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

mode is not annunciated to the pilots, but is logged as a maintenance item in CAIMS.
FLIGHT INSTRUMENTS
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
11−10−101
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED) (CONT'D)
EVS Ice Protection System Overview (Cont’d)
The EVS Heated Fairing is a cast body of aluminium with a heater mat bonded to the inner
surface. The heater mat has 3 zones of differing watt densities to account for the variation of
accretion and heat transfer rates along the body of the fairing.
The EVS Ice Protection System is automatically activated upon selection of either the Left or Right
Cowl Anti−Ice (CAI) switch. No additional pilot action is required to activate the EVSIPS, thus,
when either CAI switch is selected “ON”, a ground discrete from the switch is detected and the
EVSHC enters ice protection mode (IN FLIGHT ONLY). This action activates embedded heaters
within the EVS heated fairing and IRW. The heater controller then monitors the cycle with the use
of embedded RTD temperature sensors. The IRW heater operates in “running wet anti−ice”
configuration, providing sufficient heat only to prevent impinging water from freezing on contact.
This water is free to run back and freeze on the fairing. The fairing, on the other hand is cyclically
de−iced. The period of the de−icing cycle is 180 seconds. However, the duty time the heaters are
actually active within this time frame is varible, depending on the Total Air Temperature.
The heated surfaces are each monitored by two RTDs. The fairing, being cyclically heated and not
controlled to a given temperature, has two overheat detection RTDs. The IRW is controlled to a
specific temperature set point, has one control and one overheat RTD. In the case of a single
sensor failure, the remaining sensor will assume both functions.
Status information is displayed to the pilot by means of the EICAS. The EVSHC communicates
with the CAIMS, IAC and the DAU to provide failure indication and maintenance information.
IRW Demisting Control
The IRW is controlled by the EVSHC to a temperature sufficient to prevent condensation. The
EVSHC controls the activation of the demisting based on a demist set point as calculated by the
HUD based on SAT and is only active while the ISU is ON. This set point is transmitted from the
HUD to the EVSHC via the DAU on the ARINC bus. When both deice and demist conditions are
required, the higher window temperature is utilized to ensure both clear view and ice protection are
maintained.
FLIGHT INSTRUMENTS
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
11−10−102
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED) (CONT'D)
EVS Ice Protection System Architecture
GF1110_111
HFDC
Control
ASCB (Chanel A & B)
DAU 4 IAC EICAS
MADC
Anti-Ice Anti-Ice DAU 2
Right Cowl Left Cowl
Switch Switch
EVS HEATER
CONTROLLER
ARINC 429
ARINC 429
115 Vac AC Bus 1
1 , 5A CB
IR Window
Sensor
OVHT
Sensor
OVHT
115 Vac AC Bus 1
3 , 7.5A CB
EVS FAIRING
Sensor
OVHT
Sensor
Temp
Sensors
Heater
Power Temp
Sensors
Heater
Power
28 VDC Essential Bus
SSPC 2.5 ACB
Window Power Input,
115 Vac 1
Fairing Power Input,
115 Vac 3
EVS ISU
ON
EVS Control Panel
The EVS control panel is located on the left pilot’s glareshield. The EVS control panel includes the
following functions:
• HUD OFF/BRT control
• EVS OFF/MAX control
• EVS Calibration (CAL) push button
GF1110_105b
MASTER
WARNING/CAUTION
ROLL SPLRS
PLT CONT
OFF BRT
WARNING
CAUTION
ROLL
SEL
PLT
ROLL
OFF MAX
PUSH/CAL
EVS
EVS Control Knob
HUD Control Knob
HUD
Push button (short press)
− 6 sec CAL
Push button (long press)
− 22 sec CAL
FLIGHT INSTRUMENTS
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
11−10−103
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED) (CONT'D)
EVS Clear Switch
An EVS image clear switch is incorporated into the left pilot handwheel outboard of the horizontal
stabilizer trim switches. The EVS Clear Switch can be activated at any time to remove the EVS IR
image and the raster symbology from the combiner while maintaining the aircraft flight symbology
by reverting to the stroke mode. The function of removing the IR image is an aide in obtaining or
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰者手冊7(12)