First flown in May 1996, the Scub tandem two-seat braced high-wing cabin lightplane was offered in production form. With spaceframe fuselage and wooden wings the Scrub could be flown with floats or wheels.

Empty weight: 250 kg
Wing span: 11 m
Wing area: 14.3 sq.m
Fuel capacity: 70 lt
Engine: JPX 4TX 75A, 85 hp
MAUW: 550 kg
Seats: 2
Max speed: 200 kph
Cruise speed: 160 kph
Minimum speed: 60 kph
Climb rate: 6 m/s
Fuel consumption: 8 lt/hr
Price (1998): 290 000 Fbc

The Aero-Kros MP-02 Czajka (English: Lapwing) was designed and developed by Aero-Kros of Krosno, Poland, to comply with the Fédération Aéronautique Internationale microlight rules and US light-sport aircraft rules.

It features a cantilever high-wing, a two seats in side-by-side configuration enclosed cockpit, tricycle landing gear and a single engine in tractor configuration.

The aircraft is made from carbon-fiber-reinforced polymer. Its 9.72 m (31.9 ft) span wing employs Fowler flaps to keep the stall speed low enough for the FAI microlight category. The standard engine provided is the 100 hp (75 kW) Rotax 912ULS four-stroke powerplant which gives a cruise speed of 230 km/h (143 mph). The cockpit is 1.215 m (48 in) wide.

Introduced at the Friedrichshafen Aero show held in in 2009, the aircraft is supplied ready-to-fly.

Since March 2017 the design has been built by HMS Aviation, which is also located in Krosno, Poland.

Aero-Kros MP-02 Czajka
Powerplant: 1 × Rotax 912ULS, 75 kW (101 hp)
Wingspan: 9.72 m (31 ft 11 in)
Wing area: 10.2 m2 (110 sq ft)
Empty weight: 268 kg (591 lb)
Gross weight: 472.5 kg (1,042 lb)
Fuel capacity: 112 litres (25 imp gal; 30 US gal)
Wing loading: 46.3 kg/m2 (9.5 lb/sq ft)
VNE: 146 kt / 168 mph / 270 kmh
Maximum speed: 230 km/h (140 mph, 120 kn)
Cruise speed: 170 km/h (110 mph, 92 kn)
Stall speed: 65 km/h (40 mph, 35 kn)
Rate of climb: 6.5 m/s (1,280 ft/min)
Crew: one
Capacity: one passenger

A side by side two seat single engined high-wing monoplane with conventional three axis control. The wing has unswept leading and trailing edges, and constant chord; T tail. Pitch control is by elevator on the tail; yaw control by fin mounted rudder; no separate roll control (roll control by one third span spoilers option¬al); control inputs through stick for pitch/yaw (optional: stick for pitch/roll and pedals for yaw). Wing braced from above by kingpost and cables, from below by cables; wing profile single surface. Undercarriage has three wheels in tricycle formation with additional tailskid; no suspension on any wheels (optional torsion bar suspension on main wheels). No ground steering. Optional brake on nose-wheel. Aluminium tube framework, without pod. Engine mounted below wing driving pusher propeller with V belt reduction.
With a configuration very close to that of the Quicksilver MXII, this Aerokit was only at the prototype stage in 1982. Conceived by Olivier Richard and built with the assistance of Hugues Delebard and Christian Risbourg, this machine is a direct result of experience acquired with other microlights used within the framework of one of the first private flying schools to appear in France, the Cenpre National de Formation ULM at Rustrel, Vaucluse, founded and directed by Serge Pellenc.
The Aerokit can be used either as a two axis control machine with elevators and rudders or as a conventional three axis control aircraft by the addition of spoilers, which are optional. Supplied with a central stick, this side by side two-seater machine can be converted to single seat without any difficulty, as the seats are fitted with Velcro, permitting removal of one seat and the re positioning of the other in the central location. The experience accumulated in the flying school by this manufacturer caused it to fit a wide track undercarriage which is specially reinforced. The axle of the main wheels is made of 1.6 x 0.9 inch (40 x 2.5 cm) Duralumin tube with internal bushes and nylon bearing hubs. As an option, the main wheels can have torsion bar suspension.
The Aerokit in its standard version is fitted with a single fuel tank but this can be increased as an option by fitting two supplementary tanks of the same size, tripling its range. The Aerokit is trailer transportable.

