Type Certificate Data Sheet

Rev. No. 13 13 13 13 13 13 13 13 13 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A37CE Revision 13 CESSNA 208 208B March 21, 2008 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 Cessna Aircraft Company P. O. Box 7704 Wichita, Kansas 67277 I. Model 208, Caravan, 11 PCLM (Normal Category), Approved October 23, 1984; 11 PCSM (Normal Category), Approved March 26, 1986 Engine [Applicable to S/N 20800001 through 20800276] 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 Up] 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 and FAA Approved Airplane Flight Manual. Engine Limits: [Applicable to S/N 20800001 through 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.-lbs.) 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 2 A37CE, Rev. 13 I. Model 208, Caravan (cont’d) Engine Limits: [Applicable to S/N 20800277 and Up] P&W PT6A-114A Shaft Horsepower NG Gas Generator Speed (% rpm) Indicator Torque (ft.-lbs.) 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 Limits [Applicable to S/N 20800001 through 20800276]: 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 [Applicable to S/N 20800001 and Up and all TKS equipped aircraft]: 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 VMO (Max Operating) 175 KIAS S/N 20800001 through VA (Maneuvering) at 7300 lbs. 148 KIAS 20800060 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 *Airspeed Limits VMO (Max Operating) 175 KIAS S/N 20800061 and Up VA (Maneuvering) at 8000 lbs. 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 3 A37CE, Rev. 13 I. Model 208, Caravan (cont’d) *Airspeed Limits VMO (Max Operating) 175 KIAS Amphibian VA (Maneuvering) at 7600 lbs. 141 KIAS S/N 20800014 and Up 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, flight, and landing S/N 2080001 through 20800060 (+171.91) to (+182.68) at 7300 lbs. (+162.41) to (+182.68) at 4200 lbs. Straight line variation between points given C.G. Range Takeoff and flight S/N 20800061 and Up (+174.06) to (+184.35) at 8000 lbs. (+162.41) to (+184.35) at 4200 lbs. Straight line variation between points given Landing (+173.44) to (+184.35) at 7800 lbs. (+162.41) to (+184.35) at 4200 lbs. Straight line variation between points given C.G. Range Takeoff and flight Amphibian (+172.83) to (+182.68) at 7600 lbs. S/N 20800014 and Up (+165.47) to (+182.68) at 5200 lbs. Straight line variation between points given Landing (+171.91) to (+182.68) at 7300 lbs. (+165.47) to (+182.68) at 5200 lbs. Straight line variation between points given Empty Wt. C.G. Range None Maximum Weight 7300 lb. takeoff, flight, and landing S/N 2080001 through 20800060 7335 lb. ramp Maximum Weight 8000 lb. takeoff and flight S/N 20800061 and Up 7800 lb. landing 8035 lb. ramp Maximum Weight 7600 lb. takeoff and flight Amphibian 7300 lb. landing S/N 20800014 and Up 7635 lb. ramp No. of Seats 1 through 2 (at +133.5 to +146.5) Pilot Seat Locations. 3 through 11 refer to current Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual 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. 4 A37CE, Rev. 13 I. Model 208, Caravan (cont’d) Oil Capacity 3.5 gal. total, 2.37 gal. usable in engine mounted tank at +69.2 Maximum Operating 30,000 ft. - Landplane Altitude 20,000 ft. – Amphibian and 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° 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) (tab adjusted to neutral) 50% of aileron travel +1° Up and Down Aileron (LH) 50% of aileron travel +1° Up and Down Serial Nos. Eligible 20800001 and up - Landplane 20800014 and up - Amphibian with Wipline Model 8000 Amphibious/Seaplane Floats. II - Model 208B, Caravan, 2 PCLM (Normal Category), Approved October 9, 1986 Model 208B, Caravan, 11 PCLM (Normal Category), Approved December 13, 1989 Engine Pratt & Whitney of Canada Ltd., PT6A-114 Turbo Prop, S/N 208B0001 through S/N 208B0178 and 208B0180 through 208B0229, and as modified by SK208-84 Pratt & Whitney of Canada Ltd., PT6A-114A Turbo Prop, (a) S/N 208B0001 through S/N 208B0178 and 208B0180 through 208B0229 and as modified by SK208-84 when operated to PT6A-114 operating limits (b) S/N 208B0179, S/N 208B0230 and on, and as modified by SK208-80 S/N 208B0230 and on, and as modified by SK208-80 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 and FAA Approved Airplane Flight Manual. Engine Limits P&W PT6A-114 or PT6A-114A when operated to PT6A-114 operating limits Shaft Horsepower NG Gas Generator Speed (% rpm) Indicator Torque (ft.-lbs.) 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 5 A37CE, Rev. 13 II. - Model 208B, Caravan (cont’d) Engine Limits (cont’d) PT6A-114A (675 hp) Shaft Horsepower NG Gas Generator Speed (% rpm) Indicator Torque (ft.-lbs.) 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 VMO (Max Operating) 175 KIAS VA (Maneuvering) at 8750 lbs. 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 lbs. (+193.37) to (+204.35) at 8000 lbs. (+179.60) to (+204.35) at 5500 lbs. Straight line variation between points given Landing (+197.22) to (+204.35) at 8500 lbs. (+193.37) to (+204.35) at 8000 lbs. (+179.60) to (+204.35) at 5500 lbs. Straight line variation between points given Empty Wt. C.G. Range None 6 A37CE, Rev. 13 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 through 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 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° 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) (tab adjusted to neutral) 50% of aileron travel +1° Up and Down Aileron (LH) 50% of aileron travel +1° Up and Down Serial Nos. Eligible 208B0001 and up Data Pertinent to All Models Datum 100.00 in. forward of center of nose gear jack point (Landplane). 100.00 in. forward of front face of firewall (Amphibian). Leveling Means Two jig located nutplates and screws installed on left side of fuselage below side windows and forward of cargo door. 7 A37CE, Rev. 13 Data Pertinent to All Models (cont’d) Certification Basis - Applies to Models 208 and 208B when equipped with PW PT6A-114 engine and Hartzell propeller: (1) FAR Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by Amendments 23-1 through 23-28. (2) FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-12. (3) SFAR 27 effective February 1, 1974, as amended by Amendments 27-1 through 27-4. (4) Special Conditions as follows: (a) 23-ACE-3; Dynamic Evaluation, Engine Installation. (5) Equivalent Level of Safety applicable to Model 208 and 208B not equipped with the Garmin G1000 Integrated Cockpit System: (a) FAR 23.955(f)(2), Fuel System. (6) 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 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. Certification Basis - Applies to (a) Models 208 and 208B when equipped with P&W PT6A-114 engine and McCauley propeller; and (b) Model 208B when equipped with P&W PT6A-114A engine and either McCauley or Hartzell propeller; and (c) Model 208 when equipped with P&W PT6A-114A engine and McCauley propeller: (1) FAR Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by Amendments 23-1 through 23-28. (2) FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-18. (3) SFAR 27 effective February 1, 1974, as amended by Amendments 27-1 through 27-4. Additions for the Garmin G1000 Integrated Cockpit System (ICS) and, as annotated, for the GFC-700 Automatic Flight Control System (AFCS) applicable to the Model 208 and 208B when equipped with PW PT64-114A Engine: 14 CFR 23 regulations as amended by Amendment N/C: 14 CFR 23.301(a), (d), 23.303, 23.305(a), (b), 23.307(a), 23.561(e), 23.601, 23.605 23.607, 23.671(a), 23.1367 and 23.1381. 14 CFR 23 regulations as amended by Amendment 23-7: 14 CFR 23.611, 23.689(a), and 23.867(a), (b). 14 CFR 23 regulations as amended by Amendment 23-13: 14 CFR 23.1589. 14 CFR 23 regulations as amended by Amendment 23-14: 14 CFR 23.1365(a), (b), 23.1419(b), (c), and 23.771(a). 14 CFR 23 regulations as amended by Amendment 23-17: 14 CFR 23.607, 23.685(a), and 23.1309(a)(1), (a)(2), (c), 23.1165 (b), (c). 14 CFR 23 regulations as amended by Amendment 23-20: 14 CFR 23.1301, 23.1327, 23.1335 GFC-700 Automatic Flight Control System (AFCS), 23.1547(b), (e), 23.1351(a), (b), (c), (d), (e), and 23.1361(a), (b), (c). 14 CFR 23 regulations as amended by Amendment 23-21: 14 CFR 23.1501, 23.1541(a)(1)(2), (b)(1)(2), and 23.1353(g). 14 CFR 23 regulations as amended by Amendment 23-23: 14 CFR 23.603(a), (b), and 23.605(a). 8 A37CE, Rev. 13 Data Pertinent to All Models (cont’d) Additions for the Garmin G1000 Integrated Cockpit System (ICS) (cont’d) 14 CFR 23 regulations as amended by Amendment 23-26: 14 CFR 23.1529. 14 CFR 23 regulations as amended by Amendment 23-34: 14 CFR 23.853(e), 23.1523, 23.1581(a)(2), 23.1583(a)(1), (b), (h), and 23.1585(a), (b), (d). 14 CFR 23 regulations as amended by Amendment 23-42: 14 CFR 23.677(d). 14 CFR 23 regulations as amended by Amendment 23-43: 14 CFR 23.1322, 23.1331, and 23.1357(a), (b), (c), (d), (e). 14 CFR 23 regulations as amended by Amendment 23-45: 14 CFR 23.773(a)(1), (a)(2), 23.1525, and, 23.1549. 14 CFR 23 regulations as amended by Amendment 23-49: 14 CFR 23 Safety Aspects of 23.1309(b)(3)(e), 23.1309(a)(1)(2), (b)(2)(4), (c)(1)(2)(iii)(3), (d), (e), (f)(1), 23.677(d), 23.1301(a), 23.1303(a), (b), (c), (d), (e)(1), (f), 23.1311, 23.1321(a), (c), (d), (e), 23.1323(a), (b)(1)(2), (c), 23.1329 GFC-700 Automatic Flight Control System (AFCS), 23.1351(a), (b), (c), (d), (e), 23.1361(c), 23.1365(a), (b), (d), (e), 23.1431(a), (b), (d), (e). 14 CFR 23 regulations as amended by Amendment 23-50: 14 CFR 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). 14 CFR 23 regulations as amended by Amendment 23-51: 14 CFR 23.777(a), (b), 23.955(a)(1)(2), (f), 23.959, 23.1337(a)(1)(2), (b)(1)(4), (c), (d), 23.1183, and 23.1203(b), (c), (d), (e). 