cfr_sections
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143 rows where part_number = 21 and title_number = 14 sorted by section_id
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| section_id ▼ | title_number | title_name | chapter | subchapter | part_number | part_name | subpart | subpart_name | section_number | section_heading | agency | authority | source_citation | amendment_citations | full_text |
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| 14:14:1.0.1.3.10.1.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | A | Subpart A—General | § 21.1 Applicability and definitions. | FAA | [Doc. No. FAA-2006-25877, Amdt. 21-92, 74 FR 53384, Oct. 16, 2009; Doc. No. FAA-2013-0933, Amdt. 21-98, 80 FR 59031, Oct. 1, 2015; Amdt. 21-98A, 80 FR 59031, Dec. 17, 2015; Docket FAA-2015-0150, Amdt. 21-99, 81 FR 42207, June 28, 2016; Docket FAA-2018-1087, Amdt. 21-105, 86 FR 4381, Jan. 15, 2021] | (a) This part prescribes— (1) Procedural requirements for issuing and changing— (i) Design approvals; (ii) Production approvals; (iii) Airworthiness certificates; and (iv) Airworthiness approvals; (2) Rules governing applicants for, and holders of, any approval or certificate specified in paragraph (a)(1) of this section; and (3) Procedural requirements for the approval of articles. (b) For the purposes of this part— (1) Airworthiness approval means a document, issued by the FAA for an aircraft, aircraft engine, propeller, or article, which certifies that the aircraft, aircraft engine, propeller, or article conforms to its approved design and is in a condition for safe operation, unless otherwise specified; (2) Article means a material, part, component, process, or appliance; (3) Commercial part means an article that is listed on an FAA-approved Commercial Parts List included in a design approval holder's Instructions for Continued Airworthiness required by § 21.50; (4) Design approval means a type certificate (including amended and supplemental type certificates) or the approved design under a PMA, TSO authorization, letter of TSO design approval, or other approved design; (5) Interface component means an article that serves as a functional interface between an aircraft and an aircraft engine, an aircraft engine and a propeller, or an aircraft and a propeller. An interface component is designated by the holder of the type certificate or the supplemental type certificate who controls the approved design data for that article; (6) Product means an aircraft, aircraft engine, or propeller; (7) Production approval means a document issued by the FAA to a person that allows the production of a product or article in accordance with its approved design and approved quality system, and can take the form of a production certificate, a PMA, or a TSO authorization; (8) State of Design means the country or jurisdiction having regulatory authority over the organization responsible for the design… | |||
| 14:14:1.0.1.3.10.1.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | A | Subpart A—General | § 21.2 [Reserved] | FAA | |||||
| 14:14:1.0.1.3.10.1.11.3 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | A | Subpart A—General | § 21.3 Reporting of failures, malfunctions, and defects. | FAA | [Amdt. 21-36, 35 FR 18187, Nov. 28, 1970, as amended by Amdt. 21-37, 35 FR 18450, Dec. 4, 1970; Amdt. 21-50, 45 FR 38346, June 9, 1980; Amdt. 21-67, 54 FR 39291, Sept. 25, 1989; Amdt. 21-92, 74 FR 53385, Oct. 16, 2009; Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR 9169, Mar. 5, 2018] | (a) The holder of a type certificate (including amended or supplemental type certificates), a PMA, or a TSO authorization, or the licensee of a type certificate must report any failure, malfunction, or defect in any product or article manufactured by it that it determines has resulted in any of the occurrences listed in paragraph (c) of this section. (b) The holder of a type certificate (including amended or supplemental type certificates), a PMA, or a TSO authorization, or the licensee of a type certificate must report any defect in any product or article manufactured by it that has left its quality system and that it determines could result in any of the occurrences listed in paragraph (c) of this section. (c) The following occurrences must be reported as provided in paragraphs (a) and (b) of this section: (1) Fires caused by a system or equipment failure, malfunction, or defect. (2) An engine exhaust system failure, malfunction, or defect which causes damage to the engine, adjacent aircraft structure, equipment, or components. (3) The accumulation or circulation of toxic or noxious gases in the crew compartment or passenger cabin. (4) A malfunction, failure, or defect of a propeller control system. (5) A propeller or rotorcraft hub or blade structural failure. (6) Flammable fluid leakage in areas where an ignition source normally exists. (7) A brake system failure caused by structural or material failure during operation. (8) A significant aircraft primary structural defect or failure caused by any autogenous condition (fatigue, understrength, corrosion, etc.). (9) Any abnormal vibration or buffeting caused by a structural or system malfunction, defect, or failure. (10) An engine failure. (11) Any structural or flight control system malfunction, defect, or failure which causes an interference with normal control of the aircraft for which derogates the flying qualities. (12) A complete loss of more than one electrical power generating system or hydraulic power system during a given operation of th… | |||
| 14:14:1.0.1.3.10.1.11.4 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | A | Subpart A—General | § 21.4 ETOPS reporting requirements. | FAA | [Doc. No. FAA-2002-6717, 72 FR 1872, Jan. 16, 2007, as amended by Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR 9169, Mar. 5, 2018] | (a) Early ETOPS: reporting, tracking, and resolving problems. The holder of a type certificate for an airplane-engine combination approved using the Early ETOPS method specified in part 25, Appendix K, of this chapter must use a system for reporting, tracking, and resolving each problem resulting in one of the occurrences specified in paragraph (a)(6) of this section. (1) The system must identify how the type certificate holder will promptly identify problems, report them to the responsible Aircraft Certification Service office, and propose a solution to the FAA to resolve each problem. A proposed solution must consist of— (i) A change in the airplane or engine type design; (ii) A change in a manufacturing process; (iii) A change in an operating or maintenance procedure; or (iv) Any other solution acceptable to the FAA. (2) For an airplane with more than two engines, the system must be in place for the first 250,000 world fleet engine-hours for the approved airplane-engine combination. (3) For two-engine airplanes, the system must be in place for the first 250,000 world fleet engine-hours for the approved airplane-engine combination and after that until— (i) The world fleet 12-month rolling average IFSD rate is at or below the rate required by paragraph (b)(2) of this section; and (ii) The FAA determines that the rate is stable. (4) For an airplane-engine combination that is a derivative of an airplane-engine combination previously approved for ETOPS, the system need only address those problems specified in the following table, provided the type certificate holder obtains prior authorization from the FAA: (5) The type certificate holder must identify the sources and content of data that it will use for its system. The data must be adequate to evaluate the specific cause of any in-service problem reportable under this section or § 21.3(c) that could affect the safety of ETOPS. (6) In implementing this system, the type certificate holder must report the following occurrences: (i) IFSDs, except planne… | |||
| 14:14:1.0.1.3.10.1.11.5 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | A | Subpart A—General | § 21.5 Airplane or Rotorcraft Flight Manual. | FAA | [Amdt. 21-46, 43 FR 2316, Jan. 16, 1978, as amended by Amdt. 21-92, 74 FR 53385, Oct. 16, 2009; Admt. 21-107, 89 FR 12653, Feb. 16, 2024] | (a) With each airplane or rotorcraft not type certificated with an Airplane or Rotorcraft Flight Manual and having no flight time before March 1, 1979, the holder of a type certificate (including amended or supplemental type certificates) or the licensee of a type certificate must make available to the owner at the time of delivery of the aircraft a current approved Airplane or Rotorcraft Flight Manual. (b) The Airplane or Rotorcraft Flight Manual required by paragraph (a) of this section must contain the following information: (1) The operating limitations and information required to be furnished in an Airplane or Rotorcraft Flight Manual or in manual material, markings, and placards, by the applicable regulations under which the airplane or rotorcraft was type certificated. (2) The maximum ambient atmospheric temperature for which engine cooling was demonstrated must be stated in the performance information section of the Flight Manual, if the applicable regulations under which the aircraft was type certificated do not require ambient temperature on engine cooling operating limitations in the Flight Manual. (3) Documentation of compliance with part 38 of this chapter, in an FAA-approved section of any approved airplane flight manual. Such material must include the fuel efficiency metric value as calculated under § 38.11 of this chapter, and the specific paragraph of § 38.17 of this chapter with which compliance has been shown for that airplane. | |||
| 14:14:1.0.1.3.10.1.11.6 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | A | Subpart A—General | § 21.6 Manufacture of new aircraft, aircraft engines, and propellers. | FAA | [Doc. No. FAA-2003-14825, 71 FR 52258, Sept. 1, 2006] | (a) Except as specified in paragraphs (b) and (c) of this section, no person may manufacture a new aircraft, aircraft engine, or propeller based on a type certificate unless the person— (1) Is the holder of the type certificate or has a licensing agreement from the holder of the type certificate to manufacture the product; and (2) Meets the requirements of subpart F or G of this part. (b) A person may manufacture one new aircraft based on a type certificate without meeting the requirements of paragraph (a) of this section if that person can provide evidence acceptable to the FAA that the manufacture of the aircraft by that person began before August 5, 2004. (c) The requirements of this section do not apply to— (1) New aircraft imported under the provisions of §§ 21.183(c), 21.184(b), or 21.185(c); and (2) New aircraft engines or propellers imported under the provisions of § 21.500. | |||
