chapter 9: fire protection table of contents

For Training Purposes OnlySept 04

9-i

P I L O T T R A I N I N G G U I D E

FIRE PROTECTION

Chapter 9: Fire Protection

TABLE OF CONTENTS

Page

Introduction .........................................................................................................................9-1Flight Compartment Fire Warning .................................................................................9-2Fire Detecting System...................................................................................................9-2Main Wheel Well Overheat Warning .............................................................................9-2Fire Agent Discharge Indication ....................................................................................9-2Smoke Detection...........................................................................................................9-2Portable Fire Extinguishers ...........................................................................................9-2

Description ..........................................................................................................................9-3System Overview Schematic ........................................................................................9-3FIDEEX Control Unit .....................................................................................................9-4Main Engine Fire Detection...........................................................................................9-5

Engine FIDEEX Control Schematic.........................................................................9-6APU Compartment Fire Detection.................................................................................9-7

APU FIDEEX Control Schematic ............................................................................9-8Main Wheel Well (MWW) Overheat Detection ..............................................................9-9Smoke Detection.........................................................................................................9-10Fire Handles................................................................................................................9-12Engine Fire..................................................................................................................9-13APU Fire......................................................................................................................9-14Shutoff Valves (SOV) ..................................................................................................9-15Fire Extinguisher Assembly.........................................................................................9-16

Fire Extinguisher Discharge Bottles ......................................................................9-16Fire Extinguisher Gauges......................................................................................9-17Main Engine Fire Extinguishing.............................................................................9-18APU Compartment Fire Extinguishing ..................................................................9-20APU FIDEEX/FADEC Interface.............................................................................9-20

Pilot-Initiated Test .......................................................................................................9-21EICAS Messages ........................................................................................................9-23EMS Circuit Protection ................................................................................................9-26

9-ii For Training Purposes OnlySept 04


FIRE PROTECTION

PAGE INTENTIONALLY LEFT BLANK


9-1


FIRE PROTECTION

INTRODUCTIONA Fire Detection and Extinguishing (FIDEEX) system with fault discrimination is installed with fire detectors located in each engine nacelle, and in the APU compartment.

The FIDEEX system interfaces with numerous airplane equipment and provides the following capabilities:

• Monitor zones for fire/overheat/smoke events and FIDEEX system health and status

• Automatic detection and reporting of fire events for each of the two power plants and the Auxiliary Power Unit (APU)

• Fire extinguishing for each of the power plants and APU upon receipt of pilot initiated arming and discharging commands

• Automatic detection and reporting of overheat events for the two Main Wheel Wells (MWWs)

• Automatic detection and reporting of smoke events for each of the lavatories (fwd/aft), baggage compartment, avionics bay, and up to four cabin closets (requires installation of optional smoke detectors)

The FIDEEX system includes fire detector assemblies, sensing elements, smoke detectors (optional), fire extinguishing assemblies, and a FIDEEX control unit.

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Lavatory SmokeDetection

AFTLavatory

AFT ClosetOptional

Power Plant FireDetection/Extinguishing

Forward Left and RightCloset (optional smokedetection)

Main Landing GearOverheat Detection

APU Fire Detection/Extinguishing System

Baggage CompartmentSmoke Detection

9-2 For Training Purposes OnlySept 04


FIRE PROTECTION

FLIGHT COMPARTMENT FIRE WARNINGThe fire protection system provides the means to detect and extinguish a fire in the engine nacelles and in the auxiliary power unit (APU) compartment. Engine/APU fire warning is provided by:

• MASTER warning lights (2)• Aural warning• EICAS messages• Three red warning lights (one for each engine nacelle, and one for the APU

compartment), installed in the flight compartment fire handles

Both the detection systems and extinguishing systems permit testing and/or monitoring for system faults from the flight compartment. A fire warning and extinguisher preflight test of the system is provided in the flight compartment.

FIRE DETECTING SYSTEMFire detection elements are installed in each engine and APU compartment, permitting the flight crew to monitor any fire condition in these areas.

MAIN WHEEL WELL OVERHEAT WARNINGAn overheat detection element in the wheel well area warns of an overheat condition in either of the main wheel wells. Indication and test function is provided in the flight compartment.

FIRE AGENT DISCHARGE INDICATIONThe fire extinguisher bottle is fitted with a low pressure switch. The switch provides an annunciation in the flight compartment when pressure drops below a predetermined pressure setting.

