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Propeller LO 4.2 - 4.12

Total questions: 58

Worksheet time: 29mins

Name
Class
Date
1.

The type of propeller assembly which blade pitch or angle CANNOT be changed both in flight and on ground is known as?

a)

Stator Propeller

b)

Fixed Pitch Propeller

c)

Variable Pitch Propeller

2.

The type of propeller assembly which has the ability to change the blade pitch both in flight and on ground is known as:

a)

Stator Pitch Propeller

b)

Fixed Pitch Propeller

c)

Variable Pitch Propeller

3.

What is ability of Variable Pitch Propeller?

a)

Remain static of the blade pitch both in flight and on ground

b)

Propeller assembly which blade pitch or angle cannot be changed

c)

Able to change the blade pitch both in flight and on ground

4.

In order to ease engine starting, the blades are turned to :-

a)

fine pitch

b)

coarse pitch

c)

extra fine pitch

5.

Why during starting blade attitude is selected to extra fine pitch?

a)

To reduce the air loads

b)

To achieve short takeoff capability

c)

To prevent propeller blade damage

6.

To ease engine starting the propeller blade pitch are selected passing through………. to extra fine pitch ;

a)

Fine Pitch Stop

b)

Course Pitch Stop

c)

Centrifugal Latch

7.

The RPM Control Lever is connected to a control unit, known as the………….., that is mounted on and driven by the engine:

a)

Constant Speed Unit

b)

Pitch Control Mechanism

c)

Counterweight

8.

The function of fine pitch stops or flight fine pitch stops is;

a)

to prevent the propeller moving into extra fine in flight

b)

to prevent the propeller moving coarse pitch.

c)

to prevent damage the engine.

9.

The propeller must not come out of the feathered position by accident as this may result in serious damage to the engine and also create ;

a)

asymmetric problems in controlling the aircraft.

b)

Gyroscopic problem in controlling the aircraft.

c)

Slipstream problem in controlling the aircraft.

10.

The rotation of propeller caused by air flowing over it without engine operating is termed?

a)

wind-milling

b)

plain of rotation

c)

propeller tracking

11.

What is the purpose of feathering the propeller?

a)

prevent further damage to the propeller

b)

prevent further damage to the engine

c)

prevent further damage to the governor

12.

Prevention of the propeller moving into extra fine or ground fine is by?

a)

The Fine Pitch Stops

b)

The Course Pitch Stop

c)

The Centrifugal Latch

13.

Which pitch stop is used to prevent the propeller blade from moving into feathered position during constant speed range?

a)

Fine Pitch Stop

b)

Course Pitch Stop

c)

Centrifugal Latch

14.

Which pitch stop that is used to prevent the propeller blade from going to feather position?

a)

Fine pitch stop.

b)

Coarse pitch stop.

c)

Feather pitch stop.

15.

Which pitch stop that is used to prevent the propeller blade from going to feather position at the constant speed range?

a)

Fine pitch stop.

b)

Coarse pitch stop.

c)

Feather pitch stop.

16.

To ensure the propeller moves to feather position, the blade must move beyond:-

a)

course pitch stop

b)

fine pitch stop

c)

feather pitch stop

17.

The propeller may have to be …………..in the event of an engine or propeller drive malfunction;

a)

negative pitch

b)

feathered

c)

coarse pitch

18.

The propeller held in fine pitch is by?

a)

The oil pressure

b)

The counterweight

c)

The engine rpm

19.

In a single acting propeller, the blade moves into coarse pitch under:

a)

counterweights and feathering spring forces

b)

feathering spring force

c)

engine oil pressure

20.

In a single acting propeller, blade angle is increased by.

a)

counterweights and a feathering spring.

b)

CTM.

c)

oil pressure.

21.

How the blades turn or move to coarser pitch?

a)

The oil pressure move the piston forward

b)

The engine speed and feathering spring move the piston forward

c)

The counterweights and feathering spring move the piston forward

22.

The blade angle of Single Acting Variable Pitch Propeller is controlled by?

a)

Centrifugal Latch

b)

Propeller Hub

c)

Constant Speed Unit

23.

The propeller governor control the :-

a)

spring tension on the pilot valve flyweight

b)

oil flow during feathering and reversing

c)

oil to and from the pitch change mechanism

24.

In a single acting propeller, feathering is accomplished by moving the pilot's control lever to minimum rpm position; this action would cause :-

a)

governor valve to move down

b)

governor valve to move up

c)

governor valve to remains in neutral position

25.

Forward movement of the pilot's control lever will increase spring loading and result in a?

a)

finer propeller pitch and higher engine speed.

b)

coarse propeller pitch and lower engine speed.

c)

finer propeller pitch and lower engine speed.

26.

The counterweights produce a centrifugal twisting moment, but because they are positioned at 90° to the chord line, they tend:

a)

to move the blades to coarse pitch.

b)

to move the blades to fine pitch.

c)

to move the blades to extra fine pitch.

27.

What device fitted to constant speed propeller to prevent the propeller blades move to the feathered position when the aircraft is on the ground as the engine is switched off?

a)

Pitch Stopper

b)

Fine Pitch Stop

c)

Centrifugal Latch

28.

