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(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
June 2007
Information Manual 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.
Horizontal Situation Indicator
• Note •
Serials 0435 and subsequent with PFD: The Horizontal
Situation Indicator is integrated into the PFD.
Serials with Avionics Configuration A - 0002 through 1601, 1603
through 1643 and 1645 through 1662 without PFD: The Century NSD-
1000 is a conventional HSI that provides gyro stabilized, magnetically
slaved, heading information, a pictorial VOR/LOC display with a
conventional course arrow, and glideslope presentation. The
instrument displays airplane heading by rotating a compass dial in
relation to a fixed simulated airplane image and lubber line. The HSI
directional gyro, which drives the compass dial, is slaved to a flux
detector in the right wing through an amplifier under the copilot's floor.
A FREE GYRO-SLAVE switch, below the display, allows the pilot to
select either Free Gyro mode or Slave mode. In Slave mode, the gyro
is slaved to the flux detector. In Free Gyro mode, the gyro must be
manually set to the airplane's magnetic compass using the PUSHSET-
CARD knob in the lower right corner of the instrument. The
course is set using the Course (Arrow) knob in the lower left corner of
the instrument. The HSI course and heading outputs provided to the
June 2007
7-30 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
autopilot to allow NAV/LOC/GPS course tracking or to track a preset
heading.
The HSI incorporates conventional warning flags. The HDG (Heading)
flag will be out of view whenever the instrument is receiving sufficient
electrical power for operation. The NAV (Navigation) flag will be out of
view when a VOR or LOC frequency is tuned in the NAV1 receiver and
a reliable signal is present. The GS (Glideslope) flag will be out of view
when an ILS frequency is tuned on the Nav 1 receiver and a reliable
GS signal is present.
The NSD-1000 HSI is electrically driven and a red GYRO flag
indicates loss of electrical power. Redundant circuits paralleled
through diodes at the indicator supply DC electrical power for gyro
operation. 28 VDC for the redundant power circuits is supplied through
the 5-amp HSI 1 circuit breaker on the Essential Bus and 5-amp HSI 2
circuit breaker on Main Bus 2.
Serials with Avionics Configuration B - 0002 through 1601, 1603
through 1643 and 1645 through 1662 without PFD: The Sandel
SN3308 combines the functions of an HSI, an RMI, a full color moving
map, a Stormscope display, GPS annunciator, and 3-light marker
beacon indicators. Compass information is derived from a remote
directional gyro and a flux detector. Redundant power sources provide
28 VDC for system operation. Power is supplied through the 5-amp
HSI #1 circuit breaker on the Essential Bus and the 5-amp HSI #2
circuit breaker on Main Bus 2. Either circuit is capable of powering the
Navigation Display.
The full-color display uses a rear-projection system driven by an active
matrix LCD display. The unit uses a halogen lamp as the singular
primary display projection light source. A separate dimming knob for
the display brightness is provided immediately below the display.
The HSI display shows heading and navigation information in a 360°
view similar to a conventional mechanical HSI, or in an EFIS 90° ARC
　
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