Velocity XL RG, Owner'S Manual

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30
XL
31
O
WNER
’
S
F
LIGHT
M
ANUAL
With no people in the aircraft, add enough fuel to fill only the
header fuel “sump” tank (4 gal. approx.). Now record the aircraft
weight from each scale, then the combined total.
Header Fuel Tank Weight (@ 6 lbs per gallon) =
Nose Wheel Weight (with Header fuel tank full) =
Left Main Wheel Weight (with Header fuel tank full) =
Right Main Wheel Weight (with Header fuel tank full) =
Combined Total Weight (with Header fuel tank full) =
Now bring the fuel up to 15 gallons (total fuel, including what is
already in the header tank). Record the aircraft weight from each
scale, then the combined total.
15 Gallons Fuel Weight (@ 6 lbs per gallon) = 90 lbs
Nose Wheel Weight (with Header fuel tank full) =
Left Main Wheel Weight (with Header fuel tank full) =
Right Main Wheel Weight (with Header fuel tank full) =
Combined Total Weight (with Header fuel tank full) =
Now bring the fuel up to FULL CAPACITY. Record the aircraft
weight from each scale, then the combined total.
Full Fuel Capacity (gallons) =
Full Fuel Capacity Weight (@ 6 lbs per gallon) =
Nose Wheel Weight (with Full Fuel) =
Left Main Wheel Weight (with Full Fuel) =
Right Main Wheel Weight (with Full Fuel) =
Combined Total Weight (with Full Fuel) =
This information is needed to calculate the FUEL ARM for your
Velocity.
STEP 7 Establish the Static CG of your aircraft:
Here is the text description:
•A: Nose wheel weight multiplied by the nosewheel axle ARM
•B: Mains total weight multiplied by the mains axle ARM
• Add the sum of A + B, divided by the total aircraft weight
= Static CG position
Here is the formula version (same outcome as above text ver-
sion) to obtain Static CG position:
When you multiply a weight by an ARM (distance), the result is
called a moment, and is expressed in units called INCH LBS.
Therefore, in order to simplify our calculations, the preceding for-
mula will be referred to as follows:
Here is an example using the factory Velocity N97XL:
Nosewheel Axle ARM = 31”
Nosewheel weight = 40 lbs
Main gear axle ARM = 144.6
Main wheels (L+R) combined weight = 1600 lbs
Total Weight = 1640 lbs
(40x31) + (1600x144.6)
_____________________ = 141.63 inches aft of datum
1600+40 (Static CG)
1240 in lbs + 231040 in lbs 232280 in lbs
_______________________
=
____________ = 141.63 inches
1640 1640 aft of datum
(Nose Wheel Weight X Nose Axle ARM) + (Mains Total Weight X Mains Axle ARM)
Total Weight of Aircraft
NOSE WHEEL MOMENT X MAIN MOMENT
= STATIC CG POSITION
TOTAL WEIGHT OF AIRCRAFT