-
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
-
8312. The metering pins in oleo shock struts serve to
Retard the flow of oil as the struts are compressed
-
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
-
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
-
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
-
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
-
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
-
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
-
8335. A sleeve, spacer, or bumper ring is incorporated in a landing gear oleo shock strut to
limit the extension stroke
-
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
-
8340. When servicing an air/oil strut with MIL-5606 the strut should be
collapsed and fluid added at the filler opening
-
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
-
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
toe-out
-
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
-
8347. What is the function of a cam incorporated in a nose gear shock strut?
Straightens the nosewheel
-
8348. Extension of an oleo shock strut is measured to determine the
proper operating position of the strut
-
8350. If a shock strut bottoms after it has been properly serviced, the
strut should be removed, disassembled, and inspected
-
8354. What should be checked when a shock strut bottoms during a landing?
Fluid level
-
8358. The hydraulic packing seals used in a landing gear shock strut are
used only with a specific type of fluid
-
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
-
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
-
8369. In shock struts, chevron seals are used to
prevent oil from escaping
-
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
-
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
-
8373. An electric motor used to raise and lower a landing gear would most likely be a
split field series-wound motor
-
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
-
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
-
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
-
8377. A fully-charged hydraulic accumulator provides
a source for additional hydraulic power when heavy demands are place on the system
-
8378. A hydraulic system referred to as a "power pack" system will
have all hydraulic power components located in one unit
-
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
-
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
-
8381. What condition whould most likely cause excessive fluctuation of the pressure gauge when the hydraulic pump is operating?
Inadequate supply of fluid
-
8382. A filter incorporating specially treated cellulose paper is identified as
micronic filter
-
8383. The purpose of an orifice check valve is to
restrict flow in one direction and allow free flow in the other
-
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
24
-
8385. A special bolt in a landing fear attachment requires a torque value of 40 inch-pounds. How many foot-pounds are required?
36.6
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