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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, and
• 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 MDU 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.
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-22 For Training Purposes Only
Sept 04
Stabilizer Actuator Assembly
Please 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.
For Training Purposes Only
Sept 04
10-23
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
Pitch Trim Schematic
NL NR
CH1 CH2
STAB
RUD
PUSH OFF/RESET
AIL
TRIMS
R
W
D
L
W
D
OFF OFF
GX_10_017
NOSEDN
NOSE UP
DISC
MASTER
TCS
MIC
NOSEDN
NOSEUP
DISC
MASTER
TCS
MIC
FCU 1
TO
FCU 1
FCU 2
TO
FCU 2
CHANNEL 1 CHANNEL 2
PIVOT POINT
SENSOR SENSOR
MOTOR
AND
BRAKE
MOTOR
AND
BRAKE
115 VAC 1 115 VAC
ESS
MOTOR CONTROL
AND MONITORING
MOTOR CONTROL
AND MONITORING
MODULE
1A
MODULE
1B
MODULE
2B
MODULE
2A
PILOT TRIM &
DISCONNECT SWITCHES
COPILOT TRIM &
DISCONNECT SWITCHES
IAC 1
(AUTOPILOT)
MOTOR
DRIVE
UNIT
IAC 2
(AUTOPILOT)
ADC 1 (BUS 1)
ADC 2 (BUS 1)
ADC 3 (BUS 1)
ADC 1 (BUS 2)
ADC 2 (BUS 2)
ADC 3 (BUS 2)
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-24 For Training Purposes Only
Sept 04
Stabilizer Trim Control Switches
The STAB trim control switches are located on the flight control trim panel (center
pedestal). For normal operations, both switches are normally released (not pushed in)
and remain dark. A white OFF legend is displayed only when the switch is selected.
This action will disconnect the channel from the trim system, and will remain
disconnected as long as the switch has been selected.
Failure monitoring within the FCUs provides automatic failure detection and transfer
to the opposite channel. Disabling of the failed channel will also automatically occur.
PITCH TRIM MODES OF OPERATION
The pitch trim operating priorities are shown in the table below:
PRIORITY MODE
1 MANUAL TRIM COMMAND - PILOT SWITCHES
2 MANUAL TRIM COMMAND - COPILOT SWITCHES
3 AUTOMATIC TRIM - AUTOPILOT (A/P 1 or 2)
4 MACH TRIM - AVAILABLE ONLY IF A/P OFF
NL NR
CH1 CH2
STAB
RUD
PUSH OFF/RESET
AIL
TRIMS
R
W
D
L
W
D
OFF OFF
GX_10_020
STAB Switches
Used to disconnect each channel of the
trim system or reset certain latched
transient faults.
Selecting the switch will disengage the
pitch trim channel and the “OFF” light
will illuminate.
For Training Purposes Only
Sept 04
10-25
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
Manual Pitch Trim
The horizontal stabilizer trim is commanded through trim switches located on the pilot
and copilot control columns. The switches command airplane nose up or nose down
movement of the actuator with a controlled trim rate, dependent on the airplane Mach
　
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