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minutes prior to and one minute after switch actuation will be recorded
in the EDS memory.
The following CAS illuminations are specific to the engine diagnostic
system:
CAS Color Description
CHECK EDS White Indicates one of the following about the associated
(L or R) engine diagnostic system
(EDS):
• The EDS has lost power.
• The EDS built-in test equipment (BITE)
has detected a system failure.
• The EDS memory is 80% full.
• The system has detected an engine condition
which is out of acceptable parameters.
Pilot’s Manual
2-20 PM-126A
ENGINE FIRE DETECTION SYSTEM
Three heat-sensing elements connected in series are located in each engine
nacelle to detect an engine fire. One element is located around the
accessory gearbox; one is located around the engine tailcone; and another
around the engine firewall. The fire detection system is controlled
by two fire detect control boxes located in the tailcone. In the event of
an engine fire, the applicable control box will sense a resistance change
in the sensing elements and flash the master WARN lights in the
glareshield and applicable FIRE switch located within the L or R
ENGINE panel of the aft pedestal.
The FIRE red EI will flash within the arc of the ITT dial. Warning is given
if the firewall or accessory gearbox area exceeds approximately
410° F (210° C), or the engine tailcone area exceeds approximately
890° F (477° C).
Whenever an engine fire is detected a “LEFT” or “RIGHT ENGINE
FIRE” voice message will sound to both pilots’ headphones and flight
deck speakers. This voice message is continuous, but can be silenced by
depressing the mute switch located on the right thrust lever or the master
WARN light.
Electrical power for the system is 28-vdc supplied through the 1-amp L
and R FIRE DET circuit breakers located within the ENGINE group of
the pilot’s and copilot’s circuit breaker panels respectively. Fire detect
systems are powered from the respective L and R ESS buses.
Pilot’s Manual
PM-126A 2-21
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.
- Red FIRE messages in ITTs will flash.
Both red FIRE messages on RMU ENGINE PGE 1
will flash next to the N1 display.
- L and R BLEED AIR LEAK red CAS and CWP. This
indicates continuity of the bleed air overheat sensor
system.
- WING/STAB LEAK red CAS and CWP. This indicates
continuity of the anti-ice bleed air overheat sensor
system.
- APU FIRE Switch (if installed) and a red CAS will illuminate
with the APU MASTER Switch ON. The red
CAS only will illuminate if the APU MASTER Switch is
Off.
Depressing and holding the SYS TEST/RESET
Switch in the FIRE DET position for 15 seconds will
result in the APU fire horn sounding. Holding the
switch for 30 seconds will result in an APU FAIL indication
and APU shutdown.
NOTE
NOTE
Pilot’s Manual
2-22 PM-126A
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
　
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