1998:
Postfach 1623
D-28689 Apen
Germany
UL builder
LSA/UL
Aerotecknik EV-97 Eurostar / Sportstar / Evektor Aircraft SportStar MAX / Harmony
In 1996 Aerotechnik with Evektor began development of the EV-97 team Eurostar airplane.
A two-seat light or ultralight monoplane designed for sport/leisure flying, touring and training with limitation to non-aerobatic VFR operations. The Eurostar is aerodynamically controlled, single-engine, two-seat, low-wing, all metal plane with a fixed tricycle undercarriage and controllable nose wheel. The aircraft is equipped with four cylinder four stroke 80 HP Rotax 912 UL engine, optionally 100 HP Rotax 912 ULS or 80 HP Jabiru 2200.
Beginning in 2000 was the development of the EV-97 VLA airplane. This aircraft is called SportStar in US and EuroStar in Europe. Development of the SportStar version began in 2003.
By 2009, over 800 of the EuroStar had been delivered worldwide and the 2009 price was 50000 Euro.
The EuroStar SL is an advanced ultralight airplane with 46.5 inches / 1.18 meters of shoulder room, new system of cockpit climate control, and state of the art glass cockpit avionics. During testing more than 450 spins in all configurations were carried out. The airplane was type approved by the Ministry of Defence of the Czech Republic and is operated by the Pilot Training Centre of the Czech Army for initial pilot training.
The EuroStar SL has an all metal anodised and corrosion-proofed aluminium airframe. It has all joints of construction riveted as well as bonded for durability and long fatigue life.
The EuroStar is certified for towing of the sailplanes up to 700 kilos (Duo Discus, Janus, Ventus, ASK 21, Ventus, Blanik etc.) and for towing of banners up to 140 sq.m.
The SportStar MAX is an S-SLA aircraft business travel or training.
The airplane was the very first aircraft approved by the FAA (2005) in the U.S. S-LSA category and is holder of the prestigious “S-LSA Aircraft of the Year” honour from AeroNews Network (ANN).
The SportStar MAX with a re-designed, based on an EASA JAR-VLA certified pilot training airplane, airframe at 1320 lb / 600 kg MTOW provides up to 640 lb / 290 kg of useful load combined with range 700 nm / 1300 km, and was available as an IFR version. The SportStar MAX combines aerodynamic composite materials with an all-metal primary airframe structure.
The SportStar MAX build quality and reliability is based on Evektor´s certified aircraft production by the European Aviation Safety Agency (EASA), ISO 9001:2000 Quality Management System as well as LAMA certification.
The canopy gives 46.5 inches / 1.18 meters of shoulder room, and glass cockpit avionics.
The SportStar MAX has an all metal anodised and corrosion-proofed aluminium airframe with all joints of construction riveted as well as bonded. The SportStar is certified for towing of the sailplanes up to 700 kilos (Duo Discus, Janus, Ventus, ASK 21, Ventus, Blanik etc.) and for towing of banners up to 140 sq.m.
The SportStar is a Light Sport Aircraft (LSA) designed for pilot training, sport and leisure flying and touring with limitation to non-aerobatic VFR operations.
The Evektor fully certified (European EASA standard), general aviation-quality aircraft is conventionally powered (Rotax), and has evolved to the flagship Harmony and includes the SportStar MAX, both with all-metal construction, long range economy cruise at 110 knots by 2012. Base prices 2012: US$98,000 (MAX); US$102,000 (Harmony).