| 14:14:1.0.1.3.10.1.11.7 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | A | Subpart A—General | § 21.7 Continued airworthiness and safety improvements for transport category airplanes. | FAA | [Doc. No. FAA-2004-18379, Amdt. 21-90, 72 FR 63404, Nov. 8, 2007] | (a) On or after December 10, 2007, the holder of a design approval and an applicant for a design approval must comply with the applicable continued airworthiness and safety improvement requirements of part 26 of this subchapter. (b) For new transport category airplanes manufactured under the authority of the FAA, the holder or licensee of a type certificate must meet the applicable continued airworthiness and safety improvement requirements specified in part 26 of this subchapter for new production airplanes. Those requirements only apply if the FAA has jurisdiction over the organization responsible for final assembly of the airplane. | |||
| 14:14:1.0.1.3.10.1.11.8 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | A | Subpart A—General | § 21.8 Approval of articles. | FAA | [Doc. No. FAA-2006-5877, Amdt. 21-92, 74 FR 53385, Oct. 16, 2009] | If an article is required to be approved under this chapter, it may be approved— (a) Under a PMA; (b) Under a TSO; (c) In conjunction with type certification procedures for a product; or (d) In any other manner approved by the FAA. | |||
| 14:14:1.0.1.3.10.1.11.9 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | A | Subpart A—General | § 21.9 Replacement and modification articles. | FAA | [Doc. No. FAA-2006-25877, Amdt. 21-92, 74 FR 53385, Oct. 16, 2009; Amdt. 21-92A, 75 FR 9095, Mar. 1, 2010; Doc. No. FAA-2015-1621, Amdt. 21-100, 81 FR 96688, Dec. 30, 2016] | (a) If a person knows, or should know, that a replacement or modification article is reasonably likely to be installed on a type-certificated product, the person may not produce that article unless it is— (1) Produced under a type certificate; (2) Produced under an FAA production approval; (3) A standard part (such as a nut or bolt) manufactured in compliance with a government or established industry specification; (4) A commercial part as defined in § 21.1 of this part; (5) Produced by an owner or operator for maintaining or altering that owner or operator's product; (6) Fabricated by an appropriately rated certificate holder with a quality system, and consumed in the repair or alteration of a product or article in accordance with part 43 of this chapter; or (7) Produced in any other manner approved by the FAA. (b) Except as provided in paragraphs (a)(1) through (a)(2) of this section, a person who produces a replacement or modification article for sale may not represent that part as suitable for installation on a type-certificated product. (c) Except as provided in paragraphs (a)(1) through (a)(2) of this section, a person may not sell or represent an article as suitable for installation on an aircraft type-certificated under §§ 21.25(a)(2) or 21.27 unless that article— (1) Was declared surplus by the U.S. Armed Forces, and (2) Was intended for use on that aircraft model by the U.S. Armed Forces. | |||
| 14:14:1.0.1.3.10.11.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.301 Applicability. | FAA | This subpart prescribes— (a) Procedural requirements for issuing PMAs; and (b) Rules governing holders of PMAs. | ||||
| 14:14:1.0.1.3.10.11.11.10 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.314 Transferability. | FAA | The holder of a PMA may not transfer the PMA. | ||||
| 14:14:1.0.1.3.10.11.11.11 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.316 Responsibility of holder. | FAA | Each holder of a PMA must— (a) Amend the document required by § 21.305 as necessary to reflect changes in the organization and provide these amendments to the FAA; (b) Maintain the quality system in compliance with the data and procedures approved for the PMA; (c) Ensure that each PMA article conforms to its approved design and is in a condition for safe operation; (d) Mark the PMA article for which an approval has been issued. Marking must be in accordance with part 45 of this chapter, including any critical parts; (e) Identify any portion of the PMA article ( e.g., sub-assemblies, component parts, or replacement articles) that leave the manufacturer's facility as FAA approved with the manufacturer's part number and name, trademark, symbol, or other FAA approved manufacturer's identification; (f) Have access to design data necessary to determine conformity and airworthiness for each article produced under the PMA; (g) Retain each document granting PMA and make it available to the FAA upon request; and (h) Make available to the FAA information regarding all delegation of authority to suppliers. | ||||
| 14:14:1.0.1.3.10.11.11.12 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.319 Design changes. | FAA | (a) Classification of design changes. (1) A “minor change” to the design of an article produced under a PMA is one that has no appreciable effect on the approval basis. (2) A “major change” to the design of an article produced under a PMA is any change that is not minor. (b) Approval of design changes. (1) Minor changes to the basic design of a PMA may be approved using a method acceptable to the FAA. (2) The PMA holder must obtain FAA approval of any major change before including it in the design of an article produced under a PMA. | ||||
| 14:14:1.0.1.3.10.11.11.13 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.320 Changes in quality system. | FAA | After the issuance of a PMA— (a) Each change to the quality system is subject to review by the FAA; and (b) The holder of the PMA must immediately notify the FAA, in writing, of any change that may affect the inspection, conformity, or airworthiness of its article. | ||||
| 14:14:1.0.1.3.10.11.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.303 Application. | FAA | (a) The applicant for a PMA must apply in a form and manner prescribed by the FAA, and include the following: (1) The identity of the product on which the article is to be installed. (2) The name and address of the manufacturing facilities at which these articles are to be manufactured. (3) The design of the article, which consists of— (i) Drawings and specifications necessary to show the configuration of the article; and (ii) Information on dimensions, materials, and processes necessary to define the structural strength of the article. (4) Test reports and computations necessary to show that the design of the article meets the airworthiness requirements of this subchapter. The test reports and computations must be applicable to the product on which the article is to be installed, unless the applicant shows that the design of the article is identical to the design of a article that is covered under a type certificate. If the design of the article was obtained by a licensing agreement, the applicant must provide evidence of that agreement. (5) An applicant for a PMA based on test reports and computations must provide a statement certifying that the applicant has complied with the airworthiness requirements of this subchapter. (b) Each applicant for a PMA must make all inspections and tests necessary to determine— (1) Compliance with the applicable airworthiness requirements; (2) That materials conform to the specifications in the design; (3) That the article conforms to its approved design; and (4) That the manufacturing processes, construction, and assembly conform to those specified in the design. | ||||
| 14:14:1.0.1.3.10.11.11.3 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.305 Organization. | FAA | [Doc. No. FAA-2013-0933, Amdt. 21-98, 80 FR 59031, Oct. 1, 2015] | (a) Each applicant for or holder of a PMA must provide the FAA with a document— (1) Describing how its organization will ensure compliance with the provisions of this subpart; (2) Describing assigned responsibilities, delegated authorities, and the functional relationship of those responsible for quality to management and other organizational components; and (3) Identifying an accountable manager. (b) The accountable manager specified in paragraph (a) of this section must be responsible within the applicant's or production approval holder's organization for, and have authority over, all production operations conducted under this part. The accountable manager must confirm that the procedures described in the quality manual required by § 21.308 are in place and that the production approval holder satisfies the requirements of the applicable regulations of subchapter C, Aircraft. The accountable manager must serve as the primary contact with the FAA. | |||
| 14:14:1.0.1.3.10.11.11.4 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.307 Quality system. | FAA | Each applicant for or holder of a PMA must establish a quality system that meets the requirements of § 21.137. | ||||
| 14:14:1.0.1.3.10.11.11.5 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.308 Quality manual. | FAA | Each applicant for or holder of a PMA must provide a manual describing its quality system to the FAA for approval. The manual must be in the English language and retrievable in a form acceptable to the FAA. | ||||
| 14:14:1.0.1.3.10.11.11.6 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.309 Location of or change to manufacturing facilities. | FAA | (a) An applicant may obtain a PMA for manufacturing facilities located outside of the United States if the FAA finds no undue burden in administering the applicable requirements of Title 49 U.S.C. and this subchapter. (b) The PMA holder must obtain FAA approval before making any changes to the location of any of its manufacturing facilities. (c) The PMA holder must immediately notify the FAA, in writing, of any change to the manufacturing facilities that may affect the inspection, conformity, or airworthiness of its PMA article. | ||||
| 14:14:1.0.1.3.10.11.11.7 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.310 Inspections and tests. | FAA | (a) Each applicant for or holder of a PMA must allow the FAA to inspect its quality system, facilities, technical data, and any manufactured articles and witness any tests, including any inspections or tests at a supplier facility, necessary to determine compliance with this subchapter. (b) Unless otherwise authorized by the FAA, the applicant or holder— (1) May not present any article to the FAA for an inspection or test unless compliance with § 21.303(b)(2) through (4) has been shown for that article; and (2) May not make any change to an article between the time that compliance with § 21.303(b)(2) through (4) is shown for that article and the time that the article is presented to the FAA for the inspection or test. | ||||
| 14:14:1.0.1.3.10.11.11.8 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.311 Issuance. | FAA | The FAA issues a PMA after finding that the applicant complies with the requirements of this subpart and the design complies with the requirements of this chapter applicable to the product on which the article is to be installed. | ||||
| 14:14:1.0.1.3.10.11.11.9 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | K | Subpart K—Parts Manufacturer Approvals | § 21.313 Duration. | FAA | A PMA is effective until surrendered, withdrawn, or the FAA otherwise terminates it. | ||||
| 14:14:1.0.1.3.10.12.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | L | Subpart L—Export Airworthiness Approvals | § 21.321 Applicability. | FAA | This subpart prescribes— (a) Procedural requirements for issuing export airworthiness approvals; and (b) Rules governing the holders of those approvals. | ||||
