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MTP > M6 V2 > Flashcards

M6 V2 Flashcards

1
Q

A load that is uniformly distributed over a certain area and also the per unit of area expressed is PSI

A

Unit stress or stress

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2
Q

A kind of stress that results in the tending to stretch or lengthen the material

A

Tensile Stress

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3
Q

A force that compresses or shortens the material

A

Compressive stress

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4
Q

A force that results two metal riveted to each other which causes sliding motion or shear

A

Shearing stress

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5
Q

A force that twists the material.

A

Torsion Stress

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6
Q

The relations between external forces applied to an elastic body and the deformations and internal stresses resulting from those applied forces

A

Strength of Material

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7
Q

Ability of a material to be stretched and go back to its original state or recover

A

Elasticity

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8
Q

When the stress on the area is a combination of tensile, compressive, shearing, twisting

A

Combined Stress

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9
Q

When a single stress alone is considered to act

A

Simple Stress

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10
Q

The ratio of a lateral strain to longitudinal unit strain for a given material

A

Poisson’s Ratio

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11
Q

The maximum stress that can be applied to a material without permanent deformation

A

Yield strength

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12
Q

The stress at which a material in tension, compression, or shear will fracture

A

Ultimate Strength

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13
Q

The ratio of stress to strain, within the proportional limit of a material in tension or compression or the amount of deformation.

A

Modulus of Elasticity

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14
Q

Enables a material to resist penetration, wear, or cutting action

A

Hardness

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15
Q

Ability of a material to withstand forces which tend to deform or the ability of a material to resist stress without breaking

A

Strength

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16
Q

Ability of a material to be stretched and go back to its original state or recover

A

Elasticity

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17
Q

The property of metal which allows it to be reshaped.

A

Plasticity

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18
Q

The ability of a metal to be drawn into thinner sections without breaking and can resist deformation in tension

A

Ductility

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19
Q

The ability of a material that allows it to be stretched o shaped by beating with a hammer or passing through rollers and can resist deformation through compression

A

Malleability

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20
Q

The property of a material that allows it to be deformed without breaking

A

Toughness

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21
Q

Ability of a metal to break when deformed or hammered. It is the resistance to change in the relative position of molecules within the material

A

Brittleness

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22
Q

Ability of a material that makes it possible for it to transmit heat or electrical conduction

A

Conductivity

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23
Q

Ability of a material that enables it to withstand force over a period of time

A

Durability

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24
Q

Number of metals used in applications in technical fields

A

70 metals (chemical elements)

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25
Q

Density of airframe constructions light weight metals in kg/dm3

A

Less than 5

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26
Q

On a/c structures, Density of heavy weight metals in kg/dm3

A

Between 7.85 and 9.5

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27
Q

Method that uses diamond tip to get the depth

A

Rockwell test

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28
Q

Method that uses a steel ball to get the area

A

Brinell test

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29
Q

A rigid body in which the constituent particles are arranged in a repeating pattern.

A

Crystal

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30
Q

Known as the basic building block of a crystal

A

Unit cell

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31
Q

A unit cell that has a total of 9 atoms

A

Body-Centered-Cubic (BCC)

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32
Q

A unit cell that has a total of 14 atoms

A

Face-Centered-Cubic (FCC)

i) Examples are Cu, Au, Ni, Ag, Fe

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33
Q

A unit cell that has a total of 17 atoms.

A

Hexagonal-Closed-Packed (HCP)

Examples are Co, Mg, Ti, Zn

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34
Q

The selection of materials should be the best compromise between the________ to fulfill the requested functions and all cost at the time of aircraft development

A

quality of the material

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35
Q

The base material Iron in its pure form is __.

A

Very soft, malleable, easy to form and shape

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36
Q

Main restriction of steel is because of

A

a) high density >7.85 kg/dm3 (3x the density of Al) and susceptibility to corrosion
b) can increase corrosion resistance by adding alloying agents

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37
Q

Application of steel in an aircraft

A

Between 8 and 16 % (Airbus 320: 9%, Boeing 777: 11%)

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38
Q

Primary advantages of high-strength steels

A

High strength and high modulus of elasticity

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39
Q

Steel composition

A

Iron and Carbon

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40
Q

Iron is extracted from

A

Iron ore > Pig iron (raw material of steel)

