a318_21_jar_b1_e air con.pdf

8/17/2019 A318_21_JAR_B1_E AIR CON.pdf

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PART 66 B1

Lufthansa

Lufthansa Base

For Training Purposes Only

Lufthansa 1995©

Technical Training GmbH

Training ManualA 318

ATA 21

Air Condition

Diff. to A320

A318 21 JAR B1 E


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For training purposes and internal use only.

Copyright by Lufthansa Technical Training GmbH.

All rights reserved. No parts of this trainingmanual may be sold or reproduced in any formwithout permission of:

Lufthansa Technical Training GmbH

Lufthansa Base Frankfurt

D-60546 Frankfurt/Main

Tel. +49 69 / 696 41 78

Fax +49 69 / 696 63 84

Lufthansa Base Hamburg

Weg beim Jäger 193

D-22335 Hamburg

Tel. +49 40 / 5070 22 26

Fax +49 40 / 5070 47 46


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F o r T r a i n i n g P u r p o s e s O

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AIR CONDITIONING A318 DIFF.

21

FRA US/T- 5 WeT 23.09.2003 Page: 1

ATA 21 AIR CONDITIONING


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AIR CONDITIONING

GENERAL

A318

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FRA US/T- 5 Jacobi 16.10.2003 Page: 2

21−00 GENERAL

DIFFERENCES BETWEEN A320 AND A318

The A318 Air Conditioning system is designed with several changes.

On the new Air Conditioning system, several components are replaced:

New Air Conditioning System Controllers (ACSCs)

Flow control valve (FCV)

Ram air inlet actuator (RAIA)

Anti- ice valve (AIV)

Air conditioning panel 30 VU

Pack Temperature Sensor

Some other are deleted :

Pack Outlet Pneumatic Sensor (POPS)

Compressor Pneumatic OverHeat sensor (CPNOH)

Pack flow sensor

Pneumatic sensing pipe lines

On the A318 the new pack system includes two new ACSCs, an electricallycontrolled AIV, an improved FCV with integrated pressure sensors and an im-proved RAIA with speed and direction sensors.

On the air conditioning panel the pack flow selector is replaced by a HI FLOWpushbutton which enables NORM or HI flow.


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AIR CONDITIONINGGENERAL

A318

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Figure 1 Air Cooling A320


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AIR CONDITIONING

GENERAL

A318

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Differences between A320 and A318

The A318 Air Conditioning system is designed with several changes.

On the new Air Conditioning system, several components are replaced: New Air Conditioning System Controllers (ACSCs)

Flow control valve (FCV)

Ram air inlet actuator (RAIA)

Anti- ice valve (AIV)

Air conditioning panel 30 VU

Pack Temperature Sensor

Some other are deleted :

Pack Outlet Pneumatic Sensor (POPS)

Compressor Pneumatic OverHeat sensor (CPNOH)

Pack flow sensor

Pneumatic sensing pipe lines

On the A318 the new pack system includes two new ACSCs, an electricallycontrolled AIV, an improved FCV with integrated pressure sensors and an im-proved RAIA with speed and direction sensors.

On the air conditioning panel the pack flow selector is replaced by a HI FLOWpushbutton which enables NORM or HI flow.


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Figure 2 Air Cooling A318


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PACK SYSTEM DESCRIPTION/ OPERATION

Flow Control Valve

The FCV is an electro- pneumatic butterfly valve with the following main func-

tions: control of the mass flow of bleed air entering the pack.

isolation of the pack from the bleed air supply (crew selection, engine fire,ditching, or engine start).

Air cycle machine overheat and low pressure start up protection (controlledby the ACSC).

ACSC1 controls the FCV for pack 1, while ACSC2 controls the FCV for pack 2.

Under normal conditions, each ACSC uses a closed loop electronic control cir-cuit to regulate the butterfly position and resulting pack inlet flow.

The FCV has two modes of operation:

main: electrical control (100% to 144%)

back- up: pneumatic control (140% to 174%)In the main operating mode, the FCV position is modulated to respond to:

changing flow demands

control priorities (take- off, landing, pack start, etc.)

failures and pack overheat conditions.

In the back- up mode, the FCV flow is controlled by a downstream pressureregulator.

Anti Ice Valve

The AIV is operated by an electro- mechanical actuator.

The valve is controlled by the ACSC.

The AIV main function is to remove ice build- up from components downstreamof the turbine outlet (condenser tubing, temperature sensors, check valves,mixing unit).

