# TCDS A24CE: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 132 - Revised: August 21, 2026 - Product: Aircraft, Small/Large Airplane - Certification basis: Part 23, Part 25 - Registered aircraft: 2,074, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/45/91/4591b36127f8a54f60fe77fc8a714d6ea071f459043b8ef9607b33ad4c621ad4 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID149435635720260821194755.0001 - Page: https://openairdocs.org/tcds/A24CE ## Models (37) As the data sheet lists them. - B200CT (Super King Air) - A200 (C-12C) - A100-1 (U-21J) - 200 (Super King Air) - B200C (C-12F) - B300C - A200CT (FWC-12D) - A200CT (RC-12H) - A200CT (RC-12Q) - 1900C ((C-12J) Airliner) - A200C (UC-12B) (Super King Air) - A200CT (RC-12G) (Super King Air) - B200C (Super King Air) - A200 (C-12A) - A200CT (C-12F) - A200CT (C-12D) (Super King Air) - B300C (MC-12W) (Super King Air 350C) - 1900C (C-12J) - 300 (Super King Air) - 1900 (Airliner) - A200CT (RC-12P) - 200CT (Super King Air) - B200C (UC-12M) - 200T (Super King Air) - 1900D (Airliner) - 300LW - B200CGT - B200C (UC-12F) - B200 (Super King Air) - B300C (UC-12W) - B200T (Super King Air) - A200CT (RC-12K) - 200C (Super King Air) - B200C (C-12R) - B200GT - B300 (Super King Air 350) - A200CT (RC-12D) ## 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 Rev. No. 132 101 104 97 82 97 82 99 97 101 111 104 96 101 101 128 Page No 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Rev. No. 132 130 132 95 91 108 128 132 132 101 130 101 100 78 101 110 Page No 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 Rev. No. 122 122 132 132 127 132 122 124 132 132 132 132 130 130 131 132 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A24CE Revision 132 Textron Aviation 200 A100-1 (U-21J) 200C A200 (C-12A) 200CT A200 (C-12C) 200T A200C (UC-12B) B200 A200CT (C-12D) B200C A200CT (FWC-12D) B200CT A200CT (C-12F) B200T A200CT (RC-12D) 300 A200CT (RC-12G) 300LW A200CT (RC-12H) B300 A200CT (RC-12K) B300C A200CT (RC-12P) B300C (MC-12W) A200CT (RC-12Q) B300C (UC-12W) B200C (C-12F) 1900 B200C (UC-12M) 1900C B200C (C-12R) 1900C (C-12J) B200C (UC-12F) 1900D B200GT B200CGT August 21, 2026 TYPE CERTIFICATE DATA SHEET NO. A24CE This data sheet which is part of Type Certificate No. A24CE 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 on October 12, 2016. A24CE 2 Rev. 132 I. Model 200, Super King Air (Normal Category), Approved December 14, 1973 (See NOTES 10 & 11) Model A200C (UC-12B), Super King Air (Normal Category), Approved February 21, 1979 (See NOTE 11) Model 200C, Super King Air (Normal Category), Approved February 21, 1979 (See NOTE 11) Model B200, Model B200C, Super King Air (Normal Category), Approved February 13, 1981 (See NOTES 10 & 11) Model B200C (C-12F) (UC-12F) (UC-12M) (C-12R), Super King Air (Normal Category), Approved February 13, 1981 (See NOTES 10, 11 & 12) NOTES: refer to Data Pertinent to all Model 200 series Engine Two United Aircraft of Canada or Pratt & Whitney PT6A-41 (turboprop) per Beech Specification BS 22096. Models 200, 200C, A200C. Two United Aircraft of Canada or Pratt & Whitney PT6A-42 (turboprop) per Beech Specification BS 23319/1. Models B200, B200C. 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; in addition, for Models B200 and B200C, Chinese No. 3 Jet Fuel (See NOTE 6 for emergency fuels). Oil (Engine & Gearbox) UACL PT6 Engine Service Bulletin No. 3001 lists approved brand oils Engine Limits Shaft Horsepower Torque Ft-Lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff (5 min.) 850 2230 101.5% 2000* 750 (200, 200C, A200C) Max. continuous 850 2230 101.5% 2000* 750 (200, 200C, A200C) Takeoff (5 min.) 850 101.5% 2000* 800 (B200, B200C) Max. continuous 850 101.5% 2000* 800 (B200, B200C Starting transient (5 sec.) 1000 Max. reverse (1 min.) 88% 1900 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: Minus 40˚ C. minimum starting Minus 40˚ C. to 99˚ C. low idle 10˚ C. to 99˚ C. max. continuous Propeller and Two Hartzell HC-B3TN-3G or HC-B3TN-3N hubs with Hartzell T10178B-3R or Propeller Limits T10178NB-3R blades for S/N: BB-1 thru BB-815; BB-817 through BB-824; BL-1 thru BL-29; BJ-1 & On. OR Hartzell T10178K-3R or T10178NK-3R blades for S/N: BB-816, BB-825 thru BB-1438, BB-1440 thru BB-1443; BL-30 thru BL-72; BL-124 thru BL-138; BU-1 & On. Diameter: 98.5 in. (maximum); minimum allowable for repair, 97.5 in. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5(a) Secondary Flight Idle Stop See NOTE 5(b) Reverse - 9˚ Feathered +90˚ Rev. 132 3 A24CE I. Models 200, A200C, 200C, B200, B200C (cont’d) Propeller and Two McCauley 4HFR34C754 hubs with McCauley 94LA-0 blades Propeller Limits Diameter: 94 in. (maximum); minimum allowable for repairs: 93 in. (B200C S/N: BL-73 No further reduction permitted thru BL-123)(C-12F) Pitch settings: Flight Idle Stop See NOTE 13(a) Ground Idle Stop See NOTE 13(b) Reverse -10.0˚ + 0.4˚ Continuous operation on the ground is prohibited between 600 and 1150 r.p.m. The propeller must be feathered to ground idle at rotational speeds below 600 propeller shaft r.p.m. Propeller and Two McCauley 3GFR34C702 hubs with McCauley 100LA-2 blades Propeller Limits Diameter: 98 in. (maximum); minimum allowable for repair, 97 in. (B200 S/N: BB-1193 No further reduction permitted. thru BB-1438, BB-1440 Pitch settings: thru BB-1443, BB-1463) Flight Idle Stop See NOTE 5(a) (B200C S/N: BL-124 Reverse -10˚ thru BL-138, BP-64 & On, Feathered +86.8˚ and BV-1 & On) Propeller and Two McCauley 4HFR34C771 hubs with McCauley 94LA-O blades. Propeller Limits Diameter: 94 in. (maximum); minimum allowable for repairs, 93.5 in. (B200 S/N: BB-1439, No further reduction permitted BB-1444 & On, Pitch settings: except BB-1463) Flight Idle Stop See NOTE 13(a) (B200C S/N: BL-139 Reverse -10.0˚ + 0.4˚ & On, BW-1 & On) Feathered +87.5˚ + 0.3˚ Continuous operation on the ground is prohibited between 600 and 1100 r.p.m. The propeller must be feathered at rotational speeds below 600 propeller shaft r.p.m. OR Two Hartzell HC-E4N-3G hubs with Hartzell D9390SK-1R blades. Diameter: 93 in. (maximum); Minimum Allowable for repairs: 92 in. No further reduction permitted. Pitch Settings: Flight Idle Stop See NOTE 13(c) Reverse -11.2˚ + 0.5˚ Feathered +85.8˚ + 0.5˚ Continuous operation on the ground is prohibited between 500 and 1,180 r.p.m. The propeller must be feathered at rotational speeds below 500 propeller shaft r.p.m. OR Two Hartzell HC-B3TN-3G or HC-B3TN-3N hubs with Hartzell T10178B-3R or T10178NB-3R blades Diameter: 98.5 in. (maximum); minimum allowable for repair: 97.5 in. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5(a) Secondary Flight Idle Stop See NOTE 5(b) Reverse -9˚ Feathered +90˚ A24CE 4 Rev. 132 I. Model 200, Model A200C, Model 200C, Model B200, Model B200C (cont’d) Airspeed Limits Max. operating speed 310 m.p.h. (270 knots) up to 8,500 ft. (CAS) Max. operating Mach No. 0.48 The above airspeed limits S/Ns BB-2; BB-6 through BB-198 Max. operating speed 299 m.p.h. (260 knots) up to 15,000 ft. Max. operating Mach No. 0.52 The above airspeed limits S/Ns BB-199 & On, BL-1 & On, BJ-1 & On, BP-64 & On, BU-1 & On, BV-1 & On, BW-1 & On Maneuvering speed 209 m.p.h. (182 knots) Max. flap extension speed Approach position 14° 230 m.p.h. (200 knots) 100% position 35° 165 m.p.h. (144 knots) (200, 200C, A200C) 100% position 35° 178 m.p.h. (155 knots) (B200, B200C) Landing gear extended 209 m.p.h. (182 knots) Landing gear operating Extension 209 m.p.h. (182 knots) Retraction 188 m.p.h. (164 knots) C.G. Range (Landing (+185.0) to (+196.4) at 12,500 lbs. Gear Extended) (+181.0) to (+196.4) at 11,279 lbs., or less Straight line variation between points given moment change due to retracting landing gear: 5552 in.-lb. (Standard landing gear), or moment change due to retracting landing gear: 6040 in.-lb. (High-flotation landing gear) Empty Wt. C.G. Range None Maximum Weight Ramp 12,590 lbs. Takeoff 12,500 lbs. Landing 12,500 lbs. Zero fuel 10,400 lbs. (See NOTE 1 for Models 200, 200C) Zero fuel 11,000 lbs. (See NOTE 1 for Models B200, B200C, A200C) Minimum Crew One pilot One pilot and one copilot for FAR 135 operation, Model B200 High Density Configuration (See NOTE 11). No. of Seats and Maximum 15 (including crew at +129). See Loading Instructions in the Pilot’s Cabin Loading Operating Cabin Loading Handbook for approved seating and cargo configurations. Maximum Baggage 410 lbs. (+325): Models 200, A200C, 200C, B200, prior to BB-1091; Model B200C prior to BL-58. 550 lbs. (+325): Models B200, BB-1091 & On. Model B200C, BL-58 & On, BP-64 & On, BU-1 & On, BV-1 & On, BW-1 & On. Models 200, 200C, B200 prior to BB-1091. Model B200C prior to BL-58 when kit 101-5068-1 is installed. 350 lbs., nose (+70). 260 lbs., pod forward (+165). 195 lbs., pod aft (+214). 510 lbs., aft cabin (+325): Model B200 High Density Configuration (See NOTE 11). Fuel Capacity Tank Cap. Gal. Usable Gal. Arm Auxiliary LH 79.5 79 +204 Auxiliary RH 79.5 79 +204 Main LH 195 193 +185 Main RH 195 193 +185 See NOTE 1(a) for data on unusable fuel Engine Oil Capacity 18.4 qt. total (9.2 qt. each engine) at +131 (includes 6 qt usable in each integral engine tank) (See NOTE 1(c) for data on unusable oil). Rev. 132 5 A24CE I. Model 200, Model A200C, Model 200C, Model B200, Model B200C (cont’d) Maximum Operating 35,000 ft.: S/Ns BB-38, BB-39, BB-42, BB-44, BB-54, & On,* Altitude BL-1 & On, BP-64 & On, BU-1 & On, BV-1 & On, BW-1 & On. 31,000 ft.: S/Ns prior to BB-54, except BB-38, BB-39, BB-42, and BB-44; BJ-1 & On (*And any earlier airplanes modified by Beechcraft Kits 101-5007 and 101-5008 in compliance with Beechcraft Service Instruction Number 0776-341.) 25,000 ft., Model B200 High Density Configuration (See NOTE 11). For FAR Part 91 or 135 Operations: as limited by Part 91 or 135 (as appropriate) Control Surface Movements Wing flap Maximum 35˚ Aileron tabs Up 15˚ Down 15˚ Aileron Up 25˚ Down 15˚ Elevator tabs Up 3˚ 30' Down 13˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Model Serial Numbers Eligible 200 BB-2, BB-6 thru BB-733, BB-735 thru BB-792, BB-794 thru BB-828, BB-830 thru BB-853, BB-871 thru BB-873, BB-892, BB-893, BB-895, BB-912, BB-991 200C BL-1 thru BL-36 A200C BJ-1 & On B200 BB-734, BB-793, BB-829, BB-854 thru BB-870, BB-874 thru BB-891, BB-894, BB-896 thru BB-911, BB-913 thru BB-990, BB-992 thru BB-1313, BB-1315 thru BB-1384, BB-1389 & On (See NOTES 23 & 24) B200C BL-37 & On, BP-64 & On, BU-1 thru BU-10, BV-1 thru BV-10, BW-1 & On (See NOTE 23) II. Model A200, Super King Air, (C-12A) or (C-12C) (Normal Category), Approved June 20, 1975 (See NOTE 11) NOTES: refer to Data Pertinent to all Model 200 series Engine Two United Aircraft of Canada or Pratt & Whitney PT6A-38 (turboprop) per Beech Specification BS 22550. Airplane S/N BC-1 thru BC-61 and BD-1 & On (C-12A) Two United Aircraft of Canada or Pratt & Whitney PT6A-41 (turboprop) per Beech Specification BS 22096. Airplane S/N BC-62 & On (C-12C) plus BC-1 thru BC-61 and BD-1 thru BD-30 (C-12A) when modified per Beech Service Instruction C-12-0076 (See NOTE 15). 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 6 for emergency fuels). Oil (Engine & Gearbox) UACL PT6 Engine Service Bulletin No. 3001 lists approved brand oils. A24CE 6 Rev. 132 II. Model A200 (cont’d) Engine Limits Shaft Horsepower Torque Ft-Lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff (5 min.) 750* 1970** 101.5% 2000*** 705**** Max. continuous 750 1970** 101.5% 2000*** 705**** Starting transient (5 sec.) 1000 Max. reverse (1 min.) 88% 1900 705**** (*See NOTE 8) (**See NOTE 14) (***See NOTE 4) (****See NOTE 9) 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: Minus 40˚C. minimum starting Minus 40˚C. to 99˚C. low idle 10˚C. to 99˚C. max. continuous Propeller and Two Hartzell HC-B3TN-3G or HC-B3TN-3N hubs with Hartzell T10178B-3R or Propeller Limits T10178NB-3R blades Diameter: 98.5 in. (maximum); minimum allowable for repair, 97.5 in. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5(a) Secondary Flight Idle Stop See NOTE 5(b) Reverse -9˚ Feathered +90˚ Airspeed Limits Max. operating speed 310 m.p.h. (270 knots) up to 8,500 ft. (CAS) Max. operating Mach No. 0.48 The above airspeed limits BC-1 thru BC-61 and BD-1 & On (C-12A) Max. operating speed 299 m.p.h. (260 knots) up to 15,000 ft. Max. operating Mach No. 0.52 The above airspeed limits BC-62 & On, BC-1 thru BC-61, BD-1 thru BD-30 when modified per Beech Service Instructions C-12-0076 (C-12C) Maneuvering speed 209 m.p.h. (182 knots) Max. flap extension speed Approach position 14˚ 230 m.p.h. (200 knots) 100% position 35˚ 165 m.p.h. (144 knots) Landing gear extended 209 m.p.h. (182 knots) Landing gear operating Extension 209 m.p.h. (182 knots) Retraction 188 m.p.h. (164 knots) C.G. Range (Landing (+185.0) to (+196.4) at 12,500 lbs. Gear Extended) (+181.0) to (+196.4) at 11,279 lbs. or less Straight line variation between points given Moment changes due to retracting landing gear: 5552 in.-lbs. (Standard landing gear) Moment changes due to retracting landing gear: 6040 in.-lbs. (HI-Float landing gear) Empty Wt. C.G. Range None Maximum Weight Ramp 12,590 lbs. Takeoff 12,500 lbs. Landing 12,500 lbs. Zero fuel 10,400 lbs. (See NOTE 1) Rev. 132 7 A24CE II. Model A200 (cont’d) Minimum Crew One pilot No. of Seats Maximum 15 (including crew at +129). See loading instructions in the AFM for approved seating and cargo configurations. (NOTE: AFM revision may be required to include the approved seating and cargo configurations.) Maximum Baggage 150 lbs. (+292), and 350 lbs. (+325) 150 lbs. (+292), and 410 lbs. (+325): S/N BC-30 & On Fuel Capacity Tank Cap. Gal. Usable Gal. Arm Auxiliary LH 79.5 79 +204* Auxiliary RH 79.5 79 +204* Main LH 195 193 +185 Main RH 195 193 +185 *See NOTE 7 See NOTE 1(a) for data on unusable fuel Engine Oil Capacity 31 qt. total at +131 (includes 12 qt usable in two integral engine tanks) (See NOTE 1(c) for data on unusable oil). Maximum Operating 31,000 ft. Altitude FAR Part 91 Operations, as limited by Part 91. Control Surface Movements Wing flap Maximum 35˚ Aileron tabs Up 15˚ Down 15˚ Aileron Up 25˚ Down 15˚ Elevator tabs Up 3˚ 30' Down 13˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Serial Nos. Eligible (C-12A): BC-1 thru BC-61. (C-12C) BC-62 & On, BD-1 & On (C-12C): BC-62 thru BC-75 and BD-1 thru BD-30 when modified per Beech Service Instructions C-12-0076 III. Model 200T, Super King Air (Normal Category), Approved December 15, 1976 Model 200CT, Super King Air (Normal Category), Approved February 21, 1979 Model A200CT (C-12D), (FWC-12D), (RC-12D), (C-12F), (RC-12G), (RC-12H), Super King Air (Normal Category), Approved April 17, 1980 (See NOTES 10, 11, 12 & 16) Model B200T, Model B200CT, Super King Air (Normal Category), Approved February 13, 1981 NOTES: refer to Data Pertinent to all Model 200 series Engine Two United Aircraft of Canada or Pratt & Whitney PT6A-41 (turboprop) per Beech Specification BS 22096. Models 200T, 200CT, A200CT (BP-1 thru BP-51). Two United Aircraft of Canada or Pratt & Whitney PT6A-42 (turboprop) per Beech Specification BS 23290. Models B200T, B200CT, A200CT (BP-52 thru BP-63). 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 6 for emergency fuels). Oil (Engine & Gearbox) UACL PT6 Engine Service Bulletin No. 3001 lists approved brand oils. A24CE 8 Rev. 132 III. Models 200T, 200CT, A200CT, B200T, B200CT (cont’d) Engine Limits Shaft Horsepower Torque Ft-Lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff (5 min.) 850 2230 101.5% 2000* 750 (200T, 200CT, A200CT) (BP-1 thru BP-51) Max. continuous 850 2230 101.5% 2000* 750 (200T, 200CT, A200CT) (BP-1 thru BP-51) Takeoff (5 min.) 850 101.5% 2000* 800 (B200T, B200CT, A200CT) (BP-52 thru BP-63) Max. continuous 850 101.5% 2000* 800 (B200T, B200CT, A200CT) (BP-52 thru BP-63) Starting transient (5 sec.) 1000 Max. reverse (1 min.) 88% 1900 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: Minus 40˚C. minimum starting Minus 40˚C. to 99˚C. low idle 10˚C. to 99˚C. max. continuous Propeller and Two Hartzell HC-B3TN-3G or HC-B3TN-3N hubs with Hartzell T10178B-3R or Propeller Limits T10178NB-3R blades for BT-1 thru BT-19, BT-22, BT-28, BT-31, and BT-32, BN-1, FC-1 thru FC-3, BP-1, BP-22, BP-24 thru BP-63, GR-1 thru GR-19. OR Hartzell T10178K-3R or T10178NK-3R blades for: BB-1314, BT-20, BT-21, BT-23 thru BT-27, BT-29, BT-30 thru BT-34, BN-2 thru BN-4. Diameter: 98.5 in. (maximum); minimum allowable for repair, 97.5 in. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5(a) Reverse -9˚ Feathered +90˚ Propeller and Two McCauley 3GFR34C702 hubs with McCauley 100LA-2 blades Propeller Limits Diameter: 98 in. (maximum); minimum allowable for repair: 97 in. (B200T S/N BT-31 No further reduction permitted. thru BT-34) Pitch settings: (B200CT S/N Flight Idle Stop See NOTE 5(a) BN-5 & On) Reverse -10˚ Feathered +86.8˚ Propeller and Two McCauley 4HFR34C771 hubs with McCauley 94LA-0 blades. Propeller Limits Diameter: 94 in. (maximum); minimum allowable for repair, 93.5 in. (B200T S/N No further reduction permitted. BT-35 & On) Pitch setting: (B200CT S/N Flight Idle Stop See NOTE 13(a) BN-5 & On) Reverse -10.0˚ +0.4˚ Feathered +87.5˚ ± 0.3˚ Continuous operation on the ground is prohibited between 600 and 1100 rpm. The propeller must be feathered at rotational speeds below 600 propeller shaft rpm. OR Two Hartzell HC-E4N-3G hubs with Hartzell D9390SK-1R blades. Diameter: 92 in. (maximum); minimum allowable for repairs 92 in. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 13(c) Reverse -11.2˚ ± 0.5˚ Feathered +87.9˚ ± 0.5˚ Continuous operation on the ground is prohibited between 500 and 1,180 rpm. The propeller must be feathered at rotational speeds below 500 propeller shaft rpm. Rev. 132 9 A24CE III. Models 200T, 200CT, A200CT, B200T, B200CT (cont’d) Airspeed Limits Max. operating speed 282 m.p.h. (245 knots) up to 13,000 ft. (CAS) Max. operating Mach No. 0.472 13,000 ft. to 35,000 ft. altitude Maneuvering airspeed 196 m.p.h. (170 knots) The above airspeed limits Models 200T, 200CT, B200T, B200CT, A200CT (FWC-12D, RC-12D, RC-12G, RC-12H) Max. operating speed 299 m.p.h. (260 knots) up to 15,000 ft. Max. operating Mach No. 0.52 Maneuvering airspeed 209 m.p.h. (182 knots) The above airspeed limits Models A200CT (C-12D), A200CT (C-12F) Maximum flap extension speed Approach position 14˚ 230 m.p.h. (200 knots) 100% position 35˚ 165 m.p.h. (144 knots) (S/N BC-1 thru BC-61; BD-1 & On; BP-1 thru BP-6 and BP-12 thru BP-20 only) 100% position 35˚ 178 m.p.h. (155 knots) Landing gear extended 209 m.p.h. (182 knots) Landing gear operating Extension 209 m.p.h. (182 knots) Retraction 188 m.p.h. (164 knots) C.G. Range (Landing (+185.0) to (+196.4) at 12,500 lbs. Gear Extended) (+181.0) to (+196.4) at 11,279 lbs. or less Straight line variation between points given Moment changes due to retracting landing gear (6.50 X 10 main wheels): 6040 in.