# TCDS A15EA: Seastar Corp - Type: Type certificate data sheet - Status: Current - Holder: Seastar Corp - Revision: 12 - Revised: May 30, 2006 - Product: Aircraft, Small Airplane - Certification basis: Part 23 - Registered aircraft: 8, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/b6/17/b61730c0cca9f71461cb01cfcd18f2d041eb3d798e6c85a9845362f685e7a0af - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/AB1DE2376A1894008625719D005EC5B9.0001 - Page: https://openairdocs.org/tcds/A15EA ## Models (3) As the data sheet lists them. - TSC-1A - TSC-1A2 - TSC-1A1 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A15EA Revision 12 Seastar Corp. (BOHICA) (F. D. Beckett) (Teal) (Schweizer) (Thurston) TSC-1A TSC-1A1 TSC-1A2 May 30, 2006 TYPE CERTIFICATE DATA SHEET NO. A15EA This data sheet which is a part of ty pe certificate No. A15E A, prescribes conditions and lim itations under which the product fo r which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Seastar Corp P. O. Box 2214 Homer, AK 99603 Type Certificate Holder Record: Seastar Corp assumed ownership of this TCDS from Bohica, Inc. May 30, 2006. I - Model TSC-1A, 2PCAmM (Normal Category), Approved 28 August 1969. Engine Lycoming O-320-A3B (Carburetor setting 10-3678-32) Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2700 r.p.m. (150 hp.) Propeller and Hartzell Model HC-C2YL-1B/7663-4 2 bladed metal propeller limits Pitch setting at 30 in. station: Low 12° High 27.5° Diameter: Maximum 72" minimum 70"; no further reduction permitted Governor: Hartzell F-2-6A Airspeed limits (CAS) *Vne (Never exceed speed) *V (Maximum structural cruising speed) 135 mph (117 knots) no*Va (Design maneuvering speed) 106 mph ( 92 knots) 106 mph ( 92 knots) Vlo (Maximum speed for landing gear operation) 100 mph ( 87 knots) Vle (Maximum speed for landing gear extended) 135 mph (117 knots) Side windows open 110 mph ( 96 knots) *See NOTE 2. Center of Gravity +102.3 to +109.7 at 1900 lb. or less (C.G.) range (Moment change due to landing gear retraction, plus 860 in.-lb.) (Landing gear extended) Empty weight C.G. range +109.2 to +112.7 When the empty weight C.G. falls within the range given, complete computations of critical fore and aft C.G. positions are unnecessary. Range is not valid for non-standard arrangements. Datum Bow of airplane, Hull Sta. 0; located 91.5 in. forward of wing leading edge at side of hull. Leveling means Entrance sill, left or right side. Maximum weight 1900 lb. Number of seats 2 at (+71) Maximum baggage 230 lb. at (+96) Fuel capacity 24.5 gal. at (+118) 24 gal. usable (single hull tank system) 46.0 gal. at (+103) 40.6 gal. usable (standard 2 tank system) 70.5 gal. at (+103) wing tanks (+118) hull tank, 64.6 gal. usable (3 tank system) (see NOTE 1 for data on system fuel and oil) Page No. 1 2 3 4 5 Rev. No. 12 10 10 10 10 A15EA Page 2 of 5 Oil capacity 2 gal. at (+126) 6 qt. usable Control surface movements Rudder Left 28° + or -2° Right 28° + or -2° (measured from surface Elevator Up 15° + 2° -0° Down 20° + 2° -0° chord line) Elevator tab Up 7.5° + 2.5° -0° Down 21° + 2° -0° Aileron Up 30° + 3° -0° Down 20° + 3° -0° Rudder Tab Left 30° + or -2° Right 30° + or -2° Manufacturer's Serial 2, 3, 4, 5, 7, 9, 11, 12, 13 Numbers II - Model TSC-1A1, 2PCAmM (Normal Category), Approved 23 September 1971 Engine Lycoming O-320-A3B (Carburetor setting 10-3678-32) Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2700 r.p.m. (150 hp.) Propeller and Hartzell Model HC-C2YL-1B/7663-4 2 bladed metal propeller limits Pitch setting at 30 in. station: Low 12° High 27.5° Diameter: Maximum 72" minimum 70"; no further reduction permitted