26-fire

A319/A320/A321TECHNICAL TRAINING MANUAL

MECHANICS / ELECTRICS & AVIONICS COURSE

26 FIRE PROTECTION

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.

GENERALSystem Presentation (1) 1..........................

ENGINE FIRE PROTECTIONSystem Presentation (1) 5..........................Engine Fire Detection Logic (3) 11.................Fire Push-Button Interfaces (3) 19.................System Warnings (3) 23..............................SYS Operation in Case of ENG Fire in Flight(3) 27.SYS Operation in Case of ENG Fire on GND (3) 31...Precautions (3) 35..................................Components (3) 37...................................Electrical Circuits (3) 45.........................

APU FIRE PROTECTIONSystem Presentation (1) 53.........................APU Fire Detection Logic (3) 59....................Fire Push-Button Interfaces (3) 67.................System Warnings (3) 71..............................** Auto Extinguishing Ground Test (3) 75..........System Operation in Case of APU Fire (3) 79.......Auto Extinguishing on Ground (2) 83................Precautions (3) 87..................................Components (3) 89...................................Electrical Circuits (3) 97.........................

AVIONICS SMOKE DETECTIONSystem Presentation (1) 107........................Smoke Procedures (3) 111............................Components (3) 123..................................

CARGO & LAVATORY FIRE PROTECTIONCargo Fire Protection Syst Presentation (1) 127...Lavatory Fire Protection SYS Presentation(1) 133..** Cargo & Lavatory SMK Detection SYS D/O(3) 137..Cargo Smoke Detection Warnings (3) 143............

Cargo Smoke Procedure (3) 147......................Lavatory Smoke Detection Warnings (3) 151.........Lavatory Waste Bin Fire Extinguishing (3) 155.....** Programming and Test Panel Utilization (2) 159.Precautions (3) 163.................................** Components (3) 165...............................

PORTABLE EQUIPMENTPortable Fire Extinguishers (1) 179................

MAINTENANCE PRACTICESSPECIFIC PAGES** CFDS Specific Page Presentation (3) 183......

_A319/A320/A321 TECHNICAL TRAINING MANUAL

26 FIRE PROTECTIONMECHANICS / ELECTRICS & AVIONICS COURSE

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26 FIRE PROTECTION

UFD4200 TABLE OF CONTENTS Page

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26 - FIRE PROTECTION

26-00-00 GENERAL SYSTEM PRESENTATION

CONTENTS:GeneralEngine Fire ProtectionAPU Fire ProtectionAvionics Smoke DetectionCargo Fire ProtectionLavatory Fire ProtectionPortable Fire Extinguishers

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GENERAL SYSTEM PRESENTATION

GENERAL

The fire protection system provides:- Fire detection and extinguishing systems forthe engine and the APU

- Smoke detection and extinguishing systems forthe foward and Aft/Bulk cargo compartment andfor lavatories

- Smoke detection for the avionics compartment- Portable fire extinguisher bottle for fightingfire.

ENGINE FIRE PROTECTION

The engine fire protection is provided by two systems:The fire detection systems and the fire extinguishingsystem.

APU FIRE PROTECTION

The APU fire protection is provided by two systems:The fire detection system and the fire extinguishingsystem.

AVIONICS SMOKE DETECTION

The avionics smoke detection is provided by one smokedetector installed on the air extraction duct in theavionics compartment.

CARGO FIRE PROTECTION

The cargo fire protection is provided by two systems:The cargo smoke detection system and the cargo fireextinguishing system.The forward and Aft/Bulk cargo compartment fireprotection is optional (smoke detection and fireextinguishing separately).Note that an option with a second bottle enables fireextinguishing extended duration for Etops.

LAVATORY FIRE PROTECTION

The lavatory fire protection is provided by twosystems: The lavatory smoke detection system and thewaste bin automatic fire extinguishing system.

PORTABLE FIRE EXTINGUISHERS

The portable fire extinguishers are used for fightingfire in the cockpit and cabin.

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GENERAL SYSTEM PRESENTATION




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26-12-00 SYSTEM PRESENTATION

CONTENTS:GeneralFire DetectorsFire Detection Unit (FDU)WarningsTest P/BEngine Fire P/BAgent P/BBottlesSelf Examination

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SYSTEM PRESENTATION

GENERAL

The engine fire protection is provided by two systems:The fire detection and the fire extinguishing systems.

FIRE DETECTORS

Each engine fire detection system consists of twoindependent loops A and B connected in parallel to theFire Detection Unit (FDU). Each loop comprises threefire detectors connected in parallel. Loops A and Bare connected in parallel to the Fire Detection Unit(FDU). Each loop comprises:

- Fan fire detector- Pylon fire detector- Core fire detector

FIRE DETECTION UNIT (FDU)

One Fire Detection Unit is provided for eachengine. The Fire Detection Unit (FDU) processessignals received from the fire detectors.

WARNINGS

The Fire Detection Unit generates signals for ECAMdisplay, Centralized Fault Display System utilizationand cockpit local warnings.

- Fire warning signals are sent to ECAM and enginefire and start control panels.

- Loop failure warnings are sent to ECAM andCentralized Fault Display System (CFDS).

