14 C.F.R. Subpart F—Production Under Type Certificate Only
Title 14 - Aeronautics and Space
Source: Docket No. 5085, 29 FR 14568, Oct. 24, 1964, unless otherwise noted.
This subpart prescribes rules for production under a type certificate only. Each manufacturer of a product being manufactured under a type certificate only shall— (a) Make each product available for inspection by the Administrator; (b) Maintain at the place of manufacture the technical data and drawings necessary for the Administrator to determine whether the product and its parts conform to the type design; (c) Except as otherwise authorized by the Aircraft Certification Directorate Manager for the geographic area which the manufacturer is located, for products manufactured more than 6 months after the date of issue of the type certificate, establish and maintain an approved production inspection system that insures that each product conforms to the type design and is in condition for safe operation; and (d) Upon the establishment of the approved production inspection system (as required by paragraph (c) of this section) submit to the Administrator a manual that describes that system and the means for making the determinations required by §21.125(b). [Doc. No. 5085, 29 FR 14568, Oct. 24, 1964, as amended by Amdt. 21–34, 35 FR 13008, Aug. 15, 1970; Amdt. 21–51, 45 FR 60170, Sept. 11, 1980; Amdt. 21–67, 54 FR 39291, Sept. 25, 1989] (a) Each manufacturer required to establish a production inspection system by §21.123(c) shall— (1) Establish a Materials Review Board (to include representatives from the inspection and engineering departments) and materials review procedures; and (2) Maintain complete records of Materials Review Board action for at least two years. (b) The production inspection system required in §21.123(c) must provide a means for determining at least the following: (1) Incoming materials, and bought or subcontracted parts, used in the finished product must be as specified in the type design data, or must be suitable equivalents. (2) Incoming materials, and bought or subcontracted parts, must be properly identified if their physical or chemical properties cannot be readily and accurately determined. (3) Materials subject to damage and deterioration must be suitably stored and adequately protected. (4) Processes affecting the quality and safety of the finished product must be accomplished in accordance with acceptable industry or United States specifications. (5) Parts and components in process must be inspected for conformity with the type design data at points in production where accurate determinations can be made. (6) Current design drawings must be readily available to manufacturing and inspection personnel, and used when necessary. (7) Design changes, including material substitutions, must be controlled and approved before being incorporated in the finished product. (8) Rejected materials and parts must be segregated and identified in a manner that precludes installation in the finished product. (9) Materials and parts that are withheld because of departures from design data or specifications, and that are to be considered for installation in the finished product, must be processed through the Materials Review Board. Those materials and parts determined by the Board to be serviceable must be properly identified and reinspected if rework or repair is necessary. Materials and parts rejected by the Board must be marked and disposed of to ensure that they are not incorporated in the final product. (10) Inspection records must be maintained, identified with the completed product where practicable, and retained by the manufacturer for at least two years. (a) Each person manufacturing aircraft under a type certificate only shall establish an approved production flight test procedure and flight check-off form, and in accordance with that form, flight test each aircraft produced. (b) Each production flight test procedure must include the following: (1) An operational check of the trim, controllability, or other flight characteristics to establish that the production aircraft has the same range and degree of control as the prototype aircraft. (2) An operational check of each part or system operated by the crew while in flight to establish that, during flight, instrument readings are within normal range. (3) A determination that all instruments are properly marked, and that all placards and required flight manuals are installed after flight test. (4) A check of the operational characteristics of the aircraft on the ground. (5) A check on any other items peculiar to the aircraft being tested that can best be done during the ground or flight operation of the aircraft. (a) Each person manufacturing aircraft engines under a type certificate only shall subject each engine (except rocket engines for which the manufacturer must establish a sampling technique) to an acceptable test run that includes the following: (1) Break-in runs that include a determination of fuel and oil consumption and a determination of power characteristics at rated maximum continuous power or thrust and, if applicable, at rated takeoff power or thrust. (2) At least five hours of operation at rated maximum continuous power or thrust. For engines having a rated takeoff power or thrust higher than rated maximum continuous power or thrust, the five-hour run must include 30 minutes at rated takeoff power or thrust. (b) The test runs required by paragraph (a) of this section may be made with the engine appropriately mounted and using current types of power and thrust measuring equipment. [Doc. No. 5085, 29 FR 14568, Oct. 24, 1964, as amended by Amdt. 21–5, 32 FR 3735, Mar. 4, 1967] Each person manufacturing propellers under a type certificate only shall give each variable pitch propeller an acceptable functional test to determine if it operates properly throughout the normal range of operation. Each holder or licensee of a type certificate only, for a product manufactured in the United States, shall, upon the initial transfer by him of the ownership of such product manufactured under that type certificate, or upon application for the original issue of an aircraft airworthiness certificate or an aircraft engine or propeller airworthiness approval tag (FAA Form 8130–3), give the Administrator a statement of conformity (FAA Form 317). This statement must be signed by an authorized person who holds a responsible position in the manufacturing organization, and must include— (a) For each product, a statement that the product conforms to its type certificate and is in condition for safe operation; (b) For each aircraft, a statement that the aircraft has been flight checked; and (c) For each aircraft engine or variable pitch propeller, a statement that the engine or propeller has been subjected by the manufacturer to a final operational check. However, in the case of a product manufactured for an Armed Force of the United States, a statement of conformity is not required if the product has been accepted by that Armed Force. [Amdt. 21–25, 34 FR 14068, Sept. 5, 1969]
Title 14: Aeronautics and Space
PART 21—CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS
Subpart F—Production Under Type Certificate Only
§ 21.121 Applicability.
§ 21.123 Production under type certificate.
§ 21.125 Production inspection system: Materials Review Board.
§ 21.127 Tests: aircraft.
§ 21.128 Tests: aircraft engines.
§ 21.129 Tests: propellers.
§ 21.130 Statement of conformity.
