TCDS A37CE

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 Rev. No. 25 23 17 16 13 20 23 20 21 24 22 25 25 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A37CE Revision 25 Textron Aviation 208 208B August 1, 2025 TYPE CERTIFICATE DATA SHEET NO. A37CE This data sheet, which is part of Type Certificate No. A37CE, 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 Type Certificate Holder Record Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 I. Model 208, Caravan, 11 PCLM (Normal Category), Approved October 23, 1984; Model 208, Caravan, 11 PCSM (Normal Category), Approved March 26, 1986 Engine [Applicable to S/N 20800001 thru 20800276] (600 SHP) Pratt & Whitney of Canada Ltd., PT6A-114 Turbo Prop Pratt & Whitney of Canada Ltd., PT6A-114A Turbo Prop (When operated to PT6A-114 operating limitations) Engine [Applicable to S/N 20800277 and On] (675 SHP) Pratt & Whitney of Canada Ltd., PT6A-114A Turbo Prop Fuel Aviation turbine fuel Jet A, Jet A-1, Jet B, JP-1, JP-4, JP-5 or JP-8. For required use of anti-icing additives and emergency use of aviation gasoline, refer to the Pilot’s Operating Handbook (POH) and FAA Approved Airplane Flight Manual (AFM). Engine Limits [Applicable to S/N 20800001 thru 20800276] P&W PT6A-114 or PT6A-114A when operated to PT6A-114 operating limits Shaft Horsepower NG Gas Generator Speed (% rpm) Indicator Torque (ft.-lb.) Prop Shaft Speed (rpm) Maximum Permissible Interturbine Temp. (C) Takeoff static & max. continuous 600 (1) 101.6 1658 1900 805 Maximum climb 600 (1) 101.6 1658/1970 (2) 1900 765 Maximum cruise 600 (1) 101.6 1658/1970 (2) 1900 740 Idle - 52 min. - - 685 Starting (2 sec.) - - - - 1090 Max. reverse (1 min.) 600 (1) 101.6 1658 1825 805 Transient (2 sec.) - 102.6 2200 2090 850 A37CE 2 Rev. 25 I. Model 208, Caravan (cont’d) Engine Limits [Applicable to S/N 20800277 and On] P&W PT6A-114A Shaft Horsepower NG Gas Generator Speed (% rpm) Indicator Torque (ft.-lb.) Prop Shaft Speed (rpm) Maximum Permissible Interturbine Temp. (C) Takeoff static & max. continuous 675 (1) 101.6 1865 1900 805 Maximum climb 675 (1) 101.6 1865/1970 (2) 1900 765 Maximum cruise 675 (1) 101.6 1865/1970 (2) 1900 740 Idle - 52 min. - - 685 Starting (2 sec.) - - - - 1090 Max. reverse (1 min.) 675 (1) 101.6 1865 1825 805 Transient (2 sec.) - 102.6 2200 2090 850 (1) Flat Rated: The engines may produce more power than that for which the airplane has been certificated. Under these conditions, the stated torque, ITT, or Ng limitations shall not be exceeded. (2) If maximum torque is used, propeller r.p.m. must be set so as not to exceed power limitations. Propeller and Propeller L imits [Applicable to S/N 20800001 through 20800276] (600 SHP) Hartzell composite three-bladed, constant speed, full-feathering, reversible Model: HC-B3MN3/M10083 Diameter: Maximum 100 inches, minimum 100 inches, no cutoff approved Pitch at 42-inch station: Low pitch (Beta pickup) 9° Feathered 78.4° Maximum Reverse -18° Propeller and Propeller Limits [A pplicable to S/N 20800001 and On and all TKS equipped aircraft] (675 SHP) McCauley aluminum three-bladed, constant speed, full-feathering, reversible Model: 3GFR34C703/106GA-0 Diameter: Maximum 106 inches, minimum 104 inches (2-inch cutoff on diameter allowed) Pitch at 30-inch station: Low pitch (Beta pickup) +15.6° Feathered +88° Maximum Reverse -14° *Airspeed Limits V MO (Max Operating) 175 KIAS S/N 20800001 V A (Maneuvering) at 7300 lb. 148 KIAS thru 20800060 See POH/AFM for variati ons with weight and altitude. VFE (Flaps extended) To 10° 175 KIAS 10° to 20° 150 KIAS 20° to 30° 125 KIAS *Airspeed Limits V MO (Max Operating) 175 KIAS S/N 20800061 and On V A (Maneuvering) at 8000 lb. 150 KIAS See POH/AFM for variations with weight and altitude. VFE (Flaps extended) To 10° 175 KIAS 10° to 20° 150 KIAS 20° to 30° 125 KIAS A37CE 3 Rev. 25 I. Model 208, Caravan (cont’d) *Airspeed Limits (cont’d) S/N 20800014 and On V MO (Max Operating) 175 KIAS Amphibian V A (Maneuvering) at 7600 lb. 141 KIAS See POH/AFM for variations with weight and altitude. VFE (Flaps extended) To 10° 175 KIAS 10° to 20° 150 KIAS 20° to 30° 125 KIAS C.G. Range Takeoff and Flight S/N 20800001 and On (+174.06) to (+184.35) at 8000 lb. (+162.41) to (+184.35) at 4200 lb. Straight line variation between points given Landing (+173.44) to (+184.35) at 7800 lb. (+162.41) to (+184.35) at 4200 lb. Straight line variation between points given S/N 20800014 and On Takeoff and Flight Amphibian (+172.83) to (+182.68) at 7600 lb. (+165.47) to (+182.68) at 5200 lb. Straight line variation between points given Landing (+171.91) to (+182.68) at 7300 lb. (+165.47) to (+182.68) at 5200 lb. Straight line variation between points given Empty Wt. C.G. Range None Maximum Weight 8000 lb. takeoff and flight S/N 20800001 and On 7800 lb. landing 8035 lb. ramp S/N 20800014 and On 7600 lb. takeoff and flight Amphibian 7300 lb. landing 7635 lb. ramp No. of Seats 1 and 2 (at +133.5 to +146.5) Pilot Seat Locations. 3 through 11 refer to current POH and FAA Approved AFM for passenger seating arrangements. Maximum Baggage Reference weight and balance data Fuel Capacity 335 gal. (332 gal. usable), two 167.5 gal. tanks in wings at +183.8 See NOTE 1 for data on unusable fuel. Oil Capacity 3.5 gal. total, 2.37 gal. usable in engine mounted tank at +69.2 Maximum Operating 30,000 ft. - Landplane 600 SHP Altitude 25,000 ft. - Landplane 675 SHP 20,000 ft. - Amphibian and Landplane Flight into Known Icing A37CE 4 Rev. 25 I. Model 208, Caravan (cont’d) Control Surface Wing flaps 0° +1° Up, 10° +1° -2° Down, 20° +2° Down, Movements 30° +1° -2° Down LH & RH Flap Extension to be symmetric within 1/2° at all positions Main surfaces Ailerons Up 25° +4° -0° Down 16° +1° -0° Spoiler Up 40° +5° Down 0° +0° -5° Elevator Up 25° +2° Down 20° +2° Elevator (w/TKS fairing) Up 18° +1° Down 20° +2° Rudder (Landplane) Right 25° +2° Left 25° +2° (Amphibian) Right 23° +2°, -0° Left 23° +2°, -0° (Measured perpendicular to hinge line) Tabs (main surfaces in neutral) Aileron (RH) Up 15° +2° Down 15° +2° Elevator Up 15° +2° Down 15° +2° Tabs servo actions Aileron (RH): 50% of aileron travel +1° Up and Down (tab adjusted to neutral) Aileron (LH): 50% of aileron travel +1° Up and Down Serial No. Eligible 20800001 and On - Landplane 20800014 and On - Amphibian with Wipline Model 8000 Amphibious/Seaplane Floats. II. Model 208B, Caravan, 2 PCLM (Norma l Category), Approved October 9, 1986 Model 208B, Caravan, 11 PCLM (Norma l Category), Approved December 13, 1989 Engine Pratt & Whitney of Cana da Ltd., PT6A-114 Turbo Prop: 1. S/N 208B0001 thru 208B0178 and 208B0180 thru 208B0229, and as modified by SK208-84 (600 SHP). Pratt & Whitney of Canada Ltd., PT6A-114A Turbo Prop: 1. S/N 208B0001 thru 208B0178 and 208B0180 thru 208B0229, as modified by SK208-84 when operated to PT6A-114 operating limits (600 SHP). 