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Volume 2 Flight Crew Operating Manual May 06/2005
09-01-02 CSP 100-6 REV 2
INTRODUCTION (Cont)
CFO0901002_007
ENGINE FIREDETECTION
APU FIREDETECTION
MAIN LANDING
GEAR (MLG)
OVERHEATDETECTION
FIREDETECTION-
ANDEXTINGUISHING
(FIREX)
CONTROL UNIT
ENGINE
INDICATION
AND CREW
ALERTING
SYSTEM
AUDIO
INTEGRATING
SYSTEM
(EICAS)
SYSTEM
SYSTEM
SYSTEM
FIRE DETECTION SYSTEM — BLOCK DIAGRAM
EV 2
FIRE PROTECTION
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 09-01-03
FIRE PROTECTION SYSTEM OVERVIEW SCHEMATIC
CFO0901002_002
ENGINE
L ENG
FIRE FIRE
2
ARMED
1
ARMED
APU
ON ON
FIRE EXT
IGNITION AUTO SYNC MACH HOLD
N1
OFF N2
EVENT
OFF
AUTO APR
OFF
R STARTER
CRANK START
OFF
CRANK START
L STARTER
R ENG
FIRE
FIRE
600 600
93.0 61.0
NI
MACH
HOLD
VIB VIB
ITT
IGN IGN
N2
OIL PRESS
OIL TEMP
FF PPH
84.7
46
115
7300
84.7
46
115
7300
APU RPM 300
APU EGT 250
FUEL QTY LBS
TOTAL 12000
6000 6000
STA
RT
START
STAB AIL
LWD RWD
RUD
L R
NU
ND
6.6
FLAPS 0 GEAR
CAB ALT
CAB RATE
7300
1000
FUEL
MFD CONTROL
COM1 NAV1 ATC1/TCAS ADF1 HF1 COM3 COM2
118.000 108.00 1200 1799.5 118.000 118.000
118.000 108.00 STBY 190.0 2.0000 118.000 118.000
ABV
TX
UP
O
DN
2.0000 AM
85.0 MCT 85.0 MCT TRIM
V T
FUEL USED
3900 LBS
135 ° C 135 ° C
43° C
4870 LBS 4870 LBS
TOTAL FUEL
9700 LBS
P P
25 25
APU
SPOILERS
L ENG FIRE
R ENG FIRE
APU FIRE
1
2
3
5 6
7 8
9 10
11
DCU
FIREX
CONTROL UNIT
LEFT GEAR RIGHT GEAR
LH ENGINE RH ENGINE
APU COMPARTMENT
WARNING
CAUTION
WARNING
CAUTION
AFFECTED
AREA
AFFECTED
AREA
AFFECTED
AREA
AFFECTED
AREA
4
1. ENGINE Panel.
2. Master WARNING/CAUTION
LIGHTS.
3. Left MFD EICAS display.
4. FIREX Control Unit.
5. Left Main Wheel Well Overheat
Detection.
6. Right Main Wheel Well Overheat
Detection.
7. Fire Extinguisher Bottle No. 1.
8. Fire Extinguisher Bottle No. 2.
9. Left Engine Compartment Discharge
Lines.
10. Right Engine Compartment Discharge
Lines.
11. APU Compartment Discharge
Lines.
FIRE PROTECTION
Volume 2 Flight Crew Operating Manual Sep 13/2004
09-01-04 CSP 100-6 REV 1
ENGINE FIRE DETECTION
DESCRIPTION
The engine fire detection system functions by detecting an overheat condition on the exterior of the engine.
If a fire is detected in the engine, the affected L or R ENG FIRE switch illuminates along with the master warning light,
the master warning chimes, a L or R ENGINE FIRE (W) CAS message, a FIRE EI red in the N1 indicator, and the aural
LEFT or RIGHT ENGINE FIRE.
The engine fire extinguishing system includes two bottles. If required, both bottles can be discharged into either engine.
COMPONENTS AND OPERATION
DETECTION LOOPS
Each engine is installed with dual fire detection loops. The loops provide fire detection around the core engine area, engine
accessory area, forward nacelle and pylon areas. The 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.
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 loop system minimizes the possibility of false fire warnings. Both loops must sense the fire or overheat condition under
similar parameters before flight deck fire indications are generated.
FIRE DETECTION AND EXTINGUISHING CONTROL UNIT
The fire detection and extinguishing control unit is the aircraft fire protection system electronic control unit that monitors
the electrical resistance of the loops. The control unit is located in the aft equipment bay. When both loops experience the
　
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