-lbs. (High-flotation landing gear) Moment changes due to retracting landing gear: 5552 in.-lbs. (Standard landing gear) See Operator’s Manual for Restricted Category C.G. Range. Empty Wt. C.G. Range None Maximum Weight Ramp 12,590 lbs. Takeoff 12,500 lbs. Landing 12,500 lbs. Zero fuel 10,400 lbs.* Models 200CT, A200CT (C-12D) 10,400 lbs.* Model 200T (S/N BT-1, BT-2, BT-3, BT-10) 10,800 lbs.* Model 200T (S/N BT-4 thru BT-9, BT-11 thru BT-22, BT-28) 11,000 lbs.* Models B200T, B200CT, A200CT (C-12F) 11,500 lbs.* Model A200CT (FWC-12D, RC-12D, RC-12G, RC-12H) *(See NOTE 1) Minimum Crew One pilot No. of Seats and Maximum 15 (including crew at +129). See loading instructions in Pilot's Operating Cargo Loading Handbook (POH) for approved seating and cargo configurations. Maximum Baggage 410 lbs. (+325): Models 200T, 200CT, A200CT 550 lbs. (+325): Models B200T, B200CT. Models 200T, 200CT, when kit 101-5068-1 is installed. Fuel Capacity Tank Cap. Gal. Usable Gal. Arm* Auxiliary LH 79.5 79 +204 Auxiliary RH 79.5 79 +204 Main LH 195* 193* +185 Main RH 195* 193* +185 Wing Tip LH 53 53 +193 Wing Tip RH 53 53 +193 *See NOTE 16 on Model A200CT See NOTE 1(a) for data on unusable fuel Engine Oil Capacity 18.4 qt. total at +131 (includes 6 qt usable in each integral engine tank) (See NOTE 1(c) for data on unusable oil). A24CE 10 Rev. 132 III. Models 200T, 200CT, A200CT, B200T, B200CT (cont’d) Maximum Operating 35,000 ft. Models 200T and B200T: BB-1314, BT-1 & On Altitude Models 200CT and B200CT: BN-1 & On 31,000 ft. Model A200CT: BP-1 thru BP-63; GR-1 & On, and FC-1 & On FAR Part 91 or 135 Operations, as limited by Part 91 or 135 (as appropriate) Control Surface Movements Wing flap Maximum 35˚ Aileron tabs Up 15˚ Down 15˚ Aileron Up 25˚ Down 15˚ Elevator tabs Up 3˚ 30' Down 13˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Model Serial Numbers Eligible 200T BT-1 thru BT-22, BT-28 200CT BN-1 A200CT (C-12D) BP-1, BP-19, BP-22, BP-24 thru BP-51 A200CT (C-12F) BP-52 thru BP-63 A200CT (FWC-12D) BP-7 thru BP-11 A200CT (RC-12D) GR-1 thru GR-12 A200CT (RC-12G) FC-1 thru FC-3 A200CT (RC-12H) GR-14 thru GR-19 B200T BB-1314, BT-23 thru BT-27, BT-29 thru BT-38, BT-44 & On. (See NOTES 23 & 24). B200CT BN-2 & On (See NOTE 23) IV. Model B200GT, Super King Air (Normal Category), Approved November 16, 2007 Model B200CGT, Super King Air (Normal Category), Approved November 16, 2007 NOTES: refer to Data Pertinent to all Model 200 series Engine Pratt & Whitney PT6A-52 (turboprop) per Beech Specification BS 267046. Engine Limits Shaft Horsepower Torque Ft-Lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp (Deg C) Takeoff 850 2230 104% 2000* 820 Max. continuous 850 2230 104% 2000* 820 Max. cruise 850 2230 104% 2000* 820 Starting transient (5 sec.) 2750 104% 2200* 1000 Max. reverse (1 min.) 800 88% 1900 760 *(See NOTE 4) 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; and Chinese No.3 Jet Fuel (See NOTE 29 for emergency fuels). Fuel Capacity Tank Cap. Gal. Usable Gal. Arm Auxiliary LH 79.5 79 +204 Auxiliary RH 79.5 79 +204 Main LH 195 193 +185 Main RH 195 193 +185 See NOTE 1(a) for data on unusable fuel Oil (Engine & Gearbox) Pratt & Whitney Service Bulletin No. 13001 lists approved brand oils Engine Oil Capacity 20 qt. total (10 qt. per each engine) at +131 (includes 6 qt. usable in each integral engine tank) (See NOTE 1(e) for data on unusable oil). Rev. 132 11 A24CE IV. Models B200GT, B200CGT (cont’d) Oil temperatures Minus 40˚C. minimum starting Minus 40˚C. to 110˚C. low idle 10˚C. to 110˚C. max. continuous 99˚C to 110˚C max (10 minutes) Propeller and Two Hartzell HC-E4N-3G hubs with Hartzell D9390SK-1R blades Propeller Limits Diameter: 93 in. (maximum); Minimum Allowable for repairs, 92 in. No further reduction permitted. Pitch Settings: Flight Idle Stop See NOTE 13(c) Reverse -11.2˚ + 0.5o Feathered + 85.8˚ + 0.5o Continuous operation on the ground is prohibited between 500 and 1,180 RPM. The propeller must be feathered at rotational speeds below 500 propeller shaft RPM. Airspeed Limits Max. operating speed 299 m.p.h. (260 knots) up to 15,000 ft. (CAS) Max. operating Mach No. 0.52 The above airspeed limits BY-1 & On BZ-1 & On and airplanes modified per Beechcraft Kit 101-9113 Maneuvering speed 209 m.p.h. (182 knots) Maximum flap extension speed Approach position 14˚ 230 m.p.h. (200 knots) 100% position 35˚ 178 m.p.h. (155 knots) Landing gear extended 209 m.p.h. (182 knots) Landing gear operating Extension 209 m.p.h. (182 knots) Retraction 188 m.p.h. (164 knots) The above airspeed limits BY-1 & On BZ-1 & On and airplanes modified per Beechcraft Kit 101-9113 C.G. Range (Landing (+185.0) to (+196.4) at 12,500 lbs. Gear Extended) (+181.0) to (+196.4) at 11,279 lbs. or less Straight line variation between points given Moment change due to retracting landing gear: 5552 in.-lbs. (Standard landing gear) Moment change due to retracting landing gear: 6040 in.-lbs. (High-flotation landing gear) Empty Wt. C.G. Range None Maximum Weight Ramp 12,590 lbs. Takeoff 12,500 lbs. Landing 12,500 lbs. Zero fuel 11,000 lbs. (See NOTE 1) Minimum Crew One pilot No. of Seats and Maximum 15 (including crew at +129). See Loading Instructions in POH for Cabin Loading approved seating and cargo configurations. Maximum Baggage 550 lbs. (+325) Maximum Operating 35,000 ft. S/N BY-1 & On, BZ-1 & On and airplanes modified per Beechcraft Altitude Kit 101-9113 A24CE 12 Rev. 132 IV. Model B200GT, Model B200CGT (cont’d) Control Surface Movements Wing flap Maximum 35˚ Aileron tabs Up 15˚ Down 15˚ Aileron Up 25˚ Down 15˚ Elevator tabs Up 3˚ 30' Down 13˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Serial Nos. Eligible B200GT: BY-1 & On B200CGT: BZ-1 & On, and airplanes modified per Beechcraft Kit 101-9113 V. Model A100-1 (U-21J), Super King Air (Normal Category), Approved May 29, 1974 (See NOTE 11) NOTES: refer to Data Pertinent to all Model 200 series Engine Two United Aircraft of Canada or Pratt & Whitney PT6A-41 (turboprop) per Beech Specification BS 22096 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 6 for emergency fuels). Oil (Engine & Gearbox) UACL PT6 Engine Service Bulletin No. 3001 lists approved brand oils Engine Limits Shaft Horsepower Torque Ft-Lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff (5 min.) 850 2230 101.5% 2000* 750 Max. continuous 850 2230 101.5% 2000* 750 Starting transient (5 sec.) 1000 Max. reverse (1 min.) 88% 1900 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: Minus 40˚C. minimum starting Minus 40˚C. to 99˚C. low idle 10˚C. to 99˚C. max. continuous Propeller and Two Hartzell HC-B3TN-3G or HC-B3TN-3N hubs with Hartzell T10178B-3R or Propeller Limits T10178NB-3R blades Diameter: 98.5 in. (maximum); minimum allowable for repair: 97.5 in. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5(a) Secondary Flight Idle Stop See NOTE 5(b) Reverse -9˚ Feathered +90˚ Airspeed Limits Max. operating speed 299 m.p.h. (260 knots) up to 15,000 ft. (CAS) Max. operating Mach No. 0.52 Maneuvering airspeed 209 m.p.h. (182 knots) Maximum flap extension speed Approach position 14˚ 230 m.p.h. (200 knots) 100% position 35˚ 165 m.p.h. (144 knots) Landing gear extended 209 m.p.h. (182 knots) Landing gear operating Extension 209 m.p.h. (182 knots) Retraction 188 m.p.h. (164 knots) Rev. 132 13 A24CE V. Model A100-1 (cont’d) C.G. Range (Landing (+185.0) to (+196.4) at 12,500 lb. Gear Extended) (+181.0) to (+196.4) at 11,279 lb. or less Straight line variation between points given. Moment changes due to retracting landing gear: 6040 in.-lbs. Empty Wt. C.G. Range None Maximum Weight Ramp 12,590 lbs. Takeoff 12,500 lbs. Landing 12,500 lbs. Zero fuel 10,400 lbs. (See NOTE 1) Minimum Crew One pilot No. of Seats Maximum 15 (including crew at +129). See loading instructions in the POH for approved seating and cargo configurations. Maximum Baggage 550 lbs. Fuel Capacity Tank Cap. Gal. Usable Gal. Arm* Auxiliary LH 79.5 79 +204 Auxiliary RH 79.5 79 +204 Main LH 195 193 +185 Main RH 195 193 +185 See NOTE 1(a) for data on unusable fuel Oil Capacity 31 qt. total at +131 (includes 12 qt usable in two integral engine tanks) (See NOTE 1(c) for data on unusable oil). Maximum Operating 31,000 ft. Altitude FAR Part 91 or 135 Operations, as limited by Part 91 (as appropriate) Control Surface Movements Wing flap Maximum 35˚ Aileron tabs Up 15˚ Down 15˚ Aileron Up 25˚ Down 15˚ Elevator tabs Up 3˚ 30' Down 13˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Serial Nos. eligible BB-3, BB-4, BB-5 VI. Model A200CT (RC-12K, RC-12P, RC-12Q), Super King Air (Restricted Category), Approved March 28, 1989 (See NOTES 11 & 19) NOTES: refer to Data Pertinent to all Model 200 series Engine Two Pratt & Whitney Canada PT6A-67 (Turboprop) per Beech Specification BS 24099 Fuel JP-4, JP-5 (MIL-T-5624); JP-8 (MIL-T-83133); JET A, JET A-1, and JET B conforming to Pratt & Whitney Service Bulletin 14004. See NOTE 6 for emergency fuels. Oil (Engine & Gearbox) Pratt & Whitney PT6 Engine Service Bulletin No. 14001 lists approved brand oils A24CE 14 Rev. 132 VI. Model A200CT (cont’d) Engine Limits Shaft Horsepower Torque Ft-Lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff (5 min.) (1) 1100 *100% 104% 1700 840 Max. continuous (1) 1100 *100% 104% 1700 830 Takeoff (5 min.) (2) 1200 **100% 104% 1700 840 Max. continuous (2) 1200 **100% 104% 1700 830 Starting transient (5 sec.) 1000 Max. reverse (1 min.) 900 1650 760 *100% torque: 3398 ft./lbs. (1) FE-1 thru FE-9 **100% torque: 3708 ft./lbs. (2) FE-10 & On (See NOTE 20) 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: Minus 40˚C. minimum starting Minus 40˚C. to 110˚C. low idle 10˚C. to 105˚C. max. continuous Propeller and Two McCauley 4JFR34C758 hubs with McCauley 106LNA-1 blades Propeller Limits Diameter: 105.0 in. (maximum); minimum allowable for repair: 104.0 in. No further reduction permitted. Pitch settings at Flight Idle Stop See NOTE 21 Reverse -9˚ ± 0.2˚ Feathered +87˚ ± 0.2˚ Avoid continuous operation on ground below 1000 rpm. Airspeed Limits Max. operating speed 288 m.p.h. (250 knots) up to 11,500 ft. (CAS) Max. operating Mach No. 0.472. 11,500 ft. to 35,000 ft. altitude Maneuvering airspeed 196 mph (170 knots) Maximum flap extension speed Approach position 14° 230 m.p.h. (200 knots) 100% position 35° 178 m.p.h. (155 knots) Landing gear extended 209 m.p.h. (182 knots) Landing gear operating Extension 209 m.p.h. (182 knots) Retraction 188 m.p.h. (164 knots) C.G. Range (Landing S/N FE-1 thru FE-9 Gear Extended) (+187.5) to (+195.1) at 16,000 lbs. (+177.0) to (+195.1) at 11,800 lbs. or less S/N FE-10 thru FE-24 (+188.0) to (+195.1) at 16,200 lbs. (+179.0) to (+195.1) at 12,600 lbs. or less S/N FE-25 & On (+188.7) to (+195.1) at 16,500 lbs. (+179.0) to (+195.1) at 12,600 lbs. or less Straight line variation between points given. Moment changes due to retracting landing gear (6.50 X 10 main wheels): 6820 in-lb. Empty Wt. C.G. Range None Rev. 132 15 A24CE VI. Model A200CT (cont’d) Maximum Weight Item S/N FE-1 thru FE-9 (lbs.) Military Only S/N FE-10 thru FE-24 (lbs.) S/N FE-25 & On Ramp 16,120 16,320 16,620 Takeoff 16,000 16,200 16,500 Landing 15,200 15,400 15,675 Zero fuel 12,700* 13,100* 13,100* *See NOTE 1 Minimum Crew One pilot No. of Seats and Two (+129). See loading instructions in the POH for approved seating and Cargo Loading cargo configurations. Maximum Baggage 410 lbs. (+325) Fuel Capacity Tank Cap. Gal. Usable Gal. Arm Auxiliary LH 79.5 79 +204 Auxiliary RH 79.5 79 +204 Main LH 194 192 +185 Main RH 194 192 +185 See NOTE 1(a) for data on unusable fuel Engine Oil Capacity 25 qt. total at +121 (includes 12 qt usable in two integral engine tanks) (See NOTE 1(d) for data on unusable oil). Maximum Operating Altitude 35,000 ft. Control Surface Movements Wing flap Maximum 35˚ Aileron tabs Up 15˚ Down 15˚ Aileron Up 25˚ Down 15˚ Elevator tabs Up 3˚ 30' Down 15˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Serial Nos. Eligible (RC-12K): FE-1 thru FE-9 (RC-12N): FE-10 thru FE-24 (Military Only) (RC-12P): FE-25 thru FE-31, FE-33, FE-35 (RC-12Q): FE-32, FE-34, FE-36 Data Pertinent to all Model 200 series Datum Located 190.0 in. forward of the wing main (forward) spar centerline. Leveling Means Two external screws on left side of fuselage forward of entrance door on Models 200, 200T, B200, B200T, A200, B200GT. Aft of the cargo door on Models 200C, A200C, B200C, B200CT, 200CT, A200CT, B200CGT. Certification Basis FAR Part 23, effective February 1, 1965, as amended by 23-1 through 23-9, Amendment 23-11; 23.175 and associated FARs 23.143(a), 23.145(d), 23.153, 23.161(c)(3); 23.173(a) as amended by Amendment 23-14; 23.951(c), 23.997(d) as amended by Amendment 23-15 (A200CT and B200 series only); 23.1545(a) as amended by Amendment 23-23; 23.1325(e) as amended by Amendment 23-20 (B200 Series only); 23.1305(n), 23.1529 as amended by Amendment 23-26; FAA Special Conditions 23-47- CE-5 issued October 30, 1972, Amendment 1 dated December 18, 1973, and Amendment 2 dated January 12, 1979; 25.929 and 25.1419 of FAR Part 25 as amended to December 31, 1972, and 25.831(d) through Amendment 25-41 (All Model 200 and B200 series aircraft approved for 35,000 feet); SFAR 27 through Amendment 27-4; and FAR Part 36 through Amendment 36-10. A24CE 16 Rev. 132 Data Pertinent to all Model 200 series (cont’d) Certification Basis (cont’d) Model B200 through S/N BB-1438 and Model B200C through S/N BL-138, FAR Part 36 through Amendment 36-10. Model B200 S/N BB-1439, BB-1444 & On, B200C S/N BL-139 & On and Model A200CT S/N FE-25 & On, FAR Part 36 through Amendment 36-20. Compliance with ice protection has been demonstrated in accordance with FAR 25.1419 when ice protection equipment is installed in accordance with the airplane equipment list. Effective April 20, 1993, Electronic Flight Instrument Systems shall meet the requirements of FAR 23.1322 as amended by Amendment 23-17; 23.1301, 23.1335 as amended by Amendment 23-20; 23.1305 as amended by Amendment 23-34; 23.1309, 23.1311, and 23.1321 as amended through Amendment 23-41 and Special Condition 23- ACE-68. Effective January 20, 1994, FAR 23.1457 as amended by Amendment 23-35. In addition, FAR 135, Appendix A, effective December 1, 1978 (B200 High Density Configuration (See NOTE 11)) Equivalent Safety Findings: FAR 23.621 (BB-2 through BB-1042 only); 23.997(d) (All models except A200CT and B200 series); FAR 23.1443 thru Amendment 23-9, Model 200 (BB-38, BB-39, BB-42, BB-44, BB-54 & On), Models 200C, 200CT, 200T, plus any earlier Model 200 modified by Beechcraft Kits 101-5007 and 101-5008 in compliance with Beech Service Instruction No. 0776-341. Only applicable to Model B200C (UC-12F) (BU-1 thru BU-12). Application for Type Certificate dated January 11, 1971. Type Certificate No. A24CE issued December 14, 1973, obtained by manufacturer under delegation option procedures. Additional requirements for Rockwell Collins Pro Line 21 Avionics Installation; Equivalent Level of Safety (ELOS) ACE-02-16 for FAR 23.1305c(2), 23.1305(a)(2)(3), and 23.1549(a)(b)(c), for direct reading digital only displays for oil pressure, oil temperature and fuel flow; 23.1547(e) as amended by Amendment 23-20; 23.603(b) as amended by Amendment 23-23; 23.1309(a), 23.1323(b), 23.1431(b) as amended by Amendment 23-49. Effective at S/N: Model B200, BB-1978, BB-1988 & On. Model B200C, BL-152 & On. Model B200GT, BY-1 & On. Model B200CGT; BZ-1 & On. Models B200 and B200C: 14 CFR Part 23.1529 as amended by Amendment 23-26. Effective at S/N: Model B200, BB-1978, BB-1988 & On. Model B200C, BL-152 & On. Additional requirements for the Rockwell Collins IFIS Installation: 23.771(a) as amended by Amendment 23-14; 23.1501 and 23.1541(a)(b) as amended by Amendment 23-21; 23.603, 23.605(a) as amended by Amendment 23-23; 23.1322, 23.1357(c)(d) as amended by Amendment 23-43; 23.305. 23.321, 23.613 as amended by Amendment 23-45; 23.301, 23.337, 23.571, 23.575, 23.607, 23.611 as amended by Amendment 23-48; 23.1309(b)(c)(e), 23.1311(a)(2)(3), 23.1321(e), 23,1351(e), 23.1351(a)(2)(i), 23.1359(c), 23.1365(a)(d)(e), 23.1431(a) as amended by Amendment 23-49; 23.1555(a), 23.1581(a), 23.1583(h), 23.1585(j) as amended by Amendment 23-50; and 23.777(a)(b) as amended by Amendment 23-51. Effective at S/N: Model B200, BB-1978 and BB-1988 & On. Model B200C, BL-152 & On. 23.1309(c)(d) as amended by Amendment 23-49 (Electrical Only). Effective at S/N: Model B200, BB-2001 & On. Model B200C, BL-152 & On. Rev. 132 17 A24CE Data Pertinent to all Model 200 series (cont’d) Certification Basis (cont’d) Models B200GT and B200CGT: Additional requirements for Models B200GT (S/N BY-1 & On) and B200CGT (S/N BZ- 1 & On): 14 CFR Part 23.1529 as amended by Amendment 23-26; 23.939 as amended by Amendment 23-42; 23.1351(a)(2)(i) as amended by Amendment 23-49. 14 CFR Part 34 through Amendment 34-3; 14 CFR Part 36 through Amendment 36-20 (See NOTE 39). 