SMOKE DETECTIONThe FIDEEX system can provide smoke detection capability for the baggage compartment, forward and aft lavatories, avionics bay, and up to four cabin closets.

PORTABLE FIRE EXTINGUISHERSPortable fire extinguishers are located throughout the airplane. One halon type fire extinguisher is installed in the flight crew compartment. Please refer to the EMERGENCY EQUIPMENT chapter for more information on the portable fire extinguishers.


9-3


FIRE PROTECTION

DESCRIPTION

SYSTEM OVERVIEW SCHEMATIC

DISCH

PULL

1 2

LPULL

APU

DISCH

1 2

DISCH

1 2

RPULL

8

6 7

10

9

4

3

2

1

5

FIDEEXControl Unit

DAU

IAC

LH MLG Bay RH MLG Bay

LH ENGINE RH ENGINEAPU COMPARTMENT

1

2

3

4

5

6

7

8

9

10

Fire Handles

Master WARNING/CAUTIONLIGHTS

EICAS Page displaysWarnings, Cautions, Advisoryand Status Messages

Left Main Wheel WellOverheat Detection

Right Main Wheel WellOverheat Detection

Fire ExtinguisherBottle No.1

Fire ExtinguisherBottle No.2

Left EngineCompartmentDischarge Lines

Right EngineCompartmentDischarge Lines

APU CompartmentDischarge Lines

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MASTERWARNING/CAUTION

ROLL SPLRS

PLT CONT

ROLLSEL

PLTROLL

WARNING

CAUTION

DIMOFF

BRT

HUD


ROLL SPLRS

CPLT CONT

ROLLSEL

CPLTROLL

WARNING

CAUTION

TOTAL FUEL (LBS) 4155O

1.54

146OO 146OO1OOOO

N2

FF (PPH)

OIL TEMP

OIL PRESS

93.4575O11581

1.65

CRZEPR

IGN

START START

IGN

NDSTAB

1.54

1.65

73.3

T/ON1SYNC

73.3

789

ITTSYNC

789 DN DN DN

OUT

3O

GEAR

–TRIMS–

NL NRRUDDER

AIL

RWDLWD

7.2

NU

93.4575O11581

235O



FIRE PROTECTION

FIDEEX CONTROL UNITAll interfaces from the airplane’s power and fire handles pass through the FIDEEX control unit before they reach the fire extinguishers. The FIDEEX control unit is located under the baggage compartment floor. The following functions/components are monitored continuously:

• Continuity of the squib circuits• Continuity of the pressure switches• Existence of 28 VDC on the two fire extinguishing power supply lines

The FIDEEX control unit is divided into two redundant channels (A and B). The channels power and monitor both loops of the main engines and APU, and each of the MWW loops. Both channels independently determine the presence of a fire or overheat condition. The FIDEEX control unit performs internal and operator initiated built-in tests, and reports all health and status to the flight compartment EICAS system.

R ENGINE SQUIB 2

APU SQUIB 2

L ENGINE SQUIB 2

PRESSURE SWITCH

R ENGINE SQUIB 1

APU SQUIB 1

L ENGINE SQUIB 1

PRESSURE SWITCH

A B

MAIN WHEEL WELLS

LEFT ENGINE APU RIGHT ENGINE

FIDEEX CONTROL UNIT

Pressure Gaugeand Switch

DISCHARGECHECK VALVES

TO RIGHT ENGINE

TO APU

TO LEFT ENGINE

BOTTLE #1 BOTTLE #2

Fire LoopUnit

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9-5


FIRE PROTECTION

MAIN ENGINE FIRE DETECTIONMain engine fire detection is provided by a dual loop system. Each loop (loop A and loop B) consists of three sensing elements, located on the accessory gear box, under the engine core, and along the fixed cowl. In order for a fire to be detected, at least one sensing element from each loop must detect the fire. When both loops indicate a fire condition, the FIDEEX will forward that information to the DAUs and the IACs (should one loop develop a short, the FIDEEX isolates that loop and now relies on the remaining loop for the detection of a fire).

The DAUs and IACs will illuminate the applicable engine fire DISCH handle, flash the master WARNING lights, generate a warning message on EICAS and a FIRE indication on the applicable ITT gauge, and generate a LEFT or RIGHT ENGINE FIRE voice message.

