576
14 CFR Ch. I (1–1–19 Edition)
§ 29.21
original standard airworthiness certifi-
cate, or equivalent, in that country.
[Doc. No. 26078, 56 FR 41052, Aug. 16, 1991]
Subpart B—Flight
G
ENERAL
§ 29.21
Proof of compliance.
Each requirement of this subpart
must be met at each appropriate com-
bination of weight and center of grav-
ity within the range of loading condi-
tions for which certification is re-
quested. This must be shown—
(a) By tests upon a rotorcraft of the
type for which certification is re-
quested, 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]
§ 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]
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