1.12

Requirements for issuance.

1.12-2

1.13

1.14 1.14-1

1.15

1.15-1

1.15-2

(FAA rules which apply to

Transferability.

1.12-1 Requirements for issuance of type certificates (FAA policies which apply to 1.12).

Inspection of prototype (FAA policies which apply to §1.15–(b)). Location of manufacturing facilities.

Transferability (FAA interpretations which apply to § 1.14). Inspections and tests.

Inspections and tests (FAA policies which apply to § 1.15). Production test flight authorization (FAA policies which apply to § 1.15).

Logging of production aircraft flight test time (FAA policies which apply to § 1.15 (d)).

Production inspection system (FAA rules which apply to § 1.15 (d)). Production inspection system standards (FAA rules which apply to § 1.15 (d)).

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

1.15-3

1.15-4

1.15-5

1.15-6

Applicable requirements.

Airworthiness requirements (FAA policies which apply to § 1.26). Requirements for issuance. Procedures for obtaining approval (FAA policies which apply to § 1.27).

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

Airworthiness certification or approval of modified aircraft or products (FAA policies which apply to 1.28).

PRODUCTION CERTIFICATES

Application.

Application for a production certificate (FAA rules which apply to § 1.30).

Processing application (FAA policies which apply to § 1.30). Products for which issued. Requirements for issuance. Production certification requirements (FAA policies which apply to § 1.32).

Location of manufacturing facilities.

Location of manufacturing facilities (FAA policies which apply to § 1.33). Quality control.

Quality control; general (FAA interpretations which apply to § 1.34). Quality control (FAA policies which apply to § 1.34).

Quality control; special procedure (FAA policies which apply to § 1.34).

Privileges.

Statement of conformity (FAA policies which apply to § 1.35). Quality control data requirements; prime manufacturer.

Quality control data requirements (FAA policies which apply to § 1.36). Quality control data (FAA interpretations which apply to § 1.36). Information on subsidiary manufacturers.

Information on inspection system; subsidiary manufacturers (FAA policies which apply to § 1.37). Changes in quality control system. Changes in quality control system (FAA interpretations which apply to 1.38).

Multiple products.

Multiple products (FAA policies which apply to § 1.39).

Production limitation record (FAA policies which apply to § 1.40).

Production limitation record.

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

Airworthiness certificates for restricted category aircraft. Airworthiness certificates for restricted category aircraft;

quirements for issuance.

re

Issuance of restricted airworthiness certificates (FAA policies. which apply to § 1.69).

Multiple airworthiness certification. Issuance of multiple airworthiness certificates (FAA policies which apply to § 1.70).

Airworthiness certificate for limited category aircraft.

Issuance of limited airworthiness. certificates (FAA policies which apply to § 1.71).

Airworthiness certificate for limited category aircraft; requirements for reissuance.

Procedure to be followed for recertification in the "limited category" (FAA policies which apply to § 1.72).

Experimental certificates. Experimental airworthiness certification (FAA policies which apply to § 1.73).

Experimental certificates; requirements for issuance.

Requirements for the issuance of experimental airworthiness certificates (FAA rules which apply to 1.74 (a)).

Additional information (FAA policies which apply to § 1.74 (a)). Certification of amateur-built aircraft (FAA policies which apply to § 1.74).

1.44

1.44-1

Duration (FAA policies which apply to 1.44).

1.45

Display.

1.45-1

Display (FAA policies which apply to § 1.45).

1.46

Responsibility of holder.

AIRCRAFT AND PRODUCT IDENTIFICATION

1.50

Identification.

1.50-1

REPLACEMENT AND MODIFICATION PARTS

1.55

Applicable rules.

1.55-1

1.55-2

Replacement

and modification

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

1.55-4

1.55-3 Fabrication inspection system (FAA rules which Surveillance of inspection system (FAA policies which apply to § 1.55).

apply to § 1.55).

Experimental certificates; duration. Duration of experimental airworthiness certificate (FAA policles which apply to § 1.75). Special flight permits.

Special flight permits (FAA interpretations which apply to § 1.76). Special flight permits; requirements for issuance.

Application for permit (FAA rules which apply to § 1.77).

Airworthiness (FAA policies which apply to 1.77).

Flight restrictions (FAA policies. which apply to § 1.77).

Authorization for air carrier ferry flight of a four-engine airplane with one engine inoperative (FAA rules which apply to § 1.77 (c)). NATIONALITY REGISTRATION

AND

MARKS

Display of identification marks. Assignment of registration numbers

(FAA policies which apply to § 1.101 (a)).

