Ensamble y reglaje TLA

An airplane is controlled directionally about its vertical axis by the. rudder. elevator(s). ailerons.

The elevators of a conventional airplane are used to provide rotation about the. lateral axis. longitudinal axis. vertical axis.

Washing-in the left wing of a monoplane, for purposes of rigging corrections after flight test, will have what effect on the lift and drag of that wing?. Both drag and lift will increase due to increased angle of attack. Both drag and lift will decrease due to decreased angle od attack. The drag will decrease due to the effect to the lift increase.

If the right wing of a monoplane is improperly rigged to a greater angle of incidence than designated in the manufacturer's specifications, it will cause the. airplane to be off balance both laterally and directionally. airplane to pitch and roll about the lateral axis. right wing to have both an increased lift and a decreased drag.

The chord of a wing is measured from. leading edge to trailing edge. wingtip to wingtip. wing root to the wingtip.

When the lift of an airfoil increases, the drag will. also increase. decrease. increase while the lift is changing but will return to its original value.

What physical factors are involved in the aspect ratio of airplane wings?. Span and chord. Thickness and chord. Dihedral and angle of attack.

Improper rigging of the elevator trim tab system will affect the balance of the airplane about its. lateral axis. longitudinal axis. vertical axis.

An airplane that has a tendency to gradually increase a pitching moment that has been set into motion has. poor longitudinal stability. good lateral stability. poor lateral stability.

The purpose of wing slats is to. reduce stalling speed. decrease drag. increase speed on takeoff.

The angle of incidence of an airplane at rest. does not change when in flight. affects the dihedral of the wings in flight. is the same as the angle between the relative wind and the chord of the wing.

Buffeting is the intermittent application of forces to a part of an airplane. It is caused by. an unsteady flow from turbulence. incorrect rigging of flaps. incorrect rigging of ailerons.

Movement of an airplane along its lateral axis (roll) is also movement. around or about the longitudinal axis controlled by the ailerons. around or about the longitudinal axis controlled by the elevator. around or about the lateral axis controlled by the ailerons.

The primary purpose of stall strips is to. stall the inboard portion of the wings first. provide added lift at slow speeds. provide added lift at high angles of attack.

Rigging and alignment checks should not be undertaken in the open; however, if this cannot be avoided, the aircraft should be positioned. obliquely into the wind. facing any direction since it makes no difference if the wind is steady (not gusting). with the nose into the wind.

What type of flap system increases the wing area and changes the wing camber?. Fowler flaps. Slotted flaps. Split flaps.

The correct dihedral angle can be determined by. using a dihedral board and bubble level along the front spar of each wing. measuring the angular setting of each wing at the rear spar with a bubble protactor. placing a straightedge and bubble protactor across the spars while the airplane is in flying position.

The dihedral angle of a wing may be measured by placing a straightedge and level protractor on the. front spar. wing root. wing chord.

Where would you find precise information to perform a symmetry alignment check for a particular aircraft?. Aircraft service or maintenance manual. Aircfrat specification or type certificate data sheet. Manufacturer's service bulletins.

Where is the buttock line or buttline of an aircraft?. A width measurement left or right of, and parallel to, the vertical centerline. A width measurement left of, and perpendicular to, the vertical centerline. A height measurement left or right of, and perpendicular to, the horizontal centerline.

Where is fuselage station No. 137 located?. 137 inches aft of the zero or fixed reference line. 137 centimeters aft of the nose or fixed reference line. Aft of the engine.

Proper wing twist in a sheet metal constructed wing can usually be checked by utilizing a. bubble level and special fixtures described by the manufacturer. plum bob, sting, and straightedge. straightedge, tape measure, and carpenter's square.

The vast majority of aircraft control cables are terminated with swaged terminals, that must be. checked with a go-no-go gauge before and after, to show compliance with the manufacturer's requirements after the swaging operation. corrosion treated to show compliance with the manufacturer's requirements after the swaging operation. pull tested to show compliance with the manufacturer's requirements after the swaging operation.

What nondestructive checking method is normally used to ensure that the correct amount of swaging has taken place when installing swaged-type terminals on aircraft control cable?. Use a terminal gauge to check the diameter of the swaged portion of the terminal. Check the surface of the swaged portion of the terminal for small cracks which indicate incomplete swaging. Measure the finished length of the terminal barrel and compare with the beginning length.

When inspecting a control cable turnbuckle for proper installation, determine that. the safety wire ends are wrapped a minimum of four turns around the terminal end shanks. no more than four threads are exposed on either side of the turnbuckle barrel. the terminal end threads are visible through the safety hole in the barrel.

