(3)
Eachengine mount andits supporting structure mustbedesignedfor theloads resulting from a lateral limit load factor of not less than 1.47 for the normal and utility categories, or 2.0 for the acrobatic category.
FAR 23.A11 : Control surface loads.
(a)
General. Each control surface load must be determined using the criteria of para-graph(b) ofthis section and mustlie within the simpli.edloadings ofparagraph (c)of this section.
(b)
Limit pilot forces.In each control surfaceloading conditiondescribedinparagraphs
(c) through(e) of this section, the airloads on the movable surfaces and the cor-responding de.ections need not exceed those which could be obtained in .ight by employing the maximum limit pilot forces speci.ed in the table in Sec. 23.397(b). If the surface loads are limited by these maximum limit pilot forces, the tabs must eitherbe considered to be de.ected to their maximum travelin the direction which would assistthepilot orthede.ection must correspond tothe maximumdegreeof ”out of trim” expected at the speed for the condition under consideration. The tab load, however, need not exceed the value speci.ed in Table 2 of this appendix.
(c)
Surface loading conditions. Each surface loading condition must be investigated as follows :
(1) [Simpli.ed limit surface loadings for the horizontal tail, vertical tail, aileron, wing .aps, and trim tabs are speci.ed in .gures 5 and 6 of this appendix.
(i)
The distribution of load along the span of the surface, irrespective of the chordwise load distribution, must be assumed proportional to the total chord, except on horn balanced surfaces.
(ii)
The load on the stabilizer and elevator, and the load on .n and rudder, must be distributed chordwise as shown in .gure 7 of this appendix.
(iii) In order to ensure adequate torsionalstrength and to accountfor maneu-vers and gusts, the most severe loads must be considered in association with every center of pressure position between the leading edge and the half chord of themeanchord of thesurface(stabilizerand elevator,or .n and rudder).
(iv)
To ensure adequate strength under high leading edge loads, the most se-verestabilizerand .nloadsmustbefurtherconsidered asbeingincreased by 50percent overtheleading 10percent of the chord withtheloads aft of this appropriately decreased to retain the same total load.
(v)
The mostsevere elevator and rudderloads shouldbefurther considered as being distributed parabolically from three times the mean loading of the surface(stabilizerand elevator,or .nand rudder) attheleading edgeof the elevator and rudder, respectively,to zero at the trailing edge according
to the equation :
P(x)= 3(ˉw) (c .x)2 c2 f
where–
Leading edge of elevator. and rudder, respectively
Leading. Trailing. edge edge
Fig. 35.1 – Leading Edge of Elevator and Rudder, Respectively
P(x):local pressure at the chordwise stations x,
c :chord length of the tail surface, cf :chord length of the elevator and rudder respectively, and wˉ:average surface loading as speci.ed in Figure A5.
(vi) Thechordwiseloadingdistributionforailerons,wing.aps,and trimtabs are speci.ed in Table 2 of this appendix.]
(2) If certi.cation in the acrobatic category is desired, the horizontal tail must be investigated for an unsymmetrical load of 100 percent ˉw on one side of the airplanecenterline and50percent onthe otherside of the airplanecenterline.
(d)
[Outboard .ns. Outboard .ns must meet the requirements of Sec. 23.445.]
(e)
Special devices. Special devices must meet the requirements of Sec. 23.459. Amdt. 23-48, E.. 03/11/96
FAR 23.A13 : Control system loads.
(a)
Primary .ight controls and systems. Each primary .ight control and system must be designed as follows :
(1) The .ight control system and its supporting structure must be designed for loads correspondingto125percent of the computedhinge moments of the mo-vable control surface in the conditions prescribed in A23.11 of this appendix. In addition–
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 3(10)
