[Code of Federal Regulations]

[Title 14, Volume 1]

[Revised as of January 1, 2006]

From the U.S. Government Printing Office via GPO Access

[CITE: 14CFR21.24]



[Page 123-124]

 

                     TITLE 14--AERONAUTICS AND SPACE

 

CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION

 

PART 21_CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS--Table of Contents

 

                       Subpart B_Type Certificates

 

Sec. 21.24  Issuance of type certificate: primary category aircraft.



    (a) The applicant is entitled to a type certificate for an aircraft 

in the primary category if--

    (1) The aircraft--

    (i) Is unpowered; is an airplane powered by a single, naturally 

aspirated engine with a 61-knot or less Vso stall speed as 

defined in Sec. 23.49; or is a rotorcraft with a 6-pound per square 

foot



[[Page 124]]



main rotor disc loading limitation, under sea level standard day 

conditions;

    (ii) Weighs not more than 2,700 pounds; or, for seaplanes, not more 

than 3,375 pounds;

    (iii) Has a maximum seating capacity of not more than four persons, 

including the pilot; and

    (iv) Has an unpressurized cabin.

    (2) The applicant has submitted--

    (i) Except as provided by paragraph (c) of this section, a 

statement, in a form and manner acceptable to the Administrator, 

certifying that: the applicant has completed the engineering analysis 

necessary to demonstrate compliance with the applicable airworthiness 

requirements; the applicant has conducted appropriate flight, 

structural, propulsion, and systems tests necessary to show that the 

aircraft, its components, and its equipment are reliable and function 

properly; the type design complies with the airworthiness standards and 

noise requirements established for the aircraft under Sec. 21.17(f); 

and no feature or characteristic makes it unsafe for its intended use;

    (ii) The flight manual required by Sec. 21.5(b), including any 

information required to be furnished by the applicable airworthiness 

standards;

    (iii) Instructions for continued airworthiness in accordance with 

Sec. 21.50(b); and

    (iv) A report that: summarizes how compliance with each provision of 

the type certification basis was determined; lists the specific 

documents in which the type certification data information is provided; 

lists all necessary drawings and documents used to define the type 

design; and lists all the engineering reports on tests and computations 

that the applicant must retain and make available under Sec. 21.49 to 

substantiate compliance with the applicable airworthiness standards.

    (3) The Administrator finds that--

    (i) The aircraft complies with those applicable airworthiness 

requirements approved under Sec. 21.17(f) of this part; and

    (ii) The aircraft has no feature or characteristic that makes it 

unsafe for its intended use.

    (b) An applicant may include a special inspection and preventive 

maintenance program as part of the aircraft's type design or 

supplemental type design.

    (c) For aircraft manufactured outside of the United States in a 

country with which the United States has a bilateral airworthiness 

agreement for the acceptance of these aircraft, and from which the 

aircraft is to be imported into the United States--

    (1) The statement required by paragraph (a)(2)(i) of this section 

must be made by the civil airworthiness authority of the exporting 

country; and

    (2) The required manuals, placards, listings, instrument markings, 

and documents required by paragraphs (a) and (b) of this section must be 

submitted in English.



[Doc. No. 23345, 57 FR 41367, Sept. 9, 1992; as amended by Amdt. 21-75, 

62 FR 62808, Nov. 25, 1997]