TCDS 3A20

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 82 32 70 70 65 70 36 70 70 42 70 36 36 70 36 70 70 57 70 47 Page No. 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 Rev. No. 70 57 70 70 70 62 70 70 70 70 66 77 82 78 66 82 73 73 81 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 3A20 Revision 82 Textron Aviation 65 (L-23F) 65-A90-1 (JU-21A) A65 (U-21A) A-65-8200 (RU-21A) 65-80 (RU-21D) 65-A80 (U-21G) 65-A80-8800 (RU-21H) 65-B80 65-A90-2 (RU-21B) 65-88 65-A90-3 (RU-21C) 65-90 65-A90-4 (RU-21E) 65-A90 (RU-21H) 70 C90 B90 C90A E90 C90GT H90 (T-44A) C90GTi September 5, 2019 TYPE CERTIFICATE DATA SHEET NO. 3A20 This data sheet which is part of Type Certificate No. 3A20 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, KS 67215 Type Certificate Holder Record: Beech Aircraft Corporation transferred to Raytheon Aircraft Company on April 15, 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12, 2013 Beechcraft Corporation transferred to Textron Aviation Inc. on October 12, 2016. 3A20 2 Rev. 82 I. Model 65, Queen Air (Military L-23F), 7 or 9 PCLM (Normal Category), Approved February 4, 1959 Engines 2 Lycoming IGSO-480-A1A6 or IGSO-480-A1B6 2 Lycoming IGSO-480-A1E6 (See NOTE 6 (a)) Fuel 100/130 min. grade aviation gasoline Engine Limits Straight line manifold pressure variation with altitude shown HP RPM MP Alt Takeoff 340 3400 48.0 S.L. Takeoff 340 3400 44.0 11,000 Takeoff 340 3400 43.5 11,000 (See NOTE 6 (a)) Max continuous 320 3200 45.0 S.L. Max continuous 320 3200 41.5 11,000 Propeller and Propeller Limits 2 Hartzell, full-feathering, three-bladed (a) HC-93Z20-2C1 or HC-B3Z20-2A hub with 10151-8R or 10151B-8R aluminum alloy blades and 836 spinner. (see NOTE 6(b)). Pitch settings at 30 in. sta.: low 16, high 87 Diameter: not over 93 in., not under 90 in. (b) Woodward hydraulic governor 210190 or 210635. (see NOTE 6(b)) Airspeed Limits Never exceed 270 mph (234 knots) Maximum structural cruising 205 mph (178 knots) Maneuvering 195 mph (169 knots) Flaps extended 150 mph (130 knots) Maximum landing gear operating speed: Extension 180 mph (156 knots) Retraction 150 mph (130 knots) Maximum landing gear extended speed 180 mph (156 knots) C.G. Range (Landing (+149.9) to (+158.4) at 7700 lb. Gear Extended) (+147.6) to (+158.4) at 6720 lb. or less Straight line variation between points given Moment change due to retracting landing gear -2500 in. -lb. 6000 6200 6400 6600 6800 7000 7200 7400 7600 7800 8000 146 148 150 152 154 156 158 160 REAR LIMIT FWD LIMIT IN. LB. Empty Wt. C.G. Range None Maximum Weight Takeoff - 7700 lbs. Landing - 7350 lbs. or 7700 lbs. S/N LC-203 and up, and LC-168 thru LC-202 when modified per Beech Kit dwg. 65-4012. No. of Seats Maximum 9 (2 crew at +129). See loading instructions for passenger loading. 