S 865-013

 (4)  
Make sure all the circuit breakers for the landing gear system on the P6-2 panel are closed.

 S 585-014

 (5)  
Lift the nose of the airplane with the jack until the tires are clear of the ground (AMM 07-11-21/201).

 (6)
Remove the pressure from the shock strut for the nose gear:

 S 865-012
 S 035-015
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 WARNING: DO NOT LOOSEN THE VALVE BODY UNLESS THE SHOCK STRUT IS
_______ FULLY DEFLATED. AIR PRESSURE CAN BLOW THE VALVE BODY OUT, AND CAUSE INJURY TO PERSONS.
 (a)  
Remove the valve cap from the charging valve.

 (b)  
Loosen the air release nut, one or two turns, to deflate the shock strut.

 E.
Test of the Safety Sensor

 S 215-016
 (1)
Make sure the shock strut for the nose gear is fully extended.

 (a)  
Make sure the NOSE sensing light (on the E-11 shelf) is on.

 S 495-017
 (2)  
Put an axle jack below the nose gear (AMM 07-11-31/201).

 S 725-018

 (3)  
Slowly raise the axle jack until the strut is compressed a distance of 1.55 +/- 0.05 inches.

 (a)  
Make sure the NOSE sensing light (on the E-11 shelf) is off.

 NOTE:  The NOSE sensing light may go off before the strut is compressed 1.55 inches.
 S 725-019
 (4) Slowly lower the axle jack to extend the strut to a distance of
 0.95 +/- 0.05 inches from the fully extended position.
 (a)  Make sure the NOSE sensing light (on the E-11 shelf) is on.
 NOTE:  The NOSE sensing light may come on before the strut is un-compressed to 0.95 inches.
 F. Put the Airplane in Its Usual Condition
 S 095-020
 (1)  
Lower the axle jack and remove it from the nose gear.

 S 585-021

 (2)  
Lower the nose of the airplane and remove the jack
 (AMM 07-11-21/201).

 (3)  
Remove electrical power, if it is not necessary (AMM 24-22-00/201).

 S 615-023

 (4)  
Do the servicing procedure for the nose gear shock strut
 (AMM 12-15-41/301).

 S 865-022
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 LANDING GEAR LOGIC SHELF - DESCRIPTION AND OPERATION
____________________________________________________
 1.  General (Fig. 1)_______
 A.  The landing gear logic shelf (E-11) is located forward of the nose wheel well on right side frames in the radar bay . The logic shelf is a rectangular box containing printed circuit cards, relays, and test switches for systems affected by landing gear logic.
 B.  A location diagram and equipment nomenclature is printed on the top of the box for circuit cards contained inside. The panel may be removed by unscrewing fasteners to access cards for removal and replacement.
 C.  Relays located on the front panel of the box will switch off systems required only for flight and switch on systems required only for ground operations. These relays may be removed and replaced without opening the box.
 D.  Three ON-IN-AIR SENSING test buttons are located on the front left side of the box. These buttons are pressed to momentarily switch the air-ground relays to the in-flight mode to allow for ground test of all systems normally deactivated by air-ground logic when the airplane is on the ground. Three TRANSFER VALVE test buttons are used to test continuity of the solenoids in the landing gear transfer valve.
 E.  The circuit cards and relay switching circuits are all powered by the 28-volt dc battery bus.
 2.  Solid State Switches (Circuit Cards)____________________
 A.  Three of the switches provide input from air-ground sensors to the air-ground relays. These are M990 GROUND SENSING SQUAT SWITCH, M991 AIR SENSING SQUAT SWITCH, and M1110 NOSE AIR SENSING PROX SWITCH.
　
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