WT-9 Dynamic Club S FLIGHT MANUAL Section 6 Page 6-
SECTION 6
WEIGHT AND BALANCE / EQUIPMENT LIST
Page
6.1 Introduction 6-1
6.2 Weighing procedure 6-1
6.3 Weight and balance record and permitted
payload range 6-2
6.4 Master minimum equipment list 6-4
6.1 Introduction
This section contains the payload range with which the ultralight airplane may be
safely operated. C.G. position is very important parameter which effects the safety of
flight.
6.2 Weighing procedure
To define the aeroplane C.G. it is necessary to weigh the empty aeroplane with
standard and optional equipment, with operating fluids of the engine but without the
fuel in the tanks.
The aeroplane is weighed with the help of three weighing-machines located below
the left and right main wheels and below the nose wheel. The aeroplane position for
weighing has to be parallel with the horizontal plane which passes through the side
edge of the cockpit. The reference point (datum point = DP) is leading edge of wing
root section. To measure the distance from centre of main landing wheel axle and of
nose wheel axle to reference point DP. C.G. position is calculated from the reference
point DP (leading edge) and C.G. position is calculated in % aerodynamic mean
chord (MAC) too. The leading edge of the MAC is located in distance 77 mm rear
from DP.
Centre of gravity position after loading aeroplane (crew, fuel, baggage or additional
equipment) is calculated as following: The sum moments of aeroplane all
components mass is added to the total moment of the empty aeroplane and divided
by total weight.
Date: 1.12.2001
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