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Aircraft Structures and Design 1Aero > Helicopter > Flashcards

Helicopter Flashcards

1
Q

Tandem rotor helicopters do not require a:

A. swash plate
B. tail rotor
C. flapping hinge

A

B. tail rotor

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2
Q

The airfoil used on helicopter horizontal
stabilizer are usually:

A. inverted
B. hi-camber
C. NACA series

A

A. inverted

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3
Q

What rotor systems are commonly used on
helicopters:

A. symmetrical, assymetrical and swash-plate
B. constant-speed, variable-speed and oil
controlled.
C. single-rotor, co-axial, tandem and
intermeshing

A

C. single-rotor, co-axial, tandem and
intermeshing

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4
Q

The three types of horizontal stabilizer design are:

A. Fenestron, NOTAR and conventional
B. forward-mounted, aft-mounted and T-tail
C. Constant speed, variable and
ground-adjustable

A

B. forward-mounted, aft-mounted and T-tail

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5
Q

Helicopters are examples of:

A. bladed propeller airfoil
B. fixed wing aeroplanes
C. rotary wing aircraft

A

C. rotary wing aircraft

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6
Q

Traditional tail rotor, Fenestron and the NOTAR
are examples of:

A. altitude control
B. rotor blade velocity control
C. anti-torque control

A

C. anti-torque control

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7
Q

The tail rotor drive system is powered by:

A. the main transmission
B. a dedicated isolated drive system
C. the cyclic pitch

A

A. the main transmission

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8
Q

The pylon (or vertical fin) may also provide
limited antitorque:

A. at all speed regimes
B. at cruise speed
C. within certain speed ranges

A

C. within certain speed ranges

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9
Q

Coning is caused by the combined forces of:

A. lift and centrifugal force
B. ground effect and torque
C. flapping and lift

A

A. lift and centrifugal force

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10
Q

When speed increases, induced drag:

A. increases
B. decreases
C. remain constant

A

B. decreases

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11
Q

The tip path plane:

A. is the same as the plane of rotation
B. is different from the plane of rotation
C. is perpendicular to the plane of rotation

A

B. is different from the plane of rotation

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12
Q

Ground effect is the:

A. increased efficiency of the rotor system
B. decreased efficiency of the rotor system
C. increase in induced drag near the ground

A

A. increased efficiency of the rotor system

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13
Q

In steady forward flight:
A. L=W, T>D
B. L=W, T=D
C. L>W, T>D

A

B. L=W, T=D

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14
Q

VNE means:
A. New Effective Speed, and is marked on ASI
as green line
B. Next Elevated Speed, and is marked on ASI
as amber band
C. Never Exceed Speed, and is marked on ASI
as a red line

A

C. Never Exceed Speed, and is marked on ASI
as a red line

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15
Q

Flapping is:
A. the fore and aft movement of the rotor
blades on a rigid rotor system
B. the up and down movement of rotor blades
about a hinge on a fully articulated rotor
system
C. the change in pitch due to load on a
semi-rigid system

A

B. the up and down movement of rotor blades
about a hinge on a fully articulated rotor
system

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16
Q

The force which tends to pull the blades
straight outward from the main rotor hub is
termed:
A. Centrifugal
B. Centripetal
C. Torsional

A

A. Centrifugal

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17
Q

Blade twist as it applies to main rotor means:
A. different blade stations have the same
pitch angle to compensate for speed
B. pitch angle increases from root to tip
C. pitch angle decreases from root to tip

A

C. pitch angle decreases from root to tip

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18
Q

The forward speed of a rotorcraft is restricted
primarily by:
A. transverse flow effect
B. high-frequency vibration
C. dissymmetry of lift

A

C. dissymmetry of lift

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19
Q

One effect of “coning” of the main rotor blades
is the:
A. decrease in AoA
B. increase in rotor rpm
C. conservation of angular velocity

A

B. increase in rotor rpm

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20
Q

Gyroscopic precession means:
A. the resultant action or deflection of a
spinning object when a force is applied to
this object
B. the change in rotational speed due to gust
or uncommanded rpm input
C. The delay in the movement of rotating tail
rotor due to Coriolis Effect

A

A. the resultant action or deflection of a
spinning object when a force is applied to
this object

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21
Q

Tail strike on single-rotor helicopters is most likely to occur in:

A. Forward flight
B. Rearward flight
C. Sideward flight

A

B. Rearward flight

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22
Q

Autorotation:
A. Is permitted aerodynamically if the tail
rotor fails
B. is not permitted in any conditions due to
safety issues
C. is permitted mechanically by a
freewheeling unit

