TYPE: Side-by-side kitbuilt.

PROGRAMME: First flight July 1986.

CURRENT VERSIONS: Glasair III: As described.
Glasair III Turbo: Powered by 224 kW (300 hp) Textron Lycoming TIO-540. Maximum level speed 284 kt (526 km/h; 327 mph); maximum rate of climb 1,143 m (3,750 ft0/min; withdrawn in 1998 and superseded by Glasair Super III.
Glasair Super III: Prototype (N401KT) flying by third quarter 1998, when demonstrated 322 kt (596 km/h; 280 mph) at 10,060 m (33,000 ft), powered by IO-540-AA1B5 uprated with Honeywell turbocharger to 261 kW (350 hp) at 11,275 m (37,000 ft) and with Hartzell four-blade propeller. Predicted maximum speed of 350 kt (648 km/h; 403 mph). Has enlarged rudder, extra fuel capacity and highly modified cowling. Public debut at Sun 'n' Fun 1999.

CUSTOMERS: 375 kits delivered by early 2003; 220 flying by early 2002.

COSTS: Kit: US$35,982 without engine, propeller, instruments and avionics; engine US$43,000; constant-speed propeller US$6,800 (2003). Jumpstart options for wing (US$8,350) and fuselage (US$8,450) offered.

DESIGN FEATURES: Similar configuration to earlier Glasair, but designed to offer better performance, constructional simplicity and economical kit price. Larger fuselage for increased baggage space, payload capacity and comfort, also improving the longitudinal and directional stability for better cross-country and IFR performance; windows to rear of cockpit doors. Thicker windscreen to improve protection against bird strikes at higher speeds, and additional glass fibre laminates, integral longerons, and lay-up schedule which provides structurally stronger and torsionally stiffer fuselage. Quoted build time 2,500 working hours.
Wing section LS(I)-0413; wing incidence 2° 18', dihedral 3°; strengthened; carries more fuel than previous models. Optional wingtip extensions for 8.32 m (27 ft 3½ in) or 7.86 m (25 ft 9½ in) spans.

FLYING CONTROLS: As Glasair Super II. Slotted flaps optional.

LANDING GEAR: Retractable tricycle only, otherwise as Super II-RG but with 13 cm (5 in) longer landing gear legs to accommodate larger diameter propeller. Mainwheels size 5.00-5; nosewheel 4.00-5. Differential Cleveland disc brakes on mainwheels.

POWER PLANT: One 224 kW (300 hp) Textron Lycoming IO-540-K1H5 flat-six piston engine driving a two-blade constant-speed propeller. Fuel capacity in wings 201 litres (53.0 US gallons; 44.1 Imp gallons). Fuselage header tank, capacity 30 litres (8.0 US gallons; 6.7 Imp gallons). Optional tanks in wingtip extensions, combined capacity 41.6 litres (11.0 US gallons; 9.2 Imp gallons).