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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
Revision A5
7-28 P/N 13772-001
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
(Garmin GNC 420). The CDI displays GPS track deviation on a single
deviation bar instrument. A vertical line displays GPS track deviation
against a 5-dot scale. The indicator incorporates TO/FROM
annunciation and NAV flag. An OBS knob is used to manually rotate
Revision A5
P/N 13772-001 7-29
Cirrus Design Section 7
SR22 Airplane Description
the azimuth card to the desired bearing. 28 VDC for lighting is supplied
through the 2-amp INST LIGHTS circuit breaker on Main Bus 1.
Serials with Avionics Configuration B - 0002 through 1601, 1603
through 1643 and 1645 through 1662 without PFD: The Course
Deviation Indicator (CDI) displays navigation information from GPS 2
(Garmin GNS 430). Navigation source selection is made using the CDI
button on the GPS 2 control. The CDI displays course deviation from a
VOR or Localizer (LOC) and Glideslope when 'VLOC' is the selected
navigation source and displays GPS track deviation when 'GPS' is the
selected navigation source. The instrument has two deviation bars.
The vertical line displays VOR/LOC or GPS track deviation against a
5-dot scale. The horizontal line displays glideslope deviation against a
5-dot scale. The indicator incorporates TO/FROM annunciation, NAV
flag, and GS flag. An OBS knob is used to manually rotate the azimuth
card to the desired bearing. 28 VDC for instrument lighting is supplied
through the 2-amp INST LIGHTS circuit breaker on Main Bus 1.
　
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