TCDS A00064IB

Page No. 1 2 3 4 Rev. No. 0 4 3 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00064IB Revision 4 Diamond Aircraft DA 50 C January 16, 2025 TYPE CERTIFICATE DATA SHEET NO. A00064IB This data sheet which is part of Type Certificate No. A00064IB prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Diamond Aircraft Industries GmbH Nikolaus-August-Otto Strasse 5 2700 Wiener Neustadt Austria I. Model DA 50 C (Normal Category), approved July 25, 2023 Engine 1 Continental Centurion 3.0 see Note 4 FAA Type Certification Data Sheet No. E00098EN Fuel Jet A, Jet A-1 (ASTM 1655) Engine Limits Maximum Take-Off, 2340 rpm (221 kW) Continuous Operation, 2300 rpm (200 kW) Propeller 1 MT Propeller Co. MT-propeller MTV-12-D/210-56 FAA Type Certification Data Sheet No. P25NE Propeller Limits Diameter 82.7 in., +0.0 in., -2.0 in; (2100 mm, +0.0mm, -50mm) Airspeed Limits Maximum Never Exceed Speed VNE 189 KEAS, 217 mph Maximum Structural Cruising Speed VNO 150 KEAS, 172 mph Design Cruising Speed VC 150 KEAS, 172 mph Operating Maneuvering Speed VO (up to 3637 lbs / 1650 kg) 117 KEAS, 135 mph VO (between 3640 lbs / 1651 kg to 4078 lbs / 1850 kg) 123 KEAS, 142 mph VO (above 4078 lbs / 1850 kg) 131 KEAS, 151 mph Maximum Flap Extending Speed VFE Full Flaps 118 KEAS, 136 mph VFE T/ O Flaps 130 KEAS, 150 mph Maximum Landing Gear Operation Speed VLO 160 KEAS, 184 mph Maximum Landing Gear Extended Speed VLE 160 KCAS, 184 mph C.G. Range Forward c/g position (aft of datum): at 3263 lbs. (1480 kg) 91.15 in. (2.315 meter) at 3858 lbs. (1750 kg) 91.15 in. (2.315 meter) at 4407 lbs (1999 kg) 95.28 in. (2.420 meter) Straight line variation between indicated points. Rearward c/g position (aft of datum): at 3263 lbs. (1480 kg) 92.71 in. (2.355 meter) At 3527 lbs. (1600 kg) 96.77 in. (2.458 meter) At 4407 lbs. (1999 kg) 97.25 in. (2.470 meter) Straight line variation between indicated points. A00064IB Page 2 of 4 Empty Wt. C.G. Range None Reference Datum 86.5 in. (2.196 meter) of the most forward point of the root rib on the stub wing. Leveling Means LH door frames Maximum Weight Takeoff (Normal Category) 4407 lbs. (1999 kg) Minimum Flight Mass 3263 lbs. (1480 kg) Landing 4407 lbs. (1999 kg) Zero Fuel weight 4189 lbs. (1900 kg) Minimum Crew 1 No. of Seats 5, If OÄM 50-047 is installed 4 Maximum Baggage Behind passenger seat row 198 lbs. (90 kg) Fuel Capacity LH Fuel Tank Total: 26 gallons (98.4 liters) Useable: 25 gallons (94.6 liters) RH Fuel Tank Total: 25.5 gallons (96.5 liters) Useable: 24 gallons (90.8 liters) Oil Capacity Maximum – 12.6 qts (12.0 liters) Minimum – 10.5 qts (10 liters) Maximum Operating Altitude 20,000 feet (6096 meters) Control Surface Movements Aileron trailing edge up 25º, ± 2º, trailing edge down 15º, +2/-0º Elevator trailing edge up 18.5º, ± 0.5º, trailing edge down 15º, ± 1º Elevator Trim Tab: 28º, ± 5º (nose up at elevator neutral) 25º, ± 5º (nose down at elevator neutral) Rudder: left 20º, ± 1º / right 25º, ± 1º Rudder Trim Tab: 35º, ± 2° (trim RH at rudder neutral) -13º, ± 2° (trim LH at rudder neutral) Flaps: Cruise flap setting 0°, ± 1° Take Off flap setting 20º, ± 1° Landing flap setting 38º, ± 1° Manufacturer’s Serial Numbers a) For aircraft produced at Diamond Aircraft Industries GmbH, N.A. Otto-Str. 5, A-2700 Wiener-Neustadt Austria, eligible serial numbers are 50.002, 50.003, 50.006, 50.C.A.A.007 and subsequent b) For aircraft produced at Diamond Aircraft Industries Inc., 1560 Crumlin Sideroad, London Ontario N5v 1S2, Canada, eligible serial numbers are 50.C.C.A.001 and subsequent Certification Basis Type Certification under 14 CFR Section 21.29 including the following requirements: Airworthiness Standards 14 CFR part 23, including Amendments 23-1 through Amendment 23-62 Additional regulations at Amendment 23-64 Diesel Cycle Engine Installation 14 CFR part 23, Amendment 23-64 23.2225, 23.2400, 23.2410, 23.2425, 23.2430, 23.2610, 23.2615 A00064IB Page 3 of 4 Electronic Engine Control Installation 14 CFR part 23, Amendment 23-64 23.2010, 23.2400(c), 23.2410 (a), 23.2510, 