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Bottle No.1
Fire Extinguisher
Bottle No.2
Left Engine
Compartment
Discharge Lines
Right Engine
Compartment
Discharge Lines
APU Compartment
Discharge Lines
GX_09_002
MASTER
WARNING/CAUTION
ROLL SPLRS
PLT CONT
ROLL
SEL
PLT
ROLL
WARNING
CAUTION
DIM
OFF
BRT
HUD
MASTER
WARNING/CAUTION
ROLL SPLRS
CPLT CONT
ROLL
SEL
CPLT
ROLL
WARNING
CAUTION
TOTAL FUEL (LBS) 4155O
1.54
146OO 1OOOO 146OO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4
575O
115
81
1.65
CRZ
EPR
I
G
N
START START
I
G
N
ND
STAB
1.54
1.65
73.3
T/O
N1
SYNC
73.3
789
ITT
SYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL RUDDER NR
AIL
LWD RWD
7.2
NU
93.4
575O
115
81
235O
9-4 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
FIDEEX CONTROL UNIT
All interfaces from the airplane’s power and fire handles pass through the FIDEEX
control unit before they reach the fire extinguishers. The FIDEEX control unit is
located under the baggage compartment floor. The following functions/components
are monitored continuously:
• Continuity of the squib circuits
• Continuity of the pressure switches
• Existence of 28 VDC on the two fire extinguishing power supply lines
The FIDEEX control unit is divided into two redundant channels (A and B). The
channels power and monitor both loops of the main engines and APU, and each of the
MWW loops. Both channels independently determine the presence of a fire or
overheat condition. The FIDEEX control unit performs internal and operator initiated
built-in tests, and reports all health and status to the flight compartment EICAS
system.
R ENGINE SQUIB 2
APU SQUIB 2
L ENGINE SQUIB 2
PRESSURE SWITCH
R ENGINE SQUIB 1
APU SQUIB 1
L ENGINE SQUIB 1
PRESSURE SWITCH
A B
MAIN WHEEL WELLS
LEFT ENGINE APU RIGHT ENGINE
FIDEEX CONTROL UNIT
Pressure Gauge
and Switch
DISCHARGE
CHECK VALVES
TO RIGHT ENGINE
TO APU
TO LEFT ENGINE
BOTTLE #1 BOTTLE #2
Fire Loop
Unit
GX_09_003
For Training Purposes Only
Sept 04
9-5
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
MAIN ENGINE FIRE DETECTION
Main engine fire detection is provided by a dual loop system. Each loop (loop A and
loop B) consists of three sensing elements, located on the accessory gear box, under
the engine core, and along the fixed cowl. In order for a fire to be detected, at least one
sensing element from each loop must detect the fire. When both loops indicate a fire
condition, the FIDEEX will forward that information to the DAUs and the IACs
(should one loop develop a short, the FIDEEX isolates that loop and now relies on the
remaining loop for the detection of a fire).
The DAUs and IACs will illuminate the applicable engine fire DISCH handle, flash
the master WARNING lights, generate a warning message on EICAS and a FIRE
indication on the applicable ITT gauge, and generate a LEFT or RIGHT ENGINE
FIRE voice message.
Sensing elements are located on the following areas:
• Accessory gear box
• Engine core
• Fixed cowl
Fixed Cowl Mounted
Fire Detector and
Support Rail
Gear Box Mounted
Fire Detector and
Support Rail
(wire is hidden from view)
Core Engine
Fire Detector
GX_09_004
9-6 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
ENGINE FIDEEX CONTROL SCHEMATIC
The engine fire loop elements send their information to the FIDEEX control unit. The
FIDEEX control unit in turn sends information to the DAU. In the event of a fire, the
DAU will signal the applicable engine fire DISCH handle to illuminate. The DAU
reports the status of the detection system to the IAC which provides warning
conditions to the EICAS, and audio control panel.
FIXED COWL
MOUNTED FIRE
DETECT
GEARBOX MOUNTED
FIRE DETECT
CORE ENGINE FIRE
DETECTOR SENSOR
L ENGINE
FIRE
HANDLE
“RIGHT ENGINE FIRE”
“LEFT ENGINE FIRE"
AUDIO
CONTROL
PANEL
IAC
EICAS
R ENGINE
FIRE
HANDLE
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
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庞巴迪挑战者手册5(109)
