N A57843624202 and washers P/N A57844391200 at the slat 2 track 5 

position, on both LH and RH wings. 

Effective Date: 24 April 2012 
EASA 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 instructions of Airbus Service Bulletin 

(SB) A310-57-2100 Revision 1. 

Table 1 – Actions and Applicability 

Aeroplane applicability Required Action(s) on both Wings 

A310-300 aeroplanes Replace the 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 extension eccentric 

bolts P/N A57843624200 at the slat 2 

track 5 position with bolts P/N 

A57843624202 

Replace the associated 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 accumulated flight time (counted from 

the take-off up to the landing) and divide it by the number of accumulated 

flight cycles. This gives the average 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 substantiated, 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 technical 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).