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A319/A320/A321TECHNICAL TRAINING MANUAL

MECHANICS / ELECTRICS & AVIONICS COURSE

21 AIR CONDITIONING



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.



GENERAL

System Presentation (1) 1..........................

System Controls and Indicating (1) 7...............

ZONE TEMPERATURE CONTROL

System Presentation (1) 13.........................

Pack Presentation (1) 19............................

System Controls Presentation (1) (A320/A319) 23...

System Controls Presentation (1) (A321) 29........ECAM Pages Presentation (1) 35.....................

System Warnings (3) 41..............................

** Flow Control & Pack Components D/O (2) 43......

** Pack Sensors Description/Operation (3) 49......

** Cockpit & Cabin Components D/O (3) 55..........

** Zone & Pack Controller Interfaces (3) 61.......

Emergency Ram Air Inlet Operation (3) 67..........

** Pack Components (3) 71..........................

Pack Sensor Components (3) 99......................

** Zone Components (3) 111.........................Emergency Ram Air Inlet Components (3) 139........

PRESSURIZATIONSystem Design Philosophy (1) 143...................

System Presentation (3) 147........................

System Controls and Indicating (1) 153............

ECAM Page Presentation (1) 157.....................

System Warnings (3) 163.............................

** System Control Interfaces (3) 179...............

** System Monitoring Interfaces (3) 185...........Components (3) 189..................................

Functional Test of MAN Motor (3) 197...............

GENERAL VENTILATIONSystem Design Philosophy (1) 201...................

AVIONICS VENTILATION

System Controls and Indicating (1) 205............

** System Warnings (3) 209.........................

System Description Operation (3) 221...............

** System Interfaces (3) 231.......................

** Components (3) 235...............................

FORWARD CARGO COMPARTMENT

VENTILATION/HEATINGSystem Presentation (1) 259........................

System Controls Presentation (3) 263...............


** System Warnings (3) 271.........................

** Components (3) 273...............................

AFT CARGO COMPARTMENT VENTILATION/HEATINGSystem Presentation (1) 289........................

System Controls Presentation (3) 293...............


** System Warnings (3) 301.........................

** Components (3) 303...............................

MAINTENANCE PRACTICESSPECIFIC PAGES

** CFDS Specific Page Presentation (3) 319......

_ A319/A320/A321 TECHNICAL TRAINING MANUAL

21 AIR CONDITIONING MECHANICS / ELECTRICS & AVIONICS COURSE

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21 - AIR CONDITIONING

21-00-00 GENERAL -SYSTEM PRESENTATION

CONTENTS:

Introduction

Presentation

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GENERAL - SYSTEM PRESENTATION

The air conditioning system maintains the air in the

pressurized fuselage zones at the correct levels of

temperature, freshness and pressure

INTRODUCTION

Air supply comes from the pneumatic system.

Then, air is regulated in temperature by the

temperature regulation sub-system.Proper ventilation of the avionics equipment is

ensured by the avionics ventilation sub-system.

The pressurization sub-system ensures a cabin altitude

compatible with crew and passenger comfort.

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PRESENTATION

Bleed air coming from the pneumatic system is

controlled in flow before reaching two air conditioning

packs which ensure basic temperature regulation.

Air delivered by the packs is mixed with recirculated

air from the cabin zones.

Fine temperature adjustment of air distributed in the

pressurized zones is obtained by controlling the amountof hot air added to the air coming from the mixer unit.

Correct pressurization is obtained by controlling the

conditioned air discharge through one outflow valve.

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21-00-00 GENERAL -SYSTEM CONTROLS AND INDICATING

CONTENTS:

Overhead Panel

Main Instrument Panel

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OVERHEAD PANEL

The air conditioning system controls are located on

the overhead panel.

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GENERAL - SYSTEM CONTROLS AND INDICATING

MAIN INSTRUMENT PANEL

The air conditioning system can be monitored on the

ECAM system display.

System information is shown on the following

pages :

- BLEED page: pack and emergency ram air.

- AIR COND page: cockpit and cabin temperature

control, cargo ventilation and heating.- PRESS page: pressurization and avionics

ventilation.

- CRUISE page: zone temperature and main

pressurization system parameters.

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21-60-00 ZONE TEMPERATURE CONTROL -SYSTEM PRESENTATION

CONTENTS:

Basic Principle

Pack Units

Mixer Unit

Hot Air Pressure Regulating Valve (PRV)

Hot Trim AirAir Distribution

Lavatory And Galley Ventilation

Temperature Regulation

Pack Controllers

Zone Controller

Self Examination

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ZONE TEMPERATURE CONTROL - SYSTEM PRESENTATION

BASIC PRINCIPLE

Hot air coming from the air bleed system is flow

regulated before entering the packs in order to be

temperature regulated.

Hot air pressure is maintained above the cabin pressure

allowing the hot air flow to join the pack air supply

when necessary.

A part of cabin air is recirculated to decrease airsupply demand.

Note: the lavatories and galleys are ventilated with

air coming from zones and main distribution

ducts.

PACK UNITS

The air flow from the Air Bleed system is regulated

by two pack flow control valves. Then two independent

packs provide regulated temperature air to the mixer

unit.

Both packs provide air at the same temperature.

MIXER UNIT

The mixer unit mixes regulated temperature air from

the packs with part of the cabin air supplied by

recirculation fans.

The mixer unit may also receive conditioned air from

a low pressure ground connection or fresh outside air

from the emergency Ram Air Inlet.

The emergency Ram Air Inlet provides outside fresh air

for ventilation of the aircraft in emergency conditions

(loss of both packs or smoke removal).

HOT AIR PRESSURE REGULATING VALVE

Hot air tapped upstream of the packs supplies the trim

air valves through a hot air pressure regulating valve.

This valve regulates the downstream pressure above the

cabin pressure.

HOT TRIM AIR

A trim air valve associated with each zone optimizes

the temperature by adding hot air, if necessary, to

the cold air coming from the mixer unit.

AIR DISTRIBUTION

The conditioned air is distributed to three main zones:

- cockpit,

-

forward cabin,- and aft cabin.

Normally the mixer unit allows the cockpit to be

supplied from pack 1 and, FWD and AFT cabins from pack

2.

LAVATORY AND GALLEY VENTILATION

The lavatory and galley ventilation system uses air

from the cabin zones. A fan extracts this air through

an outflow valve.

Note: The LAV and GALLEY extract air is used to

ventilate the cabin zone temperature sensors.

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ZONE TEMPERATURE CONTROL - SYSTEM PRESENTATION

TEMPERATURE REGULATION

The temperature regulation is automatic and controlled

by the corresponding pack controller which in turn is

controlled by the zone controller. This optimizes the

temperature regulation.

Each zone and pack controller consists of one primary

channel and one electrically independent secondary

channel respectively called primary and secondary

computers. The secondary computer acts as a back up

in case of failure of the primary computer.

PACK CONTROLLERS

Each pack controller provides:

- basic temperature regulation of its associated

pack in accordance with the demand from the

zone controller.

- and flow control and monitoring of its

associated pack in accordance with the flow

control demand from the zone controller.

ZONE CONTROLLER

The zone controller generates signals to the pack

controller for basic temperature regulation and flow

control optimization.

It optimizes the temperature regulation by means of

trim air valves to obtain the selected ambient

temperature in the related zone.

The lowest zone temperature demand is used by the Zone

Controller for basic temperature regulation to achieve

the required outlet temperature of both packs.

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SELF EXAMINATION

What is the purpose of the pack?

A - To regulate hot air pressure.

B - To adjust the temperature in the three

zones.

C - To regulate basic temperature.

What is the function of each pack controller?

A - To control the corresponding pack and

flow control valve.

B - To control the trim air valves.

C - To control the zone controller.

What is the purpose of the zone controller?

A - To control zone temperature.

B - To control the flow control valves.

C - To control the packs.

How is the basic temperature regulated by the Zone

Controller?

A - By using the lowest zone temperature

demand.

B - By using the temperature demanded in the

three zones.

C - By using the highest zone temperature

demand.

What is the function of the trim air valve?

A - To optimize the zone temperature byadding cold air.

B - To optimize the zone temperature by

adding hot air.

C - To regulate the hot air pressure.

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21-50-00 ZONE TEMPERATURE CONTROL -PACK PRESENTATION

CONTENTS:

Pack Flow Control Valve

Exchangers - Compressor

Turbine

Anti-Ice Valve

RAM Air Inlet Flap and ByPass Valve

Self Examination

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ZONE TEMPERATURE CONTROL - PACK PRESENTATION

PACK FLOW CONTROL VALVE

Each pack flow control valve is pneumatically operated

and electrically controlled. The flow regulation is

achieved by a torque motor under pack controller

control.

In case of pack compressor overheat, (230ºC = 446ºF),

the pack Flow Control Valve starts to close

pneumatically.

Note: Part of the hot air, downstream of the pack Flow

Control Valve, is sent to the hot air Pressure

Regulating Valve

Each pack Flow Control Valve is automatically

closed during either a same side engine start

sequence or an opposite side engine start

sequence(provided the crossbleed valve is

detected open)

It reopens 30 seconds after the end of any engine

start sequence.

EXCHANGERS - COMPRESSOR

Bleed air is ducted to the primary heat exchanger,

then to the compressor.

The air is cooled in the main heat exchanger. Then it

passes through the reheater, the condenser and the

water extractor in order to remove water particlesfrom the turbine air.

TURBINE

The air expands in the turbine section which results

in a very low turbine discharge air temperature. The

turbine drives the compressor and the cooling air fan.

ANTI-ICE VALVE

The pack controller controls the anti-ice valve to

pneumatically open in order to stop ice formation

across the pack condenser.

In case of complete pack controller failure, the

anti-ice valve is signalled to pneumatically control

the pack outlet temperature (to the mixer unit) to

15ºC(59ºF).

RAM AIR INLET FLAP AND BYPASS VALVE

The ByPass Valve and the RAM air inlet flap are

simultaneously controlled by the pack controller.

The ByPass Valve is electrically controlled to modulate

the pack discharge temperature by adding hot air.

The RAM air inlet flap modulates the air flow through

the exchangers.

- To increase cooling, the RAM air inlet flap

opens more and the ByPass Valve closes more.

- To increase heating, the RAM air inlet flap

closes more and the ByPass Valve opens more.

During take-off and landing, the RAM air Inlet flap

is fully closed to prevent ingestion of foreign

objects.

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SELF EXAMINATION

What is the main purpose of the anti-ice valve?

A - To stop ice formation across the primary

heat exchanger.

B - To stop ice formation across the main

heat exchanger.

C - To stop ice formation across the pack

condenser.

What is purpose of the ByPass Valve?

A - To reduce the air flow to the compressor

stage.

B - To modulate the pack discharge

temperature.

C - To increase the air flow to the turbine

stage.

What is the purpose of the RAM air inlet flap?

A - To ensure cabin ventilation in case both

packs fail.

B - To provide air to the pack compressor.

C - To modulate the main air flow through

the heat exchangers.

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21-60-00 ZONE TEMPERATURE CONTROL -SYSTEM CONTROLS PRESENTATION

CONTENTS:

Pack Flow Control Valve Pushbutton

Pack Flow Selector

Hot Air Valve Pushbutton

Temperature Selectors

Ram Air Pushbutton

Fan Pushbutton

Self Examination

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ZONE TEMPERATURE CONTROL - SYSTEM CONTROLS PRESENTATION

PACK FLOW CONTROL VALVE PUSHBUTTON

When pack 1 (or pack 2) pushbutton is pressed in, the

pack Flow Control Valve electro-pneumatically

regulates the pack inlet air flow.

When set to OFF, the pack Flow Control Valve is

maintained closed electrically.

The pack Flow Control Valve is electrically controlled

to close for:

- Same side engine start,

- Opposite side engine start provided the

crossbleed valve is open,

- Engine fire pushbutton released out,

- Ditching pushbutton set to ON.

and pneumatically controlled to close for:

- pack overheat,

-lack of air pressure.

PACK FLOW SELECTOR

The PACK FLOW selector permits selection of pack valve

flow according to number of passengers and ambient

conditions.

Select:

- "LO": if number of passengers is below 81,

- "HI": for abnormal hot and humid conditions

Note: When "LO" is selected and cooling or heating

cannot be carried out, the zone controller

automatically provides a normal flow and if

necessary increases the engine power.Whatever

the selection, the zone controller automatically

provides high flow in case of bleed air taken

from the APU or single pack operation.

HOT AIR VALVE PUSHBUTTON

When the HOT AIR pushbutton is pressed in, the hot air

Pressure Regulating Valve opens and pneumatically

regulates hot air pressure above the cabin pressure.

When set to OFF, the valve closes electrically as well

as the Trim Air Valves.

Without air pressure the hot air Pressure Regulating

Valve is springloaded closed.

In case of duct temperature above 88oC (190.4

oF) it is

automatically electrically closed.When it is electrically closed, the cockpit, FWD and

AFT Trim Air Valves are also closed.

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TEMPERATURE SELECTORS

The COCKPIT, FWD CABIN, AFT CABIN selectors enable the

selection of the desired ambient temperature in the

corresponding zone.

The zone controller takes into account the Mixer Unit

temperature (recircultated air influence) to generate

a Pack temperature demand to satisfy the lowest

selected zone temperature. It also controls Trim Air

Valves to add hot air for other zone fine temperature

adjustment.

RAM AIR PUSHBUTTON

When the RAM AIR pushbutton is set to ON, the emergency

ram air inlet flap opens, provided the ditching

pushbutton switch is in normal position. When it is

released out, the emergency ram air inlet flap closes.

NOTE: The outflow valve automatically opens toventilate the cabin when the cabin differential

pressure is less than 1 psi.

In these conditions the outflow valve half opens if

the RAM AIR P/B is pressed in. Otherwise, the valve

fully opens.

FAN PUSHBUTTON

When the CAB FANS pushbutton is pressed in, the cabinrecirculation fans run. When set to OFF, the fans stop.

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SELF EXAMINATION

What flow is delivered by the pack with the PACK

FLOW selector on LO and bleed air supplied by the

APU?

A - Low.

B - Normal.

C - High.

What happens when the RAM AIR pushbutton is set to

ON?

A - The ram air inlet flaps of the air

conditioning packs open.

B - The ram air intlet flaps of the air

conditioning packs close.

C - The emergency ram air inlet flap opens.

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21-60-00 ZONE TEMPERATURE CONTROL -SYSTEM CONTROLS PRESENTATION

CONTENTS:

Pack Flow Control Valve Pushbutton

ECON FLOW Pushbutton

Hot Air Valve Pushbutton

Temperature Selectors

Ram Air Pushbutton

Fan Pushbutton

Self Examination

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PACK FLOW CONTROL VALVE PUSHBUTTON

When the pack 1 (or pack 2) pushbutton is pressed in,

the pack Flow Control Valve electro-pneumatically

regulates the pack inlet air flow.

When set to OFF, the pack Flow Control Valve is

maintained closed electrically.

The Pack Flow Control valve is electrically controlled

to close for:

-Same side engine start,

- Opposite side engine start provided the

crossbleed valve is open,

- Engine fire pushbutton released out,

- Ditching pushbutton set to ON.

and pneumatically controlled to close for:

- pack overheat,

-

lack of air pressure.

ECON FLOW PUSHBUTTON

The ECON FLOW pushbutton permits economic or normal

pack flow according to the number of passengers and

ambient conditions (smoke removal, hot or wet

conditions).

- ON: ECON FLOW is selected,

-

OFF: Normal flow is selected. Normal flowprovides 20% more than ECON FLOW.

A Maximum flow is automatically selected in single

pack operation, with APU bleed supply or when cooling

demand cannot be satisfied.

HOT AIR VALVE PUSHBUTTON

When the hot air pushbutton is pressed in, the hot air

Pressure Regulating Valve opens and pneumatically

regulates hot air pressure above the cabin pressure.

When set to OFF, the valve closes electrically as well

as the Trim Air Valves.

Without air pressure, the hot air pressure regulating

valve is spring loaded closed.

In case of duct temperature above 88ºC(190.40ºF), it

is automatically electrically closed.

When it is electrically closed, the cockpit FWD and

AFT Trim Air Valves are also closed.

