TYPE: Long-range business tri-jet.
PROGRAMME: Announced, under temporary name/designation Falcon Next/NXT, at the Paris Air Show in June 2001; then became Falcon FNX; formal designation Falcon 7X announced 29 October 2001. By September 2002, high- and low-speed wind tunnel tests had been conducted at the ONERA facilities in Modane and Toulouse and in the European Transonic Wind Tunnel at Cologne, Germany; design freeze and final wind tunnel confirmation of performance projections were scheduled for second quarter 2003. First flight due early 2005; certification scheduled for mid-2006; first customer deliveries anticipated in late 2006.
CUSTOMERS: Market estimated at 400 aircraft over unspecified period. Total of 40 orders held by October 2002, split approximately evenly between US and other customers.
COSTS: Development cost estimated at US$600 million to US$700 million. Unit cost US$35 million to US$37 million (all 2002).
DESIGN FEATURES: Similar in configuration to Falcon 900C/900EX, but with cabin some 20 per cent longer, redesigned nose double curved windscreen panels and an entirely new high-subsonic section wing with 20 per cent fewer parts, 5° more sweepback, (34° on inboard section, 30° on outboard section), 40 per cent more area and featuring full-span, two-section leading-edge slats. The wing design will be employed on future developments within the Falcon range, expected to be designated Falcon 5X and 9X.
FLYING CONTROLS: Fly-by-wire controls, with sidestick controllers.
STRUCTURE: Total of 21 programme partner suppliers announced by May 2003, including: CASA (horizontal stabiliser); Fokker (trailing-edge control surfaces); Hurel Hispano/Aermacchi (engine nacelles and thrust reversers); Latecoere (T5 fuselage section); Socata (T34 upper fuselage section and body fairing); Sonaca (wing leading-edges); and Sully Saint Gobain (windscreen and cabin windows). Final assembly in new 25,000 m2 (269,097 sq ft) facility at Bordeaux.
LANDING GEAR: Retractable tricycle type by Messier-Dowry. Wheels and brakes by ABSC. Steerable nosewheel ± 60°. Minimum ground turning radius 8.80 m (61 ft 8 in).
POWER PLANT: Three Pratt & Whitney Canada PW307A turbofans, each flat-rated to 27.1 kN (6,100 lb st) at ISA +18°C. Usable fuel capacity 16,326 litres (4,313 US gallons; 3,591 Imp gallons).
ACCOMMODATION: Typical configuration will provide three lounge areas, berthing capability for six passengers, lavatories, galleys, crew rest area and a large flight-accessible baggage compartment Pressunsation system will provide a 1,830 m (6,000 ft) cabin environment at high cruise altitudes.
SYSTEMS: Honeywell air management system. Pressurisation system maintains 1,830 m (6.000 ft) cabin environment at maximum operating altitude. Honeywell 35-150(FN) APU. Honeywell/Parker hydraulic power generation system. Parker hydraulic system; Intertechnique oxygen system; L'Hotelier fire detection and extinguishing; TRW electrical generation and distribution.
AVIONICS: Dassault EASy flight deck as core system, incorporating Honeywell Primus Epic platform.
