# TCDS 1A9: Taylorcraft 2000 LLC - Type: Type certificate data sheet - Status: Current - Holder: Taylorcraft 2000 LLC - Revision: 23 - Revised: March 22, 2022 - Product: Aircraft, Small Airplane - Certification basis: CAR 3 - Registered aircraft: 142, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/0e/dc/0edcc6343a288338bb06672139840b7756790651158509340189c2e6d39b59ce - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/59865373707E5C5586258816005022AC.0001 - Page: https://openairdocs.org/tcds/1A9 ## Models (9) As the data sheet lists them. - F22C - F22 - F19 - F22A - F21 - 19 - F21B - F22B - F21A ## 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 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 22 13 13 13 13 13 13 13 13 13 13 13 13 13 14 14 14 14 14 14 Rev 22 changed TC holder. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1A9 Revision 23 Taylorcraft 2000, LLC 19 F19 F21 F21A F21B F22 F22A F22B F22C March 22, 2022 AIRCRAFT SPECIFICATION NO. 1A9 Type Certificate Holder Taylorcraft 2000, LLC Dba Aircraft Taylorcraft Co., LLC 815 N Minnesota Avenue Brownsville, TX 78521 Type Certificate Ownership Record Taylorcraft Corporation transferred ownership to Syncrom, Inc., on October 19, 1994. Syncrom, Inc. transferred ownership to Airborne Marketing, Inc. on January 8, 1997. Airborne Marketing transferred ownership to Lee F. Booth on April 26, 1999. Lee F. Booth, dba Taylorcraft Aerospace, transferred ownership to Harvey & Vera Patrick Foundation on May 10, 2000. Harvey & Vera Patrick Foundation transferred ownership to Taylorcraft 2000, LLC on August 8, 2000. Taylorcraft 2000 LLC transferred ownership to Taylorcraft Aviation LLC on March 5, 2003 Taylorcraft Aviation LLC, 2124 n. Central Ave., Brownsville, TX 78521 transferred ownership to Taylorcraft 2000 LLC on May 21, 2008 Taylorcraft 2000 LLC transferred to Taylorcraft 2000 LLC Dba Aircraft Taylorcraft Co., LLC on October 7, 2009. I - Model 19, 2 PCLM (Normal and Utility Categories), Approved June 20, 1951 Engine Continental C85-12, C85-12F Fuel 80 Octane minimum grade aviation gasoline Engine Limits For all operations, 2575 rpm (85 HP) Airspeed Limits VP (Maneuvering) (Normal) 87 mph (76 knots) (True Indicated) (Utility) 86 mph (75 knots) Vno (Maximum Structural (Normal) 108 mph (94 knots) Cruising) (Utility) 104 mph (90 knots) Vne (Never exceed) (Normal) 136 mph (118 knots) (Utility) 141 mph (123 knots) C.G. Range Normal: (+16.1) to (+20.0) at 1500 lb. (+14.2) to (+20.0) at 1280 lb. or less Utility: (+15.1) to (+20.0) at 1380 lb. (+14.2) to (+20.0) at 1280 lb. or less 1A9, Rev 22 Page 2 of 20 I - Model 19 (Cont’d) Straight line variation between points given. Empty Weight C.G. Range None Maximum Weight Normal Category: 1500 lb. Utility Category: 1380 lb. No. of Seats 2 (+23) Maximum Baggage 72 lbs. (+57) Fuel Capacity 24 gals. (12 gal. tank in fuselage at -9 and 6 gal. tank in each wing at +24) Oil Capacity 4-1/2 qts. (+30) Control Surface Movements Elevators 27” up 25” down Elevator tab 25” up 25” down Aileron 23” up 23” down Rudder 25” right 26” left Serial Nos. Eligible 12,000, 4-13000 and up, except 4-13100 and 4-13102 Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 1, 2, or 3; 201(a); 202; 203; and 401(a) II - Model F19, 2 PCLM (Normal and Utility Categories), Approved July 3, 1973 Engine Continental 0-200-A with CMC oil cap retainer assembly # 637130 Fuel 80/87 octane minimum grade aviation gasoline Oil Detergent oil meeting Continental Specification MHS-24 Page 3 of 20 1A9, Rev 21 II - Model F19 (Cont’d) Engine Limits See NOTE 3 For aircraft S/N F-001 to F-153 inclusive: For all operations: 2750 rpm (100 HP) For aircraft S/N F-154 and up: Maximum Normal Operating Power: 2500 rpm (73 HP) For all operations: 2750 rpm (100 HP) Airspeed Limits VP (Maneuvering) (Normal) 87 mph (76 knots) (True Indicated) (Utility) 86 mph (75 knots) Vno (Maximum Structural (Normal) 108 mph (94 knots) Cruising) (Utility) 104 mph (90 knots) Vne (Never Exceed) (Normal) 136 mph (118 knots) (Utility) 141 mph (123 knots) C.G. Range Normal: (+16.1) to (+20.0) at 1500 lb. (+14.2) to (+20.0) at 1280 lb. or less Utility: (+15.1) to (+20.0) at 1380 lb. (+14.2) to (+20.0) at 1280 lb. or less Straight line variation between points given. Empty Weight C.G. Range None Maximum Weight Normal Category: 1500 lb. Utility Category: 1380 lb. No. of Seats 2 (+23) Maximum Baggage 72 lb. (+57) Fuel Capacity 24 gal. total, 21 gal. usable (12 gal. tank in fuselage at -9 and 6 gal. tank in each wing at +24) See NOTE 1 for data on unusable fuel. Oil Capacity 6 qt. (-29.4) 1A9, Rev 22 Page 4 of 20 II - Model F19 (Cont’d) Control Surface Movements Elevators 27” up 25” down Elevator tab 25” up 30” down Aileron 23” up 23” down Rudder 26” right 