TEMPERATURE SELECTORS

The COCKPIT, FWD CABIN, AFT CABIN selectors enable the

selection of the desired ambient temperature in the

corresponding zone.The zone controller takes into account the Mixer Unit

temperature (recircultated air influence) to generate

a Pack temperature demand to satisfy the lowest

selected zone temperature. It also controls Trim Air

Valves to add hot air for other zone fine temperature

adjustment.

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RAM AIR PUSHBUTTON

When the ram air pushbutton is set to ON, the emergency

ram air inlet flap opens, provided the ditching

pushbutton switch is in normal position. When it is

released out, the emergency ram air inlet flap closes.

NOTE: The outflow valve automatically opens to

ventilate the cabin when the cabin differential

pressure is less than 1 psi.

In these conditions the outflow valve half opens ifthe RAM AIR P/B is pressed in. Otherwise, the valve

fully opens.

FAN PUSHBUTTON

When the CAB FANS pushbutton is pressed in, the cabin

recirculation fans run. When set to OFF, the fans stop.

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SELF EXAMINATION

What flow is delivered by the pack with ECON FLOW

P/B in off position?

A - ECON FLOW.

B - Normal flow + 20 %.

C - ECON FLOW + 20 %.

What happens when the RAM AIR pushbutton is set to

ON?

A - The ram air inlet flaps of the air

conditioning packs open.B - The ram air intlet flaps of the air

conditioning packs close.

C - The emergency ram air inlet flap opens.

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21-60-00 ZONE TEMPERATURE CONTROL -ECAM PAGES PRESENTATION

CONTENTS:

Pack Flow Control Valve

Pack Flow Indication

Pack Compressor Outlet Temperature

Turbine Bypass Valve Position

Pack Outlet Temperature

Emergency Ram Air Inlet Flap PositionDuct Supply

Hot Air Pressure Regulating Valve

Zone Controller Fault Indication

Cabin Fan Fault Indication

Trim Air Valves Position

Zone Duct Temperature

Zone Temperature

Temperature Unit

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ZONE TEMPERATURE CONTROL - ECAM PAGES PRESENTATION

PACK FLOW CONTROL VALVE

The pack flow control valve indication is normally

green. It becomes amber if the valve is not in agreement

with the demanded position.

PACK FLOW INDICATION

Normally, the pack flow indication is given by a green

pointer on a white scale.PACK FLOW: LO: LOW FLOW

HI: HIGH FLOW

Note: The flow control indication is amber if the pack

flow control valve is closed.

PACK COMPRESSOR OUTLET TEMPERATURE

Normally, the pack compressor outlet temperatureindication is green.

Amber if temperature above 230ºC (446ºF).

TURBINE BYPASS VALVE POSITION

Normally, the turbine bypass valve position indication

is given by a green pointer on a white scale.

- C: Cold (valve closed)

- H: Hot (valve open)- XX: invalid signal (amber).

PACK OUTLET TEMPERATURE

The pack outlet temperature indication is green.

Amber if temperature is above 90ºC (194ºF).

XX: invalid signal.

EMERGENCY RAM AIR INLET FLAP POSITION

The emergency ram air inlet flap position indication

is green when closed.

DUCT SUPPLY

Normally, the duct supply indication is green.

Amber if both pack valves are closed.

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ZONE TEMPERATURE CONTROL - ECAM PAGES PRESENTATION

HOT AIR PRESSURE REGULATING VALVE

The Hot Air pressure regulating valve indication is

green when open or closed, amber when faulty.

ZONE CONTROLLER FAULT INDICATION

The zone controller fault indication appears in case

of controller fault.

-ALTN MODE: Primary zone controller fault

- PACK REG: Zone controller fault (basic

regulation by packs only)

- No indication: Zone controller normal

operation.

CABIN FAN FAULT INDICATION

The cabin fan fault indication appears amber if a

fault is detected.No indication if no fault.

TRIM AIR VALVE POSITION

The zone trim air valve position indication is given

by a green pointer on a white scale.

- C: Cold (valve closed)

- H: Hot (valve open)

-XX: Invalid signal.

ZONE DUCT TEMPERATURE

Normally, the zone duct temperature indication is

green.

Amber if higher than 80ºC (176ºF).

ZONE TEMPERATURE

The zone temperature indication is green.

XX: Invalid signal.

The cockpit and cabin compartment temperature is also

displayed on the CRUISE ECAM page.

Zone temperature is normally displayed in green.

XX(amber): Temperature data is not available.

TEMPERATURE UNIT

The temperature unit of measurement is indicated incyan.

ºF: Degrees Fahrenheit.

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21-60-00 ZONE TEMPERATURE CONTROL -SYSTEM WARNINGS

CONTENTS:

Pack 1 (or 2) Overheat

Pack 1 (or 2) Fault

Pack 1 (or 2) Off

Pack 1 (or 2) Regulation Fault

Pack 1 + 2 Fault

Cockpit (or FWD Cabin or AFT Cabin) Duct OverheatHot Air Fault

Trim Air Sys Fault (Trim Air Valve Fault)

Zone Regulation Fault

Left + Right Cabin Fan Fault

Lavatory + Galley Fan Fault

Trim Air Sys Fault (Trim Air Sys Overpressure)

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21-50-00 ZONE TEMPERATURE CONTROL -FLOW CONTROL & PACK COMPONENTSD/O

CONTENTS:

Ozone Filter (Option)

Flow Sensor - Flow Control Valve

ByPass Valve (BPV)

Ram Air Inlet Flap

Anti-ice Valve (AIV)Air Cycle Machine (ACM)

Exchangers - Reheater - Condenser

Water Extractor

Check valve

Self Examination

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ZONE TEMPERATURE CONTROL - FLOW CONTROL & PACK COMPONENTS D/O

OZONE FILTER (OPTION)

An ozone filter is installed upstream of each Flow

Control Valve. It is used for catalytic removal of

ozone from the hot bleed air supplied to the pack.

FLOW SENSOR - FLOW CONTROL VALVE

A flow sensor connected to the FCV senses a

differential pressure equivalent to the airflowthrough the valve inlet. This differential pressure

is transformed into an electrical signal and sent to

the pack controller for actual flow calculation.

According to the actual flow calculation and the flow

demand, the pack controller generates an FCV drive

signal in order to control the FCV torque motor (M).

The valve butterfly is thus electro-pneumatically

operated.

The FCV has a shut-off solenoid (S), which is energizedin case of:

- engine start,

- opposite engine start provided the crossbleed

valve is detected open (the FCV reopens 30

seconds after the end of the engine start

sequence),

- ENG FIRE P/B released out,

- DITCHING P/B pressed in,

-applicable PACK P/B set to OFF.

The FCV also automatically closes in case of:

- low bleed pressure (valve spring loaded

closed),

- compressor overheat (muscle pressure venting

by means of the Compressor PNeumatic Overheat

Sensor(CPNOH)).

BYPASS VALVE (BPV)

The ByPass Valve regulates the pack discharge

temperature by adding hot bleed air to the air cycle

machine for quick pack response.

The ByPass Valve is electrically operated by a stepper

motor (M) controlled by the pack controller according

to the the water extractor temperature.

RAM AIR INLET FLAP

The ram air inlet flap modulates the airflow through

the exchangers in order to control the temperature of

the pack outlet.

The ram air inlet flap is actuated by an electric

actuator controlled by the pack controller according

to the water extractor temperature in order to obtain

optimum pack cooling airflow. The ram air inlet flap

closes during take-off and landing.

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ZONE TEMPERATURE CONTROL - FLOW CONTROL & PACK COMPONENTS D/O T M U T E M D

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21 AIR CONDITIONINGMECHANICS / ELECTRICS & AVIONICS COURSE



ZONE TEMPERATURE CONTROL - FLOW CONTROL & PACK COMPONENTS D/O

ANTI-ICE VALVE (AIV)

The Anti-Ice Valve removes any excessive ice formation

across the condenser or maintains the pack outlet

temperature at a fixed value, if the pack controller

is unable to control the ByPass Valve.

The Anti-Ice Valve is pneumatically operated and

electrically controlled by a solenoid (S).

- Solenoid energized: the Anti-Ice Valve

pneumatically operates as an anti-ice function.- Solenoid de-energized: the Anti-Ice Valve

pneumatically operates as a temperature control

valve. It maintains a pack outlet temperature

of 15°C (59°F).

The anti-ice function is provided by two ∆P relays for

high and low pressure condenser flows. When the ∆P

increases due to ice build up restricting the air flow,

the concerned relays control the Anti-Ice Valve to an

open position.The Pack Outlet Pneumatic Sensor (POPS) is used only

to modulate the Anti-Ice Valve to control pack

discharge temperature at a fixed value in case of pack

controller failure.

AIR CYCLE MACHINE (ACM)

The Air Cycle Machine which consists of a turbine, a

compressor and a fan, cools the air.The main component of the air cycle machine is a

rotating shaft. A turbine, a compressor and a fan are

mounted along the shaft.

EXCHANGERS - REHEATER - CONDENSER

The air passes through two heat exchangers and a

reheater before it enters the condenser which drops

the air temperature well below dew point.

The cooling agent for the primary heat exchanger and

the main heat exchanger is outside ram air.

The reheater is used to raise the temperature of the

air before reaching the turbine inlet to vaporize any

remaining water droplets for turbine protection.

WATER EXTRACTOR

The water extractor collects water droplets and drains

them inside the water extractor body in order to spray

the collected water into the ram air flow of the

exchangers, to increase the cooling efficiency.

CHECK VALVE

The pack downstream check valve stops leakage of air

from the distribution system when the Flow Control

Valve is closed.

The check valve is fitted to the pressure bulkhead.

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SELF EXAMINATION

How is the Flow Control Valve actuated ?A - By means of a stepper motor.

B - By means of a torque motor.

C - By means of an AC electrical motor.

If the pack controller fails, the pack outlet

temperature is controlled by:

A - The Flow Control Valve.

B - The ByPass Valve.

C - The Anti-Ice Valve.

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21-60-00 ZONE TEMPERATURE CONTROL -PACK SENSORS D/O

CONTENTS:

Pack Inlet Pressure Sensor

Flow Sensor

Compressor Temperature Sensor

Compressor Pneumatic Overheat Sensor

Compressor Overheat Sensor

Water Extractor Temperature SensorPack Outlet Pneumatic Sensor

Pack Outlet Temperature Sensor

Self Examination

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ZONE TEMPERATURE CONTROL - PACK SENSORS D/O

PACK INLET PRESSURE SENSOR

The pack inlet pressure sensor signals a pack inlet

pressure drop to the primary computer of the pack

controller.

It is used to determine the appropriate ByPass Valve

position.

When the pack inlet pressure is low, the ByPass Valve

is controlled to a more open position in order to

decrease the differential pressure of the airconditioning pack. At the same time, the RAM air inlet

flap is controlled to a more open position to

compensate for the decreased efficiency of the

turbine/compressor cycle.

Also, when engines are at idle, if the cooling demand

cannot be satisfied, the engine idle setting can be

changed by a thrust demand. The Zone Controller sends

this thrust demand to the Engine Interface Units

depending on the bleed air pressure detected by thesensor.

FLOW SENSOR

A flow sensor measures a differential pressure at the

Flow Control Valve inlet.

This ∆P, which is equivalent to the airflow, is

converted into an electrical signal and sent to the

secondary computer of the pack controller.

It is used for ECAM display and FCV control.

COMPRESSOR TEMPERATURE SENSOR

The compressor temperature sensor signals compressor

outlet temperature to the primary computer of the pack

controller for pack temperature control and for

overheat detection.

Pack temperature control:

- up to 180°C (385°F): normal operation.

- 180°C to 220°C (428°F): the RAM air inlet flap

opens more in order to increase the RAM airflow.

The pack FAULT light comes on in case of pack overheat

of 260°C (500°F), or if 230°C (446°F) is detected four

times during one flight.

COMPRESSOR PNEUMATIC OVERHEAT SENSOR

In case of overheat, the compressor pneumatic overheat

sensor causes venting of the Flow Control Valve musclepressure in order to close the valve.

In case of compressor outlet overheat, the Flow Control

Valve starts to close at 230°C (446°F) in order to

avoid reaching 260°C (500°F).

NOTE: 260°C is the temperature threshold for warning

activation.

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ZONE TEMPERATURE CONTROL - PACK SENSORS D/O

COMPRESSOR OVERHEAT SENSOR

The compressor overheat sensor signals the compressor

outlet temperature to the secondary computer of the

pack controller for overheat detection and indication

on the ECAM display.

The pack FAULT light comes on in case of pack overheat

of 260°C (500°F), or if 230°C (446°F) is detected four

times during one flight.

WATER EXTRACTOR TEMPERATURE SENSOR

The water extractor temperature sensor signals the

water extractor temperature for the pack outlet

temperature control.

The water extractor temperature sensor consists of two

thermistors, one connected to the primary computer,

the other to the secondary computer. They are used to

modulate the pack outlet temperature.

PACK OUTLET PNEUMATIC SENSOR

The pack outlet pneumatic sensor adjusts the anti-ice

valve muscle pressure to maintain the pack outlet

temperature at a fixed value when the control of the

ByPass Valve is lost.

The pack outlet pneumatic sensor pneumatically

controls the anti-ice valve to maintain the pack outlet

temperature at about 15°C (59°F).

PACK OUTLET TEMPERATURE SENSOR

The pack outlet temperature sensor signals the pack

outlet temperature to the secondary computer of the

pack controller for ECAM display.

Pack outlet temperature sensor also provides pack

overheat warning indications if the pack outlet

temperature exceeds 95°C (203°F).

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SELF EXAMINATION

Which sensor pneumatically closes the Flow ControlValve in case of pack overheat?

A - The bleed temperature sensor.

B - The compressor overheat sensor.

C - The compressor pneumatic overheat sensor.

Which sensor may signal pack overheat to the pack

controller?

A - The compressor overheat sensor.

B - The compressor temperature sensor.C - A or B.

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21-60-00 ZONE TEMPERATURE CONTROL -COCKPIT & CABIN COMPONENTS D/O

CONTENTS:

Mixer Unit

Mixer Unit Temperature Sensors

Mixer Unit Flap

Trim Air Pressure Regulating Valve (PRV)

Hot Air Pressure Switch

Trim Air Valves (TAV)Duct Temperature Sensors

Zone Temperature Sensors

Self Examination

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ZONE TEMPERATURE CONTROL - COCKPIT & CABIN COMPONENTS D/O

MIXER UNIT

The mixer unit mixes air from packs and recirculated

air from the cabin prior to distribution to each zone.

The mixer unit, installed under the cabin floor, uses

cabin air which has entered the underfloor area and

has been drawn through recirculation filters by

recirculation fans. This air is mixed with conditioned

air from the packs.

The quantity of cabin air mixed with conditioned airvaries from 37% to 51%.

MIXER UNIT SENSORS

There are two mixer unit temperature sensors, one on

either side of the mixer unit.

They indicate the actual temperature of the mixer unit

to the zone controller.

Each mixer unit temperature sensor consists of two

thermistors. One connected to the primary computer and

the other to the secondary computer.

MIXER UNIT FLAP

The mixer unit flap ensures sufficient flight deck air

supply if pack 1 is selected off.

An electrically operated mixer unit flap is installed

to ensure that sufficient fresh air is delivered to

the cockpit in case of pack 1 failure.

TRIM AIR PRESSURE REGULATING VALVE (PRV)

The trim air Pressure Regulating Valve is pneumatically

operated and electrically controlled by two solenoids.

One solenoid controls the ON/OFF function and the

second solenoid controls the safety function.

The trim air Pressure Regulating Valve regulates the

pressure of the air supplied to the trim air valves,

4 psi above the cabin pressure.

When any duct temperature exceeds 80

o

C (176

o

F), thesafety function solenoid S1 is energized and reduces

downstream pressure of the valve, from 4 psi to 2 psi

above the cabin pressure. It will be de-energized as

soon as the temperature returns below 70oC (158

oF).

The ON/OFF function solenoid S2 de-energizes when the

HOT AIR pushbutton is set to OFF or when any duct

temperature is above 88oC (190

oF) or above 80

oC (176

oF)

four times in one flight leg. This closes the valve.

