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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 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
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
The ice detectors emit icing signals to the following:
· ANTIICE
panel (cowl antiice
relay), for activation of the cowl antiicing
system (AUTO).
· BMC for activation of the wing antiicing
system (AUTO). The AUTO operation of WING
ANTIICE
is inhibited during takeoff
until the airplane is >400 feet above field elevation.
· Stall protection system, to change stick shaker control, if an ice detector has failed and to the
BMC for fault indication. For more information on Stall Protection, refer to Chapter 10 FLIGHT
CONTROLS.
Once deiced,
the probe cools within a few seconds and is ready to sense ice buildup again. This
cycling process is repeated as long as the ice detector remains in an icing environment.
The ice detectors are not capable of operating at low airspeeds of less than 29 knots IAS, therefore
they cannot be used to detect icing when the airplane is on the ground.
ICE AND RAIN PROTECTION
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
14−10−4
ICE DETECTION INDICATION
If ice is detected and the ANTIICE
system is turned OFF, a message is displayed on EICAS.
GF1410_008
ICE
AUTO AUTO
OFF ON
AUTO
L COWL WING R COWL
ANTI−ICE
OFF ON OFF ON
If ice is detected and the ANTIICE
system is turned to ON or AUTO, the following message is
displayed on EICAS.
GF1410_009
OR ICE
AUTO AUTO
OFF ON
AUTO
L COWL WING R COWL
ANTI−ICE
AUTO AUTO
OFF ON
AUTO
L COWL WING R COWL
ANTI−ICE
OFF ON
OFF ON
OFF ON
OFF ON
If both ice detectors are failed, a message is displayed on EICAS and the crew must revert to manual
selection of cowl and wing antiice.
GF1410_010
ICE DETECTOR FAIL
AUTO AUTO
OFF ON
AUTO
L COWL WING R COWL
ANTI−ICE
OFF ON OFF ON
If a single ice detector fails, a message is displayed on EICAS. If ice is detected by the other ice
detector, the Stall Protection system enables a change in stick shaker control and a message is
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