TEST P/B

On the engine fire panel the TEST pushbutton permitsthe fire detection and the extinguishing systems tobe checked. During the test, the SQUIB lights come onif the continuity of the squib circuit is correct. TheDISCH lights are also activated but as a lamp test.The TEST pushbutton checks simultaneously theintegrity of the:

- Fire detection loops A and B, FDU, indicationsand warnings.

- Squib circuit continuity of AGENT 1 and 2.

ENGINE FIRE P/B

When the ENGINE FIRE pushbutton is released out, theSQUIB lights come on and the extinguishing system isarmed. At the same time, the engine is isolated fromthe other aircraft systems. When the ENG FIREPUSHbutton is released out:

- Both SQUIB lights come on indicating bottlepercussion is available.

- Aircraft systems are isolated.

AGENT P/B

Action on the AGENT pushbutton provides bottledischarge when the ENGINE FIRE PUSHbutton is stillreleased out. A pressure switch activates thecorresponding DISCH light when the agent has beendischarged.

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SYSTEM PRESENTATION

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SYSTEM PRESENTATION

BOTTLES

Two extinguisher bottles are installed in the pylon.Each bottle is equipped with a pressure switch tomonitor agent pressure and an electrically operatedSQUIB, for agent discharge.

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SELF EXAMINATION

Is the extinguishing system controlled by the FDU?A - Yes.B - No.

Where are the fire detectors located?A - On the fan and the turbine.B - On the pylon, the fan and the core.C - On the core and the gearbox

The AGENT pushbutton is active when:A - The corresponding "DISCH" light

illuminates.B - ENGINE FIRE PUSHbutton illuminates.C - ENGINE FIRE PUSHbutton is released out

What does the TEST pushbutton check?A - Only the fire detection loops A and B,

FDU, indications and warnings.B - Only the squib circuit continuity of

AGENT 1 and 2.C - Both simultaneously.

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26-12-00 ENGINE FIRE PROTECTION: FIREDETECTION LOGIC

CONTENTS:GeneralFire WarningLoop Fault WarningDetection Fault Warning

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ENGINE FIRE PROTECTION: FIRE DETECTION LOGIC

GENERAL

The engine Fire Detection Unit (FDU) has two channelscapable of detecting any case of engine fire and loopfailure. Each channel performs the same detection logicdepending on the loop A and loop B status.

FIRE WARNING

In case of a fire detected on both loops or on oneloop with the other faulty, the channels provide afire warning to the ENGINE FIRE panel, ENGINE STARTcontrol panel and ECAM displays.The fire Detection Unit (FDU) generates a fire warningsignal if any of the following conditions are met:

- Fire on loop A and fire on loop B- Fire on loop A and fault on loop B- Fault on loop A and fire on loop B- Fault on loop A and fault on loop B within5 seconds (both loops broken due to atorching flame).

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ENGINE FIRE PROTECTION: FIRE DETECTION LOGIC - FIRE WARNING

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LOOP FAULT WARNING

In case of a loop failure the Fire Detection Unitprovides a loop fault warning signal to the ECAM andCentralized Fault Interface Unit (CFDIU).The Fire Detection Unit (FDU) generates an inoperativesignal if any of the following conditions are met:

- Electrical failure- Integrity failure- Detection of a single loop FIRE during morethan 16s while the other loop is in normalcondition.

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ENGINE FIRE PROTECTION: FIRE DETECTION LOGIC - LOOP FAULT WARNING

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DETECTION FAULT WARNING

The detection fault logic is based on a dual loopfailure. It corresponds to a total loss of thedetection system.When the Fire Detection Unit generates two inoperativesignals corresponding to loop A and loop B fault logic,the Flight Warning Computer (FWC) elaborates the faultwarning.

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ENGINE FIRE PROTECTION: FIRE DETECTION LOGIC - DETECTION FAULT WARNING

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26-12-00 ENGINE FIRE PROTECTION - FIREPUSHBUTTON INTERFACES

CONTENTS:GeneralMonitoring InterfacesSupply InterfacesSelf Examination

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ENGINE FIRE PROTECTION - FIRE PUSHBUTTON INTERFACES

GENERAL

During the engine fire procedure, the ENGINE FIREPUSHbutton is manually released out. This triggersseveral automatic sequences simplifying further crewactions and system monitoring.

MONITORING INTERFACES

Releasing the fire pushbutton out, cancels theContinuous Repetitive Chime, signals the action to theFlight Warning Computer (FWC) for further managementof other warnings and messages and illuminates theSQUIB light on the Engine Fire Control panel.

SUPPLY INTERFACES

Quick isolation of all systems on the related enginewhich could be the origin of the fire or feed the fireis achieved as soon as the fire pushbutton is releasedout. These systems are:

- Fuel.- Air.- Electric Power.- Hydraulic Power.

The electric supply to the Engine Interface (EIU) isalso disconnected.

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ENGINE FIRE PROTECTION - FIRE PUSHBUTTON INTERFACES

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SELF EXAMINATION

When the ENG FIRE PUSHbutton is released out, whichcorresponding fire valves are closed?

A - Fuel crossfeed valve.B - LP fuel and hydraulic fire Shut Off

Valves.C - HP fuel Shut Off Valve.

