# TCDS A-738: Consolidated Vultee Aircraft Corporation Stinson Division - Type: Type certificate data sheet - Status: Current - Holder: Consolidated Vultee Aircraft Corporation Stinson Division - Revision: 0 - Revised: May 13, 1949 - Product: Aircraft, Small Airplane - Certification basis: CAR 4a - Registered aircraft: 61, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/ac/f7/acf788d14e3af5c450901d075c657cd4b93012b28a5732350943f7c2e8b46ca3 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/0C3ADFDEEDB4A6D48525673E00596C54.0001 - Page: https://openairdocs.org/tcds/A-738 ## Models (2) As the data sheet lists them. - 10B - 10A ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 Rev. No. - - - - DEPARTMENT OF COMMERCE CIVIL AERONAUTICS ADMINISTRATION A-738 STINSON 10A (Army L-9B) 10B May 13. 1949 AIRCRAFT SPECIFICATION NO. A-738 Manufacturer Consolidated Vultee Aircraft Corp. Stinson Division Wayne, Michigan I - Model 10A (Army L-9B), 3 PCLM, Approved March 3, 1941 Engine Franklin 4AC-199-E3 (See Item 305a for optional engine). Fuel 80 min. octane aviation gasoline Engine limits For all operations, 2500 rpm (90 hp) Airspeed limits Level flight or climb 120 mph True Ind. Glide or dive 144 mph True Ind. Flaps extended 85 mph True Ind. Propeller limits Static rpm at maximum permissible throttle setting: Not over 2275, not under 2175. No additional tolerance permitted. Diameter: Not over 78 in., not under 70 in. (See NOTE 3 for Propeller limits with maximum weight of 1680 lbs.). C.G. range (+14.7) to (+19.0) Empty weight C.G. range (+14.6) to (+15.7) with standard fuel only. (+14.6) to (+15.3) when extra fuel tank (Item 205) is installed. Ranges are valid for either 1650 or 1680 lbs. maximum weight but not for non-standard arrangements except as noted. When empty weight C.G. falls within the pertinent range, computation of critical fore and aft C.G. positions is unnecessary. Maximum weight 1650 lbs. (See NOTE 3 regarding 1680 lbs.) No. seats 3 (two at +16 and one at +39) Maximum baggage 24 lbs. (+39). Baggage may be increased to 194 lbs. when rear passenger is not carried. Fuel capacity 20 gals. (right wing tank at +22). See Item 205 for auxiliary fuel tank. Oil capacity 5 qts. (-41). See Item 206a for larger capacity. Control surface movements Not available. Serial Nos. eligible 7761 and up and all AF nos. Use manufacturer's number when available. Required equipment Items 101, 102, 103, 104 and 105. A-738 2 II - Model 10B, 3 PCLM, Approved March 3, 1941 Engine Lycoming GO-145-C3 (See Item 305b for optional engine). Fuel 73 min. octane aviation gasoline Engine limits For all operations, 3200 rpm (75 hp) Airspeed limits Level flight or climb 120 mph True Ind. Glide or dive 144 mph True Ind. Flaps extended 85 mph True Ind. Propeller limits Static rpm at maximum permissible throttle setting: Not over 2950, not under 2850. No additional tolerance permitted. Diameter: Not over 78 in., not under 76 in. C.G. range (+14.7) to (+19.0) Empty weight C.G. range (+14.6) to (+15.7) with standard fuel only. (+14.6) to (+15.3) when extra fuel tank (Item 205) is installed. Ranges are valid for non-standard arrangements except as noted. When empty weight C.G. falls within the pertinent range, computation of critical fore and aft C.G. positions is unnecessary. Maximum weight 1600 lbs. No. seats 3 (two at +16 and one at +39) Maximum baggage 24 lbs. (+39). Baggage may be increased to 194 lbs. when rear passenger is not carried. Fuel capacity 20 gals. (right wing tank at +22). See Item 205 for auxiliary fuel tank. Oil capacity 4 qts. (-34). See Item 206b for larger capacity. Control surface movements Not available. Serial Nos. eligible 7761 and up. Required equipment Items 101, 102, 103, 104 and 105. SPECIFICATIONS PERTINENT TO ALL MODELS Datum Wing leading edge Leveling means Top of door frame Certification basis Type Certificate No. 738 (CAR 4a) Production basis None. Each aircraft manufactured for civil use subsequent to January 2, 1945, must, prior to original certification, satisfactorily pass: (a) An inspection for workmanship, materials and conformity before any covering, metal priming or final finish is applied. All woodwork may be varnished. (b) A final inspection of the completed aircraft. (c) A check of the flight characteristics. 