(c) At the end of the six-month interval, the FAA will advise the manufacturer whether the inspection system is considered acceptable. If considered acceptable, as determined by evaluating the results of the system as reflected in the conformity, quality, and airworthiness of the finished products, the FAA will thereafter reduce its inspection surveillance and increase its reliance on the manufacturer's inspection system in the determination of the airworthiness of future products.

(1) Upon approval of the production inspection system, the manufacturer may nominate one or more of his employees for appointment as a Designated Manufacturing Inspection Representative, in accordance with Part 418 of Chapter III of this title (Regulations of the Administrator). If the nominee meets the requirements for appointment, he will be authorized by the FAA to issue original airworthiness and/or export certificates for the products produced which are found to conform with the approved type design data; to conduct station and conformity inspections; and to make such additional examinations as may be necessary to ascertain that production articles are airworthy and safe for operation. Such authorization is limited to the manufacturing plant in which the designee is employed.

(d) If the inspection system is not acceptable, as evidenced by questionable parts and materials accepted for installation in the finished product, or significant discrepancies are repeatedly found in the finished products, the issuance of airworthiness certificates for aircraft, or approvals of other products for installation on an aircraft, will be deferred until the manufacturer has made necessary corrective changes. [CAM 1 Rev., 21 F. R. 8799, Nov. 14, 1956] § 1.16

Duration.

§ 1.18 Privileges.

The holder or licensee of a type certificate for a product may, in the case of aircraft, obtain airworthiness certificates (see applicable §§ 1.60 through 1.72), or in the case of engines, propellers, or other products, obtain approval for installation on certificated aircraft; he may obtain a production certificate for such products (see §§ 1.30 through 1.46).

§ 1.19 Statement of conformity.

(a) The holder of a type certificate only or of a current right to the benefits of a type certificate only under a licensing arrangement, upon the initial transfer by him of the ownership of any product manufactured under such type certificate or upon application for original issuance of an airworthiness certificate for an aircraft, shall furnish to an authorized representative of the Administrator a statement of conformity for such product on a form prescribed by the Administrator. For aircraft manufactured under a type certificate only, there shall be included a statement that the aircraft referred to has been flight checked. For aircraft engines and for variable pitch propellers manufactured under a type certificate only, there shall be included a statement that the engine or propeller referred to has been subjected by the manufacturer to a final operational check. When a production certificate is held in addition to the type certificate, the provisions of § 1.35 shall apply. The Administrator may consider military acceptance in lieu of a statement of conformity for a product which has been manufactured for the military service.

(b) A statement of conformity shall be furnished to an authorized representative of the Administrator, upon a form and in a manner prescribed by the Administrator, for any prototype product presented for type certification.

§ 1.19-1 Statement of conformity (FAA rules which apply to § 1.19 (a)).

(a) A Statement of Conformity, Form ACA 317,5 shall be signed by a person who holds a responsible position in the manufacturer's organization and who has been authorized to perform this function by the holder of the type certificate or licensing agreement.

The reporting requirements of this form are subject to the approval of the Bureau of the Budget in accordance with the Federal Reports Act of 1942.

When the type design is changed, the applicant shall demonstrate that the product complies with the requirements of that part of the regulations in this subchapter under which it was certificated.

§ 1.20-1 Changes in type design (FAA policies which apply to § 1.20).

Any design change which may affect the flight characteristics, structural integrity, or airworthiness of an aircraft, engine, propeller, or appliance for which a type certificate has been issued may require the submission of additional technical data. The examination of these data may indicate the necessity for additional engineering evaluation, inspection, and tests to substantiate the airworthiness of the product as modified. [CAM 1 Rev., 21 F. R. 8800, Nov. 14, 1956] § 1.21 Classification of changes.

Changes shall be classified as minor and major. A minor change shall be one which has no appreciable effect on the weight, balance, structural strength, reliability, operational characteristics, or other characteristics affecting the airworthiness of the product. A major change shall be one not classified as a minor change.

§ 1.22 Approval of minor changes.

Minor changes in a type design may be approved in accordance with a method acceptable to the Administrator prior to the submittal to the Administrator of any substantiating or descriptive data. § 1.23 Approval of major changes.

