iKarus C42 Owner's Manual

C42 Owner’s Manual (Microlight) Page 18
Loading plan
Position weight x lever arm = moment
kg mm kg.mm
Empty weight
1. Seats 400
2. Under seat bags 400
3.
F
uel 950
4.
S
amsonite case 950
Total W eight kg Total Moment kg.mm
Total Moment kg.mm
centre of gravity CG = ------------------------------------------ = mm
Total W eight kg
6.2 Conditions of Weighing
The dry empty weight of the aircraft is defined under the following conditions:
All normal installed equipment fitted.
Oil and coolant levels normal.
No usable fuel.
Note: Remaining within the maximum Take-off Weight (MTOW) of 450 kg (or 472.5kg with
appropriate modifications fitted) is the pilot’s responsibility.

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