Photograph:
Zenair CH-801 VH-VBG (c/n 8-8048) at Avalon, VIC in 2003 (David C Eyre)
Country of origin:
United States of America
Description:
Four-seat light utility aircraft
Power Plant:
One 134 kw (180 hp) Lycoming O-360 four-cylinder horizontally-opposed air-cooled engine
Specifications:
- Wingspan: 9.55 m (31 ft 4 in)
- Length: 7.5 m (24 ft 6 in)
- Height: 3.0 m (10 ft)
- Wing area: 15.5 m² (167 sq ft)
- Max speed: 180 km/h (112 mph)
- Cruising speed at 75% power at 2,134 m (7,000 ft): 170 km/h (106 mph)
- Stalling speed [flaps down]: 56 km/h (35 mph)
- Stalling speed [flaps up]: 69 km/h (43 mph)
- Rate of climb: 366 m/min ((1,200 ft/min)
- Service ceiling: 4,877 m (16,000 ft)
- Range [standard fuel]: 515 km (320 miles)
- Fuel capacity [standard]: 114 litres (25 imp gals)
- Take-off roll: 88 m (290 ft)
- Empty weight: 522 kg (1,150 lb)
- Useful load: 478 kg (1,050 lb)
- Loaded weight: 1,000 kg (2,200 lb)
History:
Introduced into the Zenith range of light aircraft in 1998, the CH-801 was designed to expand the utility of the STOL CH-701 series by increasing the useful load to over 454 kg (1,000 lb) whilst retaining the original design’s short and rough field capability. Seating four, the aircraft was sturdy, produced by Zenith Aircraft Co of Mexico, Minnesota, designed by Christopher Heintz, and could be fitted with engines in the 112 kw (150 hp) to 168 kw (225 hp) range.
High-speed performance was traded for a wing design that incorporated a substantial fixed leading-edge wing slat, together with trailing-edge flaperons, a short thick wing for maximum strength, and good ground manoeuvrability. The full-length flaperons acted as full-span ailerons and/or full span flaps. They formed an aerofoil hanging below the wing trailing-edge, where undisturbed air flowed over them for maximum control at low speed. Hoerner wingtips maximised the effective lift area and minimised wingtip vortices.
The fuselage was semi-monocoque stressed skin, being formed around a welded steel tube frame. Available in kit form, it was provided with a rugged all-terrain tricycle undercarriage, the main wheels having disc brakes and a steerable nose wheel. The wings were removable and the tail featured an all-flying rudder.
Similar in appearance to the CH-701 but much larger, it was aimed at pilots who required an off-airport design to operate from rough private strips, and, seating four, to have the capability of a cargo-hauling bush transport. Simple systems made the aircraft easy to build and maintain, whilst maximising the slow stalling speed.
Development commenced in 1988 when Chris Heintz commenced design and construction of a four-seat aircraft for a customer. The prototype was never completed as a suitable engine was not available at that time. Eventually development of the four-seater led to the CH-801 which could be fitted with conversions of automotive power plants to meet the requirements of operators in remote parts of the world, particularly third-world countries, the requirement to operate on auto fuel being paramount, along with consideration of spare parts for the engine.
First of the type registered in this region was c/n 8-4048, which became VH-VBG in September 2000. Further aircraft have been built, the first in New Zealand becoming ZK-PIP registered to Addis Holdings Ltd of Papakura, this aircraft having been completed in Austria where it was initially registered in 2002 as OE-KWJ, later operating with Twenty One Twelve of Christchurch.