TYPE: Business mono-jet.
PROGRAMME: Development first revealed in late 2002; first details released 14 January 2003; first flight scheduled for mid-2004 with deliveries planned from second quarter 2006. To be certified in standard and high maximum take-off weight versions for European and US markets, respectively. Eight-seat, twin-engine derivative reported to be under study in early 2003, for availability from 2008.
DESIGN FEATURES: Low-wing of laminar flow aerofoil section with moderate sweepback and small winglets; T tail; engine inlets in wingroots.
STRUCTURE: Composites throughout.
CUSTOMERS: Total of 70 orders by late April 2003.
COSTS: Unit cost €870,000; programme cost €30 million (both 2003).
POWER PLANT: Single turbofan in 11.5 kN to 12.4 kN (1,400 lb st to 1,500 lb st class; engines under consideration in mid-2003 included Pratt & Whitney Canada PW615, Williams International FJ33 and Honda light turbofan. Fuel capacity 725 litres (191.5 US gallons; 159.5 Imp gallons).
ACCOMMODATION: Five in two-plus-three seating configuration; pressurised cabin. Two cabin windows per side.
SYSTEMS: Pressurisation system, maximum differential 0.36 bar (5.2 lb/sq in) maintaining 2,440 m (8,000 ft) cabin environment to 7,620 m (25,000 ft).