MOONEY
MODEL
M2QJ
SECTION
VI
WEIGHT
AND
BALANCE
2.
Top off both tanks with full fuel. Subtract usable fuel 64.0 gal.
(242.4
liters, 53.3 Imp. Gal.)
@
6 lb/gal=384.0 Ibs. (174.2 Kg.)(.72 Kgll) from
total weight as weighed, (use 5.82
lb/ga1(.69 Kg/l) for IOOLL fuel).
OPTIONAL
METHOD
-
Ground aircraft and defuel tanks as follows:
a. Disconnect fuel line at electric boost pump outlet fitting.
b.
Connect to output fitting a flexible line that will reach fuel receptacle.
c. Turn fuel
selecPor valve to the tank to be drained, and remove filler
cap from fuel filler port.
d.
Turn on boost pump until lank is empty.
Repeal steps c. and d.
to
drain the other tank.
a.
Replace
1.25
gal.
(4.7
liters, 1.0 Imp.Gal.) fuel
@
6.0 Ib./gai.
f.72
Kg/l) into each tank j~rnusable fuel). (Use
5.82
lb/ga1.(.69 Kg/l) for 100bL
fuel).
f.
Repiace filler caps.
3.
Fill
oil to capacity-8 qts. (7.6 liters).
4.
Position
front
seats
in
full
forward
position.
5.
Position flaps
in
fill1 up position.
6.
Position a 2000-pound (907.2 Kg.) capacity scale under each of the three
wheels.
7.
Level aircraft as previously described making certain nose wheel is
centered.
8.
Weigh the aircraft and deduct any
tare
from each reading.
9.
Find
reference point
by
dropping a
plumb
bob from center of r.rose gear
trunnion (retracting pivot axis) to
the
floor.
Mark
the point
d
intersebion.
10.
Locate center line of nose wheel axle and main wheel axles in the same
manner.
I
3.
Measure the horizontal distance
from
the reference point to main wheel
axle
center line. Measure horizontal distance from center line of nose wheel
axie to center
line
of main wheel axles.
----=-we
]
NOPE
I
.,--"--
Depending on
the
airera&
COG,
iocetioss
the distance
from
the
centeriine of the
main
wheel
axios
to
the
tr~anloar
reference
point
may
be
longer
than
to
the
centerline
of
the
nose
wheel
axle.
12.
Record weights and measurements, and campute basic weight and
CG
as follows:
-_
-
NOTE:
Wing jack points are located
at
Fus. Sta. 56.658
h-k~e
jack
p"~
is
!acaleda%E~.Sta.3.4J5h.-
"-%XX
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