a380-level ii - ata 26 fire protection systems

A380TECHNICAL TRAINING MANUAL

MAINTENANCE COURSE - T1 & T2 (RR / Metric)LEVEL II - ATA 26 Fire Protection Systems

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

All rights reservedNo 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 S.A.S.

LEVEL II - ATA 26 FIRE PROTECTION SYSTEMSFire Protection SystemFire Protection System Description (2) . . . . . . . . . . . . . . . . . . . . . . . . 2Fire Protection System Operation, Control & Indicating (2) . . . . . . 14Smoke Detection SystemCargo Smoke Detection & Fire Extinguishing Description (2) . . . . 24Avionics & In-Flight Entertainment Compartment Smoke Detection

System Description (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28Lavatories Smoke Detection Description (2) . . . . . . . . . . . . . . . . . . 30Smoke Detection Systems Operation, Control & Indicating (2) . . . . 34


TABLE OF CONTENTS Mar 21, 2006Page 1

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FIRE PROTECTION SYSTEM DESCRIPTION (2)Engine Fire Detection

General PresentationThe technology of the Fire Detectors is electro-pneumatic. Each FireDetector is made of sensing element and responder assembly. Theresponder assembly sends detection signal to the Fire Detection Unit(FDU). Two independent loops (LOOP A and LOOP B) are installedin each fire zone.The FDU via the Conversion Module (CM) warns the crew throughFlight Warning System (FWS) and Engine/Fire Integrated ControlPanel (ICP).In normal mode, when fire detection is confirmed by the FDU, thefollowing fire warnings are triggered on:- the ENGine/FIRE ICP,- the ENG MASTER Control Panel,- the MASTER WARN lights located on the glareshield panel,- the EWD and the SD,These visual warnings are related to aural warnings (constant repetitivechime).A Bite function monitors the condition of the FDU, of the CM andtheir associated inputs. The BITE function analyses, confirms thefaults and stores them.

Fire And Fault IndicationsAn operational test on engines, APU and L/G bay can be done in flightor on ground, controlled by the TEST P/B on Engine/Fire ICP throughthe single FDU.In case of engine fire, visual messages appear on:- the ENG MASTER panel with a red FIRE indication on the dedicatedengine,- the ENG/FIRE ICP with a red FIRE indication on the dedicatedengine,- the MASTER WARNINGS,

- the ECAM.Aural warnings sound through the loudspeakers.In case of engine fire on ground, the action is as follows:- the THRust levers must be on IDLE position,- the PaRKing BRaKe must be on the ON position,- all the ENG MASTER panel switches must be OFF,- the FIRE P/Bs have to be pushed to be released,- the AGENT P/Bs 1 and 2 can be pushed to discharge.In addition, a failure message is transmitted to the Central MaintenanceSystem (CMS).


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ENGINE FIRE DETECTION - GENERAL PRESENTATION & FIRE AND FAULT INDICATIONS




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FIRE PROTECTION SYSTEM DESCRIPTION (2)Engine Fire Extinguishing

System DescriptionThe system has two main functions:- extinguish any fire in the protected zones of the nacelle as soon aspossible. A fire can be due to excessive overheat or flammable fluidleaks and can endanger the A/C safety,- prevent engine fire extension: the engine is isolated from the rest ofthe A/C.The engine fire extinguishing system is a High Rate Discharge system.This includes the systems based on a rapid discharge (around 1 sec.)of an extinguishing agent pressurized in a vessel.The extinguishing agent is the Halon 1301.The fire extinguishing system includes for each engine:- one ENG/FIRE P/BSW installed on the ENG/FIRE ICP,- two SQUIB/DISCH (AGENT 1 and AGENT 2) P/BSWs located onthe same panel,- two fire extinguisher bottles which are made up of a sphericalcontainer, a discharge head, a cartridge, and a TemperatureCompensated Pressure Switch,- extinguishing lines routed in the pylon and leading to the nacelle.




