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The two system proximity detectors provide signals for
both gear extended and wheel centered positions.
The towing lug is designed to shear if the towing load
is more than the limit.
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NOSE LANDING GEAR DESCRIPTION - LOCKSTAY ASSEMBLY
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LANDING GEAR AND DOORS - NOSE LANDING GEAR DESCRIPTION
ROTATING TUBE
The rotating tube is inside the shock strut. It is
equipped with a pinion which transmits steering orders
from the steering actuating cylinder to the wheels.
TORQUE LINK
The torque link is installed on the rear. It connects
the sliding tube to the rotating tube.
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32 - LANDING GEAR
32-22-00 LANDING GEAR AND DOORS - NOSE
LANDING GEAR DOORS DESCRIPTION
CONTENTS:
General
Main Doors
Proximity Detectors
Aft Doors
Leg Door
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LANDING GEAR AND DOORS - NOSE LANDING GEAR DOORS DESCRIPTION
GENERAL
The doors of the nose landing gear include:
- two main doors,
- two aft doors,
- one leg door.
MAIN DOORS
The two main doors are hydraulically operated. These
two doors are connected mechanically to the aircraft
by a linkage which has two control rods connected to
the same bellcrank.
This bellcrank is installed at the roof of the landing
gear well and is operated by one double-acting
actuator.
An uplock assembly latches the doors in the closed
position.
PROXIMITY DETECTORS
Two proximity detectors per door provide a signal it
is in the open position (one per system).
The doors must be in this position to permit the gear
to operate.
AFT DOORS
The two aft doors are symmetrical and connected by an
adjustable rod to the gear leg.
These doors close the aft part of the nose gear well
when the gear is retracted.
LEG DOOR
The leg door is attached to the rear part of the gear
leg.
When the gear is retracted, this door closes off the
area through which the drag strut passes when the gear
is extended.
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NOSE LANDING GEAR DOORS DESCRIPTION
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32 - LANDING GEAR
32-00-00 LANDING GEAR COMPONENTS
CONTENTS:
NLG Shock Absorber
MLG Shock Absorber
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LANDING GEAR COMPONENTS
NLG SHOCK ABSORBER
LOCATION
ZONE: 711
DESCRIPTION
The shock absorber is of the single chamber type
without a separator piston and is double acting.
The shock absorber is filled with hydraulic fluid and
nitrogen through a single standard servicing valve in
the upper part of the leg. Calibration of the metering
devices in the shock absorber is the same for the
different versions of the aircraft.
Holes are included in the leg to show possible leaks
from the dynamic seal of the shock absorber.
It is possible to remove the shock absorber without
drainage of the hydraulic fluid.
A placard bonded to the leg shows the filling curves.
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