# TCDS 3A20: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 82 - Revised: September 5, 2019 - Product: Aircraft, Small Airplane - Certification basis: Part 23, CAR 3 - Registered aircraft: 995, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/ec/87/ec87130e80e7eb575d729581f989b51b1ddaa9dc0d66d67247f47cda43908eb9 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/688D33B3FCC8EE4286258472005D65C7.0001 - Page: https://openairdocs.org/tcds/3A20 ## Models (22) As the data sheet lists them. - B90 - 65-A80-8800 - 65-A90-2 ((RU-21B)) - 65-A90-1 ((JU-21A,) (U-21A) (RU-21A) (RU-21D) (U-21G) (RU-21H)) - 65-B80 - 65-A80 - 65-A90-3 ((RU-21C)) - 65 ((L-23F)) - A65-8200 - E90 - 65-88 - 70 - 65-A90 - C90A - C90GTi - H90 ((T-44A)) - C90GT - 65-A90-4 ((RU-21E, RU-21H)) - 65-90 - C90 - 65-80 - A65 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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) 3A20 15 Rev. 82 VII. Model 65-A90 (cont’d) 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 Up 15 Down 15 (LH only) (See NOTE 18 & 19) 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 Rudder Right 24 Left 19 (See NOTES 17 & 19) Serial No’s. Eligible LJ-76, LJ-114 thru LJ-317 VIII. Model A65, Queen Air, 7 to 9 PCLM (Normal Category), Approved November 3, 1966 Model A65-8200, Queen Air, 11 PCLM (Normal Category), Approved October 9, 1967 Model 70, Queen Air, 11 PCLM (Normal Category), approved November 27, 1968 Engines 2 Lycoming IGSO-480-A1E6 or IGSO-480-A1B6 (Model A65) 2 Lycoming IGSO-480-A1E6 (Models A65-8200 and 70) 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 43.5 11,000 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-B3Z20-2A hub with 10151-8R or 10151B-8R aluminum alloy blades and 836 spinner. Pitch settings at 30 in. Sta.: low 16, high 87 Diameter: not over 93 in., not under 90 in. (b) Woodward hydraulic governor 210365 or 210433 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) (LC-325 & up - Model A65) (LB-1 & up - Model 70) 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) 3A20 16 Rev. 82 VIII. Model A65, Model A65-8200, Model 70 (cont’d) C.G. Range (Landing Gear (+151.1) to (+160.4) at 8200 lb. (see NOTE 16) Extended) (+149.9) to (+160.4) at 7700 lb. (+147.6) to (+160.4) at 6720 lb. or less Straight line variation between points given Moment change due to retracting landing gear -2500 in. -lb. 6200 6400 6600 6800 7200 7600 7800 8000 144 148 152 156 160 REAR LIMIT FWD LIMIT IN. LB. 8200 8400 7000 7400 Empty Wt. C.G. Range None Maximum Weight Takeoff 7700 or 8200 lb. (See NOTE 16) Landing 7700 or 8200 lb (See NOTE 16) No. of Seats Maximum 9 or 11 (2 crew at +129). See NOTE 16. See loading instructions for passenger loading. Maximum Baggage 350 lb. (300 lb. at +267, 50 lb. at +288) (aft compartment) (Structural Limits) 350 lb. (+70) (nose compartment) (LC-325 and up) Maximum Baggage 350 lb. (+275) (standard aft compartment) (Structural Limits) 250 lb. (+309) (optional aft compartment) (LC-325 and up) 350 lb. (+ 70) (nose compartment) (LB-1 and up) Fuel Capacity Tank Cap Gal Usable Gal Arm (A) L & R Wing 92.5 ea. 90 ea. +168 or (B) L & R Wing 109.5 ea. 107 ea. +166 or (C) L & R Wing 117.5 ea. 115 ea. +168 or (D) L & R Wing 134.5 ea. 132 ea. +166 Fuel system applicability: Model Serial No. Systems A65 LC-240 through LC-324 A,C,D A65 LC-325 and up B,D A65-8200 LC-273 through LC-324 A,B,D 70 LB-1 and up B,D 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. 3A20 17 Rev. 82 VIII. Model A65, Model A65-8200, Model 70 (cont’d) Control Surface Movements Wing flaps Maximum 31 ½  Aileron tabs Up 7 ½  Down 7 ½  (LH only) Aileron tabs anti-servo Up 14 Down 8 (S/N LC-240 thru LC-283) 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 Model A65 LC-240 through LC-335 Model A65-8200 LC-273 through LC-324 (see NOTE 16) Model 70 LB-1 through LB-35 IX. Model 65-A90-1 (Military U-21A, RU-21A, RU-21D, JU-21A, U-21G, RU-21H (GR V)), 12 PCLM (Normal Category), Approved April 27, 1966 Model 65-A90-4 (Military RU-21E, RU-21H (GR II & IV), RU-21H (GR V)), 12 PCLM (Normal Category), Approved December 10, 1971. 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. D1644. See NOTE 5 for emergency fuels. Oil (Engine and Gearbox) Use MIL-L-7808 or MIL-L-23699 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) 550 68 579 2200* 750 Max. Continuous 550 68 579 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 than the airplane has been certificated for. Under these conditions, the placarded torquemeter limitations shall not be exceeded. Oil Temperatures: -40F minimum starting -40F to 210F low idle 50F to 210F maximum continuous 210F maximum oil temperature not to exceed 5 minutes. Propeller and Propeller Limits 2 Hartzell HC-B3TN-3B/T10173E-8 or HC-B3TN-3/T10173E-8 or HC-B3TN-3/T10173B-8 or HC-B3TN-3M/T10173NB-8 with three blades each. Diameter: 93 3/8 in. (Nominal) Minimum allowable for repair 90 3/8 in. (no further reduction permitted) Pitch settings at 30 in. Sta.: Reversing Propeller Flight idle stop (See NOTE 10) Secondary flight idle stop (See NOTE 10) Reverse -11 Feather 87 3A20 18 Rev. 82 IX. Model 65-A90-1, Model 65-A90-4 (cont’d) 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. Gear Extended) (+144.7) to (+160.4) at 7400 lb. or less Straight line variation between points given Moment change due to retracting landing gear -3825 in. -lb. For diagram see third one of Section VII. Empty Wt C.G. Range None Maximum Weight Takeoff 9650 lb. (See NOTE 24) Landing 9168 lb. No. of Seats Maximum 12 (2 crew at +129). See loading instructions for passenger loading. Fuel Capacity Tank Cap Gal Usable Gal Arm L & R Nacelle 57 ea. 57 ea. +131 L & R Wing 128 ea. 128 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 Limits 30,000 ft. pressure altitude Control Surface Movements Wing flaps Maximum 44 Aileron Tab (left only) Up 7 ½  Down 7 ½  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 LM-1 and up. Prior to civil certification, 65-A90-1 airplanes that have been operated by the military must be modified per Beech dwg. 50-002018 (U21A, U-21G, and RU-21A) or 50-002083 (RU-21D) or 50-002084 (JU-21A) or 91-002052 (RU-21H, GR V). LU-1 and up. Prior to civil certification, 65-A90-4 airplanes that have been operated by the military must be modified per Beech dwg. 91-002050 (RU-21E) or 91-002051(RU-21H, GR II & IV) or 91-002052 (RU-21H, GR V). X. Model B90, King Air, 10 PCLM (Normal Category), Approved November 14, 1967 Model C90, King Air, 10 PCLM (Normal Category), Approved October 23, 1970 Engines 2 United Aircraft of Canada, Ltd., or Pratt & Whitney, PT6A-20 (Turboprop) (Model B90) 2 United Aircraft of Canada Ltd. or Pratt & Whitney, PT6A-20 (Turboprop), PT6A-6/20 (Turboprop), PT6A-20A (Turboprop), or PT6A-21 (Turboprop) (Model C90). See NOTE 21. 3A20 19 Rev. 82 X. Model B90, Model C90 (cont’d) 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 Engine Service Bulletin No. 1 lists approved brand oils. Engine Limits Static Sea Level Ratings (PT6A-20, PT6A-6/C20, PT6A-20A) 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 Static Sea Level Ratings (PT6A-21) Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop Shaft Speed Max Permissible Turbine Interstage Temp. (Deg. C) Takeoff (5 minutes) 550 75 580 2200* 695 Max. Continuous 550 75 580 2200* 695 Strtg. Trans. (2 seconds) 1090 Max Reverse (1 minute) 300 2100 695 * See NOTE 4 At low altitudes and low ambient temperature, the engines may produce more power at takeoff than 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 210 F low idle 50F to 210F max continuous 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 (For Model C90 Only, See Note 30.) 2 Hartzell HC-B3TN-3 or HC-B3TN-3B or HC-B3TN-3M hubs with T10173E8 or T10173B8 or T10173NB-8 blades (For Model C90 S/N LJ-954 and after) 2 Hartzell HC-B3TN-3 or HC-B3TN-3B or HC-B3TN-3M hubs with Hartzell T10173K-8 or T10173NK-8 aluminum alloy blades, and Hartzell C-3065-8P or C-3065-10P or C-3065-12P or C-3065-13P spinner assembly. 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 3A20 20 Rev. 82 X. Model B90, Model C90 (cont’d) Airspeed Limits Maximum 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. Gear Extended) (+144.7) to (+160.4) at 7400 lb. For Model B90 For Model C90 aircraft with PT6A-20, PT6A-6/C20, or PT6A-20A engines (See NOTE 21) (+153.2) to (+160.0) at 9650 lb. (+144.7) to (+160.0) at 7400 lb. For Model C90 aircraft with PT6A-21 engines (See NOTE 21) Straight line variation between points given Moment change due to retracting landing gear -3825 in. -lb. Empty Wt. C.G. Range None Maximum Weight Takeoff: 9650 lb. Landing: 9168 lb. No. of Seats Maximum 10 (2 crew at +129). See loading instructions for passenger loading. Maximum Baggage 350 lb (+275) (Structural Limit) 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) for PT6A-20 engine, 22.4 qt. total (+101) for PT6A-21 engine. 