26” left Serial Nos. Eligible F-001 thru F-1000 Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 4 or 5, 201(b), 202, 203, 401(b) III - Model F21, 2 PCLM (Normal or Utility Category), Approved July 2, 1980 The Model F21 is similar to the Model F19 except for the installation of a Lycoming 0-235-L2C engine, baffles, cowling, engine mount, and hydraulic brakes. Engine Lycoming 0-235-L2C with Marvel Schebler MA-3A, Part Number 10-3103-1, carburetor. The internally mounted Lycoming Thermostatic Oil Bypass and Pressure Relief Valve is not appropriate for this installation. See NOTE 4. Fuel 100/130 or 100 LL minimum grade aviation gasoline Engine Limits Maximum continuous, 2600 rpm (112 HP) Takeoff (5 min.), 2800 rpm (118 HP) Airspeed Limits VP (Maneuvering) (Normal): 87 mph (76 knots) (True Indicated) (Utility): 86 mph (75 knots) Vno (Maximum Structural Cruising) (Normal): 108 mph (94 knots) (Utility): 86 mph (90 knots) Vne (Never Exceed) (Normal): 136 mph (118 knots) (Utility): 141 mph (123 knots) C.G. Range Normal: (+16.1) to (+20.0) at 1500 lb. (+14.2) to (+20.0) at 1280 lb. or less Utility: (+15.1) to (+20.0) at 1380 lb. (+14.2) to (+20.0) at 1280 lb. or less Straight line variation between points given. Page 5 of 20 1A9, Rev 21 III - Model F21 (Cont’d) Empty Weight C.G. Range None Maximum Weight Normal Category: 1500 lb. Utility Category: 1380 lb. No. of Seats 2 (+23) Maximum Baggage 72 lb. (+57) Fuel Capacity 6 qt. (-28.5) Control Surface Movements Elevators 27” up 25” down Elevator tab 25” up 30” down Aileron 23” up 23” down Rudder 26” right 26” left Serial Nos. Eligible F-1001 thru F-1499 Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 6, 103, 104, 105, 106, 202, 203, 204, 401(c) IV - Model F21A, 2 PCLM (Normal or Utility Category), Approved November 15, 1982 The Model F21A is similar to the Model F21 except for increasing the wing fuel to two 21-gallon tanks and the removal of the 12-gallon fuselage tank. Engine Lycoming 0-235-L2C with Marvel Schebler MA-3A, Part Number 10-3013-1, carburetor. The internally mounted Lycoming Thermostatic Oil Bypass and Pressure Relief Valve is not appropriate for this installation. See NOTE 4. Fuel 100/130 or 100 LL minimum grade aviation gasoline Engine Limits Maximum continuous, 2600 rpm (112 HP) Takeoff (5 mins.), 2800 rpm (118 HP) Airspeed Limits VP (Maneuvering) (Normal): 87 mph (76 knots) (True Indicated) (Utility): 86 mph (75 knots) Vno (Maximum Structural Cruising) (Normal): 108 mph (94 knots) (Utility): 104 mph (90 knots) Vne (Never Exceed) (Normal): 136 mph (118 knots) (Utility): 141 mph (123 knots) C.G. Range Normal: (+16.1) to (+20.0) at 1500 lbs. (+14.2) to (+20.0) at 1280 lbs. or less Utility: (+15.1) to (+20.0) at 1380 lbs. (+14.2) to (+20.0) at 1280 lbs. or less 1A9, Rev 22 Page 6 of 20 IV - Model F21A (Cont’d) Straight line variation between points given. Empty Weight C.G. Range None Maximum Weight Normal Category: 1500 lbs. Utility Category: 1380 lbs. No. of Seats 2 (+23) Maximum Baggage 72 lbs. (+57) Fuel Capacity 42 gals. total, 40 gals. usable (a 21 gal. tank in each wing at +24). See NOTE 1 for data on unusable fuel. Oil Capacity 6 qts. (-28.5) Control Surface Movements Elevators 27” up 25” down Elevator tab 25” up 30” down Aileron 23” up 23” down Rudder 26” right 26” left Serial Nos. Eligible F-1500 thru F-1506 Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 6, 103, 104, 105, 106, 202, 203, 204, 401(d) Page 7 of 20 1A9, Rev 21 V - Model F21B, 2 PCLM (Normal or Utility Category), Approved September 6, 1985 The Model F21B is similar to the Model F21A except for increase in maximum allowable gross weight to 1750 lbs., baggage are capacity increased to 200 lbs., battery relocated to engine firewall, and improved visibility with an optional skylight, lower door window, and corresponding changes in regular windows, doors and interior upholstery. Engine Lycoming 0-235-L2C with Marvel Schebler MA-#A, Part Number 10-3103-1, carburetor. The internally mounted Lycoming Thermostatic Oil Bypass and Pressure Relief Valve is not appropriate for this installation. See NOTE 4. Fuel 100/130 or 100 LL minimum grade aviation gasoline Engine Limits Maximum continuous, 2600 rpm (112 HP) Takeoff (5 mins.), 2800 rpm (118 HP) Airspeed Limits VP (Maneuvering) (Normal): 93 mph (81 knots) (True Indicated) (Utility): 86 mph (75 knots) Vno (Maximum Structural Cruising) (Normal): 117 mph (102 knots) (Utility): 104 mph (90 knots) Vne (Never Exceed) (Normal): 148 mph (128 knots) (Utility): 141 mph (123 knots) C.G. Range Normal: (+17.2) to (+20.0) at 1750 lbs. (+14.2) to (+20.0) at 1280 lbs. or less Utility: (+14.9) to (+20.0) at 1380 lbs. (+14.2) to (+20.0) at 1280 lbs. or less Straight line variation between points given. 