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 applicable ADs. Consequently, no person may operate an 

aircraft to which an AD, 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]. 

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 aeroplanes, 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 Principal Structural 

Elements (PSE). As a result, associated 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 calculated 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 slat 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 Bulletin (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 Accomplishment 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 Airbus 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 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 

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 track 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 eccentric 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 technical 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).