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penetration when the aircraft nears the computed stall angle. The system alerts the flight
crew by means of visual and aural warnings.
Angle of attack vanes located on each side of the forward fuselage measure the aircraft
attitude in relation to the ambient airstream. The stall protection computer uses the AOA
information and airspeed to compute the stall angles.
When the aircraft approaches a high AOA, the stall protection computer will:
SWarn the crew of an impending stall through the stick shaker.
SActivate the engines auto-ignition system.
SDisengage the autopilot.
If the angle of attack continues to approach the critical stall point, the stick pusher is
activated to push the control column forward to give the aircraft a pitch down attitude. The
stick pusher can be selected off at the stall protection panel.
Vol. 1 11--80--2
FLIGHT CONTROLS
Stall Protection System REV 1, Jan 13/03
Flight Crew Operating Manual
CSP C--013--067
Stall Protection System Schematic
Figure 11---80---1
AP DISC
STALL
PTCT
OFF
ON
CHANNEL
B
CHANNEL
A
RIGHT
AOA
LEFT
AOA
SHAKER SHAKER
PUSHER
DISCONNECT
PUSHER
DISCONNECT
SPC
COPILOT
SIDE
PANEL
PILOT
SIDE
PANEL
MDC
IOC
GPWS
IOC
AHRS/IRS
ADC
SFECU
ISI
FADEC
FORWARD
QUADRANT
GLARESHIELD FCP
STICK PUSHER ASSEMBLY
STICK PUSHER
ACTUATOR
STALL
PTCT
OFF
ON
Vol. 1 11--80--3
FLIGHT CONTROLS
Stall Protection System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Stall Protection Controls
Figure 11---80---2
STALL PTCT PUSHER
Used to control operation of stick pusher.
Pilot and Copilot Control Wheels
AP/SP DISC (red)
Used to disengage the autopilot and to momentarily
deactivate the stall protection system.
Press to disengage the autopilot and to
momentarily disable the stick pusher.
Release to reactivate the stick pusher.
Stall Protection Panel
Pilot and Copilot Side Panels
WIPER
SLOW
FAST
OFF PARK
INT
When pressed for 4 seconds or longer, the
STALL FAIL caution message will come on.
The caution message will go out approximately
1 second after the switch is released.
NOTE
Both pilot and copilot switches must be
selected on to engage the stick pusher.
NOTE
STALL
PTCT
OFF
ON
Vol. 1 11--80--4
FLIGHT CONTROLS
Stall Protection System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Stall Protection --- Test and EICAS Indications <1001>
Figure 11---80---3
STALL (Guarded)
Used to initiate stall protection
system test while airplane is in
a weight--on--wheels condition.
STALL (red) light flashes to
indicate an impending stall
condition
Warbler tone alerts
flight crew of impending
a stall condition.
Stall Test
To initiate stall protection system test, momentarily press STALL light, and verify that:
Auto--ignition is activated
(CONT IGNITION status message on EICAS and illumination of ON light on ignition panel.
Pilot’s stick shaker is activated and, after 3 seconds, copilot’s stick shaker is activated.
After approximately 7 seconds, stick pusher is activated and STALL light comes on.
Press AP/SP DISC to verify stick pusher stops and STALL light goes out.
1Pilot’s stick shaker stops, copilot’s stick shaker stops and auto--ignition is deactivated.
STALL
Left and Right Glareshield
STALL FAIL caution (amber)
Indicates that pusher is deactivated or
has failed or one channel of the stall
protection computer has failed or angle
of attack sensor has failed.
STALL FAIL
700fcom1_118002ac01.cgm
Pressing STALL light a second time during
the stall protection test, will interrupt the
test sequence.
NOTE
Primary Page
Vol. 1 11--80--5
FLIGHT CONTROLS
Stall Protection System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
A. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Stall
Pusher
STALL PROT
STICK
PUSHER BATTERY
BUS 1
Q1
Protection
System
Computer
STALL PROT
L CH
Q2
y
STALL PROT
R CH
DC
ESSENTIAL 2 U5
Vol. 1 11--80--6
FLIGHT CONTROLS
Stall Protection System Sep 09/02
Flight Crew Operating Manual
　
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