[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2007]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR21.24]

[Page 126-127]
 
                     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 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

[[Page 127]]

    (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]