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ENGINE FIRE EXTINGUISHING - SYSTEM DESCRIPTION




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FIRE PROTECTION SYSTEM DESCRIPTION (2)Engine Fire Extinguishing (continued)

Activating the ExtinguisherEach SQUIB/DISCHARGE (AGENT 1 and AGENT 2) P/BSW agreesrespectively with the fire extinguisher bottle 1 and bottle 2.By acting on the ENG/FIRE P/BSW, the cartridge firing system isarmed. The SQUIB legend (white) comes on after this action.The DISCH legend (amber) comes on when the TemperatureCompensated Pressure Switch installed on the fire extinguisher bottletransmits a low-pressure signal (via FDU), which indicates thedischarge or a leakage of the fire extinguisher bottle.Human factor point:

WARNING: BAT BUS CONTINUALLY SUPPLIES THEEXTINGUISHING SYSTEM, SO THE SQUIB P/BMUST BE PUSHED ONLY IN CASE OF FIRE.




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ENGINE FIRE EXTINGUISHING - ACTIVATING THE EXTINGUISHER




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FIRE PROTECTION SYSTEM DESCRIPTION (2)APU Fire Protection

The fire protection system includes:- the fire detection sub-system,- the monitoring of fire extinguishing system,- on ground the APU automatic fire extinguishing control.The fire extinguishing system includes for each engine:- one APU/FIRE P/BSW installed on the APU/FIRE ICP,- one SQUIB/DISCH P/BSW installed on the same panel,- one fire extinguisher bottle which is made of a spherical container, adischarge head and a cartridge,The fire detectors are installed in the APU compartment and have a singleshot fire-extinguishing system. The CM is installed in a pressurized areafor the APU compartment. When the temperature in the monitored zonereaches the defined threshold, the detector triggers warning sequence.The FDU via the CM collects then all detector value. The FDU warnsthe crew through the FWS and on the APU/FIRE ICP.The technology of the Fire detector is Electro-pneumatic. Each firedetector is made of sensing element and responder assembly.An electrically operated squib, installed on the bottle, is armed from theAPU/FIRE ICP through the AGENT P/BSW for the discharge.Two independent loops (LOOP A and LOOP B) are installed in each firezone. These loops are completly segregated.If overheat is detected in flight, visual messages appear on:- the APU/FIRE ICP with red FIRE indication,- the MASTER WARNINGS through the FWS,- the ECAM through the FWS.Aural warnings sound through the loudspeakers.A message is also sent to the CMS.By acting on the APU/FIRE P/BSW, the cartridge firing system is armed.On the SQUIB/DISCH P/BSW (on the APU/FIRE Integrated ControlPanel), the SQUIB legend (white) comes on after this action.

The DISCH legend (amber) comes on when the TemperatureCompensated Pressure Switch installed on the fire extinguisher bottletransmits a low-pressure signal (via FDU), which indicates the dischargeor a leakage of the fire extinguisher bottle.In case of fire on ground, the procedure is the same except that the bottlesare automatically triggered through the FDU and the APU/FIRE lightcomes then on. An operational test can be performed in flight or on theground via TEST P/B on ENGINE/FIRE ICP.The BITE test is done at power up or when the CMS requests the test.This test can be done only on ground. Engine, APU and Main LandingGear (MLG) bays fire detection are tested.Human factor point:

WARNING: BAT BUS CONTINUALLY SUPPLIES THEEXTINGUISHING SYSTEM, SO THE SQUIB P/B MUSTBE PUSHED ONLY IN CASE OF FIRE.




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APU FIRE PROTECTION




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FIRE PROTECTION SYSTEM DESCRIPTION (2)Landing Gear Fire Protection

Four zones are protected for the Landing Gear System:- the right Wing Landing Gear (WLG) bay,- the left WLG bay,- the Body Landing Gear (BLG) bay (RH side),- the BLG bay (LH side).Each L/G compartment has two fire detectors.The L/G fire protection system uses the dual loop (LOOP A and LOOPB) principle in each L/G bay.The loops are connected in parallel and operate according to an ANDlogic.If overheat is detected, FDU sends signal to the FWS:- for horn master warning,- for visual MASTER CAUTION message on the MASTER WARNINGS,- for message on the ECAM.A message is also sent to the CMS.An operational test can be done in flight or on ground controlled by thetest P/B on the ENGINE/FIRE ICP.




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LANDING GEAR FIRE PROTECTION




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FIRE PROTECTION SYSTEM DESCRIPTION (2)Power Supply

Each FDU and CM has its own power supply. The channels A of the CMare supplied by the 28VDC (ESS BUS). The channels B of the CM aresupplied by the 28VDC (DC BUS 2) through Solid State Power Controller(SSPC).The SQUIB 1 and the SQUIB 2 of the bottles are respectively suppliedby the 28VDC (HOT BUS) and the 28VDC (ESS BUS).The AGENT P/Bs are supplied by the 28VDC (HOT BUS and ESS BUS).




