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庞巴迪挑战者300公务机机组操作手册 Bombardier Challenger-防火(7)

时间:2011-11-12 06:09来源:蓝天飞行翻译 作者:公务机
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When the electrical resistance decreases to a trip point, electrical current from the live internal wire conducts to the second internal wire and a fire indication is generated.
This dual loop system minimizes the possibility of false fire warnings. Both loops must sense the fire or overheat condition under exacting parameters before flight deck fire indications are generated.
CFO0901002_003
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
09-01-08 AUXILIARY POWER UNIT FIRE PROTECTION (Cont)

FIRE EXTINGUISHER BOTTLE
Discharge of bottle 2 to the APU compartment is controlled exclusively by the cockpit APU FIRE switch during flight. Discharge to the APU on the ground can be commanded by either the cockpit switch or automatically by the FIREX-CU during APU unattended mode operation. For both the main powerplants and APU, two switches are required to discharge the extinguisher. The first switch is a guarded latching switch that shuts down and isolates the engine/APU and arms the corresponding discharge cartridges on the bottle(s). The second switch is a momentary switch that applies discharge current to the selected cartridge. A pressure switch, a pressure gauge and one explosive squib for the APU, is installed on the fire bottle. The bottle is filled with Halon 1301.
APU FIRE SWITCH
If a fire is detected in the APU enclosure, the APU FIRE switch illuminates (along with the master warning light, the master warning chimes, an APU FIRE (W) CAS message, and the aural APU FIRE). When the APU FIRE switch is depressed:
-Bottle 2 squib is armed and EXT 2 switch illuminates ARMED
-APU fuel shutoff valve closes
-APU electronic control unit closes the APU fuel metering valve
-APU bleed-air shutoff valves closes
-APU generator is selected offline

Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
09-01-09 MAIN LANDING GEAR OVERHEAT DETECTION

DESCRIPTION
The Challenger 300 includes two main landing gear bays (MLG), also referred to as main wheel wells. due to the possibility of brake or tire overheat during takeoff and the fact that the MLG bays are constructed from composite material, an overheat detection system has been installed as part of the aircraft’s FIREX system.

Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
09-01-10 MAIN LANDING GEAR OVERHEAT DETECTION (Cont)

COMPONENTS AND OPERATION DETECTION LOOPS
The main landing gear bay is protected by a single overheat detection loop for each main landing gear bay and a dual channel overheat detection unit. Each overheat sensing loop is installed around the top of the inner surface of each main wheel bin.
The overheat detection loops are connected to the Fire Detection and Extinguishing control unit (FIREX-CU). The loops are constructed of an outer metal sheathing and two internal wires that are separated by an insulating material (thermistor). One of the wires carries electrical current, the other is grounded to the outer sheathing at the control unit. The resistance of the thermistor decreases with an increase in temperature.
 
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