INDUCCIÓN TLA I

(1) The rotors of a helicopter are considered part of the airframe since they are actually rotating wings. (2) Propellers and rotating airfoils of an engine on an airplane are not considered part of the airframe. Regarding of above sentences: The number (1) sentence is false and the number (2) sentence is true. Both the number (1) sentence and number (2) sentence are true. The number (1) sentence are true, while the number (2) sentence is false.

Constructing the airplane fuselage, the rivets, bolts, screws, fasteners, welding, adhesives, and special bonding techniques are used to ?. To join the airframe components. To carry a load or to resist stress. To made the special fuselage forms.

The airframe of a fixed-wing aircraft consists of five principal units: 1. Bulkheads. 2. Flight control surfaces. 3. Fuselage. 4. Landing gear. 5. Longerons. 6. Stabilizers. 7. Stringers. 8. Wings. 1, 2, 5, 6 and 8. 2, 3, 6, 7 and 8. 2, 3, 4, 6 and 8.

____________ is the stress that resists a force that tends to pull something apart. Bending. Tension. Torsion.

The airframe of a fixed-wing aircraft consists of five principal units: the fuselage, wings, stabilizers, flight control surfaces, and landing gear. While on the helicopter airframes consist of the fuselage, main rotor and related gearbox, tail rotor (on helicopters with a single main rotor), and the landing gear. Regarding of the above paragraph, which parts are on the airplane, but not on the helicopters, and which parts are on the helicopters, but not on the airplane?. The wings and landing gear; and the main rotor and related gearbox. The wings and the flight control surfaces; and the main rotor and related gearbox. The wings and the flight control surfaces; and the main rotor and landing gear.

In the past aircraft were constructed primarily of wood, then steel tubing and aluminum. Today, the aircraft are built from molded composite materials, such as carbon fiber. Structural members of an aircraft’s fuselage are: 1. Bonding. 2. Bulkheads. 3. Fasteners. 4. Longerons. 5. Ribs. 6. Rotors. 7. Stabilizers. 8. Stringers. 9. Wings. 1, 2, 8 and 9. 2, 4, 5 and 8. 2, 4, 6 and 8.

While moving the aircraft forward, the engine tends to twist it to one side, but other aircraft components hold it on course. This is stress: Bending. Tension. Torsion.

Aircraft structural members are designed to carry a load or to resist stress. In designing an aircraft, every square inch of wing and fuselage, every rib, spar, and even each metal fitting must be must be subject to examination called: Load factor. Stress Analysis. Tensile Strength.

There are five major stresses to which all aircraft are subjected are: (1) Bending. (2) Boarding. (3) Compression. (4) compressive. (5) Shear. (6) Strength. (7) Tensile. (8) Tension. (9) Torsion. 2, 3, 5, 5 and 9. 1, 2, 3, 5 and 9. 1, 3, 5, 8 and 9.

Crushing force is resists by the stress called: Compression. Convection. Torsion.

Some aircraft parts, subject to force are screws, bolts, and rivets: Shearing. Bending. Sliding.

By formers, frame assemblies, and bulkheads is true monocoque constructed and are uses to give shape to the fuselage. These structural members are located at intervals to: Be wide separate, thus weight is saved and the aerodynamics loads are distributed. Be wide separate, thus weight is saved and at points where fittings are used to attach other units such as wings, powerplants, and stabilizers. Carry concentrated loads and at points where fittings are used to attach other units such as wings, powerplants, and stabilizers.

A wing construction that uses two main longitudinal members with connecting bulkheads to furnish additional strength and to give contour to the wing, is called?. Box Beam. MonoSpar. MultiSSpar.

Why on the monocoque fuselage the skin must carry the primary stress and keep the fuselage rigid ?. Due monocoque type fuselage is constructed with no former. On the monocoque type fuselage there is no other bracing member. Monocoque type fuselage is designed to light aircraft, not for largest one.

