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DESCRIPTION
The Challenger 300 has two ice detectors, one on each side of the fuselage just above the nose landing gear doors. Each detector is supplied with 28 VDC and continuously monitors internal circuits and components for failure conditions.
COMPONENTS AND OPERATION
The ice detector uses a vibrating probe to detect the presence of icing conditions. Two detectors provide system redundan-cy; only one signal is needed to generate an EICAS message.
The ice detector probes vibrates at high frequency. As the ice detector enters an icing environment, ice collects on the sens-ing probe causing the frequency of the sensing probe to decrease. At the same time the ice detector de-ices the unit strut and probe through internal thermal heaters. Shedding the ice on the probe returns the vibration frequency of the probe to a non-icing value that allows the detection system to reassess if ice is accumulating. When the ice is removed, the heaters are de-energized. As ice builds again on the probe, the heater are reenergized and the process is repeated.
When ice is detected the following will occur:
-An amber ice icon is displayed on the PFD if the anti-ice systems are off
-An ICE DETECTED (C) CAS message is displayed if the anti-ice systems are off
-An ICE DETECTED (A) CAS is displayed if the anti-ice systems are on
A caution ICE DETECTOR FAIL is displayed on the EICAS when both ice detectors have failed. An advisory ICE DE-TECTOR FAULT is displayed on the EICAS when one of the ice detectors is failed.
Each ice detector is provided with a power on test capability as well as a continuous built in and pilot initiated test capa-bility. To initiate a test of the system, select ICE DET on the SYSTEMS TEST panel and push the test switch. During the test sequence, an internal check of the electronics, probe heater, and CAS messages will be performed.
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
14-01-02 WING ANTI-ICE SYSTEM
DESCRIPTION
The wing anti-icing system heats the leading edge of the wing by heating the surfaces with high-pressure bleed-air from the engines. The left and right wings are normally heated with bleed-air from the respective engine, however the capability exists to provide bleed-air from either engine to both wings.
A WING push button switch, located on the ANTI-ICE control panel, is used to operate the wing anti-ice system. The WING SOURCE rotary switch on the ANTI-ICE control panel allows the pilot to select FROM L, NORM, or FROM R as the source of anti-icing bleed-air.
The anti-ice ducting is continuously monitored for bleed-air leakage.
COMPONENTS AND OPERATION
INTEGRATED AIR SYSTEM CONTROLLER (IASC)
Two dual-channel integrated air system controller (IASC) controls the operation of the wing anti-ice and leak detection systems.
Each IASC receives data from dual temperature sensors located in the inboard and outboard section of each leading edge. The IASC uses the sensor data to independently control the amount of bleed-air supplied to each wing to ensure that the leading edges are maintained in the correct temperature range.
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本文链接地址：庞巴迪挑战者300公务机机组操作手册 Bombardier Challenger-防冰和排雨(3)
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