1A9, Rev 22 Page 8 of 20 V - Model F21B (Cont’d) Empty Weight C.G. Range None Maximum Weight Normal Category: 1750 lb. Utility Cateogry: 1380 lb. No. of Seats 2 (+23) Maximum Baggage 200 lb. (+57) Fuel Capacity 42 gal. total, 40 gal. usable (a 21 gal. tank in each wing at +24). See NOTE 1 for data on unusable fuel. Oil Capacity 6 qt. (-28.5) Control Surface Movements Elevators 27” up 25” down Elevator tab 25” up 30” down Aileron 23” up 23” down Rudder 26” right 26” left Serial Nos. Eligible F-1507 and up Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 6, 103, 104, 105, 107, 202, 203, 204, 401(e), 501. VI - Model F22, 2 PCLM (Normal or Utility Category), Approved August 1, 1988 The Model F22 is basically a Model F21B with the addition of wing flaps, wider doors, top-hinged windows, and fore and aft adjustable individual seats. Engine Lycoming 0-235-L2C with Marvel Schebler MA-3A, Part Number 10-3103-1, carburetor. The internally mounted Lycoming Thermostatic Oil Bypass and Pressure Relief Valve is not appropriate for this installation. See NOTE 4. Fuel 100/130 or 100 LL minimum grade aviation gasoline Engine Limits Maximum Continuous, 2600 rpm (112 HP) Takeoff (5 min.), 2800 rpm (118 HP) Airspeed Limits VP (Maneuvering) (Normal): 93 mph (81 knots) (Calbrated Airspeed (CAS)) (Utility): 86 mph (75 knots) Vno (Maximum Structural Cruising) (Normal): 117 mph (102 knots) (Utility): 104 mph (90 knots) Vne (Never Exceed) (Normal): 148 mph (128 knots) (Utility): 141 mph (122 knots) Vfe (Maximum Speed, Flaps Extended: 76 mph (66 knots) C.G. Range Normal: (+17.2) to (+20.0) at 1750 lb. (+14.2) to (+20.0) at 1280 lb. or less Utility: (+14.9) to (+20.0) at 1380 lb. (+14.2) to (+20.0) at 1280 lb. or less Page 9 of 20 1A9, Rev 21 VI - Model F22 (Cont’d) Straight line variation between points given. Empty Weight C.G. Range None Maximum Weight Normal Category: 1750 lb. Utility Category: 1380 lb. No. of Seats 2 (+23) Maximum Baggage 200 lb. (+57) Fuel Capacity 42 gal. total, 40 gal. usable (a 21 gal. tank in each wing at +24). See Note 1 for data on unusable fuel. Oil Capacity 6 qt. (-28.5) Control Surface Movements Elevators 27” up 25” down Elevator tab 25” up 30” down Aileron 23” up 23” down Rudder 26” right 26” left Flaps 0” up 30” down Serial Nos. Eligible F2202 and up Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 6, 103, 104, 105, 106, 202, 203, 204, 401(f), 501. 1A9, Rev 22 Page 10 of 20 VII - Model F22A, 2 PCLM (Normal Category), Approved February 20, 1991 The Model F22A is basically a Model F22 with a tricycle landing gear installed. Engine Lycoming 0-235-L2C with Marvel Schebler MA-3A, Part Number 10-3103-1, carburetor. The internally mounted Lycoming Thermostatic Oil Bypass and Pressure Relief Valve is not appropriate for this installation. See NOTE 4. Fuel 100/130 or 100 LL minimum grade aviation gasoline Engine Limits Maximum continuous, 2600 rpm (112 HP) Takeoff (5 min.), 2800 rpm (118 HP) Airspeed Limits VP (Maneuvering) (Normal): 93 mph (81 knots) (Calbrated Airspeed (CAS)) Vno (Maximum Structural Cruising) (Normal): 117 mph (102 knots) Vne (Never Exceed) (Normal): 148 mph (128 knots) Vfe (Maximum Speed, Flaps Extended: 76 mph (66 knots)) C.G. Range Normal: (+17.2) to (+20.0) at 1750 lb. (+14.2) to (+20.0) at 1280 lb. or less Straight line variation between points given. Empty Weight C.G. Range None Maximum Weight Normal Category: 1750 lb. No. of Seats 2 (+23) Maximum Baggage 200 lb. (+57) Page 11 of 20 1A9, Rev 21 VII - Model F22A (Cont’d) Fuel Capacity 42 gal. Total, 40 gal. usable (a 21 gal. tank in each wing at (+24). See NOTE 1 for data on unusable fuel. Oil Capacity 6 qt. (-28.5) Control Surface Movements Elevators 27o up 25o down Elevator tab 25o up 30o down Aileron 23o up 23o down Rudder 26o up 26o left Flaps 0o up 30o down Serial Nos. Eligible F2205 and up Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 6, 102, 103, 104, 105, 106, 202, 204, 206, 207, 401(g), 501. VIII - Model F22B, 2 PCLM (Normal Category) Approved July 14, 1992 The Model F22B is basically a Model F22 except it has a Textron Lycoming 0-360-A4M engine installation with matching propeller, battery relocated from firewall to aft fuselage and fuel line sizes increased from 3/8” to 1/2” diameter. Engine Textron Lycoming 0-360-A4M with carburetor. Since an oil cooler is installed, the internally mounted thermostatic oil by-pass and pressure relief valve can be used for this installation. Fuel 100/130 or 100 LL minimum grade aviation gasoline Engine Limits Maximum continuous, 2700 rpm (180 HP) Airspeed Limits VP (Maneuvering): 93 mph (81 knots) (Calbrated Airspeed (CAS)) Vno (Maximum Structural Cruising): 117 mph (90 knots) Vne (Never Exceed): 148 mph (128 knots) Vfe (Maximum Speed, Flaps extended): 