576
14 CFR Ch. I (1–1–24 Edition)
§ 29.1
S
OURCE
: Docket No. 5084, 29 FR 16150, Dec.
3, 1964, unless otherwise noted.
Subpart A—General
§ 29.1
Applicability.
(a) This part prescribes airworthiness
standards for the issue of type certifi-
cates, and changes to those certifi-
cates, for transport category rotor-
craft.
(b) Transport category rotorcraft
must be certificated in accordance
with either the Category A or Category
B requirements of this part. A multien-
gine rotorcraft may be type certifi-
cated as both Category A and Category
B with appropriate and different oper-
ating limitations for each category.
(c) Rotorcraft with a maximum
weight greater than 20,000 pounds and
10 or more passenger seats must be
type certificated as Category A rotor-
craft.
(d) Rotorcraft with a maximum
weight greater than 20,000 pounds and
nine or less passenger seats may be
type certificated as Category B rotor-
craft provided the Category A require-
ments of Subparts C, D, E, and F of
this part are met.
(e) Rotorcraft with a maximum
weight of 20,000 pounds or less but with
10 or more passenger seats may be type
certificated as Category B rotorcraft
provided the Category A requirements
of §§ 29.67(a)(2), 29.87, 29.1517, and sub-
parts C, D, E, and F of this part are
met.
(f) Rotorcraft with a maximum
weight of 20,000 pounds or less and nine
or less passenger seats may be type
certificated as Category B rotorcraft.
(g) Each person who applies under
Part 21 for a certificate or change de-
scribed in paragraphs (a) through (f) of
this section must show compliance
with the applicable requirements of
this part.
[Amdt. 29–21, 48 FR 4391, Jan. 31, 1983, as
amended by Amdt. 29–39, 61 FR 21898, May 10,
1996; 61 FR 33963, July 1, 1996]
§ 29.2
Special retroactive require-
ments.
For each rotorcraft manufactured
after September 16, 1992, each applicant
must show that each occupant’s seat is
equipped with a safety belt and shoul-
der harness that meets the require-
ments of paragraphs (a), (b), and (c) of
this section.
(a) Each occupant’s seat must have a
combined safety belt and shoulder har-
ness with a single-point release. Each
pilot’s combined safety belt and shoul-
der harness must allow each pilot,
when seated with safety belt and shoul-
der harness fastened, to perform all
functions necessary for flight oper-
ations. There must be a means to se-
cure belts and harnesses, when not in
use, to prevent interference with the
operation of the rotorcraft and with
rapid egress in an emergency.
(b) Each occupant must be protected
from serious head injury by a safety
belt plus a shoulder harness that will
prevent the head from contacting any
injurious object.
(c) The safety belt and shoulder har-
ness must meet the static and dynamic
strength requirements, if applicable,
specified by the rotorcraft type certifi-
cation basis.
(d) For purposes of this section, the
date of manufacture is either—
(1) The date the inspection accept-
ance records, or equivalent, reflect
that the rotorcraft is complete and
meets the FAA-Approved Type Design
Data; or
(2) The date that the foreign civil air-
worthiness authority certifies the
rotorcraft is complete and issues an
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
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§ 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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