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A319/A320/A321TECHNICAL TRAINING MANUAL

MECHANICS / ELECTRICS & AVIONICS COURSE

36 PNEUMATIC SYSTEM

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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.

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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.........

** APU Bleed & X-Bleed Components (3) 61..........

Leak Detection Components (3) 71...................

_A319/A320/A321 TECHNICAL TRAINING MANUAL

36 PNEUMATIC SYSTEMMECHANICS / ELECTRICS & AVIONICS COURSE

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36 - PNEUMATIC

36-00-00 SYSTEM PRESENTATION

CONTENTS:

Sources

Engine Bleed Air Supply

Engine Bleed Valve

Overpressure Valve

Precooler

APU BleedGround Air Supply

Cross Bleed Valve

Leak detection

Monitoring

Users

Self Examination

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SYSTEM PRESENTATION

SOURCES

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.

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 enginebleed air system.

Note: This valve is springloaded closed in the absence

of upstream pressure.

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.

OVERPRESSURE VALVE

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

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 200C. 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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SYSTEM PRESENTATION

CROSS BLEED VALVE

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 independentlyof APU bleed valve.

LEAK DETECTION

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 ofsensing 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 sensingelements.

MONITORING

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 bleedsystems (except for Pylon leak and APU leak

detection).

USERS

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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SELF EXAMINATION

Does the APU bleed valve opening have priority

over the engine bleed valves opening ?

A - YES.

B - NO.

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36 - PNEUMATIC

36-00-00 SYSTEM CONTROLS PRESENTATION

CONTENTS:

Engine Bleed Valve Pushbutton

APU Bleed Valve Pushbutton

Cross Bleed Valve Selector

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SYSTEM CONTROLS PRESENTATION

ENGINE BLEED VALVE PUSHBUTTON

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 than36 psi.

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.

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.

CROSS BLEED VALVE SELECTOR

In AUTO, the cross bleed valve takes the same

configuration as the APU bleed valve (closed or open).

When OPEN is selected, the cross bleed valve is

controlled to open.

When SHUT is selected, the cross bleed valve is

controlled to close.

NOTE: If SHUT is selected and the APU bleed valve is

open, only engine 2 bleed valve is open.

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SYSTEM CONTROL PRESENTATIONTMUPNE301-P01

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36 - PNEUMATIC

36-20-00 ECAM PAGE PRESENTATION

CONTENTS:

Sources

Engine and APU Bleed Valves

Engine HP Valve

Cross Bleed Valve

Ducts

Bleed Air Parameters

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ECAM PAGE PRESENTATION

SOURCES

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.

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.

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.

DUCTS

The ducts are represented by green lines when

corresponding valves are open, and become amber or are

not displayed when the valves are closed.

BLEED AIR PARAMETERS

Bleed temperature and pressure are shown in theshaded 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:

- 290C for more than 5 sec or,

-

270C for more than 15 sec or,- 257C for more than 55 sec.

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36 - PNEUMATIC

36-10-00 ENGINE BLEED SYSTEM DESCRIPTION

CONTENTS:

General

HPV

IPC

PRV/CTS

OPV

Pr

Pt

FAV/CT

Precooler

Heat Exchanger Outlet Temperature Sensor (T)

Self Examination

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ENGINE BLEED SYSTEM DESCRIPTION

GENERAL

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.

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.

IPC

The Intermediate Pressure Check Valve protects the IP

stage from reverse flow when the High Pressure Valve

is open.

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PRV/CTS

The PRV pneumatically regulates the bleed pressure

around 44 psi.

A thermal fuse causes the valve to close in case of

engine fire (450C).

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 235C,

the PRV downstream pressure is progressively

reduced up to 17,5 psi when the temperature

gets higher than 245C.

Reverse flow protection by closing the PRV when a P

between the precooler outlet and the PRV inlet is

detected.

Electrical mode: (PRV shut-off function through the

CTS solenoid energization)

- Eng. Bleed P/B selected "OFF".

- Eng. Fire P/B selected on.

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 257C.

- Overpressure downstream of the PRV (the

pressure regulated transducer Pt senses a

pressure greater than 57 psi).

-Leak detection in pylon/wing/fuselage ductssurrounding areas.

- APU bleed valve not closed.

- Corresponding starter valve not closed.

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OPV

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.

Pr

A transducer, connected to the Bleed Monitoring

Computer, reads the regulated pressure downstream from

the PRV. This pressure is indicated on the ECAM.

