The Cirrus SR22 is fabricated using composite materials. The smoothly contoured
design reduces drag to allow greater performance.
The length of the SR22 is 26 feet.
The airplane's height is 8.8 feet.
At the maximum weight of 3,400 pounds, propeller ground clearance is 7 inches.
If the nose tire is under inflated, propeller ground clearance will be less than 7 inches. Be
sure the nose tire is properly inflated to prevent ground strikes!
The wingspan of the SR22 is 38.3 feet, which includes position and strobe lights.
Total wing area is 144.9 square feet.
Finally, the airplane's wheel stance is 10.8 feet.
When maneuvering the airplane on the ground, the turning radius of the wing tips is 24.8
feet.
The turning radius of the nose gear is 7.0 feet.
The turning radius of the outer main gear is 10.8 feet, while the turning radius of the
inside gear is 6 inches.
Turning radius is determined using one brake and partial power. Actual turning radius
may vary as much as three feet.
The SR22 is powered by a six-cylinder Teledyne Continental engine.
The horizontally opposed, direct drive engine is air cooled and fuel injected.
The engine is rated at 310 horsepower at 2,700 rpm.
The SR22 is equipped with a three-blade, constant speed propeller.
The manufacturer of the propeller is either Hartzell or McCauley.
The diameter of the propeller is 78 inches. Minimum diameter is 76.5 inches.
The Cirrus SR22 is equipped with an 84-gallon wet-wing fuel storage system (81 gallons
usable).
The fuel tanks are located between the forward and aft wing spars. Each tank holds
42gallons (40.5 gallons usable).
Approved fuel grades include 100 and 100 low lead.
The SR22's engine incorporates a wet sump with a capacity of 8 U.S. Quarts.
CAUTION: The engine should not be operated with less than 6 quarts of oil.
For extended flights, 7 quarts, as indicated by the dipstick, is recommended.
Various grades of oil may be used in the engine.
SAE grades 15W-50, 20W-50 and 20W-60 may be used in all temperatures.
SAE 30 oil may be used in temperatures below 40º F.
SAE 50 oil may be used in temperatures above 40º F.
The SR22 has a maximum takeoff weight of 3,400 pounds.
The airplane's standard empty weight is 2,250 pounds.
This results in a maximum useful load of 1,150 pounds.
The maximum useful load of 1,150 pounds includes fuel, baggage and passengers.
Maximum fuel weight is 504 pounds which corresponds to 84 gallons.
Maximum baggage weight for the baggage compartment is 130 pounds.
With full fuel and 130 pounds of baggage in the baggage compartment, the total weight
of pilot and passengers is limited to 516 pounds.
Wing loading is gross weight divided by wing area. The SR22 has a wing loading of
23.5 pounds per square foot.
Power loading is gross weight divided by engine horsepower. The SR22 has a power
loading of 11 pounds per horsepower.
The SR22 Pilot's Operating Handbook uses certain terminology and abbreviations.
This briefing covers what is used for airspeeds, engine parameters, performance, weight
and balance, and meteorology.
Knots calibrated airspeed is indicated airspeed corrected for position and instrument
error.
Calibrated airspeed equals true airspeed at sea level in a standard atmosphere.
Knots indicated airspeed is the airspeed displayed on the airspeed indicator.
The IAS values that are published in the SR22 pilot's operating handbook assume no
instrument error.
Knots true airspeed is the airspeed in undisturbed air. It is knots calibrated airspeed
corrected for altitude and temperature.
The best glide speed is the power-off airspeed that results in the greatest horizontal
distance traveled per unit altitude lost.
The operating maneuvering speed is the maximum airspeed at which application of full
control movement will not overstress the airplane
The maximum flap extended speed is the highest permissible airspeed with wing flaps
extended.
The maximum structural cruising speed is the airspeed that should not be exceeded
except in smooth air, and then only with caution.
The never exceed speed is the airspeed that may not be exceeded at any time.
The maximum demonstrated parachute deployment speed is the maximum airspeed at
which parachute deployment has been demonstrated.
Vs is the stalling speed or minimum steady flight speed at which the airplane is
controllable.
Vs 50% is stalling speed or the minimum steady flight speed at which the airplane is
controllable with 50 percent flaps.