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41
Q

Letter used for “Structural Steel” according to EN 10027 standard

A

S

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42
Q

Letter used for “Mechanical Engineering Steels” or german word “Einsatzstahl” (case hardening steel)

A

E

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43
Q

HHT steel that is the common steel alloy for use in the 180-200 ksi range

A

4130

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44
Q

HHT steel that has a strength range of 200 ksi up to 280 ksi and commonly used in 260-280 ksi range

A

4340

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45
Q

HHT steel that is commonly used is landing gear components and has 240-290 ksi range

A

300M

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46
Q

A process that increases the yield strength by temperature depending solution of aluminum atoms within the iron-crystal

A

Precipitation Hardening (PH)

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47
Q

Small surface damage such as scratches, nicks, or corrosion, localized stress concentration

A

Notch Sensitivity

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48
Q

Occurs when low- alloyed steel are deformed chip less in the cold state.

A

Cold Shortness Sensitivity

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49
Q

An accidental application of heat such as mechanical processing/ overheating during flight, may lead to structural changes and loss of stability

A

Temperature Sensitivity

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50
Q

Any wetting with acidic fluids or Mordants can lead to

A

Hydrogen Embrittlement

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51
Q

Heat treated steels may NEVER be welded or heat

A

straightened or their structure will RESHAPE

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52
Q

Applicable for steel components, which are hardened and have to be softened for mechanical processing, also called the zero state

A

Soft Annealing (becomes austenite: soft and ductile) – after
heat treatment

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53
Q

Serve for structure refinement and releasing internal stresses in the component. Reduces stress and strain before machining

A

Normalizing and Stress Relief Annealing

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54
Q

High alloy steel, >5%.

A

Demands resistance to high temp corrosion

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55
Q

Cres 14-4-ph

A

% chromium-% nickel – precipitation hardening

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56
Q

Increases the yield strength by temperature depending solution
of aluminum atoms within the iron-crystal

A

PH- precipitation hardening

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57
Q

Stainless steels are treated on when in contact with lightweight alloys and the protection is for the other material not the stainless steel.

A

Surface protection- sacrificial metal layer
i) Stainless steel- to avoid galvanic corrosion
ii) Non-stainless steel- painting, AL spraying

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58
Q

Used in aerospace industry because of light weight, high strength, heat resistant, corrosion resistant and has approximately 56% of the density of steal

A

a) Titanium

i) Density 4.5 kg/dm3 450degC

ii)Poor heat conductor

(1) Advantages: low weight, high strength (+alloying agent), high corrosion resistant, low thermal conductivity, good heat resistance (sensitive to hydrogen embrittlement)

(2) Not castable. Can only be welded by inert gas or vacuum

(3) In A/c construction STR rivets air ducts /ENG fan area

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59
Q

Tensile strength of pure aluminum is

A

Between 80 up to 600 N/mm

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60
Q

Most important titanium alloy in aircraft construction

A

Ti6Al4V

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61
Q

Most common alloying element of Titanium

A

Aluminum

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62
Q

When Titanium is exposed to temperature above 450o it must be protected from the atmosphere. Contact with media which releases hydrogen is dangerous for titanium, especially when heated above 150oC because this leads to

A

Hydrogen Embrittlement.

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63
Q

Heat resistance of titanium alloy when used in compressor blades

A

520 degrees Celcius

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64
Q

This metal is three times lighter than steel and has a melting point of 660degC

A

a) Aluminum 2.7 kg/dm3 660degC
b) one pound has more than twice the electrical conductivity of
copper
c) pure form high resistance but soft, if hardend resistance decrease

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65
Q

Good resistance against external damage

A

Non-hardenable AL Alloy

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66
Q

The strength depends on the alloy content and can be increased by_.

