TYPE: Side-by-side kitbuilt; four-seat kitbuilt twin.

PROGRAMME: Project began 1997. Launched at AirVenture, Oshkosh, July 2000. Development prototype (C-GYCC) first flown in single-engine form 15 July 2001; exhibited at Oshkosh 24 to 30 July 2001. Reconfigured in twin-engine form and flown on 5 September 2002; first flight with floats attached (from land) 15 October 2002; water taxying trials begun 17 October 2002.

CURRENT VERSIONS: Two-seat: Single-engine version.
Four-seat: Single- or twin-engine version, retaining same dimensions.

COSTS: Complete kit US$100,000 single engine; US$130,000 twin engine (2002 estimates).

DESIGN FEATURES: Designation indicates 'multi platform aircraft'. Kitplane meeting '51 per cent' rule for amateur construction; easily completed in single- or twin-engine configuration and with amphibian and seaplane landing gear.
Cabin pod, with board outward visibility, mounted on cranked wings of two-stage taper and with sweptback tips. Engine(s) on arched cabane with central, vertical reinforcement strut. Twin tailbooms and high tailplane; forward boom sections contain main landing gear and attachment points for floats with cutouts for mainwheels when in amphibian mode.
Wing section NLF-0215 (mod); dihedral 3o; twist -4o.

FLYING CONTROLS: Conventional and manual. Horn balances on elevator and rudders; flight-adjustable tab on starboard rudder and port aileron. Fowler flaps, max deflection 40o. Third flap, between booms, is independently actuated; potential advantages during take-off and landing are being assessed during trials. Flaps actuated by wires, with electric control; rudders wire-actuated, with manual control.

STRUCTURE: All structures manufactured by 'open layup, vacuum-formed' process. Fuselage, tailbooms, rudders, ailerons, flaps and floats of glass fibre/foam core construction. Wing spars and cabane of carbon fibre/foam core; nosewheel assembly of carbon fibre.

LANDING GEAR: Tricycle type; retractable. Mainwheels 6.00-6; castoring forward retracting nosewheel, size 5.00-5; differential hydraulic mainwheel brakes. Adjustable air bag suspension. Optional Series 2500 composites floats, with or without wheeled gear. Float installation takes 45 minutes.

POWER PLANT: One or two piston engines, driving three-blade propeller of constant-speed, flight- or ground-adjustable pitch or fixed-pitch type. Prototype flown with single and twin 89 kW (120 hp) Jabiru 3300 flat-six(es) and ground-adjustable pitch propeller(s). Airmaster three-blade, constant-speed propeller on trial in 2002. Recommended options include 149 kW (200 hp) Textron Lycoming IO-360, similarly rated Jabiru or 194 kW (260 hp) Subaru turbo, all for four-seat, single-engine version. Fuel capacity (usable) 258 litres (68.0 US gallons; 56.7 Imp gallons).

ACCOMMODATION: Two or four persons, according to version. Rear seats may be replaced by freight. Door each side of cabin. Dual controls.

SYSTEMS: Electrical power 12 V; electro-pneumatic pump 6.9 bar (100 lb/sq in) for landing gear actuation.

AVIONICS: To customer's requirements. Prototype has GPS, ELT and VHF radio.


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