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They exchange data via ARINC bus for the wing double
loop detection.
NOTE: The wing loops A are connected to Bleed
Monitoring Computer 1 (BMC 1) and wing loops B
to BMC 2. The crosstalk bus allows wing leak
warnings to be activated through an AND logic.
The APU loop is connected to BMC 1 only.
The pylon loop is connected to the related BMC.
TMUPNED01-T02 LEVEL 3
EFFECTIVITY 36-22-00 Page 4
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
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ALL
LEAK DETECTION - WARNING LOGIC
TMUPNED01-P02 LEVEL 3
EFFECTIVITY 36-22-00 Page 5
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
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LEAK DETECTION
FAULT LOGIC
The engine bleed fault light comes on when a leak is
detected by the wing loops A and B or by the pylon
loop.
The APU bleed fault light comes on when an APU duct
leak is detected.
If one BMC is failed, the adjacent BMC takes over
monitoring of the bleed system and ensures the
following ECAM warnings:
- overpress
- overtemp
- wing leak
Nevertheless the associated FAULT light on the AIR
COND panel is lost, and the associated BLEED VALVE
does not close automatically.
ENG BLEED LEAK warning is lost for the associated
engine as well as APU BLEED LEAK warning if BMC 1 is
failed.
TMUPNED01-T03 LEVEL 3
EFFECTIVITY 36-22-00 Page 6
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
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UF94200
EFFECTIVITY Page 40
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LEAK DETECTION - FAULT LOGIC
TMUPNED01-P03 LEVEL 3
EFFECTIVITY 36-22-00 Page 7
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LEAK DETECTION
LEAK CONSEQUENCE
A detected leak will close associated valves, as shown
on this table.
These valves are automatically controlled to close if
they were open.
NOTE: APU and X Bleed valves do not close during Main
Engine Start.
TMUPNED01-T04 LEVEL 3
EFFECTIVITY 36-22-00 Page 8
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
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UF94200
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LEAK DETECTION - LEAK CONSEQUENCE
TMUPNED01-P04 LEVEL 3
EFFECTIVITY 36-22-00 Page 9
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SELF EXAMINATION
Which of the following are maintained by a double
loop detection system ?
A - The LH and RH wing ducts, packs and mid
fuselage APU duct.
B - The pylon.
C - A and B.
What happens in case of BMC 1 failure ?
A - BMC 2 ensures the complete leak
detection.
B - BMC 2 ensures its wing leak detection.
C - The leak detection is completely lost.
TMUPNED01 LEVEL 3
EFFECTIVITY 36-22-00 Page 10
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36 - PNEUMATIC SYSTEM
36-11-00 ENGINE BLEED AIR SUPPLY
COMPONENTS
CONTENTS:
High Pressure Valve (HPV)
Pressure Regulating Valve (PRV)
Bleed Pressure Regulated Valve Control Solenoid (CTS)
Precooler
Fan Air Valve (FAV)
Fan Air Valve Control Thermostat (CT)
Intermediate Pressure Check Valve (IPC)
Overpressure Valve (OPV)
Regulated Pressure (Pr)
Transferred Pressure (Pt)
Heat Exchanger Outlet Temperature Sensor (T)
Bleed Monitoring Computer (BMC)
TMUPNEH06 LEVEL 3
EFFECTIVITY 36-11-00 Page 1
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
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ENGINE BLEED AIR SUPPLY COMPONENTS
HIGH PRESSURE VALVE (HPV)
IDENTIFICATION
FIN: 4000HA1, 4000HA2
LOCATION
ZONE: 450, 460
COMPONENT DESCRIPTION
The valve is spring loaded closed.
TMUPNEH06-T01 LEVEL 3
EFFECTIVITY 36-11-00 Page 2
Jun 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM
UF94200
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ALL
ENGINE BLEED AIR SUPPLY COMPONENTS - HPV
TMUPNEH06-P01 LEVEL 3
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