TCDS A-737

Page No. 1 2 3 4 5 6 7 8 Rev. No. 9 9 9 9 9 9 9 9 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-737 │ Revision 9 │ INTERSTATE S-1A S-1A-65F S-1A-85F S-1A-90F │ October 31, 2007 AIRCRAFT SPECIFICATION NO. A-737 Type Certificate Holder STOL Aviation LLC c/o Downs Rachlin Martin P.O. Box 191 Lebanon, NH 03766 Type Certificate Ownership Record Interstate Aircraft and Engineering Corporation transferred ownership of Aircraft Type Certificate No. 737 to Harlow Aircraft Company on July 23, 1945. Harlow Aircraft Company transferred ownership of Aircraft Type Certificate No. 737 to Call Aircraft Company on July 15, 1950. Call Aircraft Company transferred owners hip of Aircraft Type Certificate No. 737 to Nikiski Marine Corporation on May 14, 1969. Nikiski Marine Corporation transferred ownership of Aircraft Type Certificate No. 737 to Arctic Aircraft Company, Inc., on May 15, 1970. Arctic Aircraft Company, Inc., transfe rred ownership of Aircraft Type Certificate No. 737 to Interstate Engineering & Ty pe Design Company, Inc., on June 23, 1999. Interstate Engineering & Type Design Compan y, Inc., transferred ownership of Aircraft Type Certificate No. 737 to STOL Aviation LLC, on October 31, 2007. I - Model S-1A, 2 PCLM (Normal Category), Approved February 26, 1941 Engine Continental A-65-8, Engine Type Certificate No. 205 Fuel 73 min. octane aviation gasoline Engine limits For all operations, 2300 rpm (65 hp) Airspeed limits Level flight or climb 103 mph (90 knots) TIAS Glide or dive 139 mph (121 knots) TIAS Propeller limits Static rpm at maximum permissible throttle setting: Not over 2200, not under 1900. No additional tolerance permitted. Diameter: Not over 76 in., not under 72 in. No further reduction permitted. C.G. range (+9.3) to (+19.6). When larger ve rtical tail surfaces in accordance with Interstate Aircraft and Engineering Corpora tion Drawings No. D-3-3002 and No. G-3-3006 are installed, rear limit may be (+20.3). Empty weight C.G. range (+13.9) to (+14.4) for standard airplane. (+13.9) to (+15.3) with larger vertical surfaces. When empty weight C.G. falls within pe rtinent range, computation of critical fore and aft C.G. positions is unnecessary. Ranges are not valid for non-standard arrangements except as noted. A-737, Rev. 9 Page 2 Maximum weight 1200 lb. When larger vertical tail surfaces in accordance with Interstate Aircraft and Engineering Corporation Drawings No . D-3-3002 and No. G-3-3006 are installed, maximum weight is 1250 lb. No. of seats 2 (one at +7 and one at +37) Maximum baggage 40 lb. (+70) Fuel capacity 15 gal. (-18) Oil capacity 4 qt. (-38.2) Control surface movements Elevator 30° Up 30° Down Elevator tab 23.5° Up 29° Down Ailerons 20° Up 19.5° Down Rudder 30° right and left from centerline Serial Nos. (S/N) eligible 2 and up Required equipment In addition to the pertinent basic required equipment as prescribed in the applicable airworthiness regulations (see Certifica tion basis), the following items of equipment must be installed in the aircraft fo r certification: Items 1(a), 201, and 202. II - Model S-1A-65F, 2 PCLM (Normal Category), Approved October 1, 1941 (Same as Model S-1A except fo r powerplant and engine mount.) Engine Franklin 4AC-176-B2, Engine Type Certificate No. 221 Fuel 73 min. octane aviation gasoline Engine limits For all operations, 2200 rpm (65 hp) Airspeed limits Level flight or climb 103 mph (90 knots) TIAS Glide or dive 139 mph (121 knots) TIAS Propeller limits Static rpm at maximum permissible throttle setting: Not over 2120, not under 2020. No additional tolerance permitted. Diameter: Not over 76 in., not under 72 in. No further reduction permitted. C.G. range (+9.3) to (+19.6). When larger ve rtical tail surfaces in accordance with Interstate Aircraft and Engineering Corpora tion Drawings No. D-3-3002 and No. G-3-3006 are installed, rear limit may be (+20.3). Empty weight C.G. range (+13.9) to (+14.4) for standard airplane. (+13.9) to (+15.3) with larger vertical surfaces. When empty weight C.G. falls with in pertinent range, computation of critical fore and aft C.G. positions is unnecessary. Ranges are not valid for non-standard arrangements except as noted. Maximum weight 1200 lb. When larger vertical tail surfaces in accordance with Interstate Aircraft and Engineering Corporation Drawings No . D-3-3002 and No. G-3-3006 are installed, maximum weight is 1250 lb. No. of seats 2 (one at +7 and one at +37) Maximum baggage 40 lb. (+70) Fuel capacity 15 gal. (-18) Oil capacity 5 qt. (-43.5) Page 3 A-737, Rev. 9 Control surface movements Elevator 30° Up 30° Down Elevator tab 23.5° Up 25° Down Ailerons 21° Up 22° Down Rudder 30° right and left from centerline Serial Nos. (S/N) eligible 2 and up Required equipment In addition to the pertinent basic required equipment as prescribed in the applicable airworthiness regulations (see Certifica tion basis), the following items of equipment must be installed in the aircraft fo r certification: Items 1(c), 201, and 202. III - Model S-1A-85F, 2 PCLM (Normal Category), Approved January 5, 1942 (Same as Model S-1A-65F S/N 180 and up except fo r wing, control surfaces, fuselage, and powerplant.) Engine Franklin 4AC-199-D2, Engine Type Certificate No. 226 Fuel 73 min. octane aviation gasoline Engine limits For all operations, 2500 rpm (85 hp) Airspeed limits Level flight or climb 117 mph (102 knots) TIAS Glide or dive 158 mph (137 knots) TIAS Propeller limits Range 1: Static rpm at maximum permissible throttle setting: Not over 2350, not under 2250. No additional tolerance permitted. Diameter: Not over 76 in., not under 74 in. No further reduction permitted. Range 2: Static rpm at maximum permissible throttle setting: Not over 2480, not under 2380. No additional tolerance permitted. Diameter: Not over 72 in., not under 70 in. No further reduction permitted. C.G. range (+9.9) to (+20.3) Empty weight C.G. range (+14.2) to (+17.1). When empty weight C.G. falls within this range, computation of critical fore and af t C.G. positions is unnecessary. Range is not valid for non-standard arrangements. Maximum weight 1300 lb. No. of seats 2 (one at +7 and one at +37) Maximum baggage 40 lb. (+70) Fuel capacity 15 gal. (-18) Oil capacity 5 qt. (-43.5) Control surface movements Elevator 30° Up 29° Down Elevator tab 24° Up 29° Down Ailerons 19.5° Up 20.5° Down Rudder 30° right and left from centerline Serial Nos. (S/N) eligible 180 and up provided ailer ons are balanced and wing, control surfaces, fuselage, and powerplant conform to technical data defining Model S-1A-85F on approved drawing list. A-737, Rev. 9 Page 4 Required equipment In addition to the pertinent basic required equipment as prescribed in the applicable airworthiness regulations (see Certifica tion basis), the following items of equipment must be installed in the aircraft for certification: Items 1(d), 201, 202, and 601. IV - Model S-1A-90F, 2 PCLM (Normal Category), Approved January 5, 1942 (Same as Model S-1A-85F except for powerplant and fuel grade.) Engine Franklin 4AC-199-E2, Engine Type Certificate No. 226 Fuel 80 min. octane aviation gasoline Engine limits For all operations, 2500 rpm (90 hp) Airspeed limits Level flight or climb 117 mph (102 knots) TIAS Glide or dive 158 mph (137 knots) TIAS Propeller limits Static rpm at maximum permissible throttle setting: Not over 2275, not under 2175. No additional tolerance permitted. Diameter: Not over 72 in., not under 70 in. No further reduction permitted. C.G. range (+9.9) to (+20.3) Empty weight C.G. range (+14.2) to (+17.1). When empty weight C.G. falls within this range, computation of critical fore and af t C.G. positions is unnecessary. Range is not valid for non-standard arrangements. Maximum weight 1300 lb. No. of seats 2 (one at +7 and one at +37) Maximum baggage 40 lb. (+70) Fuel capacity 15 gal. (-18) Oil capacity 5 