76 mph (66 knots) C.G. Range (+17.2) to (+20.0) at 1750 lb. (+14.2) to (+20.0) at 1280 lb. or less 1A9, Rev 22 Page 12 of 20 VIII - Model F22B (Cont’d) Straight line variation between points given. Empty Weight C.G. Range None Maximum Weight 1750 lb. No. of Seats 2 (+23) Maximum Baggage 200 lb. (+57) Fuel Capacity 42 gal. total, 40 gal. usable (a 21 gal. tank in each wing at +24). See NOTE 1 for data on unusable fuel. Oil Capacity 8 qt. (-27.5) Control Surface Movements Elevators 27” up 25” down Elevator tab 25” up 30” down Aileron 23” up 23” down Rudder 26” right 26” left Flaps 0” up 30” down Serial Nos. Eligible F2213 and up Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 7, 106, 108, 109, 110, 111, 112, 202, 203, 204, 401(h), 501. Page 13 of 20 1A9, Rev 21 IX - Model F22C, 2 PCLM (Normal Category) Approved February 20, 1992 The Model F22C is basically a Model F22A except is has a Textron Lycoming 0-360-AFM engine installation with matching propeller, battery relocated from firewall to aft fuselage and fuel line sizes increased from 3/8” to 1/2” diameter. Engine Textron Lycoming 0-360-A4M with carburetor. Since an oil cooler is installed, the internally mounted thermostatic oil by-pass and pressure relief valve can be used for this installation. Fuel 100/130 or 100 LL minimum grade aviation gasoline Engine Limits Maximum continuous, 2700 rpm (180 HP) Airspeed Limits VP (Maneuvering): 93 mph (81 knots) Vno (Maximum Structural Cruising): 117 mph (90 knots) Vne (Never Exceed): 148 mph (128 knots) Vfe (Maximum Speed, Flaps Extended): 76 mph (66 knots) C.G. Range (+17.2) to (+20.0) at 1750 lb. (+14.2) to (+20.0) at 1280 lb. or less Straight line variation between points given. Empty Weight C.G. Range None Maximum Weight 1750 lb. No. of Seats 2 (+23) Maximum Baggage 200 lb. (+57) Fuel Capacity 42 gal. total, 40 gal. usable (a 21 gal. tank in each wing at +24). See NOTE 1 for data on unusable fuel. 1A9, Rev 22 Page 14 of 20 IX - Model F22C (Cont’d) Oil Capacity 8 qt. (-27.5) Control Surface Movements Elevators 27” up 25” down Elevator tab 25” up 30” down Aileron 23” up 23” down Rudder 26” right 26” left Serial Nos. Eligible F2212 and up Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 7, 105, 108, 109, 110, 111, 112, 202, 204 , 206, 207, 401(1), 501. Specifications pertinent to all Models Datum Wing leading edge Leveling Means Upper surface of horizontal stabilizer immediately adjacent to the vertical fin. Production basis Type certificate only. Prior to original certification of each aircraft, an FAA representative must perform a detailed inspection for workmanship, materials, conformity with the approved technical data, and a check of the flight characteristics. Export eligibility Eligible for export to all countries subject to the provisions of Federal Aviation Regulations Part 21.329. Equipment A plus (+) or minus (-) sign preceding the weight of an item indicates 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 for those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the aircraft manufacturer. An item marked with an asterisk may not have been manufacturer under an FAA monitored or approved quality control system, and therefore, conformity must be determined if the item is not identified by Parts Manufacturer Approval or other evidence of FAA production approval. Specifications pertinent to Models 19, F19, F21, F21A, F21B, F22 and F22A Aircraft Certification basis Part 3 of the Civil Air Regulations effective November 1, 1949, and Part 3.84a, 3.85a, 3.87, 3.112, 3.120 and 3.124 of Amendment 3-4 dated January 15, 1951. In addition, FAR 23.1555(d), 23.1557(c)(1) and 23.221(c) effective August 11, 1971, in lieu of CAR 3.767(a) and 3.124(c) for Model F19, F21, F21A, F21B, F22 and F22A aircraft. FAR 36 effective January 15, 1979, for Model F19 (S/N F-154 and up), F21, F21A, F21B, F22 and F22A aircraft. Dates of applications for Model 19, not available; for Model F19, September 10, 1971; for Model F21, March 1, 1978; for Model F21A, September 1, 1981; for Model F21B, April 27, 1983; for Model F22, August 1, 1988; for Model F22A, April 17, 1990. Specifications pertinent to Models F22B and F22C Certification basis Part 3 of the Civil Air Regulations, effective November 1, 1949 and 3.84a, 3.85a, 3.87, 3.112, 3.120 and 3.124 of Amendment 3-4, dated January 15, 1951. In addition, FAR 23.1555(d) and 23.1557(c)(1) effective August 11, 1971, in lieu of CAR 3.767(a). FAR 36, Appendix G, Amendments 1 through 18. Date of application for F22B and F22C, April 17, 1990. Page 15 of 20 1A9, Rev 21 Propellers and Propeller Accessories 1. Propeller (with Continental C85-12 or C85-12F engine) - Sensenich 72CK46 or 72CK48 or any other fixed pitch wood propeller which meets the following limits: Diameter - not over 74 ins., not under 70.5 ins. Static rpm at maximum permissible throttle setting, not over 2350, not under 2350. No additional tolerance permitted. 