MODEL 510 SECTION VI - WEIGHT AND BALANCE DATA
CONTROL - FLUIDS
FAA APPROVED
U.S.
FLUIDS
Engine Oil Table
Figure 6 presents data for engine oil.
Hydraulic Fluid Table
Figure 7 presents data for the hydraulic reservoir and the total hydraulic fluid in the landing gear (in
flight condition), brake, antiskid and flap systems.
510WB-00 6-19
SECTION VI - WEIGHT AND BALANCE DATA MODEL 510
CONTROL - FLUIDS
FAA APPROVED
U.S.
ENGINE OIL TABLE
NOTE
Engine oil weight is 7.92 pounds per gallon at 70° Fahrenheit.
NOTE
Engine oil weight is 0.949 kilograms per liter at 21° Celsius.
Figure 6
ENGINE OIL - U.S. UNITS
INCREMENTS VOLUME
(GALLONS)
WEIGHT
(POUNDS)
ARM = FS
(INCHES)
MOMENT/100 (INCHPOUNDS)
DRAINABLE LEFT
AND RIGHT 2.40 19.00 363.11 68.99
UNDRAINABLE
LEFT AND RIGHT 0.15 1.20 363.11 4.36
TOTAL ENGINE
OIL LEFT AND
RIGHT
2.55 20.20 363.11 73.35
ENGINE OIL - METRIC UNITS
INCREMENTS VOLUME
(LITERS)
WEIGHT
(KILOGRAMS)
ARM = FS
(MILLIMETERS)
MOMENT/1000
(MM - KILOGRAMS)
DRAINABLE LEFT
AND RIGHT 9.08 8.62 9223 79.49
UNDRAINABLE
LEFT AND RIGHT 0.57 0.54 9223 5.02
TOTAL ENGINE
OIL LEFT AND
RIGHT
9.66 9.16 9223 84.51
6-20 510WB-00
MODEL 510 SECTION VI - WEIGHT AND BALANCE DATA
CONTROL - FLUIDS
FAA APPROVED
U.S.
HYDRAULIC FLUID TABLE
NOTE
Hydraulic fluid weight is 6.978 pounds per gallon at 75° Fahrenheit.
NOTE
Hydraulic fluid weight is 0.836 kilograms per liter at 24° Celsius.
Figure 7
HYDRAULIC FLUID - U.S. UNITS
RESERVOIR
INCREMENTS
VOLUME
(GALLONS)
WEIGHT
(POUNDS)
ARM = FS
(INCHES)
MOMENT/100
(INCH-POUNDS)
HYDRAULIC
RESERVOIR, FULL 0.47 3.28 140.94 4.62
MAIN SYSTEM
ACCUMULATOR 0.11 0.77 119.20 0.91
NOSE LANDING
GEAR ACTUATOR 0.03 0.21 125.95 0.26
MAIN LANDING GEAR
ACTUATORS (2) 0.19 1.35 286.15 3.87
HYDRAULIC LINES
AND FITTINGS 0.66 4.62 216.75 10.02
TOTAL HYDRAULIC
SYSTEM 1.46 10.23 192.45 19.69
HYDRAULIC FLUID - METRIC UNITS
RESERVOIR
INCREMENTS
VOLUME
(LITERS)
WEIGHT
(KILOGRAMS)
ARM = FS
(MILLIMETERS)
MOMENT/1000
(MM-KILOGRAMS)
HYDRAULIC
RESERVOIR, FULL 1.78 1.49 3580 5.33
MAIN SYSTEM
ACCUMULATOR 0.42 0.35 3028 1.06
NOSE LANDING
GEAR ACTUATOR 0.11 0.10 3199 0.32
MAIN LANDING GEAR
ACTUATORS (2) 0.72 0.61 7268 4.43
HYDRAULIC LINES
AND FITTINGS 2.50 2.10 5505 11.56
TOTAL HYDRAULIC
SYSTEM 5.53 4.65 4883 22.71
510WB-00 6-21/6-22
MODEL 510 SECTION VI - WEIGHT AND BALANCE DATA
CONTROL - PERSONNEL
FAA APPROVED
U.S.
PERSONNEL
Crew and Passenger Arrangement Diagram
Diagram of crew and passenger arrangement and associated weight and balance moment
information is included in Standard Seating Configuration (See Figures 10 - 11).
Crew and Passenger Movement Balance Effect (U.S. Units)
To determine the change in moment resulting from crew or passenger movement, multiply the
person's weight (in pounds) by the difference (in inches) between the arm of the destination location
and the arm of the starting location. Use the following equation to calculate the change in moment:
ΔM = Wt (ARMD - ARMS)
Where:
ΔM = Change in moment
Wt = Weight of the person to be moved
ARMD = Arm of the person’s destination location
ARMS = Arm of the person’s starting location
NOTE
A negative number indicates a forward movement and a positive number indicates an
aft movement.
To determine the change in moment resulting from a seat adjustment, multiply the occupant's weight
(in pounds) by the distance (in inches) the seat is moved.
Crew and Passenger Movement Balance Effect (Metric Units)
To determine the change in moment resulting from crew or passenger movement, multiply the
person's weight (in kilograms) by the difference (in millimeters) between the arm of the destination
location and the arm of the starting location. Use the following equation to calculate the change in
moment:
ΔM = Wt (ARMD - ARMS)
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