iKarus C42 Owner's Manual

C42 Owner’s Manual (Microlight) Page 17
SECTION 6 - WEIGHT AND BALANCE
6.1 Weight and Balance Calculations
The centre of gravity is measured in mm behind the zero datum. Zero datum is the leading edge root.
The aircraft’s empty weight and cg are derived first: Place the aircraft in a level position on three scales,
such that the stabilizer is horizontal, as shown below. Push down on the rear fuselage, just in front of the
tail, and chock the nose wheel to level the aircraft. Record the reading of each scale.
C
alculate the position of the empty cg, from the formula:
mm
G
G
bG
a ................ X
21
1
=
+
×
−=
(a and b are values to be measured for the specific aircraft).
Insert the values for total empty weight, (G
1
+ G
2
) and cg distance aft of datum, (X), into the table
below. Multiply Empty Weight (kg) by cg distance aft of datum (mm) to derive empty weight moment
(kg.mm) in the last column.
Complete the remaining weights for seat loads, fuel and baggage and multiply these by the lever arm
lengths (given below).
Add up the weights and moments, then divide the total weight by the total moment to give laden cg
location aft of datum.
Ensure that this cg location lies within the limits 350 to 560 aft of datum.
For operation at weights over 450kg, the forward limit is 366mm aft of datum. This is a limitation to remain
within tested nose wheel loads.
a
x
G
1
G
2
= G
L
+ G
R
b

iKarus C42 Specifications

General

Brand	iKarus
Model	C42
Category	Aircrafts
Language	English