3A20 3 Rev. 82 I. Model 65 (cont’d) Maximum Baggage 350 lbs. (300 lbs. at +267, 50 lbs. at +288) (aft compartment). (Structural Limit) 350 lbs. (+70) (optional nose compartment). Fuel Capacity Tank Cap. Gal Usable Gal Arm L & R Main 44 ea. 44 ea. +174 L & R Aux 47 ea. 45 ea. +162 or L & R Aux 72 ea. 71 ea. +165 or L & R Aux 89 ea. 88 ea. +163 See NOTE 1 for data on unusable fuel. Oil Capacity Left nacelle tank, 16 qts (+138), right nacelle tank, 16 qts. (+138). See NOTE 1 for data on unusable (undrainable) oil. Control Surface Movements Wing Flaps Maximum 31 ½  Aileron tabs Up 7 ½  Down 7 ½  (LH only) Aileron tab anti-servo Up 14 Down 8 Aileron Up 20 Down 20 Elevator tab Up 10 Down 21 Elevator tab anti-sevo Up 12 Down 8 Elevator Up 25 Down 15 Rudder tab Right 30 Left 30 Rudder Right 25 Left 25 Rudder tab servo Right 1 Left 1 Serial No’s. Eligible L-1, L-2, L-6, LF-7 and up, and LC-1 thru LC-239. (L-3, L-4, L-5 eligible when modified per Beech dwg. 50-002017). Prior to civil certification, LF-23F airplanes which have been operated by the military must be modified per BEECH dwg. 50-002016. Type Certificate issued and Delegation Option Manufacturer No. DOA-230339-CE authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. II. Model 65-80, 7 or 9 PCLM (Normal Category), Approved February 20, 1962 Engines 2 Lycoming IGSO-540-A1A Fuel 100/130 min. grade aviation gasoline Engine Limits (Straight line manifold pressure variation with altitude shown) HP RPM MP Alt Takeoff 380 3400 47.0 S.L. Takeoff 380 3400 43.5 10,500 Max. continuous 360 3200 45.0 S.L. Max. continuous 360 3200 41.7 10,500 Propeller and Propeller Limits 2 Hartzell, full-feathering, three-bladed (a) HC-B3Z30-2 hub with 10151-8 or 10151B-8 or 10151-8R or 10151B-8R aluminum alloy blades and 836 spinner. Pitch settings at 30 in sta: Low 18 1/4,  1/4, high 87,  1/2 Diameter: not over 93 in., not under 90 in. (b) Woodward hydraulic governor A210390 Airspeed Limits Never exceed 270 mph (234 knots) Maximum structural cruising 205 mph (178 knots) Maneuvering 195 mph (169 knots) Flaps extended 150 mph (130 knots) Maximum Landing Gear Operating Speed: Extension 180 mph (156 knots) Retraction 150 mph (130 knots) Maximum Landing Gear Extended Speed: 180 mph (156 knots) 3A20 4 Rev. 82 II. Model 65-80 (cont’d) C.G. Range (Landing (+152.8) to (+158.4) at 8000 lb Gear Extended) (+147.6) to (+158.4) at 7060 lb or less Straight line variation between points given Moment change due to retracting landing gear -2500 in. -lb. 6200 6400 6600 6800 7000 7200 7400 7600 7800 8000 146 148 150 152 154 156 158 160 REAR LIMIT FWD LIMIT IN. LB. 8200 Empty Wt. C.G. Range None Maximum Weight Takeoff - 8000 lb Landing - 7600 lb. or 8000 lb. (See NOTE 8) No. of Seats Maximum 9 (2 crew at +129). See loading instructions for passenger loading. Maximum Baggage 350 lb. (300 lb. at +267, 50 lb. at +288) (Structural Limit) Fuel Capacity Tank Cap Gal Usable Gal Arm L & R Main 44 ea. 44 ea. +174 L & R Aux 47 ea. 45 ea. +162 or L & R Aux 72 ea. 71 ea. +165 See NOTE 1 for data on unusable fuel Oil Capacity Left nacelle tank, 16 qt. (+138), right nacelle tank, 16 qt. (+138) See NOTE 1 for data on unusable (undrainable) oil. Control Surface Movements Wing Flaps Maximum 31 ½  Aileron tabs Up 7 ½  Down 7 ½  (LH only) Aileron tab anti-servo Up 14 Down 8 Aileron Up 20 Down 20 Elevator tab Up 10 Down 21 Elevator tab anti-servo Up 12 Down 8 Elevator Up 25 Down 15 Rudder tab Right 30 Left 30 Rudder Right 24 Left 26 Serial No’s. Eligible LD-1 thru LD-150 (except LD-34 and