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 There are three PHCs, one per probe channel:
 - PHC 1,
 - PHC 2,
 - PHC 3 (Channel 3 does not include the TAT sensor).
 The PHC is supplied with 28VDC. Three ports enable the PHC position
 to be selected.
 The PHC controls the temperature of the probes and sensors
 according to acquisition of discrete aircraft information. This
 function is achieved by a hardware logic device independent of the
 software.
 (2) Input - Output
 The PHC acquires 10 discrete inputs of standard type (ground/open):
 - 4 from the Landing Gear Control and Interface Unit (LGCIU), 2
 ground/flight information, and 2 from the LGCIU validity,
 - 2 from the EIVMU, engine running or not,
 - 1 for the ON control,
 - 1 from the CFDS for the maintenance test,
 - 1 for the reset function,
 - 1 for the low speed warning (V greater than 50 kts).
 The PHC generates 5 discrete outputs to the Flight Warning Computer
 (FWC) via the Air Data/Inertial Reference Unit (ADIRU):
 - 1 discrete output directly to the System Data Acquisition
 Concentrator (SDAC),
 - 1 for the indication of TAT sensor heating or not,
 - 1 for the indication of the pitot probe heating fault,
 - 1 for the indication of the L static probe heating fault,
 - 1 for the indication of the R static probe heating fault,
 - 1 for the indication of the AOA sensor heating fault,
 - heating availability directly to the SDAC.

 

 Probe Ice Protection - TAT Sensor
 Figure 008
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 The PHC transmits one ARINC 429 low-speed data bus for fault message to the CFDS.
R  7. Operation/Control and Indicating________________________________ 
R  (Ref. Fig. 009, 010, 011, 012) 
R R  A. Operation The conditions: 
R  - ENG 1 RUNNING 
R  - or ENG 2 RUNNING 
R R R R R R R R R  - or PROBE/WINDOW HEAT pushbutton swith in ON configuration (anticipated heating) cause heating of the probes given below: . static probe, . AOA sensor, . pitot probe. There are two heating levels for the pitot probe: * on the ground: half-wave heating, * in flight: full-wave heating. The input receives the heating command. . TAT sensor in flight.
 B. Control and indicating (Ref. Fig. 013)
 (1) Monitoring The PHC monitors heating of the static probes, AOA sensor, pitot probes and TAT sensor. Current detection with a preset threshold is provided for monitoring purposes. Low heating or overcurrent or heating loss or discrepancy between the ground and flight information sent by the LGCIUs triggers a warning. Monitoring of the TAT sensors is inhibited on the ground. A monitoring system activates a warning when heating is incorrect. Warning is triggered as follows:
 (a) For pitot probe - in flight when the current I is lower than 0.9 A or greater than 6 A, - on ground when the current I is lower than 0.4 A or greater than 4 A.
 (b) For TAT sensor When the current I is lower than 0.8 A or greater than 4 A.
 (c) For AOA sensor When the current I is lower than 0.12 A or greater than 5 A.

 

 Fault of Pitot Probes 1
 Figure 009
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 Fault of Pitot Probes 2
 Figure 010
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 Fault of Pitot Probes 3
 Figure 011
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 Fault of Probes 1 (2, 3) Heat
 Figure 012
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 Probe Ice Protection-Schematic
 Figure 013
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 (d) For L and R static probes When the current is lower than 1.3 A or greater than 4 A. The PHC serves to:
 -identify the faulty element(s),
 -memorize the faulty element.
 (2) Indication The PHC continuously emits signals via the ARINC 429 bus (low speed). A discrete output (one per probe) informs the ADIRU of associated probe channel of the heating fault. Then, the ADIRU informs the Flight Warning Computer (FWC).
　
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