A lightplane first flown in June 1998.
Aeropract A-27 Avantage
Wing Span: 10.6 m
Length: 6.3 m
Height: 2.4 m
Absolute Ceiling: 14000 ft
Optimum Ceiling: 12000 ft
Maximum Speed: 111 kts
Optimum Speed: 80 kts
Fuel Capacity: 80 lt
MTOW: 600 kg
Maximum Range: 600 nm
Seats: 2
A four-seat amphibian first flown in November 1994.
A-25 Breeze
Wing Span: 10.6 m
Length: 7.9 m
Height: 2.5 m
MTOW: 1200 kg
Fuel Capacity: 195 lt
Maximum Speed: 111 kt
Optimum Speed: 93 kt
Absolute Ceiling: 14,000 ft
Optimum Ceiling: 12,000 ft
Maximum Range: 600 nm
Maximum Climb Rate: 980 ft/min
Take Off Distance: 420 m
Seats: 4
The Coach / Baby Dragon is a light light multi-purpose aircraft. It can be flown from land (wheels), snow (skis) or water (floats). The prototype A-23 first flew in 1992 with two RMZ-640 engines (replaced later by single 64hp Rotax-582) had a narrow angular fuselage. It served for four years in the pilot’s club.
For series production, a more powerful Rotax-912 engine was chosen (while the original engine was still available in the economy package). Cockpit width was increased to 760mm providing sufficient comfort for pilot. Both composite fuselage and wing are now made in matrixes. The slab-type fiberglass tailplane unit was revised – raised to the top of the tailfin.
A-23M wings carry single “flaperon” each – there is no separation between aileron and landing flap.
The first flight of the A-23M took place on August 5, 1999. The A-23M prototype flew approximately 120 hours during Fall 1999. The only problem was insufficient compensation of the large flaperons.
The A-23M may be built (converted?) as a crop duster. Wheels, skis and floats are included in standard package.
Production was launched in the winter of 2000. First batch – 3 machines with different engines. Available as a kit.
On June 24, 2000 director of Aeroprakt-Samara I.A.Vakhrushev and co-pilot were killed in crash of the series A-23M. This happened on landing approach at Smyshliaevka airfield near Samara. Probable cause – tailplane flatter.
A-23
Engines: 2 x RMZ-640 Bouran
Crew: 1+1
A-23 Coach
Year: 1992
Engines: 2 x Rotax 582, 64hp
Maximum range: 620 km
Fuel capacity: 75 lt
Crew: 1+1
Price 2010: 25,000US$
Unassembled kit 2010: 12,700US$
A-23M Baby Dragon
Year: 1999
Crew: 1+1
Engines: 2 x Rotax 952, 100hp
Length: 7.5m
Height: 2.4m
Wingspan: 9.8m
Empty weight: 300kg
Maximum Takeoff weight: 600kg
Power load: 6 kg/hp
Maximum sustained speed: 180km/h
Cruise: 130 to 150km/h
Range
Maximum range: 1000 km
Fuel capacity: 120 lt
Payload Total: 250kg
Price 2010: 35,000US$
Unassembled kit 2010: 12,700US$
A small single-seat lightplane for recreational, agricultural, and civil patrol uses.
A-21 Solo
Wing Span: 6.6 m
Length: 4.7 m
Height: 1.8 m
Take Off Distance: 100 m
Absolute Ceiling: 14000 ft
Optimum Ceiling: 10,000 ft
Maximum Speed: 102 kt
Optimum Speed: 81 kt
Fuel Capacity: 22 lt
MTOW: 3000 kg
Maximum Range: 200 nm
Maximum Climb Rate: 1000 ft/min
Seats: 1
A single seater under FAR103 rules with a composite (Carbon Fiber) pod and metal wings. Price 2009: 6800 EURO. The Solo was only available as a kit
The wings are built by conventional sheet metal useing two spars, 12 ribs and metal skin. All parts are cut and bent on CNC equipment. Wing assembly is designed to be simple and straightforward. The rest of the airframe is a composite construction. Parts are made from carbon and glass fiber in temperature controlled vacuum molds. Sandwich construction techniques are also used to minimize weight and maximize strength. All airframe composite parts in the kit are completely finished, ready for final assembly. Experimental kit price 2009: 8000 EURO.
FAR103
Stall: 23 kt / 26 mph / 42 kmh
Cruise: 49 kt / 56 mph / 90 kmh
VNE: 65 kt / 75 mph / 120 kmh
Empty Weight: 110 kg / 243 lb
MTOW: 220 kg / 485 lb
Climb Rate: 600 fpm / 3 m/s
Glide Ratio: 10
Take-off distance (50ft obstacle): 330 ft / 100 m
Landing distance (50ft obstacle): 330 ft / 100 m
Experimental
Stall: 27 kt / 31 mph / 50 kmh
Cruise: 49 kt / 56 mph / 90 kmh
VNE: 70 kt / 81 mph / 130 kmh
Empty Weight: 115 kg / 254 lb
MTOW: 210 kg / 463 lb
Climb Rate: 600 fpm / 3 m/s
Glide Ratio: 8
Take-off distance (50ft obstacle): 490 ft / 150 m
Landing distance (50ft obstacle): 490 ft / 150 m
The design team of Aeroplanes DAR had the goal to modify the existing model DAR-21. The first serious change was a new wing. The new wing results indicated a 17-20 percent better performance than the original design. The new airframe structure had reduced weight, while increasing the rigidity. The new technology gave better results kept the general outside lines. The DAR Speedster continued this with small changes. Many details have been redesigned and improved for aerodynamic reasons.
