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Fuel Grade ................Aviation Grade 100 LL (Blue) or 100 (green)
• Note •
Refer to General Limitations – Fuel Limits in this section for
operational limitations regarding fuel and fuel storage.
March 2010
Information Manual 2-7
Cirrus Design Section 2
SR20 Limitations
Propeller
• Note •
Two-blade propellers are not EASA approved for use on this
airplane. Airplanes registered in the European Union should
ignore all references to the two-blade propeller in this POH.
Hartzell
Propeller Type ............................................................. Constant Speed
Two-Blade Propeller:
Model Number...................................................BHC-J2YF-1BF/F7694
Diameter.............................................................76.0” (73.0” Minimum)
Three-Blade Propeller:
Model Number............................................... PHC-J3YF-1MF/F7392-1
Diameter.............................................................74.0” (72.0” Minimum)
Model Number............................................... PHC-J3YF-1RF/F7392-1
Diameter.............................................................74.0” (72.0” Minimum)
Weight Limits
Maximum Takeoff Weight ......................................... 3000 lb. (1361 kg)
• Note •
All weights in excess of 2900 pounds (1315 kg) must consist
of wing fuel.
Maximum Landing Weight ....................................... 2900 lb. (1315 kg)
Maximum Weight in Baggage Compartment.................. 130 lb. (59 kg)
March 2010
2-8 Information Manual
Section 2 Cirrus Design
Limitations SR20
Figure 2-3
Instrument Markings
Instrument
(Range)
Red Line Green Arc Yellow Arc Red Line
Minimum Normal Caution Maximum
Power Plant Instrumentation
Tachometer/
Engine Speed
(0 - 3500 RPM)
–– 500 - 2700 –– 2700
Cylinder Head
Temperature
(200 F - 500 F)
–– 240 - 420
F
420 - 460
F
460 F
Exhaust Gas Temp.
(1250 - 1650 F)
–– –– –– ––
Manifold Pressure
(10 – 35 Inches Hg)
–– 15 - 29.5
in. Hg
29.5 – 35
in. Hg
––
Fuel Flow
(0 – 18 U.S. Gal./
Hr.)
–– 7 – 13 GPH –– ––
Oil Temperature
(50 - 240 F)
–– 100 - 240
F
–– 240 F
Oil Pressure
(0 - 100 PSI)
10 psi (Idle) 30 - 60 psi 10 - 30 psi
60 - 100 psi
100 psi
(Cold)
Fuel Quantity
(0 – 28 U.S. Gallon)
0 gal. –– 0 - 8.2 gal. ––
Miscellaneous Instrumentation
Voltmeter
(16 - 32 Volts)
–– 24 - 30
Volts
–– 32 Volts
Instrumentation Markings
March 2010
Information Manual 2-9
Cirrus Design Section 2
SR20 Limitations
Center of Gravity Limits
Reference Datum ....................................100 inches forward of firewall
Forward ...................................................................Refer to Figure 2-4
Aft ............................................................................Refer to Figure 2-4
C.G. - Inches Aft of Datum
Weight - Pounds
SR20_FM02_1940A
138 140 142 144 146 148 150
2000
2200
2400
2600
2800
3000
12.0 % MAC
FS 138.7
2110 lb
24.1 % MAC
FS 144.6
2110 lb
31.5 % MAC
FS 148.1
2900 lb
30.0 % MAC
FS 147.4
2570 lb
31.3 % MAC
FS 148.0
3000 lb
23.1 % MAC
FS 144.1
3000 lb
16.7 % MAC
FS 141.0
2694 lb
FORWARD LIMIT - The forward limit is FS 138.7 (12.0% MAC) at 2110 lb., with straight line taper
to FS 141.0 (16.7% MAC) at 2694 lb., and to FS 144.1 (23.1% MAC) at 3000 lb.
AFT LIMIT - The aft limit is FS 144.6 (24.1% MAC) at 2110 lb., with straight line taper to FS 147.4
(30.0% MAC) at 2570 lb., to FS 148.1 (31.5% MAC) at 2900 lb., and to FS 148.0 (31.3% MAC) at
3000 lb.
Figure 2-4
C.G. Envelope
March 2010
2-10 Information Manual
Section 2 Cirrus Design
Limitations SR20
Maneuver Limits
Aerobatic maneuvers, including spins, are prohibited.
• Note •
Because the SR20 has not been certified for spin recovery,
the Cirrus Airframe Parachute System (CAPS) must be
　
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