(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.
(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) For single-pilot con.guration, instruments which require a static source must be provided with a means of selecting an alternate source and that source must be calibrated.]
Amdt. 27-19, E.. 3/2/83
FAR27.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 VSi di.ers from VY , climb performance at VSi and with maximum continuous power throughout the ranges of weight, altitude, and temperature for which approval is requested.]
Amdt. 27-19, E.. 3/2/83
′
Elodie Roux. Septembre 2003
Appendix B : Airworthiness Criteria for Helicopter Instrument Flight
Chapitre 70
Appendix C : Criteria for Category A
Sommaire
FAR27.C1:[General.] . . . . . . . . . . . . . . . . . . . . . . 908
FAR27.C2:[Applicablepart29sections.] . . . . . . . . . . . . 908
907
Appendix C : Criteria for Category A
FAR27.C1 :[General.]
[Asmall multiengine rotorcraft may notbe type certi.catedforCategoryA operation unless it meets the design installation and performance requirements contained in this appendix in addition to the requirements of this part.] Amdt. 27-33, E.. 8/8/96
FAR27.C2 :[Applicablepart29sections.]
[The following sections of part 29 of this chapter must be met in addition to the requirements of this part : 29.45(a) and(b)(2) –General. 29.49(a) – Performance at minimum operating speed.
29.51 – Takeo. data : General.
29.53 – Takeo. : Category A.
29.55 – Takeo. decision point : Category A.
29.59 –Takeo.path:Category A.
29.60 – Elevated heliport takeo. path : Category A.
29.61 – Takeo. distance : Category A.
29.62 – Rejected takeo. : Category A.
29.64 – Climb : General.
29.65(a) – Climb : AEO.
29.67(a) – Climb : OEI.
29.75 – Landing : General. 中國航空網 m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(6)
