(2)
The four modules (altitude, computed airspeed, true airspeed and mach) contain electromechanical devices that compute by shaft rotation, gearing, and electrical methods. The chassis is made up of solid-state electronics on printed circuit cards utilizing both discrete components and microelectronic integrated circuits. These are the power supply, failure warning circuits and the necessary amplifier, isolation and coupler circuits to complete the feedback circuits, interconnect the modules and isolate the outputs. The chassis front panel contains test switches, a display of monitor lamps and an altitude digitizer encoder readout.
(3)
Each air data computer processes input data to provide shaft rotations for 21 electromechanical output devices such as potentiometers, synchros and rate generators. Shaft position information is transferred to aircraft instruments and systems requiring air data by standard three-wire synchro outputs, two-wire ac voltage analogs and dc voltage ratios.
EFFECTIVITY
ALL 06 Page 2 Apr 25/8034-12-00
AIR TEMP PROBE NO. 1
Central Air Data Computer System - Block DiagramFigure 2 (Sheet 2)
TAT/N1 OR TAT/EPR LIMIT SYSTEM
AUTOTHROTTLE SYSTEM
FLIGHT RECORDER
GROUND PROXIMITY WARNING SYSTEM
INERTIAL NAVIGATION SYSTEM
AUTOPILOT/
FLIGHT DIRECTOR AIR DATA INSTRUMENTS
AIR TRAFFIC CONTROL TRANSPONDER
NOT USED
FLIGHT RECORDER AUTOTHROTTLE SYSTEM
AUTOPILOT/ FLIGHT DIRECTOR
AIR DATA INSTRUMENTS
AUTOTHROTTLE SYSTEM
TAT/N1 OR TAT/EPR LIMIT SYSTEM
AIR DATA INSTRUMENTS
AUTOTHROTTLE SYSTEM
INERTIAL NAVIGATION SYS
AUTOPILOT/FLIGHT DIRECTOR
TO AFFECTED SYSTEM
TAT/N1 LIMIT INDICATOR
EFFECTIVITY
CADC P/N'S 60B40126
799 Page 5 AND HG480C1
Aug 25/89
34-12-00
AIR TEMP
PROBE NO. 2 Central Air Data Computer System - Block Diagram
Figure 2 (Sheet 4)
ALTITUDE ALERT COMPUTER
INERTIAL NAVIGATION SYSTEM
AUTOPILOT/
FLIGHT DIRECTOR AIR DATA INSTRUMENTS
AIR TRAFFIC CONTROL TRANSPONDER
AIR DATA INSTRUMENTS
AUTOPILOT/ FLIGHT DIRECTOR
AIR DATA INSTRUMENTS
INERTIAL NAVIGATION SYS
AUTOPILOT/FLIGHT DIRECTOR
TO AFFECTED SYSTEM
FLIGHT ENGINEER'S TOTAL AIR TEMPERATURE INDICATOR
EFFECTIVITY
CADC P/N'S 60B40126
797 Page 7 AND HG480C1
Aug 25/89
34-12-00
AF 121,122,157,161,183,184; LH 011-030,051-070,082-099;
LH 011-030,051-070,082-099; AF 115-150,157,161,172-199;
IB 406-499; AT ALL; AZ 221-299; AT ALL; IB 406-499; GN ALL; MD ALL;
VM ALL AZ 221-299; VM ALL
CADC System - Autopilot/Flight Director Simplified Block Diagram
Figure 6
T33429
EFFECTIVITY ALL
799 Page 10
Sep 25/94
34-12-00
(4) Abnormal computing servo performance or power failure triggers a self-monitoring failure warning system within each computer. The failure warning system then activates indicators on the computer's front panel display and warns each affected instrument and system using that particular computer output.
B. Digital Air Data Computer (P/N 60B40126)
(1)
Each digital air data computer is 1/2 ATR long unit and is sectionalized into three compartments, each of which contains a group of related interchangeable modules. The front part contains the pressure transducer module section. There are two pneumatic connectors on the front panel (marked P and S) to interface with the pitot-static system. The center section contains the computer electronics and the rear section contains more electronics and the power supply. Three electrical connectors on the rear chassis panel provide interface connections between the computer and airframe rack. The computers are mounted on shelves on the electronic equipment center rack and are held in place by standard cam-lock handles.
(2)
The front panel and connector assembly are the checkout interface for the computer. It contains the electrical controls, indicators, and a wire harness which connects with the computer electronics. The controls and indicators permit flight-line checkout to test the proper function of the entire LRU. Rigidly mounted behind the front panel is the transducer module assembly and 13 plug-in modules. The front panel and connector assembly, transducer module and the plug-in modules are electrically connected with each other and with the airframe interface by a wire wrap tray and connector assembly (part of computer chassis).
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本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航1(56)