Sensing elements are located on the following areas:

• Accessory gear box• Engine core• Fixed cowl

Fixed Cowl MountedFire Detector and

Support Rail

Gear Box MountedFire Detector and

Support Rail(wire is hidden from view)

Core EngineFire Detector

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FIRE PROTECTION

ENGINE FIDEEX CONTROL SCHEMATIC

The engine fire loop elements send their information to the FIDEEX control unit. The FIDEEX control unit in turn sends information to the DAU. In the event of a fire, the DAU will signal the applicable engine fire DISCH handle to illuminate. The DAU reports the status of the detection system to the IAC which provides warning conditions to the EICAS, and audio control panel.

FIXED COWLMOUNTED FIREDETECT

GEARBOX MOUNTEDFIRE DETECT

CORE ENGINE FIREDETECTOR SENSOR

L ENGINEFIRE

HANDLE

“RIGHT ENGINE FIRE”“LEFT ENGINE FIRE"

AUDIOCONTROL

PANEL

IAC

EICAS

R ENGINEFIRE

HANDLE

DAU

FIDEEX CONTROLUNIT

LEFT ENGINE

FIXED COWLMOUNTED FIREDETECT

GEARBOX MOUNTEDFIRE DETECT

CORE ENGINE FIREDETECTOR SENSOR

LEFT ENGINELOOP A

L ENGINE FIRE

LEFT ENGINELOOP B

RIGHT ENGINELOOP A

R ENGINE FIRE

RIGHT ENGINELOOP B

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RIGHT ENGINE


9-7


FIRE PROTECTION

APU COMPARTMENT FIRE DETECTIONAPU fire detection is also provided by a dual loop system. Each loop (loop A and loop B) consists of three sensing elements, located on the APU Eductor, on the right APU Compartment hatch, and along a strut supporting the APU. In order for a fire to be detected, at least one sensing element from each loop must detect the fire. When both loops indicate a fire condition, the FIDEEX will forward that information to the DAUs and the IACs (should one loop develop a short, the FIDEEX isolates that loop and now relies on the remaining loop for the detection of a fire).

The DAUs and IACs will illuminate the APU fire DISCH handle, flash the master WARNING lights, generate an APU FIRE warning message on EICAS, and generate an APU FIRE voice message.

Dual LoopSensingElement

StrutSensingElement

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FIRE PROTECTION

APU FIDEEX CONTROL SCHEMATIC

The APU fire loop elements send their information to the FIDEEX control unit. The FIDEEX control unit in turn sends information to the DAU. The DAU reports the status of the detection system to the IAC which signal the EICAS, and audio control panel of the warning condition.

When a fire is detected, the APU fire warning handle will illuminate, master WARNING lights will illuminate, a warning message will appear on EICAS, and a voice message APU FIRE will sound.

“APU FIRE”

IAC

EICAS

APUFIRE

HANDLE

DAU

HATCH SENSING ELEMENTS

EDUCTOR SENSINGELEMENTS

STRUT SENSING ELEMENTS

APU COMPARTMENT

APU LOOP A

APU FIRE

APU LOOP B

FIDEEX CONTROLUNIT

AUDIOCONTROL

PANEL

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9-9


FIRE PROTECTION

MAIN WHEEL WELL (MWW) OVERHEAT DETECTIONThe main landing gear bays can be subjected to overheat conditions due to brake/tire overheat, or fire. The MWW overheat detection is provided by a single loop system for each main wheel well (left and right); each loop consists of one sensing element. The sensing elements are mounted in the vicinity of the brakes on the top surface of each MWW bin.

The FIDEEX control unit continuously monitors the heat sensing elements in the main landing gear area. Any overheat condition or system fault detected by the monitoring system is annunciated on EICAS in the form of a main landing gear bay overheat warning message, overheat fail caution message, or main landing gear bay overheat fault. The gear bay overheat warning message will be accompanied by an aural warning.

The FIDEEX control unit receives signals from the MWW sensing elements, and in turn sends information to the DAU. The DAU reports the status of the detection system to the IAC which signal the EICAS and audio control panel for warning conditions.

OverheatDetector

“GEAR BAY OVERHEAT”

LEFT MLGLOOP

RIGHT MLGLOOP

AUDIOCONTROL

PANEL

IAC

EICAS

DAU

MAIN LANDING GEAR (MLG)SENSING ELEMENTS

MAIN LANDING GEAR (MLG)SENSING ELEMENTS

FIDEEX CONTROLUNIT

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FIRE PROTECTION

SMOKE DETECTIONThe following smoke detectors are installed on the “green” configuration of the (Global Express) aircraft:

• Forward avionics bay• Aft avionics bay• Baggage compartment (but not functionally connected)

The following smoke detectors are installed on the “green” configuration of the (Global 5000) aircraft:

• Forward avionics bay• Aft avionics bay• Avionics rack• Baggage compartment (but not functionally connected)

The smoke detectors installed in the lavatories, cabin and closets are installed by the completion center(s). Also, the completion center(s) is/are responsible for functionally connecting the baggage compartment smoke detectors once the interior has been installed.