Identification marks for nonconventional aircraft.

1.108-1 Identification marks for nonconventional aircraft (FAA rules which apply to § 1.108). Identification marks for export aircraft. 1.109-1 Identification marks for export aircraft (FAA policies which apply to § 1.109).

1.110

Removal of aircraft identification marks.

AUTHORITY: §§ 1.0 to 1.110 issued under sec. 205, 52 Stat. 984, as amended; 49 U. S. C. 425. Interpret or apply secs. 601, 603, 1102, 52 Stat. 1007, as amended, 1009, as amended, 1026, as amended; 49 U.S.C. 551, 553, 672. Additional authority is cited in parentheses following the sections affected.

SOURCE: $ 1.0 to 1.110, issued by the Civil Aeronautics Board, appear at 20 F. R. 7722, Oct. 14, 1955, as amended at 24 F.R. 5, Jan. 1, 1959, except as otherwise noted.

Sections of this part bearing two or more numbers to the right of the decimal point separated by a dash are rules, policies or interpretations issued by the former Civil Aeronautics Administration (now the Federal Aviation Agency). Sources are cited to text.

SPECIAL CIVIL AIR REGULATIONS

SR-407

1. Applicability. Contrary provisions of the Civil Air Regulations regarding certification notwithstanding,' this regulation shall provide the basis for approval by the Administrator of modifications of individual Douglas DC-3 and Lockheed L-18 airplanes subsequent to the effective date of this regulation.

2. General modifications. Except as mod!fied in sections 3 and 4 of this regulation, an applicant for approval of modifications to a DC-3 or L-18 airplane which result in changes in design or in changes to approved limitations shall show that the modifications were accomplished in accordance with the rules of either Part 4a or Part 4b in effect on September 1, 1953, which are applicable to the modification being made: Provided, That an applicant may elect to accomplish a modification in accordance with the rules of Part 4b in effect on the date of application for the modification in lieu of Part 4a or

It is not intended to waive compliance with such airworthiness requirements as are included in the operating parts of the Civil Air Regulations for specific types of operation.

Part 4b as in effect on September 1, 1953: And provided further, That each specific modification must be accomplished in accordance with all of the provisions contained in the elected rules relating to the particular modification.

An 3. Specific conditions for approval. applicant for any approval of the following specific changes shall comply with section 2 of this regulation as modified by the applicable provisions of this section.

(a) Increase in take-off power limitation1,200 to 1,350 horsepower. The engine takeoff power limitation for the airplane may be increased to more than 1,200 horsepower but not to more than 1,350 horsepower per engine if the increase in power does not adversely affect the flight characteristics of the airplane.

(b) Increase in take-off power limitation to more than 1,350 horsepower. The engine take-off power limitation for the airplane may be increased to more than 1,350 horsepower per engine if compliance is shown with the flight characteristics and ground handling requirements of Part 4b.

(c) Installation of engines of not more than 1,830 cubic inches displacement and not having a certificated take-off rating of more than 1,350 horsepower. Engines of not more than 1,830 cubic inches displacement and not having a certificated take-off rating of more than 1,350 horsepower which necessitate a major modification or redesign of the engine installation may be installed, if the engine fire prevention and fire protection are equivalent to that on the prior engine installation.

(d) Installation of engines of more than 1,830 cubic inches displacement or having certificated take-off rating of more than 1,350 horsepower. Engines of more than 1,830 cubic inches displacement or having certificated take-off rating of more than 1,850 horsepower may be installed if compliance is shown with the engine installation requirements of Part 4b: Provided, That where literal compliance with the engine installation requirements of Part 4b is extremely difficult to accomplish and would not contribute materially to the objective sought, and the Administrator finds that the experience with the DC-3 or L-18 airplanes justifies it, he is authorized to accept such measures of compliance as he finds will effectively accomplish the basic objective.

4. Establishment of new maximum certificated weights. An applicant for approval of new maximum certificated weights shall apply for an amendment of the airworthiness certificate of the airplane and shall show that the weights sought have been established, and the appropriate manual material obtained, as provided in this section.

NOTE: Transport category performance requirements result in the establishment of maximum certificated weights for various altitudes.

(a) Weights-25,200 to 26,900 for the DC-3 and 18,500 to 19,500 for the L-18. New maxi

mum certificated weights of more than 25,200 but not more than 26,900 pounds for DC-3 and more than 18,500 but not more than 19,500 pounds for L-18 airplanes may be established in accordance with the transport category performance requirements of either Part 4a or Part 4b, if the airplane at the new maximum weights can meet the structural requirements of the elected part.