Evektor EV-97 Team Eurostar
Engine: Rotax 912 ULS, 100 hp
TBO: 1,500 hrs
Propeller: Fixed, on-ground or in-flight adjust
Cabin width: 46.5 in / 1.18 m
Length: 17 ft 7.5 in / 5.98 m
Height: 8 ft 1.6 in / 2.48 m
Wing span: 26 ft 7 in / 8.1 m
Empty weight: 609 lb / 276 kg
MTOW: 992 lb / 450 kg
Design load: +6 g / -3g
Max. baggage: 33 lb / 15 kg
Wing tanks cap: 17.17 USG / 65 lt
Vne: 270 km/h
Stall speed: 65 km/h
Maximum level speed: 240 km/h
Rate of climb: 7.5 m/s
Cruise 75% power: 200 km/h
Service ceiling: 6,000 m
Take-off distance: 200 m
Maximum range: 750 km
Landing distance: 300 m
Aerotow
Engine: Rotax 912 ULS, 100 hp
Prop: Woodcomp SR 3000XC electrically variable
Take-off run: 200-300m
TO dist 50ft: 450-600m
Climb speed: 100-120 kph
ROC: 2-3 m/sec
Cruise speed: 120-160 kph
Engine: Rotax 912 UL, 80 hp
TBO: 1,500 hrs
Propeller: Fixed, on-ground or in-flight adjustable
Cabin width: 46.5 in / 1.18 m
Length: 17 ft 7.5 in / 5.98 m
Height: 8 ft 1.6 in / 2.48 m
Wing span: 26 ft 7 in / 8.1 m
Empty weight: 609 lb / 276 kg
MTOW: 992 lb / 450 kg
Design load: +6 g / -3g
Max. baggage: 33 lb / 15 kg
Wing tanks cap: 17.17 USG / 65 lt
Vne: 270 km/h
Stall speed: 65 km/h
Maximum level speed: 220 km/h
Rate of climb: 5.0 m/s
Cruise 75% power: 180 km/h
Service ceiling: 6,000 m
Take-off distance: 280 m
Maximum range: 750 km
Landing distance: 300 m
Glide Ratio: 1:12
Evektor SportStar
Engine: Rotax 912ULS, 100 hp
TBO: 1500 hr
Prop: Fixed, ground adjustable
Wingspan: 28 ft 5 in / 8.65 m
Overall length: 19 ft 7.5 in / 5.98 m
Height: 8 ft 2 in / 2.48 m
Power loading: 12.1 lb/hp
Max ramp weight: 1212 lb
Gross weight: 1212 lb
MTOW US VG: 1,320 lb / 600 kg
Landing weight: 1212 lb
Empty weight, std: 680 lb / 309 kg
Useful load: 522-640 lb /237-291 kg
Useful fuel, std: 31.2 USG / 118 lt
Payload, full std. fuel: 355 lb
Seating: 2
Cabin width: 46.5 in / 1.18 m
Vne: 146 KIAS / 270 km/h
Maximum level speed: 115 KCAS / 213 km/h
Cruise 75% pwr: 100-110 kt
Fuel consumption 75%: 4.5-5.0 USG/hr
Stall speed: 40-46 kt / 74-83 kph
Best rate of climb SL: 840 fpm
Service ceiling: 13,100 ft
Takeoff ground roll: 620 ft / 190 m
Landing ground roll: 590 ft / 180 m
Baggage volume: 6.2 cu.ft / 175 lt
Max. baggage: 55 lb /25 kg
Design load: +6 g / -3g
Maximum range: 700 nm / 1,300 km
Total endurance: 8.5 hrs
Aerotow
Engine: Rotax 912 ULS, 100 hp
Prop: Woodcomp SR 3000XC electrically variable
Take-off run: 200-300m
TO dist 50ft: 450-600m
Climb speed: 100-120 kph
ROC: 2-3 m/sec
Cruise speed: 120-160 kph
Evektor Sportstar SL
Engine: Rotax 912 ULS / Rotax 912S (IFR)
Horsepower: 100
MTOW: 1320 lb
Empty weight, equipped: 745 lb
Useful load, std: 575 lb
Overall height: 8 ft 2 in
Overall length: 19 ft 7.5 in
Wingspan: 28 ft 5 in
Baggage volume: 6.2 cu. ft
Baggage capacity: 55lb
Wing tanks cap: 31.2 USG
Design load factors: +6/-3 G
Cabin width: 46.5 in
Vne: 146 KIAS
Vs: 45 KCAS
Vso: 40 KCAS
Max speed: 115 KCAS
Cruise 75% power: 110 KCAS
Range: 700 nm
Total endurance: 8.5 hr
Rate of climb, SL: 1020 fpm
Service ceiling: 15,500 ft
Takeoff ground roll: 620 ft
Landing ground roll: 590 ft
Aerotecknik Eurostar
Engine: Rotax 912, 80 hp
Wing span: 7.9 m
Wing area: 10.2 sq.m
MAUW: 480 kg
Empty weight: 275 kg
Fuel capacity: 50 lt
Max speed: 225 kph
Cruise speed: 185 kph
Minimum speed: 65 kph
Climb rate: 4.5 m/s
Fuel consumption: 9 lt/hr
Certification: Vz, CZ UL Z
Seats: 2
Price (1998): 98,850 DM
Aerotecknik CZ Sro
On January 1, 1970 the company Aerotechnik was established. The main scope of business was development and manufacturing of small aircraft. Single-seat and two-seat versions of A-70 gyroplane belonged among the first designs.
Since 1972 Aerotechnik has extended its scope of business on overhauling, maintenance and rebuilding of small GA aircraft (Zlín aircraft series, L-60 Brygadýr). Service activities of Zlin aircraft was terminated in mid 90´s.
