AMT Aircraft Structures and Materials 2

Question 1

What type of stress acts along the longitudinal axis of a structural member, tending to pull it apart?

Accepted Answer

Tensile stress

Answer

Shear stress

Answer

Compressive stress

Answer

Torsional stress

Question 2

Which heat treatment process is used to relieve internal stresses in aluminum alloys after machining without significantly reducing hardness?

Accepted Answer

Stress relieving anneal

Answer

Solution heat treatment

Answer

Precipitation hardening

Answer

Normalizing

Question 3

What is the purpose of a doubler plate installed on an aircraft skin?

Accepted Answer

To reinforce a weakened or repaired area

Answer

To reduce aerodynamic drag

Answer

To provide a corrosion barrier

Answer

To reduce skin weight

Question 4

In a semi-monocoque fuselage, which members carry the primary bending loads?

Accepted Answer

Stringers and longerons

Answer

Formers and bulkheads

Answer

Skin panels only

Answer

Gussets and brackets

Question 5

Which material property describes resistance to scratching and surface wear?

Accepted Answer

Hardness

Answer

Ductility

Answer

Toughness

Answer

Elasticity

Question 6

What does the designation '2024-T4' indicate about an aluminum alloy?

Accepted Answer

It is a 2000-series alloy in the solution heat-treated and naturally aged temper

Answer

It contains 20% copper and was normalized at 24°C

Answer

It has a tensile strength of 24,000 PSI at 20% elongation

Answer

It was manufactured using process 4 at facility 2024

Question 7

Which type of composite fiber offers the highest stiffness-to-weight ratio commonly used in aircraft primary structures?

Accepted Answer

Carbon/graphite fiber

Answer

Fiberglass (E-glass)

Answer

Kevlar (aramid)

Answer

Boron fiber