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 C.  The main gear (Fig. 2) is hydraulically actuated to retract inboard into the fuselage. Each main gear is locked in the down position by a folding lock strut and in the up position by an uplock hook and mechanism. Shock strut doors close the opening in the wing for the main gear shock strut and drag strut. A wheel well seal closes against the main gear tire circumference when the airplane is in flight with gear retracted.

SEAL GEAR  NOSE WHEEL WELL DOORS
Landing Gear Location Figure 1
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A 737-300/400/500MAINTENANCE MANUAL

FWD

Main Gear Schematic
Figure 2

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A

737-300/400/500
MAINTENANCE MANUAL

RETRACT POSITION  SPRING BUNGEE DRAG STRUT ASSEMBLY 
DOOR LINKAGE  LOCK ACTUATOR 
FWD  NOSE GEAR STEERING VALVE  STEERING CYLINDERS  LOCK LINK ASSEMBLY TORSION LINKS 
TOW BAR FITTING 
JACKING POINT 
NOSE GEAR ACTUATOR 
NOSE GEAR TRUNNIONS 
WHEEL WELL DOOR 

Nose Gear Schematic
Figure 3

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A
737-300/400/500MAINTENANCE MANUAL
 D.  The nose gear (Fig. 3) is hydraulically actuated to retract forward into the fuselage. A lock strut assembly locks the nose gear in the up and down positions. Clamshell-type nose gear doors close to fair with the fuselage contour when the nose gear is retracted and remain open when the nose gear is extended.
 E.  The main and nose gear manual extension systems are cable operated to release each gear from the up and locked position and allow the gear to free fall to the down and locked position.
 F.  Nose wheel steering is provided for aircraft directional control during ground maneuvers. Normal steering is accomplished by using a steering wheel located at the captain's position. A reduced range of steering by rudder pedal is available.
 2.  Landing Gear Air-Ground Sensing_______________________________
 A.  Certain systems of the airplane require electrical control depending upon the condition of the airplane (airborne or on the ground) (Fig. 4). The condition of the airplane is sensed by the landing gear ground and air safety sensors (proximity switches). The safety sensors transmit signals to circuits and relays in a landing gear electrical module to provide "air" or "ground" control of the system or componments. The landing gear systems controlled by air-ground sensing are the control lever lock system and the antiskid system. Other airplane systems and components controlled by air-ground sensing are: APU fire horn system, thrust reverser, electrical system static inverter, drain mast heater, stall warning system, flight recorder system, air conditioning turbofans, takeoff warning system, cabin pressurization control system, voice recorder system, wing anti-ice system, electrical system, flap load limiter system, and automatic braking system. For additional information on the landing gear safety sensors, refer to AMM 32-09-00.
 B.  An air sensing test switch and a ground sensing test switch on the electrical module are normally used to simulate airplane-in-air condition. When the airplane is operating in the ground mode, the air sensing test switch energizes the air sensing relays and the ground sensing test switch de-energizes the ground sensing relays. Both switches must be pressed and held down to simulate the airplane-in-air condition. When the switches are released, the systems return to airplane-on-ground condition. When the airplane-in-air condition is simulated, certain precautions regarding the systems listed in Table 1 should be observed.
　
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