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 C.  The control lever position switch is mounted in the control lever support channel behind the control lever. The switch is actuated by the inner end of the control lever as the inner end drops into the detent. For more information on the switch, refer to 32-61-00, Landing Gear Position Indicating and Warning System.
 5.  Landing Gear Control Lever Lock System______________________________________
 A.  The landing gear control lever lock system prevents the control lever moving past OFF position from DN selection until airplane weight is off landing gear. The control lever lock control consists of a mechanical lock operated by a lock solenoid (Fig. 4). The lock solenoid is controlled by a safety relay operated by solid state circuits through the air safety sensor. The system operates on 28 volt dc power from a circuit breaker on panel P6. The control lever is normally released only when the solenoid is energized.
 B.  The landing gear safety relay controls the power for the lock solenoid. The relay is installed in the landing gear electrical module located in the electrical/electronic compartment. For more information on the relay, refer to AMM 32-09-00.
 C.  The landing gear air safety proximity switch controls the landing gear relay. When the airplane weight is on the landing gear, the sensor operates through solid state circuits to de-energize the relay. Spoiler linkage driven by a teleflex cable from the extension and compression movement of the shock strut operates the switch. For more information on the switch, refer to AMM 32-09-00.
 6.  Landing Gear Transfer Valve___________________________
 A.  The landing gear transfer valve normally ports hydraulic pressure from system A to the landing gear. Should hydraulic pressure be lost, the valve will automatically connect hydraulic system B to the landing gear. Hydraulic operation of the gear may thus be accomplished without manual override.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

737-300/400/500MAINTENANCE MANUAL 
GEAR DOWN CONTROL CABLE LGVB  ROLLER  COMPRESSION SPRING  CONTROL LEVER DRUM INNER SHAFT OUTER SHAFT  LANDING GEAR CONTROL LEVER 
GUIDE 
LOCK STOP 
CONTROL GEAR UP CABLE LGVA  OVERRIDE TRIGGER 
CONTROL LEVER LOCK  LOCK SOLENOID 
LEVER IN DOWN POSITION 

LEVER INNER END OUT OF DETENT

OVERRIDE TRIGGER PULLED TO ALLOW INNER
END OF LEVER TO CLEAR LOCK STOP

Landing Gear Control Lever Schematic
Figure 3

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

NOTES:_____ 1.  SWITCH CONTACTS ARE CLOSED WHEN CONDITION IS AS INDICATED BY SWITCH TITLE
2.  SWITCHES ARE REPRESENTATIVE ONLY AND MAY BE CONVENTIONAL SWITCHES OR PROXIMITY SWITCHES
Landing Gear Control Lever Lock Control Logic Flow Diagram
Figure 4

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A 737-300/400/500MAINTENANCE MANUAL
 7.  Flow Limiter Bypass Valve
_________________________
 A.  A flow limiter and a bypass valve are installed in the landing gear hydraulic supply downstream from the transfer valve. The bypass valve is normally open and permits fluid to bypass the flow limiter. Under certain air mode conditions with high hydraulic fluid flow requirements, the bypass valve closes to give priority to the wing leading edge autoslat extension. This limits flow to the landing gear. When the flow requirments decrease, the bypass valve opens and the landing gear system returns to normal.
 8.  Operation
_________
 A.  When the control lever is pulled, the inner end is raised from a detent to free the lever for movement into another position. Moving the lever up or down rotates a cable drum to operate cables running from a quadrant above the left wheel well ceiling. As the quadrant rotates, it operates the landing gear selector valve on the underside of the ceiling through a shaft, lever, and an adjustable link. Releasing the landing gear lever when the desired position has been selected allows the lever end to drop into a detent and so hold the lever in position. In DN position, the lever end operates a control lever position switch for the indicating and warning system.
　
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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 2(47)