14 CFR 23 regulations as amended by Amendment 23-52: 14 CFR 23.1305(a)(1)(2)(3)(5), (c)(1-10), (e) 14 CFR 23 regulations as amended by Amendment 23-53: 14 CFR 23.901(a), (b) 14 CFR 23 regulations as amended by Amendment 23-57: 14 CFR 23.1308 Special Conditions as follows: (a) 23-214-SC; HIRF, with guidance from AC20-158. Equivalent Level of Safety as follows: (1) Applicable to Model 208 and 208B equipped with the Garmin G1000 Integrated Cockpit System: (a) 23.1305 Powerplant instruments – (c)(2), (c)(5), Amendment 52. (b) 23.1549 Powerplant and auxiliary power unit instruments – (a) through (d), Amendment 45, additionally, with guidance from AC 23.1311-1B, Installation of Electronic Display (Section 9 – Powerplant Displays), Section 9.4 Direct-Reading Alphanumeric-Only Displays. 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 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. 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 Part 21 of the Federal Aviation Regulations. 9 A37CE, Rev. 13 Data Pertinent to All Models (cont’d) 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), and Delegation Option Manufacturer No. CE-3 (20800247 and on, 208B0502 and on) authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. 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 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual. NOTE 1 Current weight and balance 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 or not 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 FUEL lbs. @ c. g. 208 20800001 through 20800130 NOT modified with SK208-52 20.1 @ +185.7 208 20800001 through 20800130 modified with SK208-52 24.1 @ +186.4 208 20800131 and On 24.1 @ +186.4 208B 208B0001 through 208B0089 NOT modified with SK208-52 20.1 @ +205.7 208B 208B0001 through 208B0089 modified with SK208-52 24.1 @ +206.4 208B 208B0090 and On 24.1 @ +206.4 NOTE 2 The placards specified in the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manuals listed below (or later revision) must be displayed: MODEL CESSNA PART NUMBER 208 [600 SHP] D1307-27-13PH 208 [675 SHP] D1352-13PH 208 [675 SHP] 208PHBUS-00 208B [600 SHP] D1309-21-13PH 208B [675 SHP] D1329-16-13PH 208B [675 SHP] 208BPHBUS-00 Model 208 airplanes modified in accordance with SK-208-12 should use Cessna P/N D1307-27-13PH (or later revision). NOTE 3 Airplanes 20800001 through 20800060 are eligible for operation at the same weight and C.G. approved for S/N 20800061 and up when modified in accordance with SK-208-12 or SK-208-85A “208A to 208 Caravan I Cargo Configuration Conversion”. NOTE 4 Mandatory inspection times for all wing and wing carry through structural components are contained in the Model 208 Series Maintenance Manual. NOTE 5 In addition to the placards required by NOTE 2 above, the prescribed operating limitations indicated by an asterisk (*) must also be displayed as permanent markings. .....END..... * PAGE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 REV. 24 22 22 22 22 22 21 23 23 22 22 22 23 24 23 23 23 23 23 23 22 23 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: , SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E4EA TCDS NUMBER E4EA REVISION: 24* DATE: June 21, 2007 PRATT & WHITNEY CANADA MODELS: PT6A-6 PT6A-25 PT6A-40 PT6A-61 PT6A-6A PT6A-25A PT6A-41 PT6A-61A PT6A-6B PT6A-25C PT6A-41AG PT6A-65B PT6A-6/C20 PT6A-27 PT6A-42 PT6A-65R PT6A-11 PT6A-28 PT6A-42A PT6A-65AR PT6A-11AG PT6A-29 PT6A-45 PT6A-65AG PT6A-15AG PT6A-34 PT6A-45A PT6A-110 PT6A-20 PT6A-34B PT6A-45B PT6A-112 PT6A-20A PT6A-34AG PT6A-45R PT6A-114 PT6A-20B PT6A-35 PT6A-50 PT6A-114A PT6A-21 PT6A-36 PT6A-60 PT6A-116 PT6A-38 PT6A-60A PT6A-121 PT6A-60AG PT6A-135 PT6A-135A PT6A-52 PT6B-9 PT6B-35F PT6D-114A Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E4EA) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER: Pratt & Whitney Canada Corp. (Formerly Pratt & Whitney Canada, Inc., Pratt & Whitney Aircraft of Canada, Ltd., and United Aircraft of Canada, Ltd.) Longueuil, Quebec, Canada J4G 1A1 I. MODEL TYPE (see pages 2, 3, 4, 5, 6, 7) PT6A-6, -6A, -6B, -6/C20, -11, -11AG, -15AG, -20, -20A -20B, -21, -25, -25A, -25C, -27, -28, -29, -34, -34B, -34AG, -35, -36, -110, -112, -114, -114A, -116, -121, -135, -135A, PT6D-114A Free turbine turbo-prop / 3 axial plus one centrifugal stage compressor / single annular combustion chamber, single-stage gas generator turbine / single-stage power turbine II. MODEL TYPE (see pages 7, 8, 9, 10) PT6A-38, -40, -41, -41AG, -42, -42A, -45, -45A, -45B, -45R, -50, -60, -60A, -60AG, - 61, -61A, -52 Free turbine turbo-prop / 3 axial plus one centrifugal stage comp / single annular combustion chamber / single stage gas generator turbine / two stage power turbine III. MODEL TYPE (see pages 10-11) PT6A-65B, -65R, -65AR, -65AG Free turbine turbo-prop / 3 axial plus one centrifugal stage comp / single annular combustion chamber / single stage gas generator turbine / two stage power turbine TCDS E4EA PAGE 2 IV. MODEL TYPE (see pages 11-12) PT6B-9, -35F Free turbine turboshaft (free turbine turboprop -35F) / 3 axial plus one centrifugal stage comp / single annular combustion chamber / single stage gas generator turbine / single stage power turbine I. MODELS PT6A-6 PT6A-6A PT6A-6B PT6A-11, -11AG PT6A-20, -20A, - 20B,-6/C20 REDUCTION GEAR RATIO .0668:1 - - - - - - - - RATINGS Maximum continuous at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm Takeoff (5 min.) at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm 525 500 62 2,200 38,100 578 550 70 2,200 38,100 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 528 500 70(75,-11AG) - - - - 528 500 - -(75, 11AG) - - - - 579 550 72 - - - - 579 550 72 - - - - Maximum reverse Shaft hp. Output rpm (max) Output Shaft --- --- Flanged 4.250" B.C., 8 holes .594 + .005" diameter (See P&WC Installation Drawing) 500 2,100 - - - - - - - - 475 - - - - 500 - - - - FUEL (See NOTE 8) Fuels conforming to P&WC Spec. CPW204 and CPW46. For PT6-AG engines CPW381 also. - - - - - - - - OIL See NOTE 9 - - - - - - - - OIL TANK CAPACITY, gal. 2.3 - - - - - - - - USABLE OIL TANK CAPACITY, gal. 1.5 - - - - - - - - USABLE OIL WHEN INVERTED, gal. --- --- --- --- --- PRINCIPAL DIMENSIONS, in. Length Nominal diameter Maximum radius (excluding exhaust ports) 61.89 18.29 10.85 - - - - - - - - - - - - - - - - 11.50 - - - - -10.85 WEIGHT (DRY) (includes basic engine, fuel and ignition systems but ex- cludes propeller governor (-6 and -20models only) and ignition power source) 280 284 - - 339 340(-11AG) 286(20, 6/C20) 289(20A, 20B) TCDS E4EA PAGE 3 I. MODELS (cont.) PT6A-6 PT6A-6A PT6A-6B PT6A-11, -11AG PT6A-20, -20A, - 20B, -6/C20 CENTER OF GRAVITY (dry weight) (in.) Forward of mount plane Aft of forward mount plane Below engine centerline Right of engine centerline 4.20 --- 0.34 0.32 4.40 --- - - - - - - --- - - - - 3.18 --- 0.26 0.36 4.14(20, 6/C20 4.58(20A, 20B) --- 0.45(20, 6/C20) 20A, 20B) 0.07(20, 6/C20) 0.08(20A, 20B) PT6A-21,-25, -25A PT6A-25C PT6A-15AG, -27, -28 PT6A-29 PT6A-34,-34AG, -34B, -36 REDUCTION GEAR RATIO .0668:1 .0663:1 - - - - - - RATINGS Maximum continuous at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm Takeoff (5 min.) at sea level Equivalent shaft hp Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm 580 550 75 2,200 38,100 580 550 75 2,200 38,100 783 750 82 - - - - 783 750 82 - - - - 715 680 90 - - - - 715 680 90 - - - - 778 750 71 - - - - 778 750 71 - - - - 783 - - 82 - - - - 783 - - 82 - - - - Maximum reverse Shaft hp Output rpm (max) Output Shaft 500 2,100 Flanged 4.250" B.C., 8 holes .594 + .005" diameter (See P&WC Installation Drawing) 720 - - - - 620 - - - - 750 - - - - 720 - - - - FUEL (See NOTE 8) Fuels con- forming to P&WC Spec. CPW204 & CPW46. For PT6-AG engines CPW381 also. - - - - - - - - OIL See NOTE 9 - - - - - - - - TCDS E4EA PAGE 4 I. MODELS (Cont.)) PT6A-21, -25, -25A PT6A-25C PT6A-15AG, -27, -28 PT6A-29 PT6A-34, -34AG, -34B, -36 OIL TANK CAPACITY, gal 2.8(-25, -25A) - - 2.3 - - - - USABLE OIL TANK CAPACITY, gal. 1.5 - - - - - - - - USABLE OIL WHEN INVERTED, gal. .25(-25, -25A) - - --- --- --- PRINCIPAL DIMENSIONS, in. Length Nominal diameter Maximum radius (excluding exhaust ports) 61.89((62.91,- 25,-25A) 18.29(23.00, - 25, -25A) 10.85(16.00, - 25, -25A) 62.91 23.00 16.00 61.89 18.29 11.50 - - - - - - - - - - - - WEIGHT (DRY) (includes basic engine, fuel and ignition systems but ex- cludes propeller governor (-6, -20, and PT6D-114A models only) and ignition power source) 337 (-21) 362 (-25) 352 (-25A) 355 337 - - 340 (353 -34B) CENTER OF GRAVITY (dry weight) (in.) Forward of mount plane Aft of forward mount plane Below engine centerline Right of engine centerline 3.04(-21) 3.00(-25, -25A) --- 0.32(-21) 0.47(-25, -25A) 0.20(-21) 0.29(-25, -25A) 3.00 --- 0.47 0.29 3.04 --- 0.32 0.20 - - --- - - - - - -(3.38 -34B) --- - -(0.37 -34B) - -(0.38 -34B) PT6A-110 PT6A-112 PT6A-114 PT6A-114A PT6A-116 REDUCTION GEAR RATIO .0576:1 - - - - - - - - RATINGS Maximum continuous at sea level Equivalent shaft hp Shaft hp Jet thrust, lb. Output rpm Gas generator rpm Takeoff (5 min.) at sea level Equivalent shaft hp Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm 502 475 68 1,900 38,100 502 475 68 1,900 38,100 528 500 70 - - - - 528 500 70 - - - - 632 600 79 - - - - 632 600 79 - - - - 725 675 124 - - - - 725 675 124 - - - - 736 700 89 - - - - 736 700 89 - - - - TCDS E4EA PAGE 5 I. MODELS (cont.) PT6A-110 PT6A-112 PT6A-114 PT6A-114A PT6A-116 Maximum reverse Shaft hp. Output rpm (max) Output Shaft 455 1,825 Flanged 4.250" B.C., 8 holes .594+ .005: diameter (See PWC Installation Drawing 475 - - - - 600 - - - - 675 - - - - 672 - - - - FUEL (See NOTE 8) Fuels con- forming to P&WC Spec. CPW204 & CPW46. - - - - - - - - OIL See NOTE 9 - - - - - - - - OIL TANK CAPACITY, gal. 2.3 - - - - - - - - USABLE OIL TANK CAPACITY, gal. 1.5 - - - - - - - - PRINCIPAL DIMENSIONS, in. Length, in. Nominal diameter Maximum radius (excluding exhaust ports) 61.89 18.29 11.50 - - - - - - 61.89 18.29 11.73 - - 18.06 11.50 WEIGHT (DRY) (includes basic engine, fuel and ignition systems but ex- cludes propeller governor (-6, -20, and PT6D-114A models only) and ignition power