Non Ferrous Flashcards

1
Q

What is the most widely used non ferrous material used in aircraft

A

Titanium

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2
Q

Advantages of Titanium

A

High strength to weight ratio
Temperature resistance
Corrosion resistance

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3
Q

Disadvantages of titanium

A

Horrible to work with
Flammable
When exposed at high temperatures in the presence of oxygen or nitrogen it will ignite

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4
Q

Pure Aluminium

A

Extremely malleable - to soft for aircraft use
Alloyed with other metals to increase strength
Excellent corrosion resistance
Very lightweight

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5
Q

Cast aluminium

A

Cast aluminium has a grain structure that is very coarse, thus the metal is brittle. Cast aluminium is used in construction of aircraft wheels and engine crankcases.

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6
Q

Wrought aluminium

A

Wrought, its grain structure is compressed and tightened as it is forced into shapes of plates, rods, extrusions or skins. Wrought aluminium (used extensively in aircraft construction) is either non-heat- treated or heat-treated.

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7
Q

Identification of Aluminium

A

Four digit number
1st digit - major alloying element
2nd digit - Alloy modification
Last two digits - different alloys in the group

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8
Q

Clad

A

A layer of pure aluminium with 1% zinc as a means of corrosion protection
3-5% thickness of the material
Ink print corresponds to material grain structure

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9
Q

1100 Pure aluminium

A
Commercially pure 
Soft
Ductile 
Good workability 
Corrosion resistance 
NON HEAT TREATABLE
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10
Q

3003 Manganese aluminium

A

Most widely used
In trades strength up to 20%
Good corrosion resistance and workability
NON HEAT TREATABLE

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11
Q

5052 Magnesium aluminium

A
Most common 
High strength 
Good fatigue strength 
Good workability 
NON HEAT TREATABLE
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12
Q

2011 Copper aluminium

A

Most free-machining
Corrosion resistance
Good strength and hardness
HEAT TREATABLE

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13
Q

2017 Aluminium

A
Good machinablity 
High strength 
Tough 
Ductile 
HEAT TREATABLE
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14
Q

2024 Aluminium

A
Best known 
High strength 
Excellent fatigue resistance 
Low corrosion resistance 
Usually anodised finish or in clad form
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15
Q

7075 Zinc aluminium

A

High strength - density ratio
Non-weldable
Poor corrosion resistance
Normally clad

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16
Q

Annealing

A

Heat the alloy to the required temperature
Hold/soak for a length of time
Cool steadily in cool air

17
Q

Solution

A

Alloy is heated in either molten sodium or potassium nitrate
Temperature is held to within plus or minus 50°C, long enough for the copper to be taken into the solid solution with the aluminium matrix
Cooled within 10 seconds else inter granular corrosion will occur.

18
Q

Cold working

A

Will cause the copper to precipitate at grain boundaries and harden the alloy.

19
Q

Natural ageing

A

Copper penetrates grain boundaries hardening the aluminium over several days

20
Q

Artificial ageing

A

Temperature is raised to between 1200C and 1900C, depending on alloying element, this increases the precipitation hardening process and also raises the final strength of the alloy

21
Q

Code T4

A

Heat treated, naturally aged

22
Q

Code T3

A

Heat treated, cold worked

23
Q

Code T6

A

Heat treated, artificially aged

24
Q

Basic temper states

A
F = Fabricated 
O = Annealed 
H = Strain hardened 
W = Solution heat treated 
T = Heat treated to produce stable tempers
25
Q

Magnesium alloys

A
Lighter than aluminium 
Hard to work with 
Easily corrodes 
Highly flammable 
Difficult to work with
26
Q

Identification of Magnesium alloys

A

American Society for Testing Materials (ASTM) is the most widely used. The first two letters indicate the principal alloying elements. The letter corresponding to the element present in the greatest quantity is used first; if they are equal, they are listed alphabetically. The letters are followed by numbers which represent the nominal compositions of the principal alloying elements in weight (%) rounded to the nearest whole number .

27
Q

Glass Reinforced Laminate

A
Member of the fibre metal laminates family 
Consists of aluminium and glass fibres 
Fatigue resistance 
Flame resistance 
Corrosion resistance