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POWER SUPPLY




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FIRE PROTECTION SYSTEM OPERATION, CONTROL & INDICATING (2)General


FIRE PROTECTION SYSTEM OPERATION, CONTROL &INDICATING (2)

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GENERAL



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FIRE PROTECTION SYSTEM OPERATION, CONTROL & INDICATING (2)ENG FIRE Warning and Action



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ENG FIRE WARNING AND ACTION



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FIRE PROTECTION SYSTEM OPERATION, CONTROL & INDICATING (2)APU FIRE Warning and Action



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APU FIRE WARNING AND ACTION



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FIRE PROTECTION SYSTEM OPERATION, CONTROL & INDICATING (2)MLG FIRE Warning



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MLG FIRE WARNING



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FIRE PROTECTION SYSTEM OPERATION, CONTROL & INDICATING (2)Fire Warning Test



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FIRE WARNING TEST



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CARGO SMOKE DETECTION & FIRE EXTINGUISHING DESCRIPTION (2)Power Supply

The cargo smoke detection and fire extinguishing system has:- a cargo smoke panel on cockpit panel to activate and control the FireExtinguishing System via Cabin Intercommunication Data System (CIDS),- two Fire Extinguishing Data Converters to monitor and ignite the squib,- three fire extinguishing bottles to store the fire-extinguishing agentHalon 1301,- four extinguishing nozzles in the FWD and five extinguishing nozzlesin the AFT/BULK cargo compartments to supply the fire extinguishingagent,- one flow metering equipment downstream of the second and third bottleon a support to regulate the outflow of the bottles, and to maintain theminimal extinguishing agent concentration over the required suppressiontime,- one diverter valve to direct the Halon 1301 via piping system to theFWD or AFT/BULK cargo compartment.28VDC NORMal BUS and 28VDC ESSential BUS supply the FireExtinguishing Data Converter 1. 28VDC NORM BUS and 28VDCNORM BUS 2 supply the Fire Extinguishing Data Converter 2. If theA/C electrical PoWeR is the only EXTernal PWR AVAILable, the FireExtinguishing Data Converters are supplied by the 28VDC GrouND ESSBUS.


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POWER SUPPLY



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CARGO SMOKE DETECTION & FIRE EXTINGUISHING DESCRIPTION (2)Test Functions

In case of cargo smoke detection, the cargo smoke detectors send adiscrete signal to the CIDS-Smoke Detection Function (SDF). TheCIDS-SDF transmits alarm and fault indications to the Flight WarningSystem (FWS) and data to the Central Maintenance System (CMS)through AFDX Bus.The FWS provides the visual and acoustical alarms and fault indicationson:

- The EWD of the ECAM,- The Master Warning P/BSWs,- The loudspeakers.On the Cargo Smoke Panel:- a detected smoke in FWD (or AFT/BULK) Cargo compartment is shownby a red colored legend SMOKE on the AGENT TO FWD (or AGENTTO AFT) P/BSWs,- a squib fault is shown by the DISCH indication,- a low pressure in one of the three fire extinguishing bottles is shownby a white colored legend BTL1, BTL2 or BTL3,By operating the P/BSWs 'AGENT TO FWD' and 'AGENT TO AFT',fire the squibs of the FWD cartridges of the diverter valve.The smoke detection system offers two means of in-situ functional testing:- the Push To Test (PTT),- the Onboard Maintenance System (OMS).A Push To Test (PTT) P/BSW is provided on the cargo smoke panel tolet the flight crew check the capability of the system to discharge in caseof a fire event. The PTT is available during all flight phases and, whenactivated, it places all compartments falling under the categorynon-customized (lower deck cargo compartments, main avionicscompartment, emergency avionics compartment, In-Flight EntertainmentCenter (IFEC), additional electronics compartment) and inaccessible byalarm condition. The active CIDS-SDF channel does the test as long asthe PTT is commanded (however at least for 5 sec.). Smoke detection is

not available in the respective compartments while in test condition. Thecartridges inclusive associated wiring is checked either automatically(every 30 min.) or on flight crew request by the PTT. This is not acomplete test of all wires necessary for firing the squibs. The doublesquib fault is indicated in the cockpit on the ECAM and on the cargosmoke panel, or by PTT request. The faults including the fault of onesquib are transmitted to the CMS.While in interactive mode, the On-board Maintenance Terminal (OMT)allows smoke alarm testing of all compartments, and complete systemcondition testing. The system test does a system-wide check includingall redundancies. Like the PTT condition, the active CIDS-SDF channeldoes the Smoke Warn Test. Since single compartments are selectivelytested at a time, a smoke detection is available in all other compartmentsnot under test. The test is carried out continuously until manuallycancelled or interactive mode is no longer available.



