spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Section 27.25

equipped with a safety belt and shoulder harness that meets the requirements of paragraphs (a), (b), and (c) of
this section.
(1) Each occupant-s seat must have a
combined safety belt and shoulder harness with a single-point release. Each
pilot-s combined safety belt and shoulder harness must allow each pilot,
when seated with safety belt and shoulder harness fastened, to perform all
functions necessary for flight operations. There must be a means to secure belts and harnesses, when not in
use, to prevent interference with the
operation of the rotorcraft and with
rapid egress in an emergency.
(2) 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.
(3) The safety belt and shoulder harness must meet the static and dynamic
strength requirements, if applicable,
specified by the rotorcraft type certification basis.
(4) For purposes of this section, the
date of manufacture is either - 
(i) The date the inspection acceptance records, or equivalent, reflect
that the rotorcraft is complete and
meets the FAA-Approved Type Design
Data; or
(ii) The date the foreign civil airworthiness authority certifies that the
rotorcraft is complete and issues an
original standard airworthiness certificate, or equivalent, in that country.
(b) For rotorcraft with a certification
basis established prior to October 18,
1999 - 
(1) The maximum passenger seat capacity may be increased to eight or
nine provided the applicant shows compliance with all the airworthiness requirements of this part in effect on October 18, 1999.
(2) The maximum weight may be increased to greater than 6,000 pounds
provided - 
(i) The number of passenger seats is
not increased above the maximum
number certificated on October 18, 1999,
or
(ii) The applicant shows compliance
with all of the airworthiness require-

ments of this part in effect on October
18, 1999.
[Doc. No. 26078, 56 FR 41051, Aug. 16, 1991, as
amended by Amdt. 27-37, 64 FR 45094, Aug. 18,
1999]

Subpart B - Flight
GENERAL
Section 27.21

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. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27-21, 49 FR 44432, Nov. 6,
1984]

Section 27.25

Weight limits.

(a) Maximum weight. The maximum
weight (the highest weight at which
compliance with each applicable requirement of this part is shown) must
be established so that it is - 
(1) Not more than - 
(i) The highest weight selected by the
applicant;
(ii) The design maximum weight (the
highest weight at which compliance
with each applicable structural loading
condition of this part is shown);
(iii) The highest weight at which
compliance with each applicable flight
requirement of this part is shown; or
(iv) The highest weight in which the
provisions of SectionSection 27.87 or 27.143(c)(1), or
combinations
thereof,
are
demonstrated if the weights and operating
conditions (altitude and temperature)
prescribed by those requirements cannot be met; and
(2) Not less than the sum of - 
(i) The empty weight determined
under Section 27.29; and

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