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position provides maximum cooling airflow to the mixing plenum.
Cabin Air Selector
Conditioned air from the mixing plenum can be proportioned and
directed to the windshield or passengers by manipulating the Cabin Air
Selector. The control is linked to a door at the outlet end of the mixing
plenum. Rotating the control full counterclockwise to the miniature
windshield shuts off airflow to the passenger air distribution system
and allows maximum airflow to the windshield diffuser. Rotating the
knob full clockwise to the seated person icon shuts off airflow to the
windshield diffuser and allows maximum airflow to the passenger air
distribution system. The control can be positioned to allow any
proportion of windshield and passenger air.
Conditioned air for the forward seats is routed to outlets under the
instrument panel at knee level. Conditioned air for the aft seats is
ducted to outlets beneath the forward seats near the door posts and
exits at floor level.
March 2010
7-60 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Figure 7-12
AIRSPEED
INDICATOR
PRIMARY
FLIGHT DISPLAY
Serials 1005 thru 1336 ,1337
thru 1422 w/o PFD.
Serials 1337 & subs w/ PFD.
SR20_FM07_1013D
PITOT MAST
STATIC
BUTTONS
PITOT-STATIC
WATER TRAPS
ALTERNATE
STATIC
AIR SOURCE
VERTICAL SPEED
INDICATOR ALTIMETER
ALTITUDE
TRANSDUCER
(OPTIONAL)
ALTITUDE
ENCODER
ANNUNCIATOR
PITOT
HEAT
LOGIC
CURRENT
SENSOR
HEATER
7.5A
PITOT
HEAT
CB PITOT HEAT SW
Pitot-Static System
March 2010
Information Manual 7-61
Cirrus Design Section 7
SR20 Airplane Description
Pitot-Static System
The Pitot-Static system consists of a single heated Pitot tube mounted
on the left wing and dual static ports mounted in the fuselage. The
Pitot heat is pilot controlled through a panel-mounted switch. An
internally mounted alternate static pressure source provides backup
static pressure should that the primary static source becomes blocked.
Water traps with drains, under the floor in the cabin, are installed at
each Pitot and static line low point to collect any moisture that enters
the system. The traps should be drained at the annual inspection and
when water in the system is known or suspected.
Pitot Heat Switch
The heated Pitot system consists of a heating element in the Pitot
tube, a rocker switch labeled PITOT HEAT, and associated wiring. The
switch and circuit breaker are located on the left side of the switch and
control panel. When the Pitot heat switch is turned on, the element in
the Pitot tube is heated electrically to maintain proper operation in
possible icing conditions. Pitot heat should be used only when
required. The Pitot heat system operates on 28 VDC supplied through
the 7.5-amp PITOT HEAT/COOLING FAN circuit breaker on the Non-
Essential Bus.
Pitot Heat Light
Illumination of the amber PITOT HEAT caution light indicates that the
Pitot Heat switch is in the ‘on’ position and the Pitot heater is not
receiving electrical current. A current sensor on the Pitot heater power
supply wire provides current sensing. The PITOT HEAT warning light
operates on 28 VDC supplied through the 2-amp ANNUN circuit
breaker on the Essential Bus.
Alternate Static Source
An alternate static pressure source valve is installed on the switch and
control panel to the right of the pilot’s leg. This valve supplies static
pressure from inside the cabin instead of the external static port. If
erroneous instrument readings are suspected due to water or ice in
the pressure line going to the standard external static pressure source,
the alternate static source valve should be turned on. Pressures within
the cabin will vary with open heater/vents. Whenever the alternate
March 2010
7-62 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
static pressure source is selected, refer to Section 5 airspeed
calibration and altitude for corrections to be applied.
Vacuum System
The airplane vacuum system provides the vacuum necessary to
operate the attitude gyro and directional gyro. The system consists of
an engine-driven vacuum pump, an electric vacuum pump for backup,
two vacuum switches, two annunciators, a vacuum manifold, a vacuum
regulator, vacuum system air filter, and the vacuum-driven instruments
(including a suction gauge). The backup portion of the system
operates automatically to provide vacuum for the instruments should
　
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