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CSP 700−6
Volume 2
10−10−14
ELEVATOR CONTROL
Longitudinal control is provided by elevators operating in relation to control column displacement and
supplemented by a moveable horizontal stabilizer for maintaining longitudinal (pitch) trim. Pilot inputs
to the elevator circuit are from the dual control columns which are normally connected through an
automatic disconnect mechanism.
Elevator Control General Arrangement
FORWARD QUADRANT
AUTO−DISCONNECT
MECHANISM
STICK−PUSHER
ACTUATOR
CABLES
AUTOPILOT
PITCH SERVO
POWER
CONTROL
UNIT (PCU)
ELEVATOR
SURFACE
PITCH
FEEL UNITS
AFT QUADRANT
CONTROL
COLUMN
GF1010_018
Elevator Control System
Two separate pitch control systems are provided: the pilot’s side operates the lefthand
elevator
and the copilot’s side operates the righthand
elevator. Normally, both control systems are
interconnected through a torque tube assembly and there is simultaneous movement of both
elevators.
Elevator Control System Operation
The pilot and copilot pitch controls are interconnected through a pitch disconnect mechanism used
to maintain the control wheels connected, until a design torque is developed across the
mechanism.
NOTE
The AFCS (autopilot) should be disconnected if a jammed elevator
control circuit condition occurs.
FLIGHT CONTROLS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
10−10−15
ELEVATOR CONTROL (CONT'D)
Elevator Control System Operation (Cont’d)
A jammed elevator control circuit can be isolated through automatic activation of the pitch
disconnect mechanism. This procedure will allow limited pitch control using one elevator through
the operable control circuit.
A control rod located at the base of each column transmits pilot command to the left and right
forward quadrants. The left forward quadrant includes a cable interface with the stick pusher servo
of the stall protection system.
The cable circuits travel independently from the forward quadrant to the aft quadrant located in the
vertical stabilizer. A separate cable circuit is provided for the autopilot servo motor assembly which
inputs the right aft quadrant.
Disconnecting the autopilot by the pilot overpowering the pitch servo will not cause the auto pitch
disconnect system to separate the control columns.
NOTE
Overpowering the servo to disconnect the autopilot is not
recommended.
Two electrical actuators positioned at the pitch feel simulator provides input to the aft quadrant for
force feel requirements. The actuators receive command input from the FCUs based on airspeed
and horizontal trim position.
The aft quadrants drive a series of control rods and levers which input a torque tube assembly to
positions the hydraulic PCUs. Two PCUs are used for each elevator.
Elevator Surface Position Indication
Left and right elevator positions are displayed by a moving pointer on the FLIGHT CONTROLS
page on EICAS. Separate pointers indicate the left and right elevator surface positions.
Scale Pointer
Unfilled triangle moves
vertically to indicate the
range of travel.
The surface position
pointer will change color
(green or amber) based
on hydraulic pressure
availability.
Scale
Indicates the full range available
for elevator up and down travel.
Surface Outline
The surface outline has no
movement. It will change
color (magenta, green or
amber) based on electrical
power (ie: battery only or all
busses powered), and
hydraulic pressure availability.
GF1010_019
ELEV
RUDDER
ELEV
SCALE LONG TICK MARKS SHORT TICK MARKS
Left side −22.5° (top)
+17.5° (bottom)
at top and bottom at 0°
Right side −22.5° (top)
+17.5° (bottom)
at top and bottom at 0°
FLIGHT CONTROLS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
10−10−16
ELEVATOR CONTROL (CONT'D)
Elevator Control Schematic
AUTOPILOT SERVO
COMMANDS
ELEVATORS
PITCH
DISC
STICK
SHAKER
STALL
PROTECTION
SYSTEM
STICK
PUSHER
PITCH FEEL UNIT
FLIGHT CONTROL
SYNOPTIC PAGE
POWER CONTROL
UNIT
HORIZONTAL STABILIZER
STICK
SHAKER
LEGEND
Electrical input
Cable input
Mechanical input
RUDDER
ELEV ELEV
GF1010_021
FLIGHT CONTROLS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
　
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