(2)
Red paint stripes are applied to the main gear lower side strut and the lower downlock link. When a main gear is down and locked, the red paint stripes on the lower side strut will align with the red paint stripe on the lower downlock link (Fig. 3).
3. Control Lever Position Switch
_____________________________
A. The control lever position switch (Fig. 4) closes to complete a circuit to the landing gear electrical module when the control lever is moved to DN position. The position switch is mounted within the control lever support structure. The switch assembly consists of a low-travel microswitch and roller-type switch actuator. The roller on the actuator contacts the inner end of the control lever to operate the switch when the lever enters the DN detent.
4. Landing Gear Uplock and Downlock Sensors
________________________________________
A. Six lock sensors (proximity switches) provide signals to the landing gear warning system. The sensors are two main gear downlock sensors, two main gear uplock sensors, a nose gear lock sensor, and a nose gear down sensor.
B. Each main gear uplock sensor unit is mounted on the forward side of the uplock hook with the actuator attached to the uplock links. Each main gear downlock sensor unit is mounted on the outboard side of the side strut and utilizes an actuator fastened to the lock strut (Fig. 5). The main landing gear downlock sensors provide signals to the corresponding solid-state circuits in the landing gear module when the main landing gear is down and locked. The solid-state circuits will switch to a ground condition when furnished a signal from the downlock sensor and thus provide a ground to illuminate the green indicator light for the individual main gear. The downlock and uplock sensors provide signals to the solid-state circuits so that the appropriate circuit will provide a ground to illuminate the red warning light when the individual main gear is not locked or until the main gear position agrees with the landing gear control lever position.
C. The nose gear lock sensor (Fig. 6) is located on the nose gear lock brace assembly with the sensor on one side of the lock brace hinge pin and the actuator on the other. When the lock brace is fully extended, the sensor is moved into proximity with the actuator causing the sensor to conduct. This sends a signal to a solid state switch in the E-11 electrical module, and the switch removes a ground from the nose gear red light turning it off. The absence of a signal from the sensor will always allow a path to ground for the red light indicating that the nose gear neither in the up and locked or down and locked position.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL LOCK VIEWER TARGET AREA SEE A LOCK BRACE
LOCK LINK
LOCK LINK
FWD SEE B
FWD A BRACE LOCK
NOSE GEAR VIEWER TARGET AREA B
Nose Landing Gear Mechanical Downlock Indication Figure 2
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32-61-00
ALL ú ú 01 Page 4 ú Feb 20/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500
MAINTENANCE MANUAL
SEE A
LOWER DOWNLOCK LINK
UPPER SIDE
STRUT
LOWER
SIDE
STRUT
RED STRIP
SEE B
A
MAIN GEAR VIEWER TARGET AREA B
Main Landing Gear Mechanical Downlock Indication Figure 3
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32-61-00
ALL ú ú 01 Page 5 ú Oct 20/83
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
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本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 起落架 LANDING GEAR 3(147)