The FIDEEX control unit and the avionics system have built-in provisions for the smoke detectors for the baggage compartment, lavatories, avionics bay, and cabin closets. The smoke detectors are checked during power-up and during pilot initiated test. The flight deck activates the following warning devices:

• Flashing master WARNING lights (glareshield)• Appropriate smoke warning message on EICAS• Sounds the appropriate smoke warning voice message in the flight compartment

Fire suppression for the baggage compartment, lavatories and cabin closets is provided via hand-held portable fire extinguishers. Provisioning and certification of the smoke detectors and hand-held extinguishers are the responsibility of the completion center and are not further described in this chapter.


9-11


FIRE PROTECTION

AVIONICS BAY

CLOSET

• Smoke detection

– 3A...FWD’ 3B...AFT• Smoke detection

(x2, R & L, left not shown)• Overheat detection• Suppression by lowering gear

– Position varies per interior• Smoke detection (GX only)

• Smoke Detection

• Dual loop fire detection, loops common with zone 2• Two shot halon fire extinguishing system

– Core• Dual loop fire detection, loops common with zone 1• Two shot halon fire extinguishing system

• Dual loop fire detection• Two shot halon fire extinguishing system

• Smoke detection (G5000 only). Considered integralpart of avionics bay for “Smoke Warning” message

The Cabin, Closet, Lavatory, and Baggagecompartment fire protection zones are shown here forreference only. These are not part of the green A/C,except the Baggage Compartment smoke detectorwhich is installed, but not functional.

– 2A...FWD; 2B...AFT• Smoke detection

LAVATORY

MAIN LANDING GEAR BAY

CABIN

BAGGAGE COMPARTMENT

MAIN POWERPLANT ZONE 1

MAIN POWERPLANT ZONE 2

APU COMPARTMENT

AVIONICS RACK

NOTE

4

5

1

2

3

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9

5

1

10

2

4

3

6

77

8 8

9

3

F/X

F/X 2

FIDEX

6

7

8

9

10



FIRE PROTECTION

FIRE HANDLESThe three fire handles are provided for the engine and APU fire protection system. They are installed on the center overhead panel in the flight compartment.

To prevent accidental engine shutdown and fire extinguisher discharges, each fire control handle is maintained in the stowed position by four center springs and a solenoid operated switch.

When a fire warning is received, the Data Acquisition Unit unlocks the solenoid to allow ease of pulling the handle. At any other time when an arm/discharge command sequence is desired, the solenoid must be manually unlocked by depressing the manual override button, (overhead panel behind each switch) while pulling the handle. Each fire handle also has four lamps (bulbs) to illuminate each individual handle for fire detection.

When a handle is pulled to the armed position, the following events occur:

• Applicable (engine/APU) fuel Shutoff Valve (SOV) closes• Each engine - applicable hydraulic SOV closes• Each engine and APU - applicable bleed SOV closes• A signal is sent to trip the applicable Variable Frequency Generators (VFGs)• A signal is sent to the APU electronic control unit to cancel ignition• Redundant commands are sent to ARM the FIDEEX control unit’s discharge

circuits

If the warning persists following the pulling of the handle, the fire can be extinguished by discharging a fire extinguisher bottle.

DISCH

PULL

1 2

LPULL

APU

DISCH

1 2

DISCH

1 2

RPULL

“ARM”Handle Pulled

Note:Right fire pull handle shownleft and APU are similar.

Manual OverrideButton, Press In

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01

0

DISCH

PULL

1 2

L RDISCH

1 2

PULL

APU IgnitionShutoff

APU FuelShutoff

APU PowerShutoff

LEFT ENGINE RIGHT ENGINEFuel Shutoff

Hydraulic ShutoffPneumatic ShutoffAC Power Shutoff

Fire Extinguishing System Armed

Fuel ShutoffHydraulic ShutoffPneumatic ShutoffAC Power ShutoffFire Extinguishing System Armed

DISCH

PULL

1 2

APU

Fire ExtinguishingSystem Armed

PneumaticShutoff

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9-13


FIRE PROTECTION

ENGINE FIREWhen an engine DISCH fire handle is pulled, the ENGINE FUEL SOV is commanded closed, preventing fuel flow to the engine.

