TCDS A00007SE

A00007SE 1 Page No. 1 2 3 4 5 6 Rev. No. 27 26 26 28 26 26 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00007SE Revision 28 DAHER Kodiak 100 Kodiak 200 November 6, 2025 TYPE CERTIFICATE DATA SHEET A00007SE This data sheet, which is part of Type Certificate No. A00007SE, prescribes conditions and limitations under which the produc t for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. TC Holder: Daher Aircraft Design, LLC 1200 Turbine Drive Sandpoint, Idaho 83864 TC Holder Record: Quest Aircraft Design, LLC. Transferred to Daher Aircraft Design, LLC on November 7, 2019 I - Model Kodiak 100 (Normal Category), Approved May 31, 2007 Engine: Engine Manufacturer: Pratt and Whitney Canada, Inc. Number of Engines: One (1) Engine TC Number: E4EA Engine Model Designation: PT6A-34 Fuel: Primary Fuel: Jet A Alternate Fuels: Jet A-1, JP-1, JP-5, JP-8, No. 3 Jet Fuel (People’s Republic of China) Note that all fuels must conform to Pratt and Whitney Canada Specification CPW204 Engine Limits: Maximum Takeoff Power: 750 horsepower at 2,200 rpm, subject to ambient temperature and pressure conditions. See the latest approved revision of the Kodiak 100 “Pilot’s Operating Handbook & FAA Approved Airplane Flight Manual” and Engine TC Data Sheet E4EA for additional details and limitations. Propeller and Propeller Manufacturer: Hartzell Propeller Limits: Number of Propellers: One (1) Propeller TC Number: P10NE Propeller Model Designation: HC-E4N-3P(Y)/D9511FSB Diameter Limits: 95" minimum, 96" maximum; no further tolerance permitted High Pitch Angle: 86.1° ± 0.5° Low Pitch Angle: 17.5° ± 0.5° Reverse Pitch Angle: -10.0 ± 0.5° Static RPM Limits: Stabilized ground operation prohibited from between 450 rpm and 1,050 rpm Pitch angle limits to be measured at 30” radial distance. See Propeller TC Data Sheet P10NE for additional details and limitations. Airspeed Limits: VO: 143 kcas (142 kias) VFE (10°): 139 kcas (138 kias) VFE (20°): 120 kcas (120 kias) VFE (35°): 108 kcas (108 kias) VMO: 180 kcas (182 kias) A00007SE 2 Page No. 1 2 3 4 5 6 Rev. No. 27 26 26 28 26 26 Center of Gravity (C.G.) Range: Serial Numbers 100-0001 thru 100-0034 without Quest Service Notice SN-025 compliance: Aft Limits: Forward Limits: 80.8" aft of datum (3,620 lb to 6,750 lb) 63.9" aft of datum (3,620 lb to 5,000 lb) 69.4" aft of datum at 6,750 lb Straight-line variation between points Serial Numbers 100-0035 and above and Serial Numbers 100-0001 thru 100-0034 with Quest Service Notice SN-025 compliance: Takeoff and flight Aft Limits: Forward Limits: 80.8" aft of datum (4,070 lb to 7,255 lb) 63.9" aft of datum (4070 lb to 5,000 lb) 71.0" aft of datum at 7,255 lb Landing (Standard) Aft Limits: Forward Limits: 80.8" aft of datum (4,070 lb to 6,690 lb) 63.9" aft of datum (4070 lb to 5,000 lb) 69.3" aft of datum at 6,690 lb Landing (Optional) Aft Limits: Forward Limits: 80.8" aft of datum (4,070 lb to 7,255 lb) 63.9" aft of datum (4070 lb to 5,000 lb) 69.3" aft of datum at 6,690 lb 72.6" aft of datum at 7,255 lb Straight-line variation between points Optional landing weight allowed only when the aircraft is operated per, and the required tires and vortex generators(VGs) are installed per the limitations section of the latest FAA approved Kodiak 100 POH/AFM Supplement “Oversized Tires and Landing Weight” and the supplement is incorporated into the aircraft POH/AFM. Empty Weight None C.G. Range: Datum: The forward face of the firewall represents datum 0.0 inches. Leveling Means: Place a level on the seat tracks in the aft cabin next to the cargo door forward post. See the latest approved revision of the Kodiak 100 “Pilot’s Operating Handbook & FAA Approved Airplane Flight Manual” for additional details. Maximum Weights: Serial Numbers 100-0001 thru 100-0034 without Quest Service Notice SN-025 compliance: Maximum Ramp: Maximum Landing: Maximum Takeoff: Design Minimum Flying Weight: 