Pfd Displays - Beechcraft Baron G58 Pilot Operating Handbook

Section 7
Systems Description
6. Servos with autopilot processing logic in the pitch, pitch
trim and roll control systems. A servo with independent
processing logic for the Yaw Damper function. The ser-
vos are powered by the Right Bus through the Avionics
Master relay and are protected by a 5-amp AP SERVOS
circuit breaker located on the Avionics Circuit Breaker
Panel. (The pitch trim servo is used for automatic pitch
trim when the autopilot is engaged and for manual elec-
tric pitch trim operation when the autopilot is disen-
gaged.)
7. Servo mounts and brackets
8. Flight Director processing logic is contained in the two
integrated Avionics Units, GIA 63/63W No. 1 and No. 2.
The GIAs are protected by the 5-amp INTEG AVION 1
and INTEG AVION 2 circuit breakers located on the Avi-
onics circuit breaker panel. Both GIAs are required to be
operational for the AFCS to operate.
9. The AFCS also utilizes the PFD/MFD mounted altitude
preselect knob (ALT), heading select knob (HDG), and
course select knob (CRS) associated with the G1000
system.

PFD DISPLAYS

1. A Flight Director command bar is displayed on the artifi-
cial horizon when the Flight Director is active.
2. The status of the autopilot, yaw damper, and flight direc-
tor modes are displayed on the PFD in an AFCS Status
Bar which is displayed just above the Attitude Indicator.
In general, green indicates an active flight director mode
and white indicates an armed mode. When a mode is
directly selected by the pilot, no flashing of the mode will
occur. When normal automatic mode changes occur, the
new mode will flash in green for ten seconds. If a mode
becomes unavailable for whatever reason, the mode will
flash in yellow for ten seconds and then be replaced by
the new active mode in green.
7-76
Model G58
May, 2015