After Aerotechnik merged with Evektor – an aircraft and automotive design company in Czech Republic, Aerotechnik was transformed into the share holding company Evektor-Aerotechnik in 1999. Evektor-Aerotechnik is based in Kunovice airport in the Czech Republic.
Production of light sport aircraft and advanced UL aircraft was launched in 1996, starting with P220UL Koala aircraft and followed by EV-97 Eurostar (introcuced in 1997) and SportStar aircraft programes. Evektor SportStar became the very first light sport aircraft in the world approved by FAA in USA in 2004.
Also offers the P 220 UL sports two-seater in kit form in light and ultralight versions, and is marketing the braced high-wing two-seat Fox (a variant of the German Ikarusflug Eurofox, with Evektor of the Czech Republic having undertaken important design work, and Aeropro of Slovakia building airframes for Fox and Eurofox).
In 1997–2004 Evektor-Aerotechnik was participating in subdeliveries of airframe parts in program of single engine turboprop Aero 270 of Aero Vodochody. In 2004 the company introduced single engine four-seater VUT100 Cobra and in 2010 new modern twin engine turboprop Evektor EV-55 Outback made roll-out followed by first flight in 2011.
1998:
Airport
CZ-68604 Kunovice
Czech Republic
Aero Tech Canadian Skyrider
Single seat single engined high wing mono¬plane with hybrid control. Wing has constant chord; cruciform tail. Pitch control by weight¬shift; yaw control by fully flying rudder; no separate roll control; control inputs through weight shift for pitch/yaw/roll. Wing braced from above by kingpost and cables, from below by cables; single ¬surface. Undercarriage has three wheels in tricycle formation; torsion bar suspension on all wheels. Nosewheel steering. No brakes. Aluminium tube framework, without pod. Engine mounted above wing driving pusher propeller. Framework from 6061T6 and 2024T3 aluminium, 4130 aircraft steel; coated stainless steel rigging, Dacron wing surface.
The Canadian Skyrider is a hybrid control ultra¬light, the pilot using his swing seat as the principal means of control, with his weight shift aided in yaw by a rudder.
Standard power unit is a twin cylinder Cuyuna 430R with dual ignition and in flight recoil restart facility. Alternatively, the sing¬le cylinder Cuyuna 215 cc engine may be fitted. Construction time is estimated at 30 h; a trailer is needed for transportation.
After producing between 150 and 200 aircraft, the future of the company seemed in some doubt in 1983.
Engine: Cuyuna 430R, 30 hp
Propeller: 48 x 23 inch, 1.22 x 0.58 m
Reduction ratio: 2.0/1
Power per unit area: 0.19 hp/sq.ft, 2.0 hp/sq.m
Wing span: 32.0ft, 9.75m
Fuel capac¬ity: 3.8 USG, 3.2 ImpG, 14.4 lt
Contant chord: 5.0 ft, 1.52 m
Total wing area: 160 sq.ft, 14.9 sq.m
Aspect ratio: 6.4/1
Nosewheel dia. Overall: 11 inch, 28cm
Empty weight: 155 lb, 70 kg
Main wheels dia overall: 11 inch, 28cm
MTOW: 420 lb, 191 kg
Payload: 265 lb, 120 kg
Vne: 55 mph, 88 kph
Wing loading: 2.62 lb/sq.ft, 12.8 kg/sq.m
Power loading: 14.0 lb/hp, 6.4 kg/hp
Engine: Cuyuna 215R, 20 hp
Power per unit area: 0.13 hp/ sq.ft, 1.3 hp/ sq.m
Wing span 32.0ft, 9.75m.
Fuel capac¬ity: 3.8 USG, 3.2 ImpG, 14.4 lt
Contant chord: 5.0 ft, 1.52 m
Total wing area: 160 sq.ft, 14.9 sq.m
Aspect ratio: 6.4/1
Nosewheel dia overall: 11 inch, 28cm
Vne: 55 mph, 88 kph
Main wheels dia overall: 11 inch, 28cm
Aero Tech
1983: Aero Tech Aviation, Box 280, Goderich, Ontario N7A3Z2, Canada.
Built UL
Aerostyle Breezer
Powered by a modified BMW engine, which has as standard, fuel injection system, favorable mass production technology and no carburetor icing. With a view under the Cowling immediately the clear and low-maintenance installation of the engine as well as the associated aggregates is noticeable.
In 2001 an Aerostyle Breezer was equipped with a Rotax 912 S and certified.