Price 2009: 30000 EURO
Stall: 32 kt / 37 mph / 60 kmh
Cruise: 108 kt / 124 mph / 200 kmh
VNE: 127 kt / 146 mph / 235 kmh
Empty Weight: 113 kg / 250 lb
MTOW: 204 kg / 450 lb
Climb Ratio: 1800 fpm / 9 m/s
Glide Ratio: 10
Take-off distance (50ft obstacle): 490 ft / 150 m
Landing distance (50ft obstacle): 490 ft / 150 m
Of all metal construction, and priced (Ex-work Sofia, Bulgaria), complete DAR-23 with HKS 700 E in 2009, 17500 EUR and DAR-23 kit without engine, prop and instruments, 10500 EUR.
Stall: 24 kt / 28 mph / 45 kmh
Cruise: 49 kt / 56 mph / 90 kmh
VNE: 65 kt / 75 mph / 120 kmh
Empty Weight: 195 kg / 430 lbs
MTOW: 380 kg / 838 lb
Climb Rate: 800 ft/min / 4 m/s
Glide Ratio: 6
Take-off distance (50ft obstacle): 330 ft / 100 m
Landing distance (50ft obstacle): 330 ft / 100 m
The DAR-21 is a two-seat aircraft using a wide range of engines from the two stroke Rotax 582 series of 65 hp to the 4 cylinder 4 stroke Jabiru 2200 of 80 hp. Aluminium alloys 1050, 2024, 3105 and 6061 are the basic building materials of the DAR-21 airplane.
DAR-21 S is based on 2024 and 6061 aluminum alloys.
DAR21 Tropic is based on using the soft 1050 and 3105 aluminum alloys. These materials are softer, but with better anti-corrosion quality.
The welded metal parts are made of lowcarbonic structure steel 4130, while turnery and milling parts are made of structure steel 4340.
The cabin is fully closed, with tandem seating. There is only one door on the right side giving access both to seats and cargo sector. All necessary navigation and engine control instruments are set in one panel. The controls are dual and allow piloting from front or rear seats.
The DAR-21S is a little bit bigger than DAR-21.
2009 Pricing Ex-work:
Complete airplanes:
DAR-21 with Rorax 912 – 31500 EUR
DAR-21 with Jabiru 2200 – 31450 EUR
DAR-21 kit without engine, prop and instruments – 20700 EUR
Complete DAR-21 S with Rotax 582, 30840 EUR HT & 36885 EUR TTC
DAR-21 S with ROTAX 912, 38225 EUR HT & 45717 EUR TTC
DAR-21
Stall: 32 kt / 37 mph / 60 kmh
Cruise: 86 kt / 99 mph / 160 kmh
VNE: 113 kt / 130 mph / 210 kmh
Empty Weight: 230 kg / 507 lb
MTOW Weight: 450 kg / 992 lb
Climb Ratio: 800 fpm / 4 m/s
Glide Ratio: 10
Take-off distance (50ft obstacle): 660 ft / 200 m
Landing distance (50ft obstacle): 490 ft / 150 m
DAR-21 S
Stall: 35 kt / 40 mph / 65 kmh
Cruise: 81 kt / 93 mph / 150 kmh
VNE: 108 kt / 124 mph / 200 kmh
Empty Weight: 280 kg / 617 lbs
MTOW: 500 kg / 1102 lb
Climb Rate: 1000 fpm / 5 m/s
Glide Ratio: 10
Take-off distance (50ft obstacle): 490 ft / 150 m
Landing distance (50ft obstacle): 490 ft / 150 m
A high-wing monoplane, with cruciform tail, the Swallow used conventional three-axis controls with stick and rudder bar for controlling ailerons, elevator and rudder. The Swallow was powered by two single-cylinder Yamaha engines nmounted at the front using a central drive shaft to pusher Yrral 52×34-inch prop. Fitted with tricycle undercarriage with fiberglass rod-sprung suspension. Wheels are 10-inch pneumatics.
Aeroplane Marketing Swallow Article
Engines: 2 x Yamaha 200cc, 30 hp
Wingspan: 34 ft
Wing area: 136 sq.ft
Empty weight: 225 lb
Wing loading: 2.87 lb/sq.ft
Fuel capacity: 3.8 USG
The Aeropilot Legend 540 is a Czech ultralight aircraft, designed and produced by Aeropilot.
The Legend 540 is a scale two-seat version of the Cessna 182, rendered in composites, instead of sheet metal. The aircraft was designed to comply with the Fédération Aéronautique Internationale microlight rules. It features a strut-braced 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 fibre. Its 9.06 m (29.7 ft) span wing employs flaps. Standard engines available are the 100 hp (75 kW) Rotax 912ULS and the 85 hp (63 kW) Jabiru 2200 four-stroke powerplants.
Introduced at the Aero show held in Friedrichshafen in 2011, the aircraft was supplied complete and ready-to-fly-aircraft with a 2015 unit cost of €63,000.
Legend 540
Engine: 1 × Rotax 912ULS, 75 kW (100 hp)
Wingspan: 9.06 m (29 ft 9 in)
Wing area: 10.54 sq.m (113.5 sq ft)
Airfoil: MS313
Length: 7 m (23 ft 0 in)
Height: 2.6 m (8 ft 6 in)
Empty weight: 289 kg (637 lb)
Gross weight: 472.5 kg (1,042 lb)
Fuel capacity: 100 litres (22 imp gal; 26 US gal)
Maximum speed: 225 km/h (140 mph, 121 kn)
Cruise speed 75% power: 210 km/h (130 mph, 110 kn)
Stall speed: 62 km/h (39 mph, 33 kn)
Never exceed speed: 255 km/h (158 mph, 138 kn)
Range: 1,300 km (810 mi, 700 nmi)
Endurance: 7 hours
Rate of climb: 7 m/s (1,400 ft/min)
Crew: one
Capacity: one passenger
