(b)
Compliance mustbe shown(by analyses orindividualload tests) with the special factor requirementsfor control systemjoints subjectto angular motion.

FAR 23.683 : Operation tests.

(a)
It must be shown by operation tests that, when the controls are operated from the pilot compartment with the systemloaded asprescribedinparagraph(b) of this section, the system is free from–

(1)
Jamming;

(2)
Excessivefriction; and

(3)
Excessive de.ection.

(b) The prescribed test loads are–
(1)
[For the entire system, loads correspondingto the limit airloads on the appro-priate surface, or the limit pilot forces in Sec. 23.397(b), whichever are less; and]

(2)
For secondary controls, loads not less than those corresponding to the maxi-mum pilot e.ort established under Sec. 23.405.

Amdt. 23-7, E.. 09/14/69
FAR 23.685 : Control system details.
(a)
[Eachdetailof each control system mustbedesigned andinstalledtopreventjam-ming, cha.ng, andinterferencefrom cargo,passengers,loose objects, or thefreezing of moisture.]

(b)
There must be means in the cockpit to prevent the entry of foreign objects into places wherethey wouldjamthe system.

(c)
There mustbe meanstopreventthe slapping of cables ortubes againstotherparts.

(d)
Each element of the .ight control system must have design features, or must be distinctively and permanently marked, to minimize the possibility of incorrect as-sembly that could result in malfunctioning of the control system.

Amdt. 23-17, E.. 02/01/77
FAR 23.687 : Spring devices.
The reliability of any spring device used in the control system must be established by tests simulating service conditions unless failure of the spring will not cause .utter or unsafe .ight characteristics.
FAR 23.689 : Cable systems.
(a) Each cable, cable .tting, turnbuckle, splice, and pulley used must meet approved speci.cations. In addition–
1
(1) No cable smaller than inchdiameter maybe usedinprimarycontrol systems;
8
(2)
Each cable system must be designed so that there will be no hazardous change in cable tension throughout the range oftravel under operating conditions and temperature variations; and

(3)
There must be means for visual inspection at each fairlead, pulley, terminal, and turnbuckle.

(b)
[Eachkindand size ofpulley must correspondto the cable with whichitis used.Each pulley must have closely .tted guards to prevent the cables from being misplaced or fouled, even when slack. Each pulley must lie in the plane passing through the cable so that the cable does not rub against the pulley .ange.]

(c)
Fairleads must be installed so that they do not cause a change in cable direction of more than three degrees.

′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction

(d)
Clevis pins subject to load or motion and retained only by cotter pins may not be used in the control system.

(e)
Turnbucklesmustbe attached topartshaving angularmotionin a mannerthat will positively prevent binding throughout the range of travel.

(f)
Tab control cables are not part of the primary control system and may be less than

1
inch diameter in airplanes that are safely controllable with the tabs in the most
8
adversepositions.
Amdt. 23-7, E.. 9/14/69
FAR23.691:[Arti.cialstallbarrier system.]
[Ifthefunction of anarti.cial stallbarrier,for example,stickpusher,is used to show compliance with Sec. 23.201(c), the system must comply with the following :
(a)
With the system adjusted for operation, the plus and minus airspeeds at which downwardpitching control willbeprovided mustbe established.

(b)
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(28)