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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; HI and LO sensitivity.
• Altitude Hold and Command.
• Vertical Speed Hold and Command.
• GPS Steering (GPSS) for smoother turns onto a course or
during course tracking.
Refer to S-Tec System Fifty-Five SR Autopilot Pilot’s Operating
Handbook (POH), P/N 87127 dated 01 September 2003 or later
revision for full operational procedures and description of implemented
modes.
• Note •
The SR20 implementation of the System 55SR Autopilot does
not utilize the optional remote annunciator, roll servo, yaw
servo. Therefore, all references to these items in the S-Tec
System 55SR 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 roll trim actuator to
affect steering changes. Therefore, the automatic trim function
of the System 55SR is not implemented. Disregard all
references in the S-Tec System 55SR POH to this feature.
Roll information is displayed on the PFD. Autopilot Flight
Director is not implemented in this installation.
Revision 2: 07-18-05
P/N 11934-S27 3 of 16
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 disengaged for missed approach, goaround,
and balked landing.
4. Flaps must be set to 50% for autopilot operation in Altitude Hold at
airspeeds below 95 KIAS.
5. Flap deflection is limited to 50% during autopilot operations.
6. The autopilot must be disconnected in moderate or severe
turbulence.
7. Minimum engage height for the autopilot is 400 ft AGL.
8. Minimum speed with the autopilot engaged is 1.2Vs for the given
configuration.
9. For VOR/GPS and ILS glideslope and localizer intercept, capture,
and tracking, the following limitations apply:
a. The autopilot must be disengaged no later than 100 feet below
the Minimum Descent Altitude.
b. The autopilot must be disconnect during approach if course
deviation exceeds 50%. The approach should only be
continued by “hand-flying” the airplane.
c. The autopilot must be disengaged at the decision height.
d. 12 knot maximum crosswind component between the missed
approach point and outer marker.
e. The intercept of the localizer shall occur at least 5 miles
outside of the outer marker.
f. If the crosswind component is greater than 12 knots and less
than 17 knots, the intercept shall occur at least 10 miles
outside of the outer marker.
g. The intercept angle shall be no greater than a 45-degree
intercept.
h. The ILS is flown at normal approach speeds, and within any
STC or TC speed constraints and as defined in this flight
manual.
Revision 2: 07-18-05
4 of 16 P/N 11934-S27
Section 9 Cirrus Design
Supplements SR20
i. The flaps should be extended in the approach configuration
prior to the Outer Marker. No further changes in the flap
configuration should be made throughout the autopilotcoupled
approach.
10. The S-Tec System 55SR Autopilot Pilot’s Operating Handbook
(POH), P/N 87127 dated 01 September 2003 or later, must be
carried in the airplane and available to the pilot while in flight.
Revision 2: 07-18-05
P/N 11934-S27 5 of 16
Cirrus Design Section 9
SR20 Supplements
SR20_FM09_1996
HDG NAV APR REV ALT VS
S-TEC FIFTY FIVE SR
HDG NAV APR REV TRIM ALT GS VS +
R
D
Y
C
W
S
F
L
A
I
G
S
P
S
VS x 100
INCR
D ECR
Figure - 1
System Fifty-Five SR Autopilot
Revision 2: 07-18-05
6 of 16 P/N 11934-S27
Section 9 Cirrus Design
Supplements SR20
Section 3 - Emergency Procedures
Autopilot Malfunction
Refer to Electric Trim/Autopilot Failure procedure in the SR20 POH. Do
not reengage the autopilot until the malfunction has been identified
and corrected. The autopilot may be disconnected by:
1. Pressing the A/P DISC/Trim switch on the control yoke handle.
2. Pulling the AUTOPILOT circuit breaker on Essential Bus.
Altitude lost during a roll axis autopilot malfunction and recovery:
Altitude lost during a pitch axis autopilot malfunction and recovery:
　
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