Engine: Hirth 2701R 03, 43 hp at 6750 rpm
Propeller: 55 x 24 in, 1.4 x 0.6m
Reduction ratio: 2.4/1
Max static thrust: 232 lb, 105 kg
Power per unit area: 0.25 hp/ sq.ft, 2.7 hp/sq.m
Fuel capacity: 2.6 US gal, 2.2 Imp gal, 10.0
Optional res fuel capacity: 5.3 US gal, 4.4 Imp gal, 20.0 lt
Length overall: 14.6 ft, 4.43 m
Height overall: 9.0ft, 2.75m
Wing span: 32.8ft, 9.95m
Constant chord: 5.3ft, 1.6m
Dihedral: 11 deg
Sweepback: 0 deg
Tailplane span: 9.3 ft, 2.82 m
Fin height: 4.3ft, 1.3m
Total wing area: 17 sq.ft, 16.0 sq.m
Fin area: 2.2 sq.ft, 0.2 sq.m
Rudder area: 10.0 sq.ft, 0.93 sq.m
Tailplane area: 23.1 sq.ft, 2.14 sq.m
Wing aspect ratio: 6.18/1
Total elevator area: 12.7 sq.ft, 1.18 sq.m
Wheel track: 5.5 ft, 1.65 m
Wheelbase: 5.3ft, 1.60 m
Nosewheel dia. overall : 11 in, 28 cm
Main wheels dia. Overall: 16 in, 40 cm
Empty weight: 291 lb, 132 kg
Max take off weight: 623 lb, 282 kg
Payload: 332 lb, 150 kg
Max wing loading: 3.61 lb/sq.ft, 17.8 kg/sq.m
Max power loading: 14.5 lb/hp, 6.5kg/hp
Load factor: +3.5 ultimate
Max level speed: 50 mph, 80 kph
Never exceed speed: 56 mph, 90kph
Max cruising speed: 42mph, 68kph
Economic cruising speed: 34mph, 55kph
Stalling speed: 23 mph, 38 kph
Max climb rate at SL: 680 ft/min, 3.5 m/s
Min sink speed: 37 mph, 60 kph
Min sink rate: 400 ft/min, 2.0 m/s
Best glide ratio: 6/1 at 44 mph, 70 kph
Take off distance: 130 ft, 40 m
Land¬ing distance: 100 ft, 30 m
Service ceiling: 10,000 ft, 3050 m
Range at ave cruise: 50 mile, 80 km

1982: Aerokit Industrie, Rustrel, 84400 Apt, France.

UL manufacturer

Designed by Serge Cardot in 1984. 2-Axis control. Kingpost bracing.

Engine: 26 hp Rotax 277
Length: 15.1 ft
Height: 8.2 ft
Wing span: 27.9 ft
Wing area 138 sq.ft
Empty weight 207 lb
Payload 256 lb
Structural limits +6 Gs / -4.5 G
Glide ratio 6:1

A two seat, side by side, single engined, high-wing monoplane with conventional three axis control. The wing has unswept leading edge, swept forward trailing edge and constant chord, cruciform tail. Pitch control is by elevator on tail, and yaw control by fully flying rudder; roll control by half span ailerons; control inputs through stick for pitch/roll and pedals for yaw.
The wing is braced from below by struts; with a double surface wing profile. The undercarriage has three wheels in tricycle formation; no suspension on the nosewheel and bungee suspension on the main wheels. Push right go right nosewheel steering is connected to the yaw control. No brakes. An aluminium tube framework, without pod, the engine is mounted below wing driving pusher propeller.
On the two seater Aerokart 4320 the kingpost and wire used on this company’s single seaters is replaced by struts. The horizontal stabiliser, stiffened in flight and landing by cables, has the outer sections of its leading edge joined by tubes to the spars carrying the tail assembly. These tube joints form a structure of high structural integrity rather than low drag.
The 4320 has its motor mounted in front of the wing on silent bloc bushes, driving a twin bladed propeller behind the trailing edge from toothed belt reduction. The 1983 standard power pack for this aircraft was the twin cylinder in line Hirth 2701R of 43hp fitted with a tuned exhaust for each cylinder, this system having been developed by Aerokart.
The hot air from the cooling fan is fed to the carburettor and air filter by a movable flap when atmospheric conditions demand de icing and switched back at other times.
This two seater is delivered in standard form with an electric starter while retaining the capability of manual starting. Electric fuel pump and double surfacing for the wing, ailerons and tail areas, and alloy rims for the main wheels are all standard fittings on the 4320. The machine is transportable on a trailer, folded dimensions being 16.9 x 6.3 x 5.9ft (5.10 x 1.90 x 1.76m).

Engine: Hirth 2701R 03, 43 hp at 6750 rpm
Propeller: 55 x 32 in, 1.40 x 0.80 m
Reduction ratio: 2.5/1
Power per unit area: 0.19hp/sq.ft, 2.2hp/sq.m
Max static thrust: 287 lb, 130kg
Fuel capacity: 5.3 US gal, 4.4 Imp gal, 20.0 lt
Length overall: 19.0ft, 5.8m
Optional fuel capacity: 7.9 US gal, 6.6 Imp gal, 30.0 lt
Height overall: 9.8ft, 2.94m
Wing span: 34.5ft, 10.5m
Chord at root: 6.4 ft, 1.92m
Chord at tip: 6.2ft, 1.89m
Dihedral: 1.5 deg
Sweepback: 0 deg
Tailplane span: 9.1 ft, 3.00 m
Total wing area: 216 sq.ft, 20.0 sq.m
Total aileron area: 12.9 sq.ft, 1.2 sq.m
Rudder area: 12.1 sq.ft, 1.12 sq.m
Tail¬plane area: 21.6 sq.ft, 2.0 sq.m
Total elevator area: 12.3 sq.ft, 1.14 sq.m
Wing aspect ratio: 5.4/1
Wheel track: 5.7ft, 1.70 m
Wheelbase: 5.8ft, 1.72m
Nosewheel dia. Overall: 10 in, 26 cm
Main wheels dia. Overall: 16 in, 40 cm
Empty weight: 322 lb, 146kg
Max take off weight: 707 lb, 320kg
Payload: 385 lb, 174 kg
Load factors: +5.5, 2.5 design
Max wing loading: 3.27 lb/sq.ft, 16.0 kg/m
Max level speed: 56mph, 90kph
Max power loading: 16.4 lb/hp, 7.44kg/hp
Never exceed speed: 75mph, 120 kph
Max cruising speed: 50 mph, 80 kph
Economic cruising speed: 40mph, 65kph
Stalling speed: 22 mph, 35 kph
Max climb rate at SL: 450 ft/min, 2.3 m/s
Min sink speed: 31 mph, 50 kph
Min sink rate: 430 ft/min, 2.2 m/s
Best glide ratio: 7/1 at 45 mph, 65 kph
Take off distance: 230 ft, 70 m
Landing distance: 98 ft, 30 m
Service ceiling: 10,000 ft, 3050 m
Range at ave cruise: 186 mile, 300km.

