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C.G. % MAC = 100 x (C.G. Inches – LEMAC) ÷ MAC
Where:
LEMAC = 132.9
MAC = 48.4
June 2007
6-10 Information Manual
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
June 2007
Information Manual 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
June 2007
6-12 Information Manual
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
weight and moment for the loading. The calculated moment is then
compared to the Moment Limits chart or table (Figure 6-9) for a
determination of proper loading.
Airplane loading determinations are calculated using the Weight &
Balance Loading Form (Figure 6-7), the Loading Data chart and table
(Figure 6-8), and the Moment Limits chart and table (Figure 6-9).
1. Basic Empty Weight – Enter the current Basic Empty Weight and
Moment from the Weight & Balance Record (Figure 6-4).
2. Front Seat Occupants – Enter the total weight and moment/1000
for the front seat occupants from the Loading Data (Figure 6-8).
3. Rear Seat Occupants – Enter the total weight and moment/1000
for the rear seat occupants from the Loading Data (Figure 6-8).
4. Baggage – Enter weight and moment for the baggage from the
Loading Data (Figure 6-8).
• If desired, subtotal the weights and moment/1000 from steps 1
through 4. This is the Zero Fuel Condition. It includes all useful
load items excluding fuel.
5. Fuel Loading – Enter the weight and moment of usable fuel
loaded on the airplane from the Loading Data (Figure 6-8).
• Subtotal the weight and moment/1000. This is the Ramp
Condition or the weight and moment of the aircraft before taxi.
6. Fuel for start, taxi, and runup – This value is pre-entered on the
form. Normally, fuel used for start, taxi, and runup is approximately
9 pounds at an average moment/1000 of 1.394.
7. Takeoff Condition – Subtract the weight and moment/1000 for
step 8 (start, taxi, and runup) from the Ramp Condition values
(step 7) to determine the Takeoff Condition weight and moment/
1000.
• The total weight at takeoff must not exceed the maximum
weight limit of 3400 pounds.
June 2007
Information Manual 6-13
Cirrus Design Section 6
SR22 Weight & Balance
• The total moment/1000 must not be above the maximum or
below the minimum moment/1000 for the Takeoff Condition
Weight as determined from the Moment Limits chart or table
(Figure 6-9).
June 2007
6-14 Information Manual
Section 6 Cirrus Design
Weight & Balance SR22
Figure 6-6
Center of Gravity Limits
The charts below depict the airplane center-of-gravity envelope in
terms of inches aft of the reference datum and as a percentage of the
Mean Aerodynamic Cord (MAC). The relationship between the two is
detailed in the weighing instructions.
C.G. - Inches Aft of Datum
Weight - Pounds
138
3000
3400
3200
SR22_FM02_1945
136 140 142 144 146 148 150
2000
2200
2400
2600
2800
3600
10.2 % MAC
FS 138.0
2200 lb
31.5 % MAC
FS 148.1
2200 lb
31.5 % MAC
FS 148.1
3400 lb
　
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