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On the ground, the FADEC will automatically shut down the APU if a fire signal is received for at
least 5 seconds and the APU fire handle is not pulled. Although the APU will automatically shut down
if a fire is detected, there is no automatic discharging of the fire extinguishing agent. Therefore, the
APU must not be left unattended for ground operations.
The APU fire detection is self contained within the APU compartment. The detection system consists
of the following:
• Fire loop elements inside the compartment for fire detection.
• Flight deck indication (red) through the fire handle and shut down signal to the APU FADEC.
• Aural fire warning on the flight deck.
• Automatic APU shut down on the ground, if necessary.
GF0910_017
DUAL LOOP
SENSING ELEMENT
STRUT SENSING
ELEMENT
The APU fire detection is provided by a dual loop system; each loop consists of sensing elements.
Two element pairs are mounted directly to the airplane structure and the other element is mounted to
a support tube.
FIRE PROTECTION
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
09−10−13
APU COMPARTMENT FIRE DETECTION (CONT'D)
The APU compartment is protected by a two shot fire extinguishing system. Each discharge is
independently directed by the pilot, with provision to guard against accidental discharge of both
extinguishers into the APU.
GF0910_018
APU LOCK
RELEASE PIN
DISCH
PULL
1 2
On the APU fire handle assembly, there is an additional lockout release pin located on the front
panel. This release pin must be moved in conjunction with twisting the handle in order to discharge a
second shot into the APU. The additional step for the APU is deemed necessary to preserve one
shot for possible engine fire.
APU FIDEEX CONTROL SCHEMATIC
GF0910_019
EICAS
AUDIO
CONTROL
PANEL
IAC
APU FIRE
HANDLE
APU LOOP A
APU LOOP B
APU FIRE
APU COMPARTMENT
STRUT SENSING ELEMENTS
HATCH SENSING ELEMENTS
EDUCTOR SENSING
ELEMENTS
FIDEEX
CONTROL
UNIT
"APU FIRE"
D
A
U
When a fire is detected, the APU fire warning handle will illuminate, MASTER WARNING lights will
illuminate, a warning message will appear on EICAS and a voice message “APU FIRE” will sound.
The APU fire loop elements send their information to the FIDEEX control unit. The FIDEEX control
unit in turn sends information to the DAU. The DAU reports the status of the detection system to the
IAC which signal the EICAS and audio control panel of the warning condition.
FIRE PROTECTION
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
09−10−14
APU FIDEEX/FADEC INTERFACE
The fire loop elements inside the APU compartment detect a fire and send this information to the
FIDEEX control unit. The FIDEEX control unit in turn sends information to the APU FADEC which
commands an APU shut down.
NOTE
If APU fire is detected on the ground and the fire handle signal (pulled)
is not detected within 5 seconds, the FADEC will command an auto
shut down of the APU.
During normal APU operation, the APU FADEC signals the fuel management system to open the
APU SOV. If an APU fire were detected and the APU fire DISCH handle pulled, the FIDEEX control
unit will close the APU SOV.
APU FIDEEX/FADEC CONTROL SCHEMATIC
FIDEEX
CONTROL
UNIT
APU
FADEC
APU FIRE
APU SHUT DOWN
APU
SOV
FIRE ELEMENT
APU COMPARTMENT
FLIGHT COMPARTMENT
APU
GF0910_020
DISCH
PULL
1 2
When the APU DISCH fire handle is turned, a command is send to the FIDEEX control unit to
discharge the fire bottle. The EICAS will display the result of the extinguisher discharge.
FIRE PROTECTION
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
09−10−15
MAIN WHEEL WELL (MWW) OVERHEAT DETECTION
The main landing gear bays can be subjected to overheat conditions due to brake/tire overheat or
fire. The MWW overheat detection is provided by a single loop system for each main wheel well (left
and right); each loop consists of one sensing element. The sensing elements are mounted in the
vicinity of the brakes on the top surface of each MWW bin.
The FIDEEX control unit continuously monitors the heat sensing elements in the main landing gear
area. Any overheat condition or system fault detected by the monitoring system is annunciated on
EICAS in the form of a main landing gear bay overheat warning message, overheat fail caution
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