CUSTOM FLIGHT NORTH STAR

TYPE: Tandem-seat kitbuilt.

PROGRAMME: Re-creation of Piper Super Cub, but re-engineered for additional structural strength. Prototype North Star (C-FGYD) first flew in 1991 and made its public debut that year. Offered in kit form from 1992 onwards.

CURRENT VERSIONS: North Star: Standard version, as described below.
Bright Star: Basic version with no flaps, single one-piece door, leaf spring steel main landing gear, square-topped fin and fuel capacity of 87 litres (23.0 US gallons; 19.2 Imp gallons); introduced in 1996, but first aircraft had not flown by late 2002; optional tricycle or tailwheel versions. Accepts engines from 74.6 kW to 134 kW (100 to 180 hp).
North Star 4: Four-seat version, to be powered by engine in 108 to 194 kW (145 to 260 hp) range. Seeking launch customers.
North Star 6: Six-seat version currently under development; will have maximum take-off weight of around 1,810 kg (4,000 lb). Engines between 194 and 265 kW (260 and 355 hp) can be installed.

CUSTOMERS: At least 14 (of which seven completed) in Canada; five (four completed) in USA. Production aircraft Nos. 7, 8 and 16 completed in Ontario by D E Blackburn, A King and R M Harkness in 1998. Nos. 3 (Subaru engine) and 15, built by W Smith, Ontario, and J Y Gratton, Quebec, followed in the first half of 1999. Total of at least 24 kits sold by September 2002.

COSTS: North Star: C$36,000; Bright Star: C$19,602; both excluding engine (2003).

DESIGN FEATURES: Strut-braced mainplanes; wire-braced tailplanes; raked wingtips. Easy maintenance/inspection covers. Quoted build time 1,200 hours.
Compared with Super Cub, has landing gear legs 8 cm (3 in) taller; flatter spine; squared wingtips, with ailerons moved outboard by 0.61 m (2 ft 0 in); aileron and flap chord increased 10 cm (4 in); flap span increased 0.60 m (2 ft 0 in); cockpit 6 cm (2½ in) wider.
Aerofoil USA 35B.

FLYING CONTROLS: Conventional and manual. Horn-balanced rudder and elevators. Four-position flaps.

STRUCTURE: Welded 4130 chromoly tube, fabric-covered fuselage. Tubes injected with oil as anti-corrosion measure. Wing of prototype constructed of wood, but kit aircraft have I-beam spar, aluminium ribs and 2024-T3 leading-edges.

LANDING GEAR: Tailwheel configuration (fixed) with hydraulic/coil-spring suspension. Steerable tailwheel. Optional floats and skis. Mainwheel tyres 6.00-6 or 8.50-6; tailwheel 2.80-4 in.

POWER PLANT: One 112 kW (150 hp) Textron Lycoming O-320-E3D flat-four driving a McCauley two-blade fixed-pitch propeller. Fuel capacity 197 litres (52.0 US gallons; 43.3 Imp gallons) in two wing tanks.

ACCOMMODATION: Pilot and passenger in tandem within enclosed cockpit. Door on each side - upper half Perspex and lower half fabric-covered steel tubing. Baggage compartment reached through separate door on starboard side of fuselage.

 

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