4

test time will be recorded on the flight test check-off form. It need not be made a part of the aircraft or aircraft engine logbooks.

[CAM 1 Rev., 21 F. R. 8798, Nov. 14, 1956]

§ 1.15-4 Production inspection system (CAA rules which apply to § 1.15 (d))-(a) General. The production inspection system established in compliance with § 1.15 shall thereafter be maintained to assure that parts, assemblies, and the completed products are in conformity with approved type design data and are in condition for safe operation. The inspection system established shall be adequate to preclude the installation of unacceptable materials and parts in the finished product. (Statistical quality control procedures may be employed where it is shown that a satisfactory level of quality will be maintained for the particular materials or parts involved.)

The

(b) Materials review. The production inspection system shall include materials review procedures and a Materials Review Board to process parts and materials withheld because of departure from design data or specifications, but which may be serviceable, when such withheld items are to be considered for installation in the product. (See § 1.34-2 (a) (5) and (6) for procedures.) Materials Review Board shall consist at least of representatives from the inspection and engineering departments. Parts and materials which are determined by the Materials Review Board to be serviceable shall be properly identified and reinspected if rework or repair is necessary. Parts or materials rejected by the Materials Review Board, or by inspection, shall be marked accordingly and disposed of in a manner which will prevent such parts and materials from being incorporated in the finished product.

(c) Inspection records. Adequate inspection records shall be maintained, identified with the completed product where practicable, and retained in the manufacturer's files for at least two years after the product is completed. Complete records of Materials Review Board action applying to materials, parts, assemblies, and the completed product,

• All other flight test time, including accelerated service flight testing of prototype or modified aircraft after airworthiness certification, must be recorded in accordance with § 43.23 of this subchapter.

shall be retained for at least two years, and available for review by CAA representatives.

(d) Complete aircraft. (1) After the prototype is type certificated, each additional aircraft produced under the terms of a type certificate only shall be flight tested by the manufacturer as a final check on the operation of the completed product. The manufacturer shall develop a production flight test procedure and a flight check-off form, subject to CAA approval, to be used in connection with the initial flight testing of each production aircraft. The flight test procedure shall apply to aircraft to be flown, or delivered disassembled to an authorized distributor.

(2) The production flight test shall provide for at least the following:

(i) An operational check of the trim, controllability, or other flight characteristics to establish the fact that the production aircraft has the same range and degree of control as the prototype aircraft.

(ii) An operational check of each part or system operated by the crew while in flight to establish that, during flight, all instrument readings are within normal range.

(iii) A determination that all instruments are properly marked, and that all placards and/or required flight manuals are installed after flight test.

(iv) A check of the operational characteristics of the aircraft on the ground.

(v) A check on any other items peculiar to the aircraft being tested which can best be done during the ground or flight operation of the aircraft.

(e) Complete engines. Each engine, either reciprocating or turbine, produced under the terms of a type certificate only, shall be subjected to a satisfactory test run by the manufacturer, consisting of break-in runs which shall include a determination of fuel and oil consumption and maximum power characteristics. The test run shall include at least five hours of operation at the maximum rating, of which at least thirty minutes shall be at takeoff power and speed where this rating is in excess of the maximum continuous rating. These tests may be conducted with the engine appropriately mounted and utilizing current types of power and/or thrust measuring equipment (i. e., integral torque meter, thrust meter, dynamometer, calibrated test club

or propeller, reaction stand, etc.). For rocket type engines, a satisfactory sampling technique means of testing shall be established. Each engine tested shall be subject to the inspection provided for in § 1.15-1 (b) (2).

(f) Complete propellers. Each variable pitch propeller produced under the terms of a type certificate only, shall be subjected to a satisfactory functional test to determine that the propeller will operate properly throughout the normal range of operation, as a final check on its operational characteristics. Each propeller tested shall be subject to the inspection provided for in § 1.15-1 (b) (3).

[CAM 1 Rev., 21 F. R. 8798, Nov. 14, 1956]

§ 1.15-5 Production inspection system standards (CAA policies which apply to § 1.15 (d)). The inspection system should provide for at least the following:

(a) That all incoming materials and purchased or subcontracted parts used in the finished product are as specified in the type design data, or are suitable equivalents.

