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 10:10:1.0.1.1.17.0.76.1,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.1 Purpose.,NRC,,,,"The regulations in this part establish procedures and requirements for implementation of section 206 of the Energy Reorganization Act of 1974. That section requires any individual director or responsible officer of a firm constructing, owning, operating or supplying the components of any facility or activity which is licensed or otherwise regulated pursuant to the Atomic Energy Act of 1954, as amended, or the Energy Reorganization Act of 1974, who obtains information reasonably indicating: (a) That the facility, activity or basic component supplied to such facility or activity fails to comply with the Atomic Energy Act of 1954, as amended, or any applicable rule, regulation, order, or license of the Commission relating to substantial safety hazards or (b) that the facility, activity, or basic component supplied to such facility or activity contains defects, which could create a substantial safety hazard, to immediately notify the Commission of such failure to comply or such defect, unless he has actual knowledge that the Commission has been adequately informed of such defect or failure to comply." 10:10:1.0.1.1.17.0.76.2,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.2 Scope.,NRC,,,"[56 FR 36089, July 31, 1991, as amended at 59 FR 14086, Mar. 25, 1994; 59 FR 48959, Sept. 23, 1994; 60 FR 48373, Sept. 19, 1995; 66 FR 55790, Nov. 2, 2001; 72 FR 49486, Aug. 28, 2007; 85 FR 65661, Oct. 16, 2020; 88 FR 15880, Mar. 14, 2023]","(a) The regulations in this part apply, except as specifically provided otherwise in parts 31, 34, 35, 39, 40, 60, 61, 63, 70, or part 72 of this chapter, to: (1) Each individual, partnership, corporation, or other entity applying for or holding a license or permit under the regulations in this chapter to possess, use, or transfer within the United States source material, byproduct material, special nuclear material, and/or spent fuel and high-level radioactive waste, or to construct, manufacture, possess, own, operate, or transfer within the United States, any production or utilization facility or independent spent fuel storage installation (ISFSI) or monitored retrievable storage installation (MRS); and each director and responsible officer of such a licensee; (2) Each individual, corporation, partnership, or other entity doing business within the United States, and each director and responsible officer of such an organization, that constructs a production or utilization facility licensed for manufacture, construction, or operation under parts 50 or 52 of this chapter, an ISFSI for the storage of spent fuel licensed under part 72 of this chapter, an MRS for the storage of spent fuel or high-level radioactive waste under part 72 of this chapter, or a geologic repository for the disposal of high-level radioactive waste under part 60 or 63 of this chapter; or supplies basic components for a facility or activity licensed, other than for export, under parts 30, 40, 50, 52, 60, 61, 63, 70, 71, or part 72 of this chapter; (3) Each individual, corporation, partnership, or other entity doing business within the United States, and each director and responsible officer of such an organization, applying for a design certification rule under part 52 of this chapter; or supplying basic components with respect to that design certification, and each individual, corporation, partnership, or other entity doing business within the United States, and each director and responsible officer of such an organization, whose application for design certification has been granted under part 52 of this chapter, or who has supplied or is supplying basic components with respect to that design certification; (4) Each individual, corporation, partnership, or other entity doing business within the United States, and each director and responsible officer of such an organization, applying for or holding a standard design approval under part 52 of this chapter; or supplying basic components with respect to a standard design approval under part 52 of this chapter; (b) For persons licensed to construct a facility under either a construction permit issued under § 50.23 of this chapter or a combined license under part 52 of this chapter (for the period of construction until the date that the Commission makes the finding under § 52.103(g) of this chapter), or to manufacture a facility under part 52 of this chapter, evaluation of potential defects and failures to comply and reporting of defects and failures to comply under § 50.55(e) of this chapter satisfies each person's evaluation, notification, and reporting obligation to report defects and failures to comply under this part and the responsibility of individual directors and responsible officers of these licensees to report defects under Section 206 of the Energy Reorganization Act of 1974. (c) For persons licensed to operate a nuclear power plant under part 50 or part 52 of this chapter, evaluation of potential defects and appropriate reporting of defects under §§ 50.72, 50.73, or §§ 73.1200 and 73.1205 of this chapter, satisfies each person's evaluation, notification, and reporting obligation to report defects under this part, and the responsibility of individual directors and responsible officers of these licensees to report defects under Section 206 of the Energy Reorganization Act of 1974. (d) Nothing in these regulations should be deemed to preclude either an individual, a manufacturer, or a supplier of a commercial grade item (as defined in § 21.3) not subject to the regulations in this part from reporting to the Commission, a known or suspected defect or failure to comply and, as authorized by law, the identity of anyone so reporting will be withheld from disclosure. NRC regional offices and headquarters will accept collect telephone calls from individuals who wish to speak to NRC representatives concerning nuclear safety-related problems. The location and telephone numbers of the four regions (answered during regular working hours), are listed in appendix D to part 20 of this chapter. The telephone numbers of the NRC Headquarters Operations Center (answered 24 hours a day—including holidays) are listed in appendix A to part 73 of this chapter. (e) The regulations in this part apply in accordance with 10 CFR 76.60 to each individual, partnership, corporation, or other entity required to obtain a certificate of compliance or an approved compliance plan under part 76 of this chapter." 