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mechanism during main landing gear extension and retraction.
Location
The main landing gear downlock mechanism and downlock
actuator are between the reaction link and upper side strut.
Physical Description
The downlock springs attach to the inboard side of the reaction
link and to the downlock mechanism.
The downlock actuator is a piston-type, double-acting,
unbalanced actuator. The body of the downlock actuator
attaches to the inboard side of the reaction link. The rod end
of the downlock actuator attaches to the downlock mechanism.
The downlock actuator has a restrictor relief valve at the body
end of the actuator that decreases the flow to 0.26 gpm at 2550
psi. The relief valve opens at 2800 - 3100 psi.
The downlock actuator has a restrictor check valve at the rod
end of the actuator that decreases the flow to 0.29 gpm at 3000
psi.
Functional Description
During main landing gear extension, the downlock actuator
receives down pressure to retract. The actuator retracts to lock
the downlock mechanism during main landing gear extension.
During main landing gear retraction, the downlock actuator
receives up pressure to extend. The actuator extends to unlock
the downlock mechanism during main landing gear retraction.
Training Information Point
After removal and installation of the uplock actuator, you must
extend and retract the main landing gear several times. This
will bleed the air from the uplock actuator and the lines.
Examine for correct gear operation.
MLG EXTENSION AND RETRACTION - DOWNLOCK MECHANISM AND ACTUATOR
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
32-32-00-006
MLG EXTENSION AND RETRACTION - DOWNLOCK MECHANISM AND ACTUATOR
MLG EXTENSION AND RETRACTION - DOWNLOCK MECHANISM AND ACTUATOR
EFFECTIVITY
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D633A101-GUN Feb 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
32-32-00-006
Purpose
During the extension and retraction sequences, the transfer
cylinder gives a time delay. This lets the main landing gear
downlock or uplock actuators unlock before the main gear
actuator receives pressure.
Location
The transfer cylinder is on the rear spar of the left and right
wings.
Physical Description
The transfer cylinder has a piston that moves freely in the
cylinder. One side of the piston connects to the down pressure.
The other side connects to the up pressure.
Functional Description
The piston moves when up or down pressure goes to the
transfer cylinder. When the piston moves, it pushes fluid on the
side that does not have pressure. This gives a time delay to the
extend or retract side of the main gear actuator and the
downlock actuator.
MLG EXTENSION AND RETRACTION - TRANSFER CYLINDER
EFFECTIVITY
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Page 14
D633A101-GUN Oct 10/2002
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
32-32-00-007
MLG EXTENSION AND RETRACTION - TRANSFER CYLINDER
MLG EXTENSION AND RETRACTION - TRANSFER CYLINDER
EFFECTIVITY
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D633A101-GUN Feb 10/2003
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
32-32-00-007
Purpose
The frangible fitting removes up pressure from the main landing
gear actuator when a damaged, spinning tire moves into the
main landing gear wheel well. This prevents damage to
components in the wheel well.
Location
There is a frangible fitting on the outboard side of both wheel
well rings in the main landing gear wheel well.
Physical Description
The frangible fitting is a normally closed valve. It opens when a
force removes the lever from the fitting.
Functional Description
The frangible fitting operates during this sequence of events:
* A section of tread partially separates from a main landing
gear tire
* Landing gear starts to retract
* Gear retract braking has a fault and does not stop the wheel
before it moves into the wheel well
* The section of tread removes the lever from the frangible
fitting
* Frangible fitting opens
* Up pressure is removed from the main landing gear actuator
* Main landing gear that has the damaged tire stops retraction
and moves towards the extended position
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