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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 airplane. An override trigger permits the lever to bypass the lock if a malfunction of the system causes the lock to engage.

Landing Gear Control Lever Lock Control Logic Flow Diagram  532 
32-31-0  Figure 4  Feb 15/73 
Page 6 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

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 29-11-0).
500 
Feb 20/87  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-31-0 Page 101 

500 
32-31-0 Page 102  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/78 

LANDING GEAR CONTROL SYSTEM -ADJUSTMENT/TEST
1. General
A.  The landing gear control system is adjusted (rigged) when a component, or a cable is replaced or when the cable tension deviates more than ±15 pounds from the values given in Table I, (Fig. 501).
2.  Standard Tools and Equipment
A.  G32021 -Force Gage Equipment -Landing Gear Lever or Equivalent
3.  Landing Gear Control System Adjustment
A.  Equipment and Materials
(1)  
Rigging Pin MS20392-4 or equivalent 0.311 (-0.002/+0.000) inch diameter rod

(2) 
 Cable Tensiometer

(3)  
Gear Ground Lock Assemblies (Ref 32-00-01)

B.  Adjust (Rig) Landing Gear Control System
(1)  
Check that landing gear ground lock assemblies (Ref 32-00-01)

(2)  
Disconnect link assembly between selector valve and bellcrank.

(3)  
Place landing gear control handle in OFF position.

(4)  
Install rigging pin in bellcrank (Fig. 401).

(5)  
Rig cables to the valve corresponding to ambient temperature as given in Table I, (Fig 401). Turnbuckles are accessible through access door 1103. Rig to free rigging pin.

NOTE: Temperature of airplane must be stabilized for one hour before adjusting cables.

(6)  
Remove rigging pin and cycle system for no load movement on either side of OFF position (full travel).

(7)  
Reinstall rigging pin.

(8)  
Recheck cable tension. Adjust as necessary.

(9)  
Connect link assembly between selector valve and actuating bellcrank.

(10)
Remove rigging pin.

(11)
Test control system per par. 3.

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4.  Test Landing Gear Control System
A.  Check that all landing gear ground locks are installed and hydraulic systems depressurized.
B.  Set landing gear control handle in DN position.
C.  Check that force required to move control handle through its angular travel does not exceed 12 pounds.
D.  Operate override trigger and move control handle to UP position.
　
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