HOT AIR PRESSURE SWITCH

Due to a malfunction of the trim air Pressure

Regulating Valve, the hot air pressure switch signals

overpressure to the secondary computer of the zone

controller for ECAM display and the Centralized Fault

Display System (CFDS).

If pressure in the system exceeds 6.5 psi above the

cabin pressure, the zone controller activates the ECAM

system. This signal stays until the pressure falls

below 5 psi.

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ZONE TEMPERATURE CONTROL - COCKPIT & CABIN COMPONENTS D/O

TRIM AIR VALVES (TAV)

The Trim Air Valves allow the zone temperature to be

adjusted by modulating the hot air flow added to air

from the mixer unit.

The TAVs close when the trim air Pressure Regulating

Valve closes.

The butterfly of the Trim Air Valves is controlled by

a stepper motor.

The Trim Air Valve position determination is based on

the step counting principle.

DUCT TEMPERATURE SENSORS

Each duct temperature sensor detects duct temperature

for the corresponding zone temperature control,

indication and overheat detection to the zone

controller.

Each duct temperature sensor consists of two

thermistors, one connected to the primary computer and


Each thermistor provides control, indication and

overheat detection (88°C (190°F) or 4 x 80°C (176°F)).

ZONE TEMPERATURE SENSORS

Each zone sensor detects corresponding zone

temperature for zone temperature control and

indication on ECAM display.

Each zone temperature sensor consists of two

thermistors, one connected to the primary computer and


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SELF EXAMINATION

If a duct overheat is detected:A - The mixer unit flap closes.

B - The PRV and the TAVs close.

C - The PRV and the corresponding TAV close.

The mixer unit flap opens if:

A - HOT AIR pb is set to OFF.

B - PACK 2 pb is set to OFF.

C - PACK 1 pb is set to OFF.

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21-60-00 ZONE TEMPERATURE CONTROL -ZONE AND PACK CONTROLLERINTERFACES

CONTENTS:

General

System Data Acquisition Concentrator (SDAC)

Engine Interface Unit (EIU)

Air Data Inertial Reference Unit 1 (ADIRU 1)

Electronic Control Box (ECB)

Data Management Unit (DMU)

Centralized Fault Display Interface Unit (CFDIU)

Zone And Pack Controllers

Fans Parameters

Anti-ice And Pneumatic Parameters

Landing Gear Control Interface Unit 2 (LGCIU 2)

Braking And Steering Control Unit (BSCU)

Self Examination

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ZONE TEMPERATURE CONTROL - ZONE AND PACK CONTROLLER INTERFACES





ZONE TEMPERATURE CONTROL ZONE AND PACK CONTROLLER INTERFACES

GENERAL

Zone controller: crosstalk via internal bus.

Pack controller: crosstalk via RS232 connection.

SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC)

System data information is transmitted to the System

Data Acquisition Concentrator via ARINC buses for

system monitoring.

Signal: System data information (Temperature, valve

position ...), used for warning and display.

ENGINE INTERFACE UNIT (EIU)

The zone controller provides data to both Engine

Interface Units. Each EIU provides one discrete to the

zone controller and one discrete to the corresponding

pack controller.

EIU 1,2 to Pack Controller:

- Signal: take-off thrust, used for pack RAM air

inlet closure

EIU 1,2 to Zone Controller:

- Signal: HP fuel valve position, used for bleed

demand calculation.

Zone Controller to Engine Interface Unit 1, 2:

- signal: increase engine power, used for bleed

air flow increase.

- signal: bleed and anti-ice status, used for

thrust limit calculation.

AIR DATA INERTIAL REFERENCE UNIT 1 (ADIRU 1)

The Air Data Inertial Reference Unit 1 sends data to

the zone controller for zone and pack temperature

control.

Signal: aircraft altitude, used for zone temperature

compensation and pack water extractor outlet

temperature limitation.

ELECTRONIC CONTROL BOX (ECB)

The zone controller sends data to the Electronic

Control Box and receives an APU bleed valve open

discrete.

Zone controller to ECB:

- Signal: increase APU flow, used for increased

bleed air flow.

ECB to zone controller:

- Signal: APU bleed valve open, used for flow

demand calculation.

DATA MANAGEMENT UNIT (DMU)

The zone and pack controllers send system main status

data to the Data Management Unit for maintenance

monitoring purposes.

Zone controller to DMU:

- TAPRV position

Pack controllers to DMU:

- pack flow, water extractor and pack

compressor discharge temperatures, bypass

valve and RAM air inlet flap positions.

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ZONE TEMPERATURE CONTROL - ZONE AND PACK CONTROLLER INTERFACES





CENTRALIZED FAULT DISPLAY INTERFACE UNIT (CFDIU)

The zone controller sends BITE data to the Centralized

Fault Display Interface Unit for system monitoring.

Signal:BITE data, used for temperature control system

monitoring.

ZONE AND PACK CONTROLLERS

The pack controllers mainly receive temperature

demand, flow demand and CFDIU control signals from the

zone controller and send back maintenance data signals.

Zone controller to pack controllers:

- Signal: Temperature demand, zone controller

status, pack ARINC reception status, aircraft

altitude, APU bleed valve position, used for

pack temperature control.

- Signal: Flow demand, used for flow control.

- Signal: BITE command, for CFDIU.

Pack controllers to zone controller:

- Signal: pack control status, zone ARINC

reception status, BITE information, used for

temperature control system monitoring.

FANS PARAMETERS

The zone controller receives discrete signals from

recirculation and toilet fans for monitoring.

Signal: recirculation, toilet and galley and AFT cargo

ventilation fans operation, used for monitoring for

transmission to SDACs and CFDIU.

ANTI-ICE AND PNEUMATIC PARAMETERS

Anti-ice and pneumatic parameters are used to detect

faults and to ascertain the status of the bleed air

system for transmission to CFDIU and EIUs.

Signals: valve positions, low and high pressure,..

etc..., used for anti-ice system fault detection for

the CFDIU and thrust limit calculation for the EIUs.

LANDING GEAR CONTROL INTERFACE UNIT 2 (LGCIU 2)

The Landing Gear Control Interface Unit 2 sends a

GROUND/FLIGHT signal to both pack controllers for pack

RAM air inlet flap operation.

Signal: ground/flight, used for pack RAM air inlet

flap closure during take-off and landing phases.

BRAKING AND STEERING CONTROL UNIT (BSCU)

The BSCU sends a wheel speed signal to both pack

controllers for pack RAM air inlet flap operation.

Signal: wheel speed, used for pack RAM air inlet flap

closure during take-off and landing phases.

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SELF EXAMINATION





The pack controllers send to the zone controller:A - The flow demand signal.

B - The BITE demand signal.

C - BITE information and pack status signals.

To close the pack RAM air inlet flap, the pack

controller needs information from:

A - The ECB.

B - The anti-ice system.

C - LGCIU 2, BSCU and EIUs.

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21-55-00 ZONE TEMPERATURE CONTROL -EMERGENCY RAM AIR INLET OPERATION

CONTENTS:

General

Emergency Ram Air Inlet Flap Operation

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ZONE TEMPERATURE CONTROL - EMERGENCY RAM AIR INLET OPERATION





GENERAL

The aircraft is equipped with one emergency ram air

inlet flap located at the lower left-hand side of the

fuselage, sharing the same duct with the low pressure

ground connection.

EMERGENCY RAM AIR INLET FLAP OPERATION

In case of failure of both packs, an emergency ram air

inlet flap can be opened for aircraft ventilation or

smoke removal.

In case of smoke removal or loss of both packs, the

RAM AIR pushbutton must be set to ON.

When set to ON, and if DITCHING is not selected, the

EMERGENCY RAM AIR INLET FLAP opens.

The flap, installed between LP GND CONNECTION and RAM

AIR INLET, closes one side of the duct when air is

supplied from the other side. The check valve staysclosed.

The aircraft must descend to less than 10000 ft.

When the cabin to ambient air differential pressure

is less than 1 psi, the pressure controller half opens

the outflow valve.

The air then goes through the check valve to the mixing

unit.

T M U T E M F

0 2 - T

0 1

L E

V E L

3

EFFECTIVITY

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Nov 30/99

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - EMERGENCY RAM AIR INLET OPERATION T M U T E M F

0 2 - P

0 1

L E

V E L

3

EFFECTIVITY

21-55-00Page 3

Nov 30/99

U F F

4 2 0 0

Page 69EFFECTIVITY

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T M U T E M F

0 2

L E V E L

3

EFFECTIVITY

21-55-00Page 4

Nov 30/99

U F F

4 2 0 0

Page 70EFFECTIVITY

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21-50-00 ZONE TEMPERATURE CONTROL -PACK COMPONENTS

CONTENTS:

Pack Controllers

Air Conditioning Packs

Flow Control Valve (FCV)

Flow Control Valve Removal/Installation

ByPass Valve (BPV)

Ram Air Inlet (RAI) Actuator

Anti-Ice Valve (AIV)

Pack Downstream Check Valve

Air Cycle Machine (ACM)

Primary Heat Exchanger

Main Heat Exchanger

Reheater

Condenser

Water Extractor

Water Injector

Ozone Filter (Option)

T M U T E M N

0 A

L E V E L

3

EFFECTIVITY

21-50-00Page 1

Jun 31/00

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS





PACK CONTROLLERS

IDENTIFICATION

FIN: 7HM, 27HM

LOCATION

ZONE: 121, 122

COMPONENT DESCRIPTION

PACK CONTROLLER FUNCTION PRIMARY SECONDARY

Flow setting modulation yes no

Pack temp. control from zone

controller demand yes yes

ByPass Valve control yes yes

Ram air flow modulation yes no

OVHT detection and indication yes yes

Pack temp control

to 15°C (59°F) no yes

Failure analysis yes yesBITE and info transmission

to zone controller yes no

ECAM indications no yes

Anti-Ice Valve control yes yes

Data handling yes yes

T M U T E M N

0 A - T

0 1

L E V E L

3

EFFECTIVITY

21-50-00Page 2

Jun 31/00

U F F

4 2 0 0

Page 72EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - PACK CONTROLLERS T M U T E M N

0 A - P

0 1

L E V E L

3

EFFECTIVITY

21-50-00Page 3

Jun 31/00

U F F

4 2 0 0

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ALL






AIR CONDITIONING PACKS

IDENTIFICATION

FIN: 10HM, 11HM

LOCATION

ZONE: 191, 192


The air conditioning packs are identified as PACK 1

and PACK 2 depending on the pneumatic manifold to which

they are connected.

T M U T E M N

0 A - T

0 2

L E V E L

3

EFFECTIVITY

21-50-00Page 4

Jun 31/00

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - AIR CONDITIONING PACKS T M U T E M N

0 A - P

0 2

L E V E L

3

EFFECTIVITY

21-50-00Page 5

Jun 31/00

U F F

4 2 0 0

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FLOW CONTROL VALVE





FLOW CONTROL VALVE

IDENTIFICATION

FIN: 8HB, 11HB

LOCATION

ZONE: 182, 191


The flow control valves have two functions in the air

conditioning system. Their primary function is tocontrol the amount of air flowing through the system.

The secondary function is to provide an automatic or

manually selectable shut-off function.

T M U T E M N

0 A - T

0 3

L E V E L

3

EFFECTIVITY

21-50-00Page 6

Jun 31/00

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - FLOW CONTROL VALVE T M U T E M N

0 A - P

0 3

L E V E L

3

EFFECTIVITY

21-50-00Page 7

Jun 31/00

U F F

4 2 0 0

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FLOW CONTROL VALVE REMOVAL/INSTALLATION





FLOW CONTROL VALVE REMOVAL/INSTALLATION

IDENTIFICATION

FIN: 8HB, 11HB

LOCATION

ZONE: 182, 191


The Flow Control Valve is connected via V-clamps to

the bleed air duct on one side and the heat exchangerduct on the other side.

T M U T E M N

0 A - T

0 4

L

E V E L

3

EFFECTIVITY

21-50-00Page 8

Jun 31/00

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - FLOW CONTROL VALVE R/I T M U T E M N

0 A - P

0 4

L

E V E L

3

EFFECTIVITY

21-50-00Page 9

Jun 31/00

U F F

4 2 0 0

Page 79EFFECTIVITY

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BYPASS VALVE (BPV)





IDENTIFICATION

FIN: 10HH, 30HH

LOCATION

ZONE: 191, 192


The ByPass Valve (BPV) is electrically controlled andactuated by a stepper motor. Limit switches signal

fully open or fully closed positions to the pack

controller secondary computer.

Pack controller primary and secondary computers

receive a step counting signal used for the ByPass

Valve position determination.

A manual override and visual position indicator device

is installed on the bottom of the shaft.

T M U T E M N

0 A - T

0 5

L

E V E L

3

EFFECTIVITY

21-50-00Page 10

Jun 31/00

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - BYPASS VALVE (BPV) T M U T E M N

0 A - P

0 5

L

E V E L

3

EFFECTIVITY

21-50-00Page 11

Jun 31/00

U F F

4 2 0 0

Page 81EFFECTIVITY

ALL


RAM AIR INLET (RAI) ACTUATOR





IDENTIFICATION

FIN: 8HH, 28HH

LOCATION

ZONE: 191, 192


The ram air inlet actuator has:

-an AC motor, electrically supplied by the packcontroller (two different motor suppliers),

- two limit switches (one for the closed

position, the other for the 70% open position).

These send signals to the secondary computer,

- two potentiometers (one for control through

the primary computer, the other for

indication through the secondary computer).

T M U T E M N

0 A - T

0 6

L

E V E L

3

EFFECTIVITY

21-50-00Page 12

Jun 31/00

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - RAM AIR INLET (RAI) ACTUATOR T M U T E M N

0 A - P

0 6

L

E V E L

3

EFFECTIVITY

21-50-00Page 13

Jun 31/00

U F F

4 2 0 0

Page 83EFFECTIVITY

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ANTI-ICE VALVE





IDENTIFICATION

FIN: 17HH, 37HH

LOCATION

ZONE: 191, 192


The Anti-Ice Valve is electrically controlled and

pneumatically operated.Anti-ice mode: valve energized.

The valve opens if ice is detected across the high or

low pressure side of the condenser.

Pneumatic temperature control mode: valve

de-energized.

The valve is controlled by a pneumatic sensor to get

a fixed temperature (15ºC or 59ºF).

T M U T E M N

0 A - T

0 7

L

E V E L

3

EFFECTIVITY

21-50-00Page 14

Jun 31/00

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - ANTI-ICE VALVE T M U T E M N

0 A - P

0 7

L

E V E L

3

EFFECTIVITY

21-50-00Page 15

Jun 31/00

U F F

4 2 0 0

Page 85EFFECTIVITY

ALL


PACK DOWNSTREAM CHECK VALVE





IDENTIFICATION

FIN: 15HM, 16HM

LOCATION

ZONE: 191, 192


The pack downstream check valve is of the single spring

loaded flap type, directly bolted to the pressurebulkhead. It stops leakage of air if the pack is

switched off.

T M U T E M N

0 A - T

0 8

L E V E L

3

EFFECTIVITY

21-50-00Page 16

Jun 31/00

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - PACK DOWNSTREAM CHECK VALVE T M U T E M N

0 A - P

0 8

L E V E L

3

EFFECTIVITY

21-50-00Page 17

Jun 31/00

U F F

4 2 0 0

Page 87EFFECTIVITY

ALL


AIR CYCLE MACHINE (ACM)





IDENTIFICATION

FIN: 10HM1, 11HM1

LOCATION

ZONE: 191, 192


The main component of the air-cycle machine is a

rotating shaft. A turbine, a compressor and a fan aremounted along this shaft. The shaft rotates on two

self-acting foil-air-bearings. A double self-acting

air-thrust bearing takes the axial thrust loads.

T M U T E M N

0 A - T

0 9

L E V E L

3

EFFECTIVITY

21-50-00Page 18

Jun 31/00

U F F

4 2 0 0

Page 88EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - AIR CYCLE MACHINE (ACM) T M U T E M N

0 A - P

0 9

L E V E L

3

EFFECTIVITY

21-50-00Page 19

Jun 31/00

U F F

4 2 0 0

Page 89EFFECTIVITY

ALL


PRIMARY HEAT EXCHANGER

IDENTIFICATION

MAIN HEAT EXCHANGER

IDENTIFICATION





IDENTIFICATION

FIN: 10HM6, 11HM6

LOCATION

ZONE: 191, 192


The primary heat exchanger is of the plate and fin

type with a single-pass crossflow configuration. Itcools the hot bleed air before it enters the

air-cycle-machine compressor. The cooling agent is

ambiant RAM air.

