gional office of the Federal Aviation Agency.

The application shall be accompanied by a three-view drawing and such preliminary basic data as the applicant may have available.

(b) Application for an engine type certificate, Form ACA-312. This application shall be submitted in duplicate, together with preliminary technical data as required by Part 13 of this subchapter, to the Aircraft Engineering Division, Federal Aviation Agency, Washington 25, D.C.

(c) Application for a propeller type certificate, Form ACA-312. (1) This application, together with Form ACA335, Propeller Supplement to Application for Type Certificate, ACA-312, shall be submitted in duplicate to the Aircraft Engineering Division, Federal Aviation Agency, Washington 25, D.C.

(2) The Form ACA-335 shall contain a description of the design features, the proposed rating, and intended application of the propeller.

(3) The preliminary data as required in Part 14 of this subchapter, and the application forms shall be submitted prior to starting any portion of the official type test.

NOTE: The application, Form ACA-312, serves as a formal request by the applicant and shall be submitted for each new model eligible for approval under the terms of a type certificate.

[CAM 1 Rev., 21 F. R. 8797, Nov. 14, 1956] § 1.11 Products for which issued.

A type certificate may be issued for an aircraft, aircraft engine, propeller, or any appliance for which certification is provided elsewhere in this subchapter. § 1.11-1

Appliances (FAA

which apply to § 1.11).

policies

Inasmuch as Parts 15 and 16 of this subchapter have been rescinded, type certificates are no longer issued for appliances. Types of appliances formerly type certificated under the provisions of Parts 15 and 16 of this subchapter are acceptable for use on aircraft if the appliance complies with a Technical Standard Order issued by the Administrator or is approved as part of the aircraft. [Supp. 3, 23 F. R. 7481, Sept. 26, 1958]

§ 1.12 Requirements for issuance.

A type certificate for a product shall be issued when:

(a) The applicant has submitted the type design (see § 1.2), test reports, and computations as may be required by that part of the regulations in this subchapter under which the product is to be certificated.

(b) Upon examination of the type design and the completion of all tests and inspections, the Administrator finds that the type design meets the requirements of the applicable regulations in this subchapter.

§ 1.12-1

Requirements for issuance of type certificates (FAA policies which apply to § 1.12).

(a) The requirements for the issuance of a type certificate for a product may be found in the following parts of the Civil Air Regulations of this subchapter:

(1) Part 3-Airplane Airworthiness; Normal, Utility, and Acrobatic Categories.

(2) Part 4b-Airplane Airworthiness: Transport Categories.

(3) Part 5-Glider Airworthiness. (4) Part 6-Rotorcraft Airworthiness: Normal Category.

(5) Part 7-Rotorcraft Airworthiness: Transport Categories.

(6) Part 8-Aircraft Airworthiness: Restricted Category.

(7) Part 9-Aircraft Airworthiness: Limited Category.

(8) Part 10-Certification and Approval of Imported Aircraft and Related Products.

(9) Part 13-Aircraft Engine Airworthiness.

(10) Part 14-Aircraft Propeller Airworthiness.

[CAM 1 Rev., 21 F.R. 8797, Nov. 14, 1956, as amended by Supp. 3, 23 F.R. 7481, Sept. 26, 1958]

§ 1.12-2 Inspection of prototype (FAA policies which apply to § 1.15–1(b)). The inspections set forth in § 1.15-1(a) will apply to the product for which a type certificate is requested.

[CAM 1 Rev., 21 F. R. 8797, Nov. 14, 1956] § 1.13 Location of manufacturing fa

cilities.

No type certificate for a product shall be issued if the manufacturing facilities therefor are located outside the United States, unless where facilities are located outside the United States the Administrator finds that no undue burden on the Government is created in administering applicable requirements of the act or regulations issued thereunder.

§ 1.14 Transferability.

A type certificate may be transferred or made available to third persons by licensing agreements, and the grantor shall immediately notify the Administrator in writing of any transfer, licensing agreement, or termination thereof. The provisions of § 1.13 shall be complied with.

§ 1.14-1 Transferability (FAA

interpretations which apply to § 1.14).

