14 C.F.R. Subpart B—Type Certificates
Title 14 - Aeronautics and Space
Source: Docket No. 5085, 29 FR 14564, Oct. 24, 1964, unless otherwise noted.
This subpart prescribes— (a) Procedural requirements for the issue of type certificates for aircraft, aircraft engines, and propellers; and (b) Rules governing the holders of those certificates. Any interested person may apply for a type certificate. [Amdt. 21–25, 34 FR 14068, Sept. 5, 1969] (a) An application for a type certificate is made on a form and in a manner prescribed by the Administrator and is submitted to the appropriate Aircraft Certification Office. (b) An application for an aircraft type certificate must be accompanied by a three-view drawing of that aircraft and available preliminary basic data. (c) An application for an aircraft engine type certificate must be accompanied by a description of the engine design features, the engine operating characteristics, and the proposed engine operating limitations. [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21–40, 39 FR 35459, Oct. 1, 1974; Amdt. 21–67, 54 FR 39291, Sept. 25, 1989] If the Administrator finds that the airworthiness regulations of this subchapter do not contain adequate or appropriate safety standards for an aircraft, aircraft engine, or propeller because of a novel or unusual design feature of the aircraft, aircraft engine or propeller, he prescribes special conditions and amendments thereto for the product. The special conditions are issued in accordance with Part 11 of this chapter and contain such safety standards for the aircraft, aircraft engine or propeller as the Administrator finds necessary to establish a level of safety equivalent to that established in the regulations. [Amdt. 21–19, 32 FR 17851, Dec. 13, 1967; as amended by Amdt. 21–51, 45 FR 60170, Sept. 11, 1980] (a) Except as provided in §23.2, §25.2, §27.2, §29.2 and in parts 34 and 36 of this chapter, an applicant for a type certificate must show that the aircraft, aircraft engine, or propeller concerned meets— (1) The applicable requirements of this subchapter that are effective on the date of application for that certificate unless— (i) Otherwise specified by the Administrator; or (ii) Compliance with later effective amendments is elected or required under this section; and (2) Any special conditions prescribed by the Administrator. (b) For special classes of aircraft, including the engines and propellers installed thereon (e.g., gliders, airships, and other nonconventional aircraft), for which airworthiness standards have not been issued under this subchapter, the applicable requirements will be the portions of those other airworthiness requirements contained in Parts 23, 25, 27, 29, 31, 33, and 35 found by the Administrator to be appropriate for the aircraft and applicable to a specific type design, or such airworthiness criteria as the Administrator may find provide an equivalent level of safety to those parts. (c) An application for type certification of a transport category aircraft is effective for 5 years and an application for any other type certificate is effective for 3 years, unless an applicant shows at the time of application that his product requires a longer period of time for design, development, and testing, and the Administrator approves a longer period. (d) In a case where a type certificate has not been issued, or it is clear that a type certificate will not be issued, within the time limit established under paragraph (c) of this section, the applicant may— (1) File a new application for a type certificate and comply with all the provisions of paragraph (a) of this section applicable to an original application; or (2) File for an extension of the original application and comply with the applicable airworthiness requirements of this subchapter that were effective on a date, to be selected by the applicant, not earlier than the date which precedes the date of issue of the type certificate by the time limit established under paragraph (c) of this section for the original application. (e) If an applicant elects to comply with an amendment to this subchapter that is effective after the filing of the application for a type certificate, he must also comply with any other amendment that the Administrator finds is directly related. (f) For primary category aircraft, the requirements are: (1) The applicable airworthiness requirements contained in parts 23, 27, 31, 33, and 35 of this subchapter, or such other airworthiness criteria as the Administrator may find appropriate and applicable to the specific design and intended use and provide a level of safety acceptable to the