(b) During sideslips up to ±10'from trim throughout the approved ranges of airspeed, power, and vertical speed there must be no negative dihedral stability perceptible to the pilot through lateral control motion or force. Longitudinal cycle movement with sideslip must not be excessive.]
Amdt. 29-21, E.. 3/2/83
FAR29.B6:[VI.Dynamic stability.]
(a) Any oscillation having a period of less than 5 seconds must damp to站amplitude in not more than one cycle.
(b) Any oscillation having a period of 5 seconds or more but less than 10 seconds must damp to站amplitude in not more than two cycles.
(c) Any oscillationhaving aperiod of10 secondsormorebutlessthan20 secondsmust be damped.
(d) Any oscillation having a period of 20 seconds or more may not achieve double am-plitude in less than 20 seconds.
(e) Any aperiodic response may not achieve double amplitude in less than 9 seconds.
Amdt. 29-21, E.. 3/2/83
′
Elodie Roux. Septembre 2003
Appendix B : Airworthiness Criteria for Helicopter Instrument Flight
FAR29.B7 :[VII.Stability augmentation system(SAS).]
(a)
[If a SAS is used, the reliability of the SAS must be related to the e.ects of its failure.The occurrence of anyfailure condition which wouldprevent continued safe .ight and landing must be extremely improbable. For any failure condition of the SAS which is not shown to be extremely improbable–
(1)
The helicopter must be safely controllable and capable of prolonged instru-ment .ightwithoutunduepilote.ort.Additional unrelatedprobablefailures a.ecting the control system must be considered; and
(2)
The .ight characteristics requirements in Subpart B of Part 29 must be met throughout a practical .ight envelope.
(b)
The SAS must be designed so that it cannot create a hazardous deviation in .ight path or produce hazardous loads on the helicopter during normal operation or in the event of malfunction or failure, assuming corrective action begins within an appropriate period of time. Where multiple systems are installed, subsequent malfunction conditions must be considered in sequence unless their occurrence is shown to be improbable.]
Amdt. 29-21, E.. 3/2/83
FAR 29.B8 : VIII. Equipment, systems, and installation.
Thebasic equipment andinstallation must comply withSubpartF ofPart29 through Amendment 29-14, with the following exceptions and additions :
(a)
Flight and navigation instruments.
(1)
A magneticgyro-stabilizeddirectionindicatorinstead of thegyroscopicdirec-tion indicator required by Sec. 29.1303(h); and
(2)
Astandby attitudeindicator which meetsthe requirements ofSecs.29.1303(g)(1) through(7),instead of a rate-of-turnindicator requiredby Sec.29.1303(g).If standby batteriesareprovided,they maybe chargedfromthe aircraftelectri-cal systemif adequateisolationisincorporated.Thesystemmustbedesigned so that the standby batteries may not be used for engine starting.
(b)
Miscellaneous requirements.
(1)
Instrument systems and other systems essential for IFR .ight that could be adversely a.ected by icing must be provided with adequate ice protection whether or not the rotorcraft is certi.cated for operation in icing conditions.
(2)
There must be means in the generating system to automatically de-energize and disconnect from the main bus any power source developing hazardous overvoltage.
(3)
Each required .ightinstrumentusing apowersupply(electric,vacuum,etc.) must have a visual means integral with the instrument to indicate the ade-quacy of the power being supplied.
(4)
When multiple systems performing like functions are required, each system must be grouped, routed, and spaced so that physical separation between systems is provided to ensure that a single malfunction will not adversely a.ect more than one system.
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(113)