10 lb. (-50) 2. Propeller (with Continental C85-12 or C85-12F engine) - McCauley 1A90, fixed pitch metal, with the following limitations: Diameter - not over 71 ins., not under 69.5 ins. S tatic rpm at the maximum permissible throttle setting, not over 2400, not under 2300. No additional tolerance permitted. 26 lb. (-50) 3. Propeller (with Continental C85-12 or C85-12F engine) - Sensenich M74CK-2, fixed pitch metal, with the following limitations: Static rpm at the maximum permissible throttle setting, not over 2350, not under 2250. No additional tolerance permitted. Diameter - not over 72 ins., not under 70 ins. NOTE: The applicable Airplane Flight Manual shall be revised by the Modifier and approved by the FAA to reflect this installation change. 21 lb. (-50) 4. Propeller (with Continental O-200-A engine) - McCauley 1A105/SCM 6950, fixed pitch metal, with the following limitations: Diameter - not over 69 ins. Static rpm at the maximum permissible throttle setting, not over 2550, not under 2450. No additional tolerance permitted. 20 lb. (-50) 5. Propeller (with Continental O-200-A engine) - McCauley 1B90/CM7443, fixed pitch metal with the following limitations: Diameter - not over 74 ins., not under 71 ins. Static rpm at the maximum permissible throttle setting, not over 2400, not under 2300. No additional tolerance permitted. 20.9 lb. (-50) 6. (a) Propeller (with Lycoming O-235-L2C engine) - Sensenich 72CK-0-50, fixed pitch metal, with the following limitations: Diameter - not over 72 ins., not under 70 ins. Static rpm at the maximum permissible throttle setting, not over 2500, not under 240 0. No additional tolerance permitted. (b) Spinner - Taylorcraft P/N 2800-3 backing plate and 2800-4 spinner. 24.8 lb. (-50) 7. (a) Propeller (with Lycoming O-360-A4M engine) - Sensenich 76EM8S5-0-60, fixed pitch metal, with the following limitations: Diameter - not over 76 ins., not under 74 ins. Static RPM at the maximum permissible throttle setting, not over 2400, not under 2300. No additional tolerance permitted. (b) Spinner - Taylorcraft P/N 4315 backing plate and spinner installation. 39.9 lb. 5.0 lb. (-52.5) (-50.0) Engines and Engine Accessories - Fuel and Oil systems 19 F19 F21 & F21A F22 & F21B F22A F22B F22C 101. (a) Starter, Delco Remy 1109656 (b) Starter, Prestolite MZ4214 16 lb. 15.25 lb. 0.75 lb. (-24.00) - - - - - - (-24) (-17.4) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 102. Starter, Prestolite, P/N MZ4204 17 lb. - - - - (-33.75) (-33.75) (-33.75) - - - - 1A9, Rev 22 Page 16 of 20 Engines and Engine Accessories (Cont’d) 19 F19 F21 & F21A F22 & F21B F22A F22B F22C 104. Exhaust Stacks - Taylorcraft P/N/2835-1 (left), and 2840-1 (right) 10.5 lb. - - - - (-30) (-30) (-30) - - - - 105. Fuel Strainer - Taylorcraft P/N 2581 (Latour Gascolator Kit) .50 lb. (-17.4) (-17.4) (-17.4) (-17.4) (-17.4) (-17.4) (-17.4) 106. Carburetor Air Intake Housing Continental P/N A50256 or P/N 628122 or P/N 641534 1.44 lb. (-38) (-38) (-28) (-28) (-28) - - - - 107. Oil Cooler (optional) Stewart Warner P/N 8406R 2.8 lb. - - - - (-21.5) (-21.5) (-21.5) - - - - 108. Starter, Textron Lycoming, P/N 31A21210 11.3 lb. - - - - - - - - - - (-34) (-34) 109. Carburetor Air filter - Bracket Air Filter Assembly, P/N BA6110 1.0 lb. - - - - - - - - - - (-34) (-34) 110. Exhaust Stacks - Taylorcraft P/N 2835-12 (left), and 2840- 12 (right) 10.50 lb. - - - - - - - - - - (-30) (-30) 111. Fuel Strainer - Taylorcraft P/N 4313 .50 lb. - - - - - - - - - - (-17.4) (-17.4) 112. Carburetor Air Intake Hosing Taylorcraft P/N 4310 2.10 lb. - - - - - - - - - - (-25.6) (-25.6) Landing Gear and Skis 201. Two main wheel-brake assemblies, 6.00-6 type III (a) Cleveland Aircraft Products Co. Wheel Asembly No. C- 38500HMA Brake Assembly No. C-7000 (b) Cleveland Wheels and Brakes Wheel Assembly No. 401-7; Brake Assembly No. 30-3A 15 lb. (+2) - - - - (+2) - - - - - - - - - - - - - - - - - - - - 202. Two main wheel 4 ply rating tires, 6.00-6, type III, with regular tubes 17 lb. (+2) (+2) (+2) (+2) (+29.9) (+2) (29.9) Page 17 of 20 1A9, Rev 21 Landing Gear and Skis (Cont’d) 19 F19 F21 & F21A F22 & F21B F22A F22B F22C 203. Tail wheel assembly 6 x 2.00, full swiveling Scott Model 3- 24B 6 lb. (+193) (+193) (+193) (+193) - - (+193) - - Tail wheel assembly 6:50 x 2:50, full swiveling Maule Model SFSA-1-2 6.9 lb. (+193) (+193) (+193) (+193) - - (+193) - - Tail wheel assembly 8” pneumatic, full swiveling Scott Series 3200 with mounting adapter kit #3241- 1S 7.0 lb. (+193) (+193) (+193) (+193) - - (+193) - - Tail Wheel assembly 8:00 x 3:00 