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LH
AUTOIGNITION
(CONTINUOUS)
AP/SP
DISCONNECT
G-SWITCH
TEST
CHANNEL 1
CHANNEL 2
AUTOIGNITION
SIGNAL 1
AUTOIGNITION
SIGNAL 2
AUTOPILOT
DISCONNECT 1
AUTOPILOT
DISCONNECT 2
SHAKER SIGNAL
HORN SIGNAL
PUSH SIGNAL
HORN SIGNAL
SHAKER SIGNAL
PUSH SIGNAL
STALL
PROTECTION
TEST
INDICATOR
STALL
PROTECTION
TEST
INDICATOR
TEST IN
TEST IN
WARBLER
WARBLER
DCU
DCU
STALL
STALL
FLASHER
FLASHER
TEST #2
TEST #1
WOW
WOW
P604_10_007
I/C
OFF
R/T
NOSEDN
NOSEUP
AP
SC
SYNC
STALL
PROT
PUSHER
ON
OFF
STALL
PROT
PUSHER
ON
OFF
FLIGHT CONTROLS
10-22 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
The stick shaker is always armed. The STALL PROT PUSHER
switches affect only the stick pusher function.
SPS Ground Testing
Preflight testing of the system is accomplished by SPS TEST switches on the
Miscellaneous Test Panel located on the center pedestal. Either the L (R) SPS TEST
switch will cause the system to progressively sweep through the AOA range from no
stall to full stall, as indicated on the SPS Test Indicator, activating ignition (blue arc)
and shaker/autopilot disconnect (yellow arc). This is followed by red flashing STALL
lights on the glareshield and an aural warbler warning. If both switches are activated
simultaneously, the stick pusher will activate (red arc).
Pusher disconnects can then be tested by pushing, in sequence, the pilot’s AP/SP
DISC, the copilot’s AP/SP DISC and the G-switch.
See the Airplane Flight Manual for full testing procedures.
Ignition is activated during the test and may pose a hazard
in enclosed areas.
NOTE
CAUTION
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-23
P I LOT T R A I N I N G GU I D E
Controls and Indicators
Primary and secondary flight controls and indicators are accessible from both pilot
seats. Warning, caution, advisory, and status messages are presented on the Primary
Flight Display (PFD) and primary and status pages of the Engine Indication and Crew
Alerting System (EICAS).
FLIGHT CONTROLS
10-24 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Primary Flight Controls
Pitch, Roll and Yaw Controls
Figure 10-13
ROLL DISC
P
I
T
C
H
D
I
S
C
I/C
OFF
R/T
NOSEDN
NOSE
UP
AP
SC
SYNC
Pitch Disconnect Handle
Separates left and right
elevator inputs
Roll Disconnect Handle
Separates left and right aileron
inputs
COPILOT'S CONTROL WHEEL
(PILOT'S OPPOSITE)
Rudder Pedals
Incorporate an anti-jam/
breakout mechanism.
Mechanism activated by
applying additional force
on rudder pedal.
EICAS FLIGHT CONTROLS SYNOPTIC PAGE
(SECONDARY DISPLAY)
FLIGHT CONTROLS
FLAPS 30
FLAPS MOTOR OVERHEAT
AIL AIL
RUDDER
YAW DAMPER
STAB TRIM CH1 INOP
ELEV ELEV
P604_10_009
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-25
P I LOT T R A I N I N G GU I D E
Stab Trim, Aileron Trim, Rudder Trim
TRIM Controls
Figure 10-14
STAB TRIM MACH TRIM
ENGAGE
ENGAGE/
DISENGAGE
CH 1 CH 2 INOP
L
W
D
R
W
D
AIL TRIM
NL
RUD TRIM
NR
AILERON/RUDDER TRIM CONTROL PANEL
STABILIZER TRIM & MACH TRIM CONTROL PANEL
COPILOT'S CONTROL WHEEL
(MIRROR OF PILOTS)
P604_10_010
AILERON TRIM Switches (springloaded
to center)
LWD - Commands left wing down
aileron trim
RWD - Commands right wing down
aileron trim
Note: Both switches must be
pushed fully left or right to activate
trim.
RUDDER TRIM Switch (springloaded
to center)
NL - Commands nose left rudder
trim
NR - Commands nose right
rudder trim
Stabilizer Trim Switches
(spring-loaded to center)
NOSE UP - Activates nose up
trim
NOSE DN - Activates nose
down trim
Note: Both switches must be
pushed fully up or down to
activate trim.
Stabilizer Trim Disconnect Switch
(momentary-action)
Press - Disconnects stabilizer trim
(Both CH 1 and CH 2)
NOTE: Mach trim function will also
disengage when switch is actuated
　
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