AIRCRAFT SYSTEMS LANDING GEAR Flashcards

1
Q

To provide a means of maneuvering
the aircraft on the ground.

To support the aircraft at a convenient
height to give clearance for propellers
and to facilitate loading.

To absorb the kinetic energy of landing
and provide a means of controlling
deceleration.

A

Functions of the landing gear

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2
Q

2 Landing Gear Layouts

A

Tricycle, Tailwheel

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3
Q

With slow, light aircraft, and some larger
aircraft on which simplicity is of prime
importance, a ___________ is often fitted.

A

fixed (non retractable) landing
gear

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4
Q

With higher performance aircraft, drag
becomes progressively more important, and a
___________ is retracted into the
wings or fuselage during flight.

A

retractable landing gear

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5
Q

3 Main Types of Fixed Landing Gear

A

Spring Steel Leg

Rubber Cord (Shock Absorber)

Oleo-Pneumatic Struts

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6
Q

These are usually
employed at the main
undercarriage positions. The leg
consists of a tube, or strip of
tapered spring steel. The upper
end being attached by bolts to the
fuselage and the lower end
terminating in an axle on which
the wheel and brake are
assembled.

A

Spring steel legs

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7
Q

When ___________ is used as a
shock-absorber, the
undercarriage is usually in the
form of tubular struts, designed
and installed so that the landing
force is directed against a
number of turns of rubber in the
form of a grommet or loop.

A

rubber cord

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8
Q

Some fixed main undercarriages, and
most fixed nose undercarriages, are
fitted with an _____________ shock
absorber strut. The design of individual
struts varies considerably but the
operating principle is same for all.
Additionally, one point worthy of
consideration is the fitting of spats to
___________ strut.

A

oleo-pneumatic

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9
Q

These are an aerodynamic fairing
which may be required to minimize the
drag of the landing gear structure.

A

Spats

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10
Q

A _____________ consists of two
concentric cylinders, one free to slide inside the
other.

A

simple oleo-pneumatic strut

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11
Q

The cylinders are filled with hydraulic fluid and gas.
Fluid and gas are kept apart by a_________.

A

separator piston

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12
Q

The outer or upper cylinder is attached to the
___________. It houses the inner or lower
cylinder and a piston assembly.

A

airframe structure

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13
Q

The ___________ are connected to the bottom of
the inner cylinder.

A

wheels and axle

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14
Q

The inner cylinder is free to rotate and move up and
down within the outer cylinder. Rotary movement
and up and down movement is limited by the
__________ which connect the inner and outer
cylinders together.

A

torque links / torsion / scissor links

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15
Q

Landing gear is subject to_______
during ground maneuvering and these
loads are taken by the torque links.

A

torsion loads

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16
Q

The smaller the radius of turn, the
_______ will be the load felt by the
torque links so all turns should be
made as _____ as possible.

A

greater ; wide

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17
Q

The area on the outer cylinder is filled with
_____________ and the area on the inner
cylinder is filled with __________ which
may be air or nitrogen.

A

hydraulic fluid ; compressed gas

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18
Q

__________ is a free-floating piston which
keeps the fluid and gas apart.

A

Separator piston

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19
Q

The purpose of the hydraulic fluid is to ________________________________.

A

dampen oscillations and

control the rate of compression and extension of the cylinders

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20
Q

There is a component known as a _________
which is fitted to the lower cylinder piston
assembly. The _________ consists of a
free-floating circular plate with a large central hole.
It is free to move up and down within its housing.

A

flutter valve

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21
Q

the gas pressure will support the weight of the aircraft with the lower
cylinder approximately on the midway of its stroke.

A

Aircraft Stationary on the ground

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22
Q

cushioned by the gas
pressure and dampened by the limited flow of fluid
through the orifice.

A

Bumps during taxiing

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23
Q

gas pressure will cause the lower part of
the leg to extend to its fullest extent.

A

Takeoff

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24
Q

strut shortens, and fluid is forced through
the flutter valve.

A

Landing

25
Q

Wheels to leg construction

A

Fork, Half Fork, Cantilever, Dual Wheel, Multiwheel

26
Q

It is employed to improve aircraft performance by reducing drag

A

Retractable Landing Gear

27
Q

Retractable landing gear is also provided with
__________ to ensure that each
undercarriage is locked securely in the
retracted and extended positions.

