AIRCRAFT FLIGHT
MANUAL
BRISTELL B23
Document No.: ADXC-73-001-AFM
Non-approved page
Revision: A2
6-4
Date of Issue: 15.04.2021
6.5
Loaded Aircraft Weight and CG
Loaded aircraft weight and balance is determined by summing individual
masses and moments and calculating according flight condition for actual
fuel and zero fuel. Results shall be entered in the graph of permissible
range.
To do so the following blank form and graph should be used:
1
ITEM
WEIGHT
ARM
MOMENT
= WEIGHT x ARM
(kg)
(m)
(kg.m)
E
M
P
T
Y
A
IRCR
A
F
T
(w
e
igh
ing
r
e
su
lt)
RIGHT MAIN WHEEL
2.062
LEFT MAIN WHEEL
2.062
NOSE WHEEL
0.588
EMPTY AIRCRAFT
SUM =
X
CG
= SUM M / SUM W
SUM =
2
ITEM
WEIGHT
ARM
MOMENT
= WEIGHT x ARM
(kg)
(m)
(kg.m)
AIRC
RA
F
T
W
IT
HOUT
W
ING
L
OAD
EMPTY AIRCRAFT
PILOT &
PASSENGER
2.085
BAGGAGE
– BEHIND
SEATS
2.520
ZERO WING LOAD
AIRCRAFT
SUM =
X
CG
= SUM M / SUM W
SUM =
3
ITEM
WEIGHT
ARM
MOMENT
= WEIGHT x ARM
(kg)
(m)
(kg.m)
L
OADE
D AIRC
RA
F
T
ZERO WING LOAD
AIRCRAFT
BAGGAGE
– WING
LOCKERS
2.025
FUEL weight =
qty*0.72kg/liter
1.600
LOADED AIRCRAFT
SUM =
X
CG
= SUM M / SUM W
SUM =
The result of step 2 and 3 must be checked versus the limitations (check
graph on next page).