6,800 lb 6,690 lb 6,750 lb 3,620 lb Serial Numbers 100-0035 and above and Serial Numbers 100- 0001 thru 100-0034 with Quest Service Notice SN-025 compliance: Maximum Ramp: Maximum Landing Standard: Optional: Maximum Takeoff: Maximum Zero-Fuel: Design Minimum Flying Weight: 7,305 lb 6,690 lb 7,255 lb 7,255 lb 7,071 lb 4,070 lb Optional landing weight allowed only when the aircraft is operated per, and the required tires and VGs are installed per the limitations section of the latest FAA approved Kodiak 100 POH/AFM Supplement “Oversized Tires and Landing Weight” and the supplement is incorporated into the aircraft Pilot’s Operating Handbook & FAA Approved Airplane Flight Manual. Minimum Crew: 1 Pilot Number of Seats: Up to 10 seats total, including 2 seats located at 40" aft of datum and up to 8 additional seats located in accordance with latest approved revision of the Kodiak 100 “Pilot’s Operating Handbook and FAA Approved Flight Manual” Maximum Compartment As defined in latest approved revision of the Kodiak 100 “Pilot’s Operating Handbook & FAA Weights: Approved Airplane Flight Manual”. A00007SE 3 Page No. 1 2 3 4 5 6 Rev. No. 27 26 26 28 26 26 Fuel Capacity: One 160 gallon tank in each wing at 83.4" aft of datum; 157.5 gallons usable, 2.5 gallons unusable (320 gallons total; 315 gallons usable, 5 gallons unusable) Note: add weight of unusable fuel to the certificated empty weight. Oil Capacity: 13 qt total at 18.9" forward of datum; 9 qt drainable, 4 qt undrainable Note: Add the weight if oil to the certificated empty weight of the aircraft. See Pratt and Whitney Canada Service Bulletin Number 1001 for approved oil. Maximum Operating 14,000 feet without FAA approved oxygen system installed. Altitude: 25,000 feet with FAA approved oxygen system installed. Control Surface Wing Flaps: 0° 10° +1°/-2° 20° ±2° 35° ±2° Movements: Ailerons: Up: 28° ±1° Down: 15° ±1° Aileron Trim Tab: Up: 30° ±2° Down: 30° ±2° Elevator: Up: 30° ±1° Down: 22° ±1° Elevator trim tab: Up: 15° ±2° Down: 12° ±1° Rudder: Right: 26° ±1° Left: 26° ±1° See the latest FAA approved revision of the Kodiak 100 “Airplane Maintenance Manual”, or other FAA approved data, for flap rigging instructions and setting Flaps up (0°) configuration. Manufacturer’s The information contained herein is applicable to Serial Numbers 100-0001 and up. Serial Numbers: Certification Basis: Certification Basis: Part 23 of the Federal Aviation Regulations (FAR) effective February 1, 1965, as amended by 23-1 through 23-55; FAR 34 as amended through 34-3, FAR 23.1306 for Lightning Protection, per Amdt 23-61, and FAR 36 as amended through 36-28. Special Condition 23-207-SC for high intensity radiated fields (HIRF) protection, effective January 31, 2007. For aircraft equipped with the Garmin GFC 700 Automatic Flight Control System: FAR 23.1308(a), at amendment 23-57 for HIRF protection of the GFC 700 system and associated systems performing functions whose failure would prevent continued safe flight and landing. For aircraft serial number 100-0354 and up and aircraft serial numbers 100-0001 through 100-0353 that are equipped with the Mid-Continent MD302 standby attitude module and MD32 magnetometer: FAR 23.1303(c) at amendment 23-62 for flight and navigation instruments and FAR 23.1331(c) at amendment 23-62 for instruments using a power source. II - Model Kodiak 200 (Normal Category), Approved August 30, 2022 (See NOTE 5) Engine: Engine Manufacturer: Pratt and Whitney Canada, Inc. Number of Engines: One (1) Engine TC Number: E4EA Engine Model Designation: PT6A-140A Fuel: Primary Fuel: Jet A Alternate Fuels: Jet A-1, JP-5, JP-8, No. 3 Jet Fuel (People’s Republic of China) Note that all fuels must conform to Pratt and Whitney Canada Specification CPW204 Engine Limits: Maximum Takeoff Power: 900 horsepower at 1,900 rpm, subject to ambient temperature and pressure conditions. See the latest a pproved revision of the