TYPE: Business jet.
PROGRAMME: Announced Paris Air Show 1989 as Falcon X: follow-on to Falcon 20/200; launched as Falcon 2000 on 4 October 1990, following first orders: Alenia joined as 25 per cent risk-sharing partner February 1991, with responsibility for rear fuselage section and engine nacelles; selection of CFE738 engine announced 2 April 1990: first flight (F-WNAV) 4 March 1993: one prototype only; third airframe (F-WWFA) was second to fly, on 10 May 1994; ferried 'green' to US subsidiary Dassault Falcon Jet Corporation at Little Rock. Arkansas, 13 July 1994 for completion as US demonstrator, and set two world speed records 31 October to 1 November 1994 flying Los Angeles (Chino) to Bangor, Maine, in 4 hours 36 minutes 27 seconds and Bangor to Paris in 5 hours 26 minutes 12 seconds: Dassault demonstrator, second airframe (F-WNEW), flew 11 July 1994. JAA certification to JAR 25 obtained 30 November 1994. at which time five aircraft (prototype, two demonstrators and two customer aircraft) had accumulated 1.055.5 flight hours; FAR Pt 25 and FAR Pt 36 Stage 3 noise levels certification 2 February 1995; first delivery (F-WNEW/ ZS-NNF to South African customer) 16 February 1995. Approved to operate into London City Airport during 1996. Commonwealth of Independent States certification 14 April 1997. HGS-2850 HUD first flown in prototype 8 December 1995; initial JAA certification granted 30 August 1996, followed by approval for lowvisibility take-offs (down to 91 m; 300 ft RVR) and handflown Cat. II and Cat. IIIa instrument approach approved by FAA 30 July 1997. Full JAA certification 16 December 1997; FAA certification 18 May 1998.
Falcon 2000: Initial production version. As described.
Falcon 2000EX: Extended-range version. Development began October 1999; announced at the NBAA Convention in New Orleans. 10 October 2000. Prototype (c/n 01/F-WMEX) rolled out 19 July 2001 and first flown 25 October 2001: two aircraft (F-WMEX and c/n 02/F-W66A). Completed 568 hours of flight testing in 242 flights, culminating in JAA and FAA certification on 25 March 2003; first three 'green' production airframes delivered to Little Rock completion centre in January 2003, with first customer deliveries of outfitted aircraft expected in the second quarter of2003 (Pro Line avionics). EASy flight deck available from second quarter of 2004. Falcon 2000EX manufactured in parallel with Falcon 2000.
New features include two Pratt & Whitney Canada PW308C turbofans, with FADEC, each rated at 31.1 kN (7,000 lb st) for take-off at ISA +15°C; Nordam advanced single pivot (ASP) thrust reversers; revised fuel system with 2,045 kg (4,508 lb) increase in usable fuel capacity to 9,414 litres (2,487 US gallons; 2,071 Imp gallons: strengthened main landing gear with heavy-duty braking system and Falcon 900EX nose landing gear; and new bleed air system. The first 40 Falcon 2000EXs will retain the current Collins Pro Line 4 avionics suite, but aircraft delivered from March 2004 will be equipped with Dassault EASy flight deck with four-tube flat panel displays based on those of the Honeywell Primus Epic modular avionics system and designated Falcon 2000EX EASy; first flight with EASy cockpit F-WXEY) 29 January 2003.
CUSTOMERS: The 206th Falcon 2000 was delivered to the USA for outfitting on 10 December 2003. Production totalled 20 in 1997, 15 in 1998 34 in 1999, 26 in 2000, 35 in 2001, 35 in 2002 and three in the first three months of 2003. Falcon 2000 No. 159/N259QS, delivered to Executive Jet on 11 September 2001, was also 1,500th Falcon/Mystere business jet produced by Dassault. Total of 72 Falcon 2000s, and 28 Falcon 2000EXs, plus 25 Falcon 2000EXs on option, ordered by Executive NetJets and NetJets Middle East fractional ownership programmes in Europe, Middle East and USA, of which 38 were in operation by October 2002. Royal Australian Air Force ordered three in 2000 to replace five leased Falcon 900s. Total market estimated at more than 300 in 10 years.