10:10:1.0.1.1.17.0.76.3,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.3 Definitions.,NRC,,,"[42 FR 28893, June 6, 1977; 42 FR 36803, July 18, 1977, as amended at 43 FR 48622, Oct. 19, 1978; 46 FR 58283, Dec. 1, 1981; 47 FR 57480, Dec. 27, 1982; 56 FR 36089, July 31, 1991; 59 FR 5519, Feb. 7, 1994; 60 FR 48373, Sept. 19, 1995; 61 FR 65171, Dec. 11, 1996; 64 FR 72000, Dec. 23, 1999; 66 FR 55790, Nov. 2, 2001; 72 FR 49486, Aug. 28, 2007; 84 FR 63567, Nov. 18, 2019]","As used in this part: Basic component. (1)(i) When applied to nuclear power plants licensed under 10 CFR part 50 or part 52 of this chapter, basic component means a structure, system, or component, or part thereof that affects its safety function necessary to assure: (A) The integrity of the reactor coolant pressure boundary; (B) The capability to shut down the reactor and maintain it in a safe-shutdown condition; or (C) The capability to prevent or mitigate the consequences of accidents which could result in potential offsite exposures comparable to those referred to in §§ 50.34(a)(1), 50.67(b)(2), or 100.11 of this chapter, as applicable. (ii) Basic components are items designed and manufactured under a quality assurance program complying with appendix B to part 50 of this chapter, or commercial grade items which have successfully completed the dedication process. (2) When applied to standard design certifications under subpart B of part 52 of this chapter and standard design approvals under part 52 of this chapter, basic component means the design or procurement information approved or to be approved within the scope of the design certification or approval for a structure, system, or component, or part thereof, that affects its safety function necessary to assure: (i) The integrity of the reactor coolant pressure boundary; (ii) The capability to shut down the reactor and maintain it in a safe-shutdown condition; or (iii) The capability to prevent or mitigate the consequences of accidents which could result in potential offsite exposures comparable to those referred to in §§ 50.34(a)(1), 50.67(b)(2), or 100.11 of this chapter, as applicable. (3) When applied to other facilities and other activities licensed under 10 CFR parts 30, 40, 50 (other than nuclear power plants), 60, 61, 63, 70, 71, or 72 of this chapter, basic component means a structure, system, or component, or part thereof, that affects their safety function, that is directly procured by the licensee of a facility or activity subject to the regulations in this part and in which a defect or failure to comply with any applicable regulation in this chapter, order, or license issued by the Commission could create a substantial safety hazard. (4) In all cases, basic component includes safety-related design, analysis, inspection, testing, fabrication, replacement of parts, or consulting services that are associated with the component hardware, design certification, design approval, or information in support of an early site permit application under part 52 of this chapter, whether these services are performed by the component supplier or others. Commercial grade item. (1) When applied to nuclear power plants licensed pursuant to 10 CFR part 50, commercial grade item means a structure, system, or component, or part thereof that affects its safety function, that was not designed and manufactured as a basic component. Commercial grade items do not include items where the design and manufacturing process require in-process inspections and verifications to ensure that defects or failures to comply are identified and corrected ( i.e. , one or more critical characteristics of the item cannot be verified). (2) When applied to facilities and activities licensed pursuant to 10 CFR parts 30, 40, 50 (other than nuclear power plants), 60, 61, 63, 70, 71, or 72, commercial grade item means an item that is: (i) Not subject to design or specification requirements that are unique to those facilities or activities; (ii) Used in applications other than those facilities or activities; and (iii) To be ordered from the manufacturer/supplier on the basis of specifications set forth in the manufacturer's published product description (for example, a catalog). Commission means the Nuclear Regulatory Commission or its duly authorized representatives. Constructing or construction means the analysis, design, manufacture, fabrication, placement, erection, installation, modification, inspection, or testing of a facility or activity which is subject to the regulations in this part and consulting services related to the facility or activity that are safety related. Critical characteristics. When applied to nuclear power plants licensed pursuant to 10 CFR part 50, critical characteristics are those important design, material, and performance characteristics of a commercial grade item that, once verified, will provide reasonable assurance that the item will perform its intended safety function. Dedicating entity. When applied to nuclear power plants licensed pursuant to 10 CFR part 50, dedicating entity means the organization that performs the dedication process. Dedication may be performed by the manufacturer of the item, a third-party dedicating entity, or the licensee itself. The dedicating entity, pursuant to § 21.21(c) of this part, is responsible for identifying and evaluating deviations, reporting defects and failures to comply for the dedicated item, and maintaining auditable records of the dedication process. Dedication. (1) When applied to nuclear power plants licensed pursuant to 10 CFR part 50, dedication is an acceptance process undertaken to provide reasonable assurance that a commercial grade item to be used as a basic component will perform its intended safety function and, in this respect, is deemed equivalent to an item designed and manufactured under a 10 CFR part 50, appendix B, quality assurance program. This assurance is achieved by identifying the critical characteristics of the item and verifying their acceptability by inspections, tests, or analyses