Kodiak 900 “Pilot’s Operating Handbook & FAA Approved Airplane Flight Manual” and Engine TC Data Sheet E4EA for additional details and limitations. See NOTE 5. Propeller and Propeller Manufacturer: Hartzell Propeller Limits: Number of Propellers: One (1) Propeller TC Number: P20NE Propeller Model Designation: HC-E5W-3/NC9405B Diameter Limits: 97"; no further tolerance permitted High Pitch Angle: 88.6°±0.5° Low Pitch Angle: 18.5°±0.5° Reverse Pitch Angle: -10.0°±0.5° Static RPM Limits: Maximum 1900 rpm. Stabilized ground operation prohibited from between 400 rpm and 1,150 rpm. A00007SE 4 Page No. 1 2 3 4 5 6 Rev. No. 27 26 26 28 26 26 Pitch angle limits to be measur ed at 30” radial distance. See Propeller TC Data Sheet P20NE for additional details and limitations. Airspeed Limits: VO (at 8,000 lb): 153 kcas (152 kias) VFE (10°): 139 kcas (137 kias) VFE (20°): 125 kcas (123 kias) VFE (35°): 120 kcas (118 kias) VMO: 190 kcas (187 kias) Center of Gravity (C.G.) Range: Serial Numbers K2-0002 and up. Forward limits: Aft Limits: 78.8” aft of datum at 4,840 lb 78.8” aft of datum at 6,250 lb 84.4” aft of datum at 8,000 lb 92.5” aft of datum at 4,840 lb 92.5” aft of datum at 8,000 lb Straight-line variation between points Empty Weight None C.G. Range: Datum: The forward face of the firewall represents datum 0.0 inches. Leveling Means: Place a level on the seat tracks in the aft cabin next to the cargo door forward post . See the latest a pproved revision of the Kodiak 900 “Pilot’s Operating Handbook & FAA Approved Airplane Flight Manual” for additional details. See NOTE 5. Maximum Weights: Serial Numbers K2-0002 and up: Maximum Ramp: Maximum Landing: Maximum Takeoff: Maximum Zero Fuel: Design Minimum Flying Weight: 8,100 lb 7,800 lb 8,000 lb 7,210 lb 4,840 lb See the latest approved revision of the Kodiak 900 “Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual” for additional details. See NOTE 5. Minimum Crew: 1 Pilot Number of Seats: Up to 10 seats total, including 2 seats located at 41" aft of datum and up to 8 additional seats located in accordance with latest approved revision of the K odiak 900 “Pilot’s Operating Handbook & FAA Approved Airplane Flight Manual”. See NOTE 5. Maximum Compartment As defined in latest approved revision of the Kodiak 900 “Pilot’s Operating Handbook & FAA Weights: Approved Airplane Flight Manual”. See NOTE 5. Fuel Capacity: Wing Tanks: One 1 59 gallon tank in each wing at 94.2 " aft of datum; 155. 5 gallons usable, 3. 5 gallons unusable (318 gallons total; 311 gallons total usable, 7 gallons total unusable). Header Tank: One 4.1 gallon header tank at 93.5” aft of datum, 4.1 gallons unusable. Note: add weight of unusable fuel to the certificated empty weight. Oil Capacity: 14.4 qt total at 22.3" forward of datum; 14 qt drainable, 0.4 qt undrainable Note: Add the weight if oil to the certificated empty weight of the aircraft. See Pratt and Whitney Canada Service Bulletin Number 1001 for approved oil. Maximum Operating 25,000 feet with FAA approved oxygen system installed. Altitude: 14,000 feet without FAA approved oxygen system installed. 20,000 feet in icing conditions or any flight conditions with ice on the airplane. Control Surface Wing Flaps: 0° 10° +1°/-2° 20° ±2° 35° ±2° Movements: Ailerons: Up: 28° ±1° Down: 15° ±1° Aileron Trim Tab: Up: 30° ±2° Down: 30° ±2° Elevator: Up: 30° ±1° Down: 22° ±1° Elevator trim tab: Up: 18° +1°/-0° Down: 12° ±1° Rudder: Right: 20° ±1° Left: 20° ±1° See the latest FAA approved revision of the Kodiak 900 “Airplane Maintenance Manual”, or other FAA approved data, for flap rigging instructions and setting Flaps up (0°) configuration.See NOTE 5. Manufacturer’s The information contained herein is applicable to Serial Numbers K2-0002 and up. Serial Numbers: A00007SE 5 Page No. 1 2 3 4 5 6 Rev. No. 27 26 26 28 26 26 Certification Basis: 14 CFR Part 23, as amended through 23-63. 