NOTEPulling the fire DISCH handle does not command an immediate engine shutdown. In the event of a fire, the engine should be shut down, using the ENGINE RUN switches which will close the high pressure fuel shutoff valve (HPSOV).

To discharge an engine bottle, the handle must be turned fully and held (at least one second) to overcome the spring force of the handle; counterclockwise (bottle 1) or clockwise (bottle 2). This action will send redundant commands to discharge the selected fire extinguisher bottle into the armed zone. When a handle is turned fully in the opposite direction, the remaining bottle will be discharged.

DISCH

PULL

1 2

L/R

“BOTTLE 1”HANDLE PULLED, ROTATEDTO THE LEFT

“BOTTLE 2”HANDLE PULLED, ROTATEDTO THE RIGHT

ENGINE FIRE HANDLEG

X_

09

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12



FIRE PROTECTION

APU FIRE

To discharge the APU bottle, the handle must be turned fully and held (at least one second) to overcome the spring force of the handle; counterclockwise (bottle 1) or clockwise (bottle 2). This action will send redundant commands to discharge the selected fire extinguisher bottle into the armed zone.

To discharge the second extinguisher bottle, the lockout release pin must be slid to the right, to allow the handle to be rotated back to the center position. This is most often a two handed operation. The additional step for the APU is deemed necessary to preserve one bottle for possible engine fire. When a handle is turned fully in the opposite direction, the remaining bottle will be discharged.

“BOTTLE 1”HANDLE PULLED, ROTATEDTO THE LEFT

“BOTTLE 2”HANDLE PULLED, ROTATEDTO THE RIGHT

APU FIRE HANDLE

DISCH

PULL

1 2

APU G

X_

09

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13

APU LockoutRelease Pin


9-15


FIRE PROTECTION

SHUTOFF VALVES (SOV)The following valves are commanded closed as a function of pulling the applicable fire DISCH handle.

PULL

APU

DISCH

1 2

APU

LP

LOFF

R

HP

LP

HP45PSI

0PSI

APU32 °C32 °C

2B3A 3B

HYDRAULIC

RAT

22 °C

1B

62%

38 °C

63%

20 °C

62%

HydraulicShutoff Valves

Note:The right SOV is shown,operation of the left issimilar.

HYD AULIC SYNOPTIC PAGER

APU and EngineFeed Shutoff Valves

Note:The left engine SOVis shown, operationof the right is similar.

DISCH

PULL

1 2

L

DISCH

PULL

1 2

APU

BLEED/ANTI-ICE SYNOPTIC PAGE

High Pressure Valve (HPV)and Pressure RegulatorValves (PRV)

FUEL SYNOPTIC PAGE

HPV PRV

APUFADEC

BLEEDMANAGEMENT

COMPUTER

NOTE:The left bleed valves areshown, operation of theright is similar.

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DISCH

PULL

1 2

L

DISCH

1 2

RPULL



FIRE PROTECTION

FIRE EXTINGUISHER ASSEMBLYThe designated fire zones are left engine, right engine and APU. There are two fire extinguisher bottles on each airplane attached to the left rear fuselage structure. Each fire extinguisher bottle incorporates a hermetically-sealed pressure vessel filled with Halon 1301. The forward fire extinguisher bottle is designated as bottle 1, and the aft fire extinguisher is designated as bottle 2.

FIRE EXTINGUISHER DISCHARGE BOTTLESEach bottle in the Fire Extinguisher Assembly has three discharge ports. Each of these ports are designated toward one of the fire zones (left engine, right engine or APU enclosure). Therefore the contents of a bottle can be directed into any one of these three zones, if required.

A fire extinguisher discharge squib (electro-explosive device) is installed in each discharge port. Each squib has two circuits (bridgewires), each of which is capable of firing the squib. One of the circuits is wired to channel A, and the other to channel B of the FIDEEX control unit. Firing a squib shoots a “dagger” at a burst disk contained within each port. The rupture of this burst disk allows the bottle contents to discharge

FireExtinguisher

Bottle 2

FireExtinguisher

Bottle 1

2

1

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9-17


FIRE PROTECTION

into its designated zone. This burst disk also acts as a pressure relief valve within a bottle. Should the bottle become overpressurized, one of these burst disks will rupture, discharging the contents of the bottle.