COSTS: Basic price 2000 US$20.6 million (2001); 2000EX US$24 million (2000).
DESIGN FEATURES: Same fuselage cross-section as Falcon 900, but 1.98 m (6 ft 6 in) shorter. Falcon 900 wing with modified leading-edge and no inboard slats; sweepback at quarter-chord 24° 50' to 29°.
STRUCTURE: Largely as for Falcon 900. Rear tuselage. including engine pods and pylons, by Alenia and Piaggio: thrust reversers by Dee Howard. Agreement reached in early 2002 for production of fuselage components of 2000EX by Chengdu Aircraft of China. New horizontal tail surface featuring cast titanium central box with resin transfer moulding composite spars and carbon fibre skin panels, resulting in a 13.6 kg (30 lb) reduction in weight, certified by the DGAC in December 1999 and introduced as standard from December 2000 deliveries.
LANDING GEAR: Retractable tricycle type; mainwheels retract inwards, nosewheel forwards. Main tyres 26x6.6R14 (14 ply) tubeless; nose 14.5x5.5R6 tubeless. Tyre pressures: 2000 main 13.6 bar (197 lb/sq in), nose 11.1 bar (161 lb/ sq in); 2000EX main 15.1 bar (219 lb/sq in), nose 12.6 bar (183 lb/sq in). Steerable nosewheel (±60°). Minimum turning radius on ground 15.03 m (49 ft 33/4 in).
POWER PLANT: Two GE/Honeywell CFE738-1-1B turbofans, each rated at 26.3 kN (5,918 lb st) at ISA + 15°C. Usable fuel capacity 6.865 litres (1,814 US gallons; 1,510 Imp gallons). Dee Howard clamshell-type thrust reversers certified by FAA and JAA during 1995.
ACCOMMODATION: Up to 19 passengers and two flight crew; standard passenger accommodation is four seats in forward lounge and four seats and a two-person sofa in aft lounge. Pressurised, flight accessible baggage compartment at rear of cabin.
AVIONICS: Rockwell Collins Pro Line 4.
Comms: Dual com/nav; dual TRD-94D Mode-S transponders; dual RTU-4420 radio tuning units; Rockwell Collins HF-9000 transceiver.
Radar: Rockwell Collins WXR-840 colour weather radar standard: TWR-850 Doppler weather radar optional.
Flight: Rockwell Collins FMS-6100 flight management system and Cat. II autopilot standard. Rockwell Collins dual DME-442, dual ADF-462; dual AHRS and dual digital air data computers linked to dual-channel integrated avionics processor system (IAPS). Dual Honeywell Laseref III, Honeywell EGPWS, IRS, second FMS (with GPS), flight data recorder, traffic alert and collision avoidance system (TCAS) and GPWS all optional.
Instrumentation: Rockwell Collins Pro Line 4 four-tube EFIS-4000. Sextant Avionique three-tube engine indicating electronic display (EIED); Flight Dynamics HGS-2850 HUD.
Mission: Optional satcom antenna in fintip pod.
Data below apply to Falcon 2000 and 2000EX unless otherwise indicated.
