iKarus C42 Series User Manual

Pilot Operating Handbook for the C42 Series
POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 56 of 73
Rudder
Left 32° ± 2° 210 mm ± 15 mm
Right 32° ± 2° 210 mm ± 15 mm
Measuring point distance from the steering axis: 410 mm
Elevator
Upwards 28° ± 2° 210 mm ± 15 mm
Downwards 20° ± 2° 130 mm ± 15 mm
Measuring point distance from the steering axis: 410 mm
Flettner rudder (C42C & C42CS)
When the elevator neutral: Flettner rudder
0° ± 2° 78 mm ± 3 mm
Flaps
Note : Flap angle is measured from the flap bottom to the
bottom of the wing at the root area (tangent front to rear
spar)
Position I -5°± 1° 27 mm ± 5 mm
Position II +11°± 1° 60 mm ± 5 mm
(take-off/ landing)
Position III +32°± 1° 170 mm ±10 mm
(landing)
Measuring point distance from the steering axis: 310 mm
Trim tab
Lever nose-down: trim flap in relation to the rudder area -5°
Note: with mechanically actuated trim flaps do not exceed -5°
upwards.

iKarus C42 Series Specifications

General

Manufacturer	Comco Ikarus
Type	Light sport aircraft
Maximum takeoff weight	472.5 kg (1, 042 lb)
Engine	Rotax 912
Horsepower	80 hp (60 kW)
Cruise speed	160 km/h
Range	800 km
Service ceiling	4, 000 m
Stall speed	65 km/h
Rate of climb	5 m/s