23.1309(c)(d) as amended by Amendment 23-49 (Electrical Only). Effective at S/N: Model B200GT, BY-32, BY-36 & On. Model B200CGT, BZ-1 & On. Additional requirements for the Rockwell Collins Pro Line Fusion installation: 23.1301(a)(b)(c)(d), 23.1327(a)(1)(2)(b), 23.1335, 23.1547(a)(b)(c)(d)(e), as amended by Amendment 23-20; 23.1501(b) as amended by Amendment 23-21; 23.603(a)(b) and 23.605(a) as amended by Amendment 23-23; 23.853(a) and 23.1305(b)(c)(e)(j)(k) (m)(n)(q)(s)(t)(w) as amended by Amendment 23-34; 23.1322(a)(b)(c)(d)(e), 23.1331(a)(b)(c), 23.1357(a)(b)(c)(d) as amended by Amendment 23-43; 23.305(a)(b), 23.613(a)(b)(c)(d)(e), 23.773(a)(1)(2), 23.1525, 23.1549(a)(b)(c)(d) as amended by Amendment 23-45; 23.301(a)(b), 23.571(a)(b), 23.607, 23.611 as amended by Amendment 23-48; 23.867(a)(b)(1)(2)(c)(1)(2), 23.1303(a)(b)(c)(e)(f), 23.1309(a)(1)(3)(b)(c)(d)(e), 23.1311(a)(b)(c), 23.1321(a)(b)(c)(d)(e), 23.1323(a)(c)(e), 23.1329(h), 23.1351(a)(2)(i), 23.1353(h), 23.1359(c), 23.1365(a)(b)(d)(e), 23.1431(a)(b)(e) as amended by Amendment 23-49; 23.1521(a)(b)(c)(d)(e), 23.1543(b)(c), 23.1545(d), 23.1555(a), 23.1581(a)(b)(1)(3)(c)(d)(f), 23.1583(h)(m), 23.1585(a)(j) as amended by Amendment 23-50; 23.777(a)(b), 23.1141(g)(2), 23.1203(a)(d) as amended by Amendment 23-51; 23.901(a)(e)(1), as amended by Amendment 23-53; 23.1308(a)(b)(c)(d), as amended by Amendment 23-57; 23.1457(a)(6) as amended by Amendment 23-58 (see NOTE 37); 23.1306(a)(b) as amended by Amendment 23-61; 23.903(b)(2), 23.1165(d) as amended by Amendment 23-62, and ELOS ACE-15-02 for 14 CFR 23.1305(b)(c)(e)(k) Amendment 23-34, 23.1311(a)(6)(7) Amendment 23-49, and 23.1549 Amendment 23-45. Effective at S/N BY-207, BY-239, BY-250 & On, BZ-1 & On. Additional requirements for the L3 Communications Digital Flight Data Recorder installation on Rockwell Collins Pro Line Fusion equipped B200GT/B200CGT models: 23.1301 as amended by Amendment 23-20; 23.603(a)(b), 23.605(a) as amended by Amendment 23-23; 23.1357(a)(c) as amended by Amendment 23-43; 23.613(a)(b)(c) as amended by Amendment 23-45; 23.301(a)(b), 23.607, 23.611 as amended by Amendment 23-48; 23.867, 23.1309(a)(1)(3)(b)(e), 23.1365(a)(b)(d)(e), 23.1431(a)(b) as amended by Amendment 23-49; 23.1308 as amended by Amendment 23-57; 23.1459 as amended by Amendment 23-58. Effective at S/N BY-207, BY-239, BY-250 & On, BZ-1 & On. Additional requirements for GPS-4000S Installation on Models B200GT/B200CGT (see NOTE 33): 23.867(a)(b) as Amended by Amendment 23-49; 23.1301(a)(b)(c)(d) as amended by Amendment 23-20; 23.1306(b) as amended by Amendment 23-61; 23.1308(b) as amended by Amendment 23-57; 23.1309(a)(1)(3)(b)(c)(1)(2)(i)(iii)(d)(e), 23.1351(a)(1)(2)(i), and 23.1431(a)(b) as amended by Amendment 23-49; 23.1529 as amended by Amendment 23-26. Effective at S/N BY-324 & On, BZ-2 & On. Additional requirements for the Rockwell Collins Pro Line Fusion iTAWS installation: 23.1555(b) as amended by Amendment 23-50. Effective at S/N BY-444 & On; BZ-9 & On. A24CE 18 Rev. 132 Data Pertinent to all Model 200 Series (cont’d) Certification Basis (cont’d) Models B200, B200C, B200GT, B200CGT: Additional requirements for the Rockwell Collins Flight Guidance Computer FGC-3000 installation (Collins Pro Line 21 Avionics is required before having the FGC-3000 installed on the airplane): 23.1357(a) as amended by Amendment 23-43; 23.677(a), 23.867(a)(b)(c), 23.1309(b)(c)(d)(e), 23.1329(e) as amended by Amendment 23-49, 23.143(b) as amended by Amendment 23-50, 23.1308(a)(b)(c)(d) as amended by Amendment 23-57, and 23.1581(a) as amended by Amendment 23-50. Effective at S/N: Model B200, BB-2018 & On. Model B200C, BL-167 & On. Model B200GT, BY-117 & On. Model B200CGT, BZ-1 & On. Additional requirements for the installation of SMR Technologies pneumatic deicer boots: 23.1301 and 23.1438(b) as amended by Amendment 23-20, 23.1501 as amended by Amendment 23-21; 23.603, 23.605 as amended by Amendment 23-23; 23.613 as amended by Amendment 23-45; 23.1309 as amended by Amendment 23-49; 23.1581, 23.1583(h), 23.1585 as amended by Amendment 23-50. Additional requirements for Models B200GT/B200CGT Innovative Solutions and Support (IS&S) Autothrottle installation: 23.771(a) as amended by Amendment 23-14; 23.1327(a), 23.1335 as amended by Amendment 23-20; 23.29(a)(b), 23.1501(a)(b), 23.1541(a)(b) as amended by Amendment 23-21; 23.603, 23.605 as amended by Amendment 23-23; 23.1 as amended by Amendment 23-34; 23.1322, 23.1357(a)(b)(c)(d) as amended by Amendment 23-43; 23.23, 23.305, 23.613, 23.672(a)(b) as amended by Amendment 23-45; 23.301, 23.607, 23.611 as amended by Amendment 23-48; 23.691, 23.867(a)(b), 23.1307, 23.1321(a)(c)(d)(e), 23.1329(h), 23.1351(a)(1)(2)(i)(b)(1)(2)(3), 23.1359(c), 23.1365(a)(b)(d)(e)(f) as amended by Amendment 23-49; 23.143(a)(b), 23.149, 23.207(a)(b)(c)(d)(e), 23.1325(a)(b)(1)(2)(ii), 23.1543(b)(c), 23.1581 as amended by Amendment 23-50; 23.779(b)(1) as amended by Amendment 23-51; 23.1305(c)(1)(e)(1) as amended by Amendment 23-52; 23.1308 as amended by Amendment 23-57; 23.1306 as amended by Amendment 23-61; 23.561(b)(3), 23.853(a), 23.777(a)(b), 23.1301, 23.1303, 23.1309, 23.1310, 23.1311, 23.1323(a)(c), 23.1331(a)(b)(1)(c)(1), 23.1353(h) (See NOTE 34), 23.1431(a)(b)(e), 23.1545(a)(b)(c), 23.1555(a), 23.1583(m), 23.1585(a)(c)(d)(e)(f)(g)(j), 23.1587 as amended by Amendment 23-62; 23.773(a)(2) as amended by Amendment 23-63. Special Conditions 23-291-SC. Effective at S/N BY-465, BY-470 & On, BZ-10 & On Additional requirements for Model B200GT Collins TCN-500 TACAN System installation. 23.1301(a)(b)(c)(d), 23.1327(a)(2)(b) as amended by Amendment 23-20; 23.1322(a)(c)(d)(e), 23.1351(a)(1)(2)(i), 23.1357(a)(b)(c)(d) as amended by Amendment 23-43; 23.773(a)(1) as amended by Amendment 23-45; 23.867(a)(b), 23.1309(a)(1)(3)(b)(e), 23.1321(a)(e), 23.1364(a)(b)(d)(e), 23.1434(a)(b) as amended by Amendment 23-49; 23.1555(a), 23.1581(a)(1)(2), 23.1583(h), 23.1585(a)(j) as amended by Amendment 23-50; 23.777(a)(b) as amended by Amendment 23-51; 23.2000, 23.2005, 23.2010, 23.2515(b) (See NOTE 35) as amended by Amendment 23-64; 23.2520(b)(see NOTE 36) as amended by Amendment 23-65. Effective at S/N BY-470 & On. Additions for 14 CFR Part 23, Amendment 64: 14 CFR 23.2000, 23.2005, 23.2010 as amended by Amendment 23-64 (See NOTE 38). Effective at S/N BY-470 & On, BZ-4 & On Additional requirements for Models B200GT Canyon Digital Audio Control System (DACS) and USB Power Port installation. 23.1301(a)(b)(c)(d), 23.1327(a)(2) as amended by Amendment 23-20; 23.1322(c)(e), 23.1357(a)(1)(2)(b)(c)(1)(2)(d) as amended by Amendment 23-43; 23.773(a)(1)(2) as amended by Amendment 23-45; 23.1303(e)(1), 23.1309(a)(1)(3)(b)(c)(1)(2)(i)(iii)(3)(d)(e), 23.1353(h), 23.1365(a)(b)(d)(e), 23.1431(a)(b)(e) as amended by Amendment 23-49; 23.1555(a), 23.1581(a)(1)(2), 23.1583(m), 23.1585(a)(j) as amended by Amendment 23-50; 23.777(a)(b) as amended by Amendment 23-51; 23.1308(c) as amended by Amendment 23-57; 23.1306(b) as amended by Amendment 23-61. Effective at S/N BY-470 & On. Rev. 132 19 A24CE Data Pertinent to all Model 200 series (cont’d) Certification Basis (cont’d) Models B200, B200C, B200GT, B200CGT: Additional requirements for Models B200GT, L3 Harris/Safe Flight Angle of Attack (AoA) system installation. 23.1301 as amended by Amendment 23-20; 23.1322(a)(b)(c)(e), 23.1331(a), 23.1357(a)(b)(c)(d) as amended by Amendment 23-43; 23.773(a)(1)(2) as amended by Amendment 23-45; 23.1309(a)(1)(3)(b)(c)(1)(2)(i)(iii) (3)(d)(e), 23.1321(c), 23.1351(a)(1)(2)(i), 23.1353(h), 23.1365(a)(b)(d)(e), 23.1431(a)(b) as amended by Amendment 23-49; 23.1543(b)(c), 23.1581(a)(1)(2), 23.1583(m), 23.1585(j) as amended by Amendment 23-50; 23.1308(c) as amended by Amendment 23-57; 23.1306(b) as amended by Amendment 23-61. Effective at S/N BY-470 & On. Additional requirements for Models B200GT/B200CGT L3 Model 7100 CVR and optional Recorder Independent Power Supply (RIPS) system installation: 23.1301 as amended by Amendment 23-20; 23.1322(b)(c) as amended by Amendment 23-43; 23.1309(a)(1)(3)(4)(b)(2)(3)(4)(e), 23.1351(a)(2)(i), 23.1353(h), 23.1365(a)(b)(d)(e), 23.1431(a)(b) as amended by Amendment 23-49; 23.1457(a)(6)(d)(5) as amended by Amendment 23-58 (see NOTE 40); 23.2325(g) (see NOTE 41), 23.2510 (see NOTE 42), 23.2525(a) (see NOTE 43), 23.2605(c) (see NOTE 42) as amended by Amendment 23- 64. Effective at S/N BY-555 & On and BZ-10 & On. Production Basis Production Certificate No. 8. A production certificate was issued, and the manufacturer is authorized to issue airworthiness certificates under the delegation option authorization provisions of 14 CFR Part 21. Production Certificate No. 4. Effective at S/N BY-207, BY-226, BY-239, BY-247, BY-250 thru BY-275, BZ-1. Manufactured by Textron Aviation under license agreement between Beechcraft Corporation and Textron Aviation. Effective at S/N BY-276 & On; BZ-2 & On. Manufactured under Production Certificate No. 4 by Textron Aviation. 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, P/N 101-380005-7, -9, -11, -17, -19, or -41. Models 200, 200T, 200C, A200C, 200CT, B200, B200T, B200CT, B200C. 2. Pre-stall warning indicator, P/N 101-380005-9, 13, -15, -21, -31, or -37. Models A200, A200CT. 3. Maximum allowable airspeed indicator, P/N 101-384030-3, Pilot and Copilot’s sides (Model 200, BB-2 thru BB-198). Maximum allowable airspeed indicator, P/N 101-384074-3, Pilot and Copilot’s sides (Model 200, BB-199 thru BB-733, Models 200C and A200C). Maximum allowable airspeed indicator, P/N 101-384074-7, Pilot and Copilot’s sides (Model B200, BB-734 through 1636, and B200C, BL-37 thru BL-140.) Maximum allowable airspeed indicator, P/N 101-384074-11 or –13, Pilot and Copilot’s sides (Model B200, BB-1637 thru BB-1833, BB-1835 thru BB- 1842, BL-141 thru BL-147). Model B200, BB-1834, BB-1843 & On, BL-148 & On, the airspeed indication is included in the PFD. 4. Maximum allowable airspeed indicator, P/N 100-384083-5, Pilot and Copilot’s sides (Model A200, BC-1 thru BC-61 and BD-1 & On) (C-12A). 5. Maximum allowable airspeed indicator, P/N 101-384101-1, Pilot and Copilot’s sides (Model 200T, 200CT, B200T, B200CT). 6. Maximum allowable airspeed indicator, P/N 101-384128-3, Pilot and Copilot’s sides (Model A200, BC-62 & On, BC-1 thru BC-61 and BD-1 thru BD-30, when modified per Beech Service Instructions C-12-0076 (C-12C), Model A200CT (C- 12D), BP-1, BP-20 (C-12F)). A24CE 20 Rev. 132 Data Pertinent to all Model 200 series (cont’d) 7. Maximum allowable airspeed indicator, P/N 101-384128-5, Pilot and Copilot’s sides (Model A100, BC-62 & On; BC-1 thru BC-61, and BD-1 thru BD-30, when modified per Beech Service Instructions C-12-0076 (C-12C), Model A200CT (C- 12D) BP-21 through BP-51, and Model A200CT(C-12F), BP-52 thru BP-63). 8. Maximum allowable airspeed indicator, P/N 117-380000-5, Pilot and Copilot’s sides (Model A200CT (FWC-12D), BP-7 thru BP-11). 9. Maximum allowable airspeed indicator, P/N 117-380000-7, Pilot and Copilot’s sides (Model A200CT (RC-12D), GR-1 thru GR-13). 10. Maximum allowable airspeed indicator, P/N 117-380000-9, Pilot and Copilot’s sides (Model A200CT (RC-12G), FC-1 & On). 11. Maximum allowable airspeed indicator, P/N 117-380000-11, Pilot and Copilot’s sides (Model A200CT (RC-12H), GR-14 thru GR-19). 12. Maximum allowable airspeed indicator, P/N 117-384074-9, Pilot and Copilot’s sides (Model B200, High Density Configuration; See NOTE 11). 13. Maximum allowable airspeed indicator, P/N 117-380000-13, Pilot and Copilot’s sides (Model A200CT (RC-12K), FE-1 thru FE-9). 14. Maximum allowable airspeed indicator, P/N 117-380000-15, Pilot and Copilot’s sides (Model A200CT (RC-12K), FE-10 thru FE-24). 15. Maximum allowable airspeed indicator, P/N 117-380000-17, Pilot and Copilot’s sides (Model A200CT (RC-12P), FE-25 & On). 16. Maximum allowable airspeed indicator, P/N 117-380000-19, Pilot and Copilot’s sides (Model A200CT (RC-12Q), FE-32, FE-34, FE-36). NOTE 1. Current weight and balance data, loading information and a list of equipment included in empty weight must be provided for each airplane at the time of original certification. a. Basic empty weight includes unusable fuel of 44 lb. at (+170 in.) with 10.5 lb. being undrainable. (Models 200, 200T) (Model A200, BC-14 & On, BD-15 & On) (Models 200C, A200C, 200CT, A200CT, B200, B200T, B200C, B200CT). b. Basic empty weight includes unusable fuel of 37 lb. at (+163 in.) with 10 lb. being undrainable. (Model A200, BC-1 thru BC-13, BD-1 thru BD-14). c. Basic empty weight includes engine oil of 62 lbs., at (+131 in.) with 38 lbs., being unusable. d. Basic empty weight includes engine oil of 52 lbs., at (+121 in.) with 13 lbs., being unusable (Model A200CT (RC-12K), FE-1 thru FE-24 and (RC-12P), FE-25 & On). e. Basic empty weight includes engine oil of 62.2 lbs., at (+131 in.) with 38 lbs., being unusable (Model B200GT, S/N BY-1 & On, and Model B200CGT, S/N BZ-1 & On, and airplanes modified per Beechcraft Kit 101-9113.) NOTE 2. All placards required in the Airplane Flight Manual (AFM) must be installed in the appropriate location. Rev. 132 21 A24CE Data Pertinent to all Model 200 series (cont’d) NOTE 3. Mandatory retirement times for all structural components are contained in the AFM Limitation Section: Part Number (P/N) Models 101-590010-3, Rev. A6 200, 200C, A200C OR 101-590010-453 200, 200C, A200C 101-590010-453 200T, 200CT 92-38287 A200 92-38580 A200CT 92-30096 A200CT (FWC-12D) 92-30108 A200CT (RC-12D) 92-30581 A200CT (RC-12G) 992-31110 A200CT (RC-12H) 990-331320 A200CT (RC-12K), FE-1 thru FE-9 990-30440 A200CT (RC-12K, FE-10 thru FE-24 990-30894 A200CT (RC-12P), FE-25 & On, except FE-32, FE-34, FE-36 990-32244 A200CT (RC-12Q), FE-32, FE-34, FE-36 In the Airworthiness Limitations Manual (ALM): 101-590010-453 B200, B200C, B200CT, B200T, B200GT, B200CGT. These limitations may not be changed without FAA Engineering approval. Model A100-1 (BB-3) 20,000 hr., fatigue safe life for wing. NOTE 4. The maximum propeller shaft overspeed limit is 110% (2200 r.p.m.) of all ratings. A 100% propeller shaft speed is defined as 2000 r.p.m. and is the normal steady state operating limit. Gas generator speeds up to 102.6% are permissible for 10 seconds and to 101.5% for unlimited periods subject to applicable temperature and other limits. A 100% gas generator speed is defined as 37,500 r.p.m. NOTE 5. a. Flight idle propeller low pitch stop is set so that at 1800 r.p.m. there shall be an indicated 800 + 60 ft. lbs. torque corrected to sea level standard day. b. Secondary flight idle stop shall be 210 +40 propeller r.p.m. higher than flight idle stop with a gas generator speed of 70% (for airplanes not complying with SI 0808-247 only). NOTE 6. Emergency use of MIL-G-5572: Grades 80/87, 91/98, 100/130, and 115/145 are permitted for a total time not to exceed 150 hours between engine overhauls. It is not necessary to purge the unused fuel from the system when switching fuel types. NOTE 7. Auxiliary fuel system installed in Model A200, S/N BC-14 & On, BD-15 & On and any earlier airplanes modified in compliance with Beechcraft Service Instruction No. C-12-0089. NOTE 8. These values are 850 for Model A200, S/N BC-62 & On (C-12C), and any earlier airplanes modified in compliance with Beechcraft Service Instruction No. C-12-0076. NOTE 9. These values are 750 for Model A200, S/N BC-62 & On (C-12C), and any earlier airplanes modified in compliance with Beechcraft Service Instruction No. C-12-0076. A24CE 22 Rev. 132 Data Pertinent to all Model 200 series (cont’d) NOTE 10. The following models have been delivered and are eligible for multiple airworthiness certification per FAR 21.187 in Normal and Restricted Category at indicated gross weight and other limitations specified by the applicable AFM or POH for any special purpose that is specified by an AFM Supplement to the applicable AFM or POH. Model Purpose FARs Inappropriate for Restricted Category Certification Restricted Category Maximum Gross\ Weight (lbs.)* AFM/POH Supplement 200T Photographic 23.1, 23.775(e) 14,000 101-590037-21 200T Patrol 23.1 14,000 101-590037-27 or 101-590037-33 or 101-590037-39 200T, B200T Flight inspection 23.1 14,000 101-590037-35 200CT Flight inspection 23.1 14,000 101-590037-37 A200CT Aerial surveying 23.1, 23.335(c) 14,200 101-590091-5 B200T Patrol 23.1; 23.473(d) 15,000 101-590037-47 B200T, B200CT Patrol 23.1 14,000 101-590037-43 200 --- 23.775(e) 12,500 N/A B200T Aerial surveying 23.1, 23.473(d) 15,000 101-590037-49 B200C Aerial surveying 23.1 14,000 101-590010-241 B200C Aerial surveying 23.1 14,000 101-590010-261 B200 Flight inspection 23.1 14,000 101-590010-257 B200 Aerial surveying 23.1, 23.775 12,500 101-590010-317 B200T Aerial surveying 23.1 14,000 101-590037-51 B200T Patrol 23.1, 23.473(d) 15,000 101-590037-73 *See the applicable section of this data sheet for Normal Category gross weight. NOTE 11. The following models, when modified to the applicable Beechcraft Modification Drawing, are eligible for operation as noted below: Model Manufactured Configuration Eligible Operation (export to) Beechcraft Drawing 200, 200T, B200, B200T Export United Kingdom 101-005004 200C, 200CT, B200C, B200CT Export United Kingdom 101-005020 200, 200C, 200T, 200CT B200, B200C, B200T, B200CT Export France 101-005003 or 101-005006 The above models are eligible for return to U.S. certification when those portions of the above listed modifications which do not comply with U.S. requirements have been removed or replaced. Model Manufactured Configuration Eligible Operation Beechcraft Drawing A100-1 Military U-21J Civil Registration 101-005072 200, 200T, B200, B200T Up to 9 passenger seats FAR 135 with 9 or fewer passenger seats 12-1-78 101-005007 B200C, B200CT Up to 9 passenger seats FAR 135 with 9 or fewer passenger seats 12-1-78 101-005025 B200 High Density Configuration: Up to 13 passenger seats and external baggage pod FAR 135 with 10 or more passenger seats 101-000015 A200 Military C-12A/C Civil Registration in normal category 101-005008 A200C Military UC-12B Civil Registration in normal category 101-005016 A200CT Military C-12D Civil Registration in normal category 101-005019 A200CT Gov’t. of Israel FWC-12D Civil Registration in normal category 101-005001 A200CT Military RC-12D Civil Registration in normal category 101-005002 A200CT Military RC-12G Civil Registration in normal category 101-005003 A200CT Military RC-12H Civil Registration in normal category 101-005004 A200CT Military RC-12K, RC-12P and RC-12Q Civil Registration in normal category 117-005007* A200CT Military C-12F Civil Registration in normal category 101-005019 B200C Military UC-12F Civil Registration in normal category 101-005016* B200C Military C-12F Civil Registration in normal category 101-005059 B200C Military C-12F Civil Registration in normal category 127-005001 or 127-005002 B200C Military UC-12M Civil Registration in normal category 127-005001* B200C Military C-12R Civil Registration in normal category 127-005002 *See NOTE 25 Rev. 132 23 A24CE Data Pertinent to all Model 200 series (cont’d) NOTE 12. Model A200CT, (FWC-12D) S/N BP-7 thru BP-11, (RC-12G) S/N FC-1 & On, and (RC-12H) S/N GR-14 thru GR-19, are certified in only the Restricted Category for serial surveying, at 15,000 pounds gross weight, providing the pertinent limitations, as specified by the AFMS 101-590091-3 (FWC-12D), AFM 92-30581 (RC-12G), and AFM 992-31110 (RC-12H) are followed and the aircraft is marked to comply with FAR Part 45. FAR 23.1 and 23.335(c) are inappropriate (FWC-12D); FAR 23.1, 23.335(c), and 23.473(d) are inappropriate (RC-12G); and FAR 23.1, 23.67(a), 23.335(c), and 23.473(d) are inappropriate (RC-12H). Model B200C (C-12F) Serials BL-99 through BL-104 are certified in only the restricted category for aerial surveying at 14,000 pounds gross weight providing the pertinent limitations, as specified by the AFMS 101- 590010-261, are followed and the aircraft is marked to comply with FAR Part 45. FAR 23.1 is inappropriate (C-12F). NOTE 13. a. Flight idle propeller low pitch stop is set so that at 1800 r.p.m. there shall be an indicated 740 +40 ft. lb. torque corrected to sea level standard day. b. Ground idle propeller low pitch stop is set so that at 1800 r.p.m. there shall be an indicated 330 +40 ft. lb. torque corrected to sea level standard day. c. Flight Idle Propeller Low Pitch Stop is set so that at 1,800 r.p.m. there shall be an indicated 522 +20 ft. lb. torque corrected to sea level standard day. NOTE 14. These values are 2230 for Model A200, S/N BC-62 & On (C-12C), and any earlier airplanes modified in compliance with Beech Service Instruction No. C-12-0076. NOTE 15. When airplane S/Ns BC-1 thru BC-61 and BD-1 thru BD-30 (C-12A) have been modified per SI C-12-0076 to add PT6A-41 engines, the airplane is redesignated as Model A200 (C-12C). NOTE 16. These values are 194 cap. gal. and 192 usable gal. for Models A200CT (FWC-12D), A200CT (RC-12D), A200CT (RC-12G), and A200CT (RC-12H). NOTE 17. Model B200, S/N BB-1204 and BB-1205, are certified in the Restricted Category only for aerial surveillance, S/N BB-1206 is certified in the Restricted Category only for flight inspection at 14,000 lbs. gross weight, providing the pertinent limitations as specified by the POH and AFMS 101-590010-235 are followed, and the aircraft is marked to comply with FAR Part 45. FAR 23.1, 23.775(e), 23.177(a)(1)(2) are inappropriate. Once certificated in the Restricted Category, Model B200, S/N BB-1114, and Model B200C, S/N BL-65, cease to be eligible for return to Normal Category. See Summit Aviation AFMS No. 1, dated September 11, 1986, for flight hour definition. NOTE 18. For airplanes placed on the Australian register after December 31, 1987, the maximum occupancy is limited to 11 places unless equipped with a cockpit voice recorder system approved by the Department of Aviation. NOTE 19. Models A200CT (RC-12K), S/N FE-1 thru FE-24, A200CT (RC-12P), S/N FE-25 & ON except FE-32, FE-34, FE-36, and A200CT (RC-12Q), S/N FE-32, FE-34, FE-36 are certified in only the Restricted Category for aerial surveying, at 16,000 pounds gross weight (16,200 pounds, FE-10 thru FE-24 and 16,500 pounds, FE-25 & On), providing the pertinent limitations, as specified by the AFM 990-331320 (990-30440, FE-10 thru FE-24, 990-30894, FE-25 & ON except FE-32, FE-34 and FE-36, 990-32244, FE-32, FE-34, FE- 36) are followed and the aircraft is marked to comply with FAR 45. FAR 23.1, 23.67(a), 23.201(a), 23.203(b), 23.335(c), 23.473(d) and 23.1507 are inappropriate (RC-12K, RC-12P, RC-12Q). NOTE 20. The maximum propeller shaft overspeed limit is 110% (1870 r.p.m.) of all ratings. 