(c)
In addition to the stall warning required by Sec. 23.207, a warning that is clearly distinguishable to the pilot under all expected .ight conditions without requiring the pilot’s attention, must be provided for faults that would prevent the system from providing the required pitching motion.
(d)
Each system must be designed so that the arti.cial stall barrier can be quickly and positively disengagedby thepilotstoprevent unwanteddownwardpitching of the airplaneby aquick release(emergency) control that meets the requirements ofSec. 23.1329(b).
(e)
A pre.ight check of the complete system must be established and the procedure for this check made availablein theAirplaneFlightManual(AFM).Pre.ight checks that are critical to the safety of the airplane must be included in the limitations section of the AFM.
(f)
For those airplanes whose design includes an autopilot system :
(1)
Aquickrelease(emergency) controlinstalledin accordancewithSec.23.1329(b) may be usedto meetthe requirements ofparagraph(d), of this section, and
(2)
The pitch servo for that system may be used to provide the stall downward pitching motion.
(g)
In showingcompliance withSec.23.1309,the system mustbe evaluated todetermine the e.ect that any announced or unannounced failure may have on the continued safe .ight and landing of the airplane or the ability of the crew to cope with any adverse conditions that may result from such failures. This evaluation must consider the hazards that would result from the airplane’s .ight characteristics if the system was not provided, and the hazard that may result from unwanted downward pitching motion, which could result from a failure at airspeeds above the selected stall speed.]
Amdt. 23-49, E.. 03/11/96
FAR 23.693 : Joints.
Control system joints (in push-pull systems) that are subject to angular motion, except those in ball and roller bearing systems, must have a special factor of safety of not less than 3.33 with respect to the ultimate bearing strength of the softest material used as abearing.Thisfactor may be reduced to2.0forjointsin cable control systems. For ball or roller bearings, the approved ratings may not be exceeded.
FAR 23.697 : Wing .ap controls.
(a)
Each wing .ap control must be designed so that, when the .ap has been placed in anyposition upon which compliance with theperformance requirements ofthispart isbased,the .ap will notmovefromthatpositionunlessthecontrolisadjusted or is moved by the automatic operation of a .ap load limiting device.
(b)
Therateof movementof the .apsinresponsetotheoperationof thepilot’scontrol or automatic device must give satisfactory .ight and performance characteristics under steady or changing conditions of airspeed, engine power, and attitude.
(c)
[If compliance with Sec. 23.145(b)(3)necessitates wing .ap retraction to positions that are not fully retracted, the wing .ap control lever settings corresponding to those positions must be positively located such that a de.nite change of direction of movement of the lever is necessary to select settings beyond those settings.]
Amdt. 23-49, E.. 03/11/96
FAR 23.699 : Wing .ap position indicator.
There must be a wing .ap position indicator for–
(a)
Flap installations with only the retracted and fully extended position, unless–
(1)
Adirectoperating mechanismprovidesasenseof ”feel” andposition(such as when a mechanical linkage is employed); or
(2)
The .appositionisreadilydetermined without seriouslydetractingfromother piloting dutiesunderany .ightcondition,day ornight; and
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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(29)
