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ú ú 08 Page 80G ú Nov 12/01
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A737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù.AIRPLANES WITH EFIS ú
22-11-01
úú 03 Page 80H ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
PITCH ATTITUDE
ROLL ATTITUDE
IRU-L-2BODY LONG. ACCEL
PITCH ATT. RATE
VERTICAL ACCEL
VERTTICAL SPEED
M1161 INERTIAL REF UNIT 1 (E3-5)
IRU-R-3
SAME AS M1161
M1162 INERTIAL REF UNIT 2 (E3-5)
ALTITUDE (UNCORR.)
BARO CORR ALT 1
DADC-L-1
BARO CORR ALT 2
MACH
COMPUTED AIRSPEED
TRUE AIRSPEED
M196 DIGITAL AIR DATA COMPUTER 1 (E1-1) MCP-1
MCP DISCRETES
MCP DISPLAY CHG
M198 DFCS MODE CONTROL PANEL (P7)
FMC ALTITUDE
FMC AIRSPEED FMC-01
V/S COMMAND
FMC MACH
FMC DISCRETES
M1175 FLIGHT MANAGEMENT COMPUTER (E1-2) A/T-1
ALTITUDE BIAS
A/T DISRETES
M917 AUTOTHROTTLE COMPUTER (E1-1)
FCC-R-2, FCC-R-3
CROSS CHANNEL DATA
M923 FLIGHT CONTROL COMPUTER B (E1-3)
Pitch Axis Digital Interface Block Diagram Figure 33
F/D COMMANDS DISCRETES SEL V/S SEL MACH SEL ALTITUDE SEL AIRSPEEDTARGET MACH TARGET SPEEDFLAP POS DFCS BITE RESP FLT PATH ANGLE RATE AIR SPEED CURSOR
CROSS CHANNEL DATA
M924 FLIGHT CONTROL COMPUTER A (E1-3)
FCC-L-1 M198 DFCS MODE CONTROL PANEL (P7)
FCC-L-2, FCC-L-3
M1319 L-EFIS SYMBOL GEN (E2-1)
M1321 R-EFIS SYMBOL GEN (E2-1)
MCP-3 M917 AUTOTHROTTLE COMPUTER (E1-1)
M1175 FLIGHT MANAGEMENT COMPUTER (E1-2)
M923 FLIGHT CONTROLCOMPUTER B (E1-3)
A
737-300/400/500MAINTENANCE MANUAL
(3)
The DADC provides several inputs. The uncorrected altitude and the baro corrected altitude are primarily used in the altitude acquire and altitude hold modes. The mach number is used in the mach trim system as well as in the pitch channel during the level change mode. The CAS and TAS signals are also used in the level change modes.
(4)
The MCP provides discrete inputs to indicate mode changes and also indicates when selectable parameters have been changed. These would include airspeed, mach, altitude, and vertical speed.
(5)
The FMC provides inputs which are used in the submodes of V NAV operation. These include altitude for the V NAV altitude acquire mode, V/S for the V NAV V/S mode, and FMC airspeed and mach for the FMC speed modes. The discretes input is used to inform the FCC of mode status.
(6)
The A/T provides an input of altitude bias for use in the altitude hold mode to reduce A/T hunting. The discretes input provides status input to the FCC.
(7)
The flight control computers exchange cross channel data for use prior to a change in command or prior to dual operation.
(8)
The FCC provides the data which will be displayed in the various MCP LCD display windows as a result of parameter changes. The discrete outputs from the FCC to the MCP provide control logic for the operation of the pushbuttons (illuminated or not illuminated). Digital data which is sent to the A/T and FMC is transmitted through the MCP to the A/T and FMC.
(9)
The FCC provides digital data to the EFIS symbol generator. The data is flight director commands and mode discretes. The symbol generators are programmed to use only the ON-SIDE FCC flight director commands.
S. BITE Operation
(1) See 22-03-10 and 22-03-11 for complete details of the DFCS BITE operation.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
22-11-01
ú ú 06 Page 80I ú Mar 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
DIGITAL FLIGHT CONTROL SYSTEM - TROUBLE SHOOTING
________________________________________________
1. General_______
A. The FMS Built-In Test Equipment (BITE) procedures in Chapter 22 are used to identify malfunctions or failures of the DFCS system. The FMS BITE includes procedures for the FMCS, DFCS, A/T, IRS, and EFIS.
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