A

mechanical locks

28
Q

___________ are installed by which the
landing gear can be extended in the event of
failure of the power source.

A

Manual means

29
Q

_______ are provided to prevent retraction
with the aircraft on the ground.

A

Systems

30
Q

_________ are installed to guard against
landing with the landing gear retracted.

A

Warning devices

31
Q

The leg is attached to the wing spars
by a ____________ on
which the leg is free to rotate
laterally.

A

cylindrical beam or trunnion

32
Q

The strut inner cylinder is connected
to the ___________.

A

wheel bogie or truck beam

33
Q

The ________ is able to pivot
about its central point in a controlled
way. There is an axle connected to a
pair of break wheels at each end of
it.

A

truck beam

34
Q

The wing gear torque links prevent
________ between the shock strut inner
and outer cylinders without affecting
their reciprocating action during normal
operation of the strut.

A

rotation

35
Q

The ________ supports the leg in fore
and aft direction.

A

drag strut

36
Q

The ___________ struts
support the leg laterally. They fold out
when the gear is lowered and are then
held in place by the ________ strut which also
folds out during extension.

A

upper and lower side ; jury

37
Q

The _______ is pulled over center by
the down lock actuator geometrically
locking the gear down.

A

jury strut

38
Q

If the gear is lowered without hydraulic
power, then the over centering action
will be performed by an internal spring
in the __________.

A

downlock actuator

39
Q

Loads Sustained by the Landing Gear

A

Compressive loads (landing and
static on ground).

Rearward bending loads (during
breaking)

Side loads (During cross wind
landings, take offs, and taxiing)

Forward loads (during push back)

Torsional loads (Ground
Maneuvering)

40
Q

It is usually a lighter structure than a
main unit since it carries less weight and
is usually subject only to direct
compression loads.

A

Nose Landing Gear

41
Q

Design of nose landing gear are complicated by seven reqs, what are those?

A

Castoring

Self-centering

Steering

Anti-shimmy

Can withstand shear loads

42
Q

It is the ability of the nose
wheel to turn to either side in response
to the results of differential braking,
thrust, or aerodynamic forces on the
rudder, and to return back to its
central position when the forces are
removed.

A

Castoring

43
Q

To enable the aircraft to be
maneuvered about the airfield, the
nose wheel must __________.

A

castor freely

44
Q

_________ is achieved by either a cam
system or by hydraulic power through
steering actuators.

A

Centering

45
Q

A method of steering is required to enable the
pilot to maneuver the aircraft safely on the
ground. Early methods involved the use of
____________.

A

differential braking

46
Q

____________ using hydraulic systems are
now common to most large commercial
aircraft, allowing the engines to be set at the
minimum thrust for taxiing, thereby saving
fuel, an important consideration with large jet
engines.

A

Powered steering

47
Q

A hydraulically powered system may
include a ________________, a control valve steering cylinders to hold the nose gear, and a mechanical
feedback device to hold the nose wheel
at the selected angle.

A

cockpit steering wheel or
tiller

48
Q

Steering is controlled depending on the
type of aircraft by either the tiller or
________________.

A

the operation of the rudder pedals

49
Q

There are ____ steering actuators
which steer the nose gear.

A

two

50
Q

In some aircraft, a limited emergency
supply may be provided by a
_____________.

A

hydraulic accumulator

51
Q

The __________ in the pipelines
between the steering actuators provide
dampening for the steering operation
and help to prevent nose wheel
shimmy.

A

restrictors

52
Q

The __________ is
mechanically linked to the steering
control valve. A follow-up linkage
from the nose undercarriage gradually
resets the control valve as the nose
wheel turns.

A

steering wheel or tiller

53
Q

There is a __________ fitted
between the two sides of the steering
actuators. It is normally held closed by
hydraulic pressure. The purpose of the
___________ is to allow the
nosewheel to castor if there is a
hydraulic failure.

A

safety bypass valve

54
Q

Some systems have the facility to
bypass the system during towing
operations. It employs a __________
which when operated opens the
steering bypass valve. When the ______
is operated by ground operator at the
nose gear location, it opens the valve
allowing fluid to flow freely between
the steering actuators.

A

bypass lever

55
Q

A ________ with a flag attached is
fitted to hold the lever in the valve
open position. The tractor can now tow
the aircraft and turn the nosewheel as
necessary.

A

bypass pin

56
Q

Large aircraft with multiwheel main
gears have a problem with the main
gears sliding sideways in turns. This is
known as ________ and can quickly
damage tires.

A

scrubbing

57
Q
A
58
Q
A