| 14:14:1.0.1.3.10.12.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | L | Subpart L—Export Airworthiness Approvals | § 21.325 Export airworthiness approvals. | FAA | (a) An export airworthiness approval for an aircraft is issued in the form of an export certificate of airworthiness. This certificate does not authorize operation of that aircraft. (b) The FAA prescribes the form and manner in which an export airworthiness approval for an aircraft engine, propeller, or article is issued. (c) If the FAA finds no undue burden in administering the applicable requirements of Title 49 U.S.C. and this subchapter, an export airworthiness approval may be issued for a product or article located outside of the United States. | ||||
| 14:14:1.0.1.3.10.12.11.3 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | L | Subpart L—Export Airworthiness Approvals | § 21.327 Application. | FAA | [Docket No. FAA-2023-1377, Amdt. 21-109, 90 FR 35208, July 24, 2025] | (a) Any owner of a U.S.-registered aircraft (or the agent of the owner) may apply for an export certificate of airworthiness for that aircraft. (b) Any person may apply for an export airworthiness approval for an aircraft engine, propeller, or article. (c) Each applicant must apply in a form and manner prescribed by the FAA. | |||
| 14:14:1.0.1.3.10.12.11.4 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | L | Subpart L—Export Airworthiness Approvals | § 21.329 Issuance of export certificates of airworthiness. | FAA | [Docket No. FAA-2006-25877, Amdt. 21-92, 74 FR 53391, Oct. 16, 2009, as amended by Amdt. 21-109, 90 FR 35208, July 24, 2025] | (a) A person may obtain from the FAA an export certificate of airworthiness for an aircraft if— (1) A new or used aircraft manufactured under subpart F or G of this part meets the requirements under subpart H of this part for a— (i) Standard airworthiness certificate; or (ii) Special airworthiness certificate in either the “primary” or the “restricted” category; or (2) A new or used aircraft not manufactured under subpart F or G of this part has a valid— (i) Standard airworthiness certificate; or (ii) Special airworthiness certificate in either the “primary” or the “restricted” category. (b) An aircraft need not meet a requirement specified in paragraph (a) of this section, as applicable, if— (1) The importing country or jurisdiction accepts, in a form and manner acceptable to the FAA, a deviation from that requirement; and (2) The export certificate of airworthiness lists as an exception any difference between the aircraft to be exported and its type design. | |||
| 14:14:1.0.1.3.10.12.11.5 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | L | Subpart L—Export Airworthiness Approvals | § 21.331 Issuance of export airworthiness approvals for aircraft engines, propellers, and articles. | FAA | (a) A person may obtain from the FAA an export airworthiness approval to export a new aircraft engine, propeller, or article that is manufactured under this part if it conforms to its approved design and is in a condition for safe operation. (b) A new aircraft engine, propeller, or article need not meet a requirement of paragraph (a) of this section if— (1) The importing country or jurisdiction accepts, in a form and manner acceptable to the FAA, a deviation from that requirement; and (2) The export airworthiness approval lists as an exception any difference between the aircraft engine, propeller, or article to be exported and its approved design. (c) A person may obtain from the FAA an export airworthiness approval to export a used aircraft engine, propeller, or article if it conforms to its approved design and is in a condition for safe operation. (d) A used aircraft engine or propeller need not meet a requirement of paragraph (c) of this section if— (1) The importing country or jurisdiction accepts, in a form and manner acceptable to the FAA, a deviation from that requirement; and (2) The export airworthiness approval lists as an exception any difference between the used aircraft engine or propeller to be exported and its approved design. | ||||
| 14:14:1.0.1.3.10.12.11.6 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | L | Subpart L—Export Airworthiness Approvals | § 21.335 Responsibilities of exporters. | FAA | Unless otherwise agreed to by the importing country or jurisdiction, each exporter must— (a) Forward to the importing country or jurisdiction all documents specified by that country or jurisdiction; (b) Preserve and package products and articles as necessary to protect them against corrosion and damage during transit or storage and state the duration of effectiveness of such preservation and packaging; (c) Remove or cause to be removed any temporary installation incorporated on an aircraft for the purpose of export delivery and restore the aircraft to the approved configuration upon completion of the delivery flight; (d) Secure all proper foreign entry clearances from all the countries or jurisdictions involved when conducting sales demonstrations or delivery flights; and (e) When title to an aircraft passes or has passed to a foreign purchaser— (1) Request cancellation of the U.S. registration and airworthiness certificates from the FAA, giving the date of transfer of title, and the name and address of the foreign owner; (2) Return the Registration and Airworthiness Certificates to the FAA; and (3) Provide a statement to the FAA certifying that the U.S. identification and registration numbers have been removed from the aircraft in compliance with § 45.33. | ||||
| 14:14:1.0.1.3.10.14.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | N | Subpart N—Acceptance of Aircraft Engines, Propellers, and Articles for Import | § 21.500 Acceptance of aircraft engines and propellers. | FAA | An aircraft engine or propeller manufactured in a foreign country or jurisdiction meets the requirements for acceptance under this subchapter if— (a) That country or jurisdiction is subject to the provisions of an agreement with the United States for the acceptance of that product; (b) That product is marked in accordance with part 45 of this chapter; and (c) The holder or licensee of a U.S. type certificate for that product furnishes with each such aircraft engine or propeller imported into the United States, an export airworthiness approval issued in accordance with the provisions of that agreement certifying that the individual aircraft engine or propeller— (1) Conforms to its U.S. type certificate and is in condition for safe operation; and (2) Has been subjected by the manufacturer to a final operational check. | ||||
| 14:14:1.0.1.3.10.14.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | N | Subpart N—Acceptance of Aircraft Engines, Propellers, and Articles for Import | § 21.502 Acceptance of articles. | FAA | An article (including an article produced under a letter of TSO design approval) manufactured in a foreign country or jurisdiction meets the requirements for acceptance under this subchapter if— (a) That country or jurisdiction is subject to the provisions of an agreement with the United States for the acceptance of that article; (b) That article is marked in accordance with part 45 of this chapter; and (c) An export airworthiness approval has been issued in accordance with the provisions of that agreement for that article for import into the United States. | ||||
| 14:14:1.0.1.3.10.15.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.601 Applicability and definitions. | FAA | (a) This subpart prescribes— (1) Procedural requirements for issuing TSO authorizations; (2) Rules governing the holders of TSO authorizations; and (3) Procedural requirements for issuing letters of TSO design approval. (b) For the purposes of this subpart— (1) A TSO issued by the FAA is a minimum performance standard for specified articles used on civil aircraft; (2) A TSO authorization is an FAA design and production approval issued to the manufacturer of an article that has been found to meet a specific TSO; (3) A letter of TSO design approval is an FAA design approval for an article that has been found to meet a specific TSO in accordance with the procedures of § 21.621; (4) An article manufactured under a TSO authorization, an FAA letter of acceptance as described in § 21.613(b), or an article manufactured under a letter of TSO design approval described in § 21.621 is an approved article for the purpose of meeting the regulations of this chapter that require the article to be approved; and (5) An article manufacturer is the person who controls the design and quality of the article produced (or to be produced, in the case of an application), including any related parts, processes, or services procured from an outside source. | ||||
| 14:14:1.0.1.3.10.15.11.10 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.614 Transferability. | FAA | The holder of a TSO authorization or letter of TSO design approval may not transfer the TSO authorization or letter of TSO design approval. | ||||
| 14:14:1.0.1.3.10.15.11.11 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.616 Responsibility of holder. | FAA | Each holder of a TSO authorization must— (a) Amend the document required by § 21.605 as necessary to reflect changes in the organization and provide these amendments to the FAA. (b) Maintain a quality system in compliance with the data and procedures approved for the TSO authorization; (c) Ensure that each manufactured article conforms to its approved design, is in a condition for safe operation, and meets the applicable TSO; (d) Mark the TSO article for which an approval has been issued. Marking must be in accordance with part 45 of this chapter, including any critical parts; (e) Identify any portion of the TSO article (e.g., sub-assemblies, component parts, or replacement articles) that leave the manufacturer's facility as FAA approved with the manufacturer's part number and name, trademark, symbol, or other FAA approved manufacturer's identification; (f) Have access to design data necessary to determine conformity and airworthiness for each article produced under the TSO authorization. The manufacturer must retain this data until it no longer manufactures the article. At that time, copies of the data must be sent to the FAA; (g) Retain its TSO authorization and make it available to the FAA upon request; and (h) Make available to the FAA information regarding all delegation of authority to suppliers. | ||||
| 14:14:1.0.1.3.10.15.11.12 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.618 Approval for deviation. | FAA | [Docket No. FAA-2006-25877, Amdt. 21-92, 74 FR 53392, Oct. 16, 2009, as amended by Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR 9169, Mar. 5, 2018] | (a) Each manufacturer who requests approval to deviate from any performance standard of a TSO must show that factors or design features providing an equivalent level of safety compensate for the standards from which a deviation is requested. (b) The manufacturer must send requests for approval to deviate, together with all pertinent data, to the FAA. If the article is manufactured under the authority of a foreign country or jurisdiction, the manufacturer must send requests for approval to deviate, together with all pertinent data, through the civil aviation authority of that country or jurisdiction to the FAA. | |||
