TCDS E00022CH

Page No. 1 2 3 4 5 6 Rev. No. 0 0 0 0 0 0 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E00022CH Revision 0 DeltaHawk Engines, Inc. DHK180A4 April 7, 2023 TYPE CERTIFICATE DATA SHEET NO. E00022CH Engines of models described here that conform with this data sheet (which is part of Type Certificate No. E00022CH) and other approved data on file with the FAA, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations provided they are installed, operated, and maintained as prescribed by the FAA approved manufacturer’s manuals and other FAA approved instructions. TYPE CERTIFICATE HOLDER: DeltaHawk Engines, Inc. 2300 South Street Racine, Wisconsin, 53404 USA I. MODEL DHK180A4 ENGINE TYPE Four-cylinder, 202 cubic inch, inverted V-configured, liquid-cooled, piston ported 2-cycle, mechanical direct injection, turbo-supercharged, mechanical supercharged, direct drive, compression-ignition engine RATINGS (See Note 1), HP Takeoff (5 min) Max Continuous Max Recommended Cruising Max Best Economy Cruising Critical Altitude 180 at 2600 RPM 135 at 2700 RPM 135 at 2200 RPM 135 at 2200 RPM 17,500 ft CONTROL SYSTEM Analog Electro-Mechanical Idle Governor FUEL ASTM D1655 (Jet A and Jet A1 with FSII), Minimum CN 30 OIL Oil Specification Oil Sump Capacity Phillips 66 Victory® Diesel Aviation Oil 10W-40 (see Installation Manual 500010 for approved oil) Dry Sump Engine; See Installation Manual 500010 for oil sump requirements. PRINCIPAL DIMENSIONS Length, in Width, in Height, in 34 26 24 DRY WEIGHT lbs 357 lbs, including starter, alternator, turbocharger, exhaust to turbocharger DISPLACEMENT cu. in. (ltrs) BORE x STROKE, in COMPRESSION RATIO 202 (3.3) 4.01 x 4.00 20.1:1 Geometric E00022CH Page 2 of 6 PRODUCTION BASIS None. Before original airworthiness certification of each engine, an FAA representative must perform a detailed inspection for workmanship, materials, conformity with the approved technical data. In the event of an application for a standard airworthiness certificate or, if an applicant intends to produce a new engine under 14 CFR § 21.183(d), and the applicant is manufacturing, building, or assembling to another person’s type certificate, the applicant must provide written evidence of permission from the type certificate holder. Conduct of such activity without written evidence of permission may be a violation of 49 U.S.C. § 44704(a)(3). CERTIFICATION BASIS DHK180A4 14 CFR Part 33 effective February 1, 1965, and Amendments 33-1 through 33-34 Equivalent Level of Safety Findings in accordance with 14 CFR Part 21: ELOS number, date and subject Regulation modified by ELOS TC09818EN-E-0-0, dated October 14, 2020, Power Level Indication and Fuel System Icing 14 CFR §§ 33.7(b)(1) and 33.35(b) APPLICATION Application Date Type Certificate Date DHK180A4 November 08, 2018 April 07, 2023 Serial Nos. Eligible E000001 Note 1: ENGINE RATINGS Engine Ratings are based on calibrated test stand, under the conditions specified by the engine TC holder: I. Barometric and Humidity conditions corrected to Sea Level Static Standard day conditions II. Jet A and Jet A1 with FSII per ASTM D1655 E00022CH Page 3 of 6 Note 2: TEMPERATURE LIMITS Parameters Units Low Red Line Do Not Exceed Low Range Caution Normal Range High Range Caution High Red Line Do Not Exceed Coolant Temperature °F <-34 n/a <150 150 220 >220 238 >238 Cylinder Head Temperature °F n/a n/a n/a 260 >260 270 >270 Oil Temperature (manifold) °F n/a n/a <120 120 207 >207 229 >229 Fuel Inlet Temperature °F <-40 n/a -40 225 n/a >225 Interblower Temperature (IBT) °F n/a n/a n/a n/a >350 Intake Manifold Temperature °F n/a n/a n/a 185 >185 250 >250 EGT (4) °F n/a n/a n/a 1000 >1000 1200 >1200 Cylinder-Cylinder EGT Variation °F n/a n/a 0 150 >150 250 n/a Turbocharger Inlet Temperature (TIT) °F n/a n/a <400 400 1200 >1200 1400 >1400 See Operator Manual 500020 for complete limit conditions Note 3: FUEL AND OIL PRESSURE LIMITS Parameters Units Low Red Line Do Not Exceed Low Range Caution Normal Range High Range Caution High Red Line Do Not Exceed Intake Manifold Pressure in-Hg n/a n/a 30.5 107 >107 112 >112 Oil Manifold Pressure* psig <19 19 <40 40 80 >80 100 >100 Crankcase Pressure psig n/a n/a -5 8 >8 10 >10 Fuel Pressure* psig <10 10 <25 25 125 >125 150 >150 * See Operator Manual 500020 for complete limit conditions Note 4: ACCESSORY DRIVE PROVISIONS LIMITS The following accessory drives are available: Optional Accessory Rotation Direction Drive Ratio ACC: Engine Max. Torque (in-lb) Maximum Overhang Moment (lb-in) Accessory Max Weight (lb) Continuous