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27-62-00-013
SPEEDBRAKES EXTENDED Light
The SPEEDBRAKES EXTENDED light shows when all these
conditions occur:
* Airplane in the air
* Speedbrake lever is more than 7.5 degrees
* TE flaps are more than the 10 units or the altitude is less than
800 feet.
These conditions occur if the pilot uses the speedbrake lever
during the landing approach.
The SPEEDBRAKES EXTENDED light also shows when all
these conditions occur:
* Airplane on the ground
* Ground spoiler interlock valve pressure switch measures
more than 750 psi
* Speedbrake lever is in the down position.
These conditions occur if the ground spoiler actuators receive
hydraulic power with the speedbrake lever in the down position.
This is a failure condition.
The ground spoiler interlock valve pressure switch also sends
signals to the flight data aquisition unit (FDAU) when hydraulic
pressure is more than 750 psi.
See the flight data recording system (FDRS) section for more
information about the FDAU. (SECTION 31-31)
SPEEDBRAKE CONTROL SYSTEM - FUNCTIONAL DESCRIPTION - SPEEDBRAKES EXTENDED LIGHT
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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SPEEDBRAKE CONTROL SYSTEM - FUNCTIONAL DESCRIPTION - SPEEDBRAKES EXTENDED LIGHT
SPEEDBRAKE CONTROL SYSTEM - FUNCTIONAL DESCRIPTION - SPEEDBRAKES EXTENDED LIGHT
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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General
The pilots use the speedbrake lever to operate the ground
spoilers. The auto speedbrake module automatically operates
all the spoilers on the ground.
Manual Speedbrake Control
When the speedbrake lever moves, the speedbrake lever
cables move a quadrant in the spoiler ratio changer. The ratio
changer moves the spoiler mixer, which supplies an input to the
ground spoiler control valve. When the speedbrake lever
moves 31 degrees, the ground spoiler control valve sends
hydraulic power to the ground spoiler interlock valve.
A push/pull cable connects the ground spoiler interlock valve to
the right main landing gear torsion link. When the airplane is on
the ground, this cable opens the ground spoiler interlock valve.
This permits hydraulic pressure to go to the ground spoiler
actuators. This causes the ground spoilers to move up.
Auto Speedbrake Control
During landing and refused takeoffs, the auto speedbrake
module operates the auto speedbrake actuator. This actuator
moves the speedbrake lever. This operates the speedbrake
cable system the same as during manual speedbrake control.
This causes the ground spoilers to move up.
When the speedbrake lever moves, the spoiler ratio changer
also operates the flight spoilers. See the flight spoiler control
section for more information. (SECTION 27-61)
SPEEDBRAKE CONTROL SYSTEM - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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SPEEDBRAKE CONTROL SYSTEM - FUNCTIONAL DESCRIPTION
SPEEDBRAKE CONTROL SYSTEM - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
27-62-00-014
Purpose
The leading edge (LE) flaps and slats increase the wing area
and the wing camber. This increases lift to help improve the
takeoff and landing performance of the airplane.
General
The LE devices include two Krueger flaps and four slats on the
leading edge of each wing. During cruise, these surfaces fully
retract. These surfaces extend during takeoff to increase lift,
which permits slower speeds for airplane rotation. During
landing, the LE slats fully extend to increase lift and help
prevent a stall.
During normal operation, the LE flaps and slats are
mechanically controlled. During alternate operation, the LE
flaps and slats are electrically controlled.
The LE cruise depressurization function depressurizes the LE
flap and slat actuators. This occurs when all the LE devices and
the flap lever are at the up position and the airplane is in the air.
The LE uncommanded motion (UCM) detection function stops
　
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