Aircraft Structures and Design - Set 1 (Q&A)

d

Which is not a type of vibration?

a. Noise

b. Flutter

c. Buffet

d. None of the above

b

Pressurization is a type of a slowly applied load. What is the ATA chapter for pressurization?

a. 20

b. 21

c. 22

d. 23

c

Flutter can be prevented by _____ to alter the moment of inertia of the surface.

a. weight reduction

b. pulling back on the control

c. mass balancing control surfaces

d. fuel jettisoning

d

The maximum positive maneuvering load factors for a normal and an acrobatic airplane are _____, respectively.

a. 3.8 and 3.8

b. 3.8 and 4.4

c. 1.2 and 3.8

d. 3.8 and 6.0

b

An airplane's center of lift is usually located aft of its center of gravity _____.

a. so that the airplane will have a tail-heavy tendency

b. to improve stability about the longitudinal axis

c. so that the airplane will have a nose-heavy tendency

d. to improve stability about the vertical axis

b

A support designed to allow only rotation at the point of connection, and thus reactive forces (reactions) are developed in the other directions where movements are not allowed.

a. Fixed support

b. Hinge support

c. Hinge-roller support

d. Wedge support

c

It occurs in intentional flight maneuvers in which the air loads on the wing are down or when the airplane strikes sudden downdrafts while in level flight.

a. Positive High Angle of Attack

b. Positive Low Angle of Attack

c. Negative High Angle of Attack

d. Negative Low Angle of Attack

b

It is the basic structure of an aircraft and is designed to withstand all aerodynamic forces, as well as the stresses imposed by the weight of the fuel, crew, and payload.

a. Aircraft component

b. Airframe

c. Cabin system

d. Landing Gear

a

It is the slope of the initial straight portion of the stress-strain diagram.

a. Modulus of Elasticity

b. Hooke's constant

c. Modulus of Rigidity

d. Poisson's ratio

d

Calculate the load factor of an aircraft if the ratio of the centrifugal force and weight equals 4.20.

a. 2.280

b. 2.317

c. 4.280

d. 4.317

b

The capacity of a material to absorb energy in the elastic range.

a. Toughness

b. Resilience

c. Hardness

d. Permeability

d

The limit load factor of a utility aircraft when its flaps are down is _____.

a. 4.4

b. 3.8

c. 1.2

d. 2.2

d

It is known as the measurement of height in inches. It is perpendicular from a horizontal plane located at a ground, cabin floor, or some other easily referenced location.

a. Aileron Station

b. Butt Line

c. Wing Station

d. Water Line

a

It is obtained in a pullout at the highest possible angle of attack on the wing. It is where lift and forces are perpendicular and parallel to the relative wind, respectively.

a. Positive High Angle of Attack

b. Positive Low Angle of Attack

c. Negative High Angle of Attack

d. Negative Low Angle of Attack

a

About a V-n diagram, it is the slowest speed at which the maximum load factor can be reached without stalling. a. VA

b. VB

c. VSX

d. VS1

b

When looking the aircraft's front view, the angle between the vertical line passing through the aircraft C.G. and the line between aircraft C.G. and the one of the main wheels is the _____.

a. Angle of Incidence

b. Overturn Angle

c. Tipback Angle

d. Tipforward Angle

c

An aircraft is flying at an altitude of 13,280 feet with a velocity of 180 feet per second. If the coefficient of lift is 1.35, what is the wing loading if the aircraft is in a steady-and-level, unaccelerated flight?

a. 17.499 psf

b. 31.417 psf

c. 34.574 psf

d. 80.807 psf

a

Loads that are gradually applied and cause no appreciable shock or vibration of structure.

a. Static

b. Dynamic

c. Continuous

d. Shock-resistant

b

What is the gust velocity for diving at 20,000 feet and below?

a. 12.5 ft/s

b. 25.0 ft/s

c. 30.0 ft/s

d. 50.0 ft/s

b

For a conventional, single-engine airplane of 6,000 pounds or less, the minimum design maneuvering speed is given by _____.

a. 12.5 (n₁w/s)^0.5

b. 17.0 (n₁w/s)^0.5

c. 19.5 (n₁w/s)^0.5

d. 27.3 (n₁w/s)^0.5

d

A design airplane has a weight of 2,200 pounds and a wing area of 90 square foot. It is to be certified as an acrobatic under FAR part 23. What is the negative limit maneuvering load factor in which the airplane is designed for?

a. 2.1

b. 3.8

c. 2.5

d. 3.0

c

Which is not a type of gust?

a. Sharp-edged gust

b. Graded gust

c. Blunt gust

d. 1-cosine gust

d

It is a flat sheet triangular shape used to reinforce the corners of structure.

a. Webs

b. Fittings

c. Caps

d. Gussets

a

In reference to a V-n diagram, it is the slowest speed at which the maximum load factor can be reached without stalling

a. VA

b. VB

c. VSX

d. VS1

b

The tangent of this angle where the opposite side is the frictional force and the adjacent side is the normal force is called _____.