2. S/N 208B0179, 208B0230 thru 208B4999, as modified by SK208-80 (675 SHP). Fuel Aviation turbine fuel Jet A, Jet A-1, Jet B, JP-1, JP-4, JP-5 or JP-8. For required use of anti-icing additives and emergency use of aviation gasoline, refer to the POH and FAA Approved AFM. Engine Limits P&W PT6A-114 or PT6A-114A when operating to PT6A-114 operating limits: Shaft Horsepower NG Gas Generator Speed (% rpm) Indicator Torque (ft.-lb.) Prop Shaft Speed (rpm) Maximum Permissible Interturbine Temp. (C) Takeoff static & max. continuous 600 (1) 101.6 1658 1900 805 Maximum climb 600 (1) 101.6 1658/1970 (2) 1900 765 Maximum cruise 600 (1) 101.6 1658/1970 (2) 1900 740 Idle - 52 min. - - 685 Starting (2 sec.) - - - - 1090 Max. reverse (1 min.) 600 (1) 101.6 1658 1825 805 Transient (2 sec.) - 102.6 2200 2090 850 A37CE 5 Rev. 25 II. Model 208B, Caravan (cont’d) Engine Limits (cont’d) PT6A-114A (675 hp) Shaft Horsepower NG Gas Generator Speed (% rpm) Indicator Torque (ft.-lb.) Prop Shaft Speed (rpm) Maximum Permissible Interturbine Temp. (C) Takeoff static & max. continuous 675 (1) 101.6 1865 1900 805 Maximum climb 675 (1) 101.6 1865/1970 (2) 1900 765 Maximum cruise 675 (1) 101.6 1865/1970 (2) 1900 740 Idle - 52 min. - - 685 Starting (2 sec.) - - - - 1090 Max. reverse (1 min.) 675 (1) 101.6 1865 1825 805 Transient (2 sec.) - 102.6 2200 2090 850 (1) Flat Rated: The engines may produce more power than that for which the airplane has been certificated. Under these conditions, the stated torque, ITT, or Ng limitations shall not be exceeded. (2) If maximum torque is used, propeller r.p.m. must be set so as not to exceed power limitations. Propeller and Hartzell composite three-bladed, constant speed, full-feathering, reversible. Propeller Limits Model: HC-B3MN3/M10083 Diameter: Maximum 100 inches, minimum 100 inches, no cutoff approved Pitch at 42-inch station: Low pitch (Beta pickup) 9° Feathered 78.4° Maximum Reverse -18° McCauley aluminum three-bladed, constant speed, full-feathering, reversible. NOTE: All aircraft equipped with TKS anti-ice system must use this prop. Model: 3GFR34C703/106GA-0 Diameter: Maximum 106 inches, minimum 104 inches (2-inch cutoff on diameter allowed) Pitch at 30-inch station: Low pitch (Beta pickup) +15.6° Feathered +88° Maximum Reverse -14° *Airspeed Limits V MO (Max Operating) 175 KIAS VA (Maneuvering) at 8750 lb. 148 KIAS See POH/AFM for variations with weight and altitude. VFE (Flaps extended) To 10° 175 KIAS 10° to 20° 150 KIAS 20° to 30° 125 KIAS C.G. Range Takeoff and Flight (+199.15) to (+204.35) at 8750 lb. (+193.37) to (+204.35) at 8000 lb. (+179.60) to (+204.35) at 5500 lb. Straight line variation between points given Landing (+197.22) to (+204.35) at 8500 lb. (+193.37) to (+204.35) at 8000 lb. (+179.60) to (+204.35) at 5500 lb. Straight line variation between points given Empty Wt. C.G. Range None A37CE 6 Rev. 25 II. Model 208B, Caravan (cont’d) Maximum Weight 8750 lb. takeoff and flight 8500 lb. landing 8785 lb. ramp For Flight into Known Icing: With PT6A-114 engine and PT6A-114A when operated to PT6A-114 operating limits 8000 lb. takeoff and flight - cargo pod installed 8450 lb. takeoff and flight - cargo pod removed With PT6A-114A (675 hp.) engine 8550 lb. takeoff and flight - cargo pod installed 8750 lb. takeoff and flight - cargo pod removed With PT6A-114A (675 hp.) engine and TKS Anti-ice System installed 8750 lb. takeoff and flight No. of Seats 1 and 2 (at +133.5 to +146.5) Pilot Seat Locations for Cargo and Passenger Versions. 