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His son Sebastian is listed as the owner of Zenith Aircraft Company. [1] Kit designs manufactured by the company include the original two-seat STOL CH 701, a high-wing all-metal short take-off and landing design, the larger STOL CH 801 four-place aircraft, the STOL CH 750 light sport utility kit airplane, and the two-seat CH 650, an all-metal ...
The design was also influenced by the Zenith CH 601 and the Zenair CH 300. The design goals were to produce a simple four-seat aircraft capable of flying cross country flights with full seats. [2] The CH 640 is a four-seat, low-wing touring aircraft with tricycle landing gear and a single engine in tractor configuration. It has a standard empty ...
A Zenith STOL CH 701 on wheels A Czech Aircraft Works-built CH 701 AMD-built CH 750 CH 750 CH 750 instrument panel CH 701 Turboprop CH 701 Turboprop in flight. The Zenith STOL CH 701 and CH 750 are a family of light, two-place kit-built STOL aircraft designed by Canadian aeronautical engineer Chris Heintz through his Midland, Ontario, based company, Zenair.
The CH 601 HD (for heavy duty) was the follow-on to the original CH 600 and incorporated many improvements to the design. The HD version had a gross weight of 1200 lbs and a standard empty weight of 530 lbs. Aircraft kits were marketed by Zenair of Midland, Ontario in Canada and by Zenith Aircraft of Mexico, Missouri. [33] Zenair CH 601 HDS
The Zenith, which gained the designation Zenith CH 200 when Heintz produced plans for larger and smaller derivatives, is a low-winged cantilever monoplane of all metal construction. The pilot and passenger sit side by side under a clear, sideways-opening plexiglas canopy, while the aircraft is fitted with a fixed nosewheel undercarriage. It is ...
While both aircraft look alike they do not share any common parts. [ 2 ] [ 4 ] The STOL CH 801 is made from sheet aluminium and employs a deep wing chord, full-length leading edge slats and trailing edge flaperons to develop high lift at low speed, while maintaining a short wing-span for maximum strength and ground maneuverability.
Bridgeman, Leonard Jane's All The World's Aircraft 1948. MacMillan, 1948. Bridgeman, Leonard Jane's All The World's Aircraft 1959–60. Sampson, Low, Marston and Company, 1959. Fillingham, Paul Basic Guide to Flying. New York: Hawthorn, 1975. ISBN 0-801-50525-9; Jackson, Paul Janes All the Worlds Aircraft 2004–05, Janes Publishing Company, 2004.
Data from Jane's All the World's Aircraft 1992-93 General characteristics Crew: 1 Length: 20 ft 3 in (6.17 m) Wingspan: 20 ft 2 in (6.15 m) Height: 5 ft 5 in (1.65 m) Wing area: 85 sq ft (7.9 m 2) Airfoil: NACA 0015 Empty weight: 800 lb (363 kg) Max takeoff weight: 1,150 lb (522 kg) Fuel capacity: 27 imp gal (32 US gal; 120 L) in two fuselage tanks Powerplant: 1 × Textron Lycoming IO-360 4 ...