100% propeller shaft speed is defined as 1700 r.p.m. and is the normal steady state operating limit. Gas generator speeds up to 104% are for unlimited period subject to applicable temperature and other limits. 100% gas generator speed is defined as 37,500 r.p.m. (Model A200CT (RC-12K), S/N FE-1 thru FE-24, (RC-12P), S/N FE-25 & On except FE-32, FE-34, FE-36 and (RC-12Q) S/N FE-32, FE-34, FE-36). NOTE 21. Flight idle propeller low pitch stop is set so that at 1500 r.p.m. the engine torque is 25% for sea level, standard day conditions. Ground idle low pitch stop is set so that at 71 to 73% N1, propeller r.p.m. is not less than 1000 r.p.m. (Model A200CT, (RC-12K) S/N FE-1 thru FE-24, (RC-12P) S/N FE-25 & On, except FE- 32, FE-34, FE-36 and (RC-12Q) S/N FE-32, FE-34, FE-36). NOTE 22. Model B200T, S/N BB-1314, is certified in the Restricted Category only for aerial surveillance, at 14,000 pounds gross weight, providing the pertinent limitations, as specified by POH and AFMS 101- 590037-85 are followed and the aircraft is marked to comply with FAR Part 45. FAR 23.1, 23.335(c), 23.1507 and 27.473(d) are inappropriate. A24CE 24 Rev. 132 Data Pertinent to all Model 200 series (cont’d) NOTE 23. Company name change effective 4/15/96. The following serial numbers are manufactured under the name Raytheon Aircraft Company: Model B200: BB-1532 thru BB-1977. Model B200CT: BN-5 thru BN-9. Model B200C: BL-141 thru BL-151. Model B200T: BT-39 thru BN-46. NOTE 24. The following serial numbers were delivered to the Government of Israel and are not eligible for FAA certification or civil registration: Model B200: BB-1385, BB-1386, BB-1387, BB-1388, BB-1804, BB-1806, BB-1809, BB-1811, BB-1819. Model B200T: BT-39, BT-40, BT-41, BT-42, BT-43, BT-44, BT-45, BT-46. Model B200CT: BN-5, BN-6, BN-7, BN-8, BN-9. NOTE 25. The following serial numbers are not eligible for FAA certification for civil registration: Model A200CT: FE-10 thru FE-24 (RC-12K with military designation RC-12N). Model B200C: BV-11 and BV-12 (UC-12M with military designation RC-12M). Model B200C: BU-11 and BU-12 (UC-12F with military designation RC-12F). Model B200CT: (FWC-II) Designation for FG-1 and FG-2 (no FAA designation). NOTE 26. RVSM capability is per either STC ST01456SE or SA01790SE for Models 200 and 200C. RVSM capability is per (one of the following) STCs ST01070SE, ST01278SE, ST01456SE, SA01790SE or SA01798SE for Models B200 and B200C. RVSM capability is per STC SA01798SE for Models B200GT and B200CGT. These STCs approve the noted aircraft to FAR Part 91, Appendix G. Refer to the airplane maintenance logbook for specific RVSM STC incorporated at build. Authorization for RVSM operations must be obtained by the operator from the local FAA Flight Standards District Office (FSDO). RVSM requirements have been incorporated into the type design of production aircraft at BY-175 & On, BZ- 1 & On, BB-2019 & On, and BL-171 & On. These aircraft are RVSM compliant to 14 CFR Part 91, Appendix G at initial airworthiness issuance. Instructions for Continued Airworthiness (ICA) for the production airplanes are now incorporated into the applicable airplane maintenance manual. Authorization for RVSM operations must be obtained by the operator from the local FAA FSDO. For RVSM aspects only, Model B200 series Pitot-Static system meets the requirements of FAR Part 23.1301(a) Amdt [23-20]. NOTE 27. Model B200, S/N BB-1733 and BB-1744 are certified in the Restricted Category only for aerial surveillance, at 14,000 pounds gross weight, providing the pertinent limitations, as specified by POH and AFMS 101- 590010-413, are followed and the aircraft is marked to comply with FAR Part 45. FAR 23.1, 23.775(e), 23.177(a)(1)(2) are inappropriate. NOTE 28. Company name change effective 3/26/07. The following serial numbers are manufactured under the name of Hawker Beechcraft Corporation (HBC): BB-1976 through BB-2018 (200 series). NOTE 29. Emergency Engine Fuels for Models B200GT/B200CGT and airplanes modified per Hawker Beechcraft Kit 101-9113 (See Limitations Section of the POH/AFM for Limitations). 80 Red (formerly 80/87); 100LL Blue; 100 Green. NOTE 30. Company name change effective 4/12/13. The following serials numbers are manufactured under the name of Beechcraft Corporation: Model B200: BB-2019 thru BB-2021. Model B200C: BL-171. Model B200GT: BY-173 thru BY-206, BY-208 thru BY-225, BY-227 thru BY-238, BY-240 thru BY-246, BY-248 and BY-249. NOTE 31. Deleted on 8/3/26. NOTE 32. Company name change effective 10/12/16. The following serial numbers are manufactured under the name Textron Aviation: Model B200GT: BY-276 & On. Model B200CGT: BZ-2 & On. NOTE 33. Installation of GPS-4000S due to in-draw of Rockwell Collins STC, SA01848WI, to address the use of a multi-core processor and upgrading of the GPS-4000S receiver Rev. 132 25 A24CE Data Pertinent to All Model 200 series (cont’d) NOTE 34. 14 CFR 23.1353(h) Amendment [23-62] is applicable to the IS&S autothrottle installation ONLY. It is connected to the standby battery system and meets the 60-minute requirement of the later amendment. NOTE 35. The Means of Compliance for 23.2515(b) [23-64] is ASTM F3061/F3061M Section 17.3.1.3 Rev. 23a. NOTE 36. The Means of Compliance for 23.2520(b) [23-65] is ASTM F3236 Section 4.1.2 Rev. 21a. NOTE 37. Optional datalink message recording capability applies to aircraft with IOC-3100 Part Number 822-1361-622 or 822-1361-623 only. NOTE 38. 14 CFR 23.2005 Certification Level and Performance Level: Level 4, High Speed. NOTE 39. Per 14 CFR Part 36.2, all product changes that affect acoustics will comply with the latest amendment level of 14 CFR Part 36 that is current at the time of project acceptance. NOTE 40. 14 CFR 23.1457(d)(5)[23-58] applicable to Recorder Independent Power Supply (RIPS) only. NOTE 41. The Means of Compliance for 23.2325(g)[23-64] is CPP-23.2525-1 signed 4/17/2023 and CPP-23.2525-4 signed 2/13/2024. NOTE 42. The Means of Compliance for 23.2510 and 23.2605(c)[23-64] is CPP-23.2525-1 signed 4/17/2025. NOTE 43. The Means of Compliance for 23.2525(a)[23-64] is CPP-23.2525-1 signed 10/19/2023 and CPP-23.2525-4 signed 2/13/2024. VII. Model 1900, Airliner, 21 PCLM (Normal Category), Approved November 22, 1983 Model 1900C, Model 1900C (C-12J), Airliner, 21 PCLM (Normal Category), Approved November 22, 1983 NOTES: refer to Data Pertinent to Models 1900/1900C Engine Two Pratt & Whitney of Canada, Ltd. PT6A-65B (turboprop) per Beech Specification BS 23287 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. 13044 or ASTM SPEC. D1655. See NOTE 6 for emergency fuels. Oil (Engine & Gearbox) P&WC PT6 Engine Service Bulletin No. 13001 lists approved brand oils. Engine Limits Shaft Horsepower Torque Ft-Lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff (5 min.) 1100 3400 104% 1700* 820 Max. continuous 1100 3400 104% 1700* 810 Starting transient (5 sec.) 1000 Max. reverse (1 min.) 900 1650* 760 (*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. The POH provides minimum torque settings for T.O. It must be possible to achieve these settings without exceeding ITT or N1 limits. Oil temperatures: Minus 40˚C. minimum starting Minus 40˚C. to 110˚C. low idle 0˚C. to 110˚C. max. continuous A24CE 26 Rev. 132 VII. Model 1900, 1900C and 1900C (C-12J) (cont’d) Propeller and Two Hartzell HC-B4MP-3A with Hartzell M10877K blades Propeller Limits Diameter: 109.5 in. per Beech Specification BS 23424. No further reduction permitted. Pitch settings: Flight idle stop See NOTE 5 Reverse -14˚ ± 0.5˚ Feathered +80˚ ± 0.5˚ Airspeed Limits Max. operating speed 285 m.p.h. (247 knots) up to 12,600 ft. (IAS) Max. operating Mach No. 0.48 Maneuvering speed 217 m.p.h. (188 knots) Maximum flap extension speed Takeoff 10˚ 228 m.p.h. (198 knots) Approach position 20˚ 194 m.p.h. (168 knots) 100% position 35˚ 176 m.p.h. (153 knots) Landing gear extended 207 m.p.h. (180 knots) Landing gear operating Extension 207 m.p.h. (180 knots) Retraction 207 m.p.h. (180 knots) C.G. Range (Landing (+282.2) to (+299.9) at 16,600 lb. Gear Extended) (+274.5) to (+299.9) at 11,600 lb. or less Straight line variation between points given. Moment changes due to retracting landing gear: 8271 in.-lbs. with Kit 114-0002-1 or -3 installed (see NOTE 12) (+283.7) to (+297.3) at 17,600 lbs. (+282.2) to (+297.3) at 16,601 lbs. (+282.2) to (+299.9) at 16,600 lbs. (+274.5) to (+299.9) at 11,600 lbs., or less Straight line variation between points given. Moment changes due to retracting landing gear: 8271 in.-lb. Empty Wt. C.G. Range None Maximum Weight Ramp 16,710 lbs. 17,710 lbs.* Takeoff 16,600 lbs. 17,600 lbs.* Landing 16,100 lbs. 16,720 lbs.* Zero fuel 14,000 lbs. N/A Zero fuel 15,000 lbs.** 15,000 lbs.* & ** *with Raytheon Kit 114-0002-1 or -3 installed (see NOTE 12) **1900C with Beech Kit 114-5044 or 114-5045 (see NOTE 1) Minimum Crew One pilot No. of Seats and Maximum 21 (including crew at +129). See loading instructions in the POH Cabin Loading for approved seating and cargo configurations. Maximum Baggage See NOTE 7 for data on maximum baggage. Rev. 132 27 A24CE VII. Model 1900, 1900C and 1900C (C-12J) (cont’d) Fuel Capacity UA-1 & On, UB-1 & On Tank Cap. Gal. Usable Gal. Arm Main LH 215 212.5 298 Main RH 215 212.5 298 UC-1 & On, UD-1 & On Tank Cap. Gal. Usable Gal. Arm Auxiliary LH 93.3 92.3 304 Auxiliary RH 93.3 92.3 304 Main LH 244.7 241.2 296 Main RH 244.7 241.2 296 See NOTE 1(a) for data on unusable fuel Oil Capacity 29 qt. total (includes 12 qt usable in two integral engine tanks). (See NOTE 1(b) for data on unusable oil). Maximum Operating Altitude 25,000 ft. Control Surface Movements Wing flap Maximum 35˚ Aileron tabs Up 15˚ Down 15˚ Aileron Up 24˚ Down 16˚ (UA-1 & On, UB-1 & On) Up 24˚ Down 17˚ (UC-1 & On, UD-1 & On) Elevator tabs Up 5˚ Down 15˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Serial No’s Eligible 1900 UA-3 only 1900C (Bladder Tank Fuel System) UB-1 thru UB-74 1900C (Wet Wing Fuel System) UC-1 thru UC-174 1900C (C-12J) UD-1 thru UD-6 Data Pertinent to Models 1900, 1900C and 1900C (C-12J) Datum Located 290.5 in. forward of the wing main (forward) spar centerline. Leveling Means Two external screws on left side of fuselage aft of entrance door. Certification Basis Special Federal Aviation Regulation (SFAR) 41C, effective September 13, 1982 (See NOTE 8): FAR Part 23, effective February 1, 1965, through Amendment 23-9; Amendment 23-11; Amendment 23-14, 23.143(a), 23.145(d), 23.153, 23.161(c)(3), 23.173(a), 23.175, 23.427, 23.441, 23.445; Amendment 23-15, 23.951(c) and FAR 23.997(d); Amendment 23-23, 23.1545(a); Amendment 23-26, 23.967, 23.1305(n); Special Conditions No. 23- 47-CE-5 including Amendments 1, 2, 3, dated November 15, 1982, and 4 dated October 17, 1986; FAR Part 25, Paragraph 25.929 effective February 1, 1965; Amendment 25-23, 25.1419; Amendment 25-41, 25.831(d); FAR Part 36 through Amendment 36-10; and SFAR 27 through Amendment 27-4. Compliance with ice protection has been demonstrated in accordance with FAR 25.1419 when ice protection equipment is installed in accordance with the Equipment List. A24CE 28 Rev. 132 Data Pertinent to Models 1900, 1900C and 1900C (C-12J) (cont’d) Certification Basis (cont’d) For aircraft modified by Kit 114-0002-1, or -3, the following FAR Part 23 Amendment 23-34, are added to the certification basis of the 1900C at the 17,600 pound weight: 23.25(a)(b), 23.29(a)(b), 23.45(a)(b)(f), 23.49(a)(c)(d)(e), 23.51(d), 23.53(c), 23.55, 23.57, 23.59, 23.61, 23.65(a)(c)(d), 23.67(e), 23.75(a)(e)(f)(g), 23.77, 23.143, 23.145(b)(1)(e)(2), 23.147(a), 23.149(c)(2)(3)(4)(5), 23.153, 12.155, 23.157, 23.161(b)(2)(c)(3)(ii), 23.171, 23.173(b)(2), 23.175(b)(2)(c)(3), 23.177(a), 23.181(b), 23.201(a)(f), 23.203(a)(b)(4)(c)(1)(2), 23.205, 23.207, 23.231(a), 23.233, 23.235, 23.301(a)(b)(c), 23.303(c)(d)(e), 23.305, 23.307, 23.321, 23.331, 23.333, 23.335, 23.337, 23.341, 23.345, 23.347, 23.349(c)(d)(e), 23.351, 23.361(a)(c), 23.363, 23.365(a)(b)(d), 23.367, 23.371(b), 23.373(a), 23.391, 23.395(a)(c), 23.397, 23.399(a), 23.405, 23.407, 23.409, 23.415, 23.421, 23.423, 23.425, 23.427, 23.441, 23.443, 23.455, 23.457, 23.471, 23.473(a)(b)(c)(d)(e), 23.477, 23.479(a)(2)(c)(d), 23.481, 23.483, 23.485, 23.493, 23.499, 23.507, 23.509, 23.511, 23.561, 23.571, 23.572(b), 23.601, 23.603(a), 23.613, 23.615, 23.619, 23.621, 23.623, 23.625, 23.627, 23.629(a)(b)(c), 23.641, 23.651(a), 23.657, 23.659, 23.671(a), 23.675(c), 23.681, 23.683(a)(b), 23.693, 23.701(b), 23.721, 23.723, 23.729(a), 23.731, 23.733, 23.735, 23.775, 23.785(a)(b)(c)(f)(j)(l), 23.787(a)(b)(c)(g), 23.843(a), 23.903(b), 23.963(a), 23.965(a), 23.967(e), 23.1193, 23.1413, 23.1519, 23.1527(b), 23.1529, 23.1581, 23.1583(c)(3)(4), 23.1587(a)(1)(3)(4)(6)(7)(8)(d), Part 36 through Amendment 36-20. Production Basis Production Certificate No. 8. A production certificate was issued and the manufacturer is authorized to issue airworthiness certificates under the delegation option authorization provisions of 14 CFR Part 21. 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 system to include stall warning lift computer, P/N 114-380051-3 and stall warning lift transducer, P/N 114-380051-1. 2. Maximum allowable airspeed indicator, 114-380012-3, Pilot and Copilot's sides. MCOF95055-1 with Kit 114-0002-1, Pilot and Copilot’s sides. 3. POH Part Number 114-590021-3 or other AFM as allowed by 14 CFR Part 121.141 (Domestic) or 114-590021-51 (for International Civil Aviation Organization (ICAO) Operation). S/N UA-1 thru UA-3, UB-1 thru UB-74. POH Part Number 114-590021-57 or other AFM as allowed by 14 CFR Part 121.141 (Domestic) or 114-590021-81 (for ICAO Operation). If modified by Kit 114-0002-1, POH Part Number 114-590021-57 (Domestic) and 114-590021-161 AFMS or other AFM as allowed by 14 CFR Part 121.141. If modified by Kit 114- 0002-3, POH Part Number 114-590021-81 (for ICAO Operation) and 114-590021- 175 AFMS. S/N UC-1 thru UC-174. AFM Part Number 990-31475, UD-1 thru UD-6. 4. Only handheld fire extinguishers containing Halon 1211 (BCF, CBrC1F2) OR Halotron BrX (2-BTP, C3H2BrF3) are approved for use. No airplanes may have any combination of dissimilar agents installed on a particular unit. NOTE 1. Current weight and balance data, loading information and a list of equipment included in empty weight must be provided for each airplane at the time of original certification. (a) Basic empty weight includes unusable fuel of 40.6 lb. at (+298.6 in.) with 8.6 lbs., being undrainable. (UA-1 & On, UB-1 & On) Basic empty weight includes unusable fuel of 73.2 lb. at (+299.5 in.) with 16.4 lbs., being undrainable. (UC-1 & On, UD-1 & On) (b) Basic empty weight includes engine oil of 57.5 lb. at (+249.3 in.) with 33.7 lb. being unusable. NOTE 2. All placards required in the AFM must be installed in the appropriate location. Rev. 132 29 A24CE Data Pertinent to Models 1900, 1900C and 1900C (C-12J) (cont’d) NOTE 3. Structural components with life limits are contained in the Model 1900 Airliner Series ALM P/N 129-590000-133. These limitations may not be changed without FAA Engineering approval. NOTE 4. The maximum propeller shaft overspeed limit is 110% (1870 r.p.m.) of all ratings. 100% propeller shaft speed is defined as 1700 r.p.m. and is the normal steady state operating limit. Gas generator speeds up to 104% are for unlimited periods subject to applicable temperature and other limits. 