# TCDS A00053SE: Cub Crafters Inc. - Type: Type certificate data sheet - Status: Current - Holder: Cub Crafters Inc. - Revision: 8 - Revised: September 17, 2026 - Product: Aircraft, Small Airplane - Certification basis: Part 23 - Registered aircraft: 103, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/31/20/31207e154473059ecb44d07d94b4d558c40374a1f401c298f5b8d6828702348f - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID191313249120260925154917.0001 - Page: https://openairdocs.org/tcds/A00053SE ## Models (2) As the data sheet lists them. - CC19-180 - CC19-215 ## 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 Rev. No. 8 5 8 7 8 8 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00053SE Revision 8 CUB CRAFTERS CC19-180 CC19-215 Date: September 17, 2026 TYPE CERTIFICATE DATA SHEET A00053SE This data sheet, which is part of Type Certificate No. A00053SE, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of Title 14, Code of Federal Regulations. Type Certificate Holder: Cub Crafters, Inc. 1918 South 16th Ave. Yakima, WA 98903 I - Model CC19-180 (Normal and Utility Category)(Tailwheel and Floats), Approved June 2, 2016 Engine: Engine Manufacturer: Lycoming Engines, An Operating Division of AVCO Corporation Number of Engines: One (1) Engine TC Number: E-286 Engine Model Designation: O-360-C1G Fuel: 100LL (blue) grade aviation fuel. Engine Limits: Maximum takeoff power: 180 horsepower at 2700 RPM Maximum continuous power: 180 horsepower at 2700 RPM See Engine Type Certificate Data Sheet E-286 for additional limitations. Propeller: Propeller Manufacturer: Hartzell Propeller, Inc. Number of Propellers: One (1) Propeller TC Number: P-920 Propeller Model Designation: HC-C2YR-1N/NG8301-5 Diameter Limits: 78 inches. No diameter reduction allowed High Pitch angle: 29.0º-30.0º Low Pitch Angle: 9.7º-10.0º See Propeller Type Certificate Data Sheet P-920 for additional limitations. Airspeed Limits VO (2300 lbs) 86 KCAS VO (1980 lbs) 79 KCAS VFE (46º) 73 KCAS VNO 117 KCAS VNE 142 KCAS VLO (Amphibious Floats) 117 KCAS VLE (Amphibious Floats) 117 KCAS Center of Gravity Normal Category (C.G.) Range Aft Limits: 79.5” aft of datum (1,600 lbs. to 2,300 lbs.) 78.5” aft of datum (1,300 lbs.) Forward Limits: 72.0” aft of datum ((1,300 lbs. to 1,680 lbs.) 79.1’ aft of datum (2,300 lbs.) Utility Category Aft Limits: 78.0” aft of datum (1,300 lbs. to 1,980 lbs.) Forward Limits: 72.0” aft of datum ((1,300 lbs. to 1,680 lbs.) 75.4” aft of datum (1,980 lbs.) Straight line variation between points. A00053SE Page 2 of 6 I – CC19-180 (cont’d) When equipped with Wipaire 2100A amphibious and 2100S seaplane floats Normal Category Aft Limits: 79.5” aft of datum (2,070 lbs. to 2,300 lbs.) 78.0” aft of datum (1,500 lbs.) Forward Limits: 71.5” aft of datum ((1,500 lbs. to 2,015 lbs.) 75.0’ aft of datum (2,300 lbs.) Straight line variation between points. Datum: Datum is 60” forward of the wing leading edge. Levelling means: See latest approved revision of the CC19-180 “Pilot’s Operating Handbook and FAA Approved Flight Manual”. Maximum Weights: Normal Category Maximum Ramp: 2,300 lbs. Maximum Takeoff: 2,300 lbs. Maximum Landing: 2,300 lbs. Utility Category Maximum Ramp: 1,980 lbs. Maximum Takeoff: 1,980 lbs. Maximum Landing: 1,980 lbs. Minimum Crew: One (1) Pilot Number of Seats: Two (2) seats total Pilot located at 72.2” aft of datum Passenger located at 97.5” aft of datum Maximum Compartment As defined in the latest approved revision of the CC19-180 “Pilot’s Operating Handbook and Weights: FAA Approved Flight Manual”. Fuel Capacity: One 24.5 gallon tank in each wing at 84.5” aft of datum; 23 gallons usable in each wing, 1.5 gallons unusable in each wing (49 gallons total; 46 gallons usable; 3 gallons unusable). Note: add weight of unusable fuel to the certificated weight. Oil Capacity: 8 quart total See Lycoming Service Instruction 1014 for approved oil. Maximum Operating 