LD-46) 3A20 5 Rev. 82 III. Model 65-A80, 7 to 11 PCLM (Normal Category), Approved March 26, 1964 Model 65-A80-8800, 7 to 11 PCLM (Normal Category), Approved October 22, 1965 Engine 2 Lycoming IGSO-540-A1A or IGSO-540-A1D Fuel 100/130 min. grade aviation gasoline Engine Limits (Straight line manifold pressure variation with altitude shown) HP RPM MP Alt Takeoff 380 3400 47.0 S.L. Takeoff 380 3400 43.5 10,500 Max. continuous 360 3200 45.0 S.L. Max. continuous 360 3200 41.7 10,500 Propeller and Propeller Limits 2 Hartzell, full-feathering, three-bladed (a) HC-B3Z30-2 hub with 10151-8R or 10151B-8R aluminum alloy blades and spinner. Pitch settings at 30 in. sta.: low 18 1/4,  1/4, high 87,  1/2 Diameter: not over 93 in., not under 90 in. (b) Woodward hydraulic governor A210390; use 210498 with propeller synchronizer Airspeed Limits Never exceed 270 mph (234 knots) Maximum structural cruising 205 mph (178 knots) Maneuvering 195 mph (169 knots) Flaps extended 150 mph (130 knots) Maximum landing gear operating speed: Extension 180 mph (156 knots) Retraction 150 mph (130 knots) Maximum landing gear extended speed: 180 mph (156 knots) C.G. Range (Landing Model 65-A80 Model 65-A80-8800 Gear Extended) (+149.8) to (+158.4) at 8500 lb. (+150.7) to (+160.4) at 8800 lb. (+147.6) to (+158.4) at 7750 lb. or less (+147.6) to (+160.4) at 7750 lb. or less Straight line variation between points given. Straight line variation between points given Moment change due to retracting landing Moment change due to retracting gear -2500 in. -lb. landing gear -2500 in. -lb. 7000 7400 7800 8200 146 148 150 152 154 156 158 160 REAR LIMIT FWD LIMIT INCHES LB. 8600 7400 7800 8200 8600 146 148 150 152 154 156 158 160 REAR LIMIT FWD LIMIT INCHES LB. 9000 Empty Wt. C.G. Range None Maximum Weight Model 65-A80 Model 65-A80-8800 Takeoff 8500 lb. 8800 lb (see NOTE 9) Landing 8500 lb. 8800 lb. No. of Seats Maximum 11 (2 crew at +129). See loading instructions for passenger loading. 3A20 6 Rev. 82 III. Model 65-A80, Model 65-A80-8800 (cont’d) Maximum Baggage 350 lb. (+275, aft compartment, except LD-34 and LD-46) (Structural Limit) 350 lb. (300 lb. at +267, 50 lb. at +288, LD-34 only) (Standard aft compartment) 300 lb. (+267, LD-46 only) (Standard aft compartment) 250 lb. (+309) (Optional aft compartment) (65-A80-8800) (450 lb. max in both compartments) 350 lb. (+70) (Optional nose compartment) Fuel Capacity Tank Cap Gal Usable Gal Arm L & R Main 44 ea. 44 ea. +174 L & R Aux. 47 ea. 45 ea. +162 or L & R Aux. 64 ea. 63 ea. +160 or L & R Aux. 72 ea. 71 ea. +165 or L & R Aux. 89 ea. 88 ea. +163 See NOTE 1 for data on unusable fuel. Oil Capacity Left nacelle tank, 16 qt. (+138), right nacelle tank, 16 qt. (+138) See NOTE 1 for data on unusable (undrainable) oil. Control Surface Movements Wing flaps Maximum 31 ½  Aileron tabs Up 7 ½  Down 7 ½  (LH only) Aileron tab anti-servo Up 14 Down 8 Aileron Up 20 Down 20 Elevator tab Up 10 Down 21 Elevator tab anti-servo Up 12 Down 8 Elevator Up 25 Down 15 Rudder tab Right 30 Left 30 Rudder Right 24 Left 26 Serial No’s. Eligible LD-34, LD-46, LD-151 through LD-269 IV. Model 65-90, 10 PCLM (Normal Category), Approved May 19, 1964 Engines 2 United Aircraft of Canada, Ltd. PT6A-6 (Turboprop) or 2 United Aircraft of Canada, Ltd. or Pratt & Whitney PT6A-20 (Turboprop) See NOTE 11. Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); JET A, JET A-1, and JET B conforming to P&WC S.B. 1244 or ASTM Spec. D1655. See NOTE 5 for emergency fuels. 3A20 7 Rev. 82 IV. Model 65-90 (cont’d) Oil (Engine and Gearbox) UACL PT6 Service Bulletin No. 1 lists approved brand oils. Engine Limits Static Sea Level Ratings PT6A-6 Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Max. Permissible Turbine Inlet Temp. (Deg. C.) Takeoff (5 minutes) 500 62 525 2200* 994 Max. Continuous 500 62 525 2200* 952 Strtg. Trans. (2 seconds) 1038 Max Reverse (1 minute) 300 2100* 750 Static Sea Level Ratings PT6A-20 Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft speed Max. Permissible Turbine Inlet Temp. (Deg. C.) Takeoff (5 minutes) 500 68 527 2200* 750 Max. Continuous 500 68 527 2200* 750 Strtg. Trans. (2 seconds) 1090 Max Reverse ( 1 minute) 300 2100* 750 See NOTE 4 At low altitude and low ambient temperature the engines may produce more power at takeoff than the airplane has been certificated for. Under these conditions, the placarded torquemeter limitations shall not be exceeded. Oil Temperature PT6A-6 Plus 32F to 185F max continuous Maximum 195F not to exceed 5 minutes Minus 40F minimum starting PT6A-20 Plus 50 F to 200 F max. continuous Minus 40F to 200F low idle Maximum 210F not to exceed 5 minutes Minus 40F minimum starting Propeller and Propeller Limits Non Reversing Propeller: (See NOTES 12 & 13) 2 Hartzell HC-B3TN-2/T10173B-8 or HC-B3TN-2(B)/T10173B-8 or HC-B3TN-2M/ T10173NB-8 with three blades each. Diameter: 93.5 in. (nominal) Min. allowable for repair 91.5 in. (No further reduction permitted). Pitch settings at 30 in. sta.: low 19, feathered 87 Reversing Propeller: 2 Hartzell HC-B3TN-3B/T10173E-8 or HC-B3TN-3M/T10173NB-8 with three blades each Diameter: 93-3/8 in. (nominal). Min. allowable for repair 90-3/8 in. (No further reduction permitted) Flight idle stop (See NOTE 10) Secondary flight idle stop (See NOTE 10) Reverse -11 Feather -87 Airspeed Limits Maximum operating speed 240 mph (208 knots) Maneuvering 195 mph (169 knots) Flaps extended 150 mph (130 knots) Maximum landing gear operating speed : Extension 180 mph (156 knots) Retraction 150 mph (130 knots) Maximum landing gear extended speed 180 mph (156 knots) 3A20 8 Rev. 82 IV. Model 65-90 (cont’d) C.G. Range (Landing (+152.2) to (+158.4) at 9300 lb. (See NOTE 7) Gear Extended) (+151.3) to (+158.4) at 9000 lb. (+147.6) to (+158.4) at 7750 lb. or less Straight line variation between points given Moment change due to retracting landing gear -3530 in. -lb. 7500 7700 7900 8100 8300 8500 8700 8900 9100 9300 147 149 151 153 155 157 159 REAR LIMIT FWD LIMIT IN. LB. 9500 Empty Wt. C.G. Range None Maximum Weight Takeoff 9000 or 9300 lb. (See NOTE 7) Landing 8550 or 8835 lb. (See NOTE 7) No. of Seats Maximum 10 (2 crew at +129). See loading instructions for passenger loading. Maximum Baggage 350 lb. (+275) Fuel Capacity Tank Cap Gal Usable Gal Arm L & R Nacelle 61 ea. 61 ea. +131 L & R Wing 131 ea. 131 