3 thru 11 refer to POH for passenger seat locations Passenger Version only. Maximum Baggage Reference weight and balance data Fuel Capacity 335 gal. (332 gal. usable), two 167.5 gal. tanks in wings at +203.8 (See NOTE 1 for data on unusable fuel). Oil Capacity 3.5 gal. total, 2.37 gal. usable in engine mounted tank at +69.2 Maximum Operating 25,000 ft. Altitude 20,000 ft. for Flight into Known Icing Control Surface Wing flaps 0° +1° Up, 10° +1° -2° Down, 20° +2° Down, Movements 30° +1° -2° Down LH & RH Flap Extension to be symmetric within 1/2° at all positions Main surfaces Ailerons Up 25° +4° -0° Down 16° +1° -0° Spoiler Up 40° +5° Down 0° +0° -5° Elevator Up 25° +2° Down 20° +2° Elevator (w/TKS fairing) Up 22° +1° -0 ˚ Down 20° +2° Rudder Right 25° +2° Left 25° +2° (Measured perpendicular to hinge line) Tabs (main surfaces in neutral) Aileron (RH) Up 15° +2° Down 15° +2° Elevator Up 15° +2° Down 15° +2° Tabs servo actions Aileron (RH): 50% of aileron travel +1° Up and Down (tab adjusted to neutral) Aileron (LH): 50% of aileron travel +1° Up and Down Serial No. Eligible 208B0001 thru 208B2196 and 208B2198 thru 208B4999 A37CE 7 Rev. 25 III. Model 208B, Caravan, 2 PCLM or 11 PCLM (Normal Ca tegory), Approved December 21, 2012, for S/N 208B2197 and 208B5000 and On (This series differs from the basic Model 208B (Item II) by installation of a PT6A-140 engine, increase in gross weight, and other changes) Engine Pratt & Whitney of Canada Ltd. , PT6A-140 Turbo Prop, S/N 208B2197 and 208B5000 and On (867 SHP) Fuel Refer to the POH and FAA Approved AFM for approved aviation turbine fuels. Engine Limits P&WC PT6A-140: Shaft Horsepower NG Gas Generator Speed (% rpm) Indicator Torque (ft.-lb.) Prop Shaft Speed (rpm) Maximum Permissible Interturbine Temp. (C) Takeoff static & max. continuous 867 (1) 103.7 2397 1900 850 Maximum climb 867 (1) 103.7 2397 1900 825 Maximum cruise 867 (1) 103.7 2397 1900 805 Idle - 55 min. - - 700 Starting (2 sec.) - - - - 1090 Max. reverse (1 min.) 867 (1) 103.7 2500 1825 850 Transient (20 sec.) - 105.4 2600 2090 (2) 905 (1) Flat Rated: The engines may produce more power than that for which the airplane has been certificated. Under these conditions, the stated torque, ITT, or Ng limitations shall not be exceeded. (2) 2090 RPM NP may be employed in an emergency condition to complete a flight and may be employed at all ratings. Not limited to 20 seconds. Propeller and Hartzell Aluminum three-bladed, constant speed, full-feathering, reversible Propeller Limits Model: HC-B3TN-3AF/T10890CN-2 or HC-B3TN-3AF/T10890CN(B)-2 Diameter: Maximum 106 inches, minimum 104 inches, no cutoff approved Pitch at 42-inch station: Low pitch (Beta pickup) 8.5° Feathered 78.4° Maximum Reverse -21° *Airspeed Limits V MO (Max Operating) 175 KIAS VA (Maneuvering) at 8807 lb. 148 KIAS See POH/AFM for variations with weight and altitude. VFE (Flaps extended) UP – TO/APR 150 KIAS TO/APR – LAND 125 KIAS C.G. Range Takeoff and Flight (With/without (+199.15) to (+204.35) at 8807 lb. Cargo pod) (+193.37) to (+204.35) at 8000 lb. (+185.00) to (+204.35) at 6500 lb. Straight line variation between points given Landing (+197.22) to (+204.35) at 8500 lb. (+193.37) to (+204.35) at 8000 lb. (+185.00) to (+204.35) at 5500 lb. Straight line variation between points given A37CE 8 Rev. 25 III. Model 208B, Caravan, S/N 208B2197 and 208B5000 and On (cont’d) C.G. Range Takeoff and flight (With TKS Fairing) (+199.15) to (+204.35) at 8750 lb. (+193.37) to (+204.35) at 8000 lb. (+185.00) to (+204.35) at 5500 lb. Straight line variation between points given Landing (+197.22) to (+204.35) at 8500 lb. (+193.37) to (+204.35) at 8000 lb. (+185.00) to (+204.35) at 5500 lb. Straight line variation between points given Empty Wt. C.G. Range None Maximum Weight 8807 lb. takeoff and flight (with or without cargo pod) 8750 lb. takeoff and flight (TKS fairing) 8500 lb. landing 8842 lb. ramp 8785 lb. ramp (TKS fairing) For Flight into Known Icing (w/TKS): 208B with cargo pod; 8807 lbs. takeoff and flight 208B with fairing; 8750 lbs. takeoff and flight No. of Seats 1 and 2 (at +133.5 to +146.5) Pilot Seat Locations for Cargo and Passenger Versions. 3 through 11 refer to POH for passenger seat locations Passenger Version only. Maximum Baggage Reference weight and balance data Fuel Capacity 339.1 gal. (335.3 gal. usable ), two 167.5 gal. tanks in wings at +203.8 See NOTE 1 for data on unusable fuel. Oil Capacity 2.36 gal. total, 0.98 gal. usable in engine mounted tank at +69.2 Maximum Operating 25,000 ft. Altitude 20,000 ft. for Flight into Known Icing Control Surface Wing flaps 0° +1° Up, 15° +1° -2° for TO/APR, 30° +1° -2° Land, Movements LH & RH Flap Extension to be symmetric within 1/2° at all positions Main surfaces Ailerons Up 25° +4° -0° Down 16° +1° -0° Spoiler Up 40° +5° Down 0° +0° -5° Elevator Up 24° +0° -1° Down 20° +2° Elevator (w/TKS fairing) Up 22° +1° -0° Down 20° +2° Rudder Right 25° +2° Left 25° +2° (Measured perpendicular to hinge line) Tabs (main surfaces in neutral) Aileron (RH) Up 15° +2° Down 15° +2° Elevator Up 15° +2° Down 15° +2° Tabs servo actions Aileron (RH): 50% of aileron travel +1° Up and Down (tab adjusted to neutral) Aileron (LH): 50% of aileron travel +1° Up and Down Serial No. Eligible 208B2197 and 208B5000 and On A37CE 9 Rev. 25 Data Pertinent to All Models Datum Landplane: 100.00 in. forward of center of nose gear jack point. Amphibian: 100.00 in. forward of front face of firewall. Leveling Means Two jig located nutplates and screws installed on left side of fuselage below side windows and forward of cargo door. Certification Basis Applies to Models 208 and 208B wh en equipped with PW PT6A-114 engine and Hartzell propeller: 1. FAR Part 36 as amended by Amendments 36-1 through 36-12. 2. FAR Part 23 as amended by Amendments 23-1 through 23-28. 3. SFAR 27 as amended by Am endments 27-1 through 27-4. 4. Equivalent Level of Safety (ELOS) applicable to Models 208 and 208B, not equipped with the Garmin G1000 Integrated Cockpit System: FAR 23.955(f)(2), Fuel System. 