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switch positions, engine generator operation, and passenger door status.
ICE AND RAIN PROTECTION
Description
Vol. 2 14−10−8
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AIR DATA PROBES AND SENSORS ANTI-ICING (CONT'D)
Air Data Probes and Sensors Anti-Icing System
Figure 14−10−5
Components and Operation
Primary Pitot-Static Probes
There are two pitot-static masts, one on either side of the nose. The pitot-static mast consists of
a head and mounting base. The mast has two heaters, one in the head and the other in the
base.
Standby Pitot Probe
There is one standby pitot probe on the left side of the nose, which contains one integral heating
element.
ICE AND RAIN PROTECTION
Description
Vol. 2 14−10−9
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AIR DATA PROBES AND SENSORS ANTI-ICING (CONT'D)
Alternate Static Ports
Two flush alternate static ports are located on each side of the aircraft, and each contains an
integral heating element.
Angle-of-Attack (AOA) Vanes
Two angle-of-attack vanes are located on each side of the aircraft, and each contains an
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 Air Temperature (TAT) Probe
One total air temperature sensor is located on the right 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 also detect
system failures. Should any ADSHC lose control power, all probes connected to the failed
ADSHC 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.
Probe Switches
The L and R PROBES switches are used to control AC power to the probe heaters via the
ADSHCs. 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 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 AND RAIN PROTECTION
Description
Vol. 2 14−10−10
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
ICE DETECTION SYSTEM (CONT'D)
Ice Detectors
Figure 14−10−6
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 ICE caution EICAS message, 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.
CONTROLS AND INDICATORS
The ANTI-ICE panel provides the system control switches and switch/lights, and the EICAS page
provides the system warning/caution and advisory messages respectively.
ICE AND RAIN PROTECTION
Description
Vol. 2 14−10−11
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
CONTROLS AND INDICATORS (CONT'D)
　
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