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temperature indications are equal to or more than 5.0. The light
turns off when all of the brake temperature indications are less
than 3.5. High brake temperature will cause a main wheel fuse
plug to melt.
BRAKE TEMPERATURE MONITORING SYSTEM - FUNCTIONAL DESCRIPTION
EFFECTIVITY
GUN 201-999 32-46-00
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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BRAKE TEMPERATURE MONITORING SYSTEM - FUNCTIONAL DESCRIPTION
BRAKE TEMPERATURE MONITORING SYSTEM - FUNCTIONAL DESCRIPTION
EFFECTIVITY
GUN 201-999 32-46-00
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D633A101-GUN Oct 10/2005
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
32-46-00-006
GENERAL
These are the functions you can do with the BITE of the brake
temperature monitoring unit (BTMU):
* Monitor Test
* Sensor Test.
The BITE instructions are on a placard on the front of the BTMU.
Monitor Test
In the monitor test position, the BTMU does a self-test and turns
on the five red LEDs, the BRAKE TEMP light, and supplies an
indication of 7 for each brake on the systems display. When the
switch is released, the lights turn off and the indication returns
to normal.
Sensor Test
In the sensor test position, the BTMU turns on the five red LEDs.
This shows that the sensor circuit is complete. When you
release the switch, the five LEDs turn off.
BRAKE TEMPERATURE MONITORING SYSTEM - TRAINING INFORMATION POINT - BTMU BITE
EFFECTIVITY
GUN 201-999 32-46-00
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D633A101-GUN Oct 10/2005
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
32-46-00-007
BRAKE TEMPERATURE MONITORING SYSTEM - TRAINING INFORMATION POINT - BTMU BITE
BRAKE TEMPERATURE MONITORING SYSTEM - TRAINING INFORMATION POINT - BTMU BITE
EFFECTIVITY
GUN 201-999 32-46-00
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32-46-00-007
THIS PAGE IS INTENTIONALLY LEFT BLANK
32-51-00
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
Purpose
The nose wheel steering system supplies the ground
directional control of the airplane.
General Description
Steering inputs are from the steering wheel or the rudder
pedals. When you move the steering wheel full travel, the nose
wheels turn a maximum of 78 degrees in the left or right
direction. When you move the rudder pedals full travel on the
ground, the nose wheels turn a maximum of 7 degrees in the
left or right direction. Steering inputs from the steering wheel or
rudder pedals go to the metering valve through a cable loop.
CAUTION: DO NOT OPERATE THE STEERING WHEEL WITH
THE SHOCK STRUT FULLY EXTENDED AND THE
TORSION LINKS CONNECTED. DAMAGE TO THE
CENTERING CAMS OF THE SHOCK STRUT CAN
OCCUR. IF IT IS NECESSARY TO OPERATE THE
STEERING SYSTEM, MAKE SURE THAT YOU
COMPRESS THE SHOCK STRUT TO 2.10 INCHES
OR MORE. MAKE SURE THAT THE DISTANCE
BETWEEN THE BOTTOM SURFACE OF THE
LOWER STEERING PLATE AND THE TOP
SURFACE OF THE TOWING LUG IS LESS THAN
21.90 INCHES.
Hydraulic system A usually supplies pressure to extend and
retract the main landing gear. The extend pressure from the
landing gear extension and retraction system supplies pressure
for nose wheel steering.
The landing gear transfer valve changes the pressure supply of
nose wheel steering from hydraulic system A to hydraulic
system B. You manually control the landing gear transfer valve
with the alternate nose wheel steering switch in the flight
compartment.
These conditions cause the manual operation of the landing
gear transfer valve:
* Alternate nose wheel steering switch to the alternate
position
* Normal quantity in system B reservoir
* Nose air/ground system in ground mode.
The steering metering valve supplies right turn or left turn
pressure to the steering actuators.
The rotary actuator disconnects the rudder pedal input in the
air.
NOSE WHEEL STEERING SYSTEM - GENERAL DESCRIPTION
EFFECTIVITY
GUN ALL 32-51-00
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
　
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