BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual page 398

Operation
Movement of either set of rudder pedals me-
chanically positions the control valves on all
three rudder PCUs. Pressure from hydraulic
systems No. 1, No. 2, and No. 3 is directed
to the PCUs. As the rudder is deflected, a
followup linkage repositions the control
valves to neutral, stopping and holding the
rudder in the position commanded by pedal
movement. Rudder position is constantly dis-
played on the flight SURFACE position in-
dicator (see Figure 15-5).
If a control valve on any rudder PCU jams, or
if there is a hydraulic deficiency, the amber
YAW light on the servo monitor panel will il-
luminate, along with the FLT CONT annunci-
ator and the MASTER CAUTION lights.
Yaw damping is covered under AFCS Operation,
Chapter 16, "Avionics."
Rudder trim is provided by small PCU dis-
placements. Movement of the RUD TRIM ro-
tary switch (Figure 15-4) energizes an electrical
trim actuator. The actuator drives the system
control linkage to reposition the control valves
on the rudder PCUs. PCU actuation then deflects
the surface as required. The amount of trim ap-
plied is shown on the TRIM position indicator.
15-8 CL 601-3A/R
CL-600-2B16 PILOT TRAINING MANUAL
PITCH CONTROL SYSTEM
General
Two independent, hydraulically powered el-
evators, mechanically controlled by control
column fore and aft movement, provide pitch
control. Each elevator is powered by two
PCUs. Elevator travel is limited by PCU travel
and mechanical stops on the control columns.
Load feel is provided by an artificial feel unit.
A damper connected to each elevator prevents
surface flutter.
Loss of one hydraulic system powering the ele-
vator PCUs will not degrade control authority.
The elevator control system has dual control
linkages. Movement of either control column
actuates both sets of linkages to position the
control valves of all four elevator PCUs. If jam-
ming occurs in either set of mechanical link-
ages, pulling the PITCH DISCONNECT
handle on the center pedestal mechanically
disconnects the two sets of linkages (Figure
15-9), allowing control of one elevator through
the linkage that is free.
Autopilot servo control inputs are applied to
the left linkage system. Therefore, if the left
system is jammed, autopilot inputs to the
elevator system are not possible.
Figure 15-9. Pitch Disconnect
FOR TRAINING PURPOSES ONLY
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