|Wing span||19.33 m (63 ft 5 in)|
|Wing chord (mean)||2.89 m (9 ft 53/4 in)|
|Wing aspect ratio||7.6|
|Length overall||20.22 m (66 ft 4 in)|
|Height overall||7.06 m (23 ft 2 in)|
|Wheel track||4.45 m (14 ft 71/4 in)|
|Wheelbase||7.39 m (24 ft 3 in)|
|Passenger door: - Height||1.72 m (5 ft 73/4 in)|
|- Width||0.80 m ( 2 ft 71/2 in )|
|Baggage door: - Height||0.775 m (2 ft 61/2 in)|
|- Width||0.75 m (2 ft 51/2 in)|
|Emergency exits (Type III): - Height||0.92 m (3 ft 01/4 in)|
|- Width||0.53 m (1 ft 83/4 in)|
|Cabin: Length||7.98 m (26 ft 21/4 in)|
|Width: - max||2.34 m (7 ft 81/4 in)|
|- at floor level||1.91 m (6 ft 31/4 in)|
|- Max height||1.88 m (6 ft 2 in)|
|- Volume||29.0 m3 (1,024 cu ft)|
|Baggage volume: - standard||3.7 m3 (131 cu ff)|
|- optional||5.4 m3 (191 cu ft)|
|Wings, gross||49.02 m2 (527.6 sq ft)|
|WEIGHTS AND LOADINGS:|
|Weight empty, equipped: - 2000||9,405 kg (20,735 lb)|
|- 2000EX||10,142 kg (22,360 lb)|
|Basic operating weight: 2000||9,798 kg (21,600 lb)|
|Max payload: 2000||3,202 kg (7,060 lb)|
|Max fuel weight: - 2000||5,513 kg (12,154 lb)|
|- 2000EX||7,557 kg (16,660 lb)|
|Max ramp weight: - 2000 : standard||16,329 kg (36,000 lb)|
|optional||16,647 kg (36,700 lb)|
|- 2000EX: standard||18,824 kg (41,500 lb)|
|optional||19,232 kg (42,400 lb)|
|Max T-O weight: - 2000: standard||16,238 kg (35,800 lb)|
|optional||16,556 kg (36,500 lb)|
|- 2000EX: standard||18,733 kg (41,300 lb)|
|optional||19,142 kg (42,200 lb)|
|Max landing weight: - 2000||14,970 kg (33,000 lb)|
|- 2000EX||17,826 kg (39,300 lb)|
|Max zero/fuel weight||13,000 kg (28,660 lb)|
|Max wing loading: 2000:|
|- standard||331.3 kg/m2 (67.85 Ib/sq ft)|
|- optional||337.8 kg/m2 (69.18 lb/sq ft)|
|2000EX: - standard||384.0 kg/m2 (78.65 lb/sq ft)|
|- optional||392.3 kg/m2 (80.36 lb/sq ft)|
|Max power loading: 2000 -standard||308 kg/kN (3.02 lb/lb st)|
|- optional||314 kg/kN (3.08 lb/lb st)|
|2000EX: - standard||302 kg/kN (3.49 lb/lb st)|
|- optional||309 kg/kN (3.03 lb/lb st)|
|Max operating Mach No. (MMO)||0.85-0.86|
|Max operating speed (VMO)||350-370 kt (648-685 km/h; 403-425 mph)IAS|
|Max cruising speed||M0.84 or 481 kt (891 km/h; 554 mph)|
|Normal cruising speed||M0.80 or 459 kt (850 km/h; 528 mph)|
|Long-range cruising speed||M0.75 or 430 kt (796 km/h; 495 mph)|
|Approach speed: - 2000||109 kt (202 km/h; 125 mph)|
|- 2000EX||112 kt (207 km/h: 129 mph)|
|Initial cruising altitude: at M0.80||12,497 m (41,000 ft)|
|at M0.75||13,106 m (43,000 ft)|
|Max certified altitude||14,330 m (47,000 ft)|
|Time to climb to FL410:|
|FAR Pt 25 balanced T-O field length, S/L, ISA:|
|2000: with eight passengers and max fuel||1,597 m (5,240 ft)|
|at max T-O weight||1,658 m (5,440 ft)|
|2000EX: at standard max T-O weight||1,806 m (5,925 ft)|
|at optional max T-O weight||1,884 m (6,180 ft)|
|Landing field length:|
|FAR Pt 91 with eight passengers and NBAA IFR|
|reserves||780 m (2,560 ft)|
|at max landing weight||952 m (3,125 ft)|
|2000EX with six passengers and NBAA IFR reserves||803 m (2,633 ft)|
|Range with eight passengers and NBAA IFR reserves:|
|2000: at M0.75||3,120 n miles (5,778 km; 3,590 miles)|
|at M0.80||3,040 n miles (5,630 km; 3,498 miles)|
|2000EX with max fuel, six passengers, at Mach 0.80,|
|NBAA IFR reserves||3,800 n miles (7.037 km: 4,373 miles)|
|OPERATIONAL NOISE LEVELS, 2000:|