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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 (Figure 6-3):
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.
Revision A3
6-8 P/N 13772-001
Section 6 Cirrus Design
Weight & Balance SR22
4. Measuring (Figure 6-3):
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
(18.0 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.
10. Record the new weight and C.G. values on the Weight and
Balance Record (Figure 6-4).
Reissue A
P/N 13772-001 6-9
Cirrus Design Section 6
SR22 Weight & Balance
The above procedure determines the airplane Basic Empty Weight,
moment, and center of gravity in inches aft of datum. C.G. can also be
expressed in terms of its location as a percentage of the airplane
Mean Aerodynamic Cord (MAC) using the following formula:
C.G. % MAC = 100 x (C.G. Inches – LEMAC) / MAC
Where:
LEMAC = 133.1
MAC = 47.7
Revision A8
6-10 P/N 13772-001
Section 6 Cirrus Design
Weight & Balance SR22
Figure 6-4
Weight & Balance Record
Use this form to maintain a continuous history of changes and
modifications to airplane structure or equipment affecting weight and
balance:
Serial Num: Reg. Num: Page of
Date
Item
No. Description of Article
or Modification
Weight Change
Added (+) or Removed (-)
Running Basic
Empty Weight
In Out
WT
LB
ARM
IN.
MOM/
1000
WT
LB
MOM/
1000
As Delivered
Weight and Balance Record
Reissue A
P/N 13772-001 6-11
Cirrus Design Section 6
SR22 Weight & Balance
Location Length Width Height Volume
Cabin 122” 49.3” 49.7 137 cu ft
Baggage
Compartment
36” 39.8” 38.5” 32 cu ft
39.8"
49.3"
220 240
200
120 140 160 180
16.0"
49.7"
25.0"
38.5" FS
10.5"
33.4" 39.0"
20.0"
33.3"
32.0"
SR22_FM06_1019
100
222
CABIN DOOR
OPENING
BAGGAGE DOOR
OPENING
20.0"
21.0"
5.0"
Station
Fuselage
Figure 6-5
Airplane Interior Dimensions
Reissue A
6-12 P/N 13772-001
Section 6 Cirrus Design
Weight & Balance 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
　
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