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center switch panel, is installed to provide a visual indication of the
wing leading edge temperature. The indicator receives input signals
from the wing temperature sensor installed on the inner surface of the
left wing leading edge. The indicator face is divided into three colored
segments: blue, green, and red. If the indicator pointer is in the
blue segment, wing leading edge temperature is below approximately
40°F (4°C). If the indicator pointer is in the blue segment and the
STAB WING HEAT switch is On, a system malfunction is indicated.
If the indicator pointer is in the green segment, wing leading edge
temperature is above 40°F (4°C). If the indicator pointer is in the red
segment, the wing leading edge is approaching an overheat condition
and corrective action must be taken. The wing anti-ice system should
be energized whenever flying through visible moisture and the
WING TEMP indicator pointer is in the blue segment.
WING OV HT LIGHT
The red WING OV HT light, on the glareshield annunciator panel,
will illuminate in the event that the wing leading edge heats to 215°F
(102°C). The light is energized by the overheat wanting light thermoswitch
located on the inner surface of the right wing leading edge.
HORIZONTAL STABILIZER ANTI-ICE
The horizontal stabilizer anti-ice system utilizes sequenced electrical
heating elements along the horizontal stabilizer leading edge. The
system consists of an electrically heated blanket bonded to each half
of the horizontal stabilizer leading edge, a sequence timer, a caution
light, a system switch, and associated aircraft wiring. Control circuits
operate on 28 VDC supplied through the 7S-amp STAB HT circuit
breaker on the copilots circuit breaker panel. Electrical power for the
heating elements is 28 VDC supplied through a 130-amp current limiter.
PM-121
6-5
Original
Pilot's Manual
Learjet 31A
STAB WING HEAT SWITCH - STABILIZER HEAT FUNCTION
The horizontal stabilizer anti-ice system is controlled through the STAB
WING HEAT switch on the center switch panel. The switch has two positions:
On (STAB WING HEAT) and OFF When the aircraft is in flight
and the STAB WING HEAT switch is On, 28 VDC is supplied through
the stab heat relay box to the sequence timer. The timer distributes intermittent
electrical power to the individual heating elements in a forward-
to-aft sequence of 15 seconds duration each. Approximately 3
minutes are required to complete a full cycle. The center, or parting elements,
are supplied with continuous electrical power. During normal
stabilizer heat operation, the aircraft DC AMPS readout will reflect a
pulsating current drain of approximately 60-amps in 15 second cycles .
At least one engine generator must be operating to energize the stab
heat control circuits. The control circuits are routed through a start cutout
relay and theright squat switch; therefore, the systemis inoperative
when the squat switch is in the ground mode and during engine start.
STAB HEAT LIGHT
The amber STAB HT light, located on the glareshield annunciator panel
will illuminate whenever the STAB WING HEAT switch is On and the
heating blanket parting elements are not receiving electrical power.
During flight, illumination of the STAB HT light indicates system failure.
During ground operation, the STAB HT light should illuminate
whenever the STAB WING HEAT switch is ON.
WINDSHIELD ANTI-ICE
Primary windshield anti-icing is accomplished by directing conditioned
engine bleed air through ducting and control valves to external
outlet nozzles forward of the windshield. The windshield anti-ice system
consists of an anti-ice overheat shutoff valve, a windshield anti-ice
modulating valve, one low-limit (215°F [102°C]) and one high-limit
(250°F [121°C]) thermoswitch for ground operations, one low-limit
(250°F [121°C]) and one high-limit (270°F [132°C]) thermoswitch for
flight operations, a green WSHLD HT light, a red WSHLD OV HT
warning light, a ram air modulating valve, an anti-ice duct temperature
sensor, an anti-ice heat exchanger, two outlet nozzle assemblies, a system
control switch, and associated aircraft wiring and bleed air ducting.
Electrical power to the control circuits is 28 VDC supplied through
the 7.5-amp WSHLD HT circuit breaker on the pilot's circuit breaker
panel.
6-6
PM-121
Change 3
Learjet 31A
Pilot's Manual
Change 2
WINDSHIELD ANTI-ICE SYSTEM
Figure 6-2
NOTE: This figure is intended to reflect the system logic and not
necessarily all of the actual components used to accomplish that
　
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