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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
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−17
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
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−18
STABILIZER TRIM
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.
The pilot controls consist of switches on each control column and one horizontal stabilizer trim panel.
Pilot trim commands have priority and will override copilot trim command inputs. The horizontal
stabilizer can be trimmed from 2 degrees (0 units on EICAS) airplane nose down to 12 degrees (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 redundant channels in an active/standby
basis such that full performance requirements can be met with either channel.
Pitch Trim Input
The FCUs receive inputs from the following systems:
· Integrated Avionic Computer (IACs).
· Air Data Computer (ADCs).
· Automatic Flight Control System (AFCS).
· STAB switches.
· Pitch trim and disconnect switches.
For manual stabilizer trim control, the FCUs receive commands from the pilot and copilot trim
switches. To perform the Mach trim function, the FCUs receive the airplane mach number from
three ADCs. Two IACs which comprise the AFCS function provide stabilizer trim command when
the autopilot is engaged. The ADCs provide mach data used for mach trim and rate scheduling.
The FCUs in turn command the MDUs to drive the motors of the horizontal stabilizer trim
actuators. The FCUs monitor the results of the command inputs to ensure correct control trim rate
and direction is achieved.
The Stab trim switches on the STAB control panel send signals to the FCUs for engagement and
disconnect. These switches also send a signal direct to the MDU to ensure disconnect of the
applicable trim actuator.
Stabilizer Actuator Assembly
Refer to Pitch Trim Schematic
The actuator assembly positions the surface in response to electrical signals from the MDU. The
stabilizer is positioned by a jack screw driven by electric trim motors within the actuator assembly.
The actuator assembly has brakes which provide a secondary means of preventing creeping in
flight under aerodynamic loads. A sensor mounted on each motor sends signals to the MDU to
determine each motor position.
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−19
STABILIZER TRIM (CONT'D)
Pitch Trim Schematic
FCU 1
ADC 1 (BUS 1)
ADC 2 (BUS 1)
ADC 3 (BUS 1)
FCU 2
ADC 1 (BUS 2)
ADC 2 (BUS 2)
ADC 3 (BUS 2)
MODULE 1 A MODULE 1 B MODULE 2B MODULE 2A
MOTOR CONTROL
AND MONITORING
MOTOR CONTROL
AND MONITORING
MOTOR
CHANNEL 2
TRIM
Sensor
Sensor
AND
BRAKE
MOTOR
AND
BRAKE
ACTUATOR
CHANNEL 1
PILOT TRIM AND
DISCONNECT
SWITCHES
COPILOT TRIM AND
DISCONNECT
SWITCHES
to FCU 2
to FCU 1
IAC −2
(AUTOPILOT)
IAC −1
(AUTOPILOT)
MOTOR
DRIVE
UNIT
GF1010_022
STAB
CH1 CH2
PUSH OFF/RESET
OFF OFF
FLIGHT CONTROLS
　
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