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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/PFD 1 circuit breaker on the Essential Bus and the 5-amp
HSI/PFD 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
view. This includes compass card, heading bug, course pointer,
course deviation bar, TO/FROM indicator, glideslope indicator, and
flags. Heading bug and course pointer settings include digital readouts
that make it easy to set precise headings and courses. One button
operation allows primary navigation to be selected from up to four
different sources: two VOR/ILS receivers and two GPS receivers.
Either GPS1 or NAV1 may be selected as primary navigation sources.
Up to two bearing pointers can be displayed and switched to any NAV
receiver including GPS1, GPS2, NAV1, or NAV2. GPS2 and NAV2 can
only be displayed as bearing pointers, not as a primary navigation
source. The display is color-coded to indicate which navigation source
is selected: green for NAV1, yellow for NAV2, and red for GPS.
Auto Slew automatically turns the course pointer in response to
waypoint sequencing or Direct-To navigation from the GPS receiver
eliminating manual course changes at waypoints and reducing pilot
workload.
Heading and Course Sync allows the pilot, with one button, to
automatically set the heading bug directly to his current heading, or to
set the course pointer directly to a VOR station, simultaneously
centering course deviation. Course and heading command outputs for
autopilot operations are also provided.
March 2010
Information Manual 7-33
Cirrus Design Section 7
SR20 Airplane Description
The SN3308 detects and warns of abnormal conditions such as
flagged navigation receivers and failed directional gyro or flux detector.
It also monitors its own internal temperature and provides warnings for
over-temperature or loss of cooling conditions.
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.
Magnetic Compass
A conventional, internally lighted, liquid filled, magnetic compass is
installed on the cabin headliner immediately above the windshield. A
compass correction card is installed with the compass.
March 2010
7-34 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Wing Flaps
The electrically controlled, single-slotted flaps provide low-speed lift
enhancement. Each flap is manufactured of aluminium and connected
to the wing structure at three hinge points. Rub strips are installed on
the top leading edge of each flap to prevent contact between the flap
and wing flap cove. The flaps are selectively set to three positions: 0%,
50% (16) and 100% (32) by operating the FLAP control switch. The
FLAP control switch positions the flaps through a motorized linear
actuator mechanically connected to both flaps by a torque tube.
Proximity switches in the actuator limit flap travel to the selected
position and provide position indication. The wing flaps and control
circuits are powered by 28 VDC through the 15-amp FLAPS circuit
breaker on the Non-Essential Bus.
Flap Control Switch
An airfoil-shaped FLAPS control switch is located at the bottom of the
vertical section of the center console. The control switch is marked
and has detents at three positions: UP (0%), 50% and 100% (Down).
The appropriate VFE speed is marked at the Flap 50% and 100%
switch positions. Setting the switch to the desired position will cause
the flaps to extend or retract to the appropriate setting. An indicator
light at each control switch position illuminates when the flaps reach
the selected position. The UP (0%) light is green and the 50% and
FULL (100%) lights are yellow.
March 2010
Information Manual 7-35
Cirrus Design Section 7
SR20 Airplane Description
SR20_FM07_1460
Figure 7-7
Wing Flaps
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西锐20飞机信息手册CIRRUS DESIGN SR20 AIRPLANE INFORMATION MA(61)
