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near the thrust levers. The switch has four positions: UP, 8, 20, and
DN. When 8° or 20° flaps are selected, 28 VDC is directed to the applicable
(up or down) solenoid of the flap control valve. The flap control
valve will meter hydraulic pressure to the flap actuators and move
the flaps in the desired direction. As the flaps approach within 1° of
the selected setting, the applicable flap limit switch will remove power
from the flap control valve solenoid and flap travel will stop. When
UP is selected, 28 VDC is directed to the up solenoid of the flap control
valve and the flaps will move in the up direction. When DN is selected,
28 VDC is directed to the down solenoid of the flap control
valve and the flaps will move in the down direction. When the flaps
reach full extension, the "down" pressure will remain to maintain the
flaps full down.
FLAP POSITION INDICATOR
The vertical-scale FLAP position indicator, mounted in the center
switch panel, provides the crew with visual indication of flap position.
The indicator face consists of a scale, which has markings for UP
(0°), 8°, 20°, and DN (40°), and a pointer on the right margin of the
scale. A potentiometer connected to the left flap sector transmits the
flap position signal to the indicator. The indicator operates on 28 VDC
supplied through the 2-amp TRIM-FLAP IND circuit breaker on the
copilot's circuit breaker panel.
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Pilot's Manual
Learjet 31A
SPOILERS
The spoilers are located on the upper surface of the wings forward of
the flaps. The spoilers are electrically controlled and hydraulically actuated.
The SPOILER switch on the forward pedestal is used to symmetrically
extend and retract the spoilers. As the switch is moved to
the EXT position, the solenoid valve directs hydraulic pressure to the
extend port of the spoiler actuators which causes the spoilers to extend.
As the spoilers unseat and extend through 1°, the amber SPOILER
light will illuminate signifying the spoilers are not retracted and
locked. The spoilers will fully extend in 5 to 7 seconds. Full extension
is approximately 47°. However, during flight, a pressure relief allows
the spoilers to "blow down" to a lesser extension angle. When BET is
selected, the solenoid valve will direct hydraulic pressure to the retract
port of the spoiler actuators which causes the spoilers to retract.
When retracted, the spoilers are secured by an internal locking mechanism
in the actuators. During normal operation, the spoilers will fully
extend or retract in approximately 5 to 7 seconds. Spoiler control
circuits operate on 28 VDC supplied through the 3-amp SPOILER circuit
breaker on the copilot's circuit breaker panel. The spoiler control
system is operative during EMER BUSmode.
SPOILER SWITCH
Symmetric extension and retraction of the spoilers is controlled
through the SPOILER switch located on the right side of the pedestal
adjacent to the thrust levers. The switch is guarded to prevent inadvertent
spoiler actuation. The switch has two positions: EXTand RET.
When the switch is set to EXT, both spoilers will extend and the
SPOILER light will illuminate. When the switch is set to RET, both
spoilers will retract.
SPOILER LIGHT
The amber SPOILER light, located on the glareshield annunciator
panel, will illuminate steady whenever the flaps are UP and the spoilers
are extended . The light will flash if the spoilers are extended and
the flaps are beyond 3°. The light is operated by a 1°-up position
switch for each spoiler. The light will illuminate if either 1°-up switch
is actuated.
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Learjet 31A
Pilot's Manual
WARNING SYSTEMS
STALL WARNING SYSTEM
A stall warning system is installed to provide the crew with visual
and tactile warning of an impending stall. The major components of
the stall warning system consist of the following: left and right stall
vanes on the forward fuselage, a two-channel computer-amplifier,
shaker interrupt box, flap position switches for each flap, a stick shaker
for each crew position, an angle-of-attack indicator for each crew
position, L and R STALL warning lights, and associated aircraft wiring.
The flap position switches provide bias information to the computer-
amplifier which will decrease stall indication speeds as the
flaps go from 0° to 40°. Above approximately 22,500 feet pressure altitude,
a signal from the air data computers will bias the system to increase
stall indication speeds approximately 15 knots. The stick shakers
are eccentric weights driven by an electric motor and actuation is
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