100% gas generator speed is defined as 37,500 r.p.m. NOTE 5. Flight idle prop low pitch stop is set at 1500 r.p.m. The torque is a variable function of altitude and O.A.T. Sea level, standard day torque is 1500 ft-lbs. at 1500 r.p.m. NOTE 6. Emergency use of MIL-G-5572: Grades 80 Red, 91/96, 100 Green, 115/145 and 100 LL Blue are permitted for a total time not to exceed 150 hours between engine overhauls. It is not necessary to purge the unused fuel from the system when switching fuel types. NOTE 7. See Model 1900/1900C POH/AFM (P/N 114-590021-3; 114-590021-81; 990-31475; or 114-590021-57) for the Loading Data Cargo Configuration. Any exceptions to the procedures found in the POH/AFM will require approval by a local FAA Office. Maximum Baggage, Model 1900 150 lbs. at F.S. 65.5 (distributed over F.S. 43.0 to 84.0) 250 lbs. at F.S. 163.6 (distributed over F.S. 150.6 to 175.6) 293 lbs. at F.S. 190.6 (distributed over F.S. 175.6 to 205.6) 250 lbs. at F.S. 499.5 (distributed over F.S. 483.5 to 513.5) 565 lbs. at F.S. 533.0 (distributed over F.S. 513.5 to 557.5) Maximum Baggage, Model 1900C 150 lbs. at F.S. 65.5 (distributed over F.S. 43.0 to 84.0) 250 lbs. at F.S. 163.6 (distributed over F.S. 150.6 to 175.6) 880 lbs. at F.S. 483.5 (distributed over F.S. 453.5 to 513.5) 630 lbs. at F.S. 533.0 (distributed over F.S. 513.5 to 557.5) NOTE 8. Model 1900/1900C airplanes with serial numbers identified are eligible for export to countries noted below and meet the airworthiness requirements of ICAO Annex 8 at the maximum takeoff weights noted when modified by the indicated Beech drawings or kits: Country Maximum Takeoff Weight (lbs.) Serial Eligibility Beech Drawing or Kit Germany 16,600 UB-1 & On 114-4020 or 118-005007 Germany 16,600 UA-1 & On; UC-1 & On 118-005007 Zambia 16,600 UC-1 & On 118-005006 Canada 16,600 UA-1 & On; UB-1 & On, UC-1 & On 118-005008 France 16,600 UC-1 & On 118-005009 When a Model 1900/1900C series airplane is not modified with a drawing or kit referenced above, or by Raytheon Aircraft modification drawing 118-005003, the airplane does not meet ICAO requirements for weights in excess of 5,700 kg and shall have the following statement entered on the airworthiness certificate: “This airplane, at weights in excess of 5,700 kg, does not meet the airworthiness requirements of ICAO, prescribed by Annex 8 of the Convention of International Civil Aviation.” When the above referenced modifications have been completed to meet ICAO requirements, the airworthiness certificate should be re-issued removing the above referenced statement. Likewise, when the above modifications have been removed from the airplane, the standard airworthiness certificate shall be reissued including the above referenced statement. NOTE 9. SFAR 41C, Paragraph 1, includes Instrument Arrangement and Visibility requirements of Appendix A of FAR Part 135. These requirements apply to both Pilot and Copilot stations. No deletions or relocation of required instruments is authorized at either pilot station. (Refer to POH Limitations for a listing of required Navigation Instruments.) Replacement of instruments with approved substitutes is authorized. A24CE 30 Rev. 132 Data Pertinent to Models 1900, 1900C and 1900C (C-12J) (cont’d) NOTE 10. Model 1900C, UC-18 and UC-21, is certified in the restricted category only for the purpose of maritime patrol, at 17,600 pounds gross weight, provided the pertinent limitations, as specified by POH and AFMS, P/N 114-590021-103, are followed and the aircraft is marked to comply with FAR Part 45. FAR 23.1 and FAR 23.473(d) are inappropriate. NOTE 11. Model 1900C, UC-51 and UC-52, are certified in the restricted category only for the purpose of aerial surveying, at 17,600 pounds gross weight, provided the pertinent limitations as specified by POH and AFMS, P/N 114-590021-133, are followed, maximum allowable airspeed indicator 114-380012-7 is installed on pilot's and copilot's sides, and the aircraft is marked to comply with FAR Part 45. FAR 23.1 and FAR 23.473(d) are inappropriate. NOTE 12. Model 1900C, UC-1 through UC-174, are certified in the normal category at 17,600 lbs. maximum takeoff weight provided the pertinent limitations, as specified by POH and AFMS, P/N 114-590021-161, are followed and Kit 114-0002-1 is installed, or provided the pertinent limitations, as specified by POH and AFMS, P/N 114-590021-175, are followed and Kit 114-0002-3 is installed. VIII. Model 300, Super King Air (Normal Category), Approved January 24, 1984 Model 300LW, Super King Air (Normal Category), Approved September 30, 1988 (See NOTES 12 & 14) NOTES: refer to Data Pertinent to Model 300/300LW Engine Two Pratt & Whitney of Canada PT6A-60A (turboprop) per Beech Specification BS 23433B. 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. 13044 or ASTM SPEC. D1655. See NOTE 6 for emergency fuels. Oil (Engine & Gearbox) P&WC PT6 Engine Service Bulletin No. 13001 lists approved brand oils. Engine Limits Shaft Horsepower Torque Ft-Lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff (5 min.) 1050 *100% 104% 1700 820 Max. continuous 1050 **100% 104% 1700 820 Starting transient (5 sec.) 1000 Max. reverse (1 min.) 900 1650 760 (*100% torque: 3,200 ft./lbs.) (**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. The POH provides minimum torque settings for takeoff. It must be possible to achieve these settings without exceeding ITT or N1 limits. Oil temperatures: Minus 40˚C. minimum starting Minus 40˚C. to 110˚C. low idle 0˚C. to 110˚C. max. continuous Propeller and Two Hartzell HC-B4MP-3B with Hartzell M10476K, M10476NK or Propeller Limits M10476NSK blades Diameter: 105.0 in. (maximum); Minimum allowable for repair: 104 in. No further reduction permitted. Pitch settings: Flight idle stop See NOTE 5 Reverse -14˚ ± 0.2˚ Feathered +79.5˚ ± 0.3˚ Avoid continuous operation on ground below 1050 rpm Rev. 132 31 A24CE VIII. Model 300, Model 300LW (cont’d) Airspeed Limits Max. operating speed 298 m.p.h. (259 knots) up to 20,200 ft. (CAS) Max. operating Mach No. 0.58 Maneuvering speed 208 m.p.h. (181 knots) Maximum flap extension speed Approach position 14˚ 230 m.p.h. (200 knots) 100% position 35˚ 181 m.p.h. (157 knots) Landing gear extended 208 m.p.h. (181 knots) Landing gear operating Extension 208 m.p.h. (181 knots) Retraction 188 m.p.h. (163 knots) C.G. Range (Landing (+178.75) to (+192.1) at 12,500 lb. (Model 300LW) Gear Extended) (+182.5) to (+192.1) at 14,000 lb. (Model 300) (+177.0) to (+192.1) at 11,800 lbs. Straight line variation between points given moment change due to retracting landing gear: 5815 in.-lbs. Empty Wt. C.G. Range None Maximum Weight Item Model 300 (lbs.) Model 300LW (lbs.) Ramp 14,100 12,600 Takeoff 14,100 12,500 Landing 14,100 12,500 Zero fuel 11,500* 11,500 Max. basic empty weight N/A 8,819 *See NOTE 1 Minimum Crew One pilot Two pilots (FF serials only; see NOTE 10) No. of Seats and Maximum 15 (including crew at +129). (See NOTES 8 & 13 for Model 300LW.) Cabin Loading See loading instructions in POH for approved seating and cargo configurations. Maximum Baggage 550 lbs. (+325) Fuel Capacity Tank Cap. Gal. Usable Gal. Arm Main LH 193.0 190.0 185.1 Main RH 193.0 190.0 185.1 Auxiliary LH 80.0 79.5 204.7 Auxiliary RH 80.0 79.5 204.7 See NOTE 1(a) for data on unusable fuel Oil Capacity 28 qt. total (includes 12 qt usable in two integral engine tanks) (See NOTE 1(b) for data on unusable oil) Maximum Operating Altitude 35,000 ft. Control Surface Movements Wing flap Maximum 35˚ Aileron tabs Up 15˚ Down 15˚ Aileron Up 25˚ Down 15˚ Elevator tabs Up 3˚ 30’ Down 15˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Serial Nos. Eligible Model 300: FA-1 thru FA-125, FA-127, FA-128, FA-130 thru FA-230 Model 300: FF-1 thru FF-19 Model 300LW: FA-1 & On (FA-126 and FA-129 converted to FF-1 and FF-2 respectively) A24CE 32 Rev. 132 Data Pertinent to Models 300 and 300LW Datum Located 190.0 in. forward of the wing main (forward) spar centerline. Leveling Means Two external screws on left side of fuselage forward of entrance door. Certification Basis SFAR 41C, effective September 13, 1982, (See NOTE 7 or 11 (Model 300 only)); FAR Part 23, effective February 1, 1965, through Amendment 23-9; Amendment 23-11; Amendment 23-14, 23.143(a), 23.145(d), 23.153, 23.161(c)(3), 23.173(a), 23.175, 23.427, 23.441, 23.445; Amendment 23-15, 23.951(c) and FAR 23.997(d); Amendment 23-23, 23.1545(a); Amendment 23-26, 23.967, 23.1305(n), 23.1529; Special Conditions No. 23-47-CE-5, including Amendments 1, 2, 3, dated November 15, 1982, and 4 dated October 17, 1986; FAR Part 25, 25.929, effective February 1, 1965, Amendment 25-23, 25.1419; Amendment 25-41, 25.831(d); FAR Part 36, through Amendment 36-10, and SFAR 27, through Amendment 27-4. Compliance with ice protection has been demonstrated in accordance with FAR 25.1419 when ice protection equipment is installed in accordance with the Equipment List. Production Basis Production Certificate No. 8. A production certificate was issued and the manufacturer is authorized to issue airworthiness certificates under the delegation option authorization provisions of 14 CFR Part 21. 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 system to include stall warning lift computer, P/N 101-380005-23 and stall warning lift transducer, P/N 101-380005-9. 2. Maximum allowable airspeed indicator (a) 101-380068-5 Pilot and Copilot's sides (Model 300) or (b) 101-380068-9 Pilot and Copilot's sides (Model 300LW) or (c) 101-380068-7 Pilot and Copilot's sides (Model 300-ICAO Operation, (see NOTE 7) 3. POH P/N 101-590097-3 (Model 300 only) (a) Refer to Limitations Section for Special Equipment Requirements for Minimum Crew of One Pilot. or 4. POH P/N 101-590097-59 for Model 300 only for ICAO Operation. (a) Refer to Limitations Section for Special Equipment Requirements for Minimum Crew of One Pilot. or 5. POH P/N 101-590097-107 (Model 300LW only) (a) Refer to Limitations Section for Special Equipment Requirement for minimum crew of one pilot. NOTE 1. Current weight and balance data, loading information and a list of equipment included in empty weight must be provided for each airplane at the time of original certification. a. Basic empty weight includes unusable fuel of 52 lbs., at (+168 in.) with 10 lbs., being undrainable. b. Basic empty weight includes engine oil of 57 lbs., at (+118 in.) with 33.7 lbs., being unusable. NOTE 2. All placards required in the AFM must be installed in the appropriate location. NOTE 3. Mandatory retirement times for all structural components are contained in the ALM P/N 101-590097-161 for Models 300 and 300LW (FA-2 & On). These Limitations may not be changed without FAA Engineering approval. Rev. 132 33 A24CE Data Pertinent to Models 300 and 300LW (cont’d) NOTE 4. The maximum propeller shaft overspeed limit is 110% (1870 r.p.m.) of all ratings. 100% propeller shaft speed is defined as 1700 r.p.m. and is the normal steady state operating limit. Gas generator speeds up to 104% are for unlimited periods subject to applicable temperature and other limits. 100% gas generator speed is defined as 37,500 r.p.m. NOTE 5. Flight idle propeller low pitch stop is set so that at 1500 r.p.m. the engine torque is 42% for sea level, standard day conditions. Ground idle low pitch stop is set so that at 62 to 64% N1 prop r.p.m. is not less than 1050 r.p.m. NOTE 6. Emergency use of aviation gasoline: Use of Grades 80, 100, or 100LL aviation gasoline per ASTM D910, or Grades 80/87, 91/96, 100/130, or 115/145 aviation gasoline per MIL-G-5572 is permitted for a total time period not to exceed 150 hours’ time between engine overhauls. It is not necessary to purge the unused fuel from the system when switching fuel types. NOTE 7. The Model 300, FA-2 & On, is eligible for export to the countries noted below and meets the airworthiness requirements of ICAO Annex 8 at the maximum takeoff weights noted when modified to the following Beech drawings: Country Maximum Takeoff Weight (lbs.) Beechcraft Drawing or Kit United Kingdom 14,000 101-005064-1 United Kingdom 12,500 101-005064-3 Canada 14,000 101-005080-1 Germany 14,000 101-005079-1 Italy 12,500 101-5093-3 South Africa 14,000 101-005067-1 Brazil 14,000 101-5114-1 Australia 12,500 101-5093-9 Germany 12,500 101-005079-3 When a Model 300 (FA-2 and On) airplane is not modified with a drawing or kit referenced above, or by Raytheon Aircraft kit drawing 101-5084, the airplane does not meet ICAO requirements for weights in excess of 5,700 kg and shall have the following statement entered on the airworthiness certificate: “This airplane at weights in excess of 5,700 kg does not meet the airworthiness requirements of ICAO, as prescribed by Annex 8 of the Convention of International Civil Aviation.” When the above referenced modifications have been completed to meet the ICAO requirements, the airworthiness certificate should be re-issued removing the above referenced statement. Likewise, when the above modifications have been removed from the airplane, the standard airworthiness certificate shall be reissued including the above referenced statement. NOTE 8. Models 300 and 300LW meet FAR 135 criteria in effect September 26, 1978, when configured at the factory in accordance with Beech Drawing 101-000011 (FA serials) or 101-000014 (FF serials). Maximum seating capacity for Model 300LW for FAR 135 operation is nine (excluding crew). NOTE 9. SFAR 41C, Paragraph 1, includes Instrument Arrangement and Visibility requirements of Appendix A of FAR Part 135. These requirements apply to both Pilot and Copilot stations. No deletion or relocation of required instruments is authorized at either pilot station (refer to POH Limitations for a listing of required Navigation Instruments). Replacement of instruments with approved substitutes is authorized. NOTE 10. Two pilot requirements established by pedestal equipment location. FF serials are defined by Drawing 101-000014, plus POH Supplements 101-590097-93 and 101-590097-103. Upon incorporation of Beech Kit 101-5111-19, FF-1 & On, are approved for Category II Operation and POH Supplement 101-590097-127 replaces 101-590097-93. NOTE 11. For FF S/N, unless Beech Kit 101-5084-3 has been incorporated, the following must be entered on the Airworthiness Certificate: "This airplane at weights in excess of 5,700 KG does not meet the Airworthiness Requirements of ICAO, as prescribed by Annex 8 of the convention of International Civil Aviation." A24CE 34 Rev. 132 Data Pertinent to Models 300 and 300LW (cont’d) NOTE 12. Beech Drawing 101-5093-7 describes changes to the Model 300 for conversion to Model 300LW configuration. NOTE 13. Model 300LW airplanes placed on the Australian Register, the maximum occupancy is limited to 11 places unless equipped with a cockpit voice recorder system approved by the Civil Aviation Authority. NOTE 14. For any Model 300, manufactured and awarded an FAA Standard Airworthiness Certificate before October 17, 1991, and subsequently converted to a Model 300LW, there is no time limit for re-conversion to a Model 300. IX. Model B300, Super King Air (Commuter Category), Approved December 12, 1989 (See NOTE 12) Model B300C, B300C(MC-12W), B300C(UC-12W), Super King Air (Commuter Category), Approved September 7, 1990 Model B300, B300C, Super King Air (Restricted Category), Approved June 27, 2014 NOTES: refer to Data Pertinent to Model B300/B300C Engine Two Pratt & Whitney of Canada PT6A-60A (turboprop) per Beech Specification BS 23433B (See NOTE 17 for alternate P&W PT6A-67A production or kit installation). 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. 13044 or ASTM Spec. D1655; and Chinese No. 3 Jet Fuel. (See NOTE 6 for emergency fuels). Oil (Engine & Gearbox) P&WC PT6 Engine Service Bulletin No. 13001 lists approved brand oils Engine Limits Shaft Horsepower Torque ft-lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff 1050 100%* 104% 1700 820 Max. continuous 1050 100%* 104% 1700 820 Starting transient (5 sec.) 1000 Max. reverse (1 min.) 900 1650 760 (*100% torque: 3,244 ft. lbs) (*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. The POH provides static torque settings for takeoff. It must be possible to achieve these settings without exceeding ITT or N1 limits. Oil temperatures: Minus 40˚C. minimum starting Minus 40˚C. to 110˚C. low idle 10˚C. to 110˚C. max. continuous Propeller and Two Hartzell HC-B4MP-3C hubs with Hartzell M10476K, M10476NK or Propeller Limits M10476NSK blades. Diameter: 105 in. (maximum); Minimum allowable for repair: 104 in. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5 Reverse -14˚ ± 0.5˚ Feathered +80.0˚ ± 0.5˚ Minimum idle speed 1050 rpm Rev. 132 35 A24CE IX. Models B300, B300C, B300C(MC-12W), B300C(UC-12W) (cont’d) Airspeed Limits Max. operating speed 302 m.p.h. (263 knots) up to 21,000 ft. (IAS) 263 to 194 knots (0.58 Mach) 21,000 ft. up to 35,000 ft. Max. operating Mach No. 0.58 Maneuvering airspeed 212 m.p.h. (184 knots) Maximum flap extension speed Approach position 14° 232 m.p.h. (202 knots) 100% position 35° 182 m.p.h. (158 knots) Landing gear extended 212 m.p.h. (184 knots) Landing gear operating Extension 212 m.p.h. (184 knots) Retraction 191 m.p.h. (166 knots) C.G. Range (Landing (+199.4) to (+208.0) at 15,000 lb. Gear Extended) (+191.4) to (+208.0) at 11,800 lb. (See NOTES 15, 16 & 32) Straight line variation between points given. Moment changes due to retracting landing gear: 5815 in.