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Elevator Control System Operation
The pilot and copilots pitch controls are interconnected through a disconnect
mechanism which is designed to operate when a design torque is developed across the
mechanism.
GX_10_016
Control
Column
Tension
Regulator
Pitch Disconnect
Mechanism
Stick-pusher
Actuator
Cables
Aft Quadrants
Pitch Feel
Units
Load
Limiters
Elevator
Surface
Power Control
Unit (PCU)
Gain Changer
Mechanism
Autopilot Pitch Servo
(Right Aft Quadrant)
For Training Purposes Only
Sept 04
10-19
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
NOTE
The autopilot should be disconnected if a jammed elevator
control circuit condition occurs.
A jammed elevator control circuit can be isolated through 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 circuit travels 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 pitch disconnect system to disconnect the control columns.
NOTE
Overpowering the servo to disconnect the autopilot is not
recommended.
Two electrical actuators positioned at the pitch feel units 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 position 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
CONTROL page. Separate pointers indicate the left and right elevator surface
positions.
ELEV
RUDDER
ELEV
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.
Surface Outline
The surface outline has no
movement but will change
color (green or amber)
based on hydraulic pressure
availability.
,
GX_10_017
Scale
Indicates the full range available
for elevator up and down travel.
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-20 For Training Purposes Only
Sept 04
Elevator Control Schematic
AIL
ELEV
RUDDER
AIL
ELEV
PITCH DISC
GX_10_018
LEGEND
ELECTRICAL INPUT
MECHANICAL INPUT
CABLE INPUT
STICK
SHAKER
STICK
PUSHER
STALL
PROTECTION
SYSTEM
Pitch Feel
Unit
Autopilot
Servo
Commands
Horizontal
Stabilizer
Elevators Power Control
Unit
FLIGHT CONTROL SYNOPTIC PAGE
NOSEDN
NOSEUP
DISC
MASTER
TCS
MIC
NOSEDN
NOSEUP
DISC
MASTER
TCS
MIC
STICK
SHAKER
For Training Purposes Only
Sept 04
10-21
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
SECONDARY FLIGHT CONTROLS
HORIZONTAL STABILIZER
The stabilizer trim control system provides pitch trim by varying the angle of
incidence of the horizontal stabilizer. The system consists of two Flight Control Units
(FCUs), dual channel Motor Drive Unit (MDU) and a dual electric channel trim
actuator which drives a screw jack assembly to position the horizontal stabilizer.
Activation of the horizontal stabilizer trim can occur through manual trim, auto trim
and mach trim.
The pilot’s controls consist of switches on each control column and the stabilizer trim
control panel. Pilot trim commands have priority and will override copilot trim
command inputs. The horizontal stabilizer can be trimmed from 2° (0 units on EICAS)
airplane nose down to 12° (14 units on EICAS) nose up.
The FCUs are responsible for the monitoring of the trim system. They have their own
dedicated interfaces with other airplane systems and with pilot/copilot controls to
perform trim control and monitoring. The horizontal stabilizer system provides two
　
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