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Revision 2: 12-07-04
10 of 10 P/N 11934-S07
Section 9 Cirrus Design
Supplements SR20
and the pilot should manually trim the airplane in the direction
indicated. If the pilot fails to trim the airplane, the TRIM UP or TRIM
DN light, as applicable, will flash. Both light are out if the airplane is in
trim.
Flag Window – A red flag indicates insufficient electrical power (less
than 24 VDC) to the Turn Coordinator rate gyro. The turn coordinator
has its own backup power supply. Refer to basic Handbook.
GPSS and HDG mode selection for the GPSS converter is
accomplished through the GPSS/HDG switch located next to the
system annunciators on the instrument panel. Refer to Figure 1 for an
illustration of the switch.
HDG – When HDG is selected on the GPSS/HDG switch, the green
light below the HDG label will illuminate. In this mode, the autopilot is
coupled to the HSI heading error outputs and the autopilot will respond
to inputs made on the HSI heading (HDG) or course (OBS) controls.
GPSS – When GPSS is selected on the GPSS/HDG switch, the green
light above the GPSS label will illuminate. In this mode, the autopilot is
coupled to the GPS1 roll steering output and, if the autopilot is in
heading (HD) mode and GPS1 has a valid waypoint of flight plan
active, the system will automatically track to the next waypoint.
Revision 2: 12-07-04
P/N 11934-S08 1 of 16
Cirrus Design Section 9
SR20 Supplements
Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual
Supplement
for
S-Tec System 55 Autopilot
When the S-Tec System 55 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 adds to, supersedes, or
deletes information in the basic SR20 Pilot’s Operating Handbook.
• Note •
This POH Supplement Revision dated Revision 3: 07-18-05
supersedes and replaces Revision 2 of this supplement dated
12-07-04.
Revision 3: 07-18-05
2 of 16 P/N 11934-S08
Section 9 Cirrus Design
Supplements SR20
Section 1 - General
This airplane is equipped with an S-TEC System 55 Autopilot. The
System 55 autopilot 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 altitude hold through the
pitch trim motor and spring cartridge. The SR20 installation S-Tec
System 55 Autopilot features:
• Heading Hold and Command;
• NAV/LOC/GPS/GS tracking, high and low sensitivity, and
automatic 45° -course intercept;
• Altitude Hold and Command; and
• Vertical Speed Hold and Command.
Refer to S-Tec System 55 Pilot’s Operating Handbook (POH), P/N
8747 Rev B dated 03/99 or later revision for a full operational
procedures and description of implemented modes. The System 55
POH also contains detailed procedures for accomplishing GPS & VOR
course tracking, front course and back course localizer approaches,
and glideslope tracking.
• Note •
The SR20 implementation of the System 55 Autopilot does not
utilize the optional remote annunciator, optional Alt/VS
Preselect, roll servo, pitch servo, and optional trim servo.
Therefore, all references to these items in the S-Tec System
55 POH shall be disregarded. Additionally, this installation
does not utilize a CWS (Control Wheel Steering) switch or an
AUTOPILOT MASTER switch.
This installation utilizes the airplane’s pitch and roll trim
actuators to affect steering changes. Therefore, the automatic
trim function of the System 55 is not implemented. Disregard
all references in the S-Tec System 55 POH to this feature.
Revision 3: 07-18-05
P/N 11934-S08 3 of 16
Cirrus Design Section 9
SR20 Supplements
Roll information is displayed on the HSI. Autopilot Flight
Director is not implemented in this installation.
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 disengaged for missed approach, goaround,
and balked landing.
4. Flaps must be set to 50% for autopilot operation in Altitude Hold at
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