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June 2007
Information Manual 2-7
Cirrus Design Section 2
SR22 Limitations
Propeller
Hartzell
Propeller Type ........................................Constant Speed, Three Blade
Model Number...................................................PHC-J3YF-1RF/F7694
Diameter.............................................................78.0” (76.5” Minimum)
Model Number..............................................PHC-J3YF-1RF/F7693DF
Diameter.............................................................78.0" (76.5" Minimum)
or
McCauley
Propeller Type ........................................Constant Speed, Three Blade
Model Number.................................................... D3A34C443/78CYA-0
Diameter.............................................................78.0" (76.5" Minimum)
Weight Limits
Maximum Takeoff Weight ......................................... 3400 lb (1542 Kg)
Maximum Weight in Baggage Compartment.................. 130 lb (59 Kg)
June 2007
2-8 Information Manual
Section 2 Cirrus Design
Limitations SR22
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 – 30 Inches Hg)
–– 15 - 29.5
in. Hg
–– ––
Fuel Flow
(0 – 30 U.S. Gal./
Hr.)
–– 10 - 20
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 – 90 U.S. Gallon)
0 gal. –– 0 - 14 gal. ––
Miscellaneous Instrumentation
Voltmeter
(16 - 32 Volts)
–– 24 - 30
Volts
–– 32 Volts
Instrumentation Markings
June 2007
Information Manual 2-9
Cirrus Design Section 2
SR22 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
138
3000
3400
3200
SR22_FM02_1944
136 140 142 144 146 148 150
2000
2200
2400
2600
2800
3600
10.2 % MAC
FS 138.0
2200 lb
31.5 % MAC
FS 148.1
2200 lb
31.5 % MAC
FS 148.1
3400 lb
12.5 % MAC
FS 139.1
2700 lb
17.4 % MAC
FS 141.4
3210 lb
22.4 % MAC
FS 143.8
3400 lb
FORWARD LIMIT - The forward limit is FS 138.0 (10.2% MAC) at 2200 lb, with straight line
taper to FS 139.1 (12.5% MAC) at 2700 lb, to FS 141.4.0 (17.4% MAC) at 3210 lb, and to FS
143.8 (22.4% MAC at 3400 lb.
AFT LIMIT - The aft limit is FS 148.1 (31.5% MAC) at all weights from 2200 lb to 3400 lb.
Figure 2-4
C.G. Envelope
June 2007
2-10 Information Manual
Section 2 Cirrus Design
Limitations SR22
Maneuver Limits
Aerobatic maneuvers, including spins, are prohibited.
• Note •
Because the SR22 has not been certified for spin recovery,
the Cirrus Airframe Parachute System (CAPS) must be
deployed if the airplane departs controlled flight. Refer to
Section 3 – Emergency Procedures, Inadvertent Spiral/Spin
Entry.
This airplane is certified in the normal category and is not designed for
aerobatic operations. Only those operations incidental to normal flight
are approved. These operations include normal stalls, chandelles, lazy
eights, and turns in which the angle of bank is limited to 60°.
Flight Load Factor Limits
Flaps UP (0%), 3400 lb.......................................................+3.8g, -1.9g
Flaps 50%..............................................................................+1.9g, -0g
Flaps 100% (Down), 3400 lb. ................................................+1.9g, -0g
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AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(6)