When the ENG FIRE PUSHbutton is released out, arethe bleed and the pack valves closed?

A - Yes.B - No.

When the ENG FIRE PUSHbutton is released out, whathappens to the electrical generation?

A - IDG de-energized.B - IDG disconnect.C - IDG energized.

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26-12-00 ENGINE FIRE PROTECTION

CONTENTS:System Warnings

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ENGINE FIRE PROTECTION

SYSTEM WARNINGS

When an engine fire is detected, the continuousrepetitive chime sounds, the MASTER WARNING flashes,the ENGINE FIRE PUSHbutton light and the FIRE lighton the ENGINE start panel come on.ENGINE FIRE appears on the Engine Warning display.

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ENGINE FIRE PROTECTION - SYSTEM WARNINGS

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26-12-00 ENGINE FIRE PROTECTION - SYSTEMOPERATION IN CASE OF ENGINE FIRE

CONTENTS:GeneralFire Procedure

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ENGINE FIRE PROTECTION - SYSTEM OPERATION IN CASE OF ENGINE FIRE

GENERAL

The following fire procedure describes the actions tobe performed by the cockpit crew when an engine firewarning occurs in flight. The procedure takes Engine2 as an example.

FIRE PROCEDURE

When a fire is detected, the continuous repetitivechime sounds, the MASTER WARNING flashes, the ENGINEFIRE PUSHbutton light comes on and the FIRE light onthe ENGINE start control panel comes on.

- Select MASTER WARNING. The MASTER WARNING lightgoes off and the Continuous Repetitive Chimestop.

- Select thrust lever to IDLE.- Select ENG MASTER 2 lever to OFF. When theMASTER lever is set to OFF, the low pressureand the high pressure fuel valves close andcause engine shutdown.

- Select ENG 2 FIRE PUSHbutton.When the ENGINE FIRE PUSHbutton is released out thesingle chime sounds. The MASTER CAUTION comes on dueto systems deactivation.The fuel low pressure valve closure is confirmed. TheSQUIB lights come on on the AGENT pushbuttons toindicate that AGENT pushbuttons can be used.Wait for 10 seconds: this is required to reduce enginewindmilling, reducing the nacelle ventilation whichincreases the agent effect.

- Select AGENT 1 pushbutton.

When the AGENT 1 pushbutton is pressed, fire bottleone is discharged in the engine compartment and theDISCH light comes on.If the fire still persists after 30 seconds, the secondbottle must be discharged.

- Select AGENT 2 pushbutton.When the fire is extinguished, the ENGINE FIREPUSHbutton light and the FIRE indication on the ENGINESTART panel go off.

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ENGINE FIRE PROTECTION - SYSTEM OPERATION IN CASE OF ENGINE FIRE

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26-12-00 ENGINE FIRE PROTECTION - SYSTEMOPERATION IN CASE OF ENGINE FIREON GROUND

CONTENTS:GeneralFire Procedure

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ENGINE FIRE PROTECTION - SYSTEM OPERATION IN CASE OF ENGINE FIRE ON GROUND

GENERAL

The following fire procedure describes the actions tobe performed by the cockpit crew when an engine firewarning occurs on ground.The procedure takes Engine 2 as an example.

FIRE PROCEDURE

When fire is detected, the continuous repetitive chimesounds, the MASTER WARNING flashes, the ENGINE FIREPUSHbutton light comes on and the FIRE light on theENGINE start panel comes on.

- Select MASTER WARNING Pushbutton. The MASTERWARNING light goes off and the ContinousRepetitive Chime stops

- As the rolling speed of the aircraft does notexceed V1, the crew must stop the aircraft.

- Select thrust levers to IDLE. Note that Full Reverse may be used to stop the aircraft.When the aircraft is stopped and parking brake is setto ON.

- Select ENG MASTER 2 lever to OFF.When the MASTER lever is set to OFF, the low pressureand high pressure valves close and cause engineshutdown.

- Select ENG 2 FIRE PUSHbutton.When the ENGINE FIRE PUSHbutton is released out thesingle chime sounds. The fuel low pressure valve closure is confirmed. TheSQUIB lights on the AGENT pushbuttons come on toindicate that AGENT pushbuttons can be used. The MASTERCAUTION comes on due to systems deactivation.

- Select AGENT 1 pushbutton.When the AGENT 1 pushbutton is pressed, fire bottleone is discharged in the engine compartment and theDISCH light comes on.

- Select AGENT 2 pushbutton.When the AGENT 2 pushbutton is pressed, the secondfire bottle is discharged in the engine compartmentand the DISCH light comes on.

- Select ENG MASTER 1 lever to OFF.When the second engine is shut down, if the APU is notrunning the ECAM displays are lost.If the APU is running, it must be shut down.

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ENGINE FIRE PROTECTION - SYSTEM OPERATION IN CASE OF ENGINE FIRE ON GROUND

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26-12-00 ENGINE FIRE PROTECTION:PRECAUTIONS

CONTENTS:GeneralFire BottleDischarge Cartridge

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ENGINE FIRE PROTECTION: PRECAUTIONS

GENERAL

Specific precautions must be taken during removal orinstallation of a fire extinguishing bottle and adischarge cartridge.

