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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
(30.0% MAC) at 2570 lb., to FS 148.1 (31.5% MAC) at 2900 lb., and to FS 148.0 (31.3% MAC) at
3000 lb.
Center of Gravity Limits
March 2010
Information Manual 6-15
Cirrus Design Section 6
SR20 Weight & Balance
Weight & Balance Loading Form
Serial Num: ________________ Date: ________________________
Reg. Num: _________________ Initials: ______________________
• Note •
The Takeoff Condition Weight must not exceed 3000 lb. All weights above 2900 lb
must consist of fuel.
The Takeoff Condition Moment must be within the Minimum Moment to Maximum
Moment range at the Takeoff Condition Weight. (Refer to Figure 6-9, Moment
Limits).
Item Description
Weight
LB
Moment/
1000
1.
Basic Empty Weight
Includes unusable fuel & full oil
2.
Front Seat Occupants
Pilot & Passenger (total)
3. Rear Seat Occupants
4.
Baggage Area
130 lb maximum
5.
Zero Fuel Condition Weight
Sub total item 1 thru 4
6.
Fuel Loading
56 Gallon @ 6.0 lb/gal. Maximum
7.
Ramp Condition Weight
Sub total item 5 and 6
8.
Fuel for start, taxi, and runup
　
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本文鏈接地址：西銳20飛機信息手冊 SR22 AIRPLANE INFORMATION MANUAL 1148-126(48)