ICE AND RAIN PROTECTION
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 14-01-01
INTRODUCTION
The wing leading edges and the engine intake cowls are heated using engine bleed air. The windshields, windows and the
air data probes are heated using electrical power. Anti-icing of the aircraft tail surface is not required.
Two ice detectors provide indication to the flight crew of icing conditions.
The anti-ice protection system (AIPS) is controlled by the integrated air system controllers (IASC) with indications displayed
on the EICAS. The ANTI ICE synoptic display provides an overview of status of the pneumatically operated antiicing
systems.
REV 1
ICE AND RAIN PROTECTION
Volume 2 Flight Crew Operating Manual Sep 13/2004
14-01-02 CSP 100-6 REV 1
ICE DETECTION SYSTEM
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 redundancy;
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 sensing
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 DETECTOR
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 capability.
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.
CFO1401002_004
ELECTRICAL
CONNECTOR
MOUNTING
FLANGE
STRUT
VIBRATING
PROBE
ICE AND RAIN PROTECTION
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 14-01-03
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.
BLEED LEAK DETECTION SYSTEM
To detect hot air leaks from the bleed system, the anti-ice ducts are monitored by the leak detection loops. The bleed leak
detection system protects components and structure against over heating and fire hazards. Ducting is divided into four distinctive
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：Bombardier_Challenger_Global_00-Ice_and_Rain_Protection(2)
