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Heat-Sensing Elements
Each zone of the engine is protected by a single continuous heat-sensing element (loop),
connected to its respective fire detection control unit. Each sensing element is a coaxial cable,
which has an inner conductor surrounded by an insulator material. The resistance of the
insulating material decreases with an increase in temperature. The outer metal sheathing is
permanently grounded. The loop resistance information is fed to the corresponding fire detection
control unit.
The zone A sensing element is used to detect an overheat/fire condition in the combustion area
of the engine.
FIRE PROTECTION
Description
Vol. 2 09−10−1
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
ENGINE FIRE/OVERHEAT PROTECTION (CONT'D)
The zone B sensing element is used to detect an overheat/fire condition in the area where
electrical harnesses and plumbing go through the engine pylon. In addition, this sensing
element is used to detect an overheat condition in the exhaust nozzle area of the engine.
Engine Fire Detection
Figure 09−10−1
Jet Pipe/Pylon Overheat Sensing Element
Figure 09−10−2
FIRE PROTECTION
Description
Vol. 2 09−10−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
ENGINE FIRE/OVERHEAT PROTECTION (CONT'D)
Fire Detection Control Units
Each heat-sensing element has its own fire detection control unit, which monitors the resistance
of its loop. When the electrical resistance decreases to the warning trip point, the fire detection
control unit prompts EICAS messages, as well as aural and visual warnings, to alert the flight
crew of a fire and/or overheat condition.
For zone A, the fire warning signal causes the following aural and visual warnings to occur:
• L (R) ENG FIRE warning EICAS message is displayed;
• MASTER WARNING switch/lights illuminate flashing;
• Applicable red LH (RH) FIRE PUSH switch/light illuminates; and
• Fire bell sounds.
For zone B, the fire warning signal causes the following aural and visual warnings to occur:
• L (R) JETPIPE OVHT warning EICAS message is displayed;
• MASTER WARNING switch/lights illuminate flashing; and
• “JETPIPE OVERHEAT” aural warning sounds.
The aural warnings can be silenced by pressing either MASTER WARNING switch/light. The
EICAS warning message will remain displayed, and the ENG FIRE PUSH switch/light will
remain illuminated, until the fire/overheat condition is corrected.
The fire detection control units can discriminate between a true fire/overheat and a short in the
heat sensing element. In the event of a fire detector loop failure, the applicable L (R) FIRE FAIL
or L (R) JETPIPE OVHT FAIL caution EICAS message will be displayed.
Engine Fire Extinguisher Bottles
Two engine Firex bottles are installed in the aft equipment bay, under the APU enclosure. The
bottles are charged with Halon 1301, and pressurized with dry nitrogen (600 to 625 psi).
Each bottle is equipped with a left and right squib (electrically actuated discharge cartridge),
thermal discharge port, pressure gauge, and a left and right discharge line. The discharge lines
are interconnected to allow discharge of both bottles (if needed) into one engine. The selection
of the LH or RH ENG FIRE PUSH switch/light will determine which squibs are fired.
The thermal discharge port provides overpressure relief for each Firex bottle. Should the
pressure in a Firex bottle exceed 1,400 psi, the thermal discharge port will discharge the
extinguishing agent in the immediate vicinity of the bottle.
FIRE PROTECTION
Description
Vol. 2 09−10−3
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
ENGINE FIRE/OVERHEAT PROTECTION (CONT'D)
Engine and APU Fire Extinguishing System
Figure 09−10−3
LH (RH) ENG FIRE PUSH Switch/Lights
The engine fire extinguishing system is controlled by the LH (RH) ENG FIRE PUSH
switch/lights.
When the LH (RH) ENG FIRE PUSH switch/light is pressed, the following occurs:
• The Firex bottle squibs are armed, both BOTTLE 1 and 2 ARMED PUSH TO DISCH
switch/lights illuminate;
• Engine generator shuts down;
• Fuel shutoff valve (SOV) closes;
• Hydraulic shutoff valve (SOV) closes;
• Bleed air shutoff valve (SOV) closes; and
• Associated engine igniters disabled.
FIRE PROTECTION
Description
Vol. 2 09−10−4
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
ENGINE FIRE/OVERHEAT PROTECTION (CONT'D)
　
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