5. Special Conditions: 23-AC E-3, Dynamic Evaluation, Engine Installation. Applies to the following: 1. Models 208 and 208B when equipped with P&WC PT6A-114 engine and McCauley propeller; and 2. Model 208B when equipped with P&WC PT6A-114A engine and either McCauley or Hartzell propeller; and 3. Model 208 when equipped with P&WC PT 6A-114A engine and McCauley propeller: a. FAR Part 36 as amended by Amendments 36-1 through 36-18. b. FAR Part 23 as amended by Amendments 23-1 through 23-28. c. SFAR 27 as amended by Am endments 27-1 through 27-4. d. ELOS applicable to Models 208 and 208B, not equipped with the Garmin G1000 Integrated Cockpit System: FAR 23.955(f)(2), Fuel System. e. Special Conditions: 23-ACE-3; Dynamic Evaluation, Engine Installation. f. Addition of CFR 23.1459 for FDR and 23.1457 for CVR, Amendment 23-25. Effective for S/N 2080356 and On and 208B0932 and On. Applies to G1000 Model 208B S/N 208B2197, 208B5000 and On equipped with P&WC PT6A-140 (867 SHP) engine and Hartzell propeller: 1. FAR Part 36 (Acoustic s) as amended by Amendments 36-1 through 36-28. 2. FAR Part 23 as amended by Amendments 23-1 through 23-28 with additions for the Garmin G1000 and P&WC PT6A-140 engine. 3. FAR Part 34 (Emissions) original. 4. Special Conditions: 23-AC E-3, Dynamic Evaluation, Engine Installation. Additions for the Garmin G1000 Integrated Cockpit System (ICS) applicable to the following Serial Numbers (S/N): 1. 2080416, 2080500 and On 2. 208B1190, 208B1216, 208B2000 thru 208B2196, and 208B2198 thru 208B4999 3. 208B2197 and 208B5000 and On, equipped with P&WC PT6A-140 (867 SHP) Engine. Original paragraphs amended by 23-1 through 23-28 and addressed during the G1000 certification are included (14CFR): 1. Part 23 as amended by Amendment N/C: 23.303, 23.305(a)(b), 23.307(a), 23.601, 23.609, 23.671(a), 23.1367, 23.1381. 2. Part 23 as amended by Amendment 23-7: 23.561(e), 23.611, 23.689(a), 23.867(a)(b). 3. Part 23 as amended by Amendment 23-13: 23.1589. 4. Part 23 as amended by Amendment 23-14: Electrical aspects of 23.1365(a)(b), 23.1419(b)(c), 23.771(a). 5. Part 23 as amended by Amendment 23-17: 23.607, 23.685(a), and electrical aspects of 23.1309(a)(1)(2)(c), 23.1165(b)(c). 6. Part 23 as amended by Amendment 23-20: 23.1301, 23.1327, 23.1335, 23.1547(b)(e), electrical aspects of 23.1351(a)(b)(c)(d)(e), and electrical aspects of 23.1361(a)(b)(c). A37CE 10 Rev. 25 Data Pertinent to All Models Certification Basis (cont’d) 7. Part 23 as amended by Amendment 23-21: 23.1501, 23.1541(a)(1)(2)(b)(1)(2), 23.1353(g). 8. Part 23 as amended by Amendm ent 23-23: 23.603(a)(b), 23.605. 9. Part 23 as amended by Amendment 23-26: 23.1529. 10. Part 23 as amended by Am endment 23-28: 23.301(a)(d). 11. Part 23 as amended by Amendment 23-34: 23.853(e), 23.1523, 23.1581(a)(b)(d), 23.1583(a)(1)(b)(h), 23.1585(a). 12. Part 23 as amended by Ame ndment 23-35: 23.1459, 23.1457. 13. Part 23 as amended by Amendment 23-43: 23.1322, 23.1331, and 23.1357(a)(b)(c)(d)(e). 14. Part 23 as amended by Amendment 23- 45: 23.773(a)(1)(2), 23.1525, 23.1549. 15. Part 23 as amended by Amendment 23-49: 23.677(d), 23.1303(a)(b)(c)(d)(e)(1)(f), avionic aspects of 23.1309(a)(1)(2)(b)(1)(2)(3)(4) (c)(1)(2)(iii)(3)(d)(e)(f)(1), 23.1311, 23.1321(a)(c)(d)(e), 23.1323(a)(b)(1)(2)(c), 23.1329, 23.1351(c)(4)(d)(1), 23.1361(c), 23.1365(a)(b)(d)(e), 23.1431(a)(b)(d)(e). 16. Part 23 as amended by Amendment 23-50: 23.1325(a)(b)(1)(i)(ii)(iii)(b)(2)(i)(3)(c)(1)(2)(d)(e), 23.1543(b)(c), 23.1553, 23.1545(a)(b)(4)(d), 23.1555(a)(b), 23.1567(a). 