TCDS A00016WI

Page No. 1 2 3 4 5 Rev. No. 5 6 6 5 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00016WI Revision 6 Textron Aviation 408 June 26, 2026 TYPE CERTIFICATE DATA SHEET NO. A00016WI This data sheet, which is part of Type Certificate No. A00016WI, 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 Textron Aviation Inc. One Cessna Boulevard Wichita, Kansas 67215 I. Model 408 (Normal Categor y) Approved March 11, 2022 Engines Two Pratt & Whitney PT6A-65SC (turboprop) Engine Limits Shaft Horsepower Torque* (%) N1 Gas Generator Speed** (%) Prop Shaft Speed** (rpm) Max. Permissible Interstage Turbine Temp (ºC) Takeoff 1110 100 104 1700 830 Max. continuous 1110 100 104 1700 815 Max. cruise 980 100 104 1500 780 Starting transient (5 sec) 1000 Max. reverse (1 min) 900 1650 760 *100% = 3,429 lb.-ft **See NOTE 6 Fuel FUEL TYPE SPECIFICATION JP-8 MIL-DTL-83133 JET A, A-1 ASTM SPEC. D1655 Chinese No.3 Jet Fuel SAC GB 6537 RT GOST 10227 or GSTU 320.00149943.007 TS-1 GOST 10227 or GSTU 320.00149943.011 Fuel capacity Total usable fuel 4, 826 lbs. (720 gal). Two wing tanks with 2,413 lbs. (360 gal) usable each (See NOTE 1); +296.81 in. aft of datum. See NOTE 10 for increased usable fuel capacity. Oil (Engine Pratt & Whitney Maintenance Manual, Document No. 3135622, lists approved brand oils. & Gearbox) Engine Oil Capacity 7.2 gal. total (3.6 ga l. per each engine) at +242.33 in. (1.5 gal. usable in each integral engine tank). (See NOTE 1) Oil temperatures Minus 40°C minimum starting. 32°C to 99°C normal operating. >99°C to 110°C limited to 10 minutes. Refer to the Airplane Flight Manual (AFM) for other oil temperature limits. A00016WI Page 2 of 5 Rev. 6 I. Model 408 (cont’d) Propeller and Two McCauley 4-blade, full feathering and reversible, metal propellers Propeller Limits Model: 4HFR34C779/110FDA-0 Diameter: 110 in. (maximum) Minimum Allowable for repairs: 108 in. No further reduction permitted. Pitch Settings at: Reverse -9.0 +/- 0.2 degrees Feathered +88.0 +/- 0.2 degrees (See McCauley Propeller TCDS P3NE for additional details and limitations). Airspeed V MO (Maximum operating speed) Limitations Sea Level (0 ft.) to 12,614 ft. 210 KIAS (210 KCAS) MMO above 12,614 ft. 0.40 M I (0.40 MACH calibrated) VO (Maximum operating maneuvering speed Sea Level) 19,000 lbs. 151 KIAS (151 KCAS) (See AFM for variations with weight and altitude). VRA (Rough air speed) 179 KIAS (179 KCAS) 0.40 M I (0.40 MACH calibrated) Flap extension speeds VFE (Up (0°) to 1 (10°) extension) 170 KIAS (170 KCAS) VFE (1 (10°) to 2 (20°) extension) 170 KIAS (169 KCAS) VFE (2 (20°) to Full (35°) extension) 140 KIAS (137 KCAS) Minimum Control Speeds (VMCA and VMCG) Refer to AFM Section IV, Performance Maximum Tire Ground Speed 139 knots C.G. Range Design Forward: FS 276.56 in. at 10,800 lbs. to 14,330 lbs. C.G. Limits Linear variation from FS 276.56 in. at 14, 330 lbs. to FS 281.94 in. at 19,000 lbs. Aft: Linear variation from FS 290.62 in. at 10, 800 lbs. to FS 292.70 in. at 16,500 lbs. FS 292.70 in. at 16,500 lbs. to 19,000 lbs. See NOTE 12. Empty Wt. C.G. None Range Maximum Weight: Ramp: 19,070 lbs. Takeoff: 19,000 lbs. Landing: 18,600 lbs. Zero Fuel: Refer to AFM Minimum Crew One (1) pilot (left seat) for all Flights OR two (2) pilots Number of Seats The maximum number of passenger seats approved: Passenger variant is 19. Freighter variant is 0. Cabin Loading Reference Weight an d Balance