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EICAS message will appear.
Within the Elevator control mechanism, a stick shaker and stick pusher system can be
activated via the Stall Protection System (SPS). The SPS is covered later in this
chapter.
Pitch Disconnect
In the event of a control cable jam, or elevator system malfunction, the left and right
elevator control circuits can be isolated by pulling the PITCH DISC handle on the
center pedestal. This provides reduced pitch authority through the one elevator on the
operable circuit. The PITCH DISC handle can be reset at any time, locking the two
control circuits together again.
Elevator PCU Protection
An elevator PCU jam or failure can be overcome by integrated jam-tolerant input rods.
These rods collapse or expand in the event of both PCUs on one side having no
hydraulic pressure, and enable operation of the opposite side elevator. If one of the
pair of on-side PCU control valves jams, the jam-tolerant input rod will allow
operation of the adjacent PCU control valve.
Flutter Dampers
Two flutter dampers are installed on each elevator. These are identical in design and
function to those installed on the ailerons.
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-7
P I LOT T R A I N I N G GU I D E
Pitch Control - Schematic
Figure 10-3
1 3
3 2
Artificial Feel
According to
Horizontal
Stabilizer
Position
Elevator Flutter Dampers
2 Each Elevator
Horizontal
Stabilizer
0° to -9°
PITCH
DISC
STICK
SHAKER
STICK
SHAKER STICK
PUSHER
STALL
PROTECTION
SYSTEM
STALL
PROTECTION
SYSTEM
RUDDER
ELEV ELEV
EICAS FLIGHT CONTROLS SYNOPTIC PAGE
(SECONDARY DISPLAY)
Elevator
Position
Scale
Autopilot
Servo
Commands
P604_10_003
I/C
OFF
R/T
NOSEDN
NOSE
UP
AP
SC
SYNC
I/C
OFF
R/T
NOSEDN
NOSE
UP
AP
SC
SYNC
P
I
T
C
H
D
I
S
C
FLIGHT CONTROLS
10-8 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
Rudder
Yaw control is provided by a hydraulically actuated rudder hinged on the rear spar of
the vertical stabilizer. Two separate mechanical control paths are provided from the
rudder pedals to three independent PCUs. Each PCU is powered by a separate
hydraulic system. A position transmitter provides visual indication of rudder
deflection on the EICAS flight control synoptic page.
Both rudder pedal control systems have an anti-jam breakout mechanism. In the event
of a jammed rudder control on one side, both pilot and copilot rudder pedals are
capable of operating the remaining control system. Additional force on the rudder
pedals is required to bypass the inoperative side, allowing rudder operation.
A two-channel Yaw Damper system is installed and supplies small rudder corrections
in response to reference signals from the IRUs through the FCCs. This is considered a
function of the Automated Flight Control System (AFCS) system. Refer to Chapter 4
Automatic Flight Control System for additional information.
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-9
P I LOT T R A I N I N G GU I D E
Yaw Control - Schematic
Figure 10-4
ENGAGE
YAW DAMPER
DISC
YD 1 YD 2
1
2
3
INTEGRATED AVIONICS
PROCESSOR SYSTEM
FCC 1 FCC 2
LOAD LIMITER
RUDDER TRIM ACTUATOR
YAW DAMPER ACTUATOR
DC
BUS 1
FORWARD QUADRANT
WITH ANTI-JAM/
BREAKOUT
RUDDER
ELEV ELEV
EICAS FLIGHT CONTROLS SYNOPTIC PAGE
(SECONDARY DISPLAY)
P604_10_004
Rudder
Position
Indicator
NL
RUD TRIM
NR
FLIGHT CONTROLS
10-10 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
Secondary Flight Controls
Description
The secondary flight controls include the horizontal stabilizer, inboard and outboard
flaps, flight and ground spoilers, and the associated trim systems. The horizontal
stabilizer trim is electrically actuated via a jackscrew. Flaps are electrically powered
and driven by flex cables and ballscrew actuators. Spoilers are hydraulically powered.
Trim about all three axes is electrically controlled from the cockpit.
Components and Operation
Horizontal Stabilizer Trim
Pitch trim is accomplished by varying the angle of incidence of the horizontal
stabilizer. The Horizontal Stabilizer Trim Control Unit (HSTCU) commands the
　
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