A

Strain Hardening

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67
Q

Can be heat treated to increase strength

A

Hardenable AL Alloy

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68
Q

A process that means to permanently weld metals layers onto a basis material, whilst applying high pressure. For corrosion protection

A

Cladding

i) Clad thin layer of pure aluminum

ii) ALCLAD / CLAD

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69
Q

Thickness of clad layers

A

3-5%(sheets with thickness that exceeds 6mm are not catalyst, which cladded)

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70
Q

Aluminum alloy that undergoes natural aging

A

2024( solidifies in 3-8 days, after 8 hrs, 90% of strength is achieved)

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71
Q

Aluminum alloy that undergoes artificial aging and the temp is about
120-200oC

A

7075(solidifies in 6-7 hrs)

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72
Q

Quenching interval

A

a) 5-15 seconds
i) Water bath 20 to 38 deg C

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73
Q

State of material after quenching

A

W-state

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74
Q

Carried out in aluminum alloys to bring the material into the minimum state of hardness and strength, whilst achieving the maximum stretch

A

a) Soft Annealing(zero state and done between 400-454oC)
b) After soft annealing aluminum MAY NOT BE QUENCHED

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75
Q

AlCuMg-alloy in a soft annealed temper which is the 0-state

A

2024-0

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76
Q

AlCuMg-alloy in a hardened temper, and is solution annealed, quenched, strain hardened and naturally aged

A

2024-T3

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77
Q

AlZnCuMg-alloy in a hardened temper, and is solution annealed, quenched, and artificially aged

A

7075-T6

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78
Q

A layered composite material that is a member of a family of materials called FML. An is an optimized FML for aircraft and consist of alternating layers of aluminum and glass fibre prepreg layers

A

a) GLass Aluminum REinforced Laminate

i) Used on fuselage skin structures on A380, aircraft cargo bay floors and liners, aircraft cargo explosive resistant containers

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79
Q

Materials that consist of thin layers of metal sheet and unidirectional fibre layers embedded in an adhesive system

A

Fibre Metal Laminate(FML)

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80
Q

Thermoset is

A

Irreversible

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81
Q

Thermoplastic is

A

reversible by application of heat

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82
Q

Term used to describe two or more materials that are combined to form a much stronger structure than either material itself and is used mainly to reduce weight

A

a) Composite

i) ADVANTAGES

(1) To reduce weight
(2) High strength to weight ratio
(3) Reduction of parts and fastener
(4) Reduction of wear
(5) Corrosion resistance

ii) DISADVANTAGES

(1) Expensive
(2) Not easy to repair
(3) Hazardous

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83
Q

Longest thread with marking

A

Warp

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84
Q

Fibers that are already impregnated with resin in the production process and then cooled down very fast which start to cure when heat is applied.

A

Prepreg/ Pre-impregnated Fibres

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85
Q

Used to connect GFRP (resin – resin connection

A

Standard – Prepreg

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86
Q

Used to connect GFRP laminates with honeycombs or sheet metal parts

A

Bonding – Prepregs

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87
Q

Percentage of resin in and “Elitrex”

A

Prepreg
i) Standard
ii) Bonding

Resin content

i) Standard - 38%
ii) Bonding - 50%

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88
Q

During the curing process in an autoclave or in a heating press, 18-
20% of resin is pressed out

A

Resinflux

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89
Q

The third component of a composite structure

A

a) Core Material

i) Foam- filler material
ii) Honeycomb- excellent strength to weight ratio

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90
Q

A process which the bonding of honeycomb is done one at a time

A

Corrugation process

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91
Q

A process which the bonding of honeycomb is done with all materials bonded simultaneously

A

Expansion process

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92
Q

Layers that build up a monolithic wall

A

5 layers

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93
Q

Layers that build up a honeycomb or sandwich

A

7 layers

94
Q

A type of construction where a core material is the center member of the assembly

A

Sandwich construction

95
Q

Used to bond two or more surfaces together. Used to distribute
stresses at bonding points and are moisture and corrosion resistant and eliminates the need for bolts and rivets

A

a) Adhesives

i) HOW TO KNOW IF ADHESIVE IS EFFECTIVE?
(1) Resistant to slippage, malleability, cohesive strength,
adhesion

96
Q

Known as polymerization adhesives and used as a modifier of natural adhesives to perform better have a greater range of application

A

Synthetic adhesives

97
Q

Synthetic adhesive or natural adhesives based on Silicon

A

Elastomeric Adhesives

98
Q

Transformed into tough, heat resistant solids by the addition of catalyst or by application of heat e.g. epoxy resins

A

Thermosetting adhesives

99
Q

Atmospheric pressure is used to press two solids together so there will be no air between the two plane parallel surface

