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center of gravity current. All changes to the basic empty weight and
center of gravity are the responsibility of the operator.
1. Preparation:
a. Inflate tires to recommended operating pressures.
b. Service brake reservoir.
c. Drain fuel system.
d. Drain ice protection system.
e. Service engine oil.
f. Move crew seats to the most forward position.
g. Raise flaps to the fully retracted position.
h. Place all control surfaces in neutral position.
i. Verify equipment installation and location against equipment
list.
2. Leveling:
a. Level longitudinally with a spirit level placed on the pilot door
sill and laterally with of a spirit level placed across the door
sills. Alternately, level airplane by sighting the forward and aft
tool holes along waterline 95.9.
b. Place scales under each wheel (minimum scale capacity, 500
pounds nose, 1000 pounds each main).
c. Deflate the nose tire and/or shim underneath scales as
required to properly center the bubble in the level.
3. Weighing:
a. With the airplane level, doors closed, and brakes released,
record the weight shown on each scale. Deduct the tare, if
any, from each reading.
4. Measuring:
a. Obtain measurement ‘x’ by measuring horizontally along the
airplane center line (BL 0) from a line stretched between the
March 2010
6-6 Information Manual
Section 6 Cirrus Design
Weight and Balance Data SR22
main wheel centers to a plumb bob dropped from the forward
side of the firewall (FS 100). Add 100 to this measurement to
obtain left and right weighing point arm (dimension ‘A’).
Typically, dimension ‘A’ will be in the neighborhood of 157.5.
b. Obtain measurement ‘y’ by measuring horizontally and
parallel to the airplane centerline (BL 0), from center of
nosewheel axle, left side, to a plumb bob dropped from the
line stretched between the main wheel centers. Repeat on
right side and average the measurements. Subtract this
measurement from dimension ‘A’ to obtain the nosewheel
weighing point arm (dimension ‘B’).
5. Determine and record the moment for each of the main and nose
gear weighing points using the following formula:
Moment = Net Weight x Arm
6. Calculate and record the as-weighed weight and moment by
totaling the appropriate columns.
7. Determine and record the as-weighed CG in inches aft of datum
using the following formula:
CG = Total Moment / Total Weight
8. Add or subtract any items not included in the as-weighed condition
to determine the empty condition. Application of the above CG
formula will determine the C.G for this condition.
9. Add the correction for engine oil (15 lb at FS 78.4), if the airplane
was weighed with oil drained. Add the correction for unusable fuel
(15.0 lb at FS 154.9) to determine the Basic Empty Weight and
Moment. Calculate and record the Basic Empty Weight CG by
applying the above CG formula.
10. Record the new weight and CG values on the Weight and Balance
Record.
The above procedure determines the airplane Basic Empty Weight,
moment, and center of gravity in inches aft of datum. CG can also be
expressed in terms of its location as a percentage of the airplane
Mean Aerodynamic Cord (MAC) using the following formula:
CG% MAC = 100 x (CG Inches – LEMAC) / MAC
Where:
LEMAC = 133.1
MAC = 47.7
March 2010
Cirrus Design Section 6
SR22 Weight and Balance Data
Information Manual 6-7
Airplane Leveling
Figure 6-2
SR22_FM06_1440A
Spirit Level
LONGITUDINAL LEVELING
LATERAL LEVELING
Spirit Level
Straight
Edge
Door Sill Door Sill
Spacer
Block
Straight Edge Straight Edge
Spacer
Block
March 2010
6-8 Information Manual
Section 6 Cirrus Design
Weight and Balance Data SR22
Loading Instructions
It is the responsibility of the pilot to ensure that the airplane is properly
loaded and operated within the prescribed weight and center of gravity
limits. The following information enables the pilot to calculate the total
weight and moment for the loading. The calculated moment is then
compared to the Moment Limits chart or table (Figure 6-5) for a
determination of proper loading.
Airplane loading determinations are calculated using the Weight &
Balance Loading Form (Figure 6-3), the Loading Data chart and table
(Figure 6-4), and the Moment Limits chart and table (Figure 6-5).
1. Basic Empty Weight – Enter the current Basic Empty Weight and
Moment from the Weight & Balance Record (Figure 6-6).
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西锐20飞机信息手册 SR22 AIRPLANE INFORMATION MANUAL 2979(49)