pneumatic, full swiveling Maule Model SFS- P8B-1-2 8.25 lb. (+193) (+193) (+193) (+193) - - (+193) - - Tail Wheel assembly 8:00 x 3:00 pneumatic, full swiveling Maule Model SFS- P8B-1-2 9.0 lb. (+193) (+193) (+193) (+193) - - (+193) - - 204. Two main wheel-brake assemblies, 6:00 x 6, type III, Parker Hannifin Wheel assembly No. 40-86, and Brake assembly No. 30-55 53 lb. 1.4 lb. - - - - - - - - (+2) (+2) (+2) (+2) (+29.9) (+29.9) (+2) (+2) (+29.9) (+29.9) 205. Skis (a) Aero Ski M1500 (b) Aero Ski M2000 35.6 lb. 43 lb. (-2) (-2.3) (-2) (-2.3) (-2) (-2.3) - - - - - - - - - - - - - - - - 206. Nose Wheel, Parker-Hannifen (Cleveland) #040-077000, Type III 2.6 lb. - - - - - - - - (-30.6) - - (-30.6) 207. Nose Wheel 4 ply rating tire 5.00 x 5 Type III with regular tube 5.9 lb. - - - - - - - - (-30.6) - - (-30.6) 301. (a) Battery and box, 12 volts, Bowers B25 (b) Battery and box, 12 volts Rebat S25, battery relay RBM8781-2 (c) Battery and box, 12 volts, Prestolite S-25, battery relay RBM 8781-2 (d) Battery and box, 12 volts, Rebat S25M; battery relay RBM 8781-2 (e) Battery and box, 12 volts, Concorde 25 RG (CB25M) 16 lb. 24.25 lb. 24.25 lb. 24.25 lb. 24.25 lb. (+70) - - - - - - - - - - (+71) - - - - - - - - - - (+71) - - - - - - - - - - (-21) - - - - - - - - (-21) - - - - - - - - - - (105) - - - - - - - - (105) 1A9, Rev 22 Page 18 of 20 Landing Gear and Skis (Cont’d) 19 F19 F21 & F21A F22 & F21B F22A F22B F22C 302. (a) Generator, Delco Remy 1876 Voltage regulator, Delco Remy 118323 (b) Alternator, Ford GPS #DOFF-10300-F Voltage Regulator, Ford- GPD #C6FF-10316-BA Voltage regulator, Ford- #D4FF-10316-BA (c) Alternator, Prestolite ALY-8420-G Voltage regulator, Prestolite FVR 4224 Voltage regulator, Electrodelta VR 417-2 Voltage regulator, Lamar P/N 800371-4 10 lb. 1 lb. 11.75 lb. 0.80 lb. 0.80 lb. 13 lb. 1.25 lb. .53 lb. 1.25 lb. (-24) (-18) - - - - - - - - - - - - - - - - - - (-21.64) (-17.4) (-17.4) - - - - - - - - - - - - - - - - - - (-40.25) (-17.4) (-17.4) - - - - - - - - - - - - (-40.25) (-17.4) (-17.4) - - - - - - - - - - - - (-40.25) (-17.4) (-17.4) - - - - - - - - - - - - - - - - - - (-17.4) - - - - - - - - - - - - - - - - (-17.4) Interior Equipment 401. (a) FAA Approved Airplane Flight Manual for Model 19 dated May 31, 1951 (b) FAA Approved Airplane Flight Manual for Model F19 dated July 3, 1973. (c) FAA Approved Airplane Flight Manual for Model F19 dated July 2, 1980. (d) FAA Approved Airplane Flight Manual for Model F21A dated November 15, 1982. (e) FAA Approved Airplane Flight Manual for Model F21B dated September 4, 1985. (f) FAA Approved Airplane Flight Manual for model F22 dated August 1, 1988. (g) FAA Approved Airplane Flight Manual for Model F22A dated February 20, 1991. (h) FAA Approved Airplane Flight Manual for Model F22B, dated July 14, 1992. (i) FAA Approved Airplane Flight Manual for Model F22C, dated April 3, 1992. 501. Stall Warning System (Dwgs: 3300 & 4035) .60 lb. - - - - - - (-2.25) (-2.25) (-2.25) (-2.25) Page 19 of 20 1A9, Rev 21 NOTE 1: Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). For the F19 and F21 the certificated empty weight and corresponding center of gravity location must include unusable fuel 18 lb. (-9) (fwd. tank). For the F21A, F21B, F22, F22A, F22B, and F22C, the certificated empty weight and corresponding center of gravity location must include unusable fuel 12 lb. (+24) (wing tanks). NOTE 2. The following placards must be displayed in full view of the pilot: Placard 19 F19 F21 F21A F21B F22 F22A F22B F22C (a) “Operates in normal or utility category in compliance with Approved Flight Manual.” X X X X X X - - - - - - (b) “Airplane marked for normal category only.” X X X X X X - - - - - - (c) “Acrobatics (including spins) prohibited in normal category.” X X X X X X - - - - - - (d) “No Smoking X X X X X X X X X (e) “Refill main tank in level flight and only when main tank is less than full.” X X X - - - - - - - - - - - - (f) “Fuel quantity gauge indicates contents of 12 gallon fuselage tank only.” X - - - - - - - - - - - - - - - - (g) “VFR day only” or “VFR day/night only” (when approved night lights are installed) - - X X X X X X - - - - (h) “Main tank usable fuel 9 gal.” (Must be displayed above the fuel selector valve) X X - - - - - - - - - - - - - - (i) “Aux. wing tank usable fuel 6 gal.” (Must be displayed above the fuel selector valve) - - X X - - - - - - - - - - - - (j) “Baggage not to exceed 72 lb.” X X X X - - - - - - - - - - (k) “Turn off anti-collision light in visible moisture conditions.” (when anticollision light is installed) - - X X X X X X X X (l) “Usable fuel 40 gal.” (Must be displayed on the fuel selector panel) - - - - - - X X X X X X (m) “Fill to bottom of tab only.” (Must be displayed adjacent to the fuel filler