IDENTIFICATION

FIN: 10HM7, 11HM7

LOCATION

ZONE: 191, 192


The main heat exchanger is of the plate and fin type

with a counterflow configuration. It is installedbetween the air-cycle-machine compressor and turbine.

The cooling agent is ambiant air.

T M U T E M N

0 A - T

1 0

L E V E L

3

EFFECTIVITY

21-50-00Page 20

Jun 31/00

U F F

4 2 0 0

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - HEAT EXCHANGERS T M U T E M N

0 A - P

1 0

L E V E L

3

EFFECTIVITY

21-50-00Page 21

Jun 31/00

U F F

4 2 0 0

Page 91EFFECTIVITY

ALL


REHEATER

IDENTIFICATION

CONDENSER

IDENTIFICATION





IDENTIFICATION

FIN: 10HM3, 11HM3

LOCATION

ZONE: 191, 192


The reheater is of the plate and fin type with a single

crossflow configuration. It uses turbine inlet air tofurther cool air leaving the main heat exchanger.

IDENTIFICATION

FIN: 10HM2, 11HM2

LOCATION

ZONE: 191, 192


The condenser is of the tube type with a single pass

crossflow configuration. It cools air leaving thereheater below its dew point. This causes the moisture

in the air to condense into droplets. Water is then

removed by the water extractor.

T M U T E M N

0 A - T

1 1

L E V E L

3

EFFECTIVITY

21-50-00Page 22

Jun 31/00

U F F

4 2 0 0

Page 92EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - REHEATER/CONDENSER T M U T E M N

0 A - P

1 1

L E V E L

3

EFFECTIVITY

21-50-00Page 23

Jun 31/00

U F F

4 2 0 0

Page 93EFFECTIVITY

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WATER EXTRACTOR

IDENTIFICATION

WATER INJECTOR

IDENTIFICATION





FIN: 10HM8, 11HM8

LOCATION

ZONE: 191, 192


Swirl vanes centrifuge the water droplets onto the

inner surface of the water extractor body. The wateris then drained to the water injectors.

FIN: 20HM, 21HM

LOCATION

ZONE: 191, 192


The water injectors are installed in the RAM air inlet

duct, upstream of the heat exchangers. The water fromthe extractors is delivered under pressure into the

RAM airflow to increase the cooling capacity.

T M U T E M N

0 A - T

1 2

L E V E L

3

EFFECTIVITY

21-50-00Page 24

Jun 31/00

U F F

4 2 0 0

Page 94EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK COMPONENTS - WATER INJECTOR/EXTRACTOR T M U T E M N

0 A - P

1 2

L E V E L

3

EFFECTIVITY

21-50-00Page 25

Jun 31/00

U F F

4 2 0 0

Page 95EFFECTIVITY

ALL


OZONE FILTER (OPTION)

IDENTIFICATION





FIN: 100HM, 101HM

LOCATION

ZONE: 191, 192


The ozone filters (optional) are installed upstream

of the Flow Control Valves.

T M U T E M N

0 A - T

1 3

L E V E L

3

EFFECTIVITY

21-50-00Page 26

Jun 31/00

U F F

4 2 0 0

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T M U T E M N

0 A - P

1 3

L E V E L

3

ZONE TEMPERATURE CONTROL - PACK COMPONENTS - OZONE FILTER (OPTION)

EFFECTIVITY

21-50-00Page 27

Jun 31/00

U F F

4 2 0 0

Page 97EFFECTIVITY

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T M U T E M N

0 A

L E V E

L

3

EFFECTIVITY

21-50-00Page 28

Jun 31/00

U F F

4 2 0 0

Page 98EFFECTIVITY

ALL


21-50-00 ZONE TEMPERATURE CONTROL -

PACK SENSOR COMPONENTS

CONTENTS:





CONTENTS:

Flow Sensor

Pack Inlet Pressure Sensor

Compressor Overheat Pneumatic Sensor

Compressor Temperature Sensor

Compressor Overheat Sensor

Pack Outlet Temperature Sensor

Water Extractor Temperature SensorPack Outlet Pneumatic Sensor

T M U T E M R

0 9

L E V E L

3

EFFECTIVITY

21-50-00Page 1

Nov 30/99

U F F

4 2 0 0

Page 99EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK SENSOR COMPONENTS

FLOW SENSOR

IDENTIFICATION

FIN: 9HB, 10HB





FIN: 9HB, 10HB

LOCATION

ZONE: 192, 191


It measures a differential pressure which is equivalent

to the airflow through the valve.The ∆P is converted into an electrical signal, which

is sent to the pack controller.

T M U T E M R

0 9 - T

0 1

L E V E L

3

EFFECTIVITY

21-50-00Page 2

Nov 30/99

U F F

4 2 0 0

Page 100EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK SENSOR COMPONENTS - FLOW SENSOR T M U T E M R

0 9 - P

0 1

L E V E L

3

EFFECTIVITY

21-50-00Page 3

Nov 30/99

U F F

4 2 0 0

Page 101EFFECTIVITY

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PACK INLET PRESSURE SENSOR

IDENTIFICATION

FIN: 16HH, 36HH

COMPRESSOR OVERHEAT PNEUMATIC SENSOR

IDENTIFICATION

FIN: 10HM9, 11HM9





,

LOCATION

ZONE: 191, 192


It signals pressure to the primary computer. If the

pressure is too low, the bypass valve is controlled

to a more open position to decrease the delta P of the

pack.

,

LOCATION

ZONE: 191, 192


Pneumatically connected to the flow control valve to

close it in case of overheat detection.

(It vents the FCV muscle pressure).

T M U T E M R

0 9 - T

0 2

L E V E L

3

EFFECTIVITY

21-50-00Page 4

Nov 30/99

U F F

4 2 0 0

Page 102EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK SENSOR COMPONENTS - PACK INLET PRESSURE SENSOR -COMPRESSOR OVERHEAT PNEUMATIC SENSOR

T M U T E M R

0 9 - P

0 2

L E V E L

3

EFFECTIVITY

21-50-00Page 5

Nov 30/99

U F F

4 2 0 0

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COMPRESSOR TEMPERATURE SENSOR

IDENTIFICATION

FIN: 12HH, 32HH

COMPRESSOR OVERHEAT SENSOR

IDENTIFICATION

FIN: 15HH, 35HH





LOCATION

ZONE: 191, 192


The compressor temperature sensor is used for pack

temperature control functions and pack overheat

detection.

It is connected to the pack controller primary

computer.

LOCATION

ZONE: 191, 192


It is connected to the pack controller secondary

computer for overheat detection.

The sensor also provides compressor outlet temperature

on ECAM.

T M U T E M R

0 9 - T

0 3

L E V E L

3

EFFECTIVITY

21-50-00Page 6

Nov 30/99

U F F

4 2 0 0

Page 104EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK SENSOR COMPONENTS - COMPRESSOR TEMPERATURE SENSOR -COMPRESSOR OVERHEAT SENSOR

T M U T E M R

0 9 - P

0 3

L E V E L

3

EFFECTIVITY

21-50-00Page 7

Nov 30/99

U F F

4 2 0 0

Page 105EFFECTIVITY

ALL


PACK OUTLET TEMPERATURE SENSOR

IDENTIFICATION

FIN: 13HH, 34HH

WATER EXTRACTOR TEMPERATURE SENSOR

IDENTIFICATION

FIN: 11HH, 31HH





LOCATION

ZONE: 191, 192


It provides Indication for ECAM display and also

detects pack overheat if the Air Cycle Machine fails

or when the pack is off and a trim air check valve

fails.

LOCATION

ZONE: 191, 192


It consists of two thermistors and is used for pack

temperature control.

One thermistor is connected to the primary computer,

the other thermistor to the secondary one.

T M U T E M R

0 9 - T

0 4

L E V E L

3

EFFECTIVITY

21-50-00Page 8

Nov 30/99

U F F

4 2 0 0

Page 106EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK SENSOR COMPONENTS - PACK OUTLET TEMPERATURE SENSOR -WATER EXTRACTOR TEMPERATURE SENSOR

T M U T E M R

0 9 - P

0 4

L E V E L

3

EFFECTIVITY

21-50-00Page 9

Nov 30/99

U F F

4 2 0 0

Page 107EFFECTIVITY

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PACK OUTLET PNEUMATIC SENSOR

IDENTIFICATION

FIN: 10HM10, 11HM10





LOCATION

ZONE: 191, 192


It is pneumatically connected to the anti-ice valve

for pack temperature control in case of pack controller

failure (It adjusts the AIV muscle pressure).

T M U T E M R

0 9 - T

0 5

L E V E L

3

EFFECTIVITY

21-50-00Page 10

Nov 30/99

U F F

4 2 0 0

Page 108EFFECTIVITY

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ZONE TEMPERATURE CONTROL - PACK SENSOR COMPONENTS - PACK OUTLET PNEUMATIC SENSOR T M U T E M R

0 9 - P

0 5

L E V E L

3

EFFECTIVITY

21-50-00Page 11

Nov 30/99

U F F

4 2 0 0

Page 109EFFECTIVITY

ALL






T M U T E M R

0 9

L E V

E L

3

EFFECTIVITY

21-50-00Page 12

Nov 30/99

U F F

4 2 0 0

Page 110EFFECTIVITY

ALL


21-60-00 ZONE TEMPERATURE CONTROL -

ZONE COMPONENTS

CONTENTS:

Zone Controller





Mixer Unit Flap Rotary Actuator

Mixer Temperature Sensors

Trim Air Check Valve

Trim Air Pressure Regulating Valve (PRV)

Hot Air Pressure Switch

Trim Air Valve (TAV)

Duct Temperature Sensors

Zone Temperature Sensors

Recirculation Filters

Recirculation Fan

Recirculation Check Valves

Toilet And Galley Extraction Fan

T M U T E M S

0 A

L E V E L

3

EFFECTIVITY

21-60-00Page 1

Jul 31/00

U F F

4 2 0 0

Page 111EFFECTIVITY

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ZONE TEMPERATURE CONTROL - ZONE COMPONENTS

ZONE CONTROLLER

IDENTIFICATION

FIN: 8HK

LOCATION





LOCATION

ZONE: 121


ZONE CONTROLLER FUNCTIONS PRIMARY SECONDARY

Zone temp control to selected

temp yes no

Zone temp. to 24°C (75°F) no yes

TAV control yes no

PRV opening yes no

PRV closing yes yes

Flow demand optimization yes no

Failure analysis yes yes

BITE yes yes

BITE storage and transmission

to CFDS no yesECAM indications yes yes

DATA handling yes yes

Ovht detection and indication yes yes

ATA 36 bleed valve status no yes

ATA 30 anti-ice failures and

status no yes

Fan monitoring yes no

T M U T E M S

0 A - T

0 1

L E V E L

3

EFFECTIVITY

21-60-00Page 2

Jul 31/00

U F F

4 2 0 0

Page 112EFFECTIVITY

ALL





ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - ZONE CONTROLLER T M U T E M S

0 A - P

0 1

L E V E L

3

EFFECTIVITY

21-60-00Page 3

Jul 31/00

U F F

4 2 0 0

Page 113EFFECTIVITY

ALL


MIXER UNIT FLAP ROTARY ACTUATOR

IDENTIFICATION

FIN: 20HB

LOCATION





LOCATION

ZONE: 137


Operated by a 28 VDC motor

Mixer unit flap normally closed.

It opens when Pack 1 is selected OFF to ensure

sufficient airflow to the cockpit.

T M U T E M S

0 A - T

0 2

L E V E L

3

EFFECTIVITY

21-60-00Page 4

Jul 31/00

U F F

4 2 0 0

Page 114EFFECTIVITY

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T M U T E M S

0 A - P

0 2

L E V E L

3

ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - MIXER UNIT FLAP ROTARY ACTUATOR

EFFECTIVITY

21-60-00Page 5

Jul 31/00

U F F

4 2 0 0

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MIXER TEMPERATURE SENSORS

IDENTIFICATION

FIN: 24HK, 25HK

LOCATION





OC O

ZONE: 137, 137


There are two mixer temperature sensors one installed

on each side of the mixer unit. They send data to the

zone controller.

T M U T E M S

0 A - T

0 3

L E V E L

3

EFFECTIVITY

21-60-00Page 6

Jul 31/00

U F F

4 2 0 0

Page 116EFFECTIVITY

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T M U T E M S

0 A - P

0 3

L E V E L

3

ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - MIXER TEMPERATURE SENSORS

EFFECTIVITY

21-60-00Page 7

Jul 31/00

U F F

4 2 0 0

Page 117EFFECTIVITY

ALL


TRIM AIR CHECK VALVE

IDENTIFICATION

FIN: 18HM, 19HM

LOCATION





ZONE: 191, 192


They are installed upstream of the hot pressure

regulating valve. One is installed in each trim air

duct from the bleed system. They prevent back-flow.

T M U T E M S

0 A - T

0 4

L E V E L

3

EFFECTIVITY

21-60-00Page 8

Jul 31/00

U F F

4 2 0 0

Page 118EFFECTIVITY

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T M U T E M S

0 A - P

0 4

L E V E L

3

ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - TRIM AIR CHECK VALVE

EFFECTIVITY

21-60-00Page 9

Jul 31/00

U F F

4 2 0 0

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TRIM AIR PRESSURE REGULATING VALVE (PRV)

IDENTIFICATION

FIN: 14HK

LOCATION

ZONE 137





ZONE: 137


Electrically controlled and pneumatically actuated.

One microswitch for indication (ECAM and FAULT light).

Two solenoids:

- one for control: energized = valve open,

- one for reduced airflow: energized = press

reduction.

T M U T E M S

0 A - T

0

5

L E V E L

3

EFFECTIVITY

21-60-00Page 10

Jul 31/00

U F F

4 2 0 0

Page 120EFFECTIVITY

ALL





T M U T E M S

0 A - P

0

5

L E V E L

3

ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - TRIM AIR PRESSURE REGULATING VALVE (PRV)

EFFECTIVITY

21-60-00Page 11

Jul 31/00

U F F

4 2 0 0

Page 121EFFECTIVITY

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HOT AIR PRESSURE SWITCH

IDENTIFICATION

FIN: 26HK

LOCATION

ZONE: 137





ZONE: 137


It signals pressure regulating valve outlet

overpressure of 6.5 psi (0.45 bar) for ECAM display.

T M U T E M S

0 A - T

0

6

L E V E L

3

EFFECTIVITY

21-60-00Page 12

Jul 31/00

U F F

4 2 0 0

Page 122EFFECTIVITY

ALL





T M U T E M S

0 A - P

0

6

L E V E L

3

ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - HOT AIR PRESSURE SWITCH

EFFECTIVITY

21-60-00Page 13

Jul 31/00

U F F

4 2 0 0

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ALL


TRIM AIR VALVE (TAV)

IDENTIFICATION

FIN: 11HK, 12HK, 13HK

LOCATION

ZONE: 137






The Trim Air Valve is an electrically operated

butterfly valve.

It consists of:- a valve housing assembly,

- a valve flap,

- a stepper motor with a gearbox, an electrical

end stop for the closed position and two

mechanical end stops for the closed and open

position,

- a manual lever to manually operate the TAV and

show its flap position.

The TAV position is determined by the zone controller

through a step counter.

T M U T E M S

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0

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T M U T E M S

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7

L E V E L

3

ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - TRIM AIR VALVE (TAV)

EFFECTIVITY

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DUCT TEMPERATURE SENSORS

IDENTIFICATION

FIN: 15HK, 16HK, 17HK

LOCATION

ZONE: 137






They send temperature data to the zone controller for

temperature control indication and overheat detection.

Each sensor has two thermistors, one dedicated to themain computer of the zone controller, the other

dedicated to the secondary computer.

T M U T E M S

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8

L E V E L

3

EFFECTIVITY

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ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - DUCT TEMPERATURE SENSORS T M U T E M S

0 A - P 0

8

L E V E L

3

EFFECTIVITY

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ZONE TEMPERATURE SENSORS

IDENTIFICATIONFIN: 21HK, 22HK, 23HK

LOCATION

ZONE: 210, 232, 252






There are three zone-temperature-sensors one installed

in the cockpit, FWD cabin and aft cabin zones, each

is used for control and indication.