| 14:14:1.0.1.3.10.15.11.13 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.619 Design changes. | FAA | [Docket No. FAA-2006-25877, Amdt. 21-92, 74 FR 53392, Oct. 16, 2009, as amended by Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR 9169, Mar. 5, 2018; Doc. No. FAA-2022-1355, Amdt. 21-106, 87 FR 75710, Dec. 9, 2022] | (a) Minor changes by the manufacturer holding a TSO authorization. The manufacturer of an article under an authorization issued under this part may make minor design changes (any change other than a major change) without further approval by the FAA. In this case, the changed article keeps the original model number (part numbers may be used to identify minor changes) and the manufacturer must forward to the FAA, any revised data that are necessary for compliance with § 21.603(a). (b) Major changes by the manufacturer holding a TSO authorization. Any design change by the manufacturer extensive enough to require a substantially complete investigation to determine compliance with a TSO is a major change. Before making a major change, the manufacturer must assign a new type or model designation to the article and apply for an authorization under § 21.603. (c) Changes by persons other than the manufacturer. No design change by any person (other than the manufacturer who provided the statement of conformance for the article) is eligible for approval under this part unless the person seeking the approval is a manufacturer and applies under § 21.603(a) for a separate TSO authorization. Persons other than a manufacturer may obtain approval for design changes under part 43 or under the applicable airworthiness regulations of this chapter. | |||
| 14:14:1.0.1.3.10.15.11.14 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.620 Changes in quality system. | FAA | After the issuance of a TSO authorization— (a) Each change to the quality system is subject to review by the FAA; and (b) The holder of the TSO authorization must immediately notify the FAA, in writing, of any change that may affect the inspection, conformity, or airworthiness of its article. | ||||
| 14:14:1.0.1.3.10.15.11.15 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.621 Issue of letters of TSO design approval: Import articles. | FAA | [Doc. No. FAA-2006-25877, Amdt. 21-92, 74 FR 53392, Oct. 16, 2009, as amended by Amdt. 21-92A, 75 FR 9095, Mar. 1, 2010] | (a) The FAA may issue a letter of TSO design approval for an article— (1) Designed and manufactured in a foreign country or jurisdiction subject to the export provisions of an agreement with the United States for the acceptance of these articles for import; and (2) For import into the United States if— (i) The State of Design certifies that the article has been examined, tested, and found to meet the applicable TSO or the applicable performance standards of the State of Design and any other performance standards the FAA may prescribe to provide a level of safety equivalent to that provided by the TSO; and (ii) The manufacturer has provided to the FAA one copy of the technical data required in the applicable performance standard through its State of Design. (b) The FAA issues the letter of TSO design approval that lists any deviation granted under § 21.618. | |||
| 14:14:1.0.1.3.10.15.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.603 Application. | FAA | [Docket No. FAA-2006-25877, Amdt. 21-92, 74 FR 53392, Oct. 16, 2009, as amended by Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR 9169, Mar. 5, 2018] | (a) An applicant for a TSO authorization must apply in the form and manner prescribed by the FAA. The applicant must include the following documents in the application: (1) A statement of conformance certifying that the applicant has met the requirements of this subpart and that the article concerned meets the applicable TSO that is effective on the date of application for that article. (2) One copy of the technical data required in the applicable TSO. (b) If the applicant anticipates a series of minor changes in accordance with § 21.619, the applicant may set forth in its application the basic model number of the article and the part number of the components with open brackets after it to denote that suffix change letters or numbers (or combinations of them) will be added from time to time. (c) If the application is deficient, the applicant must, when requested by the FAA, provide any additional information necessary to show compliance with this part. If the applicant fails to provide the additional information within 30 days after the FAA's request, the FAA denies the application and notifies the applicant. | |||
| 14:14:1.0.1.3.10.15.11.3 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.605 Organization. | FAA | [Doc. No. FAA-2013-0933, Amdt. 21-98, 80 FR 59032, Oct. 1, 2015] | (a) Each applicant for or holder of a TSO authorization must provide the FAA with a document— (1) Describing how its organization will ensure compliance with the provisions of this subpart; (2) Describing assigned responsibilities, delegated authorities, and the functional relationship of those responsible for quality to management and other organizational components; and (3) Identifying an accountable manager. (b) The accountable manager specified in paragraph (a) of this section must be responsible within the applicant's or production approval holder's organization for, and have authority over, all production operations conducted under this part. The accountable manager must confirm that the procedures described in the quality manual required by § 21.608 are in place and that the production approval holder satisfies the requirements of the applicable regulations of subchapter C, Aircraft. The accountable manager must serve as the primary contact with the FAA. | |||
| 14:14:1.0.1.3.10.15.11.4 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.607 Quality system. | FAA | Each applicant for or holder of a TSO authorization must establish a quality system that meets the requirements of § 21.137. | ||||
| 14:14:1.0.1.3.10.15.11.5 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.608 Quality manual. | FAA | Each applicant for or holder of a TSO authorization must provide a manual describing its quality system to the FAA for approval. The manual must be in the English language and retrievable in a form acceptable to the FAA. | ||||
| 14:14:1.0.1.3.10.15.11.6 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.609 Location of or change to manufacturing facilities. | FAA | (a) An applicant may obtain a TSO authorization for manufacturing facilities located outside of the United States if the FAA finds no undue burden in administering the applicable requirements of Title 49 U.S.C. and this subchapter. (b) The TSO authorization holder must obtain FAA approval before making any changes to the location of any of its manufacturing facilities. (c) The TSO authorization holder must immediately notify the FAA, in writing, of any change to the manufacturing facilities that may affect the inspection, conformity, or airworthiness of its product or article. | ||||
| 14:14:1.0.1.3.10.15.11.7 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.610 Inspections and tests. | FAA | Each applicant for or holder of a TSO authorization must allow the FAA to inspect its quality system, facilities, technical data, and any manufactured articles and witness any tests, including any inspections or tests at a supplier facility, necessary to determine compliance with this subchapter. | ||||
| 14:14:1.0.1.3.10.15.11.8 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.611 Issuance. | FAA | If the FAA finds that the applicant complies with the requirements of this subchapter, the FAA issues a TSO authorization to the applicant (including all TSO deviations granted to the applicant). | ||||
| 14:14:1.0.1.3.10.15.11.9 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | O | Subpart O—Technical Standard Order Approvals | § 21.613 Duration. | FAA | (a) A TSO authorization or letter of TSO design approval is effective until surrendered, withdrawn, or otherwise terminated by the FAA. (b) If a TSO is revised or canceled, the holder of an affected FAA letter of acceptance of a statement of conformance, TSO authorization, or letter of TSO design approval may continue to manufacture articles that meet the original TSO without obtaining a new acceptance, authorization, or approval but must comply with the requirements of this chapter. | ||||
| 14:14:1.0.1.3.10.16.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | P | Subpart P—Special Federal Aviation Regulations | § 21.700 SFAR No. 111—Lavatory Oxygen Systems. | FAA | The requirements of § 121.1500 of this chapter also apply to this part. | ||||
| 14:14:1.0.1.3.10.2.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.11 Applicability. | FAA | 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. | ||||
| 14:14:1.0.1.3.10.2.11.10 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.24 Issuance of type certificate: primary category aircraft. | FAA | [Doc. No. 23345, 57 FR 41367, Sept. 9, 1992, as amended by Amdt. 21-75, 62 FR 62808, Nov. 25, 1997; Doc. No. FAA-2015-1621, Amdt. 21-100, 81 FR 96689, Dec. 30, 2016] | (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 V so stall speed as determined under part 23 of this chapter; 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 FAA, 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 FAA finds… | |||
| 14:14:1.0.1.3.10.2.11.11 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.25 Issue of type certificate: restricted category aircraft. | FAA | [Docket No. FAA-2023-1377, Amdt. No. 21-109, 90 FR 35204, July 24, 2025] | (a) An applicant is entitled to a type certificate for an aircraft in the restricted category for special purpose operations if the applicant shows compliance with the applicable noise requirements of part 36 of this chapter, and if the applicant 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 aircraft— (1) Meets the airworthiness requirements of an aircraft category, other than primary category or light-sport category, except those requirements that the FAA finds inappropriate for the special purpose operation for which the aircraft is to be used; or (2) Is of a type that— (i) Has been manufactured in accordance with the requirements of, and accepted for use by, the U.S. Armed Forces; (ii) Has a service history with the U.S. Armed Forces acceptable to the FAA; and (iii) Has been found capable by the FAA of performing, or has been modified to perform, the special purpose operation for which the aircraft is to be used. (b) Restricted category aircraft can be approved for: (1) Agricultural use, for one or more of the following special purpose operations, including— (i) Spraying, dusting, and seeding; (ii) Livestock and predatory animal control; (iii) Insect control; (iv) Dust control; or (v) Fruit drying and frost control. (2) Forest and wildlife conservation, for one or more of the following special purpose operations, including— (i) Aerial dispensing of firefighting materials; (ii) Fish spotting; (iii) Wild animal survey; or (iv) Oil spill response. (3) Aerial surveying, for one or more of the following special purpose operations, including— (i) Aerial imaging and mapping; (ii) Oil, gas, and mineral exploration; (iii) Atmospheric survey and research; (iv) Geophysical and electromagnetic survey; (v) Oceanic survey; or (vi) Airborne measurement of navigation signals. (4) Patrolling, for one or more of the following special purpose operations, including— (i) Pipelines; (ii) Powerline… | |||