caps) - - - - - - X X X X - - - - (n) “20 gal.” (Must be displayed on the fuel filler caps) - - - - - - X X X X X X 1A9, Rev 22 Page 20 of 20 NOTE 2 (Cont’d) 19 F19 F21 F21A F21B F22 F22A F22B F22C (o) “Baggage not to exceed 10 lb.” (Must be displayed on the baggage compartment extension cylinder cover) - - - - X X X X X X X (p) “Baggage not to exceed 200 lb.” (Must be displayed on baggage compartment rear wall) - - - - - - - - X X X X X (q) “Flaps: Maximum 30o (3rd Notch) for Landing. No flap extension for Normal Take-Off.” - - - - - - - - - - X X X X (r) “Maximum Crosswind is 10 Kts.” - - - - - - - - - - X X X X (s) “Utility Category Intentional Spins, Flaps Down, Prohibited.” - - - - - - - - - - X - - - - - - (t) “Operate in Normal Category Only in Compliance with FAA Approved Flight Manual” - - - - - - - - - - - - - - X X (u) “No Acrobatic Maneuvers (including spins) are Approved for Normal Category Operations.” - - - - - - - - - - - - - - X - - (v) “Normal Category Acrobatics, Including Spins, Prohibited.” - - - - - - - - - - - - - - - - X (w) “Never Exceed Speed 148 MPH CAS” - - - - - - - - - - - - - - X X (x) “Maneuvering Speed 93 MPH CAS” - - - - - - - - - - - - - - X X (y) “Approved for Day/Night VFR/IFR Operations When Proper Equipment is Installed and Operating.” - - - - - - - - - - - - - - X X (z) “Pilot and Passenger Seats Must Be Locked in Position Prior to Take-Off - - - - - - - - - - - - - - X - - (aa) “Fuel Min. 100 Octane.” (Must be displayed on wing upper surfaces adjacent to fuel filler caps) - - - - - - - - - - - - - - X X (bb) “Fuel Drain.” (Must be displayed on wing upper surfaces adjacent to fuel filler caps) - - - - - - - - - - - - - - X X (cc) “Remove if Oil Temperature Runs Hotter than 210oF in Climb or 180oF in Cruise.” - - - - - - - - - - - - - - X X (dd) “Removal Ballast, 7.75 lbs.” - - - - - - - - - - - - - - X X NOTE 3. In order to comply with the requirements of Part 36 of the Federal Aviation Regulations, revised engine limits have been established for the Model F19, S/N F-154 and up. Serial number effectivity was determined by FAR 36.501. NOTE 4. The engine and oil cooling of the Model F21, F21A, F21B, F22 and F22A, with the Lycoming 0-235-L2C engine installed has not been investigated for more than 2600 rpm (112 HP) at full throttle in climb. -END- ``` ## ADs (8, in force first) - [AD 2008-09-18](https://openairdocs.org/ad/2008-09-18): Wing strut attach fittings · Taylorcraft A, BF, BF-60 and 34 more. Effective Jun 6, 2008 - [AD 2008-04-09](https://openairdocs.org/ad/2008-04-09): Left and right wing front and aft lift struts · Taylorcraft 2000 19, BC, BC-65 and 35 more. Effective Mar 28, 2008 - [AD 96-09-06](https://openairdocs.org/ad/96-09-06): Air Filter Assemblies · Maule Aerospace Technology 7ACA, 7ECA, 7FC and 180 more. Effective Jun 7, 1996 - [AD 87-03-08](https://openairdocs.org/ad/87-03-08): Oil Pressure Gauge Hose · Taylorcraft 2000 19, BC, BC-65 and 8 more. Effective Mar 1, 1987 - [AD 79-04-04](https://openairdocs.org/ad/79-04-04): Charging Circuit Fire Hazard · Taylorcraft 2000 F19. Effective Feb 23, 1979 - [AD 78-20-11](https://openairdocs.org/ad/78-20-11): Aileron Control Malfunction · Taylorcraft 2000 BC12-D and F19. Effective Oct 16, 1978 - [AD 51-09-03](https://openairdocs.org/ad/51-09-03): Fuel Shutoff Valve Clip · Taylorcraft A, Army TG-6 Conversions, BF and 37 more - [AD 75-18-05](https://openairdocs.org/ad/75-18-05): Engine Mount Bolts · Taylorcraft 2000 F19 ## Registered aircraft by registry model (OpenAirDocs) - [Taylorcraft F19](https://openairdocs.org/model/taylorcraft-f19): 85 aircraft (registry code 8850904) - [Taylorcraft 19](https://openairdocs.org/model/taylorcraft-19): 18 aircraft (registry code 8850902) - [Taylorcraft F21](https://openairdocs.org/model/taylorcraft-f21): 14 aircraft (registry code 8850906) - [Taylorcraft F21B](https://openairdocs.org/model/taylorcraft-f21b): 13 aircraft (registry code 8850909) - [Taylorcraft F-21A](https://openairdocs.org/model/taylorcraft-f-21a): 4 aircraft (registry code 8850907) - [Taylorcraft F22A](https://openairdocs.org/model/taylorcraft-f22a): 4 aircraft (registry code 8850910) - [Taylorcraft F-22](https://openairdocs.org/model/taylorcraft-f-22): 2 aircraft (registry code 8850908) - [Taylorcraft F22B](https://openairdocs.org/model/taylorcraft-f22b): 1 aircraft (registry code 8850912) - [Taylorcraft F22C](https://openairdocs.org/model/taylorcraft-f22c): 1 aircraft (registry code 8850911) ## STCs approved under this data sheet (82, first 50) - [STC SA01233SE](https://openairdocs.org/stc/SA01233SE): Fabrication and installation of Alaskan Bushwheel LLC tail wheel and fork assembly. ABI, LLC - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA01005DE](https://openairdocs.org/stc/SA01005DE): Installation