A319/A320/A321
TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
This document must be used for training purpose only
Under no circumstances should this document be used as a reference.
It will not be updated.
All rights reserved.
No part of this manual may be reproduced in any form,
by photostat, microfilm, retrieval system, or any other means,
without the prior written permission of Airbus Industrie.
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
36 PNEUMATIC SYSTEM
UFD4200
TABLE OF CONTENTS
Page
System Presentation (1) .......................... 1
System Controls Presentation (1) ................. 7
ECAM Page Presentation (1) ...................... 11
** Engine Bleed System Description (3) ......... 15
Pneumatic System Warnings (3) ................... 23
APU Bleed Air SPLY/X-Bleed System (3) .......... 27
** BMC Interfaces (3)............................ 31
** Pneumatic Leak Detection System D/O (3) ..... 37
Engine Bleed Air Supply Components (3) ......... 47
** GND & APU Bleed Air Supply Components (3) ... 61
UFD4200
Leak Detection Components (3) ................... 75
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36 PNEUMATIC SYSTEM
36 PNEUMATIC SYSTEM
UFD4200
TABLE OF CONTENTS
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UFD4200
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36 CONTENTS
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
36 - PNEUMATIC
36-00-00 SYSTEM PRESENTATION
TMUPNE201 LEVEL 1
UFD4200
CONTENTS:
Sources
Engine Bleed Air Supply
Engine Bleed Valve
Overpressure Valve
Precooler
APU Bleed
Ground Air Supply
Cross Bleed Valve
Leak detection
Monitoring
Users
Self Examination
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
SYSTEM PRESENTATION
SOURCES
OVERPRESSURE VALVE
The Bleed Air system can be supplied by four different
sources: the engines, the APU and ground cart.
APU bleed air supply has priority over engine bleed
air supply.
On ground, the system may be supplied by a ground cart.
The overpressure valve is positioned downstream of the
engine bleed valve to protect the system.
The Overpressure valve is pneumatically operated and
springloaded open.
PRECOOLER
ENGINE BLEED AIR SUPPLY
The engine bleed air system is supplied by one of the
two different engine compressor stages: the
Intermediate Pressure stage or the High Pressure stage.
The Intermediate Pressure (IP) stage is normally used.
When the IP pressure is too low (low engine speed),
the HP valve pneumatically opens and regulates at 36
psi.
The valve is used to connect the HP stage to the engine
bleed air system.
Note: This valve is springloaded closed in the absence
of upstream pressure.
TMUPNE201-T01 LEVEL 1
UFD4200
ENGINE BLEED VALVE
The HP or IP air passes through the engine bleed valve
which operates as a pressure regulating and shut-off
valve.
The Engine Bleed Valve operates pneumatically and
regulates the downstream pressure to 44 psi. It is
springloaded closed in the absence of upstream
pressure.
Note: The closure of the Engine Bleed Valve causes the
HP valve to close.
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The precooler is a heat exchanger downstream of the
engine bleed valve, used to cool the bleed air. A fan
air valve regulates the cold air flow to the precooler
for bleed air temperature control.
The Fan Air Valve allows the bleed air temperature to
be maintained at 200ºC. It is springloaded closed in
the absence of air pressure.
APU BLEED
The APU bleed air passes through the APU bleed valve
which is pneumatically operated and electrically
controlled (GARRET) or fuel operated and electrically
controlled (APIC).
When open, the APU bleed valve has priority over the
engine bleed valves, which are automatically
controlled to close.
Note: The APU valve is springloaded closed in the
absence of air pressure (GARRET) or fuel pressure
(APIC).
GROUND AIR SUPPLY
The bleed air system can be supplied by the ground
cart.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
SYSTEM PRESENTATION
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36 PNEUMATIC SYSTEM
SYSTEM PRESENTATION
CROSS BLEED VALVE
MONITORING
The cross bleed valve, installed in the cross feed
line, allows the left and right bleed systems to be
interconnected or isolated.