To prevent the propeller blades moving into the feathered position when the aircraft is on ground as engine shut down is by having:

a)

Fine Pitch Stop.

b)

Course Pitch Stop.

c)

Centrifugal Latch.

29.

What are the centrifugal latches in a single acting propeller used for?

a)

Prevent CTM

b)

Prevent feathering of the prop on shutdown

c)

Prevent Propeller moving to superfine

30.

The purpose of an accumulator in a single acting propeller system is:

a)

to assist in feathering the propeller

b)

to accelerate the unfeathering process

c)

to provide back up to the governor pump

31.

The function of constant speed unit is to maintain:

a)

blade pitch constant

b)

propeller blade angle constant

c)

engine rpm constant

32.

When pilot's rpm lever is set to maximum rpm, an increased in throttle setting would cause :-

a)

an increase in blade angle to absorb engine power

b)

a decrease in blade angle to absorb engine power

c)

no effect in blade angle position

33.

During overspeed condition, the constant speed unit will moves the blade to……….. pitch, increase the load of the engine until piston valve return to neutral position.

a)

Coarser pitch

b)

Finer pitch

c)

Feather

34.

On an underspeed condition the blades are turned to:

a)

fine

b)

feather

c)

coarse

35.

When propeller blade is feathered, the blade chord line is:

a)

at negative angle

b)

at right angle to the airflow

c)

almost parallel to the airflow

36.

The propeller feathering pump is:

a)

Electrically operated through a switch

b)

Driven by the engine accessory drive

c)

Driven by constant speed unit

37.

In electrically operated variable pitch propeller, the blade angle is varied by:

a)

dc electric motor

b)

reversible electric motor

c)

electric motor

38.

The propeller blades are the most likely part which is subjected to damage by?

a)

Windy condition

b)

Being struck by foreign objects

c)

Pilot failure to engine control failure

39.

The process of determining the positions of propeller blades tips relative to each other is known as :-

a)

dynamic balance

b)

blade tracking

c)

propeller shaft run-out check

40.

How to observed blade damage if no visible sign of damage?

a)

Normally engineer or technician will use magnifying glass

b)

Normally remove propeller assembly sent to manufacture

c)

Normally be indicated by vibration from the propeller assembly

41.

Propeller blade tracking is the process of determining: -

a)

each blade has the same angle of attack to prevent vibration

b)

the position of the propeller blade tips relative to each other

c)

the plain of rotation of the propeller with respects to the aircraft longitudinal

42.

The propeller retaining nut should not be tightened if the main propeller shaft is:

a)

Hot

b)

Warm

c)

Cold

43.

Blades that are bent, twisted outside the normal blade twist profile, or cracked, or have severe surface damage must be considered ;

a)

unserviceable

b)

serviceable

c)

scrap

44.

What type of ice that formed is dense, tough and adheres closely to the surface of the blade material?

a)

Glaze Ice

b)

Rime Ice

c)

Hoar Frost

45.

The most severe and dangerous form of ice formation is:

a)

glaze ice

b)

rime ice

c)

hoar frost

46.

What type of ice formation is a light, porous, opaque, rough, deposit and results from small water drops freezing?

a)

Glaze Ice

b)

Rime Ice

c)

Hoar Frost

47.

This type of ice formation is a light, porous, opaque, rough, deposit and results from small water drops freezing is:

a)

Glaze ice

b)

Rime ice

c)

Hoar ice

48.

This type of ice is formed in clear air when water vapour is converted directly into ice and builds up a white feathery semi-crystalline coating, when the propeller is below freezing point:

a)

Glaze ice

b)

Rime ice

c)

Hoar ice

49.

What type of ice builds up a white feathery semi-crystalline coating?

a)

Glaze ice

b)

Rime ice

c)

Hoar frost

50.

The two basic types of propeller de-icing systems are?

a)

Electrical and hot air de-icing

b)

Fluid and hot air de-icing

c)

Fluid and electrical de-icing

51.

During flight, ice formation on propeller blade will cause:

a)

vibration and reduction in thrust

b)

blade angle to reduce

c)

an increase in thrust

52.

Ice formation on the propellers, when the aircraft is in flight, will.

a)

decrease available engine power

b)

increase aircraft stall speed and increase noise

c)

decrease thrust and cause excessive vibration

53.

De-icing fluid goes to a slinger ring from;

a)

an electrical pump

b)

a hand pump

c)

a tank in the prop hub, providing constant feed once released

54.

Where is the de-icing boot?

a)

Root

b)

Trailing edge

c)

Tip

55.

To provide a guide to produce an even spread of de-icing fluid across the propeller blade is by using?

a)

Overshoe

b)

Blade twist

c)

Slinger ring

56.

Effective de-icing by heat generated within heater elements construction is achieved by:

a)

Fluid anti-icing system

b)

Electrical de-icing system

c)

Bleed air anti-icing system

57.

Propeller blades are de-iced by

a)

electrical heating elements bound in rubber overshoes on the blade leading edges

b)

generating eddy currents in the blade

c)

electrical heating elements wound around rubber shoes

58.

Propeller de-icing for varying rates of icing can be varied by.

a)

increasing propeller RPM

b)

increasing cyclic timing

c)

increasing the AC or DC voltage