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FLIGHT CONTROLS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
10−10−49
STALL PROTECTION
The Stall Protection System (SPS) provides the flight crew with aural, visual and feel (stick shaker)
indications of an impending stall. Following these events and no corrective action is taken, the
system activates the stick pusher mechanism, preventing the airplane from entering the stall.
The stall protection system consists of two (electrically antiiced)
angle of attack sensors, a dual
channel computer, two stick shakers, a stick pusher system and mach sensing to back up the air
data computers. Each channel of the computer controls a stick shaker. The computer provides two
independent signals to the pusher system logic. Both channels of the computer must agree to
activate the stick pusher system based on similar system inputs.
The stall protection function is inhibited when both weightonwheels
inputs indicate on ground or
calibrated airspeed is recognized to be less than 70 kts.
The stall protection computer continuously monitors the SPS and faults detected are sent to EICAS
for aural and/or visual annunciation.
STALL PROTECTION COMPONENTS
The stall protection system consists of the following components:
AngleOfAttack
(AOA) Vane
Two AOA vanes are mounted on the forward fuselage (left and right) of the airplane. They rotate to
align with the prevailing airflow to measure the direction of the airflow relative to the fuselage.
AOA VANE
GF1010_061
The vanes provide information to both channels of the stall protection computer. There are
selfregulating
heaters controlled and monitored by the Heater and Brake temperature Monitor Unit
(HBMU ) located in the vanes. The heaters provide the sensors with deicing
and antiicing
capability in icing conditions.
FLIGHT CONTROLS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
10−10−50
STALL PROTECTION COMPONENTS (CONT'D)
Mach Transducer
The mach transducer control is installed on the right side of the flight compartment, below the
copilot’s side console. It is connected to the pitotstatic
system through a selector/isolator switch.
The mach transducer receives electrical input and pressure through connectors and supplies
secondary mach information to the channels of the Stall Protection Computer (SPC). The ADCs
supply primary mach data to the channels of the (SPC).
Mach Transducer Selector
Normal operation is selection
in the pitot/static position.
The mach transducer is operated in the pitotstatic
position and is used to cross check for errors
from the micro air data computer system. This is accomplished by providing dissimilar source for
mach number, airspeed and altitude inputs.
Stick Shaker Actuator
A stick shaker (mechanical vibratory device) actuator is located on each control column and
provides tactile sensing, simulating airplane buffeting.
The stick shakers consist of a high speed motor and the actuators are controlled from the SPC
channels.
FLIGHT CONTROLS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
10−10−51
STALL PROTECTION COMPONENTS (CONT'D)
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.
GF1010_064
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 (1½ degrees before push occurs) the pitch
disconnect locking mechanism is activated. When the push is cancelled, the solenoid for the pitch
disconnect locking mechanism is deactivated.
FLIGHT CONTROLS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
10−10−52
STALL PROTECTION COMPONENTS (CONT'D)
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
　
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