-lbs. Empty Wt. C.G. Range None Maximum Weight Ramp 15,100 lbs. (See NOTES 15 & 16) Takeoff 15,000 lbs. Landing 15,000 lbs. Zero fuel 12,500 lbs. (See NOTE 1) Minimum Crew One pilot No. of Seats and Maximum 17 (including two crew at +129) (See NOTE 7). See loading instructions in Cargo Loading POH for approved seating and cargo configurations. Maximum Baggage 550 lbs. (+359); 510 lbs. with foldup seats installed (S/N FL-1 thru FL-380, and FL-382, FM-1 thru FM-11 only) Fuel Capacity Tank Cap. Gal. Usable Gal. Arm* Main LH 193.0 190.0 199.5 Main RH 193.0 190.0 199.5 Auxiliary LH 80.0 79.5 219.1 Auxiliary RH 80.0 79.5 219.1 *See POH and FAA Approved AFM for variations *See NOTE 1(a) for data on unusable fuel. See NOTE 15 for extended range fuel capacity Oil Capacity 20 qt. total (10 qts. each engine) (includes 6 qt usable in each integral engine tank) (See NOTE 1(b) for data on unusable oil) Maximum Operating 35,000 ft. Altitude Control Surface Wing flap Maximum 35˚ Movements Aileron tabs Up 15˚ Down 15˚ Aileron Up 24˚ Down 16˚ Elevator tabs Up 3˚ Down 15˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Serial Nos. Eligible Model B300: FL-1 & On (See NOTE 10). Model B300C: FM-1 & On, FN-1 & On (See NOTE 10). A24CE 36 Rev. 132 Data Pertinent to Models B300, B300C, B300C (MC-12W), B300C (UC-12W) Datum Located 83.5 in. forward of center of front jack point. Leveling Means Two external screws on left side of fuselage immediately forward of entrance door. Certification Basis FAR Part 23 effective February 1, 1965, as amended by Amendments 23-1 through 23-34; FAR Part 36 effective December 1, 1969, as amended by Amendment 36- 1 through 36-15 (see NOTE 26); SFAR 27 effective February 1, 1974, as amended by Amendments 27-1 through 27-5 and Exemption No. 5077 from compliance with Section 23.207(c). Special Conditions 23-ACE-48A effective August 13, 1990, apply to Electronic Flight Instrument System (EFIS) equipped airplanes. FAR Part 23 Sections 23.201, 23.203, 23.205 through amendment 23-45 (S/N FN-1 & On only). Effective January 20, 1994, FAR 23.1457 as amended by Amendment 23.35. Exemption 5599 from compliance with 23.53(c)(1), for use of ground minimum control speed (Vmcg) for determination of takeoff decision speed (V1), (S/N FL-111 & On, FM-9 & On, FN-2 & On, or prior airplanes modified by Beech Kit 130-3004). Exemption 6405 from compliance with 23.807(d)(1)(i) to allow a single emergency exit, in addition to the cabin door. Compliance with ice protection has been demonstrated in accordance with FAR 23.1419 when ice protection equipment is installed in accordance with the Equipment List. Equivalent Safety Findings: 23.781(b) for shape of the propeller control knob; 23.1305(g) for use of fuel low pressure warning annunciators in lieu of the fuel pressure indicators; 23.1321(d) for the basic "T" instrument panel arrangement. Does Not Apply to Pro Line 21 Equipped Aircraft Additional requirements for Collins Pro Line 21 Avionics Installation: Special Conditions 23-131-SC, and ELOS ACE-02-17 for FAR 23.1305(c)(2), 23.1305(a)(2)(3), 23.1549(a)(b)(c)(d), for direct reading only displays for oil pressure, oil temperature, and fuel flow; 23.301(a) as amended by Amendment 23-42; 23.1322(a)(b)(c)(d)(e), 23.1331(a)(b)(c), 23.1357(a)(b)(c)(d) as amended by Amendment 23-43; FAR 23.305(a)(b), 23.397(a)(b), 23.613(a)(b)(c)(d)(e), 23.672(a)(b)(c), 23.1525, 23.1549(a)(b)(c)(d) as amended by Amendment 23-45; 23.561(a)(b), 23.607(a)(b)(c), 23.611 as amended by Amendment 23-48; 23.677(a)(b)(c)(d), 23.867(a)(b), 23.1303(a)(b)(c)(d)(e)(f), 23.1309(a)(b)(c)(e), 23.1311(a)(b), 23.1321(a)(b)(c)(d)(e), 23.1323(a)(b)(c)(e), 23.1329(a)(b)(d)(e)(f)(g)(h), 23.1351(a)(c), 23.1353(h), 23.1359(c), 23.1365(d)(e), 23.1431(a)(b)(d)(e) as amended by Amendment 23-49; 23.1325(a)(b), 23.1545(a)(b)(c), 23.1583(h), 23.1585(a)(j) as amended by Amendment 23-50; 23.771(a), 23.777(a)(b) an amended by Amendment 23-51; 23.1305(a)(c)(e) as amended by Amendment 23-52. Additional requirements for Rockwell Collins Pro Line Fusion Installation: FAR 23.301(a) as amended by Amendment 23-42, 23.937(a), 23.1322, 23.1331(a)(b)(c), 23.1357(a)(b)(c)(d) as amended by Amendment 23-43, 23.305(a)(b), 23.613(a)(b)(c)(d)(e), 23.1525, 23.1549(a)(b)(c)(d) as amended by Amendment 23-45, 23.607, 23.611 as amended by Amendment 23-48, 23.867(a)(b)(c), 23.1303(a)(b)(c)(e)(f)(g), 23.1309(a)(1)(3)(4)(b)(c)(d)(e), 23.1311(a)(b)(c), 23.1321(a)(b)(c)(d)(e), 23.1323(a)(c)(e), 23.1329(c)(h), 23.1351(a)(2)(ii), 23.1353(h), 23.1359(c), 23.1365(a)(b)(d)(e), 23.1431(a)(b)(e) as amended by Amendment 23-49, 23.1325(a)(b)(1)(2)(ii), 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(h)(m), 23.1585(a)(j) as amended by Amendment 23-50, 23.777(a)(b) as amended by Amendment 23-51, 23.1305(a)(2)(3) (5)(c)(1)(2)(3)(4)(5)(6)(7)(e)(1)(2) as amended by Amendment 23-52, 23.1308(a)(b)(c) as amended by Amendment 23-57, 23.1457(a)(6) as amended by Amendment 23-58 (see NOTE 25), and 23.1306(a)(b) as amended by Amendment 23-61, and ELOS ACE-15-06 for 23.1549(a)(b)(c) Amendment 23-45, 23.1311(a)(6) Amendment 23-49, and 23.1305(a)(2)(3)(c)(2)(5) Amendment 23-52. Effective at S/N FL-954, FL-1010, FL- 1031 & On, FM-66 & On. Rev. 132 37 A24CE Data Pertinent to Models B300, B300C, B300C (MC-12W), B300C (UC-12W) Certification Basis (cont’d) Additional requirements for the L3 Communications Digital Flight Data Recorder installation on Rockwell Collins Pro Line Fusion equipped B300/B300C models: 23.301(b) as amended by Amendment 23-28; 23.301(a) as amended by Amendment 23-42; 23.1357(a)(c) as amended by Amendment 23-43; 23.613(a)(b)(c) as amended by Amendment 23-45; 23.607, 23.611 as amended by Amendment 23-48; 23.867, 23.1309(a)(1)(3)(4)(b)(e), 23.1365(a)(b)(d)(e), 23.1431(a)(b) as amended by Amendment 23-49; 23.1308 as amended by Amendment 23-57; 23.1459 as amended by Amendment 23-58. Effective at S/N FL-954, FL-1010, FL-1031 & On, FM-66 & On. Additional requirements for the Collins IFIS Installation: 23.321 as amended by Amendment 23-45; 23.337, 23.574, 23,575 as amended by Amendment 23-48; 23.1365(a) as amended by Amendment 23-49; 23.1555(a), 23.1581(a), 23.1583(h), 23.1585(j) as amended by Amendment 23-50; Effective at S/N: Model B300, FL-538 and FL-544 & On, and Model B300C, FM-15 & On. Additional requirements for the Rockwell Collins Flight Guidance Computer FGC-3000 installation (Collins Pro Line 21 Avionics is required before having the FGC-3000 installed on the airplane): 23.1357(a) as amended by Amendment 23-43; 23.677(a), 23.867(a)(b)(c), 23.1309(b)(c)(d)(e), 23.1329(e) as amended by Amendment 23-49, 23.143(b) as amended by Amendment 23-50, 23.1308(a)(b)(c)(d) as amended by Amendment 23-57, and 23.1581(a) as amended by Amendment 23-50. Effective at S/N: Model B300, FL-748 & On, and Model B300C, FM-50 & On. Additional requirements for the installation of SMR Technologies pneumatic deicer boots: 23.613, 23.1525 as amended by Amendment 23-45, 23.1309 as amended by Amendment 23-49, 23.1581, 23.1583(h), 23.1585 as amended by Amendment 23-50. Additional requirements for Rockwell Collins Pro Line Fusion iTAWS Installation: 23.1555(b); 23.1581(a) as amended by Amendment 23-50. Effective at S/N: FL-1310 & On; FM-110 & On. Additional requirements for Models B300/B300C operated in restricted category at increased gross weight of 17,500 lbs. (See NOTES 8 & 19) Additional requirements for Model B300 equipped with the optional high density 11 or 13 passenger slick headliner configurations: 23.1443(b)(1)(2)(c) as amended by Amendment 23-62. Effective at S/N: FL-1101 & On. Additional requirements for Models B300/B300C operated at increased maximum zero fuel weight of 13,400 lbs., (see NOTE 21): 23.337 and 23.343 as amended by Amendment 23-48. Additional requirements for GPS-4000S Installation on Models B300/B300C (see NOTE 22): 23.867(a)(b) as Amended by Amendment 23-49; 23.1301(a)(b)(c)(d) as amended by Amendment 23-20; 23.1306(b) as amended by Amendment 23-61; 23.1308(b) as amended by Amendment 23-57; 23.1309(a)(1)(3)(4)(b)(c)(1)(2)(i)(iii) (3)(d)(e), 23.1351(a)(1)(2)(ii), and 23.1431(a)(b) as amended by Amendment 23-49; 23.1529 as amended by Amendment 23-26. Effective at S/N: FL-1140 & On, FM-76 & On A24CE 38 Rev. 132 Data Pertinent to Models B300, B300C, B300C (MC-12W), B300C (UC-12W) Certification Basis (cont’d) Additional requirements for Models B300/B300C IS&S Autothrottle installation: 23.1322, 23.1357(a)(b)(c)(d) as amended by Amendment 23-43; 23.23, 23.305, 23.613, 23.672(a)(b) as amended by Amendment 23-45; 23.301, 23.607, 23.611 as amended by Amendment 23-48; 23.691, 23.867(a)(b), 23.1307, 23.1321(a)(c)(d)(e), 23.1329(h), 23.1351(a)(1)(2)(ii)(b), 23.1359(c), 23.1365 as amended by Amendment 23-49; 23.143(a)(b), 23.149, 23.207(a)(b)(c)(d)(e), 23.1325(a)(b)(1)(2)(ii), 23.1543(b)(c), 23.1581 as amended by Amendment 23-50; 23.779(b)(1) as amended by Amendment 23- 51; 23.1305(c)(1)(e)(1) as amended by Amendment 23-52; 23.1308 as amended by Amendment 23-57; 23.1306 as amended by Amendment 23-61; 23.561(b)(3), 23.777(a)(b), 23.1301, 23.1303, 23.1309, 23.1310, 23.1311, 23.1323(a)(c), 23.1331(a)(b)(1)(c)(1)(2), 23.1353(h) (See NOTE 24), 23.1431(a)(b)(e), 23.1545(a)(b)(c), 23.1555(a), 23.1583(m), 23.1585(a)(c)(d)(e)(f)(g)(j), 23.1587 as amended by Amendment 23-62; 23.773(a)(2) as amended by Amendment 23-63. Special Conditions 23-291-SC, effective at S/N: FL-1300, FL-1307 & On, FM-110 & On Additional requirements for Models B300/B300C equipped with extended nose kit (See NOTE 23): 36.2(b) as Amended by Amendment 36-24; 36.9(a) as Amended by Amendment 36-19; 36.501(c) as Amended by Amendment 36-19; 36.1581(a)(2)(b)(c) as Amended by Amendment 36-25. Additional requirements for Models B300/B300C operated at a Max Takeoff Weight of 16,500 lbs. (See NOTES 15 and 16): 23.49, 23.201, 23.203, 23.205, 23.207 as amended by Amendments 23-1 through 23-50. Additions for 14 CFR Part 23, Amendment 64: 14 CFR 23.2000, 23.2005, 23.2010 as amended by Amendment 23-64 (see NOTE 27). Effective at S/N FL-1385 & On and FM-142 & On. Additional requirements for Models B300/B300C L3 Model 7100 CVR and optional Recorder Independent Power Supply (RIPS) system installation: 23.1322(b)(c) as amended by Amendment 23-43; 23.1309(a)(1)(3)(4)(b)(2)(3)(4)(e), 23.1351(a)(2)(ii), 23.1353(h), 23.1365(a)(b)(d)(e), 23.1431(a)(b) as amended by Amendment 23-49; 23.1457(a)(6)(d)(5) as amended by Amendment 23-58 (see NOTE 28); 23.2325(g) (see NOTE 29), 23.2510 (see NOTE 30), 23.2525(a) (see NOTE 31), 23.2605(c) (see NOTE 30) as amended by Amendment 23-64. Effective at S/N FL-1385 & On and FM-142 & On. Additional requirements for the Model B300 Becker Digital Voice Communications System installation (see NOTE 32): 23.1322(b)(c)(e), 23.1357(a)(1)(2)(b)(c)(1)(2)(d) as amended by Amendment 23-43; 23.773(a)(1)(2) as amended by Amendment 23-45; 23.867(a)(b)(c), 23.1303(e)(1), 23.1309(a)(1)(3)(4)(b)(2)(3)(4)(c)(1)(2)(i)(iii)(3)(d)(e), 23.1351(a)(2)(ii), 23.1353(h), 23.1365(a)(b)(d)(e), 23.1431(a)(b)(e) as amended by Amendment 23-49; 23.49(a)(2)(3)(4)(5)(6)(b), 23.1555(a), 23.1581(a)(1)(2)(b)(1)(d), 23.1583(m), 23.1585(j) as amended by Amendment 23-50; 23.777(a)(b) as amended by Amendment 23-51; 23.1308(a)(b)(c) as amended by Amendment 23-57; 23.1457(a)(1)(2)(3)(4)(5)(c)(1)(2)(4) as amended by Amendment 23-58; 23.1306(a)(b) as amended by Amendment 23-61. Effectivity at S/N FL-1357 & On. Additional requirements for the Model B300 Genesys Aerosystems Digital Radio installation (see NOTE 33): 23.1322(b)(c)(e), 23.1357(a)(1)(2)(b)(c)(1)(2)(d) as amended by Amendment 23-43; 23.773(a)(2) as amended by Amendment 23-45; 23.1309(a)(1)(3)(4)(b)(2)(3)(4)(c)(1)(2)(i)(iii)(3)(d)(e), 23.1351(a)(2)(ii), 23.1353(h), 23.1365(a)(e), 23.1431(a)(b) as amended by Amendment 23-49; 23.1555(a), 23.1581(a)(1)(2), 23.1585(j) as amended by Amendment 23-50; 23.777(a)(b) as amended by Amendment 23-51; 23.1308(b)(c) as amended by Amendment 23-57; 23.1306(b) as amended by Amendment 23-61. Effective at S/N FL-1357 & On Rev. 132 39 A24CE Data Pertinent to Models B300, B300C, B300C (MC-12W), B300C (UC-12W) Production Basis Production Certificate No. 8. A production certificate was issued, and the manufacturer is authorized to issue airworthiness certificates under the delegation option authorization provisions of FAR Part 21. Production Certificate No. 4. S/N FL-954, FL-975, FL-988, FL-992, FL-996 thru FL- 999, FL-1001 thru FL-1003, FL-1007, FL-1009 thru FL-1011, FL-1013 thru FL-1079, and FM-63 thru FM-68. Manufactured by Textron Aviation, under license agreement between Beechcraft Corporation and Textron Aviation. S/N FL-1080 & On; FM-69 & On Manufactured under Production Certificate No. 4 by Textron Aviation. 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. Stall warning lift transducer, P/N 101-380005-33, for all serials. Stall warning lift computer, P/N 101-380005-35 (for S/N FL-1 thru FL-393, FM-1 thru FM-11); P/N 101-380005-39 (for S/N FL-394 and On, FM-12 and On or earlier aircraft incorporating Raytheon Aircraft Company Kit 130-3022). 2. Maximum allowable airspeed indicator, P/N 130-380039-3 (S/N FL-1 thru FL-92) or P/N 130-380005-3 (S/N FL-93 thru FL-380 and FL-382). For FL-381 and FL- 383 & On, the airspeed indication is included in the PFD pilot's and copilot's sides. 3. POH P/N 130-590031-1 (for S/N FL-1 thru FL-110 and FM-1 thru FM-8) or P/N 130-590031-71 (for S/N FL-111 thru FL-380, and FL-382; FM-9 thru FM-11) or P/N 130-590031-181 (S/N FL-381, FL-383 thru FL-499, except FL-493, FM-12 and FM-13); or P/N 130-590031-235 (for S/N FL-493, FL-500 thru FL-953, FL-955 thru FL-1009, FL-1011 thru FL1030, FM-14 thru FM-65); or P/N 130-590031-245 (for S/N FL-493, FL-500 thru FL-678, FL-771 thru FL-937 and FM-14 thru FM-35, FM- 39, FM-40, FM-42, FM-44 thru FM-51, FM 54, and FM-55 when modified by drawings 130M000009, 130M000030, 130-4014 or 130-4030); or P/N 130-590031- 499 (for S/N FL-679, FL-770, FL-938 thru FL-953, FL-955 thru FL-1009, and FM- 36 thru FM-38, FM-41, FM-43, FM-52, FM-53, FM-56 thru FM-65 when modified by drawings 130M000009, 130M000030, 130-4014 or 130-4030) or P/N 434- 590169-0003 (for S/N FL-954, FL-1010, FL-1031 & On and FM-66 & On) or P/N 434-590170-0003 (for S/N FL-954, FL-1010, FL-1031 & On and FM-66 & On when modified by drawings 130M000009, 130M000030, 130-4014 or 130-4030). NOTE 1. Current weight and balance data, loading information, and a list of equipment included in empty weight must be provided for each airplane at the time of original certification. a. Basic empty weight includes unusable fuel of 52 lbs., at (+182.4 in.) with 10 lbs., being undrainable. b. Basic empty weight includes engine oil of 57 lbs., at (+132.4 in.) with 33.7 lbs., being unusable. NOTE 2. All placards required in the POH, (P/N 130-590031-1 or P/N 130-590031-71 or P/N 130-590031-181 or P/N 130-590031-235 or P/N 130-590031-245 or P/N 130-590031-499 or P/N 434-590169-0003 or P/N 434- 590170-0003) must be installed in the appropriate locations. NOTE 3. Mandatory retirement times for all structural components are contained in the ALM P/N 130-590031-211 (for FL-1 & On, FM-1 & On) and Chapter 4 of the Beechcraft B300 Maintenance Manual Supplement 130- 590031-67 (for FN-1 & On). These limitations may not be changed without FAA Engineering approval. NOTE 4. The maximum propeller shaft overspeed limit is 110% (1870 r.p.m.) of all ratings. 100% propeller shaft speed is defined as 1700 r.p.m. and is the normal steady state operating limit. Gas generator speeds up to 104 percent are for unlimited periods subject to applicable temperature and other limits. 100% gas generator speed is defined as 37,500 r.p.m. NOTE 5. Flight idle propeller low pitch stop is set so that at 1500 r.p.m. the engine torque is 36% for sea level, standard day conditions. Ground idle low pitch stop is set so that at 62 to 64 percent N1 prop r.p.m. is not less than 1050 r.p.m. A24CE 40 Rev. 132 Data Pertinent to Models B300, B300C, B300C(MC-12W), B300C(UC-12W) (cont’d) NOTE 6. Alternate use of aviation gasoline: Use of Grades 80, 100, or 100LL aviation gasoline per ASTM D910, or Grades 80/87, 91/96, 100/130, or 115/145 aviation gasoline per MIL-G-5572 is permitted for a total time period not to exceed 150 hours’ time between engine overhauls. It is not necessary to purge the unused fuel from the system when switching fuel types. NOTE 7. Airplanes with the optional passenger seating of 10 or more through S/N FL-155, must be equipped with the following: the eight cabin seats in the double club cabin arrangement must be of the narrow back configuration, P/N 130-530074-1, -2, -3, -4, -5, -6, -7 or -11, -9 or -12. NOTE 8. The following models have been delivered and are eligible for multiple airworthiness certification per 14 CFR 21.187 in Commuter or Restricted Category at indicated gross weight and other limitations specified by the applicable POH/AFM for any special purpose that is specified by an AFM Supplement to the applicable POH/AFM: Model Purpose FAR’s Inappropriate for Restricted Category Certification Restricted Category Maximum Gross Weight AFM/POH Supplement* B300C Photographic 23.1, 23.775(e), 23.1545(b) 15,000 lbs. 130-590031-65 B300, B300C Patrol 23.335(c), 23.337(a)(b), 23.473(d) 17,500 lbs. 130-590031-501 or 130-590031-537 (see NOTE 19 for kit drawing) B300, B300C Patrol 23.335(c), 23.337(a)(b), 23.473(d) 17,637 lbs. 130-590031-0713 or 130-590031-729 (see NOTE 19 for kit drawing) *Contact Textron Aviation as necessary to obtain availability information concerning the drawings and kits which are referenced by this publication. NOTE 9. The following models are eligible for export to the countries noted when modified to the following Beechcraft drawings: Model Manufactured Configuration Export Country Beechcraft Drawing B300 Export United Kingdom 130-005002* B300, B300C Export Canada 130-005003 B300, B300C Export France 130-005005* B300 Export Russia (CIS) 130-005007 * Only required if modified prior to September 2003 with this installation NOTE 10. Company name change effective 4/15/96. The following serial numbers are manufactured under the name Raytheon Aircraft Company: B300: FL-137 thru FL-423. B300C: FM-9 thru FM-13, FN-1 (RAC, 300). NOTE 11. RVSM capability is per the following STCs, ST01456SE or SA01790SE for Models 300 and 300LW. RVSM capability is per (one of the following) STCs, ST01070SE, ST01278SE, ST01456SE, SA01790SE or SA01798SE for Models B300 and B300C. These STCs approve the noted aircraft to 14 CFR Part 91, Appendix G. Refer to the airplane maintenance logbook for specific RVSM STC incorporated at build. Authorization for RVSM operations must be obtained by the operator from the local FAA Flight Standards District Office (FSDO). RVSM requirements have been incorporated into the type design of production aircraft at FL-850 & On, and FM-55 & On. These aircraft are RVSM compliant to 14 CFR 91, Appendix G at initial airworthiness issuance. Instructions for Continued Airworthiness (ICA) for the production airplanes are now incorporated into the applicable airplane maintenance manual. Authorization for RVSM operations must be obtained by the operator from the local FAA FSDO. NOTE 12. Airplanes modified per Beech drawing 130-4402 are eligible for increased weights in the Commuter Category as defined in POH P/N 130-590031-219. Airplanes that also have the extended range fuel tanks installed are to use POH P/N 130-590031-255. Airworthiness limitations changes are defined Airworthiness Limitations Manual Supplement P/N 130- 590031-221. Certification Basis per Model B300 except FAR 23.49, 23.201, 23.203, 23.205, 23.207 as amended by Amendments 23-1 through 23-50. Rev. 132 41 A24CE Data Pertinent to Models B300, B300C, B300C(MC-12W), B300C(UC-12W) (cont’d) NOTE 13. Company name change effective 3/16/07. The following serial numbers are manufactured under the name of Hawker Beechcraft Corporation: FL-424, FL-521, FL-522, FL-523 and FL-526 thru FL-845; FM-14 thru FM-54 (HBC, 300). NOTE 14. Re-evaluation of structure and fatigue will be required for serial numbers FM-14, FM-16, FM-17, FM-18 and FM-48, with the Wing Hardpoints installed (MOD007710), prior to import back into the United States. NOTE 15. The areas of change from a standard B300 and B300C are listed below: Airplanes modified per Hawker Beechcraft Drawing 130M000030 or Kit Drawing 130-4014 are eligible for increased weights and increased fuel capacity in the commuter category as defined by POH/AFM P/N 130- 590031-245 or POH/AFM P/N 130-590031-499 or POH/AFM P/N 434-590170-0003. Design Weights Max Ramp Weight 16,600 lbs. (7530 kg) Max Takeoff Weight 16,500 lbs. (7484 kg) Max Landing Weight 15,675 lbs. (7110 kg) Max Zero Weight 13,000 lbs. (5897 kg) (see NOTE 21) C.G. Range (Landing Gear Extended) (+203.3) to (+208.0) at 16,500 lbs. (+191.4) to (+208.0) at 11,800 lbs. Straight line variation between points given moment change due to retracting landing gear (-8 307 in.lb.) Fuel Capacities Max Useable Fuel Capacity 5192 lbs. (2361 kg) (1 U.S. gallon = 6.7 lb/ U.S. gal.) 775 U.S. gal Extended Range Fuel Tanks Useable Fuel Capacity (one side) 790 lbs. (359 kg) Extended Range Fuel Tanks Useable Fuel Capacity (total) 1581 lbs. (718 kg) (2 tanks, 118 gal. each) 236 U.S. gal. NOTE 16. The areas of change from a standard B300 and B300C are listed below: Models B300 and B300C airplanes, modified by Hawker Beechcraft Drawing 130M000009 or Drawing 130- 4030, are eligible for increased gross weights in the commuter category as defined by POH/AFM P/N 130- 590031-245 and POH/AFM Supplement for Heavy Weight Aircraft without ER Tanks, P/N 130-590031-321 or as defined by POH/AFM P/N 434-590170-0003. Design Weights Max Ramp Weight 16,600 lbs. (7530 kg) Max Takeoff Weight 16,500 lbs. (7484 kg) Max Landing Weight 15,675 lbs. (7110 kg) Max Zero Weight 13,000 lbs. (5897 kg) (see NOTE 21) C.G. Range (Landing Gear Extended) (+203.3) to (+208.0) at 16 500 lbs. (+191.4) to (+208.0) at 11 800 lbs. Straight line variation between points given. Moment changes due to retracting landing gear: 8307 in. lbs. A24CE 42 Rev. 132 Data Pertinent to Model B300, B300C, B300C(MC-12W), B300C(UC-12W) (cont’d) NOTE 17. Model B300 and B300C airplanes manufactured by Hawker Beechcraft General Assemblies 130-000003 or 130-000004; or modified by Field Service Kit, Drawings 130-9022, 130-9027, or 130-9033, which install Two Pratt & Whitney of Canada, Ltd. PT6A-67A (turboprop) engine per Beech Specification BS 383843. 