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TEST FUNCTIONS



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AVIONICS & IN-FLIGHT ENTERTAINMENT COMPARTMENT SMOKE DETECTION SYSTEMDESCRIPTION (2)Detection Function

Pairs of duct-type smoke detectors carry out the smoke detection function.They are installed in the air extraction ducts ventilating the clusters ofavionics racks. Each smoke detector relies on ducted air to continuouslytransport combustion particles into the housing.The smoke detectors monitor the air extracted from:- the main avionics compartment,- the emergency avionics compartment,- the In-Flight Entertainment Center (IFEC),- the rear avionics compartment (optional).The main system controller is the Cabin Intercommunication Data System(CIDS) - Smoke Detection Functions (SDFs), located in the CIDSdirectors, which manage the smoke detection function.Two segregated Controller Area Network (CAN) buses (C and D) allowthe communication between the CIDS-SDF and the smoke detectors inthe main avionics compartment, the emergency avionics compartmentand the IFEC. Two other segregated CAN buses (A and B) allow thecommunication with the smoke detectors in the rear avionics compartment(optional).The smoke detectors are supplied with 28 VDC from the DC NORMalBUS 2 or DC ESSential BUS.In case of smoke detected by one smoke detector, a smoke signal is sentto the CIDS-SDF. If smoke is detected by both smoke detectors at thesame location, an alarm status is generated; the CIDS-SDF sends a smokewarning to the Flight Warning Computer (FWC) via the Avionics FullDuplex Switched Ethernet (AFDX) network.Test Function

The smoke detection system can be tested via:- the TEST P/B on the CARGO SMOKE overhead panel,

- the Onboard Maintenance Terminal (OMT).The operational test is triggered from the TEST P/B. This allows amomentary check of the complete chain from the smoke detector, overthe CIDS-SDF to the indication system generated by the Flight WarningSystem (FWS) on loudspeakers and Integrated Cockpit Panels (ICPs):- AVioNiCS SMOKE P/B on the VENTilation control panel,- PAX SYStem P/BSW on the Flight/ConTroL panel.This test is available during all flight phases. When the test is in progress,smoke detection function is not available in the related compartmentsunder test.When the OMT is in interactive mode and ground condition fulfilled, aselective test of smoke alarms in the different compartments and theperformance of a complete system test can be done. As each compartmentcan be selectively tested, smoke detection function still available in allother compartments not under test. The test is carried out either from theTEST P/B or from the OMT; but the smoke warning tests are alwaysdone by the active CIDS-SDF only.


AVIONICS & IN-FLIGHT ENTERTAINMENT COMPARTMENTSMOKE DETECTION SYSTEM DESCRIPTION (2)

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DETECTION FUNCTION & TEST FUNCTION


AVIONICS & IN-FLIGHT ENTERTAINMENT COMPARTMENTSMOKE DETECTION SYSTEM DESCRIPTION (2)

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LAVATORIES SMOKE DETECTION DESCRIPTION (2)Electrical Power

The Smoke Detection System is based on a controller-sensor architecture.The main system controller is installed in the Cabin IntercommunicationData System (CIDS) Director. The smoke detection control function isdone by the CIDS-Smoke Detection Function (SDF).The CIDS-SDF is powered by the 28VDC NORMal DC BUS 2 and the28VDC ESSential BUS.Each lavatory is a separate compartment from a fire protection point ofview. A single ambient smoke detector is installed in the lavatory ceilingadjacent to the air extraction. The smoke detector is connected to aDecoder/Encoder Unit (DEU)-B in the vicinity of the lavatory. TheDEU-B is supplied with the 28VDC NORM DC BUS 2 and the 28VDCESS BUS.In case of lavatory smoke alert, lavatory smoke detection alarm and faultsignals are shown on the Flight Attendant Panel (FAP) and mini-FAP(optional). The CIDS-SDF sends also a smoke alert that generates visualand acoustical cockpit warnings.


