34-62-01
AND A SINGLE FMC ú CONFIG 1 ú 04 Page 24 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
INERTIALD2161B
IRU-L-3
M1161 IRU NO. 1 D2419 EFCP-L-1
(E3-5)
DISPLAY MODE 3635VOR
EFCP-1 (P8) D2165A DAA-L-2 DME
D2179AA3B3
A5
B5
A1
B1
D1
E1
G1
H1
D5
E5
G15
H15
D7
E7
G7
H7
429RECEIVERS
G5
H5
D2179BA3B3
D1E1
G5
H5
G7
H7
G3
H3
D5
E5
D3
E3
D9
E9M1175 FLIGHT MGMTCOMPUTER (E1-2)
REFERENCE C10
DATA C11
INPUT DATA WORDS SOURCE BUS
R-1L-1,EFCP A/T-1 L-1CLK- L-2DAA- R-2DAA- R-1L-1,EFSG R-4L-4,DADC MCP-3 R-3L-3,IRU-
110 FOREIGN SELECTED COURSE102 SELECTED ALTITUDE100 LOCAL SELECTED COURSE035 DME FREQUENCY034 VOR FREQUENCY033 ILS FREQUENCY XXX XXX XXX
173 LOC DEVIATION155 DAA MAINTENANCE DISCRETES137 FLAP POSITION125 GREENWICH MEAN TIME X XX XX X
204 BARO CORRECTED ALTITUDE 1205 MACH203 ALTITUDE202 DME DISTANCE X X XXX
213 SAT211 TAT210 TAS206 CAS XXXX
270 AFDS DISCRETE WORD 2270 IRS DISCRETES260 CLOCK DATE247 TOTAL FUEL222 VOR OMNIBEARING220 BARO CORRECTED ALTITUDE 2 X XX X X X X
273 EFIS DISCRETES272 AFDS DISCRETE WORD 1272 EFIS DISCRETES311 PRESENT POSITION - LONG310 PRESENT POSITION - LAT274 AFDS DISCRETE WORD 3 XX XX XX
324 PITCH ANGLE320 MAGNETIC HEADING314 TRUE HEADING312 GROUND SPEED XXXX
356 EFIS BITE RESPONSE356 DFCS BITE RESPONSE356 DAA BITE RESPONSE356 A/T BITE RESPONSE325 ROLL ANGLE X X X X X X
366 N-S VELOCITY367 E-W VELOCITY365 INERTIAL VERTICAL SPEED361 INERTIAL ALTITUDE XXXX
SENSOR DATA A12A13
M1163 DAA NO. 1(E1-2)
D301 DFCS DATA 12
M198 DFCS MCP (P7)
D1647A BITE RESPONSE 5041
M917 AUTOTHROTTLE(E1-3)
D2167A
D2431E EFIS BITE A13B13
M1319 EFSG-1 (E2-3)
MCP-3
A/T-1
INERTIAL D2163B
REFERENCE C10
DATA C11
M1162 IRU NO. 2 (E3-5)
LOC
FUEL
EFSG-L-1
D309B DADC-L-4
AIR DATA 17
18
M196 ADC NO. 1 (E1-1)
IRU-R-3
VOR
DAA-R-2
SENSOR DATA A12
LOC
A13
M1164 DAA NO. 2(E1-2)
D714 GMT/DATE 2423
N145 CAPT'S CLOCK (P1)
D2433E EFIS BITEA13B13
M1321 EFSG-2 (E2-3)
CLK-L-1
D2421 DISPLAY MODE3635
EFCP-2 (P8)
DME
EFSG-L-1
D311B DADC-R-4
AIR DATA 17
18
M368 ADC NO. 2 (E1-1)
EFCP-R-1
FMCS Digital Inputs
Figure 6
C95232
A
737-300/400/500MAINTENANCE MANUAL
(2) Figure 6 shows all of the input data words read by the FMC.
C. FMC Digital Outputs (Fig. 7)
(1) The FMCS provides digital data to various systems. Four output buses are used. Figure 7 shows the FMC output data words, and the systems that use the words.
D. Discrete Input/Output
(1) In addition to the digital inputs and outputs, discrete signals are also input to and output from the FMC. The discretes are either 5-volts or 28-volts. These signals are buffered and translated to TTL logic levels within the FMC. Management and interpretation of these discretes is a function of the I/O processor.
E. Processor Units
(1)
There are three independent computing units within the FMC. These are the navigation processor, the performance processor, and the input/output processor. Each computing unit uses identical parallel address/data buses. These buses are independent electrically and physically. The only communication between computing elements is via a Mailbox random access memory (RAM) and interprocessor interrupts.
(2)
Navigation Processor
(a)
The navigation processor performs most of the functions associated with navigation computations. These functions are management of the CDU, and lateral and vertical steering guidance. The navigation processor uses a Central Processing Unit (CPU), which executes instructions through the use of a microprogrammed control unit. Integrated circuits are featured in both the control section and the arithmetic section.
(b)
The CPU design allows for efficient execution of floating point arithmetic. This is done through the use of microprogramming techniques and logic circuitry. The entire microprogram is stored in a semiconductor Read-Only Memory (ROM). The logic section uses integrated circuits and a multiplier element for floating point arithmetic.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 5(35)