ea. +167 See NOTE 1 for data on unusable fuel. Oil Capacity 18.4 qt. total (+101) See NOTE 1 for data on unusable oil. Max Oper Limit 30,000 ft. pressure altitude Control Surface Movements Wing flaps Maximum 44 Aileron Tab Up 7 ½  Down 7 ½  (LH only) Aileron tab anti-servo Up 14 Down 8 Aileron Up 20 Down 20 Elevator Tab Up 10 Down 21 Elevator Tab anti-servo Up 12 Down 8 Elevator Up 25 Down 15 Rudder Tab Right 30 Left 30 Rudder Right 24 Left 26 Serial No’s. Eligible LJ-1 thru LJ-113 (except LJ-76) 3A20 9 Rev. 82 V. Model 65-88, 10 PCLM (Normal Category), Approved September 21, 1965 Engines 2 Lycoming IGSO-540-A1D Fuel 100/130 minimum grade aviation gasoline Engine Limits (Straight line manifold pressure variation with altitude shown) HP RPM MP Alt Takeoff 380 3400 47.0 S.L. Takeoff 380 3400 43.5 10,500 Max. continuous 360 3200 45.0 S.L. Max. continuous 360 3200 41.7 10,500 Propeller and Propeller Limits 2 Hartzell, full-feathering, three-bladed (a) HC-B3Z30-2 hub with 10151-8R or 10151B-8R aluminum alloy blades and 836 spinner. Pitch settings at 30 in. sta.: low 18 1/4  1/4 high 87  1/4 Diameter: not over 93 in., not under 90 in. (b) Woodward hydraulic governor A210390 (use 210498 with propeller synchronizer) Airspeed Limits Never exceed 270 mph (234 knots) Maximum structural cruising 205 mph (178 knots) Maneuvering 195 mph (169 knots) Maximum flap extension speed Approach position - 50% 200 mph (174 knots) Full down flap psn. - 100% 150 mph (130 knots) Maximum landing gear operating speed: Extension 180 mph (156 knots) Retraction 150 mph (130 knots) Maximum landing gear extended speed 180 mph (156 knots) C.G. Range (Landing (+150.7) to (+160.4) at 8800 lb. Gear Extended) (+147.6) to (+160.4) at 7750 lb. or less Straight line variation between points given Moment change due to retracting landing gear -2050 in. -lb. 7500 7700 7900 8100 8300 8500 8700 8900 9100 9300 147 149 151 153 155 157 159 REAR LIMIT FWD LIMIT IN. LB. 9500 161 Empty Wt. C.G. Range None Maximum Weight Takeoff 8800 lb Landing 8800 lb No. of Seats Maximum 10 (2 crew at +129). See loading instructions for passenger loading. 3A20 10 Rev. 82 V. Model 65-88 (cont’d) Maximum Baggage 350 lb. (+275) (Structural Limit) Fuel Capacity Tank Cap Gal Usable Gal Arm L & R Main 44 ea. 44 ea. +174 L & R Aux 89 ea. 88 ea. +162 or L & R Wing 134.5 ea. 132 ea. +166 See NOTE 1 for data on unusable fuel Oil Capacity Left nacelle tank, 16 qt. (+138), right nacelle tank, 16 qt. (+138). See NOTE 1 for data on unusable (undrainable) oil. Control Surface Movements Wing flaps Maximum 31 ½  Aileron Tab Up 7 ½  Down 7 ½  (LH only) Aileron tab anti-servo Up 14 Down 8 (S/N LP-1 thru LP-45) Aileron Up 20 Down 20 Elevator Tab Up 10 Down 21 Elevator tab anti-servo Up 12 Down 8 Elevator Up 25 Down 15 Rudder tab Right 30 Left 30 Rudder Right 24 Left 26 Serial No’s. Eligible LP-1 thru LP-47 (except LP-27 and LP-29) 3A20 11 Rev. 82 VI. Model 65-B80, Queen Air, 13 PCLM (Normal Category), Approved October 22, 1965 Engines 2 Lycoming IGSO-540-A1A or 2 Lycoming IGSO-540-A1D Fuel 100/130 minimum grade aviation gasoline Engine Limits (Straight line manifold pressure variation with altitude