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 (left only) Up 15 Down 15 Aileron Up 20 Down 20 Elevator tab Up 10 Down 21 Ele. tab anti-servo Up 12 Down 8 Elevator Up 25 Down 15 Rudder tab Right 30 Left 30 Rudder Right 24 Left 19 Serial No’s. Eligible Model B90: LJ-318 thru LJ-501 Model C90: LJ-502 thru LJ-1062 XI. Model 65-A90-2 (Military RU-21B) and 65-A90-3 (Military RU-21C), 5 PCLM (Normal Category), Approved March 20, 1969 Engines 2 United Aircraft of Canada, Ltd. or Pratt & Whitney PT6A-29 (turboprop), or 2 United Aircraft of Canada, Ltd. or Pratt & Whitney PT6A-34 (turboprop) 3A20 21 Rev. 82 XI. Model 65-A90-2 (cont’d) 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) PT6A-29 Engine Service Bulletin No. 1 lists approved brand oils. PT6A-34 Engine Service Bulletin No. 1 lists approved brand oils. Engine Limits (PT6A-29) Static Sea Level Ratings Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop. Shaft Speed Max. Permissible Turbine Interstage Temp. (Deg. C) Takeoff (5 minutes) 620 70 648 2200* 750 Max. Continuous 620 70 648 2200* 750 Strtg. Trans. (2 seconds) 1090 Max Reverse (1 minute) 470 2068 750 *See NOTE 4 At low altitude and low ambient temperature the engines may produce more power at takeoff than 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 min. Engine Limits (PT6A-34) Static Sea Level Ratings Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop. Shaft Speed Max. Permissible Turbine Interstage Temp. (deg. C) Takeoff (5 minutes) 620 82 648 2200* 790 Max Continuous 620 82 648 2200* 790 Strtg. Trans. (2 seconds) 1090 Max Reverse (1 minute) 470 2068 790 *See NOTE 4 At low altitude and low ambient temperature, the engines may produce more power at takeoff than 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 210F low idle 50F to 210F max. continuous 210F max oil temperature not to exceed 5 minutes Propeller and Propeller Limits 2 Hartzell HC-B3TN-3B/T10173E-8 or HC-B3TN-3/T10173E-8 or HC-B3TN-3/T10173B-8 or HC-B3TN-3M/T10173NB-8 with three blades each. Diameter: 93-3/8 in. (Nominal) Minimum allowable for repair: 90-3/8 in. (no further reduction permitted) Pitch settings at 30 in. Sta.: Reversing Propeller Flight idle stop (see NOTE 10) Secondary flight idle stop (see NOTE 10) Reverse -11 Feather 87 3A20 22 Rev. 82 XI. Model 65-A90-2 (cont’d) Airspeed Limits Maximum operating speed 240 mph (208 knots) Maneuvering speed 195 mph (169 knots) Maximum flap extended speed Approach position 35% 200 mph (174 knots) Full down flap position - 100% 164 mph (143 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 Gear (+155.2) to (+160.4) at 10,900 lb. Extended) (+144.7) to (+160.4) at 7400 lb or less Straight line variation between points given Moment change due to retracting landing gear -4500 in. -lb. 7000 7400 7800 8200 9000 9800 10200 10600 144 148 152 156 160 IN. LB. 11000 8600 9400 164 Empty Wt. C.G. Range None Maximum Weight Takeoff: 10,900 lb. Landing: 10,900 lb. No. of Seats Maximum 5 (2 crew at +129). See loading instructions for passenger loading. Fuel Capacity Tank Cap. Gal Usable Gal Arm L & R Nacelle 53 ea. 53 ea. +131 L & R Wing 145 ea. 145 ea. +165 See NOTE 1 for data on unusable fuel. Oil Capacity 22.4 qt. total (+101) See NOTE 1 for data on unusable oil. Control Surface Movements Wing flaps Maximum 44 Aileron tab (left only) Up 7 ½  Down 7 ½  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 19 Serial No’s. Eligible LS-1 and up. Prior to civil certification, 65-A90-2 airplanes that have been operated by the military must be modified per Beech dwg. 50-002081. LT-1 and up. Prior to civil certification 65-A90-3 airplanes that have been operated by the military must be modified per Beech dwg. 50-002082. 3A20 23 Rev. 82 XII. Model E90, King Air, 10 PCLM (Normal Category), Approved April 13, 1972 Engines 2 United Aircraft of Canada, Ltd., or Pratt & Whitney, PT6A-28 (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 Engine 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) Max. cont. and takeoff 550** 76 580 2200* 750 Strtg. Trans (2 seconds) 1090 Max Reverse (1 minute) 300 2100 750 *See NOTE 4 **Flat rated At low altitudes and low ambient temperature, the engines may produce more power at takeoff than that for which the airplane has been certificated. Under these conditions, the placarded torquemeter limitations shall not be exceeded. Oil Temperature: -40F minimum starting -40F to 210F low idle 50F to 210F maximum continuous Propeller and Propeller Limits Non Reversing Propeller: 2 Hartzell HC-B3TN-2(B)/T10173B-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 (See NOTE 30.) 2 Hartzell HC-B3TN-3 or HC-B3TN-3B or HC-B3TN-3M hubs with T10173E8 or T10173B8 or T10173NB-8 blades. (For Model E90 S/N LW-348 and after only): 2 Hartzell HC-B3TN-3 or HC-B3TN-3B or HC-B3TN-3M hubs with Hartzell T10173K-8 or T10173NK-8 aluminum alloy blades, and Hartzell C-3065-8P or C-3065-10P or C-3065-12P or C-3065-13P spinner assembly. 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 Maximum Operating Speed 260 mph (226 knots) Maneuvering 202 mph (175 knots) Flaps extended speed 150 mph (130 knots) (S/N LW-1 through LW-42) 161 mph (140 knots) (S/N LW-43 and after) 3A20 24 Rev. 82 XII. Model E90 (cont’d) Airspeed Limits (cont’d) Maximum Landing Gear Operating Speed: Extension 180 mph (156 knots) Retraction 150 mph (130 knots) (S/N LW-1 through LW-42) 168 mph (146 knots) (S/N LW-43 and after) Maximum Landing Gear Extended Speed: 180 mph (156 knots) C.G. Range (Landing (+152.0) to (+160.0) at 10,100 lb. Gear Extended) (+144.7) to (+160.0) at 7850 lb. or less Straight line variation between points given Moment change due to retracting landing gear -3825 in. -lb. Empty Wt. C.G. Range None Maximum Weight Takeoff: 10,100 lb. Landing: 9,700 lb. No. of Seats Maximum 10 (2 crew at +129). See loading instructions for passenger loading. Maximum Baggage 350 lb. (+275) (Structural Limit) Fuel Capacity Tank Cap Gal Usable Gal Arm L & R Aux 41 ea. 41 ea. +174 L & R Main 196 ea. 196 ea. +153 See NOTE 1 for data on unusable fuel. Oil Capacity 18.4 qt. total (+101). See NOTE 1 for data on unusable oil. Control Surface Movements Wing flaps Maximum 44 Aileron tab (left only) Up 15 Down 15 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 19 Serial No’s. Eligible Model E90: LW-1 and up XIII. Model H90, King Air (T-44A), 10 PCLM (Normal Category), Approved March 23, 1977 Engines 2 United Aircraft of Canada, Ltd., or Pratt & Whitney, PT6A-34B (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 Engine Service Bulletin No. 1 lists approved brand oils. 3A20 25 Rev. 82 XIII. Model H90 (cont’d) Engine Limits Static Sea Level Ratings Shaft Horsepower Jet Thrust Equivalent Shaft Horsepower Prop. Shaft Speed Max. Permissible Turbine Interstage Temp (Deg. C) Max Cont & Takeoff 550** 74 579 2200* 790 Strtg. Trans (2 seconds) 1090 Max. Reverse (1 minute) 300 2100 790 *See NOTE 4 **Flat rated At low altitude and low ambient temperature, the engines may produce more power at takeoff than 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 210F low idle 50F to 210F maximum continuous Propeller and Propeller Limits Reversing Propeller (See NOTE 30.) 2 Hartzell HC-B3TN-3B or HC-B3TN-3M hubs with 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) Reverse -11 Feather 87 Airspeed Limits Maximum operating speed 260 mph (226 knots) Maneuvering 203 mph (175 knots) Flaps extended speed 161 mph (140 knots) Maximum landing gear operating speed: Extension 180 mph (156 knots) Retraction 168 mph (146 knots) Maximum landing gear extended speed 180 mph (156 knots) See NOTE 23 C.G. Range (Landing Gear (+152.4) to (+160.0)at 10,200 lb. Extended) (+144.7) to (+160.0) at 7,850 lb. Straight line variation between points given Moment change due to retracting landing gear -3825 in.-lb. Empty Wt. C.G. Range None Maximum Weight Takeoff 10,200 lb. Landing 9,700 lb. No. of Seats Maximum 10 (2 crew at +129). See loading instructions for passenger loading. Maximum Baggage 350 lb. (+277) (Structural Limit) Fuel Capacity Tank Cap Gal Usable Gal Arm L & R Aux. 61 ea. 61 ea. +135 L & R Main 131 ea. 131 ea. +165 See NOTE 1 for data on unusable fuel. Oil Capacity 22.4 qt. total (+101) See NOTE 1 for data on unusable oil. 3A20 26 Rev. 82 XIII. Model H90 (cont’d) Maximum Operating Limit 31,000 ft. pressure altitude Control Surface Movements Wing flaps Maximum 44 Aileron tab (left only) Up 15 Down 15 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 19 Serial No’s. Eligible Model H90 (T-44A): LL-1 and up XIV. Model C90A, King Air (Normal Category), Approved December 1, 1983 Engines 2 Pratt & Whitney Aircraft of Canada, Ltd. PT6A-21 (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) P&WC PT6 Engine Service Bulletin No. 1 lists approved brand oils Engine Limits Shaft Horsepower N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Deg. C) Takeoff (5 minutes) 550 101.5 2200* 695 Max Continuous 550 101.5 2200* 695 Starting Transient (2 seconds) 102.6 1090 Max Reverse (1 minute) 300 88.0 2100 695 * See NOTE 4 At low altitude and low ambient temperature, the engines may produce more power at takeoff than that for which the airplane has been certificated. Under these conditions, the placarded torquemeter limits shall not be exceeded. Oil temperatures: -40F minimum starting -40F to 210F low idle 50F to 210F max. continuous Propeller and Propeller Limits Reversing Propeller (See Note 30.) 