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pressure switch. The pressure alarm gauge automatically signals the FIDEEX control unit when
the fire extinguisher pressure drops below the minimum operating pressure.
If one of the circuits detect a fault, it will report to Central Aircraft Information Maintenance System
(CAIMS) and 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 PROTECTION
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
09−10−7
FIRE EXTINGUISHER ASSEMBLY (CONT'D)
Fire Extinguisher Gauges
Each fire extinguisher assembly includes a pressure gauge to display fire extinguisher pressure at
the extinguisher and a pressure switch to automatically signal below minimum operating pressure
(250 psi).
GF0910_010
PRESSURE GAUGES
Lower View SQUIBS
The pressure switch (monitored by the FIDEEX control unit) will generate the following caution
EICAS message FIRE BTL 1(2) LO PRESS to alert the flight crew.
Fire Zone Discharge Schematic
Both extinguishing bottles have a discharge outlet for each zone. There are three fire extinguisher
discharge heads on each fire extinguisher bottle assembly. Two of the discharge heads are for
main engines and the other for APU.
GF0910_011
LEFT ENGINE
FIRE
FIDEEX CONTROL UNIT
APU
RIGHT ENGINE
EXTINGUISHING
CONTAINER
#1
FIRE
EXTINGUISHING
#2
CONTAINER
Outlets designated for the same fire zone from the two extinguishing bottles are fed into a common
distribution piping system. Discharging through any of the three outlets discharges the entire
contents of the fire extinguisher bottle (one shot only).
FIRE PROTECTION
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
09−10−8
FIDEEX CONTROL UNIT
All interfaces from the airplane’s power and fire control handles pass through the FIDEEX control unit
before they reach the fire extinguishers. The FIDEEX control unit is located below the baggage
compartment floor. The following functions/components are monitored continuously:
· Continuity of the squib circuits.
· Continuity of the pressure switches.
· Existence of 28VDC on the two fire extinguishing power supply lines.
GF0910_012
PRESSURE GAUGE
CONTAINER #1 AND SWITCH CONTAINER #2
DISCHARGE
CHECK VALVES
TO RIGHT ENGINE
TO APU
TO LEFT ENGINE
R ENGINE SQUIB 1
APU SQUIB 1
L ENGINE SQUIB 1
PRESSURE SWITCH
R ENGINE SQUIB 2
APU SQUIB 2
ENGINE SQUIB 2
PRESSURE SWITCH
FIDEEX CONTROL UNIT
A B
LEFT ENGINE APU RIGHT ENGINE
MAIN WHEEL WELL
FIRE LOOP INPUT
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 condition. The FIDEEX control unit performs internal
and operator initiated builtintests
and reports all health and status to the flight compartment EICAS
system.
FIRE PROTECTION
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
09−10−9
MAIN ENGINE FIRE DETECTION
Main engine fire detection is provided by a dualloop
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 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 GF0910_013
SENSOR ELEMENTS
(3 Ea. PER ASSEMBLY)
ENGINE FIRE DETECTOR ELEMENTS
FIRE PROTECTION
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
09−10−10
MAIN ENGINE FIRE DETECTION (CONT'D)
The detection loops of both zones are monitored as a single zone and the fire extinguishing system
　
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