14,000 feet Altitude Control Surface Wing flaps: 0º, 16º, 33º, 46º ± 1.0º Movements: Ailerons: Up: 20º ± 1.5º Down 14º ± 1.5º Elevator: Up 25º ± 1.5º Down 15º ± 1.5º Stabilizer Leading edge Up 4.9º +0.1º/-0.0º Down 2.5º +0.1º/-0.0º Rudder Left 22.5º +0/-0.75º Right 25º +0/-0.75º See the latest FAA approved revision of the CC19 “Airplane Maintenance Manual CC19 Series,” or other FAA approved data, for control system rigging instructions and setting flaps up (0º) configuration. Operational Limitations: Day-Night, Visual Flight Rules (VFR) Airframe Life Limits: See the latest FAA approved revision of the CC19-180/CC19-215 Document number XC10000AMM “Aircraft Maintenance Manual CC19 Series,” revision NC or later FAA approved version. Additional Equipment The latest FAA Approved/ Revision of CC19-180 document number XC10000AFM “CC19-180 Necessary for Type Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual,” revision NC or later Certification: FAA approved version. Page 3 of 6 A00053SE II – Model CC19-215 (Normal Category)(Tailwheel, Tricycle, and Floats), Approved November 10, 2020 Engine: Engine Manufacturer: Lycoming Engines, An Operating Division of AVCO Corporation Number of Engines: One (1) Engine TC Number: E00006NY Engine Model Designation: IO-390-D3B6 Fuel: 100LL (blue) grade aviation fuel. Engine Limits: Maximum takeoff power: 215 horsepower at 2700 RPM (3 minute) Maximum continuous power: 180 horsepower at 25.5 inches mercury manifold pressure See Engine Type Certificate Data Sheet E-286 for additional limitations. Propeller: See NOTE 6 for approved propellers. Airspeed Limits VO (2300 lbs) 86 KCAS VO (1980 lbs) 79 KCAS VFE (46º) 73 KCAS VNO 117 KCAS VNE 142 KCAS VLO (Amphibious Floats) 117 KCAS VLE (Amphibious Floats) 117 KCAS Center of Gravity Normal Category – Tailwheel Configuration (C.G.) Range Aft Limits: 79.5” aft of datum (1,600 lbs. to 2,300 lbs.) 78.5” aft of datum (1,300 lbs.) Forward Limits: 72.0” aft of datum (1,300 lbs. to 1,680 lbs.) 79.1” aft of datum (2,300 lbs.) Normal Category – Tricycle Configuration Aft Limits: 79.5” aft of datum (1,868 lbs. to 2,300 lbs.) 78.5” aft of datum (1,300 lbs.) Forward Limits: 71.0” aft of datum (1,300 lbs. to 1,812 lbs.) 79.1” aft of datum (2,300 lbs.) Normal Category –Floats Configuration, Wipaire 2100A or 2100S Aft Limits: 79.5” aft of datum (2,070 lbs. to 2,300 lbs.) 78.0” aft of datum (1,500 lbs.) Forward Limits: 71.5” aft of datum (1,500 lbs. to 2,015 lbs.) 75.0” aft of datum (2,300 lbs.) Straight line variation between points. Datum: Datum is 60” forward of the wing leading edge. Levelling means: See latest FAA approved revision of the CC19-215 tailwheel version document number XC11000AFM “Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual,” or CC19-215 tricycle version document number XC11020AFM “Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual.” Maximum Weights: Normal Category Maximum Ramp: 2,300 lbs. Maximum Takeoff: 2,300 lbs. Maximum Landing: 2,300 lbs. Minimum Crew: One (1) Pilot Number of Seats: Two (2) seats total Pilot located at 72.2” aft of datum Passenger located at 97.5” aft of datum A00053SE Page 4 of 6 Maximum Compartment See latest FAA approved revision of the CC19-215 tailwheel version document number Weights: XC11000AFM “Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual” or CC19-215 tricycle version document number XC11020AFM “Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual.” Fuel Capacity: One 24.5 gallon tank in each wing at 84.5” aft of datum; 22.3 gallons usable in each wing, 2.2 gallons unusable in each wing (49 gallons total; 44.6 gallons usable; 4.4 gallons unusable). Note: add weight of unusable fuel to the certificated weight. Oil Capacity: 7 quart total See Lycoming Service Instruction 1014 for approved oil. Maximum Operating 14,000 feet Altitude Control Surface Wing flaps: 0º, 16º, 33º, 46º ± 1.0º Movements: Ailerons: Up 20º ± 1.5º