2 Hartzell HC-B3TN-3M or HC-B3TN-3B hubs with T10173K-8 or T10173NK-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 Propeller and Propeller Limits Non Reversing Propeller S/N LJ-1063 thru LJ-1287, 2 Hartzell HC-B3TN-2(B)/T10173B-8 LJ-1288 thru LJ-1294 Diameter: 93-3/8 in. (Nominal) Minimum allowable for repair 90-3/8 in. LJ-1296 thru LJ-1299 (no further reduction permitted) Pitch settings at 30 in. Sta.: Low 19, Feather 87 3A20 27 Rev. 82 XIV. Model C90A (cont’d) S/N LJ-1288, LJ-1295 Reversing Propeller LJ-1302, LJ-1303, LJ-1305 2 McCauley 4HFR34C768 hubs with 94LMA-4 blades thru LJ-1308, LJ-1311, LJ-1312 Diameter: 90 in. (Nominal) Minimum allowable for repair LJ-1314 thru LJ-1316, LJ-1318 89 in. (no further reduction permitted) LJ-1320 thru LJ-1366, LJ-1368 Pitch settings at 30 in. sta.: thru LJ-1372, LJ-1374 thru Flight Idle Stop (See NOTE 27) LJ-1376, LJ-1378 thru Reverse -10  .2 LJ-1383, LJ-1385, LJ-1387, Feather 85.8  .2 LJ-1388, LJ-1390 thru LJ-1393, minimum idle speed 1100 rpm (See NOTE 33) LJ-1395, LJ-1396, LJ-1398 thru LJ-1402, LJ-1404 thru LJ-1410, LJ-1412 thru LJ-1424, LJ-1426 thru LJ-1430, LJ-1432 thru LJ-1434, LJ-1436 thru LJ-1726, LJ-1728 thru LJ-1753, LJ-1755. Airspeed Limits CAS CAS IAS S/N LJ-1063 thru Maximum operating speed 260 mph (226 knots) 226 knots LJ-1137 and LJ-1146 Maneuvering 176 mph (153 knots) 153 knots Flaps extended speed 161 mph (140 knots) 148 knots Maximum landing gear operating speed Extension 209 mph (182 knots) 182 knots Retraction 189 mph (164 knots) 163 knots Maximum landing gear extended speed 209 mph (182 knots) 182 knots S/N LJ-1138 thru LJ-1145 Maximum operating speed 260 mph (226 knots) 226 knots Maneuvering 195 mph (169 knots) 169 knots LJ-1147 thru LJ-1726, Flaps extended speed 161 mph (140 knots) 148knots LJ-1728 thru LJ-1753, LJ-1755 Maximum landing gear operating speed Extension 209 mph (182 knots) 182 knots Retraction 189 mph (164 knots) 163 knots Maximum landing gear extended speed 209 mph (182 knots) 182 knots C.G. Range (Landing (+153.2) to (+160.0) at 9650 lb. Gear Extended) (+144.7) to (+160.0) at 7400 lb. or less S/N LJ-1063 thru Straight line variation between points given LJ-1137 and LJ-1146 Moment change due to retracting landing gear -3825 in. -lb. C.G. Range (Landing (+152.0) to (+160.0) at 10,100 lb. Gear Extended) (+151.7) at 9999 lbs. (Note 28) (+144.7) to (+160.0) at 7850 lb or less S/N LJ-1138 thru LJ-1145, Straight line variation between points given LJ-1147 thru LJ-1726, and after Moment change due to retracting landing gear -3825 in. -lb. LJ-1728 thru LJ-1753, LJ-1755 (See NOTE 28) Empty Wt. C.G. Range None Maximum Weight Ramp: 9710 lb. Landing: 9168 lb. S/N LJ-1063 thru Takeoff: 9650 lb. LJ-1137 and LJ-1146 Maximum Weight Ramp: 10,160 lb. Landing: 9600 lb. S/N LJ-1138 thru Takeoff: 10,100 lb. LJ-1145, LJ-1147 thru LJ-1726 LJ-1728 thru LJ-1753, LJ-1755 No. of Seats Maximum 13 (including 2 at +129). See loading instructions for passenger loading. Maximum Baggage 350 lb. (+275) (Structural Limit) 350 lb. (+70) (Baggage and Avionics) 3A20 28 Rev. 82 XIV. Model C90A (cont’d) 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 22.4 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 (left only) Up 15 Down 15 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 19 Serial No’s. Eligible LJ-1063 thru LJ-1726, LJ-1728 thru LJ-1753 and LJ-1755 See NOTE 29. XV. Model C90GT, King Air (Normal Category), Approved December 16, 2005 Engines 2 Pratt & Whitney Aircraft of Canada, Ltd. PT6A-135A (Turboprop) Per Hawker Beechcraft Corporation Specification BS184061. Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); Jet A, Jet A-1, Jet B conforming to P&WC S.B. 1244 or ASTM Spec D1655; and Chinese Jet Fuel No. 3. See NOTE 5 for emergency fuels. Oil (Engine and Gearbox) P&WC PT6 Engine Service Bulletin No. 1001 lists approved brand oils Engine Limits Shaft Horsepower N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Deg. C) Takeoff (5 minutes) 550 101.5 1900* 805 Max Continuous 550 101.5 1900* 805 Starting Transient (2 seconds) 102.6 1090 Max Reverse (1 minute) 300 88.0 1825 805 * See NOTE 31 At low altitude and low ambient temperature, the engines may produce more power at takeoff than that for which the airplane has been certificated. Under these conditions, the placarded torquemeter limits shall not be exceeded. Oil temperatures: -40F minimum starting -40F to 210F low idle 50F to 210F max. continuous Propeller and Propeller Limits Reversing Four Bladed Propeller (See Note 30.) 2 Hartzell HC-E4N-3N hubs with D8990SK blades per Hawker Beechcraft Corporation Specification BS186497. Diameter: 90.00 in. (Nominal) Minimum allowable for repair 89.00 in. (no further reduction permitted) Pitch settings at 30 in. Sta.: Flight idle stop (See NOTE 32) Reverse -10  .5 Feather 85.8  .5 Minimum idle speed 1100 RPM (See Note 33) 3A20 29 Rev. 82 XV. Model C90GT (cont’d) Airspeed Limits CAS CAS IAS Maximum operating speed 260 mph (226 knots) 226 knots Maneuvering 195 mph (169 knots) 169 knots Flaps extended speed (full down) 161 mph (140 knots) 148 knots Maximum landing gear operating speed Extension 209 mph (182 knots) 182 knots Retraction 189 mph (164 knots) 163 knots Maximum landing gear extended speed 209 mph (182 knots) 182 knots C.G. Range (Landing Gear (+152.0) to (+160.0) at 10,100 lb. Extended) (+144.7) to (+160.0) at 7850 lb or less Straight line variation between points given Moment change due to retracting landing gear -3825 in. -lb. Empty Wt. C.G. Range None Maximum Weight Ramp: 10,160 lb. Takeoff: 10,100 lb. Landing 9,600 lb. No. of Seats Maximum 13 (including 2 at +129). See loading instructions for passenger loading. Maximum Baggage 350 lb. (+275) (Structural Limit) 350 lb. (+70) (Baggage and Avionics) 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 (left only) Up 15 Down 15 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 19 Serial No’s. Eligible LJ-1727, LJ-1754, LJ-1756 thru LJ-1846, and LJ-1848 thru LJ-1852. See NOTE 29. XVI. Model C90GTi, King Air (Normal Category), Approved December 13, 2007 Engines 2 Pratt & Whitney Aircraft of Canada, Ltd. PT6A-135A (Turboprop) Per Hawker Beechcraft Corporation Specification BS184061. Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); Jet A, Jet A-1, Jet B conforming to P&WC S.B. 1244 or ASTM Spec D1655; and Chinese Jet Fuel No. 3. See NOTE 5 for emergency fuels. Oil (Engine and Gearbox) P&WC PT6 Engine Service Bulletin No. 1001 lists approved brand oils 3A20 30 Rev. 82 XVI. Model C90GTi (cont’d) Engine Limits Shaft Horsepower N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Deg. C) Takeoff (5 minutes) 550 101.5 1900* 805 Max Continuous 550 101.5 1900* 805 Starting Transient (2 seconds) 102.6 1090 Max Reverse (1 minute) 300 88.0 1825 805 * See NOTE 31 At low altitude and low ambient temperature, the engines may produce more power at takeoff than that for which the airplane has been certificated. Under these conditions, the placarded torquemeter limits shall not be exceeded. Oil temperatures: -40F minimum starting -40F to 210F low idle 50F to 210F max. continuous Propeller and Propeller Limits Reversing Four Bladed Propeller (See Note 30.) 2 Hartzell HC-E4N-3N hubs with D8990SK blades per Hawker Beechcraft Corporation Specification BS186497. Diameter: 90.00 in. (Nominal) Minimum allowable for repair 89.00 in. (no further reduction permitted) Pitch settings at 30 in. Sta.: Flight idle stop (See NOTE 32) Reverse -10  .5 Feather 85.8  .5 Minimum idle speed 1100 RPM (See Note 33) Airspeed Limits CAS CAS IAS Maximum operating speed 260 mph (226 knots) 226 knots Maneuvering 195 mph (169 knots) 169 knots Flaps extended speed (full down) 161 mph (140 knots) 148 knots Maximum landing gear operating speed Extension 209 mph (182 knots) 182 knots Retraction 189 mph (164 knots) 163 knots Maximum landing gear extended speed 209 mph (182 knots) 182 knots C.G. Range (Landing Gear (+152.0) to (+160.0) at 10,100 lb. Extended) (+144.7) to (+160.0) at 7850 lb or less Straight line variation between points given Moment change due to retracting landing gear -3825 in. -lb. Empty Wt. C.G. Range None Maximum Weight Ramp: 10,160 lb. Takeoff: 10,100 lb. Landing 9,600 lb. No. of Seats Maximum 13 (including 2 at +129). See loading instructions for passenger loading. Maximum Baggage 350 lb. (+275) (Structural Limit) 350 lb. (+70) (Baggage and Avionics) 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. 