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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 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
92 Gallon @ 6.0 lb/gal. Maximum
7.
Ramp Condition Weight
Sub total item 5 and 6
8.
Fuel for start, taxi, and runup
Normally 9 lb at average moment of 1394.
– –
9.
Takeoff Condition Weight
Subtract item 8 from item 7
Original: 03-27-07
46 of 58 13772-130
Section 9 Cirrus Design
Supplements SR22
Loading Data
Use the following chart or table to determine the moment/1000 for fuel
and payload items to complete the Loading Form.
*130 lb Maximum **92 U.S. Gallons Usable
Weight
LB
Fwd
Pass
FS 143.5
Aft
Pass
FS 180.0
Baggage
FS 208.0
Fuel
FS 154.9
Weight
LB
Fwd
Pass
FS 143.5
Aft
Pass
FS 180.0
Fuel
FS 154.9
20 2.87 3.6 4.16 3.098 300 43.05 54 46.47
40 5.74 7.2 8.32 6.196 320 45.92 57.6 49.568
60 8.61 10.8 12.48 9.294 340 48.79 61.2 52.666
80 11.48 14.4 16.64 12.392 360 51.66 64.8 55.764
100 14.35 18 20.8 15.49 380 54.53 68.4 58.862
120 17.22 21.6 24.96 18.588 400 57.4 72 61.96
140 20.09 25.2 27.04* 21.686 420 60.27 75.6 65.058
160 22.96 28.8 24.784 440 63.14 79.2 68.156
180 25.83 32.4 27.882 460 71.254
200 28.7 36 30.98 480 74.352
220 31.57 39.6 34.078 500 77.45
240 34.44 43.2 37.176 520 80.548
260 37.31 46.8 40.274 552** 85.5048
280 40.18 50.4 43.372
0
100
200
300
400
500
600
0.0 20.0 40.0 60.0 80.0 100.0
Moment/1000
Weight - Pounds
Original: 03-27-07
13772-130 47 of 58
Cirrus Design Section 9
SR22 Supplements
Moment Limits
Use the following chart or table to determine if the weight and moment
from the completed Weight and Balance Loading Form (Figure 6-7)
are within limits.
Weight
LB
Moment/1000 Weight
LB
Moment/1000
Minimum Maximum Minimum Maximum
2200 304 326 2850 398 422
2250 311 333 2900 406 430
2300 318 341 2950 414 437
2350 326 348 3000 421 444
2400 333 355 3050 429 452
2450 340 363 3100 437 459
2500 347 370 3150 444 467
2550 354 378 3200 452 474
2600 362 385 3250 460 481
2650 369 392 3300 467 489
2700 375 400 3350 475 496
2750 383 407 3400 483 504
2800 390 415
2000
2200
2400
2600
2800
3000
3200
3400
300 350 400 450 500 550
Moment/1000
Weight - Pounds
Original: 03-27-07
48 of 58 13772-130
Section 9 Cirrus Design
Supplements SR22
Original: 03-27-07
Intentionally Left Blank
13772-130 49 of 58
Cirrus Design Section 9
SR22 Supplements
Section 7 - Systems Description
Airframe
Wings
The wing structure is constructed of composite materials producing
wing surfaces that are smooth and seamless. The wing cross section
is a blend of several high performance airfoils. A high aspect ratio
results in low drag. Each wing provides attach structure for the main
landing gear and contains a 47.25-gallon fuel tank.
The G3 Wing is constructed in a conventional spar, rib, and shear
section arrangement. The upper and lower skins are bonded to the
spar, ribs, and aft shear web forming a torsion box that carries all of
the wing bending and torsion loads. The rear shear webs are similar in
construction but do not carry through the fuselage. The main spar is
laminated epoxy/carbon fiber in a C-section, and is continuous from
wing tip to wing tip. The wing spar passes under the fuselage below
the two front seats and is attached to the fuselage in two locations. Lift
and landing loads are carried by the single carry-through spar, plus a
pair of rear shear webs (one on each wing) attached to the fuselage.
Rudder System
G3 Wing geometry is slightly changed with an increase in dihedral of
1° which allows for the elimination of the aileron-rudder interconnect
　
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