Pt. 25, SFAR No. 13 14 CFR Ch. I (1-1-19 Edition) APPENDIX I TO PART 25 - INSTALLATION OF AN AUTOMATIC TAKEOFF THRUST CONTROL SYSTEM (ATTCS) APPENDIX J TO PART 25 - EMERGENCY EVACUATION APPENDIX K TO PART 25 - EXTENDED OPERATIONS (ETOPS) APPENDIX L TO PART 25 - HIRF ENVIRONMENTS AND EQUIPMENT HIRF TEST LEVELS APPENDIX M TO PART 25 - FUEL TANK SYSTEM FLAMMABILITY REDUCTION MEANS APPENDIX N TO PART 25 - FUEL TANK FLAMMABILITY EXPOSURE AND RELIABILITY ANALYSIS APPENDIX O TO PART 25 - SUPERCOOLED LARGE DROP ICING CONDITIONS AUTHORITY: 49 U.S.C. 106(f), 106(g), 40113, 44701, 44702 and 44704. SOURCE: Docket No. 5066, 29 FR 18291, Dec. 24, 1964, unless otherwise noted. SPECIAL FEDERAL AVIATION REGULATION NO. 13 spaschal on DSK3GDR082PROD with CFR 1. Applicability. Contrary provisions of the Civil Air Regulations regarding certification notwithstanding, 1 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 modified 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 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. 3. Specific conditions for approval. An 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 limitation - 1,200 to 1,350 horsepower. The engine take-off power limitation for the airplane may be in1 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. creased 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 takeoff 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 of 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 1,350 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 maximum 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. 200 VerDate Sep<11>2014 12:50 Apr 30, 2019 Jkt 247046 PO 00000 Frm 00210 Fmt 8010 Sfmt 8002 Y:\SGML\247046.XXX 247046