The primary design requirements of this aircraft were to duplicate as closely as possible the performance and flight characteristics of the B├╝cker Jungmeister. The prototype flew for the first time in October 1962. Sets of plans have been available to amateur constructors for many years, with several hundred sets sold.

TYPE: Single-seat sporting homebuilt.

AIRFRAME: Braced biplane with wood structure, plywood and fabric covered except for aluminium alloy engine cowling. Wing section NACA 4413. Non-retractable tailwheel landing gear.

POWER PLANT: Options include 63.4-74.5 kW (85-100 hp) Teledyne Continental C85, C90 or O-200; 93-97 kW (125-130 hp) Franklin Sport 4, 4A or 4B; 80.5-86 kW (108-115 hp) Textron Lycoming O-235-C or -C1; 93-100.6 kW (125-135 hp) Textron Lycoming O-290-D or -D2; 104.5-112 kW (140-150 hp) Textron Lycoming O-320; or European engines in the same weight/power class. Fuel capacity 62 litres (16.5 US gallons; 13.7 Imp gallons); optional 26 litre (7 US gallon; 5.8 Imp gallon) tank in upper wing centre-section, increasing total capacity to 88 litres (23.5 US gallons; 19.5 Imp gallons).

DIMENSIONS, EXTERNAL (prototype):

  • Wing span: 5.08 m (16 ft 8 in)
  • Length overall: 4.88 m (16 ft 0 in)
  • Propeller diameter: 1.73 m (5 ft 8 in)

AREA:

  • Wings, gross: 7.43 m² (80.0 sq ft)

WEIGHTS:

  • Weight empty: 275 kg (606 lb)
  • T-O weight, aerobatic: 385 kg (850 lb)
  • Max T-O weight: 455 kg (1,000 lb)

PERFORMANCE (prototype, at max T-O weight, Textron Lycoming O-235 engine):

  • Max level speed at S/L: 109 knots (201 km/h; 125 mph) IAS
  • Max cruising speed at S/L: 103 knots (192 km/h; 119 mph)
  • Stalling speed: 45 knots (84 km/h; 52 mph) IAS
  • Max rate of climb at S/L: 455 m (1,500 ft)/min
  • Service ceiling: 3,960 m (13,000 ft)
  • T-O run: 91 m (300 ft)
  • Landing run: 152 m (500 ft)
  • Range with max fuel (incl centre-section tank): 260 nm (482 km; 300 miles)
  • g limits: +9/-6