STD 120
.535
29.29 IN260 MHDG
PRIMARY FLIGHT DISPLAY B
MTRS BARO
IN HPA STD BARO SET CONTROL
SELECTED ALTITUDE
VERTICAL SPEED
ALTITUDE
STANDARD BAROMETRIC CORRECTION
PRESELECT BAROMETRIC CORRECTION
EFIS CONTROL PANEL (EXAMPLE)
C
Air Data System - Component Location Figure 1 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 34-12-00
 ALL  ú ú 02 Page 2 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

Air Data System - Component Location
Figure 1 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 34-12-00
 ALL  ú ú 01 Page 3 ú Oct 10/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

ANGLE OF ATTACK SENSOR

Air Data System - Component Location
Figure 1 (Sheet 3)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 34-12-00
 ALL  ú ú 01 Page 4 ú Feb 10/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
E17576
A
747-400
MAINTENANCE MANUAL

ADC SOURCE SELECT RELAYS
FLIGHT INTERPHONE JACK AND ATTITUDE SENSOR ASSEMBLY
SEEJ K RIGHT ADC (E2-3) LEFT ADC (E1-2) CENTER ADC (E1-3)
SEE L
PITOT CONNECTOR
GEAR DOWN  FIFTH ENGINE 
DISPATCH  CARRIAGE  STATIC 
CONNECTOR 
SWITCH  SWITCH  MONITER INPUT SIGNAL SINGLE DIGIT  INDICATOR FAILURE BALL TYPE 
GUARD  GUARD 
TEST  TEST ONLY  FUNCTIONAL 
CONNECTOR  TEST SWITCH 
SWITCH  SWITCH 
HANDLE 

NORMAL NORMAL VMO VMO
GEAR DOWN DISPATCH FIFTH ENGINE CARRIAGE
AIR DATA COMPUTER SWITCH SWITCH L JK
Air Data System - Component Location Figure 1 (Sheet 4)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 34-12-00
 ALL  ú ú 01 Page 5 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 2) FMC/TMC
 3) EIU
 4) FCU
 5) YDM
 6) IRU

 (5) The No. 5 bus supplies test only data output.
 2.  Air Data Computer_________________
 A.  The air data computer provides the air data information required by the integrated display system and other interfacing systems. The ADC outputs are computed functions of altitude, airspeed, angle of attack, Mach, and temperature. The outputs are derived from inputs from the pitot-static system, angle of attack sensor, total air temperature probe, and barometric correction. The ADC processes the input data and outputs the air data information in serial form on four identical digital buses.
 B.  The ADC is of modular construction and consists of two pressure sensor modules, four plug-in circuit card assemblies, a plug-in power supply assembly, and a chassis assembly. The ADC front panel provides pitot and static pressure input connectors, an external fault LED display, an ADC fail annunciator, and a functional test pushbutton switch. A TEST ONLY connector on the ADC front panel provides monitoring of the No. 1 ARINC 429 output bus.
 C.  All three air data computers are located on the electrical equipment racks in the main equipment center. The left computer (B163) is on shelf No. 1 and the center computer (B166) is on shelf No. 3 of electrical equipment rack E1. The right computer (B164) is on shelf No. 3 of electrical equipment rack E2.
 3.  Angle of Attack (AOA) Sensor____________________________
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 導航 NAVIGATION 1(83)