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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.
Revision A1
P/N 13772-001 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).
Reissue A
6-14 P/N 13772-001
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.
2000
2200
2400
2600
2800
3000
3200
3400
3600
136 138 140 142 144 146 148 150
C.G. - Inches Aft of Datum
Weight - Pounds
12.5% M AC
FS 139.1
2700 lb
9.8% MAC
FS 137.8
2100 lb
31.5% MAC
FS 148.1
2100 lb
19.2% M AC
FS 142.3
3400 lb
31.5% M AC
FS 148.1
3400 lb
17.4% M AC
FS 141.4
3210 lb
20.5% MAC
FS 142.6
3400 lb
Landing Limitation
(Shaded)
FORWARD LIMIT - The forward limit is FS 137.8 (9.8% MAC) at 2100 lb, with straight line taper
to FS 139.1 (12.5% MAC) at 2700 lb, to FS 142.3 (19.2% MAC) at 3400 lb.
AFT LIMIT - The aft limit is FS 148.1 (31.5% MAC) at all weights from 2100 lb to 3400 lb.
LANDING LIMITATION - The Landing Limitation is FS 141.4 (17.4% MAC) at 3210 lb, to FS
142.3 (19.2% MAC) at 3400 lb, to FS 142.6 (20.5% MAC) at 3400 lb, to FS 141.4 (17.4% MAC)
at 3210 lb. CAUTION: Before landing, verify aircraft Center of Gravity does not fall in the Landing
Limitation Zone. Allow flight time for fuel burn so the landing C.G. falls outside of this zone.
Center of Gravity Limits
Revision A8
P/N 13772-001 6-15
Cirrus Design Section 6
SR22 Weight & Balance
Weight & Balance Loading Form
Serial Num: ________________ Date: ________________________
Reg. Num: _________________ Initials: ______________________
• Note •
The Takeoff Condition Weight must not exceed 3400 lb.
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
81 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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