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case as the primary turn and roll rate sensor. In addition to the turn
coordinator instrument, the roll axis computer receives signals from
the HSI and the #1 NAV/GPS radio. The roll computer computes roll
steering commands for turns, radio intercepts, and tracking. Roll axis
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Supplements SR22
steering is accomplished by autopilot steering commands to the
aileron trim motor and spring cartridge.
The pitch computer receives altitude data from the altitude encoder
pressure transducer plumbed into the static system, an accelerometer,
and glideslope information from the HSI and #1 NAV radio. Pitch axis
command for altitude hold, vertical speed hold, and glideslope tracking
is accomplished by pitch computer commands to the autopilot pitch
servo.
The altitude selector provides altitude and vertical speed pre-select
capability for the autopilot. A pre-programmed altitude and vertical
speed can be input into the altitude selector/alerter and then coupled
to the autopilot. The autopilot will then follow the selected vertical
speed until the selected altitude is reached. Then the altitude selector
will signal the autopilot to hold the selected altitude. The altitude
selector/alerter receives uncorrected altitude data from the same
altitude encoder used by the transponder. In addition to the preselect
functions, the altitude selector provides altitude alert, decision height,
and altitude readout.
28 VDC for autopilot and altitude selector/alerter is supplied through
the 5-amp AUTOPILOT circuit breaker on the Essential Bus.
All Autopilot mode selection is performed by using the mode select
buttons and VS knob on the autopilot programmer/computer in the
center console. Annunciators in the programmer/computer display
window annunciate modes. Refer to Figure 1 for an illustration of the
programmer/computer.
RDY (Ready)– Illuminates when autopilot is ready for engagement.
When the airplane’s Battery Master switch is turned on and the rate
gyro RPM is correct, the RDY annunciator will come on indicating the
autopilot is ready for the functional check and operation. The autopilot
cannot be engaged unless the RDY light is illuminated.
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Cirrus Design Section 9
SR22 Supplements
HDG (Heading) Mode – When HDG is selected, the autopilot will
engage the HDG mode, fly the airplane to, and hold the heading set on
the HSI. Subsequent heading changes are made using the HDG knob
on the HSI. For smoothest transition to HDG mode, it is recommended
that the airplane be aligned to within 10° of the selected heading
before engaging HDG. The HDG mode is also used in combination
with the NAV mode to set up a pilot selected intercept angle to a
course.
GPSS (GPS Steering) – Pressing NAV twice will cause the autopilot
to go to GPSS for smoother tracking and transitions. When GPSS is
selected, the autopilot can be switched between heading and GPSS
modes of operation. In the heading mode, the converter receives a
heading error signal from the heading bug on the Horizontal Situation
Indicator. GPSS converts this information and sends this heading error
directly to the autopilot.
In the GPSS mode, the converter receives ground speed and bank
angle digital signals that are calculated and converted to a
commanded turn rate. The turn rate is then scaled and converted to a
DC heading error signal that is compatible with the autopilot. The end
result is an autopilot that can be directly coupled to the roll steering
commands produced by the GPS Navigator, eliminating the need for
the pilot to make any further adjustments to the HSI course arrow.
REV (Reverse Course) – When REV is selected, the autopilot will
automatically execute high sensitivity gain for an approach where
tracking the front course outbound or tracking the back course inbound
is required. The APR and REV annunciators will illuminate when REV
is selected.
APR (Approach) – When APR is selected, the autopilot provides
increased sensitivity for VOR or GPS approaches. APR may also be
used to provide increased sensitivity for enroute course tracking.
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Supplements SR22
GS (Glideslope) – The autopilot GS function will capture and track an
ILS glideslope. To arm the GS function, the following conditions must
be met: (1) the NAV receiver must be tuned to the appropriate ILS
frequency; (2) The glideslope signal must be valid – no flag; (3) the
　
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