Major changes in a type design shall be approved only after receipt by the Administrator of substantiating data and necessary descriptive data for inclusion in the type design.

ба

ucts of the same type design, he shall provide notice 5 thereof for all operators of products of that type, and the product shall not thereafter be operated until the unsafe condition has been corrected, unless otherwise authorized by the Administrator under specified conditions and limitations, including inspections. In addition, the provisions of subparagraphs (1) and (2) of this paragraph shall apply.

(1) When the Administrator finds that design changes are necessary to correct the unsafe condition of the product, the holder of the type certificate, upon request of the Administrator, shall submit appropriate design changes for the approval of the Administrator.

(2) Upon approval, the descriptive data covering the changes shall be made available by the holder of the type certificate to all operators of products previously certificated under such type certificate.

(b) Where no current unsafe condition exists but the Administrator 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 the approval of the Administrator. Upon approval of such changes the manufacturer shall make available to all operators of the same type of product information on the design changes.

SUPPLEMENTAL TYPE CERTIFICATES

§ 1.25 Supplemental type certificates.

When a person, other than the holder of the type certificate for a product, alters the product by introducing a major change (see § 1.21) in a previously approved type design, and the change is not so extensive as to require application for a new type certificate (see §§ 3.11 (e), 4b.11 (e), 5.11 (e), 6.11 (e), 13.11 (e), and 14.11 (e) of this chapter), such person shall apply for the issuance of a supplemental type certificate covering the design change. The application shall be made upon a form and in a manner prescribed by the Administrator.

Ba Notification of any unsafe condition, of the required corrective action, and of compliance dates is usually provided through the medium of Airworthiness Directives issued by the Administrator.

§ 1.25-1

Application for a supplemental type certificate (FAA policies which apply to § 1.25).

(a) Applicant. A supplemental type certificate may be issued to more than one applicant for the same design change provided each applicant shows compliance with the applicable airworthiness requirements in accordance with § 1.26. (See § 1.28-1.)

(b) Form and manner of application. The applicant should complete three copies of Form ACA-2417 and submit them to the local FAA Aviation safety agent. The drawings and technical data substantiating compliance with the applicable airworthiness requirements should also be submitted for approval in accordance with § 1.27-1.

[CAM 1 Rev., 21 F. R. 8800, Nov. 14, 1956] § 1.26 Applicable requirements.

The applicant for a supplemental type certificate shall demonstrate that the altered product meets the airworthiness requirements which are applicable to the product involved (see §§ 3.11(d), 4b.11 (d), 5.11(d), 6.11(d), 13.11(d), and 14.11 (d) of this chapter).

§ 1.26-1 Airworthiness

requirements

(FAA policies which apply to § 1.26). The methods used to show compliance with the applicable airworthiness requirements are the same as those used for original type certification; namely, by preparing drawings, stress analysis, and by conducting ground and flight tests and preparing reports thereon. Acceptable methods of showing compliance are outlined in Civil Aeronautics Manuals 3 and 4b.

[CAM 1 Rev., 21 F. R. 8800, Nov. 14, 1956] § 1.27 Requirements for issuance.

Upon receipt of an application and a satisfactory demonstration of compliance with the applicable requirements

• Examples of the types of changes defined in § 1.21 as major design changes are contained in § 18.1-1 of this chapter and of Civil Aeronautics Manual 18. A change in the empty weight or balance is not a major design change unless an increase in the maximum weight, center of gravity limits, or other factors listed in the definition of a major change are also involved.

Detailed information on the applicable airworthiness requirements used for the original type certification of the product involved may be obtained from the Federal Aviation Agency.

in accordance with §§ 1.25 and 1.26, the Administrator shall indicate approval of the change in type design. Such approval together with the previously issued type certificate for the product shall constitute a supplemental type certificate.

§ 1.27-1 Procedures for obtaining approval (FAA policies which apply to § 1.27).

