Multiple Choice Structures & Materials
Structural Materials and Aircraft Quiz
Test your knowledge about structural materials, their properties, and applications in aviation with this comprehensive quiz! Perfect for students and professionals alike, it covers a variety of topics to challenge your understanding.
- 60 multiple-choice questions
- Insightful explanations
- Enhance your learning experience in aerospace materials
How is aluminium anodised?
Sprayed with a nickel solution
Made the anode of an electrolytic cell
Dipped in a bath of molten zinc
Tempering steel gives
Increased hardness
Increased brittleness
Increased ductility
In a tensile strength test
The material is pulled to destruction
The material is pulled till the elastic limit is reached
The material is pulled till UTS is reached
A sheet of aluminium has the code 2024 - TH6 marked on its surface. Which part of the code identifies the percentage of allowing element?
First two digits
Second two digits
Final three characters
For a composite material containing phenol-formaldehyde to cure properly
Low temperature is required
Room temperature is required
High temperature is required
What NDT testing method is primarily used to detect damage in composite panels?
X-ray
Coin tap
Ultrasound
Damage tolerant design
Can be applied only to tertiary structure
Allows a certain amount of damage to go un-repaired between scheduled maintenance events
Allows a certain amount of damage to go un-repaired by redistributing loads
Aircraft skin is classified as
Primary structure
Secondary structure
Tertiary structure
If a piece of structure must be replaced after a certain number of cycles, flying hours or calendar hours then it is referred to as
Fail safe
Safe life
Condition monitored
The primary purpose of sealant used in pressurised aircraft is
To seal the cabin
To reduce water ingression
To improve external streamlining
The maximum level of resistance acceptable between adjacent components of aircraft skin is
5 Ω
0.5 Ω
0.05 Ω
Which of the following is a method of lighting discharge protection in non-metallic aircraft structures?
Conducting compound in nose wheel tyres
Conducting lead trailing from the main landing gear leg
A current carrying cage embedded in the structure
Which structural item is designed to resist hoop stress in the pressure cabin?
Stringer
Frame
Spar
In a damage tolerant design which of the following is the most likely method of attachment of a large structural item such as a wing empennage or engine?
A large number of small bolts carrying low loads
A small number of large bolts carrying large loads
A small number of small bolts carrying large loads
Which of the following is needed to allow a control cable to pass through a pressure bulkhead?
An O-Ring
A fairlead
A grommet
How may moveable aircraft parts be bonded to the main structure
Use of conductive paint
Rigid aluminium rods
Flexible braded aluminium leads
Which parts of the aircraft are classified as secondary structure
Lightly stressed parts that if damaged will not cause immediate danger to the airframe
Heavily stressed parts that if damaged will cause immediate danger to the airframe
Heavily stressed parts that if damaged will not cause immediate danger to the airframe
The main landing gear load is usually carried by
The wing rear spar only
The wing rear spar and an auxiliary spar
The wing front and rear spars
Which one of the following items is intended to carry circumferential loads
Frame
Longeron
Stringer
Which of the following items may be needed near a cut out such as an aircraft door?
Longeron
Stringer
Butt Strap
Aircraft skin is joggled to
Provide smooth airflow at faying surfaces
Make a frame lighter without reducing its strength
Conform to the aircraft contour
The main metal in the allow monel is
Iron
Nickel
Aluminium
Which of these tests involves indenting a material with a ball?
Brinell
Rockwell A
Rockwell C
What is the purpose of small holes in aircraft stringers next to the skin?
To allow condensation to drain toward the bilge of the aircraft
To allow for thermal expansion and contraction of the aircraft
To reduce faying damage between the stringer and the skin
A tie is a structural item that is strong in
Tension
Compression
Shear
ATA zone 400 is
Left wing
Right wing
Nacelle and engine
Semi-Monocoque construction
Utilises the safe life design concept
Offers good damage resistance
Is used only for the fuselage
Stringers are used in which type of aircraft construction?
Truss
Semi-monocoque
Monocoque
If an aircraft structure has multiple load paths it is
Failsafe design
Safe life design
Monocoque design
A bonded waffle doubler acts a skin strengthener and what else?
Tear stopper
Jury strut
Shear tie
Medium carbon steels have a carbon content of
0.3 - 0.5 %
0.5 - 0.8 %
0.8 - 1.05 %
A ferrous metal contains
Aluminium
Iron
Magnesium
Exhaust systems are usually made from stainless steel which is susceptible to
Surface corrosion
Filiform corrosion
Intergranular corrosion
During a rockwell hardness test what dimension is measured?
The diameter of the indent
The depth of the indent
The diameter and depth of the indent
What does the 0 in 2024-T3 mean?
The percentage of impurities in the alloy
The allow has not been modified
The allow has been modified
Impact resistance measures the
Material toughness
Material hardness
Material ductility
The charpy test measures
Strain
Impact energy
Youngs modulus
Pure aluminium is
Highly resistant to corrosion
Not resistant to corrosion
Reasonably resistant to corrosion
Clad aluminium allow (alclad) has a pure aluminium coating of
0.002
1% of alloy thickness
5% of alloy thickness
Why is nickel chromium used in many exhaust systems?
Corrosion resistant and high heat conductivity
Lightweight and flexible
Corrosion resistant and low expansion coefficient
Why is stop drilling carried out at the end of a crack?
To change the direction of the crack
To stop the crack from propagating
To increase the stress concentration at the crack end
Youngs modulus is a measure of
Strain
Stress
Stiffness
Fibre weave strength is greatest in the direction of the
Weft
Warp
Bias
A composite flap panel has structural damage. What NDT method will you use to detect?
High voltage x-ray
Low voltage x-ray
Coin tap test
A thermoplastic can be
Heated and formed only once
Is not affected by even low temperatures
Can be reheated and reformed more than once
Sandwhich panels made of metal honeycomb construction are used on modern aircraft because this type of construction
May be repaired by gluing replacement skin to the innner core material with thermoplastic resin
Is lighter than single sheet skin of the same strength and is more corrosion resistant
Has a high strength to weight ratio
The vacuum connections on a fibreglass repair must be placed onto the
Top layer of glass fabric directly
Breather mat
Peel ply
In a poorly produced repair to skin structure where would stress corrosion start?
Radiate from the corner or sharp edges
Along the edges of repair
Form internally to produce surface corrosion
Corrosion at the grain boundaries is called
Intergrannular
Fretting
Filiform
What do the letters and numbers on a british rivet mean
Material specification only
Material and finish
Head shape, material and finish
Rivet allowance is
1.5D
1D plus the thickness of the material
1.5D plus the thickness of the material
A factor which determines the minimum space between rivets is the
Thickness of the material being riveted
Diameter of the rivets being used
Length of the rivets being used
The length of solid rivets is in graduations of
1/16 inch
1/8 inch
1/4 inch
Rivets main strength quality is to resist
Tensile loads
Shear loads
Torsion
In aircraft zoning the water line is considered
Vertical distance from longitudinal datum
Vertical distance from station 100
Vertical distance from cabin flooring
An aircraft skin is classed as a
Primary structure
Tertiary structure
Secondary structure
An aircraft stressed skin will primarily resist
Bending forces
Compression forces
Tension forces
On pressurised aircraft the rear bulkhead is domed
To create more internal space
To ease fabrication times
To withstand pressure loading without deformation
A damage tolerant structure will
Require extra structural members
Eliminate extra structural members
Structural strengthening is dependent on aircraft zone
Semi-Monocoque construction
Offers good damage resistance
Is used only for the fuselage
Utilises the safe life design concept
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