Assy and Rigging Unit 2 Exam

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Assy and Rigging Unit 2 Exam
2012-07-18 22:18:56
Assembly Rigging

ASA test guide
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  1. 8257. The vast majority of aircraft control cables are teminated with swaged terminals, that must be
    checked with a go-no-go gauge before and after, to show compiance with the manufactures's requirements after the swaging operation
  2. 8258. What nondestructive checking method is normally used to ensure that the correct amout 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
  3. 8259. When inspection a control cable turnbuckle for proper installation, determine that
    the safety wire ends are wrapped a minimum of four turns around the teminal end shanks
  4. 8260. If all insturctions 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
  5. 8261.Which is an acceptable safety device for a castle nut when installed on secondary sturctures?
    cotter pin
  6. 8262. When used in close proximity to magnetic compasses, cotter pins are made of what material?
    corrosion resisting steel
  7. 8263. When a fiber or nylon insert-type, self-locking nut can be threaded on a bolt or stud through the insert with ony the fingers, it should be
  8. 8264. The purpose of the vertical fin is to provide
    directional stability
  9. 8265. How are changes in direction of a control cable accomplished?
  10. 8266. What is the smallest size cable that may be used in aircraft primary control systems?
    1/8 inch
  11. 8267. After repairing or re-covering a rudder, the surface should be rebalance
    to manufacturer's specification
  12. 8268. 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
  13. 8269. The cable-operated control system of an all-metal aircraft, not incoporation a temperature compensating device, has been rigged to the correct tension in a heated hanger. If the aircraft is operated in very cold weather, the cable tension will
    decrease when the aircraft structure and cables become cold
  14. 8270. Very often, repairs to a control surface require static rebalancing of the control surface. Generally, flight control balance condition may be determied by
    the behavior of the trailing edge when the surface is suspended from its hing points
  15. 8271. Excessive wear on both of the sides of a control cable pully groove is evidence of
    pulley misalignment
  16. 8272. Fairleads should never deflect the alignment of a cable more than
  17. 8273. Where does the breakage of control cable wieres occur most frequently?
    Breakage usually occurs where cables pass over pulleys and through fairleads
  18. 8274. With which system differential control associated?
  19. 8275. 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 or the amount of thread engagement by means of the inspection hole provided
  20. 8276. If control cables are adjusted properly and the control surfaces tend to vibrate, the probable cause is
    worn attachment fittings
  21. 8277. Aircraft flight control trim systems must be designed and installed so that the
    pilot can determine the realtive position of the trim tab from the cockpit
  22. 8278. Stability about the axis which runs parallel to the line of flight is referred to as
    lateral stability
  23. 8279. The purpose of spring tabs or sevo tabs is to
    assist the pilot in moving the control surfaces
  24. 8280. If the control stick of and 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
  25. 8281. Movement of the cockpit control toward the nose-down position during a ground operation check of the elevator trim tabe system will cause the trailing edge of the trim tab to move in which direction?
    Upward regardless of elevator position
  26. 8282. If the control stick of an aircrafte with properly rigged flight controls is move foward and to the right, the left aileron will move
    down and the elevator will move down
  27. 8283. 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
  28. 8284. 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
  29. 8285. A universal propeller protractor used to measure the degrees of aileron travel should be zeroed
    with the aileron in the NEUTRAL position
  30. 8286. The universal propeller protractor can be used to measure
    degrees of flap travel
  31. 8287. Identify the cabel that is used in primary control system and in other places where operation over pulleys is frequent
  32. 8288. A tension regulator in the flight control cable system of a large all-metal aircraft is used primarily to
    retain a set tension
  33. 8289. When the outside air temperatrue is 80oF, select the acceptabel 3/16 cable tension range
    117 pounds minimum,  pounds maximum
  34. 8290. Differential control on an airleron system means that
    the up travel is more than the down travel
  35. 8291. Why is it generally necessary to jack an aircraft indoors for weighing?
    So that air currents do not destabilize the scales
  36. 8292. Which should be accomplished before jacking an aircraft?
    Install critical stress panels or plates