曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

located on the center pedestal, controls the displayed information.
Engine indications are provided on the EICAS primary page. Color is used to depict normal and
non-normal ranges of operation.
The Crew Alerting System (CAS) provides visual and aural alerts as determined by the Data
Concentrator Unit (DCU) upon occurrence of a malfunction. The CAS prioritizes messages by
order of occurrence and order of importance.
Components and Operation
EICAS Control Panel
The EICAS control panel is located on the center pedestal. The panel remains illuminated
during a complete AC power failure and the PRI, STAT, STEP and CAS keys remain
operational.
EICAS Displays
The EICAS displays are computer-controlled video displays. EICAS display no. 1 (ED 1) is
installed on the left of the center instrument panel and EICAS display no. 2 (ED 2) is installed on
the right of the center panel.
The EICAS displays present system information on primary, status, synoptic and menu pages.
ED 1 displays the primary page by default. ED 2 is defaulted to the status page. Page selection
is accomplished via the ECP.
Data Concentrator Unit (DCU)
The data concentrator unit is the heart of the EICAS. The DCU collects data from various
aircraft systems, processes the information, and relays it to the proper component or display. In
a standard configuration, there are two DCUs installed in the aircraft. They are designated
DCU 1 and DCU 2. An optional third DCU can be installed, and is labeled DCU 3 as per Service
Bulletin 604–31–001.
All DCUs share in providing information to the EICAS displays. Internal switching logic
determines how the information is provided by the two (or three) DCUs. If a partial or complete
failure of a DCU occurs, system redundancy ensures that no displayed data is lost. In aircraft
with the optional third DCU, an additional level of redundancy is provided.
Data concentrator units receive inputs from the following systems:
• Engines
• Landing Gear
• Flaps
• Spoilers
• Auxiliary Power Unit (APU)
• Flight controls
AURAL/VISUAL WARNING SYSTEM
Description
Vol. 2 03−10−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
ENGINE INDICATING AND CREW ALERTING SYSTEM (EICAS) (CONT'D)
• Avionics
• Stall Protection System
• Ground Proximity Warning System (GPWS)
• Traffic Alert and Collision Avoidance System (TCAS)
• Crew Alerting System (CAS)
• Air Data Computer (ADC) altitude alerting
The DCUs process and format this information, then transmit the data on the ARINC bus to the
following:
• EICAS displays
• Lamp Driver Unit (LDU)
• Audio Electronic Control Unit (AECU)
• Flight Data Recorder (FDR)
• Maintenance Diagnostic Computer (MDC)
The two-channel lamp driver unit receives information from the DCUs and controls the
associated panel and glareshield switch/light illumination.
When a DCU generates an EICAS message, the data is sent to the LDU. The LDU then
interprets the information, and illuminates the switch/light on the appropriate control panel.
Should one channel of the LDU fail, the remaining channel continues to operate. Testing of the
LDU and panel lamps is accomplished by using the test switch located on the miscellaneous
test panel. The three−position LAMP TEST switch is spring loaded to the center OFF position.
Holding the switch to position 1 or 2 tests the associated LDU channel and lamps.
NOTE
AC power is required to perform the lamp test.
CONTROLS AND INDICATORS
Master Warning Switch/Lights
The master warning switch/lights are located on the glareshield. When the DCUs generate a
warning message, the two master warning switch/lights flash red. A triple chime always
accompanies the master warning lights and, in addition, dedicated tones or voice messages may
sound.
When the switch/light is pressed, the flashing red light and the audio alerts are reset.
Master Caution Switch/Lights
The master caution switch/lights are located on the glareshield. When the DCUs generate a
caution message, the two master caution switch/lights flash amber. A single chime always
accompanies the master caution lights.
When the switch/light is pressed, the flashing amber light is reset.
AURAL/VISUAL WARNING SYSTEM
Description
Vol. 2 03−10−3
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
Master Warning and Caution Lights
Figure 03−10−3
Aural Warning Testing
A two-position, spring-loaded to neutral AURAL WARN TEST switch is located on the
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰者604操作手冊 Operating Manual 3(29)