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when discharged, supplies both zones simultaneously.
GF0910_014
FEED TO THE
RIGHT ENGINE
DISCHARGE INTO
FIRE ZONE
FEED TO THE APU
FIRE BOTTLES
Discharge into RH engine
is similar, but not shown.
NOTE
DISCHARGE INTO
FIRE ZONE
DISCHARGE INTO
FIRE ZONE
The fire extinguishing for the main engine is supplied by two discharges (shots) of extinguishant,
which can be independently directed by pilot’s selection, to either main power plant. The
extinguishing piping from the bottles extend through the pylon to the engine. The piping is then
directed within the engine to a tee which divides the flow into two zones, accessory and core. A
nozzle assembly directs halon to different sections of each zone.
FIRE PROTECTION
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
09−10−11
MAIN ENGINE FIDEEX CONTROL
The FIDEEX control unit monitors the engine fire detecting elements. It sends information to the flight
compartment and commands the fire bottle to discharge the extinguishing agent.
GF0910_015
When an engine DISCH fire handle is pulled, the ENGINE SOV is commanded closed preventing
fuel flow to the engine.
NOTE
Pulling the fire DISCH handle does not command an immediate engine
shut down. In the event of a fire, the engine should be shut down using
the ENGINE RUN switches.
When the engine DISCH fire handle is turned, a command is sent to the FIDEEX control unit to
discharge the fire bottle. The EICAS will display the result of the extinguisher discharge.
FIRE PROTECTION
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
09−10−12
MAIN ENGINE FIDEEX CONTROL (CONT'D)
When an engine fire is detected, the applicable engine fire DISCH handle will illuminate, MASTER
WARNING lights flash, a warning message will appear on EICAS and a voice message “LEFT or
RIGHT ENGINE FIRE” will sound.
ENGINE FIDEEX CONTROL SCHEMATIC
GF0910_016
EICAS
AUDIO
CONTROL
PANEL
IAC
R ENGINE
FIRE
HANDLE
D
A
U
LEFT ENGINE
LOOP A
L ENGINE FIRE
FIDEEX
CONTROL
UNIT
R ENGINE FIRE
LEFT ENGINE
LOOP B
RIGHT ENGINE
LOOP A
RIGHT ENGINE
LOOP B
L ENGINE
FIRE
HANDLE
LEFT ENGINE
FIXED COWL
MOUNTED FIRE
DETECT
GEARBOX MOUNTED
FIRE DETECT
CORE ENGINE FIRE
DETECTOR SENSOR
RIGHT ENGINE
FIXED COWL
MOUNTED FIRE
DETECT
GEARBOX MOUNTED
FIRE DETECT
CORE ENGINE FIRE
DETECTOR SENSOR
"RIGHT ENGINE FIRE"
"LEFT ENGINE FIRE"
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.
FIRE PROTECTION
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
09−10−13
APU COMPARTMENT FIRE DETECTION
The APU fire protection system provides a means for detection of a fire condition within the APU
enclosure. The APU uses the left or right fire bottle located in the aft fuselage section. Pulling the
APU fire handle will signal the APU FADEC unit to initiate APU shut down. Turning the handle will
discharge the selected fire extinguisher bottle.
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.
The APU fire detection is self contained within the APU compartment. The detection system consists
of the following:
· Fire loop elements inside the compartment for fire detection.
· Flight deck indication (red) through the fire handle and shut down signal to the APU FADEC.
· Aural fire warning on the flight deck.
· Automatic APU shut down on the ground, if necessary.
GF0910_017
DUAL LOOP
SENSING ELEMENT
STRUT SENSING
ELEMENT
The APU fire detection is provided by a dual loop system; each loop consists of sensing elements.
Two element pairs are mounted directly to the airplane structure and the other element is mounted to
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