(d)
Seaplanes must demonstrate satisfactory directional stability and control for water operations up to the maximum wind velocity speci.ed in paragraph (a) of this section.

Amdt. 23-50, E.. 03/11/96
FAR23.235:[Operationonunpaved surfaces.]
[The airplane must be demonstrated to have satisfactory characteristics and the shock-absorbing mechanism must not damage the structure of the airplane when the airplane is taxied on the roughest ground that may reasonably be expected in normal operation and when takeo.s and landings areperformed on unpaved runwayshaving the roughest surface that may reasonably be expected in normal operation.] Amdt. 23-50, E.. 03/11/96
FAR23.237 :[Operation on water.]
[A wave height, demonstrated to be safe for operation, and any necessary water handling procedures for seaplanes and amphibians must be established.] Amdt. 23-50, E.. 03/11/96
FAR 23.239 : Spray characteristics.
Spray may not dangerously obscure the vision of the pilots or damage the propellers or otherparts of a seaplane or amphibian at anytimeduringtaxiing, takeo., andlanding.
29.10 Miscellaneous Flight Requirements
FAR 23.251 : Vibration and bu.eting.
[There mustbe no vibration orbu.etingsevere enough to resultin structuraldamage, and eachpart ofthe airplane mustbefreefrom excessive vibration, under any appropriate speed and power conditions up to VD/MD. In addition, there must be no bu.eting in any normal .ightconditionsevereenough tointerferewith thesatisfactory control of the airplane or cause excessive fatigue to the .ightcrew. Stall warning bu.eting within these limits is allowable.] Amdt. 23-45, E.. 09/07/93
FAR 23.253 : High speed characteristics.
If a maximum operating speed VMO/MMO is established under Sec. 23.1505(c), the following speed increase and recovery characteristics must be met :
(a) Operating conditions and characteristics likely to cause inadvertent speed increases (includingupsets in pitch and roll) must be simulated with the airplane trimmed at any likely speed up to VMO/MMO. These conditions and characteristics include gust upsets, inadvertent control movements, low stick force gradients in relation to control friction, passenger movement, leveling o. from climb, and descent from Mach to airspeed limit altitude.
(b)
Allowingforpilot reaction time after occurrence of the e.ectiveinherent or arti.cial speed warning speci.ed in Sec. 23.1303, it must be shown that the airplane can be recovered to a normal attitude and its speed reduced to VMO/MMO, without–

(1)
[ExceedingVD/MD, the maximum speed shown underSec.23.251, orthe struc-tural limitations; or

(2)
Bu.eting that would impair the pilot’s ability to read the instruments or to control the airplane for recovery.]

(c)
There may be no control reversal about any axis at any speed up to the maximum speed shown under Sec. 23.251. Any reversal of elevator control force or tendency of the airplane to pitch, roll, or yaw must be mild and readily controllable, using normalpiloting techniques.

Amdt. 23-50, E.. 03/11/96
′
Elodie Roux. Septembre 2003
Subpart B : Flight
Chapitre 30 Subpart C : Structure
Sommaire
30.1General ............................... 264 FAR23.301:Loads. ....................... 264 FAR23.302:[Canard ortandemwing con.gurations.] . . . . 264 FAR23.303:Factorof safety.. . . . . . . . . . . . . . . . . . 264 FAR 23.305 : Strength and deformation. . . . . . . . . . . . . 264 FAR23.307:Proof of structure. . . . . . . . . . . . . . . . . 265
30.2FlightLoads ............................ 265 FAR23.321:General. ...................... 265 FAR 23.331 : Symmetrical .ight conditions. . . . . . . . . . . 265 FAR23.333:Flightenvelope.. . . . . . . . . . . . . . . . . . 265 FAR23.335:Designairspeeds. ................. 266 FAR 23.337 : Limit maneuvering load factors. . . . . . . . . . 268 FAR23.341:Gustloadfactors.. . . . . . . . . . . . . . . . . 269 FAR23.343:[Designfuelloads.] . . . . . . . . . . . . . . . . 269 FAR23.345:Highliftdevices. ................. 270 FAR 23.347 : Unsymmetrical .ight conditions. . . . . . . . . 270 FAR23.349:Rolling conditions. . . . . . . . . . . . . . . . . 271 FAR23.351:Yawing conditions. . . . . . . . . . . . . . . . . 271 FAR23.361:Enginetorque. .................. 271 FAR23.363:Sideload onenginemount. . . . . . . . . . . . 272 FAR23.365:Pressurized cabinloads. . . . . . . . . . . . . . 272 FAR23.367:[Unsymmetricalloadsduetoenginefailure.] . . 273 FAR23.369:Rearlifttruss. .................. 273 FAR 23.371 : Gyroscopic and aerodynamic loads. . . . . . . . 273 FAR23.373:[Speed controldevices.] . . . . . . . . . . . . . . 274
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 1(140)