(b), 1.13, 1.15 (a) and (d), 1.20, and 1.50 (also see § 1.25).

NOTE: The provisions of this section are not applicable to parts produced under the terms of a type and/or production certificate, to parts produced by owners or operators for maintaining or altering their own product, or to standard parts (such as bolts and nuts) conforming to established industry or Government specifications; e. g., SAE and military specifications, and FAA Technical Standard Orders.

§ 1.55-1 Replacement and modification parts; design approval (FAA policies which apply to § 1.55).

Any person, whether or not a citizen of the United States, may apply to the FAA regional office for approval of the design of a part for use on a type certificated product. Such part must comply with the Civil Air Regulations governing the basic design for the product on which the part will be installed.

(a) Engineering design approval is a prerequisite for FAA approval of the fabrication inspection system. Evidence of design approval may be shown by one of the following means:

(1) A statement confirming that the design data has been approved by the FAA. This statement must contain the date and nature of the design approval.

(2) Evidence of a licensing arrangement with the holder of the type certifcate covering the product on which the part is to be installed.

(3) A statement confirming that the approved design data of the type certificate holder was obtained from the FAA. Such data is available only when the type certificate holder has given permission for its release.

(b) A design that is obtained by copying an approved part but is not substantiated by technical data is not acceptable as a basis for production inspection system approval.

(c) The design approval entitles the holder to production privileges equivalent to those accorded to the holder of a type certificate.

(d) After FAA approval, the design data for a part should be retained by the manufacturer and made available to any FAA representative. Each change to a part should be approved by the FAA and the manufacturer should identify such change on the drawing. The manufacturer should keep a record of each change with its date of FAA approval. [CAM 1 Rev., 21 F. R. 8805, Nov. 14, 1956]

§ 1.55–2

Replacement and modification parts; inspection approval (FAA policies which apply to § 1.55).

(a) The request, in duplicate, for a fabrication inspection system approval, together with evidence of design approval, should be submitted to the appropriate regional office or to the local FAA agent (letter form). The request should list the nomenclature of the part, part number, manufacturer's name, and model of the type certificated product for which the part has been approved for installation.

(b) Prior to the approval of the fabrication inspection system Approval Tag, Form ACA-186, will be used by the FAA representative, not to exceed six months, as evidence of inspection approval. After the inspection system is approved, the manufacturer must indicate on the part or package of small parts, evidence that they were produced under an approved inspection system. The symbol "FAA-PMA" is evidence that the part(s) has been manufactured under a FAA-Parts Manufacturer Approval.

(c) Each part or package shipped should be accompanied by approved installation drawings or specifications, where applicable, to assure that the installation will conform to the basic approval.

(d) Each part manufactured or modified shall be marked with such of the following data as the Administrator finds appropriate:

(1) Manufacturer's or modifier's name, trade-mark or symbol. The trade-mark or symbol should be filed with the FAA and will be included on the supplemental type certificates and approved replacement parts listing.

(2) Part number.

(3) Name and model designation of the type certificated product(s) for which the part is eligible for installation, or if impractical, a tag should be attached to the part indicating installation eligibility information.

(e) If the Administrator finds that the fabrication inspection system cannot be approved or that parts manufactured or modified subsequent to the approval of the inspection system repeatedly contain significant discrepancies, the installation of parts on certificated products in either case may be restricted until satisfactory corrective action is initiated by the manufacturer.

(f) The approval of a fabrication inspection system will be evidenced by a letter from the Chief, Manufacturing Inspection Branch to the manufacturer. The letter of approval is not transferable and will be surrendered to the FAA upon written request.

[CAM 1 Rev., 21 F. R. 8806, Nov. 14, 1956]

§ 1.55-3 Fabrication inspection system (FAA rules which apply to § 1.55). Section 1.55 requires the manufacturer of replacement or modification parts to comply with § 1.15 (d) and thereby establish an inspection system. Persons manufacturing replacement or modification parts for sale shall establish within six months from the date of initial production of the parts and thereafter maintain a fabrication inspection system to assure that such parts are in conformity with the design data and safe for installation on type certificated products.

