曝光台 注意防骗
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CONDITIONED AIR
VALVE
CHECK VALVE
TEMP/PRESS SENSOR
ELECTRICAL
LEGEND
1. L BLEED OVHT
2. R BLEED OVHT
3. PACK HIGH FLOW
4. L EMER PRESS
5. R EMER PRESS
6. L PYLON OVHT
7. R PYLON OVHT
PACK
HI FLOW
EICAS MESSAGES
F 40-060000-001-01
Pilot’s Manual
6-4 PM-132A
ANTI-ICE SYSTEMS
Aircraft anti-ice protection is provided through the use of electrically
heated and engine bleed air heated anti-ice systems. Electrically heated
systems include the pitot-static probes, total air temperature probe, engine
inlet air temperature/pressure sensors, stall warning vanes, and
windshields. Engine bleed air is utilized to provide anti-icing for the
leading edge surfaces of the wings, horizontal stabilizer, and engine nacelle
inlets. The engine fan spinners are unheated.
ICE DETECTOR SYSTEM
The ice detector system is installed to detect an icing condition and notifies
the crew by illumination of the ICE DETECTED amber or white
CAS described below. The ice detector system is always capable of detecting
ice, provided aircraft electrical power is available. A self-test of
the ice detector system is conducted every time aircraft power is turned
on, and the ICE DETECT circuit breaker is engaged. The ice detector
system receives 28-vdc power from the right essential bus through the
10-amp ICE DETECT circuit breaker on the copilot’s circuit breaker
panel (ANTI-ICE group).
The ICE DETECTED white CAS illuminates when ice is detected, the
aircraft is airborne, and the following anti-icing systems are turned on:
- WING/STAB anti-ice selected ON.
- L and R NAC anti-ice selected ON and inlet pressure is present.
The ICE DETECTED amber CAS illuminates when ice is detected, the
aircraft is airborne, and any of the following anti-icing systems are
turned off:
- WING/STAB anti-ice selected Off,
or
- L or R NAC anti-ice selected Off.
The following CAS illuminations are specific to the ice detection
system:
CAS Color Description
ICE DET FAIL Amber The ice detection system has failed.
ICE DETECTED Amber Ice is detected and the appropriate (left and
right nacelle heat, and wing/stab heat) antiice
systems are not turned on.
ICE DETECTED White Ice is detected and the appropriate (L and R
nacelle heat, and wing/stab heat) anti-ice
systems are turned on.
Pilot’s Manual
PM-132A 6-5
WING INSPECTION LIGHT
The wing inspection light, located on the right forward fuselage, may
be used to visually inspect the right wing leading edge for ice accumulation
during night operations. The light is illuminated by depressing
the WING INSP momentary switch located in the LIGHTS group of the
center switch panel. The light illuminates a black dot on the outboard
wing leading edge to enhance visual detection of ice accumulation.
Power is supplied from the R MAIN bus through the 3-amp WING
INSP circuit breaker on the copilot’s circuit breaker panel (LIGHTS
group).
ENGINE AND NACELLE INLET ANTI-ICE
The engine and nacelle inlet anti-ice system provides anti-ice protection
for the nacelle inlets and the engine inlet air pressure/temperature sensors.
The engine inlets are anti-iced by directing engine bleed air
through piccolo tubes to the inner surfaces of the nacelle inlet lip. After
circulating around the inlet lip, excess bleed air is vented overboard
through a hose at the bottom of the nacelle lip. The engine inlet air pressure/
temperature sensors are anti-iced by integral heating elements
whenever the respective L or R NAC anti-icing system is selected ON.
Each engine and nacelle anti-ice system consists of a bleed air duct, a
nacelle anti-ice pressure switch, a nacelle anti-ice pressure regulating
shutoff valve and a nacelle anti-ice switch. All anti-ice systems require
electrical power to operate except the engine nacelle inlet heating systems
which fail on when electrical power is not available to the respective
nacelle anti-ice pressure regulating shutoff valve. Electrical power
is provided from the L and R MAIN buses through the respective NAC
circuit breakers located within the ANTI-ICE group [L and R HEAT] on
the pilot’s and copilot’s circuit breaker panels.
System activation is indicated by a NAC green EI illuminated next to
each engine ITT display. This illumination indicates that the respective
L or R NAC switches are ON and that adequate bleed air pressure is being
supplied to each nacelle lip.
An amber NAC illumination indicates that the respective L or R NAC
switches are on with inadequate bleed air pressure being supplied to
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