Federal Aviation Administration, DOT

Section 36.5

Nacelle angle is defined as the angle
between the rotor shaft centerline and
the longitudinal axis of the aircraft fuselage.
Tiltrotor means a class of aircraft capable of vertical take-off and landing,
within the powered-lift category, with
rotors mounted at or near the wing tips
that vary in pitch from near vertical to
near horizontal configuration relative
to the wing and fuselage.
Vertical takeoff and landing (VTOL)
mode means the aircraft state or configuration having the rotors orientated
with the axis of rotation in a vertical
manner (i.e., nacelle angle of approximately 90 degrees) for vertical takeoff
and landing operations.
VCON is defined as the maximum authorized speed for any nacelle angle in
VTOL/Conversion mode.
VTOL/Conversion mode is all approved
nacelle positions where the design operating rotor speed is used for hover
operations.
VTOL mode RPM means highest range
of RPM that occur for takeoff, approach, hover, and conversion conditions.
[Doc. No. 13243, Amdt. 36-4, 40 FR 1034, Jan.
6, 1975]

spaschal on DSK3GDR082PROD with CFR

EDITORIAL NOTE: For FEDERAL REGISTER citations affecting Section 36.1, see the List of CFR
Sections Affected, which appears in the
Finding Aids section of the printed volume
and at www.govinfo.gov.

Section 36.2 Requirements as of date of application.
(a) Section 21.17 of this chapter notwithstanding, each person who applies
for a type certificate for an aircraft
covered by this part, must show that
the aircraft meets the applicable requirements of this part that are effective on the date of application for that
type certificate. When the time interval between the date of application for
the type certificate and the issuance of
the type certificate exceeds 5 years, the
applicant must show that the aircraft
meets the applicable requirements of
this part that were effective on a date,
to be selected by the applicant, not
earlier than 5 years before the issue of
the type certificate.
(b) Section 21.101(a) of this chapter
notwithstanding, each person who applies for an acoustical change to a type

design specified in Section 21.93(b) of this
chapter must show compliance with
the applicable requirements of this
part that are effective on the date of
application for the change in type design. When the time interval between
the date of application for the change
in type design and the issuance of the
amended or supplemental type certificate exceeds 5 years, the applicant
must show that the aircraft meets the
applicable requirements of this part
that were effective on a date, to be selected by the applicant, not earlier
than 5 years before the issue of the
amended or supplemental type certificate.
(c) If an applicant elects to comply
with a standard in this part that was
effective after the filing of the application for a type certificate or change to
a type design, the election:
(1) Must be approved by the FAA;
(2) Must include standards adopted
between the date of application and the
date of the election;
(3) May include other standards
adopted after the standard elected by
the applicant as determined by the
FAA.
[Amdt. 36-54, 67 FR 45211, July 8, 2002; Amdt.
36-24, 67 FR 63195, Oct. 10, 2002]

Section 36.3 Compatibility with airworthiness requirements.
It must be shown that the aircraft
meets the airworthiness regulations
constituting the type certification
basis of the aircraft under all conditions in which compliance with this
part is shown, and that all procedures
used in complying with this part, and
all procedures and information for the
flight crew developed under this part,
are consistent with the airworthiness
regulations constituting the type certification basis of the aircraft.
[Doc. No. 9337, 34 FR 18364, Nov. 18, 1969, as
amended by Amdt. 36-14, 53 FR 3540, Feb. 5,
1988]

Section 36.5 Limitation of part.
Pursuant to 49 U.S.C. 44715, the noise
levels in this part have been determined to be as low as is economically
reasonable,
technologically
practicable, and appropriate to the type of
aircraft to which they apply. No determination is made, under this part, that

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