| 14:14:1.0.1.3.10.2.11.12 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.27 Issue of type certificate: surplus aircraft of the Armed Forces. | FAA | [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] | (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 this subchapter. (d) The FAA may relieve an applicant from strict compliance with a specific provision of the applicable requirements in paragraph (f) of this section, if the FAA 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 FAA may use experience that was satisfactory to an Armed Force of the United States in making such a determination. (e) The FAA may require an applicant to comply with special conditions and later requirements than those in paragraphs (c) and (f) of this section, if the FAA finds that compliance with the listed regulations would not ensure an adequate level of airworthiness for the aircraft. (f) Except as provided in paragrap… | |||
| 14:14:1.0.1.3.10.2.11.13 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.29 Issue of type certificate: import products. | FAA | [Amdt. 21-92, 74 FR 53386, Oct. 16, 2009, as amended by Amdt. No. 21-107, 89 FR 12653, Feb. 16, 2024] | (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, exhaust emissions, and fuel efficiency requirements of this subchapter as designated in § 21.17, or the applicable aircraft noise, fuel venting, exhaust emissions, and fuel efficiency requirements of the State of Design, and any other requirements the FAA may prescribe to provide noise, fuel venting, exhaust emission, and fuel efficiency levels no greater than those provided by the applicable aircraft noise, fuel venting, exhaust emissions, and fuel efficiency 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 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 § 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 determined to be compliant with the fuel venting and exhaust emission standards of part 34 of this subchapter, the noise standards of part 36 of this subchapter, and the fuel efficiency requirements of part 38 of this subchapter. Compliance with parts 34, 36, and 38 of this subchapter is certified under paragraph (a)(1)(i) of this section, and the applicable a… | |||
| 14:14:1.0.1.3.10.2.11.14 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.31 Type design. | FAA | [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; Amdt. No. 21-107, 89 FR 12653, Feb. 16, 2024] | 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 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 efficiency, fuel venting, and exhaust emissions (where applicable) of later products of the same type. | |||
| 14:14:1.0.1.3.10.2.11.15 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.33 Inspection and tests. | FAA | [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] | (a) Each applicant must allow the FAA to make any inspection and any flight and ground test necessary to determine compliance with the applicable requirements of this subchapter. However, unless otherwise authorized by the FAA— (1) No aircraft, aircraft engine, propeller, or part thereof may be presented to the FAA 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 FAA 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. | |||
| 14:14:1.0.1.3.10.2.11.16 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.35 Flight tests. | FAA | [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; Amdt. 21-95, 76 FR 64233, Oct. 18, 2011; Doc. No. FAA-2015-1621, Amdt. 21-100, 81 FR 96689, Dec. 30, 2016] | (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 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 applicant must make all flight tests that the FAA 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 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 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 me… | |||
| 14:14:1.0.1.3.10.2.11.17 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.37 Flight test pilot. | FAA | [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987] | 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. | |||
| 14:14:1.0.1.3.10.2.11.18 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.39 Flight test instrument calibration and correction report. | FAA | [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-59, 52 FR 1835, Jan. 15, 1987] | (a) Each applicant for a normal, utility, acrobatic, commuter, or transport category aircraft type certificate must submit a report to the FAA 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 FAA to conduct any flight tests that he finds necessary to check the accuracy of the report submitted under paragraph (a) of this section. | |||
| 14:14:1.0.1.3.10.2.11.19 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.41 Type certificate. | FAA | 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 FAA records compliance, and any other conditions or limitations prescribed for the product in this subchapter. | ||||
| 14:14:1.0.1.3.10.2.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.13 Eligibility. | FAA | [Amdt. 21-25, 34 FR 14068, Sept. 5, 1969] | Any interested person may apply for a type certificate. | |||
| 14:14:1.0.1.3.10.2.11.20 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.43 Location of manufacturing facilities. | FAA | Except as provided in § 21.29, the FAA does not issue a type certificate if the manufacturing facilities for the product are located outside of the United States, unless the FAA finds that the location of the manufacturer's facilities places no undue burden on the FAA in administering applicable airworthiness requirements. | ||||
| 14:14:1.0.1.3.10.2.11.21 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.45 Privileges. | FAA | [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Amdt. 21-92, 74 FR 53386, Oct. 16, 2009] | 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 on certificated aircraft; (c) In the case of any product, upon compliance with subpart G of this part, obtain a production certificate for the type certificated product; (d) Obtain approval of replacement parts for that product. | |||
| 14:14:1.0.1.3.10.2.11.22 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.47 Transferability. | FAA | [Doc. No. FAA-2006-25877, Amdt. 21-92, 74 FR 53386, Oct. 16, 2009; Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR 9169, Mar. 5, 2018] | (a) A holder of a type certificate may transfer it or make it available to other persons by licensing agreements. (b) For a type certificate transfer in which the State of Design will remain the same, each transferor must, before such a transfer, notify the FAA in writing. This notification must include the applicable type certificate number, the name and address of the transferee, and the anticipated date of the transfer. (c) For a type certificate transfer in which the State of Design is changing, a type certificate may only be transferred to or from a person subject to the authority of another State of Design if the United States has an agreement with that State of Design for the acceptance of the affected product for export and import. Each transferor must notify the FAA before such a transfer in a form and manner acceptable to the FAA. This notification must include the applicable type certificate number; the name, address, and country of residence of the transferee; and the anticipated date of the transfer. (d) Before executing or terminating a licensing agreement that makes a type certificate available to another person, the type certificate holder must notify the FAA in writing. This notification must include the type certificate number addressed by the licensing agreement, the name and address of the licensee, the extent of authority granted the licensee, and the anticipated date of the agreement. | |||
| 14:14:1.0.1.3.10.2.11.23 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.49 Availability. | FAA | [Doc. No. 5085, 29 FR 14564, Oct. 24, 1964, as amended by Doc. No. 8084, 32 FR 5769, Apr. 11, 1967] | The holder of a type certificate must make the certificate available for examination upon the request of the FAA or the National Transportation Safety Board. | |||
| 14:14:1.0.1.3.10.2.11.24 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.50 Instructions for continued airworthiness and manufacturer's maintenance manuals having airworthiness limitations sections. | FAA | [Amdt. 21-23, 33 FR 14105, Sept. 18, 1968, as amended by Amdt. 21-51, 45 FR 60170, Sept. 11, 1980; Amdt. 21-60, 52 FR 8042, Mar. 13, 1987; Amdt. 21-90, 72 FR 63404, Nov. 8, 2007; Amdt. 21-92, 74 FR 53386, Oct. 16, 2009; Doc. No. FAA-2015-1621, Amdt. 21-100, 81 FR 96689, Dec. 30, 2016] | (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, must make those changes available upon request to any operator of the same type of rotorcraft. (b) The holder of a design approval, including either a type certificate or supplemental type certificate for an aircraft, aircraft engine, or propeller for which application was made after January 28, 1981, must furnish at least one set of complete Instructions for Continued Airworthiness to the owner of each type aircraft, aircraft engine, or propeller upon its delivery, or upon issuance of the first standard airworthiness certificate for the affected aircraft, whichever occurs later. The Instructions for Continued Airworthiness must be prepared in accordance with §§ 23.1529, 25.1529, 25.1729, 27.1529, 29.1529, 31.82, 33.4, 35.4, or part 26 of this subchapter, or as specified in the applicable airworthiness criteria for special classes of aircraft defined in § 21.17(b), as applicable. If the holder of a design approval chooses to designate parts as commercial, it must include in the Instructions for Continued Airworthiness a list of commercial parts submitted in accordance with the provisions of paragraph (c) of this section. Thereafter, the holder of a design approval must make those instructions available to any other person required by this chapter to comply with any of the terms of those 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. (c) To designate commercial parts, the holder of a design approval, in a manner acceptable to the FAA, must submit: (1) A Commercial Parts List; (2) Data for each part on the List showing that… | |||
| 14:14:1.0.1.3.10.2.11.25 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.51 Duration. | FAA | A type certificate is effective until surrendered, suspended, revoked, or a termination date is otherwise established by the FAA. | ||||
