638
14 CFR Ch. I (1–1–14 Edition)
§ 27.1
27.1509
Rotor speed.
27.1519
Weight and center of gravity.
27.1521
Powerplant limitations.
27.1523
Minimum flight crew.
27.1525
Kinds of operations.
27.1527
Maximum operating altitude.
27.1529
Instructions for Continued Air-
worthiness.
M
ARKINGS AND
P
LACARDS
27.1541
General.
27.1543
Instrument markings: general.
27.1545
Airspeed indicator.
27.1547
Magnetic direction indicator.
27.1549
Powerplant instruments.
27.1551
Oil quantity indicator.
27.1553
Fuel quantity indicator.
27.1555
Control markings.
27.1557
Miscellaneous markings and plac-
ards.
27.1559
Limitations placard.
27.1561
Safety equipment.
27.1565
Tail rotor.
R
OTORCRAFT
F
LIGHT
M
ANUAL AND
A
PPROVED
M
ANUAL
M
ATERIAL
27.1581
General.
27.1583
Operating limitations.
27.1585
Operating procedures.
27.1587
Performance information.
27.1589
Loading information.
A
PPENDIX
A
TO
P
ART
27—I
NSTRUCTIONS FOR
C
ONTINUED
A
IRWORTHINESS
A
PPENDIX
B
TO
P
ART
27—A
IRWORTHINESS
C
RI
-
TERIA
FOR
H
ELICOPTER
I
NSTRUMENT
F
LIGHT
A
PPENDIX
C
TO
P
ART
27—C
RITERIA FOR
C
AT
-
EGORY
A
A
PPENDIX
D
TO
P
ART
27—HIRF E
NVIRON
-
MENTS AND
E
QUIPMENT
HIRF T
EST
L
EV
-
ELS
A
UTHORITY
: 49 U.S.C. 106(g), 40113, 44701–
44702, 44704.
S
OURCE
: Docket No. 5074, 29 FR 15695, Nov.
24, 1964, unless otherwise noted.
Subpart A—General
§ 27.1
Applicability.
(a) This part prescribes airworthiness
standards for the issue of type certifi-
cates, and changes to those certifi-
cates, for normal category rotorcraft
with maximum weights of 7,000 pounds
or less and nine or less passenger seats.
(b) Each person who applies under
Part 21 for such a certificate or change
must show compliance with the appli-
cable requirements of this part.
(c) Multiengine rotorcraft may be
type certified as Category A provided
the requirements referenced in appen-
dix C of this part are met.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–33, 61 FR 21906, May 10,
1996; Amdt. 27–37, 64 FR 45094, Aug. 18, 1999]
§ 27.2
Special retroactive require-
ments.
(a) 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.
(1) 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.
(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 har-
ness must meet the static and dynamic
strength requirements, if applicable,
specified by the rotorcraft type certifi-
cation basis.
(4) For purposes of this section, the
date of manufacture is either—
(i) The date the inspection accept-
ance records, or equivalent, reflect
that the rotorcraft is complete and
meets the FAA-Approved Type Design
Data; or
(ii) The date the foreign civil air-
worthiness authority certifies that the
rotorcraft is complete and issues an
original standard airworthiness certifi-
cate, or equivalent, in that country.
(b) For rotorcraft with a certification
basis established prior to October 18,
1999—
(1) The maximum passenger seat ca-
pacity may be increased to eight or
nine provided the applicant shows com-
pliance with all the airworthiness re-
quirements of this part in effect on Oc-
tober 18, 1999.
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