3A20 31 Rev. 82 XVI. Model C90GTi (cont’d) Max. Oper. Limit 30,000 ft. pressure altitude Control Surface Movements Wing flaps Maximum 44 Aileron tab (left only) Up 15 Down 15 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 19 Serial Nos. Eligible LJ-1847, LJ-1853 and after. Data Pertinent to All Models Datum Located 160 in. forward of wing main (forward) spar centerline. Leveling Means 2 external screws on left side of fuselage forward or aft of entrance door. Certification Basis Applicable to Model 65 (L-23F), 65-80, 65-A80, 65-88, 65-A80-8800; A65; A65-8200; and 70: CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); 14 CFR 23.1385(c) (Amdt. Original). 23.1387(a), 23.1387(e) (Amdt. 12). Applicable to Model 65-B80: CAR 3, Effective May 15, 1956, (Am. 3-1, 3-2, 3-8); 3.705 (Amdt. 3-7); 14 CFR 23.1385(c) (Amdt. Original). 23.1387(a), 23.1387(e) (Amdt. 12). Applicable to Model 65-90: CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8), CAR 3 (Amdt. 3-6); 14 CFR 23.1385(c) (Amdt. Original). 23.1387(a), 23.1387(e) (Amdt. 12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963 and February 27, 1963. Applicable to Models 65-A90, 65-A90-1 (U-21A, RU-21A, RU-21D, JU-21A, RU-21H, (GR V, U-21G)), 65-A90-4 (RU-21E, RU-21H (GR II & IV), RU-21H (GR V)), and B90: CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); CAR 3 (Amdt. 3-6); 3.705 (Amdt. 3-7); 14 CFR 23.1385(c) (Amdt. Original). 23.1387(a), 23.1387(e) (Amdt. 12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963, February 27, 1963 and May 5, 1965. Applicable to Models 65-A90-2 (RU-21B) and 65-A90-3 (RU-21C): CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); CAR 3 (Amdt. 3-6); 3.705 (Amdt. 3-7); 14 CFR 23.1385(c) (Amdt. Original). 23.1387(a), 23.1387(e) (Amdt. 12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963, February 27, 1963, May 5, 1965, and November 8, 1961. Applicable to Model C90: CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); CAR 3 (Amdt. 3-6); 3.705 (Amdt. 3-7); 14 CFR Part 23 §23.1385(c) (Amdt. Original); 23.1111 (Amdt. 23-7). 23.1387(a), 23.1387(e) (Amdt. 12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963, February 27, 1963 and May 5, 1965. FAA Exemption No. 1554A, issued March 4, 1977 from CAR 3 §3.115(a). 3A20 32 Rev. 82 Data Pertinent to All Models Certification basis (cont’d) Applicable to Model E90: CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); CAR 3 (Amdt. 3-6); 3.705 (Amdt. 3-7). 14 CFR 23.1385(c) (Amdt. Original). 23.954, 23.959, 23.1111 (Amdt. 23-7). 23.1387(a), 23.1387(e) (Amdt. 23-12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963, February 27, 1963, and May 5, 1965. FAA Exemption No. 1554 issued March 31, 1972 from CAR 3 3.115(a). Applicable to Model H90 (T-44A): CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); CAR 3 (Amdt. 3-6). 3.705 (Amdt. 3-7). 14 CFR 23.1385(c) (Amdt. Original). 23.954, 23.959, 23.1111 (Amdt. 23-7). 23.1387(a), 23.1387(e) (Amdt. 23-12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963, February 27, 1963 and May 5, 1965. FAA Exemption No. 1554A, issued March 4, 1977 from CAR 3 §3.115(a). Applicable to Model C90A: CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); CAR 3 (Amdt. 3-6). 3.705 (Amdt. 3-7). 14 CFR 23.1385(c) (Amdt. Original). 23.959, 23.1111, 23.1583(a) (Amdt. 23-7). 23.1387(a), 23.1387(e) (Amdt. 23-12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963, February 27, 1963 and May 5, 1965. 23.143(a), 23.145(d), 23.153, 23.161(c)(3), 23.173(a) (Amdt. 23-14). 23.175 (Amdt. 23-17). 23.967(a)(5) (Amdt. 23-18). 23.1545(a) (Amdt. 23-23). 23.729 (Amdt. 23-26). 25.831(d) (Amdt. 25-41). 14 CFR Part 36, December 1, 1969 thru Amendment 36-10; SFAR 27, February 1, 1974 thru Amendment 27-4. Applicable to Model C90A with EFIS: CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); CAR 3 (Amdt. 3-6). 3.705 (Amdt. 3-7). 14 CFR 23.1385(c) (Amdt. Original). 23.959, 23.1111, 23.1583(a) (Amdt. 23-7). 23.1387(a), 23.1387(e) (Amdt. 23-12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963, February 27, 1963 and May 5, 1965. 23.143(a), 23.145(d), 23.153, 23.161(c)(3), 23.173(a) (Amdt. 23-14). 23.175 (Amdt. 23-17). 23.967(a)(5) (Amdt. 23-18). 23.1545(a) (Amdt. 23-23). 23.729 (Amdt. 23-26). Effective April 17, 1992, Electronics Flight Instrument Systems shall meet the requirements of 23.1301, 23.1309, 23.1311, 23.1321, 23.1322 and 23.1335 (Amdt. 23-41). Effective January 20, 1994, 23.1457 (Amdt. 23-35). 14 CFR 25.831(d) (Amdt. 25-41). 14 CFR Part 36, December 1, 1969 thru Amendment 36-10; SFAR 27, February 1, 1974 thru Amendment 27-4. Applicable to Model C90GT: CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); CAR 3 (Amdt. 3-6). 3.705 (Amdt. 3-7). 14 CFR 23.1385(c) (Amdt. Original). 23.959, 23.1111, 23.1583(a) (Amdt. 23-7). 23.1387(a), 23.1387(e) (Amdt. 23-12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963, February 27, 1963 and May 5, 1965. 23.143(a), 23.145(d), 23.153, 23.161(c)(3), 23.173(a) (Amdt. 23-14). 23.175 (Amdt. 23-17). 23.967(a)(5) (Amdt. 23-18). 23.1545(a) (Amdt. 23-23). 23.729, 23.1529 (Amdt. 23-26). Effective April 17, 1992, Electronics Flight Instrument Systems shall meet the requirements of 23.1301, 23.1309, 23.1311, 23.1321, 23.1322 and 23.1335 (Amdt. 23-41). Effective January 20, 1994, 23.1457 (Amdt. 23-35). 23.201, 23.203, 23.207 (Amdt. 23-50). 14 CFR 25.831(d) (Amdt. 25-41). 14 CFR 34.11(a)(b)(c), 34.21(e), 34.71, 34.89 (Amdt. 34-3). 14 CFR Part 36, December 1, 1969 thru Amendment 36-25; SFAR 27, February 1, 1974 thru Amendment 27-4. Additional Requirements for IHAS 800 Installation on Model C90A/C90GT: 14 CFR 23.301(a), 23.303, 23.305(a)(b), 23.307(a), 23.321, 23.331, 23.333, 23.335, 23.337, 23.341, 23.347, 23.349, 23.351, 23.365(a)(b)(c), 23.425, 23.441, 23.471, 23.473, 23.571, 23.573, 23.609(b), 23.613(a)(b), 23.615, 23.619, 23.621, 23.623, 23.625, 23.627, 23.629, 23.1331(a)(b), 23.1365(a)(d)(e), 23.1367(a)(b)(c)(d) (Amdt.Original). 23.611, 23.617, 23.777(a)(b), 23.867(a)(b), 23.561(a)(b), 23.1351(b) (Amdt. 23-7). 23.1581 (Amdt. 23-13); 23.1322(a)(b)(c)(d) (Amdt. 23-17). 23.1301(a)(b)(d), 23.1321(a)(b)(c)(d)(e), 23.1357(a)(b)(c)(d) (Amdt. 23-20). 23.1541 (Amdt. 23-21). 23.1307(b) (Amdt. 23-23). 23.1529 (Amdt. 23.26). 23.1583(m), 23.1585(j), 23.1587 (Amdt. 23-34). 23.1311(a)(b), 23.1331(c), 23.1359(c) (Amdt. 23-35). 23.1309(a)(b), (Amdt. 23-41). 3A20 33 Rev. 82 Data Pertinent to All Models Certification basis (cont’d) Additional Requirements for RDR2100/KDM850 Installation on Model C90A/C90GT: 14 CFR 23.301(a), 23.303, 23.305(a)(b), 23.307(a), 23.321, 23.331, 23.333, 23.335, 23.337, 23.341, 23.347, 23.349, 23.351, 23.365(a)(b)(c), 23.421, 23.423, 23.425, 23.441, 23.471, 23.473, 23.571, 23.573, 23.601, 23.603(a)(b), 23.605(a), 23.607, 23.609(a)(b), 23.613(a)(b), 23.615, 23.619, 23.621, 23.623, 23.625, 23.627, 23.629, 23.1331(a)(b), 23.1365(a)(d)(e), 23.1367(a)(b)(c)(d) (Amdt.Original). 23.611, 23.617, 23.777(a)(b), 23.867(a)(b), 23.561(a)(b), 23.959, 23.1111, 23.1351(a) (Amdt. 23-7). 23.1581 (Amdt. 23-13). 23.1322(a)(b)(c)(d) (Amdt. 23-17). 23.1301(a)(b)(d), 23.1321(a)(b)(c)(d)(e), 23.1357(a)(b)(c)(d) (Amdt. 23-20). .23.1307(b) (Amdt. 23-23). 23.1529 (Amdt. 23.26). 23.1583(m), 23.1585(j), 23.1587 (Amdt. 23-34). 23.1311(a)(b), 23.1331(c), 23.1359(c) (Amdt. 23-35). 23.1309(a)(b) (Amdt. 23-41). Additional Requirements for GPS 400 Installation on Model C90A/C90GT: 14 CFR 23.301(a), 23.303, 23.305(a)(b), 23.307(a), 23.321, 23.331, 23.333, 23.335, 23.337, 23.341, 23.347, 23.349, 23.351, 23.365(a)(b)(c), 23.421, 23.423, 23.425, 23.441, 23.471, 23.473, 23.571, 23.573, 23.601, 23.603(a)(b), 23.605(a), 23.607, 23.609(a)(b), 23.613(a)(b), 23.615, 23.619, 23.621, 23.623, 23.625, 23.627, 23.1331(a)(b), 23.1365(a)(d)(e), 23.1367(a)(b)(c)(d), 23.1431(a)(b)(c) (Amdt.Original). 23.611, 23.617, 23.777(a)(b), 23.867(a)(b). 23.561(a)(b), 23.1351(b) (Amdt. 23-7); 23.1581 (Amdt. 23-13); 23.1322(a)(b)(c)(d) (Amdt. 23-17). 23.1301(a)(b)(c)(d), 23.1321(a)(b)(c)(d)(e), 23.1357(a)(b)(c)(d) (Amdt. 23- 20). 23.1307(b) (Amdt. 23-23). 23.1529 (Amdt. 23.26). 23.1583(m), 23-1585(j), 23.1587 (Amdt. 23-34). 23.1329(h), 23.1331(c), 23.1359(c) (Amdt. 23-35). 23.1309(a)(b) (Amdt. 23-41). Applicable to Model C90GTi: CAR 3, Effective May 15, 1956, (Amdt. 3-1, 3-2, 3-8); CAR 3 (Amdt. 3-6). 3.705 (Amdt. 3-7). 14 CFR 23.1385(c) (Amdt. Original). 23.959, 23.1111, 23.1583(a) (Amdt. 23-7). 23.1387(a)(e) (Amdt. 23-12). Special Conditions outlined by FAA letters to Beech dated January 21, 1963, February 15, 1963, February 27, 1963 and May 5, 1965. 23.143(a), 23.145(d), 23.153, 23.161(c)(3), 23.173(a) (Amdt. 23-14). 23.175 (Amdt. 23-17). 23.967(a)(5) (Amdt. 23-18). 23.1545(a) (Amdt. 23-23). 23.729, 23.1529 (Amdt. 23-26). 23.201, 23.203, 23.207 (Amdt. 23-50). 25.831(d) (Amdt. 25-41). SFAR 27, February 1, 1974 thru Amendment 27-4. 34.11(a)(b)(c), 34.21(e), 34.71, 34.89 (Amdt. 34-3). Additional Requirements for Rockwell Collins Pro Line 21 Avionics Installation on Model C90GTi: 14 CFR 23.601, 23.1367(a)(b)(c)(d), 23.1381(a)(b)(c) (Amdt. Original). 23.1301(a)(b)(c)(d), 23.1335 (Amdt. 23-20). 23.1501(a) (Amdt. 23-21). 23.1457(a)(c) (Amdt. 23-35). 23.1322(a)(b)(c)(d), 23.1357 (Amdt. 23-43). 23.1549 (Amdt. 23-45). 