FIRE BOTTLE

WARNING: The fire bottle cartridges are explosive.Remove them before working on the bottle.Protective caps must be installed duringbottle removal/installation to preventdamage to discharge diaphragm which couldresult in injury to personnel.

DISCHARGE CARTRIDGE

WARNING: Before power is supplied to the aircraft makecertain that electrical circuits upon whichwork is in progress are isolated.

WARNING: Cartridges are class "C" explosives and mustbe handled or stored by authorized personnelor disposed of by an approved method.When cartridge electrical connectors aredisconnected, the cartridge electrical pinsmust be shunted with a protective shunt whichis provided by the manufacturer. A shunt plugor shorting clip, will prevent bottledischarge which could cause injury tomaintenance personnel.The cartridge installed must be of the samemake as the fire bottle and correspond to thespecification indicated in the MaintenanceManual.

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26-12-00 ENGINE FIRE PROTECTION:COMPONENTS

CONTENTS:Fire Detection Unit (FDU)Fire BottlesFire Detectors

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ENGINE FIRE PROTECTION: COMPONENTS

SAFETY PRECAUTIONS

WARNING:

Cartridges are explosive, remove them before workingon the bottle. Protective caps must be installed duringbottle removal/installation to prevent damage to thedischarge diaphragm which could result in injury topersonnel.

Before power is spplied to the aircraft make certainthat electrical circuits upon which work is in progressare isolated.Discharge cartridges are class "c" explosives and mustbe handled/stored by authorized personnel or disposedof by an approved method.When cartridge electrical connectors are disconnectedthe cartridge electrical pins must be shunted with aprotective shunt which is provided by the manufacturer.A shunt plug or shorting clip will prevent bottledischarge which could cause injury to maintenancepersonnel.The cartridge installed must be of the same make asthe bottle and correspond to the specificationindicated in the Maintenance Manual.

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IDENTIFICATIONFIN: 2WD1, 2WD2

LOCATIONZONE: 126

COMPONENT DESCRIPTIONFIRE DETECTION UNIT(S):- ENG1- ENG2

FIRE BOTTLES

IDENTIFICATIONFIN: 6WE2, 8WE2

LOCATIONZONE: 425

COMPONENT DESCRIPTION- Two per engine.- type of agent: bromotrifluoromethane.- Nominal Nitrogen pressure: at 21 deg.C, 600 psi.

PRESSURE SWITCHThe pressure switch is calibrated at:- 450 psi when the pressure increases (refilling).- 225/275 psi when the pressure decreases (dischargeor leak).A spring loaded finger permits the electricalcontinuity of the pressure switch to be manuallychecked.

DISCHARGE HEADThe discharge head has a leakproof metallic diaphragm.The rupture of the leakproof metallic diaphragm, iscaused by:- Gas pressure released after cartridge firing.- An excessive pressure (between 1600 to 1800 psi at95 deg.C, 203 deg.F), in the extinguisher bottle, incase of overheat condition in the engine pylon. Thefull quantity of the agent is released into thenacelle.

SQUIBThe squib is an electro pyrotechnic cartridgecontaining explosive powder, fired by two filamentssupplied with 28 VDC.

WARNING: Never check the continuity of the squib using aconventional ohmmeter.

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ENGINE FIRE PROTECTION: COMPONENTSFIRE DETECTION UNIT (FDU) - FIRE BOTTLES

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FIRE DETECTORS

COMPONENT DESCRIPTIONThe detector is pneumatically operated by heating itssensing element which contains helium gas and anhydrogen charged core material.

Alarm StateThe application of heat to the sensor causes anincrease of the gas pressure which in turn closes thealarm switch. The detector sends a fire signal.

Fault StateIn the event of gas pressure loss, the integrity switchopens and generates a fault signal.

PYLON FIRE DETECTORS


LOCATIONZONE: 425

CORE FIRE DETECTORS


LOCATIONZONE: 463

FAN FIRE DETECTORS


LOCATIONZONE: 445

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ENGINE FIRE PROTECTION: COMPONENTS - FIRE DETECTORSFAN AND PYLON FIRE DET. - PYLON FIRE DET. - FAN FIRE DET. - CORE FIRE DET.

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26-12-00 ENGINE FIRE PROTECTION:ELECTRICAL CIRCUITS

CONTENTS:DetectionExtinguishingInterfaces

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ENGINE FIRE PROTECTION: ELECTRICAL CIRCUITS - DETECTION




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ENGINE FIRE PROTECTION: ELECTRICAL CIRCUITS - EXTINGUISHING




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ENGINE FIRE PROTECTION: ELECTRICAL CIRCUITS - TEST




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ENGINE FIRE PROTECTION: ELECTRICAL CIRCUITS - ENG 2 FIRE PUSH




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ENGINE FIRE PROTECTION: ELECTRICAL CIRCUITS - DISCH




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ENGINE FIRE PROTECTION: ELECTRICAL CIRCUITS - INTERFACES




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CONTENTS:GeneralFire DetectorFire Detection Unit (FDU)WarningsTest P/BAuto ExtinguishingAPU Fire P/BAgent P/BBottleRed DiscSelf Examination

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EFFECTIVITY 26-13-00 Page 1Aug 31/98



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SYSTEM PRESENTATION

GENERAL

The APU fire protection is provided by two systems :The fire detection system and the fire extinguishingsystem.