Data in AFM for approved seating and cargo configurations. Maximum Baggage COMPARTMENT POUNDS Nose 300 Passenger Variant Aft Baggage (including shelf) 1,200 Freighter Variant Cargo (including shelf) 6,000 Passenger Variant Overhead Bin (each) 60 Aft Baggage Shelf 400 Rev. 6 Page 3 of 5 A00016WI I. Model 408 (cont’d) Maximum Operating 25,000 ft. Altitude Control Surface Movements (Up/Down/Left/Right refers to motion of the trailing edge of each control surface) Elevator Up 24.0 +1.0/-0.0 degrees Down 15.0 +/-1.0 degrees Elevator Tab Up 6.5 +/-1.0 degrees Down 13.0 +/-1.0 degrees Rudder Right 30.5 +/-0.5 degrees Left 30.5 +/-0.5 degrees Rudder Tab Right 11.0 +/-0.5 degrees Left 11.0 +/-0.5 degrees Aileron Left and Right Up 17.5 +1.0/-0.0 degrees Down 17.5 +/-1.0 degrees Aileron Tab Right Up 13.0 +/-1.0 degrees Down 13.0 +/-1.0 degrees Wing Flap Up 0.0 +/-0.1 degrees 1 10.0 +/-1.0 degrees 2 20.0 +/-1.0 degrees Full 35.0 +/-1.0 degrees (See Airplane Maintenance Manual for rigging instructions) Serial No. Eligible 408-0001 and On Data Pertinent to all Models Datum 91.89 in. forward of nose jack point. Leveling Means Longitudinal: Place level directly on the outboard pilot seat rail and ensure it is parallel with the seat rail. Lateral: Place the leveling bar across the pilot seat rails flush against the rear seat stops at approximately FS 163.98 in. Certification Basis 1. 14 CFR Part 23, effective February 1, 1965, including Amendments 23-1 through 23-64. 2. The detailed design standard s used as a means of compliance in accordance with 23.2010 are documented in PR-408-001, Model 408 Detailed Design Standard Summary. 3. Special Conditions. At this time, no special conditions have been identified. 4. Equivalent Safety. At th is time, no equivalent safety findings have been identified. 5. Exemptions. At this time, no exemptions have been identified. 6. Additional Design Requirements and Conditions . At this time, no additional design requirements have been identified. 7. Optional Design Regulations. Model 408 complies with the following optional design regulations. Ice protection in accordance with: - 23.2165 Performance and Flight Characteristics Requirements for Flight in Icing Conditions, AND - 23.2540 Flight in Icing Conditions, provided the optional ice protection systems are installed. - Refer to the AFM for limitations. A00016WI Page 4 of 5 Rev. 6 Data Pertinent to all Models Certification Basis 8. 23.2005 Certific ation Level and Performance Level: (cont'd) Freighter Variant Level 1, Low Speed Passenger Variant Level 4, Low Speed Environmental 1. Noise Standards: 14 CFR Part 36, as amended by Amendments 36-1 through 36-31 (See Standards NOTE 11). 2. Noise Standards: A finding of regulatory ad equacy pursuant to the “Noise Control Act of 1972” (49 USC Section 44715). 3. Fuel Venting and Exhaust Em issions Standards: 14 CFR Part 34, as amended by Amendments 34-1 through 34-5A. Production Basis Production Certificat e No. 4 amended to add Model 408, effective June 6, 2022. (See NOTE 7 for airplane Serial Number (S/N) effectiveness of Production Certificate No. 4 on new airplanes S/N). Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. NOTE 1. Current weight and ba lance information, including list of equipment included in certificated empty weight, and loading instructions are provided for each airplane at the time of original certification. The certificated empty weight and corresponding center of gravity location must include: Unusable Fuel 39.80 lbs. at +296.69 in. Full Oil 58.32 lbs. at +242.33 in. NOTE 2. Airplanes must be operated according to the FAA Approved AFM, part number 408FM-00 AFM Volume 1, 408NP-00 AFM Volume 2 Normal Procedures, and 408EAP-00 AFM Volume 3 Emergency/Abnormal Procedures (or later FAA approved revision). All placards required by either the FAA Approved AFM, the applicable operating rules, or the certification basis, must be installed as specified for this Type Certificate via Parts List 7800000, Airplane Assembly. A useful placard reference is the Textron Aviation Illustrated Parts Catalog (IPC). Any discrepancies identified between the IPC and an aircraft under inspection needs to be reconciled using the previously stated parts list. NOTE 3. See Airworthiness Limitations Manual, Chapter 4, fo r inspections, mandatory retirement life information, and other requirements for continued airworthiness. NOTE 4. Aircraft definition for Type Certificat e (TC) is Parts List 7800000, Airplane Assembly. NOTE 5. Certification Maintenance Requirements (CMR) are found in Airworthiness Limitations Manual, Chapter 4. Engineering approval of the CMR's is documented in the Textron Aviation System Safety Assessment reports. NOTE 6. The maximum propeller shaft over speed limit is 110 percent (1,870 rpm) in an emergency to complete flight. 100 percent propeller shaft speed is defined as 1,700 rpm and is the normal steady state operating limit. Gas generator speeds up to 104 percent are approved for unlimited periods subject to applicable temperature and other limits. 100 percent gas generator speed is defined as 37,468 rpm. NOTE 7. The following S/N will be certified TC only: 408-0001 through 408-0008. Production Certificate No. 4 applies to the following Model 408 S/N: 408-0009 and On. NOTE 8. Airplanes utilizing the pilot’s cockpit door for passenger boarding or deboarding must use the Forward Passenger Entry Stairs with handrail positioned on the aft side of the cockpit door entry. Refer to AFM Supplement 408FM-S6-00 (or later FAA approved revision) Passenger/Freighter Combination. Rev. 6 Page 5 of 5 A00016WI Data Pertinent to all Models NOTE 9. Required Equipment. The basic required equipment prescribed in the applicable airworthiness requirements (see certification basis) must be installed in the aircraft. Only handheld fire extinguishers containing Halon 1211 (BCF, CBrC1F2) OR Halotron BrX (2-BTP, C3H2BrF3) are approved for use. No airplanes may have any combination of dissimilar agents installed on a particular unit. NOTE 10. Refer to AFM Supplement 408FM- S11-00 (or later FAA approved revision) Increased Fuel Capacity, for data pertaining to usable fuel in the wing tanks with the increased fuel capacity option installed. Total usable fuel capacity is 5,356 lbs. (799 gal.). NOTE 11. Per 14 CFR Part 36.2, all product changes that affect acoustics will comply with the latest amendment level of 14 CFR Part 36 that is current at the time of the project application. NOTE 12. Airplanes with High Float Tires (N ose: 22 x 6.75; and Mains: H31 x 9.75). C.G. Limits, Aft: Linear variations from FS 290.62 in. at 10,800 lbs. to FS 292.70 in. at 16,500 lbs. FS 292.70 in. at 16,500 lbs. to 18,680 lbs. Linear variations from FS 292.70 in. at 18,680 lbs. to FS 289.22 in. at 19,000 lbs. ----------- END ------------