The cross bleed valve is electrically controlled by
two independent electrical motors. In auto mode, it
is controlled to the same position as the APU bleed
valve. In manual mode, it is controlled independently
of APU bleed valve.
Engine bleed pressure, temperature and leak detection
are monitored by two bleed monitoring computers:
- In normal configuration, computer 1 monitors
the left bleed system and computer 2 the right
bleed system.
- If one Bleed Monitoring Computer fails, the
remaining BMC is able to monitor both bleed
systems (except for Pylon leak and APU leak
detection).
LEAK DETECTION
TMUPNE201-T01 LEVEL 1
UFD4200
USERS
A leak detection system is provided to detect overheat
in the vicinity of hot air ducts, in the pylons, wings
and fuselage.
The leak detection system monitors the following zones:
- Wing and packs: ensured by a double loop of
sensing elements.
The left loops also monitor bleed ducts up to
cross bleed valve and APU check valve.
The right loops also monitor bleed ducts up to
cross bleed valve.
- Pylons: ensured by a single loop with one
sensing element.
- APU bleed duct (from APU bleed valve to check
valve): ensured by a single loop of sensing
elements.
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The pneumatic system supplies pressurized air to
different users.
The users are:
- the engine start system,
- the wing ant-ice system,
- the air conditioning pack,
- the water tank and hydraulic reservoir
pressurization,
- the AFT cargo heating (Optional),
- the nacelle anti-ice valve (CFM only).
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36 PNEUMATIC SYSTEM
SELF EXAMINATION
TMUPNE201 LEVEL 1
UFD4200
Does the APU bleed valve opening have priority
over the engine bleed valves opening ?
A - YES.
B - NO.
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TMUPNE201 LEVEL 1
UFD4200
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36 PNEUMATIC SYSTEM
36 - PNEUMATIC
36-00-00 SYSTEM CONTROLS PRESENTATION
TMUPNE301 LEVEL 1
UFD4200
CONTENTS:
Engine Bleed Valve Pushbutton
APU Bleed Valve Pushbutton
Cross Bleed Valve Selector
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36 PNEUMATIC SYSTEM
SYSTEM CONTROLS PRESENTATION
ENGINE BLEED VALVE PUSHBUTTON
CROSS BLEED VALVE SELECTOR
When pressed in, the related engine bleed valve opens,
provided the engine is running, the APU bleed not ON
and no fault is detected (by its Bleed Monitoring
Computer).
When released out, the related bleed valve and HP valve
are closed.
The HP valve opens if the bleed pressure is less than
36 psi.
In AUTO, the cross bleed valve takes
configuration as the APU bleed valve (closed
When OPEN is selected, the cross bleed
controlled to open.
When SHUT is selected, the cross bleed
controlled to close.
the same
or open).
valve is
valve is
NOTE: If SHUT is selected and the APU bleed valve is
open, only engine 2 bleed valve is open.
APU BLEED VALVE PUSHBUTTON
When pressed in, the APU bleed valve opens provided
the APU is running and no leak is detected by BMC1.
When released out, the APU bleed valve is closed.
TMUPNE301-T01 LEVEL 1
UFD4200
NOTE: When the APU bleed valve is open, the X bleed
valve is open and both engine bleed valves are
closed, provided X bleed valve selector at AUTO.
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UFD4200
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36 PNEUMATIC SYSTEM
SYSTEM CONTROL PRESENTATION
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UFD4200
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36 PNEUMATIC SYSTEM
36 - PNEUMATIC
36-20-00 ECAM PAGE PRESENTATION
TMUPNE401 LEVEL 1
UFD4200
CONTENTS:
Sources
Engine and APU Bleed Valves
Engine HP Valve
Cross Bleed Valve
Ducts
Bleed Air Parameters
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36 PNEUMATIC SYSTEM
ECAM PAGE PRESENTATION
SOURCES
DUCTS
Engine symbol 1 or 2 is amber when the corresponding
engine is stopped. It becomes white when engine is
running. The green ground symbol and the white GND
indication are displayed when the aircraft is on
ground, independently of ground cart connection.