FIRE DETECTOR

The fire detection system consists of two independentloops (A and B). Each loop comprises one fire detector.Loops A and B are connected in parallel to a FireDetection Unit (FDU).


A Fire Detection Unit is provided for the APU. TheFire Detection Unit (FDU) processes signals receivedfrom the fire detectors.

WARNINGS

The Fire Detection Unit generates signals for ECAMdisplay, Centralized Fault Display Systemutilization and cockpit local warnings.

- Fire warning signals are sent to ECAM, APU firepanel and external power control panel whenaircraft is on ground.

- Loop failure warnings are sent to ECAM andCentralized Fault Display System (CFDS).

TEST P/B

On the APU FIRE panel a TEST pushbutton permits thefire detection and the extinguishing systems to bechecked. During the TEST, the SQUIB light comes on ifthe continuity of the squib circuit is correct. TheDISCH light is also activated but as a lamp test.The TEST pushbutton checks simultaneously theintegrity of:

- Fire detection loops A and B, FDU, indicationsand warnings.

- Squib circuit continuity.

AUTO EXTINGUISHING

If an APU fire occurs while on ground, the APU isautomatically shutdown and the fire extinguishingsystem automatically triggered.

APU FIRE P/B

When the APU FIRE PUSHbutton is released out:- the SQUIB light comes on indicating bottlepercussion is available,

- and APU systems are isolated.

AGENT P/B

Action on the AGENT pushbutton provides bottledischarge if the APU FIRE PUSHbutton is still releasedout. A pressure switch activates the DISCH light whenthe agent has been discharged.

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SYSTEM PRESENTATIONT MU

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SYSTEM PRESENTATION

BOTTLE

An extinguisher bottle is installed outside of the APUcompartment, forward of the firewall. The bottle isequipped with a pressure switch to monitor agentpressure and an electrically operated squib for agentdischarge.

RED DISC

A red disc is visible from outside. The absence of thered disc indicates bottle overpressure discharge.

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SELF EXANIMATION

How is an APU fire on ground normally extinguished?A - From APU FIRE panel.B - Automatically.C - From EXTERNAL POWER panel.

How can a thermal discharge of the bottle bedetected on a cold aircraft?

A - By the FDU.B - By the ECAM.C - By the red disc indicator.

How many fire detectors does the APU fire detectionsystem comprise?

A - Three.B - Two.C - One.

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26 - FIRE PROTECTION:

26-12-00 APU FIRE PROTECTION: FIREDETECTION LOGIC

CONTENTS:GeneralFire WarningLoop Fault WarningDetection Fault Warning

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APU FIRE PROTECTION: FIRE DETECTION LOGIC

GENERAL

The APU Fire Detection Unit (FDU) has two channelscapable of detecting any case of APU fire and loopfailure. Each channel performs the same detection logicdepending on the loop A and loop B status.

FIRE WARNING

In case of a fire detected on both loops or on oneloop with the other faulty, the channels provide afire warning to the APU FIRE panel, EXTERNAL POWERCONTROL panel and ECAM displays.The Fire Detection Unit (FDU) generates a fire warningsignal if any of the following conditions are met :

- Fire on loop A and fire on loop B- Fire on loop A and fault on loop B- Fault on loop A and fire on loop B- Fault on loop A and fault on loop B within5 seconds (both loops broken due to atorching flame).

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APU FIRE PROTECTION: FIRE DETECTION LOGIC - FIRE WARNING

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LOOP FAULT WARNING

In case of a loop failure the Fire Detection Unitprovides a loop fault warning signal to the ECAM andCentralized Fault Display Interface Unit (CFDIU).The Fire Detection Unit (FDU) generates an inoperativesignal if any of the following conditions are met:

- Electrical failure- Integrity failure- Detection of a single loop FIRE during morethan 16s while the other loop is in normalcondition.

An electrical failure is signaled by a loop faultmessage if there is a loss of electrical power of theAPU fire detection system.An integrity failure is signaled by a loop faultmessage if there is a loss of pressure in a Fire SensorElement.

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APU FIRE PROTECTION: FIRE DETECTION LOGIC - LOOP FAULT WARNING

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DETECTION FAULT WARNING

The detection fault logic is based on a dual loopfailure. It corresponds to a total loss of thedetection system.When the Fire Detection Unit generates two inoperativesignals corresponding to loop A and loop B fault logic,the Flight Warning Computer (FWC) elaborates adetection fault warning.

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APU FIRE PROTECTION: FIRE DETECTION LOGIC - DETECTION FAULT WARNING

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26-13-00 APU FIRE PROTECTION - FIREPUSHBUTTON INTERFACES

CONTENTS:GeneralMonitoring InterfacesSupply InterfacesAuto Extinguishing on GroundSelf Examination

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APU FIRE PROTECTION - FIRE PUSHBUTTON INTERFACES

GENERAL

During the APU fire procedure, the APU FIRE PUSHbuttonis manually released out. This triggers severalautomatic sequences simplifying further crew actionsand system monitoring.

