(b)
During sideslips up to ±10'from trim throughout the approved ranges of airspeed, power, and vertical speed,there mustbe no negativedihedral stabilityperceptible to the pilot through lateral control motion or force. Longitudinal cyclic movement with sideslip must not be excessive.]
Amdt. 27-19, E.. 3/2/83
FAR27.B6 :[VI.Dynamicstability.]
(a) [For single-pilot approval–
(1) Any oscillation having a period of less than 5 seconds must damp to
12
ampli-
tude in not more than one cycle.
(2) Any oscillation having a period of 5 seconds or more but less than 10 seconds
must damp to
12
amplitude in not more than two cycles.
(3)
Any oscillationhaving aperiod of10 secondsormorebutlessthan20 seconds must be damped.
(4)
Any oscillationhaving aperiod of20 seconds or more may not achievedouble amplitude in less than 20 seconds.
′
Elodie Roux. Septembre 2003
Appendix B : Airworthiness Criteria for Helicopter Instrument Flight
(5) Any aperiodic response may not achieve double amplitude in less than 6 se-conds.
(b) For helicopters approved with a minimum crew of two pilots–
(1)
Any oscillation having a period of less than 5 seconds must damp to 12 ampli-tude in not more than two cycles.
(2)
Any oscillation having a period of 5 seconds or more but less than 10 seconds must be damped.
(3)
Any oscillationhaving aperiod of10 seconds or more may not achievedouble
amplitude in less than 10 seconds.] Amdt. 27-19, E.. 3/2/83
FAR27.B7 :[VII.Stabilityaugmentationsystem(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 27 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. 27-19, E.. 3/2/83
FAR27.B8 :[VIII.Equipment,systems,andinstallation.]
[The basic equipment and installation must complywith Secs. 29.1303, 29.1431, and 29.1433 through Amendment 29-14, with the following exceptions and additions :
(a)
Flight and Navigation Instruments.
(1)
A magneticgyro-stabilizeddirectionindicatorinstead of agyroscopicdirection indicator required by Sec. 29.1303(h); and
(2)
A standby attitude indicator which meets the requirements of Secs. 29.1303 (g)(1)through(7)insteadof a rate-of-turnindicator requiredbySec.29.1303(g). For two-pilotcon.gurations, onepilot’sprimaryindicator maybedesignedfor thispurpose.If standbybatteriesareprovided,they maybe chargedfromthe aircraft electrical system if adequate isolation is incorporated.
(b)
Miscellaneous requirements.
(1) Instrument systems and other systems essential for IFR .ight that could be adversely a.ectedbyicing mustbe adequatelyprotected whenexposed tothe continuous and intermittent maximum icing conditions de.ned in Appendix C of Part 29 of this chapter, whether or not the rotorcraft is certi.cated for operation in icing conditions.
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 5(5)