The white HP, IP and APU indications are always
displayed.
The ducts are represented by green lines when
corresponding valves are open, and become amber or are
not displayed when the valves are closed.
ENGINE AND APU BLEED VALVES
Green is used when the engine bleed valve position
corresponds to the required position, and amber in
case of disagreement. The APU bleed valve is green in
line when open, and green cross line when closed.
The engine bleed valve symbol is replaced by XX when
information is not valid.
The APU bleed valve is displayed when APU is running;
it is not displayed when APU MASTER SW is set to OFF.
BLEED AIR PARAMETERS
Bleed temperature and pressure are shown in the
shaded boxes; they are green when normal, amber
when out of limits.
Bleed pressure parameter becomes amber if lower
than 4 psi or in case of overpressure detected by
BMC (above 57 psi). Temperature parameter becomes
amber in case of overheat detection by BMC.
Overheat is detected if temperature exceeds:
- 290°C for more than 5 sec or,
- 270°C for more than 15 sec or,
- 257°C for more than 55 sec.
TMUPNE401-T01 LEVEL 1
UFD4200
ENGINE HP VALVE
The engine HP VALVE is displayed cross line when
closed, and in line when open. Green is used when HP
valve position corresponds to the required position,
and amber in case of disagreement.
The engine HP valve symbol is replaced by XX when HP
valve information is not valid
CROSS BLEED VALVE
The cross-bleed valve is displayed in line when open,
and cross line when closed.
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TMUPNE401-P01 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
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UFD4200
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36 PNEUMATIC SYSTEM
36 - PNEUMATIC
36-10-00 ENGINE BLEED SYSTEM DESCRIPTION
TMUPNEB03 LEVEL 3
UFD4200
CONTENTS:
General
HPV
IPC
PRV/CTS
OPV
Pr
Pt
FAV/CT
Precooler
Heat Exchanger Outlet Temperature Sensor (T)
Self Examination
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36 PNEUMATIC SYSTEM
ENGINE BLEED SYSTEM DESCRIPTION
GENERAL
IPC
The engine air bleed pressure is pneumatically
regulated by the High Pressure Valve (HPV) when air
is supplied by the HP stage or by the Pressure
Regulating Valve (PRV) when the air is supplied by the
IP stage.
The pressure regulation system is monitored by two
BMCs.
The Intermediate Pressure Check Valve protects the IP
stage from reverse flow when the High Pressure Valve
is open.
TMUPNEB03-T01 LEVEL 3
UFD4200
HPV
The switching between Intermediate Pressure (IP) and
High Pressure (HP) is achieved pneumatically when the
IP stage pressure is not sufficient.
The HPV pneumatically regulates the air supply between
8 to 36 psi.
The HPV is forced closed when the PRV is closed via
the PRV/HPV sense line.
In flight, the EEC (Engine Electronic Controller)
maintains the HPV closed. It vents the HPV-PRV sense
line when :
- engine is above idle (PS3 > 110 PSI)
- Wing Anti-Ice OFF
- Altitude over 15000 ft
- Normal pack configuration.
When one of the four conditions is no longer met, the
solenoid is de-energized and the opening of the HPV
is no longer inhibited.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED SYSTEM DESCRIPTION
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36 PNEUMATIC SYSTEM
ENGINE BLEED SYSTEM DESCRIPTION
PRV/CTS
TMUPNEB03-T02 LEVEL 3
UFD4200
The PRV pneumatically regulates the bleed pressure
around 44 psi.
A thermal fuse causes the valve to close in case of
engine fire (450°C).
The PRV is pneumatically controlled by an external
servo-control, the Bleed Pressure Regulated Valve
Control Solenoid (CTS), located downstream from the
precooler.
The CTS operates in two modes, pneumatically and
electrically, causing a partial or complete closure
of the PRV.