a. bank

b. friction

c. incidence

d. attack

a

It is essentially a beam which transmits and gathers all the applied airload to the central attachment to the fuselage. a. Wings

b. Horizontal stabilizer

c. Landing gear

d. Dorsal fin

b

Which among the following statements best describes a cantilever wing?

a. Externally braced with either struts and /or bracing wires

b. Supported at one end only with no external bracing

c. Braced at both the upper and lower section of the airfoil

d. Able to be folded at the root section to ease storage in confined spaces

c

In FAR Part 23, there must be a clearance of at least _____ between each propeller and the water.

a. 7 inches

b. 9 inches

c. 18 inches

d. 19 inches

c

It is the maximum aircraft nose-up attitude with the tail touching the ground and strut fully extended.

a. Angle of Incidence

b. Overturn Angle

c. Tipback Angle

d. Tipforward Angle

b

Which among the following choices articulates the relationship of stress to strain?

a. Young's Modulus law

b. Hooke's Law

c. Poisson's ratio

d. Varignon's Law

a

Normally designed to provide restraints against rotation and all translations; therefore, reactive forces and moments (reactions) are developed along the directions where movements are not permitted.

a. Fixed support

b. Hinge-roller support

c. Wedge support

d. Hinge support

b

It is the weight of the airframe structure, powerplant installation, and fixed equipment. It is essentially a "dry" weight, excluding unusable fuel and oil, anti-icing fluid, portable water and chemicals in toilets.

a. Operational Empty Weight (OEW)

b. Manufacturer's Empty Weight (MEW)

c. Basic Empty Weight (BEW)

d. Maximum Takeoff Weight (MTOW)

c

For the design maneuvering wing loading for aileron, the average surface loading is given by _____.

a. 0.566 (n₁w/s)

b. 0.534 (n₁w/s)

c. 0.466 (n₁w/s)

d. 0.366 (n₁w/s)

a

The positive limit maneuvering load factor (+n) for an acrobatic category airplane shall not be less than ____.

a. 2.5

b. 3.8

c. 4.4

d. 6.0

b

This tail design is chosen to keep the tail out of the engines' wake or to avoid complex interference drag.

a. Conventional

b. Cruciform

c. Dual-tail

d. T-tail

d

It is the maximum structural cruising speed that should not be exceeded except in smooth air, and then only with caution.

a. VS0

b. VS1

c. VFE

d. VNO

d

It is the simplest system that can represent any general force and couple moment system acting on a body.

a. Beam

b. Truss

c. Lever

d. Wrench

b

There are _____ unknowns for a cantilever support.

a. two

b. three

c. four

d. five

d

The shear diagram on a certain portion of the beam intensifies from 0 N to 2,000 N. What is the bending moment experienced by this 3-feet portion?

a. 3,000 N-m

b. 6,000 N-m

c. 1,830 N-m

d. 915 N-m

d

Compared with the other types of wing vertical location, this type has more lateral dynamic stability

a. Parasol

b. Low

c. Mid

d. High

c

The positive limit maneuvering load factor (+n) for utility category airplane shall not be more than ____.

a. 2.5

b. 3.8

c. 4.4

d. 6.0

d

It is the angle between the vertical and the line passing through the aircraft most forward C.G. and the contact point between tire and the ground.

a. Angle of Incidence

b. Overturn Angle

c. Tipback Angle

d. Tipforward Angle

c

The main gear carries about _____ of the aircraft load.

a. 60%

b. 70%-75%

c. 80%-95%

d. 100%

a

During the landing gear design process, it may be assumed that the airplane rotation speed is _____.

a. 1.1 to 1.3 VS

b. 1.1 to 1.3 VFE

c. 1.1 to 1.3 VD

d. 1.1 to 1.3 VC

c

Airspeed corrected for instrument error, position error, and adiabatic compression flow for the altitude is called _____ airspeed.

a. true

b. indicated

c. equivalent

d. calibrated

b

When the shear diagram is _____, the moment diagram _____.

a. increasing; concaves downward

b. increasing; concaves upward

c. decreasing; concaves upward

d. constant; is also constant

d

What is the length of the moment arm of a 40 Newton force producing a moment of 40 foot-pounds?

a. 1.00 meter

b. 1.36 feet

c. 1.00 feet

d. 4.45 feet

a

It is the maximum speed at which application of full control will not overstress the airplane.

a. VA

b. VB

c. VC

d. VD

a

Which part of the window is the primary pressure-carrying pane?

a. Outer pane

b. Middle pane

c. Inner pane

d. Middle third pane

b

The U.S. FAA requires that control surface hinges, except ball and roller bearings, incorporate a special factor of not less than ____ with respect to the ultimate bearing strength of the softest material used as a bearing.

a. 5.67

b. 6.67

c. 5.76

d. 6.76