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SR20 Supplements
Weight & Balance Loading Form
Serial Num: ________________ Date: ________________________
Reg. Num: _________________ Initials: ______________________
• Note •
The Takeoff Condition Weight must not exceed 3050 lb.
The Takeoff Condition Moment must be within the Minimum Moment to Maximum
Moment range at the Takeoff Condition Weight. (Refer to Moment Limits graphs).
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
Normally 6 lb at average moment of 922.8
– –
9.
Takeoff Condition Weight
Subtract item 8 from item 7
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Section 9 Cirrus Design
Supplements SR20
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 **56 U.S Gallons Usable
Weight
LB
Fwd
Pass
FS 143.5
Aft
Pass
FS 180.0
Baggage
FS 208.0
Fuel
FS 153.8
Weight
LB
Fwd
Pass
FS 143.5
Aft
Pass
FS 180.0
Fuel
FS 153.8
20 2.87 3.60 4.16 3.10 220 31.57 39.60 34.08
40 5.74 7.20 8.32 6.20 240 34.44 43.20 37.18
60 8.61 10.80 12.48 9.29 260 37.31 46.80 40.27
80 11.48 14.40 16.64 12.39 280 40.18 50.40 43.37
100 14.35 18.00 20.80 15.49 300 43.05 54.00 46.47
120 17.22 21.60 24.96 18.59 320 45.92 57.60 49.57
140 20.09 25.20 (27.04)* 21.69 336** 48.79 61.20 52.05
160 22.96 28.80 24.78 360 51.66 64.80
180 25.83 32.40 27.88 380 54.53 68.40
200 28.70 36.00 30.98 400 57.40 72.00
0
100
200
300
400
500
600
0.0 20.0 40.0 60.0 80.0
Moment/1000
Weight - Pounds
Fwd Pass
Fuel
Aft Pass
Baggage
Revision 01: 08-26-09
11934-S37 47 of 56
Cirrus Design Section 9
SR20 Supplements
Moment Limits
Use the following chart or table to determine if the weight and moment
from the completed Weight and Balance Loading Form are within
limits.
Weight
LB
Moment/1000 Weight
LB
Moment/1000
Minimum Maximum Minimum Maximum
2200 304 326 2700 375 398
2250 311 333 2750 383 406
2300 318 341 2800 390 414
2350 326 348 2850 398 421
2400 333 354 2900 406 429
2450 340 362 2950 414 437
2500 347 369 3000 421 444
2550 354 375 3050 429 452
2600 362 383 2700 375 398
2650 369 390
2000
2200
2400
2600
2800
3000
3200
300 320 340 360 380 400 420 440 460
Moment/1000
Weight - Pounds
Revision 01: 08-26-09
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Section 9 Cirrus Design
Supplements SR20
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Intentionally Left Blank
11934-S37 49 of 56
Cirrus Design Section 9
SR20 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 29.3-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
system.
Revision 01: 08-26-09
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Section 9 Cirrus Design
　
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