A

C. is permitted mechanically by a
freewheeling unit

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23
Q

The total lift force:
A. is always perpendicular to the tip-path
plane of the main rotor
B. is always parallel to the tip-path plane
of the main rotor
C. is always at an angle to the tip-path
plane of the main rotor

A

A. is always perpendicular to the tip-path
plane of the main rotor

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24
Q

In a single-engine helicopter in forward flight,
the angle of attack of advancing blade is:
A. more than the retreating blade
B. equal to the retreating blade
C. less than the retreating blade

A

C. less than the retreating blade

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25
Q

Helicopters that are designed with tandem rotors do
not have an antitorque rotor because:
A. The enormous amount of thrust generated by the
rotors cancels the need for a tail rotor
B. both rotor systems rotating in opposite
directions counteract the torque rather than a
tail rotor
C. They were certified to maintain sufficient
dynamic stability

A

B. both rotor systems rotating in opposite
directions counteract the torque rather
than a tail rotor

26
Q

It was noted on a piston helicopter that both
main rotor rpm and manifold pressure is low.
This can be corrected by:
A. increasing the throttle
B. increasing the collective pitch
C. Increasing the cyclic pitch

A

A. increasing the throttle

27
Q

Helicopter flight control inputs are:
A. cyclic, collective, antitorque and
throttle
B. lateral, vertical and longitudinal
C. directional, rotational, altitude and roll

A

A. cyclic, collective, antitorque and
throttle

28
Q

The purpose of midspan weight added to main
rotor blade is to:
A. maintain static balance
B. Reduce dynamic balance
C. increase inertia

A

C. increase inertia

29
Q

K-coupling is the coupling between:
A. flapping and feathering
B. flapping and dragging
C. feathering and dragging

A

A. flapping and feathering

30
Q

Cyclic control varies the:
A. pitch of the tail rotor blades
B. pitch angle of all the main rotor blades
collectively
C. pitch of the rotor blades throughout each
revolution of the main rotor system

A

C. pitch of the rotor blades throughout each
revolution of the main rotor system

31
Q

Collective control varies the:
A. pitch of the tail rotor blades
B. pitch angle of all the main rotor blades
collectively
C. pitch of the rotor blades throughout each
revolution of the main rotor system

A

B. pitch angle of all the main rotor blades
collectively

32
Q

Chemical rain repellant should not be used on
dry windshields because:
A. it causes microcracks which propagates and
become a No-Go Item over time
B. it reduces/restricts visibility
C. it reacts with plastic

A

B. it reduces/restricts visibility

33
Q

The three basic classifications of main rotor
system are:
A. semi-rigid, rigid and fully articulated
B. tandem, conventional and offset
C. Clockwise, counter-clockwise and combined

A

A. semi-rigid, rigid and fully articulated

34
Q

The basic components of the rotor system are:
A. doubler, grip and torque link
B. blade, swash-plate and pin
C. mast, hub and rotor blades

A

C. mast, hub and rotor blades

35
Q

How are main rotor systems classified:
A. according to the number of blades and
their relative position
B. according to how the main rotor blades are
attached and move relative to the main
rotor hub
C. according to ATA Chapter 61

A

B. according to how the main rotor blades are
attached and move relative to the main
rotor hub

36
Q

What is the purpose of the swash plate assembly
A. to convert stationary control inputs from the
pilot into rotating inputs which can be
connected to the rotor blades or control
surfaces
B. to convert rotating inputs from the pilot into
stationary inputs which can be connected to
the rotor blades or control surfaces
C. to provide a means to control the movement of
tail rotors through control of the main rotor
system

A

A. to convert stationary control inputs from the
pilot into rotating inputs which can be
connected to the rotor blades or control
surfaces

37
Q

The part of the swash plate connected to the
cyclic and collective pitch controls by a series
of pushrods is called?
A. flight control swash plate
B. rotating swash plate
C. stationary swash plate

A

C. stationary swash plate

38
Q

A direct-drive helicopter engine or fixed
turbine means that:
A. all power produced by the engine is used
to rotate the main rotor blades
B. the first and second stage turbines are
mechanically coupled to each other,
sharing a common shaft
C. N1 and N2 are independent of each other

A

B. the first and second stage turbines are
mechanically coupled to each other

39
Q

Main rotor and tail rotor drive systems and
other accessories such as generators,
alternators, and air conditioning is usually
driven by:

A. N1
B. N2
C. N3

A

B. N2

40
Q

The purpose of the transmission system is to:
A. Transfer energy from the horizontal pilot
inputs to rotational output on the rotor
systems
B. transfer power from the rotating main
rotor blades to turn the tail rotor blades
C. transfer power from the engine to the main
rotor, tail rotor, and other accessories
during normal flight conditions

