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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
B. A transistorized auto-on-off circuit and relay provide 115 volts ac power to the flight recorder. The transistor circuit is normally conducting when ground power is on the airplane and the airplane engines are not running. During these conditions, the relay is energized and power is not provided to the flight recorder. The relay will become de-energized thus providing power to the flight recorder, in any one of three ways. Starting either one of the airplane engines causes an engine oil pressure switch to close thus grounding the transistor and causing the relay to open. If the airplane is airborne and all engines should be shut down, a ground is provided through the ground sensing relay (AIR/GND), keeping the transistor circuit grounded and thus the flight recorder still operating. The test switch on the flight recorder test module may be used to operate the flight recorder during ground maintenance checkout.
7. Position Sensors________________
A. General
(1) The position sensors generate electrical signals which are input to the FDAU.
B. Rudder Position Sensor - The rudder position sensor is a dedicated synchro which generates electrical signals corresponding to the movement of the rudder. The sensor is connected to the rudder position crank arm mounted at rudder station 6.13.
C. Rudder Pedal Position Sensor - The rudder pedal position sensor is a synchro which generates electrical signals corresponding to the movement of the rudder pedal jack shaft. The electrical signals are sent to the FDAU and then to the flight data recorder for recording. The sensor is to the right of the rudder jackshaft. Access to the rudder pedal position sensor is through the nose wheel well compartment door 1103.
D. Aileron Position Sensors - The aileron position sensors are dedicated synchros which generate electrical signals corresponding to the movement of the ailerons. The sensors are connected to the aileron position crank arms at left and right wing stations 505.
E. Control Column Position sensor - The control column position sensor is a synchro which generates electrical signals corresponding to the movement of the control column. The electrical signals are sent to the FDAU and then to the flight data recorder for recording. The sensor is mounted at the left end of the control column pivot shaft under the captain's control column.
F. Control Wheel Position sensor - The control wheel postion sensor is a synchro which generates electrical signals corresponding to the movement of the control wheel. The electrical signals are sent to the FDAU and then to the flight data recorder for recording. The sensor is located next to the control column roll mechanism.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
G. Elevator Position Sensors - The elevator position sensors are dedicated synchros which generate eletrical signals corresponding to the movement of the elevators. The sensors are connected to the elevator position crank arms mounted at left and right elevator stations 29.5.
(1) The two elevator position sensors are identical. One sensor is on the left side of the airplane. The other sensor is on the right side of the airplane. Because the sensors are on opposite sides of the airplane, one sensor will be 180 degrees out of phase with respect to the other. This phase difference causes one signal to the flight data recorder to be positive and the other signal to be negative for the same elevator position.
H. Horizontal Stabilizer Position Sensor - The horizontal stabilizer position sensor is a synchro which generates electrical signals corresponding to the movement of the stabilizer. The sensor is connected to the stabilizer position crank arm and mounted on the aft bulkhead station 1156.
I. Speed Brake Handle Position Sensor - The speed brake handle position sensor is a synchro which generates electrical signals corresponding to the movement of the speed brake handle. The sensor is installed inside the pilot's control stand. Access to the sensor is through removable side panels of the control stand.
8. Power Distribution and Control (Fig. 4)______________________________
A. The flight recorder system receives power from the FLIGHT RECORDER AC, FLIGHT RECORDER DC, and POSITION SENSORS circuit breakers on the P18-2 panel. Power to the DFDR is supplied automatically by the GND/SENSING relay thru the control panel when the airplane is in flight. When the airplane is on the ground, power is automatically supplied through the engine no. 1 or engine no. 2 oil pressure switches when one of the engines is running or by placing the flight recorder TEST NORMAL switch in the TEST position.
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本文链接地址：737-300 400 500 AMM 飞机维护手册 仪表 INSTRUMENTS(18)
