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when these conditions occur:
* Airplane in the air
* Landing gear lever not down
* One main landing gear not up
* Left engine N2 speed less than 50%
* Hydraulic system B pressure supplied to valve.
You move the landing gear control lever to control landing gear
extension and retraction. The control lever moves the selector
valve through cables.
The selector valve also gets an electrical input from the manual
extension system. This operates a bypass valve in the selector
valve to connect the landing gear retraction to the hydraulic
system return. This lets the manual extension system extend
the landing gear.
See the Air/Ground System section for more information about
the proximity switch electronics unit (PSEU). (SECTION 32-09)
LANDING GEAR CONTROL SYSTEM - GENERAL DESCRIPTION
EFFECTIVITY
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Nose Wheel Steering
The pressure for nose wheel steering comes from the nose
landing gear extension pressure only. Hydraulic system A
normally supplies pressure to the nose gear steering through
the landing gear control system.
When you move the alternate nose wheel steering switch to the
alternate position, the landing gear transfer valve moves to the
alternate position. The landing gear transfer valve moves the
pressure source, for the landing gear retraction and the nose
wheel steering, from hydraulic system A to hydraulic system B.
See the Nose Wheel Steering section for more information
about the nose wheel steering. (SECTION 32-51)
LANDING GEAR CONTROL SYSTEM - GENERAL DESCRIPTION
EFFECTIVITY
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LANDING GEAR CONTROL SYSTEM - GENERAL DESCRIPTION
LANDING GEAR CONTROL SYSTEM - GENERAL DESCRIPTION
EFFECTIVITY
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LANDING GEAR CONTROL SYSTEM - GENERAL DESCRIPTION
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Purpose
The landing gear control lever assembly operates the landing
gear selector valve through the landing gear control cables.
Location
The landing gear control lever is on the P2 center forward panel
in the flight compartment.
Physical Description
The control lever assembly has these components:
* Control lever
* Position switch (4)
* Lock mechanism
* Lever lock solenoid.
Functional Description
The landing gear control lever has these three positions with
detents:
* UP
* OFF
* DOWN.
You must first pull the control lever out before you can move the
lever. The lever operates a push-pull cable which moves the
forward quadrant. You do not adjust the push-pull cable. The
forward quadrant is below the flight compartment floor.
The control lever assembly has a lever lock mechanism
operated by a lever lock solenoid. The lever lock prevents
accidental movement of the landing gear lever to the up
position when the airplane is on the ground. When the airplane
takes off, the solenoid gets electrical power and retracts. This
turns the lever lock mechanism to the unlocked position.
The landing gear control lever assembly has four control lever
position switches. Two down position switches send signals
when the lever moves to the down position. Two up position
switches send signals when the lever moves to the up position.
When you put the landing gear lever in the down position, the
down position switches move to the closed position. This sends
signals to the landing gear position indication and warning
system. The position indication system uses these signals to
operate the red landing gear position lights.
When you put the landing gear lever in the up position, the up
position switches move to the closed position. This sends
signals to the antiskid system. The antiskid system uses these
signals to inhibit antiskid operation during gear retract braking.
See the Landing Gear Position Indicating And Warning System
Section for more information. (SECTION 32-61)
　
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