shown) HP RPM MP Alt Takeoff 380 3400 47.0 S.L. Takeoff 380 3400 43.5 10,500 Max. continuous 360 3200 45.0 S.L. Max. continuous 360 3200 41.7 10,500 Propeller and Propeller Limits 2 Hartzell, full-feathering, three-bladed (a) HC-B3Z30-2 hub with 10151-8R or 10151B-8R aluminum alloy blades and 836 spinner. Pitch settings at 30 in. sta.: low 18 1/4  1/4, high 87  1/2 Diameter: not over 93 in., not under 90 in. (b) Woodward hydraulic governor A210390 (use 210498 with propeller synchronizer) Airspeed Limits Never exceed 270 mph (234 knots) Maximum structural cruising 205 mph (178 knots) Maneuvering 195 mph (169 knots) Maximum flap extension speed Approach position - 50% 200 mph (174 knots) Full down position - 100% 150 mph (130 knots) Maximum landing gear operating speed: Extension 180 mph (156 knots) Retraction 150 mph (130 knots) Maximum landing gear extended speed 180 mph (156 knots) C.G. Range (Landing (+150.7) to (+160.4) at 8800 lb. Gear Extended) (+147.6) to (+160.4) at 7750 lb. or less Straight line variation between points given Moment change due to retracting landing gear -2500 in. -lb. For diagram see Section V. Empty Wt. C.G. Range None Maximum Weight Takeoff 8800 lb. Landing 8800 lb. No. of Seats Maximum 13 (2 crew at +125). See loading instructions for passenger loading. Maximum Baggage 350 lb (+275) (standard aft compartment) (Structural Limit) 250 lb. (+309) (optional aft compartment) (450 lb. maximum in both compartments) 350 lb. (+70) (nose compartment) 300 lb. (+161) (optional cargo pod) (See NOTE 20) Fuel Capacity (1) (2) Tank Cap Gal Usable Gal Usable Gal Arm (LD-270 thru LD-279) L & R Main 44 ea. 44 ea. 39 ea. +174 L & R Aux 64 ea. 63 ea. 61 ea. +160 or L & R Aux 89 ea. 88 ea. 85 ea. +162 L & R Wing 19.5 ea. 107 ea. +166 or L & R Wing 107.5 ea. 100 ea. +166 or L & R Wing 134.5 ea. 132 ea. 127 ea. +166 See NOTE 1 for data on unusable fuel (1) Prior to incorporation of S.I. 0539-381 (2) After incorporation of S.I. 0539-381 3A20 12 Rev. 82 VI. Model 65-B80 (cont’d) Oil Capacity Left nacelle tank, 16 qt. (+138), right nacelle tank, 16 qt. (+138) See NOTE 1 for data on unusable (undrainable) oil. Control Surface Movements Wing Flaps Maximum 31 ½  Aileron Tab Up 7 ½  Down 7 ½  (LH only) Aileron tab anti-servo Up 14 Down 8 (S/N LD-270 thru LD-368) Aileron Up 20 Down 20 Elevator tab Up 10 Down 21 Elevator tab anti-servo Up 12 Down 8 Elevator Up 25 Down 15 Rudder tab Right 30 Left 30 Rudder Right 24 Left 26 Serial No’s. Eligible LD-270 thru LD-511 VII. Model 65-A90, King Air, 10 PCLM (Normal Category), Approved March 7, 1966 Engines 2 United Aircraft of Canada, Ltd. or Pratt & Whitney, PT6A-20 (Turboprop) Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); Jet A, Jet A-1, and Jet B conforming to P&WC S.B. 1244 or ASTM Spec. D1655. See NOTE 5 for emergency fuels. Oil (Engine and Gearbox) UACL PT6 Service Bulletin No. 1 lists approved brand oils. Engine Limits Static Sea Level Ratings Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop. Shaft Speed Max. Permissible Turbine Interstage Temp. (Deg. C.) Takeoff (5 minutes) 500 68 527 2200* 750 Max Continuous 500 68 527 2200* 750 Strtg. Trans. (2 seconds) 