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than the published slope, lengthening (or shortening) landing
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: Example:
• Winds ..........................................Zero Outside Air Temp........................10°C
• Runway .................. Dry, Level, Paved Weight .................................. 3400 LB
• Flaps. ........................................100% Pressure Altitude .................. 2000 FT
• Power .................. 3° Power Approach Headwind ................................... Zero
to 50 FT obstacle, then reduce power
passing the estimated 50 foot point Obstacle Speed (VREF) .........77 KIAS
and smoothly continue power Landing Ground Roll ............ 1206 FT
reduction to reach idle just prior to
touchdown.
Dist. over 50' Obstacle.......... 2436 FT
Original: 03-27-07
38 of 58 13772-130
Section 9 Cirrus Design
Supplements SR22
Landing Distance
WEIGHT = 3400 LB
Speed over 50 Ft Obstacle = 77 KIAS
Flaps - 100%· Idle · Dry, Level Paved Surface
Headwind: Subtract 10% for 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 1082 1121 1161 1200 1240 1141
Total 2262 2316 2372 2428 2485 2344
1000 Grnd Roll 1122 1163 1204 1245 1286 1175
Total 2317 2374 2433 2492 2551 2391
2000 Grnd Roll 1163 1206 1248 1291 1334 1210
Total 2375 2436 2497 2559 2621 2441
3000 Grnd Roll 1207 1251 1295 1339 1384 1247
Total 2437 2501 2565 2630 2696 2493
4000 Grnd Roll 1252 1298 1344 1390 1436 1285
Total 2503 2569 2637 2705 2774 2548
5000 Grnd Roll 1300 1348 1395 1443 1490 1324
Total 2572 2642 2713 2785 2857 2605
6000 Grnd Roll 1350 1399 1449 1498 1547 1365
Total 2645 2719 2794 2869 2945 2665
7000 Grnd Roll 1402 1453 1504 1556 1607 1408
Total 2723 2800 2879 2958 3038 2728
8000 Grnd Roll 1456 1509 1563 1616 1669 1452
Total 2805 2887 2969 3052 3136 2794
9000 Grnd Roll 1513 1569 1624 1679 1735 1497
Total 2892 2978 3064 3152 3240 2863
10000 Grnd Roll 1573 1630 1688 1746 1803 1545
Total 2984 3074 3165 3257 3350 2936
Original: 03-27-07
13772-130 39 of 58
Cirrus Design Section 9
SR22 Supplements
Section 6 - Weight and Balance
FS
100.0
230.0
WL
165.5
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)
SR22_FM09_2607
Original: 03-27-07
40 of 58 13772-130
Section 9 Cirrus Design
Supplements SR22
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=
SR22_FM06_1441
x
WL 100.0
y
A
B
FS 100.0 FS 145.0
A = x + 100
B = A - y
y = ____________ Measured
x = ____________ Measured
REF DATUM
FS 0.0
Figure - 5
Airplane Dimensional Data
Original: 03-27-07
13772-130 41 of 58
Cirrus Design Section 9
SR22 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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AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(148)
