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part of the airplane preflight, and can be carried out at any time during normal
operation of the system.
To initiate the fire system test, press the TEST activation button on the EMS/CDU.
The command test signal is sent to the FIDEEX control unit. The crew initiated fire
test consists of:
• A periodic test of all fire/overheat loops with all flight deck reporting active
• A smoke detector test of all installed smoke detectors
When the TEST button on the EMS/CDU is selected, the FIRE TEST is automatically
highlighted on the SYSTEM TEST page.
To initiate the test, the right side button must be selected. Test will automatically
terminate after approximately 15 seconds, or can be aborted by a reselect of the FIRE
TEST key.
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUS
PREV
PAGE
NEXT
PAGE
CNTL TEST
BUS
EMER
CONT
EMS/CDU
GX_09_021 GX_09_022
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUS
PREV
PAGE
NEXT
PAGE
CNTL TEST
BUS
EMER
CONT
TEST CONTROL 1/2
FIRE TEST
STALL WARNING
AURAL WARNING TEST 1
AURAL WARNING TEST 2
LAMP TEST 1
LAMP TEST 2
TEST
OFF
OFF
OFF
OFF
OFF
9-22 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
A PIT is successful if each of the following events occur:
1. Both master WARNING lights flash and an aural warning sounds.
2. Left engine, right engine, and APU fire handles illuminate.
The following EICAS warning messages appear:
• L/R ENG FIRE
• APU FIRE
• MLG BAY OVHT
• SMOKE BAGGAGE, SMOKE FWD LAV, SMOKE AFT LAV, and SMOKE
CABIN, SMOKE CLOSET FWD, SMOKE CLOSET AFT, (if smoke detectors
are installed)
The fire test duration is approximately 10 seconds. When the fire test is completed, all
warning messages will go out, fire aural warning will deactivate, master WARNING
lights will go out, and the fire DISC handle lights will go out.
If loss of detection for either engine, APU, MWW or smoke sensing is detected by the
FIDEEX, the appropriate zone fire fail caution message will be displayed on the
EICAS until the fail condition no longer exists.
“LEFT ENGINE FIRE,
RIGHT ENGINE FIRE,
APU FIRE,
SMOKE,
GEAR BAY OVERHEAT”
GLARESHIELD
GX_09_023
TRIPLE CHIME
AURAL
MASTER
WARNING/CAUTION
WARNING
CAUTION
DISCH
PULL
1 2
L PULL
A
P
U
DISCH
1 2
DISCH
1 2
RPULL
GX_09_024
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
L-R ENG FIRE
APU FIRE
MLG BAY OVHT
SMOKE AVIONICS BAY
SMOKE BAGGAGE
SMOKE FWD LAV
SMOKE AFT LAV
SMOKE CABIN
SMOKE CLOSET FWD
SMOKE CLOSET AFT
SMOKE CLOSET
If Installed
GX_09_025
15
ITT
SYNC
15
FIRE FIRE
For Training Purposes Only
Sept 04
9-23
P I LOT T R A I N I N G GU I D E
FIRE PROTECTION
EICAS MESSAGES
789
1 . 65 L (R) ENG FIRE
APU FIRE
MLG BAY OVHT
SMOKE AVIONICS BAY
SMOKE BAGGAGE
SMOKE FWD LAV
SMOKE AFT LAV
SMOKE CLOSET FWD
SMOKE CLOSET AFT
SMOKE CABIN
SMOKE CLOSET
L (R) ENG FIRE FAIL
MLG BAY OVHT FAIL
APU FIRE FAIL
L (R) ENG FIRE FAIL
Indicates a left or right
dual loop failure, and
complete loss of fire
detection capability in
the affected engine.
APU FIRE FAIL
Indicates a dual loop
failure and a complete
loss of fire detection
capability in the APU.
MLG BAY OVHT FAIL
Indicates a left and/or
right detection system
failure.
L (R) ENG FIRE
Indicates fire has occurred
on the affected engine.
GX_09_026
APU FIRE
Indicates that an APU
fire has occurred.
“APU FIRE”
SMOKE BAGGAGE
(if installed)
Indicates a smoke
warning in the baggage
compartment.
“SMOKE”
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