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AAMT2-8 > 2106 PRELIMS > Flashcards

2106 PRELIMS Flashcards

1
Q

used to describe two or more materials that are combined to form a structure that is much stronger than the individual components.

A

composite

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2
Q

The simplest composite is composed of two elements:

A

matrix and reinforcing materials

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3
Q

generally in a liquid form that serves as a bonding substance

A

matrix

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4
Q

solid form that provide the primary structural strength to the composite structure when combined in a matrix

A

reinforcing materials

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5
Q

This manual developed by the aircraft Manufacturers that includes information prepared for the AMT or technicians who performs work on units, components and system while they are installed on the airplane.

A

AIRCRAFT MAINTENANCE MANUAL

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6
Q

a chemical additives that quicken cure, or chemical reactions

A

ACCELERATOR

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7
Q

A material that are mixed into a two –part resin system to improve the properties of the systems.

A

ADDITIVES

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8
Q

A substance that is applied to two mating surfaces to bond them together by surface attachments.

A

ADHESIVES

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9
Q

Fibrous materials embedded in a resin matrix. The term ADVANCED applied those materials, which have superior strength and stiffness and the process in which they are manufactures

A

ADVANCED COMPOSITES

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10
Q

The weight of the fiber reinforcement per unit area of tape of fabric.

A

AREA WEIGHT.

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11
Q

A manual developed BY THE COMPONENT manufacturer and frequently adopted by the airframe manufacturer. A CMM is most frequently not approved by the FAA. Blanket approval comes through the AMM and SRM.

A

COMPONENT MAINTENANCE MANUAL (CMM)

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12
Q

combination of two or more materials (reinforcing elements, fillers, and composite matrix binder), differing in form or composition on a macro-scale. The constituents retain their identities—that is, they do not dissolve or otherwise merge completely into one another, although they act in concert. Normally, the components can be physically identified and exhibit an interface between one another.

A

COMPOSITE

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13
Q

The resistance to resist the crushing force

A

COMPRESSIVE STRENGTH

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14
Q

An impurity of foreign substance present in the marterials or environment that affects one or more properties of the materials, particularly adhesion.

A

CONTAMINANT.

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15
Q

A compression damage of the core

A

CORE CRUSH

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16
Q

to change the physical properties of the mteril by chemical reaction, by the application of catalyst , heat and pressure , alone or in combination.

A

CURE

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17
Q

Individual fibers woven together to produce cloth.

A

FABRIC

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18
Q

Single strands of materials used reinforcement because of its high strength and stiffness.

A

FIBER.

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19
Q

A require document which is produced by the manufacturer. It has the parts and their part numbers exploded for identification.

A

ILLUSTRATED PARTS CATALOG

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20
Q

One Fabric resin layer that is bonded to adjacent layers in the curing process

A

LAMINATE

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21
Q

Persons performing a repair or alteration under parts 121 and 135, or repair stations certificated under part 145. As used in this AC, this term includes Maintenance Repair Organization(MRO), certificated repair stations (CRS), and operators’ maintenance facilities.

A

Maintenance Organization (MO).

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22
Q

The alignment of the fibers to the baseline set by the manufacturer for the perpendicular component.

A

ORIENTATION

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23
Q

The length of time that the resin, mixed with catalyst will be in a workable state.

A

POT-LIFE

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24
Q

a manual which developed by the manufacturer to cover all items not listed as minor, maintenance , including instructions for structural repair, major component removal, installation and adjustment set up. Etch.

A

STRUCTURAL REPAIR MANUAL

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25
Q

The life span that a product will remain useful, and in FAA AC 43-214 define shelf life as the length of time a raw material may be in storage under specific conditions and still meet the requirements of the applicable material specification, also known as storage life.

A

SHELF LIFE.

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26
Q

The cumulative length of time a material may be out of freezer storage, prior to curing, and still maintain the required processability characteristics and mechanical properties. Also known as a limit on the amount of accumulated out time before further action needs to be taken to ensure the raw material is still usable (also known as work life).