Pneumatic mode:
- Temperature limitation downstream of the
precooler by means of the CTS thermostat. When
the temperature increases and reaches 235°C,
the PRV downstream pressure is progressively
reduced up to 17,5 psi when the temperature
gets higher than 245°C.
Reverse flow protection by closing the PRV when a ∆P
between the precooler outlet and the PRV inlet is
detected.
The solenoid is automatically energized by the BMC
in the following cases:
- Overtemperature downstream of the precooler
(the heat exchanger outlet temperature sensor
T senses a temperature above 257°C.
- Overpressure downstream of the PRV (the
pressure regulated transducer Pt senses a
pressure greater than 57 psi).
- Leak detection in pylon/wing/fuselage ducts
surrounding areas.
- APU bleed valve not closed.
- Corresponding starter valve not closed.
Electrical mode: (PRV shut-off function through the
CTS solenoid energization)
- Eng. Bleed P/B selected "OFF".
- Eng. Fire P/B selected on.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED SYSTEM DESCRIPTION
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36 PNEUMATIC SYSTEM
ENGINE BLEED SYSTEM DESCRIPTION
OPV
PRECOOLER
The OverPressure Valve (OPV), normally open,
pneumatically closes.
The OPV starts to close at 75 psi. It is fully closed
at 85 psi and opens again at 35 psi.
The precooler is an air to air heat exchanger.
Pr
A transducer, connected to the Bleed Monitoring
Computer, reads the regulated pressure downstream from
the PRV. This pressure is indicated on the ECAM.
HEAT EXCHANGER OUTLET TEMPERATURE SENSOR (T)
The Heat Exchanger Outlet Temperature Sensor,
connected to both Bleed Monitoring Computers, reads
the regulated temperature downstream from the
precooler.
This temperature is indicated on the ECAM and used to
monitor the system.
Pt
A transducer, connected to the Bleed Monitoring
Computer, reads the transferred pressure downstream
from the HPV.
This pressure is used to monitor PRV and HPV.
TMUPNEB03-T03 LEVEL 3
UFD4200
FAV/CT
The Fan Air Valve (FAV) pneumatically regulates the
fan air flow to the precooler for bleed air temperature
regulation (200°C).
The FAV is pneumatically controlled by an external
servo-control: the Fan Air Valve Control Thermostat
(CT), located downstream from the precooler.
A thermal fuse installed in the valve body closes the
valve if a temperature of 450°C is reached.
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36 PNEUMATIC SYSTEM
SELF EXAMINATION
What is the purpose of IP/HP switching ?
A - To regulate the output pressure,
depending on Fan Air Valve position.
B - To keep air bleed at a sufficient
pressure at low engine speed.
C - To regulate the output temperature,
depending on the configuration of users.
What is the purpose of the CTS ?
A - To send a pneumatic signal to the OPV,
in case of overpressure.
B - To send a pneumatic signal to regulate
or shut-off the PRV.
TMUPNEB03 LEVEL 3
UFD4200
What is the purpose of the CT ?
A - To send a pneumatic signal to control
the FAV.
B - To send a pneumatic signal to the OPV in
case of overpressure.
C - To send a pneumatic signal to control
the PRV.
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TMUPNEB03 LEVEL 3
UFD4200
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36 PNEUMATIC SYSTEM
36 - PNEUMATIC
36-20-00 PNEUMATIC SYSTEM WARNINGS
TMUPNE502 LEVEL 3
UFD4200
CONTENTS:
Engine 1 (2) Bleed Abnormal Pressure
Engine 1 (2) Bleed Low Temperature
X Bleed Fault
Engine 1 (2) HP Valve Fault
Bleed Monitoring Fault
Left (Right) Wing Leak Detection Fault
Eng 1 (2) Bleed Fault
Left (Right) Wing Leak
Engine 1 (2) Bleed Leak
Engine 1 (2) Bleed not closed
Bleed 1 (2) OFF
APU Bleed Fault
APU Bleed Leak.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
PNEUMATIC SYSTEM WARNINGS
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
PNEUMATIC SYSTEM WARNINGS
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TMUPNE502 LEVEL 3
UFD4200
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36 PNEUMATIC SYSTEM
36 - PNEUMATIC SYSTEM
36-12-00 APU BLEED AIR SUPPLY / X-BLEED
SYSTEM
TMUPNEC01 LEVEL 3
UFD4200
CONTENTS:
APU Bleed
X-Bleed System
HP Ground Connection
Self Examination
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36 PNEUMATIC SYSTEM
APU BLEED AIR SUPPLY / X-BLEED SYSTEM
APU BLEED
The pneumatic system can be supplied by APU bleed air
through the APU bleed valve provided the APU is
running.
