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The right hydraulic SOV
is shown, operation of
the left is similar.
APU
HP
LP
0
PSI
P P
1075 LBS
32 °C 32 °C
APU
70°C 68°C 70°C
HYDRAULIC
62 % 64 % 62 %
1B 3A 3B 2B
L
LP
HP
R
45
PSI
DISCH
PULL
1 2
DISCH
PULL
1 2
DISCH
PULL
1 2
DISCH
PULL
1 2
FIRE PROTECTION
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
09−10−6
FIRE EXTINGUISHER ASSEMBLY
The designated fire zones are left engine, right engine and APU. There are two fire extinguisher
bottles on each airplane attached to the left rear fuselage structure. Each fire extinguisher bottle
incorporates a hermetically-sealed pressure vessel filled with Halon 1301. The forward fire
extinguisher bottle is designated as bottle 1 and the aft fire extinguisher is designated as bottle 2.
GF0910_008
FIRE BOTTLES
For war d
Aft
Left Side
View
Fire Extinguisher Discharge Squibs
A fire extinguisher discharge squib (electro-explosive device) is installed in each fire extinguisher
discharge port. Each of the three discharge squibs per extinguishing bottle is assigned to each of
the three fire protection zones. The zones have two circuits, 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.
GF0910_009
A pressure alarm gage displays fire extinguisher pressure at the extinguisher and includes a
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 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
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.
GF0910_010
PRESSURE GAUGES
Lower View SQUIBS
The pressure switch (monitored by the FIDEEX control unit) will generate the following cautions
EICAS message FIRE BTL 1 (2) LO PRESS to alert the flight crew, if the fire extinguisher
pressure drops below minimum operating pressure.
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 51, Aug 14, 2006
CSP 700−6
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
　
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