qt. (-43.5) Control surface movements Elevator 30° Up 29° Down Elevator tab 21.5° Up 29° Down Ailerons 19.5° Up 20.5° Down Rudder 30° right and left from centerline Serial Nos. (S/N) eligible 180 and up provided ailer ons are balanced and wing, control surfaces, fuselage, and powerplant conform to technical data defining Model S-1A-90F on approved drawing list. Required equipment In addition to the pertinent basic required equipment as prescribed in the applicable airworthiness regulations (see Certifica tion basis), the following items of equipment must be installed in the aircraft for certification: Items 1(d), 201, 202, and 601. Specifications Pertinent to All Models Datum Wing leading edge Leveling means Fuselage tube at door sill Certification basis Aircraft Type Certificate No. 737 Model S-1A : Part 04 of the Civil Air Regulations effective November 1, 1937, and amendments in effect on March 20, 1940. Date of Application for Type Certificate March 20, 1940. Page 5 A-737, Rev. 9 Model S-1A-65F : Part 04 of the Civil Air Regulations effective November 1, 1937, and amendments in effect on October 15, 1940. Date of Application for Type Certificate October 15, 1940. Models S-1A-85F and S-1A-90F : Part 04 of the Civil Air Regulations as amended to April 1, 1941, and additional amendments in effect on October 23, 1941. Date of Applications for Type Certificate October 23, 1941. Production basis None. Prior to original certifi cation of each aircraft manufactured subsequent to April 2, 1943, a CAA or FAA repres entative must perform a detailed inspection for workmanship, material s, and conformity with the approved technical data, and a check of the flight characteristics. 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) Wood (fixed or adjustable pitch) and Continental A3746 hub assembly 15.4 lb. (-56.5) (Model S-1A only) (b) Wood (fixed or adjustable pitch) (Model S- 1A with Item 101(a) engine only) 11 lb. (-56.5) (c) Wood (fixed or adjustable pitch) (Model S-1A-65F only) 11 lb. (-57.5) (d) Wood (fixed or adjustable pitch) (Models S-1A-85F & S-1A-90F) 13 lb. (-58) 2. Propeller (a) McCauley 1A90/CH or 1A90/CF fixed pitch metal, 25.4 lb. (-56.5) Propeller Type Certificate No. 842, and Continental A3746 hub assembly (Model S-1A only) with the following limits: Static rpm at maximum permissible throttle setting: Not over 2200, not under 1900. No additional tolerance permitted. Diameter: not over 76 in., not under 72 in. No further reduction permitted. (b) McCauley 1A90/CF fixed pitch metal, Propeller Type Certificate No. 842 21 lb. (-56.5) (Model S-1A with Item 101(a) or Item 101(d) engine only) with the following limits: When installed on Item 101(a) engine: Static rpm at maximum permissible throttle setting: Not over 2200, not under 1900. No additional tolerance permitted. Diameter: not over 76 in., not under 72 in. No further reduction permitted. When installed on Item 101(d) engine: Static rpm at maximum permissible throttle setting: Not over 2375, not under 2275. No additional tolerance permitted. Diameter: not over 73 in., not under 71.5 in. No further reduction permitted. *3. Propeller - Sensenich M74CK fi xed pitch metal, Propeller Type Certificate No. 1P2 21 lb. (-56.5) (Model S-1A with Item 101(a) engine only) with the following limits: Static rpm at maximum permissible throttle setting: Not over 2200, not under 1900. No additional tolerance permitted. Diameter: Not over 74 in., not under 72. 5 in. No further reduction permitted. A-737, Rev. 9 Page 6 *4. Propeller - fixed pitch wood and Con tinental A3746 hub assembly 15.4 lb. (-56.5) (Model S-1A with Item 101*(c) engine only) with the following limits: Static rpm at maximum permissible throttle setting: Not over 2200, not under 2000. No additional tolerance permitted. Diameter: Not over 74 in., not under 72 in. No further reduction permitted. 