T M U T E M S

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0 9

L E V E L

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EFFECTIVITY

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ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - ZONE TEMPERATURE SENSORS T M U T E M S

0 A - P

0 9

L E V E L

3

EFFECTIVITY

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RECIRCULATION FILTERS

IDENTIFICATIONFIN: 4012HM, 4013HM

LOCATION

ZONE: 137, 138






One recirculation filter is installed upstream of each

recirculation fan. Each filter consists of multi-layer

glassfiber filter cartridge, installed inside aperforated carbon-filter reinforced plastic cylinder.

T M U T E M S

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1 0

L E V E L

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EFFECTIVITY

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ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - RECIRCULATION FILTERS T M U T E M S

0 A - P

1 0

L E V E L

3

EFFECTIVITY

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RECIRCULATION FAN

IDENTIFICATIONFIN: 15HG, 14HG

LOCATION

ZONE: 137, 138






They are installed in line with the recirculation

ducts. AC powered with 3 phases. A thermal switch

isolates the electrical supply in case of stator tempof 140°C (284°F). A relay signals malfunction to the

ECAM and CFDS via the zone controller.

T M U T E M S

0 A - T

1 1

L E V E L

3

EFFECTIVITY

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ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - RECIRCULATION FAN T M U T E M S

0 A - P

1 1

L E V E L

3

EFFECTIVITY

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RECIRCULATION CHECK VALVES

IDENTIFICATIONFIN: 4020HM, 4021HM

LOCATION

ZONE: 137, 138






They are installed downstream of each cabin

recirculation fan. They prevent back flow to the FWD

cargo compartment if case of fan failure.

T M U T E M S

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1 2

L E V E L

3

EFFECTIVITY

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ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - RECIRCULATION CHECK VALVES T M U T E M S

0 A - P

1 2

L E V E L

3

EFFECTIVITY

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TOILET AND GALLEY EXTRACTION FAN

IDENTIFICATIONFIN: 1HU

LOCATION

ZONE: 172







The fan (AC powered with 3 phases) extracts toilet and

galley air to the outflow valve area. A thermal switch

isolates the electrical supply in case of statortemperature of 134°C (273°F) A relay signals malfunction

to the ECAM and CFDS via the zone controller.

T M U T E M S

0 A - T

1 3

L E V E L

3

EFFECTIVITY

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ZONE TEMPERATURE CONTROL - ZONE COMPONENTS - TOILET AND GALLEY EXTRACTION FAN T M U T E M S

0 A - P

1 3

L E V E L

3

EFFECTIVITY

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T M U T E M S

0 A

L

E V E L

3

EFFECTIVITY

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21-55-00 ZONE TEMPERATURE CONTROL -EMERGENCY RAM AIR INLET

COMPONENTS

CONTENTS:

Emergency Ram Air Inlet Actuator

Emergency Check Valve





T M U T E M Q

0 1

L

E V E L

1

EFFECTIVITY

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ZONE TEMPERATURE CONTROL - EMERGENCY RAM AIR INLET COMPONENTS

EMERGENCY RAM AIR INLET ACTUATOR

IDENTIFICATIONFIN: 7HZ

LOCATION

ZONE: 191






It consists of a 28 VDC motor with 2 travel limit

switches and 2 limit switches for ECAM indication.

EMERGENCY RAM AIR INLET CHECK VALVE

IDENTIFICATION

FIN: 4022HL

LOCATION

ZONE: 137


The check valve is installed in line with the air

delivery duct, between the ram air inlet and the mixer

unit. It prevents mixer unit back flow.

T M U T E M Q

0 1 - T

0 1

L E V E L

1

EFFECTIVITY

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T M U T E M Q

0 1 - P

0 1

L E V E L

1

ZONE TEMPERATURE CONTROL - EMERGENCY RAM AIR INLET COMPONENTS

EFFECTIVITY

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T M U T E M Q

0 1

L

E V E L

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21-31-00 PRESSURIZATION -SYSTEM DESIGN PHILOSOPHY

CONTENTS:

General

Design Philosophy

Self Examination





T M U P R E

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E V E L

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PRESSURIZATION - SYSTEM DESIGN PHILOSOPHY

GENERAL

The pressurization system ensures a cabin altitudesafe and compatible with crew and passenger comfort.

Pressurization is performed by controlling the amount

of air discharged overboard through one outflow valve.

DESIGN PHILOSOPHY

The system has two identical and independent automatic





The system has two identical and independent automatic

controllers.

Only one controller operates at a time, the other is

in active stand-by.

In normal condition, the system operation is fully

automatic.

The automatic cabin pressure control operation is

dependent on programmed control laws and

information from FMGCs and ADIRUs.

Manual mode permits full pressurization control in

case of failure of both automatic systems.

The cabin altitude can be manually controlled by

operating the outflow valve in manual mode.

Two safety valves are installed on the aft pressure

bulkhead to prevent excessive positive and negative

differential pressure.

The two safety valves are installed above the aircraft

floatation line.

T M U P R E

7 0 2 - T

0 1

L E V E L

1

EFFECTIVITY

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PRESSURIZATION - SYSTEM DESIGN PHILOSOPHY T M U P R E

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0 1

L E V E L

1

EFFECTIVITY

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SELF EXAMINATION

What is the number of outflow valves and safety

valves ?

A - One outflow valve and one safety valve.B - One outflow valve and two safety valves.

C - Two outflow valves and two safety valves.

What happens when manual mode is used ?

A - The system continues to operate

automatically.

B - The outflow valve can be manually





B The outflow valve can be manually

controlled to adjust the cabin altitude.

C - The safety valves open.

What is the purpose of the safety valves ?

A - To avoid negative differential pressure.

B - To replace the outflow valves.

C - To prevent excessive positive and

negative differential pressure.

T M U P R E

7 0 2

L E V E L

1

EFFECTIVITY

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21-31-00 PRESSURIZATION -SYSTEM PRESENTATION

CONTENTS:

Cabin Pressure Controllers

Outflow Valve

Safety Valves

Cabin Pressure Altitude Enveloppe

Self Examination





T M U P R E

8 0 A

L E V E L

1

EFFECTIVITY

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PRESSURIZATION - SYSTEM PRESENTATION - CABIN PRESSURE CONTROLLERS - OUTFLOW VALVE -SAFETY VALVES T

M U P R E

8 0 A - P

0 1

L E V E L

1

EFFECTIVITY

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PRESSURIZATION - SYSTEM PRESENTATION

CABIN PRESSURE ALTITUDE ENVELOPPE

The cabin altitude is limited to 8000 feet with adifferential pressure of 8.06 psi for an aircraft

altitude of 39000 feet.

If cabin altitude increases:

- at 9550 ft, the master warning comes on,

- at 11300 ft, passenger signs are activated.

In the outflow valve, a safety device closes the valve





when the cabin altitude reaches 15000 ft.

T M U P R E

8 0 A -

T 0 2

L E V E L

1

EFFECTIVITY

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T M U P R E

8 0 A -

P 0 2

L E V E L

1

PRESSURIZATION - SYSTEM PRESENTATION - CABIN PRESSURE ALTITUDE ENVELOPPE

EFFECTIVITY

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SELF EXAMINATION

Which motor(s) is(are) controlled from the cabin

pressure panel ?

A - Motor 3.B - Motor 2 and motor 1.

C - Motor 1.

What is the maximum normal cabin altitude for

maximum cruise level (39000 ft) ?

A - A cabin altitude of 8000 ft.

B - A cabin altitude of 9550 ft.

C - A cabin altitude of 11300 ft





C - A cabin altitude of 11300 ft.

T M U P R E

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L E V E L

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EFFECTIVITY

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21-31-00 PRESSURIZATION -SYSTEM CONTROLS AND INDICATING

CONTENTS:

Landing Elevation Selector

Control MODE SEL Pushbutton And MAN V/S Toggle SW

Ditching Pushbutton

Self Examination





T M U P R E

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L E V E L

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PRESSURIZATION - SYSTEM CONTROLS AND INDICATING

LANDING ELEVATION SELECTOR

When the LDG ELEV selector is in AUTO position, the

system is in normal operation conditions. The landing

elevation comes from the Flight Management & Guidance

System (automatic operation).

In other positions the selected landing elevation is

used (semi-automatic operation).

When not set to AUTO and as the scale on the LDG ELEV

rotary selector is inaccurate, use the ECAM CAB PRESS

page to correctly set the landing elevation (if QNH

Note 1: In MANual mode, CPC1 has a backup system with

a pressure sensor which ensures excessive

cabin altitude warning generation and pressure

outputs for the indication on the EIS.

Note 2: The MANual mode can only be selected a maximum

of two times in a single flight. On the third

selection, the auto system previously in

control will remain in the latched state.

DITCHING PUSHBUTTON





p g y g

used) or zero (if QFE used).

CONTROL MODE SEL PUSHBUTTON AND MAN V/S TOGGLE SW

When the MODE SEL pushbutton is in the AUTO position,

the outflow valve is automatically controlled by the

active system. The CPCs use the data from the Flight

Management and Guidance System (FMGS) and the Air

Inertial/Reference System (ADIRS).

When in MAN position, the outflow valve is controlled

by the MANual Vertical Speed control switch.When the MANual mode is selected, it overrides the

automatic pressure control system. Normally, this mode

is only used in the event of the failure of both

automatic systems.

The MANUAL Vertical Speed control switch is spring

loaded to neutral. It is used to manually control the

outflow valve only when MANual mode has been selected

using the MODE SELector pushbutton.

-UP: the valve moves towards the open position.-DN: the valve moves towards the closed position.

When the DITCHING pushbutton is selected ON, the

operating controller sends a closure signal to the

outflow valve.

DITCHING

When ON: The outflow valve closes, and in addition,

the emergency ram air inlet, avionics ventilation

extract valve and pack flow control valves close.

Note:If MANual mode has been selected, the outflow valve

does not close automatically.

T M U P R E

4 0 A -

T 0 1

L E V E L

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PRESSURIZATION - SYSTEM CONTROLS AND INDICATING T M U P R E

4 0 A -

P 0 1

L E V E L

1

EFFECTIVITY

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SELF EXAMINATION

Where do you check the correct Manual landing

elevation setting ?

A - On the scale of LDG ELEV switch

selector.

B - On the ECAM CAB PRESS page.

C - No need because it is automatic.

What happens if the MODE SELECTOR is set to MAN and

the DITCHING pushbuttom is set ON ?

A - The outflow valve, emergency RAM AIR

inlet, avionics ventilation and pack





flow control valves close.

B - Only the outflow valve closes.

C - Only the outflow valve is not

automatically controlled to close.

T M U P R E

4 0 A

L E V E L

1

EFFECTIVITY

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21-31-00 PRESSURIZATION -ECAM PAGE PRESENTATION

CONTENTS:

Outflow Valve

Safety Valves

System: SYS 1 Or SYS 2

Cabin Differential Pressure

Cabin Vertical Speed (V/S)

Manual Mode (MAN)

Cabin Altitude (CAB ALT)





Landing Elevation

T M U P R E

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PRESSURIZATION - ECAM PAGE PRESENTATION

OUTFLOW VALVE

The outflow valve position is normally displayed in

green. If fully open in flight it changes to amber.

SAFETY VALVES

The safety valve position is displayed in green when

the two safety valves are closed. It becomes amber if

either safety valve is not closed.

SYSTEM SYS 1 OR SYS 2

CABIN VERTICAL SPEED (V/S)

The cabin vertical speed is normally displayed in

green. It changes to amber when out of normal range.

It is also displayed on the cruise page.

- Indicated values in green when in normal range,

- and amber when V/S greater than 2000ft/mn up

or down.

- Pulsing advisory when V/S greater than

1200 ft/mn.





SYSTEM: SYS 1 OR SYS 2

SYS 1 or SYS 2 indication is displayed in :

- green when active

- amber when faulty

- It is not displayed when inactive.

CABIN DIFFERENTIAL PRESSURE

The cabin differential pressure is displayed in green

when in normal range. It changes to amber when out of

limits.

- Indicated values in green when in normal range,

- and amber when less than 0.4 PSI or greater

than 8.5 PSI.

- Pulsing advisory when ∆P greater than 1.5PSI

during final approach (below 800 feet).

T M U P R E

5 0 3 - T

0 1

L E V E L

1

EFFECTIVITY

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T M U P R E

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L E V E L

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EFFECTIVITY

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MANUAL MODE: MAN

MAN indication appears in white when the manual mode

is selected.

NOTE: on the cruise page, the CABin Vertical Speed

indication changes as shown.

CABIN ALTITUDE

The cabin altitude is displayed in green when in

normal range. It changes to red if excessive. It is

also displayed on the cruise page





also displayed on the cruise page.

-Indicated values in green when in normal range,

and red when cabin altitude reaches 9550 ft.

- Pulsing advisory when cabin altitude greater

than 8800 ft.

LANDING ELEVATION (LDG ELEV)

Landing elevation indication is displayed green and

indicated in feet. In AUTO it corresponds to the value

selected by the FMGS. In MANual it corresponds to the

value selected by rotary selector.

- AUTO : When LDG ELEV selector is on AUTO.

- MAN : when LDG ELEV selector is not on AUTO.

- No indication if the MODE SEL pushbutton is

on MAN.

T M U P R E

5 0 3 - T

0 2

L E V E L

1

EFFECTIVITY

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PRESSURIZATION - ECAM PAGE PRESENTATION T M U P R E

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0 2

L E V E L

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EFFECTIVITY

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T M U P R E

5 0 3

L E V E L

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EFFECTIVITY

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21-31-00 PRESSURIZATION -SYSTEM WARNINGS

CONTENTS:

Excessive Cabin Altitude

System 1 (or 2) Fault

System 1 and 2 Fault

Outflow Valve Not open

Landing Elevation Fault

Safety Valve Open

Low Differential Pressure





T M U P R E

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L E V E L

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EFFECTIVITY

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PRESSURIZATION - SYSTEM WARNINGS

EXCESSIVE CABIN ALTITUDE

When cabin altitude is greater than 9550 ft, the MASTER

WARN flashes, the aural warning sounds and the

indication becomes red.

Depending on the CABIN Vertical Speed, a descent or

an Emergency descent must be initiated.





T M U P R E

6 0 4

- T

0 1

L E V E L

3

EFFECTIVITY

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PRESSURIZATION - SYSTEM WARNINGS - EXCESSIVE CABIN ALTITUDE

T M U P R E

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0 1

L E V E L

3

EFFECTIVITY

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SYSTEM 1 (or 2) FAULT

In case of system 1 or system 2 fault, only the

indication of the faulty system changes to amber.

The pressurization control is automatically

transferred to the healthy system.





T M U P R E

6 0 4

- T

0 2

L E V E L

3

EFFECTIVITY

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PRESSURIZATION - SYSTEM WARNINGS - SYSTEM 1 (OR 2) FAULT T M U P R E

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L E V E L

3

EFFECTIVITY

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SYSTEM 1 + 2 FAULT

In case of system 1 and system 2 fault, the MASTER

CAUT comes on, the aural warning sounds, the FAULT

light comes on and the indication becomes amber.

Both controllers are faulty.

MAN mode must be used, in order to control the cabin

pressure by means of the MAN V/S CTL toggle switch.





T M U P R E

6 0 4

- T

0 3

L E V E L

3

EFFECTIVITY

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PRESSURIZATION - SYSTEM WARNINGS - SYSTEM 1 + 2 FAULT T M U P R E

6 0 4

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L E V E L

3

EFFECTIVITY

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OUTFLOW VALVE NOT OPEN

When the outflow valve is not fully open, the MASTER

CAUT comes on and the aural warning sounds.When the outflow valve is not fully open in ground

mode, MAN mode and MAN V/S CTL toggle switch must be

used in order to fully open the outflow valve.





T M U P R E

6 0 4

- T

0 4

L E V E L

3

EFFECTIVITY

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PRESSURIZATION - SYSTEM WARNINGS - OUTFLOW VALVE NOT OPEN T M U P R E

6 0 4

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0 4

L E V E L

3

EFFECTIVITY

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LANDING ELEVATION FAULT

In case of landing elevation fault (LDG ELEV FAULT),

the MASTER CAUT comes on and the aural warning sounds.There is no landing elevation data available from the

Flight Management and Guidance System (FMGS).

