AME airframe Rev.03

Which statement is correct concerning torque effect on helicopters?. Torque direction is the same as rotor blade rotation. Torque direction is the opposite of rotor blade rotation. As horsepower decreases, torque increases.

Longitudinal (fore and aft) structural members of a semi monocoque fuselage are called. longerons and stringers. spars and stringers. spars and ribs.

Which statement is true regarding a cantilever wing?. No external bracing is needed. It requires only one lift strut on each side. It has nonadjustable lift struts.

The monocoque fuselage relies largely on the strength of. skin or covering. longerons and formers. bulkheads and longerons.

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

The auxiliary (tail) rotor of a helicopter permits the pilot to compensate for and/or accomplish which of the following?. Torque and directional control. Lateral and yaw position. Attitude and airspeed.

The vertical flight of a helicopter is controlled by. collective pitch changes. cyclic pitch changes. increasing or decreasing the RPM of the main rotor.

A decrease in pitch angle of the tail rotor blades on a helicopter. causes the tail to pivot in the direction of torque rotation around the main rotor axis. is required to counteract main rotor torque produced by takeoff RPM. causes the tail to pivot in the opposite direction of torque rotation around the main rotor axis.

In rotorcraft external-loading, the ideal location of the cargo release is where the line of action passes. aft of the center of gravity at all times. forward of the center of gravity at all times. through the center of gravity at all times.

The acute angle formed by the chord line of a wing and the relative wind is known as the: angle of attack. longitudinal dihedral angle. angle of incidence.

A helicopter in forward flight, cruise configuration, changes direction by. varying the pitch of the main rotor blades. changing rotor RPM. tilting the main rotor disk in the desired direction.

The purpose in checking main rotor blade tracking is to determine the. extent of an out of balance condition during rotation. flight path of the blades during rotation. relative position of the blades during rotation.

In a hovering helicopter equipped with a tail rotor, directional control is maintained by. tilting the main rotor disk in the desired direction. changing the tail rotor RPM. varying the pitch of the tail rotor blades.

If a single rotor helicopter is in forward horizontal flight, the angle of attack of the advancing blade is. equal to the retreating blade. more than the retreating blade. less than the retreating blade.

Main rotor blades that do not cone by the same amount during rotation are said to be out of. balance. collective pitch. track.

One purpose of the freewheeling unit required between the engine and the helicopter transmission is to. automatically disengage the rotor from the engine in case of an engine failure. permit practice of autorotation landings. disconnect the rotor from the engine to relieve the starter load.

What is the purpose of the free wheeling unit in a helicopter drive system?. It releases the rotor brake for starting. It relieves bending stress on the rotor blades during starting. It disconnects the rotor whenever the engine stops or slows below the equivalent of rotor RPM.

Movement about the longitudinal axis (roll) in a helicopter is effected by movement of the. cyclic pitch control. collective pitch control. tail rotor pitch control.

Movement about the lateral axis (pitch) in a helicopter is effected by movement of the. collective pitch control. cyclic pitch control. tail rotor pitch control.

Wing dihedral, a rigging consideration on most airplanes of conventional design, contributes most to stability of the airplane about its. longitudinal axis. lateral axis. vertical axis.

Other than the manufacturer maintenance manual what other document could be used to determine the primary flight control surface deflection for an imported aircraft that is reassembled after shipment?. The certificate of airworthiness issued by the importing country. Import manual for the aircraft. Aircraft type certificate data sheet.

If a pilot reports that an airplane flies left wing heavy, this condition may be corrected by. increasing the dihedral angle of the left wing, or decreasing the dihedral angle of the right wing, or both. adjusting the dihedral angle of the left wing so that differential pressure between the upper and lower wing surfaces is increased. increasing the angle of incidence of the left wing, or decreasing the angle of incidence of the right wing, or both.

If the vertical fin of a single engine, propeller driven airplane is rigged properly, it will generally be parallel to. both the longitudinal and vertical axes. the vertical axis but not the longitudinal axis. the longitudinal axis but not the vertical axis.

An airplane which has good longitudinal stability should have a minimum tendency to. pitch. roll. yaw.

As the angle of attack of an airfoil increases, the center of pressure will. move toward the leading edge. remain stationary because both lift and drag components increase proportionally to increased angle of attack. move toward the trailing edge.

The angle of incidence is that acute angle formed by. a line parallel to the wing from root to tip and a line parallel to the lateral axis of the aircraft. a line parallel to the wing chord and a line parallel to the longitudinal axis of the aircraft. the angular difference between the setting of the main airfoil and the auxiliary airfoil (horizontal stabilizer) in reference to the longitudinal axis of the aircraft.

An airplane's center of lift is usually located aft of its center of gravity. to improve stability about the longitudinal axis. so that the airplane will have a tail heavy tendency. so that the airplane will have a nose heavy tendency.

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

The elevators of a conventional airplane are used to provide rotation about the. vertical axis. longitudinal axis. lateral 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?. The drag will decrease due to the effect of the lift increase. Both drag and lift will increase due to increased angle of attack. Both drag and lift will decrease due to decreased angle of attack.

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

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 adecreased 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. increase while the lift is changing but will return to its original value. also increase. decrease.

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

Improper rigging of the elevator trim tab system will affect the balance of the airplane about its. vertical axis. lateral axis. longitudinal 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 angle of incidence of an airplane. does not change in flight. affects the dihedral of the wings. is that 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. incorrect rigging of flaps. an unsteady flow from turbulence. incorrect rigging of ailerons.

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

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

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

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

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

Where would you find precise information to perform a symmetry alignment check for a particular aircraft?. Manufacturer's service bulletins. Aircraft service or maintenance manual. Aircraft Specification or Type Certificate Data Sheet.

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

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

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

The vast majority of aircraft control cables are terminated with swaged terminals, that must be. corrosion treated to show compliance with the manufacturers requirements after the swaging operation. pull tested to show compliance with the manufactures requirements after the swaging operation. checked with a go-no-go gauge before and after, to show compliance with the manufacturers 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?. 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. Use a terminal gauge to check the diameter of the swaged portion of the terminal.

When inspecting a control cable turnbuckle for proper installation, determine that. the terminal end threads are visible through the safety hole in the barrel. 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.

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. 70 percent of the full rated strength of the cable. 80 percent of the full rated strength of the cable.

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

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

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. re-torqued frequently. rejected. reused only in a different location.

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

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

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

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

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 wear or corrosion. inspecting for broken wires. applying par-al-ketone.

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. suspending the control surface from its leading edge in the streamline position and checking weight distribution. the behavior of the trailing edge when the surface is suspended from its hinge points. checking for equal distribution of weight throughout the control surface.

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

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

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

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. excessive cable tension. worn attachment fittings. oil can effects on the control surfaces.

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. longitudinal stability. lateral stability. directional stability.

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

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?. Downward regardless of elevator position. Upward regardless of elevator position. Downward if the elevator is in the UP position and upward if the elevator 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 up. up and the elevator will move down. down 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 pilot will be unable to fly the airplane hands off. The airplane will be heavy on the controls. The airplane will tend to fall off on one wing.

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

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

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. provide a means of changing cable tension in flight.

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

Why is it generally necessary to jack an aircraft indoors for weighing?. So aircraft may be placed in a level position. So weighing scales may be calibrated to 0 pounds. So that air currents do not destabilize the scales.

Which should be accomplished before jacking an aircraft?. Install critical stress panels or plates. Determine that the fuel tanks are empty. Make sure the aircraft is leveled laterally.