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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
Fire
Extinguisher
Bottle 2
Fire
Extinguisher
Bottle 1
2
1
GX_09_015
For Training Purposes Only
Sept 04
9-17
P I LOT T R A I N I N G GU I D E
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 GAUGES
Each 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 engine
not shown)
Squib Location
Gauge
GX_09_016
Lower View
Pressure Gauges
Squibs
GX_09_017
9-18 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
MAIN ENGINE FIRE EXTINGUISHING
The 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 The
Right Engine Feed to the Apu
Discharge Into
Fire Zone
Discharge Into
Fire Zone
Discharge Into
Fire Zone
Note:
Discharge into RH engine is similar but
not shown.
GX_09_018
For Training Purposes Only
Sept 04
9-19
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
Fire Detector
FUEL SHUTOFF
Ventilation
Air In
AIR EXHAUST
FIRE
EXTINGUISHANT
AIRFRAME
ENGINE
FLIGHT DECK CONTROLS
DISCH HANDLE ENGINE RUN SWITCH
FLIGHT DECK
INDICATIONS
FIDEEX
CONTROL UNIT
ENGINE SOV
FUEL FLOW
GX_09_019
9-20 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
APU COMPARTMENT FIRE EXTINGUISHING
The 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 INTERFACE
On 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.
NOTE
If 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
A
P
U
DISCH
1 2
APU Lockout
Release Pin
GX_09_020
For Training Purposes Only
Sept 04
9-21
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
PILOT-INITIATED TEST
A Pilot-Initiated Test (PIT) of the fire extinguishing system shall be commanded as
　
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