(5)
Forsystemsthatoperatetherequired.ightinstrumentsat eachpilot’sstation–
(i)
Only the required .ight instruments for the .rst pilot may be connected to that operating system;
(ii)
Additional instruments, systems, or equipment may not be connected to an operating system for a second pilot unless provisions are made to ensure the continued normal functioning of the required instruments in the event of any malfunction of the additional instruments, systems, or equipment which is not shown to be extremely improbable;
(iii) The equipment, systems, and installations must be designed so that one displayoftheinformationessentialtothesafety of.ight whichisprovided by the instruments will remain available to a pilot, without additional crewmember action, after any single failure or combination of failures that is not shown to be extremely improbable; and
(iv) Forsingle-pilot con.gurations,instrumentswhich requirea staticsource must be provided with a means of selecting an alternate source and that source must be calibrated.
(6) [ In determining compliance with the requirements of Sec. 29.1351(d)(2), the supply of electrical power to all systems necessary for .ight under IFR must be included in the evaluation.]
(c) Thunderstormlights.In additionto theinstrumentlights requiredbySec.29.1381(a), thunderstorm lights which provide high intensity white .ood lighting to the basic .ight instruments must be provided. The thunderstorm lights must be installed to meet the requirements of Sec. 29.1381(b).
Amdt. 29-40, E.. 8/8/96
FAR29.B9 :[IX.RotorcraftFlightManual.]
[A Rotorcraft Flight Manualor Rotorcraft Flight Manual IFR Supplement must be provided and must contain–
(a)
Limitations. The approved IFR .ight envelope, the IFR .ightcrew composition, the revised kinds of operation, and the steepest IFR precision approach gradient for which the helicopter is approved;
(b)
Procedures. Required information for proper operation of IFR systems and the re-commended procedures in the event of stability augmentation or electrical system failures; and
(c)
Performance. If VYi di.ers from VY , climb performance at VYi and with maximum continuous power throughout the ranges of weight, altitude, and temperature for which approval is requested.]
Amdt. 29-21, E.. 3/2/83
FAR29.C1 :[Icing certi.cation.]
(a) [Continuous maximum icing. The maximum continuous intensity of atmospheric icing conditions (continuous maximum icing) is de.ned by the variables of the cloud liquid water content, the mean e.ective diameter of the cloud droplets, the ambient air temperature, and theinterrelationship ofthese three variables as shown in (Figure 79.1, p. 1086) of this appendix. The limiting icing envelope in terms of altitude and temperature is given in (Figure 79.2, p. 1087) of this appendix. The interrelationship of cloud liquid water content with drop diameter and altitude is
′
Elodie Roux. Septembre 2003
Appendix B : Airworthiness Criteria for Helicopter Instrument Flight
determined from (Figure 79.1, p. 1086) and (Figure 79.2, p. 1087). The cloud liquid water content for continuous maximum icing conditions of a horizontal extent, other than 17.4 nautical miles, is determined by the value of liquid water content of (Figure 79.1, p. 1086), multiplied by the appropriate factor from (Figure 79.3,
p. 1088) of this appendix.
(b) Intermittent maximum icing. The intermittent maximum intensity of atmospheric icing conditions (intermittent maximum icing is de.ned by the variables of the cloud liquid water content, the mean e.ective diameter of the cloud droplets, the ambient air temperature, and theinterrelationship ofthese three variables as shown in (Figure 79.4, p. 1088) of this appendix. The limiting icing envelope in terms of altitude and temperature is given in (Figure 79.5, p. 1089) of this appendix. The interrelationship of cloud liquid water content with drop diameter and altitude is determined from (Figure 79.4, p. 1088) and (Figure 79.5, p. 1089). The cloud liquid water content for intermittent maximum icing conditions of a horizontal extent, other than 2.6 nautical miles, is determined by the value of cloud liquid water content of (Figure 79.4, p. 1088)multipliedby the appropriatefactorin (Figure 79.6,
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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(114)
