Tandem two seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges and constant chord; conventional tail. Pitch control by fully flying tail; yaw control by fully flying rudder; roll control by half span ailer¬ons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables; wing profile double surface. Steel tube framework, with optional pod. Engine mounted below wing driving pusher propeller. Wings use two aluminium tubes as spars, with ribs in foam, capped top and bottom with wood; all flying surfaces covered in Ceconite.

This tandem two seater version of the Uli made its first flights in February 1983 and by 1983 two prototypes had been built, which were undergoing certification. The aircraft is fitted with the four cylinder Konig 570cc engine and uses either a two blade or a three blade design of 51 inch (1.30 m) dia¬meter.

Length overall 18.1ft, 5.52m
Wing span 35.4 ft, 10.80 m
Constant chord 4.4 ft, 1.33 m
Sweepback 0 deg
Tailplane span 7.2 ft, 2.20 m
Total wing area 161 sq.ft, 15.0 sq.m
Wing aspect ratio 7.8/1
Wheel track 4.6 ft, 1.40 m
Engine: Konig SD570, 28 hp at 4200 rpm
Propeller diameter 58 inch, 1.47 m. 2-blade
Belt reduction, ratio 1.8/1
Max static thrust 177 lb, 80 kg
Power per unit area 0. 17 hp/sq.ft, 1.9hp/sq.m
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre
Empty weight 221 lb, 100kg
Max take off weight 618 lb, 280kg
Payload 397 lb, 180kg
Max wing loading 3.81 lb/sq.ft, 18.7 kg/sq.m
Max power loading 22.1 lb/hp, 10.0kg/hp
Load factors; +6.0, 3.0 ultimate
Economic cruising speed 37 mph, 60 kph
Stalling speed 28 mph, 45 kph
Best glide ratio with power off: 9/1
Take off distance 260 ft, 80 m

Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges and constant chord; conventional tail. Pitch control by fully flying tail; yaw control by fully flying rudder; roll control by half span ailer¬ons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables; wing profile double surface. Undercarriage has two wheels side by side with tailskid (three wheels in tricycle formation optional); glass fibre tails¬kid and glass fibre suspension on main wheels. No brakes. Steel tube framework, with optional pod. Engine mounted below wing driving pusher propeller. Wings use two aluminium tubes as spars, with ribs in foam, capped top and bottom with wood; all flying surfaces covered in Ceconite.

The prototype of the single seater Uli microlight flew for the first time at the end of 1982 and was shown at Aero 83 Salon at Friedrichshafen. At Aero 83 the Uli I was given a pod, as an option, and a tailwheel had replaced the tailskid. This machine uses welded steel tubes for the framework.

Length overall 18.0ft, 5.50m
Wing span 31.8 ft, 9.70 m
Constant chord 4.4 ft, 1.33 m
Sweepback 0 deg
Tailplane span 7.2 ft, 2.20 m
Total wing area 140 sq.ft, 13.0 sq.m
Wing aspect ratio 7.2/1
Wheel track 4.6 ft, 1.40 m
Engine: Hirth 383cc, 22 hp at 4000 rpm
Propeller diameter 51 inch, 1.30 m
Belt reduction, ratio 1.88/1
Power per unit area 0.16 hp/sq.ft, 1.7 hp/sq.m
Fuel capacity 5.3 US gal, 4.4 Imp gal, 20.0 litre
Empty weight 221 lb, 100kg
Max take off weight 442 lb, 200kg
Payload 221 lb, 100 kg
Max wing loading 3.25 lb/sq.ft, 15.9 kg/sq.m
Max power loading 20.1 lb/hp, 9.1kg/hp
Load factors; +6.0, 3.0 ultimate
Max level speed 50mph, 80kph
Never exceed speed 56mph, 90kph
Max cruising speed 37mph, 70kph
Economic cruising speed 30mph, 48kph
Stalling speed 27 mph, 43 kph
Max climb rate at sea level 400 ft/min, 2.0 m/s
Min sink rate 310 ft/min at 35 mph, 1.6 m/s at 56 kph
Best glide ratio with power off 9/1
Take-off distance 150ft, 45m
Landing dis¬tance 100 ft, 30 m
Range at average cruising speed 112 mile, 180km