.
maximum pressure – 3500 psi

.
normal precharge – 1000 psi.

Brake Temperature Indicator YC411, YC413

Brake Temperature (BRAKE TEMP) Light
Illuminated (amber) -
.
temperature of one or more brakes is excessive

.  
extinguishes when a hot brake condition is no longer indicated on the display unit.

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14.10.6   June 1, 2005
Landing Gear -Controls and Indicators
737 Flight Crew Operations Manual
2 MFD System (SYS) Switch
Push – SYS
.  
displays brake temperature indications on lower DU; or if the lower DU is
unavailable, displays it on upper DU or inboard DU based on the position
of the display select panel selector

.  
second push blanks lower DU.

3 Brake Temperature
Indicates a relative value of wheel brake temperature
.  
values range from 0.0 to 9.9

.  
displayed (white) - normal brake temperature range, 0.0 to 4.9

.  
displayed (amber) - high brake temperature, > 4.9.

4 Brake Symbol
Displayed (blank) - indicates any brake less than 2.5.
Displayed (solid white) - indicates the hottest brake on each main gear truck, within the range of 2.5 to 4.9.
Displayed (solid amber) - indicates brake overheat condition on each wheel within the range of 5.0 to 9.9. Symbol remains until value is less than 3.5.
Rudder/Brake Pedals
1
2

CREW STATION
Rudder/Brake Pedals
Push full pedal – turns nose wheel up to 7 degrees in either direction.
Push top of pedal only – activates wheel brakes.
Refer to Chapter 9 Flight Controls for rudder description.

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June 1, 2005   14.10.7
Landing Gear -Controls and Indicators 737 Flight Crew Operations Manual

RUDDER PEDAL ADJUSTMENT Crank AFT (counter–clockwise) – adjusts rudder pedals aft. FWD (clockwise) – adjusts rudder pedals forward.
Nose Wheel Steering Switch

NOSE WHEEL STEERING Switch
ALT – hydraulic system B provides power for nose wheel steering.
NORM (guarded position) – hydraulic system A provides power for nose wheel steering.
Nose Wheel Steering Wheel

Nose Wheel Steering Wheel
Rotate –
. turns nose wheel up to 78 degrees in either direction
. overrides rudder pedal steering.

Nose Wheel Steering Indicator
LEFT – indicates nose wheel steering displacement left of center position.
CENTER – normal straight ahead position.
RIGHT – indicates nose wheel steering displacement right of center position.

Copyright . The Boeing Company. See title page for details.
14.10.8  June 1, 2005

737 Flight Crew Operations Manual

Introduction
The airplane has two main landing gear and a single nose gear. Each main gear is a conventional two–wheel landing gear unit. The nose gear is a conventional steerable two–wheel unit.
Hydraulic power for retraction, extension, and nose wheel steering is normally supplied by hydraulic system A. A manual landing gear extension system and an alternate source of hydraulic power for nose wheel steering are also provided.
The normal brake system is powered by hydraulic system B. The alternate brake system is powered by hydraulic system A. Antiskid protection is provided on both brake systems, but the autobrake system is available only with the normal brake system.
YC411, YC413 A brake temperature monitoring system displays each main landing gear brake temperature on the lower DU.
Landing Gear Operation
The landing gear are normally controlled by the LANDING GEAR lever. On the ground, a landing gear lever lock, prevents the LANDING GEAR lever from moving to the up position. An override trigger in the lever may be used to bypass the landing gear lever lock. In flight, the air/ground system energizes a solenoid which opens the lever lock.
Landing Gear Retraction
When the LANDING GEAR lever is moved to UP, the landing gear begins to retract. During retraction, the brakes automatically stop rotation of the main gear wheels. After retraction, the main gear are held in place by mechanical uplocks. Rubber seals and oversized hubcaps complete the fairing of the outboard wheels.
The nose wheels retract forward into the wheel well and nose wheel rotation is stopped by snubbers. The nose gear is held in place by an overcenter lock and enclosed by doors which are mechanically linked to the gear.
Hydraulic pressure is removed from the landing gear system with the LANDING GEAR lever in the OFF position.
　
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