performed by the purchaser or third-party dedicating entity after delivery, supplemented as necessary by one or more of the following: commercial grade surveys; product inspections or witness at holdpoints at the manufacturer's facility, and analysis of historical records for acceptable performance. In all cases, the dedication process must be conducted in accordance with the applicable provisions of 10 CFR part 50, appendix B. The process is considered complete when the item is designated for use as a basic component. (2) When applied to facilities and activities licensed pursuant to 10 CFR parts 30, 40, 50 (other than nuclear power plants), 60, 61, 63, 70, 71, or 72, dedication occurs after receipt when that item is designated for use as a basic component. Defect means: (1) A deviation in a basic component delivered to a purchaser for use in a facility or an activity subject to the regulations in this part if, on the basis of an evaluation, the deviation could create a substantial safety hazard; (2) The installation, use, or operation of a basic component containing a defect as defined in this section; (3) A deviation in a portion of a facility subject to the early site permit, standard design certification, standard design approval, construction permit, combined license or manufacturing licensing requirements of part 50 or part 52 of this chapter, provided the deviation could, on the basis of an evaluation, create a substantial safety hazard and the portion of the facility containing the deviation has been offered to the purchaser for acceptance; (4) A condition or circumstance involving a basic component that could contribute to the exceeding of a safety limit, as defined in the technical specifications of a license for operation issued under part 50 or part 52 of this chapter; or (5) An error, omission or other circumstance in a design certification, or standard design approval that, on the basis of an evaluation, could create a substantial safety hazard. Deviation means a departure from the technical requirements included in a procurement document, or specified in early site permit information, a standard design certification or standard design approval. Director means an individual, appointed or elected according to law, who is authorized to manage and direct the affairs of a corporation, partnership or other entity. In the case of an individual proprietorship, director means the individual. Discovery means the completion of the documentation first identifying the existence of a deviation or failure to comply potentially associated with a substantial safety hazard within the evaluation procedures discussed in § 21.21(a). Evaluation means the process of determining whether a particular deviation could create a substantial hazard or determining whether a failure to comply is associated with a substantial safety hazard. Notification means the telephonic communication to the NRC Operations Center or written transmittal of information to the NRC Document Control Desk. Operating or operation means the operation of a facility or the conduct of a licensed activity which is subject to the regulations in this part and consulting services related to operations that are safety related. Procurement document means a contract that defines the requirements which facilities or basic components must meet in order to be considered acceptable by the purchaser. Responsible officer means the president, vice-president or other individual in the organization of a corporation, partnership, or other entity who is vested with executive authority over activities subject to this part. Substantial safety hazard means a loss of safety function to the extent that there is a major reduction in the degree of protection provided to public health and safety for any facility or activity licensed or otherwise approved or regulated by the NRC, other than for export, under parts 30, 40, 50, 52, 60, 61, 63, 70, 71, or 72 of this chapter. Supplying or supplies means contractually responsible for a basic component used or to be used in a facility or activity which is subject to the regulations in this part." 10:10:1.0.1.1.17.0.76.4,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.4 Interpretations.,NRC,,,"[42 FR 28893, June 6, 1977, as amended at 90 FR 55628, Dec. 3, 2025]","Except as specifically authorized by the Commission in writing, no interpretation of the meaning of the regulations in this part by any officer or employee of the Commission other than a written interpretation by the General Counsel will be recognized to be binding upon the Commission. This section shall cease to have effect on January 8, 2027 unless the NRC determines that the cessation deadline should be extended to a date not more than 5 years in the future after offering the public an opportunity to provide input on the costs and benefits of this section and considering that input. The NRC will publish a document in the Federal Register announcing its determination and revising or removing this section accordingly." 10:10:1.0.1.1.17.0.76.5,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.5 Communications.,NRC,,,"[72 FR 49487, Aug. 28, 2007, as amended at 74 FR 62680, Dec. 1, 2009; 80 FR 74979, Dec. 1, 2015]","Except where otherwise specified in this part, written communications and reports concerning the regulations in this part must be addressed to the NRC's Document Control Desk, and sent by mail to the U.S. Nuclear Regulatory Commission, Washington, DC 20555-0001; by hand delivery to the NRC's offices at 11555 Rockville Pike, Rockville, Maryland; or, where practicable, by electronic submission, for example, Electronic Information Exchange, or CD-ROM. Electronic submissions must be made in a manner that enables the NRC to receive, read, authenticate, distribute, and archive the submission, and process and retrieve it a single page at a time. Detailed guidance on making electronic submissions can be obtained by visiting the NRC's Web site at http://www.nrc.gov/site-help/e-submittals.html; by e-mail to MSHD.Resource@nrc.gov; or by writing the Office of the Chief Information Officer, U.S. Nuclear Regulatory Commission, Washington, DC 20555-0001. The guidance discusses, among other topics, the formats the NRC can accept, the use of electronic signatures, and the treatment of nonpublic information. In the case of a licensee or permit holder, a copy of the communication must also be sent to the appropriate Regional Administrator at the address specified in appendix D to part 20 of this chapter." 