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

PM-132A 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-132A
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-132A 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
and storage for up to twelve pre-set channels for the VHF COM and
VHF NAV functions. Cross-side operation, maintenance display, power
on self-test and pilot activated self-test and optional FMS radio tuning
features are also available on each RMU. Each RMU also provides
backup engine and navigation display facilities in the event of EFIS/EICAS
failure. Automatic presentation of engine data occurs on RMU #1
if neither IC-600 is providing EICAS data.
There are six line select keys on each side of the RMUs (Figure 5-15).
The top key is referred to as a transfer button and has directional arrows
on them. The remaining keys are referred to as line select keys.
There are also eight function keys located at the bottom of the RMUs.
The RMU main tuning page is divided into six dedicated windows.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：BOMBARDIER_Learjet_0-Flight_Controls_and_Avionics(23)