The APU bleed valve (GARRET) is electrically controlled
and pneumatically operated by a Solenoid.
It is springloaded closed in absence of air pressure.
NOTE: This valve is of the ON/OFF type.
The APU bleed valve (APIC) is electrically controlled
and fuel operated by a ServoValve.
The ECB monitors the fuel muscle pressure which closes
or opens the APU bleed valve.
TMUPNEC01-T01 LEVEL 3
UFD4200
X-BLEED SYSTEM
The position of the valve is controlled by the X-BLEED
selector (SHUT or OPEN) on the overhead panel.
It is operated by two electrical motors:
- the primary motor is used for AUTO mode,
- the position of the valve is controlled by the
BMC according to APU bleed configuration,
- the secondary motor is used to override the
AUTO mode.
HP GROUND CONNECTION
The pneumatic system may be supplied by a ground cart.
The supply duct is located to the left of the cross
bleed valve.
Only the left-hand bleed system is supplied.
When the X-BLEED selector is in the OPEN position, the
ground air supply will be available to start ENG2.
The X-BLEED valve permits the isolation or the
interconnection of the left and right bleed air
systems.
OPEN Manual control is used for:
- cross supply of the packs,
- engine crossbleed start (on ground only),
- engine bleed air failure in icing conditions
for wing anti-ice supply,
- ENG2 start from ground cart supply.
SHUT Manual control is used for closure of the valve.
The X-Bleed valve is an electrically controlled
shut-off valve.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
APU BLEED AIR SUPPLY / X-BLEED SYSTEM - APU BLEED
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36 PNEUMATIC SYSTEM
SELF EXAMINATION
With the X-BLEED selector at AUTO and air supplied
by ENG1 ONLY, the X-BLEED valve :
A - Does not receive any order.
B - Is automatically controlled to open.
C - Is controlled to close.
How does the GARRET APU Bleed valve operate ?
A - As a regulating valve.
B - As an ON/OFF valve.
C - A and B.
TMUPNEC01 LEVEL 3
UFD4200
How does the APIC APU Bleed valve operate ?
A - Pneumatically.
B - Fuel operated
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
36 - PNEUMATIC
36-11-34 BMC INTERFACES
TMUPNEV03 LEVEL 3
UFD4200
CONTENTS:
Inputs
Outputs
EFFECTIVITY
EFFECTIVITY
ALL
36-11-34
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
BMC INTERFACES
INPUTS
TMUPNEV03-T01 LEVEL 3
UFD4200
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).
EFFECTIVITY
EFFECTIVITY
ALL
36-11-34
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TMUPNEV03-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
BMC INTERFACES(INPUTS)
EFFECTIVITY
EFFECTIVITY
ALL
36-11-34
Page
Page33
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
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.
TMUPNEV03-T02 LEVEL 3
UFD4200
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.
EFFECTIVITY
EFFECTIVITY
ALL
36-11-34
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TMUPNEV03-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
BMC INTERFACES(OUTPUTS)
EFFECTIVITY
EFFECTIVITY
ALL
36-11-34
Page
Page35
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
TMUPNEV03 LEVEL 3
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
EFFECTIVITY
ALL
36-11-34
Page
Page36
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
36 - LEAK DETECTION
36-22-00 LEAK DETECTION
TMUPNED01 LEVEL 3
UFD4200
CONTENTS:
Routing
Warning Logic
Fault Logic
Leak Consequence
Self Examination
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
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A319/A320/A321 TECHNICAL TRAINING MANUAL
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
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
TMUPNED01-T01 LEVEL 3
UFD4200
NOTE: Each loop consists of sensing elements connected
in series.