If one of the circuits detects a fault, it will report to Central Aircraft Information Maintenance System (CAIMS), but no EICAS message will be posted since there is no loss of bottle discharge capability. If both circuits to a squib are detected to be nonfunctional, a squib advisory message will be posted for the affected system.

FIRE EXTINGUISHER GAUGESEach bottle in the Fire Extinguisher Assembly has a pressure gauge to display bottle pressure and a pressure switch to act as an “alarm gauge”. This alarm gauge automatically signals the FIDEEX control unit if the fire extinguisher pressure drops below the minimum operating pressure (250 psi). This will generate the following EICAS message “FIRE BTL 1 (2) LO PRESS” to alert the flight crew.

Fill Port

APU Port

R Engine Port(left enginenot shown)

Squib Location

Gauge

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Lower View

Pressure Gauges

Squibs

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FIRE PROTECTION

MAIN ENGINE FIRE EXTINGUISHINGThe FIDEEX control unit monitors the engine fire detecting elements. It sends information to the flight compartment and if initiated by the flight crew, commands the fire bottle to discharge the extinguishing agent.

The extinguishing piping from the bottles extend through the pylon to the engine. The piping is then directed within the engine to a “T” junction which divides the flow into two zones, accessory and core. A nozzle assembly directs halon to different sections of each zone.

Fire Bottles

Feed To TheRight Engine Feed to the Apu

Discharge IntoFire Zone



Note:Discharge into RH engine is similar butnot shown.

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9-19


FIRE PROTECTION

Fire Detector

FUEL SHUTOFFVentilation

Air In

AIR EXHAUST

FIREEXTINGUISHANT

AIRFRAME

ENGINE

FLIGHT DECK CONTROLS

ENGINE RUN SWITCHDISCH HANDLE

FLIGHT DECKINDICATIONS

FIDEEXCONTROL UNIT

ENGINE SOV

FUEL FLOW

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9



FIRE PROTECTION

APU COMPARTMENT FIRE EXTINGUISHINGThe APU compartment is protected by a two shot fire extinguishing system. Each discharge is independently directed by the pilot, with provision to guard against accidental discharge of both extinguishers into the APU.

APU FIDEEX/FADEC INTERFACEOn the ground, the FADEC will automatically shut down the APU if a fire signal is received for at least 5 seconds, and the APU fire handle is not pulled. Although the APU will automatically shut down if a fire is detected, there is no automatic discharging of the fire extinguishing agent. Therefore, the APU must not be left unattended for ground operations.

If in an airborne state, the EICAS will give aural and visual warnings but the APU must be shut down via the fire handle.

NOTEIf an APU fire is detected on the ground, and the fire handle signal (pulled) is not detected within 5 seconds, the FADEC will command an auto shutdown of the APU.

During normal APU operation, the APU FADEC signals the fuel management system to open the APU SOV. If an APU fire were detected and the APU fire DISCH handle pulled, the FIDEEX control unit will close the APU SOV.

PULL

APU

DISCH

1 2

APU LockoutRelease Pin

GX

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9_

02

0


9-21


FIRE PROTECTION

PILOT-INITIATED TESTA Pilot-Initiated Test (PIT) of the fire extinguishing system shall be commanded as part of the airplane preflight, and can be carried out at any time during normal operation of the system.

To initiate the fire system test, press the TEST activation button on the EMS/CDU. The command test signal is sent to the FIDEEX control unit. The crew initiated fire test consists of:

• A periodic test of all fire/overheat loops with all flight deck reporting active• A smoke detector test of all installed smoke detectors

When the TEST button on the EMS/CDU is selected, the FIRE TEST is automatically highlighted on the SYSTEM TEST page.

To initiate the test, the right side button must be selected. Test will automatically terminate after approximately 15 seconds, or can be aborted by a reselect of the FIRE TEST key.

BRT

CIRCUIT BREAKER SYSTEM

STAT SYS BUSPREVPAGE

NEXTPAGE

CNTL TEST

BUS

EMERCONT

EMS/CDU

GX

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9_

02

1G

X_

09

_0

22

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

TEST CONTROL 1/2

FIRE TEST

STALL WARNING

AURAL WARNING TEST 1

AURAL WARNING TEST 2

LAMP TEST 1

LAMP TEST 2

TEST

OFF

OFF

OFF

OFF

OFF



FIRE PROTECTION

A PIT is successful if each of the following events occur:

1. Both master WARNING lights flash and an aural warning sounds.

2. Left engine, right engine, and APU fire handles illuminate.

The following EICAS warning messages appear:

• L/R ENG FIRE• APU FIRE• MLG BAY OVHT• SMOKE BAGGAGE, SMOKE FWD LAV, SMOKE AFT LAV, and SMOKE

CABIN, SMOKE CLOSET FWD, SMOKE CLOSET AFT, (if smoke detectors are installed)

The fire test duration is approximately 10 seconds. When the fire test is completed, all warning messages will go out, fire aural warning will deactivate, master WARNING lights will go out, and the fire DISC handle lights will go out.

