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operational limitations regarding fuel and fuel storage.
Revision A9
P/N 13772-001 2-7
Cirrus Design Section 2
SR22 Limitations
Propeller
Hartzell
Propeller Type ........................................Constant Speed, Three Blade
Model Number..............................................PHC-J3YF-1RF/F7694(B)
Diameter.............................................................78.0” (76.0” Minimum)
Model Number.........................................PHC-J3YF-1RF/F7693DF(B)
Diameter.............................................................78.0" (76.0" Minimum)
or
McCauley
Propeller Type ........................................Constant Speed, Three Blade
Model Number.................................................... D3A34C443/78CYA-0
Diameter.............................................................78.0" (76.0" Minimum)
or
MT Propeller
Propeller Type ........................................Constant Speed, Three Blade
Model Number.............................................................MTV-9-D/198-52
Diameter.............................................................78.0" (76.0" Minimum)
Weight Limits
Maximum Takeoff Weight ......................................... 3400 lb (1542 Kg)
Maximum Weight in Baggage Compartment.................. 130 lb (59 Kg)
Revision A9
2-8 P/N 13772-001
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
Revision A5
P/N 13772-001 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
2000
2200
2400
2600
2800
3000
3200
3400
3600
C.G. - Inches Aft of Datum
Weight - Pounds
12.5% MAC
FS 139.1
2700 lb
9.8% MAC
FS 137.8
2100 lb
31.5% MAC
FS 148.1
2100 lb
19.2% MAC
FS 142.3
3400 lb
31.5% MAC
FS 148.1
3400 lb
17.4% MAC
FS 141.4
3210 lb
20.5% MAC
FS 142.7
3400 lb
Landing Limitation
(Shaded)
136 138 140 142 144 146 148 150
SR22_FM02_3216
FORWARD LIMIT - The forward limit is FS 137.8 (9.8% MAC) at 2100 lb, with straight line taper
to FS 139.1 (12.5% MAC) at 2700 lb, to FS 142.3 (19.2% MAC) at 3400 lb.
AFT LIMIT - The aft limit is FS 148.1 (31.5% MAC) at all weights from 2100 lb to 3400 lb.
LANDING LIMITATION - The Landing Limitation is FS 141.4 (17.4% MAC) at 3210 lb, to FS
142.3 (19.2% MAC) at 3400 lb, to FS 142.7 (20.5% MAC) at 3400 lb, to FS 141.4 (17.4% MAC)
at 3210 lb. CAUTION: Before landing, verify aircraft Center of Gravity does not fall in the Landing
Limitation Zone. Allow flight time for fuel burn so the landing C.G. falls outside of this zone.
Figure 2-4
C.G. Envelope
Revision A9
2-10 P/N 13772-001
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
　
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