10:10:1.0.1.1.17.0.76.6,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.6 Posting requirements.,NRC,,,"[42 FR 28893, June 6, 1977, as amended at 60 FR 48374, Sept. 19, 1995]","(a)(1) Each individual, partnership, corporation, dedicating entity, or other entity subject to the regulations in this part shall post current copies of— (i) The regulations in this part; (ii) Section 206 of the Energy Reorganization Act of 1974; and (iii) Procedures adopted pursuant to the regulations in this part. (2) These documents must be posted in a conspicuous position on any premises within the United States where the activities subject to this part are conducted. (b) If posting of the regulations in this part or the procedures adopted pursuant to the regulations in this part is not practicable, the licensee or firm subject to the regulations in this part may, in addition to posting section 206, post a notice which describes the regulations/procedures, including the name of the individual to whom reports may be made, and states where they may be examined. (c) The effective date of this section has been deferred until January 6, 1978." 10:10:1.0.1.1.17.0.76.7,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.7 Exemptions.,NRC,,,"[42 FR 28893, June 6, 1977, as amended at 43 FR 48622, Oct. 19, 1978]","The Commission may, upon application of any interested person or upon its own initiative, grant such exemptions from the requirements of the regulations in this part as it determines are authorized by law and will not endanger life or property or the common defense and security and are otherwise in the public interest. Suppliers of commercial grade items are exempt from the provisions of this part to the extent that they supply commercial grade items." 10:10:1.0.1.1.17.0.76.8,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.8 Information collection requirements: OMB approval.,NRC,,,"[62 FR 52185, Oct. 6, 1997]","(a) The Nuclear Regulatory Commission has submitted the information collection requirements contained in this part to the Office of Management and Budget (OMB) for approval as required by the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ). The NRC may not conduct or sponsor, and a person is not required to respond to, a collection of information unless it displays a currently valid OMB control number. OMB has approved the information collection requirements contained in this part under control number 3150-0035. (b) The approved information collection requirements contained in this part appear in §§ 21.7, 21.21 and 21.51." 10:10:1.0.1.1.17.0.77.9,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.21 Notification of failure to comply or existence of a defect and its evaluation.,NRC,,,"[42 FR 28893, June 6, 1977, as amended at 46 FR 58283, Dec. 1, 1981; 47 FR 57480, Dec. 27, 1982; 52 FR 31611, Aug. 21, 1987; 56 FR 36089, July 31, 1991; 59 FR 14086, Mar. 25, 1994; 60 FR 48374, Sept. 19, 1995; 66 FR 55790, Nov. 2, 2001; 67 FR 77652, Dec. 19, 2002; 72 FR 49487, Aug. 28, 2007]","(a) Each individual, corporation, partnership, dedicating entity, or other entity subject to the regulations in this part shall adopt appropriate procedures to— (1) Evaluate deviations and failures to comply to identify defects and failures to comply associated with substantial safety hazards as soon as practicable, and, except as provided in paragraph (a)(2) of this section, in all cases within 60 days of discovery, in order to identify a reportable defect or failure to comply that could create a substantial safety hazard, were it to remain uncorrected, and (2) Ensure that if an evaluation of an identified deviation or failure to comply potentially associated with a substantial safety hazard cannot be completed within 60 days from discovery of the deviation or failure to comply, an interim report is prepared and submitted to the Commission through a director or responsible officer or designated person as discussed in § 21.21(d)(5). The interim report should describe the deviation or failure to comply that is being evaluated and should also state when the evaluation will be completed. This interim report must be submitted in writing within 60 days of discovery of the deviation or failure to comply. (3) Ensure that a director or responsible officer subject to the regulations of this part is informed as soon as practicable, and, in all cases, within the 5 working days after completion of the evaluation described in paragraphs (a)(1) or (a)(2) of this section if the manufacture, construction, or operation of a facility or activity, a basic component supplied for such facility or activity, or the design certification or design approval under part 52 of this chapter— (i) Fails to comply with the Atomic Energy Act of 1954, as amended, or any applicable rule, regulation, order, or license of the Commission or standard design approval under part 52 of this chapter, relating to a substantial safety hazard, or (ii) Contains a defect. (b) If the deviation or failure to comply is discovered by a supplier of basic components, or services associated with basic components, and the supplier determines that it does not have the capability to perform the evaluation to determine if a defect exists, then the supplier must inform the purchasers or affected licensees within five working days of this determination so that the purchasers or affected licensees may evaluate the deviation or failure to comply, pursuant to § 21.21(a). (c) A dedicating entity is responsible for— (1) Identifying and evaluating deviations and reporting defects and failures to comply associated with substantial safety hazards for dedicated items; and (2) Maintaining auditable records for the dedication process. (d)(1) A director or responsible officer subject to the regulations of this part or a person designated under § 21.21(d)(5) must notify the Commission when he or she obtains information reasonably indicating a failure to comply or a defect affecting— (i) The manufacture, construction or operation of a facility or an activity within the United States that is subject to