MONITORING INTERFACES

Releasing the fire pushbutton out, cancels theContinuous Repetitive Chime, signals the action to theFlight Warning Computer (FWC), for further managementof other warnings and messages and illuminates theSQUIB light on the APU Fire Control panel.

SUPPLY INTERFACES

Quick isolation of all systems on the APU which couldbe the origin of the fire or feed the fire is achievedas soon as the fire pushbutton is released out.These systems are:

- Fuel.- Air.- Electric Power.

The Electronic Control Box (ECB) of the APU istriggered to initiate an emergency APU shutdown.

AUTO EXTINGUISHING ON GROUND

When an APU fire is detected on ground, the APU shutsdown automatically and the fire extinguishing systemis automatically triggered.

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APU FIRE PROTECTION - FIRE PUSHBUTTON INTERFACES

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SELF EXAMINATION

When the APU FIRE pushbutton is released out, whichvalve is affected?

A - LP Fuel SOV.B - Hydraulic Fire SOV.C - Fuel Isolation Valve.

Is the APU bleed air supply maintained when the APUFIRE pushbutton is released out?

A - No.B - Yes.

When the APU FIRE pushbutton is released out, whathappens to the electrical generation?

A - APU generator is de-energized.B - APU generator is disconnected.C - APU generator is energized.

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26-13-00 APU FIRE PROTECTION

CONTENTS:System Warnings (APU FIRE IN FLIGHT)

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APU FIRE PROTECTION

SYSTEM WARNINGS (APU FIRE IN FLIGHT)

When an APU fire is detected, the continuous repetitivechime sounds, the MASTER WARNING flashes and the APUFIRE pushbutton light comes on. The APU FIRE procedureappears on the Engine Warning display.

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APU FIRE PROTECTION - SYSTEM WARNINGS (APU FIRE IN FLIGHT)

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26-13-00 APU FIRE PROTECTION: AUTOEXTINGUISHING GROUND TEST

CONTENTS:Auto Extinguishing Ground Test

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APU FIRE PROTECTION: AUTO EXTINGUISHING GROUND TEST

The test is performed from the maintenance panel.

CAUTION: This test has to be performed with the APUshutdown and the MASTER SWitch in the ONposition.

- Select AUTO EXTING TEST pushbutton.When the TEST pushbutton is pressed, the ON light andthe APU FIRE PUSH light come on.The squib circuit is isolated during the test.The FUEL LP/ISOL VALVE closes and the EMER SHUT DOWNcontrol relay is energized.After a time delay, the external horn sounds, the APUFIRE light on the external power receptacle panel andthe OK light on the TEST pushbutton come on.The illuminated OK light indicates the correct autoextinguishing relay operation.

- Select the RESET pushbutton.When the RESET pushbutton is pressed, the OK light,ON light, APU FIRE PUSH light and APU FIRE light gooff. The external horn stops.Three seconds after the reset, the automaticextinguishing circuit is recovered.

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APU FIRE PROTECTION: AUTO EXTINGUISHING GROUND TEST

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CONTENTS:System Operation in Case of APU Fire (ManualExtinguishing)

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APU FIRE PROTECTION

SYSTEM OPERATION IN CASE OF APU FIRE (ManualExtinguishing)

APU running in flight:When a fire is detected, the continuous repetitivechime sounds, the MASTER WARNING flashes and the APUFIRE pushbutton light on the APU FIRE panel comes on.- Select the APU FIRE pushbutton.When the APU FIRE pushbutton is released out, thecontinuous repetitive chime stops, the Fuel LowPressure Shutoff valve and the Fuel Solenoid valveclose and cause APU shutdown.The single Chime sounds, the MASTER CAUTION and theFAULT LIGHT on the APU MASTER switch pushbutton comeon. The SQUIB light comes on to indicate that the AGENTpushbutton can be used.The Electronic Control Box (ECB) controls the closureof the fuel valves.A ten seconds delay allows the airflow to reduce, thisincreases the agent effect.- Select the AGENT pushbutton .When AGENT pushbutton is pressed, the fire bottle isdischarged in the APU compartment and the DISCH lightcomes on.When the fire is extinguished, the MASTER WARNING andthe APU FIRE pushbutton lights go off.- Select APU MASTER SWITCH .When the APU MASTER SWITCH pushbutton is released out,the FAULT light goes off.

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APU FIRE PROTECTION - SYSTEM OPERATION IN CASE OF APU FIRE (Manual Extinguishing)

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CONTENTS:Auto Extinguishing on Ground

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APU FIRE PROTECTION

AUTO EXTINGUISHING ON GROUND

The aircraft is on ground, and the APU is runningwithout supervision:- When a fire is detected, the continuous repetitivechime sounds, the MASTER WARNING flashes and the APUFIRE pushbutton light on the APU FIRE panel comes on.The APU FIRE light on the EXTERNAL POWER panel comeson, the external horn sounds.The fuel low pressure shutoff valve and the fuelsolenoid valve close and the APU shuts down.The single chime sounds, THE MASTER CAUTION and theFAULT light on the APU MASTER SWITCH pushbutton comeon.Three seconds later, the APU fire bottle is dischargedautomatically and the DISCH light on the AGENTpushbutton comes on.- When the fire is extinguished, the MASTER WARNING.the APU FIRE pushbutton light on the APU FIRE paneland the APU FIRE light on the EXTERNAL POWER panel gooff, the external horn stops.Note that it is not necessary to use the APU SHUT OFFswitch on the EXTERNAL POWER panel in case of APU fireauto extinguishing.

