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CAUTION: DO NOT DEFLATE THE SHOCK STRUTS IF YOU
DO A GEAR RETRACTION TEST. THE SHOCK
STRUTS MUST BE FILLED CORRECTLY AND NOT
INFLATED ABOVE THE CORRECT PRESSURE. IF
YOU DO NOT OBEY THESE INSTRUCTIONS,
DAMAGE TO THE WHEEL WELL AND THE
SHOCK STRUTS WILL OCCUR.
MAIN LANDING GEAR AND DOORS - SHOCK STRUT - TRAINING INFORMATION POINT - 2
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
32-10-00-006
MAIN LANDING GEAR AND DOORS - SHOCK STRUT - TRAINING INFORMATION POINT - 2
MAIN LANDING GEAR AND DOORS - SHOCK STRUT - TRAINING INFORMATION POINT - 2
EFFECTIVITY
GUN ALL 32-10-00
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MAIN LANDING GEAR AND DOORS - SHOCK STRUT - TRAINING INFORMATION POINT - 2
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D633A101-GUN Oct 10/2002
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
Purpose
The main gear shimmy damper decreases vibration between
the inner and outer cylinders during high speed taxi and heavy
brake use.
Location
The body of the main gear shimmy damper attaches to the
forward end of the upper torsion link.
Physical Description
The main gear shimmy damper contains these components:
* Housing assembly
* Piston
* Bleed plugs
* Manifold assembly
* Inlet check valve
* Relief valve
* Compensator.
Functional Description
Vibration between the inner and outer cylinders causes the
inner cylinder to turn inside the outer cylinder. This causes the
main gear shimmy damper piston to move from side to side
inside the housing assembly.
When the piston moves, hydraulic fluid moves through the
damping orifices. This decreases piston movement. The
damper connects to the return line of the main landing gear
actuator.
The compensator maintains system pressure between 18 and
33 psi.
The inlet check valve controls the hydraulic fluid flow rate into
the damper to 70 cu in/min at 50 psi. It also controls the fluid that
leaves the damper to 14 cu in/min at 3750 psi.
The relief valve protects the compensator if the pressure
increases to more than 240 psi.
Training Information Point
Use the two bleed plugs on the main gear shimmy damper to
remove trapped air when you install a new damper.
NOTE: Hydraulic return pressure that remains after you have
depressurized system A will force fluid out the bleed
port when you remove the bleed plug.
MAIN LANDING GEAR AND DOORS - MAIN GEAR SHIMMY DAMPER
EFFECTIVITY
GUN ALL 32-10-00
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D633A101-GUN Oct 10/2002
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
32-10-00-007
WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE
FLIGHT CONTROL SURFACES, THE THRUST
REVERSERS, AND THE LANDING GEAR. THESE
COMPONENTS CAN MOVE SUDDENLY WHEN YOU
SUPPLY HYDRAULIC POWER. THIS CAN CAUSE
INJURY TO PERSONS AND DAMAGE TO
EQUIPMENT.
MAIN LANDING GEAR AND DOORS - MAIN GEAR SHIMMY DAMPER
EFFECTIVITY
GUN ALL 32-10-00
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D633A101-GUN Oct 10/2002
BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
32-10-00-007
MAIN LANDING GEAR AND DOORS - MAIN GEAR SHIMMY DAMPER
MAIN LANDING GEAR AND DOORS - MAIN GEAR SHIMMY DAMPER
EFFECTIVITY
GUN ALL 32-10-00
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32-10-00-007
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D633A101-GUN Oct 10/2002
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
General
The nose landing gear absorbs landing forces and holds the
forward part of the airplane weight when the airplane makes a
landing.
The nose landing gear doors open to permit gear operation.
They close to aerodynamically seal the nose landing gear
wheel well.
Nose Landing Gear Components
The nose landing gear has two wheel assemblies.
The nose landing gear has these components:
　
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