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 B.  When the right main gear shock strut is compressed by airplane weight on the gear, a circuit opens to de-energize the landing gear safety relay. When de-energized, the relay opens contacts, cutting off power to the lock solenoid. The control lever lock then moves into locked position. When the shock strut extends, the proximity switch closes and the reverse sequence of operations energizes the lock solenoid to release the lock. The lock solenoid remains energized when gear is retracted and electrical power is on the airplane. An override trigger permits the lever to bypass the lock if a malfunction of the system causes the lock to engage.
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 32-31-00
 ALL  ú ú 01 Page 7 ú Jun 25/85
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 LANDING GEAR CONTROL SYSTEM - TROUBLE SHOOTING
______________________________________________
 1.  General
_______
 A.  This procedure covers all landing gear control system components (control handle, control cable, and selector valve) with exception of the control handle lock which is covered in 32-31-21, Control Lever Lock System -Trouble Shooting.
 B.  Trouble shooting is accomplished by performing an operation check of gear control handle and monitoring of hydraulic pressure at selector valve. Operate lock override mechanism (override trigger on handle) as required to clear lock stop when moving control handle. Airplane jacking or gear operation is not necessary in procedure.
 2.  Preparation for Trouble Shooting
________________________________
 A.  Check that landing gear control handle is in OFF position.
 B.  Check that landing gear ground lock assemblies are installed (Ref 32-00-01).
 WARNING: CHECK THAT GROUND LOCK ASSEMBLIES ARE INSTALLED IN ALL LANDING GEAR
_______ TO PREVENT INADVERTENT OPERATION OF GEAR. INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT COULD RESULT IF GEAR RETRACTS.
 C.  Pressurize hydraulic system A (Ref 29-15-00, MP).
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
No hydraulic pressure pulse is detected at selector valve DN port outlet hose when control handle is moved from OFF to DN position. Check control cable linkage to selector valve for proper adjustment. IF -
OK - Replace landing gear control NOT OK - Adjust cable per 32-31-0. selector valve per 32-31-51.
No hydraulic pressure pulse is detected at selector valve UP port outlet hose when control handle is moved from OFF to UP position. Check control cable linkage to selector valve for proper adjustment. IF -
OK - Replace landing gear control NOT OK - Adjust cable per 32-31-0. selector valve per 32-31-51.
Force required to move control handle through its angular travel is excessive (exceed 12 pounds). Check for jamming of cable by falling object or any other obstructions and repair as required.
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 ALL  ú ú 01 Page 102 ú Jun 25/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 LANDING GEAR CONTROL SYSTEM - ADJUSTMENT/TEST
_____________________________________________
 1.  General
_______
 A.  You will adjust the control system for the landing gear when you have one of these conditions:
 (1)  
A component is replaced

 (2)  
The cable tension is more than +/- 15 pounds from the values in table I.

 TASK 32-31-00-735-001
 2.  Landing Gear Control System Adjustment (Fig. 501)
______________________________________
 A.  Special Tools and Equipment
 (1)  
Force Gage Equipment, Landing Gear Lever - G32021-18 (G32021-1, Optional)
　
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