TYPE: Light utility turboprop.

PROGRAMME: Launched (as WF 600W) 1999; construction of first prototype began May 2001, at which time first flight planned for following September, but not achieved until 30 January 2003 (following roll-out on 16 July 2002 and first 'hop' on 4 December 2002); public debut (I-VAVF) at Paris Air Show 14 June 2003; manufacture of first production aircraft scheduled for 2003. JAA/FAA Pt 23 certification expected by end of 2003, with first customer deliveries in early 2004.

CUSTOMERS: Aimed at cargo/feeder market, law enforcement/security agencies, paratrooping and military logistics support.

COSTS: Unit cost approximately US$1 million (2003).

DESIGN FEATURES: Single-engined derivative of Canguro. Nose-mounted engine; longer-span wings with new (modified NACA 63A3.515) aerofoil section; modified landing gear.
Following details summarise main differences from SF.600A

LANDING GEAR: Single mainwheels, with size 8.50-10 tyres, pressure 3.79 bar (55 lb/sq in); nosewheel tyre 6.50-8, pressure 5.17 bar (75 lb/sq in). Cleveland mainwheel disc brakes. Seaplane version being studied in 2002.

POWER PLANT: One 580 kW (778 shp) Walter M 601F-11 turboprop, driving an Avia V 510 five-blade constant-speed feathering and reversing metal propeller. Optional Pratt & Whitney Canada PT6A turboprop installation. Alternative power plants may be offered according to market requirements. Fuel capacity (two wing tanks plus reservoir) 1,338 litres (353 US gallons; 294 Imp gallons), of which 1,300 litres (343 US gallons; 286 Imp gallons) are usable.

ACCOMMODATION: Pilot and up to 10 passengers, or up to 15 passengers where local certification criteria permit. In cargo configuration the cabin can accommodate up to three standard Euro pallets. Pilot's door on port side: cargo/passenger sliding door on port side.


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