(c)
[In the absence of a more rational analysis, the gust load must be computed as follows :
Kgt Ude Vaνt Sνt Lνt =
498
where–
Lνt Vertical surfaceloads(lbs.);
0.88μgt
Kgt gust alleviation factor : Kgt =;
5.3+μgt 2W
μgt lateral mass ratio : μgt = K2 ;
ρcˉt gaνt Sνt lνt Ude Derivedgust velocity(f.p.s.); ρ Air density(slugs/cu.ft.); W the applicable weight of the airplaneintheparticularload case(lbs.); Sνt Area of vertical surface(ft.2); cˉt Meangeometric chord of vertical surface(ft.); aνt Lift curve slope of vertical surface(per radian); K Radius ofgyrationinyaw(ft.); lνt Distancefrom airplane c.g.tolift center of vertical surface(ft.); g Acceleration due to gravity(ft./sec.2);and V Equivalent airspeed(knots).]
Amdt. 23-48, E.. 03/11/96
FAR23.445:Outboard .ns[orwinglets.]
(a)
[If outboard .ns or winglets are included on the horizontal surfaces or wings, the horizontal surfaces or wings must be designed for their maximum load in combina-tion with loads induced by the .ns or winglets and moments or forces exerted on the horizontal surfaces or wings by the .ns or winglets.]
(b)
If outboard .ns [or winglets] extend above and below the horizontal surface, the critical vertical surfaceloading(theloadper unit area asdetermined underSecs.
23.441 and 23.443) must be applied to–
(1)
The part of the vertical surfaces above the horizontal surface with 80 percent of that loading applied to the part below the horizontal surface; and
(2)
The part of the vertical surfaces below the horizontal surface with 80 percent of that loading applied to the part above the horizontal surface;
(c)
The end plate e.ects of outboard .ns [or winglets] must be taken into account in applying the yawing conditions of Sec. 23.441 and Sec. 23.443 to vertical surfaces inparagraph(b) of this section.
(d)
[When rational methods are used for computing loads, the maneuvering loads of Sec.23.441onthevertical surfacesand the one-ghorizontal surfaceload,including induced loads on the horizontal surface and moments or forces exerted on the horizontal surfaces by the vertical surfaces, must be applied simultaneously for the structural loading condition.]
Amdt. 23-42, E.. 02/04/91
30.6 Ailerons and Special Devices
FAR 23.455 : Ailerons.
(a)
The ailerons must be designed for the loads to which they are subjected–
(1)
In the neutral position during symmetrical .ight conditions; and
(2)
By thefollowing de.ections(except aslimitedbypilot e.ort),during unsym-metrical .ight conditions :
(i)
Sudden maximum displacement of the aileron control at VA. Suitable al-lowance may be made for control system de.ections.
(ii)
Su.cient de.ection at VC, where VC is more than VA, to produce a rate of roll notlessthan obtainedinparagraph(a)(2)(i) ofthis section.
(iii) Su.cientde.ection atVD toproduce a rate of roll notless than one-third of that obtainedinparagraph(a)(2)(i) of this section.
(b)
[Reserved.] Amdt. 23-48, E.. 3/11/96
FAR23.457 :[Removed.]
[Removed.] Amdt. 23-48, E.. 03/11/96
FAR 23.459 : Special devices.
Theloadingfor specialdevices usingaerodynamic surfaces(such as slots and spoilers) must be determined from test data.
30.7 Ground Loads
FAR 23.471 : General.
Thelimitgroundloads speci.edinthis subpartare consideredtobe externalloads and inertiaforcesthatact upon an airplane structure.In each speci.edgroundload condition, the external reactions must be placed in equilibrium with the linear and angular inertia forces in a rational or conservative manner.
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(8)