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
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TMUPNED01-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
LEAK DETECTION - ROUTING
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page39
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
LEAK DETECTION
WARNING LOGIC
Both Bleed Monitoring Computers receive signals from
the leak detection loops.
They exchange data via ARINC bus for the wing double
loop detection.
TMUPNED01-T02 LEVEL 3
UFD4200
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.
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
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TMUPNED01-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
LEAK DETECTION - WARNING LOGIC
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page41
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
LEAK DETECTION
FAULT LOGIC
TMUPNED01-T03 LEVEL 3
UFD4200
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.
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page42
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TMUPNED01-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
LEAK DETECTION - FAULT LOGIC
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page43
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
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.
TMUPNED01-T04 LEVEL 3
UFD4200
NOTE: APU and X Bleed valves do not close during Main
Engine Start.
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page44
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A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMUPNED01-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
LEAK DETECTION - LEAK CONSEQUENCE
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page45
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
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.
TMUPNED01 LEVEL 3
UFD4200
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.
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page 46
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A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
36 - PNEUMATIC SYSTEM
36-11-00 ENGINE BLEED AIR SUPPLY
COMPONENTS
TMUPNEH05 LEVEL 3
UFD4200
CONTENTS:
High Pressure Valve (HPV)
HPV Closure Control Solenoid
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)
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
HIGH PRESSURE VALVE (HPV)
HIGH CLOSURE CONTROL SOLENOID
IDENTIFICATION
FIN: 4000HA1, 4000HA2
IDENTIFICATION
FIN: 4029KS
LOCATION
ZONE: 450, 460
LOCATION
ZONE: 438, 448
COMPONENT DESCRIPTION
The valve is spring loaded closed.
COMPONENT DESCRIPTION
It controls the HPV to close upon EEC command.
TMUPNEH05-T01 LEVEL 3
UFD4200
ENGINE BLEED AIR SUPPLY COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
Page48
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_
TMUPNEH05-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS - HPV - HPV CLOSURE CONTROL SOLENOID
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
Page49
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
PRESSURE REGULATING VALVE (PRV)
BLEED PRESSURE REGULATED VALVE CONTROL SOLENOID (CTS)
IDENTIFICATION
FIN: 4001HA1, 4001HA2
IDENTIFICATION
FIN: 10HA1, 10HA2
LOCATION
ZONE: 450, 460
LOCATION
ZONE: 413, 423
COMPONENT DESCRIPTION
The valve is spring loaded closed.
COMPONENT DESCRIPTION
Three functions:
- PRV electrical shut off (Solenoid)
- Temperature Limitation
- Reverse flow inhibition
TMUPNEH05-T02 LEVEL 3
UFD4200
ENGINE BLEED AIR SUPPLY COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
Page50
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_
TMUPNEH05-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS - PRV - CTS
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
Page51
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS
PRECOOLER
FAN AIR VALVE CONTROL THERMOSTAT (CT)
IDENTIFICATION
FIN: 7150HM1, 7150HM2
IDENTIFICATION
FIN: 7170HM1, 7170HM2
LOCATION
ZONE: 410, 420
LOCATION
ZONE: 410, 420
COMPONENT DESCRIPTION
Single cross pass heat exchanger.
COMPONENT DESCRIPTION
It is pneumatically coupled to the Fan Air Valve to
control it open if the temperature downstream of the
precooler exceeds 200°C ( 392°F ).
FAN AIR VALVE (FAV)
IDENTIFICATION
FIN: 9HA1, 9HA2
LOCATION
ZONE: 453, 463
TMUPNEH05-T03 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
The valve is spring loaded closed.