If loss of detection for either engine, APU, MWW or smoke sensing is detected by the FIDEEX, the appropriate zone fire fail caution message will be displayed on the EICAS until the fail condition no longer exists.

“LEFT ENGINE FIRE,RIGHT ENGINE FIRE,APU FIRE,SMOKE,GEAR BAY OVERHEAT”

GLARESHIELD

GX

_0

9_

02

3

TRIPLE CHIME

AURAL


WARNING

CAUTION

DISCH

PULL

1 2

LPULL

APU

DISCH

1 2

DISCH

1 2

RPULL

GX

_0

9_

02

4

TOTAL FUEL (LBS) 4155O

1.54

146OO 146OO1OOOO

N2

FF (PPH)

OIL TEMP

OIL PRESS

93.4575O11581

1.65

CRZEPR

IGN

START START

IGN

NDSTAB

1.54

1.65

73.3

T/ON1SYNC

73.3

789

ITTSYNC

789 DN DN DN

OUT

3O

GEAR

–TRIMS–

NL NRRUDDER

AIL

RWDLWD

7.2

NU

93.4575O11581

235O

L-R ENG FIREAPU FIREMLG BAY OVHTSMOKE AVIONICS BAYSMOKE BAGGAGESMOKE FWD LAVSMOKE AFT LAVSMOKE CABINSMOKE CLOSET FWDSMOKE CLOSET AFTSMOKE CLOSET

If Installed

GX

_0

9_

02

5

15

ITTSYNC

15

FIRE FIRE


9-23


FIRE PROTECTION

EICAS MESSAGES

789

1 . 65 L (R) ENG FIREAPU FIREMLG BAY OVHTSMOKE AVIONICS BAYSMOKE BAGGAGESMOKE FWD LAVSMOKE AFT LAVSMOKE CLOSET FWDSMOKE CLOSET AFTSMOKE CABINSMOKE CLOSETL (R) ENG FIRE FAILMLG BAY OVHT FAILAPU FIRE FAIL

L (R) ENG FIRE FAILIndicates a left or rightdual loop failure, andcomplete loss of firedetection capability inthe affected engine.

APU FIRE FAILIndicates a dual loopfailure and a completeloss of fire detectioncapability in the APU.

MLG BAY OVHT FAILIndicates a left and/orright detection systemfailure.

L (R) ENG FIREIndicates fire has occurredon the affected engine.

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APU FIREIndicates that an APUfire has occurred.

“APU FIRE”

SMOKE BAGGAGE(if installed)Indicates a smokewarning in the baggagecompartment.

“SMOKE”

SMOKE AFT LAV(if installed)Indicates a smokewarning in the aftlavatory.

“SMOKE”

MLG BAY OVHTInd cates that a leftand/or right main wheelwell overheat hasoccurred.

i

“GEAR BAYOVERHEAT”

SMOKE AVIONICS BAY(if installed)Indicates a smokewarning in the avionicsbay. G5000 SMOKEcould be present inavionics bay/rack onlyor in both areas.

“SMOKE”

SMOKE FWD LAV(if installed)Indicates a smokewarning in the forwardlavatory.

“SMOKE”

SMOKE CLOSET FWD

(if installed)

SMOKE CLOSET AFTSMOKE CABINSMOKE CLOSET

Indicates a smokewarning in at least one ofthe closet / cabin areas.Smoke Cabin notavailable in G5000.

“SMOKE”

“LEFT or RIGHTENGINE”



FIRE PROTECTION

EICAS MESSAGES (Cont)

789

1 . 65 SMOKE AV RACK FAIL

SMOKE CLO FWD FAILSMOKE CLO AFT FAILSMOKE CABIN FAILSMOKE AV BAY FAIL

SMOKE BAGGAGE FAILSMOKE FWD LAV FAILSMOKE AFT LAV FAILSMOKE CLOSET FAIL

FIRE BTL1 LO PRESSFIRE BTL2 LO PRESSL ENG SQUIB 1 FAILR ENG SQUIB 1 FAILL ENG SQUIB 2 FAILR ENG SQUIB 2 FAIL

SMOKE FWD LAV FAILIndicates the smokedetector in the forwardlavatory has failed.