source) 343 - - 359 360 348 CENTER OF GRAVITY (dry weight) (in.) Forward of mount plane Aft of forward mount plane Below engine centerline Right of engine centerline 3.80 --- 0.26 0.34 - - --- - - - - 3.88 --- - - 0.38 - - - - - - - - 3.87 --- 0.25 0.35 PT6A-121 PT6A-135,- 135A PT6D-114A PT6A-35 REDUCTION GEAR RATIO .0576:1 - - .1875 .0663:1 RATINGS Maximum continuous at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm Takeoff (5 min.) at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm 647 615 80 1,900 38,100 647 615 80 1,900 38,100 787 750 93 - - - - 787 750 93 - - - - 729 680 124 6,188 38,100 729 680 124 6,188 - - 787 750 93 2,190 - - 787 750 93 2,190 - - TCDS E4EA PAGE 6 I. MODELS (cont.) PT6A-121 PT6A-135, -135A PT6D-114A PT6A-35 Maximum reverse Shaft hp. Output rpm (max) Output Shaft 591 1,825 Flanged 4.250" B.C., 8 holes .594 + .005" diameter (See PWC Installation Drawing 720 - - - - 680 5,940 - - 720 2,100 - - FUEL (See NOTE 8) Fuels con- forming to P&WC Spec. CPW204 & CPW46. - - - - - - OIL See NOTE 9 - - - - - - OIL TANK CAPACITY, gal. 2.3 - - - - - - USABLE OIL TANK CAPACITY, gal. 1.5 - - - - - - PRINCIPAL DIMENSIONS, in. Length Nominal diameter Maximum radius (excluding exhaust ports) 61.89 18.29 11.50 - - - - - - 52.8 18.29 11.73 61.89 - - - - WEIGHT (DRY) (includes basic engine, fuel and ignition systems but excludes propeller governor (-6, -20 and PT6D-114A models only) and ignition power source) 343 347 297 334 CENTER OF GRAVITY (dry weight) (in.) Forward of mount plane Aft of forward mount plane Below engine centerline Right of engine centerline 3.8 --- 0.26 0.34 3.87 --- 0.25 0.35 0.19 --- 0.31 0.25 3.87 --- 0.25 0.35 PT6A-38 PT6A-40 PT6A-41, -41AG, -42 -42A PT6A-45 PT6A-45A, -45B REDUCTION GEAR RATIO .0663:1 - - - - .0568:1 - - RATINGS Maximum continuous at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm Takeoff (5 min.) at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm 801 750 127 2,000 38,100 801 750 127 2,000 38,100 749 700 122 - - 39,000 749 700 122 - - 39,000 903 850 134 - - 38,100 903 850 134 - - 38,100 1,070 1,020 127 1,700 38,100 1,174 1,120 136 1,700 38,100 - - - - - - - - 39,000 1,229 1,173 - - 140(-45B) - - 39,000 TCDS E4EA PAGE 7 II. MODELS PT6A-38 PT6A-40 PT6A-41, -41AG -42, -42A PT6A-45 PT6A-45A, - 45B Maximum reverse Shaft hp. Output rpm (max) Output Shaft 700 1,900 Flanged 4.250” B.C., 8 holes .594 + .005” diameter (See PWC Installation Drawing) - - - - - - 800 - - - - 900 1,650 - - - - - - - - FUELS (See NOTE 8) Fuels con- forming to PWC Spec. CPW204 & CPW46. For PT6-AG engines CPW381 also. - - - - - - - - OIL See NOTE 9 - - - - - - - - OIL TANK CAPACITY, gal. 2.5 - - - - - - - - USABLE OIL TANK CAPACITY, gal. 1.5 - - - - - - - - PRINCIPAL DIMENSIONS, in. Length Nominal diameter Maximum radius (excluding exhaust ports) 66.47 18.29 12.84 - - - - - - - - - - - - 72.62 - - - - - - - - - - WEIGHT (DRY) (includes basic engine, fuel and ignition systems but ex- cludes propeller governor (-6, -20 and PT6D-114A models only) and ignition power source) 405 419 - - 445 - - CENTER OF GRAVITY (dry weight)(in.) Forward of mount plane Aft of forward mount plane Below engine centerline Right of engine centerline 2.49 --- 0.32 0.19 - - --- - - - - - - --- - - - - 5.38 --- 0.12 0.27 5.38 --- 0.12 0.27 TCDS E4EA PAGE 8 II. MODELS PT6A-45R PT6A-50 PT6A-60, -60A PT6A-61, -61A PT6A-60AG PT6A-52 REDUCTION GEAR RATIO .0568:1 .0438:1 .0568:1 .0663:1 .0663:1 RATINGS Maximum continuous at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm Takeoff (5 min.) at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm 1,070 1,020 127 1,700 39,000 1,254 1,197 141 1,700 39,000 1,022 973 124 1,210 38,100 1,174 1,120 136 1,210 38,500 1,113 1,050 157 1,700 39,000 1,113 1,050 157 1,700 39,000 902 850 132 2,000 - - 902 850 132 2,000 - - 1,081 1,020 154 1,700 - - 1,113 1,050 157 1,700 - - 898 850 120 2000 - - 898 850 120 2000 - - Maximum reverse Shaft hp. Output rpm (max) Output Shaft 900 1,650 Flanged 4.250" B.C., 8 holes .594 + .005" diameter (See PWC Installation Drawing 1,120 1,210 Flanged 5.125" B.C., 8 holes .594 + .005" diameter (See PWC Installation Drawing) 900 1,650 Flanged 4.250" B.C., 8 holes .594 + .005" diameter (See PWC Installation Drawing) 800 1,900 - - 900 1,650 - - 800 1900 Flanged 4.250" B.C., 8 holes .594 + .005" diameter (See PWC Installation Drawing) FUEL (See NOTE 8) Fuels con- forming to P&WC Spec. CPW204 & CPW 46. For PT6-AG engines CPW381 also. - - - - - - - - See PWC SB 13044 for approved fuel types. OIL See NOTE 9 - - - - - - - - - - OIL TANK CAPACITY, gal. 2.5 3.0 2.5 - - - - - - USABLE OIL TANK CAPACITY, gal. 1.5 1.0 1.5 - - - - - - PRINCIPAL DIMENSIONS, in. Length Nominal diameter Maximum radius (excluding exhaust ports) 72.62 18.29 12.84 79.89 - - 15.44 72.09 18.29 12.84 66.76 - - - - 72.09 - - - - 66.76 - - - - WEIGHT (DRY) (includes basic engine, fuel and ignition systems but ex- cludes propeller governor (-6, -20, and PT6D-114A models only) and ignition power source) 449 459 622 487 443 489 TCDS E4EA PAGE 9 II. MODELS (continued) PT6A-45R PT6A-50 PT6A-60, -60A PT6A-61, -61A PT6A-60AG PT6A-52 CENTER OF GRAVITY (dry weight) (in.) Forward of mount plane Aft of forward mount plane Below engine centerline Right of engine centerline 5.38 --- 0.12 0.27 --- See NOTE 17 See NOTE 17 See NOTE 17 5.22 --- .300 .28 2.630 --- - - .29 5.22 --- - - .28 2.51 --- .260 .330 III. MODELS PT6A-65B PT6A-65R PT6A-65AR PT6A-65AG REDUCTION GEAR RATIO .0568:1 - - - - - - RATINGS Maximum continuous at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm Takeoff (5 min.) at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm Alternative takeoff (5 min. at sea level) Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm 1,249 1,173 189 1,700 39,000 1,249 1,173 189 1,700 39,000 --- --- --- --- --- - - - - - - - - - - 1,459 1,376 209 - - - - 1,308 1,230 195 1,700 39,000 1,298 1,220 194 - - - - 1,509 1,424 214 - - - - - - - - - - - - - - - - - - - - - - - - 1,381 1,300 202 - - - - --- --- --- --- --- Maximum reverse Shaft hp. Output rpm (max) Output Shaft 900 1,650 Flanged 4.250" B.C., 8 holes .594 + .005" diameter (See PWC Installation Drawing) - - - - - - - - - - - - - - - - - - FUEL (See NOTE 8) Fuels con- forming to P&WC Spec. CPW204 & CPW46. For PT6- AG engine CPW381 also. - - - - - - OIL See NOTE 9 - - - - - - OIL TANK CAPACITY, gal. 2.5 - - - - - - USABLE OIL TANK CAPACITY, gal. 1.5 - - - - - - PRINCIPAL DIMENSIONS, in. Length Nominal diameter Maximum radius 74.79 18.29 12.84 - - - - - - - - - - - - - - - - - - TCDS E4EA PAGE 10 III. MODELS (continued) PT6A-65B PT6A-65R PT6A-65AR PT6A-65ag WEIGHT (DRY) (includes basic engine, fuel and ignition systems but excludes propeller governor (-6,-20, and PT6D-114A models only) and ignition power source) 495 496 501 - - CENTER OF GRAVITY (dry weight) (in.) Forward of mount plane Aft of forward mount plane Below engine centerline Right of engine centerline 3.75 --- .29 .17 - - --- - - - - - - --- - - - - - - --- - - - - IV. MODELS PT6B-9 PT6B-35F REDUCTION GEAR RATIO .1889:1 .1875:1 RATINGS Maximum continuous at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm Takeoff (5 min.) at sea level Equivalent shaft hp. Shaft hp. Jet thrust, lb. Output rpm Gas generator rpm --- 500 124 6,230 38,100 --- 550 136 6,230 38,100 684 650 --- 6,188 - - 684 650 --- 6,188 - - Maximum reverse Shaft hp. Output rpm (max) --- --- --- --- OUTPUT SHAFT SAE Aero Std. 84d Spline 1.5 in P.D. 36 teeth, 1.5 in. P.D. See Installation Manual FUEL (See NOTE 8) Fuels conforming to P&WC Spec. CPW204 & CPW46. - - OIL See NOTE 9 - - OIL TANK CAPACITY, gal. 2.3 - - USABLE OIL TANK CAPACITY, gal. 1.5 - - PRINCIPAL DIMENSIONS, in. Length Nominal diameter Maximum radius (excluding exhaust ports) 58.68 18.06 10.85 - - - - 12.6 WEIGHT (DRY) (includes basic engine, fuel and ignition systems but ex- cludes propeller governor (-6,-20, and PT6A-114A models only) and ignition power source) 255 305 TCDS E4EA PAGE 11 IV. MODELS (continued) PT6B-9 PT6B-35F CENTER OF GRAVITY (dry weight) (in.) Forward of mount plane Aft of forward mount plane Below engine centerline Right of engine centerline --- 22.08 0.13 0.52 --- 23.56 RH/23.3 LH* .52 RH/.63 LH .16 RH/.15 LH CERTIFICATION BASIS Applicable to the following engines and serial numbers: FAR 21.29, CAR 13. (Except Serial numbers shown below which were certified under FAR 21.21, FAR 33-5 NOTE 19) MODEL S/N DATE OF APPLICATION DATE TYPE CERTIFICATE NO. E4EA ISSUED/REVISED PT6A-6 PT6A-6A PT6A-6B PT6B-9 PT6A-11 PT6A-11AG PT6A-15AG PT6A-20 PT6A-20A PT6A-20B PT6A-6/C20 PT6A-21 PT6A-25 PT6A-25A PT6A-25C PT6A-27 All All All All All All All All All except 024103-024160 All All All All except 058013-058018 058025-058040 058042-058047 058049-058055 058059-058064 058068-058073 058077-058084 058089-058204 All All All except 044878-040879 040883-040884 040894-040895 040899-040921 040929-040934 040937-040943 040946-040949 040982-040988 040993-040999 041006-041007 041015-041021 041027-041032 041036 041041-041044 041050-041053 041060-041063 041067-041098 041105-041110 041113-041146 041152-041156 041162-041175 041180-041194 041199-041201 June 4, 1962 April 6, 1965 November 30, 1967 June 4, 1962 August 19, 1977 January 10, 1979 January 9, 1978 April 9, 1965 February 19, 1973 August 20, 1973 February 19, 1973 December 2, 1974 May 5, 1976 December 13, 1976 March 5, 1990 November 15, 1966 December 31, 1963 May 28, 1965 December 20, 1967 May 28, 1965 September 16, 1977 May 17, 1979 January 27, 1978 October 29, 1965 March 9, 1973 October 2, 1973 March 9, 1973 December 10, 1974 May 6, 1976 December 28, 1976 June 8, 1990 December 20, 1967 TCDS E4EA PAGE 12 PT6A-28 PT6A-29 PT6A-34 PT6A-34B PT6A-34AG PT6A-35 PT6B-35F PT6A-36 All except 050676-050925 050928-050934 All All except 056071-056075 056080-056081 056086-056090 056098-056107 054011, 054012 only prior to 054007 All All All All January 27, 1969 October 6, 1967 April 29, 1971 July 