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 B. AIR COND Panel 30VU On the AIR COND panel, three BLEED pushbutton switches control the related engine and APU bleed valves. Two ENG BLEED pushbutton switches (ENG 1 BLEED and ENG 2 BLEED) control the related engine bleed pressure regulator valves and HP bleed valves. Each ENG BLEED pushbutton switch has an OFF and a FAULT legend. The APU BLEED pushbutton switch controls the APU bleed valve. It has an OFF and a FAULT legend.
 C. Temperature and Pressure Monitoring (Ref. 36-21-00) Temperature sensors and pressure transducers monitor the temperature and the pressure of the engine bleed air. They transmit temperature and pressure data to the Bleed Monitoring Computers (BMCs) which are installed in the avionics compartment. Valve position switches transmit the valve position data to the BMCs. The BMCs transmit the bleed-air temperature and pressure data and the valve position data to the System Data Aquisition Concentrators (SDACs). The SDACs transmit the data to the lower ECAM display unit. The BLEED page of the lower ECAM display unit shows:
 -
the valve positions (HP bleed valves, bleed pressure regulator valves, crossbleed valve and APU bleed valve),

 -
the duct temperature (downstream of the precooler),

 -
the duct pressure (downstream of the engine bleed pressure regulator valves).

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 D. Overheat Detection (Ref. 36-22-00) The overheat detection system adjacent to the bleed-air ducts monitors the ducts for leaks and bursts. It automatically shuts off the related bleed air supply if a leak or burst occurs on a duct. The overheat detection loops are installed adjacent to the pneumatic ducts in:
 -
the fuselage,

 -
the belly fairing,

 -
the wings,

 -
the engine pylons.

 **ON A/C ALL
 4. Power Supply
____________ (Ref. Fig. 009, 010) The indicating system gets electrical power from the aircraft DC system which supplies 28VDC through circuit breakers 2HA1, 2HA2, 3HA1 and 3HA2 to:
 -
the BMC1 and BMC2,

 -
the relays of the AIR COND overhead panel,

 -
the ENG/APU FIRE panel (Ref. 26-00-00),

 -
the pressure transducers.

 5. Component Description
_____________________
 A. BMC
 (1) Function Two BMCs (BMC1 and BMC2) are installed in the FWD avionics compartment. They monitor and control the bleed air system permanently when power is supplied to the aircraft. The BMCs monitor the valve positions, the pressure and the temperature of the supplied bleed air. Additionally, they monitor different zones to protect the adjacent systems and components against damage if a duct leaks or bursts (ambient overheat). To get correct limits or to prevent abnormal conditions, the BMCs control the necessary position of the valves. Both BMCs are identical and communicate via an ARINC 429 bus. They receive analog and discrete inputs from interface items and systems. The BMCs process these inputs and transmit analog and discrete outputs to the interface items and systems.
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 (2)
 Interfaces

 (a)
 Interface items for the inputs:

 -AIR COND overhead panel,
 -pressure transducers,
 -temperature sensor,
 -valves (bleed pressure regulator valve, HP bleed valve, overpressure valve and fan air valve),
 -APU bleed valve,
 -crossbleed valve,
 - overheat detection loops,

 -ENG/APU FIRE panel,
 -Electronic Control Box (ECB),

 (b)
 Interfaces items for the outputs:

 -AIR COND overhead panel
 -ECB.

 (c)
 Interface system for the outputs:

 -Environment control system (ECS).

 (d)
 Interface items for the ARINC inputs:

 -Centralized Fault Display Interface Unit (CFDIU)
 -Engine Interface Units (EIU).

 (e)
 Interface items for the ARINC outputs:
 - opposite BMC

 

 -CFDIU
 -SDAC.

 (3)
 BITE The BMCs incorporate a Built-In Test Equipment (BITE). They receive and transmit information from/to the CFDIU. This permits a self-test of the BMCs which is called up from the Multipurpose Control and Display Unit (MCDU) menu.

 

 6. Operation/Control and Indicating
________________________________
 A. AIR COND Overhead Panel
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
 (Ref. Fig. 001)

 Indication - Power supply Figure 009 (SHEET 1)
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