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June 2007
Information Manual 7-59
Cirrus Design Section 7
SR22 Airplane Description
FUEL
OIL
LOW VOLTS
PITOT HEAT
ALT 1
ALT 2
9
LEGEND
4. Fuel Flow
5. Fuel Used (EMax only)
6. Fuel Remaining (EMax only)
7. Time Remaining (EMax only)
8. Fuel Economy (EMax only)
9. Fuel Caution Light Serials 1602, 1644, 1663 & subs. SR22_FM07_2228
Multifunction Display
Primary Flight Display 4
Annunciator
Panel
4
5
6
7
8
Figure 7-11
Fuel System Controls and Indicating (Sheet 2 of 2)
June 2007
7-60 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
Fuel Flow Indication
Serials 0002 through 1601, 1603 through 1643 and 1645 through
1662: Fuel flow indication is integral to the combination Fuel Flow/
Manifold Pressure Gage. Refer to preceding discussion on Fuel Flow
and Manifold Pressure Gage for complete description of fuel flow
indication.
Serials 1602, 1644, 1663 and subsequent: Fuel flow is shown as text
in the fuel data block located in the lower right section of the MFD and
is also continuously displayed in the engine data block located in the
lower right corner of the PFD. The MFD and PFD receives a fuel-flow
rate signal via the DAU 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.
In the event fuel flow exceeds 30.0 gallons per hour, the MFD will
display “Check Fuel Flow” 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.
Fuel Caution Light
The amber FUEL caution light in the annunciator panel comes on to
indicate a low fuel condition. The light is illuminated by switches in the
fuel quantity indicator if the fuel quantity in both tanks drops below
approximately 14 gallons (28 gallons total with tanks balanced in level
flight). Since both tanks must be below 14 gallons to illuminate the
light, the light could illuminate with as little as 14 gallons in one tank
during level flight if the other tank is allowed to run dry. If the FUEL
caution light comes on in flight, refer to the Fuel Quantity gages to
determine fuel quantity. The light is powered by 28 VDC through the 2-
amp ANNUN / ENGINE INST circuit breaker on the Essential Bus.
June 2007
Information Manual 7-61
Cirrus Design Section 7
SR22 Airplane Description
Boost Pump Switch
Boost pump operation and engine prime is controlled through the Fuel
Pump BOOST-PRIME switch located adjacent to the fuel selector
valve. The PRIME position is momentary and the BOOST position is
selectable. A two-speed prime allows the fuel pressure to rapidly
achieve proper starting pressure.
Serials 0002 through 0277 before SB 22-73-01: For engine starting,
pressing PRIME causes the boost pump to operate at high speed until
the fuel pressure reaches 2-4 psi. When the fuel pressure reaches the
2-4 psi range, a pressure switch in the fuel injection line switches the
boost pump to the low-speed mode to provide a 4-6 psi fuel pressure
boost. Selecting BOOST energizes the boost pump in low-speed
mode to deliver a continuous 4-6 psi boost to the fuel flow for vapor
suppression in a hot fuel condition.
Serials 0278 and subs, and serials 0002 through 0277 after SB 22-73-
01: An oil pressure based system is used to control boost pump
operation. The oil pressure/oil temperature sensor provides a signal to
the starting circuit/DAU to generate a ground for the oil annunciator
and the fuel system. This system allows the fuel pump to run at high
speed (PRIME) when the engine oil pressure is less than 10 PSI.
Whenever the engine oil pressure exceeds 10 PSI, pressing PRIME
will have no effect. Selecting BOOST energizes the boost pump in lowspeed
mode regardless of oil pressure to deliver a continuous 4-6 psi
boost to the fuel flow for vapor suppression in a hot fuel condition.
The boost pump operates on 28 VDC supplied through the 5-amp
FUEL PUMP circuit breaker on Main Bus 2.
June 2007
7-62 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
Brake System
The main wheels have hydraulically operated, single-disc type brakes,
individually activated by floor mounted toe pedals at both pilot stations.
A parking brake mechanism holds induced hydraulic pressure on the
disc brakes for parking.
The brake system consists of a master cylinder for each rudder pedal,
　
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