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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.
For Training Purposes Only
Sept 04
9-11
P I LOT T R A I N I N G GU I D E
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 integral
part of avionics bay for “Smoke Warning” message
The Cabin, Closet, Lavatory, and Baggage
compartment fire protection zones are shown here for
reference only. These are not part of the green A/C,
except the Baggage Compartment smoke detector
which 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
GX_09_009
5
1
10
2
4
3
6
7 7
8 8
9
3
F/X
F/X 2
FIDEX
6
7
8
9
10
9-12 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
FIRE HANDLES
The 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
L PULL
A
P
U
DISCH
1 2
DISCH
1 2
RPULL
“ARM”
Handle Pulled
Note:
Right fire pull handle shown
left and APU are similar.
Manual Override
Button, Press In
GX_09_010
DISCH
PULL
1 2
L R
DISCH
1 2
PULL
APU Ignition
Shutoff
APU Fuel
Shutoff
APU Power
Shutoff
LEFT ENGINE RIGHT ENGINE
Fuel Shutoff
Hydraulic Shutoff
Pneumatic Shutoff
AC Power Shutoff
Fire Extinguishing System Armed
Fuel Shutoff
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
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