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.

FAV/CT

The Fan Air Valve (FAV) pneumatically regulates the

fan air flow to the precooler for bleed air temperature

regulation (200C).

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 450C is reached.

PRECOOLER

The precooler is an air to air heat exchanger.

HEAT EXCHANGER OUTLET TEMPERATURE SENSOR (T)

The Heat Exchanger Outlet Temperature Sensor,

connected to the Bleed Monitoring Computer, reads the

regulated temperature downstream from the precooler.

This temperature is indicated on the ECAM and used to

monitor the system.

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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.

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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36 - PNEUMATIC

36-20-00 PNEUMATIC SYSTEM WARNINGS

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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PNEUMATIC SYSTEM WARNINGSTMUPNE502-P01LEVEL

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36 - PNEUMATIC SYSTEM

36-12-00 APU BLEED AIR SUPPLY / X-BLEEDSYSTEM

CONTENTS:

APU Bleed

X-Bleed System

HP Ground Connection

Self Examination

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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.

X-BLEED SYSTEM

The X-BLEED valve permits the isolation or theinterconnection 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.

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.

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APU BLEED AIR SUPPLY / X-BLEED SYSTEM - APU BLEEDTMUPNEC01-P01

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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.

How does the APIC APU Bleed valve operate ?

A - Pneumatically.

B - Fuel operated

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36 - PNEUMATIC

36-11-34 BMC INTERFACES

CONTENTS:

Inputs

Outputs

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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).

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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.

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BMC INTERFACES(OUTPUTS)TMUPNEV03-P02

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36 - LEAK DETECTION

36-22-00 LEAK DETECTION

CONTENTS:

Routing

Warning Logic

Fault Logic

Leak Consequence

Self Examination

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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.

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LEAK DETECTION - ROUTINGTMUPNED01-P01

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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.

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 leakwarnings 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.

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LEAK DETECTION - WARNING LOGICTMUPNED01-P02

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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.

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LEAK DETECTION - FAULT LOGICTMUPNED01-P03

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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.

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LEAK DETECTION - LEAK CONSEQUENCETMUPNED01-P04

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SELF EXAMINATION

Which of the following are maintained by a doubleloop 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.

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36-11-00 ENGINE BLEED AIR SUPPLYCOMPONENTS

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)

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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.

HIGH CLOSURE CONTROL SOLENOID

IDENTIFICATION

FIN: 4029KS

LOCATION

ZONE: 438, 448


It controls the HPV to close upon EEC command.

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ENGINE BLEED AIR SUPPLY COMPONENTS - HPV - HPV CLOSURE CONTROL SOLENOIDTMUPNEH05-P01

LEV

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PRESSURE REGULATING VALVE (PRV)

IDENTIFICATION

FIN: 4001HA1, 4001HA2

LOCATION

ZONE: 450, 460



BLEED PRESSURE REGULATED VALVE CONTROL SOLENOID (CTS)

IDENTIFICATION

FIN: 10HA1, 10HA2

LOCATION

ZONE: 413, 423


Three functions:- PRV electrical shut off (Solenoid)

- Temperature Limitation

- Reverse flow inhibition

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ENGINE BLEED AIR SUPPLY COMPONENTS - PRV - CTSTMUPNEH05-P02

LEV

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PRECOOLER

IDENTIFICATION

FIN: 7150HM1, 7150HM2

LOCATION

ZONE: 410, 420


Single cross pass heat exchanger.

FAN AIR VALVE (FAV)

IDENTIFICATION

FIN: 9HA1, 9HA2

LOCATION

ZONE: 453, 463



FAN AIR VALVE CONTROL THERMOSTAT (CT)

IDENTIFICATION

FIN: 7170HM1, 7170HM2

LOCATION

ZONE: 410, 420


It is pneumatically coupled to the Fan Air Valve tocontrol it open if the temperature downstream of the

precooler exceeds 200C ( 392F ).

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ENGINE BLEED AIR SUPPLY COMPONENTS - PRECOOLER - FAV - CTTMUPNEH05-P03

LEV

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INTERMEDIATE PRESSURE CHECK VALVE (IPC)

IDENTIFICATION

FIN: 7110HM1, 7110HM2

LOCATION

ZONE: 450, 460

OVERPRESSURE VALVE (OPV)

IDENTIFICATION

FIN: 5HA1, 5HA2

LOCATION

ZONE: 453, 563


The valve is spring loaded open.