Vso is stalling speed or the minimum steady flight speed at which the airplane is
controllable in the landing configuration (100% flaps).
Vso is determined with the most unfavorable weight and balance loading.
The best angle of climb airspeed is the airspeed that results in the greatest gain in altitude
for a given horizontal distance.";
The best rate of climb speed is the airspeed that results in the greatest gain in altitude in a
given time.
Horsepower is the power developed by the engine.
Maximum continuous power is the maximum power that can be used continuously.
Manifold pressure is the pressure in the engine's induction system and is indicated in
inches of mercury (in Hg).
Engine rotation speed is measured in revolutions per minute.
Static RPM is the RPM achieved during a full-throttle engine run up when the airplane is
on the ground and stationary.
One ''g'' is a quantity of acceleration equal to that produced by earth's gravity.
The demonstrated crosswind velocity is the velocity of the crosswind component for
which adequate control was demonstrated.
Adequate control is demonstrated for taxi, takeoff, and landing during certification
testing.
The demonstrated crosswind velocity is not considered to be limiting.
Service ceiling is the maximum altitude at which the airplane, at maximum weight, is
able to achieve a climb rate of 100 feet per minute.
The amount of fuel consumed by the engine is measured in gallons per hour.
Nautical miles per gallon is the distance traveled per gallon of fuel consumed at a specific
power setting and/or flight configuration.
Unusable fuel is the quantity of fuel that cannot be safely used in flight.
Usable fuel is the fuel that is available for flight planning.
The Center of Gravity is the point at which an airplane will balance if suspended.
Its distance from the reference datum is determined by dividing the total moment by the
total weight of the airplane.
The arm is the horizontal distance from the reference datum to the center of gravity of an
item.
The arm is calculated by adding the airplane's individual moments and dividing the sum
by the airplane's total weight.
Basic empty weight is the weight of the airplane including all operating equipment that
has a fixed location in the airplane.
The basic empty weight includes the weight of unusable fuel and full oil.
The mean aerodynamic chord is the chord that is drawn through the centroid of the wing
plan area.
The leading edge of the mean aerodynamic chord is the forward edge of the MAC given
in inches aft of the reference datum.
Maximum gross weight is the maximum permissible weight of the airplane and its
contents as listed in the aircraft specifications.
Moment is the product of an item's weight multiplied by its arm.
Useful load is the basic empty weight subtracted from the maximum weight of the
airplane.
It is the maximum allowable combined weight of the pilot, passengers, fuel and baggage.
Station is a location along the airplane fuselage measured in inches from the reference
datum.
For example, a point 123 inches aft of the reference datum is Fuselage Station 123.
The reference datum is an imaginary vertical plane from which all horizontal distances
are measured for balance purposes.
Tare is the weight of all items used to hold or position the airplane on the scales for
weighing.
Tare includes blocks, shims, and chocks. Tare weight must be subtracted from the scale
reading.
Instrument Meteorological Conditions is weather expressed in terms of visibility,
distance from cloud, and ceiling less than the minimums for VFR.
International Standard Atmosphere (standard day) is an atmosphere with specific
properties.
The air is a dry, perfect gas, with a sea level temperature of 15º C and a sea level pressure
of 29.92 inches of mercury.
In addition, the temperature gradient from sea level to the altitude with a temperature of 56.5º C is -2º C per 1000 feet, and is zero above that altitude.
Mean Sea Level is the average height of the surface of the sea for all stages of tide.
In the SR22 POH, altitude given as MSL is altitude above mean sea level.
It is the altitude indicated by the altimeter when the altimeter's barometric adjustment has
been set using meteorological sources.
Outside Air Temperature is the free air static temperature obtained from inflight
temperature indications or ground meteorological sources.
Outside Air Temperature is expressed in either degrees Celsius or degrees Fahrenheit.
Pressure altitude is the altitude that is indicated by the altimeter when the barometric
adjustment is set to 29.92 inches of mercury and corrected for position and
instrument error.
In the SR22 POH, altimeter instrument errors are assumed to be zero.
Standard Temperature is the temperature at a given altitude in a standard atmosphere.
It is 15º C at sea level pressure altitude and decreases about 2º C for each 1,000 feet of
altitude increase.