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3. Heading Hold interfaced with DG or HSI coupled heading bug.
4. NAV/LOC/GPS tracking, HI and LO sensitivity.
5. Altitude Hold.
S-TEC System 55 / 55X Autopilot (Optional)
The optional S-TEC System 55 or 55X is a two-axis autopilot system.
The system consists of a flight guidance programmer/computer,
altitude transducer, turn coordinator, and HSI. Mode selection and
vertical speed selection is made on the programmer/computer panel.
A button on each control yoke handle may be used to disengage the
autopilot. The autopilot makes roll changes through the aileron trim
motor and spring cartridge and makes pitch changes for vertical speed
and altitude hold through the pitch trim motor and spring cartridge.
The autopilot operates on 28 vdc supplied through the 5-amp
AUTOPILOT circuit breaker on the Main Bus #1.
The SR20 installation S-TEC System 55 and 55X Autopilot features:
1. Heading Hold and Command.
2. NAV/LOC/GPS/GS tracking, high and low sensitivity, and
automatic 45° course intercept.
3. Altitude Hold and Command.
4. Vertical Speed Hold and Command.
• GPS Steering (GPSS) for smoother capture and tracking of
enroute or approach course (System 55X only).
March 2010
7-72 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
GPS Navigation
The airplane is equipped with two GPS navigators. The Garmin GNS
430 navigator is the primary system, is IFR certified, and is coupled to
the airplane's CDI and Multi-Function display. The Garmin GNC
250XL provides backup and is approved for VFR use only. GPS1
navigators are capable of providing IFR en route, terminal, and
approach navigation with position accuracies better than 15 meters.
GPS1 utilizes the Global Positioning System (GPS) satellite network to
derive the airplane's position (latitude, longitude, and altitude) and the
altitude digitizer to enhance the altitude calculation. The GPS1
antenna is located above the headliner along the airplane centerline.
The GPS2 antenna is located below the glareshield and behind the
ARNAV MFD. All GPS navigator controls and functions are accessible
through the GPS receiver units' front control panels located in the
center console. The panels include function keys, power switches,
MSG and Nav status annunciators, a color LCD display (GNS 430), a
monochromatic display (GNC 250XL), two concentric selector knobs
on each panel, and a Jeppesen NavData card slot in each panel. The
displays are daylight readable and automatically dimmed for low-light
operation. The GNS 430 navigator is powered by 28 VDC through the
5-amp GPS1 and 7.5-amp COM1 circuit breakers on the Avionics
Essential Bus. The GNC 250XL navigator is powered by 14 VDC
through a 28 to 14 VDC converter mounted under the center console.
28 VDC to power the voltage converter is supplied 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.
March 2010
Information Manual 7-73
Cirrus Design Section 7
SR20 Airplane Description
Communication (COM) Transceivers
Two VHF communications (COM) transceivers are installed to provide
VHF communication. The transceivers and integrated controls are
mounted in the Garmin GNS 430 and GNC 250XL units. The
transceivers receive all narrow- and wide-band VHF communication
transmissions transmitted within range of the selected frequency. The
antennas pick up the signals and route the communication signals to
the transceivers, which digitize the audible communication signal. The
digitized audio is then routed to the audio control unit for distribution to
the speakers or headphones.
COM 1 - The Garmin GNS 430 (upper unit) is designated COM 1. The
Garmin GNS 430 control panel provides COM 1 transceiver active and
standby frequency indication, frequency memory storage, and knoboperated
frequency selection. The COM 1 transceiver provides either
720-channel (25 kHz spacing) or 2280-channel (8.33 kHz spacing)
operation in a frequency range from 118.000 to 136.975 MHz. The
COM 1 antenna is located above the cabin on the airplane centerline.
28 VDC for COM 1 transceiver operation is controlled through the
　
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