Nose Gear - Component Location Figure 006
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Nose Gear Shock Absorber - Schematic
Figure 007
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Nose Gear Shock Absorber - Section
Figure 008
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Nose Gear Shock Absorber Charging Valve
Figure 009
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Nose Gear Shock Absorber Charging Valve
Figure 009A
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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 (FHS) and nitrogen
through a single standard servicing valve at 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 (64,4 T, 66 T, 68 T, 70 T, 73,5 T,
75,5 T and 77 T).
Hole is included in the leg to show possible leaks from the dynamic seal
of the shock absorber.
It should be noted that the dynamic seal is located at the top part of
the shock absorber (between the plunger tube and the sliding rod). The
dynamic seal is therefore in a protected area which is not subjected to
side loads during ground maneuvers.
It is possible to remove the shock absorber without drainage of the
hydraulic fluid (removal of retaining ring at upper part of leg).
Main data:
-total travel: 430 mm,
-filling pressure: 19 bars,
-threshold load: 1351 daN,
-volume of fluid: 5.577 liters.
A placard bonded to the leg shows the filling curves. These curves show
whether the shock absorber is at the correct pressure for the standout
length of the sliding rod.
The shock absorber includes 2 centering cams, one is part of the plunger
tube and the other is part of the sliding tube.
When the shock absorber is fully extended the pressure of the nitrogen
causes the cams to engage.
The wheels then return automatically to the center position.
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R B. Nose Wheel Steering Control
R Refer to 32-51 for the description of the control system.
R Towing is possible through a range of 95 degrees without disconnection of
R the torque links.
R Any possible leakage of the steering actuating cylinder can be detected
R by means of a drainage hole at the bottom of the leg.
R The steering actuating cylinder is parallel to the aircraft centerline to
R keep to a minimum the risk of damage by tire tread shedding.
R The towing lug has two bolts that break if the towing load is more than
R the specified limit. This prevents the risk of damage to the sliding rod.
R (Ref. Fig. 010)
R
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R Nose Gear - Towing Lug Figure 010
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C. Shock Absorber and Nose Wheels Position Information (Ref. Fig. 011) A control mechanism with full redundancy controls the proximity detectors which monitor the shock absorber and wheel position. The data "Ground" is given when the shock absorber is at more than 4.4 mm (0.1732 in.) to 8 mm (0.3149 in.) from its extended position. The data "Ground" is also given when the nose wheels are at more than
1.95 to 5.28 degrees from their centered position.
If not, the data "Flight" is given and retraction of the nose gear is
then possible.
D. Drag Strut Assy and Lockstay-Downlock Indicating (Ref. Fig. 012)
(1)
The lockstay assembly controls alignment of the folding drag strut.
(2)
The stable position of the lockstay assembly is set overcenter (approx. 13 mm) to give added safety in the downlocked position.
(3)
Within this range, downlock indicating is given by 2 proximity detectors. Each proximity detector is installed on two separate brackets. (Ref. Fig. 012)
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