MOONEY
M20V ACCLAIM ULTRA
SECTION VI
WEIGHT AND BALANCE
6 - 5
AIRPLANE FLIGHT MANUAL
ORIGINAL ISSUE - 03-16-2017
M20V - WEIGHT & BALANCE CHART
REF.POINT
(NOSE GEAR
TRUNNION
STA. - 13)
Lm/n
Lm/r
Lc/g
Wn
Lm
Wr
Wl
L M/N
M/R
L
MEASUREMENTS
DATUM(STA.0)
REFERENCE
(LEVELING SCREWS)
LEVEL REF.
INCHES/CM
INCHES/CM
SCALE POSITION AND SYMBOL
SCALE READING
TARE
NET WEIGHT
NOSE WHEEL (W )
RIGHT MAIN WHEEL (W )
LEFT MAIN WHEEL (W )
BASIC EMPTY WEIGHT (W )
AS WEIGHED (W )
of fuel has been drained
of fuel has not been drained
LBS/Kg
Weight @ Nose
(W
N
)
×
In/cm/mm
Distance Between
Main & Nose Wheel
Axle Centers
÷
(L
M/N
)
Total Weight of
Aircraft
(W
T
)
=
CG Forward of
Main Wheels
(L
M
)
a. CG Forward of Main Wheels
b. CG Aft of Datum (Station 0)
13 In/33.0 cm/330 mm
Distance from Center
Nose Gear Trunnion to
Center of Main Wheel
Axles (Horizontal)
(L
M/R
)
Distance from
Nose Gear Trun-
nion to Datum
Result of
Computation
Above (a.)
(L
M
)
(CONSTANT)
CG (FUS STA)
Distance Aft of
Datum (Empty
Weight CG)
(L
C/G
)
−
=
LBS/Kg
In/cm/mm
In/cm/mm
In/cm/mm
In/cm/mm
−
WEIGHT
As Weighed (W )
Usable Fuel
Basic Empty Wt.
LBS. (Kg)
C.G. In/cm/mm
MOMENT Lb- In (Kg- cm)(Kg- mm)/1000
49.23 In/125 cm/1250 mm
T
-
-
N
R
L
T
T
