FAR29.519 :Hulltype rotorcraft :[Water-based and amphi-bian.] .......................... 948 FAR29.521:Floatlanding conditions. . . . . . . . . . . . . . 949
73.6 MainComponentRequirements . . . . . . . . . . . . . . . . 950
FAR29.547:[Mainandtail rotorstructure.] . . . . . . . . . 950 FAR 29.549 : Fuselage and rotor pylon structures. . . . . . . 950 FAR 29.551 : Auxiliary lifting surfaces. . . . . . . . . . . . . 951
73.7EmergencyLandingConditions . . . . . . . . . . . . . . . . . 951
FAR29.561:General. ...................... 951 FAR 29.562 : Emergency landing dynamic conditions. . . . . 952 FAR 29.563 : Structural ditching provisions. . . . . . . . . . . 953
73.8FatigueEvaluation. . . . . . . . . . . . . . . . . . . . . . . . . 954
FAR29.571:Fatigueevaluationof[structure.] . . . . . . . . 954
73.1 General
FAR 29.301 : Loads.
(a)
Strength requirements are speci.edin terms oflimitloads(the maximumloadsto be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety).Unless otherwiseprovided,prescribedloads arelimitloads.
(b)
Unless otherwiseprovided, the speci.ed air,ground, and waterloads mustbeplaced in equilibrium with inertia forces, considering each item of mass in the rotorcraft. These loads must be distributed to closely approximate or conservatively represent actual conditions.
(c)
If de.ections under load would signi.cantly change the distribution of external or internal loads, this redistribution must be taken into account.
FAR 29.303 : Factor of safety.
Unless otherwiseprovided, afactor of safety of1.5 mustbe used.Thisfactor applies to external and inertia loads unless its application to the resulting internal stresses is more conservative.
FAR 29.305 : Strength and deformation.
(a)
The structure mustbe able to supportlimit loads withoutdetrimental orpermanent deformation.At anyload up tolimitloads,thedeformationmay notinterferewith safe operation.
(b)
The structure must be able to support ultimate loads without failure. This must be shown by–
(1)
Applying ultimate loads to the structure in a static test for at least three seconds; or
(2)
Dynamic tests simulating actual load application.
FAR 29.307 : Proof of structure.
(a)
[Compliance withthe strength anddeformation requirements ofthis subpart mustbe shown for each critical loading condition accounting for the environment to which the structurewillbe exposedin operation.Structural analysis(static orfatigue) maybe used onlyif the structure conforms to those structuresfor which experience has shown this method tobe reliable.In other cases, substantiatingload tests must be made.]
(b)
Proof of compliance with the strength requirements of this subpart must include–
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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(20)