23.1309(a)(b)(c)(d)(e), 23.1311(a)(b)(c), 23.1321(a)(b)(c)(d)(e), 23.1329(a)(b)(d)(e)(f), 23.1359(c), 23.1365(a)(b)(c)(d)(e), 23.1431(a)(b)(c) (Amdt. 23-49). 23.1521(b)(c), 23.1543(c), 23.1545(a)(b)(c), 23.1555(a) (Amdt. 23-50). 23.1305(a)(2)(3)(c)(1)(2)(5)(e)(1) (Amdt. 23-52). 23.901(e)(1) (Amdt. 23-53). 14 CFR Part 36, through Amendment 36-28. Special Condition 23-108-SC “Protection of Systems for High Intensity Radiated Fields (HIRF)” Equivalent Level of Safety ACE-07-06 “Installing Electronic Engine Indicating Systems (EIS)” Additional Requirements for Rockwell Collins Pro Line Fusion Avionics Installation on Model C90GTi (See NOTE 37): 14 CFR 23.601, 23.1367, 23.1381(a)(b) (Amdt. Original). 23.937(a) (Amdt. 23-7). 23.1301(a)(b)(c)(d), 23.1327(a)(1)(2)(b), 23.1335, 23.1547(a)(b)(c)(d)(e) (Amdt. 23-20). 23.1501(b) (Amdt. 23-21). 23.853(a) (Amdt. 23-34). 23.1322(a)(b)(c)(d)(e), 23.1331(b)(c), 23.1357(a)(b)(c)(d) (Amdt. 23-43). 23.613, 23.773(a)(1)(2), 23.1525, 23.1549(d), (Amdt. 23-45). 23.867(a)(b)(1), 23.1303(a)(b)(c)(e)(f), 23.1309(a)(1)(3)(b)(c)(1)(2)(i)(iii)(3)(d)(e), 23.1311(a)(b)(c), 23.1321, 23.1323(a)(c), 23.1329(c)(h), 23.1351(a)(1)(2)(i), 23.1353(h), 23.1359(c), 23.1365(a)(b)(c)(d)(e), 23.1431(a)(b)(c)(e) (Amdt. 23-49). 23.1521(a)(b)(1)(3)(4)(c)(1)(3), 23.1543(b)(c), 23.1545(d), 23.1555(a), 23.1581(a)(2)(b)(1)(3)(c)(d)(f), 23.1583(b)(h)(m), 23.1585(a)(j) (Amdt 23-50). 23.777(a)(b), 23.1141(g)(2), 23.1203(a)(d) (Amdt. 23-51). 23.1305(c)(1)(3)(6)(7)(e)(1) (Amdt. 23-52). 23.901(a)(1)(2)(e)(1) (Amdt. 23-53). 23.1308(a)(b)(c)(d) (Amdt. 23-57). 23.1306(a)(b) (Amdt. 23-61). 23.251(b), 23.903(b)(2) (Amdt. 23-62). Equivalent Level of Safety ACE-15-18 for 23.1305(a)(2)(3)(c)(2)(5) (Amdt 23-52), 23.1311(a)(6)(7) (Amdt 23-49). 23.1549(a)(b)(c) (Amdt 23-45). Effective at Serial Numbers LJ-2129 and on. Additional Requirements for GPS-4000S Installation on Model C90GTi (See NOTE 38): 14 CFR 23.867(a)(b) (Amdt. 23-49). 23.1301(a)(b)(c)(d) (Amdt. 23-20). 23.1306(b) (Amdt. 23-61). 23.1308(b) (Amdt. 23-57). 23.1309(a)(1)(3)(b)(c)(1)(2)(i)(iii)(3)(d)(e), 23.1351(a)(1)(2)(i), 23.1431(a)(b) (Amdt. 23-49). 23.1529 (Amdt 23-26). Effective at Serial Numbers LJ-2151 and on. Application for Type Certificate dated May 1, 1958 Type Certificate No. 3A20 issued February 4, 1959, obtained by the manufacturer under delegation option procedures. 3A20 34 Rev. 82 Data Pertinent to All Models Production Basis: Production Certificate No. 8. Delegation Option Manufacturer No. DOA-230339-CE authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. Serial Numbers LJ-2125 through LJ-2133: Manufactured under Production Certificate No. 4 by Textron Aviation, Inc., under license agreement between Beechcraft Corporation and Textron Aviation, Inc. Serial Numbers LJ-2134 and after: Manufactured under Production Certificate No. 4 by Textron Aviation Inc. Organization Delegation Authorization No. ODA-100129-CE is authorized to issue airworthiness certificates under the provisions of 14 CFR Part 21 and Part 183 of the Federal Aviation Regulations. Data Pertinent to All Models Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. Pre-stall warning indicator, Safe Flight Corp., P/N 168-2 or P/N 168-3, to be used if deicing equipment is installed per Beech Dwg. 50-369100 and 50-361100. 2. Pre-stall warning indicator, Safe Flight Instrument Corp., P/N 793-1 or P/N 795-3, to be used if deicing equipment is installed per Beech Dwg. 50-369100 and 50-361100 for Model s 65-A90 and B90. 3. Pre-stall warning indicator, Safe Flight Instrument Corp., P/N 168-3 to be used if deicing equipment is installed per Beech dwg. 50-970103 and 50-361104 or 91-361001 for Models 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4. 4. Pre-stall warning indicator, Safe Flight Instrument Corp., P/N 795-1 for Model C90, P/N 795-13 for Models C90A, C90GT, C90GTi. 5. Pre-stall warning indicator, Safe Flight Instrument Corp., P/N 795-5 for Model E90. 6. Pre-stall warning system, Rosemount P/N 92AT for Model H90 (T-44A). 7. FAA Approved Airplane Flight Manual or Pilot’s Operating Handbook (a) Model 65-90* S/N LJ-1 thru LJ-113 Model 65-A90* S/N LJ-114 thru LJ-317, LJ-317, LJ-76, LJ-178A *Model 65-90 and 65-A90 aircraft were delivered in and/or are modified by Beech kits to various configurations with non-reversing and reversing propellers: with PT6A-6, -20, -20A, and -21 engines, and at 9300 and 9650 lbs. An FAA Approved Airplane Flight Manual appropriate to the aircraft configuration is required. Refer to the Limitations Section of FAA Approved Airplane Flight Manual Supplement, P/N 131044, for equipment requirements for flight into known icing conditions. (b) Model B90 P/N 65-001123-31 S/N LJ-318 thru LJ-501 Model C90 P/N 90-590010-5 S/N LJ-502 thru LJ-624 Model C90 P/N 90-590010-53 S/N LJ-625 thru LJ-667 and LJ-670 Refer to the Limitations Section of FAA Approved Airplane Flight Manual Supplement, P/N 131044, for equipment requirements for flight into known icing conditions. 3A20 35 Rev. 82 Data Pertinent to All Models Equipment (cont’d) (c) Model E90 P/N 90-590012-5 S/N LW-1 thru LW-347 Model C90 P/N 90-590010-61 S/N LJ-668 thru LJ-1010 except LJ-670, LJ-986 and LJ-996 Model C90 P/N 90-590010-87 S/N LJ-986, LJ-996, LJ-1011 thru LJ-1062 Model C90A P/N 90-590024-5 S/N LJ-1063 thru LJ-1137 and LJ-1146 Model C90A P/N 90-590024-23 S/N LJ-1138 thru LJ-1145, LJ-1147 thru LJ-1287, LJ-1289 thru LJ-1294, LJ-1296 thru LJ-1299 Model C90A P/N 90-590024-35 S/N LJ-1288, LJ-1295, LJ-1302, LJ-1303, LJ-1305 thru LJ-1308, LJ-1311, LJ-1312, LJ-1314 thru LJ-1316, LJ-1318, LJ-1320 thru LJ-1352 Model C90A P/N 90-590024-43 S/N LJ-1300, LJ-1301, LJ-1304, LJ-1309, LJ-1310 LJ-1313, LJ-1317 and LJ-1319 Model C90A P/N 90-590024-61 S/N LJ-1367, LJ-1373, LJ-1377, LJ-1384, LJ-1386, LJ-1389, LJ-1394 and LJ-1397, LJ-1403, LJ-1411, LJ-1425, LJ-1431 and LJ-1435 Model C90A P/N 90-590024-69 S/N LJ-1353 through LJ-1726, LJ-1728 thru LJ-1753 and LJ-1755, except –61 manual serial. Model C90GT P/N 90-590024-111 S/N LJ-1727, LJ-1754, LJ-1756 thru LJ-1846, and LJ-1848 thru LJ-1852. Model C90GTi P/N 90-590024-163 S/N LJ-1847, LJ-1853 thru LJ-1963, LJ-1965, LJ-1967, LJ-1969 thru LJ-1971and LJ-1973 thru LJ-1976. Model C90GTi P/N 90-590024-217 S/N LJ-1964, LJ-1966, LJ-1968, LJ-1972, LJ-1977 thru LJ-2128. Model C90GTi P/N 434-590171-0003 S/N LJ-2129 and after. Refer to the Limitations Section of the FAA Approved Airplane Flight Manual or Pilot’s Operating Handbook for equipment requirements for flight into known icing conditions. NOTE 1 At the time of original certification, the following must be provided for each aircraft: current weight and balance data; loading information; list of equipment included in the empty weight. The Certificated Empty Weight must include unusable fuel and unusable (undrainable) oil as shown below: Fuel 15 lbs. (+162 in.) and oil 21 lbs. (+111 in.) for Models 65 (L-1 and up, LF-1 and up, and LC-1 through LC-229), 65-80, 65-A80, 65-A80-8800, 65-88 (except LP-28), 65-B80 (LD-270 through LD279 unless S.I. 0539-281 is incorporated). Fuel 30 lbs. (+170 in.) and oil 21 lbs. (+111in.) for Models 65 (LC-230 and up), 65-88 (LP-28 only), A65, A65-8200, 70, 65-B80 (LD-280 through LD-467 unless S.I. 0539-281 is incorporated). Fuel 96 lbs. (+168 in.) and oil 21 lbs. (+111 in.) for Model65-B80 (prior to LD-468 that have S.I. 0539-281 incorporated. Fuel 24 lbs. (+140 in.) and oil 16 lbs. (+101 in.) for Model 65-90. Fuel 24 lbs. (+140 in.) and oil 28 lbs. (+101 in.) for Models 65-A90. Fuel 24 lbs. (+140 in.) and oil 32 lbs. (+101 in.) for Models 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, and B90. The Basic Empty Weight must include unusable fuel and engine oil (includes capacity oil and undrainable, where applicable) as shown below: Fuel 96 lbs. (+168) and oil 81 lbs. (+131) for Model 65-B80 (LD-468 and up). Fuel 24 lbs. (+140) and oil 56 lbs. (+101) for Model C90, C90A, C90GT, H90 (T-44A) and C90GTi. Fuel 40 lbs. (+140) and oil 56 lbs. (+101) for Model E90. NOTE 2 The following placard must be displayed in full view of the pilot: “This airplane must be operated as a normal category airplane in compliance with the operation limitations stated in the form of placards, markings, and manuals.” 