page-6

490

14 CFR Ch. I (1–1–19 Edition)

§ 27.27

(ii) The weight of usable fuel appro-

priate 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 re-
quested.

(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—

(1) Not more than the sum of—
(i) The empty weight determined

under § 27.29; and

(ii) The weight of the minimum crew

necessary to operate the rotorcraft, as-
suming for each crewmember a weight
no more than 170 pounds, or any lower
weight selected by the applicant or in-
cluded 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 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 § 27.865 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 § 27.865(a) and (d) of this
part.

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral 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]

§ 27.27

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 § 27.25. 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

pliance with the applicable flight re-
quirements is shown.

[Amdt. 27–2, 33 FR 962, Jan. 26, 1968]

§ 27.29

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—
(i) Oil;
(ii) Hydraulic fluid; and
(iii) Other fluids required for normal

operation of roto-craft systems, except
water intended for injection in the en-
gines.

(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

VerDate Sep<11>2014

12:50 Apr 30, 2019

Jkt 247046

PO 00000

Frm 00500

Fmt 8010

Sfmt 8010

Y:\SGML\247046.XXX

247046

spaschal on DSK3GDR082PROD with CFR