TYPE: Business turboprop.

PROGRAMME: Launched by Farnborough-Aircraft.com Ltd 14 October 1999, at which time initial wind tunnel testing had been completed. Further wind tunnel testing verified laminar wing design and performance of Fowler flap system. Assets of original company acquired by FACL mid-2002; this company actively seeking investment to complete development and place aircraft in production.

CUSTOMERS: Intended for air taxi operators providing on-demand point-to-point travel from small airfields. Initial market estimated to be 250 per year from 2007.

COSTS: Development and production tooling US$125 million; unit cost, equipped US$2 million (2003).

DESIGN FEATURES: Designed with heavy reliance on computational fluid dynamics, backed up by wind tunnel tests. Design goals include ability to operate from small airstrips, carrying five passengers at up to 325 kt (602 km/h; 374 mph) over a range of 1,000 n miles (1,852 km; 1,150 miles) with NBAA IFR reserves. Sidestick controls; low-rpm propeller for low noise.
Wing aerofoil proprietary High-Lift, Laminar Flow sections: HLLF29155 at root, HLLF13130 at tip.

FLYING CONTROLS: Unpowered sidestick connected to conventional controls; 30 per cent chord Fowler flaps occupy approximately two-thirds span. Novel Fowler mechanism retracts almost entirely into wing.

STRUCTURE: Primarily carbon composites; fuselage of carbon fibre skins with foam core, moulded in two vertically split halves; carbon fibre wing with aluminium alloy landing gear pick-up ribs, flap tracks and aileron attachments.

LANDING GEAR: Retractable tricycle type; trailing-link main units retract inwards, nosewheel rearwards.

POWER PLANT: One 908 kW (1,218 shp) Pratt & Whitney PT6A-60A turboprop, flat rated at 634 kW (850 shp).

ACCOMMODATION: Pilot and five passengers in pressurised cabin, maximum pressure differential 0.55 bar (8.0 lb/sq in) maintaining sea level cabin altitude to 5.790 m (19,000 ft). Three cabin windows on each side; door on starboard side aft of wing; overwing emergency exit on starboard side. Optional lavatory at rear of cabin. Alternative configurations for commuter, medevac and cargo applications.

AVIONICS: 'Glass cockpit' compatible with existing and planned ATC procedures and GPS-based en-route navigation and airfield approach systems. Weather radar in wingtip pod.

DIMENSIONS, EXTERNAL:

• Wing span: 12.39 m (40 ft 8 in)
• Wing aspect ratio: 8.4
• Length overall: 11.10 m (36 ft 5 in)
• Height overall: 4.24 m (13 ft 11 in)

DIMENSIONS, INTERNAL:

• Cabin: Length: 3.51 m (11 ft 6 in)
• Max width: 1.40 m (4 ft 7 in)
• Max height: 1.40 m (4 ft 7 in)

AREAS:

Wings, gross: 18.30 m² (197.0 sq ft)

WEIGHTS AND LOADINGS:

• Operating weight empty: 1,783 kg (3,930 lb)
• Max fuel weight: 758 kg (1,671 lb)
• Max payload: 567 kg (1,250 lb)
• Payload with max fuel: 174 kg (383 lb)
• Max T-O weight: 2,700 kg (5,954 lb)
• Max landing weight: 2,566 kg (5,656 lb)
• Max ramp weight: 2,714 kg (5,984 lb)
• Max zero-fuel weight: 2,350 kg (5,180 lb)
• Max wing loading: 147.6 kg/m² (30.22 lb/sq ft)
• Max power loading: 4.26 kg/kW (7.00 lb/shp)

PERFORMANCE (estimated):

• Max operating speed (V_MO): 256 kt (474 km/h; 294 mph)
• High cruising speed at FL300: 325 kt (602 km/h; 374 mph)
• Long-range cruising speed at FL300: 208 kt (385 km/h; 239 mph)
• Stalling speed, flaps and landing gear down: 59 kt (110 km/h; 68 mph)
• Time to 7,620 m (25,000 ft): 10 min
• Service ceiling: 10,670 m (35,000 ft)
• T-O run: 470 m (1,540 ft)
• Range with max fuel: 1,548 n miles (2,866 km; 1,781 miles)
• Range with 363 kg (800 lb) payload, NBAA IFR reserves, 100 n mile (185 km; 115 mile) alternate: 884 n miles (1,637 km; 1,017 miles)
• Ferry range: 1,833 n miles (3,394 km; 2,109 miles)

The article appears in the following publication:
Jane's All the World's Aircraft 2004-2005. Jane's Information Group Ltd. 2004. ISBN: 0-7106-2614-2