3A20 36 Rev. 82 Data Pertinent to All Models NOTE 3 Mandatory retirement time for all fuselage structural components of Models 65-88, 65-90, 65-A90, B90, and C90 (prior to LJ-1011 except LJ-986 and LJ-996) is 20,000 hours time in service. However, the Fuselage Life may be unlimited if the airplane is maintained and inspected at the required intervals in both Chapter 5 of the Airplane’s Maintenance Manual and Airworthiness Limitations Manual P/N 90-590024-187, latest revision. For the Model C90 (LJ-986, LJ-996, LJ-1011 and after), the retirement limit is 13,500 hours time in service. However, the Fuselage Life may be unlimited if the airplane is maintained and inspected at the required intervals in both Chapter 5 of the Airplane’s Maintenance Manual and Airworthiness Limitations Manual P/N 90-590024-187, latest revision. For the E90 and H90 fuselage pressure vessel structural life limit, refer to the latest revision of the airplane flight manual for mandatory retirement time. For the Model C90A and C90GT, the retirement limit is 13,500 hours time in service. However, the Fuselage Life may be unlimited if the airplane is maintained and inspected at the required intervals in both Chapter 5 of the Airplane’s Maintenance Manual and Airworthiness Limitations Manual P/N 90-590024-187, latest revision. Mandatory replacement time for the model 65-90, 65-A90, B90, C90, C90A and E90; serials LJ-1 through LJ-1084, LJ-1085, LJ-1087, LW-1 thru LW-347, for all wing attach bolts and nuts, is as required in Chapter 4-00-00 of the Airworthiness Limitations Manual P/N 90-590024-187, latest revision. Mandatory replacement time for Model C90A and C90GT; serials LJ-1086, LJ-1088 and after for upper and lower forward attach bolt, upper and lower aft wing attach bolt and nuts is as required in Chapter 4-00-00 of the Airworthiness Limitations Manual P/N 90-590024-187, latest revision. Mandatory replacement time for Model C90GTi, serials LJ-1847 and LJ-1853 and after for upper and lower forward attach bolt, upper and lower aft wing attach bolt and nuts is as required in Chapter 4-00-00 of the Airworthiness Limitations Manual P/N 90-590024-187, latest revision. NOTE 4 The maximum propeller shaft overspeed limits for Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, E90, and H90 (T-44A) is 104 percent at all ratings and may be employed for sustained periods in emergencies. 100 percent propeller shaft speed is defined as 2200 rpm and is the normal steady state operating limit. Gas generator speeds up to 102.7 percent are permissible for 10 seconds and to 101.6 percent for unlimited periods subject to applicable temperature and other limits. 100 percent gas generator speed is defined as 37,500 rpm. NOTE 5 Emergency use of MIL-G-5572: Grades 80/87, 91/98, 100/130, and 115/145 are permitted on Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, C90GT, E90, H90 (T-44A) and C90GTi for a total time period not to exceed 150 hours during any overhaul period. It is not necessary to purge the unused fuel from the system when switching fuel types. NOTE 6 Required for Model 65, S/N LC-163 through LC-239: 2 Lycoming IGSO-480-A1E6 engines. Aircraft prior to S/N LC-163 eligible for IGSO-480-A1E6 engines provided FAA approval related equipment is installed; such as, Bendix fuel injector, cockpit and engine control system, higher pressure engine and boost pumps, induction air modification, etc. Required for Model 65, S/N LC-163 thru LC-239: Hartzell HC-B3Z20-2A hub with 10151-8R or 10151B-8R aluminum alloy blades and 210365 Woodward governor. NOTE 7 Model 65-90 (S/N LJ-1 thru LJ-22) eligible for maximum landing weight of 8835 lb. and a maximum takeoff weight of 9300 lb. when modified per Beech Kit No. 90-4001. Subsequent serials are eligible for these weights. NOTE 8 Model 65-80 (S/N LD-1 thru LD-150, except LD-34) eligible for a maximum landing weight of 8000 lb. when modified per Beech Mod. C.O. C00766. 3A20 37 Rev. 82 Data Pertinent to All Models NOTE 9 Model 65-A80 (S/N LD-151 thru LD-269) eligible for a maximum landing and takeoff gross weight of 8800 lb. when modified per Beech dwg. 80-4004 which defines Modification Kit No. 80-4004-1 (S/N LD-254 thru LD-269) and Kit No. 80-4004-3 (S/N LD-151 thru LD-253). Upon completion of this modification, the aircraft is eligible for designation as a Model 65-A80-8800. NOTE 10 Flight idle at 2000 propeller rpm shall be an indicated 600  60 ft. -lb. torque corrected for sea level standard day. Secondary flight idle stop when installed shall be 210  40 propeller rpm higher than flight idle stop with a gas generator speed of 70%. NOTE 11 Model 65-90 (S/N LJ-1 thru LJ-113) (except LJ-76) are eligible for installation of PT6A-20 engines when modified in accordance with Beech Kit 90-9027 or 90-9027 and 90-9029. For airplane LJ-9, use Beech Kit 90-9007. For airplane LJ-24, use Beech dwgs. 90-9016 and 90-9023 for PT6A-20 engine installation. NOTE 12 Model 65-90 (S/N LJ-24) eligible for full feathering, three-bladed Hartzell HC-B3TN-3B/T10173E-8 reversing propeller installation when modified per Beech dwgs. 90-9016 and 90-9023. NOTE 13 Model 65-90 (S/N LJ-1 thru LJ-113) equipped with PT6A-6 engines eligible for full-feathering, three bladed Hartzell HC-B3TN-3B/T10173E-8 or HC-B3TN-3B/T10173B-8 reversing propeller installation when modified per Beech dwg. 90-9028. NOTE 14 Models A65 and A65-8200 (S/N LC-240 thru LC-335), 65-80, 65-A80, 65-A80-8800, 65-B80 (S/N LD-1 and up), and 70 (S/N LB-1 thru LB-35) eligible to operate with cabin door removed when operated as prescribed in Approved Airplane Flight Manual Supplement No. 130758. NOTE 15 Model 65, A65, 65-80, 65-A80, 65-A80-8800, 65-B80, 70 eligible for installation of cargo door when modified per Beech Kit No. 65-4014. NOTE 16 Model A65-8200 (S/N LC-273 thru LC-324) when manufactured per Beech dwg. 50-000200 and Model 70 (S/N LB-1 thru LB-35) are eligible for a maximum weight of 8200 lbs. and 11 place seating capacity. NOTE 17 Model 65-A90 (S/N LJ-76 and LJ-114 thru LJ-301) when modified per Beech Kit No. 90-4032, and Model 65-A90 (S/N LJ-302 thru LJ-317) when modified per Beech Kit No. 90-4032-1 eligible for maximum landing weight of 9168 lb. and a maximum takeoff weight of 9650 lb. NOTE 18 Model 65-A90 (S/N LJ-76 and LJ-114 thru LJ-317) when modified per Beech Kit No. 90-4035 eligible to move forward center of gravity limit 2.9 in. forward. NOTE 19 Model 65-A90 (S/N LJ-76 and LJ-114 thru LJ-301) when modified per Beech Kit Nos. 90-4031 or 90-4032 and 90-4035, and 65-A90, (S/N LJ-302 thru LJ317) when modified per Beech Kit Nos. 90-4031-1 or 90-4032-1 and 90-4035 eligible for maximum landing weight of 9168 lb., maximum takeoff weight of 9650 lb., and to move forward center of gravity limit 2.9 in. forward. NOTE 20 Model 65-B80 eligible for optional Cargo Baggage Pod installation when modified per Beech Kit No. 80-4013. NOTE 21 Model C90 aircraft, LJ-670 and LJ-584 thru LJ-667 except LJ-585, LJ-590, LJ-592, LJ-593, LJ-601, LJ-604, LJ-612, LJ-619, LJ-620, LJ-622, and LJ-652 are equipped with PT6A-20A engines. Model C90 Aircraft LJ-668, LJ-669, LJ-671 and after are equipped with PT6A-21 engines. Model C90 aircraft with PT6A-20A engines are eligible for installation of PT6A-21 engines when modified per Beech Kit Drawing No. 90-9066. NOTE 22 Model H90 (T-44A) airplanes are eligible for FAA certification as Model H90 aircraft when modifed as required by Beech Aircraft Corporation Drawing 90-005004. NOTE 23 Model H90 (T-44A) airplanes are licensed at gross weight of 9650 lb. and gross weight C.G. range of 150.6 to 160.0 inches at 9650 lb., and C.G. range of 144.7 to 160.0 inches at 7850 lb. or less. 3A20 38 Rev. 82 Data Pertinent to All Models NOTE 24 The following U-21 series aircraft are eligible for maximum takeoff weight of 10,200 lbs. and maximum landing weight of 9,700 lbs., when modified with Beech Kit 91-5002-1: a. 65-A90-1 (RU-21A) aircraft serial numbered LM-108 through LM-111. b. 65-A90-1 (RU-21H, GUARDRAIL V) aircraft serial numbered LM-101, LM-107, LM-115, LM-125, LM-127 thru LM-129, LM-132, LM-133, and LM-136 thru LM-138. c. 65-A90-4 (RU-21H, GUARDRAIL V) aircraft serial numbered LU-1 thru LU-15. These aircraft must be equipped with wingtip H.F. antenna pods and wingtip extensions, or equivalent ballast, as specified on Drawing 91-5001, in order to operate at the increased weights. NOTE 25 Export: a. The Beech Model C90 is eligible for export to United Kingdom when modified in accordance with Modification Drawing 90-005000. b. The Beech Model C90A is eligible for export to United Kingdom when modified in accordance with Modification Drawing 90-005006. The above models are eligible for return to U.S. certification when the modifications incorporated by the above drawings have been removed. NOTE 26 Models 65-90, 65-A90, B90, C90, C90A, C90GT, E90 and C90GTi are eligible for flight into known icing conditions when the required equipment is installed and operational. NOTE 27 Flight idle propeller low pitch stop is set so that at 2000 rpm the engine torque is 608  40 ft. lb. torque corrected to sea level standard day conditions. Ground idle low pitch stop is set so that at 58% to 60% N1, prop rpm is not less than 1100 rpm. NOTE 28 Model C90A Airplanes which incorporate MOD Drawing MOD005147-1 are limited to a maximum ramp weight of 10,059 lbs., a maximum takeoff weight of 9,999 lbs., and a maximum landing weight of 9,600 lbs. MOD Drawing MOD005147-1 requires an AFM and POH supplement PN 90-590024-81 and an operating weight limitation placard, MOD005147-3. Eligible Serial Numbers are LJ-1469 thru LJ-1726, LJ-1728 thru LJ-1753, and LJ-1755. NOTE 29 Company name change effective April 15, 1996. The following serial numbers are manufactured under the name of Raytheon Aircraft Company: C90A and C90GT: LJ-1437 through LJ-1826. NOTE 30 By model, any combination of reversing hub and blade part numbers listed is acceptable. It is permissible to mix blade part numbers on the same hub. NOTE 31 The maximum propeller shaft overspeed limit for the Model C90GT and C90GTi is 110 percent (2090 rpm). 