A

Contact adhesives

100
Q

Contains plastic and resins dissolved in a solvent

A

Solvent adhesives

101
Q

Adhesives dissolved in water solution

A

Dispersion adhesives

102
Q

Bonding of Same Material

A

Cohesive

103
Q

Bonding of different material

A

Adhesive

104
Q

Bonding substance of composite and most likely be liquid in form

A

Matrix

105
Q

Resins that are best used in aircraft external structures. Used in high- tech composites because their mechanical properties are superior to those of polyesters

A

a) Epoxy resins

i) DISAVANTAGES
(1) TOXICITY (can cause dermatitis)
(2) LOW POT AND SHELF LIFE
(3) COST

106
Q

Resin + hardener ratio

A

By volume

107
Q

Adhesives that are best used inside the aircraft structures/cabin. Low toxicity

A

Phenolic Resins

108
Q

Does not have the quality for structural components because it does not bond well to fibres

A

Polyester resin

109
Q

The most important factor for bonding, and is frequently expressed with the contact angle that is formed between a droplet of a liquid and a solid

A

Surface wetting

110
Q

Take into account that the adhesives must penetrate into the cavities before curing to prevent bubbles

A

Mechanical Hooking

111
Q

The amount of time you have to work with the resins

A

Pot life

112
Q

The time which the product is still good in an unopen container

A

Shelf Life

113
Q

Too much resin is used and affects the strength of the composite by making the part brittle and add extra weight

A

Resin rich

114
Q

Damage classification

A

a) Allowable
b) Repairable
c) Non repairable

115
Q

Denomination of a process to abrade the bonding surfaces with a chemical treatment in order to enlarge the adhesive surface

A

Pickling

116
Q

A result with a contact with a sharp object and only the surface of are affected and the edges are sharp

A

Scratch

117
Q

Wider and deeper than a scratch, several plies are affected. But edges are generally smooth

A

Gouge

118
Q

Gouge and scratch repaired by

A

Removing the damage plies and hand lay- up

119
Q

Damage to a surface caused by scuffing, rubbing, or scraping of the component

A

Abrasion

120
Q

When humidity penetrates a sandwich structure this happens

A

Corrosion on sandwich structures

121
Q

Separation of materials or laminates due to adhesive failure

A

Debonding

122
Q

Method used to detect water absorption

A

Non Destructive Testing (NDT)/ Thermograph

123
Q

A deformity caused by extraneous forces, which are applied to the structure

A

Depression or Dent

124
Q

Repair recommended for small damage on honeycomb materials and loses half of the material’s original strength

A

Filling repair

125
Q

Consist of applying several layers of fabric material impregnated with a resin onto the repair surface, in order to restore the damaged skin.

A

Wet Lay – Up

126
Q

it is used to consolidate the layers in the laminated repair, remove trapped air and gases produced during curing, hold heater blankets, thermocouples and other materials in place during the curing cycle and produce desired surface finish on the repair

A

Vacuum Bagging

127
Q

Defines as an undesirable, natural reaction of materials with substances in their environments

A

a) Corrosion (derived from Latin word corrodere which means
“gnawing away”)

i) Influence Factors of Corrosion
(1) Type of metal
(2) Anode and cathode
(3) Temperature
(4) Presence of electrolyte
(5) Heat treatment

128
Q

Occurs due to the tendency of most metals to return to their natural state by combining it with atmospheric oxygen

A

Corrosion of metals

129
Q

______do not corrode since they are chemically pure.

A

Noble Metals such as gold and platinum

130
Q

Corrosion on the surface grains of the metal because of its crystalline structure and happens at the boundaries between grains

A

Intercristalline corrosion

131
Q

Material used as coating of a metal and used as anti-corrosion

A

pure aluminum coating (AlClad)

132
Q

Preventive measures on corrosion

A

i) Steel requires cadmium plating, zinc plating and aluminum coating, etc.
ii) Aluminum alloys are usually anodized
iii) Magnesium and magnesium alloys requires special chemical and electrochemical treatments and paint
finishes.