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
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TMUPNEH05-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS - PRECOOLER - FAV - CT
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
Page53
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS
INTERMEDIATE PRESSURE CHECK VALVE (IPC)
OVERPRESSURE VALVE (OPV)
IDENTIFICATION
FIN: 7110HM1, 7110HM2
IDENTIFICATION
FIN: 5HA1, 5HA2
LOCATION
ZONE: 450, 460
LOCATION
ZONE: 453, 563
TMUPNEH05-T04 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
The valve is spring loaded open.
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
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TMUPNEH05-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS - IPC - OPV
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
Page55
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS
REGULATED PRESSURE (Pr)
HEAT EXCHANGER OUTLET TEMPERATURE SENSOR (T)
IDENTIFICATION
FIN: 8HA1, 8HA2
IDENTIFICATION
FIN: 6HA1, 6HA2
LOCATION
ZONE: 415, 425
LOCATION
ZONE: 413, 423
COMPONENT DESCRIPTION
It is connected to both BMCs for pressure indication
and system fault monitoring purposes.
It is also connected by a sense line to the duct
downstream of the PRV.
COMPONENT DESCRIPTION
It is connected to both BMCs for temperature indication
(ECAM) and FAULT logic.
It also monitors the temperature downstream of the
precooler.
TRANSFERRED PRESSURE (Pt)
IDENTIFICATION
FIN: 7HA1, 7HA2
TMUPNEH05-T05 LEVEL 3
UFD4200
LOCATION
ZONE: 415, 425
COMPONENT DESCRIPTION
It is connected to its dedicated BMC for faulty
component identification in case of failure.
It is also connected by a sense line to the duct
downstream of the HP bleed valve.
It gives the transferred relative static pressure.
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
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_
TMUPNEH05-P05 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS - Pr - Pt - T
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
Page 57
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS
BLEED MONITORING COMPUTER (BMC)
IDENTIFICATION
FIN: 1HA1, 1HA2
LOCATION
ZONE: 121, 122
TMUPNEH05-T06 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
It monitors and controls the engine bleed system.
At each power-up, a test of the BMC and of the leak
detection system is done.
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
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_
TMUPNEH05-P06 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
ENGINE BLEED AIR SUPPLY COMPONENTS - BMC
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
Page 59
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
TMUPNEH05 LEVEL 3
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
EFFECTIVITY
ALL
36-11-00
Page
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
36 - PNEUMATIC SYSTEM
36-12-00 GND AND APU BLEED AIR SUPPLY
COMPONENTS
TMUPNEI01 LEVEL 3
UFD4200
CONTENTS:
APU Bleed Valve (GTCP 36-300)
APU Bleed Valve (APIC)
APU Bleed Valve (GTCP 131-9A)
X Bleed Valve
APU Bleed Check Valve
HP Ground Connector
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
Page61
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS
APU BLEED VALVE (GTCP 36-300)
IDENTIFICATION
FIN: 4005KM
LOCATION
ZONE: 310
TMUPNEI01-T01 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
Spring loaded closed
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
Page62
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_
TMUPNEI01-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS - APU BLEED VALVE (GTCP 36-300)
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS
APU BLEED VALVE (APIC)
IDENTIFICATION
FIN: 110KD
LOCATION
ZONE: 316
TMUPNEI01-T02 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
The Bleed Control Valve is located on the right lower
part of the APU at the scroll outlet.
It delivers air to the aircraft while avoiding load
compressor surge.
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
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_
TMUPNEI01-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS - APU BLEED VALVE (APIC)
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
Page65
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS
APU BLEED VALVE (GTCP 131-9A)
IDENTIFICATION
FIN: TBD
LOCATION
ZONE: 316
TMUPNEI01-T03 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
Spring loaded closed.
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
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_
TMUPNEI01-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS - APU BLEED VALVE (GTCP 131-9A)
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
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36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS
X BLEED VALVE
IDENTIFICATION
FIN: 6HV
LOCATION
ZONE: 192
TMUPNEI01-T04 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
For safety reasons, the valve is equipped with two
electric motors which can both actuate the butterfly
in opening or closing directions.
