EV-AT EV-97 TEAMEUROSTAR

TYPE: Side-by-side ultralight/kitbuilt.

PROGRAMME: Developed as P 220 UL from Pottier P 220 S Koala; extensive redesign started in September 1996; prototype (OK-CUR 97), then known as Eurostar, made first flight May 1997; first customer delivery October 1997. Certified as ultralight in Belgium, Czech Republic, Finland, France, Germany, Italy, Slovak Republic and United Kingdom. First UK-built example (G-NIDG, by distributor Cosmik Aviation) flown in April 2000; local assembly in China by Guizhou Evektor Aircraft Corporation (GEAC); first flight by Chinese-assembled EV-97, 24 October 2000.

CURRENT VERSIONS: Eurostar 2000: Introduced late 1999. Increased fuselage width (4 cm; 1½ in); modified wingtips and increased span; larger ailerons; steerable nosewheel; flush, oval nose air intake. Available factory-built or as kit.
teamEurostar 2001: Further-improved version, introduced in early 2001; choice of Rotax 912 UL or more powerful 912 ULS engine. Name changed to avoid conflict with Eurostar France-UK rail link. teamEurostar 2002: Further improved version meeting Sport Pilot NRPM in USA (where marketed as SportStar), as described.

CUSTOMERS: More than 200 (all versions) ordered, including 36 Model 2000. Sales in 2001 totalled 56 and in 2002, 72. Customers in Belgium, Czech Republic, Estonia, Finland, France, Germany, Ireland, Italy, Netherlands, Poland, Portugal, Russia, Slovak Republic, Spain, Sweden, UK, Ukraine and USA.

COSTS: €49,900 exluding taxes (2003); Chinese version approximately RMB700,000 Yuan (2000).

DESIGN FEATURES: Low-wing monoplane; modified NACA 4415 aerofoil section; dihedral 3o. Wing folding optional.

FLYING CONTROLS: Conventional and manual. Four-position (0/15/30/50o) split flaps. Elevators, starboard aileron and rudder have trim tabs.

STRUCTURE: Mostly of riveted metal; wingtips and mainwheel legs in GFRP.

LANDING GEAR: Fixed tricycle with hydraulic mainwheel disc brakes and (in current version) steerable nosewheel. Wheel sizes 350x140 (main), 300x100 (nose). Optional wheel fairings or mudguards. Optional floats.

POWER PLANT: One 59.6 kW (79.9 hp) Rotax 912 UL flat-four engine standard, with VZLU V230C two-blade, fixed-pitch wooden propeller; 73.5 kW (98.6 hp) Rotax 912 ULS and V534BD-UL three-blade, constant-speed (hydraulic), wooden propeller optional. Jabiru 2200 also optional. Fuel capacity 65 litres (17.2 US gallons; 14.3 Imp gallons) standard, optionally 50 litres (13.2 US gallons; 11.0 Imp gallons).

ACCOMMODATION: Front-hinged, upward-opening canopy, with additional transparency aft of rear frame. Space for 15 kg (33 lb) of baggage aft of seats. Early versions had canopy/rear transparency break line further forward. Optional replacement of rear transparency by metal fairing and bulged cabin sides.

SYSTEMS: 12 V (battery) electrical system.

AVIONICS: To customer's specification.

EQUIPMENT: Optional ballistic parachute, wing-folding mechanism and aero-tow hook.

 

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