29.1 General
FAR 23.21 : 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)
Thefollowinggeneral tolerancesareallowedduring .ighttesting.However,greater tolerances may be allowed in particular tests :
Item Tolerance
Weight +5%, -10%
Critical items a.ected by weight +5%, -1%
C.G. ±7% total travel.
FAR 23.23 : Load distribution limits.
(a)
[Ranges of weights and centers of gravitywithin which the airplane may be safely operated mustbe established.If aweightand centerofgravity combinationisallo-wable only within certainlateralloaddistributionlimits that couldbeinadvertently exceeded, these limits must be established for the corresponding weight and center of gravity combinations.
(b)
The load distribution limits may not exceed any of the following :
(1)
The selectedlimits;
(2)
The limits at which the structure is proven; or
(3)
The limits at which compliance with each applicable .ight requirement of this subpart is shown.]
Amdt. 23-45, E.. 09/07/93
FAR 23.25 : Weight limits.
(a) [Maximum weight. The maximum weight is the highest weight at which compliance with each applicable requirement of thispart(other than those complied with at the design landing weight) is shown. The maximum weight must be established so that it is–
(1) Not more than the least of–
(i)
Thehighest weight selectedby the applicant; or]
(ii)
The design maximum weight, which is the highest weight at which com-pliance with each applicable structural loading condition of this part (other than those compliedwith at the design landing weight) is shown; or
(iii) [The highest weight at whichcompliance with each applicable .ight re-quirement is shown, and]
′
Elodie Roux. Septembre 2003
Subpart B : Flight
(2) Not less than the weight with–
(i)
Each seat occupied, assuming a weight of 170 pounds for each occupant for normal and commuter category airplanes, and 190 pounds for utility and acrobatic category airplanes, exceptthat seats otherthanpilot seats may be placarded for a lesser weight; and
(A)
Oil at full tank capacity, and
(B)
At least enough fuel for maximum continuous power operation of at least 30 minutes for day-VFR approved airplanes and at least 45 minutes for night-VFR and IFR approved airplanes; or
(ii)
The required minimum crew, and fuel and oil to full tank capacity.
(b) Minimum weight.The minimum weight(thelowest weight at which compliance with each applicable requirementof thispartis shown) mustbe established sothatitis not more than the sum of–
(1)
The empty weight determined under Sec. 23.29;
(2)
The weight ofthe required minimum crew(assuming a weight of170pounds for each crewmember); and
(3)
The weight of–
(i)
For turbojetpowered airplanes,5percent of the totalfuel capacity of that particular fuel tank arrangement under investigation; and
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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(120)
