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For additional information on the System Annunciations And
Alerts, refer to the Perspective Integrated Avionics System
description in this section.
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-33
Figure 7-7
Engine Controls and Indicating
Density Alt 8000 Ft
Oat 31°F -1°C (ISA +0°C)
8
Engine Instruments
Engine Controls
9
10
7
1 3 4 5 6
LEGEND
1. Percent Power
2. CHT
3. Tachometer
4. EGT
5. Manifold Pressure
6. Oil Temperature
and Pressure
7. Alternate Air Control
8. Power Lever
9. Friction Control
10. Mixture Control
2
SR22_FM07_2796
March 2010
7-34 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Tachometer
Engine speed (RPM) is shown in the upper mid-left corner of the
ENGINE page as both a simulated tachometer and as a digital value.
The tachometer pointer sweeps a scale range from 0 to 3000 RPM in
100 RPM increments. The digital RPM value is displayed in
increments of 10 RPM in white numerals below the gage.
The tachometer receives a speed signal from a magnetic pickup
sensor on the right hand magneto from the Engine Indicating System
via the Engine Airframe Unit.
Exhaust Gas Temperature (EGT)
Exhaust gas temperatures for all six cylinders are displayed in the
Engine Temperature block of the ENGINE page as vertical bars. The
EGT graph is marked from 1000°F to 1600°F in 100°F increments.
The digital EGT value of the cylinder is displayed above the bar in
white numerals. A sensor in the exhaust pipe of each cylinder
measures exhaust gas temperature and provides a voltage signal to
the Engine Airframe Unit which processes and transmits the data to
the Engine Indicating System.
Cylinder Head Temperature (CHT)
Cylinder head temperatures for all six cylinders are displayed in the
Engine Temperature block of the ENGINE page as vertical bars. The
CHT graph is marked from 100°F to 500°F in 100°F increments. The
digital CHT value of the cylinder is displayed above the bar in white
numerals.
A sensor in each cylinder head measures cylinder head temperature
and provides a voltage signal to the Engine Airframe Unit which
processes and transmits the data to the Engine Indicating System.
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-35
Oil Temperature
Oil temperature is shown in the upper right corner of the ENGINE
page, opposite the oil pressure scale, as both a simulated temperature
gage and as a digital value. The gage pointer sweeps a scale range
from 75°F to 250°F in 50°F increments. The digital temperature value
is displayed in white numerals below the gage.
The oil temperature sensor is mounted below the oil cooler and
provides a signal to the Engine Airframe Unit that is processed and
transmitted to the Engine Indicating System for display.
Oil Pressure
Oil Pressure is shown in the upper right corner of the ENGINE page,
opposite the oil temperature scale, as both a simulated pressure gage
and as a digital value. The gage pointer sweeps a scale range from 0
to 90 PSI in 10 PSI increments. The digital pressure value is displayed
in white numerals below the gage.
The oil pressure sensor is mounted below the oil cooler and provides a
signal to the Engine Airframe Unit that is processed and transmitted to
the Engine Indicating System for display.
Manifold Pressure Gage
Manifold pressure is shown in the upper center portion of the ENGINE
page as both a simulated pressure gage and as a digital value. The
gage pointer sweeps a scale range from 10 to 35 inches Hg in 1 inch
Hg increments. The digital MAP value is displayed in white numerals
below the gage. The manifold pressure sensor is mounted in the
induction air manifold near the throttle body and provides a signal to
the Engine Airframe Unit that is processed and transmitted to the
Engine Indicating System for display.
Percent Power Gage
Percent power is shown in the upper left corner of the ENGINE page
as both a simulated gage and as a digital value. The percent power
gage sweeps a scale marked from 0 to 100 percent in 5 percent
increments. The digital percent power value is displayed in white
numerals below the gage. The display units calculate the percentage
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.
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西锐20飞机信息手册 SR22 AIRPLANE INFORMATION MANUAL 2979(62)