the licensing requirements under parts 30, 40, 50, 52, 60, 61, 63, 70, 71, or 72 of this chapter and that is within his or her organization's responsibility; or (ii) A basic component that is within his or her organization's responsibility and is supplied for a facility or an activity within the United States that is subject to the licensing, design certification, or approval requirements under parts 30, 40, 50, 52, 60, 61, 63, 70, 71, or 72 of this chapter. (2) The notification to NRC of a failure to comply or of a defect under paragraph (d)(1) of this section and the evaluation of a failure to comply or a defect under paragraphs (a)(1) and (a)(2) of this section, are not required if the director or responsible officer has actual knowledge that the Commission has been notified in writing of the defect or the failure to comply. (3) Notification required by paragraph (d)(1) of this section must be made as follows— (i) Initial notification by facsimile, which is the preferred method of notification, to the NRC Operations Center at (301) 816-5151 or by telephone at (301) 816-5100 within two days following receipt of information by the director or responsible corporate officer under paragraph (a)(1) of this section, on the identification of a defect or a failure to comply. Verification that the facsimile has been received should be made by calling the NRC Operations Center. This paragraph does not apply to interim reports described in § 21.21(a)(2). (ii) Written notification to the NRC at the address specified in § 21.5 within 30 days following receipt of information by the director or responsible corporate officer under paragraph (a)(3) of this section, on the identification of a defect or a failure to comply. (4) The written report required by this paragraph shall include, but need not be limited to, the following information, to the extent known: (i) Name and address of the individual or individuals informing the Commission. (ii) Identification of the facility, the activity, or the basic component supplied for such facility or such activity within the United States which fails to comply or contains a defect. (iii) Identification of the firm constructing the facility or supplying the basic component which fails to comply or contains a defect. (iv) Nature of the defect or failure to comply and the safety hazard which is created or could be created by such defect or failure to comply. (v) The date on which the information of such defect or failure to comply was obtained. (vi) In the case of a basic component which contains a defect or fails to comply, the number and location of these components in use at, supplied for, being supplied for, or may be supplied for, manufactured, or being manufactured for one or more facilities or activities subject to the regulations in this part. (vii) The corrective action which has been, is being, or will be taken; the name of the individual or organization responsible for the action; and the length of time that has been or will be taken to complete the action. (viii) Any advice related to the defect or failure to comply about the facility, activity, or basic component that has been, is being, or will be given to purchasers or licensees. (ix) In the case of an early site permit, the entities to whom an early site permit was transferred. (5) The director or responsible officer may authorize an individual to provide the notification required by this paragraph, provided that, this shall not relieve the director or responsible officer of his or her responsibility under this paragraph. (e) Individuals subject to this part may be required by the Commission to supply additional information related to a defect or failure to comply. Commission action to obtain additional information may be based on reports of defects from other reporting entities." 10:10:1.0.1.1.17.0.78.10,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.31 Procurement documents.,NRC,,,"[60 FR 48374, Sept. 19, 1995]","Each individual, corporation, partnership, dedicating entity, or other entity subject to the regulations in this part shall ensure that each procurement document for a facility, or a basic component issued by him, her or it on or after January 6, 1978, specifies, when applicable, that the provisions of 10 CFR part 21 apply." 10:10:1.0.1.1.17.0.79.11,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.41 Inspections.,NRC,,,"[60 FR 48374, Sept. 19, 1995]","Each individual, corporation, partnership, dedicating entity, or other entity subject to the regulations in this part shall permit the Commission to inspect records, premises, activities, and basic components as necessary to accomplish the purposes of this part." 10:10:1.0.1.1.17.0.79.12,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.51 Maintenance and inspection of records.,NRC,,,"[56 FR 36090, July 31, 1991, as amended at 60 FR 48374, Sept. 19, 1995; 72 FR 49488, Aug. 28, 2007]","(a) Each individual, corporation, partnership, dedicating entity, or other entity subject to the regulations in this part shall prepare and maintain records necessary to accomplish the purposes of this part, specifically— (1) Retain evaluations of all deviations and failures to comply for a minimum of five years after the date of the evaluation; (2) Suppliers of basic components must retain any notifications sent to purchasers and affected licensees for a minimum of five years after the date of the notification. (3) Suppliers of basic components must retain a record of the purchasers of basic components for 10 years after delivery of the basic component or service associated with a basic component. (4) Applicants for standard design certification under subpart B of part 52 of this chapter and others providing a design which is the subject of a design certification, during and following Commission adoption of a final design certification rule for that design, shall retain any notifications sent to purchasers and affected licensees for a minimum of 5 years after the date of the notification, and retain a record of the purchasers for 15 years after delivery of design which is the subject of the design certification rule or service associated with the design. (5) Applicants for or holders of a standard design approval under subpart E of part 52 of this chapter and others providing a design which is the subject of a design approval shall retain any notifications sent to purchasers and affected licensees for a minimum of 5 years after the date of the notification, and retain a record of the purchasers for 15 years after delivery of the design which is the subject of the design approval or service associated with the design. (b) Each individual, corporation, partnership, dedicating entity, or other entity subject to the regulations in this part shall permit the Commission the opportunity to inspect records pertaining to basic components that relate to the identification and evaluation of deviations, and the reporting of defects and failures to comply, including (but not limited to) any advice given to purchasers or licensees on the placement, erection, installation, operation, maintenance, modification, or inspection of a basic component." 