The FAA and the manufacturer to whom the type certificate is issued are the first and second persons involved, and any other person to whom the type certificate holder may transfer privileges incidental to the type certificate is the "third person."

[CAM 1 Rev., 21 F.R. 8797, Nov. 14, 1956]

$ 1.15 Inspections and tests.

(a) A representative of the Administrator shall be permitted to make such inspections and, in the case of aircraft, flight tests as may be necessary to determine compliance with applicable requirements.

(b) A product manufactured under a type certificate only shall be required to undergo inspection by a representative of the Administrator to determine whether individual products conform with the type design.

(c) The manufacturer of a product being manufactured under a type certificate only shall maintain at the place of manufacture such technical data and drawings as may be necessary to determine whether the product or any part thereof conforms to the current type design.

(d) A manufacturer producing a product under the terms of a type certificate without a related production certificate shall provide, for products manufactured after six months from the date of issuance of the type certificate, a production inspection system approved by the Administrator which will give assurance that each article produced is in conformity with the type design and is in a condition for safe operation. § 1.15-1 Inspections and tests

policies which apply to § 1.15).

(FAA

(a) Prototype inspection. Each product presented for type certification will be subjected to such conformity inspections, investigations of the workmanship and fabrication processes, and the witnessing of such structural, endurance

and operational tests as may be deemed necessary by the Federal Aviation Agency to assure that the product meets applicable requirements and is eligible for a type certificate. The inspection of test articles and the prototype will be conducted after acceptance by the manufacturer's inspectors.1

(b) Fabrication inspection. Subsequent to type certification parts, assemblies, or products fabricated by the prime, subsidiary, or subdivisional manufacturers operating under the terms of a type certificate only will be subjected to inspection' by an authorized representative of the Administrator (hereinafter called FAA representative) while the articles are in an "inspectable" condition. Drawings and other technical data maintained at the place of manufacture should be made available by the manufacturer to the FAA representative to enable him to ascertain that the finished product, or any part thereof, conforms with the applicable requirements and current approved type design data. During the course of fabrication of all critical parts, major assemblies, and the final assembly of the product, the following will be ascertained: that the product is in conformity with the type design data; that fabrication processes and treatments are in conformity with pertinent specifications; and that workmanship and materials are acceptable. All parts, assemblies, and completed products checked by the FAA representative should bear record of having first

1 The FAA inspections are not intended to duplicate the manufacturer's inspections, but rather to verify the effectiveness and accuracy of his inspections. The FAA verification will consist of sampling inspections such as witnessing certain inspections and tests conducted by the manufacturer, spot checking the manufacturer's inspection records, conducting sampling conformity inspections of critical parts or dimensions, witnessing the assembly of major components and critical parts, and examination of the flight test report or operational log sheets. In addition, the inspection will include the checking of design features for compliance with the requirements which are not readily evaluated from the technical data, such as suitable inspection provisions, suitable provisions for servicing and maintenance, and fits, tolerances, clearances, interferences, ventilation, drainage, etc. The frequency of the sampling inspections will depend, to a large extent, on the degree of conformity with the type design data and other requirements applicable to the particular product.

been accepted by the manufacturer. At least the following inspections will be made by the FAA representative on aircraft, aircraft engines, propellers and major components to insure conformance with the applicable type certification data:

(1) Aircraft. An inspection for quality of workmanship, materials, processes, and for conformity of critical and major parts with the type design data; such as the complete wing, fuselage, tail surfaces, major attachment fittings, primary controls, installation of the hydraulic, fuel, and electrical systems, and powerplant installations.

(i) Each aircraft should be weighed to determine the empty weight and c. g. and the report should be submitted when the aircraft is presented for airworthiness certification.

(ii) Aircraft manufactured under a type certificate only are required by § 1.15-4 (d) to be flight tested at the manufacturer's plant by, or under the supervision of, a FAA Aviation Safety Agent.

(iii) Upon completion of the inspection and flight test at the manufacturer's plant, the aircraft may be shipped unassembled, provided Approval Tags, Form ACA-186, signed by the FAA representative, are attached to all major assemblies, components, and boxes of parts. These will indicate the make, model and serial number of the aircraft.

