switch must be simultaneously moved in the same direction. When
electric pitch trim reaches the nose up or nose down limit of
allowable travel, messages are prompted for display on CAS. The
type of messages depend upon whether or not the autopilot is
engaged.
D. Stall Barrier System:
(See Figure 3, Figure 4 and Figure 6.)
The stall barrier system consists of stick shaker motors located on each
control column, a stick pusher actuator located in the tail compartment and
Angle of Attack (AOA) probes located on each side of the fuselage forward
section.
The stall barrier system can be deactivated by depressing the autopilot
disconnect switches (A/P DISC / BARR DISC) on either control wheel, or
by selecting the STALL BARR switch, located on the center console, to the
OFF position. When the stall barrier system is selected off, a message is
prompted for display on CAS.
NOTE:
The autopilot servo input to the elevator control
system is through a separate set of cables connected
to the elevator actuator. Servo inputs are introduced at
the actuator. The force generated by the stall barrier
system will overcome autopilot force.
(1) Stick Shaker Motor:
Two stick shaker motors are connected to the pilot and copilot
control columns. Upon activation, the motor provides a warning by
shaking the control column. The pilot’s stick shaker motor is
connected to the Left Essential DC bus through the SHAKER #1
circuit breaker and a relay activated by Data Acquisition Unit (DAU)
#1. The copilot’s stick shaker motor is connected to the Right Main
DC bus through SHAKER #2 circuit breaker and a relay activated by
DAU #2. If a failure is detected in either stick shaker, a message is
prompted for display on CAS.
(2) Stick Pusher Actuator:
The stick pusher actuator is controlled through two independent
electro-hydraulic valves. The left valve is controlled by either
channel of DAU #1 and Fault Warning Computer (FWC) #1, and the
right valve is controlled by either channel of the DAU #2 and FWC
#2, in order to eliminate single point failures. The #1 stick pusher
valve is connected to the Left Essential DC bus through the STALL
BARR VALVE #1 circuit breaker and the PUSH #1 relay. The #2
stick pusher valve is connected to the Right Main DC bus through
the STALL BARR VALVE #2 circuit breaker and the PUSH #2 relay.
The actuator is normally loaded in the retracted position. When the
stick pusher is activated, a message is prompted for display on
CAS, the solenoids are energized and the actuator extends.
Extension of the actuator provides mechanical force to push the
control column forward.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS2A-27-00
Page 8
May 22/01
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