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Assembly and Rigging
| Question | Answer |
|---|---|
| The auxiliary (tail) rotor of a helicopter permits the pilot to compensate for and/or accomplish which of the following? | Torque and directional control |
| the vertical flight of a helicopter is controlled by | Collective pitch changes |
| A reduction in anti-torque thrust will cause the | tail to pivot in the 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 | 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 |
| A helicopter in forward flight, cruise configuration, changes direction by | Tilting the main rotor disk in the desired direction |
| The purpose in checking main rotor blade tracking is to determine the | Relative position of the blades during rotation |
| in a hovering helicopter equipped with a tail rotor, directional control is maintained by | 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 | Less than the retreating blade |
| Main rotor blades that do not cone by the same amount during rotation are said to be out of | 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 |
| Which statement is correct concerning torque effect on helicopters? | Torque direction is the opposite of rotor blade rotation |
| What is the purpose of the free-wheeling unit in a helicopter drive system? | It disengages the engine from the main rotor when engine RPM is less than rotor RPM. |
| Movement about the lateral axis (pitch) in a helicopter is effected by movement of the | Cyclic pitch control |
| Movement about the longitudinal axis (roll) in a helicopter is effected by movement of the | Cyclic pitch control |
| Wing dihedral, a rigging consideration on most airplanes of conventional design, contributes most to stability of the airplane about its | Longitudinal 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 the is reassembled after shipment? | Aircraft type certificate data sheet. |
| If a pilot reports that an airplane flies left wing heavy, this condition may be corrected by | 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 | The vertical axis but not the longitudinal axis. |
| An airplane which has good longitudinal stability should have a minimum tendency to | Pitch |
| As the angle of attack of an airfoil increase, the center of pressure will | move toward the leading edge. |
| The angle of incidence is that acute angle formed by | A line parallel to the wing chord and a line parallel to the longitudinal axis of the aircraft. |
| An airplane's center of lift is usually located aft of its center of gravity. | So that the airplane will have nose-heavy tendency. |
| An airplane is controlled directionally about its vertical axis by the | Rudder. |
| The elevators of a conventional airplane are used to provide rotation about the | 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 increase due to increased angle of attack. |
| What type of flap system increases the wing area and changes the wing camber? | Fowler flaps. |
| If the right wing of a monoplane is improperly rigged to a greater angle of incidence than designated in the manufacturers specifications, it will cause the | Airplane to be off balance both laterally and directionally. |
| The chord of a wing is measured from. | leading edge to trailing edge. |
| When the lift of an airfoil increases, the drag will. | Also increase |
| What physical factors are involved in the aspect ratio of airplane wings? | Span and chord. |
| Improper rigging of the elevator trim tab system will affect the balance of the airplane about its | lateral axis. |
| An airplane that has a tendency to gradually increase a pitching moment that has been set into motion has? | poor longitudinal stability. |
| The purpose of wing slats is to? | reduce stalling speed |
| The angle of incidence of an airplane at rest? | does not change when in flight. |
| Buffeting is the intermittent application of forces to a part of an airplane. It is caused by? | an unsteady flow from turbulence. |
| Movement of an airplane along its lateral axis (roll) is also movement? | around or about the longitudinal axis controlled by the ailerons. |
| The primary purpose of stall strips is to? | stall the inboard portion of the wings first |
| Rigging and alignment checks should not be undertaken in the open; however, if this cannot be avoided, the aircraft should be positioned? | nose into the wind. |
| The correct dihedral angle can be determined by? | 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? | front spar |
| Where would you find precise information to perform a symmetry alignment check for a particular aircraft? | aircraft service or maintenance manual. |
| Where is the buttock line or buttline of an aircraft? | a width measurement left or right of, and parallel to, the vertical centerline. |
| Where is fuselage station No. 137 located? | 137 inches aft of the zero or fixed reference line. |
| 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. |
| 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. |
| 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. |
| 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. |
| 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 |
| Which is an acceptable safety device for a castle nut when installed on secondary structures? | cotter pin. |
| When installing a castle nut, start alignment with the cotter pin hole at the | minimum recommended torque plus friction drag torque. |
| When used in close proximity to magnetic compasses, cotter pins are made of what material? | corrosion resisting 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 |
| The purpose of the vertical fin is to provide? | directional stability. |
| How are changes in direction of a control cable accomplished? | pulleys |
| What is the smallest size cable that may be used in aircraft primary control systems? | 1/8 inch |
| After repairing or re-covering a rudder, the surface should be rebalanced? | 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? | broken strands |
| 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. |
| 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. |
| Excessive wear on both of the sides of a control cable pulley groove is evidence of? | pulley misalignment. |
| Fairleads should never deflect the alignment of a cable more than? | 3 degrees |
| Where does the breakage of control cable wires occur most frequently? | breakage usually occurs where cables pass over pulleys and through fairleads. |
| With which system is differential control associated? | 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. |
| If control cables are adjusted properly and the control surfaces tend to vibrate, the probable cause is? | 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. |
| Stability about the axis which runs parallel to the line of flight is referred to as? | lateral stability. |
| The purpose of spring tabs or servo tabs is to? | 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? | down and the elevator will move up. |
| 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. |
| 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. |
| 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 |
| 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. |
| A universal propeller protractor used to measure the degrees of aileron travel should be zeroed? | with the aileron in the neutral position. |
| The universal propeller protractor can be used to measure? | degrees of flap travel. |
| (Refer to Figure 8.) Identify the cable that is used in primary control systems and in other places where operation over pulleys is frequent. | 3. |
| A tension regulator in the flight control cable system of a large all-metal aircraft is used primarily to? | retain a set tension. |
| (Refer to Figure 9) When the outside air temperature is 80F, select the acceptable 3/16 cable tension range | 117 pounds minimum, 143 pounds maximum |
| Differential control on an aileron system means that | the up travel is more than the down travel |
| why is it generally necessary to jack an aircraft indoors for weighing? | so that air currents do not destabilize the scales |
| Which should be accomplished before jacking an aircraft | Install critical stress panels or plates |
Created by:
C3ntrix
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