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ground roll estimated from the table.
• For operation in outside air temperatures colder than this table
provides, use coldest data shown.
• For operation in outside air temperatures warmer than this table
provides, use extreme caution.
Conditions:
• Technique ..................................................................................................Normal
• Winds.............................................................................................................. Zero
• Runway.........................................................................................................Paved
• Flaps. .............................................................................................................100%
• Power....................................................................................... 3° Power Approach
to 50 FT obstacle, then reduce power passing the estimated 50 foot point and
smoothly continue power reduction to reach idle just prior to touchdown.
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Section 9 Cirrus Design
Supplements SR20
Landing Distance
WEIGHT = 3050 LB
Speed over 50 Ft Obstacle = 77 KIAS
Flaps - 100% · Idle · Dry, Level Paved Surface
Headwind: Subtract 10% per each
13 knots headwind.
Tailwind: Add 10% for each 2 knots
tailwind up to 10 knots.
Runway Slope: Ref. Factors.
Dry Grass: Add 20% to Ground Roll
Wet Grass: Add 60% to Ground Roll
PRESS
ALT
FT
DISTANCE
FT
TEMPERATURE ~ °C
0 10 20 30 40 ISA
SL Grnd Roll 809 838 868 897 927 853
Total 2557 2609 2663 2717 2773 2636
1000 Grnd Roll 838 869 900 931 961 878
Total 2610 2665 2722 2779 2838 2682
2000 Grnd Roll 870 901 933 965 997 905
Total 2666 2725 2785 2846 2907 2731
3000 Grnd Roll 902 935 968 1001 1034 932
Total 2726 2788 2852 2916 2981 2782
4000 Grnd Roll 936 971 1005 1039 1073 960
Total 2790 2856 2923 2991 3060 2837
5000 Grnd Roll 972 1007 1043 1079 1114 990
Total 2858 2928 2999 3070 3143 2894
6000 Grnd Roll 1009 1046 1083 1120 1157 1021
Total 2931 3004 3079 3155 3232 2954
7000 Grnd Roll 1048 1086 1125 1163 1201 1052
Total 3008 3086 3165 3245 3326 3017
8000 Grnd Roll 1089 1128 1168 1208 1248 1085
Total 3091 3173 3256 3341 3427 3084
9000 Grnd Roll 1131 1173 1214 1255 1297 1119
Total 3179 3265 3353 3443 3533 3154
10000 Grnd Roll 1176 1219 1262 1305 1348 1155
Total 3272 3364 3457 3551 3646 3228
Revision 01: 08-26-09
11934-S37 39 of 56
Cirrus Design Section 9
SR20 Supplements
Section 6 - Weight and Balance
FS
100.0
230.0
WL
165.5
FS
350.2
FS
222.0
FS
157.4
FS
38.3
FS
142.5
FS
55.6
(FS)
STATION
FUSELAGE
NOTE
Reference datum located at
fuselage station 0.0.
MAC 47.7"
50.0
100.0
150.0
200.0
50.0
100.0
150.0
230.0
LEMAC
FS 133.1
RBL 87.7
Typical LBL
RBL 54.8
LBL 54.8
RBL 77.3
BL 0.0
LBL 77.3
RBL 229.5
LBL 229.5
200.0
50.0
150.0
WL 100.0
100.0
50.0
0.0
150.0
200.0
250.0
300.0
350.0
BUTTOCK LINE (BL)
BL 0.0
WATER LINE (WL)
SR20_FM09_2734
Figure - 4
Airplane Dimensional Data
Revision 01: 08-26-09
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Section 9 Cirrus Design
Supplements SR20
Airplane Weighing Form
Weighing
Point
Scale
Reading - Tare = Net Weight X Arm = Moment
L Main A=
R Main A=
Nose B=
Total
As Weighed
CG=
CG = Total Moment / Total Weight
Space below provided for additions or subtractions to as weighed condition
Empty Weight CG=
Engine Oil (if oil drained)
15 lb at FS 78.4, moment = 1176
Unusable Fuel 15.0 154.9 2324
Basic Empty Weight CG=
SR20_FM06_2539
x
WL 100.0
y
A
B
FS 100.0 FS 142.5
A = x + 100
B = A - y
y = ____________ Measured
x = ____________ Measured
REF DATUM
FS 0.0
Revision 01: 08-26-09
11934-S37 41 of 56
Cirrus Design Section 9
SR20 Supplements
Airplane Weighing Procedures
A basic empty weight and center of gravity were established for this
airplane when the airplane was weighed just prior to initial delivery.
However, major modifications, loss of records, addition or relocation of
equipment, accomplishment of service bulletins, and weight gain over
　
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