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M6c3

M6c3
52問 • 1年前
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  • 1

    In aircraft engineering terms, a composite usually consists of

    a plastic resin matrix and reinforcing fibres of various materials.

  • 2

    Epoxy resins

    are the most widely used resin types for aerospace adhesive and composite applications.

  • 3

    Epoxy resins advantage that they

    do not react with the solvents and dopes used for fabric coverings.

  • 4

    a thermosetting resin

    once cured , it cannot be become liquid again by heating .

  • 5

    A disadvantages of Thermoplastic

    lack rigidity not commonly used for aeronautical composite resins.

  • 6

    a resin characteristics

    Have ambient temperature storage

  • 7

    Cyanate esters

    the material’s has dielectric properties for manufacturing high speed radomes.

  • 8

    The composite part must be as strong and durable as

    the original.

  • 9

    the fibres in composite can be wound tightly to increase

    strength

  • 10

    Non-heat treatable aluminum alloys can be hardened by

    strain hardening.

  • 11

    In (5052-H24) the letter H indicates

    Strain hardening .

  • 12

    The composite structural defect of separation of composite panel plies is called

    delamination.

  • 13

    Common method of non-destructive of composite material are:

    ●Tap test ●Ultrasonic inspection ●Radiography/ X ray ●Vibration method and ●Thermal imaging

  • 14

    Specific repair instruction and limitations of damage of composite are provided in

    Structural Repair Manual.

  • 15

    Adhesive joints are liable to experience main types of stress:

    ●Tensile ●Shear ●Cleavage and ●Peel .

  • 16

    proposed repair scheme should meet all the original design requirements

    for the structure.

  • 17

    Strength

    is the name of the ability to support load without breaking.

  • 18

    Impact resistance

    is the ability of a material to withstand impact without shattering.

  • 19

    Stiffness

    is the ability of a material to support a load without bending too much.

  • 20

    The name given to the longitudinal direction of the fiber in woven fabric is

    warp

  • 21

    is a standard soda glass in common use for windows , etc.

    ‘A’ Glass

  • 22

    is high resistance to corrosive materials. It is normally produced and used only as a surface matt to reduce cost

    C’ Glass

  • 23

    is an improved electrical grade of glass for modern radomes

    D’ Glass

  • 24

    A fibre made

    of glass.

  • 25

    do not resist flame well and burn through more quickly than other fibres.

    Aramid fibres

  • 26

    are made from pure carbon and are black in colour.

    Carbon fibres

  • 27

    Carbon fibre composites are known of these general characteristics :

    High tensile strength and High compressive strength

  • 28

    Ceramic fibres are used in heat resistant blankets and to weave fireproof cloth for engine and pylon protection.

    high temperature application is required ,e.g. a firewall.

  • 29

    Phenolics are fairly brittle system but they have a

    good fire/smoke toxicity performance.

  • 30

    are two or three-part systems have good environmental resistance and heat resistance up to150˚C.

    Polyesters

  • 31

    Polyester fabric, used on a fabric covered airplane may be attached to the structure by

    strings or by use of fabric adhesives.

  • 32

    is a simple structure built-up from layers of cloth impregnated with resin.

    A laminate

  • 33

    Plastics are made from materials obtained from

    animal or vegetable products and coal or petroleum by-products.

  • 34

    Most aircraft control system pulleys are made from

    Tufnol

  • 35

    The best type of wood to be used in the construction of aircraft is

    Sitka Spruce

  • 36

    The standard wood type for aircraft wood structures is

    Spruce

  • 37

    When selecting wood suitable for aircraft structural use, the growth

    rate should be more than 6 rings per inch (25 mm).

  • 38

    The usual method of repairing elongated bolts in a wooden structure is done by

    fitting steel bushes.

  • 39

    Ring shake defect of wood is indicated by a parting of the

    annular rings.

  • 40

    A visible wrinkle found across the face of piece of wood , in a wooden structural member , is most likely

    a compression shake caused by compression load.

  • 41

    On a wooden aircraft structure if there is no evidence of fiber adhesion in the glue in a failed glued joint,

    this may indicate glue deterioration .

  • 42

    Curved wooden parts are made by

    soaking or steaming wood strips then clamping in a jig to set the bend.

  • 43

    wood shrinkage occurs greatest in the

    tangential direction to the growth ring.

  • 44

    Fish – eyes are small areas which have not dried uniformly due to

    surface contamination with oil, wax or silicone products.

  • 45

    Iron oxide is sometimes added to aircraft dope to improve its

    durability to adhesion

  • 46

    Retarder is used to slow the drying time of dope finishes to prevent

    blush

  • 47

    is the only inspection method for identifying excess tension in aircraft fabric covering .

    Observation

  • 48

    Excessive tension in aircraft fabric is

    usually caused by excessive dope film on new covering.

  • 49

    Fabric repair seams on a fabric covered aeroplane should be

    covered with tape.

  • 50

    Lacing cord or stringing chord used on aircraft fabric covering must have a minimum breaking strength of

    60 Ib

  • 51

    Lap seam is the only seam type in a fabric covering requires that the selvedge be left on ,or the fabric edge cut with

    pinking shears.