What is the basic difference between monocoque and semimonocoque?: Monocoque is primary designed for light aircraft and rotorcraft, while the semimonocoque is designed for large aircraft. Monocoque consists of frame assemblies, bulkheads, and formers, and on the semimonocoque the skin is reinforced by longerons. Monocoque consists of frame assemblies, bulkheads, and formers, and on the semimonocoque the frames assemblies are replaced by longerons.

(1) Stringers and longerons together prevent tension and compression from bending the fuselage. (2) Stringers have high rigidity, and are chiefly used for giving strength and rigidity of the skin. Regarding of above sentences: The number (1) sentence is false and the number (2) sentence is true. Both the number (1) sentence, and number (2) sentence are true. The number (1) sentence is true, while the number (2) sentence is false.

The pressurized cabin is withstanding the difference in pressure between the air inside and outside the cabin, cycling from unpressurized to pressurized and back again each flight. According to this study guide, what in the effect over the aircraft structure ?. The metal structure experience fatigue. The metal structure reduces its strength. The structure becomes rigid quickly.

Wings are airfoils that, when moved rapidly through the air, create lift. They are built in many shapes and sizes. Wing design can vary to provide certain desirable flight characteristics. Control at various operating speeds, the amount of lift generated, balance, and stability all change as the shape of the wing is altered. Both the leading edge and the trailing edge of the wing may be straight or curved, or one edge may be straight and the other curved. One or both edges may be tapered so that the wing is narrower at the tip than at the root where it joins the fuselage. The wing tip may be square, rounded, or even pointed. Regarding of above paragraph, choose five wing descriptive sentences: 1) Their design depends on the flight characteristics. 2) Their leading edge are always straight and the trailing edge always curved. 3) Their tips are in different forms. 4) They are airfoils that create lift. 5) They are constructed form the frames and bulkheads. 6) They are constructed in many shapes and sizes. 7) They can change their mto varies stability They may be swapped between the aircrafts, they support the aircraft pressurized load They support the strength, twisting, compression, but no shear tension. one, two, four, five, and seven. one, three, four, six and seven. three, two, four, five and six.

(1) The semi cantilever wings are supported internally by structural members assisted by the skin of the aircraft, so that no external bracing is needed. (2) External struts or wires to assist in supporting the wing and carrying the aerodynamic and landing loads, are used on the full cantilever wings. Regarding of above sentences: The number (1) sentence is false, and the number (2) sentence is true. Both the number (1) sentence, and number (2) sentence are false. The number (1) sentence are true, while the number (2) sentence is false.

The wings of aircraft are designated left and right, corresponding to the left and right sides. depending of the operator procedure. of the operator when seated in the cockpit. seeing the aircraft in front of it.

The Basic Structure of the Airplane Wings is made of next parts: 1. Brace. 2. Bulkheads. 3. Ribs. 4. Shims. 5. Skin. 6. Spars. 7. Stringers. 8. Struts. 9. Truss. One, three, five, six, and eight. Two, three, five, six, and seven. Two, three, four, seven and eight.

The Spars support all distributed loads, as well as concentrated weights such as the fuselage, landing gear, and engines, they are the principle structural members of a wing. The Ribs which is attached to the wing structure, carries part of the loads imposed during flight. It also transfers the stresses to the wing ribs. The, Skin in turn, transfer the loads to the wing spars. Regarding of above paragraph: Is completely false, does not even refer to the beam or skin characteristics. It is completely true, these are beams, skin and ribs characteristics. Is partially true, since these are not skin and ribs functions.

The empennage of an aircraft is also known as the tail section. Most empennage designs consist of a tail cone, fixed aerodynamic surfaces or stabilizers, and movable aerodynamic surfaces. What parts commonly conform the empennage?. The rudder and elevator located at the aft edge of the vertical stabilizer and aft edge the horizontal stabilizer, respectively; And the horizontal and vertical stabilizers. The fixed horizontal stabilizer; and the rudder located at the aft edge of the vertical stabilizer and an elevator located at the aft edge the horizontal stabilizer. The movable rudder located at the aft edge the horizontal stabilizer and an elevator located aft edge of the vertical stabilizer; And fixed horizontal stabilizer and vertical stabilizer.

