English name: Corvette
US marketing name: Pelican
TYPE: Three-seat amphibian/kitbuilt.
PROGRAMME: Developed on basis of four earlier amateur-built, Vikhr-engined Che-20s, winners of many light aircraft competitions; design and construction of prototype started 1988, first flight 1989; construction of production aircraft started 1992, first flight 1993; more than 5,000 hours of test and training flights, and more than 120 amateur pilots trained on prototype and production aircraft in first five years. Promotion also undertaken by Refly; launched as Refly Pelican at EAA AirVenture, Oshkosh, 2000.
Upgraded version under development and certification during 2001 features cantilever wing, strengthened tail unit with increased rudder area, new control system, redesigned engine support and modified instrument panel; flight testing was completed at the end of 2001 and JAR/FAR Pt 23 certification awarded in early 2002.
CURRENT VERSIONS:Corvette 503: With two Rotax 503 UL two-cylinder two-stroke engines.
Corvette 582: With two Rotax 582 UL two-cylinder two-stroke engines.
Corvette 912: With one Rotax 912 UL four-cylinder four-stroke engine.
Refly Pelican: Generally as for Corvette 582.
CUSTOMERS: First preproduction delivery to a forest control organisation 1990. One (Che-22R-2 c/n 006, RP-X1548 of OVOS WLL Co) sold in Philippines. Other to China, Spain and Vietnam. Total 60 built by February 2002, including 10 in 2000. First Pelican in US (N27NS, ex-RA-02777) registered in March 2001.
COSTS: Standard aircraft US$35,000 to US$55,000 (2002).
DESIGN FEATURES: Designed to JAR-VLA, FAR Pt 23 and AP-23 requirements, for maximum simplicity of design and construction; primarily for forestry applications, but suitable for patrol, inspection and ecological monitoring of hunting and fishing locations, border patrol, training and business operations. Quoted build time 1,500 hours, or 50 hours for fast build kit.
Braced parasol monoplane, with light central cabane and single main bracing, strut and bracing wire each side; downturned wingtips serve as stabilising floats; flying-boat hull with two steps; unswept strut-braced horizontal tail surfaces mounted on fin of sweptback vertical surfaces; engine(s) mounted on leading-edge of wing centre-section. US demonstrator has fin of reduced heigh. Unswept constant chord wing; CAHI (TsAGI) P-IIIA section, thickness/chord ratio 15 per cent; incidence 4o 30'; dihedral 1o 30'. Airframe life 3,000 flying hours.
FLYING CONTROLS: Conventional and manual, with pushrod actuation. Full-span slotted flaperons, elevators and horn-balanced rudder; fixed tab on port elevator.
STRUCTURE: Single-spar wing of riveted duralumin; fuselage, tail unit and integral wingtip floats of vacuum-moulded GFRP sandwich; flaperons fabric-covered.
LANDING GEAR: Optional tailwheel type; mainwheels, tyre size 350x120, carried on cantilever GFRP spring. GFRP skis optional.
POWER PLANT: Two 37 kW (49.6 hp) Rotax 503 UL-2V or two 47.8 kW (64.1 hp) Rotax 582 UL or 59.6 kW (79.9 hp) Rotax 912 UL. Two-blade wooden or three-blade GFRP fixed-pitch propeller(s) of Russian manufacture. Two fuel tanks in wing centre-section, 100 litres (26.4 US gallons; 22.0 Imp gallons); gravity fuelling.
ACCOMMODATION: Pilot and two passengers under large glazed blister canopy, giving exceptional field of view. Detachable windscreen panels. Gull-wing canopy/door each side.
SYSTEMS: 12/24 V electrical system.
AVIONICS: Comms: VHF radios.
Flight: Garmin GPS.
EQUIPMENT: Optional BRS parachute.