6-8 P/N 13772-003
Section 6 Cirrus Design
Weight and Balance Data SR22T
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 6-5) for a
determination of proper loading.
Airplane loading determinations are calculated using the Weight &
Balance Loading Form (Figure 6-3), the Loading Data chart and table
(Figure 6-4), and the Moment Limits chart and table (Figure 6-5).
1. Basic Empty Weight – Enter the current Basic Empty Weight and
Moment from the Weight & Balance Record (Figure 6-6).
2. Front Seat Occupants – Enter the total weight and moment/1000
for the front seat occupants from the Loading Data (Figure 6-4).
3. Rear Seat Occupants – Enter the total weight and moment/1000
for the rear seat occupants from the Loading Data (Figure 6-4).
4. Baggage – Enter weight and moment for the baggage from the
Loading Data (Figure 6-4).
• 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 6-4).
• 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 run-up – This value is pre-entered on the
form. Normally, fuel used for start, taxi, and run-up 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 run-up) 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. 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 6-5).
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