14 CFR 23.2010 Accepted means of compliance and 14 CFR 23.2150 Stall characteristics, stall warning, and spins, as amended by 23-64. Project Specific Policy Memorandum (PSPM) for correction of Amendment 23-62 and prior amendment errors, as described in an FAA Memorandum, under the subject, “Project Specific Policy Memorandum for 14 CFR Part 23, up to and including Amdt 62.” ELOS Finding for Quest, Project No. AT13028SE-A, “Equivalent Level of Safety Finding for 14 CFR §23.1353(h), Storage Battery Design and Installation: in the event of a complete loss of the primary electrical generating system.” dated August 31, 2020. 14 CFR Part 34, as amended through 34-6. 14 CFR Part 36, as amended through 36-31. DATA PERTINENT TO ALL MODELS: TC Number: A00007SE TC Issuance Date: May 30, 2007 TC Application Date: April 7, 2005 TC Amendment Date August 30, 2022 Operational Restrictions: Day-Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR). Flight into known icing conditions allowed when the required equipment listed in the latest FAA approved revision of the Kodiak 100 POH/AFM Supplement, “TKS Ice Protection System,” or Kodiak 900 POH/AFM Supplement, “TKS Ice Protection System,” as applicable, is installed. For Kodiak 100 only: installation may have been accomplished when the airplane was produced (may have required system activation in accordance with Quest Service Notice SN-043), or may have been installed in accordance with the latest FAA approved revision of Quest Field Service Instruction FSI- 013. See NOTE 5. Minimum Operating OAT -25°C for Kodiak 100 models Serial Numbers 100-0001 thru 100-0017 without Quest Service Bulletin SB-016 compliance. Minimum Operating OAT -55°C for Kodiak 100 models Serial Numbers 100-0018 and up and Serial Numbers 100-0001 thru 100-0017 with Quest Service Bulletin SB-016 compliance. Minimum Operating OAT -55°C for Kodiak 200 models Serial Numbers K2-0002 and up. Production Basis: Production Certificate 728NM. Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. Additional Equipment The latest FAA Approved Revision of the Kodiak 100 “Pilot’s Necessary for Type Operating Handbook & FAA Approved Airplane Flight Manual.” Certification: or the Kodiak 900 “Pilot’s Operating Handbook and FAA Approved Flight Manual,” as applicable. See NOTE 5. - NOTE 1: 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. NOTE 2: The placards specified in the latest FAA approved revision of the Kodiak 100 “Pilot’s Operating Handbook & FAA Approved Airplane Flight Manual” or the Kodiak 900 “Pilot’s Operating Handbook & FAA Approved Airplane Flight Manual”, as applicable, are required. See NOTE 5. NOTE 3: The airplane must be subsequently maintained in accordance with the Instructions for Continued Airworthiness, and Airworthiness Limitations section, as contained in the latest FAA approved revision of the Kodiak 100 “Airplane Maintenance Manual” or the Kodiak 900 “Airplane Maintenance Manual”, as applicable, or other FAA approved data. See NOTE 5. For Kodiak 100 serial numbers 100-0354 and up use document AM902.0, Kodiak 100 Airplane Maintenance Manual, Revision 32 or later FAA-approved revision. For Kodiak 200 serial numbers K2-0020 and up use document AM922.0. Kodiak 900 Airplane Maintenance Manual, Revision 03 or later FAA-approved revision. See NOTE 5. A00007SE 6 Page No. 1 2 3 4 5 6 Rev. No. 27 26 26 28 26 26 NOTE 4: The airplane shall be manufactured in accordance with the latest FAA approved revision of the Kodiak 100 “Master Drawing List” or the Kodiak 200 “Master Drawing List”, as applicable, or other FAA approved data. NOTE 5: The marketing name for the model Kodiak 200 is the “Kodiak 900”. Some documents that apply to the Kodiak 200 model such as the Airplane flight manual and Airplane maintenance manual are labeled with the Kodiak 900 trade name. Documents that are entitled with Kodiak 900 are applicable to the Kodiak 200 model. .....END.....