Administrator. (2) The noise standards of part 36 applicable to primary category aircraft. [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21–19, 32 FR 17851, Dec. 13, 1967; Amdt. 21–24, 34 FR 364, Jan. 10, 1969; Amdt. 21–42, 40 FR 1033, Jan. 6, 1975; Amdt. 21–58, 50 FR 46877, Nov. 13, 1985; Amdt. 21–60, 52 FR 8042, Mar. 13, 1987; Amdt. 21–68, 55 FR 32860, Aug. 10, 1990; Amdt. 21–69, 56 FR 41051, Aug. 16, 1991; Amdt. 21–70, 57 FR 41367, Sept. 9, 1992] Each person who proposes to change a product must apply for a new type certificate if the Administrator finds that the proposed change in design, power, thrust, or weight is so extensive that a substantially complete investigation of compliance with the applicable regulations is required. [Doc. No. 28903, 65 FR 36265, June 7, 2000] An applicant is entitled to a type certificate for an aircraft in the normal, utility, acrobatic, commuter, or transport category, or for a manned free balloon, special class of aircraft, or an aircraft engine or propeller, if— (a) The product qualifies under §21.27; or (b) The applicant submits the type design, test reports, and computations necessary to show that the product to be certificated meets the applicable airworthiness, aircraft noise, fuel venting, and exhaust emission requirements of the Federal Aviation Regulations and any special conditions prescribed by the Administrator, and the Administrator finds— (1) Upon examination of the type design, and after completing all tests and inspections, that the type design and the product meet the applicable noise, fuel venting, and emissions requirements of the Federal Aviation Regulations, and further finds that they meet the applicable airworthiness requirements of the Federal Aviation Regulations or that any airworthiness provisions not complied with are compensated for by factors that provide an equivalent level of safety; and (2) For an aircraft, that no feature or characteristic makes it unsafe for the category in which certification is requested. [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21–15, 32 FR 3735, Mar. 4, 1967; Amdt. 21–27, 34 FR 18368, Nov. 18, 1969; Amdt. 21–60, 52 FR 8042, Mar. 13, 1987; Amdt. 21–68, 55 FR 32860, Aug. 10, 1990]
Title 14: Aeronautics and Space
PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS
Subpart B—Type Certificates
§ 21.11 Applicability.
§ 21.13 Eligibility.
§ 21.15 Application for type certificate.
§ 21.16 Special conditions.
§ 21.17 Designation of applicable regulations.
§ 21.19 Changes requiring a new type certificate.
§ 21.21 Issue of type certificate: normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; special classes of aircraft; aircraft engines; propellers.
§ 21.23 [Reserved]
§ 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 §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 §21.17(f); and no feature or characteristic makes it unsafe for its intended use;
(ii) The flight manual required by §21.5(b), including any information required to be furnished by the applicable airworthiness standards;
(iii) Instructions for continued airworthiness in accordance with §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 §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 §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]
§ 21.25 Issue of type certificate: Restricted category aircraft.
(a) An applicant is entitled to a type certificate for an aircraft in the restricted category for special purpose operations if he shows compliance with the applicable noise requirements of Part 36 of this chapter, and if he shows that no feature or characteristic of the aircraft makes it unsafe when it is operated under the limitations prescribed for its intended use, and that the aircraft—
(1) Meets the airworthiness requirements of an aircraft category except those requirements that the Administrator finds inappropriate for the special purpose for which the aircraft is to be used; or
(2) Is of a type that has been manufactured in accordance with the requirements of and accepted for use by, an Armed Force of the United States and has been later modified for a special purpose.
(b) For the purposes of this section, “special purpose operations” includes—
(1) Agricultural (spraying, dusting, and seeding, and livestock and predatory animal control);
(2) Forest and wildlife conservation;
(3) Aerial surveying (photography, mapping, and oil and mineral exploration);
(4) Patrolling (pipelines, power lines, and canals);
(5) Weather control (cloud seeding);
(6) Aerial advertising (skywriting, banner towing, airborne signs and public address systems); and
(7) Any other operation specified by the Administrator.
[Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21–42, 40 FR 1033, Jan. 6, 1975]
§ 21.27 Issue of type certificate: surplus aircraft of the Armed Forces.
(a) Except as provided in paragraph (b) of this section an applicant is entitled to a type certificate for an aircraft in the normal, utility, acrobatic, commuter, or transport category that was designed and constructed in the United States, accepted for operational use, and declared surplus by, an Armed Force of the United States, and that is shown to comply with the applicable certification requirements in paragraph (f) of this section.
(b) An applicant is entitled to a type certificate for a surplus aircraft of the Armed Forces of the United States that is a counterpart of a previously type certificated civil aircraft, if he shows compliance with the regulations governing the original civil aircraft type certificate.
(c) Aircraft engines, propellers, and their related accessories installed in surplus Armed Forces aircraft, for which a type certificate is sought under this section, will be approved for use on those aircraft if the applicant shows that on the basis of the previous military qualifications, acceptance, and service record, the product provides substantially the same level of airworthiness as would be provided if the engines or propellers were type certificated under Part 33 or 35 of the Federal Aviation Regulations.
(d) The Administrator may relieve an applicant from strict compliance with a specific provision of the applicable requirements in paragraph (f) of this section, if the Administrator finds that the method of compliance proposed by the applicant provides substantially the same level of airworthiness and that strict compliance with those regulations would impose a severe burden on the applicant. The Administrator may use experience that was satisfactory to an Armed Force of the United States in making such a determination.
(e) The Administrator may require an applicant to comply with special conditions and later requirements than those in paragraphs (c) and (f) of this section, if the Administrator finds that compliance with the listed regulations would not ensure an adequate level of airworthiness for the aircraft.
(f) Except as provided in paragraphs (b) through (e) of this section, an applicant for a type certificate under this section must comply with the appropriate regulations listed in the following table:
------------------------------------------------------------------------ Date accepted for operational use Type of aircraft by the Armed Regulations that Forces of the apply \1\ United States------------------------------------------------------------------------Small reciprocating-engine Before May 16, CAR Part 3, as powered airplanes. 1956. effective May 15, After May 15, 1956. 1956. CAR Part 3, or FAR Part 23.Small turbine engine-powered Before Oct. 2, CAR Part 3, as airplanes. 1959. effective Oct. 1, After Oct. 1, 1959. 1959. CAR Part 3 or FAR Part 23.Commuter category airplanes.... After (Feb. 17, 1987). FAR Part 23 as of (Feb. 17, 1987)..Large reciprocating-engine Before Aug. 26, CAR Part 4b, as powered airplanes. 1955. effective Aug. 25, After Aug. 25, 1955. 1955. CAR Part 4b or FAR Part 25.Large turbine engine-powered Before Oct. 2, CAR Part 4b, as airplanes. 1959. effective Oct. 1, After Oct. 1, 1959. 1959. CAR Part 4b or FAR Part 25.Rotorcraft with maximum certificated takeoff weight of: 6,000 pounds or less......... Before Oct. 2, CAR Part 6, as 1959. effective Oct. 1, After Oct. 1, 1959. 1959. CAR Part 6, or FAR Part 27. Over 6,000 pounds............ Before Oct. 2, CAR Part 7, as 1959. effective Oct. 1, After Oct. 1, 1959. 1959. CAR Part 7, or FAR 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.------------------------------------------------------------------------
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[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] § 21.29 Issue of type certificate: import products.(a) A type certificate may be issued for a product that is manufactured in a foreign country 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 country in which the product was manufactured 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 §21.17, or the applicable aircraft noise, fuel venting and exhaust emissions requirements of the country in which the product was manufactured, and any other requirements the Administrator 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 §21.17; and (ii) The applicable airworthiness requirements of this subchapter as designated in §21.17, or the applicable airworthiness requirements of the country in which the product was manufactured and any other requirements the Administrator may prescribe to provide a level of safety equivalent to that provided by the applicable airworthiness requirements of this subchapter as designated in §21.17; (2) The applicant has submitted the technical data, concerning aircraft noise and airworthiness, respecting the product required by