Static AND20000* CCW 1.4:1 100 800 25 6 AND20010** CCW 1.4:1 125 825 50 No requirement * No oil supply hole is provided ** Driven speed is 1.4x engine speed E00022CH Page 4 of 6 Note 5: MODEL DESCRIPTION DHK180A4 is the base model. Note 6: TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN: The following components are provided as part of the engine type design: Engine Component Manufacturer and Part Number Installation Requirements Starter SKY-TEC® 122-24HT See Maintenance Manual 500040 Alternator Plane-Power® AL24-70-1 See Maintenance Manual 500040 Engine Idle Governor DeltaHawk® 099765 Install in cabin; 24 V aircraft electrical power Engine Speed Sensor Honeywell® LCZ260 See Installation Manual 500010 Fuel Isolation Valve Lee® CKRB2506201A See Installation Manual 500010 Glow Plug Bosch® F 033 000 004 (GLP2-5) See Maintenance Manual 500040 Note 7: AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF ENGINE TYPE DESIGN: The following components have been shown to be compatible with the engine installation by incorporation during type design testing. See Installation Manual 500010 for system requirements which must be fulfilled by alternative components, or other components approved or accepted by the FAA Engine Component Manufacturer and Part Number Installation Requirements Air Filter Pro-M 117 See Installation Manual 500010 Fuel Filtration: 2µm: Racor 110A Fuel Filter Hsg with R11S 2µm filter 30µm: 31863 Fuel Manager Series 30µm Filter and Water Separator See Installation Manual 500010 Electric Fuel Boost Pump: Weldon P/N 18032-B See Installation Manual 500010 Fuel Hose: Aeroquip® AE3663161 Fire Resistant, See Installation Manual 500010 Oil Filtration: Champion® Spin-On Oil Filter CH48109-1 SAE ARP1400 (75% @ 25µm) See Installation Manual 500010 Oil Hose: Aeroquip® AE601, AE666 used for suction line Fire Proof, Vacuum Rated, See Installation Manual 500010 Coolant Hose: Federal Hose 5515-1500 See Installation Manual 500010 Note 8: SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS I. Fuel system icing inhibitor (FSII): PRIST® or other fluids approved or accepted by the FAA II. Use of wet propeller de-icing fluids containing alcohol or solvents is prohibited E00022CH Page 5 of 6 Note 9: ENGINE MOUNT SYSTEM PROVISIONS The following mounts have been shown compatible with the engine installation by incorporation during type design testing: • LORD® P/N: J-27402-24 • Barry® P/N: 94150-40 Other mounts as approved or accepted by the FAA Note 10: POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS AND LIMITS AS APPLICABLE The engine is equipped with a turbosupercharger and a mechanical supercharger. These components are part of the type design. See Notes 1 and 2 for operating limits associated with these components. Note 11: Special Installation Requirements I. Engine may be mounted in pusher or tractor configuration II. Propeller: a. Mounting Flange: AS-127 #2 b. Minimum Propeller Mass Moment of Inertia (lb-in²): 3707 c. Maximum Propeller Mass Moment of Inertia (lb-in²): 7181 d. Maximum propeller extension: 6 inches III. Dry Sump Oil tank Note 12: MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS None Note 13: SPECIAL OPERATING PROCEDURES OR LIMITATIONS I. Start and warm up the engine every 30 days II. Cold ambient engine starting procedure described in Operator Manual 500020 Note 14: SPECIAL REPAIR OR OVERHAUL LIMITATIONS Refer to DeltaHawk Maintenance Manual 500040 and Overhaul Manual 500030 for component and core engine life and repair information E00022CH Page 6 of 6 Note 15: APPLICABLE MANUALS Instructions for Continued Airworthiness are incomplete. The engine will be eligible for return to service when the ICA is complete and accepted. The following manuals have not been approved and/or accepted by the FAA: Installation Manual 500010 Operator Manual 500020 Maintenance Manual 500040 Overhaul Manual 500030 Note 16: IMPORT REQUIREMENTS STATEMENT FOR FOREIGN MANUFACTURED ENGINES Not applicable Note 17: LIFE LIMITED PART INFORMATION See DeltaHawk Maintenance Manual 500040 for information relating to Airworthiness Limitations, including Life Limited Parts and Mandatory Inspections Note 18: MILITARY MODEL INFORMATION Not applicable Note 19: HORIZONTAL OR VERTICAL INSTALLATION (ROTORCRAFT) Not applicable Note 20: CENTER OF GRAVITY TABULATION Envelope 34 L x 26 W x 24 H inches Center of gravity (Approximate) 3.38 below thrust line 13.32 rear of flywheel face 0.22 offset from midline (toward alternator) inches Note 21: VIBRATION DAMPER PROVISION LIMITATIONS Not Applicable -- END --