10:10:1.0.1.1.17.0.80.13,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.61 Failure to notify.,NRC,,,"[60 FR 48374, Sept. 19, 1995, as amended at 72 FR 49488, Aug. 28, 2007]","(a) Any director or responsible officer of an entity (including dedicating entity) that is not otherwise subject to the deliberate misconduct provisions of this chapter but is subject to the regulations in this part who knowingly and consciously fails to provide the notice required as by § 21.21 shall be subject to a civil penalty equal to the amount provided by section 234 of the Atomic Energy Act of 1954, as amended. (b) Any NRC licensee or applicant for a license (including an applicant for, or holder of, a permit), applicant for a design certification under part 52 of this chapter during the pendency of its application, applicant for a design certification after Commission adoption of a final design certification rule for that design, or applicant for or holder of a standard design approval under part 52 of this chapter subject to the regulations in this part who fails to provide the notice required by § 21.21, or otherwise fails to comply with the applicable requirements of this part shall be subject to a civil penalty as provided by Section 234 of the Atomic Energy Act of 1954, as amended. (c) The dedicating entity, pursuant to § 21.21(c) of this part, is responsible for identifying and evaluating deviations, reporting defects and failures to comply for the dedicated item, and maintaining auditable records of the dedication process. NRC enforcement action can be taken for failure to identify and evaluate deviations, failure to report defects and failures to comply, or failure to maintain auditable records." 10:10:1.0.1.1.17.0.80.14,10,Energy,I,,21,PART 21—REPORTING OF DEFECTS AND NONCOMPLIANCE,,,,§ 21.62 Criminal penalties.,NRC,,,"[57 FR 55071, Nov. 24, 1992]","(a) Section 223 of the Atomic Energy Act of 1954, as amended, provides for criminal sanctions for willful violation of, attempted violation of, or conspiracy to violate, any regulation issued under sections 161b, 161i, or 161o of the Act. For purposes of section 223, all the regulations in part 21 are issued under one or more of sections 161b, 161i, or 161o, except for the sections listed in paragraph (b) of this section. (b) The regulations in part 21 that are not issued under sections 161b, 161i, or 161o for the purposes of section 223 are as follows: §§ 21.1, 21.2, 21.3, 21.4 21.5, 21.7, 21.8, 21.61, and 21.62." 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 and continued airworthiness of a civil aeronautical product or article; (9) State of Manufacture means the country or jurisdiction having regulatory authority over the organization responsible for the production and airworthiness of a civil aeronautical product or article. (10) Supplier means a person at any tier in the supply chain who provides a product, article, or service that is used or consumed in the design or manufacture of, or installed on, a product or article." 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 the aircraft. (13) A failure or malfunction of more than one attitude, airspeed, or altitude instrument during a given operation of the aircraft. (d) The requirements of paragraph (a) of this section do not apply to— (1) Failures, malfunctions, or defects that the holder of a type certificate (including amended or supplemental type certificates), PMA, TSO authorization, or the licensee of a type certificate determines— (i) Were caused by improper maintenance or use; (ii) Were reported to the FAA by another person under this chapter; or (iii) Were reported under the accident reporting provisions of 49 CFR part 830 of the regulations of the National Transportation Safety Board. (2) Failures, malfunctions, or defects in products or articles— (i) Manufactured by a foreign manufacturer under a U.S. type certificate issued under § 21.29 or under an approval issued under § 21.621; or (ii) Exported to the United States under § 21.502. (e) Each report required by this section— (1) Must be made to the FAA within 24 hours after it has determined that the failure, malfunction, or defect required to be reported has occurred. However, a report that is due on a Saturday or a Sunday may be delivered on the following Monday and one that is due on a holiday may be delivered on the next workday; (2) Must be transmitted in a manner and form acceptable to the FAA and by the most expeditious method available; and (3) Must include as much of the following information as is available and applicable: (i) The applicable product and article identification information required by part 45 of this chapter; (ii) Identification of the system involved; and (iii) Nature of the failure, malfunction, or defect. (f) If an accident investigation or service difficulty report shows that a product or article manufactured under this part is unsafe because of a manufacturing or design data defect, the holder of the production approval for that product or article must, upon request of the FAA, report to the FAA the results of its investigation and any action taken or proposed by the holder of that production approval to correct that defect. If action is required to correct the defect in an existing product or article, the holder of that production approval must send the data necessary for issuing an appropriate airworthiness directive to the FAA." 