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Pilot’s Manual
2-20 PM-132A
SYS TEST/RESET SWITCH
FIRE DETECTION FUNCTION
The rotary-type SYS TEST/RESET switch on the forward pedestal is
used to test the fire detection system. Rotating the switch to FIRE DET
and depressing the switch (PRESS TEST) button will connect a resistance
into both fire detect system circuits. This resistance, simulating an
engine fire, will test system indications as follows:
• Master WARN tone and light will activate followed by a “LEFT
ENGINE FIRE . . . RIGHT ENGINE FIRE” voice.
• Both red FIRE and all white EXTINGUISHER #1 and #2
ARMED switches (ENGINE panel) will illuminate. Illumination
of the FIRE switch indicates continuity of the fire detect systems
and illumination of the EXTINGUISHER #1 and #2 ARMED
switches indicate continuity of the fire extinguisher squibs.
Both red FIRE messages on RMU ENGINE PGE 1 will
flash next to the N1 display.
• Red FIRE messages in ITTs will flash.
• L and R BLEED AIR LEAK red CAS and CWP illuminated. This
indicates continuity of the bleed air overheat sensor system.
• WING/STAB LEAK red CAS and CWP illuminated. This indicates
continuity of the anti-ice bleed air overheat sensor system.
NOTE
Pilot’s Manual
PM-132A 2-21
ENGINE FIRE EXTINGUISHING SYSTEM
The engine fire extinguishing system components include: two spherical
extinguishing agent containers, a red FIRE PUSH light/switch for
each engine, two white EXTINGUISHER #1 and #2 ARMED light/
switches for each engine, one hydraulic shutoff valve for each engine,
one fuel shutoff valve for each engine, a thermal discharge indicator, a
manual discharge indicator, and associated wiring and plumbing. The
system also utilizes the pneumatic system bleed air shutoff valves. The
system is plumbed to provide the contents of either or both extinguishing
agent containers to either engine nacelle. Shuttle valves are installed
to prevent extinguishing agent flow between containers. The
extinguishing agent, Halon 1301 (Bromotrifluromethane [CF3Br]), is
stored under pressure (600 psi) in the extinguisher containers and a
pressure gauge on each container is visible from inside the tailcone. Halon
1301 is non-toxic at normal temperatures and is non-corrosive. As
Halon 1301 is non-corrosive, no special cleaning of the engine or nacelle
area is required in the event the system has been used. The system operates
on 28-vdc supplied through the 5-amp L and R FIRE EXT circuit
breakers located within the respective ENGINE group of the pilot’s and
copilot’s circuit breaker panels. Fire extinguishing systems are powered
from the EMER BATT hot bus.
Pilot’s Manual
2-22 PM-132A
L AND R ENGINE FIRE AND EXTINGUISHER #1/#2 SWITCHES
The engine fire extinguishing system is operated through the L and R
FIRE switches and the EXTINGUISHER #1 and #2 switches located in
the respective L and R ENGINE panel on the aft pedestal. Activating
the applicable FIRE switch will cause the following events:
• Close the respective shutoff valves. (Refer to Figure 2-3.)
• CLOSED indication will appear on respective FIRE switch.
Flashing FIRE PUSH illumination goes to steady.
• Arm the extinguishing agent containers.
• EXTINGUISHER #1 and #2 light illuminated.
• Trip respective DC generator and alternator off-line.
• Trip respective engine ignitors off-line.
• Trip respective thrust reverser control unit off-line and prevent
the thrust reverser isolation valve from opening.
Illumination of the EXTINGUISHER #1/#2 ARMED light(s) indicates
that the fire extinguishing system is armed and the squibs are good. Depressing
an illuminated EXTINGUISHER #1 ARMED light will discharge
the contents of the first extinguisher bottle into the associated
nacelle. Depressing the EXTINGUISHER #2 ARMED light will discharge
the contents of the second bottle. Either or both EXTINGUISHER
#1/#2 ARMED lights may be depressed to extinguish the fire.
Should the first container control the fire, the other container is available
to either engine.
FIRE EXTINGUISHER DISCHARGE INDICATORS
Two disk-type indicators are flush-mounted in the fuselage under the
right engine pylon. If the contents of either or both containers have
been discharged into the engine nacelles, the yellow disk will be ruptured.
If the contents of either or both containers have been discharged
overboard as the result of an overheat condition causing excessive pressure
within the containers, the red disk will be ruptured. If both disks
are intact, the system has not been discharged.
　
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