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. 14004 or ASTM Spec. D1655; Chinese No. 3 Jet Fuel and Commonwealth of Independent States (CIS) RT & TS-1 Fuels. Alternate use of aviation gasoline: Use of Grades 80, 100 or 100LL aviation gasoline per ASTM D910, or Grades 80/87, 91/96, 100/130 or 115/145 aviation gasoline per MIL-G-5572 is permitted for a total time not to exceed 150 hours between engine overhauls. It is not necessary to purge the unused fuel from the system when switching fuel types. Oil P&WC PT6 Engine Service Bulletin No. 13001 lists approved brand oils (Engine & Gearbox) Engine Limits Shaft Horsepower Torque ft. lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff 1050 *100% 104% 1700 850 Max. continuous 1050 *100% 104% 1700 840 Starting transient (20 sec.) 1870 870 Max. reverse (1 min.) 900 1650 760 (*100% torque – 3,244 ft. lbs.) (*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. The POH provides static torque settings for takeoff. It must be possible to achieve these settings without exceeding ITT or N¹ limits. Oil temperatures: Minus 40˚C. minimum starting Minus 40˚C. to 110˚C. low idle 0˚C. to 110˚C. max. continuous Propeller and Two Hartzell HC-E4A-3M hubs with Hartzell E10478SK blades. Propeller Limits Diameter: 105 in. (maximum); minimum allowable for repair, 104 in. No further reduction permitted. Pitch setting: Flight idle stop See NOTE 5 Reverse -14˚ ± 0.5˚ Feathered +80.0˚ ± 0.5˚ Minimum idle speed 1050 rpm NOTE 18. Company name change effective 4/12/13. The following serial numbers are manufactured under the name of Beechcraft Corporation: Model B300: FL-846 thru FL-953, FL-955 thru FL-974, FL-976 thru FL-987, FL-989 thru FL-991, FL-993 thru FL-995, FL-1000, FL-1004 thru FL-1006, FL-1008, FL-1012. Model B300C: FM-55 thru FM-62. NOTE 19. For Models B300 and B300C airplanes modified by Kit 130-9102 or Kit 130-8004 and operated in the restricted category at 17,500 lbs., an Interim Safe Life limit or inspection intervals on the wing and associated structure are required, as noted in Maintenance Manual Supplement, P/N 130-590031-503 or P/N 130- 590031-539 (FL-1 & On and FM-1 & On). For airplanes modified by Kit 130-8011 in the restricted category at 17,637 lbs., (8,000 Kg), an Interim Safe Life limit or inspection intervals on the wing and associated structure are required, as noted in Maintenance Manual Supplement, P/N 130-590031-0743. NOTE 20. Company name change effective 10/12/16. The following serial numbers are manufactured under the name Textron Aviation. Model B300: FL-1080 & On. Model B300C: FM-69 & On. Rev. 132 43 A24CE Data Pertinent to Model B300, B300C, B300C(MC-12W), B300C(UC-12W) (cont’d) NOTE 21. Models B300/B300C airplanes modified by Kit 130-5150 are eligible for operations at an increased maximum zero fuel weight of 13,400 lbs., with additional limitations as defined by POH/AFM Supplement P/N 130-590031-0609, ALM Supplement P/N 130-590031-0605, and SIRM Supplement P/N 130-590031- 0607, unless superseded by a unique serial number fatigue evaluation. NOTE 22. Installation of GPS-4000S due to in-draw of Rockwell Collins STC, SA01848WI, to address the use of a multi-core processor and upgrading of the GPS-4000S receiver. NOTE 23. Model B300 airplanes modified by Textron Aviation kit 130-4050 have an extended nose and use POH/AFM Supplement P/N 130-590031-0681 and Instructions for Continued Airworthiness (ICA) Supplement P/N 130- 590031-0685. Airplanes that also have the Extended Nose Lift Kit 130-4051 installed, additionally use POH/AFM Supplement P/N 130-590031-0683 and ICA Supplement P/N 130-590031-0687. NOTE 24. 14 CFR 23.1353(h) Amendment [23-62] is applicable to the IS&S autothrottle installation ONLY. It is connected to the standby battery system and meets the 60-minute requirement of the later amendment. NOTE 25. Optional datalink message recording capability applies to aircraft with IOC-3100 Part Number 822-1361-622 or 822-1361-623 only. NOTE 26. Per 14 CFR Part 36.2, all product changes that affect acoustics will comply with the latest amendment level of 14 CFR Part 36 that is current at the time of project acceptance. NOTE 27. 14 CFR 23.2005 Certification Level and Performance Level: Level 4, High Speed. NOTE 28. 14 CFR 23.1457(d)(5)[23-58] applicable to Recorder Independent Power Supply (RIPS) only. NOTE 29. The Means of Compliance for 23.2325(g)[23-64] is CPP-23.2525-1 signed 4/17/2023 and CPP-23.2525-4 signed 2/13/2024. NOTE 30. The Means of Compliance for 23.2510 and 23.2605(c)[23-64] is CPP-23.2525-1 signed 4/17/2025. NOTE 31. The Means of Compliance for 23.2525(a)[23-64] is CPP-23.2525-1 signed 10/19/2023 and CPP-23.2525-4 signed 2/13/2024. NOTE 32. The area of change from a standard B300 is listed below: Airplanes modified per Textron Aviation Kit 130-0016 have a CG envelope shift as defined in POH/AFMS P/N 130-590031-0819. C.G. Range (Landing Gear Extended) (+203.2) to (+208.0) at 16,500 lbs. (+196.4) to (+208.0) at 13,800 lbs. (+192.9) to (+207.0) at 12,400 lbs. (+191.4) to (+207.0) at 11,800 lbs. Straight line variation between points given moment change due to retracting landing gear: -8307 in. lbs. NOTE 33. Genesys Aerosystems Digital Radio System cannot be installed without the installation of kit 130-3107, Modular Mission System Provisions, Flight Inspection. NOTE 34. The areas of change from a standard B300 and B300C are listed below: Airplanes modified per Hawker Beechcraft Drawing 130M000030, Kit Drawing 130-4014 or Kit Drawing 130-8004 and Kit Drawing 130-8010 are eligible for increased weights and increased fuel capacity in the commuter category as defined by POH/AFM P/N 130-590031-0775 and Maintenance Manual and SIRM Supplement P/N 130-590031-0773. Design Weights Max Ramp Weight 17,600 lbs. (7983 kg.) Max Takeoff Weight 17,500 lbs. (7938 kg.) Max Landing Weight 16,200 lbs. (7348 kg.) Max Zero Weight 13,000 lbs. (5897 kg.) (see NOTE 21) A24CE 44 Rev. 132 Data Pertinent to Model B300, B300C, B300C(MC-12W), B300C(UC-12W) (cont’d) (NOTE 34 cont’d) C.G. Range (Landing Gear Extended) (+205.8) to (+208.0) at 17,500 lbs. (+191.4) to (+208.0) at 11,800 lbs. Straight line variation between points given moment change due to retracting landing gear: -8307 in. lbs. Fuel Capacities Max Useable Fuel Capacity 5192 lbs. (2361 kg.) 775 U.S. gal. (1 U.S. gallon = 6.7 lb./ U.S. gal.) Extended Range Fuel Tanks Useable Fuel Capacity (one side) 790 lbs. (359 kg.) Extended Range Fuel Tanks Useable Fuel Capacity (total) 1581 lbs. (718 kg.) 236 U.S. gal. (2 tanks, 118 gal. each) X. Model 1900D, Airliner, 21 PCLM (Commuter Category), Approved March 19, 1991 NOTES: refer to Data Pertinent to Model 1900D. Engine Two Pratt & Whitney of Canada PT6A-67D (turboprop) per Beech Specification BS 24442 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. 14004 or ASTM Spec. D1655. See NOTE 7 for emergency fuels. Oil (Engine & Gearbox) P&WC PT6 Engine Service Bulletin No. 14001 lists approved brand oils. Engine Limits Shaft Horsepower Torque ft. lbs. N1 Gas Generator Speed Prop Shaft Speed Max. Permissible Turbine Interstage Temp. (Dec. C) Takeoff (5 min.) 1279 3950 104% 1700* 800 Max. continuous 1214 3750 104% 1700* 780 Starting transient (5 sec.) 1000 Max. reverse (1 min.) 900 1650* 760 (*See NOTE 4) The AFM provides minimum torque settings for T.O. It must be possible to achieve these settings without exceeding ITT or N1 limits. Oil temperatures: Minus 40˚C. minimum starting Minus 40˚C. to 110˚C. low idle 10˚C. to 105˚C. max. continuous Rev. 132 45 A24CE X. Model 1900D (cont’d) Propeller and Two Hartzell HC-E4A-3A hubs with Hartzell E10950K blades (original configuration) Propeller Limits (S/N UE-1 thru UE-136) One or Two Hartzell HC-E4A-3A hubs with Hartzell E10950K blades AND/OR One or Two Hartzell HC-E4A-3I or HC-E4A-3J hubs with Hartzell E10950PK or E10950PCK blades (See NOTES 10 & 12). AND/OR One or Two Hartzell HC-E4A-3I or HC-E4A-3J hubs with Hartzell E10950PB or E10950PCB blades (See NOTES 10 & 13). Diameter: 110.0 in. per Beech Specification 24476. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5 Reverse -14.5° ±0.5° Feather +79° ±0.5° Propeller and Two Hartzell HC-E4A-3I hubs with Hartzell E10950PK blades (original configuration) Propeller Limits (S/N UE-137 thru UE-326) One or Two Hartzell HC-E4A-3I or HC-E4A-3J hubs with Hartzell E10950PK or E10950PCK blades (See NOTES 10 & 12). AND/OR One or Two Hartzell HC-E4A-3I or HC-E4A-3J hubs with Hartzell E10950PB or E10950PCB blades (See NOTES 10 & 13). Diameter: 110.0 in. per Beech Specification 24476. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5 Reverse -14.5˚ ± 0.5˚ Feather +79˚ ± 0.5˚ Propeller and Two Hartzell HC-E4A-3J hubs with Hartzell E10950PB blades (original configuration) Propeller Limits (S/N UE-327 thru UE-401) One or Two Hartzell HC-E4A-3I or HC-E4A-3J hubs with Hartzell E10950PK or E10950PCK blades (See NOTES 10 & 12). AND/OR One or Two Hartzell HC-E4A-3I or HC-E4A-3J hubs with Hartzell E10950PB or E10950PCB blades (See NOTE 10). Diameter: 110.0 In. per Beech Specification 24476. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5 Reverse -14.5˚ ± 0.5˚ Feather +79˚ ± 0.5˚ Propeller and Two Hartzell HC-E4A-3J hubs with Hartzell E10950PCB blades (original configuration) Propeller Limits (S/N UE-402 & On) One or Two Hartzell HC-E4A-3I or HC-E4A-3J hubs with Hartzell E10950PK or E10950PCB blades (See NOTES 10 & 12). AND/OR One or Two Hartzell HC-E4A-3I or HC-E4A-3J hubs with Hartzell E10950PB or E10950PCB blades (See NOTE 10). Diameter: 110.0 in. per Beech Specification 24476. No further reduction permitted. Pitch settings: Flight Idle Stop See NOTE 5 Reverse -14.5˚ ± 0.5˚ Feather +79˚ ± 0.5˚ A24CE 46 Rev. 132 X. Model 1900D (cont’d) Airspeed Limits Max. operating speed 285 m.p.h. (248 knots) up to 13,200 ft. (IAS) Max. operating Mach No. 0.48 Maneuvering airspeed 205 m.p.h. (178 knots) Maximum flap extension speed Partial flap 17.5˚ 216 m.p.h. (188 knots) 100% position 35˚ 165 m.p.h. (143 knots) UE-1 thru UE-78 100% position 35˚ 177 m.p.h. (154 knots) UE-79 & On, and UE-1 thru UE-78, when modified per Beech Service Bulletin No. 2512 Landing gear extended 207 m.p.h. (180 knots) Landing gear operating Extension 207 m.p.h. (180 knots) Retraction 207 m.p.h. (180 knots) C.G. Range (Landing F.S. 282.9 to F.S. 299.9 at 17,120 lbs. Gear Extended) F.S. 274.5 to F.S. 299.9 at 11,600 lbs. or less Straight line variation between points given Moment changes due to retracting landing gear: 8966 in.-lbs. For cruise and descent flight phases at weights 12,313 lbs., and above operation is approved to an aft limit of F.S. 303.0. Empty Wt. C.G. Range None Maximum Weight Ramp 17,230 lbs. Takeoff 17,120 lbs. Landing 16,765 lbs. Zero fuel 15,165 lbs. (See NOTES 1 & 11) Minimum Crew One pilot No. of Seats and Maximum 21 (including two crew at +129) (See NOTE 7). See loading instructions in Cargo Loading the AFM for approved seating and cargo configurations. Maximum Baggage See NOTE 6 for data on maximum baggage. Fuel Capacity Tank Cap. Gal. Usable Gal. Arm Main LH 244.7 240.5 296 Main RH 244.7 240.5 296 Auxiliary LH 93.3 92.2 304 Auxiliary RH 93.3 92.2 304 See NOTE 1(a) for data on unusable fuel Oil Capacity 29 qt. total (includes 12 qt usable in two integral engine tanks) (See NOTE 1(b) for data on unusable oil). Maximum Operating Altitude: 25,000 ft. Control Surface Movements Wing flap Maximum 35˚ Aileron tabs Up 15˚ Down 15˚ Aileron Up 24˚ Down 17˚ Elevator tabs Up 5.5˚ Down 16.5˚ Elevator Up 20˚ Down 14˚ Rudder tab Right 15˚ Left 15˚ Rudder Right 25˚ Left 25˚ Serial Nos. Eligible UE-1 & On (See NOTE 9). Rev. 132 47 A24CE Data Pertinent to Model 1900D Datum Located 290.5 in. forward of the wing (forward) spar centerline. Leveling Means Two external screws on left side of fuselage aft of entrance door. Certification Basis FAR Part 23, effective February 1, 1965, as amended by Amendments 23-1 through 23-34; FAR Part 36 effective December 1, 1969, as amended by Amendment 36- 1 through 36-18; FAR Part 34 effective September 10, 1990. Also, Exemption No. 5078 from 23.207(c), dated August 23, 1989, and Exemption No. 5216 from 23.201(e)(f)(4)(5); 23.203(c)(4)(5); 23.1545(b)(5)(6), dated August 9, 1990, have been granted. Special Conditions 23-ACE-48A, effective August 13, 1990. Equivalent Safety Findings (1) Propeller control knob 23.781(b) (2) Fuel pressure gage 23.1305(g) (3) Instrument panel arrangement 23.1321(d) (4) Landing gear warning "Q" switch 23.729(f)(1) Compliance with ice protection has been demonstrated in accordance with 23.1419 when ice protection equipment is installed in accordance with the Equipment List. Production Basis Production Certificate No. 8. A production certificate was issued, and the manufacturer is authorized to issue airworthiness certificates under the delegation option authorization provisions of FAR Part 21. Equipment The basic required equipment as prescribed in the applicable airworthiness regulation (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. Pre-stall warning system to include: stall warning lift computer, P/N 114-380051-5 and stall warning lift transducer, P/N 114-380051-1. 2. Maximum allowable airspeed indicator, P/N 130-380005-5 on UE-1 thru UE-78. Maximum allowable airspeed indicator P/N 130-380005-7 on UE-79 & On, UE-1 thru UE-78 when modified per Beech Service Bulletin No. 2512. 3. AFM, P/N 129-590000-3, or other AFM as allowed by FAR Part 121.141. 4. Only handheld fire extinguishers containing Halon 1211 (BCF, CBrC1F2) OR Halotron BrX (2-BTP, C3H2BrF3) are approved for use. No airplanes may have any combination of dissimilar agents installed on a particular unit. NOTE 1. Current weight and balance data, loading information and a list of equipment included in empty weight must be provided for each airplane at the time of original certification. a. Basic empty weight includes unusable fuel of 84.3 lbs., at (+300.1 in.) with 14.6 lbs., being undrainable. b. Basic empty weight includes engine oil of 57.5 lbs., at (+249.3 in.) with 33.7 lbs., being unusable. NOTE 2. All placards required in the approved AFM (P/N 129-590000-3) must be installed in the appropriate location. NOTE 3. Structural components with life limits are contained in the Model 1900 Airliner Series ALM P/N 129-590000-133. These limitations may not be changed without FAA engineering approval. NOTE 4. The maximum propeller shaft overspeed limit is 110% (1870 r.p.m.) of all ratings. 100% propeller shaft speed is defined as 1700 r.p.m. and is the normal steady state operating limit. Gas generator speeds up to 104% are for unlimited periods subject to applicable temperature and other limits. 100% gas generator speed is defined as 37,500 r.p.m. NOTE 5. Flight idle prop low pitch stop is set at 1500 r.p.m. The torque is a variable function of altitude and O.A.T. For sea level, standard day conditions, torque is 1650 ft-lbs. to obtain 1500 r.p.m. NOTE 6. Maximum Baggage 250 lbs. at F.S. 163.6 (distributed over F.S. 150.6 to 175.6). 1000 lbs. at F.S. 483.5 (distributed over F.S. 453.5 to 513.5). 