EASA AD No : 20 1 4

- 0 061

TE. CAP.0011 0

- 00 3 © 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 - 0 061

Date: 11 March 2014

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 co ntinuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 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) exemption]

. 

### Design Approval Holder’s Name: DASSAULT AVIATION Type/Model designation(s): Falcon 9 00 , Falcon 900EX, Falcon 2000 and Falcon 2000EX aeroplanes

TCDS Number: EASA.A.062 and EASA.A. 008 Foreign AD: Not applicable Supersedure: None



### ATA 2 5 Equip ment / Furnishings
– Cockpit S eat / Locking S prings
– Replacement

Manufacturer(s): Dassault Aviation Applicability: Falcon 900, Falcon 900EX, Falcon 2000 and F2000EX aeroplanes which are equipped with SICMA 132

- series or 142

- series pilot and co

- pilot seats.

Reason: During take

- off at rotation , a co - pilot reported to slide aft on his seat

. The results of the i nvestigations concluded that one spring of the seat locking system was broken and the other was weak

. The root cause was determined to be fatigue wear. As springs accumulate cycles in service , they become increasingly exposed to the risk of unnoticed degradation or rupture

. This condition, if not corrected, could cause the pilot or the co

- pilot to lose contact with the controls, leading to an inadvertent input on the flight control commands during take

- off or climb, possibly resulting in loss of contr ol of the aeroplane

. To address this unsafe condition, it was decided to require replacement of the affected seat springs for older aero planes and for newer aeroplanes; this task has been embodied in the aeroplane maintenance manual. For the reasons descri bed above, this AD requires replacement of the spring s installed on the pilot and co

- pilot seats with serviceable springs.
Effective Date: 25 March 2014EASA AD No : 20 1 4

- 0 061

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved

. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s): Required as indicated, unless accomplished previously : (1) For aeroplanes that , on the effective date of this AD, have accumulated more than 3 750 flight cycles or have exceeded 74 months since aeroplane first flight, whichever occurred first, w ithin 9 months after the effective date of this AD, replace each spring Part Number (P/N) 132100

- 19 and P/N 147100

- 19 installed on the pilot and co

- pilot seats with a spring as specified in, and in accordance with the accomplishment instructions of Dassault Aviation Service Bulletin (SB) F900

- 429, SB F900EX

- 446, SB F2000

- 401 or SB F2000EX

- 267 , as applicable t o aeroplane type

. (2) From the effective date of this AD , install ation of a spring P/N 132100

- 19 or P/N 147100

- 19 on an aeroplane is allowed, provided the spring is new.

Ref. Publications: Dassault Aviation SB F900

- 429, F900EX

- 446, F2000

- 401, F2000EX

- 267 , all dated 15 May 2012

. The use of later approved revisions of th e s e document s 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 30 January 2014 as PAD 1 4

- 0 25 for consultation until 27 February 2014. The Comment Response Document can be found at http://ad.easa.europa.eu

. 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 conte nt of the requirements in this AD, please 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) 201 541 474 0