Section 29.21

14 CFR Ch. I (1-1-19 Edition)

original standard airworthiness certificate, or equivalent, in that country.
[Doc. No. 26078, 56 FR 41052, Aug. 16, 1991]

Subpart B - Flight
GENERAL
Section 29.21

Proof of compliance.

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 certification is requested. This must be shown - 
(a) By tests upon a rotorcraft of the
type for which certification is requested, or by calculations based on,
and equal in accuracy to, the results of
testing; and
(b) By systematic investigation of
each required combination of weight
and center of gravity, if compliance
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]

spaschal on DSK3GDR082PROD with CFR

Section 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 takeoff, enroute operation, 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 compliance with each applicable flight requirement 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
Section 29.143(c) and may include other demonstrated wind velocities and azimuths. 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 requirement 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 compliance with each applicable flight requirement of this part is shown.
(c) Total weight with jettisonable external load. A total weight for the rotorcraft with a jettisonable external load
attached that is greater than the maximum weight established under paragraph (a) of this section may be established for any 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 Section 29.865 or under equivalent operational 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 increase over that established under
paragraph (a) of this section, and
(5) Operation of the rotorcraft at a
total weight greater than the maximum certificated weight established
under paragraph (a) of this section is
limited by appropriate operating limitations under Section 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]

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