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 comphed 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, fight 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.

(e) The manufacturer of a product beng manufactured under a type certifrate only shall maintain at the place of anufacture such technical data and rawings as may be necessary to determine whether the product or any part thereof conforms to the current type design.

a

(d) A manufacturer producing product under the terms of a type cercate without a related production ertificate shall provide, for products manufactured after six months from the e of issuance of the type certificate, production inspection system approved

the Administrator which will give urance that each article produced is conformity with the type design and in a condition for safe operation. L15-1 Inspections and tests (FAA policies which apply to § 1.15).

Prototype inspection. Each prodpresented for type certification will subjected to such conformity inspecas investigations of the workmanship

fabrication processes, and the witng 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

2 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 certifie 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' plant. The conformity, quality, and ac ceptability of major components and critical parts manufactured by a sub sidiary manufacturer in accordance with the prime manufacturer's approved drawings will be determined in accord ance with § 1.34-2 (a) (11), except tha an FAA representative will conduct suc additional inspections as may be deeme necessary to assure conformity, compli ance, and acceptability of materials an workmanship.

(c) Evidence of inspection approva When products, or major component other than complete aircraft or commu nication equipment, are manufacture under the terms of a type certifica only, the FAA representative, having d termined by inspection that the produ or component is acceptable, will prepa and attach thereto, an Approval Ta Form ACA-186. This tag will show t make, model, and serial number of t product, and will be signed by the FA representative.

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

(a) To facilitate compliance by mar facturers with related provisions § 43.10 of this chapter, the reverse s of the Dealer's Aircraft Registration C tificate, Form ACA-1707, will be used provide flight authorization for prod tion flight testing prior to the initial suance of individual airworthir certificates. This flight authorizat is provided for the convenience of ma

A new aircraft, in which a Manufactu Special Flight Authorization, Form ACA 1 is displayed, may be given a production f test subject to the following operations 1 tations which are specified on such form

Flights, except takeoffs and landings, hibited over thickly populated areas or gatherings of people. No flight shall be ducted for hire or reward. Cross-cot flights prohibited. Occupancy of the air restricted to personnel essential to the pose 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 cerification, 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 the finished product are as specified the type design data, or are suitable valents.

(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 spec ifications.

(e) That parts and components i process are inspected for conformit; with type design data at points in pro duction where accurate determination can be made.

(f) That current design drawings a readily available to manufacturing an inspection personnel, and used whe necessary.

(g) That design changes, includin material substitutions, are controlle and approved before being incorporate in the finished product.

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

(1) That materials and parts withhe because of departures from design da or specifications, which are to be co sidered for installation in the finish product, are processed through est lished materials review procedures ( § 1.15-4 (b)).

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

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

[Supp. 2, 22 F. R. 6587, Aug. 16, 1957] § 1.15-6 Surveillance of production spection system (FAA policies w apply to § 1.15(d)).

(a) During the six month inte pending the establishment of the m facturer's production inspection sys the FAA will conduct inspections to certain that the finished product conformity with the type design da airworthy, safe for installation on ce cated aircraft, or, in the case of airc is eligible for an airworthiness certif

(b) Materials review disposition: be spot checked by a representati the Administrator to verify that n vious adverse effect will result from dispositions.

(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 Admintrator). If the nominee meets the reurements for appointment, he will be authorized by the FAA to issue original arworthiness and/or export certificates for the products produced which are und to conform with the approved pe design data; to conduct station and tonformity inspections; and to make ch additional examinations as may be tecessary to ascertain that production

cles are airworthy and safe for opration. Such authorization is limited the manufacturing plant in which the signee is employed.

(d) If the inspection system is not acceptable, as evidenced by questionable

s and materials accepted for instalst.on in the finished product, or sig#ficant discrepancies are repeatedly and in the finished products, the isance of airworthiness certificates for rcraft, or approvals of other products

installation on an aircraft, will be erred 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 surrendered, suspended, revoked, or termination date is otherwise estabbed by the Administration.

PR 7722, Oct. 14, 1955]

117 Display.

Type certificates shall be made availWe for examination by an authorized resentative 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).

§ 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, 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.