AIRFRAME AME TEST 1

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

Which statement is true regarding a canti­lever wing?. No externa! 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. bulkheads and longerons. longerons and formers. skin or covering.

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

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

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

The chord of a wing is measured from. A- leading edge to trailing edge. B- wingtip to wingtip. C- 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?. A- Dihedral and angle of attack. B- Span and chord. C- Thickness and chord.

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

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

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 reassernbled 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. A- increasing the dihedral angle of thc left wing, or decreasing the dihedral angle ofthe right·wing, or both. B- increasing the angle of incidence of the left wing, or decreasing the angle of incidence of the right wing, or both. C- adjusting the dihedral angle of the left wing so that differential pressure between the upper and lower wing surfaces is increased.

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 mínimum tendency to. pitch. roll. yaw.

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

An airplane's center of lift is usually locat­ ed aft of its center of gravity. A- to improve stability about the longitudinal axis. B- so that the airplane will have a tail heavy tendency. C- 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. A- vertical axis. B- longitudinal axis. C- 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?. Both drag and lift will decrease due to decreased angle of attack. Both drag and lift will increase due to increased angle of attack. The drag will decrease dueto the effect of the lift increase.

What type of flap system increases the wing area and changes the wing camber?. Fowler flaps. Slotted flaps. Split 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. A- airplane to be off balance both laterally and directionally. B- airplane to pitch and roll about the lateral axis. C- right wing to have both an increased lift and a decreased drag.

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

An airplane that has a tendency to gradu­ ally increase a pitching moment that has been set into motion has. A- poor lateral stability. B- poor longitudinal stability. C- good 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. - 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. A- around or about the longitudinal axis controlled by the elevator. B- around or about the lateral axis controlled by the ailerons. C- around or about the longitudinal axis controlled by the ailerons.

The primary purpose of stall strips is to. A- provide added lift at high angles of attack. B- 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. facing any direction since it makes no difference if the wind is steady (not gusting). with the nose into the wind. obliquely into the wind.

The correct dihedral angle can be deter­ mined 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 mea­ sured 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?. A- Aircraft Specification or Type Certificate Data Sheet. B- Manufacturer's service bulletins. C- Aircraft service or maintcnance manual.

Proper wing twi.st in a sheet metal con­structed wing can usually be checked by utilizing a. A- plum bob, string, and straightedge. B- straightedge, tape measure, and carpenter's square. C- bubble level and special fixtures described by the manufacturar.

The vast majority of aircraft control cables are terminated with swaged terminals, that must be. A- corrosion treated to show compliance with the manufacturers requirements after the swaging operation. B- pull tested to show compliance with the manufactures requirements after the swa:ging operation. C- checked with a go-no-go gaugc 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 air­ craft control cable?. Check the surface of the swaged portian of the terminal for small cracks which indicate incompleta 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 portian 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 mínimum 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 manufacturar 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?. Star washer. Cotter pin. Lock washer.

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

The purpose of the vertical fin is to pro­vide. A- lateral stability. B- directional stability. C- 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?. 1/8 inch. 1/4 inch. 5/16 inch.

After repairing or recovering a rudder, the surface should be rebalanced. A- in its normal flight position. B- to its span wise axis. C- 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 gener­ ally a satisfactory method of. applying par-al-ketene. inspecting for wear or corrosion. inspecting for broken wires.

The cable operated control system of an all metal aircraft, not incorporating a tempera­ tura compensating device, has been rigged to the correct tension in a heated hangar. If the aircraft is operated in very cold weath­ er, the cable tension will. A- decrease when the aircraft structure and cables become cold. B- increase when the aircraft structure and cables become cold. C- 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. A- suspending the control surface from its leading edge in the streamline position and checking weight distribution. B- the behavior of the trailing edge when the surface is suspended from its hinge points. C- 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. excessive cable tension. pulley misalignment. cable misalignment.

Fairleads should never deflect the align­ ment of a cable more than. 12°. 3°. 8°.

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

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 terminal end threads of the turnbuckles should be visible through the safety hole in the barrel. 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 threaded rod ends should be checked for the amount of thread engagement by means of the inspection hole provided.

