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Aircraft Systems > Fuselage, Wings, and Stabilizing Surfaces > Flashcards

Fuselage, Wings, and Stabilizing Surfaces Flashcards

1
Q

ATA 01 to ATA 18

A

Aircraft General

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2
Q

ATA 20 to ATA 50

A

Airframe Systems

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3
Q

ATA 51 to ATA 57

A

Structure

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4
Q

ATA 61 to ATA 92

A

Powerplant

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5
Q

tends to stretch a structural member

A

Tension or Tensile

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6
Q

components designed to resist tensile loads

A

Ties

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7
Q

opposite of tensile loads and tend to shorten structural members

A

compression

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8
Q

components that are designed to resist compressive loads

A

struts

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9
Q

a force which tends to slide one face of the material over an adjacent face

A

shear

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10
Q

designed to resist shear forces

A

riveted joints

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11
Q

involves the three basic loadings

A

bending

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12
Q

three basic loadings

A

tension (outer), compression (inner), shear (across)

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13
Q

twisting force that produce tension, compression, and shear

A

torsion

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14
Q

occurs to thin sheet materials when they are subjected to end loads and to ties if subjected to compressive forces

A

buckling

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15
Q

internal force inside a structural member which resists an externally applied force

A

stress

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16
Q

defined as the force per unit area and is measured in units of N/mm^2 or MN/m^2

A

stress

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17
Q

ratio of the change in length to the original length

A

strain

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18
Q

a measure of the deformation of any loaded structure

A

strain

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19
Q

the maximum load that the designer would expect the airframe or component to experience in service

A

Design Limit Load

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20
Q

What is DLL?

A

Design Limit Load

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21
Q

Lift over weight is equal to

A

G

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22
Q

design limit load for utility aircrafts

A

3.4G 3.8G

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23
Q

design limit load for aerobatic aircrafts

A

6G

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24
Q

when it is applied the aircraft structure must not suffer any permanent deformation and all flying control and other systems must function normally

A

proof load

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25
Q

normally 1.125 x the DLL

A

proof load

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26
Q

it is the Design Limit Load multiplied by the safety factor

A

Design Ultimate Load (DUL)

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27
Q

What is DUL?

A

Design Ultimate Load

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28
Q

minimum safety factor required for a Design Ultimate Load

A

1.5

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29
Q

ratio of the ultimate load to the limit load

A

safety factor

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30
Q

defined as the minimum number of flying hours, landings, cycles, etc. which should elapse before a major structural failure occurs

A

safe life

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31
Q

this is a structure having multiple load paths which means that the loads are shared by adjacent members

A

fail safe structure

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32
Q

if one part fails, the load it carried will now be carried by the ________ member for a limited period

A

adjacent

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33
Q

eliminates the extra structural members by spreading the loading of a particular structure over a larger area

A

damage tolerant structure

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34
Q

a structure which is subjected to continual reversals of loading will fail at a load of less than would be the case for a steadily applied load

A

fatigue

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35
Q

a method of locating components on the aircraft must be established in order that maintenance and repairs can be carried out

A

station numbers

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36
Q

reference to a zero datum line at or near the forward portion of the aircraft

A

fuselage station lines

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37
Q

are given in inches forward (“-“) or aft (“+”) of the zero datum

A

station numbers

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38
Q

sign for inches forward and aft

A

-, +

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39
Q

are measured from the center line of the aircraft

A

wing stations

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40
Q

vertical position from a ground line or horizontal datum

A

water line (WL) or buttock line

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41
Q

What is WL?

A

water line

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42
Q

zoning of large aircraft is specified by the Air Transport Association of America in the ATA-100 Specification

A

Aircraft Structural Zoning System

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43
Q

Zones in Aircraft Structural Zoning System

A

Major Zone, Major Sub-zone, Simply a zone

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44
Q

lower half of the fuselage to the rear pressure bulkhead (below the main cabin deck)

A

Zone 100

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45
Q

upper half of the fuselage to the rear pressure bulkhead

A

Zone 200

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46
Q

Empennage, including fuselage aft of the rear pressure bulkhead

A

Zone 300

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47
Q

Power plants and struts or pylons

A

Zone 400

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48
Q

left wing

A

Zone 500

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49
Q

right wing

A

Zone 600

50
Q

landing gear and landing gear doors

A

Zone 700

51
Q

doors

A

Zone 800

52
Q

reserved for uncommon differences between aircraft types not covered by standard series numbers

A

Zone 900

53
Q

major zones divided to major sub-zones

A

2nd digit

54
Q

major sub-zones are divided into zones

A

3rd digit

55
Q

main structure or body of the aircraft and carries the aircraft payload in safe, comfortable conditions

A

fuselage

56
Q

stresses are set up in the fuselage of aircraft when pressurized

A

axial stress (longitudinal)

57
Q

tend to elongate the fuselage

A

axial stress (longitudinal)

58
Q

set up in addition to axial stress

A

hoop stress (radial)

59
Q

tend to expand fuselage cross section area

A

hoop stress (radial)

60
Q

internal pressure of hoop stretch (radial) can reach ______

A

65.5 kN/m^2 or 9.5 psi

61
Q

used for light, non-pressurized aircraft

A

truss type

62
Q

a strong, easily constructed and relatively trouble free basic structure

A

truss type

63
Q

covered by a lightweight aluminum alloy or fabric skin

A

truss type

64
Q

more widely used fuselage construction

A

monocoque structure

65
Q

all the loads are taken by the skin with just light internal frames or formers to give the required shape

A

monocoque structure

66
Q

materials to provide rigidity and strength

A

sandwich construction, honeycomb core with a skin of composite material, glass fiber reinforced plastics (GFRP), carbon fiber reinforced plastics (CFRP), aluminum alloy

67
Q

What is GFRP?