The A Kart 30 was developed into two other prototypes; the tandem 4320 two seater and the single seat 3315, both of which made their first flights at the beginning of summer 1982.
Aerokart continued the trials, refining and developing the machines, until that Septem¬ber, at the first European Microlight Salon at Lyon Bron, it was able to show two pre¬-production machines. The first was a single-¬seater, the type 3315 and the second was the 4320 side by side two seater. Both went on sale in November 1982, though the company has put most of its marketing effort into the Aerokart two seater. This manufacturer uses the first two digits of the type number to indicate the maximum power of the motor used, while the last two numbers indicate the wing area in square metres.
The single seater 3315 uses a Hirth 260R engine of 338 cc developing 33 hp at 7250 rpm, with a 23/1 reduction drive and a 51 inch (1.3m) two blade propeller. The type 4315 is more powerful and is fitted with a Hirth 2701R, 493cc engine developing 43hp at 6750rpm with toothed belt reduction. Of traditional configuration, these machines use of ailerons instead of spoilers, and their engine is fitted inverted in front of the wing below the level of the leading edge. It drives through the reduction drive to a shaft which crosses the wing to connect with a pusher propeller at the trailing edge. Flexible mountings absorb the vibrations caused by using such a long shaft whilst retaining for the Aerokart the advan¬tages of prop wash over the tail surfaces and a well cooled engine.
The machine is trans¬portable on a road trailer.

4315
Engine: Hirth 2701R 03, 43 hp at 6750 rpm
Propeller: 55 x 32 in / 1.4 x 0.8 m
Reduction ratio: 2.5/1
Max static thrust: 287 lb / 130 kg
Power per unit area: 0.27hp/sq.ft / 2.9hp/sq.m
Wing span: 34.5ft / 10.5m.
Fuel capacity main: 5.3 US gal, 4.4 Imp gal, 20.0 lt
Constant chord: 4.8ft / 1.43m.
Fuel capacity reserve: 2.6 US gal, 2.2 Imp gal, 10.0 lt
Dihedral: 1.5 degrees
Total aileron area: 25.9 sq.ft / 2.4 sq.m
Sweepback: 0 degrees
Total wing area: 161 sq.ft / 15.0 sq.m
Tailplane span: 9.1 ft / 3.0 m
Fin area: 7.5 sq.ft / 0.7 sq.m
Rudder area: 12.1 sq.ft / 1.12 sq.m
Tailplane area: 21.6 sq.ft / 2.0 sq.m
Wing aspect ratio: 7.35/1
Total elevator area: 12.3 sq.ft / 1.14 sq.m
Wheel track: 5.7 ft / 1.70 m
Nosewheel dia. overall: 10 in / 26 cm
Wheelbase: 5.8ft / 1.72 m
Main wheels dia. Overall: 16 in / 40cm
Empty weight: 278 lb / 126 kg
Max take off weight: 497 lb / 225 kg
Payload: 219 lb / 99 kg
Max wing loading: 3.07 lb/sq.ft / 15.0 kg/sq.m
Max pwr loading: 11.6 lb/hp / 5.2kg/hp
Load factors: +5.5, 2.5 design
Max level speed: 65 mph / 105 kph
Never exceed speed: 75 mph / 120 kph
Max cruise: 56 mph / 90 kph
Economic cruising speed: 50 mph / 80 kph
Stalling speed: 22 mph / 35 kph
Max climb rate at SL: 600ft/min / 3.0m/s
Take off dist: 165 ft / 50 m
Best glide pwr off: 8/1 at 40 mph / 65 kph
Landing distance: 82 ft / 25 m
Range ave. cruise: 186 sm / 300 km
Service ceiling: 10,000 ft / 3050 m
Min sink rate: 430 ft/min at 31 mph / 2.2 m/s at 50 kph

Known under the name of A Kart 30, this first machine did not go on sale. It was instead developed into two other prototypes, one tandem two seater and the other a single seater, both of which made their first flights at the beginning of summer 1982.