The landing field elevation must be manually selected

by using the LDG ELEV rotary selector.





T M U P R E

6 0 4

- T

0 5

L E V E L

3

EFFECTIVITY

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PRESSURIZATION - SYSTEM WARNINGS - LANDING ELEVATION FAULT T M U P R E

6 0 4

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0 5

L E V E L

3

EFFECTIVITY

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SAFETY VALVE OPEN

In case of safety valve open warning, the MASTER CAUT

comes on, the aural warning sounds and the indicationbecomes amber.

High Differential pressure causes the opening of the

safety valves. Select the MODE SEL to MAN and adjust

MAN V/S to reduce cabin delta P.





T M U P R E

6 0 4 - T

0 6

L E V E L

3

EFFECTIVITY

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PRESSURIZATION - SYSTEM WARNINGS - SAFETY VALVE OPEN T M U P R E

6 0 4 - P

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L E V E L

3

EFFECTIVITY

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LOW DIFFERENTIAL PRESSURE

In case of low differential pressure warning (LO DIFF

PR), the MASTER CAUT comes on and the aural warningsounds.

Low differential pressure warning occurs when the

aircraft rate of descent is too high with respect to

cabin differential pressure.

Time to reach delta P = 0 ≤ 1.5 mm and time to reach

delta P = 0 (time for CAB alt. to reach landing

elevation) + 30 s and aircraft is at least 3000 ft

above landing field.

NOTE: The warning is maintained when aircraft descends





NOTE: The warning is maintained when aircraft descends

below 3000 ft above landing field.

T M U P R E

6 0 4 - T

0 7

L E V E L

3

EFFECTIVITY

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PRESSURIZATION - SYSTEM WARNINGS - LOW DIFFERENTIAL PRESSURE T M U P R E

6 0 4 - P

0 7

L E V E L

3

EFFECTIVITY

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T M U P R E

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EFFECTIVITY

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21-31-00 PRESSURIZATION -SYSTEM CONTROL INTERFACES

CONTENTS:Engine Interface Unit (EIU)

Landing Gear Control Interface Unit (LGCIU)

Air Data Inertial Reference Unit (ADIRU)

Flight Management And Guidance Computer (FMGC)

Motors

Controller 1/Controller 2

Air Conditioning Panel And Cabin Pressurization Panel

Pressurization Panel/Motor 3

Self Examination





T M U P R E B

0

2

L E V E L

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PRESSURIZATION - SYSTEM CONTROL INTERFACES


Each Engine Interface Unit sends a thrust lever angle

associated with an N2 signal to both controllers toinitiate the prepressurization and the pressurization

sequences.

Signals: thrust lever angle in take-off position (MAX

CONT or FLX detent) and N2 at or above idle, used for

prepressurization and pressurization sequences.

LANDING GEAR CONTROL INTERFACE UNIT (LGCIU)

Each Landing Gear Control Interface Unit sends aflight/ground signal to both controllers to initiate

i i h i i d h

FLIGHT MANAGEMENT AND GUIDANCE COMPUTER (FMGC)

Each Flight Management and Guidance Computer sends

cruise flight level and landing field elevation datato both controllers.

Signals: cruise flight level, landing field elevation,

used for pressurization profile.

MOTORS

A discrete signal from the active controller will

select the corresponding motor ( enable signal ) while

outflow valve positioning and monitoring signals aretransmitted by RS 422 buses.

Si l i AUTO MODE " bl i l" i





prepressurization, the pressurization and the

depressurization sequences.

Signal: ground/flight, used for prepressurization,

pressurization, depressurization sequences and system

transfer.

AIR DATA INERTIAL REFERENCE UNIT (ADIRU)

Each Air Data Inertial Reference Unit sends the static

pressure and the barometric correction signals to both

controllers for pressure control.

Signals: static pressure, baro correction and ADIRU

validity, used for all sequences and priority

selection.

ADIRU 1, 2, 3 : controller 1

ADIRU 2, 1, 3 : controller 2

Signals in AUTO MODE: "enable signal" to motor in

control, outflow valve positioning and monitoring.

Signals in MANUAL MODE: feedback position from motor

3 is sent to the controller 1.

CONTROLLER 1 / CONTROLLER 2

Discrete signals between both controllers ensure

controller transfer.

Signal: system 1 or 2 active, used for controller

transfer.

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PRESSURIZATION - SYSTEM CONTROL INTERFACES

AIR CONDITIONING PANEL AND CABIN PRESSURIZATION PANEL

The position of the pressure panel switches and

emergency ram air switch is transmitted to bothcontrollers.

CABIN PRESS PANEL

Signals: ditching, landing field elevation, manual

mode selection, used for ditching and manual operation.

AIR COND PANE

Signal: emergency ram air inlet selection, used for

outflow valve half opening.

PRESSURIZATION PANEL / MOTOR 3





PRESSURIZATION PANEL / MOTOR 3

Motor 3 is controlled by a discrete signal directly

sent by the CABIN PRESS panel.

Signal: motor 3 control, used for manual mode.

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SELF EXAMINATION

Which interfaces are used for prepressurization and

pressurization sequence initialization?

A - EIU and ADIRU.

B - EIU and LGCIU.C - EIU and FMGC.

Motor 3 is controlled from:

A - Controller 1.

B - The AIR COND panel.

C - The CABIN PRESS panel.





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21-31-00 PRESSURIZATION -SYSTEM MONITORING INTERFACES

CONTENTS:Flight Warning Computer (FWC)

System Data Acquisition Concentrator (SDAC)


Cabin Intercommunication Data System (CIDS)

Cabin Pressurization Panel

Cabin Pressurization Panel/SDACs

Safety Valves/SDACs

Self Examination





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FLIGHT WARNING COMPUTER (FWC)

In case of excessive cabin altitude in manual mode,

controller 1 sends a discrete signal to both FWCs forlevel 3 warnings.

Signal: excessive cabin altitude (9550 ft), used in

manual mode (discrete signal from controller 1 manual

part only).

NOTE: Each manual part is a separated electrically

supplied part.

SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC)

Both controllers send ARINC and discrete signal to the

CABIN INTERCOMMUNICATION DATA SYSTEM (CIDS)

In case of excessive cabin altitude, the pressure

controllers send a discrete signal to the CIDS.Signal: excess cabin altitude (11300 ft), used for

passenger signs.

CABIN PRESSURIZATION PANEL

In case of failure of both automatic systems, the

controllers send a discrete signal to the pressure

panel for FAULT light illumination.

Signal: failure of both automatic systems, used forFAULT light illumination.





System Data Acquisition Concentrator. Controller 1

(manual back-up part) also sends 3 analog signals used

when the system is operating in manual mode.

Signals: warnings and indications, used in auto mode

(ARINC and discrete signals from both controllers),

manual mode (3 analog signals from controller 1 only).


Both controllers send BITE data to the CFDIU via ARINC

buses. This data is sent continuously or on request.

Signal: BITE data, used for CFDS monitoring.

CABIN PRESSURIZATION PANEL / SDACs

A manual mode selection signal is sent from the

pressure panel to both SDACs.

Signal: MAN mode selection, used for ECAM display.

SAFETY VALVES / SDACs

The safety valve position signals are sent to both

SDACs.

Signal: safety valve position, used for ECAM display.

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SELF EXAMINATION

In manual mode, warnings and indications come from:

A - Controller 1.

B - Controller 2.

C - The outflow valve.CABIN PRESS FAULT light comes on when:

A - Automatic system 1 fails.

B - Both automatic systems fail.

C - Manual system fails.





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21 - PRESSURIZATION

21-31-00 PRESSURIZATION -COMPONENTS

CONTENTS:Cabin Pressure Controllers (CPC1 and CPC2)

Outflow Valve LRUs

- Valve Assembly

- Electronic Actuators

- Gearbox Assembly

Safety Valves





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PRESSURIZATION - COMPONENTS

CONTROLLER

IDENTIFICATION

FIN: 11HL, 12HL

LOCATION

ZONE: 121, 122


CPC1 and CPC2 are interchangeable and provided with

system identification pins.

Each one is equipped with a pressure transducer module

of the DMS pressure sensor type.





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OUTFLOW VALVE LRUs

IDENTIFICATION

FIN: 10HL

LOCATION

ZONE: 172


The skin mounted outflow valve is of the dual-gate and

motor driven type design.

It consists of:

- a valve assembly (a frame and two gates),

- two electronic actuators (a single electronic

board connected to its associated CPC via RS422

bus),

ELECTRONIC ACTUATORS

The electronic actuator modules receive a position

reference signal (desired outflow valve position) from

the controller. This signal is compared with theoutflow valve actual position. The electronic module

then drives the outflow valve until its position

matches the desired one.

A pressure switch is installed in each box. It operates

independently from the automatic operation. It closes

the outflow valve if the pressure in the fuselage is

less than the atmospheric pressure at an altitude of

15000 ft.

GEARBOX AND FEEDBACK ASSEMBLY

The gearbox transmits the movement from the activated

motor to the outflow valve flap. A mechanical stop





bus),

- a gearbox assembly (two automatic motors, a

manual motor, a gearbox and feedback

assembly).

VALVE ASSEMBLY

The outflow valve body has two gates, one forward andone aft. The gates are installed in a rectangular

frame. The forward gate opens outwards and is

mechanically connected to the aft gate. The aft gate

opens inwards and is mechanically connected to the

gear box and the forward gate.

p p

limits the rotation of the drive shaft for the valve

flap movement. The feedback module is a triple

potentiometer integrated with the gearbox. It sends

data to the cabin pressure controllers.

There are two brushless DC motors for automatic

control. Each motor has an integral electromechanical

brake. The manual motor is a brush-type DC motor. It

drives the outflow valve through an irreversible

worm-gear.

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PRESSURIZATION - COMPONENTS - OUTFLOW VALVE T M U P R E E

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SAFETY VALVES

IDENTIFICATION

FIN: 6HL, 7HL

LOCATION

ZONE: 262


The safety valve is of the diaphragm pneumatic valve

type and consists of:

- a body, a filter, a moving valve element

(diaphragm).

- a pneumatic pressure controller sensing cabin

and outside pressures

- a position switch for ECAM indication.





p

Opening: when ∆P = 8.6 or - 0.5 psi.

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PRESSURIZATION - COMPONENTS - OUTFLOW VALVE SUB-COMPONENTS T M U P R E E

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21-31-00 PRESSURIZATION -FUNCTIONAL TEST OF MAN MOTOR

CONTENTS:

Aircraft configuration

Procedure





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PRESSURIZATION - FUNCTIONAL TEST OF MAN MOTOR

AIRCRAFT CONFIGURATION

On the ground.

No air supply.

Electrical power available.

LDG ELEV selector and DITCHING pushbutton selection

is not necessary to perform this test.

PROCEDURE

Set the MODE SEL pushbutton to MAN.

As long as the MAN V/S CTL switch is held in the DN

position, the MANUAL MOTOR controls the outflow valve

to close.

As long as the MAN V/S CTL switch is held in the UP

position, the outflow valve is controlled to open by





position, the outflow valve is controlled to open by

means of the MANUAL MOTOR.

Set the MODE SEL pushbutton back to AUTO.

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21-20-00 GENERAL VENTILATION -SYSTEM DESIGN PHILOSOPHY

CONTENTS:

Avionics

Lav & Galleys

Cargo (Option)

Controllers





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GENERAL VENTILATION - SYSTEM DESIGN PHILOSOPHY

AVIONICS

The avionics ventilation system ensures a proper

ventilation of the electrical equipment. Air is taken

from different sources depending on the aircraft

configuration and ambient conditions.

Ventilation air is blown to the equipments by a blower

fan and extracted by an extraction fan.

LAV & GALLEYS

The lavatory and galleys ventilation system is used

to remove unpleasant odors before they enter the cabin.

Ventilation air is supplied from cabin distribution

ducts and discharged overboard by an extraction fan.

CARGO (Option)





The FWD & AFT cargo compartments are ventilated by

cabin ambient air coming from the cabin zones through

openings in the cabin floor behind the sidewall panels.

The FWD & AFT cargo compartments are ventilated by

means of an extraction fan or by differential pressure.Note that the ventilation system is optional and

independent for each compartment.

CONTROLLERS

The avionics equipment ventilation computer (A.E.V.C)

ensures control and monitoring of the avionics

ventilation system.

The cargo ventilation controller controls andmonitors the isolation valves and the extraction

fan of the cargo ventilation system. T M U V E N

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SELF EXAMINATION

Where does the LAV and GALLEYS ventilation air

come from ?

A - From cabin distribution ducts.

B - From pack 1.

C - From pack 2.

What is the purpose of the Avionics Equipment

Ventilation Computer ?

A - To ensure control and monitoring of the

avionics ventilation system.

B - To control and monitor the cargo

ventilation components.

C - To control and monitor the packs.

What is the purpose of the avionics ventilation

system in the avionics bay ?

A - To ventilate the avionics equipment.

B To ensure the heating of the avionics





B - To ensure the heating of the avionics

bay.

C - To avoid avionics bay structural damage.

How is the FWD cargo compartment ventilated ?

A - With avionics bay ambient air.B - With air coming directly from the pack

outlet.

C - With cabin ambient air.

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21-26-00 AVIONICS VENTILATION -SYSTEM CONTROLS AND INDICATING

CONTENTS:

Blower Pushbutton

Extract Pushbutton

Skin Air Inlet Valve

Vent Indication

Skin Air Outlet Valve (extract Valve)





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21-26-00 AVIONICS VENTILATION -SYSTEM WARNINGS

CONTENTS:

Blower Fault

Extract Fault

Skin Valve Fault

Avionics System Fault

Avionics Smoke





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AVIONICS VENTILATION - SYSTEM WARNINGS

BLOWER FAULT

Aural warning sounds, MASTER CAUT and BLOWER FAULT

lights come on. VENT and INLET words become amber on

the ECAM in case of low blowing pressure or duct

overheat.





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EXTRACT FAULT

Aural warning sounds, MASTER CAUT and EXTRACT FAULT

lights come on. VENT and EXTRACT words become amber

on the ECAM in case of low extract pressure.





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SKIN VALVE FAULT

Aural warning sounds, MASTER CAUT comes on. The skin

air inlet or outlet valve position is displayed amber

in case of a SKIN VALVE FAULT.SKIN VALVE FAULT warning is triggered if:

- Skin air outlet valve fully open in phase 3 or

- Skin air outlet valve fully open in flight or

- Skin air inlet valve not fully closed in flight.





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AVIONICS SYSTEM FAULT

Aural warning sounds, MASTER CAUT comes on. VENT word

is amber in case of avionics system fault.

AVNCS SYS FAULT warning is triggered in case of AEVCfailure.





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AVIONICS SMOKE

Aural warning sounds, MASTER CAUT, GEN 1 SMOKE (on the

EMER ELEC PWR panel), BLOWER and EXTRACT FAULT lights

come on in case of avionics smoke detection.VENT, INLET and EXTRACT words are displayed amber on

the ECAM page.

Note that if smoke detection is confirmed, both BLOWER

and EXTRACT pushbuttons must be set to OVRD position.





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21-26-00 AVIONICS VENTILATION -SYSTEM DESCRIPTION/OPERATION

CONTENTS:

GeneralOpen Circuit Configuration

Closed Circuit Configuration

Partially Open Circuit Configuration

Self Examination





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AVIONICS VENTILATION - SYSTEM DESCRIPTION/OPERATION

GENERAL

The system is automatically controlled by the Avionics

Equipment Ventilation Computer and no crew action is

required.The Avionics Equipment Ventilation Computer (AEVC)

will change the system configuration depending on

whether the aircraft is on ground or in flight and on

aircraft skin temperature.

Note that the BLOWER and EXTRACT pushbuttons must be

in AUTO position.





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OPEN CIRCUIT CONFIGURATION

In OPEN CIRCUIT CONFIGURATION, ambient air, drawn

through the skin air inlet valve by the blower fan,

is blown into the system. The air, after coolingavionics equipment, is drawn by the extract fan

directly overboard.