SMOKE CLOSET FAILSMOKE CLO FWD FAILSMOKE CLO AFT FAILSMOKE CABIN FAIL(If installed)Indicates one or morecloset smoke detectorshave failed. In G5000,SMOKE CABIN FAIL isreplaced by SMOKE AVRACK FAIL

FIRE BTL2 LO PRESSIndicates low pressurein fire extinguishingbottle 2.

R ENG SQUIB 1 FAILIndicates that the rightengine squib 1 hasfailed. Fire bottle 1 isnot available to theright engine.

R ENG SQUIB 2 FAILIndicates that the right engine squib 2 hasfailed. Fire bottle 2 is not available to theright engine.

L ENG SQUIB 2 FAILIndicates that the leftengine squib 2 hasfailed. Fire bottle 2 isnot available to the leftengine.

L ENG SQUIB 1 FAILIndicates that the leftengine squib 1 hasfailed. Fire bottle 1 isnot available to the leftengine.

FIRE BTL1 LO PRESSIndicates low pressurein fire extinguishingbottle 1.

SMOKE AV BAY FAILIndi ates one or more(if two installed) smokedetector(s) in theavionic bay has failed.

c

SMOKE BAGGAGEFAILIndicates one or bothsmoke detectors inthe baggage area hasfailed.

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SMOKE AFTLAV FAILIndi ates the smokedetector in the aftlavatory has failed.

c

SMOKE AV RACK FAIL(G5000 only)Indi ates the smokedetector in the avionics

has failed.

c

rack


9-25


FIRE PROTECTION

EICAS MESSAGES (Cont)

789

1 . 65 APU SQUIB 1 FAILAPU SQUIB 2 FAILFIRE SYS FAULTL (R) ENG FIRE FAULTMLG BAY OVHT FAULTAPU FIRE FAULTL (R) ENG SOVS CLSDAPU SOVS CLSDL (R) ENG BLEED OFFL (R) HYD SOV CLSDAPU BLEED OFF

APU SQUIB 2 FAILIndicates that APUsquib 2 failed. Firebottle 2 is not availableto the APU.

APU SQUIB 1 FAILIndicates that APUsquib 1 failed. Firebottle 1 is not availableto the APU.

FIRE SYS FAULTIndicates FIDEEXsystem fault. Engineand APU fire detectionand extinguishingsystem is operational.Other fire systemfunctions may beunreliable.

MLG BAY OVHTFAULTIndicates a detectionelement system fault.One channel of thesystem is unreliable,other channel is stilloperational.

L (R) ENG FIRE FAULTIndicates a left or rightengine fire detectionelement system fault.One channel of thesystem is unreliable,other channel is stilloperational.

APU FIRE FAULTIndicates a fire detectionelement system fault. Onechannel of the system isunreliable, other channel isstill operational.

APU SOVS CLSDIndicates the applicablevalve is closed with thefire handle pulled:• APU SOV• APU LCV

L (R) HYD SOV CLSDIndicated when the L-Rvalve remains closed withthe fire handle pulled, ormanual selected via theL(R) HYD SOV switch, andno "L-R ENG SOVSCLSD" status message isposted.

APU BLEED OFFIndicated when the APUmanual bleed is selected offand the LCV closes, orAPU fire handle pulled andno "APU SOVS CLSD"status message is posted.

L (R) ENG BLEED OFFIndicated when thebleed manual switch isselected off, or L-R firehandle pulled and no“L-R ENG SOVSCLSD” status messageis posted.

L (R) ENG SOVS CLSDIndicates the applicablevalves are closed withthe fire handle pulled:• PRV and HPV• R or L ENG SOV• HYD SOV 1 or 2

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FIRE PROTECTION

EMS CIRCUIT PROTECTION

M

M

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

CIRCUIT BREAKER - SYSTEM 1/2

AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

CB - FIRE SYSTEM 1/2

APU FIRE HANDLE

FIRE DETECT CH A

FIRE DETECT CH B

FIREX CH A

FIREX CH B

L FIRE HANDLE

BATT

BATT

BATT

DC EMER

DC EMER

BATT

IN

IN

IN

IN

IN

IN

DCPC

DCPC

CB - SYSTEM 2/2

R FIRE HANDLE BATT IN

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chapter 9: fire protection table of contents

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