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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
March 2010
Information Manual 6-11
Cirrus Design Section 6
SR20 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
Fuselage
Station
5.0"
21.0"
20.0"
BAGGAGE DOOR
OPENING
CABIN DOOR
OPENING
222
100
SR20_FM06_1019
32.0"
33.3"
20.0"
33.4" 39.0"
10.5"
38.5" FS
25.0"
49.7"
16.0"
120 140 160 180
200
220 240
49.3"
39.8"
Figure 6-5
Airplane Interior Dimensions
March 2010
6-12 Information Manual
Section 6 Cirrus Design
Weight & Balance SR20
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
6 pounds at an average moment/1000 of 0.92.
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 3000 pounds.
March 2010
Information Manual 6-13
Cirrus Design Section 6
SR20 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).
March 2010
6-14 Information Manual
Section 6 Cirrus Design
Weight & Balance SR20
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
SR20_FM02_1940A
138 140 142 144 146 148 150
2000
2200
2400
2600
2800
3000
12.0 % MAC
FS 138.7
2110 lb
24.1 % MAC
FS 144.6
2110 lb
31.5 % MAC
FS 148.1
2900 lb
30.0 % MAC
FS 147.4
2570 lb
31.3 % MAC
FS 148.0
3000 lb
23.1 % MAC
FS 144.1
3000 lb
16.7 % MAC
FS 141.0
2694 lb
FORWARD LIMIT - The forward limit is FS 138.7 (12.0% MAC) at 2110 lb., with straight line taper
to FS 141.0 (16.7% MAC) at 2694 lb., and to FS 144.1 (23.1% MAC) at 3000 lb.
AFT LIMIT - The aft limit is FS 144.6 (24.1% MAC) at 2110 lb., with straight line taper to FS 147.4
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