FAA approval of a major change in type design is based upon examination of the supporting data, conducting or reviewing tests, inspection of the altered product, and a finding by the FAA that the applicable requirements are met. Such approval involves two steps:

(a) Design examination. Approval of the technical supporting data describing the design change and showing compliance with the applicable airworthiness requirements should be obtained from one of the following:

(1) A FAA Designated Engineering Representative (DER). After DER approval of the data, the DER will complete, sign, and send Form ACA-1600 "Statement of Compliance of Aircraft or Aircraft Components with the Civil Air Regulations," to the regional FAA Aircraft Engineering Division. Whereas a DER's authority may be limited to certain areas, the DER should indicate on Form ACA-1600 whether any additional areas require FAA approval. On a complex project the DER should contact the appropriate FAA Aircraft Engineering office as early as possible.

(2) The FAA. The technical data describing and substantiating the design change should be submitted to the local FAA Aviation Safety Agent for forwarding to the FAA regional office. When necessary, arrangements should be made with FAA for completing any flight or ground testing required by the applicable airworthiness requirements, and the reports of such tests should be included in the technical data pertaining to the design change.

(3) A Designated Manufacturer's Certification Representative (DMCR). If the aircraft was originally certificated under the Delegation Option Procedures of Part 410 of this title (Regulations of the Administrator, ref. § 410.37), a copy of the DMCR's approval letter should be included with the supporting data.

(b) Inspection of the product. A new design change normally requires an inspection of a modified article by an FAA

representative in order to establish compliance with the applicable airworthiness requirements. See § 1.15. In the case of a complex modification program involving FAA flight tests, the FAA will conduct the appropriate portions of a standard type inspection.

[CAM 1 Rev., 21 F. R. 8800, Nov. 14, 1956]

§ 1.27-2 Issuance and recording of supplemental type certificates (FAA policies which apply to § 1.27).

(a) Issuance. When the design examination and inspection described in § 1.27-1 have been satisfactorily completed, the FAA will approve the change in type design by completing Form ACA2417. This form, signed by the Chief, Aircraft Engineering Division, FAA Regional Office, or other person authorized to perform this function, will constitute the supplemental type certificate for the change in type design.

(b) Recording and disposition of supplemental type certificates. One signed copy of Form ACA-2417 will be given a number and returned to the applicant; one copy will be retained in the issuing FAA regional office; and one copy will be sent to the FAA Washington office for use in publishing a summary list of supplemental type certificates. Technical

data submitted with the application will be filed in the FAA regional office. [CAM 1 Rev., 21 F. R. 8800, Nov. 14, 1956]

The holder or licensee of a supplemental type certificate for an altered product may, in the case of aircraft, obtain airworthiness certificates (see applicable §§ 1.60 through 1.72), or in the case of engines, propellers, or other products, obtain approval for installation on certificated aircraft; he may obtain a production certificate (see §§ 1.30 through 1.46) with respect to the change in the type design for which approval was obtained in accordance with § 1.27.

NOTE: The provisions of this section are not intended to affect in any way the proprietary rights of the holder of a type certificate or of a supplemental type certificate. § 1.28-1 Airworthiness certification or approval of modified aircraft or products (FAA policies which apply to § 1.28).

(a) After a supplemental type certificate has been issued in accordance with § 1.27-2, airworthiness certificates for aircraft, or approval for products incor

porating the design change may be issued on the basis of an inspection for conformity with the approved data conducted in accordance with § 1.67 or § 18.11 of this subchapter.

(b) The privileges specified in § 1.28 also apply to approvals of major design changes issued prior to August 25, 1955, the effective date of § 1.28. Such approvals are indicated on a Major Repair and Alteration Form ACA-337, air carriers' records, or listed on the FAA Aircraft Specification for the product involved.

8

Any person, whether or not a citizen of the United States, may apply for the issuance of a production certificate The application for a production certificate shall be made upon a form and in a manner prescribed by the Administrator. § 1.30-1 Application for a production certificate (FAA rules which apply to § 1.30).

The applicant for a production certificate shall submit to the appropriate FAA regional office, an application file consisting of the following:

(a) Original and one copy, properly completed, of Application for Production Certificate, Form ACA-332. (This form

'An aircraft specification is a document prepared by the Federal Aviation Agency in support of a type certificate to set forth the type design, the operating limitations, and any other conditions or limitations prescribed by the Civil Air Regulations for a specific type of aircraft. FAA Aircraft Specifications are available free of charge from the Federal Aviation Agency, Aviation Information, W-47, Washington 25, D.C.