(b) That all incoming materials and purchased or subcontracted parts are properly identified, when the physical and chemical properties cannot be readily and accurately determined.

(c) That all materials subject to damage and deterioration are suitably stored and adequately protected.

(d) That all processes affecting the quality and safety of the finished product are accomplished in accordance with established industry or government specifications.

(e) That parts and components in process are inspected for conformity with type design data at points in production where accurate determinations can be made.

(f) That current design drawings are readily available to manufacturing and inspection personnel, and used when necessary.

(g) That design changes, including material substitutions, are controlled and approved before being incorporated in the finished product.

(h) That rejected materials and parts are segregated and identified in such a manner as to preclude installation in the finished product.

(i) That materials and parts withheld because of departures from design data

or specifications, which are to be considered for installation in the finished product, are processed through established materials review procedures (see § 1.15-4 (b)).

(j) That inspection records are maintained (see § 1.15-4 (c)).

(k) That an acceptable flight test procedure and flight test check-off list are provided in the case of aircraft (see § 1.15-4 (d)).

[CAM 1 Rev., 21 F. R. 8799, Nov. 14, 1956]

§ 1.15-6 Surveillance of production inspection system (CAA policies which apply to § 1.15 (d)). (a) During the six month interval pending the establishment of the manufacturer's production inspection system, the CAA will conduct inspections to ascertain that the finished product is in conformity with the type design data, is airworthy, safe for installation on certificated aircraft, or, in the case of aircraft, is eligible for an airworthiness certificate.

(b) Materials review dispositions will be spot checked by a representative of the Administrator to verify that no obvious adverse effect will result from such dispositions.

(c) At the end of the six-month interval, the CAA 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 CAA 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 II of this title (Regulations of the Administrator). If the nominee meets the requirements for appointment, he will be authorized by the CAA 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 op

eration. 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. A type certificate shall remain in effect until surrendered, suspended, revoked, or a termination date is otherwise established by the Board.

1.17 Display. Туре certificates shall be made available for examination by an authorized representative of the Board or of the Administrator.

§ 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).

(a)

§ 1.19 Statement of conformity. 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 (CAA 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.

(b) The flight and operational tests certified to on the Statement of Conformity shall be in accordance with § 1.15-4 (d) through (f).

[CAM 1 Rev., 21 F. R. 8799, Nov. 14, 1956]

CHANGES IN TYPE DESIGN

§ 1.20 General. 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 (CAA 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 air

5 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.

worthiness 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.

§ 1.24 Service experience changes. (a) Where the Administrator finds as a result of service experience that an unsafe condition exists with respect to a design feature, part or characteristic of any product, and that such a condition is likely to exist or develop in other products of the same type design, he shall provide notice 5a 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

5a 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.

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.

§ 1.25-1 Application for a supplemental type certificate (CAA 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 CAA 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).

6 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.

7

§ 1.26-1 Airworthiness requirements (CAA 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 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.

a

§ 1.27-1 Procedures for obtaining approval (CAA policies which apply to § 1.27). CAA approval of 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 CAA 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 CAA 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 CAA Aircraft Engineering Division. Whereas a DER's authority may be limited to certain areas, the DER should indicate on Form ACA-1600 whether any addi

Detailed information on the applicable airworthiness requirements used for the original type certification of the product involved may be obtained from the Civil Aeronautics Administration.

tional areas require CAA approval. On a complex project the DER should contact the appropriate CAA Aircraft Engineering office as early as possible.

(2) The CAA. The technical data describing and substantiating the design change should be submitted to the local CAA Aviation Safety Agent for forwarding to the CAA regional office. When necessary, arrangements should be made with CAA 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 a CAA representative in order to establish compliance with the applicable airworthiness requirements. See § 1.15. In the case of a complex modification program involving CAA flight tests, the CAA 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 (CAA policies which apply to § 1.27)-(a) Issuance. When the design examination and inspection described in § 1.27-1 have been satisfactorily completed, the CAA will approve the change in type design by completing Form ACA-2417. This form, signed by the Chief, Aircraft Engineering Division, CAA 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 CAA regional office; and one copy will be sent to the CAA Washington office for use in publishing a summary list of supplemental type certificates. Technical