20, 1976 February 3, 1977 October 24, 2001 August 10, 1979 December 13, 1973 March 11, 1969 October 28, 1968 November 11, 1971 August 4, 1976 February 14, 1977 May 29, 2002 March 26, 1982 December 13, 1973 PT6A-38 PT6A-40 PT6A-41 PT6A-41AG PT6A-42 PT6A-42A PT6A-45 PT6A-45A PT6A-45B PT6A-45R PT6A-50 PT6A-60 PT6A-60A PT6A-60AG PT6A-61 PT6A-61A PT6A-65B PT6A-65R PT6A-65AR PT6A-65AG PT6A-110 PT6A-112 PT6A-114 PT6A-114A PT6A-116 PT6A-121 PT6A-135 PT6A-135A PT6D-114A PT6A-52 079156, 079157 only prior to 079153 All All All All All All All All All All All All All All All All All All All All All All All All All All All All All May 12, 1975 April 19, 1983 August 30, 1973 December 21, 1978 July 11, 1979 September 21, 1998 May 12, 1975 March 25, 1976 March 2, 1979 June 25, 1980 September 21, 1976 April 20, 1982 April 19, 1983 October 1, 1996 April 20, 1982 January 6, 1984 April 20, 1982 April 20, 1982 January 6, 1984 July 23, 1987 August 8, 1980 October 12, 1978 December 21, 1982 October 4, 1989 October 4, 1984 April 12, 1982 September 9, 1977 February 3, 1982 October 30, 1996 May 26, 2006 May 30, 1975 July 13, 1983 October 2, 1973 May 17, 1979 October 12, 1979 December 4, 1998 May 30, 1975 April 22, 1976 March 29, 1979 August 1, 1980 October 22, 1976 March 15, 1983 November 7, 1983 October 10, 1996 March 15, 1983 May 1, 1985 September 17, 1982 September 17, 1982 May 1, 1985 August 19, 1987 February 15, 1981 October 30, 1978 May 21, 1984 March 19, 1990 May 1, 1985 August 3, 1982 September 12, 1977 April 29, 1982 September 22, 1997 May 31, 2007 IMPORT REQUIREMENTS: To be considered eligible for installation on U.S. registered aircraft, each engine to be exported to the United States shall be accompanied by a Certificate of Airworthiness for export or certifying statement endorsed by the exporting cognizant civil airworthiness authority which contains the following language: (1) This engine conforms to its United States type design (Type Certificate Number E4EA) and is in a condition for safe operation. (2) This engine has been subjected by the manufacturer to a final operational check and is in a proper state of airworthiness. Reference FAR Section 21.500, which provides for the airworthiness acceptance of aircraft engines or propellers manufactured outside of the U.S. for which a U.S. type certificate has been issued. Additional guidance is contained in FAA Advisory Circular 21.23, Airworthiness Certification of Civil Aircraft, Engines, Propellers and Related Products, Imported into the United States. TCDS E4EA PAGE 13 NOTES NOTE 1. Maximum permissible temperatures: PT6A-20, -20A, -20B, -6/C20 PT6A-6, -6A, -6B, PT6A-28, -29 PT6B-9 PT6A-11, -11AG Measured Rated Turbine Temperature as Indicated by the Average of 24 Gas Temp. Thermocouples Measured Rated Inter-Turbine Temperature as Indicated by the Average of 8 or 10 Gas Temp. Thermocouples - - Takeoff 1821 oF (994o C) 1382ºF(750ºC) (PT6A-20,-20A,-20B,-6/C20) 1382 o F (750o C) 1292o F (700o C) Maximum Continuous 1745 oF (952o C) 1382ºF(750ºC) (PT6A-20,-20A,-20B,-6/C20) 1382 o F (750o C) 1319 o F (715o C) (PT6B) 1292 o F (700o C) Starting Transient (2 sec.) 1900o F (1038o C) 1994ºF(1090ºC) (PT6A-20,-20A,-20B,-6/C20) 1994 o F (1090o C) - - PT6A-21 PT6A-25, -25A PT6A-15AG, -27, -112, -121 Measured Rated Inter-Turbine Temperature as Indicated by the Average of 8 or 10 Gas Temp. Thermocouples - - - - Takeoff 1283 oF (695o C) 1283 o F (695o C) 1336 o F (725o C) Maximum Continuous 1283 oF (695o C) 1283 o F (695o C) 1336 o F (725o C) Starting Transient (2 sec.) 1994o F (1090o C) - - 1994 o F (1090o C) PT6A-34, -34B, -34AG, -25C PT6A-35,-36,-114,-114A,- 116,-135,-135A,-PT6B- 35F,PT6D-114A PT6A-110 Measured Rated Inter-Turbine Temperature as Indicated by the Average 8 or 10 Gas Temp. Thermocouples Measured Rated Inter- Turbine Temperature as Indicated by the Average of 8 Gas Temp. Thermocouples - - Takeoff 1454 oF (790o C) 1481 o F (805o C) 1265 o F (685o C) Maximum Continuous 1454 oF (790o C) 1481 o F (805o C) 1265 o F (685o C) Starting Transient (2 sec.) 1994o F (1090o C) - - - - PT6A-38 PT6A-41, -41AG PT6A-45 PT6A-42, -42A, -45A,-45B, -50, -40 Measured Rated Inter- Turbine Temperature as Indicated by the Average of 8 Gas Temp. Thermocouples - - - - (8 or 10) - - Takeoff 1301o F (705o C) 1382o F (750o C) 1400o F (760o C) 1472o F (800o C) Maximum Continuous 1301 o F (705o C) 1382o F (750o C) 1400o F (760o C) 1472o F (800o C) Starting Transient (5 sec.) 1832o F (1000oC) - - - - - - Alternate Takeoff --- --- --- --- TCDS E4EA PAGE 14 NOTE 1.(continued) PT6A-45R PT6A-60 PT6A-61 PT6A-60A, -61A, -60AG, -52 Measured Rated Inter- Turbine Temperature as Indicated by the Average of 8 Gas Temp. Thermocouples Measured Rated Inter- Turbine Temperature as Indicated by the Average of 8 or 10 Gas Temp. Thermocouples - - - - Takeoff 1553oF (845o C) 1472ºF (800ºC) - - 1508ºF(820ºC) Maximum Continuous 1494oF (812o C) 1472 o F (800o C) - - 1508 o F (820o C) 1472ºF(775ºC)(-60AG) Starting Transient (5 sec.) 1832 o F (1000o C) - - - - - - Alternate Takeoff 1472oF (800o C) --- --- --- PT6A-65B PT6A-65R PT6A-65AR PT6A-65AG Measured Rated Inter- Turbine Temperature as Indicated by the Average of 8 or 10 Gas Temp. Thermocouples - - - - - - Takeoff 1508ºF(820ºC) 1553ºF(845ºC) 1571 o F (855o C) 1508o F (820o C Maximum Continuous 1490 o F (810o C) 1539 o F (835o C) 1544 o F (840o C) 1508 o F (820o C) Starting Transient 1832 o F (1000o C) - - - - - - Alternate Takeoff --- 1490 o F (810o C) 1508 o F (820o C) --- All except:PT6A-40,-41,-42,-42A,-45,-45A,-45B,-45R,-60, -60A,-60AG,-61,-61A,-65AG,-65AR,-65B, and -65R models, Oil Temperature Continuous minus 40 o F (-40 o C) to 210o F (99o C) except for MIL-L-7808 (where approved; See NOTE 9) for which the maximum allowable temperature is 185o F (85o C). Limited periods of 10 minutes of 220o F (104o C) are allowable, except on A- 25, A-25A, A-25C, A-11 and A-11AG (5 minute maximum), and A-50 (15 minutes maximum). PT6A-40,-41,-42,-42A, and -61A, Oil Temperature Continuous minus 40ºF(-40ºC) to 220ºF(104ºC). Maximum ground operation 230ºF(110ºC). PT6A-45,-45A,-45B,-45R,-52, -60,-60A,-60AG, -61, -65AG,-65AR,-65B,-65R, Oil Temperature Continuous minus 40ºF(-40ºC) to 230ºF(110ºC). Fuel temperature maximum fuel pump inlet of 135o F (57o C). Fuel temperature minimum fuel pump inlet of -65 o F (-54 o C) or 12 centistokes. NOTE 2. Fuel and Oil Pressure Limits: Fuel: Minimum pressure at inlet to the engine fuel system shall not be less than 5 p.s.i. above true vapor pressure of the fuel. For emergency operation, with airframe boost pump inoperative, it must be such that vapor liquid ratio does not exceed 0.1 for continuous operation and does not exceed 0.3 for more than 10 hours in a pump overhaul life. Oil: Operating range PT6A-6, -6A, -6B, -20, -20A, -20B, -6/C20, PT6B-9 28000 rpm gas generator speed and above: Below 28000 rpm gas generator speed: 65-85 p.s.i.g., 80 (max. B-9) 40 p.s.i.g. (min.) PT6A-11, -11AG, -15AG, -21, -27, -28, -29, -50, -110, -112, -121 27000 rpm gas generator speed and above, with an oil temperature of 140-158o F: Below 27000 rpm gas generator speed: 80-100 p.s.i.g. 40 p.s.i.g. (min) 60 (-50) TCDS E4EA PAGE 15 NOTE 2. (Cont.) Oil: Operating range PT6A-25, -25A, -25C 27000 rpm gas generator speed and above, with an oil temperature of 140-160o F: Below 27000 rpm gas generator speed: 65-85 p.s.i.g. (75-95(A-25C) 40 p.s.i.g. (min) PT6A-34, -34B, -34AG, -35,-135, -135A, -36, -114, -114A, -116, PT6B-35F, PT6D-114A 27000 rpm gas generator speed and above, with an oil temperature of 140-158o F: Below 27000 rpm gas generator speed: 85-105 p.s.i.g. (75-100(B-35F)) 40 p.s.i.g. (min) PT6A-38, -40, -41, -41AG, -42, -42A 27000 rpm gas generator speed and above, with an oil temperature of 140-160o F: Below 27000 rpm gas generator speed: 85-135 p.s.i.g. (PT6A-38) 105-135 p.s.i.g. (PT6A-41, -41AG) 100-135 p.s.i.g. (PT6A-40, -42, -42A) 60 p.s.i.g. (min) PT6A-45, -45A, -45B, -45R,-52, -60, -61, -65B, -65R, -60A, - 60AG, -61A, -65AR, -65AG 27000 rpm gas generator speed and above, with an oil temperature of 140-160o F: Below 27000 rpm gas generator speed: 90-135 p.s.i.g. 60 p.s.i.g. (min) NOTE 3. The engine ratings are based on static sea level condition 29.92 in Hg pressure, compressor intake screen installed, no external accessory loads and no airbleed. These ratings are available up to the following compressor inlet air (dry) temperatures. Maximum Continuous Takeoff Maximum Continuous Takeoff PT6A-6, -6A, - 6B 64 o F 70 o F PT6A-45R 92 o F 73, 52(1)o F PT6A-20, -20A, -20B, -6/C20 70 70 PT6A-50 90 59, 93(2) PT6A-11, - PT6A-11AG 108 90 108 90 PT6A-60, -60A 77 77 PT6A-21 91 91 PT6A-60AG 63 79 PT6A-25, -25A 93 93 PT6A-61, -61A 115 115 PT6A-25C 87 87 PT6A-15AG, - 27 71 71 PT6A-65B 101 101 PT6A-28 70 70 PT6A-65R 101 82, 76(1) PT6A-29 73 73 PT6A-65AR 101 82, 84(1) PT6A-34, -34B, -34AG 86 86 PT6A-65AG 101 71 PT6A-35,-135A 93 93 PT6A-36 97 97 PT6A-110 101 101 PT6A-38 102 102 PT6A-112 133 133 PT6A-40 135 135 PT6A-114 136 136 PT6A-41, - 41AG, -42, - 42A 106(86, -42A) 106 PT6A-114A 115 115 TCDS E4EA PAGE 16 Maximum Continuous Takeoff Maximum Continuous Takeoff PT6A-45 79 59 PT6A-116 105 105 PT6A-45A 79 46 PT6A-121 91 91 PT6A-45B 84 52 PT6A-135 85 85 PT6B-9 72 77 PT6B-35F 110 110 PT6D-114A 104 104 PT6A-52 142 142 1 Alternative Takeoff 2. Takeoff with Augmentation Fluid NOTE 4. Accessory Drive Provisions: (All Models except -50) The following accessory drive provisions are available and are included in the basic engine weight. Maximum Driven by Gas Rotating Facing Speed Ratio Maximum Torque Overhang Generator Turbine Drive Pad (to Turbine) Continuous Static (in. - lbs.) Tachometer, Accessory Gearbox CC 0.112 7 100 10 Starter and/or Generator C 0.293 170 1600 250 (38, 40, 41, 42, 42A,45, 45A, 45B, 45R, 52, 60, 60A, 60AG, 61, 61A, 65B, 65R, 65AR, 65AG, 114, 114A, B- 35F, D-114A) 150 Vacuum Pump CC 0.103 60 800 25 Hydraulic Pump CC 0.203 150 800 25 Aircraft