5. Propeller spinner installation (a) Spinner installation in accordance with Inte rstate Aircraft and Engineering 0.3 lb. (-59.9) Corporation Drawing No. B-6259 (Model S-1A with Item 1(a), Item 2(a), or Item *4 propeller only) (b) Spinner installation in accordance with Inte rstate Aircraft and Engineering 0.3 lb. (-60.9) Corporation Drawing No. B-6256 (Model S-1A-65F only) (c) Spinner installation in accordance with Inte rstate Aircraft and Engineering 0.3 lb. (-61.4) Corporation Drawing No. B-6256 (Models S-1A-85F and S-1A-90F) Engines and Engine Accessories - Fuel and Oil System 101. Engine (a) Continental A-65-8F, Engine Type Certificate No. 205 +1 lb. (-55) (Model S-1A only) with limits unchanged from Contin ental A-65-8 engine as installed on Model S-1A (Item 1(b), Item 2(b), or Item *3 propeller required) (b) Franklin 4AC-199-E3, Engine Type Certificate No. 226 +7 lb. (-36.1) (Model S-1A-90F only) with limits unchanged from Frank lin 4AC-199-E2 engine as installed on Model S-1A-90F *(c) Continental C75-8, Engine Type Certificate No. 233 +7 lb. (-44.25) (Model S-1A only) with the following limits: For all operations, 2275 rpm (75 hp) Fuel: 73 min. octane aviation gasoline (Item *4 propeller required) (d) Continental C90-8F, Engine Type Ce rtificate No. 252 Use actual weight change (Model S-1A only) with the following limits: For all operations, 2475 rpm (90 hp) Fuel: 80 min. octane aviation gasoline (Item 2(b) propeller required) Installation of this engine requi res fuel system revisions and engine cowl modifications as outlined in approved Call Aircraft Company technical data. 102. Starter - 6 volt or 12 volt, Auto-Lite MBG or MZ 16 lb. (-33) (Model S-1A-90F with Item 101(b) engine only) (Item 301(a) 6 volt battery or Item 301(b) 12 volt battery and Item 305(a) 6 volt wind-driven generator, Item 305(b) 12 volt wind-driven generator, or Item 308 6 volt or 12 volt engine-dri ven generator to match voltage rating of starter required) 103. Carburetor air filter in accordance with Intersta te Aircraft and Engineering Neglect weight change Corporation Drawing No. D-6221 (Models S-1A-65F, S-1A-85F, and S-1A-90F) 104. Cabin heater in accordance with Inters tate Aircraft and Engineering 1 lb. (-39) Corporation Drawing No. K-6041 (Model S-1A only) or in accordance with Interstate Aircraft and Engineering Corporation Drawing No. K-6087 (Models S-1A -65F, S-1A-85F, and S-1A-90F) Page 7 A-737, Rev. 9 Landing Gear and Floats 201. Two main wheel/brake assemblies a nd tires - Firestone (Shinn) 29 lb. (-1.6) 6C5WB or 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-5099 203. Wheel fairings in accordance with Inters tate Aircraft and Engineering 5 lb. (-1.6) Corporation Drawing No. D-5112 and inner cutout cover plates in accordance with Interstate Aircraft and Engineering Corporation Drawing No. A-5090 204. Two main wheel replacement skis - Federal SC-2 Use actual weight change (Eligible provided the propeller installation meets the minimum 9-in. ground clearance requirement specified by § 04.611 of CAR Part 04 as amended to April 1, 1941) Electrical and Radio Equipment 301. Battery installation (a) Battery - 6 volt, Willard Type SYR- 7-3 (Pacific Airmotive No. 4209), 10 lb. (-23) and box in accordance with Interstate Aircraft and Engineering Corporation Drawings No. D-8036 and No. A-8037 (b) Battery - 12 volt, Reading Model R24L, and box in accordance 28 lb. (+13) with Interstate Aircraft and Engineering Corporation Drawing No. D-8102 302. Position light installation (a) Position lights - Grimes Model B tail and wing lights, and wiring, 2.7 lb. (+58.2) in accordance with Interstate Aircraft and Engineering Corporation Drawings No. R-0006, No. D-3087, and No. A-8037 (Models S-1A and S-1A-65F with original vertical tail surfaces) (Item 301(a) 6 volt battery or Item 301(b) 12 volt battery to match voltage rating of installed bulbs required) (b) Position lights - Grimes Model A tail li ght and Grimes Model B wing 2.7 lb. (+58.6) lights, and