TCDS A00079CE

Page No. 1 2 3 4 Rev. No. 0 0 0 0 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00079CE Revision 0 KC-100 May 19, 2021 TYPE CERTIFICATE DATA SHEET No. A00079CE This Data Sheet which is a part of Type Certificate No. A00079CE 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 Korean Aerospace Industries, LTD 78, Gongdan 1-Ro, Sanam-Myun Sacheon-City, Gyeongnam (52529) Republic of Korea I. Model KC-100 (Normal Category), Approved May 19, 2021 Engines One Teledyne Continental Motors. TSIOF-550-K, Type Certificate Data Sheet (TCDS) E5S0 Fuel 100LL minimum grade aviation gasoline Engine Limits Maximum Continuous Power Rating 315 HP (2,500 RPM) Propeller and Propeller Limits Hartzell Propeller Inc. PHC-J3Y1F-1N/N7605B, TCDS P36EA Diameter : 78in (1,981.2 mm) No. of Blades : 3 Low Pitch : 12.4°±0.2° High Pitch : 35.0°±1.0° Spinner : Hartzell P/N A2295-13P No operating Limitation to 2,500RPM Airspeed Limits KIAS KCAS VNE Never Exceed Speed (Up to 14,000ft) 200 202 VNE Never Exceed Speed (25,000ft) 159 160 Decrease 3.7 Knots for each 1,000-ft above 14,000ft (Press Alt) VNO Maximum Structural Cruising Speed (Up to 14,000ft) 174 175 VNO Maximum Structural Cruising Speed (25,000ft) 138 139 Decrease 3.3 Knots for each 1,000-ft above 14,000ft (Press Alt) VO Operating Maneuvering Speed (3,600lbs) 145 146 VO Operating Maneuvering Speed (3,300 – 3,600 lbs) 138 139 VO Operating Maneuvering Speed (2,900 – 3,300 lbs) 130 131 VO Operating Maneuvering Speed (Up to 2,900 lbs) 124 125 VFE Flap Extended Speed (Take-off) 120 120 VFE Flap Extended Speed (Landing) 108 107 Center of Gravity (C.G.) Range Forward limit 152.0 in (3,860 mm) (21% MAC) aft of datum at Maximum Takeoff Weight 151.6 in (3,850 mm) (20.2% MAC) aft of datum at Maximum Landing Weight 151.4 in (3,846 mm) (19.89% MAC) aft of datum at Maximum Zero fuel Weight 150.5 in (3,822 mm) (18% MAC) aft of datum at Minimum Weight Aft limit 157.0 in (3,987 mm) (31% MAC) aft of datum at All Weight Empty Weight (C.G.) Range None Page 2 of 3 A00079CE Maximum Weights Take-off 3,600 lbs (1,633 kg) Landing 3,470 lbs (1,574 kg) Zero Fuel 3,410 lbs (1,547 kg) Datum. 108.5 in (2,755 mm) in front of the forward of firewall Leveling Means. Door sill and leveling points as defined in AFM Minimum Crew 1 pilot Number of Seats 4 (2 at 153 in (3,890 mm), 2 at 187 in (4,758 mm)) See NOTE 4 Maximum Baggage 150 lbs (68 kg) at 217 in (5,500 mm) Fuel Capacity Total: 94 gallon (355.8 L) at 161.4 in (4,101 mm) Usable: 88 gallon (333.1 L) at 161.5 in (4,103 mm) (See NOTE 1) Oil Capacity 8 quarts (7.6 L) Maximum Operational Altitude The aircraft is limited to 25,000 ft MSL Control Surface Movements Aileron 15.5°±1.0° upward 12.5°±1.0° downward Aileron trim 15.0°±1.5° upward 15.0°±1.5° downward Elevator 15.0°±1.0° upward 20.0°±1.0° downward Elevator trim 15.0°±1.5° upward 15.0°±1.5° downward Rudder 25.0°±1.0° left 25.0°±1.0° right Flaps 20.0°±2.0° (Take-off) 40.0°±2.0° (Landing) Additional Limitation Airframe life limit: 12,000 flight hours DATA PERTINENT TO ALL MODELS. Serial Numbers Eligible. Each individual aircraft manufactured under this type certificate must be accompanied by an Export Certificate of Airworthiness as noted below under “Import Requirements” when an application for a U.S. airworthiness certificate is made. Model KC-100 serial number 13-001 and subsequent - YY (2 digit Year) – XXX (Number of production of the year) Import Requirements For aircraft produced in Korea, the FAA can issue a U.S. airworthiness certificate based on a Ministry of Land, Infrastructure and Transport (MOLIT) Export Certificate of Airworthiness (Export C of A). The Export C of A should contain the following statement, “The [insert aircraft MODEL] covered by this certificate conforms to the type design approved under U.S. Type Certificate Number A00079CE, and is found 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. Certification Basis 14 CFR Part 23 Amendments 23-59 14 CFR Part 36 Amendments 36-28 Page 3 of 3 A00079CE Equivalent Level of Safety as follows: (a) ACE-15-07 for §23.777(d) Cockpit controls and §23.781(b) Cockpit control knob shape; Refer to FAA Memorandum dated April 14, 2015 (b) ACE-15-05 for §23.1143(g) Engine controls; Refer to FAA Memorandum dated May 4, 2015 (c) ACE-15-12 for §23.1326(b)(1) Pitot Heat Indication Systems; Refer to FAA Memorandum dated July 8, 2015 Special Conditions as follows: 23-268-SC for Installation of Full Authority Digital Engine Control (FADEC) System for KC-100 Airplane Reciprocating Engine 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, to the above required equipment, the following equipment are also required. The latest MOLIT APPROVED Revision of the Pilot’s Operating Handbook MOLIT approved Airplane Flight Manual for the KC-100, Document KPAFM00101. Service Information -- NOTE 1. A current weight and balance report including list of equipment included in the certificated empty weight must be provided for each aircraft at the time of original certification. The certificated empty weight and loading corresponding center of gravity location must include unusable fuel of : 32.3 lbs at (+168.4 in) NOTE 2. All placards specified in the approved Airplane Flight Manual, and those listed in Chapter 11 of the Airplane Maintenance Manual, Document number KPAMM 00102, must be displayed in the airplane in the appropriated. NOTE 3. Components which are life limited are listed in Airplane Maintenance Manual, Document number KPAMM 00102, Revisions to the Airworthiness Limitations must be approved by MOLIT on behalf of FAA NOTE 4. The passenger weight in rear seats is limited to 190 lbs total. .....END.....