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COMPUTER
NOSEDN
NOSE UP
DISC
MASTER
TCS
MIC
NOSEDN
NOSE UP
DISC
MASTER
TCS
MIC
For Training Purposes Only
Sept 04
10-57
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
STALL PUSHER
If the angle of attack increases to a point where the airplane’s stall margin is too small,
the SPC will command a push of both control wheels. This is accomplished using a
motor assembly which will drive the forward left elevator quadrant. The right control
wheel will receive its input to push through the coupled automatic pitch disconnect
mechanism.
The pitch disconnect mechanism has a function to engage a solenoid piston to prevent
elevator split during push.
The pitch disconnect solenoid is controlled by the SPC and when operated, prevents
the automatic pitch disconnect mechanism from activating when push is commanded
by the SPC.
When the AOA approaches pusher firing angle (1 1/2 degrees before push occurs), the
pitch disconnect locking mechanism is activated. When the push is canceled, the
solenoid for the pitch disconnect locking mechanism is deactivated.
STALL PROTECTION DISCONNECT BUTTONS
The stall protection disconnect buttons are located on the pilot and copilot control
column. These switches also provide a disconnect command to the autopilot and pitch
trim functions.
NOTE
A STALL PROTECT FAIL caution message will be displayed if
the disconnect button is held for approximately 12 seconds.
This stick pusher may be stopped by pressing and holding the autopilot/stick pusher
disconnect (AP/SP DISC) switch. This will remove power to the actuator as long as
either switch is depressed. The stick pusher is capable of operating immediately once
the autopilot/stick pusher disconnect switch is released, and a stall push is requested
by the computer.
GX_10_055
STICK
SHAKER
STICK
SHAKER
STALL
PROTECTION
COMPUTER
LEFT
ELEVATOR
QUADRANT
RIGHT
ELEVATOR
QUADRANT
Pitch Lock
Solenoid
Pusher
Actuator
NOSEDN
NOSEUP
DISC
MASTER
TCS
MIC
NOSEDN
NOSEUP
DISC
MASTER
TCS
MIC
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-58 For Training Purposes Only
Sept 04
The remaining stall warning functions are available with the disconnect button held.
Only the pusher function is disabled with either switch held. All other SPS events are
normal.
STALL PUSHER ON/OFF SWITCHES
The stall pusher ON/OFF switches are used for long term disabling of the pusher
system. The switches are located on the pilot and copilot side panels.
NOTE
Selecting either stall pusher switch to OFF will cause a STALL
PROTECT FAIL caution message to be displayed.
In the event of a malfunction, the stick pusher may be disabled by selecting the
PUSHER switch to OFF on the pilot’s or copilot’s stall protection panel. When either
or both switches are selected to OFF, the SPC cannot command a push.
GX_10_056
NOTE:
The pilot control column is shown:
copilot control column is similar.
PUSHER DISCONNECT
SWITCH
LEFT HAND
COLUMN
NOSE
DN
NOSE UP
DISC
MASTER
TCS
MIC
GX_10_057
STICK
PUSHER
SYSTEM
PILOT’S SIDE PANEL COPILOT’S SIDE PANEL
PUSHER
STALL
ON
OFF
ER
PUSHER
STALL
ON
OFF
ER
For Training Purposes Only
Sept 04
10-59
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
STALL PROTECTION COMPUTER
A dual-channel Stall Protection Computer (SPC) monitors the following inputs:
• LH, RH Angle-Of Attack (AOA) transducers Angle of attack
• LH, RH Lateral, accelerometers Lateral acceleration
• LH, RH Slat/Flap Slat/Flap position
• Weight-On-Wheels 1, 2 (WOW) WOW and SPS inhibit
• ADC 1, 2 and 3 Mach, airspeed and altitude
• Inertial Reference Unit (IRU) Normal and lateral acceleration
• WOW Fail Weight-On-Wheels
The SPC receives data input from the bleed management computer, landing gear
electronic control unit, heater brake monitor unit and EMS/CDU through the data
acquisition units.
Low speed awareness output is a function of the SPC to the Electronic Flight
Instrument System (EFIS).
• Red line - Shaker or stall warning speed.
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-60 For Training Purposes Only
Sept 04
STALL PROTECTION COMPUTER SCHEMATIC
GX_10_058
　
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