The ACSC uses the Pack Discharge Pressure Sensor (PDPS) to compare thepack discharge pressure to the turbine outlet pressure. If the difference be-tween these two pressures exceeds a predetermined limit, then icing is as-sumed.

As a result, the ACSC will command the AIV to open, hot air flows directly intothe turbine outlet and pack discharge. This hot air will melt the ice, causing thepack discharge pressure to return to a normal value.

Once the pressures are within a certain limit, the AIV will fully close.

The AIV is identical and interchangeable with the system Trim Air Valves (TAV).

Pressure Sensors

Each pack has 3 pressure sensors. These sensors are used for the followingpurposes:

flow control, actual flow calculation

icing detection

The PDPS detect an increase in the ACM turbine outlet pressure relative to theaircraft cabin. This indicates icing conditions exist.

Ram Air Inlet Actuator

The Ram Air Inlet Actuator (RAIA) is monitored and controlled by the ACSCs.


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A318

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Figure 3 Air Cooling Pack System Description/ Operation


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Air Conditioning System Controller

The ACSC is a 2 lane, fully redundant computer system with independent cen-tral, processing units and duplicated hardware interfaces.

One lane is active while the other lane is passive (“hot- standby“).

If the active lane is not able to control the system, the passive lane will becomeactive and take over system control.

The active lane switches at each aircraft landing, assuming the passive lanehas no faults which are more severe than those in the active lane.

The ACSCs perform the following functions:

temperature control

zone control

mixer- pack control

flow control (pack FCV)

demand calculation

pack flow

pack temperature

overheat monitoring/ control (pack and ducts)

ACS component monitoring and fault detection

ACS failure storage

data exchange (ACSC1, ACSC2, A/C systems)

ACSC1 and ACSC2 have different functions. Functional differences betweenthe two controllers are determined by pin programming after installation in theaircraft.

In general, the functions allocated to each controller are as follows:

ACSC1:

control of F/D zones, trim system and trim air pressure relief valve, wing and nacelle anti ice logic.

ACSC2:

control of cabin zones and trim system,

CFDS interface and fault storage,

wing anti ice fault analysis,

mixer flap drive and monitoring.

The ACSCs 1 and 2 interface with:

the engine FADEC system for pack shut down during engine start,

the APU ECB for increased or decreased bleed air flow according to packdemand.


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Figure 4 Air Cooling Pack System Description/ Operation


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COCKPIT AND CABIN DESCRIPTION/OPERATION

There is one major modification on the A318.

During normal or abnormal operation the control of the cockpit and cabin sys-tem is now ensured by the two ACSCs.

Cabin zones demanding a higher temperature than that available from themixer unit will receive additional hot trim- air by TAV.

Operating of the TAVs will be done by ACSC1 for cockpit and ACsc2 for thefwd and aft cabin zones.


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A318

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Figure 5 Air Cooling Cockpit and Cabin


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CFDS MCDU PAGES

Some minor modifications have been applied on the MCDU CAB TEMP CONTmenu page:

A GROUND REPORT line is added.


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A318

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Figure 6 Air Cooling CFDS MCDU Pages


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TABLE OF CONTENTS

A318 21 JAR B1 E

Page iFRA US/T- 5 Jacobi OCT 2003

ATA 21 AIR CONDITIONING 1. . . . . . . . . . . . . . . . . .

21−00 GENERAL 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DIFFERENCES BETWEEN A320 AND A318 2. . . . . . . . . . . . . . . . . . . .

PACK SYSTEM DESCRIPTION/ OPERATION 6. . . . . . . . . . . . . . . . . .

COCKPIT AND CABIN DESCRIPTION/OPERATION 10. . . . . . . . . . . . .

CFDS MCDU PAGES 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


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TABLE OF FIGURES

A318 21 JAR B1 E

Page iiFRA US/T- 5 Jacobi OCT 2003

Figure 1 Air Cooling A320 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Figure 2 Air Cooling A318 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Figure 3 Air Cooling Pack System Description/ Operation 7. . . . .

Figure 4 Air Cooling Pack System Description/ Operation 9. . . . .

Figure 5 Air Cooling Cockpit and Cabin 11. . . . . . . . . . . . . . . . . . . . . .

Figure 6 Air Cooling CFDS MCDU Pages 13. . . . . . . . . . . . . . . . . . . .

a318_21_jar_b1_e air con.pdf

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