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recognize icing conditions and alert the appropriate Bleed Management Controllers.
The BMCs will then activate the wing anti-ice systems and alert the stall protection
system. The ice detection system will operate a relay in the anti-ice control panel to
activate cowl anti-ice. The system will also recognize single-engine conditions or
system failures and configure all appropriate valves to ensure sufficient heat for antiicing.
All systems can also be activated manually. Built-in initiated tests are
continuously monitoring the system.
GENERAL
Thermal anti-icing, electrical anti-icing, and ice detection and alerting systems are
provided for airplane ice and rain protection. Selections for anti-ice functions are made
on the ANTI-ICE panel located on the overhead panel.
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
ice detection probe and signal the Bleed Management Controllers to activate wing
anti-ice. The ice detection system will 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 prevents the formation of ice on the
wing leading edge, slats and the engine intake cowls.
ANTI-ICE
L COWL WING R COWL
WING XBLEED
AUTO AUTO AUTO
OFF ON OFF ON OFF ON
AUTO
FROM L FROM R
GX_03_001
P I LOT T R A I N I N G GU I D E
ANTI-ICE SYSTEM (IAMS)
3-2 For Training Purposes Only
Sept 04
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.
The heaters are automatically turned ON after engine start.
NOTE
All heaters are tested ON when AC power is applied. It is
recommended to remove all probe covers prior to starting APU
or connecting external power.
Selections for the Pilot’s and Copilot’s Windshield and Side Window heating are made
on the WINDSHIELD HEAT panel located on the overhead panel.
Anti-ice system data is displayed on the BLEED/ANTI-ICE synoptic page and any
faults or failures are displayed on the EICAS and recorded by the CAIMS.
WINDSHIELD HEAT
L
ON
OFF/
RESET
R
ON
OFF/
RESET
GX_03_002
For Training Purposes Only
Sept 04
3-3
P I LOT T R A I N I N G GU I D E
ANTI-ICE SYSTEM (IAMS)
BLEED/ANTI-ICE SYNOPTIC
For more information on BLEED System, refer to Chapter 13, IAMS.
GX_03_003
BLEED / ANTI-ICE
APU
LP
AIR
COND
HP
L
LP
HP 26
PSI
26
PSI
R
Wing Anti-ice
Crossbleed
Valve (CBW)
Cowl Anti-Ice
Valve (CAI)
Open-Close Type
Wing Anti-Ice
Valve (WAIV)
Modulated by
BMC
P I LOT T R A I N I N G GU I D E
ANTI-ICE SYSTEM (IAMS)
3-4 For Training Purposes Only
Sept 04
ANTI-ICE PANEL
Controls are provided on the ANTI-ICE panel located on the overhead panel.
ANTI-ICE
L COWL WING R COWL
WING XBLEED
AUTO AUTO AUTO
OFF ON OFF ON OFF ON
AUTO
FROM L FROM R
GX_03_004
L & R COWL Selectors
OFF
AUTO
ON
• Disarms the cowl anti-ice system and closes the
associated valves.
• Arms the cowl anti-ice system to enable
automatic operation when ice is detected.
• Activates cowl anti-ice system independently of ice
detector signals.
–
–
–
WING Selector
OFF
AUTO
ON
• Disarms the wing anti-ice system and closes
the associated valves.
• Arms the wing anti-ice system to enable
automatic operation when ice is detected. System
inhibited on the ground until 400 feet above field
elevation.
• Activates wing anti-ice system independently
of ice detector signals.
–
–
–
WING XBLEED Selector
FROM L
AUTO
FROM R
• – Closes the RH WAIV and opens
the CBW independently of the BMC.
• Arms the CBW to enable automatic
opening by the BMC in the event of a failure in
one WAIV.
• Closes the LH WAIV and opens
the CBW independently of the BMC.
–
–
For Training Purposes Only
Sept 04
3-5
P I LOT T R A I N I N G GU I D E
ANTI-ICE SYSTEM (IAMS)
DESCRIPTION
ICE DETECTION
The airplane is fitted with two ice detectors, one on each side of the front fuselage.
　
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