TCDS TC 2-558

Page No. 1 2 3 Rev. No. 5 -- -- DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 2-558 Revision 5 INTERSTATE S-1 October 31, 2007 GROUP 2 AIRCRAFT SPECIFICATION NO. 2-558 An aircraft identified as Interstate Airplane Model S-1 and conforming to CAA approved Interstate Aircraft and Engineering Corporation Model S-1 Numerical Drawing List as revised to September 18, 1940, or later CAA or FAA approved revision, will be eligible for an airworthiness certificate upon showing compliance with this specification if the Administrator determines such aircraft is in condition for safe operation. Such certificate shall incorporate the operating limitations listed herein. Aircraft Approval Holder STOL Aviation LLC c/o Downs Rachlin Martin P.O. Box 191 Lebanon, NH 03766 Aircraft Approval Ownership Record Interstate Aircraft a nd Engineering Corporation transferred ownership of Group 2 Aircraft Approval No. 2-558 to Harl ow Aircraft Company on July 23, 1945. Harlow Aircraft Company transferre d ownership of Group 2 Aircraft Approval No. 2-558 to Call Aircraft Company on July 15, 1950. Call Aircraft Company transferred ow nership of Group 2 Aircraft Approval No. 2-558 to Nikiski Marine Corporation on May 14, 1969. Nikiski Marine Corporation transferre d ownership of Group 2 Aircraft Approval No. 2-558 to Arctic Aircraft Company, Inc., on May 15, 1970. Arctic Aircraft Company, Inc., transf erred ownership of Group 2 Aircraft Approval No. 2-558 to Interstate Engineering & Ty pe Design Company, Inc., on June 23, 1999. Interstate Engineering & Type Design Co mpany, Inc., transferred ownership of Group 2 Aircraft Approval No. 2-558 to STOL Aviation LLC on October 31, 2007. I - Model S-1, 2 PCLM (Normal Category), Approved October 31, 1940 Engine Continental A-50-8, Engine Type Certificate No. 190 Fuel 73 min. octane aviation gasoline Engine limits For all operations, 1900 rpm (50 hp) Airspeed limits Level flight or climb 100 mph (87 knots) TIAS Glide or dive 135 mph (117 knots) TIAS Propeller limits Static rpm at maximum permissible throttle setting: Not over 1800, not under 1700. No additional tolerance permitted. Diameter: Not over 84 in., not under 74 in. No further reduction permitted. C.G. range (+14.2) (22.3 percent MAC) to (+16. 5) (26.1 percent MAC). Leading edge of MAC is located at longitudinal station (+0.66). MAC is 60.8 in. Maximum weight 1150 lb. No. of seats 2 (one at +7.7 and one at +38) 2-558, Rev. 5 Page 2 Maximum baggage None Fuel capacity 12 gal. (one tank in fuselage) (-19) Oil capacity 4 qt. (-44) Control surface movements Elevator 33.5° Up 33° Down Elevator tab 9° Up 17° Down Ailerons 20° Up 20° Down Rudder 30° right and left from centerline Serial Nos. (S/N) eligible 1 only Required equipment In addition to the pertinent basic required equipment as prescribed in the applicable airworthiness regulations (see Approval ba sis), the following items of equipment must be installed in the aircraft for certifica tion: Items 1(a) or (b), 101, 201, and 202. Datum Wing leading edge at side of fuselage Leveling means Fuselage tube at door sill Approval basis Group 2 Aircraft Approval No. 2- 558 issued in accordance with the provisions of §§ 04.031, 04.04, and 04.040 through 04.042 of the Civil Air Regulations effective November 1, 1937, as amended to Ma rch 20, 1940. Date of application for approval March 20, 1940. Equipment: A plus (+) or minus (-) sign preceding the we ight of an optional item indicates the net weight change when that item is installed. Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). This symbol denotes that approval has been obtained by someone ot her than the aircraft manufacturer. An item so marked may not have been manufactured under a CAA or FAA monitored or approved quality control system and, therefore, its conformity with CAA or FAA approved technical data must be determined if the item is not identif ied by a CAA Form ACA-186, FAA Form 186, FAA Form 8130-3, FAA PMA, or other evidence of CAA or FAA conformity inspection or production approval. Propellers and Propeller Accessories 1. Propeller (a) U.S. Propellers, Inc., Model 5726A fixed pitch wood, Propeller 16.4 lb. (-63) Type Certificate No. 748, and Continental A3746 hub assembly (b) Wood (fixed or adjustable pitch, maximum weight 12.6 lb.) and 17 lb. (-63) Continental A3746 hub assembly Engines and Engine Accessories - Fuel and Oil System 101. Carburetor air heater in accordance w ith Interstate Aircraft and 1 lb. (-44) Engineering Corporation Drawing No. D-6010 102. Cabin heater in accordance with Inters tate Aircraft and Engineering 1 lb. (-42) Corporation Drawings No. A-6009 and No. D-6010 Landing Gear and Floats 201. Two main wheel/brake assemblies a nd tires - Firestone (Shinn) 29 lb. (-1.6) 6C5WFB 6.00 - 6 wheels with brakes and Firestone 6.00 - 6, 2-ply tires 202. Steerable tail wheel and tire - Firestone 6 x 2.00 solid tail wheel/tire 3 lb. (+174.4) assembly in accordance with Interstate Aircraft and Engineering Corporation Drawing No. D-5002 2-558, Rev. 5 Page 3 Miscellaneous (not listed above) 601. Miscellaneous items of optional equipment whic h may be installed or Use actual weight change removed subject to inspection and a check of the aircraft C.G. limits, originally listed under Class II, Item No. 200, on the approved equipment list in the Aircraft Operation Record NOTE 1. A current weight and balance report including a list of the equipment included in the certificated empty weight, and loading instructions when necessary must be provided for the aircraft at the time of original certification. NOTE 2. The following placards must be displayed in pl ain view and installed in the appropriate locations. (a) On the instrument panel or in another appropriate location in the front of the cockpit: "SOLO FLYING FROM REAR SEAT ONLY" (b) On the fuel tank filler opening and in an appropriate location in the rear of the cockpit: "MAXIMUM FUEL 7½ GALLONS WHEN FLOWN DUAL" …END…