Governor: Hartzell F-2-6A Airspeed limits (CAS) *Vne (Never exceed speed) 123 mph (107 knots) *Vno (Maximum structural cruising speed) 97 mph ( 84 knots) *Va (Design maneuvering speed) 97 mph ( 84 knots) Vlo (Maximum speed for landing gear operation) 100 mph ( 87 knots) Vle (Maximum speed for landing gear extended) 123 mph (107 knots) Side windows open 110 mph ( 96 knots) *See NOTE 2. Center of Gravity +103.5 to +107.8 at 2200 lb. (C.G.) range +103.1 to +108.4 at 2100 lb. (Landing gear extended) +102.3 to +109.7 at 1900 lb. or less Straight line variation between points given (Moment change due to landing gear retraction, plus 860 in.-lb.) Empty weight C.G. range +110.2 to +112.7 When the empty weight C.G. falls within the range given, complete computations of critical fore and aft C.G. positions are unnecessary. Range is not valid for non-standard arrangements. Datum Bow of airplane, Hull Sta. 0; located 91.5 in. forward of wing leading edge at side of hull. Leveling means Entrance sill, left or right side. Maximum weight 2200 lb. for land operations 2100 lb. for water operations Number of seats 2 at (+71) Maximum baggage 230 lb. at (+96) Fuel capacity 46 gal. at (+103.0) 40.6 gal. usable (standard 2 tank system) 70.5 gal. at (+103) wing tanks (+118) hull tank, 64.6 gal. usable (3 tank system) (see NOTE 1 for data on system fuel and oil) Oil capacity 2 gal. at (+126) 6 qt. usable Control surface movements Rudder Left 28° + or -2° Right 28° + or -2° (measured from surface Elevator Up 15° + 2° -0° Down 20° + 2° -0° chord line) Elevator tab Up 7.5° + 2.5° -0° Down 21° + 2° -0° Aileron Up 30° + 3° -0° Down 20° + 3° -0° Rudder tab Left 30° + or -2° Right 30° + or -2° Manufacturer's Serial 1, 6, 8, 10, 14 through 21, 23 Numbers Page 3 of 5 A15EA III - Model TSC-1A2, 2PCAmM (Normal Category), Approved June 28, 1973 Engine Lycoming O-320-A3B (Carburetor setting 10-3678-32) Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2700 r.p.m. (150 hp.) Propeller and Hartzell Model HC-C2YL-1B/7663-4 2 bladed metal propeller limits Pitch setting at 30 in. station: Low 12° High 27.5° Diameter: Maximum 72" minimum 70"; no further reduction permitted Governor: Hartzell F-2-6A Airspeed limits (CAS) *Vne (Never exceed speed) 123 mph (107 knots) *Vno (Maximum structural cruising speed) 97 mph ( 84 knots) *Va (Design maneuvering speed) 97 mph ( 84 knots) Vlo (Maximum speed for landing gear operation) 100 mph ( 87 knots) Vle (Maximum speed for landing gear extended) 123 mph (107 knots) Side windows open 110 mph ( 96 knots) Vfe (Maximum speed for flaps extended) 90 mph ( 78 knots) *See NOTE 2. Center of Gravity +102.8 to +107.4 for all weights to 2200 pound max. gross weight (C.G.) range (Moment change due to landing gear retraction, plus 860 in.-lb.) (Landing gear extended) Empty weight C.G. range +110.2 to +112.7 When the empty weight C.G. falls within the range given, complete computations of critical fore and aft C.G. positions are unnecessary. Range is not valid for non-standard arrangements. Datum Bow of airplane, Hull Sta. 0; located 91.5 in. forward of wing leading edge at side of hull. Leveling means Entrance sill, left or right side. Maximum weight 2200 lb. for land and water operations Number of seats 2 at (+71), 1 at (+96) Maximum baggage 230 lb. at (+96) Fuel capacity 46 gal. at (+103.0) 40.6 gal. usable (std 2 tank system) 70.5 gal. at (+103) wing tanks (+118) hull tank, 64.6 gal. usable (3 tank system) (see NOTE 1 for data on system fuel and oil) Oil capacity 2 gal. at (+126) 6 qt. usable Control surface movements Rudder Left 28° + or -2° Right 28° + or -2° (measured from surface Elevator