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stabilizer. The Horizontal Stabilizer Trim Control Unit (HSTCU) commands the
actuation of the stabilizer leading edge with a jackscrew driven by two electric motors
through a range of 0° to -9° at specific rates of movement. The HSTCU receives
inputs from the pilot’s and copilot’s control wheel pitch trim switches, the autopilot,
and the Mach Trim System. The HSTCU has two channels that are engaged by the
CH 1 and CH 2 switch/lights on the STAB TRIM panel on the center pedestal.
Normally, with both channels engaged, CH 1 is in command with CH 2 in standby.
Operation of the horizontal stabilizer is continuously monitored by the HSTCU. In the
event of a single-channel failure, the STAB CH 1(2) INOP status EICAS message will
appear, and the remaining channel will provide control. If both channels fail, the
STAB TRIM caution EICAS message appears, and stabilizer trim becomes
inoperative.
Horizontal stabilizer trim position is displayed on the EICAS primary page and the
FLIGHT CONTROLS synoptic page. The normal trim setting for takeoff (-3 to -6
degrees) is depicted on the indicator as a green band.
If stabilizer trim is not set in this range with the aircraft in the takeoff mode, a
CONFIG STAB warning EICAS message will be displayed, and an aural “CONFIG
TRIM” will sound.
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-11
P I LOT T R A I N I N G GU I D E
Stab Trim Panel
Figure 10-5
Stab Trim Indications
Figure 10-6
Horizontal Stabilizer Trim Priority
The stabilizer trim can be operated manually with the pilot’s and copilot’s control
wheel pitch trim switches or automatically with the autopilot or the Mach Trim
system. The order of priority and rate of movement are as follows:
1. Pilot Manual Trim - The pilot’s control wheel pitch trim switch is highest in the
order of priority. The stabilizer rate of movement is 0.5°/sec.
2. Copilot Manual Trim - The copilot’s control wheel pitch trim switch is next
highest in the order of priority. The stabilizer rate of movement is 0.5°/sec.
3. Autopilot Trim - The stabilizer rate of movement is 0.1°/sec. If a flap selection is
made with the autopilot engaged, the rate of movement reverts to the higher rate of
0.5°/sec. during flap transition.
4. Mach Trim - The Mach Trim is lowest in the order of priority. The stabilizer rate of
movement is between 0.03° and 0.06°/sec.
STAB TRIM MACH TRIM
ENGAGE
ENGAGE/
DISENGAGE
CH 1 CH 2 INOP
P604_10_014
Horizontal
Stabilizer
Trim Gauge
DN DN DN
- GEAR - - FLAPS -
STAB
- TRIM -
20
NU
ND
4.0
RUDDER
AIL
LWD RWD
NL NR
P604_10_015
FLIGHT CONTROLS
10-12 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
Horizontal Stabilizer Trim Clacker
If the horizontal stabilizer is in motion at a rate of more than 0.3°/sec. for more than 3
seconds, a clacker (“drumroll” sound) is activated to alert the pilot of a possible
horizontal stabilizer trim runaway condition.
In the event of a runaway stabilizer trim condition, both channels can be quickly
disconnected by pressing the STAB TRIM DISC button on either outboard control
wheel horn.
Mach Trim
The Mach Trim system, when engaged and active, compensates for the rearward shift
of the aerodynamic center of pressure as Mach number increases. The Mach Trim
system schedules inputs to the HSTCU to command movement of the horizontal
stabilizer when hand-flying at speeds greater than Mach 0.4.
Aileron Trim
Aileron trim is accomplished by activation of the AIL TRIM switches on the center
pedestal. Actuation of both switches provides arming and directional signals which
bias the control circuits to actuate the PCUs and deflect the ailerons. Actuation of the
aileron trim will cause the control wheels to deflect in the direction of trim input.
Aileron trim position is indicated on the EICAS primary page.
Rudder Trim
Rudder trim is accomplished by turning the RUD TRIM switch. Rudder trim input is
applied by the trim actuator into the yaw damper/trim mixer assembly and will
supplement the primary rudder input as applicable. Actuation of the rudder trim does
not cause rudder pedal deflection. The rudder trim position is indicated on the EICAS
primary page.
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-13
P I LOT T R A I N I N G GU I D E
Aileron/Rudder Trim Panel
Figure 10-7
Aileron/Rudder Trim Indications
Figure 10-8
L
W
D
　
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