FAR25.161:Trim. ....................... 513
45.5Stability ............................... 514 FAR25.171:General. ...................... 514 FAR 25.173 : Static longitudinal stability. . . . . . . . . . . . 514
491
Subpart B : Flight
FAR 25.175 : Demonstration of static longitudinal stability. . 515 FAR 25.177 : Static lateral-directional stability. . . . . . . . 517 FAR25.181:Dynamicstability. . . . . . . . . . . . . . . . . 517
45.6Stalls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 517
FAR25.201:Stalldemonstration. . . . . . . . . . . . . . . . 517 FAR25.203:Stall characteristics. . . . . . . . . . . . . . . . 518 FAR25.205:[Removed.] .................... 518 FAR25.207:Stall warning. .................. 519
45.7 Ground and Water Handling Characteristics . . . . . . . . . 519
FAR 25.231 : Longitudinal stability and control. . . . . . . . 519 FAR 25.233 : Directional stability and control. . . . . . . . . 520 FAR25.235:Taxiing condition. . . . . . . . . . . . . . . . . 520 FAR25.237:Wind velocities. ................. 520 FAR 25.239 : Spray characteristics, control, and stability on water. ......................... 520
45.8 Miscellaneous Flight Requirements . . . . . . . . . . . . . . . 521
FAR25.251:Vibrationandbu.eting. . . . . . . . . . . . . . 521 FAR 25.253 : High-speed characteristics. . . . . . . . . . . . 522 FAR25.255:[Out-of-trimcharacteristics.] . . . . . . . . . . 522
45.1 General
FAR 25.21 : Proof of compliance.
(a)
Each requirement of this subpart must be met at each appropriate combination of weight and center of gravity within the range of loading conditions for which certi.cation is requested. This must be shown–
(1)
By tests upon an airplane of the type for which certi.cation is requested, or by calculationsbased on, and equalin accuracy to,the results of testing; and
(2)
By systematicinvestigation of eachprobable combination of weight and center of gravity, if compliance cannot be reasonably inferred from combinations investigated.
(b)
[[Reserved.]]
(c)
The controllability, stability, trim, and stalling characteristics of the airplane must be shown for each altitude up to the maximum expected in operation.
(d)
[Parameters critical for the test being conducted, such as weight, loading (center of gravity and inertia), airspeed, power, and wind, must be maintained within acceptable tolerances of the critical values during .ight testing.]
(e)
If compliancewith the .ightcharacteristicsrequirementsisdependentuponastabi-lity augmentation system or upon any other automatic orpower-operated system, compliance must be shown with Secs. 25.671 and 25.672.
(f)
In meeting the requirementsofSecs.25.105(d),25.125,25.233,and25.237,the wind velocity must be measured at a height of 10 meters above the surface, or corrected for the di.erence between the height at which the wind velocity is measured and the 10-meter height.
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 3(21)