A

Out Life

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27
Q

FAA

A

Federal Aviation Administration

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28
Q

CAAP

A

Civil Aviation Authority of the Philippines

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29
Q

ACAP

A

Army’s Advanced Composite Airframe Program

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30
Q

FRP

A

Fiber Reinforced Plastic

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31
Q

NDT

A

Nondestructive Testing

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32
Q

NDI

A

Nondestructive Inspections

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33
Q

PVC

A

Polyvinyl chloride

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34
Q

SRM

A

Structural Repair Manual

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35
Q

AMM

A

Aircraft Maintenance Manual

36
Q

MSDS

A

Material Safety Data Sheet

37
Q

contains the reference to the ATA numbering system which is a common referencing standard for commercial aircraft documentation. This commonality permits greater ease of learning and understanding for pilots, aircraft maintenance technicians, and engineers alike.

A

ATA 100

38
Q

ADVANTAGES OF USING A COMPOSITE

A
  1. High strength to weight ratio
  2. Flexible
  3. Can resist high vibrations
  4. Do not corrode
  5. Reduced wear
39
Q

APPLICATION OF COMPOSITE PLASTICS

A
  1. Fairings
  2. Flight control surfaces
  3. Landing gear doors
  4. L&T panels on the wing and stabilizers
  5. Interior components
  6. Floor beams & floor boards
  7. H&V stabilizers primary structures on the large A/C
  8. Primary wing and fuselage structures on new generation large aircraft
  9. Turbine engine fan blades
  10. Propellers
40
Q

provide the primary structural strength to the composite structure when combined with a matrix

A

reinforcing fibers

41
Q

types of reinforcing materials

A
  1. Fiberglass
  2. Aramid
  3. Carbon/Graphite
  4. Boron
  5. Ceramic
42
Q

made from small strands of molten silica glass that are spun together and woven into cloth. Many different weaves of fiberglass are available, depending on a particular application.

A

fiberglass

43
Q

advantage of fiberglass

A

Widely available &low cost make fiber glass one of the most popular reinforcing fibers.

44
Q

disadvantage of fiberglass

A

weighs more and has less strength than most other composite fibers.

45
Q

three common types of fiber glass

A

e-glass
s-glass
c-glass

46
Q

two most common types of fiberglass

A

s-glass and e-glass

47
Q

otherwise known as “electric glass” because of its high resistivity to current flow, is produced from borosilicate glass and is the most common type of fiberglass used for reinforcement.

A

e-glass

48
Q

produced from magnesia-alumina-silicate, and is used where a very high tensile strength fiberglass is needed.

A

s-glass

49
Q

Is a borosilicate glass commonly used for reinforcement because of its low cost and good strength characteristics

A

e-glass

50
Q

Is a magnesia-silicate glass that its up to 40 percent stronger than the e-glass and retains its strength characteristic at higher temperature.

A

s-glass

51
Q

Is used in materials that require chemical resistance.

A

c-glass

52
Q

usually characterized by its yellow color, light weight, tensile strength , and remarkable flexibility.

A

aramid

53
Q

exhibits high tensile strength, exceptional flexibility, high tensile stiffness, low compressive properties, and excellent toughness.

A

aramid

54
Q

In the early 1970s, DuPont introduced aramid, an organic aromatic-polymide polymer, commercially known as

A

kevlar

55
Q

is a registered trademark of the El DuPont company and its most widely used Aramid. The tensile strength of aluminum is about 4 times that of Kevlar composite

A

kevlar

56
Q

Grade of Kevlar fibers

A
  1. Kevlar grade 49
  2. Kevlar grade 29
  3. Kevlar grade 129
57
Q

Aramid is ideal for use in aircraft parts that are subject to

A

high stress and vibration.

58
Q

advantage of aramid

A

strength-to-weight ratio; it is very light compared to other composite materials.

Flexible

ideal material for use in aircraft parts that are subject to high stress and vibration.