The OPEN CIRCUIT CONFIGURATION allows avionics

equipment to be cooled with ambient air under certain

conditions (on ground and skin temperature above 11°C

(51.8°F) increasing, or above 4°C (39.2°F)

decreasing).

Note: the skin air inlet and outlet valves are fullyopen.





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CLOSED CIRCUIT CONFIGURATION

In CLOSED CIRCUIT CONFIGURATION, the extracted

avionics equipment air goes, through the skin exchanger

isolation valve, into the skin heat exchanger to becooled. then this air is blown into the avionics

equipment again.

When the AEVC detects airflow higher than the requested

value, part of the hot air is bled under the cargo

compartment floor by means of opening of the skin

exchanger inlet ByPass Valve.

the skin exchanger outlet ByPass Valve opens in order

to decrease the noise level in the avionics bay.





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PARTIALLY OPEN CIRCUIT CONFIGURATION

In PARTIALLY OPEN CIRCUIT CONFIGURATION, the system

is almost like in closed configuration, part of the

extracted air is expelled overboard.Note that the skin air outlet valve is an electrically

operated single flap with a smaller flap built into

it.

This smaller flap is opened in flight (or on ground

with take-off power selected) when the skin temperature

is above 34°C (93.2°F). It returns to the closed

position when the skin temperature decreases below

27°C (80.6°F).





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EFFECTIVITY

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SELF EXAMINATION

When does the skin exchanger inlet bypass valve

open?

A - In open circuit configuration.

B - In partially open circuit configuration,

or in closed circuit configuration withairflow higher than the requested value.

C - When the ambient avionics bay

temperature is above 34°C (93.2°F).

When does the skin heat exchanger operate on the

ground?

A - When the circuit operates in open

circuit configuration.

B - In closed circuit configuration when theskin temperature is below 11°C (51.8°F)

(skin temperature increasing).

C - In closed circuit configuration when the

skin temperature is above 11°C (51.8°F)

(skin temperature increasing).





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21-26-00 AVIONICS VENTILATION -SYSTEM INTERFACES

CONTENTS:

Landing Gear Control Interface Unit (LGCIU)Engine Interface Unit (EIU)


Skin Temperature Sensor

Blowing Pressure Switches And Duct Temperature Sensor

Extract Pressure Switch

Skin Air Valves/SDAC

Controller (AEVC)/SDAC

Smoke Detector





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AVIONICS VENTILATION - SYSTEM INTERFACES

LANDING GEAR CONTROL INTERFACE UNIT (LGCIU)

The Landing Gear Control Interface Unit 1 and 2 send

a signal to the avionics controller for ventilation

system control.Signal: Ground/flight, used for system control.


The Engine Interface Unit 1 and 2 send the "take-off

thrust on" signal to the avionics controller for

ventilation system control.

Signal: Thrust lever set to take off and N2 above idle,

used for system control.


The avionics controller sends BITE data to the

Centralized Fault Display Interface Unit via ARINC

bus. Test of the system is performed by sending a test

demand discrete signal to the controller.

BLOWING PRESSURE SWITCHES AND DUCT TEMPERATURE SENSOR

The blowing pressure switches and the duct temperature

sensor signal a low flow and a high duct temperature

to the controller, to both System Data AcquisitionConcentrators and to the BLOWER pushbutton.

On the ground, the ADIRU & AVNCS VENT light illuminates

amber on the external power receptacle 108VU

accompanied by the horn activation.

Signal: Low pressure delta P = 0.025 psi (1,73 hPa)

or high duct temperature temp = 62oC (144

oF), used for

fault and ventilation ground warnings located on

external power receptacle 108VU.

EXTRACT PRESSURE SWITCH

The extract pressure switch signals a low flow to the

controller, to both SDACs and to the EXTRACT

pushbutton.

On the ground, the ADIRU & AVNCS VENT light illuminates

amber on the external power receptacle 108VU





Signals: BITE data via ARINC bus and MCDU test demand

via discrete, used for avionics equipment ventilation

system monitoring.

SKIN TEMPERATURE SENSOR

The skin temperature sensor signals the skin

temperature to the computer for configuration control.

Signal: Skin temperature, used for configuration

control.

accompanied by the horn activation.

Signal: Extract low pressure, used for fault and

ventilation ground warnings located on external power

receptacle 108VU.

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AVIONICS VENTILATION - SYSTEM INTERFACES

SKIN AIR VALVES / SDAC

The skin air valves position signals are sent to both

SDACs for system display and for skin valve fault

warning.Signal: Skin valve position feedback, used for system

display and valve position disagree warning in flight

(SKIN VALVE FAULT).

CONTROLLER (AEVC) / SDAC

The avionics controller monitors the skin air valves

position, the conditioned air inlet valve and the

exchanger inlet bypass valve position.

In case of valve position disagree or loss of power

supply of the controller, the controller sends an

avionics system fault signal to both SDACs.

Signal: Avionics system fault, used for valve position

disagree warning on ground (except the skin exchanger

outlet bypass valve) or loss of power supply of the

Avionics Equipment Ventilation Computer.





SMOKE DETECTOR

The smoke detector signals smoke to the controller,

to both SDACs, to both VENT pushbuttons and to GEN 1

LINE pushbutton.

Signal: Smoke detected, used for smoke warning.

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21-26-00 AVIONICS VENTILATION -COMPONENTS

CONTENTS:

Avionics Equipment Ventilation Computer (AEVC)Skin Air Inlet Valve

Skin Air Outlet Valve

Blower Fan

Extract Fan

Skin Exchanger Inlet Bypass Valve

Skin Exchanger Isolation Valve

Skin Exchanger Outlet Bypass Valve

Conditioned Air Inlet Valve

Filter Assembly

Check Valves

Pressure Switches

Duct Temperature Sensor

Skin Temperature Sensor

Skin Heat Exchanger





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AVIONICS VENTILATION - COMPONENTS

AVIONICS EQUIPMENT VENTILATION COMPUTER (AEVC)

IDENTIFICATION

FIN: 10HQ

LOCATION

ZONE: 128


The avionics computer controls the valves and fans in

the avionics ventilation system. System condition

information is sent to the avionics computer by

pressure switches and temperature sensors in the

system.





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SKIN AIR INLET VALVE

IDENTIFICATION

FIN: 15HQ

LOCATION

ZONE: 127


This valve is an electrically operated single flap

valve which can be manually overridden. Before the

valve is closed manually, it must first be isolated

electrically with a toggle switch located inside the

valve.

TRAINING INFORMATION POINT

After a maintenance action on this valve, check that

the deactivation switch is put back to ON position in

order to recover a normal operation of the system.

_ A319/A320/A321 TECHNICAL TRAINING MANUAL21 AIR CONDITIONING MECHANICS / ELECTRICS & AVIONICS COURSE



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SKIN AIR OUTLET VALVE

IDENTIFICATION

FIN: 22HQ

LOCATION

ZONE: 126


This valve is an electrically operated single flap

valve with a smaller flap built into it. Before the

valve is closed manually, it must first be isolated

electrically with a toggle switch inside the valve.

TRAINING INFORMATION POINT

After a maintenance action on this valve, check that

the deactivation switch is put back to ON position in

order to recover a normal operation of the system.





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BLOWER FAN

IDENTIFICATION

FIN: 20HQ

LOCATION

ZONE: 128


The blower fan is powered with:

- a three phase, four pole single induction motor

for high speed,

- a three phase, six pole single induction motor

for low speed.

A thermo switch and relay are installed on the stator

of the blower fan. If the temperature of the stator

reaches +140 +6 -6 deg C (+284.00 +10.80 -10.80 deg.F),

the thermo switch isolates the electrical supply to

the fan. A fault indication light and reset button are

installed on the fan body.

EXTRACT FAN

IDENTIFICATION

FIN: 18HQ

LOCATION

ZONE: 128


The extraction fan is identical to the blower fan.





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_

A319/A320/A321 TECHNICAL TRAINING MANUAL21 AIR CONDITIONING MECHANICS / ELECTRICS & AVIONICS COURSE



AVIONICS VENTILATION - COMPONENTS - BLOWER FAN - EXTRACT FAN T M U V

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SKIN EXCHANGER INLET BYPASS VALVE

IDENTIFICATION

FIN: 16HQ

LOCATION

ZONE: 126


This valve is of the butterfly type, with an actuator

which moves the butterfly to the open or closed

position. Two microswitches signal the valve position

to the avionics computer 10HQ. A visual position

indicator is located on the top of the actuator unit.

SKIN EXCHANGER ISOLATION VALVE

IDENTIFICATION

FIN: 24HQ

LOCATION

ZONE: 126

SKIN EXCHANGER OUTLET BYPASS VALVE

IDENTIFICATION

FIN: 23HQ

LOCATION

ZONE: 125


The skin exchanger outlet bypass valve is installed

downstream of the skin heat exchanger. This valve is

identical to the skin exchanger inlet bypass valve

16HQ.

_




ZONE: 126


The skin exchanger isolation valve 24HQ is installed

upstream of the skin heat exchanger. This valve is

identical to the skin exchanger inlet bypass valve

16HQ.

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AVIONICS VENTILATION - COMPONENTS - SKIN EXCHANGER INLET BYPASS VALVE - SKIN EXCHANGERISOLATION VALVE - SKIN EXCHANGER OUTLET BYPASS VALVE T

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CONDITIONED AIR INLET VALVE

IDENTIFICATION

FIN: 21HQ

LOCATION

ZONE: 127


The conditioned air inlet valve is installed in a duct

which is connected to the cockpit main supply duct.

This valve is similar to the skin exchanger inlet

bypass valve.





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FILTER ASSEMBLY

IDENTIFICATION

FIN: 2081HM, 2082HM, 2083HM

LOCATION

ZONE: 127


A two-stage filter assembly is installed upstream of

the blower fan 20HQ. The first-stage is a cleanable

plate type filter 2081HM which removes dust particles

above 1000 microns and a multi-layer filter which

removes water particles. The second stage is a

cleanable, corrugated-cartridge-barrier filter 2082HMwhich removes any dust particles above 400 microns.

The filter assembly is also equipped with pressure test

ports for checking the clogging level of the demister

and dust filter assembly (through a portable manometer).





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CHECK VALVES

IDENTIFICATION

FIN: 2140HM, 2150HM

LOCATION

ZONE: 128


A check valve 2140HM is installed downstream of the

blower fan. The check valve is designed to be installed

in line between the ducts. Two semicircle flaps are

installed on a hinge-bar, a spring holds these

semicircle flaps in the closed position.

A check valve 2150HM is installed downstream the skin

air inlet valve. The purpose of the check valve is to

protect the system at the air inlet against possible

adverse effects caused by cabin differential pressure.





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PRESSURE SWITCHES

IDENTIFICATION

FIN: 17HQ, 19HQ, 30HQ

LOCATION

ZONE: 121, 127, 127


Three pressure switches are installed in the avionics

ventilation system, two in the blowing circuit and one

in the extraction circuit. The switches are of the

capsule/microswitch type with an electrical connector

at the top. A low flow indication is given at a

differential pressure of 1.7 mbar plus 1.3 or minus0.5 mbar.





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DUCT TEMPERATURE SENSOR

IDENTIFICATION

FIN: 26HQ

LOCATION

ZONE: 128


It consists of a thermistor mounted in a

stainless-steel tube, an electrical connector is

mounted at the top.

The set temperature values are:

- increasing temperatures 62 deg.C +1 deg.C

(143.6 deg.F +1.8 deg.F).- decreasing temperatures 60 deg.C +1 deg.C (140 deg.F

+1.8 deg.F)





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SKIN TEMPERATURE SENSOR

IDENTIFICATION

FIN: 28HQ

LOCATIONZONE: 126


It consists of a sensor element through which an

electrical current passes to measure the potential

difference proportional to the temperature. The set

temperature values are as follows:

- on ground, increasing values +7 deg.C (+44.60 deg.F),

decreasing values +4deg.C (+39.20 degF).- after takeoff, increasing values +36 deg.C

(+96.80 deg.F), decreasing values +31 deg.C

(+87.80 deg.F).

SKIN HEAT EXCHANGER


A skin heat exchanger is located in the upper fuselage

between frames 12 and 14 and, in normal flight

operations, is used to cool the avionics ventilationair. A thermally insulated internal wall is bolted to

the frames to form two rectangular ducts. This internal

wall is easily removed for structural inspection. A

drainage system is included to deal with any

condensation when the heat exchanger is in operation.





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21-43-00 FWD CARGO COMPARTMENTVENTILATION/HEATING -SYSTEM PRESENTATION

CONTENTS

GeneralPressure Regulating Valve (PRV)

Trim Air Valve

Inlet Isolation Valve

Extraction Fan

Outlet Isolation Valve

Pressure Switch

Ventilation Controller

Heating Controller





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FWD CARGO COMPARTMENT VENTILATION/HEATING - SYSTEM PRESENTATION

GENERAL

The FWD cargo compartment ventilation system operates

in two different modes.

The first mode operates with the aircraft on the ground

and in flight.The second mode operates in flight only.

- First mode: On the ground and in flight with

∆P ≤ 1 psi.

- Second mode: Only in flight with ∆P > 1 psi.

PRESSURE REGULATING VALVE

The hot air is pressure regulated by the cockpit and

cabin hot air pressure regulating valve above the cabinpressure.

The Pressure Regulating Valve regulates pressure of

the hot air (4 psi above the cabin pressure) to the

Trim Air Valve.

TRIM AIR VALVE

The trim air valve regulates the hot air flow. The hot

air is then mixed with the cabin ambient air to obtainthe desired temperature

EXTRACTION FAN

The suction of the air is caused by the extraction fan

when it is running.

The extraction fan runs, when the aircraft is on

the ground or in flight, when both isolation valvesare open with a ∆P ≤1 psi.

Note that, in flight only, when ∆P > 1 psi,the fan

stops.

OUTLET ISOLATION VALVE

The outlet isolation valve permits the FWD cargo

compartment air to be discharged overboard at a skin

mounted venturi.

PRESSURE SWITCH

The pressure switch detects a differential pressure

and sends a signal to the ventilation controller.

In flight only, when a ∆P > 1 psi is detected by the

pressure switch, the ventilation controller stops

the extraction fan.

Note that when the ∆P decreases below 1 psi, thecontroller starts the fan





the desired temperature.

INLET ISOLATION VALVE

The inlet isolation valve permits the air which has

been mixed to enter into the FWD cargo compartment.

controller starts the fan.

VENTILATION CONTROLLER

The cargo ventilation system part is controlled by the

ventilation controller. It controls and monitors the

isolation valves and the extraction fan.

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FWD CARGO COMPARTMENT VENTILATION/HEATING - SYSTEM PRESENTATION

HEATING CONTROLLER

The cargo heating system part is controlled by the

cargo heating controller.

The Heating Controller receives temperature

indications from two temperature sensors and controlsthe Trim Air Valve in order to regulate the amount of

hot air added to cabin ambient air.

It closes the Trim Air Valve when:

- one isolation valve is closed,

- the hot air Press Regul Valve is closed,

- the extraction fan has failed,

- the cargo door is not closed and locked.

It also determines the Trim Air Valve position by means

of a step counter (it counts the steps of the TAV

stepper motor).





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21-43-00 FWD CARGO COMPARTMENTVENTILATION/HEATINGSYSTEM CONTROLS PRESENTATION

CONTENTS:

FWD Isol Valve PushbuttonTemperature Selector

Hot Air Pushbutton

Self Examination





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FWD CARGO COMPARTMENT VENTILATION/HEATING - SYSTEM CONTROLS PRESENTATION

FWD ISOL VALVE PUSHBUTTON

The FWD ISOL VALVE pushbutton controls the isolation

valves and the extraction fan through the ventilation

controller.

When it is pressed in, the cargo ventilation controllerwill start the extraction fan ( if both valves are

fully open and ∆P ≤ 1psi ). When it is set to OFF or

if smoke is detected or DITCHING pushbutton switch is

on, the isolation valves are closed and the extraction

fan stops.

TEMPERATURE SELECTOR

The temperature rotary selector gives the desiredtemperature to the heating controller which controls

the Trim Air Valve to add hot air to cabin ambient

air, if necessary.

The selector temperature range is between 5ºC(41ºF)

and 26ºC(79ºF), with 16ºC (60ºF) at the 12 o’clock

position.

