737-300 400 500 AMM 飞机维护手册 起落架 LANDING GEAR 1(12)

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 CAUTION: MAKE SURE THE SUBSEQUENT INSPECTIONS CHECK THE REPAIR
_______ UNTIL THE SHOCK STRUT IS OVERHAULED. CONTINUED USE OF A LANDING GEAR WITH THE REPAIR FOR CRACKING CHROME MAY RESULT IN SEAL DAMAGE, SHOCK STRUT FLUID CONTAMINATION, AND POSSIBLE STRUT PRESSURE LOSS. THERE IS NO PERMANENT REPAIR FOR CRACKED CHROME, THE CRACK WILL REMAIN UNTIL THE CHROME IS REMOVED AND REPLACED.
 (b)  After the temporary repair is done, make sure the inspection procedure (AMM 32-00-03/601) is done between four and six months again, and again until the shock strut is removed and replaced. Once chrome is damaged, there is no permanent repair, and the damage can continue to spread. The only permanent repair is to strip and replate the chrome. 1) Measure the size of the area that has the cracks, and make
 a sketch of the location and shape of the area, and mark the dimensions on the sketch. Make sure you keep this data so it can be used for the next inspection.
 2)  Use a wiper to apply a thick layer of primer to the cracked chrome surface.
 3)  Before the primer dries, remove the excess with a clean, dry cloth. Make sure no primer gets on the seals or scrapers, as they can be damaged by the primer and may start to leak.
 4)  Let the primer cure for at least 4 hours.
 F.  Put the Airplane back to its Usual Condition
 S 416-007
 WARNING: YOU MUST CAREFULLY DO THE STEPS WHEN YOU REMOVE THE DOOR LOCKS
_______ FROM THE LANDING GEAR DOORS. THE DOORS CAN CLOSE QUICKLY IF YOU DO NOT REMOVE THE DOOR LOCKS CORRECTLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (1) Remove the ground locks from all landing gear (AMM 32-00-01/201).
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 32-00-03
 ALL  ú ú 02 Page 603 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 LANDING GEAR SAFETY SENSORS - DESCRIPTION AND OPERATION
_______________________________________________________
 1.  General_______
 A. Main Landing Gear Safety Sensors
 (1)  
The main landing gear safety sensors (Fig. 1) provide signals to solid state circuits in the landing gear electrical module to energize or de-energize the safety relays depending upon whether the airplane is airborne or on the ground. The sensors are mounted near the ground spoiler (lockout) valve above the right main gear. The sensors are proximity switches that sense the presence or the absence of a metal actuator. A double-paddle metal actuator is connected to the spoiler valve linkage to actuate the sensors. The spoiler valve linkage is operated by extension and compression of the shock strut through a teleflex cable. Linkage movement positions the actuator for the respective sensor to provide the appropriate signal.

 B.
Nose Landing Gear Safety Sensor

 (1)  
A nose gear air sensing proximity sensor is located on the steering collar of the nose gear shock strut (Fig. 2). The sensor is a proximity switch operated by an actuator mounted on the upper torsion link. When the airplane leaves the ground, the shock strut extends, pivoting the upper torsion link toward the shock strut. This moves the actuator in front of the sensor and causes the sensor to conduct.

 (2)  
The NOSE sensing light ( LED ) uses the nose air sensing proximity sensor for input. The light ( LED ) is on in the air mode and is located on the E11 logic shelf. The light is labeled NOSE and has the note at the top that the light is " on in air ".

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 32-09-00
 ALL  ú ú 01 Page 1 ú Nov 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
CABLE TELEFLEX LANDING GEAR RIGHT MAIN 
FWD  SAFETY SENSORS LANDING GEAR 
SEE  A  GROUND SPOILER INTERLOCK VALVE 
SENSOR AIR SAFETY 

TELEFLEX 
ACTUATOR  CABLE 
GROUND SAFETY SENSOR 

GROUND SPOILER 
INTERLOCK VALVE 
FWD  OUTBD 
A 
Main Landing Gear Safety Sensors 
Figure 1 

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