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|Role||Fixed wing microlight and light-sport aircraft|
The Ikarus C42 is a two-seat, fixed tricycle gear, general aviation microlight airplane, manufactured in Germany by Comco Ikarus. It is used primarily for flight training, touring, and personal flying.
Design and development
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.
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.
These specifications relate to the Ikarus C42 fitted with a Rotax 912ULS (100hp) engine.
Where a single speed appears, it is applicable to the aircraft at maximum gross weight of 1,040 pounds (470 kg). Where a range appears, the lower speed is applicable at empty weight of 572 pounds (259 kg), while the higher speed is applicable at maximum gross weight.
- VR (rotation): 40 KIAS (74 km/h)
- VY (best rate of climb): 62 KIAS (115 km/h)
- VA (maneuvering): 82 KIAS (152 km/h)
- VNO (max cruise): 105 KIAS (194 km/h), 83 KIAS in Still Air
- VNE (never exceed): 121 KIAS (224 km/h)
- VFE (flaps extended): 63 KIAS (117 km/h)
- VREF (40° flaps, approach): 52 - 60 KIAS (96 – 111 km/h)
- VS0 (stall, dirty): 33 KIAS (61 km/h)
- VS1 (stall, clean): 42 KIAS (78 km/h)
- Crew: 1
- Capacity: 1 passenger
- Length: 20 ft 6 in (6.25 m)
- Wingspan: 31 ft 0 in (9.45 m)
- Height: 7 ft 4 in (2.24 m)
- Wing area: 134.5 ft² (12.5 m²)
- Empty weight: 583 lb (265 kg)
- Max. takeoff weight: (depends on country) approx 1,041 lb (450 kg (UK without BRS, 472.5kg With BRS Fitted)
- Wing loading: 37.8 kg/m²)
- Powerplant: 1 × Rotax 912s flat-4 engine, 100 hp (75 kW) three-blade, ground adjusted, carbon fibre, fixed-pitch propeller
- Range: 432 miles (375 nm, 695 km)
- Extended range 898 miles (780 nm, 1,445 km) with long-range tanks
- Rate of climb: 1050 ft/min (320 m/min)
- Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, pages 36-37. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
- Kent Misegades (March 2009). "The History of Comco Ikarus Aircraft Company". Sport Aviation.
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