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APU FIRE PROTECTION - AUTO EXTINGUISHING ON GROUND

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26-13-00 APU FIRE PROTECTION: PRECAUTIONS

CONTENTS:GeneralFire BottleDischarge Cartridge

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APU FIRE PROTECTION: PRECAUTIONS

GENERAL

Specific precautions must be taken during removal orinstallation of a fire extinguishing bottle and adischarge cartridge.

FIRE BOTTLE

WARNING: The fire bottle cartridges are explosive.Remove them before working on the bottle.Protective caps must be installed duringbottle removal/installation to preventdamage to discharge diaphragm which couldresult in injury to personnel.

DISCHARGE CARTRIDGE

WARNING: Before power is supplied to the aircraft makecertain that electrical circuits upon whichwork is in progress are isolated.

WARNING: Cartridges are class "C" explosives and mustbe handled or stored by authorized personnelor disposed of by an approved method.When cartdridge electrical connectors aredisconnected, the cartridge electrical pinsmust be shunted with a protective shunt whichis provided by the manufacturer. A shunt plugor shorting clip, will prevent bottledischarge which could cause injury tomaintenance personnel.The cartridge installed must be of the samemake as the fire bottle and correspond to thespecification indicated in the MaintenanceManual.

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26-13-00 APU FIRE PROTECTION: COMPONENTS

CONTENTS:Fire DetectorFire Detection Unit (FDU)Fire BottleRed Disc

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APU FIRE PROTECTION: COMPONENTS

SAFETY PRECAUTIONS

WARNING:

Cartridges are explosive, remove them before workingon the bottle. Protective caps must be installed duringbottle removal/installation to prevent damage to thedischarge diaphragm which could result in injury topersonnel.

Before power is spplied to the aircraft make certainthat electrical circuits upon which work is in progressare isolated.Discharge cartridges are class "c" explosives and mustbe handled/stored by authorized personnel or disposedof by an approved method.Wuen cartridge electrical connectors are disconnectedthe cartridge electrical pins must be shunted with aprotective shunt which is provided by the manufacturer.A shunt plug or shorting clip will prevent bottledischarge which could cause injury to maintenancepersonnel.The cartridge installed must be of the same make asthe bottle and correspond to the specificationindicated in the Maintenance Manual.

FIRE DETECTOR

IDENTIFICATIONFIN: 21WG, 22WG

LOCATIONZONE: 316

COMPONENT DESCRIPTIONOne per loop.The detector is pneumatically operated by heating itssensing element which contains helium gas and anhydrogen charged core material.

Alarm StateThe application of heat to the sensor causes anincrease of the gas pressure which in turn closes thealarm switch. The detector sends a FIRE signal.

Fault StateIn the event of gas pressure loss, the integrity switchopens and generates a fault signal.

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IDENTIFICATIONFIN: 13WG

LOCATIONZONE: 126

FIRE BOTTLE

IDENTIFICATIONFIN: 11WF

LOCATIONZONE: 314

COMPONENT DESCRIPTION- Type of agent: bromotrifluoromethane.- Nominal Nitrogen pressure at 21 deg.C: 600 psi.

Pressure SwitchThe pressure switch operates at 225 psi.An allen key can be inserted in the manual test pointin order to check the pressure.The pressure switch is calibrated at:

- 450 psi when the pressure increases(refilling).

- 225/275 psi when the pressure decreases(discharge or leak).

SquibThe squib is an electropyrotechnic cartridgecontaining explosive powder fired by two filamentssupplied with 28 VDC.

WARNING: Never check the continuity of the squib usinga conventional ohmmeter.

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RED DISC

Is blown out in case of thermal discharge.

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26-13-00 APU FIRE PROTECTION: ELECTRICALCIRCUITS

CONTENTS:DetectionExtinguishingAuto Extinguishing

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APU FIRE PROTECTION: ELECTRICAL CIRCUITS - DETECTION




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APU FIRE PROTECTION: ELECTRICAL CIRCUITS - EXTINGUISHING

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APU FIRE PROTECTION: ELECTRICAL CIRCUITS - APU FIRE PUSH

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APU FIRE PROTECTION: ELECTRICAL CIRCUITS - DISCH

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APU FIRE PROTECTION: ELECTRICAL CIRCUITS - AUTO EXTINGUISHING

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APU FIRE PROTECTION: ELECTRICAL CIRCUITS - FIRE DETECTION

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APU FIRE PROTECTION: ELECTRICAL CIRCUITS - TEST

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APU FIRE PROTECTION: ELECTRICAL CIRCUITS - RESET

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CONTENTS:Smoke DetectorAvionic Equipment Ventilation Computer (AEVC)Gen 1 Line P/BBlower and Extract P/BSelf Examination

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EFFECTIVITY 26-15-00 Page 1Mar 31/94



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SYSTEM PRESENTATION

SMOKE DETECTOR

The avionics compartment smoke detection is providedby a smoke detector installed on the air extractionduct of the avionics ventilation system. In case ofsmoke detection, the smoke detector sends signals tothe Flight Warning Computer, the local warnings andthe Avionics Equipment Ventilation Computer. The smokedetector is of the ionization type.

