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300.0
350.0
BUTTOCK LINE (BL)
BL 0.0
WATER LINE (WL)
SR22_FM09_2607
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Section 9 Cirrus Design
Supplements SR22
Airplane Weighing Form
Weighing
Point
Scale
Reading - Tare = Net Weight X Arm = Moment
L Main A=
R Main A=
Nose B=
Total
As Weighed
CG=
CG = Total Moment ÷ Total Weight
Space below provided for additions or subtractions to as weighed condition
Empty Weight CG=
Engine Oil (if oil drained)
15 lb at FS 78.4, moment = 1176
Unusable Fuel 15.0 154.9 2324
Basic Empty Weight CG=
SR22_FM06_1441
x
WL 100.0
y
A
B
FS 100.0 FS 145.0
A = x + 100
B = A - y
y = ____________ Measured
x = ____________ Measured
REF DATUM
FS 0.0
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Cirrus Design Section 9
SR22 Supplements
Figure - 5
Airplane Weighing Procedures
A basic empty weight and center of gravity were established for this
airplane when the airplane was weighed just prior to initial delivery.
However, major modifications, loss of records, addition or relocation of
equipment, accomplishment of service bulletins, and weight gain over
time may require re-weighing to keep the basic empty weight and
center of gravity current. The frequency of weighing is determined by
the operator. All changes to the basic empty weight and center of
gravity are the responsibility of the operator. Refer to Section 8 for
specific servicing procedures.
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 by comparison to
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.
Airplane Dimensional Data
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Section 9 Cirrus Design
Supplements SR22
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
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 C.G. in inches aft of datum
using the following formula:
C.G. = 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 C.G.
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 C.G. by
applying the above C.G. formula.
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Cirrus Design Section 9
SR22 Supplements
10. Record the new weight and C.G. values on the Weight and
　
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