59
Q

disadvantage of aramid

A

The high strength of this materials can cause a problem when Aramid structure are subjected to repair.

it does not have as much compressive strength

60
Q

produced in an inert atmosphere by the pyrolysis of organic fibers such as rayon, poly-acrylonitrile, and pitch.

A

carbon fibers

61
Q

Carbon fibers are typically carbonized at approximately

A

2400 F and composed of 93% to 95% carbon

62
Q

graphite fibers are produced at approximately

A

3450 to 5450 F and are more than 99% carbon.

63
Q

advantage of carbon/granite

A

very strong, stiff reinforcement and used for its rigid strength characteristics.

high compressive strength and degree of stiffness.

64
Q

disadvantage of carbon/granite

A

Has a problem of being corrosive when bonded to aluminum.

65
Q

made by depositing the element boron on a thin filament of tungsten.

A

boron fibers

66
Q

advantage of boron

A

has excellent compressive strength and stiffness, and is extremely hard. Have a very high strength and stiffness in tension, compression and bending stress.

67
Q

disadvantage of boron

A

Hazardous to work with its high expense
* Not common to used with civil aviation

68
Q

used where a high-temperature application is needed.

A

ceramics

69
Q

allows for manipulation of the fabric to form contoured shapes. Fabrics can often be stretched along the bias but seldom along the warp or fill.

A

bias

70
Q

The threads that run the length of the fabric as it comes off the bolt and designated at 0 , more threads and stronger than fill directions.

A

warp

71
Q

Are those that run perpendicular to the warp fibers, designated as 90 and weft are the threads that interweave with the warp threads.

A

Weft (FILL)

72
Q

It is parallel to the warp threads, and its been removed for all fabrication and repair works.

A

SELVAGE EDGE

73
Q

Fabrics used in composite construction are manufactured in several different styles:

A

unidirectional, bi-directional, multidirectional, and mat.

74
Q

Materials used in aircraft constructions are commonly found in three styles

A
  1. Non-woven unidirectional fabric
  2. Woven fabric
  3. Mat
75
Q

This fiber orientation in which all of the major fibers run in one direction, giving strength in that direction is known as the unidirectional or the non woven fabric.

A

unidirectional

76
Q

This fabric are woven together in a number of weaves and weights and are more resistant to fiber breakout, delamination, and more damage tolerant than unidirectional materials

A

woven fabric

77
Q

woven with the warp threads usually outnumbering the weft, so there is usually more strength in the warp direction than the fill.

A

bi-directional

78
Q

This type of fabric is woven from different types of fibers. Intraply hybrid fabrics give composites specific strength, flexibility, and durability characteristics, depending on the combination and proportion of the fibers woven together.

A

intraphy hybrid

79
Q

Most common weaves used in advanced composite aircraft construction are the

A

plain and satin weaves

80
Q

not as strong as a unidirectional or woven fabric , and therefore is not commonly used in a repair work.

A

mat

81
Q

Fabric styles are characterized by the ff:

A
  1. Yarn construction
  2. Count
  3. Weight
  4. Thickness
  5. Weaves
82
Q

A manufacturer can design a part by using different types of fiber combination to tailor a part for strength or to reduce cost.

A

hybrid

83
Q

three common types of hybrid

A
  1. intraply hybrid
  2. interply hybrid
  3. selevtive placement
84
Q

utilize reinforcing material that is woven from two or more different fibers. The strength of the final structure can be designed based on the proportions of each fiber used .

A

intraply hybrid

85
Q

uses two or more layers of different reinforcing materials that are laminated together.Each layer in addition to being a different material, may be used in the form of unidirectional or bi-directional fabric

A

interply hybrid

86
Q

FiBERrs may be selectively palce to give greater strength , flexibility or reduced cost.

A

selective placement

87
Q

To find the amount of strength in a laminate that is 50% fibers and a 50% resin

A

add the tensile strength of the resin and divided by 2.

AAMT2-8 (10 decks)

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