If all instructions issued by the swaging tool manufacturer are followed when swaging a cable terminal, the resultant swaged terminal strength should be. the full rated strength of the cable. 80 percent of the full rated strength of the cable. 70 percent of the full rated strength of the cable.

Which is an acceptable safety device for a castle nut when installed on secondary structures?. Cotter pin. Star washer. Lockwasher.

When used in close proximity to magnetic compasses, cotter pins are made of what material?. Corrosion resisting steel. Anodized aluminum alloy. Cadmium-plated low carbon steel.

When a fiber or nylon insert-type, self-locking nut can be threaded on a bolt or stud through the insert with only the fingers, it should be. rejected. re-torqued frequently. reused only in a different location.

The purpose of the vertical fin is to provide. directional stability. longitudinal stability. lateral stability.

How are changes in direction of a control cable accomplished?. Pulleys. Bell cranks. Fairleads.

What is the smallest size cable that may be used in aircraft primary control systems?. 1/8 inch. 5/16 inch. 1/4 inch.

After repairing or re-covering a rudder, the surface should be rebalanced. to manufacturer's specifications. to its spanwise axis. in its normal flight position.

Placing a piece of cloth around a stainless steel control cable and running it back and forth over the length of the cable is generally a satisfactory method of. inspecting for broken wires. applying par-al-ketone. inspecting for wear or corrosion.

The cable-operated control system of an all-metal aircraft, not incorporating a temperature compensating device, has been rigged to the correct tension in a heated hangar. If the aircraft is operated in very cold weather, the cable tension will. decrease when the aircraft structure and cables become cold. increase when the aircraft structure and cables become cold. be unaffected if stainless steel cable is installed.

Very often, repairs to a control surface require static rebalancing of the control surface. Generally, flight control balance condition may be determined by. the behavior of the trailing edge when the surface is suspended from its hinge points. checking for equal distribution of weight througout the control surface. suspending the control surface from its leading edge in the stream line position and chacking weight distribution.

Excessive wear on both of the sides of a control cable pulley groove is evidence of. pulley misalignment. cable misalighment. excessive cable tension.

Fairleads should never deflect the alignment of a cable more than. 3_degrees_. 8_degrees_. 12_degrees_.

Where does the breakage of control cable wires occur most frequently?. Breakage usually occurs where cables pass over pulleys and through fairleads. Breakage sited are unpredictable and usually occur randomly anywhere along the length of a cable. Breakage usually occurs where cables are swaged to turnbuckle and ball terminals.

With which system is differential control associated?. Aileron. Trim. Elevator.

Which statement concerning the 100-hour inspection of an airplane equipped with a push-pull tube-type control system is true?. The threaded rod ends should be checked for the amount of thread engagement by means of the inspection hole provided. The threaded rod ends should not be adjusted in length for rigging purposes because the rod ends have been properly positioned and staked during manufacture. The terminal end threads of the turnbuckles should be visible through the safety hole in the barrel.

If control cables are adjusted properly and the control surfaces tend to vibrate, the probable cause is. worn attachment fittings. oil can effects on the control surfaces. excessive cable tension.

Aircraft flight control trim systems must be designed and installed so that the. pilot can determine the relative position of the trim tab from the cockpit. operating control and the trim tab will always move in the same direction. trim system will disengage or become inoperative if the primary flight control system fails.

Stability about the axis which runs parallel to the line of flight is referred to as. lateral stability. longitudinal stability. directional stability.

The purpose of spring tabs or servo tabs is to. assist the pilot in moving the control surfaces. contribute to the static balance of the control surfaces. make in-flight trim adjustments possible.

If the control stick of an aircraft with properly rigged flight controls is moved rearward and to the left, the right aileron will move. down and the elevator will move up. down and the elevator will move down. up and the elevator will move down.

Movement of the cockpit control toward the nosedown position during a ground operational check of the elevator trim tab system will cause the trailing edge of the trim tab to move in which direction?. Upward regardless of elevator position. Downward regardless of elevator position. Downward if the elevator is in the UP position and upward if the elecator is in the DOWN position.

If the control stick of an aircraft with properly rigged flight controls is moved forward and to the right, the left aileron will move. down and the elevator will move down. down and the elevator will move up. up and the elevator will move down.

If the travel of an airplane's controls is correct but the cables are rigged exceptionally tight, what probable effect will this have when flying the airplane?. The airplane will be heavy on the controls. The airplane will tend to fall off on one wing. The pilot will be unable to fly the airplane hands-off.

