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DISCONNECT handle can be reset at any time, locking the two control circuits together again.
Aileron Power Control Unit Protection
If a PCU is malfunctioning, a failure detection will cause the EICAS to display a PCU valve jam
symbol on the flight controls synoptic page (an amber half-circle above the aileron outline), and
an amber AILERON PCU caution EICAS message to appear. Two sets of shear rivets on each
aileron PCU provide additional protection against internal PCU linkage jams. If the linkage to
one cylinder jams, the pilot can overpower the jammed condition, which will shear the rivets on
that side and allow the other cylinder to operate the aileron.
Flutter Damper
A flutter damper is installed on each aileron. This prevents control surface flutter in flight in the
event of a complete loss of hydraulic fluid at the PCU. A breakaway link provides jam
protection in the case of flutter damper seizure.
Elevators
Longitudinal (pitch) control is provided by elevators, and supplemented by a movable horizontal
stabilizer. Two separate control paths are provided through the pilot’s and copilot’s control
columns. The pilot’s control column controls the left elevator and the copilot’s control column
controls the right elevator. Movement of both pilot’s and copilot’s controls is simultaneous when
the systems are interconnected (normal operation). Moving either control column activates, via
cables and pulleys, the PCUs (hydraulic actuators) for the elevators. Two actuators are used for
each elevator. The left elevator PCUs use hydraulic pressure from systems 1 and 3, and the
right PCUs use systems 2 and 3.
A position transmitter linked to each elevator provides visual indication of the elevator deflection
on the EICAS FLIGHT CONTROLS synoptic page. If a differential of greater than 5° between
each elevator position exists, an ELEVATOR SPLIT caution EICAS message will appear.
Within the elevator control mechanism, a stick shaker and a stick pusher system can be
activated via the stall protection system (SPS). The SPS is covered later in this chapter .
Pitch Disconnect
In the event of a control cable jam or elevator system malfunction, the left and right elevator
control circuits can be isolated by pulling the PITCH DISC handle on the center pedestal. This
provides reduced pitch authority through the one elevator on the operable circuit. The PITCH
DISC handle can be reset at any time, locking the two circuits together again.
Elevator PCU Protection
An elevator PCU jam or failure can be overcome by integrated jam-tolerant input rods. These
rods collapse or expand in the event of both PCUs on one side having no hydraulic pressure,
and enable operation of the opposite side elevator. If one of the pair of on-side PCU control
valves jams, the jam-tolerant input rod will allow operation of the adjacent PCU control valve.
FLIGHT CONTROLS
Description
Vol. 2 10−10−4
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
PRIMARY FLIGHT CONTROLS (CONT'D)
Flutter Damper
Two flutter dampers are installed on each elevator. These are identical in design and function
to those installed on the ailerons.
FLIGHT CONTROLS
Description
Vol. 2 10−10−5
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
PRIMARY FLIGHT CONTROLS (CONT'D)
Pitch Control − Schematic
Figure 10−10−3
FLIGHT CONTROLS
Description
Vol. 2 10−10−6
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
PRIMARY FLIGHT CONTROLS (CONT'D)
Rudder
Yaw control is provided by a hydraulic actuated rudder, hinged on the rear spar of the vertical
stabilizer. Two separate mechanical control paths are provided from the rudder pedals to three
independent PCUs. Each PCU is powered by a separate hydraulic system. A position
transmitter provides visual indication of rudder deflection on the EICAS flight control synoptic
page.
Both rudder pedal control systems have an anti-jam breakout mechanism. In the event of a
jammed rudder control on one side, both pilot and copilot rudder pedals are capable of
operating the remaining control system. Additional force on the rudder pedals is required to
bypass the inoperative side, allowing rudder operation.
A two-channel yaw damper system is installed, and supplies small rudder corrections in
response to reference signals from the IRUs through the FCCs. This is considered a function of
the automatic flight control system (AFCS). Refer to Chapter 4, Automatic Flight Control
System, for additional information.
FLIGHT CONTROLS
　
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