(b) Weights of more than 26,900 for the DC-3 and 19,500 for the L-18. New maximum certificated weights of more than 26,900 pounds for DC-3 and 19,500 pounds for L-18 airplanes shall be established in accordance with the structural performance, flight characteristics, and ground handling requirements of Part 4b: Provided, That where literal compliance with the structural requirements of Part 4b is extremely difficult to accomplish and would not contribute materially to the objective sought, and the Administrator finds that the experience with the DC-3 or L-18 airplanes justifies it, he is authorized to accept such measures of compliance as he finds will effectively accomplish the basic objective.

(c) Airplane flight manual-performance operating information. An approved airplane flight manual shall be provided for each DC-3 and L-18 airplane which has had new maximum certificated weights established under this section. The airplane flight manual shall contain the applicable performance information prescribed in that part of the regulations under which the new certificated weights were established and such additional information as may be necessary to enable the application of the takeoff, en route, and landing limitations prescribed for transport category airplanes in the operating parts of the Civil Air Regulations.

(d) Performance operating limitations. Each airplane for which new maximum certificated weights are established in accordance with paragraphs (a) or (b) of this section shall be considered a transport category airplane for the purpose of complying with the performance operating limitations applicable to the operations in which it is utilized.

5. Reference: Unless otherwise provided, all references in this regulation to Part 4a and Part 4b are those parts of the Civil Air Regulations in effect on September 1, 1953.

NOTE: Parts 4a and 4b as amended and in effect on September 1, 1953, were published in the FEDERAL REGISTER at the following citations: Part 4a, 14 F. R. 4072, 14 F. R. 3742, 14 F. R. 6769, 15 F. R. 28, 17 F. R. 11631; Part 4b, 15 F. R. 3543, 15 F. R. 8903, 15 F. R. 9184, 16 F. R. 314, 16 F. R. 11759, 16 F. R. 12220, 17 F. R. 1087, 17 F. R. 11631, 18 F. R. 2213.

This regulation supersedes Special Civil Air Regulation SR-398 and shall remain effective until superseded or rescinded by the Board.

[19 F.R. 5039, Aug. 11, 1954]

SR-425C

GENERAL

1. Applicability. Contrary provisions of the Civil Air Regulations notwithstanding, provisional type and airworthiness certificates, amendments to provisional type certificates, and provisional amendments to type certificates, will be issued as prescribed in this regulation to a manufacturer or an air carrier. As used in this regulation, a manufacturer shall mean only a manufacturer who is a citizen of the United States; and the term air carrier shall not include an air taxi operator.

2. Eligibility.

(a) A manufacturer of aircraft manufactured by him within the United States may apply for Class I or Class II provisional type and provisional airworthiness certificates, for amendments to provisional type certificates held by him, and for provisional amendments to type certificates held by him.

(b) An air carrier holding an air carrier operating certificate authorizing him to conduct operations under Parts 40, 41, 42, or 46 of the Civil Air Regulations may apply for Class II provisional airworthiness certificates for transport category aircraft which meet the conditions of either subparagraphs (1) or (2) of this paragraph.

(1) The aircraft has a currently valid Class II provisional type certificate or an amendment thereto;

(2) The aircraft has a currently valid provisional amendment to a type certificate which was preceded by a corresponding Class II provisional type certificate.

(c) An engine manufacturer who has altered a type certificated aircraft by installing different type certificated engines, manufactured by him within the United States, in place of the original engines, may apply for Class I provisional type and provisional airworthiness certificates for such aircraft, and for amendments to Class I provisional type certificates held by him, if the basic aircraft, before alteration, was type certificated in the normal, utility, acrobatic, or transport category.

3. Application—(a) General. Applications for provisional type and airworthiness certificates, for amendments to provisional type certificates, and for provisional amendments to type certificates, shall be submitted to the Chief, Flight Standards Division, FAA, of the Regional Office in which the manufacturer or air carrier is located and shall be accompanied by the pertinent information specified in this regulation.

4. Duration. Unless sooner surrendered, superseded, revoked, or otherwise terminated, certificates and amendments thereto, shall have periods of duration in accordance with paragraphs (a) through (f) of this section.

(a) A Class I provisional type certificate shall remain in effect for 24 months after the date of its issuance or until the date of issuance of the corresponding type or supple