A

C. transfer power from the engine to the main
rotor, tail rotor, and other accessories
during normal flight conditions

41
Q

The transmission system is:
A. lubricated and cooled with their own oil
supply
B. lubricated with their own oil supply
C. lubricated with their own oil supply and
cooled by fuel heat exchanger

A

A. lubricated and cooled with their own oil
supply

42
Q

The engine output rpm, compared with the optimum
rotor rpm is:
A. slower
B. faster
C. the same

A

B. faster

43
Q

Suppose the engine rpm of a specific helicopter
is 2,700. A rotor speed of 450 rpm would require
a:
A. 6:1 reduction
B. 1:6 reduction
C. 33% reduction

A

A. 6:1 reduction

44
Q

Helicopters usually have how many tachometers:
A. 6
B. 4
C. 2

A

C. 2

45
Q

When engine starter is engaged, the rotor is:
A. disconnected from the engine
B. positively seated on the engine
C. free-wheeling

A

A. disconnected from the engine

46
Q

Dual tachometers on helicopters would show the
rpm or % rpm of:
A. N1 and N2
B. Main rotor and tail rotor
C. Engine and Main rotor

A

C. Engine and Main rotor

47
Q

Where is a fuel drain valve usually located, and
what is its function?
A. topmost section of the fuel tank, and
allows draining of vented fuel
B. bottom of the fuel tank, and allows
draining of water and sediment
C. mid-section of the fuel tank, and allows
draining of expanding fuel

A

B. bottom of the fuel tank, and allows
draining of water and sediment

48
Q

Most engine anti-ice system utilize:
A. bleed air
B. electrically heated tube
C. ram air compressor

A

A. bleed air

49
Q

Pilot’s compliance with the operating
limitations specified in approved rotorcraft
flight manuals:
A. 14 CFR Part-91
B. 14 CFR Part-29
C. 14 CFR Part-27

A

A. 14 CFR Part-91

50
Q

A green band on instrument markings indicates:
A. maximum or minimum operation allowed
B. caution or transition area
C. range of continuous operation

A

C. range of continuous operation

51
Q

Aside from the usual color markings, helicopter
airspeed indicators sometimes have a blue line
to:
A. show the minimum safe autorotation speed
B. show the maximum safe autorotation speed
C. show the range of safe autorotation speed

A

B. show the maximum safe autorotation speed

52
Q

The adverse impact of high rotor rpm is:
A. possible structural damage
B. insufficient lift
C. engine fuel starvation

A

A. possible structural damage

53
Q

Which of the following limits aircraft
powerplant operations:
A. inlet temperature
B. fuel flow
C. turbine outlet temperature

A

C. turbine outlet temperature

54
Q

Fuel tanks:
A. are usually mounted to the airframe as close
as possible to the CG, to ensure negligible
effect on the CG
B. are usually mounted to the tail boom as far as
possible to the CG, to ensure effective
trimming
C. are usually mounted to the airframe on the
nose section to introduce a low pitch
environment

A

A. are usually mounted to the airframe as
close as possible to the CG, to ensure
negligible effect on the CG

55
Q

Helicopter cg is described as:
A. a given number of inches from the
reference datum
B. percent of reference chord
C. either forward or aft distance measured in
centimeters from the main rotor axis of
rotation

A

A. a given number of inches from the
reference datum

56
Q

The location of helicopter reference datum:
A. is 100 inches from helicopter nose
B. is cm from the tip of the most forward
rotor blade
C. depends on the manufacturer, as there is
no fixed rule for its location

A

C. depends on the manufacturer, as there is
no fixed rule for its location

57
Q

Higher gross weight would translate to:
A. increased power required to hover
B. decreased power required to hover
C. gross weight has no effect on power
required to hover

A

A. increased power required to hover

58
Q

How does high density altitude affect rotorcraft
performance:
A. Engine and rotor efficiency are increased
B. Engine and rotor efficiency are reduced
C. Increases rotor drag, requiring more power
for normal flight

A

B. Engine and rotor efficiency are reduced

59
Q

vX and vY refers to:
A. Engine and rotor efficiency are increased
B. Engine and rotor efficiency are decreased
C. best angle of climb speed and best
rate-of-climb speed

A

C. best angle of climb speed and best
rate-of-climb speed

60
Q

Deferral of rectification of inoperative
equipment should in accordance with the:
A. MMEL
B. MEL
C. CDL

A

B. MEL

61
Q

Hot refueling means:
A. Refueling of a turbine aircraft while the
blades are turning
B. Refueling of a turbine aircraft while the
engines are still hot
C. Refueling of a turbine aircraft while the
passengers are disembarking

A

A. Refueling of a turbine aircraft while the
blades are turning

Aircraft Structures and Design 1Aero (10 decks)

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