A

glass fiber reinforced plastics

68
Q

What is CFRP?

A

carbon fiber reinforced plastics

69
Q

pure monocoque structure with added stringers (stiffeners) and longerons to run lengthwise along the fuselage joining the frames together

A

semi-monocoque construction

70
Q

What are the stiffeners of a semi-monocoque fuselage?

A

stringers

71
Q

must withstand both the loads of pressurization and impact loads from bird strikes

A

flight deck windows

72
Q

constructed from toughened glass panels attached to each side of a clear vinyl interlayer

A

flight deck windows

73
Q

prevents ice from forming and makes the window more resilient and able to withstand bird strikes

A

electrically conducting coating

74
Q

allow pilots to land the aircraft safely in the event of windscreen obscurity

A

direct vision windows

75
Q

these are designed to be fail safe and normally have two panes of acrylic plastic mounted in an airtight rubber seal fitted into a metal window frame

A

passenger cabin windows

76
Q

support the weight of the aircraft in the air and so must have sufficient strength and stiffness

A

wings

77
Q

very few of this fly at more than 200 knots in level flight and so the air loads are low

A

bi-plane

78
Q

biplanes flying at more than ___ knots are very few

A

200

79
Q

this type of design is also used on low speed aircraft

A

braced monoplane

80
Q

the mainplanes have to absorb the stresses due to lift and drag in flight and, if of cantilever design, their own weight when on the ground

A

cantilever monoplane

81
Q

main load bearing members

A

spars

82
Q

constructed so that they will absorb the downwards bending stresses when on the ground and the upwards, rearwards and twisting stresses when in flight

A

spars

83
Q

generates direct stresses in a span wise direction as a response to bending moments and also reacts against twisting (torsion)

A

skin

84
Q

these are span wise members that give the wing rigidity by stiffening the skin in compression

A

stringers

85
Q

these maintain the airfoil shape if the wings support the spars, stringers, and skin against buckling and pass concentrated loads

A

ribs

86
Q

What does MZFM stand for?

A

Maximum Zero Fuel Mass

87
Q

maximum permissible mass of an airplane with no usable fuel

A

Maximum Zero Fuel Mass (MZFM)

88
Q

the maximum permissible airplane mass at the start of the take-off run

A

Maximum Structural Take Off Mass (MSTOM)

89
Q

What does MSTOM stand for?

A

Maximum Structural Take Off Mass

90
Q

What does MSTM stand for?

A

Maximum Structural Taxi Mass

91
Q

the maximum mass of the airplane at the commencement of the taxi

A

Maximum Structural Taxi Mass (MSTM)

92
Q

the maximum permissible total airplane mass on landing in normal circumstances

A

Maximum Structural Landing Mass (MSLM)

93
Q

What does MSLM stand for?

A

Maximum Structural Landing Mass

94
Q

types of empennage

A

conventional, t-tail, h-tail, v-tail

95
Q

provide the longitudinal and directional stability and the means of longitudinal control

A

tail

96
Q

generally smaller versions of the mainplanes in that they use spars, ribs, stringers, and skin in their construction

A

tail

97
Q

provides some aircraft their longitudinal stability and control

A

Foreplanes (canards)

98
Q

What is another term for Foreplanes?

A

canards

99
Q

what is another term for horizontal surfaces?

A

tailplane

100
Q

provide longitudinal stability by generating upwards or downwards forces as required

A

horizontal surfaces (tailplane)

101
Q

generates sideways forces as required

A

vertical surfaces (fin)

102
Q

other term for vertical surfaces

A

fin

103
Q

is the rapid and uncontrolled oscillation of a flight control which occurs as a result of an unbalanced surface

A

flutter

104
Q

can prevent flutter

A

mass balancing

105
Q

alter the moment of inertia of the surface and therefore the period of vibration

A

mass balancing

106
Q

most widely used metals for structural use due to a good strength to weight ratio

A

aluminum

107
Q

an aluminum and copper based alloy which has poor corrosion resistance except when clad with pure aluminum

A

duralumin

108
Q

duralumin is an aluminum and copper based alloy which has poor corrosion resistance except when clad with ________

A

pure aluminum

109
Q

has good conductivity and is difficult to weld

A

duralumin

110
Q

only used where strength is vital and weight penalties can be ignored

A

steel

111
Q

is much lighter than steel and can be used where fire protection is required

A

titanium

112
Q

has good strength and retains this and its corrosion resistance up to 400 deg cel

A

titanium

113
Q

Titanium retains strength and corrosion resistance up to temperatures of ______

A

400 deg cel

114
Q

their principal advantage being their weight

A

magnesium

115
Q

has an excellent strength to weight ratio because of its weight

A

magnesium

116
Q

aluminum is ______ heavier than magnesium

A

1 1/2 times

117
Q

have good resistance to corrosion and can easily be formed into complex shapes but their fatigue behavior is different to that of conventional metal alloys and is not generally a consideration at stress cycles below approximately ___ of ultimate stress

A

composite materials, 80%

118
Q

suffering fatigue retain their design strength up to a critical point after which failure occurs rapidly whereas composites lose their properties gradually

A

metal structures

119
Q

What is KFRP?

A

Kevlar Fiber Reinforced Plastics

120
Q

outperform the commonly used aircraft structural materials

A

CFRP and KFRP

121
Q

is designed to withstand landing at a particular aircraft weight and vertical descent velocity

A

aircraft landing gear

Aircraft Systems (9 decks)

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