| 14:14:1.0.1.3.10.2.11.26 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.53 Statement of conformity. | FAA | [Amdt. 21-17, 32 FR 14926, Oct. 28, 1967, as amended by Amdt. 21-92, 74 FR 53386, Oct. 16, 2009] | (a) Each applicant must provide, in a form and manner acceptable to the FAA, a statement that each aircraft engine or propeller presented for type certification conforms to its type design. (b) Each applicant must submit a statement of conformity to the FAA for each aircraft or part thereof presented to the FAA 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). | |||
| 14:14:1.0.1.3.10.2.11.27 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.55 Responsibilities of type certificate holders who license the type certificate. | FAA | [Docket No. FAA-2021-0419, Amdt. No. 21-108, 89 FR 33108, Apr. 26, 2024] | A type certificate holder who allows a person to use the type certificate to manufacture a new aircraft, aircraft engine, or propeller must meet the applicable requirements of part 5 of this chapter and provide that person with a written licensing agreement acceptable to the FAA. | |||
| 14:14:1.0.1.3.10.2.11.3 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.15 Application for type certificate. | FAA | [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; Amdt. 21-92, 74 FR 53385, Oct. 16, 2009; Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR 9169, Mar. 5, 2018] | (a) An application for a type certificate is made on a form and in a manner prescribed by the FAA. (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. | |||
| 14:14:1.0.1.3.10.2.11.4 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.16 Special conditions. | FAA | [Amdt. 21-19, 32 FR 17851, Dec. 13, 1967, as amended by Amdt. 21-51, 45 FR 60170, Sept. 11, 1980] | If the FAA 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 FAA finds necessary to establish a level of safety equivalent to that established in the regulations. | |||
| 14:14:1.0.1.3.10.2.11.5 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.17 Designation of applicable regulations. | FAA | [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; Amdt. 21-90, 72 FR 63404, Nov. 8, 2007; Doc. No. FAA-2015-1621, Amdt. 21-100, 81 FR 96688, Dec. 30, 2016; Amdt. No. 21-107, 89 FR 12653, Feb. 16, 2024] | (a) Except as provided in §§ 25.2, 27.2, and 29.2 of this subchapter, and in parts 26, 34, 36, and 38 of this subchapter, 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 FAA; or (ii) Compliance with later effective amendments is elected or required under this section; and (2) Any special conditions prescribed by the FAA. (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 FAA to be appropriate for the aircraft and applicable to a specific type design, or such airworthiness criteria as the FAA 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 FAA 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… | |||
| 14:14:1.0.1.3.10.2.11.6 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.19 Changes requiring a new type certificate. | FAA | [Doc. No. 28903, 65 FR 36265, June 7, 2000] | Each person who proposes to change a product must apply for a new type certificate if the FAA 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. | |||
| 14:14:1.0.1.3.10.2.11.7 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.20 Compliance with applicable requirements. | FAA | [Doc. No. FAA-2006-25877, Amdt. 21-92, 74 FR 53385, Oct. 16, 2009] | The applicant for a type certificate, including an amended or supplemental type certificate, must— (a) Show compliance with all applicable requirements and must provide the FAA the means by which such compliance has been shown; and (b) Provide a statement certifying that the applicant has complied with the applicable requirements. | |||
| 14:14:1.0.1.3.10.2.11.8 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.21 Issue of type certificate: normal, utility, acrobatic, commuter, and transport category aircraft; manned free balloons; special classes of aircraft; aircraft engines; propellers. | FAA | [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; Amdt. 21-92, 74 FR 53385, Oct. 16, 2009; Amdt. No. 21-107, 89 FR 12653, Feb. 16, 2024] | 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, exhaust emission, and fuel efficiency requirements of this subchapter and any special conditions prescribed by the FAA, and the FAA 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, emissions, and fuel efficiency requirements of this subchapter, and further finds that they meet the applicable airworthiness requirements of this subchapter 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. | |||
| 14:14:1.0.1.3.10.2.11.9 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | B | Subpart B—Type Certificates | § 21.23 [Reserved] | FAA | |||||
| 14:14:1.0.1.3.10.3.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | C | Subpart C—Provisional Type Certificates | § 21.71 Applicability. | FAA | This subpart prescribes— (a) Procedural requirements for the issue of provisional type certificates, amendments to provisional type certificates, and provisional amendments to type certificates; and (b) Rules governing the holders of those certificates. | ||||
| 14:14:1.0.1.3.10.3.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | C | Subpart C—Provisional Type Certificates | § 21.73 Eligibility. | FAA | [Doc. No. 5085, 29 FR 14566, Oct. 24, 1964, as amended by Amdt. 21-12, 31 FR 13380, Oct. 15, 1966; Amdt. 21-59, 52 FR 1836, Jan. 15, 1987; Amdt. 21-92, 74 FR 53387, Oct. 16, 2009] | (a) Any manufacturer of aircraft manufactured within the United States who is a United States citizen may apply for Class I or Class II provisional type certificates, for amendments to provisional type certificates held by him, and for provisional amendments to type certificates held by him. (b) Any manufacturer of aircraft in a State of Manufacture subject to the provisions of an agreement with the United States for the acceptance of those aircraft for export and import may apply for a Class II provisional type certificate, for amendments to provisional type certificates held by him, and for provisional amendments to type certificates held by him. (c) An aircraft engine manufacturer who is a United States citizen and who has altered a type certificated aircraft by installing different type certificated aircraft engines manufactured by him within the United States may apply for a Class I provisional type certificate for the aircraft, and for amendments to Class I provisional type certificates held by him, if the basic aircraft, before alteration, was type certificated in the normal, utility, acrobatic, commuter, or transport category. | |||
| 14:14:1.0.1.3.10.3.11.3 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | C | Subpart C—Provisional Type Certificates | § 21.75 Application. | FAA | [Doc. No. FAA-2006-25877, Amdt. 21-92, 74 FR 53387, Oct. 16, 2009; Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR 9169, Mar. 5, 2018] | Each applicant for a provisional type certificate, for an amendment thereto, or for a provisional amendment to a type certificate must apply to the FAA and provide the information required by this subpart. | |||
| 14:14:1.0.1.3.10.3.11.4 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | C | Subpart C—Provisional Type Certificates | § 21.77 Duration. | FAA | [Doc. No. 5085, 29 FR 14566, Oct. 24, 1964, as amended by Amdt. 21-7, 30 FR 14311, Nov. 16, 1965] | (a) Unless sooner surrendered, superseded, revoked, or otherwise terminated, provisional type certificates and amendments thereto are effective for the periods specified in this section. (b) A Class I provisional type certificate is effective for 24 months after the date of issue. (c) A Class II provisional type certificate is effective for twelve months after the date of issue. (d) An amendment to a Class I or Class II provisional type certificate is effective for the duration of the amended certificate. (e) A provisional amendment to a type certificate is effective for six months after its approval or until the amendment of the type certificate is approved, whichever is first. | |||
| 14:14:1.0.1.3.10.3.11.5 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | C | Subpart C—Provisional Type Certificates | § 21.79 Transferability. | FAA | Provisional type certificates are not transferable. | ||||
| 14:14:1.0.1.3.10.3.11.6 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | C | Subpart C—Provisional Type Certificates | § 21.81 Requirements for issue and amendment of Class I provisional type certificates. | FAA | [Doc. No. 5085, 29 FR 14566, Oct. 24, 1964, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989] | (a) An applicant is entitled to the issue or amendment of a Class I provisional type certificate if he shows compliance with this section and the FAA finds that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated in accordance with the limitations established in paragraph (e) of this section and in § 91.317 of this chapter. (b) The applicant must apply for the issue of a type or supplemental type certificate for the aircraft. (c) The applicant must certify that— (1) The aircraft has been designed and constructed in accordance with the airworthiness requirements applicable to the issue of the type or supplemental type certificate applied for; (2) The aircraft substantially meets the applicable flight characteristic requirements for the type or supplemental type certificate applied for; and (3) The aircraft can be operated safely under the appropriate operating limitations specified in paragraph (a) of this section. (d) The applicant must submit a report showing that the aircraft had been flown in all maneuvers necessary to show compliance with the flight requirements for the issue of the type or supplemental type certificate applied for, and to establish that the aircraft can be operated safely in accordance with the limitations contained in this subchapter. (e) The applicant must establish all limitations required for the issue of the type or supplemental type certificate applied for, including limitations on weights, speeds, flight maneuvers, loading, and operation of controls and equipment unless, for each limitation not so established, appropriate operating restrictions are established for the aircraft. (f) The applicant must establish an inspection and maintenance program for the continued airworthiness of the aircraft. (g) The applicant must show that a prototype aircraft has been flown for at least 50 hours under an experimental certificate issued under §§ 21.191 through 21.195, or under the auspices of an Armed Force of the United States. However, in… | |||
