FULTON FA-1

Development of the FA-1 took place in Canada, where the prototype first flew in August 1985. A production prototype was built in the UK.

TYPE: Side by side two-seat, dual-control microlight trainer; conforms to FAI/CAA requirements, and to CAP 482 Section S.

AIRFRAME: Constructed of rigid composite materials (glassfibre, epoxy and PVC foam plastics). Three-axis control. Non-retractable tricycle landing gear.

POWER PLANT: One 38.7 kW (52 hp) Rotax 503 2V. Fuel capacity 36.5 litres (9.6 US gallons; 8 Imp gallons).

DIMENSIONS, EXTERNAL:

  • Wing span: 9.375 m (30 ft 9 in)
  • Length overall: 6.08 m (19 ft 11 in)
  • Height overall: 2.29 m (7 ft 6 in)
  • Propeller diameter: 1.65 m (5 ft 5 in)

AREA:

  • Wings, gross: 15.0 m² (161.5 sq ft)

WEIGHTS (open cockpit version):

  • Weight empty: 148 kg (326 lb)
  • Crew weight range: 50-180 kg (110-396 lb)
  • Max T-O weight: 360 kg (794 lb)

PERFORMANCE (at max T-O weight):

  • Max level speed: 70 knots (129 km/h; 80 mph)
  • Max cruising speed: 65 knots (120 km/h; 75 mph)
  • Stalling speed: 25 knots (46 km/h; 29 mph)
  • Max rate of climb at S/L: 225 m (740 ft)/min
  • Endurance with max fuel, with reserves: 2 h
  • g limits: +6/-3