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Airframes > Assembly and Rigging > Flashcards

Assembly and Rigging Flashcards

1
Q

Which statement is true regarding cantilever wing?

A

No external bracing is needed.

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2
Q

The monocoque fuselage relies largely on the strength of…?

A

skin or covering.

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3
Q

Which part(s) of a semi monocoque fuselage prevent(s) tension and compression from bending the fuselage?

A

Longerons and stringers.

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4
Q

The acute angle formed by the chord line of a wing and the relative wind is known as the…?

A

angle of attack.

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5
Q

As the angle of attack of an airfoil increases, the center of pressure will…?

A

move toward the leading edge.

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6
Q

The chord of a wing is measured from

A

leading edge to trailing edge.

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7
Q

When the lift of an airfoil increases, the drag will

A

also increase

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8
Q

What physical factors are involved in the aspect ratio of airplane wings?

A

Span and chord.

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9
Q

Where is the buttock line or buttline of an aircraft?

A

A width measurement left or right, of and parallel to, the vertical centerline.

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10
Q

Where is fuselage station No. 137 located?

A

137 inches aft of the zero or fixed reference line.

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11
Q

Wing dihedral, a rigging consideration on most airplanes of conventional design, contributes most to stability of the airplane about its

A

longitudinal axis

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12
Q

Other than the manufacturer maintenance manual what other document could could be used to determine the primary flight control surface deflection for an imported aircraft that is reassembled after shipment?

A

Aircraft type certificate data sheet.

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13
Q

If a pilot reports that an airplane flies left wing heavy, this condition may be corrected by

A

increasing the angle of incidence of the left wing, or decreasing the angle of incidence of the right wing, or both.

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14
Q

If the vertical fin of a single engine, propeller driven airplane is rigged properly, it will generally be parallel to

A

the vertical axis but not the longitudinal axis.

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15
Q

An airplane which has good longitudinal stability should have a minimum tendency to

A

pitch

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16
Q

The angle of incidence is that acute angle formed by

A

a line parallel to the wing chord and a line parallel to the longitudinal axis of the aircraft.

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17
Q

An airplane’s center of lift is usually located aft of its center of gravity

A

so that the airplane will have a nose heavy tendency.

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18
Q

An airplane is controlled directionally about its vertical axis by the

A

rudder.

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19
Q

The elevators of a conventional airplane are used to provide rotation about the

A

lateral axis

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20
Q

Washing in the left wing of a monoplane, for purposes of rigging corrections after flight test, will have what effect on the lift and drag of that wing?

A

Both drag and lift will increase due to increased angle of attack.

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21
Q

What type of flap system increases the wing area and changes the wing camber?

A

Fowler flaps.

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22
Q

If the right wing of a monoplane is improperly rigged to a greater angle of incidence than designated in the manufacturer’s specifications, it will cause the

A

airplane to be off balance both laterally and directionally

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23
Q

Improper rigging of the elevator trim tab system will; affect the balance of the airplane about its

A

lateral axis

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24
Q

An airplane that has a tendency to gradually increase a pitching moment that has been set into motion has

A

poor longitudinal stability

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25
Q

The purpose of wing slats is to

A

reduce stalling speed.

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26
Q

The angle of incidence of an airplane at rest

A

does not change when in flight

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27
Q

Buffeting is the intermittent application of forces to a part of an airplane. It is caused by

A

an unsteady flow from turbulence?

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28
Q

Movement of an airplane along its lateral axis (roll) is also movement

A

around or about the longitudinal axis controlled by the ailerons.

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29
Q

The primary purpose of stall strips is to

A

stall the inboard portion of the wings first.

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30
Q

Rigging and alignment checks should not be undertaken in the open; however, if this cannot be avoided, the aircraft should be positioned

A

with the nose into the wind

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31
Q

The correct dihedral angle can be determined by

A

using a dihedral board and bubble level along the front spar of each wing.

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32
Q

The dihedral angle of a wing may be measured by placing the straightedge and level protractor on the

A

front spar.

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33
Q

Where would you find precise information to perform a symmetry alignment check for a particular aircraft?

A

Aircraft service or maintenance manual

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34
Q

Proper wing twist in a sheet metal constructed wing can usually be checked by utilizing a

A

bubble level and specific fixtures described by the manufacturer

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35
Q

The vast majority of aircraft control cables are terminated with swaged terminals, that must be

A

checked with a go-no-go gauge before and after, to show compliance with the manufactures requirements after the swaging operation

36
Q

What nondestructive checking method is normally used to ensure that the correct amount of swaging has taken place when installing swaged-type terminals on aircraft control cable?

A

Use a terminal gauge to check the diameter of the swaged portion of the terminal

37
Q

When inspecting a control cable turnbuckle for proper installation, determine that

A

the safety wire ends are wrapped a minimum of four turns around the terminal end shanks.

38
Q

If all instructions issued by the swaging tool manufacture are followed when swaging a cable terminal, the resultant swaged terminal strength should be

A

the full rated strength of the cable.

39
Q

Which is an acceptable safety device for a castle nut when installed on secondary structures?

A

Cotter pin.

40
Q

When used in close proximity to magnetic compasses, cotter pins are made of what material?

A

Corrosion resistant steel.

41
Q

When a fiber or nylon insert-type, self-locking nut can be threaded on a bolt or stud through the insert with only the fingers, it should be

A

rejected.

42
Q

The purpose of the vertical fin is to provide

A

directional stability.

43
Q

How are changes in the direction of a control cable accomplished?

A

Pulleys.

44
Q

What is the smallest size cable that may be used in aircraft primary control systems?

A

1/8 inch.

