Landing Gear Unit 1 exam ASA

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Landing Gear Unit 1 exam ASA
2012-06-12 16:23:11
Landing Gear

ASA questions
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  1. 8308. To prevent a very rapid extension of an oleo shock strut after initial compression resulting from landing impact,
    various types of valves or orifices are used which restrict the reverse fluid flow
  2. 8312. The metering pins in oleo shock struts serve to
    Retard the flow of oil as the struts are compressed
  3. 8313. After performing maintenance on an aircraft's landing gear system which may have affected the system's operation, it is usually necessary to
    make an operational check with the aircraft on jacks
  4. 8323. The repair for an out-of -tolerance toe-in condition of main landing gear wheels determined not to be the result of bent or twisted components consists of
    inserting, removing, or changing the location of washers or spacers at the center pivotal point of the scissor torque links
  5. 8327. On all aircraft equipped with retractable landing gear, some means must be provided to
    extend the landing gear if the normal operating mechanism fails
  6. 8328. An automatic damping action occurs at the steering damper if for any reason the flow of high-pressure fluid is removed from the
    inlet of the steering damper
  7. 8329. What is the purpose of the torque links attached to the cylinder and piston of a landing gear oleo strut?
    Maintain correct wheel alignment
  8. 8333. When and air/oil type of landing gear shock strut is used, the initial shock of landing is cushioned by
    the fluid being forced through a metered opening
  9. 8335. A sleeve, spacer, or bumper ring is incorporated in a landing gear oleo shock strut to
    limit the extension stroke
  10. 8336. The purpose of a sequence valve in a hydraulic retractable landing gear system is to
    ensure operation of the landing gear and gear doors in the proper order
  11. 8340. When servicing an air/oil strut with MIL-5606 the strut should be
    collapsed and fluid added at the filler opening
  12. 8341. Instructions concerning the type of fluid and amount of air pressure to be put in a shock strut are found
    in the aircraft manufacture's sevice manual
  13. 8344. If the extended longitudinal axis of the main landing gear wheel assemblies intersects aft of the aircraft, the wheels can be termed as having
  14. 8346. If and aircraft shock strut (air/oil type) bottoms upon initial landing contact, but functions correctly during taxi, the most probable cause is
    low fluid
  15. 8347. What is the function of a cam incorporated in a nose gear shock strut?
    Straightens the nosewheel
  16. 8348. Extension of an oleo shock strut is measured to determine the
    proper operating position of the strut
  17. 8350. If a shock strut bottoms after it has been properly serviced, the
    strut should be removed, disassembled, and inspected
  18. 8354. What should be checked when a shock strut bottoms during a landing?
    Fluid level
  19. 8358. The hydraulic packing seals used in a landing gear shock strut are
    used only with a specific type of fluid
  20. 8359. Lockout deboosters are prmarily pressure reducing valves that
    allow full debooster piston travel without fluid from the high pressure side entering the low pressure chamber
  21. 8368. When an empty shock strut is filled with fluid, care should be taken to extend and compress the strut completely at least two times to
    ensure proper packing ring seating and removal of air bubbles
  22. 8369. In shock struts, chevron seals are used to
    prevent oil from escaping
  23. 8370. On most aircraft, the oil level of an air and oil shock strut is checked by
    releasing the air and seeing that the oil is to the level of the filler plug
  24. 8372. A landing gear position and warning system will provide a warning in the cockpit when the throttle is
    retarded and gear is not down and locked
  25. 8373. An electric motor used to raise and lower a landing gear would most likely be a
    split field series-wound motor
  26. 8374. When installing a chevron-type seal in an aircraft hydraulic cylinder, the open side of the seal should face
    the direction of fluid pressure
  27. 8375. Nose gear centering cams are used in many retractable landing gear systems. The primary purpose of the centering device is to
    center the nosewheel before it enters the wheel well
  28. 8376. What device in a hydraulic system with a constant-delivery pump allows circulation of the fluid when no demands are on the system?
    Pressure regulator
  29. 8377. A fully-charged hydraulic accumulator provides
    a source for additional hydraulic power when heavy demands are place on the system
  30. 8378. A hydraulic system referred to as a "power pack" system will
    have all hydraulic power components located in one unit
  31. 8379. A hydraulic hose identified as MIL-8794 will have a yellow stripe running the length of the hose. This stripe
    is used to ensure that the hose is installed without excessive twisting
  32. 8380. An O-ring intended for use in a hydraulic system using MIL-H-5606 (mineral base) fluid will be marked with
    a blue stripe or dot
  33. 8381. What condition whould most likely cause excessive fluctuation of the pressure gauge when the hydraulic pump is operating?
    Inadequate supply of fluid
  34. 8382. A filter incorporating specially treated cellulose paper is identified as
    micronic filter
  35. 8383. The purpose of an orifice check valve is to
    restrict flow in one direction and allow free flow in the other
  36. 8384. (Refer to figure 10.) The trunnion nut on an aircraft landing gear requires a torque of 320 inch-pounds. To reach the nut, a 3-inch straight adapter must be used on and 18-inch torque wrench. How many foot-pounds will be indicated on the torque wrench when the required torque of the nut is reached
  37. 8385. A special bolt in a landing fear attachment requires a torque value of 40 inch-pounds. How many foot-pounds are required?