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the Engine Interface Unit (EIU) when the related engine
is not running.
If you have to pull the EIU power supply circuit
breaker, the related ENGINE OIL LOW PRESS AND GROUND
relays are deenergized, this will cause related probes
and static ports to be heated.
POWER SUPPLY
The PHC is supplied with 28 Volts DC.
The static ports are supplied with 28 Volts DC ; the
AOA sensor, TAT sensor and pitot probe are supplied
with 115 Volts AC.
If you pull the PHC power supplied circuit breaker,
the related probes and static ports will be fully
heated.
AIR DATA/INERTIAL REFERENCE UNIT (ADIRU)
In case of a probe heating fault the PHC sends a
discrete output to its respective ADIRU which in turn
transmits the failure to the Flight Warning Computers
(FWCs).
CENTRALIZED FAULT DISPLAY INTERFACE UNIT (CFDIU)
The CFDIU is connected to the PHC for fault system
transmission.
The PHC is a type 2 system (ARINC 429 output,
maintenance test discrete input).
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30 - ICE AND RAIN PROTECTION
30-31-00 PROBES ICE PROTECTION SYSTEM
WARNINGS
CONTENTS:
Single Probe Failure
Probe Heat Computer Failure
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30-31-00 PROBES ICE PROTECTION SYSTEM
COMPONENTS
CONTENTS:
Probe Heat Computer
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PROBES ICE PROTECTION SYSTEM COMPONENTS
PROBE HEAT COMPUTER
IDENTIFICATION
FIN : (PHC1) 6DA1, (PHC2) 6DA2, (PHC3) 6DA3
LOCATION
ZONE : (PHC1 and PHC3) 121, (PHC2) 122
DESCRIPTION
PHC is a type 2 computer.
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30-42-00 WINDOWS ANTI-ICING AND DEFOGGING
SYSTEM PRESENTATION
CONTENTS:
Function
Control
Window Heat Computer (WHC)
Caution
Self Examination
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WINDOWS ANTI-ICING AND DEFOGGING SYSTEM
PRESENTATION
FUNCTION
Windshields and side windows are electrically
heated to maintain clear visibility in icing or
misting conditions.
The system is made up of two independent systems.
Each one includes one Window Heat Computer (WHC),
　
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