45
Q

After repairing or recovering a rudder, the surface should be rebalanced

A

to manufacturer’s specifications.

46
Q

Placing a piece of cloth around a stainless steel control cable and running it back and forth over the length of the cable is generally a satisfactory method of

A

inspecting for broken wires.

47
Q

The cable operated control system of an all metal aircraft, not incorporating a temperature compensating device, has been rigged to the correct tension in a heated hangar. If the aircraft is operated in a very cold weather, the cable tension will

A

decrease when the aircraft structure and cables become cold.

48
Q

Very often, repairs to a control surface require static rebalancing of the control surface. Generally, flight control balance condition may be determined by

A

the behavior of the trailing edge when the surface is suspended from its hinge points.

49
Q

Excessive wear on both of the sides of a control cable pulley groove is evidence of

A

pulley misalignment.

50
Q

Fairleads should never deflect the alignment of a cable more than

A

3 degrees

51
Q

Where does the breakage of control cable wires occur most frequently?

A

Breakage usually occurs where cables pass over pulleys and through fairleads.

52
Q

With which system is differential control associated?

A

Aileron.

53
Q

Which statement concerning the 100-hour inspection of an airplane equipped with a push pull tube type control system is true?

A

The threaded rod ends should be checked for the amount of thread engagement by means of the inspection hole provided.

54
Q

If control cables are adjusted properly and the control surfaces tend to vibrate, the probable cause is

A

worn attachment fittings.

55
Q

Aircraft flight control trim systems must be designed and installed so that the

A

pilot can determine the relative position of the trim tab from the cockpit.

56
Q

Stability about the axis which runs parallel to the line of flight is referred to as

A

lateral stability

57
Q

The purpose of spring tabs or servo tabs is to

A

assist the pilot in moving the control surfaces.

58
Q

If the control stick of an aircraft with properly rigged flight controls is moved rearward and to the left, the right aileron will move

A

down and the elevator will move up

59
Q

Movement of the cockpit control toward the nose down position during a ground operational check of the elevator trim tab system will cause the trailing edge of the trim tab to move in which direction?

A

Upward regardless of elevator position.

60
Q

If the control stick of an aircraft with properly rigged flight controls is moved forward and to the right, the left aileron will move

A

down and the elevator will move down

61
Q

If the travel of an airplane’s controls is correct but the cables are rigged exceptionally tight, what probable effect will this have when flying the airplane?

A

The airplane with be heavy on the controls.

62
Q

During inspection of the flight control system of an airplane equipped with differential-type aileron control, side to side movement of the control stick will cause

A

each aileron to have greater up travel (from the streamlined position) than down travel.

63
Q

A universal propeller protractor used to measure the degress of aileron travel should be zeroed

A

with the aileron in the NEUTRAL position

64
Q

The universal propeller protractor can be used to measure

A

degrees of flap travel

65
Q

A tension regulator in the flight control cable system of a large all metal aircraft is used primarily to

A

retain a set tension

66
Q

Differential control on an aileron system means that

A

the up travel is more than the down travel

67
Q

(refer to figure 8 pg 1-16)

Identify the cable that is used in primary control systems and in other places where operation over pulleys is frequent

A

3

The 7 x 19 cable is made up of seven strands of 19 wires each. It is extra flexible, and is used in primary control systems.

68
Q

Longitudinal (Fore and aft) structural members of a semi monocoque fuselage are called…?

A

Longerons and stringers

69
Q

Refer to figure 9 pg 1-17)

When the outside air temperature is 80 degrees F, select the acceptable 3/16 cable tension range.

A

117 pounds minimum, 143 pounds maximum

70
Q

Why is it generally necessary to jack an aircraft indoors for weighing?

A

So that air currents do not destabilize the scales.

71
Q

Which should be accomplished before jacking an aircraft?

A

Install critical stress panels or plates.

72
Q

The auxiliary (tail) rotor of a helicopter permits the pilot to compensate for and/or accomplish which of the following?

A

Torque and directional control

73
Q

The vertical flight of a helicopter is controlled by

A

collective pitch changes

74
Q

A decrease in pitch angle of the tail rotor blades on a helicopter

A

causes the tail to pivot in the direction of torque rotation around the main rotor axis

75
Q

In rotorcraft external-loading, the ideal location of the cargo release is where the line of action passes

A

through the center of gravity at all times.

76
Q

A helicopter in forward flight, cruise configuration, changes direction by

A

tilting the main rotor disk in the desired rotation

77
Q

The purpose in checking main rotor blade tracking is to determine the

A

flight path of the blades during rotation

78
Q

In a hovering helicopter equipped with a tail rotor, directional control is maintained by

A

varying the pitch of the tail rotor blades.

79
Q

If a single rotor helicopter is in forward horizontal flight, the angle of attack of the advancing blade is

A

less than the retreating blade.

80
Q

Main rotor blades that do not cone by the same amount during rotation are said to be out of

A

track.

81
Q

One purpose of the freewheeling unit required between the engine and the helicopter transmission is to

A

automatically disengage the rotor from the engine in case of an engine failure.

82
Q

Which statement is correct concerning torque effect on helicopters?

A

Torque direction is the opposite of rotor blade rotation.

83
Q

What is the purpose of the free wheeling unit in a helicopter drive system?

A

It disconnects the rotor whenever the engine stops or slows below the equivalent of rotor RPM

84
Q

Movement about the longitudinal axis (roll) in a helicopter is effectedby movement of the

A

cyclic pitch control

85
Q

Movement about the lateral axis (pitch) in a helicopter is effected by movement

A

cyclic pitch control.

Airframes (14 decks)

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