P/N 13772-140 21 of 24
Cirrus Design Section 9
SR22 / SR22T Supplements
Altitude Transducer
The altitude transducer, installed behind the bolster panel and
plumbing directly into the Pitot Static system provides altitude
information to the Programmer/Computer.
#2 Integrated Avionics Units
The #2 Integrated Avionics Unit located behind the MFD and
instrument panel, functions as the main communication hub to the
Avionics System and Programmer / Computer, linking the systems to
the PFD and MFD displays. The Integrated Avionics Unit receives air
and attitude data parameters from the Air Data Computer and Attitude
and Heading Reference System. The Integrated Avionics Unit
contains a GPS WAAS receiver, VHF COM/NAV/GS receivers, and
system integration microprocessors.
28 VDC for #2 Integrated Avionics Unit operation is supplied through
the 7.5-amp COM 2 and 5-amp GPS NAV GIA2 circuit breakers on the
MAIN BUS 2.
Pitch Servo
The Pitch Servo, located below the baggage compartment position the
aircraft flight controls in response to commands generated by the
Programmer/Computer autopilot calculations.
28 VDC for Pitch Servo operation is supplied through the 5-amp
KEYPADS/AP CTRL circuit breaker on MAIN BUS 1.
Roll and Pitch Trim Cartridges
Roll and pitch trim is provided by adjusting the neutral position of the
compression spring cartridge in the elevator control system by means
of an electric motor. For detailed description of the Trim Cartridges
refer to the basic POH.
Electric Pitch/Roll-Trim Hat Switch
The yoke mounted Electric Pitch Trim and Roll Trim Hat Switch allows
the pilot to manually adjust aircraft trim when the autopilot is not
engaged. For detailed description of the Electric Pitch/Roll-Trim Hat
Switch refer to the basic POH.
Autopilot Disconnect Switch
Revision 01: 01-06-10
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