630 lbs. at F.S. 533.0 (distributed over F.S. 513.5 to 557.5). A24CE 48 Rev. 132 Data Pertinent to Model 1900D NOTE 7. Emergency use of aviation gasoline. Use of Grades 80, 100, or 100LL aviation gasoline per ASTM D910 or Grades 80/87, 91/96, 100/130, or 115/145 aviation gasoline per MIL-G-5572 is permitted for a total time not to exceed 150 hours between engine overhauls. Operation is prohibited if either standby pump is inoperative. Operation is prohibited above 18,000 feet. Standby pumps must be on for takeoff and landing. NOTE 8. Airplanes with serial numbers identified are eligible for export to the countries listed below when modified by the indicated Beech drawings or kits: Model Serial Number Export Country Beechcraft Drawing 1900D UE-1 & On France 129-005002 1900D UE-1 & On Canada 129-005005 1900D UE-1 & On Germany 129-005006 NOTE 9. Company name change effective 4/15/96. The following serial numbers are manufactured under the name Raytheon Aircraft Company: Model 1900D: UE-209, UE-211 thru UE-439. NOTE 10. On Hartzell propeller hubs HC-E4A-3I or HC-E4A-3J, E10950PCB blades may replace E10950PB blades and/or E10950PB blades may replace E10950PCB blades in opposing pairs or in complete sets of four. On Hartzell propeller hubs HC-E4A-3I or HC-E4A-3J, E10950PCK blades may replace E10950PK blades and/or E10950PK blades may replace E10950PCK blades in opposing pairs or in complete sets of four. NOTE 11. Maximum Zero Fuel Weight is 15,700 lbs., for airplane serial numbers UE-1 thru UE-423 (with Kit 129- 5045 installed), and UE-424 thru UE-439, operated per Beech 1900D AFMS P/N 129-590000-121. NOTE 12. Hartzell hub/blade combinations using E10950PK or E10950PCK blades may be modified at the option of the operator to use deicers with lower watt density per Kit 129-9024. NOTE 13. Hartzell hub/blade combinations using E10950PB or E10950PCB blades require that the airplane has been modified by the installation of Kit 129-9024. --------- END ---------- ``` ## ADs (142, first 50, in force first) - [AD 2026-15-05](https://openairdocs.org/ad/2026-15-05): Wing Structure · Textron B300 and B300C. Effective Aug 10, 2026 - [AD 2025-20-11](https://openairdocs.org/ad/2025-20-11): Rudder Control System · Textron B200GT, B200CGT, B300 and 1 more. Effective Oct 17, 2025 - [AD 2025-07-01](https://openairdocs.org/ad/2025-07-01): Air Data Computer · Synthetic Vision Electronic Flight Information System (Arrow STC SR09595RC or ST01523WI). Effective May 15, 2025 - [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 2022-03-23](https://openairdocs.org/ad/2022-03-23): Rudder Control System · Garmin G1000 Integrated Avionics System and GFC 700 Automatic… (STC SA01535WI-D). Effective Feb 22, 2022 - [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 2014-02-03](https://openairdocs.org/ad/2014-02-03): Flight Controls · Textron 1900, 1900C and 1900D. Effective Mar 7, 2014 - [AD 2013-24-03](https://openairdocs.org/ad/2013-24-03): Stabilizers · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Jan 13, 2014 - [AD 2011-15-05](https://openairdocs.org/ad/2011-15-05): Charts · Textron B300 and B300C (C-12W). Effective Aug 19, 2011 - [AD 2011-01-09](https://openairdocs.org/ad/2011-01-09): Oxygen · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 290 more. Effective Feb 9, 2011 - [AD 2010-26-03](https://openairdocs.org/ad/2010-26-03): Ice and Rain Protection · Textron B200, B200GT, B300 and 1 more. Effective Dec 20, 2010 - [AD 2010-05-10](https://openairdocs.org/ad/2010-05-10): Instruments · Textron B300 and B300C (C-12W). Effective Apr 8, 2010 - [AD 2009-23-03](https://openairdocs.org/ad/2009-23-03): Flanges · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Dec 14, 2009 - [AD 2009-23-01](https://openairdocs.org/ad/2009-23-01): Main Landing Gear · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Dec 8, 2009 - [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 2006-19-09](https://openairdocs.org/ad/2006-19-09): Passenger seat mod kit · Textron B300. Effective Oct 24, 2006 - [AD 2006-18-51](https://openairdocs.org/ad/2006-18-51): Left and right wing rear spar lower caps · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Sep 8, 2006 - [AD 2006-12-25](https://openairdocs.org/ad/2006-12-25): Actuator nut assembly · General Machine - Diecron Actuator nut assembly, 100, 200 and 15 more. Effective Jul 28, 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 2005-18-21](https://openairdocs.org/ad/2005-18-21): Elevator hinge support attachments · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Sep 13, 2005 - [AD 2005-01-18](https://openairdocs.org/ad/2005-01-18): Fuselage stringers · Textron 200, 200C, 200CT and 24 more. Effective Mar 1, 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 98-20-38 R1](https://openairdocs.org/ad/98-20-38-R1): Airplane Flight Manual (AFM) · Textron 200, 200C, 200CT and 15 more. Effective Feb 18, 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 2004-09-30](https://openairdocs.org/ad/2004-09-30): Landing Gear Electrical Power Current Limiter · Textron 1900C and 1900C (C-12J). Effective Jun 18, 2004 - [AD 2004-09-07](https://openairdocs.org/ad/2004-09-07): Canted Bulkhead Located at Fuselage Station (FS) 588.10 · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Jun 14, 2004 - [AD 2004-08-15](https://openairdocs.org/ad/2004-08-15): TAWS8000 terrain awareness warning systems (TAWS) · Cessna 421, 500, 501 and 18 more. Effective Jun 7, 2004 - [AD 2004-01-13](https://openairdocs.org/ad/2004-01-13): Vent blower assemblies · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Feb 19, 2004 - [AD 2003-20-10](https://openairdocs.org/ad/2003-20-10): Elevator Trim System Maintenance Procedures · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Oct 15, 2003 - [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 2003-09-12](https://openairdocs.org/ad/2003-09-12): Rivets · Textron 1900D. Effective Jun 27, 2003 - [AD 2003-04-26](https://openairdocs.org/ad/2003-04-26): AC Inverter and Inverter Sync Wire Shield · Textron 1900D. Effective Apr 21, 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 2003-03-18](https://openairdocs.org/ad/2003-03-18): Elevator Control System · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Feb 5, 2003 - [AD 2002-23-11](https://openairdocs.org/ad/2002-23-11): Elevator Balance Weight Attachment Screws · Textron 1900, 1900C, 1900C (C-12J) and 30 more. Effective Jan 10, 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 2001-22-16](https://openairdocs.org/ad/2001-22-16): Engine Truss Assembly · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Dec 17, 2001 - [AD 2001-18-07](https://openairdocs.org/ad/2001-18-07): Flap Flexible Shaft Assemblies · Textron 1900, 1900C, 1900C (C-12J) and 1 more. Effective Oct 12, 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 2001-04-05](https://openairdocs.org/ad/2001-04-05): Global Positioning System · Textron 1900D with STC SA00245WI-D. Effective Apr 9, 2001 - [AD 2000-20-07](https://openairdocs.org/ad/2000-20-07): Cockpit Voice Recorder (CVR) System · Textron 1900, 1900C and 1900D. Effective Nov 22, 2000 - [AD 2000-19-04](https://openairdocs.org/ad/2000-19-04): Wing Fuel Quantity Wiring Harness · Textron 1900C, 1900C (C-12J) and 1900D. Effective Oct 31, 2000 - [AD 99-16-12](https://openairdocs.org/ad/99-16-12): Electric Elevator Trim · Textron 1900D. Effective Sep 27, 1999 - [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 99-12-07](https://openairdocs.org/ad/99-12-07): Passenger Oxygen Container And Mask Assembly · Textron 1900D. Effective Jul 23, 1999 All 142: https://openairdocs.org/tcds/A24CE/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Beech B200](https://openairdocs.org/model/beech-b200): 281 aircraft (registry code 1152922) - [Beech 200](https://openairdocs.org/model/beech-200): 234 aircraft (registry code 1152920) - [Raytheon B300](https://openairdocs.org/model/raytheon-b300): 233 aircraft (registry code 7150007) - [Raytheon B200](https://openairdocs.org/model/raytheon-b200): 206 aircraft (registry code 7150006) - [Textron B300](https://openairdocs.org/model/textron-b300): 195 aircraft (registry code 4220038) - [Hawker Beechcraft B300](https://openairdocs.org/model/hawker-beechcraft-b300): 144 aircraft (registry code 4220003) - [Beech 300](https://openairdocs.org/model/beech-300): 125 aircraft (registry code 1152930) - [Beech 1900C](https://openairdocs.org/model/beech-1900c): 88 aircraft (registry code 1154161) - [Beech B300](https://openairdocs.org/model/beech-b300): 85 aircraft (registry code 1152932) - [Textron B200GT](https://openairdocs.org/model/textron-b200gt): 79 aircraft (registry code 4222080) - [Hawker Beechcraft B200GT](https://openairdocs.org/model/hawker-beechcraft-b200gt): 76 aircraft (registry code 4220014) - [Beechcraft B300](https://openairdocs.org/model/beechcraft-b300): 64 aircraft (registry code 4220035) - [Beech 1900D](https://openairdocs.org/model/beech-1900d): 40 aircraft (registry code 1154162) - [Textron B300C](https://openairdocs.org/model/textron-b300c): 34 aircraft (registry code 4220039) - [Beechcraft B200GT](https://openairdocs.org/model/beechcraft-b200gt): 30 aircraft (registry code 4220033) - [Raytheon 1900D](https://openairdocs.org/model/raytheon-1900d): 22 aircraft (registry code 7150005) - [Beech A200](https://openairdocs.org/model/beech-a200): 17 aircraft (registry code 1152921) - [Beech B200C](https://openairdocs.org/model/beech-b200c): 16 aircraft (registry code 1152924) - [Hawker Beechcraft B300C](https://openairdocs.org/model/hawker-beechcraft-b300c): 14 aircraft (registry code 4220012) - [Hawker Beechcraft B200](https://openairdocs.org/model/hawker-beechcraft-b200): 12 aircraft (registry code 4220004) - [Textron B200CGT](https://openairdocs.org/model/textron-b200cgt): 9 aircraft (registry code 4222079) - [Beech 200T](https://openairdocs.org/model/beech-200t): 8 aircraft (registry code 1152928) - [Beech 1900](https://openairdocs.org/model/beech-1900): 7 aircraft (registry code 1154160) - [Beech 200C](https://openairdocs.org/model/beech-200c): 7 aircraft (registry code 1152926) - [Beech 300LW](https://openairdocs.org/model/beech-300lw): 6 aircraft (registry codes 1152931, 115293A) - [Beech B300C](https://openairdocs.org/model/beech-b300c): 5 aircraft (registry code 1152933) - [Beechcraft B300C](https://openairdocs.org/model/beechcraft-b300c): 5 aircraft (registry code 4220031) - [Raytheon A200CT](https://openairdocs.org/model/raytheon-a200ct): 5 aircraft (registry code 7150063) - [Raytheon B200C](https://openairdocs.org/model/raytheon-b200c): 5 aircraft (registry code 7150041) - [Raytheon B300C](https://openairdocs.org/model/raytheon-b300c): 5 aircraft (registry code 7150002) - [Beech A200CT (RC-12P)](https://openairdocs.org/model/beech-a200ct-rc-12p): 4 aircraft (registry code 1152224) - [Beech A200C](https://openairdocs.org/model/beech-a200c): 2 aircraft (registry code 1152898) - [Beech A200CT (RC-12N)](https://openairdocs.org/model/beech-a200ct-rc-12n): 2 aircraft (registry code 1152204) - [Beech KING AIR A200CT](https://openairdocs.org/model/beech-king-air-a200ct): 2 aircraft (registry code 1155503) - [Beech A200 (C-12C)](https://openairdocs.org/model/beech-a200-c-12c): 1 aircraft (registry code 115292A) - [Beech A200CT (RC-12D)](https://openairdocs.org/model/beech-a200ct-rc-12d): 1 aircraft (registry code 1152206) - [Beech A200CT (RC-12Q)](https://openairdocs.org/model/beech-a200ct-rc-12q): 1 aircraft (registry code 1144150) - [Beech A200CT(C-12D)](https://openairdocs.org/model/beech-a200ct-c-12d): 1 aircraft (registry code 1152205) - [Beech Acft B200T](https://openairdocs.org/model/beech-acft-b200t): 1 aircraft (registry code 1152929) - [CASA 300](https://openairdocs.org/model/casa-300): 1 aircraft (registry code 241030A) - [Textron B200 KING AIR](https://openairdocs.org/model/textron-b200-king-air): 1 aircraft (registry code 4222081) - [Beech A100-1](https://openairdocs.org/model/beech-a100-1): 0 aircraft (registry code 1152899) - [Beech B200CT](https://openairdocs.org/model/beech-b200ct): 0 aircraft (registry codes 1152897, 1152925) - [Beechcraft B200](https://openairdocs.org/model/beechcraft-b200): 0 aircraft (registry code 4220036) - [Beechcraft B200C](https://openairdocs.org/model/beechcraft-b200c): 0 aircraft (registry code 4220037) - [Hawker Beechcraft B200C](https://openairdocs.org/model/hawker-beechcraft-b200c): 0 aircraft (registry code 4220019) - [Raytheon 1900](https://openairdocs.org/model/raytheon-1900): 0 aircraft (registry code 7150020) - [Raytheon 200](https://openairdocs.org/model/raytheon-200): 0 aircraft (registry code 7150064) - [Raytheon B200CT](https://openairdocs.org/model/raytheon-b200ct): 0 aircraft (registry code 7150042) - [Raytheon B200T](https://openairdocs.org/model/raytheon-b200t): 0 aircraft (registry code 7150043) ## STCs approved under this data sheet (895, first 50) - [STC SA03025CH](https://openairdocs.org/stc/SA03025CH): Installation of weather research equipment and weather modification equipment for the purpose of modifying weather conditions. 3S Certification, LLC - [STC SA04617NY](https://openairdocs.org/stc/SA04617NY): Installation of the Medivac Audio System. Avmax Aviation Services Inc. - [STC SA04218NY](https://openairdocs.org/stc/SA04218NY): Installation of Wing Tip Low Profile Pylons with Pods, Underwing Wiring Tunnel and Optional Underwing Antenna Provisions and Antennas. Aerospace Design & Compliance LLC - [STC SA4175NM](https://openairdocs.org/stc/SA4175NM): Installation of fully enclosed main landing gear door system for high-flotation- gear-equipped aircraft.. Raisbeck Engineering 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 SA02309SE](https://openairdocs.org/stc/SA02309SE): Installation of the Garmin G950 Integrated Avionics and Display System. AeroMech Incorporated - [STC SA02658LA](https://openairdocs.org/stc/SA02658LA): Replacement of the original Pratt and Whitney PT6A-60A engines and propellers with Pratt and Whitney PT6A-67A engines and MT Propeller MTV-27-1-N-C-F-R(P)/CFR260-65b propellers. Blackhawk Modifications LLC - [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 SA12400WI](https://openairdocs.org/stc/SA12400WI): Installation of Garmin Avionics Modernization Package. Alpine Aviation, Inc. - [STC SA04221CH](https://openairdocs.org/stc/SA04221CH): Installation of Thermal Acoustic Kit. Skandia Inc. - [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 SA04808NY](https://openairdocs.org/stc/SA04808NY): Installation of Mission Systems for Flight Inspection. Delta Engineering Corporation - [STC SA03204CH](https://openairdocs.org/stc/SA03204CH): Installation of an RF Transparent Pod. DS Technologies LLC D/B/A DST - [STC ST04328NY](https://openairdocs.org/stc/ST04328NY): The Manufacture and Installation of Exterior Placards, Labels and Signs is to be performed, installed. Libellule Monde Inc - [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 ST03875NY](https://openairdocs.org/stc/ST03875NY): Installation of interior placards, signs and markings. Libellule Monde Inc. - [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 SA11302DS](https://openairdocs.org/stc/SA11302DS): Installation of the Pro Line Fusion embedded display system (EDS) latest version 3.7 software upgrade and additional factory options. BHE & Associates Ltd. - [STC SA03930NY](https://openairdocs.org/stc/SA03930NY): Installation of King Air Belly Payload Mount. Icarus Aero Inc. - [STC SA02355AK](https://openairdocs.org/stc/SA02355AK): Installation of cargo barrier net; Tednologies Inc.(TI) P/N 150A-28-000. Tednologies Inc. - [STC SA02017WI](https://openairdocs.org/stc/SA02017WI): The Installation of the Parker-Meggitt iPRESS™ System. 3S Certification LLC - [STC SA03275CH](https://openairdocs.org/stc/SA03275CH): Installation of an antiskid brake system. Lee Air Inc. - [STC ST00052BO](https://openairdocs.org/stc/ST00052BO): Installation of a Rockwell Collins TCAS-94 Traffic Alert and Collision Avoidance Systemm (TCAS II)with dual Rockwell Collins TVI-920D TA/RA/VSI indicators and dual Rockwell Collins TDR-94D mode S transponders.. Ameriflight 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 SA12242IB](https://openairdocs.org/stc/SA12242IB): Manufacturing and Installation of King Air Equipment. ICARUS AERO INC. - [STC ST04442CH](https://openairdocs.org/stc/ST04442CH): Installation of SmartSky LiTE System. Apcela IFC JV, LLC dba Apcela ATG - [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 SA04757NY](https://openairdocs.org/stc/SA04757NY): Installation of a Lower-Fuselage Radome with Extended Nose & updated ECS. Metrea Special Aerospace, ISR Inc. (an Arizona Corporation) - [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 SA01535WI-D](https://openairdocs.org/stc/SA01535WI-D): Installation of the Garmin G1000 Integrated Avionics System and GFC 700 Automatic Flight Control System and optional Electronic Stability and Protection (ESP). Garmin International Inc. - [STC SA12133IB](https://openairdocs.org/stc/SA12133IB): Manufacture and Installation of EVASAIR Loading System Installation. Exploits Valley Air Services Ltd. - [STC SA10941SC](https://openairdocs.org/stc/SA10941SC): Installation of a 3-Tube Rockwell Collins Pro Line 21 Avionics System with Rockwell Collins Integrated Flight Information System 5000, TCAS II, and Honeywell Enhanced Ground Proximity Warning System. BHE and Associates - [STC SA10965SC](https://openairdocs.org/stc/SA10965SC): 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 SA04749NY](https://openairdocs.org/stc/SA04749NY): Atmospheric Research Aircraft Modification. Avcon Industries, Inc. - [STC SA04797NY](https://openairdocs.org/stc/SA04797NY): Atmospheric Research Aircraft Modification. Avcon Industries Inc. - [STC SA11300DS](https://openairdocs.org/stc/SA11300DS): Upgrade previously installed Collins Aerospace Radar Altimeter. BHE & Associates Ltd. - [STC SA2300CE](https://openairdocs.org/stc/SA2300CE): Installation of Removable External Baggage Compartment.. Avcon Industries Inc - [STC SA00263WI](https://openairdocs.org/stc/SA00263WI): Installation of 60 cubic foot cargo compartment on fuselage lower surface.. Metrea Special Aerospace ISR Inc. - [STC SA01853LA](https://openairdocs.org/stc/SA01853LA): Installation of a Wescam FLIR unit into an extended fuselage nose (STC SA00367SE).. Metrea Special Aerospace ISR Inc. - [STC SA01868LA](https://openairdocs.org/stc/SA01868LA): Installation of a Wescam FLIR unit into an extended fuselage nose (STC SA00367SE).. Metrea Special Aerospace ISR Inc. - [STC SA01936LA](https://openairdocs.org/stc/SA01936LA): Installation of a Wescam FLIR unit into an extended fuselage nose (STC SA00367SE).. Metrea Special Aerospace ISR Inc. - [STC SA03343CH](https://openairdocs.org/stc/SA03343CH): Extended Range Fuel Tanks. Metrea Special Aerospace ISR Inc. - [STC SA2307CE](https://openairdocs.org/stc/SA2307CE): Incorporation of STCs and associated modifications identified by Commuter Air Transport drawing list.. Metrea Special Aerospace ISR Inc. - [STC SA2352CE](https://openairdocs.org/stc/SA2352CE): Increase maximum zero fuel weight from 10,400 lbs. To 11,000 lbs.. Metrea Special Aerospace ISR Inc. - [STC SA2404CE](https://openairdocs.org/stc/SA2404CE): Installation of engine low oil pressure warning system.. Metrea Special Aerospace ISR Inc. - [STC SA2451CE](https://openairdocs.org/stc/SA2451CE): Installation of an external Baggage/cargo carrier "Super 60 Pod". Metrea Special Aerospace ISR Inc. - [STC SA2794NM](https://openairdocs.org/stc/SA2794NM): Installation of Flight Equipment and Engineer Corp. passenger seats.. Metrea Special Aerospace ISR Inc. All 895: https://openairdocs.org/tcds/A24CE/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.