Up 21° + or -2° Down 17° + or -2° chord line)_ Elevator tab Up 16° + or -2° Down 30° + or -2° Aileron Up 30° + 3° -0° Down 20° + 3° -0° Rudder tab Left 30° + or -2° Right 30° + or -2° Flap Down 15° + 2° -0° Manufacturer's Serial 22, 24 and subsequent, IFR operation approved per note 2 (a) (8). Numbers Certification basis Federal Aviation Regulations Part 23, effective 1 February 1965 and Amendments 23-1 through 23-6. Production basis None. Prior to original certification of each aircraft, an FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, and a check of the flight characteristics. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: Stall warning indicator installed per TAC drawing No. 1-6715 A15EA Page 4 of 5 NOTE 1. Current weight and balance report including list of e quipment included in certificated empty weight, and loading instruction when necessary must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include undrainable system oil of 1 lb. at +126 and unusable fuel as follows: 3 lb. at (+118.0) (single tank system) 32 lb. at (+103.0) (standard 2 tank system) 35 lb. at (+103) wing tanks (+118) hull tank (3 tank system) NOTE 2. The following placards must be displayed: (a) In front of and in full view of the pilot: (1) "THIS AIRPLANE MUST BE OPER ATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS. ALL ACROBATIC MANEUVERS, INCLUDING SPINS PROHIBITED." (2) Models TSC-1A, TSC-1A1 and TSC-1A2 S/Ns 22 and 24 only "OPERATION OF THIS AIRPLANE IS LIMITED TO VFR FLYING UNDER NON-ICING CONDITIONS." (3) Model TSC-1A only "OPERATE LANDING GEAR BELOW 100 m.p.h. GEAR DOWN SPEED LIMIT 135 m.p.h. WINDOW OPEN SPEED LIMIT 110 m.p.h. CROSSWIND OPERATING LIMIT 15 m.p.h. land; 20 m.p.h. water DESIGN MANEUVERING SPEED 106 m.p.h. ALTITUDE LOSS IN POWER OFF STALL 250 ft. USABLE FUEL IS AVAILABLE IN ALL APPROVED FLIGHT CONDITIONS." (4) Models TSC-1A1 and TSC-1A2 only "OPERATE LANDING GEAR BELOW 100 m.p.h. GEAR DOWN SPEED LIMIT 123 m.p.h. WINDOW OPEN SPEED LIMIT 110 m.p.h. CROSSWIND OPERATING LIMIT 15 m.p.h. land; 20 m.p.h. water DESIGN MANEUVERING SPEED 97 m.p.h. ALTITUDE LOSS IN POWER OFF STALL 250 ft. USABLE FUEL IS AVAILABLE IN ALL APPROVED FLIGHT CONDITIONS." (5) Model TSC-1A only "WEIGHT AND BALANCE LIMITS MAXIMUM DESIGN GROSS WEIGHT - 1900 LB. CENTER OF GRAVITY RANGE - 102.3 TO 109.7 INCHES - 18.0% TO 30.4% MAC REFER TO AIRPLANE WEIGHT & BALANCE REPORT FOR PROPER LOADING INFORMATION." (6) Model TSC-1A1 only "WEIGHT AND BALANCE LIMITS MAXIMUM DESIGN GROSS WEIGHT - 2200 LB., 2100 lb. water CENTER OF GRAVITY RANGE 103.5 to 107.8 at 2200 lb. +103.1 to +108.4 at 2100 lb. +102.3 to +109.7 at 1900 lb. or less STRAIGHT LINE VARIATION BETWEEN POINTS GIVEN REFER TO AIRPLANE WEIGHT AND BALANCE REPORT FOR PROPER LOADING INFORMATION." (7) Model TSC-1A2 only "TEAL II - WEIGHT AND BALANCE LIMITS MAXIMUM DESIGN GROSS WEIGHT: 2200 LB. CENTER OF GRAVITY RANGE : 102.8 to 107.4 in. at 2200 lb. or less REFER TO AIRPLANE WEIGHT AND BALANCE REPORT FOR PROPER LOADING INFORMATION." (8) Model TSC-1A2, S/N's 25 and up "THIS AIRPLANE APPROVE D FOR DAY OR NIGHT VFR OR IFR FLIGHT IN NON-ICING CONDITIONS WHEN PROPERLY EQUIPPED IN ACCORDANCE WITH FAR 91." Page 5 of 5 A15EA (b) On top surface of landing gear retraction mechanism housing: "RAISE PIVOT TO LOWER GEAR IN WATER. LOWER PIVOT PRIOR TO WATER TAKE OFF." (c) On top surface of landing gear retraction mechanism housing: "NOTE: IF GEAR IS INADVERTENTLY LOWERED IN FLIGHT WITH PIVOT UP, BLEED AIR CYLINDERS TO RETRACT GEAR." (d) On or adjacent to air cylinder: "CAUTION" "PRESSURIZED AIR CYLINDER. RELEASE PRESSURE BEFORE REMOVING. AFTER INSTALLATION INFLATE