Accessory Drive C 0.321 135 800 25 Driven by Rotating Facing Speed Ratio Maximum Torque Power Turbine Drive Pad (to Turbine) Continuous Static Maximum Overhang (in. - lbs.) TCDS E4EA PAGE 17 Tachometer (Tachometer and overspeed governor for PT6A-6,-6A,-6B and-20 only) C 0.1264(PT6A-15AG, -25C,-27,-28,-29,-34,- 34B,-34AG,-35,-36,- 38,-40,-41,-41AG,- 42,-42A,-52, -61,- 61A) 0.1263 (B-35F); 0.1273(PT6A-6,-6A,- 6B,-11,-11AG,-20,- 20A,-20B,-6/C20,-21,- 25,-25A,-110,-112 114, 114A, -116, 121,- 135,-135A); 0.1405 (45, 45A, 45B, 45R, 60, 60A, 60AG, 65B, 65R, 65AR, 65AG) 7 100 10 NOTE 4. (Cont'd) Driven by Power Rotating Facing Speed Ratio Maximum Torque Turbine Drive Pad (to Turbine) Continuous Static Maximum Overhang (in. - lbs.) Propeller Governor and Overspeed Governor* C 0.1264(PT6A-15AG, -25C,-27,-28,-29,-34,-34B,- 34AG,-35,-36,-38,-40,-41,- 41AG,-42,-42A,-52,-61,-61A) 0.1273(PT6A-6,-6A,-6B,-11,- 11AG,-20,-20A,-20B,-6/C20,- 21,-25,-25A,-110,-112 114, 114A, -116, 121,-135,- 135A); 0.1405(PT6A-45, 45A, 45B, 45R, 60, 60A, 60AG, 65B, 65R, 65AR, 65AG) 50 850 25 * May be an optional drive, which is not included in the basic engine weight, is included. The hydraulic pump drive requires the aircraft accessory drive to complete the train. Cabin pressurization may be provided by the approved combination of the Beech Aircraft Corporation Gearbox No. 50-9903 with the Godfrey Engineering type 9 cabin supercharger, mounted directly on the accessories gearbox. PT6A-38,-40,-41,-41AG,-42,-42A are approved for operation with an accessory mounted on the reduction gearbox and belt driven from the propeller assembly provided that the accessory is mounted and driven in accordance with the location dimensions and weight prescribed in Sheet 5 of Drawing Number 3018500, revision dated August 20, 1973. C = Clockwise CC = Counterclockwise TCDS E4EA PAGE 18 Accessory Drive Provisions: (PT6A-50 only) Maximum Driven by Gas Rotating Facing Speed Ratio Maximum Torque Overhang Generator Turbine Drive Pad (to Turbine) Continuous Static (in. - lbs.) Tachometer Accessory Gearbox CC 0.112 7 100 10 Starter and/or Generator C 0.293 170 1600 230 Hydraulic Pump* CC 0.204 150 800 30 Driven by Power Turbine Tachometer CC 0.1400 7 100 10 Alternator C 0.529 120 1600 105 Prop. Governor CC 0.1400 100 1700 40 Prop. Overspeed Governor CC 0.1400 50 850 25 TCDS E4EA PAGE 19 NOTE 5. External airbleed shall not exceed 5.25%, except as specified in specific installation manuals. A maximum of 1.5 lbs. Per minute may be bled during starting. Bleed air meets the requirements of Paragraph 3.18 of MIL-E-5007C. NOTE 6. Maximum Allowable Torque: The Maximum allowable steady state and acceleration torque, as measured by the torquemeter, are: Model Continuous lb. Ft. Transient Acceleration lb. Ft. PT6A-11, 11AG 1194 1500 PT6A-6, 6A, 6B, 20, 20A, 20B, 6/C20, 21 25, 25A 1315 1500 PT6A-15AG, 27 1628 2100 PT6A-28 1786 2100 PT6A-29, 34, 34B, 34AG, 35, 36, 25C 1970 2100 PT6A-38 1970 2750 PT6A-40 2230 2750 PT6A-41, 41AG, 42, 42A 2230 2750 PT6A-45, 45A, 45B 3625 5100 PT6A-45R 3625 5100 PT6A-50 4860 5900 PT6A-135, 135A 2080 2400 PT6B-9 464 --- PT6A-112 1480 1900 PT6A-110 1313 1700 PT6A-60, 60A, 60AG 3625 5100 PT6A-61, 61A 2230 2750 PT6A-65B 3625 5100 PT6A-65R 4250 (3800 Alternative Takeoff 5100 PT6A-114, 114A 1980 2400 PT6A-121 1710 2200 PT6B-35F 570 658 PT6A-65AR 4400(3800 Alternative Takeoff) 5100 PT6A-116 1940 2400 PT6A-65AG 3800 5100 PT6D-114A 610 740 PT6A-52 2230 2750 TCDS E4EA PAGE 20 NOTE 7. The maximum output shaft overspeed limit is 110 percent (except 100% for PT6A-38, 41, 41AG, 42 and 42A only) at all ratings and may be employed for sustained periods in emergencies. The normal steady state output shaft operating limit speeds are defined as 2200 rpm (100%) for the PT6A-6, 6A, 6B, 6/C20, 11, 11AG, -15AG, - 20, -20A, -20B, -21, -25, -25A, -25C, -27, -28, -29, -34, -34B, -34AG, -36, 2190 rpm (99.6%) for the PT6A-35, 2000 rpm (90.7%) for the PT6A-38, -40, -41, -41AG, -42, -42A, -52, -61, and -61A, 1900 rpm (100%) for the PT6A-45,-45A,-45B,-45R,-65B,-65R,-60,-60A,-60AG,-65AR,-65AG, -135, 135A, 110, 112, 114, 114A, 121, and 116, 1210 rpm (100%) for the PT6A-50, 6230 rpm (100%) for the PT6B-9 and 6188 rpm (100%) for the PT6B-35F and PT6D-114A and is the normal steady state operating limit. The normal steady state operating limit speed rises linearly as power is decreased, reaching a maximum of 105% at idle power for the PT6B-9. 100% gas generator speed is defined as 37,468 rpm. Unlimited and limited gas generator speeds are: Model Unlimited Speed, rpm Limited Speed, rpm Duration PT6A-6,-6A,-6B,-11,-11AG,- 20,-20A,-20B,-6/C20,-21,- 25,-25A,-25C,-27,-28,-29,- 34,-34B,-34AG,-36,-38,-41 38,100 (101.7%) 38,500 (102.8%) 10 Sec PT6A-35,-110,-112,-114,- 114A,-116,-121,-135,- 135A,PT6D-114A 38,100 (101.7%) 38,500 (102.8%) 2 Sec PT6A-50 38,500 (102.8%) --- --- PT6A-40,-42,-42A 38,100 (101.7%) 39,000 (104.1%) 10 Sec PT6A-45,-45A,-45B,-45R,- 52, -60,-60A,-60AG,-61,- 61A,-62,-65B,-65R,-65AR,- 65AG 39,000 (104.1%) --- --- NOTE 8. Emergency use of MIL-G-5572, Grades 80/07, 91/98, 100/130 and 115/145 is permitted for a total time period not exceeding 150 hours during any overhaul period. It is not necessary to purge the unused fuel from the system when switching fuel type. NOTE 9. The following oils are eligible for these engines: PWC PT6 Engine Service Bulletin Nos. 1001, 1601, 3001, 4001, 12001 and 13001 list approved brand oils. NOTE 10. These engines meet FAA requirements for operation in icing conditions when the intake system conforms with the PWC Installation Manual instruction for inertial separation of snow and icing particles; when the alternative approved alcohol system is used, flight in visible moisture is restricted as specified in the PWC Installation Manual. These engines also meet FAA requirements for adequate disk integrity and rotor blade containment and do not require external armoring. NOTE 11. For reversing application the PT6A-6A and PT6A-20 engines must be equipped with Woodward Propeller Governor Type X210XXX. NOTE 12. Fuel controls approved for each engine model are listed in the applicable Parts Catalog. NOTE 13. The above models incorporate the following characteristics: Model Characteristics PT6A-6 Basic model PT6A-6A Incorporates provisions for reversing propeller. PT6A-6B Incorporates provisions for reversing propeller, PT6A-20 mechanism. PT6B-9 Single stage reduction gearing. (Output shaft speed 6,230 r.p.m.) PT6A-20 Maximum continuous rating equal to takeoff. Provisions for reversing. PT6A-20A Similar to PT6A-20 except for exhaust port configuration and optional propeller reversing system. PT6A-20B Similar to PT6A-20 except for optional propeller reversing system. PT6A-11 Similar to PT6A-21 except derated. TCDS E4EA PAGE 21 NOTE 13. (Cont.) Model Characteristics PT6A-11AG Similar to PT6A-11, intended for agricultural aviation. Permissible rotor component lives, overhaul, inspection intervals and fuel requirements are listed in PWC Engine Service Bulletin Nos. 12102, 12103, and12144 respectively. PT6A-15AG Similar to PT6A-27, intended for agricultural aviation. Permissible rotor component lives, overhaul inspection intervals and fuel requirements are listed in PWC Engine Service Bulletin Nos. 12102, 12103, and 12144 respectively. PT6A-6/C20 Similar to PT6A-20 except this configuration previously PT6A-6 converted to PT6A-20 by service bulletin. PT6A-21 Similar to PT6A-27 except derated. PT6A-25 Similar to PT6A-27 except for modifications required for inverted flight optional torque controller, and aluminum alloy castings. PT6A-25A Similar to PT6A-25 except for magnesium alloy major castings in place of aluminum alloy. PT6A-25C Similar to PT6A-25A except for A-34 hot section; T-3B first stage compressor blades and long inducer propeller; A-100 large bore reduction gears; and A-25A installation features. Ratings and limits are the same as the A-34. PT6A-27 Features higher ratings, revised engine parts and integrated propeller reversing control. PT6A-28 Similar to PT6A-27 except for higher inter-turbine temperature limit. PT6A-29 Features higher ratings, revised first stage reduction gearing. PT6A-34 Similar to PT6A-27 except incorporates a compressor turbine similar to PT6T-3 for higher ratings. PT6A-34B Similar to PT6A-34, except for aluminum alloy major castings in place of magnesium alloy. PT6A-34AG Similar to PT6A-34, intended for agricultural aviation. Permissible rotor component lives, overhaul, inspection intervals and fuel requirements are listed in P&WACL Engine Service Bulletin Nos. 1302, 1303, and 1344 respectively. PT6A-35 Similar to PT6A-135 but incorporating the reduction gearbox of the PT6A-34. PT6A-36 Similar to PT6A-34 except for increased turbine inlet temperature limits. PT6A-38 Similar to PT6A-41 except derated. PT6A-40 Similar to PT6A-42 except for increased flat rating and manual fuel control override. PT6A-41 Features an enlarged compressor and two stage power turbine for higher ratings. PT6A-41AG Similar to PT6A-41, intended for agricultural aviation. PT6A-42 Similar to PT6A-41 except for increased cruise rating and increased inter-turbine temperature limits with improved compressor and reduced loss exhaust ducts. PT6A-42A Same as PT6A-42 except for addition of fuel control unit with manual override, compressor wash ring, accessory gearbox chip detector, P3 filter drain, and oil filler neck with check valve. PT6A-45 Similar to PT6A-41 except for increased ratio reduction gearbox and higher ratings. PT6A-45A Similar to PT6A-45 except for increased takeoff rating and increased inter-turbine temperature limits. PT6A-45B Similar to PT6A-45A except for increased augmentation fluid flow for takeoff rating to a higher air inlet temperature. PT6A-45R Similar to PT6A-45B except for provision for automatic power increase from alternate takeoff power to takeoff power. PT6A-50 Similar to PT6A-45A except for new reduction