曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專營(yíng)店坑蒙拐騙欺詐消費(fèi)者

DU #2 and DU #3 displays, reversing the MFD and EICAS display locations.
Placing the reversion selector to the PFD position on either side
causes the PFD format to move to the inboard display tube on that side
and the outboard display to blank.
It is important to note that when selecting display unit reversion, the
bezel controllers on DU #1 and DU #4 continue to work with the PFD
display when it is transferred to an inboard display unit. The airplane
master warning/caution lights are also located on the display unit reversion
panels.
DU 2
NORM
PFD
CAUT
WARN
DU 3
NORM
CAUT
WARN
OFF
EICAS REV PUSH
PFD
EICAS REV PUSH
DISPLAY UNIT REVERSION PANELS
Figure 5-13
Pilot’s Manual
PM-126A 5-49
DATA ACQUISITION UNITS (DAUs)
There are two dual channel data acquisition units (DAUs) installed in
the tailcone equipment area of the airplane. The DAUs receive engine
and airplane systems sensor information and pass it, primarily, to the
IC-600 computers. Both channels of DAU #1 provide left engine data
and both channels of DAU #2 provide right engine data. For redundancy,
both channels of each DAU independently convert on-side engine
information to a common ARINC 429 data bus format and send it to
both IC-600s. The IC-600s process the information and send it to the selected
display unit (normally DU #2) for EICAS display. In addition to
engine information, the DAUs also collect analog data from other airplane
systems such as fuel, hydraulic and accumulator pressure, dc
electrical power, flight control settings, cabin pressure settings/indications,
and oxygen temperature/pressure.
A three-position DAU reversionary switch is provided on the reversionary
control panel located below DU #2 (Figure 5-14). The switch positions
are labeled A, DAU NORM, and B. With the switch in DAU
NORM, both IC-600s use Channel A from the left DAU and Channel B
from the right DAU for engine/systems displays. In the reversionary
positions (A or B), each IC-600 uses only the selected channel from both
DAUs.
IC/SG NORM
AHRS NORM
ADC NORM
DAU NORM
1 2
1 2
1 2
A B
REVERSION
REVERSIONARY CONTROL PANEL
Figure 5-14
Pilot’s Manual
5-50 PM-126A
If either channel of either DAU should fail, if either A or B reversion is
selected, if an engine or system miscompare is detected, an appropriate
CAS will illuminate.
The following CAS illuminations are specific to the DAUs:
The DAU circuit breakers are located in the INSTRUMENT/INDICATIONS
group on each circuit breaker panel. On the left side is DAU 1
CH A and CH B, and on the right side is DAU 2 CH A and CH B.
DAU 1 CH A and DAU 2 CH A are powered by the EMER BATT bus.
DAU 1 CH B and DAU 2 CH B are powered by the L and R essential
buses respectively.
CAS Color Description
DAU 1A-1B FAIL Amber Channel A and/or B of the #1 Data Acquisition
Unit (DAU) has failed.
DAU 2A-2B FAIL Amber Channel A and/or B of the #2 Data Acquisition
Unit (DAU) has failed.
DAU A REV White Reversion of both Data Acquisition Units
(DAUs) to Channel A is selected by the crew.
DAU B REV White Reversion of both Data Acquisition Units
(DAUs) to Channel B is selected by the crew.
DAU ENG MISCMP Amber The associated (L or R) Data Acquisition Unit
(DAU) has detected a miscompare between
channel A and B involving an engine parameter
(N1,N2,ITT).
DAU SYS MISCMP Amber The associated (L or R) Data Acquisition Unit
(DAU) has detected a miscompare between
channel A and B involving a system parameter
(dc voltage, Emergency Bus voltage, dc
amperage, Battery temperature, Main
Hydraulic pressure, Brake Accumulator pressure,
Oxygen temperature and pressure).
LBS/KGS CONFIG Amber The configuration of the integrated avionics
computer is not compatible with that of the
data acquisition unit (i.e., one is configured
for pounds while the other for kilograms) on
the ground.
LBS/KGS CONFIG White The configuration of the integrated avionics
computer is not compatible with that of the
data acquisition unit (i.e., one is configured
for pounds while the other for kilograms) in
flight.
Pilot’s Manual
PM-126A 5-51
RADIO MANAGEMENT UNITS (RMUs)
The two RM-855B Radio Management Units (RMUs) provide the central
controlling functions for the entire basic radio system. Each RMU
is a color, active matrix, Liquid Crystal Display (LCD) based unit. The
primary function of each RMU is to select and control the frequencies
and operational modes of each radio. Each RMU also provides access
　
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：Bombardier_Learjet-Flight_Control_Systems_and_Avionics(23)