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Rodina-2209 midterm
| Question | Answer |
|---|---|
| what is the aileron? | primary flight control on the wing. controls Roll movement about the Longitudinal axes, and controls Lateral stability |
| what is the elevator/ stabilator? | Primary flight control on the horizontal stabilizer. controls Pitch movement about the Lateral axes, and controls Longitudinal stability |
| what is the Rudder? | Primary flight control on the vertical stabilizer. controls Yaw movement about the Vertical axes, and controls Directional stability |
| What are flaps? | on the Inboard trailing edge of wings, Extends the camber of the wing for greater lift and slower fight. Allows control at low speeds for short field takeoffs and landings. |
| what are Trim tabs ? | on the Trailing edge of primary fight control surfaces, Reduces the force needed to move a primary control surface. |
| what are Balance tabs? | on the Trailing edge of primary fight control surfaces, Reduces the force needed to move a primary control surface. |
| what are Anti-balance tabs? | on the Trailing edge of primary fight control surfaces, Increases feel and efectiveness of primary control surface. |
| what are Servo tabs? | on the Trailing edge of primary fight control surfaces, Assists or provides the force for moving a primary flight control. |
| what are Spoilers? | on the Upper and/or trailing edge of wing, Decreases (spoils) lift. Can augment aileron function. |
| what are Slats? | on the Mid to outboard leading edge of wing, Extends the camber of the wing for greater lift and slower flight. Allows control at low speeds for short field takeoffs and landings. |
| what are Slots? | on the Outer leading edge of wing forward of ailerons, Directs air over upper surface of wing during high angle of attack. Lowers stall speed and provides control during slow flight. |
| what are Leading edge flap? | on the Inboard leading edge of wing, Extends the camber of the wing for greater lift and slower fight. Allows control at low speeds for short field takeoffs and landings. |
| How are most flight controls controlled and actuated? | they are electrically controlled and hydraulicly actuated. |
| airplanes intended for limited aerobatic operations with a load factor of 4.4 | utility category |
| a stress that tends to crush or press together? | compression |
| the centerline of the fuselage? | buttline |
| Hinged sections of the trailing edge of the left and right wing which operate in a series to provide lateral control? | aileron |
| a stress that develops when a force tends to cause a layer of material to slide along an adjacent layer? | shear |
| fuselage station 0.00 usually at or near the forward portion of the fuselage? | datum |
| a line established for locating stations of a vertical line? | waterline |
| a heavy structural member in the fuselage to contain pressure or disperse concentrated loads? | bulkhead |
| a fixed component to provide directional stability. The trailing edge is hinged to the rudder? | vertical fin |
| A beam or member supported at or near one end only without external bracing? | cantilever |
| a principal longitudinal member of the framing of an aircraft fuselage? | longeron |
| a removable cover or housing placed over or around an aircraft fuselage? | cockpit |
| the body of an aircraft to which the wings and tail unit are attached? | fuselage |
| a fore and aft member of an airfoil structure used to give the airfoil its form? | rib |
| The longitudinal member in the fuselage or spanwise member in the wing to transmit skin loads into the body frame or the wing ribs? | stringer |
| the principal span wise beam in the structure in the wing, it is usually the primary load carrying structure in the wing? | spar |
| a tubular fuselage member where the longerons are connected with rigid vertical and lateral members called struts? | pratt |
| a framework of vertical and longitudinal members covered with a structural skin that carries a large percentage of the stresses imposed on the structure? | monocoque |
| a major longitudinal fuselage component in the wing center section and wheel well area of the transport category aircraft? | keel beam |
| an attachment method and design philosophy that provides 2 load carrying paths for operational loads? | fail-safe |
| which resource contains the flight control travel limits? | TCDS |
| what controls the vertical flight of the helicopter? | collective |
| what category is the non-aerobatic category 3.8 G's | normal |
| what is used to change the direction of a flight control cable? | pulley |
| what are maneuvering and gust loads? | flight loads |
| what controls the horizontal movement of an helicopter? | cyclic |
| what is an ultimate load? | 1.5 times the load limit factor |
| what is the twisting stress? | torsion |
| flight control cable tension is affected by what? | temperature |
| what is the removeable cover/housing placed over or around the engine? | cowling |
| how are lift and drag proportional? | directly |
| what is the angle formed by the wing chord line and the relative wing | angle of attack |
| what is the angle formed by the intersection of the wing chord line and the horizontal axis of the A/C | angle of incidence |
| what is the most used cable? | 7X19 |
| areas that come in contact with pully or fairlead where cable is worn? | critical fatigue area |
| crimped fittings to the end of cables? | swaged-on fitting |
| cables must be untwisted slightly for? | close inspection |
| fairleads are Teflon or plastic sections that cables can? | run across/ rub against |
| used to look for corrosion or ware | close examination |
| corrosion on cables is NOT to be cleaned with a? | wire brush |
| what condition affects cables? | temperature. |
| 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. |
| 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. |
| What is the smallest size cable that may be used in aircraft primary control systems? | 1/8 inch. |
| 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. |
| Fairleads should never deflect the alignment of a cable more than? | 3° |
| Wing dihedral, a rigging consideration on most airplanes of conventional design, contributes most to stability of the airplane about its? | longitudinal 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. |
| If control cables are adjusted properly and the control surfaces tend to vibrate, the probable cause is? | worn attachment fittings. |
| Differential control on an aileron system means that? | the up travel is more than the down travel. |
| Excessive wear on both of the sides of a control cable pulley groove is evidence of? | pulley misalignment. |
| The dihedral angle of a wing may be measured by placing a straightedge and level protractor on the? | front spar. |
| The correct dihedral angle can be determined by? | using a dihedral board and bubble level along the front spar of each wing. |
| With which system is differential control associated? | Aileron. |
| Improper rigging of the elevator trim tab system will affect the balance of the airplane about its? | lateral axis. |
| A tension regulator in the flight control cable system of a large all-metal aircraft is used primarily to? | retain a set tension. |
| 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. |
| A universal propeller protractor used to measure the degrees of aileron travel should be zeroed? | with the aileron in the NEUTRAL 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. |
| 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 angle of incidence of an airplane at rest? | does not change when in flight. |
| 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 strands. |
| Where would you find precise information to perform a symmetry alignment check for a particular aircraft? | Aircraft service or maintenance manual. |
| 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. |
| Where does the breakage of control cable wires occur most frequently? | Breakage usually occurs where cables pass over pulleys and through fairleads. |
| 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. |
| 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. |
| How are changes in direction of a control cable accomplished? | Pulleys. |
| 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. |
| 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. |
| 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. |
| 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 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. |
| 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? | Aircraft Type Certificate Data Sheet. |
| 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. |
| Buffeting is the intermittent application of forces to a part of an airplane. It is caused by? | an unsteady flow from turbulence. |
| 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. |
| ATA for flight controls is? | 27 |
Created by:
Lucas1999