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250XL front control panel located in the center console. The panel
includes function keys, power switches, MSG and Nav status
annunciators, LCD display, two concentric selector knobs, and a
Jeppesen NavData card slot in each panel. The GNC 250XL navigator
is powered by 28 VDC through the 7.5-amp COM2 circuit breaker on
the Avionics Non-Essential Bus.
The Jeppesen Navigation Database provides access to data on
Airports, Approaches, Standard Instrument Departures (SIDs),
Standard Terminal Arrivals (STARs), VORs, NDBs, Intersections,
Minimum Safe Altitudes, Controlled Airspace Advisories and
Frequencies. North American and International databases are
available. Database information is provided on a card that can be
inserted into the card slot on the GPS unit. Subscription information is
provided in a subscription packet provided with each system.
Original: 3-31-99
6 of 6 P/N 11934-S05
Section 9 Cirrus Design
Supplements SR20
Communication (COM) Transceiver
The GNC 250XL includes a digitally-tuned integrated VHF
communications (COM) transceiver. The transceiver and integrated
controls are mounted in the Garmin GNC 250XL unit and are
designated COM2. The transceiver receives all narrow- and wideband
VHF communication transmissions transmitted within a
frequency range of 118.000 MHz to 136.975 MHz in 25.0 kHz steps
(720 channels). The tuning controls are collocated with the NAV at the
right side of the GNC 250XL front panel. Frequency tuning is
accomplished by rotating the large and small concentric knobs to
select a standby frequency and then transferring the frequency to the
active window. The active frequency is always displayed at the upper
left corner of the GNC 250XL display. The standby frequency is
displayed below the active frequency in the map mode and to the right
of the active frequency in all other modes. Auto-tuning can be
accomplished by entering a frequency from a menu. The COM 2
antenna is located below the cabin on the airplane centerline. 28 VDC
for transceiver operating is controlled through the Avionics Master
Switch and supplied through the 7.5-amp COM2 circuit breaker on the
Avionics Non-Essential Bus.
Original: 3-31-99
P/N 11934-S06 1 of 8
Cirrus Design Section 9
SR20 Supplements
Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual
Supplement
for
S-Tec System Twenty Autopilot
When the S-Tec System Twenty Autopilot is installed in the Cirrus
Design SR20, this Supplement is applicable and must be inserted in
the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s
Operating Handbook. This document must be carried in the airplane at
all times. Information in this supplement either adds to, supersedes, or
deletes information in the basic SR20 Pilot’s Operating Handbook.
• Note •
This POH Supplement Revision dated 12-07-04 supersedes
and replaces the original issue of this supplement dated 03-
31-99.
Revision 1: 12-07-04
2 of 8 P/N 11934-S06
Section 9 Cirrus Design
Supplements SR20
Figure - 1
Section 1 - General
This airplane is equipped with an S-TEC System Twenty Autopilot.
This single-axis autopilot system is a rate-based system, deriving roll
axis control inputs from its integral electric turn coordinator. The
programmer, computer/amplifier, and annunciators are contained
entirely within the turn coordinator case. Pilot inputs to the autopilot
are made through the multi-function control knob at the upper left
corner of the turn coordinator. The control knob provides mode
selection, disengage, and turn command functions. The autopilot
drives the aileron trim motor and spring cartridge to control airplane
roll. The S-Tec System Twenty Autopilot features:
• Roll Stabilization.
• Turn Command.
• NAV/LOC/GPS tracking; HI and LO sensitivity.
L R
SR20_FM09_1052
N O P I T C H I N F O R M A TI O N
P US H/H OL D A P D IS C
LO HI
TURN COORDINATOR
2 MIN
UP
TRIM
RDY DN
ALT
ST HD TRK
L R
Turn Coordinator
Revision 1: 12-07-04
P/N 11934-S06 3 of 8
Cirrus Design Section 9
SR20 Supplements
Section 2 - Limitations
1. Autopilot operation is prohibited above 180 KIAS.
2. The autopilot must not be engaged for takeoff or landing.
3. The autopilot must be disconnected in moderate or severe
turbulence.
4. The autopilot must be disengaged no later than 100 feet below the
Minimum Descent Altitude.
5. Minimum engage height for the autopilot is 400 ft AGL.
6. Minimum speed with the autopilot engaged is 1.2Vs for the given
　
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