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LATERAL ACCELEROMETER
SFCU 1/2
MACH TRANSDUCER
(MACH)
FLIGHT CONTROL UNIT 1
IRS 1/3
ADC #1/2
AOA TRANSDUCER LH
(ANGLE OF ATTACK)
WOW 1
WOW 2
AOA TRANSDUCER RH
(ANGLE OF ATTACK)
ADC #2/3
IRS 2/3
FLIGHT CONTROL UNIT 2
MACH TRANSDUCER
(MACH)
SFCU 1/2
LATERAL ACCELEROMETER
M
O
N
I
T
O
R
C
O
M
M
A
N
D
C
O
M
M
A
N
D
M
O
N
I
T
O
R
STICK
SHAKER
LH
ENGINE
IGNITION
(CONTINUOUS)
AUTOPILOT
DISCONNECT
STICK
SHAKER
RH
TEST
INPUT
TEST
INPUT
EMS
EMS
CHANNEL 1
CHANNEL 2
PUSH
FAIL
PUSH
FAIL
DISCONNECT/
PUSH SIGNAL
DISCONNECT/
PUSH SIGNAL
EICAS
GPWS
EICAS
GPWS
PUSHER
DISCONNECT
SWITCH
LEFT-HAND
COLUMN
PILOT’S
SIDE PANEL
COPILOT’S
SIDE PANEL
STICK
PUSHER
DAU 4
DAU 3
NOSEDN
NOSEUP
DISC
MASTER
TCS
MIC
PUSHER
STALL
ON
OFF
ER
PUSHER
STALL
ON
OFF
ER
For Training Purposes Only
Sept 04
10-61
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
STALL PROTECTION OPERATION
The stall protection computer uses numerous system inputs to calculate the angle of
attack trip points. As a high angle of attack is approached:
• Ignition is activated
If the angle of attack continues to increase:
• The stick shakers are activated
• Autopilot disengages, and
• The voice advisory sounds
If the angle of attack continues to increase:
• The pitch disconnect system will lock
• The stick pusher mechanism is activated
• The word STALL appears in a red box on the attitude sphere. (The stall
annunciation shall initially blink at a rate of 1 second on and 1/2 seconds off for 5
seconds, and then shall remain steady)
This results in both control columns advancing to the full forward limit to correct the
stall condition.
When stall has been corrected the SPC will cancel:
• The push and pitch disconnect locking mechanism
• Voice advisory
• STALL on the attitude sphere
• Ignition
• Stick shakers
GX_10_059
“STALL”
GX_10_060
20
10
20
STALL 10
Stall
Annunciation
PRIMARY FLIGHT DISPLAY
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-62 For Training Purposes Only
Sept 04
STALL WARNING ADVANCE
In specific conditions, the SPC will cause warnings to occur sooner than normal. The
stall warning advance system will advance the stick shaker firing angles through the
SPC when these conditions are sensed. Examples of conditions leading to a stall
warning advance are listed below.
• Slat malfunction
• Flap malfunction
• Flight in icing conditions with wing anti-ice off or failed
The pilot has an interface through the Electrical Management System (EMS)/Control
Display Unit (CDU) to select the stall warning advance for undetected failures
(example: damage to slat panel due to bird strike or ice accretion on the wing which
cannot be dispersed). Either pilot’s EMS/CDU can command mode changes from the
control page 1/2. Once selected, it can only be canceled by pilot input. The two modes
of operation selectable on the EMS/CDU are NORM or REV.
NOTE
Only pilot action can return the advance mode to normal mode.
Pilot command interface on EMS/CDU:
• Command mode change from the control page
• Either pilot’s EMS/CDU can command mode changes
NOTE
The pilot cannot override advanced mode for detected failures.
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUS
PREV
PAGE
NEXT
PAGE
CNTL TEST
BUS
EMER
CONT
GX_10_061
SWITCH CONTROL 1/2
SLAT/FLAP RESET
STALL WARN ADVANCE
LEFT FOOTWARMER
RIGHT FOOTWARMER
ON
NORM
ON
ON
STALL WARN ADVANCE
NORM
REV
Select the mode “ ” or
“ ” from control page 1/2.
Select the SYSTEM CONTROL page
to display the STALL WARN ADVANCE
mode of operation.
For Training Purposes Only
Sept 04
10-63
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
Advanced mode indication on EICAS and EMS/CDU:
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
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