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A - As a regulating valve.
B - As an ON/OFF valve.
C - A and B.
How does the APIC APU Bleed valve operate ?
A - Pneumatically.
B - Fuel operated
TMUPNEC01 LEVEL 3
EFFECTIVITY 36-12-00 Page 4
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM
UF94200
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36 - PNEUMATIC
36-11-34 BMC INTERFACES
CONTENTS:
Inputs
Outputs
TMUPNEV02 LEVEL 3
EFFECTIVITY 36-11-34 Page 1
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM
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BMC INTERFACES
INPUTS
Each Bleed Monitoring Computer has three types of
inputs:
- DIGITAL INPUTS via ARINC 429 buses, from
opposite BMC, corresponding EIU and CFDIU.
- ANALOG INPUTS from the bleed sensors.
- DISCRETE INPUTS from valve position switches,
BMC and overhead panel.
28 Volts Direct Current power is supplied for
energization of the Bleed Pressure Regulated Valve
Control Solenoid (CTS).
TMUPNEV02-T01 LEVEL 3
EFFECTIVITY 36-11-34 Page 2
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM
UF94200
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TMUPNEV02-P01 LEVEL 3
BMC INTERFACES(INPUTS)
EFFECTIVITY 36-11-34 Page 3
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM
UF94200
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BMC INTERFACES
OUTPUTS
Each Bleed Monitoring Computer has two types of
outputs:
- DIGITAL OUTPUTS via ARINC 429 buses to the
SDACs (for ECAM warnings and indications), the
CFDIUs (for maintenance purposes), and the
opposite BMC (for bleed monitoring purposes).
- DISCRETE OUTPUTS to APU Electronic Control Box
for APU availability, to overhead panel for
bleed faults, to Cross Bleed Valve, CTS and
Zone Controller.
NOTE: In case of BMC failure, the monitoring of main
parameters (HPV and PRV, Heat Exchanger Outlet
Temperature Sensor, Pr) is kept, but the
automatic control of the PRV is lost.
TMUPNEV02-T02 LEVEL 3
EFFECTIVITY 36-11-34 Page 4
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM
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BMC INTERFACES(OUTPUTS)
TMUPNEV02-P02 LEVEL 3
EFFECTIVITY 36-11-34 Page 5
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
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THIS PAGE INTENTIONALLY LEFT BLANK
TMUPNEV02 LEVEL 3
EFFECTIVITY 36-11-34 Page 6
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
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UF94200
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36 - LEAK DETECTION
36-22-00 LEAK DETECTION
CONTENTS:
Routing
Warning Logic
Fault Logic
Leak Consequence
Self Examination
TMUPNED01 LEVEL 3
EFFECTIVITY 36-22-00 Page 1
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM
UF94200
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LEAK DETECTION
ROUTING
The leak detection system is used to detect leaks in
the vicinity of the packs, wings, pylons and APU hot
air ducts.
Each wing is monitored by a double loop.
The pylon and APU hot air ducts are monitored by a
single loop.
A continuous monitoring system detects ambient
overheat in the vicinity of the hot air ducts.
Protected areas:
Double loop for:
- RH wing and pack 2
- LH wing, pack 1 and mid fuselage APU duct.
Single loop for:
- LH and RH pylons
- Aft fuselage APU duct
NOTE: Each loop consists of sensing elements connected
in series.
TMUPNED01-T01 LEVEL 3
EFFECTIVITY 36-22-00 Page 2
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM
UF94200
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LEAK DETECTION - ROUTING
TMUPNED01-P01 LEVEL 3
EFFECTIVITY 36-22-00 Page 3
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM
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LEAK DETECTION
WARNING LOGIC
Both Bleed Monitoring Computers receive signals from
the leak detection loops.
　
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