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select are also provided.
28 VDC for Flight Management System Keyboard operation is
supplied through the 5-amp KEYPADS / AP CTRL circuit breaker on
MAIN BUS 1.
HDG - Heading Knob.
The HDG knob controls the selected heading bug on the HSI portion
of the PFD. It provides the reference for heading select mode. Pushing
the HDG knob synchronizes the selected heading to the current
heading.
CRS - Course Knob
The CRS knob controls the course pointer on the HSI portion of the
PFD. Pushing the CRS knob re-centers the CDI and returns the
course pointer to the bearing of the active waypoint or navigation
station.
ALT SEL - Altitude Select Knob
Mode Step Value Range
Altitude Hold (ALT) 20 Feet +/- 360 Feet*
Vertical speed (VS) 100 Feet per Minute +/- 1600 Feet per Minute
Original Issue: 12-18-08
P/N 11934-S40 17 of 20
Cirrus Design Section 9
SR20 Supplements
The ALT knob controls the Selected Altitude, which is used as the
reference for the altitude alerter and the altitude capture function.
Pushing the ALT SEL knob synchronizes the selected altitude to the
displayed altitude to the nearest 10 ft.
Turn Coordinator
The electric turn coordinator, installed behind the RH bolster panel,
provides roll data to the Programmer/Computer. Roll rate is sensed by
a single-gimbal, electric-powered gyro.
28 VDC for Turn Coordinator operation is supplied through the 5-amp
KEYPADS / AP CTRL circuit breaker on MAIN BUS 1.
Altitude Transducer
The altitude transducer, installed behind the bolster panel and
plumbing directly into the Pitot Static system provides altitude
information to the Programmer/Computer.
#2 Integrated Avionics Units
The #2 Integrated Avionics Unit located behind the MFD and
instrument panel, functions as the main communication hub to the
Avionics System and Programmer / Computer, linking the systems to
the PFD and MFD displays. The Integrated Avionics Unit receives air
and attitude data parameters from the Air Data Computer and Attitude
and Heading Reference System. The Integrated Avionics Unit
contains a GPS WAAS receiver, VHF COM/NAV/GS receivers, and
system integration microprocessors.
28 VDC for #2 Integrated Avionics Unit operation is supplied through
the 7.5-amp COM 2 and 5-amp GPS NAV GIA2 circuit breakers on the
MAIN BUS 2.
Original Issue: 12-18-08
18 of 20 P/N 11934-S40
Section 9 Cirrus Design
Supplements SR20
Figure - 2
HDG NAV APR REV ALT VS
S-TEC FIFTY FIVE SR
HDG NAV APR REV TRIM ALT VS + R
D
Y
C
W
S
F
L
A
I
G
S
P
S
VS x 100
IN C R
D E C R
4
3
Flight Management System Keyboard
System 55SR Autopilot
RANGE
PUSH
- +
PAN
HDG
CRS
ALT SEL
GARMIN
A B C D E F
G H I J K
L M N O P Q
R
W
S
X
T
Y
U
Z
V
SPC BKSP
1 2 3
4 5 6
7 8 9
0 +/-
CRSR/1-2 EMERG
PUSH
FMS/XPDR
COM/NAV
IDENT
DFLT MAP
PUSH SYNC
PUSH CTR
PUSH SYNC
D
FPL
CLR
MENU
PROC
ENT
FMS XPDR
COM NAV
Legend
1. Heading Selection
2. Course Selection
3. Altitude Selection
4. Heading Select Mode
5. Navigation Mode
6. Approach Mode
7. Reverse Course Mode
8. Altitude Hold
9. Vertical Speed Mode
10. VS Modifier Knob
1
2
SR20_FM09_3020
5 6 7 8 9 10
System Fifty Five SR Autopilot
Original Issue: 12-18-08
P/N 11934-S40 19 of 20
Cirrus Design Section 9
SR20 Supplements
Pitch Servo
The Pitch Servo, located below the baggage compartment position the
aircraft flight controls in response to commands generated by the
Programmer/Computer autopilot calculations.
28 VDC for Pitch Servo operation is supplied through the 5-amp
KEYPADS/AP CTRL circuit breaker on MAIN BUS 1.
Roll and Pitch Trim Cartridges
Roll and pitch trim is provided by adjusting the neutral position of the
compression spring cartridge in the elevator control system by means
of an electric motor. For detailed description of the Trim Cartridges
refer to the basic POH.
Electric Pitch/Roll-Trim Hat Switch
The yoke mounted Electric Pitch Trim and Roll Trim Hat Switch allows
the pilot to manually adjust aircraft trim when the autopilot is not
engaged. For detailed description of the Electric Pitch/Roll-Trim Hat
Switch refer to the basic POH.
Autopilot Disconnect Switch
The yoke mounted Autopilot Disconnect Switch disengages the
　
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