AVIONIC EQUIPMENT VENTILATION COMPUTER (AEVC)

The Avionic Equipment Ventilation Computer controlsthe avionics ventilation system, monitors the smokedetector condition, and allows the detector to betested by the Centralized Fault Display System. TheAvionics Equipment Ventilation Computer (AEVC) checksthe smoke detector when a test is initiated from theCentralized Fault Display Interface Unit (CFDIU).

GEN 1 LINE PUSHBUTTON

The smoke detector activates the GEN 1 LINE SMOKE lighton the EMER ELEC PWR panel.

BLOWER AND EXTRACT PUSHBUTTON

The smoke detector activates the BLOWER FAULT andEXTRACT FAULT lights on the ventilation panel.

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SYSTEM PRESENTATION

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SELF EXAMINATION

How can the avionics smoke detector be tested?A - Permanently by the AEVC.B - By a dedicated TEST pushbutton.C - By a manual test from the CFDS.

Which warning lights are triggered in case of anavionic smoke detection?

A - GEN 1 LINE SMOKE light.B - BLOWER FAULT.C - GEN 1 LINE SMOKE and BLOWER and EXTRACT

FAULT lights.

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26-15-00 AVIONICS SMOKE DETECTION:AVIONICS SMOKE PROCEDURE

CONTENTS:Master CautionOxygen MaskCabin and Cockpit IsolationSmoke Source IsolationEssential Electrical Network

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AVIONICS SMOKE DETECTION: AVIONICS SMOKE PROCEDURE

MASTER CAUTION

When a smoke is detected the MASTER CAUTION comes on,the single chime sounds, GEN 1 SMOKE light comes onon the emergency electrical power panel and the BLOWERfault and EXTRACT fault lights on the ventilation panelcome on.The actions to be performed appear on the upper ECAMdisplay.Note that the smoke is directly perceptible by thecrew through the center pedestal.

- Select the MASTER CAUTION before performingECAM actions.

OXYGEN MASK

As smoke is confirmed, use the OXYGEN MASKS andestablish crew communication.

- Select the OXYGEN MASK.

CABIN AND COCKPIT ISOLATION

CABIN FANSAvoid the use of interphone position to minimize theinterference from oxygen mask breathing noise.Stop the cabin fans to prevent smoke from enteringinto the cockpit and cabin.

- Set CAB FANS pushbutton to OFF.When it is set to off, the cabin FANS stop.

BLOWER FAN

The blower and extract fans of the avionics ventilationsystem must be set to the override position, toevacuate the smoke overboard.

- Set the BLOWER pushbutton to OVRD position.When the BLOWER pushbutton is set to override, theblower fan stops and the air conditioning system isused as a cold air source.

EXTRACT FAN- Set the EXTRACT pushbutton to OVRD position.

EXTRACT VALVEWhen the EXTRACT pushbutton is set to override, theair is extracted overboard through the extract valvewhich is partially open. The extract fan continues torun.

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AVIONICS SMOKE DETECTION: AVIONICS SMOKE PROCEDUREMASTER CAUTION - OXYGEN MASK - CABIN AND COCKPIT ISOLATION




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SMOKE SOURCE ISOLATION

GENERATOR 1As smoke is still perceptible, it is necessary to acton the electrical system. The following actions allowthe normal electrical network to be shed to isolatethe smoke source.

- Set GEN 1 LINE pushbutton to OFF position.

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AVIONICS SMOKE DETECTION: AVIONICS SMOKE PROCEDURESMOKE SOURCE ISOLATION

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RAM AIR TURBINEAction on the GEN 1 LINE pushbutton opens the generator1 line contactor. Generator 1 continues to supply onefuel pump on each wing tank, and the galleys are shed.AC BUS 1 is supplied by generator 2 through the bustie contactor.

- Select the MAN ON pushbutton to extend theRam Air Turbine.

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AVIONICS SMOKE DETECTION: AVIONICS SMOKE PROCEDURESMOKE SOURCE ISOLATIONT M

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ESSENTIAL ELECTRICAL NETWORK

SUPPLYThe Ram Air Turbine is now extended and the emergencygenerator is connected to keep the aircraft essentialelectrical network supplied.Notice that the emergency generator parameters aredisplayed on the ECAM.

GENERATOR 2With the emergency generator running, the engine 2 andAPU generators have to be switched off in order toisolate the normal electrical network. Enginegenerator 1 must be kept running for fuel pumpoperation.

- Set GEN 2 pushbutton to OFF.

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AVIONICS SMOKE DETECTION: AVIONICS SMOKE PROCEDURESMOKE SOURCE ISOLATIONT M

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EMERGENCY CONFIGURATIONAs both engine generators have been disconnected, theelectrical system is now in emergency configurationand the lower ECAM display is no longer supplied.Land as soon as possible observing the emergencyprocedure.The avionics smoke procedure has now been completed.

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26 FIRE PROTECTIONMECHANICS / ELECTRICS & AVION

26-fire

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