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clockwise for right turns. The compass dial should be set in agreement
with the magnetic compass just prior to takeoff. As the gyro will
precess slightly over a period of time, the directional gyro compass
dial should be readjusted occasionally on extended flights. 28 VDC for
lighting is supplied through the 2-amp INST LIGHTS circuit breaker on
Main Bus 1.
To adjust compass card:
1. Push and hold knob at lower left corner of instrument.
2. While holding knob in, rotate knob to adjust gyro compass dial
with current magnetic heading.
3. Release knob.
March 2010
7-30 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Course Deviation Indicator
• Note •
Serials 1337 and subsequent: The Course Deviation Indicator
is integrated into the PFD.
Avionics Configuration 2.0 and 2.1:
The Course Deviation Indicator (CDI) displays navigation information
from the GPS navigator. 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
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.
Avionics Configuration 2.2:
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.
March 2010
Information Manual 7-31
Cirrus Design Section 7
SR20 Airplane Description
Horizontal Situation Indicator
• Note •
Serials 1337 and subsequent: The Horizontal Situation
Indicator is integrated into the PFD.
Avionics Configuration 2.1:
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 PUSH-SET-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 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/PFD 1 circuit breaker on the Essential Bus and 5-amp
HSI/PFD 2 circuit breaker on Main Bus 2.
March 2010
7-32 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Avionics Configuration 2.2:
The Sandel SN3308 combines the functions of an HSI, an RMI, a full
color moving map, a Stormscope display, GPS annunciator, and 3-light
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西锐20飞机信息手册CIRRUS DESIGN SR20 AIRPLANE INFORMATION MA(60)