A brake system locks the valve in position when
electrical power is cut off.
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
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_
TMUPNEI01-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS - X BLEED VALVE
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS
APU BLEED CHECK VALVE
IDENTIFICATION
FIN: 7260HM
LOCATION
ZONE: 150
TMUPNEI01-T05 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
The APU bleed check valve is of the flapper type.
It protects the APU from reverse flow when another
source is supplying Bleed air at a higher pressure.
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
Page 70
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_
TMUPNEI01-P05 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS - APU BLEED CHECK VALVE
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS
HP GROUND CONNECTOR
IDENTIFICATION
FIN: 7300HM
LOCATION
ZONE: 191
TMUPNEI01-T06 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
The HP ground connector contains a check valve of the
flapper type and a built-in nipple.
A duct connects the HP ground connector with the
crossfeed duct on the left hand side of the cross bleed
valve.
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
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_
TMUPNEI01-P06 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
GND AND APU BLEED AIR SUPPLY COMPONENTS - HP GROUND CONNECTOR
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
Page 73
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
TMUPNEI01 LEVEL 3
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
EFFECTIVITY
ALL
36-12-00
Page
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MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
36 - PNEUMATIC SYSTEM
36-22-00 PNEUMATIC LEAK DETECTION
COMPONENTS
TMUPNEK01 LEVEL 3
UFD4200
CONTENTS:
Wing Leak Detection Element
Pylon Detection Element
APU Detection Element
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36-22-00
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Page75
1
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
PNEUMATIC LEAK DETECTION COMPONENTS
WING LEAK DETECTION ELEMENT
IDENTIFICATION
FIN: 21HF → 79HF
LOCATION
ZONE:
TMUPNEK01-T01 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
Installed in each wing along the forward face of the
front spar and in the mid fuselage along the hot air
ducts.
Triggering signal: Temperature > 124°C.
Sensing elements mounted in series with connecting
cables where necessary.
At the alarm temperature, the impedance between the
solid nickle conductor and the outer tubing decreases
suddenly, the center conductor grounds and gives an
alarm signal to the BMC.
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page76
2
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMUPNEK01-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
PNEUMATIC LEAK DETECTION COMPONENTS - WING LEAK DETECTION ELEMENT
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page77
3
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
PNEUMATIC LEAK DETECTION COMPONENTS
PYLON DETECTION ELEMENT
IDENTIFICATION
FIN: 1HF1, 1HF2
LOCATION
ZONE: 410, 420
TMUPNEK01-T02 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
Located at the outlet of the pylon ventilation duct.
Triggering signal: Temperature > 204°C.
Only one sensing element.
At the alarm temperature, the impedance between the
solid nickle conductor and the outer tubing decreases
suddenly, the center conductor grounds and gives an
alarm signal to the BMC.
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page78
4
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMUPNEK01-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
PNEUMATIC LEAK DETECTION COMPONENTS - PYLON DETECTION ELEMENT
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page79
5
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
PNEUMATIC LEAK DETECTION COMPONENTS
APU DETECTION ELEMENT
IDENTIFICATION
FIN: 11HF → 20 HF
LOCATION
ZONE: APU duct
TMUPNEK01-T03 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
Installed between check valve and APU compartment
Triggering signal: Temperature > 124°C.
Sensing elements mounted in series.
At the alarm temperature, the impedance between the
solid nickle conductor and the outer tubing decreases
suddenly, the center conductor grounds and gives an
alarm signal to the BMC.
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page80
6
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMUPNEK01-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
PNEUMATIC LEAK DETECTION COMPONENTS - APU DETECTION ELEMENT
EFFECTIVITY
EFFECTIVITY
ALL
36-22-00
Page
Page81
7
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
36 PNEUMATIC SYSTEM
TMUPNEK01 LEVEL 3
UFD4200
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EFFECTIVITY
EFFECTIVITY
ALL
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