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庞巴迪挑战者605公务机机组操作手册 CL605-防冰和排雨 ICE and RAIN PROTECTION(6)

时间:2011-10-29 11:01来源:蓝天飞行翻译 作者:公务机
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L (R) PROBES switch ON; and

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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  14.10.11 
Oct 05/06 


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  14.10.12 
Oct 05/06 


ANTI-ICE Panel
Figure 14.10.7

 

 ICE AND RAIN PROTECTION Description  Vol. 2  14.10.13 
Oct 05/06 


AURAL WARNING
MEANING
(IF ANY)

Bleed air leak detected in left and/or right fuselage or
“ANTI-ICE DUCT”

wing anti-ice ducts.
Overheat condition detected in left and/or right wing
“WING OVERHEAT”

leading edge.
With wing anti-ice selected on, insufficient pressure and temperature in
respective wing leading edge for anti-icing.

Wing anti-ice sensor failure detected (control and/or overheat sensor).
Wing anti-ice is selected on with sufficient heat and pressure available for
anti-icing.
Wing and cowl anti-ice selected on and sufficient heat/pressure available for

anti-icing.
Successful test of the wing anti-ice system.
 
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