E ASA AD No : 20 14

- 0 115

TE.CAP.00110

- 003 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 4

- 0 115

Date: 13 May 201 4

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 EU 748/2012, Part 21.A.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 :

DASSAULT AVIATION Type/Model designation(s) :

Falcon 2000EX and Falcon 900EX aeroplanes

TCDS Number s : EASA. A.008 and EASA.A. 062

F oreign AD: Not applicable

Supersedure: None



### ATA 57 Wings

– Slat E xtension M echanical S top A ssembly

– Modification

Manufacturer(s): Dassault Aviation

Applicability: Falcon 2000EX aeroplanes , all serial numbers (S / N) on which Dassault Aviation modification (Mod) M284 6 has bee n e mbod ied

, except those on which Dassault Aviation Mod M3678 has been embodied in production

. Falcon 900EX aeroplanes , all S / N on which Dassault Aviation Mod M 5281 has been embodied

, except those on which Dassault Aviation Mod M5870 has been embodied in production.

Reason: A fter landing, a n aer o plane experienced a significant fuel leakage at the middle position of the left outboard slat. Investigations showed that the fuel spill age originated in a structural cap

, which had been punctured by a broken locking pin of the slat extension mechanical stop

. A design review revealed that the locking pin could become loose due to an incorrect installation combined with a non

- fault

- tolerant design

. T his condition, if not corrected, may lead to a significant fuel leak

, possibly result ing in an uncontained fire

. To address this potential unsafe condition, Dassault Aviation developed a modification of the slat extension mechanical stop assembly ( Mod M3678 for F2000EX aeroplanes and Mod M5870 for F900EX aeroplanes ) with the purpose to increase its robustness with regard s to possible mishandling on production or durin g maintenance. Dassault Aviation also published Service Bulletin (SB) F2000EX

- 344 and SB F900EX

- 45 0, for embodiment in service of th at modification

. For the reasons described above, this require s modification of the slatE ASA AD No : 20 14

- 0 115

TE.CAP.00110

- 003 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. extension mechanical stop assembly

.

Effective Date: 27 May 2014

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously :
Within 9 months or 440 flight hours

, whichever occurs first after the effective date of this AD

, modify the slat extension mechanical stop assembly in accordance with the accomplishment instructions of Dassault Aviation SB 2000EX

- 344 or Dassault Aviation SB F900EX

- 45 0

, as applicable to aeroplane.

Ref. Publications: Dassault Aviation SB F 2000 EX

- 344

, initial issue , dated 10 March 2014

. Dassault Aviation SB F 9 00EX

- 450

, initial issue, dated 10 March 2014

. The use of later approved revisions of these documents 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 24 March 2014 as PAD 14

- 0 54 for consultation until 21 April 2014. No comments were received during the consultation period

. 3. Enquiries regarding this AD sho uld 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, contact your Dassault Falcon Technical Assistance:

 For Europe, Middle East and Africa based operators: Hot Line: (33) 1 47 11 37 37 / Fax: (33) 1 47 11 89 49.

 For USA, Canada and Mexico based operators: Help Desk: (1) 800

- 2FALCON (2325266) / Fax: (1) 201 541 4740.

 All other areas : Help Desk: (1) 201 541 4747 / Fax: (1) 201 541 4740.