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ELECTRICAL POWER




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LAVATORIES SMOKE DETECTION DESCRIPTION (2)Test Functions

In case of lavatory smoke alert, a SMOKE DETECTION page appearson the FAP as a synoptic graphic and a red icon is displayed at the affectedlocation.Simultaneous, the CIDS-SDF sends smoke alerts to the Flight WarningComputer (FWC) that generates:- a warning message on the Engine/Warning Display (EWD) of theECAM,- a red MASTER WARNINGS,- a repetitive chime.In the cabin, a smoke alert from the lavatory triggers the respective AreaCall Panel (ACP) and an amber light comes on. The related message isshown on all Attendant Indication Panels (AIP). Also the respective calllight comes on in the flashing mode.The SMOKE P/B RESET of the Additional Attendant Panel (AAP) canbe activated to silence the chime and to reset all visual warnings on theACPs, the AIPs, and the outside wall-mounted smoke/PAX call indicatorof the affected lavatory.The CIDS director transmits a signal to the DEU-A, which activates atriple low chime sequence emitted through the loudspeaker in the cabin.Maintenance data and specific tests are done by the Onboard MaintenanceSystem (OMS) through an Onboard Maintenance Terminal (OMT). TheOMT allows smoke alarm testing of all compartments, and completesystem condition testing. The system test does a system-wide checkincluding all redundancies. The smoke warn test is done by the activeCIDS-SDF channel.




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TEST FUNCTIONS




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SMOKE DETECTION SYSTEMS OPERATION, CONTROL & INDICATING (2)General


SMOKE DETECTION SYSTEMS OPERATION, CONTROL &INDICATING (2)

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GENERAL



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SMOKE DETECTION SYSTEMS OPERATION, CONTROL & INDICATING (2)Cargo Bay Smoke Warning



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CARGO BAY SMOKE WARNING



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SMOKE DETECTION SYSTEMS OPERATION, CONTROL & INDICATING (2)Avionics Compartment Smoke Warning



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SMOKE DETECTION SYSTEMS OPERATION, CONTROL & INDICATING (2)IFE Bay Smoke Warning



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IFE BAY SMOKE WARNING



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SMOKE DETECTION SYSTEMS OPERATION, CONTROL & INDICATING (2)Smoke Warning Test by PTT for Non-Customized Areas



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SMOKE WARNING TEST BY PTT FOR NON-CUSTOMIZED AREAS



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SMOKE DETECTION SYSTEMS OPERATION, CONTROL & INDICATING (2)Crew Rest Smoke Warning



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CREW REST SMOKE WARNING



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SMOKE DETECTION SYSTEMS OPERATION, CONTROL & INDICATING (2)Lavatory Smoke Warning



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LAVATORY SMOKE WARNING



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AIRBUS S.A.S.31707 BLAGNAC cedex, FRANCE

STMREFERENCE L0Y06082

MARCH 2006PRINTED IN FRANCEAIRBUS S.A.S. 2006

ALL RIGHTS RESERVED

AN EADS JOINT COMPANYWITH BAE SYSTEMS

Table of ContentsFire Protection SystemFire Protection System Description (2)Engine Fire DetectionGeneral PresentationFire And Fault Indications

Engine Fire ExtinguishingSystem DescriptionActivating the Extinguisher

APU Fire ProtectionLanding Gear Fire ProtectionPower Supply

Fire Protection System Operation, Control & Indicating (2)GeneralENG FIRE Warning and ActionAPU FIRE Warning and ActionMLG FIRE WarningFire Warning Test

Smoke Detection SystemCargo Smoke Detection & Fire Extinguishing Description (2)Power SupplyTest Functions

Avionics & In-Flight Entertainment Compartment Smoke Detection System Description (2)Detection FunctionTest Function

Lavatories Smoke Detection Description (2)Electrical PowerTest Functions

Smoke Detection Systems Operation, Control & Indicating (2)GeneralCargo Bay Smoke WarningAvionics Compartment Smoke WarningIFE Bay Smoke WarningSmoke Warning Test by PTT for Non-Customized AreasCrew Rest Smoke WarningLavatory Smoke Warning

a380-level ii - ata 26 fire protection systems

Documents

protection system operation

master warnings

detection signal

detection unitfdu

extinguishing description

retrieval system

eng master control panel

visual warnings