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 planned IFSDs performed for flight training. (ii) For two-engine airplanes, IFSD rates. (iii) Inability to control an engine or obtain desired thrust or power. (iv) Precautionary thrust or power reductions. (v) Degraded ability to start an engine in flight. (vi) Inadvertent fuel loss or unavailability, or uncorrectable fuel imbalance in flight. (vii) Turn backs or diversions for failures, malfunctions, or defects associated with an ETOPS group 1 significant system. (viii) Loss of any power source for an ETOPS group 1 significant system, including any power source designed to provide backup power for that system. (ix) Any event that would jeopardize the safe flight and landing of the airplane on an ETOPS flight. (x) Any unscheduled engine removal for a condition that could result in one of the reportable occurrences listed in this paragraph. (b) Reliability of two-engine airplanes —(1) Reporting of two-engine airplane in-service reliability. The holder of a type certificate for an airplane approved for ETOPS and the holder of a type certificate for an engine installed on an airplane approved for ETOPS must report monthly to their respective Aircraft Certification Service office on the reliability of the world fleet of those airplanes and engines. The report provided by both the airplane and engine type certificate holders must address each airplane-engine combination approved for ETOPS. The FAA may approve quarterly reporting if the airplane-engine combination demonstrates an IFSD rate at or below those specified in paragraph (b)(2) of this section for a period acceptable to the FAA. This reporting may be combined with the reporting required by § 21.3. The responsible type certificate holder must investigate any cause of an IFSD resulting from an occurrence attributable to the design of its product and report the results of that investigation to its responsible Aircraft Certification Service office. Reporting must include: (i) Engine IFSDs, except planned IFSDs performed for flight training. (ii) The world fleet 12-month rolling average IFSD rates for all causes, except planned IFSDs performed for flight training. (iii) ETOPS fleet utilization, including a list of operators, their ETOPS diversion time authority, flight hours, and cycles. (2) World fleet IFSD rate for two-engine airplanes. The holder of a type certificate for an airplane approved for ETOPS and the holder of a type certificate for an engine installed on an airplane approved for ETOPS must issue service information to the operators of those airplanes and engines, as appropriate, to maintain the world fleet 12-month rolling average IFSD rate at or below the following levels: (i) A rate of 0.05 per 1,000 world-fleet engine-hours for an airplane-engine combination approved for up to and including 120-minute ETOPS. When all ETOPS operators have complied with the corrective actions required in the configuration, maintenance and procedures (CMP) document as a condition for ETOPS approval, the rate to be maintained is at or below 0.02 per 1,000 world-fleet engine-hours. (ii) A rate of 0.02 per 1,000 world-fleet engine-hours for an airplane-engine combination approved for up to and including 180-minute ETOPS, including airplane-engine combinations approved for 207-minute ETOPS in the North Pacific operating area under appendix P, section I, paragraph (h), of part 121 of this chapter. (iii) A rate of 0.01 per 1,000 world-fleet engine-hours for an airplane-engine combination approved for ETOPS beyond 180 minutes, excluding airplane-engine combinations approved for 207-minute ETOPS in the North Pacific operating area under appendix P, section I, paragraph (h), of part 121 of this chapter." 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 that— (i) The aircraft complies with those applicable airworthiness requirements approved under § 21.17(f) of this part; and (ii) The aircraft has no feature or characteristic that makes it unsafe for its intended use. (b) An applicant may include a special inspection and preventive maintenance program as part of the aircraft's type design or supplemental type design. (c) For aircraft manufactured outside of the United States in a country with which the United States has a bilateral airworthiness agreement for the acceptance of these aircraft, and from which the aircraft is to be imported into the United States— (1) The statement required by paragraph (a)(2)(i) of this section must be made by the civil airworthiness authority of the exporting country; and (2) The required manuals, placards, listings, instrument markings, and documents required by paragraphs (a) and (b) of this section must be submitted in English." 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) Powerlines; (iii) Data transmission lines and towers; (iv) Railroads; (v) Canals; or (vi) Harbors. (5) Weather control, including the special purpose operation of cloud seeding. (6) Aerial advertising, for one or more of the following special purpose operations, including— (i) Skywriting; (ii) Banner towing; (iii) Displaying airborne signs; or (iv) Public address systems. (7) Other special purpose operations, including— (i) Rotorcraft external-load operations conducted under part 133 of this chapter; (ii) Carriage of cargo incidental to the owner's or operator's business; (iii) Target towing; (iv) Search and rescue operations; (v) Glider towing; (vi) Alaskan fuel hauling; (vii) Alaskan fixed-wing external load operations; (viii) Space vehicle launch; or (ix) Any other special purpose operation specified by the FAA." 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 paragraphs (b) through (e) of this section, an applicant for a type certificate under this section must comply with the appropriate regulations listed in the following table: 1 Where no specific date is listed, the applicable regulations are those in effect on the date that the first aircraft of the particular model was accepted for operational use by the Armed Forces." 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 airworthiness standards of this subchapter, or an equivalent level of safety, with which compliance is certified under paragraph (a)(1)(ii) of this section." 