779
Subpart B : Flight
62.1 General
FAR 27.21 : Proof of compliance
[Eachrequirement of this subpart must be met at each appropriate combination of weight and center ofgravity within the range ofloading conditionsfor which certi.cation is requested. This must be shown–
(a)
By tests upon a rotorcraft of the type for which certi.cation is requested, or by calculationsbased on, and equalin accuracy to,the results oftesting; and
(b)
By systematic investigation of each required combination of weight and center of gravity if compliance cannot be reasonably inferred from combinations investiga-ted.]
Amdt. 27-21, E.. 12/6/84
FAR 27.25 : Weight limits
(a)
Maximum weight.The maximum weight(thehighest weight at which compliance with each applicable requirement of this Partis shown) mustbe established so that it is–
(1)
Not more than–
(i)
Thehighest weight selectedby the applicant;
(ii)
The design maximum weight (the highest weight at which compliance with each applicable structural loading condition of this Part is shown); or
(iii) The highest weight at which compliance with each applicable .ight re-quirement of this Part is shown; and
(2)
Not less than the sum of–
(i)
The empty weight determined under Sec. 27.29;
(ii)
The weight of usable fuel appropriate to the intended operation with full payload;
(iii) The weight of full oil capacity; and
(iv) For each seat, an occupant weightof170pounds oranylowerweightfor which certi.cation is requested.
(b)
Minimum weight.The minimum weight(thelowestweight at which compliance with each applicable requirement of this Part is shown) must be established so that it is–
(1)
Not more than the sum of–
(i)
The empty weight determined under Sec. 27.29; and
(ii)
The weight of the minimum crew necessary to operate the rotorcraft, assuming for each crewmember a weight no more than 170 pounds, or any lower weight selected by the applicant or included in the loading instructions; and
(2)
Not less than–
(i)
Thelowest weight selectedby the applicant;
(ii)
Thedesign minimum weight(thelowest weight at which compliance with each applicable structuralloading condition of thisPartis shown); or
(iii) Thelowest weight at which compliancewith each applicable .ight requi-rement of this Part is shown.
(c)
[Totalweight withjettisonable externalload.A total weightfor the rotorcraft with a jettisonable externalloadattachedthatisgreaterthanthe maximum weight establi-shed underparagraph(a) of this sectionmaybe establishedforany rotorcraft-load combination if–
(1)
The rotorcraft-load combination does not include human external cargo,
(2)
Structural component approval for external load operations under either Sec.
27.865 or under equivalent operational standards is obtained,
(3)
The portion of the total weight that is greater than the maximum weight established underparagraph(a) of this sectionis made up only of the weight of all orpart of thejettisonable externalload,
(4)
Structural components of the rotorcraft are shown to comply with the ap-plicable structural requirements of this part under the increased loads and stresses caused by the weight increase over that established under paragraph (a)of this section, and
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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 4(66)
