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Fuel Flow and/or Manifold Pressure Gage
Serials 0002 through 1601, 1603 through 1643 and 1645 through
1662: A 2¼” combination Fuel Flow and Manifold Pressure indicator is
mounted on the right instrument panel immediately below the
Revision A5
P/N 13772-001 7-51
Cirrus Design Section 7
SR22 Airplane Description
tachometer. The indicator is internally lighted. 28 VDC for instrument
operation is supplied through the 5-amp ENGINE INST circuit breaker
on Main Bus #1.
The Fuel Flow pointer sweeps a scale marked from 0 to 30 Gal/Hr.
The electrically operated Fuel Flow indicator receives a fuel-flow rate
signal from a fuel-flow transducer on the right side of the engine in the
fuel line between the engine driven fuel pump and throttle body
metering valve.
The Manifold Pressure pointer sweeps a scale marked from 10 to 30
inches Hg in one-inch Hg increments. The electrically operated
manifold pressure indicator receives a pressure signal from a pressure
sensor mounted in the induction airstream on the left side of the
induction air manifold near the throttle body.
Serials 1602, 1644, 1663 and subsequent: Manifold pressure is shown
in the upper left corner of the MFD as both a simulated temperature
gage and as text.
The simulated gage receives a pressure signal from a pressure sensor
mounted in the induction air manifold near the throttle body via the
DAU and sweeps a scale marked from 10 to 30 inches Hg in one-inch
Hg increments.
Manifold pressure is also continuously displayed in the engine data
block located in the lower right corner of the PFD.
28 VDC for the digital instrument operation is supplied through the 2-
amp ANNUN / ENGINE INST circuit breaker on the Essential Bus.
Percent Power Gage
Serials 1602, 1644, 1663 and subsequent: Percent power is shown in
the upper middle section of the MFD as both a simulated gage and as
text.
The simulated gage displays calculated percent of maximum engine
power produced by the engine based on an algorithm employing
manifold pressure, indicated air speed, outside air temperature,
pressure altitude, engine speed and fuel flow. The percent power gage
sweeps a scale marked from 0 to 100 percent in 5 percent increments.
Percent power is also continuously displayed in the upper left area of
the PFD in vertical tape format and as text immediately above.
Revision A5
7-52 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
28 VDC for the digital instrument operation is supplied through the 2-
amp ANNUN / ENGINE INST circuit breaker on the Essential Bus.
Oil Warning Light
The red OIL warning light in the annunciator panel comes on to
indicate either high oil temperature or low oil pressure. The light is
illuminated by a switch in the oil temperature gage/DAU if the oil
temperature reaches 240°F or if the oil pressure drops to 10 psi or
less. If the OIL warning light comes on in flight, refer to the oil
temperature and pressure gages to determine the cause. Typically, low
oil pressure will be accompanied by a high oil temperature indication.
The light is powered by 28 VDC through the 2-amp ANNUN / ENGINE
INST circuit breaker on the Essential Bus.
Revision A5
P/N 13772-001 7-53
Cirrus Design Section 7
SR22 Airplane Description
Propeller
The airplane is equipped with a constant-speed, aluminum-alloy
propeller with a three-blade (78" diameter) propeller and governor.
The propeller governor automatically adjusts propeller pitch to
regulate propeller and engine RPM. The propeller governor senses
engine speed by means of flyweights and senses throttle setting
through a cable connected to the power (throttle) control lever in the
cockpit. The propeller governor boosts oil pressure in order to regulate
propeller pitch position. Moving the throttle lever forward causes the
governor to meter less high-pressure oil to the propeller hub allowing
centrifugal force acting on the blades to lower the propeller pitch for
higher RPM operation. Reducing the power (throttle) lever position
causes the governor to meter more high-pressure oil to the propeller
hub forcing the blades to a higher pitch, lower RPM, position. During
stabilized flight, the governor automatically adjusts propeller pitch in
order to maintain an RPM setting (throttle position). Any change in
airspeed or load on the propeller results in a change in propeller pitch.
Revision A5
7-54 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
Fuel System
An 81-gallon usable wet-wing fuel storage system provides fuel for
engine operation. The system consists of a 42-gallon capacity (40.5-
　
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