gearbox. PT6A-112 Similar to PT6A-27 except incorporates PT6A-41 fuel system concepts and PT6A-135 reduction gearbox. PT6A-114 Similar to PT6A-135 with a single port exhaust and PT6A-41 fuel system concepts and PT6A- 135 reduction gearbox. PT6A-114A Throttle push version of -114 incorporating the -135A compressor, and a new strengthened propeller shaft. PT6A-135 Similar to PT6A-36 except for new reduction gearbox and higher cruise rating. PT6A-135A Similar to PT6A-135 except for increased thermodynamic capability compressor. PT6A-110 Similar to PT6A-11 except for incorporation of PT6A-135 reduction gearbox. PT6A-65B Similar to PT6A-45 except for additional axial compressor stage and increased diameter gas producer turbine wheel. PT6A-65R Identical to PT6A-65B except for reserve takeoff rating. TCDS E4EA PAGE 22 NOTE 13. (Cont'd) Model Characteristics PT6A-65AR Uprated maximum continuous power PT6A-65R. PT6A-65AG Similar to PT6A-65, intended for Agricultural Aviation. Ratings similar to the 65AR without automatic reserve power. PT6A-60 Uprated PT6A-42, featuring new first stage compressor gas producer turbine from PT6A-65 and gearbox from PT6A-45. PT6A-60A Uprated altitude performance PT6A-60. PT6A-60AG Similar to PT6A-60A, but with derated max continuous power, and intended for agricultural aviation. PT6A-61 Similar to PT6A-60 except for PT6A-42 gearbox. PT6A-61A Updated altitude performance PT6A-61. PT6A-116 Similar to PT6A-135 except for reduced takeoff and maximum continuous power and torque limit with PT6A-121 externals. PT6A-121 Similar to PT6A-21 except for a PT6A-135 reduction gearbox and a PT6A-112 power turbine. PT6B-35F Combines the aerodynamic components of the PT6A-135, the mechanical layout of the PT6A-34 and the PT6T-3 generator and exhaust case. Intended for remote drive propeller applications. PT6D-114A Based on the PT6A-114A with the main difference being the deletion of the second stage reduction gearing and output shaft. Intended for integration with a combining gearbox incorporated power turbine governors and a propeller output shaft. PT6A-52 Similar to the PT6A-61 with the PT6A-60A thermal rating. NOTE 14. Certain engine parts are life limited. These limits are listed in P&WC Engine Service Bulletin Nos. 1002, 1302, 1402, 1602,, 3002, 4002, 12002, 12102, 13002, and 13202 as revised. Permissible overhaul and inspection intervals are listed in PWC Engine Service Bulletin Nos. 1003, 1303, 1403, 1603, 1703, 1803, 3003, 3303, 4003, 12003, 12103, 13003, 13203, and 13303 as revised. NOTE 15. Fuel anti-icing additives conforming to specifications 3GP526A PFA 55MB, MIL-I-27686E may be used, at a concentration not exceeding 0.15% by volume. NOTE 16. For PT6A-34, PT6A-34B, PT6A-36, PT6A-45, PT6A-45A and PT6A-45B power may be restored in hot day conditions by means of water or water/methanol injection when accomplished in accordance with the requirements of the PWC Installation Manual. NOTE 17. For PT6A-50 C.G. location (dry weight) is 27.69 in. behind forward mounting ring, 0.27 in. below horizontal centerline and 0.15 in. left of vertical centerline. NOTE 18. Augmentation fluid, when used, must meet the requirements of PWC Specification CPW No. 328. NOTE 19. This Type Certificate Data Sheet reflects the certification basis and approval for those serial numbered model PT6A, PT6B and PT6D series engines listed under "Certification Basis". Two Type Certificates have been issued for administrative purposes: E4EA under FAR 21.29 for engines produced in Canada and E2NE under FAR 21.21 for engines produced in the United States. The type design for each model engine, regardless of where produced, is identical. The information on this Type Certificate Data Sheet applies to all Pratt & Whitney model PT6A, PT6B and PT6D series engines, including: (A) Those serial numbered engines listed on and certificated under FAA Type Certificate E2NE, originally issued to Pratt & Whitney Aircraft Division of United Technologies Corporation, East Hartford, Connecticut, U.S.A. and reissued to Pratt & Whitney of Canada Ltd. (Formerly United Aircraft of Canada, LTd.), Longueuil, Quebec, Canada. (B) Those serial numbered engines listed above under "Certification Basis," certificated under this Type Certificate, E4EA, issued to Pratt & Whitney Canada Corp, Longueuil, Quebec, Canada. NOTE 20. Service Bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is Transport Canada approved, are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only. ----END---- Page No. 1 2 Rev. No. 1 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION P9NE Revision 1 Hartzell HC-B3M July 24, 1985 TYPE CERTIFICATE DATA SHEET NO. P9NE Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P9NE) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and aplicable portions of the Federal Aviation Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Type Certificate Holder Hartzell Propeller Inc. Piqua Ohio 45356 Type Constant speed; hydraulic (see NOTES 3 and 4) Engine shaft Special flange 4¼" bolt circle with eight 9/19" bolts Hub material Alloy steel Blade material See below Number of blades Three Hubs eligible HC-B3MN-3 Maximum Diameter Approx. Max. Weight Complete Blades Eligible Continuous Takeoff Limits (For reference only) Blade (See Note 2) HP RPM HP RPM (See Note 2) (See Notes 3 & 7) Construction M10083 600 2200 600 2200 100" 134 lb. Aramid Composite Certification basis FAR Part 35 effective October 14, 1980, with amendments 1 through 5. Type Certificate No. P9NE issued August 29, 1984. Date of application for Type Certificate February 13, 1984 Production basis Production Certificate No. 10 NOTE 1. Hub Model Designation HC - B 3 M N - 3 A L Denotes left-hand rotation Denotes minor change not affecting eligibility Denotes specific design features (see NOTE 4) N denotes special flange 4-1/4" bolt circle with eight 9/16" bolts and two dowel bushings Hartzell blade shank size Number of blades Identifies basic design Hartzell controllable P9NE 2 NOTE 2. Blade Model Designation L M 100 83 8 B or K denotes deicing boots Basic model or template Basic diameter in inches Denotes needle bearing installation in blade shank Denotes left hand blade NOTE 3. Pitch Control. Eligible with the following governors: Woodward Model x210xxx or x210 x-xxx Maximum Output Pressure 500 PSI NOTE 4. (1) Featherng. The -3 model incorporates feathering and unfeathering features. (2) Reversing. The -3 model is eligible for installation as reversing propellers with appropriate reversing controls. NOTE 5. Left-Hand Models. The left-hand version of an approved propeller model is approved at the same rating and diameter as listed for right-hand model. (See NOTES 1 and 2.) NOTE 6. Interchangeable Blades. Not applicable. NOTE 7. Accessories. (a) Propeller Spinner (1) Approved with Hartzell spinners (weight of spinners extra) (b) Propeller Deicing (1) Eligible with Goodrich 77-xxx or 65-xxx deicing kit when installed in accordance with manufacturer's instructions. NOTE 8. Shank Fairings. Not applicable. NOTE 9. Special Limits. Not applicable. NOTE 10. Special Notes. Propeller installation must be approved as part of the aircraft Type Certificate and demonstrate compliance with the applicable aircraft airworthiness requirements. NOTE 11. Retirement Time. There is no longer a mandatory retirement time for blade part number M10083 when installed on the Cessna model 208 airplane. ....END.... Page No. 1 2 3 Rev. No. 3 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION P60GL Revision 3 McCAULEY 3GFR34C(7--) May 30, 2006 TYPE CERTIFICATE DATA SHEET NO. P60GL Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P60GL) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with the pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Type Certificate Holder McCauley Accessory Division Cessna Aircraft Company 7751 East Pawnee Wichita, KS 67207 Type Constant speed, full feathering and reversing; hydraulic (see Note 4). Engine Shaft Special flange with 4.25" bolt circle [(8)-9/16" studs and (2)-1/2" dowels in engine flange]. Hub Material Aluminum Alloy Blade Material Aluminum Alloy No. of Blades Three Hubs Eligible 3GFR34C701, 3GFR34C702, 3GFR34C703, 3GFR34C704 Blades Eligible Maximum Continuous Take-Off Diameter Limits Approx. Max. Wt. Complete (See NOTE 2) HP RPM HP RPM (See NOTE 2) (Max. Dia.) Hub Model 3GFR34C701 93K[X]-0 to 93K[X]-5 565 2200 565 2200 93" - 88" (-0 to -5) 120.0 Lbs. Hub Model 3GFR34C702 100L[X]-0 to 100L[X]-5 850 2000 850 2000 100" - 95" (-0 to -5) 122.0 Lbs. Hub Model 3GFR34C703 106G[X]-0 to 106G[X]-6 900 2000 900 2000 106" - 100" (-0 to -6) 117.0 Lbs. Hub Model 3GFR34C704 93K[X]-0 to 93K[X]-5 850 2200 850 2200 93" - 88" (-0 to -5) 117.0 Lbs. P60GL Page 2 of 3 Certification Basis Type Certificate No. P60GL issued January 30, 1981, under Delegation Option Authorization Provisions of Part 21, Subpart J, of the Federal Aviation Regulations. Date of Application for Type Certificate: November 11, 1980. Models 3GFR34C701, 3GFR34C702, 3GFR34C703, 3GFR34C704: Federal Aviation Regulations Part 35 including Amendments 35-1 through 35-5 (October 14, 1980) thereto. Production Basis Production Certificate No. 3 NOTE 1. Hub Model Designation. Basic Model Designation X 3 G F R 34 C 701 - [X][X][X] Letters denoting changes that may affect eligibility or interchangeability. Numerals defining specific design and major change affecting eligibility or interchangeability of parts. Type of propeller - C, constant speed. McCauley blade shank size. When present, indicates reverse pitch capability. Type of propeller - F, full-feathering. G denotes special flange - 4 1/4" bolt circle with eight 9/16" studs and two 1/2" dowels. Number of blades. Indicates dowel location with respect to centerline of No. 1 blade socket, viewing hub from flange mounting face. Blank - 0° and 180° clockwise. P60GL Page 3 of 3 NOTE 2. Blade Model Designation. Basic Model Designation X - X 