(2) Aircraft engines. An inspection for quality of workmanship, materials, processes, and conformity of critical and major parts with the type design data, including such internal inspections and examination after completion of the engine test run (see § 1.15-4 (e)) as may be necessary to ascertain that no unsafe conditions exist. Enough of the operation tests of each engine should be witnessed to determine that the operational characteristics are in conformity with the type design data.

(3) Propellers. An inspection for quality of workmanship, materials, processes, and conformity of critical and major parts with the type design data. In the case of variable pitch propellers, enough of the operation tests of each propeller should be witnessed to deter

Aircraft which pass the inspection set forth in this paragraph, and found to be in condition for safe operation, are eligible to receive an original airworthiness certificate issued under the authority of § 1.67 (b).

mine that the propeller will operate properly throughout the approved range of operation (see § 1.15-4 (f)).

(4) Major components. Any major spare or replacement component of an aircraft, aircraft engine, or propeller manufactured under a type certificate only will be subjected to inspection for conformity and airworthiness by an FAA representative at the manufacturer's plant. The conformity, quality, and acceptability of major components and critical parts manufactured by a subsidiary manufacturer in accordance with the prime manufacturer's approved drawings will be determined in accordance with § 1.34-2 (a) (11), except that an FAA representative will conduct such additional inspections as may be deemed necessary to assure conformity, compliance, and acceptability of materials and workmanship.

(c) Evidence of inspection approval. When products, or major components, other than complete aircraft or communication equipment, are manufactured under the terms of a type certificate only, the FAA representative, having determined by inspection that the product or component is acceptable, will prepare and attach thereto, an Approval Tag, Form ACA-186. This tag will show the make, model, and serial number of the product, and will be signed by the FAA representative.

[CAM 1 Rev., 21 F. R. 8798, Nov. 14, 1956] § 1.15-2 Production test flight authorization (FAA policies which apply to § 1.15).

(a) To facilitate compliance by manufacturers with related provisions of § 43.10 of this chapter, the reverse side of the Dealer's Aircraft Registration Certificate, Form ACA-1707, will be used to provide flight authorization for production flight testing prior to the initial issuance of individual airworthiness certificates. This flight authorization is provided for the convenience of manu

A new aircraft, in which a Manufacturer's Special Flight Authorization, Form ACA 1707, is displayed, may be given a production flight test subject to the following operations limitations which are specified on such form:

Flights, except takeoffs and landings, prohibited over thickly populated areas or large gatherings of people. No flight shall be conducted for hire or reward. Cross-country flights prohibited. Occupancy of the aircraft restricted to personnel essential to the purpose of the flights.

facturers, and has no connection with the issuance, validity, or continuation of the Dealer's Aircraft Registration Certificate. The flight authorization is limited to production test flights, and does not provide for prototype or experimental flight testing. The flight authorization will be issued at the time the Dealer's Aircraft Registration Certificate is issued. The Application for Dealer's Aircraft Registration Certificate(s), Form ACA-1706, contains a section for the use of manufacturers in applying for authorization to conduct production flight tests.

(b) Aircraft to be flown for production flight tests, which are intended for U. S. registration and certification, are required to display the appropriate U. S. identification markings in accordance with §§ 1.100 through 1.108.

(c) New aircraft intended for export should display the appropriate foreign identification markings during the production flight testing. If these markings are not available, the aircraft may display temporarily assigned U. S. identification markings.

[CAM 1 Rev., 21 F. R. 8798, Nov. 14, 1956] § 1.15-3 Logging of production aircraft flight test time (FAA policies which apply to § 1.15(d)).

Production flight 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 (FAA 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

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.

the particular materials or parts involved.)

(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.) The 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.

Com

(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. plete records of Materials Review Board action applying to materials, parts, assemblies, and the completed product, shall be retained for at least two years, and available for review by FAA 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 FAA 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 (FAA rules which apply to § 1.15(d)).

The inspection system shall 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 acceptable 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 an aircraft (see § 1.15-4 (d)).

[Supp. 2, 22 F. R. 6587, Aug. 16, 1957]

§ 1.15-6 Surveillance of production inspection system (FAA policies which apply to § 1.15(d)).

(a) During the six month interval pending the establishment of the manufacturer's production inspection system, the FAA 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.