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• GND SPOILERS Switch in the AUTO
position, and
• Flight Spoiler Lever > 1/4 detent
OR
• GND SPOILERS Switch in the ARM
position
Deploy Logic
• L and R Thrust Lever at IDLE
AND
• Main Landing Gear Weight-on-Wheels
OR
• Wheel Speed > 16 kts
Automatic Retract
• L or R Thrust Lever > IDLE (goaround),
OR
• L or R Thrust Lever < Min required for
Takeoff, and
• Inboard and Outboard Wheel Speed <
16 kts, and
• Deploy Logic (airplane on the ground
for at least 3 seconds)
Manual Retract
• GND SPOILERS Switch in the
DISARM position
OR
• Flight Spoiler Lever < 1/4 detent (if
spoilers were manually armed using
the Flight Spoiler Lever and the GND
SPOILERS Switch at AUTO)
L ARMED
EMER STOW
OFF
R ARMED
OFF
GND SPOILERS
THRUST
REVERSER
ARM
AUTO
DISARM
UNLK UNLK
L R
GROUND SPOILER PANEL
FLIGHT CONTROLS
10-20 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
Stall Protection System
The Stall Protection System (SPS) provides the flight crew with aural, visual and
tactile (stick shaker) indications of an impending stall and, if no corrective action is
taken, will activate a stick pusher to prevent the aircraft from entering a full stall.
A dual-channel SPS computer monitors the following inputs:
• angle of attack - LH, RH Angle-of-Attack vanes
• lateral acceleration - Inertial Reference System (IRS)
• flap position
• pressure altitude - Air Data Computers (ADCs)
The SPS uses these inputs to continuously calculate Angle-of-Attack (AOA) trip
points while in flight. The AOA trip points are biased with the lateral accelerometers
(sideslip and skid), flap position and pressure altitude.
As the trip point is approached, continuous ignition is activated. If the AOA continues
to increase, the stick shaker activates and the autopilot disengages. If the AOA still
continues to increase, the stick pusher activates, along with red flashing STALL and
Master Warning lights on the glareshield and a warbler aural warning. The stick
pusher only activates when the signals from both channels of the SPS computer are in
agreement.
The crew should initiate approved recovery techniques at the
first indications of an impending stall (i.e., recognition of
proximity of low-speed cue, at airframe buffet, at autoignition, or
any time the stick shaker or pusher activates).
In the event of an AOA increase rate greater than 1 degree per second, the SPS
computer lowers the AOA trip points to activate the aural, visual and tactile
indications at a lower AOA. This prevents the aircraft’s pitching momentum from
carrying it through the stall warning/stick pusher sequence into the stall.
Stick Pusher Disconnect
The stick pusher subsystem is armed when both STALL PROT PUSHER switches,
located on the pilot and copilot side panels, are ON. An acceleration switch will
disconnect the stick pusher, to prevent an unusual attitude, if less than +0.5 ‘G’ is
reached during pusher operation. The pusher may also be disabled momentarily by
pushing the AP/SP DISC button on the pilot’s or copilot’s control wheels. This will
disconnect the pusher only as long as either button is held in. In the event of a
malfunction, the stick pusher may be deactivated by switching either STALL PROT
NOTE
FLIGHT CONTROLS
For Training Purposes Only
May 03
10-21
P I LOT T R A I N I N G GU I D E
PUSHER switch to OFF (located on the side panels). To enable pusher operation, both
switches must be returned to the ON position.
Stall Protection System - Schematic
Figure 10-12
SPS TEST
INDICATOR
SPS TEST
INDICATOR
STALL PROTECTION COMPUTER
AOA TRANSDUCER LH
(ANGLE OF ATTACK)
AOA TRANSDUCER RH
(ANGLE OF ATTACK)
ADC 1 (ALTITUDE)
ADC 2 (ALTITUDE)
FLAP POSITION LH
FLAP POSITION RH
LATERAL ACCELERATION
LATERAL ACCELERATION
WOW 1
WOW 2
WOW FAIL
CB4-C5
0
STALL
PROT RH
CHAN
CB1-N4
0
STALL PROT
STICK PUSH
28 VDC
ESS
BUS
BATT
BUS
CB1-N5
0
STALL
PROT LH
CHAN
28 VDC
ESS
BUS
PILOT'S SIDE
PANEL
COPILOT'S SIDE
PANEL
RH CONTROL
COLUMN
OFF
ON
G-SWITCH
STICK
PUSHER
STICK
SHAKER
RH
STICK
SHAKER
　
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