TO 300 PSI WITH NITROGEN OR AIR WITH GEAR DOWN." (e) On or adjacent to baggage compartment: "BAGGAGE LIMIT, 60 LB. WITH PILOT AND PASSENGER, 230 LB. WITH PILOT ONLY." (f) Adjacent to fuel filler cap: "23.0 GALLON CAPACITY 80/87 OCTANE (WING TANKS) 24.5 GALLON CAPACITY 80/87 OCTANE (HULL TANK)." (g) Adjacent to fuel control valve: "FUEL VALVE 20.3 GAL. USABLE (STANDARD 2 TANK SYSTEM) FUEL VALVE 24 GAL. USABLE (SINGLE TANK AND 3 TANK SYSTEM)." (h) Such that horizontal bar on placard is 10.38 in. above side window sill. "MAXIMUM WINDOW OPENING IN FLIGHT." (i) Adjacent to light switches on instrument panel: "WARNING: TO AVOID OPTICAL ILLUSION AND SEVERE VERTIGO, TURN ANTI-COLLISION LIGHTS OFF UPON ENTERING CLOUDS, FOG OR HAZE." (j) Adjacent to cabin heater controls (Janitrol model B-1500, P/N 99C42):. "WARNING: WAIT 2 MINUTES AFTER TURNING HEATER OFF BEFORE TURNING OFF HEATER MASTER SWITCH." (k) Beneath the left and right fuel quantity gages on the instrument panel: "THE 2.7 GALLONS OF UNUSABLE FUEL IN EACH WING TANK WHEN QUANTITY INDICATOR READS ZERO CANNOT BE SAFELY USED IN FLIGHT." (l) On the selector valve plate for the three tank system (Model TSC-1A2 only): "CAUTION: USE HULL FUEL FIRST" In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) under Section I, II and III of this data sheet must also be displayed by permanent markings. NOTE 3. None NOTE 4. Model TSC-1A Type Certificate issued 28 August 1969 for a maximum gross weight of 1850 lb. Maximum gross weight of 1900 lb. approved 9 December 1969. .....EN D..... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Teal-Washac Industries TSC-1A2](https://openairdocs.org/model/teal-washac-industries-tsc-1a2): 3 aircraft (registry code 8880102) - [Thurston TSC-1A](https://openairdocs.org/model/thurston-tsc-1a): 3 aircraft (registry code 8960404) - [Thurston TSC-1A1](https://openairdocs.org/model/thurston-tsc-1a1): 2 aircraft (registry code 8960405) ## STCs approved under this data sheet (19) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc. - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation - [STC SA02293AK](https://openairdocs.org/stc/SA02293AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Chelton Flight Systems Inc. - [STC SA563CH](https://openairdocs.org/stc/SA563CH): Authorizes installation of engines equipped w/Unison Limited Authority Spark Advance Regulator (LASAR) ignition system w/Cylinder Head Temp. (CHT) monitoring capability on airframes. engines.. Champion Aerospace LLC - [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC - [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 SA489EA](https://openairdocs.org/stc/SA489EA): Installation of ARP Inc. carburetor ice detection system. Aircraft & Rotorcraft Products (ARP) Inc - [STC SA02520AT](https://openairdocs.org/stc/SA02520AT): Installation of M-20 Oil Separator, model 600-WP.. M-20 Oil Separators LLC - [STC SA5159NM](https://openairdocs.org/stc/SA5159NM): Installation of chip detector system.. Northwest Aircraft Inc - [STC SA308EA](https://openairdocs.org/stc/SA308EA): Installation of carburetor ice detection system 105AP in single and twin engine aircraft and single engine helicopters powered by Continental, Franklin, and Lycoming type engines equipped with Marvel-Schebler MA-2, MA-3, MA-4, MA-4-5, MA-6 and HA-6 series carburetors. (Normal,Utility and Acrobatic Category airplanes and helicopters equipped with engines and carburetors as described.). Alfred R Puccinelli - [STC SA2386SW](https://openairdocs.org/stc/SA2386SW): Installation of S.A.F.E., EGT, CHT Systems.. Avicon Development 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.