of a EarthX ETX900-TSO Lithium battery. EarthX Inc. - [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [STC SA1070SO](https://openairdocs.org/stc/SA1070SO): Installation of Aqua Model 1500 floats.. Outpost X Aviation Inc. - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA24CH](https://openairdocs.org/stc/SA24CH): Installation of Baumann Model 1420 floats.. Baumann Floats LLC - [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc. - [STC SA03819NY](https://openairdocs.org/stc/SA03819NY): Installation and maintenance of Oratex 6000 Covering and Coating System. Lanitz-Prena Folien Factory GmbH - [STC SA01015SE](https://openairdocs.org/stc/SA01015SE): Installation of eligible Alaska Bushwheel, Inc. wheels and TSO-C62d tires. ABI LLC - [STC SA02553AK](https://openairdocs.org/stc/SA02553AK): Fabrication and installation of a Tail Wheel Anti-Shimmy Dampener. Keller Engineering Group LLC - [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 SA00344BO PAGE 2](https://openairdocs.org/stc/SA00344BO%20PAGE%202): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [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 SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley - [STC SA10077SC](https://openairdocs.org/stc/SA10077SC): Installation of push-button starter system.. Hartzell Engine Technologies, LLC - [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc. - [STC SA01768SE](https://openairdocs.org/stc/SA01768SE): Installation of an oil cooler system.. Steve's Aircraft - [STC SA4305WE](https://openairdocs.org/stc/SA4305WE): Installation of GAR-AERO wheel adapters and tundra type tires on the main landing gear. Seaplanes North LLC - [STC SA01669CH](https://openairdocs.org/stc/SA01669CH): Installation of Challenger Reusable Air Filter. Challenger Aviation Products Inc. - [STC SA10921SC](https://openairdocs.org/stc/SA10921SC): Installation of an alternator and regulator as a replacement to existing OEM generators and mechanical voltage regulators. Hartzell Engine Technologies, LLC - [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 SA02428AK](https://openairdocs.org/stc/SA02428AK): Installation of a hydraulically actuated ski drag assembly. Northern Airframes LLC - [STC SA02295SE](https://openairdocs.org/stc/SA02295SE): Installation of an alternate method of fastening aluminum wing ribs to wood spars. Rainbow Flying Service LLC - [STC SA01765SE](https://openairdocs.org/stc/SA01765SE): Installation of Alaskan Bushwheel TSO-C26d wheels, Part Number (P/N) ABI-1010. ABI, LLC - [STC SA01026SE](https://openairdocs.org/stc/SA01026SE): Improved fuel gascolator assembly.. Steve's Aircraft - [STC SA02825NY PAGE 2](https://openairdocs.org/stc/SA02825NY%20PAGE%202): Installation of Aerospace Logic Aircraft Instruments. Aerospace Logic Inc. - [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [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 SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC - [STC SA01227SE](https://openairdocs.org/stc/SA01227SE): Farication of Vortex Generator Kit.. Micro AeroDynamics 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 SA02300AK](https://openairdocs.org/stc/SA02300AK): Installation of FAA approved sealed lift struts in accordance with Airframes, Inc., Master Drawing List No. 315, Revision B, dated October 2, 2007, or later FAA approved revision and Airframes, Inc. Installation Instructions, AFI-II-TCSTRUT, Revision A, dated October 8, 2007, or later FAA approved revision.. Northern Airframes LLC - [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc - [STC SA2557NM](https://openairdocs.org/stc/SA2557NM): Installation of KS Avionics EGT/CHT-2( ) combined exhaust gas and cylinder head temperature monitoring system.. K S Avionics Inc - [STC SA00402SE](https://openairdocs.org/stc/SA00402SE): Installation of a remote spin-on oil filter adapter. (GC-1B w/Lycoming or Cont 360 engine installed). Aviation Development Corporation - [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International - [STC SA01158WI](https://openairdocs.org/stc/SA01158WI): Installation of Aero Enhancements UV250-1 Supplemental Instrument Panel Lightning System.. Aero Enhancements Inc. - [STC SA2683NM](https://openairdocs.org/stc/SA2683NM): Installation of Precise Flight, Inc. stand-by vacuum system (SVS). Precise Flight Inc - [STC SA01944CH](https://openairdocs.org/stc/SA01944CH): Modify airplane to fly on unleaded automotive gasoline, 87 minimum antiknock index, per ASTM Specification D-439 or D-4818 of any volatility class, A through E, or 82UL AVGAS per ASTM D-6227.. Experimental Aircraft Association Inc. All 82: https://openairdocs.org/tcds/1A9/stcs.md --- 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.