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Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
FIRE PROTECTION
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).
PRESSURE GAUGES
Lower View SQUIBS
GF0910_010
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.
FIDEEX CONTROL UNIT
FIRE
RIGHT ENGINE
EXTINGUISHING
CONTAINER
#1
APU
FIRE
EXTINGUISHING
LEFT ENGINE
CONTAINER
#2
GF0910_011
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).
Volume 2 Flight Crew Operating Manual Rev 3, Apr 25, 2005
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.
A B
R ENGINE SQUIB 1 R ENGINE SQUIB 2
APU SQUIB 1 APU SQUIB 2
L ENGINE SQUIB 1 ENGINE SQUIB 2
PRESSURE SWITCH PRESSURE SWITCH
GF0910_012
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 built-in-tests and reports all health and status to the flight compartment EICAS system.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
FIRE PROTECTION
MAIN ENGINE FIRE DETECTION
Main 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 detection of a fire).
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