(2)  
A lever lock solenoid is included in the module for safety. This electrical solenoid moves to structurally stop movement of the lever to the UP detent when a ground mode signal is received from the air/ground relay system. This prevents retraction of the landing gear when the airplane is on the ground. A manual override rod mechanically moves the solenoid when there is a failure in the system which causes the solenoid not to be energized.

 B.  
Selector Valve (Fig. 2)

______________
 (1)  The selector valve sends hydraulic fluid from the left hydraulic system reservoir to the actuators and valves in the extension and retraction systems for the main and nose landing gear. The valve has three positions which agree with the positions of the control lever. The selector valve and the control lever are connected by quadrants and cables. Movement of the control lever moves the selector valve into the position that agrees with the control lever. The selector valve is installed in the wheel well for the right main landing gear. It can be found in the top, forward, inboard corner of the wheel well.
 3.  Operation (Fig. 3)
_________
 A.  Functional Description
______________________
 (1)  Landing gear control starts with movement of the control lever. The lever is pulled out of detent and moved up for landing gear retraction or down for extension. This movement is transmitted to the control cables through a link and quadrant behind the control lever module. The cables transmit the movement to the selector valve through another link and quadrant. The selector valve moves to the position that agrees with the position of the control lever. This supplies hydraulic pressure to the extension and retraction hydraulic lines for the landing gear.
 

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MAINTENANCE MANUAL

SEE A
CONTROL LEVER

A
MODULE
PILOT'S CENTER INSTRUMENT PANEL, P3-1
CONTROL LEVER MODULE (CUTAWAY SHOWN)
A
HANDLE
A
LOCK OVERRIDE
LOCK
SOLENOID
CONTROL LEVER QUADRANT
A-A
Landing Gear Control Lever Module
Figure 1

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SEE  A 
CONTROL VALVE QUADRANT  CONTROL ROD  LANDING GEAR SELECTOR VALVE INBD  FWD 
A 
Figure 2 Landing Gear Selector Valve 

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MAINTENANCE MANUAL

MECHANICALLY PREVENTS LEVER MOVEMENT TO THE UP POSITION WHEN THE SOLENOIDIS NOT ENERGIZED
Landing Gear Control Operation Schematic Figure 3

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MAINTENANCE MANUAL

 LANDING GEAR CONTROL - ADJUSTMENT/TEST
______________________________________
 1.  General
_______
 A.  This procedure contains two tasks. The first task is an operational test and the second task is a system adjustment for the landing gear control system.
 TASK 32-31-00-705-001
 2.  Operational Test - Landing Gear Control (Fig. 501)
_______________________________________
 A.  General
 (1)  
This test is used to make sure the landing gear control system is serviceable.

 B.  
Equipment

 (1)  
Force Gage Equipment - P/N G32021-18

 (2)  
Spring Scale - 0 to 20 pound capacity
 (Optional to Force Gage Equipment)

 C.  
References

 (1)  
AMM 24-22-00/201, Electrical Power - Control

 (2)  
AMM 27-61-00/201, Spoiler/Speedbrake Control System

 (3)  
AMM 29-11-00/201, Pressurize/Depressurize Main Hydraulic System

 (4)  
AMM 32-00-20/201, Landing Gear Downlocks

 (5)  
AMM 32-09-02/201, Air/Ground Relays

 D.  
Access

 (1)  
Location Zones
 211 Control Cabin (Left)
 212 Control Cabin (Right)

 E.  
Prepare for the Operational Test

 S 495-002
 WARNING: MAKE SURE THE MAIN AND NOSE LANDING GEAR AREAS ARE CLEAR OF
_______ PERSONS BEFORE YOU DO THIS TEST. THE LANDING GEAR DOORS OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (1)  
Make sure the downlocks are installed on the nose and main landing gear (AMM 32-00-20/201).
　
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本文鏈接地址：757 AMM 飛機維護手冊 起落架 CHAPTER 32 - LANDING GEAR 2(35)