577 

Federal Aviation Administration, DOT 

§ 29.29 

cannot be reasonably inferred from 
combinations investigated. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–24, 49 FR 44435, Nov. 6, 
1984] 

§ 29.25

Weight limits. 

(a) 

Maximum weight. The maximum 

weight (the highest weight at which 
compliance with each applicable re-
quirement of this part is shown) or, at 
the option of the applicant, the highest 
weight for each altitude and for each 
practicably separable operating condi-
tion, such as takeoff, enroute oper-
ation, and landing, must be established 
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) The highest weight at which com-

pliance with each applicable flight re-
quirement of this part is shown. 

(4) For Category B rotorcraft with 9 

or less passenger seats, the maximum 
weight, altitude, and temperature at 
which the rotorcraft can safely operate 
near the ground with the maximum 
wind velocity determined under 
§ 29.143(c) and may include other dem-
onstrated wind velocities and azi-
muths. The operating envelopes must 
be stated in the Limitations section of 
the Rotorcraft Flight Manual. 

(b) 

Minimum weight. The minimum 

weight (the lowest weight at which 
compliance with each applicable re-
quirement of this part is shown) must 
be established so that it is 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) The lowest weight at which com-

pliance with each applicable flight re-
quirement of this part is shown. 

(c) 

Total weight with jettisonable exter-

nal load. A total weight for the rotor-
craft with a jettisonable external load 
attached that is greater than the max-
imum weight established under para-
graph (a) of this section may be estab-

lished for any rotorcraft-load combina-
tion if— 

(1) The rotorcraft-load combination 

does not include human external cargo, 

(2) Structural component approval 

for external load operations under ei-
ther § 29.865 or under equivalent oper-
ational standards is obtained, 

(3) The portion of the total weight 

that is greater than the maximum 
weight established under paragraph (a) 
of this section is made up only of the 
weight of all or part of the jettisonable 
external load, 

(4) Structural components of the 

rotorcraft are shown to comply with 
the applicable structural requirements 
of this part under the increased loads 
and stresses caused by the weight in-
crease over that established under 
paragraph (a) of this section, and 

(5) Operation of the rotorcraft at a 

total weight greater than the max-
imum certificated weight established 
under paragraph (a) of this section is 
limited by appropriate operating limi-
tations under § 29.865 (a) and (d) of this 
part. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–12, 41 FR 55471, Dec. 20, 
1976; Amdt. 29–43, 64 FR 43020, Aug. 6, 1999; 
Amdt. 29–51, 73 FR 11001, Feb. 29, 2008] 

§ 29.27

Center of gravity limits. 

The extreme forward and aft centers 

of gravity and, where critical, the ex-
treme lateral centers of gravity must 
be established for each weight estab-
lished under § 29.25. Such an extreme 
may not lie beyond— 

(a) The extremes selected by the ap-

plicant; 

(b) The extremes within which the 

structure is proven; or 

(c) The extremes within which com-

pliance with the applicable flight re-
quirements is shown. 

[Amdt. 29–3, 33 FR 965, Jan. 26, 1968] 

§ 29.29

Empty weight and cor-

responding center of gravity. 

(a) The empty weight and cor-

responding center of gravity must be 
determined by weighing the rotorcraft 
without the crew and payload, but 
with— 

(1) Fixed ballast; 
(2) Unusable fuel; and 
(3) Full operating fluids, including— 

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