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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 0002 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
1602, 1644, 1663 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.
Revision A8
7-46 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
Figure 7-9
Engine Instruments
7,8
9
5,6
4
Serials 0002 thru 1601,
1603 thru 1643, 1645 thru 1662.
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
SR22_FM07_1603A
Serials 0002 thru 0434:
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)
Revision A5
P/N 13772-001 7-47
Cirrus Design Section 7
SR22 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
Serials 1602, 1644, 1663 & subs. SR22_FM07_2218
Multifunction Display
Primary Flight Display 4,9,8
10
Annunciator
Panel
Figure 7-9
Engine Controls and Indicating (Sheet 2 of 2)
Revision A5
7-48 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
Tachometer
Serials 0002 through 1601, 1603 through 1643 and 1645 through
1662: 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
operation is supplied through the 5-amp ENGINE INST circuit breaker
on Main Bus 1.
Serials 1602, 1644, 1663 and subsequent: Engine RPM is shown in
the upper left-most corner of the MFD as both a simulated tachometer
and as text. The simulated tachometer receives a speed signal from a
magnetic pickup on the right hand magneto via the DAU and sweeps a
scale marked from 0 to 3000 RPM in 50 RPM increments.
Engine RPM is also continuously displayed in the engine data block
located in the lower right corner of the PFD.
In the event engine speed exceeds 2710 RPM for five seconds, the
MFD will display “Check RPM” in a red advisory box in the lower right
corner of the MFD.
28 VDC for the digital instrument operation is supplied through the 2-
amp ANNUN / ENGINE INST circuit breaker on the Essential Bus.
Exhaust Gas Temp / Cylinder Head Temp Gage/Bar Graphs
Serials 0002 through 1601, 1603 through 1643 and 1645 through
1662 without EMax Engine Monitoring: 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
　
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