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ENGINE BLEED AIR SUPPLY COMPONENTS - IPC - OPVTMUPNEH05-P04

LEVEL

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EFFECTIVITY

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REGULATED PRESSURE (Pr)

IDENTIFICATION

FIN: 8HA1, 8HA2

LOCATION

ZONE: 415, 425


It is connected to the SDAC, for pressure indication

and FAULT logic, and to the CFDIU via the BMC.

It is also connected by a sense line to the duct

downstream of the PRV.

TRANSFERRED PRESSURE (Pt)

IDENTIFICATION

FIN: 7HA1, 7HA2

LOCATION

ZONE: 415, 425


It is connected to the CFDIU via the BMC for faulty

component identification in case of failure, and to

the duct downstream of the HP bleed valve with a sense

line.

It gives the transferred relative static pressure.

HEAT EXCHANGER OUTLET TEMPERATURE SENSOR (T)

IDENTIFICATION

FIN: 6HA1, 6HA2

LOCATION

ZONE: 413, 423


It is connected to the BMC for temperature indication

(ECAM) and FAULT logic.

It also monitors the temperature downstream of the

precooler.

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ENGINE BLEED AIR SUPPLY COMPONENTS - Pr - Pt - TTMUPNEH05-P05

LEVEL

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BLEED MONITORING COMPUTER (BMC)

IDENTIFICATION

FIN: 1HA1, 1HA2

LOCATION

ZONE: 121, 122


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.

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ENGINE BLEED AIR SUPPLY COMPONENTS - BMCTMUPNEH05-P06

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TMUPNEH05

LEVEL

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36 PNEUMATIC SYSTEM

36-12-00 APU BLEED AND X BLEED COMPONENTS

CONTENTS:

APU Bleed Valve (GTCP 36-300)

APU Bleed Valve (APIC)

APU Bleed Valve (GTCP 131-9A)

X Bleed Valve

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APU BLEED VALVE (GTCP 36-300)

IDENTIFICATION

FIN: 4005KM

LOCATION

ZONE: 310


Spring loaded closed

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APU BLEED AND X BLEED COMPONENTS - APU BLEED VALVE (GTCP 36-300)TMUPNEI01-P01LE

VEL

3

EFFECTIVITY

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APU BLEED VALVE (APIC)

IDENTIFICATION

FIN: 110KD

LOCATION

ZONE: 316


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.

TMUPNEI01-T02LE

VEL

3

EFFECTIVITY

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TMUPNEI01-P02LE

VEL

3

APU BLEED AND X BLEED COMPONENTS - APU BLEED VALVE (APIC)

EFFECTIVITY

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APU BLEED VALVE (GTCP 131-9A)

IDENTIFICATION

FIN: TBD

LOCATION

ZONE: 316


Spring loaded closed.

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VEL

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APU BLEED AND X BLEED COMPONENTS - APU BLEED VALVE (GTCP 131-9A)TMUPNEI01-P03LE

VEL

3

EFFECTIVITY

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X BLEED VALVE

IDENTIFICATION

FIN: 6HV

LOCATION

ZONE: 192


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.

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APU BLEED AND X BLEED COMPONENTS - X BLEED VALVETMUPNEI01-P04LEVEL

3

EFFECTIVITY

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36-22-00 PNEUMATIC LEAK DETECTIONCOMPONENTS

CONTENTS:

Wing Leak Detection Element

Pylon Detection Element

APU Detection Element

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WING LEAK DETECTION ELEMENT

IDENTIFICATION

FIN: 21HF 79HF

LOCATION

ZONE:


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 > 124C.

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.

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PNEUMATIC LEAK DETECTION COMPONENTS - WING LEAK DETECTION ELEMENTTMUPNEK01-P01LEVEL

3

EFFECTIVITY

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PYLON DETECTION ELEMENT

IDENTIFICATION

FIN: 1HF1, 1HF2

LOCATION

ZONE: 410, 420


Located at the outlet of the pylon ventilation duct.

Triggering signal: Temperature > 204C.Only one sensing element.





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PNEUMATIC LEAK DETECTION COMPONENTS - PYLON DETECTION ELEMENTTMUPNEK01-P02L

EVEL

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APU DETECTION ELEMENT

IDENTIFICATION

FIN: 11HF 20 HF

LOCATION

ZONE: APU duct


Installed between check valve and APU compartment

Triggering signal: Temperature > 124C.Sensing elements mounted in series.





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