Federal Aviation Administration, DOT

Section 21.31

Date accepted for operational use
by the Armed Forces
of the United States

Type of aircraft
Large reciprocating-engine powered airplanes
Large turbine engine-powered airplanes .........
Rotorcraft with maximum certificated takeoff
weight of:
6,000 pounds or less ................................
Over 6,000 pounds ...................................

Regulations that apply 1

Before Aug. 26, 1955 ......................
After Aug. 25, 1955 .........................
Before Oct. 2, 1959 .........................
After Oct. 1, 1959 ............................

CAR
CAR
CAR
CAR

Part
Part
Part
Part

4b, as effective Aug. 25, 1955.
4b or 14 CFR Part 25.
4b, as effective Oct. 1, 1959.
4b or 14 CFR Part 25.

Before Oct. 2, 1959 .........................
After Oct. 1, 1959 ............................
Before Oct. 2, 1959 .........................
After Oct. 1, 1959 ............................

CAR
CAR
CAR
CAR

Part
Part
Part
Part

6,
6,
7,
7,

as effective Oct. 1, 1959.
or 14 CFR Part 27.
as effective Oct. 1, 1959.
or 14 CFR Part 29.

1 Where no specific date is listed, the applicable regulations are those in effect on the date that the first aircraft of the particular
model was accepted for operational use by the Armed Forces.

[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987;
52 FR 7262, Mar. 9, 1987; 70 FR 2325, Jan. 13, 2005; Amdt. 21-92, 74 FR 53386, Oct. 16, 2009]

spaschal on DSK3GDR082PROD with CFR

Section 21.29 Issue of type certificate: import
products.
(a) The FAA may issue a type certificate for a product that is manufactured
in a foreign country or jurisdiction
with which the United States has an
agreement for the acceptance of these
products for export and import and
that is to be imported into the United
States if - 
(1) The applicable State of Design
certifies that the product has been examined, tested, and found to meet - 
(i) The applicable aircraft noise, fuel
venting, and exhaust emissions requirements of this subchapter as designated in Section 21.17, or the applicable aircraft noise, fuel venting, and exhaust
emissions requirements of the State of
Design, and any other requirements
the FAA may prescribe to provide
noise, fuel venting, and exhaust emission levels no greater than those provided by the applicable aircraft noise,
fuel venting, and exhaust emission requirements of this subchapter as designated in Section 21.17; and
(ii) The applicable airworthiness requirements of this subchapter as designated in Section 21.17, or the applicable airworthiness requirements of the State
of Design and any other requirements
the FAA may prescribe to provide a
level of safety equivalent to that provided by the applicable airworthiness
requirements of this subchapter as designated in Section 21.17;
(2) The applicant has provided technical data to show the product meets
the requirements of paragraph (a)(1) of
this section; and

(3) The manuals, placards, listings,
and instrument markings required by
the applicable airworthiness (and
noise, where applicable) requirements
are presented in the English language.
(b) A product type certificated under
this section is considered to be type
certificated under the noise standards
of part 36 of this subchapter and the
fuel venting and exhaust emission
standards of part 34 of this subchapter.
Compliance with parts 36 and 34 of this
subchapter is certified under paragraph
(a)(1)(i) of this section, and the applicable airworthiness standards of this subchapter, or an equivalent level of safety, with which compliance is certified
under paragraph (a)(1)(ii) of this section.
[Amdt. 21-92, 74 FR 53386, Oct. 16, 2009]

Section 21.31

Type design.

The type design consists of - 
(a) The drawings and specifications,
and a listing of those drawings and
specifications, necessary to define the
configuration and the design features
of the product shown to comply with
the requirements of that part of this
subchapter applicable to the product;
(b) Information on dimensions, materials, and processes necessary to define
the structural strength of the product;
(c) The Airworthiness Limitations
section of the Instructions for Continued Airworthiness as required by parts
23, 25, 26, 27, 29, 31, 33 and 35 of this subchapter, or as otherwise required by
the FAA; and as specified in the applicable airworthiness criteria for special

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