100 percent propeller shaft speed is defined as 1900 rpm and is the normal steady state operating limit. Gas generator speeds up to 102.6 percent are permissible for 2 seconds and to 101.5 percent for unlimited periods subject to applicable temperature and other limits. 100 percent gas generator speed is defined as 37,500 rpm. NOTE 32 Flight idle propeller low pitch stop is set so that at 1800 rpm the engine torque is 545 -0/+40 ft. lb. torque corrected to sea level standard day conditions. NOTE 33 The following warning concerning propeller operation is in both the AFM and Maintenance Manual: “Stabilized ground operation within the propeller restricted RPM range can generate high propeller stresses and result in fatigue damage to the propeller. This damage can lead to a reduced propeller fatigue life, propeller, propeller failure and loss of control of the aircraft”. NOTE 34 Company name change effective 3-26-07. The following serial numbers are manufactured under the name of Hawker Beechcraft Corporation: LJ-1827 through LJ-2069. 3A20 39 Rev. 82 Data Pertinent to All Models NOTE 35 Company name change effective 4-12-13. The following serial numbers are manufactured under the name of Beechcraft Corporation: C90GTi: LJ-2070 through LJ-2124. NOTE 36. Company name change effective 10/12/16. The following serials are manufactured under the name Textron Aviation Inc.: C90GTi: LJ-2134 and after. NOTE 37. STC SA10747SC must be installed with the Rockwell Collins Pro Line Fusion® installation. NOTE 38. Installation of GPS-4000S due to in-draw of Rockwell Collins STC SA01848WI, which addressed the use of a multi-core processor and upgrading of the GPS-4000S receiver. ..... END ..... ``` ## ADs (93, first 50, in force first) - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2021-05-17](https://openairdocs.org/ad/2021-05-17): NAVIGATION SYSTEM · Rockwell Collins FDSA-6500, CL-600-2B16 (CL-604), 525B and 7 more. Effective Apr 29, 2021 - [AD 2020-25-01](https://openairdocs.org/ad/2020-25-01): Wings · Textron 100, 65-90, 65-A90 and 17 more. Effective Jan 11, 2021 - [AD 2012-21-06](https://openairdocs.org/ad/2012-21-06): Electric power · Textron C90GTi. Effective Nov 27, 2012 - [AD 2009-05-05](https://openairdocs.org/ad/2009-05-05): Primary Flight Displays · Avidyne Primary Flight Display (S-TEC STC SA09543AC-D or 2 others). Effective Apr 3, 2009 - [AD 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008 - [AD 2007-12-06](https://openairdocs.org/ad/2007-12-06): Flight controls · Textron B200, B200C, B300 and 2 more. Effective Jul 16, 2007 - [AD 2006-13-10](https://openairdocs.org/ad/2006-13-10): Rudder trim tab · Textron 100, 65-90, 65-A90 and 18 more. Effective Aug 7, 2006 - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2005-01-04](https://openairdocs.org/ad/2005-01-04): Fuel hose · Textron 100, 200, 200C and 29 more. Effective Feb 22, 2005 - [AD 2004-23-02](https://openairdocs.org/ad/2004-23-02): Nose Landing Gear (NLG) Fork · Textron 100, 1900, 1900C and 50 more. Effective Dec 23, 2004 - [AD 2004-17-02](https://openairdocs.org/ad/2004-17-02): Cross shaft attach bolt · Textron 100, 1900, 1900C and 52 more. Effective Oct 4, 2004 - [AD 2003-13-16](https://openairdocs.org/ad/2003-13-16): Aft Pressure Bulkhead of Fuselage · Textron 100, 200, 200C and 33 more. Effective Aug 25, 2003 - [AD 2003-02-03](https://openairdocs.org/ad/2003-02-03): Airstair door and emergency exits · Textron 100, 200, 2000 and 46 more. Effective Mar 7, 2003 - [AD 2002-14-19](https://openairdocs.org/ad/2002-14-19): Collins Air Data Computers (ADC) · Boeing DC-8-11, DC-8-12, DC-8-21 and 36 more. Effective Aug 23, 2002 - [AD 2002-10-13](https://openairdocs.org/ad/2002-10-13): Exterior Door Operating Procedures · Textron 58P, 60, 65-88 and 2 more. Effective Jul 8, 2002 - [AD 2002-09-12](https://openairdocs.org/ad/2002-09-12): Rivets in Left- and Right-Hand Nacelle and Spar Assembly · Textron C90A. Effective Jun 21, 2002 - [AD 2002-01-10](https://openairdocs.org/ad/2002-01-10): Main Landing Gear Torque Knees · Textron 65-90, 65-A90, 65-A90-1 and 6 more. Effective Feb 22, 2002 - [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001 - [AD 2001-15-17](https://openairdocs.org/ad/2001-15-17): Transponder Control Panels · Bombardier ATR42-200, ATR42-300, ATR42-320 and 30 more. Effective Aug 20, 2001 - [AD 2001-11-03](https://openairdocs.org/ad/2001-11-03): Blower Motor Circuit · Textron 1900D, 58, 58A and 5 more. Effective Jul 20, 2001 - [AD 2000-18-02](https://openairdocs.org/ad/2000-18-02): Elevator Skin Assemblies · Textron 56TC, 58, 58P and 12 more. Effective Sep 22, 2000 - [AD 99-05-13 R1 WD](https://openairdocs.org/ad/99-05-13-R1-WD): Withdrawal of AD 99-05-13 · Beech B17B, B17L, B17R (Army UC-43H) and 107 more. Effective Jul 5, 2000 - [AD 2000-02-15](https://openairdocs.org/ad/2000-02-15): Engine and Propeller Configuration · Walter Motorlet M601E-11 engine model and Avia-Hamilton… (Phoenix STC SA01366AT). Effective Feb 18, 2000 - [AD 99-18-15](https://openairdocs.org/ad/99-18-15): Landing Gear Emergency Hand Pumps · Textron 1900D, B200, B300 and 1 more. Effective Sep 27, 1999 - [AD 99-10-07](https://openairdocs.org/ad/99-10-07): Elevator Control Cable · Textron 65-90, 65-A90, 65-A90-1 and 9 more. Effective Jun 8, 1999 - [AD 99-09-10](https://openairdocs.org/ad/99-09-10): Landing Gear Hand Pump · Textron 200CT, 300, A200CT (C-12D) and 19 more. Effective Jun 7, 1999 - [AD 99-09-15](https://openairdocs.org/ad/99-09-15): Flight Control Mechanism · Textron 1900D, 58, 58A and 5 more. Effective May 18, 1999 - [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998 - [AD 98-04-24](https://openairdocs.org/ad/98-04-24): AFM - Limitations Section - Icing · Textron 100, 300, 58 and 13 more. Effective Mar 13, 1998 - [AD 97-25-03](https://openairdocs.org/ad/97-25-03): AFM - Limitations - Power Levers · Textron 100, 1900, 1900C and 44 more. Effective Jan 21, 1998 - [AD 97-25-01](https://openairdocs.org/ad/97-25-01): Outflow/Safety Valve · Textron 100, 200, 2000 and 38 more. Effective Jan 11, 1998 - [AD 97-23-17](https://openairdocs.org/ad/97-23-17): Pneumatic Tubing · Textron 200, 200C, 200CT and 30 more. Effective Dec 29, 1997 - [AD 97-16-10](https://openairdocs.org/ad/97-16-10): Filters · Cessna 310R, T310R, 36 and 17 more. Effective Sep 18, 1997 - [AD 97-06-06](https://openairdocs.org/ad/97-06-06): Pilot and Copilot Chairs Locking Pins · Textron 100, 1900, 1900C and 43 more. Effective May 9, 1997 - [AD 95-26-15 R1](https://openairdocs.org/ad/95-26-15-R1): Traffic Alert and Collision Avoidance Systems · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 159 more. Effective Dec 26, 1996 - [AD 96-11-12](https://openairdocs.org/ad/96-11-12): Elevator Electric Trim Tab Or Autopilot System · Textron C90A. Effective Jul 24, 1996 - [AD 96-03-13](https://openairdocs.org/ad/96-03-13): Main Landing Gear Drag Leg Lock Link · Textron 100, 200, 200C and 24 more. Effective Apr 1, 1996 - [AD 95-20-01 R1](https://openairdocs.org/ad/95-20-01-R1): Placard - Cabin Door · Textron 65. Effective Nov 3, 1995 - [AD 94-01-05](https://openairdocs.org/ad/94-01-05): Traffic Alert and Collision Avoidance System II Processors · Airbus A340-211, A340-212, A340-213 and 85 more. Effective Feb 4, 1994 - [AD 94-01-06](https://openairdocs.org/ad/94-01-06): Traffic Alert and Collision Avoidance System II Processors · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 176 more. Effective Feb 4, 1994 - [AD 93-17-01](https://openairdocs.org/ad/93-17-01): Leading Edge Fuel Cell Nipples · Textron B90, C90 and C90A. Effective Oct 12, 1993 - [AD 92-15-01](https://openairdocs.org/ad/92-15-01): Truss-To-Firewall Bolts · Textron 100, 200, 200C and 40 more. Effective Aug 21, 1992 - [AD 90-08-17](https://openairdocs.org/ad/90-08-17): Fuselage Moisture Drain System · Textron 100, 200, 200C and 32 more. Effective May 7, 1990 - [AD 89-25-08](https://openairdocs.org/ad/89-25-08): Wing Main Spar Inspection · Textron 65, 65-80, 65-A80 and 1 more. Effective Jan 4, 1990 - [AD 89-25-10](https://openairdocs.org/ad/89-25-10): Wing Main Spar Inspection · Textron 100, 65-90, 65-A90 and 10 more. Effective Jan 4, 1990 - [AD 89-22-14](https://openairdocs.org/ad/89-22-14): Aileron Flutter · Textron 200, 200C, 200CT and 9 more. Effective Nov 17, 1989 - [AD 88-04-07](https://openairdocs.org/ad/88-04-07): Wing Spar Nuts Inspection · Textron 100, 65, 65-80 and 18 more. Effective Apr 18, 1988 - [AD 87-04-24](https://openairdocs.org/ad/87-04-24): Elevator Trim Cable System · Textron 1900, 1900C, 200 and 28 more. Effective Apr 14, 1987 All 93: https://openairdocs.org/tcds/3A20/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Beech C90](https://openairdocs.org/model/beech-c90): 216 aircraft (registry codes 1152913, 1153928) - [Raytheon