Stall: 35 kt / 40 mph / 64 kmh
Cruise: 108 kt / 124 mph / 200 kmh
VNE: 132 kt / 152 mph / 245 kmh
Empty Weight: 295 kg / 650 lbs
MTOW Weight: 450 kg / 992 lbs
Climb Ratio: 1000 ft/min / 5.1 m/s
Aerostructure PLM 80
Single seat single engined mid wing mono¬plane with conventional three axis control. Wing has swept forward leading and trailing edges, and tapering chord; T tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by one third span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; wing profile Worthmann FX 66SA96 V1; dou¬ble surface. Undercarriage has two wheels in tandem with wing tip skids and tailskid; no suspension on any wheels. Push right go right tailwheel steering connected to yaw control. Brake on main wheel. Glass fibre fuselage, totally enclosed. Engine mounted above wing driving pusher propeller.
The designation PLM80 clearly shows that this aircraft is what the French call a planeur leger motorise, which translates as motor glider rather than micro¬light. As we write, this prototype has hardly completed its first flights and at present exceeds most countries’ definition of a micro¬light. In 1982, this latest product from Aerostruc¬ture is being test flown with a view to conventional certification.
Its structure is made entirely of glass fibre laminates, as with all modern conventional gliders, and the PLM80 has a Worthmann FX66S-196V1 profile, set at 1½O incidence and with the maximum coefficient of lift of 1.5. The drag coefficient 0.45. The wing is also fitted with air brakes, totalling 1.79sq.ft (0.166sq.m) in surface area and which can travel from + 16 to 21%. The T tail uses Worthmann FK71L 150/42.5 profiles vertical fin and 150/30 for the horizontal, with the latter installed at 2.5% incidence.
The engine is also a prototype, the three ¬cylinder French PAL640 from JPX, which was on static show at the end of July 1982 at Brienne le Chateau, the annual convention for European homebuilders. At that time it had just completed its bench testing. It drives a three bladed propeller directly, of fixed pitch and 37 inch (0.93 m) diameter.
Engine: JPX PAL640, 32 hp at 4600 rpm.
Propeller diameter: 37 inch, 0.93 m.
Power per unit area: 0.46 hp/sq.ft, 5.0 hp/sq.m.
Empty weight: 353 lb, 160kg.
Max take off weight: 618 lb, 280kg.
Payload: 265 lb, 120kg.
Max wing loading: 8.95 lb/ sq.ft, 43.8 kg/sq.m.
Max power loading: 19.3 lb/hp, 8.8kg/hp.
Load factors: +8.0, 4.0 ultimate.
Length overall: 16.7 ft, 5.1 m.
Height overall: 3.5ft, 1.04m.
Wing span: 36.1ft, 11.0m.
Chord at root: 2.7ft, 0.8m.
Chord at tip: 1.2ft, 0.35m.
Dihedral: 4 degs
Sweep forward: 3.5degs
Tailplane span: 5.9 ft, 1.8 m.
Fin height: 3.4ft, 1.0 m.
Total win area: 69 sq.ft, 6.4 sq.m.
Total aileron area: 9.1 sq.ft, 0.85 sq.m.
Fin area: 6.5 sq.ft, 0.6 sq.m.
Rudder area: 2.7 sq.ft, 0.25 sq.m.
Tailplane area: 7.8 sq.ft, 0.72 sq.m.
Total elevator area: 2.3 sq.ft, 0.22 sq.m.
Wing aspect ratio: 18.9/1.
Tailwheel diar overall: 8 inch, 20 cm.
Main wheel dia overall: 12 inch, 30 cm.
Aerostructure
1982: Aerostructure, ZI, La Lande, 33450 Saint¬Loubes France.
Aerostar Festival R40S
The Festival, manufactured by SC Aerostar S.A. of Romania, is a ready-to-fly, FAA certified, Special Light Sport Aircraft, and has been designed with one idea in mind: To create an affordable airplane which is safe, simple, and easy to inspect, maintain and operate.
Stall: 36 kt / 41 mph / 66 kmh
Cruise: 101 kt / 116 mph / 187 kmh
VNE: 130 kt / 150 mph / 241 kmh
Empty Weight: 388 kg / 855 lbs
MTOW: 599 kg / 1320 lbs
Climb Ratio: 770 ft/min / 4 m/s
Glide Ratio: 1:12
Take-off distance (50ft obstacle): 1246 ft / 380 m
Landing distance (50ft obstacle): 951 ft / 290 m
Aerostar 01
A two seat ultralight first flown on 31 May 2001.
Seats: 2.
Range: 450 nm.
All Aero 