'The issuance of the production certificate automatically places greater responsibility in the manufacturer and obviates the requirement for a Statement of Conformity, Form ACA-317, for products produced under the terms of a production certificate, whether for domestic or export certification (see § 1.35). The production certificate is an indication that all major groups of a company are adequately contributing to the production of a quality product; that the quality control (or inspection) department is employing sound principles and procedures in determining and controlling the quality of raw materials, purchased equipment, detall parts and assemblies throughout all phases of manufacture to assure structural and functional conformity of the completed product to approved type design data.

may be obtained from the local FAA Aviation Safety Agent or the appropriate FAA regional office.) Regional office addresses and the states under their jurisdiction are listed in the appendix this manual.

10

to

(b) One copy of the applicant's quality control data," as required by § 1.36. [CAM 1 Rev., 21 F. R. 8800, Nov. 14, 1956] § 1.30-2 Processing application (FAA policies which apply to § 1.30).

(a) Upon receipt of an application file, the FAA will examine it and, if it is considered satisfactory, establish a Production Certification Board " to inspect the applicant's facilities and determine their adequacy for the production of duplicates of the product. If the application file is not considered satisfactory, the FAA will request the applicant to furnish additional information or data. [CAM 1 Rev., 21 F. R. 8800, Nov. 14, 1956] § 1.31 Products for which issued.

A production certificate shall be issued only for products for which a type certificate is currently in effect. The applicant shall hold a currently effective type certificate for the product to be manufactured or shall hold a current right to the benefits of such certificate under a licensing agreement.

10 Not filled with the Office of the Federal Register.

" When the holder of a currently effective production certificate applies for extension of the certifiate to cover other type certifcated products in the same general category, only such additional quality control data as may be necessary to cover those new procedures, methods, or processes required by the new product, need be submitted. If no change is necessary, appropriate notation will be made on the application form. For additional information, see § 1.41-1.

12 The Production Certification Board reviews the quality control data, establishes procedures for conducting the inspection of the applicant's facilities, advises applicant of any controversial or marginal conditions pertaining to the quality control data, and related regulations, interpretations, and policies governing the issuance and continuation of a production certificate. After the inspection has been conducted, the Board will discuss with the applicant any decisions reached on marginal or controversial items in an effort to arrive at a satisfactory solution.

The Board will also function in special cases of a major nature involving an annual or interim inspection, to determine continued eligibility of the manufacturing facilities under the terms of the production certificate.

§ 1.32

Requirements for issuance.

A person shall be issued a production certificate when the Administrator finds, after examination of the supporting data and after inspection of the organization and production facilities, that the applicant complies with the requirements of §§ 1.33 through 1.36.

§ 1.32-1 Production

re

certification quirements (FAA policies which apply to § 1.32).

The provisions set forth in paragraphs (a) through (f) of this section 13 are the minimums which the manufacturer should have established to be eligible for a production certificate.

(a) Purchasing. The purchase orders for raw stock and parts should be based on approved specifications or other information which will assure the receipt of materials and parts that will be suitable for aircraft construction and meet the design requirements for the product. The specifications and other data should be sufficiently detailed and comprehensive to insure procurement of materials and parts of a uniformly high grade, equaling or exceeding the minimum strength properties in the structural design data. The applicant may use parts, components, and assemblies over which he does or does not have design control, which are fabricated by vendors. either case, the prime manufacturer (applicant) is responsible for the airworthiness of the completed product and all of its components, and he should establish procedures and methods to assure that the completed product will be structurally sound, safe for operation, and in conformity with approved design data. These procedures may provide for vendors' and suppliers' affidavits and inspection reports in lieu of extensive tests and inspections by the applicant.

In

(b) Receiving. The applicant should have a receiving system and facilities which will provide for the identification, storage, and routing of raw materials, parts, components, and assemblies obtained from vendors and suppliers. This system should provide for the mating of the incoming items with the purchase orders, specifications, or other procurement data so that receiving inspection will be apprised of the requirements and details under which the items were pur

13 The assigned FAA Aviation Safety Agents will use this section as a guide in conducting the factory inspection.