TYPE: Side-by-side ultralight.

PROGRAMME: Prototype (G-CCJJ) registered in August 2003 and made unannounced first flight about same time. Further two development/demonstrator aircraft flown early 2006 before public unveiling at International Microlight Exhibition, Popam, Hampshire, on 29-30 April 2006.

COSTS: GBP28.995 including tax with Rotax 912 UL; GBP1.000 extra for Rotax 912 ULS (2006).

DESIGN FEATURES: High, constant-chord wing braced to lower longerons by streamlined V-struts and auxiliary struts. Sweptback fin with full-height rudder; empennage mutually braced by wires.

FLYING CONTROLS: Conventional and manual. Flaps. Actuation by cables; electrically operated pushrods for flaps. Flight-adjustable tab on port elevator.

STRUCTURE: Bolted tubular aluminium with laced Dacron covering for all surfaces, except composites forward of windscreen.

LANDING GEAR: Tricycle type; fixed. Twin Vs (forward strut streamlined; aft tubular) hinged on centreline, plus oleo-damped tubular leg attached to lower longerons, each side. Forward-canted, steerable cantilever nosewheel leg. Mainwheels 3.50-6; nosewheel 5.50-6. Hydraulic brakes. Optional mainwheel fairings.

POWER PLANT: One liquid-cooled Rotax flat-four driving a three-blade, ground adjustable pitch propeller: 59.6 kW (79.9 hp) Rotax 912 UL; or 73.5 kW (98.6 hp) Rotax 912 ULS. Fuel behind seats: capacity 100 litres (26.4 US gallons; 22.0 Imp gallons) when flown solo; 20 litres (5.3 US gallons; 4.4 Imp gallons) with two crew.


  • Wing span: 9.69 m (31 ft 9½ in)
  • Length overall: 5.71 m (18 ft 9 in)
  • Height overall: 2.26 m (7 ft 5 in)


  • Cabin max width: 1.19 m (3 ft 10¾ in)


  • Max T-O weight: 450 kg (992 lb)


  • Never-exceed speed (VNE): 107 kt (200 km/h; 124 mph)
  • Max level speed: 82 kt (153 km/h; 95 mph)
  • Cruising speed at 4,800 rpm: 70 kt (129 km/h; 80 mph)
  • Stalling speed, flaps down: 33 kt (60 km/h; 37 mph)
  • Max rate of climb at S/L: 259 m (850 ft)/min