(a) Inspection system standards. The inspection system shall provide assurance for the following, where appropriate:

(1) That all incoming materials used in the finished part are as specified in the design data.

(2) That all incoming material is properly identified when physical and chemical properties cannot otherwise be readily and accurately determined.

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

(4) That all processes affecting quality and safety of the finished product are accomplished in accordance with acceptable specifications.

(5) That parts in process are inspected for conformity with the design data at points in production where accurate determination can be made. Statistical quality control procedures may be employed where it is shown that a satisfactory level of quality will be maintained for the particular part involved.

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

(7) That major changes to the basic design are adequately controlled and approved before being incorporated in the finished part.

(8) That rejected materials and components are segregated and identified in such a manner as to preclude their use in the finished part.

(9) That inspection records are maintained, identified with the completed part, where practicable, and retained in the manufacturer's file for a period of at least two years after the part has been completed.

[Supp. 1, 22 F. R. 657, Feb. 1, 1957]

§ 1.55-4 Surveillance of inspection system (FAA policies which apply to § 1.55).

(a) The assigned Aviation Safety Agent will use §§ 1.55-1 through 1.55-3 as a guide in conducting inspection of the manufacturing facilities. If the manufacturer's facilities are found acceptable by evaluating the results of the inspection system and as reflected in the quality and workmanship of the finished parts, the inspection system should be approved. The FAA thereafter will reduce its inspection surveillance and increase its reliance on the manufacturer's inspection system in the determination of the acceptability of future parts.

(1) The FAA representative will conduct periodic inspections of the manufacturer's facilities; make such spot inspections of individual parts as may be necessary to ascertain that the manufacturing facilities and inspection system continuously complies with the standards set forth in §§ 1.55-1 through 1.553; that the individual parts conform to the approved design data; that fabrica. tion processes and treatments are in compliance with pertinent specifications and that the quality of workmanship an materials are acceptable.

(2) Drawings and other technical dat maintained in the place of manufactur should be made available by the manu facturer to the FAA representative t enable him to ascertain that the finishe part conforms to applicable requirement and current design data.

(3) If the manufacturer's inspectio system is not considered acceptable a evidenced by significant discrepancie found in the finished parts, the issuand of the fabrication inspection system ap proval will be deferred until necessar corrective action has been taken.

(4) Upon approval of the inspectic system, the manufacturer may nomina one or more employees for appointme as Designated Manufacturing Inspectic Representative, in accordance with Pa 418 of this title (Regulations of the A ministrator). If the nominee meets t requirements for appointment, he will authorized by the FAA to issue certi

Any U.S. citizen may apply for instance of an airworthiness certificate for an aircraft provided that he is the registered owner of the aircraft or his agent. The application for an airworthiness certificate shall be made upon a form and in a manner prescribed by the Administrator.

§ 1.60-1 "Registered owner" (FAA interpretations which apply to § 1.60).

The term "registered owner of the aircraft," as used in § 1.60, means the person listed on the official FAA register as the owner of the aircraft. Part 501 of this title (regulations of the Administrator), sets forth the rules and procedures concerning aircraft registration certificates).

[CAM 1 Rev., 21 F. R. 8806, Nov. 14, 1956]

§ 1.60-2

Application form (FAA rules which apply to § 1.60).

Application for an airworthiness certificate shall be made by completing Form ACA-305, Application for Airworthiness Certificate and/or Annual Inspection of an Aircraft, original only, and submitting it to the local FAA Aviation Safety field representative. (Application forms, Form ACA-305, are available from all FAA regional and district offices, and Designated Manufacturing Inspection Representatives.)

[CAM 1 Rev., 21 F. R. 8806, Nov. 14, 1956] § 1.60-3 Processing application (FAA policies which apply to § 1.60).

