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evidenced by a high-frequency vibration of the control columns. The
left and right systems are completely independent and utilize separate
electronics, stall vanes, altitude bias signals, shaker motors, and
flap switches. The stall warning system operates on 28 VDC supplied
through the 5-amp L and R STALL WARN circuit breakers on the pilot's
and copilot's circuit breaker panels respectively. The stall warning
system is operative during EMER BUS mode. The stick shaker
and STALL warning light circuits are wired through the shaker interrupt
box and squat switches; therefore, the stick shaker and STALL
warning lights are deactivated when the squat switches are in the
ground mode. The stick shaker and STALL warning lights will be deactivated
for 3 to 5 seconds after lift-off. The angle-of-attack indicators
remain active both on the ground and inflight . The stall warning systems
may be tested on the ground using the rotary-type systems test
switch, located on the pilot's instrument panel. The stall vanes are
heated to provide anti-ice protection during flight (Refer to PITOTSTATIC
AND STALL WARNING ANTI-ICE, Section VI).
During flight, the stall warning vanes align with the local airstream
and transducers produce a voltage proportional to airplane angle of
attack . The transducer signals are transmitted to the appropriate computer-
amplifier channel along with flap position information from the
flap position switches and altitude information from the air data computers
. The angle-of-attack indicator pointers will enter the yellow
segment, the L and R STALL lights will illuminate and flash, and the
stick shakers will actuate when the angle of attack increases to an angle
corresponding to an airspeed at least 7% above the stall speed
published in the Airplane Flight Manual.
PM-121
5-5
Change 2
Pilot's Manual
Learjet 31A
LEFT
SHAKER
LEFT STAR
ANNUNCIATOR
AUTOPILOT/
SHAKER INTEFFACE
ADC z
STALL WARNING SYSTEM BLOCK DIAGRAM
Figure 5-2
RKaHT
SHAKER
RK;HT STALL
ANNUNCIATOR
5-6
PM-121
Original
Learjet 31A
Pilot's Manual
ANGLE-OF-ATTACK INDICATORS
The angle-of-attack indicators, located on the pilot's and copilot's instrument
panels, translate signals from the stall warning computeramplifier
into visual indication of stall margin . The left stall warning
system utilizes the pilot's angle-of-attack indicator and the right stall
warning system utilizes the copilot's angle-of-attack indicator. Each
indicator face is divided into three segments as follows: green - safe,
yellow - caution/shaker, and red - danger.
STALL WARNING LIGHTS
The red L and R STALL warning lights, located in the glareshield annunciator
panel, are installed to indicate impending stall or a system
malfunction. During flight operations, the lights will illuminate and
flash when the shaker is actuated. The lights are pulsed at the same
frequency and duration as the shakers; therefore, the flash duration
will increase as the angle-of-attack increases from initial shaker actuation.
At or just prior to the angle-of-attack pointer entering the red
segment, the flash duration is sufficient to cause the lights to appear
steady.
SYSTEM TEST SWITCH - STALL WARNING FUNCTION
The rotary-type system test switch, located on the pilot's instrument
panel, is used to test the left and right stall warning systems. Each
system is individually tested through the L STALL and R STALL positions
of the system test switch. The test is initiated by rotating the
system test switch to L or RSTALL (as applicable) and then depressing
the switch PRESS TEST button. When the test sequence is initiated,
the corresponding angle-of-attack indicator pointer will begin to
sweep from the green segment toward the red segment. As the pointer
passes the green-yellow margin, the stick-shaker will actuate, the
MSTR WARN lights will illuminate, and the applicable STALL light
will begin to flash. Shaker actuation is made evident by high frequency
vibration of the control column.
PM-121
5- 7
Change 2
Pilot's Manual
Learjet 31A
OVERSPEED WARNINGSYSTEM
The overspeed warning system provides an audible overspeed warning
in the event aircraft speed exceeds a Mach or airspeed limit. The
overspeed warning hom is activated by the air data computers when
the position of the airspeed pointer and the maximum allowable
pointer (barber pole) coincide. 28 VDC for system circuits is supplied
through the 5-amp WARN HORNS circuit breaker on the copilot's
circuit breaker panel. The overspeed warning horn is operative during
　
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