-ON BAT
-
ADR OFF
-
ADR FAILURE WARNING
-
IR FAILURE WARNING
-
IR ALIGN.
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4. Component Description
_____________________
A. ADIRS CDU (Ref. Fig. 005) The CDU is a three-channel unit. Each CDU channel includes the following features:
-a three-position mode selector switch. The modes are:
. power off (OFF)
. navigation (NAV)
. reversionary attitude (ATT)
-
an indicator announcing when the IR is aligning (ALIGN legend of IR annunciator)
-
an IR fault indicator (FAULT legend of IR annunciator)
-a pushbutton switch to disable ADR output buses. It is a momentary action pushbutton switch
-
an indicator announcing when the ADR output buses are turned off (OFF legend of ADR pushbutton switch)
-
an ADR fault indicator (FAULT legend of ADR pushbutton switch). The following items of equipment are shaped between the three channels :
-a keyboard to enter the initial position in degrees, minutes and tenth of minutes or magnetic heading in the attitude mode
-two data pushbutton switches (ENT and CLR) with cue lights
-
a liquid crystal display for selected parameters. The LCD has 16 digits and each digit has 14 segments
-
a DATA DISPLAY selector switch to select parameters for display on the LCD:
*
wind (WIND)
*
present position (PPOS)
*
true heading (HDG)
*
status of selected system (STS)
*
track and ground speed (TK/GS)
*
test values (TEST)
-
a SYS DISPLAY selector switch with four positions: OFF, 1, 2, 3. The OFF position disables the display of the CDU but the mode control of the ADIRUs remains active
-an ON BAT annunciator.
The CDU contains three identical connectors referenced J1, J2 and J3.
(Ref. Fig. 006)
This LRU uses an Intel 8031 microprocessor. The CDU receives an IR bus
from each ADIRU to display navigation data.
It provides one bus per ADIRU to permit IR initialization.
(Ref. Fig. 007)
No cooling air is provided to the CDU.
The CDU is supplied with 28VDC from the selected ADIRU to drive internal
circuits and the data display. The 28VDC inputs are isolated from each
other. The aircraft supplies 5VAC power for panel lighting/LCD
backlighting and for annunciator lighting.
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ADIRS CDU
Figure 005
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ADIRS CDU - Identical Connectors
Figure 006
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ADIRS CDU - Internal Block Diagram
Figure 007
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B. ADIRU (Ref. Fig. 008)
(1)
General The ADIRU is contained in a 4 MCU case as defined in ARINC 600. The ADIRU has to be aligned on a special shelf in the avionics compartment in accordance with the installation design described in ARINC 738. This installation involves modification of the ARINC 600 standard to include three alignment pins and a floating connector. Pins 12 and 13 of the bottom plug have been modified with a reducer to accept power input instead of coax input as defined in ARINC 738. All input discretes are electrically isolated by an in-line diode or an equivalent device. The discrete outputs are protected by means of diodes to permit a wired OR circuit with other outputs. The ADIRU is designed to reach a high level of protection for lightning and Electromagnetic Interference (EMI). The lightning protection circuitry is made up of discrete components which consist of high-powered Zener diode type semiconductors called Transzorbs. Varistors are used on the power supply input lines. Varistors are voltage-controlled resistors that go to a low impedance state when a voltage above their clamp voltage is applied, thus shunting the lightning current. As each ADIRU is a common point to all engines installed on the aircraft, special care is taken to make impossible any electrical disturbance to propagate through the ADIRU/engine interface to other inputs/outputs dedicated to engines. The ADIRU contains an ADR and an IR portion supplied by a common power (115VAC, 28VDC).
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