• Bleed air system got 3 different sauces
• APU
• Engines
• Ground cart Engine
• Two different stages
• IP – 7th HP stage
• HP – 10th HP stage, HP valve
• Opens and regulates at 36psi when IP pressure is low
• Spring loaded to close in absence of up stream pressure
• Closer of PRV leads HP valve to close by PRV – HPV sense line
• In flight EEC maintain HPV close by energizing solenoid located on the sense line if
• Engine speed > Idle speed
• Altitude > 15000 ft
• Wing anti-ice close
• Normal pack configuration (2 pack operation)
• In case of low and excessive up stream pressure (closer pneumatically)
• Position indication goes to ECAM via BMC Intermediate pressure valve
• Protects IP stage by reverse flow when HP valve open Engine Bleed valve (PRV)
• HP & IP bleed pressure goes through PRV
• Operates pneumatically, control down stream pressure to 44psi
• Spring loaded to close in up stream pressure is lost
• Position indication goes to ECAM via BMC
• CTS powered by 28VDC via BMC
• Pneumatically Controlled by CTS located in down stream of precooler. CTS operation in TWO modes
• Pneumatically
• Over temp. protection of down stream of precooler by thermostat to reduce PRV flow rate
• Over heat protection of down stream of the precooler
• Controlled close in case of reverse flow
• Electrical Mode
• PRV shut off function solenoid energized by
• Flight deck panel (engine bleed valve P/B select OFF or Fire P/B push)
• BMC if
• Over temperature
• Over pressure
• Leak detected
• Engine starter valve open
• APU bleed set to ON
ENG BLEED Fault LT ON – Down stream of bleed valve hi bleed temp. or pressure
- Wing leak detection
- Engine bleed leak detection - Engine bleed not closed - Pylon leak detection
- If one loop inoperative then other detects fire - Bleed valve not close during engine start - Bleed valve not close with APU bleed ON Switch pressed IN – Bleed valve opens if
- Upstream pressure > 8 psi.
- APU bleed P/B switch OFF or APU bleed valve close
- No on side wing or pylon leak and no over pressure or over temperature has detected - Engine fire P/B not pop out
- Engine start valve closed FAULT
OFF
Pressure transducers
• Located down stream of the PRV (one in each side) to provide ECAM bleed pressure via BMC 1 & 2 and SDAC
• Located down stream of HPV (one in each side) and provides signal to BMCs to monitor HPV and PRV Precooler
• Located in pylon, air to air heat exchanger regulates temp. at 200 °C
• Cooled by fan air and air controlled by FAN AIR VALVE Precooler outlet temp. sensor
• Provide ECAM indication and used to system monitoring via BMC (one for each side) Fan Air Valve
• Controlled by CT (control thermostat) pneumatically located down stream of precooler
• Spring loaded to close in the absence of air pressure APU
• Bleed passes through APU bleed valve, electrically controlled and operated by fuel pressure
• APU bleed valve got priority over engine bleed valves APU Bleed valve
APU BLEED
Fault Lt. ON – APU bleed leak detected (APU bleed valve and cross bleed valve close)
Valv If engine was running own bleed valve opens Vvvvv Sw. pressed IN – APU bleed valve open if
- APU fire P/B not released
- No L/H & APU leak detection (if leak dection on R/H side cross bleed valve closes)
- APU RPM > 95%
- NO shut command Cross Bleed Valve
AUTO SHUT OPEN
AUTO – Open & Close with APU bleed valve Auto open if
- Mode selector auto - APU bleed not close
- Engine Fire P/B not released - No leak inhibition during engine start Manual Mode
OPEN – Valve open CLOSE – Valve close
• Cross bleed valve located in L/H side of the cross bleed duct allows to interconnect engine air systems
• Electrically controlled by 2 motors
• Primary motor – Auto mode
• Secondary motor – Manual mode (can OVRD auto mode) Leak Detection
• Provides to detect over heat in the vicinity of hot air ducts in the wings, pylons and fuselage
• Monitors following zones
• Wing and Packs – Double loop
• Left loop monitors bleed ducts, cross bleed valve and APU check valve
• Right loop monitors bleed ducts and cross bleed valve
• Pylons – Single loop with one sensing element
• APU bleed duct – Single loop
• BMC 1 receive Loop “A” , Eng.1 Pylon and APU loop leak detection signals
• BMC 2 receive Loop ”B”, Eng. 2 Pylon leak detection signals
• BMC 1 & 2 cross talk then via AND logic provide warnings FAULT
ON
Wing leak detection causes
• Bleed valve of the related side to close automatically
• Associated Fault Lt. located on the air-condition panel comes ON
• Cross bleed valve closes automatically except engine start
• APU bleed valve goes to close automatically if leak concerns at the left wing except engine start Pylon leak signal causes
• Bleed valve on the related side closes automatically
• Associated Fault Lt. located on the air-condition panel comes ON
• Cross bleed valve closes automatically except engine start APU leak signal causes
• APU bleed valve closes automatically except engine start
• Associated Fault Lt. located on the air-condition panel comes ON
• Cross bleed valve closes automatically except engine start BMC • Monitoring by 2 BMCs
• Bleed pressure
• Bleed Temperature
• Leek detection
• Normal configuration
• BMC 1 – Monitors left side of cross bleed system
• BMC 2 – Monitors right of cross bleed system
• If BMC 1 fails other will monitor except APU and Pylon
• Both BMC fail no aural warning only ECAM message + crosses on system page
• BMC interfaces
• With SDAC to provide ECAM indication
• CFDIU for maintenance data
• Opposite BMC to provide wing loop leak status, bleed parameters
• APU ECU to bleed valve control
• Zone controller
IF one BMC failed monitoring of main parameters kept valid
• HPV
• PRV
• Precooler outlet temp. sensor
• Following ECAM warnings will be avail
• Over pressure
• Over temperature
• Wing leak
• Automatic control of PRV will be lost
• Associated Fault Lt. on air-condition panel lost
• Pylon leak warning for associated engine
• If BMC 1 APU bleed leak warning will be lost