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for full operational procedures and description of implemented modes.
The System 55X POH also contains detailed procedures for
accomplishing GPS & VOR course tracking, front course and back
course localizer approaches, and glideslope tracking.
March 2010
Information Manual 7-93
Cirrus Design Section 7
SR20 Airplane Description
Refer to S-Tec Altitude Selector / Alerter Pilot’s Operating Handbook
(POH) P/N 8716 or P/N 87110 (no revision or later) for full operational
procedures and detailed description of operational modes of the
Altitude Selector / Alerter.
Avionics Configuration PFD:
This airplane is equipped with an S-TEC System 55SR Autopilot. The
System 55SR autopilot is a two-axis autopilot system. The system
consists of a flight guidance programmer/computer, altitude
transducer, turn coordinator, and primary flight display (PFD). Mode
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 altitude hold through the
elevator trim motor. The autopilot operates on 28 VDC supplied
through the 5-amp AUTOPILOT circuit breaker on the Essential Bus.
The S-Tec System 55SR Autopilot features:
• Heading Hold and Command;
• NAV/LOC/GPS tracking;
• Altitude Hold and Command;
• GPS Steering (GPSS) for smoother turns onto a course or
during course tracking.
GPS Navigation
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.
Avionics Configuration 2.0 and PFD:
The airplane is equipped with two GPS navigators. The Garmin GNS
430 navigator is designated GPS 1, IFR certified, and is coupled to the
airplane’s CDI and Multi-Function display. The Garmin GNC 250XL
provides backup, is approved for VFR use only, and is not coupled to
the Multi-Function or Primary Flight Displays. The primary GPS
March 2010
7-94 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
navigator is powered by 28 VDC through the 5-amp GPS 1 and 7.5-
amp COM 1 circuit breakers on the Avionics Essential Bus. The
secondary GPS navigator is powered by 28 VDC through the 7.5-amp
COM 2 circuit breaker on the Avionics Non-Essential Bus.
Avionics Configuration 2.1 and 2.2:
The airplane is equipped with two GPS navigators. The Garmin GNS
430 is designated GPS 1 and the Garmin GNS 420 (Configuration 2.1)
or an additional GNS 430 (Configuration 2.2) is designated GPS 2.
Both Garmin GPS navigators are IFR certified. The primary unit,
designated GPS 1, is coupled to the airplane’s HSI, Autopilot, and
multifunction display. The secondary unit, designated GPS 2, is
coupled to the airplane’s CDI.
The GPS navigators are capable of providing IFR enroute, terminal,
and approach navigation with position accuracies better than 15
meters. Each GPS navigator utilizes the Global Positioning System
(GPS) satellite network to derive the airplane’s position (latitude,
longitude, and altitude) and the altitude encoder 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 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), 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
primary GPS navigator is powered by 28 VDC through the 5-amp GPS
1 and 7.5-amp COM 1 circuit breakers on the Avionics Essential Bus.
The secondary GPS navigator is powered by 28 VDC through the 5-
amp GPS 2 and the 7.5-amp COM 2 circuit breaker on the Avionics
Non-Essential Bus.
Avionics Configuration SRV:
Optional SRV configuration: An optional Garmin GNS 430 GPS
transceiver is available as an upgrade to the Garmin GNS 420. The
　
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