Created by Claude Guilbault, the Delta is an amphibious pusher with retractable undercarriage. The cabin is carbonfibre, and the floats and tail are aluminium. Wings are fabric covered aluminium. The Delte was in the experimental stage in 1998.
Engine: Arrow 1000, 100 hp
Wing span: 9.75 m
Wing area: 16 sq.m
MAUW: 610 kg
Empty weight: 390 kg
Fuel capacity: 136 lt
Max speed: 195 kph
Cruise speed: 180 kph
Climb rate: 3 m/s
Seats: 2
Plan price (1998): Can$200
Kit price (1998): Can$18,000
Following on from the Krate, the Crystal was available in microlight or homebuilt form. The Crystal is of riveted sheet dural.
Empty weight: 300 kg
Wing span: 10.35 m
Wing area: 17 sq.m
Fuel capacity: 68 lt
Engine: Arrow, 100 hp
MAUW: 450 kg
Seats: 2
Max speed: 130 kph
Cruise speed: 125 kph
Minimum speed: 59 kph
Climb rate: 3 m/s
Plan price (1998): Can$200
Kit price (1998): Can$13,125
The tube and fabric Krate was followed by the Crystal.
Twenty-nine Krate were operating in 1989.
1998:
2835, Haut St Francois
H7E 4P2 Laval
Quebec
Canada
UL builder
AIEP established 1979 to assemble kits of the US Van’s RV-6A, known locally as Air Beetle and used by the Nigerian Air Force as the T18 trainer.
In 1974 Aeronautica Industrial SA (AISA) started construction of the prototype AISA-GN, which was an all-metal four-seat autogyro with a small stub wing, three-blade main rotor, twin booms and a fixed tricycle undercarriage. After a long development, the prototype was first flown on 20 July 1982, powered by a 225kW Lycoming IO-540-K-1A5 engine. The prototype was damaged in September 1982, and the project was then abandoned.
AISA GN
Engine: 1 x Lycoming IO-540-K-1A5, 225kW
Main rotor diameter: 12.8m
Fuselage length: 6.5m
Height: 3.2m
Wingspan: 2.6m
Take-off weight: 1200kg
Empty weight: 708kg
Max speed: 240km/h
Range: 800km
Aeronáutica Industrial S.A. was established in Madrid in 1923, engaged on aircraft manufacture, repair, and maintenance. In 1927 built some of earliest Cierva Autogiros, a type originated in Spain. H.M.1 and 5 trainers and H.M.9 glider tug built 1943; H.M.3 seaplane and H.M.7 cabin monoplane 1947; took over Aircraft Department of Iberavia SA (including helicopter designs); flew I-11 1953; built AVD-12 high-wing all-metal monoplane to designs of Emile Dewoitine mid- 1950s. Tandem-seat trainer I-115 went into production for Spanish Air Force at same period, also I-11B tourer/trainer. Repair work has embraced several modern types of helicopter, while fixed-wing production continued with Italian-designed Siai-Marchetti four-seater. Rotarywing work continued with AISA Autogyro GN, having jump take-off capability.
The company was bought by CASA in 1995, but continued to operate under its own name.
In production since 1977, the Mustang is a weight shift trike, made from certified aviation hardware and with a wing tested to +5, 43g. Car toppable with only 10 minutes rigging time.
Mustang 1
Engine: JPX 425 (424 cc) 26 hp
Wing span: 10 m
Length: 3.88m
Empty wt: 62 kg
Max wt: 162 kg
Max cruise: 65 kph
Range: 220 km.
Side by side two seat single engined highwing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile double surface. Undercarriage has three wheels in tricycle formation with additional tailskid; steel spring suspension on nosewheel and torsion bar suspension on main wheels. Push right go right nosewheel steering connected to yaw control. Optional brake on nosewheel. Aluminium tube framework, with optional pod. Engine mounted below wing driving tractor propeller.
Designed by Philippe Tisserand, the two seat version made its first flight in December 1982. Apart from the engine position, very few changes were deemed necessary on this machine, which is directly descended from the single seater.
First sales were in February 1983. Like its elder, it is of conventional three axis control with large control surfaces. The two seater retains the advantage of being foldable to small dimensions, so it can be car topped or carried on a trailer; folded it measures 16.5 x 1.8 x 1.8ft (5.50 x 0.50 x 0.50m). It is offered as standard with the Hirth 2701R engine of 43hp or the Rotax 503 of 46 hp with toothed belt reduction. A partial fairing of the cockpit area is offered as an option. Also, Aeronautic 2000 offers it in kit form complete, for export only, a move aimed particularly at the American continent. Composed of pre formed factory built units, cut and drilled, this kit requires 100h for assembly. The Baroudeur Biplace is fitted with dual controls as standard version.
