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wheel trim switch input will result in immediate autopilot disengagement.
The yaw damper and flight director modes are not affected by manual
pitch or roll trim commands. Actuation of the control wheel trim switch
without pressing the arm switch allows manual autopilot commands.
During autopilot engagement, basic attitude commands (pitch and roll)
can be entered through either the pilot’s or copilot’s control wheel trim
switch (dependent upon which flight director is coupled to the autopilot).
With the autopilot engaged, activation of the control wheel trim
switch (without arm switch depressed), on the side coupled to the
autopilot, causes the flight director roll and/or pitch hold mode to be
activated.
Control Wheel Master Switch (MSW)
The MSW switch immediately disconnects all autopilot and yaw
damper servo drives. The selected flight director modes are not affected.
In normal operation, a 28-vdc signal is routed through the normally
closed contacts of each MSW and then to the onside IC-600. This input
to the IC-600s is the autopilot disengage discrete, and if 28-vdc is removed
from this discrete on either IC-600, the autopilot will disengage.
Pilot’s Manual
PM-132A 5-71
Touch Control Steering (TCS)
TCS allows the pilot to manually fly and retrim the aircraft without disengaging
the autopilot. To use the TCS function, the pilot will press the
TCS button on the control wheel, maneuver the aircraft to the desired
condition, and release the TCS. Operation of the TCS button has no effect
on flight director mode of operation. While the TCS button is held
depressed (AP engaged), a white TCS ENG annunciator appears in the
autopilot display area at the top of the PFDs.
Autopilot Engagement/Disengagement
Engagement of the autopilot is achieved via the AP push button on the
FGC. Each button has a vertical green bar that illuminates when engaged.
Engagement of the autopilot will cause the yaw damper to automatically
engage. When engaged, the autopilot will couple to the
master flight director, and will follow the guidance commands from the
master FD. If no flight director is active, engagement of the autopilot
will cause the master FD to default to the basic PIT and ROL modes.
When engaged, the appropriate annunciation will be provided on both
PFDs, and the green bar on the AP push button will be illuminated.
Disengagement of the autopilot via the AP switch will cause the AP
annunciation to be removed from both PFDs and the green bar on the
AP push button will extinguish. Other actions that will cause autopilot
disengagement include:
(1) Control wheel master switch activation.
(2) Pilot initiated trim commands with control wheel trim
switch depressed.
(3) Yaw damper disengagement.
(4) AP switch on the FGC disengaged.
(5) Autopilot primary or secondary monitor trip.
For a normal disconnect, AP flashes red for 5 seconds, then is removed.
For a monitored disconnect, it flashes red for 5 seconds, then steady,
and the aural alert is continuous until the crew cancels it with the MSW.
Pilot’s Manual
5-72 PM-132A
Yaw Damper Engagement/Disengagement
Selection of the autopilot via the AP push button will automatically engage
the yaw damper. Alternatively, the yaw damper may be selected
via the YD push button on the FGC. When engaged, the green YD annunciation
will be provided on both PFDs, and the green bar on the YD
push button will illuminate. Manual disengagement of the yaw damper
via the YD button will cause the YD annunciation to flash amber then
be removed from both PFDs and the green bar on the YD push button
will extinguish. In the case of a monitored disconnect, the YD annunciation
will turn amber and flash for five seconds and then remain steady.
Other actions that will disengage yaw damper include:
(1) Control wheel master switch activation.
(2) YD switch on the FGC disengaged.
(3) Yaw damper monitor trip.
Mistrim Annunciation
When the autopilot is engaged and the roll or pitch servo remains energized
for a longer than normal period, this condition will be annunciated
with a CAS. The autopilot does not have a capability to trim in
the roll axis; therefore, if there is a mistrim in the roll axis, this will also
display a CAS.
The following CAS illuminations are specific to the autopilot:
Power Supply Configuration
The power supply for all the AFCS servos is supplied from the L MAIN
bus, and is routed through the #2 IC-600 to the servos. The system is designed
so that power failure to any major component in the system will
result in the system reverting to the safe, disconnect mode. The AFCS
　
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