106 G[X] - 0 Reduction in diameter from basic, in inches. Characteristics of blade design (planform, etc.). Suffix [X] indicates blade butt staking dimensions for the actuating pin. Blade design diameter in inches. Letter designating direction of rotation; no letter (blank) indicates clockwise (viewed from downstream); L indicates counter-clockwise. Letter designating minor change not affecting eligibility or interchangeability. NOTE 3. Not applicable. NOTE 4. Feathering. Feathering and unfeathering capability when installed with appropriate feather/unfeathering controls. Reversing. For installation as reversing propeller with appropriate reversing controls. NOTE 5. Left Hand Models. The left hand version of an approved model is eligible at the same rating and diameter limitations as listed for the right hand model. NOTE 6. Not applicable. NOTE 7. Accessories. (a) Propeller Deicing (1) Model 93KB blades with Goodrich deicer per Goodrich Report 59-728 and installed per McCauley drawing E-5128. (2) Model 100LA blades with Safeway deicer B-40245-50 per McCauley Report MC-2611 and installed per McCauley drawing E-5423. (3) Model 106GA blades with McCauley deicer B-40245-54 per McCauley Report MC-2611 and installed per McCauley drawing E-6368. (b) Propeller Spinner (1) Model 3GFR34C701/93KB and 3GFR34C704/93KB with spinner, reference McCauley drawing E-5146. (2) Model 3GFR34C702/100LA with spinner; reference McCauley drawing E-5424. (3) Model 3GFR34C703/106GA with spinner; reference McCauley drawing E-6383. NOTE 8. Not applicable. NOTE 9. Not applicable. NOTE 10. Special Notes. Aircraft installation must be approved as part of the aircraft type certificate upon compliance with the applicable aircraft airworthiness requirements. ... END ... Page No. 1 2 3 Rev. No. 29 29 29 Reformatted 6/94. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-252 Revision 29 CONTINENTAL C90-8F, -8FJ C90-12F, -12FH, -12FJ, -12FP C90-14F, -14FH, -14FJ, -16F 0-200-A, 0-200-B, 0-200-C September 15, 1982 TYPE CERTIFICATE DATA SHEET NO. E-252 Engine of models described herein conforming with this data sheet (which is a part of type certificate No. 252) and other approved data on file with the Federal Aviation Agency, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Civil Air Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Type Certificate Holder Teledyne Continental Motors P.O. Box 90 Mobile, Alabama 36601 Model C90-8F C90-12F, -14F, -16F 0-200-A, -B, -C Type 4HOA - - - - - - Rating, standard atmosphere Max. continuous hp., r.p.m., 90-2475 - - - 100-2750 at sea level pressure altitude Takeoff hp., 5 min., r.p.m., full 95-2625 - - - 100-2750 throttle, at sea level pressure alt Fuel (min. grade aviation gasoline) 80/87 - - - - - - Lubricating oil, ambient air temp. Oil Grade Below 40° F. SAE 20 - - - - - - Above 40° F. SAE 40 - - - - - - Bore and stroke, in. 4.062 x 3.875 - - - - - - Displacement, cu. in. 201 - - - - - - Compression ratio 7:1 - - - - - - Weight (dry), lb. 184 188 190 C.G. location (with accessories) Fwd. or rear face of mounting lugs, in. 6.2 4.6 - - - Below crankshaft center line, in. 1.5 1.3 1.2 Propeller shaft, SAE No. 1 Flange - - - - - - Carburetion (see NOTE 4 for injectors) Marvel-Schebler MA-3SPA (CMC P/N 627367, 629175, 637101 or 637835) - - - Marvel-Schebler MA-3SPA Bendix-Stromberg NA-S3A1 (CMC P/N 530625, 530726, 531126, 530846, 531157) - - - (TCM P/N 627143, 640416 or 633028) Ignition 2 Bendix-Scintilla S4RN-21 or -1227; or Slick -Electro 443 or 4003 magnetos or 1 ea. Bendix-Scintilla S4RN-200 and 204 2 Bendix-Scintilla S4LN- 21 or -1227 or 1 ea. S4LN- 200 and -204; Slick-Electro 447, 4001 or 4201 magnetos - - - E252 Page 2 Model C90-8F C90-12F, -14F, -16F 00-200-A, -B, -C Timing, °BTC 26 Top, 28 Bottom - - - 24 Top, 24 Bottom Spark plugs See NOTE 6 - - - - - - Oil sump capacity, qt. 5 or 6 - - - - - - NOTES 1 through 6 1, 2, 3, 4, 6 1, 2, 3, 4, 6 "- - -" indicates "same as preceding model" Certification Basis Part 13 of the Civil Air Regulations. Type Certificate No. 252 Production Basis Production Certificate No. 7 Production Certificate No. 508 (All models except C90-16F) NOTE 1. Maximum permissible temperatures: C90 Series 0-200 Series Cylinder head 525° F. 525° F. Cylinder barrel 275° F. 290° F. Oil inlet 225° F. 225° F. (Straight mineral) 240° F. (Detergent meeting MHS-24, See NOTE 6) NOTE 2. Carburetor fuel inlet pressure lmits: Minimum Maximum MA-3SPA, TCM P/N 627143, 633028, 637101, 637835, 640416 5 In. Fuel Head 6 PSIG MA-3SPA, TCM P/N 627367, 629175 6 In. Fuel Head 6 PSIG MA-3SPA, TCM P/N 530625, 530726, 530846, 531126, 531157 6 In. Fuel Head 6 PSIG Carburetor Air Intake Assembly, TCM A40793, used with MA-3SPA, Marvel-Schebler Carb. Carburetor Air Intake Assembly, TCM A40522, used with NA-53A1, Stromberg Carburetor. C90 Series 0-200 Series Oil pressure limits: 30 to 40 p.s.i.g. 30 to 60 p.s.i.g. Minimum idling with hot oil 10 p.s.i.g. NOTE 3. The following accessory drive or mounting provisions are available. Direction Speed Ratio Max. Torque (in.-lb.) Maximum Overhang Accessory of Rotation* to Crankshaft Continuous Static Moment (in.-lb.) Tachometer C 0.500:1 7 50 25 Generator CC 2.035:1 60 600 100 Starter C 35.7:1 ** Vacuum Pump CC 1.0:1 100 800 25 *** Fuel Pump (diaphragm) 0.500:1 Accessories previously listed in NOTE 3 are satisfactory for continued use with C90 Series engines. * C - Clockwise viewing drive pad; CC - Counterclockwise. ** C90-16F and 0-200 Series engines only. *** CMC Eq. 5809 incorporating CMC P/N 40585 pump approved as part of type design of the 0-200 Series engine. AC fuel pump, CMC P/N 631391, available as optional equipment on C90-16F. NOTE 4. The C90-8F is identical to the C90-12F model except that the accessory section does not incorporate porvisions for generator and starter drives. The C90-14 models incorporate Lord type engine mounts which are not interchangeable with C90-12 models due to different machining of the engine mounting lugs on the engine crankcase. The C90-16F is similar to the C90-12F except that vacuum pump drive provisions have been added. The Model 0-200-B is similar to the 0-200A except for special crankshaft and crankcase providing for thrust application toward the engine only. E-252 Page 3 The Model 0-200-C is similar to the 0-200-A except for incorporation of provisions to supply oil pressure to a controllable pitch propeller through the crankshaft from an external boss on the crankcase. Those C90 Series models listed in the heading of this data sheet, suffixed by letters H, J and P, differ from the basic model designation as follows: "H" denotes a special SAE No. 1 flange crankshaft and special crankcase for the installation of a hydraulically operated controllable pitch propeller requiring oil supply through the crankshaft. "J" denotes incorporation of Model B-46 Ex-Cell-O fuel injector, P/N 530499, or American Bosch Model PSC-4A-95A2, P/N 534505, at a weight increase of 4 lb. over the corresponding carburetor equipped engine. "P" denotes pusher installation incorporating special crankshaft and thrust bearing. Oil sump gauge rods will be marked as per installer's requirements. NOTE 5. Bendix-Stromberg NAS-3A1 carburetor, P/N 530726, eligible only on Piper PA-11 airplanes equipped with Piper mufflers. NOTE 6. Detergent oil meeting Continental Specification MHS-24 reuqired when using 240° F oil inlet limits except during break-in period. Follow manufacturer's instructions for break-in or when changing oil types. marking or placards prescribing use of Continental Specification MHS-24 oil only shall be installed on or near the oil filler on installations using 240 ° F oil inlet temperatures. NOTE 7. The following spark plugs are approved for use on engine models as indicated: C90-8F, -12F, -14F, -16F AC HSR83IR, SR83IR, HSR83P, SR83P, A88, HS88, HSR88, S88, S88D, HSR88, SR88, SR88D, HSR93, SR93 Auto Lite 18A1, BR4, BR4S, BR4SB, SH15, H15, SH15R, SH20A, SH150, SH200A BG RB485S, 706, 706R, 706S, 706SR, 919SR5, RB955S Champion C26, C26S, C27, C27S, RC27S, REM38P, REM38W, RHM38P, RHM38W, REM40E, RHM40E, ED41N, D41N, EM41E, EM41N, HM41E, M41E, M41N, EM42E, M42E Red Seal SA190, SE190, SJ190, SE230, SJ230 0-200-A, -B, -C AC HSR83IR, SR83IR, HSR83P, SR83P, A88, HS88, HSR88, S88, S88D, SR88, SR88D, HSR93, SR93 Auto Lite 18A1, SH15, H15, SH15R, SH20A, SH150, SH200A, PH26 BG RB485S, 706, 706S, 919SR5, RB955S Champion C27, C27S, RC27S, REM38P, REM38W, RHM38P, RHM38W, REM40E, RHM40E, ED41N, D41N, EM41E, EM41N, HM41E, M41E, M41N, EM42E, M42E Red Seal SA190, SE190, SJ190 SE230, SJ230 ....END.... DEPARTME0NT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 2A13 Revision 48 Piper Aircraft, Inc PA-28-140 PA-28-151 PA-28-150 PA-28-161 PA-28-160 PA-28-181 PA-28-180 PA-28R-201 PA-28-235 PA-28R-201T PA-28S-160 PA-28-236 PA-28S-180 PA-28RT-201 PA-28R-180 PA-28RT-201T PA-28R-200 PA-28-201T August 7, 2006 TYPE CERTIFICATE DATA SHEET NO. 2A13 This data sheet, which is a part of Type Certificate 2A13, 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 Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida 32960 Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC 2A13 to Piper Aircraft, Inc on August 7, 2006. I - Model PA-28-160 (Cherokee), 4 PCLM (Normal Category), Approved October 31, 1960, for S/N 28-03; 28-1 through 28-4377; and 28-1760A. Engine Lycoming O-320-B2B or O-320-D2A with carburetor setting 10-3678-32 Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (160 hp) Propeller and Propeller Limits Sensenich M74DM or 74DM6 on S/N 28-1 through 28-1760, and 28-1760A. Sensenich M74DMS or 74D6S5 on S/N 28-1761 through 28-4377. Static r.p.m. at maximum permission throttle setting not over 2425 r.p.m., not under 2325 r.p.m. No additional tolerance permitted. Diameter: Not over 74", not under 72.5". Propeller Spinner Piper P/N 14422-00 on S/N 28-1 through 28-1760, and 28-1760A. Piper P/N 63760-04 or P/N 65805-00 on S/N 28-1761 through 28-4377. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Revision No. 48 48 48 48 48 48 48 48 48 48 48 48 48 48 48 48 48 48 Page No. 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 Revision No. 48 48 48 48 48 48 48 48 48 48 48 48 48 48 48 48 48 48 Page No. 37 38 39 40 41 42 43 Revision No. 48 48 48 48 48 48 48 2A13 Page 2 of 43 Center of Gravity Range (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+89.2) to (+95.9) at 2200 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 2200 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 125 lb. at (+142.8) on S/N 28-1 through 28-1760, and 28-1760A. See NOTE 8. 200 lb. at (+142.8) on S/N 28-1761 through 28-4377. Fuel Capacity 50 gallons at (+95) ( 2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5), 6 quarts usable See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (± 2°) Up 0° Down 40° Ailerons (± 2°) Up 30° Down 15° Rudder (± 2°) Left 27° Right 27° Stabilator (± 2°) Up 18° Down 2° Stabilator Tab (± 1°) Up 3° Down 12° Nose Wheel Travel (±1°) Left 30° Right 30° (Effective on S/N 28-1 through 28-3377, and 28-1760A) (�1�) Left 22° Right 22° (Effective S/N 28-3378 through 28-4377) Manufacturer's Serial Nos. 28-03; 28-1 through 28-4377; and 28-1760A. II - Model PA-28-150 (Cherokee), 4 PCLM (Normal Category), Approved June 2, 1961, for S/N 28-03; 28-1 through 28-4377; and 28-1760A. Engine Lycoming O-320-A2B or O-320-E2A with carburetor setting 10-3678-32 Fuel 80/87 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (150 hp) Propeller and Propeller Limits Sensenich M74DM or 74DM6 on S/N 28-1 through 28-1760, and 28-1760A. Sensenich M74DMS or 74DM6S5 on S/N 28-1761 through 28-4377. Static r.p.m. at maximum permissible throttle setting not over 2375 r.p.m., not under 2275 r.p.m. No additional tolerance permitted. Diameter: Not over 74", not under 72.5". Propeller Spinner Piper P/N 14422-00 on S/N 28-1 through 28-1760, and 28-1760A. Piper P/N 63760-04 or 65805-00 on S/N 28-1761 through 28-4377. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Page 3 of 43 2A13 Center of Gravity Range (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+88.4) to (+95.9) at 2150 lb. Straight line variation between points given. Empty Wt. C. G. Range None Maximum Weight 2150 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 125 lb. at (+142.8) on S/N 28-1 through 28-1760, and 28-1760A. See NOTE 8. 200 lb. at (+142.8) on S/N 28-1761 through 28-4377. Fuel Capacity 50 gallons at (+95) ( 2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (± 2°) Up 0° Down 40° Ailerons (± 2°) Up 30° Down 15° Rudder (± 2°) Left 27° Right 27° Stabilator (± 1°) Up 18° Down 2° Stabilator Tab (± 1°) Up 3° Down 12° Nose Wheel Travel (± 2�) Left 30° Right 30° (Effective on S/N 28-03; 28-1 through 28-3377; and 28-1760A) (� 2�) Left 22° Right 22° (Effective on S/N 28-3378 through 28-4377) Manufacturer's Serial Nos. 28-03; 28-1 through 28-4377; and 28-1760A. III - Model PA-28-180 (Cherokee), 4 PCLM (Normal Category), Approved August 3, 1962; 2 PCLM (Utility Category), Approved December 6, 1966, for S/N 28-03; 28-671 through 28-5859; and 28-7105001 through 28-7205318. Engine Lycoming O-360-A3A or 0-360-A4A with carburetor setting 10-3878 or 10-4164-1 Fuel 91/96 minimum grade aviation gasoline Engine Limits S/N 28-671 through 28-1760, and 28-1760A (except S/N 28-1571 and S/N 28-1573) (See NOTE 4): Maximum permissible takeoff, 2475 r.p.m. For all other operations, 2700 r.p.m. (180 hp) S/N 28-1571; 28-1573; 28-1761 through 28-5859; and 28-7105001 through 28-7205318: For all operations, 2700 r.p.m. (180 hp) Propeller and Propeller Limits Sensenich M76EMM or 76EM8 on S/N 28-671 through 28-1760, and 28-1760A (except S/N 28-1571 and S/N 28-1573). Sensenich M76EMMS or 76EM8S5 on S/N 28-1571, 28-1573; 28-1761 through 28-5859; and 28-7105001 through 28-7205318. Static r.p.m. at maximum permissible throttle setting not over 2450 r.p.m., not under 2275 r.p.m. No additional tolerance permitted. Diameter: Not over or under 76". See NOTE 10. 2A13 Page 4 of 43 Propeller Spinner Piper P/N 14422-00 on S/N 28-671 through 28-1760, and 28-1760A. Piper P/N 63760-04 or 65805-00 on S/N 28-1761 through 28-5859; and 28-7105001 through 28-7205318. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity Range Utility Category (See NOTE 9) (+84.0) to (+86.5) at 1650 lb. or less (+85.8) to (+86.5) at 1950 lb. Normal Category (See NOTE 15) (S/N 28-671 through 28-5859) (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+89.2) to (+95 9) at 2200 lb. (+92.1) to (+94.5) at 2400 lb. Normal Category (S/N 28-7105001 through 28-7205318) (+84.0) to (+95.9) at 1650 lb. or less (+87.0) to (+95.9) at 2150 lb. (+87.8) to (+95.9) at 2200 lb. (+91.0) to (+94.5) at 2400 lb. Straight Line Variation Between Points Given 2400 2200 2000 1800 1600 84 86 88 90 92 94 96 Normal Only Aft Limit Normal Aft Limit Utility Fuselage Station - Inches Normal & Utility 2400 2200 2000 1800 1600 84 86 88 90 92 94 96 Aft Limit Normal Fuselage Station - Inches (S/N 28-7105001 thru 28-7205318) Normal & Utility Aft Limit Utility Normal Only (S/N 28-671 thru 28-5859) Lbs. Lbs. Empty Weight C. G. Range None Page 5 of 43 2A13 Maximum Weight Normal Category: 2400 lb. Utility Category: 1950 lb. No. of Seats Normal Category: 4 (2 at +85.5, 2 at +118.1) Utility Category: 2 (2 at +85.5) Maximum Baggage Eligible Normal Category Only: 125 lb. at (+142.8) on S/N 28-671 through 28-1760, and 28-1760A. See NOTE 8. 200 lb. at (+142.8) on S/N 28-1761 through 28-5859, and 28-7105001 through 28-7205318. Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (± 2°) Up 0° Down 40° Ailerons (± 2°) Up 30° Down 15° Rudder (± 2°) Left 27° Right 27° Stabilator (± 1°) Up 18° Down 2° Stabilator Tab (± 1°) Up 3° Down 12° Nose Wheel Travel (± 2°) Left 30° Right 30° (Effective on S/N 28-671 through 28-3377) (� 2�) Left 22° Right 22° (Effective on S/N 28-3378 through 28-5859, and 28-7105001 through 28-7205318) Manufacturer's Serial Nos. 28-03; 28-671 through 28-5859; and 28-7105001 through 28-7205318. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers: 28-4704 28-4745 28-4754 28-4763 28-4776 28-4791 28-4795 28-4826 28-4834 28-4859 28-4875 28-4879 28-4891 28-4907 28-4919 28-4922 28-4935 28-4945 28-4946 28-4947 28-4955 28-4959 28-4961 27-4964 28-4967 28-4968 28-4971 28-4975 28-4977 28-4985 28-4995 28-4999 28-5004 28-5007 28-5015 28-5017 28-5018 28-5019 28-5020 28-5023 28-5026 28-5027 28-5028 28-5031 28-5039 28-5041 28-5046 28-5051 28-5053 28-5057 28-5060 28-5061 28-5062 28-5063 28-5064 28-5066 through 28-5859, and 28-7105001 through 28-7205318 under the delegation option provisions of FAR 21. See NOTE 17 and 20. IV - Model PA-28S-160 (Cherokee), 4 PCSM (Normal Category), Approved February 25, 1963, for S/N 28-1 through 28-1760; and S/N 28-1760A. Engine Lycoming O-320-D2A with carburetor setting 10-3678-32 (See NOTE 18) Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (160 hp) Propeller and Propeller Limits McCauley 1A175-GM Static r.p.m. at maximum permissible throttle setting not over 2360 r.p.m., not under 2260 r.p.m. No additional tolerance permitted. Diameter: Not over 79", not under 78". 2A13 Page 6 of 43 Propeller Spinner Piper P/N 14422-00 spinner required. Airspeed Limits Never exceed 153 mph (133 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity (+85.1) to (+93.5) at 1850 lb. or less (+87.0) to (+93.5) at 2100 lb. (+87.9) to (+93.5) at 2140 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 2140 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 125 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 18° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Manufacturer's Serial Nos. 28-03; 28-1 through 28-1760; and 28-1760A. V - Model PA-28S-180 (Cherokee), 4 PCSM (Normal Category), Approved May 10, 1963, for S/N 28-671 through 28-5859, and 28-7105001 through 28-7105234. Engine Lycoming O-360-A3A or 0-360-A4A with carburetor setting 10-4164-1 See NOTE 19. Fuel 100/130 minimum grade aviation gasoline Engine Limits S/N 28-671 through 28-1760, and 28-1760A (except S/N 28-1571 and S/N 28-1573): Maximum permissible takeoff, 2350 r.p.m. For all other operations, 2700 r.p.m. (180 hp) See NOTE 4. S/N 28-1571; 28-1573; 28-1761 through 28-5859; and 28-7105001 through 28-7105234: For all operations, 2700 r.p.m. (180 hp) Propeller and Propeller Limits McCauley 1A200-FA8248 on S/N 28-671 to 28-1760, and 28-1760A. McCauley 1A200-DFA8248 on S/N 28-1761 through 28-5859, and 28-7105001 through 28-7105234. Static r.p.m. at maximum permissible throttle setting not over 2190 r.p.m., not under 2140 r.p.m. No additional tolerance permitted. Diameter: Not over 82", not under 81". Page 7 of 43 2A13 Propeller Spinner Spinner required. Piper P/N 14422-00 on S/N 28-671 through 28-1760, and 28-1760A. Piper P/N 63760-04 or 65805-00 on S/N 28-1761 through 28-5859, and 28-7105001 through 28-7105234. Airspeed Limits Never exceed 153 mph (133 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity (+85.1) to (+92.5) at 1850 lb. or less (+87.0) to (+92.5) at 2100 lb. (+89.8) to (+92.5) at 2222 lb. Straight line variation between points given. Empty Weight C. G. Range None Maximum Weight 2222 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Maximum Baggage 125 lb. at (+142.8) Fuel Capacity 50 gallons at (+95) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (±2°) Up 0° Down 40° Ailerons (±2°) Up 30° Down 15° Rudder (±2°) Left 27° Right 27° Stabilator (±1°) Up 18° Down 2° Stabilator Tab (±1°) Up 3° Down 12° Manufacturer's Serial Nos. 28-671 through 28-5859, and 28-7105001 through 28-7105234. See NOTE 3. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers: 28-4704 28-4745 28-4754 28-4763 28-4776 28-4791 28-4795 28-4826 28-4834 28-4859 28-4875 28-4879 28-4891 28-4907 28-4919 28-4922 28-4935 28-4945 28-4946 28-4947 28-4955 28-4959 28-4961 27-4964 28-4967 28-4968 28-4971 28-4975 28-4977 28-4985 28-4995 28-4999 28-5004 28-5007 28-5015 28-5017 28-50