133
Q

The corrosion process that takes place at the surface of the electrode
under the influence of electrolyte and creates a half cell

A

Electrochemical Reaction

134
Q

Consist of two half cells and a noble metal and a base metal, which serves as electrodes and are each in a sulfate solution

A

Galvanic cell

135
Q

forming of oxide films/exposed from oxygen causes corrosion

A

Oxidation

136
Q

Absorbing of electrons

A

Reduction

137
Q

Oxidation Is Loss, Reduction Is Gain

A

OIL RIG

138
Q

presence of aggressive chemical in the atmosphere/ without
ELECTROLYTE

A

Chemical corrosion

139
Q

Electrically conductive fluid or moisture

A

Electrolyte

140
Q

A galvanic dissolution that commonly occurs between adjacent components, whose metals have different electrochemical potential and under the influence of electrolyte

A

Electrochemical Corrosion

141
Q

Also called the Microbes corrosion and is caused y a direct chemical attack of metabolic products of microorganisms

A

Biological corrosion

142
Q

When mechanical forces act on a component which leads to corrosion

A

Stress corrosion

143
Q

Corrosion color in steel

A

Red rust (hydrated ferric oxides)

144
Q

Corrosion product on aluminum

A

White – grey powdery material

145
Q

Special form of crevice corrosion which occurs on metals surface having an organic coating system and is identified by wormlike trace of corrosion

A

Filiform Corrosion

146
Q

Corrosion that is a combination of stress and corrosion

A

Stress corrosion

147
Q

Used as protection on titanium

A

Chromium acid anodize

148
Q

Used as lubricant for fastener

A

a) Cetylalkohol
i) Most cathodic is Carbon
ii) Most anodic is Magnesium

149
Q

Occurs when two dissimilar metals make electrical contact in the presence of an electrolyte

A

Galvanic Corrosion

150
Q

The most common type of corrosion on aluminum and magnesium and appears a white powdery deposit and the starting point for intergranular corrosion

A

Pitting Corrosion

151
Q

A corrosion on the grain boundaries of the metal and occurs when cladding is damaged

A

Intergranular Corrosion

152
Q

Mostly seen on extruded sections, this advanced type of intergranular corrosion exhibits itself by lifting up the surface of a metal by force

A

Exfoliation Corrosion

153
Q

Results in the rubbing movement between two heavily loaded surfaces and can eventually cause cracking fatigue

A

Fretting Corrosion

154
Q

A corrosion cause by bacteria, fungi or yeast in an unclean fuel and looks like a sludge like deposit.

A

Microbial Corrosion

155
Q

Necessary if a contamination of fuel tank is detected

A

Biocide (kathon or biobor)

156
Q

Occurs between two materials that come into contact, metallic or non-metallic

A

a) Crevice Corrosion
i) Solid rivets are Self-sealing fasteners
ii) For shearing loads in fasteners small head is used for
weight saving

157
Q

Fahrenheit to Celsius
a)

Celsius to Fahrenheit
a)

A
158
Q

Used to attach components or assemblies to the aircraft structures

A

Fastener

159
Q

used to attach high-strength components to the assemblies

A

aluminum solid rivets

160
Q

used for joints in high-temp areas

A

steel, titanium or monel fasteners

161
Q

If groove is formed on the external

A

Male thread

162
Q

If groove is formed internal

A

Female Thread

163
Q

Thread formed on a cylinder is known as

A

Straight or Parallel Thread

164
Q

Thread formed and cut onto a conical part

A

Taper thread

165
Q

thread with an angle of 55 degrees

A

British Standard Whitworth (BSW)

166
Q

Finer version of the whitworth thread form and the smaller thread provides a finer form of adjustment and greater resistance to vibration in all fastening devices

A

British Standard Fine (BSF)

167
Q

This is another fine-pitch adaptation of the whitworth thread form. It is used for pipeline couplings where the fine pitch ensures that sufficient uncut metal remains on the wall of a pipe to guarantee a strong connection

A

British Standard Pipe (BSP)

168
Q

Has a thread angle of 47.5 degrees

A

British Association (BA)

169
Q

They have a thread angle of 60 degrees

A

ANC and ANF (American National Coarse and Fine)

170
Q

Incorporates features from both American and British ntnl threads

A

Unified

171
Q

A screw that has a deeper thread and have fewer threads, greater lead

A

Coarse Pitch

172
Q

A screw that have a stronger root portion, tighter grip and more resistant to shaking loose, strong against vibration,

A

Fine Pitch

173
Q

Most common thread form and shaped to combine strength with ease of engagement

A

a) Vee Thread
i) Install bolts and screws foremost and uppermost

174
Q

Install nuts not less than what of the bolt

A

1/32 in (0.8mm)

