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CAS Messages ................................................................................................................. 8-5
OPERATION ........................................................................................................................... 8-5
Preflight........................................................................................................................... 8-5
In Flight........................................................................................................................... 8-6
EMERGENCY/ABNORMAL ................................................................................................ 8-7
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ILLUSTRATIONS
Figure Title Page
8-1 Engine Fire-Detection and Extinguishing System ................................................... 8-3
8-2 Engine Fire Bottle .................................................................................................... 8-4
8-3 Portable Fire Extinguisher........................................................................................ 8-4
8-4 ENGINE FIRE and BOTTLE ARMED Lights........................................................ 8-5
8-5 Rotary TEST Knob................................................................................................... 8-5
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INTRODUCTION
This chapter describes the fire protection system on the Citation Mustang aircraft. The engine
fire-detection system consists of two separate detection circuits (one for each engine),
which provide visual warnings. The engine fire-extinguishing system includes one fire bottle,
which is activated from the cockpit. A portable fire extinguisher is in the cabin.
GENERAL
The fire-protection system consists of engine
fire detection, engine fire extinguishing, a
portable fire extinguisher, and aircraft construction
that reduces a fire risk. The engine
fire-detection system detects fires and overheat
conditions in the engine nacelles and alerts
the crew. The engine fire-extinguishing system
suppresses those fires upon pilot command by
supplying fire-extinguishing agent.
Fire suppression in the cabin area is accomplished
using a portable fire extinguisher.
For additional protection, the engine nacelle
fire zone is separated from the pylon and the
rest of the aircraft by a stainless steel firewall.
At the firewall penetrations and in the nacelle,
fuel is contained in stainless steel
fittings, stainless steel tubes, and fire-resistant
hoses.
The rotary TEST knob on the instrument panel
is used to test the fire warning system.
CITATION MUSTANG OPERATING MANUAL
CHAPTER 8
FIRE PROTECTION
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DESCRIPTION
ENGINE FIRE DETECTION
SYSTEM
The engine fire-detection system consists of:
• Fire-detection loop
• Pressure sensor
• Red L and R ENGINE FIRE lights
Excessive heat by fire or other heat sources expands
inert gas inside the fire-detection loop.
The expansion of gas closes a pressure switch
that sends a signal to illuminate the left or
right ENGINE FIRE light.
The fire-detection system requires DC power.
FIRE DETECT circuit breakers for the independent
sides are on the left and right CB panels
within the ENGINE SYSTEMS grouping.
ENGINE FIRE-EXTINGUISHING
SYSTEM
The single bottle engine fire-extinguishing
system enables the flightcrew to suppress a fire
in the left or right engine compartment. This
action is limited to one use.
The engine fire-extinguishing system consists
of:
• Engine fire bottle assembly
• Distribution tubes
• Nozzles in each engine nacelle
• BOTTLE ARMED lights
• Fuel shutoff valve and generator disconnect
These components shut off the generator and
fuel supply as well as discharge extinguishing
agent, which is pressurized with nitrogen and
discharged by electrically activated cartridges
to the engine nacelles.
PORTABLE FIRE
EXTINGUISHER
A portable fire extinguisher provides fire protection
inside the aircraft.
COMPONENTS
FIRE DETECTION LOOP
Each fire detection loop detects a fire or overheat
condition in the respective engine compartment
(Figure 8-1). The tube routes along
both sides of the engine.
An increase in temperature on any part of the
tube increases the pressure of the gas (helium)
inside the tube.
　
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