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FROM L FROM R
WING XBLEED
Ice Detection
Independent ice detection probes (2), located on the fuselage, sense the formation of ice. If ice is
detected, the ice detectors automatically turn on the electrical heat to the various probes, signalling
the Bleed Management Controllers (BMC) to activate wing anti-ice and operate a relay in the
ANTI-ICE Control panel to activate cowl anti-ice.
Pneumatic Anti-Icing
Hot air anti-icing, provided by engine bleed air, through piccolo ducting, wing anti-ice valves and cowl
anti-ice valves, prevents the formation of ice on the wing leading edge, slats and the engine intake
cowls.
Electrical Anti-Icing
Electrical anti-icing is provided for Pitot Static Probes, Ice Detectors, Total Air Temperature (TAT)
Probes, Heater/Brake Temperature Monitoring Units (HBMUs) and Angle of Attack (AOA) Vanes.
Selections for the Pilot’s and Copilot’s Windshields and Side Windows heating, are made on the
WINDSHIELD HEAT panel, located on the overhead panel.
GF1410_002
R
WINDSHIELD HEAT
OFF/ ON
RESET
L
OFF/ ON
RESET
Anti-ice system data is displayed on the BLEED /ANTI-ICE synoptic page and any faults or failures
are displayed on EICAS and CAIMS.
ICE AND RAIN PROTECTION
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
14−10−1
BLEED/ANTI-ICE SYNOPTIC
GF1410_003
WING ANTI-ICE
CROSS BLEED VALVE
(CBW)
WING ANTI-ICE VALVE
(WAIV)
COWL ANTI-ICE VALVE
(CAIV)
For more information on BLEED System, refer to Chapter 2, AIR CONDITIONING and PRESSURIZATION.
LP
HP
L R
APU
HP
LP
COND
AIR
BLEED/ANTI-ICE
40
PSI
40
PSI
COMPONENTS
CBW
CAIV
WAIV
BMC
ANTI-ICING
TEMPERATURE
SENSORS
ICE
DETECTORS PICCOLO
DUCTS
GF1410_004
TO EICAS
ICE AND RAIN PROTECTION
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
14−10−2
ANTI-ICE PANEL
Controls are provided on the ANTIICE
panel, located on the overhead panel.
L & R COWL Selectors
associated valves.
operation, when ice is detected by the ice detector.
detector signals.
WING Selector
and closes the associated valves.
to enable automatic operation, when ice is
System inhibited on the ground until 400 feet
above takeoff
field elevation.
independent of ice detector signals.
WING XBLEED Selector
the CBW, independent of BMC commands.
operation in the event of a failure in one WAIV.
the CBW, independent of BMC commands.
GF1410_005
− Disarms the cowl antiice
system and closes the
− Arms the cowl antiice
system, to enable automatic
− Activates cowl antiice
operation, independent of ice
OFF
AUTO
ON
FROM L
AUTO
FROM R
− Closes the RH WAIV and opens
− Closes the LH WAIV and opens
OFF
AUTO
− Activates wing antiice
operation,
− Disarms the wing antiice
system
− Arms the wing antiice
system,
ON
detected by the ice detector.
− Arms the CBW to enable automatic
AUTO
OFF ON
AUTO
OFF ON
AUTO
OFF ON
L COWL WING R COWL
ANTI−ICE
AUTO
FROM L FROM R
WING XBLEED
ICE AND RAIN PROTECTION
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
14−10−3
ICE DETECTION
The airplane is fitted with two ice detectors, one on each side of the front fuselage.
VIBRATING
MOUNTING FLANGE
ELECTRICAL
STRUT
GF1410_006
PROBE CONNECTOR
The ice detector incorporates a vibrating probe, that maintains a preset frequency (40 KHz), to detect
icing conditions. As the ice detector enters an icing environment, ice collects on the vibrating probe.
The added mass of ice causes the frequency of the probe to decrease, .010 inch thickness of ice
equals a 65 HZ decrease and immediately the ice detector deices
the strut and the probe through
internal heaters. Heater power is applied until the frequency rises to a predetermined set point, plus a
time delay factor (60+/− 5 seconds) to ensure complete deicing.
If an additional icing/deicing
cycle
occurs during that time interval, the 60 seconds cowl and wing antiice
activation period is begun
again.
VIBRATING PROBE
STRUT HEATERS
PROBE HEATER
SECTIONAL VIEW
GF1410_007
　
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