175
Q

Torque values are at what manual

A

SRM ch51 or AMM

176
Q

It is where the code marking of aircraft bolts are identified

A

a) Bolt head
i) NE = Long Thread
ii) NF= Short Thread
iii) Diameter of bolt is always in 1/16
iv) Diameter of Hi- Lok and Rivet is always 1/32
v) Grip Length is always 1/16

177
Q

T> 2.4mm = max 2 thread pitches

A
178
Q

T< 2.4mm = no thread pitches w/in the hole

A
179
Q

Maximum of 3 washers may be used to adjust a grip length

A

(1 under the head, 2 under the nut)

180
Q

A piece of rod, threaded at each end with a plain portion in the middle

A

Stud

181
Q

A piece of a hexagonal metal bar, drilled and tapped through its axial center – line

A

Stud box

182
Q

Used extensively to secure thin – gauge sheet metal parts where nuts and bolts are either impractical or too expensive

A

Self-Tapping Screws

183
Q

Are used with drilled shank hex head bolts, clevis bolts, eye bolts and rivets and is designed to lock cotter pin or wirelocking

A

Non- Self Locking Nuts

Classifications:
➢ Shear Castle Nut – used only for shear load on clevis bolts
➢ Castle Nut- Are designed to fit on standard airframe bolts and
may be used when the bolt is subjected to either shear or tensile strength
➢ Slotted Engine Nut- designed for use on aircraft engine and is not approved for airframe use. Made of Heat- treated steel
➢ Wing Nut- intended for use on hose clamps and battery
connections where the desired tightness is ordinarily obtained by
the use of fingers

184
Q

Locking nuts (5) not reuseable

A

➢ Lock nut- Is a thin, plain nut which is tightened down firmly
onto the main, plain nut.
*Nyloc Stiff nuts- has an unthreaded nylon insert permanently
housed at the outer end
➢ Oddie Stiff nuts-Have six tongues at their outer end which are
bent inwards to form a circle slightly less in diameter than the
minor diameter of the bold thread
➢ Aerotight and Philidas Stiffnuts- have slotted locking
extensions which are closed during manufacture to put the screwthread out of alignment

185
Q

is used when a slight range of movement is necessary to ensure the
bolt can locate

A

Anchor Nuts / Floating type anchor nut

186
Q

High- temp self- locking Nuts

A

temp self locking >121degC (250F)

187
Q

Low- temp self- locking Nuts

A

temp self locking < 121degC (250F)

188
Q

Permit each thread to adjust to the screw and assure full load
distribution throughout the entire length of the thread, Protection for soft material

A

Heli – Coil Inserts

189
Q

A process of securing all aircraft bolts, nuts, screws, pins and other fasteners so that they do not work loose due to vibration

A

Safetying

190
Q

Most positive and satisfactory method of safetying and is a method of wiring together two or more units in such a manner that any tendency of one to loosen is counteracted by the tightening of the wire

A

Wirelocking

191
Q

Most common method of wire locking

A

Double - Twist Method

192
Q

either a single coil or square section spring with sharp corners or a double coil spring.

A

Spring Washers

193
Q

is a metal washer with two or more tabs, suitable for use with plain nuts. One tab is bent against one of the flats of the nut and the other is bent over an edge of the component or fitted into or hole machined in the component. Not reusable

A

Tab Washers

194
Q

is a spring steel washer with slanting serrations on its internal or external circumferences

A

Shakeproof Washer

195
Q

is a simple and secure, non-threaded fastener, allowing rapid installation and removal of parts without tooling

A

Pip pin

196
Q

A single ball locates the pin, no positive
lock

A

Ring Pull Detent Pin

197
Q

it is a instantaneous self locking, vibration resistant and easy application pin

A

Double Acting Steel Pin

198
Q

designed so that it can be quickly inserted into the grommet by compression of the spring

A

Camloc Fasteners

199
Q

It has 2 types which are the light duty that is used on box covers,
access hole covers and light weight fairing and the second type which is the heavy duty type which is used on cowling and heavy fairings

A

Dzus Fasteners

200
Q

It consists of a receptacle , stud and cross pin. It has two types which is the fixed type and floating type

A

Airloc Fasteners

201
Q

used to secure bolts, screws, nuts and pins

A

Cotter Pins

202
Q

Given to a specially – shaped piece of metal that is used to transmit at considerable mechanical power from a shaft to hub

A

Keys

i) A. Taper Keys
➢ Hollow Saddle Key- is hollowed to fit the radius of the shaft
➢ Flat saddle key- is a rectangular or square section that is driven into a keyway in the hub and bears upon a flat on the shaft
➢ Gib headed key- is fitted into keyways which are machined partly in the shaft and partly in the hub. It is capable of transmitting a much greater driving load than the saddle type keys
➢ Feather key- is used when axial movement is required between the hub and the shaft
➢ Woodruff key- is made in the shape of a segment of a parallel sided disc similar to capital D. it is suitable for fitting to either parallel or taper shafts.

