TYPE: Utility autogyro.

PROGRAMME: Technology demonstrator development of Hawk 4. Will not be marketed. Announced late 2000 as Hawk 6G with an expected first flight (prototype N9112A) in January 2001; first flight eventually made 22 September 2001. Based around Cessna 337 fuselage with single 335kW Rolls-Royce 250-B17F2 turboprop in nose for propulsion, driving FC9684C-6RX three-blade propeller; Rolls-Royce 250-C18 above fuselage for rotation; inverted Cessna 337 tailplanes and shortened wing with spoilers and two-blade rotor system from Hawk 4. Estimated cruising speed 209 to 241km/h; useful load 907kg.

COSTS: US$950.000 (2003).

DESIGN FEATURES: Basically similar to Hawk 4.

FLYING CONTROLS: Broadly similar to Hawk 4.

STRUCTURE: Аs Hawk 4.

POWER PLANT: Powered by a 335kW Rolls-Royce 250-C18 turboprop engine. Fuel capacity 416 litres. External tanks mounted at wingtips are modified Piper PA-24 Comanche wingtip units.

AVIONICS: Instrumentation: Full IFR.

Technical data for Hawk H4 Rotor diameter: 12.80m, fuselage length: 7.31m, overall height: 4.11m, empty weight: 835kg, max. take-off weight: 1587kg, max. speed: 238km/h, cruising speed at 75% power: 212km/h max. rate of climb at sea level: 457m/min, service seiling: 4875m, take-off run: 8m, range with max fuel at 75% power: 584km