3 A-738 Export eligibility Eligible for export to all countries except as follows, subject to the provisions of ASR 312 (MOP 2-4 contains the same information): (a) Canada - Landplane -eligible Skiplane - not eligible. However, structure complies with Canadian requirements for ski installation with a maximum ski height of 8-11/16 in. and a tread of 6 ft. 11-5/8 in. (center-line of ski 3-11/16 in. out from edge of torque plate). Equipment: A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Propellers and Propeller Accessories 10A 10B 101. Propeller - wood (fixed pitch) with hub 12 lbs. (-53) (-57) Engines and Engine Accessories - Fuel and Oil System 105. Carburetor air heater 3 lbs. (-35) (-35) 106. AC air filter 1529265 (Aircooled Motors Dwg. SK-534-2) 1 lb. (-41) ----- 107. Oil Filter, Fram PB-5, Kit No. 501 (Model 10A only) Weight includes one qt. of oil 4 lbs. (-25) ----- (a) Fram installation dwg. 61068 (Oil return to fuel pump pad). (b) Fram installation dwg. 61566 (Oil return to drain plug) 202. Starter, including wiring and switch (Item 203(a) or 301 required) (a) Autolite, less solenoid 21 lbs. (-22) ----- (b) Eclipse 22 lbs. ----- (-24) (c) Delco-Remy 21 lbs. (-22) ----- 205. Fuel tank - 20 gal. (in left wing) (Item 206(a) or (b) required) 15 lbs. (+22) (+22) 206. Oil pans (a) Franklin - 8 qt. +2 lbs. (-41) ----- (b) Lycoming - 8 qt. +5 lbs. ----- (-34) 216. Shielding 4 lbs. (-32) ----- 305. Engines (a) Model 10A (1) Franklin 4AC-199E2 -7 lbs. (-40) ----- (b) Model 10B (1) Lycoming GO-145-C2 -2 lbs. ----- (-41) Landing Gear 102. 6.00-6 wheels with brakes (Hayes 600M) and 4 ply tires (wheels must be placarded for these tires) 28 lbs. (+1) (+1) 103. 6x2.00 solid tail wheel 2 lbs. (+168) (+168) 204. Wheel streamlines 6 lbs. (+1) (+1) 211. Puncture seal tubes +1 lb.ea. (+1) (+1) 212. Steerable tail wheel unit +1 lb. (+155) (+155) 214. Skis (Eligible provided the propeller installation meets the minimum 9 in. ground clearance. The maximum weight for the skiplane will be the same as for the corresponding landplane or that shown in parenthesis after each ski model, whichever is less) Use actual weight change (a) Federal SC-2 (Maximum 1650 lbs.) 215. Dual brakes +2 lbs. (-6) (-6) 216. Steerable tail wheel (Mack SFS-1) 5 lbs. (+168) (+168) installed per wheel manufacturer's instructions 303. Parking brake 3 lbs. (+14) (+14) 306. 8.00-4 wheels with brakes (Hayes 841) and 4 ply tires Neglect weight change (Wheels must be placarded for these tires) A-738 4 Electrical Equipment 10A 10B 104. Battery - 6 volt, with box 14 lbs. (+14) (+14) 201. Generator (a) Engine driven (Autolite 12 volts) 12 lbs. (-28) ----- (b) Wind driven (Air Associates GE-20) (6 or 12 volts) 8 lbs. (+12) (+12) 203. Battery - 12 volt, with box and wiring, Dwg. No. 10-64111 40 lbs. (+29) (+29) 209. Landing lights (Grimes ST-250) - one or two 5 lbs.ea. (+14) (+14) 301. Battery - 12 volt with box and wiring (Dwg. No. 10-64111) 40 lbs. (+15) (+15) Interior Equipment 207. Cabin heater 2 lbs. (-32) (-32) 208. Additional instruments 15 lbs. (-4) (-4) 213. Flares - three 1-minute (International) 8 lbs. (+34) (+34) 302. Carpet5 lbs. (+17) (+17) NOTE 1. Weight and balance report, together with list of equipment included in certificated weight empty, must be submitted for each aircraft with original agent's report and each subsequent report showing changes in equipment. NOTE 2. The following placard is to be conspicuously posted at each filler cap for Model 10A: "Fill with 80 octane minimum." NOTE 3. Model 10A also eligible at maximum weight of 1680 lbs. provided the propeller installed falls within the following limits: Propeller Static rpm at maximum permissible throttle setting: Not over 2350, not under 2250. No additional tolerance permitted. Diameter: Not over 72 in., not under 70 in. .....END..... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Stinson 10A](https://openairdocs.org/model/stinson-10a): 61 aircraft (registry code 8632102) - [Stinson 10B](https://openairdocs.org/model/stinson-10b): 0 aircraft (registry code 8632106) - [Stinson/Greiert 10-A](https://openairdocs.org/model/stinson-greiert-10-a): 0 aircraft (registry code 8632005) ## STCs approved under this data sheet (27) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc. - [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA01928WI](https://openairdocs.org/stc/SA01928WI): Replacement of Franklin Engine Model #4AC-199-E#. James Kjeldgaard - [STC SA00433NY](https://openairdocs.org/stc/SA00433NY): Installation of Airwolf remote mounted engine oil filter model AFC-500 or AFC-600 on multi engine fixed wing light aircraft incorporating Franklin reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA02283SE PAGE 2](https://openairdocs.org/stc/SA02283SE%20PAGE%202): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc. - [STC SA02402SE PAGE 2](https://openairdocs.org/stc/SA02402SE%20PAGE%202): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc. - [STC ST00961LA](https://openairdocs.org/stc/ST00961LA): Installation of MASS Systems fire extinguisher cartridges as replacements for Walter Kidde Aerospace fire extinguisher cartridges in fire extinguisher bottles installed in the airplane models noted on the FAA Approved Model List dated June 29, 2000, or later FAA approved revisions. These fire extinguisher cartridges are in accordance with the MASS Systems Master Drawing List No. 30980-1, "Slug Thrower Cartridges Master Drawing List", Revision N/C, dated June 26, 2000, or later FAA approved revisions.. AMETEK AMERON LLC d/b/a MASS Systems - [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [STC SA02354AK](https://openairdocs.org/stc/SA02354AK): Installation of Lycoming O-320 (no suffix) engine and aft fuselage modification. Tundrahawk Aviation LLC - [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc. - [STC SA02033AT](https://openairdocs.org/stc/SA02033AT): Modification to install an air-oil separator to prevent oil from being aspirated from the engine breather line.. M-20 Oil Separators LLC - [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc - [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc. - [STC SA02168AK](https://openairdocs.org/stc/SA02168AK): Installation of hourmeter airspeed switch. For unpressurized aircraft only. Pressurized aircraft must have pressurization system deactivated.. Avalaska Inc - [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc - [STC SA342SW](https://openairdocs.org/stc/SA342SW): Installation of Lycoming O-235-C1 engine with Sensenich M76AM-2 propeller, associated powerplant changes and electrical changes.. James A Schultze - [STC SA4-1210](https://openairdocs.org/stc/SA4-1210): Installation of Eonnex cover on aircraft surfaces.. Ceconite, Inc - [STC SA798EA](https://openairdocs.org/stc/SA798EA): Installation of Monitair exhaust gas combustion monitor kit.. Rosemount Engineering Co - [STC SA124EA](https://openairdocs.org/stc/SA124EA): Shur-Vent fuel tank filler cap.. Alfred R Puccinelli - [STC SA3-63](https://openairdocs.org/stc/SA3-63): Replacement of original center elevator hinge and bearing assembly by split bearing and split housing hinge assembly.. Flanders Vern E - [STC SA4-1575](https://openairdocs.org/stc/SA4-1575): Ceconite 101 covering of complete airplane.. Cooper Engineering Corporation - [STC SA001410BO](https://openairdocs.org/stc/SA001410BO) (historical): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.