spaschal on DSK3GDR082PROD with CFR

Section 27.27

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

(ii) The weight of usable fuel appropriate to the intended operation with
full payload;
(iii) The weight of full oil capacity;
and
(iv) For each seat, an occupant
weight of 170 pounds or any lower
weight for which certification is requested.
(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 - 
(1) Not more than the sum of - 
(i) The empty weight determined
under Section 27.29; and
(ii) The weight of the minimum crew
necessary to operate the rotorcraft, assuming for each crewmember a weight
no more than 170 pounds, or any lower
weight selected by the applicant or included in the loading instructions; and
(2) Not less than - 
(i) The lowest weight selected by the
applicant;
(ii) The design minimum weight (the
lowest weight at which compliance
with each applicable structural loading
condition of this part is shown); or
(iii) 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 27.865 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 in-

crease 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 27.865(a) and (d) of this
part.
(Secs. 313(a), 601, 603, 604, and 605 of the Federal Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424, and 1425); and sec. 6(c) of the
Dept. of Transportation Act (49 U.S.C.
1655(c)))
[Doc. No. 5074, 29 FR 15695, Nov. 29, 1964, as
amended by Amdt. 27-11, 41 FR 55468, Dec. 20,
1976; Amdt. 25-42, 43 FR 2324, Jan. 16, 1978;
Amdt. 27-36, 64 FR 43019, Aug. 6, 1999; Amdt.
27-44, 73 FR 10998, Feb. 29, 2008; 73 FR 33876,
June 16, 2008]

Section 27.27

Center of gravity limits.

The extreme forward and aft centers
of gravity and, where critical, the extreme lateral centers of gravity must
be established for each weight established under Section 27.25. Such an extreme
may not lie beyond - 
(a) The extremes selected by the applicant;
(b) The extremes within which the
structure is proven; or
(c) The extremes within which compliance with the applicable flight requirements is shown.
[Amdt. 27-2, 33 FR 962, Jan. 26, 1968]

Section 27.29 Empty
weight
and
responding center of gravity.

(a) The empty weight and corresponding 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 - 
(i) Oil;
(ii) Hydraulic fluid; and
(iii) Other fluids required for normal
operation of roto-craft systems, except
water intended for injection in the engines.
(b) The condition of the rotorcraft at
the time of determining empty weight
must be one that is well defined and
can be easily repeated, particularly

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