iKarus C42 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 Specifications

General

Manufacturer	Comco Ikarus
Type	Ultralight Aircraft
Engine	Rotax 912
Cruise Speed	160 km/h
Stall Speed	65 km/h
Seats	2
Height	2.3 m
Maximum Takeoff Weight	472.5 kg
Range	800 km
Service Ceiling	4000 m
Power Output	80 hp
Rate of Climb	5 m/s