EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
22-11-01
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A 737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
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A
737-300/400/500MAINTENANCE MANUAL
(4)
Engage logic is processed both in MCP and the FCC. Hydraulic solenoids in A/P actuator are energized to activate A/P control. Mode selection is determined as a function of both the FCC and the MCP.
(5)
The FCC provides a digital output to a EFIS symbol generator to provide a visual display of the selected mode and status on the EADIs. Each mode is processed by A/P pitch command computer. The pitch command is converted to a analog signal. The signal is then amplified and applied to the elevator actuator. Elevator actuator position (LVDT) is returned as a feedback signal. The elevator position sensor is used prior to engaging the A/P to synchronize the FCC A/P actuator with surface position. The actuator in turn mechanically provides an input to the power control unit which hydraulically and mechanically operates the ailerons.
(6)
The FCC also provides outputs to the stabilizer for maintaining proper pitch attitude. A combination of stabilizer position and elevator output command is used to determine when the stabilizer should be repositioned. The output to the mach trim actuator is used to reposition the elevators as a function of mach number. This is accomplished by mechanical connections to the elevator feel and centering unit. The neutral shift sensor provides feedback to determine the elevator neutral position for a given stabilizer position.
(7)
A/P actuator monitor (AAM) monitors command versus response of the elevator actuator. The surface position monitor (SPM) monitors relative motion between elevator actuator position and elevator surface position.
(8)
The F/D signal processing is very similar to the A/P signal processing. A command mode logic is used, however, the F/D command processing is accomplished as a separate control. The digital output is sent to a EFIS symbol generator which processes the signal to be displayed on the respective EADI.
Q. Pitch Axis Analog Interface (Fig. 32)
(1) The Analog Interface diagram illustrates the various LRU's which are associated with the generation and implementation of logic and command signals used using pitch axis modes of operation. All of the signals are converted from analog to digital for inputs and digital to analog for outputs.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
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ú ú 07 Page 80D ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù.AIRPLANES WITH EFIS ú
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úú 05 Page 80E ú Nov 12/01
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FCCA-DC
FCC A ENGA DC M980 AUTO SPEED BRAKE MOD (E3-2)
M924 FLIGHT CONTROL COMPUTER A (E1-3) Pitch Axis Analog Interface Block Diagram Figure 32
A
737-300/400/500MAINTENANCE MANUAL
(2) The following is a breakdown of the various inputs and their relationship to pitch axis operation.
(a)
Cross channel disconnect B is a 28 volt dc logic signal to inform one channel that the other has disengaged. The LCL channel is disengaged when the signal is present.
(b)
The pitch equalization signal is used as a comparison between Elevator Actuator A and B feedback for dual autoland operation.
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