wiring, in accordance with Interstate Aircraft and Engineering Corporation Drawings No. R-0014, No. D-3-3002, No. A-8037, No. B-8038, and No. B-8041 (Models S-1A and S-1A-65F with larger vertical tail surfaces, and Models S-1A-85F and S-1A-90F) (Item 301(a) 6 volt battery or Item 301(b) 12 volt battery to match voltage rating of installed bulbs required) 303. Antenna installation (a) Trailing - reel, in accordance with Interstate Aircraft and Engineering 4 lb. (+37) Corporation Drawing No. B-8041 (b) Overhead - fixed, in accordance with In terstate Aircraft and Neglect weight change Engineering Corporation Drawing No. B-8043 (c) Overhead - fixed, with Air Associates AR-6 loading coil, in Neglect weight change accordance with Interstate Aircraft and Engineering Corporation Drawing No. D-8069 (d) Belly - fixed, in accordance with Interstate Aircraft and Engineering 1 lb. (+49) Corporation Drawing No. D-8064 (e) Whip - Air Associates Model AR-7, in accordance with Interstate 2 lb. (+47) Aircraft and Engineering Corporation Drawing No. B-8049 304. Radio installation (a) Receiver - Air Associates Model BR-3, in accordance with Interstate 7 lb. (+11) Aircraft and Engineering Corporation Drawing No. B-8048 (b) Receiver-Transmitter - American Aircra ft Model AAR-7 receiver and 16 lb. (+15.9) Model AAT-5 transmitter, in accord ance with Interstate Aircraft and Engineering Corporation Drawing No. D-8051 A-737, Rev. 9 Page 8 (c) Receiver-Transmitter - Air Associates Model BR-3T, in accordance with 12 lb. (-10.6) Interstate Aircraft and Engi neering Corporation Drawing No. R-8070 (d) Receiver-Transmitter - Air Associates Model BR-3T, in accordance with 12 lb. (+9.4) Interstate Aircraft and Engi neering Corporation Drawing No. R-8100 305. Wind-driven generator installation in accordance with Interstate Aircraft and Engineering Corporation Drawing No. D-8072 (a) Wind-driven generator - 6 volt, Champion Model W612 12 lb. (-25) (Item 301(a) 6 volt battery required) (b) Wind-driven generator - 12 volt, Champion Model W128 12 lb. (-25) (Item 301(b) 12 volt battery required) 306. Instrument panel light installation - 6 vo lt or 12 volt, 2 Western Auto #E6317 0.5 lb. (-8) dash lights and 1 Pacific Airmotive Grif-Ho instrument light, in accordance with Interstate Aircraft and Engi neering Corporation Drawings No. A-8037 and No. D-8073 (Item 301(a) 6 volt battery and Item 305(a) 6 volt wind-driven generator, or Item 301(b) 12 volt battery and either Item 305(b) 12 volt wind-driven generator or Item 308 12 volt engine -driven generator to match voltage rating of installed bulbs required) 307. Landing light installation - 12 volt, U.S. Army Air Corps Type A6A 4.5 lb. (+8) with Type A19 12 volt, 240 watt bulb in accordance with Interstate Aircraft and Engineering Corporation Drawing No. D-8074 (Item 301(b) 12 volt battery and either Item 305(b) 12 volt wind-driven generator or Item 308 12 volt e ngine-driven generator required) 308. Engine-driven generator - 6 volt or 12 vo lt, Auto-Lite Model GDY or GAS 12 lb. (-32.5) (Model S-1A-90F with Item 101(b) engine only) (Item 301(a) 6 volt battery or Item 301(b) 12 volt battery to match voltage rating of generator required) Miscellaneous (not listed above) 601. Lead ballast in accordance with Interstate Ai rcraft and Engineering Weight as required (+190) Corporation Drawing No. D-1262 (Models S-1A-85F and S-1A-90F) 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 each aircraft at the time of original certification. NOTE 2. The following placards must be displayed in plain view a nd installed in the appropriate locations. If the aircraft is approved for night flight, the interior placards must be suitably lighted during night operations. (a) On the instrument panel of each aircraft approved for night flight: "SOLO NIGHT FLYING FROM FRONT SEAT ONLY" (b) On the front of the baggage compartment: "BAGGAGE COMPARTMENT MAXIMUM CAPACITY 40 LB." …END…