TYPE: Two-seat amphibian kitbuilt.
PROGRAMME: Extensively redesigned Aero Composite Sea Hawker, obviating deficiencies of that discontinued aircraft. Modifications initially applied to Tom Scott's Sea Hawker and later marketed for incorporation by other Sea Hawker operators, although no longer available.
Prototype new-build Glass Goose flew 1996, but lost to flaperon flutter. Second prototype, in definitive configuration, first flew (N96GG) 20 March 1999. Production undertaken on Sea Hawker tools and jigs, acquired by Quikkit in 1993.
CUSTOMERS: Total 42 under construction, of which seven flying, by October 2003. At least six others extant by 2000, reflecting Sea Hawker conversions.
COSTS: US$29,500, excluding engine, avionics and equipment (2003).
DESIGN FEATURES: Pusher, cantilever biplane, with single-step hull, sponsons and underwing pods for retractable main landing gear. Dished upper rear fuselage; mid-mounted tailplane. Wing positive stagger of 20 cm (8 in); upswept lower wingtips; downswept upper wingtips.
Modifications to Sea Hawker design include extended (91 cm; 3 ft 0 in) upper wing span; sponsons of aerofoil section (replacing wingtip floats); and extended pylon chord, with associated fillets, vortex generators and augmentation slots in reshaped cowling to eliminate proppeller vibration.
FLYING CONTROLS: Conventional and manual, with drooping ailerons on all wings, max deflection +10/-40°. Actuation by pushrods and cables.
STRUCTURE: Glass fibre, with Kevlar reinforcement. Forward wing spars of glass fibre beam type, with carbon caps, at 27 per cent chord; glass fibre C-type rear spar at 85 per cent chord; glass fibre/foam core sandwich ribs. Pre-moulded flaperons aid construction. Intersecting fuselage bulkheads for additional strength. Quoted build time 1,000 hours.
LANDING GEAR: Retractable tricycle type for land operation. Two, side-by-side Cheng Shin 11x4.00-5 tyres on each main unit, underside of landing gear stowage pod also being forward-hinged leg/door. Mainwheel brakes.
Rearward retracting, stainless steel, fully castoring nose leg, with 4.00-5 tyre, extends against spring-loaded single door. Electrohydraulic actuation. Ventral rudder, cable operated, for water manoeuvring.
POWER PLANT: One 119 kW (160 hp) Textron Lycoming O-320-B2B flat-four driving a Warp Drive, four-blade, ground-adjustable pitch propeller. Four equal-size, integral fuel tanks in wings (upper pair main; lower pair for long range), total capacity 265 litres (70.0 US gallons; 58.3 Imp gallons). No crossfeed. Optional provision for total of 455 litres (120 US gallons; 100 Imp gallons) involves fuselage tank.
ACCOMMODATION: Two, side by side, with baggage stowage areas behind seats and between lower wings.