(b)
Compliance with the special factors requirements of Secs. 25.619 through
25.625 and 25.657 for control surface hinges must be shown by analysis or individual load tests.
FAR 25.655 : Installation.
(a)
Movable tail surfaces must be installed so that there is no interference bet-ween any surfaces when oneisheldinits extremeposition and the others are operated through their full angular movement.
(b)
If an adjustable stabilizer is used, it must have stops that will limit its range of travel to the maximum for which the airplane is shown to meet the trim requirements of Sec. 25.161.
FAR 25.657 : Hinges.
(a)
[For control surface hinges, including ball, roller, and self-lubricated bearing hinges, the approved rating of the bearing may not be exceeded. For non-standard bearing hinge con.gurations, the rating must be established on the basis of experience or tests and, in the absence or a rational investigation, a factor of safety of not less than 6.67 must be used with respect to the ultimate bearing strength of the softest material used as a bearing.
(b)
Hinges must have enough strength and rigidity for loads parallel to the hinge line.]
Amdt. 25-23, E.. 5/8/70
47.3 Control Systems
FAR 25.671 : General.
(a)
Each control and control system must operate with the ease, smoothness, and positiveness appropriate to its function.
(b)
Each element of each .ight control system must be designed, or distinctively and permanently marked, to minimize the probability of incorrect assembly that could result in the malfunctioning of the system.
(c)
[The airplane must be shown by analysis, tests, or both, to be capable of continued safe .ight andlanding afterany of thefollowingfailuresorjamming inthe .ightcontrolsystemandsurfaces(includingtrim,lift,drag,andfeel systems), within the normal .ight envelope, without requiring exceptional piloting skill or strength. Probable malfunctions must have only minor e.ects on control system operation and mustbe capable ofbeing readily counteracted by the pilot.
(1)
Any singlefailure, excludingjamming(for example,disconnection orfai-lure ofmechanical elements, or structuralfailure ofhydraulic components, such as actuators, control spool housing, and valves).
(2)
Anycombination offailures not shown tobe extremelyimprobable, exclu-dingjamming(for example,dual electrical orhydraulic systemfailures, or any singlefailurein combination with anyprobablehydraulic or electrical failure).
(3)
Anyjamin a controlposition normallyencounteredduring takeo., climb, cruise, normalturns,descent, andlanding unlessthejamis showntobe extremely improbable, or can be alleviated. A runaway of a .ight control to an adverse position and jam must be accounted for if such runaway and subsequentjamming is not extremely improbable.
(d)
The airplane mustbedesigned so thatitis controllableif all enginesfail.Com-pliance with this requirement may be shown by analysis where that method has been shown to be reliable.]
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本文鏈接地址：FAA規(guī)章 美國(guó)聯(lián)邦航空規(guī)章 Federal Aviation Regulations 3(75)