the Administrator; 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, and the fuel venting and exhaust emission standards of part 34, of the Federal Aviation Regulations where compliance therewith is certified under paragraph (a)(1)(i) of this section, and under the airworthiness standards of that part of the Federal Aviation Regulations with which compliance is certified under paragraph (a)(1)(ii) of this section or to which an equivalent level of safety is certified under paragraph (a)(1)(ii) of this section. [Amdt. 21–27, 34 FR 18363, Nov. 18, 1969, as amended by Amdt. 21–68, 55 FR 32860, Aug. 10, 1990; 55 FR 37287, Sept. 10, 1990] § 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, 27, 29, 31, 33, and 35 of this chapter or as otherwise required by the Administrator; and as specified in the applicable airworthiness criteria for special classes of aircraft defined in §21.17(b); and (d) For primary category aircraft, if desired, a special inspection and preventive maintenance program designed to be accomplished by an appropriately rated and trained pilot-owner. (e) Any other data necessary to allow, by comparison, the determination of the airworthiness, noise characteristics, 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] § 21.33 Inspection and tests.(a) Each applicant must allow the Administrator to make any inspection and any flight and ground test necessary to determine compliance with the applicable requirements of the Federal Aviation Regulations. However, unless otherwise authorized by the Administrator— (1) No aircraft, aircraft engine, propeller, or part thereof may be presented to the Administrator for test unless compliance 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 aircraft, aircraft engine, propeller, or part thereof between the time that compliance 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 presented to the Administrator for test. (b) Each applicant must make all inspections and tests necessary to determine— (1) Compliance with the applicable airworthiness, aircraft noise, fuel venting, and exhaust emission requirements; (2) That materials and products conform to the specifications in the type design; (3) That parts of the products conform to the drawings in the type design; and (4) That the manufacturing processes, construction and assembly conform to those specified in the type design. [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] § 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 section. Before making the tests the applicant must show— (1) Compliance with the applicable structural requirements of this subchapter; (2) Completion of necessary ground inspections and tests; (3) That the aircraft conforms with the type design; and (4) That the Administrator 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 applicant must make all flight tests that the Administrator finds necessary— (1) To determine compliance with the applicable requirements of this subchapter; and (2) For aircraft to be certificated under this subchapter, except gliders and except airplanes of 6,000 lbs. or less maximum certificated weight that are to be certificated under 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 practicable, 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 endurance 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 crew for emergency egress and the use of parachutes. (e) Except in gliders and manned free balloons, an applicant must discontinue flight tests under this section until he shows that corrective action has been taken, whenever— (1) The applicant's test pilot is unable or unwilling to make any of the required flight tests; or (2) Items of noncompliance with requirements are found that may make additional test data meaningless or that would make further testing unduly hazardous. (f) The flight tests prescribed in paragraph (b)(2) of this section must include— (1) For aircraft incorporating turbine engines of a type not previously used in a type certificated aircraft, at least 300 hours of operation with a full complement of engines that conform to a type certificate; and (2) For all other aircraft, at least 150 hours of operation. [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21–40, 39 FR 35459, Oct. 1, 1974; Amdt. 21–51, 45 FR 60170, Sept. 11, 1980; Amdt. 21–70, 57 FR 41368, Sept. 9, 1992] § 21.37 Flight test pilot.Each applicant for a normal, utility, acrobatic, commuter, or transport category aircraft type certificate must provide a person holding an appropriate pilot certificate to make the flight tests required by this part. [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21–59, 52 FR 1835, Jan. 15, 1987] § 21.39 Flight test instrument calibration and correction report.