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during night operations. The light is illuminated by depressing
the WING INS? LIGHT momentary button on the copilot's dimmer
panel. The light illuminates a black dot on the outboard wing
leading edge to enhance visual detection of ice accumulation. Power
is supplied through the 5-ampWING INSP LT circuit breaker on the
copilot's circuit breaker panel.
ENGINE AND NACELLEINLET ANTI-ICE
The engine and nacelle inlet anti-ice system provides anti-ice protection
for the nacelle inlets and the engine inlet air temperature and
pressure sensor masts. Theengine inlets are antiToed by directing engine
bleed air through diffuser tubes to the inner surfaces of the nacelle
inlet lip. The engine air temperature (TZ`2) and pressure (Pn)
sensor masts are antiiced by electrical heating elements installed in
the base of the masts. Each engine anti-ice system is independently
operated and consists of a PZ-2/T~-2 mast heating element, a nacelle
anti-ice control valve, a pressure switch, a control switch, an amber
NACHT light, and associated aircraft wiring and bleedair plumbing.
Control drcuits are powered by 28 VDC supplied through the 75-
ampL andRNACHT circuit breakers on the pilot's and copilot's circuit
breaker panels respectively.
NAC HEAT SWITCHES
The left and right engine and nacelle inlet anti-ice systems are independently
controlled through theNAC HEAT switches in the ANTIICE
group on the center switch panel. Each NAC HEAT switch has
two positions: On (L or R) and OFF. When a NAC HEAT switch is
placed in the On (L or R) position, the associated P12/T17 sensor element
is energized, the associated solenoid-operated nacelle anti-ice
control valve opens, and thegreen NACHT ON annunciator will illuminate.
Engine bleed air flows through the open valve to diffuser
tubes which distribute the heated air on the inner surface of the nacelle
inlet lip. Since the solenoid-operated control valve is energized
dosed, nacelle inlet anti-ice protection is operational in the event of
an electrical system failure.
6-2
PM-121
Original
Learjet 31A
Pflot'e Manual
NAC HT ON LIGHT
The green NAC HT ON light, on the glareshield annunciator panel,
provides the crew with visual indication that one or both nacelle heat
systems are on. The NAC HT ON light will illuminate anytime a
NACHEAT Switch is in theOn position.
L AND R NAC HT LIGHTS
The amber L and R NAC HT lights on the glareshield annunciator
panel provide the crew with visual indication of a nacelle inlet antiice
system malfunction. The lights are operated by pressure switches
in the associated nacelle inlet bleed air plumbing. Illumination of a
NAC HT light when the associated NAC HEAT switch is in the On
position, indicates that insufficient pressure is being applied to the engine
anti-ice system due to a malfunction of a nacelle anti-ice control
valve. Illumination of a NAC HT light when the associated NAC
HEAT switch is in the OFF position, indicates that bleed air pressure
is being applied to the engine anti-ice system due to a malfunction of
a nacelle anti-ice control valve.
WING ANTI-ICE
The wing anti-ice systems utilize engine bleed air directed through
diffuser tubes in each wing leading edge. The heated air is distributed
to the wing root and leading edge and then allowed to exit into the
center wing/wheel well area. The system consists of wing diffuser
tubes, an overheat warning light, a thermoswitch, a wing temperature
sensor, an anti-ice shutoff valve, a wing temperature indicator, a system
switch, and associated aircraft wiring. Electrical power for system
operation is 28 VDC supplied through the 7.5-amp WING HT circuit
breaker on the copilot's circuit breaker panel.
STAB WING HEAT SWITCH -WING HEAT FUNCTION
The wing anti-ice system is controlled through the STAB WING
HEAT switch located in the ANTI-ICE group on the center switch
panel. The switch has two positions: On (STAB WING HEAT) and
OFF. When the STAB WING HEAT switch is set On, the anti-ice shutoff
valve control solenoid will close allowing pressure to build within
the valve reference chambers. The building pressure will open a valve
in the bleed-air airstream and allow heated air to flow through the
ducting into the wing diffuser tubes. In the event of an electrical system
failure, the valve will shut off the bleed air flow and wing anti-ice
protection will not be available.
PM-121
6-3
Change 1
Pilovs Manual
Learjet 31A
WING ANTI-ICE SYSTEM
Figure 6-1
6-4
PM-121
Original
Learjet 31A
Pilots Manual
WING TEMP INDICATOR
The WING TEMP indicator, located in the ANTI-ICE group on the
　
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