HOT AIR PUSHBUTTON

The hot air pushbutton switch is used to control the

k it d bi h t i P R l ti V l





cockpit and cabin hot air Pressure Regulating Valve.

When it is set to OFF, the valve is closed.

Note : In case of duct temperature above 88ºC(190ºF),

the heating controller controls the HOT AIR Pressure

Regulating Valve to close.

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SELF EXAMINATION

What does the FWD ISOL VALVE pushbutton switch

control?

A - The extract fan

B - The Pressure Regulating Valve.

C - The isolation valves and the extraction

fan.





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21-43-00 FWD CARGO COMPARTMENTVENTILATION/HEATING -ECAM PAGE PRESENTATION

CONTENTS:

GeneralCargo Compartment Temperature

Zone Indication

Duct Inlet Temperature

Trim Air Valve







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FWD CARGO COMPARTMENT VENTILATION/HEATING - ECAM PAGE PRESENTATION

GENERAL

The FWD cargo compartment can be optionally equipped

with Ventilation and heating systems. The AFT

ventilation and heating systems are also optional.

CARGO COMPARTMENT TEMPERATURE

The cargo compartment temperature is indicated in green

and given by the cargo temperature sensor .

ZONE INDICATION

The zone indication is displayed in white.

DUCT INLET TEMPERATURE

The duct inlet temperature indication is normally

green and given by the duct temperature sensor.

The indication becomes amber if the duct inlet

temperature is at 80ºC (176ºF) or more.

TRIM AIR VALVE

The trim air valve indication on the ECAM page normally

shows the true position of the trim air valve.


The outlet isolation valve is displayed in green when

open or closed and amber when faulty.






The inlet isolation valve is displayed in green when


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21-28-00 FWD CARGO COMPARTMENTVENTILATION/HEATING -SYSTEM WARNINGS

CONTENTS:

FWD Cargo Isolation Valve FaultFWD Cargo Duct Overheat

FWD Cargo Heating Fault

FWD Cargo Ventilation Fault





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21 - FWD CARGO COMPARTMENT VENT/HEATING

21-28-00 FWD CARGO COMPARTMENTVENTILATION/HEATING -COMPONENTS

CONTENTS:

Cargo Ventilation ControllerHeating Controller

Isolation Valves

Extraction Fan

Pressure Switch

Trim Air Valve

Temperature Sensors





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FWD CARGO COMPARTMENT VENTILATION/HEATING - COMPONENTS


IDENTIFICATION

FIN: 10HN

LOCATIONZONE: 126


It is a modular construction and consists of:

- AFT cargo ventilation module,

- AFT cargo power relay,

- FWD cargo ventilation module,

- FWD cargo power relay,

-common power supply module,

- spare module connector,

- spare power relay socket.

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HEATING CONTROLLER

IDENTIFICATION

FIN: 1HC

LOCATIONZONE: 121


The heating controller consists of a MCU box installed

in the avionics compartment, in rack 95 VU.

Power up test:

- computer internal tests,

- check of sensor,

-check for Trim Air Valve closure,

- check for HOT AIR Pressure Regulating Valve

closure.

Test duration: 40 seconds.

3





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ISOLATION VALVES

IDENTIFICATION

FIN: 4HN, 5HN

LOCATIONZONE: 132, 131


The electrically operated butterfly valves consist of:

- a 28 VDC motor which drives a gear train,

- two microswitches (signal fully open/fully

closed position of isolation valves to the

ventilation controller),

-a manual override and visual positionindicator.

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EXTRACTION FAN

IDENTIFICATION

FIN: 6HN

LOCATIONZONE: 132


The extraction FAN is:

- powered by a 3 phase 4 pole induction motor,

the fan runs at about 11700 rpm,

- thermal switches isolate the electrical supply

in case of stator temperature of 140°C (284°F),

-a relay signals malfunction to the ECAM andto the CFDS via the ventilation controller.

L

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FWD CARGO COMPARTMENT VENTILATION/HEATING - COMPONENTS - EXTRACTION FAN T

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PRESSURE SWITCH

IDENTIFICATION

FIN: 21HN

LOCATION

ZONE: 132


The pressure switch consists of a body with two

pressure ports, a diaphgrapm, a spring, a microswitch

and an electrical connector.

When the ∆P reaches 1 psi, the spring snaps over and

depresses the microswitch actuator. A signal is sent

to the cargo ventilation controller which stops the

extract fan. When the pressure decreases, the

microswitch returns to original position, this removes

the pressure signal and the extract fan starts.

E L

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T

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TRIM AIR VALVE

IDENTIFICATION

FIN: 2HC

LOCATION

ZONE: 137


- a stepper motor drives the shaft of the

butterfly,

- limit switches stop the valve (mechanical stops

are as back up),

- a manual override and visual position

indicator,- a return spring closes the trim air valve

if power supply is lost or if the

controller does not operate.

V E L

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T

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TEMPERATURE SENSORS

IDENTIFICATION

FIN: 3HC, 4HC

LOCATION

ZONE: 131, 132


The two temperature sensors are used for temperature

control, indication and overheat detection.

V E L

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21-43-00 AFT CARGO COMPARTMENTVENTILATION/HEATING -SYSTEM PRESENTATION

CONTENTS:

Pressure Regulating Valve (PRV)

Trim Air Valve


Extraction Fan



Heating Controller

L

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AFT CARGO COMPARTMENT VENTILATION/HEATING - SYSTEM PRESENTATION


The hot air is tapped from the bleed air duct and

pressure regulated by the cargo HOT AIR Pressure

Regulating Valve above the cabin pressure.

The cargo HOT AIR Pressure Regulating Valve regulates

the HOT AIR pressure (4 psi above the cabin pressure)

going to the Trim Air Valve.

TRIM AIR VALVE

The trim air valve regulates the hot air flow, the hot

air is then mixed with the cabin ambient air to obtain

the desired temperature.


The inlet isolation valve permits the air which has

been mixed to enter into the aft cargo compartment.

EXTRACTION FAN

The suction of the air is caused by the extraction fan

when it is running.

The extract fan runs only if both isolation valves areopen.



The cargo ventilation system part is controlled by the

ventilation controller.

The cargo ventilation controller controls the

isolation valves and the extract fan. In normal

operation they are open and the fan runs continuously

HEATING CONTROLLER

The cargo heating system part is controlled by the

cargo heating controller.

The heat controller receives temperature indications

from two temperature sensors and controls the Trim Air

Valve in order to regulate the amount of hot air added

to cabin ambient air.It closes the Trim Air Valve when:

- the isolation valve is closed,

- the cargo HOT AIR Pressure Regulating Valve is

closed,

- the extract fan has failed,

- the cargo door is not closed and locked.

It also determines the Trim Air Valve position by means

of a step counter (it counts the steps of the TAV

stepper motor).

L E V E L

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The outlet isolation valve permits the aft cargo

compartment air to be discharged in the area of the

outflow valve.

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21-43-00 AFT CARGO COMPARTMENTVENTILATION/HEATING -SYSTEM CONTROLS PRESENTATION

CONTENTS:

Aft Isol Valve Pushbutton

Temperature Selector

Hot Air Pushbutton

Self Examination

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AFT CARGO COMPARTMENT VENTILATION/HEATING - SYSTEM CONTROLS PRESENTATION

AFT ISOL VALVE PUSHBUTTON

The AFT ISOL VALVE pushbutton controls the isolation

valves and the extraction fan through the ventilation

controller.

When it is pressed in, the cargo ventilation controller

will start the extract fan (only if both isolation

valves are fully open).

When it is set to OFF or if smoke is detected, the

isolation valves are closed and the extract fan stops.

TEMPERATURE SELECTOR

The temperature rotary selector gives the desired

temperature to the heating controller which controls

the Trim Air Valve to add hot air to cabin ambientair, if necessary.

The selector temperature range is between 5ºC (41ºF)

and 26ºC (79ºF) with 16ºC (60ºF) at the 12 o’clock

position.

HOT AIR PUSHBUTTON

The hot air pushbutton switch is used to control the

cargo HOT AIR Pressure Regulating Valve (PRV).When it is set to OFF, the valve is closed.

Note In case of duct temperature above 88ºC (190ºF),

the heating controller controls the cargo HOT AIR

P R l ti V l t l

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Pressure Regulating Valve to close.

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SELF EXAMINATION

The HOT AIR pushbutton switch controls the:

A - Blower fan.

B - Aft cargo door.

C - Pressure Regulating Valve.

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21-43-00 AFT CARGO COMPARTMENTVENTILATION/HEATING -ECAM PAGE PRESENTATION

CONTENTS:

General

Cargo Compartment Temperature

Zone Indication

Duct Inlet Temperature

Trim Air Valve

Pressure Regulating Valve



E V E L

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AFT CARGO COMPARTMENT VENT/HEATING - ECAM PAGE PRESENTATION

GENERAL

The AFT cargo compartment can be optionally equipped

with ventilation and heating systems. The FWD

ventilation and heating systems are also optional.

CARGO COMPARTMENT TEMPERATURE

The cargo compartment temperature is indicated in green

and given by the cargo temperature sensor.

ZONE INDICATION

The zone indication is displayed in white.

DUCT INLET TEMPERATURE

The duct inlet temperature indication is normally green

and given by the duct temperature sensor.

Indication becomes amber if the duct inlet

temperature is at 176oF (80ºC) or more.

TRIM AIR VALVE

The Trim Air Valve indication on the ECAM page normallyshows the true position of the trim air valve.


The Pressure Regulating Valve indication is displayed


The inlet isolation valve is displayed in green when



The outlet isolation valve is displayed in green when


0 1

L E V E L

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in green when open or closed and amber when faulty.

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21-43-00 AFT CARGO COMPARTMENTVENTILATION/HEATING -SYSTEM WARNINGS

CONTENTS:

Aft Cargo Isolation Valve Fault

Aft Cargo Duct OverheatAft Cargo Heating Fault

Aft Cargo Ventilation Fault

L E V E L

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T M U V E

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- P

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T M U V E

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AFT CARGO COMPARTMENT VENTILATION/HEATING - SYSTEM WARNINGS

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21-28-00 AFT CARGO COMPARTMENTVENTILATION/HEATING -COMPONENTS

CONTENTS:


Heating ControllerIsolation Valves

Extraction Fan

Pressure Regulating Valve

Trim Air Valve

Temperature Sensors

L E V E L

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AFT CARGO COMPARTMENT VENTILATION/HEATING - COMPONENTS


IDENTIFICATION

FIN: 10 HN

LOCATION

ZONE: 126


It is a modular construction and consists of:

- AFT cargo ventilation module,

- AFT cargo power relay,

- FWD cargo ventilation module,

- FWD cargo power relay,

- common power supply module,

- spare module connector,

- spare power relay socket.

- T

0 1

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0 A

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HEATING CONTROLLER (Temperature Controller)

IDENTIFICATION

FIN: 10 HC

LOCATION

ZONE: 121


The heating controller consists of an MCU box installed

in the avionics compartment, in rack 96 VU.

Power up test:

- computer internal tests,

- check of sensor,

- check for Trim Air Valve closure,

-check for aft Trim Air Pressure Regulating

Valve closure.

Test duration: 40 seconds.

A - T

0 2

L E V E L

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T M U V E N P

0 A

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0 2

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0

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ISOLATION VALVES

IDENTIFICATION

FIN: 33 HN, 34 HN

LOCATION

ZONE: 172, 151


Electrically operated butterfly valves consist of:

- a 28 VDC motor which drives a gear train,

- two microswitches (signal fully open/fully

closed position of isolation valves to the

ventilation controller),


indicator.

0 A - T

0 3

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3





T M U V E N P

0

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0 3

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0



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EFFECTIVITY

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EXTRACTION FAN

IDENTIFICATION

FIN: 35 HN

LOCATION

ZONE: 172


The extraction FAN is:

- powered by a 3 phase 4 pole induction motor,

the fan runs at about 11400 rpm,

- thermal switches isolate the electrical supply

in case of stator temperature of 123°C (254°F),

- a relay signals malfunction to the ECAM and

to the CFDS via the ventilation controller.

P 0 A - T

0 4

L E V E L

3



0



T M U V E N P

EFFECTIVITY

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0



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IDENTIFICATION

FIN: 11 HC

LOCATION

ZONE: 151


Electrically controlled and pneumatically actuated.

Consists of:

- a valve body assembly,

- a regulator servo valve,

- an actuator assembly,

- a solenoid valve assembly,

-an actuator body assembly,

- an indicator assembly,


indicator,

- a locking mechanism.

N P

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0 0



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0 A - P

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0 0



T M U V E N

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EFFECTIVITY

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TRIM AIR VALVE

IDENTIFICATION

FIN: 12 HC

LOCATION

ZONE: 151


- a stepper motor drives the shaft of the

butterfly,

- limit switches stop the valve (mechanical stops

are as backup),


indicator,

-a return spring closes the trim air valveif power supply is lost or if the

controller does not operate.

N P

0 A - T

0 6

L E V E L

3



2 0 0



T M U V E

EFFECTIVITY

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EFFECTIVITY

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TEMPERATURE SENSORS

IDENTIFICATION

FIN: 13 HC, 14 HC

LOCATION

ZONE: 154, 160


used for temperature control, indication and overheat

detection.

E N P

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0 7

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2 0 0



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EFFECTIVITY

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21-00-00 CFDS SPECIFIC PAGE PRESENTATION

CONTENTS:

CPC 1

Last Leg Report

Previous Legs Report

Class 3 FaultsTEMP CTL

Last Leg Report

Previous Legs Report

GND Report

FWD CHC & AFT CHC

Last Leg Class 3 Faults

Ground Report

T E M Y

0 1

L E V E L

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4 2 0 0



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CFDS SPECIFIC PAGE PRESENTATION

CPC 1

LAST LEG REPORT

This item presents the same type of failure messages

as described in chapter 31 (type 1 system) with the

same presentation, the FIN number is in addition.

NOTE: a GND indication appears at the end of the failure

messages in case of failure detected on the

ground.Fault codes are transmitted in addition

to CFDS messages (engineering level).

PREVIOUS LEGS REPORT


as described in chapter 31 (type 1 system) with

different presentation: phase, FIN and flight number

indications are added to the leg, the date, time and

ATA reference indications.

NOTE: a GND indication appears at the end of the failure

messages in case of failure detected on the

ground.

Fault codes are transmitted in addition to CFDS

messages (engineering level).

CLASS 3 FAULTS



different presentation: leg, phase and FIN number

indications are added to the date, time and ATA

reference indications.Fault codes are transmitted in addition to CFDS

messages (engineering level).

U T E M Y

0 1 - T

0 1

L E V E L

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F 4 2 0 0



T M U

EFFECTIVITY

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U T E M Y

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F 4 2 0 0



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EFFECTIVITY

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TEMP CTL

LAST LEG REPORT


as described in chapter 31 (type 1 system) with the

same presentation, the FIN number is in addition.

PREVIOUS LEGS REPORT



different presentation: phase and FIN number

indications are added to the leg, the date, time and

ATA reference indications.

GND REPORT

This item is the equivalent of the LAST LEG REPORT for

the failures that have occured on the ground.

The failure messages contain the time, the phase, the

ATA reference and the FIN number.

U T E M Y

0 1 - T

0 2

L E V E L

3



F 4 2 0 0



T M

EFFECTIVITY

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CFDS SPECIFIC PAGE PRESENTATIONM U T E M Y

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EFFECTIVITY

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FWD CHC & AFT CHC

Note : The FWD CHC and AFT CHC pages are optional.

LAST LEG CLASS 3 FAULTS

This item presents the class 3 failures concerning

this system that appeared during the last flight.These

failure messages contain the name of the equipment

affected and the date.

GROUND REPORT

This item is the equivalent of the LAST LEG REPORT for

the failures that have occured on the ground.The

failure messages contain the date, the time, the ATA

reference and the class failure.

M U T E M Y

0 1 - T

0 3

L E V E L

3



F F

4 2 0 0



T M

EFFECTIVITY

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CFDS SPECIFIC PAGE PRESENTATIONT M U T E M Y

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EFFECTIVITY

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T M U T E M Y

0 1

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U F F

4 2 0 0



T

EFFECTIVITY

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a32x training manual

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