  • 52

    The name of time between heating and quenching

    is cooling time (typically seven seconds)

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    M11c18⚡️

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    M11c20⚡️

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    M11c1-3

    M11c1-3

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    問題一覧

  • 1

    In aircraft engineering terms, a composite usually consists of

    a plastic resin matrix and reinforcing fibres of various materials.

  • 2

    Epoxy resins

    are the most widely used resin types for aerospace adhesive and composite applications.

  • 3

    Epoxy resins advantage that they

    do not react with the solvents and dopes used for fabric coverings.

  • 4

    a thermosetting resin

    once cured , it cannot be become liquid again by heating .

  • 5

    A disadvantages of Thermoplastic

    lack rigidity not commonly used for aeronautical composite resins.

  • 6

    a resin characteristics

    Have ambient temperature storage

  • 7

    Cyanate esters

    the material’s has dielectric properties for manufacturing high speed radomes.

  • 8

    The composite part must be as strong and durable as

    the original.

  • 9

    the fibres in composite can be wound tightly to increase

    strength

  • 10

    Non-heat treatable aluminum alloys can be hardened by

    strain hardening.

  • 11

    In (5052-H24) the letter H indicates

    Strain hardening .

  • 12

    The composite structural defect of separation of composite panel plies is called

    delamination.

  • 13

    Common method of non-destructive of composite material are:

    ●Tap test ●Ultrasonic inspection ●Radiography/ X ray ●Vibration method and ●Thermal imaging

  • 14

    Specific repair instruction and limitations of damage of composite are provided in

    Structural Repair Manual.

  • 15

    Adhesive joints are liable to experience main types of stress:

    ●Tensile ●Shear ●Cleavage and ●Peel .

  • 16

    proposed repair scheme should meet all the original design requirements

    for the structure.

  • 17

    Strength

    is the name of the ability to support load without breaking.

  • 18

    Impact resistance

    is the ability of a material to withstand impact without shattering.

  • 19

    Stiffness

    is the ability of a material to support a load without bending too much.

  • 20

    The name given to the longitudinal direction of the fiber in woven fabric is

    warp

  • 21

    is a standard soda glass in common use for windows , etc.

    ‘A’ Glass

  • 22

    is high resistance to corrosive materials. It is normally produced and used only as a surface matt to reduce cost

    C’ Glass

  • 23

    is an improved electrical grade of glass for modern radomes

    D’ Glass

  • 24

    A fibre made

    of glass.

  • 25

    do not resist flame well and burn through more quickly than other fibres.

    Aramid fibres

  • 26

    are made from pure carbon and are black in colour.

    Carbon fibres

  • 27

    Carbon fibre composites are known of these general characteristics :

    High tensile strength and High compressive strength

  • 28

    Ceramic fibres are used in heat resistant blankets and to weave fireproof cloth for engine and pylon protection.

    high temperature application is required ,e.g. a firewall.

  • 29

    Phenolics are fairly brittle system but they have a

    good fire/smoke toxicity performance.

  • 30

    are two or three-part systems have good environmental resistance and heat resistance up to150˚C.

    Polyesters

  • 31

    Polyester fabric, used on a fabric covered airplane may be attached to the structure by

    strings or by use of fabric adhesives.

  • 32

    is a simple structure built-up from layers of cloth impregnated with resin.

    A laminate

  • 33

    Plastics are made from materials obtained from

    animal or vegetable products and coal or petroleum by-products.

  • 34

    Most aircraft control system pulleys are made from

    Tufnol

  • 35

    The best type of wood to be used in the construction of aircraft is

    Sitka Spruce

  • 36

    The standard wood type for aircraft wood structures is

    Spruce

  • 37

    When selecting wood suitable for aircraft structural use, the growth

    rate should be more than 6 rings per inch (25 mm).

  • 38

    The usual method of repairing elongated bolts in a wooden structure is done by

    fitting steel bushes.

  • 39

    Ring shake defect of wood is indicated by a parting of the

    annular rings.

  • 40

    A visible wrinkle found across the face of piece of wood , in a wooden structural member , is most likely

    a compression shake caused by compression load.

  • 41

    On a wooden aircraft structure if there is no evidence of fiber adhesion in the glue in a failed glued joint,

    this may indicate glue deterioration .

  • 42

    Curved wooden parts are made by

    soaking or steaming wood strips then clamping in a jig to set the bend.

  • 43

    wood shrinkage occurs greatest in the

    tangential direction to the growth ring.

  • 44

    Fish – eyes are small areas which have not dried uniformly due to

    surface contamination with oil, wax or silicone products.

  • 45

    Iron oxide is sometimes added to aircraft dope to improve its

    durability to adhesion

  • 46

    Retarder is used to slow the drying time of dope finishes to prevent

    blush

  • 47

    is the only inspection method for identifying excess tension in aircraft fabric covering .

    Observation

  • 48

    Excessive tension in aircraft fabric is

    usually caused by excessive dope film on new covering.

  • 49

    Fabric repair seams on a fabric covered aeroplane should be

    covered with tape.

  • 50

    Lacing cord or stringing chord used on aircraft fabric covering must have a minimum breaking strength of

    60 Ib

  • 51

    Lap seam is the only seam type in a fabric covering requires that the selvedge be left on ,or the fabric edge cut with

    pinking shears.

  • 52

    The name of time between heating and quenching

    is cooling time (typically seven seconds)