Down 14º ± 1.5º Elevator: Up 25º ± 1.5º Down 15º ± 1.5º Tailwheel Configuration: Stabilizer Leading Edge: Up 4.9º +0.1º/-0.0º Down 2.5º +0.1º/-0.0º Rudder: Left 22.5º +0/-0.75º Right 25º +0/-0.75º Tricycle Configuration: Stabilizer Leading Edge: Up 5.1º +0.1º/-0.0º Down 2.8º +0.1º/-0.0º Rudder: Left 19.5º +0/-0.75º Right 22º +0/-0.75º Floats Configuration: Stabilizer Leading Edge: Up 5.1º +0.1º/-0.0º Down 2.8º +0.1º/-0.0º Rudder: Left 22.5º +0/-0.75º Right 25º +0/-0.75º See the latest FAA approved revision of the CC19 “Airplane Maintenance Manual CC19 Series,” or other FAA approved data, for control system rigging instructions and setting flaps up (0º) configuration. Operational Limitations: Day-Night, Visual Flight Rules (VFR) Airframe Life Limits: See the latest FAA approved revision of the CC19-180/CC19-215 document number XC10000AMM “Aircraft Maintenance Manual CC19 Series,” revisions M or later FAA approved version. Additional Equipment The latest FAA approved revision of the CC19-215 tailwheel version document number Necessary for Type XC11000AFM “Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual” Certification: or CC19-215 tricycle version document number XC11020AFM “Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual.” DATA PERTINENT TO ALL MODELS Manufacturer’s The information contained herein is applicable to Serial Numbers CC19-0003 and greater. Serial Numbers: Certification Basis: Title 14, Code of Federal Regulations (14 CFR), Part 23, effective December 18, 1964, as amended by Amendments 23-1 through 23-62. 14 CFR Part 36 as amended on the date of certification. For airplanes equipped with an EarthX rechargeable lithium battery, compliance has been shown with the following 14 CFR Part 23 sections at Amendment 23-64 for the battery system: 23.2010, 23.2325(g), 23.2410, 23.2510, 23.2605(c), and Appendix A to Part 23. Page 5 of 6 A00053SE DATA PERTINENT TO ALL MODELS (cont’d) Equivalent Level of Emergency exit requirements of 14 CFR §23.807 in accordance with ELOS Memorandum number Safety Finding: TC10279SE-A-C-1. Electronic display instruments of 14 CFR §23.1311 in accordance with ELOS Memorandum number AT12936SE-A-S-1. Correction to errors in 14 CFR Part 23 Amendment 23-62 in accordance with ELOS Memorandum number TC10279SE-A-G-9. Trim requirements of 14 CFR §23.161(c)(1)(i) and (c)(4)(i) in accordance with ELOS Memorandum number AT12949SE-A-F-1 Engine power and mixture controls requirements of 14 CFR §23.1143(g) and §23.1147(b) in accordance with ELOS Memorandum number AT-13911SE-A-P-1 Exemption: Exemption from the requirements of 14 CFR §23.562 Regulatory Docket No. FAA-2009-1161. TC Number: CC19-180 CC19-215 TC Issuance Date: June 2, 2016 November 10, 2020 TC Application Date: February 11, 2013 January 30, 2019 Production Basis: Production Certificate 72NM. Required Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. NOTES FOR ALL MODELS: NOTE 1: A current weight and balance report with a list of equipment included in the certificated empty weight must be provided for each aircraft at the time of original airworthiness certification. This is contained in the latest FAA Approved/Accepted Revision of document XC10000AFM “CC19-180 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual,” document XC11000AFM “CC19-215 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual,” or document XC11020AFM “CC19-215 Pilot’s Operation Handbook and FAA Approved Airplane Flight Manual.” This is in accordance with 14 CFR §23.23, §23.25, §23.29, and §23.31. NOTE 2: The placards specified in the latest FAA Approved/Accepted Revision of document XC10000AFM “CC19-180 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual,” document XC11000AFM “CC19-215 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual,” or document XC11020AFM “CC19-215 Pilot’s Operation Handbook and FAA Approved Airplane Flight Manual,” the applicable operating rules, or