142 

14 CFR Ch. I (1–1–24 Edition) 

§ 21.29 

Type of aircraft 

Date accepted for operational use 

by the Armed Forces 

of the United States 

Regulations that apply

1

 

Large reciprocating-engine powered airplanes 

Before Aug. 26, 1955 ......................
After Aug. 25, 1955 .........................

CAR Part 4b, as effective Aug. 25, 1955. 
CAR Part 4b or 14 CFR Part 25. 

Large turbine engine-powered airplanes .........

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

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

Rotorcraft with maximum certificated takeoff 

weight of: 

6,000 pounds or less ................................

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

CAR Part 6, as effective Oct. 1, 1959. 
CAR Part 6, or 14 CFR Part 27. 

Over 6,000 pounds ...................................

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

CAR Part 7, as effective Oct. 1, 1959. 
CAR Part 7, 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] 

§ 21.29

Issue of type certificate: import 

products. 

(a) The FAA may issue a type certifi-

cate 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 ex-
amined, tested, and found to meet— 

(i) The applicable aircraft noise, fuel 

venting, and exhaust emissions re-
quirements of this subchapter as des-
ignated in § 21.17, or the applicable air-
craft 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 emis-
sion levels no greater than those pro-
vided by the applicable aircraft noise, 
fuel venting, and exhaust emission re-
quirements of this subchapter as des-
ignated in § 21.17; and 

(ii) The applicable airworthiness re-

quirements of this subchapter as des-
ignated in § 21.17, or the applicable air-
worthiness requirements of the State 
of Design and any other requirements 
the FAA may prescribe to provide a 
level of safety equivalent to that pro-
vided by the applicable airworthiness 
requirements of this subchapter as des-
ignated in § 21.17; 

(2) The applicant has provided tech-

nical 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 applica-
ble airworthiness standards of this sub-
chapter, or an equivalent level of safe-
ty, with which compliance is certified 
under paragraph (a)(1)(ii) of this sec-
tion. 

[Amdt. 21–92, 74 FR 53386, Oct. 16, 2009] 

§ 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, mate-

rials, and processes necessary to define 
the structural strength of the product; 

(c) The Airworthiness Limitations 

section of the Instructions for Contin-
ued Airworthiness as required by parts 
23, 25, 26, 27, 29, 31, 33 and 35 of this sub-
chapter, or as otherwise required by 
the FAA; and as specified in the appli-
cable airworthiness criteria for special 

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143 

Federal Aviation Administration, DOT 

§ 21.35 

classes of aircraft defined in § 21.17(b); 
and 

(d) For primary category aircraft, if 

desired, a special inspection and pre-
ventive maintenance program designed 
to be accomplished by an appropriately 
rated and trained pilot-owner. 

(e) Any other data necessary to 

allow, by comparison, the determina-
tion of the airworthiness, noise charac-
teristics, fuel venting, and exhaust 
emissions (where applicable) of later 
products of the same type. 

[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as 
amended by Amdt. 21–27, 34 FR 18363, Nov. 18, 
1969; Amdt. 21–51, 45 FR 60170, Sept. 11, 1980; 
Amdt. 21–60, 52 FR 8042, Mar. 13, 1987; Amdt. 
21–68, 55 FR 32860, Aug. 10, 1990; Amdt. 21–70, 
57 FR 41368, Sept. 9, 1992; Amdt. 21–90, 72 FR 
63404, Nov. 8, 2007] 

§ 21.33

Inspection and tests. 

(a) Each applicant must allow the 

FAA to make any inspection and any 
flight and ground test necessary to de-
termine compliance with the applica-
ble requirements of this subchapter. 
However, unless otherwise authorized 
by the FAA— 

(1) No aircraft, aircraft engine, pro-

peller, or part thereof may be pre-
sented to the FAA for test unless com-
pliance with paragraphs (b)(2) through 
(b)(4) of this section has been shown for 
that aircraft, aircraft engine, propeller, 
or part thereof; and 

(2) No change may be made to an air-

craft, aircraft engine, propeller, or part 
thereof between the time that compli-
ance with paragraphs (b)(2) through 
(b)(4) of this section is shown for that 
aircraft, aircraft engine, propeller, or 
part thereof and the time that it is pre-
sented to the FAA for test. 

(b) Each applicant must make all in-

spections and tests necessary to deter-
mine— 

(1) Compliance with the applicable 

airworthiness, aircraft noise, fuel vent-
ing, and exhaust emission require-
ments; 

(2) That materials and products con-

form to the specifications in the type 
design; 

(3) That parts of the products con-

form to the drawings in the type de-
sign; and 

(4) That the manufacturing proc-

esses, construction and assembly con-

form to those specified in the type de-
sign. 

[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as 
amended by Amdt. 21–17, 32 FR 14926, Oct. 28, 
1967; Amdt. 21–27, 34 FR 18363, Nov. 18, 1969; 
Amdt. 21–44, 41 FR 55463, Dec. 20, 1976; Amdt. 
21–68, 55 FR 32860, Aug. 10, 1990; Amdt. 21–68, 
55 FR 32860, Aug. 10, 1990; Amdt. 21–92, 74 FR 
53386, Oct. 16, 2009] 

§ 21.35

Flight tests. 

(a) Each applicant for an aircraft 

type certificate (other than under 
§§ 21.24 through 21.29) must make the 
tests listed in paragraph (b) of this sec-
tion. Before making the tests the appli-
cant must show— 

(1) Compliance with the applicable 

structural requirements of this sub-
chapter; 

(2) Completion of necessary ground 

inspections and tests; 

(3) That the aircraft conforms with 

the type design; and 

(4) That the FAA received a flight 

test report from the applicant (signed, 
in the case of aircraft to be certificated 
under Part 25 [New] of this chapter, by 
the applicant’s test pilot) containing 
the results of his tests. 

(b) Upon showing compliance with 

paragraph (a) of this section, the appli-
cant must make all flight tests that 
the FAA finds necessary— 

(1) To determine compliance with the 

applicable requirements of this sub-
chapter; and 

(2) For aircraft to be certificated 

under this subchapter, except gliders 
and low-speed, certification level 1 or 2 
airplanes, as defined in part 23 of this 
chapter, to determine whether there is 
reasonable assurance that the aircraft, 
its components, and its equipment are 
reliable and function properly. 

(c) Each applicant must, if prac-

ticable, make the tests prescribed in 
paragraph (b)(2) of this section upon 
the aircraft that was used to show 
compliance with— 

(1) Paragraph (b)(1) of this section; 

and 

(2) For rotorcraft, the rotor drive en-

durance tests prescribed in § 27.923 or 
§ 29.923 of this chapter, as applicable. 

(d) Each applicant must show for 

each flight test (except in a glider or a 
manned free balloon) that adequate 
provision is made for the flight test 

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