| 14:14:1.0.1.3.10.3.11.7 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | C | Subpart C—Provisional Type Certificates | § 21.83 Requirements for issue and amendment of Class II provisional type certificates. | FAA | [Amdt. 21-12, 31 FR 13386, Oct. 15, 1966, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989] | (a) An applicant who manufactures aircraft within the United States is entitled to the issue or amendment of a Class II provisional type certificate if he shows compliance with this section and the FAA finds that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated in accordance with the limitations in paragraph (h) of this section, and §§ 91.317 and 121.207 of this chapter. (b) An applicant who manufactures aircraft in a country with which the United States has an agreement for the acceptance of those aircraft for export and import is entitled to the issue or amendment of a Class II provisional type certificate if the country in which the aircraft was manufactured certifies that the applicant has shown compliance with this section, that the aircraft meets the requirements of paragraph (f) of this section and that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated in accordance with the limitations in paragraph (h) of this section and §§ 91.317 and 121.207 of this chapter. (c) The applicant must apply for a type certificate, in the transport category, for the aircraft. (d) The applicant must hold a U.S. type certificate for at least one other aircraft in the same transport category as the subject aircraft. (e) The FAA's official flight test program or the flight test program conducted by the authorities of the country in which the aircraft was manufactured, with respect to the issue of a type certificate for that aircraft, must be in progress. (f) The applicant or, in the case of a foreign manufactured aircraft, the country in which the aircraft was manufactured, must certify that— (1) The aircraft has been designed and constructed in accordance with the airworthiness requirements applicable to the issue of the type certificate applied for; (2) The aircraft substantially complies with the applicable flight characteristic requirements for the type certificate applied for; and (3) The aircraft can be operated saf… | |||
| 14:14:1.0.1.3.10.3.11.8 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | C | Subpart C—Provisional Type Certificates | § 21.85 Provisional amendments to type certificates. | FAA | [Amdt. 21-12, 31 FR 13388, Oct. 15, 1966, as amended by Amdt. 21-66, 54 FR 34329, Aug. 18, 1989] | (a) An applicant who manufactures aircraft within the United States is entitled to a provisional amendment to a type certificate if he shows compliance with this section and the FAA finds that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated under the appropriate limitations contained in this subchapter. (b) An applicant who manufactures aircraft in a foreign country with which the United States has an agreement for the acceptance of those aircraft for export and import is entitled to a provisional amendment to a type certificate if the country in which the aircraft was manufactured certifies that the applicant has shown compliance with this section, that the aircraft meets the requirements of paragraph (e) of this section and that there is no feature, characteristic, or condition that would make the aircraft unsafe when operated under the appropriate limitations contained in this subchapter. (c) The applicant must apply for an amendment to the type certificate. (d) The FAA's official flight test program or the flight test program conducted by the authorities of the country in which the aircraft was manufactured, with respect to the amendment of the type certificate, must be in progress. (e) The applicant or, in the case of foreign manufactured aircraft, the country in which the aircraft was manufactured, must certify that— (1) The modification involved in the amendment to the type certificate has been designed and constructed in accordance with the airworthiness requirements applicable to the issue of the type certificate for the aircraft; (2) The aircraft substantially complies with the applicable flight characteristic requirements for the type certificate; and (3) The aircraft can be operated safely under the appropriate operating limitations in this subchapter. (f) The applicant must submit a report showing that the aircraft incorporating the modifications involved has been flown in all maneuvers necessary to show compliance with the flight requiremen… | |||
| 14:14:1.0.1.3.10.4.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | D | Subpart D—Changes to Type Certificates | § 21.91 Applicability. | FAA | This subpart prescribes procedural requirements for the approval of changes to type certificates. | ||||
| 14:14:1.0.1.3.10.4.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | D | Subpart D—Changes to Type Certificates | § 21.93 Classification of changes in type design. | FAA | [Amdt. 21-27, 34 FR 18363, Nov. 18, 1969] | (a) In addition to changes in type design specified in paragraph (b) of this section, changes in type design are classified as minor and major. A “minor change” is one that has no appreciable effect on the weight, balance, structural strength, reliability, operational characteristics, or other characteristics affecting the airworthiness of the product. All other changes are “major changes” (except as provided in paragraph (b) of this section). (b) For the purpose of complying with Part 36 of this chapter, and except as provided in paragraphs (b)(2), (b)(3), and (b)(4) of this section, any voluntary change in the type design of an aircraft that may increase the noise levels of that aircraft is an “acoustical change” (in addition to being a minor or major change as classified in paragraph (a) of this section) for the following aircraft: (1) Transport category large airplanes. (2) Jet (Turbojet powered) airplanes (regardless of category). For airplanes to which this paragraph applies, “acoustical changes” do not include changes in type design that are limited to one of the following— (i) Gear down flight with one or more retractable landing gear down during the entire flight, or (ii) Spare engine and nacelle carriage external to the skin of the airplane (and return of the pylon or other external mount), or (iii) Time-limited engine and/or nacelle changes, where the change in type design specifies that the airplane may not be operated for a period of more than 90 days unless compliance with the applicable acoustical change provisions of Part 36 of this chapter is shown for that change in type design. (3) Propeller driven commuter category and small airplanes in the primary, normal, utility, acrobatic, transport, and restricted categories, except for airplanes that are: (i) Designated for “agricultural aircraft operations” (as defined in § 137.3 of this chapter, effective January 1, 1966) to which § 36.1583 of this chapter does not apply, or (ii) Designated for dispensing fire fighting materials to which § 36… | |||
| 14:14:1.0.1.3.10.4.11.3 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | D | Subpart D—Changes to Type Certificates | § 21.95 Approval of minor changes in type design. | FAA | Minor changes in a type design may be approved under a method acceptable to the FAA before submitting to the FAA any substantiating or descriptive data. | ||||
| 14:14:1.0.1.3.10.4.11.4 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | D | Subpart D—Changes to Type Certificates | § 21.97 Approval of major changes in type design. | FAA | [Amdt. 21-40, 39 FR 35459, Oct. 1, 1974, as amended by Amdt. 21-92, 74 FR 53387, Oct. 16, 2009; Amdt. 21-96, 77 FR 71695, Dec. 4, 2012] | (a) An applicant for approval of a major change in type design must— (1) Provide substantiating data and necessary descriptive data for inclusion in the type design; (2) Show that the change and areas affected by the change comply with the applicable requirements of this subchapter, and provide the FAA the means by which such compliance has been shown; and (3) Provide a statement certifying that the applicant has complied with the applicable requirements. (b) Approval of a major change in the type design of an aircraft engine is limited to the specific engine configuration upon which the change is made unless the applicant identifies in the necessary descriptive data for inclusion in the type design the other configurations of the same engine type for which approval is requested and shows that the change is compatible with the other configurations. | |||
| 14:14:1.0.1.3.10.4.11.5 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | D | Subpart D—Changes to Type Certificates | § 21.99 Required design changes. | FAA | [Doc. No. 5085, 29 FR 14567, Oct. 24, 1964, as amended by Amdt. 21-3, 30 FR 8826, July 24, 1965] | (a) When an Airworthiness Directive is issued under Part 39 the holder of the type certificate for the product concerned must— (1) If the FAA finds that design changes are necessary to correct the unsafe condition of the product, and upon his request, submit appropriate design changes for approval; and (2) Upon approval of the design changes, make available the descriptive data covering the changes to all operators of products previously certificated under the type certificate. (b) In a case where there are no current unsafe conditions, but the FAA or the holder of the type certificate finds through service experience that changes in type design will contribute to the safety of the product, the holder of the type certificate may submit appropriate design changes for approval. Upon approval of the changes, the manufacturer must make information on the design changes available to all operators of the same type of product. | |||
| 14:14:1.0.1.3.10.4.11.6 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | D | Subpart D—Changes to Type Certificates | § 21.101 Designation of applicable regulations. | FAA | [Doc. No. 28903, 65 FR 36266, June 7, 2000, as amended by Amdt. 21-90, 72 FR 63404, Nov. 8, 2007; Amdt. 21-96, 77 FR 71695, Dec. 4, 2012; Doc. No. FAA-2015-1621, Amdt. 21-100, 81 FR 96689, Dec. 30, 2016; Doc. No. FAA-2022-0241, Amdt. No. 21-107, 89 FR 12653, Feb. 16, 2024] | (a) An applicant for a change to a type certificate must show that the change and areas affected by the change comply with the airworthiness requirements applicable to the category of the product in effect on the date of the application for the change and with parts 34, 36, and 38 of this chapter. Exceptions are detailed in paragraphs (b) and (c) of this section. (b) Except as provided in paragraph (g) of this section, if paragraphs (b)(1), (2), or (3) of this section apply, an applicant may show that the change and areas affected by the change comply with an earlier amendment of a regulation required by paragraph (a) of this section, and of any other regulation the FAA finds is directly related. However, the earlier amended regulation may not precede either the corresponding regulation included by reference in the type certificate, or any regulation in §§ 25.2, 27.2, or 29.2 of this chapter that is related to the change. The applicant may show compliance with an earlier amendment of a regulation for any of the following: (1) A change that the FAA finds not to be significant. In determining whether a specific change is significant, the FAA considers the change in context with all previous relevant design changes and all related revisions to the applicable regulations incorporated in the type certificate for the product. Changes that meet one of the following criteria are automatically considered significant: (i) The general configuration or the principles of construction are not retained. (ii) The assumptions used for certification of the product to be changed do not remain valid. (2) Each area, system, component, equipment, or appliance that the FAA finds is not affected by the change. (3) Each area, system, component, equipment, or appliance that is affected by the change, for which the FAA finds that compliance with a regulation described in paragraph (a) of this section would not contribute materially to the level of safety of the product or would be impractical. (c) An applicant for a change to an air… | |||