23.2515, 23.2520 TKS Ice Protection System Installation, modification OÄM 50-11/k 14 CFR part 23, Amendment 23-64 23.2010, 23.2415, 23.2540 and 14 CFR part 23, Amendment 23-65 23.2165 The detailed design standards used as a means of compliance for those regulations at Amendment 23-64 or later in accordance with § 23.2010 are documented in Diamond Model DA 50 C Detailed Design Standard Summary, Report No. 9.07.00 Chapter N007/2, Rev 1, dated 17 July 2024. Environmental Standards: 14 CFR part 36 Noise standards at Amendment 36-31 Special Conditions: None at this time Equivalent Safety Findings: None at this time Exemption: No exemptions have been identified Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) is listed in the Airplane Flight Manual and must be installed in the airplane for certification. In addition, the following items of equipment are required: Airplane Flight Manual, Document No. 9.01.01-E, Issue 11, dated 14-Dec-2022, or later approved revision. Maintenance Manual (including Airworthiness Limitations Section), Document No. 9.02.01, Issue 9, dated 15-Dec-2022, or later approved revision. Import requirements To be considered eligible for operation in the United States, each aircraft manufactured under this type certificate must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting foreign civil airworthiness authority which states: “The aircraft covered by this certificate has been examined, tested, and found to conform to the type design approved under the U.S. Type Certificate Number A00064IB and to be in a condition for safe operation.” Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. The type design approved under Type Certificate A00064IB is defined by Diamond Aircraft Report No. 9.07.00 Chapter V002/7 Rev. 2, dated 19 July 2023, or later approved revision. Service Information Each of the documents listed below must state that it is approved by the European Union Aviation Safety Agency (EASA). · Service bulletins · Structural Repair Manuals · Vendor Manuals A00064IB Page 4 of 4 · Aircraft Flight Manuals, and · Overhaul and Maintenance Manuals The FAA accepts such documents and considers them FAA-approved unless one of the following condition exists: · The documents change the limitations, performance, or procedures of the FAA approved manuals; or · The documents make an acoustical or emissions changes to this product’s U.S.type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. NOTE 1: Weight and Balance: A current weight and balance report, including a list of equipment included in the certificated empty weight, and loading instructions 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 full oil, coolant, and unusable fuel. NOTE 2: The placards specified in the FAA approved Airplane Flight Manual must be displayed. NOTE 3: Instructions for Continued Airworthiness and Service Life Limited components are included in the Maintenance Manual Document No. 9.02.01. (Revisions to Airworthiness Limitations must be approved by the FAA). NOTE 4: Approved engine configuration for installation in the DA 50 C: Continental Centurion 3.0 (sales designation CD-300). NOTE 5: For approved software versions of Garmin G1000 Integrated Avionics System, see DAI MSB 50-003, always latest version. NOTE 6: Exterior color is limited to that specified in Diamond Document No. 9.02.01. NOTE 7: Major structural repair must be accomplished at a FAA certified repair stations rated for composite aircraft structure work, in accordance with Diamond repair methods approved by EASA and accepted by FAA. NOTE 8: The following modification is required to be incorporated on the Diamond DA 50: MÄM 50-097 Exhaust System Modification. NOTE 9: Flights into known or forecast icing conditions is approved, if the ice protection system in accordance to Design Change OÄM 50-011 is installed. NOTE 10: Approved Non-Basic Major Changes on the DA 50 C are: MÄM 50-110 Turbocharger Interface Change OÄM 50-011/k Ice protection system (TKS) OÄM 50-047 Business Seating Configuration 1st Passenger Row .....END.....