(a) Application requirements. (1) The FAA will not require the applicant for a Certificate of Airworthiness to show legal evidence that he is a U.S. citizen and the owner of the aircraft, nor will his agent be required to furnish such evidence. The certifying statement made upon the application, Form ACA-305, will be accepted as satisfying the citizen

ship and ownership requirements of § 1.60.

(2) However, at the time the aircraft is presented for the airworthiness inspection, a current registration certificate executed in the name of the applicant must be displayed in the aircraft. Failure to present a current registration certificate will be considered an incomplete application and cause for rejection of the application. There are three types of registration certificates, any one of which will be considered acceptable for the purpose of indicating that the aircraft is currently registered. The three types of registration certificates acceptable are:

(b) The permanent type. Part A of Form ACA-500 is the permanent registration certificate. This certificate is the one returned to the registered owner from the Aircraft Records Branch, Washington, D. C. The certificate will have been validated by the Washington office of the FAA and is current as of the date of issue shown on the form.

(c) The temporary type. This certificate is the original of Part B of Form ACA-500. This form is completed by the applicant and displayed in the aircraft in accordance with instructions furnished with the form. The duration of this certificate is set forth in item 5 of the certificate.

(d) Dealer's Aircraft Registration Certificate. A current Dealer's Aircraft Registration Certificate, Form ACA-1707, is recognized as a current registration certificate for the purpose of making application for an airworthiness certificate. (Dealers' aircraft registration certificates are described and provided for in Part 502 of this title (regulations of the Administrator).)

(e) FAA procedure. During the course of the inspection, the FAA representative conducting the airworthiness inspection will indicate on the Aircraft Inspection Report, Form ACA-305a, which is forwarded to Washington, the type of registration certificate displayed in the aircraft. This information will be compared with the official registration records in Washington to determine if the applicant is the official registered owner. Discrepancies involving official registration will be brought to the attention of the registered owner by the Washington office.

[CAM 1 Rev., 21 F. R. 8806, Nov. 14, 1956]

§ 1.60-4

Airworthiness certificates (FAA policies which apply to § 1.60).

(a) Upon satisfactory application, and when the aircraft described in the application is found to conform with the airworthiness requirements specified in other related sections of the Civil Air Regulations, the FAA representative making the airworthiness determination will prepare a Certificate of Airworthiness, Form ACA-1362, or ACA-1362A, and deliver it to the applicant.

(b) The Certificate of Airworthiness will contain the following information: aircraft nationality and registration mark, airworthiness classification, expiration date of certificate, date certificate was issued, signature of validating FAA representative, and scope of certificate. [CAM 1 Rev., 21 F. R. 8806, Nov. 14, 1956]

§ 1.61 Aircraft categories for which air

worthiness certificates are issued. Airworthiness certificates are issued for aircraft whose type design has been certificated under the normal, utility, acrobatic, or transport categories, for aircraft of the restricted category, and for surplus military aircraft in the limited category. In addition, experimental certificates and special flight permits are issued.

§ 1.61-1

Airwothiness certificate classifications (FAA policies which apply to § 1.61).

For purposes of airworthiness identification and administration, airworthiness certificates are classified as Standard, Limited, Restricted, and Experimental. Aircraft found to conform to the "limited" or "restricted category" requirements will be issued a Limited or Restricted Certificate of Airworthiness, respectively. Aircraft found eligible for certification under the "normal," "utility," "acrobatic," or "transport category" requirements will be issued a Standard Airworthiness Certificate. Experimental airworthiness certificates will be issued for aircraft conforming to the requirements of § 1.74.

[CAM 1 Rev., 21 F. R. 8807, Nov. 14, 1956] § 1.62

Amendment or modification.

An airworthiness certificate may be amended or modified only upon application to the Administrator.

§ 1.62-1 Changing airworthiness classification (FAA policies which apply to § 1.62).