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

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 nms 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 thc static balance of the control surface. make in flight trim adjustments possible. assist the pilot in moving the control surfaces.

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

Movement of the cockpit control toward the nose down 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. Upward regardless of elevator 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.

During inspection of the flight control systern of an airplane equipped with dif­ ferential-type aileron control, side to side rnovement of the control stick will cause. each aileron to have greater down travel (frorn the strearnlined position) than up travel. the left aileron to rnove through a greater nurnber of degrees (frorn full up to full down) than the right aileron. each aileron to have a greater up travel (frorn the strearnlined position) than down travel.

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

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

A tension regulator inthe flight control cable system of a large all metal aircraft is used primarily to. provide a means of changing cable tension in flight. retain a set tension. increase the cable tension incold weather.

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

Identify the cable that is used in primary control systems and in other places where operation over pulleys is frequent. 2. 1. 3.

When the outside air temperatura is 80°F, select the acceptable 3/16 cable tension range. 130 pounds mínimum, 140 pounds maximum. 120 pounds mínimum, 140 pounds maximum. 117 pounds mínimum, 143 pounds maximum.

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

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

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

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 rotorblades on a helicopter. causes the tail to pivot in the opposite direction of torque rotation around the main rotor axis. causes the tail to pivot in the direction of torque rotation around the main rotor .axis. is required to counteract main rotorarque produced by takeoff RPM.

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.

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. relativa 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. disconnect the rotor from the engine to relieve the starter load. automatically disengage the rotor from the engine in case of an engine failure. permit practice of autorotation landings.

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

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.

The aluminum alloys used in aircraft con­ struction are usually hardened by which method?. Heat treatment. Aging. Cold working.

When repairing a small hole on a metal stressed skin, the major consideration in the design of the patch should be. that the bond between the patch and the skin is sufficient to prevent dissimilar metal corrosion. the shear strength of the riveted joint. -to use rivet spacing similar to a seam in the skin.

Clad aluminum alloys are used in aircraft because they. A- are stronger than unciad aluminum alloys. B- are less subject to corrosion than uncoated aluminum alloys. C- can be heat treated much easier than the other forms of aluminum.

When fabricating parts from Alelad 2024-T3 aluminum sheet stock. bends should be made with a small radius to develop maximum strength. all bends must be 90° to the grain. all scratches, kinks, tool marks, nicks,etc., must be held to a mínimum.

Thc primary alloying agent of 2024-T36 is indicated by the number. 20. 24. 2.

Which part ofthe 2017-T36 aluminum alloy designation indicates the primary alloying agent used in its manufacture?. 20. 17. 2.

Mild steel rivets are used for riveting. nickel steel parts. magnesium parts. steel parts.

When riveting dissimilar metals together, what precautions must be taken to prevent an electrolytic action?. A- Avoid the use of dissimilar metals by redesigning the unit according to the recommendations outlined in AC 43.13-ZA. B- Treat the surfaces to be riveted together with a process called anodic treatment. C- Place a protective separator between areas of potential electrical difference.

Joggles in removed rivet shanks would indicate partial. bearing failure. torsion failure. shear failure.

What type loads cause the most rivet fail­ures?. Shear. Head. Bearing.

You can distinguish between aluminum and aluminum alloy by. testing with a 10 percent solution of caustic soda. filing the metal. testing with an acetic acid solution.

Annealing of aluminum. increases the tensile strength. inakes the material brittle. removes stresses caused by forming.

When repairing puncture type damage of a metal faced laminated honeycomb panel, the edges of the doubler should be tapered to. whatever is desired for a neat, clean appearance. 100 times the thickness of the metal. - two times the thickness of the metal.

A main difference between Lockbolt/Huck­ bolt tension and shear fasteners (other than their application) is in the. A- method of installation. B- number of locking collar grooves. C- shape of the head.

One of the main advantages of Hi-Lok type fasteners over earlier generations is that. the squeezed on collar installation provides a more secure, tighter fit. they can be removed and reused again. they can be installed with ordinary hand tools.