C90A](https://openairdocs.org/model/raytheon-c90a): 155 aircraft (registry code 7150004) - [Beech E-90](https://openairdocs.org/model/beech-e-90): 145 aircraft (registry code 1152914) - [Beech C90A](https://openairdocs.org/model/beech-c90a): 125 aircraft (registry codes 1152911, 115291A) - [Beech 65-A90-1](https://openairdocs.org/model/beech-65-a90-1): 90 aircraft (registry code 1152901) - [Hawker Beechcraft C90GTI](https://openairdocs.org/model/hawker-beechcraft-c90gti): 57 aircraft (registry code 4220017) - [Beech 65-A90](https://openairdocs.org/model/beech-65-a90): 34 aircraft (registry code 1152908) - [Beech B90](https://openairdocs.org/model/beech-b90): 29 aircraft (registry code 1152912) - [Raytheon C90GT](https://openairdocs.org/model/raytheon-c90gt): 25 aircraft (registry code 7150062) - [Beech 65](https://openairdocs.org/model/beech-65): 22 aircraft (registry code 1152802) - [Beechcraft C90GTI](https://openairdocs.org/model/beechcraft-c90gti): 17 aircraft (registry code 4220030) - [Beech 65-B80](https://openairdocs.org/model/beech-65-b80): 15 aircraft (registry code 1152812) - [Beech 65-A90-4](https://openairdocs.org/model/beech-65-a90-4): 13 aircraft (registry code 1152811) - [Beech 65-90](https://openairdocs.org/model/beech-65-90): 7 aircraft (registry code 1152904) - [Beech 65 (LF-23F)](https://openairdocs.org/model/beech-65-lf-23f): 6 aircraft (registry code 1152804) - [Beech A65](https://openairdocs.org/model/beech-a65): 6 aircraft (registry code 1152803) - [Hawker Beechcraft C90GT](https://openairdocs.org/model/hawker-beechcraft-c90gt): 6 aircraft (registry code 4220002) - [Textron C90GTI](https://openairdocs.org/model/textron-c90gti): 6 aircraft (registry code 4226568) - [Beech 70](https://openairdocs.org/model/beech-70): 4 aircraft (registry code 1152807) - [Beech 65-88](https://openairdocs.org/model/beech-65-88): 3 aircraft (registry code 1152809) - [Beech 65-A80](https://openairdocs.org/model/beech-65-a80): 3 aircraft (registry code 1152808) - [Beech 65-A80-8800](https://openairdocs.org/model/beech-65-a80-8800): 3 aircraft (registry code 1152810) - [Beech 65-80](https://openairdocs.org/model/beech-65-80): 2 aircraft (registry code 1152806) - [Beech 65 (L23F)](https://openairdocs.org/model/beech-65-l23f): 1 aircraft (registry code 1152798) - [Beech 65-A90-1 (U-21A)](https://openairdocs.org/model/beech-65-a90-1-u-21a): 1 aircraft (registry code 1152895) - [Beech A65-8200](https://openairdocs.org/model/beech-a65-8200): 1 aircraft (registry code 1152805) - [Monocoupe 70](https://openairdocs.org/model/monocoupe-70): 1 aircraft (registry code 9250212) - [Raytheon E90](https://openairdocs.org/model/raytheon-e90): 1 aircraft (registry code 7150051) - [Rockwell International 65](https://openairdocs.org/model/rockwell-international-65): 1 aircraft (registry code 7630704) - [Beech H90 (T-44A)](https://openairdocs.org/model/beech-h90-t-44a): 0 aircraft (registry code 1152939) ## STCs approved under this data sheet (616, first 50) - [STC SA02054SE](https://openairdocs.org/stc/SA02054SE): Installation of winglets and related system changes.. 3S Certification, LLC - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc. - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position Light System, and applicable associated power supplies. Whelen Aerospace Technologies - [STC SA02133SE](https://openairdocs.org/stc/SA02133SE): Installation of a Luma Technologies LT-4500 Series Integrated Light\Emitting Diode (LED) Display Panel and LT-3500 LED light modules. Luma Technologies LLC - [STC SA12345IB](https://openairdocs.org/stc/SA12345IB): Replacement of the Halon Type 1211 portable fire extinguisher with the Halotron BrX portable fire extinguisher. Cessna Duesseldorf Citation Service Center GmbH - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA03930NY](https://openairdocs.org/stc/SA03930NY): Installation of King Air Belly Payload Mount. Icarus Aero Inc. - [STC SA02017WI](https://openairdocs.org/stc/SA02017WI): The Installation of the Parker-Meggitt iPRESS™ System. 3S Certification LLC - [STC SA01638WI](https://openairdocs.org/stc/SA01638WI): Part Fabrication and Installation of Arm Ledge System and Table Assembly for aircraft cabin interior. Aviation Fabricators Inc. - [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc. - [STC SA12202IB](https://openairdocs.org/stc/SA12202IB): Installation of Garmin GWX Weather Radar System. Maxcraft Avionics Ltd. - [STC SA10800SC](https://openairdocs.org/stc/SA10800SC): Installation of a 3-tube Rockwell Collins IDS-3000 Electronic Flight Instrument System with File Server Unit (FSU).. BHE & Associates LTD - [STC SA10966SC](https://openairdocs.org/stc/SA10966SC): Installation of upgraded hardware to the Rockwell Collins Pro Line 21 FMS-3000 to provide Localizer Performance with Vertical Guidance (LPV). BHE & Associates LTD - [STC SA11300DS](https://openairdocs.org/stc/SA11300DS): Upgrade previously installed Collins Aerospace Radar Altimeter. BHE & Associates Ltd. - [STC SA10370SC](https://openairdocs.org/stc/SA10370SC): Installation of exhaust gas extractors on Pratt & Whitney Canada PT6A-21, -28, -29, -34, -34B, -135, or -135A turboprop engines. Metrea Special Aerospace ISR Inc. - [STC SA01663CH-D](https://openairdocs.org/stc/SA01663CH-D): Installation of an L-3 Communications Avionics Systems Terrain Awareness & Warning System TAWS 8000 or TAWS 8100.. Acron Aviation Inc. - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA378CH](https://openairdocs.org/stc/SA378CH): Installation of TCAS I.. Acron Aviation Inc. - [STC SA9210SC-D](https://openairdocs.org/stc/SA9210SC-D): Installation of the L-3 Communications Avionics Systems Infrared Imaging System (IRIS). Acron Aviation Inc. - [STC SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica Cellular Module (avCM. Aircraft Systems and Manufacturing Inc. - [STC SA11301DS](https://openairdocs.org/stc/SA11301DS): Installation of an AirSync flight data monitoring system. BHE & Associates Ltd. - [STC SA01848WI](https://openairdocs.org/stc/SA01848WI): Modification of a Rockwell Collins Global Positioning System (GPS). Rockwell Collins Inc. - [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC - [STC SA10935SC](https://openairdocs.org/stc/SA10935SC): Remove existing Pratt & Whitney Canada PT6A-20 engines and install PT6-21, -28, or -34 engines. CenTex Aerospace Inc. - [STC SA04051CH](https://openairdocs.org/stc/SA04051CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA01456WI-D](https://openairdocs.org/stc/SA01456WI-D): Installation of the Garmin G1000 Integrated Avionics System and GFC 700 Automatic Flight Control System.. Garmin International Inc. - [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc. - [STC SA01454CH](https://openairdocs.org/stc/SA01454CH): Installation of Butterfield Industries Oil Residue Collection System, kit Part Number BI 8030-1. Raisbeck Engineering Inc. - [STC SA01800CH](https://openairdocs.org/stc/SA01800CH): Installation of Butterfield Industries Oil Residue Collection System, kit Part Number BI 2001-1. Raisbeck Engineering Inc. - [STC SA02620SE](https://openairdocs.org/stc/SA02620SE): Installation of Butterfield Industries Air/Oil Separator System, kit Part Number BI 8055-1. Raisbeck Engineering Inc. - [STC SA2116NM](https://openairdocs.org/stc/SA2116NM): Installation of Raisbeck fully enclosed main landing gear doors. Raisbeck Engineering Inc. - [STC SA2133NM](https://openairdocs.org/stc/SA2133NM): Installation of fully enclosed main landing gear doors. Raisbeck Engineering Inc. - [STC SA2623NM](https://openairdocs.org/stc/SA2623NM): Installation of fully enclosed main landing gear door system and associated actuation mechanism. Raisbeck Engineering Inc. - [STC SA2939NM](https://openairdocs.org/stc/SA2939NM): Installation of nacelle overwing storage lockers and lower flap fairing.. Raisbeck Engineering Inc. - [STC SA3593NM](https://openairdocs.org/stc/SA3593NM): Installation of Raisbeck/Hartzell Quiet Turbofan Propellers or Swept Turbofan Propellers, and optional Increased Gross Weight. Raisbeck Engineering Inc. - [STC SA3683NM](https://openairdocs.org/stc/SA3683NM): Installation of exhaust stack fairings.. Raisbeck Engineering Inc. - [STC SA4010NM](https://openairdocs.org/stc/SA4010NM): Installation of lower aft fuselage strakes.. Raisbeck Engineering Inc. - [STC SA02014WI](https://openairdocs.org/stc/SA02014WI): Installation of a swept vertical stabilizer and rudder assembly.. Bemidji Aviation Services, Inc. - [STC SA01814AT-D](https://openairdocs.org/stc/SA01814AT-D): Modification of Nose Gear Doors. Summit Aviation Inc. - [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine - [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics - [STC SA02372AK](https://openairdocs.org/stc/SA02372AK): Installation of the Max-Viz Enhanced Vision System (EVS) Model-1500 or 2300 Enhanced Vision System (EVS). Avio Design Group Inc. All 616: https://openairdocs.org/tcds/3A20/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.