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If the tube develops a leak, normal pressure
vents and closes the test pressure switch; this
is indicated by L and R ENGINE FIRE lights
not illuminating when the rotary TEST knob
is placed in the FIRE WARN position.
PRESSURE SENSOR
A pressure sensor is at the end of the fire-detection
loop. When the loop is heated by fire
or a bleed-air leak, the gas in the tube expands,
activating the pressure sensor. This
produces an electrical signal that provides a
warning to the flightcrew. The signal is in the
form of:
• L or R ENGINE FIRE lights
• MASTER WARNING lights
ENGINE FIRE BOTTLE
ASSEMBLY
The engine fire bottle (with two squibs) is in the
tail compartment. It can be used to extinguish
a fire in either engine nacelle (Figure 8-2). The
fire bottle contains enough extinguishing agent
to protect against one engine fire (0.85 pound
of Halon 1301 extinguishing agent).
CITATION MUSTANG OPERATING MANUAL
8-2 510OM-00
CITATION MUSTANG OPERATING MANUAL
510OM-00 8-3
P P
GAUGE
SQUIB
SQUIB
FUSIBLE
PLUG
CONTROL
BOXES
FIRE DETECTION LOOP
(HELIUM-FILLED TUBE)
BOTTLE
HELIUM
LEGEND
DISCHARGE AGENT
Figure 8-1. Engine Fire-Detection and Extinguishing System
The fire-extinguisher bottle contains two individual
firing cartridges (squibs). The cartridges
are connected to distribution tubes that
are routed to the left and right engine compartments.
The bottle has a safety relief valve
that thermally relieves (discharges) its contents
into the tail cone if the internal bottle temperature
rises above 210°F.
FUEL SHUTOFF VALVE AND
GENERATOR DISCONNECT
The firewall shutoff valve closes and electrical
flow from the generator is stopped when an
illuminated ENGINE FIRE light is pushed.
An amber F/W SHUTOFF L-R message in the
crew alerting system (CAS) window indicates
that the fuel shutoff valve is fully closed. When
the generator is disconnected, the respective
GEN OFF message appears in the CAS window.
PORTABLE FIRE
EXTINGUISHER
One portable handheld fire extinguisher is in
a drawer in the cabinet behind the pilot (Figure
8-3). It is accessible from either the pilot,
copilot, or passenger positions. The Halon
1301 type extinguishing agent discharges as
a vapor with no residue or decrease in vision
to personnel. The discharge distance is approximately
9–15 feet with a discharge time
of 10 seconds.
CONTROLS AND
INDICATIONS
ENGINE FIRE LIGHTS
Red L and R ENGINE FIRE lights are on the
upper part of the center instrument panel
(Figure 8-4). They respond to signals from the
respective engine fire sensors. Each light is covered
by a spring-loaded, transparent plastic
guard and has an integral pushbutton switch.
If the red L and/or R ENGINE FIRE light illuminates
steady, it indicates a fire or overheat
condition in the corresponding engine.
MASTER WARNING LIGHTS
The MASTER WARNING lights are on the
instrument panel above each primary flight
display (PFD). The MASTER WARNING
lights illuminate flashing when the L or R
ENGINE FIRE lights illuminate. The pilot
acknowledges by pressing one of the MASTER
WARNING lights. Pressing will extinguish
both lights.
WHITE BOTTLE ARMED
LIGHTS
A white BOTTLE ARMED light is below each
red ENGINE FIRE light on the upper-center
panel (Figure 8-4). Each BOTTLE ARMED
light has an integral pushbutton switch.
CITATION MUSTANG OPERATING MANUAL
8-4 510OM-00
Figure 8-2. Engine Fire Bottle Figure 8-3. Portable Fire Extinguisher
These lights indicate when the bottle is armed
for the respective engine and prepared to release
extinguishing agent. After the extinguishing
agent is released, the light
extinguishes, indicating to the crew the extinguisher
bottle is empty and is no longer
available for use.
CAS MESSAGES
GEN OFF L-R
When either of the ENGINE FIRE lights are
pushed, the respective amber GEN OFF message
appears in the CAS window.
F/W SHUTOFF L-R
When either of the ENGINE FIRE lights are
pushed, the respective amber F/W SHUTOFF
message displays in the CAS window. This indicates
that the corresponding fuel shutoff
valve is closed.
OPERATION
PREFLIGHT
Rotary TEST Knob
Test the engine fire-detection system before
each flight by using the rotary TEST knob
(Figure 8-5) during the preflight inspection.
This test verifies connections to the fire bottles
and warning system. Illumination of both
　
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