Alloy 2117 rivets are heat treated. to a temperatura of 910 to 930°F and quenched in cold water. by the manufacturar and do not require heat treatment befare being driven . by the manufacturar but require reheat treatment befare being driven.

The markings on the head of a Dzus fasten­er identify the. A- manufacturar and type of material. B- body type, head diameter, and type of material. C- body diameter, type of head, and length af the fastener.

The Dzus turnlock fastener consists of a stud, grommet, and receptacle. The stud length is measured in. sixteenths of an inch. tenths of an inch. hundredths of an inch.

The Dzus turnlock fastener consists of a stud, grommet, and receptacle. The stud diameter is measured in. sixteenths of an inch. hundredths of an inch. tenths of an inch.

Threaded rivets (Rivnuts) are commonly used to. A- join two or more pieces of sheet metal where shear strength is desired. B- join two or more pieces of sheet metal where bearing strength is desired. C- attach parts or components with screws to sheet metal.

Cherrymax and Olympic-Lok rivets. A- may be installed with ordinary hand tools. B- utilize a pulling tool for installation. C- utilize a rivet gun, special rivet set, and bucking bar for installation.

Select the alternativa which best describes the function of the flute section of a twist drill. Forms the cutting edges of the drill point. Forros the area where the drill bit attaches to the drill motor. Prevents overheating of the drill point.

What should be the included angle of a twist drill for soft metals?. 118°. 90°. 65°.

When comparing the machining tech­ niques for stainless steel sheet material to those for aluminum alloy sheet, it is normally considerad good practice to drill the stainless steel at a. A- higher speed with less pressure applied to the drill. B- lower speed with less pressure applied to the drill. C- lower speed with more pressure applied to the drill.

When drilling stainless steel, the drill used should have an included angle of. 140° and turn ata low speed. 118° and turn at a high speed. 90° and turn at a low speed.

Which is correct concerning the use of a file?. A smoother finish can be obtained by using a double cut file than by using a single cut file. Apply pressure on the forward stroke, only, except when filing very soft metals such as lead or aluminum. The terms "double cut" and "second cut" have fhe same meaning in reference to files.

Which procedure is correct when using a reamer to finish a drilled hole to the cor­rect size?. Turn the reamer only in the cutting direction. Apply considerable pressure on the reamer when starting the cut and reduce the pressure when finishing the cut. Turn the reamer in the cutting direction when enlarging the hole and in the opposite dircction to remove from the hole.

What shoulcl he the included angle of a twist drill for hard metal?. 118°. 90°. 100°.

Which of the rivets shown will accurately fit the conical depression made by a 100° countersink?. 3. 2. 1.

The identifying marks on the heads of alu­minum alloy rivets indicate the. A- degree of dimensional and process control observed during manufacture. B- specific alloy used in the manufacture of the rivets. C- head shape, shank size, material used, and specifications adhered to during manufacture.

When an MS20470D rivet is installed, its full shear strength is obtained. A- by the cold working of tho rivet metal in forming a shop head. B- only after a period of age hardening. C- by heat treating just prior to being driven.

What is the purpose of refrigerating 2017 and 2024 aluminum alloy rivets after heat treatment'?. To retard age hardening. To relieve internal stresses. To accelerate age hardening.

Under certain conditions, type A rivets are not used because of their. A- low strength characteristics. B- tendency toward embrittlement when subjected to vibration. C- high alloy content.

Heat treated rivets in the D and DD series that are not drivcn within the prescribed time after heat treatment or removal from refrigeration. A- may be returned to refrigeration and used later without reheat treatment. B- must be reheat trcatcd before use. must be discarded.

The dimensions of an MS20430AD-4-8 rivet are. A- 1/8 inch in diameter and 1/2 inch long. B- 1/8 inch in diameter and 1/4 inch long. C- 4/16 inch in diameter and 8/32 inch long.

Most rivets used in aircraft construction have. A- a raised dot. B- smooth heads without markings. C- dimples.

MS20426AD-6-5 indicates a countersunk rivet which has. A- an overalllength of 5/16 inch. B- a shank length of 5/16 inch (excluding head). a shank length of 5/32 inch (excluding head).