1090 Max. Reverse (1 minute) 300 2100 750 Static Sea Level Ratings (See NOTES 17 & 19) Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop. Shaft Speed Max. Permissible Turbine Interstage Temp. (Deg. C.) Takeoff (5 minutes) 550 72 579 2200* 750 Max. Continuous 550 72 579 2200* 750 Strtg. Trans. (2 seconds) 1090 Max. Reverse (1 minute) 300 2100 750 *See NOTE 4 At low altitudes and low ambient temperature, the engines may produce more power at takeoff that for which the airplane has been certificated. Under these conditions the placarded torquemeter limitations shall not be exceeded. Oil Temperatures: -40F minimum starting -40F to 200F low idle 50F to 200F max continuous 210F max oil temperature not to exceed 5 minutes. Oil Temperatures: -40F minimum starting (see NOTES -40F to 210F low idle 17 & 19) 50F to 210F max continuous 3A20 13 Rev. 82 VII. Model 65-A90 (cont’d) Propeller and Propeller Limits Non Reversing Propeller: 2 Hartzell HC-B3TN-2 (b)/T10173B-8 or HC-B3TN-2M/T10173NB-8 Diameter: 93 3/8 in. (Nominal) minimum allowable for repair 90 3/8 in. (no further reduction permitted) Pitch settings at 30 in. Sta.: Low 19, Feather 87 Reversing Propeller: 2 Hartzell HC-B3TN-3 or HC-B3TN-3B or HC-B3TN-3M hubs with T10173E8 or T10173B8 or T10173NB-8 blades. Diameter: 93-3/8 in. (nominal) minimum allowable for repair 90-3/8 in (no further reduction permitted) Pitch Settings at 30 in. Sta.: Flight idle stop (See NOTE 10) Secondary flight idle stop (See NOTE 10) Reverse -11 Feather 87 Airspeed Limits Max Operating Speed 240 mph (208 knots) Maneuvering Speed 195 mph (169 knots) Flaps extended speed 150 mph (130 knots) Maximum landing gear operating speed: Extension 180 mph (156 knots) Retraction 150 mph (130 knots) Maximum landing gear extended speed 180 mph (156 knots) C.G. Range (Landing (+153.2) to (+160.4) at 9650 lb. (See NOTE 17) Gear Extended) (+152.2) to (+160.4) at 9300 lb. (+147.6) to (+160.4) at 7750 lb. or less Straight line variation between points given Moment change due to retracting landing gear -3411 in. -lb. 7800 8000 8200 8400 8600 8800 9000 9200 9400 9600 146 148 150 152 154 156 158 REAR LIMIT FWD LIMIT IN. LB. 9800 1627600 3A20 14 Rev. 82 II. Model 65-A90 (cont’d) (+152.2) to (+160.4) at 9300 lb. (+144.7) to (+160.4) at 7400 lb. or less (See NOTE 18) Straight line variation between points given. Moment change due to retracting landing gear -3825 in. -lb. 7200 7400 7600 7800 8000 8200 8400 8600 8800 9000 144 148 152 156 158 162 REAR LIMIT FWD LIMIT IN. LB. 9200 9400 (+153.2) to (+160.4) at 9650 lb. (See NOTE 19) (+144.7) to (+160.4) at 7400 lb. or less (See NOTE 19) Straight line variation between points given. Moment change due to retracting landing gear -3825 in. -lb. 144 146 148 150 152 154 156 158 160 162 7000 7200 7400 7600 7800 8000 8200 8400 8600 8800 9000 9200 9400 9600 9800 LB. INCHES REAR LIMIT FWD LIMIT Empty Wt. C.G. Range None Maximum Weight Takeoff 9300 lb. Takeoff 9650 lb. (See NOTE 17 & 19) Landing 8835 lb. Landing 9168 lb. (See NOTE 17 & 19) No. of Seats Maximum 10 (2 crew at +129). See loading instructions for passenger loading. Maximum Baggage (Structural limit) 350 lb. (+275)