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integral heating element in the vane.
Auxiliary Angle-Of-Attack Vane
One auxiliary angle-of-attack vane is located on the right side of the nose and contains
two integral heating elements, one for the vane and the other for the base.
Total Temperature (TAT) Probe
One total air temperature sensor is located on the right side of the aircraft and contains
an integral heating element.
Air Data Sensor Heat Controllers (ADSHCs)
The ADSHCs provide control of AC power to respective heating elements and detect
system failures. Should any ADSHC lose control power, all probes connected to the
failed ADHSC will receive full AC power (fail-safe ON). Should a fault condition be
detected by any ADSHC, the applicable EICAS caution message(s) will be displayed.
ICE AND RAIN PROTECTION
For Training Purposes Only
May 03
14-11
P I LOT T R A I N I N G GU I D E
Probe Switches
The L and R PROBES switches are used to control AC power to the probe heaters via
the ADHSCs. The L PROBES switch controls the left pitot-static probe, the standby
pitot-probe, the left angle-of-attack vane and the left static port. The R PROBES
switch controls the right pitot-static probe, the total air temperature probe, the right
angle-of-attack vane, the right static port and the auxiliary angle-of-attack probe.
Electrical power is applied to the respective heaters under the following conditions:
• L (R) PROBES switch ON, and
• any one engine generator on-line or PAX door is locked
With the L and R PROBES switches selected ON, all probes are heated and no EICAS
caution messages are displayed.
ICE AND RAIN PROTECTION
14-12 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
Ice Detection System
Description
The ice detection system alerts the flight crew of icing conditions. The system consists
of two independent ice detector/microprocessors, one installed on each side of the
forward fuselage.
Ice Detectors
Figure 14-6
Components and Operation
Each ice detector consists of a probe and a microprocessor, which operate
continuously (no switch control). The probe extends into the airstream to detect icing
conditions. The microprocessor is a self-contained unit and interfaces with the data
concentrator units (DCUs) to provide the flight crew with a visual indication of icing
conditions.
The ice detector probes vibrate at high frequency. When icing conditions are
encountered, ice accumulation on the probe causes a frequency change in the probe.
The microprocessor detects the frequency change, triggers an ICE advisory or caution
EICAS message on the EICAS and begins the probe’s deicing cycle. During probe
deicing, the probe is electrically heated for 5 seconds followed by 55 seconds with no
heat. The cycle repeats automatically as long as a frequency change is detected. When
no ice accumulation is detected, the heat cycle ceases and the ICE message on the
EICAS is removed.
Ice Detection Test
Selecting the TEST switch on the ANTI-ICE Panel to the DET position checks the
circuitry of the ice detectors.
P604_14_007
ICE AND RAIN PROTECTION
For Training Purposes Only
May 03
14-13
P I LOT T R A I N I N G GU I D E
Controls and Indicators
The ANTI-ICE Panel provides the system control switches and switch/lights, and the
EICAS Primary and Secondary displays provide the system warning/caution and
advisory messages respectively (see Figure 14-7, Tables 14-1 and 14-2).
ANTI-ICE Panel
ANTI-ICE Panel
Figure 14-7
OFF
ON
OFF
ON
ANTI-ICE
STBY
OFF
NORM
LOW LOW
OFF/
RESET
HI HI
WING COWL
L R R
R
L
L
WSHLD/WIND PROBES
TEST
L HEAT
R HEAT
ON
TEST
DET
WING
ON
OFF/
RESET
D
W
WING ANTI-ICE Switch
STBY
OFF
NORM
– Wing anti-ice valves cycle
open and closed at a predetermined
temperature (49°C /120 F open,
82°C/180 F closed).
– Wing anti-ice valves close.
– Wing anti-ice
(88°C /190 F).
°
°
controller
modulates wing anti-ice valves to
maintain a constant wing leading
edge temperature °
Wing HEAT Lights
Illuminated – Indicates
sufficient heat on respective
wing for anti-icing.
DET/WING TEST Switch
(spring-loaded to center
position)
DET
WING
– Initiates test of the
ice detectors.
– Initiates test of the
wing anti-ice controller and
overheat sensors.
　
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