The primary design requirements of this aircraft were to duplicate as closely as possible the performance and flight characteristics of the Bücker 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