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| C42 | |
|---|---|
 | |
| Role | Fixed wing microlight and light-sport aircraft |
| Manufacturer | Comco Ikarus |
| First flight | 1996 |
| Number built | >1,200 |
| Variants | Ikarus C52 |
The Ikarus C42 is a two-seat, fixed tricycle gear, general aviation microlight aircraft, manufactured in Germany by Comco Ikarus. It is used primarily for flight training, touring and personal flying. [1] [2]
The Ikarus C42 is a single-engined high-wing monoplane with side-by-side seats for two in a 1.22 m (48 in) wide cabin. The C42 is manufactured with either an 80 hp (60 kW) Rotax 912 engine or a 100 hp (75 kW) Rotax 912s engine. The Rotax engine has a low fuel consumption and relatively low noise. The engine drives the propeller, which has ground-adjustable pitch, through a gearbox with a 2.273:1 reduction ratio.
The aircraft is structurally supported by a backbone of large diameter aluminium tube which runs the length of the aircraft. The cabin and fuselage shell is a composite material which, being non-structural, can be removed for inspection and repair.
The wings are constructed of tubular front and rear spars. The wings and flying control surfaces are covered in Kevlar/Mylar/Polyester laminate. The wings can be removed or folded (if an optional folding kit is installed) for storage and transportation. The wing tips are of composite construction which reduces drag and improves low speed handling. Access to the cabin is provided by two gull-wing doors. [3]
A single centre stick controls the ailerons and elevators. Electrical pitch trim is controlled by two buttons on the top of the stick, operated by the thumb. A push to talk button is on the front of the stick, operated by the index finger, together with a vertical hand-operated brake lever similar to a motorcycle front brake lever.
Rudder pedals are dual control. The distance from the seat to the pedals is fixed because the seat position is not adjustable.
The dual control throttle levers are situated between the legs, and pivot from side to side so can be folded out of the way making entry and exit of the aircraft easier.
The flaps are controlled by a centrally-mounted lever on the roof of the cabin. The relatively short lever does make the operation of lowering flaps quite physical when combined with holding the centre control stick at the same time.
In conjunction with a Rotax 912 ULS, the Ikarus C42 may be used to tow gliders. The maximum nominal ultimate strength at weak link must not exceed 660 pounds. Banner towing is allowed with the smaller Rotax 912 UL.
Data from Jane's All the World's Aircraft 2000–01 [4]
General characteristics
Performance
Related development
Aircraft of comparable role, configuration, and era
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