17. Part 23 as amended by Amendment 23-51: 23.777(a)(b), 23.955(a)(1)(2)(f), 23.959, 23.1337(a)(1)(2)(b)(1)(4)(c)(d), 23.1183, 23.1203(b)(c)(d)(e). 18. Part 23 as amended by Amendment 23-52: 23.1305(a)(1)(2)(3)(5)(c)(1-10)(e) 19. Part 23 as amended by Amendment 23-53: 23.901(a)(b) 20. Part 23 as amended by Amendment 23-57: 23.1308 Additions for Model 208B equipped with Garmin G1000 and P&WC PT6A-140 Engine (14CFR): 1. Part 23 as amended by Amendment 23-51: 23 .955(a)(4)(b), 23.1203(a)(1), 23.1337(a)(3). 2. Part 23 as amended by Amendment 23-52: 23.1305(a)(4) Additions for new or changed lithium battery installations: 1. 14 CFR Part 23 as amended by Amendment 23-64 (see NOTE 9): 23.2000, 23.2005, 23.2010, 23.2325(g), 23.2510 Additions for new or changed installations affecting aeronautical security (cybersecurity): 1. 14 CFR Part 23 as amended by Amendment 23-64 (see NOTE 9): 23.2000, 23.2005, 23.2010, 23.2500, 23.2505, 23.2510 ELOS: 1. Applicable to Model 208 and 208B equipp ed with the Garmin G1000 Integrated Cockpit System: a. 23.1305(c)(2)(5), Amendment 52; Powerplant instruments. b. 23.1549(a)(b)(c), Amendment 45; Powerplant and auxiliary power unit instruments. Additionally, with guidance from AC 23.1311-1B, Installation of Electronic Display (Section 9 – Powerplant Displays), Section 9.4 Direct-Reading Alphanumeric-Only Displays. 2. Applicable to Model 208 with Garmin G 1000 and Model 208B with or without Garmin G1000 and equipped with the optional TKS ice protection system: 23.207(c) Amendment 7; Stall Warning. 3. Applicable to Model 208B equipped with P&WC PT6A-140 Engine: 23.145, Amendment 17; Longitudinal Control. Compliance with ice protection has been demonstrated in accordance with 23.1419 when ice protection equipment is installed in accordance with the airplane equipment list and is operated per the POH and FAA Approved AFM. Application for type certificate dated June 2, 1982. Type Certificate No. A37CE issued October 23, 1984, obtained by the manufacturer under delegation option provisions of FAR Part 21. A37CE 11 Rev. 25 Data Pertinent to All Models Production Basis Production Certificate No. 4. Delegation Option Manufacturer No. CE-1 (2080001 through 20800246, 208B0001 through 208B0501) and CE-3 (20800247 and On, 208B0502 and On, *except the S/N listed below), authorized to issue airworthiness certificates under delegation option provisions of FAR Part 21. *S/N 208B5230, 208B5247, 208B5267 and 208B5270 were manufactured under Type Certificate A37CE and authorized to issue airworthiness certificate after the FAA inspection and flight test with the provision of 14 CFR 21.183(b). Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. This equipment must include a current POH and FAA Approved AFM. NOTE 1. Current weight and ba lance report including list of equipment included in certificated empty weight and loading instructions, when necessary, must be provided for each aircraft at the time of original certification. Verify from aircraft records whether SK 208-52 “Wing Take External Sump Installation” has been installed. The certified empty weight and corresponding center of gravity location must include full oil of 29 lbs. (at +69.2), and unusable fuel as follows: Model Serial Effectivity Modification Unusable Fuels lb. @ c. g.