(9)
Inertial Reference Units (IRUs) (AMM 34-21-00/001)
(10)
AIRPLANES WITH ILS RECEIVERS; Instrument Landing System (ILS) Receivers (AMM 34-31-00/001)
(11)
Multi-Mode Receivers (MMR) (AMM 34-31-00/001)
(12)
Radio Altimeter (RA) Receiver/transmitters (AMM 34-33-00/001)
(13)
Flight Management Computers (FMCs) (AMM 34-61-00/001)
E. The processing and recording of the above parameters are determined by individual airline's requirements. These can be controlled by programming in the DMU software.
F. The DMU has the following discrete inputs:
(1)
HF transceiver key event (AMM 23-11-00/001)
(2)
VHF transceiver key event (AMM 23-12-00/001)
(3)
Primary nose gear squat relay (FIM 31-01-39/101)
(4)
EICAS Event/Record switch (AMM 31-61-00/001)
(5)
AIR/GND relay (AMM 32-09-00/001)
(6)
Airborne data loader (ADL) switch (AMM 34-61-00/001)
G. The DMU collects data from airplane systems, analyzes the data, and distributes the data to the output devices. The ACMS reports are produced and can be shown on the center CDU (AMM 34-61-00/001) or can be downloaded to the following components:
(1) Quick Access Recorder
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A 747-400 MAINTENANCE MANUAL
SEE B CENTER CONTROL DISPLAY UNIT
P415 PANEL STATUS
ASEE DATA MANAGEMENT UNIT FAIL READ
E1-3 E1-5 CSEE RECORDER QUICK ACCESS
DATA MANAGEMENT UNIT
A
KEYS LINE SELECT
KEY AND MODE FUNCTION D S P L F A I L 1 4 REF FIX MENU PREV PAGE 7 INIT 2 6 8 9 5 RTE LEGS NEXT PAGE 3 NAV RAD A DEP ARR HOLD F P U K B G L Q V VNAV PROG C D H I M N R S W X EXEC E J O Y T BRT M S G F S T O
. 0 +/- Z SP DEL / CLR
B CONTROL DISPLAY UNIT (CDU) C QUICK ACCESS RECORDER
Figure 1 ACMS Component Location
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(2)
ACARS Management Unit (AMM 23-27-00/001)
(3)
Airborne Data Loader (ADL) (AMM 34-61-00/001)
(4)
Multi-input printer (AMM 45-10-00/001)
H. The DMU also transmits airplane status data to the central maintenance computer (CMC) (AMM 45-10-00/001). The CMC monitors the DMU for failure and other DMU inputs port status. The CMC messages of the ACMS can be displayed on any CDU.
I. The ACMS circuit breaker is on P415 Power Distribution Center - Right. The power supply to the DMU is 115v ac, 400 Hz single-phase power.
2. Component Details
_________________
A. Data Management Unit (DMU) (Fig. 1)
(1)
The DMU form factor is six modular concept unit (MCU). Input power is 115v ac, 400 Hz single phase.
(2)
The DMU has cooling air apertures on the top and the bottom surfaces. An airplane interface connector is located on rear of the unit. A READ switch, an ATE test connector, DMU FAIL indicator and a STATUS display are located on the DMU front panel. The READ switch is used to display stored fault codes in the STATUS display. These fault codes are used for bench maintenance. The ATE test connector is provided for connecting to external equipment. The DMU FAIL indicator comes on to indicate that the DMU has failed.
(3)
The DMU can be programmed in software for a specific airline's requirement. A wide range of user's defined algorithms and output report formats may be accommodated. Additional hardware capabilities can also be added to the unit.
(4)
The unit is located in the main equipment center on E1-3 shelf.
B. Quick Access Recorder (QAR) (Fig. 1)
(1)
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