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position, and then release the lock button. Pulling the knob opens the
alternate air induction door on the engine induction air manifold,
bypasses the air filter, and allows warm unfiltered air to enter the
engine. Alternate induction air should be used if blocking of the normal
air source is suspected. Operation using alternate induction air should
be minimized and the cause of filter blocking corrected as soon as
practical.
Engine Indicating
The SR20 is equipped with engine instrumentation and warning lights
to monitor the engine performance.
• Note •
For additional information on instrument limit markings, refer
to Section 2, Limitations.
March 2010
Information Manual 7-47
Cirrus Design Section 7
SR20 Airplane Description
Serials 1268 through 1581: The engine instruments are located on the
right side of the instrument panel and the oil temperature/pressure
warning light is located in the annunciator panel immediately in front of
the pilot.
Serials 1582 and subsequent: The engine instrumentation is displayed
on the MFD’s Engine Page. A separate Data Acquisition Unit (DAU),
mounted above the right hand kickplate, converts analog signals from
the CHT, EGT, MAP, oil pressure, oil temperature, and tachometer
sensors to digital format, which are then transmitted to the MFD and/or
PFD for display. 28 VDC for Data Acquisition Unit operation is supplied
through the 2-amp ANNUN / ENGINE INST circuit breaker on the
Essential Bus
The PFD presents percent power in the upper left area of the display
in vertical tape format and as text immediately above. Engine RPM,
manifold pressure, fuel flow and oil pressure are continuously
displayed in the engine data block located in the lower right corner of
the PFD.
System health, caution, and warning messages are displayed in colorcoded
advisory boxes in the lower right corner of the MFD. In addition,
the text of the engine parameters displayed on the PFD change to the
corresponding color of advisory box during an annunciation event.
The oil temperature/pressure warning light is located in the
annunciator panel immediately in front of the pilot.
• Note •
Serials 1268 and subsequent with optional EMax Engine
Monitoring after factory installation or after Service Bulletin SB
22-77-01: The following engine instrument component
descriptions are the same as those listed for airplane serials
1582 and subsequent except:
• EGT and CHT probes are installed to each exhaust pipe and
cylinder head respectively. MFD functionality is enhanced by
displaying six channels of EGT and CHT data.
Refer to Avidyne FlightMax EX5000C Pilot’s Guide, for a more
complete description of the MFD, its operating modes, and additional
detailed operating procedures for the EMax option.
March 2010
7-48 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Figure 7-9
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
Engine Controls and Indicating (Sheet 1 of 2)
March 2010
Information Manual 7-49
Cirrus Design Section 7
SR20 Airplane Description
FUEL
OIL
LOW VOLTS
PITOT HEAT
ALT 1
ALT 2
11
LEGEND
4. Tachometer
5. EGT ( shown with EMax )
6. CHT (shown with EMax)
7. Oil Temperature
8. Oil Pressure
9. Manifold Pressure
10. Percent Power
11. Oil Warning Light
5
4 11 7 8
Engine Instruments
9
6
Multifunction Display
Primary Flight Display 4,9,8
10
Annunciator
Panel
Serials 1582 & subs. SR20_FM07_2217
Figure 7-9
Engine Controls and Indicating (Sheet 2 of 2)
March 2010
7-50 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Tachometer
Serials 1268 through 1581: 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.
The electrically operated tachometer receives a speed signal from a
magnetic pickup on the right hand magneto. 28 VDC for instrument
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西锐20飞机信息手册CIRRUS DESIGN SR20 AIRPLANE INFORMATION MA(66)