Engine: Rotax 503, 46hp at 6500rpm
Propeller diameter: 63 in, 1.6 m
Reduction ratio: 2.5/1
Max static thrust: 287 lb, 130 kg
Power per unit area: 0.30hp/sq.ft, 3.3hp/sq.m
Fuel capacity main: 5.3 US gal, 4.4 Imp gal, 20.0 lt
Fuel capacity reserve: 6.6 US gal, 5.5 Imp gal, 25.0 lt
Length overall: 18.1 ft, 5.5 m
Height overall: 8.2 ft, 2.5 m
Wing span: 29.6 ft, 9.0 m
Constant chord: 5.1ft, 1.55m
Dihedral: 2 degs
Sweepback: 0 degs
Tailplane span: 7.9ft, 2.40 m
Total wing area: 151 sq.ft, 14.0 sq.m
Total aileron area: 16.2 sq.ft, 1.5 sq.m
Rudder area: 7.5 sq.ft, 0.7 sq.m
Fin area: 4.3 sq.ft, 0.4 sq.m
Tailplane area: 16.2 sq.ft, 1.5 sq.m
Total elevator area: 9.7 sq.ft, 0.9 sq.m
Wing aspect ratio: 5.78/1
Wheel track: 4.5 ft, 1.35 m
Wheelbase: 4.9 ft, 1. 45 m
Nosewheel dia. Overall: 12 in, 30 cm
Main wheels dia. Overall: 12 in, 30cm
Empty weight: 287 lb, 130kg
Max take off weight: 662 lb, 300kg
Payload: 375 lb, 170kg
Max wing loading: 4.38 lb/sq.ft, 21.4kgsq.m
Max power loading: 14.4 lb/hp, 6.5kg/hp
Load factors: +6, 2.5 design
Max level speed: 62 mph, 100 kph
Never exceed speed: 71 mph, 115 kph
Max cruising speed: 56 mph, 90 kph
Economic cruise: 50 mph, 80 kph
Stalling speed: 24 mph, 40 kph
Max climb rate SL: 600ft/min, 3.0m/s
Min sink speed: 37 mph, 60 kph
Min sink rate: 350 ft/min, 1.7 m/s
Best glide ratio: 10/1 at 37 mph, 60 kph
Take off distance: 165 ft, 50 m.
Land¬ing distance: 165 ft, 50 m
Service ceiling: 10,000ft, 3050 m
Range at ave. cruise: 186 mile, 300 km
Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fully flying rudder; roll control by ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile double surface. Undercarriage has three wheels in tricycle formation with additional tailskid; suspension on all wheels Push right go right nosewheel steering connected to yaw control. Optional brake on nosewheel. Aluminium tube/fabric framework, partially enclosed. Engine mounted below wing driving pusher propeller.
Baroudeur prototype number 01 made its first flights in September 1981. The machine had been designed by a specialist team directed by Henri de Beaufort with Philippe Tisserand, and coupled a fully flying wing, free to move in three axes, with fixed tail surfaces. Next came serial 02, with wing warping and fully flying elevator. After various modifications this became prototype 03, eventually being succeeded by 04, which appeared with ailerons and a classic empennage.
The structure of this was re used for the fifth, similar prototype, and fitted with a stick which was articulated from above the pilot. At the same time, 06 was built with a stick placed conventionally, between the pilot’s knees. These latter two were pre production aircraft.
Designed for low power engines, the Baroudeur was initially fitted with the flat twin French JPX PUL425 engine, developing 26 hp at 4600 rpm with toothed belt reduction. It was offered with a Robin EC34PM, Robin EC44 or Hirth HL2701 RR179 engine. On sale since February 1982, the machine has acquired a reputation for robustness and ease of operation and rigging. It has also been designed with military uses in mind. Options include a cockpit, a special pod, a nosewheel brake and resin reinforced leading edges. The Baroudeur is transportable on a trailer or on a roof rack. Folded dimensions are 16.5 x 1. 8 x 1. 8 ft (5.0 x 0.5 x 0.5m).
Engine: Hirth HL2701 RR179, 40 hp at 3800 rpm
Prop¬eller diameter: 47 in, 1.20m
Reduction, ratio: 2.0/1
Max static thrust: 199 lb, 90 kg
Power per unit area: 0.26hp/sq/ft, 2.9 hp/sq.m
Fuel capacity main: 7.9 USG, 6.6 Imp gal, 30.0 lt
Fuel capacity reserve: 6.6 USG, 5.5 Imp gal, 25.0 lt
Length overall: 16.5 ft, 5.0 m
Height overall: 8.2ft, 2.5m
Wing span: 29.6ft, 9.0m
Constant chord: 5.1ft, 1.55m
Dihedral: 2 degs
Sweepback: 0 degs
Tailplane span: 7.9ft, 2.40 m
Total wing area: 151 sq.ft, 14.0 sq.m
Total aileron area: 16.2 sq.ft, 1.50 sq.m
Rudder area: 7.5 sq.ft, 0.70 sq.m
Tailplane area: 16.2 sq.ft, 1.50 sq.m
Total elevator area: 9.7 sq.ft, 0.9 sq.m
Wing aspect ratio: 5.78/1
Wheel track: 4.9 ft, 1.50 m
Wheelbase: 5.3 ft, 1.6 m
Nosewheel dia. Overall: 12 in, 30 cm
Main wheels dia. Overall: 12 in, 30cm
Empty weight: 220 lb, 100kg
Max take off weight: 552 lb, 250kg
Payload: 332 lb, 150kg
Max wing loading: 3.65 lb/sq.ft, 17.9 kg/sq.m
Max power loading: 13.8 lb/hp, 6.25 kg/hp
Load factors: +6.0, 2.5 ultimate
Max level speed: 63 mph, 100 kph
Never exceed speed: 71 mph, 115 kph
Max cruising speed: 56 mph, 90 kph
Economic cruise: 50 mph, 80 kph
Stalling speed: 22 mph, 35 kph
Max climb rate SL: 690 ft/min, 3.5 m/s
Min sink rate: 335 ft/min, 1.7 m/s
Min sink speed: 37 mph, 60 kph
Best glide: 10/1 at 37 mph, 60 kph
Take off distance: 130 ft, 40 m
Land¬ing distance: 130 ft, 40 m
Service ceiling: 13,120 ft, 4000 m
Range ave. cruise: 373 mile, 600 km