Make a list of the Primary Flight Control Surfaces: (1) Spoilers. (2) Slots. (3) Ailerons. (4) Slats. (5) Servo Tabs. (6) Rudder. (7) Flaps. (8) Elevators. One, three and eight. Three, six and eight. Three, four and six.

They extend forward and down from the inboard wing leading edge. They are usually inboard on the wings’ trailing edges adjacent to the fuselage. They are lowered to increase the camber of the wings and provide greater lift and control at slow speeds. The above paragraph describes at: Elevator. Slat. Flaps.

This provides directional control and thus points the nose of the aircraft in the direction desired. It causes an aircraft to yaw or move about the vertical axis. The above paragraph describes at: Elevator. Rudder. Ailerons.

Modern airplanes are equipped with fly- by-wire, this basically: A system of control cables and pulleys or push pull tubes to transfer cockpit inputs to the movement of the elevator. A combination of electrical and hydraulic power. A combination of cables and pulleys and hydraulic power.

Another secondary or auxiliary is one that not only extend out of the leading edge of the wing increasing camber and lift, but most often, when fully deployed leave a slot between their trailing edges and the leading edge of the wing, they extend wing camber and can be operated independently in the cockpit. The above paragraph describes at: Trailing edge flaps. Leading Edge flaps. Slat.

Which of the next paragraphs best describes the Stall Fence ?. Small airfoil sections usually attached to the upper surface of a wing. They are designed to promote positive laminar airflow over the wing and control surfaces. Assist to maintain the boundary layer of air flowing over the wing. Usually made of aluminum, is a fixed structure most common on swept wings, which have a natural spanwise tending boundary air flow. During low speed flight, this can maintain proper chordwise airflow reducing the tendency for the wing to stall. Usually made from aluminum or composite materials, they can be designed to optimize performance at a desired speed. It is an aerodynamic device designed to reduce the drag created by the vortices in flight.

Landing gear must be strong enough to withstand the forces of landing when the aircraft is fully loaded. In addition to strength, a major design goal is to have the gear assembly be as light as possible. To accomplish this, landing gear are made from a wide range of materials including steel, aluminum, and magnesium. Wheels and tires are designed specifically for aviation use and have unique operating characteristics. Main wheel assemblies usually have a braking system. To aid with the potentially high impact of landing, most landing gear have a means of either absorbing shock or accepting shock and distributing it so that the structure is not damaged. Choose the paragraph that best summarize the above paragraph: Landing gear must be strong enough to withstand the forces of landing when the aircraft is fully loaded. To aid with the potentially high impact of landing, most landing gear have a means of either absorbing shock or accepting shock and distributing it so that the structure is not damaged. The landing gears must be very strong, but light, so they are made of steel, magnesium and aluminum. The wheels and the brakes are designed for aviation. Most gears are equipped with shock absorbers to absorb impacts. Landing gear must be strong enough to withstand the forces of landing when the aircraft is fully loaded. Wheels and tires are designed specifically for aviation use and have unique operating characteristics. Most gears are equipped with shock absorbers to absorb impacts.

The monocoque fuselage relies largely on the strength of. Longerons and formers. Skin or covering. Bulkheads and longerons.

Which part(s) of a semi-monocoque fuselage prevent(s) tension and compression from bending the fuselage ?. The fuselage covering. Longerons and stringers. Bulkheads and skin.

The I-beam wooden spar is routed to: Increase strength. Obtain uniform strength. Reduce weight.

Aircraft structural units, such as spars, engine supports, etc., which have been built up from sheet metal, are normally: Repairable, using approved methods. Repairable, except when subjected to compressive loads. Not repairable but must be replaced when damaged or deteriorated.