TYPE: Two-seat lightplane.
PROGRAMME: Prototype C-FQCU first flown 26 June 1993; Canadian and US certification of prototypes 26 and 31 July 1994, respectively; first two production models (C-FRSK and C-FRSV) completed April 1994. First delivery September 1994; US type certification 25 July 1995 in Utility category and 29 January 2003 in Normal capacity. A test example fitted with 104.5 kW (140 hp) Lycoming O-320 was produced in 1995. Certified for IFR operations and spins on 2 October 1996. JAA certification received March 2000. Company revealed it would produce a lighter version during 2001, with 95 litre (25.0 US gallons; 20.8 Imp gallon) fuel capacity.
CURRENT VERSIONS: CH 2000: Standard production model, as described.
CH2T: Total of 43 delivered by time production moved from Canada to US in June 1999. First US-built aircraft (N17KA, one of 11 CH2Ts for KeyFlite Academy at Utica, New York, and Nashua, New Hampshire) received C of A on 14 January 2000 and delivered following day. Additionally, Zenair built production aircraft 0063 to 0065. A total of 86 built by August 2003.
COSTS: CH 2000 US$119,000 (2002). Provisional cost of lightweight version US$84,900 (2001).
DESIGN FEATURES: Side-by-side two-seat and smaller-span derivative of Tri-Z CH 300. Designed to conform to FAR Pt 23 (JAR-VLA equivalent level of safety). Conventional, low-wing configuration, with mid-mounted tailplane and sweptback fin.
Wing section LS (1) 0417 (mod).
FLYING CONTROLS: Manual. All-moving tailplane deflects 12° up and 9° 30' down with anti-balance tabs; all-moving fin/rudder with horn balance deflects 21° 30' each way. Electrically actuated split flaps lower to 50°; ailerons deflect ±15°.
STRUCTURE: Semi-monocoque fuselage of aluminium alloy, with stressed skins. Wings and tailplane aluminium skinned.
LANDING GEAR: Non-retractable tricycle type with steerable (±14°) nosewheel. Shock-cord absorption on nosewheel. Cleveland 5.00-5 in wheels with hydraulic disc brakes on mainwheels. Optional wheel fairings.
POWER PLANT: One 86.5 kW (116 hp) Textron Lycoming O-235-N2C, driving metal Sensenich 72-CK-0-46 or 72-CK-0-48 two-blade propeller. Fuel capacity 106 litres (28.0 US gallons; 23.3 Imp gallons) standard of which 104 litres (27.5 US gallons; 22.9 Imp gallons) are usable. 129 litres (34.0 US gallons; 28.3 Imp gallons) optional. Oil capacity 5.7 litres (1.5 US gallons; 1.25 Imp gallons).
SYSTEMS: 12 V 60 A, heavy-duty battery.
ACCOMMODATION: Two persons, side by side, with dual controls; upward-hinged door each side; fixed windscreen; rear side windows. Baggage shelf behind seats.
AVIONICS: Comms: Based around Garmin GNS 430 COM/VOR/GPS. GI 106CDI. GMA 340 audio panel and GTX 327 transponder. Options include PS 100II intercom.