Ice Protection of Probes 1 - Schematic
Figure 002
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Ice Protection of Probes 2 - Schematic
Figure 003
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R Ice Protection of Probes 3 - Schematic Figure 004
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-------------------------------------------------------------------------------
|COMPONENT/FUNCTION | CIRCUIT | BUS |
| | BREAKER | |
|-------------------------------------------------|--------------|------------|
R | |----------------------------------|--------------|------------|
R | | Supply of pitot probe heating | 3DA3 | 103XP-C |
R | PROBES |----------------------------------|--------------|------------|
R | 3 | Supply of angle of attack sensor | 4DA3 | 103XP-C |
R | | heating | | |
R | |----------------------------------|--------------|------------|
R | | Supply of static probe heating | 5DA3 | 103PP |
R -------------------------------------------------------------------------------
R
5. Interface_________
R (Ref. Fig. 002, 003, 004)
R The ice protection system of the probes is associated with:
R - the Engine Interface Unit (EIU) (Functional Interfaces),
R - the shock absorbers of the landing gear,
R - the Centralized Fault Display Interface Unit (CFDIU),
R to control and select the heating mode of the probes.
6. Component Description_____________________
R A. Probes
R (1) Pitot probe
R (Ref. Fig. 005)
R Power is applied to:
R - the main portion of the detection tube of total pressure,
R - the inner surface of the cavity located in the mast.
R Power is supplied with 115 VAC nominal.
R Heating of the pitot probe is reduced on the ground.
R The PHC automatically controls the changeover of the probe heating
R level.
R (2) Static probe
R (Ref. Fig. 006)
R Power is applied to the periphery of the orifice.
R Power is supplied with 28VDC nominal.
R (3) AOA sensor
R (Ref. Fig. 007)
R The AOA sensor is of the vane type.
R Power is applied to the internal solid-state heaters of the vane.
R Power is supplied with 115VAC nominal.
Probe Ice Protection - Pitot Probe
Figure 005
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Probe Ice Protection - Static Probe
Figure 006
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Probe Ice Protection - Angle of Attack Sensor
Figure 007
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R (4) TAT sensor
R (Ref. Fig. 008)
R Power is applied to the leading edge of the air inlet.
R Power is supplied with 115VAC nominal.
R Heating is cut off on the ground. The PHC automatically controls this
R changeover.
B. PHC
(Ref. Fig. 002, 003, 004)
(1) The PHCs are installed in the avionics compartment.
The PHC controls and monitors heating of the probes given below:
- one pitot probe,
- two static probes,
- one AOA sensor,
- one TAT sensor.
The PHC identifies and memorizes the failures.
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本文鏈接地址：A320飛機(jī)維護(hù)手冊 AMM ICE AND RAIN PROTECTION 防冰和排雨1(88)