the Certification Basis are required to be installed in the airplane. NOTE 3 The airplane must be subsequently maintained in accordance with the Instructions for Continued Airworthiness, and Airworthiness Limitations section, as contained in CC19-180/CC19-215 document number XC10000AMM “Aircraft Maintenance Manual CC19 Series,” revision NC or later FAA approved version for the CC19-180, revision M or later FAA approved version for the tailwheel CC19-215, or revision N or later FAA approved version for the tricycle CC19-215. This is in accordance with 14 CFR 23.1529. NOTE 4 Installation of Wipaire 2100A amphibious or 2100S seaplane floats series floats in accordance with latest FAA Approved Cub Crafters drawings: XC44001 XC44100, XC44500, XC44700, XC44750, XC84000. Installation requires approved flight manual supplements. NOTE 5 Installation of Wipaire 2100A amphibious floats requires installation of Wipaire STC SA39CH “Installation of an Amphibian Landing Gear Position Advisory System”. NOTE 6 The following propellers are approved for installation on model CC19-215 airplanes: Propeller Manufacturer: Hartzell Propeller, Inc. Number of Propellers: One (1) Propeller TC Number: P-920 A00053SE Page 6 of 6 Propeller Model Designation: HC-C2YR-1N/NG8301-7 Diameter Limits: 76 inches. No diameter reduction allowed High Pitch angle: 29.0º to 30.0º Low Pitch Angle: 12.3° to 13.3º See Propeller Type Certificate Data Sheet P-920 for additional limitations. Propeller Manufacturer: Hartzell Propeller, Inc. Number of Propellers: One (1) Propeller TC Number: P-920 Propeller Model Designation: HC-C2YR-1NW/NG8301W-7 Diameter Limits: 76 inches. No diameter reduction allowed High Pitch angle: 29.0º to 30.0º Low Pitch Angle: 12.3° to 13.3º See Propeller Type Certificate Data Sheet P-920 for additional limitations. Propeller Manufacturer: Hartzell Propeller, Inc. Number of Propellers: One (1) Propeller TC Number: P00016CH Propeller Model Designation: 3C1-R430A1/80C01-4 Diameter Limits: 76 inches. No diameter reduction allowed High Pitch angle: 29.0° to 30.0° Low Pitch Angle: 10.4° to 11.4° See Propeller Type Certificate Data Sheet P00016CH for additional limitations. Propeller Manufacturer: Hartzell Propeller, Inc. Number of Propellers: One (1) Propeller TC Number: P00016CH Propeller Model Designation: 3C1-R430A1/80C01W-4 Diameter Limits: 76 inches. No diameter reduction allowed High Pitch angle: 29.0° to 30.0° Low Pitch Angle: 10.4° to 11.4° See Propeller Type Certificate Data Sheet P00016CH for additional limitations. --END-- ``` ## ADs (1, in force first) - [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022 ## Registered aircraft by registry model (OpenAirDocs) - [Cub Crafters CC19-215](https://openairdocs.org/model/cub-crafters-cc19-215): 63 aircraft (registry code 2470009) - [Cub Crafters CC19-180](https://openairdocs.org/model/cub-crafters-cc19-180): 40 aircraft (registry codes 2470004, 05632CR) ## STCs approved under this data sheet (15) - [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation - [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [STC SA02765SE](https://openairdocs.org/stc/SA02765SE): Installation of Acme Stinger tailwheel landing gear shock absorber. Acme Suspensions LLC - [STC SA39CH](https://openairdocs.org/stc/SA39CH): Installation of an Amphibian Landing Gear Position Advisory System/Laser Gear Advisory System. Wipaire Inc. - [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc. - [STC SA02576AK](https://openairdocs.org/stc/SA02576AK): Installation of Cleveland and ABI, LLC Wheel and Brake Kits. ABI LLC - [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation - [STC SA02553AK](https://openairdocs.org/stc/SA02553AK): Fabrication and installation of a Tail Wheel Anti-Shimmy Dampener. Keller Engineering Group LLC - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc. --- 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.