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inside of the airspeed tape which rises from the bottom
of the tape as the airplane AOA increases. The point at
which the red bar reaches the airspeed pointer will
coincide with the point at which other stall warning
indications are activated.
(2) The left and right channels of the stall computer will
activate the control column shaker motors.
(3) The non-cancelable voice message “STALL” will repeat
until the AOA is decreased.
(4) The AOA indicators (if installed) will enter the red
band on the indicator.
Pilot’s Manual
PM-126A 5-27
STALL WARNING OPERATION
The stall warning system is powered when the circuit breakers are in.
The shakers, along with other visual and aural stall indications, are inhibited
until the airplane is airborne. If installed, the AOA indicators
will operate in both the air and ground modes. The stall warning system
performs a power-up self-test (BIT) and monitors for a number of
possible system faults. Detection of a fault appears on CAS.
The following CAS illumination is specific to the stall warning system:
STALL VANE ANTI-ICE
The stall vanes are equipped with a 28-vdc heater to anti-ice the vane
surfaces during icing conditions. The AOA vane heater of the angle-ofattack
transmitter is monitored for open circuit when the vane heater
power is applied. Detection of an open circuit will result in the appropriate
CAS message as well as being logged into the stall computer as
a fault for that flight. The vane heaters are controlled by the L and R
PROBE anti-ice switches located on the anti-ice section of the center
switch panel. Each vane heater is supplied power from the left and
right main bus respectively and protected by the AOA 15-amp circuit
breakers on the pilot’s and copilot’s circuit breaker panel (ANTI-ICE
group).
The following CAS illumination is specific to the stall vane anti-ice
system:
CAS Color Description
STALLWARN FAIL Amber The associated (L or R) stall warning system
has failed.
CAS Color Description
AOA HT FAIL Amber Associated (L or R) angle-of-attack vane
heater has failed.
Pilot’s Manual
5-28 PM-126A
STALL SYSTEM TEST
A self-test mode is available when the weight-on-wheels signal indicates
that the airplane is on the ground and no system failure is detected.
When the system test switch is rotated to the STALL position and
held down for approximately 7 to 10 seconds, the stall warning computer
shall demonstrate that the stall warning system is fully operational
by performing the following events in the order listed:
(1) L AOA HT FAIL message appears in CAS.
(2) Low Speed Awareness (LSA) bar will begin to sweep
up the pilot side airspeed tape, the left (pilot’s) column
will shake when the LSA bar approximately reaches
the indicated airspeed pointer, and the aural voice
warning “STALL” will be repeated through the cockpit
speakers and crew headphones.
(3) L AOA HT FAIL message extinguishes from the CAS
window, the LSA bar scrolls down the airspeed tape,
the left column stops shaking and the aural warning
stops.
(4) R AOA HT FAIL message appears in CAS. (Note: Master
caution tone may not sound when the R AOA HT
FAIL is annunciated. If the master caution tone is not
heard, then the STALL aural warning will be heard as
called out in the next step below).
(5) The LSA bar will begin to sweep up the copilot side
airspeed tape, the right (copilot’s) column will shake
when the LSA bar approximately reaches the indicated
airspeed pointer, and the aural voice warning “STALL”
will be repeated through the cockpit speakers and crew
headphones (if the master caution tone was not heard
in the previous step).
(6) R AOA HT FAIL message extinguishes from the CAS,
the LSA bar scrolls down the airspeed tape, the right
column stops shaking and the aural warning stops (if
the aural warning was present in the previous step).
The left and right stall warning failure discretes are not checked during
self-test. It was necessary to inhibit the output of the left and right
failure discretes in order to permit display of the LSA bar on the PFDs
during test.
Pilot’s Manual
PM-126A 5-29
ANGLE-OF-ATTACK INDICATORS (OPTIONAL)
The optional Angle-of-Attack (AOA) indicators system consists of two
angle-of-attack indicators mounted in the instrument panel, one outboard
of the pilot PFD and one outboard of the copilot PFD, Figure 5-5.
The angle-of-attack indicators display continuous angle-of-attack position
to the flight crew. The AOA indicators are driven by the stall warning
　
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