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(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. 29-24, E.. 12/6/84
FAR 29.25 : Weight limits.
(a)
Maximum weight. The maximum weight (the highest weight at which compliance with each applicable requirement of this Part is shown) or, at the option of the applicant, the highest weight for each altitude and for each practicably separable operating condition, such as takeo., enroute operation, and landing, must be esta-blished so that it is not more than–

(1)
The highest weight selected by the applicant;

(2)
The design maximum weight (the highest weight at which compliance with each applicable structural loading condition of this Part is shown); or

(3)
Thehighestweight at which compliancewith each applicable .ight requirement of this Part is shown.

 

(b)
Minimum weight.The minimum weight(thelowest weight at which compliance with each applicablerequirement of thisPartisshown) mustbe established sothatitis not less than–

(1)
The lowest weight selected by the applicant;

(2)
The design minimum weight(the lowest weight at which compliance with each structural loading condition of this Part is shown); or

(3)
Thelowest weight at which compliancewith each applicable .ight requirement of this Part is shown.

 

(c)
[Total weight withjettisonable externalload. A total weight for 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.

29.865 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

 

′
Elodie Roux. Septembre 2003
Subpart B : Flight
(5) Operation of the rotorcraft at a total weight greater than the maximum cer-ti.cated weight established underparagraph(a) of this sectionislimitedby appropriate operating limitations underSec.29.865(a) and(d) ofthispart.]
Amdt. 29-43, E.. 10/5/99
FAR 29.27 : Center of gravity limits.
The extremeforwardand[aft centers ofgravity and, where critical,the extremelateral centersofgravity mustbe establishedfor each weight established underSec.29.25.Such an extreme may not lie beyond–]
(a)
The extremes selected by the applicant;

(b)
The extremes within which the structure is proven; or

(c)
The extremes within which compliance with the applicable .ight requirements is

shown. Amdt. 29-3, E.. 2/25/68
FAR 29.29 : Empty weight and corresponding center of gravity.
(a)
The empty weight and corresponding center of gravity must be determined by wei-ghing the rotorcraft without the crew and payload, but with–

(1)
Fixed ballast;

(2)
Unusable fuel;[and

(3)
Full operating .uids, including–

(i)
Oil;

(ii)
Hydraulic .uid; 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 5(10)