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monitor the engine performance. The instruments are located on the
right side of the instrument panel and the warning lights are located in
the annunciator panel immediately in front of the pilot.
• Note •
For additional information on instrument limit markings, refer
to Section 2, Limitations.
March 2010
Information Manual 7-37
Cirrus Design Section 7
SR20 Airplane Description
Engine Instruments
7,8
9
5,6
4
Serials 1005 thru 1581.
G I
T
F
E
L R
FUEL
Controls
LEGEND
1. Power Lever
2. Mixture Control
3. Friction Control
4. Tachometer
5. EGT
Alternate Air Control
Start / Ignition Switch
3
2
1
SR20_FM07_1603A
Serials 1005 thru 1336:
Switch is located on the
left bolster panel.
6. CHT
7. Oil Temperature
8. Oil Pressure
9. Manifold Pressure
Figure 7-7
Engine Controls and Indicating
March 2010
7-38 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Tachometer
A 2¼” tachometer is mounted on the right instrument panel adjacent to
the other engine instruments. The tachometer pointer sweeps a scale
marked from 0 to 3500 RPM in 100 RPM increments. Refer to Section
2 (Limitations) for instrument limit markings. The electrically operated
tachometer receives a speed signal from a tachometer generator
mounted on the aft end of the engine between the magnetos. 28 VDC
for instrument operation is supplied through the 5-amp ENGINE INST
circuit breaker on the Essential Bus.
Exhaust Gas Temp / Cylinder Head Temp Gage
A 2¼” combination Exhaust Gas Temperature (EGT) and Cylinder
Head Temperature (CHT) indicator is mounted in the right instrument
panel. 28 VDC for instrument operation is supplied through the 5-amp
ENGINE INST circuit breaker on the Essential Bus 1.
The EGT pointer sweeps a scale marked from 1250 F to 1650 F in
25 F increments. The EGT scale has no limit markings. The
electrically operated EGT indicator receives a temperature signal from
a thermocouple mounted in the left exhaust pipe.
The CHT pointer sweeps a scale marked from 200 F to 500 F. Refer
to Section 2 (Limitations) for instrument limit markings. The electrically
operated CHT indicator receives a temperature signal from a
temperature sensor mounted in the #2 cylinder head on the left side of
the engine.
Oil Temperature / Oil Pressure Gage
A 2¼” combination Oil Temperature and Oil Pressure indicator is
mounted on the right instrument panel immediately below the EGT/
CHT indicator. The instrument is internally lighted. 28 VDC for
instrument operation is supplied through the 5-amp ENGINE INST
circuit breaker on the Essential Bus.
The Oil Temperature pointer sweeps a scale marked from 75 F to
250 F in 25 F increments. Refer to Section 2 (Limitations) for
instrument limit markings. The Oil Temperature indicator receives a
temperature signal from a temperature sending unit mounted on the
engine near the left magneto.
The Oil Pressure pointer sweeps a scale marked from 0 psi to 100 psi.
Refer to Section 2 (Limitations) for instrument limit markings. The Oil
March 2010
Information Manual 7-39
Cirrus Design Section 7
SR20 Airplane Description
Pressure indicator receives a pressure signal from an oil pressure
sensor on the left side of the engine. Normally, oil pressure may drop
to 10 psi at idle but will be in the 30 - 60 psi range at higher RPM.
Fuel Flow / Manifold Pressure Gage
A 2¼” combination Fuel Flow and Manifold Pressure indicator is
mounted on the right instrument panel immediately below the
tachometer. The indicator is internally lighted. 28 VDC for instrument
operation is supplied through the 5-amp ENGINE INST circuit breaker
on the Essential Bus.
The Fuel Flow pointer sweeps a scale marked from 0 to 18 Gal/Hr.
Refer to Section 2 (Limitations) for instrument limit markings. The
electrically operated Fuel Flow indicator receives a fuel-flow rate
signal from a fuel-flow transducer installed in the fuel line between the
throttle body metering valve and the injector manifold (spider).
The Manifold Pressure pointer sweeps a scale marked from 10 to 35
inches Hg in 5-inch Hg increments. Refer to Section 2 (Limitations) for
instrument limit markings. 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.
　
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