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Airspeed Indicator
• Note •
Serials 0435 and subsequent with PFD: The standby airspeed
indicator is mounted on the LH bolster panel.
Indicated and true airspeeds are indicated on a dual-scale, internally
lit precision airspeed indicator installed in the pilot's instrument panel.
The instrument senses difference in static and Pitot pressures and
displays the result in knots on an airspeed scale. A single pointer
sweeps an indicated airspeed scale calibrated from 40 to 220 knots.
The 'zero' index is at the 12 o'clock position. A sub-scale aligns true
airspeed with the corresponding indicated airspeed when the altitude/
June 2007
Information Manual 7-27
Cirrus Design Section 7
SR22 Airplane Description
temperature correction is set in the correction window. A knob in the
lower left corner of the instrument is used to rotate the pressure
altitude scale in the correction window to align the current pressure
altitude with the outside air temperature.
Vertical Speed Indicator
• Note •
Serials 0435 and subsequent with PFD: The Vertical Speed
Indicator is integrated into the PFD.
Airplane rate of climb or descent in feet per minute is displayed on the
internally lit Vertical Speed indicator installed in the pilot's instrument
panel. The instrument senses rate of change in static pressure from a
reference pressure and displays the result in climb or descent feet per
minute (FPM). Climb is indicated by clockwise rotation of the pointer
from zero and descent is indicated by counter clockwise rotation. The
'0' (zero) reference point is at the 9 o'clock position. The scale is
calibrated from 0 to 2000 FPM in 100-FPM increments in both the 'UP'
and 'DOWN' directions.
Altimeter
• Note •
Serials 0435 and subsequent with PFD: The standby altimeter
is mounted on the LH bolster panel.
Airplane altitude is depicted on a conventional, three-pointer, internally
lit barometric altimeter installed in the pilot's instrument panel. The
instrument senses the local barometric pressure adjusted for altimeter
setting and displays the result on the instrument in feet. The altimeter
is calibrated for operation between -1000 and 20,000 feet altitude. The
scale is marked from 0 to 10 in increments of 2. The long pointer
indicates hundreds of feet and sweeps the scale every 1000 feet (each
increment equals 20 feet). The short, wide pointer indicates thousands
of feet and sweeps the scale every 10,000 feet (each increment equals
200 feet). The short narrow pointer indicates tens of thousands feet
and sweeps from 0 (zero) to 2 (20,000 feet with each increment equal
to 2000 feet). Barometric windows on the instrument's face allow
barometric calibrations in either inches of mercury (in.Hg) or millibars
June 2007
7-28 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
(mb). The barometric altimeter settings are input through the
barometric adjustment knob at the lower left of the instrument.
Turn Coordinator
• Note •
Serials 0435 and subsequent with PFD: Turn Coordinator
function and roll data display is integrated into the PFD.
Serials with Avionics Configuration A - 0002 through 1601, 1603
through 1643 and 1645 through 1662 without PFD: The electric turn
coordinator displays roll information and provides roll data to the
integral System 30 autopilot. Roll rate is sensed by a single-gimbal,
electric-powered gyro and displayed on the face of the instrument. The
display consists of a symbolic airplane rotates to indicate turn rate and
a standard glass tube and ball inclinometer. Markings, labeled L & R,
indicate roll for a standard rate turn in the direction indicated.
Redundant circuits paralleled through diodes at the indicator supply
DC electrical power. 28 VDC for roll rate gyro operation is supplied
through the 2-amp TURN COORD #1 circuit breaker on the Essential
Bus and the 2-amp TURN COORD #2 circuit breaker on the Main Bus
2.
Serials with Avionics Configuration B - 0002 through 1601, 1603
through 1643 and 1645 through 1662 without PFD: The electric turn
coordinator, installed in the instrument panel, displays roll information
and provides roll data to the System 55X autopilot. The instrument and
power supplies are as described above.
Course Deviation Indicator
• Note •
Serials 0435 and subsequent with PFD: The Course Deviation
Indicator is integrated into the PFD.
Serials with Avionics Configuration A - 0002 through 1601, 1603
through 1643 and 1645 through 1662 without PFD: The Course
Deviation Indicator (CDI) displays navigation information from GPS 2
　
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