(a) Application to amend or modify an airworthiness certificate should be submitted to an FAA representative on Form ACA-305, entitled "Application for Airworthiness Certificate and/or Annual Inspection of an Aircraft." Upon finding the aircraft eligible for the classification of airworthiness specified on the application, the FAA representative will reissue the Certificate of Airworthiness, Form ACA-1362 and/or prescribe changes, if necessary, to the aircraft operating limitations required by § 43.10 (b).

(b) An example of a condition which would require amendment or modification of the Airworthiness Certificate and/or operating limitations is cited below:

(1) An aircraft certificated in the standard classification of airworthiness, to be used for research and development. The experimental installation does not conform to the design requirements for standard certification. Therefore, it would be necessary to have this aircraft certificated in the experimental classification of airworthiness in order to conduct the research and development experiments. The FAA representative would, in this case, prescribe the appropriate operating limitations.

[CAM 1 Rev., 21 F. R. 8807, Nov. 14. 19561 § 1.63 Transferability.

An airworthiness certificate shall be transferred with the aircraft.

(a) Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, an airworthiness certificate shall remain in effect as long as the maintenance requirements of Part 43 of this subchapter are complied with.

(b) The Administrator may, from | time to time, reinspect any aircraft or i part thereof to see whether it is in an airworthy condition. The owner, operator, or bailee of the aircraft shall make it available for such inspection upon request.

(c) Upon suspension, revocation, or the general termination by order of the Board of an airworthiness certificate, the

§ 1.67

Airworthiness

certificates for normal, utility, acrobatic, and transport category aircraft; requirement for issuance.

The requirements for the issuance of an airworthiness certificate are stated in paragraphs (a) through (d) of this section.

(a) Aircraft manufactured under a production certificate. An applicant for the original issuance of an airworthiness certificate for an aircraft manufactured under the terms of a production certificate, may be issued such certificate without further showing. The Administrator may inspect the aircraft to see if it conforms to the type design.

(b) Aircraft manufactured under type certificate only. An applicant for the original issuance of an airworthiness certificate for an aircraft manufactured under the terms of a type certificate only, shall be issued such certificate upon presentation of a statement of conformity for such aircraft issued by the manufacturer when, upon inspection of the

aircraft, the Administrator finds that the aircraft conforms to the type design, and is in a condition for safe operation.

(c) Import aircraft. An applicant for the original issuance of an airworthiness certificate for an import aircraft type certificated in accordance with Part 10 of this subchapter shall be issued such certificate when the government of the country where the aircraft was manufactured certifies, or the Administrator finds, that the aircraft conforms to the type design and is in a condition for safe operation.

(d) Other aircraft. An applicant for the issuance of an airworthiness certificate for an aircraft other than provided for in paragraphs (a) through (c) of this section shall be issued such a certificate when:

(1) The applicant presents evidence to the Administrator that the aircraft conforms to a type design approved under a type certificate or a supplemental type certificate and with all applicable Airworthiness Directives issued by the Administrator;

NOTE: The evidence of conformity referred to in subparagraph (1) of this paragraph normally consists of showing that the aircraft conforms with the applicable aircraft specification or type certificate data sheet, and presenting records showing the history of the aircraft including all alterations and repairs and the approvals thereof. Where such records are unavailable or inadequate, supplementary evidence may be required, such as, showing that the aircraft conforms with pertinent drawings, specifications, manuals or parts catalogs.

(2) The aircraft (other than an aircraft which is certificated in the experimental classification and immediately prior thereto possessed an airworthiness certificate issued in accordance with this section which aircraft shall be governed by the provisions of subparagraphs (1) and (3) of this paragraph) has been inspected and found airworthy by the manufacturer, by an appropriately certificated domestic repair station, or by a certificated air carrier possessing adequate overhaul facilities and having a maintenance and inspection organization appropriate to the type of aircraft; except that, in the case of a singleengine fixed-wing aircraft, the inspection and finding may be made by a certificated mechanic holding an inspection authorization; and