203
Q

Deformed portion of the Rivet

A

Upset Head

i) Selection of correct Rivet diameter is at least 3 times the
thickness of the thickest sheet being joined

204
Q

Used to attach aluminum alloy components where a low-strength rivet is sufficient to hold the load

A

Aluminum Alloy Rivets

205
Q

Without heat treatment before use, are used in steel, titanium or aluminum alloy riveted assemblies

A

Monel Rivets

206
Q

Are rivets with a cylindrical or a partial tapered shank. No heat treatment is necessary for this type of rivet

A

Titanium Rivets

207
Q

a process which a rivet material have to be heat treated before using them in the manufacturing process

A

Solution Annealing( Annealed at 495o and quenched at 20o)

i) At -18o temperature rivets can be stored for up to 7 days
ii) At -20o temperature rivets can be stored for up to 20 days

208
Q

the time between opening the furnace or removing the rivets from
the salt bath and the complete immersion of the load into the quenching medium

A

Quench Delay

209
Q

The time, within which the rivets must be upset, at room temp. 25o

A

Maximum Handling Time

210
Q

A tapered bolt with a threaded end and a self – locking nut and used in areas where a high fatigue performance is required

A

Taper – Lok

211
Q

A combination of a rivet and a nut, resembling a hollow rivet with threads inside its shank

A

Rivnut

212
Q

Combined thickness of the material to be joined

A

Grip Length

213
Q

Heat treatment of Al. Rivets
Solution Annealing

A
  • The material is annealed at 495 degrees for a certain time and after that it is quenched at 20 degrees cold water. The material can be deformed without high loads and crystal damage
  • All rivets 3.1324, 2017,2017 A and 2024- alloys must be stored at -18 degrees. At this temperature, the rivets can be stored up to 7 days and at -20 degrees, it can be stored up to 20 days
214
Q

Is a tapered bolt with a threaded end and a self locking nut. It also includes it’s own washer.

A

Taper lok fastener

215
Q

The numbers are printed in

A

Light or dark green

216
Q

They are label with white numbers

A

Red, black, or dark green wires

217
Q

The current capacity of wires is directly dependent on the

A

Conductor material, the insulation, and wire size

218
Q

There is a general rule for determining the socket side:

A

Sockets shall always be installed on the live part of the connector

219
Q

Emitting of electrons

A

Oxidation

220
Q

Tensile strength of pure titanium

A

Between 300 and 700 N/mm2

221
Q

Can be distinguished into construction steels and carbon steels

A

Non alloyed steels

222
Q

Used for aforementioned application on aircraft

A

Carbon steel

223
Q

is hollowed to fit the radius of the shaft

A

Hollow Saddle Key

224
Q

is a rectangular or square section that is driven into a keyway in the hub and bears upon a flat on the shaft

A

Flat saddle key-

225
Q

is fitted into keyways which are machined partly in the shaft and partly in the hub. It is capable of transmitting a much greater driving load than the saddle type keys

A

Gib headed key-

226
Q

is used when axial movement is required between the hub and the shaft

A

Feather key-

227
Q

is made in the shape of a segment of a parallel sided disc similar to capital D. it is suitable for fitting to either parallel or taper shafts.

A

Woodruff key-

228
Q

Is a thin, plain nut which is tightened down firmly onto the main, plain nut.

A

Lock nut-

229
Q

has an unthreaded nylon insert permanently housed at the outer end

A

Nyloc Stiff nuts-

230
Q

Have six tongues at their outer end which are
bent inwards to form a circle slightly less in diameter than the minor diameter of the bold thread

A

Oddie Stiff nuts

231
Q

have slotted locking
extensions which are closed during manufacture to put the screwthread out of alignment

A

Aerotight and Philidas Stiffnuts-

MTP (14 decks)

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