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 meaningless or that would make further testing unduly hazardous. (f) The flight tests prescribed in paragraph (b)(2) of this section must include— (1) For aircraft incorporating turbine engines of a type not previously used in a type certificated aircraft, at least 300 hours of operation with a full complement of engines that conform to a type certificate; and (2) For all other aircraft, at least 150 hours of operation." 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: (i) The failure of the commercial part, as installed in the product, would not degrade the level of safety of the product; and (ii) The part is produced only under the commercial part manufacturer's specification and marked only with the commercial part manufacturer's markings; and (3) Any other data necessary for the FAA to approve the List." 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 earlier than the date which precedes the date of issue of the type certificate by the time limit established under paragraph (c) of this section for the original application. (e) If an applicant elects to comply with an amendment to this subchapter that is effective after the filing of the application for a type certificate, he must also comply with any other amendment that the FAA finds is directly related. (f) For primary category aircraft, the requirements are: (1) The applicable airworthiness requirements contained in parts 23, 27, 31, 33, and 35 of this subchapter, or such other airworthiness criteria as the FAA may find appropriate and applicable to the specific design and intended use and provide a level of safety acceptable to the FAA. (2) The noise standards of part 36 applicable to primary category aircraft." 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 the case of an amendment to a provisional type certificate, the FAA may reduce the number of required flight hours." 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 safely under the appropriate operating limitations in this subchapter. (g) The applicant must submit a report showing that the aircraft has been flown in all maneuvers necessary to show compliance with the flight requirements for the issue of the type certificate and to establish that the aircraft can be operated safely in accordance with the limitations in this subchapter. (h) The applicant must prepare a provisional aircraft flight manual containing all limitations required for the issue of the 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. (i) The applicant must establish an inspection and maintenance program for the continued airworthiness of the aircraft. (j) The applicant must show that a prototype aircraft has been flown for at least 100 hours. In the case of an amendment to a provisional type certificate, the FAA may reduce the number of required flight hours." 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 requirements applicable to those modifications and to establish that the aircraft can be operated safely in accordance with the limitations specified in §§ 91.317 and 121.207 of this chapter. (g) The applicant must establish and publish, in a provisional aircraft flight manual or other document and on appropriate placards, all limitations required for the issue of the type certificate applied for, including weight, speed, flight maneuvers, loading, and operation of controls and equipment, unless, for each limitation not so established, appropriate operating restrictions are established for the aircraft. (h) The applicant must establish an inspection and maintenance program for the continued airworthiness of the aircraft. (i) The applicant must operate a prototype aircraft modified in accordance with the corresponding amendment to the type certificate for the number of hours found necessary by the FAA." 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 § 36.1583 of this chapter does not apply, or (iii) U.S. registered, and that had flight time prior to January 1, 1955 or (iv) Land configured aircraft reconfigured with floats or skis. This reconfiguration does not permit further exception from the requirements of this section upon any acoustical change not enumerated in § 21.93(b). (4) Helicopters except: (i) Those helicopters that are designated exclusively: (A) For “agricultural aircraft operations”, as defined in § 137.3 of this chapter, as effective on January 1, 1966; (B) For dispensing fire fighting materials; or (C) For carrying external loads, as defined in § 133.1(b) of this chapter, as effective on December 20, 1976. (ii) Those helicopters modified by installation or removal of external equipment. For purposes of this paragraph, “external equipment” means any instrument, mechanism, part, apparatus, appurtenance, or accessory that is attached to, or extends from, the helicopter exterior but is not used nor is intended to be used in operating or controlling a helicopter in flight and is not part of an airframe or engine. An “acoustical change” does not include: (A) Addition or removal of external equipment; (B) Changes in the airframe made to accommodate the addition or removal of external equipment, to provide for an external load attaching means, to facilitate the use of external equipment or external loads, or to facilitate the safe operation of the helicopter with external equipment mounted to, or external loads carried by, the helicopter; (C) Reconfiguration of the helicopter by the addition or removal of floats and skis; (D) Flight with one or more doors and/or windows removed or in an open position; or (E) Any changes in the operational limitations placed on the helicopter as a consequence of the addition or removal of external equipment, floats, and skis, or flight operations with doors and/or windows removed or in an open position. (5) Tiltrotors. (c) For purposes of complying with part 34 of this chapter, any voluntary change in the type design of the airplane or engine which may increase fuel venting or exhaust emissions is an “emissions change.” (d) For the purpose of maintaining compliance with part 38 of this chapter, any voluntary change in the type design of an airplane that may increase the fuel efficiency metric value or the MTOM of that airplane is a “fuel efficiency change”, in addition to being a minor or major change as classified in paragraph (a) of this section." 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."