| 14:14:1.0.1.3.10.5.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | E | Subpart E—Supplemental Type Certificates | § 21.111 Applicability. | FAA | This subpart prescribes procedural requirements for the issue of supplemental type certificates. | ||||
| 14:14:1.0.1.3.10.5.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | E | Subpart E—Supplemental Type Certificates | § 21.113 Requirement for supplemental type certificate. | FAA | [Doc. No. FAA-2006-25877, Amdt. 21-92, 74 FR 53387, Oct. 16, 2009; Doc. No. FAA-2018-0119, Amdt. 21-101, 83 FR 9169, Mar. 5, 2018] | (a) If a person holds the TC for a product and alters that product by introducing a major change in type design that does not require an application for a new TC under § 21.19, that person must apply to the FAA either for an STC, or to amend the original type certificate under subpart D of this part. (b) If a person does not hold the TC for a product and alters that product by introducing a major change in type design that does not require an application for a new TC under § 21.19, that person must apply to the FAA for an STC. (c) The application for an STC must be made in the form and manner prescribed by the FAA. | |||
| 14:14:1.0.1.3.10.5.11.3 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | E | Subpart E—Supplemental Type Certificates | § 21.115 Applicable requirements. | FAA | [Amdt. 21-17, 32 FR 14927, Oct. 28, 1967, as amended by Amdt. 21-42, 40 FR 1033, Jan. 6, 1975; Amdt. 21-52A, 45 FR 79009, Nov. 28, 1980; Amdt. 21-61, 53 FR 3540, Feb. 5, 1988; Amdt. 21-68, 55 FR 32860, Aug. 10, 1990; Amdt. 21-71, 57 FR 42854, Sept. 16, 1992; Amdt. 21-77, 65 FR 36266, June 7, 2000; Amdt. No. 21-107, 89 FR 12653, Feb. 16, 2024] | (a) Each applicant for a supplemental type certificate must show that the altered product meets applicable requirements specified in § 21.101 and— (1) In the case of an acoustical change described in § 21.93(b), show compliance with the applicable noise requirements of part 36 of this chapter; (2) In the case of an emissions change described in § 21.93(c), show compliance with the applicable fuel venting and exhaust emissions requirements of part 34 of this chapter; and (3) In the case of a fuel efficiency change described in § 21.93(d), show compliance with the applicable fuel efficiency requirements of part 38 of this chapter. (b) Each applicant for a supplemental type certificate must meet §§ 21.33 and 21.53 with respect to each change in the type design. | |||
| 14:14:1.0.1.3.10.5.11.4 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | E | Subpart E—Supplemental Type Certificates | § 21.117 Issue of supplemental type certificates. | FAA | [Doc. No. 5085, 29 FR 14568, Oct. 24, 1964, as amended by Amdt. 21-92, 74 FR 53387, Oct. 16, 2009] | (a) An applicant is entitled to a supplemental type certificate if the FAA finds that the applicant meets the requirements of §§ 21.113 and 21.115. (b) A supplemental type certificate consists of— (1) The approval by the FAA of a change in the type design of the product; and (2) The type certificate previously issued for the product. | |||
| 14:14:1.0.1.3.10.5.11.5 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | E | Subpart E—Supplemental Type Certificates | § 21.119 Privileges. | FAA | [Doc. No. 5085, 29 FR 14568, Oct. 24, 1964, as amended by Amdt. 21-92, 74 FR 53387, Oct. 16, 2009] | The holder of a supplemental type certificate may— (a) In the case of aircraft, obtain airworthiness certificates; (b) In the case of other products, obtain approval for installation on certificated aircraft; and (c) Obtain a production certificate in accordance with the requirements of subpart G of this part for the change in the type design approved by the supplemental type certificate. | |||
| 14:14:1.0.1.3.10.5.11.6 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | E | Subpart E—Supplemental Type Certificates | § 21.120 Responsibility of supplemental type certificate holders to provide written permission for alterations. | FAA | [Doc. No. FAA-2003-14825, 71 FR 52258, Sept. 1, 2006] | A supplemental type certificate holder who allows a person to use the supplemental type certificate to alter an aircraft, aircraft engine, or propeller must provide that person with written permission acceptable to the FAA. | |||
| 14:14:1.0.1.3.10.6.11.1 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | F | Subpart F—Production Under Type Certificate | § 21.121 Applicability. | FAA | This subpart prescribes rules for production under a type certificate. | ||||
| 14:14:1.0.1.3.10.6.11.2 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | F | Subpart F—Production Under Type Certificate | § 21.122 Location of or change to manufacturing facilities. | FAA | [Doc. No. FAA-2006-25877, Amdt. 21-92, 74 FR 53387, Oct. 16, 2009; Amdt. 21-92A, 75 FR 9095, Mar. 1, 2010] | (a) A type certificate holder may utilize manufacturing facilities located outside of the United States if the FAA finds no undue burden in administering the applicable requirements of Title 49 U.S.C. and this subchapter. (b) The type certificate holder must obtain FAA approval before making any changes to the location of any of its manufacturing facilities. (c) The type certificate holder must immediately notify the FAA, in writing, of any change to the manufacturing facilities that may affect the inspection, conformity, or airworthiness of its product or article. | |||
| 14:14:1.0.1.3.10.6.11.3 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | F | Subpart F—Production Under Type Certificate | § 21.123 Production under type certificate. | FAA | [Doc. No. FAA-2006-25877, Amdt. 21-92, 74 FR 53387, Oct. 16, 2009] | Each manufacturer of a product being manufactured under a type certificate must— (a) Maintain at the place of manufacture all information and data specified in §§ 21.31 and 21.41; (b) Make each product and article thereof available for inspection by the FAA; (c) Maintain records of the completion of all inspections and tests required by §§ 21.127, 21.128, and 21.129 for at least 5 years for the products and articles thereof manufactured under the approval and at least 10 years for critical components identified under § 45.15(c) of this chapter; (d) Allow the FAA to make any inspection or test, including any inspection or test at a supplier facility, necessary to determine compliance with this subchapter; (e) Mark the product in accordance with part 45 of this chapter, including any critical parts; (f) Identify any portion of that product ( e.g., sub-assemblies, component parts, or replacement articles) that leave the manufacturer's facility as FAA approved with the manufacturer's part number and name, trademark, symbol, or other FAA-approved manufacturer's identification; and (g) Except as otherwise authorized by the FAA, obtain a production certificate for that product in accordance with subpart G of this part within 6 months after the date of issuance of the type certificate. | |||
| 14:14:1.0.1.3.10.6.11.4 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | F | Subpart F—Production Under Type Certificate | § 21.125 [Reserved] | FAA | |||||
| 14:14:1.0.1.3.10.6.11.5 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | F | Subpart F—Production Under Type Certificate | § 21.127 Tests: aircraft. | FAA | (a) Each person manufacturing aircraft under a type certificate must establish an approved production flight test procedure and flight check-off form, and in accordance with that form, flight test each aircraft produced. (b) Each production flight test procedure must include the following: (1) An operational check of the trim, controllability, or other flight characteristics to establish that the production aircraft has the same range and degree of control as the prototype aircraft. (2) An operational check of each part or system operated by the crew while in flight to establish that, during flight, instrument readings are within normal range. (3) A determination that all instruments are properly marked, and that all placards and required flight manuals are installed after flight test. (4) A check of the operational characteristics of the aircraft on the ground. (5) A check on any other items peculiar to the aircraft being tested that can best be done during the ground or flight operation of the aircraft. | ||||
| 14:14:1.0.1.3.10.6.11.6 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | F | Subpart F—Production Under Type Certificate | § 21.128 Tests: aircraft engines. | FAA | [Doc. No. 5085, 29 FR 14568, Oct. 24, 1964, as amended by Amdt. 21-5, 32 FR 3735, Mar. 4, 1967] | (a) Each person manufacturing aircraft engines under a type certificate must subject each engine (except rocket engines for which the manufacturer must establish a sampling technique) to an acceptable test run that includes the following: (1) Break-in runs that include a determination of fuel and oil consumption and a determination of power characteristics at rated maximum continuous power or thrust and, if applicable, at rated takeoff power or thrust. (2) At least five hours of operation at rated maximum continuous power or thrust. For engines having a rated takeoff power or thrust higher than rated maximum continuous power or thrust, the five-hour run must include 30 minutes at rated takeoff power or thrust. (b) The test runs required by paragraph (a) of this section may be made with the engine appropriately mounted and using current types of power and thrust measuring equipment. | |||
| 14:14:1.0.1.3.10.6.11.7 | 14 | Aeronautics and Space | I | C | 21 | PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES | F | Subpart F—Production Under Type Certificate | § 21.129 Tests: propellers. | FAA | Each person manufacturing propellers under a type certificate must give each variable pitch propeller an acceptable functional test to determine if it operates properly throughout the normal range of operation. |
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title_number INTEGER,
title_name TEXT,
chapter TEXT,
subchapter TEXT,
part_number TEXT,
part_name TEXT,
subpart TEXT,
subpart_name TEXT,
section_number TEXT,
section_heading TEXT,
agency TEXT,
authority TEXT,
source_citation TEXT,
amendment_citations TEXT,
full_text TEXT
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CREATE INDEX idx_cfr_agency ON cfr_sections(agency);