During inspection of the flight control system of an airplane equipped with differential-type aileron control, side-to-side movement of the control stick will cause. each aileron to have a greater up travel (from the streamlined position) than down travel. each aileron to have a greater down travel (from the streamlined position) than up travel. the left aileron to move through a greater number of degrees (from full up to full down) than the right aileron.

A universal propeller protractor used to measure the degrees of aileron travel should be zeroed. with the aileron in the NEUTRAL position. with the aileron in the DOWN position. when the aircraft is in a level flight attitude.

The universal propeller protractor can be used to measure. degrees of flap travel. propeller track. aspect ratio of a wing.

(Refer to Figure 8.) Identify the cable that is used in primary control systems and in other places where operation over pulleys is frequent. 2. 1. 3.

A tension regulator in the flight control cable system of a large all-metal aircraft is used primarily to. retain a set tension. increase the cable tension in cold weather. decrease the tension.

(Refer to Figure 9.) When the outside air temperature is 80°F, select the acceptable 3/16 cable tension range. 117 pounds minimum, 143 pounds maximum. 130 pounds minimum, 140 pounds maximum. 120 pounds minimum, 140 pounds maximum.

Differential control on an aileron system means that. the up travel is more than the down travel. the down travel is more than the up travel. one aileron on one wing travels further up than the aileron on the opposite wing to adjust for wash-in and wash-out.

What tubings have the characteristics (high strength, abrasion resistance) necessary for use in a high-pressure (3,000 PSI) hydraulic system for operation of landing gear and flaps?. Corrosion-resistance steel annealed or 1/4H. 2024-T or 5052-0 aluminum alloy. 1100-1/2H or 3003-1/2H aluminum alloy.

which statement relating to the residual magnetizing inspection method is true?. Subsurface discontinuities are made readily apparent. It is used in practically all circular and longitudinal magnetizing procedures. It may be used only with steels which have been heat treated for stressed applications.

A Mechanic has completed a bonded honeycomb repair using the potted compound repair technique. What nondestructive testing method is used to determine the soundness of the repair after the repair has cured?. Metallic ring test. Eddy current test. Ultrasonic test.

A part which is being prepared for dye penetrant inspection should be cleaned with. a volatile petroleum-base solvent. the penetrant developer. water-base solvents only.

When checking an item with the magnetic particle inspection method, circular and longitudinal magnetization should be used to. reveal all possible defects. evenly magnetize the entire part. ensure uniform current flow.

Circular magnetization of a part can be used to detect what defects?. Defects parallel to the long axis of the part. Defects perpendicular to the long axis of the part. Defects perpendicular to the concentric circles of magnetic force within the part.

Which heat-treating process of metal produces a hard, wear-resistance surface over a strong, tough core?. Case hardening. annealing. Tempering.

Why is steel tempered after being hardened?. To relieve its internal stresses and reduce its brittleness. To increase its hardnedd and ductility. To increase its strength and decrease its internal stresses.

What aluminum alloy designations indicate that the metal has received no hardening or tempering treatment?. 3003-F. 5052-H36. 6061-O.

Which material cannot be heat treated repeately without harmful effects?. Clad aluminum alloy. unclad aluminum alloy in sheet form. 6061-T9 strainless steel.

What is descriptive of the annealing process of steel during and after it has been annealed?. slow cooling; low strength. slow cooling; high strength. Rapid cooling; high strength.

Unless otherwise specified, torque values for tightening aircraft nuts and bolts relate to. Clean, dry threads. Clean, lightly oiled threads. Both dry and lightly oiled threads.

What is generally used in the contruction of aircraft engine firewalls?. Stainless steel. Chrome-molybdenum alloy steel. Titanium nickel alloy.

Unless otherwise specified or required, aircraft bolts should be installed so that the bolthead is. upward, or in a forward direction. upward, or in a rearward direction. downward, or in a forward direction.

(Refer to the figure 43.) Identify the clevis bolt illustrated. 1. 2. 3.

A bolt with a single raised dash on the head is classified as an. AN corrosion-resistant steel bolt. NAS standard aircraft bolt. NAD close tolerance bolt.

How is a clevis bolt used with a fork-end cable terminal secured?. With a shear nut tightened to a snug fit, but with no strain imposed on the fork and safetied with a cotter pin. With a castle nit tightened until slight binding occurs between the fork and the fitting to which it is being attached. With a shear nut and cotter pin ot a thin self-locking nut tightened enough to prevemt rotation of the bolt in the fork.

Where is an AN clevis bolt used in an airplane?. Only for shear load applications. For tension and shear load conditions. Where external tension loads are applied.