(a) Each applicant for a normal, utility, acrobatic, commuter, or transport category aircraft type certificate must submit a report to the Administrator showing the computations and tests required in connection with the calibration of instruments used for test purposes and in the correction of test results to standard atmospheric conditions. (b) Each applicant must allow the Administrator to conduct any flight tests that he finds necessary to check the accuracy of the report submitted under paragraph (a) of this section. [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21–59, 52 FR 1835, Jan. 15, 1987] § 21.41 Type certificate.Each type certificate is considered to include the type design, the operating limitations, the certificate data sheet, the applicable regulations of this subchapter with which the Administrator records compliance, and any other conditions or limitations prescribed for the product in this subchapter. § 21.43 Location of manufacturing facilities.Except as provided in §21.29, the Administrator does not issue a type certificate if the manufacturing facilities for the product are located outside of the United States, unless the Administrator finds that the location of the manufacturer's facilities places no undue burden on the FAA in administering applicable airworthiness requirements. § 21.45 Privileges.The holder or licensee of a type certificate for a product may— (a) In the case of aircraft, upon compliance with §§21.173 through 21.189, obtain airworthiness certificates; (b) In the case of aircraft engines or propellers, obtain approval for installation or certified aircraft; (c) In the case of any product, upon compliance with §§21.133 through 21.163, obtain a production certificate for the type certificated product; (d) Obtain approval of replacement parts for that product. § 21.47 Transferability.A type certificate may be transferred to or made available to third persons by licensing agreements. Each grantor shall, within 30 days after the transfer of a certificate or execution or termination of a licensing agreement, notify in writing the appropriate Aircraft Certification Office. The notification must state the name and address of the transferee or licensee, date of the transaction, and in the case of a licensing agreement, the extent of authority granted the licensee. [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21–67, 54 FR 39291, Sept. 25, 1989] § 21.49 Availability.The holder of a type certificate shall make the certificate available for examination upon the request of the Administrator or the National Transportation Safety Board. [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967] § 21.50 Instructions for continued airworthiness and manufacturer's maintenance manuals having airworthiness limitations sections.(a) The holder of a type certificate for a rotorcraft for which a Rotorcraft Maintenance Manual containing an “Airworthiness Limitations” section has been issued under §27.1529 (a)(2) or §29.1529 (a)(2) of this chapter, and who obtains approval of changes to any replacement time, inspection interval, or related procedure in that section of the manual, shall make those changes available upon request to any operator of the same type of rotorcraft. (b) The holder of a design approval, including either the type certificate or supplemental type certificate for an aircraft, aircraft engine, or propeller for which application was made after January 28, 1981, shall furnish at least one set of complete Instructions for Continued Airworthiness, prepared in accordance with §§23.1529, 25.1529, 27.1529, 29.1529, 31.82, 33.4, or 35.4 of this chapter, or as specified in the applicable airworthiness criteria for special classes of aircraft defined in §21.17(b), as applicable, to the owner of each type of aircraft, aircraft engine, or propeller upon its delivery, or upon issuance of the first standard airworthiness certificate for the affected aircraft, whichever occurs later, and thereafter make those instructions available to any other person required by this chapter to comply with any of the terms of these instructions. In addition, changes to the Instructions for Continued Airworthiness shall be made available to any person required by this chapter to comply with any of those instructions. [Amdt. No. 21–23, 33 FR 14105, Sept. 18, 1968, as amended by Amdt. No 21–51, 45 FR 60170, Sept. 11, 1980; Amdt. 21–60, 52 FR 8042, Mar. 13, 1987] § 21.51 Duration.A type certificate is effective until surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator. § 21.53 Statement of conformity.(a) Each applicant must submit a statement of conformity (FAA Form 317) to the Administrator for each aircraft engine and propeller presented to the Administrator for type certification. This statement of conformity must include a statement that the aircraft engine or propeller conforms to the type design therefor. (b) Each applicant must submit a statement of conformity to the Administrator for each aircraft or part thereof presented to the Administrator for tests. This statement of conformity must include a statement that the applicant has complied with §21.33(a) (unless otherwise authorized under that paragraph). [Amdt. 21–17, 32 FR 14926, Oct. 28, 1967] Browse Previous | Browse Next |
